diff --git "a/designv8-17.json" "b/designv8-17.json" new file mode 100644--- /dev/null +++ "b/designv8-17.json" @@ -0,0 +1,21127 @@ +[ + { + "image_filename": "designv8_17_0004203_f_version_1598534949-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004203_f_version_1598534949-Figure7-1.png", + "caption": "Figure 7. Magnetic flux density distributions of (a) 35CS300 and (b) Somaloy 700 1P motors at maximum torques.", + "texts": [ + " The BEMF was computed at a rotational speed of 9000 RPM. Figure 6a,b shows the BEMFangle curves for the two motors. The BEMF of the silicon steel and SMC motors is 3.77 V and 3.34 V, respectively. The motor characteristics are summarized in Table 4. The performance of the SMC motor was poorer than that of the silicon steel motor because of its lower saturation magnetic flux density and permeability. The maximum torque of the silicon steel motor occurred at a 94\u00b0 angle and the magnetic flux density distribution is shown in Figure 7a. Magnetic saturation occurred at the tooth and yoke of the stator since the maximum flux density of 1.72 T was higher than the saturation magnetic flux density of 1.63 T for 35CS300. The maximum torque of the SMC motor occurred at an 86\u00b0 angle and the magnetic flux density distribution is shown in Figure 7b. There was also magnetic saturation in this case because the maximum flux density of 1.75 i r . T l Energies 2020, 13, x FOR PEER REVIE 5 of 11 2.3. Electromagnetic Analysis of I set er e t et c r s otor The performances of the i set t l i t silicon steel 35CS300 and Somaloy 7 0 1P materials for co pariso . t si gle-phase square wave cur ent input of 1 A at rotational spee f iti . ig re 5 shows the torque-angle curves of the silicon steel an S t a average torque of 3.01 mNm and torque ripple of 74.8 . f 2.73 - and torque rip le of 64.4%. The BE F as co t t . Figure 6a,b shows the BEMFangle curves for the t o otors. l otors is 3.77 V and 3.34 V, respectively. The otor characteristi l . The performance of the SMC motor was poorer than that of the silicon steel motor because of its lower saturation magnetic flux density and permeability. The maximum torque of the silicon steel motor occurred at a 94\u00b0 angle and the magnetic flux density distribution is shown in Figure 7a. Magnetic saturation occurred at the tooth and yoke of the stator since the maximum flux density of 1.72 T was higher than the saturation magnetic flux density of 1.63 T for 35CS300. The maximum torque of the SMC motor occurred at a 86\u00b0 a gle and the magnetic flux density distribution is shown in Fig re 7b. There was also magnetic saturation in this case because the maximum flux de sity of 1.75 The perfor motor was p orer than that of the silicon steel motor because of its lower saturation magnetic flux density and p rmeability. The aximum torque of the silicon steel motor occurred at a 94\u25e6 angle and the magnetic flux density distribution is shown in Figure 7a. Magnetic saturatio c rr t t t t f t st t r si ce the axi um flux density of 1.72 T was higher than the saturation magnetic flux density of 1.63 T for 35CS300. The maximum torque of the SMC motor occurred at an 86\u25e6 angle and the magnetic flux density distribution is sho n in Figure 7b. There as also agnetic saturation in this case because the axi u flux density of 1.75 T Energies 2020, 13, 4445 6 of 11 was higher than the saturation magnetic flux density of 1.31 T for Somaloy 700 1P. If the geometries of the stator are redesigned, the magnetic saturation problem in the motors will be resolved. Energies 2020, 13, x FOR PEER REVIEW 6 of 11 Figure 7. Magnetic flux density distributions of (a) 35CS300 and (b) Somaloy 700 1P motors at maximum torques. 2.4. Improved Designs of Inset Permanent Magnet Synchronous Motors The magnetic saturation problem of two motors can be solved by increasing the cross-sectional areas and chamfers in the yoke and tooth. The performance of the SMC motor was further enhanced by changing the soft magnet material to Somaloy 1000 3P. The stator of the silicon steel motor was redesigned with an external diameter of 15" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001044_a8fa772056d4fd55d520-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001044_a8fa772056d4fd55d520-Figure2-1.png", + "caption": "Fig. 2. Main plate configuration (unit: mm). (Color online only)", + "texts": [], + "surrounding_texts": [ + "Figure 3 shows the M2 Support Ring mounted onto the Top Panel by ring supporters and connected to the Main Plate by the M2 Struts Frame. Three (3) M2 Spiders are installed in the inner side of the M2 Support Ring to support the M2 bracket. The M2 bracket is the interface between the M2 Baffle and M2 Fitting. The secondary mirror is then mounted to the M2 Fitting. The M2 Support Ring is a ring shaped sandwich panel made of CFRP face sheet with an aluminium core. The M2 Support Ring face sheet material is [0\u00b02/\u00b145\u00b02/90\u00b02]S ply orientation with M55J/954-3 prepared material, and 5056 alloy of 1/8-5056-0.002P hexagonal aluminum honeycomb material is used for the core material. Before these two sandwich panels are cured in the autoclave, Redux 312 film is paved between the face sheet and core, with FM410 adhesive glue inserted between the titanium fittings and honeycomb core. This fitting installation process is called a hot bonding process. After curing in the autoclave, the sandwich panel is machined to the designed configurations and the inserts are potted into the panel with EA9394 adhesive glue. The Main Plate and M2 Support Ring honeycomb panel manufacturing process is illustrated in Fig. 4." + ] + }, + { + "image_filename": "designv8_17_0001904_017_ms-8-11-2017.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001904_017_ms-8-11-2017.pdf-Figure5-1.png", + "caption": "Figure 5. Front beam suspension in ADAMS/Car.", + "texts": [ + " Still, a design with constant thickness along the length has been chosen to balance cost and performance, also because the space required for mounting the tapered beam is not available, and it is very difficult to prototype. The beams have been designed to have two different shapes for front and rear axle. The beam on the front is designed to have an isosceles trapezium shape to have higher longitudinal stiffness considering driving axle may sustain heavier load on the longitudinal direction during acceleration. Another reason is that the mounting system became more reliable for constraining the beam movements during driving condition as shown in Fig. 5 for front suspension beam and its mounting design. The CFRP beam has the shape of a bow to have a higher constructional strength and curved to have correct preload. At the end of both sides, two plates are mounted by thread fasteners, making a \u201csandwich structure\u201d. The beam is drilled through to let the thread fastener pass. On the lower plate, there is another hole left for the spherical joint, which is further connected with upright. The bushing housings have been milled from a block of 7075 aluminum alloy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000706_O201332479507885.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000706_O201332479507885.pdf-Figure12-1.png", + "caption": "Fig. 12, 13\uc740 \uada4\ub3c4\ucc28\ub7c9\uc5d0 \uc7a5\ucc29\ud558\uae30 \uc804 \uc644\uc131\ub41c \ucf69 \ud0c8\uace1 \uae30\uc758 3\ucc28\uc6d0 \ud615\uc0c1\uc744 \ubcf4\uc5ec\uc900\ub2e4.", + "texts": [], + "surrounding_texts": [ + "Fig. 16\uc740 \ucf69 \ud0c8\uace1\uae30\uc758 \uc791\uc5c5 \uc6d0\ub9ac\ub97c \uc124\uba85\ud558\uae30 \uc704\ud558\uc5ec \ubc88\ud638\ub97c \uae30\uc785\ud558\uc600\ub2e4. \uc218\ud655\ud55c \ud6c4 \ub9c8\ub978 \ucf69\uc744 \uc88c\uce21\uc55e\ucabd\uc758 \ud22c \uc785\uad6c\u24ea\uc744 \ud1b5\ud574 \ud22c\uc785\ud558\uba74 \ubc14\uc774\ud2b8\u2460\uc774 \ud68c\uc804\uc744 \ud558\uba74\uc11c \ucf69\uae4d \uc9c0\ub97c \ubb3c\uace0 \ud0c8\uace1\uc2e4\ub85c \ubcf4\ub0b8\ub2e4. [Fig. 16] Sequence of threshing work principle \ud0c8\uace1\uc2e4\uc548\uc5d0 \uc788\ub294 \ud0c8\uace1\ud1b5\u2461\uc740 \ub0a0\uc744 \ub098\uc120\ud615\uc73c\ub85c \ubc30\uce58\ud558 \uc5ec \uc55e\ucabd\uc5d0\uc11c \ub4a4\ucabd\uc73c\ub85c \ucf69\uae4d\uc9c0\ub97c \ubb3c\uba74\uc11c \ud0c8\uace1\uc744 \ud55c \ud6c4 \ucf69 \uae4d\uc9c0\ub294 \ub4a4\ucabd\uc758 \uad6c\uba4d\uc744 \ud1b5\ud574 \ubc30\ucd9c\ub418\uace0 \ucf69\uc740 \uc120\ubcc4\ub9dd\u2462\uc744 \ud1b5\ud574 \uc544\ub798\ub85c \ub5a8\uc5b4\uc9c4\ub2e4. \uc774\ub54c \ucf69\uae4d\uc9c0 \uc720\ub3c4\ud310(2-1)\uc774 \uc55e\uc5d0 \uc11c \ub4a4\ub85c \ube44\uc2a4\ub4ec\ud788 \ub193\uc5ec \ubc29\ud5a5\uc744 \uc7a1\uc544\uc8fc\uc5b4 \ucf69\uae4d\uc9c0\uc758 \ud750\ub984 \uc744 \ub3d5\uace0 \ucf69\uae4d\uc9c0\uac00 \uc801\ucc44\ub418\uc9c0 \uc54a\uac8c \ud55c\ub2e4. \uc120\ubcc4\ub9dd\u2462\uc744 \ud1b5\ud574 \ub5a8\uc5b4\uc9c4 \ucf69\uc740 \ud754\ub4e4\ucc44\u2464\uc5d0 \ub5a8\uc5b4\uc9c0\uace0 \ud754\ub4e4\ucc44\u2464 \uc704\uc5d0 \ub5a8\uc5b4\uc9c0 \uc9c0 \ubabb\ud558\uace0 \uc55e\uc73c\ub85c \ud280\uc5b4\ub098\uac00\ub294 \ucf69\uc740 \ucf69\uc720\ub3c4\ud310\u2463\uc5d0 \ub9de\uace0 \ud754\ub4e4\ucc44\u2464\uc704\uc5d0 \ub2e4\uc2dc \ub5a8\uc5b4\uc9c4\ub2e4. \ud754\ub4e4\ucc44\u2464 \uc704\uc5d0 \ub5a8\uc5b4\uc9c4 \ucf69\uc740 \ucea0\uc0e4\ud504\ud2b8(5-1)\uac00 \ud754\ub4e4\ucc44\u2464 \ub97c \ud754\ub4e4\uba74\uc11c \ud754\ub4e4\ucc44\u2464\uc758 \uacbd\uc0ac\ub97c \ub530\ub77c \ubca8\ud2b8\u2466 \uc704\uc5d0 \ub5a8\uc5b4 \uc9c0\uace0 \uc1a1\ud48d\ud32c\u2465\uc774 \ud68c\uc804\ud558\uba74\uc11c \ud754\ub4e4\ucc44\uc640 \ubca8\ud2b8 \uc0ac\uc774\uc5d0 \uc1a1\ud48d \uc744 \ud558\uac8c\ub41c\ub2e4. \ubd80\ud53c\uac00 \uc791\uace0 \ubb34\uac70\uc6b0\uba70 \uacf5\ucc98\ub7fc \ub465\uadfc\ud615\uc0c1\uc758 \ucf69\uc740 \ubc14\ub78c\uc5d0 \ub0a0\ub9ac\uc9c0 \uc54a\uace0 \ubca8\ud2b8 \uc544\ub798\ub85c \uad74\ub7ec \ub5a8\uc5b4\uc9c0\uace0 \ubd80 \uc11c\uc9c4 \ucf69\uae4d\uc9c0\ub294 \uac00\ubccd\uace0 \ubd80\ud53c\uac00 \ucee4\uc11c \ubca8\ud2b8\uc640 \ubc14\ub78c\uc5d0 \uc2e4\ub824 \ubc16\uc73c\ub85c \ubc30\ucd9c\ub41c\ub2e4. \uc774\ub54c \ubc14\ub78c\uc758 \uac15\ub3c4\ub97c \uc870\uc808\ud558\uae30 \uc704\ud558\uc5ec \uacf5\uae30\uc758 \uc591\uc744 \uc870\uc808\ud560 \uc218 \uc788\uac8c \uc124\uacc4\ub418\uc5c8\ub2e4. \ubca8\ud2b8 \uc544\ub798\ub85c \ub5a8 \uc5b4\uc9c4 \ucf69\uc740 \uc720\uc790\ud615\uad00\u2467\uc73c\ub85c \ub5a8\uc5b4\uc9c0\uace0 \uc720\uc790\ud615\uad00\u2467 \uc548\uc5d0 \uc788 \ub294 \uc774\uc1a1 \uc2a4\ud06c\ub958\u2468\ub97c \ud0c0\uace0 \ubc30\ucd9c\uad6c\ub85c \ubcf4\ub0b4\uc9c4\ub2e4. \ubc30\ucd9c\uad6c\ub85c \ub5a8\uc5b4\uc9c4 \ucf69\uc740 \ubc30\ucd9c\ud32c\u2469\uc774 \uc1a1\ud48d\ud558\ub294 \ubc14\ub78c\uc744 \ud0c0\uace0 \ubc30\ucd9c\uad6c\u246a \ubc16\uc73c\ub85c \ubcf4\ub0b4\uc9c4\ub2e4. \ubc30\ucd9c\ud32c\uc758 \uc1a1\ud48d\ub7c9\uc740 \uc2dc\ud5d8\uac00\ub3d9\uc744 \ud1b5\ud574 \uc801 \uc815\ud55c \uacf5\uae30\uc758 \uc591\uc73c\ub85c \uc870\uc808\ub418\uc5c8\ub2e4. \ubc30\ucd9c\uad6c\uc5d0 \uc774\ubb3c\uc9c8\uc774 \ub07c\uc77c \uc218 \uc788\uc73c\ubbc0\ub85c \uc190\uc774\ub098 \uccad\uc18c\ub3c4\uad6c\uac00 \ub4e4\uc5b4\uac08 \uc218 \uc788\ub3c4\ub85d \ucabd\ubb38 \uc744 \ub450\uc5b4 \uc5b8\uc81c\ub4e0 \uccad\uc18c\ub97c \ud560 \uc218 \uc788\uac8c \ub418\uc5b4 \uc788\ub2e4. \ubc30\ucd9c\uad6c\u246a \uc744 \ud1b5\ud574 \ub098\uc628 \ucf69\uc740 \uc790\ub8e8\ubc1b\uce68\ub300\u246b \uc704\uc5d0 \uc62c\ub824\uc9c4 \uc790\ub8e8\uc5d0 \ubc14 \ub85c \ub2f4\uae30\uac8c \ub41c\ub2e4. \ucd5c\uc885\uc801\uc73c\ub85c \ubc30\ucd9c\ub418\uc5b4 \uc790\ub8e8\uc5d0 \ub2f4\uae34 \ucf69\uc5d0 \ub294 \uc774\ubb3c\uc9c8\uc774 \uac70\uc758 \uc11e\uc774\uc9c0 \uc54a\uace0 \uae54\ub054\ud558\uac8c \ud0c8\uace1\uc744 \ud560 \uc218 \uc788 \ub2e4." + ] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure2.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure2.7-1.png", + "caption": "Figure 2.7. MacPherson independent suspension, reproduced from [26].", + "texts": [ + " Like the rod link, it has a superfluous rotation r that does not affect wheel carrier motion. In practice, the ball joint end of the turning-and-sliding link is at the vehicle body. Matschinsky provides the following mobility formula for suspensions: F = 6(k + l \u2212 g)\u2212 r + g\u2211 i=1 fi, where F is mobility, k is the number of wheel carriers (k = 1 for independent suspensions), l is the number of links, g is the number of joints, r is the number of superfluous link rotations, and fi is the degree-of-freedom of the ith joint. For example, the MacPherson suspension of Figure 2.7 has one wheel carrier K (k = 1); three links a, b, and c (l = 3); six joints labeled one through six (g = 6); two superfluous link rotations (r = 2); and (f1, . . . , f6) = (3, 3, 3, 3, 1, 2). Consequently, F = 1. Unfortunately, Matschinsky does not use his mobility formula as the basis of a systematic enumeration, instead presenting various architectures of interest and showing how they conform to the formula. He does however, consider rigid axle suspensions and the extremely rare compound suspensions, which guide multiple wheel 51 carriers, showing the generality of his approach" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004585_5_secm-2016-0335_pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004585_5_secm-2016-0335_pdf-Figure3-1.png", + "caption": "Figure 3: Final shape of the solid part.", + "texts": [ + " 3 Finite element modeling and\u00a0analysis In order to investigate the behavior of the proposed mono-leaf spring configurations, the FEM of the spring was created using Abaqus 6.12-1\u00a0software. This model was used to simulate the response of the spring and to check whether or not the proposed configuration complies with the requirements. A solid mono-leaf spring model created in CATIA CAD (Dassault Systemes, US) software was imported into Abaqus 6.12-1, and then repaired using partition methods to provide great convenience in mesh generation and prepared for composite modeling. Figure 3 depicts the final shape of the part after the repair and partition process. Within the study, the Abaqus/Standard implicit finite element procedure was selected as the FEM solver. This procedure solves the algebraic equations at the next time step by use of the solution of the previous time step. In addition, the equilibrium is inspected at each time increment. The quasi-static finite element formulations and convergence criteria are given in Abaqus 6.12-1 Theory Manual [24]. The composite lay-up interface of Abaqus was used as a composite modeler, and solid composite lay-up was selected as the element type" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000154_1145_3603269.3604873-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000154_1145_3603269.3604873-Figure3-1.png", + "caption": "Figure 3: Beam Pattern of the MilBack\u2019s Dual-Port FSA. Our dual-port FSA enables creating two sets of beams while their frequency assignments are mirror of each other.", + "texts": [ + " In contrast to a typical FSA, described 1In Van Atta, the length of traces between antennas should be carefully tuned. Thus, we cannot easily insert switches and/or ports in the middle of the traces to direct the signal to a local processor for downlink. ACM SIGCOMM \u201923, September 10\u201314, 2023, New York, NY, USA H. Lu, M. H. Mazaheri, R. Rezvani, and O. Abari in section 2, we design and build a dual-port FSA for MilBack\u2019s backscatter nodes. Dual-port FSA: The FSA structure is symmetric, and hence by adding a second port to the other side of the FSA structure, we can enable two sets of beams as shown in Figure 3. The red beams are created by Port A and the blue beams are created by Port B. Therefore, for each direction, there will be two beams that correspond to different frequencies. For instance, in Figure 3, the rightmost beam corresponds to frequency \ud835\udc531 and \ud835\udc537 for Port A and Port B, respectively. As we describe in the following sections, this dual-port FSA will enable MilBack to sense the orientation of nodes as well as support higher data-rate uplink and downlink communication. The node\u2019s architecture: Figure 4 shows the block diagram of a MilBack\u2019s backscatter node. Our design consists of a dual-port FSA antenna where each of its ports is connected to a switch. Each switch connects the FSA port to either the ground plane of the FSA (i", + " In the previous section, we explained how MilBack enables localization and orientation sensing. In this section, we explain how MilBack also enables both downlink and uplink communication using its novel architecture. Due to the significant path loss of mmWave signals, any mmWave transmitters and receivers must focus their energy into narrow beams to compensate for the loss. Therefore, communication is only possible once their transmitter and receiver beams are aligned. Recall that MilBack\u2019s node uses our dual-port FSA to passively create two beams as shown in Figure 3, where the direction of each beam depends on the signal frequency, and the signal of each beam is received by only one of the port. Hence, for the AP to send data to the backscatter node, the AP first needs to know which two signal frequencies to use for communication. In particular, one frequency aligns the beam for the Port A of the FSA toward the AP while the other frequency aligns the beam for the Port B of the FSA toward the AP. Note, these frequencies can be selected based on the orientation of the node" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002227_354-68291803075P.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002227_354-68291803075P.pdf-Figure1-1.png", + "caption": "Figure 1: Pillar jib crane", + "texts": [ + ",j n= - number of projected variables, X - project vector consisting of n projected variables. Project variables are the values which do have to determine during the optimization process (each project variable is defined by its lower and upper limit). To define the objective function and constraint functions, firstly the engineering problem that is the basis of this research will be presented.In this paper, the main subjects of research are related to the analysis and optimization of the I-beam structure (Figure 1). The main idea is to thoroughly analyze and optimize the welded I-beam or to demonstrate the justification of making such a carrier that would replace the standard INP Optimal Design of Welded I-beam of Slewing Pillar Jib Crane or IPE profiles which are most commonly used in these types of structures to reduce the carrier weight. In Figure 1, one type of pillar jib crane and the basic input geometric parameters are shown. The structure consists of two basic parts, column structure, with height Hs and diameter Dk, and boom structure, with length Lk, which rotates around the axis of the column, over the axle with the length H1, at distance a from the axis of the column. The hoist trolley is taken in the analysis at end of the span, or at a distance L from the axis of the column (the most unfavorable position). The input values that are necessary for this analysis are shown via the vector of input parameters: ( )1 ,, , , , , , , , ", + "The stress comparing is given as follows: ,2 x \u0161 \u0161 dop x \u0161 F S I a \u03c3 \u03c3 \u22c5 = \u2264 \u22c5 \u22c5 (25) , 1 0.75 e \u0161 dop R \u03c3 \u03bd = \u22c5 (26) ( ), 2x \u0161 b tS h t\u22c5 = \u22c5 + (27) where are: \u0161\u03c3 - the stress in the weld, ,x \u0161S - section modulus appropriate for weld calculation, ,\u0161 dop\u03c3 - the allowed stress in weld. The constraint function in this case has the following form: 2 , 0\u0161 \u0161 dopg \u03c3 \u03c3= \u2212 \u2264 (28) 4.2.2 Stress criterion of weld for connection between beam and swivel part In this criterion, checking the angular welds that connect the welded I-beam with the swivel part (Figure 1 - Detail \"A\"). The design of this compound is shown in Figure 3a. The welds area which is relevant for the calculation is given in Figure 3b. (a \u2013 detail of connection between the welded beam and swivel part, b \u2013 the area of the weld) The geometrical characteristics of the weld contour necessary for analysis are determined on the basis of the following relations: Optimal Design of Welded I-beam of Slewing Pillar Jib Crane ( ) ( )2 23 3 3 , 1 1 1 1 1 1 1 6 6 3 2x \u0161 \u0161 \u0161 \u0161 \u0161 \u0161 \u0161 \u0161I a h b a b a b a h a b a h a= \u22c5 \u22c5 + \u22c5 \u22c5 + \u22c5 \u22c5 + \u22c5 \u22c5 \u22c5 + + \u22c5 \u22c5 \u2212 (29) ( ) ( )2 23 3 3 , 1 1 1 1 1 1 1 1 1 6 3 6 2y \u0161 \u0161 \u0161 \u0161 \u0161 \u0161 \u0161I a b a b b a b b h a h a s a= \u22c5 \u22c5 + \u22c5 \u22c5 + \u22c5 \u22c5 \u2212 + \u22c5 \u22c5 + \u22c5 \u22c5 \u22c5 + (30) , 1, 1, x \u0161 x \u0161 \u0161 I W y = (31) 1, 2\u0161 \u0161 Hy a= + (32) , 1, 1, x \u0161 y \u0161 \u0161 I W x = (33) 1, 2\u0161 bx = (34) , 2, 2, x \u0161 x \u0161 \u0161 I W y = (35) 1 2, 2\u0161 hy = (36) , 2, 2, x \u0161 y \u0161 \u0161 I W x = (37) 2, 2\u0161 \u0161 sx a= + (38) , 12 4x \u0161 \u0161 \u0161A b a b a= \u22c5 \u22c5 + \u22c5 \u22c5 (39) , 12y \u0161 \u0161A h a= \u22c5 \u22c5 (40) ( )1 1 4 2 \u0161b b a s= \u22c5 \u2212 \u22c5 \u2212 (41) 1 4 \u0161h h a= \u2212 \u22c5 (42) where are: , ,,x \u0161 y \u0161I I - the planar moments of inertia of the weld contour in x and y direction, 1, 1,,x \u0161 y \u0161W W - the resistant moment of the weld contour in x and y direction for point 1, 2, 2,,x \u0161 y \u0161W W - the resistant moment of the weld contour in x and y direction for point 2, , ,,x \u0161 y \u0161A A - the area of the weld contour in x and y direction", + "3 A criterion of beam deflection The deflection of cantilever top fu (at end position of the hoist trolley) which must be less than the allowed one fd is determined by the following expression (51), and consists of three components: 1 2u S K K df f f f f= + + \u2264 (51) ( )d S ff H L K= + \u22c5 (52) The cantilever deflection of jib crane at the top is accurately calculated as the superposition of the deflection due to the impact of the column, the boom deflection at the top causes by static force (concentrated load at end of the span) and deflection due to cantilever weights. As seen in Figure 1, the cantilever is observed exactly to the point at which it is actually located, shifted by the value a from the axis of the column, so that the deflection of this part is unobserved, because it can be considered sufficiently rigid to move along with the column, primarily because of the connection with the column itself as well as the size of the value a. The deflection components are determined based on the following relations: , 1 , ( / 2)v st S S K x S M H H f tg L E I \u22c5 \u2212 = \u22c5 \u22c5 (53) 2 , 2 K K v st st K q LM F L \u22c5 = \u22c5 + (54) 3 1 ,3 st K K x K F L f E I \u22c5 = \u22c5 \u22c5 (55) 4 2 ,8 K K K x K q Lf E I \u22c5 = \u22c5 \u22c5 (56) where are: Sf - deflection due to column structure influence, ,v stM - the moment of bending due to statical load, 1Kf - deflection due to load weight and hoist trolley weight, 2Kf - deflection due to welded I-beam weights" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004553_ai.7-12-2021.2314491-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004553_ai.7-12-2021.2314491-Figure2-1.png", + "caption": "Fig. 2.", + "texts": [ + " Various Conceptual design were created in order to understand and interpret the details about the seat support frame. It is clear that th to overcome difficulties with the existing twisted seat support frame. Various concepts were created by replacing the positions of twists in the supporting frame and also \u2018I\u2019 section with rips are used in redesign of seat supporting frame. In the existing conceptual design of seat support frame, twist is presented in the middle. Here the position of twist is placed in both ends and also placed in different shown in figure 2. Frame is welded to the seat at one end and bolted at the bottom. In this concept, double twist are placed at both ends and also placed in different orientation as shown in figure 3. Frame is welded to the seat at one end and bolted at the bottom side. e developed concept should have the capability Model with twists at both the ends orientation as -time In this concept, double twist present at the bottom and one twist at the top as shown in figure 4. Frame is welded to the seat at one end and bolted at the bottom" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002208_load.php_id_15010201-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002208_load.php_id_15010201-Figure2-1.png", + "caption": "Figure 2. Distributions of the electromagnetic field of the TM 110 and TM 210 modes.", + "texts": [ + " Combining with the electric field distributions of the microstrip elliptical ring resonator\u2019s resonant modes in [14], the electric field distributions of the open elliptical-ring slot resonator\u2019s TM 110 and TM 210 modes, which are shown in Figure 1, can be reduced with the Babinet\u2019s principle. According to duality principle, there is an interchange between the electromagnetic fields of the slot and the complementary ring which is also presented in Figure 1. The resonant frequencies of both the TM 110 and TM 210 modes can be estimated by the microstrip line resonator analysis method which is used in [13]. The TM 110 mode is the one with the lowest resonant frequency, as shown in Figure 2(a). And it can be considered as the resonance on a curved \u03bb/2 microstrip line. The distribution of the magnetic field strength far away from the gap is nearly equal to that of a straight microstrip line. Only in the gap area does the field distribution change, because the field must be perpendicular to the boundaries at the end of the lines. The electric field component EZ is nearly constant across the microstrip line and only changes slightly from the inner to the outer circumference. For TM 210 mode, an additional zero of the azimuthal component H\u03c6 is found, and the corresponding field distribution is shown in Figure 2(b). The mean value of the resonator length now is nearly equal to one wavelength. The resonance characteristics of the proposed antenna and the effects of key parameters are performed in the following section. Figure 3 presents the geometry of the proposed antenna. The circular patch with radius r2 is printed on a substrate of thickness h = 6mm, relative permittivity 2.65 and loss tangent 0.0025. And both the substrate and ground plane have radius r1. Six shorting vias of radius r4 are uniformly distributed along a circle with a displacement of r3 from the feeding point", + "4 GHz, the electric field distributions of monopolar patch mode assuredly similar to the top-loaded monopole are invariable in the \u03a6-direction, and their directions are along the radial direction of the patch with only Z-component, so that the monopolar patch mode gives a null in the broadside. For the TE 110 and TE 210 modes, the electric field distributions on the open elliptical-ring slots agree well with the magnetic field distributions on the complementary open elliptical-ring which is shown in Figure 2. For the radiation patterns test of the prototype, we have used a standard antenna test set with a horn antenna as a source in an anechoic chamber. Simulated and measured co-polarization (E\u03b8) and cross-polarization (E\u03d5) radiation patterns on E-plane and H-plane are exhibited in Figure 10 at different resonant frequencies, with the x-z plane and x-y plane referred to as the E- and H-planes, respectively. The results show that the proposed antenna radiates stable vertical-polarized waves (E\u03b8) with conical radiation patterns across the whole operating bandwidths, and the maximum power levels occur at elevation angle \u03b8 of 81\u25e6, 66\u25e6, 39\u25e6 and 33\u25e6 as it is operated at 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002593_9312710_09335981.pdf-Figure26-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002593_9312710_09335981.pdf-Figure26-1.png", + "caption": "FIGURE 26. Manufactured prototype machine (a) Permanent magnet synchronous rotor module lamination (b) Permanent magnet synchronous rotor module lamination (c) Novel modular permanent magnet-assisted synchronous reluctance motor (d) stator.", + "texts": [ + " Therefore, under the same operation state the eddy current loss of MPMA-SynRM is lower, and the possibility of thermal demagnetization of the permanent motor magnet is lower. For the MPMA-SynRM rotor, a modular combination design is adopted. When the motor rotor faults, not all of the rotor structures need to be repaired. The faulty module is just removed and replaced with a new one, which can greatly improve the motor repair and material utilization, save motor repair time. and reduce the motor material cost. V. EXPERIMENTAL VALIDATION This article creates a 4-pole 24-slot MPMA-SynRM motor to verify the motor performance. As shown in Fig. 26. the rotor is composed of an IPM module and two four-layer PMA-SynRM rotors. The load experiment setup is shown in Fig. 27.The no-load back EMF of the motor is obtained by using the inverter. Table 4 shows the comparison between the motor\u2019s simulation and the experimental values. The no-load back-EMF is higher than the simulated value because the manufacturer\u2019s magnetic energy product index is higher than the standard value to ensure product quality when ordering permanent magnets. The magnetic powder brake is adjusted to adjust the load, thus obtaining the current when the motor is running to compare it with the simulated value, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003944_6514899_10305151.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003944_6514899_10305151.pdf-Figure16-1.png", + "caption": "FIGURE 16. Simulated (black) and measured (red) radiation patterns of the proposed 1\u00d72 ME-dipole Antenna at different frequencies when port 1 is excited.", + "texts": [ + " Hence, moving these rings away from these surface currents increases the mutual coupling between the antenna elements. This explains the results of Figs. 12 and 13. Fig, 15 compares the simulated and measured Sparameters of the 1\u00d72 ME-Dipole. A close resemblance be- tween the simulated and measured reflection coefficients and coupling with and without the metasurface can be observed. Particularly, the maximum measured isolation enhancement is about 53 dB over the bandwidth. The simulated and measured far-field radiation patterns of the antenna at 53, 60, and 64 GHz, in the E- and H-planes are shown in Fig. 16. It is clear that across the 52-64 GHz, the proposed antenna exhibits stable radiation patterns in the E- This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License. For more information, see https://creativecommons.org/licenses/by-nc-nd/4.0/ Oludayo Sokunbi and Ahmed Kishk: Millimeter-wave ME-Dipole Array Antenna Decoupling Using a Novel Metasurface Structure and H-planes. Also, the measured and simulated results are close to each other except the differences due to the antenna mounting structures" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003260_f_version_1665713726-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003260_f_version_1665713726-Figure3-1.png", + "caption": "Figure 3. Structure of oilseed rape threshing device. 1\u2014concave; 2\u2014shaft; 3\u2014screw feeding head; 4\u2014spreading disc; 5\u2014threshing elements; 6\u2014guide plate angle.", + "texts": [ + " Parameters Value Normal stiffness per unit area (N\u00b7m\u22122) 8 \u00d7 108 Shear stiffness per unit area (N\u00b7m\u22122) 6 \u00d7 108 Critical normal stress (Pa) 1 \u00d7 108 Critical shear stress (P ) 9 \u00d7 107 To obtain a s mulation model of oilseed rape pl nts, 100 oilseed rape plants were sel cted, and the plant length, ar length, and stalk diam ter were measured. The biometric parameters of oilseed rap pl nts a e shown in Table 3. Primary branch Length of primary branch (mm) 60 To obtain a simulation model of oilseed rape plants, 100 oilseed rape plants were selected, and the plant length, ear length, and stalk diameter were measured. The biometric parameters of oilseed rape plants are shown in Table 3. Agriculture 2022, 12, 1580 5 of 21 The oilseed rape threshing device includes the threshing concave plate and threshing cylinder, as shown in Figure 3. The threshing concave plate is a grid-type concave plate, and the guide plate angle is designed to be 360\u25e6, effectively improving the threshing efficiency. The threshing concave plate consists of four groups of concave plate sieves connected by a circular support ring. Each set of concave plate sieves consists of three sieves held together by rectangular connecting plates. This design makes the installation and removal of the threshing concave plate easier and facilitates maintenance. Considering the size of the feeding volume, size of oilseed rape seeds, and other parameters, the length of the sieve holes of the concave plate is 35 mm and the width is 15 mm, and each concave plate sieve is distributed with 360 holes. In addition, the first two groups of concave plate sieves are installed with angle-adjustable deflector plates, as shown in Figure 4. Agriculture 2022, 12, 1580 6 of 21 Agriculture 2022, 12, x FOR PEER REVIEW 6 of 22 2.2. Modeling of the Threshing Device The oilseed rape threshing device includes the threshing concave plate and threshing cylinder, as shown in Figure 3. The threshing concave plate is a grid-type concave plate, and the guide plate angle is designed to be 360\u00b0, effectively improving the threshing efficiency. The threshing concave plate consists of four groups of concave plate sieves connected by a circular support ring. Each set of concave plate sieves consists of three sieves held together by rectangular connecting plates. This design makes the installation and removal of the threshing concave plate easier and facilitates maintenance. Considering the size of the feeding volume, size of oilseed rape seeds, and other parameters, the length of the sieve holes of the concave plate is 35 mm and the width is 15 mm, and each concave plate sieve is distributed with 360 holes", + " The oilseed rape threshing method adopts the compound threshing form of \u201clong ribs + spike teeth,\u201d with six groups of threshing elements, each including one long rib and six spike teeth. The role of the long ribs is to strip the oilseed rape seeds from the angular fruits, and the part of the peg teeth is to discharge the oilseed rape stalks and other impurities outside the device. The length of the long striker is 750 mm, the height is 90 mm, the spacing of the peg teeth is 80 mm, and the size is 90 mm [33]. Figure 3. Structure of oilseed rape threshing device. 1 co ca ; 2 s ft; f i ; 4 spreading disc; 5 threshing elements; 6\u2014guide plate angle. Agriculture 2022, 12, x FOR PEER REVIEW 7 of 22 Figure 4. Structure of threshing concave plate. The oilseed rape threshing process feeds multiple bunches of oilseed rape plants into the threshing device, as shown in Figure 5. The feeding area is used to feed oilseed rape plants, the threshing area is used to thresh, and the miscellaneous area is where impurities such as hulls and broken stalks are discharged out of the device" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001040_77_aoje_2_021025.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001040_77_aoje_2_021025.pdf-Figure10-1.png", + "caption": "Fig. 10 Unit prototype experimental setup. (a) The torque\u2013angle relationship of each unit prototype is measured through a constant torque test, while the loaded and cantilevered side is held horizontal to keep a constant moment arm. (b) A mechatronic balancing system (rear view) moves the prototype according to the accelerometer readings. (c) The L-channel walls are labeled with colored dots to obtain the curling angles through photogrammetry.", + "texts": [ + "2 Unit Curling Model Experimental Setup. A constant torque test measures the curling angle of the unit prototypes under different vacuum pressures by applying a known external load. To apply the external torque, one L-channel is cantilevered with a weight hanging from a perpendicular mounting shaft at a fixed distance from the hinge. To maintain a constant moment arm and a perpendicular applied moment, the opposing L-channel is mounted to a movable fixture, which is part of a mechatronic balancing system (Fig. 10(a)). This system is controlled to maintain a horizontal orientation of the loaded and cantilevered L-channel as measured by an accelerometer and driven by a linear stepper through a linkage (Fig. 10(b)). A vacuum pump is used to actuate the unit prototypes, where the vacuum pressure is controlled manually by a regulator and measured with a pressure gauge. The side walls of both L-channels are marked with different colored dots to measure the curling angle, i.e., the angle difference between the two L-channels, through photogrammetry (Fig. 10(c)). 4.2.3 Pressure Scaling of Torque\u2013Angle Data. Each unit prototype is run through loops of straightening and curling motions to obtain its curling torque\u2013angle performance. To produce a loop, a high vacuum pressure is first applied to the bladder under no external load, fully curling it to a maximum curling angle \u03b8max. A weight is then hung from the mounting shafts on the loaded side of the prototype, producing a constant torque at which the unit remains fully curled at the initial high pressure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003548_om_article_19879.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003548_om_article_19879.pdf-Figure2-1.png", + "caption": "Figure 2. The rotor yoke structure", + "texts": [], + "surrounding_texts": [ + "Because of the different structure, compared permanent magnet fault-tolerant motor with the traditional permanent magnet synchronous motor, there are many differences in terms of parameter design. In this section, we use a four-phase six-pole permanent magnet fault-tolerant motor as an example, and research the design of motor structure and electromagnetic parameters. The main performance parameters of this motor are as follows: rated power PN=1KW, rated voltage UN=36V, rated speed nN=1200rpm, number of the stator Ns=8, rotor pole pairs p=3, number of phase m=4, rated efficiency \u03b7N=90%, the rated power factor cos\u03c8N=0.8. A. Design of stator inner diameter and core length The main dimensions of the permanent magnet fault-tolerant motor are specified the inside diameter and the effective axial length of stator core which can be determined according to the need of maximum torque and dynamic response indication [10] . When the biggest electromagnetic torque of motor is Temmax(N . m), then the relationship between main dimensions and electromagnetic loads is: 42 11 10 4 2 max ADLBT iefem (1) where B1 is the flux density of fundamental amplitude (T), A is the stator electric load valid value (A/CM). Obtained the relationship between the main dimensions of motor and the electromagnetic loads according to formula (1): AB T LD em efi 1 4 2 1 1022 max (2) p KmNI A dp1 (3) where m is the motor phase, N is the winding turns, I1 is the stator current, p is the rotor pole pairs, Kdp is the winding factor, \u03c4 is the motor pole pitch. Here we take power load A=150A/cm, the flux density of fundamental amplitude B\u03b41=0.8T. Because the dynamic response performance index of a permanent magnet fault-tolerant motor mainly refers to the motor that under the effect of maximum electromagnetic torque Temmax can accelerate linearly from rest to turning speed \u03c9b during time of tb , that is: b b em pt J tp J T max (4) where J is the rotor and load inertia (kg . m 2 ). Therefore, according to formula (4) we can obtain the ratio of maximum electromagnetic torque to the moment of inertia is: b bem ptJ T max (5) The moment of inertia of the motor rotor can approach to: 741 10) 2 ( 2 i efFe D LJ (6) where \u03c1Fe is the mass density of the rotor material iron (g/cm 3 ). We take formula (1) and formula (6) into equation (5), can obtain the stator inner diameter Di1(cm) is: 3 1 1 10 28 Feb b i ABpt D (7) Then according to equation (2), we can obtain the effective axial length of the stator core Lef(cm) is: 22 11 2 1 4 4 101022 maxmax ABpt T ABD T L b Febem i em ef (8) B. Design of groove parameters Fig .1 shows the block diagram of stator slots of permanent magnet fault-tolerant motor after straightening. From Fig .1, we can know that the parameters which need be calculated include: notch thickness Hs0, slot width Bs0, stator tooth width Bt and stator tooth height Hs2. Firstly, according to the magnetic saturation constraint conditions of the stator teeth, we obtained the tooth height and the tooth width. Secondly, according to the design requirements of slot leakage inductance, we derived the notch height and width. Finally, in accordance with the requirements of internal winding current density of stator slot, we calculated the other parameters, like the width of the groove bottom Bs2 and the width of the groove top Bs1. 1) Parameter calculation of stator teeth Assuming all of the air-gap magnetic flux through the main stator teeth, so the stator tooth width is obtained as follows: maxt i t b B B (9) where B\u03b4 is magnetic load, \u03b1i is calculated pole arc coefficient. Because when ferromagnetic material under normal circumstances, the maximum magnetic flux density of the stator teeth btmax equal to 1.4~1.6T, therefore, this article selected btmax=1.5T, and according to formula (9) can derive the stator tooth width Bt. Generally, the height and width ratio of the stator teeth is between 1.5 and 3. Because, if the ratio is small, the stator slot is very shallow, this may cause very high current density that through the inner winding. But if the ratio is large, then the stator slot is very deep, the stator yoke is easy to reach saturation, and the electromagnetic torque may reduce. So in this paper, we take the value of 2, and the stator tooth height is: ts BH 22 (10) 2) Calculation of notch parameter In order to reduce the saturation degree of the stator tooth tip maximum extent, at the same time to improve the slot leakage inductance Ls0\u03c3, the notch thickness Hs0 generally taken to be (0.35~0.5)Bt, this article is taken as 0.4 times, that is: ts BH 4.00 (11) Slot leakage inductance Ls0\u03c3 is: 0 000 2 0 0 ))((2 s sefss s B BLBHN L (12) Because the notch width Bs0 is much smaller than the effective axial length of stator core Lef, therefore, formula (12) can be simplified as: 0 00 2 0 0 )(2 s efss s B LBHN L (13) Rearranging slot width Bs0 is: efs efs s LNL LHN B 2 00 0 2 0 0 2 2 (14) where the slot leakage inductance Ls0\u03b4 taken as 0.33 times of the coil inductance Ls, and has the following formulas: eese s If E I E L 2 00 (15) NNN N e mU P I cos (16) where E0 is the motor back electromotive force (V), \u03c9e is the electrical angular frequency (rad/s), Is is the steady-state short-circuit current (A), Ie is the motor rated current (A), fe is the rated synchronization frequency (Hz). 3) Calculation of armature winding turns and coil diameter The definition of motor no-load back electromotive force(EMF) is: 010 44.4 we NkfE (17) where fe is the rated synchronization frequency(Hz), kw1 is the winding factor, \u03a60 is the fundamental magnetic flux air gap(Wb), and has the following formulas: ef i LB ) 2 sin 4 ( 2 0 (18) So the number of turns of the armature winding N is: )2sin( 18.0 11 0 iefiwe LDBkf pE N (19) According to the dimensions of slot form, we can get the area of stator slots As is: 2 sin)( 221 sss s HBB A (20) where \u03b8 is the mechanical angle that relative to the centerline of the pole (rad), and: Width of the top slot is: t si s B Q HD B )2( 01 1 (21) Width of the bottom slot is: t sssi s B Q HHHD B )(2 2101 2 (22) where Q is the number of stator slots, in order to reduce the degree of magnetic saturation of tooth boots, Hs1 generally taken as 0.5~1mm. 4) Calculation of stator and rotor yoke portion thickness The thickness of the yoke of stator and rotor needs to meet the constraints of magnetic saturation, for the four-phase six-pole permanent magnet fault-tolerant motor in this article, the maximum value of yoke flux density is 1.6~1.8T, which is slightly larger than the maximum limit value of flux density in tooth portion, in this paper the value is 1.6T. Then the thickness of the stator yoke portion Hsy is: sy im sy b b H 2 1 (23) The thickness of the rotor yoke is: ry p ry b B H 2 1 (24) where bsy is the flux density of stator yoke portion (T), bry is the flux density of rotor yoke portion (T). C. Magnetic circuit design Magnetic circuit design includes the determination of overall structure, the determination of sizing and the selection of material, which focuses on the work of choosing permanent magnetic materials and designing the operating point. 1) Permanent magnet material selection In this paper, we chose NdFeB N38H as the permanent magnet material, the remanence density Br20 is 1.23T, the temperature coefficient \u03b1Br is 0.12 %/\u2103, the irreversible demagnetization loss IL is 0.7%, the calculated coercive force of permanent magnet Hc20 is 899kA/m. We can obtain following results according to the selection of NdFeB N38H: (1)Remanent flux density during the operating temperature: 20 [1 ( 20) /100] [1 /100] 1.18 r Br r B t IL B T (2)Calculated coercive force during the operating temperature: mkA HILtH cBrc /7.833 ]100/1[]100/)20(1[ 20 (3)Relative permeability of the permanent magnet: 20 0 20 1.089 1000 r r c B H where 0 is vacuum permeability, 0=410 -7 H/m. 2) Determine the shape of permanent magnet Surface magnetic pole structure can improve the ability of isolation between the windings, in this article we use the surface-type tile-shaped magnetic poles in the permanent magnet fault tolerant motor, shown in Fig .3. The structure of permanent magnet contacting the air gap directly is easy processing and installation. And uses a concentric tile-shaped magnetic poles, i.e., the outer diameter and the inter diameter of the permanent magnets have a common center, it shown as in the Fig .4. 3) Calculate the size of permanent magnet The main size parameters of permanent magnet part include the thickness and the width of permanent magnet, and can be determined by the following formula: The thickness of permanent magnet hM is: i r r M B B h 1 (25) The width of permanent magnet bM is: pM b (26) where \u03bcr is the relative permeability of ferromagnetic material; \u03b4i is the calculating air gap length of motor(cm); Br is the residual magnetic induction intensity of permanent magnet (T); B\u03b4 is the magnetic load (T); \u03b1p is the percentage of pole embrace. Generally Br/B\u03b4 equal to 1.1~1.35. 4) Permanent magnet magnetization way of design In this paper, the arrangement of permanent magnet is in the way of Halbach array [11] , this kind of arrangement can not only enhance the air gap flux of motor, but also can weaken the magnetic flux of rotor yoke, which is particularly suitable for the rotor structure of using surface-mounted permanent magnet. Halbach array is a novel magnetic structure array that combines radial array with tangential array, as Fig .5(a) shows, so that we can make the magnetic field in one side of permanent magnet strengthening and the other side weakening. The rational design of Halbach array can make the air-gap flux density and the no-load back electromotive force having good sinusoidal. Fig .5 (b) shows the distribution of magnetic equipotential line of the permanent magnet motor with Halbach array which is calculated by the ANOSOFT which is one of the finite element analysis software. As we can see, after using Halbach array, the magnetic flux of rotor yoke significantly reduced, while the magnetic flux that across air gap into the stator significantly increased, which increases the magnetic load of permanent magnet motor and the density of force and energy, so Halbach array is very suitable for the ideal for the permanent magnet fault-tolerant motor with the inter rotor structure of permanent magnet posted outside." + ] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.11-1.png", + "caption": "Figure 2.11: Fixed-wing prototype in its hovering orientation (16)", + "texts": [ + " Five proportional-integral (PI) control systems were implemented, allows the aircraft to navigate in three-dimensional space while maintaining Chapter 2: Previous work on MAV development 11 an arbitrary heading angle, however, takeoff and landing still need to be manually performed (15). People at Drexel University (the USA) developed a very interesting fixed-wing MAV which can hover like a helicopter. The design is like a conventional aircraft with three basic types of control surface: Ailerons, elevator and rudder which are shown in Figure 2.11. Avionics system\u2019s components are quite standard with gyroscopes, accelerometers and a microprocessor. Chapter 2: Previous work on MAV development 12 Although dashing and transition were not controlled autonomously, in hovering mode, the proportional-differential (PD) controller demonstrated its excellent performance. In the vertical orientation, the MAV was very unstable, and it required a skillful pilot to constantly manipulate the aircraft\u2019s yaw and pitch control surfaces to sustain the hover" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004532_56_4_56_T-12-53__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004532_56_4_56_T-12-53__pdf-Figure3-1.png", + "caption": "Fig. 3. Variation of interaction of shock waves: (a) unstructured mesh visualization, (b) pressure distribution at d=2 \u00bc 0:125, (c) at d=2 \u00bc 0:225 and (d) at d=2 \u00bc 0:325.", + "texts": [ + " 2, the base radial distribution of the individual fuselage (of twin-body) considered in this research is indicated. This configuration has the fixed radius of l=24 in the range of \u00bdl=4; 3l=4 , where l represents body length. The volume of this individual single body is defined as V in this research. A quadratic curved configuration which has the same fuselage volume V is also discussed in this section, whose radial distribution is also included in Fig. 2. We call these bodies \u2018\u2018base\u2019\u2019 and \u2018\u2018curved,\u2019\u2019 respectively. As shown in Fig. 3, a twin-body fuselage configuration (2V) is constructed by placing two single bodies in parallel, and the distance ratio between these two bodies is defined by d. Here, the distance ratio is defined by the distance that is normalized by the body length l. Then, depending on the types of radial distributions of the single body, two different types of twin-body configurations (2V) are generated, and we call them \u2018\u2018base (twin, 2V)\u2019\u2019 and \u2018\u2018curved (twin, 2V),\u2019\u2019 respectively. The variation of wave drag coefficient with respect to the normalized distance from the symmetry line of the twinbody d=2 is shown for both twin-body fuselage configurations in Fig. 4. Two computational mesh resolution levels are compared here that are approximately 200 and 600 thousands mesh points, respectively, for the half side of the twinbody fuselage (see Fig. 3(a)). The drag coefficients obtained by those coarse/fine meshes show a certain level of agreement, which indicates the coarse mesh resolution level is sufficient for the current aerodynamic study. Therefore, the coarse mesh resolution level is retained in this study hereafter. The variation of wave drag can be classified into four regions as indicated in Fig. 4. At the first region, shock waves generated from the head of a fuselage affect the frontend portion of the other fuselage. The total drag, therefore, is increased in this region. At the second region which exists only in the base geometry, the shock waves affect the constant radial locations of the other fuselage (Fig. 3(b) and (c)). At the third region, the shock waves affect the rearend portion of the other fuselage (Fig. 3(d)). Since the pressure rise due to the shock waves increases the thrust force at the rear-end portion, the drag is minimal in this region. At the fourth region, there is no interaction between the twin bodies, which results in a constant drag force. The amount of wave drag of the twin-body is exactly twice that of the individual single body. The distributions of pressure coefficient at the inner side of the base (twin, 2V) configuration are compared in Fig. 5. Although the third region \u00f0d=2 \u00bc 0:325\u00de is the most promising from the viewpoint of aerodynamics, those two bodies are separated too far to form a realistic airplane fuselage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001672_nu_140_01_011010.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001672_nu_140_01_011010.pdf-Figure4-1.png", + "caption": "Fig. 4 Calibration experiments: (a) system schematic and inprocess image sample and (b) force displacement data", + "texts": [ + " These experiments are designed to extract the specific load\u2013displacement curves for the fiber\u2013aluminum carrier substrate interface and the fiber\u2013polymer matrix interface. While 90-deg peel experiments have been used in literature to extract CZM parameters for pliable macroscale interfaces [15], the experiments here are challenging because the forces developed during the peeling of the microscale electrospun fibers are too low to be detected using conventional load cells. Therefore, a microscale tensile/compression system MicroSquisher TM (CellScale, Waterloo, ON, Canada) was used. Figure 4(a) shows the general layout of the system that uses a digital camera and pixel-tracking software to calculate the force exerted during the test. This force measurement is based on the movement of the piezoelectric stages (input) and the relative movement of the tip of a tungsten microbeam. The software calculates the force magnitude by solving a basic beam-deflection equation. Data are output at 5 Hz, with a resolution of 60.1 lN. The MicroSquisher TM system is typically used to measure the stiffness and surface tension of microscale soft materials and biomaterials", + ", samples where the fibers were attached to the aluminum carrier substrate (product of the near field electrospinning) and samples where the fibers were stamped onto the UV curable polymer matrix substrate. These samples were created such that the length of the fibers extended beyond the substrates. For each of the tests, a bundle of 4 to 8 free fibers ends was bonded to the microbeam of the instrument, using an adhesive. The adhesive was dried for 30 min before conducting the peel test by moving the piezoelectric stage vertically along the positive Y-direction (shown in Fig. 4(a)). The peel rate, the peel angle, and the diameter of the microbeam were selected to be 0.005 mm/s, 90 deg, and 0.30 mm, respectively. The inset in Fig. 4(a) shows the view from the camera during a peel test used to extract parameters for fiber\u2013polymer substrate interface. Figure 4(b) shows a representative force\u2013displacement curve from each of two sets of samples. As expected, the data clearly show that the bond between the fiber and the polymer matrix is significantly stronger than that between the fiber and the aluminum carrier substrate. It should be noted here that in these curves the region before the steady-state peel region (Fig. 4(b)) is a function of the slack in the fibers that needs to be taken up by the system. A total of three replicates were performed for each of the two sets of measurements denoted in Fig. 4(b). 3.1.3 Step 3: Estimating the Cohesive Zone Parameters Using a 3D Fiber-Peeling Simulation. Figures 5(a) and 5(b) shows the 3D finite element framework used to model the fiber-peeling experiments that were conducted in step 2. As seen, this model has 3D fibers that have modified contact areas as estimated in step 1. Two separate simulations were conducted for the two tests represented in Fig. 4(b). For the peeling simulation involving the polymer substrate and the fiber, cohesive zone elements were only attached along their interfacial area of contact (as shown in Fig. 5(a)). This allows the estimation of the CZM parameters specific to the fiber\u2013polymer matrix interface by tuning the CZM parameters to match the steady-state peel force from the calibration experiments. The same process was repeated but this time for the aluminum carrier substrate and the fiber combination where the CZEs were only attached along their interfacial area of contact (Fig", + " Table 2 lists the key cohesive zone parameters that yielded a steady-state peel force within 5.2% of the average experimental value. Figure 6 displays the model predicted load\u2013displacement curves for the parameters listed in Table 2. The spread in the experimentally measured steady-state peel force values is shown as a shaded region in the same figure. It should be noted that in the simulation, the steady-state peel force values are attained over much shorter lengths when compared to the experimental data (Fig. 4). This is because the simulation does not encounter the slack in the fibers encountered by the experiments. In addition, the \u201cpresteady-state\u201d portion of the simulated peel force graph (Fig. 6) represents the domain where the cohesive zone elements transition from their initial condition of having a uniform peel front for all fiber diameters, to a fiber diameter-dependent, uneven peel front, seen in the steady-state region (Figs. 5(a) and 5(b)). As such, comparisons cannot be made between the presteady-state portions of the simulated peel force and the experimental data, because of a mismatch of the fiber slack and peel front conditions", + " The boundary condition is that of a vertical velocity of 0.005 m/s applied to the aluminum carrier substrate, while the polymer substrate is kept stationary. In Fig. 7(b), after 0.16 s into the simulation, the CZEs are seen to fail at different rates based on the diameter of the fibers. After 1.89 s, the simulation results show the effective transfer of the fiber from the aluminum carrier substrate and onto the polymer substrate. 3.2.2 Model Validation. In order to validate the Stage 2 model, the setup described in Fig. 4(a) was used again to perform peeling experiments involving the three-material system modeled in Fig. 7. The validation experiment was set up by first placing a fiber-carrying aluminum substrate, 20 mm (length) 1 mm (width) 0.016 mm (thick), on the 3D-printed polymer substrate. This substrate size was limited by the smallest size that could be physically handled to run the peeling experiment. A weight of 5 g was then placed on the top surface of the fiber-carrying aluminum carrier substrate to simulate the stamping process", + " These findings imply that the predictions of the model need to be interpreted conservatively. The fiber transfer model developed in Sec. 3 can be used to improve the design of the fiber stamping unit, which is a critical part of the 3D printer configuration. The original fiber stamping unit designed by Spackman et al. [1] consisted of a flat plate onto which the fiber-carrying aluminum carrier substrate was mounted (Fig. 1). After the stamping operation was completed, the peeling Fig. 8 Experimental configuration for validation experiments (Note: Axis configuration is from Fig. 4(a), and velocity vector V is from Fig. 7(a).) 011010-6 / Vol. 140, JANUARY 2018 Transactions of the ASME D ow nloaded from http://asm edigitalcollection.asm e.org/m anufacturingscience/article-pdf/140/1/011010/6405745/m anu_140_01_011010.pdf by guest on 20 D ecem ber 2024 of the fibers from the aluminum substrate (and its subsequent deposition on the polymer matrix substrate) was achieved by a vertical motion of the flat-plate. This flat-plate design and the corresponding vertical peeling velocity boundary condition was seen to result in low fiber transfer efficiencies ( 50%) for fiber mats that have an effective area coverage <50% [1]", + " The peak stress levels in the fibers are then used as a measure to evaluate the efficacy of the design. Model-educated experiments are then run to confirm the fiber transfer efficiencies obtained by the new design. The remainder of this section presents the results of these model-enabled design efforts. 4.1 Boundary Conditions for a Roller-Based Stamping Unit Design. The experiments used to calibrate and validate the 3D model predictions were performed using the microtensile platform described in Fig. 4(a). However, the implementation of the stamping operation on the 3D printer involves not only significantly larger length scales but also entirely different boundary conditions than those encountered during the peeling operation using the microtensile platform. For the model to be useful for realistic process planning, the boundary conditions in the model must be mapped to that expected during the stamping process encountered on the 3D printer. Figure 9(a) shows the schematic of the new roller design envisioned for the fiber stamping and transfer process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002593_9312710_09335981.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002593_9312710_09335981.pdf-Figure8-1.png", + "caption": "FIGURE 8. MPMA-SynRM axial opening magnetic separation structure diagram.", + "texts": [ + " Because the deflection angle between different segments is small, and because the d-axis space of different rotors has little difference, the interaction of the axial magnetic circuits is not considered at this time. The MPMA-SynRM motor has a different modular rotor structure. After calculation, the deflection angle between different rotor modules is large, so it is necessary to set amagnetic isolation between different rotor modules in the axial direction. Whether there is an impact on theMPMA-SynRMmotor rotor is also considered a problem. As shown in Fig. 8. to analyse the impact of the magnetic isolation structure on the performance, this article uses an axial magnetic isolation of 10 times the air gap length between the different modules of the MPMA-SynRM motor. To minimize the edge effect, the corresponding position of the stator is also left with the same axial magnetic isolation length, as shown in Fig. 8. The MPMA-SynRMmotor with ten times the axial air gap length and without axial magnetic separation is simulated by the finite element method. Fig. 9 shows the distribution of the rotor flux density under a static magnetic field simulation, VOLUME 9, 2021 19951 in which Fig. 9 (a) shows the rotor flux density distribution with a 10g magnetic separation length in the axial direction. and Fig. 9 (b) shows the distribution of the rotor flux density without axial magnetic separation. The rotor flux density distribution of MPMA-SynRM has nothing to do with whether the axial direction is set under the no-load state" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002722_download_58477_60372-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002722_download_58477_60372-Figure9-1.png", + "caption": "Figure 9: Convection Enclosed block", + "texts": [ + "0103 The developed cylinder block was subjected to Finite element analysis to ascertain the optimal values of the thermal condition of the component. The AutoCAD designed internal combustion engine component was imported into the Steady state thermal analysis environment of the Finite element ANSYS software. The component was meshed into 10190 and 19616 elements and nodes respectively as shown in Figure 7. The already meshed component had its cylindrical compartment inputted with a temperature of 100oC as shown in Figure 8. Also, a stagnant-air horizontal at 22oC was used as the convection value for the entire cylinder block as shown in Figure 9. The cylinder block was further subjected to temperature and total heat flux output analysis in order to ascertain the effect of the inputted parameters on the component as shown on Figures 10 and 11 respectively. The temperature output result showed that the highest temperature of 100oC occurred around the cylinderical bore axis while the lowest temperature of 51.97oC was found on the cooling fins of the component . Similarly, the total heat flux had its maximum value around the cylindrical bore and its minimum on the cooling fins" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003588_O201305740751996.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003588_O201305740751996.pdf-Figure5-1.png", + "caption": "Fig. 5. Flow around a rotor", + "texts": [], + "surrounding_texts": [ + "QTW \ube44\ud589\uccb4\uc758 \ub3d9\uc5ed\ud559 \ubaa8\ub378\ub9c1\uc744 \uc704\ud574\uc11c\ub294 \ud56d \uacf5\uae30\uc758 \uc9c8\ub7c9\ubcc0\ud654\ub098 \uc9c8\ub7c9\ubd84\ud3ec\uc758 \ubcc0\ud654\uac00 \uc5c6\ub2e4\uace0 \uac00 \uc815\ud558\uace0 \ud56d\uacf5\uae30\uc5d0 \uc791\uc6a9\ud558\ub294 \uacf5\uae30\uc5ed\ud559\uc801 \ud798, \ucd94\ub825 \uc5d0 \uc758\ud55c \ud798, \uc911\ub825\uc5d0 \uc758\ud55c \ud798 \ub4f1\uc744 \uace0\ub824\ud55c\ub2e4. \ud56d\uacf5 \uae30\uc5d0 \uace0\uc815\ub418\uc5b4 \uc788\ub294 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\uac00 \uad00\uc131\uc88c\ud45c \uacc4\uc5d0 \ub300\ud574 \ud68c\uc804\ud558\uace0 \uc788\ub2e4\uace0 \uac00\uc815\ud558\uace0 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\uc5d0 \ub300\ud558\uc5ec \uac01\uc131\ubd84\ubcc4\ub85c \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc744 \uc815\ub9ac \ud558\uba74, Fig. 3\uacfc \uac19\uc774 \uc124\uacc4\ub41c \ube44\ud589\uccb4 \ud615\uc0c1\uc5d0 \ub300\ud574 6\uc790\uc720\ub3c4 \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc744 \uc5bb\uc744 \uc218 \uc788\ub2e4[6]. 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(13) \uc5ec\uae30\uc11c \ub294 \uc2dd(14)\uc640 \uac19\ub2e4. \u221e \u221e (14) \uc218\ub834\uc2dc\uae4c\uc9c0 \ubc18\ubcf5 \uacc4\uc0b0\ud558\uc5ec \uad6c\ud55c \uc720\ub3c4\uc18d\ub3c4 \ub97c \uc2dd(15)\uc5d0 \uc801\uc6a9\ud558\uba74 \ub2e4\uc74c\uacfc \uac19\uc774 \ucd94\ub825\uc744 \uad6c\ud560 \uc218 \uc788\ub2e4. \u221e (15) Slip stream \ud6a8\uacfc Slip stream\uc774\ub780 \ud504\ub85c\ud3a0\ub7ec\uac00 \ucd94\ub825\uc744 \uc77c\uc73c\ud0a4\uba74 \uc11c \ud68c\uc804\ud560 \ub54c \uadf8 \ud68c\uc804\uba74\uc758 \ub4a4\ucabd\uc5d0 \ud504\ub85c\ud3a0\ub7ec\uc758 \uc804 \uc9c4 \uc18d\ub3c4\ubcf4\ub2e4 \ud070 \uc720\uc18d\uc758 \uae30\ub958\uac00 \uc0dd\uae30\ub294 \uac83\uc744 \ub9d0\ud55c \ub2e4. 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(16) \ub294 \ud504\ub85c\ud3a0\ub7ec \ud6c4\ub958\uc5d0 \ub300\ud55c \uc8fc\uc775\uc758 \ubd99 \uc784\uac01\uacfc \uac19\uc740 \ud6a8\uacfc\uc640 \ucea0\ubc84\ub97c \uac00\uc9c4 \uc5d0\uc5b4\ud3ec\uc77c\uc774\ub77c\ub294 \uc810\uc744 \uace0\ub824\ud558\uc5ec 3\ub3c4\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub294 \uc870\uc885\uba85 \ub839\uc778 \ud50c\ub7a9\uac01\ub3c4\uc5d0 \ub530\ub978 \uc591\ub825\uacc4\uc218 \uc99d\uac00\ub97c \uace0\ub824\ud55c \ud56d\uc73c\ub85c 0.02\ub85c \uac00\uc815\ud588\uc73c\uba70 \ub294 \ud50c\ub7a9\uc758 \ubcc0\uc704\uc774 \ub2e4. (17) \uc2dd(17)\uacfc \uac19\uc774 \uc591\ub825\uacc4\uc218\ub97c \uc801\uc6a9\ud558\uc5ec \ud6c4\ub958\uc5d0 \uc7a0 \uae30\ub294 \ubd80\ubd84\uc5d0 \ub300\ud55c \uc591\ub825\uacfc \ud56d\ub825\uc744 \uad6c\ud560 \uc218 \uc788\uc73c \uba70, Fig. 4\uc640 \uac19\uc774 \ud6c4\ub958\uc5d0 \uc7a0\uae30\ub294 \ubd80\ubd84\uc758 \uba74\uc801\uc774 \uc77c\uc815\ud558\uc9c0 \uc54a\uc740 \uc810\uacfc \uc124\uacc4\ub41c QTW \ube44\ud589\uccb4\uc758 \uae30\ud558 \ud559\uc801 \ud615\uc0c1\uc744 \uace0\ub824\ud558\uc5ec \ud504\ub85c\ud3a0\ub7ec \uc9c0\ub984\uc758 70%\ub97c \ud3c9\uade0\uc801\uc73c\ub85c \uc7a0\uae30\ub294 \uc601\uc5ed\uc758 \uc2a4\ud32c\uc73c\ub85c \uac00\uc815\ud558\uace0 \uba74\uc801 \ub97c \uacc4\uc0b0\ud558\uc600\ub2e4. \ud56d\ub825\ubd80\ubd84\uc5d0\uc11c\ub294 QTW \ud615\uc0c1\uc758 \ud2b9\uc131\uc0c1 \ud504\ub85c\ud3a0\ub7ec\uc758 \ud6c4\ub958\uac00 \uc8fc\uc775 \ub05d\ub2e8\uae4c \uc9c0 \uc7a0\uae30\uae30 \ub54c\ubb38\uc5d0 \uc720\ud55c\ud55c \ub0a0\uac1c\uc758 \ud2b9\uc131\uc778 Vortex\uc5d0 \uc758\ud55c Downwash\uc640 Downwash\uc5d0 \uc758 \ud55c \uc720\ub3c4\ud56d\ub825\uc744 \ubb34\uc2dc\ud558\uace0 \ud615\uc0c1\ud56d\ub825\ub9cc\uc744 \uace0\ub824\ud558 \uc600\ub2e4. \uc2dd(17)\uc5d0\uc11c \ub3d9\uc555\uc740 \uc2dd(18)\uacfc \uac19\uc73c\uba70, \uc5ec\uae30 \uc11c \uc720\ub3c4\uc18d\ub3c4\ub294 \uc2dd(14)\uc5d0\uc11c \uacc4\uc0b0\ub41c \ud504\ub85c\ud3a0\ub7ec\uc758 \ud6c4\ub958\uc18d\ub3c4\uc5d0 \ud574\ub2f9\ub41c\ub2e4. (18) Slip stream\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\ub4e4\uc740 \ud2f8\ud2b8 \uac01\uc774\ub098 \ube44\ud589\uccb4 \uc790\uc138\uac01\uc5d0 \ubb34\uad00\ud558\uba70 \ud504\ub85c\ud3a0\ub7ec\uc5d0 \uc758 \ud574 \ubc1c\uc0dd\ub418\ub294 \ud6c4\ub958 \uc720\ub3c4\uc18d\ub3c4\uc640 \ud50c\ub7a9\ubcc0\uc704\uc5d0\ub9cc \uc601\ud5a5 \uc744 \ubc1b\uac8c \ub41c\ub2e4. Total force and Moment \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc740 Fig. 7\uacfc \uac19\uc774 \ud2f8\ud2b8 \uac01\ub3c4\uc5d0 \ub530\ub77c \uac01 \ud798\uc758 \ubc29\ud5a5\uc774 \ub2ec\ub77c\uc9c0\uae30 \ub54c\ubb38\uc5d0 \uac01 \ucd95 \ubc29\ud5a5\uc758 \ud798\uc758 \ud06c\uae30\ub97c \uacc4\uc0b0\ud560 \ub54c \ud2f8 \ud2b8 \uac01\ub3c4\ub97c \uace0\ub824\ud558\uc5ec\uc57c \ud55c\ub2e4. \uacc4\uc0b0\ub41c \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801\uc778 \ud798\uacfc \ubaa8\uba58\ud2b8\ub294 \ub2e4\uc74c\uacfc \uac19\uc774 \uae30\uccb4 \uace0\uc815 \uc88c\ud45c\uacc4\ub85c \ud45c\ud604 \ub420 \uc218 \uc788\ub2e4. sin (19) cos (20) cos sin cos (21) \uac01 \ub0a0\uac1c\uc5d0\uc11c \uc5bb\uc5b4\uc9c4 \ud798\ub4e4\uc744 \uc131\ubd84\ubcc4\ub85c \ub2e4\uc2dc \uc815\ub9ac \ud574 \ubcf4\uba74 \ub2e4\uc74c\uacfc \uac19\ub2e4. cossin (22) sin (23) sincos (24) cos (25) \ud2f8\ud2b8 \uac01\ub3c4\uc5d0 \ub530\ub77c \uac01 \ud798 \uc131\ubd84\ub4e4\uc744 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\ub85c \ubcc0\ud658\ud558\uc600\uc73c\uba70, \uac01 \ucd95\ubc29\ud5a5\uc758 \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc5d0 \ud6c4\ub958\uc5d0 \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84\uc5d0 \ub300\ud55c \ud798\uc744 \ucd94\uac00 \ud574 \uc8fc\uc5c8\ub2e4. \ud68c\uc804\uc775\ubaa8\ub4dc\uc5d0\uc11c\ub294 \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84 \uc774 \ud56d\ub825\uc73c\ub85c \uc791\uc6a9\ud558\uac8c \ub418\uace0 \ucc9c\uc774\ubaa8\ub4dc\ub97c \uac70\uccd0 \uace0 \uc815\uc775\ubaa8\ub4dc\ub85c \ud2f8\ud2b8\ub428\uc5d0 \ub530\ub77c \ud56d\ub825\uc740 \uc904\uace0 \uc591\ub825\uc740 \uc99d\uac00\ud558\uac8c \ub41c\ub2e4. \uc2dd(21)\uc758 \ud53c\uce6d\ubaa8\uba58\ud2b8\ub294 \uc804\ubc29\uc8fc\uc775 \uacfc \ud6c4\ubc29\uc8fc\uc775\uc758 \ucd94\ub825, \uc591\ub825 \ubc0f \ud56d\ub825\uc758 \ucc28\uc774\uc5d0 \uc758 \ud574 \ud06c\uae30\uac00 \uacb0\uc815\ub41c\ub2e4." + ] + }, + { + "image_filename": "designv8_17_0003921_3272-021-00517-7.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003921_3272-021-00517-7.pdf-Figure1-1.png", + "caption": "Fig. 1 Contra-rotating fan engine", + "texts": [ + " Integrating an engine into the airframe enhances this effect. Finally, ducted engines provide a high specific thrust relating to the cross-sectional area. In summary, future research on ducted electric fan engines should focus on improving both internal and propulsive efficiency to allow these engines to compete against propeller-driven engines in the low-to-moderate cruise speed segment. At this point, the contra-rotating fan engine (CRF) is unfolding its potential to achieve the abovementioned goals and become a game changer. Figure\u00a01 depicts an exemplary model of a CRF. Strictly speaking, conceptual contra-rotating fans have already been introduced during the last century, being integrated in gas turbine engines. Anyway, integrating and synchronizing contra-rotating fans into an engine powered by a gas generator is both complex and expensive\u2014a common drawback all these concepts suffered from. Most of the conceptual engines never attained more than prototype status [8]. Due to the ongoing enhancement of electric motors, a new opportunity arises to implement contra-rotating fan stages into aircraft engines, successfully" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure31-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure31-1.png", + "caption": "Figure 31 1st Mode of Power-On/Purge Style Back Plate", + "texts": [ + "24, while the acceptable margin of safety for yield strength analysis is greater than 0.0. The next analysis case was to show the effect of the back plate changes on the fundamental frequency of the P-POD. The concern was that cutting a hole in the back plate would cause a reduction in stiffness that would lower the fundamental frequency of the P-POD. The outer walls of the back plate were assumed to be fixed, and the resulting displacement plot of the 1st mode of the new back plate is shown below in Figure 31. As expected a basic panel mode appeared as the first mode. However, instead of reducing in natural frequency, the lack of mass at the center of the back plate increased the first mode substantially. Comparison frequencies from the Mk. III Rev. E back plate, and the Power-On/Purge back plate are shown below in Table 11. For reference, the P-PODs Page 45 natural frequency is around 120 Hz, therefore it was concluded that the modifications to the back plate would not significantly effect the natural frequency of the P-POD" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003030_al-02351699_document-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003030_al-02351699_document-Figure2-1.png", + "caption": "Fig. 2. Elementary cell of the metasurface (dielectric substrates not represented).", + "texts": [ + " GENERAL APPROACH The active metasurface is schematized in Fig. 1. It is made of the passive metasurface structure (META), and the NIC circuit and its load. The proposed methodology for designing the wideband metasurface relies on the optimization of the NIC and its load, which are connected to this fixed metasurface resonant structure in order to achieve a reflection coefficient (referred as \u0393) strictly equal to one. III. CHARACTERIZATION OF THE METASURFACE The metasurface used in this study is shown in Fig. 2. Two Neltec NY9220 (\u025br = 2.2, tan \u03b4 = 0.0009) substrates are stacked above a metallic ground plane. The thicknesses of lower and upper dielectric substrates are respectively 2.286 mm and 0.127mm. The periodicity of the unit cell is 24mm \u00d7 24mm. The 0.127mm thick dielectric substrate has square copper patches printed on both sides. The patches of the top layer of the elementary periodic cell are connected 2 by 2 with metallic junctions. The patches of the bottom copper layer are translated with respect to the top copper layer by half the periodicity and do not have any junctions between them" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000466_f_version_1668679703-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000466_f_version_1668679703-Figure10-1.png", + "caption": "Figure 10. Evaluation of adhesion to punch via EPMA for 5 \u03bcm-textured punch: (a) 1st and (b) 5th extrusion; nanometer-textured punch: (c) 1st and (d) 5th extrusion.", + "texts": [ + " (a) (b) (c) Figure 8. KAM map of the extrusion via EBSD: (a) mirror surface, (b) 5 \u03bcm-textured, and (c) nanometer-textured punches. 3.4. Comparison of Microtexture and Nanotexture Punches To investigate the anti-adhesion and anti-wear properties of micro- and nanotex- tured punches, a comparison in terms of the first and fifth extrusion cycles was conducted as shown in Figure 9. The nanotexture punch continues to reduce the force, whereas the 5 \u00b5m-textured punch tends to increase the extrusion force. Figure 10 shows the results of EPMA measurements of Al element adhesion on the punch surfaces after the first and fifth extrusion cycles. In the case of the 5 \u00b5m-textured punch, the EPMA results show increased adhesion in the grooves, and Al adhesion in the recesses of the grooves, which is not observed in the first cycle, is also observed in the fifth cycle. In the case of the 5 \u00b5m- textured punch, the grooves are worn out by the fifth cycle of processing, and the in- creased amount of adhesion is considered to have caused the increased extrusion force", + " (a) (b) (c) Figure 8. KAM map of the extrusion via EBSD: (a) mirror surface, (b) 5 \u03bcm-textured, and (c) nanometer-textured punches. 3.4. Comparison of Microtexture and Nanotexture Punches To investigate the anti-adhesion and anti-wear properties of micro- and nanotextured punches, a comparison in terms of the first and fifth extrusion cycles was conducted as shown in Figure 9. The nanotexture punch continues to reduce the force, whereas the 5 \u00b5m-textured punch tends to increase the extrusion force. Figure 10 sho s the results of EPMA measureme ts of Al element adhesion on the punch surfaces after the fir t and fifth extrusion cycles. In th case of the 5 \u00b5m-textured punch, the EPMA r sults show increased adhesion in the grooves, and Al adhesion in the recesses of the grooves, which is not observed in the first cycle, is also observed in the fifth cycle. In the case of the 5 \u00b5mtextured punch, the grooves are worn out by the fifth cycle of processing, and the increased amount of adhesion is considered to have caused the increased extrusion force. Figure 8. KAM map of the extrusion via EBSD: (a) mirror surface, (b) 5 \u00b5m-textured, and (c) nanometer-textured punches. To investigate the anti-adhesion and anti-wear properties of micro- and nanotextured punches, a comparison in terms of the first and fifth extrusion cycles was conducted as shown in Figure 9. The nanotexture punch continues to reduce the force, whereas the 5 \u00b5m-textured punch tends to increase the extrusion force. Figure 10 shows the results of EPMA measurements of Al element adhesion on the punch surfaces after the first and fifth extrusion cycles. In the case of the 5 \u00b5m-textured punch, the EPMA results show increased adhesion in the grooves, and Al adh sion in the recesses of t e gro ves, which is not observ in the first cycl , is als observed in the fifth cycle. In the case of the 5 \u00b5m-texture punch, the grooves are worn out by the fifth cycle of proc ssing, and the increased amount of adhesion is considered to have caused the increased extrusion force", + " The microtextured punches applied a force perpendicular to the edges of the texture ring, and the nanotextured punches applied a force parallel to th direction of the punch, which may have further damaged th texture ring. Considering the lifetime of the texture and durability of the force reduction effect, the nanotextured punch is a tool with superior wear resistance and a longer life surface function than that of the microtextured punch. However, reducing the texture size to the nano-level and lower is limited by laser texturing technology, and advanced microsurface creation technology, such as i n beam texturing, is needed. Figure 9. Extrusion force vs. number of extrusions. (a) (b) (c) (d) Figure 10. Evaluation of adhesion to punch via EPMA for 5 \u03bcm-textured punch: (a) 1st and (b) 5th extrusion; nanometer-textured punch: (c) 1st and (d) 5th extrusion. Figure 9. Extrusion force vs. number of extrusions. Micromachines 2022, 13, x 9 of 11 However, the nanotextured punch shows no significant change in the amount of adhesion compared to that in the first punching, indicating that the effect of reducing the amount of adhesion is sustained. This finding suggests that the forces of adhesion and detachment are repeatedly pplied to the textured part of the 5 \u00b5m t xture, leadi g to t wear of the texture and, consequently, an increase in force because the friction reduction effect cannot be maintained", + " The microtextured punches applied a force perpendicular to the edges of the texture ring, and the nanotextur d punches applied a force parallel to the direction of the punch, which ay have further damaged the textu e ring. Considering the lifetime of the texture a d d rability of the force reduction effect, the nanotextured punch is a tool with superior wear resistance and a longer life surface function than that of the micro extured pu ch. Howeve , reducing the texture size to th nano-level and lower is limited by laser texturing technology, and advanced microsurface creation technology, such as ion beam text ring, is nee ed. Figure 9. Extrusion force vs. number of extrusions. (a) (b) (c) (d) Figure 10. Evaluation of adhesion to punch via EPMA for 5 \u00b5m-textured punch: (a) 1st and (b) 5th Micromachines 2022, 13, x 10 of 11 5. Repeated experiments showed that the extrusion force and adhesion to the punch increased with increasing extrusion frequency for the microscale texture. For the nanotextured punches, the extrusion force decreased with increasing extrusion frequency, while adhesion to the punches decreased. Future research will include an investigation into texture direction in nanotextured punches and their application to the preparation of biomaterials based on magnesium and titanium" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000307__2018jamdsm0123__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000307__2018jamdsm0123__pdf-Figure4-1.png", + "caption": "Fig. 4 Stroke process", + "texts": [ + " 3 2 \u00a9 2018 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2018jamdsm0123] After the p iston\u2019s return process is completed, the p iston is located at the back end of the drifter body, whereas the shuttle valve is on the body\u2019s left side. The piston in itiates stroke accelerat ion motion under the action of the high-pressure oil in the back chamber V2. When the piston reaches a certain position, the signal hole b opens and the right chamber V4 of the shuttle valve is connected to the oil tank to prepare for the reverse process, as shown in Fig. 4(a). The piston continues its stroke acceleration mot ion to open the signal hole d. The left chamber V3 of the valve is connected to the high-pressure oil in the back chamber V2 of the piston, and the valve begins to reverse toward the right. The piston is accelerat ing at this moment, as shown in Fig. 4 (b). When the valve moves toward the right to close the e and g ports and open the f and h ports, the piston\u2019s front chamber V1 is connected to the high-pressure oil, whereas its back chamber V2 is connected to the oil tank. If the p iston impacts the shank adapter, then it will start the next return process cycle under the action of the high-pressure oil and the shank adapter\u2019s rebound force. Otherwise, the piston will begin to decelerate until it stops under the action of the high-pressure oil and then enters into the next return process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000853_9668973_09718336.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000853_9668973_09718336.pdf-Figure4-1.png", + "caption": "FIGURE 4. Rotational motion from (a) 0\u25e6 to (b) 70\u25e6.", + "texts": [ + " The length between the revolute axis and linear guide block as a function of the angle \u03b8 , l\u03b8 , can be obtained as follows, l\u03b8 = h cos\u03b8 . (2) When the angle of the revolute joint changes from 0\u25e6 to 70\u25e6, the length changes from 24 mm to approximately 70 mm. To cover the linear displacement, we applied another linear guide with a displacement of approximately 50 mm between the revolute link and the block. In addition, to compensate for the angular displacement, a bearing was applied at the linear guide block. Fig. 4 shows the motion of the proposed revolute joint. When the block is in the center of the lead-screw-based linear guide, the angle of the revolute link is 0\u25e6. Based on the location of the center, the block can move using the same number of strokes on both sides and will change the rotation angle by up to \u00b170\u25e6. C. MATERIALS The linear actuator consists of a lead-screw-driven linear guide (LX1502-B2-N-175, MISUMI Group Inc., Tokyo, Japan) and a rotary motor (BXTH 3216, FAULHABER MINIMOTOR SA, Croglio, Switzerland)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003103_26_tylek_203-215.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003103_26_tylek_203-215.pdf-Figure9-1.png", + "caption": "Fig. 9 Robot\u2019s planting module, mounted on a frame with an adjustable swing drive axle, while working on a slope \u2013 rear view", + "texts": [ + " The main element of the planting unit is in the form of a cylindrical dibble connected to the carriage, which is mounted slidably in relation to the frame and is moved in relation to it along the horizontal axis by means of an independent drive. Ultimately, the planting module is to be mounted on a specialised, autonomous carrier, while in the case of aggregating the module with agricultural or forestry tractors, the frame of the working unit should be equipped with an appropriate levelling system. The developed conceptual model of such a solution is presented in Fig. 9. Attached to the frame in its rear part, there is an adjustable swing axle with support wheels and, in its front part, a swing hitch to the tractor. Levelling is performed by analysing the indications from the acceleration sensor (gravity sensor) mounted to the frame of the working unit. Fig. 10 and 11 below show an openable dibble in which the jaws and the cylinder are opened by one drive. The appropriate kinematics is ensured by rockers with pivots placed at an angle, thanks to which the opening occurs as a result of lifting the movable parts of the dibble" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure4-1.png", + "caption": "Figure 4. Overview of the transducer.", + "texts": [ + " It was therefore determined that, in order to allow full and correct identification, a dynamic parameter meter of low values should be used, for which the following preliminary assumptions were made: (1). force along the Z axis \u2212 F_z = 450 N, (2). force along the Y axis \u2212 F_y = 200 N, (3). torque about the X axis \u2212M_x = 200 Nm. For the purpose of measurement of such small force components, it was decided that the spatial measurement method of dynamic loads with the use of crossbars should be implemented. In the adopted solution, a system comprising three elements: two measurement bars and a connector arranged as in Figure 4 was proposed. The system elements were designed so that they can be reconfigured depending on the type of agricultural tool (Figure 5). At the same time, this solution made it possible to simplify the production process of precision measurement bars and thus decreased their cost of production. In terms of the design, the top and bottom bars are carbon copies of each other. They were designed as cubic elements with a square cross-section and dimensions of 20 mm \u00d7 20 mm with four drilled out rectangular holes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure6-17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure6-17-1.png", + "caption": "Figure 6-17. Vue des antennes patchs de r\u00e9f\u00e9rence avant rotation", + "texts": [ + " Repr\u00e9sentation de la g\u00e9om\u00e9trie du syst\u00e8me d'antennes FTRD .............................. 195 Figure 6-13. Coefficients de r\u00e9flexion (S11) des deux syst\u00e8mes UWB ..................................... 196 Figure 6-14. Antenne miniature utilis\u00e9e dans le syst\u00e8me \u00e0 diversit\u00e9.......................................... 201 Figure 6-15. Syst\u00e8me d'antennes miniatures avant rotation ....................................................... 201 Figure 6-16. Repr\u00e9sentation du dip\u00f4le dans le rep\u00e8re initial ...................................................... 202 Figure 6-17. Vue des antennes patchs de r\u00e9f\u00e9rence avant rotation............................................. 203 Figure 6-18. Coefficients de r\u00e9flexion des antennes patchs polaris\u00e9es verticalement et horizontalement et de l'antenne miniature (\"chip antenna\") ....................................................... 204 Figure 7-1. Probabilit\u00e9s de densit\u00e9 cumul\u00e9e avant et apr\u00e8s recombinaison et mesure du gain de diversit\u00e9........................................................................................", + " Les deux autres antennes de r\u00e9f\u00e9rence que nous avons utilis\u00e9es sont des antennes patchs 203 avec des polarisations orthogonales, l'une produit une polarisation verticale et l'autre une polarisation horizontale. Ces deux antennes sont r\u00e9alis\u00e9es sur un substrat CLTE de Arlon avec une permittivit\u00e9 de 2,98 et une \u00e9paisseur de 3,81 mm. Le substrat comme le plan de masse mesure 100 x 50 mm pour rester en accord avec les contraintes du syst\u00e8me d'antennes \u00e9tudi\u00e9. Les deux antennes sont repr\u00e9sent\u00e9es sur la Figure 6-17. Dans le cas de l'antenne polaris\u00e9e verticalement, le patch mesure 32,5 mm x 29 mm. L'antenne est plac\u00e9e \u00e0 10,25 mm du bord du substrat et le point d'alimentation du patch est plac\u00e9 \u00e0 12 mm du bord du patch. Dans le cas de l'antenne polaris\u00e9e horizontalement, les dimensions du patch polaris\u00e9 verticalement ont \u00e9t\u00e9 conserv\u00e9es avec une rotation de 90\u00b0. Le patch mesure donc 29 mm x 32,5. L'antenne est plac\u00e9e \u00e0 12 mm du bord du substrat et le point d'alimentation est \u00e9galement plac\u00e9 \u00e0 12mm du bord du patch" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000952_tation-pdf-url_71269-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000952_tation-pdf-url_71269-Figure3-1.png", + "caption": "Figure 3. Motor gearbox.", + "texts": [ + "91059 Tm \u00bc Po=\u03c9 (18) \u03c9 \u00bc 2\u03c0N 60 \u00bc 314:16 rps (19) where according to the real specification of the 3PSM, the torque of the motor can be calculated using Eqs. (1) and (2): Tm \u00bc 1200W= 2 3:14 3000=60\u00f0 \u00de \u00bc 3:8n m This anticipated torque is significantly adequate with 3000 rpm for the present load and as an input of mechanical gearbox. The next qualifications of the mechanical gear box will depend firmly upon the two manufactured torques: torque of the 3PSM and traction torque required for the vehicle load. Figure 2 shows the three-phase synchronous motor which is used for vehicle and its nameplate. The gearbox used in the vehicle is shown in Figure 3. It is subjected to many factors: input and output speeds and input and output torques required. The present vehicle has a steady-state linear speed which reaches slightly more than 40 km/hr. The angular velocity of vehicle tires is explained by Eq. (20), where r is identified as the tire radius. The real tire radius is measured to give 0.125 m. The angular speed of gearbox pulley is determined by Eq. (21): V t \u00bc 2\u03c0r\u03c9t (20) \u03c9tD \u00bc \u03c92 d2 (21) where according to the real linear speed of the vehicle\u2019 tires, the angular speed of the tire can be calculated using Eq" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003512_e_download_9236_8414-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003512_e_download_9236_8414-Figure3-1.png", + "caption": "Figure 3: Mesh model along with boundary conditions (left) & Preserved region for Generative design", + "texts": [ + " Solid Edge was used to create the part model to conduct the finite element analysis, also it was used to do generative design and redesign of the component as well. First, the articulated rod, which is the focused part for improvement, was created. Then, the boundary conditions are applied to the model. The fix constraint was applied to the smaller circular ring. The force of 25000 N was given to the inner surface of the bigger cylinder. The boundary conditions of articulated rod model can be seen in the Figure 3 (left). After that, in order to observe the stress and displacement distribution in the model, finite element analysis was run. Also, mesh analysis was conducted to observe the change in the maximum stress, maximum displacement, and elapse time of the different subjective mesh size in order to select the most reasonable mesh size for the finite element analysis. In the mesh analysis, 10 different mesh sizes were applied to the model. Figure 3 (right) also shows the preserved region of the rod which will not undergo any changes during generative design so that the connecting parts doesn\u2019t need any changes after the generative design results are obtained. Next, the generative design of the part was started. The goal is to reduce the mass of the rod while the stress and displacement is within the acceptable range. The bigger and smaller cylinder were selected to be a preserved region, which will not change in shape after the new design is finished so that compatibility with existing parts remains unchanged" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003454_6_61_4_61_4_501__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003454_6_61_4_61_4_501__pdf-Figure5-1.png", + "caption": "Fig. 5 Calculated result of the maximum outside diameter and the minimum inside diameter", + "texts": [], + "surrounding_texts": [ + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\nRg: \u57fa \u790e \u5186 \u7b52 \u534a \u5f84 R0: \u57fa \u790e \u30d4 \u30c3\u30c1 \u5186 \u7b52 \u534a \u5f84\nRx: \u6b6f \u5f62 \u4e0a \u306e \u4efb \u610f \u306e \u534a \u5f84 Tg: \u57fa\u790e\u5186\u7b52\u4e0a\u306e\u5186\u5f27\u6b6f\u539a T0: \u57fa \u6e96 \u30d4 \u30c3\u30c1 \u5186\u7b52 \u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a\nTx: Rx\u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a 2\u03c8g: \u5f27Tg\u306b \u5bfe \u3059 \u308b\u4e2d \u5fc3 \u89d2\n2\u03c80: \u5f27T0\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2\n2\u03c8x: \u5f27Tx\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2 \u03b1x: Rx\u4e0a \u306b \u304a \u3051 \u308b\u304b \u307f \u5408 \u3044 \u5727 \u529b \u89d2 \u03b10: \u5de5 \u5177 \u5727 \u529b \u89d2\n\u3092\u8868 \u3059.\n(a) \u5927 \u7aef \u76f4 \u5f84\n\u56f32\u3067 \u4efb \u610f \u306e \u534a \u5f84Rx\u306b \u304a \u3051 \u308b \u5186\u5f27 \u6b6f \u539aTx\u306f,X\u3092 \u8ee2 \u4f4d\n\u4fc2 \u6570 \u3068 \u3057\u3066\n( 1 )\n\u3067\u8868\u305b\u308b.\u307e \u305f\u57fa\u6e96\u30d4\u30c3\u30c1\u5186\u4e0a\u306e\u5186\u5f27\u6b6f\u539aT0 \u306f\n( 2 )\n\u3068\u306a \u308b.\u5f0f(1)\u306b \u5f0f(2)\u3092 \u4ee3 \u5165\u3059 \u308b \u3068\n( 3 )\n\u3068\u306a \u308b.\u5f93 \u3063\u3066,\u5927 \u7aef \u76f4 \u5f84 \u306f \u6b6f \u5148 \u306e \u3068\u304c \u308a\u3092\u9650 \u754c \u306b\u3059 \u308b \u306b \u306fTx=0\u3068 \u3059 \u308c \u3070 \u3088 \u3044.\u5f0f(3)\u3092inv\u03b1x\u306b \u3064 \u3044 \u3066 \u89e3\n\u304f\u3068\n( 4 )\n\u3068 \u306a \u308b.\u3053 \u3053\u3067\n( 5 )\n( 6 )\n\u3068\u3059 \u308b \u3068,\u76f8 \u5f53 \u5e73 \u6b6f \u8eca \u306e\u6b6f \u6570Zv\u306f,\u03b3 \u3092\u57fa \u790e \u5186 \u7b52 \u306d \u3058\u308c\n\u89d2 \u3068 \u3057\n( 7 )\n\u3068\u306a\u308b.\u307e \u305f\u4efb\u610f\u306e\u534a\u5f84Rx\u4e0a \u306e\u8ee2\u4f4d\u4fc2\u6570X \u306f\n( 8 )\n\u3067 \u8868 \u3055\u308c \u308b.\u3088 \u3063\u3066 \u5927 \u7aef \u534a \u5f84D0 \u306f\n( 9 )\n\u3088 \u308a\u6c7a \u5b9a \u3055 \u308c \u308b.\n(b) \u5c0f \u7aef \u76f4\u5f84\n\u5c0f \u7aef \u76f4 \u5f84 \u306e \u6c7a \u5b9a \u306b \u3064 \u3044 \u3066 \u306f,\u56f33\u306b \u793a \u3059 \u3088 \u3046 \u306b,\u6b6f \u306e\u5207 \u308a\u4e0b \u3052 \u3092 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5e73 \u9762 \u307e \u3067 \u751f \u3058\u3066 \u3082 \u826f\u3044 \u3068\u4eee\n\u5b9a5)\u3059 \u308b.\u8ca0 \u306e \u8ee2 \u4f4d \u304b \u3089,\u57fa \u6e96 \u5727 \u529b \u89d220\u309c \u306e \u5834 \u5408,\u5e73 \u6b6f \u8eca \u306e \u9650 \u754c \u6b6f \u6570 \u306fZmin=17\u3067 \u3042 \u308a,\u8ee2 \u4f4d \u4fc2 \u6570X \u306f\n( 10 )\n\u5f93 \u3063\u3066 \u5c0f \u7aef \u76f4\u5f84Di\u306f \u6b21 \u5f0f \u3088 \u308a\u6c42 \u307e \u308b.\npositive shift\n502 \u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u5893\u3064\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n( 11 )\n\u305f \u3060 \u3057,Z'\u306f \u5207 \u308a\u4e0b \u3052 \u3092 \u3069 \u3053 \u307e \u3067 \u8a31 \u3059 \u304b \u306b \u3088 \u3063\u3066 \u6c7a \u307e \u308b\n\u6b6f \u6570 \u3067,\u56f33\u306e \u5834 \u5408 \u3067 \u306fZ'=6\uff5e8\u306b \u3059 \u308c \u3070 \u3088 \u3044.\n(c) \u30aa \u30d5 \u30bb \u30c3 \u30c8\u4e0b \u3067 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84\n\u56f34\u306b \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3057\u3066 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84 \u306e \u5909 \u5316 \u306e\n\u69d8 \u5b50 \u3092 \u793a \u3059.\u56f3 \u4e2d \u306e \u5404 \u8a18 \u53f7 \u306f \u305d \u308c \u305e \u308c\na: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf Z: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e\u6b6f \u6570 \u03c9: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u89d2 \u901f \u5ea6\n\u03b2: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u89d2 R0: \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84 Ra: \u30aa \u30d5\u30bb \u30c3 \u30c8\u3067 \u5909 \u5316 \u3057\u305f \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84\nV0: \u534a \u5f84R0\u4e0a \u306e \u901f \u5ea6 Va: \u534a\u5f84Ra\u4e0a \u306e \u901f \u5ea6\n\u3092\u8868 \u3059.\u3053 \u308c \u3088 \u308a,\u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306b\u5bfe \u3057\u3066 \u5c0f \u6b6f \u8eca \u304c \u30aa \u30f3\u30bb \u30f3 \u30bf(P\u306e \u4f4d \u7f6e)\u306b \u304a \u3044 \u3066 \u306f,\u5c0f \u6b6f \u8eca \u306e \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84 \u306e \u6bd4 \u306f\u6b6f \u6570 \u306e \u6bd4(\u89d2 \u901f \u5ea6 \u306e \u6bd4)\u306b \u7b49 \u3057 \u304f\u306a \u308b \u304c,\u30aa \u30d5 \u30bb \u30c3 \u30c8 (\nP'\u306e \u4f4d \u7f6e)\u4e0b \u3067 \u306f \u4e21 \u534a \u5f84 \u306e \u6bd4 \u306f,\u306f \u3059 \u3070 \u89d2 \u306e \u5f71 \u97ff \u3092 \u53d7\n\u3051\u3066 \u5fc5 \u305a \u3057\u3082\u6b6f \u6570 \u306e \u9006 \u6bd4 \u306b\u7b49 \u3057 \u304f\u306f \u306a \u3089 \u306a \u3044.\u3059 \u306a \u308f \u3061 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3059 \u308b \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84Ra \u306f\n( 12 )\n\u3068\u306a \u308b.\u307e \u305f,\u5f0f(12)\u3067 \u03b2\u306e \u4ee3 \u308f \u308a\u306b \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf a\n\u3092\u7528 \u3044\u3066 \u8868 \u3059 \u3068\n( 13 )\n\u3068\u306a \u308b.\u305f \u3060 \u3057,\u30aa \u30f3\u30bb \u30f3 \u30bf\u3067 \u306fa=0\u3067 \u3042 \u308b.\u3088 \u3063\u3066 \u30d4 \u30c3\u30c1 \u5186\u76f4 \u5f84Dp \u306f\n( 14 )\n\u3067\u8868 \u305b \u308b.\u4ee5 \u4e0a \u304c \u8a2d \u8a08 \u6cd5 \u3067 \u3042 \u308b.\u6b21 \u306b \u5177 \u4f53 \u7684 \u8a08 \u7b97 \u6cd5 \u306f, \u307e\n\u305a \u5404 \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u306b\u5bfe \u3057\u3066 \u5f0f(13)\u3088 \u308aDp\u3092 \u6c42 \u3081 \u308b. \u305d \u306eDp\u306b \u5bfe \u3057\u5f0f(9),(10)\u3088 \u308aDo,Di\u3092 \u7b97 \u51fa \u3059 \u308b\n\u56f35\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e\u6b6f \u6570 \u3068 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u3067 \u5927 \u7aef,\u5c0f \u7aef \u76f4 \u5f84 \u304c \u3069\u306e \u3088 \u3046 \u306b\u5909 \u5316 \u3059 \u308b \u304b \u306e \u8a08 \u7b97\u7d50 \u679c \u3092\u793a \u3059.\u3053 \u308c \u3088 \u308a\n\u6b6f \u6570 \u304c \u5897 \u3059 \u3068,\u4e21 \u76f4\u5f84 \u304c \u5927 \u304d \u304f \u306a \u308b \u3068\u540c \u6642 \u306b\u4e21 \u76f4 \u5f84 \u306e \u5dee, \u3064 \u307e \u308a\u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b.\u307e \u305f,\u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u304c \u5927 \u304d \u3044 \u307b\n\u3069\u5927 \u7aef,\u5c0f \u7aef \u76f4\u5f84 \u53ca \u3073 \u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b \u3053 \u3068\u304c \u308f \u304b \u308b.\u3053 \u308c \u306f \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u306e \u5897 \u52a0 \u306b\u4f34 \u3044 \u30d4 \u30c3\u30c1 \u5186 \u76f4\u5f84 \u304c \u5927 \u304d \u304f\u306a \u308b \u304b \u3089\u3067 \u3042 \u308b.\u3057 \u304b \u3057\u306a \u304c \u3089\u6b6f \u6570 \u304c40\u679a,\u30aa \u30d5 \u30bb \u30c3 \u30c8 10\n\u30fbm\u306b \u5bfe \u3057\u6b6f \u5e45 \u306f5mm\u7a0b \u5ea6 \u3067 \u3042 \u308a,\u540c \u3058 \u304f\u6b6f \u6570140 \u679a\n\u3067 \u308210mm\u7a0b \u5ea6 \u3068\u6b6f \u5e45 \u304c \u72ed \u3044.\u3053 \u306e \u3053 \u3068\u306f \u5148 \u306b\u8ff0 \u3079 \u305f \u3088\n\u3046\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e1\u3064 \u306e \u6b20 \u70b9 \u3067 \u3082\u3042 \u308b \u308f \u3051 \u3067 \u3042 \u308b.\u3055 \u3089\npitch plane\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 503", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a8\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n\u306b\u304b \u307f \u5408 \u3044 \u5727 \u529b \u89d2 \u306f \u5c0f \u7aef \u304b \u3089 \u5927\u7aef \u306b \u5411 \u304b \u3063\u3066 \u5927 \u304d \u304f\u306a \u308b5) \u305f\u3081,\u6709 \u52b9 \u306a\u52d5 \u529b \u4f1d \u9054 \u4e0a,\u4eee \u306b \u6b6f \u5e45 \u3092\u6e1b \u5c11 \u3055\u305b \u308b \u306b \u306f, \u5927\n\u7aef \u304b \u3089\u6e1b \u3089\u3059 \u3079 \u304d \u3067 \u3042 \u308b.\n3. \u901a \u5e38 \u306e \u30dc \u30d6 \u76e4 \u306b \u3088 \u308b \u6b6f \u5207 \u308a \u3068\u304b \u307f \u5408 \u3044 \u8a66 \u9a13\n\u4e0a\u8a18 \u306e \u8a08 \u7b97\u7d50 \u679c \u306b \u57fa \u3065 \u3044 \u3066 \u901a \u5e38 \u306e \u30dc \u30d6 \u76e4(HAMAI,H- 102 )\n\u3068\u5e02 \u8ca9 \u30db \u30d6(\u30e2 \u30b8 \u30e5 \u30fc \u30eb1,\u5de5 \u5177 \u5727 \u529b \u89d220\u309c,\u306d \u3058\u308c \u89d21\u309c 57',\n\u5207\u308c \u6b6f \u5217 \u65706)\u3092 \u7528 \u3044 \u3066 \u6b6f \u5207 \u308a\u3092 \u884c \u3063\u305f.\u5f53 \u521d,\u30dc \u30d6 \u3067 \u6b6f \u5207 \u308a \u3057\u305f \u5834 \u5408,\u5185 \u6b6f \u6b6f \u8eca \u306e \u30c8\u30ed \u30b3 \u30a4 \u30c9\u5e72 \u6e09 \u306b\u4f3c \u305f \u3053 \u3068\u304c \u30dc \u30d6 \u3068\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u3068 \u306e \u9593 \u306b\u8d77 \u3053 \u308a,\u6b6f \u5f62 \u306e \u5927 \u304d \u306a \u304f\u305a \u308c \u304c \u4e88\n\u60f3 \u3055 \u308c \u305f \u306e \u3067,\u30dc \u30d6 \u306e \u5207 \u308c \u6b6f \u304c3\u5217(\u5e458mm)\u306b \u306a \u308b \u3088 \u3046 \u306b \u5207 \u65ad \u3057\u305f \u3082\u306e \u3092\u7528 \u3044 \u3066 \u8a66 \u9a13 \u7684 \u306b \u6b6f \u5207 \u308a\u3092 \u884c \u3063\u305f(\u30db \u30d6 \u5e45 \u306b\u3088\n\u308b\u6b6f \u5e45 \u7b49 \u3078 \u306e \u5f71 \u97ff \u306f \u5225 \u5831 \u3067 \u8a73 \u7d30 \u306b \u8ff0 \u3079 \u308b).\n\u56f36\u306b \u5177 \u4f53 \u7684 \u6b6f \u5207 \u308a\u6cd5 \u3068\u6b6f \u5207 \u308a\u5f8c \u306e \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u3092 \u793a \u3059.\n\u6b6f \u5207 \u308a\u306f \u3044 \u308f \u3086 \u308b \u30b3 \u30f3\u30d9 \u30f3 \u30b7 \u30e7\u30ca \u30eb \u6cd5 \u3067 \u3042 \u308a,\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u7d20 \u6750 \u306b \u5bfe \u3057 \u3066,(1)\u30db \u30d6 \u306e \u4e2d \u5fc3 \u3092 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u4e2d\u5fc3 \u304b \u3089\u6a2a \u306b\u79fb \u52d5 \u3055\u305b \u6240 \u5b9a \u306e \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u3092 \u4e0e \u3048 \u308b.(2)\u30dc \u30d6 \u3092 \u3042 \u3089\u304b\n\u3058\u3081 \u5168\u6b6f \u305f \u3051 \u5206 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u8ef8 \u65b9\u5411 \u306b\u9001 \u308a,\u305d \u3057\u3066(3) \u4e0a \u65b9 \u5411 \u306b\u9001 \u3063\u3066 \u7d42 \u4e86\u3059 \u308b.\u88fd \u4f5c \u3055\u308c \u305f \u30d5 \u30a7\u30fc \u30b9\u30ae \u30a2\u306e \u6b6f \u5f62 \u4f8b\n\u3092 \u56f37\u306b \u793a\u3059.\u5168 \u4f53 \u7684 \u306b\u6b6f \u306e \u4e21 \u7aef \u306f \u5927 \u7aef \u76f4 \u5f84 \u3068\u5c0f \u7aef \u76f4\u5f84 \u554f\n\u306b \u3046 \u307e \u304f\u914d \u7f6e \u3055\u308c \u3066\u304a \u308a,\u8fd1 \u4f3c \u5f0f \u306e \u59a5 \u5f53\u4ef6 \u304c \u8a00\u3048 \u308b.\n\u6b21 \u306b\u88fd \u4f5c \u3057\u305f \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u6b6f \u9762 \u306b \u30b9 \u30b9 \u3092\u4ed8 \u3051,\u5e73 \u6b6f \u8eca\n(Z=20)\u3068 \u304b \u307f \u5408 \u3044\u8a66 \u9a13 \u3092 \u884c \u3044 \u30b9 \u30b9\u306e \u5265 \u304c \u308c\u5177 \u5408\u304b \u3089\n\u6b6f \u5f53 \u305f \u308a\u72b6 \u614b \u3092\u89b3 \u5bdf \u3057\u305f.\u56f38\u306b,\u56f37\u3067 \u793a \u3057 \u305f \u30d5\u30a7\u30fc \u30b9\n504 \u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61. No. 4. 1995" + ] + }, + { + "image_filename": "designv8_17_0001487_1071-019-05058-7.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001487_1071-019-05058-7.pdf-Figure1-1.png", + "caption": "Fig. 1 Mechanical models with non-collocated (a) and collocated (b) force sensor configurations. The stiffness k2 of the force sensor is an order of magnitude larger than the stiffness k1 of the actuator. P refers to proportional gain; \u03c4 stands for time delay", + "texts": [ + " 3, the stability analysis of the steady-state desired contact force is presented together with the Hopf bifurcation calculation done by the method of multiple scales extended for nonlinear delay differential equations. The same calculations are presented for the collocated configuration in Sect. 4. The analytical results and conclusions are summarized in Sect. 5. Consider the basic task of force control when a block of mass m is in contact with the rigid environment through a spring of stiffness k1 along a horizontal axis as shown in Fig. 1. The actual contact force ismeasured by means of a serially connected spring of large stiffness k2( k1). In Fig. 1a, the so-called non-collocated configuration is presented where the force sensor is at the contact point to the rigid environment and its signal is fed back to the control force Q of the actuator, while Fig. 1b is the sketch of the collocated configuration with contact force measured at the actuator force. 2.1 Modeling the non-collocated configuration In case of Fig. 1a, the Newtonian equations assume the form mq\u03081 = Q \u2212 k1(q1 \u2212 q2) 0 = k1(q1 \u2212 q2) \u2212 k2q2, (2) where the selected generalized coordinates q1 and q2 are the absolute positions of the block and the end point of the spring that senses the force, respectively. The actuator force Q depends on the force error Fe = Fm \u2212 Fd, (3) which is the difference in the actual measured force Fm = k2q2 (4) and the constant desired force Fd. Consider the simplest possible linear control strategy using a single (dimensionless) proportional gain P for the force error Fe while adding the actual measured force (see [3]): Q = \u2212P(Fm \u2212 Fd) + Fm", + " Substituting all these into the Newtonian equation (2) and eliminating the state variable q2, we obtain the nonlinear delay differential equation (DDE) of retarded type in the dimensionless form of x\u0308(t) + (\u03c9n\u03c4)2x(t) = (\u03c9n\u03c4)2x(t \u2212 1) \u2212(\u03c9n\u03c4)2 tanh (Px(t \u2212 1)) (9) with trivial solution at zero.Note that the dimensionless parameter \u03c9n\u03c4 = 2\u03c0(\u03c4/T ) can also be expressed with the ratio of the reaction time \u03c4 and the time period T of the free oscillation of the uncontrolled system. 2.2 Modeling the collocated configuration When the collocated configuration is considered as shown in Fig. 1b, the Newtonian equations assume the form mq\u03081 = k2q2 \u2212 k1q1 0 = Q \u2212 k2q2, (10) where the generalized coordinates q1 and q2 now stand for the absolute position of the block of massm and the position of the end of the spring of stiffness k2 relative to the position of the block. This choice of coordinates means that the measured force Fm can be expressed in the same way as in (4) and the saturated and delayed actuator force can be expressed as given in (6). The equations of motion (10) with the control force (6) have a trivial solution at q10 = 1 k1 Fd, q20 = 1 k2 Fd" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004400_e_download_7768_6705-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004400_e_download_7768_6705-Figure4-1.png", + "caption": "Fig 4. Torsion angle of the helicopter rotor blade", + "texts": [ + " Thermal strain analogy between piezoelectric strains and thermally induced strains is used to model piezoelectric effects, when piezoelectric coefficients characterizing an actuator are introduced as thermal expansion coefficients determined by the following relationship: , ES ij ij d \u0394 =\u03b1 where dij is the effective piezoelectric constant and \u2206ES is the electrode spacing (Fig 3) taken as \u2206ES = 0.5 mm. Then steady-state thermal analysis is carried out to determine a torsion angle of the rotor blade (Fig 4), static torsion analysis \u2013 to determine the location of the elastic axis and modal analysis \u2013 to determine the first torsion eigenfrequency of the rotor blade. Before formulation of optimisation problem, the parametric study has been carried out with the purpose to decrease the number of design parameters (Fig 5) and by this way to increase the accuracy of obtained optimal results. In this connection the influence of possible design parameters \u2013 spar \u201cmoustaches\u201d thickness and length, spar circular fitting, skin thickness, MFC chordwise length, web thickness and length, web and spar \u201cmoustaches\u201d thickness together and voltage, on the behaviour functions - torsion angle, location of centre of gravity and elastic axis, mass of cross-section, strains and first torsion eigenfrequency (Fig 6\u201310) were considered" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002783_f_version_1671785199-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002783_f_version_1671785199-Figure4-1.png", + "caption": "Figure 4. Torque acting on the spur gear by the extension spring.", + "texts": [ + " \u03b8s + ( kr n ) \u03b8S (6) Biomimetics 2023, 8, 6 5 of 14 Denoting the total moment of inertia ( n(IM + IP) + 1 n (IS + IW) ) as IT , the total damp- ing coefficient (n(DM + DP) + 1 n (DS + DW)) as DT , and the effective total spring constant( kr n ) as KT , the natural frequency of the entire system \u03c9n is expressed as \u221a KT IT , and the damped natural frequency \u03c9d is given as \u03c9n \u221a 1 \u2212 \u03b62 = \u221a KT IT \u00d7 \u221a 1 \u2212 \u03b62. The rotational elastic constant can be derived from the torque generated from the extension spring. Figure 3 shows the motion of extension spring when the spur gear and wing are rotated from (a) to (b). Referring to Figure 4, when d1, d2, r, the rotation angle \u03b8s of the spur gear, and the rotation angle \u03b1 of the extension spring are given, the torque by the extended spring is obtained as: \u03c4es = ke(d2 \u2212 d1)\u00d7 cos (\u03c0 2 \u2212 (\u03b8S + \u03b1) ) \u00d7 r (7) where, ke is the linear elastic constant of the extension spring, d1 is the spring length at zero position without extension, d2 is the spring length when it is extended according to the rotation of the spur gear, and r is the distance between the center of the spur gear, and the point where the spring is fixed on the spur gear", + " Biomimetics\u00a02023,\u00a08,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 5\u00a0 of\u00a0 14\u00a0 \u00a0 Using\u00a0the\u00a0abbreviated\u00a0notation \ud835\udc5b ,\u00a0Equation\u00a0(1)\u00a0of\u00a0the\u00a0total\u00a0flapping\u00a0wing\u00a0sys\u2010 tem\u00a0can\u00a0be\u00a0described\u00a0as:\u00a0 \ud835\udf0f \ud835\udc5b \ud835\udc3c \ud835\udc3c 1 \ud835\udc5b \ud835\udc3c \ud835\udc3c \ud835\udf03 \u00a0 \ud835\udc5b \ud835\udc37 \ud835\udc37 1 \ud835\udc5b \ud835\udc37 \ud835\udc37 \ud835\udf03 \ud835\udc58 \ud835\udc5b \ud835\udf03 \u00a0 (6) Denoting\u00a0the\u00a0total\u00a0moment\u00a0of\u00a0inertia\u00a0 \ud835\udc5b \ud835\udc3c \ud835\udc3c \ud835\udc3c \ud835\udc3c as \ud835\udc3c ,\u00a0the\u00a0total\u00a0damp\u2010 ing\u00a0coefficient\u00a0 \ud835\udc5b \ud835\udc37 \ud835\udc37 \ud835\udc37 \ud835\udc37 as\u00a0 \ud835\udc37 ,\u00a0and\u00a0the\u00a0effective\u00a0total\u00a0spring\u00a0constant\u00a0 \u00a0 as\u00a0 \ud835\udc3e ,\u00a0the\u00a0natural\u00a0frequency\u00a0of\u00a0the\u00a0entire\u00a0system \ud835\udf14 \u00a0 is\u00a0expressed\u00a0as\u00a0 ,\u00a0and\u00a0the\u00a0 damped\u00a0natural\u00a0frequency\u00a0 \ud835\udf14 \u00a0 is\u00a0given\u00a0as \ud835\udf14 1 \ud835\udf01 1 \ud835\udf01 .\u00a0 The\u00a0ro ational\u00a0elastic\u00a0constant\u00a0can\u00a0be\u00a0derived\u00a0 from\u00a0 the\u00a0 torque\u00a0generated\u00a0 from\u00a0 the\u00a0 extension\u00a0spring.\u00a0Figure\u00a03\u00a0shows\u00a0the\u00a0motion\u00a0of\u00a0extension\u00a0spring\u00a0when\u00a0the\u00a0spur\u00a0gear\u00a0and\u00a0 wing\u00a0are\u00a0rotated\u00a0from\u00a0(a)\u00a0to\u00a0(b).\u00a0Referring\u00a0to\u00a0Figure\u00a04,\u00a0when\u00a0 \ud835\udc51 , \ud835\udc51 , \ud835\udc5f,\u00a0the\u00a0rotation\u00a0angle\u00a0 \ud835\udf03 \u00a0 of\u00a0the\u00a0spur\u00a0gear,\u00a0and\u00a0the\u00a0rotation\u00a0angle\u00a0 \ud835\udefc\u00a0 of\u00a0the\u00a0extension\u00a0spring\u00a0are\u00a0given,\u00a0the\u00a0torque\u00a0 by\u00a0the\u00a0extended\u00a0spring\u00a0is\u00a0obtained\u00a0as:\u00a0 \ud835\udf0f \ud835\udc58 \ud835\udc51 \ud835\udc51 cos \ud835\udf0b 2 \ud835\udf03 \ud835\udefc \ud835\udc5f\u00a0 (7) where,\u00a0 \ud835\udc58 \u00a0 is\u00a0the\u00a0linear\u00a0elastic\u00a0constant\u00a0of\u00a0the\u00a0extension\u00a0spring,\u00a0 \ud835\udc51 \u00a0 is\u00a0the\u00a0spring\u00a0length\u00a0at\u00a0 zero\u00a0position\u00a0without\u00a0extension,\u00a0 \ud835\udc51 \u00a0 is\u00a0the\u00a0spring\u00a0length\u00a0when\u00a0it\u00a0is\u00a0extended\u00a0according\u00a0to\u00a0 the\u00a0rotation\u00a0of\u00a0the\u00a0spur\u00a0gear,\u00a0and \ud835\udc5f\u00a0 is\u00a0the\u00a0distance\u00a0between\u00a0the\u00a0center\u00a0of\u00a0the\u00a0spur\u00a0gear,\u00a0 and\u00a0the\u00a0point\u00a0where\u00a0the\u00a0spring\u00a0is\u00a0fixed\u00a0on\u00a0th \u00a0spur\u00a0gear.\u00a0The\u00a0 \ud835\udc58 , \ud835\udc51 ,\u00a0and\u00a0 \ud835\udc5f\u00a0 are\u00a0fixed\u00a0con\u2010 stants,\u00a0and\u00a0when\u00a0 \ud835\udf03 \u00a0 is\u00a0given,\u00a0 \ud835\udc51 \u00a0 and\u00a0 \ud835\udefc\u00a0 are\u00a0determined.\u00a0The\u00a0angle\u00a0of\u00a0the\u00a0spur\u00a0gear\u00a0and\u00a0 the\u00a0rotation\u00a0angl \u00a0of\u00a0the\u00a0wing\u00a0are\u00a0the\u00a0same.\u00a0Thus,\u00a0the\u00a0torque\u00a0in\u00a0Equation\u00a0(7)\u00a0is\u00a0the\u00a0function\u00a0 of\u00a0the\u00a0wing\u00a0rota ion\u00a0angle\u00a0 \ud835\udf03 .\u00a0 The\u00a0torque\u00a0enforced\u00a0by\u00a0the\u00a0extensio \u00a0spring\u00a0to\u00a0th \u00a0spur\u00a0gear\u00a0with\u00a0the\u00a0wing\u00a0rotation\u00a0 angle\u00a0 \ud835\udf03 \u00a0 is\u00a0 shown\u00a0as\u00a0 the\u00a0blue\u00a0 line\u00a0 in\u00a0Figur \u00a05.\u00a0Here\u00a0 the\u00a0 \ud835\udc58 \u00a0 is\u00a00.796\u00a0N/mm,\u00a0 \u00a0 \ud835\udc51 \u00a0 is\u00a0 13.4 mm\u00a0 and\u00a0the\u00a0 \ud835\udc5f is\u00a0 5 mm.\u00a0 \u00a0 Figure\u00a04.\u00a0Torque\u00a0acting\u00a0on\u00a0the\u00a0spur\u00a0gear\u00a0by\u00a0the\u00a0extension\u00a0spring.\u00a0 The\u00a0slope\u00a0of\u00a0the\u00a0graph\u00a0in\u00a0Figure\u00a05\u00a0is\u00a0the\u00a0rotational\u00a0elastic\u00a0constant\u00a0 \ud835\udc58 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"\u00a0The\u00a0moment\u00a0of\u00a0inertia\u00a0of\u00a0all\u00a0 of\u00a0the\u00a0rotating\u00a0components,\u00a0which\u00a0is\u00a0computed\u00a0by\u00a0CATIA\u00a0simulation\u00a0program,\u00a0is\u00a07.53\u00a0\u00d7\u00a0 10\u22128\u00a0g\u2219m2.\u00a0Therefore,\u00a0the\u00a0natural\u00a0frequency\u00a0of\u00a0the\u00a0whole\u00a0flapping\u00a0system\u00a0is\u00a0around\u00a022\u00a0Hz,\u00a0 as\u00a0calculated\u00a0from\u00a0Equation\u00a0(6)\u00a0with\u00a0the\u00a0given\u00a0parameters\u00a0 \ud835\udc58 and\u00a0 \ud835\udc5b.\u00a0 3.\u00a0Prototype\u00a0Flapping\u00a0Winged\u00a0Robot\u00a0 Biomimetics 2023, 8, 6 6 of 14 The torque enforced by the extension spring to the spur gear with the wing rotation angle \u03b8W is shown as the blue line in Figure 5. Here the ke is 0.796 N/mm, the d1 is 13.4 mm and the r is 5 mm. Biomimetics\u00a02023,\u00a08,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 6\u00a0 of\u00a0 14\u00a0 \u00a0 \u00a0 \u00a0 Figure\u00a04.\u00a0Torque\u00a0acting\u00a0on\u00a0the\u00a0spur\u00a0gear\u00a0by\u00a0the\u00a0extension\u00a0spring.\u00a0 The\u00a0slope\u00a0of\u00a0the\u00a0graph\u00a0in\u00a0Figure\u00a05\u00a0is\u00a0the\u00a0rotational\u00a0elastic\u00a0constant\u00a0 \ud835\udc58 .\u00a0When\u00a0the\u00a0wing\u00a0 rotation\u00a0angle\u00a0is\u00a0small,\u00a0the\u00a0torque\u00a0generated\u00a0by\u00a0the\u00a0extension\u00a0spring\u00a0to\u00a0the\u00a0spur\u00a0gear\u00a0is\u00a0 minor.\u00a0 \u00a0 Figure\u00a05.\u00a0Spring\u00a0torque\u00a0with\u00a0wing\u00a0rotation\u00a0angle.\u00a0 By\u00a0stretching\u00a0the\u00a0extension\u00a0spring\u00a0at\u00a0the\u00a0zero\u00a0position\u00a0by\u00a0moving\u00a0away\u00a0the\u00a0fixing\u00a0 point\u00a0to\u00a0the\u00a0body\u00a0frame,\u00a0tension\u00a0can\u00a0be\u00a0provided,\u00a0even\u00a0when\u00a0the\u00a0wing\u00a0is\u00a0at\u00a0zero\u00a0position.\u00a0 In\u00a0this\u00a0case,\u00a0the\u00a0spring\u00a0torque\u00a0at\u00a0low\u00a0wing\u00a0angle\u00a0range\u00a0is\u00a0increased,\u00a0compared\u00a0with\u00a0the\u00a0 toque\u00a0increase\u00a0in\u00a0higher\u00a0angle\u00a0range,\u00a0and\u00a0thus\u00a0the\u00a0rotational\u00a0elastic\u00a0constant\u00a0is\u00a0linearized" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure18-1.png", + "caption": "Figure 18. Bar chart of calculated ratio of stator winding losses to slot area for Motor #1 and Motor #2; rotational torque is treated as input quantity and is identical for both motors.", + "texts": [ + " Thus, while lengths of both motors are identical, the area of heat removal is greater in Motor #2. Bar charts showing the ratio of stator total losses to area of structure, where stator is positioned, are presented in Figure 17. If we compare losses shown in Figure 14 charts, with charts showing the ratio of these losses to the heat removal area (Figure 17), then we see that Motor #2 is much more promising; this is especially noticeable in the case of maximum speed at load torque equal to Tm = 450 Nm and Tm = 350 Nm. A similar comparison was performed for winding losses in Figure 18. Total slot area is much greater in Motor #2 (SQ = 3389.4 cm2) than in Motor #1 (SQ = 235.6 cm2). Ratio of power losses generated in permanent magnets to the rotor surface area where magnets are mounted is shown in Figure 19. The ratio of PM loss to heat removal area again underlines the advantages displayed by Motor #2, with respect to Motor #1. In order to compare properties of these two motors, and taking into account the fact that cooling systems of the two motors differ since dimensions of structural elements are not identical, calculations were conducted for the S1 duty cycle, assuming that steadystate winding temperature cannot exceed TCu = 150 \u25e6C, while steady-state temperature of permanent magnets cannot exceed Tmag" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002223_u.158083066.60121082-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002223_u.158083066.60121082-Figure4-1.png", + "caption": "Figure 4 Geometrical variations in the ground plane geometry for isolation enhancement", + "texts": [ + " D = log (N) log (1/s) (12) As shown in Figure 1 (b), the lower FR-4 substrate layer consists of a reduced ground with DGS. A funnelshaped decoupling structure extends vertically (at an angle 90@) from the reduced ground plane. It obstructs the steady flow of current between the two radiating patches and hence minimizes the effect of cross-coupling. To further improve the isolation performance, two rectangular (each with dimensions 5 \u00d7 2.5) and L-shaped (11.6 \u00d7 0.5) slots, each with a length of \u03bbg/2 (where \u03bbg is the guided wavelength), is etched from the upper edge of the reduced ground. Figure 2 and Figure 4 show the geometrical variations in the patch and ground plane configuration of the proposed fractal array respectively for designing the final optimized geometry. The corresponding improvement in impedance bandwidth (S11/S22) and isolation (S21/S12) performance for variations in patch and ground plane geometries is depicted in Figure 3 and Figure 5 respectively. P os te d on A u th or ea 4 F eb 20 20 \u2014 C C B Y 4. 0 \u2014 h tt p s: // d oi .o rg /1 0. 22 54 1/ au .1 58 08 3 0 66 .6 01 21 08 2 \u2014 T h is a p re p ri n t an d h as n ot b ee n p ee r re v ie w ed " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003456_8948470_09084082.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003456_8948470_09084082.pdf-Figure7-1.png", + "caption": "FIGURE 7. Layout of the designed 320 GHz 1 \u00d7 2 OSAR on-chip antenna array.", + "texts": [ + " The simulated \u221210dB impedance bandwidth of microstrip antenna, OSAR antenna are 10 GHz (318-328 GHz) and 13 GHz (317-330 GHz), respectively. The simulated gain are 0.7 dBi, 1.4 dBi and efficiency is 35.4 %, 41 % at 320 GHz, respectively. The OSAR antenna element achieves 0.8 dB higher gain at 320 GHz, which are much higher than the traditional on-chip patch antenna. III. A 320 GHz 1 \u00d7 2 OSAR ON-CHIP ANTENNA ARRAY DESIGN Since the high gain performance is required to ensure long distance communication, 1\u00d7 2 OSAR on-chip antenna array is designed to improve the gain, as shown in Fig.7. The 1 \u00d7 2 OSAR antenna array consists of two OSAR antenna VOLUME 8, 2020 84285 elements, ground, power divider, Ground-Signal-Ground (G-S-G) pad. The two OSAR antenna elements are separated with the distance of 0.5 mm (0.53\u03bb0). The input impedance of OSAR antenna element is 100 to design without 1/4\u03bbg impedance transformer. The feeding network is placed on the M2 layer, which connect by the feeding probe fromM1 layer to M2. The G-S-G pad is design to 50 for measurement. The length (w6) and the width (w7, w8) of the power divider are 480 \u00b5m, 20 \u00b5m and 30 \u00b5m, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004550_cle_download_621_509-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004550_cle_download_621_509-Figure3-1.png", + "caption": "Fig. 3. 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"designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure5-1.png", + "caption": "Figure 5. Flux density plot of 2 kW, 200 000 rpm reference motor.", + "texts": [ + " Motors are designed with an assumed stator teeth flux density of 1.8 T and stator core flux density of 1.5 T. To compare and analyse performance, initial designs are used as benchmarks. Design data is used to create finite element models, and meshing is done. The performance results obtained for FEA of the initial models designed using M19 material for core are enlisted in Table 2. Torque profiles and flux density plots are plotted as per the recorded results. Figure 4 represent the torque profile of 2 kW, 200 000 rpm IPMSM obtained from FEA. Figure 5 shows the flux density plot of 2 kW, 200 000 rpm IPMSM. This reference 2 kW, 200 000 rpm IPMSM has average torque of 0.0956 N.m. The actual flux density is close to the assumed flux density in various magnetic sections of the motor. The closeness between actual flux density and assumed flux density validates the sizing of the motor. The torque profile and flux density plot of 5 kW, 24 000 rpm IPMSM using M19 material is in Figure 6 and Figure 7, respectively. This 5 kW, 24 000 rpm IPMSM has average torque of 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004385_aper_ETC2017-356.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004385_aper_ETC2017-356.pdf-Figure8-1.png", + "caption": "Figure 8: CORN concept \u2013 90o version (1/4 of the overall nozzle configuration is presented due to symmetry conditions)", + "texts": [], + "surrounding_texts": [ + "Trying to further optimize the recuperation installation, two alternative designs were conceptualized. For the design and investigations a customizable numerical tool modelling the recuperation system operational heat transfer and pressure loss characteristics was developed. This numerical tool was based on an advanced porosity model approach in which the HEXs macroscopic behaviour was included through the integration of predefined heat transfer and pressure loss correlations which were previously calibrated through detailed 2D and 3D CFD computations in Fluent CFD software (with the use of the Shear Stress Transport (SST) turbulence model of Menter (1994) and experimental measurements. These correlations were incorporated in the CFD computations with the addition of appropriate source terms in the momentum and energy equations, as presented in detail in Fig. 5. More specifically, Fig.5a presents the system of equations (momentum and energy equations) for the hot-gas outer flow. In these equations the effect of the pressure losses on the outer hot-gas flow is included by the addition of source terms in the x, y and z directions. These correlations correspond to modified formulation of the Darcy-Forchheimer equation and take into account the viscous and inertial effects on the hot-gas pressure losses through the coefficients 10 ,aa and 210 ,, bbb . These coefficients were derived by experimental measurements and CFD computations through a trend line curve fitting process, for various heat exchanger conditions. The energy source term is responsible for the linking and the achieved heat exchange between the hot-gas flow and the cold-air. This is achieved by the use of the overall heat transfer coefficient, U. This coefficient is calculated, as shown in Fig.5b, by the independent calculation of the inner (cold-air) and outer (hot-gas) heat transfer coefficients (by neglecting the effect of conduction in the thin tube walls) with the help of specifically derived Nusselt number correlations. These correlations were also derived with the combined use of experimental measurements and CFD computations. Regarding the inner (cold-air) flow, this was modeled by the inclusion of an additional set of equations (Fig.5c) corresponding to the transport of the total specific enthalpy and the inner flow total pressure. The calculation of the inner flow pressure losses was performed with the use of a friction loss coefficient, f . In addition, the numerical tool included the effect of the most important and deterministic HEX design decisions such as: dimensions and positioning of the tubes collectors, tubes geometrical characteristics (diameter, length, profile) and arrangement, modifications in the inner-outer flow currents relative orientation and HEX material selection among others. Additional details about the customizable numerical tool can be found in Yakinthos et al. (2015). The first of the two alternative concepts was named as CORN (COnical Recuperative Nozzle). The CORN concept is following a conical design with a 6/5/6 elliptic tubes arrangement, presented in Fig. 6. The elliptic tubes are bent as also shown in Fig. 6, in order to be aligned to the flow direction through the HEX and minimize inner pressure losses since the hot-gas mass flow encounters a much larger recuperator inlet region, thus entering inside the recuperator with significantly reduced flow velocity resulting in reduced outer pressure losses. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. The upstream region of the installation right before the HEX was redesigned in relation to the NEWAC nozzle configuration (including various modifications in the guiding walls and aerodynamic cone) in order to eliminate the size of the recirculation region which was developed there in the previous recuperation installations (reference, NEWAC) as much as possible. Two CORN versions, presented in Figs. 7 and 8, were investigated where the collectors of the cold air are placed circumferentially either every 45o or every 90o leading to a total of 8 or 4 collectors, respectively for the 360o of the Nozzle. The second of the two alternative concepts was named as STARTREC (STraight AnnulaR Thermal RECuperator). The STARTREC concept is following a straight annular design, presented in Fig. 9. Two STARTREC versions were investigated consisting of two and three banks respectively, which are presented in Figs. 10 and 11. In these versions, the gap spacing between the elliptic tubes was altered in relation to the initial MTU design, in order to reduce the pressure losses. All banks were having a 4/3/4 elliptic tubes arrangement with the gap spacing being coarser at the front banks and sparser at the back banks which, due to the gradual cooling of the hot-gas, operated with higher density values and lower flow velocities. In addition, the upstream region of the installation right before the HEX was redesigned (including various modifications in the guiding walls and aerodynamic cone) in order to reduce the size of the recirculation region which was developed there as much as possible. The distribution of the inner flow (cold air) through the collectors is presented in Figs. 10 and 11. The orientation of the elliptic tubes in relation to the main axis of the installation is shown in Fig. 9 (right), where it can be seen that the elliptic tubes are aligned to the main flow direction in the installation in order to ease the flow guidance through the HEX. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. Additionally, the elliptic tubes are aligned to the main flow direction in the installation in order to ease the flow guidance through the HEX. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. At the next step, 3D CFD models were created for all CORN and STARTREC versions (presented in Figs. 12 and 13) and CFD computations were carried out for Average Cruise conditions (details about the conditions can be found in Schonenborn et al. (2004)) with the use of the SST turbulence model of Menter (1994) and Fluent CFD software. Due to its complexity and the extremely large number of elliptic tubes, the modelling of the precise HEXs geometry could not be afforded since the required size of the computational grid capable of providing grid independent results for a single HEX could easily surpass one hundred millions computational grid points. Figure13: CFD grid for STARTREC two banks (left) and STARTREC three banks (right) As a result, the HEXs were modelled by following a porous media approach, with the use of the customizable numerical tool. In this approach CFD models of approximately two million computational nodes were used and could provide grid independent results. At the inlet of the computational domain the mass flow, flow direction, total temperature and turbulence intensity were defined. At the outlet of the computational domain, average static pressure was imposed. The total pressure losses of the aero engine hot-gas exhaust nozzle installation, together with the inner total pressure losses and the recuperator thermal efficiency (as calculated form the CFD results) were then incorporated as input values in the thermodynamic cycle analysis software GasTurb 11, Kurzke (2011), and the thermodynamic cycle for each CORN and STARTREC version (two and three banks versions) were calculated. An indicative view of the IRA engine thermodynamic cycle is presented in Fig. 14. Comparative performance of the various recuperation concepts which were examined are presented in Table 1 in relation to a conventional non-intercooled and nonrecuperated aero-engine of similar technology level with the IRA engine for the specific fuel consumption, and in relation to the NEWAC nozzle configuration for the recuperator major characteristics (pressure losses, effectiveness and weight) in order to proceed to a state-of-the-art comparison and present a quantification of the recuperator achieved improvement. As it can be seen, for the most beneficial concept (CORN 45o) the strongest effect is due to the pressure losses significant reduction which compensates for a small reduction in recuperator effectiveness. This pressure loss reduction is particularly important for the CORN 45o and is the result of two parameters. More specifically, regarding the outer pressure losses, the conical shape of the CORN 45o hot-gas inlet available area results in a drastic reduction of the hot-gas mean flow velocity. This is the same reason due to which CORN 90o configuration presents also reduced outer pressure losses as shown in Table 1. However, regarding the inner pressure losses the most critical parameter is the use of sufficient number of collectors in order to reduce the cold-air flow velocity inside the feed tubes and at the same reduce the tubes length. Thus, the use of 8 collectors provided a very good combination of tubes inner flow velocity and tubes length, resulting in significantly reduced inner pressure losses for the CORN 45o configuration." + ] + }, + { + "image_filename": "designv8_17_0001345_f_version_1621584150-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001345_f_version_1621584150-Figure5-1.png", + "caption": "Figure 5. Mesh near the propeller.", + "texts": [ + " The rotation domain\u2019s speed is ns, whereas the static domain is stationary. The interface boundary condition was used as the exchange data between the static and the rotation domains, the velocity inlet and pressure outlet were adopted as the boundary conditions of the static domain, and the surface of the propeller was set as the wall. The rotational domain was composed of 5.55 million meshes, the blade surface was a triangular mesh, and the boundary layer around the surface was an hexagonal mesh, which is shown in Figure 5. A tetrahedral mesh was used to fill the space between the propeller surface and the interface. The static domain is shown in Figure 6, which composed of 1.97 million hexagonal meshes, which were generated based on a three-dimensional O-Block. FLUENT with a pressure-based solver was used to perform the CFD analyses. The control equation was discretized using the finite volume method, and the RANS equation and the k\u2013\u03c9 SST Low\u2013Re corrections turbulence model were adopted. The multiple reference frame (MRF) model was used to calculate the rotational motion of the propeller" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002806__download_11595_7978-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002806__download_11595_7978-Figure2-1.png", + "caption": "Fig. 2 Typical failure of O-rings. (a) Excessive wear, (b) Extrusion, (c) Excessive initial compression [6].", + "texts": [ + " (a) (b) (c) 149Viscoelastic Material Model for O-rings 2018 62 2 Many researchers have investigated the behavior and failure of O-rings. Karaszkiewicz studied and calculated analytically the deformed geometry, the arising contact pressure and the contact force of O-rings [2]. Zhang and Zhang carried out finite element calculations to study the sealing performance of both static and dynamic O-rings [3]. One typical failure of O-rings is caused by the too rough surfaces of the contacting elements, which leads to excessive wear as shown in Fig. 2 (a). Gawli\u0144ski investigated the influence of friction and wear of static and dynamic elastomer seals [4]. Overpressure or too large gap cause extrusion of the material. Unequivocal sign of this failure mode is the sharp edges appearing on the O-ring as shown in Fig. 2 (b). Eshel studied the extrusion of O-rings and proposed a theoretical model to estimate the failure in this mode [5]. In Fig. 2 (c) circumferential cracks can be seen on the O-ring seal caused by excessive initial compression. There are several other factors that can lead to the deterioration of the O-ring [1, 6, 7]. Excessive remaining compression set, which is probably the most common failure type of O-rings, is caused by too high temperatures, low heat resistance of the material, poor compression-set properties of the elastomer, swelling of O-ring material, excessive initial compression or operating pressure. Chemical failure caused by the incompatibility of the contacting materials which causes change of the rubber\u2032s physical properties" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002483_ees-2020-20-2-91.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002483_ees-2020-20-2-91.pdf-Figure2-1.png", + "caption": "Fig. 2 compares the frequency response of the proposed filter", + "texts": [ + " In the proposed structure, the linewidth of the ring resonator is unevenly formed, and the line impedances at 45\u00b0 and 135\u00b0 are automatically changed with respect to the input and output stages, thereby realizing the dualmode characteristic. The feed is implemented by a circular arc, and the linewidth of the feed is set to w. The gap between the feed line and the resonator is set to g, and the angle is set to . In this study, the parameters of the feed structure are optimized using an HFSS simulator. Fig. 1. The proposed dual-band dual-mode filter. Fig. 2 Simulated frequency responses with different dual-mode filters. in structures where only the inductor (\u201cInductor only\u201d) or the capacitor (\u201cCapacitor only\u201d) is applied. As shown, the resonant frequency of the filter is formed at 1.55 GHz in the case of the inductor-only filter. As the capacitor is added, the resonant frequency of the filter is lowered to the 1.3 GHz band which is the first resonant frequency of the proposed filter. The first resonant frequency can therefore be adjusted by changing the capacitor or inductor value" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001569__downloads_6969z181x-Figure3.25-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001569__downloads_6969z181x-Figure3.25-1.png", + "caption": "Figure 3.25: Sample Layout of fabricated PMOS devices", + "texts": [], + "surrounding_texts": [ + "Variants of both NMOS and PMOS transistors were laidout and fabricated as shown in Figures 3.23, 3.24, and 3.25. As can be seen in Figures 3.23 and 3.24, there are three variants of MOS devices laid out, presented in Table 3.1. The transistors are close to minimum size. It would have been beneficial if the transistors were much larger in order to increase their gate oxide volume for better capture of incident photons but the initial thought on the design was to keep the dimensions to a minimum in order to draw the least amount of current at lower bias voltages. Radiation exposure test has been performed on these devices and the results will be explained herein. 82 Another approach to a sub-threshold MOSFET radiation sensor design has been proposed. Referring back to Equation 3.8, another important factor in sub-threshold current of the MOSFET is the gate voltage which also has an exponential effect. A design proposed utilizes on-chip series chain of diodes which would develop a voltage under radiation across them. Once the chain of diodes is connected to the gate of the 83 MOSFET, it biases it in sub- or near-threshold region depending on the number of diodes in series. A small drain/source bias at the MOS device results in current in the channel which could be integrated to determine the amount of radiation dose. The same developed voltage under radiation across the diodes can be applied to a chain of inverters in a current starved ring oscillator configuration. A counter then can be employed to measure the frequency. Another approach is to embed a MOS transistor biased with the diodes in a current mirror to set the current, hence the frequency of oscillation in the ring oscillator. An example of a voltage-controlled ring oscillator is shown in Figure 3.26. Figure 3.27 shows the irradiation results of a sample gate-connected NMOS device. The same irradiation conditions were applied (Blood irradiator machine, same ambient temperature, pressure, and duration) to the devices mentioned in Table 3.1. Preliminary experiments showed that low gate biases in the range of sub-threshold values between \u2248 0.3 V to 0.5 V would not result in any change within the 300 seconds of irradiation. Therefore, it was decided to increase the gate voltage to 1.0 V. This already goes against the sub-threshold idea, but the experiments are nonetheless valuable. 84 In the first 300 seconds of Figure 3.27, irradiation is happening and from that time onwards the rest period is presented. The rest period is there to monitor the behavior of the device immediately after irradiation to confirm whether there is any significant changes due to radiation exposure. The device was never physically moved between the two time period and the plot shows one continuous operation. As can been seen from the figure, there is insignificant change in current during each of the three irradiation sessions in this device. This change could even be attributed to temperature changes within the device due to current draw or the X-ray machine heating up. Overall, the change is less than 1%. Also, at a V DS = 1.0V, the power consumption is already more than the FG-PMOS case which consumed \u2248 30 \u00b5W at its highest current draw which shows this solution might not be favored due to lack of radiation response and increased power consumption. Unfortunately for the PMOS devices, the same lack of sensitivity to ionizing radiation 85 from the blood irradiator machine was observed. Hence their measurement plots are not presented." + ] + }, + { + "image_filename": "designv8_17_0004895_ejjia_3_6_3_405__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004895_ejjia_3_6_3_405__pdf-Figure3-1.png", + "caption": "Fig. 3. FE meshes", + "texts": [ + " However, the skin depth depends on not only the order of the time harmonics but also the permeability that varies with flux density (9). From these viewpoints, we have developed a combination of the 2-D and 1-D FEMs (9) (11)\u2013(14). In this method, the 1- D FEM along the thickness of the electrical steel sheet is employed for the post calculation of the main 2-D FEM, as shown in Fig. 2. We have already confirmed that the proposed method gives acceptable results in various kinds of rotating machines (9) (13) (14). Figure 3 shows the FE meshes for this analysis. Table 3 lists the discretization data. First, the electromagnetic field in the IM is analyzed by the multi-sliced 2-D FEM that considers the rotor skew. The conductivity of the rotor bar is modified by the coefficient, 406 IEEJ Journal IA, Vol.3, No.6, 2014 which is determined by a partial (one rotor slot pitch) threedimensional (3-D) FEM in advance (17) in order to consider the voltage drop of end rings. The primary voltage equation is coupled with FEM. In this case, the input of this analysis is the theoretical voltage waveform of the PWM inverter shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000222_O201606776010775.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000222_O201606776010775.pdf-Figure4-1.png", + "caption": "Fig. 4. Two fabricated dipole antennas with the conventional balun (left) and broadband balun (right). The broadband balun with lumped elements is much smaller", + "texts": [ + "9 \u2126 and 53.3 \u2126, respectively. Fig. 3 shows the theoretical phase propagation of each transmission line for a broadband 180\u00b0 phase differentiation between the outputs in Fig. 2. As can be seen in Fig. 3, the bandwidth corresponding to the 180\u00b0 phase difference between outputs is very broad. We fabricated two dipole antennas, on FR4 boards with a 1.6 mm thickness and a relative permittivity of 4.4: one with the proposed compact broadband balun, and a second one with the conventional balun, as shown in Fig. 4. To fabricate the compact and broadband balun, we used Murata Manufacturing Co.\u2019s chip inductors and Walsin Technology Co.\u2019s chip resistors and capacitors. Their values can be seen in Fig. 2. http://www.jeet.or.kr \u2502 1779 Before we combined the baluns with the dipole-type antennas, we separately tested the performance of each balun. The target frequency of the baluns is approximately 2 GHz. The circuit size of the conventional balun using only a microstrip line is 52.5 mm \u00d7 35.8 mm, whereas the proposed broadband balun has a circuit size of only 9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000407_d.aspx_paperID_27293-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000407_d.aspx_paperID_27293-Figure2-1.png", + "caption": "Figure 2. Variation of minority carrier concentration in an nMOS transistor in weak inversion.", + "texts": [ + " It is found that the proposed techniques give improved performance in terms of reduced subthreshold leakage power dissipation in standby mode as compared with the other techniques available in the literature [8-14]. Subthreshold or weak inversion conduction current is the current flow between source and drain region in a MOS transistor, even when gate voltage, VGS is below the threshold voltage, VTH of the MOS transistor. It is due to the minority carrier drift through the channel from the drain to the source region in weak inversion region. Figure 1 shows the flow of subthreshold leakage current in an nMOS transistor, when VGS is less than VTH of the transistor. Figure 2 [15] shows the variation of minority carrier concentration along the length of the channel for an n-channel MOSFET biased in the weak inversion region. This figure shows that the concentration of minority carriers in weak inversion region is small, but not zero. Subthreshold leakage power dominates the other leakage power components because of the necessity to use low threshold voltage transistors to maintain the desired performance of the device. This leakage power should be minimized through new and improved circuit design techniques" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure5-1.png", + "caption": "Fig. 5, Geometry and boundary conditions of the case studies considered", + "texts": [ + " If the length of the virtual part is represented by \u201cLVP\u201d, and the left end of the part is clamped, the important stiffnesses are given by the following expressions: 16th LACCEI International Multi-Conference for Engineering, Education, and Technology: \u201cInnovation in Education and Inclusion\u201d, 19-21 July 2018, Lima, Peru. The spring constants can be translational and/or rotational in nature and up to six such constants can be inputted in the appropriate dialogue box which is provided in Fig. 4. Note that one can also specify such values using experimental data if available. V. THE CASE STUDIES UNDER CONSIDERATION In the present paper, the geometry under the consideration is very simple so that the salient parts of the discussion are not lost to insignificant details. These geometries are shown in Fig. 5. For the case of axial and bending modes, the cross section is square, whereas for the torsional study, the cross section is circular. The material in all cases is assumed to be linear and elastic with the Young\u2019s modulus E = 200 GPa, and Poisson\u2019s ratio \u03c5 = 0.266. The material density is taken to be \u03c1 = 7860 kg/m3. The details of the dimensions of the part studied are presented next. In reference to the geometries shown in Fig. 5, the actual total length of the bar is \ud835\udc3f = 150 \ud835\udc5a\ud835\udc5a . This total length is consisting of two parts. \ud835\udc3f\ud835\udc40\ud835\udc43 = 100 \ud835\udc5a\ud835\udc5a and \ud835\udc3f\ud835\udc49\ud835\udc43 = 50 \ud835\udc5a\ud835\udc5a . The subscripts \u201cMP\u201d and \u201cVP\u201d refer to the \u201cModeled Part\u201d and \u201cVirtual Part\u201d respectively. Looking at Fig. 5, the \u201cModeled Part\u201d is the solid grey color and the \u201cVirtual Part\u201d is the transparent grey color. VI. AXIAL MODES OF A CLAMPED BAR The bar under consideration is that of Fig.6, whose left end is fixed, and the right end is free. The axial vibration in the Zdirection are of primary interest. Two cases are considered in the analysis. In the first instance, the virtual part is \u201cRigid\u201d, followed by \u201cRigid Spring\u201d virtual part. Case (a) Rigid Virtual Part, Axial Vibration: The location of the \u201cHandler\u201d point has no effect on the analysis, however, for the sake of uniformity (with the case of \u201cRigid Spring\u201d analysis) it is placed at the centroid of the virtual part", + " The above theoretical frequencies are based on stress wave propagation ie, solving the one-dimensional partial differential equation. Furthermore, length of the bar is \ud835\udc3f = \ud835\udc3f\ud835\udc40\ud835\udc43 + \ud835\udc3f\ud835\udc49\ud835\udc43 = 150 \ud835\udc5a\ud835\udc5a. As the approach in case(a), a single degree of freedom system can be developed which still takes into account the stiffness of the ignore portion of the model. In this situation, the two springs associated with the \u201cModelled Part\u201d and the \u201cVirtual Part\u201d are placed in series with an equivalent stiffness. VII. BENDING MODES OF A CLAMPED BAR The bar under consideration is that of Fig.5, whose left end is fixed, and the right end is free. The bending vibration in the X-direction is of primary interest. Two cases are considered in the analysis. In the first instance, the virtual part is \u201cRigid\u201d followed by \u201cRigid Spring\u201d virtual part. Case (c) Rigid Virtual Part, Bending Vibration: This is precisely what is shown in Fig. 11. Note that since the theoretical solution to be used corresponds to transverse vibration (ie in X-direction), the rotary inertia of the virtual part needs to be ignored" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004557_9312710_09416651.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004557_9312710_09416651.pdf-Figure5-1.png", + "caption": "FIGURE 5. Flux density distribution of basic model.", + "texts": [ + " Which significantly decreased the unwanted losses. Furthermore, less winding reactance also improves the power factor of the machine. Flux focusing effect significantly decreased leakage flux, consequently, the power profile of DSAFST-PMVM is highly enhanced. 3D FEA simulation results of the DSAFST-PMVM are shown in Fig. 12. Stator and rotor are made from non-oriented silicon steel (50JNE350), which has good performance at high and medium-range frequencies. Magnetic flux density distributions without load (by PMs) are shown in Fig. 5. In this machine stator and rotor is of 1.75 T out of material saturation which is up to the mark. Flux density distribution clearly illustrates that it has 2 winding poles. Via flux focusing effect, spoke arranged PM provides a greater flux density nevertheless along with gigantic harmonics in one airgap. Fig. 14 defines the average radius in one airgap which noticeably displays the peak value of 1.5 T, which proves the presence of flux focusing effect. Fig. 6 shows fast Fourier transform (FFT) results for each harmonic component of the airgap flux density, where the magnet pole pairs number Zr = 17 is the fundamental harmonic order, with one rotor pole pair number (17+1), the 35th is the working harmonic" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004975_load_0_0_49825_53866-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004975_load_0_0_49825_53866-Figure5-1.png", + "caption": "Figure 5: Magnetic flux distribution for the [0 deg] (a) SRM2 and (b) D-SRM; and [15 deg] (c) SRM2 and (d) D-SRM", + "texts": [ + " It is likely that the magnetic flux-linkage (a parameter critical to determine the Co-Energy W\u2019) is being computed (by FEMM) via following the flux lines until they close a loop, following by integrating along that path [as explained in Guilera (2018)]. This is done for each circuit (\u201dR\u201d being one already mentioned, and another called \u201dB\u201d), resulting in the values exported from the software. The total flux-linkage \u03a8 of the motor is the sum of those computed for each circuit (i.e., \u201dR\u201d plus \u201dB\u201d). The Magnetic Field Intensity B distribution within stator and rotor for both motors are shown as color plots in Figure 5. The predicted magnetic loops (in Figure 5) are clearly seen all around the rotor-stator assembly. High regions of flux are observed around the coils, with the flux direction alternating as expected between each of the six rotor segments. Comparing the aligned cases of the SRM2 (Figure 5a) and the Dual-sided SyncRM (Figure 5b) shows that the flux density is maintained high at the stator pole and inner rotor pole in both cases, but drops visibly (radially immediately after the stator pole) because of the introduction of the new (outer) gap. This drop is to be expect since air has a much lower magnetic permeability than steel. Therefore, qualitatively the extra gap is expected to have a noticeable impact on the induction for the aligned case. However, comparing the flux intensity for the unaligned cases between the SRM2 (Figure 5c) and the Dual-sided SyncRM (Figure 5d) shows that first is much higher. This occurs because for the Dual-sided SyncRM the source of magnetism (i.e., the stator pole) is now much more isolated from the rest of the magnetic material, resulting in a substantial reduction in induced magnetic flux on all of the steel material (both rotor and stator). That is, the magnetization effect from the coils is much more isolated, and thus weak. Qualitatively, this isolation of the stator poles is expected to have a substantial impact on the overall induction for the unaligned case", + " The factor R removes the overlap between subsequent rotational unaligned-aligned segments (where the electrical input switches sequentially between the 3 phases), being defined as a factor dependent on the segment angle \u03b2s, the number of stator poles Ns and the number of rotor poles Ns, resulting in R = 1 + 1 \u03b2s [ \u03b2s \u2212 (360 Nr \u2212 360 Ns )] = 1 + 1 10.5 [ 10.5 \u2212 (360 12 \u2212 360 18 )] = 1.0476 (2) The magnetic co-energy W \u2032 is computed from the mapping of flux-linkage response (as the rotor transits from unaligned to aligned to the stator) for varying electrical current. In fact, the co-energy is the area in between the response lines from the completely unaligned to completely aligned cases. The previous qualitative magnetic flux density change with stator-rotor alignment in Figure 5 (for both motors) are now seen quantitatively in Figure 6 (for a wider range of rotor angles and currents). Figure 6a shows the flux-linkage \u03a8 response (a parameter directly proportional to the flux density \u03d5 at the stator pole) for varying rotor mechanical angle for the SRM2, and Figure 6b for the Dual-sided SyncRM). Both cases present a similar response, in that a maximum is observed when aligned (i.e., 0 deg) that gradually reduces towards unalignment (i.e., towards 15 deg), where current plays in general an amplification effect of the response" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000002_jmoea-18-02-0227.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000002_jmoea-18-02-0227.pdf-Figure5-1.png", + "caption": "Fig. 5. The geometry of a rectangular microstrip patch antenna. (a) 3D illustration and (b) cross-sectional view.", + "texts": [ + "1590/2179-10742019v18i21554 Brazilian Microwave and Optoelectronics Society-SBMO received 24 Nov 2018; for review 29 Nov 2018; accepted 11 Apr 2019 Brazilian Society of Electromagnetism-SBMag \u00a9 2019 SBMO/SBMag ISSN 2179-1074 232 III. RECTANGULAR MICROSTRIP ANTENNA DESIGN, FABRICATION AND RESULTS Typically, a rectangular microstrip antenna is composed of a conducting patch of width W and length L, printed on a dielectric substrate, of height h, relative permittivity r, and loss tangent tan, which is mounted on a ground plane as illustrated in Fig. 5. In this work, the inset-feed technique is used to improve the impedance matching between the microstrip line and the antenna input impedance. The inset-feed physical dimensions are length y0, slot width x0, and strip width W0, which is the same of the feeding microstrip line, as shown in Fig. 5. The overall feeding length of the microstrip line is L0. The analysis of the rectangular microstrip antenna is performed using the approximate expressions given in (1) to (4) [1], [11]. \ud835\udc4a = \ud835\udc50 2\ud835\udc53\ud835\udc5f \u221a 2 \ud835\udf00\ud835\udc5f + 1 (1) \ud835\udf00\ud835\udc5f\ud835\udc52\ud835\udc53\ud835\udc53 = \ud835\udf00\ud835\udc5f + 1 2 + \ud835\udf00\ud835\udc5f \u2212 1 2 [1 + 12 \u210e \ud835\udc4a ] \u22121/2 (2) \u2206\ud835\udc3f \u210e = 0.412 (\ud835\udf00\ud835\udc5f\ud835\udc52\ud835\udc53\ud835\udc53 + 0.300) ( \ud835\udc4a \u210e + 0.264) (\ud835\udf00\ud835\udc5f\ud835\udc52\ud835\udc53\ud835\udc53 + 0.258) ( \ud835\udc4a \u210e + 0.813) (3) \ud835\udc3f = \ud835\udc50 2\ud835\udc53\ud835\udc5f\u221a\ud835\udf00\ud835\udc5f \u2212 2\u2206\ud835\udc3f (4) where c is the light velocity in free space, \u03b5r is the relative permittivity of the substrate material, fr is the resonant frequency, h is the dielectric substrate height, \u03b5reff is the effective permittivity, and \u0394L is the fringing length [12]", + " 6(a), is fabricated using a typical copper clad laminate, the second one, shown in Fig. 1 12 1 (0) 2( ) inR G G = Journal of Microwaves, Optoelectronics and Electromagnetic Applications, Vol. 18, No. 2, June 2019 DOI: http://dx.doi.org/10.1590/2179-10742019v18i21554 234 6(b), is painted with carbon ink of the CHIPsce brand, commonly used in electronics circuits for conductive traces\u2019 repairs, and the third one, shown in Fig. 6(c), is painted with the fabricated silver ink, which is synthesized from nitrocellulose. The main structural parameters (Fig. 5) of the patch antenna prototypes on fiberglass substrate shown in Fig. 6, are given in Table II. These dimensions values were defined using (1) to (5) and then adjusted with Ansoft HFSS, for Wi-Fi operation at 2.45 GHz. A very thin conducting patch made out of copper is considered. For comparison purpose, the conducting patches and feeding microstrip lines of the antenna prototypes shown in Fig. 6 were fabricated with the same dimensions, being composed of a metallic thin plate, Fig. 6(a), painted with carbon ink, Fig", + " The observed agreement confirms that the manufactured silver ink exhibits a good potential to be used in the fabrication of painted microstrip patch antennas on a fiberglass substrate, which is a simple and efficient alternative to conventional techniques. Thereafter, the manufactured silver ink was used in the fabrication of a microstrip patch antenna on a glass substrate, to explore the simplicity and flexibility provided by this manufacturing technique. Fig. 9 shows a photograph of the rectangular microstrip patch antenna prototype fabricated on a glass substrate with relative permittivity \u03b5r = 5.5 and height h = 1.4 mm. The structural parameters (Fig. 5) are given in Table IV. The patch element was painted by simple air spraying using a pressurized reservoir which is the same technique previously used. Journal of Microwaves, Optoelectronics and Electromagnetic Applications, Vol. 18, No. 2, June 2019 DOI: http://dx.doi.org/10.1590/2179-10742019v18i21554 Brazilian Microwave and Optoelectronics Society-SBMO received 24 Nov 2018; for review 29 Nov 2018; accepted 11 Apr 2019 Brazilian Society of Electromagnetism-SBMag \u00a9 2019 SBMO/SBMag ISSN 2179-1074 237 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004765_-IJERTV9IS080317.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004765_-IJERTV9IS080317.pdf-Figure3-1.png", + "caption": "Fig. 3 Bevel gear mechanism", + "texts": [], + "surrounding_texts": [ + "There are many reasons for a vehicle to lose its controllability: unfavorable weather and road conditions, lack of regular vehicle care, maintenance and repair, the driver\u2018s inexperience, sharp cornering (when passing an obstacle or underestimating a curve). A vehicle will react in a different way when the driver steers smoothly, or when the vehicle slightly declines from the lane. Loss of stability of a vehicle may cause its skidding on the road.In above mention conditions for the safety and comfort of an automobile as well as driver, stability is the major concern which needs to be considered. II. INTRODUCTION Variable Roll Stiffness System of an Automobile is a system which provides varying roll stiffness, adequate stability as well as prevents the rolling of vehicle while excessive turning. By observing the current road scenario it becomes mandatory to understand vehicle behavior in accordance with respective road conditions. Imperative condition to co-relate the vehicle behavior with different road condition is that, vehicle stiffness must vary as per various road condition. Successful implementation of this system will decreases the chances of vehicle getting rolled over. This system includes anti-roll bar, pneumatic system, coil spring, electronic control unit, bevel gears, suspensions and wheel. Anti-roll bar is connected to the suspension strut. Anti-roll bar and suspension strut are interconnected through a ball jointed link. Combination of three mitre type bevel gear mechanism is placed in centered section of antiroll bar. Which provides opposite rotational motion relatively. We have double acting cylinder with 3/2 DCV which controls engage and disengage of gear mechanism.Shape of anti-roll bars for automobile suspension systems are usually designed from a standpoint of avoiding physical interference with other components mounted on the bottom of a vehicle. Also the diameter of the bar is usually pre-selected and fixed to achieve a desired anti-roll stiffness. After having this much amount of constraints in shape and dimensions there is little design flexibility for engineers/designers. So in present invention we have configured the mechanism consisting of three mitre type bevel gears which can be engaged and disengaged. In engaged position of gears Anti-Roll bar will provide continuous traction while cornering, in disengaged position of gears it will flourish the riding comfort during uneven road conditions. International Journal of Engineering Research & Technology (IJERT) ISSN: 2278-0181http://www.ijert.org IJERTV9IS080317 (This work is licensed under a Creative Commons Attribution 4.0 International License.) Published by : www.ijert.org Vol. 9 Issue 08, August-2020 916 III. DESIGN & CALCULATION Fig. 4 Analysis of Chassis ( Total deformation) A. Design International Journal of Engineering Research & Technology (IJERT) ISSN: 2278-0181http://www.ijert.org IJERTV9IS080317 (This work is licensed under a Creative Commons Attribution 4.0 International License.) Published by : www.ijert.org Vol. 9 Issue 08, August-2020 917" + ] + }, + { + "image_filename": "designv8_17_0002401__md_4102461_p040.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002401__md_4102461_p040.pdf-Figure1-1.png", + "caption": "Fig. 1. (a) Equivalent circuit diagram of unit cell of patch. (b) Top view of unit cell of patch realization. (c) Block diagram of the proposed CP antenna.", + "texts": [ + " The electromagnetic (EM) simulations throughout the manuscripts has been done using Computer Simulation Technology (CST) design studio. Our proposed CP antenna is comprised of four-unit cells interconnected to each other. The CP antenna is widely used because of its better flexibility towards the orientation of the transmitting and receiving antenna. It also minimizes the multipath effects including constructive and destructive interference and phase shifting of the signal. The equivalent circuit of the proposed antenna unit cell is shown in Fig. 1(a). The equivalent circuit is realized by using two rectangular patches and a spiral strip to connect the patches, as shown in Fig. 1(b) [11]. The series inductance \ud835\udc3f\ud835\udc451is realized by the rectangular patch of area \u210e \u00d7 \ud835\udc50. The interconnected spiral strip of area (\ud835\udc4e + \ud835\udc54 + \ud835\udc53) \u00d7 \ud835\udc57 and rectangular patch of area \ud835\udc52 \u00d7 \ud835\udc51 is contributing to the other series inductance \ud835\udc3f\ud835\udc452 . Coupling capacitor (\ud835\udc36\ud835\udc36) is realized by the capacitive coupling between the patch and spiral strip. The shunt inductance (\ud835\udc3f\ud835\udc3f) is realized by the shorted via between the smaller patch and ground plane. The shunt capacitor (\ud835\udc36\ud835\udc45) is due to the capacitive coupling between the top radiator and ground plane. The orientation of the radiators is shown in Fig. 1(c), where cells A and B are interconnected with each other through a port (P), which possesses an area of \ud835\udc58 \u00d7 \ud835\udc5a. For measurement of the proposed design, a coaxial cable is inserted in the top metal layer through the ground plane and positioned in port (P), which is pointed in Fig. 2(a). The total size of the antenna is 20 \ud835\udc5a\ud835\udc5a \u00d7 20 \ud835\udc5a\ud835\udc5a \u00d7 2.4 \ud835\udc5a. The position of the coaxial cable and vias is shown in Fig. 2(b). Here, Coaxial feeding technique is used. Coaxial feed point is at (\ud835\udc4b, \ud835\udc4c) = (1.5 mm, 1.5 mm) with an inner and outer diameter of 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003103_26_tylek_203-215.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003103_26_tylek_203-215.pdf-Figure8-1.png", + "caption": "Fig. 8 Working unit elements for planting trees with covered root system", + "texts": [ + " The combination of satellite navigation (GPS) methods and the need to take into account information from other sources, necessary for the proper operation of the robot, will allow it to overcome the difficulties caused by a variety of possible soil conditions and terrain configurations (the existence of various, difficult to define obstacles) (Typiak et al. 2019). At the current stage of the project, a complete machine planting module has been designed (Adamczyk et al. 2019). It is composed of three main components (Fig. 8). The first one is a tool for planting spot prepa- ration. The second component is a movable dibble for placing seedlings in the soil. According to the assumed efficiency, the work of the machine should take place while travelling (without stopping), with the best possible vertical positioning of the seedling. The last element is a system of two pressing wheels with continuously adjustable geometry. The planting spot preparation tool is mounted in an oscillatory manner on the frame of the working unit via the first rocker arm and an actuator that allows adjusting the position and force of the tool pressing against the soil, while the pressing element is mounted on the frame by the second rocker, the position and pressure of which are regulated by a separate actuator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure17.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure17.4-1.png", + "caption": "Fig. 17.4. Comparison of total energy directional dispersion factors of floor panel vibration for different engine rotational speed", + "texts": [], + "surrounding_texts": [ + "VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 209 For the purpose of analysis the vibration dispersion factors at the path of propagation into human body via dash panel, floor panel and seat the comparison was collected in Fig. 17.5." + ] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.3-1.png", + "caption": "Figure 2.3: Wasp (left), Wasp II (middle) and Hornet (right) designs (8)", + "texts": [ + " Chapter 2: Previous work on MAV development 6 Figure 2.2 shows the initial design of MicroStar with a single vertical tail and a pusher propeller at the back, and the later design with the winglets replacing the tail and a tractor propeller replacing the pusher propeller (5). After successful development of the Black Widow MAV, AeroVironment continued their work to develop the next MAV which was named the Wasp and the Hornet. Although both of them are categorized as flying wing, their designs are slightly different which can be seen in Figure 2.3. The main difference is in the power source, the Wasp is powered by lithium batteries, while the Hornet is powered by fuel cells. In the Wasp\u2019s design, batteries are integrated into the wing structure; therefore, battery-capacity-to-MAV-size ratio is maximized (5). The Wasp has a wingspan of 33 centimeters (13 inches) and a weight of 210 grams (6 ounces). The Wasp can perform autonomous flight using its GPS navigation system or can be controlled by radio frequency signal. The Wasp II is the bigger version of the Wasp which was developed for operational use (8)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002205_e_download_1962_1697-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002205_e_download_1962_1697-Figure5-1.png", + "caption": "Figure 5. Model with skew applied to the magnet of the rotor", + "texts": [ + " In order to find the level of the factor with the THD and cogging torque, the smaller the characteristic value, the better the Manso characteristic is used. D means the overall satisfaction of the experiment and y means the predicted response value. Hi 2 is divided into 3 stages of skew and Lo is divided into 2 stages of skew. Cur represents the level of the factors at the lowest cogging torque and THD. Therefore, when the skew group has three stages and the skew angle is 7 degrees, the lowest characteristic value is shown. Figure 5 shows a model with skew applied to the magnet of the rotor. Figure 6. Wave of base model (2,200rpm) (a) Torque (b) Line Voltage Figure 7. Waveform of skewed model (2,200rpm) (a) Torque (b) Line Voltage In this paper, a study was conducted on the reduction of torque ripple by skew angle and skew stage. Based on the software data, the optimal coefficient level with the lowest cogging torque and THD through the coefficient placement method is a skew angle of 7 degrees and a 3-step skew. Based on this, when applied to the analysis model, the torque ripple and line voltage at the base speed and maximum speed were confirmed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure6-1.png", + "caption": "Fig. 6, Model used for Case (a), \u201cRigid\u201d virtual part, axial", + "texts": [ + " The details of the dimensions of the part studied are presented next. In reference to the geometries shown in Fig. 5, the actual total length of the bar is \ud835\udc3f = 150 \ud835\udc5a\ud835\udc5a . This total length is consisting of two parts. \ud835\udc3f\ud835\udc40\ud835\udc43 = 100 \ud835\udc5a\ud835\udc5a and \ud835\udc3f\ud835\udc49\ud835\udc43 = 50 \ud835\udc5a\ud835\udc5a . The subscripts \u201cMP\u201d and \u201cVP\u201d refer to the \u201cModeled Part\u201d and \u201cVirtual Part\u201d respectively. Looking at Fig. 5, the \u201cModeled Part\u201d is the solid grey color and the \u201cVirtual Part\u201d is the transparent grey color. VI. AXIAL MODES OF A CLAMPED BAR The bar under consideration is that of Fig.6, whose left end is fixed, and the right end is free. The axial vibration in the Zdirection are of primary interest. Two cases are considered in the analysis. In the first instance, the virtual part is \u201cRigid\u201d, followed by \u201cRigid Spring\u201d virtual part. Case (a) Rigid Virtual Part, Axial Vibration: The location of the \u201cHandler\u201d point has no effect on the analysis, however, for the sake of uniformity (with the case of \u201cRigid Spring\u201d analysis) it is placed at the centroid of the virtual part. This means, it is placed at a distance of 125 mm from the fixed end" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004917_O201709641401598.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004917_O201709641401598.pdf-Figure1-1.png", + "caption": "Fig. 1. ACM applied on urban railway vehicle", + "texts": [ + "com) Received: July 6, 2016; Accepted: September 28, 2016 http://www.jeet.or.kr \u2502 467 reliability of rotor position because it cannot secure the position accuracy of transient state zone, where start-up and speed variability occur. To overcome the problem of the existing sensorless control method, this study proposes a ZCP detection method without noise by setting a noncommutation area during medium speed driving. This method enables a stable sensorless control until reaching a rated speed without additional circuit formation. Fig. 1 shows an ACM structure using the existing DC motor. The existing ACM (MH99-AK19) is currently installed and used in lines no. 9 of Seoul subway, and it generates compressed air by maintaining consistent discharge pressure through DC motor. DC motor has a brush and commutator in general, so it is commutated when the two structures come into contact and can rotate to a consistent direction; however, friction occurs due to its structure and thus requires maintenance as abrasion increases accordingly" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000170_article_25904432.pdf-FigureI-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000170_article_25904432.pdf-FigureI-1.png", + "caption": "FIGURE I. SCHEMATIC DIAGRAM AND SIMULATION MODEL OF HIGH PRESSURE TORSION PROCESSING IN TORSION STAGE AND MEASUREMENT OF HARDNESS DISTRIBUTION OF", + "texts": [ + " By analyzing the efficient strain distribution of the HPT disks, combined with hardness experience measurement, heterogeneous plastic deformation characteristic in the stage of torsion and effects of friction on heterogeneous deformation are investigated. II. ESTABLISHMENT OF FINITE ELEMENT MODEL AND EXPERIMENT DESIGN In the HPT process, the disk is limited by the groove of the bottom die, and is compressed by the upper die of pressure, leading to compression deformation in the axial direction. After the end of the process of compression, the disk is loaded torsion by the rotation of the bottom die, and produces an axial compression and shape deformation. The model of the torsion stage is shown in Figure I(a) and (b). DISKS (A) SCHEMATIC DIAGRAM, (B) SIMULATION MODEL (C) TESTING PLANES OF THE HARDNESS The disks material adopted IF steel (manufactured by the Pohang Steel Company, POSCO, Korea), the main components include 0.008% C, 0.096% Mn, 0.045% Al, 0.041%Ti, Fe allowance. The HPT-processed IF steel disks were 20 mm of diameter and 2.0 mm of thickness, and the initial hardness was about 80 Hv. Surface pressure of 2.5 GPa was imposed on the disks at room temperature. The time of compression stage and torsion stage were both conducted at 10 s", + " Published by Atlantis Press. This is an open access article under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/). HPT, the disk surfaces are coated with graphite powder, another did not be disposed as control group. The graphite powder can form a thin film of graphite on the surface of the disk and reduce the friction coefficient significantly. An FM-700 micro-hardness tester was used to measure the hardness at different positions on the disks. Testing planes of the hardness is show in Figure I(c). Along with the radius direction, from center to edge, adjacent hardness testing pots is at 0.5 mm intervals. The finite element software (DEFORM-3D) is applied to simulate the plastic deformation of IF steel disks in HPT process. In the FEM simulation, the initial disks dimension is 20 mm in diameter and 2 mm thick. During the simulation process, 0.008% C carbon steel material in the DEFORM-3D material library is selected as the physical parameter of the IF steel disks material. It can regard the model as a rigid model and not need to mesh the model", + " In order to ensure the accuracy of the simulation results and improve the calculation efficiency, the best number of the initial mesh in the disks was 22000. In the compression stage, pressure of 2.5 GPa was developed on the disks. In the torsion stage, the bottom die rotated at 1 rad/s with a constant pressure of 2.5 GPa. The applied friction between die and disks was 0.05, 0.1, 1, 1.5 and 2, and the time of compression stage and torsion stage both were 10 s in all cases. In this paper, the turn adopted the early torsion stage (1/4 turns). III. RESULTS AND DISCUSSION A. Heterogeneous Distributions of Effective Strain and Hardness Figure II (a)~(f) indicates the Effective Strain distribution of HPT-processed disks at the different stage with finite element simulation approach. PRESSURE STAGE (C) 1/4 TURNS (D) 2/4 TURNS (E)3/4 TURNS (F)1 TURNS From Figure II(a) to (f), the thickness of disk will be decreased in the whole process of HPT, whether compression or torsion stage. The experimental results clearly show that the disks thickness decreases following the increase of angles of torsion turns. The original thickness of disk is 2 mm, while reduces to 1.9 mm after pressure stage. As to the early torsion stage(1/4 turns), the decrease rate of disks thickness will be severe changed. With the increase of angles of turns, the thickness of disk continuously reduces. From Figure II, the plastic deformation varied obviously in the early torsion stage(1/4 turns). Figure III shows the effective strain distribution on the transversal plane of the HPT-processed IF steel disks in the finite element model (2.5 GPa; 1/4 turns, \u03bc=1.5). In Figure III(a), the effective strain of disk in different position of center, middle, and edge were about 1, 4, 8, correspondingly. The value of effective strain of disks is significantly increased along the radial direction. Within a distance of 5 mm from center of disks, the values on all testing plane are about same. In Figure III(b), the enlarged partial detail figure (5 mm ~ 10 mm) exhibited that the value of effective strain on the bottom surface is above others. And this regular is more and more obviously exhibited from center to edge. Thus, there is deformation lagging character in early HPT stage. B. Heterogeneous Distributions of Hardness Figure IV shows the hardness distribution on the transversal plane of the early torsion stage disks. EXPERIENCE MODEL As the Figure IV(a) shown, the value of hardness is heterogeneous in the early torsion stage of the HPT process. From Figure IV(a), the hardness values in the center, middle, and edge of the disks were about 130 Hv, 180 Hv and 220 Hv. The figure indicates significantly that low hardness values in the center and the high at the edge along radius direction. Besides, hardness distribution is heterogeneous in axial direction. Compared with the bottom surface, the hardness values is lower in other test plane after torsion, especially test plane which is close to the upper surface. In Figure IV(b), the hardness gradually increases from center to edge. Within a distance of 2 mm from the center, the hardness is above 130 HV. Compared with the initial state, the hardness value is increasing about 60 percent after the process of HPT. During 2 mm ~ 6 mm from the center, the hardness values sustained growth, and the bottom is above others. That is to say, large deformation proceeds gradually from the edge to the center along the radial direction and from the bottom surface to the upper surfaces along the axial direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureC.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureC.3-1.png", + "caption": "Figure C.3: Improved base clamp concept.", + "texts": [ + " Results with the new concept and the original base clamp are presented in Fig. 9 of Appendix D. Differences between the computational models and the experimental results lead to the next improvement in the test rig, the base clamp. Base clamp The main consideration for redesign of the base clamp is the alignment of the finger. The largest differences between the models and the experimental results were found in rest position. It is understood that the stiffness of flexures are sensitive to small misalignment. A new concept was developed and it is presented in Fig. C.3. By attaching the finger with bolts to the base clamp the alignment depends in the manufacturing processes. Besides the stiffness of the base clamp was studied to create a requirement for the test rig. The stiffness of the base clamp should be higher than 338.95N/mm, according to equation C.2, to produce an error below between 1% the measurement and the finger stiffness. The 3D-print PLA considered in original Pot design was studied and compared to a machined aluminum design. The higher elastic modulus of the aluminum will increase the stiffness of the base clamp" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000292_download_70511_39859-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000292_download_70511_39859-Figure2-1.png", + "caption": "Figure 2. Free body diagram of the CB", + "texts": [ + " Consider an inextensible slender CB of length L with a constant flexural stiffness EI subjected to a concentrated non-follower end load P inclined with an angle \u03b4 measured from the positive x-axis and tip-moment M(L). These loading conditions are presented in the global (x, y) coordinate-system, where the curved coordinate along the deflected axis of the beam is denoted by the arc length , as shown in Fig. 1. The concentrated end force P is decomposed into two components Fx and Fy. Considering the free body diagram of the right segment of the beam, where the length of this segment becomes (L-s), as shown in Fig. 2. Since the beam weight is assumed to be neglected, the horizontal and vertical static equilibrium equations lead that the components Fx and Fy are independent of the arc length . However, the internal bending moment is a function of the arc length , as shown in Fig. 3. In this figure, \u03b8 represents the angle of rotation of the beam with respect to the positive x-axis and ds denotes the length of infinitesimal element of the beam. Hence, the moment equilibrium equation of the beam can be written as dM dy dx F Fx yds ds ds = \u2212 \u2212 (1) where sin( ( )), cos( ( )) dy dx s s ds ds \u03b8 \u03b8= = (2) ( ) ( ) d s M s EI ds \u03b8 = (3) s s s Differentiating both sides of Eq" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure5-1.png", + "caption": "Figure 5. Cont.", + "texts": [ + " The weight of the winding and the mass of the magnetic core were reduced as assumed. The flux density in the rotor\u2019s magnetic core increased with increasing width of the permanent magnet (at the expense of the core width). The weight of the winding was reduced by 0.9 kg, the mass of the stator magnetic core by 2.3 kg, the mass of the rotor magnetic core by 2.1 kg, and the mass of permanent magnets increased by 0.66 kg. The simulation models and the calculated flux density distribution from the permanent magnets in the magnetic core are shown in Figure 5. The calculations were made for the given power supply parameters, which are dictated by the permissible operating parameters of the inverter UDCmax = 350 V, Imax = 350 A. The control system performs work in two zones, the work zone with constant torque and the work zone weakening the magnetic field from permanent magnets. Thermal calculations were made using two models in the thermal of the MotorCAD module. As the stator inner diameter increases, the diameter of the stator support structure increases", + " In this case, higher losses are clearly generated in Motor #2 windings; this is supplied at a much higher frequency since the number of pole pairs is increased from p = 16 to p = 28, and speed range remains unchanged. Even though AC winding losses are higher, their contribution to total losses (Figure 11) is insignificant. Calculated total losses in the stator core are shown in Figure 13. Losses in Motor #2 core are greater than those of Motor #1 on account of higher values of flux density (produced by permanent magnets) in the electromagnetic circuit (see Figure 5) and higher supply currents (Figure 11). We may observe in these curves that core losses increase as rotational speed increases and then they stabilize at more or less constant levels; this is due to field weakening and operation in the second control zone. The field weakening zone for Motor #1 is commenced somewhat earlier. Characteristics of calculated stator total losses are presented in Figure 14; this is the sum of losses shown in Figures 11 and 13. It must be noted that these losses determine temperature distribution in the stator core" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002208_load.php_id_15010201-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002208_load.php_id_15010201-Figure10-1.png", + "caption": "Figure 10. The measured and simulated radiation patterns of the prototype at different resonant frequencies. (a) At 2.4 GHz. (b) At 3.5 GHz. (c) At 5.5 GHz. (d) At 5.8 GHz.", + "texts": [ + "4 GHz, the electric field distributions of monopolar patch mode assuredly similar to the top-loaded monopole are invariable in the \u03a6-direction, and their directions are along the radial direction of the patch with only Z-component, so that the monopolar patch mode gives a null in the broadside. For the TE 110 and TE 210 modes, the electric field distributions on the open elliptical-ring slots agree well with the magnetic field distributions on the complementary open elliptical-ring which is shown in Figure 2. For the radiation patterns test of the prototype, we have used a standard antenna test set with a horn antenna as a source in an anechoic chamber. Simulated and measured co-polarization (E\u03b8) and cross-polarization (E\u03d5) radiation patterns on E-plane and H-plane are exhibited in Figure 10 at different resonant frequencies, with the x-z plane and x-y plane referred to as the E- and H-planes, respectively. The results show that the proposed antenna radiates stable vertical-polarized waves (E\u03b8) with conical radiation patterns across the whole operating bandwidths, and the maximum power levels occur at elevation angle \u03b8 of 81\u25e6, 66\u25e6, 39\u25e6 and 33\u25e6 as it is operated at 2.4, 3.5, 5.5, and 5.8 GHz, respectively, which are similar to the simulation results by HFSS. Finally, the measured gain variations against frequency for various elevation angles \u03b8 across three operating bands are measured and shown in Figure 11" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000307__2018jamdsm0123__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000307__2018jamdsm0123__pdf-Figure3-1.png", + "caption": "Fig. 3 Return process", + "texts": [ + " The high-pressure oil Q1 released by the hydraulic pump reaches the piston\u2019s front chamber V1 via the valve port f and the oil duct Qp1. Th is oil acts on the work face A1 of the piston. Meanwhile, the low-pressure oil in the back chamber V2 of the piston is connected to the return line via the oil duct Qp2 and the valve port h; thus, the piston begins to accelerate the return process under the high-pressure oil in the front chamber V1. Subsequently, the signal hole c is opened and the oil in the left chamber V3 of the valve is returned to the oil tank via the oil duct Qp3, as shown in Fig. 3(a). The p iston returns to open the signal hole a. The h igh-pressure oil in the front chamber V1 of the piston is connected to the right chamber V4 of the valve and pushes the shuttle valve to start moving toward the left. When the valve movement opens the valve ports e and g and closes the valve ports f and h, the piston\u2019s front chamber V1 is connected to the oil tank, whereas its chamber V2 is connected to the high-pressure oil Q1. At this moment, the piston exh ibits reverse deceleration until it stops, as shown in Fig. 3(b). 3 2 \u00a9 2018 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2018jamdsm0123] After the p iston\u2019s return process is completed, the p iston is located at the back end of the drifter body, whereas the shuttle valve is on the body\u2019s left side. The piston in itiates stroke accelerat ion motion under the action of the high-pressure oil in the back chamber V2. When the piston reaches a certain position, the signal hole b opens and the right chamber V4 of the shuttle valve is connected to the oil tank to prepare for the reverse process, as shown in Fig", + " The in fluence of torque on motion state is not considered in this study. It was found that if the position of the signal port is not designed reasonably, secondary or multip le v ibrations exists after one impact of the piston is completed, and the piston does not return until all energy is consumed, thus causing trembling. Hydraulic drifter impact is a periodic vibrat ion course with position feedback and piston control by shuttle valve, as described in Sect ion 2.1 entitled \u201cPrinciple of d rifter operat ion.\u201d In Fig. 3(b), signal port a is opened to cause the hydraulic o il to enter the back chamber of the p iston via the shuttle valve, and the accelerat ion direction of the piston is the same as that of the stroke. In Fig . 4(b ), signal port d is opened to cause the hydraulic oil to enter the front chamber of the piston via the shuttle valve, and the acceleration direct ion of the piston is the same as that of the return. Signal ports b and c exert zero pressure on the left and right chambers of the valve before reversing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002025_f_version_1645096164-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002025_f_version_1645096164-Figure1-1.png", + "caption": "Figure 1. (a) SEM cross-section of a silicon-integrated spiral inductor; (b) simplified representation of main loss phenomena in silicon-integrated inductive components. Reprinted with permission from ref. [9]. Copyright 2020, IEEE.", + "texts": [ + " Indeed, they are exploited to implement irreplaceable functionality, such as simultaneous impedance/noise matching to the 50-ohm input source in LNAs, impedance matching and tuned resonant loads in amplifiers, LC tank in voltage-controlled oscillators, and integrated single-ended-to-differential conversion [3\u20137]. The Q-factor maximization at a given value of inductance, L, is the most common design issue. Other important figures of merit are the inductor \u03c9QL product, the transformer characteristic resistance (TCR) and the insertion loss (IL) [8,9]. A scanning electron microscope (SEM) cross-section of a silicon-integrated spiral inductor is shown in Figure 1a. Geometrical parameters (i.e., layout parameters) can be properly tuned within the technology constraints, namely, the coil shape (i.e., circular, polygonal or squared), the number of turns, n, the inner diameter, dIN, the metal width, w, and the metal spacing, s. The process parameters, such as the metal BEOL, the thickness and permittivity of the insulation layers, and the substrate conductivity, cannot be modified. Generally, the design of inductive devices is aimed at minimizing energy loss. The main energy dissipation phenomena of silicon-integrated inductive components are shown in Figure 1b. They occur in the metal layers that form the coil (series losses), as well as in the conductive layers below (parallel losses). The former is mainly due to the current crowding on the internal sides of the coil, due to skin and proximity effects. Current crowding rises with an increase in the operating frequency, thus increasing the equivalent resistance of the inductor. Thick conductive metals and multi-layer structures are common arrangements to lower the series losses, but their effectiveness degrades at RF/mm-wave frequencies", + " Indeed, they are exploited to implement irreplaceable functionality, such as simultaneous impedance/noise matching to the 50-ohm input source in LNAs, impedance matching and tuned resonant loads in amplifiers, LC tank in voltage-controlled oscillators, and integrated single-ended-to-differential conversion [3\u20137]. The Q-factor maximization at a given value of inductance, L, is the most common design issue. Other important figures of merit are the inductor \u03c9QL product, the transformer characteristic resistance (TCR) and the insertion loss (IL) [8,9]. A scanning electron microscope (SEM) cross-section of a silicon-integrated spiral inductor is shown in Figure 1a. Geometrical parameters (i.e., layout parameters) can be properly tuned within the technology constraints, namely, the coil shape (i.e., circular, polygonal or squared), t e number of turns, n, the in er diameter, dIN, the metal width, w, and the metal spacing, s. The process parameters, such as th metal BEOL, the thickness a p r ittivity of the insulation layers, and the substrate conductivity, cannot be modified. Generally, the desig of inductive devices is aime a minimizing energy loss. The main en rgy dissipation phenomena of s licon-integrated i ductive components are shown in F gure 1b", + " T f rmer is mainly due to the current crowding on the internal sides f the coil, due to kin and proximity eff c s. Current crowd g ises with an increase in the operating f equency, thus increasing the equivalent resistance of the inductor. Thick co ductive met ls and m lti-layer tructures are comm n arrangements to lower the series osses, but their effectiveness degrades at RF/mm-wave fr quencies. According to Faraday\u2019s law, current crowding is stronger in the inner turns. Therefore, the adoption of spirals with a low fill ratio, \u03c1, is a common rule [10]. Figure 1. (a) SEM cross-section of a silicon-integrated spiral inductor; (b) simplified representation of main loss phenomena in silicon-integrated inductive components. Reprinted with permission from Ref [9]. Copyright 2020, IEEE. Figure 1b also depicts two different mechanisms taking place in the substrate layers, i.e., the (vertical) displacement currents and the (horizontal) magnetically induced currents. Both electrically and magnetically induced currents increase at RF/mm-wave frequencies and dominate the inductor losses. Substrate shielding can be implemented to reduce the effect of parallel losses for RF operation [11,12]. Appl. Sci. 2022, 12, 2103 3 of 13 The design of an inductive component starts with its geometrical parameters, which set the low-frequency inductance, LDC" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001671_O201325954480036.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001671_O201325954480036.pdf-Figure10-1.png", + "caption": "Fig. 10 Equivalent stresses at critical frequencies", + "texts": [ + "944 Table 4 Maximum total deformation and natural frequency per mode at model 2 Frequency (Hz) Total deformation (mm) 1\u2019st Mode 43.001 16.019 2\u2019nd Mode 66.895 33.087 3\u2019rd Mode 108.97 14.083 4\u2019th Mode 111.25 31.77 5\u2019th Mode 134.35 20.562 6\u2019th Mode 222.41 36.565 (a) Model 1 (b) Model 2 \uc218\uc5d0\uc11c \uadf8 \uc9c4\ud3ed\ubcc0\uc704\ub294 0.105 mm\uc640 0.154 mm\ub85c \uc0dd\uae40\uc744 \uc54c \uc218 \uc788\ub2e4. \uc774\ub7ec\ud55c \uc704\ud5d8\uc9c4\ub3d9\uc218\uac00 \ud074\uc218\ub85d \ubaa8\ub378\uc758 \ub0b4\uad6c\uc131\uc774 \uc88b\uac8c \ub418\ub294\ub370, Model 1\uc758 \uc704\ud5d8 \uc9c4\ub3d9\uc218\uac00 Model 2\ubcf4\ub2e4 \ud07c\uc73c\ub85c\uc11c Model 1\uc758 \ub0b4 \uad6c\uc131\uc774 Model 2\ubcf4\ub2e4 \ub354 \uc591\ud638\ud574\uc9c4\ub2e4\ub294 \uac83\uc744 \ubcfc \uc218 \uc788\ub2e4. \ub530\ub77c\uc11c Model 1\uacfc 2\uc5d0\uc11c\uc758 159 Hz\uc640 110 Hz\uc758 \uc704\ud5d8 \uc9c4\ub3d9\uc218\uc5d0\uc11c Model 1\uacfc 2\uc758 \uc2e4\uc81c\uc801\uc778 \ub4f1\uac00 \uc751\ub825\uacfc \uc804\ubcc0\ud615\ub7c9\uc740 \uac01\uac01 Fig. 9(a), (b) \ubc0f Fig. 10(a), (b)\uacfc \uac19\uc774 \ub098\ud0c0\ub0ac\ub2e4 [9] . 4. \uacb0 \ub860 \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 \uc8fc\ud589 \uc911\uc778 \uc790\ub3d9\ucc28 \uc55e \ubc94\ud37c\uc5d0 \ub300\ud55c \uad6c\uc870 \ubc0f \uc9c4\ub3d9\uc5d0 \ub530\ub978 \uac15\ub3c4 \ub0b4\uad6c\uc131\uc744 \ud574\uc11d\ud558\uc600\ub2e4. \uc774\uc5d0 \ub300\ud574 \uc5f0\uad6c\ud55c \uacb0\uacfc\ub294 \ub2e4\uc74c\uacfc \uac19\ub2e4. \uad6c\uc870\ud574\uc11d \uacb0\uacfc, Mode1\uacfc Mode2 \uc55e \ubc94\ud37c\uc758 \ucd5c\ub300\uc758 \ub4f1\uac00\uc751\ub825\uc774 \uac01\uac01 187.09 MPa \ubc0f 278.4 MPa\uc774\uace0, \ubcc0\ud615\ub7c9\uc774 \uac01\uac01 1.3772 mm \ubc0f 2.675 mm\ub85c\uc11c \ucd5c\ub300\ub85c \ub098\ud0c0\ub0ac\ub2e4. 2\ubc88 \ubaa8\ub378\uc774 1\ubc88 \ubaa8\ub378\ubcf4\ub2e4 \ub354 \ubcc0\ud615\ub418\ub294 \uac83\uc744 \uc54c \uc218 \uc788\ub2e4. \ub610\ud55c Model 1\uacfc Model 2\uc5d0\uc11c \uace0\uc720\uc9c4 \ub3d9\uc218\ub294 \uacf5\ud788 230 Hz\uc774\ub0b4\uc5d0\uc11c \uc77c\uc5b4\ub0a8\uc744 \uc54c \uc218 \uc788\uc73c\uba70 \uc2e4\uc81c\uc801\uc73c\ub85c \ubcc0\ud615\uc774 \uc26c\uc6b0\uba70 \uacf5\uc9c4\uc774 \uc77c\uc5b4\ub0a0 \uac00\ub2a5\uc131\uc774 \ud070 \uac83\uc73c\ub85c \ubcf4\uc774\ub294 Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc758 \uc9c4\ub3d9\uc218\ub294 157.88 Hz\uc774\uace0 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc758 \uc9c4\ub3d9\uc218\ub294 222.41 Hz\uc774\ub2e4. \ub610\ud55c \uc9c4\ub3d9\uc218 \uc751\ub2f5\uc744 \ubcf8 Fig. 8(a), (b)\uc5d0 \uc11c \ubcf4\uba74 \uc54c \uc218 \uc788\ub4ef\uc774 Mode1\uc740 159 Hz\uc5d0\uc11c\uc640 Mode2\uc740 110 Hz \uc5d0\uc11c \ucd5c\ub300\uc758 \uc9c4\ud3ed\ubcc0\uc704\uac00 0.105 mm\uc640 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003882_f_version_1645520937-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003882_f_version_1645520937-Figure2-1.png", + "caption": "Figure 2. Naming of parts in a side view of the device. In brackets are biological structures in corresponds. *: structures on support board (SB).", + "texts": [ + " Based on the working principle of the weevil\u2019s jumping mechanism and aimed at better engineering implementation, the jumping mechanism is redesigned into a mechanical structure. In our design, the pull from the flexor muscle is removed through a mechanical position-limiting design. Representing the tibial flexor sclerite, a triangular slider (TS) is driven by rectangular slider (RS) through the upper string (US), and the RS is driven by the motor, thereby saving a degree of freedom. This design can be approximated as a two-dimensional model as shown in Figure 2, where the parts are named. The shell of the femur becomes the Support board (SB), which contains structures including the guide rail of the RS, the sliding bolt-nut pair (NBP), the string hole, and the protrusion structure (PS). The latter corresponds to the internal protrusion in the biological jumping mechanism. The biotical TFS becomes the TS mechanical structure. The slider is designed to move downward freely in its guide rail beneath the PS, and go through the gap between the RS and the PS" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure8-1.png", + "caption": "Fig. 8, The single degree of freedom approximation", + "texts": [ + " The middle column consists of the Catia generated frequencies whereas the third column is the one calculated from the theoretical formula presented earlier. The FEA results are in excellent agreement with theory as reflected in the table. The deformation modes of the FEA calculations are also in good agreement with the theoretical ones but are not displayed due to the space limitations. Keep in mind that the position of the handler point used for a rigid virtual part is irrelevant. A simple, single degree of freedom approximation to the problem at hand is also presented in Fig. 8. Here, the lumped mass associated with the virtual part is attached to the linear spring using a massless rigid bar as indicated. The stiffness of the spring is the same as the stiffness of the modeled portion of the bar. Namely, \ud835\udc58\ud835\udc40\ud835\udc43 = \ud835\udc34\ud835\udc38 \ud835\udc3f\ud835\udc40\ud835\udc43 . The natural frequency of the SDOF system is then given by = \u221a \ud835\udc58\ud835\udc40\ud835\udc43 \ud835\udc5a\ud835\udc49\ud835\udc43+\ud835\udc5a\ud835\udc40\ud835\udc43/3 . Using the data for the present problem, the frequency value estimated by this expression is = 8795 Hz which a reasonable approximation to the value reported in table I. Case (b) Rigid Spring Virtual Part, Axial Vibration: As a next model, a \u201cRigid Spring\u201d virtual part is representing the latter \ud835\udc3f\ud835\udc49\ud835\udc43 = 50 \ud835\udc5a\ud835\udc5a of the 150 \ud835\udc5a\ud835\udc5a part as shown in figure 9 below" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000250_f_version_1613985157-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000250_f_version_1613985157-Figure2-1.png", + "caption": "Figure 2. (a) Overview of ATD and its defined parameters; and (b) the model of ATD. The blocked region shows feasible control force volume and parameters corresponding to (a). The coordination is defined as the same as the body frame of multirotor.", + "texts": [ + " In this research, we designed and manufactured ATD using three ducted fans, which is the minimum configuration. To construct ATD, to be equipped on a typical multirotor UAV, we use ducted fan as the main actuator unit, which is lightweight, compact, and able to generate relatively high thrust. The generated thrust from ATD acts on the multirotor to allow it to translate and generate the force in horizontal direction. At least three forces applied in a plane are required for positioning a body in that plane. The structure of ATD is shown in Figure 2a. Three ducted fans are placed every 120 degrees and set as Y-configurations, so that a well-balanced force can be generated by the combination of any of two thrusts of ducted fans. To avoid exhaust from the ducted fan from being affected by the downwash of the multirotor\u2019s propellers, the ducted fans are mounted outside the propeller radius of the multirotor. ATD comprises three ducted fans, power module, PCA9685-I2C to PWM interface, ESC, and a CPU board (LattePanda Alpha 864). The ducted fan is 50 mm in diameter and can generate 0.95 kg of maximum thrust. The CPU board is used for processing feedback control. The distance L from ducted fan can be set depending on the size of multirotor platform. The specifications of the device are summarized in Table 1. To control ATD, for any feasible control force F, the output thrust of three ducted fans should be calculated. According to the arrangement of ducted fans, the model of ATD is shown in Figure 2b. The coordination is defined as the same as the multirotor body frame. F1, F2, and F3 show the output thrusts of the ducted fans. The blocked region in Figure 2b is the feasible control force volume which is mixed by thrust of three ducted fans. The region can be separated into S1, S2, and S3 and given as follows. S1 := {F \u2208 <2 | \u2212kFx \u2264 Fy, kFx \u2212 Fmax \u2265 Fy, \u2212kFx \u2212 Fmax \u2265 Fy, kFx \u2264 Fy} (1) S2 := {F \u2208 <2 | kFx \u2265 Fy, \u2212 k 2 Fmax \u2264 Fx \u2264 0, kFx + Fmax \u2264 Fy} (2) S3 := {F \u2208 <2 | \u2212kFx \u2265 Fy, 0 \u2264 Fx \u2264 k 2 Fmax, \u2212kFx + Fmax \u2264 Fy} (3) In Equations (1)\u2013(3), \u00b1k represents the slope of F1 and F2 based on the coordination, and the value is \u00b1 \u221a 3 3 . Fmax shows the maximum output thrust of ducted fan", + " Fi = \u03b6ui + C (0 \u2264 ui \u2264 100, i = 1, 2, 3) (5) In Equation (5), \u03b6 and C are constants, and these parameters are estimated in Section 3. The proposed system (shown in Figure 1a) consists of a multirotor UAV with ATD. The multirotor platform is constructed using DJI F550 frame (the diameters of the body and propellers are 550 and 238 mm, respectively) and DJI N3 flight controller. High level control for the multirotor navigation is achieved by the communication link between the flight controller and the on-board CPU. The pictures of ATD with multirotor system is shown Figure 3. The coordination is defined as the same as in Figure 2. RealSense T265 is used for estimating velocity of the UAV. Through the communication between flight controller of the multirotor and the onboard CPU, we constructed the system, as shown in Figure 4, based on ROS(Robot Operating System). In the figure, the processes inside the CPU board block shows ROS nodes what we mainly developed and data flow shows the topics being published and subscribed in each nodes. Constructing the system using ROS improves the reusability of the system, and additional devices can be easily integrated into the system" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002658_2452-020-03846-0.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002658_2452-020-03846-0.pdf-Figure14-1.png", + "caption": "Fig. 14 Stability analysis with thin shell finite element model with the stabilizing webs", + "texts": [ + " However, the incremental loading analysis indicated that geometric nonlinearity still caused instability with a limit load factor of 0.49, which is about half of its self-weight. Figure\u00a013c) shows the deformation under the limit loading. It was observed that the end bottom panels still buckle, but the propagation was localized only to the outer strips. In order to mitigate instability and prevent such progressive deformation, web stiffener elements were introduced between valleys on the exterior side of the canopy at three levels as shown in Fig.\u00a014a. Other configurations remain the same with the model described in the Sect.\u00a05.2.2. The analysis shows that they stabilized the structure significantly, such that local buckling of the end bottom panels was prevented, and the lowest eigenvalue factor increased to 1.13. As each web consists of two triangle pieces linked with hinges combined with \u201cwatoji\u201d lacing, they can fold in during closing transformation and function only in tension in the expanded position. They keep the folded plate system from flattening under its own weight as shown in Fig.\u00a014c). A load limit factor of 1.32 by the output of incremental loading analysis with geometric nonlinearity is higher than the lowest factor of eigenvalue buckling analysis. This implies that the structure can undergo post-buckling behavior beyond the linear buckling load by reconfiguring the geometry to an updated equilibrium state. By correctly understanding the critical cause of the unstable behavior, the stabilizing elements were successfully accommodated in the folding system while increasing stability during deployment. Figure\u00a014d) shows the actual implementation of the stabilizing webs. This section describes the fabrication of the canopy with a focus on the FRP hinges, the cutting pattern, module making, and the connection details for on-site assembly. Vol.:(0123456789) Vol:.(1234567890) Figure\u00a015 shows a perspective view and drawings of the fabricated canopy. The origami structure is formed using foldable Fiber Reinforced Plastics (FRP) using both carbon and grass fibers. The foldable FRP sheet consists of panel parts and joint parts" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001486_843_PDF_26_paper.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001486_843_PDF_26_paper.pdf-Figure6-1.png", + "caption": "Fig. 6. Current-mode 1.5 bit SDAC", + "texts": [ + " Current sources IFS /2 and \u2212IFS /2 are used to add current to or subtract current from current copiers resulting in two relevant current levels converted to temperature digital code C = c2c1c00. The output coder converts the code C into 2 bit 4-state digital output codes B0 = b01b00 of the 2 bit SADC described in Eq. (2). The output codes Bi described by (1) and (2) are the initial digital outputs, after code conversion but before error correction. 2.3. 1.5 bit SDAC. The 1.5 bit SDAC structure is shown in Fig. 6. The structure consists of reference current sources IFS/2 and \u2212IFS /2, and cascaded current copiers. The temperature digital code Ci = ci1ci (corresponding to the output code Bi = bi1bi) of the 1.5 bit SADC is used to add or subtract reference current to or from the output current. Thus, the 1.5 bit SDAC current iSDACi outputs are \u2212IFS /2, 0, IFS /2 for the SADCi output codes 00, 01 and 10, respectively: iSDACi = \u2212 IF S 2 for Bi = 00 0 for Bi = 01 IF S 2 for Bi = 10 , i = N \u2212 1, . . . , 1, (3) where N denotes the number of stages. 2.4. Reference current sources. The structures of 1.5 bit SDAC (Fig. 4), 2 bit SADC (Fig. 5) and 1.5 bit SDAC (Fig. 6) contain reference current sources IFS/2, \u2212IFS /2, IFS/4 and \u2212IFS /4. Bull. Pol. Ac.: Tech. 61(4) 2013 981 Fig. 7. Reference current sources As shown in Fig. 7, cascaded current sources provide with all the desired sources to the ADC converter functional blocks. Two mirrors are used to produce reference currents IREF and \u2212IREF . 2.5. Current multiply by two circuit. In each stage, the 1.5 bit SDAC output current is subtracted from the residue current of the previous stage, and the difference is multiplied by 2 to produce a residue current that is passed to the next stage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000017_9312710_09452043.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000017_9312710_09452043.pdf-Figure4-1.png", + "caption": "FIGURE 4. Layout of HPAA with 3 driven elements.", + "texts": [ + " A 2\u00d7 1 antenna array could have been selected for use within the proof-of-concept design; however, the steering resolution would have been poorer. The target operating frequency for the proof-of-concept design was 11 GHz. The radiating element, within the array, is a circular microstrip patch operating in the TM110 mode. The radius of the patch was calculated to be 4.74 mm. Each driven element was fed using a via. The vias were offset, along the y-axis, by 2.9 mm from the centre of the patch, as shown in Figure 4. A series of detailed parametric studies were performed in order to determine the optimum dimensions for the antenna. The spacing between the driven elements was set to 0.53\u03bb. Taking the centre of each driven element as the origin, the co-ordinates for the centres of the parasitic elements are: (\u22120.265\u03bb, 0.265\u03bb), (\u22120.265\u03bb, \u22120.265\u03bb), (0.265\u03bb, 0.265\u03bb), and (0.265\u03bb, \u22120.265\u03bb). Each parasitic element has a radius of 4.5 mm. The vias, in the parasitic elements, have a radius of 1 mm. The minimum spacing between the parasitic and driven elements was set to 0.71 mm. Figure 4 shows that the parasitic elements are arranged in rows and they are located above and below the driven elements. The parasitics are operated in pairs. To be specific parasitics having the same identification number are operated simultaneously. For this reason, there are 2Np possible combinations of parasitic switch states, where Np/2 is the number of pairs of parasitics. For the proposed HPAA this means that there are 24 = 16 switch states. The structure of the proposed antenna is symmetrical and hence, some of these combinations are the mirror image of one another along the y-axis symmetry plane", + " The first two pairs of parasitics are in the ON-state (connected to ground with vias) for this switch state. The current density on those parasitics is negligible. These parasitics act as reflectors forcing the main beam of the antenna towards the opposite direction. The third and fourth pair of parasitics are in the OFF-state (i.e. not connected to ground). The electromagnetic fields from the second and third driven elements couple strongly with the third and fourth parasitics and they act as directors. This leads to the steered 3D farfield patterns shown in Figure 14(b). Based on Figure 4, the E-plane corresponds to the xz-plane and the H-plane corresponds to the yz-plane. Figure 15 shows the E-plane radiation patterns corresponding to parasitic switch states 1111 and 0011. Please note that all of the curves, in Figures 15-17, were normalised against the peak of the curve having the highest realised gain. Let us first consider parasitic switch state 1111. The measured realised gain of the HPAA is 9.15 dBi which is close to the simulated realised gain of 9.18 dBi. The main beam of the antenna is directed towards 0\u25e6 (i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002629__12_129_12_1155__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002629__12_129_12_1155__pdf-Figure3-1.png", + "caption": "Fig. 3. The image in a location estimated using the active vision", + "texts": [ + "jp) Yasuchika Mori Member (Tokyo Metropolitan University, ymori@cc.tmit.ac.jp) Keywords: image processing, active vision, stereo vision era. System configuration is shown in Fig. 1. Correspondence points are determined by using the image obtained with the camera. The next position of the camera is determined by using a unique evaluation function in the active vision system. The camera is moved according to the information conveyed to the servo driver through the motion control board. Fig. 2 shows an image shot by a camera initial position, and Fig. 3 shows an image in a location estimated using an active vision. From Fig. 2 and Fig. 3, it can be seen that the objects were not occluded. This validates the accuracy of the unique evaluation function. The coordinates of the objects obtained by moving the parallel stereo camera (limit of parallel movement; 40 mm) and the proposed system are listed in Table 1. The accuracy Table 1. Coordinate of objects real value[mm] parallel stereo (40 mm)[mm] proposed method[mm] (\u2212170, 775, 905) (\u2212154, 800, 882) (\u2212154, 767, 882) (\u2212270, 815, 905) (\u2212258, 820, 866) (\u2212256, 817, 866) (\u2212220, 955, 905) (\u2212207, 914, 896) (\u2212207, 931, 897) \u2013 3 \u2013 \u8ad6 \u6587 \u80fd\u52d5\u8996\u899a\u3092\u7528\u3044\u305f\u63a2\u7d22\u30ed\u30dc\u30c3\u30c8\u306e\u958b\u767a \u5b66\u751f\u54e1 \u718a\u8c37\u69d9\u4e00\u90ce\u2217 \u6b63 \u54e1 \u68ee \u6cf0\u89aa\u2217 Development of Search Robot with Active Vision Shin-ichiro Kumagai\u2217, Student Member, Yasuchika Mori\u2217, Member For environment recognition with the camera, it is preferable to reduce the number of images to be processed in order to reduce the processing time" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000107_e_download_6617_5459-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000107_e_download_6617_5459-Figure4-1.png", + "caption": "Fig. 4. Sketches of a mock-up sample of the manual self-cleaning fork (version 2).", + "texts": [ + " Cleaning of the tines 3 is performed by the cleaning plate 4, which is moved along the tines 3. To do this, the user withdraws the movable handle 4, overcoming the resistance of the spring 6. By doing so, the frame 2 passes through the longitudinal grooves 7 and serves as one guide for the movable handle 5, and the handle 1 serves as the second guide. The fork returns to its original state by releasing the spring 6 after the user releases the movable handle 5. In the course of the experimental design work, the author of the device modeled two versions of mock-up samples (Fig. 3 and Fig. 4). Each of these versions differs in the direction of distribution of the user's force on the cleaning plate: above a plane of the tines (version 1) and below this plane (version 2). The results of the evaluation of the comparative effectiveness of the use of the design solutions will be presented based on the test results. In general, the technical result of the claimed utility device is an increase in the operational characteristics of the self-cleaning fork, reduction in the time and effort spent on cleaning of the tines" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000987_ees-2022-4-r-112.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000987_ees-2022-4-r-112.pdf-Figure1-1.png", + "caption": "Fig. 1. Geometry of the proposed antenna.", + "texts": [ + " The ground plane is characterized by a coplanar configuration proportional to the excitation line. It is fed with a microstrip feed line with characteristic impedance of 50 \u03a9. A circular patch printed on a low-cost FR4-type substrate with a thickness h = 0.8 mm, relative permittivity \ud835\udf00\ud835\udc5f = 4.3, and loss tangent tan \u03b4 = 0.025 was utilized to fabricate the antenna whose geometry is presented in Table 1. The substrate had a total size of 70 mm \u00d7 60 mm \u00d7 0.8 mm. The ultra-wide impedance bandwidth was achieved using CST software to simulate a compact structure. Fig. 1 shows the final design for a triple- MEKKI et al.: A UHF/UWB MONOPOLE ANTENNA DESIGN PROCESS INTEGRATED IN AN RFID READER BOARD band monopole antenna. The main aim of this study was to create a triple-band antenna reader for UHF/UWB operation. A circular patch disc monopole antenna with two-sided corner truncation and two circular and (+)-shaped slots make up this antenna [27]. Fig. 2 depicts the evolution of the introduced triple-band an- tenna from the basic UWB antenna step by step. There are three basic phases in the antenna design process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001821_f_version_1591065925-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001821_f_version_1591065925-Figure6-1.png", + "caption": "Figure 6. Homokinetic condition: The balls and the cage are in the bisecting plane between outer race and inner race for each deflection angle \u03b2ba.", + "texts": [ + " To guarantee the functionality of the simulation model, it is necessary to verify it first. Therefore, the influence of the numerical contact parameters on the joint kinematics is investigated. These parameters must be chosen in such a way that the model behaviour corresponds as closely as possible to the real joint behaviour. This includes, above all, that the homokinetic condition [12] be fulfilled, which is characterised by the position of the balls in the bisecting plane between the inner and outer race (see Figure 6). However, due to the chosen approach, which allows penetrations between the contact bodies, this cannot be completely fulfilled. For this reason, a compromise must be found for the contact stiffness, under which a sufficient fulfillment is guaranteed. In a previous work [25], it is shown that the use of the contact stiffnesses listed in the literature, which were calculated according to the method of Hamrock and Brewe [22] for the Hertzian contact theory, results in a too soft system behaviour for our application case", + " This limit torque is mainly characterised by the contact stiffness used, which was selected to be very high for the model to fulfil the homokinetic condition. Due to the approach used, the friction forces are directly proportional to the normal force, thus even small variations in the friction coefficient have a significant influence. The effect is particularly clear in connection with the secondary torque ~T2XY in the joint, which is defined according to the authors of [4,26] as ~T2XY = ~TL \u00b7 tan ( \u03b2ba 2 ) , for \u00b5 = 0 , (25) with the load torque ~TL and the deflection angle \u03b2ba (see Figure 6). This results on the one hand from the joint geometry as soon as the joint is loaded with a torque Mt in the deflected state. On the other hand, previous studies [2,4] have already shown that friction in the tracks affects the magnitude of the resulting secondary torque, which can be explained by the friction forces acting tangentially. With the model presented here, this relationship can be proven. The functional correlation between friction coefficient and secondary torque for 2000 Nm under 2 \u25e6 deflection angle is shown in Figure 11" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002045_nkhair2021_07004.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002045_nkhair2021_07004.pdf-Figure5-1.png", + "caption": "Fig. 5. Connection of the frame using welding", + "texts": [], + "surrounding_texts": [ + "Chassis design with specifications chassis length 6000mm, chassis width 2500mm, using AISI 1018 steel material, rectangular model with dimensions 120x80x3mm. The Von Mises stress value for AISI 1018 106 HR steel material is 29.06 MPa for the standard mesh, 28.6 MPa for the 10 mm control mesh and 28.15 MPa. The displacement value for AISI 1018 106 HR steel material is 0.3643 mm for the standard grid, 0.3704 mm for the 10 mm control grid and 0.3764 mm for the 5 mm control grid. The safety factor for AISI 1018 106 HR steel material is 9.32 for the standard fabric, 9.45 for the 10 mm control fabric and 9.58 for the control fabric." + ] + }, + { + "image_filename": "designv8_17_0004314_496_ams.2014.016.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004314_496_ams.2014.016.pdf-Figure3-1.png", + "caption": "Fig. 3: Temperature distributiony.", + "texts": [], + "surrounding_texts": [ + "Using the energy equation of the process of braking: ( )Q I m v J 2 1 2 braking1 2 2 $ $ $~= + n 60 2 $ $~ r= (5) (6) Where: I - Moment of inertia of the total rotating mass participating in the process of braking (598.4 kg2m), \u03c9 - Rotational speed (55.07 rad/sec), m - Vehicle mass (30000 kg), o - Rate of travel of vehicle (40 kph), n \u2013 Revolution number of sun wheel (525.9 rev/min). Supposing that power efficiency of sun-andplanet gear is 97%, the amount of heat released Acta Mechanica Slovaca Journal published by Faculty of Mechanical Engineering - Technical University of Ko\u0161ice 31 during one brake application is Q1 braking = 2682.63 MJ The amount of heat calculated with the energy equation, which is the sum of the rotational and translational motion, is the same as the heat amount removed from the system after braking. The heat released at the time of braking is removed by means of air and oil cooling as mentioned above. Prior to this article, a study was published by the author (Thermodynamical examination of the oily disc brake of an agricultural motor vehicle, Periodica Politechnica, Transportation Engineering, Budapest. Just being published) in which values of coefficient of heat transfer necessary for the determination of heat removal are calculated for the air outside the brake drum (20\u00b0C) and the internal coefficient of heat transfer of the wheel body is also calculated by means of criterion equations. The external coefficient of heat transfer can be given as follows by the number Nu from Article [6]: d Nu 1 $a m= (7) Where: d \u2013 Diameter of wheel body (0.62 m), y - Kinematic viscosity for ambient temperature of 20 C\u00b0 (15.7\u202210-6 m2/sec), m \u2013 Coefficient of heat conduction (0.025 W/mK). The value of Reynolds number is 438343.949. ReNu c n$= (8) Values of c and n constants can be determined from Table 16 [4]: n \u2013 In case of flow becoming eddy, the tangent of angle of obliquity of curve. It can be seen in the diagram showing the relation between numbers Re and Nu [4] that the function is linear therefore we can give the Nu number belonging to the wheel body of 0.62 m diameter. Substituting then extrapolating, we get value of Nu number: ,Nu 952 41662 = Value of coefficient of heat transfer a62 is: Heat-transfer coefficient 1 means the heat transfer coefficient for the flat plate of wheel body, while heat-transfer coefficient 2 for the cylindrical surface of wheel body. Similarly, heat amount 1 removed by air cooling means the heat removed through the flat plate of the brake drum, while heat amount 2 through the cylindrical shell of the brake drum. Note that the brake drum is limited with two flat plates, so amount of heat removed through these surfaces will be double of this value. Under normal operating circumstances, heat is removed by air cooling and oil cooling. The study determines the greatest number of brake applications possible in one hour under various circumstances. In each case, the vehicle is slowed down from the rate of travel with a very short emergency braking in 2 seconds till full stop. Rate of travel of vehicle will be 10, 20, 30, 40 kph in the following. The following cases are examined in the article: It determines how many is the greatest number of brake applications permitted when air cooling 32 VOLUME 18, No. 2, 2014 and oil cooling are operating simultaneously. It analyses the critical event when the oil cooler does not operate, and heat removal is done only by air cooling. After that it shows how the change of wall temperature of wheel body influences number of brake applications." + ] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.2-1.png", + "caption": "Figure 6.2: Vane Attached to Rotor Geometric Relations", + "texts": [ + " 85 Figure 5.28: Rotor Endface Leakage Mass Flow Rate with Different Pressure Ratios ......... 86 Figure 5.29: Equivalent Channel Width for Rotor Endface Leakage .................................... 87 Figure 5.30: Vane Endface Leakage Mass Flow Rate with Pslot = Psuc ................................. 88 Figure 5.31: Rotor Endface Leakage with Different Pressure Ratios at 120\u00b0 Vane Angle ... 89 Figure 6.1: Vane Attached to Cylinder Geometric Relations ................................................ 95 Figure 6.2: Vane Attached to Rotor Geometric Relations ..................................................... 97 Figure 6.3: Compressor Housing Cross-section and Friction Losses .................................... 99 Figure 6.4: RV Prototype Cyliner-Rotor Assembly Cross-Section ..................................... 100 Figure 6.5: Motor Load Curve ............................................................................................. 102 x Figure 6.6: Rotor Endface Friction and Vane Sliding Friction ", + "11) with the cylinder rotation angle 97 being the main parameter of interest. The friction torques for each generalised coordinate has been combined into a single term Tf which represents the total friction torque for the assembly. \ud835\udc3c\ud835\udc50\ud703\u0308\ud835\udc50 = \ud835\udc47\ud835\udc5a + \ud835\udc47\ud835\udc54 \u2212 \ud835\udc51\ud703\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 (\ud835\udc3c\ud835\udc5f\ud703\u0308\ud835\udc5f) \u2212 \ud835\udc51\ud835\udf19 \ud835\udc51\ud703\ud835\udc50 (\ud835\udc5a\ud835\udc4f\ud835\udc51\ud835\udc4f?\u0308?) \u2212 \ud835\udc51\ud703\ud835\udc4f \ud835\udc51\ud703\ud835\udc50 (\ud835\udc3c\ud835\udc4f\ud703\u0308\ud835\udc4f) \u2212 \ud835\udc47\ud835\udc53 (6.11) As there are variants of the RV mechanism in which the vane may be attached to the rotor [20], the dynamics of this design variant will be covered in this section for comprehensiveness. Figure 6.2 shows the geometric relations for the components in the RV mechanism in which the vane is attached to the rotor. The Lagrangian of the system is the same as that of the vane attached to the cylinder as shown in Equation (6.12). For the non-conservative torques, the gas torque and motor torque now act on the rotor as it is the main driving component. These non-conservative torques are expressed in Equation (6.13). \ud835\udc3f = 1 2 (\ud835\udc3c\ud835\udc5f\ud703\u0307\ud835\udc5f 2 + \ud835\udc3c\ud835\udc50\ud703\u0307\ud835\udc50 2 + \ud835\udc3c\ud835\udc4f\ud703\u0307\ud835\udc4f 2 + \ud835\udc5a\ud835\udc4f\ud835\udc5f\ud835\udc4f\ud835\udc5f?\u0307? 2) (6.12) 98 \ud835\udc47\ud835\udc5b,\ud835\udf03\ud835\udc5f = \ud835\udc47\ud835\udc5a + \ud835\udc47\ud835\udc54 \u2212 \ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc5f \ud835\udc47\ud835\udc5b,\ud835\udf03\ud835\udc50 = \u2212\ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc50 \ud835\udc47\ud835\udc5b,\ud835\udf03\ud835\udc4f = \u2212\ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc4f \ud835\udc47\ud835\udc5b,\ud835\udf19 = \u2212\ud835\udc47\ud835\udc53,\ud835\udf19 } (6.13) The set of holonomic constraints for the vane on rotor RV mechanism derived from Figure 6.2 are shown in Equation (6.14). sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc50 = sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc50\ud835\udc5f , \u2192 \ud835\udc531 = sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc50 \u2212 sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc50\ud835\udc5f = 0 sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc4f = sin\ud835\udf19 \ud835\udc5f\ud835\udc4f\ud835\udc5f , \u2192 \ud835\udc532 = sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc4f \u2212 sin\ud835\udf19 \ud835\udc5f\ud835\udc4f\ud835\udc5f = 0 sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc4f = sin \ud703\ud835\udc4f \ud700 , \u2192 \ud835\udc533 = sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc4f \u2212 sin \ud703\ud835\udc4f \ud700 = 0 } (6.14) The set of Lagrange equations for the RV mechanism can then be written as shown in Equation (6.15). Apart from the generalised coordinates for the cylinder and rotor, the bush component stays the same. \ud835\udc3c\ud835\udc5f\ud703\u0308\ud835\udc5f = \ud835\udc47\ud835\udc5a + \ud835\udc47\ud835\udc54 \u2212 \ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc5f + \ud7061 \ud835\udf15\ud835\udc531 \ud835\udf15\ud703\ud835\udc5f + \ud7062 \ud835\udf15\ud835\udc532 \ud835\udf15\ud703\ud835\udc5f + \ud7063 \ud835\udf15\ud835\udc533 \ud835\udf15\ud703\ud835\udc5f \ud835\udc3c\ud835\udc50\ud703\u0308\ud835\udc50 = \u2212\ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc50 + \ud7061 \ud835\udf15\ud835\udc531 \ud835\udf15\ud703\ud835\udc50 \ud835\udc3c\ud835\udc4f\ud703\u0308\ud835\udc4f = \u2212\ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc4f + \ud7063 \ud835\udf15\ud835\udc533 \ud835\udf15\ud703\ud835\udc4f \ud835\udc5a\ud835\udc4f\ud835\udc5f\ud835\udc4f\ud835\udc5f" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004553_ai.7-12-2021.2314491-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004553_ai.7-12-2021.2314491-Figure17-1.png", + "caption": "Fig. 17.Cad model of a flat and twisted structure.", + "texts": [], + "surrounding_texts": [ + "Rapid Upper Limb Assessment (RULA) analysis was carried out in CATIA package and score for the body at different regions include upper arm, lower arm, wrist, neck, trunk, and legs are obtained [7]. The score indicates the risk of Musculoskeletal Disorders (MSD). MSDs are injuries and disorders that affect the human body's movement or musculoskeletal system. The analysis was carried out under various sitting posture conditions. Posture which has high level of risk need to evaluated first. Importance should be given for higher level of score." + ] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure7-1.png", + "caption": "Figure 7 Captive Screw", + "texts": [ + " This flanged access port is shown below in Figure 6. Gasket Interface with Captive Screws In an effort to move away from the 2-56 screws other design options were considered. The next design utilized captive screws. These screws consist of a small cylinder that would be press fit into the tabs on the access port cover, along with a screw that is held captive by that cylinder. These screws have a very low profile, meaning that a Page 9 larger screw size will fit into the strict height allowance available. Captive screws are shown below in Figure 7. In addition to their low profile, another benefit of these screws is that the screw itself is contained by the outer sleeve. This simplifies handling and integration operations greatly, as there is no longer a need to keep track of individual screws and also significantly less risk of foreign object debris (FOD) on the inside of the P-POD. The downside of these captive screws is that in the size necessary for this task, the only head style available is a standard flat head, which is typically not a preferred screw head to work with" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure3-1.png", + "caption": "Figure 3 Finite Element Model of Magnetic Planetary Gears.", + "texts": [ + " Set the material of the material, the magnetic block is made of neodymium iron boron material, and the N and S poles are staggered; The supporting device is made of stainless steel material, and its properties do not affect magnetism, keeping the magnetic field strength H and magnetic induction strength B continuous. The boundary condition is set to the balloon boundary, and the boundary is set to infinity. Divide the mesh, select a triangular mesh to divide the model, and set the triangle edge length to 8mm. Finally, the vector magnetic potential A is used for solving. The obtained modeling parameters are shown in Table 1, finite element modeling is shown in Figure 3. Published by Francis Academic Press, UK -21- The magnitude of transmission torque is influenced by factors such as gear mesh clearance, number of magnetic poles, thickness of magnetic rings, and gear size. In this article, a gear model is established in a static magnetic field, the mesh is divided and solved, and simulation analysis is completed for four influencing variables. Among them, the maximum number of magnetic poles is selected based on the size of the gear; In the supporting material, due to the magnetic properties of stainless steel similar to vacuum, the size of the gear does not affect the result of transmitting torque" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000302_f_version_1554344750-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000302_f_version_1554344750-Figure3-1.png", + "caption": "Figure 3. Cavity shortwave radiometer solid model cross-section a d photograph, top and bottom panels, resp ctively.", + "texts": [ + " The VACNT forests used in RAVAN were grown at the Johns Hopkins University Applied Physics Laboratory (JHU/APL) using water-assisted chemical vapor deposition with ethylene as the carbon feedstock on silicon wafers covered with an iron catalyst layer. Post-growth vapor modifications and plasma etching were then performed to decrease the material\u2019s reflectivity further. We experimented with a number of processes with varying VACNT forest thickness, single/multiple growths, and a range of post-growth modification severity, in order to optimize the performance for RAVAN. The infrared reflectivity indicative of early experiments and the final RAVAN flight VACNT radiometer absorbers are shown in Figure 3. The RAVAN VACNTs stay below a target 0.1% reflectivity out to about 13 \u00b5m. We found agreement with literature techniques12 that increasing the forest thickness to 1 mm and a more aggressive O2 plasma etching post-growth each improved the infrared performance compared to our early experiments. Figure 3: Spectral reflectivity of VACNT forests produced with two different processes. Both are single growths, but the latter (b) was grown to a greater thickness (1 mm) and with more aggressive post-growth modification. Figure 2. Scanning electron micrograph of a Vertically Aligned Carbon Nanotube (VACNT) forest, similar to those flown on RAVAN. The image is an edge-on view or cross section of the forest. The VACNTs used in RAVAN\u2019s radiometers were grown at the Johns Hopkins University Applied Physics Laboratory by a process described in Appendix A. The growth and post-growth treatment procedure was developed over time and refined for RAVAN. Our reflectivity target is 10\u22123. For RAVAN we generated a library of VACNT growths (and post-growth treatments) and then selected the best performing (blackest out to 16 \u00b5m). Figure 3 shows the progress made toward our reflectivity goal. Our initial attempts, with a 200-\u00b5m tall forest, were not satisfactory. We experimented with forests of different heights and with multiple stages of growth (where an intern l discontinuity along the CNTs is introduced by stopping and restarting the carbon gas flow mid-growth), and we found that the best results were obtained with a 1000-\u00b5m (1-mm) growth. Tall r growths were not practical given the internal geometry of the radiometer heads. Th 1-mm VACNTs barely met our reflectivity target, so we turned to the ost-growth treatment. We employed an aggressive oxygen plasma etch [32]. This resulted in reflect viti s below 10\u22123 at wavelengths out to 13 \u00b5m. Incidentally, we found that the aggressive oxygen etch was less effecti e for \u201cblackening\u201d the initial, shorter VACNT forests. Figure 3. VACNT reflectivity as measured at APL for several growth processes and post-growth modifications. The 0.1% reflectivity target is indicated with horizonal orange lines in each panel. The colored (red, blue, green) lines are the raw data (black) smoothed over wavelength. (a) Initial process: 200-\u00b5m-tall VACNT forest. (b) 1000-\u00b5m (1-mm)-tall forest. (c) 1000-\u00b5m-tall forest growth, with the addition of aggressive post-growth oxygen plasma etching. 2.1.2. Radiometer Design The broadband radiometers employed in RAVAN are effectively linear-response thermal detectors that sense the heating of an optical absorber, the receiver, by incident radiation", + " The first is that the gallium, gallium cell housing, and thermistor are not in perfect thermal contact, and it is possible that the beginning of the freeze is not communicated well to the thermistor, allowing the thermistor to cool below the freezing gallium. Another possibility is that the gallium supercools prior to freezing. This behavior has been noted previously. Topham et al. experienced gallium supercooling in their on-orbit International Space Station experiment evaluating the effect (if any) of microgravity on gallium phase changes [33]. In any case, gallium melts were used exclusively for RAVAN radiometer stability measurements; the freezing behavior had no effect. Remote Sens. 2019, 11, 796 10 of 29 Figure 3. Cavity shortwave radiometer solid model cross-section and photograph, top and bottom panels, respectively. Figure 4. (Top panel) Solid model cross-section of one of the two Gallium BB reference sources that is integrated into each door (light gray). The Gallium is contained by a 1-mm thick Silicon wafer (dark grey), a rubber gasket (green), and a stainless-steel cover (red). A clamp (orange) compresses the two gaskets; the lower forms a seal between the cover and Silicon wafer while the upper allows for vertical expansion of the contained volume during a freezing transition" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure2-5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure2-5-1.png", + "caption": "Figure 2-5: Relative position vector.", + "texts": [ + "1 T w o jo in t fram es w h ose orig ins are co in cid en t Since there is no translation between the two frames, only the ro tational trans form ation for the orientation m apping is performed and the fourth component of the vector is dropped. i p % DO 0 p O p _ 0 p i i n \u00b1 m \u2014 11 A m iPm = f R\u00b0 \u00b0R1 = [I] 17 where m = any point in frame i and [I] is the identity m atrix and XR\u00b0 = orientation subm atrix of *T\u00b0 W hen the point m is the origin of frame i + 1, \u00b0Pi+1 =\u00b0 R { iPi+r = \u00b0 {{Pi+1} 2 .3 .1 .2 T w o jo in t fram es w h ose orig in s are n ot co in cid en t The general transform ation including rotational and translational m apping is used (Fig. 2-5). = \u201crfV P rr 1 \u00b0R{ \u00b0Pi 'P\u201e 0 1 = \u00b0Pi + \u00b0 I P iPm = \u00b0Pi + \u00b0 { iPm} 18 when the point m is the origin of frame i + 1, \u00b0Pi+1 =\u00b0 Pi +\u00b0 {{Pi+l} 2 .3 .2 V elo c ity Similarly the numerical values of the velocity vector depend on the two frames. One in which the differentiation is performed and the other in which the results are expressed. To avoid confusion, the same notation as used for a position vector is applied. A linear velocity vector a t the point m is \u00b0v m = d(\u00b0Pm)/dt = + St) - \u00bb Pm(t))/St], where a differentiation is done w ith respect to frame 0 and expressed in frame 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001369_9fb40a0e36ab0a7e.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001369_9fb40a0e36ab0a7e.pdf-Figure2-1.png", + "caption": "Figure 2. Schematic diagram of the individual components of the developed prototype.", + "texts": [ + " These measurements based on the theoretical seed spacing and include the multiple index, miss index, quality of feed index and the precision in spacing. They recommended using these measurements for summarizing Misr J. Ag. Eng., October 2009 1755 the uniformity of seeder metering rather than meaning or sampling coefficient of variation. MATERIALS AND METHODS Prototype Description A developed single precision vacuum seeder prototype (Figure 1) consists of the following components. 1- seed box The seed box (Figure 2a) has a trapezoidal shaped in the lower part and a rectangular shaped at the upper part. The lower part is inclined 63\u00b0 from the vertical direction. The shape of the seed chamber is triangular shape and it designed to be connected with the seed box for receiving the seeds from seed box and transfer the seeds to the holes on the seed plate. Vertical seed plate and the plate of vacuum flow Three seed plates (Figure 2b) were fabricated with different hole diameters. The hole diameters were 0.8, 1.0 and 1.2 mm. The holes in each seed plate were drilled into two rows. Since the developed prototype was designed to plant two rows, the pitch circle diameters were 190 mm and 165 mm for the first and the second rows, respectively. The number of holes in each row was 80 holes. The plate of vacuum flow (Figure 2c) was fabricated from sort of plastics called (Teflon) with outer diameter of 220 mm and 8 mm thickness. Two vacuum canals were drilled into the plate to enable the developed seeder prototype to plant two rows. The cross-sectional areas of vacuum canals were 226.95 mm2 and 176.6 mm2 for the first and the second rows, respectively. Misr J. Ag. Eng., October 2009 1756 Two rigid brush-off devices were fabricated from rubber material and fixed in the back of the seeder case prated 2 mm from the pitch circle diameters of seed plate for the two rows. The two brush-off devices were curved shape with the radius of curvatures of 88 and 76 mm (Figure 2d). The dimensions of the brush-off device were 70, 75 mm length and 5 mm thickness for the first and the second rows, respectively. Depth control device The depth control device consists of two press wheels with a linkage between them. The diameter of both press wheels is 280 mm. The planting depth is changing by means of a rotating locking mechanism (Figure 1) attached with the front and rear press wheels. Furrow opener A runner-type opener (Figure 2e) with two outlets was used to enable the developed prototype to plant two rows instead of one row. The cutting edge of the opener is 20 mm width and 114 mm length. The total length of the furrow opener was 195 mm and 110 mm height. Blower (vacuum pump) The blower (vacuum pump) was developed according to the design of the Keverneland vacuum seeder blower. It was fabricated from the local plain carbon steel with 3 mm thickness. The dimensions of the blower shell and the centrifugal fan are shown in Figures (2f and 2g)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.9-1.png", + "caption": "Figure 2.9: MAV prototype of Blue Bear Systems Research Ltd. (left) and complete control board (right) (14)", + "texts": [ + " The sensor system consists of a two-axis magnetometer for compass heading sensing, a pitot-static tube and an absolute pressure sensor for altitude sensing, a different pressure sensor for dynamic pressure sensing, and a gyroscope for turn rate sensing. Fully Chapter 2: Previous work on MAV development 10 autonomous state has not been achieved yet; the MAV still needs to receive commands from the ground control station by a command uplink receiver and onboard computations are performed by two microprocessors (7). Another flying wing MAV, developed by Blue Bear Systems Research Ltd (United Kingdom), is similar to Black Widow\u2019s design. It is two times bigger than the Black Widow, with total wingspan of 30cm (Figure 2.9). Control surface is also elevons configuration. However, due to the bigger size of the MAV, it can accommodate more components than the Black Widow. The complete control board is about 10cm long, consists of a tri-axis gyroscope, a tri-axis accelerometer, absolute and differential pressure sensors, on-board and environment temperature sensors, and a GPS module (14). A team at Stellenbosch University (South Africa) built an autonomous ducted-fan UAV shown in Figure 2.10. It was named as SLADe (Surface Launched Aerial Decoy)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003512_e_download_9236_8414-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003512_e_download_9236_8414-Figure1-1.png", + "caption": "Figure 1: Assembly Design", + "texts": [ + " Assembly of Radial Engine The objective of this work is to redesign the articulated rod from the radial engine by using generative method. A reciprocating type internal combustion engine is known as a radial engine. Prior to the invention of gas turbine engines, the radial configuration was widely used for aircraft engines. Since the axes of the cylinders are coplanar, connecting rods cannot always be directly linked to the crankshaft, so the pistons are connected to the crankshaft by a master-and-articulating-rod assembly. The model of the radial engine that was produced using solid edge software can be observed in the Figure 1 and the details of individual parts are given in Table 1. 2.2. Articulated Rod The part that is focused for the design optimization is Articulated Rod. The model of Articulated Rod can be seen in the Figure 2. As mentioned earlier, the material of this part is Steel 4340, and its properties can be seen in Table 2. 2.3. Applied force calculation: In this work, the applied force on the model is the force that is acting on the connecting rod in the engine. The force that is acted on the connecting rod is involved with 3 other forces, which are force on piston due to gas pressure, force that is caused by inertia of reciprocating mass and connecting rod, and force due to friction of piston and of piston ring" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000403_citation-pdf-url_382-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000403_citation-pdf-url_382-Figure4-1.png", + "caption": "Figure 4. Tricept Robot (Neumann and Neos Robotics, 1998)", + "texts": [ + " It is a closed-loop kinematic system with parallel links and is considered to be far more rigid than that of its serial counterparts of the same size and weight. Its force-output-to-manipulator-weight-ratio is generally an order of magnitude bigger than that of most industrial robots (Liu, 1993). The same closed-loop kinematic configuration that gives its rigidity also complicates the solution of the forward kinematics in such a way that no closed-loop solution for this problem has been found (Lacaze, Tasoluk and Meystel, 1997). Tricept robot, shown in Figure 4, logically derived from the Tetrabot (Thornton, 1988), has a 3-DOF (degree of freedom) configuration of the parallel type to execute translational motions and a 3-DOF spherical wrist to execute rotational motions (Neumann and Neos Robotics, 1998). Its workspace is to be considered relatively large compared to the size of the robot. In order to further enlarge the size of the workspace, the addition of a revolute joint at the fixed base has been envisaged, introducing kinematic redundancy into the robotic manipulator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001232_f_d2me2017_02004.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001232_f_d2me2017_02004.pdf-Figure1-1.png", + "caption": "Figure 1. The pattern of rotatable balance-arm system", + "texts": [ + " Therefore, for the crane construction characteristics of transmission line tower erection, developing a new type of movable balance-weight, which not only achieves the predetermined lifting ability, but also reduces the quality of total weight, is an important issue to be solved for the construction of high voltage transmission line. 99i9iIn this paper, a new type of movable balance-weight system is proposed, which is suitable for design of different cranes. To form the design of rotatable balance-arm, the new type and structure are studied. Based on the characteristics of crane SXD50, a series of new structures are proposed, including rotatable parallelogram balancearm, latticed head and platform. Shown as Figure 1, there is small-sized vertical luffing mechanism is arranged on the platform of rotatable parallelogram balance-arm. The balance-weight is set under of platform. The balance-arm is pulled by luffing mechanism under amplitude control system in working, the movement of balance-arm makes the backward torque generated by balance-weight equal to the forward torque by working lifting-arm. This design can realize the goal of reducing the lopsided moment of crane body. \u00a9 The Authors, published by EDP Sciences", + " The minimum work angle of balance-bar is 7\u00b0, maximum is 87.5\u00b0. 4 3 5 1 2 1- Balance-arm, 2-Connect rod, 3-Platform, 4-Luffing mechanism, 5-Balance-weight Figure 2. Rotatable parallelogram balance-arm Shown as Figure 3, the upper truss is designed with opening downwards to assure the balance-arm not impact with the crane head. The lower truss has enough blank in the end to make the balance-weight pass through. 2.3 Platform of balance-arm and balance-weight MATEC Web of Conferences lifting-arm head balance-arm rotational support Figure 1. The pattern of rotatable balance-arm system The rotatable balance-arm, which is located on the rotational support, includes two parallel truss structures, four connecting rods and platform. All parts are connected by pins. As shown in Figure 2, the parallelogram structure can remain the platform horizontal and make the luffing mechanism work normally. The minimum work angle of balance-bar is 7\u00b0, maximum is 87.5\u00b0. 4 3 5 1 2 1- Balance-arm, 2-Connect rod, 3-Platform, 4-Luffing mechanism, 5-Balance-weight Figure 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003421_agritech-x_06001.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003421_agritech-x_06001.pdf-Figure6-1.png", + "caption": "Fig. 6. Heroic transmission.", + "texts": [], + "surrounding_texts": [ + "4 Conclusion\nThe design of heroic programs requires the use of various methods and tools. They include evolute construction methods, reverse engineering, finite element method, and computer modeling.\nThese methods make it possible to optimize the design of gerotor transmissions in order to achieve high efficiency and reliability. They help determine optimal transmission parameters, such as tooth shape, radii and profiles, and analyze its strength and deformations.\nComputer simulations and simulations allow virtual transmission tests, reducing the risks and costs of physical prototyping. This allows designers to develop transmissions faster and more efficiently.\nThe optimal design of heroic transmission depends on the requirements and conditions of a particular application. Designers must consider factors such as required torque, rotational speed, loads and operating conditions to create a gear that will perform its functions optimally.\nReferences\n1. I.V. Karnaukhov, E.A. Sorokin, A.A. Nikitin, V.V. Abramov, M.D. Pankiv, IOP Conference Series: Earth and Environmental Science 981, 042054 (2022)\n2. V.I. Posmetev, V.O. Nikonov, V.V. Posmetev, IOP Conference Series: Earth and Environmental Science 392, 012038 (2019)\n3. V.O. Nikonov, V.I. Posmetev, V.V. Posmetev, IOP Conference Series: Earth and Environmental Science 392, 012039 (2019)\n4. I.I. Gabitov, A.V. Negovora, M.M. Razyapov, A.A. Kozeev, R.J. Magafurov, IOP Conference Series: Materials Science and Engineering 632, 012048 (2019)\n5. Wen Jing Hu, Zheng Meng, Journal of Physics: Conference Series 1574, 012028 (2022) 6. Yuanzhi Huang, Journal of Physics: Conference Series 2143, 012048 (2021) 7. C. Khamnounsak, S. Likit, Journal of Physics: Conference Series 1380, 012018 (2019) 8. R.T. Emelyanov, A.S. Klimov, K.S. Kravtsov, I.B. Olenev, E.S. Turysheva, Journal of\nPhysics: Conference Series 1515, 042078 (2020)" + ] + }, + { + "image_filename": "designv8_17_0004506_cle_download_289_330-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004506_cle_download_289_330-Figure5-1.png", + "caption": "Figure 5. Diagram showing the basic parts of the pneumatic actuator (based on [12]).", + "texts": [ + " With the help of a muscle, it is possible to obtain a working stroke within 25% of the nominal length of the muscle [17]. Pneumatic actuators (Fig. 3) are elements that convert compressed air energy into mechanical energy. Depending on the application, they can be divided into: piston, diaphragm, bellows, plunger, bag and tube. This division is presented in Fig. 4. The design of a pneumatic actuator is much more complex than a pneumatic muscle. A typical piston air cylinder consists of a number of components as shown in Fig. 5. In recent years, there has been a lot of interest in the subject of rehabilitation robots using pneumatic actuators in their work. Many centers adapt already existing robots to the requirements of rehabilitation. Others, in turn, try to create completely new devices. The aim of the research is to help the therapist in his physical work and to reduce the costs of rehabilitation. Many robots, including service and industrial robots, have been developed to help people [5]. Work on the implementation of therapeutic robots to improve human limbs is constantly ongoing (PhysiotherapyRobot, Berkeley, Therapy Robot MiT-Manus, ARM Guide, VA Palo Alto HCS)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001252_O201620240595779.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001252_O201620240595779.pdf-Figure7-1.png", + "caption": "Fig. 7. Cross section of Inset LSPMSM rotor", + "texts": [ + " Numerical results are calculated using the FEA by Ansoft\u2019s Maxwell 2D. The magnet shifting method presented in previous section is applied to a 4 pole 24 slot inset LSPMS motor with the parameters shown in Table 1. The machine has an integer number of slots per pole and as a result by using Eq. (11) the magnet shift angle is calculated as 7.5 degrees. By placing every two adjacent magnets in a group, each magnet is being shifted by 7.5 degree relative to the other magnet in the group, as shown in Fig. 7. Cogging torque profile of the LSPMS motor with 882 \u2502 J Electr Eng Technol.2016; 11(4): 878-888 normal rotor and also cogging torque of the LSPMS motor with shifted PMs have been obtained from 2-D FEA and results are shown in Fig. 8 for comparison. As shown the peak to peak cogging torque for LSPMS motor with uniformly distributed magnet on the rotor is calculated as 2.19 N.m. This value for the LSPMS motor with shifted magnet rotor is calculated as 0.52 N.m which shows a reduction of 76% in cogging torque" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure4-1.png", + "caption": "Figure 4: Cloud Chart of Magnetic Field Intensity", + "texts": [ + " Therefore, appropriate clearances and magnetic tooth thickness should be selected. This way, the transmission effect is the best, and the torque generated by magnetic field coupling is the most ideal, which can achieve the maximum output torque. According to the simulation experiment analysis, the model diagram of the magnetic planetary gear with the best parameters is obtained, and the distribution nephogram of magnetic field intensity and magnetic induction intensity is obtained, as shown in Figure 4 and Figure 5 respectively. Published by Francis Academic Press, UK -22- Magnetize the driving wheel and obtain the torque analysis diagram of the driven wheel. The torque varies in a function, with the minimum value being when the N pole is relative to the S pole. At this time, the N pole generates a downward magnetic field line, while the S pole generates an upward magnetic field line. At this time, the magnetic force is not circulating; When the maximum value is two N poles facing each other, the magnetic field lines of the two magnetic blocks are all downward, and when passing through the magnetic block, the magnetic force direction is upward" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure59-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure59-1.png", + "caption": "FIGURE 59. Configuration of the proposed antenna [41].", + "texts": [ + " 58(c) illustrates the characteristic currents and modal radiation patterns of these modes at the resonant frequencies. Else, if the resonant frequencies are beyond the maximum range of 43 GHz, this frequencywill be chosen. It is observed that themodes 1 and 2 are a pair of degenerated modes, which combination provides vertically and horizontally polarized radiations at boresight. All the other modes presented are out-of-phase characteristic currents with hollow radiation patterns. In [41], CMAwas used effectively in designing an antenna shown in Fig. 59 by understanding its operating mechanisms and guiding its excitation placement and optimization. The antenna consists of three metallic layers (from top to bottom), a metasurface (P-P\u2019 plane), a ground plane (G-G\u2019 plane), and a microstrip line (F-F\u2019 plane). The metasurface is located on the top of a 3.454 mm -thick grounded dielectric layer as shown in Fig. 60(a) whereas the first four CMs are shown in Fig. 60(b). As observed, mode 1 and 2 are a pair of resonant modes at 5.9 GHzwith the sameMSs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure2-1.png", + "caption": "Figure 2: Schematic diagram of magnetic gear transmission principle", + "texts": [], + "surrounding_texts": [ + "Published by Francis Academic Press, UK -18-\nKeywords: Magnetic planetary gears, Axial coupling, Static magnetic field, Torque\nAmong various transmission forms, gear transmission is the most widely used in modern machinery. However, traditional gears are usually meshed contact transmission, which has many failure forms and is also affected by processing and installation accuracy, resulting in problems such as high vibration and noise. In response to the problems existing in meshing contact gears, researchers have proposed the concept of non-contact transmission. The invention of magnetic gears has changed the transmission mode of gears. Through its advantages of meshing clearance, magnetic gears have changed power transmission to non-contact transmission torque [1], effectively solving a series of problems caused by traditional contact gear transmission.\nMagnetic gears use magnetic force to couple and transmit torque to gears, which has the following advantages [2]: Firstly, magnetic gear transmission has the advantages of no friction, low noise during operation, and low vibration during operation; Second, this structure is suitable for situations where there is no lubrication, high reliability is required, and maintenance is difficult after work; Finally, simple structure for non-contact transmission.\nThe development of magnetic gears has undergone a long period of sedimentation. In 1987, Japanese scholars S. Kikuchi and K. Tsurumoto put forward the involute structure. The transmission torque of this structure was improved by optimizing the parameters such as pole number, pressure angle, transmission ratio, center distance, air gap, etc., and the structure of the magnetic gear was designed as an involute [3]. In 2004, Professor D. Howe from the University of Sheffield in the United Kingdom proposed a new type of magnetic gear based on the principle of magnetic field modulation. Subsequently, Professor D. Howe proposed a magnetic field modulated magnetic gear structure in the literature, which consists of linear and axial structures, and introduced the structure and working principle [4-6]. K. from the University of Hong Kong T. Chau, envisioning the application of magnetic gears in large-scale wind power systems and electric vehicles, replacing mechanical gearboxes and transmissions with new types of magnetic gears, and adopting a coaxial concentric structure to combine the generator with magnetic gears [7-8].\nNowadays, the development of magnetic gear technology is becoming mature [9], and single pair magnetic gear transmission technology has been widely applied. However, for magnetic planetary gears, theoretical research is still not systematic and in-depth enough. Magnetic planetary gear transmission", + "Published by Francis Academic Press, UK -19-\nbelongs to a type of axial transmission, and its structural advantage is that through secondary gear transmission, not only can the torque generated during power transmission be divided into power, but also the input and output shafts are in the same horizontal line; Moreover, it has the characteristic of non-contact transmission, which reduces space occupation and improves transmission efficiency compared to traditional mechanical gears. In order to improve the feasibility of the application of alternating magnetic planetary gears, Maxwell simulation software is used in this article to analyze and study the characteristics of magnetic planetary gears.\nDesign a magnetic planetary gear using neodymium iron boron material as the magnetic block, which has extremely high magnetic energy product and coercive force, making it difficult to demagnetize and ensuring stable torque transmission performance. The support material is stainless steel, which has magnetic properties similar to vacuum and almost no magnetic conductivity. The designed magnetic planetary gear is shown in Figure 1 below.\nThe main application of magnetic planetary gear transmission is the principle of magnetic field theory, which states that the same type repels each other and the opposite type attracts each other. When the driving wheel and the driven wheel are matched, the magnetic poles of the magnetic teeth are opposite, and the adjacent magnetic poles of the same gear are different. The magnetic field generated during operation generates gravity, which changes in a sine function. During operation, the transmission torque is provided by the tangential component force in the direction of the coupling force. The torque generated in the coupling area increases, decreases, and disappears with the rotation of the magnetic driving wheel, and the corresponding magnetic coupling transmission cycle disappears, decreases, increases, and generates, Two pairs of magnetic teeth form a complementary relationship, so that the active wheel drives the driven wheel to transmit stable torque.\nThe transmission principle of the designed magnetic planetary gear is that the sun gear is magnetized by the excitation of the motor, and according to the magnetic theory of same-sex repulsion and opposite-sex attraction, the torque is transmitted to the planet gear for revolution[10]. The planet rotates while cooperating with the gear ring for revolution, and the output torque is transmitted to the planet carrier to complete the torque output of the device. The feasibility of designing a new type of transmission device based on ferromagnetic theory has also been demonstrated in the process of a series of planetary gear train transmissions.", + "Published by Francis Academic Press, UK -20-\nThe solver used in this article is a static field, which generates a constant magnetic field excited by a constant excitation source of a permanent magnet [11]. In the static excitation formula, linear and nonlinear materials can be solved, and the magnetic potential A satisfies the following equation:\n\ud835\udc3d\ud835\udc3d\ud835\udc67\ud835\udc67(\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66) = \ud835\udefb\ud835\udefb \u00d7 \ufffd 1\n\ud835\udf07\ud835\udf07\ud835\udc5f\ud835\udc5f\ud835\udf07\ud835\udf070 [\ud835\udefb\ud835\udefb \u00d7 \ud835\udc34\ud835\udc34\ud835\udc67\ud835\udc67(\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66)]\ufffd (1)\nIn the formula, Az (x, y) is the component of the vector magnetic potential on the Z-axis, and Jz (x, y) is the current density of the current flow cross-section, \u03bcr is the relative magnetic permeability of the material in the solution domain, \u03bc0 is the magnetic permeability of the material in vacuum.\nAccording to Ampere's loop law in a static magnetic field:\n\u2207 \u00d7 H = J (2)\nAccording to Maxwell's equation:\n\ufffd \u2207\u00d7B=0\nH= B\n\u03bcr\u03bc0\n(3)\nObtain:\n\u2207\u00d7\ufffd B\n\u03bcr\u03bc0 \ufffd = \ud835\udc3d\ud835\udc3d (4)\nBy B=\u0394 \u00d7 A can obtain:\n\u2207\u00d7\ufffd 1\n\u03bcr\u03bc0 \u2207\u00d7A\ufffd = \ud835\udc3d\ud835\udc3d (5)\nCalculate the vector magnetic potential A based on the above calculation formula. Substitute the following formula:\n\ufffd B=\u2207\u00d7A\nH= B\n\u03bcr\u03bc0\n(6)\nThe final result is that the magnetic induction intensity of the static magnetic field is equal to the magnetic field intensity.\nThe theory used in Maxwell to calculate static torque is the virtual work theory, and the expression for torque is:\n\ud835\udc47\ud835\udc47 = \ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51(\ud835\udf03\ud835\udf03, \ud835\udc56\ud835\udc56)\n\ud835\udc51\ud835\udc51\ud835\udf03\ud835\udf03 \ufffd \ud835\udc56\ud835\udc56= \ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\n= \ud835\udf15\ud835\udf15 \ud835\udf15\ud835\udf15\ud835\udf03\ud835\udf03 \ufffd\ufffd \ufffd\ufffd \ud835\udc35\ud835\udc35 \ud835\udc3b\ud835\udc3b 0 \u22c5 \ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ufffd\ud835\udc51\ud835\udc51 \ud835\udc49\ud835\udc49 \ud835\udc49\ud835\udc49\ufffd (7)\nIn the equation, W\uff08 \u03b8, i) is the magnetic field energy storage of the system, and i is a constant current.\nSave the assembly model in Solid Works in an. step file format that Maxwell can open, open the 3D model simulation solver in Maxwell software, set the corresponding solution type, import the required 3D model of Solid Works into Maxwell simulation software, and generative model. Set the material of the material, the magnetic block is made of neodymium iron boron material, and the N and S poles are staggered; The supporting device is made of stainless steel material, and its properties do not affect magnetism, keeping the magnetic field strength H and magnetic induction strength B continuous. The boundary condition is set to the balloon boundary, and the boundary is set to infinity. Divide the mesh, select a triangular mesh to divide the model, and set the triangle edge length to 8mm. Finally, the vector magnetic potential A is used for solving. The obtained modeling parameters are shown in Table 1, finite element modeling is shown in Figure 3." + ] + }, + { + "image_filename": "designv8_17_0000904_cle_download_386_285-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000904_cle_download_386_285-Figure2-1.png", + "caption": "Figure 2: Configuration of the dual-band printed inverted-F antenna. (a) Top view. (b) Cross sectional.", + "texts": [ + " To obtain a planar inverted F antenna, the thin top wire of the inverted F is replaced by planar elements [1], [15]. Like PILA, PIFA also consists of a ground plane, radiator, feed line, and short pin. To reduce the length of the antenna, the top radiating patch plane is folded at one edge of the patch and shortened to the base plane [1], [14], [15]. A dual-band PIFA antenna is proposed [10] to cover the frequency bands of 2.50-2.62 GHz and 5.28\u20135.78 GHz for WLAN applications, and the antenna is designed by selecting the parameters l1a,l1b,h1,l2a,l2b,h2 , and line width as shown in Figure 2(a). The antenna is designed on an FR-4 (Panasonic R-1705) substrate, and the antenna is fed through a 50 microstrip line with a signal line of 3 millimeters wide. The antenna structure consists of two F-shaped patterns nested in the top metal layer. Shorter elements are used for higher frequency bands and longer ones for lower bands. Two via holes with a diameter of 1.27 mm are used to connect the top and bottom metal layers. The Sub-Miniature version A (SMA) connector is attached to the edge of the substrate (shown in Figure 2(b)) used for measurement. The antenna structure occupies a board dimension area of 30 \u00d7 22 \u00d7 1.57 mm3. Vol. 01, No. 01, December 2022 17 Another PIFA antenna is proposed [11], as illustrated in Figure 3(a), which depicts the fabrication structure and geometry of a capacitively coupled dual-band PIFA antenna. The antenna consists of a metal top plane and a ground plane system, It is excited by a single probe feed connected to a square capacitive strip. In the upper plane, the antenna also consists of an L-shaped slotted line, and it is suspended above the ground plane and shortened to the ground plane by a short metal plane" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003418_ice_Designed_for.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003418_ice_Designed_for.pdf-Figure4-1.png", + "caption": "Figure 4. Design of prototype a device for offsetting tensile forces with rope sensor", + "texts": [ + " This different loading of the individual carrier ropes leads to an uneven wear of the friction disc grooves and different wear of the individual carrier ropes. As for this condition [3] considers and requires the elevator contractor to test that the load is evenly distributed into all cross-sections of the carrier ropes. FORCES IN ROPES Several principles are currently known on the consumer market allowing subtraction of the acting tensile force in the ropes and eventually offsetting the different tensile force values in the individual ropes. Well known is the principle of a rope sensor, see Figure 4, e.g. [4], measuring the tensile force in the rope using the principle of bending deformation of the beam loaded with single force, see Figure 1. This device uses bodies with a measuring member and three contact points in a plane. The measured rope runs between these points. The two outside contact points on the device body, located at a known distance apart, serve as support of the measured rope. The third contact point is located at the midpoint distance of the pitch of the two outside contact points, which is distanced by the h value [m] from the axes intersection of the outside contact points, se Figure 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003418_ice_Designed_for.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003418_ice_Designed_for.pdf-Figure1-1.png", + "caption": "Figure 1. Rope sensor enables recording of tensile force in the rope [6]", + "texts": [ + " As for this condition [3] considers and requires the elevator contractor to test that the load is evenly distributed into all cross-sections of the carrier ropes. FORCES IN ROPES Several principles are currently known on the consumer market allowing subtraction of the acting tensile force in the ropes and eventually offsetting the different tensile force values in the individual ropes. Well known is the principle of a rope sensor, see Figure 4, e.g. [4], measuring the tensile force in the rope using the principle of bending deformation of the beam loaded with single force, see Figure 1. This device uses bodies with a measuring member and three contact points in a plane. The measured rope runs between these points. The two outside contact points on the device body, located at a known distance apart, serve as support of the measured rope. The third contact point is located at the midpoint distance of the pitch of the two outside contact points, which is distanced by the h value [m] from the axes intersection of the outside contact points, se Figure 2. Due to the acting tensile force T [N] in the rope, a compressive force F [N] is then exerted on the third contact point, see the relation (1), which is recorded by the measuring sensor. ( )F = 2. T. sin [N]\u03b1 (1) According to Figure 2, the following dependencies can be determined between the relevant parameters: = arctg(d/b) = arctg [(h + 2. R. cos)/(a - 2. R.sin)] d = h + 2. c = h + 2. R. cos [m] c = R. cos [m] b = a - 2. e = a - 2. R. sin [m] e = R. sin [m] (2) Obtaining the value of the tensile force in the carrier rope using a rope sensor, see Figure 1, is a commonly used method, however, it has certain limitations and drawbacks. Under certain circumstances, the basic limitation is the way of obtaining tensile force values in the individual ropes of rope suspensions that use a higher number of ropes. As a result of the lead of the individual ropes into the grooves in the friction disc, it is required that the longitudinal axes of the carrier ropes are lead into the axes of the grooves of the friction disc at a maximum allowed, relatively small angle of attack" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000535_school_dissertations-Figure4.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000535_school_dissertations-Figure4.4-1.png", + "caption": "Figure 4.4 The photo of the bicrystalline specimen surface with grain boundary position shown.", + "texts": [ + " It was grown from the melt with the Bridgman technique (Vukelic et al., 2009, 2011). It was mounted on a three circle goniometer and the orientations of its crystals were determined using Laue diffraction to within \u00b11\u00b0. The grain boundary between the crystals was a CSL \u03a39 symmetrical tilt-type with the [110] direction parallel to the tilt axis of the adjoining grains. The specimen was cut from the as-grown bicrystal using a wire electro-discharge machine (EDM). A photo of the specimen surface is presented in Figure 4.4 and the grain boundary shown was determined during the manufacturing procedures. The other specimen is a copper bicrystal purchased in the supplying market. 48 To capture the ISE, one needs to verify the quality of the specimen, especially the surface roughness and oxidation layer. The oxidation layer is an unavoidable phenomenon caused by the chemical reaction between the surface of the specimen and the oxygen in the air. To limit the influence of the oxidation layer, one needs to perform the indentation tests as soon as possible after polishing the specimen" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure8-1.png", + "caption": "Figure 8. (a). 2D shape of target RFPM motor; (b) 3D shape of target RFPM motor.", + "texts": [ + " Among them, the NS type rotor has a structure in which the permanent magnetization direction of the two-sided rotor is opposite. One rotor permanent magnet magnetic flux flow to the opposite rotor. The advantage is that there is no magnetic flux flowing through the Stator back-yoke, making the design easier. Furthermore, by removing the stator backyoke, manufacturing can be performed in a split core structure, and the fill factor can be enhanced [26\u201330]. In this paper, 500 W SPMSM was selected as the target motor among the motors for robot joints. Figure 8a,b show the shape of the target RFPM motor. Table 1 shows the specifications of the target RFPM motor. The motor\u2019s back electromotive force (BEMF) and total harmonic distortion (THD) can be identified through a no-load analysis. As the THD decreases, the vibration noise of the motor decreases. The no-load analysis is based on 1000 rpm. Figure 9 shows the BEMF waveform of the target RFPM motor. The THD of the target RFPM motor obtained from Figure 9 is 5.51%. The smaller the THD, the more sinusoidal the waveform is" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003507_jmrsp.2023.48.62.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003507_jmrsp.2023.48.62.pdf-Figure11-1.png", + "caption": "Fig. 11: ANSYS FEA modal deflection analysis for the TLFM link", + "texts": [ + " Performing a modal Finite Element Analysis (FEA) on both flexible links (Table 1 for the geometrical parameters of the links) yielded the conclusion that the first two modes of vibration were the most dominant. Thus, using Eq. 34 and considering only two modes of vibration for each link, the mathematical model block diagram was constructed in LabVIEW control and simulation environment. Coupled with actuator dynamics, the mathematical model allowed for the preliminary development of both trajectory tracking and vibration suppression FLCs. The FEA results are presented in Fig. 11 and Table 7. Sinusoidal trajectory tracking is investigated in this study since it reflects common repetitive back-and-forth applications. As such, the actual trajectory of both links in a constructive interference case is shown in Fig. 12. Both cases in Figs. 12-13 are conducted at 0.2 cycles per second (cps) with a 100 g payload. Figure 13 shows the results of a destructive interference case, where destructive interference refers to the trajectories of both links being out of phase by 180. Figure 15 shows that the destructive test case resulted in a more uniform strain error" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure69-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure69-1.png", + "caption": "Figure 69 : M\u00e9thode de simulation et de calculs des coefficients de r\u00e9flexion actifs dans le cas de deux sources.", + "texts": [ + " Page 61 sur 182 Dans un premier temps, il est n\u00e9cessaire de valider les m\u00e9thodes de simulation et de calcul des quatre coefficients de r\u00e9flexion actifs (\u03931, \u03932, \u03933 et \u03934) de chacune des sources. En effet, ces coefficients de r\u00e9flexion actifs doivent \u00eatre calcul\u00e9s \u00e0 partir des coefficients de r\u00e9flexion (Sij) obtenus par le logiciel HFSS au niveau de chacun des ports d\u00e9finis. Un essai avec deux sources a d\u2019abord \u00e9t\u00e9 r\u00e9alis\u00e9 et valid\u00e9. Puis, l\u2019essai avec quatre sources a \u00e9t\u00e9 valid\u00e9. Dans tous les cas, les simulations se font en r\u00e9seau infini-p\u00e9riodique. \u2022 Dans le cas de deux sources : Dans le cas o\u00f9 nous consid\u00e9rons deux sources bande X, comme pr\u00e9sent\u00e9 sur la Figure 69, il y a deux ports d\u2019excitation, un par source bande X. Le logiciel HFSS nous donne donc 2x2 = 4 param\u00e8tres S correspondant aux coefficients de transmissions et de r\u00e9flexion de ces deux ports : S12, S21, S11 et S22. C\u2019est \u00e0 partir de ces quatre param\u00e8tres S que nous reconstruisons les deux coefficients de r\u00e9flexion actifs \u03931 et \u03932 au niveau de chacun des deux ports. Les deux formules permettant de calculer ces deux coefficients de r\u00e9flexion actifs sont donn\u00e9es dans la suite, dans 4.1. L\u2019angle de d\u00e9pointage est not\u00e9 \u03b8scan et il y a un d\u00e9phasage \u03b1 entre deux sources successives" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000870__download_10160_3620-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000870__download_10160_3620-Figure7-1.png", + "caption": "Fig 7: a) Base antenna with a ground slot\u2019s) Back view of proposed antenna\u2019s) Front view of proposed antenna.", + "texts": [], + "surrounding_texts": [ + "Now-a-days, wireless technologies had a rapid growth so that antenna must be in a compact size and should have a wide bandwidth. Microstrip patch antenna is advantageous because of its simple structure, stable gain, low profile, low cost [1] and it can support multiple frequency bands which can be dual or triple. Microstrip antennas are used in airborne and spacecraft systems because there requires dielectric cover over the radiating element to give protection against the heat, environment and physical damage [9]. A patch antenna consists of radiating patch on one side and ground plane on the other side, which is fed with microstrip line. The width of conducting strip line is smaller as compared to patch used. The dielectric material of thick size and with lower dielectric constant will improve the antenna performance [3]. As the microstrip patch antenna is of small size, the wideband characteristics can be achieved with the appropriate choice of parameter. The monopole antenna is used for improvement in the frequency bandwidth and the radiation properties of the antenna [6]. A simple slot on the ground plane under the fed line has been used as the base antenna for maximum utilization of bandwidth and to improve the impedance matching of the antenna so that it operates in UWB range [2]. Ultrawideband is a technology that utilizes very low energy level for short-range and covers a large portion of radio spectrum [5]. The ground slots can be of many shapes such as rectangular, circular, hexagonal etc. out of which we have used rectangular shaped ground slot [1]. In the design of microstrip fed monopole antenna the use of serrations has enhanced the bandwidth. A serrated antenna has a saw-toothed shape with material being cut is in contact with some small points and this serrated edge are preferred when using tough and thick materials [8]. A part of edges on the square patch are truncated to get a serrated edged square patch the antenna is designed by placing serrations on single, double, three sides. Ten serrations are examined in this work by changing the number of serrated edges. The serrations are used to improve the isolation and radiation characteristics of the elements [10]. In this paper, attempts are made by varying number of serrations for the UWB antenna. The performance of antenna is simulated using commercial Electro Magnetic tool (HFSS) [4]. One of the serious issue that hinders the performance of the antenna is the isolation between the two feed locations, input and output. Decimating this coupling between the feed locations represents a significant improvement in the performance of antenna because it eliminates the unwanted feedback, providing a stable output, thus, improving overall performance of the antenna [11]. The result of study on the effect the using different number of serrations to evaluate the performance of an UWB antenna in terms of impedance bandwidth, return loss, gain (peak and+ average)." + ] + }, + { + "image_filename": "designv8_17_0003560_robt.2020.590076_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003560_robt.2020.590076_pdf-Figure2-1.png", + "caption": "FIGURE 2 | The fin-ray finger with its design parameters and its deformation during interaction with object.", + "texts": [ + " This quality function is more generic and can be extend to many other soft robots with different kinematics. As shown in Figure 1, the problem can be formulated as finding a mapping from a given task to a desired hand design, namely M : T \u2192 H(\u03c6), where T and H represent the task requirement and hand design space, respectively. The task requirement in this paper is chosen as the quality of the final grasp and the hand design space depend on the design parameters of the hand \u03c6. A soft fin-ray finger is chosen as an example in this paper (see Figure 2), where the design parameters \u03c6 include the thickness a and the spacing distance h. Note that some other more complex parameters (angle, morphology) are not considered here for simplicity. During the hand object interaction, different selection of the design parameters will lead to different level of deformation and therefore different task performance. To compute these deformations, a dataset of the hand deformation is collected in simulation using Ansys Workbench R\u00a9. The parameters a, h, and the applied force F are all chosen with fixed spacing and range. The material we used is TPU 95A with Young\u2019s modulus 26 MPa, yield strength 8.6 MPa, breaking strength 39 MPa, and Poisson ratio 0.481. Some of the results are shown in Figure 2. After the simulations, a dataset of Nh hand feature is collected as: Dh = {Fi f , hi, ai, di, xin, y i n, z i n} i=1..Nh , where superscript represents the order of the hands. Fi f represents the contact force between the hand and the object, and di represents the maximal deformation. xin, y i n, z i n represents the coordinates of the nodes Pn after deformation as shown in Figure 3. As discussed above, note that some other analytical methods can be also used here to compute the deformation as presented in Fang et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003946_al-04249580_document-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003946_al-04249580_document-Figure7-1.png", + "caption": "Fig. 7: Side view of the EM geometry.", + "texts": [ + " In order to facilitate the manufacturing and testing process of the large dimensions (7m aperture) RA, a reduced-size engineering model (EM) was developed. The EM consists of two out of the nine panels of the RA, with modified optics. This allows it to fit into the near-field test range (NFTR) located in Thales Alenia Space facilities in Toulouse. The primary objectives of the EM are to validate the design and technological processes of the large deployable RA for future product deployment. The following section provides an overview of the EM\u2019s features. The EM comprises two panels with modified optics, as shown in Figure 7. This necessitates a new RF layout design and optimization from scratch. The relative inclination between the two panels is maintained, as well as the focal distance. The panels are separated by a gap of 10mm, with 5mm coplanar alignment for each panel. The offset distance has been reduced from 5300 mm to 3100 mm, resulting in a corresponding decrease in the offset angle. The same feed used for the nine-panel RA is retained, but to achieve an almost uniform taper at the panel borders, the feed is directed towards the junction between the two panels, introducing two additional consecutive feed reference frame rotations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003781_f_version_1680255727-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003781_f_version_1680255727-Figure6-1.png", + "caption": "Figure 6. Pendulum\u2013cam contour line design.", + "texts": [ + " (13) where LOF is the length of the connecting rod OF; LFG is the length of the connecting rod FG; LEH is the length of the connecting rod EH; LEG is the length of the connecting rod EG; LEF is the distance between EFs in the graph; \u03b8 is the initial installation angle of the connecting rod FG; \u03b81\u2014initial installation angle of the connecting rod OF; \u03b82 is the angle between the EG rod and the EH rod; \u03b4 is the angle of rotation of the E point; \u03b41 is the acute angle between EF and the horizontal direction; and \u03b42 is the angle between the EF and FG rod. As shown in Figure 6, the center of the cam, point O, was the origin of the coordinate axis, and the line between point O and the axis of the oscillating pusher, E, was the x-axis. Further, EH was the initial position of the pendulum. If the cam was fixed, point E was rotated clockwise around center O, and point H was swung relative to point E according to the above displacement equation. Subsequently, the motion curve of point H was recorded after one week of rotation of point E to derive the profile curve of the cam. The displacement equation for the clockwise rotation of point H around point O is as follows:{ XH0 = LOE cos(\u2212\u03b4) + LEH cos(\u03c0 \u2212 \u03b4 \u2212 \u03d5 \u2212 \u03d50) YH0 = LOE sin(\u2212\u03b4) + LEH sin(\u03c0 \u2212 \u03b4 \u2212 \u03d5 \u2212 \u03d50) , (14) \u03b4 = \u03c9t, (15) \u03d50 + \u03d5 = \u03c0 \u2212 arctan( YH \u2212 YE XH \u2212 XE ). (16) where \u03d5 is the angular displacement of the pendulum EH angular displacement, and \u03d50 is the initial installation angle of the pendulum EH. Agriculture 2023, 13, 810 8 of 18 Agriculture 2023, 13, x FOR PEER REVIEW 9 of 18 Figure 6. Pendulum\u2013cam contour line design. 2.2. Optimization Objectives and Variables After reviewing the relevant literature, to improve the success rate of the seedling picking mechanism and adapt it to the characteristics of a variety of vegetables in the seedling tray, the trajectory of the seedling picking mechanism must be optimized. The optimization objectives include the following five points [17,23]. 1. The trajectory of the withdrawal of the seedling needle from the seedling tray should be approximately straight, and as vertical as possible with the cavity tray" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004430_.srce.hr_file_311135-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004430_.srce.hr_file_311135-Figure2-1.png", + "caption": "Figure 2 Circular plate model", + "texts": [ + " Maxwell stress is represented by the magnetic pull force acting between the rotor disks and can be calculated as magnetic pressure multiplied by active surface area of all PMs (SPM) as shown in [1]: ( ) 2 d PM 02 B F S \u00b5 = (4) ( )2 2 PM out in \u03c0 4iS D D\u03b1= \u2212 (5) PM 2 360i p\u03b1 \u03b1 = (6) where F is the pull force between opposite PMs, \u03b1PM the angle of PMs, \u03b1i the coefficient, which is calculated as angle of PMs multiplied by the number of PMs per rotor disk (poles) and divided by 360 degrees, and Dout and Din are the outer and inner diameters of PMs, respectively. In [13], the authors present equations for various types of loads on a circular plate where the case suitable for rotor disks of AFPMM with surface mounted PMs is presented in Fig. 2. Equations for deflection calculations are [12-14]: 2 3 4 r r r a rb 2 b 3 11 a a ay M C Q C q L D D D = + + (7) ( ) 2 2 29r rb r 0 17 8 r r2 CqaM a r L C a b \u2212 = \u2212 \u2212 (8) ( )2 2 b r 0 r qQ a r 2b = \u2212 (9) 2 r r 2 r r 1 1 1 2ln 4 b aC a b = \u2212 + (10) 2 2 r r r r 3 r r r r 1 ln 1 4 b b a bC a a b a = + + \u2212 (11) ( ) 2 r 8 r 1 1 1 2 bC v v a = + + \u2212 (12) 2 r r r 9 r r r 1 1ln 1 2 4 b a bv vC a b a + \u2212 = + \u2212 (13) 3 212(1 ) EtD v = \u2212 (14) ( ) 4 0 17 r 2 0 r r 0 1 11 1 4 4 1 1 ln rvL a r av a r \u2212 = \u2212 \u2212 \u2212 \u2212 + + (15) 2 4 0 0 11 r r 2 2 0 0 r r r 0 1 1 4 5 64 4 2 ln r r L a a r r a a a r = + \u2212 \u2212 \u2212 + (16) where: ya is the deflection of the rotor disk, Mrb the bending moment, ar the outer radius of the rotor disk, br the inner radius of the rotor disk, r0 the radial location of unit line loading or start of a distributed load, D the stiffness factor of the material, Qb the unit shear force (force per unit of circumferential length), and q the magnetic pressure (or Maxwell stress)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002418__32_5_32_32_456__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002418__32_5_32_32_456__pdf-Figure8-1.png", + "caption": "Fig. 8 Socket and hand holder", + "texts": [ + " 7\u306b\u793a\u3059\uff0e\u307e\u305a\uff0c\u64cd\u4f5c\u3092\u884c \u3046\u524d\u306b\u30e6\u30fc\u30b6\u306b\u5408\u308f\u305b\u3066\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u3092\u884c\u3046\uff0e\u30cf\u30f3\u30c9\u672c \u4f53\u306e\u30b9\u30a4\u30c3\u30c1\u3092\u9577\u62bc\u3057\u3059\u308b\u3068\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u958b\u59cb\u3055\u308c\u308b\uff0e \u306f\u3058\u3081\u306b\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u524d\u8155\u306b\u88c5\u7740\u3057\u305f\u72b6\u614b\u3067\u30b9\u30a4\u30c3\u30c1\u3092\u62bc\u3057\uff0c \u7b4b\u53ce\u7e2e\u3057\u3066\u3044\u306a\u3044\u5e73\u5e38\u6642\u306e\u30bb\u30f3\u30b5\u5024\u3092 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3057\uff0c \u305d\u306e\u5e73\u5747\u5024 Xrest \u3092\u8a08\u7b97\u3059\u308b\uff0e\u6b21\u306b\uff0c\u6700\u5927\u306b\u7b4b\u53ce\u7e2e\u3057\u305f\u72b6\u614b\u3067 \u30b9\u30a4\u30c3\u30c1\u3092\u518d\u5ea6\u62bc\u3059\u3068\uff0c\u30bb\u30f3\u30b5\u5024\u304c 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3055\u308c\uff0c \u305d\u306e\u5e73\u5747\u5024 Xmax \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e\u6b21\u306b\uff0cXmax \u3068 Xrest \u306e\u5dee\u5206 Xdif \u3092\u6b21\u5f0f\u3067\u8a08\u7b97\u3059\u308b\uff0e Xdif = Xmax \u2212Xrest \uff081\uff09 \u3053\u306e Xdif \u3068\u6307\u304c\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5 \u30c8\u306e\u6700\u5927\u7e70\u308a\u51fa\u3057\u91cf Lmax \u3092\u7528\u3044\u3066\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u99c6\u52d5\u30d1\u30e9\u30e1\u30fc \u30bf R \u3092\u6c7a\u5b9a\u3059\u308b\uff0e R = Lmax Xdif \uff082\uff09 \u4ee5\u4e0a\u3067\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u7d42\u4e86\u3059\u308b\uff0e\u3053\u306e\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7 \u30f3\u30d7\u30ed\u30bb\u30b9\u306f\uff0c3\u56de\u306e\u30b9\u30a4\u30c3\u30c1\u64cd\u4f5c\u3067\u884c\u3048\u308b\u305f\u3081\u30e6\u30fc\u30b6\u81ea\u8eab\u3067 \u884c\u3046\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u307e\u305f\uff0c3 \u79d2\u4ee5\u5185\u306b\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3 \u304c\u5b8c\u4e86\u3059\u308b\u306e\u3067\uff0c\u518d\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u6642\u9593\u3092\u5fc5\u8981\u3068\u3057\u306a\u3044\uff0e \u6b21\u306b\u64cd\u4f5c\u6642\u306b\u3064\u3044\u3066\u8aac\u660e\u3059\u308b\uff0e\u64cd\u4f5c\u6642\u306e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5e73\u6ed1\u5316 \u5f8c\u306e\u5024\u3092 xs(k)(k = 0, \u00b7 \u00b7 \u00b7 ,K) \u3068\u3059\u308b\u3068\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u30b7\u30e3\u30d5\u30c8 \u306e\u7e70\u308a\u51fa\u3057\u91cf l(k) \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e l(k) = R(xs(k)\u2212Xrest) \uff083\uff09 \u3053\u306e\u3068\u304d\uff0c\u4f55\u3089\u304b\u306e\u539f\u56e0\u306b\u3088\u308a l(k) > Lmax \u3068\u306a\u3063\u305f\u5834\u5408\u306f\uff0c l(k) = Lmax \u3068\u3057\uff0cl(k) \u306e\u5024\u3092\u6307\u4ee4\u5024\u3068\u3057\u3066\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u305f\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306b\u9001\u308b\uff0e 2. 5 \u30bd\u30b1\u30c3\u30c8\u5f62\u72b6\u3068\u30cf\u30f3\u30c9\u30db\u30eb\u30c0 Fig. 8 \u306b\u65ad\u7aef\u3092\u633f\u5165\u3059\u308b\u5de6\u624b\u7528\u306e\u30bd\u30b1\u30c3\u30c8\u3068\u30cf\u30f3\u30c9\u30db\u30eb\u30c0 \u3092\u793a\u3059\uff0e\u30bd\u30b1\u30c3\u30c8\u306e\u9060\u4f4d\u7aef\u306f\u30cf\u30f3\u30c9\u30db\u30eb\u30c0\u3068\u63a5\u7d9a\u3057\uff0c\u30cf\u30f3\u30c9\u3092 \u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201457\u2014 2014 \u5e74 6 \u6708 \u638c\u80cc\u5c48\u3059\u308b\u8ef8\u306b\u3088\u308a\u4f5c\u696d\u306e\u884c\u3044\u6613\u3044\u89d2\u5ea6\u3067\u56fa\u5b9a\u3067\u304d\u308b\uff0e\u30cf\u30f3\u30c9 \u30db\u30eb\u30c0\u306f\u30cf\u30f3\u30c9\u3092\u631f\u307f\u8fbc\u3093\u3067\u56fa\u5b9a\u3057\uff0c\u89d2\u578b\u30ea\u30c1\u30a6\u30e0\u30a4\u30aa\u30f3\u96fb\u6c60 \uff089V-Li-ion-ACSET\uff0c\u30ed\u30ef\u30fb\u30b8\u30e3\u30d1\u30f3\uff09\u306e\u30b1\u30fc\u30b9\u3082\u517c\u306d\u3066\u3044\u308b\uff0e \u30bd\u30b1\u30c3\u30c8\u306f\u6a48\u9aa8\u5074\u3068\u5c3a\u9aa8\u5074\u3092\u30bd\u30b1\u30c3\u30c8\u306e\u30d5\u30ec\u30fc\u30e0\u3067\u631f\u307f\u8fbc\u3080\u69cb \u9020\u306b\u306a\u3063\u3066\u3044\u308b\uff0e\u524d\u8155\u306e\u65ad\u9762\u3092\u3060\u5186\u3067\u8fd1\u4f3c\u3059\u308b\u3068\uff0c\u524d\u8155\u306e\u56de\u5185\u5916 \u3092\u884c\u3063\u3066\u3044\u306a\u3044\u72b6\u614b\u3067\u524d\u8155\u8fd1\u4f4d\u306b\u304a\u3051\u308b\u3060\u5186\u306e\u9577\u8fba\u306f\u77e2\u72b6\u9762\u306b \u5bfe\u3057\u3066\u5916\u5074\u65b9\u5411\u306b\u7d04 45\u25e6 \u50be\u3044\u3066\u304a\u308a\uff0c\u624b\u95a2\u7bc0\u4ed8\u8fd1\u306b\u3044\u304f\u306b\u5f93\u3063 \u3066\u50be\u304d\u304c\u6e1b\u5c11\u3057 0\u25e6 \u3068\u306a\u308b\uff0e\u3053\u306e\u89e3\u5256\u5b66\u7684\u7279\u5fb4\u3092\u518d\u73fe\u3059\u308b\u305f\u3081\uff0c Fig. 8\u306e\u5c3a\u9aa8\u5074\u3068\u6a48\u9aa8\u5074\u306e\u30d5\u30ec\u30fc\u30e0\u4e2d\u5fc3\u3092\u7d50\u3076\u7834\u7dda\u3068\uff0c\u624b\u9996\u306e \u638c\u80cc\u5c48\u6a5f\u69cb\u306e\u8ef8\uff08\u5b9f\u7dda\uff09\u3068\u306e\u95a2\u4fc2\u304c 45\u25e6 \u3068\u306a\u308b\u3088\u3046\u306b\u30bd\u30b1\u30c3\u30c8 \u306b\u3072\u306d\u308a\u3092\u3044\u308c\u3066\u3044\u308b\uff0e\u30bd\u30b1\u30c3\u30c8\u306e\u30b5\u30a4\u30ba\u306f\u6a19\u6e96\u7684\u306a\u65e5\u672c\u4eba\u6210 \u4eba\u7537\u6027\u306b\u5408\u308f\u305b\u3066\u4f5c\u6210\u3057\u3066\u3044\u308b\u304c\uff0c\u30b9\u30ea\u30c3\u30c8\u306b\u3088\u3063\u3066\u3042\u308b\u7a0b\u5ea6 \u306e\u8abf\u6574\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u30bd\u30b1\u30c3\u30c8\u306b\u88ab\u305b\u305f\u30b5\u30dd\u30fc\u30bf\u306e\u7559\u3081\u5177\u3067\u7de0 \u3081\u4ed8\u3051\u308b\u3053\u3068\u3067\u5bb9\u6613\u306a\u88c5\u7740\u3092\u53ef\u80fd\u3068\u3057\u305f\uff0e\u30b5\u30dd\u30fc\u30bf\u306e\u88cf\u5730\u306f\u9069 \u5ea6\u306a\u6469\u64e6\u3068\u67d4\u3089\u304b\u3044\u63a5\u89e6\u9762\u304c\u5f97\u3089\u308c\u308b\u7279\u6b8a\u7d20\u6750\uff08\u30b9\u30ad\u30f3\u30ea\u30d0\u30fc \u30b9\uff0c\u30c0\u30a4\u30e4\u5de5\u696d\uff09\u306b\u306a\u3063\u3066\u304a\u308a\uff0c\u5207\u65ad\u7aef\u306e\u629c\u3051\u843d\u3061\u9632\u6b62\u3068\u5207\u65ad \u7aef\u306e\u4fdd\u8b77\u306e\u5f79\u5272\u3092\u679c\u305f\u3059\uff0e\u305d\u306e\u305f\u3081\uff0c\u4e0a\u8155\u9aa8\u9846\u307e\u3067\u30bd\u30b1\u30c3\u30c8\u3067 \u8986\u3046\u3053\u3068\u306b\u3088\u3063\u3066\u61f8\u5782\u3059\u308b\u30df\u30e5\u30f3\u30b9\u30bf\u30fc\u5f0f\u30bd\u30b1\u30c3\u30c8\u3088\u308a\u3082\uff0c\u8098 \u306e\u52d5\u4f5c\u3092\u59a8\u3052\u306a\u3044\uff0e\u30b5\u30dd\u30fc\u30bf\u306f\u30bd\u30b1\u30c3\u30c8\u304b\u3089\u53d6\u308a\u5916\u3057\u3066\u6d17\u6fef\u53ef \u80fd\u306a\u305f\u3081\u885b\u751f\u7684\u3067\u3042\u308b\uff0e 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure19-1.png", + "caption": "Figure 19. Double shear fixture between the clamps (left) composite double shear specimen inside double shear fixture (center) close-up of the composite double shear specimen assembly (right)", + "texts": [ + " Procedure A double shear tension, in ASTM 5961 [18], was followed closely. The user needed to make sure that all the dimensions were recorded such as specimen width, specimen length, and specimen thickness and distance between the edge of the specimen to the hole edge. The fixture used for the double shear test consisted of an assembly made up of three cold drawn Steel plates with two bolts and nuts connecting all three plates. The double shear fixture is shown in between the clamps on the left in Figure 19. The double shear fixture is shown, in the center, in Figure 19. The close-up of the collar-specimen assembly is shown, on the right side, in 35 Figure 19 as well. Each double shear joint specimen was sandwiched between two Steel plates, two Steel collars, four washers and a nut, which can be seen on the left and the center in Figure 20. The extensometer, as required by the ASTM 5961 [18], is fixed on the fixture with a small steel plate and two bolts, shown on the right in Figure 20. The extensometer's knife edge was carefully placed inside the slit of the specimen and secured with a rubber band. The nut which held the screw assembly together with the specimen was only hand tightened" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003454_6_61_4_61_4_501__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003454_6_61_4_61_4_501__pdf-Figure1-1.png", + "caption": "Fig. 1 Virtual shifted gear under offset", + "texts": [], + "surrounding_texts": [ + "\u8ad6\u6587\n\u4eee\u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6 \u306b\u57fa\u3065 \u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\n\u5275\u6210\u6b6f\u5207 \u308a*\n\u8429 \u539f \u89aa \u4f5c* *\nPractical Face Gear Hobbing based on a Theory of Virtual Shifted Gear\nShinsaku HAGIWARA\nFace gears are made by a continuous generating-shaping process on a Fellows Gear Shaper or\nsimilar type machine using a special fixture. Their gears, which have some advantages of easy setting, smooth mating for the mating pinion of spur or helical, low cost, and other things, are often substituted for bevel gears. In order to hob by use of a conventional hob machine and commercial hob, a theory of virtual shifted gear for determining the maximum practical outside diameter, the minimum practical inside diameter, and the face width of face gears, is proposed in face gear design. As a result, hobbed face gear could be obtained to become the point which the teeth become pointed at the outside and the point where tooth trimming occurs at the inside. In addition, contact test will be permitted to touch smoothly if being burnished enough.\nKey words : practical face gear, virtual shifted gear, maximum practical outside diameter,\nminimum practical inside diameter, contact test\n1. \u306f \u3058 \u3081 \u306b\n\u73fe \u5728 \u4f7f \u7528 \u3055\u308c \u3066 \u3044 \u308b \u5404 \u7a2e \u6b6f \u8eca \u306f,\u8a2d \u8a08 \u304c \u8907 \u96d1 \u306b\u306a \u308b \u3068 \u305d \u308c \u306b\u4f34 \u3044\u305d \u306e\u88fd \u4f5c \u306b \u306f \u5c02 \u7528 \u306e \u6b6f \u5207 \u308a\u76e4 \u304c \u5fc5 \u8981 \u3068\u306a \u308b \u5834 \u5408 \u304c\n\u591a\u3044.\u305d \u306e \u4ee3\u8868 \u7684 \u306a \u3082\u306e \u306e \u4e00 \u3064 \u306b \u304b \u3055\u6b6f \u8eca \u304c \u6319 \u3052 \u3089\u308c \u308b. \u3057\u304b \u3082\u304b \u3055\u6b6f \u8eca \u306f \u5404 \u6b6f \u5207 \u308a\u76e4 \u30e1\u30fc \u30ab \u72ec \u81ea\u306e \u898f \u683c \u3092 \u3082 \u3061\u4ed6 \u793e\n\u3068\u306e \u4e92 \u63db \u6027 \u304c \u60aa \u3044 \u306a \u3069\u306e \u6b20 \u70b9 \u304c \u3042 \u308a,\u3055 \u3089 \u306b\u4fa1 \u683c \u306e \u9762 \u3067 \u3082 \u4e00\u822c \u306e \u30ae \u30e4 \u306b \u6bd4 \u3079 \u9ad8 \u4fa1 \u3067 \u3042 \u308b .\u305d \u306e \u305f \u3081 \u3057\u3070 \u3057\u3070 \u901a \u5e38 \u306e \u6b6f\n\u5207 \u308a\u76e4 \u306b \u3088 \u308b \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u304c \u304b \u3055\u6b6f \u8eca \u306e \u4ee3 \u7528 \u3068 \u3057\u3066\u6ce8 \u76ee \u3055 \u308c\u305f1).\u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306f \u901a \u5e38,\u5e73 \u6b6f \u8eca \u307e \u305f \u306f \u306f \u3059 \u3070\u6b6f \u8eca \u306e \u30d4\u30cb \u30aa \u30f3 \u3068 \u76f4 \u89d2 \u306b \u304b \u307f \u5408 \u3046\u4e00 \u7a2e \u306e \u30af \u30e9 \u30f3 \u30af\u30ae \u30e4 \u3067 \u3042 \u308b. \u304b\n\u3055\u6b6f \u8eca \u3068\u6bd4 \u8f03 \u3057\u3066 \u76f8 \u624b \u6b6f \u8eca \u306b \u305f \u3044 \u3057\u3066 \u30aa \u30f3\u30bb \u30f3 \u30bf \u3067 \u3082\u30aa \u30d5 \u30bb \u30c3 \u30c8\u3067 \u3082 \u7528 \u3044 \u308b \u3053 \u3068\u304c \u3067 \u304d,\u7d44 \u7acb \u8abf \u6574 \u304c \u7c21 \u5358,\u3057 \u304b \u3082\u5b89\n\u4fa1 \u306a \u3069\u306e \u5229 \u70b9\u304c \u3042 \u308b.\n\u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e \u88fd \u4f5c \u306f \u4e00 \u822c \u7684 \u306b,\u30d5 \u30a7\u30ed \u30fc \u30b9 \u578b \u6b6f \u8eca \u5f62 \u524a\n\u308a\u76e4 \u306b \u4ed8\u5c5e \u88c5 \u7f6e \u3092 \u53d6 \u308a\u4ed8 \u3051 \u3066 \u5275 \u6210 \u6b6f \u5207 \u308a\u306b \u3088 \u308a \u884c \u3046.\u3057 \u304b\n\u3057\u3053 \u3053 \u3067 \u3082 \u5c02 \u7528\u6a5f \u306e \u666e \u53ca \u7387 \u306f\u4f4e \u304f,\u3057 \u304b \u3082\u9ad8 \u4fa1 \u3067 \u3042 \u308b \u3068\u8a00 \u3063\u305f\u554f \u984c \u304c \u3042 \u308b 2).\n\u3053 \u308c \u307e \u3067 \u306b \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306b \u95a2\u3059 \u308b\u5831 \u544a1)\uff5e6)\u306f \u6975 \u3081 \u3066 \u5c11\n\u306a \u3044 \u304c,\u306a \u304b \u3067 \u3082\u5742 \u672c1)2)\u3089 \u306f \u666e \u901a \u30dc \u30d6 \u306b \u3088 \u308b \u6b6f \u5207 \u308a\u53ef \u80fd\n\u306a \u30dc \u30d6 \u306e \u958b \u767a \u306a \u3069 \u3092\u691c \u8a0e \u3057,\u5b9f \u7528 \u306e \u53ef \u80fd \u6027 \u3092 \u793a \u5506 \u3057\u3066 \u3044 \u308b.\n\u672c \u7814\u7a76 \u3067 \u306f,\u5b9f \u7528 \u7684 \u306a \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u3092 \u901a \u5e38 \u306e \u30db \u30d6 \u76e4 \u3068\u5e02\n\u8ca9 \u30db \u30d6 \u3092 \u82e5 \u5e72 \u5de5 \u592b \u3059 \u308b \u3053 \u3068 \u3067,\u5f93 \u6765 \u3088 \u308a\u7c21 \u5358 \u306b\u88fd \u4f5c \u3059 \u308b \u3053 \u3068\u306b \u4e3b \u76ee\u7684 \u3092\u304a \u304f.\u305d \u306e \u305f \u3081 \u306b \u4eee \u60f3 \u306e \u8ee2 \u4f4d \u6b6f \u8eca \u7406 \u8ad6 \u3092 \u7528 \u3044 \u305f\u8fd1 \u4f3c \u7684 \u306a \u8a2d \u8a08 \u30fb\u8a08 \u7b97 \u6cd5 \u3092\u63d0 \u6848 \u3059 \u308b.\u305d \u3057\u3066 \u8fd1 \u4f3c \u5f0f \u306b \u5f93 \u3044\n\u6b6f\u5207 \u308a\u3055\u308c\u305f\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4 \u306b\u5bfe \u3057,\u304b \u307f\u5408\u3044\u8a66\u9a13\u3088 \u308a\u672c\u624b \u6cd5\u306e\u59a5\u5f53\u6027 \u3068\u5b9f\u7528\u6027\u3092\u691c\u8a0e \u3057\u305f.\n2. \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u8a2d \u8a08 \u30fb\u8a08 \u7b97 \u6cd5\n\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u88fd\u4f5c\u306b\u5fc5\u8981\u306a\u57fa\u790e\u8cc7\u6599\u3068\u3057\u3066,\u6b6f \u6570, \u30e2 \u30b8\u30e5\u30fc\u30eb,\u5727 \u529b\u89d2,\u53ca \u3073\u5927\u7aef\u76f4\u5f84\u3068\u5c0f\u7aef\u76f4\u5f84\u304c\u3042\u308b.\u3053 \u3053\n\u3067\u672c\u6765\u306e\u6b6f\u5f62 \u3068\u4e21\u76f4\u5f84\u306e\u53b3\u5bc6\u306a\u7406\u8ad6\u5f0f\u306f\u975e\u5e38\u306b\u8907\u96d1\u306b\u306a\u308b \u305f\u3081,\u901a \u5e38\u306e\u30dc\u30d6\u76e4\u3068\u5e02\u8ca9\u30db\u30d6\u306b\u3088\u308b\u6b6f\u5207\u308a\u3067\u306f\u7406\u60f3\u306e\u6b6f\n\u5f62\u5275\u6210\u306f\u4e0d\u53ef\u80fd\u3067\u3042\u308b.\u3057 \u304b \u3057\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u3068\u76f8\u624b\u30d4\u30cb\u30aa \u30f3\u3068\u306e\u9593\u3067,\u5b9f \u969b\u4e0a\u3055\u307b\u3069\u554f\u984c \u3068\u306a\u3089\u306a\u3044\u304b\u307f\u5408\u3044\u304c\u88fd\u4f5c \u3067\u304d\u308b\u306a\u3089\u5b9f\u7528\u7684\u4fa1\u5024\u306f\u3042\u308b\u3068\u8a00\u3048\u308b.\u305d \u306e\u305f\u3081\u306b\u4eee\u60f3\u306e\n\u8ee2\u4f4d\u6b6f\u8eca\u306b\u3088\u308b\u8fd1\u4f3c\u7684\u306a\u8a2d\u8a08 \u30fb\u8a08\u7b97\u6cd5\u3092\u8a66\u307f\u305f.\u305d \u306e\u57fa\u672c\n\u7684\u306a\u8003\u3048\u306f,\u5927 \u80c6\u306a\u4eee\u5b9a\u3067\u3042\u308b\u304c,\u56f31\u306e \u3088\u3046\u306b1\u679a \u306e\u5c0f \u6b6f\u8eca\u304c\u540c\u3058\u6b6f\u6570\u306e\u8907\u6570(\u56f3 \u3067\u306f3\u679a)\u306e \u76f8\u5f53\u5e73\u6b6f\u8eca\u3068\u30aa\u30d5 \u30bb \u30c3\u30c8\u306e\u4f4d\u7f6e\u3067\u304b\u307f\u5408\u3063\u3066\u3044\u308b\u3068\u8003\u3048\u308b.\u3053 \u3053\u3067G2\u306f \u30d5\u30a7 \u30fc\u30b9\u30ae\u30e4\u306e\u30d4 \u30c3\u30c1\u5186\u4e0a\u306b\u3042\u308b\u306e\u3067\u8ee2\u4f4d\u91cf=O\u3067 \u3042\u308b. G1 \u306f\u8ca0,G3\u306f \u6b63\u306e\u8ee2\u4f4d\u3068\u306a\u308b.\u3053 \u306e\u3088\u3046\u306b\u3059\u308c\u3070\u30d5\u30a7\u30fc\u30b9\n\u30ae\u30e4\u306e\u5927\u7aef\u76f4\u5f84\u3068\u5c0f\u7aef\u76f4\u5f84\u3092\u6c7a\u5b9a\u3059\u308b\u554f\u984c\u306f,\u5358 \u306a\u308b\u8ee2\u4f4d \u6b6f\u8eca\u306e\u554f\u984c \u3068\u306a\u308b.\u307e \u305f,\u6b63 \u306e\u8ee2\u4f4d\u65b9\u5411\u3067\u306f\u6b6f\u5148\u304c\u3068\u304c\u308a,\n\u8ca0\u306e\u8ee2\u4f4d\u65b9\u5411\u3067\u306f\u5207\u308a\u4e0b\u3052\u3092\u8d77\u3053\u3059.\u305d \u3053\u3067\u5927\u7aef\u306f\u6700\u5927\u3067 \u6b6f\u5148\u306e\u3068\u304c \u308a\u3092\u751f\u305a\u308b\u70b9\u304c\u9650\u754c\u3068\u306a \u308a,\u5c0f \u7aef\u306f\u6b6f\u306e\u5207\u308a\u4e0b\n\u3052\u3092\u3069\u306e\u3088\u3046\u306b\u6271 \u3046\u304b\u306b\u3088 \u3063\u3066\u9650\u754c\u304c\u6c7a\u5b9a\u3055\u308c\u308b.\u5143 \u6765, \u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306f\u6b6f\u5e45\u3092\u5927\u304d\u304f\u3068\u308c\u306a\u3044\u3068\u3044\u3046\u6b20\u70b9\u304c\u3042\u308b\u304c, \u3053\u3053\u3067\u306f\u3067\u304d\u308b\u3060\u3051\u5927\u304d\u304f\u3068\u308b\u3088\u3046\u306b\u8a2d\u8a08\u3059\u308b.\n\u56f32\u306f,\u57fa \u6e96\u30e9\u30c3\u30af\u3067\u6b63\u306e\u8ee2\u4f4d\u91cf\u3092X\u30fbm\u4e0e \u3048\u3066\u6b6f\u5207 \u308a\n\u3057\u305f\u306f\u3059\u3070\u6b6f\u8eca\u306e\u6b6f\u76f4\u89d2\u65ad\u9762\u3067\u3042\u308b.\u56f3 \u4e2d\u306e\u8af8\u8a18\u53f7\u306f * \u539f\u7a3f\u53d7\u4ed8 \u5e73\u62106\u5e74 6 \u6708 22 \u65e5\n* * \u6b63 \u4f1a \u54e1 \u5c71\u68a8 \u5927 \u5b66 \u5de5 \u5b66 \u90e8(\u7532 \u5e9c \u5e02\u6b66 \u75304- 3- 11 )\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 501", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\nRg: \u57fa \u790e \u5186 \u7b52 \u534a \u5f84 R0: \u57fa \u790e \u30d4 \u30c3\u30c1 \u5186 \u7b52 \u534a \u5f84\nRx: \u6b6f \u5f62 \u4e0a \u306e \u4efb \u610f \u306e \u534a \u5f84 Tg: \u57fa\u790e\u5186\u7b52\u4e0a\u306e\u5186\u5f27\u6b6f\u539a T0: \u57fa \u6e96 \u30d4 \u30c3\u30c1 \u5186\u7b52 \u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a\nTx: Rx\u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a 2\u03c8g: \u5f27Tg\u306b \u5bfe \u3059 \u308b\u4e2d \u5fc3 \u89d2\n2\u03c80: \u5f27T0\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2\n2\u03c8x: \u5f27Tx\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2 \u03b1x: Rx\u4e0a \u306b \u304a \u3051 \u308b\u304b \u307f \u5408 \u3044 \u5727 \u529b \u89d2 \u03b10: \u5de5 \u5177 \u5727 \u529b \u89d2\n\u3092\u8868 \u3059.\n(a) \u5927 \u7aef \u76f4 \u5f84\n\u56f32\u3067 \u4efb \u610f \u306e \u534a \u5f84Rx\u306b \u304a \u3051 \u308b \u5186\u5f27 \u6b6f \u539aTx\u306f,X\u3092 \u8ee2 \u4f4d\n\u4fc2 \u6570 \u3068 \u3057\u3066\n( 1 )\n\u3067\u8868\u305b\u308b.\u307e \u305f\u57fa\u6e96\u30d4\u30c3\u30c1\u5186\u4e0a\u306e\u5186\u5f27\u6b6f\u539aT0 \u306f\n( 2 )\n\u3068\u306a \u308b.\u5f0f(1)\u306b \u5f0f(2)\u3092 \u4ee3 \u5165\u3059 \u308b \u3068\n( 3 )\n\u3068\u306a \u308b.\u5f93 \u3063\u3066,\u5927 \u7aef \u76f4 \u5f84 \u306f \u6b6f \u5148 \u306e \u3068\u304c \u308a\u3092\u9650 \u754c \u306b\u3059 \u308b \u306b \u306fTx=0\u3068 \u3059 \u308c \u3070 \u3088 \u3044.\u5f0f(3)\u3092inv\u03b1x\u306b \u3064 \u3044 \u3066 \u89e3\n\u304f\u3068\n( 4 )\n\u3068 \u306a \u308b.\u3053 \u3053\u3067\n( 5 )\n( 6 )\n\u3068\u3059 \u308b \u3068,\u76f8 \u5f53 \u5e73 \u6b6f \u8eca \u306e\u6b6f \u6570Zv\u306f,\u03b3 \u3092\u57fa \u790e \u5186 \u7b52 \u306d \u3058\u308c\n\u89d2 \u3068 \u3057\n( 7 )\n\u3068\u306a\u308b.\u307e \u305f\u4efb\u610f\u306e\u534a\u5f84Rx\u4e0a \u306e\u8ee2\u4f4d\u4fc2\u6570X \u306f\n( 8 )\n\u3067 \u8868 \u3055\u308c \u308b.\u3088 \u3063\u3066 \u5927 \u7aef \u534a \u5f84D0 \u306f\n( 9 )\n\u3088 \u308a\u6c7a \u5b9a \u3055 \u308c \u308b.\n(b) \u5c0f \u7aef \u76f4\u5f84\n\u5c0f \u7aef \u76f4 \u5f84 \u306e \u6c7a \u5b9a \u306b \u3064 \u3044 \u3066 \u306f,\u56f33\u306b \u793a \u3059 \u3088 \u3046 \u306b,\u6b6f \u306e\u5207 \u308a\u4e0b \u3052 \u3092 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5e73 \u9762 \u307e \u3067 \u751f \u3058\u3066 \u3082 \u826f\u3044 \u3068\u4eee\n\u5b9a5)\u3059 \u308b.\u8ca0 \u306e \u8ee2 \u4f4d \u304b \u3089,\u57fa \u6e96 \u5727 \u529b \u89d220\u309c \u306e \u5834 \u5408,\u5e73 \u6b6f \u8eca \u306e \u9650 \u754c \u6b6f \u6570 \u306fZmin=17\u3067 \u3042 \u308a,\u8ee2 \u4f4d \u4fc2 \u6570X \u306f\n( 10 )\n\u5f93 \u3063\u3066 \u5c0f \u7aef \u76f4\u5f84Di\u306f \u6b21 \u5f0f \u3088 \u308a\u6c42 \u307e \u308b.\npositive shift\n502 \u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u5893\u3064\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n( 11 )\n\u305f \u3060 \u3057,Z'\u306f \u5207 \u308a\u4e0b \u3052 \u3092 \u3069 \u3053 \u307e \u3067 \u8a31 \u3059 \u304b \u306b \u3088 \u3063\u3066 \u6c7a \u307e \u308b\n\u6b6f \u6570 \u3067,\u56f33\u306e \u5834 \u5408 \u3067 \u306fZ'=6\uff5e8\u306b \u3059 \u308c \u3070 \u3088 \u3044.\n(c) \u30aa \u30d5 \u30bb \u30c3 \u30c8\u4e0b \u3067 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84\n\u56f34\u306b \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3057\u3066 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84 \u306e \u5909 \u5316 \u306e\n\u69d8 \u5b50 \u3092 \u793a \u3059.\u56f3 \u4e2d \u306e \u5404 \u8a18 \u53f7 \u306f \u305d \u308c \u305e \u308c\na: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf Z: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e\u6b6f \u6570 \u03c9: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u89d2 \u901f \u5ea6\n\u03b2: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u89d2 R0: \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84 Ra: \u30aa \u30d5\u30bb \u30c3 \u30c8\u3067 \u5909 \u5316 \u3057\u305f \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84\nV0: \u534a \u5f84R0\u4e0a \u306e \u901f \u5ea6 Va: \u534a\u5f84Ra\u4e0a \u306e \u901f \u5ea6\n\u3092\u8868 \u3059.\u3053 \u308c \u3088 \u308a,\u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306b\u5bfe \u3057\u3066 \u5c0f \u6b6f \u8eca \u304c \u30aa \u30f3\u30bb \u30f3 \u30bf(P\u306e \u4f4d \u7f6e)\u306b \u304a \u3044 \u3066 \u306f,\u5c0f \u6b6f \u8eca \u306e \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84 \u306e \u6bd4 \u306f\u6b6f \u6570 \u306e \u6bd4(\u89d2 \u901f \u5ea6 \u306e \u6bd4)\u306b \u7b49 \u3057 \u304f\u306a \u308b \u304c,\u30aa \u30d5 \u30bb \u30c3 \u30c8 (\nP'\u306e \u4f4d \u7f6e)\u4e0b \u3067 \u306f \u4e21 \u534a \u5f84 \u306e \u6bd4 \u306f,\u306f \u3059 \u3070 \u89d2 \u306e \u5f71 \u97ff \u3092 \u53d7\n\u3051\u3066 \u5fc5 \u305a \u3057\u3082\u6b6f \u6570 \u306e \u9006 \u6bd4 \u306b\u7b49 \u3057 \u304f\u306f \u306a \u3089 \u306a \u3044.\u3059 \u306a \u308f \u3061 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3059 \u308b \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84Ra \u306f\n( 12 )\n\u3068\u306a \u308b.\u307e \u305f,\u5f0f(12)\u3067 \u03b2\u306e \u4ee3 \u308f \u308a\u306b \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf a\n\u3092\u7528 \u3044\u3066 \u8868 \u3059 \u3068\n( 13 )\n\u3068\u306a \u308b.\u305f \u3060 \u3057,\u30aa \u30f3\u30bb \u30f3 \u30bf\u3067 \u306fa=0\u3067 \u3042 \u308b.\u3088 \u3063\u3066 \u30d4 \u30c3\u30c1 \u5186\u76f4 \u5f84Dp \u306f\n( 14 )\n\u3067\u8868 \u305b \u308b.\u4ee5 \u4e0a \u304c \u8a2d \u8a08 \u6cd5 \u3067 \u3042 \u308b.\u6b21 \u306b \u5177 \u4f53 \u7684 \u8a08 \u7b97 \u6cd5 \u306f, \u307e\n\u305a \u5404 \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u306b\u5bfe \u3057\u3066 \u5f0f(13)\u3088 \u308aDp\u3092 \u6c42 \u3081 \u308b. \u305d \u306eDp\u306b \u5bfe \u3057\u5f0f(9),(10)\u3088 \u308aDo,Di\u3092 \u7b97 \u51fa \u3059 \u308b\n\u56f35\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e\u6b6f \u6570 \u3068 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u3067 \u5927 \u7aef,\u5c0f \u7aef \u76f4 \u5f84 \u304c \u3069\u306e \u3088 \u3046 \u306b\u5909 \u5316 \u3059 \u308b \u304b \u306e \u8a08 \u7b97\u7d50 \u679c \u3092\u793a \u3059.\u3053 \u308c \u3088 \u308a\n\u6b6f \u6570 \u304c \u5897 \u3059 \u3068,\u4e21 \u76f4\u5f84 \u304c \u5927 \u304d \u304f \u306a \u308b \u3068\u540c \u6642 \u306b\u4e21 \u76f4 \u5f84 \u306e \u5dee, \u3064 \u307e \u308a\u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b.\u307e \u305f,\u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u304c \u5927 \u304d \u3044 \u307b\n\u3069\u5927 \u7aef,\u5c0f \u7aef \u76f4\u5f84 \u53ca \u3073 \u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b \u3053 \u3068\u304c \u308f \u304b \u308b.\u3053 \u308c \u306f \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u306e \u5897 \u52a0 \u306b\u4f34 \u3044 \u30d4 \u30c3\u30c1 \u5186 \u76f4\u5f84 \u304c \u5927 \u304d \u304f\u306a \u308b \u304b \u3089\u3067 \u3042 \u308b.\u3057 \u304b \u3057\u306a \u304c \u3089\u6b6f \u6570 \u304c40\u679a,\u30aa \u30d5 \u30bb \u30c3 \u30c8 10\n\u30fbm\u306b \u5bfe \u3057\u6b6f \u5e45 \u306f5mm\u7a0b \u5ea6 \u3067 \u3042 \u308a,\u540c \u3058 \u304f\u6b6f \u6570140 \u679a\n\u3067 \u308210mm\u7a0b \u5ea6 \u3068\u6b6f \u5e45 \u304c \u72ed \u3044.\u3053 \u306e \u3053 \u3068\u306f \u5148 \u306b\u8ff0 \u3079 \u305f \u3088\n\u3046\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e1\u3064 \u306e \u6b20 \u70b9 \u3067 \u3082\u3042 \u308b \u308f \u3051 \u3067 \u3042 \u308b.\u3055 \u3089\npitch plane\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 503" + ] + }, + { + "image_filename": "designv8_17_0003165_Levitator_System.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003165_Levitator_System.pdf-Figure2-1.png", + "caption": "Fig. 2. Magnetic Suspension Levitator.", + "texts": [ + " Adding forces, following Newton's second law and considering the suspended object along axis, we have: \u2211 \u0308 ( ) \u20d7\u20d7 \u20d7 \u0308 ( ) (4) Where the current in the coil of the electromagnet is, is the gravitational constant, is the magnetic force constant and is the mass of the object. The levitator consists of a magnet that create a magnetic field and electromagnets that control that magnetic field. It is necessary to vary the value of the electromagnetic force by adjusting the current that passes through the electromagnet because the electromagnet is responsible for generating the electromagnetic force that allows the levitation of the object, as it shown in Fig. 2. Each magnet has two poles: the north and the south. Experiments show that opposites are attracted and the same poles repel each other. Four cylindrical magnets are placed in a square and have the same polarity, around forming a magnetic field up to push any magnet, which has the same pole and in the middle of them. Together with four levitation coils, placed equidistantly and symmetrical magnets, it is possible to create an opposite magnetic field. Sets of dynamic equations (Newton's and Kirchhoff's equations) that provide theory to the system are given by the following set of equations using equation (4) we have the equation of mechanical system and the differential equation of the circuit", + " CONCLUSIONS As a future work, we want to implement the electronic circuit and also add a magnetic levitator by repulsion to identify the sum of the forces exerted on an object when subjected by 2 electromagnetic fields. 430 | P a g e www.ijacsa.thesai.org The use of the TRIAC is based on the level of operating current of the circuit, compared to a transistor because as a maximum it can work at 1 ampere, thus limiting the desired power in the coil to generate the electromagnetic field. ACKNOWLEDGMENTS We would like to thank Isabel Ivanka Cotrina she is the visual artist who drew the Fig. 2 in this document. [1] Nayak A., Controller design for magnetic levitation system, Thesis for Master, Department of Electrical Engineering NIT, India, April 2015. [2] Giancoli, Douglas C.; Physics Principles with Applications, Person Education Limited, England, Chapter 16-21, 2016. [3] M. Ahmed, M. F. Hossen, M. E. Hoque, O. Farrok, and M. Mynuddin; \u201cDesign and Construction of a Magnetic Levitation System Using Programmable Logic Controller,\u201d Am. J. Mech. Eng. Vol. 4, 2016, Pages 99-107, vol. 4, no" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002192_r.asee.org_42539.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002192_r.asee.org_42539.pdf-Figure1-1.png", + "caption": "Figure 1. Principle of vacuum thermoforming, Groover [1].", + "texts": [ + " The purpose of this project is to introduce students to thermoforming and drape forming. Drape forming is a simplified version of vacuum forming where a sheet of plastic is heated to a sufficiently high temperature so that it can be formed around an object. The plastic sheet can be heated in an oven and stretched over the pattern using suction or vacuum. Thin-gauge thermoforming is used to manufacture parts such as containers, cups, lids and trays while thickgauge thermoforming is used to make plastic pallets, vehicle door and dash panels, and utility vehicle beds. Figure 1 shows the principle of thermoforming as described by Groover [1] . The fundamentals of plastics thermoforming and tool design have been studied by Klein [2],[3]. Three different object patterns or positive molds were used for thermoforming in this project: an instrument panel, a seat and a cowl for the Paolo Severin \u00bc scale Piper J3 Cub [4]. Figure 2a) is showing the object pattern made of wood for the instrument panel. Holes with diameter 1/10\u201d were drilled at the center of each instrument circle to enable suction and a better final shape of the thermoformed plastic" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001599_sue-17_Article16.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001599_sue-17_Article16.pdf-Figure6-1.png", + "caption": "Figure 6. Current and maximum radiation.", + "texts": [ + " Few things have to be shown attention when designing the radiating patch are as follows performing frequency, material on the top of which the radiating element is to be raised, materials permittivity. The scale values for the prompted equal sided structure are obtained using the relations. The side dimensions are 29.2 mm. Indian Journal of Science and Technology 3Vol 11 (17) | May 2018 | www.indjst.org The preferred substrate material is FR4 (Lossy) and the permittivity value is 4.4 and the thicknes chosen for the design is 1.6 mm. Larger conducting area of the design is built with copper and the consistency of the layer is 35 micron. Figure 6 shows the maximum current distribution on the structure. The infinite ground concept is applied for the proposed structure. It is intended in such a way that it intrudes within the substrate. Square shaped patch is designed with a slot on it to have the better operating results. The feed offered for the antenna is edge feeding with 50ohms impedance. The designed patch with inverted U Shape is simulated using the advanced design system software. The methods of moments are used in ADS software. The S11 parameter simulation is nearly at -13 dB on the designed frequency 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000550_9551808_09551816.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000550_9551808_09551816.pdf-Figure1-1.png", + "caption": "Fig. 1. Hydraulic actuator and electric actuator in four-legged robots: (a) Boston Dynamics Wildcat and (b) MIT Cheetah robot.", + "texts": [ + "(Corresponding Author: Do-Kwan Hong) Tae-Woo Lee and Do-Kwan Hong are with the Energy and Power Conversion Engineering Department, University of Science and Technology, Changwon, 51543 Korea and Electric Machines and Drives Research Center, Korea Electrotechnology Research Institute, Changwon, 51543 South Korea (corresponding author\u2019s email: dkhong@keri.re.kr). Tae-Uk Jung is with the Electrical Engineering Department, Kyungnam University, Changwon, 51767 South Korea (e-mail: tujung@kyungnam.ac.kr). Digital Object Identifier 10.30941/CESTEMS.2021.00026 Hydraulic actuators with engines are commonly applied for quadruped robots, which therefore require high power for heavy loads, as shown Fig. 1 (a). However, such engines come with disadvantages in terms of space and weight. These disadvantages can be resolved with the electric actuators shown in Fig. 1 (b) based on motors, but the output power of electric actuators is lower than that of hydraulic actuators [3-5]. Despite their relatively low output power, electric motors are widely used in industry and robot fields because of the great savings of space and weight. Nowadays, permanent magnet (PM) motors can achieve high speed and high power due to development of rare earth PMs that have high residual magnetic flux density. The PM motors have other advantages such as simple magnetic circuit design, fast response, linear torque-current and speed-voltage characteristics, and have low vibration and high efficiency" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001308_8948470_09179759.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001308_8948470_09179759.pdf-Figure1-1.png", + "caption": "FIGURE 1. Ballbot model for the Y -Z plane.", + "texts": [ + " In Section II, the dynamics of the ballbot is described and the problem formulation is presented. In Section III, the robust controller for the trajectory tracking and balancing of a ballbot is designed. In Section IV, the simulation results are presented to demonstrate the performance of the proposed method. In Section V, the conclusion is given. II. SYSTEM MODEL Consider a ballbot equipped with three omni-wheel motors. The ballbot is represented by a combination of three independent planar models. Fig. 1 shows the Y -Z plane model. Since the X -Z plane model is similar to the Y -Z plane model, the figure of the X -Z plane model is omitted. The X -Y plane model represents rotating along the Z -axis, but it is not considered in this article because it is not related to the trajectory tracking and balancing of the ballbot. Under the assumption that no slip occurs between the ball and the floor and between the ball and the omni-directional wheels, the dynamic equations of the ballbot can be given as follows [4]: y\u0308b = fy1(\u03b8y, \u03b8\u0307y)+1fy1(y\u0307b, \u03b8\u0307y)+ gy1(\u03b8y)\u03c4y + \u03c4d1 \u03b8\u0308y = fy2(\u03b8y, \u03b8\u0307y)+1fy2(y\u0307b, \u03b8\u0307y)+ gy2(\u03b8y)\u03c4y + \u03c4d2 (1) x\u0308b = fx1(\u03b8x , \u03b8\u0307x)+1fx1(x\u0307b, \u03b8\u0307x)+ gx1(\u03b8x)\u03c4x + \u03c4d3 \u03b8\u0308x = fx2(\u03b8x , \u03b8\u0307x)+1fx2(x\u0307b, \u03b8\u0307x)+ gx2(\u03b8x)\u03c4x + \u03c4d4 (2) where fy1 = a\u22121y sin \u03b8y{a5(a3 cos \u03b8y\u2212a4)\u2212 (a2 + Iy)a3\u03b8\u03072y } 1fy1 = a\u22121y {\u2212bry\u03b8\u0307y(a3 cos \u03b8y\u2212a4)\u2212 (a2 + Iy)byy\u0307b)} fy2 = a\u22121y sin \u03b8y{a3\u03b8\u03072y (a4\u2212a3 cos \u03b8y)+ a1a5} 1fy2 = a\u22121y {byy\u0307b(a4 \u2212 a3 cos \u03b8y)\u2212 a1bry\u03b8\u0307y} gy1 = a\u22121y r\u22121w (a2 + Iy + a3rb cos \u03b8y \u2212 a4rb) gy2 = a\u22121y r\u22121w (a3 cos \u03b8y \u2212 a4 + a1rb) ay = a1(a2 + Iy)\u2212 (a4 \u2212 a3 cos \u03b8y)2 fx1 = a\u22121x sin \u03b8x{\u2212a5(a3 cos \u03b8x\u2212a4)+ (a2 + Ix)a3\u03b8\u03072x } 1fx1 = a\u22121x {brx \u03b8\u0307x(a3 cos \u03b8x\u2212a4)\u2212 (a2 + Ix)bx x\u0307b)} fx2 = a\u22121x sin \u03b8x{a3\u03b8\u03072x (a4\u2212a3 cos \u03b8x)+ a1a5} 1fx2 = a\u22121x {\u2212bx x\u0307b(a4 \u2212 a3 cos \u03b8x)\u2212 a1brx \u03b8\u0307x} gx1 = a\u22121x r\u22121w (\u2212a2 \u2212 Ix \u2212 a3rb cos \u03b8x + a4rb) gx2 = a\u22121x r\u22121w (a3 cos \u03b8x \u2212 a4 + a1rb) ax = a1(a2 + Ix)\u2212 (a4 \u2212 a3 cos \u03b8x)2 a1 = mb + Ib r2b + mo + 3Iw cos2 \u03b1 2r2w a2 = mol2 + 3Iwr2b cos 2 \u03b1 2r2w a3 = mol, a4 = 3rbIw cos2 \u03b1 2r2w , a5 = mogl In these expressions, xb and yb denote the position of the ball along the X - and Y -axes, respectively, \u03b8x and \u03b8y are body angles along the X -Z and Y -Z planes, respectively, \u03c4x and \u03c4y are the control inputs of the three driving motors acting on the ball, mb is the mass of the ball, mo is the mass of the body, rb is the radius of the ball, rw is the radius of the omni-directional wheel, l is the distance between the center of the ball and the center of the mass of the body, Ix and Iy denote the moments of inertia of the body about the X - and Y -axes, respectively, Ib and Iw denote the moments of inertia of the ball and omni-directional wheel, respectively, \u03b1 is the zenith angle, by, bx , bry, and brx are the viscous damping coefficients that model the spherical wheel-ground friction, \u03c4d1, \u03c4d2, \u03c4d3, and \u03c4d4 denote the external disturbances, and g is the gravitational acceleration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002355_f_usme2019_01032.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002355_f_usme2019_01032.pdf-Figure4-1.png", + "caption": "Fig. 4. Test-bench pattern with the lever-type exciter of axle loading.", + "texts": [ + " In order to determine the rate of such load the factor is introduced for its adjusting to equivalent symmetrical alternating loading. Hydraulic exciters of dynamic loads are quire complex and there are costly. Inertial exciters are less expensive regarding the hardware configuration, but the same implemented using the complex designs. The simplest and inexpensive are the lever-type mechanisms of axle loading. The lever-type exciter contains several rods (beams) forming a transfer mechanism axle loading (Fig. 4). In accordance with acting workloads the test-bench mechanism shall create cyclic load on the axle with the amplitude of not less than 1300 kN and the frequency within 5 \u2013 10 Hz and asymmetry parameter of 0.1 [14]. In its design the test-bench is a spatial mechanism, however, if to place a support in the test-bench lever contact point the test-bench can be considered as a planar mechanism. The test-bench can provide a force action on this support corresponding to design force of 1300 kN. The planar structure of the test-bench (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.3-1.png", + "caption": "Figure B.3: Change in wing's angle of attack in rolling flight (26)", + "texts": [ + "9: Vertical/horizontal tail\u2019s pitching moment coefficient vs. angle of attack .......... 95 Figure A.10: Stators\u2019 drag coefficient vs. angle of attack....................................................... 96 Figure A.11: Stators\u2019 rolling moment coefficient vs. angle of attack ..................................... 96 Figure B.1: Side force at vertical tail in rolling flight (26) ....................................................... 99 Figure B.2: Change in vertical tail's angle of attack due to yaw rate (26) ............................ 100 Figure B.3: Change in wing's angle of attack in rolling flight (26) ........................................ 101 Figure B.4: Change in wind speed due to yaw rate (26) ...................................................... 105 x LIST OF TABLES Table 3.1: Flight conditions for altitude-hold mode and climbing mode .............................. 34 Table 4.1: Longitudinal derivatives in stability axes system .................................................. 41 Table 4.2: Longitudinal derivatives in body axes system ", + "19) The following part is to derive the relationship of wing \u2013 body rolling moment and yawing moment due to roll rate perturbation p and yaw rate perturbation r in stability axes system because the moment contribution from the wing is easier to derive in stability axes system. Then the results will be transformed to body axes system. For the contribution from the vertical and horizontal tail, it will be derived directly in body axes system, then all the results will be combined together to produce the final derivatives in body axes system. Referring to Figure B.3 below, let\u2019s consider a pair of symmetric chord-wise strip elements of the wing. Each pair of elements has the following characteristics: - Located at a distance y from the center line - Length of yc (chord at y ), width of y\u2202 - Lift curve slope of y LC \u03b1 and drag curve slope of y DC \u03b1 102 When the aircraft experiences a positive roll rate perturbation p , the right wing strip element will have an increment in angle of attack of: tan e py U \u03b1 \u03b1\u2248 = (B.20) Lift and drag in steady state are the same for both right wing and left wing strip elements: 21 2 y e e y L eL U c dyC \u03b1 \u03c1 \u03b1= (B" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure5-1.png", + "caption": "Fig. 5. Connecting element \u2013 \u201ccross brace\u201d", + "texts": [ + " Three different hexagonal honeycomb structures with a 1 mm thick wall and appropriately inscribed circles were used (Fig. 4). Structure A was used for the top layer, to which the manipulator will be attached. Structure B was used for the side walls, which are both load-bearing walls and connectors with the suspension. Structure C was used for the front and back walls, and for the floor bearing a lighter load, on which the electronics are placed. Additionally, a \u201ccross brace\u201d support element is used to connect the upper layer, the lower layer and the beam - a suspension element (Fig. 5). This element is the support for the differential mechanism (rocker-bogie suspension). The beam element, connecting the right and left suspension, consists of an aluminium tube of \u00d820 mm with a wall thickness of 2 mm, and a sleeve made using 3D printing technology from PLA material with a diameter of \u00d830 mm and an internal opening of \u00d820 mm (Fig. 5). The outer element of the beam, printed from PLA, is laminated with additional layers of carbon fibre in the place of connection with the frame, at the point where concentrated forces occur. Due to the production technology selected \u2014 3D printing \u2014 the \u201ccross brace\u201d element consists of five parts. The support element is removable and bolted to the frame with screws. The frame is laterally inclined by 15\u00b0 along the long sides of the B structure. This results from thesuspension geometry, which allows for running over obstacles larger than the wheel diameter, which in our case is 200 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000410__ALI_RAVANBAKHSH.pdf-Figure2.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000410__ALI_RAVANBAKHSH.pdf-Figure2.1-1.png", + "caption": "Fig. 2.1.", + "texts": [], + "surrounding_texts": [ + "For the new project the UPMSat-1 architecture has been used as the basis of the platform configuration. This approach has some advantages in the design process, first because UPMSat-1 structure is a space qualified platform approved as suitable for flight in Ariane 4 launcher by Arianespace, and second because UPMSat-1 structure had successfully demonstrated its robustness during all the qualification and acceptance tests. It must be pointed out that this microsatellite platform will be qualified according to the most restrictive requirements envelope of several existing launchers [30]. The satellite geometrical configuration is selected bearing in mind an easy manufacturing process which can be carried out by university facilities. Due to this approach, and based on other university microsatellite projects [4-7], the geometry is selected as a four-sided, square-based prism as shown in Fig. 1.2. Figure 1.2: Satellite geometrical configuration composed of trays A, B, C and D. For subsystem equipment accommodation, four trays, A, B, C and D, including the bottom and top trays of the satellite are considered. The mass budgets of different subsystems including Attitude Determination and Control, Command and Data Handling, Power, Telecommunication, Thermal Control, and Structure and Payload, have been assumed based on the design estimation relationships from a variety of sources [31-35] which are indicated in For the structural sizing tool which is described in chapter 2, the payload and structure mass budgets are not pre-assumed although their sum mass budgets should not exceed more than 55% of the satellite total mass. By reducing as much as possible the structure mass, there is more mass budget available for the payload. As mentioned in introduction, this approach has special advantages for university-class microsatellite projects which in the early phases of the design have no exact information about the payload. Chapter 2. Satellite structural design The structural model is combined of static and dynamic models. For static calculations, the analyses are done on each set of primary structures consisting of four equal leg angles L-bars as the satellite main frame, four plates as the side panels and four plates as the satellite trays, In order to facilitate low cost and low dependency on industry for structure manufacturing, the material is assumed to be an isotropic type space-qualified aluminum alloy. The material properties of primary structural elements are indicated in Table 2.1. Table 2.1: Satellite primary structural elements material properties. Subsystems E [GPa] \u03c5 G [GPa] \u03c1 [kg/m 3 ] \u03c3[MPa] \u03c4 [MPa] AL7075-T6 72 0.33 27 2800 505 330 The trays are considered to be sized under an isogrid pattern to reduce the total mass. The satellite bottom tray is assumed to be clamped to the launcher, and maximum stress, maximum deflection and buckling of each primary structure element is analyzed. For dynamic analysis, in order to estimate the natural frequencies, a simple mass-spring model is considered in both longitudinal and lateral directions. Structural modeling is done based on analytical design formulas from classic structure design references [36-39]. The structural calculations should meet some specific requirements of the foreseen satellite launcher. Usually, for university-class microsatellite projects, the exact information about the satellite launcher cannot be provided at the initial phases of the program. However, it is highly desirable to use the opportunity of being launched as an auxiliary payload to reduce the cost of the project. Based on these reasons, the strength and stiffness of different launcher requirements have been reviewed and the most severe requirements considered as the basis of structural calculations. This approach also gives versatility to the project and does not limit it to a specific launcher. Finally, the Arian Structure for Auxiliary Payload 5, ASAP 5, requirements is selected as the baseline of structural design. The strength and stiffness requirements applied to the structural design are indicated in Table 2.2. Table 2.2: Structural requirements from ASAP5 [40]. Requirement Longitudinal Lateral Strength Acceleration (g) -7.5g/+5.5g \u00b16g Stiffness Fundamental freq. \u226590 Hz \u226545 Hz" + ] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure17.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure17.3-1.png", + "caption": "Fig. 17.3. Comparison of TFR directional dispersion factor of floor panel vibration for different engine rotational speed", + "texts": [], + "surrounding_texts": [ + "VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 209 For the purpose of analysis the vibration dispersion factors at the path of propagation into human body via dash panel, floor panel and seat the comparison was collected in Fig. 17.5." + ] + }, + { + "image_filename": "designv8_17_0004768_9668973_09764722.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004768_9668973_09764722.pdf-Figure5-1.png", + "caption": "FIGURE 5. Magnetic flux density contour plot. (a) NO model, load. (b) NO model, no-load. (c) GO model, load. (d) GO model, no-load.", + "texts": [ + "40% reduced compared with the NO model. The line to line back-electromotive force (B-EMF) was 0.53% increased, the B-EMF total harmonic distortion (THD) was 5.56% reduced, and the cogging torque was 7.42% increased. For the load condition, the average torquewas 5.50% increased, the iron loss was 9.64% reduced, and the efficiency was 0.25% increased. However, the torque ripple was 43.89% increased. The torque increase and iron loss decrease effect of applying the GO was confirmed by the results in Table 2. Fig. 5 shows the magnetic flux density contour plots of the NO and GO models at the load and no-load condition. As shown in Fig. 1(a), the GO has superior B-H curve characteristics in the rolling direction. Therefore, the GO model shows higher saturation (Fig. 5(c)) compared with the NO model (Fig. 5(a)), and the reason for the torque increase was higher saturation on the stator. However, due to the severe saturation on the core, the torque ripple of the GO model was 43.89% higher compared with the NO model. In this paper, VOLUME 10, 2022 46601 design optimization is conducted to handle the pulsation problem. III. OPTIMAL DESIGN OF THE IPMSM USING IMROA For the traction motors of the HEVs, high pulsation characteristics can cause mechanical vibration and acoustic noise in the vehicles [26]. Such torque ripple problems can be solved through the optimal design of the motor structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002672_05.2019.91.20_175779-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002672_05.2019.91.20_175779-Figure2-1.png", + "caption": "Figure 2 \u2013 The grinding wheel MOLEMAB B126-100639 S.630090 type: (a) overall view; (b) during the operation", + "texts": [ + " Grinding is one of the final machining processes of the crankshaft fabrication. Main journals and cranks obtain the dimensions close to the upper tolerance, so that the surface can be finished by hand (lapping and polishing procedures). The examined grinding process was performed with a grinder DB12500 type (Figure 1) equipped with the control system Sinumerik 840D, measurement system MARPOSS and eccentric machining system PENDULUM. The grinding tool was the disc-type grinding wheel MOLEMAB B126- 100639 S.630090 shown in the Figure 2. Its diameter was \u00f82000 mm, and width B = 140 mm, and it was covered with the cubic-form boron nitride (c-BN). The use of large-diameter grinding wheels with abrasives of the highest hardness (diamond, cubic boron nitride) in various tasks of precise shaping makes it possible to carry out preliminary and final grinding of operationally responsible external surfaces in one processing cycle, due to the increased durability of the tool in the technologically correctly built cycle, for example, when grinding rolls of rolling mills after surfacing with wear-resistant wire material [14]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003220_20JIYE_G1103158C.pdf-Figure2.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003220_20JIYE_G1103158C.pdf-Figure2.2-1.png", + "caption": "Figure 2.2 Positive normal and shearing stresses", + "texts": [ + " By studying TSVs with different liner materials, we find it is also possible to control the stress level via the selection of a suitable liner material with a lower elastic modulus. The interesting findings can be attributed to the fact that the choice of a lower Young\u2019s modulus and a porous dielectric liner material could effectively reduce the compressive near surface stress in Si. vii List of figures Figure 2.1 Internal forces in a solid body under a self-equilibrating system of forces.. 8 Figure 2.2 Positive normal and shearing stresses .......................................................... 9 Figure 2.3 LOCOS birds beak ..................................................................................... 14 Figure 2.4 Schematic of a fully filled TSV structure near the wafer surface .............. 16 Figure 2.5 Inelastic scattering in Raman Spectroscopy ............................................... 19 Figure 2.6 Simplified Raman spectrometer layout ....................................", + " Dividing the infinitesimal force dF by the infinitesimal area dA, we get the internal force per unit of area or stress [5]. avg dF dA (2.1) 9 In complex application circumstances, mechanical bodies usually subjected to more than one type of stress at the same time; this brings out the concept of combined stress. In the case of two or more stresses act on one plane, i.e. bending and shear, the internal forces are categorized as biaxial stress. For combined stresses that act in all directions, i.e. bending, torque, and pressure, is triaxial stress. Figure 2.2 shows the stress acting in a rectangular parallelepiped defined by three pairs of facets, which are perpendicular to the three coordinate axis and are located in an infinitesimal neighbourhood of point P [5]. From Figure 2.2, there are three pairs of facets. Each pair of facets is perpendicular to a particular coordinate axis. The stress \u03c311 is positive if it have the same direction as the coordinate axis it parallels to, and also the facet is known as a positive facet for axis x1. According to the convention, the principle stress in the positive direction of axis x1, x2 and x3 are denoted as \u03c311,\u03c322 and \u03c333, respectively. The 10 shearing stresses on the facets i are denoted depending on the direction of the shearing stress vector" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002141_ngRunqiG1000407F.pdf-Figure4-7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002141_ngRunqiG1000407F.pdf-Figure4-7-1.png", + "caption": "Figure 4-7. (a) Even-mode network of the prototype II. (b) Odd-mode network of the prototype II.", + "texts": [ + " Synthesis procedure for the dual-band BPFs discussed in this chapter. ................. 68 Figure 4-5. (a) Even-mode network of the prototype I. (b) Odd-mode network of the prototype I. ..................................................................................................................... 69 Figure 4-6. Frequency responses of the prototype I under different values of tz2 (other design specifications: \u03b81= 112.5o and \u03b82= 144o). ................................................................... 71 Figure 4-7. (a) Even-mode network of the prototype II. (b) Odd-mode network of the - XI - prototype II..................................................................................................................... 73 Figure 4-8. Frequency responses of the prototype II under different values of tz1 (other design specifications: tz2= 30, \u03b81= 112.5o and \u03b82= 144o). ......................................... 74 Figure 4-9. (a) Even-mode network of the prototype III. (b) Odd-mode network of the prototype III", + " As tz2 varies from a negative to positive value, the second pair of TZs is moved from imaginary to real frequencies. The calculated response is indistinguishable from the desired theoretical one, which has verified the synthesis procedure. 73 4.3.2 Prototype II with Two Pair of Controllable TZs For the prototype II, coupled lines are used to control the pair of TZs in the imaginary frequencies (also it has the influence toward the other pair of TZs as tabulated in Table 4.1). Its even- and odd-mode networks are shown in Figure 4-7(a) and (b), respectively. Since the structure of the even- and odd-mode networks remain unchanged, the S-parameters of the prototype II are in the format as that of the prototype I (as seen in (4.8)), with the only difference in the coefficients of the polynomials as 2 2 2 0 0 3 1 2 1 3 2 3 1 3 2 1 2 2 3 1 1 3 2 3 2 2 3 3 4 3 2 1 2 5 3 1 2 2 6 3 2 1 3 1 3 1 3 2 3 7 2 1 8 3 1 2 3 s o e e e s e s s s e s e o o s o s s s o s o k jY Z Z Z Z Z Z Z Z k Z Z Z k Z Z Z Z Z Z Z Z Z k Z Z k jZ Z Z Z k jZ Z Z k Z Z Z Z Z Z Z Z Z Z Z Z Z k Z Z Z k jZ Z Z Z Z (4", + "3, the rejection for the lower/upper side of the 1st/2nd passband improves slightly, while the rejection between the two passbands drops. Figure 4-11 shows the variation of the TZs in the imaginary frequency plane (as the variation of tz1) with fixing the other design specifications. As tz1 changes from -1 to -5, there is little change of the filtering responses as seen in Figure 4-11(a), while there is an obvious change for the group delay as seen in Figure 4-11(b). In a summary of the three circuit prototypes as tabulated in Table 4.1, according to Figure 4-5, Figure 4-7 and Figure 4-9, these circuit schematics share the similar circuit structure and the design principle, while prototype II has an additional degree of freedom in controlling the group delay and prototype III having the capability in further adjusting the in-band ripple factor. Therefore, it can be concluded that the proposed structure and the synthesis procedure has the capability in effectively controlling the in-band ripple factor (\u025b) and the dual-band isolation. 77 Table 4.4 Design Parameters of Prototype III under Different \u025b Characteristic Impedance (\u03a9) \u025b Z1e Z1o Z2 Z3 Zs1 Zs2 160" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004145_f_version_1641441394-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004145_f_version_1641441394-Figure3-1.png", + "caption": "Figure 3. Configuration of a deployment analysis model. Figure 3. Configuration of a deployment analysis model.", + "texts": [ + " 2 22 3 ( ) ( )F C F CL x x z z= \u2212 + \u2212 (2) 6 6 6 6( , ) ( cos , sin )H H G Gx z x L z L\u03d5 \u03d5= + \u2212 (3) 2 22 7 6 6 6 6( ( cos )) ( ( sin ))F G F GL x x L z z L\u03d5 \u03d5= \u2212 + + \u2212 \u2212 (4) 1 1 1 1( , ) ( cos , sin )B B A Ax z x L z L\u03d5 \u03d5= \u2212 + (5) 2 22 2 1 1 1 1( cos ) ) ( sin ) )A F A FL x L x z L z\u03d5 \u03d5= \u2212 \u2212 + + \u2212 (6) 1 2 2 cos ( )B Fx x L \u03d5 \u2212 \u2212= (7) 4 4 4 4( , ) ( cos , sin )E E D Dx z x L z L\u03d5 \u03d5= \u2212 + (8) 2 22 5 4 4 4 4( cos ) ) ( sin ) )D F D FL x L x z L z\u03d5 \u03d5= \u2212 \u2212 + + \u2212 (9) 1 3 3 cos ( )F Cx x L \u03d5 \u2212 \u2212= (10) 1 5 5 cos ( )F Ex x L \u03d5 \u2212 \u2212= (11) 1 7 7 cos ( )F Hx x L \u03d5 \u2212 \u2212= (12) (xH , zH) = (xG + L6 cos \u03d56, zG \u2212 L6 sin \u03d56) (3) L7 = 2 \u221a (xF \u2212 (xG + L6 cos \u03d56)) 2 + (zF \u2212 (zG \u2212 L6 sin \u03d56)) 2 (4) (xB, zB) = (xA \u2212 L1 cos \u03d51, zA + L1 sin \u03d51) (5) L2 = 2 \u221a (xA \u2212 L1 cos \u03d51)\u2212 xF)2 + (zA + L1 sin \u03d51)\u2212 zF)2 (6) \u03d52 = cos\u22121( xB \u2212 xF L2 ) (7) (xE, zE) = (xD \u2212 L4 cos \u03d54, zD + L4 sin \u03d54) (8) L5 = 2 \u221a (xD \u2212 L4 cos \u03d54)\u2212 xF)2 + (zD + L4 sin \u03d54)\u2212 zF)2 (9) \u03d53 = cos\u22121( xF \u2212 xC L3 ) (10) Appl. Sci. 2022, 12, 451 5 of 17 \u03d55 = cos\u22121( xF \u2212 xE L5 ) (11) \u03d57 = cos\u22121( xF \u2212 xH L7 ) (12) For practical design, a 3D configuration design was conducted by CATIA. The 3D model consists of an inner panel, an outer panel, and 12 truss-links, with dimensions of 1620 mm \u00d7 800 mm in the fully deployed configuration (see Figure 3) and a total mass of 11.45 kg as shown in Table 4. The mass of hinges is included in the mass of the panel, and the mass of the bracket is included in the mass of each link. The truss-links connection was finally realized as illustrated in Figure 4a, with several connection angles, as shown in Figure 4b. The connection angles according to the truss-links are summarized in Table 5. The material of the truss-link is aluminum 6061, which has a Young\u2019s modulus of 68.9 GPa, a Poisson\u2019s ratio of 0.33, and density of 2700 kg/m3 [24]", + "77\u00b0 L4 86.00 mm L2 726.28 mm L6 661.34 mm L3 753.58 mm XA (57.00, \u2212288.00) L5 309.38 mm XC (43.00, \u2212120.00) L7 129.54 mm XD (43.00, \u2212640.00) XB (60.79, \u2212148.05) XF (21.44, \u2212873.27) XE (97.34, \u2212573.34) XG (\u221269.40, \u2212152.00) XH (\u221293.18, \u2212812.91) XO (\u221213.00, 11.00) XI (\u221213.20, \u2212813.00) For practical design, a 3D configuration design was conducted by CATIA. The 3D model consis s of an in er panel, an o ter panel, a d 12 truss-links, with dimensions of 1620 mm \u00d7 800 mm in th fully deployed configur tion (see Figure 3) and a total mas 1.45 kg as shown in Tabl 4. The mass of hinges is included in the mass of the panel, and the mass of the bracket is included in the mas of each link. T tru -links connection was finally realized as illustrate in Figure 4 , with several conn ction angles, as show in Figure 4b. The connection angles according to the truss-links are summarized in Table 5. The material of th truss-link is aluminum 6061, which ha Yo ng\u2019s modulus of 68.9 GPa, a Poisson\u2019s ratio of 0.33, and density of 2700 kg/m3 [24]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002984__8_2_8_20-00446__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002984__8_2_8_20-00446__pdf-Figure1-1.png", + "caption": "Fig. 1 Multi-directionally flexibly constrained revolute pair (Kimura et al., 2020)", + "texts": [ + " For example, a robot working in an environment close to people is hard to absorb shock completely when a human bumps into it unintentionally without multi-directional flexibility. When multi-directional flexibility is required for such applications, a mechanism has to be synthesized with many joints which have single-directional flexibility. In this case, the mechanism tends to have a complex structure and a large weight. In order to solve this problem, the authors have proposed a passive revolute pair with multi-axial passive flexibility as shown in Fig.1 (Kimura et al., 2020). This is called the multi-directionally flexibly constrained revolute pair (MFCRP). The MFCRP has a link with two spherical surfaces and a link with two cam surfaces. Each set of a spherical surfaces and cam surfaces is kept in contact at a point by two linear springs. When two links are kept in contact at the two points, the MFCRP has 4 DOF. Since an endpoints of each linear spring is attached on the axis through two spherical surfaces, rotational stiffness around the axis is theoretically zero although stiffness in the other three relative directions are not zero", + " These sizes were bigger than the specified displacement (10 mm). Two cam surfaces were finally arranged in parallel because 1-axial main-rotation was allowed. One of the two cam surfaces was obtained by placing this surface symmetrically about x1 \u2212 z1 plane, y1 \u2212 z1 plane and z1 axis. Then, the two cam surfaces were placed next to each other so that the centers of the spheres were located at [x1 y1 z1]T = [16 0 33]T , [\u221216 0 33]T [mm] as shown in Fig.10 (b). Based on the calculated cam surfaces, a 3D-CAD model of the MFCRP can be made as shown in Fig.1. The FCP which allows the translation along the specified trajectory and three axial rotations was designed. Fig.11 shows the schematic diagram of the motion specification. In this example, tm, \u03b8r,m, \u03b8p,m, \u03b8y,m were chosen as the mainparameters, and um was specified to be zero. In contrast, us was chosen as the sub-parameters, and the other sub-parameters were specified to be zero. As the main-translation for tm, the ordinary helix which is represented as the following equation was specified. 1p(tm) = 60 cos( \u03c0tm2 ) 60 sin( \u03c0tm2 ) 30tm [mm] (26) The range of the main-relative motion was also specified as Am = {tm, \u03b8r,m, \u03b8p,m, \u03b8y,m| 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure9-1.png", + "caption": "Figure 9: Deformed shapes of optimized structures for the inverter.", + "texts": [ + " In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.5-1.png", + "caption": "Figure 10.5: Aerodynamic surface mesh pictured with FFD control points", + "texts": [ + " The MACH framework integrates several high-fidelity analysis tools with geometry engines while propagating design variable derivatives [154]. The subset of aerodynamic shape optimization tools is open-source and freely available. I used the open-source ADflow solver for aerodynamic analysis and derivatives [267]. ADflow is a structured, multiblock, overset RANS solver with discrete adjoint gradients. I use the Spalart\u2013 Allmaras turbulence model and an approximate Newton\u2013Krylov solver for this problem [252]. The aerodynamic mesh (Figure 10.5) consists of approximately 800,000 volume cells and was generated using pyHyp [251], an open-source implementation of the hyperbolic scheme described by Chan and Steger [258]. The aerodynamic solver settings and mesh are virtually identical to those in the MACH aerodynamic shape optimization tutorial. For structural analysis, I use the open-source finite element solver TACS [273]. TACS com- 213 putes efficient adjoint derivatives with respect to the structural sizing (thickness) variables and geometry", + " I only performed a linear static analysis in this scenario, though TACS supports geometric nonlinearity and buckling. Because structural deflections affect the aerodynamic surface and vice-versa, an aerostructural solver is required. I use a block Gauss\u2013Seidel approach to solve the aerostructural analysis and a Krylov method to solve the coupled adjoint [154]. I use two different geometry engines in this problem; one for the wing and one for the hydrogen tanks. The wing was parameterized using the free-form deformation (FFD) method [274] using the open-source implementation in pyGeo [228]. The FFD volume (Figure 10.5) is identical to the one generated in the MACH aerodynamics tutorial and contains 96 design variables. Both the CFD surface mesh coordinates and the structural elements are embedded in the same FFD volume, so geometric displacements are always consistent between the two. CFD surface mesh displacements are propagated to the volume using IDwarp, an open-source implementation of the inverse-distance weighted warping scheme from [257]. 214 I use a different approach to parameterize the tank geometry" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure5.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure5.11-1.png", + "caption": "Figure 5.11: Flow Area around Deflected Valve", + "texts": [ + "40) \ud835\udc34\ud835\udc52\ud835\udc53,\ud835\udc51 = \ud835\udc5f\ud835\udc5d\ud835\udc61,\ud835\udc51 2 [\ud703\ud835\udc5d\ud835\udc61,\ud835\udc51 + 1 2 sin(2\ud703\ud835\udc5d\ud835\udc61,\ud835\udc51)], \ud703\ud835\udc51,\ud835\udc60\ud835\udc61\ud835\udc4e\ud835\udc5f\ud835\udc61 \u2264 \ud703\ud835\udc50 < \ud703\ud835\udc51,\ud835\udc52\ud835\udc5b\ud835\udc51 (5.41) \ud835\udc34\ud835\udc52\ud835\udc53,\ud835\udc51 = 0, \ud703\ud835\udc50 \u2265 \ud703\ud835\udc51,\ud835\udc52\ud835\udc5b\ud835\udc51 (5.42) where \ud703\ud835\udc5d\ud835\udc61,\ud835\udc51 = cos\u22121 ( \ud835\udc5f\ud835\udc50 sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc5d\ud835\udc61,\ud835\udc51 ) (5.43) 68 When the valve is deflected due to fluid pressure in the working chamber, an opening is created. At this point in time, there are two possible flow areas occurring simultaneously; the first of which is the discharge port area as shown in Figure 5.9 and the second would be the circumferential space between the deflected valve and port depicted in Figure 5.11. Assuming negligible curvature of the valve at the discharge port, an approximation for the flow area around the valve is shown in Equation (5.44). \ud835\udc34\ud835\udc53\ud835\udc59\ud835\udc5c\ud835\udc64,\ud835\udc63\ud835\udc4e\ud835\udc59\ud835\udc63\ud835\udc52 = \ud835\udf0b\ud835\udc5f\ud835\udc5d\ud835\udc61,\ud835\udc51(\ud835\udc66\ud835\udc51,\ud835\udc60\ud835\udc61\ud835\udc4e\ud835\udc5f\ud835\udc61 + \ud835\udc66\ud835\udc51,\ud835\udc52\ud835\udc5b\ud835\udc51) (5.44) The effective flow area around the valve is then compared to the effective discharge port area and the orifice flow area for the discharge flow model would be the smaller of the two values as shown in Equation (5.45). \ud835\udc34\ud835\udc5c\ud835\udc5f\ud835\udc53,\ud835\udc51 = min(\ud835\udc34\ud835\udc53\ud835\udc59\ud835\udc5c\ud835\udc64,\ud835\udc63\ud835\udc4e\ud835\udc59\ud835\udc63\ud835\udc52 , \ud835\udc34\ud835\udc52\ud835\udc53\ud835\udc53,\ud835\udc51) (5.45) 69 Based on the prototype design, four internal leakage channels have been identified and are illustrated in Figure 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000372_9312710_09425552.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000372_9312710_09425552.pdf-Figure18-1.png", + "caption": "FIGURE 18. Pictures of a 6/10 E-core DSAFFSPM machine. (a) 10-pole rotor. (b) Stator with 6 E-core modules. (c) Prototype machine.", + "texts": [ + " From Table 4, in terms of stationary harmonics, the dominant harmonic of DSAFFSPM machines with same number of stator poles is approximately the same, while for rotating harmonics, the dominating harmonics of DSAFFSPM machines with odd-rotor-pole-pair-number are different from that with evenrotor-pole-pair-number. IV. EXPERIMENTAL RESULTS In order to validate the above analysis, a 12/10 U-core DSAFFSPM machine and a 6/10 E-core DSAFFSPM machine are prototyped. Their stator, rotor and whole structure photos are displayed in Fig. 17 and Fig. 18, respectively. The no-load flux density and its corresponding spectrum based on flux modulation in the above sections cannot be tested directly in the prototyped machines, only the back-EMF and electromagnetic torque can be shown in the experimental results. Firstly, the line-line back EMF is tested and compared with the FEA result in Fig. 19(a) and Fig. 20(a). It can be seen that the FEA predicted results are in good agreements with the measured waveforms. Fig. 19(b) and Fig. 20(b) show the electromagnetic torque waveforms predicted by FEA and tested by experiment, and two curves match well" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003506_8355919_08355939.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003506_8355919_08355939.pdf-Figure4-1.png", + "caption": "Fig. 4 Coordinates", + "texts": [ + " If the dual vector is expressed as a\u0302a = aa + \u03b5ba in coordinate A and as a\u0302b = ab + \u03b5bb in coordinate B, then there is a\u0302b = q\u0302\u2217 \u25e6 a\u0302a \u25e6 q\u0302. (26) Besides, as for dual quaternion defined by (21), its log- arithm is given as ln q\u0302 = ln q + \u03b5 1 2 rb. (27) Noting that the logarithm maps dual quaternion to a 6D vector. By comparison of sections 2.1 and 2.3, it can be seen that, when describing motion, dual quaternion has many parallels with quaternion. In fact, according to the Kotelnikov transference principle, dual quaternion completely inherits properties of quaternion as shown in Table 1. As shown in Fig. 4, to establish the model of relative motion between the chaser and the target, some necessary coordinates are defined. Earth centered inertial (ECI): denoted as frame I . It is a nonaccelerating reference frame with its origin in the center of the earth, xi pointing to the vernal equinox, and zi pointing to the north pole. yi is given by the right-hand rule. Orbital coordinate: denoted as frame O. Its origin is at the centroid of spacecraft. zo points from the origin to the PENG Xuan et al.: Integrated modeling of spacecraft relative motion dynamics using dual quaternion 371 earth center" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001610_ai.13-12-2017.153473-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001610_ai.13-12-2017.153473-Figure1-1.png", + "caption": "Figure 1. the geometry of proposed antenna , (a) without slot, (b) with one slot, (c) with tuning circuit .Unit in mm", + "texts": [ + " On the other hand, the proposed tunable design (third version), achieves a wider continuous tuned frequency range compared to works [18- 23]; in addition, this version provides a degree of miniaturization compared to works in [ 18,19,20,22]. In all, there is a clear need for a cost-effective and reconfigurable antenna design based on mircrostip technology that is able to communicate with legacy (GPS, GSM, UMTS, LTE) and shows promising adaptability towards 5G (sub 6GHz), enabled by CR technology. The full configurations of the three proposed microstrip multi-band patch antennas are displayed in Figure 1. The layout of the proposed design is based on printed patch radiator. The patch has a compact volume of 50x28.4mm2 printed over an RF4 substrate with size of 70x54x1.6mm3. This type of antenna usually derives its name from its shape/structure. Figure 1 shows a patch antenna, which has a rectangular top layer and thus names appropriately. This patch antenna consists of two metal planes, the bottom layer being the ground plane (70x54mm2) and the top layer is the radiating patch and a dielectric material between them. EAI Endorsed Transactions on Cognitive Communications 05 2017 - 12 2017 | Volume 3 | Issue 12 | e1 Reconfigurable Microstrip Patch Antenna for Future Cognitive Radio Applications 3 A 50-Ohm microstrip line is used to feed the proposed structure. This feed was chosen due to ease of fabrication and matching. Several simulation optimisations were carried out to select the optimal location of the feedline. However, there was no a significant effect on the antenna return loss, when the feedline set at both edges or in the middle. Thus, the feeding strip was connected at the edge of the middle part of the patch as shown in Figure 1. An I-shape slot is embedded over the surface of the patch as shown in Figure 1(b). The main objectives of this etched slot are to shift the resonant frequencies downwards, as well as reducing the antenna size. The slot has uniform width of 2mm. The full dimensions of the top patch is stated in Figure 1. To prove the contribution of the embedded slots over the patch surface, the calculated and measured S11 of the present antenna with and without slot is studied and presented in Figure 2. One can note that the simulated model of the antenna without the inclusion of the uniform slot operates at the LTE2600MHz. However, as previously mentioned, the main target of the embedded slots is to shift the resonant frequencies downwards in order to cover the spectrum of other standards. Therefore, by carefully optimizing the shape and locations of the embedded slot, other services such as WLAN was easily accomplished within the same antenna structure", + " Although, the above-mentioned antennas (with and without slot) have achieved some advantages such as size miniaturization and covering two important frequency bands of LTE and WLAN, however, these two resonant frequencies are fixed and cannot be altered/tuned once the antenna is fabricated, and this may not be considered attractive for cognitive radio system. Thus, in the first instance , a lumped capacitor is attached over the proper position of the I-shaped slot of the second antenna as shown in Figure 1 (d). By varying the capacitance of the used capacitor from 0.5pF to 3pF, the resonant frequency is widely shifted downwards from 2300MHz to 1500MHz, covering several wireless standards such as GPS, GSM and UMTS as indicated in Figure 5. For validation purposes, the I-shaped slot antenna along with a varactor diode and a suitable DC bias circuit were further explored as shown in Figure 6. The exploited BBY5202W varactor diode has come up with a tuning reverse bias voltage range from 0\u201315 V. The two RF chokes value of 100 nH were used for DC passing, and a 100 ohm resistor to control the current flowing to the varactor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure8-1.png", + "caption": "Fig. 8. The model comprised two rims of the twin rear wheels of the rear axis of the tipper: a) general view; b) and c) wireframe style perpendicular views; d) wireframe style isometric view", + "texts": [ + " This increased twice the loading of twin wheels of the tipper-truck rear axle. This led to reaching a value of 2 \u00b7Tra\u2212perm by the torque transferrable by the twin wheel of the tipper-truck rear axle. The stress distribution in the assembly comprised of two rims of twin rear wheels of the rear axis and was obtained using the Finite Element Method implemented in the software Autodesk Inventor Professional v. 2021. The single rim was presented in Fig. 7. To carry out a numerical calculation of the model of the mentioned assembly was elaborated (Fig. 8). Each rim was made of weldable steel with a carbon content below 0.3 wt.%. It was assumed that the mechanical properties of steel AS/NZS 3679.1- 300 [64] were very close to these of the steel applied to the rim analyzed. This assumption was supported by the fact, that during the initial (rough, due to the unsatisfactory technical condition of the used portable X-ray fluorescence (XRF) analyzer) analysis of the chemical composition of steel, an increased manganese content was observed. Also, from conversations with MercedesBenz truck dealers, information was obtained that the wheel rims are made of hot-rolled steel. The Yield stress for such steel was equal to 300 MPa, and the Tensile Strength was equal to 440 MPa [64]. The rims are connected by the plane interface covering the rim end faces (Fig. 8c). The corresponding pin holes / bolts in both hubs are coaxial with each other (Fig. 8b). The contact elements were plane ones with the augmented option. The surfaces of the rims contacting with the wheel tires were fixed on one bottom half of their circumference (Fig. 9). The common practice is that the rim is fixed in its holes and possibly on the inner surface of the hole [65\u201368]. The fixing of the rim surfaces, as in the present case, facilitates the introduction of changes in the rim load without the need to model a very complex and difficult element, which is the tire. However, it may introduce some rigidity of the analyzed rims concerning reality" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004930_O201024441466953.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004930_O201024441466953.pdf-Figure1-1.png", + "caption": "Fig. 1 Flywheel energy storage system", + "texts": [], + "surrounding_texts": [ + "\ud55c\uad6d\uc18c\uc74c\uc9c4\ub3d9\uacf5\ud559\ud68c\ub17c\ubb38\uc9d1/\uc81c 20 \uad8c \uc81c 8 \ud638, 2010\ub144/717\n* 1. \uc11c \ub860\n\uc5d0\ub108\uc9c0 \uc800\uc7a5\uc6a9 \ud50c\ub77c\uc774\ud720 \uc7a5\uce58\ub294 \ud06c\uac8c \ud50c\ub77c\uc774\ud720\uc744 \ud3ec\ud568\ud55c \ud68c\uc804\uccb4\ubd80, \uc804\uae30 \uc5d0\ub108\uc9c0\uc640 \ud68c\uc804 \uc5d0\ub108\uc9c0\uc758 \uc0c1 \ud638 \ubcc0\ud658\uc744 \uc704\ud55c \uc804\ub3d9/\ubc1c\uc804\uae30, \ud68c\uc804\uccb4\ub97c \uc9c0\uc9c0\ud558\ub294 \ubca0 \uc5b4\ub9c1\ubd80\ub85c \uad6c\uc131\ub41c\ub2e4. \ud50c\ub77c\uc774\ud720\uc740 \uacf5\uae30 \ub9c8\ucc30\uc744 \ucd5c\uc18c\ud654 \ud558\uae30 \uc704\ud574\uc11c \uc9c4\uacf5 \ub0b4\uc5d0\uc11c \ud68c\uc804\ud558\ub294 \uacbd\uc6b0\uac00 \ub9ce\uc740\ub370, \uc774 \ub54c\ub294 \uad6c\ub984 \ubca0\uc5b4\ub9c1\uacfc \uac19\uc740 \uc811\ucd09\uc2dd \ubca0\uc5b4\ub9c1\uc758 \uc0ac\uc6a9\n\uc774 \ubd88\uac00\ub2a5\ud558\uc5ec \ub9c8\uadf8\ub124\ud2f1 \ubca0\uc5b4\ub9c1\uc774\ub098 \ucd08\uc804\ub3c4 \ubca0\uc5b4\ub9c1 \uacfc \uac19\uc740 \ube44\uc811\ucd09 \ubca0\uc5b4\ub9c1\uc774 \uc0ac\uc6a9\ub41c\ub2e4. \uc0ac\uc2e4 \ucd08\uc804\ub3c4 \ubca0\n\u2020 \uad50\uc2e0\uc800\uc790; \uc815\ud68c\uc6d0, \ud55c\uad6d\uacfc\ud559\uae30\uc220\uc5f0\uad6c\uc6d0 \uc5d0\ub108\uc9c0\uba54\uce74\ub2c9\uc2a4\uc13c\ud130 E-mail : sjongkim@kist.re.kr Tel : (02)958-5610, Fax : (02)958-5659 * \ud55c\uad6d\uacfc\ud559\uae30\uc220\uc5f0\uad6c\uc6d0 \uc5d0\ub108\uc9c0\uba54\uce74\ub2c9\uc2a4\uc13c\ud130 ** \uc815\ud68c\uc6d0, \ud55c\uad6d\uc804\ub825\uacf5\uc0ac \uc804\ub825\uc5f0\uad6c\uc6d0\n\uc5b4\ub9c1\uc744 \uc4f0\ub294 \uacbd\uc6b0\uc5d0\ub3c4 \ub0ae\uc740 \uac10\uc1e0\ub825\uc744 \ubcf4\uc644\ud558\uae30 \uc704\n\ud574\uc11c \ucd94\uac00\ub85c \uc18c\ud615 \ub9c8\uadf8\ub124\ud2f1 \ubca0\uc5b4\ub9c1\uc744 \ub310\ud37c\ub85c \uc0ac\uc6a9 \ud558\ub294 \uacbd\uc6b0\uac00 \ub9ce\uc73c\ubbc0\ub85c, \uc5d0\ub108\uc9c0 \uc800\uc7a5\uc6a9 \ud50c\ub77c\uc774\ud720\uc5d0\uc11c \ub9c8\uadf8\ub124\ud2f1 \ubca0\uc5b4\ub9c1\uc758 \uc0ac\uc6a9\uc740 \ub300\uc138\ub77c\uace0 \ub9d0\ud560 \uc218 \uc788\ub2e4. \uadf8\ub7ec\ub098, \ub9c8\uadf8\ub124\ud2f1 \ubca0\uc5b4\ub9c1\uc740 \uc2e4\uc2dc\uac04 \ud53c\ub4dc\ubc31 \uc81c\uc5b4\ub85c\uc368\n\uc5b4\ub5a4 \uc0c1\ud669\uc5d0\uc11c\ub3c4 \uc548\uc815\uc131\uc744 \ubcf4\uc7a5\ud574\uc57c \ud55c\ub2e4\ub294 \ubd80\ub2f4 \uc678 \uc5d0\ub3c4, \ud68c\uc804\uccb4\ub97c \uc7a5\uc2dc\uac04 \ubd80\uc0c1\uc2dc\ud0a4\uae30 \uc704\ud574 \uc790\uccb4\uc801\uc73c\ub85c \uc18c\ubaa8\ud558\ub294 \uc804\ub825\uc774 \ud06c\ub2e4\ub294 \ub2e8\uc810\uc774 \uc788\ub2e4. \uc548\uc815\uc131 \ubcf4\uc7a5\uc744 \uc704\ud574\uc11c\ub294 \ud558\ub4dc\uc6e8\uc5b4\uc801 \uc789\uc5ec\uc131(redundancy)\uacfc \ud68c\uc804\uccb4\n\uc5ed\ud559 \uae30\ubc18\uc758 \ub2e4\uc591\ud55c \uc81c\uc5b4\uae30 \uac15\uac74 \uc124\uacc4 \uae30\ubc95\ub4e4\uc774 \uc5f0 \uad6c\ub418\uc5b4 \uc654\uace0, \uc18c\ubaa8\uc804\ub825 \ubb38\uc81c\ub97c \uadf9\ubcf5\ud558\ub294 \ubc29\ubc95\uc73c\ub85c \ub294 \uc601\uad6c\uc790\uc11d\uc774 \uc815\uc801\uc778 \ud798(static force)\uc744 \uc81c\uacf5\ud558\uace0\n\uc804\uc790\uc11d\uc774 \uc81c\uc5b4\ub825\ub9cc\uc744 \ub2f4\ub2f9\ud558\ub294 \ud558\uc774\ube0c\ub9ac\ub4dc \uad6c\uc870\uac00 \ud6a8\uacfc\uc801\uc778 \uac83\uc73c\ub85c \uc54c\ub824\uc838 \uc788\ub2e4. \uc774\ub97c \ud558\uc774\ube0c\ub9ac\ub4dc \ub9c8 \uadf8\ub124\ud2f1 \ubca0\uc5b4\ub9c1(hybrid magnetic bearing, HMB)\uc774\ub77c", + "\uae40 \uc6b0 \uc5f0 \u2024\uc774 \uc885 \ubbfc \u2024\ubc30 \uc6a9 \ucc44 \u2024\uae40 \uc2b9 \uc885\n718/\ud55c\uad6d\uc18c\uc74c\uc9c4\ub3d9\uacf5\ud559\ud68c\ub17c\ubb38\uc9d1/\uc81c 20 \uad8c \uc81c 8 \ud638, 2010\ub144\n\ud55c\ub2e4(1~3). HMB\uc5d0\uc11c\ub294 \ud68c\uc804\uccb4\uac00 \ubd80\uc0c1 \uc0c1\ud0dc\uc5d0\uc11c \uc9c4\ub3d9 \uc774 \ubbf8\uc18c\ud560 \uacbd\uc6b0 \uc774\ub860\uc801\uc73c\ub85c \uc18c\ubaa8 \uc804\ub825\uc740 \uac70\uc758 \uc5c6\ub2e4. \uc774 \ub17c\ubb38\uc5d0\uc11c\ub294 1 kWh\uae09 \uc5d0\ub108\uc9c0 \uc800\uc7a5\uc6a9 \ud50c\ub77c\uc774\ud720 \uc7a5\uce58\uc5d0 \uc7a5\ucc29\ub418\ub294 \uc57d 140 kg\uc758 \ud68c\uc804\uccb4\ub97c \uc9c0\uc9c0\ud558\uae30 \uc704\ud55c HMB\uc758 \uc124\uacc4\uacfc\uc815\uc744 \uc18c\uac1c\ud55c\ub2e4. \ud50c\ub77c\uc774\ud720\uc758 \uc5d0\n\ub108\uc9c0 \uc800\uc7a5 \ud6a8\uc728\uc744 \ub192\uc774\uae30 \uc704\ud574\uc11c\ub294 \uc8fc \uc9c8\ub7c9 \uad00\uc131 \ubaa8\uba58\ud2b8\uac00 \ucee4\uc57c \ud558\uae30\uc5d0(4), Fig. 1\uc5d0 \ub098\ud0c0\ub0b8 \ubc14\uc640 \uac19\uc774 \ud68c\uc804\uccb4\ub294 \uc678\uc804\ud615(outer-rotor type)\uc73c\ub85c \uc124\uacc4\ub418\uc5c8\uc73c \uba70 \ucd95 \ubc29\ud5a5 \ub192\uc774\ub97c \ucd5c\uc18c\ud654\ud558\uae30 \uc704\ud55c \uad6c\uc870\ub97c \uac16\ub294\ub2e4. \ud2b9\ud788, \ucd95 \ubc29\ud5a5 HMB\uac00 \ud68c\uc804\uccb4\uc758 \uc790\uc911\uc744 \uac10\ub2f9\ud558\uae30 \uc704\ud55c \uc601\uad6c\uc790\uc11d\uacfc \uc77c\uccb4\ud654\ub41c \uac83\uc774 \uad6c\uc870\uc801 \ud2b9\uc9d5\uc774\ub2e4. \uc774\ud558 \ubcf8\ub860\uc5d0\uc11c\ub294 \ucd95 \ubc29\ud5a5 \ubc0f \ubc18\uacbd \ubc29\ud5a5 HMB\uc758 \uad6c \uc870\uc640 \uc6d0\ub9ac\ub97c \uc18c\uac1c\ud558\uace0, \uc790\uae30\ud68c\ub85c \ud574\uc11d\uacfc \uc720\ud55c\uc694\uc18c\n\ud574\uc11d\uc744 \ud1b5\ud574 \uc124\uacc4 \uc0ac\uc591\uc744 \uacb0\uc815\ud558\ub294 \uacfc\uc815\uacfc \ucd5c\uc885\uc801 \uc73c\ub85c \uc608\uce21\ub41c \uc131\ub2a5\uc744 \uc81c\uc2dc\ud55c\ub2e4.\n2. \ucd95 \ubc29\ud5a5 HMB\uc758 \uc124\uacc4\n2.1 \uad6c\uc870 \ubc0f \uc6d0\ub9ac \uc774 \ub17c\ubb38\uc5d0\uc11c \uc81c\uc548\ud558\ub294 \ucd95 \ubc29\ud5a5 HMB\uc758 \uad6c\uc870\ub294 Fig. 2\uc640 \uac19\ub2e4. \ucd95 \ubc29\ud5a5\uc73c\ub85c \uc790\ud654\ub41c \ub9c1(ring)\ud615 \uc601\uad6c\n\uc790\uc11d\uc774 \ud68c\uc804\uccb4\uc758 \uc0c1\ubd80 \ud45c\uba74\uacfc \uc77c\uc815\ud55c \uacf5\uadf9\uc744 \ub450\uace0 \ubc30\uce58\ub418\uc5b4 \ud68c\uc804\uccb4\uc758 \uc815\uc801 \ud558\uc911\uc744 \uc9c0\uc9c0\ud558\ub294 \ub3d9\uc2dc\uc5d0, \ucd95 \ubc29\ud5a5 HMB\ub97c \uc704\ud55c \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\uc744 \uc81c\uacf5\ud560 \uc218 \uc788\ub3c4\ub85d \ud55c \uac83\uc774 \uad6c\uc870\uc801\uc778 \ud2b9\uc9d5\uc774\ub2e4. \uc774\ub7ec\ud55c \ucd95 \ubc29\ud5a5 HMB\ub294 \ud558\uc911 \uc9c0\uc9c0\uc640 \ucd95 \ubc29\ud5a5 \uc81c\uc5b4\uac00 \ub3d9\uc2dc\uc5d0 \uac00\ub2a5\ud558\n\uc5ec \ud558\uc911 \uc9c0\uc9c0\ub97c \uc704\ud55c \uc601\uad6c\uc790\uc11d\uc744 \ucd94\uac00\ub85c \uc7a5\ucc29\ud558\uc9c0 \uc54a\uc544\ub3c4 \ub418\ubbc0\ub85c \uc804\uccb4\uc801\uc73c\ub85c \uc2dc\uc2a4\ud15c\uc758 \ud06c\uae30\ub97c \uc904\uc774\uace0, \ubb34\uac8c\ub97c \uacbd\ub7c9\ud654\ud560 \uc218 \uc788\ub294 \uc774\uc810\uc774 \uc788\ub2e4.\nFig. 2\uc5d0\uc11c \ub204\uc124 \uc790\uc18d\uc774 \uc5c6\uace0 \ucf54\uc5b4\uc5d0\uc11c\uc758 \uc790\uae30 \uc800\nCoil Stator\nPM gap1\nRotor gap2\nFig. 2 Thrust HMB design for flywheel\n\ud56d\uc774 \uc5c6\ub294 \uc774\uc0c1\uc801\uc778 \uacbd\uc6b0\ub97c \uac00\uc815\ud560 \ub54c, \uc601\uad6c\uc790\uc11d\uc5d0\n\uc758\ud574 \ubc1c\uc0dd\ud558\ub294 \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\uc740 \uad75\uc740 \uc2e4\uc120 \ud654\uc0b4\ud45c \ub85c \ud45c\uc2dc\ub41c \uacbd\ub85c\ub97c \ub530\ub978\ub2e4. \uc774 \uacbd\ub85c\ub294 3\uac1c\uc758 \uacf5\uadf9\uc744 \ud3ec\ud568\ud558\ub294\ub370, \uba3c\uc800 \uadf8\ub9bc\uc5d0\uc11c gap1\uc73c\ub85c \ud45c\uc2dc\ub41c \uacf5\uadf9 \uc744 \uc9c0\ub098\ub294 \uc790\uc18d\uc740 \ud68c\uc804\uccb4 \uc790\uc911\uc744 \uc9c0\uc9c0\ud558\ub294 z\ubc29\ud5a5 \uc804\uc790\uae30\ub825\uc744 \uc0dd\uc131\ud558\uace0, \uc774\ud6c4 \uc591\ubd84\ub418\uc5b4 gap2\ub85c \ud45c\uc2dc \ub41c \uc0c1\ud558 \uacf5\uadf9\uc744 \uc9c0\ub09c\ub2e4. \ud68c\uc804\uccb4\uc758 \ubd80\uc0c1\uc774 \uc815\uc0c1 \uc0c1\ud0dc \uc77c \ub54c, \uc989, \uc0c1\ud558 gap2\uc758 \ud06c\uae30\uac00 \ub3d9\uc77c\ud560 \ub54c\ub294 \uc591\ubd84\ub418 \ub294 \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\uc758 \ud06c\uae30\ub3c4 \ub3d9\uc77c\ud558\ub2e4. \uadf8\ub7ec\ub098 \uc0c1\ud558 gap2\uc758 \ud06c\uae30\uac00 \uc0c1\uc774\ud560 \uacbd\uc6b0\uc5d0\ub294, \uc608\ub97c \ub4e4\uc5b4 \ud68c\uc804\uccb4 \uac00 -z\ubc29\ud5a5\uc73c\ub85c \uc774\ub3d9\ud558\uc5ec \ud558\uce21 gap2\uac00 \uc0c1\uce21 gap2\ubcf4 \ub2e4 \uc881\uc544\uc9c8 \uacbd\uc6b0\uc5d0\ub294, \ud558\uce21 gap2\ucabd\uc73c\ub85c \ud750\ub974\ub294 \uc790\uc18d\n\uc774 \uc99d\uac00\ud558\uace0 \uc790\uae30\ub825\ub3c4 \uc99d\uac00\ud558\uc5ec \ud68c\uc804\uccb4\ub294 \ub354\uc6b1 \uc544 \ub798\ucabd\uc73c\ub85c \ub04c\ub824\uac00\uac8c \ub41c\ub2e4. \uc989, \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\ub9cc\uc73c\ub85c\n\ub294 \uc815\uc0c1 \uc0c1\ud0dc\ub97c \uc720\uc9c0\ud560 \uc218 \uc5c6\ub294 \ubd88\uc548\uc815\uc131\uc774 \uc874\uc7ac\ud55c \ub2e4. \uc774\ub97c \uc548\uc815\ud654\ud558\uae30 \uc704\ud574\uc11c, Fig. 2\uc640 \uac19\uc774 \uc911\uc2ec\ucd95 \uc8fc\uc704\ub85c \ub3c4\ub11b \ud615\ud0dc\uc758 \ucf54\uc77c\uc774 \uac10\uaca8\uc788\ub2e4. \ucf54\uc77c\uc5d0\uc11c \ubc1c\n\uc0dd\ud558\ub294 \uc81c\uc5b4 \uc790\uc18d\uc740 \uc810\uc120 \ud654\uc0b4\ud45c\ub85c \ud45c\uc2dc\ub41c \uacbd\ub85c\ub97c \uac16\ub294\ub370, \ud654\uc0b4\ud45c\uc758 \ubc29\ud5a5\uc740 \ucf54\uc77c\uc758 \uc804\ub958 \ubc29\ud5a5\uc5d0 \ub530\ub77c \ubc14\ub00c\uace0 \uc790\uc18d\uc758 \uc138\uae30\ub294 \uc804\ub958\uc758 \ud06c\uae30\uc5d0 \ube44\ub840\ud55c\ub2e4. \uadf8\n\ub9bc\uc758 \uc81c\uc5b4 \uc790\uc18d \ubc29\ud5a5\uc740 \ud68c\uc804\uccb4\ub97c \uc704\ucabd\uc73c\ub85c \uc774\ub3d9\uc2dc \ud0a4\uae30 \uc704\ud55c \uacbd\uc6b0\ub85c\uc11c, \uc0c1\uce21 gap2\uc5d0\uc11c\ub294 \uc81c\uc5b4 \uc790\uc18d\uacfc\n\ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\uc758 \ubc29\ud5a5\uc774 \uc77c\uce58\ud558\uc5ec \uc804\uc790\uae30\ub825\uc774 \uc99d\uac00 \ud558\uace0, \ud558\uce21 gap2\uc5d0\uc11c\ub294 \uadf8\ub4e4\uc758 \ubc29\ud5a5\uc774 \ubc18\ub300\uac00 \ub418\uc5b4 \uc804\uc790\uae30\ub825\uc774 \uac10\uc18c\ud55c\ub2e4. \uc81c\uc5b4 \uc790\uc18d\uc774 \uc99d\uac00\ud558\uc5ec \uc0c1\uce21\n\uacf5\uadf9\uc5d0\uc11c\uc758 \uc804\uc790\uae30\ub825\uc774 \ub354 \ucee4\uc9c0\uba74 \ud68c\uc804\uccb4\ub294 \uc704\ucabd\uc73c \ub85c \uc774\ub3d9\ud55c\ub2e4. \uc989, \ud68c\uc804\uccb4\uc758 \uc0c1\ud558 \ubc29\ud5a5(\ucd95 \ubc29\ud5a5) \ubcc0\uc704\n\ubc1c\uc0dd \uc2dc\uc5d0 \uc81c\uc5b4 \uc804\ub958\ub97c \uc801\uc808\ud788 \uc81c\uc5b4\ud558\uba74 \ud68c\uc804\uccb4\ub97c \uc815\uc0c1 \uc0c1\ud0dc \uc704\uce58\ub85c \ubcf5\uc6d0\uc2dc\ud0a4\ub294 \uac83\uc774 \uac00\ub2a5\ud558\ub2e4. \ud55c\ud3b8, \ud68c\uc804\uccb4\uac00 \uc815\uc0c1 \uc0c1\ud0dc \uc704\uce58\ub97c \uc720\uc9c0\ud558\uace0 \uc788\ub2e4 \uba74 \uc81c\uc5b4 \uc804\ub958\ub294 \uac70\uc758 0A\uac00 \ub420 \uac83\uc774\ub2e4. \uadf8\ub7ec\ub098, \uc815\uc0c1 \uc0c1\ud0dc\uc5d0\uc11c \uc601\uad6c\uc790\uc11d\uc5d0 \uc758\ud55c \ucd95 \ubc29\ud5a5 \uc790\uae30\ub825\uc774 \ud68c\uc804\n\uccb4\uc758 \uc790\uc911\uacfc \uc77c\uce58\ud558\ub3c4\ub85d \uc601\uad6c\uc790\uc11d\uacfc \uacf5\uadf9\uc758 \ud06c\uae30\ub97c", + "\ud55c\uad6d\uc18c\uc74c\uc9c4\ub3d9\uacf5\ud559\ud68c\ub17c\ubb38\uc9d1/\uc81c 20 \uad8c \uc81c 8 \ud638, 2010\ub144/719\n\uc815\ud655\ud788 \uc124\uacc4\ud558\uace0 \uc81c\uc791\ud558\uae30\ub780 \ubd88\uac00\ub2a5\uc5d0 \uac00\uae5d\ub2e4. \uadf8\ub7ec\n\ubbc0\ub85c \uadf8 \ub450 \ud798 \uc0ac\uc774\uc758 \ucc28\uc774\ub97c \ubcf4\uc0c1\ud560 \ud544\uc694\uc131\uc740 \ud56d \uc0c1 \ubc1c\uc0dd\ud558\uba70, \uc774\ub97c \ucd95 \ubc29\ud5a5 HMB\uc5d0\uc11c \ubcf4\uc0c1\ud558\uae30 \uc704 \ud558\uc5ec \ucd95 \ubc29\ud5a5 \ucf54\uc77c\uc5d0 \uc57d\uac04\uc758 \uc624\ud504\uc14b(offset) \uc804\ub958\ub97c \uc9c0\uc18d\uc801\uc73c\ub85c \uc778\uac00\ud574\uc57c \ud55c\ub2e4. \uc774\ub294, \ucd95 \ubc29\ud5a5 HMB\uc758\n\uc601\uad6c\uc790\uc11d \uc124\uacc4 \uc815\ud655\ub3c4\uc5d0 \ub530\ub77c \uc804\uccb4 \ud50c\ub77c\uc774\ud720 \uc2dc\uc2a4 \ud15c\uc758 \uc18c\ubaa8\uc804\ub825\uc774 \uc88c\uc6b0\ub420 \uc218 \uc788\uc74c\uc744 \uc758\ubbf8\ud55c\ub2e4. 2.2 \uc790\uae30\ud68c\ub85c \ud574\uc11d \ubc0f \uc124\uacc4 \ubcc0\uc218 \uc120\uc815 Fig. 3\uc740 \uc774 \ub17c\ubb38\uc5d0\uc11c \uc81c\uc548\ud558\ub294 \ucd95 \ubc29\ud5a5 HMB\uc758 \uc124\uacc4 \uacfc\uc815\uc744 \ubcf4\uc5ec\uc8fc\ub294 \ud50c\ub85c\uc6b0\ucc28\ud2b8(flow chart)\uc774\ub2e4. \uc6b0\uc120, \ud50c\ub77c\uc774\ud720 \uc2dc\uc2a4\ud15c\uc758 \uc5d0\ub108\uc9c0 \uc800\uc7a5 \uc6a9\ub7c9\uc5d0 \ub530\ub77c \ud68c\uc804\uccb4\uc758 \ud615\uc0c1, \ud06c\uae30\uc640 \ubb34\uac8c, \ud68c\uc804\uc18d\ub3c4, \uadf8\ub9ac\uace0 Fig. 1\uacfc \uac19\uc740 \ub300\ub7b5\uc801\uc778 \uad6c\uc870 \ub4f1\uc774 \uc815\ud574\uc9c0\uba74, \uba3c\uc800 \ucd95 \ubc29 \ud5a5 HMB\uc758 \uc601\uad6c\uc790\uc11d\uacfc \ucf54\uc77c\uc5d0 \ub300\ud55c \uc790\uae30\ud68c\ub85c\uc758 \ud574 \uc11d\uc744 \uc218\ud589\ud55c\ub2e4. \uc774\ub294 \ucd95 \ubc29\ud5a5 HMB\uac00 \uc801\uc808\ud55c \uc815\uc801\n(static), \ub3d9\uc801 \ubd80\ud558\uc6a9\ub7c9\uc744 \uac16\ub3c4\ub85d, \uc601\uad6c\uc790\uc11d \ud06c\uae30\uc640 \uacf5\uadf9\uc758 \ud06c\uae30, \ucf54\uc5b4 \uba74\uc801, \uad8c\uc120\uc218 \ub4f1\uc5d0 \ub300\ud55c \ucd08\uae30 \uc124 \uacc4\uce58\ub97c \uc5bb\uae30 \uc704\ud568\uc774\ubbc0\ub85c, \ub204\uc124 \uc790\uc18d\uacfc \ud504\ub9b0\uc9d5 (fringing) \ud6a8\uacfc \ubc0f \ucf54\uc5b4\uc5d0\uc11c\uc758 \uc790\uae30\uc800\ud56d(reluctance)" + ] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure10-1.png", + "caption": "FIGURE 10. Geometry of the antenna (a): simulation prototype (b): measurement prototype [24].", + "texts": [ + " This is done by suppressing the unwanted HOMs in the metasurfaces to avoid radiation pattern distortion. Suppression is done in this work by adding slots and ground into the unit cells of the metasurface. From Fig. 9, it is noticed that three new modes resonating below 5GHz are introduced, denoted as Jsc, where the subscript indicates the \u2018\u2018short-circuit\u2019\u2019 condition. In [24], the CMA method is used to determine the most promising current modes which can contribute to form the desired pattern. The structure of the proposed antenna in this study is illustrated in Fig. 10. Firstly, the CM analysis on the conducting plane, which is modeled based on a handheld device dimensioned at 150\u00d775 mm2. This is done to find the proper position of the capacitive coupling elements (CCEs) used to excite the relevant current modes at 2.45 GHz. The MS of the first eight modes of the proposed antenna is shown in Fig. 11. It is observed that in the frequency range of interest, most of the modes have a value near to one, except for mode 5 and mode 6. It is found that only modes 4 and 8 are relevant to be excited, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000437_-ijaefea20210709.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000437_-ijaefea20210709.pdf-Figure6-1.png", + "caption": "Figure 6. Total deformation", + "texts": [], + "surrounding_texts": [ + "In addition, the machine's sorting speed is faster than that of a human operator, resulting in a significant reduction in the cost of inventory. When it comes to packaging, the industry where it is made is where it belongs. Used as a large-scale piece of machine hardware (such a machine's construction). Nuts of close dimension are utilized in construction of structures and towers. Structural analysis is done for the sorter machine. Equivalent stresses, total deformation and factor of safety is checked. Design is safe. Design and Analysis of Nut and Bolt Separating Machine 101 Int. J. of Analytical, Experimental and Finite Element Analysis www.rame.org.in" + ] + }, + { + "image_filename": "designv8_17_0001217_7419931_07372383.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001217_7419931_07372383.pdf-Figure4-1.png", + "caption": "FIGURE 4. Structure of the designed model. (a) Core and coil parts. (b) Concentrator part. (c) Complete model.", + "texts": [ + " The Cartesian coordinates (Ex, Ey, Ez) are used for describing the locations of the elements in the array, and the cylindrical coordinates (Er, E\u03b8, Ez) are used for magnetic field derivations for individual electromagnet. For haptic rendering devices, the repulsive magnetic force generated is the most important criterion when VOLUME 4, 2016 301 making decisions, besides which there is also stiffness which is the rigidity of the virtual object. In the simulation step, magnetic flux density B is solved by FEM simulation. A. MAGNETIC FIELD CONCENTRATED ELECTROMAGNET MODEL STRUCTURE AND DESIGN PARAMETERS The components of the designed magnetic field concentrated electromagnet model is depicted in Fig. 4. We start with a basic electromagnet model shown in Fig. 4a which only consists of a metal core and a coil. To augment the power usage efficiency, we introduce a magnetic field concentrator which concentrates the magnetic field to the upper part of the model as shown in Fig. 4b. When constructing an array, the model is expected to be isolated so that the magnetic field generated by neighbouring elements would not cause serious interference. To realize this, an isolator is designed to shield the magnetic field and the complete structure of a single designed electromagnet model is depicted in Fig. 4c. From innermost to outermost the components of the electromagnet model are soft iron core, multi-turn coil which are for magnetic field generation, permanent magnet concentrator for magnetic field concentration andmu-metal shell for magnetic field isolation. A summary of the designed parameters is listed in Table 1 The detailed design is discussed in the following order: in Section III-B, we describe the configuration of the core and the coil of the electromagnet model. In Section III-C, we introduce the design and mechanics of the magnetic field concentrator", + " In addition, MATLAB scripting environment is integratedwithMultiphysics via the LiveLink, which provides additional flexibility in generating, running and processing the model in MATLAB while applying its functions. Therefore the whole modeling and simulating process can be done in MATLAB from scratch. Our models are built directly in 3D and is under magnetostatic analysis framework where the current is considered as stable. The 3D model is meshed with tetrahedra elements. To solve the spatial magnetic field, all the field equations are set. B. PERFORMANCE OF THE DESIGNED ELECTROMAGNET MODEL The magnetic field distributions of the electromagnet models depicted in Fig. 4 when stimulated by 1A DC are shown in Fig. 12. VOLUME 4, 2016 307 The basic electromagnet model produces uniformly distributed magnetic field as in Fig. 12a. The concentrating effect of the concentrator and the isolating effect of the isolator can be seen in Fig. 12b and Fig. 12c respectively. The vertical force strength exerted is compared among the basic model, the concentrated model and the complete model shown in Fig. 4. All of the threemodels have the same settings for the coil, i.e., the dimensions, the turns of wire and the current value. Simulations are done which scan the force generated along the x-axis at 1 cm and 2 cm above the array model. The current value of the three models is set as 1A. As can be seen in Fig. 13, the magnetic force forms a bell shaped field above the element. The force generated is augmented significantly by the introduction of the concentrator and the isolator in the complete model" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure48-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure48-1.png", + "caption": "Figure 48 P-POD Mk. IV Bracket FEA Results", + "texts": [ + " The load imparted on the Door is transferred in unequal parts to the Bracket and the hinges on the Collar. Because of the geometry, the bracket takes 58% of the Z-axis loading. In reality, this load is transferred through the NEA Release Mechanism, as the door is attached to it through the Bracket. Therefore, to apply the load in the FEA, the load was applied to the NEA\u2019s section area that interfaces to the back face of the bracket, behind the conical cup interface. The FEA results are shown below in Figure 48. Areas of heighest stress include areas near the point where the top side spar meets the the back face, and under the part in the edge blend under where the switch attaches to the bracket. These areas contain high concentrations of stress. Other areas of high load include the side spars themselves, and the area at the bottom of the conical cup, where material was removed to make room for the new door geometry, but these areas still exhibited high margins. The margin of safety at the high stress areas was Page 64 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004336_s-3941981_latest.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004336_s-3941981_latest.pdf-Figure14-1.png", + "caption": "Fig. 14: A comparison of the original and optimized motor geometries for each case shows a general reduction in size. The latter cases (4-6) differ more due to the higher torque demand, resulting in the further detailed design of the stator and magnet dimensions.", + "texts": [ + " The largest relative changes are visible in the current amplitude, the driving force behind meeting the torque balance constraint, and the winding and slot dimensions, which play a role in reducing the radial station of the stator core and adjusting the wire resistance based on the available area of the slot. The latter parameters heavily dictate the geometric influence on the overall power losses and motor efficiency. A subset of design variables are omitted from the plot because they do not vary significantly throughout each optimization case; this is due to the modeling limitations and the physics within the methodology, discussed further in Section 5. Additionally, the optimized geometry relative to the initial motor dimensions is shown in Figure 14. Each parameter sweep case began with identical motor dimensions; this allows for a common reference when comparing optimized designs. We see a reduction in overall size for each parameter sweep case; this is expected considering the objective of minimizing overall aircraft mass. For the high torque cases, additional changes in the optimal layout are seen around the magnets and stator slots, as the geometry tries to compensate for the higher current needed to satisfy the higher load. The tight bounds on the geometric design variables are motivated by the difficulties of our mesh warping technique", + " This is a consequence of utilizing a constant mesh parameterization throughout the optimization. Although re-meshing and reparameterization of the mesh during optimization would solve this issue, it is not feasible during gradient-based optimization because they are discrete operations. As a result, tight geometric design variable bounds have been set to avoid this issue. A caveat to this decision is the freedom of the motor geometry to change is limited, and resultant optimized motor designs are falsely constrained by design variable bounds rather than physics. Figure 14 shows side-by-side comparisons of initial and optimized geometries for each parameter sweep case. Although the internal motor structure shows variation, many of the geometric variables approach the same value due to the tight bounds. An example of this is the shaft diameter, which is dictated by the maximum shear stress of the shaft material; however, the shaft diameter bound was reduced to prevent significant skewing of the rotor mesh elements. An alternative approach is necessary to allow for larger geometric changes without compromising the mesh quality" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure7-1.png", + "caption": "Figure 7. H-M-H strain map for the force value of 450 N acting along the Z axis.", + "texts": [], + "surrounding_texts": [ + "In order to perform simulation tests, a properly parametrised virtual models were prepared, as presented in Figure 6. Specialist CAD-3D software was used to prepare them. With the use of pre- and postprocessors of graphic engineering interpretation, the calculation model was described with solid elements enabling approximation of operating characteristics of an object in real conditions [47,48]. Based on the adopted transducer construction and the occurring loads, tetrahedral parabolic second-order elements were used in the prepared model. This ensured a more accurate mathematical representation than in the case of linear elements [49]. The degrees of freedom were defined based on the actual operation of the transducer by depriving the nodes around the installation holes of the capability to move along the longitudinal and transverse axes of the transducer. As a result, its contact with the area of tool installation to the test stand was reflected [9]. The capability of the nodes in the installation holes to move along all axes was removed. During the tests, forces and torques were applied to the nodes constituting the face surface of the connector. As a result of the performed simulation tests (FEM), strain distribution for three cases was obtained, corresponding to the permissible forces and torques. Strain values reduced for the analysed structure were obtained using the von Mises yield criterion. In each simulation experiment, the loads were applied to the surface constituting the agricultural tool installation area. The first of the considered load states concerned the maximum permissible strain of the construction along the Z axis, i.e., perpendicular to the surface. For the adopted force Fz = 450 N, the maximum strain values of 29 MPa were obtained and were concentrated around the internal through holes. The second considered load component was the excitation along the Y axis, i.e., in the direction parallel to the installation surface. The applied load with the value of Fy = 200 N caused a concentration of strain around the outermost holes. The read values did not exceed 39 MPa. The last of the tested states concerned the effects related to the torque moment about the X axis. For the adopted load of Mx = 150 Nm, strains with a maximum value of 0.24 MPa were obtained. The strains were concentrated in the terminal points of the crosswise edge of the connection with the brackets. The results of the analyses of the body structure, presenting the strain distribution caused by the effect of loads in the form of force acting along the Y axis and the torque about the X axis, were provided in figures from Figures 7\u20139. The strength tests performed with the use of the finite element method provided essential information about the strain distribution in the considered body structure. They showed an adequate degree of transducer stress relief, and no cross-sensitivity occurred between various channels. The obtained results form the basis for the proper selection of appropriate points for the positioning of the strain gauge sensors. Moreover, the test results made it possible to evaluate the concurrent effect of a higher number of loads on the body structure. The tests also took into account an extreme example, when all the maximum value loads act on the system. It was found that the structure had adequate strength and that the permissible strain values were not exceeded." + ] + }, + { + "image_filename": "designv8_17_0001092_2_1_12_22004507__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001092_2_1_12_22004507__pdf-Figure4-1.png", + "caption": "Fig. 4. Magnetic flux distribution of the dovetailshaped magnet", + "texts": [ + " To mitigate the performance differences and meet the needs of practical applications, the specifications used in preplanning are shown in Table 2 (7). 3. Magnet Fixation Optimization Design In this study, for the magnet fixation method, a common dovetail groove cut on silicon steel sheet was used first, and the magnet was embedded in the groove to achieve fixation. However, as seen from Fig. 3, the traditional dovetail groove design causes the magnetic flux of the dovetail magnet to saturate easily at the bottom of the groove when flowing through the silicon steel sheet. Figure 4 shows the distribution of the magnetic field lines for the traditional dovetail groove design. Second, because of the design used for magnet fixation, there may be wear and tear of the magnet material during processing; correspondingly, owing to the poor structural stresses at the sharp corners of the magnet, the magnet may break or result in other problems if the assembly is not performed carefully (8)\u2013(22). This work proposes an improved design scheme for the traditional dovetail groove and verification of its feasibility through FEA and simulation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000548_3_NgTeckChew2009.pdf-Figure4.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000548_3_NgTeckChew2009.pdf-Figure4.2-1.png", + "caption": "Figure 4.2: Measurement model for follower vehicle.", + "texts": [ + "13) For the type of vehicle following under consideration, it can be assumed that no prior knowledge of the lead vehicle is available. Hence, only the input controls (VF , \u03c9F ) to the follower vehicle are available for system analysis, where VF and \u03c9F are the translational and angular velocities of the follower vehicle respectively. It is assumed that the follower vehicle is equipped with an on board gyroscope, and a sensor that can provide both range and bearing information of the environment as shown in Figure 4.2. The observation model of the system can be formulated as shown in Equation 4.14 Measurement model: H = h1 h2 h3 = \u221a x2 r + y2 r \u03c0 2 \u2212 \u03b8F + tan\u22121 yr xr \u03c0 2 \u2212 \u03b8F (4.14) where h1 is the relative range of the two vehicles, h2 is the relative bearing of the lead vehicle in relation to the follower vehicle as measured by the laser scanner Chapter 4. Bayesian Estimation Formulation For Vehicle Following 117 and h3 is the absolute orientation of the follower vehicle in relation to a known reference frame" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.2-1.png", + "caption": "Figure 1.2. Rack and pinion steering mechanism, where (1) steering wheel, (2) steering column, (3) rack and pinion, (4) actuated suspension link (tie rod), (5) wheel carrier [58].", + "texts": [ + " The spring and shock absorber serve as control devices with competing functions: reducing vehicle body acceleration, improving ride, and maintaining tire-ground contact, improving handling. Further influencing ride and handling are wheel position and attitude with wheel travel, and how the suspension reacts cornering, braking, driving, and impact loads. Additionally, for road vehicles, at least the front wheels are steered, so the suspension must allow one of the links to be actuated by a steering mechanism, typically a rack-and-pinion, Figure 1.2. Remaining links in the steered suspension must be arranged to allow rotation of the wheel about the desired steer axis. Link connections are typically cylindrical rubber bushings, Figure 1.3, where isolation from the road is desired, or metal ball joints, Figure 1.4, where well-defined motion is necessary, such as the connections allowing a steered wheel to rotate. Independent suspensions are not the only option for road vehicles; however, their superior performance has led to their eventual adoption in most segments of the market", + " In addition to leaf springs and coil springs, torsion springs were also in use. An example can be seen in Figure 1.14. In this figure, there is also a hydraulic shock absorber. As the century went along, the MacPherson strut suspension, Figure 1.15, introduced in the late 1940s, became an increasingly popular IFS. This was due to its relatively few number of components, especially when the spring is placed over the strut, and its ability to provide a steer DOF. The rack and pinion steering system, seen in Figure 1.2, in use in Europe by the 1930s, found its way to American cars in the 1970s. While the shimmy problem and styling demands led to the almost total extinction of the traditional front axle in favor of the double wishbone and MacPherson suspensions, there was no similarly urgent reason to discard the rear axle. That 10 11 12 is not to say that the advantages of the independent suspension are unique to a front application. Indeed, even on rear axles, the independent suspension has the following advantages [18, p" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003848__Issue3-05_paper.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003848__Issue3-05_paper.pdf-Figure2-1.png", + "caption": "Fig. 2. Load on the horizontal link contacting the front torus with the seat bottom and rear torus with the side surface of tooth", + "texts": [ + " When a sprocket drum is interworking with a chain with the elongated pitch, the running-on horizontal link does not contact the seat bottom along its entire length. This meshing variant is characterised by the fact that the horizontal chain links positioned on the sprocket drum with the number of teeth z are inclined relative to the seat bottoms under the angle \u03b5 so that their front tori are contacting the seat bottoms and the rear tori are contacting the working sides of the drum teeth segments with the inclination angle relative to the seat bottom \u03b2 (Fig. 2). The following parameters are determined in order to clearly describe the position of the chain links in the drum seats (Dolipski et al., 2010): \u2013 the links\u2019 inclination angle relative to the bottoms of the drum seats \u03b5; \u2013 the distance between the centre of the joint with the front torus of the horizontal link from the beginning of the side of a regular polygon u; \u2013 the rotation angle of the vertical link relative to the preceding horizontal link in the middle of the joint with the horizontal link rear torus \u03b1u", + " The slide of the front torus on the bottom seat is causing the friction force perpendicular to the reaction R dependent on the friction coefficient value between the front torus of the link and the seat bottom \u03bc g. The second interval lasts from the moment the rear torus of the horizontal link is contacting the tooth flank until the reaction R reaches a zero value. The horizontal link is loaded with the run-on force SH, reactive force R at the contact point with the seat bottom, with the reactive force F in the contact point of the rear torus with the tooth flank and with the force SV transmitted onto the preceding vertical link (Fig. 2). The third interval commences from the moment where the value of the reaction R falls to zero and lasts until the front torus contacts the next horizontal link with the bottom of the next seat. In the third interval, the force T occurs on the tooth flank, perpendicular to the reaction F, necessary for maintaining the balance of the horizontal link, preventing the slide of the rear torus of the horizontal link at the tooth flank towards the seat bottom. If the reaction R in the second interval does not reach the zero value until the moment the front torus of the next horizontal link contacts the bottom of the next seat, then no third interval occurs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure6-1.png", + "caption": "Figure 6. Heat press cure process set-up", + "texts": [ + " Once the fibers were cut out from the roll, the two-part epoxy is mixed with the correct ratio and then applied to the dry fibers. The part is then sealed, with a vacuum bag (where all the air is removed from the part). Then the cure cycle of the 14 resin is applied to the vacuum-bagged part. All of the tensile and double shear specimens were made on the heat press. When making a composite plate in the heat press, the user needed to sandwich the laminate between two nonporous sheets and two 0.25 in. thick Steel plates. Figure 6 shows how the heat press cure process was set-up. The non-porous sheets served to prevent the resin from sticking to the steel plates. The composite plate, the steel plates and the non-porous sheets were placed inside the heat press and then the cure cycle was programmed. Once cured, the composite plate was cut into various size specimens. 2.2.1 Double Shear Specimens All the composite double shear specimens were made with the quasi-isotropic laminate orientation. The quasi-isotropic laminate orientation, [0 0 +45 -45 +45 -45 90 90]s, is short hand for [0 0 +45 -45 +45 -45 90 90//90 90 -45 +45 -45 +45 0 0]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure50-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure50-1.png", + "caption": "Figure 50 P-POD Mk. IV Collar FEA Results", + "texts": [ + " This Collar is shown below in Figure 49. The only strength concern was that of the gasket groove causing stress concentrations. An FEA was conducted to check this prediction, with the Collar fixed at its mounting holes, with the Z-axis load left over from the Bracket analysis applied to the hinge hole. The results involved a slight increase in stress from the previous design, yielding a Margin of Safety of 0.4, down from 0.5 for the previous design. This decrease was not seen as an issue. The FEA results are shown below in Figure 50. Page 65 P-POD Mk. IV Door The next part evaluated was the Door. This part was seen as a part that was due for a redesign. It is consistently the weak point of the P-POD, and often deflects enough to exhibit a noticeable increase in door-collar gap. A stiffer door that could better compress the EMI gasket was desired. The P-POD Mk. III Rev. E Door is shown below in Figure 51. The first item addressed was the material coating employed on the P-POD Door. A PTFE impregnated hard anodization was used on the part, which requires a high temperature bake that lowers the yield stress to 80% of its original value" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003865_9669085_09731522.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003865_9669085_09731522.pdf-Figure8-1.png", + "caption": "FIGURE 8. Radiation patterns and the corresponding required chemical potential changed by the DC biasing of each graphene patch cell for the antenna with different radiation angels, the simulation result of the main beam: (a) 9.24 dB at \u03b8 = \u221230\u25e6 . (c) 9.93 dB at \u03b8 = 30\u25e6 . (e) 8.22 dB at \u03b8 = 44\u25e6 . (g) 6.78 dB at \u03b8 = 57\u25e6 .", + "texts": [ + " To maximize the modulation capability, the mean reactance and the modulation depth are chosen as X = 417 and M = 50, respectively, the resultant surface impedance pattern is given as Zsurf(xt) = { j[417 + 50 cos(k0x sin \u03b8 \u2212 ktr)], x \u2265 0 j[417 \u2212 50 cos(k0x sin \u03b8 \u2212 ktr)], x < 0 (16) The beam direction \u03b8 can be dynamically controlled by varying the chemical potential \u03bcc of each graphene patch, where the exact value of \u03bcc is further determined by the DC biasing according to (4) and (10). In this example, the target beam direction \u03b8 of the holographic antenna is designed to point at \u221230\u25e6, 30\u25e6, 45\u25e6, and 60\u25e6 in the X-Z plane, respectively. In Fig. 8, the simulated radiation patterns and the required chemical potential of each patch are presented. As can be seen, the practical beam direction is \u221230\u25e6, 30\u25e6, 44\u25e6, and 57\u25e6, respectively, a small shift happening at \u03b8 = 45\u25e6 and 60\u25e6 is observed, which can be remedied by slightly modifying the impedance modulation formula without cost. It is also noted that the pertinent gains are 9.24 dB, 9.93 dB, 8.22 dB, and 6.78 dB, respectively, and the corresponding 3 dB beamwidth is 13.89\u25e6, 11.25\u25e6, 15.46\u25e6, and 16" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003337_f_version_1677642889-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003337_f_version_1677642889-Figure2-1.png", + "caption": "Figure 2. Three sections of deployable booms: (a) STEM. (b) CTM. (c) TRAC (orient 90\u25e6).", + "texts": [ + " During deployment, the deployable booms drive the cables, and the cables drive the membrane to unfold and be tensioned by the web-like tensioned membrane scheme. Compared with the rigid truss, the deployable boom is utilized as the unfolding support mechanism for the triangular space membrane deployable mechanism because of its light weight, high deployment ratio and self-deployable performance, and the prerequisites for the same stowed height and mass are set when selecting sections. As shown in Figure 2, there are mainly three different sections of deployable booms: the storable tubular extendable member (STEM), the collapsible tube mast (CTM) and the triangular rollable and collapsible (TRAC) boom (orient 90\u25e6), so that these three sections are symmetric with respect to the y-axis of the established local coordinate system. Then, the flexural stiffness EIx and principal moment of inertia Ix of the deployable booms can be calculated analytically according to the inertia moment, the static moment and the formula of parallel displacement axis, and the STEM is taken as an example to illustrate the calculation procedure, as shown in Equation (1)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003708_19_ms-10-47-2019.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003708_19_ms-10-47-2019.pdf-Figure1-1.png", + "caption": "Figure 1. Development of the proposed transmission configuration: (a) the SISO spur gear configuration (cited in Lu and Fan, 2013); (b) the MISO configuration; (c) Bevel gear configuration; (d) a combination of MISO and bevel gear transmission configuration.", + "texts": [ + " At last, a prototype of MISO with bevel gear configuration cable drive mechanism (MBCDM) has been built, with which a series of experiments are carried out. The driving capability is validated through experiments. The dominant nonlinear factors for deteriorating the position control accuracy are analyzed based on experimental results in such a system. The transmission backlash is tested, and corresponding results are in good agreement with theoretical ones. The SISO spur gear configuration is a typical layout, as shown in Fig. 1a. The input pulley and output drum are connected by steel cable in a figure eight pattern, with a preload mechanism at one end. A proper preload force is exerted on the cable to prevent slack and improve transmission capability. The steel cable is usually wound around the input drum for several circles to increase the wrap angle. But the transmission capacity is limited by the SISO configuration on the condition that either the single electric motor size or torque is restricted. In response, the MISO configuration of precise cable drive has been put forward to enlarge transmission capacity under a restricted weight, as shown in Fig. 1b. It includes multiple input pulleys connected by separate cables to a single output drum. The input pulleys are evenly placed around the output drum. Each steel cable wraps around one of the input pulleys and the same output drum to transmit the motion to the output shaft. Each cable would be pre-tensioned by the preload mechanism at one end. Moreover, the bevel gear Mech. Sci., 10, 47\u201356, 2019 www.mech-sci.net/10/47/2019/ is used for transmitting motion across orthogonal shafts, as shown in Fig. 1c. In this configuration, two cables cross over from input pulley to output drum at a transfer point to provide bi-directional rotation. In order to prevent the cables cross over at an exact same point, the pulleys are axially stepped and two cables wrap on each step. Each cable is terminated and pre-tensioned at ends. It could decrease the size along the axes of the output drum. In order to extremely improve the torque-to-weight ratio with a compact structure, this paper initially proposes a novel transmission configuration which utilizes a combination of MISO configuration and bevel gear configuration, as shown in Fig. 1d. It is composed of four pulleys, four cables and preload mechanisms. The input pulleys and the guide pulley are parallel to each other, and they are all perpendicular to the output drum. Each input pulley is wrapped by two cables to provide bi-directional rotation. It is noted that the pulleys are axially stepped to produce two smooth surfaces on input pulleys and four smooth surfaces on guide pulley and output drum, without flanges or grooves to guide the cable. Because grooves or flanges on the surface will cause the scrubbing when the cable jump from guide pulley to output drum at the transfer point" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureB.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureB.4-1.png", + "caption": "Figure B.4: Straight, convex and concave leafsprings [17].", + "texts": [ + " However, they do not consider the behavior in the other directions, as these compliances change in the large range of motion, and consequently the load-carrying capacity of the hand. Furthermore, rigid body transformations are valid for small ranges of motion [16] and mostly for planar elements. B.2.3 Huazhong U.and Georgia Tech An equivalent pin model (EPM) approach to understand the non-linear behavior of flexure hinges, under pure moment, for robotic fingers was proposed by Guo and Lee [17], Fig. B.4. Page 37 The EPM is similar to a Pseudo-Rigid Body Model (PRBM), with the difference that the location of the joint is close to the center of rotation. The models consider the axis drift [72] existing in the compliance mechanism as the center of rotation changes for large displacements. The model is based on a multibody dynamics approach. The intention was to develop a rigid body model less sensitive than the pseudo-rigid body model to the type of load applied. The errors in the orientation of the phalange and the position of the end effector were found to have a non-linear behavior. The latter is less sensitive to the type of load applied. Guo and Lee studied three type of hinges: straight, convex and concave leafsprings [17] (Fig. B.4). According to the researchers, the center of rotation of the EPM plays an important role in the dynamic influence compared to a typical PRB model. Guo and Lee\u2019s publication focused on the model, and the flexure-based hand is a case study. Trajectories of the center of rotation and tip of the fingers are presented. Functional requirements in terms of load-carrying capacity or weight of the device were not considered. B.2.4 Yale University Yale University introduced the use of leafsprings made of urethane for prosthetic hands [18], see Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004597_s-4255722_latest.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004597_s-4255722_latest.pdf-Figure1-1.png", + "caption": "Fig. 1: Pneumatic bellow-type actuator classification according to type of movement obtained when pressurized. Each image depicts the resting and pressurized forms of the actuator.", + "texts": [ + " In some instances, vacuum conditions are applied to produce a contraction or to increase the stiffness and opposing forces exerted by a gripper [15]. The resulting movements are often achieved thanks to the combination of multiple materials that react differently to the pressure changes in the fluid; fibers reinforcements is the typical solution applied, in most cases, to control the deformation of the actuator and constraint it, preventing the ballooning effect observed in positivepressure-driven actuators [16]. This article focuses on bellow-type actuators (Fig. 1), sometimes referred to as PneuNets [17]; these are controlled with a positive pressure differential that causes the enlargement of a series of chambers positioned side by side and intentionally designed to be the elements deforming the most. The interaction between inflated chambers produce a global and controllable deformation of the actuator. Different bellows shapes and orientations allow for the generation of various movements. Three main categories of actuators can be identified considering their type of movement: linear, twisting and bending actuators. Linear actuators (Fig. 1c) can be obtained with a symmetrical disposition of the bellows on the lateral surfaces of the actuator. Twisting actuator (Fig. 1b and 1d) are manufactured with different strategies, which include the design of multiple internal chambers that differ in size and shape, or through the disposition of fibers in a helicoidal shape on the lateral surfaces of the actuator. The disposition of non-extensible fibers defines a series of directions along which the extension is constrained; the expansion of the inner chambers can continue only without changing the length of the fiber, hence triggering the desired twisting motion. Finally, bending actuators (Fig. 1a) can be obtained easily by stacking a series of chambers on just one side of the actuator that, when inflated, produces a flexion in the opposite direction. Occasionally, fiber reinforcements are added to better guide the desired deformation or to avoid the deformation of certain parts. More complicated movements can be obtained by mixing such components, obtaining hybrid, three-dimensional, deformations (e.g. the planar-twisting motion depicted in Fig. 1d. This article focuses on planar bending actuators (Fig. 1a) which present a wide range of application; they can be designed to mimic the motion of a human finger, allowing for multiple grasping operations and interaction; whenever multiple actuators are integrated in a single gripper, capabilities similar to the human hand might be achieved. As a result, a wide range of significant application scenarios can be identified; moreover, the potential similarity to human grasping make them interesting for human-robot interaction scenarios, where their flexibility make them safe to use in interaction and cooperative tasks" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure56-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure56-1.png", + "caption": "Figure 56. Drawing of the center plate of the fixture", + "texts": [], + "surrounding_texts": [ + "1 = variable 1 2 = variable 2 3 = variable 3 br = bearing comp = compressive extes = extensometer i = at ith data point long = longitudinal direction max = maximum xxii min = minimum pin = pin location s = symmetric spec = specimen ten = tensile trans = transverse direction ult = ultimate x = x-direction xx = in the axial direction for the +/-45\u00b0 shear tensile test y = y-direction xy = xy-direction (plane) 1 CHAPTER 1: INTRODUCTION In this chapter, previous and current thesis work is introduced. Section 1.1 introduces the different two different types of aircraft structures. In Section 1.2, the differences between an adhesively bonded joint and a mechanically fastened joint are explained. In Section 1.3, previous work is mentioned, considerations are made in order to avoid testing parameters, which have already been tested, and the three different failure mechanisms are explained. Section 1.4 explains the thesis goal and the thesis scope. 1.1 Introduction to Conventional & Advanced Composite Structures When you think of an aircraft\u2019s wing, it is composed of multiple panels and not usually made as a single piece. The use of joints becomes essential in an aircraft\u2019s wing (since joints serve to attach multiple structural components together to form one part). Ideally, the designer wants to avoid using them, since they can contribute a significant amount of weight to the overall aircraft\u2019s structure. Current aircraft manufactures are transitioning from a conventional aircraft structure to an advanced composite structure since the advantage of switching to an advanced composite structure is the significant reduction in parts and joints. Composite materials have desirable characteristics such as being: very stiff, extremely strong, and extremely light. For example, the Airbus\u2019 A350 aircraft structure is made up of 53% composite materials [1]. Even though the total amount of joints can be significantly reduced, that does not mean they can be avoided altogether. 2 As composites become more widely used in the Aerospace Industry, there still lies limited research in their ability to perform as joints. Their main flaw is their poor behavior in redistributing stress concentrations. Even though there has been a lot of research in composite joints, not enough advancement has been made compared to its metal counterpart. Metal joints (in particular, Aluminum joints) have been used for years in the Aerospace Industry. Currently, composite joints are overdesigned (made a lot thicker than they need to be) which leads to weight penalties. Design that is more detailed needs to done on composite joints in order to improve its ultimate bearing strength. 1.2 Introduction to Adhesively Bonded Joints & Mechanically Fastened Joints Two types of joints exist: one is the mechanically fastened joint, and the other is the adhesively bonded joint. In Figure 1, one can see an adhesively bonded single shear joint, a mechanically fastened single shear joint and a mechanically fastened double shear joint. The region between the two plates, in the adhesively bonded double shear joint, is the thin layer of structural adhesive used to bond both structural components together. Adhesively bonded joints are typically lighter but are often more difficult to design. No holes need to be made in an adhesively bonded joint. Reduction of holes reduces the amount of stress concentrations. Adhesively bonded joints can be problematic since the surface finish needs to be accounted for to achieve a strong bond between two surfaces. Another issue with adhesively bonded joints is that they cannot be removed as easily as a mechanical joint. 3 Mechanically fastened joints are widely used in the Aerospace Industry since they are more practical in the sense that they can be easily removed if a part needs to be replaced, repaired, or checked. Two types of mechanically fastened joints exist: single shear and double shear. In addition, a mechanically fastened joint can contain many fasteners. Mechanically fastened joints require a hole through both structural components, which creates stress concentrations. Both of the structural assemblies are held together by a bolt, and nut. 4 1.3 Previous Literature on Mechanically Fastened Composite Joints Numerous papers have been made on mechanically fastened composite joints, and in this section, the most important finds will be mentioned. According to Alan Baker[3], for a mechanically fastened double shear joint, load is transferred mainly through compression on the internal face of the fastener holes and as well as on a component of shear on the outer faces of the plate due to friction. Mechanically fastened composite joints can be made very durably but the designer needs to spend a longer time in the design process. According to Okutan [4], problems arise when the designer wants to analyze them since they have an anisotropic and heterogeneous nature. According to Chen [5], the behavior of a composite joint could be influenced by four parameters. The first is the material parameter. The material parameter includes fiber types, form, resin type, fiber orientation, laminate stacking sequence, material cure cycle, etc. The second is the geometric parameter. This includes the specimen width (W) and the hole edge distance (e). These are usually reported as W/D and e/D ratios where D is the diameter of the hole. A huge contributor to the strength of the specimen is the specimen thickness (t). The pitch is the distance between two or more holes in a multiple hole composite joint. The third (also very important) is the fastener parameter. This includes fastener type, fastener size, washer size, hole size, and tolerance. The last is the design parameter. The design parameter includes loading type (tension, compression, fatigue), loading direction, loading speed, hydraulic clamping pressure, joint type (single lap, double lap), environment, etc. 5 The lay-up sequence also played a significant role in the overall strength of the double shear joint, as well. Quinn & Matthews [6] studied in detail the effect of stacking sequences on the pin bearing strength in glass-reinforced plastics. They concluded that placing a 90\u00b0 layer ply on the outer surface of the laminate increased the overall bearing strength. Liu [7] tested different laminate thicknesses by varying the bolt diameter. He concluded that thick laminates with smaller diameter holes and thin laminates with larger diameter holes were a lot weaker than laminates with similar hole and laminate thicknesses. Stockdale & Matthews [8] studied the effects of bolt clamping pressure and found that boltclamping pressure played a huge role in the overall strength of the composite joint. Kim [9] tested to see the effects of temperature and moisture on the strength of graphite-epoxy laminates. From this experiment, the actual stress distribution of the joint is very difficult to find since the region is so small. The use of strain gages is impractical because that region is under a very high stress so any kind of strain gage applied would crush because of the force. That is why numerous researchers have been working on methods of modeling composite joints with the help of various finite element programs. The load capacity of a laminate is severely degraded due to the effects of hole clearance and friction. Hyer & Klang [10] investigated this phenomenon with a pin-loaded orthotropic plate. Pierron [11] used Abaqus to calculate the stress distribution around the hole of a woven composite joint. Most finite element modeling was done using 2D shell elements and recently there has been an increased amount of 3D modeling of composite joints. Previous researchers mention that the joint strength depends mainly on the failure criterion. 6 Only a small section of the bearing stress vs. bearing strain curve is linear, and then after, it becomes nonlinear. Stress concentrations cause crushing in a small section of the geometry, making it a very difficult nonlinear problem. Chang [12] created a 2D finite element model and assumed a frictionless contact with a rigid pin and a cosine normal load distribution in the pin-hole boundary. Another difficulty in modeling the composite joint requires the user to combine the failure criteria with a property degradation model. As the composite takes more load, the actual material properties are degrading over time, which would mean the modulus is decreased after each new load is applied. Lessard [2] used a 2D linear model along with a non-linear model to predict the strength of the composite joint. There are five different kinds of failure, which can occur in a laminate: matrix tensile, compressive failure, fiber/matrix shearing, fiber tensile, and fiber compressive failure. The Hashin failure criterion is an important criterion used to characterize failure within a laminate. 1.3.1 Previous Literature on Loading Rate Effects on Mechanically Fastened Composite Joints In flight, the aircraft might experience various dynamic loading conditions, so not only do composites need to be tested in quasi-static loading case, but also in a dynamic load case. Metals are not as load rate dependent as composite materials. Ger [13] tested a number of carbon and carbon fiber glass hybrid composites at dynamic loading rates of 6 to 7 m/s. The double shear joint configuration carried more load at high loading rates. It was also noted that for all joint configurations the stiffness of the joint increased significantly with 7 loading rate. In addition, what was noted was that the total energy absorption of the joint decreased significantly in the dynamic tests. Contradictory to Ger [13], Li [14] tested different types of joint configurations subject to a bearing load and found that energy absorption increased. Li [14] tested at higher rates of 4-8 m/s and found this interesting trend. The dynamic behavior of composite joints is much more complicated than its behavior for the quasi-static condition due to the involvement of strain rate and inertial effects. Li [14] concluded that crashworthiness design of tested composite joints could be based on their tensile strength design. Ger [13] mentioned there must be a significant safety factor applied to take into account bearing strength variations with loading rate. The failure modes might also be affected due to an increased loading rate. 1.3.2 Types of Failure in Mechanically Fastened Composite Joints According to Larry Lessard [2], it has been observed experimentally that mechanically fastened composite joints fail under three basic mechanisms: net-tension, shear-out, and bearing (in addition, combinations of these mechanisms are often given separate names). Typical damage mechanism is shown below in Figure 2. Looking at previous work, a net-tension and a shear-out failure are more catastrophic than a bearing failure. The best way to see if a bearing failure has occurred is to look at the bearing stress vs. bearing strain plot. Once the stress gets to its peak value and suddenly drops off to zero, then one can conclude it was a shear-out or a net-tension failure. If after the ultimate bearing stress, the specimen continues to carry load but deforms as a result, this means that the joint was designed very safely. According to Okutan [4], the optimum orientation for a bearing type of failure is a quasi-isotropic laminate orientation. A quasi-isotropic laminate 8 orientation means the laminate has the isotropic properties in plane. According to USNA [15], a quasi-isotropic part has either randomly oriented fiber in all directions, or has fibers oriented such that equal strength is developed all around the plane of the part. The geometry of a mechanically fastened composite joint is quite complex since it can affect the failure mode of the double shear joint specimen. Kretsis [16] & Matthews [16] tested fiber glass and carbon fiber reinforced plastics and found that the width(W), end distance(e), diameter of hole(D), and laminate thickness(h) all contribute to the overall mechanically fastened double shear joint strength. The most interesting aspect is that as the width of the specimen decreases to a specific amount, the mode of failure changes from bearing to net-tension. The W/D (width to hole diameter ratio of the composite double shear joint specimen) must be at least 5 order to avoid the net tensile type failure. Another interesting thing to note is when the end distance of the hole is a certain distance from the edge of the plate, the failure turned from bearing to shear-out (where shear-out is considered a special case of bearing failure). 9 1.4 Thesis Goals & Scope In the preceding sections of this thesis paper, the word double shear specimen will be used to represent one test specimen with a mechanically fastened double shear joint configuration. The goal of the thesis is to determine how the strength of a composite double shear joint is affected by two different cure cycles and five different loading rates. The composite joint will be tested in the double shear case and the laminate orientation was decided to be a quasi-isotropic laminate (based upon based on Yeole\u2019s double shear experimental results [17]). Yeole [17] tested three different laminate orientations in his thesis, and concluded that a quasi-isotopic laminate took the highest stress. Yeole [17] also mentioned that the testing of composite materials at fast loading rates could be an interesting topic to explore. ASTM 5961[18], which is the ASTM for bearing response of composite materials, required an extensometer to measure the relative pin displacement since using crosshead displacement is not an accurate method. A fixture was designed and manufactured in order to accommodate an extensometer. Finally, the numerical model was made to validate only the linear elastic portion of the experimental results. There are seven chapters in this thesis. Chapter 1, the introduction, includes a brief introduction to: composite materials, the difference between adhesively bonded joints and mechanically fastened composite joints, and the loading rate effects on mechanically fastened composite double shear joint bearing strengths. It also includes a brief literature review, the statement of the problem and the objective and organization of thesis. Chapter 2 focuses on manufacturing of the double shear specimens and the tensile specimens. Chapter 3 focuses on the experimental material testing 10 procedure conducted on the MTM49 Unidirectional Carbon Fiber pre-preg. It also explains the double shear fixture used for the testing. Chapter 4 focuses on the equations used in the experimental and theoretical calculations. Chapter 5 introduces the experimental result validation and then discusses the experimental results. Chapter 6 introduces: the numerical model, which was created using Abaqus 6.14 software, the convergence plot, and lastly, what, influences the numerical results. Chapter 7 is where the experimental results are compared to the numerical finite element results. Lastly, Chapter 8 is where the conclusions are drawn and different recommendations are made for the future work. In the reference section, one can find most of the related topics in the form of theses, books, reports and even papers published in numerous journals. In the appendix section, one find: drawings of the fixture, a tutorial on setting up the Bluehill2 double shear test method, a tutorial on finding the unknown engineering constants with the Autodesk software, a tutorial on outputting the force vs. hole deformation in Abaqus, and a tutorial on the composite double shear specimen Abaqus model. 11 CHAPTER 2: MANUFACTURING & PREPARING OF THE SPECIMENS This chapter will introduce the type of specimens that were manufactured and tested in the Instron machine along with their dimensions. All the dimensions were based on published ASTM test standards. ASTM is an international standards organization, which develops and publishes voluntary consensus technical standards for a wide range of materials, products, systems and services. 2.1 Tensile Specimen & Double Shear Specimen Dimensions The dimensions for the 0\u00b0 tensile specimens and the 90\u00b0 tensile specimens were found in ASTM D3039 [19] Standard test method for tensile properties of fiber-resin composites. The dimensions used for the shear modulus +/- 45\u00b0 were found in ASTM D3518 [20]. Below in Figure 3, one can see all of the tensile specimen dimensions for each specific fiber orientation angle. Figure 4 shows a drawing of all four different fiber orientation tensile specimens. The +/- 45\u00b0 shear specimens and the quasi-isotropic laminate specimens had the same dimensions. Figure 5 shows the dimensions, based on ASTM D5961 [18], of the composite double shear specimens. The quasiisotropic tensile specimens were tested to see how the theoretical material properties matched. 12 13 2.2 Manufacturing Process In the Cal Poly\u2019s Aerospace Engineering Composites Lab, there are two ways to manufacture a composite. One can use pre-preg material or apply a wet layup process. Pre-preg material is a lot easier to use since it already has the resin infused inside the material. In order to preserve the resin in the pre-preg material, it needed to be stored in a freezer at low temperatures. Once the pre-preg material is thawed, then the user is able to apply it to a mold or create a plate out of it. The second way, the wet-layup process, consisted of having the fibers in their pure form, which usually come in a roll, and having a two-part epoxy. Once the fibers were cut out from the roll, the two-part epoxy is mixed with the correct ratio and then applied to the dry fibers. The part is then sealed, with a vacuum bag (where all the air is removed from the part). Then the cure cycle of the 14 resin is applied to the vacuum-bagged part. All of the tensile and double shear specimens were made on the heat press. When making a composite plate in the heat press, the user needed to sandwich the laminate between two nonporous sheets and two 0.25 in. thick Steel plates. Figure 6 shows how the heat press cure process was set-up. The non-porous sheets served to prevent the resin from sticking to the steel plates. The composite plate, the steel plates and the non-porous sheets were placed inside the heat press and then the cure cycle was programmed. Once cured, the composite plate was cut into various size specimens. 2.2.1 Double Shear Specimens All the composite double shear specimens were made with the quasi-isotropic laminate orientation. The quasi-isotropic laminate orientation, [0 0 +45 -45 +45 -45 90 90]s, is short hand for [0 0 +45 -45 +45 -45 90 90//90 90 -45 +45 -45 +45 0 0]. The subscript s means that the laminate 15 is symmetrical about the last ply (which in this case is a 90\u02da ply). The alternate cure cycle was the Cytec\u2019s MTM 49 cure cycle and the datasheet cure cycle was the Umeco\u2019s MTM 49 cure cycle.. The material was first thawed since according to the Umeco\u2019s [22] MTM 49 datasheet, if the roll is open to the environment, condensation will occur on the pre-preg material, which will degrade the quality and the aesthetic look of the material. Sixteen 12 in. by 12 in. plies were cut out and orientated in the quasi-isotropic laminate orientation of [0 0 +45 -45 +45 -45 90 90]s. All the respective angles within each ply of the laminate were carefully kept within \u00b1 1\u00b0. Shown in Figure 7, a protractor was used to make sure each ply in the laminate was within \u00b1 1\u00b0. Once all the plies were stacked very carefully (in order to prevent air pockets from occurring within the laminate), the cure cycle was programmed into the heat press. Air pockets create areas where delamination can occur, which leads to the formation of cracks. Cracks can severely weaken composite structures. The second step consisted of programming the cure cycle into the heat press. Shown in Figure 16 8, is Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22]. Two different cure cycles were tested to see its effects on the material\u2019s double shear bearing stress. Increasing the dwell temperature from 248\u00b0F to 275\u00b0F and increasing the dwell time from 60 minutes to 90 minutes both affect the mechanical characteristics of the resin. The dwell temperature is the temperature which is held constant in the cure process (for this material, it occurs after the temperature ramp up stage). The dwell time is the duration of the dwell temperature stage. Each different carbon fiber matrix system will have its own recommended cure cycle printed in its specific datasheet. In the experimental section, one can see the difference in mechanical properties of the material based on the two different cure cycles. The first cure cycle was Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22] (also known as the alternate cure cycle). The heat press was adjusted to the specific cure cycle. First, the cure cycle temperature ramped up from room temperature of 77\u00b0F to 275\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 275\u00b0F for 90 minutes. After the 90 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. A uniform pressure of 2 psi was applied on top and bottom of the plate. 17 The second cure cycle was Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [21], shown in Figure 9 (also known as the datasheet cure cycle). The heat press was adjusted to the specific cure cycle. First, the press ramped the temperature up from the room temperature to 248\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 248\u00b0F for 60 minutes. After the 60 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. The pressure was held constant between both cure cycles. 18 The third step consisted of preparation of the test specimens. Once the composite laminate finished curing, the material was removed from the press and was cut with a tile saw, which had a diamond-coated blade. The tile saw had an adjustable clamp that helped keep the cuts within 0.1 of an inch. Figure 10 shows the tile saw used to cut the specimens. A straight cut was made on the composite laminate, in order to clean up the edge of the plate. Next, the top side of the plate was aligned to the straight section of the small tile saw. The cuts were made carefully in order to keep a 90\u00b0 angle on the side of the cured laminate. Once all the cuts were made, and the zero direction of the laminate was located accordingly, specimens were cut to the correct width. Based on ASTM D5961 [18], a W/D (specimen width to hole diameter ratio of the composite double shear joint specimen) of 6 and e/D (hole edge distance to diameter of hole ratio) of 3 were used. These geometric conditions guaranteed the double shear composite specimens failed in bearing and not in net-tension or shear-out. Based on these geometric conditions, the specimens needed to be 1.5 in. wide by 5.5 in. in length. The tile saw 19 was used to trim the long 1.5 in. wide specimens to their final length of 5.5 in. A small aluminum block was clamped to the tile saw, which helped minimize variations in the length of all the specimens and allowed multiple specimens to be cut at the same time. After the specimens were cut to their specified length and width, they were grouped into sets of five. A mini microfiber-board fixture was created in order for five holes to be drilled at the same time. The fixture was clamped into the drill press. Five composite double shear specimens were stacked onto the drill fixture and the top left corner of each composite double shear specimen was aligned to the top left corner of the fixture. An Aluminum template was placed on top of the composite double shear specimens and was used to align the 0.25 in. diamond coated end mill bit. Once the composite double shear specimens were aligned accordingly, a small c-clamp was used to constrain the specimens along with the Aluminum template from moving/rotating during the drilling process. In Figure 11, one can see the fixture, the Aluminum template and the end mill bit used for the hole drilling process. 20 Once the holes were created for all the composite double shear specimens, there needed to be a 0.5 in. wide horizontal slit on each face of the composite double shear specimens. A thin Aluminum template was created to assist in locating a specific distance from the hole. This slit needed to be placed accurately within a tolerance of 0.01 in. The template is shown below in Figure 12, and the flat edge of the Aluminum template was used to locate the slit location. The slit needed to be as horizontal as possible and deep enough to catch the moveable knife-edge of the extensometer. 21 Emery cloth helped distribute the high clamping pressure (which is applied by the hydraulic clamps) which occurred at the bottom of the double shear specimen and the emery cloth prevented the composite double shear specimen from slipping during the test. Aluminum tabs were not needed for the double shear test because the specimens failed before reaching 7,000 lbs. The emery cloth works up to a maximum load of 7,000 lbs. The emery cloth was 1.5 in. wide and had a grit level of 120, which is shown in Figure 13. Each specimen only needed emery cloth on one end. Only a 3 in. long piece was needed to cover all of the specimen\u2019s width. A small portion of painters tape served to hold the emery cloth in position. The emery cloth was also reusable; so one piece of emery cloth could be used on two or more specimens. In Figure 13, on the right, shows the ready-to-test composite double shear specimen. 22 2.2.2 Tensile Specimens The same method was applied for the composite tensile specimens, except that these specimens did not have a hole. Stacking the layers needed to be done in a very careful manner in order to prevent misalignment. Once the composite shear modulus specimens and the 90\u00b0 composite tensile specimens were cut to 10 in. by 1 in., then all that was needed was to apply the emery cloth to the ends. Painters tape was used to secure the emery cloth in position. Then, the composite shear modulus specimens and the 90\u00b0 specimens were ready for testing. The 0\u00b0 unidirectional carbon fiber composite tensile specimens required 2 in. long aluminum tabs (as specified by ASTM 3039 [19]). Sandpaper was used on the surface, near the ends of the 0\u00b0 unidirectional carbon fiber composite tensile specimens. A small section of the surface was 23 abraded, and then, acetone was used to clean the surface. Structural adhesive was used to bond the Aluminum tabs to the 0\u00b0 unidirectional carbon fiber composite tensile specimens. After a full day of curing, the 0\u00b0 unidirectional carbon fiber composite tensile specimens were ready to be tested in the Instron 8801 machine. In Figure 14, one can see the ready-to-test 0\u02da unidirectional carbon fiber composite tensile specimens and the +/-45\u02da composite shear modulus specimens. 24 CHAPTER 3: TESTING PREPARATION & PROCEDURE In this chapter, the test preparation and procedure are explained thoroughly. Section 3.1 introduces the type of testing machine used for the experiment. Various test recommendations are made and included inside the preceding subsection. The Auto-Loop tuning feature is explained in detail and an example is made to assist the user in using this feature. The Specimen Protect feature in Bluehill2 is explained with full detail, which helped produce very consistent experimental results. Finally, in Section 3.3, the tensile double shear test and tensile test procedures are explained. The design and set-up of the double shear fixture is shown in detail as well. In the Appendix, the Bluehill2 test method creation was explained for a double shear tensile test. 3.1 Intro to Uniaxial Testing Using the Instron 8801 Servo-hydraulic Test Machine All the material tests were conducted on an Instron 8801. This machine is a dual column servohydraulic testing system. It meets the challenging demands of various dynamic and static testing requirements. The machine allows the user to hook up external force or strain transducers. A dynamic knife-edge extensometer was used for both, the tensile and double shear tests. The machine works in conjunction with a controller, which can be used to control the machine without the use of a computer. A servo-hydraulic system is composed of an actuator, which can apply a tremendous amount of load onto a test specimen. The load cell has a +/- 100 kN limit which means it can measure accurately up to +/- 22,000 lbs. axial force (in compression/tension). For the tensile double shear test, the maximum load that was seen during the test was around 1,700 lbs. and for 25 the tensile test, a maximum load of 7,000 lbs. was seen. The thicker the laminate, the higher the load the specimen could take before failure. Shown in Figure 15, one can see the Instron 8801 testing setup. The machine\u2019s crossheads contain metal jaws, which (powered by a hydraulic system) are able to clamp the specimen. The hydraulic clamping pressure is adjustable so for standard tensile testing, the pressure is set to 160 bar and for testing fragile composite resins, one would want to drop the pressure to 80 bar. Lowing the hydraulic pressure helped reduce premature specimen cracking. The crosshead mechanism loaded with a specimen is shown below in Figure 16. The specimen is placed carefully between two the hydraulically powered metal clamps which secure 26 the specimen in place. 3.1.1 Instron Servo-hydraulic Test Machine Recommendations For determining the modulus of elasticity along with the modulus of rigidity, the most accurate measuring tools were the extensometer and the strain gage. The crosshead displacement was not very accurate since the system displaces due to the compliance in the grips, and the actuator assembly. This displacement of the crosshead can cause unreliable results in the modulus of elasticity where accuracy is very important. The Instron crosshead and the extensometer both yielded slightly different stress/strain curves. This difference in stress/strain curves is due to the Instron crossheads displacing a little more than the extensometer. The extensometer measured only the deflection of the specimen relative to both of the extensometer knife-edges. The extensometer 27 had a gage length of 0.5 in. and a knife-edge width of 0.5 in. The dynamic extensometer, catalog no. 2620-826, can be seen in Figure 17. The top knife-edge is fixed and the bottom knife-edge records precise deflections. The extensometer was attached using two rubber bands. The rubber bands were wrapped multiple times around the specimen to prevent the knife-edges from slipping. Whenever the extensometer was handled, the safety pin was in place at all times. If the user wants to run a three-point or 4-point bend test, the crosshead displacement is accurate enough to capture the vertical displacement accurately. If the user wants even more accuracy, they are able to hook up an extensometer to the three-point bend fixture and record vertical displacement with that device rather than the crosshead displacement. The Instron 8801 machine has a few features, which need to be utilized in order to minimize testing errors. The load and position calibration should never be changed or conducted. Before any 28 test is conducted, the user should Auto-loop tune the load cell only once. Each time a new material is being tested; for example, carbon fiber compared to Aluminum, the load cell should be Autoloop tuned. A list of load cell control gains should be recorded in a separate table for each material, to avoid having inexperienced individuals auto-loop tune the machine. Some precautions in the auto-loop tuning process include to never auto-loop tune a material that will fails under 120 lbs. and to never set the force amplitude above 500 lbs. This may cause the machine to cycle through very rapidly. 3.1.2 Tutorial on Auto-Loop Tuning of the Load Cell for an 1 in. wide By 1/16 in. Thick Aluminum Specimen Each time a new type of material is tested in the machine the load cell needs to be auto-loop tuned whether it be Aluminum, Steel, carbon fiber, hemp composite, fiberglass or any other composite material. Auto-loop tuning the force insured that the load cell is set up to perform accurately for each specific material. The auto-loop tuning tool adjusted various gains on the load cell controller. This was done through the Bluehill2 console (under the load cell menu). Measure the cross-sectional area of the tensile specimen and note its yield stress (if a metal) or ultimate stress (if a brittle material). For example, for Aluminum, the yield stress is around 35 ksi and the tensile specimen had a cross-sectional area of 0.062 in.2. Make sure to apply a force which keeps the material well under its yield or ultimate stress (so 25 ksi was applied to the Aluminum specimen). 29 Insert the Aluminum tensile specimen into the hydraulic clamps and load the specimen to 1,500 lbs. Also, set the amplitude force to 500 lbs. In the auto-loop tuning wizard, the Proportional gain (P) needs to be set to one before any auto-loop tuning is conducted. The specimen will be exposed to a cyclic load of 1,500 lbs. \u00b1 500 lbs. After the auto-loop tuning completes, it will say Auto-loop tuning completed successfully and then, in the next window record the P, I, D and L values. The P value should be 12.564, the I value should be 0.56, the D value should be 0.49 and the L value should be 0.8. These gain values are essential to the auto-loop tuning process. Each time a new material is tested, it is advised to specify the correct P, I, D and L values in the console and only if those values are unknown then the material needs to be auto-loop tuned. After running the auto-loop tuning tool on the MTM 49 unidirectional carbon fiber material, the P (proportional gain) equaled 13.481 and I (integral gain) equaled 0.578. Both D and L equaled zero. Typically, the material needs to be auto-loop tuned in a load range where accuracy is needed. This range is typically, where the modulus of elasticity is measured in between 25% to 50% of ultimate stress as stated by ASTM D3039 Tensile Properties of Polymer Matrix Composite Materials [19]. If the material fails during the auto-loop tuning process, the actuator will shake violently and will not stop itself. Hit the red emergency stop button on the control panel or hit the red button on the Instron servo-hydraulic machine to power off the actuator. Start back up the machine and run the auto-loop tuning tool again at a lower force. 30 3.1.3 Tutorial on Specimen Protect The specimen is prone to premature failure due to high clamping forces exerted by the hydraulic clamps. Instron's Specimen Protect feature protects a specimen against this phenomenon. This feature is found inside the console, it is labeled Specimen Protect, and the symbol looks like small shield. Before using the Specimen Protect feature, go into the console, enter the Specimen Protect option menu and make sure the load threshold is set to 44 lbs. Clamp the bottom of the test specimen. Once the bottom of the specimen is clamped, move the actuator up until the top of the specimen sits in between the top crosshead's clamps. Turn on the Specimen Protect feature in the console and this will automatically move the bottom crosshead slightly up or down in order to prevent the specimen from experiencing more than 44 lbs. After both the top and bottom of the specimen are clamped, turn off the Specimen Protect feature and continue with the test. Every time a new specimen is inserted into the hydraulic clamps, this feature needs to be utilized in order to prevent premature failure. 3.2 Bluehill2 Test Preparation The machine was connected to a Windows desktop and from there Bluehill2 and the console were used to monitor machine inputs and outputs. According to Instron, the console software provides full system control from a PC: including waveform generation, calibration limit set up, and status monitoring. In real-time, Bluehill2 outputted various experimental results: strain values, load values, displacement values, and exc. All the raw data was outputted into an Excel file, which 31 could be used for post-processing calculations. 3.2.1 Bluehill2 Test Parameter Setup The main software of interest was the Bluehill2 software. In Bluehill2, the user has options of changing various testing parameters. Each test can be created and saved to a separate testing file, which can later be accessed when the user needs to conduct that type of test. Three different tests were created in the Bluehill2 software. The tensile test and tensile double shear test were created with the Bluehill2 software. Before a test file is created, it is required of the user to know what values are of interest for a specific structural test. The ASTM should exactly specify which the testing parameters should be used for the specific test. ASTM D5961 [18] suggested to test at a load rate of 0.05 in./min., to sample at a rate of at least 2 samples per second, and to output the extensometer displacement instead of the crosshead displacement. It also specified to run the test until a maximum force is reached and until the maximum force decreased by 30%. If the force didn\u2019t drop to 30% of the maximum; run the test until the pin displacement is equal to half of the hole diameter. For the pin displacement, the test ended once the extensometer read a displacement of 0.1 in. since that was the maximum range of the extensometer. The test specimen slipped in the grips when the force in the force vs. time plot flattens out, with respect to time, the specimen was slipping. The hydraulic pressure was manually set to 160 bar on the side of the machine. The fastener, which secured the Steel collars to the sides of the specimen, was hand tightened. Five different loading rates were 32 applied and adjusted accordingly inside the Bluehill2 software. 3.3 Instron Experimental Test Procedure The Instron start-up checklist was followed in the lab in order to start the machine safely. The first step of the checklist was to turn on the main power switch in the back of the lab. After turning on the main power switch, the next step was to turn on the Instron controller by pressing the power switch in the back of the Instron controller. Once the controller warmed up fully, a small blinking light appeared on the load calibration section of the controller. The calibrate button was pressed on the load menu of the controller. Next, the Cal button was pressed. Once the Restore button was pressed, the machine was fully calibrated even though it read \u201cCalibration not restorable.\u201d The desktop was turned on, and once the system booted up, the Bluehill2 software was started. As the software started up, it automatically started the console. The console is how the computer communicates with the Instron machine. The extensometer was plugged into the back of the Instron machine and it showed up under Strain 1 (in the Bluehill2 software). Once the extensometer was plugged in, it flashed in the console screen reminding the user that it needed to be calibrated. The extensometer\u2019s calibration was restored to a previous calibration. From this point on, the tensile test, or the double shear bearing test could be started. 3.3.1 Tensile Testing Procedure Before starting any ordinary tensile test, the user needed to have at least six tensile specimens 33 prepared for the test. For each tensile specimen, the thickness, width and gage length (distance between the tabs) were recorded. The Specimen Protect feature was also used when initially clamping the specimens. The first composite tensile specimen was tested to failure (without the extensometer), in order to find its ultimate failure load. A limit load was created for the extensometer and was decided based on the ASTM D3039 [19]. As stated in ASTM D3039 [19], the material's modulus of elasticity can be measured anywhere between 25% and 50% of its ultimate load or yield load (if it is a metal). The limit load was calculated by multiplying the 1st specimen\u2019s ultimate load by 0.25 and this value was specified in Bluehill2\u2019s end of test criteria. In Bluehill2 software, there is an option of recording the strain using an extensometer and once the limit load is reached, the test will pause allowing the user to remove the extensometer. Next, the remaining five composite tensile specimens were tested. The next composite tensile specimens were loaded in the machine and the extensometer was attached for each specimen. Figure 18 shows a composite tensile specimen (with an extensometer mounted on its surface). Once at the limit load, the extensometer was removed, and the test continued up to the ultimate load. Note that the initial modulus recorded by the extensometer was very accurate, and after removal of the extensometer, the crosshead took over and the accuracy declined. 34 3.3.2 Double Shear Testing Procedure Once the standard Instron startup procedure was completed, the tensile double shear Bluehill2 test method was started. In the Appendix, one can find a detailed tutorial on the tensile double shear Bluehill2 test method. Procedure A double shear tension, in ASTM 5961 [18], was followed closely. The user needed to make sure that all the dimensions were recorded such as specimen width, specimen length, and specimen thickness and distance between the edge of the specimen to the hole edge. The fixture used for the double shear test consisted of an assembly made up of three cold drawn Steel plates with two bolts and nuts connecting all three plates. The double shear fixture is shown in between the clamps on the left in Figure 19. The double shear fixture is shown, in the center, in Figure 19. The close-up of the collar-specimen assembly is shown, on the right side, in 35 Figure 19 as well. Each double shear joint specimen was sandwiched between two Steel plates, two Steel collars, four washers and a nut, which can be seen on the left and the center in Figure 20. The extensometer, as required by the ASTM 5961 [18], is fixed on the fixture with a small steel plate and two bolts, shown on the right in Figure 20. The extensometer's knife edge was carefully placed inside the slit of the specimen and secured with a rubber band. The nut which held the screw assembly together with the specimen was only hand tightened. In the Bluehill2 software, as stated earlier, the end of test occured if the maximum force droped by 30% or if the maximum extensometer displacement was 0.1 in. This end of test criteria worked perfectly for the 0.05 in./min., 0.1 in./min. and 1 in./min. loading rates. But for the 2 in./min. and 6in./min. loading rates, the maximum extensometer displacement was lowered to 0.05 in. At faster loading rates (above 2 in./min.), the actuator had problems stopping immediately at very small deflections (0.1 in.) so applying this adujstment prevented the extensometer from accidently breaking due to over-deflection of the crossheads. 36 37 CHAPTER 4: THEORETICAL SOLUTION METHOD In this chapter, information is given on the equations that were used to find all of the mechanical properties of the material used. The theoretical equations used to come up with the macromechanical behavior of a lamina and laminate are included as well. 4.1 Experimental Equations 4.1.1 Equations Used for Unidirectional Carbon Fiber and Aluminum Double Shear Specimens The width to diameter ratio of the specimens needed to be measured and recorded. Below, W, is the specimen width, and D is the diameter of the hole. \ud835\udc4a \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc4a/\ud835\udc37 The edge to diameter ratio of the specimens needed to be measured and recorded. \ud835\udc38 \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = (\ud835\udc54 + \ud835\udc37/2)/\ud835\udc37 The diameter to thickness ratio of the specimens was measured and recorded. Below h is specified as the thickness of the specimen. \ud835\udc37 \u210e \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc37/\u210e The bearing stress was calculated by dividing the force, P, by the force per hole factor, k (equal (1) (2) (3) 38 to 1 for double shear test), with the diameter of the whole, D and by the thickness of the specimen, h. \ud835\udf0e\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strength was calculated by dividing the maximum force, Pmax, by the force per hole factor, k, with the diameter of the hole, D and by the thickness of the specimen, h. \ud835\udc39\ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strain was determined from the extensometer displacement, \ud835\udeff\ud835\udc56 divided by the k, force per hole factor, and the diameter of the hole, D. \ud835\udf16\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udeff\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37) The bearing chord stiffness was only reported if there existed an offset bearing strength. The linear portion, where the bearing stress ranges from 25 \u2013 40 ksi, is the bearing chord stiffness region. \ud835\udc38\ud835\udc4f\ud835\udc5f = \u2206\ud835\udf0e\ud835\udc4f\ud835\udc5f/\u2206\ud835\udf16\ud835\udc4f\ud835\udc5f 4.1.2 Equations Used for Tensile Testing of Unidirectional Carbon Fiber and Aluminum Specimens The maximum tensile strength F, was calculated by dividing the maximum force by the cross- (7) (6) (5) (4) 39 sectional area A. \ud835\udc39 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/\ud835\udc34 The tensile stress, \ud835\udf0e, was calculated by dividing the force by the cross-sectional area, A. \ud835\udf0e\ud835\udc56 = \ud835\udc43\ud835\udc56/\ud835\udc34 The chord modulus of elasticity, E, was calculated by the difference two tensile stress points and their equivalent tensile strain points. \ud835\udc38 = \u0394\ud835\udf0e/\u0394\u03b5 The extensometer strain, \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 , was calculated by dividing the extensometer displacement, \ud835\udeff\ud835\udc56, by the extensometer\u2019s gage length, \ud835\udc3f\ud835\udc54. The gage length of the extensometer was always 0.5 in. \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 = \ud835\udeff\ud835\udc56/\ud835\udc3f\ud835\udc54 The axial and transverse strains were plotted with respect to axial force. The slope of the transverse strain vs. axial load, \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 , was divided by the slope of the axial strain vs. axial load, \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 , and this equaled the Poisson\u2019s ratio of the material. \ud835\udf10 = \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 / \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 (8) (9) (10) (11) (12) 40 4.1.3 Equations Used with the Rosette Strain Gage Using the Equations (13) \u2013 (15), one can find the principle strains in the x-direction, \ud835\udf16\ud835\udc65, y- direction, \ud835\udf16\ud835\udc66 and finally the shear strain in the xy-direction, \ud835\udefe\ud835\udc65\ud835\udc66 . The three different theta values, \u03b81, \u03b82, \u03b83 were all angles relative to the axial strain gage. The strain rosette was placed on the composite quasi-isotropic specimen's surface so that each strain gage was in 0\u00b0, +45\u00b0 and 90\u00b0. So \u03b81 equaled 0\u00b0, \u03b82 equaled +45\u00b0, and lastly \u03b83 equaled 90\u00b0. The principle plane stresses were also transformed with a transformation matrix to the desired angle, \u03b8. In the transformation matrix c = cos \u03b8 and s = sin \u03b8. Where A is considered the transformation matrix below. The transformed plane stresses, \ud835\udf0e\u2032, equaled the transformation matrix, A times the plane stresses, \ud835\udf0e. (13) (14) (15) (16) (17) 41 Once the three principle strains were calculated then a transformation matrix was used to transform each of the three strains to the desired angle, \u03b8. The transformed plane strains, \ud835\udf16\u2032, equals Reuter's Matrix, R, times the transformation matrix, A, by the inverse of the R matrix, and lastly times the plane strains. The modulus of rigidity, G, was found by dividing the modulus of elasticity, \ud835\udc38, by 2 times Poisson\u2019s ratio, \ud835\udf10, plus 1. \ud835\udc3a = \ud835\udc38 2(1+\ud835\udf10) 4.1.4 Equations Used for In-Plane Shear Modulus Testing of Unidirectional Carbon Fiber Specimens The maximum shear stress, \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 (18) (19) (20) (21) 42 divided by the cross-sectional area times two. \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 2\ud835\udc34 The shear stress, \ud835\udf0f12, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65divided by the cross- sectional area times two. \ud835\udf0f12,\ud835\udc56 = \ud835\udc43\ud835\udc56 2\ud835\udc34 The modulus of elasticity in the +/- 45\u00b0 shear modulus test, \ud835\udc38\ud835\udc65\ud835\udc65, was calculated by the difference two stress points and their equivalent strain points. \ud835\udc38\ud835\udc65\ud835\udc65 = \u2212\u0394\ud835\udf0e \u0394\u03b5 The shear chord modulus of elasticity, \ud835\udc3a12, was calculated by the Equation (25). \ud835\udc3a12 = 1/( 4/\ud835\udc38\ud835\udc65\ud835\udc65 \u2212 1/\ud835\udc381 \u2212 1/\ud835\udc382 + 2\ud835\udf1012/\ud835\udc381 ) Converting normal strain to shear strain is done by dividing the shear strain by 2. \ud835\udf16 = 1/2 \u2217 \ud835\udefe 4.1.5 Equations Used for Volume Fraction Testing of Cured Reinforced Resins The ignition loss of the specimen in weight percent is calculated by subtracting the weight of the specimen, W1, and the weight of the residue, W2. (22) (23) (24) (25) (26) 43 Ignition lost, weight % = [(\ud835\udc4a1 \u2212 \ud835\udc4a2)/\ud835\udc4a1 ] \u2217 100 4.2 Theoretical Equations 4.2.1 Equations Used to Find Laminate In-Plane Engineering Constants The NASA Composite Laminate Report [24] was used to find all the laminate in-plane engineering constants (or also known as in-plane laminate material properties). Before finding the laminate in-plane engineering constants, the assumptions must be stated. The quasi-isotropic laminate, with a layup sequence of [0 0 +45 -45 +45 -45 90 90]s, meant that it\u2019s symmetrical and balanced. A symmetrical laminate simplifies the calculations since all that is needed to determine the in-plane engineering constants is the A matrix since the B matrix is composed of all zeros. But for asymmetrical laminates, one would need A, B, and D matrices. The subscripted numbers after the matrix, for example, the 1 and 2 in A12, which is in the number in the first row and second column of the matrix. The theoretical method of finding the laminate in-plane engineering constants required knowledge of Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material properties [21]. The experimental datasheet material properties were used inside the theoretical method. In Equation (28), to find the modulus in the x-direction, the stress in the x-direction is divided by the strain in the x-direction. Which can be also written as force per length in the x-direction, Nx , divided by the laminate thickness, h all over the strain. (27) 44 The A matrix simplifies to the one below since the Bij matrix is all zeros. For each layer in the laminate one needs to solve for a unique Q matrix. If a laminate has 16 different layers then there will be 16 Q matrices and after they are all solved they need to be summed together to form the A matrix. Equations (29) \u2013 (40) will be needed in order to solve for each value in the Q matrix. For any angled ply, one uses Equations (33) \u2013 (40). (32) (31) (30) (29) (33) (34) (28) 45 There is no force (or stress in the other two directions) so those are set to zero. This further simplifies the equations. (35) (36) (37) (41) (40) (39) (38) 46 After further simplification of the Equations (42) \u2013 (44), Equation (46) was equal to our modulus in the x-direction, Ex , only after this number was divided by the laminate thickness, h. \ud835\udc38\ud835\udc65 = \ud835\udc41\ud835\udc65/(\ud835\udf16\ud835\udc65 0 ) \u2217 1/\u210e Next, the same exact method is applied to the y-direction. The modulus in the y-direction, Ey equaled Equation (48). \ud835\udc38\ud835\udc66 = \ud835\udc41\ud835\udc66/(\ud835\udf16\ud835\udc66 0 ) \u2217 1/\u210e Next, the same exact method is applied to the xy-direction. The shear modulus in the xy- direction was found, in Equation (50), Gxy , only after divided by the laminate thickness, h. (42) (43) (44) (45) (46) (48) (47) 47 \ud835\udc3a\ud835\udc65\ud835\udc66 = \ud835\udc41\ud835\udc65\ud835\udc66/(\ud835\udefe\ud835\udc65\ud835\udc66 0 ) \u2217 1/\u210e Poisson\u2019s ratio, \u03c5xy , of the laminate was calculated using Equation (51). Poisson\u2019s ratio, \u03c5yx , of the laminate can was calculated using Equation (52). (51) (52) (50) (49) 48 CHAPTER 5: EXPERIMENTAL RESULTS In this chapter, the experimental results are explained in detail. Section 5.1 explained the validation process, which was conducted, on all the strain measurement devices. The axial modulus of elasticity and Poisson\u2019s ratio of Aluminum were validated. Section 5.2 summarized the material testing which was conducted on the unidirectional carbon fiber material. Section 5.3 explained the unidirectional carbon fiber material property testing. Section 5.4 explained the quasiisotropic carbon fiber laminate material property testing. Section 5.5 explained the experimental results found for the Aluminum double shear specimens. Section 5.6 explained the quasi-isotropic carbon fiber double shear specimens\u2019 experimental results. 5.1 Experimental Measurement Device Validation Before any strain measurement device was used on a composite material, its accuracy needed to be validated with commonly known material. In this case, an Aluminum specimen was tensile tested with a strain gage orientated in the axial direction, and another strain gage orientated in the transverse direction. Since the axial strain gage, the extensometer and the crosshead were measuring axial strain, their readings were compared. In the past theses, students were using the crosshead displacement to measure the modulus of elasticity. Using the crosshead displacement was very unreliable and it is explained in more detail in the next sub section. 49 5.1.1 Extensometer vs. Axial Strain Gage vs. Crosshead Displacement The test set-up of the Aluminum specimen is shown in Figure 21. The three principle directions and the clamped sections of a standard uniaxial tensile specimen are shown in Figure 21. Below in Table 1, an Aluminum sample was loaded and unloaded three times up to a tensile stress of 25 ksi. The tensile stress was calculated using Equation (9). A tensile stress of 25 ksi lies in the material\u2019s linear elastic region and it is far away from materials yield stress of 35 ksi. Table 1 shows the comparison of experimental results between the extensometer, strain gage and crosshead. Table 1 also shows the dimensions of the Aluminum specimen. The strain gage and extensometer experimental results were validated with the Aluminum 2024-T4 datasheet mechanical properties [25]. The moduli of elasticity, in Table 1, are in msi (10E6 lbs./in.2) and were calculated using Equation (10). There was less than 1% error between the extensometer and the strain gage when compared to the Aluminum 2024\u2019s modulus of elasticity. When comparing to the crosshead, there was an error of 64%. The crosshead displacement is not as accurate as an extensometer or a strain gage, because the crossheads have compliance (inside the actuator assembly) which elongates as load is applied. The actuator assembly starts to elongate, which significantly affects the experimental strain results. The small standard deviation showed how consistent the results were when using the three different measurement tools and the testing machine. 50 showing the clamped sections and the 3 principle directions (right) 51 Below in Figure 22, one can see the three runs that were done using the extensometer and the axial strain gage. The crosshead displacement was excluded from Figure 22, since the experimental strain varied so drastically from the extensometer and the axial strain gage. The strain gage and the extensometer read very similar moduli of elasticity. The extensometer and strain gage proved to be reliable, so both measurement tools were used on the composite specimens. 52 5.1.2 Poisson\u2019s Ratio Validation Using Axial and Transverse Strain Gages The Poisson's ratio of the Aluminum 2024-T4 needed to be validated. In Figure 23, one can see the axial and transverse strains plotted with respect to the axial force. The axial strain gage output is shown in blue and the transverse strain gage is shown in red. A linear curve fit was applied to both sets of strain gage data and their respective linear equations are shown, as well. Poisson's Ratio equaled to a value of 0.26, for the Aluminum specimen, using Equation (13). 53 5.2 Summary of Carbon Fiber Material Properties Below in Table 2, the results accumulated from Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg material datasheet [21] are summarized. The values which have a (-) dash meant that they were not given in the material's datasheet. The strengths were specified in ksi, which is 10E^3 lbs./in. Table 3 shows the experimental material properties of the Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material, which were experimentally tested in the Cal Poly\u2019s Aerospace Composites Lab. Table 4 shows the experimentally tested and calculated quasi-isotropic laminate properties. Poisson's ratio, for Umeco\u2019s MTM49 Unidirectional pre-preg material was used from a previous report\u2019s value [26] of 0.25. All these material properties are further explained in the next few sections. Looking at Table 2 and Table 3, the 0\u00b0 compressive modulus is 22.3 msi and the 0\u00b0 tensile modulus is 26.6 msi. All of the tensile axial moduli of elasticity were similar but they were slightly higher than the compressive modulus specified in the datasheet. The tensile and compressive modulus should be very similar since the fibers are assumed to behave like an isotropic material. This material was not tested in compression since compression specimens need to be a lot shorter, in length (ideally have less than 0.5in. in gage length). An extensometer could not be mounted on the surface of the compression specimen since there is not enough room between the grips. The best way to measure, the compressive modulus of elasticity would be to use an optical high-speed camera, which records the relative motion through optics. 55 5.3 Unidirectional Carbon Fiber Material Property Testing 5.3.1 Test for 0\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens A laminate of 8 plies, [0]8T, was laid up and tested along the fiber direction. The 0\u00b0 direction is always the direction of the applied load in a uni-axial test. The ASTM 3039 [19] required a minimum of five specimens per test, and having more than five specimens helped improve the 56 consistency of the results. Each specimen was 10 in. long by 0.5 in. wide and with a thickness of 0.046 in. The ASTM 3039 [19] required curing 2 in. long by 0.5 in. wide Aluminum tabs on the specimens to prevent premature failures from occurring. The grip pressure was set to 160 bar. The tensile test began with testing one 0\u00b0 unidirectional carbon fiber composite tensile specimen (without an extensometer) to failure, to find its ultimate load. The limit load of 2,000 lbs. was chosen since the ultimate load was 4,600 lbs. The last six 0\u00b0 unidirectional carbon fiber composite tensile specimens were loaded to 2,000 lbs., and at 2,000 lbs., the test was paused so that the extensometer could be removed safely. Once the extensometer was removed, the Instron machine's crossheads took over in measuring the tensile strain. The load cell accurately measured the ultimate load up to an accuracy of +/- 45 lbs. In Figure 24, the 0\u00b0 unidirectional carbon fiber composite tensile specimens are shown to the left and one of the clamped post-test 0\u00b0 unidirectional carbon fiber composite tensile specimen is shown on the right. Figure 25 shows all seven of the tested 0\u00b0 unidirectional carbon fiber composite tensile specimens (each color represents a different specimen). Figure 26 shows the extensometer mounted on the 0\u02da unidirectional carbon fiber composite tensile specimen with two rubber bands. The compressive modulus was specified in the datasheet and the tensile modulus was not specified in the datasheet. The experimental tensile modulus was compared to the compressive modulus and the difference between the two values was 19%. A 17% difference between the tensile strength when compared to the datasheet values. 57 58 60 5.3.2 Test for 90\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens Next, a laminate of 14 plies, [90]14T, was laid up and tested along the matrix direction. A couple extra test specimens were tested to find the optimum hydraulic clamping pressure. The clamping pressure was initially set to 160 bar and once the specimen was clamped, it cracked. The hydraulic clamp pressure was reduced to 60 bar in order to prevent this premature failure from occurring. Eight specimens were tested since the material is very brittle and unpredictable. When examining the stress-strain plot of the 90\u00b0 unidirectional carbon fiber composite tensile specimens, the ultimate tensile stress determined the location of where the specimen would fail. As one can see in Figure 27, the four 90\u02da unidirectional carbon fiber composite specimens, which failed at an ultimate tensile stress of around 5 ksi, ended up breaking in the center. Whereas, the specimens which failed at a lower ultimate tensile stress failed near the emery cloth. The experimental results (between all the specimens) showed a very consistent modulus of elasticity. The ultimate tensile strength of the material varied, due to the matrix is very brittle. The failure of a brittle material is very unpredictable which one can see in the Figure 28. There was 17% difference between the datasheet 90\u00b0 modulus of elasticity and a 29% difference between the 90\u00b0 tensile strength when compared to the datasheet values. The ultimate tensile strength variations might have been due to the low accuracy of the load cell, which typically occurs at low loads (around 100 lbs.) since the accuracy of the load cell is +/- 45 lbs. Table 6 shows the experimental results of all the 90\u00b0 unidirectional carbon fiber composite tensile specimens. 61 63 5.3.3 Test for +/-45\u00b0 Shear Modulus Specimens After following ASTM D3518 [20], a laminate was created with an orientation of [+/- 45]4S which is a symmetric laminate with alternating positive and negative 45\u00b0 plies. Another way to write this is [+45 -45 +45 -45 +45 -45 +45 \u2013 45]s. The extensometer was placed at 0\u00b0 relative to the specimen. The axial modulus of elasticity, Exx, was recorded and Equation (25) was used to find G12. Equation (25) requires knowledge of E1, E2, and \u03c512. Eight shear modulus specimens, for consistency, were tested since ASTM D3518 [20] required a minimum of five shear modulus specimens. The shear modulus specimens are shown in Figure 29. The post-tested shear modulus specimens looked the same as the pre-tested shear modulus specimens (since the failure occurred in the matrix and not in the fiber). Figure 30 shows the highly consistent shear specimen results. Table 7 showed the detailed experimental results. There was 35% difference between the in-plane shear modulus and a 43% difference between the in-plane shear strength when compared to the datasheet values. Testing for the shear strength is not an easy task since the shear modulus specimen has to be in full shear state at failure. The tabs on the ends of the specimen create stress concentrations on the ends, which cause the specimen to fail prematurely. 64 66 5.4 Quasi-Isotropic Laminate Material Testing 5.4.1 Test for Quasi-isotropic Tensile Specimens The same test method used for the 0\u00b0 and 90\u00b0 specimens was used to test the carbon fiber quasi-isotropic tensile specimens. Once one quasi-isotropic tensile specimen was tested to failure, the ultimate load was recorded to be 6,500 lbs. The next six quasi-isotropic tensile specimens were tested with the extensometer up to a force of 2,000 lbs. The test paused once the force reached 2,000 lbs. and then the extensometer was removed. Figure 31 shows the quasi-isotropic tensile specimens before (on left) and after (on right) they were tested. The region circled in red showed the area where there was a fiber failure. Figure 32 showed a close-up of the tensile failure. In Figure 32, looking at the picture on the right, one can see the 0\u00b0 fibers on the outer layer held together, while in the center of the laminate, a crack began to form. The crack, in Figure 32, is circled in red. 67 68 From Figure 33, one can see a close-up of the strain rosette, which was on Specimen #1. Shown in Figure 34, a rectangular strain rosette (CEA- 06-120CZ-120 made by VishayPG) produced very accurate results. The rosette was placed on the quasi-isotropic tensile specimen at a 0\u00b0-45\u00b0-90\u00b0 orientation and the wires were soldered very accurately. Each strain gage resistance was checked (with a voltmeter) and read 120 Ohms. The strain gage worked correctly if the resistance across the strain gage read the correct resistance specified in the user manual. The quasi-isotropic tensile specimen #1 was tested one time by recording the strains in the 0\u00b0 direction, 45\u00b0 direction and 90\u00b0 direction. In addition, when the strain gage was being applied to the surface, an 80-grit sandpaper was applied to the surface of the quasi-isotropic tensile specimen. The sanding of the outer 0\u00b0 layer might have affected the material\u2019s mechanical properties. Table 8 shows this 8% difference in modulus of elasticity between the extensometer and the strain gage. From Figure 35, one can see the slight drop in stress (at 20 ksi) due to the pause in the test. The different line colors show the seven different quasi-isotropic tensile specimens that were tested. The main thing to note is the percentage difference between the modulus of elasticity found with the strain rosette and the extensometer. The ultimate tensile strengths were very consistent which showed from a very low standard deviation of 3.87 ksi. 69 70 72 5.4.2 Quasi-Isotropic Tensile Specimen #1 In-Plane Experimental Material Properties Figure 36 shows experimental strain values of the extensometer, the axial strain gage, the +45\u00b0 strain gage and the transverse strain gage. A slight variation exists between the axial strain gage and the extensometer because the extensometer was not placed in the same location as the strain gage. The sanding error, like stated in the previous section, might have also contributed to the error of 8%. The test was stopped at a force of 2,000 lbs. A linear curve fit was applied to all of the three separate strain gage readings and are shown in Figure 36. Next, the Poisson\u2019s ratio of the quasiisotropic tensile specimen was found using Equation (12) and in-plane shear modulus of the quasiisotropic laminate was found using Equation (23). The axial modulus of elasticity was found using Equation (10). 73 5.4.3 Quasi-Isotropic Laminate In-Plane Theoretical Material Properties The theoretical material properties were found using the NASA report on Basic Mechanics of Laminated Composite Plates [24]. In Section 4.2.1, one can find the equations used to calculate the theoretical material properties. Before these equations could be used, a few assumptions were made: (1) The material to be examined is made of up of one or more plies (layers), each ply consisting of fibers that are all uniformly parallel and continuous across the material. The plies do not have to be of the same thickness or the same material. [23] (2) The material to be examined is in a state of plane stress, i.e., the stresses and strains in the through-the-thickness direction are ignored. [23] (3) The thickness dimension is much smaller than the length and width dimensions. [23] The values in Table 9 were needed in order to come up with the theoretical material properties. Table 9 shows the values that were applied into the laminate theory since the laminate theory required knowledge of the material properties of one layer of the unidirectional carbon fiber material. With the help of a strain rosette and the use of Equations (13) - (15), all the in-plane principle strains could be found. 74 Below in Table 10, one can see the calculated experimental material properties using the strain gage rosette. Three different in-plane laminate material properties were calculated based on three different force values (1500 lbs., 1750 lbs. and 1900 lbs.). The theoretical material properties were in agreement with the experimental material properties since the error between the modulus of elasticity was only around 10% and only 2% for the Poisson\u2019s ratio. The low standard deviation showed the reliability of the testing equipment and the strain measurement devices. 75 5.5 Fiber Volume Fraction Test ASTM D2584 [27], Standard Test Method for Ignition Loss of Cured Reinforced Resins, was followed closely. Three volume fraction specimens were tested inside the furnace shown on the right in Figure 37. On the left of Figure 37, one can see a fiber volume fraction test specimen. The fiber volume fraction specimen was placed on top of an Aluminum plate. While the furnace was preheated to a temperature of 1000\u00b0F, the Aluminum plate was weighed and each fiber volume fraction specimen was weighed in grams and then converted to lbs. in order to keep the units consistent. The measuring scale had a least scale reading of 0.1 g. The dimensions of each fiber 76 volume fraction specimens were carefully measured and recorded. Each specimen was placed on the Aluminum plate and left inside the furnace for one hour. Once all the epoxy burned off, the fiber volume fraction specimen was weighed and this was weight of the fibers. The initial weight of the fiber volume fraction specimen minus the final weight of the fiber volume fraction specimen was the weight of the resin (matrix). After doing some simple calculations, along with using the cured resin matrix density of 1.24 g/cm3(from the material\u2019s datasheet); the fiber weight fraction along with the fiber volume fraction was calculated and compared to the datasheet. In Table 11, one can see the three different fiber volume fractions along with the fiber weight fractions. The fiber volume fraction specimen dimensions are crucial to the determination of the fiber volume fraction. The measured thickness of the fiber volume fraction specimen varied from 0.1 in. to 0.103 in., which meant that the heat press cooked unevenly. The slight variation of the specimen\u2019s thickness affected the volume fraction by 4%. The 8.3% difference between the experimental fiber volume fraction and the datasheet fiber volume fraction varied because not enough pressure was applied to the laminate during the curing process. The lower fiber volume fraction of 0.55 compared to 0.6 meant that there was more resin in the laminate. Not enough resin was squeezed out in the cure process. The pressure applied by the heat press was limited, so achieving the optimum fiber volume fraction (of 0.6) was difficult. The fiber volume fraction significantly affected all of the material property testing which was conducted on the Umeco MTM 49 unidirectional material. A low standard deviation showed that the data was very consistent. 78 Section 5.6 was conducted in order to validate the numerical model with the experimental data. Modeling a metal before modeling a composite is very important because metals behave in a more predictable fashion. Metals are a lot simpler to model since they exhibit isotropic behavior whereas composites exhibit orthotropic behavior. The material property inputs for an isotropic material are much less than for a composite material. For a composite, the user has to input three different moduli of elasticity, three moduli of rigidity, and three Poisson\u2019s ratios. For metals, the user only inputs the modulus of elasticity and the Poisson\u2019s ratio. In this validation, Aluminum 2024-T4 was used as the material of choice. Once the linear elastic model was validated with a metal, then any other material should be validated as well, but only for the linear elastic region of the material. This also validates the boundary conditions and any interactions, which were used in the numerical model. 5.6 Aluminum 2024-T4 Double Shear Test The Aluminum 2024-T4 double shear specimens were tested on the same double shear fixture as the composite double shear specimens. From Figure 38, one can see the bearing stress vs. bearing strain response of the five tested Aluminum double shear specimens. The first section of the bearing stress vs. bearing strain plot (the flat initial region) is the strain correction region. Compliance between the Instron parts, along with the clamps, occurred upon initial loading of the specimen. The deformation of all the internal parts of the Instron machine in the strain correction region. The linear elastic region, (shown inside the red square in Figure 38) for the Aluminum, was between 5 ksi and 40 ksi and after this region; the material experienced a non-linear behavior 79 up to its ultimate bearing strength. The strain correction region and the non-linear region were removed, which can be seen in Figure 39. The non-linear region and the strain correction region were not part of the numerical model. Figure 38 showed that specimen #5 failed at an ultimate bearing stress of 130 ksi and the other four specimens failed around 114 ksi. The extensometer\u2019s knife-edge slipped on the face of specimen #1 through #4, but for specimen #5, the extensometer did not slip. The linear elastic region can be seen in Figure 39. The specimen alignment might have caused the variations in the linear elastic strain values. The ultimate bearing strength matched up the Aluminum 2024-T4 material\u2019s datasheet [25]. Table 12 shows the experimental results of the Aluminum double shear specimens. Both the yield and ultimate strengths were calculated in the Table 12. Figure 40 shows a bearing type of failure, which occurred in all the Aluminum double shear specimens. Figure 41 shows the Aluminum double shear specimens before and after they were tested. The region circled in red shows the area where the failure occurred. Each specimens\u2019 hole diameter increased in size and also each specimens\u2019 hole diameter did not go back to its original shape once the load was removed, which showed that the material reached a plastic deformation. 80 82 5.7 Composite Double Shear Test As one can see in Figure 42 (from a paper by Yi Xiao [28]), the composite double shear specimens behaved differently than Aluminum double shear specimens. Recall, all the composite double shear specimens were manufactured with a quasi-isotropic laminate orientation of [0 0 +45 83 -45 +45 -45 90 90]s. The 4%D is considered the bearing strength of the material. The composite double shear specimens held load (without failing) up to the knee point. At the knee point, the first ply failed (after this point, the material properties started to degrade) and the slope of the curve was reduced. The load increased up to the final point, also known as the ultimate bearing strength of the material, where it maxed out. One positive thing about designing a structure to fail in bearing, as opposed to net-tension or shear-out, is that the force dropped 30% of the maximum load. Whereas, in net-tension or shear-out failure, the load dropped down to zero. Figure 43 shows a close-up of the bearing failure, which occurred on the composite double 84 shear specimens. As one can see, there is an excessive amount of damage near the pin location. All of the specimens exhibited a similar type of failure, so there was no need to take a picture of each of the failed specimens. Figure 44 shows ASTM 5961\u2019s [18] failure codes used to characterize any of the failure modes seen in a composite double shear test. The failure code, B1I, is used throughout the rest of the experimental section, which signifies a bearing type of failure. 85 86 5.7.1 Curing Cycle 1 (Cytec\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test Figure 45 shows the composite double shear specimens before and after the double shear test. In Figure 45, on the right, highlights the crushing regions, in red. All the failures are consistent. Eight specimens were tested for each of the five loading rates. For load rate 0.1 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. When looking at the alternate cure cycle experimental data, in Tables 13 & 14, an interesting 87 trend appeared. At slower loading rates, the composite double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min. the composite double shear specimens failed at an average stress of 64.4 ksi and 63.5 ksi whereas at 1 in./min., 2 in./min. and 6 in./min. the composite double shear specimens failed around 52.3 ksi. Looking at all the different loading rates, it seemed as if all the composite double shear specimens had a similar knee point. 2 in./min. and 6in./min. showed a greater drop in load after the composite double shear specimens reached their ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. did not show a huge drop in load after the specimens reached the ultimate load. 89 The maximum values of all the plots, in Figure 46, were the ultimate bearing strengths. When looking at Figure 46, one can see that as the loading rate increased the non-linear region decreased in size. The red-circled sections, in Figure 46, show how the non-linear region decreased in size. The linear region does not change as drastically as the non-linear region. As the load rate increased, the rate of damage also increased which explained the reduction, in size, of the non-linear region. 90 Looking at all of the load rates, the moduli in the non-linear regions are lower than the linear elastic regions. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. 91 5.7.2 Curing Cycle 2 (Umeco\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test When looking at the datasheet cure cycle experimental data, in Tables 15 & 16, a similar trend appeared. At slower loading rates, the double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min., the specimens failed at an average stress of 62.7 ksi and 67.7 ksi, whereas at 1.0 in./min., 2 in./min. and 6 in./min., the specimens failed around or under 52.0 ksi. It also looks like at 2 in./min. and 6in/min. show a greater drop in bearing strength after the specimen reaches its ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. do not show a huge drop in strength after the specimens reach the ultimate load. In general, fast loading causes more damage to the specimen which overall reduces the specimen's ability to carry load. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. Eight specimens were tested for each of the five loading rates. For load rates 2 & 6 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. 93 When looking at Figure 47, one can see that as the loading rate increased the non-linear region decreased in size. In Figure 47, the red-circled section also showed the non-linear region decreased, in size, with increased loading rate. 94 5.7.3 Comparison between Cure 1 & Cure 2 In Figure 48, it is very clear that as loading rate increased, the ultimate bearing strength of the 95 material decreased regardless of the cure cycle. Further research can be done on how different cure cycles can affect the bearing response of a composite double shear specimen. Making the matrix less brittle and more ductile might improve the ultimate bearing strength of the material. Cure cycle 2 (Umeco\u2019s cure cycle) was 2% stronger in bearing when compared to the cure cycle 1 (Cytec\u2019s cure cycle). The MTM 49 Unidirectional carbon fiber pre-preg material was very sturdy by not being affected by an alternate cure cycle. 5.7.4 Comparison Between The Aluminum Double Shear Specimens & Quasi-Statically Loaded (0.05 in./min.) Composite Double Shear Specimens Aluminum is standardly tested at quasi-static load rate of 0.05 in./min, since it\u2019s strain rate independent [30] (not affected by different loading rates). The Aluminum double shear specimens 96 performed a lot better in bearing than the composite double shear specimens. Since the carbon fiber is more brittle by nature, its ultimate bearing strength is significantly lower than Aluminum. of the Aluminum double shear specimens was around 118 ksi and the ultimate bearing strength of the composite double shear specimens was around 63 ksi. That means that carbon fiber is 53% weaker than Aluminum 2024-T4 in a double shear joint configuration. The Aluminum double shear specimens yielded at around 40 ksi compared to the composite double shear specimens, which yielded at 30 ksi. As one can see from the bearing stress vs. bearing strain graphs, there is a huge difference in ultimate bearing strength between of both materials. It is interesting to note that both materials showed a strain correction region. The Aluminum double shear specimens and the composite double shear specimens did not catastrophically fail (they deformed without significantly dropping the applied load). 97 CHAPTER 6: NUMERICAL ANALYSIS Chapter 6 explains the overall finite element approach. Section 1 introduces the finite element model and different considerations, which were applied to the model. Section 2 explains the idea behind a convergence plot and its importance. Section 2 explains what factors influenced the numerical results. 6.1 Finite Element Analysis Introduction Once a Finite Element Analysis model is validated with experimental results, it can then be used in the design process. Abaqus 6.14-1 was used to model the double shear bearing test experiment conducted. All the different Finite Element software work very similarly and the only difference between them is their program interface. However, they all essentially break up the model into small elements and calculate the stress state on each element. The material properties are assigned to the elements and then, the boundary conditions and loads are applied to the model. In some cases when there are two or more parts, one might have to define different types of interactions or constraints for the model (for example, how those parts move relative to each other). The numerical software also predicts non-linear behavior, which requires a lot more material properties. Plasticity required the user to model the damage done on the material as load increased, which meant, implementing a degradation model. First, a numerical model was created and validated for the Aluminum 2024-T4 double shear 98 specimen. The Aluminum numerical model was only validated through the linear elastic region of the experimental data, which was shown in Figure 39. The Aluminum numerical model was adjusted for the composite specimen and the experimental results were compared to the numerical results. Abaqus keeps the units consistent, so when working with US Customary units make sure to stay consistent with the units, if using inches, stick to using inches. The displacement plots should be in the same units as one started with, and the stresses should be in pounds per square inch (psi). 6.1.1 Geometric Definitions The numerical model contained four parts. The two side plates, double shear specimen, and pin were modeled as deformable 3D solids. Both steel plates along with the double shear specimen were partitioned. The steel collars and center middle plate were neglected for simplicity. All the bolts, nuts and washers were also neglected in the model for simplicity reasons. 6.1.2 Material Creation, Section Assignments, & Meshing All the dimensions were defined in English units and the dimensions for each of the parts came from the fixture design. The fixture used in the numerical model was simplified. All the composite material properties were inputted in the elastic engineering constants. Table 17 showed the material properties, which were, applied to the Aluminum numerical model. A Steel solid homogeneous section and an Aluminum solid homogeneous section were created. 99 A composite layup section was applied to the composite double shear specimen and the element type was set to solid. Table 18 shows the material properties that were applied to the composite double shear specimen. In the composite layup section, the user is able to set the element stacking direction, the coordinate system, and the rotation axis. The user can also specify the laminate orientation and select the region for each ply within the model. In the Appendix, there is a tutorial of how the Abaqus composite double shear specimen was modeled. A single layer of unidirectional carbon fiber material is considered a transversely orthotropic material, where E2 is equal to E3 and G12 is equal to G13. E2 and E3 are both considered the matrix and E1 is considered the fiber. One thing to note was that the compressive modulus in the 1- direction (axial) was slightly lower than the tensile modulus, which was found in the Experimental section of the report. The Poisson\u2019s ratio in the 23-direction and the shear modulus in the 23- direction are usually very difficult to find experimentally. Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager was used to find some of the material properties that could not 100 be found experimentally. In the Appendix, one can find the tutorial on how to use Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager. One can also find a step-by-step Abaqus tutorial on the composite double shear specimen. Parts of the step-by-step tutorial were found from D.S. Mane [29] . The parts were individually partitioned which made meshing them very simple. Once the partition was created, the user needed to use the Seed Edge command, then select whole part, and for method select \u201cby number\u201d. As indicated below in sizing control, the user is able to assign the number of elements from one to however many. The convergence plot was constructed using four different nodes per element. The element\u2019s relative thickness was set to 0.5 since there were only two elements that made up the thickness of the part. 101 6.1.3 Assembly, Interactions & Steps The whole assembly was modeled very similarly to the experiment. Each part was given a dependent instance and no tie constraints were used in the model. A contact step and a load step were added to the analysis. The contact step initiated the contact between the pin and the steel plates and also the pin and the specimen. The load step served to apply load to the analysis once full contact was established. The pin was not constrained to the specimen with a tie constraint because that implied a condition similar to being welded. So in contrast, a surface-to-surface interaction was established between the pin, the steel plates and the specimen. The sliding formulation selected was finite sliding. The pin was set as the master surface and the slave surface consisted of two surfaces. One was the surface in contact with the pin and the inner side of the specimen and the other was the surface in contact with the pin and the inner side of both steel plates. The slave adjustment was set to a value of 0.007 in. A contact property with a tangential behavior (the friction formulation was set to penalty and the friction coefficient was set to 0.46). In addition, a normal behavior contact property with the pressure-overclosure was set to \u201cHard\u201d Contact; constraint enforcement method was set to default, and allowed separation after contact. 6.1.4 Boundary Conditions & Loads The boundary conditions applied to the model needed to be assigned carefully. The top face of the specimen (opposite face with the hole) was fully fixed in the x, y and z directions. This was 102 similar to the clamped condition, which is applied by Instron\u2019s crossheads. The second boundary condition that was applied was on the outer pin surface and the inner hole surfaces of the steel plates and the bearing specimen. In the contact step, the pin, steel plates and specimen were not allowed to move in the x, y and z directions. The load step was modified to allow the side plates, pin and specimen to move in only the y-direction. The combined load of 600 lbs. was applied to both of the bottom faces of the steel plates. This was done by applying the load, in the load step, as a total force distribution pressure load. The loading condition used in the model was similar to the experimental loading condition, where a fraction of the force is applied at each time interval. Some elements in the model experienced plastic deformation only when the applied load was over 800 lbs. This meant that certain elements were in stress state beyond their linear elastic limit. The ultimate force was not predicted, by the numerical analysis, since that occurred in the non-linear region. 6.2 Numerical Results This section provides the explanation of the convergence plot and talks about the factors, which influenced the numerical results. In Chapter 7, the numerical results are explained in detail. 6.2.1 Convergence Plot For the numerical model, a partition was created on the face of the specimen. Taking time to draw a symmetrical and neat partition prevented the mesh from becoming unsymmetrical and 103 prevented unusual results. The partitioned double shear specimen is shown in Figure 49. In Figure 50, one can see a close up of the partitioned region around the hole. After a partition was created, the user was able to assign a specific amount of elements using the Seed Edge command. Here the user is able to set the total amount of nodes per element to any value. For the convergence plot, 2, 6, 8, and 10 nodes per element were chosen, and the final vertical deflection at the pin was compared. A convergence plot was created to see if adding more elements to the model actually improved accuracy. Knowing the optimum amount of elements for the least amount of time for the model to complete is very important in the design process. As one can see from Figure 51, as the total amount of nodes per element increased, the deflection did not change significantly. Using more than six elements per node did not significantly improve accuracy, but it did take longer to run. 6.2.2 Factors That Influenced the Numerical Results Increasing the total amount of elements through the thickness of the part, did not significantly affect the pin deflection results. Changing the axial modulus (from tensile to compressive) significantly affected the pin deflection results. The compressive axial modulus was imported into Abaqus rather than the tensile modulus, because the double shear test is mainly a compression type of loading. The fibers are in compression around the hole. When initially assuming a frictionless contact (when the frictional coefficient equaled zero) the specimen ended up colliding with one of the side plates. Changing the frictionless coefficient 104 from zero to 0.46 helped prevent the specimen from colliding with one of the side plates. 105 106 CHAPTER 7: COMPARISON BETWEEN EXPERIMENTAL & NUMERICAL DOUBLE SHEAR RESULTS The slope of the reaction force vs. pin displacement was compared between both the experiment data and the numerical model. First, the numerical Aluminum model was validated. Then the numerical composite model was validated. 7.1 Numerical Aluminum Model Comparison to Experimental Results Looking at Figure 59, the region highlighted in red was due to the compliance in the testing assembly. The bearing stress vs. bearing strain plot was then converted to a load (reaction force in the y-direction) vs. pin displacement plot. All of the specimens were plotted up until the linear region. Looking at Figure 60, of the five tested Aluminum double shear specimens, the numerical results only matched up with one. The four other Aluminum double shear specimens might have slipped with respect to the extensometer\u2019s knife-edge. One way to tell is by the lower load (reaction force in the y-direction) vs. pin displacement slopes. In Table 19, the total error when comparing the experimental slope to the numerical slope was 16%. Misalignment of the specimen might have caused this significant error to occur. 107 108 7.2 Composite Numerical Model Comparison to Experimental Results Figure 54 showed the load (reaction force in y-direction) vs. pin displacement response of the 0.05 in./min. composite double shear specimens that were cured to the recommended datasheet cure cycle. Three of the eight tested composite double shear specimens at 0.05 in./min. did not slip. The strain was corrected using the same method that was applied to the Aluminum double shear specimens. Of the eight carbon fiber specimens that were tested, only three of them closely matched up to the numerical results. The numerical model was loaded to 600 lbs., which was still within linear elastic limit of the material. The load (reaction force in y-direction) vs. pin displacement slopes between all the experimental specimens shown were compared to the numerical model. In Table 20, the average error between the numerical slope and the experimental slopes was about 7.1%. Alignment is a huge factor, which can affect experimental results quite significantly. There will always be error between the experimental and numerical results. The numerical 109 results are the idealized results and the experimental results have so many factors, which can influence their results. Errors from 7% to 16%, for both the aluminum double specimens and the composite double shear specimens, are actually quite reasonable because there is always error in the manufacturing process, displacement measuring equipment, load cell, specimen alignment exc. 111 CHAPTER 8: CONCLUSION The first important contribution of this study was to see how different loading rates affected the ultimate bearing strength of a composite material. One can see that at 0.05 in./min. and 0.1 in./min. (for both cure cycles) the composite double shear specimens carried more load compared to higher load rates of 1 in./min., 2 in./min. and 6 in./min.. All of the specimens failed in bearing and not in net-tension or shear-out. The second important contribution of this study was to see how the recommended datasheet cure cycle and the alternate cure cycle affected the ultimate bearing strength. The two different cure cycles behaved very similarly under the five different loading rates. The average ultimate bearing strength of the Aluminum double shear specimens was 118 ksi and for the composite double shear specimens it was 65 ksi. The experiment showed that carbon fiber material is significantly weaker, in a double shear tensile loading configuration, compared to Aluminum. Ductile materials, like Aluminum for example, handle the double shear tensile loading configuration a lot better than the carbon fiber material, which is brittle. Each carbon fiber sheet is relatively thin which is also very poor for carrying bearing stress. Usually what designers do is use inserts inside and around the hole if they need to improve the bearing strength of a composite joint. The inserts help redistribute the stress concentrations (which are caused by mechanical fasteners) and prevent the brittle material from cracking. The inserts are usually made from ductile materials, like fiberglass or Aluminum. 112 8.1 Recommendations The experiments were carried out using carbon fiber unidirectional pre-preg tape. Similar research can be done using various other materials like: kevlar, fiberglass, or even hemp. Similar testing can be done using a single shear joint configuration. Various carbon fiber types can be tested as well. MTM-28 material is a thicker type of unidirectional fiber, which would be very interesting to test. A high-speed video camera would be a more efficient way to monitor deflection since the extensometer's range was the limiting factor in the data capture. A more in depth case study can be conducted on different cure cycles of composite resins. The pre-load function in the Bluehill2 software can be utilized in order to try to eliminate some of the strain correction region. 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Strength of mechanically fastened composite joints. Journal of Composite Materials, 16, 470-494. 13. Ger, G.S., Kawata, K., Itabashi, M.: Dynamic tensile strength of composite laminate joints fastened mechanically. Theor. Appl. Fract. Mech. 24(2), 147\u2013155 (1996). 14. Li, Q.M., Mines R.A.W., Birch R.S. (2000, September). Static and dynamic behavior of composite riveted joints in tension. 15. United States Naval Academy (USNA). (2003). Composite Orientation Code. http://www.usna.edu/Users/mecheng/pjoyce/composites/Short_Course_2003/7_PAX_Sh ort_Course_Laminate-Orientation-Code.pdf 16. Kretsis, G., & Matthews, F.L. (1985, April). The strength of bolted joints in glass fiber/epoxy laminates. Journal of Composite Materials, 16, 92-102. 17. Yeole, Amit. (2006, December). Experimental Investigation and Analysis for Bearing Strength Behavior of Composite Laminates. 115 18. Anonymous, \u201cStandard Test Method for Bearing Response of Polymer Matrix composite Laminates,\u201d ASTM Standards, Designation: 5961/5961M-05. 19. Anonymous, \u201cStandard test method for tensile properties of fiber-resin composites,\u201d ASTM Standards, Designation: 3039-76. 20. Anonymous, \u201cStandards. In-plane shear stress-strain response of unidirectional reinforced plastics,\u201d ASTM Standards, Designation: 3518-76. 21. Umeco, \u201cMTM 49 Series Pre-preg System \u2013 Unidirectional Material Properties.\u201d 22. Cytec, \u201cMTM 49-3 \u2013Unidirectional Material Properties.\u201d 23. Instron, \u201cInstron 8801 Servo-hydraulic Machine Photo.\u201d http://www.instron.us/en-us/ 24. Nettles, A.T., (1994, October) \u201cBasic Mechanics of Laminated Composite Plates.\u201d 25. ASM Aerospace Specification Metals Inc., \u201cDatasheet Mechanical Properties of Aluminum 2024-T4.\u201d 26. Anonymous, \u201cProject 1 Report\u201d ME-412. 27. Anonymous, \u201cStandard test method for ignition loss of cured reinforced resins,\u201d ASTM Standards, Designation: 2584-02. 28. Xiao, Yi. \u201cBearing strength and failure behavior of bolted composite joints (part II: modeling and simulation). 29. De, S. MANE 4240/CIVL 4240: Introduction to Finite Element. Abaqus Handout. 30. Semb, Evind. \u201cBehavior of Aluminum at Elevated Strain Rates and Temperatures.\u201d 116 APPENDICES A.1. Drawings for the Fixture Assembly 117 118 A.2. Tutorial on Bluehill2 Test File Setup Various settings were changed inside the BlueHill2 software. Below, I will show a couple of the parameters that were changed. Navigating through the menus is self-explanatory. In the Control submenu, the load rate was changed for each test. The quasi-static case was tested first at a load rate of 0.05 in./min. The second load rate, which was tested, was 0.1 in./min., the third was 1 in./min., the fourth was 2 in./min. and the fifth speed, which was tested, was 6 in./min. 119 The end of test criteria was changed to the ASTM specification. End of test 1 specifies the drop in the load of 30% the peak value and end of test 2 is specified as an extensometer displacement of 0.1 in. The extensometer shows up at Displacement (Strain 1) as a separate channel. 120 In the Control submenu, the sampling rate was changed from the default rate of 10 samples/sec to 3 samples/sec as required by ASTM D5961. This change showed a significant reduction of noise within the extensometer displacement readings. A value of 500 ms was adjusted for the time channel and the load sampling rate was left to default interval of 56 lbf. 121 Below in the Control submenu, the source of tensile strain was changed from the BlueHill2 default channel of \u201cTensile Strain\u201d to the \u201cStrain 1\u201d. The extensometer shows up as \u201cStrain 1\u201d. 122 Bluehill2 also has the option of calculating numerous parameters. In my experimental testing, I needed to calculate the ultimate bearing strength so I picked User Calculation. Then Bluehill2 gives you an option to define various variables like: D (diameter of hole), k (calculation factor for double shear k = 1), Pmax (maximum force carried by the specimen prior to failure), and t (defined as the thickness of the laminate). After all of your variables are defined, the equation designer tool 123 is used to create your equation of interest. In the Results submenu, the user is able to pick exactly which values he/she wants to output while in the test screen. The results are outputted as a column of values for each of the different test specimens. I wanted to output all of these parameters below while I was conducting my tests. 124 In the Graph submenu, the user is able to output two real-time changing graphs. For graph 1, I chose to output Instron crosshead displacement vs. load and for graph 2 I chose to output extensometer displacement vs. load. The X-Data was set to either Extension (for Instron crosshead displacement) or Displacement (Strain 1) (for extensometer displacement. The Y-Data was set to Load for both graph 1 and graph 2. 125 In the Raw Data submenu, Bluehill2 has a great function, which allows the user to export any given output of experimental data into a .csv file. This file can later be opened up with Excel and used to calculate various experimental stresses, strains and other parameters of interest. For my experimental testing, I was interested in outputting: time, crosshead displacement, extensometer 126 displacement, load and corrected position. The last bit of raw data, which needed to be outputted, is shown below. This set of data is saved onto the same .CSV file as the one specified in the previous screen. This set of data is located in its own set of two columns in the .CSV file. 127 A.3. Tutorial on Finding the Unknown Engineering Constants Autodesk created a very powerful tool, which can help the user figure out unknown engineering constants of a ply. For example from the experimental results, the user is able to experimentally determine E1, E2, G12 and \u03c512. Shown below are all the values, which the user inputs into the Autodesk Simulation Composite Analysis 2015 Material Manager. Make sure to label the 128 material a unique name and choose the correct units. The fiber type should be carbon intermediate for the MTM 49 since it is not the ultra-high fiber modulus. The volume fraction should be the one, which was found experimentally in the Results chapter, of 0.55. In Figure 67, in the first row of the Ultimate Lamina Strengths the user inputs the tensile strength in the 0\u00b0 and the 90\u00b0 directions. In the second row, the user inputs the compressive strength in the 0\u00b0 and 90\u00b0 directions and finally, in the last row, the user the user inputs the in-plane shear strengths. 129 In Figure 68, the user will input the known modulus of elasticity into the Lamina Elastic Constants section. The in-plane Poisson's ratio, which was assumed to be around 0.244, was used from a previous paper, which found the material property experimentally on the same MTM 49 Unidirectional material. The in-plane shear modulus was inputted from the experimental testing. 130 The key is to assume a value if you do not know what it is. After all the values have been inserted into the program go into the File, menu and then click optimize. It will ask you if you want to save the material properties somewhere and all you do is specify where you want to save the data. It will take a couple seconds to optimize the values accordingly. A.4. Tutorial on Outputting Force vs. Pin Deflection from Abaqus The pin deflection needed to be monitored for one node on the specimen. The area of interest is shaded in dark blue and the red dot signifies which node was monitored for its vertical deflection. In Figure 70, one can see the deflection in the y-direction, which occurs around the hole. This hole 131 is a localized compression zone. 132 Next what was needed was to have a force vs. time graph. The top most nodes on the specimen were fixed using the encastre boundary condition. The reaction force in the y-direction was captured for all the nodes that make up the top of the specimen. Once all the reactions at each nodes were captured, the whole region was summed up. Under create XY plot click ODB field output and then click continue. Under the Variables tab, find the Output variable box, and in the position menu, click Unique Nodal and then go into RF: Reaction Force and check the RF2 button. Since we are interested in the reaction force in the y-direction (2 direction). Next, click the Elements/Nodes tab and then pick the from viewport button and then click Edit Selection. Once all the fixed nodes are selected, as shown in Figure 72 below, click the Done button in the viewport. Lastly, go into Active Steps/Frames; make sure All steps are selected and set it to Frame. In the bottom of the window, make sure a green checkmark is applied to both the Contact and the Load steps. 133 Using the Create XY Data option in Abaqus, the user is able to go into Operate on XY data. In the Operators window, pick sum((A,A,...)), then under XY data, select all the Reaction Force nodes, which show up as _RF:RF2 and then click Add to Expression. Once all the nodes are inside the Sum operator, hit the Plot Expression button. This will output a force vs. time graph. 134 Once both the force vs. time graph and deflection vs. time graph are created, one needs to combine both graphs. In the Create XY Data, click Operate on XY Data and then press Continue. Under the operator tab, find combine(X,X) and then click it once. The combine operator requires two variables for the plot. For the first variable, click the deflection XY data, and for the second variable, click the Reaction Force 2 XY data. Make sure a comma separates both variables. Once done click the plot expression button and this should bring up a Force vs. Pin Deflection plot as shown in Figure 74. 135 A.5. Tutorial on Modeling the Double Shear Bearing Specimen Assembly Open up Abaqus 6.14. The numerical model should look like something like this. The complete assembly, the pin and one of the side plates modeled with Abaqus 6.14. 136 A.5.1. Model Creation Create a new model by right clicking the Models category. Name it DoubleShear. Then press Ok. 137 A.5.2. Part Creation Next, we have to create the parts for the model, after that, we partition each of the parts. Click on the + button to expand the options inside the DoubleShear model. Right click on Parts and press Create. A menu will appear like the one shown below. Name the part SteelPin. Keep the modeling space: 3D, the type: deformable, the base feature shape: Solid and for the base feature type: Extrusion. Click continue. 138 Click the Create Circle button. Using the dimension tool below set the radius to 0.125 in. Always be consistent with your units (I am using inches). 140 Next, we need to create the double shear specimen. Copy the step above and only change the name of the part to Specimen. Use the rectangle tool (to the right of the circle tool) and make a basic rectangle. 141 Using the dimension tool set the width of the part to 1.5 in. and the length of the part to 5.5 in. Create a Line down the middle of the part. Locate the center of hole 0.75 in. from the bottom edge of the specimen and make sure the hole is centered along the specimen\u2019s width. 142 Now, delete the centerline with the eraser tool, which is highlighted and then click on the centerline (which should highlight in red) and click done. Click the eraser tool to disable it. 143 In the bottom of the drawing window, it should read, \u201cSketch the section for the solid extrusion\u201d. Click the Done button. Set the depth to 0.1 in. Since the carbon fiber specimen\u2019s thickness was 0.1 in. Next, we need to create the side steel plate. Copy the step above and only change the name of the part to SidePlate. Use the rectangle tool (to the right of the circle tool), make a basic rectangle, and use the circle tool to create a hole in the plate. The side steel plate should be 2 in. by 4 in. and it should have a 0.141 in. radius hole. Which is located 1.0 in. from the top of the side plate. Lastly, remove the centerline and then set the depth to 0.25 in. Since the side steel plates had a thickness of 0.25 in. The three parts should look like this once they are completed. 144 A.5.3. Partition Creation A partition was created on the side plates and on the specimen. This made sure that when the mesh was generated all the elements stayed symmetrical. One major source of error in finite element analysis is due to elements not being symmetrical and the same size. One way to avoid this problem is to create your own mesh, which requires the user to partition the part based on what is of interest to him/her. Pick Tools, in the top drop down menu, and choose Partition. Click Face for the partition type and then click on the side plate face highlighted in orange. 145 Click Done and then it will ask to click a line vertical and to the right. Shown below, the highlighted edge is shown in pink, and the non-highlighted edges are shown in red. The part will switch from 3D to 2D and then here the user is able to create the partition desired. Create the partition below with these dimensions using the circle and line tools. It is important to keep the mesh coarse on parts which are not of main interest. 146 Apply the same method to the double shear specimen. The partition on this specimen was a lot more detailed than on the steel side plate. There are six circles, which are all equally spaced apart. The three outer radii were 0.5 in., 0.375 in., and 0.625 in. The three inner radii were 0.1875 in., 0.25 in., and 0.3125 in. A finer partition was created on the three inner radii where the circle was segmented into 64 equally spaced smaller sections. 147 The final partitioned parts should look like this. 148 A.5.4. Material Creation The material properties need to be created. Two materials were used in the analysis: steel and a unidirectional carbon fiber material. Under the Parts category, right click and click create. Name the material Steel. Go into the Mechanical option, then press elasticity, then elastic. Keep the type set to a default isotropic setting. Set the Young\u2019s Modulus to 34e6 and set the Poisson\u2019s ratio to 0.3. Follow the step right above, and create a new material and name it Uni. For the type, select 149 Engineering Constants. Include the material properties in the Table below (remember that msi is 106 psi)." + ] + }, + { + "image_filename": "designv8_17_0000365_ai.28-6-2020.2298143-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000365_ai.28-6-2020.2298143-Figure11-1.png", + "caption": "Fig. 11. 3D beams in data-mode.", + "texts": [ + " The 2D-cartesian beam-steering of the presented design over the scanning angle of -70\u00b0~70\u00b0 plotted in Fig. 10. It is clear from the figure that the designed 5G phased array antenna exhibits symmetrical beam steering in minus/plus scanning angles [33-36]. In addition, it provides almost constant gain levels with value around 10 dB at different scanning angles. The antenna characteristics in the adjacency of the user including the hand and head can be reduced. This also depends on the distance and placement of the antenna component [37-40]. Figure 11 investigated the performances in data-mode for different angles. As plotted, the antenna provides well-defined radiation beams and beam-steering at different scanning angles. This might be due to miniaturized and compact sizes of the employed element which not covered by user-hand. As can be seen, the gain levels of the beams are reduced but not significantly. Conclusion In this study, a compact phased array with miniaturized radiation elements is presented for 5G smartphone applications. It contains eight folded dipoles which have been linearly arranged to form a phased array on the PCB top side" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure17-1.png", + "caption": "Fig. 17 Instantaneous discharged pressure range from the casing outlet of the RB and DFB", + "texts": [ + " It can be observed that the suggested modification increases the range of discharged pressure (pressure coefficient), about 50% more than that discharged from the simple radial impeller (standard one). . 5-2 Assessment of the suggested modifications By comparing, both Figs 15 and 16, it can be observed that the pressure of the flow field around the blades in case of double forward blade modification, DFB, is larger than that of the radial blade, RB. Figures 17 shows the instantaneous discharge flow pressure at the outlet pipe ports after three complete revolutions of impeller for both cases: radial blades and double forward blades. It is also observed from Fig. 17 that the discharged local pressure range for the double forward blade, DFB, is higher than the standard radial impeller, RB. This means that the DFB produces largest discharge pressure compared with that of RB one. This result can be also be concluded from tracking the pressure developing between each blade of the double forward, DFB, and the radial blades, RB, through a flow path located +5 mm from the X-Y plan. Figure 18 shows the velocity vectors and the direction of the flow at the tracked path for the radial pump" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure49-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure49-1.png", + "caption": "FIGURE 49. Simulated normalized radiation patterns and surface current distributions of the first three dominant CMs at 2.4 GHz (a): Mode 1 (b): mode 2 (c): mode 3 [37].", + "texts": [ + " The desired modes are excited by direct coupling using sets of gap sources in the open slots. Any modification of the initial structure changes the modal decomposition. Therefore, the modes do not remain the same when the structure is modified from its initial shape. In [37], CMA enables to use of a symmetric conductor as a multiport MIMO antenna using a mode-decoupling network (MDN). The proposed designs are shown in Fig. 48. In the first design step, CMA is performed on the bug-like conductor to find the available set of modes operating within the 2.4 GHz band. Fig. 49 examines the current distribution and radiation pattern for the first three dominant CMs, with a modal significance of 0.98, 0.92, and 0.38 at 2.4 GHz, respectively. Two options are chosen to excite the CMs of the MIMO antenna: one employs ICE, and the other uses capacitive coupling elements (CCE). CCE requires additional components, whereas ICE excitation uses additional slots on the structure. For this reason, ICE has been chosen to be studied. The last two steps involve the excitation of the 98850 VOLUME 9, 2021 first three modes and the design of the matching and feeding networks, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.23-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.23-1.png", + "caption": "Figure 2.23 : Configuration of a disk rotating at \ud835\udf14 and facing stationary one with impinging jet [62].", + "texts": [ + " Air Jet Impingement on Rotating Disk The adequate cooling of the rotor end-disks will enhance the reduction of rotor temperature. Hamdan et al. [62] reviewed the case of the geometry of a rotating disk facing a stationary one, with an air jet. They focused on the case where a confined (closed surrounding space) round jet impinged onto the rotating disk from the center of the stationary one, at a flow rate \ud835\udc5e\ud835\udc57 and through a diameter \ud835\udc37\ud835\udc57 , which is expected to improve the heat transfer process. Since the same fluid is impinged through the cavity then this is a submerged jet (Figure 2.23). They found that only few groups of researchers focused on the study of the rotating disk with jet impingement. In [123], the authors studied experimentally shrouded parallel disks with both rotation and coolant through-flow and visualized the flow and the heat transfer for the different values of the following parameters: \ud835\udc3a\ud835\udc5f, \ud835\udc45\ud835\udc52\ud835\udf14 and \ud835\udc36\ud835\udc64 = \ud835\udc5e\ud835\udc57/(\ud835\udf08\ud835\udc57 \ud835\udc5f\ud835\udc51) (flow rate coefficient) in Table 2.9. Nusselt number is found to be increasing with the rotation rate as well as with the flow-rate but decreasing with \ud835\udc3a\ud835\udc50" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004576__AME_2009_132087.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004576__AME_2009_132087.pdf-Figure5-1.png", + "caption": "Fig. 5. A-frame divided into three beams which were divided into rfes and sdes", + "texts": [ + "2, J0 is polar moment of inertia of a cross section, J2, J3 are second area moments of inertia of a cross-section with respect to axis x2 and x3. More information, also for other shapes of cross-section e. g. open pro- files, can be found in [15] and [11]. In our previous works [5] and [8], at first three beams were distinguished (right-1, top-2, left-3) in the frame. Thus, the subsystems modelled have been treated as rectilinear beams with constant or variable cross section. Then, each beam was divided into rigid finite elements and spring-damping elements, Fig. 5. This necessitates taking into account the reaction forces and moments at points BL and BR, and increases the number of constraint equations. This approach is described in [5]. In this paper, we present a different approach. The frame is treated as one beam, which is divided into rfes and sdes. The obtained chain of rfes and sdes is presented in Fig. 6. The position of each rfe of the undeformed beam is defined by the coordinate system E{i} with respect to the coordinate system {0} of rfe 0, by a transformation matrix with constant components: 0 ETi = 0 E\u0398i 0 Esi 0 1 , (8) where 0 E\u0398i is the matrix of cosines of the system E{i} with respect to {0}, and 0 Esi is the vector of coordinates of the origin of the system E{i} in {0} (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003047_article_25864285.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003047_article_25864285.pdf-Figure1-1.png", + "caption": "Fig. 1. Cross-section of a HEM", + "texts": [ + " [4] studied on the rule that the pre-load, the vibration amplitude and vibration frequency affect the dynamic characteristics of HDM and its rubber spring by measurement on the static and dynamic mechanical characteristics of inertia track HDM with fixed decoupler, inertia track HDM with floating decoupler and its rubber spring. In the design and study of HEM, it is important to confirm the dynamic vibration characters of the HEM. A lumped model of a hydraulic engine mount based on parameters of the upper and bottom chamber, the rubber spring, the inertia track and the decoupler was established in this study. A method to identify the lumped parameters in model was also proposed. This paper focus on experimental study on an inertia track HEM with fixed decoupler illustrated in Fig. 1. In this kind of HEM, the rubber spring supports the engine and acts as a piston, the mount is divided into upper and bottom chamber and liquid can flow in the upper and bottom chamber through the annular inertia track in middle plate. When the upper end of HEM is drove by low-frequency and high-amplitude displacement, the liquid can flow in the upper and bottom chamber through the inertia \u00a9 2016. The authors - Published by Atlantis Press 209 track and HEM dissipates vibration energy by the flow of liquid", + " The principal physical effects are taken to be those associated with the primary rubber including dynamic stiffness and damping, bulge stiffness, piston area and with the inertia track including fluid inertia and damping [3]. The stiffness of the secondary rubber is small enough that it can be ignored for reducing the requisite state dimension by one. The fluid is assumed incompressible for the bulge compliance of the primary rubber is much greater and the fluid inertia and damping in the upper chamber are ignored for inertia and damping in the track is much greater. Considering the HEM in Fig.1 at large amplitude drive, the LP model for this HEM is shown in Fig. 2. The rubber spring is simplified as one degree of freedom (DOF), and its dynamic stiffness and damping property are described by Kr and Br, respectively. The rubber spring also functions as a piston with an effective area Ap. Finally, the rubber spring adds volumetric compliance to the model, represented by C1. The reciprocal of the C1 is defined as the volumetric stiffness of the upper chamber and is represented by Kb. The bulge stiffness of the upper chamber is defined as Where \u2206V1 is the volume change of the upper chamber which due to the pressure change of the upper chamber, \u2206P1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004695_oradea2018_02004.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004695_oradea2018_02004.pdf-Figure13-1.png", + "caption": "Fig. 13. The displacement distribution", + "texts": [ + " On the elements found in contact there was made a finer meshing, meaning it had more layers of finite elements and nodes in order to have a better convergence of the results and contact from that area. After meshing there were obtained 16234 finite elements and 67696 modes. For this model there are shown two calculation cases, as follows: case 1: guide material PA46, F=5 N and \u03bc=0.28; case 2: guide material PA66, F=5 N and \u03bc=0.28; The method of applying the force is presented in figure 12 being identical for both analyzed cases. For load case 1, of this model, the obtained value of maximum displacement is 0.0005 mm, figure 13 a. If it is made a detailed value on the guide it is observed that the guide is deformed locally and only on the contact zone between the guide and bolt. In figure 13 b, it is shown the guide deformation at a scale 1:1, and in figure 13 c, it is shown the guide deformation at an enlarged scale by 3000 times, only for visualization. The distribution of the contact pressure between guide and bolt, in this case, it is shown in figure 14 and has an uniform distribution with higher values towards the interior of the bolt, the maximum value of the contact pressure being 0.54 MPa. The maximum contact pressure between bolt and sprocket is 4.57 MPa being distributes uniformly on the tangent line between the bolt and the sprocket generator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003506_8355919_08355939.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003506_8355919_08355939.pdf-Figure3-1.png", + "caption": "Fig. 3 Coordinates transform in dual quaternion", + "texts": [ + " Multiplication q\u0302a \u25e6 q\u0302b = qa \u25e6 qb + \u03b5(qa \u25e6 q\u2032 b + q\u2032 a \u25e6 qb) = (q\u0302s1q\u0302s2 \u2212 q\u0302v1 \u00b7 q\u0302v2) + (q\u0302s1q\u0302v2 + q\u0302s2qv1 + q\u0302v1 \u00d7 q\u0302v2) Conjunction q\u0302\u2217 = q\u2217 + \u03b5(q\u2032)\u2217 = q\u0302s \u2212 q\u0302v (q\u0302a \u25e6 q\u0302b)\u2217 = q\u0302\u2217 b \u25e6 q\u0302\u2217 a Norm \u2016q\u0302\u20162 = q\u0302\u2217 \u25e6 q\u0302 = q\u0302 \u25e6 q\u0302\u2217 = (q + \u03b5q\u2032) \u25e6 (q\u2217 + \u03b5q\u2032\u2217) = q \u00b7 q + \u03b52q \u00b7 q\u2032 = (q\u0302s + q\u0302v) \u25e6 (q\u0302s \u2212 q\u0302v) = q\u0302sq\u0302s + q\u0302v \u00b7 q\u0302v \u2208 Hs d (16) If \u2016q\u0302\u20162 = 1 + \u03b50 = 1\u0302, q\u0302 is called unit dual quaternion, which satisfies q\u0302\u2217 = q\u0302\u22121. Similar to quaternion, multiplication of dual quaternion can be expressed in matrix form as p\u0302 \u25e6 q\u0302 = [ p p\u2032 ] \u25e6 [ q q\u2032 ] = (p\u0302)+q\u0302 = (q\u0302)\u2212p\u0302 (17) (p\u0302)+ = [ (p)+ 0 (p\u2032)+ (p)+ ] , (q\u0302)\u2212 = [ (q)\u2212 0 (q)\u2212 (q)\u2212 ] . As for arbitrary three dual quaternions p\u0302, q\u0302, r\u0302, their multiplication satisfies p\u0302 \u25e6 q\u0302 \u25e6 r\u0302 = (p\u0302)+(r\u0302)\u2212q\u0302 = (r\u0302)\u2212(p\u0302)+q\u0302. (18) As Fig. 3 shows, describe the screw motion of the space rigid body by the motion of the coordinate. Coordinate A firstly rotates \u03a6 around screw axis L\u0302, then shifts d along L\u0302 and finally becomes coordinateB. 370 Journal of Systems Engineering and Electronics Vol. 29, No. 2, April 2018 According to geometric meaning, this screw motion can be expressed by dual quaternion which is defined as q\u0302 = [ cos(\u03a6\u0302/2) L\u0302 sin(\u03a6\u0302/2) ] (19) where \u03a6\u0302 = \u03a6 + \u03b5d and L\u0302 = l0 + \u03b5(p \u00d7 l0) are the dual angle and the screw axis" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004354_129_8_129_8_549__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004354_129_8_129_8_549__pdf-Figure8-1.png", + "caption": "Fig. 8. Photograph of trial made 3dB coupler with the step impedance of n=(3).", + "texts": [], + "surrounding_texts": [ + "552 IEEJ Trans. FM, Vol.129, No.8, 2009\n\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u7d50\u5408\u578b\u30de\u30a4\u30af\u30ed\u30b9\u30c8\u30ea\u30c3\u30d7\u7dda\u8def\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\u3002 \u3044\u307e\u6bd4\u8a98\u96fb\u7387 \u03b5r\u3092\u6301\u3064\u5e45 h \u306e\u8a98\u96fb\u4f53\u57fa\u677f\u306e\u8868\u9762\u306b\uff0c\u5e45 W1 \u306e\u30de\u30a4\u30af\u30ed\u30b9\u30c8\u30ea\u30c3\u30d7\u7dda\u8def\u3092 2 \u500b\uff0c\u63a5\u5730\u677f\u3092\u5171\u6709\u3059\u308b\u3088\u3046\n\u306b\u69cb\u6210\u3059\u308b\u3002\u3053\u308c\u3089 2 \u500b\u306e\u30de\u30a4\u30af\u30ed\u30b9\u30c8\u30ea\u30c3\u30d7\u7dda\u8def\u304c\u7d50\u5408\n\u3059\u308b\u3088\u3046\u306b\u56f3 5 \u306e\u65ad\u9762\u306b\u793a\u3059\u3088\u3046\u306b\u63a5\u5730\u677f\u306b\u5e45 W2\u306e\u30a2\u30d1\u30fc\n\u30c1\u30e3\u30fc\u304c\u3042\u3051\u3089\u308c\u308b\u3002\u3053\u306e\u3088\u3046\u306a\u69cb\u9020\u306f\u53e4\u304f\u304b\u3089\u7528\u3044\u3089\u308c \u3066\u304a\u308a(7)\uff0c\u7d50\u5408\u91cf\u306e\u89e3\u6790\u3084(8)\uff0c\u7dda\u8def\u5b9a\u6570\u3092\u6709\u9650\u8981\u7d20\u6cd5\u3067\u6c42\u3081 \u3066\u65b9\u5411\u6027\u7d50\u5408\u5668\u306e\u8a2d\u8a08\u304c\u306a\u3055\u308c\u3066\u3044\u308b(9)\u3002\u306a\u304a\u3053\u306e\u65b9\u6cd5\u306f\u5e83 \u5e2f\u57df\u30d5\u30a3\u30eb\u30bf\u30fc\u306b\u3082\u5fdc\u7528\u3055\u308c\u3066\u3044\u308b(10)\u3002 \u3053\u306e\u69cb\u9020\u3067\u306f\uff0c\u5947\u30e2\u30fc\u30c9\u3067\u306f\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u90e8\u5206\u306f\u63a5\u5730\u677f\n\u3068\u540c\u3058\u96fb\u4f4d\u306b\u306a\u308b\u306e\u3067\uff0c\u4f4d\u76f8\u901f\u5ea6 vod\u3084\u7279\u6027\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9 Zod\u306f W2\u306b\u5f71\u97ff\u3055\u308c\u306a\u3044\u304c\uff0c\u5076\u30e2\u30fc\u30c9\u4f4d\u76f8\u901f\u5ea6 vev\u3084\u7279\u6027\u30a4 \u30f3\u30d4\u30fc\u30c0\u30f3\u30b9 Zev \u306f W2 \u306e\u5897\u52a0\u3068\u3068\u3082\u306b\u5897\u52a0\u3059\u308b\u3002\u672c\u8ad6\u6587\u3067 \u306f\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u306e\u5e45 W2\u3092\u56f3 6 \u306e\u5982\u304f\u5927\u5c0f\u3092\u7e70\u308a\u8fd4\u3059\u3053\u3068\u306b \u3088\u308a\uff0cZev\u304c\u56f3 4 \u3092\u6e80\u305f\u3059\u3088\u3046\u306a\u5024\u3067\u5927\u5c0f\u306b\u7e70\u308a\u8fd4\u3057\uff0c\u4e14\u3064 \u30b9\u30ed\u30c3\u30c8\u9577\u3092 / 4od\u03bb \u306b\u3059\u308b\u3053\u3068\u3067\u30a2\u30a4\u30bd\u30ec\u30fc\u30b7\u30e7\u30f3\u3068\u6574\u5408 \u3092\u5e83\u5e2f\u57df\u306b\u3057\u3088\u3046\u3068\u3059\u308b\u3082\u306e\u3067\u3042\u308b\u3002\u3059\u306a\u308f\u3061\u56f3 6 \u3067 2 'W \u306e \u5e45\u306e\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u306f\uff0c\u56f3 4 \u306e Z1\u306e\u5076\u30e2\u30fc\u30c9\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9 \u3092\u4e0e\u3048\u308b\u3082\u306e\u3067\uff0c 2 \"W \u306e\u5e45\u306e\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u306f Z2 \u306e\u5076\u30e2\u30fc\u30c9\n\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3092\u4e0e\u3048\u308b\u3082\u306e\u3067\u3042\u308b\u3002\u307e\u305f\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u90e8 \u5206\u306e\u9577\u3055 'l \u306f\u6b21\u306e(14)\u5f0f\u3067\u4e0e\u3048\u3089\u308c\u308b\u3002\n0\n, ' 4 r od l \u03bb \u03c0 \u03b5 = (n\u30fb\u6bb5\u6570\uff0c\u03bb0\uff1a\u81ea\u7531\u7a7a\u9593\u6ce2\u9577) ...(14)\n\u4e0a\u8a18\u306e\u3088\u3046\u306b\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u5e45\u3092\u5909\u3048\u3066\u3082\u5f53\u7136\u5947\u30e2\u30fc\u30c9\u306b\u306f\n\u95a2\u4fc2\u304c\u306a\u304f\uff0c\u5076\u30e2\u30fc\u30c9\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u306e\u307f\u304c\u5909\u5316\u3067\u304d\u308b\u70b9\n(a)\n(b) n=5\n(c) n=6\n\u56f3 3 ,r od\u03b5 =1.9, ,r od\u03b5 =1.37 \u306e 3dB \u65b9\u5411\u6027\u7d50\u5408\u5668\u3067\uff0c Wev=120.914[\u03a9], Wod=20.676[\u03a9]\u306e\u5834\u5408(a), Wev\u3092 Z1 =180[\u03a9]\u3068 Z2=81[\u03a9]\u3068\u306e\u30b9\u30c6\u30c3\u30d7\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3067 \u69cb\u6210\u3057\u305f n=5 \u306e\u5834\u5408(b)\uff0c\u53ca\u3073 Wev \u3092 Z1=217.64[\u03a9] \u3068 Z2=61.14[\u03a9]\u3068\u306e\u30b9\u30c6\u30c3\u30d7\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3067\n\u69cb\u6210\u3057\u305f n=6 \u306e\u5834\u5408(c)\u306e\u7279\u6027 Fig. 3. Performance of 3dB coupler of ,r od\u03b5 =1.9 and ,r ev\u03b5 =1.37 in the case of Wev=120.914[\u03a9], Wod=20.676[\u03a9] (a), in the case of the step impedances of Z1=217.64[\u03a9] and Z2=81[\u03a9] for n=5 (b) and Z1=217.64[\u03a9] and Z2=61.4[\u03a9] for n=6 (c).", + "\u5bfe\u79f0\u5bc6\u7d50\u5408\u7dda\u8def\u306e\u8a2d\u8a08\n\u96fb\u5b66\u8ad6 A\uff0c129 \u5dfb 8 \u53f7\uff0c2009 \u5e74 553\n\u304c\u4fbf\u5229\u3067\u3042\u308b\u3002\u3053\u306e\u969b\uff0cvev \u3082\u5f53\u7136\u5909\u5316\u3059\u308b\u304c\uff0c\u305d\u306e\u5909\u5316\u7387 \u306f Zev\u306e\u5909\u5316\u304c\u7d04 2.6 \u500d\u5909\u5316\u3057\u3066\u3082 vev \u306e\u5909\u5316\u306f 1.15 \u500d\u3067\u5c11\n\u306a\u304f\uff08\u56f3 7 \u53c2\u7167\uff09\uff0c\u3053\u306e\u305a\u308c\u306b\u4f34\u3063\u3066\u3082 S11\u53ca\u3073 S41\u306f\uff0d20dB \u4ee5\u4e0b\u306b\u4fdd\u305f\u308c\u308b\u3053\u3068\u304c\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u3067\u78ba\u8a8d\u3055\u308c\u308b\u3002 \u3055\u3066\u3053\u308c\u3089\u306e\u30b9\u30c6\u30c3\u30d7\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3092\u56f3 6 \u306e\u69cb\u9020\u3067\u5b9f\n\u73fe\u3059\u308b\u5834\u5408\uff0c\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u306e\u69cb\u9020\u306b\u4e0d\u9023\u7d9a\u90e8\u304c\u751f\u3058\u3053\u308c\u306b\n\u57fa\u3065\u3044\u3066\u767a\u751f\u3059\u308b\u30a8\u30d0\u30cd\u30bb\u30f3\u30c8\u306a H \u6ce2\u306b\u3088\u308b\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\n\u30b9\u304c\u751f\u3058\u308b\u3002n \u304c\u5947\u6570\u306e\u5834\u5408\u306b\u306f\u5165\u51fa\u529b\u5bfe\u79f0\u3067\u3042\u308b\u305f\u3081\uff0c\u5165\n\u51fa\u529b\u306e\u4e0d\u9023\u7d9a\u52b9\u679c\u304c\u5165\u51fa\u529b\u9593\u306e\u96fb\u6c17\u89d2 \u03c0/2 \u306b\u3088\u308a\u6253\u3061\u6d88\u3055\n\u308c\u308b\u305f\u3081\u597d\u307e\u3057\u3044\u304c\uff0cn \u304c\u5076\u6570\u306e\u6642\u306f\u6253\u3061\u6d88\u3055\u308c\u306a\u3044\u3002\u5f93\u3063\n\u3066 n\u300b10 \u306e\u5834\u5408\u4ee5\u5916\u306f n \u304c\u5947\u6570\u3067\u3042\u308b\u3053\u3068\u304c\u597d\u307e\u3057\u3044\u3002 \u6b21\u306b\u30b9\u30c6\u30c3\u30d7\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3092\u7528\u3044\u305f\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u7d50\u5408\n\u306e\u30de\u30a4\u30af\u30ed\u30b9\u30c8\u30ea\u30c3\u30d7\u65b9\u5411\u6027\u7d50\u5408\u5668\u306e\u7279\u6027\u3092\u8ff0\u3079\u308b\u30023dB \u65b9\u5411\u6027\u7d50\u5408\u5668\u3067\u306f Wod = 20.676[\u03a9] \u3067\u3042\u308b\u304b\u3089\uff0c\u56f3 5 \u3067 h = 0.5[mm], \u03b5r = 2.17 \u3068\u3059\u308b\u3068\uff0cW1 = 4.945[mm] \u3068\u306a\u308b\u3002\u3044\u307e \u56f3 4 \u3067 n=5 \u306e\u5834\u5408\u306b\u306f\uff0cZ1 = 180[\u03a9], Z2 = 81[\u03a9] \u3068\u306a\u308a\uff0c\u3053 \u308c\u3089\u306b\u76f8\u5f53\u3059\u308b\u56f3 6 \u306e 2 'W \uff0c\u3068 2 \"W \u3092\u5f62\u72b6\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\n\u3067\u6c42\u3081\u308b\u3068\uff0c\u305d\u308c\u305e\u308c\u306b\u5bfe\u5fdc\u3057\u305f\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u5e45\u306f\uff0c\n[ ] [ ] [ ] [ ] ' 2 1 '' 2 2 ( 180 ) 8.7 mm ( 81 ) 5.2 mm W Z W Z = \u2126 = = \u2126 =\n\u306b\u306a\u308b\u3002\u307e\u305f\u3053\u306e\u6570\u5024\u3092\u7528\u3044\u305f\u56f3 5 \u306e\u30a2\u30d1\u30fc\u30c1\u30e3\u30d1\u30bf\u30fc\u30f3\n\u56f3 6 \u5076\u30e2\u30fc\u30c9\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3092\u5927\u5c0f\u4ea4\u4e92\u306b\n\u5909\u3048\u308b\u305f\u3081\u306e\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u69cb\u9020\n\u56f3 7 \u5947\u30e2\u30fc\u30c9\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9 20.67\u03a9\uff0c\u57fa\u76e4\u306e\u539a\u307f 0.5 mm \u306e\u3068\u304d\u306e W2\u306b\u3088\u308b (a) \u5076\u30e2\u30fc\u30c9\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9 \u3068\uff0c(b) \u5076\u30e2\u30fc\u30c9\u53ca\u3073\u5947\u30e2\u30fc\u30c9\u5b9f\u52b9\u6bd4\u8a98\u96fb\u7387\u306e\u5024\nFig. 7. Odd mode impedance (a) even mode and odd mode effective dielectric constant (b) for the substrate with 0.5 mm thick.", + "554 IEEJ Trans. FM, Vol.129, No.8, 2009\n\u3092\u7528\u3044\u56f35\u306e\u65ad\u9762\u69cb\u9020\u3092\u3082\u3064\u69cb\u9020\u306e\u7279\u6027\u3092HFSS\u306b\u3088\u308a\u89e3\u6790\n\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u3092\u884c\u3063\u305f\u7d50\u679c\uff0c\u4e2d\u5fc3\u5468\u6ce2\u6570 1[GHz] \u3067 S11, S21, S41\u3068\u3082\u306b 0 \uff5e 2.5[GHz] \u307e\u3067\uff0d23dB \u4ee5\u4e0b\uff0c2.5[GHz] \u4ee5 \u4e0a\u3067\uff0d20dB \u4ee5\u4e0b\u306e\u826f\u597d\u306a\u7d50\u679c\u304c\u5f97\u3089\u308c\u305f\u3002\u306a\u304a\u30a2\u30d1\u30fc\u30c1\u30e3\n\u30fc\u5e45\u3092\u5909\u3048\u305f\u6642\u306e\u5076\u30e2\u30fc\u30c9\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3068\u5b9f\u52b9\u6bd4\u8a98\u96fb\u7387\n\u306e\u5024\u306e\u8a08\u7b97\u4f8b\u3092\u56f3 7 \u306b\u793a\u3057\u3066\u304a\u304f\uff08\u8a08\u7b97\u306b\u306f Q3D (2D EXTRACTOR), HFSS \u3092\u4f7f\u7528\uff09\u3002 \u30083\uff653\u3009 \u8a66\u4f5c\u3068\u5b9f\u9a13\u7d50\u679c n=3 \u306e\u5834\u5408\u3092\u56f3 3 \u306e Z1\u3068 Z2 \u3068\u3092\u7528\u3044\u3066\u8a66\u4f5c\u3057\u305f\u3002\u8a66\u4f5c\u306e\u5199\u771f\u3092\u56f3 8 \u306b\u793a\u3059\u3002Z1\u3068 Z2\u306e \u90e8\u5206\u306e\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u5e45\u306f\uff0ch=0.5[mm] \u03b5r=2.17 \u306e\u57fa\u677f\u306e\u3068\u304d \u305d\u308c\u305e\u308c 8.2[mm] \u53ca\u3073 5.7[mm] \u3068\u306a\u308a\uff0c\u5c1a\u5165\u51fa\u529b\u30a2\u30d1\u30fc\u30c1\n\u30e3\u30fc\u306e\u4e0d\u9023\u7d9a\u90e8\u306b\u7b49\u4fa1\u7684\u306b\u5165\u308b\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\u306e\u5f71\u97ff\u3092\u5c11\n\u306a\u304f\u3059\u308b\u305f\u3081\uff0c\u5165\u51fa\u529b\u306e\u30a2\u30d1\u30fc\u30c1\u30e3\u9577\u3092\u50c5\u304b\u77ed\u304f\u3057\u3066\u5165\u51fa\n\u529b\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u90e8\u306e\u96fb\u6c17\u9577\u3092\u8abf\u6574\u3057\u305f\uff0e\u5b9f\u9a13\u7d50\u679c\u306f\u56f3\n9(a),(b)\u306e\u826f\u597d\u306a\u7279\u6027\u3092\u5f97\u305f\u3002\n4. \u7d50 \u8ad6\n\u672c\u8ad6\u6587\u3067\u306f\uff0c\u5076\u30e2\u30fc\u30c9\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u306b\u5927\u5c0f\u4ea4\u4e92\u306e\u30b9\u30c6\n\u30c3\u30d7\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3092\u7528\u3044\u308b\u65b9\u6cd5\u306b\u3088\u308a\uff0c\u5076\u30e2\u30fc\u30c9\u3068\u5947\u30e2\n\u30fc\u30c9\u306e\u4f4d\u76f8\u901f\u5ea6\u3092\u4e00\u81f4\u3055\u305b\u308b\u65b9\u6cd5\u3092\u63d0\u6848\u3059\u308b\u3068\u3068\u3082\u306b\uff0c\u305d\n\u306e\u624b\u6cd5\u3092\u5e73\u9762\u56de\u8def\u3067\u3042\u308b 2 \u500b\u306e\u30de\u30a4\u30af\u30ed\u30b9\u30c8\u30ea\u30c3\u30d7\u7dda\u8def\u306b\n\u304a\u3051\u308b\u30a2\u30d1\u30fc\u30c1\u30e3\u30fc\u7d50\u5408\u306e\u8a2d\u8a08\u306b\u304a\u3044\u3066\u9069\u7528\u3057\uff0c\u305d\u306e\u6709\u52b9\n\u6027\u3092\u793a\u3057\u305f\u3002 \u56de\u8def\u69cb\u6210\u306e\u89b3\u70b9\u304b\u3089\u7570\u306a\u308b\u4f4d\u76f8\u901f\u5ea6\u306e\u56fa\u6709\u30e2\u30fc\u30c9\u3092\u6301\u3064\n\u5bc6\u7d50\u5408\u7dda\u8def\u306e\u8a2d\u8a08\u6cd5\u3092\u8ff0\u3079\u305f\u304c\uff0c\u5b9f\u969b\u69cb\u9020\u3092\u5b9f\u73fe\u3059\u308b\u306b\u3042\n\u305f\u3063\u3066\uff0c\u4f8b\u3048\u3070\u30b9\u30c6\u30c3\u30d7\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u306e\u30b9\u30c6\u30c3\u30d7\u90e8\u5206\u306b\n\u306f\u30a8\u30d0\u30cd\u30bb\u30f3\u30c8\u6ce2\u767a\u751f\u306b\u4f34\u3046\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\u304c\uff0c\u308f\u305a\u304b\u3067\n\u306f\u3042\u308b\u304c\u751f\u3058\u308b\u306e\u3067\uff0c\u305d\u306e\u5f71\u97ff\u306e\u89e3\u6790\u3082\u5fc5\u8981\u3067\u3042\u308b\u3002\u3053\u308c\n\u3092\u78ba\u304b\u3081\u308b\u305f\u3081\u306e 3 \u6b21\u5143\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u3082\u884c\u3044\uff0c\u307b\u307c\u6e80\n\u8db3\u3067\u304d\u308b\u7279\u6027\u306f\u5f97\u305f\u304c\uff0c\u66f4\u306a\u308b\u8a73\u7d30\u306a\u691c\u8a0e\u304c\u5fc5\u8981\u3067\u3042\u308d\u3046\u3002 \u8b1d \u8f9e \u672c\u8ad6\u6587\u3092\u307e\u3068\u3081\u308b\u306b\u5f53\u305f\u308a\u3054\u5354\u529b\u3044\u305f\u3060\u3044\u305f\u6771\u4eac\u5de5\u82b8\u5927\n\u5b66\u5de5\u5b66\u90e8\u661f\u967d\u4e00\u6559\u6388\uff0c\u306a\u3089\u3073\u306b\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u3054\u5354\u529b\n\u3044\u305f\u3060\u3044\u305f\u30a2\u30f3\u30bd\u30d5\u30c8\u30b8\u30e3\u30d1\u30f3\uff08\u682a\uff09\u306e\u9234\u6728\u8aa0\u6c0f\uff0c\uff08\u6709\uff09EM \u30c6\u30af\u30ce\u30ed\u30b8\u30fc\u306e\u85ae\u5185\u5e83\u4e00\u6c0f\u306b\u8b1d\u610f\u3092\u8868\u3059\u308b\u3002 \uff08\u5e73\u6210 21 \u5e74 1 \u6708 9 \u65e5\u53d7\u4ed8\uff0c\u5e73\u6210 21 \u5e74 3 \u6708 18 \u65e5\u518d\u53d7\u4ed8\uff09\n\u6587 \u732e\n(\uff11) \u5c0f\u897f\u826f\u5f18\uff1a\u5b9f\u7528\u30de\u30a4\u30af\u30ed\u6ce2\u8a2d\u8a08\u30de\u30cb\u30e5\u30a2\u30eb\uff0c\u30b1\u30a4\u30e9\u30dc\u51fa\u7248\u767a\u884c (\uff12) \u5c0f\u897f\u826f\u5f18\uff1a\u9ad8\u5468\u6ce2\u30fb\u30de\u30a4\u30af\u30ed\u6ce2\u30d5\u30a3\u30eb\u30bf\u30fc\u3068\u5fdc\u7528\uff0c\u30b1\u30a4\u30e9\u30dc\u51fa\u7248\n(2007) (\uff13) K. C. Wolters, P. L. Clar, and C. W. Stiles : \u201cAnalysis and Experimental\nEvaluation of Disributer Overlay Structures in Microwave Integrated Circuit\u201d, MTT International Microwave Symposium, pp.123-130 (1968) (\uff14) R. S. Mongia : RF of Microwave Coupled Line Circuits, pp.415-445, Artech House (1999) (\uff15) F. C. de Ronde : Wide-Band High Directivity in MIC Proximity Couplers by Planar Means, IEEE MIT-S Int. Microwave Symp. Digest, pp.480-482 (1980) (\uff16) \u5c0f\u897f\u826f\u5f18\uff1a\u300c\u5bb9\u91cf\u8ca0\u8377\u5f62 VIP\uff08\u7e26\u5f62\u5e73\u9762\u56de\u8def\uff09\u3092\u7528\u3044\u305f\u65b9\u5411\u6027\u7d50\u5408\u5668\u300d\uff0c\n\u8f3b\u5c04\u79d1\u5b66\u7814\u7a76\u4f1a, RS07-16 (2008-3) (\uff17) D. M. Pozar : Microwave Engineering, p.364, John Wiley of Sons, Inc. (\uff18) N. Herscoviei and D. M. Pozar : \u201cFull-wave Analysis of Aperture-Coupled\nMicrostrip Lines\u201d, IEEE Trans. Microwave Theory Tech., Vol.39, pp.1108-1114 (1991-7) (\uff19) T. Tanaka, K. Tsunoda, and M. Aikawa : \u201cSlot-Coupled Directional Couplers Between Double-Sided Substrate Microstrip Lines and Their Applications\u201d, IEEE Trans. Microwave Theory Tech., Vol.36, pp.1752-1757 (1988-12) (10) L. Zhu and K. Wu : \u201cUltrabroad-Band Vertical Transition for Multilayer Integrated Circuits\u201d, IEEE Microwave & Guide Wave Lett., Vol.9 (1999-11) (11) \u5c0f\u897f\u826f\u5f18\uff1a\u5b9f\u7528\u30de\u30a4\u30af\u30ed\u6ce2\u6280\u8853\u8b1b\u5ea7 \u7b2c 2 \u5dfb, pp.217-218, \u30b1\u30a4\u30e9\u30dc\n\u51fa\u7248\u767a\u884c (12) (\uff11)\u306e pp.276-278\n\u5c0f \u897f \u826f \u5f18 \uff08\u6b63\u54e1\uff09 1928 \u5e74 9 \u6708 24 \u65e5\u751f\u30021951 \u5e74 3 \u6708\u4eac\u90fd\n\u5927\u5b66\u5352\u696d\u3002\u540c\u5e74\u65e5\u672c\u653e\u9001\u5354\u4f1a\u5165\u793e\u30021962 \u5e74\u7c73\u56fd \u30d6\u30eb\u30c3\u30af\u30ea\u30f3\u5de5\u79d1\u5927\u5b66\u5ba2\u54e1\u7814\u7a76\u54e1\u30021984 \u5e74\u30e6\u30cb \u30c7\u30f3\u526f\u793e\u9577\u30021994 \u5e74\u6771\u4eac\u5de5\u82b8\u5927\u5b66\u5de5\u5b66\u90e8\u6559\u6388\u3002\n\u73fe\u5728\uff0c\uff08\u682a)\u30b1\u30a4\u30e9\u30dc\u30e9\u30c8\u30ea\u30fc\u53d6\u7de0\u5f79\u3002\u8457\u66f8\uff1a Microwave Integrated Circuits (Marcel Dekker), Microwave Electronic Circuit Technology (Marcel Dekker), \u5b9f\u7528\u30de\u30a4\u30af\u30ed\u6ce2\u6280\u8853\u8b1b\u5ea7\u5f1f 1 \u5dfb\u20157 \u5dfb\n\uff08CQ \u51fa\u7248\uff09\uff0c\u4ed6\u591a\u6570\u30021982 \u5e74\u7d2b\u7dac\u8912\u7ae0\u6388\u4e0e\u30021994 \u5e74 IEEE \u30de\u30a4\u30af\u30ed\n\u6ce2 Career Award \u53d7\u8cde\u30021981 \u5e74 IEEE Fellow, \u73fe\u5728 Life Fellow\u3002" + ] + }, + { + "image_filename": "designv8_17_0001048_e_download_7701_4905-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001048_e_download_7701_4905-Figure1-1.png", + "caption": "Fig. 1. Device design", + "texts": [ + " This device used an Arduino microcontroller board equipped with a flow sensor. It was Prisma Megantoro, Validation Method for Digital Flow Meter for Fuel Vendors limited to error values, uncertainties, and corrections from the devices. II. METHOD The method used in carrying out research was planning, conducting, checking, and evaluating. Underlining it, the research involved literature reviews, device and material preparation, design, hardware manufacture, programming, testing, and data analysis. Figure 1 shows the tube used as a part of the device. It has the specifications of 12L volume, 25cm height, 25cm diameter, and 1.1 mm thickness. The material is aluminum. A microcontroller is used for processing media performance, a solenoid valve for controlling the flow of fuel oil, and a flow sensor for detecting or measuring the flow of fuel oil. a. Hardware design Figure 2 illustrates the Arduino Mega [21] - [23] board connected to the Pins used. The pins are the LCD Pin, Keypad Pin, Relay Pin, and Sensor Flow Pin" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001456_18_ms-9-327-2018.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001456_18_ms-9-327-2018.pdf-Figure9-1.png", + "caption": "Figure 9. (a) PRBM of the curved beam, and (b) initially curved wiper pressing arm.", + "texts": [ + "3) that is suitable for the windscreen used in this study, the required pressing force is Ft = 70(0.22)= 15.4N. (10) In conventional wipers, pressing force is generated by a helical spring. As in this study, the wiper pressing force is obtained by the curved segment as described in Sect. 1; radius of curvature and cross section of the beam should be determined. The wiper pressing force, Ft, which is generated by the curved beam, is the required force, and an iterative solution method is applied. The wiper pressing arm is normally at rest in a horizontal position, as shown in Fig. 9. In this horizontal position, the wiper pressing arm should apply a constant Ft perpendicular to the windscreen. The PRBM of the curved beam is shown in Fig. 9a. The torsional spring, with a spring constant K , provides the required pressing force, determined by the value of 2i . FtLv\u03b3 \u2217 =K2i (11) www.mech-sci.net/9/327/2018/ Mech. Sci., 9, 327\u2013336, 2018 As can be seen from Fig. 9a, Eq. (11) defines the moment equilibrium between wiper pressing force Ft and torsion from the torsional spring, about the pivot point. The torsional spring constant is defined as (Howell, 2001) K = \u03c1K2 EI Lv , (12) and the radius of curvature, Ri , can be determined as Ri = Lv \u03ba0 , (13) where E is the modulus of elasticity of steel; I is the moment of inertia of the beam; K2 is the stiffness coefficient; Lv is the wiper pressing arm length (where the beam is initially straight) that was determined as 320 mm in Sect" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001549_tation-pdf-url_35276-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001549_tation-pdf-url_35276-Figure2-1.png", + "caption": "Fig. 2. Normal section of the rack cutter with asymmetric teeth (Fetvaci, 2011; Yang, 2005)", + "texts": [ + " As a result, Section 5 deals with computer simulation of the generating process for the verification and the validation of the matematical models. Simulated motion path of the cutter during generation process is also illustrated. The varieties of the cutter tip geometry are investigated. Finally, a conclusive summary of this study is given in Section 6. For simplicity, the generation of spur gears with shaper cutters can be simplified into a twodimensional problem. Due to the asymmetry of the rack cutter, left and right sides of the cutter are considered seperately. Figure 2. presents the design of the normal section of a rack cutter n , where regions ac and bd are the left- and right-side top lands, regions ce and df are the left- and right-side fillets and, regions eg and fh are the left- and right-side working regions. The regions ac and bd are used to generate the bottomland of asymmetric spur gear and al and bl represent design parameters of normal section of the rack cutter. In order to generate complete profile of the rack cutter surface a tooth of rack cutter will be repeated for ,", + " The side with a higher pressure angle has a lower radius of rounding and a lower clearance. The tooth semi-thicknesses at pitch line of the cutter are different from each other. Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 2.01 and right side radius of rounding m 3.02 . Figure 8 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. As illustrated in Fig. 2. and classifed type-1b in Table 1, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The tooth semi-thicknesses at pitch line of the cutter are same. This type of cutter is adopted from the standard generating rack to asymmetric gearing. The relation ship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 38" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003315__Issue1-15_paper.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003315__Issue1-15_paper.pdf-Figure1-1.png", + "caption": "Fig. 1. Scheme of frictional joint with the resistance wedge", + "texts": [ + " In these models friction forces between the cooperating sections was taken into account, what allowed to model the yield capacity of the frictional joint. External loading was assumed in a form of complex exponential function. Mathematical model was subjected to numerical analysis, whose results was also presented in the work. The aim of application of the resistance wedge in the frictional joint is to increase the resistances related to the displacement of cooperating sections. These resistances are connected with the process of deformation of sections, stirrups, and wedge, which can undergo also the cutting process. In a Figure 1 scheme of the frictional joint with the resistance wedge is presented. In this joint the wedge is assembled between the cooperating sections, so as to fill the empty space between their bottoms. Geometrical parameters describing shape of the wedge and having significant influence on the operational characteristics of frictional joint with the wedge are: angle inclination of wedge\u2019s generatrix \u03b1, height of the wedge in its initial part h and length L (Fig. 1). It was assumed that the width of the resistance wedge will be equal to the width of internal section\u2019s bottom. Principle of operation of the frictional joint with the resistance wedge depends on the increase of the resistances to motion of upper section displacing during the yield, which is pressed against to the lower section in a result of stirrups\u2019 action (Fig. 1). Beginning of the increase of these resistances occurs at the moment of beginning of contact of upper section with the resistance wedge. In this case, to yield could occur, an increase of value of external force acting on the upper section is necessary. It results in an increase of the value of force transmitted through the frictional joint, i.e. load capacity of the frictional joint. Therefore application of the resistance wedge in the frictional joint causes that the resistances in the joint at which the yield can occur and resistances during the yield increase", + " To determine the influence of the resistance wedge on the operational characteristics of the frictional joint, operational characteristics of the frictional joints with and without the resistance wedge are presented in a Figure 3. In both joints values of initial axial forces in the bolts of stirrups were the same and amounted to 82,5\u00b12,5 kN in each bolt. Resistance wedge was made of the steel S235JR of inclination angle of generatrix (\u03b1) amounting to 6\u00b0, initial height (h) equal to the height of slit between the cooperating sections and length (L) equal to 0.2 m (Fig. 1). Analyzing obtained characteristics one can state, that for the frictional joint with the resistance wedge, the loading transmitted through it, increases with the displacement of section sliding down. Also drops of load capacity during the yield in joint, characteristic for the frictional joints without the resistance wedge, do not occur. The consequence of these drops are the great values of displacements (yields) in the frictional joint. Presence of the resistance wedge limits the possibility of occurrence of large drops of value of force transmitted through the frictional joint (its load capacity) during the occurrence of a yield, what causes that sudden yields in the frictional joint do not occur" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003971__2462_context_theses-Figure4-9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003971__2462_context_theses-Figure4-9-1.png", + "caption": "Figure 4-9: Backlash at gear teeth (Reference [9, p. 734])", + "texts": [ + " Working conditions such as the lubrication and possible heat expansion during operation, are further reasons for the use of a backlash. This backlash ensures that just under sizing of the gear pair take place. By oversizing of the gear pair the gear cannot be assembled or the gear will get stuck which could lead to a completed failure of the gear system. To obtain the appropriate amount of backlash for spur gears two alternative ways are used by the industry today. \u2022 Decreasing the tooth thickness \u2022 Increase the center distance Figure 4-9 shows the different ways to add backlash to a gear. The left side a) of the Figure 4-9 shows how to generate backlash by decreasing the tooth thickness due to Circular backlash ! and Normal backlash ! . The right side b) shows how to generate backlash by increasing the center distance of the gear pair due to center backlash ! . 35 Reference [20] 36 Circular backlash \" : Is the distance of the working flank to the rear flank along the pitch circle, when the working flanks are in contact. Normal backlash \" : Is the shortest distance in normal direction between the rear flanks of the gear when the working flanks are in contact" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001821_f_version_1591065925-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001821_f_version_1591065925-Figure4-1.png", + "caption": "Figure 4. Elastic deformation of exemplary contact bodies as a result of the Hertzian contact force FN,el according to Fritz [24].", + "texts": [ + " (16) In the present work, a one-dimensional approach is used to calculate the contact forces with high efficiency, since this approach provides sufficient accuracy while maintaining a low level of complexity. In this case, the contact force acts exclusively along a direction vector between two contact points. The elastic component of the contact normal force is therefore calculated with the previously determined penetration based on the Hertzian contact theory [19], so that the penetration between the bodies can be interpreted as a local elastic deformation (see Figure 4). Mathematically, this can be described as a power law according to Johnson [20]. Besides an elastic force component, a simple viscous model for numeric stability is also used, so that the following equation according to Hunt and Crossley [21] results for calculating the contact normal force FN FN = (Keqv \u00b7 \u03b4n + D \u00b7 \u03b4\u0307) \u00b7 n1 , (17) with the equivalent contact stiffness Keqv calculated according to the method of Hamrock and Brewe [22] for the Hertzian contact theory, the scalar penetration \u03b4, the exponent n, the scalar penetration velocity \u03b4\u0307, the damping constant D and the contact normal vector n1 for the respective contact between ball and track or ball and cage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003024_3272-019-00421-1.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003024_3272-019-00421-1.pdf-Figure2-1.png", + "caption": "Fig. 2 Aero-structure coupled design of the LamAiR configuration; bending and torsional deformation of the forward swept wing at \u03b7 = 0.9 under load, [6]", + "texts": [ + " But this phenomenon can be avoided by a structural layout of the wing box employing fiber composites. The anisotropic characteristics of carbon fiber reinforced plastics (CFRP) allows for a coupling of flexional and torsional deformation of wings. This is achieved by an appropriate layer structure with variation of fiber direction that will lead to a derotation of wing sections parallel to the oncoming flow in case of an upward bending. This technology, well known as Aeroelastic Tailoring, was already applied during the LamAiR project to perform an aero-structure-coupled wing design (see Fig.\u00a02 and [6]) with high-fidelity methods. By this measure, a wing was realized with a structural mass not higher than for a backward swept wing of conventional construction. Hence, for the TuLam project presented here it was assumed that the aeroelastic problem is basically resolved and the structural modeling in the preliminary design methods used here was updated accordingly. Based on the above explanations the target configuration for the TuLam project was defined. Herein not only the important results from the LamAiR project were taken into consideration but also those from the EU-project DeSiReh (Design, Simulation and Flight Reynolds Number Testing for Advanced High-Lift Solutions)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure24-1.png", + "caption": "Figure 24. Path line on the rotor and permanent magnets surface.", + "texts": [ + " The velocity vectors on the x = 0 plane in Fig. 23(a) show the prevailing axial flow at the inlet. On this plane, as opposed to the case of the x = 0 plane, after the bend in the radial direction the cooling air passes through the groove between the magnets and the velocity magnitude is greater. The radial velocity in the back clearance is higher than in the front one because of its smaller size (Fig. 23(b)). A negative radial velocity region is visible at the front rotor inlet where the air intake occurs. Fig. 24 shows the colored path lines on rotor and permanent magnets showing a circulation. It\u2019s the result of low velocities in the relevant inlet recess around the inner radius and vice versa higher velocities in the relevant outlet recess around the outer radius. The velocity magnitude contours have been obtained on the radial surfaces shown in Fig. 25 (at angles 34\u25e6, 0\u25e6 and +34\u25e6). The region of the running clearance close to the rotor shows higher velocities than the one close to the stator (see Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure6-1.png", + "caption": "Figure 6. Rotation Mechanism", + "texts": [ + " When the motor is actuated, friction between the wheel and the pipe causes the wheel to drive itself around the pipe. This motion rotates the entire Pipe Traveler around the pipe until the unit is aligned with the next pipe. Gussets are used to support the drive wheel cage which houses the drive wheel. The drive wheel cage slides along support ridges along the inside of the gussets. A gusset brace allows the gussets to transfer the moment applied to the Pipe Traveler when the drive wheel is actuated. These components and can be seen in Figure 6 & Figure 7. Page 5 of 15 The pneumatic cylinders are controlled using 4-way 2-position manual valves. A manual return valve is used to control the drive wheel actuation so that the air pressure would continue to be applied until the operator decided to disengage the wheel. The extension cylinders are controlled with a momentary valve to provide the operator with finer control of the extension. The extension cylinders have a single control valve and the drive wheel cylinders have a single control valve since there is no situation where independent control would be required" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000511_9312710_09402773.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000511_9312710_09402773.pdf-Figure3-1.png", + "caption": "FIGURE 3. Common configurations of PMSMs. (a) SPMSM. (b) IPMSM.", + "texts": [ + " The main online modelling techniques, including HF signal injection, will be illustrated in Section IV in greater detail. However, there are still some general issues in the parameter estimation, e.g. rank-deficient problem, VSI nonlinearity, as well as the influence of signal injection, which must be addressed first. III. BASIS OF PMSM AND GENERAL ISSUES OF PARAMETER ESTIMATION In the last few decades, numerous PMSM topologies have been developed [1], with the common configurations being shown in Fig. 3. The surface-mounted PMSM (SPMSM), Fig. 3 (a), has a simple construction and higher power density, but it can only produce PM torque due to non-saliency and the magnets are directly exposed to the armature reaction field, and consequently, the stator inductances are relatively low and almost equal in dq-axes. In comparison, the interior PMSM (IPMSM), Fig. 3 (b), is constructed with magnets embedded in the rotor core, and has a high saliency ratio, i.e. q-axis inductance > d-axis inductance. Thus, these machines are able to utilize the reluctance torque. Fig. 4 shows the scheme of the most popular FOC system, where the currents are represented by a space vector in the dq-axis rotating frame, Fig. 5. The Park transformation from three-phase currents to dq-axis currents is expressed as[ id iq ] = 2 3 Tabc iaib ic , Tabc = cos (\u03b8r ) cos ( \u03b8r\u2212 2\u03c0 3 ) cos ( \u03b8r+ 2\u03c0 3 ) \u2212sin (\u03b8r ) \u2212 sin ( \u03b8r\u2212 2\u03c0 3 ) \u2212 sin ( \u03b8r+ 2\u03c0 3 ), (9) where \u03b8r is the rotor angular position" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure6-8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure6-8-1.png", + "caption": "Figure 6-8. Identification des ports RF du syst\u00e8me \u00e0 deux patchs \u00e0 double polarisation", + "texts": [ + " Toutes les antennes sont con\u00e7ues pour travailler sur la bande ISM 2,45 GHz et nous consid\u00e9rons les diagrammes de rayonnement \u00e0 la fr\u00e9quence de 2,45 GHz. A cette fr\u00e9quence, toutes les voies du syst\u00e8me \u00e0 deux patchs pr\u00e9sentent une efficacit\u00e9 totale de 0,94 contre 0,84 pour la Pifa agile. En r\u00e9sum\u00e9 cela nous conduit \u00e0 \u00e9tudier neuf associations antenne/traitement diff\u00e9rentes pour cet exemple. Les quatre voies RF du syst\u00e8me \u00e0 deux patchs \u00e0 double polarisation, V1, V2, H1, H2 sont identifi\u00e9es sur la Figure 6-8. Le Tableau 6-4 pr\u00e9sente les neuf associations avec les diversit\u00e9s mises en jeu pour chacune d'elles. 187 N\u00b0 Associations Diversit\u00e9 mise en jeu 1 Syst\u00e8me \u00e0 deux patchs V1V2/ s\u00e9lection 2 Syst\u00e8me \u00e0 deux patchs V1V2/MRC Spatiale avec les 2 voies polaris\u00e9es verticalement 3 Syst\u00e8me \u00e0 deux patchs H1H2/ s\u00e9lection 4 Syst\u00e8me \u00e0 deux patchs H1H2/ MRC Spatiale avec les 2 voies polaris\u00e9es horizontalement 5 Syst\u00e8me \u00e0 deux patchs H1V1/ s\u00e9lection 6 Syst\u00e8me \u00e0 deux patchs H1V1/ MRC Polarisation avec des voies sur le m\u00eame patch 7 Syst\u00e8me \u00e0 deux patchs H2V1/ s\u00e9lection 8 Syst\u00e8me \u00e0 deux patchs H2V1/ MRC Polarisation et spatiale 9 Pifa agile / s\u00e9lection Polarisation Tableau 6-4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001734_e_download_2825_3901-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001734_e_download_2825_3901-Figure10-1.png", + "caption": "Figure 10. The critical areas of safety factor", + "texts": [ + " Nevertheless, the displacement critical areas (Figure 8) that occur on the turbocharger shaft with the same load more indicates close to another one end of the compressor seat. It is due to the throwing force as the function of the length of the shaft. Same as the critical areas of stress, the strain (Figure 9) results also indicate the most potentially highest strain is located on the shaft between the turbine and compressor seat. Also, the areas could be potentially located on the right end of the compressor seat. While for the safety of factor (Figure 10), indicates that the entire area of the turbocharger shaft is a critical area. It can be said that this shaft has a good design for loads beyond its normal operations. If there is an excessive force this shaft can distribute the force to other parts of the shaft thus it becomes equal. However, on the shaft end area close to the turbine side indicates uneven loads. It may be caused by improper bearing treads. Based on data analysis and simulation result using FEM, it can be concluded that : 1) The more increasing load engine causes the compressor and turbine torque increased too, but the difference between both torques will be decreased" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001252_O201620240595779.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001252_O201620240595779.pdf-Figure2-1.png", + "caption": "Fig. 2. Cross section of LSPMSM with different rotor", + "texts": [ + " Therefore in machines where the rotor and stator contain magnets and winding slots, which are periodically distributed in angle, the cogging torque increases through an additive effect. This is due to the fact that each magnet has the same relative position with respect to the stator slots so the torque from each magnet is in phase with other magnets and as a result the harmonic components of each magnet are added together. To illustrate the influence of pole numbers and pole position on the cogging torque a 4 pole 24 stator slot inset LSPMS motor is selected for investigation. As shown in Fig. 2, motors with different pole numbers (one, two, four and also one shifted magnet) are taken into account. The simulation results are presented in Fig. 3. As shown the results verify that the total cogging torque can be obtained as the sum of contributions from each magnet. In addition the results also show that the phase of cogging torque of a magnet changes when the magnet is shifted. 880 \u2502 J Electr Eng Technol.2016; 11(4): 878-888 Therefore in a motor with 4 poles which are symmetrically distributed on a rotor with 24 stator slots, the overall cogging torque is four times the contribution of each pole" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure4-1.png", + "caption": "Figure 4 Sources of EMI Leakage", + "texts": [ + " EMI/RFI can escape from a container through any opening of a certain size. This size is determined based on the wavelength of the specific frequency that needs to be contained. In order to properly shield any radio frequencies or EMI, any gaps or openings must have no dimension larger than half the wavelength (\u03bd) of the source. Examples of unacceptable gaps/openings are shown below in Figure 3. Page 6 The P-POD Mk. III Rev. E has many gaps that are perfectly illustrate the reality EMI/RFI leakage. These gaps are noted below in Figure 4. Additionally, some launch vehicles require that the P-POD accommodate a venting rate that is typically accomplished through a venting hole, which becomes another area of EMI/RFI leakage. The first step in containing all EMI/RFI was to seal all gaps in the P-POD. In order to seal these gaps, it is necessary to implement a conductive EMI gasket to any potential gaps. This includes the gap between the door and collar, as well as the gap around the access port covers. In order to gasket the access port covers, a flanged interface needed to be created to house the gasket" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002238_e_download_8004_8699-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002238_e_download_8004_8699-Figure2-1.png", + "caption": "Figure 2. Geometry of the proposed antenna", + "texts": [ + " When compared with other microstrip dual band antenna our antenna possesses the advantage of not only having a broad bandwidth, high gain but also a smaller size [5]-[9]. The elliptical patch antenna proposed is applied on the dielectric material FR4 substrate with a thickness h=1.58 mm, relative permittivity and Tangent loss . Initially an elliptical patch antenna is considered with inset-feed and the different design stage is shown in Figure 1. The final geometry of the proposed antenna is shown in Figure 2, consists of two rectangular slots in the radiation patch that plays a significant role in determining the resonating frequency because they can control the electromagnetic coupling effects between the patch and the ground plane. The parameters calculated and optimized of the proposed antenna for 14 GHz operating frequency are shown in Table 1. ISSN: 2088-8708 Int J Elec & Comp Eng, Vol. 8, No. 3, June 2018 : 1596 \u2013 1601 1598 The proposed antenna is designed and simulated using an electromagnetic solver based on the finite element method (FEM) and another solver based on the finite integration technique (FIT), to compare the results of the proposed antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002098__icssf2024_02007.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002098__icssf2024_02007.pdf-Figure6-1.png", + "caption": "Fig. 6. The peeler, splitter, and separator of dry soybean husk operate on an electric blower technology basis.", + "texts": [], + "surrounding_texts": [ + "The results of the discussion and literature study resulted in the identified design results as shown in Figure 5. The machine's design process begins with a concept design that is refined through comprehensive drawings before being assembled on the machine in accordance with the necessary parameters [10], such as: a) This tool uses an electric motor drive with a power of 1 PK; b) The tool uses stainless steel 304 with dimensions of 60 x 90 x110 cm; c) This tool is used to separate the seeds and the epidermis using a 2-inch Electric blower; d) The main regulator on the blower uses a dimmer, while as a backup it uses a ball valve; e) This tool has dimensions of 600 mm x 400 mm x 930 mm; And f) This tool has a 30 Kg reservoir. The goal is for the machine's construction to be finished in 1.5 months. This phase covers machine design from component assembly through engine preparation. Students studying machine design engineering are also involved in the assembly process." + ] + }, + { + "image_filename": "designv8_17_0002208_load.php_id_15010201-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002208_load.php_id_15010201-Figure1-1.png", + "caption": "Figure 1. Open elliptical-ring slot resonator and the complementary open elliptical-ring resonator.", + "texts": [ + " It is well known that any slot has its complementary form in wires or strips, thus, patterns and impedances data of these forms can be used to predict the patterns and impedances of corresponding slots. The electric field distributions of microstrip open-ring resonator\u2019s resonant modes are given in [13]. Combining with the electric field distributions of the microstrip elliptical ring resonator\u2019s resonant modes in [14], the electric field distributions of the open elliptical-ring slot resonator\u2019s TM 110 and TM 210 modes, which are shown in Figure 1, can be reduced with the Babinet\u2019s principle. According to duality principle, there is an interchange between the electromagnetic fields of the slot and the complementary ring which is also presented in Figure 1. The resonant frequencies of both the TM 110 and TM 210 modes can be estimated by the microstrip line resonator analysis method which is used in [13]. The TM 110 mode is the one with the lowest resonant frequency, as shown in Figure 2(a). And it can be considered as the resonance on a curved \u03bb/2 microstrip line. The distribution of the magnetic field strength far away from the gap is nearly equal to that of a straight microstrip line. Only in the gap area does the field distribution change, because the field must be perpendicular to the boundaries at the end of the lines" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002450_9668973_09729868.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002450_9668973_09729868.pdf-Figure5-1.png", + "caption": "FIGURE 5. Measuring the actual steering radius of the tracked vehicle.", + "texts": [ + " In the conventional method, the sprocket rotation speed np and the actual steering radius RS are initially measured, and the track slippage coefficient can be calculated through Eqs. (1), (2), and (3). In the proposed method, the sprocket rotation speed np and the time T of the steering around were measured, then the slippage coefficient of the track was calculated by the proposed model in the MATLAB environment. The actual steering radius RS of the combined harvester was calculated by measuring the real trajectory of a certain point when the tracked vehicle was being steered. Fig. 5 shows the hourglass device installed at point B at the rear of the vehicle. Transverse and longitudinal distances of the hourglass device relative to the geometric center OV of the vehicle were measured. Then the coordinate value (xv,yv) of point B relative to the geometric center OV of the vehicle was determined [22]. When the vehicle entered the stable steering state, the hourglass device was used to record the steering trajectory of the vehicle. Then the starting point A and the ending point B were determined using the path remaining on the sand, and the midpoint C was marked" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002162_tation-pdf-url_53237-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002162_tation-pdf-url_53237-Figure1-1.png", + "caption": "Figure 1. System configuration of the proposed array antenna.", + "texts": [ + " Added complexity of this system outweighs the benefits of fulfilling electrical specifications. At this point, it will be suggested to use two panels built from microstrip patch antennas for each polarization to minimize the added complexity of this implementation. The array will be formed in order to have a tilted beam. Since the array can be mechanically tilted, it would be easier to scan low elevation angles without exceeding the overall height limits. The system configuration of the proposed design is illustrated in Figure 1. The directivity of a TM01 mode broadside patch is roughly: DP \u00bc 4\u03c0 \u03a9A \u2248 4\u03c0 \u03c0 \u00bc 4\u00f06 dBi\u00de (1) where, \u03a9A represents beam solid area. For K elements, the array directivity DA becomes: DA\u2248KDP (2) DA\u2248 40, 000 HPBW\u03b8HPBW\u2205 \u2248 444\u00f026:47 dBi\u00de (3) Furthermore, if 55% total efficiency (due to feed network loss, mismatch loss) is assumed, the gain of the array should be 807 (29 dBi). Number of broadside patch elements required for this gain is 202. To preserve symmetry and to account for other losses (e.g. random, mutual coupling among array elements), we estimate that 256 elements per polarization is needed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure27-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure27-1.png", + "caption": "Figure 27 : D\u00e9tail de la structure [25].", + "texts": [ + " Ceci implique que ces derniers ont peu de limitations concernant leur design, et que quasiment n\u2019importe quel type d\u2019\u00e9l\u00e9ment peut \u00eatre utilis\u00e9 pour Page 26 sur 182 les r\u00e9aliser. \u00c0 l\u2019inverse, les \u00e9l\u00e9ments rayonnants \u00e0 la bande de fr\u00e9quence la plus basse sont plus restreints, puisqu\u2019ils doivent s\u2019adapter \u00e0 l\u2019espace qui leur est affect\u00e9, tout en garantissant une largeur de bande convenable, ainsi qu\u2019un encombrement r\u00e9duit. Ces derniers ont donc un impact relativement important sur les performances des r\u00e9seaux bi-bandes r\u00e9alis\u00e9s. 1) Dip\u00f4les et patchs [24, 25] (Figure 26 et Figure 27) Ces r\u00e9seaux n\u2019offrent pas des ratios de fr\u00e9quences importants, 3:1 pour le premier [24], et 2.2:1 pour le second [23]. Les bandes de fr\u00e9quences du premier sont relativement bonnes (8,9 % en bande S et 17 % en bande X), contrairement au second, qui est un r\u00e9seau r\u00e9flecteur (< 1%). Les deux r\u00e9seaux permettent de r\u00e9aliser une double polarisation. 2) Patchs en forme d\u2019anneau et patchs circulaire [26] (Figure 28) Les patchs circulaires fonctionnant en bande X sont aliment\u00e9s en s\u00e9rie par groupe de quatre afin d\u2019avoir un r\u00e9seau plus compact mais \u00e9galement moins de pertes dues aux lignes Page 27 sur 182 microruban" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000262_O201530848560227.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000262_O201530848560227.pdf-Figure10-1.png", + "caption": "Fig. 10. Experimental results I.", + "texts": [ + " 12 shows the experimental results when S1 is from the normal operation mode to the short-circuit mode at 0.8 s, and the target speed and torque are 1500 rpm and 3 Nm respectively. Figs. 10(a) to 10(d) show that the flux error is larger in the startup process, and the flux error is approximately stable with speed into the steady state in the proposed method and DCC. However, the change in torque has little impact on the flux in the proposed method and DCC. A smoother flux curve and smaller flux error are also obtained for the voltage vector selection table. The stator resistance online estimate (Fig. 10e) and DC voltage compensation are introduced in proposed method. Thus, the proposed flux observer can provide an accurate flux size and position information for the method in the low-speed range. Figs. 10(f) to 10(i) clearly show that the proposed method can improve current distortion caused by the uncontrolled phase, and the current and back-EMF response speeds are faster than that of traditional DCC in the low-speed range. Figs. 10(j) and 10(k) show that the proposed method can improve torque pulsation and have better dynamic and static performance characteristics of the torque compared with those of traditional DCC in the low-speed range" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001813_tation-pdf-url_37022-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001813_tation-pdf-url_37022-Figure15-1.png", + "caption": "Fig. 15. Conceptual schematics of the conventional (left) and CLL loaded dipole (right).", + "texts": [ + " 14, shows the surface current densities on the CLL loaded and unloaded dipole antennas. As can be seen, the current in the CLL loaded region is the superposition of two currents oriented in opposite directions. However, the surface current caused by CLL cells is dominant, and thus the current in all parts of the dipole has the same phase. To clarify the operation mechanism of the CLL loaded dipole antenna. We assume that dipole antenna is surrounded by CLL cells, where the current direction of the dipole is reversed. Fig. 15, conceptually explains the distribution of the surface current density on the CLL loaded dipole antenna. However, one must consider the complex interactions between the dipole arms and the CLL structures, such as the effects of the finite dimensions of the CLL structures on the current distribution. Consequently, full wave analysis methods have to be used in the antenna designs. However, to simplify the analysis, one can assume that the transverse dimensions of CLL loaded region are infinite in extent. Thus, as previous section, one can explain the concept based on the image theorem, i.e., when an electric current is vertical to a PMC (PEC) region, the current image has the reversed (same) direction. For the current at the bottom of the dipole flowing into the CLL loaded region, the CLL loaded region acts as a PMC cover (Erentok et al., 2005). At the result, the direction of the image current is opposite to that of the original current, as shown in Fig. 15. In contrast, for the current at the top of dipole flowing into the CLL loaded region, the CLL loaded region acts as an AEC (Erentok et al., 2005), and thus the image current in the CLL loaded region has the same direction as the original current. The total surface current in the CLL loaded region is obtained as the sum of the two image currents and original current. At the result, the current phase of the CLL loaded dipole antenna remains unchanged through the antenna, as shown in Fig. 15. www.intechopen.com Applications of Artificial Magnetic Conductors in Monopole and Dipole Antennas 589 The radiation patterns of the conventional and CLL loaded dipole antennas are also shown in Fig. 16, respectively. As can be seen, when the dipole antenna is loaded with CLL structure, the radiation patterns improve significantly, especially at the second harmonic (27GHz) of the main resonant frequency where antenna is matched well. The Simulation shows that above 20dB gain enhancement has been achieved in azimuth plane using CLL loading technique" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure10-1.png", + "caption": "Fig. 10. The loading of rims in the model of the twin rear wheels of the rear axis of the tipper. T \u2013 the maximum drive torque, G \u2013 the maximum vertical load on the rear axle of the tipper by one twin wheel of this axle", + "texts": [ + " During the current analysis, the following principle was followed: if the calculated von Mises stresses in the rim caused by the load from the car weight and the driving torque exceed the plasticity limit of the rim material, they will exceed it even more if the influence of the presence of compressed air in the tire is considered. Two cases were considered: the first one when both twin wheels contacted the ground (Fig. 9a) and the second one when only one tire of the twin wheel contacted the ground (Fig. 9b). The maximal drive torque T was symmetrical, half its value, applied to the annular part of the plane of each hub containing the holes for pins/bolts connecting the twin wheels (Fig. 10). Half of the maximum vertical load G on the rear axle of the tipper by one twin wheel of this axle was applied to the same annular fragments of the plane (Fig. 10). The maximum vertical load G reached the value equal to a weight resulting from the permissible rear axle mass m mra\u2212perm, namely 16 0000 N. The grid of the curvilinear 10-node tetrahedral finite elements was shown in Fig. 11. Five options of average element size were utilized to conduct convergence evaluation in terms of the effect of the average element size on the maximum values of calculated von Mises stresses. It was assumed that solution convergence can be obtained when the decrease of average element size results in the stabilizing of the maximum values of von Mises stress calculated for the same geometrical and material parameters, loads, and boundary conditions in the analyzed model" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001922_1044-023-09952-2.pdf-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001922_1044-023-09952-2.pdf-Figure22-1.png", + "caption": "Fig. 22 Circle\u2013circle interaction-based model (C4): (a) Geometrical description; (b) Complete model", + "texts": [ + " Since multiple interactions are simultaneously taking place, it can become a stiff problem for the integrator. The comparison of the dynamic response obtained for both C2 and C3 approaches is represented in Fig. 20 and Fig. 21. While Fig. 21 shows that the loading of the rolling elements is identical for both models, Fig. 20 demonstrates that a greater number of planes used on the cage definition produced more stable results, reducing the amplitude of the oscillations. The fourth approach of this group, named C4 and illustrated in Fig. 22, is based on the internal circle\u2013circle interaction introduced above. In this model, the radius of the cage pocket was defined with sufficient clearance to allow free movement of the balls while ensuring that the interactions between the balls and races are not compromised. However, it is important to note that if the radial clearance of the bearing is excessively large, the rolling elements may make contact with a non-existent part of the cage pocket instead of the rings, as schematically represented in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure42-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure42-1.png", + "caption": "Figure 42: Y axis deformation of pantograph design 1.", + "texts": [], + "surrounding_texts": [ + "The figures below show the deformation plots for the pantograph designs. Figure 44: Y axis deformation of design 3. Figure 45: Y axis deformation of final design. 36" + ] + }, + { + "image_filename": "designv8_17_0000938_.2478_mspe-2020-0039-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000938_.2478_mspe-2020-0039-Figure5-1.png", + "caption": "Fig. 5 Schematic diagram of introducing the installation behind the dynamic head: 1 \u2013 dynamic head, 2 \u2013 starting platform, 3 \u2013 installation, 4 \u2013device pressing down the pipe, 5 \u2013 control device, 6 \u2013 compressor, 7 \u2013 hose delivering compressed air", + "texts": [ + " The first ground rocket was designed in England in 1916. This device consisted of a metal cylinder with a sharpened front. Rams, controlled with compressed air, were installed inside the cylinder. In Fig. 3 a diagram of this ground rocket of Terra-Hammer type, made by Terra Company [19], is presented and in Fig. 4 a solution, developed by the Terra Max Company [17], is shown. Source: [17]. Source: [16]. The schematic diagram of this method, consisting in an implementation of an in-coming installation with the dynamic head is presented in Fig. 5. Source: [10]. It is one of the simplest excavationless methods and it is based on an introduction into the ground of the installation 3 (usually flexible) directly behind the dynamic head, [1, 10]. In the head of a cigar shape there is a ram put into reciprocating motion, which hits the head, relocating it in the ground. The ram motion is obtained due to compressed air from the compressor 6 conducted to the device through the hose 7. The air flow can be controlled by the control equipment 5. The frequency of the ram strokes onto the head, in relation to the design solution and the device diameter, varies from 150 and 600 strokes per minute" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.7-1.png", + "caption": "Figure 4.7: COlnparator offset causes signal saturation.", + "texts": [ + "5-bit stage is shown in Figure 4.6. 4.1.3 Digital Error Correction In a pipelined ADC where the interstage amplifier gain equals to the resolution of this stage, e.g. amplifier gain =4 for resolution = 2-bit, the comparators in sub-ADC must be very accurate. An offset error of the comparator can saturate the input of next stage. As an 48 ATTENTION: The Singapore Copyright Act applies to the use of this document. Nanyang Technological University Library example, the transfer function of a 2-bit stage is shown in Figure 4.7. Because of the signal saturation, there is a large conversion error and the effective resolution of ADC is reduced. To relax the requirements on comparators, digital error correction can be use [6]. One significant advantage of pipelined ADC is the possible applications of the digital error correction technique which significantly relaxes the accuracy requirement of the comparators in the sub-ADC. Therefore the sub-ADC needs only to be accurate enough to 49 ATTENTION: The Singapore Copyright Act applies to the use of this document" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002155_ulture2024_02028.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002155_ulture2024_02028.pdf-Figure8-1.png", + "caption": "Fig. 8. General view of the membrane type flow divider with compensation rods", + "texts": [ + " At the same time, the adjustable pressure drop affects the part of the membrane element that lies on the gap and does not participate in regulation, and the absence of a rigid center makes the membrane element practically indifferent to small-scale movements. The high accuracy of the described flow divider makes it very promising from the point of view of application in non-reversible synchronous hydraulic drives. Another way to improve the accuracy of a diaphragm-type DP with variable hydraulic resistances of the flat valve type is to compensate for the effect of an adjustable pressure drop in the branches on the shut-off and control element, which was carried out in a number of designs of flow dividers. Figure 8 shows a design diagram of a throttle flow divider with a compensation rod, the principle of operation of which is as follows. The working fluid enters the control chambers 5,6 through the inlet openings 1,2 and the inlet resistances 3,4, and through the outlet resistances of the flat valve type 7 and 8 - into the outlet openings 9 and 10. If the loads in the branches are the same, then the flow rates through the input resistances 3 and 4 are the same, and therefore the pressure losses on them are the same", + " The introduction of a movable rod of variable cross-section into the design makes it possible to compensate for the effect of an adjustable pressure drop on the membrane elements, which significantly improves the static characteristics of the divider. The presence of the same rod of variable cross-section allows for a constant volume of control of the divider, which increases its dynamic capabilities. In addition, in this design, the membrane elements always experience pressure drops in one direction, which allows the use of both flat and corrugated membrane elements. This, in turn, makes it possible to vary the stiffness of the membrane elements in a wide range, including zero. Thus, in the design of the divider under consideration (see Fig. 8) it is possible to regulate the ratio of expenses in the branches depending on changes in working conditions, which none of the DDP described above allows. And the fact that when regulating the divider, not the pressures in the branches are compared, but the pressure losses on the throttles, allows it to be used both for the purpose of dividing and for the purpose of summing flows. The analysis shows that of the presented throttle flow dividers of non-spool type, the flow dividers presented in Figures 7 and 8 are of the greatest interest from the point of view of their use in synchronous hydraulic drives of technological machines, which make it possible to ensure synchronous operation of hydraulic drives with high accuracy at minimal cost" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002806__download_11595_7978-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002806__download_11595_7978-Figure11-1.png", + "caption": "Fig. 11 Specimens used to verify the material model. (a) Uniaxial tension; (b) Pure shear; (c) Equibiaxial tension.", + "texts": [ + " The resulting large-strain viscoelastic model is the modification of the model originally proposed by Simo [14, 17]. To verify the behavior of the material model, FE simulatios were performed in uniaxial tension, pure shear and equibiaxial tension modes. The modelled specimen\u2019s dimensions are in accordance with the ones seen in Fig. 3. For the finite element simulation 1/8-th of the test specimens were modeled to reduce computational time. The tensile speed in all three cases was 100 mm/s. In Fig. 11 one can see the modelled specimens. (6) 152 Period. Polytech. Mech. Eng. Gy. Szab\u00f3, K. V\u00e1radi Fig. 12 shows the response of the model compared to the measurements. The material model supplemented with the 5 parameter Mooney-Rivlin term was fitted in the region of 0 - 150 % strain and gives a good correlation with the measured data. The model follows the inflexion of the measured curves though it slightly overrates the rubbers response at moderate strains. For the finite element simulation of the O-ring an axisymmetric model was built" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004353_v.org_pdf_2402.18897-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004353_v.org_pdf_2402.18897-Figure3-1.png", + "caption": "Fig. 3. Modeling of the contact controller. The frames Or,Oc,Od, frame displacements dpc,r, dpr,d, contact jacobians Gi,Ji, stiffness matrices Kc,Kr,Ko are illustrated. Note that Od can be obtained with forward kinematics FK(\u03bed). The model compliance creates a coupling effect between force and motion.", + "texts": [ + " The smoothed dynamics has side-effects that shift the object at a non-zero contact distance (i.e., force-at-a-distance). Thus directly executing the high-level references would lead to contact slippage or missing. To mitigate such modeling errors, a model-based controller is proposed to adapt the generated references locally. The controller incorporates an equivalent virtual spring system with a compliant contact model. By coupling joint positions and reaction forces with compliance, a balance is achieved between tracking both. The modeling is illustrated in Fig. 3. 1) Compliant Contact Model: Any compliant contact model that maps relative contact distances to reaction forces can be used. One example is [14], while the damping effect related to contact velocity is ignored here due to quasi-static assumptions. The compliant contact model is guaranteed to have continuous gradients. Thus, we can define the equivalent stiffness in the contact frame, CKc = diag ( \u2202f \u2202\u03d5 [\u03b1 \u03b1 1] ) (6) where the y-axis aligns with the sliding direction, and the z-axis coincides with the contact normal, \u03b1 is an adjustable parameter" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004266_0005208_10013670.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004266_0005208_10013670.pdf-Figure1-1.png", + "caption": "FIGURE 1. Layout of monopole radiator (a) Front View (b) Layered View.", + "texts": [ + " The proposed dual-band MIMO antenna operates in the 5G Sub-6 GHz and Wi-Fi 6E bands with measured impedance bandwidths of 2.39-2.57 GHz and 3.82- 6.95 GHz, respectively. The proposed antenna uses a novel Parasitic Dollar Shaped Structure (PDSS) which improves the isolation of the proposed MIMO antenna. Due to its compact size, dual-band operation in 5G Sub-6 GHz and Wi-Fi 6E bands, and reduced mutual coupling between the antenna radiators, the proposedMIMO antennawill be a good candidate for future next-generation wireless devices. The layout and appearance of the single monopole radiator is illustrated in Figure 1. Here, the main rectangular monopole is loaded with an inverted E-shaped structure at its left and an asymmetrical T-shaped strip at its right. To achieve better impedancematching of the CPW-feed technique, two identical ground planes 5618 VOLUME 11, 2023 having an area of 8.6 \u00d7 9.5mm2 each are positioned at the lower left and right corners of the substrate. A 50 microstrip transmission feeding line of size 10 \u00d7 1.8 mm2 is embedded within the two ground planes with an air gap of 0.5mm on each side, as depicted in Figure 1. The overall planar size of this monopole radiator engraved on 0.8mm FR-4 substrate is 20 \u00d7 30 mm3. To explore the working mechanism and excitation of the single monopole radiator within the two wide operational bandwidths of 2.40 to 2.55 GHz and 3.85 to 6.93 GHz, the remainder of this section describes the steps of antenna development and its corresponding reflection coefficient curve (S11). Initially, a vertical rectangular radiator (ANT@1) is introducedwith symmetrical CPW-fed ground planes, as indicated in Figure 2a", + "5 GHz yielding a 10-dB impedance bandwidth between 2.40 and VOLUME 11, 2023 5619 2.55 GHz, along with slight enhancement in the higher band of 4.11-6.01GHz. (Figure 3). However, theANT@2 still does not cover the higher Wi-Fi 6E band. 3) DEPLOYMENT OF AN INVERTED-E-SHAPED STRUCTURE (ANT@3) In order to obtain the entire Wi-Fi 6E band, an inverted-Eshaped structure with equal-sized arms is deployed on the left side of ANT@2 (ANT@3, Figure 2c). Each of the three rectangular arms of the E-shaped structure has a size of 4\u00d71mm2 (see Figure 1a), and, notably, the air gap between these arms acts as a capacitor to cancel the inductive reactance created by the E-shape. Furthermore, the entire inverted E-shaped structure increases the path for electrical current, thus aiding in enhancing the higher frequency bandwidth from (4.11- 6.01 GHz) to the range of ANT@2 (3.85-6.93 GHz) along with better impedance matching at 2.5 GHz for ANT@3, as depicted in Figure 3. Therefore, the ANT@3 successfully functions in the lower frequency band of 2.40-2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004878_1_1_article-p394.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004878_1_1_article-p394.pdf-Figure1-1.png", + "caption": "Fig. 1. Flow control valve.", + "texts": [ + " There are few methods for closure RANS equations which are called turbulence models: - zero equation turbulence models, - one equation turbulence models, - two equations turbulence models, Above models use the Boussinesq hypothesis: \u2212\u03c1uiuj\u0305\u0305 \u0305\u0305 \u0305 = \u03bct ( \u2202ui \u2202xj + \u2202uj \u2202xi ) \u2212 2 3 \u03b4ij (\u03c1k + \u03bct \u2202uk \u2202xk ) (4) There are also turbulence models which does not use the Boussinesq hypothesis like Reynolds stress models. CFD tools allows to simulate fluid flow inside valves as well as simulations of phenomena which may cause valves failure or malfunction (Domagala et al., 2018a; Domagala et al., 2018b). Flow control valve function is to maintain constant flow rate independently on pressure to inlet or outlet. Valve presented in Fig. 1. is a flow control valve controlled by proportional solenoid. The valve itself consists of two valve: throttle valve and compensation valve which means that the valve can be characterized as a structure with high scale of complexity. The value of flow rate which will be maintain in the system is set by the position of the spool on the left side. Constant flow rate is maintain by the position of the spool on the right side, which is determined by the flow conditions on inlet and outlet. Numerical simulations of fluid flow inside hydraulic valves are conducted for various goals, to investigate flow forces (Domagala, 2008; Lisowski et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001086_1934_context_journal-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001086_1934_context_journal-Figure1-1.png", + "caption": "Fig. 1. The structure of planetary gear train of running mechanism.", + "texts": [ + " The sea-floor is interlaced of rock, sand and mud, of which the compressive strength is 0.08-68.2 Mpa [10], and terrain grade is 5-35\u00b0 [6]. Conventional walking mechanisms always turn out to be incompetent when confronting this terrain of multivariate substrate, such as wheeled model, track, legged and complex ways [2]. Planetary gear wheel walking mechanism has a strong adaptability to overcome obstacle [1]. The articulated frame performs good steady-state characteristic, and enhances the stability of the mechanism [7]. The structure of planetary gear train is shown in Fig. 1. The center gear 5 drives transition gear 4 and driving gear 2. And the driving gear 2 is fixed with wheel 1, which leads wheel 1 to rotate. According to different forces applied to the wheel 1 by ground, the running mechanism turns into the fixed wheels or the planetary wheels pattern. When it walks on flat ground, two wheels below are restrained by ground, and the planetary Paper submitted 08/24/09; revised 11/16/09; accepted 03/22/10. Author for correspondence: Ya-Li Feng (e-mail: ylfeng126@126", + " There are four sets of planetary gear train, each of which is driven by the running mechanism\u2019s wheel. As the fixed-spindle gear train, two wheels are on flat ground, which is equal to 8 \u00d7 8 wheels drive. While surmounting obstacles, they evolve into the planetary gear train. The planetary gear carrier rotates to overcome the barrier. To change direction, the pressure oil, produced by the hydraulic system through application valve, drives steering cylinder piston rod to move telescopically [5]. They are located on both the front and rear frame. So, as shown in Fig. 1, either of the frames turns a certain angle, to achieve turning function. Running mechanism makes circular movement around the center of intersection point of front wheel\u2019s vertical line and rear wheel\u2019s. The distance between the intersectional point and the centerline of the frame is the steering radius as the geometric relationship shown in Fig. 3. 0 costan a b R \u03b8\u03b8 + = 0 cos tan a b R \u03b8 \u03b8 + = (1) When a vehicle is negotiating a turn, to balance the centrifugal force, the tires must develop an appropriate side force [11]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000174_f_version_1641029125-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000174_f_version_1641029125-Figure5-1.png", + "caption": "Figure 5. Leakage-flux path of the short-pitched winding 2 when operates at high current densities.", + "texts": [ + " The control parameters of the 12/8 SRM in the dynamic simulation are the same. The advance turn\u2013on angle is 0 degrees, the conduction period is 22.5 degrees in the short-pitched winding, the conduction period is 30 in the fully-pitched winding, and the rotational speed is 500 r/min. A conventional hysteresis current control is applied and the maximum current is 9 A. The five winding configurations of the 12/8 SRM are simulated. Average torque and torque ripple are the essential considerations in this simulation. Figure 5 shows the flux density and flux path of the dynamic simulation. The result of the dynamic simulation is shown in Figures 6 and 7 and comparative results in Table 7. The dynamic torque performance of the double-phase excitation of the fully-pitched winding is shown in Figure 7. The torque ripple rate of the fully-pitched winding 1 and the fullypitched winding 2 is 1.3 and 1.0, respectively. The average torque of the fully-pitched winding is the highest, at 36.55 Nm. However, with double-phase excitation and high phase resistance of the fully-pitched winding, it produces more copper losses compared with the other winding arrangements. The dynamic torque performance of the single-phase excitation in Figure 6 shows that the short-pitched winding 1 has a dramatically torque ripple rate of 10.28, and the average torque is lowest at 3.54 Nm. The short-pitched winding 2 has a torque ripple rate of 2.25 and the average torque decreases to 11.81 Nm. compared with the short-pitched winding 3 having a low torque ripple rate at 0.66 and average torque at 19 Nm. To describe this phenomenon, Figure 5 shows the flux density and flux path of the short-pitched winding 2. The simulation results of the short-pitched winding 2 show that the leakage\u2013flux paths appear on the adjacent stator poles when operating at high torque density. Therefore, the number of flux reversals in the stator yoke increases and generates more negative torque during phase commutation. The leakage\u2013flux paths are shown in the red dot circle in Figure 5. The short-pitched winding 2 has good torque performance and reduces the number of flux reversals when operating at low torque density, as was revealed in [15]. For this reason, the average torque of the short-pitched winding 2 decreases, and the performance of the SRM drops to 76.63%, while the short-pitched winding 3 has a higher average torque and efficiency at 84.9%. However, the core loss of the short-pitched winding 2 is still lower than the short-pitched winding 3. Table 8 reveals comparative results of dynamic simulation performance between short-pitched 2 and short-pitched 3 in terms of core loss at the stator and efficiency performance" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure2-1.png", + "caption": "Fig. 2 Definition of the inlet blade angles (chevron angle) and outlet blade angles (inclination angle).", + "texts": [ + " Due to the drawbacks of these type of pumps, many researchers introduced various ways of design modifications methods to improve the performance of these pumps as reported by Kaelsen-Davies et al. 2016 [5]. Horiguchi et al. 2009 [6] performed experimental and numerical study to compare two different types of impellers: symmetric and asymmetric. They observed that the pressure of the symmetric impeller was about 2.5 times the asymmetric one. The most common suggested modifications in previous works were the changing of inclination or chevron angles of the blades. Figure 2 shows the side view of the pump casing where the inlet blade angle \u03b1 is called chevron angle the outlet blade angle \u03b2 is called inclination angle. These modifications were done on each angle separately, which have crucial impacts on the head of RP as discussed by Horiguchi et al. 2009 [7], Teshome and Dribsa 2007 [8]. Nejad et al. 2017 [9] tested a symmetric impeller with three different values for the inclination angles +10\u2218, +30\u2218 and +50\u2218, it was observed that the head coefficient increased at inclination angles of +10\u2218 and +30\u2218 and decreased at angle of +50\u2218 compared with the radial blades" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004801_cle_2630_context_etd-Figure6.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004801_cle_2630_context_etd-Figure6.1-1.png", + "caption": "FIGURE 6.1 :TEST SET UP FOR MONOPOLE OVER GROUND PLANE.", + "texts": [ + " This was again accomplished by testing a known antenna, in this case a thin wire monopole. This antenna was installed in our test stand and connected to the test equipment through a coaxial panel-mount BNC connector mounted in the aluminum sheet forming the ground plane. The purpose was to compare the practical results of this wellknown antenna, and compare them to existing theoretical and practical data, as well as to MININEC results. This would give us some information about the validity of our test set-up and the performance of the test-equipment used. Figure 6.1 shows the test stand with the monopole antenna connected. Note that the probe is under the ground plane, therefore not interfering in any way with the antenna radiated field. The monopole was built of thin 22 AWG tinned-copper wire. This gage represents a wire radius of approximately 0.32 mm. The wire was soldered to the center tip of the BNC connector, using standard Tin-Lead electrical solder. The ground-plane, had the dimensions and characteristics already described in section 6.1. 104 105* The antenna was mounted on a piece of styrofoam" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure3-1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure3-1-1.png", + "caption": "Figure 3-1: Link i under linear motion.", + "texts": [ + " The com puter graphic simulation results of motion effects and relative contributions of the dynamic term s are presented. The motion profiles are presented in Cartesian and joint configuration spaces. The simulation results provide valuable inform ation for understanding the com plex behavior of the dynamic m anipulator motion and for improving m anipulator performance. Concepts of this chapter could be extended to determ ine optim um feedforward torque requirem ents for each joint actuator for a specified task. 40 3.2 N ew to n -E u ler F orm u lation Newton\u2019s equation of m otion applied to link i yields (Fig. 3-1) = m i \u2019{% <} Euler\u2019s equation of motion applied to link i yields (Fig. 3-2) * { \u00b0 iV , } = \u00ab U i f W i } +*' { \u00b0 W i } X [ciI i \u2018 { \u00b0 ^ } ] , where \u00b0FCJ- and \u00b0 iV , denote the net force and torque applied to link i. m-i is the mass of link i. ctIi is the m oment of inertia of link i w ith respect to the centroid coordinate frame ci. The fram e ci is located at the centroid of link i and has the same orientaion as joint fram e i resulting in c,/j =* Jj. Appendix D shows the derivation of the above expression and the structure of the inertia tensor \u2019/,\u2022 and transform ation between *1; and \u00b0Ii" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004470_8948470_09129694.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004470_8948470_09129694.pdf-Figure5-1.png", + "caption": "FIGURE 5. Schematic diagram of tractor kinematics during transport conditions.", + "texts": [ + " Operating characteristics of reference tractor. In conventional tractor designs, the engine power is usually determined by the rated traction: Pe = 0.7335Feq \u00d7 \u03c5 \u00d7 \u03b7\u03b4 9.8\u00d7 270\u00d7 \u03b7f \u00d7 \u03b7\u00b5 . (6) where \u03b7\u03b4 = 0.8, \u03b7f = 0.7, and \u03b7\u00b5 = 0.85. Therefore, by using eq. (6), the following can be calculated: Pe = 95.883kW . The rated power of the selected diesel engine is 110 kW, which can satisfy the traction resistance and tractor working demand. When the tractor is under transport conditions, the speed is low, as shown in Fig. 5; therefore, the resistance \u2211 Fxmax overcome by the tractor is approximately:\u2211 Fxmax = mgf cos\u03b1max + mg sin\u03b1max (7) In addition, the driving forceFt generated by the tractor needs to be greater than the resistance overcome on the slope road and less than the ground adhesion F\u03d5 to prevent the vehicle from skidding:\u2211 Fxmax \u2264 Ft = Temax igminiord \u2264 F\u03d5 = \u03d5mg cos\u03b1 (8) 195414 VOLUME 8, 2020 TABLE 2. Basic parameters of P/M form SAUER-DANFOSS. Meanwhile, the grade ability and starting capability of the designed PCHMCVT tractor are better than the reference vehicle, therefore: Temax igminib1io \u00b7 \u03b7g \u2265 Temax i\u2032gmini \u2032 b1i \u2032 o \u00b7 \u03b7\u2032g" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003248_jees-2021-4-r-36.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003248_jees-2021-4-r-36.pdf-Figure7-1.png", + "caption": "Fig. 7. (a) Simulation model and (b) realized antenna.", + "texts": [ + " As the frequency increases, the current intensity reduces towards the ends with all antennas. However, this trend is more pronounced as the number of sleeves increases. The length and (d) spacing between first and second sleeve, e. SAIRAM et al.: DESIGN OF BROADBAND COMPACT CANONICAL TRIPLE-SLEEVE ANTENNA OPERATING IN UHF BAND of all antennas is 2.56 wavelengths at 5,000 MHz. A conventional dipole of this length would have multiple lobes. The simulation model and the photograph of the realized canonical triple sleeve antenna are shown in Fig. 7. The metallic portions of this antenna were fabricated using aluminum alloy. Poly-urethane foam (PUF) supports were used for the assembly of the antenna. The antenna was fed using a semi-rigid coaxial cable of 0.141-inch diameter. The coaxial cable was assembled with an SMA connector at one end as shown in Fig. 4. The VSWR measurement of canonical triple sleeve antenna is performed using a Vector Network Analyzer. The comparison of simulated and measured VSWR is given in Fig. 8. The antenna has VSWR \u2264 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002672_05.2019.91.20_175779-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002672_05.2019.91.20_175779-Figure5-1.png", + "caption": "Figure 5 \u2013 The linearity measurement of the bed: (a) overall scheme; (b) measuring magnifier", + "texts": [ + " It is equipped with a digital/analog display, and its internal mechanism is submerged in an oil-bath box. Achievable sensitivity of the level LE051 is 1 \u03bcm/m or 0.2 second of arc. It has 5 measuring scales providing resolutions from 250 \u03bcm/m per division down to 1 \u03bcm/m per division. The data can be transferred to a PC through the serial connections RS-232. Linearity of the bed with the fixed headstocks of the grinding machine was inspected using the collimator device with a string and measuring magnifier, presented in Figure 5. Moreover, the parallelism of the bed with fixed headstocks and the support was inspected. In the measurement, the electronic dial gauges (produced by Kordt) were used, with a resolution of 0.001 mm. They were placed on the grinding machine support and bed as illustrated in Figure 6. Similar electronic dial gauges were used in the measurement of the grinding disc runout as well as of the fixed headstocks. In the latter case, both radial and axial runout was measured. Additionally, the following parameters were inspected: parallelism between the axes of the disc cone during the headstock movement, distance between the vertical positions of the disc and headstock axes, runout of the disc cone, and the coaxiality of the fixed headstocks" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004385_aper_ETC2017-356.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004385_aper_ETC2017-356.pdf-Figure4-1.png", + "caption": "Figure 4: Stream lines in the NEWAC nozzle configuration (colors indicate velocity magnitude value, red:high, blue: low)", + "texts": [ + " These modifications, which were performed through CFD computations and experimental measurements, resulted in a more than 10% reduction of the outer pressure losses (the inner losses remained unaffected since the same basic HEX was used) which led to a relative reduction of specific fuel consumption of 1%. However, since these modifications were extended throughout the nozzle installation it became evident that limited optimization potential remained yet to be exploited by insisting on the same HEXs basic design and arrangement. Furthermore, the CFD computations revealed that strong recirculation regions were still present in the NEWAC nozzle configuration, as presented in Fig.4 (where the inlet of the hot-gas from and LTP and into the recuperator is indicated with red arrow), which led to strong swirl effects and additional pressure losses. As a result, alternative designs had to be conceptualized in order to try to further optimize the flow field development, reduce the pressure losses and enhance the achieved heat transfer. Trying to further optimize the recuperation installation, two alternative designs were conceptualized. For the design and investigations a customizable numerical tool modelling the recuperation system operational heat transfer and pressure loss characteristics was developed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002958_8600701_08662671.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002958_8600701_08662671.pdf-Figure7-1.png", + "caption": "FIGURE 7. Simulated radiation patterns of the two-element array: (a) E-plane and (b) H-plane of Antenna 1 working at 1.16 THz. (c) E-plane and (d) H-plane of Antenna 2 working at 1.41 THz.", + "texts": [ + " One can observe that there is strong induced current and field distribution on antenna 2 when antenna 1 is excited, and vice versa. More importantly, part of electric field is absorbed and guided through the high permittivity substrate. After inserting the FSS between the elements, the induced fields are efficiently blocked and the surface current density on terminated antenna is also been suppressed by the FSS decoupling structure, as shown in Fig. 6. The radiation patterns are also strongly affected due to the coupling between antenna elements. Fig. 7 shows the radiation patterns of Antenna 1 and 2 at the targeted working frequencies. Three cases are considered to validate the reduction of mutual coupling effects because of the FSS decoupling structure: an isolated antenna, an antenna in array without FSS and an antenna in array with FSS. Particularly, both the E-plane and H-plane patterns are given. In Fig. 7a and Fig. 7c, the E-planes of both antennas are slightly influenced due to the arrangement of the array elements. However, the coupling between the elements would strongly affect the H-plane of the radiation pattern, as shown in Fig. 7b and Fig. 7d. After inserting of the FSS structure, both radiation patterns are recovered well as if the antennas are originally isolated without coupling. The max variation of the gain values of both antennas is lower than 0.1 dB. The results reveal that the coupling effects have negligible influence on E-plane radiation pattern of antenna and FSS structure can efficiently recover the H-plane pattern. VOLUME 7, 2019 33219 B. MULTI-BAND GRAPHENE-BASED ARRAY WITH FOUR ELEMENTS For the case with four nano-antennas, three FSSs are employed for the reduction of coupling effects among the elements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001135_cle_download_672_566-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001135_cle_download_672_566-Figure4-1.png", + "caption": "Fig. 4. Particle trajectory (a). Shear stress on the surface of the cochlea (\u0431). Shear stress on the rotor (\u0432)", + "texts": [], + "surrounding_texts": [ + "SUPPORT IN CARDIAC SURGERY (REVIEW)" + ] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure1-1.png", + "caption": "Figure 1. Models The cross-section of disassembled three-dimensional (3D) model of SMzs200S32 motor, manufactured by \u0141ukasiewicz Research Network\u2013KOMEL Institute, and dedicated for assembly in wheel hub of car: 1\u2014rotor, 2\u2014rotor\u2019s magnetic core, 3\u2014magnet, 4\u2014stator\u2019s magnetic core, 5\u2014stator winding coil ends, 6\u2014resin, 7\u2014permanent anchoring shield, 8\u2014supporting structure, 9\u2014casing with coolant ducts, 10\u2014radiator of coil outhang, drive end, 11\u2014radiator of coil outhang, non-drive drive, 12\u2014brake drum, 13\u2014bearing assembly, 14\u2014entry for supply wires, 15\u2014cooling system ports, 16\u2014rotor assembly openings, 17\u2014stator assembly openings.", + "texts": [ + " The procedure proposed by the authors leads to the development of a proposal for a new engine solution with a significantly reduced mass, supported by a verified thermal model. This method allows for a more accurate approximation of design solutions to be put into production. Multi-pole motors with external rotors are often used for assembly in EV wheels. This is due to the character of space in the wheel, where the motor is placed. The electromagnetic circuit of such a motor is toroidal, so that additional space found inside this toroid may be used. The cross-section of the three-dimensional (3D) model of the discussed SMzs200S32 motor is shown in Figure 1. Most of the hull is the rotating element. It contains a magnetic core with mounted permanent magnets. The stationary element is the anchor disc with the supporting structure, in which there is a labyrinth cooling system. The stator\u2019s magnetic core with winding is mounted on the supporting structure (Figure 1). The motor is dedicated for assembly in a 17\u201d wheel rim. A rotor position sensor is required to control the motor. Typically, an incremental encoder is used. The space in which the electric motor must fit is limited by the dimensions of the wheel rim (outer diameter and motor length), while the inner diameter depends on how the space inside the toroid is used. In the case of the presented structure, this space houses the vehicle brake drum. The space containing the electromagnetic circuit is limited by the dimensions of the support structure, anchor shell, and rotor, which must be thick enough to ensure the required mechanical strength (Figure 1). Pictures of the prototype SMzs200S32 motor are shown in Figure 2. For research purposes, this motor was equipped with a number of PT100 temperature sensors, placed in various elements of the stator and rotor (permanent magnets). Additionally, a small wireless temperature recorder was developed. It is installed on the rotor surface and the sensor mounted on the magnet is connected to the recorder. Temperature can be registered continuously and data are sent wirelessly [34]. The cross-section of the motor with the positions of the temperature sensors is shown in Figure 3", + "5, the increased power losses in permanent magnets may lead to a situation, where the magnet temperature will limit the maximum load of the motor (especially when the motor is running with field weakened to increase the speed range [36]). Under field weakening conditions, magnets are exposed, not only to an increase in temperature caused by the magnitude and frequency of the supply current, but also to an external magnetic field. By increasing the number of pole pairs, we obtain a toroidal motor with an increased internal diameter. As a result, the weight is reduced and additional space is gained inside the motor, which can be used, for example, for mounting a car brake drum (Figure 1). The used Ansys Motor-CAD software (Ansys Canonsburg, Pensylwania, USA) greatly supports the design of electrical machines, because work simulations can be carried out in the entire working range of torque and speed. At the same time, it is distinguished by very high computing speeds. It is possible to solve conjugated electromagnetic and thermal fields. It uses a combination of advanced analytical equations and calculations based on 2D FEM. The temperature can be determined in steady and transient conditions; the program uses advanced models in the form of thermal networks [37\u201342]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure3-1.png", + "caption": "Figure 3. System of loads acting on the coulter.", + "texts": [ + " The calibration of the transducer was done on a test stand designed especially for the purpose of testing, making it possible to simplify the construction and the operating procedures of the developed measuring device. The basis for the development of the transducer is a system of actual loads acting on a working element in the form of two symmetrically positioned coulters. A coulter is a mechanical system in the form of a flexible beam, which is subjected to loads listed in the figure below (Figure 3). Longitudinal force F_1 generates a bending moment on the \u201cr\u201d arm, which is the main source of strain. Apart from the longitudinal force, there is also vertical force F_2. In order to record these loads, it is necessary to develop a dedicated measuring system, i.e., one that (1). can measure forces within a specific range (from 10 to 600 N), (2). has a natural frequency of vibration that is higher than usable frequencies (for reso- nance prevention). The proper selection of geometrical features of the transducer structure is a complex process, which requires multiple criteria to be taken into account" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.2-1.png", + "caption": "Figure 2.2 : 3-D section of a permanent magnet synchronous e-motor showing in black color the air spaces inside the machine.", + "texts": [ + " They show a relatively high resistivity to temperature compared to NdFeB, which makes them appropriate for use in high specific power synchronous machines where high temperatures may be easily attained. 2.2.2 Convection Mode In this paragraph, we are interested in presenting the numerical and experimental models (and resulting reliable correlations) elaborated by authors for setting the thermal parameters for convection heat transfer in the machine internal cavities. These cavities refer to the internal spaces between the rotor-stator configuration and the motor housing (black areas in Figure 2.2). The convection transfer inside the motor is divided into three main regions of convection in the motor: iv. The airgap between rotor and stator, v. The rotor end-disk, vi. The end-space regions (mainly the end-windings and the frame inner surfaces at both motor sides). Let us begin with general definitions in this field. Essentially, convection is the heat transfer mode where a fluid interacts with a surface such that the fluid and the surface exchange thermal energy. Three types of convection exist: natural, forced, and mixed convection types" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000872_f_version_1696935856-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000872_f_version_1696935856-Figure3-1.png", + "caption": "Figure 3. Schematics of the simulated systems. (a) Manipulator. (b) UAV.", + "texts": [ + " In this case, all cooperative inputs are multiplied by 1 \u03b7i and the damping on the cooperative coordinates is scaled accordingly. The resulting cooperative behavior corresponds to a heavier or lighter cooperative system. In the following section, we provide a qualitative comparison between IDA-PBC and r-PBC in simulation, with and without communication delays. We also provide results for the case of underactuated systems (IDA-PBC) and subtask optimization (r-PBC). To compare the two methods, we consider a scenario with two robotic manipulators, each with three joints as depicted in Figure 3a. The control objective is to reach consensus z1 = z2 in the 2-dimensional plane, without specifying a convergence point a priori. We define the inputs and joint-coordinates as the torque and angle of each joint, respectively. The end-effector dynamics of this system are nonlinear and the states have a redundant degree-of-freedom; hence, it is suitable to illustrate both approaches. For completeness, we first derive a model for the manipulator. Denote by xk, yk the center of gravity, by mk the mass, by lk the length and by Ik the inertia each of link k, and let \u03b3k = q1 + ", + " For r-PBC, the transient behavior has changed. The cooperative energy is dissipated in distinct waves. This is clearly visible in the coordinates of the blue manipulator, which decays exponentially within a distinct set of time intervals (most visibly around 1 and 3 s). Nevertheless, the convergence rate is unaffected. To illustrate cooperative IDA-PBC with underactuated and fully actuated systems, we replace one of the manipulators with an Unmanned Aerial Vehicle (UAV) moving in the x,y-plane (see Figure 3b). The system is actuated by a thrust force and a rotation in the plane around its center. Since thrust force is vertical with respect to the vehicle frame, it cannot move in all directions instantaneously and is underactuated. The cooperative endeffector is a point on the landing gear of the UAV at a distance \u03b5 below its center of rotation. For completeness, we give the model and single-agent IDA-PBC solution; more details are given in [29], Chapter 11. The UAV joint configuration is defined by its x, y position (q1, q2) and its orientation (q3)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002053_e_download_2200_1306-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002053_e_download_2200_1306-Figure10-1.png", + "caption": "Figure 10: Attachment to shin pad", + "texts": [], + "surrounding_texts": [ + "The routing system must also be connected to a harness attached to the user\u2019s waist in order to hold the system up, and this is where the servo used to provide strength will be located. ISSN: 2167-1907 www.JSR.org 8 As seen from figure 11, the initial design of the attachment connects the harness together with the servo through the use of a basic 3D printed attachment that fastens the two together with a screw. However, as seen from figure 12, the distance between the servo and harness is quite significant in this design and had to be accounted for using small plastic placeholders as seen in figure 11. This is due to the size of the reel, as the reel is significantly larger than the servo, meaning extra space had to be added so that the reel wouldn\u2019t collide with the harness or user. Therefore, the overall structure of the system is much looser and weaker and is much more susceptible to being damaged or changing form while in use, leading to a much shorter overall life span." + ] + }, + { + "image_filename": "designv8_17_0002047_download_25756_11867-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002047_download_25756_11867-Figure1-1.png", + "caption": "Figure 1. Geometry of the design antenna", + "texts": [ + " 3, June 2024: 510-518 512 that the proposed antenna configurations yielded performance metrics closely aligned with those of earlier studies conducted at the same frequency. This substantiates the efficacy of the proposed antenna design. Positioning it as an ideal candidate for deployment in 5G wireless communication systems. The enhanced gain, directivity, and bandwidth characteristics contribute to the antenna\u2019s potential to meet the evolving demands of advanced and efficient wireless communication technologies. The schematic representation of the antenna\u2019s structure is presented in Figure 1. The antenna under consideration is manufactured on a 1.6 mm thick dielectric substrate composed of FR-4 material. It covers a spatial extent of 24\u00d734 mm\u00b2 and is connected through a 50 \u03a9 impedance strip line. The substrate is characterized by a relative permittivity (\u03b5r) of 4.4 and a loss tangent of 0.02. The circular monopole antenna is designed using the (1)-(2) outlined in the methodology. In these equations the radius of the circular patch is denoted as \u2018a\u2019, the dielectric constant of the substrate is represented by \u2018\u03b5r\u2019, and the substrate thickness measured in millimeters is indicated by \u2018h\u2019 [22], [23]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000470_onf_eece18_07007.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000470_onf_eece18_07007.pdf-Figure2-1.png", + "caption": "Fig. 2. MBS models of the front (a) and rear (b) suspension.", + "texts": [ + " Bringing a system of algebraic nonlinear equations characterizing the relations in the system under consideration: ( ) ( ) ( ) ( ) ( )( )1 2 1 0 , , , , , , T n n i x F x f x f x f x f x R = = \u2026 \u2208 \u2208\u0440 (5) Having linearized system (5), we obtain, retaining the linear terms ( ) ( ) ( )( ) ( )0 0 0 0F x F x F x x x o x x= + + \u2212\u2032 \u2212 (6) Where the matrix of derivatives has the standard form ( ) ( ) ( ) ( ) ( ) ( ) 1 1 1 1 , , , , n n n n f x f x x x F x F x x f x f x x x \u2202 \u2202 \u2026 \u2202 \u2202 \u2202 = = \u2026 \u2026 \u2026 \u2202 \u2202 \u2202 \u2026 \u2202 \u2202 \u2032 (7) Then the Newton-Raphson method for solving the resulting system (5) has the following standard form: ( ) ( )11k k k kx x F x F x \u2212 + = \u2032\u2212 (8) MBS models of front and rear suspensions were implemented, as indicated, in the MSC.ADAMS software package. Above all elements of the model have mass-inertial characteristics and are connected to each other at the hardpoints of the suspension [14-17]. In addition the type and composition of the considered models is presented in Fig. 2. The MacPherson type front suspension has 20 key points (excluding steering). Taking into account symmetry, one half of the suspension has 10 independent hardpoints (Fig. 2a). The connection points between the lower wishbone and the subframe are designated as hardpoints 1 and 2, the connection point of the lower wishbone and the upright is 3, the shock absorber strut points are 4 and 5, the stabilizer mount point to the subframe is 6, the stabilizer strut points are 7 and 8, the steering point traction - 9 and 10. The double wishbone rear suspension has 20 key points. Given symmetry, one half of the rear suspension has 10 independent anchor points (Fig. 2b). The connection points between the lower arm and subframe are designated as hardpoints 1 and 2, the connection point of the lower arm and upright is 3, the connection points between the upper wishbone and subframe are 4 and 5, the connection point of the upper wishbone and upright is 6, the shock absorber points are 7 and 8, tie rod points - 9 and 10. Mutual arrangement of hardpoints affects the operational characteristics of the suspension. Based on the suspension models, some quasi-static K&C events have been simulated in ADAMS/Car [18]: - Vertical motion \u2013 A displacement controlled parallel wheel movement over a specified jounce interval (max jounce / max rebound movement)", + " Consequently, obtaining a significant correlation in this case will require significant resources. Therefore, in this work, we considered the key points most susceptible to displacement during the production and assembly of the car, and also which do not have the ability to adjust after assembly. Among them: the point of attachment of the wishbones on the frame, as well as the point of connection of the steering link with the steering rack. So for the front suspension, these are points 1,2,9 in Fig. 2a, for the rear suspension - points 1,2,4,5,9 in Fig. 2b. In fact to find the critical displacements of the suspension points, changes in their coordinates by \u00b1 5 mm along one axis were considered. Changes occur in two directions: Y or Z. The displacement along the longitudinal axis X was not considered due to the small effect on the K&C parameters. Thus, for each point, 5 possible positions are determined: initial, shifted to the left (y-5), shifted to the right (y+5), raised vertically (z + 5), dropped vertically (z-5). In Fig. 4 below are selected suspension points and their displacements are illustrated" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004334_f_version_1614604730-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004334_f_version_1614604730-Figure14-1.png", + "caption": "Figure 14. Reduced stress contour lines in the lower part of the container, according to Huber and Mises hypothesis [MPa] (a) hopper area of the fluidized bed material tank; (b) the hopper weld area of the fluidized bed material reservoir where the crack has occurred", + "texts": [ + " The thermal gradient of the boiler\u2019s casing that occurred in consequence, as well as the rise in air temperature inside the container\u2014which translated into the rise in air pressure\u2014both contributed to the emergence of cracks in the area of weld lines on the fuel hopper and sudden damage of its upper part that followed. Strength analysis was performed for the following air pressure values: 5 kPa, 10 kPa, 15 kPa, . . . , 50 kPa (values increased by 5 kPa). Impact strength of approximately 200 MPa was assumed for the observed low quality of weld lines on the fuel hoppers. The strength analysis showed that at air pressure inside the container equal to 50 kPa and at uneven thermal impact that occurred simultaneously, reduced stress in the area of hopper weld lines reached approximately 270 MPa (Figure 14). This contributed to the breaking of the discussed area of the container 8z. At the same time, reduced stress in the container\u2019s upper part was observed at approximately 870 MPa (Figure 15). The latter observation, along with the fact that the tests performed prove the ultimate strength of steel S235 to be at the level of 315 MPa, means that this area experienced a sudden discontinuity of the investigated object\u2019s casing [20]. The strength analysis also showed clearly that as the air pressure inside the container rose to approximately 50 kPa and the casing heated unevenly, the casing broke in its both upper and lower parts", + " - Inspections of welded joints were performed only in available places, on the unit\u2019s main elements, i.e., on the load-bearing structure, second pass chamber, cyclone, ash removal system, air ducts, auxiliary elements, etc. As indicated in the article, much attention was paid to the levels on which the fire wave passed. The passing fire wave caused greatest damage in front of the unit, at the coal and biomass supply galleries. Coal and biomass ignition in the space between the units generated soot, which combined with ash and water was used to extinguish the fire and produced compressed mass (Figure 14). The mass had the consistency of concrete and covered electric wires placed in conduits. The wires that were laid in conduits close to each other stopped the flowing mass, which set shortly. This phenomenon was observed only on the 6m level of the power unit [20]. Author Contributions: Conceptualization, M.P.; methodology, A.G.; software, M.P. validation, M.P.; formal analysis, A.G., M.P.; investigation, A.G.; resources, A.G.; data curation M.P.; writing\u2014original draft preparation, A.G., M.P.; writing\u2014review and editing, M" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002929_ticles_srep09113.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002929_ticles_srep09113.pdf-Figure2-1.png", + "caption": "Figure 2 | The topology of the proposed antenna. (a)\u2013(b) The geometry of the proposed antenna. (c) The air horn (an empty horn filled with the air) and the comprising metamaterials. (d) The photograph of the meta-horn. The detailed dimensions (unit: mm) are: A 5 47.55, B 5 22.15, C 5 90, D 5 86, L 5 82, and T 5 4.", + "texts": [ + " According to the energy conservation law, we can obtain Pa(ra)~ Pf (h)sinhdh radra : \u00f04\u00de It is obviously shown that the refraction index of the lens determines the distribution of the aperture field. Therefore, we can manipulate the distribution of the aperture field over the aperture of the GRIN lens through tailoring the refractive index distribution. Design of the metamaterial-loaded horn antenna. The performance of a pyramidal horn antenna can be improved using the proposed approach of manipulating aperture field. By loading a GRIN metamaterial lens inside a pyramidal horn, we succeed to suppress the side lobes of the far-field radiation patterns. Figure 2 illustrates the geometry and the photograph of the metamaterial- loaded antenna. Notice that equivalent media are used to replace metamaterials for design, since the theory of the equivalent theory of the metamaterial is able to efficiently simplify the process22. The metamaterial lens consists of a core layer (CL) and two impedance matching layers (IMLs). Following, the design of the loaded GRIN lens using equivalent media and its physical implementation are demonstrated in detail. It is well known that the radiation patterns of an antenna are determined by its aperture field. In the traditional horn, the amplitude of tangential component of the aperture field is approximated by following forms:23 Ey(x,y) ~E0 cos ( p C x) Hx(x,y)j j~ E0 g cos ( p C x) 8>< >: , \u00f05\u00de where C is aperture dimension of the pyramidal horn along x direction (see Fig. 2(a)). From Equation 5, we can obtain that the E-field on the aperture of an air horn (the empty pyramid horn) is nearly uniform in E-direction (y direction) and tapered in H-direction (x direction), as simulated in Fig. 3(a) or (c). This results in narrow beamwidth and high side-lobes in the E-plane. In order to reduce the side-lobe level in the radiation pattern, tapered distribution in E-direction is also required. GRIN metamaterial lens are adopted to the horn to modify the aperture field distribution in E-direction, making the amplitude SCIENTIFIC REPORTS | 5 : 9113 | DOI: 10", + " For the substrate with thickness t1, the refractive index varies from 1.16 to 1.7 when the length of the strip changes from zero to 5.9 mm. While for the substrate with thickness t2, the refractive index varies from 1.11 to 1.29 corresponding to the length of the strip increasing from zero to 5 mm. Therefore, the refractive index can cover the target refractive index distribution. Finally, the metamaterial-loaded antenna is composed of two parts \u2013 one is the pyramid horn with 16 parallel narrow slots cut along the walls (as shown in Fig. 2(b)), and the other is 8 pieces of metamaterial slices with different scales (as shown in Fig. 2(c)). The slices are made of Rogers RO4350B with printed metallic strips on it, and constructed inside the pyramid horn as shown in Fig 2(d). The core layer includes 4 slices and the IMLs include 4 slices. The shape of each slice is designed to evenly match the horn, as illustrated in Fig. 4(d) for Figure 3 | Electric field in E-plane of horns and amplitude of the electric field on the aperture. (a) (c) The air horn, (b) (d) The horn loaded with equivalent media. SCIENTIFIC REPORTS | 5 : 9113 | DOI: 10.1038/srep09113 3 example. The separation between the slices is 6 mm, which is one tenth of the wavelength at the center frequency of f0 5 5 GHz" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000517_f_version_1587772466-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000517_f_version_1587772466-Figure1-1.png", + "caption": "Figure 1. The machine node (schematically).", + "texts": [ + " In addition, by transfer functions, simply converting them into frequency transfer functions, obtain the amplitude-phase frequency characteristics (Nyquist diagram) and conduct frequency analysis for any link in the dynamic system. During observations of the boring process, we found that it is advisable to include the following bodies in the design scheme: \u2022 machine support with a tool holder; \u2022 boring mandrel; \u2022 inertial body (damper). The characteristics of the listed bodies (mass, fixing rigidity or damping coefficient) significantly affect the oscillations of the tool cutting part. Figure 1 shows the machine node for which the calculation is made. General theoretical principles for such vibrational systems study have been considered in works [41\u201344], on the basis of which this study has been based. Materials 2020, 13, x FOR PEER REVIEW 3 of 13 vibration mandrels with dynamic vibration dampers are typically used for boring holes up to 14 \u00d7 D in depth. The claimed increase in productivity when using such mandrels is from 50% to 400%, depending on the range of depth/diameter ratios. Some of the existing solutions have the ability to configure the mandrel for a specific situation with the selected cutting conditions and the workpiece parameters", + " In addition, by transfer functions, simply converting them into frequency transfer functions, obtain the amplitude-phase frequency characteristics (Nyquist diagram) and conduct frequency analysis for any link in the dynamic system. 2. Design of Mathematical Model During observations of the boring process, we found that it is advisable to include the following bodies in the design scheme: \u2022 machine support with a tool holder; \u2022 boring mandrel; \u2022 inertial body (damper). The characteristics of the listed bodies (mass, fixing rigidity or damping coefficient) significantly affect the oscillations of the tool cutting part. Figure 1 shows the machine node for which the calculation is made. General theoretical principles for such vibrational systems study have been consider d in works [41\u201344], on the basis of which this study has been based. Figure 1. The machine node (schematically). We created the mathematical model of the system and we consider it as the system of interacting bodies connected by a viscoelastic coupling. In this case, the mandrel is divided into 2 parts: a less rigid hollow part, in which the damper is placed, and a more rigid part. We consider the system oscillations under the action of the variable radial component of the cutting force Py, which, for simplicity, will be denoted by P. The deformation in the direction of the force Py is the most critical from the point of the view of item size accuracy, waviness and surface roughness" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000074_8948470_09035441.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000074_8948470_09035441.pdf-Figure7-1.png", + "caption": "FIGURE 7. Structural configuration and dimensions of the superstrates in front of the RF layer.", + "texts": [ + " A 1:4 power divider and four 5-bit digital phase-shifters are incorporated in the multi-channel phase shifter. Finally, the output RF signals are fed to each element of the antenna array. Compared with conventional RF transmitter chip sets with a phase shifter and a power amplifier for each antenna element, the proposed RF front end has less integrated chips and occupies a smaller area. Subsequently, the next step is to determine the superstrates composed of the upper face-sheet and lower foam depicted in Fig. 7. The thickness of the super-strates locating above the antenna array not only contributes to the structural stiffness and strength, but also influences the 52362 VOLUME 8, 2020 electromagnetic performance. In order to meet the mechanical and electrical requirements simultaneously, the electromechanical co-design method is developed to design the super-strates.Tables 1 and 2 give the electrical and mechanical properties of the materials used in the antenna structure. The coarse thicknesses of the facesheet and foam are optimized by the electromechanical co-design method in [34]", + " The coarse thickness can provide an optimal structural stiffness and strength. However, it cannot guarantee an optimal design for the electromagnetic performance of the antenna array with the super-strates. In the last step, the coarse dimensions were applied to develop a full-wave electromagnetic model using the commercial simulation software HFSS from ANSYS. The thicknesses of the face-sheet and foam were further optimized and the final dimensions of the super-strates are determined as indicated in Fig. 7. C. DESIGN OF MICRO-CHANNEL HEAT SINK As mentioned above, high-power amplifiers are adopted in the Tx modules to enhance the signal power level. However, each amplifier is a heat source, which could influence the electrical performance of the active antenna array. In this work, a micro-channel heat sink is designed to cool the RF front end. Figure 8 shows the structural configuration of the micro-channel heat sink which consists of a micro-channel inlet header and a micro-channel outlet header, eight small micro-channels, an inlet and an outlet" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003816_er.asee.org_4279.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003816_er.asee.org_4279.pdf-Figure2-1.png", + "caption": "Figure 2. Turbine Technologies SR-30 Major Engine Components 1", + "texts": [ + " During this experiment the students actually learn how to operate a gas turbine engine, collect and analyze the output data and relate the result to the theory learned in the thermodynamics courses. The broader educational objectives are to improve the students\u2019 understanding of thermodynamics, to help them integrate this knowledge with other subjects, and to give them a better basic understanding of how a gas turbine engine works. P age 13.721.2 The gas turbine experiment was conducted using the SR-30 turbojet engine manufactured by \u201cThe Turbine Technologies, LTD\u201d; a cut-away view of the SR-30 model gas turbine engine is shown in Figure 1.and its major engine components are shown in Figure 2. The SR-30 turbo jet engine is comprised of: 1. A single stage axial flow turbine, 2. Radial flow compressor and 3. Reverse flow annular combustion chamber. 4. The engine is of single shaft design. 5. Both the compressor and turbine rotate on the shaft at the same speed. 6. The engine is fully throttleable from an idle speed of 45,000 rpm to a maximum speed of up to 90,000 rpm. P age 13.721.3 Aircraft gas turbines operate on an open cycle, as shown in Figure 3, called jet- propulsion cycle. The ideal jet-propulsion cycle differs from the simple ideal Brayton cycle in that the gases are not expanded to the ambient pressure in the turbine" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002155_ulture2024_02028.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002155_ulture2024_02028.pdf-Figure5-1.png", + "caption": "Fig. 5. Diaphragm type throttle flow divider with hydraulic locking", + "texts": [ + " Figure 4 shows the design of the throttle flow divider, in which the functions of the shutoff and control element are performed by a flexible diaphragm element with a rigid center in combination with adjustable hydraulic resistances of the flat valve type. This divider has mechanically interlocked set points - the same membrane simultaneously participates in the control of variable resistances of both branches. There are known designs of flow dividers using variable hydraulic resistances such as a flat valve with hydraulic locking [8], the scheme of such a flow divider is shown in Figure 5. Here, to control the variable resistances of each branch, its own membrane elements are used, connected to each other hydraulically by means of a liquid enclosed in a closed volume. There are completely no movable rubbing pairs, which significantly increases the reliability of their operation and eliminates the influence of the quality of the working fluid on the control process. However, the adjustable pressure drop in them, as in dividers manufactured according to the scheme shown in Figure 4, affects the shut-off and control element, causing an increased synchronization error" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000098_ats.2023.1096839_pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000098_ats.2023.1096839_pdf-Figure13-1.png", + "caption": "FIGURE 13 Total deformation on half fuselage of RUAV with Epoxy-Carbon-Woven-Wet.", + "texts": [], + "surrounding_texts": [ + "The typical relationship between mechanical power required and its subordinates of drone design parameters is given in Eq. 4 (Mathaiyan et al., 2021; Murugesan et al., 2021; Raja et al., 2021; Senthilkumar et al., 2021; Raja et al., 2022a; Vijayanandh et al., 2022a; Raja et al., 2022b; Raja et al., 2022c; Raja et al., 2022d; Raja M. K. et al., 2022; Wang et al., 2022; Raja et al., 2023). FIGURE 11 Ultimate equivalent stress of CFRP woven based test specimen. Frontiers in Materials frontiersin.org09 P k*RMR 3*D4*p (4) 31349.2284 5.3 *10\u221215*RMR 3* 36( )4*pMR0Pitch pMR( ) 3521607769107.33235 RMR 3 Eq. 5 is representing the dynamic thrust relationship for drone, wherein the design parameters of propellers are plays major role. To proceed further, the additional unknowns presented are reduced through comparative relationship approach (Mathaiyan et al., 2021; Murugesan et al., 2021; Raja et al., 2021; Senthilkumar et al., 2021; Raja et al., 2022a; Vijayanandh et al., 2022a; Raja et al., 2022b; Raja et al., 2022c; Raja et al., 2022d; Raja M. K. et al., 2022; Wang et al., 2022; Raja et al., 2023). T 4.392399*10\u22128*RMR* d3.5( ) pMR \u221a * 4.23333*10\u22124*RMR*pMR \u2212 Ve[ ] (5) 1119.6153 4.392399*10\u22128*RMR* 36( )3.5( ) pMR \u221a * 4.23333*10\u22124*RMR*pMR \u2212 25[ ] RMR 2.5*0.0000001638061[ ] \u2212 RMR[ 0.5*9.76817] + 1119.6153 00RMR 3678 Frontiers in Materials frontiersin.org10 From the literature survey it was found that propeller hub thicknesses are varies from 48.9 mm to 50 mm, the internal diameter of hub is 32 mm, and external diameter of hub is 50 mm. From the base of pitch description, the pitch relationship is expressed in Eq. 6 (Mathaiyan et al., 2021; Murugesan et al., 2021; Raja et al., 2021; Senthilkumar et al., 2021; Raja et al., 2022a; Vijayanandh et al., 2022a; Raja et al., 2022b; Raja et al., 2022c; Raja et al., 2022d; RajaM. K. et al., 2022; Wang et al., 2022; Raja et al., 2023). pMR InducedVelocity in inch s Revoution Per Second inch/s revolutions/s inch revolution (6) pMR 984.252 61.29999997548 16 inch" + ] + }, + { + "image_filename": "designv8_17_0000266__titds2023_05005.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000266__titds2023_05005.pdf-Figure1-1.png", + "caption": "Fig. 1. Sections of the caterpillar bypass: lfr - free branch, lw - working branch, lre - reference branch.", + "texts": [ + " In turn, the caterpillar bypass is divided into several sections: the reference branch lre (through which the weight of the TTV is transferred to the bearing surface), the working branch lw (which transmits traction and is located from the reference branch to the drive wheel) and the free branch lfr (which is not loaded with force traction and is located from the drive wheel to the supporting branch). Moreover, the length of the free and working branches depends on the location of the drive and guide wheels. On Figure 1 shows a bypass scheme with a rear drive wheel. The constant component of tension forces in the free branch of the bypass [13]: .fr pr cT \u0422 \u0422 (1) Tension forces in the working branch [13]: w fr vkT \u0422 \u0420 (2) In a static position, when the bypass is stretched by the pretension force, the length (perimeter) of the bypass Sby is equal to the length of the caterpillar (taking into account the deformation of the hinges): ,fr w cat cat cat fr cat w \u0422 \u0422 S z t \u0441 l \u0441 l (3) where z is the number of tracks in the caterpillar, tcat is the track pitch, cgus is the specific longitudinal stiffness of the caterpillar" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure42-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure42-1.png", + "caption": "Figure 42 P-POD Mk. III Rev. E Back Plate", + "texts": [ + " This is because of certain Page 58 containment requirements, along with mounting interfaces that make the part more robust than it needs to be for the loads themselves. P-POD Mk. IV Back Plate The next part analyzed was the Back Plate, that makes up the \u2013Z face of the P- POD. In the past, this part was strengthened due to concerns with the screw interfaces having high stress concentrations, making the exterior walls thicker and taller, and adding more screws. The P-POD Mk. III Rev. E P-POD is shown below in Figure 42. These changes made the part very strong, but the thick, tall walls are only needed for areas where fasteners are located. In an effort to save mass, parts of the walls not near Page 59 mounting screws or other features were thinned but remained constant height with the rest of the part. Additionally, four standoffs were added to streamline the implementation of a gaseous purge system or the Power-On system. If either system is required, the part can simply be sent out and have mission specfic holes drilled into it" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004177_-3-319-44431-4_5.pdf-Figure5.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004177_-3-319-44431-4_5.pdf-Figure5.8-1.png", + "caption": "Fig. 5.8 (a) The aperture of an east\u2013west, two-element interferometer. The corresponding spatial frequency coverage for cross-correlated signals is shown by the shaded areas in (b). If the antennas track the source, the spacing vector traces out an elliptical locus (the solid line) in the .u; v/ plane. The area between the broken lines in (b) indicates the spatial frequencies that contribute to the measured values. The spacing between the broken lines is determined by the cross-correlation of the antenna aperture.", + "texts": [ + " The spatial frequency coverage is the same as would be obtained in a single observation with an antenna of aperture equal to that simulated by the movement of the small antenna, although the magnitude of the spatial sensitivity is not exactly the same. The term aperture synthesis was introduced to describe such observations, but to be precise, it is the autocorrelation of the aperture that is synthesized (see Sect. 5.4). The range of spatial frequencies that contribute to the output of an interferometer with tracking antennas is illustrated in Fig. 5.8b. The two shaded areas represent the cross-correlation of the two apertures of an east\u2013west interferometer for a source on the meridian. As the source moves in hour angle, the changing .u; v/ coverage is represented by a band centered on the spacing locus of the two antennas. Recall from Sect. 4.1 that the locus for an Earth-based interferometer is an arc of an ellipse, and that since V. u; v/ D V .u; v/, any pair of antennas measures visibility along two arcs symmetric about the .u; v/ origin, both of which are included in the spatial transfer function" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003743_load.php_id_12051019-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003743_load.php_id_12051019-Figure14-1.png", + "caption": "Figure 14. Measured normalized radiation patterns using a rotating linear source at frequencies within the UHF band (a) 860MHz, (b) 910 MHz, and (c) 960 MHz.", + "texts": [], + "surrounding_texts": [ + "The fabrication and measurement of the prototype antenna with chosen dimensions was completed in the Antenna and Microwave Laboratory (AML) at San Diego State University which has an Anritsu Vector Network Analyzer (VNA) model #37269D and an anechoic chamber of 2.4\u00d72.4\u00d73.6meter3 size with measurement system from Orbit F/R. A perspective and bottom view of the fabricated model is displayed on Figure 12(a). The hybrid network on FR-4 substrate was fabricated using LPKF milling machine including drilling of the via holes at the appropriate positions. The microstrip patch with the center crossslots and truncated corners are sitting on a 11.2 mm thick layer of Cuming foam (\u03b5r = 1.06) substrate. Single sided adhesive copper tape is employed for the patch fabrication. A metallic wire was then soldered inside the via holes to realize the via connections. Figure 12(b) shows the antenna under test (AUT) placed inside the anechoic chamber for radiation pattern measurements. For convenience in the fabrication process, the patch is sitting on an 11.2 mm thickness layer of foam (\u03b5r = 1.06). Figure 12(b) shows the antenna under test (AUT) placed inside the anechoic chamber for measurement of the radiation patterns. The comparison of the measured and simulated reflection coefficients and axial ratio (AR) of the fabricated antenna are shown in Figures 13(a) and 13(b), respectively. The measured reflection coefficient magnitude (Figure 13(a)) covers a band from 840 to 1150MHz with respect to (w.r.t) S11 \u2264 \u221210 dB which yields a percentage bandwidth of 31.2% and agrees well with the simulated result of 830 to 1130 MHz (30.6%). The measured AR versus frequency at broadside angle (\u03b8 = 0\u25e6) was obtained after post-processing of the rotating linear patterns following the technique described in [29]. The measured data (Figure 13(b)) exhibited AR better than 3 dB for the entire UHF RFID band and a percentage bandwidth better than 23% from 840 to 1050 MHz. The normalized measured rotating linear radiation patterns are shown in Figures 14(a) to 14(c) for three different frequencies within the UHF band: 860MHz, 910MHz, and 960MHz. A fairly wide AR beamwidth w.r.t. AR \u2264 3 dB of 60\u25e6 is obtained for the three cases which suggest wide angular coverage for the RFID reader. The cross-polarization rotating linear components are not included with the plots because figure becomes too crowded. The presented patterns are directional and almost symmetric as expected for this antenna." + ] + }, + { + "image_filename": "designv8_17_0000762_article-file_1262493-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000762_article-file_1262493-Figure1-1.png", + "caption": "Figure 1- Three point linkage mechanism: a, three point linkage geometry; b, position of mast and lower link, and forces acting on these elements, during ploughing with forces", + "texts": [ + " Built in control system allows control of the implement position and/or draft force. Fully mounted implement carries over forces to the three-hitch point. The intensity of the force depends on the position of hitching point and length of the links. Variations of the force in upper link with its length were shown by \u010cupera et al (2011). Tractor manufacturer usually has a test report of link length and pivot point position, measured from the rear wheel axis center. Side view of three point linkage with example of its dimensions is presented in Figure 1a. The goal of present study was to estimate forces acting on the three hitch point. Background data includes known three point linkage geometry (l1\u00f7l6) and position (\u03b11\u00f7\u03b15), estimated soil resistance (Rx, Ry, c1, c3), plough weight (G, c2) and tractor rearwheel radius (R). Position of three point linkage is determined by ploughing depth. It is not necessary to measure distance from all hitch points to the ground, but only the distance from lower link to the ground l7, because the mast height l6 is already known, Figure 1b. Equations (3)\u00f7(7) were developed to determine three point positions with input data presented in Figure 1a. \ud835\udefc1 = \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc445 (3) \ud835\udefc2 = \ud835\udc4e\ud835\udc50\ud835\udc5c\ud835\udc60 [(\ud835\udc594 2 + \ud835\udc441 + \ud835\udc592 2 \u2212 2 \u2219 \ud835\udc441 1/2 \u2219 \ud835\udc592 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udf0b + \ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc442 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443) \u2212 \ud835\udc593 2)/ (2 \u2219 \ud835\udc594(\ud835\udc441 + \ud835\udc592 2 \u2212 2 \u2219 \ud835\udc441 1/2 \u2219 \ud835\udc592 \u2219 cos(\ud835\udf0b + \ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc442 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443)) 1/2 )] + \ud835\udc4e\ud835\udc50\ud835\udc5c\ud835\udc60 [(\ud835\udc592 \u2212 \ud835\udc441 1/2 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udf0b + \ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc442 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b \ud835\udc443)) /(\ud835\udc441 + \ud835\udc592 2 \u2212 2 \u2219 \ud835\udc441 1/2 \u2219 \ud835\udc592 \u2219 cos(\ud835\udf0b + \ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b \ud835\udc442 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443) 1/2 ] (4) \ud835\udefc3 = \ud835\udc4e\ud835\udc50\ud835\udc5c\ud835\udc60[(\ud835\udc596 2 + \ud835\udc595 2 \u2212 \ud835\udc444 \u2212 \ud835\udc591 2 + 2 \u2219 \ud835\udc444 1/2 \u2219 \ud835\udc591 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc445 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443)/(2 \u2219 \ud835\udc595 \u2219 \ud835\udc596)] (5) \ud835\udefc4 = \ud835\udc4e\ud835\udc50\ud835\udc5c\ud835\udc60 [(\ud835\udc591 \u2212 \ud835\udc444 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc445 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443))/ (\ud835\udc444 + \ud835\udc591 2 \u2212 2 \u2219 \ud835\udc444 1/2 \u2219 \ud835\udc591 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc445 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443)) 1/2 ] + \ud835\udc4e\ud835\udc50\ud835\udc5c\ud835\udc60 [(\ud835\udc596 2 \u2212 \ud835\udc595 2 + \ud835\udc444 + \ud835\udc591 2 \u2212 2 \u2219 \ud835\udc444 1/2 \u2219 \ud835\udc591 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc445 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443)) / (2 \u2219 \ud835\udc596 \u2219 (\ud835\udc444 + \ud835\udc591 2 \u2212 2 \u2219 \ud835\udc444 1/2 \u2219 \ud835\udc591 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udc4e\ud835\udc61\ud835\udc4e\ud835\udc5b\ud835\udc445 + \ud835\udc4e\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udc443)) 1/2 )] (6) \ud835\udefc5 = \ud835\udefc1 + \ud835\udefc4 \u2212 \ud835\udf0b 2 (7) Where; \ud835\udc441 = (\ud835\udc652 \u2212 \ud835\udc651) 2 + (\ud835\udc662 \u2212 \ud835\udc661) 2; \ud835\udc442 = \ud835\udc662\u2212\ud835\udc661 \ud835\udc652\u2212\ud835\udc651 ; \ud835\udc443 = \ud835\udc45\u2212\ud835\udc597+\ud835\udc661 \ud835\udc591 ; \ud835\udc444 = (\ud835\udc653 \u2212 \ud835\udc651) 2 + (\ud835\udc663 \u2212 \ud835\udc661) 2; \ud835\udc445 = \ud835\udc663\u2212\ud835\udc661 \ud835\udc653\u2212\ud835\udc651 ; Vertical component of soil force for moldboard can be related with draft force (Martinov & Markovi\u0107 2002): \ud835\udc45\ud835\udc66 \u2248 0", + " The center point of soil resistance T4 on a mouldboard plough is located halfway along the slice width and one-third of the ploughing depth by Bernacki & Haman (1967), while Wilkinson & Braunbeck (1977) placed center of soil resistance on one-fourth of the slice width from landside and one-fourth of the ploughing depth. 274 Journal of Agricultural Sciences (Tar\u0131m Bilimleri Dergisi) 26 (2020) 271-281 Implement motion is limited by three-point linkage, except it has freedom to rise up. By knowing the moving pattern (Equations (3)-(7)), it is possible to calculate forces acting on the three hitch point for each working position. The calculations only take into account the simplified 2D model of loading. Loading scenario for the mast and lower link is presented in Figure 1b. Uniform motion of tractor is assumed in this analysis, so there is no inertial force. Newton\u00b4s second law gives three independent equations of equilibrium needed to determine the forces acting on the mast. \ud835\udc391 = (\ud835\udc45\ud835\udc65 \u2219 \ud835\udc503 \u2212 0,1 \u2219 \ud835\udc45\ud835\udc65 \u2219 \ud835\udc501 \u2212 \ud835\udc3a \u2219 \ud835\udc502)/(\ud835\udc596 \u2219 \ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udefc3)) (9) \ud835\udc3b = (\ud835\udc45\ud835\udc65 + \ud835\udc391 \u2219 \ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udefc3 + \ud835\udefc5))/2 (10) \ud835\udc49 = (\ud835\udc3a + 0,1 \u2219 \ud835\udc45\ud835\udc65 \u2212 \ud835\udc391 \u2219 \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udefc3 + \ud835\udefc5))/2 (11) Where; \ud835\udc391 \u20d7\u20d7 \u20d7 is the force acting on upper link hitch point, while H and V are horizontal and vertical component of force acting on both lower link hitch point", + " After entering all data in Goryachkin Equation (1), it became obvious that the second term of the formula is dominant for small working velocity. Based on Eqs. (1)\u00f7(11) and presented data, the computer algorithm was developed for approximate calculation of average longitudinal and vertical forces in the lower link and force in the upper link, Figure 4. An important role in the transfer of forces acting on a plough onto the links has the links geometry and position. Lengths of all links and pivot point position (sketched in the Figure 1a) were entered into the Fortran program (Adams et al 1997). After the position of links were calculated according to Eqs. (3)\u00f7(7), the program prompts how to calculate the draft: only by Equation (2) or by both Equations (1) and (2). Applied Eqs. (8)\u00f7(11) gave a simplified solution for forces. The program has a loop for estimation of average horizontal and vertical forces acting on the lower link and force acting on the top link for different soil depths and tractor velocities. Horizontal and vertical force dependence on the tillage depth and working velocity is presented graphically in Figure 5, while Figure 6 displayed top link force change with soil depths and tractor velocities" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure17-1.png", + "caption": "Figure 17. Time to reach ejection temperature and average temperature distribution at that time.", + "texts": [ + " The contour colors represent the flow of the material into the cavity at different intervals of time. The simulation result shows that the maximum filling time is 4.89 s and the edge of the blade fills at last (left side). The confidence of fill result displays the probability of plastic filling a region within the cavity under conventional injection molding conditions. The quality prediction result is used to estimate the quality of the mechanical properties and appearance of the final part. It is shown that there is possible degradation of the quality nearby gate location. Figure 17 shows the amount of time required to reach the ejection temperature, which is measured from the start of the cycle, is 259.4 s. Moreover, the average temperature result (Figure 17) shows the average bulk temperature through the thickness of the part at the end of the fill. The temperature of melted polymer changes not only with time and location but also with thickness during the entire injection molding cycle. Figure 18 shows the air traps and weld lines that are likely to occur during the injection molding process. Air traps can be reduced by appropriate venting in the molds, which can be then be used to design vents required to minimize the air traps. The weld lines distribution displays the angle of convergence as the two flow fronts meet" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003803_various-engine-types-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003803_various-engine-types-Figure9-1.png", + "caption": "Figure 9 Roadable PAV configuration, drive mode vs flight mode", + "texts": [], + "surrounding_texts": [ + "In this study, a computer program for the initial sizing of roadable PAVs that considers their operability in Korea was developed. Using the program, a roadable PAV concept that meets Korean road transportation regulations was designed. A constraint analysis can be performed using the sizing program based on the defined PAV configuration and mission profile, setting the requirements for the ground roll, rate of climb, max cruise speed, service ceiling and stall constraint. Furthermore, a performance analysis can be conducted for mission segments through aerodynamic, propulsion and weight analyses. The sizing program allows users to set up a DOE table, where various settings of design variables can be automatically populated for the optimalmission profile and sizing results. The DOE table was populated considering the regulations and infrastructure elements ofKorea and theFARPART23 regulations. The key design variables for the PAV sizing program are the driving speed, driving distance, flying range, maximum speed, cruising speed, cruising altitude, diversion range, passengers, baggage, take-off ground roll, take-off altitude, rate of climb, rate of climb altitude, stall speed and service ceiling. Among these variables, the take-off ground roll, cruise speed, rate of climb, stall speed, range and cruising altitude showed higher rates of sensitivity to the sizing results. Therefore, a DOE table was created, varying these six variables. From all of the sizing results obtained by running the DOE table, the results meeting the FAR PART 23 limits and those within the statistical ranges of the single-engineGA aircraft class were selected. The stall speedhad themost significant impact on the sizing results. The sizing results showed that PAVs with hybrid engines had higher MTOWs compared to those with IC engines. Hybrid propulsion-powered PAVs also had a larger wing area, larger wing span and greater engine power, leading to fuel economy penalties. The poor fuel efficiency of hybrid engines led to reduced mission ranges. Unlike automobiles, the weight penalty of the hybrid system due to the additional electrical components reduced the fuel efficiency considerably.When the four engine typeswere compared, matching the total engine system weight, the IC engine PAVs had better fuel efficiency rates than the hybrid powered PAVs. Finally, a gasoline-powered PAV configuration was selected as the final design because it had the lowest MTOW, despite its slightly worse fuel efficiency compared to that of the diesel-powered engine. For automobile applications, various hybrid systems have been proven to provide environmental benefits, achieving significantly better fuel economy rates. However, for air vehicles, hybrid engines do not offer a reduction in fuel consumption. Therefore, future work will investigate the potential environmental benefits of electric propulsion using either batteries or fuel cells for environmentally friendly PAVs. Type Case MTOW (lb) Wing area (ft2) Wing span (ft) T/W (lb/lb) W/S (lb/ft2) P/W (hp/lb) Engine power (BHP) Fuel efficiency (mpg) Gasoline 313 2,119 118 30 0.21 18 0.06 126 10.00 Diesel 39 2,369 132 32 0.20 18 0.06 143 10.30 Hybrid gasoline 50 2,943 161 35 0.21 18 0.06 209 8.17 Hybrid diesel 50 3,198 175 36 0.21 18 0.06 229 8.34 Aircraft Engineering and Aerospace Technology Volume 93 \u00b7 Number 11 \u00b7 2021 \u00b7 1\u201314" + ] + }, + { + "image_filename": "designv8_17_0001040_77_aoje_2_021025.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001040_77_aoje_2_021025.pdf-Figure8-1.png", + "caption": "Fig. 8 Tile unit geometry after themembranewall contact. When the membrane becomes tangent to the tile protrusions, the membrane contacts and aligns with the tile protrusions for a distance \u0394h before it deflects circularly.", + "texts": [ + " Scaling with the geometric scale gives insight on the form of the phenomenological terms, which may also scale with C2, allowing them to be condensed into dimensionless terms in the model along with the first principle torques. The phenomenological terms must be empirically characterized. 4.1.4 Membrane Wall Contact. As the tile curls, the membrane arc eventually becomes tangent to the tile protrusions such that the arc cannot curl further against the tile. Rather, it contacts and aligns with the tile protrusions for a distance \u0394h from the points M to the points N (Fig. 8). The remaining membrane length remains circular and tangent to the tile protrusions, resulting in a simple expression for the arc angle \u03b2 \u03b2 = \u03c0 2 + \u03b8 2 (14) which indicates the start of the membrane wall contact and gives an expression for the membrane tangent angle \u03b3 using Eq. (9). However, this membrane wall contact also introduces the contact distance \u0394h that requires an additional transcendental equation to solve, which is derived in a similar process as for \u03b2 before the contact: W(1 + \u03b5(F\u0302T )) \u2212 \u0394h C cos \u03b8 2 + \u03b1 ( ) + \u0394h sin \u03b8 2 = \u03c0 2 + \u03b8 2 cos \u03b8 2 (15) where F\u0302T is itself a function of \u0394h: F\u0302T = \u0394p \u00b7 C cos \u03b8 2 + \u03b1 ( ) + \u0394h sin \u03b8 2 ( ) cos \u03b8 2 (16) Normal force at the contact area over\u0394h offsets the external pressure applied at this region in the free body diagrams, which shifts the effective pressure facing areas on the membrane and on the curling tile, resulting in new expressions for the two torques as follows: T\u0302mem = \u0394p \u00b7 C C cos \u03b8 2 + \u03b1 ( ) + \u0394h sin \u03b8 2 ( ) cos \u03b8 2 cos \u03b1 (17) T\u0302p = 1 2 \u0394p(W2 + (H \u2212 \u0394h)2) (18) The torque from the membrane tension in this case is always negative due to the angle of the tension \u03b3 (Eq" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004563_blicFiles_00187b.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004563_blicFiles_00187b.pdf-Figure1-1.png", + "caption": "Figure 1. The device M\u010cB1 for measuring of the puling resistance", + "texts": [ + " For the time being, sensors based on metallic and/or semiconductor tensometers are being used due to their exactness and high sensitivity; the magnitude of the measured force is converted (using the deformation of the so-called deformation member) into the deformation of the tensometer, which is attached to this deformation member. Design and construction of the measuring device When selecting the tensometric sensor it was decided to use a product manufactured by the company TEVAS. Products of this company are used above all as sensors of pressure forces and for that reason it was at first necessary to convert this type of force to a pulling force. In co-operation with the University Training Farm \u017dab\u010dice we have developed and constructed a measuring device M\u010cB1 (Figure 1). This device was dimensioned for the maximum pulling force of 4 kN. The pulling force is transmissed through connecting ends fixed by means of nuts to pulling rods, which press to the tensometric member; this member is directly and across of a silentblock screwed to one and to the other pulling rod, respectively. Because of assembly reasons, one of these rods has two parts that are connected by means of fitted bolts. The silentblock is required partly for the registration of forces caused by the suspension of the device and partly for the elimination of undesired shocks that could damage the tensometer" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001163_O201110441050686.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001163_O201110441050686.pdf-Figure7-1.png", + "caption": "Fig. 7 Schematic of the rear wheel for adjusting crushing height(unit: mm).", + "texts": [], + "surrounding_texts": [ + "\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 \uc904\uae30\uc808\ub2e8 \ubc0f \ube44\ub2d0\ud53c \ubcf5 \uc81c\uac70\uae30\ub97c \uc774\uc6a9\ud558\uc5ec \uc808\ub2e8\ub192\uc774 100 mm, \uc8fc\ud589\uc18d\ub3c4 0.53 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 67.86 m/s\uc5d0\uc11c \uc808\ub2e8\uc815\ub3c4 95.5%\ub85c 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\ub369\uad74\ucc98\ub9ac\uae30\ubcf4\ub2e4 \ud6a8\uc728\uc801\uc778 2\uc870 \uc6a9 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ub97c \uac1c\ubc1c\ud558\uace0\uc790 \ud558\uc600\ub2e4.\n2. \uc7ac\ub8cc \ubc0f \ubc29\ubc95\n\uac00. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc124\uacc4\uff65\uc81c\uc791\n1) \uc8fc\uc694 \uad6c\uc870 \ubc0f \uc81c\uc6d0\n\uadf8\ub9bc 1\uc5d0\uc11c\uc640 \uac19\uc774 \ud2b8\ub799\ud130 PTO\ub97c \uc774\uc6a9\ud558\uc5ec \ub3d9\ub825\uc774 \uc804\ub2ec\ub418 \ub294 \ud2b8\ub799\ud130 \ubd80\ucc29\ud615\uc73c\ub85c 2\uc870\uc758 \ub450\ub451 \ub369\uad74 \ud30c\uc1c4\uac00 \uac00\ub2a5\ud558\ub3c4\ub85d \uc81c\uc791\ud558\uc600\ub2e4. \uc8fc\uc694\uad6c\uc870\ub294 \ub369\uad74 \ud30c\uc1c4\ub0a0\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\ub85c \uad6c\uc131\ub418\uc5b4 \uc788\ub294 \ub369\uad74 \ud30c\uc1c4\ubd80, \ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc744 \ub369\uad74 \ud30c\uc1c4\ubd80 \uad6c\ub3d9\ucd95\uc73c\ub85c \uc804\ub2ec\ud574\uc8fc\ub294 \uae30\uc5b4\ubc15\uc2a4, \uc2a4\ud504\ub85c\ucf13, \uccb4 \uc778, \uae30\uc5b4 \ub4f1\uc73c\ub85c \uad6c\uc131\ub41c \ub3d9\ub825 \uc804\ub2ec\ubd80, \ub369\uad74 \ud30c\uc1c4\uc791\uc5c5 \uc2dc \ub450\ub451\n\uc758 \ub192\uc774\uc5d0 \ub530\ub77c \ubbf8\ub95c\uc758 \ub192\ub0ae\uc774\ub97c \uc870\uc808\ud568\uc73c\ub85c\uc11c \ub369\uad74 \ud30c\uc1c4\ubd80 \uc758 \ub192\uc774\ub97c \uc870\uc808\ud560 \uc218 \uc788\ub294 \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80, \ud2b8\ub799\ud130 \ubd80\ucc29\uc7a5\uce58 \ubc0f \ud504\ub808\uc784 \ub4f1\uc73c\ub85c \uc8fc\uc694\ubd80\ub97c \uad6c\uc131 \uc124\uacc4\uff65\uc81c\uc791\ud558\uc600\ub2e4.\n2) \ub369\uad74 \ud30c\uc1c4\ubd80\n\ub369\uad74 \ud30c\uc1c4\ubd80\ub294 \uadf8\ub9bc 2\uc5d0\uc11c\ucc98\ub7fc \ud68c\uc804\ub0a0 \ud30c\uc1c4\uc2dd\uc73c\ub85c \ub369\uad74 \ud30c \uc1c4\ub0a0, \ud30c\uc1c4\ub0a0 \ubd80\ucc29 \ube0c\ub77c\ucf13, \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5 \ucd95, \ub369\uad74 \uac77\uc5b4\uc62c \ub9bc\ub0a0, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ubd80\ucc29 \uc6d0\ud310, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95, \uc9c0\uc9c0 \ubca0\uc5b4\ub9c1 \ub4f1 \uc73c\ub85c \uad6c\uc131 \uc81c\uc791\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0\uc740 \uadf8\ub9bc 3\uc5d0\uc11c\ucc98\ub7fc \uc81c\ucd08\n\uc6a9\uc73c\ub85c \ub9ce\uc774 \uc4f0\uc774\ub294 \uae38\uc774 120 mm, \ub450\uaed8 5 mm\uc758 \ud504\ub808\uc77c\ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \ud53c\uce58 70 mm \ub098\uc120\uc73c\ub85c \uc88c\uff65\uc6b0 \uac01\uac01 48\uac1c, \ucd1d 96\uac1c\ub97c \ubc30\uce58\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub0b4\uacbd 75 mm \uc911\uacf5\ucd95\uc778 \ud30c\uc1c4\ub0a0 \ucd95 \uc744 \ubca0\uc5b4\ub9c1\uc73c\ub85c \ub07c\uc6cc \ub9de\ucda4\ud558\uc5ec \uc88c, \uc6b0 \ud30c\uc1c4\ub0a0\ub4e4\uc744 \uac01\uac01 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ubd84\ub9ac \uad6c\ub3d9\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc740 \uadf8\ub9bc 4\uc5d0\uc11c\ucc98\ub7fc \ub05d\uc774 \ubfb0\uc871\ud55c \uae38\uc774 250 mm 6\uac1c \uc9c1\uc120\ub0a0\uc744 \uc6d0\uc8fc \ud53c\uce58\uac01 60\u00b0 \uac04\uaca9\uc73c\ub85c \ub192\uc774 \uc870\uc808\uc774 \uac00 \ub2a5\ud55c \ube0c\ub77c\ucf13\uc5d0 \ubd80\ucc29\ud558\uace0 \ube0c\ub77c\ucf13\uc744 \uc6d0\ud310\uc5d0 \uace0\uc815\ud558\uc600\ub2e4. \uc88c\uff65 \uc6b0\uff65\uc911\uc559 3\uacf3 6\uac1c\uc529 \ubaa8\ub450 18\uac1c\uc758 \ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \uccb4\uc778 \uc804 \ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5\ucd95 \uc548\uc758 \uc9c1\uacbd 35 mm \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\uc5ec \uac77\uc5b4\uc62c\ub9bc \uc791\uc6a9\uc744 \ud558\ub3c4\ub85d \ud558 \uc600\ub2e4.\n3) \ub3d9\ub825 \uc804\ub2ec\ubd80\n\ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc774 \uae30\uc5b4\ubc15\uc2a4\uc5d0\uc11c 2.5\ubc30\ub85c \uc99d \uc18d\ub418\uc5b4 \uad6c\ub3d9\ucd95 \uc88c\uff65\uc6b0\ub85c \ub098\ub258\uc5b4\uc838 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77 \uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\ub294 \uacfc\uc815\uc744 \uadf8\ub9bc 5\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \uad6c\ub3d9\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc6b0\uce21\uc758 \uad6c\ub3d9\ucd95\uc73c\ub85c", + "J. of Biosystems Eng. Vol. 36, No. 1.\n\ubd80\ud130 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95 \uc548\uc5d0 \uc788\ub294 \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uc9c1\uc811 \uad6c\ub3d9\uc2dc\ud0a8\ub2e4. \uadf8\ub9bc 6\uc740 \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\ucd95\uc758 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \uc2dc\uc758 \ub3d9\ub825 \uc804\ub2ec \ubc29\ubc95\uc744 \ub098\ud0c0\ub0b8 \uac83\uc774\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \uc804\uc9c4\ubc29 \ud5a5 \ud68c\uc804(\uc815\ud68c\uc804)\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c \ucf13\uacfc \uae30\uc5b4\uac00 \uc870\ud569\ub41c 2\uac1c\uc758 \ubc29\ud5a5\uc804\ud658 \ucd95\uacfc \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\n\ucd95\uc744 \uac70\uccd0 \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc \ud0a4\uace0, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \ud6c4\uc9c4\ubc29\ud5a5 \ud68c\uc804(\uc5ed\ud68c\uc804)\uc740 \uae30\n\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c\ucf13\uacfc \ud150\uc158 \uc2a4\ud504\ub85c\ucf13\uc744\n\uac70\uccd0 \uc911\uacf5\uc758 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc\ud0a4\ub3c4\ub85d \ud558 \uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \ud68c\uc804\uc18d\ub3c4\ube44\ub294 9 : 1\ub85c \uace0\ub791\uc5d0 \uc788\ub294 \ub3cc\uc5d0 \uc758\ud55c \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \uc190\uc0c1 \ubc0f \ub369\n\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc5d0 \uc758\ud55c \ube44\ub2d0\ud53c\ubcf5 \uc190\uc0c1 \ub4f1\uc758 \ubb38\uc81c\uc810\uc774 \ubc1c\uc0dd\ub420 \uc218\ub3c4 \uc788\uae30 \ub54c\ubb38\uc5d0 \ud68c\uc804\uc18d\ub3c4\uc758 \ucc28\uc774\uac00 \uc788\ub3c4\ub85d \ud558\uc600\ub2e4.\n4) \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80\n\ub369\uad74\ucc98\ub9ac \uc791\uc5c5 \uc2dc \ub369\uad74 \ud30c\uc1c4\ubd80\uc758 \ud30c\uc1c4\ub192\uc774\ub97c \uc81c\uc5b4\ud558\uba70, \uace0 \ub791\uc744 \uc774\ud0c8\ud558\uc9c0 \uc54a\uace0 \uc791\uc5c5\uae30\uc758 \uc8fc\ud589 \uc548\uc815\uc131\uc744 \ub192\uc774\uae30 \uc704\ud558\uc5ec \uc124\uce58\ud55c \ubbf8\ub95c\uc758 \uad6c\uc870\ub97c \uadf8\ub9bc 7\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ubbf8\ub95c\uc740 \uc9c1\uacbd 400 mm, \ud3ed 100 mm\ub85c \ub450\ub451\uc758 \ud615\uc0c1\uc5d0 \ub530\ub77c \ub369\uad74\ud30c\uc1c4\ubd80\uc758\n\ub192\ub0ae\uc774\ub97c \uc704\ucabd\uc758 \ub808\ubc84\ub97c \ud68c\uc804\uc2dc\ucf1c \uc870\uc808\ud560 \uc218 \uc788\ub3c4\ub85d \ud558\uc600\uc73c \uba70, \ub192\uc774 \uc870\uc808\uc740 300 mm\uae4c\uc9c0 \uac00\ub2a5\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ubbf8\ub95c\uc758 \uc124 \uce58 \uc704\uce58\ub294 \uc791\uc5c5\uae30 \ud6c4\ubc29 \uc791\uc5c5\uae30\ub97c \uc911\uc2ec\uc73c\ub85c \uc88c\uc6b0 2\uac1c, \ubbf8\ub95c \uc911 \uc2ec\uac04 \uac70\ub9ac\uac00 1400 mm\uac00 \ub418\ub3c4\ub85d \ubd80\ucc29\ud558\uc600\ub2e4.\n\ub098. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc131\ub2a5\uc2e4\ud5d8\n1) \uc2e4\ud5d8\ud3ec\uc7a5 \ubc0f \uc7ac\ub8cc\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc758 \uc2e4\ud5d8 \uc911 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc5d0 \ub530\ub978 \ud30c\n\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c\ub9c8\ub294 \uc728\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758 \ud3c9 \uade0 \ud568\uc218\uc728\uc740 83.0%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \uc2e4\ud5d8\ud3ec\uc7a5\uc758 \ud1a0\uc131\uc740 \uc0ac\uc591 \ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 30 cm, \ub450\ub451\ub192 \uc774 25 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4. \uc8fc\ud589\uc18d\ub3c4 \ubc0f \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c \ub9c8\ub294 \uc2e0\ud669\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758\ud3c9\uade0 \ud568\uc218\uc728\uc740 79.1%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \ud1a0\uc131\uc740 \uc0ac\uc9c8\ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 40 cm, \ub450\ub451\ub192\uc774 30 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4.\n2) \uc2e4\ud5d8\ub0b4\uc6a9 \ubc0f \ubc29\ubc95\n\uac00) \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8\n\ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ud30c\uc1c4\uc131\ub2a5\uc758 \ucc28\uc774\ub97c \uc870\uc0ac\ud558\uae30 \uc704\n\ud558\uc5ec \uc2e4\uc2dc\ud55c \uc2e4\ud5d8\uc73c\ub85c \ud2b8\ub799\ud130 \uc5d4\uc9c4 \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uc5d0 \ub530\ub77c \uc8fc \ud589\uc18d\ub3c4, PTO \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uac00 \uc5c6\ub3c4\ub85d \ud2b8\ub799\ud130 \uc5d4\uc9c4\uc18d\ub3c4\ub97c 2000 rpm\uc73c\ub85c \uace0\uc815\ud558\uace0, \uc8fc\ud589 \ubcc0\uc18d\ub2e8\uc218\ub97c Park and Choi (1995)\uac00 \ubcf4\uace0\ud55c \uc8fc\ud589\uc18d\ub3c4 0.35, 0.46 m/s\uc5d0\uc11c \uc8fc\ud589\uc18d\ub3c4\uac00 \ub0ae \uc744\uc218\ub85d \ub369\uad74 \ud30c\uc1c4\uc728\uc774 \ub192\uc558\uc73c\uba70, \ub18d\uac00\uc5d0\uc11c \uc8fc\ub85c \uc800\uc18d 1, 2\ub2e8 \uc744 \uc0ac\uc6a9\ud558\ub294 \uac83\uc744 \uace0\ub824\ud558\uc5ec \ubcf8 \uc2e4\ud5d8\ub3c4 \uc800\uc18d 1, 2\ub2e8\uc5d0 \ub9de\ucd94\uc5b4 \uc8fc\ud589\uc18d\ub3c4\ub97c \uac01\uac01 0.27, 0.37 m/s\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \ubcc0\uacbd\uc740 \uadf8\ub9bc 6\uc5d0\uc11c", + "\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uc640 \uac19\uc774 \ub3d9\ub825 \uc804\ub2ec\uc7a5\uce58\ub97c \ubcc0\uacbd\ud558\uc5ec \uc218\ud589\ud558\uc600\uc73c\uba70, \ud2b8\ub799\ud130 PTO \ubcc0\uc18d\ub2e8\uc218\ub97c 1\ub2e8\uc5d0 \ub9de\ucd94\uc5b4 \ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\uc18d\ub3c4\ub294 570 rpm\uc73c\ub85c \uc124\uc815\ud558\uc600\ub2e4. \uc2e4\ud5d8\uc694\uc778\uacfc \uc694\uc778\ubcc4 \uc218\uc900\uc5d0 \ub530\ub77c \uc2e4 \ud5d8\uad6c\uac04\uc740 50 m \uad6c\uac04\uc744 2\uacf3 \ubc18\ubcf5 \uc791\uc5c5\ud558\uc600\uc73c\uba70, \uc774 \uc911 10 m, 3\uad6c\uac04\uc744 \uc784\uc758\ub85c \uc120\ud0dd\ud558\uc5ec \uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728, \uc794\ub958 \ub369\uad74\uae38 \uc774\ub97c \uce21\uc815\ud558\uc600\ub2e4. \ubcf8 \uc2e4\ud5d8\uc5d0\uc11c \ub369\uad74 \uc81c\uac70 \ud6c4, \ube44\ub2d0 \uba40\uce6d \uc81c\uac70\uc791\uc5c5 \uc2dc \ubc29\ud574\uac00 \ub418\uc9c0 \uc54a\ub294 \ub369\uad74\uae38\uc774\ub294 \uc57d 300 mm \uc774\ub0b4\ub85c \ud310\ub2e8\ub418\uc5b4, \uc794\ub958 \ub369 \uad74 \ud30c\uc1c4\ube44\uc728\uc740 10 m \uc784\uc758\uc758 3\uce21\uc815 \uad6c\uac04 \uc911 \uc804\uccb4 \uc8fc\uc218\uc5d0 \ub300\ud55c \ub369\uad74 \ud30c\uc1c4\uc791\uc5c5 \ud6c4 \uc794\ub958 \ub369\uad74\uae38\uc774\uac00 300 mm \ubbf8\ub9cc\uc778 \uc8fc\uc218\uc758 \ube44\uc728\ub85c \uc815\uc758\ud558\uc600\uc73c\uba70, \uc794\ub958 \ub369\uad74\uae38\uc774\ub294 10 m \uc784\uc758\uc758 3\uad6c\uac04 \uc5d0\uc11c \uc8fc\uc5d0 \ub0a8\uc544 \uc788\ub294 \ub369\uad74\uc758 \uae38\uc774\ub85c \ucd5c\ub300, \ucd5c\uc18c, \ud3c9\uade0\uae38\uc774\ub97c \uc870\uc0ac\ud558\uc600\ub2e4.\n\ub098) \uc8fc\ud589\uc18d\ub3c4 \ubc0f \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5\n\uc2e4\ud5d8\n\uc8fc\ud589\uc18d\ub3c4 \ubc0f \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \uc758 \uc2e4\ud5d8\uc694\uc778\uacfc \uc694\uc778\ubcc4 \uc218\uc900\uc740 \uc8fc\ud589\uc18d\ub3c4 0.27, 0.37 m/s 2\uc218 \uc900, \ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\uc18d\ub3c4\ub294 570, 800 rpm(\ub369\uad74 \ud30c\uc1c4\ub0a0 \uc6d0 \uc8fc\uc18d\ub3c4\ub294 \uac01\uac01 10.7, 15.1 m/s) 2\uc218\uc900\uc73c\ub85c \uc2e4\ud5d8\ud558\uc600\uc73c\uba70, \ub369 \uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc740 \uc5ed\ud68c\uc804\uc73c\ub85c \uace0\uc815\ud558\uc600\ub2e4.\n\uc2e4\ud5d8\ubc29\ubc95 \uc911 \uc8fc\ud589\uc18d\ub3c4\ub294 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8\uacfc \uac19\uc740 \ubc29\ubc95\uc73c\ub85c \uac01\uac01 0.27, 0.37 m/s\ub85c \uc124\uc815\ud558\uc600\uc73c\uba70, \ud2b8\ub799\ud130 PTO \ubcc0\uc18d\ub2e8\uc218\ub97c 1, 2\ub2e8\uc5d0 \ub9de\ucd94\uc5b4 \ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\uc18d\ub3c4\ub97c 570, 800 rpm\uc73c\ub85c \uac01\uac01 \uc124\uc815\ud558\uc600\ub2e4. \uc2e4\ud5d8\uc694\uc778\uacfc \uc694\uc778\ubcc4 \uc218\uc900 \uc5d0 \ub530\ub77c \uc2e4\ud5d8\uad6c\uac04\uc740 100 m\uad6c\uac04\uc744 4\uacf3 \ubc18\ubcf5 \uc791\uc5c5\ud558\uc600\uc73c\uba70, \uc774 \uc911 20 m, 3\uad6c\uac04\uc744 \uc784\uc758\ub85c \uc120\ud0dd\ud558\uc5ec \uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728, \uc794 \ub958 \ub369\uad74\uae38\uc774, \ud30c\uc1c4 \ub369\uad74\uae38\uc774\ub97c \uce21\uc815\ud558\uc600\ub2e4.\n\uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728\uacfc \uc794\ub958 \ub369\uad74\uae38\uc774\uc758 \uc815\uc758\ub294 \ub369\uad74 \ud30c\uc1c4 \ub0a0 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8\uc5d0 \ub098\ud0c0\ub09c \ubc14\uc640 \uac19\uc73c\uba70, \ud30c\uc1c4 \ub369 \uad74\uae38\uc774\ub294 \uc794\ub958 \ub369\uad74\uc758 \ud30c\uc1c4\ube44\uc728\uc744 \uc870\uc0ac\ud55c 20 m 3\uad6c\uac04\uc5d0\uc11c \uc218\uc9d1\ud55c \ud30c\uc1c4\ub369\uad74 \uc911 \uc784\uc758\uc758 \ud30c\uc1c4 \ub369\uad74 100\uac1c\ub97c \ucc44\ucde8\ud558\uc5ec \ucd5c \ub300, \ucd5c\uc18c, \ud3c9\uade0\uae38\uc774\ub97c \uc870\uc0ac\ud558\uc600\ub294\ub370, \uc870\uc0ac \uc774\uc720\ub294 \uae38\uac8c \ud30c\uc1c4\n\ub41c \ub369\uad74\uc774 \uace0\uad6c\ub9c8 \uc218\ud655 \uc791\uc5c5 \uc2dc \uace0\uad6c\ub9c8 \uc218\ud655\uae30\uc758 \uad74\ucde8\ubd80 \uac78 \ub9bc, \uc120\ubcc4\ubd80 \uc120\ubcc4\ub2a5\ub825 \uc800\ud558\ub97c \ucd08\ub798\ud560 \uc218\ub3c4 \uc788\uae30 \ub54c\ubb38\uc774\uc5c8\ub2e4.\n3. \uacb0\uacfc \ubc0f \uace0\ucc30\n\uac00. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5\n\ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5 \ubc0f \uc8fc\ud589\uc18d\ub3c4\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5\uc744 \ud45c 1\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728\uc740 \uc8fc\ud589\uc18d\ub3c4\uac00 0.37, 0.27 m/s\uc77c \ub54c \uc5ed\ud68c\uc804\uc5d0\uc11c\ub294 \uac01\uac01 95.3, 97.8%, \uc815\ud68c\uc804\uc5d0\uc11c\ub294 \uac01 \uac01 90.2, 93.8%\ub85c \ub098\ud0c0\ub098 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc774 \uc815\ud68c\uc804 \ubcf4 \ub2e4\ub294 \uc5ed\ud68c\uc804\uc5d0\uc11c, \uadf8\ub9ac\uace0 \uc8fc\ud589\uc18d\ub3c4\uac00 \ub290\ub9b4\uc218\ub85d \uc794\ub958 \ub369\uad74 \ud30c \uc1c4\ube44\uc728\uc740 \ud06c\uac8c \ub098\ud0c0\ub098\ub294 \uacbd\ud5a5\uc744 \ubcf4\uc600\ub2e4. \ub610\ud55c \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c \uc804\ubc29\ud5a5 \uc5ed\ud68c\uc804, \uc8fc\ud589\uc18d\ub3c4 0.27 m/s\uc77c \ub54c \uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728 \uc740 97.8%\ub85c \uac00\uc7a5 \ud06c\uac8c \ub098\ud0c0\ub0ac\ub2e4. \ud3c9\uade0 \uc794\ub958 \ub369\uad74\uae38\uc774\ub294 \uc8fc\ud589\uc18d\ub3c4\uac00 0.37, 0.27 m/s\uc77c \ub54c \uc5ed \ud68c\uc804\uc5d0\uc11c\ub294 \uac01\uac01 72, 58 mm, \uc815\ud68c\uc804\uc5d0\uc11c\ub294 \uac01\uac01 380, 325 mm \ub85c \ub098\ud0c0\ub098 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc774 \uc815\ud68c\uc804 \ubcf4\ub2e4\ub294 \uc5ed\ud68c\uc804\uc5d0 \uc11c, \uadf8\ub9ac\uace0 \uc8fc\ud589\uc18d\ub3c4\uac00 \ub290\ub9b4\uc218\ub85d \ud3c9\uade0 \uc794\ub958 \ub369\uad74\uae38\uc774\ub294 \uc9e7\uc544 \uc9c0\ub294 \uacbd\ud5a5\uc744 \ubcf4\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5 \uc5ed\ud68c\uc804, \uc8fc\ud589\uc18d\ub3c4 0.27 m/s\uc77c \ub54c \ud3c9\uade0 \uc794\ub958\uae38\uc774\ub294 58 mm\ub85c \uac00\uc7a5 \uc9e7\uac8c \ub098\ud0c0\ub0ac \ub2e4. \ud45c\uc5d0\uc11c \ucd5c\uc18c \uc794\ub958 \ub369\uad74\uae38\uc774\uac00 0 mm\uc778 \uacbd\uc6b0\ub294 \ub450\ub451\uc774 \uace0\n\ub974\uc9c0 \ubabb\ud558\uc5ec \ub369\uad74 \ud30c\uc1c4\ub0a0\uc5d0 \uc758\ud558\uc5ec \ube44\ub2d0\ud53c\ubcf5\uc774 \uc190\uc0c1\uc744 \uc785\uace0 \ube44\ub2d0\ud53c\ubcf5 \uc548\ucabd\uc73c\ub85c \ub369\uad74\uc774 \ud30c\uc1c4\ub41c \uac83\uc73c\ub85c \ud310\ub2e8\ub418\uc5c8\ub2e4.\n\ub098. \uc8fc\ud589\uc18d\ub3c4 \ubc0f \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5\n1) \uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728, \uc794\ub958 \ub369\uad74\uae38\uc774\n\uc8fc\ud589\uc18d\ub3c4 \ubc0f \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728, \uc794\ub958 \ub369\uad74\uae38\uc774\ub97c \ud45c 2\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4.\n\uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728\uc740 \uc8fc\ud589\uc18d\ub3c4\uac00 0.27 m/s, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\uac00 570, 800 rpm\uc77c \uacbd\uc6b0\ub294 \uac01\uac01 96.2, 98.0%\ub85c \ub098 \ud0c0\ub0ac\uc73c\uba70, \uc8fc\ud589\uc18d\ub3c4\uac00 0.37 m/s, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\uac00 570, 800 rpm\uc77c \uacbd\uc6b0\uc5d0\ub294 \uac01\uac01 94.4, 95.7%\ub85c \ub098\ud0c0\ub098 \uc8fc\ud589\n\uc18d\ub3c4\uac00 \ub290\ub9b4\uc218\ub85d \uadf8\ub9ac\uace0 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\uac00 \ucee4\uc9c8\uc218\ub85d \uc794\ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728\uc740 \ud06c\uac8c \ub098\ud0c0\ub098\ub294 \uacbd\ud5a5\uc744 \ubcf4\uc600\ub2e4. \uc774 \uc911 \uc8fc\ud589\uc18d\ub3c4 0.27 m/s, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4 800 rpm\uc77c \ub54c \uc794 \ub958 \ub369\uad74 \ud30c\uc1c4\ube44\uc728\uc740 98.0%\ub85c \uac00\uc7a5 \ud06c\uac8c \ub098\ud0c0\ub0ac\ub2e4. \ud3c9\uade0 \uc794\ub958 \ub369\uad74\uae38\uc774\ub294 \uc8fc\ud589\uc18d\ub3c4\uac00 0.27 m/s\uc77c \ub54c \ub369\uad74 \ud30c \uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\uac00 570, 800 rpm\uc77c \uacbd\uc6b0\ub294 \uac01\uac01 111, 104 mm, \uc8fc\ud589\uc18d\ub3c4\uac00 0.37 m/s, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\uac00 570, 800 rpm" + ] + }, + { + "image_filename": "designv8_17_0001232_f_d2me2017_02004.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001232_f_d2me2017_02004.pdf-Figure3-1.png", + "caption": "Figure 3. Balance-arm truss", + "texts": [ + " The rotatable balance-arm, which is located on the rotational support, includes two parallel truss structures, four connecting rods and platform. All parts are connected by pins. As shown in Figure 2, the parallelogram structure can remain the platform horizontal and make the luffing mechanism work normally. The minimum work angle of balance-bar is 7\u00b0, maximum is 87.5\u00b0. 4 3 5 1 2 1- Balance-arm, 2-Connect rod, 3-Platform, 4-Luffing mechanism, 5-Balance-weight Figure 2. Rotatable parallelogram balance-arm Shown as Figure 3, the upper truss is designed with opening downwards to assure the balance-arm not impact with the crane head. The lower truss has enough blank in the end to make the balance-weight pass through. 2.3 Platform of balance-arm and balance-weight MATEC Web of Conferences lifting-arm head balance-arm rotational support Figure 1. The pattern of rotatable balance-arm system The rotatable balance-arm, which is located on the rotational support, includes two parallel truss structures, four connecting rods and platform. All parts are connected by pins. As shown in Figure 2, the parallelogram structure can remain the platform horizontal and make the luffing mechanism work normally. The minimum work angle of balance-bar is 7\u00b0, maximum is 87.5\u00b0. 4 3 5 1 2 1- Balance-arm, 2-Connect rod, 3-Platform, 4-Luffing mechanism, 5-Balance-weight Figure 2. Rotatable parallelogram balance-arm Shown as Figure 3, the upper truss is designed with opening downwards to assure the balance-arm not impact with the crane head. The lower truss has enough blank in the end to make the balance-weight pass through. (a) upper truss (b) lower truss Figure 3. Balance-arm truss 2.3 Platform of balance-arm and balance-weight D2ME 2017 The platform (shown as Figure 4) is box-type structure. The luffing mechanism of balance-arm installed on the platform generates the backward torque with weight block under platform together. The head is latticed structure located in the center of rotational support. There is a limit putter on the head to avoid the impact of lifting-arm and balance-arm. The rotational assembly is shown as in Figure 5. The rotational upper support is shown in Figure 6, and the hinged joint of lifting-arm end is arranged on the edge of rotational support" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004291_advpub_22-00301__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004291_advpub_22-00301__pdf-Figure3-1.png", + "caption": "Fig. 3 LF and SAT directions when turning in planar view. In the left-turn cornering, leftward LF and clockwise SAT act on the two front wheels.", + "texts": [], + "surrounding_texts": [ + "\u00a9 The Japan Society of Mechanical Engineers\n\u3055\u308c\u305f\u30b7\u30e7\u30c3\u30af\u30a2\u30d6\u30bd\u30fc\u30d0\uff0c\u8d64\u8272\u3067\u793a\u3055\u308c\u305f\u30ed\u30a2\u30a2\u30fc\u30e0\uff0c\u9752\u8272\u3067\u793a\u3055\u308c\u305f\u30bf\u30a4\u30ed\u30c3\u30c9\u304a\u3088\u3073\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30ae\u30e4\u30dc \u30c3\u30af\u30b9\u3067\u3042\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u3068\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30ca\u30c3\u30af\u30eb\uff0c\u30b7\u30e7\u30c3\u30af\u30a2\u30d6\u30bd\u30fc\u30d0\u306f\uff0c\u30a2\u30af\u30b9\u30eb\u30b7\u30e3\u30d5\u30c8\u307e\u308f\u308a\u306e\u30db\u30a4\u30fc\u30eb \u306e\u56de\u8ee2\u3092\u9664\u3044\u3066\u4e00\u4f53\u3068\u306a\u3063\u3066\u52d5\u304f\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u306f\uff0c\u56f3 1 \u4e2d\u306b\u793a\u3055\u308c\u305f[D]\u304a\u3088\u3073[G]\u3067\u30e9\u30d0\u30fc\u30d6\u30c3\u30b7\u30e5\u3092\u4ecb\u3057\u3066\u30dc \u30c7\u30fc\u306b\u56fa\u5b9a\u3055\u308c\u3066\u3044\u308b\uff0e\u307e\u305f\uff0c[B]\u3067\u30dc\u30fc\u30eb\u30b8\u30e7\u30a4\u30f3\u30c8\u3092\u4ecb\u3057\u3066\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30ca\u30c3\u30af\u30eb\u3068\u7d50\u5408\u3055\u308c\u3066\u3044\u308b\uff0e\u30bf\u30a4\u30ed \u30c3\u30c9\u306f[C]\u3067\u30dc\u30fc\u30eb\u30b8\u30e7\u30a4\u30f3\u30c8\u3092\u4ecb\u3057\u3066\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30ca\u30c3\u30af\u30eb\u3068\u7d50\u5408\u3055\u308c\u3066\u3044\u308b\uff0e\u307e\u305f\uff0c[H]\u3067\u30dc\u30fc\u30eb\u30b8\u30e7\u30a4\u30f3\u30c8 \u3092\u4ecb\u3057\u3066\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30ae\u30e4\u30dc\u30c3\u30af\u30b9\u3068\u7d50\u5408\u3055\u308c\u3066\u3044\u308b\uff0e\n\u56f3 2 \u306b\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u5e73\u9762\u8996\u6a21\u5f0f\u56f3\u3092\u793a\u3059\uff0e\u56f3 1 \u4e2d\u306e[A]\u304b\u3089[I]\u306f\uff0c\u56f3 2 \u306e\u70b9 A \u304b\u3089 \u70b9 I\u306b\u5bfe\u5fdc\u3059\u308b\uff0e\u4ee5\u964d\u306f\uff0c\u3053\u308c\u3089\u3092\u70b9 A\u306a\u3069\u3068\u8868\u3059\uff0e\u56f3 2\u306b\u304a\u3044\u3066\u306f\uff0c\u30db\u30a4\u30fc\u30eb\u3068\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30ca\u30c3\u30af\u30eb\uff0c\u30b7\u30e7 \u30c3\u30af\u30a2\u30d6\u30bd\u30fc\u30d0\u306f\u4e00\u4f53\u3068\u306a\u3063\u3066\u52d5\u304f\u305f\u3081\uff0c\u5168\u3066\u7dd1\u7dda\u3067\u793a\u3057\u3066\u3042\u308b\uff0e\u4ee5\u4e0b\u3067\u306f\u3053\u308c\u3092\u30db\u30a4\u30fc\u30eb\u90e8\u3068\u547c\u3076\uff0e\u307e\u305f\uff0c\u30ed \u30a2\u30a2\u30fc\u30e0\u306f\u70b9 B, D, G\u3092\u7d50\u3076\u8d64\u7dda\u3067\u793a\u3057\u3066\u3042\u308b\uff0e\u3055\u3089\u306b\uff0c\u30bf\u30a4\u30ed\u30c3\u30c9\u306f\u70b9 C\u3068\u70b9 H\u3092\u7d50\u3076\u9752\u7dda\u3067\u793a\u3057\u3066\u3042\u308b\uff0e\u70b9 A, D, G\u306b\u306f\u30e9\u30d0\u30fc\u30d6\u30c3\u30b7\u30e5\u304c\u4f7f\u7528\u3055\u308c\uff0c\u70b9 B, C, H\u306b\u306f\u30dc\u30fc\u30eb\u30b8\u30e7\u30a4\u30f3\u30c8\u304c\u4f7f\u7528\u3055\u308c\u308b\uff0e3\u7ae0\u304a\u3088\u3073 4\u7ae0\u3067\u5b9a\u6027 \u7684\u306b\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u6319\u52d5\u3092\u8003\u5bdf\u3059\u308b\u969b\uff0c\u70b9 A, D, G, H\u306b\u3064\u3044\u3066\u306f Y\u8ef8\u65b9\u5411\u306e\u529b\u3084\u5909\u4f4d\u306b\u6ce8\u76ee\u3059\u308b\uff0e\u3053\u306e\u305f\u3081\u56f3 2 \u3067\u306f\u70b9 A, D, G, H\u306b\u304a\u3051\u308b\u30e9\u30d0\u30fc\u30d6\u30c3\u30b7\u30e5\u3084\u30dc\u30fc\u30eb\u30b8\u30e7\u30a4\u30f3\u30c8\u3092 Y \u8ef8\u65b9\u5411\u306e\u3070\u306d\u3068\u3057\u3066\u30e2\u30c7\u30eb\u5316\u3092\u884c\u3044\uff0c\u3053\u308c\u3089 \u306e\u3070\u306d\u5b9a\u6570\u3092 kAY, kDY, kGY, kHY\u3068\u3057\u305f\uff0e\u306a\u304a\u672c\u8ad6\u6587\u3067\u306f\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u6319\u52d5\u306b\u6ce8\u76ee\u3059\u308b\u306e\u3067\uff0c\u30dc\u30c7\u30fc\u525b\u6027\u306b\u3064\u3044 \u3066\u306f\u5341\u5206\u9ad8\u3044\u3082\u306e\u3068\u3057\u3066\u3044\u308b\uff0e\n\u8868 1\u306b\u5e02\u8ca9\u8eca\u306b\u304a\u3051\u308b kAY, kDY, kGY, kHY\u306e\u5024\u306e\u4f8b\u3092\u793a\u3059\uff0e\u3053\u306e\u8868\u306b\u304a\u3044\u3066 kAY\u306f\uff0c\u70b9 A \u306b\u304a\u3051\u308b\u30e9\u30d0\u30fc\u30d6\u30c3\u30b7\u30e5 \u525b\u6027\u304a\u3088\u3073\u30b7\u30e7\u30c3\u30af\u30a2\u30d6\u30bd\u30fc\u30d0\u306e\u30ed\u30c3\u30c9\u66f2\u3052\u525b\u6027\u3092\u8003\u616e\u3057\u305f\u3082\u306e\u3068\u3057\u3066\u3044\u308b\uff0e\u307e\u305f kHY \u306f\uff0c\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30ae\u30e4\u30dc \u30c3\u30af\u30b9 ASSY\u306e\u8eca\u4f53\u53d6\u4ed8\u3051\u525b\u6027\u304a\u3088\u3073\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30b7\u30e3\u30d5\u30c8\u306e\u306d\u3058\u308a\u525b\u6027\u3092\u8003\u616e\u3057\u305f\u3082\u306e\u3068\u3057\u3066\u3044\u308b\uff0e\u5e02\u8ca9\u3055\u308c \u3066\u3044\u308b\u8eca\u4e21\u3067\u306f kDY\u304a\u3088\u3073 kHY\u306f\u9ad8\u3044\u5024\u306b\u8a2d\u5b9a\u3055\u308c\uff0ckAY\u304a\u3088\u3073 kGY\u306f\u4f4e\u3044\u5024\u306b\u8a2d\u5b9a\u3055\u308c\u308b\u3053\u3068\u304c\u591a\u3044\uff0e\n\u4ee5\u4e0b\u306b\uff0c\u56f3 2\u306b\u793a\u3059\u30ea\u30f3\u30af\u914d\u7f6e\u306e\u7279\u5fb4\u3068\u305d\u306e\u7406\u7531\u304a\u3088\u3073\u3070\u306d\u5b9a\u6570\u304c\u4e0a\u8ff0\u306e\u3088\u3046\u306b\u8a2d\u5b9a\u3055\u308c\u308b\u7406\u7531\u306b\u3064\u3044\u3066\u7c21\u5358 \u306b\u8aac\u660e\u3057\u3066\u304a\u304f\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u524d\u8fba B-D \u306f\uff0c\u70b9 B\u304c\u70b9 D \u306b\u5bfe\u3057\u308f\u305a\u304b\u306b\u8eca\u4e21\u524d\u65b9\u306b\u4f4d\u7f6e\u3057\u3066\u3044\u308b\u304c\uff0c\u8eca\u4e21 Y \u8ef8\u306b \u8fd1\u3044\u89d2\u5ea6\u306b\u914d\u7f6e\u3055\u308c\u308b\uff0e\u3053\u308c\u306f LF\u3092\u8ef8\u529b\u3068\u3057\u3066\u53d7\u3051\uff0c\u525b\u6027\u3092\u9ad8\u304f\u3059\u308b\u305f\u3081\u3067\u3042\u308b\uff0e\u3053\u308c\u306b\u4f34\u3044 kDY\u306e\u5024\u3082\u9ad8\u304f\u8a2d \u5b9a\u3055\u308c\u308b\uff0e\u30bf\u30a4\u30ed\u30c3\u30c9\u8ef8 C-H \u306f\u30a2\u30af\u30b9\u30eb\u30bb\u30f3\u30bf\u3088\u308a\u5f8c\u65b9\u3067\u8fba B-D \u306b\u5bfe\u3057\u307b\u307c\u7b49\u9577\u5e73\u884c\u306b\u306a\u308b\u3088\u3046\u306b\u914d\u7f6e\u3055\u308c\u308b\uff0e", + "\u00a9 The Japan Society of Mechanical Engineers\n\u3053\u308c\u306f\uff0c\u7b49\u9577\u5e73\u884c\u306b\u8fd1\u304f\u306a\u308b\u3088\u3046\u8a2d\u5b9a\u3059\u308b\u3053\u3068\u3067\u8fba B-D\u3068\u8ef8 C-H\u3092\u30d1\u30e9\u30ec\u30eb\u30ea\u30f3\u30af\u5316\u3057\uff0c\u3053\u308c\u306b\u3088\u308a\u30b5\u30b9\u30da\u30f3\u30b7 \u30e7\u30f3\u3078\u306e\u524d\u5f8c\u5165\u529b\u6319\u52d5\u306b\u5bfe\u3057\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u3092\u5c0f\u3055\u304f\u6291\u3048\u308b\u305f\u3081\u3067\u3042\u308b\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u70b9 G \u306e\u3070\u306d\u5b9a\u6570 kGY\u306e\u5024\u306f\uff0c\u6bb5\u5dee\u4e57\u308a\u8d8a\u3048\u7b49\u306e\u524d\u5f8c\u65b9\u5411\u306e\u30b7\u30e7\u30c3\u30af\u3092\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u56de\u8ee2\u3067\u5438\u53ce\u3067\u304d\u308b\u3088\u3046\u4f4e\u304f\u8a2d\u5b9a\u3055\u308c\u3066\u3044\u308b\uff0e\n2\u30fb2 \u65cb\u56de\u6642\u306e\u30db\u30a4\u30fc\u30eb\u306b\u4f5c\u7528\u3059\u308b LF\u3068 SAT \u8eca\u4f53\u9032\u884c\u65b9\u5411\u306b\u5bfe\u3057\u3066\u30db\u30a4\u30fc\u30eb\u306e\u5411\u304d\u306b\u89d2\u5ea6\u5dee\u3092\u4e0e\u3048\u308b\u3053\u3068\u3067\u30db\u30a4\u30fc\u30eb\u306b LF\u3068 SAT \u304c\u4f5c\u7528\u3059\u308b\uff0e\u56f3 3\u306b\u793a\u3059 \u3088\u3046\u306b\u8eca\u4e21\u304c\u5de6\u65cb\u56de\u3059\u308b\u5834\u5408\u30d5\u30ed\u30f3\u30c8\u5de6\u53f3\u8f2a\u306b\u4f5c\u7528\u3059\u308b LF \u306f\u3068\u3082\u306b\u5de6\u5411\u304d\u3067\u3042\u308a\uff0cSAT \u306f\u3068\u3082\u306b\u6642\u8a08\u307e\u308f\u308a\u3067 \u3042\u308b\uff0e\u4ee5\u964d\u306e\u8003\u5bdf\u3067\u306f\u5de6\u65cb\u56de\u6642\u306e\u53f3\u8f2a\u3059\u306a\u308f\u3061\u65cb\u56de\u5916\u8f2a\u3092\u53d6\u308a\u4e0a\u3052\u308b\u304c\uff0c\u65cb\u56de\u5185\u8f2a\u306b\u3064\u3044\u3066\u3082\u307e\u3063\u305f\u304f\u540c\u69d8\u306e\u8b70 \u8ad6\u304c\u5f53\u3066\u306f\u307e\u308b\uff0e\n2\u30fb3 LF\u306b\u5bfe\u3059\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306e\u5b9f\u6e2c\u5024 \u5b9f\u8eca\u306b\u304a\u3051\u308b\uff0cLF\u306b\u5bfe\u3059\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306e\u5b9f\u6e2c\u5024\u306e\u4f8b\u306b\u3064\u3044\u3066\u8ff0\u3079\u3066\u304a\u304f\uff0e\u6e2c\u5b9a\u306fAB Dynamics\u793e\u306e K&C\u306b\u3088 \u308a\u884c\u3063\u305f\uff0e\u8868 2 \u306b\u6e2c\u5b9a\u3055\u308c\u305f\u5e02\u8ca9\u8eca 4 \u8eca\u7a2e\u306e\u30c8\u30fc\u89d2\u5909\u5316\u304a\u3088\u3073\u30ad\u30e3\u30f3\u30d0\u89d2\u5909\u5316\u3092\u793a\u3059\uff0e\u6e2c\u5b9a\u306e\u969b\u306f LF \u3068\u3057\u3066\u5de6 \u53f3\u8f2a\u306b\u540c\u6642\u304b\u3064\u540c\u65b9\u5411\u306b 1000 N\uff08\u30bf\u30a4\u30e4\u5206\u62c5\u8377\u91cd\u306e\u7d04 25%\u76f8\u5f53\uff09\u3092\u8ca0\u8377\u3057\u305f\uff0e\u6e2c\u5b9a\u3055\u308c\u305f\u30c8\u30fc\u89d2\u5909\u5316\u306e\u8ca0\u8868\u793a\u306f\uff0c \u30c8\u30fc\u89d2\u5909\u5316\u306f\u8eca\u4f53\u304c\u66f2\u304c\u308b\u65b9\u5411\u3068\u306f\u9006\u65b9\u5411\u3067\u3042\u308b\u3053\u3068\u3092\u793a\u3057\uff0c\u30ad\u30e3\u30f3\u30d0\u89d2\u5909\u5316\u306e\u6b63\u8868\u793a\u306f\u30bf\u30a4\u30e4\u306e\u63a5\u5730\u70b9\u304c\u8eca\u4e21 \u5185\u5074\u3078\u5909\u4f4d\u3057\u3066\u5012\u308c\u308b\u52d5\u304d\u3067\u3042\u308b\u3053\u3068\u3092\u793a\u3057\u3066\u3044\u308b\uff0e\u4e00\u822c\u7684\u306a\u81ea\u52d5\u8eca\u306e\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u3067\u306f\u8868 2\u306e\u30c8\u30fc \u89d2\u5909\u5316\u306e\u6b04\u306e\u3088\u3046\u306b\uff0c\u8eca\u4e21\u304c\u66f2\u304c\u308d\u3046\u3068\u3059\u308b\u65b9\u5411\u3068\u306f\u53cd\u5bfe\u306e\u65b9\u5411\u306b\u30c8\u30fc\u89d2\u5909\u5316\u304c\u751f\u3058\u308b\u3088\u3046\u8a2d\u5b9a\u3055\u308c\u308b\uff0e\u3053\u3046\u3057 \u305f\u8a2d\u5b9a\u306e\u4e8b\u3092 LF-C/S \u304c\u30a2\u30f3\u30c0\u30b9\u30c6\u30a2\u3067\u3042\u308b\u3068\u547c\u3093\u3067\u3044\u308b\uff0e\u3053\u308c\u306e\u76ee\u7684\u306f\u9ad8\u901f\u8d70\u884c\u306a\u3069\u306b\u304a\u3044\u3066\u64cd\u8235\u306b\u5bfe\u3059\u308b\u8eca \u4e21\u306e\u904e\u654f\u306a\u53cd\u5fdc\u3092\u6291\u5236\u3057\uff0c\u9069\u5207\u306a\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30db\u30a4\u30fc\u30eb\u30c8\u30eb\u30af\u3092\u5f97\u308b\u3053\u3068\u306b\u3042\u308b\uff0e\u524d\u8ff0\u306e\u3088\u3046\u306b\u672c\u8ad6\u6587\u3067\u306f\u65cb\u56de \u5916\u8f2a\u306e\u6319\u52d5\u306b\u6ce8\u76ee\u3057\u3066\u8aac\u660e\u3092\u884c\u3046\uff0e\u65cb\u56de\u5916\u8f2a\u306b\u304a\u3051\u308b\u30a2\u30f3\u30c0\u30b9\u30c6\u30a2\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u8eca\u4e21\u5916\u5411\u304d\u306e\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a \u308b\uff0e\u306a\u304a\u8868 2\u306e\u5404\u5024\u306e\u7d76\u5bfe\u5024\u306f\u5927\u304d\u306a\u3082\u306e\u3067\u306f\u306a\u3044\uff08\u7279\u306b\u30c8\u30fc\u89d2\u5909\u5316\u306f 10-2deg\u7a0b\u5ea6\uff09\u304c\uff0c\u3053\u306e\u7a0b\u5ea6\u306e\u5024\u3067\u3082\u52d5\u7684 \u306a\u30b9\u30c6\u30a2\u30ea\u30f3\u30b0\u30db\u30a4\u30fc\u30eb\u30c8\u30eb\u30af\u3084\u8eca\u4e21\u30e8\u30fc\u6319\u52d5\u306b\u5f71\u97ff\u3092\u4e0e\u3048\u308b\u3053\u3068\u306f\u77e5\u3089\u308c\u3066\u3044\u308b\uff08\u7686\u5ddd\uff0c2013\uff09\uff0e\n\u30f3\u30b7\u30e7\u30f3\u306e\u8a2d\u8a08\u8af8\u5143\u3092\u660e\u3089\u304b\u306b\u3057\u305f\uff0e\n3\u30fb1 LF\u4f5c\u7528\u6642\u306e\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u6319\u52d5", + "\u00a9 The Japan Society of Mechanical Engineers\n\u30db\u30a4\u30fc\u30eb\u63a5\u5730\u70b9\u306b LF\u304c\u4f5c\u7528\u3059\u308b\u3068\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u5404\u70b9\u306f\u4e3b\u306b XY\u5e73\u9762\u306b\u5e73\u884c\u306a\u9762\u5185\u3067\u5909\u4f4d\u3057\uff0c\u305d\u306e\u7d50\u679c\u3068\u3057 \u3066\u30db\u30a4\u30fc\u30eb\u306b\u30c8\u30fc\u89d2\u5909\u5316\u304c\u751f\u3058\u308b\uff0e\u3053\u3053\u3067\u306f\uff0c\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u5404\u70b9\u306b\u4f5c\u7528\u3059\u308b\u529b\u3068\u305d\u308c\u306b\u3088\u308b\u6319\u52d5\u306b\u3064\u3044\u3066\u8003 \u5bdf\u3092\u884c\u3046\uff0e\u307e\u305a\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u652f\u6301\u70b9\u3067\u3042\u308b\u70b9 A, B, C \u306b\u4f5c\u7528\u3059\u308b\u529b\u306e Y \u8ef8\u65b9\u5411\u6210\u5206\u306e\u5411\u304d\u304a\u3088\u3073\u5927\u304d\u3055\u306b\u3064\u3044 \u3066\u8003\u5bdf\u3092\u884c\u3046\u305f\u3081\uff0c\u56f3 4(a)\u306b\u793a\u3059\u8eca\u4e21\u5185\u5074\u304b\u3089\u898b\u305f\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u5074\u9762\u8996\u3092\u8003\u3048\u305f\uff0e \u56f3 4(a)\u306b\u304a\u3044\u3066 LF \u306f\u63a5\u5730\u70b9 J\u3067\u7d19\u9762\u624b\u524d\u65b9\u5411\u3059\u306a\u308f\u3061 Y\u8ef8\u8ca0\u306e\u5411\u304d\u306b\u4f5c\u7528\u3059\u308b\uff0e\u3053\u306e\u529b\u306f\u8eca\u4e21\u306b\u5bfe\u3057\u3066\u306f\u5185\u5411\u304d\u306b\u306a\u308b\uff0e\u3053\u306e\u3068\u304d\u70b9 B, C\u3092 \u901a\u308b\u8ef8\u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u91e3\u5408\u3044\u306b\u3088\u308a\uff0c\u70b9 A \u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u63a5\u5730\u70b9 J \u306b\u4f5c\u7528\u3059\u308b LF \u3068\u540c\u3058\u5411\u304d\u3059\u306a\u308f\u3061\u8eca \u4e21\u5185\u5411\u304d\u3068\u306a\u308b\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\u307e\u305f\uff0c\u70b9 A, J\u3092\u901a\u308b\u8ef8\u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u304a\u3088\u3073\u30db\u30a4\u30fc\u30eb\u90e8\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u91e3\u5408 \u3044\u306b\u3088\u308a\uff0c\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u3068\u3082\u306b\u8eca\u4e21\u5916\u5411\u304d\u3068\u306a\u308b\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\u6b21\u306b\u70b9A, B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5927\u304d\u3055 \u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u4ee5\u4e0b\u3067\u306f\u3053\u308c\u3089\u306e\u529b\u306e\u5927\u304d\u3055\u3092\u305d\u308c\u305e\u308c FAY\uff0cFBY\uff0cFCY\u3068\u8868\u3057\uff0cLF\u306e\u5927\u304d\u3055\u3092 FY\u3068\u8868\u3057\u305f\uff0e\u8ef8 A-J\u3068\u8ef8 B-C\u306e\u4ea4\u70b9\u3092 L\u3068\u3057\uff0c\u70b9 L\u304b\u3089\u70b9 A, B, C, J\u307e\u3067\u306e\u8ddd\u96e2\u3092\u305d\u308c\u305e\u308c a\uff0cb\uff0cc\uff0cd\u3068\u3057\u3066\u5404\u70b9\u306b\u4f5c\u7528\u3059\u308b\u529b \u306e\u5927\u304d\u3055\u306e\u6bd4\u3092\u8868\u3059\u3068 FAY : FY =d : a, FBY : FCY = c : b\u3068\u306a\u308b\uff0e\u3053\u308c\u3089\u3092\u30db\u30a4\u30fc\u30eb\u90e8\u80cc\u9762\u8996\u3067\u3042\u308b\u56f3 4(b)\u306b\u9ed2\u77e2\u5370\u3067 \u793a\u3059\uff0e\u3064\u304e\u306b\uff0c\u70b9 A \u306e\u5909\u4f4d\u306e\u5411\u304d\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u70b9 A \u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u70b9 A \u306b\u8a2d\u7f6e\u3055\u308c\u305f\u3070\u306d\u306b\u3088\u308a\u751f\u3058\u308b\uff0e \u305d\u306e\u305f\u3081\u70b9 A\u306f\u8eca\u4e21\u5916\u5411\u304d\u306b\u5909\u4f4d\u3059\u308b\uff0e\u3053\u308c\u3092\u56f3 4(b)\u306b\u767d\u629c\u304d\u77e2\u5370\u3067\u793a\u3057\u305f\uff0e\n\u3064\u304e\u306b\u56f3 5\u306e\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u5e73\u9762\u8996\u3092\u4f7f\u3063\u3066\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u304a\u3088\u3073\u5909\u4f4d\u306b\u3064\u3044\u3066\u8003\u3048\u305f\uff0e\u307e\u305a\u30db\u30a4\u30fc\u30eb\u90e8 \u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u3053\u3053\u3067\u306f X\u8ef8\u65b9\u5411\u6210\u5206\u3082\u542b\u3081\u3066\u8003\u3048\u308b\uff0e\u70b9 C\u304a\u3088\u3073\u70b9 H\u306f\u30dc\u30fc\u30eb\u30b8\u30e7 \u30a4\u30f3\u30c8\u3067\u3042\u308b\u305f\u3081\uff0c\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u30bf\u30a4\u30ed\u30c3\u30c9\u8ef8 C-H\u306b\u6cbf\u3046\u3082\u306e\u306b\u306a\u308b\uff0e\u524d\u8ff0\u306e\u3088\u3046\u306b\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 C\u306b \u4f5c\u7528\u3059\u308b\u529b\u306e Y\u8ef8\u65b9\u5411\u6210\u5206\u306f\u8eca\u4e21\u5916\u5411\u304d\u306e\u305f\u3081\uff0c\u56f3 5\u306e\u5e73\u9762\u8996\u306b\u304a\u3051\u308b\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u8eca\u4e21\u5916 \u5411\u304d\uff0c\u304b\u3064\u3084\u3084\u524d\u65b9\u3092\u5411\u304f\uff0e\u70b9 A\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f Y\u8ef8\u306b\u6cbf\u3063\u305f\u65b9\u5411\u3068\u3059\u308b\u3068\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u529b\u306e\u91e3\u5408\u3044\u304b\u3089\uff0c\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u8eca\u4e21\u5916\u5411\u304d\uff0c\u304b\u3064\u3084\u3084\u5f8c\u65b9\u3092\u5411\u304f\uff0e\u56f3 5\u3067\u306f\u3053\u308c\u3089\u306e\u529b\u3092\u9ed2\u77e2\u5370\u3067\u8868\u3057\u305f\uff0e\u307e\u305f\u70b9 B, C\u306b\u4f5c\u7528 \u3059\u308b\u529b\u306e\u5927\u304d\u3055\u3092\u305d\u308c\u305e\u308c FB, FC\u3068\u8868\u793a\u3057\u305f\uff0e\u3072\u304d\u3064\u3065\u304d\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u304a\u3088\u3073\u30bf\u30a4\u30ed\u30c3\u30c9\u4e0a\u306e\u70b9 C\u306b\u4f5c\u7528 \u3059\u308b\u529b\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u3053\u308c\u3089\u306e\u70b9\u306b\u306f\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u53cd\u4f5c\u7528\u304c\u50cd\u304f\u305f\u3081\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u3068\u306f\u5411\u304d\u304c\u9006\u3067\u5927\u304d\u3055\u304c\u540c\u3058\u529b\u304c\u4f5c\u7528\u3059\u308b\uff0e" + ] + }, + { + "image_filename": "designv8_17_0000764_f_version_1633592417-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000764_f_version_1633592417-Figure3-1.png", + "caption": "Figure 3. Payload swing angle sensor optimized using a generative design approach.", + "texts": [ + " x ( \u03d5x, \u03d5y ) = l sin \u03d5x cos \u03d5y y ( \u03d5x, \u03d5y ) = l sin \u03d5y cos \u03d5x (1) Assuming that the angles \u03d5x and \u03d5y are small, the relations (1) are simplified to an approximate shape (2). x(\u03d5x) = l\u03d5x y ( \u03d5y ) = l\u03d5y (2) The entire functional prototype of this device was created using additive manufacturing technologies, thus it was printed on a conventional 3D printer. This approach makes it possible to produce components that cannot be produced in any other way. The parts were very strong and the equipment showed no signs or excessive wear during the tests. A more interesting version of the device is in Figure 3. The shape of the device of Figure 1 has been optimized using the Generative Design module so the voltage is the same at each point of the device. Of course, except for the flexible elements with strain gauges, which are the sensitive part of the sensor. At first glance, a highly peculiar shape is, of course, unproducible by conventional chip machining. However, this is not a problem with additive manufacturing technologies. The second prototype of the device was made the same as this. For more information on optimizing the design of this device using the generative design module, see [8]. In this paper, all measurements made were performed on the second prototype shown in Figure 3. The experiment was designed to determine the accuracy and repeatability of the measuring device. In Figure 4, a ruler is visible and a point is attached to the weight on the rope. In the equilibrium position of the system, the tip of the weight points to the zero of the ruler. The ruler has a symmetrical distribution, i.e., from zero in the middle to 10 cm on each side. Thus, it is possible to measure the displacement from the equilibrium position to each side. In this experiment, the pendulum moved only in the plane; the spherical motion would say nothing about the accuracy of the device" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002984__8_2_8_20-00446__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002984__8_2_8_20-00446__pdf-Figure4-1.png", + "caption": "Fig. 4 Schematic diagram of the FCP for the optimal arrangement of linear springs", + "texts": [ + " 1p(tm, um) = [x1(tm, um) y1(tm, um) z1(tm, um)]T , (1) where x1(tm, um), y1(tm, um) and z1(tm, um) are arbitrary functions. If 1p is a curve (line), only tm is used and um is specified to be zero. Besides, ranges of relative motion between the links are specified as range of main parameters as follows. Am = {(tm, ...)| tm,0 \u2266 tm \u2266 tm,1, ...} (2) As described above, parameters which have not been chosen are fixed to zero in Am. In order to reduce stiffness in main-directions, linear springs are optimally arranged between the links so as to minimize elastic forces applied in main-directions. Fig.4 shows the schematic diagram of the FCP. \u03a31 is the reference 4 2 \u00a9 2021 The Japan Society of Mechanical Engineers [DOI: 10.1299/mej.20-00446] coordinate system fixed on the link with the cam surface (link1). \u03a32 is the reference coordinate system fixed on the link with the spherical surface (link2), of which origin is normally at1p. Several linear springs are arranged between the two links. The endpoint positions of the i-th linear spring attached on the link 1 and link 2 are represented as 1c1,i on \u03a31 and 2c2,i on \u03a32, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003167_ostyka2018_01003.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003167_ostyka2018_01003.pdf-Figure1-1.png", + "caption": "Fig. 1. 3-D model of hydrodynamic brake-retarder.", + "texts": [ + " In this regard, to obtain the desired efficiency, the retarder should have a greater energy intensity. The purpose of the work is to select the parameters that provide a high level of power consumption of the hydraulic brake-retarder. According to the results of the analysis of literature sources [2-3], it was found that the mechanism in the form of a double fluid coupling has the greatest efficiency. Therefore, as an initial version of the hydrodynamic brake-retarder mechanism was adopted in the form of a dual fluid coupling. Figure 1 shows a three-dimensional model of the hydrodynamic retarder brake, made in CAD program Solid Edge ST9. Increasing the energy consumption of the brake-retarder is possible by changing its design parameters and increasing the speed. In this paper, we investigate the dependence of the energy intensity of the hydrodynamic brake-retarder on the type of its blade system, with constant other design parameters. The study was conducted using Computational Fluid Dynamics (CFD) of software product FlowVision [4]", + " In this regard, to obtain the desired efficiency, the retarder should have a greater energy intensity. The purpose of the work is to select the parameters that provide a high level of power consumption of the hydraulic brake-retarder. According to the results of the analysis of literature sources [2-3], it was found that the mechanism in the form of a double fluid coupling has the greatest efficiency. Therefore, as an initial version of the hydrodynamic brake-retarder mechanism was adopted in the form of a dual fluid coupling. Figure 1 shows a three-dimensional model of the hydrodynamic retarder brake, made in CAD program Solid Edge ST9. Increasing the energy consumption of the brake-retarder is possible by changing its design parameters and increasing the speed. In this paper, we investigate the dependence of the energy intensity of the hydrodynamic brake-retarder on the type of its blade system, with constant other design parameters. The study was conducted using Computational Fluid Dynamics (CFD) of software product FlowVision [4]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002883_9393742_09393751.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002883_9393742_09393751.pdf-Figure6-1.png", + "caption": "Fig. 6. Topology modification of the 2D analysis model of ADS-SRM. (a) Modified MEC model. (b) Flux line distributions after modification.", + "texts": [ + " The leakage flux paths bypass a portion of magnetic flux in the air gap, thus reducing the electrical utilization and narrowing the speed range [16]. B. Inspiration for Leakage Field Reduction In the previous section, the leakage field in ADS-SRM is reflected by the 2D analysis model. However, the leakage field in ADS-SRM should be much more complex due to the multiple air gaps, but it has no impact on the discussion on the solutions. To shield the flux leakage in Fig. 5(a), the additional MMF in reverse series in the gap between the excitation pole and the flux-conductive ring is necessary, as shown in Fig. 6(a). It is observed that the PMs are installed with the magnetic polarity conflicting with that of the excitation pole. The corresponding flux line distributions are shown in Fig. 6(b). It is indicated in Fig. 6(b) that the leakage flux is almost eliminated. By contrast, much more flux lines go through the rotor segments. The comparison of the static-torque characteristics between the 2D analysis model without and with the PM shield at the phase excitation of 8A is shown in Fig. 7. It can be observed that, with the PM shield, the torque-production capability increases significantly. Hence, 2D finite-element analysis (FEA) proves the effectiveness of the PM shield for the leakage field shielding and the torque out improvement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004555_f_version_1699369650-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004555_f_version_1699369650-Figure3-1.png", + "caption": "Figure 3. Ultrasonic fatigue testing machine schematic [23] (used under Creative Commons CC-BY license).", + "texts": [ + " Fatigue tests conducted at low frequencies (<150 Hz) will hereafter be referred to as conventional fatigue tests. The frequency of 20 kHz is used for UFT as it is outside of the audible range of the human ear, but greater frequencies than this result in increased cycle counting errors and a reduction in the length of the specimen [18]. It is possible to employ UFT for cyclic bending [19], torsional [20], or multiaxial [21] loading, but only uniaxial tension-compression loading will be considered in this paper. UFT machines (Figure 3) use ultrasonic transducers (usually a piezoelectric actuator) to generate mechanical vibration from an electrical signal [22]. The longitudinal vibration is then amplified as it is transmitted through the booster and horn to the specimen, typically attached by threads [22]. Specimens are excited at their natural frequency; therefore, the maximum stress, but minimum displacement, is experienced at the centre of the specimen. VHCF tests have been demonstrated with both bespoke UFT apparatuses constructed at research institutions and equipment from commercial manufacturers [16]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002228_0158-022-03174-4.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002228_0158-022-03174-4.pdf-Figure4-1.png", + "caption": "Fig. 4 Block structure of eight-block structured C-meshes", + "texts": [ + " Also shown is the aerodynamic surface mesh and the structural grid. A 2515 node wing-box structural model is used with the modes defined by Haase et\u00a0al. (2002). Throughout this work, a trimmed cruise condition of CL = 0.4 at M\u221e = 0.85 is used. Unless otherwise stated, all wings are trimmed to this condition. The MDO wing has 18 defined structural modes and all are used for this work. To ensure sufficient aerodynamic resolution, a mesh dependence study is presented. A family of eight-block structured C-meshes (block structure is given in Fig.\u00a04 was generated using the methods of Allen (2008) to give high quality meshes. These range in size from 2.1 million to 0.13 million cells, and are designated L1 (2.1M), L2 (1.1M), L3 (580k), L4 (260k) and L5 (130k); sizes were chosen with approximately a two-times scaling between mesh levels, and to maximise the number of multigrid levels for each mesh. Each mesh was used to produce both a rigid and aeroelastic solution and the final force coefficients of each run are given in Table\u00a01. The structural deflection is calculated based on the deformation of the structural node closest to the aerodynamic tip" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003647_f_version_1577096875-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003647_f_version_1577096875-Figure9-1.png", + "caption": "Figure 9. Linear table for normal force, shear force and spatial mapping experiments; (a) depicts an overview of the linear table; (b) shows a close up of the f/t sensor and finger attached to the axes", + "texts": [ + " As the PCB for the joint angle encoders contains just two sensors and a connector, it is fairly easy to adjust the distance between the two sensors for different finger sizes directly in the PCB layout. We hence produced PCBs in three different sizes for the little finger, the middle finger, and the other two fingers which can accommodate the same PCB size due to their similar dimension. A series of experiments were conducted on the physical demonstrators to assess the performance of the sensors individually and as a coherent system. For the experiments regarding normal and shear forces, as well as a spatial mapping, a two-axis linear table was used as depicted in Figure 9. Each axis was a precision linear stage (PT4808, MM Engineering GmbH, Brackenheim, Germany) with 0.5 mm displacement per turn attached to a stepper motor with 200 steps per turn. A force/torque sensor (Mini 40, ATI Industrial Automation, Apex, NC, USA) was mounted on one axis. The sensor could be equipped with a cylindrical probe with a diameter of 5.3 mm, which was small enough to allow applying loads to individual sensors. A sensorised finger could be attached to the other axis, enabling the probe to apply normal forces to different parts of the finger along one axis, as well as shear forces when the finger was moved while normal forces were applied", + " An overview over the positions of all tactile sensors and their corresponding designators in all physical demonstrators can be seen in Figure 10. Two types of normal force sensors were built into the fingers. The barometer-based normal force sensors were able to resolve small forces but also saturate at comparatively low forces. The Hall effect-based sensors did not offer the same level of resolution but were able to measure magnitudes higher forces before saturation sets in. For the normal force experiments we used the aforementioned linear table (see Figure 9) to allow applying and measuring well-defined forces. In Figure 11 two measurements for Hall effect-based sensors (a,b) and two measurements for barometer-based sensors (c,g) are presented in green. The ground truth measurement of the force/torque sensor is plotted in orange (labelled Fn). These two measurements together are combined in the hysteresis plots (d\u2013f,h) corresponding to the four sensor measurements (a\u2013c,g). To show the difference in resolution we carried out an additional experiment where a small metal plate was placed on the adjacent sensors RIB and RIH on the ring finger" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004917_O201709641401598.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004917_O201709641401598.pdf-Figure2-1.png", + "caption": "Fig. 2. Modeling and external linkage circuit diagram of BLDC motor designed", + "texts": [ + " The motor was modeled through the finite elements method, the number of poles was the same as 4 poles of the existing DC motor, and the number of slots were set at 4 poles and 6 slots for the combination (2/3) of the number of poles and number of slots considering its making. Since heat is generated inside the motor due to the copper loss of stator winding, it is more favorable to protect against the heat if more surface area of slots inside is secured inside. Therefore, the tooth concentrated winding method was applied to secure the surface area of slots as much as possible by increasing the coil space factor. Fig. 2 is the model and external linkage circuit for finite elements method of BLDC motor that replaces DC motor. Fig. 3 is the 120\u00b0 two-phase commutation method showing the motor phase current and torque waveform in which finite elements method was applied [12]. 468 \u2502 J Electr Eng Technol.2017; 12(1): 466-471 The sensorless control method of BLDC motor often uses a method that detects the ZCP of back EMF included in terminal voltage. This is because it enables control by forming a relatively simple external circuit and achieves the maximum size of back EMF once the motor reaches the rated speed, making ZCP detection easier" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001092_2_1_12_22004507__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001092_2_1_12_22004507__pdf-Figure5-1.png", + "caption": "Fig. 5. Dimension reference drawing for magnet fixation by splicing", + "texts": [ + " First, the design focuses on fixing the magnet effectively to relieve magnetic saturation. Accordingly, the magnet is fixed by splicing, which is suitable for applications with arbitrary steering. the advantages of this approach are as follows: because the magnet structure is relatively complete, its overall mechanical strength is improved; because the bolt is fixed, the force is more uniform and service life is improved. An additional process for installing the plug is included, and the geometrical structure of the fixed magnets in the motor is shown in Fig. 5. Here A, B and C are the Magnet thickness, Magnet angle of spread and Frame thickness. Figure 6 is a color block representation of the magnetic flux density of the spliced magnets. The rated saturation magnetic flux density is 2.2 T. The areas where the maximum magnetic saturation occur after applying the new improvement strategy are clearly seen. Compared with the traditional design, the dovetail grooves are more evenly distributed. Figure 7 depicts the distribution of the magnetic field lines for the spliced configuration that relieves magnetic saturation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003069_df_ru_2024_02_07.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003069_df_ru_2024_02_07.pdf-Figure6-1.png", + "caption": "Figure 6 \u2014 Air flow velocity fields in the flow area with belting", + "texts": [], + "surrounding_texts": [ + "\u0414\u043b\u044f \u0443\u043b\u0443\u0447\u0448\u0435\u043d\u0438\u044f \u0441\u0445\u043e\u0434\u0438\u043c\u043e\u0441\u0442\u0438 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0432 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u0441\u0445\u0435\u043c\u044b \u0438\u043d\u0442\u0435\u0440\u043f\u043e\u043b\u044f\u0446\u0438\u0438 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u043f\u0440\u0438\u043d\u044f\u0442\u0430 \u043e\u043f\u0446\u0438\u044f PRESTO! 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\u0443\u0441\u0440\u0435\u0434-\n\u043d\u0435\u043d\u043d\u0430\u044f \u043f\u043e \u0440\u044f\u0434\u0430\u043c1 2 3 4 5 6 \u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0441 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u043e\u043c\n\u0442. 1 3,2 2,8 2,7 2,8 2,9 3,1 2,9 3,2 \u0442. 2 2,8 2,6 2,4 2,3 2,8 2,9 2,6 2,8 \u0442. 3 2,9 2,7 2,4 2,4 2,7 2,8 2,7 2,9 \u0442. 4 2,8 2,8 2,4 2,4 2,6 2,9 2,7 2,9 \u0442. 5 4,0 3,4 3,2 3,3 3,5 3,9 3,6 3,8 \u0442. 6 3,8 3,3 3,2 3,3 3,5 3,7 3,5 3,4 \u0442. 7 3,3 3,0 2,9 2,8 2,8 3,0 3,0 3,2 \u0442. 8 3,1 3,0 2,5 2,4 3,1 3,0 2,9 3,1 \u0442. 9 3,7 3,6 3,2 3,3 3,7 3,8 3,6 3,8 \u0442. 10 3,1 3,2 3,1 3,0 3,4 3,3 3,2 3,3 \u0442. 11 3,2 2,8 3,0 3,1 3,1 3,3 3,1 3,3 \u0442. 12 6,1 6,1 6,0 6,1 6,0 6,2 6,1 6,6 \u0442. 13 8,2 8,2 8,0 7,9 8,0 8,1 8,1 8,5\n\u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0431\u0435\u0437 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u0430 \u0442. 1 3,9 3,8 3,7 3,5 3,6 4,0 3,8 4,1 \u0442. 2 2,8 2,6 2,6 2,7 2,9 3,1 2,8 3,0 \u0442. 3 3,0 3,0 2,9 3,0 3,2 3,4 3,1 3,2 \u0442. 4 3,1 3,0 2,8 2,9 3,0 3,2 3,0 3,2 \u0442. 5 3,2 3,1 2,7 2,8 3,0 3,1 3,0 3,2 \u0442. 6 3,0 3,0 2,9 2,7 2,7 2,9 2,9 3,1 \u0442. 7 3,2 3,1 2,6 2,5 3,1 3,0 2,9 3,2 \u0442. 8 3,1 3,2 2,8 2,8 3,0 2,9 3,0 3,1 \u0442. 9 3,2 3,2 2,7 3,0 3,2 3,3 3,1 3,3 \u0442. 10 2,8 2,9 2,6 2,6 2,9 3,0 2,8 3,1 \u0442. 11 3,1 2,9 2,8 2,9 3,2 3,0 3,0 3,3 \u0442. 12 3,7 3,5 3,3 3,6 3,4 3,5 3,5 3,8 \u0442. 13 6,6 6,1 5,9 6,3 6,5 6,2 6,3 6,8\n\u041f\u0440\u0438\u043c\u0435\u0447\u0430\u043d\u0438\u0435: *\u043e\u0442\u0441\u0447\u0435\u0442 \u0432\u0435\u0434\u0435\u0442\u0441\u044f \u043e\u0442 \u043f\u0440\u0430\u0432\u043e\u0439 \u0431\u043e\u043a\u043e\u0432\u0438\u043d\u044b \u043f\u043e \u0445\u043e\u0434\u0443 \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044f \u043a\u043e\u043c\u0431\u0430\u0439\u043d\u0430.\n\u0422\u0430\u0431\u043b\u0438\u0446\u0430 \u2014 \u0420\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432 \u0438 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f Table \u2014 Results of experimental measurements and modeling", + "\u041f\u0430\u0434\u0435\u043d\u0438\u0435 \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0438 \u043f\u043e\u0442\u043e\u043a\u0430 \u043d\u0430\u0431\u043b\u044e\u0434\u0430\u0435\u0442\u0441\u044f \u043f\u043e \u0446\u0435\u043d\u0442\u0440\u0443 \u043e\u0447\u0438\u0441\u0442\u043a\u0438 (\u0441\u043c. 3 \u0438 4 \u0440\u044f\u0434\u044b \u0437\u043e\u043d\u0434\u043e\u0432 \u0432 \u0442\u0430\u0431\u043b\u0438\u0446\u0435), \u0447\u0442\u043e \u043e\u0431\u044a\u044f\u0441\u043d\u044f\u0435\u0442\u0441\u044f \u0437\u0430\u0442\u0440\u0443\u0434\u043d\u0438\u0442\u0435\u043b\u044c\u043d\u044b\u043c \u0437\u0430\u0431\u043e\u0440\u043e\u043c \u0432\u043e\u0437\u0434\u0443\u0445\u0430 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\u043c\u0430\u0442\u0435\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f, \u0432\u044b\u0448\u0435 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u0439 \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u0440\u0435\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432, \u043d\u043e \u0440\u0430\u0441\u0445\u043e\u0436\u0434\u0435\u043d\u0438\u044f \u043d\u0435 \u043f\u0440\u0435\u0432\u044b\u0448\u0430\u044e\u0442 10 % (\u0441\u043c. \u0442\u0430\u0431\u043b\u0438\u0446\u0443). \u042d\u0442\u043e \u043f\u043e\u043a\u0430\u0437\u044b\u0432\u0430\u0435\u0442 \u0430\u0434\u0435\u043a\u0432\u0430\u0442\u043d\u043e\u0441\u0442\u044c 2D-\u043c\u043e\u0434\u0435\u043b\u0438 \u0438 \u043f\u043e\u0437\u0432\u043e\u043b\u044f\u0435\u0442 \u043f\u0440\u043e\u0432\u043e\u0434\u0438\u0442\u044c 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\u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u0437\u0435\u0440\u043d\u0430.\n\u0421\u043f\u0438\u0441\u043e\u043a \u043b\u0438\u0442\u0435\u0440\u0430\u0442\u0443\u0440\u044b 1. \u0424\u0440\u043e\u043b\u043e\u0432, \u041a.\u0412. \u041c\u0430\u0448\u0438\u043d\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u0438\u0435. \u042d\u043d\u0446\u0438\u043a\u043b\u043e\u043f\u0435\u0434\u0438\u044f: \u0432 40 \u0442. /\n\u041a.\u0412. \u0424\u0440\u043e\u043b\u043e\u0432. \u2014 \u041c.: \u041c\u0430\u0448\u0438\u043d\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u0438\u0435, 2002. \u2014 \u0422. IV-16: \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0448\u0438\u043d\u044b \u0438 \u043e\u0431\u043e\u0440\u0443\u0434\u043e\u0432\u0430\u043d\u0438\u0435. \u2014 720 \u0441. 2. Experimental study on the influence of working parameters of centrifugal fan on airflow field in cleaning room / C. Zhang [et al.] // Agriculture. \u2014 2023. \u2014 Vol. 13, iss. 7. \u2014 DOI: https://doi.org/10.3390/agriculture13071368. 3. Operation technological process research in the cleaning system of the grain combine / I. Badretdinov [et al.] // Journal of Agricultural Engineering. \u2014 2021. \u2014 Vol. 52, no. 2. \u2014 DOI: https://doi.org/10.4081/jae.2021.1129. 4. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0418.\u0414. \u041d\u0430\u0443\u0447\u043d\u043e\u0435 \u043e\u0431\u043e\u0441\u043d\u043e\u0432\u0430\u043d\u0438\u0435 \u0438 \u0441\u043e\u0432\u0435\u0440\u0448\u0435\u043d\u0441\u0442\u0432\u043e\u0432\u0430\u043d\u0438\u0435 \u043f\u043d\u0435\u0432\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0438\u0445 \u0441\u0438\u0441\u0442\u0435\u043c \u0441\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0445 \u043c\u0430\u0448\u0438\u043d \u043d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u0442\u0435\u0445\u043d\u043e\u043b\u043e\u0433\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u0430 / \u0418.\u0414. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0421.\u0413. \u041c\u0443\u0434\u0430\u0440\u0438\u0441\u043e\u0432 // \u0412\u0435\u0441\u0442\u043d. \u041d\u0413\u0418\u042d\u0418. \u2014 2019. \u2014 \u2116 9(100). \u2014 \u0421. 5\u201316. 5. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u041d.\u0413. \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0442\u0435\u0440\u0438\u0430\u043b\u044b (\u0432\u0438\u0434\u044b, \u0441\u043e\u0441\u0442\u0430\u0432, \u0441\u0432\u043e\u0439\u0441\u0442\u0432\u0430) / \u041d.\u0413. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u0413.\u0410. \u0425\u0430\u0439\u043b\u0438\u0441, \u041c.\u041c. \u041a\u043e\u0432\u0430\u043b\u0435\u0432. \u2014 \u041c.: \u0418\u041a \u00ab\u0420\u043e\u0434\u043d\u0438\u043a\u00bb, \u0436\u0443\u0440\u043d\u0430\u043b \u00ab\u0410\u0433\u0440\u0430\u0440\u043d\u0430\u044f \u043d\u0430\u0443\u043a\u0430\u00bb, 1998. \u2014 208 \u0441." + ] + }, + { + "image_filename": "designv8_17_0004255_cle_download_175_155-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004255_cle_download_175_155-Figure12-1.png", + "caption": "Figure 12 Aircraft pressure diagram with angle of attack of 6\u00b0 and pneumatic impeller at different positions", + "texts": [], + "surrounding_texts": [ + "Assuming that the medium flowing through the aircraft and the pneumatic impeller is compressible ideal air and the flow process is adiabatic, the continuity equation (mass conservation law), momentum conservation equation and energy conservation equation are satisfied in the working process[11-13]. (1) Equation of continuity ( ) ( ) ( ) 0u v w t x y z \u03c1 \u03c1 \u03c1 \u03c1\u2202 \u2202 \u2202 \u2202 + + + = \u2202 \u2202 \u2202 \u2202 (5) where, \u03c1 is the fluid density; t is time, and u, v, w is the velocity component in x, y, and z. (2) Momentum conservation equation ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) u v w u div puU div gradu S t x v div pvU div gradv S t y w div pwU div gradw S t z \u03c1 \u03c1\u03b7 \u03c1 \u03c1\u03b7 \u03c1 \u03c1\u03b7 \u23a7\u2202 \u2202 + = + \u2212\u23aa \u2202 \u2202\u23aa \u2202 \u2202\u23aa + = + \u2212\u23a8 \u2202 \u2202\u23aa \u23aa\u2202 \u2202 + = + \u2212\u23aa \u2202 \u2202\u23a9 (6) where, Su, Sv, Sw is the generalized source term of the momentum equation and div is the divergence. The momentum conservation law equations in fluid mechanics are called N-S equations (Navier-Stokes equations), which reveal the basic laws of viscous flow and are an important theoretical basis of fluid mechanics[14,15]. (3) Energy conservation equation ( ) ( ) ( ) T p T kdiv uT div gradT S t c \u03c1 \u03c1\u2202 + = + \u2202 (7) where, T is the temperature; k is the heat transfer coefficient; Cp is the specific heat capacity, and ST is the viscous dissipation term. Due to its high prediction of separated flows, the SST k-\u03c9 model has been widely used in the field of aerodynamic performance research of pneumatic components[10]. Therefore, the SST k-\u03c9 model was selected as the turbulence model in this paper. The SST k-\u03c9 model uses the k-\u03c9 model for the calculation of the near wall area, and the k-\u03c9 model is used for the fully developed flow field area. The function expression of SST k-\u03c9 model is as follows: ( ) ( )i k k k k j j kk ku G Y S x x \u03c1 \u03c1 \u23a1 \u23a4\u2202 \u2202 \u2202 \u2202 + = \u0393 + \u2212 +\u23a2 \u23a5\u2202 \u2202 \u2202 \u2202\u23a3 \u23a6 (8) ( ) ( )i j j u G Y S x x\u03c9 \u03c9 \u03c9 \u03c9 \u03c9\u03c1\u03c9 \u03c1\u03c9 \u23a1 \u23a4\u2202 \u2202 \u2202 \u2202 + = \u0393 + \u2212 +\u23a2 \u23a5\u2202 \u2202 \u2202 \u2202\u23a3 \u23a6 (9) where, k is the turbulent kinetic energy; \u03c9 is the turbulent energy dissipation rate; kG is the production term resulting in k due to the average velocity gradient; G\u03c9 is the production term of \u03c9; k\u0393 and \u03c9\u0393 are the diffusivity of k and \u03c9, respectively; Yk and Y\u03c9 are diffusion terms of k and \u03c9, respectively; D\u03c9 is the cross diffusion term; Sk and S\u03c9 are custom source items, respectively." + ] + }, + { + "image_filename": "designv8_17_0002281_aem_30_2_30_173__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002281_aem_30_2_30_173__pdf-Figure3-1.png", + "caption": "Fig. 3 Detailed drawing of proposed model.", + "texts": [ + " 1 \u306b\u793a\u3059\u3002\u5185\u5074\u306e\u56fa\u5b9a\u5b50\u306f\u5404\u8ef8\u99c6\u52d5\u7528\u306e 3 \u3064 \u306e\u30b3\u30a4\u30eb\u3068\uff0c\u30a4\u30f3\u30ca\u30fc\u30e8\u30fc\u30af\u304b\u3089\u69cb\u6210\u3055\u308c\u308b\u30023 \u3064\u306e \u30b3\u30a4\u30eb\u306f\u305d\u308c\u305e\u308c\u304c\u76f4\u4ea4\u3059\u308b\u3088\u3046\u306b\uff0c\u30a4\u30f3\u30ca\u30fc\u30e8\u30fc\u30af \u306b\u91cd\u306d\u5dfb\u304b\u308c\u3066\u3044\u308b\u3002\u307e\u305f\uff0c\u5916\u5074\u306e\u53ef\u52d5\u5b50\u306f\u30d0\u30c3\u30af\u30e8 \u30fc\u30af\u3068 2 \u3064\u306e\u5bfe\u5411\u3059\u308b\u6c38\u4e45\u78c1\u77f3\u304b\u3089\u69cb\u6210\u3055\u308c\u3066\u3044\u308b\u3002 \u9023\u7d61\u5148\uff1a \u5c71\u672c \u7fd4\u5927\uff0c\u3012565-0871 \u5927\u962a\u5e9c\u5439\u7530\u5e02\u5c71\u7530\u4e18 2-1\uff0c 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\u3066\u3044\u305f\u306e\u306b\u5bfe\u3057\uff0c\u63d0\u6848\u3067\u306f 1 \u8ef8\u306e\u307f\u306b\u914d\u7f6e\u3057\u305f\u3053\u3068\u3067 \u3042\u308b\u3002\u65e2\u5b58\u306e\u78c1\u6c17\u56de\u8def\u3067\u306f\uff0c3 \u81ea\u7531\u5ea6\u632f\u52d5\u3092\u5b9f\u73fe\u3059\u308b \u305f\u3081\u306b\uff0c\u6700\u4f4e 6 \u500b\u306e\u6c38\u4e45\u78c1\u77f3\u304c\u5fc5\u8981\u3068\u306a\u308b\u3002\u4e00\u65b9\uff0c\u63d0 \u6848\u30e2\u30c7\u30eb\u3067\u306f Fig. 2(c)\u3067\u793a\u3059\u3088\u3046\u306b\uff0c2 \u500b\u306e\u6c38\u4e45\u78c1\u77f3\u3060 \u3051\u3067 3 \u81ea\u7531\u5ea6\u99c6\u52d5\u304c\u53ef\u80fd\u306a\u78c1\u6c17\u56de\u8def\u3092\u63a1\u7528\u3059\u308b\u3053\u3068\u3067\uff0c \u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u6a5f\u80fd\u3092\u640d\u306a\u308f\u305a\u306b\uff0c\u69cb\u9020\u90e8\u54c1\u6570\u306e\u524a \u6e1b\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002 2.2 \u652f\u6301\u69cb\u9020 Fig. 3(a)\u306b\u53ef\u52d5\u5b50\u306e\u8a73\u7d30\u56f3\u3092\uff0cFig. 3(b)\u306b\u56fa\u5b9a\u5b50\u306e\u8a73 \u7d30\u56f3\u3092\u793a\u3057\u305f\u3002\u672c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u3067\u306f\uff0c4 \u672c\u306e\u30b3\u30a4\u30eb \u3070\u306d\u3092\u7528\u3044\u3066\u652f\u6301\u3092\u884c\u3046\u3002\u6c38\u4e45\u78c1\u77f3\u306b\u8fd1\u3065\u304f\u65b9\u5411(y\u8ef8 \u65b9\u5411)\u3067\u306f\uff0c\u78c1\u77f3\u306e\u5438\u5f15\u529b\u304c\u5927\u304d\u3044\u305f\u3081\uff0c\u30b3\u30a4\u30eb\u3070\u306d\u306e \u4f38\u7e2e\u65b9\u5411\u3068\u3057\u305f\u3002x\u30fbz\u8ef8\u65b9\u5411\u306b\u306f\u30b3\u30a4\u30eb\u3070\u306d\u306e\u6a2a\u525b\u6027 \u3092\u7528\u3044\u3066\u652f\u6301\u3092\u884c\u3046\u3002\u3070\u306d\u304c\u4f38\u7e2e\u65b9\u5411\u306b\u5909\u4f4d\u3057\u305f\u5834\u5408\uff0c \u6a2a\u525b\u6027\u306b\u5f71\u97ff\u304c\u51fa\u308b\u304c\uff0c\u30b9\u30c8\u30ed\u30fc\u30af\u304c\u5c0f\u3055\u304f\uff0c\u5f71\u97ff\u306f \u5c0f\u3055\u3044\u3068\u8003\u3048\u3089\u308c\u308b\u3002\u307e\u305f\uff0c\u4e8b\u524d\u306b\u4f38\u7e2e\u306b\u5bfe\u3059\u308b\u6a2a\u525b \u6027\u3092\u5b9f\u6e2c\u3057\uff0c\u6a2a\u525b\u6027\u306e\u5909\u52d5\u3092\u88dc\u6b63\u3059\u308b\u96fb\u6d41\u3092\u52a0\u3048\u308b\u3053 \u3068\u3067\uff0c\u5236\u5fa1\u4e0a\u3067\u88dc\u511f\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002\u53ef\u52d5\u5b50\u306f\u975e\u78c1\u6027\u4f53 \u306e\u306d\u3058\u3092\u7528\u3044\u3066\u3070\u306d\u3092\u53d6\u308a\u4ed8\u3051\u3066\u3044\u308b\u3002 2.3 \u52d5\u4f5c\u539f\u7406 \u672c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u3067\u306e\u5404\u8ef8\u99c6\u52d5\u306e\u52d5\u4f5c\u539f\u7406\u3092 Fig. 4 \u306b\u793a\u3059\u3002Coil-X \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067\u767a\u751f\u3059\u308b\u78c1\u675f\u306b\u3088\u308a\uff0c \u53ef\u52d5\u5b50\u306f x\u8ef8\u65b9\u5411\u306b\u99c6\u52d5\u3059\u308b\uff08Fig. 4(a)\uff09\u3002\u30b3\u30a4\u30eb\u306b\u5370 \u52a0\u3059\u308b\u96fb\u6d41\u306e\u5411\u304d\u306b\u3088\u308a\u99c6\u52d5\u65b9\u5411\u3092\u5236\u5fa1\u53ef\u80fd\u3067\u3042\u308b\u3002 \u540c\u69d8\u306bCoil-Y \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067 y\u8ef8\u65b9\u5411\u306b\uff08Fig. 4(b)\uff09\uff0c Coil-Z \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067 z \u8ef8\u65b9\u5411\u306b\u99c6\u52d5\u53ef\u80fd\u3067\u3042\u308b \uff08Fig. 4(c)\uff09\u3002 \uff13 \u9759\u63a8\u529b\u7279\u6027\u89e3\u6790 \u672c\u7ae0\u3067\u306f\u63d0\u6848\u3059\u308b 3 \u81ea\u7531\u5ea6\u632f\u52d5\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u9759 \u63a8\u529b\u7279\u6027\u3092\u660e\u3089\u304b\u3068\u3059\u308b\u3002\u5404\u8ef8\u65b9\u5411\u306b\u72ec\u7acb\u3057\u3066\u63a8\u529b\u3092 \u767a\u751f\u53ef\u80fd\u3067\u3042\u308b\u3053\u3068\uff0c\u3055\u3089\u306b\uff0c3 \u8ef8\u540c\u6642\u99c6\u52d5\u6642\u306b\u3082\uff0c \u63a8\u529b\u5e72\u6e09\u304c\u306a\u3044\u3053\u3068\u3092\u793a\u3059\u3002 175(117) \u5f93\u6765\u30e2\u30c7\u30eb 2 \u3064\u306e\u78c1\u6c17\u56de\u8def\u306e\u7c21\u7565\u56f3\u3092 Fig. 2(a)\uff0cFig. 2(b)\u306b\u793a\u3059\u3002\u3053\u308c\u3089\u306f\u99c6\u52d5\u8ef8\u65b9\u5411\u306b\u5bfe\u6297\u3059\u308b\u6c38\u4e45\u78c1\u77f3 \u3068\uff0c\u52b1\u78c1\u3055\u308c\u305f\u30b3\u30a4\u30eb\u306b\u3088\u308b\u78c1\u6c17\u5438\u5f15\uff0c\u53cd\u767a\u529b\u306b\u3088\u3063 \u3066\u99c6\u52d5\u3059\u308b\u3002\u6241\u5e73\u69cb\u9020\u304c\u9054\u6210\u3067\u304d\u305f\u4e00\u756a\u306e\u8981\u56e0\u306f\uff0c\u5f93 \u6765\u3067\u306f\u5404\u8ef8\u306b 2 \u500b\u306e\u78c1\u77f3\u3092 3 \u8ef8\u65b9\u5411\u306b\u305d\u308c\u305e\u308c\u914d\u7f6e\u3057 \u3066\u3044\u305f\u306e\u306b\u5bfe\u3057\uff0c\u63d0\u6848\u3067\u306f 1 \u8ef8\u306e\u307f\u306b\u914d\u7f6e\u3057\u305f\u3053\u3068\u3067 \u3042\u308b\u3002\u65e2\u5b58\u306e\u78c1\u6c17\u56de\u8def\u3067\u306f\uff0c3 \u81ea\u7531\u5ea6\u632f\u52d5\u3092\u5b9f\u73fe\u3059\u308b \u305f\u3081\u306b\uff0c\u6700\u4f4e 6 \u500b\u306e\u6c38\u4e45\u78c1\u77f3\u304c\u5fc5\u8981\u3068\u306a\u308b\u3002\u4e00\u65b9\uff0c\u63d0 \u6848\u30e2\u30c7\u30eb\u3067\u306f Fig. 2(c)\u3067\u793a\u3059\u3088\u3046\u306b\uff0c2 \u500b\u306e\u6c38\u4e45\u78c1\u77f3\u3060 \u3051\u3067 3 \u81ea\u7531\u5ea6\u99c6\u52d5\u304c\u53ef\u80fd\u306a\u78c1\u6c17\u56de\u8def\u3092\u63a1\u7528\u3059\u308b\u3053\u3068\u3067\uff0c \u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u6a5f\u80fd\u3092\u640d\u306a\u308f\u305a\u306b\uff0c\u69cb\u9020\u90e8\u54c1\u6570\u306e\u524a \u6e1b\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002 2.2 \u652f\u6301\u69cb\u9020 Fig. 3(a)\u306b\u53ef\u52d5\u5b50\u306e\u8a73\u7d30\u56f3\u3092\uff0cFig. 3(b)\u306b\u56fa\u5b9a\u5b50\u306e\u8a73 \u7d30\u56f3\u3092\u793a\u3057\u305f\u3002\u672c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u3067\u306f\uff0c4 \u672c\u306e\u30b3\u30a4\u30eb \u3070\u306d\u3092\u7528\u3044\u3066\u652f\u6301\u3092\u884c\u3046\u3002\u6c38\u4e45\u78c1\u77f3\u306b\u8fd1\u3065\u304f\u65b9\u5411(y\u8ef8 \u65b9\u5411)\u3067\u306f\uff0c\u78c1\u77f3\u306e\u5438\u5f15\u529b\u304c\u5927\u304d\u3044\u305f\u3081\uff0c\u30b3\u30a4\u30eb\u3070\u306d\u306e \u4f38\u7e2e\u65b9\u5411\u3068\u3057\u305f\u3002x\u30fbz\u8ef8\u65b9\u5411\u306b\u306f\u30b3\u30a4\u30eb\u3070\u306d\u306e\u6a2a\u525b\u6027 \u3092\u7528\u3044\u3066\u652f\u6301\u3092\u884c\u3046\u3002\u3070\u306d\u304c\u4f38\u7e2e\u65b9\u5411\u306b\u5909\u4f4d\u3057\u305f\u5834\u5408\uff0c \u6a2a\u525b\u6027\u306b\u5f71\u97ff\u304c\u51fa\u308b\u304c\uff0c\u30b9\u30c8\u30ed\u30fc\u30af\u304c\u5c0f\u3055\u304f\uff0c\u5f71\u97ff\u306f \u5c0f\u3055\u3044\u3068\u8003\u3048\u3089\u308c\u308b\u3002\u307e\u305f\uff0c\u4e8b\u524d\u306b\u4f38\u7e2e\u306b\u5bfe\u3059\u308b\u6a2a\u525b \u6027\u3092\u5b9f\u6e2c\u3057\uff0c\u6a2a\u525b\u6027\u306e\u5909\u52d5\u3092\u88dc\u6b63\u3059\u308b\u96fb\u6d41\u3092\u52a0\u3048\u308b\u3053 \u3068\u3067\uff0c\u5236\u5fa1\u4e0a\u3067\u88dc\u511f\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002\u53ef\u52d5\u5b50\u306f\u975e\u78c1\u6027\u4f53 \u306e\u306d\u3058\u3092\u7528\u3044\u3066\u3070\u306d\u3092\u53d6\u308a\u4ed8\u3051\u3066\u3044\u308b\u3002 2.3 \u52d5\u4f5c\u539f\u7406 \u672c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u3067\u306e\u5404\u8ef8\u99c6\u52d5\u306e\u52d5\u4f5c\u539f\u7406\u3092 Fig. 4 \u306b\u793a\u3059\u3002Coil-X \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067\u767a\u751f\u3059\u308b\u78c1\u675f\u306b\u3088\u308a\uff0c \u53ef\u52d5\u5b50\u306f x\u8ef8\u65b9\u5411\u306b\u99c6\u52d5\u3059\u308b\uff08Fig. 4(a)\uff09\u3002\u30b3\u30a4\u30eb\u306b\u5370 \u52a0\u3059\u308b\u96fb\u6d41\u306e\u5411\u304d\u306b\u3088\u308a\u99c6\u52d5\u65b9\u5411\u3092\u5236\u5fa1\u53ef\u80fd\u3067\u3042\u308b\u3002 \u540c\u69d8\u306bCoil-Y \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067 y\u8ef8\u65b9\u5411\u306b\uff08Fig. 4(b)\uff09\uff0c Coil-Z \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067 z \u8ef8\u65b9\u5411\u306b\u99c6\u52d5\u53ef\u80fd\u3067\u3042\u308b \uff08Fig. 4(c)\uff09\u3002 \uff13 \u9759\u63a8\u529b\u7279\u6027\u89e3\u6790 \u672c\u7ae0\u3067\u306f\u63d0\u6848\u3059\u308b 3 \u81ea\u7531\u5ea6\u632f\u52d5\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u9759 \u63a8\u529b\u7279\u6027\u3092\u660e\u3089\u304b\u3068\u3059\u308b\u3002\u5404\u8ef8\u65b9\u5411\u306b\u72ec\u7acb\u3057\u3066\u63a8\u529b\u3092 \u767a\u751f\u53ef\u80fd\u3067\u3042\u308b\u3053\u3068\uff0c\u3055\u3089\u306b\uff0c3 \u8ef8\u540c\u6642\u99c6\u52d5\u6642\u306b\u3082\uff0c \u63a8\u529b\u5e72\u6e09\u304c\u306a\u3044\u3053\u3068\u3092\u793a\u3059\u3002 Fig. 1 Three-degree-of-freedom oscillatory actuator. (a) Conventional model 1 (b) Conventional model 2 (c) Proposed Fig. 2 Magnetic circuit. (a) Outer mover (b) Inner stator Fig. 3 Detailed drawing of proposed model. z x y Whole view of Inner statorExploded view Spring (SUS316) Screw (SUS304) Inner case (SUS304) Whole view Inner stator Outer mover Without supporting mechanism Inner yoke Coil-X,Y,Z Back yoke PM supporting mechanism supporting mechanism z x y z x y Magnetic flux path by PM PM Magnetic flux path by PM y z x z y x Whole view of Outer mover Without supporting mechanism Supporting mechanism z x y 3.1 \u89e3\u6790\u8af8\u5143 3 \u6b21\u5143\u6709\u9650\u8981\u7d20\u6cd5\u3092\u7528\u3044\u305f\u78c1\u5834\u89e3\u6790\u306b\u3088\u308a\u529b\u7279\u6027\u306e \u89e3\u6790\u3092\u884c\u3046\u3002\u307e\u305f\uff0c\u89e3\u6790\u6761\u4ef6\u3092 Table 3 \u306b\u793a\u3059\u3002\u30a4\u30f3\u30ca \u30fc\u30e8\u30fc\u30af\uff0c\u30d0\u30c3\u30af\u30e8\u30fc\u30af\u3068\u3082\u306b\u96fb\u78c1\u8edf\u9244\u3092\u4f7f\u7528\u3057\uff0c\u6c38 \u4e45\u78c1\u77f3\u306f\u78c1\u5316\u304c 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001726_el-01651589_document-Figure2.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001726_el-01651589_document-Figure2.8-1.png", + "caption": "Figure 2.8: From default frame to camera landscape frame (rotation of 90\u00b0around x-axis then another rotation of 90\u00b0around z-axis)", + "texts": [ + " In Augmented Reality (AR), for example, it is interesting to use algorithms which provide good estimations of only two of the three Euler angles in order to enhance rendering. We defined pitch and roll as the rotations around y-axis and z-axis. As Euler angles suffer from singularity and this singularity is a problem when the smartphone is held in AR mode we apply a rotation of 90\u00b0 around x-axis then another rotation of 90\u00b0 around z-axis. The smartphone is now considered in \u201cCamera landscape\u201d frame, as shown in Figure 2.8. Table 2.9 shows algorithms precision during AR motions in a highly perturbated magnetic environmnent. During motions with low external accelerations, which this is especially the case for AR motions, we can use a specific technique for limiting the impact of magnetic perturbations. We use a cross product between the magnetometer and the accelerometer as yielding our observation vector. This allows algorithms to be more robust to errors from magnetometer mesurements on pitch and roll angles [Martin and Salau\u0308n, 2010]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure6-6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure6-6-1.png", + "caption": "Figure 6-6. Repr\u00e9sentation des diff\u00e9rentes orientations pouvant \u00eatre prises par le t\u00e9l\u00e9phone mobile Unik", + "texts": [ + " Compteur d'eau sous les diff\u00e9rentes orientations consid\u00e9r\u00e9es ................................. 175 Figure 6-2. Distribution normalis\u00e9e du champ incident pour les composantes \u03b8 et \u03c6 ............. 177 Figure 6-3. Repr\u00e9sentation du dip\u00f4le dans le rep\u00e8re initial ........................................................ 178 Figure 6-4. Repr\u00e9sentation des syst\u00e8mes d'antennes \u00e9valu\u00e9s ..................................................... 179 Figure 6-5. Orientation du t\u00e9l\u00e9phone mobile Unik avant rotation.............................................. 182 Figure 6-6. Repr\u00e9sentation des diff\u00e9rentes orientations pouvant \u00eatre prises par le t\u00e9l\u00e9phone mobile Unik ................................................................................................................................ 183 Figure 6-7. Repr\u00e9sentation 3D des composantes selon \u03b8 et \u03c6 du champ incident urbain ........ 185 Figure 6-8. Identification des ports RF du syst\u00e8me \u00e0 deux patchs \u00e0 double polarisation........... 186 Figure 6-9. Repr\u00e9sentation des trois orientations dans l'espace d'un des syst\u00e8mes UWB \u00e9tudi\u00e9s ", + " Il utilise donc des antennes travaillant sur la bande ISM 2,45 GHz en plus d'antennes destin\u00e9es \u00e0 couvrir les bandes de t\u00e9l\u00e9phonie mobile. 182 L'application, le t\u00e9l\u00e9phone mobile Unik, est repr\u00e9sent\u00e9e dans son orientation initiale sur la figure FF. Il peut \u00eatre utilis\u00e9 sous diff\u00e9rentes orientations qui correspondent \u00e0 des services diff\u00e9rents. Nous avons distingu\u00e9 quatre orientations diff\u00e9rentes chacune d'elles \u00e9tant associ\u00e9e \u00e0 un service diff\u00e9rent. Le premier service consid\u00e9r\u00e9 est la communication vocale classique, le terminal est alors inclin\u00e9 de 60\u00b0 par rapport \u00e0 la verticale comme le montre la Figure 6-6.a. L'\u00e9volution des technologies a cependant permis l'apparition d'autres services, comme par exemple la visiophonie. Dans ce cas repr\u00e9sent\u00e9 Figure 6-6.b, le t\u00e9l\u00e9phone est vertical, face \u00e0 l'utilisateur pour que celui-ci puisse \u00eatre dans le champ de la cam\u00e9ra du t\u00e9l\u00e9phone. La troisi\u00e8me orientation consid\u00e9r\u00e9e se r\u00e9f\u00e8re \u00e0 tous les services li\u00e9s au transfert de donn\u00e9es comme par exemple l'envoi de SMS, de MMS ou de mails ou encore le t\u00e9l\u00e9chargement de musique. Pour ce type de service le t\u00e9l\u00e9phone est dans la main de l'utilisateur avec une orientation de 45\u00b0 par rapport \u00e0 la verticale comme l'illustre la Figure 6-6.c. La derni\u00e8re orientation consid\u00e9r\u00e9e est plus originale, le t\u00e9l\u00e9phone mobile est inclin\u00e9 de 45\u00b0 selon l'axe Oy. Cette orientation permet d'exploiter au mieux l'\u00e9cran du t\u00e9l\u00e9phone lorsque l'utilisateur regarde la t\u00e9l\u00e9vision ou des vid\u00e9os en streaming sur son terminal comme le montre la Figure 6-6.d. Lorsque l'utilisateur fait appel \u00e0 l'option Unik, il est soit pr\u00e8s d'une Livebox, donc dans un environnement indoor, soit pr\u00e8s d'un hotspot que l'on trouve le plus fr\u00e9quemment dans des zones urbaines. Nous allons donc consid\u00e9rer deux environnements diff\u00e9rents pour chacune des quatre orientations pr\u00e9sent\u00e9es, ce qui nous conduit \u00e0 traiter huit situations diff\u00e9rentes. 183 Concernant la pond\u00e9ration des diff\u00e9rentes situations, nous avons d\u00e9fini les valeurs des poids Wn en fonction du service sollicit\u00e9 donc de l'orientation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure22-1.png", + "caption": "FIGURE 22. Simulated modal current distributions of (a) Mode 1, (b) Mode 2, (c) Mode 3, (d) Mode 4, (e) Mode 5 on the proposed antenna in [27].", + "texts": [ + " Thesemethods are explained as follows. It is well known that the ground, and the substrate structures will not significantly affect the distribution of eigen currents on the radiating plane. Despite that, changes in these components are expected to affect the modal resonances. Modes become complex after the ground, feeding strip and substrate are incorporated. This concept is demonstrated using a planar dipole antenna in [27]. The current distributions for the five significant modes of the dipole are depicted in Fig. 22. For the first mode shown in Fig. 22(a), currents on the radiating body and the feeding strip are flowing in the same direction, whereas a current null appears on the feeding strip in the second mode, as shown in Fig. 22(b). The third mode contains a null at the bottom of the radiating body and another on the feeding strip (Fig. 22(c)). For the fourth mode illustrated in Fig. 22(d), there are nulls at the middle of the radiating body and around the junction between the feeding strip and the radiating body. Finally, in Fig. 22(e), 98842 VOLUME 9, 2021 two nulls are observed on the radiating body in the fifth mode, and its feeding strip also contain one current null. On the radiating body, all five significant modes have currents located along its length, as expected. Based on this modal surface current analysis, CMA guides designers in selecting the best feeding design and potential methods in its parameter optimization. The antenna operation from 600MHz to 1 GHz is significantly determined by mode 2. Modes 3 and 4 are dominant within the range of 1 to 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003816_er.asee.org_4279.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003816_er.asee.org_4279.pdf-Figure5-1.png", + "caption": "Figure 5. Engine Sensor Locations of SR-30 1", + "texts": [ + "18 Engine Oil: Turbine Oils meeting military specification Mil-L-236993C (Exxon 2380 Turbo oil and Aeroshell 500) Approved Fuels: Commercial Grades: Jet A, Jet A-1, Jet B, Kerosene, Diesel, Heating fuel oil #1 or #2 Military Grades: JP-4, JP-5, JP-8 The Turbine Technologies, LTD Gas Turbine engine 1 comes equipped with a turnkey data acquisition system shown in Figure 4. Thirteen data points (pressures, temperatures, thrust, rpm, and fuel flow) are collected via sensors located at each key engine station. Engine sensor locations are shown in Figure 5. 1. Compressor Inlet Pressure, P1 (Displayed on Data Acquisition Screen) 2. Compressor Inlet Temperature, T1 (Displayed on Data Acquisition Screen) 3. Compressor Exit Pressure, P2 (Displayed on Data Acquisition Screen) 4. Compressor Exit Temperature, T2 (Displayed on Data Acquisition Screen) 5. Turbine Inlet Pressure, P3 (Displayed on Panel and Data Acquisition Screen) 6. Turbine Inlet Temperature, T3 (Displayed on Panel as TIT and Data Acquisition Screen) 7. Turbine Exit Pressure, P4 (Displayed on Data Acquisition Screen) 8" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002894_9312710_09367232.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002894_9312710_09367232.pdf-Figure5-1.png", + "caption": "FIGURE 5. The proposed antenna: (a) front view, (b) bottom view.", + "texts": [ + " Figure 4 shows the effect of changes in the ground plane on the reflection coefficient. We can see an improvement in terms of adaptation after the addition of the rectangular slots, with a minimum value of around \u221233 dB and a considerable decrease in the level of the S11 by making the U-slot while expanding the bandwidth. The U-slot antenna with notches in the ground plane provides a signal less than \u221210 dB in a bandwidth that spans from 2.18 GHz to 18 GHz with a relative band of over 140%. This is our proposed antenna. Figure 5 illustrates the final proposed antenna. The optimal parameters obtained by simulation are summarized in Table 2. Figure 6 shows the simulation results of the evolution of the real and imaginary parts of the antenna impedance as a function of the frequency. We notice that the impedance has good adaptability: inmost of the required frequency bands the real part changes around 50 and in most of the frequency band the imaginary part is around 0 . Figure 7 shows the variation of the gain of the entire antenna as a function of the frequency in the desired band", + " STUDY OF THE CHARACTERISTICS OF A MIMO SYSTEM WITH TWO ANTENNAS In this section, an isolation technique based on the insertion of a metamaterial, consisting of a periodic structure composed of 5 SRRs, will be applied to an antenna system composed of two elements in order to ensure an increase in \u2019insulation at 15 dB. For this, a single band antenna system dedicated to UWB coverage will be developed. This system is of the VOLUME 9, 2021 38549 massive MIMO type with 2 elements. It is necessary to have two power ports. To do this, we first designed a reference system made up of two ULB antennas. Figure 15 illustrates the geometry of two identical MIMO-UWB antenna elements initially proposed in Figure 5, which are placed on a PCB of dimensions Wsub \u00d7 lsub = 48 x 35 mm2. The distance between the two elements (center to center) is noted d = 16.8 mm. A partially truncated shared ground plane is implemented and placed at the rear of the substrate, which guarantees good impedance matching over a wide range of frequencies. The parameters of antenna 1 are optimized in terms of reflection coefficient. Thanks to a parametric study, we obtain the following values: Wsub = 48 mm, Lsub = 35 mm, Lgnd = 12.5 mm, Lf = 13" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000721_5_KJ00005579267__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000721_5_KJ00005579267__pdf-Figure1-1.png", + "caption": "Fig\uff0e 1 Analytical medet of engile block and rotatin \uff0eg shattS", + "texts": [], + "surrounding_texts": [ + "The Japan Society of Mechanical Engineers\nNII-Electronic Library Service\nhe apan ooiety f eohanioal ngineers\n789\n\u65e5\u672c \u6a5f\u68b0 \u5b66 \u4f1a \u8ad6 \u6587 \u96c6 \uff08C \u7de8 \uff09 75\u5dfb 752\u53f7 \uff082009\u22124\uff09 \u8ad6\u6587 No \uff0e08\u22127022\n\u30af\u30e9 \u30f3 \u30af\u8ef8 \u30fb \u6b6f\u8eca\u8ef8\u7cfb \u3068\u30a8 \u30f3 \u30b8 \u30f3 \u30d6 \u30ed \u30c3 \u30af\u306e \u9023\u6210\u632f\u52d5\u5fdc\u7b54\n\u53ca \u3073\u9a12\u97f3\u653e\u5c04\u4e88\u6e2c\u6cd5 \uff0a\n\u592a \u7530 \u548c \u79c0 \uff0a 1 \uff0c\u6c60 \u7530 \u5e78 \u4e00 \u90ce \uff0a 2 \uff0c \u912d \u5149 \u6fa4 \uff0a 1\n\u6c96 \u672c \u8cb4 \u5bdb \uff0a 3 \uff0c\u672c \u7530 \u5dcc \uff0a 3\nVibration Response and Noise Radiation of Engine Block Coupled\nwith the Rotating Crankshaft and Gear Train\nKazuhide OHTA \uff0a4 \uff0c Kouichiro IKEI\uff09A \uff0c Guangzu ZHENG \uff0c\nTakahiro OKIMOTO and Iwao IIONDA\n\uff0a aDepartment of Mechan \uff3dcal Eng\u2019inecring\uff0c Kyushu Universiti\uff0c\uff0e\n744MDtooka \uff0e Ni \uff04hi\u2212ku\uff0c Fukuuka \u2212 s\uff5d1i\u3001 Fukuoka \uff0e\u8dbe 9\u22120395 Japan\nThis paper presents the theoretical procedure to predict \u4ea1he vibratory response and radiated\nnoise of the engine blo\u2282k coupled with the rotating crankshaft and gear train shafts which drives the fuel inje\u2282tion pump alld valve systeln \uff0e The exciting ferces acting ol\u30b3 the engine block and shaft systern are combust \u58econ pressure \uff0c inertia forces of the nloving Parts \uff0e piston slap \u3014orees \uff0c ruel injection pressure and valve drivjng\u3014orce and torque \uff0e The \u3014\uff5dretica1 procedures consist of the folluwing four steps \uff1b \uff08i\uff09Dynamic characte \uff3b\n\u30fbistics of the \u03b1 1glne biock alld shafts are detemined separateIyby FEM or experimental modal analysis \uff0c\u30142 \uff09Nerma \uff3d\u03c4nI\u3015de expansi \u3014\u3015n technique is err\u30e6ployed to derive the equation of motion \u3014\uff0cf the total sys \uff3bem in which rotating shafts w\u30fbith gear \u4ea1rain are coinbined to the engine blocl\uff5b by the oil filni and contact stiffness \uff0c\uff083 \uff09The time histories of tl\u30e6e vibratory response of the engine block and rotating shafts are calculated by the numerical integration technique \u3001\uff0c\u30144 \uff09 Engine noise radiated from thc engine blQck surface is evaluated using the Boundary Element I\uff1e\u5de5e \u3057hod \uff0c \u5382 1\u2019his rnethud is applied t\u308a estiIna \u3057c the ef\uff3bect of the backlash of thc gcar tl \u2019 aill on the engine b\uff3dock vibi \u2019 atioii and radiated II\u3014\u3015ise\uff0e\nKe \uff0ev Vrords \uff0c\u5de5nternal Combustion Ellgine\uff0c N \u308aise Control\uff0e Coupled Vibra \u5de8Qn \uff0c Moda \uff3bAnalysis \uff0c Gear\n1\uff0e\u306f\u3058\u3081\u306b\n\u767a\u96fb \u30bb \u30c3 \u30c8\u3084 \u30d5 \u30a9 \u30fc\u30af \u30ea\u30d5 \u30c8\uff0e\u5efa\u8a2d\u6a5f\u68b0\u306a \u3069\u306b \u7528 \u3044 \u3089 \u308c \u308b\u30c7 \u30a3 \u30fc\u30bc \u30eb \u30a8 \u30f3 \u30b8 \u30f3 \u306f\u9023\u7d9a\u7684\u306a\u9ad8\u8ca0\u8377\u904b\u8ee2\u3092\u884c \u3046 \u305f \u3081\uff0c\u30af \u30e9 \u30f3 \u30af\u8ef8 \u304b \u3089\u71c3\u6599\u5674\u5c04\u30dd \u30f3 \u30d7\u3084\u52d5\u5f01\u7cfb\u8ef8\u3092\u99c6 \u52d5\u3059 \u308b \u305f\u3081 \u306e \u6b6f\u8eca\u5217 \u304c \u7528 \u3044 \u3089\u308c \u308b\uff0c\u7121\u8ca0\u8377\u904b\u8ee2\u6642 \u306b \u306f \u6b6f 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mQdd\n\u4e00 2\u4e86 \u4e00\n\u5de5\u5de5 \u4e00leotronio ibra y" + ] + }, + { + "image_filename": "designv8_17_0003455_download_96502_83042-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003455_download_96502_83042-Figure1-1.png", + "caption": "Figure 1. Prototype. Source: The author.", + "texts": [ + " The first part is considered linear when the motor is working near nominal voltage and current, same estimation for the second part, but the mechanical component includes nonlinear aspects, such as saturation, friction, and asymmetries due to the rotation sense. Controlling the motor requires sensing the angular position of the shaft, because the controller constantly compensates any deviation from an ideal position, given by a reference. The most common choice for that sensor is an incremental encoder, due to the low cost and its easy set-up, however a magnetic sensor is used, because it provides absolute measurements instead of discrete values. In addition, the plant includes a protractor and a needle, as shown in Fig. 1, to facilitate the visualization of the position of the shaft. In addition to the motor and the sensors, the plant requires a power amplifier. This stage transforms the actuating signal coming from the controller (implemented inside a computer) into a proportional signal that moves the motor. The connection between the control algorithm and the power amplifier is a Data Acquisition Card (DAQ), which in addition receives the signal from the sensor, as shown in Fig. 2. The identification of the plant in this paper does not look an exactly accurate model, but a model that captures the key features of the dynamic, because that proved to be enough using Time Scaling Control" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000074_8948470_09035441.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000074_8948470_09035441.pdf-Figure14-1.png", + "caption": "FIGURE 14. Connections of different layers. (a) Interconnections between the RF layer and the control and signal process layer. (b) Interconnections between the RF layer and the package layer.", + "texts": [ + " Figures 12(a) and (b) show the front view and back view of the RF layer specimen, respectively, and the length, width and thickness of the specimen are 46 mm, 44 mm and 2.8 mm, respectively. Then, the fabricated control and signal process layer is shown in Fig. 13. First, the beam control circuit is fabricated by using the PCB manufacturing technology. Then, the pin connections are applied to realize the interconnection 52364 VOLUME 8, 2020 between the beam control circuit and the DC power. The interconnections are conducted to form an initial assembly of the active antenna array without the package layer. The connections of different layers are shown in Fig. 14. Figure 14(a) shows the interconnection between the RF layer and the control and signal process layer, and two groups of pins (36 pins in all) are applied to connect the RF chips and the beam control circuit. Figure 14(b) shows the interface between the RF layer and external devices. The control and signal process layer is removed from the drawing, to allow a deeper insight into the structure. The inlet and the outlet which connect the RF layer and external devices, go through the control and signal process layer. The wire crosses the DC power, and connects the beam control circuit and an external computer terminal. Finally, the package layer is fabricated, and the antenna and the package layer are integrated to form the final antenna prototype by using the composite technology" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure14-1.png", + "caption": "Figure 14: Topologie d\u2019une cellule \u00e9l\u00e9mentaire du r\u00e9seau transmetteur [13].", + "texts": [ + " Seule une polarisation lin\u00e9aire est consid\u00e9r\u00e9e. Parmi les r\u00e9seaux d\u2019antennes bi-bandes poss\u00e9dant une p\u00e9riodicit\u00e9 identique, ceux exploitant une unique couche rayonnante ont \u00e9t\u00e9 pr\u00e9sent\u00e9s pr\u00e9c\u00e9demment. Il reste \u00e0 d\u00e9crire ceux adoptant plusieurs couches rayonnantes et les structures 3D. Le fait d\u2019obtenir un fonctionnement dans deux bandes de fr\u00e9quences distinctes par le biais d\u2019un \u00e9l\u00e9ment bi-bandes sur plusieurs couches rayonnantes diff\u00e9rentes n\u2019est pas commun. En voici un exemple exploitant un r\u00e9seau transmetteur [13] (Figure 14) : Page 21 sur 182 Le design consiste en trois couches, la premi\u00e8re et la troisi\u00e8me \u00e9tant identique. Sur ces couches se trouvent des patchs capacitifs et des anneaux fendus inductifs. Sur la couche centrale, y figurent une fente circulaire capacitive et un patch tr\u00e8s fin inductif. C\u2019est en jouant sur ces diff\u00e9rents \u00e9l\u00e9ments que les performances du r\u00e9seau transmetteur sont modifi\u00e9es, comme le montre le sch\u00e9ma, sur la Figure 15, ci-apr\u00e8s : Le ratio de fr\u00e9quences r\u00e9alis\u00e9 par cette antenne est relativement faible, 1,5:1, entre les bandes X et Ku, et les largeurs de bandes de fr\u00e9quences sont assez diff\u00e9rentes, environ 8 % en bande X mais seulement 2 % en bande Ku" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure20-1.png", + "caption": "Figure 20. 3\" Diameter Drive Wheel Pneumatic Cylinder", + "texts": [ + " On the mockup of four pipes used for testing, this configuration produced consistent rotation on one of the pipes given a specific gripper force setting. However, rotation was not consistently achieved when attempting to rotate around other mockup pipes. Slippage of the drive wheel on the pipe caused the inconsistent rotational motion observed during initial testing. In order to provide additional normal force between the drive wheel and pipe, the 2\u201d diameter drive wheel pneumatic cylinder was replaced with a 3\u201d cylinder. When using the 3\u201d cylinder (Figure 20) was able to consistently rotate from pipe to pipe with minimal slippage. Page 14 of 15 3 RESULTS Extensive testing of the Pipe Traveler led to a number of design modifications. In order to improve control of the gripping force, encoders were added to the gripper motors. In order to improve control of the drive wheel motion, the drive wheel DC motors were replaced with stepper motors. The software was optimized to utilize these motor control improvements. A number of different gripper roller configurations were tested, leading to the use of rubber gripper rollers and knurled steel drive rollers" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001892_e_download_4116_2763-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001892_e_download_4116_2763-Figure9-1.png", + "caption": "Fig. 9. Influence of the parameters h and kb on the force characteristics (f = 1.4Hz, a = 4 cm, \u03b2 = 0.004, \u03b2 = 0.04, kp = 2)", + "texts": [ + " When the parameter Sv changes, the characteristic shape related to opening of the orifices changes for higher velocities x\u0307. Simultaneously, the maximum values of the damping force increase. The damper performance within the range of large relative displacements of the piston depends additionally on parameters characterising the bypass, i.e. on the parameter \u03b3 (\u03b32\u22121 = \u03b31\u22122 = \u03b3) (determining the orifice cross-section area), on distance h (it is assumed that h1 = h2 = h) determining placement of bypass openings in the working cylinder, and on the parameter kb (characterising elastic properties of the valve). Figure 9 shows the influences of the parameters h and kb on the damping force as a function of piston displacements. The sudden change of the damping force occurs in two ranges of the displacements: \u2212h\u2212r < x < \u2212h+r and h\u2212r < x < h+r. In these both ranges the area change is given by equation (2.24). Since for higher values of the parameter h the oil flow through the bypass can be blocked only in the case of large piston displacements, the shock absorber in a wide range of vibration amplitudes behaves in a similar fashion as the classic shock absorber without the bypass (curve for h = 5cm)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003704_86_s40648-016-0055-1-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003704_86_s40648-016-0055-1-Figure4-1.png", + "caption": "Fig. 4 Jamming diagram for ring assembly", + "texts": [ + " Mechanical parameters for Jamming diagram is shown in Fig.\u00a0 3. The parameters summarize in Table\u00a02. By approximating \u03b8 \u2248 0 and assuming that the radial thickness of the ring is zero, three equations are given as follows, (1)\u03b8 \u2264 \u03b8m = cos\u22121 ( Rs Rri ) By eliminating f1 and f2 from Eqs. (2), (3) and (4), Eq. (5) is given, In the case that the angle of a ring is negative, Eq. (7) is given, Additionally, a condition of friction is given as follows, According to Eqs. (5), (7) and (8), Jamming diagram for ring assembly is obtained as shown in Fig.\u00a04. If relationship of mechanical parameters are in a closed area (hatching area in Fig.\u00a04) of Jamming diagram, it is guaranteed that ring assembly is realized smoothly. (5) M RriFz = \u00b5(1\u2212 \u03bb) Fx Fz + \u03bb (6)\u03bb = l 2\u00b5Rri , 0 \u2264 l \u2264 2L (7) M RriFz = \u00b5(1\u2212 \u03bb) Fx Fz \u2212 \u03bb (8)\u2212 1 \u00b5 \u2264 Fx Fz \u2264 1 \u00b5 Based on the successful conditions of ring assembly, this section proposes a precise assembly method of a ring with hollowed finger. A characteristic of the proposed method is to assemble a ring part into a shaft part with a hollow of each finger of a robotic hand. The proposed method consists of three phases: approach, adjustment of axes, and mating and insertion", + " The second advantage is geometrical restriction of a ring part. A position and an angle of a ring part are restricted by the hollows of fingers. The successful condition of ring assembly \u03b8 \u2264 \u03b8m in the previous section is satisfied by the hollows of fingers. This means that a ring part can be assembled without jamming. The final advantage is giving optimal mating force to a ring part. A ring part closed by hollows receives mating (9) x = K \u00d7 Fwrist x y = K \u00d7 Fwrist y force from the top of the hollows. If the mating force satisfies Jamming diagram (Fig.\u00a0 4), the ring part can be assembled without jamming. In this section, we determine parameters of the hollow. One of the characteristics of the proposed method is to assemble a ring part with hollows of fingers. The hollows need to be designed to be able to assemble a ring part successfully. The hollow has three parameters as follows: width a, height b, incline angle \u03c6. Geometric condition of ring assembly is shown as Eq. (1). Therefore, the hollow is designed as Eq. (1) is satisfied. We consider a ring assembly with \u03b8 = \u03b8m (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002524_O201020065114094.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002524_O201020065114094.pdf-Figure8-1.png", + "caption": "Fig. 8 Internal flow of gap section", + "texts": [ + " Although detailed descriptions are not provided here, this vortex flows in and out of the impeller to the volute or shifts between the upper and lower sides with the impeller rotation. Hence, vortexes formed at the volute also become asymmetrical. This deviation of the flow could be the cause for the decreased pressure as shown in Fig.4. Considering all the above, it can be thought the gap in this pump induces development of the backward current not only inside the impeller but also in the gap. This prevents development of a deviated vortex inside the impeller, and as a consequence, the flow is rectified with the minimum loss of energy. The followings are described in Fig.8: (a) Radial velocity inside the upper gap at Q=5.0 L/min (the flow from inside to outside is defined positive), (b) pressure distribution, and (c) path lines. Each figure shows the result of computation at the central section in the direction of the height of the gap indicated as A-A\u2019 in Fig.8 (d). According to Fig.8 (a), the radial velocity is negative for the entire circumference of the gap; the fluid flows in from the volute to the inlet, and the flow-in velocity is high especially around \u03b8 =110\u00b0-190\u00b0 (area A) and 310\u00b0- 10\u00b0 (area B). This is because the high pressure at the volute around the tongue as in Fig.6 (b) induces an increase of pressure in the areas A and B in the gap as in Fig.8 (b), resulting in high radial pressure gradient in these areas which makes it easier for the fluid to flows in. The flow paths in (c) show that the fluid in the gap flows (backward) to the inlet without causing stagnation while circulating in the same direction as the impeller rotation. Hence, it seems that an adequate \u201cwash-out\u201d effect has been achieved in prevention of thrombosis formation inside the narrow gap, which is one of the most significant elements of the blood pump. Similar tendency is observed at the different blade positions and also in the lower gap; further details are not provided here" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000542_41230-021-0141-8.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000542_41230-021-0141-8.pdf-Figure11-1.png", + "caption": "Fig. 11: Simulated grain size distribution (a), and hot cracking potential (b) in ingot", + "texts": [ + " Since the two criteria both judge the hot cracking susceptibility by the ratio of the vulnerable time tV (when hot cracks may develop) to the time available for the stress relief process tR (when mass and liquid feeding occur), two simulated results are very similar with different critical times. The CD criterion and Katgerman criterion successfully predict the hot cracking in the ingot center line, but overestimate the hot cracking susceptibility in the ingot chilled layer. In fact, there are no visible hot cracks on the side wall and bottom of the ingot. The possible reason is that the cooling rate in the ingot chilled layer is too rapid and it is inadequate for the cracking prediction. These two criteria are based on non-mechanical characteristics, and have limitations. Figure 11(a) shows the simulated grain size distribution with large size in the core and the upper part, and small size in the side wall and the lower part of ingot. The result of HCP criterion is shown in Fig. 11(b), in which the positive value means tensile stress and the negative value means compressive stress. Compared with the CD and Katgerman criteria (Fig. 10), the HCP criterion also successfully predicts the hot cracking in the ingot center, and avoids overestimation of the hot cracking in the ingot chilled layer. As shown in Fig. 2, the ultrasonic inspection results reveal that the ultrasonic signal is shallow \u00b7 A Q \u00b7 \u00b7 BTR in the ingot upper part and deep in the ingot lower part. The simulation results of HCP criterion reflect the inverted cone shape of the defects zone, and more accurately predict the lower position of the defects" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000056_tation-pdf-url_54247-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000056_tation-pdf-url_54247-Figure12-1.png", + "caption": "Figure 12. Prototype of a five-wheeled wheelchair with an add-on mechanism. (a) Add-on mechanism. (b) Diagonal view of a wheelchair prototype.", + "texts": [ + " By using the measured height of the step h, and the distance to the step L s , the static wheelie motion and translation motion of the wheelchair can be performed simultaneously to minimize the time for approaching to a step. Moreover, coordinated controls of the linear actuator and the active-caster can be realized for maintaining certain contacts between the large wheels and a step edge for climbing the large wheels. The prototype wheelchair was designed and built whose 3-dimensional Computer Aided Design (3D CAD) models are shown in Figure 12. The add-on mechanism, which includes the active-caster and the reconfigurable link mechanism with a linear actuator, is attached on the back of a frame of a manual wheelchair. The stroke of the linear actuator is 200 mm and the maximum power is 144 W. To drive the active-caster, two motors are installed, whose capacities are 200 W each. The diameter of the drive wheel is 130 mm with 45 mm caster offset. Two sensors (LRF) are attached on the side of the wheelchair frame to measure the step whose locations are illustrated in Figure 13" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001613_el-04520421_document-Figure1.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001613_el-04520421_document-Figure1.1-1.png", + "caption": "Figure 1.1: PM motor construction [11].", + "texts": [], + "surrounding_texts": [ + "motor. A three-phase stator winding is wound to produce a trapezoidal or sinusoidal distribution of air-gap flux depending on whether the motor is a BLDC motor or a PMSM one. The rotor of these motors is made up of high-performance permanent magnets firmly attached to the core. There are a variety of motor characteristics that can be achieved by adjusting the arrangement, shapes, and positioning of these magnets [10]." + ] + }, + { + "image_filename": "designv8_17_0003169_1_1_article-p624.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003169_1_1_article-p624.pdf-Figure1-1.png", + "caption": "Fig. 1. Mechanism of the rotation for crane", + "texts": [ + " The stability is further degraded when the payload swings. This thesis presents a carrying capacity study of mobile cranes (Liang et al., 2012). As a first step, a static carrying capacity analysis of a boom crane is conducted in order to provide basic insights into the effects of the payload weight and crane throughout the workspace. A crane is regarded as stable as long as all wheel contact forces are positive. The influences of the boom attachment point and the boom weight are investigated (Kania et al., 2012). Mechanisms of the rotation (Fig.1) for crane are most often constructed with using rolling slewing bearings. They are these are sub-assemblies of machines that transferring the whole of the loading resulting from the work of machine (Kania, 2012). Their particularities features that cause big load capacity at the relatively clenched construction and comparatively small dimensions, not only in classical machines and devices, as diggers, of all kinds cranes and different building machines, military vehicles are finding application" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003081_le_download_1199_891-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003081_le_download_1199_891-Figure10-1.png", + "caption": "Fig. 10. The Results of The Deformation Model and The Graph of The Relationship Between Load and Deformation From Variations in The Thickness of The Model", + "texts": [ + " On top of that, the deformation result of the wrist-hand orthosis model analysis showed that the area of the palm end of the model experienced the most significant deformation. It is reasonable and can occur because the area is the border of the palm with the fingers, where the hand's position tends to be bent as the center of the load. The most considerable deformation value occurred in the 5 mm thickness model, 0.614 mm, while the smallest deformation value occurred in the 6 mm model, 0.172 mm. Figure 10 shows the deformation results with the indication of the maximum deformation area and a graph of the relationship between load and deformation from variations in the model's thickness. The wrist-hand orthosis model using Polylactic Acid (PLA) material was fabricated separately between the lower and upper parts using the 3D Printing Fused Deposition Modeling (FDM). The parameters used were nozzle size 0.4 mm, layer height 0.2 mm, shell thickness 0.8 mm, infill density 80%, material printing temperature 208 \u00b0C, and printing speed 50 mm/s" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure13-1.png", + "caption": "Figure 13 Top Panel Vent Hole with Mesh.", + "texts": [ + " Additionally, with so many meshes attached to the PPOD, it is difficult to keep track of all of them, making P-POD handling more difficult, and increasing the risk of damaging one of the meshes. A possible solution to mitigate some of these issues, is to put the vent hole on the thin area of the top panel, where there is ample surface area available and no impact to mounting interfaces. Having only one mesh, is much easier to keep track of, greatly reducing the risk of damage to the mesh. It also simplifies the installation, as only one mesh needs to be attached. This design is show below in Figure 13. Unfortunately, this design is not without drawbacks. With the vent Page 16 holes in the side panels, the holes lead to a vacant area of the P-POD, in the corner between the rails. Having such a large hole with direct path to the CubeSat payload, creates some risk of foreign object debris (FOD) penetrating the mesh and causing damage to the CubeSat. Additionally, the material thickness in the Top Panel is very thin, providing little thread engagement for the fasteners affixing the mesh to the Top Panel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003925_f_version_1684286543-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003925_f_version_1684286543-Figure2-1.png", + "caption": "Figure 2. Finite element model of chassis frame.", + "texts": [ + " Excessively large grid size easily causes low computational accuracy issues. After multiple attempts, the grid size was finally set to 15 mm as the most appropriate. Automatic grid division is suitable for automatically identifying the entities that can be swept. For the entities that cannot be swept, their corresponding grid is divided by the \u2018Patch confirming\u2019 algorithm. In order to simulate the constraints of the chassis frame in actual work, the constraints are set at the connection between chassis frame and track. The finite element model is shown in Figure 2. After the modal analysis preprocessing was completed, the first six natural frequencies of the chassis frame were solved, as provided in Figure 3. As shown in Figure 3, the first six natural frequencies of the chassis frame are between 23\u201376 Hz, which can be used to compare the vibration frequencies of the main vibration sources of the pepper harvester, in order to determine whether there is resonance and vibration coupling. The DH5902N robust data acquisition system produced by Donghua Testing Technology Co" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure101-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure101-1.png", + "caption": "Figure 101. Three views of the assembly (top) close up of pin and side plate (bottom)", + "texts": [], + "surrounding_texts": [ + "Inputs E 1 Axial Modulus, msi E 2 Transverse Modulus, msi E 3 Modulus, msi G 12 = G 13 Shear Modulus, msi G 23 Shear Modulus, msi \u03c5 12 = \u03c5 13 Poisson\u2019s Ratio \u03c5 23 Poisson\u2019s Ratio MTM 49-LT Unidirectional 19.9 0.99 0.99 0.302 0.398 0.244 0.257 A.5.5. Isotropic Section Creation One section was created for the steel. To make a new section right click Section category and click create. Name it Isotropic, for the category chooses Solid, and for the type choose 150 Homogeneous. Click continue, and then choose Steel as the material. Apply the steel section to the steel pin part and the steel side plate. In this step, we also want to duplicate the SidePlate part. Right click on the SidePlate and click copy, name it SidePlate2. Expand the SidePlate options by pressing the (+) icon next to the part name, click Section Assignments, click the part and then it should highlight in red. Click done once selected. For the section choose the Isotropic section which was created then hit Ok. 151 Apply this same method to the SteelPin part and the Sideplate2 part. A.5.6. Composite Laminate Section Creation The specimen which was created was a carbon fiber laminate composed of 16 layers with an orientation of [0 0 +45 -45 +45 -45 90 90]s. Abaqus has a Composite layup tool which is found in each individual part. Keep the name default, set the initial ply count to eight and set the element type to solid. 152 A new window appears. In this window, all of the laminate stacking directions along with the rotation axis are specified. 153 Before a layup orientation can be created; a datum coordinate system needs to be defined. Click Create Datum CSYS. Create a rectangular coordinate system and keep the default name. Next, it will ask you to specify a point, click the point in the center of the hole shown below in the figure. Keep the Rotation axis to Axis 3 and keep the Stacking Direction to Element direction 3. Check the box that says, \u201cMake calculated sections symmetric\u201d. Since we are only going to specify eight of the plies, which are part of the orientation. Next, we need to specify where on the part we have this orientation. In the region section, double click it, click on the specimen, and then click the done button. Do that for each layer and then for the material section, choose Uni as the material. The element relative thickness should 154 equal the reciprocal of the amount of elements through the thickness of the part. For example, my mesh consists of two element, which span the thickness of the specimen. My element relative thickness was set to 0.5 (2-1). 155 Last of all, set each ply orientation angle starting with the outermost layer. Keep the integration point to one. The result should look like this. 156 A.5.7. Assembly Creation Under the Assembly submenu, create an Instance. Make each of the parts are set as Dependent also make sure to check the Auto-offset from other instances. 157 The next part requires getting used to Abaqus\u2019 assembly options. This can be tricky, but it takes practice. After moving each part around, the final assembly should look something like this below. Make sure the specimen is centered between both of the side steel plates. The specimen should sit 1 in. into the pin, which is how it was loaded in the experiment. The distance between the two side plates is 0.25 in. Make sure the top of the pin is touching the top of both of the side steel plates. 158 A set needed to be created for a specific node. Abaqus gives you an option to select a specific node of interest and name it whatever you please. Therefore, in my model I wanted to select a node, which is in the middle of the specimen and located at the bottom of the hole. This location is of critical importance to the model because that is the location I want to monitor the vertical 159 deflection. This is the location where we will want to compare the experimental extensometer displacement and the nodal displacement in the numerical model. While in the Assembly module, I created a new set, picked the corresponding node, and named it Monitor. Switch to the Step module and then you will see the main horizontal bar at the top of the screen change accordingly. Now the main horizontal bar should have an Output menu. Click into this menu and click DOF Monitor. There should be an option to toggle on, Monitor a degree of freedom throughout the analysis. Click Edit, and then click Points in the prompt area and choose the node set Monitor from the region selection dialog box. Now we set the Degree of Freedom we want to monitor. In our model, we are interested in the displacement in the Y direction because that is actually, what the extensometer measured in the experiment. As we can see in, we want to monitor the Y-axis displacement so we set the Degree of Freedom to 2. Now we click Ok. 160 Surfaces needed to be created for each specific part. A very important feature is located in the surface option, here the user is able to select and define a surface on any particular part in your model. So what I did was define a surface called InnerSpecimen, this was defined as the inner surface of the specimen\u2019s hole. The second surface I defined was the outer surface of the pin and named it Pin. A.5.8. Step Creation Two steps need to be created one for the contact step and another for the load step. Abaqus runs the steps in order so first we are going to tell Abaqus that there is contact between some of the parts and after that, contact is established the load step can be applied. Create the contact step 161 and make sure all of these match. Create the load step and make sure all of these match. 162 A.5.9. Interaction Creation Next, we need to create an interaction between the pin and the specimen along with the two side plates. Right click the Interactions submenu and click Create. Choose Surface-to-surface contact. Keep the name to default and make sure to make it for the Initial Step. Click the outer surface of the pin as the Master Surface. After this step, go into the assembly and hide the SteelPin part by right clicking on it, and selecting Hide. 163 Once the pin is hidden, selecting the slave surfaces is a lot easier. Select Slave at the bottom menu and then select the inner hole surface of the two steel plates along with the specimen (hold Shift to select more than one at a time). Then click done and that should be all. Keep it at Finite Sliding and keep the Discretization method to Surface-to-Surface. 164 Then click the create Contact interaction property button. Choose Contact and name it NoFric. Then under Mechanical Submenu add Normal and a Tangential Behavior. Pick penalty for Tangential Behavior and choose a friction coefficient of 0.46. For the normal Behavior, Pressure Over-closure \u201cHard\u201d Contact, Constraint enforcement method Default and make sure to allow separation after contact is checked. 165 A.5.10. Defining the Load Next, we need to define a load in the model. Right click the load submenu and click create. Name the load, then apply the load in the load step. Choose a Pressure load for type. Select bottom faces of the two steel plates (shown red in the figure). Select Total Force for the Distribution type, and enter a magnitude of -600 and keep amplitude as ramp. 166 167 A.5.11. Defining the Boundary Conditions Three boundary conditions were applied to the model. One boundary condition was applied to the top face of the specimen and this will simulate the clamps in the Instron machine. The second boundary condition was applied to the side steel plates. For this condition, we want to prevent the plates from moving out from the z-plane. The last boundary condition was initially applied to the contact step and then it became modified from the load step. The last boundary condition dictated how the pin was to move in the model. Right click on the boundary conditions (BCs) submenu and click create. Name it Fixed and apply it to the Contact step. For the category choose Mechanical and for type, choose Symmetry/Antisymmetry/Encastre. Then click Continue. Select all of the outer sections of the steel side plates. Choose Encastre as the type. 168 Right click on the boundary conditions (BCs) submenu and click create. Name it SideFaces and apply it to the Load step. For category choose mechanical and for type choose Displacement/Rotation. Then click continue. Select all of the outer sections of the steel side plates. Set the U3 equal to zero since no deflection is expected to occur in this direction. 169 Right click on the boundary conditions (BCs) submenu and click create. Name it PinBC and apply it to the Contact step. For category, choose mechanical and for type choose Displacement/Rotation. Then click continue. Select all the surfaces of the pin. 170 Right click on the load and press edit. Disable the U2 boundary condition by unchecking the box. A.5.12. Defining the Mesh The partitions that were created for the side plates and the specimen simplified the mesh defining process. The Seed Edges command was used for each part and each part was highlighted. 171 In the options, the number method was chosen and the bias was set to none. The sizing controls options defined how many elements would be assigned to each element of the partition. For my model, I kept the number of elements equal to two. After this, I clicked Ok. Apply the same method to all the parts. Apply these settings under the Mesh Controls options. 172 In the element type settings, make sure all of these are applied to both the pin and side plate parts. All of these settings should be default. For the specimen, only difference was to uncheck the Reduced integration box. 173 A.5.13. Creating the Job Lastly, we need to create a specific job for your model. Once a job is created, you need to right click on the job and submit it. Once submitted, the job will run and once it converges, it will say Completed assuming everything runs smoothly. To see the results, right click on the job and click the results. This should open up another tab where the user is able to see the different displacements and stresses in the different directions." + ] + }, + { + "image_filename": "designv8_17_0001013_load.php_id_15102004-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001013_load.php_id_15102004-Figure11-1.png", + "caption": "Figure 11. With the proposed R-FBN, the measured radiation patterns of the three-element array.", + "texts": [ + " 8, printed dipole array is chosen as the radiating element due to its simplicity and versatility, which are fed by the R-BFN. The geometry and main parameters of the array are shown in Fig. 9. The spacing between two adjacent radiating elements is \u03bb/2 (80 mm), where \u03bb is the air wavelength at 2.5 GHz. In contrast, the measured radiation patterns of each printed dipole antenna without the proposed R-FBN are shown in Fig. 10. With the proposed R-FBN, the measured radiation patterns of the three-element array are presented in Fig. 11 when the 2-bit phase shifter is at State 1 or State 2, respectively. The array can be excited by different input ports, and two symmetrical patterns are obtained. By switching the two states of the 2-bit phase shifter, two different symmetrical patterns are achieved. When the 2-bit phase shifter is at State 1, the main beam points to the 14\u25e6 or \u221214\u25e6 as Port 1 or Port 2 is excited. When the 2-bit phase shifter is at State 2, the main beam points to the 26\u25e6 or \u221226\u25e6 as Port 1 or Port 2 is excited. In this paper, a simple 2\u00d7 3 reconfigurable beam-forming network (R-FBN) with 2-bit phase shifter for four-beam reconfiguration has been designed and realized" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.9-1.png", + "caption": "Figure 6.9: Rotor Free Body Diagram", + "texts": [ + "39) represents the friction loss at the endface of the rotor that is in contact with the stationary bearing surface, in which the method of evaluation is similar to that for the bearing flange friction in Equation (6.31). \ud835\udc7b\ud835\udc53,\ud835\udc5f \ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61 = \u222b \u222b (\ud835\udc93\ud835\udc4f,\ud835\udc5f\u00d7\ud835\udc87\ud835\udc52\ud835\udc5b\ud835\udc53) \u2219 \ud835\udc4f\ud835\udc5f \ud835\udc51\ud703\ud835\udc5f \ud835\udc51\ud835\udc4f\ud835\udc5f 2\ud835\udf0b 0 \ud835\udc5f\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61,\ud835\udc50 0 \u2212 2\ud835\udf0b 3 |\ud835\udc87\ud835\udc52\ud835\udc5b\ud835\udc53|(\ud835\udc5f\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61,\ud835\udc50 3 \u2212 \ud835\udc5f\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61,\ud835\udc5f 3 ) (6.39) \ud835\udc7b\ud835\udc53,\ud835\udc50 \ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61 = \u222b \u222b (\ud835\udc93\ud835\udc4f,\ud835\udc50\u00d7\ud835\udc87\ud835\udc52\ud835\udc5b\ud835\udc53) \u2219 \ud835\udc4f\ud835\udc5f \ud835\udc51\ud703\ud835\udc5f \ud835\udc51\ud835\udc4f\ud835\udc5f 2\ud835\udf0b 0 \ud835\udc5f\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61,\ud835\udc50 0 (6.40) Friction losses occur at the vane slot as the vane slides in and out of the slot, and these losses affect both the rotor and the cylinder. Figure 6.9 shows the free body diagram of the rotor, depicting the normal force to the vane slot and its resultant friction force. Based on the free body diagram, the equation of motion for the rotor can be written as Equation (6.41) and the normal reaction force at the vane slot is given in Equation (6.42). \ud835\udc3c\ud835\udc5f\ud703\u0308\ud835\udc5f = \ud835\udc41\ud835\udc63,\ud835\udc5f\ud835\udc5f\ud835\udc63\ud835\udc5f \u2212 \ud835\udc47\ud835\udc53,\ud835\udc5f (6.41) 109 \ud835\udc41\ud835\udc63,\ud835\udc5f = 1 \ud835\udc5f\ud835\udc63\ud835\udc5f (\ud835\udc3c\ud835\udc5f\ud703\u0308\ud835\udc5f + \ud835\udc47\ud835\udc53,\ud835\udc5f) (6.42) The friction in the vane slot can then be calculated from Equation (6.43) and the corresponding friction torque vane component is then expressed as Equation (6", + "48) \ud835\udc39\ud835\udc66,\ud835\udc60 \ud835\udc5f = \ud835\udc5d\ud835\udc60\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f sin \ud703\ud835\udc5f (6.49) Compression: Cylinder: \ud835\udc39\ud835\udc65,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc50 = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50(1 \u2212 cos \ud703\ud835\udc50) (6.50) \ud835\udc39\ud835\udc66,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc50 = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50 sin \ud703\ud835\udc50 (6.51) Rotor: \ud835\udc39\ud835\udc65,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc5f = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f(1 \u2212 cos \ud703\ud835\udc5f) (6.52) \ud835\udc39\ud835\udc66,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc5f = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f sin \ud703\ud835\udc5f (6.53) For clarity of presentation, the resolved gas pressure forces are summed as shown in Equations (6.54)\u2013(6.57). 111 Cylinder: \ud835\udc39\ud835\udc65,\ud835\udc54 \ud835\udc50 = (\ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a \u2212 \ud835\udc5d\ud835\udc60)\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50(1 \u2212 cos \ud703\ud835\udc50) (6.54) \ud835\udc39\ud835\udc66,\ud835\udc54 \ud835\udc50 = (\ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a \u2212 \ud835\udc5d\ud835\udc60)\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50 sin \ud703\ud835\udc50 (6.55) Rotor: \ud835\udc39\ud835\udc65,\ud835\udc54 \ud835\udc5f = (\ud835\udc5d\ud835\udc60 \u2212 \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a)\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f(1 \u2212 cos \ud703\ud835\udc5f) (6.56) \ud835\udc39\ud835\udc66,\ud835\udc54 \ud835\udc5f = (\ud835\udc5d\ud835\udc60 \u2212 \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a)\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f sin \ud703\ud835\udc5f (6.57) Based on Figure 6.9, the resolved forces at the vane slot due to the vane normal force and sliding friction can be expressed in Equations (6.58) and (6.59). \ud835\udc39\ud835\udc65,\ud835\udc63 \ud835\udc5f = \u2212(\ud835\udc41\ud835\udc63,\ud835\udc5f cos \ud703\ud835\udc5f + \ud835\udc39\ud835\udc53,\ud835\udc63 \ud835\udc5f sin \ud703\ud835\udc5f) (6.58) \ud835\udc39\ud835\udc66,\ud835\udc63 \ud835\udc5f = \ud835\udc41\ud835\udc63,\ud835\udc5f sin \ud703\ud835\udc5f \u2212 \ud835\udc39\ud835\udc53,\ud835\udc63 \ud835\udc5f cos \ud703\ud835\udc5f (6.59) On the other hand, the resolved forces at the vane tip acting on the cylinder are just equal and opposite to that of the vane slot as shown in Equations (6.60) and (6.61). \ud835\udc39\ud835\udc65,\ud835\udc63 \ud835\udc50 = \ud835\udc41\ud835\udc63,\ud835\udc5f cos \ud703\ud835\udc5f + \ud835\udc39\ud835\udc53,\ud835\udc63 \ud835\udc5f sin \ud703\ud835\udc5f (6.60) \ud835\udc39\ud835\udc66,\ud835\udc63 \ud835\udc50 = \u2212\ud835\udc41\ud835\udc63,\ud835\udc5f sin \ud703\ud835\udc5f + \ud835\udc39\ud835\udc53,\ud835\udc63 \ud835\udc5f cos \ud703\ud835\udc5f (6.61) The resolved forces can then be summed up and the resultant forces acting on the cylinder and rotor are expressed as shown in Equations (6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004734_za_pdf_rd_v39_02.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004734_za_pdf_rd_v39_02.pdf-Figure11-1.png", + "caption": "Figure 11 Rotor Bench Isometric View", + "texts": [], + "surrounding_texts": [ + "[1] L. Wood. Commercial Drones Market: Global Industry Trends, Share, Size, Growth, Opportunity and Forecast 2022-2027. URL https://www.researchandmarkets.com/reports/5642337/ commercial-drones-market-global-industry-trends. [2] S. Ueland. Drone Delivery Companies. Practical Commerce URL https://www.practicalecommerce.com/8-commercialdrone-delivery-companies [3] DRONEII. Drone Energy Sources \u2013 Pushing the Boundaries of Electric Flight. DRONEII.com. https://www.droneii.com/drone-energy-sources. [4] L. R. Jenkinson and J. Marchman. Aircraft Design Projects: For Engineering Students. ButterworthHeinemann, 2003. [5] S. G. Kee. Guide for Conceptual Helicopter Design. Master\u2019s thesis, Naval Postgraduate School, Monterey, California, 1983. [6] J. M. G. F. Stevens, J. F. Boer, W. F. Lammen, W. J. Vankan, and C. Sevin. Helicopter Pre-design Strategy: Design-to-mass or Design-to-cost? National Aerospace Laboratory NLR, NLR-TP-2009-306, The Netherlands, 2009. [7] W. Johnson. Helicopter Theory. Dover Publications, 1994. [8] A. R. S. Bramwell, D. Balmford, and G. Done. Bramwell's Helicopter Dynamics. Elsevier, 2nd edition, 2001. [9] S. Newman. The Helicopter - Efficiency or Efficacy? Aircraft Engineering and Aerospace Technology, 78(1):15-19. [11] T. Bingelis. The Fixed Pitch Propeller Dilemma. EAA Sport Aviation. URL https://www.eaa.org/eaa/aircraftbuilding/builderresources/while-yourebuilding/building-articles/propellers-and-spinners/thefixed-pitch-propeller-dilemma [12] Skyfront. Skyfront Tailwind. URL https://skyfront.com/products/tailwind-drone/ [13] Griff Aviation. Griff 135. URL https://www.griffaviation.com/drones/griff-135/ [14] Dragon Fly. Draganfly Heavy Lift Drone. URL https://draganfly.com/wpcontent/uploads/2022/06/Draganfly-Heavy-Lift.pdf [15] New Atlas. SOAPdrones variable pitch quadcopter uses petrol power for heavy-lifting endurance. URL https://newatlas.com/soapdrones-variable-pitchmultirotor-endurance/48202/ [16] M. J. Cutler. Design and Control of an Autonomous Variable-pitch Quadrotor Helicopter. PhD thesis, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, 2012. [17] T. Pang, K. Peng, F. Lin, and B. M. Chen. Towards Long-endurance Flight: Design and Implementation of a Variable-pitch Gasoline-engine Quadrotor. In 12th IEEE International Conference on Control and Automation (ICCA), pages 767-772, 2017. [18] A. Abhishek, A. Duhoon, M. Kothari, S. L. Kadukar Rane and G. Suryavanshi. Design, Development, and Closed-loop Flight-Testing of a Single Power Plant Variable Pitch Quadrotor Unmanned Air Vehicle. In: Proceedings of the 73rd American Helicopter Society Annual Forum, pages 205-218, 2017. [19] X. Wu. Design and Development of Variable Pitch Quadcopter for Long Endurance Flight. PhD thesis, Mechanical and Aerospace Engineering, Oklahoma State University, Stillwater, OK, 2018. [20] A. Abhishek, A. Duhoon, M. Kothari, S. Kadukar, L. Rane and G. Suryavanshi. Design, Development, and Closed-loop Flight-testing of a Single Power Plant Variable Pitch Quadrotor Unmanned Air Vehicle. In Proceedings of the 73rd American Helicopter Society Annual Forum, pages 205-218, 2017. [21] A. Seeni and P. Rajendran. Analysis of Pressure Coefficient Around Three Airfoils Operating at Different Reynolds Number Using CFD and XFOIL. In Proceedings of International Conference of Aerospace and Mechanical Engineering, Universiti Sains Malaysia, Malaysia, pages 127-137, 20\u201321 November 2019. [22] J. Seddon and S. Newman. Basic Helicopter Aerodynamics: An Account of First Principles in the Fluid Mechanics and Flight Dynamics of the Single Rotor Helicopter. Blackwell Science, 2002. [23] F. J. Bailey, F. B. Gustafson. Charts for Estimation of the Characteristics of a Helicopter Rotor in Forward Flight. I -Profile Drag-Lift Ratio for Untwisted Rectangular Blades. National Advisory Committee for Aeronautics, 1944. [24] J. Morgado, R. Vizinho, M. A. R. Silvestre, and J. C. P\u00e1scoa. XFOIL vs CFD Performance Predictions for High Lift low Reynolds Number Airfoils. Aerospace Science and Technology, 52:207-214, 2016. R & D Journal of the South African Institution of Mechanical Engineering 2023, 39, 12-22 http://dx.doi.org/10.17159/2309-8988/2023/v39a2 http://www.saimeche.org.za (open access) \u00a9 SAIMechE All rights reserved. 19 [25] I. Berezin, P. Sarkar, and J. Malecki. Fluid\u2013Structure Interaction Simulation. In Recent Progress in Flow Control for Practical Flows: Results of the STADYWICO and IMESCON Projects, pages 263-281, 2017. [26] M. Drela. XFOIL. MIT. URL https://web.mit.edu/drela/Public/web/xfoil/ [27] R. C. Hibbeler. Engineering Mechanics: Statics and Dynamics. Pearson, 2015. [28] MATLAB. Polynomial Curve Fitting. URL https://www.mathworks.com/help/matlab/ref/polyfit.ht ml [29] S. Bell. Analysis of a Rotor Blade System using Blade Element Momentum Theory. URL https://ww2.mathworks.cn/matlabcentral/fileexchange/ 21994-analysis-of-a-rotor-blade-system-using-bladeelement-momentum-theory 7 Appendix A R & D Journal of the South African Institution of Mechanical Engineering 2023, 39, 12-22 http://dx.doi.org/10.17159/2309-8988/2023/v39a2 http://www.saimeche.org.za (open access) \u00a9 SAIMechE All rights reserved. 20 8 Appendix B R & D Journal of the South African Institution of Mechanical Engineering 2023, 39, 12-22 http://dx.doi.org/10.17159/2309-8988/2023/v39a2 http://www.saimeche.org.za (open access) \u00a9 SAIMechE All rights reserved. 21 9 Appendix C R & D Journal of the South African Institution of Mechanical Engineering 2023, 39, 12-22 http://dx.doi.org/10.17159/2309-8988/2023/v39a2 http://www.saimeche.org.za (open access) \u00a9 SAIMechE All rights reserved. 22 10 Appendix D" + ] + }, + { + "image_filename": "designv8_17_0004747_article_25861568.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004747_article_25861568.pdf-Figure3-1.png", + "caption": "Fig. 3. The far field model of horn antenna", + "texts": [ + " The antenna system formed by two more antennas is called multiple element antenna, array antenna is the most common used multiple element antenna. A simple antenna is called antenna unit which is generally weak directional antenna such as horn antenna and slot antenna. Horn antennas are used to form the 2dimension surface array, we approximately consider that electric current on horn antennas is the line electric current sine distributed as the axis of horn antenna bore when calculating the radiation wave. In figure 3, axis of horn antenna bore is placed on z axis, center point of horn antenna bore is placed on original point, the watch point is in the far-field area of horn antenna, r is path vector from original point to point P, \u03b8 is the included angle between path vector r and z axis. \u03b8 can be approximately considered 90 degree under condition of far-field, so the far-field model generated by horn antenna on point P can be expressed as [3] : 0( ) - 60 cos 2 jkrI e E P j kl r \uff083\uff09 0( ) - 60 cos jkre H P j I kl r \uff084\uff09 B. Superposed field mathematical model of antenna array The electromagnetic field of a multi antenna can be applied to the superposition principle, because in general, the electromagnetic field of the antenna is linear with the source. If iE is generated by the antenna element, the total field of multiple antenna system made up by N antenna element is: N i iEE 1 \uff085\uff09 Using N*N two element planar array, as shown in Figure 3, the horn antenna is located in the xoy plane, and the horn is placed along the X direction. The distance between the array elements along the X direction is dx, and the distance between the array elements is dy along the Y direction. The distance of the target surface (the observation plane) to the center of the array is d. As the target aperture for the radius R of the circular, using polar coordinates representation, \u03b8 is the angle between the line points P to O and the x-axis, \u03c1 represents the distance of the observation point P to O1 point" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002041_cle_download_355_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002041_cle_download_355_pdf-Figure2-1.png", + "caption": "Figure 2: Geometry of scattering by periodic patched on a grounded dielectric slab.", + "texts": [ + " This approximation can be accepted since the variation between adjacent cells is usually very small compared to wavelength in a close area. Another approach based on macro cell configuration can also be used to present the effect of a small group of scattering elements on the reflectarray structure [6]. However, this approach may not be directly suitable in the present case to obtain the equivalent surface impedance of each element. Thus, the present analysis would be limited on the infinite array approach. Periodic conducting patches, as shown in Fig. 2, can be represented as an equivalent surface impedance by using averaged boundary conditions (ABC). For the case of periodic patches on a grounded dielectric slab, the problem can be modeled as a short-circuited transmission line section loaded by the surface impedance of the patches as shown in Fig. 3. The corresponding characteristic impedances of these transmission line sections depend on the polarization of the incident wave and the angle of incidence as follows [13]: \ud835\udc4d\ud835\udc5b \ud835\udc47\ud835\udc38 = \ud835\udf02\ud835\udc5b/cos\ud835\udf03\ud835\udc5b (2) \ud835\udc4d\ud835\udc5b \ud835\udc47\ud835\udc40 = \ud835\udf02\ud835\udc5bcos\ud835\udf03\ud835\udc5b (3) where \ud835\udf02\ud835\udc5b is the characteristic impedance of the medium n", + " Here \ud835\udf030 is the angle of incident wave and \ud835\udf031 is the angle of transmitted wave inside the dielectric slab. The equivalent surface impedance of the periodic patches is a function of the periodic cell, the dimensions of the patch, the angle of incidence and the polarization of the incident wave as follows [13]: \ud835\udc4d\ud835\udc54 \ud835\udc47\ud835\udc38 = \u2212\ud835\udc57 \ud835\udf020 {2\ud835\udefc(1 \u2212 (sin2\ud835\udf030)/2)}\u2044 (4) \ud835\udc4d\ud835\udc54 \ud835\udc47\ud835\udc40 = \u2212\ud835\udc57 \ud835\udf020 {2\ud835\udefc}\u2044 (5) where \ud835\udefc is the grid parameter which is given by: \ud835\udefc = \ud835\udc58\ud835\udc52\ud835\udc53\ud835\udc53\ud835\udc37/\ud835\udf0b \u2219 ln(1/sin(\ud835\udf0b\ud835\udc64/2\ud835\udc37)) (6) D is the unit cell size and w is the spacing between the patches as shown in Fig. 2. \ud835\udc58\ud835\udc52\ud835\udc53\ud835\udc53 = \ud835\udc580\u221a\ud835\udf00\ud835\udc52\ud835\udc53\ud835\udc53 , \ud835\udf00\ud835\udc52\ud835\udc53\ud835\udc53 = (\ud835\udf00\ud835\udc5f + 1)/2 is the relative effective permittivity and k0 is the wave number in free space. Equations (4) and (5) are valid only if \ud835\udc58\ud835\udc52\ud835\udc53\ud835\udc53\ud835\udc37 < 2\ud835\udf0b [13]. It should be noted from (5) that equivalent surface impedance of periodic patches is independent on the angle of incidence for the case of TM polarization. Based on Eq. (4) and (5) and the equivalent transmission line circuit one can obtain the equivalent surface impedance of a grounded dielectric slab loaded by periodic patches for both TE and TM polarization as follows: \ud835\udc4d\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 \ud835\udc47\ud835\udc38 = \ud835\udc4d\ud835\udc54 \ud835\udc47\ud835\udc38// \ud835\udc57\ud835\udc4d1 \ud835\udc47\ud835\udc38tan\ud835\udf051\ud835\udc61 (7) \ud835\udc4d\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 \ud835\udc47\ud835\udc40 = \ud835\udc4d\ud835\udc54 \ud835\udc47\ud835\udc40// \ud835\udc57\ud835\udc4d1 \ud835\udc47\ud835\udc40tan\ud835\udf051\ud835\udc61 (8) where t represents the substrate thickness and \ud835\udf051 = \ud835\udc581cos\ud835\udf031 is the normal component of the propagation constant inside the dielectric slab" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002750_e_download_2487_2499-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002750_e_download_2487_2499-Figure10-1.png", + "caption": "Fig. 10. Crane \u2013 a laboratory model and its diagram", + "texts": [ + " For example, the ramp control function with limited both the slope and maximum value could be prepared to avoid actuator saturation (Benes\u030c, 2012). Then, using the finite time Laplace transform we can change it to the form of the re-entry shaper. This possibility to synthetize re-entry shapers of prescribed time lengths or optimized to chosen goals is the main contribution of this paper. It eliminates the drawbacks of both previous approaches (Bhat and Miu, 1990; Singhose, 1997). An antisway crane is one of the typical benchmarks for tests of non-vibration control strategies. The laboratory model shown in Fig. 10 is controlled by simple buttons with 2 states (on/off). But the rectangular input that goes from the buttons excites vibrations of the load. The goal is to design an on-line shaper which modifies the signal from the buttons to a non-vibrational one. According to the approach described in previous Sections primarily the optimized control curve is calculated and then it is transformed using the finite time Laplace transform to an on-line shaper. The shape of the control curve in parametrical form (5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003895_tation-pdf-url_63652-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003895_tation-pdf-url_63652-Figure2-1.png", + "caption": "Figure 2. Laminated composite cylindrical shell under external pressure (u displacement in the axial direction x, v in the tangential direction s, w in the radial direction z).", + "texts": [ + " The proposed model deals with dimensionless quantities in order to be valid for thin shells having different thickness-to-radius ratios. Results have been obtained for cases of filament wound cylinders fabricated from different types of composite materials. The basic analysis and analytical formulation presented in this chapter are based on the work given by Maalawi [14], which provides good sensitivity to lamination parameters and allows the search for the needed optimal stacking sequences in a reasonable computational time. Referring to the structural model depicted in Figure 2, the significant strain components are Optimum Composite Structures4 the hoop strain (\u03b50ss) and the circumferential curvature (Kss) of the mid-surface. The reduced form of the stress-strain relationships in matrix form is Nss Mss \u00bc A22 B22 B22 D22 \u03b5oss \u03bass (5) where Nss and Mss are the resultant distributed force and moment and (Aij, Bij, Dij) are the extensional, coupling, and bending stiffness coefficients, respectively [1]. The governing differential equations of anisotropic long cylinders subjected to external pressure are cast in the following: M0 ss \u00fe R N0 ss \u03b2Nss \u00bc \u03b2 pR2 (6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure32-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure32-1.png", + "caption": "Figure 32: Deformed model of the 8 joint mechanism.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0001023_article-file_2203208-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001023_article-file_2203208-Figure7-1.png", + "caption": "Fig. 7: Nema 14 Motor", + "texts": [ + " Two stepper motors were used in the system: the Nema 14 and Nema 17 stepper motors. They provide x- and y-axis movement. Nema 17 moves the carrier arm on the x axis, while the Nema 14 motor moves the pouring mouth on the carrier arm on the y axis. Nema14 is a kind of stepper motor and in the system, one Nema 14 motor was used. Nema 14 is powered by 2.7 V and 1000 mA. With its holding torque of 1.4 kg-cm, it provides the movement of the Y axis as integrated with the liquid pouring system in the hardware design. Figure 7 presents this motor. To drive the Nema14 and Nema17 stepper motors used in the machine, two Toshiba Tb6560 Stepper motor drivers were used. This type of stepper motor driver, which can work with 24V and 3A, is suitable for 2, 4, and 6 phase stepper motors. A general view of the stepper motor driver is presented in Figure 8 and a connection diagram is shown in Figure 9. In order for the machine to transfer the food liquid onto the grill, an air pump powered by 220V and through which we can pour the food liquid was used" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure7.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure7.1-1.png", + "caption": "Figure 7.1: Subdivision of RV Components", + "texts": [ + "82 W m-1 K-1, spatial temperature variation in PEEK components might be significant even during steady-state operation. The sliding thermal contact resistance of PEEK is investigated in Section 7.2.2 and the heat transfer for the PEEK rotor component is discussed in Section 7.3. 130 There are six components in the compressor which are subdivided into a total of 14 elements with simple geometric shapes. In addition, these elements are concentrically aligned with each other. As the bearing sleeves are thin, each of them is considered as a single element. Figure 7.1 shows the sub-division of the compressor components that will be used for the model. The rotor elements r2, r3 and r4 are concentric as elaborated in Figure 7.1(c). The following assumptions are made for the thermal model: Steady-state condition Isothermal elements 131 Rotor component is assumed to be concentric with the entire compressor prototype since the eccentricity is small (7.5 mm) compared to the housing diameter (160.0 mm) Similarly, the rotor shaft hole in element h4 is also assumed to be concentric One-dimensional heat transfer between adjacent elements in either the radial or axial directions as they are concentrically aligned One-dimensional heat transfer between the surroundings and the compressor as the overall prototype is axisymmetric The temperatures of the fluid in the housing shell and working chamber are assumed to remain constant during heat transfer Thermal contact resistance between steel components are negligible Volume changes in element due to thermal expansion/contraction are negligible Radiation heat transfer between compressor components is negligible Existing convection correlations found in the literature will be used for heat transfer at the solid-fluid interfaces [16, 33, 123\u2013126]", + " 139 To this end, here are the additional assumptions for the PEEK components: The absorption of friction heat by the PEEK elements are negligible; all friction heat is absorbed by steel instead Friction heat at the bearings is assumed to be split evenly between the steel shaft and bearing surfaces due to free rotation of the PEEK bearing liner. The steady-state temperatures of the PEEK bearing liners would be the average of the steel shaft and bearing temperatures. The breakdown of the components presented in Figure 7.1 results in most of the element having standard geometric shapes mostly in the form of cylinders. For element H1 with a slightly more complicated geometry, it is simplified to that of an annular cylinder for the study. The relevant heat transfer correlations for horizontal surfaces, vertical surfaces and cylindrical surfaces of the elements are presented: i. Free convection heat transfer correlations for housing shell and base cover elements \u2013 the Nusselt number correlation for free convection [128] on the upper surface of the housing shell and lower surface of the base cover is given by Equations (7", + "47) 145 From the rotor shaft, the fluid in the suction line continues inside the rotor. Based on the Reynold\u2019s number, it is an internal laminar flow with uniform wall temperature. The heat transfer coefficient is thus given in Equation (7.48). Nu = 3.66 , Re\ud835\udc60\ud835\udc62\ud835\udc50 < 104 (7.48) With 12 elements, there will be 12 simultaneous equations that must be solved to obtain the steady state operating temperatures of these elements. The equations can be arranged into a matrix and solved as a linear algebra equation. As an example, for the cylinder element c1 shown in Figure 7.1, it is affected by free convection and heat transfer from element c2. Hence, the heat transfer to and from the element can be written as shown in Equation (7.49) which is rearranged into Equation (7.50). \ud835\udc3b\ud835\udc501,\ud835\udc502(\ud835\udc47\ud835\udc501 \u2212 \ud835\udc47\ud835\udc502) + \ud835\udc3b\ud835\udc501,\u221e(\ud835\udc47\ud835\udc501 \u2212 \ud835\udc47\u221e) = 0 (7.49) (\ud835\udc3b\ud835\udc501,\ud835\udc502 + \ud835\udc3b\ud835\udc501\u221e)\ud835\udc47\ud835\udc501 + \ud835\udc3b\ud835\udc501,\ud835\udc502\ud835\udc47\ud835\udc502 = \ud835\udc3b\ud835\udc501,\u221e\ud835\udc47\u221e (7.50) where \ud835\udc3b\ud835\udc501,\ud835\udc502 = \ud835\udc3b\ud835\udc502,\ud835\udc501 = \ud835\udc58\ud835\udc60\ud835\udc61\ud835\udc52\ud835\udc52\ud835\udc59\ud835\udc34\ud835\udc501,\ud835\udc502 \ud835\udc59\ud835\udc501,\ud835\udc502 = 2\ud835\udc58\ud835\udf0b\ud835\udc5f\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61 2 \ud835\udc59\ud835\udc501 + \ud835\udc59\ud835\udc502 (7.51) \ud835\udc3b\ud835\udc501,\u221e = \ud835\udc58\ud835\udc4e\ud835\udc56\ud835\udc5f\ud835\udc34\ud835\udc501,\u221e \ud835\udc59\ud835\udc501,\u221e (0.119Re\ud835\udc5f 2 3\u2044 ) + 0.25\ud835\udc34\ud835\udc501,\u221e\ud835\udf0e(\ud835\udc47\ud835\udc501 + \ud835\udc47\u221e)(\ud835\udc47\ud835\udc501 2 + \ud835\udc47\u221e 2) = 2\ud835\udc58\ud835\udc4e\ud835\udc56\ud835\udc5f\ud835\udf0b\ud835\udc5f\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61\ud835\udc59\ud835\udc501 \ud835\udc59\ud835\udc501 [0.119 ( 2\ud835\udf0c\ud835\udf14\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61\ud835\udc5f\ud835\udc60\u210e\ud835\udc4e\ud835\udc53\ud835\udc61 2 \ud707 ) 2 3\u2044 ] + 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003369_9312710_09348901.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003369_9312710_09348901.pdf-Figure5-1.png", + "caption": "FIGURE 5. Thermal-resistance calculation method.", + "texts": [ + " HTRB LEAKAGE-CURRENT TEMPERATURE MEASUREMENT VERIFICATION AND CONTRAST TEST To verify the accuracy of leakage current measurement method proposed in this work, the result of typical thermal resistance computational method in HTRB test is compared, meanwhile, the result of small current temperature measurement is utilized as the benchmark to further validate the accuracy of the presented leakage current measurement method. A. COMPARISON OF EXPERIMENTAL METHODS-THERMAL RESISTANCE CALCULATION The thermal-resistance calculation method is usually adopted to monitor the junction temperature of a device in real time in an HTRB experiment [22]. The method is shown in Fig.5. In thermal-resistance calculation method, thermal resistance of the device under test requires to be tested in the first place, then the temperature of the constant-temperature platform is set according to device dissipation power P together with the thermal resistance value under high-temperature condition. In this test, junction temperature is the sum of temperature in constant-temperature platform and the rising temperature caused by dissipation power. The formula for calculating the device junction temperature is Tj = Tth,couple + Rjc \u00b7 Poff (7) where Tj is the operating junction temperature of the device, Tth, couple is the thermocouple temperature and Rjc is the junction thermal resistance of the device" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002044_8948470_09078103.pdf-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002044_8948470_09078103.pdf-Figure19-1.png", + "caption": "FIGURE 19. Eddy current density of radial conductor rotor with different thicknesses. (a) 5mm (b) 6mm (c) 7mm (d) 8mm.", + "texts": [ + " When the thickness is large enough, the effective magnetic field is reduced and the magnetic flux leakage is increased, the torque transmission capability decreases obviously. Theoretically, the eddy current density will increase as the thickness of conductor rotor increases when the other parameters are fixed. If the thickness of the conductor rotor reaches the optimal value and continues to increase, the eddy current density will not increase, or even decrease. The simulation of eddy current density is performed on the axial-radial combined permanent magnet eddy current coupler to verify the above conclusions. As shown in Fig. 18 and Fig. 19, with the thickness of the axial conductor rotor increases from 7 mm to 9 mm under 5% slip, the eddy current density also increases. However, when the conductor rotor thickness reaches 10 mm, the eddy current density decreases, and the radial conductor rotor eddy current density is similar to the axial condition. The eddy current effect is generated in the conductor rotor. The resistance and eddy current increase together with the thickness of the conductor rotor, which increases the torque and temperature" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000354_f_version_1555418839-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000354_f_version_1555418839-Figure2-1.png", + "caption": "Figure 2. T700 cutaway drawing, illustrating the sub-system assembly.", + "texts": [ + " We do this via a simple representation of a particle-laden stream leaving the combustor and approaching the high-pressure turbine NGVs. We present the data with non-dimensional parameters to enable their use in any environment-airframe-engine system. We then use these parameters to estimate the mass deposited on the NGVs of a T700-GE-701c engine, during the brownout landing of an HH-60 Pave Hawk. We represent the engine as a one-dimensional system composed of several sub-systems, each of which processes the particulate laden flow, modifying its properties. These subsystems are depicted in Figure 2. In the current work, we developed a simple model of particle deposition for the turbine NGVs. We then applied these to the dose principle defined above. 2.1.1. Dust Dose Model The dose \u03b4\u221e is defined as the dust concentration multiplied by the duration of exposure: \u03b4\u221e = cvp\u2206tE (1) where cvp is the mass of dust per unit volume of particulate-laden air and \u2206tE is the duration of exposure. The mass flow rate of particles into the engine, Wp\u221e, is: Wp\u221e = cmpW\u221e = cmp\u03c1p\u221eV\u0307p\u221e (2) where cmp is the mass of particles per unit mass of engine-bound air (or mass concentration), W\u221e is the engine mass flow rate, \u03c1 and V\u0307 are the density and volume flow rate, respectively, and the subscripts p and p\u221e relate to particulate and bulk air-particle mix, respectively", + " The mass flow rate, combustor exit temperature, pressure and ratio of specific heats are included in this, but the other quantities must be inferred by applying mass continuity, ideal gas law and Sutherland\u2019s correction (Ch. 9, [39]), The density is found from the pressure, temperature and ratio of specific heats by applying the ideal gas law. However, to apply mass continuity to determine the bulk velocity requires knowledge of the flow cross-sectional area. For commercial reasons, engine manufacturers only publish a very limited set of data relating to the geometry of the engine. In the absence of direct measurements of the combustor exit/HP turbine entry cross-sectional area, we have used the cutaway shown in Figure 2. The temperature and velocity at entry into each stage is illustrated in Figure 6. The static pressure at each stage was also computed. 2.3.2. Dust Exposure Event We have selected two test dust blends of known composition to compare as analogues of the dusty environment: \u2022 Arizona A2 Fine, a commonly-used test dust for certification of particle separators. \u2022 AFRL02, a commercially available blend developed by Krisak et al. [5] at the U.S. Air Force Research Laboratories (AFRL) for sand ingestion testing to mimic the chemistry of CMAS-forming natural dusts" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004768_9668973_09764722.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004768_9668973_09764722.pdf-Figure3-1.png", + "caption": "FIGURE 3. Flux path on the core according to the rotor position. (a) At a mechanical degree of 0. (b) At a mechanical degree of 11.25.", + "texts": [ + " TARGET IPMSM FOR HEV APPLICATION The IPMSM is a suitable type of motor for the traction motor for the HEV applications, as the IPMSM satisfies the requirements on high torque density, superior power factor, and high efficiency [21]\u2013[24]. The target model benchmarked the model of the [25]. The specifications and requirements of the IPMSM are tabulated in Table 1, and configuration of the target model is shown in Fig. 2. 46600 VOLUME 10, 2022 To determine where to apply the GO, FEA is conducted to confirm the magnetic flux path of the target model. The JMAG, which is the commercial FEA analysis tool, is used to analyze the load and no-load conditions of the IPMSM. Fig. 3 shows the load condition flux path on the core according to the rotor position. The flux path on the rotor core is uniform regardless of the rotor position. However, the rotor is not suitable for GO application, as the flux path highly relies on the array of the magnet, and there is a mechanical stability problem at high-speed rotation. The stator core can be divided into two parts, the yoke and the teeth. The flux path on the yoke part varies greatly depending on the position of the rotor. However, the flux path on the teeth part is constant in the radial direction regardless of the rotor position" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002722_download_58477_60372-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002722_download_58477_60372-Figure8-1.png", + "caption": "Figure 8: Temperature inputted cylinder block", + "texts": [ + "0103 The developed cylinder block was subjected to Finite element analysis to ascertain the optimal values of the thermal condition of the component. The AutoCAD designed internal combustion engine component was imported into the Steady state thermal analysis environment of the Finite element ANSYS software. The component was meshed into 10190 and 19616 elements and nodes respectively as shown in Figure 7. The already meshed component had its cylindrical compartment inputted with a temperature of 100oC as shown in Figure 8. Also, a stagnant-air horizontal at 22oC was used as the convection value for the entire cylinder block as shown in Figure 9. The cylinder block was further subjected to temperature and total heat flux output analysis in order to ascertain the effect of the inputted parameters on the component as shown on Figures 10 and 11 respectively. The temperature output result showed that the highest temperature of 100oC occurred around the cylinderical bore axis while the lowest temperature of 51.97oC was found on the cooling fins of the component " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004975_load_0_0_49825_53866-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004975_load_0_0_49825_53866-Figure1-1.png", + "caption": "Figure 1: (a) The hybrid automobile Toyota Yaris, (b) its electric motor and (c) a possible SyncRM alternative", + "texts": [], + "surrounding_texts": [ + "Increasing environmental awareness is pushing the design of electic motors to favor none rare-earth solutions (i.e., without permanent magnets), and one such example is the SyncRM 2 (or concentrated-coiled SRM2) being proposed for the electric hybrid automobile Toyota Yaris. Following on an already established line of research on this topic, this article proposes a new design that re-assigns most of the magnetic material in the stator to the rotor \u2014 resulting in the Dual-sided SyncRM (a variant of the SRM2). The detrimental effect (caused by the extra gap) of slightly reducing the aligned inductance is overwhelmingly outweighed by the beneficial effect of drastically reducing the unaligned inductance. Extensive back-to-back FEMM analysis was conducted, where the recomputed SRM2 matches previous research, providing confidence to the favorable predictions of the Dual-sided SyncRM. Both performances are compared, with the venue being available for download on an open-source database. A realistic photo-rendered three-dimensional model is displayed and also available. An important outcome is the Dual-sided SyncRM torque (and power) increased by 29% (with respect to the SRM2), achieving a saliency ratio of 10 and an efficiency boost to 91% (at the rated operational speed of 1200rpm).\nKeywords: switched reluctance motor, magnetic FEM, analytic method, torque, power, efficiency\nThe hybrid vehicle Toyota Yaris (Figure 2a) runs on an electric motor possessing permanent magnets (Figure 2b) [Takeno et al, 2012]. There is a contemporary global effort to reduce the usage of rare-earth materials that has fueled research to find alternative solutions. A recent effort resulted in the formulation of an alternate design (Figure 2c) that uses solely the reluctance torque effect to operate [the Synchronous Reluctance Motor 2, or SRM2 as defined by Takeno et al (2012)]. Upon numerical simulations and experimental tests, this was proven to be an effective solution. Then building on this foundation, Stuikys and Sykulski (2020) created an effective and traceable low-order model (assisted by FEM magnetic numerical modeling) that predicted the SRM2 performance with impressive accuracy.\nContinuing on this approach, the present article builds on this collective research effort, and uses this low-order model to modify the stator and rotor design towards boosting its torque, power and efficiency. Over the past 50 years, research studies (Menzies 1972, Landislav et al 2020, Ionel and Popescu 2011) involving SR motors designed them such that the stator\u2019s magnetic mass was equivalent (or larger) than that of the rotor. This over unity stator-to-rotor mass ratio greatly influences the magnetic circuit impedance response, as the rotor turns between the aligned to the unaligned cases, and consequentially its performance.", + "A larger co-energy production (and thus torque/power per motor step rotation) is potentially achievable by minimizing the mass portion of magnetic conductor in the stator (that is, by re-assigning this mass to the rotor), such that the impedance when the rotor is unaligned is dramatically reduced (with an acceptable collateral reduction of the aligned impedance).\nThe SRM2 is a radial flux synchronous reluctance motor possessing at the center an aluminium shaft, a steel rotor with 18 physical poles, and a surrounding steel stator with 12 physical poles (Figure 2a). The gap between the stator and rotor is 0.5mm wide. Each stator pole has concentrated coils composed of twenty two sets of 17 parallel connected turns of AWG wire with 0.6mm internal diameter. They are driven by a three-phased electric bus controlled via a Pulse-Width Modulation (PWM) scheme (characteristic for this type of motor). This means that sets of 6 coils disposed in a hexagonal manner are driven by one of the phases, creating six electromagnetic poles that (with alternation from one phase to the next) creates the effect of a rotating magnetic field. The rotor cavities between the stator and rotor are filled with air, as is the surroundings of the motor/stator (representing an important boundary condition to be implemented later during the numerical analysis).\nThe proposed design modification (hereafter termed Dual-sided SyncRM shown in Figure 2b) circumferential splits the stator at the radially outer extremity of the windings, and re-assigns that outer part of the magnetic circuit to the rotor (which is hence forth termed the rotor outer ring). This has the consequence of generating an outer gap (in addition to the inner gap), and of making the motor slightly bigger (i.e., the outer diameter increased). However, the modification of the motor did not affect its inner dimensions, that is the diameter of the shaft remains the same, and so does the (now termed) rotor inner ring (where before, it was just the rotor in Figure 2a), the size and locations of the windings is also the same, and so is the location and size of the stator poles. It is worth mentioning that the modified design is just a first attempt that is by no means optimized; there is plenty of room for improvement. It is assumed that the Dual-sided SyncRM will operate via the same power bus and PWM-controller scheme as the SRM2 [for further details, please see Stuikys and Sykulski (2020)].\nA 3D model of the Dual-sided SyncRM is shown in Figure 3, and available (FCStd1, Step, Stl) to download here at this author\u2019s open profile page. This was built with the open-source software FreeCAD, and professionally photo-rendered using the open-source software CADrays. It\u2019s key characteristics are now briefly explained. The stator is composed of a rear structural disc-like feature that fixes onto the vehicle interface, and to which (on the other side) the poles are connected (Figure 3a). In turn, these stator poles slide inside the Dual-sided rotor, in itself composed of an inner and outer ring linked by structural connectors. The windings are virtually the same as the SRM2, with slight modifications being made at each extremity (necessary to hold the windings in place). As shown in the zoom at the lower left corner of Figure 3a, the individual wires are turned around the open slot/gap at the front end and at the closed slot/gap at the back. These" + ] + }, + { + "image_filename": "designv8_17_0000938_.2478_mspe-2020-0039-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000938_.2478_mspe-2020-0039-Figure3-1.png", + "caption": "Fig. 3 A diagram of Terra-Hammer ground rocket 1 \u2013 control edges, 2 \u2013 control hose, 3 \u2013 front conical part of housing, 4 \u2013 core, 5 \u2013 transverse drill hole, 6 \u2013 air outlet", + "texts": [ + " It is connected with the resistances of the ground environment during a dislocation of the cutting head [8]. In the case of uncontrolled, pushing-out ground thickening methods ramming and ground pushing devices, called ground rockets, are used very often. In Poland these devices have a common name \u201cmole\u201d [1, 10]. The first ground rocket was designed in England in 1916. This device consisted of a metal cylinder with a sharpened front. Rams, controlled with compressed air, were installed inside the cylinder. In Fig. 3 a diagram of this ground rocket of Terra-Hammer type, made by Terra Company [19], is presented and in Fig. 4 a solution, developed by the Terra Max Company [17], is shown. Source: [17]. Source: [16]. The schematic diagram of this method, consisting in an implementation of an in-coming installation with the dynamic head is presented in Fig. 5. Source: [10]. It is one of the simplest excavationless methods and it is based on an introduction into the ground of the installation 3 (usually flexible) directly behind the dynamic head, [1, 10]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002178_18_24_10724.full.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002178_18_24_10724.full.pdf-Figure1-1.png", + "caption": "Figure 1. Description of the task. A, Front view of the object held in the vertical position and side view of the tilted object. The load force is the vector sum of the forces Fx and Fy ; c.g, center of gravity. B, Side view of the six spherically curved grasp surfaces. C, Time traces of the major parameters measured during the various phases of a trial in the first experiment. Grip force is averaged for the two digits; tangential torque is shown independently for the thumb (broken line) and index finger (solid line); load force is averaged. The measurements representing the static hold phase before tilting are shown by a (1 sec period), the tilting phase is shown by b, the static tilt phase is shown by c (1 sec period), and the slip test is shown by d. Curvature, 50 m 21; target torque, 66 mNm. D, In the second experiment, there was no slip test; instead, the object was returned to its holder. Curvature, 100 m 21; target torque, 74 mNm.", + "texts": [ + " A test object, resting in a holder on the floor, had its grasp surfaces located 35 cm above the ground and ;10 cm to the right of and 20 cm anterior to the subject\u2019s right hip. Subjects grasped the object in a precision grip using the right index finger and thumb, lifted the object, and then tilted it through ;65\u00b0 by principally using a combination of elbow flexion and radial flexion of the wrist. The subjects could see the object and their hand throughout the experiments. The test object had two symmetrical grasp surfaces and a 31 cm long aluminum rod that protruded orthogonal to the axis between the centers of the grasp surfaces (Fig. 1 A). Pairs of exchangeable matching grasp surfaces were attached to the test object. All surfaces were spherically curved (Fig. 1 B); two pairs were concave with radii of 20 and 40 mm (curvatures, 250 and 225 m 21), one was flat (curvature, 0 m 21), and three were convex with radii of 20, 10, and 5 mm (curvatures, 50, 100, and 200 m 21). Surfaces were coated with silicon carbide grains (50\u2013100 mm) covered with a thin layer of cyanoacrylate to give a finish similar to that of a fine grain sandpaper. When attached, the lateral edges of the surfaces were separated by 59 mm. Each surface was attached to the object via a six-axis force\u2013torque sensor (Nano F/T transducer; ATI Industrial Automation, Garner, NC) that measured forces and torques in three dimensions", + " Observation of our subjects revealed no obvious violation of this instruction; over all trials and all subjects, the ratio of the two grip forces during phase 3 above was 1.01 6 0.01 (mean 6 SD; n 5 888). Thus, in Results, we present data for the average grip force of the two digits. Tangential torques are either specified for each digit independently or are given as the total torque (sum for the two digits) as appropriate. Time traces of the measured parameters are illustrated for the various phases of the task in Figure 1C. For each trial, the grip forces, tangential torques, linear load forces, and tilt angle were measured as their mean values during a 1 sec interval when the object was held steady before the tilting movement (Fig. 1C, a). This interval commenced 4 sec after the object was first contacted (defined by the time at which the sum of the grip forces for the two digits first exceeded 0.3 N). Mean values of the same signals were also calculated during a 1 sec interval, located in the middle of the 4 sec static tilt phase (Fig. 1C, c). During the tilt phase (Fig. 1C, b), grip force measurements were taken at times when the total tangential torque at the two digits had increased by 10, 50, and 90% of the increase in total tangential torque that occurred from the period before tilt (Fig. 1C, a) to the period when the object was maintained tilted (Fig. 1C, c). In addition, the maximum grip force was measured as the peak value within 61 sec after the end of the tilt phase. Angular velocity and angular acceleration were assessed from the first and second time derivatives of the tilt angle, respectively, using a 66 point numerical differentiation (650 msec window). The rise time of the angle during the tilting movement (Fig. 1C, b) was taken as the interval from 10 to 90% of the increase in tilt angle that occurred from phase a to phase c in Figure 1C. For each trial in the first experiment, the relationship between grip force and tangential torque over the window of rotational slip (Fig. 1C, d) was established independently for each digit by linear regression. This window was determined off-line by visual inspection of the time traces of tilt angle, grip force, and tangential torque and by inspection of the corresponding force\u2013torque plots. The regression constants and the measured tangential torques were used to estimate, for each digit, the minimum grip forces required to prevent slip (slip forces) during the static tilt phase. The safety margin was calculated as the difference between the static grip force and the larger of the slip forces for the thumb and index finger" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004555_f_version_1699369650-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004555_f_version_1699369650-Figure8-1.png", + "caption": "Figure 8. Cruciform welded joints ultrasonic fatigue testing specimens with main dimensions shown (mm) [15] (with permission from Elsevier, 2023).", + "texts": [ + " The fatigue strength of the welded joints was less than that of the base metal, especially as the number of cycles to failure increased. Fractography revealed that the fatigue crack initiation sites in welded specimens were inclusions and pores; hence, these were the principal reasons for the reduction in fatigue strength [41]. One limitation of this study is the absence of recorded runout specimens, which would have aided in the statistical evaluation of the results [42]. The VHCF properties of cruciform arc-welded joints of Q235 and Q345 structural steels were studied by Yin et al. [15]. The cruciform joints, shown in Figure 8, were comprised of four non-load-carrying fillet welds and assessed using UFT. A continually decreasing S\u2013N curve in the VHCF regime was observed for welded specimens of both Q235 and Q345. Failures occurred above 109 cycles, and no runout specimens were reported; hence, a fatigue limit was not observed for the cruciform joints and cracks initiated at the weld toes from slag inclusions or machining marks. Additionally, the effect of ultrasonic peening treatment (UPT) was investigated; it was found that the VHCF strength was significantly increased for welded joints of both base metals due to grain refinement and the generation of beneficial compressive residual stresses [15]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001251_al-02449247_document-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001251_al-02449247_document-Figure9-1.png", + "caption": "Figure 9: Pressure fields (CFD Euler calculations) for two studied configurations (up: symmetrical NACA, bottom: double-wedge) at subsonic regime (Mach number: 0.5, angle of attack: 5 deg)", + "texts": [ + " Moreover, these two components have an important impact not only on the return phase but also on the ascent phase (additional dry mass and drag at ascent). In order to estimate the influence of the wing planform and airfoil, a sensitivity study has been performed for two wing profiles: double wedge and symmetrical NACA (Figure 8). The first tends to present advantages for the supersonic regime whereas the latter is more efficient for the subsonic regime. For this analysis, two aerodynamic databases have been generated (Figure 9) and Lift-over-Drag (L/D) ratio of the configurations have been compared. Aerodynamic results show a benefit to use NACA airfoil profile due to a better L/D ratio especially in the subsonic regime that is of prime interest concerning the return gliding trajectory (Figure 10). However, the configuration with NACA airfoil profile presents a larger drag in supersonic regime due to the radius of curvature, that can be disadvantageous for the ascent phase inducing more propellant for this phase. Then a global trade-off between the performance for both ascent and return phases has to be performed. The difference in terms of pressure field along the airfoils is illustrated in Figure 9. A coupled analysis between aerodynamics and trajectory optimization is required to assess this trade-off (see next Section). Concerning the wing planform, two different wingspans, corresponding to 3 and 5 times the main core diameter have been studied (the wing share the same root chord, that is set with respect to the thrust frame length). As expected, the L/D ratio for the larger wing presents better characteristics. However, it comes to the cost of increasing the size of the reusability kit and additional space needed on the launch pad for the ground operations and lift-off" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003043_f_version_1611835323-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003043_f_version_1611835323-Figure2-1.png", + "caption": "Figure 2 shows the FRM designs and the flux density magnitude plots before and after the optimization. An asymmetrical rotor was chosen for the FRM since it was shown in [11,14] that such a rotor design provides positive values of the torque waveform during the entire period, in contrast to a symmetrical rotor.", + "texts": [ + " The Nelder\u2013Mead algorithm, described in [32], was used in designing a new FRM with bonded magnets. The number of optimization parameters was nine. The mathematical model described in [33] was used to evaluate the objectives <\u03b7> and max(S) included in the optimization function (2). Mathematics\u00a02021,\u00a09,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 8\u00a0of\u00a013\u00a0 \u00a0 \u00a0 Table\u00a02\u00a0shows\u00a0the\u00a0variable\u00a0design\u00a0parameters\u00a0of\u00a0the\u00a0FRM\u00a0before\u00a0and\u00a0after\u00a0the\u00a0opti\u2010 mization.\u00a0Next\u00a0to\u00a0the\u00a0initial\u00a0value\u00a0of\u00a0the\u00a0variable\u00a0parameter,\u00a0its\u00a0increment\u00a0at\u00a0constructing\u00a0 the\u00a0initial\u00a0simplex\u00a0is\u00a0given.\u00a0As\u00a0seen\u00a0in\u00a0Table\u00a02\u00a0and\u00a0Figure\u00a02,\u00a0the\u00a0maximum\u00a0flux\u00a0density\u00a0 decreased\u00a0as\u00a0a\u00a0result\u00a0of\u00a0optimization.\u00a0In\u00a0addition,\u00a0the\u00a0thickness\u00a0of\u00a0the\u00a0yoke,\u00a0which\u00a0was\u00a0 underutilized\u00a0in\u00a0the\u00a0initial\u00a0design,\u00a0was\u00a0reduced,\u00a0which\u00a0increased\u00a0the\u00a0flux\u00a0density\u00a0in\u00a0the\u00a0 yoke.\u00a0It\u00a0made\u00a0it\u00a0possible\u00a0to\u00a0increase\u00a0the\u00a0value\u00a0of\u00a0Rstat,inner.\u00a0Figure\u00a03\u00a0shows\u00a0the\u00a0dependence\u00a0 of\u00a0the\u00a0torque\u00a0on\u00a0the\u00a0rotor\u00a0angular\u00a0position\u00a0before\u00a0and\u00a0after\u00a0optimization\u00a0for\u00a0two\u00a0loading\u00a0 modes\u00a0of\u00a0the\u00a0FRM\u00a0with\u00a0bonded\u00a0magnets.\u00a0Figures\u00a04\u00a0and\u00a05\u00a0demonstrate\u00a0the\u00a0waveforms\u00a0of\u00a0 the\u00a0current\u00a0and\u00a0voltage\u00a0depending\u00a0on\u00a0the\u00a0rotor\u00a0angular\u00a0position\u00a0before\u00a0and\u00a0after\u00a0optimi\u2010 zation\u00a0 for\u00a0 two\u00a0 loading\u00a0modes\u00a0of\u00a0 the\u00a0FRM\u00a0with\u00a0bonded\u00a0magnets", + " Figure 3 shows the dependence of the torque on the rotor angular position before and after optimization for two loading modes of the FRM with bonded magnets. Figures 4 and 5 demonstrate the waveforms of the current and voltage depending on the rotor angular position before and after optimization for two loading modes of the FRM with bonded magnets. PPTR and AMinTD changed only slightly. This is because the initial design was obtained by scaling the design of the optimized FRM with sintered rare-earth magnets [11]. Mathematics 2021, 9, 256 7 of 11 Mathematics\u00a02021,\u00a09,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 8\u00a0of\u00a013\u00a0 \u00a0 \u00a0 \u00a0 (a)\u00a0 (b)\u00a0 Figure\u00a02.\u00a0Calculation\u00a0area\u00a0arrangement\u00a0and\u00a0flux\u00a0density\u00a0magnitude\u00a0plot\u00a0(T)\u00a0in\u00a0the\u00a0FRM\u00a0(a)\u00a0before\u00a0optimization\u00a0and\u00a0(b)\u00a0after.\u00a0 Table\u00a02\u00a0shows\u00a0the\u00a0variable\u00a0design\u00a0parameters\u00a0of\u00a0the\u00a0FRM\u00a0before\u00a0and\u00a0after\u00a0the\u00a0opti\u2010 mization.\u00a0Next\u00a0to\u00a0the\u00a0initial\u00a0value\u00a0of\u00a0the\u00a0variable\u00a0parameter,\u00a0its\u00a0increment\u00a0at\u00a0constructing\u00a0 the\u00a0initial\u00a0simplex\u00a0is\u00a0given.\u00a0As\u00a0seen\u00a0in\u00a0Table\u00a02\u00a0and\u00a0Figure\u00a02,\u00a0the\u00a0maximum\u00a0flux\u00a0density\u00a0 decreased\u00a0as\u00a0a\u00a0result\u00a0of\u00a0optimization.\u00a0In\u00a0addition,\u00a0the\u00a0thickness\u00a0of\u00a0the\u00a0yoke,\u00a0which\u00a0was\u00a0 underutilized\u00a0in\u00a0the\u00a0initial\u00a0design,\u00a0was\u00a0reduced,\u00a0which\u00a0increased\u00a0the\u00a0flux\u00a0density\u00a0in\u00a0the\u00a0 yoke.\u00a0It\u00a0made\u00a0it\u00a0possible\u00a0to\u00a0increase\u00a0the\u00a0value\u00a0of\u00a0Rstat,inner.\u00a0Figure\u00a03\u00a0shows\u00a0the\u00a0dependence\u00a0 of\u00a0the\u00a0torque\u00a0on\u00a0the\u00a0rotor\u00a0angular\u00a0position\u00a0before\u00a0and\u00a0after\u00a0optimization\u00a0for\u00a0two\u00a0loading\u00a0 modes\u00a0of\u00a0the\u00a0FRM\u00a0with\u00a0bonded\u00a0magnets.\u00a0Figures\u00a04\u00a0and\u00a05\u00a0demonstrate\u00a0the\u00a0waveforms\u00a0of\u00a0 the\u00a0current\u00a0and\u00a0voltage\u00a0depending\u00a0on\u00a0the\u00a0rotor\u00a0angular\u00a0position\u00a0before\u00a0and\u00a0after\u00a0optimi\u2010 zation\u00a0 for\u00a0 two\u00a0 loading\u00a0modes\u00a0of\u00a0 the\u00a0FRM\u00a0with\u00a0bonded\u00a0magnets" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure5-6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure5-6-1.png", + "caption": "Figure 5-6. Champs \u00e9lectriques d'un dip\u00f4le avant et apr\u00e8s rotation de 45\u00b0 selon l'axe x", + "texts": [ + " La Figure 5-5 illustre cette n\u00e9cessit\u00e9 d'interpolation pour pouvoir se replacer dans le rep\u00e8re sph\u00e9rique initial en prenant comme exemple le champ \u00e9lectrique total d'un dip\u00f4le polaris\u00e9 verticalement auquel nous avons fait subir une rotation de 45\u00b0 selon \u03b8 . Il faut cependant noter que dans le cas d'une rotation uniquement selon l'axe z d'un pas entier, il n'est pas n\u00e9cessaire d'effectuer ces \u00e9tapes de r\u00e9-\u00e9chantillonnage et d'interpolation. 151 5.2.6 Exemple : rotation d'un dip\u00f4le Afin d'illustrer l'ensemble des consid\u00e9rations pr\u00e9sent\u00e9es dans cette partie, nous prenons l'exemple de la rotation d'un dip\u00f4le initialement orient\u00e9 selon l'axe z. La Figure 5-6 pr\u00e9sente le champ \u00e9lectrique total, les champs \u00e9lectriques selon les composantes \u03b8 et \u03c6 , avant et apr\u00e8s rotation de 45\u00b0 selon l'axe x. Avant la rotation de l'antenne, la composante du champ \u00e9lectrique selon \u03c6 est nulle car le dip\u00f4le \u00e0 une polarisation purement verticale. Apr\u00e8s rotation, repolarisation, interpolation et r\u00e9-\u00e9chantillonnage nous obtenons une composante non nulle sur les deux composantes du champ \u00e9lectrique. 152 5.3.1 Le gain de diversit\u00e9 Comme nous l'avons abord\u00e9 dans le chapitre pr\u00e9c\u00e9dent, l'efficacit\u00e9 d'un syst\u00e8me \u00e0 diversit\u00e9 d'antennes est g\u00e9n\u00e9ralement \u00e9tablie \u00e0 partir du gain de diversit\u00e9 (DG)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure11-1.png", + "caption": "Figure 11: Second iteration of compliant landing mechanism.", + "texts": [ + " 7 Figure 6: Deformation profile over 2000 seconds of 4 bar compliant mechanism. ...................... 7 Figure 7: Modal analysis of viscoelastic and non-viscoelastic material. ....................................... 8 Figure 8: Response PSD results for viscoelastic and non-viscoelastic materials. ......................... 9 Figure 9: Deformed shapes of optimized structures for the inverter. ............................................ 9 Figure 10: First iteration of compliant landing mechanism. ........................................................ 10 Figure 11: Second iteration of compliant landing mechanism......................................................11 Figure 12: Third iteration of compliant landing mechanism. .......................................................11 Figure 13: Fourth iteration of compliant landing mechanism. .....................................................11 Figure 14: Failure mode of landing gear during impact FEA test. .............................................. 12 Figure 15: Reference dynamic landing gear mechanism [9]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004162_icle_download_175_77-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004162_icle_download_175_77-Figure1-1.png", + "caption": "Figure 1. Conceptualized design of terrace-based hydroponics system using hydraulic ram pump", + "texts": [ + " The last component of the system was a 1/2-inch diameter PVC suction pipe, which connects to the main water source, enabling Parami et al. - CLSU International Journal of Science and Technology - Vol. 8 No. 1, 2024 DOI: https://doi.org/10.22137/ijst.2023.v8n1.03 29 water to be drawn from the excess water collectors. The final design of the terrace-based hydroponic system was composed of five major components, namely (a) channels and pipes, (b) water storage tanks, (c) a ram pump, (d) excess water collectors, and (e) a suction pipe, as shown in Figure 1. Figure 2 shows how the nutrient solution started to flow from the water storage tank, passing through the drive pipe to the hydraulic ram pump, which pumped up 10% of the nutrient solution to the channels, exiting the excess water collectors. The remaining 90% was splashed out from the waste valve of the ram pump and was collected by the excess water collectors as well. The suction pipe brought back some of the nutrient solution to the water storage tank to continue the 15- minute operation Figure 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003725_f_version_1602316734-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003725_f_version_1602316734-Figure1-1.png", + "caption": "Figure 1. A buoy-type direct-drive wave energy converter.", + "texts": [ + " These systems are often bulky and less robust due to the dual/multistep conversion process. In recent years, more and more direct-drive energy converters, which extract power directly from the reciprocating wave motion, have been proposed. In these direct-drive energy converters, the linear-to-rotary conversion process can be eliminated, improving the system performance. A direct-drive wave energy converter can be realized by connecting the translator of a linear machine to a floating buoy, as shown in Figure 1 [8,9]. The relative motion between the stator and the translator is used to extract energy from the ocean waves. This relative motion needs to be maximized for effective power extraction. The machine is therefore installed on the seabed. As the wave speed is usually about 1 m/s, the thrust force of the converter needs to be large. The permanent magnet (PM) linear machines are a good choice for these systems since they have the inherent merits of high force density and high efficiency. However, wave energy has significant seasonal variability [10,11]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004361_rs-740948_latest.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004361_rs-740948_latest.pdf-Figure4-1.png", + "caption": "Fig 4 : (a) Compliant slider crank mechanism and (b) its PRBM", + "texts": [ + " The related design procedure for designing a flexure hinge is presented in Fig.3. In addition, the method using the generic design equations is also described in the flow chart of Figure 3. Fig.3: Design flow chart for designing a FCM Before approaching towards design procedure of flexure based compliant slider-crank mechanism it was necessary to calculate values of certain parameters to construct model of compliant slider-crank mechanism i.e. length of flexible hinge l, \u019f3 (angle between crank and coupler) and XB (slider displacement) with respect to \u019f2. As shown in Figure 4(b), link r2 is the rigid parts of the flexible slider crank mechanism; l is the flexible hinge connecting joint between coupler and slider to make the mechanism movable by using theirs elastic deformation instead of traditional revolute pair [3]. The template is used to format your paper and style the text. All margins, column widths, line spaces, and text fonts are prescribed; please do not alter them. You may note peculiarities. For example, the head margin in this template measures proportionately more than is customary" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000591_f_version_1671613940-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000591_f_version_1671613940-Figure7-1.png", + "caption": "Figure 7. Magnetic flux density distribution in the investigated IMs.", + "texts": [ + " The results show that both cases\u2019 efficiency remains the same at 89%. The optimized stator and rotor slots design shows a significant improvement in terms of breakdown torque with an increment of 7.21 Nm or 14.3% improvement. The power factor is slightly increased by 0.005 or 0.6% improvement compared with the initial setting. The optimized motor is further validated by using a finite element method and discussed in the following subsection. Ansys Maxwell 2D software is used to carry out a finite element analysis for IM model validation in this work. Figure 7 shows the magnetic flux density distribution in IMs from the finite element analysis at initial and optimal settings. The results show that high flux density can be observed near to the stator and rotor slot wedges where the readings are between 1.82 and 1.95 T for initial setting and 1.88 and 2.01 T for optimal setting. The magnetic flux density in the narrowest stator teeth at some places show almost the same readings. However, the high values of flux density only occur at small parts of the IMs and most of the readings are roughly between 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001086_1934_context_journal-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001086_1934_context_journal-Figure6-1.png", + "caption": "Fig. 6. The schematic of running mechanism with oversteer characteristic.", + "texts": [ + " In other words, the turning radius decreases when the vehicle is accelerated with fixed steering wheel. For the same steering wheel position and vehicle forward speed, the turning radius of an understeer vehicle is smaller than that of a neutral steer vehicle. When a side force acts at the center of gravity of an oversteer vehicle originally moving along a straight line, the front tires will develop a slip angle less than that of the rear tires. As a result, a yaw motion is initiated, and the vehicle turns into the opposite direction of side force, as shown in Fig. 6. Steering simulation analysis of the running mechanism with planetary gear is conducted in ADAMS software with different speed. ADAMS is the abbreviation for \u201cAutomatic Dynamic Anal- ysis of Mechanical Systems\u201d. It is a software for virtual prototyping analysis developed by MDI corporation in America. The structure of running mechanism has been simplified in the process of modeling. The link rod components are used instead of the suspension of running mechanism, wheels and ground are connected by tire force, driving force is set on the sun gear of the planetary gear train, and the articulation joint is replaced by two superposed revolute joint of orthogonal Zaxis [14]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001922_1044-023-09952-2.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001922_1044-023-09952-2.pdf-Figure16-1.png", + "caption": "Fig. 16 First contact-cage model (C1): (a) Normal planes of the cage for each pocket; (b) Complete model", + "texts": [ + " This second group includes six bearing model designs, named contact-cage models, which distinguish themselves from the solutions presented in the previous section by defining the cage as a single body with its own properties (inertia, material and geometry) that interacts with all rolling elements simultaneously, thus resulting in a more complex behaviour. The first model considering a contacting cage, referred to as C1, utilised the circle\u2013plane interaction methodology described in Sect. 4.1 to define two planes for each pocket within the balls would freely move, while kept separated from the other rolling elements. Figure 16 illustrates a schematic representation of the C1 model. Points PJ1 and PJ2, which define the limits of the cage pocket, were determined by setting a value for the angular amplitude with respect to the central line of the pocket. They, as well as the geometrical centre of the pocket, are set along the pitch circle, and the normal vector for the two cage planes is derived from them. However, this approach presented certain drawbacks. Since no interaction between the cage and the rings had been defined, a revolute joint was necessary to keep the cage centred with respect to the outer ring" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001999_f_version_1692867577-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001999_f_version_1692867577-Figure12-1.png", + "caption": "Figure 12. 2 aglev valve [135].", + "texts": [ + " The new 2D maglev valve comprises a linear electro-mechanical converter (LEMC), a maglev coupler, and a 2D valve. The LEMC is connected to an external armature, and the linear motion of the external armature is converted into a rotary motion of the spool by the maglev coupling. There is a high-pressure orifice and a low-pressure orifice in the spool, and spool rotation changes the opening of the high-pressure and low-pressure orifices, thus changing the pressure at both ends of the spool, as shown in Figure 12. Wang XP et al. [136] proposed an electro-mechanical converter with two pushrods. The inner coil controls the movement of the inner rod, and the outer coil controls the movement of the outer rod. The inner and outer rods are connected to a proportional valve spool. By controlling the current in the coil, the inner and outer rods can be moved simultaneously, or one of them can be moved. The direction of movement of the inner and outer rods can be changed by changing the direction of the current. Thus, changing the current of the double pushrod electro-mechanical converter can drive the spool movement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002053_e_download_2200_1306-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002053_e_download_2200_1306-Figure17-1.png", + "caption": "Figure 17: Diagram for tilt sensing using accelerometer", + "texts": [ + " Tilt it one way and the voltage will increase, tilt it the other way and it will decrease. With a Triple axis accelerometer, the z-axis will be measuring 1g with the device horizontal. The output of an accelerometer is a sinewave of the acceleration measured. The inclination sensing used in this project uses the gravity vector and its projection upon the accelerometer\u2019s axes to find the angle of tilt. As the human leg will induce a centripetal acceleration upon the accelerometer and rotate, the output will also change accordingly as gravity is a DC acceleration. As seen from Figure 17, the angle of tilt can be determined through the accelerometer\u2019s variable X as we are only measuring a relatively limited angle that can be measured by a single axis. Using the diagram above, we can ISSN: 2167-1907 www.JSR.org 12 infer using basic trigonometry that the output acceleration produced by the projection of the gravity vector is equal to sine theta, the angle between the accelerometer x-axis and the horizontal, which is perpendicular to the gravity vector. Taking gravity to be equal to 1g, the output acceleration can be expressed as: \ud835\udc34\ud835\udc34 = \ud835\udc54\ud835\udc54 \u00d7 \ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60(\u03b8)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureC.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureC.1-1.png", + "caption": "Figure C.1: Test rig for measurement of sideways stiffness, W. Pot design Section C.1.5.", + "texts": [ + " The initial requirement for Pot of accomodate different fingers without modifying them was removed and the clamping could be improved. In the presented appendix, further analysis of the existing design and improvements are carried. The main focus is the sideways stiffness measurement. C.1.2 Measured Stiffness The stiffness measured in the test rig is a relation between the load applied and the displacement measured by the LVDT sensor. Furthermore the stiffness of the elements of the test rig must be considered to calculate the stiffness of the finger. From Fig. C.1 it can be observed that the parallel guidance is in parallel with the finger. The stiffness measured by the test rig must be subtracted by the stiffness of the parallel guidance in order to obtain the stiffness of the finger. Page 49 Km = Kpg +Kl (C.1) Where Km is the measured stiffness, Kpg the stiffness of the parallel guidance and Kl is the stiffness of the components in series. Kl = ( 1 Kclamp + 1 Kfinger )\u22121 (C.2) Where Kclamp is the stiffness of the clamping of the finger and Kfinger the stiffness of the finger, including the phalange" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure4-1.png", + "caption": "Figure 4: Compliant 4 bar mechanism.", + "texts": [ + " 36 iv Nomenclature \ud835\udc3a\ud835\udc5b Shear Modulus \ud835\udc3e\ud835\udc5b Bulk Modulus \ud835\udf0f\ud835\udc5b Relaxation time \ud835\udc62\ud835\udc56\ud835\udc5b Input displacement \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 Output displacement PRBM Pseudo-rigid-body model \ud835\udc58 Stiffness of PRBM \ud835\udc38 Elastic Modulus \ud835\udc61 Smallest width of compliant joint \ud835\udc45 Radius of compliant joint cutout \ud835\udc4f Thickness of compliant joint \ud835\udf03 Angle of deflection of complaint mechanism \ud835\udefe Drone landing slope angle \ud835\udefe\ud835\udc5f Characteristic radius factor \ud835\udc40 Moment imposed on compliant joint \ud835\udc3c Second area moment of inertia \ud835\udc50 Perpendicular distance from neutral point to furthest point on cross section v Figure 1: Mechanical model comprising of Hooke\u2019s element and \u201cn\u201d Maxwell Elements [4]. .... 3 Figure 2: Load and Boundary Conditions of 4 Bar Mechanism. ................................................... 4 Figure 3: Deflection distribution over time. .................................................................................. 4 Figure 4: Compliant 4 bar mechanism. .......................................................................................... 5 Figure 5: Maximum deformation 33.78 mm in -x at 120 seconds. ............................................... 7 Figure 6: Deformation profile over 2000 seconds of 4 bar compliant mechanism. ...................... 7 Figure 7: Modal analysis of viscoelastic and non-viscoelastic material. ....................................... 8 Figure 8: Response PSD results for viscoelastic and non-viscoelastic materials", + " The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002162_tation-pdf-url_53237-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002162_tation-pdf-url_53237-Figure6-1.png", + "caption": "Figure 6. Aperture-coupled stacked microstrip patch antenna.", + "texts": [ + " We observe that all nonresonant slot coupled antennas have very similar performance, but hourglass is slightly better than the others. A resonant slot with two stacked patches achieves almost 54% BW. Earlier sections have led us to a conclusion on the topology of the element antenna. The final results show that an aperture-coupled stacked patch antenna with an hour-glass shaped Design of a Ku Band Planner Receive Array for DBS Reception Systems http://dx.doi.org/10.5772/66374 249 nonresonant aperture would be the best solution for the element antenna. Figure 6 shows the structure of the antenna to be designed. The antenna was optimized through simulations in a commercial full-wave electromagnetic solver to give the best results possible, followed by this optimization the realized antenna is shown in Figure 7. Target band is the Ku band downlink frequencies. Radiating and parasitic Microwave Systems and Applications250 patches were formed on flexible PCBs with 75 \u00b5m thickness and were placed over the slots using Rohacell HF 31 foam (\u03b5r = 1.046, tan\u03b4 = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001734_e_download_2825_3901-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001734_e_download_2825_3901-Figure4-1.png", + "caption": "Figure. 4. Stress at 50% of the engine load", + "texts": [ + " P\ud835\udc61 = \u03b7 \ud835\udc5a x P\ud835\udc50 (6) Then the value of turbine torque (\u03c4\ud835\udc61) can be calculated using the following equation (Eq. 7). \u03c4\ud835\udc61 = P\ud835\udc61 2\u03c0 x n (7) According to the calculation before, the result of the torque calculation is in Table 6 and Table 7. Then, it has been calculated the difference torque between compressor and turbine for torque value (Table 8). Thus, the \u0394\u03c4 can be obtained that shows the magnitude of the torsion value given to simulation. Furthermore, the value of \u0394\u03c4 becomes input data to FEM simulation. Some simulation to do such as stress, amount of displacement, strain and safety factor. The result (Figure 4) at 50% of the engine load is an example from several engine load variations (50%, 60%, 70%, 80%, 90% and 100%). It is found that the minimum value is at the end of compressor side one with the value about 6.94279 x 10-12 Mpa, while the maximum value is 0.015906 Mpa. The result is still far from the stress limit of material used (17NiCrMo6-4) that is about 295.594 Mpa. It means that the turbocharger shaft material is stronger than the load given. Another result of some loads is about 0.015296 Mpa at 60% of the engine load, 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure16-1.png", + "caption": "Fig. 16 Central hollow tread wear results occasionally in local conformal or bad contact between worn 923 wheel and rail on some rail sections, which forces bogie frame to produce lateral forced vibration when 924 running in tangent lines. (a \u2013 b) Equivalent conicity and RRD curves calculated by slight central hollow 925", + "texts": [ + " For this 887 purpose, the collaborative and innovative efforts of rail professionals are required, such 888 as preventive or maintenance rail grinding treatments to avoid the RCF failure on rail 889 shoulder at one side of gauge corner as much as possible. 890 4.5 Design optimization of service car body system 891 In order to ensure the 30-year service life of aluminium alloy car body, as shown in Fig. 892 (16 - 18), the passenger transport discipline should carry out the optimal route planning 893 and design, so as to remove and eliminate the negative impacts of central hollow tread 894 wear on the lateral coupling vibration of service car body. 895 (1) External excitation source belongs to unsaturated and unsteady state. As 896 shown in Fig. 16, the mutual influence will take place occasionally between the 897 parametric disturbance of wheel spin and the forced vibration of bogie frame. As for 898 slight central hollow tread wear, the local conformal or bad contact is occasionally 899 constructed on specific rail sections, the rail running light band becomes widened and the 900 wheel wear is concentrated on the central tread. Different from the bogie hunting 901 instability failure caused by the primary or secondary hunting phenomenon, the slight 902 central hollow tread wear forces the wheels to produce spin creepage", + " 906 This forced vibration response can only change into resonance when the vehicle 907 speed is greater than 450 km/h, the dominant frequency of which changes ca. 6.0 Hz. 908 Therefore, within the service speed of (300 - 450) km/h, the above forced vibration 909 response has obvious broadband characteristics, with the dominant frequency of ca. (7.0 - 910 8.0) Hz and the leading frequency of 10 Hz or more in general, which constructs a 911 sufficiently strong external excitation source. Specifically, in the general curving 912 negotiation with speed of 250 km/h, the UK small defect spectrum does not change the 913 wear characteristics shown in Fig. 16 (c). 914 In order to avoid the further deterioration of such forced vibration responses, it is 915 necessary for the passenger transport discipline to carry out the planning and design 916 optimization of the operating routes, as shown in Fig. 17, to enhance the self-cleaning 917 capability of central hollow tread wear. The German track spectrum of high interference 918 does not weaken the excitation inputs for small defects of wavelength \u2264 3 m and long-919 wave irregularities. Especially, the long-wave horizontal irregularity excitation input can 920 cause the roll and rock of service car body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000437_-ijaefea20210709.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000437_-ijaefea20210709.pdf-Figure3-1.png", + "caption": "Fig. 3 Meshing", + "texts": [], + "surrounding_texts": [ + "To select dc motor, we need to calculate total weight which need to slide from motor on frame, Factor considered for weight 1. Tray weight 2. Nut, bolts weight 3. Frame weight 1. Tray weight Tray weight from cad model = 1.3 kg x 3 Tray = 3.9 kg = 4kg round off (1) Assume 15 nuts, M6 \u00d7 15 nuts = 2.50gm \u00d7 15 = 37.5 grams M8 \u00d7 15 nuts =5.1 gm \u00d715 = 76.5 grams M10 \u00d7 15 nuts = 11.6 gm \u00d715 = 174 grams Overall Weight of Nuts, Total weight = 37.5 +76.5+174 Design and Analysis of Nut and Bolt Separating Machine 99 Int. J. of Analytical, Experimental and Finite Element Analysis www.rame.org.in Total weight of nut = 288 grams Total weight of Bolts (15 \u00d7 M6) + (15 \u00d7 M8) + (15 \u00d7 M10) bolts = 4 kg weight Frame weight; From cad by assign mild steel material density to frame = 7.8 kg. Overall Weight, Tray = 4kg round off. (2) Total weight of nut = 288 grams (3) Total weight of bolts= 4 kg weight (4) Frame = 7.8 kg (5) Overall Weight = A +B+C+D = 16 Kg Consider factor of safety and other factors = 16 + 4 kg extra wright 20 kg, Total weight with factor of safety = 20 kg Power = Force \u00d7 Velocity Here, assuming we are lifting the weight at a constant speed, the force applied by the motor is equal and opposite to the force applied by gravity, which is F=m g =20kg (10m/s2) = 200N Velocity V= 1m/60Sv =1m/60s Power P=F V =200N (1m/60s) =3.33watt From market we got below dc motor suitable for our project with 12V power. \u2022 Speed in rpm = 600 \u2022 Number of poles = 4 \u2022 Shaft Length = 30 mm \u2022 Motor Diameter = 28.5 mm \u2022 Gearbox Diameter = 37mm Now for calculating Working Frequency we use the formula, N = 120f /P Where, N= Rpm and P = No. of Poles. 600 = 120f/4 f = 20 Hz Hence our working frequency is 20 Hz. IV. FEA ANALYSIS Finite Element Analysis or FEA is the simulation of a physical phenomenon using a numerical mathematic technique referred to as the Finite Element Method, or FEM. This process is at the core of mechanical engineering, as well as a variety of other disciplines. It also is one of the key principles used in the development of simulation software. Engineers can use these FEM to reduce the number of physical prototypes and run virtual experiments to optimize their designs. Meshing is the process in which the continuous geometric space of an object is broken down into thousands or more of shapes to properly define the physical shape of the object. The more detailed a mesh is, the more accurate the 3D CAD model will be, allowing for high fidelity simulations. Details of meshing used \u2022 Element Size: 5.0 mm \u2022 Minimum Edge Length: 0.41406 mm 100 Int. J. of Analytical, Experimental and Finite Element Analysis \u2022 Nodes: 159258 \u2022 Elements: 73740 Figure 4. load apply Figure 5. Equivalent Stress TABLE1" + ] + }, + { + "image_filename": "designv8_17_0000087_5_secm-2014-0048_pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000087_5_secm-2014-0048_pdf-Figure3-1.png", + "caption": "Figure 3 Novel driveshaft concept with modified cross-section consisting of a profiled shell (1), axial reinforcements (2), and cylindrical shell (3).", + "texts": [ + " Although this design is highly flexible and permits the manufacturing of potentially cost-efficient semifinished products, the undulated laminate cross-section reduces the load bearing capacity of the driveshaft when compared to a shaft with cylindrical cross-section. Therefore, in a further work, this modular concept has been adapted to meet the requirements of high-performance applications. The newly developed driveshaft concept focuses on the provision of high-performance semifinished driveshaft bodies, which are equipped with metallic end fittings for concentrated load introduction (Figure 3, top). A basic geometry as depicted in Figure 3 is chosen. It features a profiled inner laminate, the so-called profiled shell (1), for load introduction, supplemented by axial reinforcements (2) and enclosed by a cylindrical laminate, or cylindrical shell (3). This cylindrical shell efficiently transmits loads over the span of the driveshaft, enhancing the performance of the component when compared with the previous design (Figure 2). This novel design recently was successfully patented [10]. In order to maintain the advantage of a continuous manufacturing process, the profile is linearly extruded to constitute the shaft body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001882_O201336447764690.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001882_O201336447764690.pdf-Figure1-1.png", + "caption": "Figure 1. Schematic diagram of the test rubber crawler vehicle (HC-300C).", + "texts": [ + " Texture of soil of the test field was SiL (silt loam) at water depth of 0.2 m. Soft ground layer thickness of the test field was 0.3 m and it has a very hard layer under the soft layer. Test device: the crawler vehicle (HC-300C)The test device used in the test was the commercial rubber crawler vehicle (model: HC-300C, Hanseo Precision Industry Co. Ltd.).The test rubber crawler vehicle is a walking carrier with a maximum load capacity of 2.94 kN. It has a chain that efficiently transmits the engine power to the crawler without power loss. Figure 1 shows the schematic diagram of the test rubber crawler vehicle.The crawler vehicle has a weight of 2.55 kN and an allowable load of 2.94 kN. The rubber crawler of the vehicle has an average height of 270 mm, width of 180 Table 1. Specification of the test rubber crawler vehicle Parameters Unit Value Weight of the test vehicle kN 2.55 Power of the test vehicle kW 5.1 Thickness of crawler mm 20 Ground contact length of crawler mm 740 Width of crawler mm 180 Lug height of crawler mm 15 Front height of crawler mm 303 Rear height of crawler mm 240 Front-end inclination of crawler \u00b0 45 Rear-end radius of crawler mm 120 Lug pitch of crawler mm 65 Ground contact area of crawlers m2 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004691_9133596_09133600.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004691_9133596_09133600.pdf-Figure1-1.png", + "caption": "Fig. 1 Magnetic flux density distribution of a typical SynRM FEA model", + "texts": [ + " For the inductances, the constant value cannot fully describe their characteristics. Inductances as a function of current or flux-current map models are mostly adopted and are more reliable to fit the magnetic characteristics of SynRMs well. Different aspects of parameter identification for SynRMs, adopted by various studies, will be discussed and reviewed in this section. FEA is the basic method that can obtain the parameters based on the motor structure during the design process. The magnetic flux density distribution of a typical SynRM FEA model is shown in Fig. 1 [22]. However, the application of the FEA based method has some limitations since the detailed design data can only be accessed by the motor designer and producer, which are protected trade secrets and hinder the industrial applications of FEA based method. The winding function is adopted in Refs. [6-7] to calculate the SynRMs inductances. The analytical model is a simpler way to compute the SynRMs parameters, which are then compared to the results obtained from the FEA in Ref. [8]. A combination of analytical equations and FEA is used for inductance identification for a machine model in terms of stator quantities in Ref" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004768_9668973_09764722.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004768_9668973_09764722.pdf-Figure13-1.png", + "caption": "FIGURE 13. Load condition magnetic flux density contour plot. (a) NO model. (b) Robust model.", + "texts": [ + " As the performances of the considered objectives of the robust model were improved compared with GO initial model, the applicability of the IMROA to the practical motor design optimization is verified. The effect of GO utilization and design optimization is tabulated in Table 2 and Table 5, respectively, and each method improves the performance of the IPMSM of the HEV application. To conduct the overall comparison, the analysis result comparison of the NO model and the robust model is listed in Table 6, and the waveform comparison of the 46604 VOLUME 10, 2022 NO and robust models are shown in Fig. 12. The magnetic flux density contour plot comparison is shown in Fig. 13. For the no-load analysis, the B-EMF THD was 18.63% reduced, cogging torque was 24.12% reduced, and iron loss was 28.30% reduced. The load condition results show 7.42% torque increase, 10.21% torque ripple reduction, 6.61% iron loss reduction, and 0.28% efficiency increase. The detailed comparison of the iron loss is conducted, and the results comparison is tabulated in Table 7. Especially for the stator teeth part, where the GO is applied, the iron loss was 41.45% and 30.34% reduced for the no-load and load condition" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004437_load.php_id_10052811-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004437_load.php_id_10052811-Figure5-1.png", + "caption": "Figure 5. (a) ESPRIT decomposition at 950 MHz. (b) ESPRIT fitting at 950 MHz.", + "texts": [], + "surrounding_texts": [ + "To illustrate the current decomposition using ESPRIT, we first simulate the current distribution along an 8-turn, right-handed helix antenna using NEC. Nominal design numbers are used for the axial mode helix. Fig. 1 shows the geometry of the helix antenna. The center frequency is 750 MHz. The circumference of the helix is one wavelength and the wire radius is 0.001 wavelength, both at the center frequency. The pitch angle is 13 degrees. An infinitely PEC ground plane is assumed in the simulation. Fig. 2 plots the simulated current distribution along the helix structure at 750 MHz. The above NEC simulated current are total current flowing along the helix structure. By decomposing the total current into various forward and backward traveling wave modes, we can better investigate each mode\u2019s contribution to the antenna performance and gain more physical insights into the antenna working principles. Therefore, next we model the current distribution on the helical antenna as a summation of N current modes, each with a distinct wave number \u03b2n, (or the corresponding wave velocity vn=2\u03c0f/\u03b2n), attenuation constant \u03b1n and a complex strength cn: J (\u03be) = \u2211 n cne\u2212j\u03b2n\u03be\u2212\u03b1n\u03be (1) where \u03be is the length parameter measured along the helix winding. To determine \u03b2, \u03b1 and c from the observed current, the ESPRIT algorithm is applied to the simulated current one frequency at a time. ESPRIT [9] was originally developed as a Direction-of-Arrival (DOA) estimation algorithm. It is based on the data model: y (\u03bei) = d\u2211 k=1 ake j\u03b2k\u03bei + n (\u03bei) i = 1, 2, . . . , N (2) where n is additive white noise. Given N > 2d + 1, ESPRIT can estimate d, ak and \u03b2k without error. Therefore, ESPRIT is an eigenspace parameter estimator that estimates a set of \u03b2n, \u03b1n in Eq. (1) based on the generalized singular value decomposition of the covariance matrix. Once they are estimated, cn can be found by the total least-squares criterion to arrive at the best fit of the total current J . In applying ESPRIT, we use the maximum model order N/2 to achieve a good fit to the data, where N (= 41) is the total number of data samples. Fig. 3(a) plots the extracted wave velocity of the four dominant modes. The vertical axis shows the phase velocity scale, which has been normalized to the speed of light in free space. The horizontal axis shows the distance along the helix winding (\u03be). The color in the plot indicates the strength of the each current mode versus distance, cne\u2212\u03b1n\u03be, displayed on a decibel scale. The change of the current mode strength along the helix winding is clearly seen. In Fig. 3(b), it is shown that the sum of the four dominant modes accurately reconstructs the original simulated current distribution. At this frequency, higher order modes are much weaker and can be neglected. In Fig. 3(a), T+ 0 and T+ 1 are the positive traveling current modes while T\u22120 and T\u22121 are the corresponding reflected current modes from the open end. It is seen that the magnitude of T+ 1 is almost constant along the helix and its phase velocity is smaller than that of the free space. This is the familiar slow wave on the helix and is typically considered the dominant radiation mode in the literature [8]. We also observe that at this frequency, T+ 0 exhibits a larger phase velocity but decays much faster than the T+ 1 mode. The phase velocities of the reflected waves T\u22120 and T\u22121 are equal and opposite of their corresponding positive traveling counterparts. However, their magnitudes are much weaker. The helix current distributions at the low frequency end of 550MHz and at the high frequency end of 950MHz are similarly simulated using NEC and decomposed using ESPRIT. Figs. 4(a) and 5(a) show respectively the decomposed current modes at 550 MHz and 950MHz. Figs. 4(b) and 5(b) show respectively the reconstruction of the currents at both frequencies. Both reconstructed currents agree well with the original simulation. At 550MHz, the dominant mode is the fast wave T+ 0 while the slow wave T+ 1 is only weakly excited. At 950MHz, the strength of T+ 1 is strong and slowly decaying. Consequently, the reflected mode T\u22121 persists over the entire length of the helix. We also notice the phase velocities of the current modes change as a function of frequency. To illustrate such frequency dependence, the phase velocities of different current modes are extracted from 500 MHz to 1000 MHz and plotted in Fig. 6. It is well known that, the phase velocity of the dominant wave propagation on the helix is such that the phase delay between turns fulfils the Hansen-Woodyard (increaseddirectivity) condition [2]. In Fig. 6, our extracted phase velocity of T+ 1 confirms this conclusion, as it shows good agreement with the phase velocity track required by the Hansen-Woodyard condition, which is plotted as the dashed line. For the T+ 0 mode, the phase velocity increases as the frequency goes up and can be greater than the speed of light in free space. This observation is somewhat contrary to that previous reported in the literature [2, 8], in which the speed of T+ 0 is assumed to be equal to the speed of light in free space. For the T+ 2 mode, which has previously been observed in measurements only when the circumference is larger than 1.4 wavelengths [2], can be observed at 850 MHz, where the circumference is equal to 1.1 wavelengths." + ] + }, + { + "image_filename": "designv8_17_0001163_O201110441050686.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001163_O201110441050686.pdf-Figure4-1.png", + "caption": "Fig. 4 Schematic of the lifting blade(unit: mm).", + "texts": [], + "surrounding_texts": [ + "9 The article was submitted for publication on 2010-11-16, reviewed on 2011-01-19, and approved for publication by editorial board of KSAM on 2011-01-31. The authors are Sung Il Kang, Graduate Student, Soo Nam Yoo, Professor, Chonnam National University, Gwangju, Korea, Yong Choi, Agricultural Researcher, National Academy of Agricultural Science, RDA, Suwon Korea, and Young Joo Kim, Senior Researcher, KSAM member, Environmental Materials & Components Center, Korea Institute of Industrial Technology, Jeonju, Korea. Corresponding author: S. N. Yoo, Professor, Department of Rural and Bio-systems Engineering and College of Agricultural and Life Sciences, Chonnam National University, Gwangju, 500-757, Korea; Tel: +82-62-530-2155; Fax: +82-62-530-2159; E-mail: .\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uac15\uc131\uc77c \uc720\uc218\ub0a8 \ucd5c \uc6a9 \uae40\uc601\uc8fc\nDevelopment of a Vine Crusher for Harvesting Sweet Potato\nS. I. Kang S. N. Yoo Y. Choi Y. J. Kim\nThis study was carried out to develop a vine crusher for harvesting sweet potato. The experimental two-row vine crusher attachable to agricultural tractor composed of vine crushing part with frail type vine crushing blades and vine lifting blades, power transmission part with chain and gear transmission mechanism, crushing height control part with two control wheels and manual levers, and implement frames, was designed and fabricated. And this vine crushing performance was also analyzed.\nFrom vine crushing tests, backward travel direction (i.e., rotational direction of the vine crushing blades) showed better vine crushing performance than forward travel direction. Crushing ratio of remained vine was increased, and length of remained vine and length of crushed vine were decreased as working speed was decreased and rotational speed of vine crushing blades was increased. At a working speed of 0.27 m/s and rotational speed of vine crushing blades of 800 rpm, crushing ratio of remained vine was 98%, length of remained vine was 104 mm, and length of crushed vine was 327 mm. But, when crushing vine on irregular ridges, vines and mulching vinyl were wound in the vine crushing part. Therefore, change of location of power transmission chain mechanism, and an automatic control device for controlling crushing height were needed.\nKeywords : Vine crusher, Sweet potato, Frail blade\n1. \uc11c \ub860\n\uc77c\ubc18\uc801\uc73c\ub85c \uad6d\ub0b4\uc758 \uace0\uad6c\ub9c8 \uc7ac\ubc30\ubc29\ubc95\uc740 \ubcd1\ud574\ucda9 \ubc29\uc9c0, \uc218\ud655 \ub7c9 \uc99d\uac00 \ub4f1\uc758 \uc7a5\uc810\uc73c\ub85c \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\uac00 \ub9ce\uc740 \ubc18\uba74, \uc678\uad6d\uc758\n\uacbd\uc6b0 \uc7ac\ubc30\uba74\uc801\uc774 \ub300\uaddc\ubaa8\ub85c \uac70\uc758 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\ub97c \ud558\uc9c0 \uc54a\uc73c \uba70, \ubcc4\ub3c4\uc758 \ub369\uad74\ucc98\ub9ac\uc791\uc5c5 \uc5c6\uc774 \uc218\ud655\uc791\uc5c5 \ud6c4 \ub369\uad74 \ubc0f \ud611\uc7a1\ubb3c\ub85c \ubd80\ud130 \uace0\uad6c\ub9c8\ub97c \uc120\ubcc4\ud558\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \uad6d\uc678\uc758 \uacbd\uc6b0 \uace0\uad6c\ub9c8 \ub369 \uad74\ucc98\ub9ac\uae30\uc5d0 \uad00\ud55c \uc5f0\uad6c\ub294 \uac70\uc758 \uc5c6\ub294 \uc2e4\uc815\uc774\ub2e4. \uace0\uad6c\ub9c8 \uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \uc904\uae30\uc808\ub2e8\uae30\uc640 \ube44\ub2d0\uc81c\uac70 \uae30\uc758 \uc774\uc6a9\uc73c\ub85c ha\ub2f9 \uc791\uc5c5\uc2dc\uac04\uc740 \uc57d 8\uc2dc\uac04\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4 (Namerikawa, 1989). \ub610\ud55c \uc904\uae30\uac77\uc5b4\uc62c\ub9bc\ubd09\uacfc \ud504\ub808\uc77c type \ud68c\n\uc804\ub0a0 \uc808\ub2e8\ubc29\uc2dd\uc744 \uc774\uc6a9\ud55c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 1\uc870 \uace0\uad6c\ub9c8 \uacbd\uc5fd\ucc98\ub9ac \uc7a5\uce58\ub97c \uc774\uc6a9\ud558\uc5ec \uc8fc\ud589\uc18d\ub3c4 0.35\uff5e0.46 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 28.6 m/s\uc5d0\uc11c \uacbd\uc5fd\ucc98\ub9ac\uc728 91.7\uff5e92%, \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774 38\uff5e43 cm\ub85c \uacbd\uc5fd\ucc98\ub9ac \uc815\ub3c4\uac00 \uc591\ud638 \ud558\uc600\ub2e4\uace0 \ubcf4\uace0\ud558\uc600\uc73c\uba70 (Park and Choi, 1995), \uae30\uc874 \ub369\uad74\uc808\ub2e8\uc7a5\uce58 \ub4a4\uc5d0 \ub514\uc2a4\ud06c\ud615 \ub369 \uad74\uc808\ub2e8\uc7a5\uce58\ub97c \ucd94\uac00\ub85c \ubd80\ucc29, \uac1c\ub7c9\ud558\uc5ec \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774\uac00 15.4 cm\ub85c \ub0ae\uc544\uc84c\uc74c\uc744 \ubcf4\uace0\ud558\uc600\ub2e4(Park and Choi, 1997). Ha(2006)\ub294 \ub3d9\ub825 \uacbd\uc6b4\uae30\ub97c \uc774\uc6a9, \uacbd\uc6b4\uae30 \ud6c4\ubc29\uc5d0 1\uc870\uc6a9 \ub369 \uad74\ucc98\ub9ac\uc7a5\uce58\ub97c \ubd80\ucc29\ud558\uc5ec 92%\uc758 \ub369\uad74\ucc98\ub9ac\uc728, 2.5 h/10a \uc791\uc5c5 \uc2dc\uac04\uc73c\ub85c \uad00\ud589 \uc778\ub825\uc758 \uc791\uc5c5\uc2dc\uac04\uc778 26 h/10a \ubcf4\ub2e4 \uc57d 1/10\ub85c \uc791\uc5c5\uc2dc\uac04\uc744 \uc808\uc57d\ud560 \uc218 \uc788\ub294 \uac83\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub9c8\ub298\n\ubc14\uc774\uc624\uc2dc\uc2a4\ud15c\uacf5\ud559 (J. of Biosystems Eng.) Vol. 36, No. 1, pp.9~14 (2011. 2) DOI:10.5307/JBE.2011.36.1.9\nOpen AccessResearch Article", + "\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 \uc904\uae30\uc808\ub2e8 \ubc0f \ube44\ub2d0\ud53c \ubcf5 \uc81c\uac70\uae30\ub97c \uc774\uc6a9\ud558\uc5ec \uc808\ub2e8\ub192\uc774 100 mm, \uc8fc\ud589\uc18d\ub3c4 0.53 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 67.86 m/s\uc5d0\uc11c \uc808\ub2e8\uc815\ub3c4 95.5%\ub85c \ubcf4\uace0\ud55c \ubc14 \uc788\ub2e4(Noh et al., 1999). \uc6b0\ub9ac\ub098\ub77c\uc758 \uace0\uad6c\ub9c8\uc758 \ucd1d \uc7ac\ubc30\uba74\uc801\uc740 2003\ub144\ub3c4 14,161 ha\uc5d0 \uc11c 2007\ub144 21,093 ha\ub85c \uafb8\uc900\ud55c \uc99d\uac00 \ucd94\uc138\uc5d0 \uc788\uc73c\ub098(MFAFF, 2009), \uc9c0\uae08\uae4c\uc9c0 \uae30\uc874\uc758 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc5d0 \ub300\ud55c \uc5f0\uad6c\ub294 1 \uc870\uc6a9\uc73c\ub85c \uc791\uc5c5\ub2a5\ub960\uc774 \ub5a8\uc5b4\uc9c0\uace0 \uc0ac\ub78c\uc774 \uc9c1\uc811 \ub530\ub77c\ub2e4\ub140\uc57c \ud558\ub294 \ub2e8\uc810\uc774 \uc788\uc73c\uba70 \ud604\uc7ac \ub18d\uac00\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8\uc218\ud655\uae30\uac00 \ubcf4\uae09 \ub418\uc5b4 \uc0ac\uc6a9\ub418\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8 \uc218 \ud655\uae30\uc5d0 \uc801\ud569\ud558\uace0 \uae30\uc874 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ubcf4\ub2e4 \ud6a8\uc728\uc801\uc778 2\uc870 \uc6a9 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ub97c \uac1c\ubc1c\ud558\uace0\uc790 \ud558\uc600\ub2e4.\n2. \uc7ac\ub8cc \ubc0f \ubc29\ubc95\n\uac00. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc124\uacc4\uff65\uc81c\uc791\n1) \uc8fc\uc694 \uad6c\uc870 \ubc0f \uc81c\uc6d0\n\uadf8\ub9bc 1\uc5d0\uc11c\uc640 \uac19\uc774 \ud2b8\ub799\ud130 PTO\ub97c \uc774\uc6a9\ud558\uc5ec \ub3d9\ub825\uc774 \uc804\ub2ec\ub418 \ub294 \ud2b8\ub799\ud130 \ubd80\ucc29\ud615\uc73c\ub85c 2\uc870\uc758 \ub450\ub451 \ub369\uad74 \ud30c\uc1c4\uac00 \uac00\ub2a5\ud558\ub3c4\ub85d \uc81c\uc791\ud558\uc600\ub2e4. \uc8fc\uc694\uad6c\uc870\ub294 \ub369\uad74 \ud30c\uc1c4\ub0a0\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\ub85c \uad6c\uc131\ub418\uc5b4 \uc788\ub294 \ub369\uad74 \ud30c\uc1c4\ubd80, \ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc744 \ub369\uad74 \ud30c\uc1c4\ubd80 \uad6c\ub3d9\ucd95\uc73c\ub85c \uc804\ub2ec\ud574\uc8fc\ub294 \uae30\uc5b4\ubc15\uc2a4, \uc2a4\ud504\ub85c\ucf13, \uccb4 \uc778, \uae30\uc5b4 \ub4f1\uc73c\ub85c \uad6c\uc131\ub41c \ub3d9\ub825 \uc804\ub2ec\ubd80, \ub369\uad74 \ud30c\uc1c4\uc791\uc5c5 \uc2dc \ub450\ub451\n\uc758 \ub192\uc774\uc5d0 \ub530\ub77c \ubbf8\ub95c\uc758 \ub192\ub0ae\uc774\ub97c \uc870\uc808\ud568\uc73c\ub85c\uc11c \ub369\uad74 \ud30c\uc1c4\ubd80 \uc758 \ub192\uc774\ub97c \uc870\uc808\ud560 \uc218 \uc788\ub294 \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80, \ud2b8\ub799\ud130 \ubd80\ucc29\uc7a5\uce58 \ubc0f \ud504\ub808\uc784 \ub4f1\uc73c\ub85c \uc8fc\uc694\ubd80\ub97c \uad6c\uc131 \uc124\uacc4\uff65\uc81c\uc791\ud558\uc600\ub2e4.\n2) \ub369\uad74 \ud30c\uc1c4\ubd80\n\ub369\uad74 \ud30c\uc1c4\ubd80\ub294 \uadf8\ub9bc 2\uc5d0\uc11c\ucc98\ub7fc \ud68c\uc804\ub0a0 \ud30c\uc1c4\uc2dd\uc73c\ub85c \ub369\uad74 \ud30c \uc1c4\ub0a0, \ud30c\uc1c4\ub0a0 \ubd80\ucc29 \ube0c\ub77c\ucf13, \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5 \ucd95, \ub369\uad74 \uac77\uc5b4\uc62c \ub9bc\ub0a0, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ubd80\ucc29 \uc6d0\ud310, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95, \uc9c0\uc9c0 \ubca0\uc5b4\ub9c1 \ub4f1 \uc73c\ub85c \uad6c\uc131 \uc81c\uc791\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0\uc740 \uadf8\ub9bc 3\uc5d0\uc11c\ucc98\ub7fc \uc81c\ucd08\n\uc6a9\uc73c\ub85c \ub9ce\uc774 \uc4f0\uc774\ub294 \uae38\uc774 120 mm, \ub450\uaed8 5 mm\uc758 \ud504\ub808\uc77c\ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \ud53c\uce58 70 mm \ub098\uc120\uc73c\ub85c \uc88c\uff65\uc6b0 \uac01\uac01 48\uac1c, \ucd1d 96\uac1c\ub97c \ubc30\uce58\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub0b4\uacbd 75 mm \uc911\uacf5\ucd95\uc778 \ud30c\uc1c4\ub0a0 \ucd95 \uc744 \ubca0\uc5b4\ub9c1\uc73c\ub85c \ub07c\uc6cc \ub9de\ucda4\ud558\uc5ec \uc88c, \uc6b0 \ud30c\uc1c4\ub0a0\ub4e4\uc744 \uac01\uac01 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ubd84\ub9ac \uad6c\ub3d9\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc740 \uadf8\ub9bc 4\uc5d0\uc11c\ucc98\ub7fc \ub05d\uc774 \ubfb0\uc871\ud55c \uae38\uc774 250 mm 6\uac1c \uc9c1\uc120\ub0a0\uc744 \uc6d0\uc8fc \ud53c\uce58\uac01 60\u00b0 \uac04\uaca9\uc73c\ub85c \ub192\uc774 \uc870\uc808\uc774 \uac00 \ub2a5\ud55c \ube0c\ub77c\ucf13\uc5d0 \ubd80\ucc29\ud558\uace0 \ube0c\ub77c\ucf13\uc744 \uc6d0\ud310\uc5d0 \uace0\uc815\ud558\uc600\ub2e4. \uc88c\uff65 \uc6b0\uff65\uc911\uc559 3\uacf3 6\uac1c\uc529 \ubaa8\ub450 18\uac1c\uc758 \ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \uccb4\uc778 \uc804 \ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5\ucd95 \uc548\uc758 \uc9c1\uacbd 35 mm \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\uc5ec \uac77\uc5b4\uc62c\ub9bc \uc791\uc6a9\uc744 \ud558\ub3c4\ub85d \ud558 \uc600\ub2e4.\n3) \ub3d9\ub825 \uc804\ub2ec\ubd80\n\ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc774 \uae30\uc5b4\ubc15\uc2a4\uc5d0\uc11c 2.5\ubc30\ub85c \uc99d \uc18d\ub418\uc5b4 \uad6c\ub3d9\ucd95 \uc88c\uff65\uc6b0\ub85c \ub098\ub258\uc5b4\uc838 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77 \uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\ub294 \uacfc\uc815\uc744 \uadf8\ub9bc 5\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \uad6c\ub3d9\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc6b0\uce21\uc758 \uad6c\ub3d9\ucd95\uc73c\ub85c", + "J. of Biosystems Eng. Vol. 36, No. 1.\n\ubd80\ud130 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95 \uc548\uc5d0 \uc788\ub294 \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uc9c1\uc811 \uad6c\ub3d9\uc2dc\ud0a8\ub2e4. \uadf8\ub9bc 6\uc740 \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\ucd95\uc758 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \uc2dc\uc758 \ub3d9\ub825 \uc804\ub2ec \ubc29\ubc95\uc744 \ub098\ud0c0\ub0b8 \uac83\uc774\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \uc804\uc9c4\ubc29 \ud5a5 \ud68c\uc804(\uc815\ud68c\uc804)\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c \ucf13\uacfc \uae30\uc5b4\uac00 \uc870\ud569\ub41c 2\uac1c\uc758 \ubc29\ud5a5\uc804\ud658 \ucd95\uacfc \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\n\ucd95\uc744 \uac70\uccd0 \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc \ud0a4\uace0, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \ud6c4\uc9c4\ubc29\ud5a5 \ud68c\uc804(\uc5ed\ud68c\uc804)\uc740 \uae30\n\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c\ucf13\uacfc \ud150\uc158 \uc2a4\ud504\ub85c\ucf13\uc744\n\uac70\uccd0 \uc911\uacf5\uc758 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc\ud0a4\ub3c4\ub85d \ud558 \uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \ud68c\uc804\uc18d\ub3c4\ube44\ub294 9 : 1\ub85c \uace0\ub791\uc5d0 \uc788\ub294 \ub3cc\uc5d0 \uc758\ud55c \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \uc190\uc0c1 \ubc0f \ub369\n\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc5d0 \uc758\ud55c \ube44\ub2d0\ud53c\ubcf5 \uc190\uc0c1 \ub4f1\uc758 \ubb38\uc81c\uc810\uc774 \ubc1c\uc0dd\ub420 \uc218\ub3c4 \uc788\uae30 \ub54c\ubb38\uc5d0 \ud68c\uc804\uc18d\ub3c4\uc758 \ucc28\uc774\uac00 \uc788\ub3c4\ub85d \ud558\uc600\ub2e4.\n4) \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80\n\ub369\uad74\ucc98\ub9ac \uc791\uc5c5 \uc2dc \ub369\uad74 \ud30c\uc1c4\ubd80\uc758 \ud30c\uc1c4\ub192\uc774\ub97c \uc81c\uc5b4\ud558\uba70, \uace0 \ub791\uc744 \uc774\ud0c8\ud558\uc9c0 \uc54a\uace0 \uc791\uc5c5\uae30\uc758 \uc8fc\ud589 \uc548\uc815\uc131\uc744 \ub192\uc774\uae30 \uc704\ud558\uc5ec \uc124\uce58\ud55c \ubbf8\ub95c\uc758 \uad6c\uc870\ub97c \uadf8\ub9bc 7\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ubbf8\ub95c\uc740 \uc9c1\uacbd 400 mm, \ud3ed 100 mm\ub85c \ub450\ub451\uc758 \ud615\uc0c1\uc5d0 \ub530\ub77c \ub369\uad74\ud30c\uc1c4\ubd80\uc758\n\ub192\ub0ae\uc774\ub97c \uc704\ucabd\uc758 \ub808\ubc84\ub97c \ud68c\uc804\uc2dc\ucf1c \uc870\uc808\ud560 \uc218 \uc788\ub3c4\ub85d \ud558\uc600\uc73c \uba70, \ub192\uc774 \uc870\uc808\uc740 300 mm\uae4c\uc9c0 \uac00\ub2a5\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ubbf8\ub95c\uc758 \uc124 \uce58 \uc704\uce58\ub294 \uc791\uc5c5\uae30 \ud6c4\ubc29 \uc791\uc5c5\uae30\ub97c \uc911\uc2ec\uc73c\ub85c \uc88c\uc6b0 2\uac1c, \ubbf8\ub95c \uc911 \uc2ec\uac04 \uac70\ub9ac\uac00 1400 mm\uac00 \ub418\ub3c4\ub85d \ubd80\ucc29\ud558\uc600\ub2e4.\n\ub098. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc131\ub2a5\uc2e4\ud5d8\n1) \uc2e4\ud5d8\ud3ec\uc7a5 \ubc0f \uc7ac\ub8cc\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc758 \uc2e4\ud5d8 \uc911 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc5d0 \ub530\ub978 \ud30c\n\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c\ub9c8\ub294 \uc728\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758 \ud3c9 \uade0 \ud568\uc218\uc728\uc740 83.0%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \uc2e4\ud5d8\ud3ec\uc7a5\uc758 \ud1a0\uc131\uc740 \uc0ac\uc591 \ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 30 cm, \ub450\ub451\ub192 \uc774 25 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4. \uc8fc\ud589\uc18d\ub3c4 \ubc0f \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c \ub9c8\ub294 \uc2e0\ud669\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758\ud3c9\uade0 \ud568\uc218\uc728\uc740 79.1%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \ud1a0\uc131\uc740 \uc0ac\uc9c8\ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 40 cm, \ub450\ub451\ub192\uc774 30 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4.\n2) \uc2e4\ud5d8\ub0b4\uc6a9 \ubc0f \ubc29\ubc95\n\uac00) \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8\n\ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ud30c\uc1c4\uc131\ub2a5\uc758 \ucc28\uc774\ub97c \uc870\uc0ac\ud558\uae30 \uc704\n\ud558\uc5ec \uc2e4\uc2dc\ud55c \uc2e4\ud5d8\uc73c\ub85c \ud2b8\ub799\ud130 \uc5d4\uc9c4 \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uc5d0 \ub530\ub77c \uc8fc \ud589\uc18d\ub3c4, PTO \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uac00 \uc5c6\ub3c4\ub85d \ud2b8\ub799\ud130 \uc5d4\uc9c4\uc18d\ub3c4\ub97c 2000 rpm\uc73c\ub85c \uace0\uc815\ud558\uace0, \uc8fc\ud589 \ubcc0\uc18d\ub2e8\uc218\ub97c Park and Choi (1995)\uac00 \ubcf4\uace0\ud55c \uc8fc\ud589\uc18d\ub3c4 0.35, 0.46 m/s\uc5d0\uc11c \uc8fc\ud589\uc18d\ub3c4\uac00 \ub0ae \uc744\uc218\ub85d \ub369\uad74 \ud30c\uc1c4\uc728\uc774 \ub192\uc558\uc73c\uba70, \ub18d\uac00\uc5d0\uc11c \uc8fc\ub85c \uc800\uc18d 1, 2\ub2e8 \uc744 \uc0ac\uc6a9\ud558\ub294 \uac83\uc744 \uace0\ub824\ud558\uc5ec \ubcf8 \uc2e4\ud5d8\ub3c4 \uc800\uc18d 1, 2\ub2e8\uc5d0 \ub9de\ucd94\uc5b4 \uc8fc\ud589\uc18d\ub3c4\ub97c \uac01\uac01 0.27, 0.37 m/s\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \ubcc0\uacbd\uc740 \uadf8\ub9bc 6\uc5d0\uc11c" + ] + }, + { + "image_filename": "designv8_17_0001810_2478_bipcm-2023-0030-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001810_2478_bipcm-2023-0030-Figure9-1.png", + "caption": "Fig. 9 \u2212 von Mises distribution along GH line for all the study cases.", + "texts": [ + " For the D case, the Uz maximum value, at the right end, from FEA simulation is: UzMAX(FEA results) = 5.74 mm. In the D case, the value for UzMAX, at the right end was also calculated by use of analytical formulas recommended by (Young et al., 2011): UzMAX(Analytic) = 5.709 mm. The variation of Uz along AB line is presented in Fig. 6. It presents, by comparison the variation of Uz for all the study cases. b) Stresses The distribution of stresses was investigated along: - CD line for von Mises , Fig. 7 - GH line for x in Fig. 8 and von Mises in Fig. 9. The stress distributions were also presented in each and every figure, by comparison, for all study cases. 3. Discussions and Conclusions - a) For the D case: both UzMAX (FEA results) and UzMAX (Analytic) are influenced by some approximations. Each of the two, compared with the other one considered as reference differs with less than \u00b10.55%. In this case analytical formulas and FEA results gave results in good agreement. - b) The compared study of the Uz variation along AB line, Fig.6, found that the maximum deformation, Uz is possible using geometries in cases D and E", + " Under this value the number of Degrees of Freedom, DOFs, for the FEA models increases exponentially making the practical processing with the available hardware extremely difficult. - e) The analysis of compared results in Fig.8 noticed that the x distribution along GH line presents nonlinearity with almost sinusoidal shape in the vicinity of the interface surface between layers. These areas extend approximate 0.4 mm each side of interface surface. For the rest the variation is practically linear. - f) The compared von Mises distribution along GH line, Fig. 9, noticed that in all studied cases the curves presents a sudden change of shape, an inflexion point, for the z value corresponding the interface surface between layers, where materials discontinuity take place. This could suggest \u2013in addition to what was mentioned at paragraph (d) above - the necessity to used extreme finer meshes in FEA models in this area. - g) Although the optimized layer thickness defined for the case E did not produced outstanding optimized parameters in the other compared investigations presented above, Fig. 9 shows that in case E the von Mises value on the interface it is by comparison with the other cases the minimum possible: 0 MPa. Definitely, for many practical usual applications the use of analytical formulas is more convenient and rapid. The present study had found good concordance between the results found with analytical formulas and those determined by use of FEA. For any new complex shaped bimetals or for any effort to optimize the classical shape of bimetals it is important to study and understand their elastic behaviour, by comparison in various situations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure9-1.png", + "caption": "Fig. 9 (a) Maximum and minimum deformation; Deformation under static load condition I (b) Antero-lateral (c) Postero-lateral", + "texts": [], + "surrounding_texts": [ + "The distribution of von-Mises stress, maximum deflection, number of cycles before failure, and safety factor of the modified polycentric prosthetic knee are investigated in this fatigue analysis. The results of von-Mises stress distribution during cyclic strength simulation are shown in Figs. 11 and 12. For both loading conditions, the von-Mises stress developed at the front and back joint bars is 18 to 23 MPa as shown in Figs. 11a, 11b, 12a, and 12b. The maximum stresses of 91 and 71 MPa are developed in the knee joint unit lower for load conditions I and II respectively as depicted in Figs. 11c and 12c. Therefore, it can be predicted that the modified polycentric prosthetic knee prosthesis employed in this research can withstand cyclic stress considering the high fatigue strength of AA7075-T6. The cyclic strength test results for the modified knee prosthesis are shown in terms of total deformation in Fig. 13. A maximum deformation has been observed at the point of load application which is 0.38 mm as shown in Fig. 13a. The alignment coupling unit of the knee prosthesis experiences the maximum deformation of 0.18 mm as depicted in Figs. 13b and 13c, suggesting the least amount of displacement. A deformation less than 2.5 mm during fatigue testing suggests that this modified prosthetic knee has sufficient strain-bearing ability to meet the structural norms, as recommended by the ISO 10328:2016 standard. The results of cyclic strength simulations for commonly failing components are summarized in Table 4. It is observed that the maximum developed stress is sufficiently below the fatigue strength of AA7075 T6 and the deformation produced is extremely minimal. There is a significant increase in fatigue life (no. of cycles) of most of the knee components. These values indicate that the modified polycentric knee prosthesis qualifies the requirements of ISO 10328:2016 standard." + ] + }, + { + "image_filename": "designv8_17_0003220_20JIYE_G1103158C.pdf-Figure3.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003220_20JIYE_G1103158C.pdf-Figure3.6-1.png", + "caption": "Figure 3.6 3D image of Raman line scan spectrum along [110] direction", + "texts": [ + " The penetration depth of the laser radiation is approximately 200 nm into silicon in my study [12]. Figure 3.8 shows a representative Raman spectrum. The signal\u2013to-noise ratio were measured in order to determine the optimum laser power for the Raman measurements. In particular, the laser power was reduced by using filters to a level that heating of the Si (in principle visible as line shift and broadening) was below the detection limit. The suitable laser power density was set to be around 1 mW/\u03bcm2. In Figure 3.6, the drop in the intensity of Raman signal indicates the locations of the Si/copper TSV interfaces. Close to the interface, the sum of the two principle stresses in Si can be deducted directly from the Raman frequency shift with equation(2.4). 34 The stress in the TSV structures may result from both thermal and athermal contributions. However, the athermal contributions are typically process dependent, which are unknown for the TSV specimen in my study. To account for the athermal contributions, we take an empirical approach by assuming a reference temperature at which the TSV samples are stress free" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000653_f_version_1670406718-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000653_f_version_1670406718-Figure3-1.png", + "caption": "Figure 3. The structures and dimensions (mm) of the M-EBG.", + "texts": [ + " The parameters of the inductive (Lin) and capacitive (C) parts are described by Equations (8)\u2013(10) [37]. Lin = 0.2h [ ln ( 2h r ) \u2212 0.75 ] (8) C = \u03b50 \u03b5r w2 h (9) w0 = 1\u221a LC (10) In Equations (8)\u2013(10), \u03b50 and \u03b5r denote permittivity parameters, while h and r denote the via\u2019s height and radius, respectively. Further, w and w0 are the EBG\u2019s width and the resonant angular frequency, respectively. The EBG structure could be observed as a mushroom-swollen surface, studied in [36], and was enhanced to produce M-EBG (see Figure 2). Figure 3 gives the structure and dimensions of the M-EBG. The M-EBG is portable, simple, and capable of generating decoupling effect in any common UWB array antennas when positioned in the feed line vicinity of the UWB micro-strip antenna. This section presents an analysis of the significance of the decoupling structure in reducing the MC in MIMO UWB antennas. The antenna design with and without the inclusion of the decoupling structure was discussed. Figure 4 presents the layout of the UWB MIMO antenna created with HFSSv15 software" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003142_0245-024-10117-6.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003142_0245-024-10117-6.pdf-Figure5-1.png", + "caption": "Fig. 5 Representation of the computed optimal deformation and contour plot distribution of a \u03bb\u03021 ( \u22121(x) ) , b \u03bb\u03022 ( \u22121(x) ) and c \u03bb\u03023 ( \u22121(x) ) for the example with initial configuration depicted in Fig. 2. The translucid geometry represents the initial configuration. d Agreement between the target configuration (grey colour) and the deformed solid subjected to the optimal growth tensor (red) (Color figure online)", + "texts": [ + " 3, correspondingwith the optimal solutions that yield the closest growth-driven configurations to the target configurations denoted as shape morphing configurations 1 and 2. In addition, Fig. 4 depicts the evolution of the cost function for the case of the shape morphing configuration 1. The interior-point algorithm has been used as the optimization method. With regard to the circular cross-section beam in Fig. 2b, with target configuration given in Eq. (5.16), the final growth-driven configuration is displayed in Fig. 5, along with the contour plot distribution of the three design variables {\u03bb\u03021, \u03bb\u03022, \u03bb\u03023}. The tight agreement with respect to the target configuration initially prescribed in Eq. (5.16) is shown in Fig. 5d. Next, we consider the two undeformed configurations given in Fig. 6a and the beam with circular cross-section in Fig. 6b. For both cases, the eigenvectors {v1, v2, v3} are defined as v1 = [ cos \u03b8, sin \u03b8, 0 ]T v2 = [\u2212 sin \u03b8, cos \u03b8, 0 ]T v3 = [ 0, 0, 1 ]T . In both cases, the boundary conditions are such that the displacements vanish in X3 and r = R1 (for Fig. 6a) and r = R (for Fig. 6b) in the three directions {E1, E2, E3} of the configuration {X1, X2, X3}. Two target configurations, target = d ( 0), have been prescribed: (i) Shape morphing configuration 4: initial geometry given in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000514_9-9292_8_10_1090_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000514_9-9292_8_10_1090_pdf-Figure1-1.png", + "caption": "Figure 1. (a) The multiple antenna system for multiple-input multiple-output (MIMO) application in a smartphone. (b) Geometric configuration of unit slot antenna. (c) Inverted-L feeding strip.", + "texts": [ + " The MIMO performance measures, such as envelope correlation coefficient (ECC), mean effective gain (MEG), and MIMO channel capacity, and customer\u2019s hand effect are studied extensively for the proposed multiple antenna system. The detailed design procedure of the six open-end slot antenna system is discussed in this section. The main circuit board or Printed circuit board (PCB) supporting the proposed multiple antenna system consists of FR-4 substrate with relative permittivity of 4.4 and loss tangent of 0.02. The dimensions of PCB are 136 \u00d7 68 \u00d7 1.6 mm3, as shown in Figure 1. To swiftly accommodate (2G/3G/4G) antennas, space reservation is made. The dimensions of each open-end slot antenna are 8.5 \u00d7 3 mm2 fed by microstrip with tuning stub, also referred to as inverted-L microstrip feed. The tuning stub is helpful to effectively couple electromagnetic energy to the antenna. The detailed analysis of the proposed multiple antenna system or multiple antenna system is carried out with commercial electromagnetic software, namely Computer Simulation Technology (CST) Microwave Studio" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure2-6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure2-6-1.png", + "caption": "Figure 2-6: Schematic diagram of serially connected links.", + "texts": [ + "2 A n gu lar acceleration For a revolute joint i + 1, differentiating \u00b0Wi+i yields \u00b0W'-+1 - \u00b0 Wi + \u00b0 Wi x\u00b0 Ri+i(9i+iz i+1) + \u00b0 Ri+1(0i+i z i+1) 23 \u00b0{\u00b0Wi+1} =l {\u00b0Wi} -p {\u00b0Wi} x i i T + ^ m ^ + i ) + f R i+1(0i-m *+ i) i+1{ \u00b0 * W = i+1 i\u00b0Wi} + i+1 {\u00b0FF,} x (0i+1z,+1) + 0i+xzi+i For a prism atic joint i + 1, from \u00b0Wi+1 =\u00b0 Wh \u00b0Wi+1 Wi l {\u00b0lF i+1} ='\u25a0 R\u00b0 \u00b0Wi {0TFi} i+1{\u00b0TFf+1} = i+1 & i{\u00b0Wi} 2 .3 .4 E x a m p les o f R ecu rsio n o f K in em atic V ariab les The relative expressions for position, velocity, and acceleration of each link can be obtained recursively using the results derived above in a specific example (Fig. 2-6): Let zi = *Zi. For link 1 (revolute joint), \u00b0Pi = [ 0 0 l0 ]r , \u00b0W0 = 0, \u00b0JFo = 0, \u00b0Vj = 0, and % = 0 \u00b0W l=0 W0 +\u00b0 R \\0 iz a) i f l V j = 0lZl = *1 * 1 1{\u00b0Vi}=0 H % } = 0 24 For link 2 (revolute joint), 2 {\u00b0w 2} =2 i21{ \u00b0 w 1} + e2z2 = 2 r 1\u0302 0 + e2z2 2{0W2} \u20142 1 { 0 ^ } + 2 #1 1 ( 0 ^ } X ( 0 2Z 2 ) + 6*2Z2 = 2 /21((9iZx) -f2 jR ^^Z x) x ($2z2) + 02z2 2{0Fz} =2 Vi} + 1 {0W i} X1 p 2] = 2 ^ [ ( t f i Z i ) X 1 P 2] 2{ M 2} = 2 + 1 { \u00b0 m } x 1 P 2 + 1 {0TFX} x P { \u00b0 m } X 1 P 2]] = 2 # [ ( * ! Zj) x 1 P 2 + (^Z x) X P x Z l) X 1 P J] For link 3 (prism atic joint), 3{\u00b0W3} = 3 R 2 2{\u00b0W2} 3 {0 ^ 3} = 3 R2 2 {0 ^ 2} 3{0y3} =3 R*[*{\u00b0V2} + 2 |0 W72J" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure9-1.png", + "caption": "Figure 9. Pressure contour along the wind turbine surfaces.", + "texts": [ + " Considering turbulence models of RANS widely used in engineering cases, we compared models of torque and power calculation in Table 4. It is evident that SST made the closest prediction to the rated output condition among the RANS models. In Figure 8, the analysis revealed that the upcoming wind was blocked by a generator and then separated from the surfaces, which increased the inflow blockage. This caused a low velocity and increased pressure in the blade passage. A vortex near the tip edge, which flowed downstream with regular motion, was observed. From the results of the velocity and pressure contour (Figure 9), it is observed that the surface pressure increased as the blade radius increased except for the backside of the blade tip and swept area due to the supporting rods where the velocity increased. It was critical to understand the motion of flow inside the blade passage. Figure 10 reveals the velocity vector around the cylindrical surfaces at a constant radius. When the radius was smaller than that of the generator, the reverse flow appeared in the blade passage. In addition, the vortex influenced flow directions, which caused low velocities near the pressure side of the blade" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000372_9312710_09425552.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000372_9312710_09425552.pdf-Figure2-1.png", + "caption": "FIGURE 2. Configurations of two different stator modules. (a) U-core. (b) E-core.", + "texts": [ + ",12/10U-core and 6/10 E-core DSAFFSPMmachines are built andmeasured in order to verify the FEA results and the above analysis based on the flux modulation. II. TOPOLOGY AND MODULATION PRINCIPLE The basic structure of DSAFFSPM machines with concentrated tooth-wound windings and U-core/E-core stator modules are presented in Fig. 1(a) and Fig. 1(b), respectively. They contain three parts, namely dual stators and one rotor sandwiched in between. The stator is constituted by the several identical modules, which can be seen in Fig. 2. Stator-side PMs are all circumferentially magnetized in the opposite direction, and circumferentially aligned between adjacent modules. It can be observed that the rotor has salient poles and the rotor-PMs are removed. The stator-side PMs provide a stationary PM MMF, which is modulated by the uneven permeance distribution of the rotatory salient poles. Then, the stationary MMF can be modulated into an air-gap magnetic field composed of abundant harmonics based on the flux modulation principle. To investigate the field flux modulation effect of DSAFFSPM machines, the MMF-permeance model considering the uneven air-gap permeance distribution due to the rotor slotting is utilized", + "3(b) illustrates the air-gap permeance model accounting for rotor iron pieces, respectively. Since the MMF-permeance model has been proven to be valid, the no-load air-gap flux density can be deduced by multiplying Fpm(\u03b8s) and Pr (\u03b8s, t) as [25] B(\u03b8s, t) = Fpm(\u03b8s)\u00d7 Pr (\u03b8s, t) (1) whereFpm(\u03b8s) is the PMMMF,Pr (\u03b8s, t) is the specific air-gap permeance function. The first term in (1) is static while the latter one is rotary under the same stator reference frame, \u03b8s is the angle along the stator circumference. The stationary PM MMF can be derived according to Fig. 2(a) in Fourier series as (2): FPM (\u03b8s) = \u221e\u2211 i=1,3,5 Fi sin(ipm\u03b8s) Fi = 8F \u03c0 i sin(ipm \u03b2s 2 ) sin(ipm \u03b8s 2 ) F = Brhpm \u00b5r\u00b50 (2) where i is the order of Fourier Series, Fi denotes the Fourier coefficient of FPM (\u03b8s) waveform related to i,F is the amplitude of PM MMF, \u03b2s refers to the width of PMs, \u03b8s indicates the sum of the width of PM and stator tooth, Br , hpm, \u00b5r are the remanence, the height and the relative permeability of PMs respectively. The air-gap permeance function Pr (\u03b8s, t) is a relatively complex function about the shape of stator and rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.2-1.png", + "caption": "Figure B.2: Change in vertical tail's angle of attack due to yaw rate (26)", + "texts": [ + " angle of attack ................................. 94 Figure A.9: Vertical/horizontal tail\u2019s pitching moment coefficient vs. angle of attack .......... 95 Figure A.10: Stators\u2019 drag coefficient vs. angle of attack....................................................... 96 Figure A.11: Stators\u2019 rolling moment coefficient vs. angle of attack ..................................... 96 Figure B.1: Side force at vertical tail in rolling flight (26) ....................................................... 99 Figure B.2: Change in vertical tail's angle of attack due to yaw rate (26) ............................ 100 Figure B.3: Change in wing's angle of attack in rolling flight (26) ........................................ 101 Figure B.4: Change in wind speed due to yaw rate (26) ...................................................... 105 x LIST OF TABLES Table 3.1: Flight conditions for altitude-hold mode and climbing mode .............................. 34 Table 4.1: Longitudinal derivatives in stability axes system ", + " The force increments generated by these two elements are equal in magnitude but opposite in direction; hence, they will cancel each other out. As a result, the total side force due to a roll rate perturbation is zero, i.e. side force derivative due to roll rate is zero: ( ) 0p b In a yaw rate perturbation, the vertical tail\u2019s angle of attack in body axes system is: ( ) tan VT e b rl U \u03b1 \u03b1\u2032 \u2032\u2248 = (B.17) This change in vertical tail\u2019s angle of attack generates a lift and drag at the vertical tail as shown in Figure B.2. It can also be seen that a positive yaw rate perturbation will generate a positive side force. The resultant lift and drag generated by the vertical tail are resolved into body Y axis to give a rise of VTY to side force: 101 ( ) cos sin cos sin VT VT VT VT VT VT VT L e D e L e e b Y L D rl C q S C q S C q S U\u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u2032 \u2032= + \u2032 \u2032 \u2032 \u2032= + \u2248 (B.18) Hence, the side force derivative due to yaw rate is: ( ) ( )VT VT r L eb e b l Y C q S m U\u03b1 = (B.19) The following part is to derive the relationship of wing \u2013 body rolling moment and yawing moment due to roll rate perturbation p and yaw rate perturbation r in stability axes system because the moment contribution from the wing is easier to derive in stability axes system", + "54) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) 2 0 2 2 2 2 c s c 2 s 2 c s c s e e ee e e e ee e s A e yb s D L e D L e e L e b bD e D L e e L D e n U c y dy C C C C C p C C C C C r \u03b1 \u03b1 \u03b1 \u03b1 \u03c1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 = \u00d7 \u2212 + \u2212 \u2212 \u2212 + + \u2212 + \u222b (B.55) The notation c e\u03b1 and s e\u03b1 stand for cos e\u03b1 and sin e\u03b1 respectively. It should be reminded that these moments are only contributed by the wing \u2013 body. The contribution of the tails to the rolling moment due to roll rate perturbation is insignificant because their span is relatively small. However, their contribution to yawing moment due to yaw rate perturbation needs to be considered, and it can be seen in Figure B.2 that most of this contribution is from the vertical tail due to the side force generated in yawing motion. Yawing moment from vertical tail due to yaw rate perturbation is: ( ) 2 VT VT VT A VT VT L e e b rl n Y l C q S U\u03b1 = \u2212 = \u2212 (B.56) Then the total yawing moment is now changed to: ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) 2 2 0 2 2 2 2 c s c 2 s 2 c s c s VT e e ee e e e ee e s VT bA L e e yb s e b D L e D L e e L e b bD e D L e e L D e l n C q S r U c y dy U C C C C C p C C C C C r \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03c1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 = \u2212 + \u00d7 \u2212 + \u2212 \u2212 \u2212 + + \u2212 + \u222b (B" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000677_ejjia_4_3_4_196__pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000677_ejjia_4_3_4_196__pdf-Figure10-1.png", + "caption": "Fig. 10. Photographs of tested WFSM", + "texts": [], + "surrounding_texts": [ + "V0I f \u2217 = 2Rf I f \u22172 + R(Id \u22172 + Iq \u22172) + \u03c9\u03c4\u2217 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (17)\nThe left-hand side of (17) expresses the input from the DC power source. The first term on the right side expresses the copper loss of the field coils. The second and third terms are the copper loss of armature windings and the motor output, respectively. 5.2 Constraint of Field Current Reference The field current reference I f \u2217 and the current Ii being fed to inverter bridge at the active state have to satisfy the following equation to avoid the freewheeling diode shoot through state.\n2I f \u2217 > Ii \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (18)\n5.3 Constraint of Operable Duty Ratio The ZSI is controlled by the duty ratios of the three states. The control reference parameters have to be chosen such that the sum of the duty ratios at operating points does not exceed 1. The following equation is obtained by rearranging (11).\nm\u2217 = DA \u2217 + DZ min \u2217 \u2264 1 \u2212 DS \u2217 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (19)\nWhere DZ min \u2217 is the minimum duty ratio reference of the active zero state. m\u2217 is the sum of DA \u2217 and DZ min\n\u2217 and expressed by another equation below for the reason that the duty ratio equals the area ratio as shown in Fig. 8.\nm\u2217 = 2\u03c0\n3 \u221a 3 DA \u2217 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (20)\nRearranging (19) and (20), the following equation is derived.\nDA \u2217 \u2264 3\n\u221a 3\n2\u03c0 (1 \u2212 DS \u2217) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (21)\nThus, the ZSI has to be controlled such that the duty ratios DA \u2217 and DS \u2217 satisfy (21).\n200 IEEJ Journal IA, Vol.4, No.3, 2015", + "5.4 Control Parameter Search at Given Motor Operating Points The flowchart of control reference parameters search at given operating points of the drive system of the WFSM integrated with the ZSI is shown in Fig. 9. The field current I f \u2217, the armature current Id \u2217, Iq\n\u2217 and the capacitor voltage Vc\u2217 as the control reference parameters satisfying the constraint conditions of (17), (18) and (21) is searched at given torque reference and motor speed condition. They are eventually stored in a look-up table.\n6. Experimental Results\nExperimental verifications of the proposed control algorithm are conducted using a test WFSM and a test ZSI as shown in Figs. 10 and 11. The measured WFSM parameters and the capacitance C of impedance-network used in the ZSI appear in Table 1. The dimensions of the main machine part of the WFSM are the outer diameter of 100 mm and the stack length of 26.6 mm, respectively. The rated torque of the test\nTable 1. Measured parameters of WFSM and ZSI\nWFSM is approximately 1.5 Nm under ambient air cooling. The rated speed of the motor is 3,000 r/min when the conventional three-phase inverter with the rated DC bus voltage of 283 V is used. In experiments, the DC voltage source is set to 60 V constant in order to check voltage boost-up capability. Since the capacitor voltage vc is fluctuated owing to the use of a small capacitance of 9.9 \u03bcF, the maximum capacitor voltage limit is set to 130 V considering the withstand voltage of the switching devices in the inverter (600 V). This results in\n201 IEEJ Journal IA, Vol.4, No.3, 2015", + "the maximum voltage across the inverter leg vi at the active state is 200 V as determined by (7). Thus, the rated motor speed is reduced by 2,000 r/min. The test WFSM is in torque control mode under speed control by the dynamo side.\nFigure 12 demonstrates the experimental result at 0.94 Nm under 250 r/min. The command values of d-axis current Id\n\u2217 and q-axis current Iq\n\u2217 are set to 0 A and 6.8 A, respectively. The field current command I f\n\u2217 is set to 8.0 A. In this experiment, the maximum capacitor voltage limit is intentionally changed from 130 V to 100 V to verify the effectiveness of the proposed capacitor voltage control. It is found that all currents converge to their references. The actual capacitor voltages Vc1 and Vc2 are boosted more than 100 V, resulting in the voltage across the inverter leg vi being more than 140 V. The detected capacitor voltage Vc det in the controller follows the maximum capacitor voltage limit Vc limit. Thus, it is concluded that the proposed capacitor voltage control works well. The two traces from the bottom in the figure show the three-phase current waveforms for the enlarged time scale during 1 to 1.03 s and 3 to 3.03 s before and after the maximum capacitor voltage limit change, respectively. As apparent from the waveforms, the three-phase currents are controlled pure sinusoidal. The torque ripple, which can be\nobserved after starting the capacitor voltage control, would be due to low-frequency capacitor voltage ripple.\nFigure 13 demonstrates the experimental result at an approximately rated torque of 1.34 Nm under 1,000 r/min. The command values of d-axis current Id \u2217, q-axis current Iq \u2217 and field current I f \u2217 are \u22125.2 A, 9.0 A and 10.0 A, respectively. From the figure, it can be seen that all currents follow their references.\nFigure 14 shows the experimental result at 0.63 Nm under 2,000 r/min. The command values of d-axis current Id\n\u2217, qaxis current Iq \u2217 and field current I f \u2217 are \u22123.5 A, 6.0 A and 5.0 A, respectively. From the figure, it can be found that all currents follow their references. Consequently, it is concluded that the proposed control algorithm is effective for operating the proposed drive system.\nHere, Table 2 summarizes the comparisons of the motor efficiency and the losses of the tested motor at each operating point corresponding to Figs. 13 and 14 when the proposed drive system and a non-integrated drive system are used. The non-integrated drive system is composed of separated circuits such as a DC chopper for field coil excitation and a threephase inverter for feeding current to the armature windings. Pmin is measured by a Yokogawa Digital Power Meter WT\n202 IEEJ Journal IA, Vol.4, No.3, 2015" + ] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure25-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure25-1.png", + "caption": "Figure 25. Velocity contours planes.", + "texts": [ + " The radial velocity in the back clearance is higher than in the front one because of its smaller size (Fig. 23(b)). A negative radial velocity region is visible at the front rotor inlet where the air intake occurs. Fig. 24 shows the colored path lines on rotor and permanent magnets showing a circulation. It\u2019s the result of low velocities in the relevant inlet recess around the inner radius and vice versa higher velocities in the relevant outlet recess around the outer radius. The velocity magnitude contours have been obtained on the radial surfaces shown in Fig. 25 (at angles 34\u25e6, 0\u25e6 and +34\u25e6). The region of the running clearance close to the rotor shows higher velocities than the one close to the stator (see Fig. 26). It is therefore desirable to have a low running clearance as it increases the turbulent mixing. However, an excessively low running clearance could reduce the flow rate due to the excessive flow resistance. For given values of the permanent magnet depth and the rotational speed an increase of the clearance to a certain value results in the rise of the mass flow rate; however, further widening the clearance would not result in more increase of mass flow rate" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003279__17_17.20190714__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003279__17_17.20190714__pdf-Figure8-1.png", + "caption": "Fig. 8. Exploded view of the integrated antenna module.", + "texts": [ + " In the practical application of the phased array antenna, there is a temperature environment control system. The minimum temperature of the environment is \u221220 \u00b0C. The simulation is based on the real application scenario. The peak chip temperature is around 68\u00b0C. Fig. 7(b) depicts the transient thermal analysis result. When the module works for five minutes, the maximum temperature can be achieved in roughly 300 seconds after module starts up, fully validating the effectiveness of heat design. Then the temperature slowly drops to \u221220\u00b0C after the module shuts down. Fig. 8 shows the exploded view of the integrated antenna module and Integrated design has been realized. Fig. 9 shows the photograph of the integrated antenna module. To demonstrate the functionality of the proposed phased array antenna, a prototyping system is manufactured and tested. As the photograph shown, the devised systems are measured in a microwave anechoic chamber. The required configuration commands are sent to the systems through a remote-controlled laptop. Simulation and optimization of the slotted waveguide antenna has been carried out by means of the HFSS software, and testing of the voltage standing wave ratio of the phased array antenna has been measured with the Agilent vector network analyzer" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000833_r.asee.org_19542.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000833_r.asee.org_19542.pdf-Figure2-1.png", + "caption": "Figure 2. Enhanced Propulsion Demonstrator Design", + "texts": [ + " The barrel (acrylic cylinder) of the new system is one inch longer than the original one making the process last longer. In addition, the rear end (injector) of the apparatus was modified making it easier to P age 23.528.3 connect to the oxygen hose. This change also allows for quick refueling. The original four posts connecting both ends of the device was changed to two standoffs, one on each side making it easier to remove without disassembling the whole unit. The new device also includes pressure and temperature sensors, mounted on the top and bottom, respectively. Figure 2 shows sketches of the design. The following paragraphs describe the major system components and their functionality. Ignition Circuit: The ignition circuit is shown in Figure 3. A Single Pole Double Throw (SPDT) Relay is used to energize the system via the Data Acquisition board DAQ (NI USB-6211). The Op-Amp voltage follower isolates the DAQ from the rest of the circuit and provides the required current to operate the transistor 4 . The DAQ closes the relay and activates the ignition using the transistor as an amplifier" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure22-1.png", + "caption": "Fig. 22. Characteristic forms of flange-mounted single-stage gear reducer (PGR solution) [9].", + "texts": [ + " 10 and 15) presents the most universal gear reducer. This type of reducer is adapted for all positions and ways of mounting, but at the same time, it is the most expensive due to extensive machine processing and the largest consumption of materials. Therefore, their intensive development could not be expected further, but they will be produced by an only small number of manufacturers to satisfy operating requirements. Gear reducers with vertical shaft arrangement footmounted (Fig. 21), flange-mounted (Fig. 22) and foot and flange-mounted (Fig. 12) are probably the most basic positions of mounting that will be required in future due to relatively low production costs, suitable form and low cost of materials. Other forms are less required and they are produced by smaller manufacturers who want to cover the market segment which is not covered by large manufacturers. Further intensive development of shaft-mounted single-stage gear reducers can be also expected. Their installation doesn\u2019t require flanges at the output shaft which provide cheaper construction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001339_ad.aspx_paperID_1114-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001339_ad.aspx_paperID_1114-Figure3-1.png", + "caption": "Figure 3. (a) 2-D motor configuration and magneto-motive force, and (b) effective air gap width due to slotting effect", + "texts": [ + " In addition to the assumptions of material linearity and the collinearity of flux and field densities, it is also necessary to make three additional assumptions for the 2D magnetic circuit model: 1) The motor is operated in the linear range of the B-H curve of the magnetic material. 2) The air-gap reluctance of the slotted stator structure is approximated by the effective air-gap length with Carter\u2019s coefficient [13]. 3) The flux flows straight across the air gaps between the stator and rotor, ignoring the fringing flux to simplify the analysis. Therefore, the 3D motor structure in Figure 1 can be approximated by a 2D configuration in Figure 3(a) to facilitate the magnetic circuit analysis. By neglecting the flux leakage and armature reaction between the stator and rotor, the MMF from stator windings Fs is simply a square function of magnitude NtI; while the MMF from rotor magnets Fr is a square function of magnet Hclm, where Hc and lm are the coercivity and length of magnet, respectively. The overall MMF distribution is a linear combination of the MMFs of stator windings and rotor magnets ( , ) ( , ) ( , )s rF x s F x s F x s= + (5) Optimal Design and Control of a Torque Motor for Machine Tools Copyright \u00a9 2009 SciRes JEMAA 224 where s denotes the rotor shift, which is defined as the relative angle between the rotor and stator. The magnetic flux density in the air gap is described as 0 ( , ) ( , )g F x sB x s \u00b5 \u03b4 = (6) where \u00b50 is the permeability of air, \u03b4 (x,s) is the effective air gap as a function of slot opening and slot pitch, as shown in Figure 3(b). By the use of the detailed expression of effective air gap [13], the field coenergy in the air gap is expressed as 2 2 0 0 ( , )( ) ( , ) R c g F x sW s FB dA L dx x s \u03c0 \u00b5 \u03b4 = =\u222b \u222b (7) where L is the axial length of the motor. The torque produced in the motor is then obtained by calculating the variation of magnetic coenergy in the air gap with respect to the rotor shift: ( ) ( ) c I constant W sT s R s = \u2202 = \u2202 (8) It may be possible to express the coenergy and torque in analytical forms. However, the numerical analysis is used instead to get torque distribution from such a complicated magnetic model" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure8-1.png", + "caption": "Figure 8: Patch circulaire \u00e0 fentes, (a) sch\u00e9ma du design, (b) alimentation [7].", + "texts": [ + " N\u00e9anmoins, la double polarisation est obtenue en excitant l\u2019antenne dans deux directions orthogonales par le biais des deux diff\u00e9rents ports. \u2022 Alimentation quasi-optique (r\u00e9flexion) Les antennes r\u00e9seau excit\u00e9es par r\u00e9flexion (r\u00e9seaux r\u00e9flecteurs), compos\u00e9es d'une source primaire qui illumine une surface r\u00e9flectrice contenant un r\u00e9seau de cellules d\u00e9phaseuses, permettant un fonctionnement dans deux bandes de fr\u00e9quences distinctes sont de types patchs ou dip\u00f4les, avec des motifs originaux permettant d\u2019obtenir deux bandes de fr\u00e9quences, comme pr\u00e9sent\u00e9 ci-apr\u00e8s : 7) Patch circulaire \u00e0 fentes avec lignes de d\u00e9phasages [7] (Figure 8) Page 18 sur 182 8) Dip\u00f4le en forme de \u00ab I \u00bb dans un anneau [8] (Figure 9) 9) R\u00e9seau r\u00e9flecteur utilisant la cellule Phoenix [9] (Figure 10) Ces trois antennes poss\u00e8dent des ratios de fr\u00e9quences faibles, 2,15:1 pour la premi\u00e8re, et 1,5:1 pour les deux autres, en bandes X et K ou X et Ku. De plus, leurs bandes de fr\u00e9quences Page 19 sur 182 sont extr\u00eamements faibles (< 1%), ce qui est un probl\u00e8me caract\u00e9risque des r\u00e9seaux r\u00e9flecteurs. Les deux premiers designs ne permettent qu\u2019une polarisation lin\u00e9aire, tandis que le dernier, utilisant la cellule Phoenix, peut r\u00e9aliser aussi bien une double polarisation lin\u00e9aire que circulaire" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure1-1.png", + "caption": "Figure 1: Structural model of magnetic planetary gears", + "texts": [ + " In order to improve the feasibility of the application of alternating magnetic planetary gears, Maxwell simulation software is used in this article to analyze and study the characteristics of magnetic planetary gears. Design a magnetic planetary gear using neodymium iron boron material as the magnetic block, which has extremely high magnetic energy product and coercive force, making it difficult to demagnetize and ensuring stable torque transmission performance. The support material is stainless steel, which has magnetic properties similar to vacuum and almost no magnetic conductivity. The designed magnetic planetary gear is shown in Figure 1 below. The main application of magnetic planetary gear transmission is the principle of magnetic field theory, which states that the same type repels each other and the opposite type attracts each other. When the driving wheel and the driven wheel are matched, the magnetic poles of the magnetic teeth are opposite, and the adjacent magnetic poles of the same gear are different. The magnetic field generated during operation generates gravity, which changes in a sine function. During operation, the transmission torque is provided by the tangential component force in the direction of the coupling force" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-3-1.png", + "caption": "Figure 2-3. Illustration des r\u00e9gions du champ \u00e9lectromagn\u00e9tique d'une antenne", + "texts": [ + ".................................................. 20 Figure 1-15. Exemple de r\u00e9seau corporel sans fil ou WBAN....................................................... 23 Figure 1-16. Evolution de l'ergonomie et de l'esth\u00e9tisme des t\u00e9l\u00e9phones portables..................... 26 Figure 2-1. Sch\u00e9ma de principe d'un syst\u00e8me de communication radio....................................... 30 Figure 2-2. Illustration de la bande passante \u00e0 -10 dB d'une antenne........................................... 34 Figure 2-3. Illustration des r\u00e9gions du champ \u00e9lectromagn\u00e9tique d'une antenne......................... 35 Figure 2-4. Exemples de diagramme de rayonnement d'antenne ................................................. 37 Figure 2-5. Illustration de l'angle d'ouverture............................................................................... 37 Figure 2-6. Illustration de la conservation de l'\u00e9nergie dans une antenne .................................... 39 Figure 2-7. Composantes orthogonales du champ \u00e9lectrique ", + " ( ) 2 1% 100 res f f BP en f \u2212= \u22c5 (2.7) Un grand nombre de param\u00e8tres \u00e9lectriques que nous venons de d\u00e9finir sont valables pour d'autres composants d'une chaine de transmission radiofr\u00e9quence. Mais, ce qui diff\u00e9rencie r\u00e9ellement les antennes sont leur capacit\u00e9 \u00e0 rayonner qui se d\u00e9finit au moyen de plusieurs param\u00e8tres que nous allons pr\u00e9senter dans cette partie. 35 2.3.1 Les r\u00e9gions du champ \u00e9lectromagn\u00e9tique D'apr\u00e8s [2.1], l'espace entourant une antenne peut \u00eatre divis\u00e9 en trois r\u00e9gions distinctes comme le montre la Figure 2-3. La structure du champ \u00e9lectromagn\u00e9tique est diff\u00e9rente en fonction des r\u00e9gions. Bien qu'il n'y ait pas de changement brutal de la configuration des champs aux fronti\u00e8res de ces r\u00e9gions, il existe de r\u00e9elles diff\u00e9rences entre elles. Ces r\u00e9gions sont d\u00e9limit\u00e9es par des sph\u00e8res de rayon R1 et R2 qui sont d\u00e9crites par les expressions (2.8) et (2.9) respectivement, et o\u00f9 a correspond \u00e0 la plus grande longueur de l'antenne et \u03bb est la longueur d'onde. La r\u00e9gion entourant directement l'antenne est appel\u00e9e la r\u00e9gion de champ proche r\u00e9actif" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure9-1.png", + "caption": "Fig. 9, Model used for Case (b), \u201cRigid Spring\u201d virtual part, axial", + "texts": [ + " The stiffness of the spring is the same as the stiffness of the modeled portion of the bar. Namely, \ud835\udc58\ud835\udc40\ud835\udc43 = \ud835\udc34\ud835\udc38 \ud835\udc3f\ud835\udc40\ud835\udc43 . The natural frequency of the SDOF system is then given by = \u221a \ud835\udc58\ud835\udc40\ud835\udc43 \ud835\udc5a\ud835\udc49\ud835\udc43+\ud835\udc5a\ud835\udc40\ud835\udc43/3 . Using the data for the present problem, the frequency value estimated by this expression is = 8795 Hz which a reasonable approximation to the value reported in table I. Case (b) Rigid Spring Virtual Part, Axial Vibration: As a next model, a \u201cRigid Spring\u201d virtual part is representing the latter \ud835\udc3f\ud835\udc49\ud835\udc43 = 50 \ud835\udc5a\ud835\udc5a of the 150 \ud835\udc5a\ud835\udc5a part as shown in figure 9 below. The axial stiffness of this spring is calculated based on half the length of the virtual part, ie 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 = 25 \ud835\udc5a\ud835\udc5a . The rationale behind using 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 has to do with the fact that the mass of the virtual part is represented by a lumped value at the centroidal location. The exact location of the handler point should be taken into account when the stiffness of VP is calculated. In our analysis, because the lumped mass is placed at the centroid, the stiffness is calculated as shown below \ud835\udc58\ud835\udc49\ud835\udc43 = \ud835\udc34\ud835\udc38 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000194_6_36_3_36_3_104__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000194_6_36_3_36_3_104__pdf-Figure3-1.png", + "caption": "Fig. 3 Configuration of a 70MW class model SCG.", + "texts": [], + "surrounding_texts": [ + "10\nTable 1 Overview of the worldwide research and development of superconducting generators.\nThe figures attached to each item correspond to the number in Table 1.\n106 \u4f4e \u6e29 \u5de5 \u5b66", + "11\n(HTC: Helium Transfer Coupling) \u304c \u3042 \u308a\u8ef8 \u4e2d\u5fc3\u5b54 \u3092\u901a \u3057 \u3066\u56de\u8ee2\u5b50\u5185\u90e8\u3078\u6db2\u4f53 \u30d8 \u30ea\u30a6\u30e0 \u306e\u4f9b\u7d66 \u3068\u30ac \u30b9\u30d8 \u30ea\u30a6\u30e0 \u306e \u56de\u53ce\u304c\u884c\u308f\u308c \u308b. \u56fa\u5b9a\u5b50 \u306b\u3042 \u308b\u96fb\u6a5f \u5b50\u5dfb\u7dda \u306f, \u975e\u78c1\u6027 \u306e\u30c6\u30a3\u30fc\u30b9\u3067\u652f\u6301 \u3055\u308c\u7a7a \u9699\u96fb\u6a5f \u5b50\u5dfb\u7dda \u547c \u3070\u308c \u308b. \u78c1\u6c17\n\u30b7\u30fc\u30eb \u30c9\u306f, \u5916\u90e8\u3078 \u306e\u78c1\u675f \u306e\u6f0f \u308c \u3092\u9632 \u3050\u305f \u3081, \u7a7a\u9699\u96fb \u6a5f\u5b50\u5dfb\u7dda\u3092\u8cab\u901a \u3057\u305f\u78c1 \u675f \u3092\u6574\u5f62 \u3057\u5468 \u65b9\u5411 \u306b\u5c0e \u304d\u9589\u78c1\u8def \u3092\u5f62\u6210\u3059\u308b.\n3.3 \u6280\u8853\u958b\u767a\u8ab2 \u984c\u306e\u62bd \u51fa \u30d5\u30a7\u30fc\u30baI\u306e1988\u5e74 \u304b \u3089\u306e\u672c \u683c \u7684\u7814\u7a76 \u958b\u767a \u306e \u958b\u59cb\n\u306b\u5148\u7acb\u3063\u30661986, 1987\u5e74 \u306b, \u30d5 \u30a3\u30fc \u30b8 \u30d3 \u30ea\u30c6 \u30a3\u8abf\u67fb\u7814 \u7a76\u304c\u884c\u308f\u308c \u305f. \u8abf \u67fb\u7814 \u7a76 \u3067\u306f, \u305d\u308c \u307e \u3067\u306e\u5185\u5916 \u306e\u958b\u767a \u52d5\u5411\u3092\u8e0f\u307e\u3048, \u8d85 \u96fb \u5c0e\u6a5f \u306e\u5b9f\u7528\u5316 \u306b\u5fc5\u8981 \u3068\u306a \u308b\u6280\u8853 \u958b\n\u767a\u8ab2\u984c\u3092\u62bd \u51fa \u3057, \u30d5\u30a7\u30fc \u30baI\u3067 \u6280\u8853\u78ba \u7acb\u3059 \u3079 \u304d\u6280\u8853 \u958b \u767a\u5185\u5bb9\u304c\u6c7a\u5b9a \u3055\u308c \u305f. \u4e3b\u8981 \u306a\u6280\u8853 \u958b\u767a \u8ab2\u984c \u3068\u5404 \u30ed\u30fc \u30bf \u306e\u5206\u62c5\u3092Table 2\u306b \u793a\u3059.\n\u90fd\u5e02\u8fd1\u90ca \u7528 \u306f\u96fb \u5727\u7dad \u6301 \u52b9 \u679c \u3092\u9ad8 \u3081 \u308b\u5fc5 \u8981 \u304b \u3089\u540c\u671f \u30ea\u30a2\u30af\u30bf\u30f3\u30b9\u304c\u5c0f \u3055\u3044\u767a\u96fb\u6a5f \u304c\u671b \u307e\u308c, \u307e\u305f, \u9060 \u9694\u5730\n\u7528\u306f\u754c\u78c1\u96fb\u6d41 \u3092\u8d85 \u901f \u3067\u5909\u5316 \u3055\u305b \u3066\u96fb \u529b\u7cfb\u7d71 \u306e\u5b89 \u5b9a\u5ea6\u5411 \u4e0a\u52b9\u679c\u3092\u5927 \u304d \u304f\u3057\u305f\u767a \u96fb\u6a5f \u304c\u671b \u307e\u308c \u305f. \u305d\u306e \u305f\u3081, \u4f4e \u901f\u5fdc\u578b\u30ed\u30fc\u30bf \u3092\u90fd \u5e02\u8fd1 \u90ca\u7528 \u3068 \u3057\u3066, \u8d85 \u901f\u5fdc \u578b \u30ed\u30fc \u30bf\u3092\n\u9060 \u9694\u5730 \u7528 \u3068 \u3057\u3066 \u958b\u767a\u3059 \u308b\u3053 \u3068\u306b\u306a \u3063\u305f.\nTable 2 Major components to be developed on each rotor of a 70MW class model SCG.\n\u30ed\u30fc \u30bf\u958b\u767a \u3067 \u306f, \u754c\u78c1 \u5dfb\u7dda \u7528\u8d85 \u96fb\u5c0e \u5c0e\u4f53, \u591a\u91cd \u5186\u7b52\n\u56de\u8ee2\u5b50 \u3092\u69cb\u6210 \u3059 \u308b\u5e38\u6e29 \u30fb\u4f4e \u6e29 \u30c0\u30f3\u30d1, \u71b1\u53ce \u7e2e\u6a5f\u69cb, HTC \u306a \u3069, \u8d85 \u96fb\u5c0e\u6a5f \u3092\u69cb\u6210 \u3059 \u308b\u8981 \u7d20\u6bce \u306b\u6570\u7a2e \u985e \u306e\u9078\u629e\u80a2 \u3084\n\u89e3 \u6c7a\u3059 \u3079 \u304d\u6280 \u8853\u8ab2 \u984c \u304c\u62bd \u51fa \u3055\u308c \u305f. \u3055 \u3089\u306b, \u30ed\u30fc\u30bf \u3068\n\u3057\u3066\u5171 \u901a \u306b\u6280 \u8853\u78ba \u7acb\u3059 \u3079 \u304d\u591a\u91cd \u5186\u7b52\u56de \u8ee2\u5b50 \u306e\u8a08 \u6e2c\u6280\u8853,\n\u9577 \u671f\u4fe1 \u983c\u6027, \u51b7\u5374 \u6280\u8853 \u306a \u3069\u306e\u8ab2\u984c \u3082\u62bd \u51fa \u3055\u308c\u305f. \u3053\u308c\n\u3089\u591a\u5c90 \u306b \u308f\u305f \u308b\u8d85 \u96fb\u5c0e \u7279\u6709 \u306e\u5148\u7aef \u7684 \u306a\u6280\u8853\u8ab2 \u984c \u3092\u4f4e\u901f\n\u5fdc \u578bA, B\u6a5f, \u8d85 \u901f\u5fdc \u578bC\u6a5f \u306e3\u30ed \u30fc \u30bf\u3067\u5206 \u62c5 \u3057\u305f. \u307e\u305f, \u30b9\u30c6 \u30fc \u30bf\u958b\u767a \u3067\u306f\u7a7a \u9699\u96fb\u6a5f \u5b50\u5dfb \u7dda \u306a \u3069\u306e\u8ab2 \u984c\u304c\n\u62bd \u51fa \u3055\u308c \u305f\u304c, \u5404 \u30ed\u30fc \u30bf\u306b\u5171\u901a \u3057\u305f\u8ab2 \u984c \u3067\u3042 \u308a, 1\u30b9 \u30c6\u30fc \u30bf\u3067 \u958b\u767a \u3092\u884c \u3046\u3053 \u3068\u306b \u3057\u305f. 3\u30ed \u30fc \u30bf\u306f, \u305d\u308c\u305e \u308c \u65e5\u7acb\u88fd\u4f5c \u6240, \u4e09\u83f1\u96fb\u6a5f, \u6771\u829d \u304c\u5206\u62c5 \u3057, 1\u30b9 \u30c6\u30fc \u30bf \u306f \u65e5\u7acb\u88fd \u4f5c\u6240\u304c \u5206\u62c5 \u3057\u305f \u3053 \u3068\u304b \u3089, \u76f8 \u4e92 \u306b\u88dc\u5b8c \u3057\u6280\u8853 \u306e\u6c34\u5e73 \u5c55 \u958b\u3092\u306f \u304b \u308a\u52b9 \u7387\u7684 \u306b\u958b\u767a \u3092\u9032 \u3081\u305f.\n3.4 70MW\u7d1a \u30e2\u30c7 \u30eb\u6a5f\u4ed5 \u69d86) 70MW\u7d1a \u30e2\u30c7 \u30eb\u6a5f \u306f, 200MW\u7d1a \u30d1\u30a4 \u30ed \u30c3 \u30c8\u6a5f \u3068\u540c\n\u5f84 \u7e2e\u9577 \u578b\u304a \u3088\u3073 \u30d0 \u30e9\u30f3\u30b9\u7e2e \u5c0f\u578b \u3067\u69cb\u6210 \u3055\u308c \u308b\u3053 \u3068\u304b \u3089, \u30d1\u30a4 \u30ed \u30c3 \u30c8\u6a5f \u306e\u6982 \u5ff5\u4ed5 \u69d8 \u3092\u691c\u8a0e \u3057\u305f \u4e0a\u3067\u4ed5 \u69d8 \u3092\u6c7a\u5b9a \u3057\n\u305f. \u3053\u308c \u3089\u306b \u3088 \u308a, \u5404\u90e8 \u306e\u96fb\u78c1 \u529b, \u6a5f \u68b0\u5fdc \u529b, \u71b1 \u5fdc\u529b\n\u306a \u3069\u304c\u660e \u3089\u304b \u3068\u306a \u308a, \u305d \u306e\u5f8c \u306b\u958b\u767a\u3059 \u3079 \u304d\u5404\u8981 \u7d20\u6280\u8853\n\u958b\u767a \u304a \u3088\u3073\u5404\u90e8 \u5206\u30e2 \u30c7\u30eb \u306e\u958b\u767a \u898f\u6a21 \u3092\u6c7a \u5b9a \u3057\u305f.\n70MW\u7d1a \u30e2 \u30c7 \u30eb\u6a5f \u306e\u4ed5\u69d8 \u3092Table 3\u306b \u793a\u3059. \u306a\u304a,\n\u8d85 \u901f\u5fdcC\u6a5f \u306f\u9060 \u9694\u5730 \u7528\u3067\u52b1 \u78c1\u65b9 \u5f0f\u304c\u8d85 \u901f\u5fdc \u3068\u306a\u3063\u3066\u3044\n\u308b\u3053 \u3068\u304b \u3089, \u7cfb \u7d71\u64fe \u4e71\u6642 \u306e\u754c\u78c1 \u96fb\u6d41 \u306e\u5fdc\u7b54 \u304c\u65e9 \u3044. \u3053\n\u308c \u306b\u5bfe \u5fdc\u3059 \u308b\u305f \u3081, \u8d85 \u96fb\u5c0e \u754c\u78c1\u5dfb \u7dda \u306e\u5b89 \u5b9a\u6027 \u3092\u7279\u306b\u8003 \u616e \u3057\u305f\u8a2d\u8a08 \u306b \u3057\u3066\u3044 \u308b\u305f \u3081, \u540c \u4e00\u4f53\u683c \u3067\u4f4e \u901f\u5fdc\u578bA, B\u6a5f \u3088 \u308a\u51fa\u529b \u304c\u5c0f \u3055 \u304f\u306a\u3063\u3066 \u3044 \u308b2).\nTable 3 Specifications of a 70MW class model SCG.\nVol. 36 No. 3 (2001) 107", + "12\n3.5 \u8981\u7d20 \u30fb\u90e8 \u5206\u30e2 \u30c7\u30eb \u306b \u3088\u308b\u7814\u7a76 \u958b\u767a \u8d85 \u96fb \u5c0e\u767a\u96fb\u6a5f \u306e\u958b\u767a \u30d5 \u30ed\u30fc \u3092Fig. 4\u306b \u793a \u3059. \u8981 \u7d20\n\u6280\u8853 \u958b\u767a \u6bb5\u968e \u3067\u306f, \u30d5\u30a3\u30fc \u30b8 \u30d3 \u30ea\u30c6 \u30a3\u8abf \u67fb\u7814 \u7a76 \u3067\u62bd \u51fa \u3055\u308c\u305f \u6280\u8853\u8ab2 \u984c \u3092\u7740\u5b9f \u306b\u958b\u767a \u3057, \u90e8\u5206\u30e2 \u30c7 \u30eb\u3067\u78ba\u5b9f \u306b\n\u691c \u8a3c \u3057\u3066\u6280\u8853 \u84c4\u7a4d \u3092\u306f \u304b \u3063\u305f. \u307e\u305f, \u90e8 \u5206\u30e2 \u30c7\u30eb \u958b\u767a \u6bb5 \u968e\u3067 \u306f, \u524d \u6bb5 \u3067\u884c \u3063\u305f\u8981\u7d20 \u6280\u8853 \u306b\u7acb \u3061\u8fd4 \u308a\u691c\u8a3c\u7d50 \u679c \u306e\u30c1 \u30a7 \u30c3\u30af&\u30ec \u30d3\u30e5\u30fc \u3092\u884c\u3044, \u6b21 \u306e \u30b9\u30c6 \u30c3\u30d7\u306b\u958b\u767a \u3092\n\u9032 \u3081\u3066 \u3044 \u3063\u305f. \u3053\u306e\u6bb5\u968e \u3067 \u306f\u5206\u62c5 \u3057\u305f\u6280 \u8853 \u958b\u767a \u8ab2\u984c \u304c\n\u591a \u304f, \u76db \u3093 \u306b\u7d44 \u5408 \u54e1\u9593 \u3067\u6280\u8853 \u306e\u6c34 \u5e73\u5c55 \u958b \u3092\u884c \u3063\u305f.\nTable 4 Factory and verification-test schedule of a 70MW class model SCG.\n3.6 70MW\u7d1a \u30e2 \u30c7\u30eb\u6a5f \u306e\u88fd \u4f5c \u3068\u8a66 \u9a136) \u30d5 \u30a7\u30fc\u30baI\u306e \u958b \u59cb (1988\u5e74) \u304b \u3089\u7d42 \u4e86 (1999\u5e74) \u307e\u3067\u306e 12\u5e74 \u9593\u306e\u958b\u767a \u5de5\u7a0b \u3092Table 4\u306b \u793a \u3059. 1988\u5e74 \u304b \u30891989\n\u5e74 \u307e\u3067 \u30e2\u30c7 \u30eb\u6a5f \u57fa\u672c \u8a2d\u8a08 \u3068\u8981 \u7d20\u6280\u8853 \u958b\u767a \u3092, 1990\u5e74 \u304b \u30891992\u5e74 \u9803 \u307e\u3067\u5404\u7a2e\u30e2 \u30c7\u30eb \u304a \u3088\u3073\u90e8\u5206 \u30e2\u30c7 \u30eb\u306b\u3088\u308b\n\u958b\u767a \u3092\u884c \u3063\u305f. \u305d \u306e\u5f8c, 70MW\u7d1a \u30e2\u30c7\u30eb\u6a5f \u7528 \u30ed\u30fc\u30bf\u3068\n\u3057\u3066\u4f4e\u901f \u5fdc\u578bA\u6a5fB\u6a5f, \u8d85\u901f\u5fdc \u578bC\u6a5f \u304a \u3088\u3073\u30e2\u30c7\u30eb\n\u6a5f \u7528\u30b9 \u30c6\u30fc \u30bf\u306e\u88fd \u4f5c, \u8a66 \u9a13 \u3092\u5b9f\u65bd \u3057\u305f. \u3053\u306e\u5f8c, \u95a2\u897f \u96fb \u529b\u5927 \u962a\u767a\u96fb \u6240\u69cb \u5185\u306e\u8a66 \u9a13\u30bb \u30f3\u30bf\u30fc\u3067\u30e2 \u30c7\u30eb\u6a5f\u7528\u30b9\u30c6 \u30fc \u30bf \u3068\u5404 \u30ed\u30fc \u30bf\u3092\u9806 \u306b\u7d44 \u307f\u5408 \u308f\u305b \u3066 , 1996\u5e74 \u5ea6\u672b\u304b\u3089 \u9806\u6b21, \u5b9f \u8a3c\u8a66 \u9a13 \u3092\u884c \u3063\u305f.\n\u5b9f \u8a3c\u8a66\u9a13 \u3067 \u306f\u8fd4\u9084 \u8ca0\u8377 (M-G) \u65b9 \u5f0f \u3092\u63a1 \u7528 \u3057\u3066, \u3042\n\u3089\u304b \u3058\u3081\u8ad6\u8b70 \u3057\u305f\u8a66 \u9a13\u6cd5 (\u57fa\u672c \u8a66\u9a13, \u8d85\u96fb \u5c0e\u56fa\u6709\u8a66\u9a13,\n\u8ca0\u8377 \u8a66\u9a13, \u904e\u9177 \u8a66\u9a13) \u306b\u57fa\u3065 \u304d\u5fb9\u5e95 \u3057\u3066\u6280\u8853 \u306e\u691c\u8a3c\u3092 \u884c \u3063\u305f. \u5404 \u30ed\u30fc \u30bf \u3068\u30b9\u30c6 \u30fc \u30bf\u306f\u5b9f\u8a3c\u8a66 \u9a13\u7d42 \u4e86\u5f8c, \u9010\u6b21, \u5de5\u5834 \u306b\u304a \u3044 \u3066\u89e3 \u4f53\u8abf \u67fb \u3092\u5b9f\u65bd \u3057\u305f. \u307e\u305f, \u5b9f\u8a3c\u8a66\u9a13\u3068\n\u5e73\u884c \u3057\u3066\u8a66 \u9a13\u7d50 \u679c \u306b\u57fa\u3065 \u304d\u8a2d\u8a08 \u30fb\u89e3\u6790 \u6280\u8853 \u306e\u9ad8\u7cbe\u5ea6\u5316 \u3068\u30d1 \u30a4 \u30ed \u30c3 \u30c8\u6a5f \u306e \u57fa\u672c\u8a2d \u8a08 \u3092\u5b9f\u65bd \u3057\u305f.\n4. \u6280 \u8853 \u958b\u767a \u6210 \u679c\n4.1 \u8d85\u96fb \u5c0e\u754c\u78c1 \u5dfb\u7dda6)\n\u8d85 \u96fb \u5c0e \u6a5f \u306b\u7528 \u3044 \u3089\u308c \u305f \u8d85 \u96fb \u5c0e \u5c0e \u4f53 \u306e \u958b\u767a \u6210\u679c\u3092 Table 5\u306b \u793a \u3059. \u4f4e \u901f\u5fdc \u578bA\u6a5f \u3067\u306f\u5b89 \u5b9a\u5316\u6750 \u306e\u4e00\u90e8\u306b\n\u9ad8\u7d14 \u5ea6 \u30a2\u30eb \u30df\u30cb \u30a6\u30e0 \u3092\u7528 \u3044\u305f \u9ad8\u5b89\u5b9a\u578b \u5c0e\u4f53 \u3092, B\u6a5f \u3067 \u306f \u9ad8\u96fb\u6d41\u5bc6 \u5ea6 \u3068\u9ad8\u525b \u6027 \u3092\u7279\u5fb4 \u3068\u3059 \u308b\u9ad8\u96fb \u6d41\u5bc6\u5ea6\u578b\u5c0e\u4f53\n\u3092, \u8d85 \u901f\u5fdc\u578bC\u6a5f \u3067\u306f\u52b1\u78c1 \u5909\u5316 \u6642 \u306e\u4ea4\u6d41\u640d \u5931 \u3092\u4f4e\u6e1b\u3057 \u305f\u4f4e \u640d\u5931\u578b \u5c0e\u4f53 \u3092\u958b\u767a \u3057\u3066\u8d85 \u96fb\u5c0e\u6a5f \u306b\u63a1\u7528 \u3057\u305f.\n\u306a\u304a, \u8d85\u96fb \u5c0e\u5c0e \u4f53 \u306f, Super-GM\u5185 \u3067\u7d20\u7dda \u30ec\u30d9\u30eb\u306b \u9061 \u3063\u3066\u30c6 \u30b9 \u30c8\u30b3\u30fc \u30c9\u3092\u4f5c\u6210 \u3057, \u307e\u305f, \u96fb\u529b \u4e2d\u592e\u7814\u7a76\u6240\n108 \u4f4e \u6e29 \u5de5 \u5b66" + ] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure35-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure35-1.png", + "caption": "Figure 35 P-POD Mk. IV Top Panel FEA Results", + "texts": [ + " The ribs are now considerably thinner, but wide enough to accommodate a non-structural 4-40 screw for harness routing if needed. The Page 52 FEA was conducted, while hand calculations were used to determine the strength of the fastener through-holes. The finite element model used a symmetric constraint in order to reduce solving time, which solves a mirror image of the model across the centerline. All other edges were fixed. The Top Panel was subjected to the Y-axis load case, applied at the panel rails. The resulting Top Panel stress from FEA is shown below in Figure 35. Stress was very low throughout the entire part, the max being at the venting holes. This is expected as a hole in a panel will always produce stress concentration. Fortunately, the stress was already so low that even the max stress exhibited by the part yielded an M.S. of 4.6. The 3 4-40 through-holes at the \u2013Z end of the part exhibited a lower M.S. of 2.8, which is still very high. The Top Panel was not expected to be the limiting factor in considering P-POD strength, even after mass reduction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000943_4005_1_rschewe_1.pdf-Figure1.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000943_4005_1_rschewe_1.pdf-Figure1.7-1.png", + "caption": "Figure 1.7: Schematic of the intravenous respiratory assist catheter, consisting of a pulsating balloon surrounding by a bundle of hollow fibers. Federspiel et al. ASAIO J 42:M435-42, 1996.", + "texts": [ + "5: (a) Picture of the IVOX in its unfurled state and (b) cross-sectional schematic of the IVOX, showing the gas flow path through the device. Kallis et al. Eur J of Cardiothorac Surg 7(4): 206-210, 1993. .......................................................................... 11\u00a0 Figure 1.6: Highly integrated intravascular membrane oxygenator (HIMOX) utilizing a series of disc-shaped fiber bundles along a core and an axial blood pump. Cattaneo et al. ASAIO J 52:180-5, 2006. .................................................................................................. 11\u00a0 ix Figure 1.7: Schematic of the intravenous respiratory assist catheter, consisting of a pulsating balloon surrounding by a bundle of hollow fibers. Federspiel et al. ASAIO J 42:M435-42, 1996............................................................................................................. 12\u00a0 Figure 1.8: Schematic of the paracorporeal assist lung (PRAL) which utilizes a rotating fiber bundle to enhance gas exchange. Svitek et al. ASAIO J 51(6): 773-80, 2005. ........ 13\u00a0 Figure 1.9: Cross-sectional view of the artificial pump lung (APL) showing the blood flow path", + "6: Highly integrated intravascular membrane oxygenator (HIMOX) utilizing a series of disc-shaped fiber bundles along a core and an axial blood pump. Cattaneo et al. ASAIO J 52:180-5, 2006. 12 Gas exchange was also increased by decreasing fiber porosity, however this lead to a higher pressure drop resulting in bundle deformation and a blood shunt around the device [27]. Another method of increasing blood velocities and enhancing gas exchange is the utilization of a pulsating balloon in the center of a bundle of fibers (Figure 1.7). The fiber bundle is constrained around an un-inflated balloon, making the device smaller than the vessel lumen size and allowing blood to shunt past the device to reduce flow resistance. By rapidly pulsating the balloon, blood flows through the fiber bundle and passes by the fibers as relatively higher velocities. This intravenous respiratory assist catheter, also known as the Hattler catheter, has been shown to enhance gas exchange over the IVOX, providing O2 transfer rates of 175-305 mL/min/m2, depending on balloon pulsation rate [28]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002765_11633-014-0800-y.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002765_11633-014-0800-y.pdf-Figure1-1.png", + "caption": "Fig. 1 The model of n-DOF free-floating space manipulator", + "texts": [ + " Finally, conclusions are drown in Section 5. The space manipulator in this paper assumes the followings: 1) The system is considered as a rigid system. 2) In the space the micro-gravity is ignored, and the system is in a free-floating condition. And no external forces or torques apply on the system. 3) The system consists of a base and several links. The pose of the base is not controlled actively, and every joint between the links can rotate freely within a range under active control. The space manipulator system is shown in Fig. 1, where MC is the mass center of the system. When the space manipulator system is in the ground alignment stage the base can be fixed, for there exists gravity. To facilitate discussion, in this paper a planar 2-link manipulator is chosen, as shown in Fig. 2. In Fig. 2, Bi is the i-th link; Ci is the centroid of the link; mi is the link mass; i is the link length. ai is a scalar from the i-th joint to the centroid of the next link; bi is a scalar from the i-th centroid of the link to the joint of the next link; qi is the joint position", + " According to the properties that have been assumed previously, the free floating space manipulator is shown in Fig. 3. The freedom of the selected planar manipulator will be added to five for the space manipulator will rotate around its centroid and translate along the axis. When the main body of manipulator moves, a dynamic force or torque will apply on the base and the attitude and position of the base will change. In the figure, B0 is the base of the space manipulator; C0 is the centroid of the base; m0 is the mass of the base; other symbols have been defined in Fig. 1. The kinematic and dynamic equations can be established in the similar method of the ground case. The position of the end-effector is pe = \u23a1 \u23a2\u23a3 xc0 \u2212 b0s0 \u2212 l1s01 \u2212 l2s012 yc0 + b0c0 + l1c01 + l2c012 0 \u23a4 \u23a5\u23a6 (4) where s0, s01, s012, c0, c01, c012 have the same definitions as (1). When (4) is differentiated, the end q\u0307 velocity of the robot manipulator can be available. J\u2217(q)q\u0307 = x\u0307 (5) where J\u2217(q) = [ Jb(q), Jm(q) ] \u2208 R2\u00d75 is the generalized Jacobian matrix, Jb(q) = \u2202x/\u2202qb \u2208 R2\u00d73 is the base Jacobian matrix, Jm(q) = \u2202x/\u2202qm \u2208 R2\u00d72 is the robot manipulator Jacobian matrix and q = [ qT b , qT m ]T = [ x0, y0, q0, q1, q2 ]T \u2208 R5 are the center of mass, the base attitude angle and each joint angle, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000337_cle_download_850_912-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000337_cle_download_850_912-Figure1-1.png", + "caption": "Figure 1. Smart bench design", + "texts": [ + " 262 ISSN: 2716-3865 (Print), 2721-1290 (Online) Copyright \u00a9 2023, Journal La Multiapp, Under the license CC BY-SA 4.0 the system. The solar panel strategically installed on the top of the bench serves to capture solar energy and convert it into usable electrical energy. On the other hand, the Arduino, as the system's control center, is responsible for managing the process of collecting, storing, and using energy intelligently and efficiently. The design of this park bench can be seen visually in Figure 1. The technical specifications of the solar bench include a solar panel capacity of 20 Wp/h with a size of 35 cm x 49 cm, a storage battery with a capacity of 20V 18 Ah that allows energy storage and supply during periods of low light intensity or at night, and the integration of environmental sensors in the form of Light Dependent Resistor Sensors connected to Arduino for data collection of light intensity and environmental conditions. Figure 2 shows the mechanical and electrical design details including the connection of solar panels through a power converter to convert energy into an electric current that can be used by the system" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure3.34-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure3.34-1.png", + "caption": "Figure 3.34: Designed GDSM-based leaky-wave antenna with launcher (dimensions in mm) (a) metasurface side (b) ground side", + "texts": [ + "4 GHz, which is very suitable for our operating frequency band (57 - 64 GHz). In this section, we present the simulation results for the designed GDSMbased leaky-wave antenna that is fed by the launcher presented in the previous section. It should be noted that the launcher needs to be placed to a suitable distance from the metasurface to properly excite the propagating wave inside the GDSM-based waveguide [200, 204]. In our simulation, the launcher is placed at 0.388 mm from the edge of the metasurface, as shown in figure 3.34. Figure 3.35 shows the S11 parameters of the simulated model. The -10 dB frequency bandwidth is 7.8 GHz from 56.4 GHz to 64.1 GHz, which is slightly larger than the launcher simulation in figure 3.33. The simulated farfield pattern of the leaky-wave antenna in the xz-plane is shown in figure 3.36, where the main beam direction and gain are shown in table 3.9. The total scanning range is 36.6\u25e6 from -52\u25e6 to -15.4\u25e6 at the operating frequency band of 57 GHz to 64 GHz, which is in good agreement with the simulation results in section 3", + " A transition from grounded coplanar line to ungrounded coplanar line should be further designed and added to the beginning of the launcher to eliminate the perturbation from the fixation ground plate of the connector. Moreover, the transition between the coaxial connector and the grounded coplanar line should be also optimized. We have conducted several attempts of optimizing smoother transition, but due to a lack of time, this work has not succeeded (e.g. the simulation of the metasurface-based antenna with launcher in figure 3.34 takes 36 hours, and the same simulation model with the additional connector, even if the calculation accuracy is reduced by a quarter, takes 32 hours). Although the designed antenna is not suitable with the Southwest Microwave connector, the manufacturing process was tested in this work. Due to the planar and patch-printing features of the antenna, a simple fabrication process can be achieved with a laser structuring machine. Laser processing is a maskless process with no chemical and low cost [158]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003768_tation-pdf-url_12705-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003768_tation-pdf-url_12705-Figure2-1.png", + "caption": "Fig. 2. The model of the rivet", + "texts": [ + " As we wished to analyse the riveting operation and its consequences on the residual stresses between plates, the obvious choice was to use a dynamic explicit FEM code, namely Ls- Dyna\u00ae, whose capabilities make it most valuable to model high-speed transients without much time consumption. www.intechopen.com Numerical Simulations - Applications, Examples and Theory 288 www.intechopen.com Simulating the Response of Structures to Impulse Loadings 289 A finer mesh \u2013 with a 0.2 mm average length \u2013 was adopted to model the stem of the rivet (fig. 2) and those parts of the sheets which, around the hole and below the rivet head, are more interested by high stress gradients; a coarser mesh was then adopted for the other zones, as the rivet head and the parts of the sheets which are relatively far from the rivet. The whole model was composed, in the basic reference case, of 101,679-109,689 nodes and 92,416-100,096 brick elements, according to the requirements of single cases, which is quite a large number but also in that case runtimes were rather long, as they resulted to be around 9-10 hours on a common desktop; more complex cases were run on a single blade of an available cluster, equipped with 2 Xeon 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004120_f_version_1646303113-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004120_f_version_1646303113-Figure2-1.png", + "caption": "Figure 2. Scaled aircraft model at the end of design loop 2. Units in meters.", + "texts": [ + " In fact, the design of a three-lifting surfaces airplane with a reduced vertical stagger between wings involves several aerodynamic issues coming from the combined downwash of both canard and wing, as well as the canard wake interference on the lifting capabilities of the horizontal tailplane and consequently on the aircraft longitudinal stability. Apparently, the complicated interactions among the wakes of the lifting surfaces was not well predicted by the MDAO process of Refs. [8,11]. Thus, from the results of the first test campaign, the canard and the tailplane group were re-designed and a second test campaign on the updated scaled model, shown in Figure 2, was performed. This constitutes the output of the design loop 2. This paper discusses the aircraft evolution from the first to the second design loop and describes, in detail, the complex aerodynamic interference and wake phenomena among the lifting surfaces on the last configuration. A literary review of the three-lifting surfaces aircraft configuration follows this first part of the introduction. A crucial issue for the aerodynamic assessment of this innovative configuration is an accurate estimation of the canard downwash", + " Finally, a non-critical change was also made on the wing root incidence angle and fairing [33], which shifted up the lift curve, achieving an increase of CLmax of 0.2, as shown in Figure 10. As concerns the drag polars shown in Figure 11, it is here remarked that the drag coefficient values attained in low Reynolds wind tunnels are usually higher than those in full-scale conditions. Nonetheless, the maximum aerodynamic efficiency achieved by the test article is about 13. The main changes in aerodynamic coefficients, efficiency, and stability derivatives are resumed in Table 6. The evolved design at the end of loop 2 was shown in Figure 2. In this section, details are given on the data extracted from the wind tunnel tests results on this last configuration. The focus is on the effects of the canard on the longitudinal and directional stability. Additionally, the estimation of the downwash effect is given. Several experimental tests have been conducted on different combinations of aircraft components (wing, body, and tailplane), as illustrated in Figure 12, where some of the tested configurations are shown. It could be useful for a designer to have an estimation of the downwash for a such three-lifting surfaces configuration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004947_f_version_1711705143-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004947_f_version_1711705143-Figure5-1.png", + "caption": "Figure 5. The force\u2013moment direction of the dynamometer. \ud835\udc39 = \ud835\udc39 \ud835\udc39 \ud835\udc39 (1) \ud835\udc39 = \ud835\udc39 \ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udf03 \ud835\udc39 \ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udf03 (2)", + "texts": [ + " The component force\u2013moment equation for the triangular three-point hitch dynamometer was developed based on these considerations. Figure 4 summarizes the direction and magnitude of moments. The location information where the load cells are mounted on the dynamometer is shown in Figure 4. This is very important information regarding moment calculations. The location values in this study are as follows. l1 = 0.0506 m l2 = 0.2878 m l3 = 0.2461 m l4 = 0.3081 m l5 = 0.3233 m l6 = 0.1938 m Agriculture 2024, 14, x FOR PEER REVIEW 7 of 12 Figure 4. Moment direction of load cells. Figure 5 shows the direction of each force and moment, and the dynamometer equation developed is represented by Equations (1)\u2013(6). The coordinate system for calculation was set based on the end point of the dynamometer axis connected to the PTO axis. The tractor\u2019s forward direction was set to the x-axis, the left and right directions were set to the y-axis, and the vertical direction was set to the z-axis. This system is local coordinate system [21]. Figure 4. o ent direction of load cells. Figure 5 shows the direction of each force and moment, and the dynamometer equation developed is r presented by Equa ions (1)\u2013(6). The coordinate system for c lculation was set based the end point f the dy am meter axis connected o the PTO axis. The tractor\u2019s forward di e ion was set to the x-axis, th left and right directions were set to the y-axis, and he v rtic l direction was set to the z-axis. This sys em is local coordinate system [21]. Agriculture 2024, 14, 544 7 of 11 Agriculture 2024, 14, x FOR PEER REVIEW 7 of 12 Figure 4. Moment direction of load cells. Figure 5 shows the direction of each force and moment, and the dynamometer equation developed is represented by Equations (1)\u2013(6). The coordinate system for calculation was set based on the end point of the dynamometer axis connected to the PTO axis. The tractor\u2019s forward direction was set to the x-axis, the left and right directions were set to the y-axis, and the vertical direction was set to the z-axis. This system is local coordinate system [21]. Figure 5. The force\u2013moment direction of the dynamometer. \ud835\udc39 = \ud835\udc39 \ud835\udc39 \ud835\udc39 (1) \ud835\udc39 = \ud835\udc39 \ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udf03 \ud835\udc39 \ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udf03 (2) The dynamometer consists of a single-axis load cell, its value should be modified according to the pitch angle of the dynamometer. Since the dynamometer was initially connected vertically to the lower link, the transport pitch is the dynamometer\u2019s angle. Let the x\u2032y\u2032z\u2032 coordinate system move and rotate with the dynamometer such that the load cells are always in the y\u2032z\u2032 plane and with the same y\u2032z\u2032 coordinates (x\u2032 coordinate of all load cells is zero since all load cells are in the y\u2032z\u2032 plane)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002739_2567-021-00383-3.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002739_2567-021-00383-3.pdf-Figure5-1.png", + "caption": "Fig. 5 NASA public domain picture of the St 5 X-band antenna, launched on a microsatellite as part of the Space Technology (ST5) mission in 2005 [48]. The evolved antenna meets the mission specification of a required, nearly uniform gain for a spinning satellite. NASA public domain picture of the St 5 X-band antenna, launched on a microsatellite as part of the Space Technology (ST5) mission in 2005 [48]. The evolved antenna meets the mission specification of a required, nearly uniform gain for a spinning satellite", + "texts": [ + " A very illustrative example of the effectiveness of an evolutionary algorithms (EA) applicability of very complex design problems is given in the form of the evolved antenna [48]. The difference between an EA and a GA is a similar loop as given in Fig.\u00a03, but data are not organised in a genome form, but heuristic changes and fitness function evaluation remain. In [48], it is clearly stated that EAs are capable of replacing \u201ctime and labour intensive tasks\u201d and allows to determine \u201cnovel antenna designs that are more effective than would otherwise be developed\u201d, see an example of an evolved antenna in Fig.\u00a05. The first approaches of full spacecraft system modelling canonical GAs were made in 1998 [49]. The automated approach allowed for achieving \u2018optimality\u2019 rather than \u2018feasibility\u2019, considering cost functions and schedule constraints. [49] concluded the GA approach as promising in terms of cost and quality of design. Recent work on EA application for CubeSat and small spacecraft design is found in the 2017 paper [50]. Initially, it focused on CubeSat power supply system design and was found to produce vast improvements over human-guided \u201cengineering judgement and point design\u201d" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001922_1044-023-09952-2.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001922_1044-023-09952-2.pdf-Figure1-1.png", + "caption": "Fig. 1 Description of the geometry of a rolling contact bearing", + "texts": [ + " The first includes those cases where mechanical contact among their elements happens in the form of sliding, rolling or flexing, hence identifying three subtypes (sliding contact, rolling contact or flexure bearings, respectively), whereas the second group encompasses those bearings in which their elements do not hold direct contact among the elements and the supporting load is transmitted through an intermediate fluid or by magnetic forces, which are not in the scope of this work. This work will focus on the modelling of bearings based on the rolling contact mechanism, where rolling elements with varied geometries are introduced between two rings or washers, as shown in Fig. 1(a). These elements serve two functions: (i) to transmit the load from one element of the bearing (shaft or housing) to the other; and (ii) to transform the sliding motion endured in the plain bearings into rolling motion, so the friction resistance is reduced [46]. A cage, also known as separator, retainer or crown, is included, so the rolling elements are equally distributed, keeping them separated and allowing a uniform distribution of the loads. These rolling elements can have different geometries depending on the application of the bearing, as represented in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004550_cle_download_621_509-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004550_cle_download_621_509-Figure1-1.png", + "caption": "Fig. 1. Low-pressure nozzles with aerodynamic spray: \u0430 \u2013 general form, b \u2013 bypass valve, \u0441 \u2013 air swirl blade section", + "texts": [], + "surrounding_texts": [ + "\u0442\u0435\u043c\u043f\u0435\u0440\u0430\u0442\u0443\u0440 \u043f\u043e \u0436\u0430\u0440\u043e\u0432\u044b\u043c \u0442\u0440\u0443\u0431\u0430\u043c. \u041a\u0440\u043e\u043c\u0435 \u0442\u043e\u0433\u043e, \u043d\u0435\u0440\u0430\u0432\u043d\u043e\u043c\u0435\u0440\u043d\u043e\u0441\u0442\u044c \u0440\u0430\u0441\u043f\u0440\u0435\u0434\u0435\u043b\u0435\u043d\u0438\u044f \u0442\u043e\u043f\u043b\u0438\u0432\u0430 \u043f\u043e \u0442\u043e\u043f\u043b\u0438\u0432\u043d\u043e\u043c\u0443 \u043a\u043e\u043b\u043b\u0435\u043a\u0442\u043e\u0440\u0443 \u043f\u0440\u0438\u0432\u043e\u0434\u0438\u0442 \u043a \u0438\u0437\u043c\u0435\u043d\u0435\u043d\u0438\u044e \u043f\u0430\u0440\u0430\u043c\u0435\u0442\u0440\u043e\u0432 \u043f\u043e\u0442\u043e\u043a\u0430 \u043f\u043e \u0434\u043b\u0438\u043d\u0435 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turbulent kinetic energy; \u03c9 is the turbulent energy dissipation rate; kG is the production term resulting in k due to the average velocity gradient; G\u03c9 is the production term of \u03c9; k\u0393 and \u03c9\u0393 are the diffusivity of k and \u03c9, respectively; Yk and Y\u03c9 are diffusion terms of k and \u03c9, respectively; D\u03c9 is the cross diffusion term; Sk and S\u03c9 are custom source items, respectively. In order to illustrate the influence of the pneumatic impeller on the aerodynamic performance of the aircraft, it is necessary to obtain the aerodynamic performance of the aircraft without the pneumatic impeller. Firstly, the plane mesh and volume mesh were generated for the aircraft model, and the unstructured mesh was divided, as shown in Figure 8. In order to ensure the accuracy of calculation, cylindrical body is used in the outflow field. The inlet surface is one fuselage length from the aircraft, and the outlet surface is five fuselage length from the aircraft. Calculation state: the atmospheric state is the standard atmospheric state near the ground, the calculated angle of attack is \u20132\u00b0 to 14\u00b0, and the incoming wind speed is 50 m/s. Table 4 shows the lift coefficient and drag coefficient of the aircraft without impeller. Calculation state: the atmospheric state is the standard atmospheric state near the ground, the angle of attack of the aircraft is calculated as \u20132\u00b0 to 14\u00b0, the incoming wind speed is 50 m/s, and the installation positions of the pneumatic impeller are respectively in front of the wing, under the wing and behind the wing and a total of 27 calculation examples are carried out" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002658_2452-020-03846-0.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002658_2452-020-03846-0.pdf-Figure17-1.png", + "caption": "Fig. 17 Cutting pattern", + "texts": [ + " The stiffness of the joints were modeled using three linear (axial) springs for the axial, in-plane and out-of-plane shear directions, and one rotational spring for out-of-plane bending. Table\u00a01 shows the coefficients of the springs with a length of 1\u00a0mm assumed in the model per one-meter breadth. The stiffness values shown above were estimated by structural analysis prior to prefabrication. Those in the integrated hinges were set equal to a strip of 0.1\u00a0mm thick plate, while actual panel thickness ranges from 0.5\u00a0mm in the upper parts, 0.9\u00a0mm in the middle parts, to 1.3\u00a0mm at the lower parts as shown in Fig.\u00a017. The hinges coupled by \u201cwatoji\u201d lacing undergo larger deformations. Small samples were made to see how flexible they were. The order of the rotational spring coefficient was set to as low as one tenth of the integrated one, which is almost a simple hinge with no stiffness. These estimations push the limits of elastica theory for such large deformations but were accepted for this project considering the scale and experimental usage of the canopy. The modeling of looseness in the \u201cwatoji\u201d lacing was translated to softening of the axial and shear stiffness arbitrarily to the order of 1% of the integrated joint for the sake of convenience", + " The canopy consists of deployable strips and webs. This section describes the cutting pattern and module manufacture process. Because each strip is approximately three meters long and two meters wide, they must be divided into smaller modules in consideration of cost and ease of fabrication and transportation. The modules should be less than 1.0 \u00d7 3.0\u00a0m whilst there should also not be more than three cutting modules for easy assembly. Under these requirements, the cutting modules are determined as follows (Fig.\u00a017). 28 50 25 37 2606 Fig. 15 Perspective, top, and front views of the fabricated canopy The number of the modules is set to three because of the maximum size allowed. A half of each web is integrated to the lower side of each module. The margins for on-site assembly are integrated to the edges of the modules. The webs and margins are integrated to the module via above-mentioned FRP hinges. The deployable modules have two types of FRP hinges. The ones along the horizontal foldable lines are integrated between panels in each module, with a required fold angle of about 15\u00b0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-FigureA-3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-FigureA-3-1.png", + "caption": "Figure A-3: Local coordinate frames of the RPY wrist.", + "texts": [], + "surrounding_texts": [ + "184\nsta te [Ref. 27]. Euler wrist has one singular condition and the two corresponding configurations. For the case of Sfi = 0, i.e. fi = 0 or 2tt, ip can be defined with\n(f> = 0 . For fi = 0, <{> = 0 and from elements (1,1) and (1,2), Cip = N x and \u2014 Sip = Sx. Therefore, ip = Atan2(\u2014SX, N X). For ix = 2n,

\u03b5c2.", + "texts": [], + "surrounding_texts": [ + "For the parabolic-rectangle stress-strain relation case, we use the same methodology as in the case of the bilinear stress-strain relation. The only difference is the shape of the concrete stress distribution where the triangular section becomes now parabolic, and also the ultimate Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis strain and the strain corresponding to the start of the rectangular section which become \u03b5cu2 (instead of \u03b5cu3) and \u03b5c2 (instead of \u03b5c3), respectively, as shown in the figure below. In the above figure, x2 is the distance from the neutral axis to the centroid of the parabolic section. The parabolic section is \u201cfull\u201d in the figure, as \u03b5c>\u03b5c2. In the bi-linear case, the calculation of the area and centroid of the non-rectangular part was obvious, because of the triangular shape, but for the parabolic case, integration has to be used, as will be described in detail later. Again, we need to determine if at the ULS the concrete zone or the steel is at the critical strain. First, we put both materials at the ultimate strain, so we have: 2c cu (65) s ud (66) 2 22 2 2 2 2 21 1 2 cu ud cucu ud cu cu c cu c ud cu x d x d x x d (67) 1 1c cdF x f b (68) 1 1 2 x z d (69) The above equations are almost the same as the ones used in the bi-linear case, but of course in the parabolic-rectangle case we use \u03b5c2 and \u03b5cu2 instead of \u03b5c3 and \u03b5cu3. Yet, this time in order to calculate Fc2 we need to integrate Eq. (2) to calculate the area of the parabolic part. For the parabolic part of the stress, i.e. for strains \u03b5c in the region [0, \u03b5c2], we have the indefinite integral: 1 2 2 2 1 1 1 1 n c n c cd cc c c cd c c cd c f d f d f n (70) Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis Thus the area E1 of the full parabolic part [0, \u03b5c2] is given by the definite integral: 2 1 2 0 1 c c c c cd n E d f n (71) The area E1 of the full parabolic part is shown in the figure below in black color. If the integration is done on the cross section height, for the strain \u03b5c2 the corresponding height of the section is (x-x1) and as a result the corresponding area of the full parabolic part A1 is given by: 1 11 cd n A x x f n (72) The area A1 of the full parabolic part is shown in the figure below in black color. The area A1 of the full parabolic part is shown in black color. The concrete force Fc2 is given by: 2 1 11c cd n F A b x x f b n (73) In order to calculate z2 we need to calculate the distance x2 defining the centroid of the A1 area. In terms of strains, the centroid \u03b5centroid of the E1 area is given by the definite integral: Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 2 1 1 0 1 c centroid c c cd E (74) The indefinite integral in this case is given by: 12 2 2 2 2 1 d 1 1 d 2 2 1 nn cd c c c cc c cd c c c c cd c n c c f nf f n n (75) Thus the centroid of the full parabolic part is given by: 2 1 2 1 0 1 3d 2 2 c centroid c c c c n E n (76) If the integration is done on the section height, for the strain \u03b5c2 the corresponding height of the cross section is (x-x1) and as a result the corresponding centroid of the full parabolic part x2 is given by: 1 2 1 1 2 3 2 2 centroid c n x x x x x n (77) Then we have 2 2z d x x (78) 1 2c c cF F F (79) Again, we will calculate the sum of moments at the steel reinforcement position. The sign of the sum of moments will show us whether the concrete zone or the steel is at the ultimate strain at the ULS. The sum of moments is (clockwise positive): 1 1 2 2steel c c sdM F z F z M (80) We then have again two cases: Case 1. \u03a3\u039c\u22650 The concrete force has to be decreased for the equilibrium of the cross section. The steel stays at the ultimate strain (\u03b5s=\u03b5ud), while \u03b5c\u2264\u03b5cu2. Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis Case 2. \u03a3\u039c<0 The concrete force has to be increased for the equilibrium of the cross section. The concrete stays at the ultimate strain (\u03b5c=\u03b5cu2), while \u03b5s<\u03b5ud. The methodology is exactly the same as the one of the bi-linear case. To start, we assume a value for x and we should change it until we reach the final equilibrium. The equations below end up with the calculation of the sum of moments which has to be zero at the equilibrium. Case 1. \u03a3\u039c\u22650, Steel at the ultimate strain We assume an initial value for x and we use the following equations: s ud (81) c ud c ud x x d x d x (82) Case 1a: If \u03b5c>\u03b5c2 In this case we have the parabolic diagram plus a rectangular diagram and the upmost fiber of concrete works at the ultimate stress fcd. From the similar triangles we have: 31 1 3 c c c c c s c s x d x d (83) 1 1c cdF x f b (84) 1 1 2 x z d (85) In a similar way as previously (integrations), and since we have again a full parabolic part, we have: 2 11c cd n F x x f b n (86) 2 1 3 2 2 n x x x n (87) 2 2z d x x (88) 1 2c c cF F F (89) Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 1 1 2 2c c sdM F z F z M (90) After we reach the equilibrium (\u03a3\u039c=0), and given that the steel reinforcement works in full stress, above the yield strain, the steel area can be easily calculated by Eq. (31). Case 1b: If \u03b5c\u2264\u03b5c2 In this case we have only part of the parabolic diagram, there is no rectangular diagram and the upmost fiber of concrete works at stress \u03c3c\u2264fcd. 2 c c cd cd c f f (91) \u03a4his time in order to calculate Fc2 we need to integrate Eq. (2) to calculate the area of the parabolic part, not for the full parabola (up to \u03b5c2), but for the region [0, \u03b5c] where \u03b5c\u2264\u03b5c2. Using the indefinite integral of Eq. (70) we can calculate the corresponding area E2 of the parabolic part for the region [0, \u03b5c] where \u03b5c\u2264\u03b5c2 as a definite integral as follows: 1 1 2 2 2 2 2 0 1 1 1 1 1 1 c n n c c c cd c c c c c cd c cd c f E d f f n n (92) The area E2 of the parabolic part for the region [0, \u03b5c] is shown in the figure below in black color. If the integration is done on the section height, for a strain \u03b5c<\u03b5c2 the corresponding height of the cross section is x while for the theoretical strain \u03b5c2 the corresponding height of the cross section would be x\u2219\u03b5c2/\u03b5c and as a result the corresponding area of the parabolic part A2 is given by: Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 1 1 2 2 2 2 2 1 1 1 1 1 1 1 n n c c c c c c c c cd cd x A f x f x n n (93) The area A2 of the parabolic part in this case is shown in the figure below in black color. \u03b5C<\u03b5c2 \u03b5s=\u03b5ud x Fs Strains Forces z2 Fc2 \u03c3c Vcg, injection takes place and Vcg rises linearly. . . . . . . . . . . . . . . . . . . . 34 3.7 Measured Programming Accuracy", + " Two distinct injection techniques were discussed in 2.6.1 and 2.6.2, pulsed programming and continuous-time programming. Pulsed programming was shown to be accurate but it requires large circuitry to switch between program/ read mode and it takes longer time to converge especially when programming for higher targets in FG-dense applications. Alternatively, continuous-time programming is faster and provides linear injection with predictable results. Two different continuous-time programming FG cells are shown in Fig. 3.1 and Fig. 3.2. Fig. 3.1 shows a basic self-converging cell that stops programming once the target is reached. When injection starts, the floating-gate node voltage Vfg will continue to decrease, causing Vsd to decrease and therefore decreasing Iinj [40]. To set the injection target, different I1 values are used with constant Vcg or a constant I1 is used with different Vcg values. The problem with this self-conversing cell is that convergence time depends on the initial condition on the floating gate node, thus if Vfg was initially high yielding to a small initial drain current, therefore convergence can take up to several seconds. A negative feedback can be used to solve the slow convergence of a self-converging FG cell. The circuit shown in Fig. 3.2 (a) uses a negative feedback amplifier to linearize injection process by holding all Mfg terminals constant throughout injection. During injection process, Vfg is held constant and Vcg ramps up to compensate the charge change on the floatinggate node Fig. 3.3. The source follower configuration shown in 3.2 (b) is the same as that used in pulsed programming and achieved 13-bit precision and programming times on the order of 50sec/200mV [32]. While this configuration provides linear injection and gives accurate results, additional programming circuitry is needed to stop injection once the target is reached" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002853_78_v10187-012-0024-8-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002853_78_v10187-012-0024-8-Figure6-1.png", + "caption": "Fig. 6. The cross sectional areas of PMSMs with different winding arrangements: (a) \u2013 motor A, (b) \u2013 motor B, (c) \u2013 motor C", + "texts": [ + "12 m have been calculated. There are no cooling channels and therefore the core length of the machine is by, [11] l = l\u2032 \u2212 2\u03b4 . (3) The chosen B\u03b4max1 represents the amplitude of the fundamental harmonic component of the air gap magnetic flux density. Due to the rectangular shape of PM, the waveform of the magnetic flux density in the air gap is approximately rectangular. The maximum value of this waveform is calculated by Bmax = \u03c0B\u03b4max 1 4 sin ( \u03b1PM\u03c0 2 ) (4) This value is used for computation of the tooth width bd (Fig. 6) not to exceed the maximal magnetic flux density in the stator tooth Bdper , see Tab. 2 bd = l\u2032\u03c4u kFel Bmax Bdper , \u03c4u = \u03c0Ds Q (5,6) where \u03c4u is the slot pitch, with the stator bore diameter Ds = Dr+2\u03b4 . For the stator dimension it is necessary to calculate the slot dimensions. The first step is to calculate the stator turns needed for the induced EMF by PM in the first step equal to Usph Ns = Usph \u221a 2\u03c0fk1s\u03a6av . (7) where kws is the operating harmonic winding factor, see chapter 3, \u03a6av is the amount of magnetic flux per pole and can be calculated by \u03a6av = 2 \u03c0 B\u03b4max1 Ds\u03c0 2p l\u2032", + " Therefore, the magnetic voltages Umds , Umys and Umyr can be ignored in rotor surface PM machine without making a big mistake. By substituting (15) into (14) the permanent magnet height can be calculated hPM = Um\u03b4\u03b4 Hc \u2212 Hc Br Bmax (16) The last important dimension for a PMSM design is the height of the stator yoke hys . Its value can be gained on the base of the magnetic flux and cross sectional area of it hys = \u03a6av 2kFelByper (17) where kFe and Byper are taken from Tab. 2. Table 5 shows the results of the calculated parameters hPM , wPM and hys . These parameters are shown in Fig. 6. It is possible to design a PMSM with a distributed winding and also with a concentrated non-overlapping winding. Both winding types are popular in PMSMs and in the next chapters the design process is shown. Schematically both types are shown in Fig. 2. The concentrated non-overlapping winding becomes popular due to its advantages because of very good manufacturability which decreases cost, shorter nonoverlapping end turns or higher power density. The next chapter 3.1 shows that the design procedure of both windings is similar", + " Table 6 shows all calculated parameters mentioned above. The phasor diagrams of the base windings constructed by Tab. 6 are shown in Fig. 3a and 4a. The arrangements of both base windings are shown in Fig. 3b and 4b. The total distributed winding is completed by three base windings, shown in Fig.3b. The complete concentrated non-overlapping winding is assembled of six base windings shown in Fig. 4b. The winding factors of both windings for the fundamental harmonic are determined by means of graphics method shown in Fig 5. OF THE DESIGNED PMSM Fig. 6 shows cross section areas of one quarter of all three motors. Table 6 shows the final dimensions of all three PMSMs and also the original PMSM. In this chapter the operation of designed motors is investigated by simulations. The main interest is focused on V - curves, maximal developed torque and ripple torque, losses and efficiency. For this investigation some parameters of PMSM have to be known, see Tab. 8. The parameters have been determined by procedures applied in [8]. The parameters of original motor have been verified by measurements [8] and [9], therefore we suppose that parameters and properties of new designed motors are also reliable" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004139_O201428854483258.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004139_O201428854483258.pdf-Figure9-1.png", + "caption": "Fig. 9. Image acquisition scheme for multi-camera system calibration", + "texts": [ + " Afterwards, we need to acquire multiples images of this test field. In order to avoid dependencies between the IOPs and EOPs within the system calibration adjustment, convergent images and images in portrait and landscape mode should be acquired. These images can be acquired either by rotating the individual cameras with respect to the test field or rotating the test field with respect to the fixed cameras. In this research, since the cameras have been rigidly fixed on the designed arm, the test field board is rotated during image acquisition. Fig. 9 illustrates the implemented rotations of the test field relative to the multi-camera system for the image capture and Fig. 10 shows the position and orientation of the captured images by the central camera using the proposed acquisition procedure. In this section, experiments using the collected data are conducted to demonstrate the feasibility of the introduced automated single-step procedure for multi-camera system calibration. The first set of experiments is implemented to quantitatively and qualitatively assess the outcome of the utilized automated target extraction procedure for the automation of the multi-camera system calibration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000812_wnload_266261_262421-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000812_wnload_266261_262421-Figure3-1.png", + "caption": "Fig. 3. Deformation contour: a \u2013 module 1; b \u2013 module 2", + "texts": [ + " Effect of module number on the values of stresses and distortions The module number, where 1 and 2 modules were used, is one of the most important dimensional variables that affect the dimensions of the gear. Through the results of distortions, it is noted that the distortion value in the first case at module 1 was 3.87\u00d710-6 m. While in module 2, the distortion value was 3.75\u00d710-6, where it is noticed through that module 2 is less distorted compared to the first case, and then it is in terms of its tolerance to distortions as shown in Fig. 3. The following elements were noted during the analysis: due to deformations in the system\u2019s elastic domain, it was possible to see the effects of bending teeth in contact, Hertzian contact (local) between the two pairs of teeth in contact, and structural displacements. The stress applied on the part\u2019s maximum and minimum total deformation values are depicted in color. Red and blue in this coloring represent the greatest and minimum deformation values, respectively. The values of the stresses that affect the gears must be known by changing the module", + "93\u00d7108 Pa at the helix angle of 20, 1.86\u00d7108 Pa at the helix angle of 30, and 1.39\u00d7108 Pa at the helix angle of 45 degrees. It is noticed that the increase in the helix angle increases the contact area between the gears and thus reduces the value of the stresses occurring between them. A favorable behavior at the contact pressure with the Hertzian deformation can be seen (small deformation). In the first scenario, the distortion value at module 1 was 87\u00d710-6 m, whereas the distortion value at module 2 was 3.75\u00d710-6 m (Fig. 3, 4). Previous results show that the module 2 exhibits less distortion than the second scenario. By altering the module, it is possible to have a better understanding of the stresses that the gears are subject to and how much movement they can tolerate. Due to the absence of pressures on its gears, module 2\u2019s confirmation is superior than the other instance. One of the fundamental factors that affects both the technical design and the gears\u2019 size is the pressure angle. In order to calculate the bearing stress and movement of a wind turbine in terms of its diameter, stiffness, and tensile strength, two different kinds of pressure angles were employed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure6.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure6.3-1.png", + "caption": "Figure 6.3: General arrangement of the motor heat sink", + "texts": [ + " Without knowing even 114 rough parameters of the coolant channels, a bottom-up physics-based estimate of hconv (or indeed, even the geometric parameter A) is ill-advised. Based on an informal survey of liquid-cooled electric motors, most of them either use coolant channels machined into the motor casing outer diameter (indirect liquid cooling), or direct liquid cooling on the windings inside the motor case. In either event, the area available for heat transfer is roughly proportional to the area of the outer ring of the motor case (Acase, the yellow area in Figure 6.3). Ideally, the model would automatically scale Acase with rated power, as waste heat is proportional to the rated power. Using rough photogrammetry, I estimated Acase for the magniX motors and the Siemens SP200D and obtain values in a narrow band between 630 and 800 kW/m2 case area. The best view I could find of an aerospace motor\u2019s detailed thermal design is a grainy image of a thermal finite element model of the Siemens SP200D motor in a corporate presentation [201]. Based on the color scale, my best (imprecise) estimate is that the maximum winding temperature is approximately 108\u00b0 C, the cooling inlet temperature is about 85\u00b0 C, and the maximum coolant temperature is somewhere around 98\u00b0 C" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000724_f_version_1539258598-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000724_f_version_1539258598-Figure5-1.png", + "caption": "Figure 5. Geometry of the simplified human body model in the XGtd\u2122 program: (a) Top view; (b) Front view.", + "texts": [ + " The cylindrical model of the human body approximated with polygonal prisms developed and applied previously by the author to study the body-shadowing effect in the 3.6 GHz band was used as the basis for designing a body model suitable for simulating body shadowing in XGtd for the 2.4 GHz band. The number of sidewalls used for cylinder approximation was optimized to obtain the best correspondence between the body shadowing simulations and the results of FDTD. The human body model was simplified using 2 polygonal prisms, as shown in Figure 5. The dimensions were as follows: D1 = 310 mm, D2 = 110 mm, H1 = 1800 mm, H2 = 530 mm, L = 200 mm. The material used to model the human body had the same properties as the human body model proposed by the author to study the body-shadowing effect in the 3.6 GHz band [25]. Its relative electric permittivity was \u03b5 = 52, and its specific conductance was \u03c3 = 1.8 S/m. Those values of material parameters were also successfully used by the author for simplified numerical models of the human body in the FDTD method [40,41]", + " The cylindrical model of the human body approximated with polygonal prisms developed and applied previously by the author to study the body-shadowing effect in the 3.6 GHz band was used as the basis for designing a body model suitable for simulating body shadowing in XGtd for the 2.4 GHz band. The number of sidewalls used for cylinder approximation was optimized to obtain the best correspondence between the body shadowing simulations and the results of FDTD. The human body model was simplified using 2 polygonal prisms, as shown in Figure 5. The dimensions were as follows: D1 = 310 mm, D2 = 110 mm, H1 = 1800 mm, H2 = 530 mm, L = 200 mm. The material used to model the human body had the same properties as the human body model proposed by the author to study the body-shadowing effect in the 3.6 GHz band [25]. Its relative electric permittivity was \u03b5 = 52, and its specific conductance was \u03c3 = 1.8 S/m. Those values of material parameters were also successfully used by the author for simplified numerical models of the human body in the FDTD method [40,41]. The simulations were performed in a free space environment, assuming that the only obstacle between the dipole antennas was the human body model. Figure 5. Geometry of the simplified human body model in the XGtd\u2122 program: (a) Top view; (b) Front view. Figure 6 presents the results of path loss simulations in XGtd\u2122 with different numbers of prism sidewalls used to approximate the main cylinder. The influence of the number of sidewalls used to model the arm cylinders was negligible. In further analysis, only the number of sidewalls in the main prism was considered, while the number of sidewalls approximating the arms was adjusted to match the number of walls in the main prism" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002965_f_version_1690556294-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002965_f_version_1690556294-Figure5-1.png", + "caption": "Figure 5. Assemblage position of capacitive sensor. . .", + "texts": [ + " In addition, only one seed extraction hole is present in the detection region at the same time. As shown in the dibble\u2019s working process, there are seed groups in the seed-filling zone, and the state of the seeds is unstable. However, the seeds in the seed-carrying zone remain stable, and after gravity cleaning, there is usually no surplus seed around the perforations. Therefore, the sensor assembly site was tentatively set up to be in the seed-carrying region and was assembled on the internal seed guard of the seed spacer, as illustrated in Figure 5. Figure 5. Assemblage position of capacitive sensor. Fig re 4. The working process of the toothed-disc cotton precision dibble. 1: Seed picking disc; 2: spacer ring; I: seed filling region; II: seed carrying region; III: s ed storage-transfer region; IV: t ; V: . i l i i by the tractor and rolls clockwise on the ground. The seed-picking disk revolves alongside th moving disk towards the seed filling area, and the cotton seed is deposited into the toothed holes of the seed picker along the seed guide rooves under the influence of the seed-picking disc", + " In addition, only one seed extraction hole is present in the detection region at the same time. As shown in the dibble\u2019s working process, there are seed groups in the seed-filling zone, and the state of the seeds is unstable. However, the seeds in the seed-carrying zone remain stable, and after gravity cleaning, there is usually no surplus seed around the perforations. Therefore, the sensor assembly site was tentatively set up to be in the seed-carrying region and was assembled on the internal seed guard of the seed spacer, as illustrated in Figure 5. Agriculture 2023, 13, x FOR PEER REVIEW 5 of 18 for the sensor by analyzing the working process of the hole seeder. The working process of the dibble can be divided into five stages: seed filling region, seed carrying region, seed storage-transfer region, seed transfer region, and seed discharging region, as shown in Figure 4. Figure 4. The working process of the toothed-disc co on precision dibble. 1: Seed picking disc; 2: spacer ring; \u2160: seed filling region; \u2161: seed carrying regi ; \u2162: seed storage-transfer regio ; \u2163: seed tr nsfer region; \u2164: seed discharging region", + " In addition, only one seed extraction hole is present in the detection region at the same time. As shown in the dibble\u2019s working process, there are seed groups in the seed-filling zone, and the state of the seeds is unstable. However, the seeds in the seed-carrying zone remain stable, and after gravity cleaning, there is usually no surplus seed around the perforations. Therefore, the sensor assembly site was tentatively set up to be in the seed-carrying region and was assembled on the internal seed guard of the seed spacer, as illustrated in Figure 5. Agriculture 2023, 13, 1515 6 of 18 To pinpoint the exact assemblage location of the sensor, the width of the sensor must first be established. The analysis of the trajectory of the cotton seeds shows that the horizontal displacement of the cotton seeds during a single sampling time is: LC = 2R sin( \u03c9\u00d7 90 \u25e6 f\u03c0 ) (9) where Lc is the horizontal displacement of the cotton seeds during a single sampling time; R is the radius of the cotton seed trajectory, mm; \u03c9 is the angular velocity of the seed-picking disc, rad/s; and f is the capacitive sensor sampling frequency, Hz" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003895_tation-pdf-url_63652-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003895_tation-pdf-url_63652-Figure4-1.png", + "caption": "Figure 4. Design space for a sandwich lay-up graphite/epoxy cylinder [90/ 20/90].", + "texts": [ + " A substantial increase in the critical buckling pressure by changing the ply angles can be observed. Similar solutions were obtained for the stacking sequences [0 2/90 ]s and [90 2/0 ]s. The same graphite/epoxy cylinder is reconsidered here with changing the stacking sequence to become 20 equal-thickness layers sandwiched in between outer and inner 90 hoop layers with unequal thicknesses, i.e., ( h\u03022 \u00bc h\u03023) and ( h\u03021 6\u00bc h\u03024), such that the thickness equality constraint P4 k\u00bc1 h\u0302k\u00bc1 is always satisfied. Figure 4 shows the developed p\u0302cr -isomerits in the ( h\u03021, h\u03022) design space. The contours inside the feasible domain, which is bounded by the three lines h\u03021 \u00bc 0 and h\u03022 \u00bc 0 and h\u03021 \u00fe 2 h\u03022 \u00bc 1 (i.e., h\u03024 \u00bc 0), are obliged to turn sharply to be asymptotes to the line h\u03024 \u00bc 0, in order not to violate the thickness equality constraint. This is why they appear in the figure as zigzagged lines. At the design point ( h\u03021, h\u03022) = (0.25, 0.25), the dimensionless buckling pressure p\u0302cr = 16.43 (see Figure 4 and Table 5). As a general observation, as the thickness of the hoop layers increases, a substantial increase in the critical buckling pressure will be achieved, e.g., at ( h\u03021, h\u03022) = (0.33, 0.17), p\u0302cr= 17.92 representing a percentage increase of (17.92 16.43)/16.43 = 9.1%. Finally, the obtained results have indicated that the optimized laminations induce significant increases, always exceeding several tens of percent, of the buckling pressures with respect to the reference or baseline design" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-Figure2.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-Figure2.8-1.png", + "caption": "Figure 2.8: Proximal arm of torsion [11].", + "texts": [ + " Page 9 Nonetheless, it is possible to find certain configurations of parameters and layouts with a relatively flat behavior over the range of motion. For example, see Iteration 5 of Figure 2.7. Current flexure-based hands present deficiencies in support stiffness in the large range of motion (Appendix B), and the reported grasping force goes up to 21.5 N in a three-finger, flexure-based robotic hand [11]. One of the issues reported by Odhner is the increase of the arm with respect to the metacarpophalangeal joint (MCP). See Figure 2.8 [11]. As observed in Figure 2.8, the distance d1 increases as the finger is flexed to grasp an object. This distance is referred to by Odhner as the \u201dproximal arm of torsion\u201d, and it can indeed produce torsion over the proximal flexure joint [11]. When a mug is grasped and carried in the air, the weight of the object produces a sideways force at the contact point. This force, translated to the proximal / metacarpophalangeal joint, acts as torsion due to the arm d1 and acts in-plane bending in the flexure mechanism. In conclusion, at large deflections, when it is necessary to grasp and carry the weight of an object, the flexure joint is at its weakest point" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure8-1.png", + "caption": "Fig. 8. Maximum reduced stresses for the base load", + "texts": [ + " 7): \u2022 point A \u2014 support, \u2022 point B \u2014 support, \u2022 point C \u2014 manipulator 200N (due to the lim- ited budget of the project and difficult to predict dynamic loads, a doubled force value was assumed), \u2022 point D \u2014 battery 75N, \u2022 point E \u2014 computer and electronics 5N, \u2022 point F \u2014 laboratory 29N. The analysis was performed for several variants of the grid in order to verify the convergence of the results. The similarity of the obtained results confirms the appropriate densification of the grid (Table 2). The analysis was carried out iteratively, starting from the base load value up to the dangerous load value (Table 3). The following drawings presented (Fig. 8, Fig. 9, Fig. 10) show the results for the analysis without force multipliers. Figures 11, 12, and 13 shows the results for the analysis with the critical load included. Figure 14 show where the frame joins the rocker-bogie suspension beam. It is possible to identify the point where the reduced stresses reach a value close to the hazardous value for the material used in the structure. Due to the complex state of stresses occurring in this point, potentially dangerous for the structure, additional local laminate layers should be applied to increase the durability of the structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003966__130_1_130_1_84__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003966__130_1_130_1_84__pdf-Figure3-1.png", + "caption": "Fig. 3. Parameters of helical antenna", + "texts": [ + " However, the exact manner in which this method can be used to design antennas and circuits has not yet been clarified. Therefore, this study focuses on defining the exact frequency and efficiency required for electromagnetic coupling on the basis of the antenna theory, circuit theory, experimental observations, and electromagnetic computations. In particular, the structure of equivalence circuits is described in detail. Fig. 1 shows magnetic and helical antennas, which are loop antennas used to generate a strong magnetic field. One antenna is made the transmitting antenna, and the other is made the receiving Fig. 3. Equivalent circuit with two magnetically coupled antennas antenna. Fig. 2 shows the magnetic field at two different resonant frequencies. At the resonant frequency, amplitudes of current are the same in the transmitting antenna and receiving antenna for each resonance. However, the current phase is different at two different frequencies. The equivalent circuit of this magnetic antenna is shown in Fig. 3. Thus, this figure provides information on the efficiency of power transfer. Similarly, electric antennas are shown in Fig. 4, Fig. 5 and Fig. 6. In this paper, we clarify why the efficiency at the two resonant frequencies is high and propose a method for deriving an equivalent circuit to be used in electromagnetic computations and experiments. (a) Equivalent circuit for electric resonant coupling (b) \u03c0-type equivalent circuit Fig. 6. Equivalent circuit with two electrically coupled antennas \u2013 11 \u2013 \u8ad6 \u6587 \u7b49\u4fa1\u56de\u8def\u304b\u3089\u898b\u305f\u975e\u63a5\u89e6\u96fb\u529b\u4f1d\u9001\u306e\u78c1\u754c\u7d50\u5408\u3068 \u96fb\u754c\u7d50\u5408\u306b\u95a2\u3059\u308b\u7814\u7a76 \u2014\u2014\u5171\u632f\u6642\u306e\u96fb\u78c1\u754c\u7d50\u5408\u3092\u5229\u7528\u3057\u305f\u30ef\u30a4\u30e4\u30ec\u30b9\u96fb\u529b\u4f1d\u9001\u2014\u2014 \u5b66\u751f\u54e1 \u5c45\u6751 \u5cb3\u5e83\u2217 \u975e \u4f1a \u54e1 \u5ca1\u90e8 \u6d69\u4e4b\u2217 \u975e\u4f1a\u54e1 \u5185\u7530 \u5229\u4e4b\u2217 \u4e0a\u7d1a\u4f1a\u54e1 \u5800 \u6d0b\u4e00\u2217 Study of Magnetic and Electric Coupling for Contactless Power Transfer Using Equivalent Circuits \u2014\u2014Wireless Power Transfer via Electromagnetic Coupling at Resonance\u2014\u2014 Takehiro Imura\u2217, Student Member, Hiroyuki Okabe\u2217, Non-member, Toshiyuki Uchida\u2217, Non-member, Yoichi Hori\u2217, Senior Member This paper proposes a novel method of contactless power transfer from a transmitting antenna to a receiving an- tenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.7-1.png", + "caption": "Figure 1.7. Toe angle illustrated in a top view; positive (toe-in) shown [61].", + "texts": [ + " \u2022 The camber angle of the wheel is the angle between the wheel plane and the vertical. It is positive when the top of the wheel leans away from the vehicle; negative when it leans into the vehicle. See Figure 1.6. \u2022 The toe angle of a wheel is the angle between a longitudinal axis of the vehicle and the line of intersection of the wheel plane and the road surface. It is positive when the front of the wheel aims toward the vehicle (toe-in) and negative when the front of the wheel aims away from the vehicle (toe-out). See Figure 1.7. \u2022 Track is the lateral distance between the tire contact points of an axle, measured along the ground. See Figure 1.8. \u2022 Wheelbase is the longitudinal distance between the front and rear tire contact points of one side of the vehicle, measured along the ground. See Figure 1.8. 4 5 6 Early, animal-drawn, four-wheeled vehicles consisted of a platform mounted on two axles, with a wheel at each end of the axles. At the center of the front axle was a flat plate with a pin, which fit into a hole in a plate on the platform" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001479_f_version_1716187387-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001479_f_version_1716187387-Figure5-1.png", + "caption": "Figure 5. The vibration mode cloud diagram of the first three non-zero modes of the residual structure. (a) The first non-zero mode; (b) the second non-zero mode; (c) the third non-zero mode.", + "texts": [ + " The first 10 non-zero modal frequencies are shown in Table 2. Figure 4. The dynamic model of China Space Station assembly. Aerospace 2024, 11, 411 10 of 30 The space station assembly is without constraint during in-orbit operation, so the dynamic characteristics of the residual structure without constraint should be analyzed. Based on the finite element model established in the Nastran-2012, the frequency and mode shape of the residual structure were obtained through modal analysis. The first 10 non-zero modal frequencies are shown in Table 2. (c) Figure 5. The vibration mode cloud diagram of the first three non-zero modes of the residual structure. (a) The first non-zero mode; (b) the second non-zero mode; (c) the third non-zero mode. Aerospace 2024, 11, 411 11 of 30 Aerospace 2024, 11, x FOR PEER REVIEW 12 of 34 (a) (b) Figure 5. The vibration mode cloud diagram of the first three non-zero modes of the residual structure. (a) The first non-zero mode; (b) the second non-zero mode; (c) the third non-zero mode. To facilitate the description of the vibration mode of the residual structure, ignoring the Y-direction manned spacecraft, the space station assembly can be viewed as a cross shaped configuration formed by the intersection of two lines. One line is composed of Mengtian and Wentian modules, and the other is composed of cargo spacecraft, the core module and the manned spaceship" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004283_id_0354-46051303285S-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004283_id_0354-46051303285S-Figure3-1.png", + "caption": "Fig. 3 Different stress states of columns, on which the impact load is applied later", + "texts": [ + " CONI\u0106 290 Based on the mentioned standards for calculation of the intensity and form of impact load, an analysis was conducted as well as comparison of the deformations of the concrete column loaded by the equivalent static force, according to the Eurocode 1,section 7, annex C. For modeling and impact analysis in the column, the software package \"Radimpex Tower 6\" [7] was used, that is, the finite element method [8]. Four columns, identical in terms of material and boundary conditions were individually modeled, and in each of them a different stress state, axial force, pure bending, torsion and bending were generated, (Figure 3). The goal of the research is determination of displacement of the impact force point, that is, drawing conclusion about the most favorable stress state on the occasion of vehicle collision with the column. 4.2. Modeling of elements and equivalent static load The column is modeled as a beam element with the characteristics of rectangular cross section 20/20cm, concrete class MB 30 (C25/30), 4m height. The element is hinged on both ends, and the desired stress state is cause in it, and later the equivalent static load from the vehicle impact (Figure 4)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000475_cle_download_209_208-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000475_cle_download_209_208-Figure5-1.png", + "caption": "Figure 5: Amplification of the Motion Profile.", + "texts": [ + " These task velocities and accelerations are derived from contact and curvature specifications between the foot and the (a) Attached marker positions (b) Acquired foot trajectory (c) A cycle of walking motion in the 3D Motion Capture System Figure 4: Capturing a normal treadmill walking cycle. natural walking \u201cteardrop\u201d shape and then are used in defining the position, velocity and acceleration design equations. After solving the equations, the resulting linkages produce a motion profile at the knee that closely resembles the natural walking gait. When attached to a coupler, the motion profile that was generated at the knee amplifies at the foot (Figure 5). Apart from the walking trajectory, another main goal for the Exo-Limb was to be comfortable for the user to wear. This requires attaching the device in a way that is non-invasive and sturdy. Multiple attachment points (hip, glute, thigh, and seat) were considered and compared. Overall, the design matrices showed two preferred methods, a combination of knee and thigh support was chosen for the final design. The design of the leg attachment was completed using statistical averages of anthropometric data" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure29-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure29-1.png", + "caption": "Figure 29: 8 Joint compliant mechanism y axis deformation \ud835\udefe = 8.48\u00b0.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0000098_ats.2023.1096839_pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000098_ats.2023.1096839_pdf-Figure18-1.png", + "caption": "FIGURE 18 Total deformation on full fuselage of RUAV with Epoxy-Carbon-Woven-Wet.", + "texts": [ + "2 Results of full RUAV fuselage\u2013Various perspectives\u2013II The best performing two materials from the full fuselage simulation are Epoxy-Carbon-Woven-Wet and Aluminium alloy. For this second modified computation, the same boundary conditions are imposed and thereafter the primary structural outcomes are computed. In the fine-tuning process with the hybrid composites, Epoxy-Carbon-Woven-Wet with Aluminium alloy produced the favorable output. The displaced structure of full fuselage of RUVA for important lightweight material is revealed in Figure 18. The comprehensive FEA outcomes are revealed in Figures 19\u201322. FIGURE 30 Comprehensive report of equivalent elastic stress of RUAV. Frontiers in Materials frontiersin.org21 Figures 19\u201322 describe the graphical representation of different output values of RUAV\u2019s full fuselage analysis. Based on the extensive structural analysis, Epoxy-Carbon-Woven-Wet has been observed as the suitable individual composite material and Epoxy-CarbonWoven-Wet with Aluminium alloy has been observed as the suitable hybrid composite material" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure24-1.png", + "caption": "Figure 24. Simulation results for the maximum overall frame stress of 16.54 MPa (a), displacement of 0.79 mm (b)", + "texts": [ + " It happens because the rod supporting the rollbar body is arranged in a horizontal profile position in the direction of the z-axis, so the moment of inertia of the resulting section is small. As a result, the rod supporting the rollbar body experiences greater maximum stress. 9. Overall frame simulation The force used in the truss as a whole is the force used in the seven types of supporting rods. Simulations were also carried out using the Autodesk Inventor analysis frame. The results of the simulation on the frame as a whole are bending moment, maximum stress, displacement and safety factor, respectively, the values are 78179 N.mm, 16.54 MPa, 0.79 mm and 16.63. Figure 24 shows the simulation results of the maximum stress (a) and displacement (b) values for the prototype car frame as a whole. Based on the simulation results on the frame as a whole, which was carried out using Autodesk Inventor software, calculation results were obtained in the form of bending moment values, maximum stress, displacement, and safety factors, as shown in Table 5. The results of manual calculations and computer simulations found that the vehicle prototype frame design was successfully designed with dimensions of 2500 mm long, 410 mm wide, and 540 mm high, using 6061 aluminum material with a hollow box tube truss profile" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000372_9312710_09425552.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000372_9312710_09425552.pdf-Figure17-1.png", + "caption": "FIGURE 17. Pictures of a 12/10 U-core DSAFFSPM machine. (a) 10-pole rotor. (b) Stator with 12 U-core modules. (c) Prototype machine.", + "texts": [ + " From Table 4, in terms of stationary harmonics, the dominant harmonic of DSAFFSPM machines with same number of stator poles is approximately the same, while for rotating harmonics, the dominating harmonics of DSAFFSPM machines with odd-rotor-pole-pair-number are different from that with evenrotor-pole-pair-number. IV. EXPERIMENTAL RESULTS In order to validate the above analysis, a 12/10 U-core DSAFFSPM machine and a 6/10 E-core DSAFFSPM machine are prototyped. Their stator, rotor and whole structure photos are displayed in Fig. 17 and Fig. 18, respectively. The no-load flux density and its corresponding spectrum based on flux modulation in the above sections cannot be tested directly in the prototyped machines, only the back-EMF and electromagnetic torque can be shown in the experimental results. Firstly, the line-line back EMF is tested and compared with the FEA result in Fig. 19(a) and Fig. 20(a). It can be seen that the FEA predicted results are in good agreements with the measured waveforms. Fig. 19(b) and Fig. 20(b) show the electromagnetic torque waveforms predicted by FEA and tested by experiment, and two curves match well" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004909_ion-Applications.pdf-FigureI-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004909_ion-Applications.pdf-FigureI-1.png", + "caption": "Fig2 I shape microstrip patch antenna", + "texts": [], + "surrounding_texts": [ + "[3.1]. Geometry & Designing\nA little compact T form and I shape microstrip patch transmitter is presented in this study. We used mirror image designs to improve the performance of this T-and I shaped microstrip patch transmitter The efficiency of a simple patch cannot be influenced by any single structure that lacks a mirror reflection. In this study, the two structures in the shape of T and I have been utilized, and outcomes are very similar. The T and I forms can help with impedance matching. Figures 1 and 2 depict the suggested microstrip patch satellite's design. The patch antenna is small in size of 45.644mm x 35.142mm (W x L) and is built on a FR4 substrate with a depth of 3.2mm and an absolute dielectric constant (r) of 4.4, as illustrated in Figs. 1 and 2.\nA microstrip line with a cut length of 5 mm and a cut length of 10 mm feeds the burner. A 50 microstrip line with such a frequency of 2GHz is printed on the partially grounded substrate as the excitation.\nThe redesigned first and second ground planes serve as an impedance matching component in square microstrip patch antennas, controlling the resistance bandwidth Where ws stands for antenna width and ls stands for antenna length. The suggested transmitter may be configured to function at 2.0GHz frequency by selecting these variables. The findings of both simulations and experiments are also discussed. The Zeland IE3D model yielded the simulation results in this research. [3.2] Design parameters of I Shape Microstrip Patch Antenna\nCo-ordinates 1st:\nVolume 23, Issue 5, May - 2021 Page - 811", + "The slot size of ws1, ws2, ws3, ws4, ws5, ws6, ws7, w8, ws9, ws10, ws11, ws12, ws13, ls1, ls2, ls3, ls4, ls5, ls6, ls7, ls8, ls9, ls10, ls11, ls12, ls13, 9, 11, 11, -11, -11, -9, -9, -11, -11, 11, 11, 9, 9, 17.8, 17.8, 22.8, 22.8, 17.8, 17.8, 8.8, 8.8, 3.8, 3.8, 8.8, 8.8, 17.8 respectively.\nCo-ordinates 2nd\nThe slot size of\nws1, ws2, ws3, ws4, ws5, ws6, ws7, ws8, ws9, ws10, ws11, ws12, ws13, ls1, ls2, ls3, ls4, ls5, ls6, ls7, ls8, ls9, ls10, ls11, ls12, ls13, 9, 11, 11, -11, -11, -9, -9, -11, -11, 11, 11, 9, 9, -17.8, -17.8,- 22.8, -22.8, -17.8, -17.8, -8.8, -8.8, -3.8, -3.8, -8.8, -8.8, -17.8 respectively.\n[3.3]. Return Loss & VSWR The inset feed utilized is design to have inset depth of 10.0mm, feed-line width of 5.0mm as well\nas feed path length of 32.0mm. A frequency span of 2.0GHz is chosen and 151frequency points are chosen over this span to acquire precise and effective results.\nThe centre frequency is chosen to have return loss minimal. The span of frequencies during which the RL is higher than -10 dB is referred to as the antenna's bandwidth (A VSWR of 1 yields 10 dB, which would be a good value). The best feed depth, as determined by IE3D, is Yo = 13.2mm, with an RL of -38.01dB, The achieved centre frequency of 2.0GHz is quite near to the required design frequency of 1.998 GHz.\nThe numerical simulation in Figures 1 and 2 support this approach. T slots and I slots have an impact on antenna effectiveness. The S11 hits -39.12 dB and 40 dB at 2 GHz, respectively, and the VSWR is 1.0212 and 1.012. The increased bandwidth is attributed to the T shape and I shape achieving even more vertically electrical current throughout the patch, resulting in an even more\nVolume 23, Issue 5, May - 2021 Page - 812", + "consistent supply of magnetic current in digits. The suggested antenna's predicted current distribution around 2.0GHz frequencies is shown in Fig.\nAn antenna model was built and evaluated to verify the simulation results. Measurements are taken in this prototype using a coaxial port connected to underside edge of both the microstrip feed line. Several disparities between simulated and observed results, however, can be easily detected.\n[3.4]. Simulated Results and Discussions\nThe suggested antenna is simulated using the IE3D simulation tool in determining its performance. By altering one of several physical model parameters while leaving the others constant, the antenna was analysed for various physical model parameters. This research is being done to see how flexible design of a two layer patch antenna may be.\nFig2(a) simulation results of return loss of I shape microstrip antenna\nVolume 23, Issue 5, May - 2021 Page - 813" + ] + }, + { + "image_filename": "designv8_17_0001086_1934_context_journal-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001086_1934_context_journal-Figure5-1.png", + "caption": "Fig. 5. The schematic of running mechanism with understeer characteristic.", + "texts": [ + " In other words, the turning radius increases when the vehicle is accelerated with fixed steering wheel. At the same steering wheel position and vehicle forward speed, the turning radius of an understeer vehicle is larger than that of a neutral steer vehicle. When a side force acts at the center of gravity of understeer vehicle originally moving along a straight line, the front tires will develop a slip angle greater than that of the rear tires. As a result, a yaw motion is initiated, and the vehicle turns to the direction of the side force, as shown in Fig. 5. If \u03b11 < \u03b12, R < R0, it is said to be \u201coversteer\u201d. For an oversteer vehicle, when it is accelerated in a constant radius turn, the driver must decrease the steering wheel\u2019s angle. In other words, the turning radius decreases when the vehicle is accelerated with fixed steering wheel. For the same steering wheel position and vehicle forward speed, the turning radius of an understeer vehicle is smaller than that of a neutral steer vehicle. When a side force acts at the center of gravity of an oversteer vehicle originally moving along a straight line, the front tires will develop a slip angle less than that of the rear tires" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure9.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure9.4-1.png", + "caption": "Figure 9.4: Secondary Vibration Mode in RV Air Expander", + "texts": [ + " 177 The main source of these discrepancies is due to the bimodal nature of the assembly vibration as displayed in the measured data. The presence of a secondary waveform in the measurements indicates that the vibration of the RV prototype is bimodal; arising from the presence of a clearance gap between the vane and the vane slot due to manufacturing tolerances. This phenomenon is termed as \u2018vane knocking\u2019 [157]. The eccentricity between the rotor and cylinder centres of rotation causes their rotation speeds to vary during operation as shown in Figure 9.4. Due to the presence of the clearance gap and differences in rotation speeds, there will be instances when the vane will lose contact momentarily with the vane slot wall on the cylinder resulting in the oscillation of the vane slot wall about the vane. In the RV air expander, the driven cylinder component has a larger moment of inertia compared to the rotor, the resulting impacts would distort the output torque of the pneumatic engine as observed in the measurements. In Figure 9.3(a), Figure 9.3(e) and Figure 9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000812_wnload_266261_262421-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000812_wnload_266261_262421-Figure8-1.png", + "caption": "Fig. 8. Stress contour helix angle: a \u2013 20 degrees; b \u2013 30 degrees; c \u2013 14.5 degrees", + "texts": [ + "1\u00d710-6 m when the helix angle is 45 degrees. Figs show that the increase in the angle of the helix increases the contact area and thus increases the ability of the gear to withstand deformations, as in the angle of the helix of 45 degrees. Along the length of the tooth in contact, a fluctuation in the range of values is seen. Both the contact area and the tooth root exhibit the behavior of the teeth under load. The value of the stresses is necessary to know the amount of contact between the gears. It is noted from Fig. 8 that the stress value was 1.93\u00d7108 Pa at the helix angle of 20, 1.86\u00d7108 Pa at the helix angle of 30, and 1.39\u00d7108 Pa at the helix angle of 45 degrees. It is noticed that the increase in the helix angle increases the contact area between the gears and thus reduces the value of the stresses occurring between them. A favorable behavior at the contact pressure with the Hertzian deformation can be seen (small deformation). In the first scenario, the distortion value at module 1 was 87\u00d710-6 m, whereas the distortion value at module 2 was 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002967_article_25881122.pdf-FigureI-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002967_article_25881122.pdf-FigureI-1.png", + "caption": "FIGURE I. THE SCHEME OF A QUAD ROTOR UAV", + "texts": [], + "surrounding_texts": [ + "Keywords-UAV; state feedback; error adjustment; adaptive fault tolerant control\nI. INTRODUCTION\nWith the development of UAV, improving the control quality of aircraft has become an important research content in the field of aircraft control and design field, ensuring that it can automatically identify faults, deal with the failure and interference has become a key link to improve the autonomy of the aircraft. Fault-tolerant control technology is a kind of advanced control method [1] which can be used to compensate the influence of failure and maintain the effect of system control when the control system has a certain range of fault interference. It has been widely used in the field of aerospace control [2-4].\nFour rotor UAV flight state is changing at any time, the aerodynamic parameters are not accurate, the body dynamics is complex, the model library is imperfect, flight mechanism is nonlinear, variability and uncertainty, these unmodeled factors greatly increased UAV control difficulty. The attitude control system has the feature of over-drive, strong coupling and complex working conditions. The uncertainties of the flight process could also cause the sensor, the controller, the transmission link and the control system, once happened,actuators and other failures will do a fatal damage to the entire system. it is necessary to study the UAV external interference and fault compensation on the impact of the flight process.\nIn the present field of control, the nonlinear disturbance observer has been applied in many fields. Based on a class of nonlinear uncertain systems, it\u2019s main function is to observe uncertainties such as unmodeled impact of the system or unknown disturbances, so as to provide the design for the subsequent controller, the paper [5] design a robust tracking controller based on disturbance observer. According to the attitude control problem of rigid body satellites, in the paper [6], based on the output of disturbance observer, a fuzzy sliding mode interference compensation control method based on error quaternion is proposed. In the paper[7],an inversion control method based on sliding mode European technology is designed by using nonlinear observation jammers to\napproximate unmodeled dynamic and boundary unknown disturbances. In the paper [8] it propose an adaptive fault tolerant control system for the gain fault of the rotor, which can deal with the fault of the drive unit, but the lack of in-depth analysis of the fault detection, so it\u2019s no significance in practical application.\nII. PROBLEM DESCRIPTION\nA. Mechanics Model of Four Rotor\nGeneral, UAV use coordinate system is body coordinate system, ground coordinate system, and track coordinate system, Euler angle ( ),,( ,which represent the yaw angle, the pitch angle and the roll angle respectively, is used to describe the flight attitude, The generalized coordinate system of the UAV is 6),,,,,( Rzyxq ,Where ),,( zyx\nrepresents the distance from the fuselage to the origin of the inertial coordinate system, M1\uff0cM2\uff0cM3\uff0cM4 represent the four motors respectively, F1\uff0cF2\uff0cF3\uff0cF4 represent the lift force of four motors respectively. Firstly we need make a few assumptions [8]:\n(1) UAV is a completely symmetrical rigid body structure.\n(2) The output voltage of DC motor is linear with the output torque.\n(3) The center of mass of UAV is completely coincident with the origin of the coordinate system.\n(4) The ground coordinate system is the inertial coordinate system (ICS), the curvature of the earth can ignored, Acceleration of earth is a constant.\nLet's assume it. 33 S),,(,Rz)y,(x, ,\nThe linear kinetic energy, the angular momentum, and the gravitational potential energy of the four rotor UAV in the inertial space can be expressed as\nCopyright \u00a9 2017, the Authors. Published by Atlantis Press. This is an open access article under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).\n70", + " \n \n\n\n\n\n\n\n\n\nJTrot\nmgzU\nm T\nT\nT trans\n2\n1\n2 (1)\nWhere m represent the quality of UAV, J represent the moment of inertia, g represent the gravity acceleration, then the Lagrangian equation of system could be as:\nmgzJ m\nUTTqqL TT rottrans \n2\n1\n2 ),( (2)\nWhen F q\nL\nq\nL\ndt\nd , we can make a conclusion\nFqJq q qJqJ T ) 2 1 ( (3)\nWhere ],[ TTFF is the force of each channel, is\nthe torque of each channel. Then there is next force equation:\nFRF ~ , Where\n \n\n \n\n \n \n \n\nsincoscoscoscossinsinsinsincossincos sincoscoscossinsinsincossinsinsincos\nsinsinsincoscos R\n(4)\nIs represent the coordinate transformation function matrix,\n \n\n \n\n \n4321\n0\n0 ~\nFFFF\nF is represent the lift force of\nrotor. According to Newton Law\n \n\n \n\n \n \n \n\n \n \n)(\n)(\n)()(\n43\n21\n2143\nVVlK\nVVlK\nVVKVVK\nf\nf\ntntc\n\n\n (5)\n ) 2 1 ( JJJ T , then Coriolis vector\ncan be represented as follow:\n \n \n\n\n),()( 2\n1\n)( 2\n1 ),(\nCJJ\nJJV\nT\nT\n \n \n (6)\nIn order to simplify the operation, we can make a command: ~),( JC , then ~ .\nIn this paper, we doing lots of research on each system of UAV respectively, on the base of follow assumption, the attitude change angle is not more than 5 degrees,\n0,0 J , so the axis equation of UAV is just\nas follow:\n \n\n \n\n \n \n \n\n \n \n)(\n)(\n)()(\n43\n21\n2143\nVVlK\nVVlK\nVVKVVK\nJ\nJ\nJ\nJ\nf\nf\ntntc\nr\np\ny (7)\nSo the control input vector is TVVVVtu ),,,()( 4321 , the state variable of the system is Tx ),,,,,( , the\noutput vector is Ty ),,( , so the System state space\nExpression can be as:\n \n )()()( )()()( tDutCty tButAxtx (8)\nIn which A is state matrix, B is input matrix, C is output matrix, D is incidence. Where\n \n\n \n \n\n\n \n\n\n 000100 000010\n000001\n000000\n000000\n000000\n100000\n010000\n001000\nCA \uff0c\n \n\n \n \n\n \n\n\n\n 000 000\n000\n00\n00\n0000\n0000\n0000\nD\nJ\nlK\nJ\nlK J\nlK\nJ\nlK J\nK\nJ\nK\nJ\nK\nJ\nK\nB\nr\nf\nr\nf\np\nf\np\nf\ny\ntn\ny\ntn\ny\ntc\ny\ntc\n\uff0c\nB. Control Problem Description\nFace with the case of external disturbance and actuator failure, the model of the attitude control system of four rotor UAV with three degrees of freedom can be described:\n)()()()( tBtButxAAx (9)" + ] + }, + { + "image_filename": "designv8_17_0001079_cle_download_650_405-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001079_cle_download_650_405-Figure1-1.png", + "caption": "Figure 1. Configuration of the SIW synthesized by metallic via-hole arrays", + "texts": [ + " This study aims to use frequency reconfigurable substrate-integrated waveguide (SIW), which is believed that results of this study will significantly improve the miniaturization, antenna performance, increasing the gain as well as radiation pattern. It\u2019s believed this study will help academician\u2019s research in understanding the effectiveness of Frequency reconfigurable substrate-integrated waveguide (FRSIW) F- slot antenna in terms of E-field radiation and its capability of achieving a reasonable value of efficiency and gain. A distinctive geometry is appeared in Figure 1 where metallic by means of gap clusters function as side dividers of the waveguide while the substrate's metal cover and ground plane form the waveguide broad walls. Setup of the SIW orchestrated by metallic by means of via-hole Arrays as said before, SIW is made out of two parallel varieties of through via holes delimiting the TE10 wave spread zone, as its cutoff frequenc y is just identified with the width an of the waveguide as long as the substrate thickness or waveguide height ' b' is smaller than 'Wsiw'" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003738_school_dissertations-FigureA.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003738_school_dissertations-FigureA.6-1.png", + "caption": "Figure A.6: CMOS operational amplifier circuit of Figure A.2 with injected faults.", + "texts": [ + "1//142 3 8 24 1//142 3 8 2 , / 2 3 1 3 2 1 3 22 , / 2 1 1 12 \u239f \u239f \u23a0 \u239e \u239c \u239c \u239d \u239b \u239f\u239f \u23a0 \u239e \u239c\u239c \u239d \u239b \u2212\u2212\u239f\u239f \u23a0 \u239e \u239c\u239c \u239d \u239b +\u239f\u239f \u23a0 \u239e \u239c\u239c \u239d \u239b + + +\u239f\u239f \u23a0 \u239e \u239c\u239c \u239d \u239b \u2212\u2212\u239f\u239f \u23a0 \u239e \u239c\u239c \u239d \u239b += \u2212 \u2212 sb sequ kTqv so m a Dm m m SBfsb sequ kTqv so m a Dm eqt c reqI gf IK kTg g g vc reqI gf I K kTg v SB SB \u03c9 \u03c6 \u03b3 \u03c9 133 134 135 136 noise of the CMOS amplifier circuit with frequency. In Figure A.5, dotted line corresponds to SPICE simulations and solid line corresponds to Eq. (A.13). The modeled output noise without injected faults obtained from Figure A.5 is 215 V\u03bc , which is in close agreement with the corresponding SPICE simulated noise of 254 V\u03bc . The total input referred noise is 19 nV/ Hz . Seven faults are injected in the amplifier circuit using fault injection transistors (FITs) [4] which are distributed as shown in Figure A.6. The injected faults in the amplifier are as follows: Fault 1: M10 drain-source short (M10DSS), Fault 2: M5 gate-drain short (M5GDS), Fault 3: M5 drain-source short (M5DSS), Fault 4: M11 drain-source short (M11DSS), Fault 5: compensation capacitor short (CCS), Fault 6: M7 gate-drain short (M7GDS) and Fault 7: M6 gate-drain short (M6GDS). These faults simulate bridging type faults due to manufacturing defects. When a fault is introduced, the noise at the output deviates from the value which corresponds to a fault-free condition" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001401__downloads_tb09j677c-Figure3.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001401__downloads_tb09j677c-Figure3.3-1.png", + "caption": "Figure 3.3: Modal eigencurrent distribution on bow-tie structure for a) J1 at 1 GHz and b) J3 at 4 GHz. Eigencurrents are normalized to their respective maximums and have units of dBA/m.", + "texts": [ + "2 Normalized modal charge distribution on U-slot antenna for a) the in-phase mode, CM1, and b) the anti-phase mode, CM3. The images are obtained from [14]. . . . . . . . . . . . . . . . . . . . . . . 10 Figure 2.3 Eigenvalues and the decoupled auxiliary eigenvalues for CM1 and CM3 of a thin dipole. Plot is obtained from [16]. . . . . . . . . . 11 Figure 3.1 Bow-tie antenna. . . . . . . . . . . . . . . . . . . . . . . . . . 13 Figure 3.2 Characteristic attributes for characteristic modes excited by the port and the driven reflection coefficient of the bow-tie antenna. . . . 14 Figure 3.3 Modal eigencurrent distribution on bow-tie structure for a) J1 at 1 GHz and b) J3 at 4 GHz. Eigencurrents are normalized to their respective maximums and have units of dBA/m. . . . . . . . . . . . . 15 Figure 3.4 Bow-tie antenna with stubs. . . . . . . . . . . . . . . . . . . . 16 Figure 3.5 Modal significance and reflection coefficient for bow-tie antenna with no stubs and at stubs lengths of 40 mm and 60 mm. . . . . . . . 16 Figure 3.6 Characteristic attributes for the characteristic modes excited by the port and the driven reflection coefficient of the bow-tie antenna with 60 mm stubs", + " The maximums for an of the excited modes line up with the minimums for the driven reflection coefficient. This is expected as the modal admittance is directly related to an as expressed in (2.12). Notice no minimum for the reflection coefficient occurs between the CM1 and CM3, where the modal resonance of CM2 would be. This 14 is because a2 (not shown in Fig. 3.2) is zero at all frequencies due to CM2 having an eigencurrent null at the location of the excitation. The eigencurrent distributions on the bow-tie structure is shown in Fig. 3.3 for CM1 and CM3 near their respective modal resonances. The eigencurrent for mode 1, J1, has a half wavelength current distribution and the eigencurrent for mode 3, J3, has a three half wavelength current distribution [23]. For both modes, an eigencurrent maximum occurs at the center of the structure where the excitation is located, enforcing why an for these modes is large. The phase of J3 undergoes a 180\u00b0 phase shift near the center of the structure causing current nulls to appear on each arm offset from the center on the x-axis by 14.5 mm. At the same location, the magnitude of the eigencurrent for J1 is not at maximum but is significant. The eigencurrent maximum\u2019s and minimum\u2019s for the excited modes shown in Fig. 3.3 can be used as a guide to manipulate the modal resonances. Stated in the previous section, a current null for J3 is located close to the current maximum of J1. By placing stubs at the null perpendicular to the longitudinal axis (x-axis), the modal resonance of CM3 can be electrically lengthened without affecting CM1 by increasing the length of the stub. A similar method was applied to a slotline antenna in [24] by placing stubs at the nulls of its electric field and in [25] by placing stubs at the current nulls of a dipole\u2019s 5th order mode to shift its resonance close to the 3rd order mode" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004283_id_0354-46051303285S-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004283_id_0354-46051303285S-Figure4-1.png", + "caption": "Fig. 4 Equivalent static vehicle impact load", + "texts": [ + " The goal of the research is determination of displacement of the impact force point, that is, drawing conclusion about the most favorable stress state on the occasion of vehicle collision with the column. 4.2. Modeling of elements and equivalent static load The column is modeled as a beam element with the characteristics of rectangular cross section 20/20cm, concrete class MB 30 (C25/30), 4m height. The element is hinged on both ends, and the desired stress state is cause in it, and later the equivalent static load from the vehicle impact (Figure 4). Equivalent static force was determined according to the Eurocode 1, section 7, annex C, for the vehicle up to 3000kg weight and maximum velocity at impact up to 20 km/h. P=30kN Mt=30kNm M=30kNm Structural Vehicle Impact Loading 291 Calculation of the vehicle impact, according to the standing standards, and using the contemporary modeling and simulation software differs from the traditional design methods. Depending on the Codes, there is large result scattering, that is, discrepancies in the force intensity of the same initial parameters (vehicle mass and velocity)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000703_46_aoje_1_011041.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000703_46_aoje_1_011041.pdf-Figure3-1.png", + "caption": "Fig. 3 (a) The hexagonal twist fold pattern. Mountain folds are shown as solid lines. Valley folds are shown as dashed lines. The sector angles of the degree-4 vertices in the pattern are also shown and (b) the dimensions of each of the unique panels (hexagon, pentagon, and triangle) in the hexagonal twist.", + "texts": [ + " 1, 2022 Transactions of the ASME D ow nloaded from http://asm edigitalcollection.asm e.org/openengineering/article-pdf/doi/10.1115/1.4055357/6918346/aoje_1_011041.pdf by guest on 20 D ecem ber 2024 In this paper, the aforementioned five techniques described will be evaluated as they apply to the hexagonal twist pattern to create deployable space array designs. The hexagonal twist pattern [19] is composed of three unique panels: a hexagonal panel (1), a pentagonal panel (6), and a triangular panel (6). Figure 3(a) shows the hexagonal twist origami pattern. This pattern is an array of repeating degree-4 vertices consisting of intersections of three mountain folds and one valley fold, or three valley folds and one mountain fold. The sector angles of these vertices are \u03b11= 90 deg, \u03b12= 60 deg, \u03b13= 90 deg, and \u03b14= 120 deg. Each edge of the hexagon is equal to a, which is also equal to the radius of the circumscribing circle of the central hexagonal panel. The sides of the pentagonal panels that share fold lines with the triangular panels are equal to 3 \u221a /3 a. These are shown in Fig. 3(b). The hexagonal twist pattern is flat-foldable, meaning it will fold flat in the open and closed configurations. Figure 1 shows the folding motion from the flat, closed configuration to the flat, open configuration. The pattern is also rigid-foldable, meaning that the only deformation during the motion of the pattern occurs in the creases. The hexagonal twist is a single-degree-of-freedom pattern, therefore it can be fully actuated with only one input, and if any fold angle is defined, the other three-fold angles are defined throughout the deployment", + " 6, the mechanical advantage starts at \u22122, meaning that for an input displacement or torque, double the output displacement or torque is realized. The mechanical advantage is reduced to 0.5 at the flat-unfolded state. This trend shows that the mechanical advantage starts out high and as the folding motion occurs, the mechanical advantage decreases. This allows the determination of how much actuation force is needed throughout the hexagonal twist folding. 3.3 Modified Hexagonal Twist. If additional deployed area is desired, the hexagonal twist shown in Fig. 3(a) can be modified to increase the deployed area, without causing any panel interference during the folding motion or in the flat, stowed configuration as shown in Ref. [29]. Figure 7(a) shows the modified hexagonal twist pattern with the triangular panels increased to rhombus-shaped panels. This change is shown with the hinge-shift and offset panel technique presented later in this paper. As a note, figures of the other techniques do not show this change, however, all calculated metrics presented in this paper consider this change from a triangular panel to a rhombus panel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000226__Thesis_Redacted.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000226__Thesis_Redacted.pdf-Figure6-1.png", + "caption": "Figure 6 - The application of an external disturbance to the body that triggered the emergency control response.", + "texts": [ + " 5 Figure 2 \u2013 Finite state machine that governs the operation of the exoskeleton. The four stages mimic the stages seen in the STG technique. .. 7 Figure 3 - Exploded view of simulated exoskeleton model. ............................ 8 Figure 4 - Side by side comparison of simulation and experimental models. . 9 Figure 5 - The Emergency control state machine that takes effect once the sensors detect a fall event. The state machine attempts to correct the trajectory of the body and avoid the fall. ....................................................... 11 Figure 6 - The application of an external disturbance to the body that triggered the emergency control response. .................................................. 13 Figure 7 - Motion profile of body when disturbance is applied during regular STG motion. The controller detects a fall, prevents it, corrects the trajectory, and proceeds with the STG motion. .............................................................. 14 Figure 8 - Variation of torso angle against time during initial angle disturbance. The fall prevention mechanism is enabled during the fall and prevents the fall from occurring", + " 12 In summary, the emergency control mode analyzes the direction of the fall and prevents it by placing the arms in a position that catches the body. To simulate a failure during the STG motion, various disturbances in the form of forces and initial conditions are systematically introduced into the physics simulation to test the safety mechanism\u2019s functionality in this paper\u2019s proposed controller. This controller is shown to recover from a step-function force application of 150N that is applied to the static body as shown in Figure 6. This force magnitude is chosen as an initial assessment and controller demonstration as it was the minimum required force to tip over the body in the simulation space. Each of the events of the force application simulation are explained in Table IV. The motion can also be seen in the supplementary file titled FLCSimulation.mp4. 13 Table IV Event Function 1 A force application interrupts regular motion. 2 A fall is detected by the FLC, and the emergency mode is triggered. 3 The elbows retract to allow for shoulder rotation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure19-1.png", + "caption": "Fig. 19. The von Mises stress distribution in the assembly of the modelled rims for the case of transport of pallets with paving stones during driving on the dirt road when both tires of each twin wheel of the rear axle were in contact with the road", + "texts": [ + " In this case, both tires of each twin wheel of the rear axle were in contact with the road. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during driving on the asphalt road were shown in Fig. 18. They did not exceed values of 61 MPa. In this case, both tires of each twin wheel of the rear axle were in contact with the road. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during driving on the dirt road were shown in Fig. 19. They did not exceed values of 160 MPa. In this case, both tires of each twin wheel of the rear axle were in contact with the road as well. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during driving on the dirt road were shown in Fig. 20. They did not exceed values of 400 MPa. In this case, only one tire of the one twin wheel of the rear axle was in contact with the road. Although in most cases analyzed, the obtained values of the von Mises stresses did not exceed the value of the Yield Stress of assumed steel, in the last case they were higher than the Yield Stress by about 25%" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002837_cle_download_968_284-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002837_cle_download_968_284-Figure2-1.png", + "caption": "Figure 2: Schematic diagram of the proposed permanent-magnet", + "texts": [ + " Under consideration is a cylindrical shape with notches, which makes it possible to stick to a planar problem due to the rotational symmetry. The length and the maximum diameter are set to 10 mm and 4 mm, re- spectively, which implies a reasonable size of the device, and, as a rule of thumb, matches to N = 400 turns in the coil. We adopt the magnetic properties of a state-of-the-art sintered magnet (NdFeB-50) with sufficiently high remanent magnetization. An example of the proposed magnet shape is presented in Figure 2, with the dimensions defined in Figure 3 and Table 1. The notches in the magnet design are the key innovation, contributing to a lower weight, reduced consumption of the raw material, and the required field inhomogeneity necessary for a non-zero time derivative in Equation (1). The complete flow chart of the magnet-modelling procedure is presented in Figure 4. The finite-element calculations of the magnetic flux density were carried out with FEMM software.14,17 The first-type (Dirichlet) boundary conditions and a triangular mesh were applied" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002355_f_usme2019_01032.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002355_f_usme2019_01032.pdf-Figure7-1.png", + "caption": "Fig. 7. Test-bench design pattern.", + "texts": [ + " The values of loads acting on test-bench levers are quite high. Therefore, for manufacturing of levers the high-quality structural carbon steel is preferred, such as steel 40. Upon fatigue strength criteria the known methods of the strength of materials determined inertia moments and resistance moments of enclosed rectangular sections of test-bench levers. For the first approximation the construction of the mathematic model of the test-bench vibrations was made as for a simple vibration system with weights of m1 and m2 (Fig. 7). Linear movements of these weights take place in generic coordinates q1 and q2. The Lagrange differential equations of motion are composed with the following assumptions: \u2013 small vibrations of the test-bench lever system are being considered; \u2013 the system is conservative; \u2013 the weights of test-bench levers are lumped; \u2013 the weight of the pusher 2 (see Fig. 7) is disregarded due to its nullity; \u2013 the system elastic elements feature linear characteristics; \u2013 stiffness of elastic elements are equal to rigidness of corresponding test-bench levers. In accordance with accepted assumptions for steady-state operation mode the following system of equations for motions of test-bench levers was obtained: 11 1 11 1 12 2 22 2 21 1 22 2 sin ; 0, a q c q c q F t a q c q c q \u03c9\u2032+ + = + + = (1) where ( ) 1 11 1 2 1 cos Ja m l \u03b2 = + , 2 22 2 2 2 Ja m l = + are inertial coefficients of the system; 2 1 11 1 1 cosClc c l \u03b2 = , 1 2 12 1 1 2 cosC Cl l c c l l \u03b2 = \u2212 , 21 12c c= ; ( ) 2 2 22 1 2 2 Clc c c l = + are elastic coefficient of the system ; m1, m2 are weights of drive and axle levers; J1, J2 are inertia moments of drive and axle levers; c1, c2 are stiffness of drive and axle levers; l1, l2 are distance from lever rotation axes to their centers of mass; lC1, lC2 are distance from lever rotation axles to elastic elements; \u03b2 is drive lever tilt angle; F\u2032 = 2F is loading force amplitude reduced to lever center of masses; \u03c9 is frequency of system loading ; t is time" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure39-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure39-1.png", + "caption": "Figure 39. The schematic and mechanism of optical encoder.", + "texts": [ + " A: The reference sheet was glued to the force-plate and the center of origin was considered as the bottom-left. B: Test loads were applied to circles on the plate. ............................................................................................................ 59 Figure 37: Spatial accuracy map in application of two standard loads to the force-plate ........................... 59 Figure 38: Total force accuracy map in application of two standard loads to the force-plate. ................... 60 Figure 39: The schematic and mechanism of optical encoder. ................................................................... 63 Figure 40: The footplate axis of rotation, where the encoders were installed in the early trials.. ............... 64 Figure 41: The optical encoder attachment to the DFPF axis of rotation: 1) the 3D printed pulley housing, 2) the optical encoder, 3) the extension rod, 4) the encoder electrical wiring to the data acquisition board ..............................................", + " Considering the maximum applicable load to the springs (600 N), the anterior and posterior springs were preloaded by 220 N and 390 N respectively. These values were acquired experimentally to achieve a better accuracy in force measurement. Four compression load cells (53CR from Honeywell Inc., Morristown, NJ, 226 Kg) were used to measure the subject\u2019s interaction forces with the footplate. The load cell signals were amplified and sampled at 1 KHz into the real-time machine target (using the NI PCI 6251), as shown in Figure 39. Each load cell was connected to the corresponding external amplifier and analog channel on data acquisition board. Load cells produce 10 mv output (2 mV/V \u00d7 5 V excitation voltage) at the full load condition (226 Kg). Using the built-in potentiometers, the amplifier gain was adjusted to 1000 (to create a 10 V output) and the offset voltage was removed. Considering the 16-bit data acquisition board, the minimum load resolution can be theoretically estimated as 3.5 g. 56 In the presence of active motors, significant amount of radio frequency interference (RFI) was observed on the load cells" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003835_f_version_1676453559-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003835_f_version_1676453559-Figure15-1.png", + "caption": "Figure 15. Front module, detail of ECS interface.", + "texts": [ + " Similarly, this approach held also for the auxiliary tanks (Figure 14), with the difference that the outlet line of LH2 was mathematically connected to the overall flow exiting from the primary tank (not shown in the schematic). The boil-off line was physically connected to the compressor (the boil-off was not mixed inside the primary tank but it was connected directly to the cycle). Additionally, the ECS interface was introduced in order to simulate the segment of the circuit from the CAU compressor outlet up to the cabin, including the boil-off-based heat exchanger and airflow turbine (Figure 15). This rationale was also applied to the second module (middle TMS module) as well as the third one (rear module). For the second module, the primary tank was the FAT-middle part (FAT-MP), while auxiliary tanks were the center wing tank (CWT) and the wing tip tank (WTT) (see Figure 7, second picture). The same hypotheses on the routings of LH2 and the boil-off circuits applied, even if these were referred to the middle module only. Where possible, the different elements (such as pumps, compressors, turbines etc" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure6-1.png", + "caption": "Figure 6. Transducer calculation model.", + "texts": [ + " The adopted solutions enable easy and quick disassembly and replacement, making the sensor a universal solution that can be used with many types of agricultural tools. Prepared in this way, the structure enables easy installation and removal of the tested tools. 17-4PH steel was used as the construction material, which has the elastic modulus E = 1.96 \u00d7 1011 N\u00b7m\u22122, the Poisson ratio \u03bd = 0.30, the density \u03c1 = 7.85 \u00d7 103 kg\u00b7m\u22123, and the yield strength \u03c3s = 1100 \u00d7 106 N\u00b7m\u22122. In order to perform simulation tests, a properly parametrised virtual models were prepared, as presented in Figure 6. Specialist CAD-3D software was used to prepare them. With the use of pre- and postprocessors of graphic engineering interpretation, the calculation model was described with solid elements enabling approximation of operating characteristics of an object in real conditions [47,48]. Based on the adopted transducer construction and the occurring loads, tetrahedral parabolic second-order elements were used in the prepared model. This ensured a more accurate mathematical representation than in the case of linear elements [49]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000020__ms-13-1011-2022.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000020__ms-13-1011-2022.pdf-Figure8-1.png", + "caption": "Figure 8. Maximum contact stress calculated by the finite element method, where \u03d51 = 0.25\u03c0 .", + "texts": [ + " Under the same bearing conditions, the maximum contact stress of the improved NHGM changes more smoothly, which means it has a stronger bearing capacity. The reason for this result is that the parameters of the contact ellipses are changed (see Fig. 9). The contact ellipses can be calculated, and they are shown in Fig. 10. https://doi.org/10.5194/ms-13-1011-2022 Mech. Sci., 13, 1011\u20131018, 2022 The maximum contact stresses of meshing gears can be calculated by the finite element method. For this case, maximum contact stresses that can be calculated by the finite element method are shown as Fig. 8, where \u03d51 = 0.25\u03c0 . Compared with the results obtained by the finite element method shown in Fig. 8, the relative error in the maximum contact stress which is obtained by the theoretical calculation method shown in Fig. 7 is 1.32 % and 0.93 %, respectively. As shown in Fig. 9, the values of the long and short axes of the contact ellipse of the unimproved gear drive decrease linearly. The values of the long and short axes of the contact ellipse of the improved gear drive are larger than the unimproved one, and they are not linearly changed. For the improved gear drive, the values of the long and short axes reach the minimum, where \u03d51 = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000930_ent_86800_PDF_16.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000930_ent_86800_PDF_16.pdf-Figure1-1.png", + "caption": "Fig. 1. Geometry of CPW-fed monopole antenna.", + "texts": [ + " The proposed antenna has a reasonable average gain and good radiation pattern. Details of antenna design, simulated and measured results are presented and discussed. Section II presents the geometry of the proposed antenna. Then in section III the effect on the impedance bandwidth, full band and band-notched function design are analyzed. After that the experimental results including measured return losses and radiation patterns are presented in section IV. Section V gives the conclusions. The proposed UWB CPW-fed monopole antenna with a band-notch function is shown in Fig. 1. The antenna is printed on FR4 substrate with thickness of 1mm and relative permittivity of 4.4 and loss tangent 0.02. The proposed antenna consists of a square substrate which a square slot is etched at the center of the ground plane. A CPW-fed line is a staircase strip and two gaps of width g which are located between the ground plane and a CPWfed line. The gaps between the strips and ground plane are adjusted to reach reasonable impedance matching. In proposed CPW-fed monopole antenna, two grounded semi-triangles metallic strips placed at down corners of the square slot and two circular metallic strips placed at up corners of the square slot which is modified ground plane to achieve a wide bandwidth", + "8, 2 (units are in mm), and lengths of L1, L2, L3, L4, L5 which are respectively 2.6, 2.8, 4.2, 3.9, 0.5(units are in mm). The inner of values of square slot with dimensions of Ls\u00d7Ls are 18.8\u00d718.8 mm2. In proposed CPW-fed monopole antenna, the lengths of each semi-triangles, T1, T2, T3 and T4 are 4.6 mm, 4.9 mm, 1.93 mm and 2.18 mm respectively, A=3.7 mm and gap distance is g=0.5 mm. The H-shaped slot has width of W6=0.8 mm, W7=2 mm, and lengths of L6=3.2 mm, L7=1.67 mm and L8=0.85 mm. The prototype of the antenna is shown in Fig. 1. with Fig. 3. Simulated reflection coefficients of the proposed antenna with different Ls with a fixed values of P2=4.5 and T2=4.87 (Units are in mm). Ls=18.8 mm, P1=4.4 mm, P2=4.8 mm, A=3.7 mm, T2=4.76 mm has been fabricated and tested. In this section, the monopole antenna with various design parameters is constructed. It is clearly seen that the monopole antenna exhibits a broad impedance bandwidth of 8 GHz (3-11 GHz). However, by inserting an H-slot on the staircase feed line one notched band at 5", + " When g is increasing the impedance matching can be greatly improved. The results show that changing the size of ground plane in all four figures (Fig. 3-Fig. 6) has a direct effect on its area as the area was nearly around 300 mm2, bandwidth of the antenna were almost one and the same. The geometry of antenna with four grounded semi-triangles metallic strips is shown in Fig. 7. Two circles show in this figure specify the location of circular grounded strip. Fig. 8 shows the effect of the antenna using circular grounded strip as shown in Fig. 1. (antenna I) in comparison with the antenna using four semi-triangle grounded strip (without circular grounded strip) as shown in Fig. 7. at Ls=18.8 mm (antenna II). It can be seen that in the case of antenna I, circular grounded strip on ground plane cause to achieve a broadband width. The prototype of the proposed antenna is shown in Fig. 9. The measured reflection coefficients of the proposed antenna (Ls=18.8 mm, P1=4.4 mm, P2=4.8 mm, A=3.7 mm, T2=4.76 mm) using an hp 8510 network analyzer in comparison with simulated reflection coefficients is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003249_O200932056740446.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003249_O200932056740446.pdf-Figure4-1.png", + "caption": "Fig. 4. Broken model and analysis results at high-speed test (18000[rpm]).", + "texts": [ + " In the rotor structure, permanent magnets were partially inserted into each layer to obtain the sinusoidal back-EMF waveform. The shape and length of each layer was designed to enhance the inductance difference. The material which was used is nonoriented silicon steel (S18) suitable for a rotating electrical machine. Its yield strength is 300 [MPa]. The IPMSM was operated at 18000 [rpm] with intent to break the rotor core structure in order to study the effect of mechanical stress. The broken model and analysis results at high-speed test are shown in Fig. 4. The comparison of computational results is summarized in Table 2. As a simulation result, the maximum stress calculated by the stress analysis was 519 [MPa] at the center-post. This value is larger than the yield strength and tensile strength of the steel. Also, the location with maximum value coincides with the broken region. However, the maximum value estimated by the conventional method is smaller than the yield strength. Therefore, it can\u2019t explain the reason for the broken region. From the simulation results, we can see that our methods agree well with the experimental ones compared to the conventional method" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002535_al-02925036_document-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002535_al-02925036_document-Figure2-1.png", + "caption": "Figure 2: Geometric intuition behind our approach, at several length scales. At the scale of a single star, the contraction of the pre-stretched fabric back to its rest dimensions is arrested by the plastic star bonded to the fabric. The star arms buckle to form a small bump (a); neighborhoods of thicker stars contract less due to the star arms bending less. At the scale of a neighborhood of several stars, the fabric contracts unimpeded, since stars are not connected (b). A sparser star pattern with smaller stars (and hence more spacing between them) allows more contraction. At the scale of a large patch of star meta-material, several factors control the surface shape: differential contraction due to variations in star thickness and spacing induces buckling of the surface to relieve metric frustration; boundary conditions can impose additional contraction and buckling (c); and if stars are laid out in a regular pattern, there is global coupling in how each star breaks symmetry while buckling, introducing large-scale curvature (d).", + "texts": [ + " Three scalar sizing fields specify the design of the star pattern: ` : \u2126\u2192 [0,1] specifies the length of the star\u2019s arms at different locations on the fabric, with `= 0 indicating no star at all and `= 1 a star with arm lengths d (so that the star touches its neighbors); and h,w : \u2126\u2192R specify the thickness (in the direction perpendicular to the fabric and printing plane) of the stars and (in-plane) width of the star arms, both in millimeters. To summarize, a star pattern design consists of a choice of: 1. fabric tension s and star spacing d, both global to the entire pattern; 2. three functions `,h,w over \u2126; which encode variations in the star sizing; 3. boundary conditions for how the border of the pattern should be pinned to the ground after printing. After the star pattern has been printed and the fabric is allowed to relax to static equilibrium, the meta-material buckles into a 3D structure with residual internal stress. Figure 2 illustrates how the choice of design parameters provides several means of lifting the resulting surface into controllable shapes. In the neighborhood of each individual star, the star arms bend to form a bump under the action of the fabric\u2019s compressive forces (Figure 2a). The size of this bump depends on the fabric tension s and the length and thickness of the star arms, which control the star\u2019s resistance to bending and thus final curvature. In between stars, the fabric contracts unimpeded (Figure 2b), by an amount proportional to the length of the star arms. At a coarse scale much larger than that of an individual star, we can treat the meta-material as a homogenized smooth surface without the bumps around each star. In this homogenized view, the effect of each bump is to change the surface area of a neighborhood of the star at equilibrium, where the spatially-varying amount of surface contraction depends on the thickness, width, and length of the stars. Therefore `,h,w equip the homogenized surface with a rest state described by a non-Euclidean metric (Sharon and Efrati, 2010)", + " In addition to changing the local surface area of the homogenized surface, the stars modify the surface\u2019s rest extrinsic curvature, since the stars are printed on top of the fabric (rather than embedded within it); in other words the metric of the metamaterial varies in the thickness as well as the curvilinear directions. The differential contraction described by this metric causes the suface to buckle out of plane, in order to exchange large amounts of stretching strain for slight bending strain (Figure 2c). This relationship between change of metric and buckling has also been exploited by related self-shaping fabrication technologies based on swelling (Kim et al., 2012) or auxetic linkages Konakovi\u0107-Lukovi\u0107 et al. (2018). In our case, the precise relationship between the surface metric and the values of `, h, and w depends on a complex physical coupling for Self-Shaping Architectural Models between the fabric and the rods. We also observed a coupling phenomenon between neighboring stars, where the bending of each individual star propagates to adjacent stars through deformation of the fabric in between (Figure 2d). It is unclear whether this behavior is a consequence of, or an additional effect independent of the induced non-Euclidean metric. This coupling leads to globally consistent symmetry-breaking in the surface, a phenomenon that is especially visible when we do not fix the boundary of the domain, since in this case the accumulation of local bending makes the entire surface fold on itself to form a tube, as shown in Figure 3. Given the complexity of the physical phenomena involved, from local contraction of the surface to global propagation of bending, we propose a dedicated numerical simulation model to predict the shape that user-provided star patterns would take" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure2-1.png", + "caption": "Figure 2 P-POD Coordinate System and Component Diagram", + "texts": [], + "surrounding_texts": [ + "Page 2\nare shown in Figure 1. Since its inception, the P-POD has undergone a series of design improvements and increased capabilities, including a more sound structural design, CubeSat access port covers, and a more sophisticated deployment mechanism.\nOne concern launch providers typically have is the radiofrequency (RF) and\nelectromagnetic (EM) interference (or RFI/EMI) that can emanate from working electronics on a satellite. This interference can potentially disrupt normal function of the launch vehicle and/or primary payload(s). In order to mitigate this risk, CubeSats are currently required to remain powered off on ascent, and cannot make any RF transmissions for a pre-determined amount of time after launch. However, if the P-POD was able to contain all RFI/EMI to an extent that would satisfy launch providers, the onascent power-off requirement could potentially be relaxed, allowing CubeSat function during launch. This could create new avenues for science and exploration, including launch environment measurement, which would bring in high fidelity data pertaining to the launch environment. A greater knowledge of different launch environments could potentially reduce recurring engineering costs and prevent over-testing. RFI/EMI containment can also support more specific mission objectives, such as inter-CubeSat communication on launch, and systems monitoring during launch.\nThesis Motivation and Goal\nAs CubeSat systems become increasingly complex, the need for more specific\ncapabilities can also arise. In some instances, CubeSats can contain complex sensing instruments that require a controlled or stable environment. Sometimes this can include an Oxygen-free environment, which would require some sort of inert gas purge. In other", + "Page 3\ninstances, it can benefit the CubeSat payloads to have an electrical interface to the launch vehicle. Such an interface could provide power and data capabilities but also cannot hinder deployment in anyway. Incorporating a standard interface for these extra missionspecific capabilities can reduce recurring engineering costs and create a P-POD that can rapidly adapt to mission-specific requirements.\nThroughout this Master\u2019s Thesis, different components and P-POD axes will be\nreferred to. The figure below shows the P-POD coordinate system and notes the names of each component. The +/- X panels refer to the side panels, +Y is the Top Panel, -Y refers to the Bottom Panel, +Z is the Door, and \u2013Z refers to the Back Plate. It is common practice to refer to panels by their coordinate representation.", + "Page 4\nOver the last few iterations of the P-POD, the CubeSat Program has gone to great\nlengths to decrease stress concentrations and increase the strength capabilities of the PPOD. While these changes have improved the P-POD, they have also increased its mass. Upon closer examination, there are some areas where material can be removed while retaining the strength added throughout the previous iterations. This will prove to be a worthwhile exercise as launch costs decrease with decreasing mass. The goal is to decrease some of the accumulated mass without negatively effecting the strength of the P-POD. In fact, another avenue explored was a review and redesign of the door, which is historically a weak point for the P-POD. In this instance, increasing strength without increasing mass is the primary objective, while also reducing mass wherever possible.\nThis Master\u2019s Thesis explores the possible capabilities that the P-POD can offer,\nwhile improving its base functions along the way. Supporting increasingly complex CubeSats is necessary in order to continue to further space research. CubeSats have greatly expanded the market of space exploration, allowing entities access to space, when previously it was far out of reach. Offering CubeSat Developers a more capable P-POD provides them with more tools for innovation." + ] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure7-1.png", + "caption": "Fig. 7. The single rim utilized in the twin rear wheels of the rear axis of the tipper: a) general view; b) and c) wireframe style perpendicular views; d) wireframe style isometric view", + "texts": [ + " (5) During the transport of pallets with paving stones, the loading from cargo was equal to 48 000 t. This increased twice the loading of twin wheels of the tipper-truck rear axle. This led to reaching a value of 2 \u00b7Tra\u2212perm by the torque transferrable by the twin wheel of the tipper-truck rear axle. The stress distribution in the assembly comprised of two rims of twin rear wheels of the rear axis and was obtained using the Finite Element Method implemented in the software Autodesk Inventor Professional v. 2021. The single rim was presented in Fig. 7. To carry out a numerical calculation of the model of the mentioned assembly was elaborated (Fig. 8). Each rim was made of weldable steel with a carbon content below 0.3 wt.%. It was assumed that the mechanical properties of steel AS/NZS 3679.1- 300 [64] were very close to these of the steel applied to the rim analyzed. This assumption was supported by the fact, that during the initial (rough, due to the unsatisfactory technical condition of the used portable X-ray fluorescence (XRF) analyzer) analysis of the chemical composition of steel, an increased manganese content was observed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004633_1145_3498361.3538936-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004633_1145_3498361.3538936-Figure3-1.png", + "caption": "Figure 3: A step-by-step illustration of the Spatial Dimension Expansion algorithm. (a) The phase difference encountered by each antenna indicates the radial distance change. However, the drone\u2019s 3D location would be ambiguous with only 1D distance information. (b) By embracing multipath, PMT uniquely determines the 3D location of one specific antenna. (c) Finally, putting all the measured 3D translations of antennas together, the 6-DoF motion of the drone can be resolved using the rigid-body constraint among multiple antennas.", + "texts": [ + " 12 is treated as a linear function of \u0394\ud835\udc53\ud835\udc57 across all subcarriers, and both the common phase slope \ud835\udefd\ud835\udc59 \ud835\udc58 = \ud835\udf0f\ud835\udc59 \ud835\udc58 \u2212\ud835\udf0fLoS \ud835\udc58 across the subcarriers and the corresponding overall attenuation [\ud835\udc59 \ud835\udc58 = \ud835\udefcLoS \ud835\udc58 \ud835\udefc\ud835\udc59\u2217 \ud835\udc58 are jointly estimated [35]:{ \ud835\udefd\ud835\udc59 \ud835\udc58 , [\u0302\ud835\udc59 \ud835\udc58 } = argmin \ud835\udefd\ud835\udc59 \ud835\udc58 ,[\ud835\udc59 \ud835\udc58 \u00a9\u00ab\ud835\udc6a\ud835\udc37\ud835\udc58 \u2212 \u2211\ufe01 \ud835\udc59 \u2208L\ud835\udc41 ( [\ud835\udc59 \ud835\udc58 \ud835\udc52 \ud835\udc57\u0394\ud835\udf19 \ud835\udc59 \ud835\udc58 + [\ud835\udc59\u2217 \ud835\udc58 \ud835\udc52\u2212\ud835\udc57\u0394\ud835\udf19 \ud835\udc59 \ud835\udc58 )\u00aa\u00ae\u00ac , \u0394\ud835\udf19\ud835\udc59 \ud835\udc58 = 2\ud835\udf0b (\ud835\udc53\ud835\udc50 + \u0394\ud835\udc53\ud835\udc57 + \ud835\udf16\ud835\udc53 )\ud835\udefd\ud835\udc59\ud835\udc58 , (13) and the phase could be reconstructed as: \u0394\ud835\udf19\ud835\udc59 \ud835\udc58 = 2\ud835\udf0b (\ud835\udc53\ud835\udc50 + \u0394\ud835\udc53\ud835\udc57 )\ud835\udefd\ud835\udc58 \ud835\udc59 , (14) So far, both \ud835\udf16\ud835\udc53 and \ud835\udf16\ud835\udc61 are eliminated, leaving the sanitized phase \u0394\ud835\udf19\ud835\udc59 \ud835\udc58 in Eqn. 14, which indicates the phase difference between the NLoS path \ud835\udc59 and the LoS path. To infer the drone\u2019s 6-DoF relative pose from the 1D sanitized phase, PMT performs Spatial Dimension Expansion algorithm. For ease of notion, we first consider the geometric meaning of the CSI phase. As shown in Fig. 3a, the phase difference \u0394\ud835\udf19 between two consecutive packets reveals the radial distance change \u0394\ud835\udc51 = \u0394\ud835\udf19 2\ud835\udf0b _, where the _ indicates the wavelength of the radio signal. However, the distance change is only of one dimension. Therefore, the spatial dimension expansion algorithm is proposed to bridge the dimensional gap in two steps: 1) bridge the gap between 1D distance change and 3D location change based on multipath, and 2) bridge the gap between 3D location change and 6D pose change based on multiple antennas", + " Correspondingly, subtract the direction vector of the LoS path \ud835\udc8f0 from the direction vector of \ud835\udc3f NLoS paths to get \ud835\udc75 \ud835\udc56 = ( \ud835\udc8f1 \ud835\udc56 \u2212 \ud835\udc8f0 \ud835\udc56 , \u00b7 \u00b7 \u00b7 , \ud835\udc8f\ud835\udc3f \ud835\udc56 \u2212 \ud835\udc8f0 \ud835\udc56 )T . Thus, we have the following approximate relationship between the phase change and the 3D location change \ud835\udeab\ud835\udc85\ud835\udc56,\ud835\udc58 = \ud835\udc85\ud835\udc56,\ud835\udc58 \u2212 \ud835\udc85\ud835\udc56\u22121,\ud835\udc58 : \ud835\udeab?\u0302?\ud835\udc56,\ud835\udc58 \u2212 \ud835\udeab?\u0302?\ud835\udc56\u22121,\ud835\udc58 = 2\ud835\udf0b \ud835\udc75 \ud835\udc56\ud835\udeab\ud835\udc85\ud835\udc56,\ud835\udc58 _ , (15) which indicates that the phase change on each propagation path is induced by the projection of the drone\u2019s 3D location change on each corresponding direction, as shown in Fig. 3b. From 3D location to 6D pose. To derive the drone\u2019s relative rotation and translation, our key insights are as follows: \u2022 As the drone rotates, different antennas may experience distinctive location changes, as shown in Fig. 3c. \u2022 Multiple antennas on the drone are rigidly attached. Therefore, PMT infers macroscopic pose change from the microscopic motion of each antenna based on rigid body kinematics [50]. Denote location changes of antennas as \ud835\udeab\ud835\udc6b\ud835\udc56 = ( \ud835\udeab\ud835\udc85\ud835\udc56,1, \u00b7 \u00b7 \u00b7 ,\ud835\udeab\ud835\udc85\ud835\udc56,\ud835\udc3e ) . With preknown antenna arrangement \ud835\udec0 = (\ud835\udf4e1, \u00b7 \u00b7 \u00b7 ,\ud835\udf4e\ud835\udc3e ), the equation below can be derived: \ud835\udeab\ud835\udc6b\ud835\udc56 = (\ud835\udeab\ud835\udc79\ud835\udc56\ud835\udec0 + \ud835\udeab\ud835\udc95\ud835\udc56 ) \u2212 \ud835\udec0, (16) indicating the location change of each antenna is induced by an overall rotation and translation of the array. So far, the basic ideas of the spatial dimension expansion algorithm have been illustrated" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure18-1.png", + "caption": "Figure 18: Overall design of the virtually interfaced robotic ankle and balance trainer (vi-RABT): The support frame (1) provides room for stepping forward/backward; Subjects feet will be strapped on the robotic force-plates (2); The surrounding rails (3) provides safety features to the patients during practice; The system can be used in standing or sitting posture using the adjustable chair (4); and patients will be instructed to play the VR game on the screen (5) (modified from [131]).", + "texts": [ + " 30 Figure 16: Virtual environment in a rural street (left) and ice on the ground (right) [87], Copyright \u00a9 2011 IEEE ............................................................................................................................................... 30 Figure 17: The model of 2-DOF NUVABAT and the schematic for ankle and balance training [35], Copyright \u00a9 2010 IEEE ..................................................................................................................... 31 Figure 18: Overall design of the virtually interfaced robotic ankle and balance trainer (vi-RABT): The support frame (1) provides room for stepping forward/backward; Subjects feet will be strapped on the robotic force-plates (2); The surrounding rails (3) provides safety features to the patients during practice; The system can be used in standing or sitting posture using the adjustable chair (4); and patients will be instructed to play the VR game on the screen (5) (modified from [131]) ................." + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002046_O201336447759533.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002046_O201336447759533.pdf-Figure3-1.png", + "caption": "Fig. 3\uc740 \uace0\uc555\uc138\ucc99\uae30 \ub0b4\ubd80\uc758 Mesh \ud615\uc0c1\uc744 \ub098\ud0c0\ub0b4\uace0 \uc788 \ub2e4. \ucd1d 1,593,523\uac1c\uc758 \uc808\uc810\uacfc 1,499,373\uac1c\uc758 \uc694\uc18c\ub85c \uad6c\uc131 \ub418\uc5b4 \uc788\ub2e4.", + "texts": [ + " \ub610\ud55c \ubaa8\ub378\ub9c1\ub41c \uace0\uc555\uc138 \ucc99\uae30\uc5d0 \ub300\ud558\uc5ec 3\ucc28\uc6d0 \uc720\ud55c\uc694\uc18c\ud574\uc11d \ud504\ub85c\uadf8\ub7a8\uc778 ANSYS[2-3]\ub97c \uc0ac\uc6a9\ud558\uc5ec \uc720\ub3d9\ud574\uc11d\uc744 \uc218\ud589\ud558\uc5ec \ub0b4\ubd80\uc555\ub825 \uc5d0 \ub530\ub978 \uc720\uccb4\uc758 \ud750\ub984\uc744 \uad6c\ud558\uc600\ub2e4. \uc774\ub7ec\ud55c \ud574\uc11d\uacb0\uacfc\ub294 \uc0c8 \ub85c\uc6b4 \uace0\uc555\uc138\ucc99\uae30\uc758 \uc81c\ud488\uac1c\ubc1c\uc5d0 \ud65c\uc6a9\ub420 \uc608\uc815\uc774\ub2e4. 2. \ubcf8\ub860 \ub17c\ubb38\uc758 \ud574\uc11d\ub300\uc0c1\uc740 \ud604\uc7a5\uc5d0\uc11c \ud65c\ubc1c\ud788 \uc0ac\uc6a9\uc911\uc778 \uace0\uc555\uc138 \ucc99\uae30\ub85c\uc11c Fig. 1\uacfc \uac19\ub2e4. [Fig. 1] High Pressure Cleaning Machine \ubaa8\ub378\ub9c1\uc740 \uace0\uc555\uc138\ucc99\uae30\uc758 Gun, Hose, Boiler \ubd80\ubd84\uc5d0 \ub300 \ud558\uc5ec \uc218\ud589\ud558\uc600\uc73c\uba70 \uc555\ub825\uc774 \ub192\uc544\uc9c4 \ubb3c\uc758 \ud750\ub984\uc744 \uc704\ud55c \ub0b4 \ubd80\ubaa8\ud615\uc744 \ubaa8\ub378\ub9c1\ud558\uc600\ub2e4. \uc6d0\ud65c\ud55c \ud574\uc11d\uc744 \uc704\ud558\uc5ec \ud615\uc0c1\uc744 \uac04 \ub7b5\ud654 \uc2dc\ud0a4\uace0 \ubd88\ud544\uc694\ud55c \ubd80\ubd84\uc740 \uc81c\uac70\ud558\uc600\ub2e4. Fig. 2\ub294 \uace0\uc555\uc138\ucc99\uae30\uc758 \ud615\uc0c1\uc744 \ub098\ud0c0\ub0b8\ub2e4. Table 1\uc740 \uace0\uc555\uc138\ucc99\uae30 \ub0b4\ubd80\uc640 \uc678\ubd80\uc758 Mesh \uc138\ubd80\uc0ac\ud56d \uc774\ub2e4. [Fig. 2] Geometry of High Pressure Cleaning Machine [Table 1] Mesh generation Domain Nodes Elements Default Domain 1,593,523 1,499,373 [Fig. 3] Mesh generation \uace0\uc555\uc138\ucc99\uae30 \ub0b4\ubd80\uc640 \uc678\ubd80\uc758 \uc720\uccb4 \ud750\ub984\uc744 \uc54c\uc544\ubcf4\uae30 \uc704\ud558 \uc5ec \uac01\uac01 100, 120, 150, 160, 180, 200, 250bar\uc758 \uc555\ub825\uc744 \uc8fc\uc5b4 \uc720\ub3d9\ud574\uc11d[4-7]\uc744 \uc2e4\uc2dc\ud558\uc600\ub2e4. Table 2\ub294 \ud574\uc11d\uc870\uac74\uc774\ub2e4. [Table 2] Physics conditions Domain-Default Domain Type Fluid Location B564, B732, B803 Materials Water Fluid Definition Material Library Morphology Continuous Fluid Settings Buoyancy Model Non Buoyant Domain Motion Stationary Reference Pressure 100.0000e+00[bar] ~ 2500.0000e+00[bar] Heat Transfer Model Isothermal Fluid Temperature 2.5000e+01[C] Turbulence Model kepsilon Turbulent wall functions scalable Mass Flow rate 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004553_ai.7-12-2021.2314491-Figure25-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004553_ai.7-12-2021.2314491-Figure25-1.png", + "caption": "Fig. 25.Selected Final Design after Numerical Analysis", + "texts": [ + " Static analysis was carried out for Stainless steel with both twisted and flat structure. From the analysis, conceptual design -6 has been chosen as the optimum design among the alternatives. In this work, an attempt has been made to perform ergonomic redesign of passenger seat supporting frame. Different concepts were developed by considering various factors. Further RULA analysis was carried out to determine the effects of various postures on human comfort. Selected concept suitability was determined by FEA. It is observed that the Isection concept with rib shown in figure 25 is the optimum one for given functional and comfort requirments. Table 2 Result for Existing Design Table 3 Weighted Matrix [1] Tan, CheeFai, et al. \"Conceptual design of cantilever support for long haul bus passenger seat.\" Australian Journal of Basic and Applied Sciences(2013): 383-387. [2] Hwangbo, Hwan, et al. \"Toward Universal Design in Public Transportation Systems: An Analysis of Low Floor Bus Passenger Behavior with Video Observations.\" Human Factors and Ergonomics in Manufacturing & Service Industries 25" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002265_el-02275822_document-Figure6.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002265_el-02275822_document-Figure6.7-1.png", + "caption": "Figure 6.7 \u2013 Communication: Downstream segment estimated revenue for 2018 against potential degradative use impact. Most critical regions are the ones combining high potential impact and high economic efficiency", + "texts": [ + " 99 Figure 6.5 \u2013 Cumulative mass (Earth observation & Communication) vs Debris Flux in 2018. Debris size > 1cm, MASTER-2009 Model (BAU). Circles represent cumulative launch mass of active satellites per orbital cell .................................................................................................................................................................. 100 Figure 6.6 \u2013 Estimated revenue in 2018 for the EO and communication missions ..................................... 101 Figure 6.7 \u2013 Communication: Downstream segment estimated revenue for 2018 against potential degradative use impact. Most critical regions are the ones combining high potential impact and high economic efficiency .................................................................................................................................................................. 102 Figure 6.8 \u2013 Earth Observation: Estimated benefits for end-users against potential degradative use impact. Most critical regions are the ones combining high potential impact and high economic efficiency ", + " Moreover, the EO sector is today the most dynamic market in LEO (PwC, 2018; Werner, 2018) due to data exploitation and value-added services. Lastly, in the case of the EO, the benefits for the end-users (i.e. the whole society) is relevant to calculate because of the important share of non-commercial services provided. It is not the case for the communication satellites for which we consider the revenue of the downstream segment: companies provide communication services on a for-profit and competitive basis. Chapter 6: Towards an endpoint characterisation 102 Communication: economic valuation against degradative use impact Figure 6.7 shows the most critical areas in LEO, which correspond to the orbital cells combining high degradative use potential impact and economic importance. We observe a critical area at [800 km; 86\u00b0] corresponding to Iridium 1 st generation. It is not the case for Iridium Next [600; 86\u00b0] km. Since the new constellation orbits at lower altitude, the drag compensates the potential degradative use of the resource which explains the low CF value (less than 0.01 fragment-years). However, it generates as much revenue as Iridium 1 st generation", + " To apply these growth rates for the overall orbital cells, the maturity of each EO technology should be assessed similarly to what has been done with the \u201cquality score\u201d. A \u201cmaturity score\u201d determining the growth rate of the value in the following years could be applied. The same procedure could be applied for communication satellites to estimate the potential growth of revenues. Broadening the scope of the study, the orbital cells where future services will be developed should be considered within the Figure 6.7. Indeed, the communication sector in LEO should evolve quickly with the arrival of mega-constellations. The internet services, which will be provided continuously to all areas of the earth, could generate a consequent additional revenue for the midstream segment, especially if it supports the Internet-of-Things (IoT) revolution. For instance, the OneWeb constellation (which is being deployed) consists in more than 600 satellites of around 200 kg in mass which should orbit within the [1 200 km; 88\u00b0] orbital cell" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001149_rc53_01.14060801.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001149_rc53_01.14060801.pdf-Figure16-1.png", + "caption": "Figure 16. Geometry of the wideband out-ofphase power divider.", + "texts": [ + " Then the differential reflection coefficient |Sd11| can be obtained using the Equation (1). Fig. 15 displays the simulated and measured results of the designed antenna. It can be observed that the fabricated antenna achieved a wideband performance from 3.1 to 12 GHz for |Sd11| < \u221210 dB. The discrepancy between measured and simulated results is probably owing to the fluctuation of the dielectric constant or tolerance in process. In the pattern measurement, because the differentially feeding signal is hard to be implemented directly, a wideband out-of-phase power divider as shown in Fig. 16 is used to measure the radiation characteristics of the differentially driven antenna [16]. As shown in Fig. 17, the two 180\u25e6 output ports (Port 2 and Port 3) of the divider are connected to the two inputs of the designed antenna. The measured radiation patterns in E- and H-planes at 3, 6, 9, 11, and 12 GHz are plotted in Fig. 18. It can be seen that, over the whole UWB band, the proposed antenna exhibits a stable omnidirectional radiation pattern in the H-plane and dipole-like radiation pattern in the E-plane, and the main beams are consistently stabilized on the broadside direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004177_-3-319-44431-4_5.pdf-Figure5.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004177_-3-319-44431-4_5.pdf-Figure5.9-1.png", + "caption": "Fig. 5.9 Illustration of the effect of tracking on the fringe frequency at the correlator output. The u component of the baseline is shown, and the v component is omitted since it does not affect the fringe frequency. The curved arrow indicates the tracking motion of the antennas.", + "texts": [ + "u; v/, any pair of antennas measures visibility along two arcs symmetric about the .u; v/ origin, both of which are included in the spatial transfer function. Because the antennas track the source, the antenna beams remain centered on the same point in the source under investigation, and the array measures the product of the source intensity distribution and the antenna pattern. Another view of this effect is obtained by considering the radiation received by small areas of the apertures of two antennas, the centers of which are A1 and A2 in Fig. 5.9. The antenna apertures encompass a range of spacings from u d to u C d wavelengths, where d is the antenna diameter measured in wavelengths. If the antenna beams remain fixed in position as a source moves through them, then the correlator output is a combination of fringe components with frequencies from !e.u d / cos \u0131 to !e.uCd / cos \u0131, where!e is the angular velocity of the Earth and \u0131 is the declination of the source. To examine the effect when the antennas track the source, consider the point B, which, because of the tracking, has a component of motion toward the source equal to " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure20-1.png", + "caption": "Figure 20. The maximum stress simulation results in the main stem are 27.5 MPa", + "texts": [ + " Rear body mount The rear body mount receives a load of 68.67 N, which acts in the y-axis direction. This part only consists of one rod to support the rear body. The simulation results obtained are bending moment, maximum stress, and displacement, respectively, the values are 3505.57 N.mm, 1.10 MPa, and 0.0044 mm. Figure 19 shows the simulation results of the maximum stress value on the driver's footrest. 8. Main rod The force on the main rod is caused by the reaction force acting on the seven supporting rods. Figure 20 shows the loading on the main rod and the maximum stress value obtained. The simulation results on the main rod are the maximum bending moment and stress values of 128727.37 N.mm and 27.5 MPa, respectively. Based on the simulation results on the supporting rods and main rods carried out using Autodesk Inventor software, the calculation results were obtained in the form of bending moment, maximum stress, and displacement values, as shown in Table 3 and Table 4. static load analysis in the form of maximum bending moments for seven types of supporting rods and main rods that the main rod produces the highest maximum bending moment value compared to the seven types of supporting rods" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure18-1.png", + "caption": "Figure 18: FEA boundary condition set up for conceptual design.", + "texts": [ + "5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004366_om_article_24051_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004366_om_article_24051_pdf-Figure1-1.png", + "caption": "Fig. 1. Gland seals: a) gland packing sample 1; b) gland seal sample 2; c) proposed gland packing sample 3", + "texts": [], + "surrounding_texts": [ + "In order to eliminate the leakage of working fluid in the hydraulic system of quarry hydraulic excavators, to prevent the entry of contaminating particles in the form of dust into the system, vacuum seals made of domestic raw materials, resistant to high pressure, sharply changing temperature and absorption have been developed. The dimensions of the developed packing gland seal have the same value as the dimensions of the applied basic packing gland seal. The developed sealant is prepared in the following composition: SKMS-30 (rubber), sulphur, DFG, stearic acid, ZnO and fillers. The composition and amount of filler is as follows: Calcite, zinc oxide ZnO, ankerite (Cf(Vg,Fe)[CO3]2), zinc sulphate ZnS, amorphous carbon, fluorite, graphite-3h (crystalline), quartz end potassium sulphate K2SO4. The gland seals were manufactured at Navoi Machine-Building Plant of Navoi Mining and Metallurgical Plant JSC. The developed packing gland seal has the following technical characteristics: resistant to pressure up to 350 bar at 60 \u00b0C, fluid leakage rate is 0.5 m/s, operating temperature range from - 35 \u00b0C to +100 \u00b0C, adapted to the environment of mineral oils and hydraulic fluids. In order to determine the efficiency of the developed gland seal, experimental tests were carried out. In the experimental work, the proposed packing gland seal sample 3 (Fig. 2(c)), packing gland seal sample 2 (Fig. 2(b)), and packing gland seal sample 1 (Fig. 2(a)) were investigated. Sample 2 The seal is a material from a group of thermoplastic polyurethane elastomers of the TPU type. It is characterized by special wear resistance, excellent mechanical properties, extremely low residual deformation pressure and high tear resistance. 1-a sample of the seal is examined in the process of determining the specific composition 3-a sample of the seal specified above The experimental work was carried out in several stages, at the first of which the relative elongation of gland seals was studied. Relative elongation was determined on the RMI-250 elongation testing machine for rubber materials. Tests of rubber materials were carried out on RMI-250 machines. The rupture testing machine for rubber of the RMI- 250 type is designed to determine the tensile strength and deformation of rubber and samples from rubber products according to the methodology set out in GOST 270-64. In addition, the machine can be used: 1) for testing textiles, rubberized fabrics, leather, plastics and other materials; 2) for testing the layering of duplicated fabrics, duplicated rubbers with fabrics; 3) with the use of special devices, it is possible to test: a) for rupture \u2013 samples in the form 254 ISSN PRINT 2345-0533, ISSN ONLINE 2538-8479 of rings and some ring-shaped finished products; b) compression \u2013 rubber and other materials; c) fracture \u2013 ebonite and plastic. The machine is manufactured according to the basic parameters and accuracy standards in accordance with the requirements of GOST 7762-55. The experimental and testing work was carried out as follows, the investigated sample of the removable seal was placed in the RMI-250 brand rubber materials elongation testing machine. The tensile force of the specimen was increased from 5 kg/N at each step, starting from giving it a value of 5 kg/N to a tensile force of 30 kg/N. Based on the results of the experimental work presented in Fig. 2, the dependence of the relative elongation index on the force given to stretching of the samples of the investigated gland seal was established. As can be seen from the graph shown in Fig. 2 of the dependence of the relative elongation of the seals on the force applied to the tension, the relative elongation of the seal proposed by us is close to the relative elongation of the seal of sample 2, which means that we can effectively apply the proposed seal according to this indicator. The effective operation of the gland seals used in the hydraulic system is significantly affected by temperature conditions. In a hydraulic system, a sharp increase in the temperature of the working fluid or the parts on which the gland seals are applied leads to burning of the gland seals, as a result of which their elasticity is lost and their hardness increases [5-11]. This shortens the service life of these seals and also leads to leakage of operating fluid in the hydraulic system [12-17]. Sharp low temperatures also lead to loss of elasticity of gland seals. In the Kyzylkum region the temperature of the atmosphere changes sharply, reaching +45 \u00b0C and higher in the summer heat and cooling to \u201320-25 \u00b0C in cold winter days. At the next stage of experimental work the change of properties of gland seals under the influence of temperature was investigated. In the first stage of this experimental work the effect of high temperatures on the gland seals was studied. During the experimental work, several types of packing gland seals measured the stiffness of hydraulic fluid in the range from an initial temperature of 50 \u00b0C to a temperature of 90 \u00b0C, at which temperature was exceeded by 10 \u00b0C. The following measuring instruments and materials were used during the experimental and testing works: Tellus 68 brand hydraulic fluid, UNI-T UT325 thermometer, magnetic mixing oven E1-6220, ASTM 2240 durometer, gfland packing gasket samples, stopwatch and auxiliary equipment. The hardness of the compactors was measured several times at each temperature on the shore, the initial hardness of the sample, measured on the shore (X.F. gr\u2219N) sample 1 was found to be 90, sample 2 was found to be 85, and sample 3 was found to be 70, and the dependence of the rigidity of the studied compactors on higher temperatures is given in Fig. 3. VIBROENGINEERING PROCEDIA. APRIL 2024, VOLUME 54 255 During test-experimental works the initial hardness of packing gland seals was measured at air temperature 30 \u00b0C, and it was found that the initial hardness of our proposed packing gland seal was 70 on the shore, while in this case the hardness of packing gland seal of sample 2 company was 85, and the compactor hardness in sample 1 was 90 on the shore. As can be seen from the graph above, the hardness of the gland seals increases with an increase in temperature of more than 70 \u00b0C. As mentioned earlier, an increase in the hardness of the gland seals degrades their performance. No significant change was observed under the influence of temperature with respect to the initial hardness of the proposed packing gland seal. Thus, the addition of 1.21 % ankerite (Cf(Vg, Fe)[CO3]2), 0.39 % zinc sulphate (ZnS) and 0.22 % potassium sulphate (K2SO4) 0.22 % elements in their composition during the development of gland seals eliminates the fragmentation of gland seals under the influence of high temperatures. temperature. At the next stage of experimental work the influence of low (cold) temperatures on gland seals was studied. In this case, the change in hardness of the studied gland seals was determined at temperatures of 10 \u00b0C, 0 \u00b0C, \u201310 \u00b0C and \u201320 \u00b0C. In the experimental work, coolant was used to cool the packing gland compilers, while the temperature that the coolant will create was studied using a thermostat. From the experimental results, it was found that the hardness of the packing gland seal shown in Fig. 4 is dependent on the low temperature. From the graph shown in Fig. 4, it can be seen that when exposed to low temperatures, the hardness of the gland seals increases, causing them to become brittle. 256 ISSN PRINT 2345-0533, ISSN ONLINE 2538-8479" + ] + }, + { + "image_filename": "designv8_17_0004255_cle_download_175_155-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004255_cle_download_175_155-Figure1-1.png", + "caption": "Figure 1 Three-dimensional model of agricultural aircraft", + "texts": [ + " NACA4415 was used for the wing, the installation angle of the wing was \u20132.87\u00b0, and NACA0012 was used for the vertical tail and flat tail airfoil. The specific design parameters are shown in Table 1. For the convenience of research, the influence of aircraft propeller slipflow is ignored, and the propeller and its accessories are omitted. According to the structure and design parameters of the aircraft, reverse engineering is used to obtain the appearance of the aircraft in SolidWorks, as shown in Figure 1. The aircraft is regarded as a rigid body, and its forces during flight are shown in Figure 2, which mainly include the gravity of the aircraft itself G, the thrust of the engine T, the lift force perpendicular to the velocity direction L, the drag force parallel to the velocity direction D, the side force perpendicular to the flight plane of the aircraft C, and the forces of the landing gear and the ground during take-off and landing. Lift force L, drag force D and side force C are collectively referred to as aerodynamics of the aircraft[8]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000274___lang_en_format_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000274___lang_en_format_pdf-Figure1-1.png", + "caption": "Figure 1. Analyzed B-pillar with indication of the positions from where samples were taken (side wall: samples 01, 06, 13, 16, 18; flange: samples 02, 03, 04, 07, 08, 12, 17; top: samples 05, 09, 15; radius: samples 10, 11, 14).", + "texts": [ + " The composition of their constituting 22MnB5 steel, obtained by inductively coupled plasma optical emission spectroscopy (ICP-OES) in a Foundry-Master Pro spectrometer, is shown in Table 1. Prior to the analysis, the Al-Si coating was mechanically removed from the part\u2019s surface with a 180-grit sandpaper. The part\u2019s thickness, measured in different regions with the aid of a caliper, ranged between 1.04 and 1.12 mm, and its length was around 1250 mm. The as-received B-pillar, with the indication of positions from which samples for subsequent analyses were taken, is shown in Figure 1. Eighteen (18) spots were chosen along the pillar\u2019s body. They were divided into four groups, according to the part\u2019s feature in which they were located: \u2022 Side wall: samples 01, 06, 13, 16, 18; \u2022 Flange: samples 02, 03, 04, 07, 08, 12, 17; \u2022 Top: samples 05, 09, 15; \u2022 Radius (either top or bottom): samples 10, 11, 14. In order to verify the hot stamping conditions in which the B-pillar was manufactured, numerical simulations were performed using the Simufact Forming software. These analyses were carried out to correlate the results of a reverse engineering approach with the most likely distribution of strain and cooling rates along the workpiece during the 3 Microstructural Evolution of a Hot-Stamped Boron Steel Automotive Part and Its Influence on Corrosion Properties and Tempering Behavior forming process", + " In Simufact software, this step corresponds to a simulation called \u201ccooling\u201d, into which results of the previous deformation step were imported. In this process, the time during which the sheet stays inside the dies was determined as 10 seconds, based on experiences from previous works and on the studies by Park et al.32, and Wang and Ma33. All other previously determined parameters were kept constant. Provided that automotive parts are commonly joined by resistance spot welding (RSW), the martensitic tempering behavior in typical welding positions (regions 01, 02, 07, 08, 15 and 16 in Figure 1) was assessed via physical simulation. For the simulation, coupons with dimensions of 25 \u00d7 60 mm were cut from a second B-pillar, assumed to be identical to the one shown in Figure 1, with an abrasive cutting wheel. A thermal cycle corresponding to the one observed 5 Microstructural Evolution of a Hot-Stamped Boron Steel Automotive Part and Its Influence on Corrosion Properties and Tempering Behavior in the SCHAZ was reproduced in a Gleeble\u00ae 540 physical simulator. Experiments were done using copper grips and K-type thermocouples spot-welded to the mid-length and mid-width of coupons. The free span between grips was of 20 mm. All experiments were carried out at ambient conditions, without vacuum", + " In these regions, the forming behavior becomes of the deep drawing type, which explains these concentrations. In terms of deformations observed in the Forming Limit Diagram (FLD), the same effects observed above occur, only with different numerical values. Figure 6 shows these values. This behavior is in accordance with other studies, such as those by Park et al.32 and Wang and Ma33, in which the shape of the part was similar to the one studied in this paper. stamping process Optical microscopy images of some of the regions indicated in Figure 1 are shown in Figure 7. Nital etchant reveals ferrite and martensite in most carbon and low alloy steels and is also useful to reveal the microstructure of bainitic steels. Bramfitt and Benscoter35 clarify that it etches ferritic grains and boundaries, and does not attack austenite. However, besides austenite, another microconstituent known as martensite-austenite (M-A), might also be present in these steels and appear as a non-etched structure36. Due to the extreme refinement of the martensite in M-A, the structure usually appears as non-etched blocks, quite similar to pure austenite, being more easily distinguished by electron backscatter diffraction (EBSD)37 or after a slight tempering treatment before etching38" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000754_40396_type_printable-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000754_40396_type_printable-Figure5-1.png", + "caption": "Fig 5. Computational regional boundary constraints. a) Valve components; b) fluid-structure interaction.", + "texts": [ + " According to the literature [19], in order to reduce the level of complexity of the solution of a 3D problem in PLOSONE | DOI:10.1371/journal.pone.0140396 October 21, 2015 6 / 20 axisymmetric structure, it can translate the 3D problem to a 2D problem by setting correction factors. The plunger chamber, valve body, and discharge chamber are all symmetric geometric cylinders, allowing the fluid-structure interaction model to be simplified into a 2D plane model. 2.2.2 Boundary conditions and meshing. As shown in Fig 5(A), the valve body reciprocates only in the Y direction; therefore other constraints are imposed on the valve body in addition to the y direction. Fig 5(A) illustrates the constraints imposed upon the valve body and doi:10.1371/journal.pone.0140396.g004 doi:10.1371/journal.pone.0140396.g005 PLOSONE | DOI:10.1371/journal.pone.0140396 October 21, 2015 7 / 20 valve seat. The large displacement hypothesis was proposed for valve motion, while the conical outer edge of the valve body is defined as a surface of fluid-structure interaction. Additionally, the load constraints on the valve body (i.e., gravity, spring pre-load and variable load) were defined by the time function plot-1, demonstrated by Fig 6(A). The spring pre-load is coupled at the center point of the upper surface of the valve body, as shown in Fig 5(B); this is completed by setting the installation distance of the connecting parts of the spring. The spring load was then applied through the valve motion; gravity is automatically loaded by inputting the density and directions of valve acceleration into the ANDINA software. doi:10.1371/journal.pone.0140396.g006 PLOSONE | DOI:10.1371/journal.pone.0140396 October 21, 2015 8 / 20 According to the working principles of the hydraulic end of the plunger pump, the plunger displacement is a sinusoidal function which varies with time; therefore the entire displacement of the moving wall is a sinusoidal function which varies with time, and is defined by time function 2, depicted in Fig 6(B)", + "4 Effects of spring stiffness on impact contact of valve Dynamics analysis of the discharge valve motion demonstrated that impact contact occurred during the reciprocating movement between the valve body and the valve seat, and that impact contact was the primary cause of damage to the valve assembly. Therefore, contact analysis of valve assembly was conducted for various pump valve spring stiffness values. Valve assemblies include the valve body, a sealing gasket and the valve seat; the material of the valve body and seat is 20CrMnTi, while the sealing gasket is made of polyurethane rubber. The boundary conditions and constrains of valve impact contact analysis are shown in Fig 5(B). According to the actual operating conditions of the hydraulic end of the plunger pump, the seating velocity of the valve body with various spring stiffness values is 1m/s, 0.6m/s,0.5m/s and 0.4m/s. The maximum stress-strain curve of different pump valve seating velocities is shown in Fig 16, based on ABQUS finite element analysis (S6 Fig). Results indicate that the impact contact stress and strain of the valve body and valve seat increase with an increase in seating velocity; however, the increased amplitude is small, and far less significant that the yield stress of the material" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002647__download_11082_4171-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002647__download_11082_4171-Figure1-1.png", + "caption": "FIG 1: Diagram representation of single element in circular patch.", + "texts": [], + "surrounding_texts": [ + "By the diversity technique the standard communication channels are improved[1].By using two cross polarizations the decoupling of the communication channels can be done. Two cross polarizations are provided with two dual polarised antennas[2].This information of polarization can be improved with different classification[3].To analyse that antennas that exhibit less crosstalk between various polarizations are necessary to design highly complex antenna structures, microstrip technology is the best choice because of its low cost and less weight. A sophisticated compactness and feasibility and reliable control of the parameters are the major challenges in designing and developing the planar dual polarized arrays. Several designs require more area for their feeding or they used to propose another signal layer. Two expensive materials with high natural frequencies are added together by this crosstalk can be created. The crosstalk suppression is improved because of second layer by using series microstrip antennas are fed single polarized arrays. The dual polarization can be obtained by second order technique, but it is more difficult to fabricate. Accurate dimension should be maintained among the feeding layer and antenna. Substrate integrated wave guide is another feeding technique for single radiators[4].Single polarization is done by using first technique and second technique gives the information about the spacing between the surfaces. Grid antennas are the printed with substrate on one side and ground plane on other side[5].The sidelobes of antenna array should be less than -13.5db.Feeding system consists microstrip feed lines, carefully adjusted for each and every element with a goal of analysing dolphchebychev distribution[6].The proposed antenna is dual polarized antenna in section II. The design steps and explanation of radiating components are fed and shown in section III. The measurement of scattering components are explained in section IV, which describes the measurement of radiation properties of an antenna. 2. Design of array column: Some preliminary measures of antenna array are proposed. The antenna is having ten elements with phase and amplitude. Each and every element is excited in the antenna[7]and [8].The figure gives us the detail about the antenna array. Theses an- tennas are labeled with index numbers from 1,2\u2026..N are represented in X direction. The selected design consists of ten single elements having certain amplitude and decrease in sidelobes takes place in each separation. The series arrangement of these ten elements having fanebeam and narrow halfpower beamwidth \u03d5=0 and broad for \u03d5=90." + ] + }, + { + "image_filename": "designv8_17_0000838_NGU05_2021_Fomin.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000838_NGU05_2021_Fomin.pdf-Figure1-1.png", + "caption": "Fig. 1. A Y25 bogie", + "texts": [ + " The mathematical modelling of the dynamic loads on the carrying structure of a boxcar with the design dimensions on the 18\u2013100 and Y25 bogies. 2. The mathematical modelling of the dynamic loads on the carrying structure of a boxcar with the actual dimensions on the 18\u2013100 and Y25 bogies. 3. The comparative analysis of the modelled dynamic loads for a boxcar with different bogie types. Results. The dynamic characteristics of the basic Ukrai nian freight cars can be improved on the basis of research into a possibility to use the Y25 bogie (Fig. 1). The bogie has a stampwelded frame. The primary one stage spring suspension is equipped with a friction wedge os cillation distinguisher. The bogie frame is rested on the axle box lugs through the cylindrical springs. The axlebox body is placed in the axlebox guide and has vertical travel restrains. The bogie is equipped with constant contact bearers. The basic technical characteristics of the Y25 bogie are given in Table 1 [8]. Unlike European Y25 bogies, the bogies manufactured in CIS countries have moulded side frames, bolster beam and brake shoes with unilateral pressure [9]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001913_cle_download_433_496-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001913_cle_download_433_496-Figure1-1.png", + "caption": "Fig. 1 - Turbine blade in the Cartesian coordinate system \u0430) three-dimensional model of cooling turbine blade; b) transverse section of the shoulder blade", + "texts": [ + " Full description of the finite elements that are suitable for the impeller correct modeling is given in the works [8 \u2212 10]. Study. The task of the gas turbine impeller stress-strain state determining is given. It is also assumed that the considered system of solid bodies (impeller) has the properties of cyclic symmetry. So it can be interpreted as a set of h subsystems (sections) with the same geometric, inertial and stiffness properties [7]. In this case, h determines the system order of symmetry. So a section of such impeller generally includes a disk sector and a blade set in it with parts of damper links (fig. 1). The section is located in the rectangular right X Y Z coordinate system: X axis coincides with the axis of turbine rotor rotation, Z axis is directed along the impeller radius, and the Y axis is perpendicular to the Z axis. The finite element model of an impeller blade was built on the basis of superparametric curvilinear finite elements. Each of them consisted of 20 nodes with 5 degrees of freedom in every node. The damper links, connecting the blades in a unity were modeled using a rod finite element" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003704_86_s40648-016-0055-1-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003704_86_s40648-016-0055-1-Figure2-1.png", + "caption": "Fig. 2 Parameters of ring and shaft parts", + "texts": [ + " proposed design of handling device for caging and aligning small circular objects [13]. By designing the triangular finger tips, their hand can grasp a small object robustly at a unique position of the tips. Although these conventional studies solve the problem of self-alignment of a part with gripper, the problem of alignment with other part is not considered. On the other hand, our proposed hollowed finger can align centers of a part and another part. The capability of self-alignment between two parts by using the hollowed finger is our original. Figure\u00a02 and Table\u00a01 show parameters and sizes of a ring part and a shaft part dealt with in this research. As shown in Table\u00a01, diameters of a ring part and a shaft part have size tolerance based on the Japanese Industrial Standards (JIS). Ring assembly has two states: mating and inserting. Mating is a state that is most difficult in ring assembly. A definition of the state is that length of insertion is less than height of a ring. In the state, jamming, which is a situation that assembly is fixed because a state of a ring part and a shaft part is not desirable, occurs easily" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003220_20JIYE_G1103158C.pdf-Figure4.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003220_20JIYE_G1103158C.pdf-Figure4.12-1.png", + "caption": "Figure 4.12 Von Mises stress distribution", + "texts": [ + "............................. 46 Figure 4.9 Stress distribution between two TSVs. From (a) to (f), the TSV diameter changes from 4\u03bcm to 9\u03bcm, and the pitch is 3 times of diameter. ................................ 47 Figure 4.10 Biaxial stress of PETEOS liner TSV sample. .......................................... 47 Figure 4.11 Stress distribution between two TSVs. From (a) to (f), the TSV diameter changes from 4\u03bcm to 9\u03bcm, and the pitch is 3 times of diameter. ................................ 48 Figure 4.12 Von Mises stress distribution ................................................................... 50 Figure 4.13 (a) Thermal mechanical stress distribution as a function of distance from the TSV edge (diameter: 6, 8, and 10\u03bcm) with PETEOS and low-K dielectric liners. (b) Comparison of the stress profile of FEA simulation against experimental results for 10 \u03bcm-diameter TSV having PETEOS or Low-K liner. ........................................ 51 Figure 4.14 The thermal stress in Silicon as measured by \u03bc-Raman spectroscopy along the [110] and [100] direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004935_v.org_pdf_2404.10081-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004935_v.org_pdf_2404.10081-Figure1-1.png", + "caption": "Fig. 1 Assembly drawing of the iATVA system and its components. A circular array of magnets couples the turbine and pump impellers. The turbine and pump employ dedicated bearings and housings with complete separation of arterial and venous blood in the device. The trailing and leading edges of the turbine and pump blades are marked in the figure together with the respective rotation directions.", + "texts": [ + " Later, we compared three different turbine sections to extend our investigation in turbine flow dynamics. To obtain quantitative comparisons, we compared shear rate, jet flow, and backflow magnitudes for different operating conditions and impeller phases. Finally, we suggested fluid dynamic design improvements for the future iATVA versions. The original iATVA design, reported in (Pekkan et al. 2018) which incorporates 14 neodymium magnets for coupling turbine and pump impellers, was revised for PIV experiments (see Fig. 1). A protocol for manufacturing optically transparent 3D printed PIV pump prototypes was Page | 5 already developed in our recent work on FDA benchmark blood pump (Ucak et al. 2024) which is also applied to the present iATVA system. Briefly, the casings of the turbine and pump sides were altered with flat surfaces to eliminate the light reflections. Clear Resin V4 was used to print the models using a stereolithography printer (Form 3, Formlabs, Massachusetts, US) at a layer thickness of 25 microns, and the iATVA parts were then cured", + " Eventually, with further refinement, we envision this technology will fully support pulmonary blood flow in patients with single ventricle defects, offering promising prospects and enhanced patient care. While the current analysis provided valuable insights, further investigations are needed to validate the new turbine design versions. Funding was provided by European Research Council (ERC) Proof of Concept BloodTurbine, and TUBITAK B\u0130DEB - 2247A - 120C139. List of Tables: Page | 16 List of Figures: Fig. 1 Assembly drawing of the iATVA system and its components. A circular array of magnets couples the turbine and pump impellers. The turbine and pump employ dedicated bearings and housings with complete separation of arterial and venous blood in the device. The trailing and leading edges of the turbine and pump blades are marked in the figure together with the respective rotation directions. Fig. 2 Selected views of the experiment set-up are provided. Two high speed cameras (HSC 1 and HSC 2), a hall-effect sensor-based trigger system controlled by an Arduino processor and the beam splitter are labeled", + " Other plots are comparisons of the sections with three different operating conditions, C1, C2 and C3. Fig. 8 Velocity profiles along three different lines for three different phases (P1, P2, P3). Phases are displayed in the left side figure. Suction, inter-blade and pressure lines are displayed on the right side for each phases. Radius (R) is defined the same as in Fig. 7. Pressure sections had missing points near to the beginning of the radius due to the shadows, thus they were eliminated from the dataset. Page | 18 Figure 1. E ploded side view of the iATVA system . oupled magnets separates the turbine and pump chambers, so fluids in both sides do not mi each other. The trailing and leading edge of the turbine and pump blades are marked with the rotation directions . Since usage of the magnetic couple, the rotation magnitudes are e ual each other. Page | 19 Page | 20 Page | 21 Page | 22 Page | 23 Page | 24 Page | 25 Page | 26 Atti, Varunsiri, Mahesh Anantha Narayanan, Brijesh Patel, Sudarshan Balla, Aleem Siddique, Scott Lundgren, and Poonam Velagapudi" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002274_736_73_736_3171__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002274_736_73_736_3171__pdf-Figure1-1.png", + "caption": "Fig. 1 Extended Reduced-Order Physical Model", + "texts": [], + "surrounding_texts": [ + "3171\n\u65e5\u672c\u6a5f \u68b0\u5b66\u4f1a\u8ad6\u6587\u96c6(C\u7de8)\n73\u5dfb736\u53f7(2007-12)\n\u8ad6\u6587 No.07-0389\n\u4efb\u610f\u5883\u754c \u3092\u6301\u3064\u5f3e\u6027\u4f53\u306e\u62e1\u5f35\u4f4e\u6b21\u5143\u5316\u7269\u7406\u30e2\u30c7\u30eb\u8a2d\u8a08\u6cd5*\n(\u7b2c2\u5831,2\u30ea \u30f3\u30af\u67d4\u8edf\u30ed\u30dc\u30c3\u30c8\u30a2\u30fc\u30e0\u306e\u904b\u52d5\u3068\u632f\u52d5\u306e\u5236\u5fa1)\n\u5b89 \u85dd \u96c5 \u5f66*1, \u6e21 \u8fba \u4ea8*2\n\u80cc \u6238 \u4e00 \u767b*3, \u7530 \u5cf6 \u6d0b*4\nModeling Method for Flexible Multibody Systems with Arbitrary Boundary\nConditions by Using Extended Reduced-Order Physical Model\n(2nd Report, Motion and Vibration Control of a Two-link Flexible Robot Arm)\nMasahiko AKI, Toru WATANABE*5, Kazuto SETO and Hiroshi TAJIMA\n*5 Department of Mechanical Engineering , Nihon University,\n1-8-14 Kanda Surugadai, Chiyoda-ku, Tokyo, 101-8308 Japan\nThis paper deals with the effectiveness of an Extended Reduced-Order Physical Model (Extended Model) with arbitary boundary condition for motion and vibration control system design. The Extended Model is proposed to apply to the simultaneous motion and vibration control of elastic structures. The Extended Model consists of some rigid bodies which are called as rigid body elements and stiffness elements. To design rigid body elements, four dynamical conditions are used (1) Total mass and Total moments of inertia, (2) Position of center of gravity, (3) Modal mass and Orthogonality, (4) Modal momentum and Modal angular momentum. The (1) - (4) values of a modeling object are needed to identify masses and moments of inertia of rigid body elements. In the case of that an elastic body has general boundary conditions, the Modal momentum and the Modal angular momenrum are not zero and needed to be identified by any means. However, it is not always easy to identify these values. Therefore, a novel formulation to identify mass and inertia matrices is presented that utilizes dynamical conditions for the original object. subjected to free boundary conditions. The presented formulation is applied to the modeling of the two-link flexible robot arm. Each flexible link is modeled by using the proposed modeling method. The two-link flexible robot arm is built by combining two independently identified link models. The effectiveness of \"an Extended Model with an arbitrary boundary condition\" is shown through the simulation and experimental control results.\nKey Words : Extended Reduced-Order Physical Model, Arbitrary Boundary Condition, Constraint Addition Method, Vibration Control, Motion Control, Multibody Dynamics, Flexible Structure, Two-link Flexible Robot Arm, Modeling\n1. \u7dd2 \u8a00\n\u5b87\u5b99\u7528 \u30ed\u30dc \u30c3 \u30c8\u30a2\u30fc\u30e0\u306f\u30a2\u30fc\u30e0\u3092\u9577\u8155\u5316,\u9ad8 \u901f\u5316\u3059 \u308b\u3068\u30a2\u30fc \u30e0\u306e\u67d4\u8edf\u6027\u3092\u7121\u8996\u3067 \u304d\u306a \u304f\u306a\u308b.\u3053 \u306e\u554f\u984c \u3092\n\u89e3\u6c7a\u3059 \u308b\u305f \u3081\u306b\u67d4\u8edf \u30a2\u30fc \u30e0\u306e\u7814 \u7a76\u304c\u76db\u3093 \u306b\u884c\u308f\u308c \u3066\u304d \u305f(1)\uff5e(8).\u3053\u308c \u3089\u306e\u67d4\u8edf\u30a2\u30fc \u30e0\u306f\u4f5c\u696d \u3092 \u3055\u305b \u308b\u3068\u540c\u6642\u306b \u632f\u52d5 \u304c\u767a\u751f\u3059 \u308b\u305f\u3081,\u904b \u52d5 \u3068\u632f\u52d5 \u306e\u540c\u6642\u5236\u5fa1 \u304c\u5fc5\u8981 \u3068 \u306a\u3063\u3066 \u304f\u308b.\u305d \u3053\u3067\u7b46\u8005 \u3089\u306f\u904b\u52d5 \u3068\u632f\u52d5 \u3092\u540c\u6642\u306b\u8868\u73fe \u3067\u304d,\u304b \u3064\u5236\u5fa1 \u306b\u9069 \u3057\u305f\u30e2\u30c7\u30eb \u3068\u3057\u3066\u62e1\u5f35\u4f4e\u6b21\u5143\u5316\u7269 \u7406\u30e2\u30c7\u30eb(\u4ee5 \u4e0b,\u62e1 \u5f35\u30e2\u30c7\u30eb)\u3092 \u63d0\u6848 \u3057\u3066\u3044\u308b(9). \u4e00\u822c \u306b\u30ed\u30dc \u30c3 \u30c8\u30a2\u30fc \u30e0\u306e\u30d1\u30e9\u30e1\u30fc \u30bf\u306f\u30a2\u30fc\u30e0\u540c\u58eb \u306e\u7d50\n\u5408\u89d2 \u03b8\u306e\u975e\u7dda\u5f62 \u95a2\u6570\u3067(10),\u525b\u4f53\u30a2\u30fc \u30e0\u3067\u3042\u3063\u3066\u3082\u305d\u306e \u5c0e \u51fa\u306f\u8907\u96d1\u3067\u3042\u308b.\u3055 \u3089\u306b,\u30a2 \u30fc \u30e0\u306b \u30d5\u30ec\u30ad\u30b7 \u30d3\u30ea\u30c6\n\u30a4\u304c\u5b58\u5728\u3059\u308b \u3068 \u300c\u03b8\u304c\u5909\u5316=\u5883 \u754c\u6761\u4ef6\u306e\u5909\u5316\u300d \u3068\u306a \u308a \u30a2\u30fc\u30e0\u306e\u632f\u52d5\u7279\u6027 \u3082\u5909\u5316\u3059 \u308b.\u3059 \u306a\u308f\u3061,\u67d4 \u8edf\u30a2\u30fc\u30e0 \u81ea\u4f53\u306e\u30d1 \u30e9\u30e1\u30fc\u30bf\u3082 \u03b8\u306b\u4f9d\u5b58 \u3057\u3066\u5909\u5316\u3059 \u308b\u3053\u3068\u3068\u306a \u308a, \u305d \u306e\u30e2\u30c7 \u30ea\u30f3\u30b0\u306f\u4e00\u5c64\u8907\u96d1 \u306b\u306a\u308b.\u4e00 \u65b9,\u7b46 \u8005 \u3089\u304c\u524d \u5831(11)\u3067\u63d0\u6848 \u3057\u305f \u300c\u4efb\u610f\u5883\u754c\u3092\u6301\u3064\u5f3e\u6027\u4f53\u306e\u62e1\u5f35\u4f4e\u6b21\u5143 \u5316\u7269\u7406\u30e2\u30c7\u30eb\u8a2d\u8a08\u6cd5\u300d\u306f\u30a2\u30fc\u30e0\u306e\u525b\u4f53\u904b\u52d5 \u3068\u5f3e\u6027\u632f\u52d5 \u3068\u3092\u4e00\u5143\u7684\u306b\u8a18\u8ff0 \u3057\u3046\u308b\u30e2\u30c7\u30eb\u3067\u3042 \u308a,\u3053 \u308c \u3068\u62d8\u675f\u6761 \u4ef6\u8ffd\u52a0 \u6cd5(12)\u3092\u4f7f \u3046\u3053\u3068\u3067,\u03b8 \u3055\u3048\u5206\u304b\u308c \u3070\u305d\u306e\u59ff\u52e2\u3067 \u306e\u30d1 \u30e9\u30e1\u30fc \u30bf\u304c\u4e00\u610f\u306b\u8a08\u7b97\u3067 \u304d,\u5408 \u7406\u7684\u306a\u30e2\u30c7 \u30ea\u30f3\u30b0 \u304c\u53ef\u80fd \u3068\u306a\u308b.\n\u524d\u5831 \u3067\u306f,\u4efb \u610f\u5883\u754c\u6761\u4ef6\u4e0b\u306e\u62e1\u5f35\u30e2\u30c7\u30eb\u306e\u8a2d \u8a08\u6cd5 \u3092 \u63d0\u6848 \u3057,\u57fa \u672c\u7684\u306a\u5883\u754c\u6761\u4ef6 \u3092\u6301\u3064\u30d9\u30eb\u30cc\u30fc\u30a4 \u30fb\u30aa\u30a4 \u30e9 \u30fc\u6881\u3092\u5bfe\u8c61 \u3068\u3057\u3066\u30e2\u30c7 \u30ea\u30f3\u30b0\u7cbe\u5ea6 \u306e\u691c\u8a3c \u3092\u884c \u3063\u305f.\u672c\n\u5831\u3067\u306f,\u3055 \u3089\u306b\u7058 \u306a\u5883\u754c\u6761\u4ef6 \u3092\u6301\u3063\u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61 \u3068\u3057\u3066,2\u30ea \u30f3\u30af\u67d4\u8edf\u30ed\u30dc \u30c3\u30c8\u30a2\u30fc\u30e0\u306b\u524d\u5831\u3067\u63d0\u6848 \u3057 \u305f\u624b\u6cd5 \u3092\u9069\u7528 \u3057\u305f.\u305d \u3057\u3066 \u3053\u308c \u3092\u5236\u5fa1\u5668\u8a2d\u8a08\u30e2\u30c7\u30eb \u3068 \u3057\u3066\u9069\u7528 \u3057,\u904b \u52d5 \u3068\u632f\u52d5\u306e\u540c\u6642\u5236\u5fa1\u3078\u306e\u6709\u52b9\u6027 \u3092\u691c\u8a3c\n* \u539f\u7a3f \u53d7\u4ed8 2007\u5e744\u670820\u65e5.\n*1 \u6b63 \u54e1 ,\u65e5 \u672c \u5927 \u5b66 \u5927\u5b66 \u9662 \u7406 \u5de5\u5b66 \u7814 \u7a76 \u79d1(\u3013101-8308\u6771 \u4eac\u90fd \u5343\n\u4ee3 \u7530\u533a\u795e \u7530\u99ff\u6cb3 \u53f01-8-14). *2 \u6b63\u54e1 ,\u65e5 \u672c\u5927 \u5b66\u7406\u5de5 \u5b66\u90e8. *3 \u6b63\u54e1\n,\u540d \u8a89\u54e1,(\u6709)\u80cc \u6238 \u632f\u52d5 \u5236\u5fa1\u7814 \u7a76\u6240(\u3013140-0004\u6771 \u4eac \u90fd\n\u54c1\u5ddd \u533a\u5357 \u54c1\u5ddd5-8-4\u30b0 \u30ec\u30fc\u30b91\u30ac\u30fc\u30c7 \u30f3\u30bc\u30fc \u30e0\u30b9\u5742408\u53f7). *4 \u6b63 \u54e1\n,\u6771 \u4eac \u5927 \u5b66\u751f \u7523 \u6280 \u8853\u7814 \u7a76 \u6240(\u3013153-8505\u6771 \u4eac \u90fd \u76ee\u9ed2 \u533a\n\u99d2\u58344-6-1).\nE-mail:toruw@mech.cst.nihon-u.ac.jp", + "3172 \u4efb\u610f\u5883\u754c\u3092\u6301\u3064\u5f3e\u6027\u4f53\u306e\u62e1\u5f35\u4f4e\u6b21\u5143\u5316\u7269\u7406\u30e2\u30c7\u30eb\u8a2d\u8a08\u6cd5(\u7b2c2\u5831)\n\u3057\u305f\u306e\u3067\u5831\u544a\u3059\u308b.\n2. \u62e1\u5f35\u4f4e\u6b21\u5143\u5316\u7269\u7406\u30e2\u30c7\u30eb\n\u62e1\u5f35\u30e2\u30c7\u30eb\u306f\u5f3e\u6027\u4f53\u306e\u904b\u52d5\u3068\u632f\u52d5\u306e\u540c\u6642\u5236\u5fa1\u306e\u305f\u3081 \u306b\u63d0\u6848\u3055\u308c\u305f\u30e2\u30c7\u30eb\u3067\u3042\u308b.\u62e1 \u5f35\u30e2\u30c7\u30eb\u306f,\u5f3e \u6027\u4f53\u306e \u632f\u52d5\u3092\u8868\u73fe\u3059\u308b\u525b\u4f53\u8981\u7d20,\u304a \u3088\u3073\u525b\u6027\u8981\u7d20\u304b\u3089\u69cb\u6210\u3055 \u308c\u308b(\u56f31).\u525b \u4f53\u8981\u7d20\u306f\u5f3e\u6027\u4f53\u4e2d\u306b\u8a2d\u5b9a\u3055\u308c\u305f\u57fa\u6e96\u5ea7 \u6a19\u4e0a\u306b\u8a2d\u7f6e\u3055\u308c,\u3053 \u308c\u3092\u7528\u3044\u3066\u5f3e\u6027\u4f53\u306e\u5927\u904b\u52d5\u3068\u632f\u52d5 \u304c\u8a18\u8ff0\u3055\u308c\u308b.\u3053 \u3053\u3067\u306f,1\u6b21 \u5143\u632f\u52d5\u3092\u4f8b\u3068\u3057\u3066\u8aac\u660e\n2\u30fb1 \u4efb\u610f\u5883\u754c \u3092\u6301\u3064\u5f3e\u6027\u4f53\u306e\u525b\u4f53\u8981\u7d20\u8a2d\u8a08\u6cd5(11)\n\u525b\u4f53\u8981\u7d20\u306e\u8cea\u91cf \u30fb\u6163\u6027\u30e2\u30fc\u30e1\u30f3 \u30c8\u3092\u540c\u5b9a\u3059\u308b\u306b\u306f\u56db \u3064\u306e\u529b\u5b66\u7684\u6761\u4ef6\u304b \u3089\u5c0e\u304b\u308c \u305f\u5f0f \u3092\u6e80\u8db3\u3059 \u308b\u89e3 \u3092\u6c42 \u3081\u308b\n\u3053 \u3068\u304c\u5fc5\u8981\u3067 \u3042\u308b.[1]\u525b \u4f53\u8981\u7d20 \u306e\u7dcf\u8cea\u91cf \u3068\u7dcf\u6163\u6027\u30e2 \u30fc \u30e1\u30f3 \u30c8\u3092\u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61 \u306e\u305d\u308c\u306b\u4e00\u81f4 \u3055\u305b \u308b .\u3053 \u308c \u306f\u5f0f(1)\u306e\u4e00\u884c \u76ee\u304b \u3089\u4e8c\u884c \u76ee\u3067\u3042\u308b.[2]\u525b \u4f53\u8981\u7d20\u5168\u4f53 \u306e\u91cd\u5fc3\u4f4d \u7f6e \u3068\u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61 \u306e\u91cd \u5fc3\u4f4d\u7f6e\u3092\u4e00\u81f4 \u3055\u305b \u308b. \u3053\u308c\u306f\u5f0f(1)\u306e\u4e09\u884c \u76ee\u3067\u3042\u308b.[3]\u525b \u4f53\u8981\u7d20\u304b \u3089\u8a08\u7b97 \u3055 \u308c \u308b\u632f\u52d5\u30a8\u30cd\u30eb\u30ae\u30fc\u3092\u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61 \u306e\u305d\u308c\u306b\u4e00\u81f4 \u3055 \u305b \u308b.\u3053 \u306e\u6761\u4ef6\u304b \u3089\u30e2\u30fc \u30c9\u8cea\u91cf \u3068\u76f4\u4ea4\u6027 \u306e\u6761\u4ef6\u304c\u5c0e\u304b \u308c \u308b.\u3053 \u308c \u306f\u5f0f(1)\u306e\u56db\u884c \u76ee\u304b \u3089\u4e94\u884c \u76ee\u3067\u3042 \u308b.[4]\u525b \u4f53\u8981\u7d20 \u304b\u3089\u8a08\u7b97 \u3055\u308c \u308b\u5358\u4f4d\u30e2\u30fc\u30c0\u30eb\u30d1 \u30e9\u30e1\u30fc \u30bf\u5f53\u305f \u308a \u306e\u904b\u52d5\u91cf(\u4ee5 \u4e0b,\u30e2 \u30fc \u30c9\u904b\u52d5\u91cf)\u3068 \u89d2\u904b\u52d5\u91cf(\u4ee5 \u4e0b, \u30e2\u30fc \u30c9\u89d2\u904b\u52d5\u91cf)\u3092 \u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61 \u306e\u305d\u308c\u306b\u4e00\u81f4 \u3055\u305b \u308b.\u3053 \u308c\u306f\u5f0f(1)\u306e\u516d\u884c \u76ee\u304b \u3089\u4e03\u884c \u76ee\u3067\u3042 \u308b.\n(1)\n\u3053\u306e \u3068\u304d,Mactual\u306f \u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61 \u306e\u5b9f\u8cea\u91cf\u3067 \u3042 \u308a, Jactual\u306f\u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61\u306e\u5b9f\u6163\u6027\u30e2\u30fc \u30e1\u30f3 \u30c8\u3067\u3042 \u308b. MA,JA\u306f \u305d\u308c\u305e\u308c\u525b\u4f53\u8981\u7d20\u306e\u8cea\u91cf \u3068\u525b\u4f53\u8981\u7d20\u306e\u91cd\u5fc3 \u4f4d\u7f6e \u306b\u304a \u3051\u308b\u6163\u6027\u30e2\u30fc \u30e1\u30f3 \u30c8\u884c\u5217\u3067 \u3042\u308b.XA\u306f \u57fa\u6e96 \u5ea7\u6a19\u304b \u3089\u5404\u525b\u4f53\u8981\u7d20\u307e\u3067\u306e\u8ddd\u96e2\u3067\u3042\u308b.(')\u306f \u30d9 \u30af \u30c8\u30eb \u306b\u4f5c\u7528 \u3055\u305b,\u525b \u4f53\u8981\u7d20\u6570 \u306e\u5bfe\u89d2\u884c\u5217\u3092\u4f5c\u6210\u3059 \u308b\u305f\u3081\u306e\n\u30aa\u30da \u30ec\u30fc\u30bf\u3067\u3042\u308b.\u3053 \u308c \u3089\u306e\u95a2\u4fc2\u306f\u4ee5\u4e0b\u306e\u3088 \u3046\u306b\u8868\u73fe \u3067 \u304d\u308b.\n\u307e\u305f,\u03a6A\u306f \u525b\u4f53\u8981\u7d20\u4f4d \u7f6e\u306b\u304a\u3051\u308b\u30e2\u30fc \u30c9\u884c\u5217\u3067\u3042 \u308a, \u03a6'A\u306f\u525b\u4f53\u8981\u7d20\u4f4d\u7f6e\u306b\u304a\u3051 \u308b\u57fa\u6e96\u5ea7\u6a19\u304b \u3089\u306e\u30e2\u30fc \u30c9\u5f62\u306e\n\u50be \u304d(\u4ee5 \u4e0b,\u30e2 \u30fc \u30c9\u52fe\u914d\u884c\u5217)\u3067 \u3042 \u308a,\u03bc \u306f\u30e2\u30fc \u30c9\u8cea\u91cf \u884c\u5217 \u3067\u3042\u308b.\n\u5f0f(1)\u3092\u89e3 \u304f\u3053\u3068\u3067\u525b\u4f53\u8981\u7d20\u306e\u8cea\u91cf \u30fb\u6163\u6027 \u30e2\u30fc \u30e1\u30f3 \u30c8\n\u304c\u5f97 \u3089\u308c \u308b.\u3053 \u306e \u3068\u304d,Moore-Penrose\u4e00 \u822c\u9006\u884c\u5217 \u3092\u7528 \u3044\u3066\u3044\u308b.\u305f \u3060 \u3057,\u81ea \u7531\u5883\u754c\u306b\u304a\u3051\u308b\u30e2\u30fc \u30c9\u5f62 \u03a6fA\u306f \u3042 \u304f\u307e\u3067\u8a2d\u8a08\u306e\u305f\u3081\u306e\u8fd1\u4f3c\u3067\u3042 \u308a(\u4ee5 \u4e0b,\u81ea \u7531\u30e2\u30fc \u30c9\n\u5f62),\u5f97 \u3089\u308c \u305f\u30e2\u30c7\u30eb\u306e\u30e2\u30fc \u30c9\u5f62\u306b\u306f\u672c \u6765\u306e\u5883\u754c\u6761\u4ef6\u306b \u5f93 \u3063\u3066\u6c42 \u3081 \u3089\u308c \u308b\u03a6A(\u4ee5 \u4e0b,\u5b9f \u30e2\u30fc \u30c9\u5f62)\u3092 \u7528 \u3044\u308b \u5fc5\u8981\u304c \u3042\u308b.\n\u5fc5\u8981\u6700\u5c11 \u306e\u525b\u4f53\u8981\u7d20\u6570\u306f,\u6761 \u4ef6\u5f0f \u306e\u6570 \u3068\u525b\u4f53\u4e00\u500b \u306e \u672a\u77e5\u6570\u306e\u95a2\u4fc2 \u304b \u3089\u5b9a\u307e \u308b.\u5b9f \u30e2\u30fc \u30c9\u6570 \u3092m,\u81ea \u7531\u5883\u754c \u30e2\u30fc \u30c9\u6570\u3092mf\u3068 \u3059 \u308b\u3068,\n\u6761\u4ef6[1]\u6761 \u4ef6\u5f0f\u6570: 2 \u6761\u4ef6[2]\u6761 \u4ef6\u5f0f\u6570: 1 \u6761\u4ef6[3.1]\u6761 \u4ef6\u5f0f\u6570(\u30e2 \u30fc \u30c9\u8cea\u91cf): m\n\u6761\u4ef6[3.2]\u6761 \u4ef6 \u5f0f\u6570(\u76f4 \u4ea4 \u6027): m(m-1)/ 2\n\u6761\u4ef6[4.1]\u6761 \u4ef6\u5f0f\u6570(\u30e2 \u30fc \u30c9\u904b\u52d5\u91cf): mf \u6761\u4ef6[\u751f2]\u6761 \u4ef6 \u5f0f\u6570(\u30e2 \u30fc \u30c9\u89d2\u904b\u52d5\u91cf): mf\n\u3068\u6761\u4ef6\u5f0f \u306e\u6570\u304c\u6c7a\u5b9a\u3059 \u308b.1\u6b21 \u5143\u632f\u52d5 \u554f\u984c \u306b\u304a\u3044\u3066\u306f \u525b\u4f53\u8981\u7d20\u4e00\u500b\u306b\u3063\u304d\u6c42 \u3081\u308b\u3079 \u304d\u672a \u77e5\u6570 \u306f\u4e8c\u500b\u3067\u3042 \u308b\u305f \u3081,\u6761 \u4ef6\u5f0f\u6570\u306e\u5408 \u8a08\u3092\u4e00\u500b\u306b\u3064\u304d\u6c42\u3081\u308b\u3079 \u304d\u672a\u77e5\u6570 \u3067 \u5272 \u3063\u305f\u6570\u4ee5\u4e0a\u306e\u525b\u4f53\u8981\u7d20\u6570\u304c\u5fc5\u8981 \u3067\u3042\u308b.\n2\u30fb2 \u525b\u6027\u8981\u7d20 \u306e\u8a2d\u8a08 \u525b\u6027 \u8981\u7d20 \u306f\u525b\u6027\u884c\u5217 \u3068\u3057\n\u3066\u5f97 \u3089\u308c \u308b.\u525b \u6027\u884c\u5217k\u306f \u30e2\u30fc \u30c9\u525b\u6027\u884c\u5217,\u30e2 \u30fc \u30c9\u884c\n\u5217 \u03a6A,\u30e2 \u30fc \u30c9\u52fe\u914d\u884c\u5217 \u03a6'A\u304b \u3089\u7b97 \u51fa\u3055\u308c \u308b.\n(2)\n\u3053\u306e \u3068\u304d\u30e2\u30fc \u30c9\u525b\u6027\u884c\u5217\u306f,\u30e2 \u30fc \u30c9\u8cea\u91cf\u884c\u5217 \u3068\u56fa\u6709\u632f\n\u52d5\u6570\u304b \u3089\u8a08\u7b97 \u3055\u308c \u308b.\n2\u30fb3 \u6e1b\u8870\u8981\u7d20\u306e\u8a2d\u8a08 \u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61 \u306e\u69cb\u9020\u6e1b \u8870 \u3092\u5fc5\u8981 \u3068\u3059 \u308b\u5834 \u5408\u306f\u6e1b\u8870\u8981\u7d20 \u3092\u7528\u610f\u3059 \u308b.\u6e1b \u8870\u8981\u7d20 \u306f\u6e1b\u8870\u884c \u5217 \u3068\u3057\u3066\u5f97 \u3089\u308c \u308b.\u6e1b \u8870\u884c\u5217c\u306f \u30e2\u30fc \u30c9\u525b\u6027 \u884c\u5217c,\u30e2 \u30fc \u30c9\u884c\u5217 \u03a6A,\u30e2 \u30fc \u30c9\u52fe\u914d\u884c\u5217 \u03a6'A\u304b\u3089\u7b97\u51fa \u3055\u308c \u308b.\n(3)\n3. 2\u30ea \u30f3\u30af\u67d4\u8edf \u30ed\u30dc\u30c3 \u30c8\u30a2\u30fc\u30e0\u3078 \u306e\u9069\u7528\n3\u30fb1 \u67d4\u8edf \u30ed\u30dc\u30c3 \u30c8\u30a2\u30fc\u30e0\u306e\u6982\u8981 \u672c\u7814\u7a76\u3067\u4f7f\u7528", + "\u4efb\u610f\u5883\u754c\u3092\u6301\u3064\u5f3e\u6027\u4f53\u306e\u62e1\u5f35\u4f4e\u6b21\u5143\u5316\u7269\u7406\u30e2\u30c7\u30eb\u8a2d\u8a08\u6cd5(\u7b2c2\u5831) 3173\n\u3059 \u308b\u67d4\u8edf \u30ed\u30dc \u30c3 \u30c8\u30a2\u30fc \u30e0\u306e\u6982\u89b3 \u3068\u30d1 \u30e9\u30e1\u30fc \u30bf\u3092\u56f32\u3068 \u88681\u306b \u793a\u3059.\u80a9 \u30e2\u30fc\u30bf\u306e\u51fa\u529b\u8ef8\u306b1st Link\u304c \u56fa\u5b9a \u3055\u308c \u3066\u304a \u308a,1st Link\u306e \u5148\u7aef \u306b\u8098\u30e2\u30fc \u30bf\u304c\u56fa\u5b9a\u3055\u308c\u3066\u3044\u308b.\n\u3059 \u308b\u969b\u306e\u67d4\u8edf \u30ea\u30f3\u30af\u306e\u5883\u754c\u6761\u4ef6\u306f\u56fa\u5b9a-\u81ea \u7531\u3067\u3042\u308b. \u305d \u3053\u3067,\u56fa \u5b9a-\u81ea \u7531\u306e\u5b9f\u30e2\u30fc \u30c9\u3068\u81ea\u7531-\u81ea \u7531\u306e \u81ea\u7531\u30e2 \u30fc \u30c9\u3092\u4f7f\u7528 \u3057\u3066,\u62e1 \u5f35\u30e2\u30c7\u30eb \u3092\u8a2d\u8a08\u3059 \u308b.\u67d4 \u8edf \u30ea\u30f3\u30af \u306e\u30e2\u30fc \u30c9\u89e3\u6790 \u306b\u306fNASTRAN\u3092 \u7528\u3044,\u5b9f \u9a13\u88c5\u7f6e\u306e\u56fa\u6709 \u632f\u52d5\u6570 \u3092\u518d\u73fe\u3059 \u308b\u3088\u3046\u306b\u6709\u9650\u8981\u7d20\u30e2\u30c7\u30eb \u3092\u4f5c\u6210 \u3057\u305f. \u56f33\u306b1st Link\u306e \u632f\u52d5\u30e2\u30fc \u30c9\u5f62\u3092,\u56f34\u306b2nd Link\u306e \u632f\u52d5\u30e2\u30fc \u30c9\u5f62 \u3092\u793a\u3059.\u306a \u304a,\u3053 \u306e\u62e1\u5f35\u30e2\u30c7\u30eb\u306e\u8a2d\u8a08\u306b \u306f\u5b9f\u9a13\u30e2\u30fc \u30c9\u89e3\u6790\u306e\u9069\u7528 \u3082\u53ef\u80fd\u3067\u3042\u308b.\n1st Link\u306f \u30a2\u30fc \u30e0\u306e\u5148\u7aef \u306b\u8098\u30e2\u30fc \u30bf\u304c\u4ed8\u3044\u305f\u72b6\u614b\u3067\u89e3\n\u6790 \u3092\u884c \u3046(\u56f33).2nd Link\u306f \u5358\u7d14\u6881 \u3068\u306a\u3063\u3066\u3044 \u308b(\u56f3 4).\u56f33,\u56f34\u306b \u793a \u3057\u305f\u30e2\u30fc \u30c9\u5f62 \u3068\u56fa\u6709\u632f\u52d5\u6570 \u3092\u5143\u306b \u5f0f(1)-(3)\u3088 \u308a\u525b\u4f53\u8981\u7d20\u306e\u8cea\u91cf \u30fb\u6163 \u6027\u30e2\u30fc\u30e1\u30f3 \u30c8\u884c\u5217, \u525b\u6027\u884c\u5217,\u6e1b \u8870\u884c\u5217\u3092\u8a08\u7b97\u3059 \u308b.\u88682,\u88683\u306b \u7b97\u51fa \u3055 \u308c\u305f\u525b\u4f53\u8981\u7d20 \u306e\u8a2d\u8a08\u4f4d \u7f6e \u30fb\u8cea\u91cf \u30fb\u6163 \u6027\u30e2\u30fc \u30e1\u30f3 \u30c8\u3092\u793a \u3059.\u88682\u306f1st Link\u306b \u304a\u3051\u308b\u525b\u4f53\u8981\u7d20\u306e\u4f4d\u7f6e \u53ca\u3073\u8cea\u91cf \u30fb \u6163\u6027\u30e2\u30fc\u30e1\u30f3 \u30c8\u306e\u8a08\u7b97\u5024 \u3067\u3042 \u308a,\u88683\u306f2nd Link\u306b \u304a \u3051\u308b\u525b\u4f53\u8981\u7d20\u306e\u4f4d\u7f6e\u53ca\u3073\u8cea\u91cf \u30fb\u6163\u6027 \u30e2\u30fc\u30e1\u30f3 \u30c8\u306e\u8a08\u7b97\n\u5024\u3067 \u3042\u308b.\u3053 \u3053\u3067\u306f,\u63a1 \u7528\u30e2\u30fc \u30c9\u306f1\u6b21 \u30e2\u30fc \u30c9\u306e\u307f\u3067 \u3042\u308b\u306e\u3067\u525b\u4f53\u8981\u7d20\u6570\u306f\u5fc5\u8981\u6700\u5c11\u6570 \u3067\u3042\u308b\u4e09\u500b \u3068\u3057\u305f.\n\u525b\u4f53\u8981\u7d20\u306e\u8cea\u91cf \u30fb\u6163\u6027\u30e2\u30fc\u30e1\u30f3 \u30c8\u306f\u8a08\u7b97\u4e0a\u8ca0 \u306e\u5024\u304c \u7b97\u51fa \u3055\u308c \u308b\u3053\u3068\u304c\u3042\u308b\u304c,\u525b \u4f53\u8981\u7d20\u306e\u8cea\u91cf \u30fb\u6163 \u6027\u30e2\u30fc \u30e1\u30f3 \u30c8\u306f\u7dcf\u548c \u3068\u3057\u3066\u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe\u8c61\u306e\u8cea\u91cf \u30fb\u6163 \u6027\u30e2\u30fc \u30e1 \u30f3 \u30c8\u306b\u4e00\u81f4\u3059\u308b\u305f\u3081,\u6b63 \u3057\u304f\u5927\u904b\u52d5 \u3092\u8a18\u8ff0 \u3067\u304d,\u66f4 \u306b\u525b\u4f53\u8981\u7d20\u304b \u3089\u8a08\u7b97 \u3055\u308c \u308b\u30e2\u30fc \u30c9\u8cea\u91cf \u3082\u30e2\u30c7 \u30ea\u30f3\u30b0\u5bfe \u8c61\u306b\u4e00\u81f4\u3059 \u308b\u305f\u3081,\u6b63 \u3057\u304f\u632f\u52d5 \u3082\u8a18\u8ff0\u3067\u304d\u308b.\n\u8a2d \u8a08 \u3057\u305f\u62e1\u5f35\u30e2\u30c7\u30eb \u306e\u691c\u8a3c\u306e\u305f \u3081\u306b,\u88682\u3068 \u88683\u306e\n\u525b\u4f53\u8981\u7d20 \u306e\u8cea\u91cf \u30fb\u6163\u6027\u30e2\u30fc \u30e1\u30f3 \u30c8\u884c\u5217 \u3068\u5f0f(2)\u304b\u3089\u7b97 \u51fa \u3055\u308c\u305f\u525b\u6027\u884c\u5217\u3092\u7528\u3044\u3066\u5404 \u30ea\u30f3\u30af\u306e\u904b\u52d5\u65b9\u7a0b\u5f0f \u3092\u69cb\u7bc9\n\u3059 \u308b.\u3053 \u3053\u3067\u4f5c\u6210 \u3057\u305f\u904b\u52d5\u65b9\u7a0b\u5f0f \u3092\u7528\u3044\u3066,\u5404 \u30ea\u30f3\u30af \u5148\u7aef\u306b\u914d\u7f6e \u3055\u308c\u305f\u525b\u4f53\u8981\u7d20\u306b\u30a4\u30f3\u30d1\u30eb\u30b9\u5165\u529b\u3092\u52a0 \u3048, \u540c \u3058\u304f\u5148\u7aef \u306b\u914d\u7f6e \u3055\u308c \u305f\u525b\u4f53\u8981\u7d20\u3092\u5909\u4f4d\u89b3 \u6e2c \u3057\u305f \u3068\u304d \u306e\u5468\u6ce2\u6570 \u5fdc\u7b54 \u3092\u8a08\u7b97 \u3057,\u305d \u306e\u7d50\u679c \u3092\u56f35\u306b \u793a\u3059.\u70b9 \u7dda \u304c\u5b9f\u6e2c\u5024,\u5b9f \u7dda\u304c\u8a08\u7b97\u5024\u3067\u3042\u308b.\nFig. 4 Mode Shapes of 2nd Link" + ] + }, + { + "image_filename": "designv8_17_0000938_.2478_mspe-2020-0039-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000938_.2478_mspe-2020-0039-Figure14-1.png", + "caption": "Fig. 14. Cutting and developed view of a traditional electric rotary motor: a) obtaining arc and flat motor, b) linear tube motor with movable magnets", + "texts": [ + " Electromagnetic forces can be used for a generation of a linear, rotary or resultant motion. In the case of a ground rocket a linear motion is required. It is possible to get it while using linear induction motors. It is an electric motor generating translational motion, which can be obtained due to a location of the motor windings perpendicular to the direction of its motion. Its design results from a transformation of magnetic and electric circuits of a conventional motor. In the result an arc motor is obtained in the first phase and then a linear flat induction motor (Fig. 14a), and in the final effect-after winding around the axis parallel to the direction of the magnetic field dislocation \u2013 a linear tube motor (Fig. 14b) is generated. In such a motor the primary part, called a magneto and the secondary part called a run, can be distinguished. The magneto, supplied from the electric network, generates a migratory magnetic field through the linear structure. This field induces currents in the secondary part and in the result a tractive force, causing a linear motion of the movable part which can be both the run and the magneto, is generated. Such a motor is characterized by a constant linear velocity dependent onthe supply voltage frequency and it is expressed in m/s as well as an acceleration expressed in m/s2 and power of the current taken from the network in kW" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000475_cle_download_209_208-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000475_cle_download_209_208-Figure8-1.png", + "caption": "Figure 8: Stress on the Foot Support.", + "texts": [], + "surrounding_texts": [ + "natural walking \u201cteardrop\u201d shape and then are used in defining the position, velocity and acceleration design equations. After solving the equations, the resulting linkages produce a motion profile at the knee that closely resembles the natural walking gait. When attached to a coupler, the motion profile that was generated at the knee amplifies at the foot (Figure 5).\nApart from the walking trajectory, another main goal for the Exo-Limb was to be comfortable for the user to wear. This requires attaching the device in a way that is non-invasive and sturdy. Multiple attachment points (hip, glute, thigh, and seat) were considered and compared. Overall, the design matrices showed two preferred methods, a combination of knee and thigh support was chosen for the final design.\nThe design of the leg attachment was completed using statistical averages of anthropometric data. By determining the average leg sizes of possible users, a design was created to fit people of different sizes by providing adjustable strapping. The end result was a form-fitting, comfortable, and adjustable leg attachment that is strong, sturdy, and lightweight.\nIn order to feel natural and comfortable, the device had to provide enough stability for the user to control. Several features of the Exo-Limb increase the stability of the device. The four-bar linkage knee design allows for a more stable range of motion than a hinge joint knee design due to a large range of motion where the instant center of the four-bar linkage lies within a stability region. That compared to a hinge joint, which is\nonly stable when the user\u2019s body weight is directly over the hinge, is a huge increase in the stability of the device.\nThe form-fitting design of the leg attachment also provides enhancements to stability. The design fits securely to the user\u2019s leg and the foot extension touches the ground where the user\u2019s own foot would be expected to be. This natural location allows the user to quickly respond to slight deviations in ground level and provides for a smaller learning curve. Since the stability of the device will also depend on the dexterity of the user, a smaller learning curve will make for a more stable device.\nLastly, the toes of a human\u2019s foot help provide stability. They essentially grab the floor and provide a stable platform when ground surfacing is uneven. The prosthetic foot chosen for this project contains a splittoe feature that helps the user grip the floor when standing on the device. This helps provide lateral stability.\nThe first iteration of the design can be seen in Figure 6. Marginal improvements were made to enhance key areas. The manufacturability of the leg attachment was improved to lower production times and weight-bearing components were adjusted to increase the strength and fatigue life of the device. The", + "four-bar linkages in the knee joint were optimized using an algorithm developed by Robson et al. [8] to allow the device to more accurately mimic the natural walking gait. The prototype of the device can be seen in Figure 7 on the left.\nFor validation, the Exo-Limb project was tested to determine if the design requirements and project goals are met. This verification process included two methods: Dynamic and Mechanical.\nDynamic testing was performed at the biomechanics laboratory with the help of the Kinesiology department at Cal State Fullerton. The lab contains a state of the art motion tracking system that will be used to analyze and evaluate the device. Users initially walked without the device attached to determine the trajectories of three key body points: the hip, knee, and ankle. The users then walked with the device attached. The trajectories of the key points with the device attached were then compared to the trajectories of the key points without the device. The result from the motion profile of walking on the threadmil with the Exo-Limb device is shown in Figure 7 on the right. The results show that the device is not able to mimick the natural \u201cteardrop\u201d shape throughout the profile successfully. However, it is necessary to emphasize that walking on the treadmill is very different from walking on the ground. The foot, which is made of rubber, sticks easily on the treadmill and so it is harder to walk. This did not prevent the team to realize an experiment, where a number of subjects were walking on the floor with the device attached. The result was pretty impressive, and the comparison between the natural teardrop and the device teardrop showed that\nthe device is able to achieve about 60%-70% of the natural human gait.\nThe mechanical performance of the device was analyzed using Finite Element Analysis (FEA). Loads on key structural components were simulated in SolidWorks to determine static loading limits. The results from the static simulation were then used to perform a fatigue analysis.\nFigures 8 and 9 show the von Mises stress on the leg and foot attachment subassemblies when a 300 lb.load is applied. The resulting factor of safety is at least 5.00.\nStatic simulation was used to determine the fatigue life of the Exo-Limb. The results of the simulation show that the device will be capable of withstanding 1,000,000 cycles. This is well past the standard", + "recovery time for a sprained ankle, which is approximately 7.5 weeks. This comes out to be about 300,000 steps [11].\nCommercialization of the Exo-Limb project can be made possible by developing large-scale production methods. The scope of this project focuses mainly on research and design, which is a major component of the overall budget. Future goals for the project, if continued, would be to develop large-scale production methods.\nThe raw materials for the Exo-Limb are relatively cheap. The cost for the metal components totals about $40 for one device. Other materials, such as the straps, padding, and miscellaneous components, total at about $20. The Exo-Limb uses a clinical prosthetic foot made by \u00d6ssur to assist in the research and development of the natural walking gait. If large-scale production methods were to be developed in the future, an alternative would be to design a cost effective foot attachment.\nThe groundwork has been laid for the research and development of a hands-free crutch. If the project were to continue, the planning and implementation of largescale production methods would certainly decrease the cost to produce the Exo-Limb.\nIn this paper, the disadvantages of conventional designs, underarm and forearm crutches, are studied.\nIn order to overcome them, required design objectives and specifications are setup. Closed\u2013loop linkage design is considered for the knee mechanism. To fulfill the main design objective, natural walking motion, a kinematic synthesis was applied. The kinematic specifications (i.e. position, velocity and acceleration compatible with contact and curvature constraint between the foot and the ground) at two gait events (i.e. heel strike and toe off) are derived from the foot trajectory obtained from a motion capture system. By imposing the position and higher derivative kinematic specifications to the synthesis design equations of the knee mechanism, the locations of the fixed and moving pivots, as well as the foot trajectory have been defined. Our future directions are primarily related to further experimental tests on safety, comfort and stability while walking with the developed prototype.\nThe authors greatly acknowledge the mentorship of Mr. Jason Taylor, a Senior Project Manager at \u00d6ssur America, a global industry leader in prosthetics, as well as the assistance of Dr. Scott Lynn from Kinesiology Department at California State University, Fullerton and Victor Lopez, graduate student at Mechanical Engineering Department at California State University.\n[1] Hai-Eng P, Swierzewski Stanley J. Overview of ankle injuries. Health communities: risk Factors & causes of ankle injuries. http://www.healthcommunities.com/ankle-injuries/ index.shtml\n[2] Nagpurkar A, Troeller A. An evaluation of crutch energetics using standard and hands-free crutches. Clinical Biomechanics (n.d.): 1-8. Web.\n[3] Epstein S. Art, History, and the Crutch. Ann Medical History 1937; 9: 304-313.\n[4] Emami M, Jamali S. Investigation of ergonomic issues in crutch design and present an innovation, in Proc. of APIEMS Asia Pacific Industrial Engineering & Management Systems Conference (APIEMS) 2009; pp. 2939-2943.\n[5] Ginanneschi F, Filippou F, Milani P, Biasella A, Rossi A. Ulnar nerve compression neuropathy at Guyon's canal caused by crutch walking: Case report with ultrasonographic nerve imaging. Archives of Physical Medicine and Rehabilitation 2009; 90(3): 522-524.\n[6] Fisher S, Patterson R. Energy cost of ambulation with crutches. Archives of Physical Medicine and Rehabilitation 1981; 62(6): 250-256.\n[7] www.iwalk-free.com [8] Robson N, McCarthy JM, Kinematic synthesis with contact\ndirection and curvature constraints on the workpiece. Proc ASME IDETC 2007.\n[9] Passive assistive walking device. Final Report. California State University, Fullerton. Senior Mechanical Engineering Students. Fullerton, CA 2012." + ] + }, + { + "image_filename": "designv8_17_0002304__06_rvol23no1p14.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002304__06_rvol23no1p14.pdf-Figure1-1.png", + "caption": "Fig. 1. CDFIM: two DFIM connected back-to-back.", + "texts": [ + " The model of DFIM in a general reference frame (\"g\") is given by: ug s = Rsi g s + d\u03c8g s dt + j\u03c9g\u03c8g s (1) ug r = Rri g r + d\u03c8g r dt + j(\u03c9g \u2212\u03c9r)\u03c8g r (2) \u03c8g s = Lsi g s +Migr (3) \u03c8g r = Migs +Lri g r (4) and the mechanical equation of the DFIM can be written as follow: m(t)\u2212mL(t) = J d\u03c9m dt +B\u03c9m. (5) The electromagnetic torque of the DFIM is given by: m =\u22123 2 P M Ls ( \u03c8g s \u00d7 igr ) =\u22123 2 PM ( igs \u00d7 igr ) . (6) The CDFIM is composed of the union of two DFIMs in back-to-back configuration, where the rotors are connected electrically and mechanically. The CDFIM is shown in Figure 1. Considering the rotor connection in positive phase sequence and the arrangement of the machines in back-toback, the electric quantities of the rotor are in opposition to the relative speed of the rotor. The individual rotor phase voltages and currents are shown in Figure 2. The rotor parameters assume the relationship: Rr = Rrp +Rrc; Lr = Lrp +Lrc ug r = ug rp = ug rc; igr = igrp =\u2212igrc. (7) The rotor connected in positive phase sequence makes the individual torque components operate in the same direction, \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd but with the negative phase connection the individual torque components work in opposite direction", + " The model of DFIM in a general reference frame (\"g\") is given by: ug s = Rsi g s + d\u03c8g s dt + j\u03c9g\u03c8g s (1) ug r = Rri g r + d\u03c8g r dt + j(\u03c9g \u2212\u03c9r)\u03c8g r (2) \u03c8g s = Lsi g s +Migr (3) \u03c8g r = Migs +Lri g r (4) and the mechanical equation of the DFIM can be written as follow: m(t)\u2212mL(t) = J d\u03c9m dt +B\u03c9m. (5) The electromagnetic torque of the DFIM is given by: m =\u22123 2 P M Ls ( \u03c8g s \u00d7 igr ) =\u22123 2 PM ( igs \u00d7 igr ) . (6) The CDFIM is composed of the union of two DFIMs in back-to-back configuration, where the rotors are connected electrically and mechanically. The CDFIM is shown in Figure 1. Pot\u00eancia M\u00e1quina de Controle M\u00e1quina de rpV rcV spV scV Power Machine Control Machine Fig. 1. CDFIM: two DFIM connected back-to-back. Considering the rotor connection in positive phase sequence and the arrangement of the machines in back-toback, the electric quantities of the rotor are in opposition to the relative speed of the rotor. The individual rotor phase voltages and currents are shown in Figure 2. The rotor parameters assume the relationship: Rr = Rrp +Rrc; Lr = Lrp +Lrc ug r = ug rp = ug rc; igr = igrp =\u2212igrc. (7) The rotor connected in positive phase sequence makes the individual torque components operate in the same direction, 1Si 2Si 3Si 1Ri 2Ri 3Ri 1S 2S 3S 1R 2R 3R 1Su 2Su 3Su 1Ru 2Ru 3Ru RRSR SR SR RR RR \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc56\ufffd\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \ud835\udc45\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \u03a8\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc62\ufffd\ufffd \ud835\udc56\ufffd\ufffd\ufffd \ud835\udc56\ufffd\ufffd\ufffd \ud835\udc56\ufffd\ufffd\ufffd \ud835\udc45r\ufffd \ud835\udc45r\ufffd \ud835\udc45r\ufffd \ud835\udc56\ufffd\ufffd\ufffd \ud835\udc56\ufffd\ufffd\ufffd \ud835\udc56\ufffd\ufffd\ufffd \ud835\udc63\ufffd\ufffd\ufffd \ud835\udc63\ufffd\ufffd\ufffd \ud835\udc63\ufffd\ufffd\ufffd \ud835\udc63\ufffd\ufffd\ufffd \ud835\udc63\ufffd\ufffd\ufffd \ud835\udc63\ufffd\ufffd3 \ud835\udc45r\ufffd \ud835\udc45r\ufffd \ud835\udc45r\ufffd \ud835\udc3fr\ufffd \ud835\udc3fr\ufffd \ud835\udc3fr\ufffd \ud835\udc3frC \ud835\udc3fr\ufffd \ud835\udc3fr\ufffd Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003882_f_version_1645520937-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003882_f_version_1645520937-Figure3-1.png", + "caption": "Figure 3. Five typical stages of the mechanism with some components marked: (a) the RS moves downwards and pulls the TS moving upwards through the US; (b) the RS moves upward and the TS reaches the L-shaped PS, whereupon it rotates because of the unbalanced torque; (c) the RS continues to move upward and the pole is unable to rotate because of the pull provided by the LS; (d) the RS continues to move upward, pushing the NBP upward in its guide rail; (e) the TS falls freely down through its guide rail and the mechanism executes the launching process.", + "texts": [ + " Hollow structures are designed so that the pole does not interfere with the SB. The guide rail of the lower string (LS) is to the right of the joint, and springs hang on the other side. The scalar design is arranged to match the length of the motor output shaft (MOS) in scale, and detailed shape design to fit the angular range of output movement with the one of biological mechanism, also to enlighten the mechanism as much as possible. Besides, the length of the pole is decided according to a rule described in Section 3.2 to maximize the jumping height. Figure 3 shows the working cycle of the mechanism. The springs are loaded for a relatively long time, during which a large amount of elastic energy is stored. Soon after, it is released in a moment so that the pole is driven freely by the springs, transforming the stored energy into kinetic energy. Throughout the whole cycle, the springs always have a preload. Between the stages shown in Figure 3a,b, the RS moves downwards and pulls the TS moving upwards through the US. Size of the PS, TS and RS are adjusted carefully to let the TS get through the gap between the RS and PS smoothly. Between the stages shown in Figure 3b,c, the RS moves upward and the two strings are both tensioned. The TS moves downward from its highest position until it reaches the L-shaped PS, whereupon it rotates because of the unbalanced torque until it comes into contact with the sliding nut\u2013bolt pair. Now, the tension in the lower string and the support from the sliding nut\u2013bolt pair and the protrusion structure form a balance in the TS, stopping it from displacing. Also, the pole is unable to rotate because of the pull provided by the LS. Between the stages shown in Figure 3c,d, the RS continues to move upward, pushing the NBP upward in its guide rail and taking the place of the NBP in the position limit of the TS. These two processes, in which the RS moves upward, stretching the springs while the pole stays locked in the pre-triggering stage, reflect the processes in the biological jumping mechanism whereby the flexor muscle holds the tibia and the tensed extensor muscle stretches the extensor ligament, storing elastic energy therein. Between the stages shown in Figure 3d,e, the RS continues to move upward. At a critical position, it loses contact with the TS, whereupon the position limit for the TS is lost. The TS then falls freely down through its guide rail. During this sliding action, the lower string slides to the other end of its guide rail on the pole. This is the launching process, whereby the pole is driven violently by the springs releasing their elastic energy in a moment. The corresponding process in the biological structure is when the fm relaxes and the TFS loses the forces that were stopping it from moving toward the tibia, whereupon the tibia is driven by the el to rotate with great acceleration. After the stage shown in Figure 3d, the RS continues to move upward until its upper limit, whereupon the motor rotates in the opposite direction, sending the sliders to their opposite ends and restoring the stage shown in Figure 3a. During this period, the lower string slides to the end farthest from the revolute joint, and the sliding nut\u2013bolt pair slides to the lower end. This is the resetting process that marks the end of the cycle. To describe how the movements of the RS, TS, and pole are related, the whole mechanism is simplified into a geometrical model as shown in Figure 4. The origin of the coordinate system is dot O, the revolute joint connecting the SB and the pole. The y axis is parallel to the motor output shaft, and the x axis is vertical" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002281_aem_30_2_30_173__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002281_aem_30_2_30_173__pdf-Figure1-1.png", + "caption": "Fig. 1 Three-degree-of-freedom oscillatory actuator.", + "texts": [ + " (2021 \u5e74 11 \u6708 3 \u65e5\u53d7\u4ed8\uff0c2022 \u5e74 1 \u6708 13 \u65e5\u518d\u53d7\u4ed8) \uff11 \u7dd2\u8a00 \u8fd1\u5e74\uff0c\u624b\u8853\u8a13\u7df4\uff0c\u6280\u8853\u6559\u793a\u7b49\u306e\u69d8\u3005\u306a\u5206\u91ce\u3067\uff0c\u529b\u899a \u63d0\u793a\u30c7\u30d0\u30a4\u30b9\u306e\u5fdc\u7528\u304c\u671f\u5f85\u3055\u308c\u3066\u3044\u308b\u3002\u3053\u308c\u3089\u306e\u5206\u91ce \u3067\u306f\u5c0f\u578b\u304b\u3064\u8efd\u91cf\u3067\u53ef\u642c\u6027\u306b\u512a\u308c\u308b\u3053\u3068\u304c\u6c42\u3081\u3089\u308c\u308b\u3002 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\u7fd4\u5927\uff0c\u3012565-0871 \u5927\u962a\u5e9c\u5439\u7530\u5e02\u5c71\u7530\u4e18 2-1\uff0c \u5927\u962a\u5927\u5b66\u5927\u5b66\u9662\u5de5\u5b66\u7814\u7a76\u79d1\u30de\u30c6\u30ea\u30a2\u30eb\u751f\u7523\u79d1\u5b66\u5c02\u653b\uff0c e-mail: shota.yamamoto@mapse.eng.osaka-u.ac.jp *1\u5927\u962a\u5927\u5b66 \u5b66\u8853\u8ad6\u6587 174 (116) \u5f93\u6765\u30e2\u30c7\u30eb 2 \u3064\u306e\u78c1\u6c17\u56de\u8def\u306e\u7c21\u7565\u56f3\u3092 Fig. 2(a)\uff0cFig. 2(b)\u306b\u793a\u3059\u3002\u3053\u308c\u3089\u306f\u99c6\u52d5\u8ef8\u65b9\u5411\u306b\u5bfe\u6297\u3059\u308b\u6c38\u4e45\u78c1\u77f3 \u3068\uff0c\u52b1\u78c1\u3055\u308c\u305f\u30b3\u30a4\u30eb\u306b\u3088\u308b\u78c1\u6c17\u5438\u5f15\uff0c\u53cd\u767a\u529b\u306b\u3088\u3063 \u3066\u99c6\u52d5\u3059\u308b\u3002\u6241\u5e73\u69cb\u9020\u304c\u9054\u6210\u3067\u304d\u305f\u4e00\u756a\u306e\u8981\u56e0\u306f\uff0c\u5f93 \u6765\u3067\u306f\u5404\u8ef8\u306b 2 \u500b\u306e\u78c1\u77f3\u3092 3 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3(b)\u306b\u56fa\u5b9a\u5b50\u306e\u8a73 \u7d30\u56f3\u3092\u793a\u3057\u305f\u3002\u672c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u3067\u306f\uff0c4 \u672c\u306e\u30b3\u30a4\u30eb \u3070\u306d\u3092\u7528\u3044\u3066\u652f\u6301\u3092\u884c\u3046\u3002\u6c38\u4e45\u78c1\u77f3\u306b\u8fd1\u3065\u304f\u65b9\u5411(y\u8ef8 \u65b9\u5411)\u3067\u306f\uff0c\u78c1\u77f3\u306e\u5438\u5f15\u529b\u304c\u5927\u304d\u3044\u305f\u3081\uff0c\u30b3\u30a4\u30eb\u3070\u306d\u306e \u4f38\u7e2e\u65b9\u5411\u3068\u3057\u305f\u3002x\u30fbz\u8ef8\u65b9\u5411\u306b\u306f\u30b3\u30a4\u30eb\u3070\u306d\u306e\u6a2a\u525b\u6027 \u3092\u7528\u3044\u3066\u652f\u6301\u3092\u884c\u3046\u3002\u3070\u306d\u304c\u4f38\u7e2e\u65b9\u5411\u306b\u5909\u4f4d\u3057\u305f\u5834\u5408\uff0c \u6a2a\u525b\u6027\u306b\u5f71\u97ff\u304c\u51fa\u308b\u304c\uff0c\u30b9\u30c8\u30ed\u30fc\u30af\u304c\u5c0f\u3055\u304f\uff0c\u5f71\u97ff\u306f \u5c0f\u3055\u3044\u3068\u8003\u3048\u3089\u308c\u308b\u3002\u307e\u305f\uff0c\u4e8b\u524d\u306b\u4f38\u7e2e\u306b\u5bfe\u3059\u308b\u6a2a\u525b \u6027\u3092\u5b9f\u6e2c\u3057\uff0c\u6a2a\u525b\u6027\u306e\u5909\u52d5\u3092\u88dc\u6b63\u3059\u308b\u96fb\u6d41\u3092\u52a0\u3048\u308b\u3053 \u3068\u3067\uff0c\u5236\u5fa1\u4e0a\u3067\u88dc\u511f\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002\u53ef\u52d5\u5b50\u306f\u975e\u78c1\u6027\u4f53 \u306e\u306d\u3058\u3092\u7528\u3044\u3066\u3070\u306d\u3092\u53d6\u308a\u4ed8\u3051\u3066\u3044\u308b\u3002 2.3 \u52d5\u4f5c\u539f\u7406 \u672c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u3067\u306e\u5404\u8ef8\u99c6\u52d5\u306e\u52d5\u4f5c\u539f\u7406\u3092 Fig. 4 \u306b\u793a\u3059\u3002Coil-X \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067\u767a\u751f\u3059\u308b\u78c1\u675f\u306b\u3088\u308a\uff0c \u53ef\u52d5\u5b50\u306f x\u8ef8\u65b9\u5411\u306b\u99c6\u52d5\u3059\u308b\uff08Fig. 4(a)\uff09\u3002\u30b3\u30a4\u30eb\u306b\u5370 \u52a0\u3059\u308b\u96fb\u6d41\u306e\u5411\u304d\u306b\u3088\u308a\u99c6\u52d5\u65b9\u5411\u3092\u5236\u5fa1\u53ef\u80fd\u3067\u3042\u308b\u3002 \u540c\u69d8\u306bCoil-Y \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067 y\u8ef8\u65b9\u5411\u306b\uff08Fig. 4(b)\uff09\uff0c Coil-Z \u3092\u52b1\u78c1\u3059\u308b\u3053\u3068\u3067 z \u8ef8\u65b9\u5411\u306b\u99c6\u52d5\u53ef\u80fd\u3067\u3042\u308b \uff08Fig. 4(c)\uff09\u3002 \uff13 \u9759\u63a8\u529b\u7279\u6027\u89e3\u6790 \u672c\u7ae0\u3067\u306f\u63d0\u6848\u3059\u308b 3 \u81ea\u7531\u5ea6\u632f\u52d5\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u9759 \u63a8\u529b\u7279\u6027\u3092\u660e\u3089\u304b\u3068\u3059\u308b\u3002\u5404\u8ef8\u65b9\u5411\u306b\u72ec\u7acb\u3057\u3066\u63a8\u529b\u3092 \u767a\u751f\u53ef\u80fd\u3067\u3042\u308b\u3053\u3068\uff0c\u3055\u3089\u306b\uff0c3 \u8ef8\u540c\u6642\u99c6\u52d5\u6642\u306b\u3082\uff0c \u63a8\u529b\u5e72\u6e09\u304c\u306a\u3044\u3053\u3068\u3092\u793a\u3059\u3002 Fig. 1 Three-degree-of-freedom oscillatory actuator. (a) Conventional model 1 (b) Conventional model 2 (c) Proposed Fig. 2 Magnetic circuit. (a) Outer mover (b) Inner stator Fig. 3 Detailed drawing of proposed model. z x y Whole view of Inner statorExploded view Spring (SUS316) Screw (SUS304) Inner case (SUS304) Whole view Inner stator Outer mover Without supporting mechanism Inner yoke Coil-X,Y,Z Back yoke PM supporting mechanism supporting mechanism z x y z x y Magnetic flux path by PM PM Magnetic flux path by PM y z x z y x Whole view of Outer mover Without supporting mechanism Supporting mechanism z x y 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure6-1.png", + "caption": "Fig. 6 Outlet and Inlet pipes", + "texts": [ + " 4b; the dynamic layer domain, that represents the fluid layer rotating between walls of the impeller and fluid layer just above the impeller body; Fig. 5a and the static domain, which represents the remained part located between the casing body of the pump and the dynamic flow layer above the impeller, Fig. 5b. The lengths of the inlet and outlet pipes are about 11.1 and 13.5 times the casing diameter, respectively similar as in [7]. The centerline of the inlet pipe and outlet pipe are at angles of - 28.6o and +28.6o from the Y-axis, respectively, as shown in Fig. 6. The Boundary conditions in these current simulations are similar to that employed in [7]: \u2022 At inlet: the boundary set to be a constant static pressure and the flow is normally directed to the boundary condition with a medium turbulence intensity of 5%, which is a standard inflow boundary condition. \u2022 At outlet: the boundary condition is set to the opening with variable pre-defined mass flow rate (0.0218, 0.05, 0.109, 0.1635, 0.218, 0.2725 and 0.3815 kg/s). \u2022 The no-slip condition is employed near the solid walls" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004002_c_free.html_id_10138-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004002_c_free.html_id_10138-Figure7-1.png", + "caption": "Figure 7: Final design of the bogie frame.", + "texts": [ + " Mass of the innovated frame was change in small percentage, as shown in Figures 5. In addition, as confirmed by a modal analysis carried out in free-free conditions, the natural dynamic behaviour of the system was very similar. As shown in Figure 6, a perfect matching in the first frequency of vibration was observed, with a value about 60 Hz. These results would allow to replace the original bogie frame with the innovated one. Following this verification, a detailed model of it was created. The result is shown in Figure 7. The new design had an open shape, which made it potentially feasible for sand casting, as it had a single direction of extraction from the mold. Moreover, the central crossbeam was reinforced with inclined sets, useful for increasing the flexural and torsional stiffness of the frame, as well as facilitating the flow of molten material inside the mold. The constraint on minimum thicknesses imposed during the optimization process allowed for speeding up the geometry reconstruction process, as there were already numerous references available" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001671_O201325954480036.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001671_O201325954480036.pdf-Figure7-1.png", + "caption": "Fig. 7 Total deformations at natural frequencies of model 2", + "texts": [], + "surrounding_texts": [ + "(b) Natural frequency at 2'nd\n(c) Natural frequency at 3'rd\n(d) Natural frequency at 4'th\n\uc11c\ub294 \uc2e4\uc81c\ub85c \uac00\ud639\ud55c \uc870\uac74\uc774\ub77c\ub3c4 \ud1b5\uc0c1 \uc774 \uc9c4\ub3d9\uc218 \uc774\uc0c1\uc73c\ub85c\ub294 \uacf5\uc9c4\uc774 \uc77c\uc5b4\ub098\uc9c0 \uc54a\ub294 \uac83\uc73c\ub85c \uc0ac\ub8cc\ub418\uc5b4 \uc774 \uc7a5\uce58 \uc124\uacc4\uc758 \ub0b4\uad6c\uc131 \uac80\uc99d\uc5d0 \uc720 \ud6a8\ud558\ub2e4\uace0 \ubcf4\uc778\ub2e4. \ubcf8 \uc5f0\uad6c \uacb0\uacfc\ub97c \uc790\ub3d9\ucc28\uc758 \ucc28\uccb4 \ubd80\ud488\uc5d0 \uc751\uc6a9\ud55c\ub2e4 \uba74, \ud53c\ub85c \ud30c\uc190 \ubc29\uc9c0 \ubc0f \uadf8 \ub0b4\uad6c\uc131\uc744 \uc608\uce21\ud560 \uc218 \uc788\ub2e4. \uc2e4\uc81c\uc801\uc73c\ub85c \ud558\uc911\uc774 \uc0c1\ub2f9\ud788 \uc791\uc544\uc9c4\ub2e4 \ud558\ub354\ub77c\ub3c4 \ub4f1\uac00\uc751\ub825\uc774\ub098 \ucd5c\ub300\uc751\ub825\uc774 \uadf8\ub2e4 \uc9c0 \uc791\uc544\uc9c0\uc9c0\ub294 \uc54a\uc558\uc73c\uba70, \uacf5\uc9c4\uc758 \uacbd\uc6b0\ub3c4 \uc704\uc5d0 \ub098\ud0c0\ub09c \uacf5\uc9c4\uc218 \uc774\uc0c1 \ub098\ud0c0\ub098\uc9c0 \uc54a\uc558\ub2e4. \ucc28\ub7c9\uc740 \uc8fc\ud589 \uc911 60\uff5e120 cycle/min (1\uff5e2 Hz) \uc758 \uc9c4\ub3d9\uc218\uc5d0\uc11c \uac00\uc7a5 \uc88b\uc740 \uc2b9\ucc28\uac10\uc744 \ubcf4\uc774\uba70 \ud604\uac00\uc7a5\uce58\ub294 \uc774 \ubc94\uc704 \ub0b4 \uc5d0\uc11c \uc124\uacc4\ub41c\ub2e4 [8] . \ub610\ud55c \uc774 \uacb0\uacfc\uc5d0\uc11c \ubcf4\uba74 \uc8fc\ud589 \uc911 157 Hz\uc640 222 Hz\uc5d0\uc11c \uacf5\uc9c4\uc774 \ubc1c\uc0dd\ud558\ub098 \uc2e4\uc81c\uc0c1\uc5d0\uc11c\ub294 \uc774\ubcf4\ub2e4 \ud6e8\uc52c \ub0ae\uc740 \uc9c4\ub3d9\uc218\ub85c \uc6b4\ud589\ub418\uae30 \ub54c\ubb38\uc5d0 \uc2b9\ucc28\uac10\uc774 \uc88b\ub3c4\ub85d \uc124\uacc4\ub97c \ud560 \uc218 \uc788\ub2e4\ub294 \uac80\uc99d \uacb0\uacfc \ub97c \ubcf4\uc600\ub2e4. \uadf8\ub9ac\uace0 \uc2e4\uc81c\uc801\uc73c\ub85c Fig. 2 \ubc0f Fig. 3\uc5d0\uc11c\uc640 \ub611\uac19\uc774 \uc55e \ubc94\ud37c\uc758 \uc55e\uba74\uc5d0 Force\ub97c 2500 N\uc758 \uad6c\uc18d\uc744 \uc8fc\uc5b4, \uc55e \ubc94\ud37c\uc5d0 \uc0dd\uae30\ub294 \ud558\ubaa8\ub2c9 \uc9c4\ub3d9\uc5d0 \ub300\ud558\uc5ec \ud574\uc11d\ud574 \ubcf4\uc558\ub2e4. \uc9c4\ub3d9\uc218\uc758 \ubc94\uc704\ub294 230 Hz\uae4c \uc9c0\ub85c \uc124\uc815\ud558\uc600\ub2e4. \uc55e\uc5d0 Modal \ud574\uc11d\uc758 \uacb0\uacfc\ub97c \ubcf4\uac8c \ub418\uba74 6\ucc28 \ubaa8\ub4dc \uc758 \uace0\uc720\uc9c4\ub3d9\uc218\uac00 230 Hz\ubc94\uc704 \ub0b4\uc5d0 \uc788\uae30 \ub54c\ubb38\uc5d0 \uac00\uc9c4 \uc8fc\ud30c\uc218 \uc601\uc5ed \uc744 \ub9de\ucdb0 \uacf5\uc9c4 \uc8fc\ud30c\uc218\ub97c \ud655\uc778\ud558\uc600\ub2e4. Model 1\uacfc 2\uc5d0 \ub300\ud558\uc5ec \uc9c4\ub3d9\uc218 \uc5d0 \ub300\ud55c \uc9c4\ud3ed \ubcc0\uc704 \uc751\ub2f5\uc744 \uc0b4\ud3b4 \ubcf8 Fig. 8(a), (b)\uc5d0\uc11c \ubcf4\uba74 \uc54c \uc218 \uc788\ub4ef\uc774 Model 1\uc740 159 Hz\uc5d0\uc11c\uc640 Model 2\ub294 110 Hz\uc758 \uc704\ud5d8 \uc9c4 \ub3d9\uc218\ub97c \uac01\uac01 \ub098\ud0c0 \ub0b4\uc5c8\ub2e4. \uc774\ub7ec\ud55c Model 1\uacfc 2\uc5d0 \ub300\ud55c \uc704\ud5d8 \uc9c4\ub3d9", + "(c) Natural frequency at 3'rd\n(d) Natural frequency at 4'th\nTable 3 Maximum total deformation and natural frequency per mode at model 1\nFrequency (Hz) Total deformation (mm)\n1\u2019st Mode 69.85 18.42 2\u2019nd Mode 77.302 19.189 3\u2019rd Mode 138.95 28.845 4\u2019th Mode 157.88 62.671 5\u2019th Mode 171.46 25.46 6\u2019th Mode 199.68 24.944\nTable 4 Maximum total deformation and natural frequency per mode at model 2\nFrequency (Hz) Total deformation (mm)\n1\u2019st Mode 43.001 16.019 2\u2019nd Mode 66.895 33.087 3\u2019rd Mode 108.97 14.083 4\u2019th Mode 111.25 31.77 5\u2019th Mode 134.35 20.562 6\u2019th Mode 222.41 36.565", + "(a) Model 1\n(b) Model 2\n\uc218\uc5d0\uc11c \uadf8 \uc9c4\ud3ed\ubcc0\uc704\ub294 0.105 mm\uc640 0.154 mm\ub85c \uc0dd\uae40\uc744 \uc54c \uc218 \uc788\ub2e4. \uc774\ub7ec\ud55c \uc704\ud5d8\uc9c4\ub3d9\uc218\uac00 \ud074\uc218\ub85d \ubaa8\ub378\uc758 \ub0b4\uad6c\uc131\uc774 \uc88b\uac8c \ub418\ub294\ub370, Model 1\uc758 \uc704\ud5d8 \uc9c4\ub3d9\uc218\uac00 Model 2\ubcf4\ub2e4 \ud07c\uc73c\ub85c\uc11c Model 1\uc758 \ub0b4 \uad6c\uc131\uc774 Model 2\ubcf4\ub2e4 \ub354 \uc591\ud638\ud574\uc9c4\ub2e4\ub294 \uac83\uc744 \ubcfc \uc218 \uc788\ub2e4. \ub530\ub77c\uc11c Model 1\uacfc 2\uc5d0\uc11c\uc758 159 Hz\uc640 110 Hz\uc758 \uc704\ud5d8 \uc9c4\ub3d9\uc218\uc5d0\uc11c Model 1\uacfc 2\uc758 \uc2e4\uc81c\uc801\uc778 \ub4f1\uac00 \uc751\ub825\uacfc \uc804\ubcc0\ud615\ub7c9\uc740 \uac01\uac01 Fig. 9(a), (b) \ubc0f Fig. 10(a), (b)\uacfc \uac19\uc774 \ub098\ud0c0\ub0ac\ub2e4 [9] .\n4. \uacb0 \ub860\n\ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 \uc8fc\ud589 \uc911\uc778 \uc790\ub3d9\ucc28 \uc55e \ubc94\ud37c\uc5d0 \ub300\ud55c \uad6c\uc870 \ubc0f \uc9c4\ub3d9\uc5d0 \ub530\ub978 \uac15\ub3c4 \ub0b4\uad6c\uc131\uc744 \ud574\uc11d\ud558\uc600\ub2e4. \uc774\uc5d0 \ub300\ud574 \uc5f0\uad6c\ud55c \uacb0\uacfc\ub294 \ub2e4\uc74c\uacfc \uac19\ub2e4.\n\uad6c\uc870\ud574\uc11d \uacb0\uacfc, Mode1\uacfc Mode2 \uc55e \ubc94\ud37c\uc758 \ucd5c\ub300\uc758 \ub4f1\uac00\uc751\ub825\uc774 \uac01\uac01 187.09 MPa \ubc0f 278.4 MPa\uc774\uace0, \ubcc0\ud615\ub7c9\uc774 \uac01\uac01 1.3772 mm \ubc0f 2.675 mm\ub85c\uc11c \ucd5c\ub300\ub85c \ub098\ud0c0\ub0ac\ub2e4. 2\ubc88 \ubaa8\ub378\uc774 1\ubc88 \ubaa8\ub378\ubcf4\ub2e4 \ub354 \ubcc0\ud615\ub418\ub294 \uac83\uc744 \uc54c \uc218 \uc788\ub2e4. \ub610\ud55c Model 1\uacfc Model 2\uc5d0\uc11c \uace0\uc720\uc9c4 \ub3d9\uc218\ub294 \uacf5\ud788 230 Hz\uc774\ub0b4\uc5d0\uc11c \uc77c\uc5b4\ub0a8\uc744 \uc54c \uc218 \uc788\uc73c\uba70 \uc2e4\uc81c\uc801\uc73c\ub85c" + ] + }, + { + "image_filename": "designv8_17_0004490_f_version_1544786225-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004490_f_version_1544786225-Figure10-1.png", + "caption": "Figure 10. The 2D measured radiation pattern at (a) 3.25, (b) 6.5, and (c) 9.5 GHz. i r . The 2 eas r r i ti tt r t ( ) . , . , .", + "texts": [ + " The far-field characteristics of the realized antenna were measured by Satimo near the field measurement facilities of the UKM microwave lab, which is shown in Figure 8c. The numerical and measured VSWR of the realized antenna is depicted in Figure 9. The numerical VSWR in HFSS less than 2 is about 3.10\u201315 GHz and 2.8\u201315 GHz in the CST simulation software. On the other hand, a measured VSWR was achieved from 2.97 to 15 GHz, which fully covered the UWB band. The simulated results significantly matched with the measured results. Figure 10 illustrated the simulated and measured 2D polar radiation pattern of the realized antenna (XZ plane and YZ plane) at 3.25, 6.50, and 9.5 GHz, respectively. The radiation pattern also displayed the co-polarization and cross-polarization results. It can be noted that the antenna exhibits a shape pattern as in Figure 8 i the XZ plan , and an omnidirectional pattern in the YZ plane, which is a dipole-like radiation Sensors 2018, 18, 4427 8 of 19 pattern. The cross-polarization is comparatively low with respect to polarization. Figure 11 depicts the simulated and measured peak realized gain of the antenna. From this figure, it can be stated that the antenna achieves more than 3 dB peak gain across the desired operating band. Sensors 2018, 18, x FOR PEER REVIEW 8 of 19 band. The simulated results significantly matched with the measured results. Figure 10 illustrated the simulated and measured 2D polar radiation pattern of the realized antenna (XZ plane and YZ plane) at 3.25, 6.50, and 9.5 GHz, respectively. The radiation pattern also displayed the copolarization and cross-polarization results. It can be noted that the antenna exhibits a shape pattern as in Figure 8 in the XZ plane, and an omnidirectional pattern in the YZ plane, which is a dipole-like radiation pattern. The cross-polarization is comparatively low with respect to polarization. Figure 11 depicts the simulated and measured peak realized gain of the antenna", + " From this figure, it can be stated that the antenna achieves more than 3 dB peak gain across the desired operating band. (a) (b) (c) Figure 8. The photograph of the proposed ultrawideband (UWB) antenna (a) top view and (b) back view, and (c) UKM StarLab. Figure 9. Measured and simulated VSWR curves. Figure 8. The photograph of the proposed ultrawideband (UWB) antenna (a) top view and (b) back vie , ( ) t . Sensors 2018, 18, x FOR PEER REVIEW 8 of 19 band. The simulated results significantly matched with the measured results. Figure 10 illustrated the simulated and measured 2D polar radiation pattern of the realized antenna (XZ plane and YZ plane) at 3.25, 6.50, and 9.5 GHz, respectively. The radiation pattern also displayed the copolarization and cross-polarization results. It can be noted that the antenna exhibits a shape pattern as in Figure 8 in the XZ plane, and an omnidirectional pattern in the YZ plane, which is a dipole-like radiation pattern. The cross-polarization is comparatively low with respect to polarization. Figure 11 depicts the simulated and measured peak realized gain of the antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001798_n_Compress_20464.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001798_n_Compress_20464.pdf-Figure3-1.png", + "caption": "Fig. 3. Arrangement of the temperature sensors. S1, upper core; S2, upper edge; S3, middle core; S4, middle edge; S5, bottom core; S6, bottom edge temperature sensor", + "texts": [ + " The prepared alfalfa stalk particle of 10 g was put into the die, and two temperature sensors were placed in the bottom core and bottom edge of the material in the die. Next, 8 g of alfalfa stalk particle was added to the die, and then two temperature sensors were placed in the middle core and middle edge of the material in the die. Lastly, the rest of the 8 g alfalfa stalk particle was added to the die and two temperature sensors were placed in the upper core and upper edge of the die, as shown in Fig. 3. The sensors should be embedded in the material. When the initial temperature of the sensors was kept constant, the compression piston moved down, at the same time the vibration system started to work. Thus, a vibrated compression force was applied to the material in the die. During the tests, the temperature was measured and recorded by a data acquisition system programmed in LabVIEW2013 to computer. To study the influence of vibration on the compression temperature and its transmission in the briquettes, when the compression piston began to return, the assisted-vibration was stopped" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001116_8feb81e58cbf41fb.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001116_8feb81e58cbf41fb.pdf-Figure1-1.png", + "caption": "Fig. 1: The electric circuit of the Fig. 2: The Open-loop step response of the armature and the free body diagram motor system using T. F. or state-space; of the rotor for a DC motor with initial speed=0.1 p.u. at steady state", + "texts": [ + " The design method uses the concepts of the system theory, such as signals and systems, transfer functions, direct and inverse Laplace transforms. This requires building the appropriate Laplace model for each component of the whole control system. In order to build the DC motor\u2019s transfer function, its simplified mathematical model has been used. This model consists of differential equations for the electrical part, mechanical part and the interconnection between them. The electric circuit of the armature and the free body diagram of the rotor are shown in the Fig. 1. All the values for the physical parameters are listed in Table A in the Appendix. The motor torque, Tm, is related to the armature current, i, by a constant factor Kt. The back emf, em, is related to the rotational speed,\u03b8& by the following equations [7]: iKT tm = \u2026.. (1) \u03b8&em Ke = \u2026.. (2) Assuming that, Kt (torque constant) = Ke (electromotive force constant) = Km (motor constant). From Fig. 1 and Table A, the following equations can be written based on Newton\u2019s law combined with Kirchhoff\u2019s law: Lm TiKbJ \u2212=+ \u03b8\u03b8 &&& \u2026.(3) \u03b8&mmm KViR dt di L \u2212=+ \u2026.. (4) a- Transfer Function Using Laplace Transforms, the above equations can be expressed in terms of s-domain. ( ) )()()( sTLm sIKsbsJs \u2212=+ \u03b8& ..(5) ( ) )()()( ssKsVsIs mmm RL \u03b8&\u2212=+ \u2026.(6) By eliminating I(s), the following open-loop transfer function can be obtained, where the rotational speed \u03b8& is the output and the voltage V is the input", + "0i, K=68.3287, poles=-0.6265, 0.7344\u00b10.1294i, and 0.2275. The plot shows that the settling time is less than 2 sec and the overshoot is around 3%. In addition, the steady-state error is zero. Therefore this response satisfies all of the design requirements. 8- Simulink Design Method for Speed Modeling: A basic feedback control system shown in Fig. 3 represents a very common block diagram form. For the proposed system, the Plant will be a DC motor. i. Building the Model: The motor system shown in Fig. 1 will be modeled by summing the torques acting on the rotor inertia and integrating the acceleration to give the velocity. Also, Kirchoff's laws will be applied to the armature circuit. First, the integrals of the rotational acceleration and of the rate of change of armature current will be modeled: dt d dt d \u03b8\u03b8 =\u222b 2 2 , and i dt di =\u222b \u2026(17) Next, both Newton's law and Kirchoff's law will be started to model. These laws applied to the motor system to give the following equations: dt d bT dt d J m \u03b8\u03b8 \u2212=2 2 \u2212= dt d biK Jdt d t \u03b8\u03b8 1 2 2 \u2026" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000100_pub_20.20230493__pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000100_pub_20.20230493__pdf-Figure9-1.png", + "caption": "Fig. 9. The whole layout of this PA for EM simulation.", + "texts": [ + " (8) After the above transform, the parameters of the transformer are changed from (a) to (b) in Fig. 7. And the \ud835\udc58 value is up to 0.2 from 0.157. The final layout of this transformer is shown in Fig. 8. In order to reduce the fulfilled metal dummy, especially the metal M7 dummy, each transformer is enclosed with a AC ground ring on metal M7, which increases the density of metal M7 and makes the EM simulation result as close as possible to the actual situation. And the whole layout for EM simulation is in Fig. 9. Fig. 10 shows the measurement setup for the S-parameters and large-signal performances of the proposed PA in 40nm CMOS technology. The on-wafer setup was calibrated using a calibration substrate calibration kit. A microphotograph of the fabricated PA is presented in Fig. 11. The measured PA consumed a DC current of 72mA from a 1.1 V supply. The measured and simulated S-parameter results are shown in Fig. 12. The measured peak power gain (S21) was 25.3dB at 76.5GHz, and the 3-dB bandwidth was about 11" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure10-1.png", + "caption": "Figure 10. The load on the main rod due to the reaction load from the rods receiving the load", + "texts": [ + " Then, the force received by the rod (\ud835\udc39\ud835\udc35\ud835\udc4f) is FBR = mass x g\ud835\udc5f\ud835\udc4e\ud835\udc63\ud835\udc56\ud835\udc61\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c\ud835\udc5b FBR = 7 kg x 9,81m/s2 = 68,67 N 8. Static analysis of the load on the main rod This rod uses a rectangular hollow profile of 75x20x1.6 mm with a vertical position in the y-axis direction. The load received is the reaction load from the rod that receives the load directly, namely the load from the electric motor mounting rod, control panel and battery, driver body, driver's legs, front body, rollbar body, and rear body, as shown in Figure 10. The main rod is assumed to be straight with a length of 2500 mm, as shown in Figure 11. The free-body diagram of the main stem can be seen in Figure 12. Based on the results of the static load analysis with manual calculations that have been carried out, the calculation results are obtained in the form of bending moment, maximum stress, and displacement values, as shown in Table 1 and Table 2. This article uses Autodesk Inventor software through the analysis frame feature to conduct the simulation process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004319_echaterobot_download-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004319_echaterobot_download-Figure5-1.png", + "caption": "Figure 5. Selected servomotor Monza SSA120M", + "texts": [], + "surrounding_texts": [ + "This variant is a combination of the preceding variants and it features all of their advantages such as simple structure and a relatively low height." + ] + }, + { + "image_filename": "designv8_17_0004245_SIJINT-2015-088__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004245_SIJINT-2015-088__pdf-Figure1-1.png", + "caption": "Fig. 1. Definition of tangential angle.", + "texts": [ + " To obtain the model, two assumptions were used: (1) that entry-side velocity difference \u0394v1 influences delivery-side curvature 1/\u03c12 scaled by 1/\u03bb2 in addition to the curvature due to delivery-side velocity difference \u0394v2; and (2) that \u0394v2 is proportional to the wedge ratio \u0394\u03c8: \u2206 \u2206 \u2206v v h h H H 2 2 = \u2212 \u03b1 . ......................... (2) According to this model, 1/\u03c11 is only determined by \u0394v1, whereas 1/\u03c12 is affected by both the \u0394v2 and 1/\u03c11. 1 \u03c1 \u03b8 \u03b8 \u03c9 = = = = d dx d vdt v v bv \u2206 . ..................... (3) However, \u03c9 in Eq. (3) is not the rotation speed of the strip but the time derivative of tangential angle d\u03b8/dt which is defined as an angle between the tangent vector and the x-axis1,2) (Fig. 1); d\u03b8/dt depends only on the shape of the strip, and not on its rotation. Also, the first assumption was based on the idea that the rotated angle of the strip at the delivery side \u03b82 is reduced to rotated angle at the entry side \u03b81 divided by \u03bb. From the definition of curvature (Eq. (3)), they explained that additional curvature is generated by the rotation of the strip scaled by \u03bb2 because dx2 increases to \u03bbx1, whereas d\u03b82 decreases to d\u03b82/\u03bb. The basis of the first assumption was established in the first study4) of side-slipping which represented the timevarying location of points on the centerline (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004559_tation-pdf-url_51513-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004559_tation-pdf-url_51513-Figure2-1.png", + "caption": "Figure 2. Normal deformation as a result of tensile and compressive forces applied to cylindrical specimens along with the shear deformation as a result of shear force applied to a cubic specimen.", + "texts": [ + " The unit of the stress is Nm\u22122. Strain is the change in the length of the object in the axial direction which is normal to the surface of applied load. Strain can be defined as the amount of change in the length of the object over the original length as a result of applying load. dL L =\u00f2 (2) where \u03b5 is strain, dL is the change in length and L is the original length (Figure 1); hence, strain does not have a unit. where \u03c4 is the shear stress, F is the applied force parallel to the surface and A is the cross-section area (Figure 2). The gradient of the force-deformation graph describes the stiffness of the material, and it is the quantification of the rigidity of the material and is expressed in Nm\u22121. Viscoelasticity in Foot-Ground Interaction http://dx.doi.org/10.5772/64170 219 dFStiffness dL= (4) where dF and dL are changes in load and displacement, respectively. Elasticity is the ability of a material to resist force and return to its original shape when the force is removed. Elastic solid materials are divided into two main groups: Hookean and nonHookean [13]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004258_0237-019-01220-7.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004258_0237-019-01220-7.pdf-Figure2-1.png", + "caption": "Fig. 2 Schematic of cilium length measurement. Note, in practice cilia are not tilted so drastically and are nearly vertical", + "texts": [ + " The cilium projects above the cell body, leaving the cells out of focus. As seen in the inset figure, the cilium appears as an in-focus dot against a blurred background. With the trap turned off, ciliated cells were located using brightfield imaging. The length of a cilium was measured optically by recording the z-distance required to move the in-focus object plane from basal end to distal end, and two images acquired to measure the projected distance \u2018r\u2019 between the basal attachment and distal tip. The cilium length L = \u221a r2 + z2 , see Fig.\u00a02. The trap location within the field of view being previously located during the calibration step, the cilium distal tip was moved to the trap location. The trap was then turned on and QPD data acquired at 50\u00a0kSamples/s for several tens of seconds. Because the trap is applied only to the cilium tip and cilia are inextensible, the applied trapping force does not vary with cilium length. Furthermore, because the trapped cilium is observed simultaneously with brightfield illumination, we exclude the case of a bent or otherwise malformed cilium being trapped" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004541_f_version_1700819683-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004541_f_version_1700819683-Figure1-1.png", + "caption": "Figure 1. Four different models for exclusion angles. The half-angle \u03b8e is the exclusion angle. The black arrows represent allowed scattering angles for each model. (a) The uniform distribution of angles allows all scattering angles between 0\u20132\u03c0. (b) The vertical exclusion angle excludes the particle from scattering in the direction of the force for a range given by the half angle \u03b8e. (c) The symmetric vertical exclusion angle disallows scattering both in the direction of the force and in the opposite direction for the same range. (d) The directional exclusion angle disallows scattering in the direction of the particle\u2019s motion just before a scattering event. The red arrow represents the direction of motion before scattering.", + "texts": [ + " A momentum reset on average after scattering. Every model presented in this research satisfies the first condition. The SDS and EDS models do not satisfy the second condition and have a drift velocity which changes (and even slows) with time. In the TDS model, the third condition is affected when the range of scattering angles is limited with exclusion angles. The TDS models are all characterized by an average constant time between collisions. Different ranges of scattering angles are also considered, as shown in Figure 1. The TDS model with a uniform scattering angle satisfies the three conditions above and results in a constant drift velocity. By changing the range of exclusion angles, the average momentum of the particles after scattering will no longer be zero in some cases. This changes the drift velocity behavior. 4.2.1. Uniform Scattering Angle In the uniform scattering angle TDS model (see Figure 1a), when the particle can scatter in any direction with equal probability, the average momentum is still reset after every collision, as in the Drude Model. If there is an average time between scattering and a constant and uniform external force in the \u2212y direction, then the average velocity between scattering events in the direction of the force, \u3008vy\u3009 f light, will be constant for all time. This velocity represents the average motion of the particles in the direction of the force, which is precisely the drift velocity", + " Therefore the TDS models are able to achieve a constant drift velocity even with elastic scattering. A constant drift velocity would also occur with elastic scattering if the the momentum lost in the y direction is completely redirected into the x direction. The redirection of the momentum from the y to the x direction replaces the loss of kinetic energy of the particle implied with inelastic scattering models. This is seen in the symmetric exclusion angle model below. 4.2.2. Vertical Exclusion Angle Once a vertical exclusion angle is introduced, as shown in Figure 1b, the average momentum after scattering is no longer reset. Because the particle is excluded from scattering in the direction of the force, the average momentum after collisions is in the opposite direction of the force. The average momentum after scattering \u3008p\u3009scat can be calculated by averaging over all allowed scattering angles. \u3008~p\u3009scat = \u222b ( px(\u03b8) x\u0302 + py(\u03b8) y\u0302 ) d\u03b8\u222b d\u03b8 (24) The integral of the average momentum is evaluated over the range of allowed scattering angles: \u2212\u03c0 2 + \u03b8e to 3\u03c0 2 \u2212 \u03b8e, where \u03b8e is the exclusion angle", + " In a model with elastic collisions, the speed of the particle is constantly increasing. After each scattering event, \u3008~v\u3009scat will approach the average velocity gained during free flight \u3008~v\u3009 f light. When \u3008~v\u3009scat = \u3008~v\u3009 f light, then the system\u2019s average displacement will stop changing and settle at a maximum value. With no net motion of the particles, the drift velocity of the TDS model with any vertical exclusion angle > 0\u25e6, vdTDS\u2212V , will approach zero. vdTDS\u2212V \u2192 0. (27) 4.2.3. Symmetric Exclusion Angles The symmetric exclusion angle is shown in Figure 1c. In this case, the particle is excluded from scattering in the \u00b1y directions for a given range of angles given by the half angle \u03b8e. The average momentum after scattering can be calculated by averaging over all of the allowed scattering angles. The ranges of allowed scattering angles are equally probable and in opposite directions, so the average momentum after scattering is zero. This means that the momentum is again reset on average after the scattering event, as it was for a uniform distribution of scattering angles between 0\u20132\u03c0", + " The net momentum after scattering is no longer zero; it is in the positive x direction. However, a constant drift velocity, which is measured in the direction of the force, could also be achieved in this case. Therefore, it is only necessary that the momentum in the y direction is reset after scattering in order for the system to reach a constant drift velocity. 4.2.4. Directional Exclusion Angles When the exclusion angle depends on the direction of motion of the particle, as in the case of the directional exclusion angle model (Figure 1d), then the constant drift velocity returns. In fact the drift velocity can be tuned by adjusting the range of excluded angles. The greater the \u03b8e, the smaller the drift velocity, as seen in the slopes of the \u3008y\u3009 vs. t plot in Figure 3d. The drift velocities plotted in Figure 4 shows an almost linear correlation between \u03b8e and vd. In fact, when the directional exclusion angles are repeated for a constant time TDS model, the linear regression is a very close fit. Several attempts have been made to analytically derive the relationship between \u03b8e and vd for directional exclusion angles" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001350__download_21321_6532-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001350__download_21321_6532-Figure1-1.png", + "caption": "Figure 1 Configuration of a two-element antenna array.", + "texts": [ + " Guard traces are widely utilized in PCB circuits for crosstalk reduction between devices on board [16][17]. They have also been used as decoupling structures to minimize EM coupling effects among radiating elements of microstrip array antennas [18]- [24]. However, the guard trace structures used are not simple, which increases the complexity of the antenna structure. This paper proposes simple guard trace structures for suppressing EM coupling between array elements of beamforming antenna arrays. To demonstrate EM coupling between two patch antennas, the configuration shown in Figure 1 was constructed. Two rectangular microstrip antennas, where each antenna patch has width Wa and length La, are arranged in a side-by-side configuration with a center-to-center distance of Sc, which corresponds to an edge-to-edge distance of Se. Each antenna is fed through a microstrip line, which has width Wf and length Lf, respectively, and a transformer line, which has width Wm and length Lm, respectively. The configuration is designed on a 1.6 mm thick FR4 dielectric substrate (\u03b5r = 4.4, tan = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004555_f_version_1699369650-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004555_f_version_1699369650-Figure4-1.png", + "caption": "Figure 4. Cylindrical hourglass-shaped ultrasonic fatigue testing specimen showing main dimensions [25] (with permission from John Wiley and Sons, 2023).", + "texts": [ + " Specimens are excited at their natural frequency; therefore, the maximum stress, but minimum displacement, is experienced at the centre of the specimen. VHCF tests have been demonstrated with both bespoke UFT apparatuses constructed at research institutions and equipment from commercial manufacturers [16]. The UFT method was standardised by the Japan Welding Engineering Society in WES 1112 [24]. Within this standard, the procedure for determining dimensions for standardshaped specimens, e.g., cylindrical hourglass (Figure 4), is specified. Additionally, aspects of the test procedure, such as the tolerance of the resonant frequency and the maximum specimen surface temperature, are detailed [25]. Similar to conventional fatigue testing, UFT can be used to construct an S\u2013N curve of a particular material by testing multiple identical specimens at a range of constant amplitude stress levels. It has been reported that the fatigue data obtained using UFT are often not comparable to that obtained at conventional frequencies, a phenomenon known as the \u201cfrequency effect\u201d [25]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001789_cle_download_505_375-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure9-1.png", + "caption": "Figure 9. Flux density plot of 120 kW, 10 000 rpm reference motor.", + "texts": [], + "surrounding_texts": [ + "In high-speed applications, the performance of the motor is one of the major concerns. And by reducing the iron losses performance of radial flux, IPMSM can be enhanced. This reduction in iron loss can be achieved with the help of better magnetic materials having higher permissible flux density, higher permeability, and lower specific iron loss. Initially, the motors were designed using M19 silicon steel material with magnetic saturation lies between 1.5 \u2013 1.8 T. With the objective of performance enhancement, all three IPMSM of 2 kW, 200 000 rpm, 5 kW, 24 000 rpm and 120 kW, 10 000 rpm are designed using Hiperco 50A magnetic material. Hiperco 50A is a soft magnetic alloy of iron-cobalt-vanadium with a high value of magnetic saturation (2.3 \u2013 2.4 T), which is greater than that of the M19 material\u2019s magnetic saturation point. It also exhibits lower specific iron loss, lower coercive force, and higher permeability. Figure 10 shows the comparison of the B-H curves of Hiperco 50A and M19 core material. It is clearly observed that Hiperco 50A has a knee point of magnetization at a higher flux density compared to that of M19 material. The comparison between specific iron loss of Hiperco and M19 core at 50 Hz frequency is shown in Figure 11. The curve shows that at 50 Hz frequency and 1.5 T, M19 magnetic material has a specific iron loss of 2.4 W/kg while Hiperco 50A material has a specific iron loss of 1.4 W/kg. Hence, it can be stated that Hiperco 50A material exhibits relatively good properties compared to the M19 material. Hiperco 50A, a higher-grade material, is used to form the stator core and teeth, whereas the rotor core material is kept unchanged. The Hiperco 50A material has magnetic saturation at 2.3 T and has properties that make it superior, as discussed in Table 3. Applying Hiperco 50A results in lower iron core losses and decreased magneto-motive force drop on the magnetic circuit. This would appear in the lower excitation requirement of IPMSM [26]. Finite element (FE) models of these ratings created based on the design details are shown in Figure 12. The design details of improved motors with Hiperco 50A material used as stator core for all three ratings are shown in Table 4. Dimensions of the improved motors listed are determined based on manual iterations assuming a higher value of flux density in the stator core as Hiperco 50A has high magnetic saturation (2.3 - 2.4 T). High flux density in the stator core is considered to reduce size and weight. During this exercise, the stator slot area is kept the same as the initial design. The width of the NdFeB permanent magnet bars used for designing the rotor poles, length of the air gap, and outer rotor diameter remain untouched and are similar to those of reference model for all three ratings. The performance results obtained for FEA of the improved models designed using Hiperco 50A material for core are enlisted in Table 5. Improved Hiperco 50A models offer 88.2%, 92.5%, and 93.3% efficiency for 2 kW, 200 000 rpm, 5 kW, 24 000 rpm and 120 kW, 10 000 rpm rating motors, respectively. Improved torque profiles and flux density plots are generated as per the FEA results obtained with the application of Hiperco 50A material as stator core and teeth material. The torque profile and flux density plot of 2 kW, 200 000 rpm IPMSM obtained from FEA for the improved motor is presented in Figure 13 and Figure 14, respectively. The torque profile and flux density plot for the improved motor with rating 5 kW, 24 000 rpm IPMSM using Hiperco 50A material are shown in Figure 15 and Figure 16, respectively. This 5 kW, 24 000 rpm improved IPMSM has average torque of 1.99 N.m., similar to the initial design. Still, the torque profile is considerably better than that of the initially designed motor with M19 material. It can be observed that the actual flux density is close to the assumed flux density in various magnetic sections of both 2 kW and 5 kW motors. Figure 17 and Figure 18 represent the improved torque profile and flux density plot of 120 kW, 10 000 rpm IPMSM with Hiperco 50A material obtained from FEA, respectively. This improved 120 kW, 10 000 rpm IPMSM has average torque of 114 N.m. It is observed that the quality of the torque profile of the 120 kW motor is improved as an added advantage of the use of Hiperco 50A. Similar to the previous two designed motors the actual flux density is close to the assumed flux density in various magnetic sections of the motor." + ] + }, + { + "image_filename": "designv8_17_0000302_f_version_1554344750-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000302_f_version_1554344750-Figure1-1.png", + "caption": "Figure 1. RAVAN payload. (a) Mechanical prototype. (b) Photograph of the flight payload (note: photograph turned 180\u25e6 compared to the model). The payload is contained within a 1U volume (10\u00d7 10\u00d7 10 cm3) and sits atop the spacecraft (s/c) bus (not shown).", + "texts": [ + " Inter-calibration of the primary and secondary radiometers (VACNT vs. cavity) provides another important basis for comparison and degradation monitoring. Finally, internal calibration, where a constant amount of energy is input directly into the radiometer absorbers, removing the thermal link, thermistors, and bridge circuit from the calibration. The RAVAN payload houses primary and redundant pairs of radiometers, as well as a pair of gallium reference sources integrated into two motor-driven doors, as illustrated in Figure 1. The primary radiometers use VACNT absorbers, while the redundant pair (the secondary radiometers) use black-painted cavity absorbers. Each radiometer pair includes a total (Total) channel whose spectral band is set by the absorber and sensitive to nearly all EOR, from the UV to the far infrared (IR), and a SW channel whose band is limited by a sapphire dome, nominally sensing reflected solar radiation. The radiometers, listed in Table 2, are actively temperature controlled and thermally isolated from the spacecraft" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure17-1.png", + "caption": "Fig. 17 The Contact status of the face worm gear drive.", + "texts": [ + " The maximum stress on i surface of the worm gear is 370Mpa and e surface is 420Mpa. From the simulation results, it can be observed that the stress on the i-side of the helicon gear is larger than that on the e-side, which is consistent with the previous analysis results. When combining the tooth surface stresses of the face worm gear drive and the spiroid worm drive, the results demonstrate the regularity of a decrease in curvature induced by a reduction in pinion cone angle. A conclusion can be drawn from Fig. 14 and Fig. 17 that the spiroid gear has a relatively uniform contact area and a larger number of contact teeth under this parameter, indicating a good contact state. (a) Contact status of the on i surface (b) Contact status of the e surface (a) Equivalent stress of the pinion (b) Equivalent stress of the wormwheel 2 \u00a9 2023 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2023jamdsm0073] This research investigates the impact of the pinion cone angle reduction on the meshing performance of the face worm gear drive and reveal the asymmetric meshing characteristics of the tooth surface on both sides of the transmission pair" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure15-1.png", + "caption": "Figure 15: Reference dynamic landing gear mechanism [9].", + "texts": [ + " The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]", + " The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]", + " Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels", + " \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004576__AME_2009_132087.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004576__AME_2009_132087.pdf-Figure7-1.png", + "caption": "Fig. 7. The systems of ith rfe and generalized coordinates", + "texts": [ + " The frame is treated as one beam, which is divided into rfes and sdes. The obtained chain of rfes and sdes is presented in Fig. 6. The position of each rfe of the undeformed beam is defined by the coordinate system E{i} with respect to the coordinate system {0} of rfe 0, by a transformation matrix with constant components: 0 ETi = 0 E\u0398i 0 Esi 0 1 , (8) where 0 E\u0398i is the matrix of cosines of the system E{i} with respect to {0}, and 0 Esi is the vector of coordinates of the origin of the system E{i} in {0} (Fig. 7). The coordinate system {i} rigidly attached to the ith rfe moves together with rfe i when the beam is deformed. Its position in the coordinate 2,AR R 1,AR R 3,AR R 1,AL R 3,AL R }{F 3,F x 1,F x 2,F x )(rfe 0 )(rfe 1 )(rfe Rn )(sde 11, )(rfe 1n 2,AL R )(rfe 21 nn + )(rfe L n )(rfe 321 nnn ++ RS L S )(rfe S n Fig. 6. A-frame as one beam, and its division into rfes and sdes system E{i} is defined by generalized coordinates of the ith element, which are the components of the vector: qi = xi \u03c6i , (9) where xi, j = [ xi,1 xi,2 xi,3 ]T and \u03c6i = [ \u03d5i,1 \u03d5i,2 \u03d5i,3 ]T are vectors of displacements and rotation angles presented in Fig. 7. If we assume that angles \u03d5i, j are small, then the transformation matrix from local coordinate system {i} to the system E{i} takes the following form [15]: Ti = 1 \u2212\u03d5i,3 \u03d5i,2 xi,1 \u03d5i,3 1 \u2212\u03d5i,1 xi,2 \u2212\u03d5i,2 \u03d5i,1 1 xi,3 0 0 0 1 = I + \u2211 D jqi, j, (10) where qi, j = xi, j qi, j+3 = \u03d5i, j for j = 1, 2, 3, D1 = 0 0 0 1 0 0 0 0 0 0 0 0 0 0 0 0 , D2 = 0 0 0 0 0 0 0 1 0 0 0 0 0 0 0 0 , D3 = 0 0 0 0 0 0 0 0 0 0 0 1 0 0 0 0 , D4 = 0 0 0 0 0 0 \u22121 0 0 1 0 0 0 0 0 0 , D5 = 0 0 1 0 0 0 0 0 \u22121 0 0 0 0 0 0 0 , D6 = 0 \u22121 0 0 1 0 0 0 0 0 0 0 0 0 0 0 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000054_f_version_1676018743-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000054_f_version_1676018743-Figure3-1.png", + "caption": "Figure 3. Principle of the experiment platform.", + "texts": [ + " According to Equation (8) and Cauchy inequality, we obtain U2 = k2 d q\u03072 + k2 pq2 + 2kdkpqq\u0307 \u2264 4 3 (k2 d q\u03072 + k2 pq2 + kpkdqq\u0307) (34) Then, substituting Equations (10) and (11) into Equation (34), it has U2 \u2264 4 3 ( kp J2 e Jmax q\u03072 + k2 pq2 + kdkpqq\u0307) \u2264 4 3 (kp Je q\u03072 + k2 pq2 + kdkpqq\u0307) = 8 3 kpV = \u03b22 (35) It is clear that the control input is limited by the parameter \u03b2. By setting U0 = \u03b2, the property P1 will been obtained. To verify the performance of the proposed control, we developed an experimental platform, which is corresponding to the OBM model in Figure 2a. Moreover, before the hardware experiments, we firstly carried out simulations as a preliminary work of the hardware experiments. Before developing the hardware experiment platform, a virtual prototype system is firstly constructed. It is shown in Figure 3. The system consists of a one-link manipulator, a mounted frame (the oscillatory base), spring-tracks and a fixed base. The manipulator together with the mounted frame can oscillate along the tracks under external excitations. The spring is used to simulate the role of the vehicle shock absorber. The manipulator is actuated by a DC motor, and the motor is driven by the computer instructions through a digital position controller. The system parameters are: J2 = 0.009 kg \u00b7m2, m2 = 1.38 kg, a2 = 0", + " The manipulator together with the frame and the spring-track are mounted on the vibration table. We call this oscillation as the compound oscillation in this study. In addition, a two-axis gyroscope is used to measure the pitch oscillation (velocity along z-axis) and roll oscillation (velocity along x-axis). A laser sensor is used to measure the shake oscillation (position along y-axis). For the control hardware system, we adopted a digital positioning controller (MAXON EPOS2) together with a personal computer, as shown in Figure 3. The master-slave technique is used for the hardware communication. The controller communicates as a slave, and the computer communicates as a master. The data transition between PC and controller is based on the USB-serial-port communication protocol. The EPOS2 controller has a build-in control loop. It is a kind of three-loop control method, which consists of a current loop, a position loop and a velocity loop. For our experiments here, the embedded current-loop is adopted, but the position-velocity loop is replaced by our self-build control loop" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001635__icoev2018_05003.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001635__icoev2018_05003.pdf-Figure1-1.png", + "caption": "Fig. 1. Cross-sectional view of an electrodynamic shaker.", + "texts": [ + " It is now possible to obtain a response in real time or even more rapidly from the response of a structure to a vibration test, to optimize the physical test or the structure to be tested, or to study the influence of specific loads, to implement the optimized signals in order to get more from the test infrastructure, to better anticipate the boundary conditions between the exciter and the structure under test, etc. The simulation of a physical vibration test is carried out by modeling each of the constituent elements of this test [1, 2]. The shaker plays a primordial role and the validity of the simulation depends almost exclusively on the validity of the model of the shaker. The latter is based on the physical characteristics of the constituent elements. A good determination of the parameters of the shaker will therefore be essential. Figure 1 shows a cross-sectional view of an electrodynamic shaker. It essentially operates as a loudspeaker \u2013 vibration is generated by a current flowing in a coil immersed in a magnetic field \u2013 but where guides and suspensions have been added, making this system an electro-mechanical system. \u00a9 The Authors, published by EDP Sciences. This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0/). The shaker can be modeled by mechanical lumped parameters but an electrodynamic relationship has to be added to represent the behavior of the coil when a signal is applied to its terminals" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.5-1.png", + "caption": "Figure 2.5 Concept of current probe [9]", + "texts": [ + "1) Ampere's law shows that a magnetic field can be induced around a contour by either conduction current or displacement current that penetrates the open surface S. A timechanging electric field produces a displacement current. If no time-changing electric field penetrates this surface, the induced magnetic field is directly related to the conduction current passing through the loop. A current probe is constructed from a core of ferrite material. When a current is passed through a ferrite core with an N number of turns, it will produce a magnetic field circulating around the core, as shown in Figure 2.5. The purpose of a current probe is to measure the amount of current passing through the conductor. However, regarding the current probe antenna [9] in general, the antenna voltage is the product of the effective length of the antenna times the incident electric field. An incoming RF signal may be considered as the incident electric field. The antenna current is obtained from the antenna voltage divided by the self-impedance of the antenna. The antenna current in turn generates the magnetic field, which is then picked up by the current probe" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002527_O201322658551356.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002527_O201322658551356.pdf-Figure3-1.png", + "caption": "Figure 3. Boundary range and balance margin of four-legged robots. COM, center of mass; COFP, centroid of the foot polygon.", + "texts": [ + " During walking, the foot polygon varies based on the location (A, B, or C for f1) of the moving foot, as shown in Figure 2. If the location of the first foot (f1) is assigned as A, the system balance improves intuitively. Therefore, our goal is to devise a feasible measure for identifying the degree of balance of any quadruped walking configuration and demonstrate the applicability of said measure to the analysis of quadruped robotic walking. Consider an arbitrary motion of a quadruped robot in a landing situation, as shown in Figure 3. The landing situation implies that all feet are stably on ground, and the entire range of body motion within the operating range of the robot system is available. For effective description, we approximated body motion to the movement of the robot system\u2019s COM. In general, a quadruped robot system can attain a balanced posture so long as the vertical projection of its COM lies within the boundary of its foot polygon. The balance worsens if the vertical projection of the robot system\u2019s COM lies outside the foot polygon. Based on this concept, we propose a boundaryrange-based balance margin that can be used for checking the degree of balance of a quadruped walking configuration. Figure 3 shows a schematic diagram of the process of defining the boundary range based on a quadruped robot\u2019s motion. Here, each foot lands on the xy plane, and the robot\u2019s COM projected on that plane can be located as being inside, on the edge, or outside of the foot polygon according to the motion trajectory in the stationary and mobile situations. As shown in Figure 3, the boundary range is defined as the distance between the centroid of the foot polygon (COFP) and p\u2217. p\u2217 lies at the point of intersection of the line between the COFP and the COM projected 101 | Byoung-Ho Kim http://dx.doi.org/10.5391/IJFIS.2013.13.2.100 on the supporting plane, and the boundary of the polygon. The supporting plane refers to the plane that is formed by the two neighboring feet, f1 and f4, and the centroid in Figure 3. If the position of the COM is the same as that of the COFP, the boundary range is assigned as the minimum distance between the COPF and the edge of the foot polygon. In order to present the balance margin during walking, we first check the point of intersection of p\u2217(x\u2217, y\u2217) for the boundary range based on the previous research [7]. We used the following procedure to effectively determine the point of intersection. First, if the coordinates of the COM are different from that of the COFP, the x- and y-directional positions of the point of intersection can be determined as follows: x\u2217 = (b12 \u2212 bcc)/(acc \u2212 a12) : \u03b11 \u2264 \u03b1 < \u03b12 (b23 \u2212 bcc)/(acc \u2212 a23) : \u03b12 \u2264 \u03b1 < \u03b13 (b34 \u2212 bcc)/(acc \u2212 a34) : \u03b13 \u2264 \u03b1 < \u03b14 (b41 \u2212 bcc)/(acc \u2212 a41) : \u03b14 \u2264 \u03b1 < \u03b11 (1) y\u2217 = accx \u2217 + bcc (2) where aij(i = 1, 2, 3, 4, j = 2, 3, 4, 1) and bij(i = 1, 2, 3, 4, j = 2, 3, 4, 1) denote the slope of the line connecting the robotic feet fi and fj, and the y-intercept, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001882_O201336447764690.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001882_O201336447764690.pdf-Figure5-1.png", + "caption": "Figure 5. View of side-overturn test of the prototype vehicle.", + "texts": [ + " Field testing for the prototype vehicle Side-overturn testing of prototype vehicleA side-overturn test of the prototype vehicle was performed to find out a side-overturn angle of the prototype vehicle due to the differential sinking while driving in paddy field. A side-overturn angle of prototype vehicle was measured with one side rubber crawler of prototype fixed on the test plate and the other side rubber crawler free when the prototype vehicle is deviated by inclining the test plate of the side-overturn measuring device. Figure 5 shows measurement of the side-overturn angle of the prototype crawler vehicle. Driving and drawbar pull test The driving test of prototype vehicle was carried with the load acting on the rubber crawler according to the weight of harvest device attached on the front of the prototype vehicle.As shown at the Table 4, the driving test of prototype vehicle was tested at 3 levels according to the weights of prototype (5.59, 7.64, 9.21 kN) while the sinking of the rubber crawlers was measured while performing each driving test" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002325_16.99.108_linkid_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002325_16.99.108_linkid_pdf-Figure1-1.png", + "caption": "Fig. 1(a-d): Vector diagram of internal flux density (a) 2-pole motor, (b) 4-pole motor, (c) 6-pole motor and (d) 8-pole motor", + "texts": [ + " Relationship between the number of magnetic poles P and maximum output torque: In the case of the same permanent magnet volume and thickness for the rotor core, it is important to study the maximum output torque of the motor under the different number of magnetic poles. Using ANSYS software, the properties, meshings, settings for solving of materials are designated through the process of creation of simulation model. In an attempt to simulate the motor magnetic field of the different number of poles, results of the motor internal flux density are shown in Fig. 1. When P = 2, the maximum output torque is 50.05 Nm, when P = 4, the maximum output torque is 70.45 Nm, when P = 6, the maximum output torque is 74.29 Nm and when P = 8 the maximum output torque is 79.81 Nm. For the permanent magnet synchronous motor, the maximum of motor output torque is also known as the pull out torque. If the load torque exceeds this value, the motor will not maintain the synchronous speed. Generally, the ratio of motor maximum output torque to the rated torque TN(t = Tmax/TN) is defined as the pull out torque multiple, which is used to measure the overload capacity t of motor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004978_0846-023-01961-9.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004978_0846-023-01961-9.pdf-Figure7-1.png", + "caption": "Fig. 7 Graphical depiction of the commanded behaviour during execution ofE2 policy", + "texts": [ + " The desired decomposition, m \u2208 Z +, is dependent on \u03b1. \u03c8 k+1,k re f = \u03c8k re f + \u03b1, \u2200 m (9) where, m \u2248 \u03c0 0.5 \u03b1 Let G \u2208 R be the information gained, which in this case corresponds to the size of P f obtained at each view pose during surveying. The target view poses to be maintained by theUAV ismodelled to face towards the direction ofmax{G}, shown in Fig. 6(c). LetE2 be the secondary survey policy. In a situationwhere G = \u2205 at the end of E1 search or at the initialization of the mission, as portrayed in Fig. 7(a), the exploration behaviour is escalated to encapsulate 360\u25e6 search space around theUAV, shown in Fig. 7(b). In addition to that, E2 policy is flagged whennoprior inspection behaviour is registered such as at the event of initialization of the mission. As shown in Eq. 9, E2 follows a similar formulation, although in this case,m \u2248 2\u03c0 \u03b1 . Figure 7(c) presents the target view-pose for max{G} at the end of E2 policy. If no new structures are detected at the end of E2, i.e. G = \u2205, or when the condition ofmax{P f (z)} < puav(z), i.e when nomore potential extension of the structure is observed above the current position of the UAV, the exploration behaviour is again escalated to its last and final stage. Let E3 be the tertiary surveypolicy.DuringE3, theUAVis directed to backtrack through a stored repository of visited inspection view poses, \u03be insp \u2286 \u03be , with an offset of 180\u25e6 to each view orientation registered at the candidate pose, shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000266__titds2023_05005.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000266__titds2023_05005.pdf-Figure2-1.png", + "caption": "Fig. 2. Calculation scheme for determining the length of the caterpillar bypass.", + "texts": [ + " As mentioned above, during movement, the tension forces in the caterpillar are redistributed, which leads to changes in the position of the TTV body and the geometry of the bypass. As a result of the difference between the perimeter of the bypass and the length of the caterpillar ,by catl S S , an additional tensile force ,cat\u0422 \u0441 l appears where cby is the stiffness of the caterpillar bypass. Then the actual tension in the free branch becomes: fr pr cT \u0422 \u0422 \u0422 . (4) The perimeter of the bypass, shown in Figure 2 can be determined by the formula: 1 1in 1 2tr 2in 2 2 1 ,by tr re up upS S S S S S S S S S (5) where S1 is the length of the guide (driving) wheel coverage, S1in is the length of the front inclined branch of the bypass, S1tr is the length of the coverage of the front road wheel, Sre is the length of the support branch, S2tr is the length of the coverage of the rear support roller, S2in is the length of the rear inclined branch of the bypass, S2 - the length of the coverage of the driving (guiding) wheel, S2up - the length of the constant part of the upper branch of the bypass, S1up - the length of the variable part of the upper branch of the bypass" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001203_el-01058504_document-Figure2.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001203_el-01058504_document-Figure2.5-1.png", + "caption": "Figure 2.5 TAS approach structure.", + "texts": [ + " Furthermore, the high currents (>10 mA) to generate magnetic fields CHAPTER 2 STATE OF THE ART 17 yield considerable power consumption meanwhile the electromigration effect limits its scalability. These issues hinder its commercialization. Thanks to the toggle switching patterned by Freescale, MRAM based on this advanced switching method was commercialized in 2006 [20]. However this approach cannot yet overcome the drawbacks of speed, density and power caused by using magnetic field for switching. To improve the performances of write selectivity, power consumption and thermal stability, thermally assisted switching (TAS) was proposed (see Figure 2.5) [21-22]. It is worthy noting that an additional anti-ferromagnetic (AFM) layer is normally added above the free layer to pin CHAPTER 2 STATE OF THE ART 18 the free layer at the standby temperature. Its basic principle is that a current flowing through MTJ heats the magnetic layers above their magnetic ordering temperature to reduce greatly the required switching field [23]. Similar to the FIMS structure, two orthogonal current lines are installed to achieve write selectivity; in contrast, one (Ih) is used to heat the MTJ and the other (Ib) is used to generate the switching field" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003597_f_version_1683599236-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003597_f_version_1683599236-Figure11-1.png", + "caption": "Figure 11. The flight chain.", + "texts": [ + " Drones 2023, 7, 308 8 of 12 Drones 2023, 7, 308 8 of 14 Figure 9. An estimation of the glider efficiency vs. height during the Fragneto Monforte experimental flight. 0 2000 4000 6000 8000 10000 12000 14000 0 1 2 3 4 5 6 7 8 height (km) e ff ic ie n c y 0 2 4 6 8 10 12 14 e ff ic ie n c y e ff ic ie n c y Figure 9. An estimation of the glider efficiency vs. height during the Fragneto Monforte experimental flight. Figure 10. (a) The payload in flight configuration; (b) The launch method: Hercules. Figure 11 (courtesy of SSC) shows the block diagram of the flight chain. Starting from the top, we find the zero-pressure balloon (ZPB, 3000 m3) which was used, the PTU sounding station (pressure, temperature, relative humidity, etc.), the termination system, the parachute (19 feet diameter, 26.4 m2), the SSC telemetry module (with transponder), the truck plate, and finally the payload. Figure 11 (courtesy of SSC) shows the block di gram of the flight chain. Starting from the top, we find the zero-pressure balloon (ZPB, 3000 m3) which was used, the PTU sounding station (pressure, temperature, relative humidity, etc.), the termination system, t e parachute (19 feet diameter, 26.4 m2), the SSC telemetry module (with transponder), the truck plate, and finally the payload. Drones 2023, 7, 308 9 of 12Drones 2023, 7, 308 10 of 14 Figure 11. The flight chain. Figure 12a shows the moments before the launch, then Figure 12b shows the balloon beginning to ascend at an ascent rate of about 4.1 m/s. After about 1 h and 40 min, the balloon reached an altitude of about 23 km and entered the floating phase. Figure 12a shows the moments before the launch, then Figure 12b shows the balloon beginning to ascend at an ascent rate of about 4.1 m/s. After about 1 h and 40 min, the balloon reached an altitude of about 23 km and entered the floating phase" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure5-1.png", + "caption": "Fig. 5 Diagram of anti-rolling torsion bar device: (a) Anti-roll torsion bar device with fixed simply 589 supported on bolster; (b) Anti-roll torsion bar device with floating simply supported on bolster 590", + "texts": [ + " 561 (3) Different from the tight track gauge or narrow track window like German ICE 562 rail system, Chinese HSR practices need to undergo the intensive research of wheel-rail 563 relationship, i.e. singularities of anti-roll complex constraints and associated negative 564 influences feedback to the creepage and wear of corresponding wheels. Especially for 565 mountain lines, open and dark lines are staggered, and unsteady aerodynamic loads will 566 force the primary hunting to turn into the secondary hunting phenomenon, which will 567 lead to high-speed car body shaking at low conicity. 568 For the anti-roll torsion bar devices adopted in German ICE3 serial bogies, as shown 580 in Fig. 5 (a, b), the torsion bar is placed on the top, by which the fixed or floating simple 581 support can be constructed on the bolster. The torsion bar itself does not work when 582 running in tangent lines or in large radius curving negotiation. While running through 583 transition curves, turnouts or trains passing each other, the roll and rock of service car 584 body occurs thereby, resulting in the torsion bar twisted and deformed. As such, the 585 stiffness contribution of the fixed simply supported torsion bar is ca" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004015_id_1451-48692102211M-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004015_id_1451-48692102211M-Figure1-1.png", + "caption": "Fig. 1 \u2013 Three-dimensional view of the proposed antenna.", + "texts": [ + " In this paper, we explore the possibility of combining slots of varying sizes and shape on a lossy substrate to achieve bandwidth improvement. A SIW cavity-backed antenna with a dual dumbbell and small rectangular slots has been designed to achieve an impedance bandwidth of 9.2%. This paper is organized as follows; Section 2 presents the design and analysis Section 3 presents the bandwidth enhancement, Section 4 shows the parametric analysis and Section 5 explains the results and discussion and the paper concludes in Section 6. The structure of the designed SIW cavity-backed antenna is shown in Fig. 1. The dumbbell-shaped slots and a rectangular slot are etched on the top layer of the cavity and at a distance of 5.5 mm from the back end of the cavity. The SIW cavity is built on a single substrate surrounded by three rows of metallic vias that form three sidewalls of the cavity. The orientation of the field is in a zigzag direction inside the SIW, and the surface waves contribute to radiations that travel in the vertical direction and not in the direction of propagation. The diameter and pitch of the cylindrical via holes are chosen in such a way to ensure minimum radiation leakage losses [4]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure53-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure53-1.png", + "caption": "Figure 53 P-POD Mk. IV Door Stress", + "texts": [ + " Door deflection values for the P-POD Mk. IV Door were roughly one half those of the previous design, which was considered to be a success. The stress of the part exhibited a slight decrease in stress at the high stress point of the door, on the inner edge of the inner hinge. Coupled with the allowable stress inscrease due to the removal of the PTFE baking process for the coating, this part exhibits a significantly higher margin of safety than the previous design. The resulting analysis stress plots are shown below in Figure 53. Additionally, a hinge closeup is shown in Figure 54. The Page 68 hinge exhibits significant stress, but shows up light blue instead of red because of some severe stress elements near boundary conditions. The Margin of Safety at the maximum stress point depicted was 0.06. This is significantly lower than other components of the P-POD, but the previous design exhibited a negative margin, so this was considered a Page 69 significant improvement. The changes to the door resulted in a 18 gram mass increase, which was worth the improvement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004291_advpub_22-00301__pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004291_advpub_22-00301__pdf-Figure9-1.png", + "caption": "Fig. 9 Top view of the suspension when SAT acts on the wheel. The black arrows represent the forces acting on points A, B and C. The white arrows represent the directions of the displacements of points D and H. The force acting on point B of the lower arm may rotate the lower arm about point D, although it is not the case in this figure.", + "texts": [], + "surrounding_texts": [ + "\u00a9 The Japan Society of Mechanical Engineers\n\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u4e00\u822c\u306b\u306f\u5c0f\u3055\u3044\u305f\u3081\uff0c\u5f8c\u306e\u6570\u5024\u4f8b\u3067\u793a\u3059\u3088\u3046\u306b\uff0c\u6700\u7d42\u7684\u306a LF-C/S \u306f\u3053\u308c\u3089 3 \u3064\u306e\u30e2\u30fc\u30c9\u306e\u7dda\u5f62 \u548c\u3067\u8fd1\u4f3c\u3067\u304d\u308b\uff0e\u901a\u5e38\u306f LF\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\u5fae\u5c0f\u306a\u30c8\u30fc\u30a2\u30a6\u30c8\u3068\u3059\u308b\u3053\u3068\u304c\u671b\u307e\u3057\u3044\uff0e\u305f\u305d\u306e\u305f\u3081\u30e2\u30fc\u30c9\u2160\u306b \u3088\u308a\u30c8\u30fc\u30a4\u30f3\u3068\u306a\u308b\u5834\u5408\u306b\u306f\uff0c\u3053\u3053\u3067\u306e\u8b70\u8ad6\u306b\u57fa\u3065\u304d\u30e2\u30fc\u30c9\u2161\u304a\u3088\u3073\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u4f7f\u7528\u3057\u3066\u6700\u7d42 \u7684\u306a\u30c8\u30fc\u89d2\u5909\u5316\u3092\u5fae\u5c0f\u306a\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\u8a2d\u8a08\u8af8\u5143\u3092\u5b9a\u3081\u308c\u3070\u3088\u3044\u3053\u3068\u306b\u306a\u308b\uff0e\n4. \u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e SAT\u306b\u3088\u308b\u6319\u52d5\n\u672c\u7ae0\u3067\u306f SAT \u306b\u3088\u308b\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u6319\u52d5\u3092\u8003\u5bdf\u3057\uff0c\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u8a2d\u8a08\u306b\u304a\u3044\u3066 SAT-\nC/S\u306b\u76f4\u63a5\u95a2\u4fc2\u3059\u308b\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u8a2d\u8a08\u8af8\u5143\u3092\u660e\u3089\u304b\u306b\u3057\u305f\uff0e\n4\u30fb1. SAT\u4f5c\u7528\u6642\u306e\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u6319\u52d5 LF\u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u3068\u540c\u69d8\u306b\uff0cSAT \u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u306b\u3082\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u5404\u70b9\u306f\u4e3b\u306b X-Y\u5e73\u9762\u5185\u3067\u5909\u4f4d\u3057\uff0c\u305d\u306e \u7d50\u679c\u3068\u3057\u3066\u30db\u30a4\u30fc\u30eb\u306b\u30c8\u30fc\u89d2\u5909\u5316\u304c\u751f\u3058\u308b\uff0e\u3053\u3053\u3067\u3082\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u5404\u70b9\u306b\u4f5c\u7528\u3059\u308b\u529b\u3068\u305d\u308c\u306b\u3088\u308b\u6319\u52d5\u306b\u3064 \u3044\u3066\u8003\u5bdf\u3092\u884c\u3046\uff0e\u307e\u305a\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u652f\u6301\u70b9\u3067\u3042\u308b\u70b9 A, B, C \u306b\u4f5c\u7528\u3059\u308b\u529b\u306e Y \u8ef8\u65b9\u5411\u6210\u5206\u306e\u5411\u304d\u304a\u3088\u3073\u5927\u304d\u3055 \u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u56f3 3\u306b\u793a\u3057\u305f\u3088\u3046\u306b\uff0c\u5de6\u65cb\u56de\u6642\u306b\u306f\u6642\u8a08\u307e\u308f\u308a\u306e SAT \u304c\u4f5c\u7528\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u306e \u91e3\u5408\u3044\u304b\u3089\uff0c\u53f3\u5074\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e Y\u8ef8\u65b9\u5411\u6210\u5206\u306f\u305d\u308c\u305e\u308c\u8eca\u4e21\u5185\u5411\u304d\u304a\u3088\u3073\u5916\u5411\u304d\u306b\u306a\u308b\uff0e \u70b9 A\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5411\u304d\u304a\u3088\u3073 3\u3064\u306e\u70b9\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5927\u304d\u3055\u306b\u3064\u3044\u3066\u691c\u8a0e\u3059\u308b\u305f\u3081\uff0c\u56f3 8\u306b\u793a\u3059\u30db\u30a4\u30fc\u30eb\u90e8\u306e \u80cc\u9762\u8996\u3092\u8003\u3048\u308b\uff0e\u3053\u3053\u3067\u306f\u70b9 J\u306b\u306f\u529b\u306f\u4f5c\u7528\u3057\u306a\u3044\u3068\u3059\u308b\uff0e\u70b9 B, C\u306b\u304a\u3044\u3066\u306f\u3059\u3050\u4e0a\u3067\u8ff0\u3079\u305f\u3088\u3046\u306b\uff0c\u305d\u308c\u305e\u308c \u8eca\u4e21\u5185\u5411\u304d\u304a\u3088\u3073\u5916\u5411\u304d\u306e\u529b\u304c\u4f5c\u7528\u3059\u308b\uff0e\u56f3 8\u3067\u306f\u3053\u308c\u3089\u306e\u529b\u3092\u9ed2\u77e2\u5370\u3067\u793a\u3057\uff0c\u305d\u306e\u5927\u304d\u3055\u3092 FBY, FCY\u3067\u8868\u3057\u305f\uff0e \u307e\u305f\uff0c\u70b9 A\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5927\u304d\u3055\u3092 FAY\u3068\u3059\u308b\uff0e\u70b9A, B\u9593\u304a\u3088\u3073\u70b9 A, C\u9593\u306e Z\u8ef8\u65b9\u5411\u306e\u8ddd\u96e2\u3092\u305d\u308c\u305e\u308c b\u2019, c\u2019\u3068 \u3059\u308b\u3068\uff0c\u70b9 A\u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u91e3\u5408\u3044\u3088\u308a FBY : FCY = c\u2019 : b\u2019\u3068\u306a\u308b\uff0e\u307e\u305f\u70b9 C\u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u91e3\u5408\u3044 \u3088\u308a\uff0c\u70b9 A\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5411\u304d\u306f\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5411\u304d\u3068\u540c\u69d8\u306b\u8eca\u4e21\u5185\u5411\u304d\u306b\u306a\u308a FAY : FBY = b\u2019c\u2019 : c\u2019\u3068\u793a\u3055 \u308c\u308b\uff0eb\u2019\u3068 c\u2019\u306e\u5dee\u306f\u5927\u304d\u304f\u306f\u306a\u3044\uff0e\u305d\u306e\u305f\u3081 FBY\u3068 FCY\u306f\u540c\u7a0b\u5ea6\u3067\u3042\u308a\uff0cFAY\u306f\u6bd4\u8f03\u7684\u5c0f\u3055\u3044\u3053\u3068\u304c\u5206\u304b\u308b\uff0e\u3064\u304e \u306b\uff0c\u70b9 A\u306e\u5909\u4f4d\u306e\u5411\u304d\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u70b9 A\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5411\u304d\u306f\u56f3 4(b)\u306b\u793a\u3059 LF\u306e\u5834\u5408\u3068\u540c\u3058\u306b\u306a\u308a\uff0c\u70b9A \u306e\u5909\u4f4d\u306f\u56f3 8 \u306b\u767d\u629c\u304d\u77e2\u5370\u3067\u793a\u3059\u3088\u3046\u306b\u8eca\u4e21\u5916\u5411\u304d\u3068\u306a\u308b\uff0e\u3053\u306e\u5909\u4f4d\u306b\u3088\u308a SAT \u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u306b\u3082 LF-C/S \u540c \u69d8\u306b\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u304c\u751f\u3058\u308b\u3053\u3068\u304c\u5206\u304b\u308b\uff0e", + "\u00a9 The Japan Society of Mechanical Engineers\n\u3064\u304e\u306b\uff0c\u56f3 9\u306b\u793a\u3059\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u5e73\u9762\u8996\u306b\u3088\u308a\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u56f3 9\u3067\u306f SAT \u3092\u70b9 I \u307e\u308f\u308a\u306b\u4f5c\u7528\u3059\u308b\u30e2\u30fc\u30e1\u30f3\u30c8\u3068\u3057\u3066\u9ed2\u77e2\u5370\u3067\u793a\u3057\u3066\u3042\u308b\uff0e\u6700\u521d\u306b\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3064\u3044\u3066\u8003 \u3048\u308b\uff0e\u3053\u3053\u3067\u306f\uff0cX\u8ef8\u65b9\u5411\u6210\u5206\u3082\u542b\u3081\u3066\u8003\u3048\u308b\uff0eLF\u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u3068\u540c\u69d8\u306b\uff0c\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u30bf\u30a4\u30ed\u30c3\u30c9\u8ef8 C-H \u306b\u6cbf\u3063\u305f\u3082\u306e\u3068\u306a\u308b\uff0e\u524d\u8ff0\u306e\u3088\u3046\u306b\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 C \u306b\u4f5c\u7528\u3059\u308b\u529b\u306e Y \u8ef8\u65b9\u5411\u6210\u5206\u306f\u8eca\u4e21\u5916\u5411\u304d\u3067\u3042\u308b\u305f \u3081\uff0c\u56f3 9\u306e\u5e73\u9762\u8996\u306b\u304a\u3044\u3066\u306f\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u8eca\u4e21\u5916\u5411\u304d\u3067\u3084\u3084\u524d\u65b9\u3092\u5411\u304f\uff0e\u70b9 A\u306b\u4f5c\u7528\u3059\u308b\u529b \u306f Y\u8ef8\u306b\u6cbf\u3063\u305f\u65b9\u5411\u3067\u3042\u308b\u3068\u3059\u308b\u3068\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u529b\u306e\u91e3\u5408\u3044\u304b\u3089\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u8eca\u4e21\u5185\u5411\u304d\u3067\u3084\u3084\u5f8c\u65b9\u3092 \u5411\u304f\uff0e\u56f3 9\u306b\u3053\u308c\u3089\u306e\u529b\u3092\u9ed2\u77e2\u5370\u3067\u8868\u3057\u305f\uff0e\u307e\u305f\uff0c\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5927\u304d\u3055\u3092\u305d\u308c\u305e\u308c FB, FC\u3068\u3057\u305f\uff0e\u3064\u304e \u306b\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u304a\u3088\u3073\u30bf\u30a4\u30ed\u30c3\u30c9\u4e0a\u306e\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u3053\u308c\u3089\u306e\u70b9\u306b\u306f\u30db\u30a4\u30fc\u30eb\u90e8\u306e \u70b9 B, C \u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u53cd\u4f5c\u7528\u304c\u50cd\u304f\uff0e\u305d\u306e\u305f\u3081\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 B, C \u306b\u4f5c\u7528\u3059\u308b\u529b\u3068\u306f\u5411\u304d\u304c\u9006\u3067\u540c\u3058\u5927\u304d\u3055 \u306e\u529b\u304c\u4f5c\u7528\u3059\u308b\uff0e\u6700\u5f8c\u306b\uff0c\u3053\u308c\u3089\u306e\u529b\u306b\u3088\u308b\u5909\u4f4d\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u70b9 D\u3092\u8eca \u4e21\u5916\u5411\u304d\u306b\u5909\u4f4d\u3055\u305b\uff0c\u30bf\u30a4\u30ed\u30c3\u30c9\u4e0a\u306e\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u70b9H\u3092\u8eca\u4e21\u5185\u5411\u304d\u306b\u5909\u4f4d\u3055\u305b\u308b\uff0e\u56f3 9\u3067\u306f\u3053\u308c\u3089\u306e\u5909 \u4f4d\u3092\u767d\u629c\u304d\u77e2\u5370\u3067\u793a\u3057\u305f\uff0e\u4e21\u8005\u306e\u5909\u4f4d\u5dee\u306b\u3088\u308a SAT \u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u306b\u3082 LF-C/S\u540c\u69d8\u306b\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316 \u304c\u751f\u3058\u308b\u3053\u3068\u304c\u5206\u304b\u308b\uff0e\u307e\u305f\uff0c\u4e00\u822c\u306b\u306f\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3088\u308a\u30ed\u30a2\u30a2\u30fc\u30e0\u306f\u70b9 D\u307e\u308f\u308a\u306b\u56de\u8ee2 \u3057\uff0cLF-C/S\u540c\u69d8\u306e\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3082\u5b58\u5728\u3059\u308b\uff0e\u305f\u3060\u3057\uff0c\u56f3 9\u306b\u793a\u3059\u3088\u3046\u306b\u8fba B-D\u3068\u8ef8 C-H\u304c\u5e73\u884c\u306b\u8fd1 \u3044\u5834\u5408\u306f\uff0c\u70b9 B \u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3088\u308b\u70b9 D \u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u306f\u5c0f\u3055\u304f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u56de\u8ee2\u3082\u5c0f\u3055\u3044\uff0e\u4ee5\u4e0b\u306b\uff0c SAT-C/S\u306b\u304a\u3051\u308b\u30e2\u30fc\u30c9\u2160\uff0c\u30e2\u30fc\u30c9\u2161\uff0c\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\n4\u30fb2 \u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316 \u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B, C \u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5411\u304d\u306f\u56f3 9 \u306b\u793a\u3059\u3088\u3046\u306b\u306a\u308b\uff0e\u305d\u306e\u305f\u3081\u70b9 D \u306e\u5909\u4f4d\u306f\u56f3 9 \u306e\u3088\u3046\u306b\u8eca \u4e21\u5916\u5411\u304d\u306b\u306a\u308a\u70b9 H\u306e\u5909\u4f4d\u306f\u8eca\u4e21\u5185\u5411\u304d\u306b\u306a\u308b\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u3068\u306a\u308b\uff0e\u672c \u30e2\u30fc\u30c9\u3067\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306e\u5927\u304d\u3055\u306f\u70b9 D, H\u306e\u5909\u4f4d\u306e\u5927\u304d\u3055\u306b\u3088\u308a\u6c7a\u307e\u308b\u306e\u3067\uff0cFBY\uff0cFCY\u304a\u3088\u3073 kDY\uff0ckHY\u306b\u3088\u308a\u6c7a\u307e \u308b\uff0e\u3053\u306e\u3046\u3061 FBY\uff0cFCY\u306f FAY\u306e\u5927\u304d\u3055\u304c\u5927\u304d\u304f\u306a\u3044\u3053\u3068\u304b\u3089\uff0cFBY\uff0cFCY\u306b\u3088\u308b\u70b9 I\u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u304c\u307b\u307c SAT \u3068\u91e3\u5408\u3046\u3088\u3046\u306b\u5b9a\u307e\u308b\u3068\u8003\u3048\u3089\u308c\u308b\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u70b9 B, C\u9593\u306e\u8eca\u4e21\u524d\u5f8c\u65b9\u5411\u306e\u8ddd\u96e2\u304c\u5927\u304d\u3051\u308c\u3070 FBY, FCY\u306f\u5c0f\u3055 \u304f\u306a\u3063\u3066\u30c8\u30fc\u30a2\u30a6\u30c8\u91cf\u304c\u6e1b\u308a\uff0c\u9006\u306b\u70b9 B, C\u9593\u306e\u8eca\u4e21\u524d\u5f8c\u65b9\u5411\u306e\u8ddd\u96e2\u304c\u5c0f\u3055\u3051\u308c\u3070 FBY, FCY\u306f\u5927\u304d\u304f\u306a\u3063\u3066\u30c8\u30fc\u30a2 \u30a6\u30c8\u91cf\u304c\u5897\u3048\u308b\uff0e\n4\u30fb3 \u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316 LF \u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u3068\u540c\u69d8\u306b\uff0c\u8ef8 C-H \u304c\u8fba B-D \u3068\u5e73\u884c\u306a\u5834\u5408\uff08\u56f3 9\uff09\uff0c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u5e83\u304c\u3063\u3066\u3044\u308b\u5834\u5408 \uff08\u56f3 10(a)\uff09\uff0c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u72ed\u304f\u306a\u3063\u3066\u3044\u308b\u5834\u5408\uff08\u56f3 10(b)\uff09\u306e 3\u3064\u306b\u884c\u3044\u3066\u8003\u3048\u305f\uff0eSAT \u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u306b \u306f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u56de\u8ee2\u65b9\u5411\u306f\uff0c\u56f3 10(a)\uff0c\u56f3 10(b)\u306e\u3088\u3046\u306b\u70b9 B\u3068\u70b9 D\u306e\u8eca\u4e21\u306e\u524d\u5f8c\u4f4d\u7f6e\u95a2\u4fc2\u306b\u4f9d\u5b58\u3057\u306a\u3044\uff0e\u305d\u306e", + "\u00a9 The Japan Society of Mechanical Engineers\n\u305f\u3081\uff0c\u3053\u3053\u3067\u306f\u70b9 B \u304c\u70b9 D \u3088\u308a\u3082\u8eca\u4e21\u524d\u65b9\u306b\u4f4d\u7f6e\u3059\u308b\u5834\u5408\u306b\u3064\u3044\u3066\u306e\u307f\u8003\u3048\u308b\uff0e\u306f\u3058\u3081\u306b\uff0c\u8ef8 C-H \u304c\u8fba B-D \u3068 \u5e73\u884c\u306a\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306f\u4e0a\u3067\u8ff0\u3079\u305f\u3088\u3046\u306b\uff0c\u70b9 B \u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3088\u308b\u70b9 D \u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u306f\u5c0f\u3055 \u304f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u56de\u8ee2\u3082\u5c0f\u3055\u3044\uff0e\u3057\u305f\u304c\u3063\u3066\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\u5c0f\u3055\u3044\u3082\u306e\u306b\u306a\u308b\uff0e\u3064\u304e\u306b\uff0c\u8ef8 C-H \u3068 \u8fba B-D \u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u5e83\u304c\u3063\u3066\u3044\u308b\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306e\u529b\u306e\u4f5c\u7528\u56f3\u3092\u56f3 10(a)\u306b\u793a\u3059\uff0e\u3053\u306e \u5834\u5408\u306f\uff0c\u8fba B-D \u3068\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B \u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5411\u304d\u306e\u95a2\u4fc2\u304b\u3089\u30ed\u30a2\u30a2\u30fc\u30e0\u306f\u53cd\u6642\u8a08\u307e\u308f\u308a\u306b\u56de\u8ee2\u3057\uff0c\u56f3 6(b)\u306b\u793a\u3057\u305f\u306e\u3068\u540c\u69d8\u306b\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\uff0e\u6700\u5f8c\u306b\uff0c\u8ef8 C-H\u3068\u8fba B-D\u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066 \u72ed\u304f\u306a\u3063\u3066\u3044\u308b\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306e\u529b\u306e\u4f5c\u7528\u56f3\u3092\u56f3 10(b)\u306b\u793a\u3059\uff0e\u3053\u306e\u5834\u5408\u306f\uff0c\u8fba B-D \u3068\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e \u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5411\u304d\u306e\u95a2\u4fc2\u304b\u3089\u30ed\u30a2\u30a2\u30fc\u30e0\u306f\u6642\u8a08\u307e\u308f\u308a\u306b\u56de\u8ee2\u3059\u308b\uff0e\u3053\u306e\u56de\u8ee2\u306e\u5411\u304d\u306f\u56f3 6(c)\u306b\u793a\u3057\u305f\u3082\u306e \u3068\u306f\u9006\u3067\u3042\u308a\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u3082\u9006\u5411\u304d\u306e\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\uff0e\u4ee5\u4e0a\u304b\u3089\uff0c\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3082\u30e2\u30fc\u30c9\u2160\u540c\u69d8\uff0c \u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u30ec\u30a4\u30a2\u30a6\u30c8\u306b\u3088\u3089\u305a\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308a\uff0c\u305d\u306e\u30c8\u30fc\u89d2\u5909\u5316\u91cf\u306f\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u5e73\u9762\u8996\u56de\u8ee2\u89d2\u304a\u3088\u3073 \u8fba B-C\u304a\u3088\u3073\u8ef8 C-H\u306e\u30ea\u30f3\u30af\u4f5c\u7528\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\u3053\u3068\u304c\u5206\u304b\u308b\uff0e\n4\u30fb4 \u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316 \u524d\u8ff0\u306e\u3088\u3046\u306b\uff0cSAT \u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u3067\u3082 LF\u304c\u4f5c\u7528\u3059\u308b\u5834\u5408\u3068\u540c\u69d8\u306b\u70b9 A\u306f\u8eca\u4e21\u5916\u5074\u3078\u5909\u4f4d\u3059\u308b\uff0e\u3057\u305f\u304c\u3063\u3066 \u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u70b9 B \u304c\u70b9 C \u3088\u308a\u4f4e\u3044\u5834\u5408\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u3068\u306a\u308a\uff0c\u70b9 B \u304c\u70b9 C \u3088\u308a\u9ad8\u3044\u5834\u5408\u306f\u30c8\u30fc\u30a4\u30f3\u306b\u306a\u308b\uff0e\u307e \u305f\u70b9 B\u3068 C\u304c\u540c\u3058\u9ad8\u3055\u306e\u5834\u5408\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u306f\u751f\u3058\u305a\u30ad\u30e3\u30f3\u30d0\u89d2\u5909\u5316\u306e\u307f\u304c\u751f\u3058\u308b\uff0e\u30c8\u30fc\u89d2\u5909\u5316\u306e\u5927\u304d\u3055\u3082\u8ef8 B-C \u306e\u524d\u5f8c\u65b9\u5411\u3078\u306e\u50be\u304d\u89d2\u304a\u3088\u3073\u8ef8 B-C\u307e\u308f\u308a\u306e\u70b9 A\u306e\u56de\u8ee2\u89d2\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\uff0e\n4\u30fb5 SAT-C/S\u3068\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u8af8\u5143\u306e\u307e\u3068\u3081 \u3053\u3053\u3067\uff0c\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306b\u304a\u3051\u308b SAT-C/S\u3068\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u8af8\u5143\u306e\u95a2\u4fc2\u306b\u3064\u3044\u3066\u307e\u3068\u3081 \u3066\u304a\u304f\uff0eSAT-C/S\u3082 LF-C/S\u3068\u540c\u69d8\u306b\u30e2\u30fc\u30c9\u2160\uff0c\u30e2\u30fc\u30c9\u2161\uff0c\u30e2\u30fc\u30c9\u2162\u306e 3\u3064\u306e\u30c8\u30fc\u89d2\u5909\u5316\u304b\u3089\u306a\u308b\uff0e\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8 \u30fc\u89d2\u5909\u5316\u306f\uff0c\u4e00\u822c\u7684\u306a FF\u7528\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u3067\u306f LF-C/S\u3068\u306f\u9006\u306e\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\uff0e\u307e\u305f\uff0c \u305d\u306e\u5927\u304d\u3055\u306f\u70b9 B, C \u9593\u306e\u8eca\u4e21\u524d\u5f8c\u65b9\u5411\u306e\u8ddd\u96e2\u304a\u3088\u3073\u3070\u306d\u5b9a\u6570 kDY\u3068 kHY\u3067\u6c7a\u307e\u308b\uff0e\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3082 LF-C/S\u3068\u306f\u7570\u306a\u308a\uff0c\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u30ea\u30f3\u30af\u914d\u7f6e\u306b\u3088\u3089\u305a\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308a\uff0c\u305d\u306e\u91cf\u306f\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u5e73\u9762\u8996\u56de\u8ee2 \u89d2\u304a\u3088\u3073\u8fba B-C \u304a\u3088\u3073\u8ef8 C-H \u306e\u30ea\u30f3\u30af\u4f5c\u7528\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\uff0e\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306b\u3064\u3044\u3066\u306f\uff0cLF-C/S \u3068\u540c\u69d8\u306b\u30c8\u30fc\u89d2\u5909\u5316\u306e\u65b9\u5411\u306f\u70b9 B \u3068\u70b9 C \u306e\u9ad8\u3055\u306e\u95a2\u4fc2\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\uff0c\u305d\u306e\u5927\u304d\u3055\u306f\u8ef8 B-C \u306e\u524d\u5f8c\u65b9\u5411\u3078\u306e\u50be \u304d\u89d2\u304a\u3088\u3073\u8ef8 B-C\u307e\u308f\u308a\u306e\u70b9 A\u306e\u56de\u8ee2\u89d2\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\uff0e\u4e00\u822c\u7684\u306a FF\u7528\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7 \u30f3\u3067\u306f\u70b9 B\u306f\u70b9 C\u3088\u308a\u3082\u4f4e\u304f\u8a2d\u5b9a\u3055\u308c\u308b\u305f\u3081\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\uff0e\u3053\u306e\u3088\u3046\u306b\uff0c\u4e00\u822c\u7684\u306a\u914d\u7f6e\u306e\u30b5 \u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306b\u304a\u3044\u3066\u306f LF-C/S \u3068\u7570\u306a\u308a\uff0cSAT-C/S \u306e\u5834\u5408\u306f\u5168\u3066\u306e\u30e2\u30fc\u30c9\u304c\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\uff0e\u30e2\u30fc\u30c9\u2160\uff0c\u30e2\u30fc" + ] + }, + { + "image_filename": "designv8_17_0004238_784_77_784_4543__pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004238_784_77_784_4543__pdf-Figure9-1.png", + "caption": "Fig. 9 Model of 3 vehicles", + "texts": [], + "surrounding_texts": [ + "3 \u6b21\u5143\u8ecc\u9053\u4e0a\u306e\u30ed\u30fc\u30e9\u30fc\u30b3\u30fc\u30b9\u30bf\u30fc\u306b\u304a\u3051\u308b\u8907\u6570\u8eca\u4e21\u306e\u904b\u52d5\u3068\u632f\u52d5\n\u00a92011 The Japan Society of Mechanical Engineers\n\u3059\u308b\u304c\uff0cBaumgarte \u3092\u52a0\u3048\u308b\u3068, \u56f3 5 \u306b\u793a\u3059\u3088\u3046\u306b\u6700\u5f8c\u307e\u3067\u307b\u307c\u5b8c\u5168\u306b\u4e0e\u3048\u3089\u308c\u305f\u8ecc\u9053\u4e0a\u3092\u8d70\u884c\u3059\u308b\u3053\u3068\u304c\u308f\u304b \u308b\uff0e\ng g gx y z \u89e3\u6790\u306b\u304a\u3044\u3066\u306f, Baumgarte \u306a\u3057\u306e\u3068\u304d\u306f, \u56f3 4 \u306b\u793a\u3059\u3088\u3046\u306b\u6ed1\u308a\u59cb\u3081\u3066\u304b\u3089\u3059\u3050\u306b\u7570\u306a\u308b\u65b9\u5411 \u306b\u8d70\u308a\u51fa\u3057\u3066\u3044\u305f\u304c, Baumgarte \u3092\u3044\u308c\u308b\u3068, \u56f3 6 \u306b\u793a\u3059\u3088\u3046\u306b\u6539\u5584\u3055\u308c, \u4e0e\u3048\u3089\u308c\u305f\u8ecc\u9053\u4e0a\u306b\u8fd1\u3065\u3044\u3066\u8d70 \u884c\u3059\u308b\u3088\u3046\u306b\u306a\u308b\uff0e\u3057\u304b\u3057, \u305d\u308c\u3067\u3082\u8ecc\u9053\u306e\u6700\u5f8c\u306e\u65b9\u306b\u884c\u304f\u306b\u3064\u308c\u3066, \u3060\u3093\u3060\u3093\u4e0e\u3048\u3089\u308c\u305f\u8ecc\u9053\u304b\u3089\u5916\u308c\u3066 \u8d70\u884c\u3057\u3066\u3057\u307e\u3046. \u3053\u306e\u3088\u3046\u306b\uff0c\u3053\u3053\u3067\u63d0\u6848\u3059\u308b\u3088\u3046\u306a\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u89e3\u6790\u306b\u306f Baumgarte \u306e\u5b89\u5b9a\u5316\u6cd5\u306e\u63a1 \u7528\u306f\u91cd\u8981\u3067\u3042\u308b\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\nFig. 5 zus simulation method with Baumgarte (target trajectory and simulated trajectory: same line)\n5\u30fb3 \u8eca\u4e21\u306e\u632f\u52d5\u306b\u95a2\u3059\u308b zus \u89e3\u6790\uff0c\u304a\u3088\u3073 g g gx y z \u89e3\u6790\u306e\u6bd4\u8f03\n\u3059\u3067\u306b\u5831\u544a\u3057\u305f\u5b9f\u9a13\uff0c zus \u89e3\u6790\uff0c\u304a\u3088\u3073 g g gx y z \u89e3\u6790\u306e\u305d\u308c\u305e\u308c\u3067\u5f97\u3089\u308c\u305f\u52a0\u901f\u5ea6\u632f\u52d5\u6ce2\u5f62\uff08 lll zyx \u5ea7 \u6a19\u7cfb\u65b9\u5411\uff09\u3092\u5404\u3005\u56f3 7\uff0c8 \u306b\u793a\u3059\uff0e\u5b9f\u9a13\u3067\u306f\uff0c\u5b9f\u969b\u306e RC \u306e\u8eca\u4e21\u306e\u5e8a\u306b\u52a0\u901f\u5ea6\u8a08\u3092\u53d6\u308a\u4ed8\u3051\u3066 RC \u3092\u8d70\u884c\u3055\u305b\uff0c\u305d \u306e\u3068\u304d\u306e 3 \u65b9\u5411\uff0c lll zyx ,, \u306e\u65b9\u5411\u306e\u52a0\u901f\u5ea6\u5fdc\u7b54\u3092\u8a08\u6e2c\u3057\u3066\u3044\u308b\uff0e\u306a\u304a\uff0c\u56f3 7 \u306b\u793a\u3059\u5b9f\u9a13\u306e\u52a0\u901f\u5ea6\u632f\u52d5\u6ce2\u5f62\u306f1\u4e21 \u76ee\u3067\u8a08\u6e2c\u3057\u305f\u3082\u306e\u3067\u3042\u308b\uff0e\u307e\u305f\uff0c\u30ac\u30bf\u7b49\u9ad8\u6b21\u306e\u632f\u52d5\u306e\u5f71\u97ff\u304c\u51fa\u3066\u3044\u308b\u306e\u3067\uff0c\u6ce2\u5f62\u3092\u8003\u5bdf\u3057\u3084\u3059\u304f\u3059\u308b\u305f\u3081, \u524d\u5831 (7)\u3067\u8ff0\u3079\u305f\u3088\u3046\u306b10\uff28\uff5a\u306e\u30ed\u30fc\u30d1\u30b9\u30d5\u30a3\u30eb\u30bf\u30fc\u3092\u304b\u3051\u3066\u51e6\u7406\u3057\u3066\u3042\u308b\uff0e\u8eca\u4e21\u306e\u632f\u52d5\u306b\u306f\uff0c\u8ecc\u9053\u306e\u5909\u5316\u306b\u5fdc\u3058\u3066\u8eca \u4e21\u304c\u904b\u52d5\u3084\u632f\u52d5\u3059\u308b\u6210\u5206\u3068\uff0c\u8ecc\u9053\u306e\u7d99\u304e\u76ee\u3084\u7c97\u3055\u306e\u4e0d\u5747\u4e00\uff0c\u3055\u3089\u306b\u306f\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306e\u30ac\u30bf\u306a\u3069\u306b\u3088\u308b\u78ba\u5b9a\u3057\u306b \u304f\u3044\u8eca\u4e21\u306e\u632f\u52d5\u5fdc\u7b54\u6210\u5206\u304c\u8907\u96d1\u306b\u5408\u6210\u3055\u308c\u305f\u3082\u306e\u3068\u306a\u3063\u3066\u3044\u308b\u304c\uff0c\u8ecc\u9053\u306e\u5909\u5316\u306b\u5fdc\u3058\u3066\u5909\u5316\u3059\u308b\u6bd4\u8f03\u7684\u3086\u3063\u304f\u308a \u3057\u305f\u6ce2\u5f62\u306e\u50be\u5411\u306f\uff0c\u5b9f\u9a13\uff0cs-u-z \u89e3\u6790\uff0cxg-yg-zg \u89e3\u6790\u3067\u4f3c\u3066\u3044\u308b\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\u3057\u304b\u3057\u306a\u304c\u3089\uff0cxg-yg-zg \u89e3\u6790\u3067\u306f\uff0c Baumgarte \u306e\u5b89\u5b9a\u5316\u6cd5\u3092\u63a1\u7528\u3057\u3066\u3082\uff0c\u6642\u9593\u306e\u7d4c\u904e\u3068\u3068\u3082\u306b\u6570\u5024\u8aa4\u5dee\u304c\u84c4\u7a4d\u3057\u3066\u304a\u308a\uff0c\u4eca\u5f8c\u306e\u6539\u5584\u306e\u8ab2\u984c\u3067\u3042\u308b\uff0e\n0\n0\n50 100 150 S [m]\n1\n2\n3\n4\n5\n6\n7\n8\n9\nZ [m\n]\n\u2015 224 \u2015\n4547", + "3 \u6b21\u5143\u8ecc\u9053\u4e0a\u306e\u30ed\u30fc\u30e9\u30fc\u30b3\u30fc\u30b9\u30bf\u30fc\u306b\u304a\u3051\u308b\u8907\u6570\u8eca\u4e21\u306e\u904b\u52d5\u3068\u632f\u52d5\n\u00a92011 The Japan Society of Mechanical Engineers\n6. \u8907\u6570\u8eca\u4e21\u306b\u95a2\u3059\u308b\u89e3\u6790\u624b\u6cd5\n6\u30fb1 \u30e2\u30c7\u30eb\u5316 \u8907\u6570\u8eca\u4e21\u3092\u8003\u3048\u308b\u5834\u5408\uff0c\u56f3 9 \u306b\u793a\u3059\u3088\u3046\u306b\u9023\u7d50\u90e8\u8cea\u91cf\u3092\u7f6e\u304d\uff0c zs \u5e73\u9762\u3067\u306e\u56de\u8ee2\u89d2\u3092\u03b8\u3068\u3059\u308b\uff0e\n6\u30fb2 \u62d8\u675f\u6761\u4ef6\u5f0f \u56f3 9 \u3088\u308a,1 \u4e21\u76ee\u3068 2 \u4e21\u76ee\u306e\u62d8\u675f\u306b\u3064\u3044\u3066\u4ee5\u4e0b\u306e\u95a2\u4fc2\u5f0f\u304c\u5f97\u3089\u308c\u308b\uff0e 1\u4e21\u76ee\u306b\u3064\u3044\u3066\u306f\uff0c\n(11)\n\u3067\u3042\u308b\uff0e2\u4e21\u76ee\u306b\u3064\u3044\u3066\u306f\uff0c\n(12)\n\u3067\u3042\u308b\uff0e\u9023\u7d50\u70b9\u306b\u3064\u3044\u3066\u306f\u6b21\u5f0f\u304c\u6210\u7acb\u3059\u308b\uff0e\n(13)\n0sin)(\n0cos)(\n112111\n111121\n\n\n\n\nlzzz\nlsss\n0cos)(\n0cos)(\n222212\n221222\n\n\n\n\nlzzz\nlsss\n21 22\n21 22\n( ) 0\n( ) 0.\ns s s\nz z z\n \n \n\u2015 225 \u2015\n4548", + "3 \u6b21\u5143\u8ecc\u9053\u4e0a\u306e\u30ed\u30fc\u30e9\u30fc\u30b3\u30fc\u30b9\u30bf\u30fc\u306b\u304a\u3051\u308b\u8907\u6570\u8eca\u4e21\u306e\u904b\u52d5\u3068\u632f\u52d5\n\u00a92011 The Japan Society of Mechanical Engineers\n\u540c\u69d8\u306b\u3057\u3066\uff0c8 \u4e21\u76ee\u307e\u3067\u305d\u308c\u305e\u308c\u306e\u62d8\u675f\u6761\u4ef6\u5f0f\u3092\u5c0e\u51fa\u3059\u308b\uff0e\u3053\u3053\u3067\u3082\u62d8\u675f\u6761\u4ef6\u5f0f\u306b Baumgarte \u306e\u5b89\u5b9a\u5316\u52a0\u901f\u5ea6\n\u65b9\u7a0b\u5f0f\u3092\u9069\u7528\u3059\u308b\uff0e\u9023\u7d50\u90e8\u306b s \uff0cz \u65b9\u5411\u4e21\u65b9\u306e\u62d8\u675f\u3092\u304b\u3051\u308b\u3068\u89e3\u304c\u767a\u6563\u3057\uff0cRC \u304c\u7cbe\u5ea6\u826f\u304f\u904b\u52d5\u3057\u306a\u304f\u306a\u308b\u306e\u3067\uff0c \u3053\u3053\u3067\u306f z \u65b9\u5411\u306e\u62d8\u675f\u3092\u306f\u305a\u3057\u3066\u89e3\u6790\u3092\u884c\u3063\u305f\uff0e\ns \u65b9\u5411\u3068 z \u65b9\u5411\u306e\u4e21\u65b9\u306b\u3064\u3044\u3066\u62d8\u675f\u3092\u304b\u3051\u308b\u3068\uff0c\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u306e\u89e3\u304c\u767a\u6563\u3057\uff0c\u53ce\u675f\u3057\u306a\u304b\u3063\u305f\u306e\u306f\uff0c\u62d8\u675f 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I compute structural loads at a 2.5 g static condition, flown at Mach 0.75 and 5,000 m altitude. Unlike the previous wing problem that featured a battery, I optimize a set of seven hydrogen tanks in each wing root (one per rib bay). The 700 bar compressed hydrogen tanks are cylindrical with spherical end caps. Each tank can vary in radius and length, with additional variables to position each tank relative to its rib bay (Figure 10.4). The tanks consist of optimized carbon fiber reinforced polymer (CFRP) laminate. 212 To perform aerostructural analysis and design, I used the MACH framework [147]. The MACH framework integrates several high-fidelity analysis tools with geometry engines while propagating design variable derivatives [154]. The subset of aerodynamic shape optimization tools is open-source and freely available. I used the open-source ADflow solver for aerodynamic analysis and derivatives [267]. ADflow is a structured, multiblock, overset RANS solver with discrete adjoint gradients", + " An initial triangulated representation of each tank surface is generated using Engineering Sketch Pad (ESP) [275], an open-source computer-aided design (CAD) application. Using a Python wrapper around ESP\u2019s OpenCSM library, I map each point on the tank surface onto the CAD B-spline surface in parametric coordinates and save the result. When the geometry is perturbed, I retrieve a new set of surface mesh points using the same parametric coordinates. This way, the topology of the mesh is preserved across geometric perturbations. A more detailed account of the ESP geometry engine is included as Appendix C. The design variables are as pictured in Figure 10.4\u2014five variables per tank, for a total of 35. Gradients with respect to geometric design variables are computed using a parallel finite differencing approach. Since the aerostructural design optimization is done in a HPC environment with 100 or more available cores, I can perform finite differences across dozens of geometry variables without incurring much cost in terms of wall time (a few seconds). The advantages of using this open-source CAD package were readily apparent at several points. For example, I was able to edit the source to suppress certain console output, which, while useful in interactive mode, clogs the output when running dozens of instances simultaneously" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000053_icersd2020_01019.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000053_icersd2020_01019.pdf-Figure1-1.png", + "caption": "Figure 1. The structure diagram of permanent magnet synchronous motor", + "texts": [ + " The PMSM has a compact structure and high power density since the amorphous alloy is applied to magnetically permeable material that with the nature of smaller magnetic resistance, and makes it possible for lower temperature rising in-wheel. An axial-flux PMSM is investigated in this paper, which mathematical model of electromagnetic loss to express thermal transformation was founded to illustrate the progress of temperature rising. Then the ANSYS workbench was employed to performed magneto-thermal coupling simulations, which consistent with the actual test of temperature rising approximately. The application in EVs of low power in-wheel motor, the structure, and physical winding unit of axial-flux PMSM is shown in Figure1 and 2. The axial flux PMSM adopting 3-phase winding, 24 pole, and 27 slots, the fraction slot concentrated wing which has the advantages of smaller copper loss, more stable torque, and higher torque density. The permanent magnets are at both ends of rotor cores, and rotor cores are fixed at the outer rotor and rotor bracket which are to form double rotors. The winding coils are arranged around in the stator bracket and amorphous alloy inserts in the winding bracket. Simultaneously, copper wire twining on the wingding bracket to form a winding unit" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure2-1.png", + "caption": "Figure 2. Prototype of SMzs200S32 motor manufactured by \u0141ukasiewicz Research Network\u2014 Institute of Electrical Drives and Machines KOMEL (\u0141-KOMEL): (a) angled view; (b) front view; (c) rear view.", + "texts": [ + " The space in which the electric motor must fit is limited by the dimensions of the wheel rim (outer diameter and motor length), while the inner diameter depends on how the space inside the toroid is used. In the case of the presented structure, this space houses the vehicle brake drum. The space containing the electromagnetic circuit is limited by the dimensions of the support structure, anchor shell, and rotor, which must be thick enough to ensure the required mechanical strength (Figure 1). Pictures of the prototype SMzs200S32 motor are shown in Figure 2. For research purposes, this motor was equipped with a number of PT100 temperature sensors, placed in various elements of the stator and rotor (permanent magnets). Additionally, a small wireless temperature recorder was developed. It is installed on the rotor surface and the sensor mounted on the magnet is connected to the recorder. Temperature can be registered continuously and data are sent wirelessly [34]. The cross-section of the motor with the positions of the temperature sensors is shown in Figure 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004978_0846-023-01961-9.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004978_0846-023-01961-9.pdf-Figure4-1.png", + "caption": "Fig. 4 Graphical representation of the modelled photogrammetric constraints for view pose synthesis during inspection", + "texts": [ + " vx = ppoi \u2212 pkuav \u2016 ppoi \u2212 pkuav\u2016 (1a) vy = cross(nz, vx ) (1b) vz = cross(vy, vx ) (1c) Let \u03b1 \u2208 R + be the Horizontal FOV of the onboard camera.According to thedesiredhorizontal overlap factor\u03b3H , the necessary overlap distance OH \u2208 R + to be maintained can be formulated as trigonometric problem by determining the camera footprint for a given rm , \u03b1 and \u03b3H parameters. Thus, solving for the relative distance, OH , to maintain the desired overlap characteristics ensures the view-planner satisfies desired photogrammetric properties. Equation 2 presents the mathematical description to determine the necessary overlap distance. Figure 4(a) provides a graphical illustration of the modelled horizontal overlap characteristics. OH = f ( pkuav, ppoi , \u03b3H , \u03b1) (2) where, f ( pkuav, ppoi , \u03b3H , \u03b1) = 2 tan \u03b1 2 \u2016 ppoi \u2212 pkuav\u2016 \u2212 2 \u03b3H tan \u03b1 2 \u2016 ppoi \u2212 pkuav\u2016 Similarly, given \u03b2 \u2208 R + representing the Vertical FOV of the camera and OV \u2208 R +, Eq. 2 can be modified and re-written as in Eq. 3. Figure 4(b) provides a graphical illustration of the modelled vertical overlap characteristics. OV = f ( pkuav, ppoi , \u03b3V , \u03b2) (3) where, f ( pkuav, ppoi , \u03b3V , \u03b2) = 2 tan \u03b2 2 \u2016 ppoi \u2212 pkuav\u2016 \u2212 2 \u03b3V tan \u03b2 2 \u2016 ppoi \u2212 pkuav\u2016 From Eqs.1 and 2, the proposed view planning policy can be formulated as follows, pk+1,k uav = pk,kuav + vyOH (4) \u03c8k+1,k uav = arctan(vx (2), vx (1)) (5) Fig. 3 Graphical representation of the implemented point-cloud down sampling process during visual inspection Figure 4 shows a visualization of themodelled photogrammetric constraints to plan view pose during inspection. Together Eqs. 4 and 5 denote the reference view pose \u03be re f fed to the tracking controller. This formulation allows the UAV to be resilient against the presence of gaps or holes along the surface of the structure due to the search for ppoi . Equation 4 is executed recursively with the sensor information being updated as the UAV moves thereby allowing the planner to adapt the inspection path and the required view orientation to the profile of the structure being inspected" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004185__2022jamdsm0003__pdf-Figure29-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004185__2022jamdsm0003__pdf-Figure29-1.png", + "caption": "Fig. 29 The A-CS and B-CS", + "texts": [ + "2022jamdsm0003] When the tooth number of the SC exceeds half of the CS, the CS slotted by the SC with more teeth has higher transmission accuracy. For testing the correctness of this theoretical analysis, one SC with 55 teeth and another SC with 69 teeth were designed and slotted two circles as shown in Fig. 28. 16 2 \u00a9 2022 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2022jamdsm0003] The CS slotted by the SC with 55 teeth is called A-CS. The CS slotted by the SC with 69 teeth is called B-CS. In the experiment, the two CSs are slotted two cycles. The two CSs are manufactured as shown in Fig. 29. The two CSs are similar. Then, the gear detector was used to detect the accumulative pitch error. The TEC of the CS is calculated based on the accumulative pitch error. As is shown in Fig. 30, the coordinates of the measuring points in the same end face of the CS are measured by the FTA-L4D4000 surface roughness and profile integrated machine. Based on the data, the theoretical accumulative pitch and actual accumulative pitch are calculated. The accumulative pitch error is the difference between the theoretical accumulative pitch and actual accumulative pitch" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001782_f_version_1663924178-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001782_f_version_1663924178-Figure2-1.png", + "caption": "Figure 2. The comparison figure between ISDR and PRECICE. (a) The schematics of intramedullary lengthening nail system between ISDR and PRECICE. 1\u2014thigh, 2\u2014bone screws, 3\u2014internal magnet driver, 4\u2014implantable lengthening nail, 5\u2014femur; (b) the schematics of driving method between ISDR and PRECICE; (c) the schematics of intramedullary lengthening nail between ISDR and PRECICE.", + "texts": [ + " Then, they use a cannulated drill to enlarge the medullary canal to facilitate implantation. After completing the enlargement procedure, they apply an osteotomy by using the osteotome, followed by the insertion of the implantable lengthening nail into the medullary canal and fixed tightly by bone screws at both the upper and lower ends. Once the clinicians complete implantation surgery, they can place the internal magnet driver near the limb to drive the implantable lengthening nail magnet for treating LLD. There are some differences between ISDR and PRECICE (Figure 2a\u2013c). PRECICE places its permanent magnet near the proximal femoral shaft, while ISDR places its permanent magnet near the distal femoral shaft. This design signifies that the air gap between the permanent magnet and the driver is minor, revealing the driving torque for the bone distraction is much more stable and forceful. Moreover, the transmission component of ISDR has a longer lifespan compared to PRECICE because the transmission of the axial load from the distraction nail towards the thrust bearing and protective shell occurs without passing through the gearbox" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004390_am_084_01_011003.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004390_am_084_01_011003.pdf-Figure7-1.png", + "caption": "Fig. 7 Experimental and numerically simulated postbuckling responses of sample SGI cylinders", + "texts": [ + "pdf by guest on 20 D ecem ber 2024 superposition of one governing mode shape (i.e., the seeded shape) with a large amplitude plus 20 random mode shapes with a very small total amplitude (0.01 mm for each mode or 2% of the shell thickness). Obviously, the seeded geometry was expected to have a governing role over the other small imperfections on the postbuckling response. Numerical simulations were conducted on selected baseline SGI cylindrical shells to evaluate the efficiency of the modeling approach. Figure 7 shows results for two cases (out of 14) for cylinders with a seeded imperfection amplitude of 200% of the shell thickness. The predicted postbuckling response Fig. 5 Experimental postbuckling response contours of SGI cylinders: (a) initial stiffness (Ki), (b) maximum single load drop (DPmax), (c) enclosed area (A), and (d) number of mode transitions (nt). (Note: cross marks indicate the 14 tested SGI designs). Table 1 Postbuckling response of SGI cylindrical shells with a single mode shape as a seeded imperfection Mode m n Ki (N/mm) Pmax (N) DPmax (N) dmax (mm) A (kJ) nt 198 12 5 610.1 500.4 70.2 \u2014 49.9 1 Fig. 6 Response domain of an SGI design with varied amplitude 011003-4 / Vol. 84, JANUARY 2017 Transactions of the ASME D ow nloaded from http://asm edigitalcollection.asm e.org/appliedm echanics/article-pdf/84/1/011003/5973488/jam _084_01_011003.pdf by guest on 20 D ecem ber 2024 curve for cylinder M5N2 is close to the experimental one, while there is larger discrepancy between responses for cylinder M8N8. The insets in Fig. 7 show that the seeded geometry in cylinder M8N8 has a higher number of localized inward regions than cylinder M5N2, which makes cylinder M8N8 more vulnerable to initial random imperfections. Nonetheless, it is interesting see that the numerical and experimental results for cylinder M8N8 attained the same number of mode transitions. The most important point is that the simulated responses captured the general postbuckling response features for two rather different designs (M8N8: softening response and M5N2: stiffening response), even though the simulated curves did not exactly match the experimental data, with relatively minor modeling difficulty" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002593_9312710_09335981.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002593_9312710_09335981.pdf-Figure3-1.png", + "caption": "FIGURE 3. Permanent magnet synchronous rotor module lamination.", + "texts": [ + " The magnets are made of Nd-Fe-B permanent magnet materials, and the iron bridge and flux bridges are magnetic barriers and air barriers, respectively. Bm is the permanent magnet\u2019s width; Hm is the length of the permanent magnet magnetizing direction; and dpm is the d-axis of the IPM permanent magnet motor. This axis provides the previous description for the calculation of the torque expression and establishing a space vector diagram. In this paper, the PMA-SynRM module built-in PMA-SynRM rotor structure is taken as an example. The rotor magnetic circuit adopts four layers in series to avoid the phenomenon of self-demagnetization. Fig. 3 shows the schematic diagram of the PMA-SynRM rotor module lamination. Magnets are made of ferrite permanent magnetic materials, where the iron bridge and flux bridges are magnetic barriers, Bmn is the width of each layer of the permanent magnet, Hmn is the length of the magnetizing direction of each layer of the permanent magnet, the angle n represents the angle between the poles of different layers. and dPMA\u2212SynRM is the rotor d-axis of PMA-SynRM. This axis provides the previous description for the calculation of the torque expression and establishing a space vector diagram" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004597_s-4255722_latest.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004597_s-4255722_latest.pdf-Figure4-1.png", + "caption": "Fig. 4: 3D models of the mold components", + "texts": [ + " Dragonskin30 silicone, a twocomponent silicone with a mixing ratio of 1:1 between the two agents, was used. It has a set time of 45 min and a complete curing time of 16 hours. The casting process was applied following the producer reccomendations, casting the material at room temperature (25\u00b0C), applying a release agent on the mold (Ease Release 200) and applying a degassing phase under vacuum post-mixing to remove air bubbles. Custom molds have been fabricated by means of FFF, using PLA material. The mold geometry is depicted in Fig. 4: the mold is composed by three parts: bank, core and base. The fabrication process considers the need of introducing two additional elements: the flexion sensor and a piece of rectangular polyethylene textile, included in the bottom part of the actuator to prevent inflation of that area and prevent the extension of the actuator during bending. The following manufacturing phases are applied: \u2022 Assemble core and bank. Pour silicone in base up to the 2.5 mm mark, located in the middle of the mold. Pour silicone in bank mold up to the top" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003924_tation-pdf-url_69281-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003924_tation-pdf-url_69281-Figure14-1.png", + "caption": "Figure 14. 3D printing system schematic diagram.", + "texts": [ + " However, they need packaging to protect from the ambient environment such as humidity, light, and temperature. On the other hand, the device itself needs protection from the user touches as it can damage the thin films and patterns. 3D printing (also called additive manufacturing) is a manufacturing technology, which is based on imposing the material layers to create the 3D objects. A 3D object is fabricated through melting filament material with controlled temperature and flow rate in combination with X, Y, and Z axis control, as shown in Figure 14. The object is design in CAD tool, i.e., AutoCAD or any other tool that can create 3D structures and converted into printer supported file format. The file is then loaded into the printer to create the object in 3D form. There are several ways to create a 3D object, which defines the types of 3D printers. 17 DOI: http://dx.doi.org/10.5772/intechopen.89377 The development of 3D object is made by either microdrops or melt near-field electrospinning of melted thermoplastics of consecutive layers, which solidifies after a certain time" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000357_2015_60_2015_29__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000357_2015_60_2015_29__pdf-Figure5-1.png", + "caption": "Fig. 5 Setup for FLP accuracy check.", + "texts": [], + "surrounding_texts": [ + "\u3070\u306d\u8ad6\u6587\u96c6 \u7b2c60\u53f7\uff082015\uff09 31\n\u529b\u306e\u767a\u751f\u306b\u3088\u308a\u30ed\u30a2\u30b7\u30fc\u30c8\u304c\u5c11\u3057\u3067\u3082\u5909\u5f62\u3059\u308b\u3068\uff0c\u5404\u8db3\u306e 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4\u306b\u4e0b\u50746\u5206\u529b\u8a08\u306e\u30b9\u30c6\u30c3\u30d7\u5fdc\u7b54\u3092\u793a\u3059\uff0e\u5236\u5fa1\u30d1\u30e9 \u30e1\u30fc\u30bf\u306e\u8abf\u6574\u3067\u3055\u3089\u306b\u65e9\u3044\u5fdc\u7b54\u306b\u3059\u308b\u3053\u3068\u306f\u53ef\u80fd\u3060\u304c\uff0c2 \u79d2\u3068\u3044\u3046\u76ee\u6a19\u5024\u3078\u306e\u6574\u5b9a\u6642\u9593\u306f\u5b9f\u7528\u4e0a\u5168\u304f\u554f\u984c\u306a\u304f\uff0c\u5468\u56f2 \u306e\u6a5f\u5668\u3078\u306e\u885d\u6483\u3092\u5c11\u306a\u304f\u3059\u308b\u610f\u5473\u3067\u3082\uff0c\u3053\u308c\u4ee5\u4e0a\u306e\u5fdc\u7b54\u901f \u5ea6\u30a2\u30c3\u30d7\u306f\u5b9f\u65bd\u3057\u306a\u3044\uff0e 3.3 FLP\u5b9f\u73fe\u7cbe\u5ea6\nFig. 5\u306b\u793a\u3059\u3088\u3046\u306b\uff0cUSPG2013\u3092\u901a\u5e38\u306e\u30b3\u30a4\u30eb\u3070\u306d\u53cd \u529b\u7dda\u6e2c\u5b9a\u6a5f\u306b\u8a2d\u7f6e\u3057\u305f\uff0e\u56f3\u4e2d\u306e\u9ec4\u8272\u70b9\u306f\uff0c\u53cd\u529b\u7dda\u6e2c\u5b9a\u6a5f\u306e \u30ed\u30fc\u30c9\u30bb\u30eb\u3067\u8a08\u6e2c\u3057\u305fFLP\uff0c\u9752\u70b9\u306fUSPG2013\u306e\u5185\u90e8\u30ed\u30fc \u30c9\u30bb\u30eb\u3067\u8a08\u6e2c\u3057\u305fFLP\u3092\u8868\u3059\uff0e\u3053\u308c\u3089\u3092\u30b3\u30a4\u30eb\u3070\u306d\u306e\u4e0a\u4e0b \u5ea7\u9762\u3067\u306eFLP\u3078\u305d\u308c\u305e\u308c\u5909\u63db\u3057\uff0c\u4e21\u8005\u3092\u6bd4\u8f03\u3059\u308b\uff0e\u9752\u70b9\u306f\uff0c USPG2013\u3078\u4e0e\u3048\u305f\u76ee\u6a19FLP\u306b\u5bfe\u3057\uff0c\u4f4d\u7f6e\u5b9a\u5e38\u504f\u5dee\u30bc\u30ed\u3067 \u5236\u5fa1\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u8aa4\u5dee\u304c\u00b10.1mm\u4ee5\u5185\u3067\u3042\u308b\u3053\u3068\u304c\u78ba\u8a8d \u3067\u304d\u3066\u3044\u308b\uff0e\u3064\u307e\u308a\uff0c\u4e0a\u4e0b\u5ea7\u9762\u4e0a\u3078\u5909\u63db\u3057\u305f\u4e21FLP\u304c\u4e00\u81f4", + "32\n\u3057\u3066\u3044\u308c\u3070\uff0cUSPG2013\u306f\u6b63\u3057\u3044FLP\u3092\u751f\u6210\u3057\u3066\u3044\u308b\u3053\u3068 \u306b\u306a\u308b\uff0e \u4e21FLP\u306e\u6bd4\u8f03\u3092Fig. 6\u306b\u793a\u3059\uff0e\u30b9\u30c8\u30e9\u30c3\u30c8\u8ef8\u5468\u308a\u03c680mm \u306e\u7bc4\u56f2\u306b\u304a\u3044\u3066\u6700\u5927\u8aa4\u5dee\u306f\uff0c1.1mm\u306b\u53ce\u307e\u3063\u3066\u304a\u308a\uff0c\u8eca\u4e21 \u7279\u6027\u3092\u691c\u8a3c\u3059\u308b\u4eca\u56de\u306e\u76ee\u7684\u306b\u304a\u3044\u3066\u306f\u5341\u5206\u306e\u5b9f\u73fe\u7cbe\u5ea6\u3092 \u3082\u3063\u3066\u3044\u308b\u3053\u3068\u304c\u78ba\u8a8d\u3067\u304d\u305f\uff0e\n4. \u30c0\u30f3\u30d1\u30fc\u30d5\u30ea\u30af\u30b7\u30e7\u30f3\uff08DF\uff09\u6e2c\u5b9a\u5b9f\u9a13 4.1 \u8a66\u9a13\u65b9\u6cd5 \u30c0\u30f3\u30d1\u30fc\u8ef8\u304c\u925b\u76f4\u306b\u306a\u308b\u3088\u3046\u306bUSPG2013\u306e\u4e0a\u4e0b\u3092\u8377\u91cd \u8a66\u9a13\u6a5f\u306b\u56fa\u5b9a\u3057\uff0c\u6e2c\u5b9a\u9ad8\u3055\u306b\u304a\u3044\u3066\u3042\u308b\u4e00\u5b9a\u306e\u8377\u91cd\u8ef8\u3092\u767a \u751f\u3055\u305b\uff0c\u305d\u306e\u72b6\u614b\u3067\u00b15mm\uff0c0.5Hz\u306e\u4e09\u89d2\u6ce2\u3067\u30a2\u30c3\u30d1\u30fc\u30de \u30a6\u30f3\u30c8\u3092\u4e0a\u4e0b\u3055\u305b\u308b\uff0e\u4e0a\u4e0b\u5909\u4f4d\u3068\u8377\u91cd\u8a66\u9a13\u6a5f\u5074\u306e\u30ed\u30fc\u30c9 \u30bb\u30eb\uff08\u5916\u90e8\u30ed\u30fc\u30c9\u30bb\u30eb\uff09\u306e\u51fa\u529b\u3068\u3067\u30ea\u30b5\u30fc\u30b8\u30e5\u56f3\u5f62\u3092\u63cf\u304f\u3068 Fig. 7\u306e\u3088\u3046\u306b\u306a\u308b\uff0e\u4e0a\u4e0b\u306e\u65b9\u5411\u304c\u5207\u308a\u66ff\u308f\u308b\u3068\u304d\u306b\u30b9\u30d1 \u30a4\u30af\u72b6\u306e\u8377\u91cd\u304c\u51fa\u3066\u3044\u308b\u3082\u306e\u306e\uff0c\u5236\u5fa1\u7cfb\u304c\u3059\u3050\u306b\u8ffd\u5f93\u3057\u5b89 \u5b9a\u72b6\u614b\u306b\u623b\u3063\u3066\u3044\u308b\uff0e\u4e0a\u4e0b\u306e\u52d5\u304d\u3067\u9006\u65b9\u5411\u306b\u767a\u751f\u3059\u308bDF \u306f\uff0c\u5b89\u5b9a\u72b6\u614b\u3067\u306e\u8377\u91cd\u30d2\u30b9\u30c6\u30ea\u30b7\u30b9\u306e\u534a\u5206\u306e\u91cf\u3068\u3057\u3066\u8a08\u6e2c \u3055\u308c\u308b\uff0e\nFig. 8\u306b\u5b89\u5b9a\u72b6\u614b\u306b\u304a\u3051\u308bUSPG2013\u5185\u90e8\u306e\u4e0a\u50746\u5206\u529b\u8a08 \u3067\u691c\u51fa\u3055\u308c\u305f\u5782\u76f4\u65b9\u5411\u306e\u53cd\u529b\u3092\u793a\u3059\uff0eFig. 7\u306e\u5916\u90e8\u30ed\u30fc\u30c9 \u30bb\u30eb\u51fa\u529b\u3068\u7570\u306a\u308a\uff0c\u8377\u91cd\u30d2\u30b9\u30c6\u30ea\u30b7\u30b9\u306f\u73fe\u308c\u3066\u3044\u306a\u3044\uff0e\u3064 \u307e\u308a\uff0c\u6cb9\u5727\u30b7\u30ea\u30f3\u30c0\u3084\u5404\u8db3\u306e\u4e21\u7aef\u306b\u4f4d\u7f6e\u3059\u308b\u30e6\u30cb\u30d0\u30fc\u30b5\u30eb \u30b8\u30e7\u30a4\u30f3\u30c8\u306b\u304a\u3051\u308b\u6469\u64e6\u3092\u542b\u3093\u3060\u72b6\u614b\u3067\u5236\u5fa1\u7cfb\u304c\u52d5\u4f5c\u3057\u3066 \u3044\u308b\u3068\u3044\u3046\u3053\u3068\u3067\u3042\u308a\uff0c\u5916\u90e8\u30ed\u30fc\u30c9\u30bb\u30eb\u51fa\u529b\u306b\u73fe\u308c\u308b\u8377\u91cd", + "\u3070\u306d\u8ad6\u6587\u96c6 \u7b2c60\u53f7\uff082015\uff09 33\n\u30d2\u30b9\u30c6\u30ea\u30b7\u30b9\u304cDF\u306b\u3088\u308b\u3082\u306e\u3067\u3042\u308b\u3053\u3068\u3092\u7acb\u8a3c\u3057\u3066\u3044\u308b\uff0e Fig. 9\u306f\u5b89\u5b9a\u72b6\u614b\u306b\u304a\u3051\u308bFLP\u3092\u30d7\u30ed\u30c3\u30c8\u3057\u305f\u3082\u306e\u3067\u3042 \u308b\uff0eFLP\u306e\u79fb\u52d5\u306f\u03c61mm\u4ee5\u5185\u306b\u53ce\u307e\u3063\u3066\u304a\u308a\uff0cUSPG2013 \u306b\u4e0a\u4e0b\u5909\u4f4d\u304c\u4e0e\u3048\u3089\u308c\u3066\u3082\uff0c\u5236\u5fa1\u7cfb\u304cFLP\u3092\u5b89\u5b9a\u3057\u3066\u5236\u5fa1 \u3057\u3066\u3044\u308b\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\u3064\u307e\u308a\uff0c\u5404FLP\u306b\u5bfe\u3059\u308bDF\u3092\u8a08 \u6e2c\u3059\u308b\u3053\u3068\u304c\u53ef\u80fd\u3068\u306a\u308b\uff0e\nFig. 10\u306b\u672c\u5b9f\u9a13\u3067\u7528\u3044\u308b\u5ea7\u6a19\u7cfb\u3092\u5b9a\u7fa9\u3059\u308b\uff0e\u8eca\u4e21\u53f3\u524d\u306e \u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u3092\u524d\u63d0\u306b\uff0c\u8eca\u4e21\u5f8c\u65b9\u3092\uff0bX\u8ef8\uff0c\u8eca\u4e21\u5916\u5074\u3092 \uff0bY\u8ef8\u3068\u3059\u308b\uff0e\u3053\u3053\u3067\u306f\uff0cFLP\u3092\u8eca\u4e21\u6a2a\u65b9\u5411\uff08Y\u8ef8\u4e0a\uff09\u306b\u8d70 \u67fb\u3055\u305b\uff08\uff1d\u4e0a\u5074Uy\u3068\u4e0b\u5074Ly\u3092\u8d70\u67fb\u3055\u305b\uff09\uff0cFLP\u3068DF\u3068\u306e\u95a2 \u4fc2\u3092\u6c42\u3081\u308b\uff0e\n4.2 \u8a66\u9a13\u7d50\u679c Fig. 11\u306fFLP\u3068\u8a08\u6e2c\u3055\u308c\u305fDF\u3068\u306e\u95a2\u4fc2\u3067\u3042\u308a\uff0c\u56f3\u4e2d\u306b \u306f\u7b49\u30d5\u30ea\u30af\u30b7\u30e7\u30f3\u7dda\u3092\u793a\u3057\u3066\u3042\u308b\uff0e\u672c\u30b9\u30c8\u30e9\u30c3\u30c8\u5358\u4f53\u3067 DF\u3092\u8a08\u6e2c\u3057\u305f\u3068\u3053\u308d45N\u3067\u3042\u308a\uff0c\u3053\u306e\u30d5\u30ea\u30af\u30b7\u30e7\u30f3\u30de\u30c3 \u30d7\u3067\u5f97\u3089\u308c\u305f\u6700\u5c0f\u30d5\u30ea\u30af\u30b7\u30e7\u30f3\u3068\u307b\u307c\u4e00\u81f4\u3059\u308b\uff0e\u307e\u305f\uff0c\u672c \u30b9\u30c8\u30e9\u30c3\u30c8\u7528\u306e\u30b3\u30a4\u30eb\u3070\u306dA\uff08\u8af8\u5143\u306fTable 3\u53c2\u7167\uff09\u306e\u6e2c\u5b9a \u9ad8\u3055\u306b\u304a\u3051\u308b\u5b9f\u6e2cFLP\u306f\uff0c\u4e0a\u5074\uff081.9, 6.1\uff09\uff0c\u4e0b\u5074\uff08-0.3, 26.2\uff09 \u3067\u3042\u308a\uff0c\u3053\u3053\u3067\u8b70\u8ad6\u3059\u308b\u90fd\u5408\u4e0a\uff0c\u4e0a\u5074\uff080, 6\uff09\uff0c\u4e0b\u5074\uff080, 26\uff09 \u3068\u8fd1\u4f3c\u3059\u308b\u3068\uff0c\u3053\u306eFLP\u306b\u304a\u3051\u308bDF\u306f\uff0cFig. 11\u306e\u30d5\u30ea \u30af\u30b7\u30e7\u30f3\u30de\u30c3\u30d7\u3088\u308a\u7d0460N\uff08\u56f3\u4e2d\u306e\u8d64\u70b9\uff09\u3068\u63a8\u6e2c\u3067\u304d\u308b\uff0e USPG2013\u306e\u4ee3\u308f\u308a\u306b\u3053\u306e\u3070\u306dA\u3092\u540c\u3058\u30b9\u30c8\u30e9\u30c3\u30c8\u306b\u30de\u30a6 \u30f3\u30c8\u3057\u3066\u8a08\u6e2c\u3057\u305fDF\u306f64N\u3067\u3042\u308a\uff0c\u4e21\u8005\u306f\u307b\u307c\u4e00\u81f4\u3057\u305f\uff0e 4.3 \u8003\u5bdf \u3053\u306e\u5b9f\u9a13\u3067\u5f97\u3089\u308c\u305fFig. 11\u306e\u30de\u30c3\u30d7\u3088\u308a\uff0cDF\u3092\u6700\u5c0f\u5316 \u3059\u308bFLP\u306f\u5e2f\u72b6\u306b\u5b58\u5728\u3059\u308b\u3053\u3068\u304c\u308f\u304b\u308a\uff0c\u7b49\u30d5\u30ea\u30af\u30b7\u30e7\u30f3\n\u7dda\u306e\u50be\u304d\uff08Uy/Ly\uff09\u304c\u7d041.5\u3067\u3042\u308b\u3053\u3068\u304b\u3089\uff0c\u672c\u30bb\u30c3\u30c8\u30a2\u30c3 \u30d7\u306b\u304a\u3051\u308b\u30c0\u30f3\u30d1\u30d5\u30ea\u30af\u30b7\u30e7\u30f3\u306b\u5bfe\u3057\u3066\u306f\uff0cLy\u306e\u307b\u3046\u304c Uy\u3088\u308a\u30821.5\u500d\u3060\u3051\u611f\u5ea6\u304c\u9ad8\u3044\u3053\u3068\u304c\u308f\u304b\u308b\uff0eDF\u3092\u3042\u308b\u5024 \u4ee5\u4e0b\u306b\u8a2d\u5b9a\u3057\u305f\u3044\u5834\u5408\uff0c\u3053\u306e\u30d5\u30ea\u30af\u30b7\u30e7\u30f3\u30de\u30c3\u30d7\u304c\u3042\u308c\u3070\uff0c \u3070\u306d\u306e\u8a2d\u8a08\u88fd\u9020\u30b3\u30b9\u30c8\u3084\u751f\u7523\u6280\u8853\u6027\u306a\u3069\u3092\u8003\u616e\u3057\u3066\uff0c\u52b9\u7387 \u306e\u3088\u3044FLP\u3092\u4ed5\u69d8\u3068\u3057\u3066\u9078\u629e\u3059\u308b\u3053\u3068\u304c\u53ef\u80fd\u3068\u306a\u308b\uff0e\nUSPG2013\u3092\u30de\u30a6\u30f3\u30c8\u3057\u305f\u30b9\u30c8\u30e9\u30c3\u30c8\u306b\u30ca\u30c3\u30af\u30eb\uff0c\u30ed\u30a2 \u30a2\u30fc\u30e0\uff0c\u30bf\u30a4\u30ed\u30c3\u30c9\u3092\u53d6\u308a\u4ed8\u3051\uff0c\u30bf\u30a4\u30ed\u30c3\u30c9\u4e0a\u306b\u57cb\u3081\u8fbc\u3093 \u3060\u30ed\u30fc\u30c9\u30bb\u30eb\u51fa\u529b\u304b\u3089\u30ad\u30f3\u30b0\u30d4\u30f3\u30e2\u30fc\u30e1\u30f3\u30c8\u3092\u7b97\u51fa\u3057\u305f \uff08Fig. 12\uff09\uff0e\u3053\u306e\u3068\u304d\u306e\u30b9\u30c8\u30e9\u30c3\u30c8\u89d2\u5ea6\u306f\u8eca\u4e21\u3067\u306e\u642d\u8f09\u89d2 \u5ea6\u3068\u540c\u3058\u306b\u3057\u305f\uff0eFLP\u306e\u8d70\u67fb\u306f\uff0c\u3070\u306dA\u306eFLP\u4ed8\u8fd1\u3067\u5207\u308a \u306e\u3088\u3044\u5834\u6240\uff08\u4e0a\u5074\uff080, 5\uff09\uff0c\u4e0b\u5074\uff080, 25\uff09\uff09\u3092\u4e2d\u5fc3\u3068\u3057\u305f\uff0e\u8d70\u67fb \u7bc4\u56f2\u306f\uff0cX,Y\u8ef8\u3068\u3082\u306b\u00b130mm\u3068\u3057\uff0c\u9593\u969410mm\u3067\u5e38\u306bMz \u3092\u30bc\u30ed\u306b\u5236\u5fa1\u3057\u305f\uff0e\u8a66\u9a131\u3067\u306f\u4e0b\u5074FLP\u56fa\u5b9a\u306e\u3082\u3068\u3067\u4e0a\u5074 FLP\u306e\u307f\u3092\u8d70\u67fb\u3057\uff0c\u8a66\u9a132\u3067\u306f\u4e0a\u5074FLP\u56fa\u5b9a\u306e\u3082\u3068\u3067\uff0c\u4e0b \u5074FLP\u306e\u307f\u3092\u8d70\u67fb\u3057\u305f\uff0e\u306a\u304a\uff0cPz\u306f\u5e38\u306b\u3070\u306dA\u306e\u6e2c\u5b9a\u9ad8\u3055 \u306b\u304a\u3051\u308b\u8377\u91cd\u3068\u306a\u308b\u3088\u3046\u306b\u5236\u5fa1\u3057\u305f\uff0e" + ] + }, + { + "image_filename": "designv8_17_0003540_850_83_16-00414__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003540_850_83_16-00414__pdf-Figure1-1.png", + "caption": "Fig. 1 The 3-D key arrangement. This shows how 3 keys is pressed by 1 finger.", + "texts": [], + "surrounding_texts": [ + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.16-00414]\n\u30dc\u30fc\u30c9\u3092\u7528\u3044\u308b\u3053\u3068\u3067\uff0c\u5065\u5e38\u8005\u306e\u30ad\u30fc\u5165\u529b\u901f\u5ea6\u306f\uff0c\u8a13\u7df4\u6642\u9593\u304c\uff15\u6642\u9593\u307b\u3069\u3067\u6a19\u6e96\u30ad\u30fc\u306e\u5165\u529b\u901f\u5ea6\u3092\u8d85\u3048\uff0c\u8a13\u7df4\u6642 \u9593\u304c 60 \u6642\u9593\u3092\u8d85\u3048\u308b\u9803\u306b\u306f\u6a19\u6e96\u30ad\u30fc\u306e\u5165\u529b\u901f\u5ea6\u306e\u7d04 1.5 \u500d\u306b\u9054\u3059\u308b\u3068\u5831\u544a\u3055\u308c\u3066\u3044\u308b\uff08Ferrellt et al., 1992\uff09\uff0e\u4e00 \u65b9\u3067\uff0c\u7247\u9ebb\u75fa\u60a3\u8005\u306f\u624b\u6307\u306e\u4f38\u5c55\u52d5\u4f5c\u304c\u56f0\u96e3\u3068\u306a\u308b\u6027\u8cea\u3092\u6301\u3064\u305f\u3081\uff08\u4e0a\u7530, 1990. Kamper and Rymer, 2001\uff09\uff0c\u624b\u6307\u306e \u4f38\u5c55\u52d5\u4f5c\u304c\u5fc5\u8981\u306a\u65b9\u5411\u306b\u30ad\u30fc\u304c\u914d\u7f6e\u3055\u308c\u305f\u51f9\u578b\u306e\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u4f7f\u7528\u306f\u7247\u9ebb\u75fa\u60a3\u8005\u306b\u306f\u8ca0\u62c5\u3092\u5f37\u3044\u308b\uff0e\u7247\u9ebb\u75fa\u60a3\u8005 \u306e\u30bf\u30a4\u30d4\u30f3\u30b0\u901f\u5ea6\u5411\u4e0a\u3092\u5b9f\u73fe\u3059\u308b\u305f\u3081\u306b\u306f\uff0c\u3088\u308a\u5fae\u5c0f\u306a\u6307\u306e\u79fb\u52d5\u306b\u3088\u308b\u5165\u529b\u3068\uff0c\u9ebb\u75fa\u624b\u306b\u3068\u3063\u3066\u6bd4\u8f03\u7684\u52d5\u4f5c\u5bb9\u6613 \u306a\u624b\u6307\u5c48\u66f2\u52d5\u4f5c\u306b\u3088\u308b\u5165\u529b\u3092\u53ef\u80fd\u306b\u3059\u308b\u30ad\u30fc\u30dc\u30fc\u30c9\u304c\u5fc5\u8981\u3067\u3042\u308b\uff0e\n\u6211\u3005\u306f\uff0c\u624b\u6307\u306e\u52d5\u4f5c\u901f\u5ea6\u306e\u4f4e\u4e0b\u3057\u305f\u8efd\u5ea6\u306e\u7247\u9ebb\u75fa\u60a3\u8005\u306f\uff0c\u5165\u529b\u306b\u8981\u3059\u308b\u6307\u306e\u79fb\u52d5\u8ddd\u96e2\u3092\u77ed\u7e2e\u3059\u308b\u3088\u3046\uff0c\u6307\u306b\u5bc6 \u7740\u3059\u308b\u7acb\u4f53\u7684\u306a\u30ad\u30fc\u3092\u7528\u3044\u308b\u3053\u3068\u3067\uff0c\u5165\u529b\u901f\u5ea6\u306f\u5411\u4e0a\u3059\u308b\u3068\u8003\u3048\u305f\uff0e\u6211\u3005\u306f\u3053\u308c\u307e\u3067\u306b\uff0c\u30ad\u30fc\u30dc\u30fc\u30c9\u5165\u529b\u6642\u306b\u304a \u3051\u308b\u624b\u6307\u306e 3 \u6b21\u5143\u52d5\u4f5c\u89e3\u6790\u306b\u57fa\u3065\u304d\uff0c\u5165\u529b\u306b\u8981\u3059\u308b\u624b\u6307\u5c48\u66f2\u65b9\u5411\u306e\u6307\u306e\u79fb\u52d5\u8ddd\u96e2\u3092\u6700\u3082\u77ed\u7e2e\u3059\u308b\u3088\u3046 PIP \u95a2\u7bc0\u3068 \u6307\u5148\u306b\u5bc6\u7740\u3059\u308b\u7acb\u4f53\u7684\u306a\u30ad\u30fc\u30dc\u30fc\u30c9\uff08\u56f3 1, 2\uff09\u3092\u958b\u767a\u3057\u305f\uff08Suzuki et al., 2015\uff09\uff0e\u3053\u306e\u7acb\u4f53\u7684\u306a\u30ad\u30fc\u30dc\u30fc\u30c9\u306f\uff0c\u30ad \u30fc\u3068\u6307\u306e\u63a5\u89e6\u4f4d\u7f6e\u306f\u5b9a\u307e\u3063\u3066\u3044\u308b\u304c\uff0c\u6307\u306e\u52d5\u4f5c\u7279\u6027\u3092\u7a4d\u6975\u7684\u306b\u30ad\u30fc\u914d\u7f6e\u306b\u53cd\u6620\u3067\u304d\u3066\u3044\u306a\u3044\uff0e\u305d\u306e\u305f\u3081\uff0c\u30ad\u30fc\u3068 \u6307\u306e\u63a5\u89e6\u5f8c\u306e\u62bc\u4e0b\u52d5\u4f5c\u3067\u306f\uff0c\u4f7f\u7528\u8005\u306f\u4e3b\u89b3\u3068\u76f8\u9055\u3059\u308b\u64cd\u4f5c\u6027\u3068\u306a\u3063\u3066\u3044\u308b\u3053\u3068\u304c\u8ab2\u984c\u3068\u3057\u3066\u6319\u3052\u3089\u308c\u305f\uff0e\u3059\u306a\u308f \u3061\uff0c\u6307\u306e\u59ff\u52e2\u3092\u6c7a\u3081\u305f\u5f8c\u306b\uff0c\u305d\u306e\u6307\u59ff\u52e2\u3078\u5bc6\u7740\u3059\u308b\u3088\u3046\u306b\u30ad\u30fc\u914d\u7f6e\u3092\u8abf\u6574\u3057\u3066\u3044\u305f\uff0e\u3057\u304b\u3057\uff0c\u512a\u308c\u305f\u64cd\u4f5c\u6027\u3092\u6709 \u3059\u308b\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u958b\u767a\u306e\u305f\u3081\u306b\u306f\uff0c\u624b\u6307\u306e\u7b4b\u8089\u306e\u52d5\u304b\u3057\u3084\u3059\u3055\u3092\u30e2\u30c7\u30eb\u5316\u3057\uff0c\u305d\u306e\u30e2\u30c7\u30eb\u306b\u57fa\u3065\u3044\u305f\u624b\u6307\u59ff\u52e2\u306b \u6cbf\u3063\u3066\u30ad\u30fc\u914d\u7f6e\u3092\u8a2d\u8a08\u3059\u308b\u3053\u3068\u304c\u91cd\u8981\u3067\u3042\u308b\uff0e\n\u305d\u3053\u3067\uff0c\u624b\u6307\u306e\u7b4b\u8089\u306e\u52d5\u304b\u3057\u3084\u3059\u3055\u3092\u69cb\u6210\u3059\u308b\u6307\u6a19\u3092\u5c0e\u5165\u3057\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u8a2d\u8a08\u3078\u53cd\u6620\u3059\u308b\u3053\u3068\u3092\u8003\u3048\u308b\uff0e\u307e\u305a\uff0c \u30bf\u30a4\u30d4\u30f3\u30b0\u901f\u5ea6\u306e\u5411\u4e0a\u3092\u53ef\u80fd\u3068\u3059\u308b\u30ad\u30fc\u30dc\u30fc\u30c9\u3092\u5b9f\u73fe\u3059\u308b\u305f\u3081\uff0c\u624b\u6307\u3092\u6700\u5927\u9650\u901f\u304f\u52d5\u4f5c\u53ef\u80fd\u306a\u6307\u306e\u59ff\u52e2\u3078\u30ad\u30fc\u3092 \u914d\u7f6e\u3059\u308b\u3053\u3068\u304c\u5fc5\u8981\u3067\u3042\u308b\u3068\u8003\u3048\u305f\uff0e\u307e\u305f\uff0c\u30ad\u30fc\u30dc\u30fc\u30c9\u30bf\u30a4\u30d4\u30f3\u30b0\u52d5\u4f5c\u306f\u9577\u6642\u9593\u306b\u308f\u305f\u308b\u624b\u6307\u306e\u7b4b\u529b\u767a\u63ee\u3092\u7e70\u308a \u8fd4\u3059\u305f\u3081\uff0c\u7b4b\u8089\u306e\u75b2\u52b4\u304c\u84c4\u7a4d\u3057\u3084\u3059\u3044\u52d5\u4f5c\u3067\u3042\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u7b4b\u75b2\u52b4\u3092\u6700\u5c0f\u9650\u306b\u6291\u3048\u308b\u3053\u3068\u304c\u53ef\u80fd\u306a\u6307\u306e\u59ff\u52e2\u3078 \u30ad\u30fc\u3092\u914d\u7f6e\u3059\u308b\u3053\u3068\u304c\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u64cd\u4f5c\u6027\u5411\u4e0a\u306b\u304a\u3044\u3066\u91cd\u8981\u3067\u3042\u308b\u3068\u8003\u3048\u305f\uff0e\u3059\u306a\u308f\u3061\uff0c\u512a\u308c\u305f\u64cd\u4f5c\u6027\u3092\u6709\u3059\u308b \u30ad\u30fc\u30dc\u30fc\u30c9\u3092\u958b\u767a\u3059\u308b\u305f\u3081\u306b\u306f\uff0c\u7d20\u65e9\u3044\u64cd\u4f5c\u3068\u75b2\u308c\u306b\u304f\u3055\u3092\u4e21\u7acb\u3059\u308b\u6307\u306e\u59ff\u52e2\u306b\u57fa\u3065\u3044\u3066\u30ad\u30fc\u914d\u7f6e\u3092\u8a2d\u8a08\u3059\u308b\u3053 \u3068\u304c\u671b\u307e\u308c\u308b\uff0e\u7d20\u65e9\u3044\u64cd\u4f5c\u3068\u75b2\u308c\u306b\u304f\u3055\u3092\u4e21\u7acb\u3059\u308b\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u8a2d\u8a08\u306e\u305f\u3081\u306b\u306f\uff0c\u624b\u6307\u306e\u52d5\u4f5c\u89e3\u6790\u306b\u57fa\u3065\u304d\uff0c\u624b \u6307\u306e\u52d5\u4f5c\u901f\u5ea6\uff0c\u7b4b\u75b2\u52b4\u5ea6\u3068\u624b\u6307\u59ff\u52e2\u306e\u95a2\u4fc2\u6027\u3092\u30e2\u30c7\u30eb\u5316\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\n\u30ad\u30fc\u30dc\u30fc\u30c9\u5165\u529b\u6642\u306e\u624b\u6307\u306e\u52d5\u4f5c\u89e3\u6790\u3092\u884c\u3063\u305f\u7814\u7a76\u3068\u3057\u3066\uff0c\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u50be\u659c\u3092\u5909\u5316\u3055\u305b\u305f\u969b\u306e\u30ad\u30fc\u30dc\u30fc\u30c9\u5165\u529b \u901f\u5ea6\u306e\u8a08\u6e2c\uff0c\u53ca\u3073\u4f7f\u7528\u8005\u306e\u8155\u306e\u75b2\u52b4\u5ea6\u306e\u4e3b\u89b3\u7684\u306a\u8a55\u4fa1\u306b\u95a2\u3059\u308b\u7814\u7a76\uff08Swanson et al., 1997\uff09\u3084\uff0c\u30ad\u30fc\u5165\u529b\u6642\u306e\u624b\u95a2 \u7bc0\u89d2\u5ea6\u3092\u5909\u5316\u3055\u305b\u305f\u969b\u306e\u624b\u95a2\u7bc0\u306e\u75db\u307f\u3092\u4e3b\u89b3\u7684\u306b\u8a55\u4fa1\u3057\u305f\u7814\u7a76\uff08Liu et al., 2003\uff09\uff0c\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u4f5c\u52d5\u529b\u3092\u5909\u5316\u3055 \u305b\u305f\u969b\u306e\u4f7f\u7528\u8005\u306e\u624b\u6307\u306e\u8ca0\u8377\u3092\u7b4b\u96fb\u4f4d\u8a08\u6e2c\u304b\u3089\u6c42\u3081\u305f\u7814\u7a76\uff08Rempel et al., 1997\uff09\u7b49\u304c\u5b58\u5728\u3059\u308b\uff0e\u307e\u305f\uff0c\u30ad\u30fc\u30dc\u30fc \u30c9\u5165\u529b\u52d5\u4f5c\u306b\u9650\u3089\u305a\u4e00\u822c\u7684\u306a\u624b\u306e\u52d5\u304d\u306b\u95a2\u3059\u308b\u7814\u7a76\u3068\u3057\u3066\u306f\uff0c\u6307\u95a2\u7bc0\u89d2\u5ea6\u3068\u6307\u306e\u8171\u529b\u53ca\u3073\u767a\u63ee\u529b\u306e\u95a2\u4fc2\u6027\u3092\u30e2\u30c7 \u30eb\u5316\u3057\u305f\u7814\u7a76\uff08Fok and Chou, 2010\uff09\u3084\uff0c\u3064\u307e\u307f\u52d5\u4f5c\u6642\u306e\u6307\u59ff\u52e2\u3092\u5909\u5316\u3055\u305b\u305f\u969b\u306e\u7b4b\u529b\u3092\u30e2\u30c7\u30eb\u5316\u3057\u305f\u7814\u7a76 \uff08Weightman and Amis, 1982\uff09\uff0c\u69d8\u3005\u306a\u6307\u59ff\u52e2\u3067\u6307\u5148\u529b\u3092\u767a\u63ee\u3057\u305f\u969b\u306e\u6307\u5148\u529b\u3068\u7b4b\u96fb\u4f4d\u3092\u8a08\u6e2c\u3057\u305f\u7814\u7a76\uff08Cruz et al., 2005\uff09\u7b49\u304c\u5b58\u5728\u3059\u308b\uff0e\u4e00\u65b9\u3067\uff0c\u624b\u6307\u306e\u59ff\u52e2\u3068\u624b\u6307\u306e\u52d5\u4f5c\u901f\u5ea6\uff0c\u7b4b\u75b2\u52b4\u5ea6\u306e\u5b9a\u91cf\u7684\u306a\u95a2\u4fc2\u6027\u3092\u6c42\u3081\u305f\u7814\u7a76\uff0c\u53ca\u3073\u624b \u6307\u306e\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3092\u4e21\u7acb\u3059\u308b\u624b\u6307\u59ff\u52e2\u306e\u30e2\u30c7\u30eb\u306b\u95a2\u3059\u308b\u7814\u7a76\u306f\u3042\u307e\u308a\u898b\u53d7\u3051\u3089\u308c\u306a\u3044\uff0e\n\u7b4b\u8089\u3092\u69cb\u6210\u3059\u308b\u904b\u52d5\u5358\u4f4d\u306b\u306f\uff0c\u53ce\u7e2e\u901f\u5ea6\u306f\u9045\u3044\u304c\u75b2\u52b4\u306f\u3057\u306b\u304f\u3044\u6027\u8cea\u3092\u6301\u3064\u904b\u52d5\u5358\u4f4d\u3068\uff0c\u53ce\u7e2e\u901f\u5ea6\u306f\u901f\u3044\u304c\u75b2 \u52b4\u306f\u3057\u3084\u3059\u3044\u6027\u8cea\u3092\u6301\u3064\u904b\u52d5\u5358\u4f4d\u304c\u5b58\u5728\u3059\u308b\uff08Burke and Edgerton, 1975\uff09\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u306f\u30c8 \u30ec\u30fc\u30c9\u30aa\u30d5\u306e\u95a2\u4fc2\u306b\u3042\u308a\uff0c\u52d5\u4f5c\u901f\u5ea6\uff0c\u7b4b\u75b2\u52b4\u5ea6\u3068\u624b\u6307\u59ff\u52e2\u306e\u95a2\u4fc2\u6027\u306f\u540c\u69d8\u306e\u50be\u5411\u306f\u793a\u3055\u305a\uff0c\u7570\u306a\u308b\u624b\u6307\u59ff\u52e2\u3067\u52d5 \u4f5c\u901f\u5ea6\u306f\u6700\u5927\uff0c\u7b4b\u75b2\u52b4\u5ea6\u306f\u6700\u5c0f\u306b\u306a\u308b\u3068\u8003\u3048\u3089\u308c\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3068\u3044\u3046 2 \u3064\u306e\u76ee\u7684\u95a2\u6570\u3092\u7528 \u3044\u3066\u6307\u59ff\u52e2\u3092\u6c7a\u5b9a\u3059\u308b\u591a\u76ee\u7684\u6700\u9069\u5316\u554f\u984c\u304c\u5b9a\u5f0f\u5316\u3055\u308c\u308b\uff0e\u3053\u3053\u3067\u306f\uff0c\u30d1\u30ec\u30fc\u30c8\u89e3\u96c6\u5408\u3068\u79f0\u3059\u308b\u89e3\u96c6\u5408\u304c\u5c0e\u51fa\u3055\u308c\uff0c \u5b9a\u5f0f\u5316\u3055\u308c\u3066\u3044\u306a\u3044\u8a2d\u8a08\u6307\u6a19\u3092\u5c0e\u5165\u3059\u308b\u3053\u3068\u306a\u304f\u6700\u9069\u89e3\u3092\u4e00\u3064\u306b\u5b9a\u3081\u308b\u3053\u3068\u306f\u56f0\u96e3\u3067\u3042\u308b\uff0e\u4e00\u65b9\u3067\uff0c\u30d1\u30ec\u30fc\u30c8\u89e3 \u96c6\u5408\u3092\u69cb\u6210\u3059\u308b\u8a2d\u8a08\u89e3\u3092\u691c\u8a0e\u3059\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u624b\u6307\u306e\u7d20\u65e9\u3044\u52d5\u304d\u3068\u75b2\u308c\u306b\u304f\u3055\u3092\u4e21\u7acb\u3057\u305f\u624b\u6307\u59ff\u52e2\u306e\u6700\u9069\u306a\u72b6\u614b \u306b\u3042\u308b\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u8a2d\u8a08\u6307\u91dd\u3092\u5f97\u308b\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u305d\u3053\u3067\u672c\u7814\u7a76\u3067\u306f\uff0c\u624b\u6307\u306e\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3092\u4e21\u7acb\u3059 \u308b\u624b\u6307\u59ff\u52e2\u30e2\u30c7\u30eb\u306e\u69cb\u7bc9\u3092\u76ee\u7684\u3068\u3059\u308b\uff0e", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.16-00414]\n\u6307\u306e\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3092\u5b9a\u91cf\u5316\u3057\u30ad\u30fc\u30dc\u30fc\u30c9\u306e\u8a2d\u8a08\u60c5\u5831\u3068\u3057\u3066\u6d3b\u7528\u3059\u308b\u305f\u3081\u306b\uff0c\u5b9f\u969b\u306e\u6307\u3088\u308a\u6e2c\u5b9a\u3059\u308b\u3053\u3068 \u306b\u3088\u308a\u5b9a\u91cf\u5316\u3059\u308b\uff0e\u3053\u3053\u3067\u306f\uff0c\u6307\u306e\u52d5\u4f5c\u901f\u5ea6\u3092\u8003\u616e\u3057\u305f\u6e2c\u5b9a\u6cd5\u306e\u69cb\u7bc9\u304c\u5fc5\u8981\u3068\u306a\u308a\uff0c\u4ee5\u4e0b\u306b\u305d\u306e\u624b\u9806\u3092\u793a\u3059\uff0e\u3055 \u3089\u306b\uff0c\u5f97\u3089\u308c\u305f\u5b9a\u91cf\u5316\u6307\u6a19\u3092\u6d3b\u7528\u3057\u305f\u6700\u9069\u8a2d\u8a08\u6cd5\u306e\u9069\u7528\u6cd5\u306b\u3064\u3044\u3066\u8aac\u660e\u3059\u308b\uff0e\n2\u30fb1 \u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u306e\u5b9a\u91cf\u5316\u624b\u6cd5 \u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3092\u4e21\u7acb\u3059\u308b\u624b\u6307\u30e2\u30c7\u30eb\u3092\u69cb\u7bc9\u3059\u308b\u305f\u3081\u306b\u306f\uff0c\u624b\u6307\u306e\u52d5\u4f5c\u89e3\u6790\u3092\u884c\u3044\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3092 \u5b9f\u6e2c\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\u4ee5\u4e0b\u306b\uff0c\u5f93\u6765\u306e\u5b9f\u65bd\u4f8b\u3092\u6574\u7406\u3057\u672c\u7814\u7a76\u3067\u63d0\u6848\u3057\u5b9f\u65bd\u3057\u305f\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u306e\u8a08\u6e2c\u624b\u6cd5\u306b \u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e\n\u52d5\u4f5c\u306e\u901f\u5ea6\u3092\u8a08\u6e2c\u3059\u308b\u624b\u6cd5\u3068\u3057\u3066\u306f\uff0c\u901f\u5ea6\u30bb\u30f3\u30b5\u3092\u7528\u3044\u308b\u624b\u6cd5\uff08\u83ca\u8c37\u4ed6, 2000\uff09\u3084\uff0c\u624b\u6307\u306b\u53d6\u308a\u4ed8\u3051\u305f\u52a0\u901f\u5ea6\u30bb \u30f3\u30b5\u304b\u3089\u53d6\u5f97\u3057\u305f\u52a0\u901f\u5ea6\u30c7\u30fc\u30bf\u3092\u7a4d\u5206\u3057\u3066\u901f\u5ea6\u3092\u7b97\u51fa\u3059\u308b\u624b\u6cd5\uff08\u5742\u7530\u4ed6, 2010\uff09\uff0c\u30e2\u30fc\u30b7\u30e7\u30f3\u30ad\u30e3\u30d7\u30c1\u30e3\u3088\u308a\u5f97\u3089 \u308c\u305f\u4f4d\u7f6e\u30c7\u30fc\u30bf\u3092\u5fae\u5206\u3057\u3066\u901f\u5ea6\u3092\u7b97\u51fa\u3059\u308b\u624b\u6cd5\uff08\u53f3\u7530\u4ed6, 2014\uff09\u304c\u3042\u308b\uff0e\u3057\u304b\u3057\uff0c\u672c\u7814\u7a76\u306b\u304a\u3051\u308b\u5bfe\u8c61\u52d5\u4f5c\u3067\u3042\u308b \u30ad\u30fc\u306e\u62bc\u4e0b\u306f\u9759\u7684\u306a\u529b\u306e\u767a\u63ee\u306b\u3088\u308b\u7b49\u5c3a\u6027\u904b\u52d5\u3067\u3042\u308b\u305f\u3081\uff0c\u52d5\u7684\u306a\u52d5\u304d\u306e\u901f\u5ea6\u3084\u52a0\u901f\u5ea6\uff0c\u4f4d\u7f6e\u306e\u5909\u5316\u306e\u8a08\u6e2c\u624b\u6cd5 \u3092\u9069\u7528\u3059\u308b\u3053\u3068\u306f\u56f0\u96e3\u3067\u3042\u308b\uff0e\u305d\u3053\u3067\uff0c\u672c\u7814\u7a76\u3067\u306f\u9759\u7684\u306a\u529b\u306e\u767a\u63ee\u901f\u5ea6\u3092\u7b97\u51fa\u3059\u308b\u305f\u3081\uff0c\u62bc\u4e0b\u529b\u306e\u901f\u5ea6\u6210\u5206\u3092\u7b97 \u51fa\u3059\u308b\u624b\u6cd5\u3092\u63d0\u6848\u3059\u308b\uff0e\u62bc\u4e0b\u529b\u306e\u901f\u5ea6\u6210\u5206\u306f\uff0c\u30ad\u30fc\u62bc\u4e0b\u958b\u59cb\u304b\u3089\u4e00\u5b9a\u6642\u9593\u7d4c\u904e\u5f8c\u306e\u62bc\u4e0b\u529b\u306e\u5230\u9054\u5024\uff0c\u3059\u306a\u308f\u3061\u5358 \u4f4d\u6642\u9593\u5f53\u305f\u308a\u306e\u62bc\u4e0b\u529b\u5897\u52a0\u91cf V\uff08\u56f3 3\uff09\u3068\u3057\u3066\u7b97\u51fa\u3059\u308b\uff0e\u5358\u4f4d\u6642\u9593\u3042\u305f\u308a\u306e\u62bc\u4e0b\u529b\u5897\u52a0\u91cf\u3092\u7b97\u51fa\u3059\u308b\u969b\u306f\uff0c\u62bc\u4e0b\u3092 \u59cb\u3081\u3066\u304b\u3089\u62bc\u4e0b\u529b\u304c\u5897\u52a0\u3057\u7d9a\u3051\u3066\u3044\u308b\u6642\u9593\u5185\u306e\u6642\u9593\u3092\u5358\u4f4d\u6642\u9593\u3068\u3057\u3066\u7528\u3044\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\u305d\u3053\u3067\uff0c\u88ab\u9a13\u8005\u304c\u62bc\u4e0b \u3092\u958b\u59cb\u3057\u3066\u304b\u3089\u62bc\u4e0b\u306e\u6700\u5927\u5024\u306b\u9054\u3059\u308b\u307e\u3067\u306e\u6642\u9593 Tp\uff08\u56f3 4\uff09\u306e\u6700\u5c0f\u5024\u3092\u5b9f\u9a13\u304b\u3089\u5c0e\u51fa\u3057\uff0c\u305d\u306e\u6700\u5c0f\u5024\u4ee5\u4e0b\u306e\u5024\u3092 \u5358\u4f4d\u6642\u9593\u3068\u3057\u3066\u7528\u3044\u308b\uff0e\u672c\u7814\u7a76\u3067\u306f\u4ee5\u4e0a\u306e\u65b9\u6cd5\u306b\u57fa\u3065\u304d\uff0c\u52d5\u4f5c\u901f\u5ea6\u306e\u6307\u6a19\u3068\u3057\u3066\u5358\u4f4d\u6642\u9593\u3042\u305f\u308a\u306e\u62bc\u4e0b\u529b\u5897\u52a0\u91cf V \u3092\u7528\u3044\u308b\uff0e\n\u7b4b\u8089\u306e\u75b2\u52b4\u3092\u8a08\u6e2c\u3059\u308b\u624b\u6cd5\u3068\u3057\u3066\u306f\uff0c\u7b4b\u96fb\u56f3\u306e\u5468\u6ce2\u6570\u89e3\u6790\u306b\u3088\u308b\u624b\u6cd5\u304c\u5e83\u304f\u7528\u3044\u3089\u308c\u3066\u3044\u308b\uff08Merletti et al., 2001\uff09\uff0e\u7b4b\u8089\u306f\u75b2\u52b4\u5f8c\u306b\u7b4b\u96fb\u56f3\u306e\u5468\u6ce2\u6570\u304c\u4f4e\u5024\u3078\u79fb\u884c\uff08\u9664\u6ce2\u5316\uff09\u3059\u308b\u6027\u8cea\u3092\u6301\u3064\uff0e\u75b2\u52b4\u5f8c\u306b\u7b4b\u96fb\u56f3\u306e\u5468\u6ce2\u6570\u5e2f\u57df\u304c \u4f4e\u4e0b\u3059\u308b\u3053\u3068\u306e\u80cc\u666f\u306b\u306f\uff0c\u75b2\u52b4\u306b\u3088\u308b\u904b\u52d5\u5358\u4f4d\u306e\u52d5\u54e1\u306e\u6e1b\u5c11\u3084\uff0c\u904b\u52d5\u5358\u4f4d\u306e\u540c\u671f\u5316\u7b49\u304c\u5f71\u97ff\u3057\u3066\u3044\u308b\uff0e\u7b4b\u96fb\u56f3\u306e \u5468\u6ce2\u6570\u5e2f\u57df\u306e\u4f4e\u4e0b\u306f\uff0c\u7b4b\u96fb\u56f3\u3092\u9ad8\u901f\u30d5\u30fc\u30ea\u30a8\u5909\u63db\u3057\u3066\u5f97\u3089\u308c\u308b\u30d1\u30ef\u30fc\u30b9\u30da\u30af\u30c8\u30eb\u5206\u5e03\u56f3\u306e\u30d1\u30ef\u30fc\u30b9\u30da\u30af\u30c8\u30eb\u306e\u9762 \u7a4d\u3092\u7b49\u5206\u3059\u308b\u5468\u6ce2\u6570\u3067\u3042\u308b\u4e2d\u9593\u5468\u6ce2\u6570\u306e\u4f4e\u4e0b\u3068\u3057\u3066\u7b97\u51fa\u3067\u304d\u308b\uff0e\u3053\u306e\u3088\u3046\u306a\u7b4b\u96fb\u56f3\u306e\u5468\u6ce2\u6570\u89e3\u6790\u306f\uff0c\u30ad\u30fc\u30dc\u30fc\u30c9", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.16-00414]\n\u306e\u4e2d\u9593\u5468\u6ce2\u6570\u304c\u4f4e\u4e0b\u3059\u308b\u3053\u3068\u304c\u5831\u544a\u3055\u308c\u3066\u3044\u308b\uff08Lin et al., 2004\uff09\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u672c\u7814\u7a76\u3067\u306f\u624b\u6307\u306e\u7b4b\u75b2\u52b4\u5ea6\u306e\u6307\u6a19 \u3068\u3057\u3066\uff0c\u30bf\u30b9\u30af\u524d\u5f8c\u306e\u7b4b\u96fb\u56f3\u306e\u4e2d\u9593\u5468\u6ce2\u6570\u306e\u4f4e\u4e0b\u7387 R \u3092\u7528\u3044\u308b\uff08\u56f3 5\uff09\uff0eR \u304c\u5927\u304d\u3044\u307b\u3069\uff0c\u7b4b\u75b2\u52b4\u306f\u5c0f\u3055\u3044\u3053\u3068\u304c \u4e88\u60f3\u3055\u308c\u78ba\u8a8d\u3059\u308b\uff0e\n2\u30fb2 \u91cd\u307f\u4fc2\u6570\u6cd5\u306b\u57fa\u3065\u304f\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3092\u4e21\u7acb\u3059\u308b\u624b\u6307\u30e2\u30c7\u30eb\u306e\u69cb\u7bc9 \u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3092\u4e21\u7acb\u3059\u308b\u624b\u6307\u30e2\u30c7\u30eb\u3092\u69cb\u7bc9\u3059\u308b\u4e0a\u3067\u306f\uff0c\u52d5\u4f5c\u901f\u5ea6\u3068\u7b4b\u75b2\u52b4\u5ea6\u3068\u3044\u3046\u8907\u6570\u306e\u76ee\u7684\u95a2\u6570\u3092\u53d6 \u308a\u6271\u3046\u5fc5\u8981\u304c\u3042\u308b\uff0e\u8907\u6570\u306e\u76ee\u7684\u95a2\u6570\u3092\u53d6\u308a\u6271\u3046\u305f\u3081\u306b\u591a\u76ee\u7684\u6700\u9069\u8a2d\u8a08\u624b\u6cd5\u304c\u3042\u308a\uff0c\u3053\u306e\u4e2d\u306b\uff0c\u91cd\u307f\u4fc2\u6570\u6cd5\uff08\u5742\u548c\uff0c 1986\uff09\u304c\u5b58\u5728\u3059\u308b\uff0e\u91cd\u307f\u4fc2\u6570\u6cd5\u3068\u306f\uff0c\u8907\u6570\u306e\u76ee\u7684\u95a2\u6570\u306b\u91cd\u307f\u4ed8\u3051\u3092\u884c\u3044\u52a0\u7b97\u3057\uff0cLp\u30ce\u30eb\u30e0\u306b\u3088\u308a\u5358\u4e00\u306e\u76ee\u7684\u95a2\u6570 \u3092\u69cb\u6210\u3057\uff0c\u5358\u4e00\u6700\u9069\u5316\u554f\u984c\u3092\u89e3\u304f\u624b\u6cd5\u3092\u9069\u7528\u3059\u308b\u3082\u306e\u3067\u3042\u308b\uff0e\u4e00\u822c\u306b\uff0c\u76ee\u7684\u95a2\u6570\u3092\u6b63\u898f\u5316\u3059\u308b\u3053\u3068\u306b\u3088\u308a\u6b21\u5143\u91cf \u304c\u7570\u306a\u308b\u7269\u7406\u91cf\u306e\u5909\u52d5\u3068\u91cd\u307f\u306e\u5909\u52d5\u306b\u5408\u7406\u7684\u306a\u95a2\u4fc2\u3092\u6301\u305f\u305b\u308b\u3053\u3068\u304c\u53ef\u80fd\u3068\u3059\u308b\u624b\u6cd5\u3067\u3042\u308b\uff0e\u91cd\u307f\u4fc2\u6570\u6cd5\u306f\uff0c\u8907 \u6570\u306e\u76ee\u7684\u95a2\u6570\u3092\u6700\u9069\u5316\u3059\u308b\u591a\u76ee\u7684\u6700\u9069\u5316\u554f\u984c\u306b\u5bfe\u3057\u3066\u5e83\u304f\u7528\u3044\u3089\u308c\u3066\u3044\u308b\u624b\u6cd5\u3067\u3042\u308a\uff0c\u624b\u8853\u652f\u63f4\u30ed\u30dc\u30c3\u30c8\u306b\u304a\u3051 \u308b\u9257\u5b50\u6a5f\u69cb\u306e\u6700\u9069\u5316\u8a2d\u8a08\uff08\u5ddd\u6751\u4ed6, 2012\uff09\u3084\uff0c\u5bb6\u5ead\u7528\u7a7a\u8abf\u6a5f\u5668\u306e\u30d2\u30fc\u30c8\u30dd\u30f3\u30d7\u30b7\u30b9\u30c6\u30e0\u306e\u69cb\u6210\u6a5f\u5668\u30b3\u30b9\u30c8\u3068\u6d88\u8cbb\u52d5 \u529b\u306e\u6700\u9069\u5316\uff08\u4f0a\u6771\u4ed6, 1986\uff09\uff0c\u53ce\u76ca\u6027\u3092\u78ba\u4fdd\u3057\u306a\u304c\u3089\u8fb2\u5730\u7d44\u7e54\u304b\u3089\u6392\u51fa\u3055\u308c\u308b\u5168\u7a92\u7d20\u8ca0\u8377\u91cf\u3092\u6291\u5236\u3059\u308b\u8ee2\u4f5c\u5703\u5834\u306e \u914d\u7f6e\u306e\u6700\u9069\u5316\uff08\u9577\u91ce\u4ed6, 2010\uff09\u7b49\u306b\u7528\u3044\u3089\u308c\u3066\u3044\u308b\uff0e\u91cd\u307f\u4fc2\u6570\u6cd5\u3092\u7528\u3044\u308b\u3053\u3068\u3067\uff0c\u5404\u76ee\u7684\u95a2\u6570\u306e\u91cd\u8981\u5ea6\u3092\u91cd\u307f\u3068\u3057 \u3066\u8868\u3059\u3053\u3068\u304c\u3067\u304d\uff0c\u8907\u6570\u306e\u76ee\u7684\u95a2\u6570\u3092\u6700\u9069\u5316\u3059\u308b\u591a\u76ee\u7684\u6700\u9069\u5316\u554f\u984c\u3092\u89e3\u304d\u30d1\u30ec\u30fc\u30c8\u89e3\u96c6\u5408\u3092\u5f97\u308b\u3053\u3068\u304c\u53ef\u80fd\u3068\u306a \u308b\uff0e\n2\u30fb1 \u7bc0\u3067\u8ff0\u3079\u305f\u52d5\u4f5c\u901f\u5ea6\u306e\u6307\u6a19 V\uff08\u521d\u671f\u5024 V0\uff09\u3068\u7b4b\u75b2\u52b4\u5ea6\u306e\u6307\u6a19 R\uff08\u521d\u671f\u5024 R0\uff09\u3092\u91cd\u307f\u4fc2\u6570\u6cd5\u306b\u57fa\u3065\u304d\u5408\u6210\u3059\n\u308b\u3068\u5f0f\uff081\uff09\u3068\u306a\u308b\uff0e\u5f0f\uff081\uff09\u306b\u304a\u3044\u3066 w \u306f\u91cd\u307f\u4fc2\u6570\u3067\u3042\u308a\u5f0f\uff082\uff09\u306e\u7bc4\u56f2\u3092\u3068\u308b\uff0e\n0 0\n(1 ) V R\nw w V R \uff081\uff09\n10 w \uff082\uff09\nFig. 3 Index of motion speed (Pressing force increment per unit time). This shows how to calculate the index of motion speed V. The calculation method needs the unit time.\nFig. 4 Pressing time. Pressing time is time from pressing start to achieve the maximum pressing force.\n0\n1\n0 0.6\nF o\nrc e\nf N\nTime t s\nPressing start\nIndex of\nmotion speed\nV\nUnit time\nF o\nrc e\nTime 0\n1\n0 0.6\nF o rc\ne f\nN\nTime t s Time\nF o rc\ne\nPressing time\nTp\nPressing start Maximum\nPressing force" + ] + }, + { + "image_filename": "designv8_17_0000545_4.03.023663.full.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000545_4.03.023663.full.pdf-Figure2-1.png", + "caption": "Fig. 2 Schematic diagram of: a) resultant and decomposition of a vector, b) geometry of approximate dipole. a) A complex number is the equivalent of a 2 dimensional vector. The resultant \u03a8 is the sum of \u03a8i (where i=1,2,3) which can be obtained by solving the Helmholtz equation with different components flap as reflect boundary and interaction term \u03a8Interaction, which is complex difference between complete shape and other parts. b) The inner/outer cavity (PI, PO) is considered as approximate dipole with distance d and rotation angle \u03b80.", + "texts": [ + " Hence, a point acoustic source is put in the canal opening, and then FEM is utilized to calculate the acoustic near field. The Kirchhoff integral formulation is used to calculate the acoustic far field projection. For the far field calculation, the spherical coordinate system is used. The radius of the calculated spherical surface is 10m, on which the calculated angle is -180\u00b0 to 180\u00b0 in azimuth and -90\u00b0 to 90\u00b0 in elevation both with 1\u00b0 interval. The acoustic near field calculated by FEM using complex numbers, for which the pressure on point can be decomposed into several vectors, as shown in Fig. 2. According to the acoustic superposition principle [14]. the overall acoustic filed is superposed by the spherical wave generated by the sound source and reflected by the baffles. Hence, the overall acoustic field can be decomposed into the summation of the wave from all sound sources and reflection. The corner reflector can be used as an example to make the concept more intuitive to be understood, which can be referred to Ref. [2,13]. One sound source is positioned in a reflector formed by two orthogonal planes, then, the acoustic near field is calculated", + " A Cartesian coordinate system is built with pi as origin, and the pressure amplitude at any point p(r, ) can be written as [13, oir ppp += (2) Where, )( 0ItkrjI i e r P p \u03d5\u03c9 \u2212\u2212\u2212= (3) )( OtrkjO o e r P p \u03d5\u03c9 \u2212\u2212\u2032\u2212 \u2032 = (4) where, PI and PO are sound pressure amplitude of dipole, \u03c6O and \u03c6I is the initial phase, r and r\u2019 are the distance between points of dipole and the calculated point, \u0394\u2212=\u2032 rr (5) )cos(* 0\u03b8\u03c6 \u2212=\u0394 d (6) where, is the elevation angle, d is the distance of two points of dipole, \u03b80 is the angle between the dipole and the horizontal plane. The Eq. (2) can be written as ]*[ *]**[ 1 )( )()( \u03d5 \u03c9 \u03c9\u03d5\u03d5 j tkrj tkrjkj O j I oir ep r e eepep r ppp OI \u2212\u2212 \u2212\u2212+\u0394 = +\u2248 += (7) where, )cos(***222 IOOIOI kppppp \u03d5\u03d5 \u2212\u0394+++= (8) and, )cos(cos )sin(sin tan 1 OOII OOII kpp kpp \u03d5\u03d5 \u03d5\u03d5\u03d5 +\u0394+ +\u0394+= \u2212 (9) As shown in Eq. (7), when r is constant, pr is determined by the phase difference between the dipole \u03c6O-\u03c6I, wave number k and d*cos( -\u03b80), which is the difference of sound path that the sound travels from far-field to each pole (see Fig. 2 (b)). As shown in Fig. 1, the flap is situated in a half-opened circle, and split one cavity into two cavities. When the two cavities are in resonance, they can be simplified into a dipole (shown as Fig. 2 (b)), and this simplification is investigated in this study. The data obtained from the both cavities are analyzed. The geometrical central points of the cavities are considered as the position of the dipole, and angle between the dipole and the horizontal line is the initial oblique angle \u03b80. The amplitude (pI, pO) and phase (\u03c6I and the outer cavity \u03c6O) of the dipole are calculated for each frequencies and plotted for each items (pinna without flap, flap, interaction), as shown in Fig. 3 (a), (c), (e)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001896_9668973_09762722.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001896_9668973_09762722.pdf-Figure11-1.png", + "caption": "FIGURE 11. Percentage sensitivity of residual oscillations using ZVD-shaped commands in (a) \u03c61 and (b) \u03c62 to uncertainties in k , and in (c) \u03c61 and (d) \u03c62 to uncertainties in r .", + "texts": [ + " Residual oscillations in both the hoisting cable and the payload angles remain below 0.75\u25e6 across the complete range of introduced errors and for all cable lengths used, as shown in Fig. 9. Fig. 10 shows a reduction of more than 90% in residual oscillation for the complete\u00b150% error range, and more than 95% reduction in an error range of\u00b135%, in both oscillation angles and for both payload parameters k and r . As for the case of a ZVD input-shaper, a reduction of more than 95% in residual oscillation for the complete \u00b150% error range, as shown in Fig. 11. VI. CONCLUSION Eliminating residual oscillations in multimode systems using input-shaping techniques requires the use of complex multimode techniques. Multimode input-shaping techniques are designed to eliminate residual oscillation at a predetermined set of discrete frequencies. The problem becomes more complicated when the frequencies of the multimode system are time-dependent as in the case of a double-pendulum crane with varying cable length presented in this work. Single-mode input-shapers can be used to eliminate vibrations in multimode systems provided that there exists a design frequency such that all ratios of the componentmode frequencies to that design frequency are odd and coprime" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001073_.srce.hr_file_280260-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001073_.srce.hr_file_280260-Figure2-1.png", + "caption": "Figure 2 Optimal robot poses according to individual criteria: a) condition number, b) joint limit avoidance, c) combination of a) and b)", + "texts": [ + " It proved to be a satisfying solution in terms of speed and optimization results considering six optimization parameters in this application. Initial conditions for the minimization algorithm can be set arbitrarily. However, depending on the application, it is convenient to set the initial positions of robots in respect to the targets in real physical boundaries of the robot workspace. This assures a good starting position for fast execution of the optimization. Different values of scaling factors k1, k2 and k3 will be shown in Fig. 2 in order to illustrate the effect of individual criteria in the objective function in respect to target positions contained in a coordinate frame of a test phantom. Regarding Fig. 2: a) k2, k3 = 0, the condition number \ud835\udc50\ud835\udc50 forces all target points in the position of maximal dexterity which lies relatively close to the origin of the robot base coordinate system. b) k1, k3 =0, joint limit avoidance \u03c6 tends to put all the target locations far from the robot base origin and 1708 Technical Gazette 24, 6(2017), 1705-1711 therefore forces the robot to operate in a stretched configuration. c) k3 = 0, combining the two criteria (c and \u03c6 ) a more neutral pose of the robot is achieved while maintaining good dexterity values" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001922_1044-023-09952-2.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001922_1044-023-09952-2.pdf-Figure8-1.png", + "caption": "Fig. 8 Geometrical description of the simulated deep groove ball bearing: (a) Full model; (b) Detail view of the pocket", + "texts": [ + " Among the several modelling scenarios, the main criterion has been established to divide the proposed designs, which consists of the way in which the cage is modelled, that is, whether the interactions between the cage and the balls are treated with the contact methodologies presented in Sect. 4.1 or not. Thus, on the one hand, those approaches that do not make use of contact interactions regarding the cage are denoted as \u201cnon-contact\u201d models and presented in Sect. 5.2, on the other hand, the solutions that do include contact events are named \u201ccontact\u201d models and given in Sect. 5.3. The dimensions of the bearing and its components are based on a real model from which the pitch diameter and the ball diameter are known. The main dimensional parameters are represented in Fig. 8. The value of the clearance has been defined according to those used in similar works [16]. Moreover, the values of the race diameters have been obtained using the following expressions: Do = Dm + Db + 1 2 Pd (5.1) Di = Dm \u2212 Db \u2212 1 2 Pd (5.2) The geometric and material properties for the deep groove ball bearing used in the model are provided in Table 1, whereas the parameters implemented in the normal and friction contact forces and the spring elements are resumed in Table 2. The same value of the coefficient of restitution and friction coefficient has been applied to all the contact events to ensure a suitable comparison of results among the different modelling approaches" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure9.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure9.1-1.png", + "caption": "Figure 9.1: Revolving Vane Expander Schematic", + "texts": [ + "6: Discharge Pressure and Motor Torque Measurement until Prototype Seizure . 161 Figure 8.7: Typical Measurement Readout for Short Operating Periods ............................ 163 Figure 8.8: Measured Discharge Pressure based on Stipulated Mass Flow Rates ............... 164 Figure 8.9: Comparison of Predicted Mass Flow rates against Measured Data .................. 166 xi Figure 8.10: Compressor Volumetric Efficiencies Computed from Measurements ............ 167 Figure 8.11: Predicted Volumetric Efficiencies with Smaller Leakage Clearance Gaps .... 168 Figure 9.1: Revolving Vane Expander Schematic ............................................................... 173 Figure 9.2: Air Expander Experimennt Schematic .............................................................. 174 Figure 9.3: Comparison between Theoretical Model and Measurements ........................... 176 Figure 9.4: Secondary Vibration Mode in RV Air Expander .............................................. 177 xii List of Tables Table 3.1: Preliminary Design Dimensions .................", + " Following the preamble on air expanders, this section will proceed to detail the mechanism of the RV air expander and explain the adaptation of the dynamics model for use in modelling the air expander. The RV mechanism for use in an air expander remains largely unchanged, except that the suction chamber now draws in pressurised air and expands it while the discharge chamber would discharge the expanded air; a reverse of the typical compression cycle. A cross-section of the RV expander cylinder-rotor assembly can be found in Figure 9.1 and more detailed explanations on the working principle of the expander can be found in the article by Subiantoro et al. [139]. 173 The dynamics model for the RV mechanism variant in which the vane attached to the rotor was covered in Section 6.3.2. As the RV mechanism for the expander is similar, the model can be easily and readily adapted. For the expander, the motor torque term (Tm) in Equation (6.16) has been changed to that of the output torque term (Tload) as shown in Equation (9.1). \ud835\udc3c\ud835\udc5f\ud703\u0308\ud835\udc5f = \ud835\udc47\ud835\udc54 \u2212 \ud835\udc47\ud835\udc59\ud835\udc5c\ud835\udc4e\ud835\udc51 \u2212 \ud835\udc51\ud703\ud835\udc50 \ud835\udc51\ud703\ud835\udc5f (\ud835\udc3c\ud835\udc50\ud703\u0308\ud835\udc50) \u2212 \ud835\udc51\ud835\udf19 \ud835\udc51\ud703\ud835\udc5f (\ud835\udc5a\ud835\udc4f\ud835\udc51\ud835\udc4f" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure20-1.png", + "caption": "Figure 20: 3D CAD image of the robotic footplate support frame built of 1.5\u201d aluminum [131].", + "texts": [ + ".................................................................................................... 36 Figure 19: The robotic force-plate with 2-DOF actuation (TOP: CAD drawing; BOTTOM: Experimental Prototype). The cubic support frame (1); internal and external layers of the footplate (2); the PF/DF motor and transmission system (3); the IN/EV motor and transmission system (4); the encoders (5); the foot strap (6); and mechanical stop (7). .................................................. 38 Figure 20: 3D CAD image of the robotic footplate support frame built of 1.5\u201d aluminum [131] .............. 39 ix Figure 21: Image of the interior frame; Left: INEV axis of rotation, right: INEV built in within the DFPF axis [131] .................................................................................................................................... 40 Figure 22: The robotic force-plate, load cells and sensing mechanism (TOP: experimental prototype; BOTTOM: CAD drawing). The load cells (1); acrylic plate (2); aluminum plate (3); metal crossbar (4); aluminum beams (5); the linear spring to create a preload (6)", + " The early goal of this project was to create a portable ankle rehabilitation device that would allow for various ankle training exercises in the clinic [33]. In the later stages of research, and due to need in the field, the concept for the device evolved into ankle and balance training system that can be used in multiple positions from sitting to standing [37]. Figure 17: The model of 2-DOF NUVABAT and the schematic for ankle and balance training [35], Copyright \u00a9 2010 IEEE. 32 NUVABAT houses a moveable platform that is able to rotate under the patient\u2019s ankle, as shown in Figure 20-top. The footplate is able to rotate freely on both the anterior-posterior and mediallateral axes to provide two degrees of freedom (2-DOF) around desired ankle motions, dorsiflexion/plantarflexion (DFPF) and inversion/eversion (INEV). The combinations of these 2- DOF contribute to supination (SUP) and pronation (PRON). The team also hypothesized to create controllable resistive forces along both axes by utilizing Magneto-Rheological Fluid (MRF) motors. This feature was not deeply studied. NUVABAT allowed for use in stable (footplate locked) mode in sitting or standing and dynamic mode (footplate movable), in sitting position. The schematic of ankle training in sitting position and balance training in standing posture are shown in Figure 20-bottom. Later, a series of pregait, weight shifting and balance control tests were studied by looking into the individual\u2019s center of pressure (COP) in standing position interacting with virtual reality games on the screen [34- 37]. The developed games were unique in design as the COP was derived unilaterally using the measurement from one leg. This is a useful feature for patients with stroke which was absent in other systems with bilateral design (using both legs). While NUVABAT had the advantage of ankle and balance derived measurements, it was not able to provide active controlled force feedback to the patient\u2019s lower extremity" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000914__ists29_12_Pc_9__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000914__ists29_12_Pc_9__pdf-Figure4-1.png", + "caption": "Fig. 4. Behavior of snare wire modeled with a rotation of rod elements.", + "texts": [ + " SSRMS was also modeled base on geometrical data. SSRMS has some number of operation modes and be assumed to change modes in HTV capture operation. Therefore, time-variable force element which simulates a joint stiffness torque and back drive torque is assign to each joint. The joint stiffness torque is applied on both in a manual operation mode and limp mode. On the other hand, the back drive torque is applied only in the limp mode. \u00a9JAXA \u00a9JAXA Pc_11 The snare wires are modeled with rotational rod elements as shown in Fig.4. Contact force functions are applied on between grapple shaft and rod elements and that reaction force is calculated based on differences between angular rotation command value and simulated operation-result value. Details are mentioned in next part. To modeling a vertical reaction force of snare wire, a simple model of the stretched wire which is fixed at both side is introduced into our model (Fig.5). In this model, the wire is deformed by force . The condition of and no slack in wire is set to initial condition" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.9-1.png", + "caption": "Figure 10.9: Solutions to the aerostructural problem with and without considering the weight of the tanks", + "texts": [ + " This example illustrates why it is essential to consider multiple disciplines when evaluating spatial integration tradeoffs. Without optimization, engineers would need to perform laborious 220 analysis and iterate internally to achieve a good result. Using an optimization framework, each of the runs used 400 to 600 core-hours on the HPC (four to six hours wall time each). If the cases run in parallel on an in-house or cloud HPC service, it is easily conceivable that the data for this trade study could be collected and analyzed in one working day. Figure 10.9 illustrates the solution for 2.4 m3 fuel volume (in black). 221 222 While the previous subsections showed a series of successful aerostructural optimization packing cases, I have still neglected a significant effect: hydrogen tank weight. Because of the extreme pressure and low density of the compressed fuel, even a CFRP composite tank will have a hydrogen fuel fraction significantly less than ten percent [279]. The radius and length of the tank will affect its weight significantly. Offline, I set up a structural optimization problem to minimize the weight of a tank made from a bidirectional carbon fiber laminate, considering both axial and hoop stresses 2", + " At 700 bar and 2.35 burst pressure safety factor, using an optimal bidirectional laminate with Toray 1100G prepreg [280], I found that the optimal tank wall thickness is a constant 0.1315 times the tank radius. Therefore, I did not need to explicitly incorporate tank structural analysis into the optimization\u2014only a weight calculation based on tank radius and length. The density of the CFRP material is 1,573 kg/m3. The problem formulation is summarized in Table 10.4. The resulting geometry is visualized in Figure 10.9 (in blue). While the OML only changes subtly at the lower trailing edge, the changes allow the tanks to become much longer and narrower, reducing hoop stress and tank weight. This is a complex tradeoff between the structural weight of a component and the structural weight and drag at the airplane level. It is a good illustration of MDO\u2019s potential to find non-obvious solutions in airplane trade studies rapidly. Figure 10.10 shows the structural sizing variables for this case. Some of the structural zones are minimum gauged, such as the ribs and some spar web zones" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000007_e_download_1546_1132-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000007_e_download_1546_1132-Figure1-1.png", + "caption": "Figure 1. Schematic diagram of the overall structure: a) the overall structure; b) side view; 1) opener blade tip; 2) opener handle; 3) the furrow side pick-up blade curved surface.", + "texts": [ + " The aim of this study is to improve seed-soil contact and develop a furrow side pickup blade based on a chisel-type furrow opener for strip-tillage of wheat in the double-cropping area of wheat and corn in Huanghuaihai. By using the Discrete Element Method (DEM), we established a model for the interaction between soil, straw, and a furrow side pickup blade. This model allowed us to determine the optimal working parameters for the furrow side pickup blade. It provides a feasible technical solution for addressing the issue of seed-soil contact under straw cover. Overall structure and working principle The overall structure of the chisel opener furrow side pick-up blade is shown schematically in Figure 1. The main components of the system include the opener blade tip, the opener handles, and the curved surface of the furrow side pick-up blade. The latter is securely welded to both sides of the opener, ensuring the structural integrity and stability of the system. During the tilling operation, the front end of the furrow side pick-up blade engages the soil level at a specific angle of soil entry. As the opener progresses, the soil located on both sides of the seed furrow is lifted along the curved surface of the furrow side pick-up blade, with the latter gradually inwardly curving front to back", + " The aim of this study is to improve seed-soil contact and develop a furrow side pickup blade based on a chisel-type furrow opener for strip-tillage of wheat in the double-cropping area of wheat and corn in Huanghuaihai. By using the Discrete Element Method (DEM), we established a model for the interaction between soil, straw, and a furrow side pickup blade. This model allowed us to determine the optimal working parameters for the furrow side pickup blade. It provides a feasible technical solution for addressing the issue of seed-soil contact under straw cover. Overall structure and working principle The overall structure of the chisel opener furrow side pick-up blade is shown schematically in Figure 1. The main components of the system include the opener blade tip, the opener handles, and the curved surface of the furrow side pick-up blade. The latter is securely welded to both sides of the opener, ensuring the structural integrity and stability of the system. During the tilling operation, the front end of the furrow side pick-up blade engages the soil level at a specific angle of soil entry. As the opener progresses, the soil located on both sides of the seed furrow is lifted along the curved surface of the furrow side pick-up blade, with the latter gradually inwardly curving front to back" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003075_nf_dts2017_01001.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003075_nf_dts2017_01001.pdf-Figure1-1.png", + "caption": "Fig. 1.The high-pressure hoses type I construction with metallic braidings. Z group: 1 \u2014 hose tube; 2 \u2014 metal braiding; 3 \u2014 squeegee; 4 \u2014 outer rubber layer. A, B, C group: 1 \u2014 hose tube; 2 \u2014 textile braiding; 3 \u2014 metal braiding; 4 \u2014 provisional rubber layer; 5 \u2014 outer rubber layer.", + "texts": [ + " According to GOST 6286-73 [19] the high-pressure hoses depending on the strength of the wire used, must be made in three groups: A, B and B. Group A is manufactured with the use of a wire with a breaking force of not less than 15 kg. Group B is manufactured using a wire with a breaking force of not less than 17.5 kg. Group B is manufactured using a wire with a breaking force of at least 20 kg. Group Z should are made of a lattin wire and a breaking force of at least 20 kg. The high-pressure hoses of each group, depending on the design, can be of two types: Type I- with one metal braiding (fig. 1) Type II- with two metal braiding (fig. 2) In the HPH, the first layer (the inner rubber hose chamber), which is firmly connected to the frame, receives a radially directed hydrostatic pressure (\ufffd\ufffd) applied to the surface of radius (\ufffd\ufffd). On the outer surface of the chamber of radius (\ufffd\ufffd), there is a pressure (\ufffd\ufffd) arising from the action of the frame. The rubber chamber is formed from a material with a Poisson's ratio close to 0.5 [4]. The second frame ply, along its inner surface of radius (\ufffd\ufffd), experiences a radially directed hydrostatic pressure (\ufffd\ufffd)", + " 3 Analysis According to GOST 6286-73 [19] the high-pressure hoses depending on the strength of the wire used, must be made in three groups: A, B and B. Group A is manufactured with the use of a wire with a breaking force of not less than 15 kg. Group B is manufactured using a wire with a breaking force of not less than 17.5 kg. Group B is manufactured using a wire with a breaking force of at least 20 kg. Group Z should are made of a lattin wire and a breaking force of at least 20 kg. The high-pressure hoses of each group, depending on the design, can be of two types: Type I- with one metal braiding (fig. 1) Fig. 1.The high-pressure hoses type I construction with metallic braidings. Z group: 1 \u2014 hose tube; 2 \u2014 metal braiding; 3 \u2014 squeegee; 4 \u2014 outer rubber layer. A, B, C group: 1 \u2014 hose tube; 2 \u2014 textile braiding; 3 \u2014 metal braiding; 4 \u2014 provisional rubber layer; 5 \u2014 outer rubber layer. Type II- with two metal braiding (fig. 2) Fig. 2. The high-pressure hoses type II construction with metallic braidings. Z group: 1 \u2014 hose tube; 2 \u2014 metal braiding; 3 \u2014 squeegee; 4 \u2014 outer rubber layer. A, B, C group: 1 \u2014 hose tube; 2 \u2014 textile braiding; 3 \u2014 metal braiding; 4 \u2014 provisional rubber layer; 5 \u2014 outer rubber layer" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004078_f_version_1570787418-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004078_f_version_1570787418-Figure2-1.png", + "caption": "Figure 2. Intuitive scheme of y-to x-polarization conversion of the metasurface unit.", + "texts": [ + " The waves undergo multiple reflections between the PCM and the metallic sheet layer, and the final reflected waves are a result of the mutual interference of waves. Therefore, the thickness of the dielectric layer can be utilized to control the phase and amplitude of the final reflected waves. To better understand the response of the PCM, we consider that the incident plane wave is polarized along the y-axis. Thus, the electric field can be decomposed into two perpendicular components u and v, as seen in Figure 2. Hence, the electric field of the incident plane wave can be expressed as \u2192 Er = r\u0303u \u2192 uEiue j\u03d5 + r\u0303v \u2192 v Eive j\u03d5 (1) and the electric field of the reflected wave can be written as \u2192 Er = r\u0303u \u2192 uEiue j\u03d5 + r\u0303v \u2192 v Eive j\u03d5 (2) In which r\u0303u and r\u0303v are the reflection coefficients along the u-and v-axes, respectively. Owing to the anisotropic characteristic of the PCM, a phase difference \u2206\u03d5 can be generated between r\u0303u and r\u0303v. when \u2206\u03d5 \u2248 \u03c0 and the modulus satisfy ru \u2248 rv, the synthetic field for Eru and Erv will be along with the x-direction, as shown in Figure 2, and the incident polarization is rotated by 90\u25e6. In fact, the double-V-shaped structure supports symmetric and anti-symmetric modes, which are excited by electric field components along the v- and u-axes, and the cut-wire structure supports multi-order dipolar resonances which are excited by electric field components along the v-axis. We predict the presence of multiple resonances for the composited structure. To numerically inverstigate the performance of our design, the reflection amplitude and phase of the unit have been simulated in CST Microwave Studio, see in Figure 3", + " Here, E denotes the electric field; the subscripts i and r indicate the incidence and reflection of electromagnetic wave (EM) waves, respectively; and the subscripts x and y denote the polarization directions of EM waves, respectively. By using the commercial software CST Microwave Studio, we can investigate the polarization conversion ability of the proposed polarization converter by simulating the reflection coefficients ryy and rxy. In the simulation, a single unit cell with periodic boundary conditions along the x- and y-directions are used to simulate ryy and rxy. The EM wave impinging on the unit is in the xy-plane, with a transverse electric polarization (i.e., E is along the y-axis, as shown in Figure 2). The cross-polarization rxy (ryx) and co-polarization rxx (ryy) of the unit under normal incident wave are shown in Figure 3. The cross-polarization reflection coefficients rxy (ryx) are close to 1 (0 dB) in UWB, which indicates that the polarization conversion can be realized under the normal incidence for both x- and y-polarization [24]. The UWB polarization conversion is resulted from its four resonant frequencies at 14.4 GHz, 20.1 GHz, 34.1 GHz and 45.5 GHz, and the polarization conversion efficiency is roughly 100% (see in Figure 3)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001786_3-540-69389-5_68.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001786_3-540-69389-5_68.pdf-Figure9-1.png", + "caption": "Fig. 9. Graph grammar production for actual breaking of an element edge", + "texts": [], + "surrounding_texts": [ + "We conclude the presentation with the sequence of triangular finite element meshes generated for the L-shape domain model problem [6]. The problem consists in solving the Laplace equation \u0394u = 0 in \u03a9 (1) over the L-shape domain \u03a9 presented in Fig. 13. The zero Dirichlet boundary condition u = 0 on \u0393D (2) is assumed on the internal part of the boundary \u0393D. The Neumann boundary condition \u2202u \u2202n = g on \u0393N (3) is assumed on the external part of the boundary \u0393N . The temperature gradient in the direction normal to the boundary is defined in the radial system of coordinates with the origin located in the central point of the L-shape domain. g (r, \u03b8) = r 2 3 sin 2 3 ( \u03b8 + \u03c0 2 ) . (4) The solution u : R2 \u2283 \u03a9 u \u2192 R is a temperature distribution inside the L-shape domain. The initial mesh consists in six triangular finite elements, presented on the first panel in Fig. 13. The self-adaptive hp-FEM code generates a sequence of meshes delivering exponential convergence of the numerical error with respect to the problem size. The initial mesh, the second mesh, the optimal mesh delivering less then 5% relative error accuracy of the solution, and the solution over the optimal mesh are presented in Fig. 13." + ] + }, + { + "image_filename": "designv8_17_0002340_e_download_1266_1009-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002340_e_download_1266_1009-Figure2-1.png", + "caption": "Figure. 2. Coulomb Gap", + "texts": [], + "surrounding_texts": [ + "Pradesh, India. E-mail: vidhate.a.d@gmail.com." + ] + }, + { + "image_filename": "designv8_17_0001232_f_d2me2017_02004.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001232_f_d2me2017_02004.pdf-Figure6-1.png", + "caption": "Figure 6. Rotational assembly", + "texts": [ + "3 Platform of balance-arm and balance-weight D2ME 2017 The platform (shown as Figure 4) is box-type structure. The luffing mechanism of balance-arm installed on the platform generates the backward torque with weight block under platform together. The head is latticed structure located in the center of rotational support. There is a limit putter on the head to avoid the impact of lifting-arm and balance-arm. The rotational assembly is shown as in Figure 5. The rotational upper support is shown in Figure 6, and the hinged joint of lifting-arm end is arranged on the edge of rotational support. The slewing gear and jib lubbing mechanism is on the support. To verify that the structure designed meets the strength requirement, the balance-arm and crane head are calculated here. The rotational support is small changed compared with the traditional type, so not check[7]. 3.1 Balance-arm MATEC Web of Conferences 136, 02004 (2017) DOI: 10.1051/matecconf/201713602004 D2ME 2017 MATEC Web of Conferences The loads on the balance-arm include the weight of counter, platform, luffing mechanism, balance-arm, the wind load and the tension of wire rope" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004367_5_phys-2022-0223_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004367_5_phys-2022-0223_pdf-Figure2-1.png", + "caption": "Figure 2: Two-dimensional topology map and three-dimensional cross-sectional view of the motor.", + "texts": [ + "csk 1 (7) A six-slot four-pole permanent magnet motor is used for verification. This motor uses a bonded magnetic ring as a permanent magnet rotor. Bonded magnets can be classified into isotropic bonded magnets and anisotropic bonded magnets. Anisotropic bonded magnets are gradually being used in various micro-motors due to their high magnetic properties [30]. The magnetic rings used in this article are radially oriented anisotropic bonded magnetic rings. The two-dimensional topology and three-dimensional cross-section of the motor used in this article are shown in Figure 2. The specifications for the motor are listed in Table 1. The motor is modeled in finite element simulation software, and the 3D model specifications used in the simulation are consistent with the actual motor specifications. As shown in Figure 3, (a) is the 3D simulation model, (b) is the disassembled diagram of themodelmotor. In the simulation, the inclination angle range \u03b8sk of the trapezoidal magnetic pole structure is 0\u201350\u00b0, with a step size of 10\u00b0. When \u03b8sk varies from 0\u201350\u00b0, the cogging torque changes as shown in Figure 4 below" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001040_77_aoje_2_021025.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001040_77_aoje_2_021025.pdf-Figure18-1.png", + "caption": "Fig. 18 Free body diagram for part of the surface above the ith hinge. Torques about a hinge in the surface include the internal torques from the vacuum curling bladder and the external torques from external loads including the tile self-weight.", + "texts": [ + " With known tile geometries, the surface curling shape can be obtained by incrementally rotating a tile by its curling angle \u03b8 at the local tile unit around its hinge, and an orientation angle \u03c6 of this tile with respect to the first tile (usually fixed horizontally) is equal to the sum of the curling angle at previous hinges: \u03c6i = \u2211i j=1 \u03b8j (28) where the orientation angle of the last tile \u03c6n may be used as a measure of total surface curling. Torque equilibrium at each hinge is analyzed using the free body diagram divided at the ith hinge (i= 1, 2,\u2026n) on the free end of the remaining tiles in Fig. 18. Torques about the hinge balance between the internal torques from the unit curling model Tcur,i (Eqs. (24) and (25)) and other torques from external loads Text,i. Each torque equilibrium is used to form the surface model and is expressed at the ith hinge as follows: \u03b8i < \u03b8max Tcur,i = Text,i { before hard stop (29) \u03b8i = \u03b8max Tcur,i \u2265 Text,i { after the hard stop is reached (30) where the maximum curling angle \u03b8max= \u03c0\u2212 2\u03d5 is limited by the hard stop chamfer angle \u03d5. At the fully curled position after the hard stop is reached, the curling torques in excess of the external torques are blocked by the chamfered tile edges", + "05 is the drag coefficient for a uniform flow perpendicular to a long flat plate [49], \u03c1 is density of the air, U is the flow speed, and A= Lhi is the area facing the flow, where hi is the sum of the tile vertical height above the ith hinge: hi =Wt \u2211n j=i sin\u03c6j (32) The torque from the drag force about the hinge is given as follows: Td,i = 1 2 Fd,i \u00b7 hi (33) Other externally applied loads such as snowfall and fallen debris on the cowling can be distributed or concentrated weight applied over or at a specific position on the surface. A cantilevered concentrated end load produced by hanging a weight we on the last tile of the surface provides an extreme yet controllable case of these externally applied loads and is used in the surface model validation, where Twe ,i = we \u00b7 12 \u2211n i Wt cos\u03c6i (34) The self-weight of each tile wt also resists curling (Fig. 18) with a total torque at the ith hinge of Twt ,i = \u2211n i wt \u00b7 12 \u2211n j=i Wt cos\u03c6j (35) Given the form of load, the surface model is solved numerically to satisfy equilibrium and find the curling angles at each hinge. The surface model enables the prediction of the surface curling shape under an external load as a function of the geometric parameters (H, W, Wt, and Wg) and the actuation vacuum pressure \u0394p. ASME Open Journal of Engineering 2023, Vol. 2 / 021025-13 nloaded from http://asm edigitalcollection" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003554__AME_2021_138393.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003554__AME_2021_138393.pdf-Figure1-1.png", + "caption": "Fig. 1. Construction of the personal rescue winch: 1 \u2013 ratchet; 1a \u2013 pawl; 2a, 2b \u2013 friction surfaces; 3, 5 \u2013 pinions; 4, 6 \u2013 gears; 4a \u2013 intermediate shaft; 5a \u2013 input shaft; 5b \u2013 handwheel; 7 \u2013 rope drum; 8 \u2013 adjustment ring; 9 \u2013 screw shaft; 10a, 10b \u2013 housing", + "texts": [ + " Therefore, the risks of insecurity caused by fire and explosion are increasing, leading to serious damage if no timely response is taken. Research and development of personal rescue equipment for people living there, with which they can equip themselves and escape, are particularly effective for zones inaccessible by professional equipment and firefighters. Based on analysis and evaluation of the rescue solutions in [1, 2] and self-climbing system in [3], the research team proposed one personal rescue winch, as shown in Fig. 1 [4]. The rescue winch\u2019s construction includes the handwheel, the gear train, the screw shaft, the rope drum, the lifting rope, the winch housing, the safety brake, B Van Tinh Nguyen, e-mail: tinhnv@nuce.edu.vn 1Faculty of Mechanical Engineering, National University of Civil Engineering, Hanoi, Vietnam 0 \u00a9 2021. The Author(s). This is an open-access article distributed under the terms of the Creative Commons AttributionNonCommercial-NoDerivatives License (CCBY-NC-ND4.0, https://creativecommons.org/licenses/by-nc-nd/4", + " They are divided into two groups. The first one is seven variables that our proposed algorithm can optimize, and Matlab software is a tool to solve this problem. They consist of the modules, the tooth numbers, and the face widths. The other is four variables manually optimized with the help of structural analysis software such as Ansys. These include the hole diameters and hole numbers on the gears. Besides, the material replacement for the gear and pinion webs is also made to optimize the weight. Gear pair 3-4 and 5-6 in Fig. 1 are spur gear train (helix angle \u03b2 = 0, pressure angle \u03b1 = 20\u25e6). The gear structure in the transmission is selected as shown in Fig. 2, its parameters and design data are set up for Table 1. The gear ratio of the system must be ensured so that the handwheel drive 5b is suitable for the driving force of one average person. i = Mx4 Mq \u03b734 \u03b756 = i34 i56 , (1) where Mx4 is the torque in the shaft for which gear 4 is fitted, Mq is the torque rotated by the operator and \u03b734, \u03b756 are efficiency of gear driver 3-4 and 5-6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000540_r.asee.org_12263.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000540_r.asee.org_12263.pdf-Figure2-1.png", + "caption": "Figure 2 Belt Drive Main Menu", + "texts": [ + " Also the software shows how all calculations are done so students understand what the software is doing. The following sections will describe some of the different programs and how they are being used. II. Belt Drive Analysis Program This program has the students learn how to size and select a belt drive system. A belt drive system1 consists of two pulleys, two bushings, two keys, and a belt as shown in figure 1. Belt drive systems are used to transmit power from one source to another. The program starts with the main menu shown in figure 2. The main menu has six options the student can select from. The first option is the student can select is the Pulley Specifications command button. This shows the different specifications of the pulleys. Synchronized belt drives can have either P age 8.1244.2 Proceedings of the 2003 American Society for Engineering Education Annual Conference & Exposition Copyright p 2003, American Society for Engineering Education English or metric belt pitches. This program covers the metric pulleys and belts" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004178_.pdf_c_1606268078000-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004178_.pdf_c_1606268078000-Figure2-1.png", + "caption": "Figure 2 The basic transmission characteristics of continuously variable noncircular gear transmission", + "texts": [ + " is the phase angle between gear 1 and gear 2, and t is maximum rotational angle at working section in a period; k and b represent the slope value and the intercept value of linear function respectively. By designing the double-row 2K-H type epicyclical gear train with specific number of teeth, the following relation can be achieved: 61 1 1 1 2 2 2m m k b n k b c (3) When a fixed speed is inputted by shaft 1, shaft 6 will output a constant speed, and the rotation speed of each level in gear transmission system are shown in Figure.2. As shown in Figure. 2, continuously variable velocity is realized at phase angle by using the second-order noncircular gear pair. The constant rotation speed can be outputted by output shaft 6, as the phase angle between two noncircular gear pairs is . And the wider range of constant rotation speed output is achieved during each period with decreased phase angle . 2.2 Transmission Ratio of Noncircular Gear in Non- working Section Obviously, the pitch curve of noncircular gear is different at two sections during a period, that is, the transmission ratio is in the form of a linear function in working section or that presents a complex curve in non-working section", + " His research interests include the development of the new type of gear transmission, fundamental study of curve-face gear, and surface topography of non-circular gear. E-mail: 20160702017@cqu.edu.cn Zhi-Qin Cai, born in 1988, is a lecturer at the School of Aeronautics and Astronautics, Xiamen University. He received his PhD in mechanical engineering from Chongqing University. His research interests include intelligent design of precision gear driven by shape coupling, micro-texture of tooth surface, and energy-saving transmission design. E-mail: caizhiqin@xmu.edu.cn Figures Figure 1 Continuously variable noncircular gear transmission Figure 2 The basic transmission characteristics of continuously variable noncircular gear transmission a) Gear velocity at all levels in continuously variable noncircular gear transmission (b) The transmission ratio of each level in continuously variable noncircular gear transmission Figure 3 The in uence of 1 b on transmission ratio of noncircular gear pair Figure 4 The in uences of 1 k on transmission ratio of noncircular gear pair Figure 5 Comparisons of transmission ratio and centrode of noncircular gear pairs with different transmission ratio parameters Figure 6 The in uence of zero modi cation on the contact ratio of noncircular gear Figure 7 The in uence of each parameter on the contact ratio (a) The in uence of the modi cation coe cient and tooth pro le angle of the rack cutter on the contact ratio (b) The in uence of module on the contact ratio Figure 8 The in uence of transmission ratio coe cient on contact ratio Figure 9 The analytical diagram of tooth pro le of driving gear Figure 10 The analytical diagram of meshing curve of noncircular gear pair Figure 11 The theoretical results of some meshing curves of noncircular gear pair by MATLAB Figure 12 The analytical diagram of contact pro le of driving gear and the addendum curve of driven gear Figure 13 The 2# theoretical contact tooth pro le of driving gear by MATLAB Figure 14 The tooth pro le curve of noncircular gear pair with MATLAB (a) Tooth pro le curve of driving gear (b) Tooth pro le curve of driven gear Figure 15 The experimental test platform of the noncircular gear transmission Figure 16 The length of contact pro le of driving gear Figure 17 The transmission ratio and contact pro le length of the driving gea" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004992_O201217653783682.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004992_O201217653783682.pdf-Figure16-1.png", + "caption": "Fig. 16. Magnetic flux distribution of proposed", + "texts": [ + " The yoke thicknesses ys, yr and rotor pole height hr can be calculated after choosing design ratios \u03b1ysts, \u03b1yrtr, \u03b1hrtr and pole arc enclosures of the stator and rotor. Therefore, shaft radius can be described as follows: rrgsh yhRR (29) when Rout, Rg and ys are known, hs can be obtained as following equation: sgouts yRgRh (30) BLSRM In this section characteristics of the proposed structure are analyzed, including magnetic flux distribution, inductance, torque and radial force vs. position. Meanwhile in order to verify the advantages of the proposed method, conventional structure is also analyzed. Fig. 16 shows magnetic flux distribution of torque winding and radial force winding. BLSRM Magnetic flux generated by radial force winding mainly goes through poles of radial force winding. A few numbers of fluxes go through poles of torque windings. However because of symmetric structure, forces on the poles of torque windings are counterbalanced. In Fig. 16(b) the path of magnetic flux is same to that of a conventional SRM. The torque characteristics are dependent on the relationship between flux-linkage and rotor position as a function of current. The developed torque is proportional to the square of the current and slope of inductance. Fig. 17 shows the inductance profiles for torque winding and radial force winding with various rotor positions and currents, respectively. From Fig. 17 it can be seen that core saturation increases with the increasing of phase current, accordingly maximum inductances of two types of windings decrease" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004908_24_TSP_CMC_27124.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004908_24_TSP_CMC_27124.pdf-Figure5-1.png", + "caption": "Figure 5: Antenna array structure", + "texts": [ + " The linear polarization perpendicular to the waveguide direction is transformed into the outward radiation of circular polarization wave to change the difference between the two vertical polarization components. The amplitude components of the two modes are controlled by adjusting the rotation angle of the polarization waveguide. Reasonable design of the size and height of the polarization waveguide and the rotation angle of the polarization waveguide can make the amplitude of the two modes TE10 and TE01 equal and the phase difference 90\u00b0, meeting the necessary conditions for realizing circular polarization. As shown in Fig. 5, the antenna array adopts the microstrip antenna array. The antenna consists of two K-band circularly polarized antenna units, and the spacing between the two units is 9.5 mm, which is fed by a K-band T/R module. In order to study the performance of the pattern in the case of the research group, the 2-unit structure is established as shown in the following figure. The spacing between the two units is set to 9.5 mm, as shown in Fig. 5. The port standing wave can meet the bandwidth of 24.5\u201328 GHz less than 1.6, and has good broadband performance. In order to achieve broadband operation, the circular polarization is realized by adjusting the height of the four-ridge open horn and the height of the ridge. The width and length of the multimode waveguide cavity, the height and length of the coaxial-waveguide conversion structure, and the length and width of the coupling gap feed are adjusted to achieve broadband operation. The optimized unit standing wave is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.13-1.png", + "caption": "Figure 1.13. Oldsmobile SLA IFS [2].", + "texts": [ + " The first production car to have an IFS was the Decauville, circa 1898, which used a sliding pillar IFS. A drawing of this type is seen in Figure 1.11. Another early independent suspension approach was the swing axle. This amounted to allowing each \u201chalf\u201d of the axle to swing independently, Figure 1.12. Some designs of this type were even employed as rear suspensions, and used the drive axle as one of the arms. The design favored by GM was the double wishbone, also known as the short-long-arm (SLA), seen in Figure 1.13. In addition to leaf springs and coil springs, torsion springs were also in use. An example can be seen in Figure 1.14. In this figure, there is also a hydraulic shock absorber. As the century went along, the MacPherson strut suspension, Figure 1.15, introduced in the late 1940s, became an increasingly popular IFS. This was due to its relatively few number of components, especially when the spring is placed over the strut, and its ability to provide a steer DOF. The rack and pinion steering system, seen in Figure 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure3.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure3.8-1.png", + "caption": "Figure 3.8: Real-time spectrum analyzer (RTSA) scheme using leaky-wave antenna [182]", + "texts": [ + " However, the array antennas need relatively larger dimension to ensure high gain. Moreover, as the dimension of the array increases, the number of phase-shifters makes the antenna very expensive and complicated to manufacture. Leakywave antennas then become good candidates for such applications. In [182], using the frequency beam scanning characteristics of a leaky-wave antenna, a microwave analog real-time spectrum analyzer (RTSA) is implemented to analyze transient complex non-stationary signals (figure 3.8). In recent years, ultra-wideband (UWB) systems have rapidly emerged in the domains of radar, security and EMC (Electromagnetic compatibility). These systems typically use ultra-fast transient signals with rapid spectral variations in time. In order to characterize these transient signals, real-time time-frequency display is required to obtain simultaneously time and spectral information, where the signal energy distribution can be color-coded at each time-frequency point [183]. At microwaves, RTSAs are typically based on digital short-time Fourier transform (STFT) [182]", + " For UWB signals with ultra-fast transients, high time-resolution STFT requires small sampling durations, which results in long acquisition times. Therefore, the STFT process requires a large amount of computing and memory resources, which can severely affects the RTSA system functionalities and limits its performance to UWB systems. The leaky-wave antenna based RTSA uses the spectral-spatial feature of the antenna. Since the leaky-wave antenna may have large bandwidth frequency-scanning characteristic, probes can be angular-separately mounted at different far field positions, as shown in figure 3.8, to easily measure the power variation of the corresponding frequency in real-time. The measurement results are then sent to the post-processing unity for data processing and display. Compared to digital RTSAs, the leaky-wave antenna based RTSA has the advantage of instantaneous acquisition, low computational cost, frequency scalability, and wideband operation. The forthcoming fifth-generation (5G) mobile cellular communications technology is considered to be a \u201ckey technology\u201d that connects everything in modern society" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure12-1.png", + "caption": "Figure 12 Side Panel Vent Hole with Mesh.", + "texts": [ + " These options include a conductive mesh installed over a hole, or an array of small holes specifically sized and spaced such that they do not allow EMI/RFI to pass through. One possible method to accomplish this was to implement a conductive mesh over a large vent hole. A conductive mesh, similar to one employed in the door of a microwave, is effective in shielding RFI/EMI if properly sized for a specific frequency. Page 15 The traditional location of a vent hole is on the ribs of the side panel, where no mounting hole is present. An example of this vent hole with mesh is shown below in Figure 12. Unfortunately, the mesh interferes with the ventable area of the hole, necessitating a larger total area. Because of limitations on positioning due to fasteners through the Side Panel, this could not be accomplished by just increasing the hole size, but required the addition of multiple holes. Having multiple venting holes imposes limitations on mounting hole locations, and also requires a great deal of install time in order to affix multiple meshes to the side panels. Additionally, with so many meshes attached to the PPOD, it is difficult to keep track of all of them, making P-POD handling more difficult, and increasing the risk of damaging one of the meshes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure4-1.png", + "caption": "Figure 4. Schematic diagram of axial cooling slots.", + "texts": [ + " As can be seen from Figure 2, the casing is double-layer, and the cooling water channels are manufactured between the two layers of the casing. The cooling water channels are eight circular channels with tops or bottoms connected, and both the inlet and the outlet of channels are distributed at the top of the casing. Figure 3 is a schematic diagram of the water flow in the water channels. It indicates that the water cooling system is symmetrical about the longitudinal section including the inlet and outlet. In the inner rotor, there are six axial cooling slots along circumferential direction, as shown in Figure 4. They can provide a cooling wind path. On one machine side, an external fan is used to provide the force air. From the above illustration of the cooling system and mechanical structure of the CS-PMSM prototype, we know that when the cooling water with a certain pressure flows through the cooling water channels of the casing, there must be a temperature difference generated in both the axial and circumferential directions of the CS-PMSM. Besides, a temperature difference along the axial direction also exists when one side of the machine is cooled by the fan" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000951_f_version_1592539735-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000951_f_version_1592539735-Figure16-1.png", + "caption": "Figure 16. The structures of the PSC pair with different matching materials: (a) PSC pair with 316LGIC and PEEK-30CF; (b) PSC pair with 316L-GIC and 316L-GIC.", + "texts": [ + " In addition to the abrasion performance, leakage performance is another important indicator. Especially under HWBHL lubrication, the leakage in friction pairs is always a severe problem. Many factors (such as structure parameters, working pressure, temperature, material properties, etc.) would affect the leakage in the PSC pair. There might exist complex interact effect among the factors [35,36]. To analysis the coupling influences of factors (including clearance, temperature, and working pressure) on leakage performance for the two kinds of matching materials as shown in Figure 16, the bidirectional fluid-structure coupling analysis is applied. Because the influence of working speed is very small, it will not be considered in this study. (a) (b) Figure 16. The structures of the PSC pair with different matching materials: (a) PSC pair with 316LGIC and PEEK-30CF; (b) PSC pair with 316L-GIC and 316L-GIC. of fluid-structure coupling analysis was implemented through commercial software ANSYS 15.0. The simulation was conducted by the combination of a Fluent module and Transient Structure module. There are two pairs of coupling surfaces: one is the outside coupling surface on the lubrication film and coupling part on the cylinder, the other is inside the coupling surface on the lubrication film and ", + " In addition to the abrasion performance, leakage performance is another important indicator. Especially under HWBHL lubrication, the leakage in friction pairs is always a severe problem. Many factors (such as structure parameters, working pressure, temperature, material properties, etc.) would affect the leakage in the PSC pair. There might exist complex interact effect among the factors [35,36]. To analysis the coupling influences of factors (including clearance, temperature, and working pressure) on leakage performance for the two kinds of matching materials as shown in Figure 16, the bidirectional fluid-structure coupling analysis is applied. Because the influence of working speed is very small, it will not be considered in this study. Energies 2020, 13, x FOR PEER REVIEW 12 of 19 (a) (b) Figure 15. Friction coefficient of 316L-GIC with 316L-GIC under different test speeds: (a) Variation curve of friction coefficient at 15 r/min; (b) Variation curve of friction coefficient at 90 r/min. Due to the running-in between the pin specimen and disk specimen being conducive to reducing the surface roughness of PEEK-30CF, the friction coefficient of hard-to-soft matching materials 316L- GIC and PEEK-30CF decreases over time at test speeds 15 rpm and 90 rpm, while for hard-to-hard matching materials 316L-GIC/316L-GIC, the friction coefficient is more stable during the 10 h abrasion test", + " In addition to the abrasion performance, leakage performance is another i orta t i icator. s ecially er l bricatio , t e lea a e i frictio airs is al a s a severe proble . a factors (s c as str ct re ara eters, or i ress re, te erat re, aterial ro erties, etc.) o l affect t e lea a e i t e PSC pair. There might exist complex interact effect among the factors [35,36]. To analysis the coupling influences of factors (including clearance, temperature, and orki ress re) leakage performance for the two kinds of matching materials as shown in Figure 16, the bidirectional fluid-structure coupling analysis is applied. Because the influence of working speed is very small, it will not be considere in this study. of fluid-structure coupling analysis was implemented through commercial software ANSYS 15.0. The simulation was conducted by the combination of a Fluent module and Transient Structure module. There are two pairs of coupling surfaces: one is the outside coupling surface on the lubrication film and coupling part on the cylinder, the other is inside the coupling surface on the lubrication film and 16" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000044__2015jamdsm0037__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000044__2015jamdsm0037__pdf-Figure3-1.png", + "caption": "Fig. 3. Vector transformations", + "texts": [ + " Therefore, vectors between the points HG, GW, and WJ are required (Fig. 2). In this study, \u201cstatic position\u201d of the suspension system presents the position where both wheel t ravel and steering angle is equal to zero. The static position is presented by subscript \u201c 0\u201d. At static position, rotation axis of the hub must be on XZ plane. Thus, at the static position of the suspension system, unit vector o f the hub (GW) can be determined as: \ud835\udc52hub0 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7 = [cos \ud835\udf000 0 \u2212 sin\ud835\udf000] \ud835\udc47 (11) where \ud835\udf000 is the positive static camber position of wheel (Fig. 3(a)). The static position of wheel center can be determined from: \ud835\udc59hubt0 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7 = \ud835\udc500 [0 \u22121 0]\ud835\udc47 + \ud835\udc59hub\ud835\udc52hub0 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7 (12) 5 \u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2015jamdsm0037] In order to obtain any position of the vectors which are on the knuckle, rotation matrices can be used and the following procedure can be employed. Caster offset GH, hub GW, and steering arm ED are on the same rig id body (parts of the knuckle) thus, all of the unit vectors on this body will have the same rotation during motion of the suspension", + " Here, rotation of the knuckle is considered to be superposition of two d ifferent rotations. Init ially, rotation of the knuckle about its own axis is disregarded. Since the unit vector \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 is calculated from Eq. (5) for every position of the mechanis m (for every ), the amount of rotation of \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 can be determined from cross product as: \ud835\udf06 = sin\u22121[(\ud835\udc52k0 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7 \u00d7 \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 ) \u2219 \ud835\udc52k\u03bb \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7] (13) where \ud835\udc52k \u03bb \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7 is the rotation axis which is perpendicu lar to the plane constituted by \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 and \ud835\udc52k0 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7 as seen in Fig. 3(b), and it is determined as: \ud835\udc52k\u03bb \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7 = (\ud835\udc52k0 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7 \u00d7 \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 ) |\ud835\udc52k0 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7 \u00d7 \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 |\u2044 Since, \ud835\udc52a\u20d1\u20d1\u20d1\u20d7 is fixed on \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 , after obtaining the amount of rotation \ud835\udf06, \ud835\udc52a0\u03bb \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d7 is also determined as seen in Fig. 3(b). The second rotation required to complete the analysis is the rotation of knuckle about the unit vector \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 , which can be determined from Fig. 3(c) as: \ud835\udf06p = sin\u22121[(\ud835\udc52a0\u03bb \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d7 \u00d7 \ud835\udc52a\u20d1\u20d1\u20d1\u20d7 ) \u2219 \ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 ] (14) The rotation matrix about an axis in the direction of unit vector ?\u20d1\u20d7?, by an angle of is: \ud835\udc45(?\u20d1\u20d7?, \ud835\udf03) = [ cos \ud835\udf03 + \ud835\udc62x 2(1 \u2212 cos \ud835\udf03) \ud835\udc62x\ud835\udc62y (1 \u2212 cos \ud835\udf03) \u2212 \ud835\udc62z sin \ud835\udf03 \ud835\udc62x\ud835\udc62z (1 \u2212 cos \ud835\udf03) + \ud835\udc62y sin\ud835\udf03 \ud835\udc62y\ud835\udc62x (1 \u2212 cos\ud835\udf03) + \ud835\udc62z sin\ud835\udf03 cos\ud835\udf03 + \ud835\udc62y 2(1 \u2212 cos \ud835\udf03) \ud835\udc62y\ud835\udc62z (1 \u2212 cos \ud835\udf03) \u2212 \ud835\udc62x sin\ud835\udf03 \ud835\udc62z\ud835\udc62x (1 \u2212 cos \ud835\udf03) \u2212 \ud835\udc62y sin\ud835\udf03 \ud835\udc62z\ud835\udc62y (1 \u2212 cos \ud835\udf03) + \ud835\udc62x sin \ud835\udf03 cos \ud835\udf03 + \ud835\udc62z 2(1 \u2212 cos \ud835\udf03) ] Since we obtained the associated rotation matrices, the unit vector \ud835\udc52hub\u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1 \u20d7 from its in itial position (\ud835\udc52hub0\u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7) to any current position can be determined as: \ud835\udc52hub\u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1 \u20d7 = \ud835\udc45(\ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 , \ud835\udf06p) \ud835\udc45(\ud835\udc52k\u03bb \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7, \ud835\udf06) \ud835\udc52hub0 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7 (15) Similarly, using the same rotation matrices any position of the wheel hub can be determined as: \ud835\udc52hubt\u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d7 = \ud835\udc45(\ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 , \ud835\udf06p)\ud835\udc45(\ud835\udc52k\u03bb \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7, \ud835\udf06)\ud835\udc52hubt0 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d7 (16) 6 \u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003767_le_download_2174_940-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003767_le_download_2174_940-Figure8-1.png", + "caption": "Fig. 8. Last Gripper Model.", + "texts": [ + " The base speed was set at 40 mm/s, where a percentage of 50 would imply a speed of 20 mm/s. Using these parameters, small beads were printed as shown in the Fig. 7. These were used to visually assess the print quality. From this DOE a printing speed of 40mm/s, an infill of 38% and a printing temperature of 203 \u00b0C was selected as the one producing the best print quality through visual inspection. This prompted the printing of the first gripper prototype. A gripper model was designed in Autodesk 360. It had two fingers with grooves to enable better gripping of an object as shown in Fig. 8. A scaled down model prototype of the gripper was printed to assess the print quality and functionality, but a stringing effect was encountered. As observed in Fig. 9, string-like structures formed when the printer\u2019s nozzle travelled from one finger to the next. These lowered the print quality and increased the post processing time of the print work. Melted filament still oozed out when the nozzle made a travel movement between the fingers, as in Fig. 10 (a), which was the cause of the stringing effect" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004599_(5)_2017_549-562.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004599_(5)_2017_549-562.pdf-Figure2-1.png", + "caption": "Figure 2. Exemplary basic vehicle layout.", + "texts": [ + " This is a challenging task since various partially contradictory requirements have to be considered during the architecture definition process. Fig. 1 shows an excerpt of common requirements onto a vehicle concept. This leads to a conflicting situation amongst the different influencing parties and requires the target-oriented search for the best compromise regarding desired technical properties of the vehicle. The initial step in conceptual development is building up a so-called layout model, in order to evaluate the basic geometric correlations within the emerging concept. Fig. 2 illustrates a typical 3D vehicle layout at an early development stage. It contains the general outer and inner vehicle main dimensions, including simplified ergonomical representations of driver and passengers. In order to retrieve an overview of the spatial situation, proportional parametric Figure 1. General requirements in vehicle development. models can be used to estimate the extensions of required space for specific technical components considering their geometrical requirements and the interaction with an initial car body design" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003249_O200932056740446.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003249_O200932056740446.pdf-Figure3-1.png", + "caption": "Fig. 3. Configuration of IPMSM with experimental devices.", + "texts": [ + " The body force at the nodes can be evaluated as { } [ ] { }( ) Te V f N X dV= \u222b\u222b\u222b (11) { } b b X X Y \u23a7 \u23ab = \u23a8 \u23ac \u23a9 \u23ad (12) eb xX 2\u03c1\u03c9= , eb yY 2\u03c1\u03c9= Where Xb and Yb are the weight densities in the x and y directions, respectively, and \u03c1 is mass density, and \u03c9 is angular velocity, and xe and ye are the center of element in the x and y directions, respectively. To verify the stress analysis method, an IPMSM with a 4-pole prototype machine having four layers was selected. The specification of the prototype is shown in Table 1. Fig. 3 shows the structure of the IPMSM and its experimental devices. In the rotor structure, permanent magnets were partially inserted into each layer to obtain the sinusoidal back-EMF waveform. The shape and length of each layer was designed to enhance the inductance difference. The material which was used is nonoriented silicon steel (S18) suitable for a rotating electrical machine. Its yield strength is 300 [MPa]. The IPMSM was operated at 18000 [rpm] with intent to break the rotor core structure in order to study the effect of mechanical stress" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004585_5_secm-2016-0335_pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004585_5_secm-2016-0335_pdf-Figure5-1.png", + "caption": "Figure 5: Meshed composite leaf spring model.", + "texts": [ + " Many elements can be used for different problems in Abaqus. Continuum, shell, beam, rigid, and membrane elements are the commonly used ones. C3D8R elements were selected firstly as the element type in reference to the proposals of Abaqus documentation and literature studies [24, 28, 29]. In addition, they gave accurate results after a validation study was performed. These elements provide an advantage especially in the hybrid composite modeling including various plies of different materials, as they can comprise different material properties. Figure 5 shows the completed mesh in the model. The boundary conditions and the load applied were determined by taking into consideration the upper limit value of the mechanical loads that take place due to the vehicle weight and road conditions. Vertical load was decided as the most dominating and critical mechanical load applied on a leaf spring [1]. The theoretical load-deflection diagram of the spring system is shown in Figure\u00a0 6. The loading was executed by the upper rigid support through the displacement of 135\u00a0 mm in z-direction (Figure 5), and alternative displacement and rotation degrees of freedom were restrained in this support. In addition, all displacements and rotations of the other supports on the bottom surface of the model were restrained. Moreover, the rigid body constraint was applied for each support so that the reference point governs the rigid body. In this study, the penalty-based algorithm was selected so as to define the interaction properties and surface-to-surface contact was defined between the composite model and the rigid supports" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001449_2_2_12_22004614__pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001449_2_2_12_22004614__pdf-Figure9-1.png", + "caption": "Fig. 9. Virtual plant in the differential mode", + "texts": [ + " Consequently, the acceleration reference \u03b8\u0308ref C in the common mode is decided as 135 IEEJ Journal IA, Vol.12, No.2, 2023 \u03b8\u0308ref C =\u2212KpfC\u03c4\u0302C\u2212KrCKfCn(\u03b8Cm\u2212 \u03b8Cl)+KrC\u03c4\u0302 dis Cl \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7(34) where KpfC denotes the force control gain. Note that the non-proper transfer function (33) is implemented by zeroorder approximation in the common mode. Fig. 10(a) shows the block diagrams of the proposed common mode space. The block diagram indicates MSC acts on the virtual plant. MLOB and the inverse system compensate for the interference from the differential mode. 3.3.3 Differential Mode Fig. 9 shows the virtual control plant in differential mode. Based on the control goal expressed in (13), we design the differential space controller and configure the acceleration reference \u03b8\u0308ref D so that the virtual control system is the position control system to regulate \u03b8Dl for zero. Semi-closed feedback control is effective for the load-side position control system instead of full-closed control. This paper implements the PD controller for the position feedback control. As with the common mode, feedback of reaction torque KfDn(\u03b8Dm \u2212 \u03b8Dl) makes vibration canceled. Furthermore, the virtual plant of the differential mode is subjected to load-side disturbance and bends shown in Fig. 9. The load-side disturbance includes the external torque \u03c4D = \u03c4h\u2212\u03c4e 2 . MLOB estimates and compensates them together. Since the PD control has a semi-closed loop, the transfer function of the inverse system is represented as \u03b8\u0308ref D \u03c4dis Dl = s2 + KvDs + KpD + KfDnKrD KfDn \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (35) where KpD and KvD denote the proportional gain and the derivative gain for the PD controller, respectively. KrD is the reaction torque feedback gain in the differential mode. As compensation for the load-side disturbance, the motor position \u03b8Dm moves so that the load position \u03b8Dl matches 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001203_el-01058504_document-Figure2.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001203_el-01058504_document-Figure2.8-1.png", + "caption": "Figure 2.8 (a) Three-terminal device based on the giant spin Hall effect in \u03b2-Ta/CoFeB. (b) Electric-fieldcontrolled switching in a CoFeB/MgO/CoFeB MTJ with interfacial PMA.", + "texts": [ + " Beyond the STT switching mechanism, it has been discovered that a spin-polarized current can be generated by the SHE [44]. Due to the spin-orbit coupling, the electrons with different spins deflect in different directions. However, this effect was usually too modest to limit its application. Recently, it was reported that a giant SHE in a high-resistivity from of tantalum (\u03b2-Ta) could generate a spin current strong enough to induce the switching of MTJ [45]. Based on this prominent phenomenon, a three-terminal SHE device was proposed as shown in Figure 2.8(a). The electric current flowing horizontally induces a spin current to pass vertically through the inplane MTJ structure. As the spin polarization of spin current is governed by the direction of the electric current, the magnetization switching direction of MTJ depends thus on the sign of electric current. Although this three-terminal device would cause area efficiency degradation compared with the conventional MTJ, it exhibits various assets in many aspects. For example, by optimizing the thickness of Ta layer, the switching current can be decreased by nearly one order of magnitude compared with STT switching mechanism", + " From the point of view of implementation, there are two voltage-based switching mechanisms that have recently been exhibited. The first one is applying an ultra-fast voltage pulse to result in temporal change of magnetic anisotropy [48]. A toggle magnetization switching process under a constant bias field is realized by controlling the pulse duration of voltage. In the second one, the coercivity of ferromagnetic layers can be modified by the voltage-controlled interfacial anisotropy [49]. Based on this phenomenon, electric-field-assisted switching in MTJ has been successfully achieved (see Figure 2.8(b)). These voltage-controlled or electric-field-induced implementations require no current or just a very small current to switch MTJ, which offers a new path towards ultra-low power MRAM and logic systems. Magnetic domain walls (DWs) are the transition regions separating the domains with distinct magnetization direction, in which the magnetization vectors indeed rotate continuously [50]. From the 1960s, as DWs were considered to have a great potential application for future logic CHAPTER 2 STATE OF THE ART 24 and memory devices, intensive studies have been carries out to deepen both experimental and theoretical understandings [51]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004054___lang_en_format_pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004054___lang_en_format_pdf-Figure14-1.png", + "caption": "Fig. 14. Measured and simulated CP and XP radiation patterns for all the four fabricated MPAs at 2.4 GHz.", + "texts": [ + " Since the gain of an MPA is dependent on the patch area, the Design_1 MPA with the smallest patch area provides the lowest gain. Depending upon the requirement, the compromise is made between the size and gain of an MPA. Brazilian Microwave and Optoelectronics Society-SBMO received 20 Dec 2020; for review 27 Dec 2020; accepted 9 Mar 2021 Brazilian Society of Electromagnetism-SBMag \u00a9 2021 SBMO/SBMag ISSN 2179-1074 Polar form representations of radiation patterns (E-plane/H-plane) for the four MPAs are depicted in Fig. 14. Each of these figures shows both co-polarization (CP) as well as cross-polarization (XP) patterns of simulated and fabricated MPAs. The CP pattern of the E-plane is similar to a monopole for Desigm_1 MPA. The H-plane pattern is almost omnidirectional for this compact MPA. Due to the fractal DGS, there is minor degradation in the CP radiation pattern of the three MPAs in comparison to the conventional MPA. This is clearly understood from Fig. 14. It is noticed from Fig. 14 that for all the MPAs, the simulated and measured CP patterns are closely matching for E-plane. Also, the simulated and measured XP patterns are matching with each other for the E-plane of an MPA. Further, Brazilian Microwave and Optoelectronics Society-SBMO received 20 Dec 2020; for review 27 Dec 2020; accepted 9 Mar 2021 Brazilian Society of Electromagnetism-SBMag \u00a9 2021 SBMO/SBMag ISSN 2179-1074 CP and XP patterns are sufficiently apart from each other. Similarly, for all the MPAs, the simulated and measured patterns are closely matching for H-plane and the CP and XP patterns are sufficiently apart from each other for the H-plane of an MPA" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002141_ngRunqiG1000407F.pdf-Figure3-6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002141_ngRunqiG1000407F.pdf-Figure3-6-1.png", + "caption": "Figure 3-6. (a) Basic schematic of the proposed UWB filter. (b) Bisection circuit under even source excitation. (c) Bisection circuit under odd source excitation.", + "texts": [ + "....................................................... 41 Figure 3-4. Characteristic impedance variations under the different cutoff frequencies (\u03b8c) and the ripple factors (\u03b5) for the circuits of. (a) n= 1. (b) n= 2. (c) n= 3. (d) n= 4 in Figure 3-1 (the input and output port impedances are defined as Z0= 1 \u2126). .... 42 Figure 3-5. Frequency responses and group delays of theoretical, EM simulated and measured results, with a photograph of the fabricated filter in the inset figure. .. 46 - X - Figure 3-6. (a) Basic schematic of the proposed UWB filter. (b) Bisection circuit under even source excitation. (c) Bisection circuit under odd source excitation. .................... 49 Figure 3-7. Frequency responses under the different shunt stubs with the inset figures denoting the characteristic impedances. (a) Short-circuited stubs. (b) Twosection open-circuited stubs. (c) Composite short- and open-circuited stubs. ..... 50 Figure 3-8. (a) LC circuit under even-mode excitation. (b) LC circuit under odd-mode excitation", + " With a closer examination of the introduced reflection zeros, it is found that there are two pairs of reflection zeroes in the complex frequency plane besides the ones in the real frequency plane of the passband. Different from the traditionally used techniques such as introducing input/output port coupling, the proposed composite short- and open-circuited stubs serve as an alternative method to generate new pair of TZs. 3.3.1 Working Mechanism and Circuit Analysis To illustrate the characteristics of the wideband filter with composite short- and open-circuited stubs (as shown in Figure 3-6), the design process is divided into three parts with reference to Figure 3-7(a), (b) and (c). First, a pair of short-circuited stubs is shunt connected at the two sides of the stepped-impedance MMR, as seen in Figure 3-7(a). According to the work in the previous section, a 5th-order Chebyshev filtering response is synthesized with the TZs located at the frequencies when the electrical length of those short-circuited stubs is \u03c0/2, which is the twice of the center frequency of the passband. In Figure 3-7(b), a pair of two-section open-circuited stubs produces a pair of TZs in the rejection band, as reported in [82] and [83]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002355_f_usme2019_01032.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002355_f_usme2019_01032.pdf-Figure1-1.png", + "caption": "Fig. 1. The axle test-bench with load application on cantilevers.", + "texts": [ + " First, when developing a model the equations for equilibrium, dynamics or other expressions are not composed; second, it is not required to use algorithmic programming languages for the purpose of software code writing; third, the process of creating a model is significantly accelerated. For the purpose of fatigue testing of axles two basic patterns of their fastening are used: cantilever and on two supports. The cyclic loading of axles can be created with symmetric alternating harmonic forces, direct intermittent forces and using the method of step-wise force value change [12]. Cantilever restraint of the axle is made on a rigid or elastic cushion [12, 13] with application of inertial harmonic disturbance (Fig. 1). Loading of the axle takes place due to imbalance located on its cantilever end. The imbalance weight through the cardan shaft is set in rotation by electric motor. Testing the axle on such a test-bench develops a strong vibration impact on the test-bench foundation and on the premises where it is in operation. Vibration impact reduction on the foundation is reached by means of installation of elastic elements under the test-bench frame. In order to reduce the vibration caused by the test process the test-bench structural design was suggested for simultaneous testing of several axles [13] installed symmetrically on the platform (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002693_9_10_89_10_1023__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002693_9_10_89_10_1023__pdf-Figure2-1.png", + "caption": "Fig. 2. Schematic diagram of the apparatus.", + "texts": [], + "surrounding_texts": [ + "1023\n\u8f2a \u6587\n\u9244 \u3068 \u92fcTetsu-to-Hagane Vol, 89 (2003) No. 10\n\u9023\u92f3\u92f3\u7247\u306e \u03b1\u76f8\u6790\u51fa\u5236\u5fa1\u306b\u3088\u308b\u9ad8\u6e29\u5ef6\u6027\u6539\u5584\n\u4f0a\u85e4 \u7fa9\u8d77*\u30fb \u52a0\u85e4 \u5fb9*\u30fb \u5c71 \u4e2d \u7ae0 \u88d5*\u30fb \u6e21\u90e8 \u5fe0 \u7537*\nImprovement of Hot Ductility in Continuously Cast Strand by Ferrite Precipitation Control\nYoshiki ITO, TOM KATO, Akihiro YAMANAKA and Tadao WATANABE\nSynopsis : In order to clarify the correlation between susceptibility to transverse cracking and microstructure of slab surface, an apparatus and a method\nof new hot tensile test were designed. Tensile specimens in a cold crucible type heater were in-situ remelted preceding the deformation . Two thermal history for simulating solidification process, mild cooling and SSC (Surface Structure Control) cooling, were examined. Mild cooling means gradual cooling after solidification corresponding to conventional secondary cooling. SSC cooling is a trial cooling pattern aimed at microstructure control which provides rapid cooling until the \u0192\u00c1-\u0192\u00bf duplex phase region and reheating up to y region.\nThe results obtained are summarized as follows. ( 1 ) It was possible to evaluate hot ductility of slab surface with microstructures by means of this hot tensile tests simulating the solidifi-\ncation process.\n( 2 ) By SSC cooling, the ductility is significantly improved and the fracture mode changes into transgranular ductile, because film-like\nferrite is restrained.\n( 3 ) Susceptibility to transverse cracking could be reduced with this microstructure. ( 4 ) Decrease of transverse cracking susceptibility and microstructure control result from fine precipitates dispersion, such as\n(Ti, Nb)(C, N), caused by SSC cooling.\n( 5 ) By utilizing carbonitride precipitation, film-like ferrite along y grain boundary could be restrained and idiomorphic ferrite could be\nformed throughout the matrix.\n( 6 ) Remelting of specimen before deformation is indispensable to evaluate cracking susceptibility on the hot tensile test.\nKey words: continuous casting; hot ductility; transverse cracking; film-like ferrite; hot tensile test; cold crucible; secondary cooling; SSC cooling .\n1. \u7dd2 \u8a00\n\u92fc\u306e\u9023\u7d9a\u92f3\u9020\u304b\u3089\u71b1\u5ef6\u306b\u304b\u3051\u3066\u306e\u30d7\u30ed\u30bb\u30b9\u306b\u304a\u3044\u3066,\u7701\n\u30a8\u30cd\u30eb\u30ae\u30fc\u3084\u5de5\u7a0b\u7701\u7565\u306b\u3088\u308b\u66f4\u306a\u308b\u30b3\u30b9 \u30c8\u4f4e\u6e1b\u3092\u56f3\u308b\u305f\u3081\n\u306b,\u71b1 \u7247\u88c5\u5165(Hot Charging)\u3084 \u76f4\u9001\u5727\u5ef6(Hot Direct Rolling) \u304c\u884c\u308f\u308c\u3066\u304d\u3066\u3044\u308b\u304c,\u92f3 \u7247\u306e\u7121\u624b\u5165\u5316\u304c\u5fc5\u9808\u6761\u4ef6\u3067\u3042\u308b. \u3057\u304b\u3057\u306a\u304c\u3089,\u539a \u677f\u3084\u30e9\u30a4\u30f3\u30d1\u30a4\u30d7\u306b\u7528\u3044\u3089\u308c\u308b\u4f4e\u70ad\u7d20 \u30fb\n\u4f4e\u5408\u91d1\u92fc\u306e\u92f3\u7247\u3067\u306f\u66f2\u3052\u3042\u308b\u3044\u306f\u77ef\u6b63\u6642\u306b\u767a\u751f\u3059\u308b\u6a2a\u3072\u3073 \u5272\u308c\u304c\u554f\u984c \u3068\u306a\u308b\u305f\u3081\u306b,\u4e0a \u8a18\u30d7\u30ed\u30bb\u30b9\u306e\u5927 \u304d\u306a\u969c\u5bb3 \u3068 \u306a\u3063\u3066\u304a\u308a,\u6a2a \u3072\u3073\u5272\u308c\u306e\u629c\u672c\u7684\u9632\u6b62\u7b56\u304c\u5207\u671b \u3055\u308c\u3066\u3044 \u308b\u3002\n\u6a2a\u3072\u3073\u5272\u308c\u306f\u03b3\u2192\u03b1\u5909\u614b\u6e29\u5ea6\u57df \u306b\u304a\u3051\u308b\u4f4e\u6b6a\u307f\u901f\u5ea6\u5909\u5f62\n\u306b\u4f34 \u3046\u9ad8\u6e29\u8106\u5316 \u306b\u8d77 \u56e0\u3059 \u308b\u3053\u3068\u304c\u3088 \u304f\u77e5 \u3089\u308c\u3066\u3044 \u308b1-5).\n\u03b3\u2192\u03b1\u5909\u614b \u306b\u4f34\u3044\u03b3\u7c92\u754c\u30d8\u30d5\u30a3\u30eb\u30e0\u72b6\u306e \u03b1\u76f8 \u304c\u6790\u51fa \u3057,\u6b6a \u307f\u304c\u3053\u306e \u03b1\u76f8\u306b\u96c6\u4e2d\u3059\u308b\u3053\u3068\u306b\u52a0\u3048,\u4f4e \u6b6a\u307f\u901f\u5ea6\u5909\u5f62\u6642\u306b NbC\u3084AIN\u306a \u3069\u304c\u52d5\u7684\u6790\u51fa\u3057\u3066\u7c92\u5185\u3092\u786c\u5316\u3059\u308b\u305f\u3081,\u3055 \u3089 \u306b\u6b6a\u307f\u306e\u96c6 \u4e2d\u304c\u52a9\u9577 \u3055\u308c \u308b\u3002\u03b3\u7c92\u754c\u306b\u6cbf \u3046\u7121\u6790\u51fa\u5e2f\u3084\u30d5\u30a3 \u30eb\u30e0\u72b6\u306e \u03b1\u3067\u754c\u9762\u5265\u96e2 \u3092\u8d77\u3053\u3057,\u3053 \u308c\u306b\u3088\u3063\u3066\u751f \u3058\u305f\u30dc\u30a4\n\u30c9\u304c\u9023\u7d50 \u3057\u3066\u03b3\u7c92\u754c\u5ef6\u6027\u7834\u58ca\u306b\u81f3 \u308b6,7)\u3002\u305d\u306e\u305f\u3081\u5f93\u6765\u306f\u907f\n\u3051\u3089\u308c\u306a\u3044\u8106\u5316 \u3068\u3057\u3066,\u77ef \u6b63\u5e2f\u306a\u3069\u306b\u304a\u3044\u3066\u306f,\u92f3 \u7247\u8868\u9762\n\u306e\u8106\u5316\u6e29\u5ea6\u57df\u3092\u56de\u907f\u3059\u308b\u3088\u3046\u306b\u92f3\u9020\u901f\u5ea6,\u51b7 \u5374\u6761\u4ef6\u3092\u5236\u5fa1 \u3059\u308b\u5fc5\u8981\u304c\u3042\u308a,\u64cd \u696d\u4e0a\u306e\u5236\u7d04\u304c\u5927 \u304d\u304f\u554f\u984c\u3068\u306a\u3063\u3066\u3044\u308b. \u307e\u305f,\u3053 \u306e\u8106\u5316\u306f\u03b3\u7c92\u3092\u7d30\u304b\u304f\u3059\u308b\u3053\u3068\u3067\u8efd\u6e1b\u3067\u304d\u308b8,9)\u304c, \u9023\u7d9a\u92f3\u9020\u6642\u306b\u03b3\u7c92\u5f84 \u3092\u9855\u8457\u306b\u5fae\u7d30\u5316\u3059\u308b\u65b9\u6cd5\u3092\u78ba\u7acb\u3059\u308b\u306e \u306f\u56f0\u96e3\u3067\u3042\u308b\u3002\u3053\u308c\u306b\u5bfe \u3057\u3066,2\u6b21 \u51b7\u5374\u6761\u4ef6\u3092\u9069\u6b63\u306b\u9078\u629e\n\u3059\u308c\u3070,\u6a2a \u3072\u3073\u5272\u308c\u304c\u9632\u6b62\u53ef\u80fd \u3068\u306a\u308b \u30df\u30af\u30ed\u7d44\u7e54\u304c\u751f\u6210\u3059 \u308b\u3053\u3068\u304c\u5831\u544a10)\u3055\u308c\u3066\u3044\u308b\u3002\u7b46\u8005 \u3089\u306f,\u92f3 \u7247\u8868\u9762\u3092\u9ad8\u6e29\u9818\n\u57df\u304b \u3089\u3044\u3063\u305f\u3093 \u03b3\u2192\u03b1\u5909\u614b\u70b9\u4ee5\u4e0b \u307e\u3067\u6025\u51b7\u5374 \u3057,\u6975 \u77ed\u6642\u9593 \u3067 \u03b3\u57df\u307e\u3067\u5fa9\u71b1 \u3055\u305b \u308b\u3053\u3068\u3067,\u92f3 \u7247\u8868\u5c64 \u3092\u30d5\u30a3\u30eb\u30e0\u72b6 \u03b1\u306e \u751f\u6210 \u3092\u6291\u5236 \u3057\u305f\u7d44\u7e54\u306b\u5236\u5fa1\u3067 \u304d,\u305d \u306e\u7d50\u679c,\u6a2a \u3072\u3073\u5272\u308c\u3092 \u9632\u6b62\u3067\u304d\u308b\u3053\u3068\u3092\u660e\u3089\u304b\u3068\u3057\u305f11)\u3002\n\u672c\u7814\u7a76\u3067\u306f,\u305d \u306e\u624b\u6cd5\u306b\u95a2\u3059\u308b\u9ad8\u6e29\u8106\u5316\u6319\u52d5\u306e\u5909\u5316\u3092\u660e \u3089\u304b \u3068\u3059\u308b\u305f\u3081\u306b,\u5b9f \u969b\u306e\u9023\u92f3\u92f3\u7247\u8868\u5c64\u7d44\u7e54 \u3092\u518d\u73fe\u53ef\u80fd \u3068\n\u3059\u308b,\u8a66 \u9a13\u7247\u3092\u3044\u3063\u305f\u3093\u6eb6\u878d\u3055\u305b\u305f\u5f8c\u306b\u51dd\u56fa\u3067\u304d\u308b\u30b3\u30fc\u30eb\n\u30c9\u30af\u30eb\u30fc\u30b7\u30d6\u30eb\u578b\u306e\u9ad8\u6e29\u5f15\u5f35\u8a66\u9a13\u624b\u6cd5 \u3092\u65b0\u305f\u306b\u8003\u6848 \u3057,\u9ad8\n\u6e29\u5ef6\u6027\u306b\u53ca\u307c\u3059\u92f3\u9020 \u307e\u307e\u7d44\u7e54\u306e\u5f71\u97ff\u306b\u3064\u3044\u3066\u691c\u8a0e \u3057\u305f\u3002\n2. \u6a2a \u3072 \u3073 \u5272 \u308c\u9632 \u6b62 \u53ef \u80fd \u306a\u6e29 \u5ea6 \u5c65\u6b74\n\u7b46\u8005 \u3089\u304c\u884c \u3063\u305fNb\u3092 \u542b\u6709\u3059 \u308b\u4f4e\u70ad\u7d20\u4f4e\u5408\u91d1\u92fc(0.07%C-\n\u5e73 \u621015\u5e744\u670825\u65e5 \u53d7 \u4ed8 \u5e73 \u621015\u5e746\u670811\u65e5 \u53d7 \u7406(Received on Apr. 25, 2003; Accepted on June 11, 2003)\n* \u4f4f \u53cb \u91d1 \u5c5e \u5de5 \u696d(\u682a)\u7dcf \u5408 \u6280 \u8853 \u7814 \u7a76 \u6240(Corporate Research & Devebpment Laboratories , Sumitomo Metal Industfies, Ltd., 16-1 Oaza-Smayama Hasakimachi Kashima-\ngun Ibaraki-ken 314-0255)", + "1024\u9244 \u3068 \u92fcTetsu\u30fbto-Hagane Vol. 89 (2003) No. 10\n1.5%Mn-Nb)\u3092 \u5bfe \u8c61 \u3068 \u3057\u305f,\u9023 \u7d9a \u92f3 \u9020 \u4e2d \u306e \u92f3 \u7247 \u66f2 \u3052 \u8a66 \u9a13H) \u306b \u304a \u3051 \u308b\u92f3 \u7247 \u8868 \u5c64 \u306e \u6e29 \u5ea6 \u5c65 \u6b74 \u5b9f \u7e3e \u3092Fig .1\u306b \u793a \u3059 \u3002 \u73fe \u72b6 \u306e \u9023\u7d9a \u92f3 \u9020 \u64cd \u696d \u3092\u6a21 \u64ec \u3057\u305f \u5f90 \u3005 \u306b\u51b7 \u5374 \u3059 \u308b\u6761 \u4ef6(\u5f90 \u51b7 \u5374)\u3068,\n\u92f3\u578b \u3092\u51fa \u305f\u76f4 \u5f8c \u306b \u3044 \u3063 \u305f \u3093 \u6025 \u51b7 \u5374 \u3057,\u305d \u306e \u5f8c \u77ed \u6642 \u9593 \u3067 \u5fa9 \u71b1\n\u3059 \u308b \u6761 \u4ef6(\u6025 \u51b7 \u5374)\u3067 \u8a66 \u9a13 \u3092\u884c \u3063 \u305f \u3002 \u305d\u306e \u7d50 \u679c,\u6025 \u51b7 \u5374 \u6761\n\u4ef6 \u3068\u3059 \u308b \u3053 \u3068 \u3067,\u92f3 \u9020 \u4e8c \u6b21 \u7d44 \u7e54 \u304c \u5909 \u5316 \u3057\u6a2a \u3072 \u3073 \u5272 \u308c \u304c \u9632 \u6b62 \u3067 \u304d\u3066 \u3044 \u308b \u3053 \u3068 \u3092\u78ba \u8a8d \u3057\u305f \u3002\n\u51b7 \u5374 \u5236 \u5fa1(SSCcooling: Surface Structure Control cooling)\u306b\n\u3088 \u308a\u660e \u767d \u306a \u6a2a \u3072 \u3073 \u5272 \u308c \u9632 \u6b62 \u52b9 \u679c \u304c \u8a8d \u3081 \u3089\u308c \u308b \u3053 \u3068\u304b \u3089,\u9ad8\n\u6e29 \u5ef6 \u6027 \u304c \u5411 \u4e0a \u3057\u305f \u3053 \u3068\u304c \u8003 \u3048 \u3089\u308c \u308b \u3002 \u305d \u3053 \u3067,\u92f3 \u9020 \u307e \u307e\u7d44\n\u7e54 \u3092\u8003 \u616e \u3057\u3066 \u9ad8 \u6e29 \u5ef6\u6027 \u3092\u660e \u3089\u304b \u3068\u3059 \u308b \u305f \u3081 \u306b,\u4ee5 \u4e0b \u306b\u8ff0 \u3079\n\u308b\u5f15\u5f35 \u8a66 \u9a13 \u306b \u3088 \u308b\u8a55 \u4fa1 \u3092 \u884c \u3063 \u305f \u3002\n3. \u8a66\u9a13\u65b9\u6cd5\n\u5f15\u5f35\u8a66\u9a13\u88c5\u7f6e\u306e\u6982\u7565 \u3092Fig.2\u306b \u793a\u3059\u3002\u52a0\u71b1\u6a5f\u69cb \u3068\u3057\u3066\u9ad8 \u5468\u6ce2\u8a98\u5c0e\u52a0\u71b1\u65b9\u5f0f\u306e\u30b3\u30fc\u30eb \u30c9\u30af\u30eb\u30fc\u30b7\u30d6\u30eb \u3092\u63a1\u7528\u3059\u308b\u3053\u3068 \u3067,\u78c1 \u5834\u6d6e\u63da\u306b\u3088\u308a\u975e\u63a5\u89e6\u72b6\u614b\u3067\u6eb6\u878d\u90e8\u3092\u4fdd\u6301\u3067\u304d\u308b\u3002\u307e \u305f,\u305d \u306e\u5f8c\u306e\u51b7\u5374\u901f\u5ea6\u3092\u5236\u5fa1\u3059\u308b\u3053\u3068\u3067,\u9023 \u7d9a\u92f3\u9020\u6642\u306e\u51dd \u56fa\u904e\u7a0b \u3092\u518d\u73fe\u53ef\u80fd \u3068\u3057\u305f\u3002\u672c\u624b\u6cd5\u306e\u7279\u5fb4 \u3068\u3057\u3066\u306fFig.3\u306b \u793a\u3059\u3088\u3046\u306b,\u65e2 \u5b58\u306e \u30b3\u30a4\u30eb\u52a0\u71b1\u65b9\u5f0f9\u300d2\u535a\u306f\u56f0\u96e3\u3067\u3042\u3063\u305f \u8a66\u9a13\u7247\u5f84\u306b\u5bfe \u3057\u3066\u7d044\u500d \u3068\u3044\u304637mm\u306e \u9577 \u3055\u3067,\u76f4 \u5f84\u304c\u6982 \u306d10.2mm\u5747 \u4e00\u3068\u306a\u308b\u6eb6\u878d\u51dd\u56fa\u90e8 \u3092\u5f62\u6210\u3067 \u304d\u308b\u3002\u307e\u305f\u975e\u63a5 \u89e6\u3067\u3042\u308b\u305f\u3081,\u30b7 \u30ea\u30ab\u30c1\u30e5\u30fc\u30d6\u3092\u4f7f\u3063\u305f\u65b9\u6cd5\u3067\u554f\u984c \u3068\u306a\u308b \u30ac\u30b9\u767a\u751f\u306b\u3088\u308b\u5f15\u3051\u5de3\u306e\u6b8b\u5b58\u306f\u306a\u304f,\u7cbe \u5ea6\u306e\u9ad8\u3044\u5ef6\u6027\u8a55\u4fa1 \u304c\u53ef\u80fd \u3068\u306a\u308b\u3002\n\u30b3\u30fc\u30eb \u30c9\u30af\u30eb\u30fc \u30b7\u30d6\u30eb \u306e\u5185\u5f84 \u306f10 \u4e005mm,\u52a0 \u71b1 \u7bc4\u56f2 \u306f 40mm\u3067,\u30af \u30eb\u30fc\u30b7\u30d6\u30eb\u76f4\u4e0a\u306b\u653e\u5c04\u6e29\u5ea6\u8a08\u3092\u8a2d\u7f6e \u3057,\u4e8b \u524d \u306b\u6e29\u5ea6\u691c\u91cf\u7dda\u3092\u4f5c\u6210\u3059\u308b\u3053\u3068\u3067,\u6eb6 \u878d\u51dd\u56fa\u90e8\u6e29\u5ea6\u3092\u691c\u5b9a\u3059\n\u308b\u65b9\u5f0f\u3092\u63a1\u7528 \u3057\u305f\u3002\u8a66\u9a13\u306f\u6eb6\u878d\u51dd\u56fa\u6642\u306e\u9178\u5316\u3092\u9632\u6b62\u3059 \u308b\u76ee\n\u7684\u3067,Ar\u96f0 \u56f2\u6c17\u4e2d\u3067\u5b9f\u65bd \u3057\u305f\u3002\u672c\u7814\u7a76\u306b\u304a\u3051\u308b\u51b7\u5374\u901f\u5ea6 \u5236\u5fa1\u306f\u8a98\u5c0e\u52a0\u71b1\u30b3\u30a4\u30eb\u306e\u51fa\u529b\u8abf\u6574\u306e\u307f\u306b\u3088\u3063\u3066\u884c \u3063\u305f\u304c, \u88c5\u7f6e\u6a5f\u69cb\u3068\u3057\u3066He\u7b49 \u306e\u51b7\u5374 \u30ac\u30b9\u5439\u304d\u3064 \u3051\u3082\u4f75\u7528\u3067 \u304d,\u3055\n\u3089\u306b\u901f\u3044\u51b7\u5374\u901f\u5ea6\u3067\u306e\u8a66\u9a13\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002\n\u8a66\u9a13\u6761\u4ef6\u3092Fig.4\u306b \u793a\u3059\u3002\u8a66\u9a13 \u306f\u6e29\u5ea6\u5c65\u6b74\u306e\u5f71\u97ff\u3068\u51dd\u56fa \u904e\u7a0b\u306e\u5f71\u97ff \u3092\u8abf\u67fb\u3059 \u308b\u305f\u3081\u306b3\u7a2e \u985e\u306e\u6761\u4ef6\u3067\u884c\u3063\u305f\u3002Fig. 1\u306b\u793a \u3057\u305f\u9023\u7d9a\u92f3\u9020\u4e2d\u306e\u92f3\u7247\u66f2\u3052\u8a66\u9a13ll)\u3067\u306e\u92f3\u7247\u8868\u5c64\u6e29\u5ea6\n(*: Surface Structure Control (SSC) cooling)", + "\u9023\u92f3\u92f3\u7247\u306e\u03b1\u76f8\u6790\u51fa\u5236\u5fa1\u306b\u3088\u308b\u9ad8\u6e29\u5ef6\u6027\u6539\u5584 1025\n\u5c65\u6b74\u3092\u518d\u73fe\u3059 \u308b\u3088\u3046\u306b,\u8a66 \u9a13\u7247(\u6db2 \u76f8\u6e29\u5ea6:1794K,\u56fa \u76f8 \u6e29\u5ea6:1767K,Ae3\u5909 \u614b\u6e29\u5ea6\u73893):1081K>\u3092 \u3044\u3063\u305f\u3093\u6eb6\u878d \u3057 \u305f\u5f8c,1523K\u307e \u3067\u306f\u540c\u4e00\u901f\u5ea6\u3067\u51b7\u5374 \u3057,\u305d \u306e\u5f8c,\u5f90 \u3005\u306b\u51b7\n\u5374\u3059\u308b\u6761\u4ef6(Fig.4(a),\u5f90 \u51b7\u5374)\u3068,\u3044 \u3063\u305f\u3093\u6025\u51b7\u5374 \u3057\u305d\u306e \u5f8c\u77ed\u6642\u9593\u3067\u5fa9\u71b1\u3059\u308b\u6761\u4ef6(Fig.4(b),\u6025 \u51b7\u5374),\u6eb6 \u878d \u3057\u306a\u3044 \u3053\u3068\u3092\u9664\u304d\u6025\u51b7\u5374 \u3068\u3059\u3079\u3066\u540c \u3058\u6761\u4ef6(Fig\u30024(c),\u518d \u52a0\u71b1\u6025\u51b7\n\u5374)\u306b \u306a\u308b\u3088\u3046\u306b,\u51b7 \u5374\u901f\u5ea6,\u6e29 \u5ea6\u5c65\u6b74 \u3092\u5909\u5316 \u3055\u305b \u305f. 873\uff5e1327K\u306e \u6240\u5b9a\u306e\u6e29\u5ea6\u30672\u5206 \u9593\u4fdd\u6301 \u3057\u305f\u5f8c,3.3\u00d710-4 s}1\u306e\u6b6a\u307f\u901f\u5ea6\u3067\u7834\u65ad\u306b\u81f3 \u308b\u307e\u3067\u7b49\u6e29\u5f15\u5f35\u5909\u5f62 \u3057\u305f\u3002\u5f15\u5f35 \u3092\u7d42\u4e86 \u3057\u305f\u8a66\u9a13\u7247\u304b \u3089\u7834\u65ad\u9762\u98aa\u5f84 \u3092\u6e2c\u5b9a \u3057,\u65ad \u9762\u53ce\u7e2e\u7387\n\u4fadA,)\u3092 \u4ee5\u4e0b\u306e\u5b9a\u7fa9\u306b\u3088\u308a(1)\u5f0f \u304b \u3089\u7b97\u51fa \u3057\u305f\u3002\n( 1 )\nAOl\u5f15 \u5f35 \u524d \u8a66 \u9a13 \u7247 \u306e \u65ad \u9762 \u7a4d(mm2)\n\u30fb\u6eb6 \u878d \u51dd \u56fa\u8a66 \u9a13\nAO=\u03c0(dO1/2)2\ndO1:\u6eb6 \u878d \u51dd \u56fa \u90e810\u7b87 \u6240 \u306e \u5e73 \u5747 \u76f4 \u5f84(mm)\n\u30fb\u518d \u52a0 \u71b1 \u8a66 \u9a13\nAO\u83f0 \u03c0(dO2/2)2\ndO2:\u52a0 \u5de5 \u5f8c \u8a66 \u9a13 \u7247 \u306e \u76f4 \u5f84(mm)\nAf:\u5f15 \u5f35 \u7834 \u65ad \u8a66 \u9a13 \u7247 \u306e \u65ad \u9762 \u7a4d(mm2)\nAf\u7bc7 \u03c0(df\u30f32)2\ndf:\u7834 \u65ad \u976210\u7b87 \u6240 \u306e \u5e73 \u5747 \u76f4 \u5f84(mm)\n\u6eb6\u878d\u51dd\u56fa\u8a66\u9a13\u3067\u306f,\u6eb6 \u89e3\u306b\u3088\u308a\u8a66\u9a13\u7247\u5f84\u304c\u5909\u5316\u3059 \u308b\u305f\u3081, \u5404\u6761\u4ef6\u306e\u6e29\u5ea6\u5c65\u6b74 \u3092\u7d4c\u904e \u3055\u305b\u305f\u306e\u3061,\u5f15 \u5f35 \u3092\u884c \u3046\u3053\u3068\u306a\u304f \u5ba4\u6e29\u307e\u3067\u51b7\u5374 \u3055\u305b\u305f\u30b5\u30f3\u30d7\u30eb\u3092\u4f5c\u88fd \u3057,\u6eb6 \u878d\u51dd\u56fa\u90e8\u5468\u65b9\u5411 \u306e10\u7b87 \u6240\u3067\u6e2c\u5b9a \u3057\u305f\u76f4\u5f84\u306e\u5e73\u5747\u5024dO1\u306b \u3088\u308a,\u5f15 \u5f35\u524d\u8a66\u9a13\n\u7247\u306e\u65ad\u9762\u7a4dAO\u3092 \u7b97\u51fa \u3057\u305f\u3002\u518d\u52a0\u71b1\u8a66\u9a13 \u3067\u306f,\u52a0 \u5de5\u5f8c\u8a66\u9a13 \u7247\u306e\u76f4\u5f84dO2\u306b \u3088 \u308a,AO\u3092 \u7b97\u51fa \u3057\u305f\u3002\u5f15\u5f35\u7834\u65ad\u8a66\u9a13\u7247\u306e \u65ad\u9762\u7a4dAf\u306b \u3064\u3044\u3066\u306f,\u6eb6 \u878d\u51dd\u56fa,\u518d \u52a0\u71b1\u8a66\u9a13\u306e\u3044\u305a\u308c\u306e \u5834\u5408\u3082,\u7834 \u65ad\u9762\u5468\u65b9\u5411\u306e10\u7b87 \u6240 \u3067\u6e2c\u5b9a \u3057\u305f\u85cf\u5f84\u306e\u5e73\u5747\u5024 df\u3092\u6c42\u3081\u308b\u3053\u3068\u3067\u7b97\u51fa \u3057\u305f\u3002\n\u7834\u65ad\u9762\u306e\u6e2c\u5b9a\u3092\u7d42\u4e86\u3057\u305f\u8a66\u9a13\u7247\u306f,\u5207 \u65ad,\u7814 \u78e8\u5f8c\u306b\u30ca\u30a4 \u30bf\u30eb\u6db2\u8150\u98df\u306b\u3088\u308b\u5149\u5b66\u9855\u5fae\u93e1\u7d44\u7e54\u89b3\u5bdf,\u900f \u904e\u578b\u96fb\u5b50\u9855\u5fae\u93e1\n(\u4ee5\u4e0bTEM)\u306b \u3088\u308b\u6790\u51fa\u7269\u89b3\u5bdf \u3092\u884c\u3044,\u9ad8 \u6e29\u5ef6\u6027 \u3068\u306e\u95a2\u9023 \u306b\u3064\u3044\u3066\u691c\u8a0e \u3057\u305f\u3002\u8a66\u9a13\u7247\u306e\u5316\u5b66\u7d44\u6210 \u3092Table1\u306b \u793a\u3059. \u8a66\u9a13\u7247\u306f\u771f\u7a7a\u6eb6\u89e3\u7089\u3067\u6eb6\u89e3 \u3057\u3066\u5f97\u305f\u92f3\u584a\u3092\u935b\u9020 \u3068\u5727\u5ef6\u306b\u3088\n\u308a\u76f4\u5f8410mm,\u9577 \u3055190mm\u306b \u52a0\u5de5 \u3057\u305f.\n4. \u6eb6\u878d\u51dd\u56fa\u90e8\u6e29\u5ea6\u306e\u5236\u5fa1\u65b9\u6cd5\n4\u30fb1 \u6e29\u5ea6\u5206\u5e03\u72b6\u6cc1\u8abf\u67fb\n\u653e\u5c04=\u6e29\u5ea6\u8a08\u306b\u3088\u308b\u6eb6\u878d\u51dd\u56fa\u90e8\u6e29\u5ea6\u306e\u691c\u5b9a\u3092\u7cbe\u5ea6\u826f\u304f\u884c\u3046\n\u305f\u3081\u306b\u306f,\u52a0 \u71b1\u7bc4\u56f2\u306b\u304a\u3051\u308b\u6e29\u5ea6\u5206\u5e03\u72b6\u6cc1\u3092\u628a\u63e1\u3059\u308b\u5fc5\u8981\n\u304c\u3042\u308b\u3002\u305d\u3053\u3067,Fig.5\u306b \u793a\u3059\u3088\u3046\u306b\u8a66\u9a13\u7247\u306b\u52a0\u5de5 \u3057\u305f\u30b9 \u30ea\u30c3\u30c8\u306bPt-13%Rh\u71b1 \u96fb\u5bfe \u3092\u633f\u5165 \u3057,\u30b9 \u30ea\u30c3\u30c8\u5e95\u90e8\u306b\u71b1\u96fb \u5bfe \u3092\u62bc \u3057\u4ed8\u3051\u305f\u72b6\u614b\u3067\u6e29\u5ea6\u6e2c\u5b9a\u3092\u884c\u3063\u305f\u3002\u6e29\u5ea6\u6e2c\u5b9a\u306f,\u8a66 \u9a13\u7247\u9577 \u3055\u65b9\u5411\u306e\u71b1\u96fb\u5bfe\u4f4d\u7f6e(\u8a66 \u9a13\u7247\u4e0a\u7aef\u304b \u3089\u306e\u8ddd\u96e2\u03ba)\u3092 \u5909\u5316 \u3055\u305b,\u5404 \u4f4d\u7f6e\u306b\u304a\u3044\u3066\u653e\u5c04\u6e29\u5ea6\u8a08\u306e\u5236\u5fa1\u6e29\u5ea6 \u3092\u5909\u5316 \u3055 \u305b\u306a\u304c\u3089\u884c\u3063\u305f\u3002\u305d\u306e\u7d50\u679c\u3092Fig.6\u306b \u793a\u3059\u3002\u8a66\u9a13\u7247\u9577 \u3055\u65b9\n\u541130mm\u306e \u7bc4\u56f2\u3067\u58eb150C\u4ee5 \u5185,15mm\u306e \u7bc4\u56f2\u3067\u00b13\u2103C\u4ee5\u5185 \u3067\u3042\u308a,\u6982 \u306d\u4e00\u69d8\u306a\u6e29\u5ea6\u5206\u5e03\u3067\u3042\u308b\u3053\u3068\u304c\u78ba\u8a8d \u3055\u308c\u305f\u3002\u307e \u305f,\u5f8c \u8ff0\u3059\u308b\u5f15\u5f35\u8a66\u9a13 \u306b\u304a\u3044\u3066\u306f,\u3053 \u306e15mm\u306e \u7bc4\u56f2\u5185\u3067 \u7834\u65ad \u3057\u3066\u3044\u308b\u3053\u3068\u3092\u78ba\u8a8d \u3057\u3066\u3044\u308b. 4\u30fb2 \u6e29\u5ea6\u691c\u91cf\u7dda\u306e\u4f5c\u6210\n\u52a0\u71b1\u7bc4\u56f2\u306e\u8a66\u9a13\u7247\u6e29\u5ea6\u5206\u5e03\u8abf\u67fb\u7d50\u679c\u3088\u308a\u5224\u660e\u3057\u305f\u5747\u4e00\u6e29 \u5ea6\u5206\u5e03\u9818\u57df\u306b\u304a\u3044\u3066,\u8a66 \u9a13\u7247\u5185\u6e29\u5ea6 \u3068,\u653e \u5c04\u6e29\u5ea6\u8a08\u306b\u3088\u308b \u5236\u5fa1\u6e29\u5ea6 \u3092\u5bfe\u6bd4 \u3057\u3066\u6e29\u5ea6\u691c\u91cf\u7dda \u3092\u4f5c\u6210 \u3057\u305f\u3002\u5747\u4e00\u6e29\u5ea6\u5206\u5e03 \u9818\u57df\u4e2d\u5fc3\u306b\u71b1\u96fb\u5bfe \u3092\u8a2d\u7f6e \u3057,\u653e \u5c04\u6e29\u5ea6\u8a08\u306e\u6e2c\u5b9a\u4f4d\u7f6e\u306b\u304a\u3051\n\u308b\u6e29\u5ea6 \u3092673\uff5e1533K\u306e \u7bc4\u56f2\u3067\u5909\u5316 \u3055\u305b,\u8a66 \u9a13\u7247\u5185\u6e29\u5ea6\u3092\n\u6e2c\u5b9a \u3057\u305f\u3001\u6e2c\u5b9a\u306f\u8a082\u56de \u884c \u3044,\u305d \u306e\u7d50\u679c\u3092Fig.7\u306b \u793a\u3059. \u6700\u5c0f\u4e8c\u4e57\u6cd5\u306b\u3088\u308a\u5404\u6e29\u5ea6\u7bc4\u56f2\u306b\u304a\u3044\u3066,\u6eb6 \u878d\u51dd\u56fa\u90e8\u6e29\u5ea6\u304c \u691c\u5b9a\u53ef\u80fd \u3068\u306a\u308b\u56de\u5e30\u5f0f[q\uff5e[4]\u5f0f \u3092\u5c0e\u51fa \u3057,\u5f15 \u5f35\u8a66\u9a13 \u306b\nTable 1. Chemical composition of steel (mass%).\nFig. 5. Measurement of temperature profile in melting zone." + ] + }, + { + "image_filename": "designv8_17_0001331_557_adv.2020.425.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001331_557_adv.2020.425.pdf-Figure3-1.png", + "caption": "Figure 3- 3 dimensional model of the proposed device.", + "texts": [], + "surrounding_texts": [ + "Origami based mechanisms could prove to be a viable solution to the need for developing a lightweight, highly-compressible deployable cylinder to house objects, materials and to be portable and transportable at the same instant. The origami cylinder, commonly referred as bellows, is a collapsible device which can expand to be deployed and contract when not in use for ultra-portable storage solutions [5]. The ideal material for the body of the disinfection device is synthetic tear resistant paper, owing to its structural features and its light weight. Since origami is an art revolving around paper, and since paper acts as a very good option in such a product, it is prudent to proceed with such. Cost is of paramount importance in this regard, and since manufacturing can be fast and relatively simple than metal or any other form of polymer, hence paper is encouraged. However, with the massive benefits of papers, comes its challenges too. Primarily, the quality is of grave concern, the preferred grade of tear resistant paper, say consists of imperfections, can accelerate fatigue in the bellow, that can result in reduced user experience time, hence serve as a failed product. Secondly, water proofing is an issue with the cost kept on mind. Using a water resistant coat on the outer surface of the device, shall contribute to increased manufacturing cost. But if used in extreme conditions, this requirement is paramount for a complete user experience. Next issue that can arise is easy deformation into something unwanted due to the structural nature of paper. Rough handling of the device can result into something like this. Precautions to prevent such incidents must be undertaken. Decreasing the likelihood of failure is another important aspect of the design. The bellows is less likely to fail at any single vertex, by minimizing the number of vertices. [3]. There are various patterns with respect to which one could be used to make the origami bellows, starting off with the Kresling fold pattern and the Accordion fold pattern [3]. Both of them are not rigid foldable structures and they have a clear cross sectional area within the annulus. However, due to fatigue in deflection cycling after a low number of repeated stress applications, the Accordion fold pattern is not a suitable pattern to use in this case [6]. One tessellation of the Kresling pattern is shown in figure 1, where the dependent parameters are a, b, c, . Equations explaining the Kresling tessellation unit are given below [3]; a = D sin ( n) \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026 (1) b= D sin (arccos (d/D) - n)\u2026\u2026\u2026\u2026\u2026... (2) c= D sin (arccos (b/D) + n)\u2026\u2026\u2026\u2026\u2026.. (3) n being an independent parameter, has greater implications on the design. It is defined as the number of panels present in one storey where the number of storey for the bellow is denoted by s. In such a case the number of panels and the mechanical strain in the bellow follow a relation- As the number of panels in each storey increases, the strain amount decreases. An ideal value of n is chosen; n=9 - which ensures, significantly lesser strain than lower n values [6]. After we understand the parameter that entail this design, now the focus shifts on to the parametric permutation, as to how to bring about the ideal bellow for the point of use this article focuses on. Another, concern when we are referring to the portability aspect of the device, is the compressibility of the bellow- a primary reason why such an origami pattern was selected. Depending on the material and requirement of deployment, when in use- the bellow can be designed accordingly altering the height of each storey (h) and the deployment angle ( ).[3] h = b sin (4) If there is a reduction in storeys required, keeping intact the overall linear dimension of the device, then we have to increase the height of each storey, consequently increasing the deployment angle. The height of storey and the deployment angle are independent of any other functional parameter, whereas they are interdependent parameters, when considered together. While different materials of the bellow have different compressibility, the one\u2019s made out of metals have a compressibility of approximately 66%, but in this scenario we use, paper where the compressibility percentage varies from 90-92 % approximately [12]. For bellows the compressibility is computed as the ratio of the change of height after being deployed to the deployed height of the bellow; Compressibility = t-t\u2019/t \u2026\u2026\u2026\u2026\u2026\u2026.. (5) Where, t = Deployed height t\u2019= Compressed height. Here, decreasing the likelihood of failure of the bellow is a major aspect of the design, since it\u2019s made out of paper, can be ensured if the bellow have significantly reduced number of vertices [13]. As discussed earlier, this can be achieved by reducing the number of layer storey and increasing the deployment angle, enforcing lesser buckling points for fracture and helping through the stress distribution, during deflection cycling. These structural features, primarily depend on the material used, which in turn is pivoted around the selection of the design, driven by cognitive and intuitive knowledge [10]. Based on the application and demands posed by the circumstances, materials can be appropriately altered to fit the need. CONSTRUCTION The rationale behind using such complex paper geometry to achieve pragmatic advantages over traditions disinfection cum storage devices, is to be able to inject the product into locations, where a sophisticated metal or HDPE disinfection device is a farfetched possibility, both economically and logistically. Hence storage of daily objects, like keys, chains, pens and other necessary items of work can find their safe house, into the origami bellow, equipped with UV lamps to kill pathogens present on the surface of the objects the bellow houses. Far UVC lamps of wavelengths 207-222 nm should be enough to destroy the SARS-CoV-2, [7] also since the entire disinfection process takes place in the closed paper bellow, which essentially acts as a closed chamber, the UVC cannot be charged with deleterious effects on humans, since precautions are to be taken for grid locking minimum light leaking possibilities [14]. 2 plastic parts that shall house 3 Far UVC LEDs on each end shall be 3D printed, out of fine PLA, and to be attached at the either end. Essentially it forms a collapsible storage space, that as the ability to disinfect, without remote contact of any human. At the rear end, the battery is housed, which is essentially a non-rechargeable 1.2 V cell, used to power the LEDs and can\u2019t disposed, once it runs out. Since the objects to disinfect are to be inserted into the interior of the bellow from A, hence the battery and the switch are to be housed on the rear side, i.e. B. With two pieces of plastic and a collapsible paper structure, this forms a collapsible system of housing objects- the embodiment when in the collapsed version, is functionally inactive, and however is extremely portable in terms of scale. By proportional alteration of the said parameters, in the origami pattern the bellow can be scaled onto any volume, depending on the requirement of the customer, organisation or even demography keeping in mind the COVID-19 scenario. Non-tearable paper, being a robust material for the extreme conditions it can function in, and the portability enabler is an important reason for driving down the overall cost of the product, making it accessible to the common masses in target countries as discussed earlier in the article. The design of the product has been articulated, keeping a personal point of use in mind. In remote areas, mass sanitising devices, are often controlled by local authorities with a lack of continued service, essentially producing a gap in between the recipients of the service and the health care benefit they ought to receive. This disparity has led to the pin point usage of the product i.e. to the consumers themselves. The product, being inexpensive to make due to the basic objects it uses in it construction, not only helps in the mass manufacturing process if proceeded with, but also enables, underprivileged sector to join the entire process of manufacturing to disinfection, creating a sustainable cycle [8]. Initially the prototyping time took approximately 68 hours, with a scaled up manufacturing process, the estimated time for manufacturing of 500 pieces is approximately 2 days. This numeric conclusion assumes that 5 semi-skilled labours are working in unison. Since the folding pattern has to be hand-made, the working rate consideration is 100 pieces/labour/day. The remaining plastic body shall be manufacture via injection moulding process, preferably a 4 cavity mould, to speed up production. This has been possible primarily due to the nature of design employed in this regard. Manufacturability of an origami bellow is highly dependent upon the number of fabrication folds required to make the bellow. Patterns with long, continuous folds are more manufacturable than a bellows with many short folds [3]. Materials Unit Cost per 10000 pcs Paper-300 sq. cm. $ 0.06 Switch $ 0.05 UV C LED and connections $ 0.42 Plastic components $ 0.15 3V button battery- CR2016 $ 0.06 TOTAL $ 0.74- $ 0.95 Now, the next question arises with respect to the ergonomics, and how a user interacts with device. It is to be understood that the aforementioned design strategy, aims to make the entire process of using the device easy and fluid. The complexity of origami and the electrical component, have been embodied in the device for the user, in a way which masks all such complexity to bring out an easy to use product. Since disinfection is of utmost importance, the design should be able to fit in to the daily lives of the people, like something they are really comfortable to use- Once the bellow is compressed, it is shrunk to a mere disk of 12 mm height and 58 mm in diameter. This compact embodiment, fits easily inside the pocket of the consumer, making it portable not only in its expanded version but also in it compact version. Further development to the product could include a latch in the top of the front lid to attach a karabiner for hooking it up with the pant or any bag. This shall augment the ergonomic aspects of the product. However, any addition of ancillary parts to the product shall increase the cost of manufacturing and should be avoided if not necessary. The volume of the product is not rigid in nature- by altering the required parameters, the volume can either be increased or decreased depending upon the user requirement, this is primarily enables by the expanding and contracting nature of the bellow, that allows options with regard to how much volume it shall contain. In order to use the product the user needs to pull apart both the 3D printed parts to expand the bellow- the bellow can expand without obstruction till 240 mm after which it shall start to contract. Following which he/she needs to open the front lid of the device, and insert belongings that need to be sanitised, after closing the lid, the switch connecting the UV C lamps need to be turned on and the wait for the objects to get disinfected. After which the bellow can be carefully compressed, ejecting the belongings and closing of the device, making it ready for the next use. This simplistic work mechanism of the device, is achieved by the modular product architecture it purports- where individual parts exist in modular form for them to be assembled and worked out in a convenient fashion. It is important to understand that between the conceptual and the prototyping stage, changes in types of product architecture plays a role with respect the manufacturing of the product i.e. it could have been one integrated product with built in parts for at the go manufacturing, however the expanded manufacturing line in this regard shall make the understanding of the product to the user not only more fluid but convenient." + ] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.7-1.png", + "caption": "Figure 2.7: Reciprocating Compressor Schematic [7]", + "texts": [ + " Due to the eccentricity of the crank and shaft in reciprocating compressors during operation, rotary compressors such as the scroll [34, 36] and rolling piston [38] have better vibration characteristics. Nevertheless, there is a need to characterise the vibration profiles of the compressors so as to implement design changes to further reduce vibration. The reciprocating compressor is one of the earliest compressor designs and there are various publications in the literature [7, 39\u201345] pertaining to its vibration analysis. Hiller and Glickman [7] show a working schematic of a typical reciprocating compressor in Figure 2.7. The abbreviations TDC and BDC represents \u2018top dead centre\u2019 and \u2018bottom dead centre\u2019 respectively, which indicates the extent of the piston movement during operation. The reciprocating compressor is a four step process as shown in Figure 2.7. To mitigate excessive vibration, numerous springs and counterweights can be employed to reduce the transmission of vibrations from the moving components to the outer compressor shell [45, 46]. 14 Furthermore, a multi-balancing approach has also been shown to reduce the vibration of the reciprocating compressor [39]. For the rolling piston compressor, the outer compressor shell may be subjected to more severe vibrations due to the orbiting motion of the eccentric roller on the inner surface [46]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004706_el-04657928_document-Figure3.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004706_el-04657928_document-Figure3.6-1.png", + "caption": "Figure 3.6 VTOL propellers location for FW-VTOL geometry", + "texts": [ + "04 for \u03c5vt [61], but other values may be applied depending on the application and stability requirements. The other geometrical parameters of the tails are derived similarly to the wing. However, lower aspect ratios will be preferred during optimization because the structural criterion is dominant over the aerodynamic criterion for these parts [62, 114]. Finally, the fuselage is made of a semi-spherical nose, a cylindrical mid-fuselage housing the batteries and the payload, and a conical rear-fuselage aft of the wing\u2019s trailing edge, as depicted in Figure 3.6. The total fuselage length is the sum of the wing position (with respect to the nose tip) and the tail moment arm. Its maximum diameter is derived from a fineness ratio provided by the designer. Appendix 3.B provides the geometrical relationships for the fuselage. Fixed-wing VTOL The VTOL propellers of a FW-VTOL drone must be located outside the high-turbulence area defined by the diameter of the fixed-wing propellers. Consequently, their distance from the axis of symmetry of the UAV must lie within the following range:( dF W pro 2 + dMR pro 2 + \u03b4pro ) \u2264 yMR pro \u2264 bw 2 (3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003900_e_download_4701_4052-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003900_e_download_4701_4052-Figure4-1.png", + "caption": "Fig. 4 Helicoidal antenna normal mode. a) front view, b) top view, c) profile view.", + "texts": [ + " The dimensions of the helix are designed in wavelength in free space at the center frequency [8]. Fig. 3 Diameter-spacing chart The antenna that is proposed for the network with LoRA technology, which has an approximate area of 10 cm2 for the antenna and the LoRa device is a 5-turn helix on a ground plane, which works in the UHF band, it is expected to have an average gain circumference of 0.4 and a spacing of 0.2 are selected, the other dimensions are obtained from those parameters and are shown in table I, the antenna layout is as shown in figure 4. Table I. Dimensions Of The Helical Antenna Frequency F(MHz) 915 Wavelength (cm) 32.78 Spacing S(cm) 6.55 Diameter D(cm) 4.17 Length L(cm) 32.78 Ground plane diameter Dpt(cm) 8 A simulation stage is developed for the calculated antenna based on the Kraus design. The design results are obtained by simulating the antenna through the (CST) program, the analysis is done over a bandwidth between 900MHz and 930MHz, for coupling using parameter S11 (a suitable value is -10 dB or less), the pattern radiation and gain" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000882_article-file_1157957-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000882_article-file_1157957-Figure8-1.png", + "caption": "Fig. 8. Von Mises stress on the critical section, respectively for the loading type of force couple and for the loading type of", + "texts": [ + "3 have been used as input data for the material of weld yoke. After the defining load and constraints, the solution process has been implemented by linear static structural method. In solution process OptiStruct has been used as solver. Von Mises stress value on the critical area (Fig. 3 and Fig. 4) which is taken into consideration for the theoretical calculations, has been obtained as 241 MPa for the loading type of force couple, while 240 MPa has been obtained for the loading type of moment as shown Fig. 8. The stress on the lower side of the weld yoke where the welding operation is performed, has been ignored because they occur due to lack of freedom. moment Equivalent stress via Von Mises was calculated to include bending and shear stresses on the critical area. By this way, equivalent stress obtained as 237.73 MPa. In this study, for the design of weld yoke, finite element analysis and analytical method are carried out. The result of 241 MPa from the finite element analysis including loading type of force couple, is highly closed to the result of 240 MPa from the finite element analysis including loading type of moment" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004544__39_article-p159.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004544__39_article-p159.pdf-Figure5-1.png", + "caption": "Fig. 5 3D model of the commonly used cardan shaft", + "texts": [ + " The construction of the universal joints allows transferring torque moment between two rotating abaxial shafts. In some cases, this allows axle shift (2). The most commonly used joint is the universal joint shown in Fig. 4. In the motor vehicles are used universal joints for maximal axes deviation 8\u00b0. Special design allows also greater deviation of the axes (5, 6). Kinematic simulation was made using the CAD/CAM/CAE system CATIA V5 on the model of the cardan shaft which contains two universal joints (Fig. 5). Between all connections with bearings, the revolute type of joint and one prismatic type of connection for central cardan shaft was used, which allows adjustment of the relative position between two parts of the cardan shaft through castellated shaft connection. All degrees of freedom were blocked for the frame. (1- flange, 2 \u2013 universal joint, 3 \u2013 cardan shaft, 4- castellated shaft) In the first case, kinematic analysis of the cardan shaft sloped at an angle 15\u00b0, was simulated. The input and output shafts were parallel during analysis as is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.3-1.png", + "caption": "Figure 2.3 : Taylor Vortices (left) and Azimuth waves (right) [53].", + "texts": [ + " Besides,the channel performance coefficient (also called aspect ratio of the radial cylindrical gap) is defined by: \ud835\udf02 = \ud835\udc5f\ud835\udc56 \ud835\udc5f\ud835\udc52 . Based on [51], for low rotor speeds, the flow is steady and laminar (Couette flow). There is a critical Taylor number \ud835\udc47\ud835\udc4e\ud835\udc50\ud835\udc5f corresponding to a critical speed \ud835\udf14\ud835\udc50\ud835\udc5f, for which the torque transmitted to the fluid begins to increase faster, as the rotational speed increases [49]. Above this value, the flow is a Taylor vortex flow and vortices (called Taylor vortices) appear as can be seen in Figure 2.3. These vortices are in an axially centered disk form. Coles et al. [52] described that when further increasing the velocity and exceeding the critical Taylor number to reach a ratio of \ud835\udc47\ud835\udc4e/\ud835\udc47\ud835\udc4e\ud835\udc50\ud835\udc5f = 1.2 with a narrow gap (\ud835\udf02 = 0.95), a wavy mode appears (Figure 2.3) with azimuth waves [53]. Then the number of waves increases with velocity to reach a constant maximum for a range of values of the ratio: 4.5 < \ud835\udc47\ud835\udc4e/\ud835\udc47\ud835\udc4e\ud835\udc50\ud835\udc5f < 25. The critical Taylor number in the case of two co-axial cylinders is determined by [51] as: \ud835\udc47\ud835\udc4e\ud835\udc50\ud835\udc5f = 1700. In a Taylor-Couette flow, [49] focused on three types of flows: Couette, Taylor vortex, and turbulent flows, and provided heat transfer correlations to well define the heat transfer phenomena happening between two co-axial cylinders. For a closed annulus system with a rotating inner cylinder in both laminar and turbulent flow modes without axial flow, [53] proposed the following expression of the global Nusselt number: \ud835\udc41\ud835\udc62\ud835\udc37\u210e = \ud835\udc37\u210e \u210e\ud835\udc5f\ud835\udc60 \ud835\udf06\ud835\udc4e\ud835\udc56\ud835\udc5f (2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001558_9310723_09161363.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001558_9310723_09161363.pdf-Figure12-1.png", + "caption": "Fig. 12. Experimental setup. (a) Structure of auger filling machine. (b) Picture of the auger part.", + "texts": [ + " In this section, experiments were conducted to confirm the validity of the proposed method. The experiments consist of two phases, an abstraction phase and an evaluation phase. In the abstraction phase, the model of RTOB compensator is extracted using experimental data. In the evaluation phase, the RTOB compensator generated in the abstraction phase is applied to the new experimental data, and the compensation accuracy is evaluated. In the experiments, compensation accuracy of the conventional method and the proposed method were compared. The experimental setup is shown in Fig. 12. This equipment is a powder-filling machine. The machine fills various powders by a screw shaft called auger. Fig. 12(b) depicts the auger part. The auger is actuated by a servo motor. In addition, the auger axis is supported by bearings to reduce the fluctuation. The bearings are sealed to avoid contamination of the powder into the actuator. Thereby, friction due to the sealed parts and the bearings exists. The characteristics of the friction are depicted in Fig. 13. In these experiments, the friction model of the auger-filling machine was abstracted for designing the RTOB. Then, time-series data were prepared for abstraction of the compensator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001734_e_download_2825_3901-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001734_e_download_2825_3901-Figure6-1.png", + "caption": "Figure. 6. Strain at 50% of the engine load", + "texts": [ + "55532 x 10-5 mm at 70% of the engine load, 2.51391 x 10-5 mm at 80% of the engine load, 2.4932 x 10-5 mm at 90% of the engine load and 2.38966 x 10-5 mm at 100% of the engine load. The strain is closely related to pulling of an object. The greater value of the strain will increasingly stretch the object and opposite. From the simulation result obtained that the maximum strain is located on the compressor seat as same as stress area with the value equal to 6.26693 x 10-8 and it is at 50% of the engine load (Figure 6). Another strain result of some loads are 6.02663x 10-8 at 60% of the engine load, 5.93051 x 10-8 at 70% of the engine load, 5.8344 x 10-8 at 80% of the engine load, 5.78634 x 10-8 at 90% of the engine load and 5.54604 x 10-8 at full load. Moreover, at the critical stress areas (Figure 7), it shows the twist moment load of the most dominant stress on the shaft between the turbine and compressor seat also some areas of the compressor seat. The most critical area shown by the red color that lies at the end of the compressor seat" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000812_wnload_266261_262421-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000812_wnload_266261_262421-Figure4-1.png", + "caption": "Fig. 4. Stress contour: a \u2013 module 1; b \u2013 module 2", + "texts": [ + " The following elements were noted during the analysis: due to deformations in the system\u2019s elastic domain, it was possible to see the effects of bending teeth in contact, Hertzian contact (local) between the two pairs of teeth in contact, and structural displacements. The stress applied on the part\u2019s maximum and minimum total deformation values are depicted in color. Red and blue in this coloring represent the greatest and minimum deformation values, respectively. The values of the stresses that affect the gears must be known by changing the module. Because it gives a stronger concept of the extent to which the gears can withstand movement, as shown in Fig. 4. As shown in Fig. 4, the value of the stresses in module 1 was 2.13\u00d7108 Pa, but in module 2, the value of the stresses was 1.85 Pa. The confirmation of module 2 is better than the other case because of the lack of stress on its gears. 5. 2. Effect of pressure angle on stress and deformation values The pressure angle is one of the basic variables that change the dimensions of the gears and their engineering structure in terms of their bearing stress and movement. The first type of pressure angle was 14.5 degrees, in which the deformation value was 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000544_le_download_6534_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000544_le_download_6534_pdf-Figure2-1.png", + "caption": "Figure 2 Schematic Circuit on Device Receiver", + "texts": [ + " Transmitter Transmitter is a system in the world of control systems and sensors, this transmitter is a tool used to hold the output signal of the transducer or sensor so that it can be received by the controller. In glue 1 is a schematic circuit for the Transmitter in the Safety System Prototype on the Komatsu PC200-7 Excavator using a Microcontroller: B. Receiver The receiver concept is ubiquitous and applies to all types of receivers in all forms of technology. All receivers can receive anything from the transmitter in the form of electromagnetic waves, electrical signals, sound waves, or sound waves without exception. In figure 2 is the schematic circuit for the receiver in the Safety System Prototype on the Komatsu PC200-7 Excavator using a Microcontroller: In figure 3 and figure 4 are block diagrams of the Transmitter and Receiver of the tool to explain the process that occurs in the prototype of this research tool consisting of 3 things, namely Input, Process, and Output, where each of these three things is very important in making a prototype of this tool. Figure 4 Receiver Block Diagram C. How the Tool Works Pada Excavator Komatsu PC 200-7 Menggunakan Microcontroller\u201d It uses MAX6675 Thermocouple sensor, HY-SRF05 Ultrasonic sensor, RFID Module, Transmitter and Receiver" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004113_.aspx_paperID_130953-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004113_.aspx_paperID_130953-Figure2-1.png", + "caption": "Figure 2. Cross-section of the reflector of parabolic antenna xz-plane.", + "texts": [ + " [2] [5], the thermal deformation of the reflector caused by temperature increase, has effect on the surface accuracy and electrical performance, it impairs performance. Theory of the Parabolic Reflector Antenna The reflector or antenna has two purposes, first they collect power in terms of electrical signals (scintillations) and second, they provide directionality, for propagation of electromagnetic signal [6]. Reflector antennas operate on the principles known long ago from the theory of geometrical optics (GO) [7] [8]. Figure 1 shows an abstraction of the coordinate system of a parabolic antenna while Figure 2 shows the cross section. DOI: 10.4236/ojapps.2024.141014 184 Open Journal of Applied Sciences The parabolic surface of the antenna in Figure 1 is described by: ( )2 4 ,fF F z p a\u03c1\u2032 \u2032\u2212= (1) Here, \u03c1\u2032 is the distance from a point A to the focal point O, where A is the projection of the point R on the reflector surface onto the axis-orthogonal plane (the aperture plane) at the focal point [9] [10]. For a given displacement: \u03c1\u2032 from the axis of the reflector, the point R on the reflector surface is a distance fr away from the focal point O" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003009_17_sm_pdf_SM1977.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003009_17_sm_pdf_SM1977.pdf-Figure4-1.png", + "caption": "Fig. 4. (Color online) Coplanar EWOD devices with Ta2O5 (anodized Ta) as the dielectric. (a) Sessile droplet actuation design, adapted from Yi and Kim,(35) to measure the contact angle change. (b) Two rows of square electrodes (1 \u00d7 1 mm2) for moving droplets side-to-side.", + "texts": [ + " On other samples intended for comparison, silicon oxide and silicon nitride were deposited onto tantalum electrodes at a thickness of 165 nm using PECVD. No dielectric was deposited on the gold-coated ground plates. valve metal oxide (Ta2O5 shown) as an EWOD dielectric. For coplanar EWOD tests, two different sets of electrodes were prepared. The first was to actuate sessile droplets to measure the contact angle changes similarly to that described by Yi and Kim,(35) and the second consisted of two rows of square electrodes to move droplets side-to-side with the sequential activation of neighboring electrodes (Fig. 4). The coplanar EWOD device fabrication began with 500 nm of sputtered tantalum on glass slides. The electrodes were patterned by photolithography with an AZ 4620 photoresist (6.2 \u00b5m thick, MicroChemicals GmbH, Germany) and dry-etched by RIE (SF6 gas, 40 mTorr, 35 V DC bias, and 115 W forward RF power). Before anodization, the photoresist was stripped using a solvent wash and H2SO4:H2O2 (4:1) cleaning step. Tantalum pentoxide was anodized under the same conditions as the parallel-plate samples. A hydrophobic layer of Teflon AF 2400\u00ae (35 nm) was spin-coated onto all of the samples and patterned by lift-off to expose the bare metal for electrical contact" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004367_5_phys-2022-0223_pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004367_5_phys-2022-0223_pdf-Figure12-1.png", + "caption": "Figure 12: Trapezoidal magnetic pole structure and original structure motor.", + "texts": [ + " In order to further verify the validity of the simulation results, a prototype rotor with trapezoidal magnetic pole structure was made for testing. According to the simulation results above, a trapezoidal magnetic pole structure magnetization fixture with a magnetic pole skew angle \u03b8sk = 30\u00b0 is made, and the magnet ring is magnetized. Figure 11 shows the trapezoidal magnetic pole structure magnetization fixture. The trapezoidal magnetic pole structure magnet ring is installed and tested, as shown in Figure 12. The one with the white fan in the figure is the trapezoidal magnetic pole structure rotor, the red fan is the original structure rotor, and the two rotors use the same stator. The cogging torque test device is shown in Figure 13. The test results are shown in Figure 14. Using the trapezoidal magnetic pole structure, the cogging torque is significantly reduced, and the peak-to-peak value is reduced from 77.64 to 9.02mNm, and the reduction is 88.4%, which is close to the simulation result of 91.3%" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004336_s-3941981_latest.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004336_s-3941981_latest.pdf-Figure9-1.png", + "caption": "Fig. 9: Magnetic flux density output fields from FEniCSx and Ansys Maxwell for no-load and 280A current cases. A qualitative comparison shows agreement in overall field trends, with numerical discrepancies at higher load cases. Despite qualitative agreement between the 280A cases between FEniCSx and Ansys Maxwell, we see a 14% error in the output torque.", + "texts": [ + "com/LSDOlab/modopt Geometric Design of Electric Motors Using Adjoint-based Shape Optimization 15 conduct a grid independence study to determine reasonable mesh sizing for the geometry. Finally, we demonstrate design optimization results for a motor within an electric aircraft system. All results are generated for a 12-pole, 36-slot radial flux permanent magnet synchronous motor; an example of the geometry is shown in Fig 8. 4.1 Model Validation The FEniCSx electromagnetic solver is verified using the Ansys Maxwell software(Ansys, Accessed 03/20/2021). We begin with a qualitative comparison of the output magnetic flux density fields, shown in Fig 9. The two cases considered here are the no-load (no current) case and the 280A current amplitude case. We see qualitative similarities in the no-load flux density field distributions between the FEniCSx solver in Figure 9a and Ansys Maxwell in Figure 9b. The flux field dissipates in a similar fashion around the boundaries and between stator teeth, and the flux density concentration around the magnets indicates that the modeling approach using Eq 8 for the magnets is accurate. However, higher saturation values of the flux density exist around the magnets in the Ansys Maxwell results. Comparing Figures 9c and 9d, we see similar trends for the 280A load case, with larger discrepancies in the saturation areas. To assess the error in the magnetic flux density fields shown in Figure 9, the output torque from the FEniCSx solution and the Ansys Maxwell solution are compared. A no-load case produces no torque; therefore, we compare the output torque using an additional load case of 100A. The results are shown in 1. We see a larger torque error as the current amplitude increases; the error does not exceed 14% within the tested cases. We believe the sources of error in these results originate from the nonlinear permeability fitting within the motor core and the nodal evaluation approach for calculating the torque from Eq", + " The results indicate the feasibility and success of an adjoint-based motor design optimization approach; we see improvements in the overall design, and the shape optimization results show that efficient exploration of the full design space is possible using adjoint-based optimization. Future development of this work has two distinct avenues: improving the modeling of the physics and addressing solver ill-conditioning due to large geometric deformations. The first area of future work addresses the shortcomings of the motor analysis model. The torque error shown in Table 1 and flux field qualitative differences in Figure 9 can be attributed to the permeability model and torque computation approach. Alteration to the permeability model is required, as the curve fit visualized in Figure 2 deviates from the data in the flux-density-magnitude range expected within the motor air-gap. In addition, we assume the direction of the air-gap flux density is purely radial. A higher fidelity method, such as virtual work or the Maxwell stress tensor, is more suitable to calculate torque using the FEM field solution. The current methodology also does not utilize periodicity, a key property of electric motor operation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000056_tation-pdf-url_54247-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000056_tation-pdf-url_54247-Figure5-1.png", + "caption": "Figure 5. A step-climbing strategy for a five-wheeled wheelchair.", + "texts": [ + " The links AC and BD are made of aluminum bars with constant lengths while link AB is composed by cylinder of a linear actuator whose length can be varied by motor actuation. As the length of AB changes, the overall link configuration changes, which results in the change of the location of the active-caster. As the linear actuator extends as shown in Figure 4(b), the active-caster moves backward and the active-caster gets closer to the wheelchair and simultaneously pushes the ground when the linear actuator shrinks as in Figure 4(c). The series of motions performed by the wheelchair is shown in Figure 5. First, the wheelchair stops in front of the step (Figure 5(a)). Next, the wheelchair performs a static wheelie motion and the front casters are hovered from the ground (Figure 5(b)). Then, the wheelchair moves forward by maintaining the static wheelie and the front casters reaches on the top of the Figure 4. A reconfigurable link mechanism and its motions. (a) Link configuration. (b) When linear actuator extends. (c) When linear actuator shrinks. Five-Wheeled Wheelchair with an Add-On Mechanism and Its Semiautomatic... http://dx.doi.org/10.5772/67558 31 step (Figure 5(c)). Note that the center of gravity locates in the area defined by the two large wheels and the drive wheel; therefore, a wheelchair user can move forward with maintaining the posture of the static wheelie without a balancing control. After the front casters climbing, the large wheels are lifted by pushing down the active-caster to the ground (Figure 5(d)). By the forward motion, the large wheels pass over the step (Figure 5(e)). After the large wheels climbing, the wheelchair performs a static wheelie motion on the step (Figure 5(f)). After the completion of the static wheelie, large wheels are locked by the braking mechanism of the wheelchair. By coordinated motions of the drive wheel and the linear actuator (Figure 5(g)), the drive wheel climbs up the wall of a step and reaches to the top. Thus, a series of stepclimbing sequence is completed (Figure 5(h)). We then explain the step-descending strategy in which a user approaches a step from the front side of the wheelchair. To avoid a risk of falling from the top of a step to the ground, we apply the static wheelie motion in the step-descending process as well. Figure 6 shows the Physical Disabilities - Therapeutic Implications32 moves to the edge of the step (Figure 6(b)). After applying gentle brake to the large wheels of a wheelchair for reducing an impact of landing on the ground, the wheelchair starts to descend a step by maintaining the static wheelie situation (Figure 6(c))", + "5772/67558 37 We propose an add-on electric drive system with a reconfigurable link mechanism for a manual wheelchair. We also propose a semiautomatic system for reducing the user effort to operate a wheelchair to surmount a step. To verify the availability of the prototype wheelchair with the semiautomatic system, we tested the step-climbing and -descending processes of the wheelchair using the prototype. In the experiment, we tested the step-climbing and -descend- ing of a 100 mm step. The experimental results are shown in Figure 14. In Figure 14(a)\u2013(h), each snapshot of the wheelchair corresponds to Figure 5(a)\u2013(h). The experiments were performed by using the semiautomatic operating system. First, the wheelchair is stopped in front of the step by the user operation using joystick (Figure 14(a)). After the user commanded to start the semiautomatic operation, LRFs measured the step height and the distance to the step. Then, the wheelchair approached to the step by performing a static wheelie motion with hovering the front casters not to collide with a step (Figure 14(b)). After the large wheels contact the step edge, the wheelchair climbed the step by pushing the active-caster down the ground to lift up the large wheels with maintaining the contacts between the large wheels and the step edge (Figure 14(c)\u2013(e))" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.21-1.png", + "caption": "Figure 4.21: I.S-bit stage transfer function with capacitor lllislnatch.", + "texts": [ + "26) In addition to the thermal noise, the op amp noise also contributes to the nonidealities. The op amp noise is dependent on the circuit topology and can be superimposed on the thermal noise once the op amp circuit is decided. Capacitance mismatch is another major error source in pipelined ADCs, which can affect the linearity directly. In the transfer function of 1.5-bit stage as shown in Figure. 4.5, If the capacitors Gsand GF are not equal, then an error proportional to the mismatch is generated in the residue output as shown in Figure 4.21 with the transfer function of 17 = 1( . 6.G + Gs + GF _ D . . 11: . 6.G + Gs Vout Yin C F ~ ref C F 67 (4.27) ATTENTION: The Singapore Copyright Act applies to the use of this document. Nanyang Technological University Library For an N-bit ADC, for this error should be less than half LSB of the following stage, the capacitance mismatch should satisfies: (4.28) In most low-to-medium resolution ADCs, capacitor sizes are not limited by thermal noise but by matching. Like the finite gain effect, the requirement on capacitance matching is also scaled down with the pipeline and both errors can be compensated by calibration techniques" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003775_f_version_1632811037-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003775_f_version_1632811037-Figure6-1.png", + "caption": "Figure 6. Final geometry of the unit cell uses cases in a FSS structure obtained by applying the proposed design framework. (The final values of the decision variables for each of the unit cell use cases are listed in Table 3. The dark red color denotes the metal surface (copper) of the unit cell; the green color indicates the dielectric substrate (FR-4) of the unit cell.) (a) UC1, (b) UC2, and (c) UC3.", + "texts": [ + "8 GHz}) is the system metric (magnitude of the reflection coefficient) of the designed EM structure at the specific frequencies of interest, \u2022 TdB is the threshold criterion for an acceptable solution of the optimization problem provided by the members of the population (in our case TdB=\u221210 dB), \u2022 \u03a8 is a positive number (multiplying factor in the objective function) that is triggered when the obtained solution is above the threshold criterion, and \u2022 OF is the objective function of the optimization problem. Figure 6 illustrates the final design solution of the unit cell for each of the use cases that are obtained by the proposed design framework and the applied optimization process. Moreover, Table 3 lists the final values of the decision variables that fully describe the geometry for each of the presented unit cell use case of Figure 6. In order to design an FSS structure suitable for RF EH applications, the performance results of the unit cell use cases should be assessed. Figure 7 displays the comparative results of the S11 magnitude of the reflection coefficient (final values of the system metric extracted from the obtained EM model using the proposed design framework and the optimization process of Figure 2) for each of the unit cell use cases. From the presented results, we can conclude that the first use case of the unit cell design achieves the best performance in terms of its reflection coefficient" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000087_5_secm-2014-0048_pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000087_5_secm-2014-0048_pdf-Figure6-1.png", + "caption": "Figure 6 Process principle with resulting reinforcement types: (A)\u00a0continuous winding and (B) braiding.", + "texts": [ + " For this, no continuous industrial process is known, so a concept is elaborated and presented in this paper. In this concept, established laydown processes are combined with the state-of-the-art infusion processes to form a production arrangement. This arrangement also contains a novel device for the continuous preforming of the profiled geometry, which is validated experimentally on a laboratory scale. By eliminating the manual process steps and utilizing the highly productive and automated preforming processes such as braiding or continuous winding (Figure\u00a06), a significant reduction of part cost combined with an enhancement of the reproducibility of the manufacturing results is aspired. Figure 7 depicts one of the currently two braiding machines in service at the ILK. This so-called axial braider features yarn carriers oriented in parallel to the mandrel axis. It provides 72 carriers on the outer track and 48 carriers on the inner track (Type: KFh 1/72/48-100). The second braider is a 288-carrier radial braiding machine, where the carriers are oriented perpendicular to the mandrel axis (Type: RF/288-100)", + " The axial braider was chosen for depiction due to its smaller dimensions. Dependent on the carrier setup, braiding machines allow a variation in the textile pattern up to the creation of unidirectionally oriented layers without interweaves. Extensive modifications of the 288-carrier braiding machine permit an additional variety of the possible braiding patterns. The choice of those patterns influences the part performance, since the resulting reinforcement architectures differ in their characteristics. Unidirectional reinforcement (Figure 6A) leads to very high mechanical properties. This can be attributed to a low level of fiber undulation. Bidirectional reinforcement obtained by braiding usually exhibits a textile binding with fiber undulation and interlocking of fibers (Figure 6B). By increasing the number of weave points, the fiber undulation in the reinforcement layer increases. This leads to a significant decrease in stiffness and strength properties but an increase in the elongation at break and damage tolerance [17, 18]. This allows for a modification of mechanical layer characteristics without a negative impact on the productivity of the continuous process, since no adjustment of braiding speed was necessary when modifying the braiding pattern (compare section 4.1)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001612_jassp.2016.73.79.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001612_jassp.2016.73.79.pdf-Figure4-1.png", + "caption": "Fig. 4. Flexure-tip needle design. The nitinol wires that comprise the flexure joint bend at the gap between the needle shaft and the tip as forces are applied to the bevel tip by tissue (Swaney et al., 2013)", + "texts": [ + " (2011) developed a flexible probe potentially capable of threedimensional steering in soft tissue inspired by natureovipositor of a Giant Ichneumon wasp (Fig. 2). In experimental studies such needles were moved with different levels of bias (Fig. 3). Positioning accuracy of the needle tip was 0.68\u00b11.45 mm. Swaney et al. (2013) proposed to improve the controllability of a needle and to increase the curvature of the trajectory by giving a degree of freedom to asymmetrical tip of the needle placing nitinol wires along the needle (Fig. 4). A degree of freedom of the tip allows increasing the angle of deviation, therefore increasing maneuverability of the needle and its controllability resulting in potentially less tissue damage. Podder et al. (2010) proposed another construction of a steerable needle with nitinol wires on its outer side in the special clamping sleeve (Fig. 5). This construction provides a direct contact of the tissue with wires which have the property of shape memory with a temperature increase. To create a robotic system for brachytherapy it is important not only to develop special needles and optimal insertion trajectory, but also to establish the methods to control the needle behavior in the body during brachytherapy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003158_23_ms-14-33-2023.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003158_23_ms-14-33-2023.pdf-Figure3-1.png", + "caption": "Figure 3. Outline of SSPGT.", + "texts": [ + " The single-stage planetary gear train is connected between the turbine rotor and hydraulic pump. The wind power is extracted by the turbine blades, and it is available at the turbine rotor in the form of mechanical energy. The same mechanical power is transmitted to run the hydraulic pump using the single-stage planetary gear train. Generally, it is a three-stage gear train, i.e., planetary stage and two more parallel stages used in wind turbines. In this study, only the planetary stage of the gear train is coupled with the power hydraulic system (refer to Fig. 3) (Tsai et al., 2010). From Fig. 3, three planet gears are engaged with a ring gear and a sun gear. The function of the carrier is to grip all planet gears. The planet gears work on two kinematic modes, such that it revolves around the sun gear and auto-rotates around its own axis. The operating mode of the planetary gear is dual inputs (primary input is angular speed of the carrier \u03c9cg and secondary input is angular speed of the ring gear \u03c9rg) and one output, i.e., the angular speed of the sun gear (\u03c9sg). During modeling of the system, it is considered that the viscous friction loss exists at the couplings between the shaft of the turbine rotor and the input shaft of the SSPGT or shaft of the carrier gear, and between the output shaft of the SSPGT or sun gear shaft and hydraulic pump shaft" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure34-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure34-1.png", + "caption": "Figure 34 P-POD Mk. IV Top Panel", + "texts": [ + "150 inches in order to accommodate through holes on the Bracket that are properly centered, as the previous design had off center through-holes. The two ribs running down the length of Page 51 the panel are currently sized to accommodate the mounting holes with both adequate width and thickness. These ribs were increased for Rev. E but are suspected to be excessive for the design intent of the Top Panel. Additionally, as discussed in Chapter II, a venting hole array designed to shield EMI/RFI was added as a non-standard mission specific case. The resulting design is shown below in Figure 34. The panel has been reduced to the minimum it needs to be. The ribs are now considerably thinner, but wide enough to accommodate a non-structural 4-40 screw for harness routing if needed. The Page 52 FEA was conducted, while hand calculations were used to determine the strength of the fastener through-holes. The finite element model used a symmetric constraint in order to reduce solving time, which solves a mirror image of the model across the centerline. All other edges were fixed. The Top Panel was subjected to the Y-axis load case, applied at the panel rails" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure5-1.png", + "caption": "Figure 5: Maximum deformation 33.78 mm in -x at 120 seconds.", + "texts": [ + " 36 iv Nomenclature \ud835\udc3a\ud835\udc5b Shear Modulus \ud835\udc3e\ud835\udc5b Bulk Modulus \ud835\udf0f\ud835\udc5b Relaxation time \ud835\udc62\ud835\udc56\ud835\udc5b Input displacement \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 Output displacement PRBM Pseudo-rigid-body model \ud835\udc58 Stiffness of PRBM \ud835\udc38 Elastic Modulus \ud835\udc61 Smallest width of compliant joint \ud835\udc45 Radius of compliant joint cutout \ud835\udc4f Thickness of compliant joint \ud835\udf03 Angle of deflection of complaint mechanism \ud835\udefe Drone landing slope angle \ud835\udefe\ud835\udc5f Characteristic radius factor \ud835\udc40 Moment imposed on compliant joint \ud835\udc3c Second area moment of inertia \ud835\udc50 Perpendicular distance from neutral point to furthest point on cross section v Figure 1: Mechanical model comprising of Hooke\u2019s element and \u201cn\u201d Maxwell Elements [4]. .... 3 Figure 2: Load and Boundary Conditions of 4 Bar Mechanism. ................................................... 4 Figure 3: Deflection distribution over time. .................................................................................. 4 Figure 4: Compliant 4 bar mechanism. .......................................................................................... 5 Figure 5: Maximum deformation 33.78 mm in -x at 120 seconds. ............................................... 7 Figure 6: Deformation profile over 2000 seconds of 4 bar compliant mechanism. ...................... 7 Figure 7: Modal analysis of viscoelastic and non-viscoelastic material. ....................................... 8 Figure 8: Response PSD results for viscoelastic and non-viscoelastic materials. ......................... 9 Figure 9: Deformed shapes of optimized structures for the inverter. ...." + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.4-1.png", + "caption": "Figure 6.4: RV Prototype Cyliner-Rotor Assembly Cross-Section", + "texts": [ + " Similar to the analysis by Yanagisawa et al. [27] for the rolling piston, these mounts are represented by a damping torque and support torque and assumed to be proportional to the twist rate and angle of twist respectively. The equation of motion for the compressor shell housing is formulated as shown in Equation (6.17). 100 \ud835\udc3c\u210e\ud703\u0308\u210e = \ud835\udc47\ud835\udc57\ud835\udc4f\ud835\udc5f,\ud835\udc5f + \ud835\udc47\ud835\udc57\ud835\udc4f\ud835\udc5f,\ud835\udc50 + \ud835\udc47\ud835\udc51 \u2212 \ud835\udc47\ud835\udc60\ud835\udc62\ud835\udc5d\ud835\udc5d \u2212 \ud835\udc47\ud835\udc51\ud835\udc4e\ud835\udc5a\ud835\udc5d (6.17) where \ud835\udc47\ud835\udc60\ud835\udc62\ud835\udc5d\ud835\udc5d = \ud835\udc36\ud835\udc60\ud835\udc62\ud835\udc5d\ud835\udc5d\ud703\u210e (6.18) \ud835\udc47\ud835\udc51\ud835\udc4e\ud835\udc5a\ud835\udc5d = \ud835\udc36\ud835\udc51\ud835\udc4e\ud835\udc5a\ud835\udc5d\ud703\u0307\u210e (6.19) For the RV compressor prototype discussed in Chapter 3, the vane is attached to the cylinder as shown in Figure 6.4 and thus, Equation (6.11) shall be adapted for use in this section. Due to the absence of the bush component, the generalised coordinates for the bush \u03b8b can be omitted from the dynamics equation. The equation of motion describing the cylinderrotor assembly is presented in Equation (6.20). \ud835\udc3c\ud835\udc50\ud703\u0308\ud835\udc50 = \ud835\udc47\ud835\udc5a + \ud835\udc47\ud835\udc54 \u2212 \ud835\udc51\ud703\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 (\ud835\udc3c\ud835\udc5f\ud703\u0308\ud835\udc5f) \u2212 \ud835\udc47\ud835\udc53 (6.20) As the cylinder is the main driving component, the rotation angle of the rotor \u03b8r is expressed in terms of the cylinder rotation angle as shown in Equation (6.21) and after rearrangement, the new equation of motion is depicted in Equation (6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003388_O201611639884145.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003388_O201611639884145.pdf-Figure4-1.png", + "caption": "Fig. 4. Pictures of inkjet-printed origami antenna.", + "texts": [], + "surrounding_texts": [ + "\ub3d9\uc791 \uc8fc\ud30c\uc218\ub97c \ub098\ud0c0\ub0b4\uba70, \uac01\uac01 2.13 GHz, 1.85 GHz, 1.62 GHz\uc5d0\uc11c \ub3d9\uc791\ud55c\ub2e4. \ub530\ub77c\uc11c \uc81c\uc548\ub41c \uc548\ud14c\ub098\ub294 \uc801\uc0c9\uc73c\ub85c \ud45c \uc2dc\ub41c \ubd80\ubd84\uc758 \uae38\uc774\uac00 16 mm\ub85c \uc124\uacc4\ub418\uc5c8\ub2e4. EM \uc2dc\ubbac\ub808\uc774 \uc158\uc740 Finite-Element Method(FEM) \ubc29\uc2dd\uc758 ANSYS HighFrequency Structure Simulator(HFSS)\ub97c \uc0ac\uc6a9\ud558\uc600\ub2e4. \uadf8\ub9bc 3(a)\ub294 \ub2e4\uc774\ud3f4 \uc0c1\ud0dc, \uadf8\ub9bc 3(b)\ub294 \ub8e8\ud504 \uc0c1\ud0dc\uc77c \ub54c \uc758 \uc804\ub958 \ubd84\ud3ec\ub3c4\uc774\ub2e4. \uc774\ub97c \ud1b5\ud574 \uc81c\uc548\ub41c \uc548\ud14c\ub098\uac00 \uac01\uac01 \ubc18 \ud30c\uc7a5(\u03bb/2) \ub2e4\uc774\ud3f4, \ud55c \ud30c\uc7a5(1\u03bb) \ub8e8\ud504 \uc548\ud14c\ub098\ub85c \ub3d9\uc791\ud558\ub294 \uac83\uc744 \ud655\uc778\ud560 \uc218 \uc788\ub2e4. \u2162. \uc81c\uc791 \ubc0f \uce21\uc815\uacb0\uacfc \uc81c\uc548\ub41c \uc885\uc774\uc811\uae30 \ubc29\uc2dd\uc758 \uc548\ud14c\ub098\ub294 \uadf8\ub9bc 4\uc5d0\uc11c \ubcf4\uc774\ub294 \uac83\uacfc \uac19\uc774 0.254 mm\uc758 \ub450\uaed8\ub97c \uac16\ub294 Kodak\uc0ac\uc758 \uc885\uc774 \ud544\ub984 \uc704\uc5d0 \uc804\ub3c4\uc131 \uc789\ud06c\ub97c \uc778\uc1c4\ud558\ub294 \ubc29\uc2dd\uc744 \ud1b5\ud574 \uc81c\uc791\ub41c\ub2e4. \uc804 \ub3c4\uc131 \uc789\ud06c\ub294 Novacentrix\uc0ac\uc758 JS-B25P \uc740\ub098\ub178\uc785\uc790\uc789\ud06c \ubaa8 \ub378[12]\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, Epson\uc0ac\uc758 WF-7011 \ud648 \ud504\ub9b0\ud130\ub85c \uc778\uc1c4\ub418\uc5c8\ub2e4. JS-B25P \uc740\ub098\ub178\uc785\uc790 \uc789\ud06c\ub294 25 Ag wt %\ub97c \ud568\uc720\ud558\uace0 \uc788\uc73c\uba70, \uc810\uc131\uc740 5cP\uc774\ub2e4. \ub610\ud55c, \uc804\ub3c4\uc131 \uc789\ud06c\uc758 \ud45c\uba74 \uc800\ud56d\uc740 60 m\u2126/square\uc774\ub2e4. \uae30\ud310\uc774 \ub418\ub294 \uc885\uc774 \ud544\ub984\uc758 \uc804\uae30\uc801 \ud2b9\uc131\uc740 \uc6d0\ud615 \uacf5\uc9c4\uae30(ring resonator)\ub97c \ud1b5\ud558\uc5ec \ucd94\ucd9c \ub418\uc5c8\ub2e4. \uc885\uc774 \ud544\ub984\uc758 \uc720\uc804\uc728(\u03b5r)\uacfc \uc720\uc804\uc190\uc2e4(tan\u03b4)\uc740 \uac01 \uac01 2.85, 0.05\uc774\ub2e4. \uc885\uc774 \ud544\ub984\uc704\uc5d0 \uc804\ub3c4\uc131 \ud328\ud134\uc744 \uc778\uc1c4\ud55c \ud6c4\uc5d0\ub294 JEIO tech\uc0ac\uc758 ON-22GW \uc624\ube10\uc744 \ud1b5\ud574 180\u2103\uc758 \uc628 \ub3c4\uc5d0\uc11c 10\ubd84\uac04\uc758 \uc18c\uacb0(sintering) \uacfc\uc815\uc744 \uc9c4\ud589\ud558\uc600\ub2e4[13]. \ub2e4\uc774\ud3f4 \uc548\ud14c\ub098\uc640 CPW(Coplanar Waveguide)\uc758 \uc591\ucabd\uc73c \ub85c \uade0\ud615\uc7a1\ud78c \uc2e0\ud638(balanced signal)\ub97c \uc804\ub2ec\ud558\uae30 \uc704\ud574 \ubc1c\ub8ec (balun)\uc744 \uc0ac\uc6a9\ud558\uc600\ub2e4. \uc81c\uc548\ub41c \uc548\ud14c\ub098\uc5d0\uc11c \uc0ac\uc6a9\ub41c \ubc1c\ub8ec\uc740 MACOM\uc0ac\uc758 MABA-009822-715254\uc774\uba70, 4.5 MHz\uff5e3 GHz \uae4c\uc9c0 RF 1:1 \uc804\uc1a1\uc120\ub85c \ubcc0\ud658\uae30\ub85c \uc0ac\uc6a9\ub41c\ub2e4. 50 \u2126 CPW\uc758 \ub2e4\uc774\ud3f4 \uc0c1\ud0dc\uc640 \ub8e8\ud504 \uc0c1\ud0dc\ub85c \ubcc0\ud658 \uac00\ub2a5\ud55c \uc885\uc774\uc811\uae30 \ubc29\uc2dd\uc758 \uc885\uc774 \uc548\ud14c\ub098 \uadf8\ub9bc 5. EPSON WF-7011 \ud504\ub9b0\ud130\ub97c \uc774\uc6a9\ud55c \uc81c\uc548\ub41c \uc548\ud14c\ub098 \uc758 \uc778\uc1c4\ubaa8\uc2b5 Fig. 5. Printing the propesed antenna on photo paper using EPSON WF-7011. \ud3ed\uacfc \uac2d\uc740 \uac01\uac01 2 mm, 0.25 mm\ub85c\uc81c\uc791\ub418\uc5c8\ub2e4. \ub610\ud55c, CPW \uc758 \ubc18\ub300\ucabd\uc5d0\ub294 Sub-Miniature version A(SMA) \ucee4\ub125\ud130\ub97c \uc5f0\uacb0\ud558\uc600\ub2e4. \ubc1c\ub8ec\uacfc SMA \ucee4\ub125\ud130\ub97c \uc5f0\uacb0\ud558\ub294\ub370 \uc788\uc5b4 \ub0a9 \ub55c\uc744 \ud558\uba74 \uc885\uc774 \ud544\ub984\uacfc \uc804\ub3c4\uc131 \uc789\ud06c\uc5d0 \uc2ec\uac01\ud55c \uc190\uc0c1\uc774 \uac00 \ud574\uc9c0\uae30 \ub54c\ubb38\uc5d0 silver epoxy\ub97c \uc774\uc6a9\ud558\uc5ec \ubc1c\ub8ec\uacfc SMA \ucee4\ub125 \ud130\ub97c \uc885\uc774 \uc704\uc5d0 \uc81c\uc791\ud558\uc600\ub2e4. \ubcf8 \ub17c\ubb38\uc5d0\uc11c \uc0ac\uc6a9\ub41c \uc885\uc774 \ud544\ub984\uc740 \ud45c\uba74\uc774 \ucf54\ud305\ucc98\ub9ac\ub418\uc5b4 \uc788\uae30 \ub54c\ubb38\uc5d0 \ucd94\uac00\uc801\uc778 \ucf54\ud305 \ucc98\ub9ac \uc5c6\uc774 \uc789\ud06c\uc82f \ud504\ub9b0\ud305 \ud560 \uc218 \uc788\uace0, \uc778\uc1c4 \ud488\uc9c8\ub3c4\uc6b0\uc218\ud558\ub2e4. \ud558\uc9c0\ub9cc \uc885\uc774 \ud544\ub984\uc758 \ucf54\ud305 \ubd80\ubd84\uc740 \uc18c\uacb0 \uacfc\uc815\uc744 \uac70\uce58\uac8c \ub418\uba74 \ub531\ub531\ud558\uac8c \ub418\uc5b4 \uc885\uc774 \ud544 \ub984\uc744 \uc811\uc5c8\uc744 \ub54c \uc811\ud78c \ubd80\ubd84\uc5d0 \uae68\uc9d0 \ud604\uc0c1\uc774 \ubc1c\uc0dd\ud558\uac8c \ub41c\ub2e4. \uadf8\ub9bc 6(a)\uff5e(c)\ub294 \uac01\uac01 \uc811\uc9c0 \uc54a\uc558\uc744 \ub54c, \uc811\uc5c8\uc744 \ub54c, \uc811\uc5c8\ub2e4 \ud3c8\uc744 \ub54c\uc758 \uc885\uc774 \ud544\ub984\uc758 \ud45c\uba74\uc744 \ud604\ubbf8\uacbd\uc744 \ud1b5\ud574 \uad00\ucc30\ud55c \uc0ac \uc9c4\uc774\uba70, \uc885\uc774 \ud544\ub984\uacfc \uc789\ud06c\uac00 \uac08\ub77c\uc9c0\ub294 \ud604\uc0c1\uc744 \uad00\ucc30\ud560 \uc218 \uc788\ub2e4. \uc774 \ubb38\uc81c\ub97c \ud574\uacb0\ud558\uae30 \uc704\ud574 \uc561\uccb4\uae08\uc18d \uc911 \ud558\ub098\uc778 EGaIn\uc744 \uc0ac\uc6a9\ud558\uc600\ub2e4[14]. \uadf8\ub9bc 6(d)\ucc98\ub7fc \uac08\ub77c\uc9c0\ub294 \ubd80\ubd84\uc5d0 EGaIn\uc73c\ub85c \ucc98\ub9ac\ud574 \uc8fc\uc5c8\ub2e4. \ub530\ub77c\uc11c \uc885\uc774\ub97c \uc811\uc5c8\uc744 \ub54c\uc5d0\ub3c4 \ub3c4\uccb4 \uc2e0\ud638\uac00 \uc5f0\uacb0\ub428\uc73c\ub85c\uc368 \uc885\uc774 \ud544\ub984\uacfc \uc789\ud06c\uc758 \uac08\ub77c\uc9c0\ub294 \ubb38\uc81c\ub97c \ud574\uacb0\ud560 \uc218 \uc788\uc74c\uc744 \uadf8\ub9bc 6(e)\uc640 (f)\ub97c \ud1b5\ud574 \ud655\uc778\ud560 \uc218 \uc788\ub2e4. \ud55c\ud3b8, \uad6c\ub9ac \ud14c\uc774\ud504\ub97c \uc5f0\uacb0 \ubd80\uc704\uc5d0 \uc811\ucc29\ud568\uc73c\ub85c\uc368 \uc789\ud06c\uc758 \uade0\uc5f4 \ubb38\uc81c\ub97c \ud574\uacb0\ud560 \uc218\ub3c4 \uc788\ub2e4. \uadf8\ub9bc 7(a)\ub294 \uc81c\uc548\ud55c \uc885\uc774\uc811\uae30 \uc548\ud14c\ub098\uc758 \ubc18\uc0ac\uacc4\uc218\ub97c \uc2dc \ubbac\ub808\uc774\uc158\uacfc \uce21\uc815\uacb0\uacfc\ub97c \ud1b5\ud574 \ube44\uad50\ud55c \uadf8\ub9bc\uc774\ub2e4. \ub2e4\uc774\ud3f4 \ubaa8 \ub4dc\ub294 \uc885\uc774\ub97c \uc811\uc9c0 \uc54a\uc558\uc744 \ub54c \uce21\uc815\ub418\uc5c8\uc73c\uba70, \ub8e8\ud504 \uc0c1\ud0dc\ub294 \uc815\uc0ac\uac01\ud615 \ubaa8\uc591\uc73c\ub85c \uc885\uc774\ub97c \uc811\uc5c8\uc744 \ub54c \uce21\uc815\ub418\uc5c8\ub2e4. \uce21\uc815\uacb0 (a) (b) (c) (d) (e) (f) \uadf8\ub9bc 6. \uc81c\uc548\ub41c \uc885\uc774\uc811\uae30 \uc548\ud14c\ub098\uc758 \uc811\ud788\ub294 \ubd80\ubd84\uc744 \ud604\ubbf8 \uacbd\uc73c\ub85c \uad00\ucc30\ud55c \ubaa8\uc2b5, (a) \uc885\uc774\ub97c \uc811\uae30 \uc804 \ubaa8\uc2b5, (b) \uc885\uc774\ub97c \uc811\uc5c8\uc744 \ub54c \ubaa8\uc2b5, (c) \uc885\uc774\ub97c \uc811\uc5c8\ub2e4 \ud3b8 \ud6c4\uc5d0 \uac08\ub77c\uc9c0\ub294 \ud604\uc0c1\uc774 \ubc1c\uc0dd\ud55c \ubaa8\uc2b5, (d) \uac08\ub77c \uc9c0\ub294 \ubd80\ubd84\uc5d0 EGain \ucc98\ub9ac\ud55c \ubaa8\uc2b5, (e) EGain \ucc98\ub9ac \ud6c4 \uc885\uc774\ub97c \uc811\uc5c8\uc744 \ub54c \ubaa8\uc2b5, (f) EGaIn \ucc98\ub9ac \ud6c4 \uc885 \uc774\ub97c \uc811\uc5c8\ub2e4 \ud3b8 \ud6c4\uc758 \ubaa8\uc2b5 Fig. 6. Magnified pictures of folded parts of proposed origami antenna. (a) conductive line without EGaIn before folding paper, (b) conductive line without EGaIn when paper is folded, (c) conductive line without EGaIn after unfolding folded paper, (d) conductive line with EGaIn before folding paper, (e) conductive line with EGaIn when paper is folded, (f) conductive line with EGaIn after unfolding folded paper. \uacfc\ub294 Anritsu\uc758 MS2038C \ubca1\ud130 \ub124\ud2b8\uc6cc\ud06c \ubd84\uc11d\uae30(vector network analyzer)\ub97c \ud1b5\ud574 \uce21\uc815\ub418\uc5c8\ub2e4. \ub2e4\uc774\ud3f4 \uc0c1\ud0dc\uc640 \ub8e8\ud504 \uc0c1\ud0dc\uc77c \ub54c\uc758 \ub3d9\uc791 \uc8fc\ud30c\uc218\ub294 \uac01\uac01 1.81 GHz, 1.85 GHz\uc778 \uac83\uc744 \ud655\uc778\ud560 \uc218 \uc788\ub2e4. \uc2dc\ubbac\ub808\uc774\uc158\uacfc \uc2e4\uc81c \uce21\uc815 \uc0ac\uc774\uc758 \uc624 \ucc28\ub294 balun\uc758 \uae30\uc0dd\uc800\ud56d \uc131\ubd84\uc5d0\uc11c \ubc1c\uc0dd\ub41c \uac83\uc73c\ub85c \uc608\uc0c1\ub41c \ub2e4. \uadf8\ub9bc 7(b)\ub294 \uc81c\uc548\ub41c \uc548\ud14c\ub098\uc758 \ub2e4\uc774\ud3f4 \uc0c1\ud0dc\uc640 \ub8e8\ud504 \uc0c1 \ud0dc\uc77c \ub54c \uac01\uac01\uc758 XZ \ud3c9\uba74\uc0c1\uc758 \ubc29\uc0ac\ud328\ud134\uc744 \ub098\ud0c0\ub0b8\ub2e4. \ub2e4\uc774 \ud3f4 \uc0c1\ud0dc\uc758 Null \ubc29\ud5a5\uc740 90\u00b0\uc640 270\u00b0\uc774\uc9c0\ub9cc, \uc774 \uac01\ub3c4\uc5d0\uc11c \ub8e8 \ud504 \uc0c1\ud0dc\uc77c \ub54c\ub294 \ucd5c\ub300 \ubc29\uc0ac\ub97c \ud558\uba70, \uc774\ub54c \ub8e8\ud504\uc0c1\ud0dc\uc758 \uc548\ud14c \ub098 \uc774\ub4dd\uc740 \u20145 dBi\uc774\ub2e4. \ubc18\uba74, \ub8e8\ud504 \uc0c1\ud0dc\uc77c \ub54c\uc758 Null \ubc29\ud5a5 \uc740 10\u00b0, 170\u00b0\uc774\uc9c0\ub9cc, \ub9c8\ucc2c\uac00\uc9c0\ub85c \uc774 \uac01\ub3c4\uc5d0\uc11c \ub2e4\uc774\ud3f4 \uc0c1\ud0dc \uc77c \ub54c \ucd5c\ub300 \ubc29\uc0ac\ub97c \uc774\ub8e8\uba70, \ub2e4\uc774\ud3f4 \uc0c1\ud0dc\uc758 \uc548\ud14c\ub098 \uc774\ub4dd\uc740 \u20144 dBi\uc774\ub2e4. \uce21\uc815 \uacb0\uacfc\ub97c \ud1b5\ud574 \uac01\uac01\uc758 \uc0c1\ud0dc\uc77c \ub54c \ubc29\uc0ac\ud328 \ud134\uc774 \uc0c1\ud638 \ubcf4\uc644\ub428\uc744 \ud655\uc778\ud560 \uc218 \uc788\ub2e4." + ] + }, + { + "image_filename": "designv8_17_0001044_a8fa772056d4fd55d520-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001044_a8fa772056d4fd55d520-Figure8-1.png", + "caption": "Fig. 8. Top panel configuration.", + "texts": [ + " The UD prepared lay-up process follows HSP-L3 specifications and curing cycle for the HSP-C2-M2 specification. When the cured CFRP tubes are taken from the autoclave, all of the tubes are demoulded and cut to the designed lengths. The final CFRP tube model is shown in Fig. 7. The main purpose of the Top Panel is to provide mechanical support for RSI components. The Top Panel is connected with the FS5 bus structure by ten (10) top supporters because the top supporters are designed to absorb thermal deformations coming from the satellite bus. The Top Panel configuration is shown in Fig. 8. The final model is shown in Fig. 9. The Top Panel is a honeycomb plate with its face sheet made of UD prepared M55J/954-3 material layers with [0\u00b0/36\u00b0/72\u00b0/-72\u00b0/-36\u00b0]S ply orientation. The top panel aluminium core is made of 5056 alloy of 1/8-5056-0.002P hexagonal aluminum honeycomb material with 62.5 mm thickness. The Top Panel is manufactured by Xperion Aerospace GmbH, one German structure manufacturer. In order to control the Top Panel surface flatness, a Cold Bonding process is used to install the fittings" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003865_9669085_09731522.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003865_9669085_09731522.pdf-Figure1-1.png", + "caption": "FIGURE 1. The graphene patches on the grounded silicon dioxide dielectric and the polysilicon DC gate pads below form the holographic surface, and it is fed by a monopole in the middle of the surface.", + "texts": [ + " By leveraging its conductivity\u2019s electric tunable feature, the proposed THz graphene holographic impedance surface antennas can be designed with equally sized and spaced patch cells, and the expected impedance pattern can be conveniently implemented by locally varying the DC biasing for each patch. Also, to achieve beam scanning and polarization conversion, instead of resorting to the traditional geometry revision methodology [12], it only needs to change the DC biasing accordingly. As shown in Fig. 1, the proposed antennas have a general structure which consists of 51\u00d751 equally sized graphene patches. To locally manipulate the conductivity of graphene, a 100nm thick polysilicon DC gate pad is placed below each patch. In addition, its atomicthickness and outstanding mechanical property make it very suitable for conformal antenna design. The rest of this paper is organized as follows. In Section III, different types of THz graphene holographic antenna are designed and the related theories are given in detail" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003554__AME_2021_138393.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003554__AME_2021_138393.pdf-Figure6-1.png", + "caption": "Fig. 6. Stress and displacement of the web of gear 6 under the loads", + "texts": [], + "surrounding_texts": [ + "To further reduce the gear weight, the construction of the proposed gears (pinions) is composed of two parts. Each gear (pinion) includes the rim and web. They are joined together by an interference joint. The rim is fabricated from highstrength steel as used for the calculation in the above items. The material of the webs is replaced by a high-strength and lightweight one such as Aluminum alloy 6061-T6. For gears 4 and 6, there are some holes on the gear web to reduce weight and easily assemble and disassemble. Thus, to reduce the weight of the webs, two processes are performed. The first is to calculate the pressure generated on the contact surface between the rim and web when assembling them together with an interference fit. The second is to increase the hole number and hole diameters while still ensuring durability, stability, and other fabrication conditions. In an interference joint, a torque is transmitted by friction force. Hence, to transmit torque M in each gear (pinion), the minimum pressure on the contact surface between the rim and web is p = M 2\u03c0 f Bc2 , (27) where f is the coefficient of friction between aluminum alloy and steel, B is the web thickness at the contact position, and c is the contact radius of two materials. The minimum force to press them to bond together is F = 2\u03c0 f cBp. (28) The minimum diametral interference to produce pressure p is \u2206 = pc { 1 EAl ( c2 + a2 c2 \u2212 a2 \u2212 \u00b5Al ) + 1 ESt ( b2 + c2 b2 \u2212 c2 + \u00b5St )} , (29) where a is the hole radius where is fitted with the shaft, b is the tooth root radius, ESt is the modulus of steel elasticity, EAl is the modulus of aluminum alloy elasticity, \u00b5St is the Poisson coefficient of steel, \u00b5Al is the Poisson coefficient of aluminum [19]. The stress and displacement of two gear pairs are investigated when the hole diameters on the webs of gears 4 and 6 change between 40\u201355 mm and 10\u201320 mm, respectively, and the hole number changes from 4 to 8. The input parameters and calculation results for the case of the maximum hole number and the maximum hole diameters that still satisfy the required conditions are shown in Figs. 4\u20136. The required conditions are stress and displacement conditions and the dimensional relationship conditions between the holes and the gear web to satisfy the working principle of the winch. In Fig. 4, the force acting on the tooth is placed in an area calculated according to the gear design theory. The pressure caused by the interference joint is also applied. Using Ansys software, the computational model meshed with the size of 0.15 mm \u00d7 0.15 mm, 0.5 mm \u00d7 0.5 mm, and 2 mm \u00d7 2 mm on where the force is applied on the tooth surface, the neighborhood of the first place, and others, respectively. The maximum stresses and displacements on the webs and gear roots in Figs. 5 and 6 show that they are within allowable limits. The maximum stress at the contact position between the teeth (position of force) when working is the local stress. It does not reflect the nature of this study. At this stage, the optimal results obtained are listed in Table 5. The total weight is greatly reduced and is only 2.365 kg instead of 4.461 kg as in the previous optimization. The weight reduction percent of gear pair 3-4 (49.77%) is larger than that of gear pair 5-6 (35.04%)." + ] + }, + { + "image_filename": "designv8_17_0004601_f_version_1695810939-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004601_f_version_1695810939-Figure14-1.png", + "caption": "Figure 14. Diagram of the station used to cool samples made of railway rails: 1\u2014connecting strip, 2\u2014push fit, 3\u2014connection ES 14 NA, 4\u2014plug, 5\u2014hydraulic hose, \u03d5 = 6 mm (used in the whole construction), 6\u2014diffuser nozzle, 7\u2014jointing sleeve, 8\u2014throttle valve, 9\u2014push fit.", + "texts": [ + " In reference to the set assumptions and the available visualizations of the potential solutions of this type, a solution was designed in the form of a casing with the shape of an even-armed trapezoid, on which, around the rail head\u2019s outline, six identical air nozzles were mounted symmetrically, three on each side, directed successively towards the side surface, the rounded head surface and the pitch surface. The design assuming the casing\u2019s dimensions and the distance between the air nozzle fronts are shown in Figure 14. Based on the preliminary tests conducted on rail head fragments, the proper cooling medium was determined to be compressed air, which, depending on the pressure, made it possible to steer the cooling rate within a wide range. Both its working pressure and the pressure supplied directly to the device were regulated, within a scope of 1\u20137 bar. The construction of the installation included the use of hydraulic hoses as well as elements separating and limiting the flow of the supplied air. Figure 14 shows a diagram of the construction of the finished station, whereas Figure 15 presents the cooling tests. The presented cooling station has been submitted for patent protection. 345 360 377 379 340 345 350 355 360 365 370 375 380 385 70 75 80 85 90 95 100 105 110 115 120 Ha rd ne ss [H V3 0] Distance between the cementite lamellae [nm] Figure 13. Relation of the distance between the cementite lamellae and the hardness. 4. Simulating the Real Process of Cooling Rails under Semi-Industrial Conditions After the determination of the cooling rates ensuring the proper microstr cture and properties of steel R350HT, a concept of a cooling station was developed, which would make it possible to control a full rail", + " In reference to the set assumptions and the available visualizations of the potential solutions of this type, a solution was designed in the form of a casing with the shape of an even-armed trapezoid, on which, around the rail head\u2019s outline, six identical air nozzles were mounted symmetrically, three on each side, directed successively towards the side surface, the rounded head surface and the pitch surface. The design assuming the casing\u2019s dimensions and the distance between the air nozzle fronts are shown in Figure 14. Based on the preliminary tests conducted on rail head fragments, the proper cooling medium was determined to be compressed air, which, depending on the pressure, made it possible to steer the cooling rate within a wide range. Both its working pressure and the pressure supplied directly to the device were regulated, within a scope of 1\u20137 bar. The construction of the installation included the use of hydraulic hoses as well as elements separating and limiting the flow of the supplied air. Figure 14 shows a diagram of the construction of the finished station, whereas Figure 15 presents the cooling tests. The presented cooling station has been submitted for patent protection. Materials 2023, 16, x FOR PEER REVIEW 12 of 17 Figure 15. View of the real testing station (own design). The conduits exiting the dividing strip were not connected to the successive push fits but were connected in pairs with respect to the symmetry axis. That is, the nozzles cooling the pitch surface were connected to opening 1 and 2, the rounded part of the head to opening 3 and 4, and the pitch surface to opening 5 and 6", + " The conduits exiting the dividing strip were not connected to the successive push fits but were connected in pairs with respect to the symmetry axis. That is, the nozzles cooling the pitch surface were connected to opening 1 and 2, the rounded part of the head to opening 3 and 4, and the pitch surface to opening 5 and 6. Such a procedure aimed at a possibly uniform distribution of the cooling agent\u2019s flow on both halves of the cross-section of the thermally processed rail. Materials 2023, 16, 6430 12 of 16 Materials 2023, 16, x FOR PEER REVIEW 12 of 17 Figure 14. Diagram of the station used to cool samples made of railway rails: 1\u2014connecting strip, 2\u2014push fit, 3\u2014connection ES 14 NA, 4\u2014plug, 5\u2014hydraulic hose, \u03d5 = 6 mm (used in the whole construction), 6\u2014diffuser nozzle, 7\u2014jointing sleeve, 8\u2014throttle valve, 9\u2014push fit. Figure 15. View of the real testing station (own design). The conduits exiting the dividing strip were not connected to the successive push fits but were connected in pairs with respect to the symmetry axis. That is, the nozzles cooling the pitch surface were connected to opening 1 and 2, the rounded part of the head to opening 3 and 4, and the pitch surface to opening 5 and 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002052_9312710_09380129.pdf-Figure29-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002052_9312710_09380129.pdf-Figure29-1.png", + "caption": "FIGURE 29. Surface current distribution for the Rx filter at 2.06 GHz.", + "texts": [ + " It can be noticed that the insertion loss of both filters is 0.9 dB (max.), and superior matching performance is obtained (less than \u221215 dB) in the range of 2.2 GHz\u22122.3 GHz for the Tx filter, and 2.04 GHz- 2.11 GHz for the Rx filter. Fig. 26, and Fig. 27 illustrate the surface current distribution for the proposed Tx filter. It can be noticed clearly that the EM wave cannot pass at the stop band (i.e., at 2.06 GHz), however, it can easily pass through the filter at 2.25 GHz. On the other hand, Fig. 28, and Fig. 29 show that the EM wave cannot propagate through the Rx filter around 2.25 GHz, while it can pass smoothly at 2.06 GHz (mid of its passband). E. PRACTICAL MEASUREMENTS In order to verify the simulations, The Tx filter is fabricated using the photolithographic technology on RT 6010 substrate. The filter is fitted in the Anrtisu test-in fixture, then its S-parameters are measured using Vector Network 45132 VOLUME 9, 2021 Analyzer (VNA) ZAV67 after standard calibration procedure. Fig. 30 shows the measurement setup" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure18-1.png", + "caption": "Fig. 18 Velocity vector of radial blades impeller RB with showing the flow path direction in a certain plane.", + "texts": [ + " Figures 17 shows the instantaneous discharge flow pressure at the outlet pipe ports after three complete revolutions of impeller for both cases: radial blades and double forward blades. It is also observed from Fig. 17 that the discharged local pressure range for the double forward blade, DFB, is higher than the standard radial impeller, RB. This means that the DFB produces largest discharge pressure compared with that of RB one. This result can be also be concluded from tracking the pressure developing between each blade of the double forward, DFB, and the radial blades, RB, through a flow path located +5 mm from the X-Y plan. Figure 18 shows the velocity vectors and the direction of the flow at the tracked path for the radial pump. The tracked flow path for the double forward pump is done with the same criteria of the radial one. The pressure tracking across this flow path is presented in Fig. 19 showing the evidence of local pressure variation between each blade of impeller for the two investigated cases. Moreover, it can be observed that the local pressure in case of the double forward impeller is greater than that in the radial impellers case for all angles \u201cfrom Y-Axis\u201d greater than 60" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000542_41230-021-0141-8.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000542_41230-021-0141-8.pdf-Figure8-1.png", + "caption": "Fig. 8: 3D FEM mesh of ingot inner mold (a) and ingot system (b)", + "texts": [ + " The average grain size is 2,200 \u00b5m at the core of the water-cooled ingot with the cooling rate of about 5 \u00b0C\u00b7min-1, as shown in Fig. 7(a), and the average grain size is 500 \u00b5m at the side wall of the ingot with the cooling rate of about 500 \u00b0C\u00b7min-1, as shown in Fig. 7(b). In numerical simulation, the water-cooled ingot system was simplified as water-cooled inner mold, ingot, hanging insulation board, exothermic compound, anti-piping compound, and bottom casting tube. The calculation domain was meshed with 171,282 nodes and 688,061 elements, as shown in Fig. 8, in which the mesh was non-uniform, tetrahedral and 20 mm in average size. where, G is the temperature gradient, \u00b7T is the cooling rate. The smaller Niyama criterion value indicates the greater possibility of shrinkage porosity. To predict the hot cracking, after completing the solidification computation of the ingot, the isochrones data from ProCAST were extracted and post-processed to obtain the Clyne and Davies (CD) criterion [23] and Katgerman (Kat) criterion [24], as shown in Eqs. (2) and (3), respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003299_11367-017-1308-9.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003299_11367-017-1308-9.pdf-Figure1-1.png", + "caption": "Fig. 1 Exploded sketch of the selected PMSM design", + "texts": [ + " The level of technical detail throughout both publications was selected to address a broad target group including LCA practioners novel to electricmotor terminology, aswell as electrical power engineers aiming to use LCA results. Because of this multidisciplinary ambition of the work, the model report contains not onlymany technical details, but also simple explanations of terms and basic theory (Nordel\u00f6f et al. 2016). The development of the LCI model required many significant methodological selections, both at the overall level and regarding details. These are described in the following chapter, also including the model structure and briefly how the modelled is used. Please turn to Fig. 1 for orientation when references are made to specific electrical machine parts. Development of electrical machines involves a large number of design variables including detailed geometrical tuning and material property considerations. It is a multi-objective engineering process with conflicting goals, and there is no single optimal solution fulfilling all desired requirements (Sizov et al. 2011; Ramakrishnan et al. 2016). Instead, there is typically a domain of solutions where the application and ad hoc trade-offs play an important role", + ", 2013 and onwards). Model calculationsfor thecomparisonswerebasedoninputofbothpowerand torque. However, in line with the stated model limitations, only machineswhere thecombinationof thepowerand torquegavean estimated base speedwithin 3000\u20135000 rpmwere included. This chapter presents a summary of how the design data was generated and compiled. For full details, and an explanation of the electromagnetic terms and principles, please read the model report (Nordel\u00f6f et al. 2016). In addition, please refer to Fig. 1 for all descriptions of parts presented in this chapter. The two main active parts of the electrical machine are the stator and the rotor. The bulk of these parts, referred to as the core, is normally made of electrical steel, with specific electromagnetic, thermal, and mechanical properties. The alloy contains silicon in order to obtain these qualities (Tong 2014). Electrical steel discs and laminations are stacked to form the cores. Laminations are preferably very thin and coated to keep electromagnetic and thermal losses low" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.17-1.png", + "caption": "Figure 2.17 : Electric motor prototype cooled with L-shaped heat pipes [108].", + "texts": [ + "[103] stated that Heat Pipes are characterized by a high thermal conductivity, a high efficiency (with no electric energy consumed), and a suitable working temperature for electric devices. Some authors were interested in studying the electric motors cooling using heat pipes [104]\u2013 [107]. Recently, authors of [108] investigated a new design of L-shaped heat pipes placed at the surface of the motor housing. Their objective was to determine experimentally the performance of the electric motor. In the design, heat sinks are mounted to each condenser side to increase heat transfer to the ambient air as in Figure 2.17. Putra et al. [108] reported that the use of heat pipes was capable of reducing the motor housing temperature less than the classical solutions (water jackets, hollow shaft), but the authors mentioned that the surface of heat exchange with ambient air in the studied motor is smaller. Two-phase loop cooling technologies are based on the same principle as heat pipes, but with liquid and vapor phases circulating in different areas of the circuit. Though, these systems can dissipate greater heat flux densities" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002584_f_version_1715414160-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002584_f_version_1715414160-Figure7-1.png", + "caption": "Figure 7. (a) Layout of the output network. (b) EM simulation and other parameters of the output network.", + "texts": [ + " The width of the coils is designed to be 1 mm to guarantee adequate powercarrying capacity. According to the IPC-2221A standard [33], a 1 mm wide microstrip line carrying a current of 1.5\u20135.5 A experiences a temperature rise of 10\u2013100 \u00b0C. For a 50 \u2126 load, the current corresponds to an output power of 112.5\u20131512.5 W. In this design, with a maximum output power of 46.5 dBm (i.e., 44.7 W), employing a line width of 1 mm ensures that the temperature rise remains below 10 \u00b0C. The layout of the output network is illustrated in Figure 7a. The values of Lp, Ls, and km are extracted from the EM simulation results, as shown in Figure 7b. Lp and Ls are both approximately 7 nH, and km is 0.4. The other parameters are subsequently calculated from (9) and displayed in Figure 7b. The physical lengths of the two TLs are 13 mm, corresponding to an electrical length of 65\u00b0, with a characteristic impedance Z02 and an associated shunt capacitance C02 calculated as 55 \u2126 and 0.54 pF, respectively, using (10). Additionally, a \u03bb/4 TL with a characteristic impedance of 55 \u2126 is positioned after the combining node, serving as a post-matching network to transform RL to 50 \u2126. It is crucial to note that the ITR between RL and 50 \u2126 is merely 1.2 in this topology. In comparison, the parallel Doherty counterpart has a much higher ITR of 7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003260_f_version_1665713726-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003260_f_version_1665713726-Figure5-1.png", + "caption": "Figure 5. Initialization of oilseed rape threshing simulation. Figure 5. Initialization f il rape threshing simulation.", + "texts": [ + " The role of the long ribs is to strip the oilseed rape seeds from the angular fruits, and the part of the peg teeth is to discharge the oilseed rape stalks and other impurities outside the device. The length of the long striker is 750 mm, the height is 90 mm, the spacing of the peg teeth is 80 mm, and the size is 90 mm [33]. Figure 3. Structure of oilseed rape threshing device. 1 co ca ; 2 s ft; f i ; 4 spreading disc; 5 threshing elements; 6\u2014guide plate angle. Agriculture 2022, 12, x FOR PEER REVIEW 7 of 22 Figure 4. Structure of threshing concave plate. The oilseed rape threshing process feeds multiple bunches of oilseed rape plants into the threshing device, as shown in Figure 5. The feeding area is used to feed oilseed rape plants, the threshing area is used to thresh, and the miscellaneous area is where impurities such as hulls and broken stalks are discharged out of the device. We set the feeding speed to 7.5 km/h, removing the limit constraint effect on the particles when the bonding bond is generated, and adding the global gravitational acceleration to 9.8 N/kg. After the oilseed rape plant is fed into the threshing device, it first enters the threshing zone, where the oilseed rape seeds fall off the spike shaft and become discrete particles under the action of the threshing ribs and concave plates [14]. The threshed seeds fall into the catch box under inertia. The operating environment of the threshing simulation is shown in Table 4. Table 4. Simulation environment. Projects Value Software version EDEM 2020 CPU 3.2 GHz Intel i7-8700 RAM 16 G Calculate step 3.5 \u00d7 10\u22126 (s) Calculation duration 28 (h) Figure 5. Initialization of oilseed rape threshing simulation. Figure 4. Structure of threshing concave plate. Suppose the guide plate angle is too small. In that case, the materials stay in the threshing device for too long, and the impurities cannot be discharged out of the machine in time, which will quickly lead to the proble of clogging the threshing cylinder and a high breakage grain rate. Suppose the angle of the guide plate angle is too large. In that case, the axial conveying speed of the oilseed rape plant is too large, which will shorten the contact time between the oilseed rape and other threshing elements, resulting in insufficient threshing operation and a high thre hing loss rate", + " The oilse d rape threshing m thod adopts the compound threshing form of \u201clong ribs + spike teeth,\u201d with six groups of threshing elements, each including one long rib and six spike teeth. The role of the long ribs is to strip the oilseed rape seeds from the angular fruits, and the part of the peg teeth is to discharge the oilseed rape stalks and other impurities outside the device. The length of the long striker is 750 mm, the height is 90 mm, the spacing of the peg teeth is 80 mm, and the size is 90 mm [33]. The oilseed rape threshing process feeds multiple bunches of oilseed rape plants into the threshing device, as shown in Figure 5. The feeding area is used to feed oilseed rape Agriculture 2022, 12, 1580 7 of 21 plants, the threshing area is used to thresh, and the miscellaneous area is where impurities such as hulls and broken stalks are discharged out of the device. We set the feeding speed to 7.5 km/h, removing the limit constraint effect on the particles when the bonding bond is generated, and adding the global gravitational acceleration to 9.8 N/kg. After the oilseed rape plant is fed into the threshing device, it first enters the threshing zone, where the oilseed rape seeds fall off the spike shaft and become discrete particles under the action of the threshing ribs and concave plates [14]. The threshed seeds fall into the catch box under inertia. The operating environment of the threshing simulation is shown in Table 4. Agriculture 2022, 12, x FOR PEER REVIEW 7 of 22 Figure 4. Structure of threshing concave plate. 2.3. Details of the Simulation The oilseed rape threshing process feeds multiple bunches of oilseed rape plants into the threshing device, as shown in Figure 5. The feeding area is used to feed oilseed rape plants, the threshing area is used to thresh, and the miscellaneous area is where impurities such as hulls and broken stalks are discharged out of the device. We set the feeding speed to 7.5 km/h, removing the limit constraint effect on the particles when the bonding bond is generated, and adding the global gravitational acceleration to 9.8 N/kg. After the oilseed rape plant is fed into the threshing device, it first enters the threshing zone, where the oilseed rape seeds fall off the spike shaft and become discrete particles under the action of the threshing ribs and concave plates [14]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003081_le_download_1199_891-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003081_le_download_1199_891-Figure8-1.png", + "caption": "Fig. 8. The Results of The Equivalent Stress Model and The Graph of The Relationship Between Load and Stress From Variations in Model Thickness", + "texts": [ + " On the opposite side, especially in the area around the wrist to the tip of the palm, a force was applied with loading ranging from 0 to 30 N. This interval force is assumed to occur when the model is applied to the patient's hand for fixation. Figure 7 shows the boundary conditions of the wrist-hand orthosis model. The analysis of the wrist-hand orthosis model for the equivalent (von Mises) stress showed that the maximum stress occurred in the area of the back end of the model's hand. This area is the link between the thumb and index finger, where the two fingers have a greater force than the other. Figure 8 shows the results of equivalent stress by indicating the maximum stress area and a graph of the relationship between load and stress from variations in the model's thickness. The maximum stress in the most significant load of 30 N was experienced in the model size of 5 mm, which was 23.46 MPa. This value is considered safe because it is still far below the Tensile Strength value of the PLA material. By calculation using the safety factor formula as follows. \ud835\udc5b = \ud835\udf0eyield \ud835\udf0eactual Therefore, the maximum stress in the model has a safety factor of 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003622_f_version_1712894587-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003622_f_version_1712894587-Figure2-1.png", + "caption": "Figure 2. Two-dimensional design of the conventional brushless WRVM model.", + "texts": [ + "\u00a0Equation\u00a0(1)\u00a0shows\u00a0that\u00a0to\u00a0operate\u00a0a\u00a0vernier\u00a0machine,\u00a0the\u00a0 following\u00a0relation\u00a0must\u00a0be\u00a0satisfied:\u00a0 \ud835\udc43 \ud835\udc41 \ud835\udc43 \u00a0 (1) where\u00a0Pr\u00a0represents\u00a0rotor\u00a0pole\u00a0pairs,\u00a0Ps\u00a0is\u00a0the\u00a0representation\u00a0of\u00a0stator\u00a0winding\u00a0pole\u00a0pairs,\u00a0 and\u00a0Ns\u00a0is\u00a0the\u00a0stator\u00a0slot\u00a0number.\u00a0 In\u00a0the\u00a0conventional\u00a0topology,\u00a0a\u00a0four-pole\u00a0stator\u00a0winding\u00a0(ABC)\u00a0is\u00a0serially\u00a0connected\u00a0 to\u00a0a\u00a0twelve-pole\u00a0excitation\u00a0winding\u00a0(X)\u00a0with\u00a0a\u00a0three-phase\u00a0diode\u00a0rectifier.\u00a0The\u00a0stator\u00a0con- sists\u00a0of\u00a024\u00a0slots\u00a0wounded\u00a0with\u00a0armature\u00a0and\u00a0excitation\u00a0windings.\u00a0The\u00a02D\u00a0design\u00a0of\u00a0the\u00a0 conventional\u00a0model\u00a0is\u00a0shown\u00a0in\u00a0Figure\u00a02.\u00a0In\u00a0order\u00a0to\u00a0create\u00a0a\u00a0third-harmonic\u00a0component\u00a0 in\u00a0the\u00a0airgap,\u00a0an\u00a0armature\u00a0winding\u00a0is\u00a0fed\u00a0with\u00a0a\u00a0single\u00a0inverter\u00a0that\u00a0supplies\u00a0currents\u00a0to\u00a0 both\u00a0armature\u00a0and\u00a0series-connected\u00a0excitation\u00a0windings.\u00a0A\u00a0three-phase\u00a0diode\u00a0rectifier\u00a0is\u00a0 connected\u00a0between\u00a0ABC\u00a0and\u00a0X,\u00a0which\u00a0delivers\u00a0the\u00a0pulsating\u00a0DC\u00a0to\u00a0X\u00a0when\u00a0energized.\u00a0In\u00a0 this\u00a0way,\u00a0fundamental\u00a0and\u00a0third-harmonic\u00a0MMF\u00a0components\u00a0are\u00a0generated\u00a0due\u00a0to\u00a0the\u00a0 four-\u00a0and\u00a0twelve-pole\u00a0stator\u00a0winding\u00a0configurations.\u00a0 Synchronous and vernier machines have different designs in terms of the number of poles on the stator and rotor", + " Equation (1) shows that to operate a vernier machine, the following relation must be satisfied: Pr = Ns \u00b1 Ps (1) where Pr represents rotor pole pairs, Ps is the representation of stator winding pole pairs, and Ns is the stator slot number. In the conventional topology, a four-pole stator winding (ABC) is serially connected to a twelve-pole excitation winding (X) with a three-phase diode rectifier. The stator consists of 24 slots wounded with armature and excitation windings. The 2D design of the conventional model is shown in Figure 2. In order to create a third-har onic component in the airgap, an ar ature winding is fed ith a single inverter that supplies currents to both armature and series-connected excitation windings. A three-phase diode rectifier is connected betw en ABC and X, which delivers the pulsating DC to X when energized. In this a , f e tal and third-harmonic M F compone ts are g nerated due to the fourand twelve-pol stator winding configurations. World Electr. Veh. J. 2024, 15, 163 4 of 16World\u00a0Electr.\u00a0Veh.\u00a0J.\u00a02024,\u00a015,\u00a0163\u00a0 4\u00a0 f\u00a0 17\u00a0 \u00a0 Figure\u00a02.\u00a0Two-dimensional\u00a0design\u00a0of\u00a0the\u00a0conventional\u00a0brushless\u00a0WRVM\u00a0model.\u00a0 The\u00a0rotor\u00a0part\u00a0consists\u00a0of\u00a0harmonic\u00a0and\u00a0field\u00a0windings\u00a0which\u00a0are\u00a0connected\u00a0through\u00a0 a\u00a0full-bridge\u00a0rectifier.\u00a0A\u00a0harmonic\u00a0winding\u00a0is\u00a0used\u00a0to\u00a0obtain\u00a0induced\u00a0voltage\u00a0to\u00a0achieve\u00a0 the\u00a0proposed\u00a0brushless\u00a0operation\u00a0of\u00a0the\u00a0machine.\u00a0The\u00a0full-bridge\u00a0rectifier\u00a0is\u00a0employed\u00a0to\u00a0 provide\u00a0DC\u00a0to\u00a0the\u00a0field\u00a0winding.\u00a0Harmonic\u00a0windings\u00a0and\u00a0excitation\u00a0windings\u00a0have\u00a0the\u00a0 same\u00a0number\u00a0of\u00a0poles.\u00a0The\u00a0rotor\u00a0consists\u00a0of\u00a044\u00a0slots\u00a0 for\u00a0a\u00a0field\u00a0winding\u00a0and\u00a0harmonic\u00a0 winding\u00a0and\u00a0is\u00a0designed\u00a0to\u00a0have\u00a044\u00a0poles\u00a0for\u00a0a\u00a0field\u00a0winding\u00a0and\u00a02\u00a0poles\u00a0for\u00a0a\u00a0harmonic\u00a0 winding", + "\u00a0 Currentcontrolled VSI A B C S ta to r V dc Full-bridge diode rectifierH a rm o n ic w in d in g F ie ld w in d in g IA IB IC E xc it at io n w in d in g Uncontrolled rectifier X IX \u00a0 Figure\u00a03.\u00a0Conventional\u00a0brushless\u00a0WRVM\u00a0topology.\u00a0 3.\u00a0Proposed\u00a0Brushless\u00a0WRVM\u00a0Topology\u00a0 For\u00a0the\u00a0proposed\u00a0topology,\u00a0a\u00a0structural\u00a0design\u00a0similar\u00a0to\u00a0the\u00a0conventional\u00a0topology\u00a0 is\u00a0adopted.\u00a0However,\u00a0in\u00a0the\u00a0case\u00a0of\u00a0the\u00a0proposed\u00a0topology,\u00a0the\u00a0auxiliary\u00a0winding\u00a0is\u00a0open- circuited.\u00a0The\u00a0stator\u00a0winding\u00a0is\u00a0designed\u00a0with\u00a0a\u00a0multi-pole\u00a0configuration,\u00a0four-pole\u00a0arma- ture,\u00a0 and\u00a0 twelve-pole\u00a0 auxiliary\u00a0 winding.\u00a0 A\u00a0 twelve-pole\u00a0 auxiliary\u00a0 winding\u00a0 is\u00a0 open- Figure 2. T o-di ensional design of the conventional brushless RVM model. The rotor part consists of har onic and field indings hich are connected through a ful -bridge rectifier. har ic i i is use to obtain induced voltage to achieve the r s f t e achine. The full-bridge rectifier is employed to provide DC to the field winding. Harmonic windings and excitation wi dings have the same number of poles. The r tor con i ts of 4 slots for a fi l har onic inding and is designed to have 44 poles for a field inding and 2 poles for a har onic inding" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002320_ejjia_9_2_9_201__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002320_ejjia_9_2_9_201__pdf-Figure5-1.png", + "caption": "Fig. 5. Overview of cylindrical linear motor.", + "texts": [ + " Although the saturation magnetic flux density of the iron core is a constraint, depending on the shape, it must be possible to design a magnetic pole that can generate a magnetic flux higher than the conventional SPM structure. Therefore, we first designed a motor using the proposed three-dimensional magnetic pole structure and calculated its thrust characteristics by finite element (FE) analysis. We compared the performance of the conventional model and the developed model by changing only the magnetic circuit configuration of the magnetic pole, while maintaining the same armature structure and the total number of permanent magnets used. 2.3 Analysis Model Figure 5 shows the external appearance of the proposed motor. The electromagnetic field analysis software \u201cANSYS Maxwell\u201d was used for the analysis. In order to ascertain the manner in which the periodic magnetic pole structure required in the developed structure differs from the conventional structure, we built a cylindrical linear motor having length in the direction of the z axis and periodicity in two axial directions; namely, the circumferential direction and the movable axis direction. The cylindrical shape was chosen to minimize the effect of the edges in any model. The armatures of all the models had the same configuration in order to be able to examine the difference in the magnetic circuit configurations in the magnetic poles. The armature windings are arranged in such a manner that three-phase alternating currents with a phase shift of 120\u25e6 in the U, V, and W phases are applied in the direction of motion (direction of z axis). In addition, concentrated winding is applied on each tooth so that the direction indicated by the arrow in Fig. 5(d) is the forward direction of the current and arranged such that the phases of adjacent windings in the circumferential direction are 180\u25e6 apart. The iron core has outlets for each wire in the radial direction to connect all the windings, but this aspect is not being considered in this model. Figure 6 shows the FE model of the magnetic pole of each 203 IEEJ Journal IA, Vol.9, No.2, 2020 motor used in the analysis, and Table 1 shows the specifications of each model. In the analysis, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure11-1.png", + "caption": "Figure 11. The load on the main rod is assumed to be straight", + "texts": [ + " Then, the force received by the rod (\ud835\udc39\ud835\udc35\ud835\udc4f) is FBR = mass x g\ud835\udc5f\ud835\udc4e\ud835\udc63\ud835\udc56\ud835\udc61\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c\ud835\udc5b FBR = 7 kg x 9,81m/s2 = 68,67 N 8. Static analysis of the load on the main rod This rod uses a rectangular hollow profile of 75x20x1.6 mm with a vertical position in the y-axis direction. The load received is the reaction load from the rod that receives the load directly, namely the load from the electric motor mounting rod, control panel and battery, driver body, driver's legs, front body, rollbar body, and rear body, as shown in Figure 10. The main rod is assumed to be straight with a length of 2500 mm, as shown in Figure 11. The free-body diagram of the main stem can be seen in Figure 12. Based on the results of the static load analysis with manual calculations that have been carried out, the calculation results are obtained in the form of bending moment, maximum stress, and displacement values, as shown in Table 1 and Table 2. This article uses Autodesk Inventor software through the analysis frame feature to conduct the simulation process. Simulations are carried out on each rod that receives a load and, as a whole, to determine the condition of the rod after experiencing static loading" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004862_0005208_10196331.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004862_0005208_10196331.pdf-Figure1-1.png", + "caption": "FIGURE 1. The antenna\u2019s development phases : (a) Antenna A, (b) Antenna B, (c) Antenna C, (d) Antenna D, (e) Antenna E.", + "texts": [ + " Later, the balun structure and the final configuration of the proposed antenna are analyzed. After that, numerical and measurement results are provided and finally, the conclusion is drawn. VOLUME 11, 2023 78755 II. BROADBAND ANTENNA DESIGN A. ANTENNA DESIGN EVOLUTION: FROM NARROW BAND TO BROAD-BAND The design concept commenced with the transformation of a basic printed dipole antenna into a broad-band filtering dipole antenna appropriate for 5G applications. To emphasize novelties, the design process will be described step by step by evolving the antenna. Fig. 1 depicts the antenna development stages. AntennaA in Fig. 1(a) represents a very simple printed dipole antenna that is used as a starting point and progresses to Antenna E, which is the final design. Antenna A is a printed dipole antenna with radiating arms placed on opposite layers of the dielectric and the feeding is accomplished using a broadside microstrip line arrangement. This configuration is advantageous due to its simplicity at the exciting port. Since the antenna and feeding line are both balance structures, there is no need to use balun to balance out the excitation. Although Antenna A has a feeding benefit, it lacks high gain values due to the absence of a reflector plate. This criterion drives the construction of Antenna B. Antenna B in Fig. 1(a) uses only one dielectric substrate layer. As a result, it is extremely beneficial if the structure is printed on a multi-layer PCB or top of a chip package. This antenna, however, cannot support a balanced feeding structure; thus, a balun (especially printed versions) is required. The performance of Antenna B depends significantly on the length and distance between the dipole arms. Fig. 2 shows a parametric study on these dimensions. The wire-type dipole antenna without the spacing between the arms excites a perfect sinusoidal current", + " 2(b) and the resonance frequency increases with the decrease in the arm length as expected. Antenna B effectively demonstrates the performance of a dipole antenna, but as can be seen in Fig. 2, it has a narrow impedance bandwidth. Another design iteration is followed to create a broadband dipole antenna as Antenna C. To make a broadband dipole antenna, another design iteration is carried out. The bandwidth of the antenna 78756 VOLUME 11, 2023 is increased by widening the dipole arms to introduce different surface current paths to the structure. Antenna C illustrated in Fig. 1(c) is created by increasing dipole width. In this design, specially shaped flared and wide dipole arms are suggested, where the current distribution maintains a consistent behavior at the operating frequencies, and the stable radiation characteristics are then observed. This antenna offers great bandwidth by arranging its width (W1), feed gap (S1), and flare angle (\u03b8). The parametric study conducted on these antenna dimensions can be seen in Fig. 3. Increasing the antenna width is the main strategy to improve the bandwidth", + " However, a very small flare angle increases the capacitance introduced by the antenna, which highly limits the impedance bandwidth as seen in Fig. 3(c) for \u03b8 = 50 case. Antenna C can be tuned to support the broadband operation requirement; however, filtering capabilities need to be introduced. In this paper, parasitic elements covering the dipole arms are designed to introduce a sharp transition in the reflection coefficient parameters. Antenna D is created by adding parasitic arc-shaped elements to Antenna C. The parasitic elements seen in Fig. 1(d) suppress the high-frequency terms. To have a filtering effect in the lower band, an orthogonal dipole and parasitic elements related to this dipole must be introduced. This iteration creates Antenna E seen in 1(e). Before explaining the important parameters of Antenna D and E iterations, the filtering mechanism introduced by the parasitic elements will be discussed and followed by a detailed parametric analysis of both antennas. B. FILTERING PARASITIC ELEMENTS DESIGN The final antenna (Antenna E) utilizes four rectangular arch-shaped parasitic elements as filter components", + " FILTERING ANTENNA DESIGN This study tries to overcome two challenges in communication antenna systems: impedance bandwidth limitation and interference due to adjacent bands. The impedance bandwidth problem is addressed in the previous chapter, and the printed dipole antenna with 76 % bandwidth is introduced. In this chapter, filtering properties will be first introduced to the higher-frequency (Antenna D), then the complete design would be achieved by filtering the lower frequencies (Antenna E) as illustrated in Fig. 1(d) and 1(e), respectively. To avoid the free communication band located after 5.5 GHz, the antenna must have low-pass components. The square arc components are modeled as the LP filters at the ends of the radiators. As explained in the previous chapter, the gap distance between the parasitic arc-dipole and the length of the arc are the main properties to determine the resonance frequency of the LP filter. The parametric study on the |S11| and Z-parameters of the Antenna D can be seen in Fig. 9. The gap between the parasitic element and dipole patch (S2) has a very important effect on the resonance frequency of the filter", + " In addition to the reflection coefficient, the antenna\u2019s radiation pattern is also very important in defining the bandwidth. The radiation patterns of the antenna are measured within VOLUME 11, 2023 78761 the entire operation band employing an Anechoic chamber facilitated in the Middle East Technical University EMT lab. The normalized radiation pattern graphs for selected frequencies can be found in Fig. 17. The measurements are done by exciting Port 2 only, and the 2D plots are created by considering the \u03c6 = 900 cut and detailed visualization of the measurement axis can be understood from Fig. 1(e). Since the antenna has a highly symmetric structure, the other port and the cut are not measured. Measured radiation pattern (solid line) results presented in Fig. 17 illustrate a great match with the simulated ones (dashed line) except for 5.5 GHz. All of the radiation patterns are shaped in a broadband fashion. This means that the antenna can operate for communication purposes in the entire operating band. At the higher end of the band, the radiation pattern deteriorates. As the direction of the radiating current at 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure7.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure7.1-1.png", + "caption": "Figure 7.1. Stylized drawing of a C joint.", + "texts": [ + " Toe results, Figure 6.9. For wheel-travel angle, see Figure 6.10. Support angle is shown in Figure 6.11. For roll center height results, see Figure 6.12. The five link suspension offers excellent kinematic performance and considerable flexibility in its packaging. Mercedes-Benz pioneered the five link suspension for production cars, as discussed in the introduction. 108 109 110 Chapter 7 The C Joint The cylindrical (C) joint directly connects the wheel carrier to the vehicle body. A stylized drawing is shown in Figure 7.1. The C joint allows both translation along and rotation about an axis. Here the search is for u0 \u2208 R3, giving the axis\u2019s direction, and x0 \u2208 R3, giving a point on the axis. For a wheel motion given by A \u2208 SO(3) and b \u2208 R3, it is required that u0 is invariant: Au0 = u0, and that the vector between x0 and its displaced position remains parallel to the C joint axis: (Ax0 + b\u2212 x0)\u00d7 u0 = 0. Only one wheel motion can be prescribed (one wheel position other than design); there are four independent design equations and four independent design variables" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004416_load.php_id_12071104-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004416_load.php_id_12071104-Figure1-1.png", + "caption": "Figure 1. Field modulated permanent magnetic gear. (a) Cross section of the considered magnetic gear. (b) Exploded view.", + "texts": [ + " Because of the magnetic flux leak and end-effect are considered in above analysis and calculation, the constituted model is more precise than 2-D analytical method or 2-D FEM. Compared with 3-D FEM, the analytical method is suited for programmable calculation and that will make the structural parameter design or optimization of CMGs simple and timesaving. It eliminates the blindfold defect of 3-D FEM in trial method with mass computer resource and time, also adapts to the parameterized and the serial applications in technical projects. Figure 1 shows the topology of a typical coaxial magnetic gear. The high speed permanent magnetic ring (inner rotor), low speed permanent magnetic ring (outer rotor), and the ferromagnetic polepieces rotate around common-axis. And their radii are Ri(1), Ri(2), Ro(1), Ro(2), Rm(1), and Rm(2) respectively. Their corresponding edge angles of tile permanent magnets in the inner rotor, ferromagnetic pole-pieces, and the outer rotor are \u03c6i(1), \u03c6i(2), \u03c6m(1), \u03c6m(2), \u03c6o(1), and \u03c6o(2) respectively. The \u03c6i(1), \u03c6m(1), and \u03c6o(1) overlap with xaxis. \u03d5 is circumferential angle, and \u03c1 is radial vector which starts from point O as shown in Figure 1(a). Because z-axial length of two rotors and the ferromagnetic polepieces may be different, their coordinates are denoted by Zi(1), Zi(2), Zo(1), Zo(2), Zm(1), and Zm(2) respectively as shown in Figure 1(b). Figure 2 is the inner rotor of Figure 1 in cylindrical coordinates system. The origin O, the same as the one showed in Figure 1, locates in the center of cylinder of inner rotor. The unit vectors of the cylindrical coordinates along \u03c1, \u03d5, and z are e\u03c1, e\u03d5, and ez respectively. A source point coordinate and a field point coordinate of a random permanent magnet in Figure 2 are p\u2032(\u03c1\u2032, \u03d5\u2032, z\u2032) and p (\u03c1, \u03d5, z) respectively. Their corresponding radius vectors are r\u2032 and r respectively. In the cylindrical coordinates system, supposed B is magnetic flux density in a random field point of air-gap, and its corresponding vector potential is A", + " It yields B\u2126\u03c13 = \u00b50M 4\u03c0 Ni\u2211 ni=1 2\u2211 j=1 2\u2211 k=1 (\u22121)(s+1+j+k) \u2206\u03c1\u2032 N\u03c1\u2032\u2211 n=0 S\u03c1\u2032 (n) \u03c1\u2032 (n) sin (\u03d5\u2212\u03c6i (j)) I1 ( \u03c1, \u03d5, z; \u03c1\u2032 (n) , \u03c6i (j) , Zi (k) ) (7) Using parameters in Table 1, (1), (5), (6), and (7) are programmed with Matlab 7. The magnets used for CMGs are sintered Nd-Fe-B material, and their magnetizations are all M = 890000 (A/m). Along the radius Ro(1) and Ri(2), divide up the surface of cylindrical air-gap into 360 segmentations (the air-gap magnetic field of the outer rotor can be calculated according replacing parameters whose subscript is i by the ones of o). With the constituted model of this paper, B\u2126\u03c1 is calculated when \u03d5 increased by each one degree as shown in Figure 1 on a 3.0 GHz computer which has quad-core CPU and 2 GB memory. The results are shown in Figure 4(a) to Figure 4(d). It takes approximately 15 s respectively to compute of air-gap magnetic field at Ro(1) of the inner rotor and at Ri(2) of the outer rotor, as shown in Figure 4(a) and Figure 4(b). The Figure 4(c) takes 20 s. The same parameters as Table 1 are checked with the same computer using the Maxwell 3-D Field Simulator from Ansoft 14, and it takes approximately 25 min respectively for the analysis not including modeling, meshing, setup and postprocess in Figure 4(a) or Figure 4(b)", + " The curvilinear plane of the constituted model of this paper and 3-D FEM are alike as shown in Figure 4(c) and Figure 4(d). Figure 5 is the equivalent current model of a tile permanent magnet on the outer rotor. The orientations about Jov and Jos are determined by right-hand rule. There are No tile permanent magnets on the outer rotor, and two surface current densities on each permanent magnet contribute to the torque transmission. For the initial position is zero (viz. an edge on tile permanent magnet overlaps with x-axis) such as Figure 1, the surface current of permanent magnet flows along the radial edge surface of \u03c6o(1) = 2\u03c0 (no \u2212 1)/No (no = 1, 2, . . . , No) And \u03c6o(2) = 2\u03c0no/No (no = 1, 2, . . . , No) When the outer rotor rotates an angle, its total volume current is zero and its surface current [26] is Jos = M \u00b7 ez Ro(1) \u2264 \u03c1 \u2264 Ro(2) \u03c6o(2) = \u03b1o0 + 2\u03c0 No no Zo(1) \u2264 z \u2264 Zo(2) \u2212M \u00b7 ez Ro(1) \u2264 \u03c1 \u2264 Ro(2) \u03c6o(1) = \u03b1o0 + 2\u03c0 No (no \u2212 1) Zo(1) \u2264 z \u2264 Zo(2) (8) Supposed T is the torque of the outer rotor as showed in Figure 1, and in literature [26] it is given by T = \u222e s ro \u00d7 (Jos \u00d7B\u2126)ds (9) Substituting (8) and B\u2126\u03c1 into (9), it yields T (\u03b1o0) = 2M No\u2211 no=1 (\u22121)no \u222b Zo(2) Zo(1) \u222b Ro(2) Ro(1) \u03c1B\u2126\u03c1d\u03c1dz (10) In (10), B\u2126\u03c1 can be calculated by (1), (5), (6), and (7) according to the corresponding boundary condition. The coefficient 2M takes into account the fact that there are two surface currents at the interface between neighboring tile permanent magnets, and these surface currents have the same orientation and function for torque calculation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure35-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure35-1.png", + "caption": "Figure 35: Design 3 of pantograph compliant mechanism.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0004385_aper_ETC2017-356.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004385_aper_ETC2017-356.pdf-Figure2-1.png", + "caption": "Figure 2: The MTU- HEX geometry", + "texts": [ + " In this concept, recuperation is achieved by using an integrated system of HEXs installed in its exhaust nozzle is investigated, as presented in Fig.1 in order to preheat the compressor discharge air before the latter enters the combustion chamber. As a result, less fuel mass flow is required and thus fuel economy and reduced pollutant emissions is achieved. More particularly, in Fig.1 red arrows represents the hot-gas after the LPT and the orange arrows represent the hot-gas after waste heat recuperation was achieved. The IRA-engine concept is based on a number of state-of-the-art tubular HEXs, presented in Fig.2, which are operating as heat recuperators, in order to exploit part of the thermal energy of the low pressure turbine exhaust gas, aiming at the decrease of fuel consumption and the corresponding reduction of pollutants. In the IRA engine the basic HEX, which was invented and developed by MTU Aero Engines AG and is presented in Fig. 2, consists of elliptic tubes placed in a 4/3/4 staggered arrangement in an attempt to achieve high heat transfer rates and reduced pressure losses. Additional details about this technology can be found in the works of Boggia and R\u00fcd (2004), Wilfert et al. (2007), Schonenborn et al. (2004), Missirlis et al. (2005) and Yakinthos et al. (2006, 2007). As recuperation is achieved through a number of HEXs mounted inside the hot-gas exhaust nozzle, their presence can impose significant pressure losses on the hot-gas flow inside the nozzle installation, which have a direct effect on the low pressure turbine achieved work capability" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001400_f_version_1634111124-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001400_f_version_1634111124-Figure2-1.png", + "caption": "Figure 2. Eccentric magnetic pole structure.", + "texts": [ + " The maximum demagnetization operating point of the permanent magnet can be checked with the aforementioned methods, which verifies whether the permanent magnet will be permanently demagnetized when in operation and ensures the reliability of the PMSM. The PMSM designed in this paper adopts surface-mounted poles with radial magnetization. If the traditional equal thickness tile-shaped permanent magnets are adopted, the air gap flux density waveform of the motor is approximately a rectangular wave with large harmonic content. Then, it will cause large cogging torque, resulting in cogging torque and noise, which greatly affects the accuracy of missile guidance. Therefore, this paper selects the eccentric magnetic pole structure shown in Figure 2 to suppress the cogging torque of PMSM. Rm is the radius of the inner arc of permanent magnet, h is the eccentric distance between the inner and outer arcs, hm is the thickness of the central magnetization direction of permanent magnet and hm(\u03b8) is the thickness in the magnetizing direction of permanent magnet at different angles. The following can be obtained. hm(\u03b8) = h cos \u03b8 + \u221a (Rm + hm \u2212 h)2 \u2212 (h sin \u03b8)2 \u2212 Rm (8) Due to the slot of the stator and rotor, the reluctance around the permanent magnet is different" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000814_13320-014-0196-x.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000814_13320-014-0196-x.pdf-Figure1-1.png", + "caption": "Fig. 1 Structure of the smart cable with embedded FBG sensors.", + "texts": [ + ": Broken Wires Diagnosis Method Numerical Simulation Based on Smart Cable Structure 367 strain FBG sensors [7] that are fastened to the peripheral wires in the cable fabricating the stage and calibration relationship between the cable force and steel wires strain in the over tensioning stage, the smart cable can output both cable force and steel wires stress. Utilizing the above characters of the smart cable, the research will focus on a proposed broken wires diagnosis strategy, establishing a broken wires sample database based on the bridge-cable and cable-steel model by numerical simulating and finishing the diagnosis method verification by the back propagation (BP) neural network. As shown in Fig. 1, several large strain FBG sensors are fastened to the peripheral wires in the connection pipe region during the cable fabricating process. The large strain FBG sensor with a special encapsulation structure [8, 9] meets the working range requirement for the stay cable, which can endure a large strain close to 5000 \u03bc\u03b5 under the over tensioning stage and the maximum combined loads in the operational stage. Besides the large range, as shown in Fig. 2, the mechanical fasten means for the sensor ensures a long-term effectiveness of force transmission" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureB.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureB.6-1.png", + "caption": "Figure B.6: SDM finger with leafspring at the MCP joint [11].", + "texts": [ + " Trajectories of the center of rotation and tip of the fingers are presented. Functional requirements in terms of load-carrying capacity or weight of the device were not considered. B.2.4 Yale University Yale University introduced the use of leafsprings made of urethane for prosthetic hands [18], see Fig. B.5. The lower young modulus of the rubber joint offers high compliance in the actuation direction. However, it also offers undesired compliance in the other directions. The undesired compliance increase dramatically at large deflections, see Fig. B.6. As shown in Fig. B.6, the distance d1 increases as a large deflection of the joints occur. The increment of the arm (d1) considerably increases the torsion on the proximal joint (MCP). For this reason, the elastic joint at the MCP was later replaced by a pinjoint [11]. The study of the flexure joints led to the development of the smooth curvature model [73\u201375]. Changes in the compliances at large deflections are considered in this model for planar structures (leafsprings). Page 38 The flexure joints are optimized in the actuation direction with interest in an ellipsis compliance in the contact point" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000853_9668973_09718336.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000853_9668973_09718336.pdf-Figure6-1.png", + "caption": "FIGURE 6. Applied load torque to the motor in the (a) conventional and (b) proposed revolute joints.", + "texts": [ + " It is related to changes in the gear ratio and will be covered in section C. B. LOAD TORQUE The proposed revolute joint reduces the load torque applied to the motor compared with the conventional revolute joint. If the weight of the revolute link is m and the length of the link from the revolute axis to the center of mass is r , the load torque in the conventional joint, \u03c4c, is expressed as \u03c4c = r \u00b7 mg \u00b7 sin\u03b8 (4) where g is the gravitational acceleration, and \u03b8 is the angle of the revolute joint, as shown in Fig. 6 (a). The torque on the revolute axis was the same in the cases of the conventional and proposed mechanisms. However, in the proposed revolute joint, the load torque was not applied to the rotational axis but to the linear actuator. When the torque equilibrium was achieved in the proposed mechanism (see Fig. 6), the applied axial load on the linear actuator, Q, can be obtained as follows, Q = \u03c4c h . (5) According to the screw mechanics, the load torque applied to the motor in the proposed revolute joint, \u03c4p, 24042 VOLUME 10, 2022 is obtained as follows, \u03c4p = d 2 Q \u00b7 tan(\u03c1 + \u03b1) (6) where d, \u03c1, and \u03b1, are the diameter, friction angle, and lead angle of the lead-screw-driven linear guide, which were approximately 5mm, 5.7\u25e6, and 7.3\u25e6, respectively. The friction angle was obtained based on the assumption that the coefficient of friction of the lead screw was equal to 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000548_3_NgTeckChew2009.pdf-Figure4.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000548_3_NgTeckChew2009.pdf-Figure4.3-1.png", + "caption": "Figure 4.3: Pose of the follower vehicle.", + "texts": [ + " Bayesian Estimation Formulation For Vehicle Following 121 Some case studies will be presented in this section. For demonstration purposes, the Extended Kalman Filter (EKF) will be extensively discussed, the derivation and notation for which can be found in [115]. However, the generic formulation presented above can also be applied when using other filters, such as the Unscented Kalman Filter (UKF) [116],[117] or Particle Filters [118],[119],[102]. The reference coordinate system and the pose of the follower vehicle are shown in Figure 4.3. The Ackerman model [120] is used to describe the motion model of the follower vehicle. One simple method for localization is via dead reckoning sensors such as wheel encoders. Unfortunately, dead reckoning involves direct instrument integration, which causes unbounded errors to be accumulated over time. A gyroscope is introduced to reduce the problem of orientation drift. A gyroscope can be mounted at the centre of the rear axle, and its position will be the reference point for the localization of the follower vehicle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-31-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-31-1.png", + "caption": "Figure 2-31.Exemples de miniaturisation par effet de charge capacitif ou inductif", + "texts": [ + " Ces m\u00e9tamat\u00e9riaux offrent de nouvelles propri\u00e9t\u00e9s physiques dont l'inversement de la loi Snell-Descartes (indice de r\u00e9fraction n\u00e9gatif) qui permet de confiner les ondes \u00e9lectromagn\u00e9tique et donc de miniaturiser des structures d'antennes. 2.5.4 L'utilisation de court circuit ou de charge Une autre technique permettant de r\u00e9duire la taille de certaines antennes repose sur l'utilisation de charge ou de court circuit \u00e0 des endroits appropri\u00e9s en fonction de la structure. Par exemple une antenne monopole peut \u00eatre raccourcie, tout en conservant la m\u00eame fr\u00e9quence de r\u00e9sonnance, en introduisant une charge capacitive ou inductive dans la structure de l'antenne comme le montre la Figure 2-31. La r\u00e9actance introduite par les effets capacitif ou inductif compense la partie imaginaire de l'imp\u00e9dance d'entr\u00e9e du monopole raccourci, ce qui permet d'obtenir un bon niveau d'adaptation. Cette technique permet d'obtenir des r\u00e9ductions de taille de l'ordre de 50% mais une diminution de la bande passante et de l'efficacit\u00e9 de rayonnement est g\u00e9n\u00e9ralement observ\u00e9e et l'adaptation de la structure reste d\u00e9licate [2.16]. 63 Une autre m\u00e9thode pour r\u00e9duire les dimensions d'antenne consiste \u00e0 placer des courts circuits plans ou filaires entre l'\u00e9l\u00e9ment rayonnant et le plan de masse" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003045_1044-019-09680-6.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003045_1044-019-09680-6.pdf-Figure2-1.png", + "caption": "Fig. 2 Initial FE configuration (IC) of a square-sectioned steel beam and the three corresponding generalized translational component modes \u03c6tl according to Eq. (8); visualized with appropriate scaling factors for presentation purposes (Color figure online)", + "texts": [ + "1, the reduction basis \u03a6 \u2208 R 3nn\u00d7(12+9nm) contains predominately generalized flexible component modes, which is why the main part of the rest of the present paper is devoted to the investigation of the flexible part of the reduction matrix, since \u03a6 f \u2208R 3nn\u00d79nm accounts for the majority of linear dependencies and the high condition number in the first place. In this section, a simple example of a 60 mm square-sectioned 900 mm long steel beam should illustrate the generalized component modes, as well as the inherent problem of linear dependencies, to gain a deeper understanding of the formulation and to show the significance of the current contribution, respectively. Figure 2 illustrates the generalized translational component modes; all nodes are displaced the same amount in the x-, y- or z-direction. Hence, any rigid body translation of the discretized body can be represented by a proper linear combination of the generalized translational component modes. The generalized rotational component modes of the square beam are depicted in Fig. 3 and, as already addressed in Sect. 2.2 and Appendix A, contain in addition to rotational rigid body motion in general stretch and shear deformations, as may be seen in the figure, i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000550_9551808_09551816.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000550_9551808_09551816.pdf-Figure7-1.png", + "caption": "Fig. 7. Electromagnetic pressure and total velocity at 3,500 rpm.", + "texts": [ + " The higher the order of the forced vibration mode, the lower the probability that it will coincide with the natural frequency of the motor, and the more likely it is to avoid resonance. For this paper, the 4-forced vibration mode was selected by the pole-slot combination. The electromagnetic pressure Pr was calculated as in (10)-(12) to use the flux density Br, Bt of the radial and tangential directions based on the Maxwell stress method. 2 2 r r t 0 1 P B B 2 \u03bc (10) r x yB B cos \u03b8 B sin \u03b8 (11) t x yB B sin \u03b8 B cos \u03b8 (12) Fig. 7 shows the electromagnetic pressure and total velocity at the maximum speed. As expected, the forced vibration mode was rectangular due to the electromagnetic force at the ends of the stator teeth. The vibration velocity of the harmonic response on the surface of the motor generates noise energy in the air. An acoustic analysis was performed by mapping the vibration velocities on the surface of the motor according to frequencies transmitted to the external air. The result of the acoustic analysis indicated that the A-weighted sound pressure levels, which were calibrated, were higher at the first and second natural frequencies and that the sound pressure levels were relatively small at the pole passing frequency" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002141_ngRunqiG1000407F.pdf-Figure3-2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002141_ngRunqiG1000407F.pdf-Figure3-2-1.png", + "caption": "Figure 3-2. (a) The short-end stub is transferred to the inductor via Richard\u2019s transformation. (b) The MMR is inductively fed by inductors.", + "texts": [ + ".......... 27 Figure 2-9. Flow chart of a typical optimization process [64]. .................................................... 32 Figure 2-10. Equivalent circuits of even- and odd-modes. (a) Even-mode circuit. (b) Odd- mode circuit. (c) Derived odd-mode circuit with modified phase velocity. ......... 34 Figure 3-1. Schematics of a class of inductively fed MMRs formed by cascading n sections of transmission lines. (a) n= 1. (b) n= 2. (c) n= 3. (d) n= 4. ................................... 39 Figure 3-2. (a) The short-end stub is transferred to the inductor via Richard\u2019s transformation. (b) The MMR is inductively fed by inductors. ......................................................... 39 Figure 3-3. The synthesis procedure as discussed in this chapter for the single wideband BPFs. ............................................................................................................................... 41 Figure 3-4. Characteristic impedance variations under the different cutoff frequencies (\u03b8c) and the ripple factors (\u03b5) for the circuits of", + " When n is further increased to 3 and 4 as shown in Figure 3-1(c) and (d), more resonances are introduced in the passband, behaving as 4th and 5th order filtering responses. Thus, the short-circuited resonators 39 of n sections is similar to the stepped-impedance shaped MMR for wide or ultrawideband BPF design, as discussed in [6] and [39], which introduces n-1 resonances within the passband. Different from the design in [6] where the parallel coupled lines are used to feed the MMR. The short-end stubs are regarded as inductive loading elements to feed the MMR, as seen in Figure 3-2. A simple explanation of this phenomenon is by applying the Richard\u2019s transformation which transfers the bandpass filtering response to the lowpass one. In the meanwhile, the short-end stubs are transferred as the inductors serving as an inductive loading nature. That is, the short-circuited resonators in the form of the cascaded transmission lines have the magnetic fields (or simply referring as the currents) reaching the maximum at the two shorted ends. To feed this resonator, the input and output ports are directly connected to the two 40 short-circuited ends to provide an inductive loading" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure2-1.png", + "caption": "Fig. 2. Composite frame Fig. 3. Sandwich", + "texts": [ + " For the sake of stability, a six-wheel rocker-bogie suspension was selected for the design (Fig. 1). By definition, a \u201cdouble tripod\u201d is more stable than the standard suspension of a four-wheeled off-road vehicle. Additional advantages of such a suspension include evenly distributed pressure of the wheels on the ground and reduction of the frequency of vibrations in the frame where the vehicle electronic components are located. This effect was achieved by a pivoting mounting of the frame in relation to two support points \u2013 1 and 2 (Fig.2). The ERC competition takes place in terrestrial conditions, on a specially prepared track, so the rover\u2019s structure has to be characterised by greater strength. During the competition, the Martian rover has to compete in 5 tasks [18]: \u2022 Science Task \u2013 soil sampling, e.g., by drilling and securing samples for analysis, \u2022 Maintenance Task \u2013 travelling the path to the control panel and performing a series of manual operations, \u2022 Collection Task \u2013 localizing and collecting containers with the samples and delivering them to a designated point, \u2022 Traverse Task \u2013 finding points placed along the track without using a camera; the vehicle uses an autonomous mode based on the map, \u2022 Presentation Task \u2013 presentation of the stages in the development of the rover" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure8-1.png", + "caption": "Fig. 8 Mesh topology for the dynamic domain: section view", + "texts": [], + "surrounding_texts": [ + "In order to investigate the suggested modifications, a commercial software ANSYS CFX-19.0 is used to perform 3D unsteady simulation for the flow analysis of the described RP. The Reynolds Averaged Naiver-Stokes equation (RANS) combined with the Sheer Stress Transport (SST) turbulence model are employed, as recommended by [7]. The Reynolds number, defined based on the diameter of impeller DT and the tip speed UT, is about 2\u00d7105. To keep the fine meshes near-wall capable of resolving the viscous sub-layer, y+ is kept in the range of 30~300 to comply with the log-law [25]. The computational domain is divided into three main parts as illustrated in Fig. 4a. The first one is the casing domain which contains the fluid flow around the impeller and surrounded by the external walls of casing body, the second and the third ones are the inlet pipe flow domain and the outlet pipe flow domain, respectively. In the casing flow part, the domain is divided into two parts as well, as shown in Fig. 4b; the dynamic layer domain, that represents the fluid layer rotating between walls of the impeller and fluid layer just above the impeller body; Fig. 5a and the static domain, which represents the remained part located between the casing body of the pump and the dynamic flow layer above the impeller, Fig. 5b. The lengths of the inlet and outlet pipes are about 11.1 and 13.5 times the casing diameter, respectively similar as in [7]. The centerline of the inlet pipe and outlet pipe are at angles of - 28.6o and +28.6o from the Y-axis, respectively, as shown in Fig. 6. The Boundary conditions in these current simulations are similar to that employed in [7]: \u2022 At inlet: the boundary set to be a constant static pressure and the flow is normally directed to the boundary condition with a medium turbulence intensity of 5%, which is a standard inflow boundary condition. \u2022 At outlet: the boundary condition is set to the opening with variable pre-defined mass flow rate (0.0218, 0.05, 0.109, 0.1635, 0.218, 0.2725 and 0.3815 kg/s). \u2022 The no-slip condition is employed near the solid walls. The multi-zone meshing topology is used, where triangular prisms are employed near the walls and tetrahedral mesh elsewhere as shown in Figs 7, 8, 9 and 10. In order to achieve convergence conditions, The study of the mesh independency is held on a various number of mesh elements N of 0.2 million (M), 0.5M, 0.7M, 1.2M, 1.9M, 3.2M and 4.5M. Two variables are tested to examine the mesh independency, the flow coefficient \u00d8 and the head coefficient . Where the flow coefficient \u00d8 is calculated from the flow rate Q passing through the pump and the cross-section area Ac = (2a1 + 2b1 + 2c1 + t) a2 - (2b1 + t) of the channel (See Figs. 2 and 3), \u00d8 = \ud835\udc44 \ud835\udc34\ud835\udc50 \ud835\udc48\ud835\udc47 , (1) Where UT = \u03c0 DT \u03c9 / 60 is the tip speed of impeller at rotational speed \u03c9 in revolutions per minute. The head (pressure) coefficient \u03c8 is calculated as a function of flow density \u03c1, UT, and the difference between the average values of pressures at discharge and suction sides (\ud835\udee5\ud835\udc43 = \ud835\udc43\ud835\udc51 \u2212 \ud835\udc43\ud835\udc60) at walls of the pipe as follow, = \ud835\udee5\ud835\udc43 0.5 \ud835\udf0c \ud835\udc48\ud835\udc47 2 , (2) The head coefficient \u201c\u03c8\u201d is calculated and plotted at different number of mesh elements as shown in Fig. 11. It can be observed that the value \u03c8 becomes independent on the grid size, when the mesh element reaches N \u2265 1.2M for different flow rates. As a consequence, and to save the computational resources, the simulations used for the analysis are discretized over N=1.2 M grid elements distributed as follows: The meshes are distributed as following: \u2022 725,000 elements in the casing (static fluid domain) as shown in Figs. 7. \u2022 325,000 elements in the impeller (dynamic domain) as shown in Figs. 8. \u2022 70,000 elements in the inlet pipe (Fig. 9). \u2022 80,000 elements in the outlet pipes (Fig. 10). In these simulations, the impeller is rotated in three complete revolutions with a total duration time of 0.3 second (unsteady simulation). The setting of the interface surfaces model between impeller and the side flow channel is set to be transient \u201crotor-stator\u201d, due to the change of the relative position between the impeller and the side channel at each time step. For time integration, the second-order backward Euler is kept in the transient scheme. Figure 12 shows comparisons between the current simulation and the experimental and numerical results introduced by Horiguchi et al. 2009 [7]. It can be concluded that, the current flow simulation shows an excellent agreement with the experimental and computed data of Horiguchi et al. 2009 [7]. Fig.12 Flow coefficient versus head coefficient of the RP: comparison between the present transient simulations of the current work with that of the experimental and numerical works done by Ref. [7]." + ] + }, + { + "image_filename": "designv8_17_0002091_rynica2018_10007.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002091_rynica2018_10007.pdf-Figure9-1.png", + "caption": "Fig. 9. FE model of the suspension footbridge.", + "texts": [ + " A variable in theoretical analyzes was the value of tension in main cables. Due to the lack of information about the values of pre-stress forces during the construction of the object, the authors made an attempt to estimate these values on the basis of dynamic tests. For this purpose, a threedimensional model of the footbridge was made in the Autodesk Simulation Multiphysics program. The model was built with use of beam, truss and shell elements. The created 3D model in accordance with [4] was classified as (e1+e2, p3). Figure 9 presents the FE model of the bridge. Below, in Table 2, the most important information on the structural elements of the footbridge is presented. The towers were set as fixed at the support without the possibility of translation nor rotation. On the basis of the inventory, the cables were defined as braided steel ropes, for which the elastic modulus E is 165 GPa. The value of the Young\u2019s modulus for girders and crossbars was 200 GPa. Two types of analyzes were carried out: static (Static Stress with Nonlinear Material Models) and modal (Natural Frequency with Nonlinear Material Models)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure2.27-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure2.27-1.png", + "caption": "Figure 2.27: Instantaneous power density of the TM Zenneck Skin/Fat mode at (a) 2 GHz and (b) 6 GHz", + "texts": [ + " At 1 GHz, the attenuations in the direction of propagation, air transverse direction, and fat transverse direction are 0.1 dB/cm, 0.39 dB/cm, and 0.36 dB/cm, respectively. If the mode can be excited, this mode performs well enough for the on-body communication. However, as it is sensitive to the body surface impedance and has a upper cut-off frequency, the variation of the human body geometry in different persons (e.g., tissue thickness) may cancel this propagating mode at some higher frequencies. The \u201cTM Zenneck Skin/Fat\u201d mode propagating at the skin/fat interface is shown in figure 2.27 at 2 GHz and 6 GHz. This Zenneck mode has a lower transverse attenuation in the fat layer than the air layer (1.5 dB/cm, 4.9 dB/cm in fat and air at 2 GHz and 3.7 dB/cm, 20.7 dB/cm at 6 GHz, respectively). Most energy propagates in the fat layer, which may overheat the fat tissue [13]. In addition, since the muscle has a higher real part of permittivity than the skin, the propagation is attracted to the muscle/fat interface. Thus, it seems that this mode is more likely to be excited by a source located inside the human body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure57-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure57-1.png", + "caption": "Figure 57. Drawing of the smaller top plate", + "texts": [], + "surrounding_texts": [ + "1 = variable 1 2 = variable 2 3 = variable 3 br = bearing comp = compressive extes = extensometer i = at ith data point long = longitudinal direction max = maximum xxii min = minimum pin = pin location s = symmetric spec = specimen ten = tensile trans = transverse direction ult = ultimate x = x-direction xx = in the axial direction for the +/-45\u00b0 shear tensile test y = y-direction xy = xy-direction (plane) 1 CHAPTER 1: INTRODUCTION In this chapter, previous and current thesis work is introduced. Section 1.1 introduces the different two different types of aircraft structures. In Section 1.2, the differences between an adhesively bonded joint and a mechanically fastened joint are explained. In Section 1.3, previous work is mentioned, considerations are made in order to avoid testing parameters, which have already been tested, and the three different failure mechanisms are explained. Section 1.4 explains the thesis goal and the thesis scope. 1.1 Introduction to Conventional & Advanced Composite Structures When you think of an aircraft\u2019s wing, it is composed of multiple panels and not usually made as a single piece. The use of joints becomes essential in an aircraft\u2019s wing (since joints serve to attach multiple structural components together to form one part). Ideally, the designer wants to avoid using them, since they can contribute a significant amount of weight to the overall aircraft\u2019s structure. Current aircraft manufactures are transitioning from a conventional aircraft structure to an advanced composite structure since the advantage of switching to an advanced composite structure is the significant reduction in parts and joints. Composite materials have desirable characteristics such as being: very stiff, extremely strong, and extremely light. For example, the Airbus\u2019 A350 aircraft structure is made up of 53% composite materials [1]. Even though the total amount of joints can be significantly reduced, that does not mean they can be avoided altogether. 2 As composites become more widely used in the Aerospace Industry, there still lies limited research in their ability to perform as joints. Their main flaw is their poor behavior in redistributing stress concentrations. Even though there has been a lot of research in composite joints, not enough advancement has been made compared to its metal counterpart. Metal joints (in particular, Aluminum joints) have been used for years in the Aerospace Industry. Currently, composite joints are overdesigned (made a lot thicker than they need to be) which leads to weight penalties. Design that is more detailed needs to done on composite joints in order to improve its ultimate bearing strength. 1.2 Introduction to Adhesively Bonded Joints & Mechanically Fastened Joints Two types of joints exist: one is the mechanically fastened joint, and the other is the adhesively bonded joint. In Figure 1, one can see an adhesively bonded single shear joint, a mechanically fastened single shear joint and a mechanically fastened double shear joint. The region between the two plates, in the adhesively bonded double shear joint, is the thin layer of structural adhesive used to bond both structural components together. Adhesively bonded joints are typically lighter but are often more difficult to design. No holes need to be made in an adhesively bonded joint. Reduction of holes reduces the amount of stress concentrations. Adhesively bonded joints can be problematic since the surface finish needs to be accounted for to achieve a strong bond between two surfaces. Another issue with adhesively bonded joints is that they cannot be removed as easily as a mechanical joint. 3 Mechanically fastened joints are widely used in the Aerospace Industry since they are more practical in the sense that they can be easily removed if a part needs to be replaced, repaired, or checked. Two types of mechanically fastened joints exist: single shear and double shear. In addition, a mechanically fastened joint can contain many fasteners. Mechanically fastened joints require a hole through both structural components, which creates stress concentrations. Both of the structural assemblies are held together by a bolt, and nut. 4 1.3 Previous Literature on Mechanically Fastened Composite Joints Numerous papers have been made on mechanically fastened composite joints, and in this section, the most important finds will be mentioned. According to Alan Baker[3], for a mechanically fastened double shear joint, load is transferred mainly through compression on the internal face of the fastener holes and as well as on a component of shear on the outer faces of the plate due to friction. Mechanically fastened composite joints can be made very durably but the designer needs to spend a longer time in the design process. According to Okutan [4], problems arise when the designer wants to analyze them since they have an anisotropic and heterogeneous nature. According to Chen [5], the behavior of a composite joint could be influenced by four parameters. The first is the material parameter. The material parameter includes fiber types, form, resin type, fiber orientation, laminate stacking sequence, material cure cycle, etc. The second is the geometric parameter. This includes the specimen width (W) and the hole edge distance (e). These are usually reported as W/D and e/D ratios where D is the diameter of the hole. A huge contributor to the strength of the specimen is the specimen thickness (t). The pitch is the distance between two or more holes in a multiple hole composite joint. The third (also very important) is the fastener parameter. This includes fastener type, fastener size, washer size, hole size, and tolerance. The last is the design parameter. The design parameter includes loading type (tension, compression, fatigue), loading direction, loading speed, hydraulic clamping pressure, joint type (single lap, double lap), environment, etc. 5 The lay-up sequence also played a significant role in the overall strength of the double shear joint, as well. Quinn & Matthews [6] studied in detail the effect of stacking sequences on the pin bearing strength in glass-reinforced plastics. They concluded that placing a 90\u00b0 layer ply on the outer surface of the laminate increased the overall bearing strength. Liu [7] tested different laminate thicknesses by varying the bolt diameter. He concluded that thick laminates with smaller diameter holes and thin laminates with larger diameter holes were a lot weaker than laminates with similar hole and laminate thicknesses. Stockdale & Matthews [8] studied the effects of bolt clamping pressure and found that boltclamping pressure played a huge role in the overall strength of the composite joint. Kim [9] tested to see the effects of temperature and moisture on the strength of graphite-epoxy laminates. From this experiment, the actual stress distribution of the joint is very difficult to find since the region is so small. The use of strain gages is impractical because that region is under a very high stress so any kind of strain gage applied would crush because of the force. That is why numerous researchers have been working on methods of modeling composite joints with the help of various finite element programs. The load capacity of a laminate is severely degraded due to the effects of hole clearance and friction. Hyer & Klang [10] investigated this phenomenon with a pin-loaded orthotropic plate. Pierron [11] used Abaqus to calculate the stress distribution around the hole of a woven composite joint. Most finite element modeling was done using 2D shell elements and recently there has been an increased amount of 3D modeling of composite joints. Previous researchers mention that the joint strength depends mainly on the failure criterion. 6 Only a small section of the bearing stress vs. bearing strain curve is linear, and then after, it becomes nonlinear. Stress concentrations cause crushing in a small section of the geometry, making it a very difficult nonlinear problem. Chang [12] created a 2D finite element model and assumed a frictionless contact with a rigid pin and a cosine normal load distribution in the pin-hole boundary. Another difficulty in modeling the composite joint requires the user to combine the failure criteria with a property degradation model. As the composite takes more load, the actual material properties are degrading over time, which would mean the modulus is decreased after each new load is applied. Lessard [2] used a 2D linear model along with a non-linear model to predict the strength of the composite joint. There are five different kinds of failure, which can occur in a laminate: matrix tensile, compressive failure, fiber/matrix shearing, fiber tensile, and fiber compressive failure. The Hashin failure criterion is an important criterion used to characterize failure within a laminate. 1.3.1 Previous Literature on Loading Rate Effects on Mechanically Fastened Composite Joints In flight, the aircraft might experience various dynamic loading conditions, so not only do composites need to be tested in quasi-static loading case, but also in a dynamic load case. Metals are not as load rate dependent as composite materials. Ger [13] tested a number of carbon and carbon fiber glass hybrid composites at dynamic loading rates of 6 to 7 m/s. The double shear joint configuration carried more load at high loading rates. It was also noted that for all joint configurations the stiffness of the joint increased significantly with 7 loading rate. In addition, what was noted was that the total energy absorption of the joint decreased significantly in the dynamic tests. Contradictory to Ger [13], Li [14] tested different types of joint configurations subject to a bearing load and found that energy absorption increased. Li [14] tested at higher rates of 4-8 m/s and found this interesting trend. The dynamic behavior of composite joints is much more complicated than its behavior for the quasi-static condition due to the involvement of strain rate and inertial effects. Li [14] concluded that crashworthiness design of tested composite joints could be based on their tensile strength design. Ger [13] mentioned there must be a significant safety factor applied to take into account bearing strength variations with loading rate. The failure modes might also be affected due to an increased loading rate. 1.3.2 Types of Failure in Mechanically Fastened Composite Joints According to Larry Lessard [2], it has been observed experimentally that mechanically fastened composite joints fail under three basic mechanisms: net-tension, shear-out, and bearing (in addition, combinations of these mechanisms are often given separate names). Typical damage mechanism is shown below in Figure 2. Looking at previous work, a net-tension and a shear-out failure are more catastrophic than a bearing failure. The best way to see if a bearing failure has occurred is to look at the bearing stress vs. bearing strain plot. Once the stress gets to its peak value and suddenly drops off to zero, then one can conclude it was a shear-out or a net-tension failure. If after the ultimate bearing stress, the specimen continues to carry load but deforms as a result, this means that the joint was designed very safely. According to Okutan [4], the optimum orientation for a bearing type of failure is a quasi-isotropic laminate orientation. A quasi-isotropic laminate 8 orientation means the laminate has the isotropic properties in plane. According to USNA [15], a quasi-isotropic part has either randomly oriented fiber in all directions, or has fibers oriented such that equal strength is developed all around the plane of the part. The geometry of a mechanically fastened composite joint is quite complex since it can affect the failure mode of the double shear joint specimen. Kretsis [16] & Matthews [16] tested fiber glass and carbon fiber reinforced plastics and found that the width(W), end distance(e), diameter of hole(D), and laminate thickness(h) all contribute to the overall mechanically fastened double shear joint strength. The most interesting aspect is that as the width of the specimen decreases to a specific amount, the mode of failure changes from bearing to net-tension. The W/D (width to hole diameter ratio of the composite double shear joint specimen) must be at least 5 order to avoid the net tensile type failure. Another interesting thing to note is when the end distance of the hole is a certain distance from the edge of the plate, the failure turned from bearing to shear-out (where shear-out is considered a special case of bearing failure). 9 1.4 Thesis Goals & Scope In the preceding sections of this thesis paper, the word double shear specimen will be used to represent one test specimen with a mechanically fastened double shear joint configuration. The goal of the thesis is to determine how the strength of a composite double shear joint is affected by two different cure cycles and five different loading rates. The composite joint will be tested in the double shear case and the laminate orientation was decided to be a quasi-isotropic laminate (based upon based on Yeole\u2019s double shear experimental results [17]). Yeole [17] tested three different laminate orientations in his thesis, and concluded that a quasi-isotopic laminate took the highest stress. Yeole [17] also mentioned that the testing of composite materials at fast loading rates could be an interesting topic to explore. ASTM 5961[18], which is the ASTM for bearing response of composite materials, required an extensometer to measure the relative pin displacement since using crosshead displacement is not an accurate method. A fixture was designed and manufactured in order to accommodate an extensometer. Finally, the numerical model was made to validate only the linear elastic portion of the experimental results. There are seven chapters in this thesis. Chapter 1, the introduction, includes a brief introduction to: composite materials, the difference between adhesively bonded joints and mechanically fastened composite joints, and the loading rate effects on mechanically fastened composite double shear joint bearing strengths. It also includes a brief literature review, the statement of the problem and the objective and organization of thesis. Chapter 2 focuses on manufacturing of the double shear specimens and the tensile specimens. Chapter 3 focuses on the experimental material testing 10 procedure conducted on the MTM49 Unidirectional Carbon Fiber pre-preg. It also explains the double shear fixture used for the testing. Chapter 4 focuses on the equations used in the experimental and theoretical calculations. Chapter 5 introduces the experimental result validation and then discusses the experimental results. Chapter 6 introduces: the numerical model, which was created using Abaqus 6.14 software, the convergence plot, and lastly, what, influences the numerical results. Chapter 7 is where the experimental results are compared to the numerical finite element results. Lastly, Chapter 8 is where the conclusions are drawn and different recommendations are made for the future work. In the reference section, one can find most of the related topics in the form of theses, books, reports and even papers published in numerous journals. In the appendix section, one find: drawings of the fixture, a tutorial on setting up the Bluehill2 double shear test method, a tutorial on finding the unknown engineering constants with the Autodesk software, a tutorial on outputting the force vs. hole deformation in Abaqus, and a tutorial on the composite double shear specimen Abaqus model. 11 CHAPTER 2: MANUFACTURING & PREPARING OF THE SPECIMENS This chapter will introduce the type of specimens that were manufactured and tested in the Instron machine along with their dimensions. All the dimensions were based on published ASTM test standards. ASTM is an international standards organization, which develops and publishes voluntary consensus technical standards for a wide range of materials, products, systems and services. 2.1 Tensile Specimen & Double Shear Specimen Dimensions The dimensions for the 0\u00b0 tensile specimens and the 90\u00b0 tensile specimens were found in ASTM D3039 [19] Standard test method for tensile properties of fiber-resin composites. The dimensions used for the shear modulus +/- 45\u00b0 were found in ASTM D3518 [20]. Below in Figure 3, one can see all of the tensile specimen dimensions for each specific fiber orientation angle. Figure 4 shows a drawing of all four different fiber orientation tensile specimens. The +/- 45\u00b0 shear specimens and the quasi-isotropic laminate specimens had the same dimensions. Figure 5 shows the dimensions, based on ASTM D5961 [18], of the composite double shear specimens. The quasiisotropic tensile specimens were tested to see how the theoretical material properties matched. 12 13 2.2 Manufacturing Process In the Cal Poly\u2019s Aerospace Engineering Composites Lab, there are two ways to manufacture a composite. One can use pre-preg material or apply a wet layup process. Pre-preg material is a lot easier to use since it already has the resin infused inside the material. In order to preserve the resin in the pre-preg material, it needed to be stored in a freezer at low temperatures. Once the pre-preg material is thawed, then the user is able to apply it to a mold or create a plate out of it. The second way, the wet-layup process, consisted of having the fibers in their pure form, which usually come in a roll, and having a two-part epoxy. Once the fibers were cut out from the roll, the two-part epoxy is mixed with the correct ratio and then applied to the dry fibers. The part is then sealed, with a vacuum bag (where all the air is removed from the part). Then the cure cycle of the 14 resin is applied to the vacuum-bagged part. All of the tensile and double shear specimens were made on the heat press. When making a composite plate in the heat press, the user needed to sandwich the laminate between two nonporous sheets and two 0.25 in. thick Steel plates. Figure 6 shows how the heat press cure process was set-up. The non-porous sheets served to prevent the resin from sticking to the steel plates. The composite plate, the steel plates and the non-porous sheets were placed inside the heat press and then the cure cycle was programmed. Once cured, the composite plate was cut into various size specimens. 2.2.1 Double Shear Specimens All the composite double shear specimens were made with the quasi-isotropic laminate orientation. The quasi-isotropic laminate orientation, [0 0 +45 -45 +45 -45 90 90]s, is short hand for [0 0 +45 -45 +45 -45 90 90//90 90 -45 +45 -45 +45 0 0]. The subscript s means that the laminate 15 is symmetrical about the last ply (which in this case is a 90\u02da ply). The alternate cure cycle was the Cytec\u2019s MTM 49 cure cycle and the datasheet cure cycle was the Umeco\u2019s MTM 49 cure cycle.. The material was first thawed since according to the Umeco\u2019s [22] MTM 49 datasheet, if the roll is open to the environment, condensation will occur on the pre-preg material, which will degrade the quality and the aesthetic look of the material. Sixteen 12 in. by 12 in. plies were cut out and orientated in the quasi-isotropic laminate orientation of [0 0 +45 -45 +45 -45 90 90]s. All the respective angles within each ply of the laminate were carefully kept within \u00b1 1\u00b0. Shown in Figure 7, a protractor was used to make sure each ply in the laminate was within \u00b1 1\u00b0. Once all the plies were stacked very carefully (in order to prevent air pockets from occurring within the laminate), the cure cycle was programmed into the heat press. Air pockets create areas where delamination can occur, which leads to the formation of cracks. Cracks can severely weaken composite structures. The second step consisted of programming the cure cycle into the heat press. Shown in Figure 16 8, is Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22]. Two different cure cycles were tested to see its effects on the material\u2019s double shear bearing stress. Increasing the dwell temperature from 248\u00b0F to 275\u00b0F and increasing the dwell time from 60 minutes to 90 minutes both affect the mechanical characteristics of the resin. The dwell temperature is the temperature which is held constant in the cure process (for this material, it occurs after the temperature ramp up stage). The dwell time is the duration of the dwell temperature stage. Each different carbon fiber matrix system will have its own recommended cure cycle printed in its specific datasheet. In the experimental section, one can see the difference in mechanical properties of the material based on the two different cure cycles. The first cure cycle was Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22] (also known as the alternate cure cycle). The heat press was adjusted to the specific cure cycle. First, the cure cycle temperature ramped up from room temperature of 77\u00b0F to 275\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 275\u00b0F for 90 minutes. After the 90 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. A uniform pressure of 2 psi was applied on top and bottom of the plate. 17 The second cure cycle was Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [21], shown in Figure 9 (also known as the datasheet cure cycle). The heat press was adjusted to the specific cure cycle. First, the press ramped the temperature up from the room temperature to 248\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 248\u00b0F for 60 minutes. After the 60 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. The pressure was held constant between both cure cycles. 18 The third step consisted of preparation of the test specimens. Once the composite laminate finished curing, the material was removed from the press and was cut with a tile saw, which had a diamond-coated blade. The tile saw had an adjustable clamp that helped keep the cuts within 0.1 of an inch. Figure 10 shows the tile saw used to cut the specimens. A straight cut was made on the composite laminate, in order to clean up the edge of the plate. Next, the top side of the plate was aligned to the straight section of the small tile saw. The cuts were made carefully in order to keep a 90\u00b0 angle on the side of the cured laminate. Once all the cuts were made, and the zero direction of the laminate was located accordingly, specimens were cut to the correct width. Based on ASTM D5961 [18], a W/D (specimen width to hole diameter ratio of the composite double shear joint specimen) of 6 and e/D (hole edge distance to diameter of hole ratio) of 3 were used. These geometric conditions guaranteed the double shear composite specimens failed in bearing and not in net-tension or shear-out. Based on these geometric conditions, the specimens needed to be 1.5 in. wide by 5.5 in. in length. The tile saw 19 was used to trim the long 1.5 in. wide specimens to their final length of 5.5 in. A small aluminum block was clamped to the tile saw, which helped minimize variations in the length of all the specimens and allowed multiple specimens to be cut at the same time. After the specimens were cut to their specified length and width, they were grouped into sets of five. A mini microfiber-board fixture was created in order for five holes to be drilled at the same time. The fixture was clamped into the drill press. Five composite double shear specimens were stacked onto the drill fixture and the top left corner of each composite double shear specimen was aligned to the top left corner of the fixture. An Aluminum template was placed on top of the composite double shear specimens and was used to align the 0.25 in. diamond coated end mill bit. Once the composite double shear specimens were aligned accordingly, a small c-clamp was used to constrain the specimens along with the Aluminum template from moving/rotating during the drilling process. In Figure 11, one can see the fixture, the Aluminum template and the end mill bit used for the hole drilling process. 20 Once the holes were created for all the composite double shear specimens, there needed to be a 0.5 in. wide horizontal slit on each face of the composite double shear specimens. A thin Aluminum template was created to assist in locating a specific distance from the hole. This slit needed to be placed accurately within a tolerance of 0.01 in. The template is shown below in Figure 12, and the flat edge of the Aluminum template was used to locate the slit location. The slit needed to be as horizontal as possible and deep enough to catch the moveable knife-edge of the extensometer. 21 Emery cloth helped distribute the high clamping pressure (which is applied by the hydraulic clamps) which occurred at the bottom of the double shear specimen and the emery cloth prevented the composite double shear specimen from slipping during the test. Aluminum tabs were not needed for the double shear test because the specimens failed before reaching 7,000 lbs. The emery cloth works up to a maximum load of 7,000 lbs. The emery cloth was 1.5 in. wide and had a grit level of 120, which is shown in Figure 13. Each specimen only needed emery cloth on one end. Only a 3 in. long piece was needed to cover all of the specimen\u2019s width. A small portion of painters tape served to hold the emery cloth in position. The emery cloth was also reusable; so one piece of emery cloth could be used on two or more specimens. In Figure 13, on the right, shows the ready-to-test composite double shear specimen. 22 2.2.2 Tensile Specimens The same method was applied for the composite tensile specimens, except that these specimens did not have a hole. Stacking the layers needed to be done in a very careful manner in order to prevent misalignment. Once the composite shear modulus specimens and the 90\u00b0 composite tensile specimens were cut to 10 in. by 1 in., then all that was needed was to apply the emery cloth to the ends. Painters tape was used to secure the emery cloth in position. Then, the composite shear modulus specimens and the 90\u00b0 specimens were ready for testing. The 0\u00b0 unidirectional carbon fiber composite tensile specimens required 2 in. long aluminum tabs (as specified by ASTM 3039 [19]). Sandpaper was used on the surface, near the ends of the 0\u00b0 unidirectional carbon fiber composite tensile specimens. A small section of the surface was 23 abraded, and then, acetone was used to clean the surface. Structural adhesive was used to bond the Aluminum tabs to the 0\u00b0 unidirectional carbon fiber composite tensile specimens. After a full day of curing, the 0\u00b0 unidirectional carbon fiber composite tensile specimens were ready to be tested in the Instron 8801 machine. In Figure 14, one can see the ready-to-test 0\u02da unidirectional carbon fiber composite tensile specimens and the +/-45\u02da composite shear modulus specimens. 24 CHAPTER 3: TESTING PREPARATION & PROCEDURE In this chapter, the test preparation and procedure are explained thoroughly. Section 3.1 introduces the type of testing machine used for the experiment. Various test recommendations are made and included inside the preceding subsection. The Auto-Loop tuning feature is explained in detail and an example is made to assist the user in using this feature. The Specimen Protect feature in Bluehill2 is explained with full detail, which helped produce very consistent experimental results. Finally, in Section 3.3, the tensile double shear test and tensile test procedures are explained. The design and set-up of the double shear fixture is shown in detail as well. In the Appendix, the Bluehill2 test method creation was explained for a double shear tensile test. 3.1 Intro to Uniaxial Testing Using the Instron 8801 Servo-hydraulic Test Machine All the material tests were conducted on an Instron 8801. This machine is a dual column servohydraulic testing system. It meets the challenging demands of various dynamic and static testing requirements. The machine allows the user to hook up external force or strain transducers. A dynamic knife-edge extensometer was used for both, the tensile and double shear tests. The machine works in conjunction with a controller, which can be used to control the machine without the use of a computer. A servo-hydraulic system is composed of an actuator, which can apply a tremendous amount of load onto a test specimen. The load cell has a +/- 100 kN limit which means it can measure accurately up to +/- 22,000 lbs. axial force (in compression/tension). For the tensile double shear test, the maximum load that was seen during the test was around 1,700 lbs. and for 25 the tensile test, a maximum load of 7,000 lbs. was seen. The thicker the laminate, the higher the load the specimen could take before failure. Shown in Figure 15, one can see the Instron 8801 testing setup. The machine\u2019s crossheads contain metal jaws, which (powered by a hydraulic system) are able to clamp the specimen. The hydraulic clamping pressure is adjustable so for standard tensile testing, the pressure is set to 160 bar and for testing fragile composite resins, one would want to drop the pressure to 80 bar. Lowing the hydraulic pressure helped reduce premature specimen cracking. The crosshead mechanism loaded with a specimen is shown below in Figure 16. The specimen is placed carefully between two the hydraulically powered metal clamps which secure 26 the specimen in place. 3.1.1 Instron Servo-hydraulic Test Machine Recommendations For determining the modulus of elasticity along with the modulus of rigidity, the most accurate measuring tools were the extensometer and the strain gage. The crosshead displacement was not very accurate since the system displaces due to the compliance in the grips, and the actuator assembly. This displacement of the crosshead can cause unreliable results in the modulus of elasticity where accuracy is very important. The Instron crosshead and the extensometer both yielded slightly different stress/strain curves. This difference in stress/strain curves is due to the Instron crossheads displacing a little more than the extensometer. The extensometer measured only the deflection of the specimen relative to both of the extensometer knife-edges. The extensometer 27 had a gage length of 0.5 in. and a knife-edge width of 0.5 in. The dynamic extensometer, catalog no. 2620-826, can be seen in Figure 17. The top knife-edge is fixed and the bottom knife-edge records precise deflections. The extensometer was attached using two rubber bands. The rubber bands were wrapped multiple times around the specimen to prevent the knife-edges from slipping. Whenever the extensometer was handled, the safety pin was in place at all times. If the user wants to run a three-point or 4-point bend test, the crosshead displacement is accurate enough to capture the vertical displacement accurately. If the user wants even more accuracy, they are able to hook up an extensometer to the three-point bend fixture and record vertical displacement with that device rather than the crosshead displacement. The Instron 8801 machine has a few features, which need to be utilized in order to minimize testing errors. The load and position calibration should never be changed or conducted. Before any 28 test is conducted, the user should Auto-loop tune the load cell only once. Each time a new material is being tested; for example, carbon fiber compared to Aluminum, the load cell should be Autoloop tuned. A list of load cell control gains should be recorded in a separate table for each material, to avoid having inexperienced individuals auto-loop tune the machine. Some precautions in the auto-loop tuning process include to never auto-loop tune a material that will fails under 120 lbs. and to never set the force amplitude above 500 lbs. This may cause the machine to cycle through very rapidly. 3.1.2 Tutorial on Auto-Loop Tuning of the Load Cell for an 1 in. wide By 1/16 in. Thick Aluminum Specimen Each time a new type of material is tested in the machine the load cell needs to be auto-loop tuned whether it be Aluminum, Steel, carbon fiber, hemp composite, fiberglass or any other composite material. Auto-loop tuning the force insured that the load cell is set up to perform accurately for each specific material. The auto-loop tuning tool adjusted various gains on the load cell controller. This was done through the Bluehill2 console (under the load cell menu). Measure the cross-sectional area of the tensile specimen and note its yield stress (if a metal) or ultimate stress (if a brittle material). For example, for Aluminum, the yield stress is around 35 ksi and the tensile specimen had a cross-sectional area of 0.062 in.2. Make sure to apply a force which keeps the material well under its yield or ultimate stress (so 25 ksi was applied to the Aluminum specimen). 29 Insert the Aluminum tensile specimen into the hydraulic clamps and load the specimen to 1,500 lbs. Also, set the amplitude force to 500 lbs. In the auto-loop tuning wizard, the Proportional gain (P) needs to be set to one before any auto-loop tuning is conducted. The specimen will be exposed to a cyclic load of 1,500 lbs. \u00b1 500 lbs. After the auto-loop tuning completes, it will say Auto-loop tuning completed successfully and then, in the next window record the P, I, D and L values. The P value should be 12.564, the I value should be 0.56, the D value should be 0.49 and the L value should be 0.8. These gain values are essential to the auto-loop tuning process. Each time a new material is tested, it is advised to specify the correct P, I, D and L values in the console and only if those values are unknown then the material needs to be auto-loop tuned. After running the auto-loop tuning tool on the MTM 49 unidirectional carbon fiber material, the P (proportional gain) equaled 13.481 and I (integral gain) equaled 0.578. Both D and L equaled zero. Typically, the material needs to be auto-loop tuned in a load range where accuracy is needed. This range is typically, where the modulus of elasticity is measured in between 25% to 50% of ultimate stress as stated by ASTM D3039 Tensile Properties of Polymer Matrix Composite Materials [19]. If the material fails during the auto-loop tuning process, the actuator will shake violently and will not stop itself. Hit the red emergency stop button on the control panel or hit the red button on the Instron servo-hydraulic machine to power off the actuator. Start back up the machine and run the auto-loop tuning tool again at a lower force. 30 3.1.3 Tutorial on Specimen Protect The specimen is prone to premature failure due to high clamping forces exerted by the hydraulic clamps. Instron's Specimen Protect feature protects a specimen against this phenomenon. This feature is found inside the console, it is labeled Specimen Protect, and the symbol looks like small shield. Before using the Specimen Protect feature, go into the console, enter the Specimen Protect option menu and make sure the load threshold is set to 44 lbs. Clamp the bottom of the test specimen. Once the bottom of the specimen is clamped, move the actuator up until the top of the specimen sits in between the top crosshead's clamps. Turn on the Specimen Protect feature in the console and this will automatically move the bottom crosshead slightly up or down in order to prevent the specimen from experiencing more than 44 lbs. After both the top and bottom of the specimen are clamped, turn off the Specimen Protect feature and continue with the test. Every time a new specimen is inserted into the hydraulic clamps, this feature needs to be utilized in order to prevent premature failure. 3.2 Bluehill2 Test Preparation The machine was connected to a Windows desktop and from there Bluehill2 and the console were used to monitor machine inputs and outputs. According to Instron, the console software provides full system control from a PC: including waveform generation, calibration limit set up, and status monitoring. In real-time, Bluehill2 outputted various experimental results: strain values, load values, displacement values, and exc. All the raw data was outputted into an Excel file, which 31 could be used for post-processing calculations. 3.2.1 Bluehill2 Test Parameter Setup The main software of interest was the Bluehill2 software. In Bluehill2, the user has options of changing various testing parameters. Each test can be created and saved to a separate testing file, which can later be accessed when the user needs to conduct that type of test. Three different tests were created in the Bluehill2 software. The tensile test and tensile double shear test were created with the Bluehill2 software. Before a test file is created, it is required of the user to know what values are of interest for a specific structural test. The ASTM should exactly specify which the testing parameters should be used for the specific test. ASTM D5961 [18] suggested to test at a load rate of 0.05 in./min., to sample at a rate of at least 2 samples per second, and to output the extensometer displacement instead of the crosshead displacement. It also specified to run the test until a maximum force is reached and until the maximum force decreased by 30%. If the force didn\u2019t drop to 30% of the maximum; run the test until the pin displacement is equal to half of the hole diameter. For the pin displacement, the test ended once the extensometer read a displacement of 0.1 in. since that was the maximum range of the extensometer. The test specimen slipped in the grips when the force in the force vs. time plot flattens out, with respect to time, the specimen was slipping. The hydraulic pressure was manually set to 160 bar on the side of the machine. The fastener, which secured the Steel collars to the sides of the specimen, was hand tightened. Five different loading rates were 32 applied and adjusted accordingly inside the Bluehill2 software. 3.3 Instron Experimental Test Procedure The Instron start-up checklist was followed in the lab in order to start the machine safely. The first step of the checklist was to turn on the main power switch in the back of the lab. After turning on the main power switch, the next step was to turn on the Instron controller by pressing the power switch in the back of the Instron controller. Once the controller warmed up fully, a small blinking light appeared on the load calibration section of the controller. The calibrate button was pressed on the load menu of the controller. Next, the Cal button was pressed. Once the Restore button was pressed, the machine was fully calibrated even though it read \u201cCalibration not restorable.\u201d The desktop was turned on, and once the system booted up, the Bluehill2 software was started. As the software started up, it automatically started the console. The console is how the computer communicates with the Instron machine. The extensometer was plugged into the back of the Instron machine and it showed up under Strain 1 (in the Bluehill2 software). Once the extensometer was plugged in, it flashed in the console screen reminding the user that it needed to be calibrated. The extensometer\u2019s calibration was restored to a previous calibration. From this point on, the tensile test, or the double shear bearing test could be started. 3.3.1 Tensile Testing Procedure Before starting any ordinary tensile test, the user needed to have at least six tensile specimens 33 prepared for the test. For each tensile specimen, the thickness, width and gage length (distance between the tabs) were recorded. The Specimen Protect feature was also used when initially clamping the specimens. The first composite tensile specimen was tested to failure (without the extensometer), in order to find its ultimate failure load. A limit load was created for the extensometer and was decided based on the ASTM D3039 [19]. As stated in ASTM D3039 [19], the material's modulus of elasticity can be measured anywhere between 25% and 50% of its ultimate load or yield load (if it is a metal). The limit load was calculated by multiplying the 1st specimen\u2019s ultimate load by 0.25 and this value was specified in Bluehill2\u2019s end of test criteria. In Bluehill2 software, there is an option of recording the strain using an extensometer and once the limit load is reached, the test will pause allowing the user to remove the extensometer. Next, the remaining five composite tensile specimens were tested. The next composite tensile specimens were loaded in the machine and the extensometer was attached for each specimen. Figure 18 shows a composite tensile specimen (with an extensometer mounted on its surface). Once at the limit load, the extensometer was removed, and the test continued up to the ultimate load. Note that the initial modulus recorded by the extensometer was very accurate, and after removal of the extensometer, the crosshead took over and the accuracy declined. 34 3.3.2 Double Shear Testing Procedure Once the standard Instron startup procedure was completed, the tensile double shear Bluehill2 test method was started. In the Appendix, one can find a detailed tutorial on the tensile double shear Bluehill2 test method. Procedure A double shear tension, in ASTM 5961 [18], was followed closely. The user needed to make sure that all the dimensions were recorded such as specimen width, specimen length, and specimen thickness and distance between the edge of the specimen to the hole edge. The fixture used for the double shear test consisted of an assembly made up of three cold drawn Steel plates with two bolts and nuts connecting all three plates. The double shear fixture is shown in between the clamps on the left in Figure 19. The double shear fixture is shown, in the center, in Figure 19. The close-up of the collar-specimen assembly is shown, on the right side, in 35 Figure 19 as well. Each double shear joint specimen was sandwiched between two Steel plates, two Steel collars, four washers and a nut, which can be seen on the left and the center in Figure 20. The extensometer, as required by the ASTM 5961 [18], is fixed on the fixture with a small steel plate and two bolts, shown on the right in Figure 20. The extensometer's knife edge was carefully placed inside the slit of the specimen and secured with a rubber band. The nut which held the screw assembly together with the specimen was only hand tightened. In the Bluehill2 software, as stated earlier, the end of test occured if the maximum force droped by 30% or if the maximum extensometer displacement was 0.1 in. This end of test criteria worked perfectly for the 0.05 in./min., 0.1 in./min. and 1 in./min. loading rates. But for the 2 in./min. and 6in./min. loading rates, the maximum extensometer displacement was lowered to 0.05 in. At faster loading rates (above 2 in./min.), the actuator had problems stopping immediately at very small deflections (0.1 in.) so applying this adujstment prevented the extensometer from accidently breaking due to over-deflection of the crossheads. 36 37 CHAPTER 4: THEORETICAL SOLUTION METHOD In this chapter, information is given on the equations that were used to find all of the mechanical properties of the material used. The theoretical equations used to come up with the macromechanical behavior of a lamina and laminate are included as well. 4.1 Experimental Equations 4.1.1 Equations Used for Unidirectional Carbon Fiber and Aluminum Double Shear Specimens The width to diameter ratio of the specimens needed to be measured and recorded. Below, W, is the specimen width, and D is the diameter of the hole. \ud835\udc4a \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc4a/\ud835\udc37 The edge to diameter ratio of the specimens needed to be measured and recorded. \ud835\udc38 \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = (\ud835\udc54 + \ud835\udc37/2)/\ud835\udc37 The diameter to thickness ratio of the specimens was measured and recorded. Below h is specified as the thickness of the specimen. \ud835\udc37 \u210e \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc37/\u210e The bearing stress was calculated by dividing the force, P, by the force per hole factor, k (equal (1) (2) (3) 38 to 1 for double shear test), with the diameter of the whole, D and by the thickness of the specimen, h. \ud835\udf0e\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strength was calculated by dividing the maximum force, Pmax, by the force per hole factor, k, with the diameter of the hole, D and by the thickness of the specimen, h. \ud835\udc39\ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strain was determined from the extensometer displacement, \ud835\udeff\ud835\udc56 divided by the k, force per hole factor, and the diameter of the hole, D. \ud835\udf16\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udeff\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37) The bearing chord stiffness was only reported if there existed an offset bearing strength. The linear portion, where the bearing stress ranges from 25 \u2013 40 ksi, is the bearing chord stiffness region. \ud835\udc38\ud835\udc4f\ud835\udc5f = \u2206\ud835\udf0e\ud835\udc4f\ud835\udc5f/\u2206\ud835\udf16\ud835\udc4f\ud835\udc5f 4.1.2 Equations Used for Tensile Testing of Unidirectional Carbon Fiber and Aluminum Specimens The maximum tensile strength F, was calculated by dividing the maximum force by the cross- (7) (6) (5) (4) 39 sectional area A. \ud835\udc39 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/\ud835\udc34 The tensile stress, \ud835\udf0e, was calculated by dividing the force by the cross-sectional area, A. \ud835\udf0e\ud835\udc56 = \ud835\udc43\ud835\udc56/\ud835\udc34 The chord modulus of elasticity, E, was calculated by the difference two tensile stress points and their equivalent tensile strain points. \ud835\udc38 = \u0394\ud835\udf0e/\u0394\u03b5 The extensometer strain, \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 , was calculated by dividing the extensometer displacement, \ud835\udeff\ud835\udc56, by the extensometer\u2019s gage length, \ud835\udc3f\ud835\udc54. The gage length of the extensometer was always 0.5 in. \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 = \ud835\udeff\ud835\udc56/\ud835\udc3f\ud835\udc54 The axial and transverse strains were plotted with respect to axial force. The slope of the transverse strain vs. axial load, \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 , was divided by the slope of the axial strain vs. axial load, \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 , and this equaled the Poisson\u2019s ratio of the material. \ud835\udf10 = \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 / \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 (8) (9) (10) (11) (12) 40 4.1.3 Equations Used with the Rosette Strain Gage Using the Equations (13) \u2013 (15), one can find the principle strains in the x-direction, \ud835\udf16\ud835\udc65, y- direction, \ud835\udf16\ud835\udc66 and finally the shear strain in the xy-direction, \ud835\udefe\ud835\udc65\ud835\udc66 . The three different theta values, \u03b81, \u03b82, \u03b83 were all angles relative to the axial strain gage. The strain rosette was placed on the composite quasi-isotropic specimen's surface so that each strain gage was in 0\u00b0, +45\u00b0 and 90\u00b0. So \u03b81 equaled 0\u00b0, \u03b82 equaled +45\u00b0, and lastly \u03b83 equaled 90\u00b0. The principle plane stresses were also transformed with a transformation matrix to the desired angle, \u03b8. In the transformation matrix c = cos \u03b8 and s = sin \u03b8. Where A is considered the transformation matrix below. The transformed plane stresses, \ud835\udf0e\u2032, equaled the transformation matrix, A times the plane stresses, \ud835\udf0e. (13) (14) (15) (16) (17) 41 Once the three principle strains were calculated then a transformation matrix was used to transform each of the three strains to the desired angle, \u03b8. The transformed plane strains, \ud835\udf16\u2032, equals Reuter's Matrix, R, times the transformation matrix, A, by the inverse of the R matrix, and lastly times the plane strains. The modulus of rigidity, G, was found by dividing the modulus of elasticity, \ud835\udc38, by 2 times Poisson\u2019s ratio, \ud835\udf10, plus 1. \ud835\udc3a = \ud835\udc38 2(1+\ud835\udf10) 4.1.4 Equations Used for In-Plane Shear Modulus Testing of Unidirectional Carbon Fiber Specimens The maximum shear stress, \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 (18) (19) (20) (21) 42 divided by the cross-sectional area times two. \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 2\ud835\udc34 The shear stress, \ud835\udf0f12, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65divided by the cross- sectional area times two. \ud835\udf0f12,\ud835\udc56 = \ud835\udc43\ud835\udc56 2\ud835\udc34 The modulus of elasticity in the +/- 45\u00b0 shear modulus test, \ud835\udc38\ud835\udc65\ud835\udc65, was calculated by the difference two stress points and their equivalent strain points. \ud835\udc38\ud835\udc65\ud835\udc65 = \u2212\u0394\ud835\udf0e \u0394\u03b5 The shear chord modulus of elasticity, \ud835\udc3a12, was calculated by the Equation (25). \ud835\udc3a12 = 1/( 4/\ud835\udc38\ud835\udc65\ud835\udc65 \u2212 1/\ud835\udc381 \u2212 1/\ud835\udc382 + 2\ud835\udf1012/\ud835\udc381 ) Converting normal strain to shear strain is done by dividing the shear strain by 2. \ud835\udf16 = 1/2 \u2217 \ud835\udefe 4.1.5 Equations Used for Volume Fraction Testing of Cured Reinforced Resins The ignition loss of the specimen in weight percent is calculated by subtracting the weight of the specimen, W1, and the weight of the residue, W2. (22) (23) (24) (25) (26) 43 Ignition lost, weight % = [(\ud835\udc4a1 \u2212 \ud835\udc4a2)/\ud835\udc4a1 ] \u2217 100 4.2 Theoretical Equations 4.2.1 Equations Used to Find Laminate In-Plane Engineering Constants The NASA Composite Laminate Report [24] was used to find all the laminate in-plane engineering constants (or also known as in-plane laminate material properties). Before finding the laminate in-plane engineering constants, the assumptions must be stated. The quasi-isotropic laminate, with a layup sequence of [0 0 +45 -45 +45 -45 90 90]s, meant that it\u2019s symmetrical and balanced. A symmetrical laminate simplifies the calculations since all that is needed to determine the in-plane engineering constants is the A matrix since the B matrix is composed of all zeros. But for asymmetrical laminates, one would need A, B, and D matrices. The subscripted numbers after the matrix, for example, the 1 and 2 in A12, which is in the number in the first row and second column of the matrix. The theoretical method of finding the laminate in-plane engineering constants required knowledge of Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material properties [21]. The experimental datasheet material properties were used inside the theoretical method. In Equation (28), to find the modulus in the x-direction, the stress in the x-direction is divided by the strain in the x-direction. Which can be also written as force per length in the x-direction, Nx , divided by the laminate thickness, h all over the strain. (27) 44 The A matrix simplifies to the one below since the Bij matrix is all zeros. For each layer in the laminate one needs to solve for a unique Q matrix. If a laminate has 16 different layers then there will be 16 Q matrices and after they are all solved they need to be summed together to form the A matrix. Equations (29) \u2013 (40) will be needed in order to solve for each value in the Q matrix. For any angled ply, one uses Equations (33) \u2013 (40). (32) (31) (30) (29) (33) (34) (28) 45 There is no force (or stress in the other two directions) so those are set to zero. This further simplifies the equations. (35) (36) (37) (41) (40) (39) (38) 46 After further simplification of the Equations (42) \u2013 (44), Equation (46) was equal to our modulus in the x-direction, Ex , only after this number was divided by the laminate thickness, h. \ud835\udc38\ud835\udc65 = \ud835\udc41\ud835\udc65/(\ud835\udf16\ud835\udc65 0 ) \u2217 1/\u210e Next, the same exact method is applied to the y-direction. The modulus in the y-direction, Ey equaled Equation (48). \ud835\udc38\ud835\udc66 = \ud835\udc41\ud835\udc66/(\ud835\udf16\ud835\udc66 0 ) \u2217 1/\u210e Next, the same exact method is applied to the xy-direction. The shear modulus in the xy- direction was found, in Equation (50), Gxy , only after divided by the laminate thickness, h. (42) (43) (44) (45) (46) (48) (47) 47 \ud835\udc3a\ud835\udc65\ud835\udc66 = \ud835\udc41\ud835\udc65\ud835\udc66/(\ud835\udefe\ud835\udc65\ud835\udc66 0 ) \u2217 1/\u210e Poisson\u2019s ratio, \u03c5xy , of the laminate was calculated using Equation (51). Poisson\u2019s ratio, \u03c5yx , of the laminate can was calculated using Equation (52). (51) (52) (50) (49) 48 CHAPTER 5: EXPERIMENTAL RESULTS In this chapter, the experimental results are explained in detail. Section 5.1 explained the validation process, which was conducted, on all the strain measurement devices. The axial modulus of elasticity and Poisson\u2019s ratio of Aluminum were validated. Section 5.2 summarized the material testing which was conducted on the unidirectional carbon fiber material. Section 5.3 explained the unidirectional carbon fiber material property testing. Section 5.4 explained the quasiisotropic carbon fiber laminate material property testing. Section 5.5 explained the experimental results found for the Aluminum double shear specimens. Section 5.6 explained the quasi-isotropic carbon fiber double shear specimens\u2019 experimental results. 5.1 Experimental Measurement Device Validation Before any strain measurement device was used on a composite material, its accuracy needed to be validated with commonly known material. In this case, an Aluminum specimen was tensile tested with a strain gage orientated in the axial direction, and another strain gage orientated in the transverse direction. Since the axial strain gage, the extensometer and the crosshead were measuring axial strain, their readings were compared. In the past theses, students were using the crosshead displacement to measure the modulus of elasticity. Using the crosshead displacement was very unreliable and it is explained in more detail in the next sub section. 49 5.1.1 Extensometer vs. Axial Strain Gage vs. Crosshead Displacement The test set-up of the Aluminum specimen is shown in Figure 21. The three principle directions and the clamped sections of a standard uniaxial tensile specimen are shown in Figure 21. Below in Table 1, an Aluminum sample was loaded and unloaded three times up to a tensile stress of 25 ksi. The tensile stress was calculated using Equation (9). A tensile stress of 25 ksi lies in the material\u2019s linear elastic region and it is far away from materials yield stress of 35 ksi. Table 1 shows the comparison of experimental results between the extensometer, strain gage and crosshead. Table 1 also shows the dimensions of the Aluminum specimen. The strain gage and extensometer experimental results were validated with the Aluminum 2024-T4 datasheet mechanical properties [25]. The moduli of elasticity, in Table 1, are in msi (10E6 lbs./in.2) and were calculated using Equation (10). There was less than 1% error between the extensometer and the strain gage when compared to the Aluminum 2024\u2019s modulus of elasticity. When comparing to the crosshead, there was an error of 64%. The crosshead displacement is not as accurate as an extensometer or a strain gage, because the crossheads have compliance (inside the actuator assembly) which elongates as load is applied. The actuator assembly starts to elongate, which significantly affects the experimental strain results. The small standard deviation showed how consistent the results were when using the three different measurement tools and the testing machine. 50 showing the clamped sections and the 3 principle directions (right) 51 Below in Figure 22, one can see the three runs that were done using the extensometer and the axial strain gage. The crosshead displacement was excluded from Figure 22, since the experimental strain varied so drastically from the extensometer and the axial strain gage. The strain gage and the extensometer read very similar moduli of elasticity. The extensometer and strain gage proved to be reliable, so both measurement tools were used on the composite specimens. 52 5.1.2 Poisson\u2019s Ratio Validation Using Axial and Transverse Strain Gages The Poisson's ratio of the Aluminum 2024-T4 needed to be validated. In Figure 23, one can see the axial and transverse strains plotted with respect to the axial force. The axial strain gage output is shown in blue and the transverse strain gage is shown in red. A linear curve fit was applied to both sets of strain gage data and their respective linear equations are shown, as well. Poisson's Ratio equaled to a value of 0.26, for the Aluminum specimen, using Equation (13). 53 5.2 Summary of Carbon Fiber Material Properties Below in Table 2, the results accumulated from Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg material datasheet [21] are summarized. The values which have a (-) dash meant that they were not given in the material's datasheet. The strengths were specified in ksi, which is 10E^3 lbs./in. Table 3 shows the experimental material properties of the Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material, which were experimentally tested in the Cal Poly\u2019s Aerospace Composites Lab. Table 4 shows the experimentally tested and calculated quasi-isotropic laminate properties. Poisson's ratio, for Umeco\u2019s MTM49 Unidirectional pre-preg material was used from a previous report\u2019s value [26] of 0.25. All these material properties are further explained in the next few sections. Looking at Table 2 and Table 3, the 0\u00b0 compressive modulus is 22.3 msi and the 0\u00b0 tensile modulus is 26.6 msi. All of the tensile axial moduli of elasticity were similar but they were slightly higher than the compressive modulus specified in the datasheet. The tensile and compressive modulus should be very similar since the fibers are assumed to behave like an isotropic material. This material was not tested in compression since compression specimens need to be a lot shorter, in length (ideally have less than 0.5in. in gage length). An extensometer could not be mounted on the surface of the compression specimen since there is not enough room between the grips. The best way to measure, the compressive modulus of elasticity would be to use an optical high-speed camera, which records the relative motion through optics. 55 5.3 Unidirectional Carbon Fiber Material Property Testing 5.3.1 Test for 0\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens A laminate of 8 plies, [0]8T, was laid up and tested along the fiber direction. The 0\u00b0 direction is always the direction of the applied load in a uni-axial test. The ASTM 3039 [19] required a minimum of five specimens per test, and having more than five specimens helped improve the 56 consistency of the results. Each specimen was 10 in. long by 0.5 in. wide and with a thickness of 0.046 in. The ASTM 3039 [19] required curing 2 in. long by 0.5 in. wide Aluminum tabs on the specimens to prevent premature failures from occurring. The grip pressure was set to 160 bar. The tensile test began with testing one 0\u00b0 unidirectional carbon fiber composite tensile specimen (without an extensometer) to failure, to find its ultimate load. The limit load of 2,000 lbs. was chosen since the ultimate load was 4,600 lbs. The last six 0\u00b0 unidirectional carbon fiber composite tensile specimens were loaded to 2,000 lbs., and at 2,000 lbs., the test was paused so that the extensometer could be removed safely. Once the extensometer was removed, the Instron machine's crossheads took over in measuring the tensile strain. The load cell accurately measured the ultimate load up to an accuracy of +/- 45 lbs. In Figure 24, the 0\u00b0 unidirectional carbon fiber composite tensile specimens are shown to the left and one of the clamped post-test 0\u00b0 unidirectional carbon fiber composite tensile specimen is shown on the right. Figure 25 shows all seven of the tested 0\u00b0 unidirectional carbon fiber composite tensile specimens (each color represents a different specimen). Figure 26 shows the extensometer mounted on the 0\u02da unidirectional carbon fiber composite tensile specimen with two rubber bands. The compressive modulus was specified in the datasheet and the tensile modulus was not specified in the datasheet. The experimental tensile modulus was compared to the compressive modulus and the difference between the two values was 19%. A 17% difference between the tensile strength when compared to the datasheet values. 57 58 60 5.3.2 Test for 90\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens Next, a laminate of 14 plies, [90]14T, was laid up and tested along the matrix direction. A couple extra test specimens were tested to find the optimum hydraulic clamping pressure. The clamping pressure was initially set to 160 bar and once the specimen was clamped, it cracked. The hydraulic clamp pressure was reduced to 60 bar in order to prevent this premature failure from occurring. Eight specimens were tested since the material is very brittle and unpredictable. When examining the stress-strain plot of the 90\u00b0 unidirectional carbon fiber composite tensile specimens, the ultimate tensile stress determined the location of where the specimen would fail. As one can see in Figure 27, the four 90\u02da unidirectional carbon fiber composite specimens, which failed at an ultimate tensile stress of around 5 ksi, ended up breaking in the center. Whereas, the specimens which failed at a lower ultimate tensile stress failed near the emery cloth. The experimental results (between all the specimens) showed a very consistent modulus of elasticity. The ultimate tensile strength of the material varied, due to the matrix is very brittle. The failure of a brittle material is very unpredictable which one can see in the Figure 28. There was 17% difference between the datasheet 90\u00b0 modulus of elasticity and a 29% difference between the 90\u00b0 tensile strength when compared to the datasheet values. The ultimate tensile strength variations might have been due to the low accuracy of the load cell, which typically occurs at low loads (around 100 lbs.) since the accuracy of the load cell is +/- 45 lbs. Table 6 shows the experimental results of all the 90\u00b0 unidirectional carbon fiber composite tensile specimens. 61 63 5.3.3 Test for +/-45\u00b0 Shear Modulus Specimens After following ASTM D3518 [20], a laminate was created with an orientation of [+/- 45]4S which is a symmetric laminate with alternating positive and negative 45\u00b0 plies. Another way to write this is [+45 -45 +45 -45 +45 -45 +45 \u2013 45]s. The extensometer was placed at 0\u00b0 relative to the specimen. The axial modulus of elasticity, Exx, was recorded and Equation (25) was used to find G12. Equation (25) requires knowledge of E1, E2, and \u03c512. Eight shear modulus specimens, for consistency, were tested since ASTM D3518 [20] required a minimum of five shear modulus specimens. The shear modulus specimens are shown in Figure 29. The post-tested shear modulus specimens looked the same as the pre-tested shear modulus specimens (since the failure occurred in the matrix and not in the fiber). Figure 30 shows the highly consistent shear specimen results. Table 7 showed the detailed experimental results. There was 35% difference between the in-plane shear modulus and a 43% difference between the in-plane shear strength when compared to the datasheet values. Testing for the shear strength is not an easy task since the shear modulus specimen has to be in full shear state at failure. The tabs on the ends of the specimen create stress concentrations on the ends, which cause the specimen to fail prematurely. 64 66 5.4 Quasi-Isotropic Laminate Material Testing 5.4.1 Test for Quasi-isotropic Tensile Specimens The same test method used for the 0\u00b0 and 90\u00b0 specimens was used to test the carbon fiber quasi-isotropic tensile specimens. Once one quasi-isotropic tensile specimen was tested to failure, the ultimate load was recorded to be 6,500 lbs. The next six quasi-isotropic tensile specimens were tested with the extensometer up to a force of 2,000 lbs. The test paused once the force reached 2,000 lbs. and then the extensometer was removed. Figure 31 shows the quasi-isotropic tensile specimens before (on left) and after (on right) they were tested. The region circled in red showed the area where there was a fiber failure. Figure 32 showed a close-up of the tensile failure. In Figure 32, looking at the picture on the right, one can see the 0\u00b0 fibers on the outer layer held together, while in the center of the laminate, a crack began to form. The crack, in Figure 32, is circled in red. 67 68 From Figure 33, one can see a close-up of the strain rosette, which was on Specimen #1. Shown in Figure 34, a rectangular strain rosette (CEA- 06-120CZ-120 made by VishayPG) produced very accurate results. The rosette was placed on the quasi-isotropic tensile specimen at a 0\u00b0-45\u00b0-90\u00b0 orientation and the wires were soldered very accurately. Each strain gage resistance was checked (with a voltmeter) and read 120 Ohms. The strain gage worked correctly if the resistance across the strain gage read the correct resistance specified in the user manual. The quasi-isotropic tensile specimen #1 was tested one time by recording the strains in the 0\u00b0 direction, 45\u00b0 direction and 90\u00b0 direction. In addition, when the strain gage was being applied to the surface, an 80-grit sandpaper was applied to the surface of the quasi-isotropic tensile specimen. The sanding of the outer 0\u00b0 layer might have affected the material\u2019s mechanical properties. Table 8 shows this 8% difference in modulus of elasticity between the extensometer and the strain gage. From Figure 35, one can see the slight drop in stress (at 20 ksi) due to the pause in the test. The different line colors show the seven different quasi-isotropic tensile specimens that were tested. The main thing to note is the percentage difference between the modulus of elasticity found with the strain rosette and the extensometer. The ultimate tensile strengths were very consistent which showed from a very low standard deviation of 3.87 ksi. 69 70 72 5.4.2 Quasi-Isotropic Tensile Specimen #1 In-Plane Experimental Material Properties Figure 36 shows experimental strain values of the extensometer, the axial strain gage, the +45\u00b0 strain gage and the transverse strain gage. A slight variation exists between the axial strain gage and the extensometer because the extensometer was not placed in the same location as the strain gage. The sanding error, like stated in the previous section, might have also contributed to the error of 8%. The test was stopped at a force of 2,000 lbs. A linear curve fit was applied to all of the three separate strain gage readings and are shown in Figure 36. Next, the Poisson\u2019s ratio of the quasiisotropic tensile specimen was found using Equation (12) and in-plane shear modulus of the quasiisotropic laminate was found using Equation (23). The axial modulus of elasticity was found using Equation (10). 73 5.4.3 Quasi-Isotropic Laminate In-Plane Theoretical Material Properties The theoretical material properties were found using the NASA report on Basic Mechanics of Laminated Composite Plates [24]. In Section 4.2.1, one can find the equations used to calculate the theoretical material properties. Before these equations could be used, a few assumptions were made: (1) The material to be examined is made of up of one or more plies (layers), each ply consisting of fibers that are all uniformly parallel and continuous across the material. The plies do not have to be of the same thickness or the same material. [23] (2) The material to be examined is in a state of plane stress, i.e., the stresses and strains in the through-the-thickness direction are ignored. [23] (3) The thickness dimension is much smaller than the length and width dimensions. [23] The values in Table 9 were needed in order to come up with the theoretical material properties. Table 9 shows the values that were applied into the laminate theory since the laminate theory required knowledge of the material properties of one layer of the unidirectional carbon fiber material. With the help of a strain rosette and the use of Equations (13) - (15), all the in-plane principle strains could be found. 74 Below in Table 10, one can see the calculated experimental material properties using the strain gage rosette. Three different in-plane laminate material properties were calculated based on three different force values (1500 lbs., 1750 lbs. and 1900 lbs.). The theoretical material properties were in agreement with the experimental material properties since the error between the modulus of elasticity was only around 10% and only 2% for the Poisson\u2019s ratio. The low standard deviation showed the reliability of the testing equipment and the strain measurement devices. 75 5.5 Fiber Volume Fraction Test ASTM D2584 [27], Standard Test Method for Ignition Loss of Cured Reinforced Resins, was followed closely. Three volume fraction specimens were tested inside the furnace shown on the right in Figure 37. On the left of Figure 37, one can see a fiber volume fraction test specimen. The fiber volume fraction specimen was placed on top of an Aluminum plate. While the furnace was preheated to a temperature of 1000\u00b0F, the Aluminum plate was weighed and each fiber volume fraction specimen was weighed in grams and then converted to lbs. in order to keep the units consistent. The measuring scale had a least scale reading of 0.1 g. The dimensions of each fiber 76 volume fraction specimens were carefully measured and recorded. Each specimen was placed on the Aluminum plate and left inside the furnace for one hour. Once all the epoxy burned off, the fiber volume fraction specimen was weighed and this was weight of the fibers. The initial weight of the fiber volume fraction specimen minus the final weight of the fiber volume fraction specimen was the weight of the resin (matrix). After doing some simple calculations, along with using the cured resin matrix density of 1.24 g/cm3(from the material\u2019s datasheet); the fiber weight fraction along with the fiber volume fraction was calculated and compared to the datasheet. In Table 11, one can see the three different fiber volume fractions along with the fiber weight fractions. The fiber volume fraction specimen dimensions are crucial to the determination of the fiber volume fraction. The measured thickness of the fiber volume fraction specimen varied from 0.1 in. to 0.103 in., which meant that the heat press cooked unevenly. The slight variation of the specimen\u2019s thickness affected the volume fraction by 4%. The 8.3% difference between the experimental fiber volume fraction and the datasheet fiber volume fraction varied because not enough pressure was applied to the laminate during the curing process. The lower fiber volume fraction of 0.55 compared to 0.6 meant that there was more resin in the laminate. Not enough resin was squeezed out in the cure process. The pressure applied by the heat press was limited, so achieving the optimum fiber volume fraction (of 0.6) was difficult. The fiber volume fraction significantly affected all of the material property testing which was conducted on the Umeco MTM 49 unidirectional material. A low standard deviation showed that the data was very consistent. 78 Section 5.6 was conducted in order to validate the numerical model with the experimental data. Modeling a metal before modeling a composite is very important because metals behave in a more predictable fashion. Metals are a lot simpler to model since they exhibit isotropic behavior whereas composites exhibit orthotropic behavior. The material property inputs for an isotropic material are much less than for a composite material. For a composite, the user has to input three different moduli of elasticity, three moduli of rigidity, and three Poisson\u2019s ratios. For metals, the user only inputs the modulus of elasticity and the Poisson\u2019s ratio. In this validation, Aluminum 2024-T4 was used as the material of choice. Once the linear elastic model was validated with a metal, then any other material should be validated as well, but only for the linear elastic region of the material. This also validates the boundary conditions and any interactions, which were used in the numerical model. 5.6 Aluminum 2024-T4 Double Shear Test The Aluminum 2024-T4 double shear specimens were tested on the same double shear fixture as the composite double shear specimens. From Figure 38, one can see the bearing stress vs. bearing strain response of the five tested Aluminum double shear specimens. The first section of the bearing stress vs. bearing strain plot (the flat initial region) is the strain correction region. Compliance between the Instron parts, along with the clamps, occurred upon initial loading of the specimen. The deformation of all the internal parts of the Instron machine in the strain correction region. The linear elastic region, (shown inside the red square in Figure 38) for the Aluminum, was between 5 ksi and 40 ksi and after this region; the material experienced a non-linear behavior 79 up to its ultimate bearing strength. The strain correction region and the non-linear region were removed, which can be seen in Figure 39. The non-linear region and the strain correction region were not part of the numerical model. Figure 38 showed that specimen #5 failed at an ultimate bearing stress of 130 ksi and the other four specimens failed around 114 ksi. The extensometer\u2019s knife-edge slipped on the face of specimen #1 through #4, but for specimen #5, the extensometer did not slip. The linear elastic region can be seen in Figure 39. The specimen alignment might have caused the variations in the linear elastic strain values. The ultimate bearing strength matched up the Aluminum 2024-T4 material\u2019s datasheet [25]. Table 12 shows the experimental results of the Aluminum double shear specimens. Both the yield and ultimate strengths were calculated in the Table 12. Figure 40 shows a bearing type of failure, which occurred in all the Aluminum double shear specimens. Figure 41 shows the Aluminum double shear specimens before and after they were tested. The region circled in red shows the area where the failure occurred. Each specimens\u2019 hole diameter increased in size and also each specimens\u2019 hole diameter did not go back to its original shape once the load was removed, which showed that the material reached a plastic deformation. 80 82 5.7 Composite Double Shear Test As one can see in Figure 42 (from a paper by Yi Xiao [28]), the composite double shear specimens behaved differently than Aluminum double shear specimens. Recall, all the composite double shear specimens were manufactured with a quasi-isotropic laminate orientation of [0 0 +45 83 -45 +45 -45 90 90]s. The 4%D is considered the bearing strength of the material. The composite double shear specimens held load (without failing) up to the knee point. At the knee point, the first ply failed (after this point, the material properties started to degrade) and the slope of the curve was reduced. The load increased up to the final point, also known as the ultimate bearing strength of the material, where it maxed out. One positive thing about designing a structure to fail in bearing, as opposed to net-tension or shear-out, is that the force dropped 30% of the maximum load. Whereas, in net-tension or shear-out failure, the load dropped down to zero. Figure 43 shows a close-up of the bearing failure, which occurred on the composite double 84 shear specimens. As one can see, there is an excessive amount of damage near the pin location. All of the specimens exhibited a similar type of failure, so there was no need to take a picture of each of the failed specimens. Figure 44 shows ASTM 5961\u2019s [18] failure codes used to characterize any of the failure modes seen in a composite double shear test. The failure code, B1I, is used throughout the rest of the experimental section, which signifies a bearing type of failure. 85 86 5.7.1 Curing Cycle 1 (Cytec\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test Figure 45 shows the composite double shear specimens before and after the double shear test. In Figure 45, on the right, highlights the crushing regions, in red. All the failures are consistent. Eight specimens were tested for each of the five loading rates. For load rate 0.1 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. When looking at the alternate cure cycle experimental data, in Tables 13 & 14, an interesting 87 trend appeared. At slower loading rates, the composite double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min. the composite double shear specimens failed at an average stress of 64.4 ksi and 63.5 ksi whereas at 1 in./min., 2 in./min. and 6 in./min. the composite double shear specimens failed around 52.3 ksi. Looking at all the different loading rates, it seemed as if all the composite double shear specimens had a similar knee point. 2 in./min. and 6in./min. showed a greater drop in load after the composite double shear specimens reached their ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. did not show a huge drop in load after the specimens reached the ultimate load. 89 The maximum values of all the plots, in Figure 46, were the ultimate bearing strengths. When looking at Figure 46, one can see that as the loading rate increased the non-linear region decreased in size. The red-circled sections, in Figure 46, show how the non-linear region decreased in size. The linear region does not change as drastically as the non-linear region. As the load rate increased, the rate of damage also increased which explained the reduction, in size, of the non-linear region. 90 Looking at all of the load rates, the moduli in the non-linear regions are lower than the linear elastic regions. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. 91 5.7.2 Curing Cycle 2 (Umeco\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test When looking at the datasheet cure cycle experimental data, in Tables 15 & 16, a similar trend appeared. At slower loading rates, the double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min., the specimens failed at an average stress of 62.7 ksi and 67.7 ksi, whereas at 1.0 in./min., 2 in./min. and 6 in./min., the specimens failed around or under 52.0 ksi. It also looks like at 2 in./min. and 6in/min. show a greater drop in bearing strength after the specimen reaches its ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. do not show a huge drop in strength after the specimens reach the ultimate load. In general, fast loading causes more damage to the specimen which overall reduces the specimen's ability to carry load. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. Eight specimens were tested for each of the five loading rates. For load rates 2 & 6 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. 93 When looking at Figure 47, one can see that as the loading rate increased the non-linear region decreased in size. In Figure 47, the red-circled section also showed the non-linear region decreased, in size, with increased loading rate. 94 5.7.3 Comparison between Cure 1 & Cure 2 In Figure 48, it is very clear that as loading rate increased, the ultimate bearing strength of the 95 material decreased regardless of the cure cycle. Further research can be done on how different cure cycles can affect the bearing response of a composite double shear specimen. Making the matrix less brittle and more ductile might improve the ultimate bearing strength of the material. Cure cycle 2 (Umeco\u2019s cure cycle) was 2% stronger in bearing when compared to the cure cycle 1 (Cytec\u2019s cure cycle). The MTM 49 Unidirectional carbon fiber pre-preg material was very sturdy by not being affected by an alternate cure cycle. 5.7.4 Comparison Between The Aluminum Double Shear Specimens & Quasi-Statically Loaded (0.05 in./min.) Composite Double Shear Specimens Aluminum is standardly tested at quasi-static load rate of 0.05 in./min, since it\u2019s strain rate independent [30] (not affected by different loading rates). The Aluminum double shear specimens 96 performed a lot better in bearing than the composite double shear specimens. Since the carbon fiber is more brittle by nature, its ultimate bearing strength is significantly lower than Aluminum. of the Aluminum double shear specimens was around 118 ksi and the ultimate bearing strength of the composite double shear specimens was around 63 ksi. That means that carbon fiber is 53% weaker than Aluminum 2024-T4 in a double shear joint configuration. The Aluminum double shear specimens yielded at around 40 ksi compared to the composite double shear specimens, which yielded at 30 ksi. As one can see from the bearing stress vs. bearing strain graphs, there is a huge difference in ultimate bearing strength between of both materials. It is interesting to note that both materials showed a strain correction region. The Aluminum double shear specimens and the composite double shear specimens did not catastrophically fail (they deformed without significantly dropping the applied load). 97 CHAPTER 6: NUMERICAL ANALYSIS Chapter 6 explains the overall finite element approach. Section 1 introduces the finite element model and different considerations, which were applied to the model. Section 2 explains the idea behind a convergence plot and its importance. Section 2 explains what factors influenced the numerical results. 6.1 Finite Element Analysis Introduction Once a Finite Element Analysis model is validated with experimental results, it can then be used in the design process. Abaqus 6.14-1 was used to model the double shear bearing test experiment conducted. All the different Finite Element software work very similarly and the only difference between them is their program interface. However, they all essentially break up the model into small elements and calculate the stress state on each element. The material properties are assigned to the elements and then, the boundary conditions and loads are applied to the model. In some cases when there are two or more parts, one might have to define different types of interactions or constraints for the model (for example, how those parts move relative to each other). The numerical software also predicts non-linear behavior, which requires a lot more material properties. Plasticity required the user to model the damage done on the material as load increased, which meant, implementing a degradation model. First, a numerical model was created and validated for the Aluminum 2024-T4 double shear 98 specimen. The Aluminum numerical model was only validated through the linear elastic region of the experimental data, which was shown in Figure 39. The Aluminum numerical model was adjusted for the composite specimen and the experimental results were compared to the numerical results. Abaqus keeps the units consistent, so when working with US Customary units make sure to stay consistent with the units, if using inches, stick to using inches. The displacement plots should be in the same units as one started with, and the stresses should be in pounds per square inch (psi). 6.1.1 Geometric Definitions The numerical model contained four parts. The two side plates, double shear specimen, and pin were modeled as deformable 3D solids. Both steel plates along with the double shear specimen were partitioned. The steel collars and center middle plate were neglected for simplicity. All the bolts, nuts and washers were also neglected in the model for simplicity reasons. 6.1.2 Material Creation, Section Assignments, & Meshing All the dimensions were defined in English units and the dimensions for each of the parts came from the fixture design. The fixture used in the numerical model was simplified. All the composite material properties were inputted in the elastic engineering constants. Table 17 showed the material properties, which were, applied to the Aluminum numerical model. A Steel solid homogeneous section and an Aluminum solid homogeneous section were created. 99 A composite layup section was applied to the composite double shear specimen and the element type was set to solid. Table 18 shows the material properties that were applied to the composite double shear specimen. In the composite layup section, the user is able to set the element stacking direction, the coordinate system, and the rotation axis. The user can also specify the laminate orientation and select the region for each ply within the model. In the Appendix, there is a tutorial of how the Abaqus composite double shear specimen was modeled. A single layer of unidirectional carbon fiber material is considered a transversely orthotropic material, where E2 is equal to E3 and G12 is equal to G13. E2 and E3 are both considered the matrix and E1 is considered the fiber. One thing to note was that the compressive modulus in the 1- direction (axial) was slightly lower than the tensile modulus, which was found in the Experimental section of the report. The Poisson\u2019s ratio in the 23-direction and the shear modulus in the 23- direction are usually very difficult to find experimentally. Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager was used to find some of the material properties that could not 100 be found experimentally. In the Appendix, one can find the tutorial on how to use Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager. One can also find a step-by-step Abaqus tutorial on the composite double shear specimen. Parts of the step-by-step tutorial were found from D.S. Mane [29] . The parts were individually partitioned which made meshing them very simple. Once the partition was created, the user needed to use the Seed Edge command, then select whole part, and for method select \u201cby number\u201d. As indicated below in sizing control, the user is able to assign the number of elements from one to however many. The convergence plot was constructed using four different nodes per element. The element\u2019s relative thickness was set to 0.5 since there were only two elements that made up the thickness of the part. 101 6.1.3 Assembly, Interactions & Steps The whole assembly was modeled very similarly to the experiment. Each part was given a dependent instance and no tie constraints were used in the model. A contact step and a load step were added to the analysis. The contact step initiated the contact between the pin and the steel plates and also the pin and the specimen. The load step served to apply load to the analysis once full contact was established. The pin was not constrained to the specimen with a tie constraint because that implied a condition similar to being welded. So in contrast, a surface-to-surface interaction was established between the pin, the steel plates and the specimen. The sliding formulation selected was finite sliding. The pin was set as the master surface and the slave surface consisted of two surfaces. One was the surface in contact with the pin and the inner side of the specimen and the other was the surface in contact with the pin and the inner side of both steel plates. The slave adjustment was set to a value of 0.007 in. A contact property with a tangential behavior (the friction formulation was set to penalty and the friction coefficient was set to 0.46). In addition, a normal behavior contact property with the pressure-overclosure was set to \u201cHard\u201d Contact; constraint enforcement method was set to default, and allowed separation after contact. 6.1.4 Boundary Conditions & Loads The boundary conditions applied to the model needed to be assigned carefully. The top face of the specimen (opposite face with the hole) was fully fixed in the x, y and z directions. This was 102 similar to the clamped condition, which is applied by Instron\u2019s crossheads. The second boundary condition that was applied was on the outer pin surface and the inner hole surfaces of the steel plates and the bearing specimen. In the contact step, the pin, steel plates and specimen were not allowed to move in the x, y and z directions. The load step was modified to allow the side plates, pin and specimen to move in only the y-direction. The combined load of 600 lbs. was applied to both of the bottom faces of the steel plates. This was done by applying the load, in the load step, as a total force distribution pressure load. The loading condition used in the model was similar to the experimental loading condition, where a fraction of the force is applied at each time interval. Some elements in the model experienced plastic deformation only when the applied load was over 800 lbs. This meant that certain elements were in stress state beyond their linear elastic limit. The ultimate force was not predicted, by the numerical analysis, since that occurred in the non-linear region. 6.2 Numerical Results This section provides the explanation of the convergence plot and talks about the factors, which influenced the numerical results. In Chapter 7, the numerical results are explained in detail. 6.2.1 Convergence Plot For the numerical model, a partition was created on the face of the specimen. Taking time to draw a symmetrical and neat partition prevented the mesh from becoming unsymmetrical and 103 prevented unusual results. The partitioned double shear specimen is shown in Figure 49. In Figure 50, one can see a close up of the partitioned region around the hole. After a partition was created, the user was able to assign a specific amount of elements using the Seed Edge command. Here the user is able to set the total amount of nodes per element to any value. For the convergence plot, 2, 6, 8, and 10 nodes per element were chosen, and the final vertical deflection at the pin was compared. A convergence plot was created to see if adding more elements to the model actually improved accuracy. Knowing the optimum amount of elements for the least amount of time for the model to complete is very important in the design process. As one can see from Figure 51, as the total amount of nodes per element increased, the deflection did not change significantly. Using more than six elements per node did not significantly improve accuracy, but it did take longer to run. 6.2.2 Factors That Influenced the Numerical Results Increasing the total amount of elements through the thickness of the part, did not significantly affect the pin deflection results. Changing the axial modulus (from tensile to compressive) significantly affected the pin deflection results. The compressive axial modulus was imported into Abaqus rather than the tensile modulus, because the double shear test is mainly a compression type of loading. The fibers are in compression around the hole. When initially assuming a frictionless contact (when the frictional coefficient equaled zero) the specimen ended up colliding with one of the side plates. Changing the frictionless coefficient 104 from zero to 0.46 helped prevent the specimen from colliding with one of the side plates. 105 106 CHAPTER 7: COMPARISON BETWEEN EXPERIMENTAL & NUMERICAL DOUBLE SHEAR RESULTS The slope of the reaction force vs. pin displacement was compared between both the experiment data and the numerical model. First, the numerical Aluminum model was validated. Then the numerical composite model was validated. 7.1 Numerical Aluminum Model Comparison to Experimental Results Looking at Figure 59, the region highlighted in red was due to the compliance in the testing assembly. The bearing stress vs. bearing strain plot was then converted to a load (reaction force in the y-direction) vs. pin displacement plot. All of the specimens were plotted up until the linear region. Looking at Figure 60, of the five tested Aluminum double shear specimens, the numerical results only matched up with one. The four other Aluminum double shear specimens might have slipped with respect to the extensometer\u2019s knife-edge. One way to tell is by the lower load (reaction force in the y-direction) vs. pin displacement slopes. In Table 19, the total error when comparing the experimental slope to the numerical slope was 16%. Misalignment of the specimen might have caused this significant error to occur. 107 108 7.2 Composite Numerical Model Comparison to Experimental Results Figure 54 showed the load (reaction force in y-direction) vs. pin displacement response of the 0.05 in./min. composite double shear specimens that were cured to the recommended datasheet cure cycle. Three of the eight tested composite double shear specimens at 0.05 in./min. did not slip. The strain was corrected using the same method that was applied to the Aluminum double shear specimens. Of the eight carbon fiber specimens that were tested, only three of them closely matched up to the numerical results. The numerical model was loaded to 600 lbs., which was still within linear elastic limit of the material. The load (reaction force in y-direction) vs. pin displacement slopes between all the experimental specimens shown were compared to the numerical model. In Table 20, the average error between the numerical slope and the experimental slopes was about 7.1%. Alignment is a huge factor, which can affect experimental results quite significantly. There will always be error between the experimental and numerical results. The numerical 109 results are the idealized results and the experimental results have so many factors, which can influence their results. Errors from 7% to 16%, for both the aluminum double specimens and the composite double shear specimens, are actually quite reasonable because there is always error in the manufacturing process, displacement measuring equipment, load cell, specimen alignment exc. 111 CHAPTER 8: CONCLUSION The first important contribution of this study was to see how different loading rates affected the ultimate bearing strength of a composite material. One can see that at 0.05 in./min. and 0.1 in./min. (for both cure cycles) the composite double shear specimens carried more load compared to higher load rates of 1 in./min., 2 in./min. and 6 in./min.. All of the specimens failed in bearing and not in net-tension or shear-out. The second important contribution of this study was to see how the recommended datasheet cure cycle and the alternate cure cycle affected the ultimate bearing strength. The two different cure cycles behaved very similarly under the five different loading rates. The average ultimate bearing strength of the Aluminum double shear specimens was 118 ksi and for the composite double shear specimens it was 65 ksi. The experiment showed that carbon fiber material is significantly weaker, in a double shear tensile loading configuration, compared to Aluminum. Ductile materials, like Aluminum for example, handle the double shear tensile loading configuration a lot better than the carbon fiber material, which is brittle. Each carbon fiber sheet is relatively thin which is also very poor for carrying bearing stress. Usually what designers do is use inserts inside and around the hole if they need to improve the bearing strength of a composite joint. The inserts help redistribute the stress concentrations (which are caused by mechanical fasteners) and prevent the brittle material from cracking. The inserts are usually made from ductile materials, like fiberglass or Aluminum. 112 8.1 Recommendations The experiments were carried out using carbon fiber unidirectional pre-preg tape. Similar research can be done using various other materials like: kevlar, fiberglass, or even hemp. Similar testing can be done using a single shear joint configuration. Various carbon fiber types can be tested as well. MTM-28 material is a thicker type of unidirectional fiber, which would be very interesting to test. A high-speed video camera would be a more efficient way to monitor deflection since the extensometer's range was the limiting factor in the data capture. A more in depth case study can be conducted on different cure cycles of composite resins. The pre-load function in the Bluehill2 software can be utilized in order to try to eliminate some of the strain correction region. In addition, a more in-depth experimental analysis can be conducted on the knee point region of the composite (carbon fiber) double shear specimen. 113 REFERENCES 1. Airbus Versus Boeing-Composite Materials: The sky's the limit. http://www.lemauricien.com/article/airbus-versus-boeing-composite-materials-sky-slimit. 2. Lessard, L.B. (1995). Computer aided design for polymer-matrix composite structures. In S.V. Hoa (Eds.), Design of joints in composite structures. New York: Marcel Dekker. 3. Baker, A. (1997). Composites engineering handbook. In P.K. Mallick (Eds.), Joining and repair of aircraft composite structures. New York: Marcel Dekker. 4. Okutan, B. (2001). Stress and Failure Analysis of Laminated Composite Pinned Joints. Journal of Composite Materials, 19. 5. Chen, J.C., Lu, C.K., Chiu, C.H., & Chin, H. (1994). On the influence of weave structure on pin-loaded strength of orthogonal 3D composites. Composites, 25, No: 4, 251-262. 6. Quinn, W.J., & Matthews F.L. (1977, April). The effect of stacking sequence on the pin- bearing strength in glass fiber reinforced plastic. Journal of Composite Materials, 11, 139- 145. 7. Liu, D., Raju, B.B., & You, J. (1999). Thickness effects on pinned joints for composites. Journal of Composite Materials, 33, 2-21. 8. Stockdale, J.H., & Matthews, F.L. (1976, January). The effect of clamping pressure on bolt bearing loads in glass fiber-reinforced plastics. Composites, 34-39. 114 9. Kim, S.J., & Kim, J.H. (1995). Effects of geometries, clearances, and friction on the composite multi-pin joints. AIAA Journal, 34, No: 4, 862-864. 10. Hyer, M.W., & Klang, E.C. (1985). Contact stresses in pin-loaded orthotropic plates. Journal of Solids and Structures, 21, No: 9, 957-975. 11. Pierron, F., Cerisier, F., & Lermes, M.G. (2000). A numerical and experimental study of woven composite pin-joints. Journal of Composite Materials, 34, No: 12, 1028-1053. 12. Chang, Fu-Kuo, Scott, R.A., & Springer, G.S. (1982, November). Strength of mechanically fastened composite joints. Journal of Composite Materials, 16, 470-494. 13. Ger, G.S., Kawata, K., Itabashi, M.: Dynamic tensile strength of composite laminate joints fastened mechanically. Theor. Appl. Fract. Mech. 24(2), 147\u2013155 (1996). 14. Li, Q.M., Mines R.A.W., Birch R.S. (2000, September). Static and dynamic behavior of composite riveted joints in tension. 15. United States Naval Academy (USNA). (2003). Composite Orientation Code. http://www.usna.edu/Users/mecheng/pjoyce/composites/Short_Course_2003/7_PAX_Sh ort_Course_Laminate-Orientation-Code.pdf 16. Kretsis, G., & Matthews, F.L. (1985, April). The strength of bolted joints in glass fiber/epoxy laminates. Journal of Composite Materials, 16, 92-102. 17. Yeole, Amit. (2006, December). Experimental Investigation and Analysis for Bearing Strength Behavior of Composite Laminates. 115 18. Anonymous, \u201cStandard Test Method for Bearing Response of Polymer Matrix composite Laminates,\u201d ASTM Standards, Designation: 5961/5961M-05. 19. Anonymous, \u201cStandard test method for tensile properties of fiber-resin composites,\u201d ASTM Standards, Designation: 3039-76. 20. Anonymous, \u201cStandards. In-plane shear stress-strain response of unidirectional reinforced plastics,\u201d ASTM Standards, Designation: 3518-76. 21. Umeco, \u201cMTM 49 Series Pre-preg System \u2013 Unidirectional Material Properties.\u201d 22. Cytec, \u201cMTM 49-3 \u2013Unidirectional Material Properties.\u201d 23. Instron, \u201cInstron 8801 Servo-hydraulic Machine Photo.\u201d http://www.instron.us/en-us/ 24. Nettles, A.T., (1994, October) \u201cBasic Mechanics of Laminated Composite Plates.\u201d 25. ASM Aerospace Specification Metals Inc., \u201cDatasheet Mechanical Properties of Aluminum 2024-T4.\u201d 26. Anonymous, \u201cProject 1 Report\u201d ME-412. 27. Anonymous, \u201cStandard test method for ignition loss of cured reinforced resins,\u201d ASTM Standards, Designation: 2584-02. 28. Xiao, Yi. \u201cBearing strength and failure behavior of bolted composite joints (part II: modeling and simulation). 29. De, S. MANE 4240/CIVL 4240: Introduction to Finite Element. Abaqus Handout. 30. Semb, Evind. \u201cBehavior of Aluminum at Elevated Strain Rates and Temperatures.\u201d 116 APPENDICES A.1. Drawings for the Fixture Assembly 117 118 A.2. Tutorial on Bluehill2 Test File Setup Various settings were changed inside the BlueHill2 software. Below, I will show a couple of the parameters that were changed. Navigating through the menus is self-explanatory. In the Control submenu, the load rate was changed for each test. The quasi-static case was tested first at a load rate of 0.05 in./min. The second load rate, which was tested, was 0.1 in./min., the third was 1 in./min., the fourth was 2 in./min. and the fifth speed, which was tested, was 6 in./min. 119 The end of test criteria was changed to the ASTM specification. End of test 1 specifies the drop in the load of 30% the peak value and end of test 2 is specified as an extensometer displacement of 0.1 in. The extensometer shows up at Displacement (Strain 1) as a separate channel. 120 In the Control submenu, the sampling rate was changed from the default rate of 10 samples/sec to 3 samples/sec as required by ASTM D5961. This change showed a significant reduction of noise within the extensometer displacement readings. A value of 500 ms was adjusted for the time channel and the load sampling rate was left to default interval of 56 lbf. 121 Below in the Control submenu, the source of tensile strain was changed from the BlueHill2 default channel of \u201cTensile Strain\u201d to the \u201cStrain 1\u201d. The extensometer shows up as \u201cStrain 1\u201d. 122 Bluehill2 also has the option of calculating numerous parameters. In my experimental testing, I needed to calculate the ultimate bearing strength so I picked User Calculation. Then Bluehill2 gives you an option to define various variables like: D (diameter of hole), k (calculation factor for double shear k = 1), Pmax (maximum force carried by the specimen prior to failure), and t (defined as the thickness of the laminate). After all of your variables are defined, the equation designer tool 123 is used to create your equation of interest. In the Results submenu, the user is able to pick exactly which values he/she wants to output while in the test screen. The results are outputted as a column of values for each of the different test specimens. I wanted to output all of these parameters below while I was conducting my tests. 124 In the Graph submenu, the user is able to output two real-time changing graphs. For graph 1, I chose to output Instron crosshead displacement vs. load and for graph 2 I chose to output extensometer displacement vs. load. The X-Data was set to either Extension (for Instron crosshead displacement) or Displacement (Strain 1) (for extensometer displacement. The Y-Data was set to Load for both graph 1 and graph 2. 125 In the Raw Data submenu, Bluehill2 has a great function, which allows the user to export any given output of experimental data into a .csv file. This file can later be opened up with Excel and used to calculate various experimental stresses, strains and other parameters of interest. For my experimental testing, I was interested in outputting: time, crosshead displacement, extensometer 126 displacement, load and corrected position. The last bit of raw data, which needed to be outputted, is shown below. This set of data is saved onto the same .CSV file as the one specified in the previous screen. This set of data is located in its own set of two columns in the .CSV file. 127 A.3. Tutorial on Finding the Unknown Engineering Constants Autodesk created a very powerful tool, which can help the user figure out unknown engineering constants of a ply. For example from the experimental results, the user is able to experimentally determine E1, E2, G12 and \u03c512. Shown below are all the values, which the user inputs into the Autodesk Simulation Composite Analysis 2015 Material Manager. Make sure to label the 128 material a unique name and choose the correct units. The fiber type should be carbon intermediate for the MTM 49 since it is not the ultra-high fiber modulus. The volume fraction should be the one, which was found experimentally in the Results chapter, of 0.55. In Figure 67, in the first row of the Ultimate Lamina Strengths the user inputs the tensile strength in the 0\u00b0 and the 90\u00b0 directions. In the second row, the user inputs the compressive strength in the 0\u00b0 and 90\u00b0 directions and finally, in the last row, the user the user inputs the in-plane shear strengths. 129 In Figure 68, the user will input the known modulus of elasticity into the Lamina Elastic Constants section. The in-plane Poisson's ratio, which was assumed to be around 0.244, was used from a previous paper, which found the material property experimentally on the same MTM 49 Unidirectional material. The in-plane shear modulus was inputted from the experimental testing. 130 The key is to assume a value if you do not know what it is. After all the values have been inserted into the program go into the File, menu and then click optimize. It will ask you if you want to save the material properties somewhere and all you do is specify where you want to save the data. It will take a couple seconds to optimize the values accordingly. A.4. Tutorial on Outputting Force vs. Pin Deflection from Abaqus The pin deflection needed to be monitored for one node on the specimen. The area of interest is shaded in dark blue and the red dot signifies which node was monitored for its vertical deflection. In Figure 70, one can see the deflection in the y-direction, which occurs around the hole. This hole 131 is a localized compression zone. 132 Next what was needed was to have a force vs. time graph. The top most nodes on the specimen were fixed using the encastre boundary condition. The reaction force in the y-direction was captured for all the nodes that make up the top of the specimen. Once all the reactions at each nodes were captured, the whole region was summed up. Under create XY plot click ODB field output and then click continue. Under the Variables tab, find the Output variable box, and in the position menu, click Unique Nodal and then go into RF: Reaction Force and check the RF2 button. Since we are interested in the reaction force in the y-direction (2 direction). Next, click the Elements/Nodes tab and then pick the from viewport button and then click Edit Selection. Once all the fixed nodes are selected, as shown in Figure 72 below, click the Done button in the viewport. Lastly, go into Active Steps/Frames; make sure All steps are selected and set it to Frame. In the bottom of the window, make sure a green checkmark is applied to both the Contact and the Load steps. 133 Using the Create XY Data option in Abaqus, the user is able to go into Operate on XY data. In the Operators window, pick sum((A,A,...)), then under XY data, select all the Reaction Force nodes, which show up as _RF:RF2 and then click Add to Expression. Once all the nodes are inside the Sum operator, hit the Plot Expression button. This will output a force vs. time graph. 134 Once both the force vs. time graph and deflection vs. time graph are created, one needs to combine both graphs. In the Create XY Data, click Operate on XY Data and then press Continue. Under the operator tab, find combine(X,X) and then click it once. The combine operator requires two variables for the plot. For the first variable, click the deflection XY data, and for the second variable, click the Reaction Force 2 XY data. Make sure a comma separates both variables. Once done click the plot expression button and this should bring up a Force vs. Pin Deflection plot as shown in Figure 74. 135 A.5. Tutorial on Modeling the Double Shear Bearing Specimen Assembly Open up Abaqus 6.14. The numerical model should look like something like this. The complete assembly, the pin and one of the side plates modeled with Abaqus 6.14. 136 A.5.1. Model Creation Create a new model by right clicking the Models category. Name it DoubleShear. Then press Ok. 137 A.5.2. Part Creation Next, we have to create the parts for the model, after that, we partition each of the parts. Click on the + button to expand the options inside the DoubleShear model. Right click on Parts and press Create. A menu will appear like the one shown below. Name the part SteelPin. Keep the modeling space: 3D, the type: deformable, the base feature shape: Solid and for the base feature type: Extrusion. Click continue. 138 Click the Create Circle button. Using the dimension tool below set the radius to 0.125 in. Always be consistent with your units (I am using inches). 140 Next, we need to create the double shear specimen. Copy the step above and only change the name of the part to Specimen. Use the rectangle tool (to the right of the circle tool) and make a basic rectangle. 141 Using the dimension tool set the width of the part to 1.5 in. and the length of the part to 5.5 in. Create a Line down the middle of the part. Locate the center of hole 0.75 in. from the bottom edge of the specimen and make sure the hole is centered along the specimen\u2019s width. 142 Now, delete the centerline with the eraser tool, which is highlighted and then click on the centerline (which should highlight in red) and click done. Click the eraser tool to disable it. 143 In the bottom of the drawing window, it should read, \u201cSketch the section for the solid extrusion\u201d. Click the Done button. Set the depth to 0.1 in. Since the carbon fiber specimen\u2019s thickness was 0.1 in. Next, we need to create the side steel plate. Copy the step above and only change the name of the part to SidePlate. Use the rectangle tool (to the right of the circle tool), make a basic rectangle, and use the circle tool to create a hole in the plate. The side steel plate should be 2 in. by 4 in. and it should have a 0.141 in. radius hole. Which is located 1.0 in. from the top of the side plate. Lastly, remove the centerline and then set the depth to 0.25 in. Since the side steel plates had a thickness of 0.25 in. The three parts should look like this once they are completed. 144 A.5.3. Partition Creation A partition was created on the side plates and on the specimen. This made sure that when the mesh was generated all the elements stayed symmetrical. One major source of error in finite element analysis is due to elements not being symmetrical and the same size. One way to avoid this problem is to create your own mesh, which requires the user to partition the part based on what is of interest to him/her. Pick Tools, in the top drop down menu, and choose Partition. Click Face for the partition type and then click on the side plate face highlighted in orange. 145 Click Done and then it will ask to click a line vertical and to the right. Shown below, the highlighted edge is shown in pink, and the non-highlighted edges are shown in red. The part will switch from 3D to 2D and then here the user is able to create the partition desired. Create the partition below with these dimensions using the circle and line tools. It is important to keep the mesh coarse on parts which are not of main interest. 146 Apply the same method to the double shear specimen. The partition on this specimen was a lot more detailed than on the steel side plate. There are six circles, which are all equally spaced apart. The three outer radii were 0.5 in., 0.375 in., and 0.625 in. The three inner radii were 0.1875 in., 0.25 in., and 0.3125 in. A finer partition was created on the three inner radii where the circle was segmented into 64 equally spaced smaller sections. 147 The final partitioned parts should look like this. 148 A.5.4. Material Creation The material properties need to be created. Two materials were used in the analysis: steel and a unidirectional carbon fiber material. Under the Parts category, right click and click create. Name the material Steel. Go into the Mechanical option, then press elasticity, then elastic. Keep the type set to a default isotropic setting. Set the Young\u2019s Modulus to 34e6 and set the Poisson\u2019s ratio to 0.3. Follow the step right above, and create a new material and name it Uni. For the type, select 149 Engineering Constants. Include the material properties in the Table below (remember that msi is 106 psi)." + ] + }, + { + "image_filename": "designv8_17_0001163_O201110441050686.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001163_O201110441050686.pdf-Figure2-1.png", + "caption": "Fig. 2 View of the vine crushing part.", + "texts": [], + "surrounding_texts": [ + "9 The article was submitted for publication on 2010-11-16, reviewed on 2011-01-19, and approved for publication by editorial board of KSAM on 2011-01-31. The authors are Sung Il Kang, Graduate Student, Soo Nam Yoo, Professor, Chonnam National University, Gwangju, Korea, Yong Choi, Agricultural Researcher, National Academy of Agricultural Science, RDA, Suwon Korea, and Young Joo Kim, Senior Researcher, KSAM member, Environmental Materials & Components Center, Korea Institute of Industrial Technology, Jeonju, Korea. Corresponding author: S. N. Yoo, Professor, Department of Rural and Bio-systems Engineering and College of Agricultural and Life Sciences, Chonnam National University, Gwangju, 500-757, Korea; Tel: +82-62-530-2155; Fax: +82-62-530-2159; E-mail: .\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uac15\uc131\uc77c \uc720\uc218\ub0a8 \ucd5c \uc6a9 \uae40\uc601\uc8fc\nDevelopment of a Vine Crusher for Harvesting Sweet Potato\nS. I. Kang S. N. Yoo Y. Choi Y. J. Kim\nThis study was carried out to develop a vine crusher for harvesting sweet potato. The experimental two-row vine crusher attachable to agricultural tractor composed of vine crushing part with frail type vine crushing blades and vine lifting blades, power transmission part with chain and gear transmission mechanism, crushing height control part with two control wheels and manual levers, and implement frames, was designed and fabricated. And this vine crushing performance was also analyzed.\nFrom vine crushing tests, backward travel direction (i.e., rotational direction of the vine crushing blades) showed better vine crushing performance than forward travel direction. Crushing ratio of remained vine was increased, and length of remained vine and length of crushed vine were decreased as working speed was decreased and rotational speed of vine crushing blades was increased. At a working speed of 0.27 m/s and rotational speed of vine crushing blades of 800 rpm, crushing ratio of remained vine was 98%, length of remained vine was 104 mm, and length of crushed vine was 327 mm. But, when crushing vine on irregular ridges, vines and mulching vinyl were wound in the vine crushing part. Therefore, change of location of power transmission chain mechanism, and an automatic control device for controlling crushing height were needed.\nKeywords : Vine crusher, Sweet potato, Frail blade\n1. \uc11c \ub860\n\uc77c\ubc18\uc801\uc73c\ub85c \uad6d\ub0b4\uc758 \uace0\uad6c\ub9c8 \uc7ac\ubc30\ubc29\ubc95\uc740 \ubcd1\ud574\ucda9 \ubc29\uc9c0, \uc218\ud655 \ub7c9 \uc99d\uac00 \ub4f1\uc758 \uc7a5\uc810\uc73c\ub85c \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\uac00 \ub9ce\uc740 \ubc18\uba74, \uc678\uad6d\uc758\n\uacbd\uc6b0 \uc7ac\ubc30\uba74\uc801\uc774 \ub300\uaddc\ubaa8\ub85c \uac70\uc758 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\ub97c \ud558\uc9c0 \uc54a\uc73c \uba70, \ubcc4\ub3c4\uc758 \ub369\uad74\ucc98\ub9ac\uc791\uc5c5 \uc5c6\uc774 \uc218\ud655\uc791\uc5c5 \ud6c4 \ub369\uad74 \ubc0f \ud611\uc7a1\ubb3c\ub85c \ubd80\ud130 \uace0\uad6c\ub9c8\ub97c \uc120\ubcc4\ud558\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \uad6d\uc678\uc758 \uacbd\uc6b0 \uace0\uad6c\ub9c8 \ub369 \uad74\ucc98\ub9ac\uae30\uc5d0 \uad00\ud55c \uc5f0\uad6c\ub294 \uac70\uc758 \uc5c6\ub294 \uc2e4\uc815\uc774\ub2e4. \uace0\uad6c\ub9c8 \uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \uc904\uae30\uc808\ub2e8\uae30\uc640 \ube44\ub2d0\uc81c\uac70 \uae30\uc758 \uc774\uc6a9\uc73c\ub85c ha\ub2f9 \uc791\uc5c5\uc2dc\uac04\uc740 \uc57d 8\uc2dc\uac04\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4 (Namerikawa, 1989). \ub610\ud55c \uc904\uae30\uac77\uc5b4\uc62c\ub9bc\ubd09\uacfc \ud504\ub808\uc77c type \ud68c\n\uc804\ub0a0 \uc808\ub2e8\ubc29\uc2dd\uc744 \uc774\uc6a9\ud55c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 1\uc870 \uace0\uad6c\ub9c8 \uacbd\uc5fd\ucc98\ub9ac \uc7a5\uce58\ub97c \uc774\uc6a9\ud558\uc5ec \uc8fc\ud589\uc18d\ub3c4 0.35\uff5e0.46 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 28.6 m/s\uc5d0\uc11c \uacbd\uc5fd\ucc98\ub9ac\uc728 91.7\uff5e92%, \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774 38\uff5e43 cm\ub85c \uacbd\uc5fd\ucc98\ub9ac \uc815\ub3c4\uac00 \uc591\ud638 \ud558\uc600\ub2e4\uace0 \ubcf4\uace0\ud558\uc600\uc73c\uba70 (Park and Choi, 1995), \uae30\uc874 \ub369\uad74\uc808\ub2e8\uc7a5\uce58 \ub4a4\uc5d0 \ub514\uc2a4\ud06c\ud615 \ub369 \uad74\uc808\ub2e8\uc7a5\uce58\ub97c \ucd94\uac00\ub85c \ubd80\ucc29, \uac1c\ub7c9\ud558\uc5ec \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774\uac00 15.4 cm\ub85c \ub0ae\uc544\uc84c\uc74c\uc744 \ubcf4\uace0\ud558\uc600\ub2e4(Park and Choi, 1997). Ha(2006)\ub294 \ub3d9\ub825 \uacbd\uc6b4\uae30\ub97c \uc774\uc6a9, \uacbd\uc6b4\uae30 \ud6c4\ubc29\uc5d0 1\uc870\uc6a9 \ub369 \uad74\ucc98\ub9ac\uc7a5\uce58\ub97c \ubd80\ucc29\ud558\uc5ec 92%\uc758 \ub369\uad74\ucc98\ub9ac\uc728, 2.5 h/10a \uc791\uc5c5 \uc2dc\uac04\uc73c\ub85c \uad00\ud589 \uc778\ub825\uc758 \uc791\uc5c5\uc2dc\uac04\uc778 26 h/10a \ubcf4\ub2e4 \uc57d 1/10\ub85c \uc791\uc5c5\uc2dc\uac04\uc744 \uc808\uc57d\ud560 \uc218 \uc788\ub294 \uac83\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub9c8\ub298\n\ubc14\uc774\uc624\uc2dc\uc2a4\ud15c\uacf5\ud559 (J. of Biosystems Eng.) Vol. 36, No. 1, pp.9~14 (2011. 2) DOI:10.5307/JBE.2011.36.1.9\nOpen AccessResearch Article", + "\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 \uc904\uae30\uc808\ub2e8 \ubc0f \ube44\ub2d0\ud53c \ubcf5 \uc81c\uac70\uae30\ub97c \uc774\uc6a9\ud558\uc5ec \uc808\ub2e8\ub192\uc774 100 mm, \uc8fc\ud589\uc18d\ub3c4 0.53 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 67.86 m/s\uc5d0\uc11c \uc808\ub2e8\uc815\ub3c4 95.5%\ub85c \ubcf4\uace0\ud55c \ubc14 \uc788\ub2e4(Noh et al., 1999). \uc6b0\ub9ac\ub098\ub77c\uc758 \uace0\uad6c\ub9c8\uc758 \ucd1d \uc7ac\ubc30\uba74\uc801\uc740 2003\ub144\ub3c4 14,161 ha\uc5d0 \uc11c 2007\ub144 21,093 ha\ub85c \uafb8\uc900\ud55c \uc99d\uac00 \ucd94\uc138\uc5d0 \uc788\uc73c\ub098(MFAFF, 2009), \uc9c0\uae08\uae4c\uc9c0 \uae30\uc874\uc758 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc5d0 \ub300\ud55c \uc5f0\uad6c\ub294 1 \uc870\uc6a9\uc73c\ub85c \uc791\uc5c5\ub2a5\ub960\uc774 \ub5a8\uc5b4\uc9c0\uace0 \uc0ac\ub78c\uc774 \uc9c1\uc811 \ub530\ub77c\ub2e4\ub140\uc57c \ud558\ub294 \ub2e8\uc810\uc774 \uc788\uc73c\uba70 \ud604\uc7ac \ub18d\uac00\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8\uc218\ud655\uae30\uac00 \ubcf4\uae09 \ub418\uc5b4 \uc0ac\uc6a9\ub418\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8 \uc218 \ud655\uae30\uc5d0 \uc801\ud569\ud558\uace0 \uae30\uc874 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ubcf4\ub2e4 \ud6a8\uc728\uc801\uc778 2\uc870 \uc6a9 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ub97c \uac1c\ubc1c\ud558\uace0\uc790 \ud558\uc600\ub2e4.\n2. \uc7ac\ub8cc \ubc0f \ubc29\ubc95\n\uac00. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc124\uacc4\uff65\uc81c\uc791\n1) \uc8fc\uc694 \uad6c\uc870 \ubc0f \uc81c\uc6d0\n\uadf8\ub9bc 1\uc5d0\uc11c\uc640 \uac19\uc774 \ud2b8\ub799\ud130 PTO\ub97c \uc774\uc6a9\ud558\uc5ec \ub3d9\ub825\uc774 \uc804\ub2ec\ub418 \ub294 \ud2b8\ub799\ud130 \ubd80\ucc29\ud615\uc73c\ub85c 2\uc870\uc758 \ub450\ub451 \ub369\uad74 \ud30c\uc1c4\uac00 \uac00\ub2a5\ud558\ub3c4\ub85d \uc81c\uc791\ud558\uc600\ub2e4. \uc8fc\uc694\uad6c\uc870\ub294 \ub369\uad74 \ud30c\uc1c4\ub0a0\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\ub85c \uad6c\uc131\ub418\uc5b4 \uc788\ub294 \ub369\uad74 \ud30c\uc1c4\ubd80, \ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc744 \ub369\uad74 \ud30c\uc1c4\ubd80 \uad6c\ub3d9\ucd95\uc73c\ub85c \uc804\ub2ec\ud574\uc8fc\ub294 \uae30\uc5b4\ubc15\uc2a4, \uc2a4\ud504\ub85c\ucf13, \uccb4 \uc778, \uae30\uc5b4 \ub4f1\uc73c\ub85c \uad6c\uc131\ub41c \ub3d9\ub825 \uc804\ub2ec\ubd80, \ub369\uad74 \ud30c\uc1c4\uc791\uc5c5 \uc2dc \ub450\ub451\n\uc758 \ub192\uc774\uc5d0 \ub530\ub77c \ubbf8\ub95c\uc758 \ub192\ub0ae\uc774\ub97c \uc870\uc808\ud568\uc73c\ub85c\uc11c \ub369\uad74 \ud30c\uc1c4\ubd80 \uc758 \ub192\uc774\ub97c \uc870\uc808\ud560 \uc218 \uc788\ub294 \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80, \ud2b8\ub799\ud130 \ubd80\ucc29\uc7a5\uce58 \ubc0f \ud504\ub808\uc784 \ub4f1\uc73c\ub85c \uc8fc\uc694\ubd80\ub97c \uad6c\uc131 \uc124\uacc4\uff65\uc81c\uc791\ud558\uc600\ub2e4.\n2) \ub369\uad74 \ud30c\uc1c4\ubd80\n\ub369\uad74 \ud30c\uc1c4\ubd80\ub294 \uadf8\ub9bc 2\uc5d0\uc11c\ucc98\ub7fc \ud68c\uc804\ub0a0 \ud30c\uc1c4\uc2dd\uc73c\ub85c \ub369\uad74 \ud30c \uc1c4\ub0a0, \ud30c\uc1c4\ub0a0 \ubd80\ucc29 \ube0c\ub77c\ucf13, \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5 \ucd95, \ub369\uad74 \uac77\uc5b4\uc62c \ub9bc\ub0a0, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ubd80\ucc29 \uc6d0\ud310, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95, \uc9c0\uc9c0 \ubca0\uc5b4\ub9c1 \ub4f1 \uc73c\ub85c \uad6c\uc131 \uc81c\uc791\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0\uc740 \uadf8\ub9bc 3\uc5d0\uc11c\ucc98\ub7fc \uc81c\ucd08\n\uc6a9\uc73c\ub85c \ub9ce\uc774 \uc4f0\uc774\ub294 \uae38\uc774 120 mm, \ub450\uaed8 5 mm\uc758 \ud504\ub808\uc77c\ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \ud53c\uce58 70 mm \ub098\uc120\uc73c\ub85c \uc88c\uff65\uc6b0 \uac01\uac01 48\uac1c, \ucd1d 96\uac1c\ub97c \ubc30\uce58\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub0b4\uacbd 75 mm \uc911\uacf5\ucd95\uc778 \ud30c\uc1c4\ub0a0 \ucd95 \uc744 \ubca0\uc5b4\ub9c1\uc73c\ub85c \ub07c\uc6cc \ub9de\ucda4\ud558\uc5ec \uc88c, \uc6b0 \ud30c\uc1c4\ub0a0\ub4e4\uc744 \uac01\uac01 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ubd84\ub9ac \uad6c\ub3d9\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc740 \uadf8\ub9bc 4\uc5d0\uc11c\ucc98\ub7fc \ub05d\uc774 \ubfb0\uc871\ud55c \uae38\uc774 250 mm 6\uac1c \uc9c1\uc120\ub0a0\uc744 \uc6d0\uc8fc \ud53c\uce58\uac01 60\u00b0 \uac04\uaca9\uc73c\ub85c \ub192\uc774 \uc870\uc808\uc774 \uac00 \ub2a5\ud55c \ube0c\ub77c\ucf13\uc5d0 \ubd80\ucc29\ud558\uace0 \ube0c\ub77c\ucf13\uc744 \uc6d0\ud310\uc5d0 \uace0\uc815\ud558\uc600\ub2e4. \uc88c\uff65 \uc6b0\uff65\uc911\uc559 3\uacf3 6\uac1c\uc529 \ubaa8\ub450 18\uac1c\uc758 \ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \uccb4\uc778 \uc804 \ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5\ucd95 \uc548\uc758 \uc9c1\uacbd 35 mm \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\uc5ec \uac77\uc5b4\uc62c\ub9bc \uc791\uc6a9\uc744 \ud558\ub3c4\ub85d \ud558 \uc600\ub2e4.\n3) \ub3d9\ub825 \uc804\ub2ec\ubd80\n\ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc774 \uae30\uc5b4\ubc15\uc2a4\uc5d0\uc11c 2.5\ubc30\ub85c \uc99d \uc18d\ub418\uc5b4 \uad6c\ub3d9\ucd95 \uc88c\uff65\uc6b0\ub85c \ub098\ub258\uc5b4\uc838 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77 \uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\ub294 \uacfc\uc815\uc744 \uadf8\ub9bc 5\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \uad6c\ub3d9\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc6b0\uce21\uc758 \uad6c\ub3d9\ucd95\uc73c\ub85c", + "J. of Biosystems Eng. Vol. 36, No. 1.\n\ubd80\ud130 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95 \uc548\uc5d0 \uc788\ub294 \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uc9c1\uc811 \uad6c\ub3d9\uc2dc\ud0a8\ub2e4. \uadf8\ub9bc 6\uc740 \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\ucd95\uc758 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \uc2dc\uc758 \ub3d9\ub825 \uc804\ub2ec \ubc29\ubc95\uc744 \ub098\ud0c0\ub0b8 \uac83\uc774\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \uc804\uc9c4\ubc29 \ud5a5 \ud68c\uc804(\uc815\ud68c\uc804)\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c \ucf13\uacfc \uae30\uc5b4\uac00 \uc870\ud569\ub41c 2\uac1c\uc758 \ubc29\ud5a5\uc804\ud658 \ucd95\uacfc \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\n\ucd95\uc744 \uac70\uccd0 \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc \ud0a4\uace0, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \ud6c4\uc9c4\ubc29\ud5a5 \ud68c\uc804(\uc5ed\ud68c\uc804)\uc740 \uae30\n\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c\ucf13\uacfc \ud150\uc158 \uc2a4\ud504\ub85c\ucf13\uc744\n\uac70\uccd0 \uc911\uacf5\uc758 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc\ud0a4\ub3c4\ub85d \ud558 \uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \ud68c\uc804\uc18d\ub3c4\ube44\ub294 9 : 1\ub85c \uace0\ub791\uc5d0 \uc788\ub294 \ub3cc\uc5d0 \uc758\ud55c \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \uc190\uc0c1 \ubc0f \ub369\n\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc5d0 \uc758\ud55c \ube44\ub2d0\ud53c\ubcf5 \uc190\uc0c1 \ub4f1\uc758 \ubb38\uc81c\uc810\uc774 \ubc1c\uc0dd\ub420 \uc218\ub3c4 \uc788\uae30 \ub54c\ubb38\uc5d0 \ud68c\uc804\uc18d\ub3c4\uc758 \ucc28\uc774\uac00 \uc788\ub3c4\ub85d \ud558\uc600\ub2e4.\n4) \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80\n\ub369\uad74\ucc98\ub9ac \uc791\uc5c5 \uc2dc \ub369\uad74 \ud30c\uc1c4\ubd80\uc758 \ud30c\uc1c4\ub192\uc774\ub97c \uc81c\uc5b4\ud558\uba70, \uace0 \ub791\uc744 \uc774\ud0c8\ud558\uc9c0 \uc54a\uace0 \uc791\uc5c5\uae30\uc758 \uc8fc\ud589 \uc548\uc815\uc131\uc744 \ub192\uc774\uae30 \uc704\ud558\uc5ec \uc124\uce58\ud55c \ubbf8\ub95c\uc758 \uad6c\uc870\ub97c \uadf8\ub9bc 7\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ubbf8\ub95c\uc740 \uc9c1\uacbd 400 mm, \ud3ed 100 mm\ub85c \ub450\ub451\uc758 \ud615\uc0c1\uc5d0 \ub530\ub77c \ub369\uad74\ud30c\uc1c4\ubd80\uc758\n\ub192\ub0ae\uc774\ub97c \uc704\ucabd\uc758 \ub808\ubc84\ub97c \ud68c\uc804\uc2dc\ucf1c \uc870\uc808\ud560 \uc218 \uc788\ub3c4\ub85d \ud558\uc600\uc73c \uba70, \ub192\uc774 \uc870\uc808\uc740 300 mm\uae4c\uc9c0 \uac00\ub2a5\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ubbf8\ub95c\uc758 \uc124 \uce58 \uc704\uce58\ub294 \uc791\uc5c5\uae30 \ud6c4\ubc29 \uc791\uc5c5\uae30\ub97c \uc911\uc2ec\uc73c\ub85c \uc88c\uc6b0 2\uac1c, \ubbf8\ub95c \uc911 \uc2ec\uac04 \uac70\ub9ac\uac00 1400 mm\uac00 \ub418\ub3c4\ub85d \ubd80\ucc29\ud558\uc600\ub2e4.\n\ub098. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc131\ub2a5\uc2e4\ud5d8\n1) \uc2e4\ud5d8\ud3ec\uc7a5 \ubc0f \uc7ac\ub8cc\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc758 \uc2e4\ud5d8 \uc911 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc5d0 \ub530\ub978 \ud30c\n\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c\ub9c8\ub294 \uc728\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758 \ud3c9 \uade0 \ud568\uc218\uc728\uc740 83.0%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \uc2e4\ud5d8\ud3ec\uc7a5\uc758 \ud1a0\uc131\uc740 \uc0ac\uc591 \ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 30 cm, \ub450\ub451\ub192 \uc774 25 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4. \uc8fc\ud589\uc18d\ub3c4 \ubc0f \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c \ub9c8\ub294 \uc2e0\ud669\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758\ud3c9\uade0 \ud568\uc218\uc728\uc740 79.1%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \ud1a0\uc131\uc740 \uc0ac\uc9c8\ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 40 cm, \ub450\ub451\ub192\uc774 30 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4.\n2) \uc2e4\ud5d8\ub0b4\uc6a9 \ubc0f \ubc29\ubc95\n\uac00) \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8\n\ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ud30c\uc1c4\uc131\ub2a5\uc758 \ucc28\uc774\ub97c \uc870\uc0ac\ud558\uae30 \uc704\n\ud558\uc5ec \uc2e4\uc2dc\ud55c \uc2e4\ud5d8\uc73c\ub85c \ud2b8\ub799\ud130 \uc5d4\uc9c4 \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uc5d0 \ub530\ub77c \uc8fc \ud589\uc18d\ub3c4, PTO \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uac00 \uc5c6\ub3c4\ub85d \ud2b8\ub799\ud130 \uc5d4\uc9c4\uc18d\ub3c4\ub97c 2000 rpm\uc73c\ub85c \uace0\uc815\ud558\uace0, \uc8fc\ud589 \ubcc0\uc18d\ub2e8\uc218\ub97c Park and Choi (1995)\uac00 \ubcf4\uace0\ud55c \uc8fc\ud589\uc18d\ub3c4 0.35, 0.46 m/s\uc5d0\uc11c \uc8fc\ud589\uc18d\ub3c4\uac00 \ub0ae \uc744\uc218\ub85d \ub369\uad74 \ud30c\uc1c4\uc728\uc774 \ub192\uc558\uc73c\uba70, \ub18d\uac00\uc5d0\uc11c \uc8fc\ub85c \uc800\uc18d 1, 2\ub2e8 \uc744 \uc0ac\uc6a9\ud558\ub294 \uac83\uc744 \uace0\ub824\ud558\uc5ec \ubcf8 \uc2e4\ud5d8\ub3c4 \uc800\uc18d 1, 2\ub2e8\uc5d0 \ub9de\ucd94\uc5b4 \uc8fc\ud589\uc18d\ub3c4\ub97c \uac01\uac01 0.27, 0.37 m/s\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \ubcc0\uacbd\uc740 \uadf8\ub9bc 6\uc5d0\uc11c" + ] + }, + { + "image_filename": "designv8_17_0003110_9874358_09831045.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003110_9874358_09831045.pdf-Figure5-1.png", + "caption": "Fig. 5. Vacuum shell of the proposed filter. The corresponding dimensions (in mm) for WR-10\u2014L1=3.800 L2=3.800, L3=5.374, L4=0.900, I1=0.400, I2=0.800, I3=1.660, and P1=0.645\u2014and WR-3\u2014L1=1.287 L2=1.287, L3=1.821, L4=0.308, I1=0.117, I2=0.278, I3=0.564, and P1=0.234. Values are rounded to three decimal places. An estimated underetching between 4.25 and 6.10 \u00b5m should be applied to the WR-3 version.", + "texts": [ + " 4 shows the magnetic field distribution of a singlet with the two resonant irises and describes the basic interaction throughout the filter. The modified topology now includes the resonant irises and is indicated in the image for reference; it can be noted that the bypass coupling is now formed between the resonant slot irises (nodes 1 and 3) in a quasi-triplet fashion. The evanescent modes of the resonant slot irises can be treated as TE101 modes while the triangular cavity (node 2) utilizes the TM120 mode. Fig. 5 shows the vacuum shell of an inline quasi-triplet structure and outlines the dimensions for each of the upcoming prototypes when fed with their respective waveguide ports. Fig. 6 is provided as a demonstration of the transmission zero control when varying the port positions to be inline or offset while the triangular cavity and the resonant irises are optimized for an equivalent passband response. After the initial design of the cavity from equation (1) for an isosceles cavity, the synthesis of the passband filter can be suitably approximated from the general equations outlined in [24] for external quality factors and synchronous coupling despite the resonant irises and cavity being asynchronous" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001092_2_1_12_22004507__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001092_2_1_12_22004507__pdf-Figure8-1.png", + "caption": "Fig. 8. Schematic of the hybrid-excitation-type DC motor", + "texts": [ + " Owing to the structural design of the hybrid-excitation-type DC machine, there is mutual interference between the magnetic field generated by the excitation winding and that of the permanent magnet in the stator, where the aluminum ring is isolated, and the interference between the two magnetic fields is bound to counter-rotate. However, since the purpose of the starter is to help the engine complete its startup work, the requirements for torque ripple in its application are relatively low; hence, there is no need to suppress this ripple. The scheme of the hybrid-excitationtype DC motor is shown in Fig. 8 (23) (24). The components of the hybrid-excitation-type DC motor and their descriptions are shown in Table 4. A study (23) explored the application of hybrid excitation to a stepper motor. The prototype was a variable-reluctance stepper motor with two phases and eight poles. Hybrid excitation was employed to solve the problem of insufficient torque. Further, structural optimization was investigated in the study, particularly in the diagonal part of the stator with an inserted permanent magnet. However, it neither discussed the optimized shape and size of the magnet nor did it use any algorithm to perform optimization" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003533_ing_To_20library.pdf-Figure4.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003533_ing_To_20library.pdf-Figure4.3-1.png", + "caption": "Figure 4.3 Fabrication process of discrete structure based stretchable memristors.", + "texts": [ + "7 Comparison of methods for measuring the thickness of thin film on elastomer. Figure 3.8 Cross-section of Au thin film on PDMS under (a-b) SEM and (c-d) FIB-SEM. Figure 3.9 Measuring the thickness of Au thin film on (a) wafer, and (b) PDMS Figure 3.10 Illustration of difference between (a) Eulerian and (b) Lagrangian. Figure 4.1 Continuous structure (CS) v.s Discrete structure (DS) during mechanical deformation. Figure 4.2 The configuration of a flexible discrete-structure memristor (DS-memristor) with crossbar. Figure 4.3 Fabrication process of discrete structure based stretchable memristors. Figure 4.4 The optical microscope images of discrete units with different sizes. Figure 4.5 A typical I-V characterization of DS-memristor under a voltage sweeping mode at room temperature. Figure 4.6 Electrical and mechanical properties of top and bottom electrodes (Au/SEBS) with crossbar configuration. Figure 4.7 The behavior of Au strip on SEBS under cycling stretching and crack morphology in Au electrode. Figure 4.8 Comparison of CS and DS based on flexibility" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000642_download_16767_17232-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000642_download_16767_17232-Figure3-1.png", + "caption": "Figure 3 Three-phase induction motor", + "texts": [ + " This converter is known as a three-phase DC/AC converter, or simply three-phase inverter. The converter used is a VSI, as shown in fi gure 2; it consists of six switching elements (IGBTs) and six freewheeling diodes. Ud represents the DC voltage of the battery bank. The three-phase AC voltage is obtained from the terminals a, b and c. For the DC/AC converter, the model presented in [19] is used. The output voltage space vector of the inverter Us depends on the value of Ud and modulation signals Sa, Sb and Sc, as expressed in the equation (1). (1) Three-phase induction motor Figure 3 shows a diagram of three-phase squirrel cage IM, which is used for obtain its model [20], it shows the three phases of the stator as, bs y cs, and the equivalent three phases of the rotor ar, br y cr. \u03b8r is the angular position of the rotor and \u03c9r is the angular velocity of the rotor. The equation (2) is the model of the electrical subsystem of squirrel cage IM in the stationary reference frame. (2) where, Us is the stator voltage space vector, is and ir are the space vector of stator and rotor currents, Rr and Rs are the resistances of stator and rotor, \u03c8s and \u03c8r are the space vector of stator and rotor fl ux-linkage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003532_article_25904217.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003532_article_25904217.pdf-Figure1-1.png", + "caption": "Figure 1. Finite System diagram", + "texts": [], + "surrounding_texts": [ + "The dust sensor converts the air to be measured into an analog voltage signal and sends it to ADC0832. ADC0832 converts the analog signal obtained into a digital signal and sends it to singlechip microcomputer. The single-chip microcomputer chip sends the input digital signal to LCD and the bee alarm through processing." + ] + }, + { + "image_filename": "designv8_17_0004506_cle_download_289_330-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004506_cle_download_289_330-Figure12-1.png", + "caption": "Figure 12. Pneu \u2013 WRE (Wilmington Robotic Exoskeleton) [11].", + "texts": [ + " The robots guide the hand along a given trajectory, imitating the work of a rehabilitator. This relieves the rehabilitator, who becomes needed only in more complex exercises and checking the work of robots [9]. The presented system shows the patient the correctness of the movements performed and monitors the patient\u2019s progress. The attractiveness of performed exercises is increased through the use of constantly refined and improved virtual reality [9]. WRE (Wilmington Robotic Exoskeleton) is shown in Fig. 12. The Pneu-Wrex exoskeleton has five degrees of freedom. Its main purpose is to help with everyday activities (e.g. eating). It is also adapted to rehabilitation at home, and the interaction with the virtual environment (tasks to be performed by the patient are displayed on the computer monitor) makes rehabilitation easier and more interesting. It is suitable both for exercises with children and the elderly after stroke. Pneumatic actuators are used for the drive. It enables a wide range of movements of the upper limb and the measurement of hand strength" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003081_le_download_1199_891-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003081_le_download_1199_891-Figure7-1.png", + "caption": "Fig. 7. Result of Boundary Condition Model", + "texts": [ + ", 2021). Figure 6 shows the results of the meshing model with mesh quality indicators. Boundary conditions for fixed support applied were on the top area of the model except for the ventilation holes starting from the back of the palm to the back of the arm. On the opposite side, especially in the area around the wrist to the tip of the palm, a force was applied with loading ranging from 0 to 30 N. This interval force is assumed to occur when the model is applied to the patient's hand for fixation. Figure 7 shows the boundary conditions of the wrist-hand orthosis model. The analysis of the wrist-hand orthosis model for the equivalent (von Mises) stress showed that the maximum stress occurred in the area of the back end of the model's hand. This area is the link between the thumb and index finger, where the two fingers have a greater force than the other. Figure 8 shows the results of equivalent stress by indicating the maximum stress area and a graph of the relationship between load and stress from variations in the model's thickness" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004509_i_10.3233_ATDE230467-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004509_i_10.3233_ATDE230467-Figure5-1.png", + "caption": "Figure 5. The stress, displacement, and strain cloud maps of optimized POM FS.", + "texts": [ + " Based on the above analysis, the order of the influence of cylinder length, wall thickness, and chamfer radius on the stress of POM FS is as follows: cylinder length > wall thickness > chamfer radius. Taking the parameters of cylinder length, wall thickness, and chamfer radius as optimization targets, the minimum stress values for each parameter were determined to be L = 60mm, d = 0.3125mm, and r = 1.4mm. A POM FS model was established based on these parameters, and the FEM simulation was performed following the procedure in section 2. The stress, displacement, and strain cloud maps of the optimized POM FS are exhibited in figure 5. By comparing figure 2 and figure 5, it can be observed that the maximum stress of POM FS decreases from 26.19MPa to 23.81MPa, the maximum displacement decreases from 0.2052mm to 0.1746mm, and the maximum strain decreases from 0.0095 to 0.0083. The stress, displacement, and strain decrease by 9.09%, 14.91%, and 12.63%, respectively. These results indicate that the structural parameter optimization method proposed in this paper achieves significant improvements in the mechanical performance and stability of the POM FS. The S-N curve represents the relationship between the stress amplitude that a material can withstand and the number of cycles it experiences before experiencing fatigue failure at that stress level" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000652_0005208_10013678.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000652_0005208_10013678.pdf-Figure1-1.png", + "caption": "FIGURE 1. Proposed antenna system: (a) 14 beams alternating RCHP and LHCP are generated in xy-plane or azimuthal plane, (b) The upper QOBF generates 7 RCHP beams while the lower 7 LHCP beams, (c) Cross sectional detail of the shaped ridge and cavity profile.", + "texts": [ + " To the best of our knowledge this is the first design of a circularly polarized quasi-optical multi-beam antenna in a fully integrated system, validated by a measured prototype. This paper is organized as follows. The antenna architecture and the design guidelines for each part of the antenna are presented in Sec. II. Manufacturing and measured results are discussed in Sec. III. Conclusions are drawn in Sec. IV. II. PROPOSED ANTENNA SYSTEM The proposed antenna system is designed to provide 14 circularly polarized beams covering a \u00b119\u25e6 scanning range with a step of about 3\u25e6 and alternating RHCP and LHCP between adjacent beams for higher isolation, as depicted in Fig. 1. VOLUME 11, 2023 4603 An array of septum polarizers is therefore used together with two identical QOBFs mirrored with respect to the beamforming plane. The septum array polarizer is connected to the QOBFs through a transition able to convert the q-TEM mode, supported by the PPW, into the fundamental TE10 supported by the input rectangular waveguides of the septum polarizers. Each QOBF can generate seven linearly polarized beams, according to the selected feeding horn. The feeding horns, positioned along the focal curve of the PPW lens, are angularly spaced of about = 6\u25e6 and shifted of \u03c8 = 3\u25e6 with respect to the other QOBF\u2019s feeds as depicted in Fig. 1b. This particular arrangement, similar to the one also described in [18], allows to have alternate RHCP/LHCP between two adjacent beams, inasmuch they are generated by different PPWs, and it allows also an adequate beam cross-over level (sightly over 3 dB below the peak directivity) while preserving enough space between two consecutive horns. The horns were designed to provide an adequate edge tapering (about \u221210 dB considering broadside beam) over the lens contour (Sec. II-A). The edge tapering is fundamental to minimize the effect of the side walls, which may increase the phase aberration and SLL. A. PPW CONTINUOUS LENS-LIKE BEAMFORMER TheQOBFs have a design similar to the one described in [18], and optimized to achieve a maximum scanning angle on the azimuthal plane of \u03c6s = \u00b131.5\u25e6. In particular a polynomial shaped delay lens profile (inner lens contour 61 and ridge height profile hw as shown in Fig. 1c) is defined as follow: 61 (x) = n\u2211 k=1 pkyk (1) hw (z) = n\u2211 k=1 qkyy \u2212 min ( n\u2211 k=1 qkyk ) (2) where x, y, z are normalized to the focal distance f , pk and qk are the k th order coefficients with 1 \u2264 k \u2264 n, n the maximum degree of the polynomial function. Using the Geometrical Optics (GO) continuous lens model pattern optimization detailed in [18] two identical QOBFs have been designed. The optimized polynomial profile coefficients are shown in table 1, while the maximum height of the ridge hw(zmax) = 21 mm. The thickness of the ridge is |62 \u221261| = 2 mm, where 62 is the outer contour of the ridge and it is obtained by a translation of the inner contour 61 along the x-axis (Fig. 1c). The choice of the thickness is the minimum achievable by milling machining without potentially bending the blade. The PPW\u2019s height is hppw = 2 mm, which guarantee the propagation of the fundamental q-TEM of the PPW structure over the whole operative band. The lens diameter is D = 20\u03bb0 at the operative frequency f0 = 30 GHz, and the focal distance is F = 0.7D. Each QOBF is fed by one of the 7 horns disposed along a circular focal curve centered in O and traced between the two focal points F1 and F2 as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002803_cle_download_681_563-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002803_cle_download_681_563-Figure6-1.png", + "caption": "Figure 6 \u2013 Hydrostatic seal with constant leaks", + "texts": [ + " Comprehensive experimental studies and field tests have shown that such seals meet stringent requirements for reliability, tightness and service life of the main NPP equipment [2]. Due to this, impulse seals have attracted the attention of developers of high-speed centrifugal machines for other industries [9]. The simplest design of a single-stage impulse seal (Figure 7) differs from a mechanical seal by the fact that closed chambers 2 are located on the end surface of axially movable ring 1 and several radial Flowserve Corp (USA) developed a hydrostatic seal (Figure 6) with constant leaks. The seal consists of disk 1 located on shaft 12 and axially movable bushing 11, which is mounted in body spacer 4. Smooth sealing belt 10 and support support shoe 9 are installed on the end disk surface. Piston 5 is fixed on bushing 11 from the side of low-pressure chamber 7. Throttle 6 is located on the line of controlled leak drain. The chamber formed between piston 5 and housing spacer plate 4 is connected to the atmosphere by channel 3. External leaks on the shaft are limited by the auxiliary stage of mechanical seal 8" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001549_tation-pdf-url_35276-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001549_tation-pdf-url_35276-Figure16-1.png", + "caption": "Fig. 16. Generated gear and generating positions of the pinion-cutter with a rounded-tip", + "texts": [], + "surrounding_texts": [ + "Computer graphs of generating and generated surfaces can be obtained by using a programming language and graphic processor. In this study codes are developed by using GW-BASIC language to obtain the coordinates of the surfaces. GRAPHER 2-D Graphing System is used for displaying computer graphs of the cutters and gears. Also the ANSYS Preprocessor module is used for displaying gear generating process. Illustrative examples are given for both rack- and pinion-type cutters for different types of tool tip geometries. For rack-type generation, types of tip fillet geometry are selected from the study proposed by Alipiev (Alipiev, 2009, 2011) and the related geometries displayed in the table are adopted to the present mathematical model. Table 1 displays the variation of tip geometry of the rack cutters. www.intechopen.com As illustrated in Table 1, the rack cutter of type-1a has different clearances at its different sides. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. The tooth semi-thicknesses at pitch line of the cutter are different from each other. Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 2.01 and right side radius of rounding m 3.02 . Figure 8 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. As illustrated in Fig. 2. and classifed type-1b in Table 1, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The tooth semi-thicknesses at pitch line of the cutter are same. This type of cutter is adopted from the standard generating rack to asymmetric gearing. The relation ship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 38.01 and right side radius of rounding m 33.02 . Generating and generated surfaces and trochoidal paths are illustrated in Fig 9. Rack cutters with asymmetric teeth can also be designed with full rounded tips. The rack cutter of type-2a has a single rounded edge. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. As depicted in Table 1 the centers of the rounded tip are at the center line of the cutter tooth. The tooth semi-thicknesses at pitch line of the cutter are same. Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 5.221 , right side pressure angle 152 , left side radius of rounding m 4.01 and right side radius of rounding m 587.02 . Figure 10 displays the generating cutter of type-1a, generated surface and trochoidal paths of the tip. For visual clearity, only the corresponding halves (of secondary trochoids) that contribute to final formation of the generated tooth shape are shown. www.intechopen.com Mechanical Engineering 518 www.intechopen.com www.intechopen.com Mechanical Engineering 520 As classifed type-2b in Table 1, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The tooth semi-thicknesses at pitch line of the cutter are different. The relation ship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 5.221 , right side pressure angle 152 , left side radius of rounding m 514.01 and right side radius of rounding As illustrated in Table 2, the shaper cutter of type-1a has different clearances at its different sides. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 35.02 . Figure 12 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. www.intechopen.com As illustrated in Fig. 3. and classifed type-1b in Table 2, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The relationship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 222.02 . Generating and generated surfaces and trochoidal paths are illustrated in Fig 13. The shaper cutter of type-2a has a single rounded edge. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. As depicted in Table 2 the centers of the rounded tip are at the center line of the cutter tooth. Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 373.01 and right side radius of rounding m 449.02 . Figure 14 displays the generating cutter of type-2a , generated surface and trochoidal paths of the tip. For visual clearity, only the corresponding halves (of secondary trochoids) that contribute to final formation of the generated tooth shape are shown. The shaper cutter with asymmetric involute teeth and with a single rounded edge can not be designed for constant clearance in case of standard tooth height. As illustrated in Fig. 3., the center of the rounding should be on the pressure line of the cutter. As a result, the geometric varieties of pinion-type tool tip is limited for indirect generation. www.intechopen.com Mechanical Engineering 522 www.intechopen.com Figure 17 displays relative positions of the pinion cutter with symmetric involute teeth and a fully-rounded tip. The trochoidal curves exhibits symmetry according to center line of gear tooth space. Generating with a sharp-edge pinion cutter is depicted in Fig.18. In this case, primary trochoids determine the shape of the generated tooth fillet. The secondary trochoids do not exist. Video files displaying generating positions of the cutter can be obtained with a proper software. In this study, ANSYS Parametric Design Language (APDL) is also used for obtaining graphic outputs and animation files displaying the simulated motion path of the generating cutters (ANSYS, 2009). Video files can be seen in the author\u2019s web page: http://www.istanbul.edu.tr/eng2/makina/cfetvaci/gearpage.htm www.intechopen.com Mechanical Engineering 524 www.intechopen.com Computer Simulation of Involute Tooth Generation 525" + ] + }, + { + "image_filename": "designv8_17_0003471_f_version_1633933254-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003471_f_version_1633933254-Figure2-1.png", + "caption": "Figure 2. Parameters and design structure of the RFID tag anten a without bumper.", + "texts": [ + " The simulated results of the proposed antenna are expected to give acceptable performances at a center frequency of a 920 MHz band for UHF RFID application. Figures 2 and 3 show the structure of the proposed automobile plate for a plastic vehicle bumper and tag antenna. It is composed of a metal plate similar to a license plate and plate holder, bolts and nuts, and a part of the vehicle bumper. The bumper is made out of plastic with a dielectric constant of \u03b5r = 3.2. In this design, the tag antenna is designed to attach to a metal part of the license plate holder. Figure 2 shows the proposed tag antenna attached next to the standard plate holder, which is shown in Figure 1. The loop-shape tag antenna facing the bumper is placed on the side of the license plate to have a frontal pattern. The tag antenna has a rectangular shape with a dimension of 130 mm\u00d7 50 mm and is attached next to the license plate holder as shown in Figure 2. The tag facing the bumper side in Figure 2 is enlarged and drawn in Figure 3 with the detailed parameters of the antenna. This tag antenna uses the back-lobe pattern to be recognized by readers since it faces the bumper side. i According to the Korean license plate sta dard, there are two commonly use plates. One is the size of 335 mm \u00d7 115 mm and the other is 520 mm \u00d7 110 mm as shown in Figure 1. The standard plate size of 520 mm \u00d7 110 mm is used in our design. The proposed antenna was simulated using CST simulation software; here, a discrete port was used to represent the RFID tag terminal", + " The simulated results of the proposed antenna are expected to give acceptable performances at a center frequency of a 920 MHz band for UHF RFID application. Figures 2 and 3 show the structure of the proposed automobile plate for a plastic vehicle bumper and tag antenna. It is composed of a metal plate similar to a license plate and plate holder, bolts and nuts, and a part of the vehicle bumper. The bumper is made out of plastic with a dielectric constant of \u03b5r = 3.2. In this design, the tag antenna is designed to attach to a metal part of the license plate holder. Figure 2 shows the proposed tag antenna attached next to the standard plate holder, which is shown in Figure 1. The loop-shape tag antenna facing the bumper is placed on the side of the license plate to have a frontal pattern. The tag antenna has a rectangular shape with a dimension of 130 mm\u00d7 50 mm and is attached next to the license plate holder as shown in Figure 2. The tag facing the bumper side in Figure 2 is enlarged and drawn in Figure 3 with the detailed parameters of the antenna. This tag antenna uses the back-lobe pattern to be recognized by readers since it faces the bumper side. Electronics 2021, 10, 2439 5 of 10 Electronics 2021, 10, 2439 5 of 10 Figure 3. Front and back side of license plate RFID tag antenna with bumper. The proposed tag antenna is designed to operate at 920 MHz. The geometric parameters defined in Figure 2 were designed and optimized by parameter sweeping. The results of the optimized values are shown in Table 1. Table 1. Optimized parameter values. Para. Dimension (mm) Parameter Dimension (mm) Plate_w 525 Mat_w 235 Tmat_h 25 mat_h 15 Ant_h 10 Loop_w 5 Tmat_w 257.5 Mloop_w 10 Plate_h 116 i r . r t rs si str ct r f t I t t it t r. Electronics 2021, 10, 2439 5 of 10 Figure 3. Front and back side of license plate RFID tag anten a with bumper. The proposed tag anten a is designed to operate at 920 MHz. The geometric parameters defined in Figure 2 were designed and optimized by parameter swe ping. The results of the optimized values are shown in Table 1. Table 1. Optimized parameter values. Para. Dimension (mm) Parameter Dimension (mm) Plate_w 525 Mat_w 235 Tmat_h 25 mat_h 15 Ant_h 10 Lo p_w 5 Tmat_w 257.5 Mlo p_w 10 Plate_h 1 6 Figure 3. Front and back side of license plate RFID tag antenna with bumper. The proposed tag antenna is designed to operate at 920 MHz. The geometric parameters defined in Figure 2 were designed and optimized by parameter sweeping. The results of the optimized values are shown in Table 1. Table 1. Optimized parameter values. Para. Dimension (mm) Parameter Dimension (mm) Plate_w 525 Mat_w 235 Tmat_h 25 mat_h 15 Ant_h 10 Loop_w 5 Tmat_w 257.5 Mloop_w 10 Plate_h 116 Electronics 2021, 10, 2439 6 of 10 The signal radiating toward the bumper cannot be identified by the reader, only the signal radiating toward the front side of the car is readable by the reader. So, we need a strong signal radiating toward the front" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002418__32_5_32_32_456__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002418__32_5_32_32_456__pdf-Figure4-1.png", + "caption": "Fig. 4 Front view and top view of the hand (left hand)", + "texts": [], + "surrounding_texts": [ + "\u4ee5\u4e0a\u306e\u91cd\u91cf\u304c\u3042\u308b\u304c\uff0c\u7fa9\u624b\u3092\u5207\u65ad\u7aef\u3067\u652f\u6301\u3059\u308b\u5207\u65ad\u8005\u306b\u3068\u3063\u3066 \u306f\u91cd\u304f\uff0c\u3088\u3046\u3084\u304f\u5165\u624b\u3057\u3066\u3082\u305d\u306e\u91cd\u3055\u306b\u6163\u308c\u305a\u306b\u4f7f\u7528\u3092\u4e2d\u6b62\u3059 \u308b\u30e6\u30fc\u30b6\u3082\u591a\u3044\uff0e \u3053\u306e\u3088\u3046\u306a\u4f5c\u696d\u7528\u7fa9\u624b\u306e\u8ab2\u984c\u306b\u3088\u308a\uff0c\u524d\u8155\u5207\u65ad\u8005\u306e\u591a\u304f\u306f\u4f5c 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1\u306b\u8a66\u4f5c\u3057\u305f\u96fb\u52d5\u7fa9\u624b\uff08\u5de6\u624b\u7528\uff09\u306e\u5916\u89b3\u3092\u793a\u3059\uff0e\u7fa9\u624b\u306e \u69cb\u6210\u8981\u7d20\u306f\uff0c\u5927\u304d\u304f\u5206\u3051\u3066\u30cf\u30f3\u30c9\uff0c\u30cf\u30f3\u30c9\u30db\u30eb\u30c0\uff0c\u30bd\u30b1\u30c3\u30c8\uff0c\u8ddd \u96e2\u30bb\u30f3\u30b5\uff0c\u30b5\u30dd\u30fc\u30bf\u306b\u5206\u3051\u3089\u308c\u308b\uff0e\u30cf\u30f3\u30c9\u306f\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc \u30bf\u3067\u958b\u9589\u3059\u308b\u5bfe\u5411\u914d\u7f6e\u306e 3\u6307\u3092\u5099\u3048\u308b\uff0e\u524d\u8155\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u88c5 \u7740\u3057\uff0c\u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u30bb\u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u5fdc\u3058 \u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\uff0e\u5207\u65ad\u7aef\u3092\u633f\u5165\u3059\u308b\u30bd\u30b1\u30c3\u30c8\u306f\uff0c\u30b5\u30dd\u30fc\u30bf\u306e \u7559\u3081\u5177\u3067\u7de0\u3081\u4ed8\u3051\u308b\u3053\u3068\u3067\u5bb9\u6613\u306b\u88c5\u7740\u53ef\u80fd\u3067\u3042\u308b\uff0e\u4ee5\u4e0b\uff0c\u7fa9\u624b \u306e\u5404\u8981\u7d20\u306b\u3064\u3044\u3066\u8a73\u7d30\u306b\u8ff0\u3079\u308b\uff0e\n2. 1 \u6307\u306e\u958b\u9589\u6a5f\u69cb \u63d0\u6848\u7fa9\u624b\u306f\u5bfe\u5411\u306b\u914d\u7f6e\u3055\u308c\u305f\u540c\u4e00\u5f62\u72b6\u306e 3\u6307\u304c\u540c\u6642\u306b\u958b\u9589\u3059 \u308b\u3053\u3068\u306b\u3088\u308a\u5bfe\u8c61\u3092\u628a\u6301\u3059\u308b\uff0eFig. 2\u306b\u30cf\u30f3\u30c9\u306e\u5185\u90e8\u65ad\u9762\u3092\u793a \u3059\uff0e\u30cf\u30f3\u30c9\u306b\u306f\u52d5\u529b\u6e90\u306e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\uff08L12-R\uff0cFirgelli Technologies Inc\uff09\uff0c\u5236\u5fa1\u7528\u30de\u30a4\u30b3\u30f3\uff08Arduino Pro Mini\uff09\u304c\n\u5185\u8535\u3055\u308c\u3066\u3044\u308b\uff0eTable 1\u306b\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4ed5\u69d8\u3092\u793a \u3059\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306f\uff0c\u4f4d\u7f6e\u5236\u5fa1\u53ef\u80fd\u306a\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u3066\u3044\u308b\uff0e\u30cf\u30f3\u30c9\u5185\u90e8\u306b\u306f\u6307\u306e\u958b\u9589\u306e\u305f\u3081\u306b Fig. 3\u306b\u793a\u3059\u3088\u3046\u306a \u30ea\u30f3\u30af\u6a5f\u69cb\u3092\u63a1\u7528\u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4f38\u7e2e\u3059\u308b \u30b7\u30e3\u30d5\u30c8\u5148\u7aef\u90e8\u306f\u30ea\u30f3\u30af 1\u306b\u76f4\u7d50\u3057\u3066\u3044\u308b\uff0e\u30b7\u30e3\u30d5\u30c8\u304c\u521d\u671f\u4f4d \u7f6e\u304b\u3089\u4f38\u5c55\u3059\u308b\u3068\uff0c\u305d\u308c\u306b\u4f34\u3063\u3066\u30ea\u30f3\u30af 1\u304c\u30cf\u30f3\u30c9\u5185\u90e8\u3092\u79fb\u52d5 \u3057\uff0c\u5916\u88c5\u90e8\u3068\u306e\u63a5\u70b9\u3092\u30ac\u30a4\u30c9\u3068\u3057\u3066\u30ea\u30f3\u30af 2\u304c\u7e70\u308a\u51fa\u3055\u308c\uff0c\u30b7\u30e3 \u30d5\u30c8\u3068\u30ea\u30f3\u30af 2\u304c\u6210\u3059\u89d2\u5ea6\u304c\u5897\u52a0\u3059\u308b\uff0e\u3053\u308c\u306b\u3088\u3063\u3066\uff0c\u6307\u304c\u958b \u304f\uff0e\u30b7\u30e3\u30d5\u30c8\u304c\u77ed\u7e2e\u3059\u308b\u3068\uff0c\u30b7\u30e3\u30d5\u30c8\u3068\u30ea\u30f3\u30af 2\u306e\u6210\u3059\u89d2\u5ea6\u304c \u6e1b\u5c11\u3057\uff0c\u30ea\u30f3\u30af 2\u304c\u30cf\u30f3\u30c9\u5185\u90e8\u306b\u5f15\u304d\u8fbc\u307e\u308c\u6307\u304c\u9589\u3058\u308b\uff0e3\u6307 \u304c\u540c\u69d8\u306b\u4f5c\u52d5\u3059\u308b\u3053\u3068\u3067\uff0c\u6307\u306e\u958b\u9589\u304c\u884c\u308f\u308c\u308b\uff0e\u3053\u306e\u3088\u3046\u306a\u30b7 \u30f3\u30d7\u30eb\u306a\u6307\u306e\u958b\u9589\u6a5f\u69cb\u306f\uff0c\u30cf\u30f3\u30c9\u306e\u8efd\u91cf\u5316\u3068\u5c0f\u578b\u5316\u306b\u5bc4\u4e0e\u3059\u308b\uff0e Fig. 2 \u306e\u6307\u306e\u65ad\u9762\u56f3\u3067\u793a\u3057\u305f\u3088\u3046\u306b\uff0c\u6307\u306e\u95a2\u7bc0\u306b\u306f\u30c8\u30fc\u30b7\u30e7 \u30f3\u30d0\u30cd\uff08\u3070\u306d\u5b9a\u6570 11.5 [N\u00b7mm/deg]\uff09\u3092\u7d44\u307f\u8fbc\u307f\uff0c\u7269\u4f53\u306b\u99b4\u67d3 \u3080\u3088\u3046\u306b\u628a\u6301\u3059\u308b\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u6307\u5148\u306b\u88c5\u7740\u3059\u308b\u30b7\u30ea\u30b3\u30f3 \u88fd\u30ad\u30e3\u30c3\u30d7\uff08\u786c\u5ea6 30\u5ea6\uff0c\u539a\u3055 1.5 [mm]\uff09\u306f\uff0c\u628a\u6301\u3057\u305f\u7269\u4f53\u304c\u6ed1 \u308b\u306e\u3092\u9632\u304e\uff0c\u9069\u5ea6\u306b\u67d4\u3089\u304b\u3044\u6307\u5148\u3092\u5b9f\u73fe\u3057\u3066\u3044\u308b\uff0e\u307e\u305f\uff0c\u6307\u5148 \u5168\u4f53\u304c\u30b7\u30ea\u30b3\u30f3\u3067\u8986\u308f\u308c\u308b\u305f\u3081\uff0c\u66f8\u7c4d\u306e\u30da\u30fc\u30b8\u3092\u6372\u308b\u5834\u5408\u3084\u673a \u4e0a\u306e\u7269\u4f53\u3092\u305f\u3050\u308a\u5bc4\u305b\u308b\u5834\u5408\u306b\u3082\u6709\u52b9\u3067\u3042\u308b\uff0e3\u6307\u306f\u540c\u4e00\u5f62\u72b6 \u306e\u305f\u3081\uff0c\u6545\u969c\u6642\u306e\u4ea4\u63db\u3082\u5bb9\u6613\u3067\u3042\u308b\uff0e\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201455\u2014 2014 \u5e74 6 \u6708", + "2. 2 \u5bfe\u5411\u914d\u7f6e\u306e 3\u6307 Fig. 4\u306b 3\u6307\u3092\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u914d\u7f6e\u3092\u793a\u3059\uff0e\u6b63\u9762\u304b\u3089\u898b \u3066\u6307\u5148\u4f4d\u7f6e\u304c\u5185\u5074\u3092\u9802\u89d2\u3068\u3059\u308b\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u3068\u306a\u308b\u3088\u3046\u306b\u914d\u7f6e \u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5\u30c8\u306e\u7e70\u308a\u51fa\u3057\u91cf\u304c\u540c\u3058 \u5834\u5408\uff0c\u6b63\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u3088\u308a\u3082\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u306e\u307b\u3046\u304c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\uff08\u4e21\u7aef\u77e2\u5370\u90e8\u5206\uff09\u3092\u3088\u308a\u5927\u304d\u304f\u78ba\u4fdd\u3067\u304d\u308b\uff0e500 [ml] \u306e\u30da\u30c3\u30c8\u30dc\u30c8\u30eb\u3092\u628a\u6301\u3067\u304d\u308b\u5341\u5206\u306a\u7a7a\u9593\u3092\u78ba\u4fdd\u3059\u308b\u305f\u3081\uff0c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\u306f 80 [mm]\u3068\u3057\u305f\uff0e Fig. 5\u306e\u5de6\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\uff0cOttobock\u793e\u306a\u3069\u306e 3\u6307\u306e\u7b4b\u96fb \u7fa9\u624b\u306f\uff0c\u30ea\u30f3\u30af\u306e\u904b\u52d5\u65b9\u5411\u304c\u56de\u8ee2\u8ef8\u306b\u5bfe\u3057\u3066\u76f4\u4ea4\u3057\u3066\u3044\u308b\u305f\u3081\uff0c \u5e73\u677f\u72b6\u306e\u5bfe\u8c61\u3092\u628a\u6301\u3059\u308b\u5834\u5408\uff0c\u56de\u5185\u5916\u3092\u884c\u308f\u305a\u306b\u628a\u6301\u53ef\u80fd\u306a\u65b9 \u5411\u306f 1 \u7a2e\u985e\u306e\u307f\u3067\u3042\u308b\uff08\u4e00\u822c\u7684\u306a 2 \u6307\u80fd\u52d5\u30d5\u30c3\u30af\u3082\u540c\u69d8\uff09\uff0e\u4e00 \u65b9\uff0cFig. 5 \u306e\u53f3\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\uff0c3 \u6307\u3092\u5bfe\u5411\u306b\u914d\u7f6e\u3059\u308b\u3068\uff0c\u56de\n\u5185\u5916\u3092\u884c\u308f\u305a\u306b 3\u7a2e\u985e\u306e\u628a\u6301\u65b9\u5411\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u80a9 \u3084\u4f53\u5e79\u306e\u52d5\u304d\u3067\u56de\u5185\u5916\u306e\u52d5\u304d\u3092\u88dc\u511f\u3059\u308b\u4ee3\u511f\u52d5\u4f5c\u3092\u6291\u5236\u3057\uff0c\u7121 \u7406\u306e\u306a\u3044\u59ff\u52e2\u3067\u306e\u64cd\u4f5c\u304c\u53ef\u80fd\u3068\u306a\u308b\uff0e3\u6307\u306b\u3088\u3063\u3066\u5177\u4f53\u7684\u306b\u3069 \u306e\u3088\u3046\u306a\u628a\u6301\u304c\u53ef\u80fd\u304b\u306f 3\u7ae0\u3067\u8ff0\u3079\u308b\uff0e 2. 3 \u30e6\u30fc\u30b6\u306e\u6307\u958b\u9589\u610f\u56f3\u3092\u691c\u51fa\u3059\u308b\u8ddd\u96e2\u30bb\u30f3\u30b5 \u63d0\u6848\u7fa9\u624b\u306f\u524d\u8155\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u88c5\u7740\u3057\uff0c\u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u30bb \u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u5fdc\u3058\u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\u65b9\u5f0f\u3092\u7528 \u3044\u3066\u3044\u308b\uff0eFig. 6\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5916\u89b3\u3092\u793a\u3059\uff0e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306b\u306f\uff0c \u975e\u63a5\u89e6\u3067\u8ddd\u96e2\u304c\u8a08\u6e2c\u53ef\u80fd\u306a\u30d5\u30a9\u30c8\u30ea\u30d5\u30ec\u30af\u30bf\uff08SG-105\uff0cKODENSHI\uff09\u3092\u7528\u3044\u305f\uff0e\u7b4b\u53ce\u7e2e\u3092\u884c\u3063\u3066\u3044\u306a\u3044\u72b6\u614b\u3067\uff0c\u8ddd\u96e2\u30bb\u30f3 \u30b5\u3068\u76ae\u819a\u9593\u306e\u8ddd\u96e2\u3092\u4e00\u5b9a\u306b\u4fdd\u3064\u305f\u3081\uff0c\u57fa\u677f\u4e0a\u306b\u914d\u7f6e\u3057\u305f\u30d5\u30a9\u30c8 \u30ea\u30d5\u30ec\u30af\u30bf\u306e\u4e0a\u4e0b\u306b\u9ad8\u3055 5 [mm] \u306e\u30dd\u30ea\u30de\u30fc\u30b7\u30fc\u30c8\uff08PORON L-24, \u30a4\u30ce\u30a2\u30c3\u30af\uff09\u306e\u30b9\u30da\u30fc\u30b5\u3092\u8a2d\u3051\u305f\uff0e\u3053\u306e\u30bb\u30f3\u30b5\u3092\u524d\u8155\u5207 \u65ad\u7aef\u306e\u7b4b\u53ce\u7e2e\u306b\u5fdc\u3058\u3066\u76ae\u819a\u8868\u9762\u306b\u9686\u8d77\u304c\u898b\u3089\u308c\u308b\u5834\u6240\uff0c\u4f8b\u3048\u3070\uff0c \u5c3a\u5074\u624b\u6839\u5c48\u7b4b\u306e\u76f4\u4e0a\u306a\u3069\u306b\u88c5\u7740\u3059\u308b\uff0e\u30bb\u30f3\u30b5\u306f\u4f38\u7e2e\u6027\u306e\u30d0\u30f3\u30c9 \u306a\u3069\u3067\u56fa\u5b9a\u3059\u308b\u304b\uff0c\u5f8c\u8ff0\u3059\u308b\u30bd\u30b1\u30c3\u30c8\u306e\u5185\u5074\u306b\u56fa\u5b9a\u3059\u308b\uff0e\u975e\u63a5 \u89e6\u306e\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u4f7f\u7528\u3059\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u7b4b\u96fb\u30bb\u30f3\u30b5\u306e\u6b20\u70b9\u3067\u3042 \u308b\u6c57\u306b\u3088\u308b\u8aa4\u52d5\u4f5c\u306e\u554f\u984c\u304c\u306a\u304f\uff0c\u91d1\u5c5e\u96fb\u6975\u304c\u76f4\u63a5\u76ae\u819a\u306b\u89e6\u308c\u306a \u3044\u30e1\u30ea\u30c3\u30c8\u304c\u3042\u308b\uff0e\u307e\u305f\uff0c\u30d5\u30a9\u30c8\u30ea\u30d5\u30ec\u30af\u30bf\u306f\u5b89\u4fa1\u306b\u8cfc\u5165\u53ef\u80fd \u306a\u6c4e\u7528\u96fb\u5b50\u90e8\u54c1\u306e\u305f\u3081\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u5168\u4f53\u3067\u3082 300\u5186\u7a0b\u5ea6\u3067\u88fd\u4f5c \u53ef\u80fd\u3067\u3042\u308a\uff0c\u7b4b\u96fb\u30bb\u30f3\u30b5\u306b\u6bd4\u3079\u3066\u5927\u5e45\u306a\u4f4e\u30b3\u30b9\u30c8\u5316\u3092\u56f3\u308c\u308b\uff0e 2. 4 \u8ddd\u96e2\u30bb\u30f3\u30b5\u306b\u57fa\u3065\u304f\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0 \u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u57fa\u3065 \u3044\u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e\u672c\u8ad6\u6587\u3067\u8aac\nJRSJ Vol. 32 No. 5 \u201456\u2014 June, 2014", + "\u660e\u3059\u308b\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306f\uff0c\u7b4b\u53ce\u7e2e\u306b\u3088\u308a\u6307\u304c\u958b\u304d\uff0c\u7b4b\u53ce\u7e2e\u3057\u306a\u3044 \u5834\u5408\u306f\u9589\u3058\u308b\u65b9\u5f0f\u306b\u306a\u3063\u3066\u3044\u308b\uff0e\u3059\u306a\u308f\u3061\uff0c\u80fd\u52d5\u30d5\u30c3\u30af\u306b\u304a\u3044\u3066 \u30cf\u30fc\u30cd\u30b9\u3092\u4ecb\u3057\u3066\u30b1\u30fc\u30d6\u30eb\u3092\u727d\u5f15\u3059\u308b\u3068\u6307\u304c\u958b\u304f\u30dc\u30e9\u30f3\u30bf\u30ea\u30fc \u30aa\u30fc\u30d7\u30f3\u3068\u540c\u69d8\u306e\u65b9\u5f0f\u3067\u3042\u308b\uff0e\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306f\u30cf\u30f3\u30c9\u306b\u5185\u8535\u3057 \u305f\u30de\u30a4\u30b3\u30f3\uff08Arduino Pro Mini\uff09\u306b\u5b9f\u88c5\u3057\u3066\u3044\u308b\uff0e\u8ddd\u96e2\u30bb\u30f3 \u30b5\u306f\u30de\u30a4\u30b3\u30f3\u306b\u63a5\u7d9a\u3055\u308c\uff0c\u30de\u30a4\u30b3\u30f3\u5185\u8535\u306e AD\u5909\u63db\u6a5f\u80fd\u306b\u3088\u3063 \u3066\uff0c\u30b5\u30f3\u30d7\u30ea\u30f3\u30b0\u5468\u6ce2\u6570 100 [Hz] \u3067\u30b5\u30f3\u30d7\u30ea\u30f3\u30b0\u3059\u308b\uff0e\u30b5\u30f3 \u30d7\u30ea\u30f3\u30b0\u3057\u305f\u5024\u306f\u73fe\u5728\u5024 x(n) \u3068\u904e\u53bb 9 \u70b9\uff0c\u5168 10 \u70b9\u306e\u5358\u7d14\u79fb \u52d5\u5e73\u5747\u306b\u3088\u308a\u5e73\u6ed1\u5316\u3055\u308c\u308b\uff0e\u3053\u3053\u3067\uff0cn \u70b9\u3081\u306e\u5e73\u6ed1\u5316\u5f8c\u306e\u5024\u3092 xs(n)(n = 0, \u00b7 \u00b7 \u00b7 , N) \u3068\u3059\u308b\uff0e \u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306e\u51e6\u7406\u306e\u6d41\u308c\u3092 Fig. 7\u306b\u793a\u3059\uff0e\u307e\u305a\uff0c\u64cd\u4f5c\u3092\u884c \u3046\u524d\u306b\u30e6\u30fc\u30b6\u306b\u5408\u308f\u305b\u3066\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u3092\u884c\u3046\uff0e\u30cf\u30f3\u30c9\u672c \u4f53\u306e\u30b9\u30a4\u30c3\u30c1\u3092\u9577\u62bc\u3057\u3059\u308b\u3068\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u958b\u59cb\u3055\u308c\u308b\uff0e \u306f\u3058\u3081\u306b\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u524d\u8155\u306b\u88c5\u7740\u3057\u305f\u72b6\u614b\u3067\u30b9\u30a4\u30c3\u30c1\u3092\u62bc\u3057\uff0c \u7b4b\u53ce\u7e2e\u3057\u3066\u3044\u306a\u3044\u5e73\u5e38\u6642\u306e\u30bb\u30f3\u30b5\u5024\u3092 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3057\uff0c \u305d\u306e\u5e73\u5747\u5024 Xrest \u3092\u8a08\u7b97\u3059\u308b\uff0e\u6b21\u306b\uff0c\u6700\u5927\u306b\u7b4b\u53ce\u7e2e\u3057\u305f\u72b6\u614b\u3067 \u30b9\u30a4\u30c3\u30c1\u3092\u518d\u5ea6\u62bc\u3059\u3068\uff0c\u30bb\u30f3\u30b5\u5024\u304c 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3055\u308c\uff0c \u305d\u306e\u5e73\u5747\u5024 Xmax \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e\u6b21\u306b\uff0cXmax \u3068 Xrest \u306e\u5dee\u5206 Xdif \u3092\u6b21\u5f0f\u3067\u8a08\u7b97\u3059\u308b\uff0e\nXdif = Xmax \u2212Xrest \uff081\uff09\n\u3053\u306e Xdif \u3068\u6307\u304c\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5 \u30c8\u306e\u6700\u5927\u7e70\u308a\u51fa\u3057\u91cf Lmax \u3092\u7528\u3044\u3066\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u99c6\u52d5\u30d1\u30e9\u30e1\u30fc \u30bf R \u3092\u6c7a\u5b9a\u3059\u308b\uff0e\nR = Lmax\nXdif \uff082\uff09\n\u4ee5\u4e0a\u3067\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u7d42\u4e86\u3059\u308b\uff0e\u3053\u306e\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7 \u30f3\u30d7\u30ed\u30bb\u30b9\u306f\uff0c3\u56de\u306e\u30b9\u30a4\u30c3\u30c1\u64cd\u4f5c\u3067\u884c\u3048\u308b\u305f\u3081\u30e6\u30fc\u30b6\u81ea\u8eab\u3067 \u884c\u3046\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u307e\u305f\uff0c3 \u79d2\u4ee5\u5185\u306b\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3 \u304c\u5b8c\u4e86\u3059\u308b\u306e\u3067\uff0c\u518d\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u6642\u9593\u3092\u5fc5\u8981\u3068\u3057\u306a\u3044\uff0e \u6b21\u306b\u64cd\u4f5c\u6642\u306b\u3064\u3044\u3066\u8aac\u660e\u3059\u308b\uff0e\u64cd\u4f5c\u6642\u306e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5e73\u6ed1\u5316 \u5f8c\u306e\u5024\u3092 xs(k)(k = 0, \u00b7 \u00b7 \u00b7 ,K) \u3068\u3059\u308b\u3068\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u30b7\u30e3\u30d5\u30c8 \u306e\u7e70\u308a\u51fa\u3057\u91cf l(k) \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e\nl(k) = R(xs(k)\u2212Xrest) \uff083\uff09\n\u3053\u306e\u3068\u304d\uff0c\u4f55\u3089\u304b\u306e\u539f\u56e0\u306b\u3088\u308a l(k) > Lmax \u3068\u306a\u3063\u305f\u5834\u5408\u306f\uff0c l(k) = Lmax \u3068\u3057\uff0cl(k) \u306e\u5024\u3092\u6307\u4ee4\u5024\u3068\u3057\u3066\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u305f\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306b\u9001\u308b\uff0e 2. 5 \u30bd\u30b1\u30c3\u30c8\u5f62\u72b6\u3068\u30cf\u30f3\u30c9\u30db\u30eb\u30c0 Fig. 8 \u306b\u65ad\u7aef\u3092\u633f\u5165\u3059\u308b\u5de6\u624b\u7528\u306e\u30bd\u30b1\u30c3\u30c8\u3068\u30cf\u30f3\u30c9\u30db\u30eb\u30c0 \u3092\u793a\u3059\uff0e\u30bd\u30b1\u30c3\u30c8\u306e\u9060\u4f4d\u7aef\u306f\u30cf\u30f3\u30c9\u30db\u30eb\u30c0\u3068\u63a5\u7d9a\u3057\uff0c\u30cf\u30f3\u30c9\u3092\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201457\u2014 2014 \u5e74 6 \u6708" + ] + }, + { + "image_filename": "designv8_17_0000371_f_version_1670506480-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000371_f_version_1670506480-Figure8-1.png", + "caption": "Figure 8. The photo of three overrunning clutches without retaining ring.", + "texts": [ + " Structure Description of Three Overrunning Clutches The structural parameters of the three overrunning clutches are shown in the data in Table 1 above. The SOC was purchased from the market, and its rated torque was 95 Nm. The other two overrunning clutches were designed and manufactured according to the data in Table 1. The material of the three overrunning clutches was GCr15, and the heat treatment hardness of the outer ring, roller, and inner star wheel was HRC55-60. The photos of the three overrunning clutches are shown in Figure 8. Although from Figure 8 it can be seen that the keys of the three overrunning clutches were not completely consistent, the experimental results show that the shapes of the keys had little influence on the stiffness. Machines 2022, 10, x FOR PEER REVIEW 13 of 18 The expe iment began with the non-lubrication condition. In this condition, the inner star wheel was fixed by chassis and loaded with a bar. The DASOC showed reliable self- locking phenomenon without sliding in clockwise rotation. The counterclockwise rotation was smooth and did not become stuck", + " Structure Description of Three Overrunning Clutches The str ctural parameters of the three overrunning clutches are shown in the data in Table 1 above. The SOC was purchased from the market, and its rated torque was 95 Nm. The other two overrunning clutches were designed and manufactured according to the data in Table 1. The material of the three overrunning clutches was GCr15, and the heat treatment hardness of the outer ring, roller, and inner star wheel was HRC55-60. The pho- tos of the three overrunning clutches are shown in Figure 8. Although from Figure 8 it can be seen that the keys of the three overrunning clutches were not completely consistent, the experimental results show that the shapes of the keys had little influence on the stiffness. 5.2.2. The Experiment Platform and Torsion Stiffness Experiment experimental device beyond the clutch. The system was composed of a chassis, monitor, overrunning clutch, force arm, micrometer, force sensor, screw, and force-adding nut. Figure 8. The photo of three overrunning clutches without retaining ring. Machines 2022, 10, 1188 13 of 17 5.2.2. The Experiment Platform and Torsion Stiffness Experiment A test system, as shown in Figure 9, was constructed to measure the torsion stiffness experimental device beyond the clutch. The system was composed of a chassis, monitor, overrunning clutch, force arm, micrometer, force sensor, screw, and force-adding nut. Machines 2022, 10, x FOR PEER REVIEW 14 of 18 Figure 9. The experiment platform of torsion stiffness" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003110_9874358_09831045.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003110_9874358_09831045.pdf-Figure2-1.png", + "caption": "Fig. 2. Vacuum shell of (a) Singlet 1 and (b) Singlet 2. The inset images depict the side views of each singlet\u2019s input positions, either inline or offset.", + "texts": [ + " Using (1), we can characterize triangular-waveguide singlets and quasitriplets operating with the TM120 mode for the first time in the literature as an alternative geometry\u2014which is also convenient for optimizing on-chip layout\u2014and is capable of achieving an equivalent Q-factor via (1) when compared with rectangular or cylindrical cavities that have similar thicknesses and center frequencies, and operate with analogous electromagnetic field distributions (i.e., the TM110 and TM010 modes, respectively). For the design at hand, we select the TM120 mode and formulate the singlet to be fed with slot-type irises in a position that can simultaneously allow for a bypass coupling to pass from the source to load; Fig. 1 depicts the magnetic field distribution for the 90 GHz triangular singlet example that follows in Fig. 2(a). In addition, the singlet topology is indicated in the image for reference. Fig. 2(a) and (b) shows two cases of a singlet, which is designed for operation at 90 GHz where the transmission zero position is selected relative to the positions of the source/load coupling; inline or offset. The structure proposed in Fig. 2(a) results in the transmission zero on the lower side (Msl < 0), while the structure proposed in Fig. 2(b) results in the transmission zero on the upper side (Msl > 0). This effect is demonstrated in Fig. 3 for the simulation of each structure over 80\u2013100 GHz. In order to extend this concept to bandpass filter design, the triangular singlet can be modified to include resonant irises similar to the formulations outlined in [22] and [23]. Fig. 4 shows the magnetic field distribution of a singlet with the two resonant irises and describes the basic interaction throughout the filter. The modified topology now includes the resonant irises and is indicated in the image for reference; it can be noted that the bypass coupling is now formed between the resonant slot irises (nodes 1 and 3) in a quasi-triplet fashion" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002052_9312710_09380129.pdf-Figure28-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002052_9312710_09380129.pdf-Figure28-1.png", + "caption": "FIGURE 28. Surface current distribution for the Rx filter at 2.25 GHz.", + "texts": [ + " It can be noticed that the insertion loss of both filters is 0.9 dB (max.), and superior matching performance is obtained (less than \u221215 dB) in the range of 2.2 GHz\u22122.3 GHz for the Tx filter, and 2.04 GHz- 2.11 GHz for the Rx filter. Fig. 26, and Fig. 27 illustrate the surface current distribution for the proposed Tx filter. It can be noticed clearly that the EM wave cannot pass at the stop band (i.e., at 2.06 GHz), however, it can easily pass through the filter at 2.25 GHz. On the other hand, Fig. 28, and Fig. 29 show that the EM wave cannot propagate through the Rx filter around 2.25 GHz, while it can pass smoothly at 2.06 GHz (mid of its passband). E. PRACTICAL MEASUREMENTS In order to verify the simulations, The Tx filter is fabricated using the photolithographic technology on RT 6010 substrate. The filter is fitted in the Anrtisu test-in fixture, then its S-parameters are measured using Vector Network 45132 VOLUME 9, 2021 Analyzer (VNA) ZAV67 after standard calibration procedure. Fig. 30 shows the measurement setup" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004361_rs-740948_latest.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004361_rs-740948_latest.pdf-Figure6-1.png", + "caption": "Fig 6 Compliant mechanism Model in Adams software", + "texts": [], + "surrounding_texts": [ + "Input parameters are:-crank length (r2 )= 25 mm; length of flexible segment( L)= 110 mm; offset (e)= -19 mm; slider is free to move in horizontal direction , there is no horizontal reaction force (n= 0) and the force on the end of the flexible coupler is therefore vertical; characteristic radius factor (\u03b3)= 0.852 mm; stiffness coefficient(K\u04e9)= 2.68, width of links (w)= 20 mm, height of flexible link (h) = 1.6 mm This model may now be analyzed using rigid-body mechanism equations:r3 = 93.72mm, l = 16.28mm, I = 6.826mm3 and K = 9895.2 (for rectangular cross section) Numerical result for displacement at various crank shown in table and fig Modeling of Slider crank compliant mechanism in Adams by PRBM Method The base of modeling in ADAMS is simulating the pseudo-rigid-body model which included rigid links related by revolute joints to each other. Length of the flexible segment is modified as it's shown in Figure. Considering the flexibility of the compliant segment a torsional spring is set on pivot. The stiffness of this spring is obtained from equation. According to the geometry and density of each link, masses automatically calculate by this software. Slider Displacement Xb VS \u03982 for compliant slider crank mechanism by PRBM FEA model which is shown below is modeled in Adams software \u2022 For FEA model, Beam element is used in the ADAMS. For flexible segment discrete flexible link will used for FEA model. Comparison of numerical and simulation result (FEA and PRBM method)" + ] + }, + { + "image_filename": "designv8_17_0003981_20_01_smdo200027.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003981_20_01_smdo200027.pdf-Figure11-1.png", + "caption": "Fig. 11. Distribution of tangential velocity at X3. (a) Contour velocity with canard. (b) Contour without canard.", + "texts": [ + " Thus, the velocity contours of auxiliary planes X1, X2, X3 and X4 are presented as following to investigate the flow tendency influenced by the canard wing as well as the velocity distribution in vertical sections (see Fig 9\u2013Fig 12), to figure out the influence by the canard configuration. By comparison of the distribution of velocity at X1, X2, X3 andX4, the flow before the delta wing is quite disturbed by the canard wing (see Fig. 9), in which two additional zones of vortices generate in X2 plan just along the transition and end parts of the canard (see Fig. 10). Contour with canard. (b) Contour without canard. ) Contour with canard (b) Contour without canard. Afterward, when the flow from the canard wing are crossing the delta wing (see Fig. 11), the velocity distribution keeps the almost same as that without canard (see Fig. 12), in which the flow will escape from the down surface to the up surface by winglet. After observation the velocity distribution, two reasons are concluded: (1) the new vortices zones are quite far from the winglet in the optimized conceptual design; (2) the strength of the vortices (maximum tangential velocity is 1.91m/s in Fig. 10) by the canard are much less than that by the delta wing (maximum tangential velocity is 21" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002052_9312710_09380129.pdf-Figure26-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002052_9312710_09380129.pdf-Figure26-1.png", + "caption": "FIGURE 26. Surface current distribution for the Tx filter at 2.06 GHz.", + "texts": [ + " FULL WAVE SIMULATION, AND PARAMETERS OPTIMIZATION For design verification, the proposed filters (Both Tx, and Rx) are simulated using Microwave Studio CSTMWS 2019 software package. Besides, for more accuracy assurance, a frequency domain solver is adopted. Both Fig. 24, and Fig. 25 show the S-parameters of the optimized Tx, and Rx filters, respectively. It can be noticed that the insertion loss of both filters is 0.9 dB (max.), and superior matching performance is obtained (less than \u221215 dB) in the range of 2.2 GHz\u22122.3 GHz for the Tx filter, and 2.04 GHz- 2.11 GHz for the Rx filter. Fig. 26, and Fig. 27 illustrate the surface current distribution for the proposed Tx filter. It can be noticed clearly that the EM wave cannot pass at the stop band (i.e., at 2.06 GHz), however, it can easily pass through the filter at 2.25 GHz. On the other hand, Fig. 28, and Fig. 29 show that the EM wave cannot propagate through the Rx filter around 2.25 GHz, while it can pass smoothly at 2.06 GHz (mid of its passband). E. PRACTICAL MEASUREMENTS In order to verify the simulations, The Tx filter is fabricated using the photolithographic technology on RT 6010 substrate" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001062_125_3_125_3_293__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001062_125_3_125_3_293__pdf-Figure1-1.png", + "caption": "Fig. 1. Basic construction of a usual rocker switch with a reset function.", + "texts": [ + " The boundary condition in the coil is set to distribute the current uniformly. 2.2 3-D Finite Element Analysis The fundamental equation of the magnetic field using the 3-D finite element method can be written using the magnetic vector potential A as follows: rot (\u03bdrot A) = J0 + \u03bd0rot M \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (3) where \u03bd is the reluctivity, \u03bd0 is the reluctivity of the vacuum, M is the magnetization of the permanent magnet and J0 is the current density. 3. Analyzed Models and Results 3.1 Usual Electromagnetic Reset Switch Figure 1 shows a basic construction of a usual rocker switch with the electromagnetic reset function. It mainly consists of the electromagnetic structure, reset springs, electric contact part and handle. Figure 2 shows its detail magnetic structure. This model consists of the armature which contains two magnetic poles equipped with a permanent magnet, and the stator \u96fb\u5b66\u8ad6 D\uff0c125 \u5dfb 3 \u53f7\uff0c2005 \u5e74 293 which has a coil wound around its leg. This figure shows the situation when the switch is turned on, and the armature is pulled towards the stator and kept closed only by the attractive force of the permanent magnet" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure2.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure2.6-1.png", + "caption": "Figure 2.6. Link types important for suspensions, reproduced from [26].", + "texts": [ + " Matschinsky notes that the turning joint is often implemented practically with two rubber joints, while the turning-and-sliding joint takes the form of a telescopic damper; see Figure 2.5. Finally, he mentions the ball-and-surface joint, Figure 2.4e, but says it is very rarely found in independent suspensions, discussing it further only in the context of rigid axle suspension linkages. Matschinsky does not construct links combinatorially like Raghavan, instead directly stating the most important types, Figure 2.6. The rod link, Figure 2.6a, has a ball joint (or equivalent rubber joint) at each end. It comes with a superfluous rotation r, which does not affect the wheel carrier motion. The triangular link, also known as the A-arm or wishbone, Figure 2.6b, has a ball joint at one end and a turning joint at the other. The turning-joint side is typically at the vehicle body, but the reverse is also possible. The trapezoidal link, also known as the H-arm, Figure 2.6c, has turning joints at each end. The turning-and-sliding link, Figure 2.6d, has a ball joint at one 49 50 end and a turning-and-sliding joint at the other, with the turning-and-sliding joint axis passing through the ball joint. Like the rod link, it has a superfluous rotation r that does not affect wheel carrier motion. In practice, the ball joint end of the turning-and-sliding link is at the vehicle body. Matschinsky provides the following mobility formula for suspensions: F = 6(k + l \u2212 g)\u2212 r + g\u2211 i=1 fi, where F is mobility, k is the number of wheel carriers (k = 1 for independent suspensions), l is the number of links, g is the number of joints, r is the number of superfluous link rotations, and fi is the degree-of-freedom of the ith joint" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure5.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure5.12-1.png", + "caption": "Fig. 5.12. Estimates as functions: a) shape factor, b) peak factor, c) impulsivity factor, d) play factor", + "texts": [], + "surrounding_texts": [ + "VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 51 The presented methods, based on stochastic nature of signals, allows to observe the single vibration signal (time realization) as series of distribution of some estimators of the vibration. This kind of approach allows to define the vibration phenomena as vector of many statistical estimators described series of vibration values changes in time. Furthermore, a statistical analysis of the vibration courses being recorded was conducted as well, leading to determination of empirical surface estimates for natural vibrations, which enabled the vibrations to be assessed with regard to the geometrical position on the floor panel. The studies performed are essentially of preliminary nature, and hence they require supplementation and further verification. VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 53" + ] + }, + { + "image_filename": "designv8_17_0003548_om_article_19879.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003548_om_article_19879.pdf-Figure4-1.png", + "caption": "Figure 4. Concentric magnetic tiles", + "texts": [], + "surrounding_texts": [ + "Because of the different structure, compared permanent magnet fault-tolerant motor with the traditional permanent magnet synchronous motor, there are many differences in terms of parameter design. In this section, we use a four-phase six-pole permanent magnet fault-tolerant motor as an example, and research the design of motor structure and electromagnetic parameters. The main performance parameters of this motor are as follows: rated power PN=1KW, rated voltage UN=36V, rated speed nN=1200rpm, number of the stator Ns=8, rotor pole pairs p=3, number of phase m=4, rated efficiency \u03b7N=90%, the rated power factor cos\u03c8N=0.8. A. Design of stator inner diameter and core length The main dimensions of the permanent magnet fault-tolerant motor are specified the inside diameter and the effective axial length of stator core which can be determined according to the need of maximum torque and dynamic response indication [10] . When the biggest electromagnetic torque of motor is Temmax(N . m), then the relationship between main dimensions and electromagnetic loads is: 42 11 10 4 2 max ADLBT iefem (1) where B1 is the flux density of fundamental amplitude (T), A is the stator electric load valid value (A/CM). Obtained the relationship between the main dimensions of motor and the electromagnetic loads according to formula (1): AB T LD em efi 1 4 2 1 1022 max (2) p KmNI A dp1 (3) where m is the motor phase, N is the winding turns, I1 is the stator current, p is the rotor pole pairs, Kdp is the winding factor, \u03c4 is the motor pole pitch. Here we take power load A=150A/cm, the flux density of fundamental amplitude B\u03b41=0.8T. Because the dynamic response performance index of a permanent magnet fault-tolerant motor mainly refers to the motor that under the effect of maximum electromagnetic torque Temmax can accelerate linearly from rest to turning speed \u03c9b during time of tb , that is: b b em pt J tp J T max (4) where J is the rotor and load inertia (kg . m 2 ). Therefore, according to formula (4) we can obtain the ratio of maximum electromagnetic torque to the moment of inertia is: b bem ptJ T max (5) The moment of inertia of the motor rotor can approach to: 741 10) 2 ( 2 i efFe D LJ (6) where \u03c1Fe is the mass density of the rotor material iron (g/cm 3 ). We take formula (1) and formula (6) into equation (5), can obtain the stator inner diameter Di1(cm) is: 3 1 1 10 28 Feb b i ABpt D (7) Then according to equation (2), we can obtain the effective axial length of the stator core Lef(cm) is: 22 11 2 1 4 4 101022 maxmax ABpt T ABD T L b Febem i em ef (8) B. Design of groove parameters Fig .1 shows the block diagram of stator slots of permanent magnet fault-tolerant motor after straightening. From Fig .1, we can know that the parameters which need be calculated include: notch thickness Hs0, slot width Bs0, stator tooth width Bt and stator tooth height Hs2. Firstly, according to the magnetic saturation constraint conditions of the stator teeth, we obtained the tooth height and the tooth width. Secondly, according to the design requirements of slot leakage inductance, we derived the notch height and width. Finally, in accordance with the requirements of internal winding current density of stator slot, we calculated the other parameters, like the width of the groove bottom Bs2 and the width of the groove top Bs1. 1) Parameter calculation of stator teeth Assuming all of the air-gap magnetic flux through the main stator teeth, so the stator tooth width is obtained as follows: maxt i t b B B (9) where B\u03b4 is magnetic load, \u03b1i is calculated pole arc coefficient. Because when ferromagnetic material under normal circumstances, the maximum magnetic flux density of the stator teeth btmax equal to 1.4~1.6T, therefore, this article selected btmax=1.5T, and according to formula (9) can derive the stator tooth width Bt. Generally, the height and width ratio of the stator teeth is between 1.5 and 3. Because, if the ratio is small, the stator slot is very shallow, this may cause very high current density that through the inner winding. But if the ratio is large, then the stator slot is very deep, the stator yoke is easy to reach saturation, and the electromagnetic torque may reduce. So in this paper, we take the value of 2, and the stator tooth height is: ts BH 22 (10) 2) Calculation of notch parameter In order to reduce the saturation degree of the stator tooth tip maximum extent, at the same time to improve the slot leakage inductance Ls0\u03c3, the notch thickness Hs0 generally taken to be (0.35~0.5)Bt, this article is taken as 0.4 times, that is: ts BH 4.00 (11) Slot leakage inductance Ls0\u03c3 is: 0 000 2 0 0 ))((2 s sefss s B BLBHN L (12) Because the notch width Bs0 is much smaller than the effective axial length of stator core Lef, therefore, formula (12) can be simplified as: 0 00 2 0 0 )(2 s efss s B LBHN L (13) Rearranging slot width Bs0 is: efs efs s LNL LHN B 2 00 0 2 0 0 2 2 (14) where the slot leakage inductance Ls0\u03b4 taken as 0.33 times of the coil inductance Ls, and has the following formulas: eese s If E I E L 2 00 (15) NNN N e mU P I cos (16) where E0 is the motor back electromotive force (V), \u03c9e is the electrical angular frequency (rad/s), Is is the steady-state short-circuit current (A), Ie is the motor rated current (A), fe is the rated synchronization frequency (Hz). 3) Calculation of armature winding turns and coil diameter The definition of motor no-load back electromotive force(EMF) is: 010 44.4 we NkfE (17) where fe is the rated synchronization frequency(Hz), kw1 is the winding factor, \u03a60 is the fundamental magnetic flux air gap(Wb), and has the following formulas: ef i LB ) 2 sin 4 ( 2 0 (18) So the number of turns of the armature winding N is: )2sin( 18.0 11 0 iefiwe LDBkf pE N (19) According to the dimensions of slot form, we can get the area of stator slots As is: 2 sin)( 221 sss s HBB A (20) where \u03b8 is the mechanical angle that relative to the centerline of the pole (rad), and: Width of the top slot is: t si s B Q HD B )2( 01 1 (21) Width of the bottom slot is: t sssi s B Q HHHD B )(2 2101 2 (22) where Q is the number of stator slots, in order to reduce the degree of magnetic saturation of tooth boots, Hs1 generally taken as 0.5~1mm. 4) Calculation of stator and rotor yoke portion thickness The thickness of the yoke of stator and rotor needs to meet the constraints of magnetic saturation, for the four-phase six-pole permanent magnet fault-tolerant motor in this article, the maximum value of yoke flux density is 1.6~1.8T, which is slightly larger than the maximum limit value of flux density in tooth portion, in this paper the value is 1.6T. Then the thickness of the stator yoke portion Hsy is: sy im sy b b H 2 1 (23) The thickness of the rotor yoke is: ry p ry b B H 2 1 (24) where bsy is the flux density of stator yoke portion (T), bry is the flux density of rotor yoke portion (T). C. Magnetic circuit design Magnetic circuit design includes the determination of overall structure, the determination of sizing and the selection of material, which focuses on the work of choosing permanent magnetic materials and designing the operating point. 1) Permanent magnet material selection In this paper, we chose NdFeB N38H as the permanent magnet material, the remanence density Br20 is 1.23T, the temperature coefficient \u03b1Br is 0.12 %/\u2103, the irreversible demagnetization loss IL is 0.7%, the calculated coercive force of permanent magnet Hc20 is 899kA/m. We can obtain following results according to the selection of NdFeB N38H: (1)Remanent flux density during the operating temperature: 20 [1 ( 20) /100] [1 /100] 1.18 r Br r B t IL B T (2)Calculated coercive force during the operating temperature: mkA HILtH cBrc /7.833 ]100/1[]100/)20(1[ 20 (3)Relative permeability of the permanent magnet: 20 0 20 1.089 1000 r r c B H where 0 is vacuum permeability, 0=410 -7 H/m. 2) Determine the shape of permanent magnet Surface magnetic pole structure can improve the ability of isolation between the windings, in this article we use the surface-type tile-shaped magnetic poles in the permanent magnet fault tolerant motor, shown in Fig .3. The structure of permanent magnet contacting the air gap directly is easy processing and installation. And uses a concentric tile-shaped magnetic poles, i.e., the outer diameter and the inter diameter of the permanent magnets have a common center, it shown as in the Fig .4. 3) Calculate the size of permanent magnet The main size parameters of permanent magnet part include the thickness and the width of permanent magnet, and can be determined by the following formula: The thickness of permanent magnet hM is: i r r M B B h 1 (25) The width of permanent magnet bM is: pM b (26) where \u03bcr is the relative permeability of ferromagnetic material; \u03b4i is the calculating air gap length of motor(cm); Br is the residual magnetic induction intensity of permanent magnet (T); B\u03b4 is the magnetic load (T); \u03b1p is the percentage of pole embrace. Generally Br/B\u03b4 equal to 1.1~1.35. 4) Permanent magnet magnetization way of design In this paper, the arrangement of permanent magnet is in the way of Halbach array [11] , this kind of arrangement can not only enhance the air gap flux of motor, but also can weaken the magnetic flux of rotor yoke, which is particularly suitable for the rotor structure of using surface-mounted permanent magnet. Halbach array is a novel magnetic structure array that combines radial array with tangential array, as Fig .5(a) shows, so that we can make the magnetic field in one side of permanent magnet strengthening and the other side weakening. The rational design of Halbach array can make the air-gap flux density and the no-load back electromotive force having good sinusoidal. Fig .5 (b) shows the distribution of magnetic equipotential line of the permanent magnet motor with Halbach array which is calculated by the ANOSOFT which is one of the finite element analysis software. As we can see, after using Halbach array, the magnetic flux of rotor yoke significantly reduced, while the magnetic flux that across air gap into the stator significantly increased, which increases the magnetic load of permanent magnet motor and the density of force and energy, so Halbach array is very suitable for the ideal for the permanent magnet fault-tolerant motor with the inter rotor structure of permanent magnet posted outside." + ] + }, + { + "image_filename": "designv8_17_0002629__12_129_12_1155__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002629__12_129_12_1155__pdf-Figure1-1.png", + "caption": "Fig. 1. System configuration", + "texts": [ + "xtended Summary \u672c\u6587\u306f pp.1155\u20131162 Development of Search Robot with Active Vision Shinichiro Kumagai Student Member (Tokyo Metropolitan University, kumagai@kisl.tmit.ac.jp) Yasuchika Mori Member (Tokyo Metropolitan University, ymori@cc.tmit.ac.jp) Keywords: image processing, active vision, stereo vision era. System configuration is shown in Fig. 1. Correspondence points are determined by using the image obtained with the camera. The next position of the camera is determined by using a unique evaluation function in the active vision system. The camera is moved according to the information conveyed to the servo driver through the motion control board. Fig. 2 shows an image shot by a camera initial position, and Fig. 3 shows an image in a location estimated using an active vision. From Fig. 2 and Fig. 3, it can be seen that the objects were not occluded" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004648_478_amns.2022.2.0091-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004648_478_amns.2022.2.0091-Figure2-1.png", + "caption": "Figure 2 Deflection of a horizontally loaded pile", + "texts": [ + " D is the outer diameter of the pile. The dimensionless number / up p is multiplied by the ultimate resistance up to obtain the reaction load concentration. The following formula expresses the p-y curve of sand: tanhu u Kxp Ap y Ap (2) Where A is a coefficient describing static or cyclic loads. K is the initial modulus 3( / )kN m of the sand foundation reaction force. It is obtained from a look-up table for the effective internal friction angle. The horizontal load pile and the coordinate axis setting are shown in Figure 2. X axis downward is positive [4]. The direction of deflection w is positive if it is the same as the direction of the external load. When subjected to external loads, the configuration of the pile body will minimize the potential energy of the pile-soil-load system. The deflection curve function represents the pile body configuration ( )w x . The system potential energy includes the following three parts: 1 2 3TE E E E (3) 1E is the potential energy of the external load. 2E is the potential energy stored by the bending of the pile body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002203_2452-023-05288-w.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002203_2452-023-05288-w.pdf-Figure6-1.png", + "caption": "Fig. 6 Dynamic simulation optimization method", + "texts": [ + "2 0.3 0.4 0.5 th e an gl e \u03b2 (d eg ) the difference \u03be (b) Front wheel excitation Rear wheel excitation Vol:.(1234567890) objective function is a mathematical expression used to evaluate the quality of a design scheme, constraint equations are mathematical relationships used to constrain the values of design variables [13, 14]. In the paper, dynamic simulation optimization method is used to optimize the vehicle vibration analysis. The vehicle dynamics simulation model is established, as shown in Fig.\u00a06. The model includes tire model, suspension model, the frame and the body model. The design variables are suspension stiffness kf and kr, and the variation range of the variable is shown in Table\u00a02. The objective function is min ||||afu|| \u2212 ||aru|||| , and the constraint equation is The relationship between the optimization variable and the objective function is implicit in the virtual prototype model. Through simulation, the optimization target value of a certain set of independent variables can be obtained" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003512_e_download_9236_8414-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003512_e_download_9236_8414-Figure8-1.png", + "caption": "Figure 8: Second Re-designed model with FEA results", + "texts": [], + "surrounding_texts": [ + "2.1. Assembly of Radial Engine The objective of this work is to redesign the articulated rod from the radial engine by using generative method. A reciprocating type internal combustion engine is known as a radial engine. Prior to the invention of gas turbine engines, the radial configuration was widely used for aircraft engines. Since the axes of the cylinders are coplanar, connecting rods cannot always be directly linked to the crankshaft, so the pistons are connected to the crankshaft by a master-and-articulating-rod assembly. The model of the radial engine that was produced using solid edge software can be observed in the Figure 1 and the details of individual parts are given in Table 1. 2.2. Articulated Rod The part that is focused for the design optimization is Articulated Rod. The model of Articulated Rod can be seen in the Figure 2. As mentioned earlier, the material of this part is Steel 4340, and its properties can be seen in Table 2. 2.3. Applied force calculation: In this work, the applied force on the model is the force that is acting on the connecting rod in the engine. The force that is acted on the connecting rod is involved with 3 other forces, which are force on piston due to gas pressure, force that is caused by inertia of reciprocating mass and connecting rod, and force due to friction of piston and of piston ring. The calculation method is obtained from [16]. The relevant parameters can be observed in the Table 3. Force on piston from gas pressure (Fa) can be calculated using the formulae below: \ud835\udc39\ud835\udc4e = \ud835\udf0b \u2146 2 \ud835\udc5d\ud835\udc52 4 (1) From (1), we then obtain Fa = 11545.35 N Force that is caused by inertia of reciprocating mass and connecting rod (Fi) can be found by the following equation: \ud835\udc39\ud835\udc56 = \ud835\udc40\ud835\udc642\ud835\udc5f (\ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udf03 + \ud835\udc5f \u2217 \ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udf03 \ud835\udc59 ) (2) Hence, from (2), Fi = 16614.04 N Force due to friction of piston and of piston ring (Ff) From the research paper [7], Ff = 4000 N Force acting on piston (Fp) is equal to three forces combined as follows: Fp = Fa + Fi + Ff = 24159.39 N Force acting on connecting rod (F) can be known by the following equation. \ud835\udc39 = ( \ud835\udc39\ud835\udc5d \ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udefd ) (3) From (3), F = 24159.39 ~ 25000 N 2.4. Method There are three main parts of the methodology, which are finite element analysis, generative design, and conventional redesigning shape of the model. Solid Edge was used to create the part model to conduct the finite element analysis, also it was used to do generative design and redesign of the component as well. First, the articulated rod, which is the focused part for improvement, was created. Then, the boundary conditions are applied to the model. The fix constraint was applied to the smaller circular ring. The force of 25000 N was given to the inner surface of the bigger cylinder. The boundary conditions of articulated rod model can be seen in the Figure 3 (left). After that, in order to observe the stress and displacement distribution in the model, finite element analysis was run. Also, mesh analysis was conducted to observe the change in the maximum stress, maximum displacement, and elapse time of the different subjective mesh size in order to select the most reasonable mesh size for the finite element analysis. In the mesh analysis, 10 different mesh sizes were applied to the model. Figure 3 (right) also shows the preserved region of the rod which will not undergo any changes during generative design so that the connecting parts doesn\u2019t need any changes after the generative design results are obtained. Next, the generative design of the part was started. The goal is to reduce the mass of the rod while the stress and displacement is within the acceptable range. The bigger and smaller cylinder were selected to be a preserved region, which will not change in shape after the new design is finished so that compatibility with existing parts remains unchanged. The chosen safety factor is 1.4. The boundary conditions of generative design can be observed in the generative design was run with different chosen mass reduction from 10-50% of the rod\u2019s original mass to observe the various shape of the design. Finally, the conventional redesign was conducted to redesign the genitive designs shape to be manufacturable in the regular process. 2.5. Results and discussions First of all, the different mesh sizes were applied to observe the maximum stress, maximum displacement, and solving time of the part. The results are illustrated in Table 4; Figure 4 represents the plot between mesh size versus maximum stress and mesh size versus maximum displacement. After analysing mess sensitivity it is concluded that the 1.10 mm of mesh size is most suitable one for our purpose because the results of stress and displacement are really good and the elapse time is not much higher. Figure 5 provides the FEA results, which show the stress and displacement distribution of the model. Once required mesh size has been finalised then generative designs can be obtained by varying different parameters, generative design of Articulated Rod of Radial Engine is created using Solid Edge CAD software. The designs are obtained in the various shapes, depending upon the constraints provided such as mass reduction percentage, elapse time and quality of the generated design. Mass reduction of the rod is observed within the range of 10-50% minimization of the original mass. The execution time varied from 20-30 minutes. Furthermore, factor of safety has been fixed as 1.4, considering the dynamic load of the rod. Figure 6 (a) and (b) shows the different designs obtained after the process along with the processing time and resultant weight of the rod. Next step is conventional or practically possible redesigning of our product inspired by generative design results. We redesigned three different types of models in a way that it can be produce by conventional methods or CAM (Computer Aided Manufacturing). Thereafter, FEA is performed once again to check the feasibility of the redesigned models, results along with model designs can is shown in Figure 7-9. Once all completed, the design will be subjected to practical load testing to cross-check the real life feasibility of the models." + ] + }, + { + "image_filename": "designv8_17_0002218_Issu02_p_827-831.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002218_Issu02_p_827-831.pdf-Figure2-1.png", + "caption": "Fig. 2: The design of stepless automatic transmission", + "texts": [ + "(19) where V0 \u2013 the working volume of the hydraulic machine, mm3; z \u2013 the number of gear teeth, which defines the working volume of the hydraulic machine; x \u2013 the offset of the original contour; \u03a8bm \u2013 the ratio of the width of the gear. The gear width is calculated after determining the engagement module \u23a5 \u23a6 \u23a4 \u23a2 \u23a3 \u23a1 \u2212+ = 12 cos12 22 w \u041e zm Vb \u03b1\u03c0\u03c0 , ...(20) where \u03b1w \u2013 the angle gear. The above procedure was applied for designing the continuous variable automatic transmission for the small light vehicle and determining its basic parameters (Figure 2). The method proposed for continuous variable transmission designing on the basis of differential hydro-mechanical variators consisting in a consecutive choice of gear ratios of the kinematic units in the mechanism from the conditions of the rotor variator (carrier) equilibrium, as well as the main parameters of tooth gear engagements providing the necessary displacement of the hydraulic machines for maximum torque transmission, enables to choose the main kinematic and power transmission parameters for different classes of vehicles, to evaluate the effect of these parameters on the car haulage and speed capacities at the designing stage and implement optimization of the selected parameters on the basis of operating conditions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001813_tation-pdf-url_37022-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001813_tation-pdf-url_37022-Figure12-1.png", + "caption": "Fig. 12. A schematic view of CLL loaded dipole antenna, unit cell parameters (See Fig. 5a): L1=0.67mm, L2=0.89mm, L3=1.37mm, W= 0.247mm, G=0.411mm, T1= 0.13mm, T2= 0.5mm, h1= 3.25mm, h2 =4mm, h3 =2mm, and antenna feed gap = 0.5mm, and length of dipole antenna =19mm.", + "texts": [ + " A miniaturized printed dipole loaded with left-handed transmission lines is also proposed in (Iizuka et al., 2006; Iizuka et al., 2007). However, it is known that the conventional dipole antenna only radiates an omnidirectional radiation pattern at the design frequency \u03c91. As described in the previous section, the suppression of phase reversal by incorporating PMC cover has led to the improved radiation pattern (Jafargholi et al., 2010). This section is focused on the pattern modification of the wire dipole antenna using artificial magnetic conductors. Fig. 12, shows a CLL loaded dipole antenna. The finite two-CLL-deep metamaterial Artificial Magnetic Conductor (AMC) cover was designed separately to operate at around 27GHz. The CLL dimensions were then optimized and placed optimally on both dipole arms to obtain good radiation patterns. The total number of the CLL elements is 88 (4\u00d711\u00d72) which symmetrically coupled to dipole antenna arms. The separation between the CLL elements is also fixed at 0.5mm. www.intechopen.com Applications of Artificial Magnetic Conductors in Monopole and Dipole Antennas 587 Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002084_010.5__63975-1___pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002084_010.5__63975-1___pdf-Figure3-1.png", + "caption": "FIGURE 3. (a) RELATIVE NORMAL GAP; (b) NORMAL AND TANGENTIAL CONTACT FORCES.", + "texts": [ + " 1 0, 0, (1 ) 0 R R R L L L R L y x y x y x x x y x y x x x x + \u2265 \u2265 + =\u23a7 \u23aa\u2212 \u2208 \u21d4 \u2203 \u2212 \u2265 \u2265 \u2212 =\u23a8 \u23aa = \u2212\u23a9 (8) This representation has to be used when a problem involving Sgn-multifunctions is formulated as an LCP in its standard form. In mechanics, relay functions at the velocity level are used to represent any kind of dry friction. In turn, when expressed at the displacement level, they describe the behavior of pre-stressed springs. More details on this decomposition can be found in the work by Pfeiffer and Glocker (1996). In the present work, the normal contact between rigid bodies is characterized by a set-valued force law called Signorini\u2019s condition. Figure 3 shows two convex rigid NII-Electronic Library Service Copyright (c) 2010 by JSME bodies apart from each other by a relative normal gap or distance denoted by gN. This relative normal gap is uniquely defined for convex surfaces, being perpendicular to the tangent planes at the contact points 1 and 2. The relative normal gap is non-negative due to impenetrability condition of the bodies. The two bodies in contact with each other when gN=0. In fact, one of the main features of unilateral contact is the impenetrability condition, which means that the candidate bodies for contact must not cross the boundaries of antagonist bodies", + " The classical Coulomb\u2019s friction law is another typical example that can be considered as a set-valued force law. The Coulomb law states that the sliding friction is proportional to the normal force of a contact. The magnitude of the static friction force is less than or equal to the maximum static friction force which is also proportional to the normal contact force. Furthermore, the sliding force is in opposite direction to the relative velocity of the frictional contact. Consider again the two contacting rigid bodies depicted in Fig. 3, in which Coulomb friction is present at the contact points 1 and 2. The relative velocity of point 1 with respect to point 2 along their tangent plane is denoted by \u03b3T. If contact between the two bodies takes place, i.e. gN = 0, then the friction phenomenon imposes a tangential force \u03bbT as is illustrated in Fig. 3(b). If the bodies are sliding over each other, then the friction force \u03bbT has the magnitude \u03bc\u03bbN and acts in the direction opposed to the relative tangential velocity, that is ( )T N TSgn\u03bb \u03bc\u03bb \u03b3\u2212 = 0T\u03b3 \u2260 (13) where \u03bc is the friction coefficient and \u03bbN is the normal contact force. If the relative tangential velocity vanishes, i.e. \u03b3T = 0, then the bodies purely roll over each other without slip. Pure rolling, or no-slip for locally flat objects, is denoted by stick. Thus, if the bodies stick, then the friction force must lie in the interval \u2013\u03bc\u03bbN \u2264 \u03bbT \u2264 \u03bc\u03bbN" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001563_f_eems2017_02002.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001563_f_eems2017_02002.pdf-Figure6-1.png", + "caption": "Fig. 6. Velocity profile (m/s): variant W0, variantW0_3p, variant W0_3p_ex", + "texts": [ + " Due to the difficulty to determine actual particle size, the fractional composition of the clinker meal was scaled so as to obtain the observed separation of the meal into the rotary kiln and the heat exchangers tower. This required the use of an iterative method where the particle diameter was gradually increased. The calculations were carried out, the meal distribution was analyzed until the desired chamber/kiln ratio of 35%/65% was reached. 4.2 Calculation results for gas-particle mixture flow Fig. 6 shows the velocity sections in the lengthwise midsection for the analyzed variants. Fig. 7 presents the temperature profile for proper conditions. Fig. 8 shows the velocity profile in cross-sections. Fig. 9 shows the particle concentration distribution in lengthwise section. Fig. 10 shows the temperature profile in crosssections. Fig. 11 presents the CO2 concentration distribution in crosswise sections and NOx mass distribution in crosswise sections is shown in Fig. 12. Table 2 and 3 show selected values in the outlet section of the chamber" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003418_ice_Designed_for.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003418_ice_Designed_for.pdf-Figure6-1.png", + "caption": "Figure 6. Construction design of a device for offsetting tensile forces in elevator ropes", + "texts": [ + " FORCE IN A ROPE A specific design and technical solution of the device for detecting and offsetting tensile forces in the elevator carrier ropes is illustrated in Figure 5. The described device is capable of continuously recording the time course of the instantaneous tensile forces, acting on elevator carrier ropes, when one free ends of the carrier ropes are mechanically attached to the openings of the suspension screws, which are mechanically tied to the bearing bracket, see Figure 3. Suspension screw 1, see Figure 6, is threaded through the opening in the bearing bracket 2. On the thread of the suspension screw, above the up- per level of the bearing bracket, a bowl is pushed 3 in a defined direction, into which one end of the compression coil spring is inserted 4. The bowl 5 is placed upon the other end of the cylindrical coil spring 4. The end section of the suspension screw 1 is attached with a washer 6 and the hexagonal nut 7 is screwed. This is how the suspension screw is locked against sliding out downwardly in the direction of the elevator shaft (due to the tensile force in the carrier rope) through the opening in the bearing bracket 2. The described device is a screw spindle 8, consisting of a double screw 9, single screw 10 and a cylindrical nut 11. The double screw 9 (see Figure 6) is fitted with an outer trapezoidal isosceles single thread and inner trapezoidal isosceles single thread. The single screw 10 is fitted with trapezoidal isosceles single thread on its outer cylindrical surface. The cylindrical nut\u2019s outer surface 11 is fitted with two openings, into which the pins formed in the end sections, the cylindrical rods 12 and screws with cylindrical head and inner hexagon are inserted 13. Pins at the ends of the cylindrical rod 12 and the screw 13 in this way mechanically interconnect the cylindrical nut 11 with the body of the movable mechanical tension off-setter 14", + " Cylindrical part of the single screw 10 is inserted into the flange opening 15; preventing the rotation of the flange 15 in relation to the single screw 10 is provided by a screw 16, washer 17, adaptable washer 18 and a low hexagonal nut 19. A force sensor 20 is screwed into the threaded opening on the opposite side of the flange 15. The force sensor 20 is secured against loosening with an adaptable washer 21 and a low hexagonal nut 22. The outer thread of the suspension screw 1 is screwed onto the inner thread of the hub 23; it is secured against loosening with a washer 25 and a low hexagonal nut 26. A nut 7 is screwed on the thread of the suspension screw 1 at the appropriate distance; see Figure 6, which leans against the bowl 5 over the washer 6. The outer diameter of the washer 6 is centered, in relation to the outer diameter of the body of the movable mechanical tension off-setter 14, by a centering ring 24. In actual practice, the required number of suspension screws is threaded through the created openings in the bearing bracket, which are spaced apart in the desired, as small as possible pitch. One free end of the carrier rope is fastened with rope clamps over the rope eyepiece into the opening (created in the end section of the suspension screw, see Figure 3)", + " Compression coil spring is compressed to the required force (required tensile force acting in the suspension screw axle) with a hexagonal nut. At the moment of achieving the desired axial force in one threaded rod 1, tensile force of a different size in the second suspension screw axle is exerted in a similar way. Different values of tensile forces exerted by different forces in the carrier ropes, see Figure 7, and thus by pre-tensioning of the cylindrical compression coil springs 4 are gauged by the tensile force sensors 20, see Figure 6. In order to achieve the same value of the tensional force in the carrier ropes, the double screw 9 of the individual screw spindle 8 is rotated, which leads to a compression (release) of the given compression coil spring 4. Compression or release (given by the purpose of rotation of the suspension screw 9 of the individual screw spindle 8) of the individual compression coil spring 4 are due to the design of the movable mechanical tension off-setter, namely the fixed length distance (at a given moment) between the plane of placement of the cylindrical nut 11 (the link is provided by the pins inserted into the openings created in the end sections of the cylindrical rod 12 and screws with cylindrical head and inner hexagon 13) and the upper surface of the bearing bracket 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003562_5_agriceng-2019-0036-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003562_5_agriceng-2019-0036-Figure2-1.png", + "caption": "Figure 2. Simplified view of the car body concept in version no. 1", + "texts": [ + " The car body manufactured in such a way would have a light mass and an elevated level of aesthetics of production; however, its impact resistance will depend on the selection of printing and material parameters. Based on structural assumptions and arrangements concerning functionality of the structure of the car body, four concepts of the car body model for the test car were suggested. 3D models were made in SolidWorks environment. Concept 1 The concept assumes production of the test car body based on simple raw shapes (Fig.2). A carcass of the vehicle along with all mechanisms would be located inside the car body. A front end of the car body keeps its shape at the whole width of the vehicle. Therefore, driver\u2019s legs are hidden under the car body. The \u201cengine\u201d space was covered with sheet metal which results directly from the structure of assembly of equipment. The rear part of the car body ends with a flat, reclining surface without the use of treatments that would mitigate the air stream turbulence. Concept 1 is technologically adjusted to production with all the abovementioned methods" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004695_oradea2018_02004.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004695_oradea2018_02004.pdf-Figure3-1.png", + "caption": "Fig. 3. Functioning principle of the prismatic tribometer", + "texts": [ + " Because of the multiple factors that can interfere in the friction process, the calculation equations for determining the friction coefficients are complex and difficult to resolve. For this reason, it is very important that the friction coefficients are determined through experimental methods, but with a high precision J. Williams [5]. For the experimental determination of the static friction coefficients between the chain links and guide segments, there will be used two types of tribometer, prismatic and UMT, presented in figures 1 and 2. The prismatic tribometer has a simple functioning principle, being expressed with the relation 1 and detailed in figure 3: Tg\u03b1=\u00b5 (1) \u00a9 The Authors, published by EDP Sciences. This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0/). Where \u03b1 is the tilt angle of the mobile table and \u00b5 is the sliding friction coeffiecient. The other tribometer, UMT, works by being controlled through a software installed on a computer. In order to determine the static friction coefficients, on the UMT tribometer there will be connected two modules: reciprocating and rotary" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002593_9312710_09335981.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002593_9312710_09335981.pdf-Figure9-1.png", + "caption": "FIGURE 9. Magnetic flux density distribution of an MPMA-SynRM no-load rotor (a) 10 times the magnetic air gap in the axial direction (b) no magnetic air gap in the axial direction.", + "texts": [ + " to analyse the impact of the magnetic isolation structure on the performance, this article uses an axial magnetic isolation of 10 times the air gap length between the different modules of the MPMA-SynRM motor. To minimize the edge effect, the corresponding position of the stator is also left with the same axial magnetic isolation length, as shown in Fig. 8. The MPMA-SynRMmotor with ten times the axial air gap length and without axial magnetic separation is simulated by the finite element method. Fig. 9 shows the distribution of the rotor flux density under a static magnetic field simulation, VOLUME 9, 2021 19951 in which Fig. 9 (a) shows the rotor flux density distribution with a 10g magnetic separation length in the axial direction. and Fig. 9 (b) shows the distribution of the rotor flux density without axial magnetic separation. The rotor flux density distribution of MPMA-SynRM has nothing to do with whether the axial direction is set under the no-load state. The rotor flux density decreases obviously at the rotor centre axis position. According to the magnetic density colour distribution, there is an obvious angle between the d-axis of different rotor modules. Fig. 10 shows the air gap flux density distribution of the static magnetic field rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002886_nal_Thesis_Suren.pdf-Figure4.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002886_nal_Thesis_Suren.pdf-Figure4.1-1.png", + "caption": "Figure 4.1: Miniature tensile test specimen design (all dimensions are in mm) a) Tensile test specimen design (thickness = 1 mm) b) Specimen loading and its fixture assembly.", + "texts": [ + " As the tests were repeated, each test requiring OM and SEM studies in between the tests, the whole test specimen should fit inside the SEM chamber and the sample table. Thus, miniature specimen designs were adopted for all the damage mechanisms studies in this work as explained in following sections. Nanyang Technological University Singapore Ch. 4. Tensile and Fatigue Damage Mechanisms in SGI 4.1. Test Specimens and Methods Page : 103 A miniature pin loaded tensile test specimen was designed considering ASTM E8 for tensile test [157] as shown in Figure 4.1 a). The pin-loaded design was chosen as it was easier to align the specimen and avoid biaxial stresses in the test specimen. The specimen loaded in the machine together with the additional clamping fixtures are shown in Figure 4.1 b). The specimen was first loaded with the pin, and a small load was applied to self-align the specimen before it was clamped by the plates. The clamping fixture presents stress concentration at the pin to ensured failure at the narrow gauge section. The specimens were metallographically ground and polished before the test to enable efficient observation of the specimen microstructure without additional preparation. However, the specimens were not etched as the etched phase boundaries and grain boundaries will make crack detection difficult" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002658_2452-020-03846-0.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002658_2452-020-03846-0.pdf-Figure13-1.png", + "caption": "Fig. 13 Stability analysis with thin shell finite element model with the modified configuration", + "texts": [ + " 1 Spring stiffness values used for linear joints between panels Spring direction Axial In-plane shear Out-of-plane shear Out-ofplane bending Unit per breadth kN/m kN/m kN/m kNm/rad Integrated hinge 6.5 \u00d7 106 2.5 \u00d7 106 2.5 \u00d7 106 5.4 \u00d7 10\u20133 Watoji joint 6.5 \u00d7 104 2.5 \u00d7 104 2.5 \u00d7 104 5.4 \u00d7 10\u20134 Vol:.(1234567890) range for the angle to include the steeper fold and increasing the importance weighting of the objective function for structural stiffness. The resulting shape has a smaller angle as seen in Fig.\u00a013a). The linear joint stiffness for \u201cwatoji\u201d lacing was introduced as defined in Table\u00a01. The overall height was reduced from 3.0\u00a0m to 2.85\u00a0m by uniformly scaling the model, which was also deemed more appropriate in consideration of reducing the package size for transportation. The lowest eigenvalue buckling factor was significantly increased from the initial model to 1.08, the buckling mode of which is shown in Fig.\u00a013b). However, the incremental loading analysis indicated that geometric nonlinearity still caused instability with a limit load factor of 0.49, which is about half of its self-weight. Figure\u00a013c) shows the deformation under the limit loading. It was observed that the end bottom panels still buckle, but the propagation was localized only to the outer strips. In order to mitigate instability and prevent such progressive deformation, web stiffener elements were introduced between valleys on the exterior side of the canopy at three levels as shown in Fig.\u00a014a. Other configurations remain the same with the model described in the Sect.\u00a05.2.2. The analysis shows that they stabilized the structure significantly, such that local buckling of the end bottom panels was prevented, and the lowest eigenvalue factor increased to 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure10-1.png", + "caption": "Figure 10. (a) Shape of target RFPM motor fill factor area. (b) AFPM motor fill factor area.", + "texts": [ + " The motor\u2019s back electromotive force (BEMF) and total harmonic distortion (THD) can be identified through a no-load analysis. As the THD decreases, the vibration noise of the motor decreases. The no-load analysis is based on 1000 rpm. Figure 9 shows the BEMF waveform of the target RFPM motor. The THD of the target RFPM motor obtained from Figure 9 is 5.51%. The smaller the THD, the more sinusoidal the waveform is. As the waveform is sinusoidal, the heat, vibration, and core loss of the motor are reduced and performance is improved. Figure 10a,b shows the shape of the target RFPM motor and the shape of the AFPM motor. The slot area is the area for obtaining the fill factor. The slot areas of the two motors are the same. In the same way as the RFPM motor, no-load analysis was performed based on 1000 rpm. Figure 11 shows the BEMF waveform of the AFPM motor. The voltage is 4.21 Vrms and 6.16% for THD. The DRAFPM motor has rotors on both sides so that the stator back-yoke can be removed. The advantage is that removing the Stator back-yoke can reduce the size of the motor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003647_f_version_1577096875-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003647_f_version_1577096875-Figure8-1.png", + "caption": "Figure 8. Section view of the little finger, with the distal/intermediate phalanx in blue, the proximal phalanx in orange and the knuckle in green, showing the joint angle encoders and magnets used to determine the joint rotational angles.", + "texts": [ + " As the Hall effect sensor outputs the magnetic field strength in x, y and z direction, these values can be used to derive the rotation angle of each joint. To calculate the rotation angle \u03b1z around the z axis, the following equation is used, where xMag and yMag are the magnetic field strengths in x and y direction, respectively: \u03b1z = arctan 2(yMag, xMag) \u00b7 180\u25e6 \u03c0 (1) In this work, however, we perform this measurement off-axis both for the magnet and the sensor (MLX90393, Melexis), due to space constraints in the joints, which is shown in Figure 8. The magnets are glued into the distal/intermediate phalanx (blue) and the knuckle (green), and rotate around their respective joints when these are rotated. At 45 degrees rotation the magnets are positioned directly above the sensors, so that they have the same distance between each other at 0 and 90 degrees, which corresponds to the minimum and maximum angle, respectively, of all joints. The above stated Equation (1) can nevertheless be used to provide an approximation of the joint rotation angle using this off-axis measurement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004400_e_download_7768_6705-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004400_e_download_7768_6705-Figure5-1.png", + "caption": "Fig 5. Design parameters of the helicopter rotor blade", + "texts": [ + " Thermal strain analogy between piezoelectric strains and thermally induced strains is used to model piezoelectric effects, when piezoelectric coefficients characterizing an actuator are introduced as thermal expansion coefficients determined by the following relationship: , ES ij ij d \u0394 =\u03b1 where dij is the effective piezoelectric constant and \u2206ES is the electrode spacing (Fig 3) taken as \u2206ES = 0.5 mm. Then steady-state thermal analysis is carried out to determine a torsion angle of the rotor blade (Fig 4), static torsion analysis \u2013 to determine the location of the elastic axis and modal analysis \u2013 to determine the first torsion eigenfrequency of the rotor blade. Before formulation of optimisation problem, the parametric study has been carried out with the purpose to decrease the number of design parameters (Fig 5) and by this way to increase the accuracy of obtained optimal results. In this connection the influence of possible design parameters \u2013 spar \u201cmoustaches\u201d thickness and length, spar circular fitting, skin thickness, MFC chordwise length, web thickness and length, web and spar \u201cmoustaches\u201d thickness together and voltage, on the behaviour functions - torsion angle, location of centre of gravity and elastic axis, mass of cross-section, strains and first torsion eigenfrequency (Fig 6\u201310) were considered" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001327_id_0354-46051002225Z-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001327_id_0354-46051002225Z-Figure1-1.png", + "caption": "Fig. 1 Diagrams of interpolation functions and physical meaning of the elements of the rigidity matrix of the member with semi-rigid joints", + "texts": [ + "MEMBERS WITH SEMI-RIGID JOINTS IN NODES The relation of the displacement of the arbitrary point of the member axis and displacement parameters at the ends of the member, in the case of straight member stressed on bending in the plane, can most simply be obtained starting from the homogenous differential equation of bending: 4 4 d ( )EI 0 d v x , x = (1) Whose solution can be presented in the form of a polynomial of the third order: 2 3 1 2 3 4( )v x x x x .\u03b1 \u03b1 \u03b1 \u03b1= + + + (2) The function v(x) at unit generalized displacement qm=1 (m=1,2,3,4), whereby all other generalized displacements are qn=0, n\u2260m, is known as the interpolation function. When the node i of the member that is semi-rigid on both ends is imparted a unit translational movement q1 = 1, while all other generalized displacement are equal to zero, according to the Fig. 1(a) it can be written as: 1 1(1 ) (1 )* *ik ik ik ik ik ki ki ki ki ik ik ki b b , , a l a l \u23a1 \u23a4 \u23a1 \u23a4 \u03b1 = \u03bc \u2212 \u2212 \u03bc \u03bc \u03b1 = \u03bc \u2212 \u2212 \u03bc \u03bc\u23a2 \u23a5 \u23a2 \u23a5 \u23a3 \u23a6 \u23a3 \u23a6 (3) where ik , ki,\u03bc \u03bc are degrees of rigidity of joints at the ends of the member, and which can be determined experimentally or through calculation as * * ik ik i ki ki k/ , / ,\u03bc = \u03d5 \u03d5 \u03bc = \u03d5 \u03d5 a i k,\u03d5 \u03d5 are angles of rotation of the nodes, while * * ik ki,\u03d5 \u03d5 are the angles of rotation of cross-sections at the ends of the members. Interpolation functions for the member with semi-rigid joints at the ends i and k, are determined starting from the function v(x) and the corresponding boundary conditions at the ends of the member in the cases qm=1 (m=1,2,3,4), as displayed in [4], have the following forms: 2 3 1 2 2 3 2 2 2 3 3 2 2 3 4 2 21( ) 1 ( ) 2 ( ) 21( ) ( ) 2 2 ( ) ( ) ik ki ik ki ik ik ki ki ik ki ki ik ik ki ik ki ik ik ki ki ik ki ki ik ik N x x x x l l l l l N x x x x l l N x x x x l l l l l N x l x x x l l \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u03b1 + \u03b1 \u03b1 + \u03b1 = \u2212 \u2212 \u03b1 \u2212 + \u03bc \u2212 \u03bc + \u03b1 \u03bc \u2212 \u03bc + \u03b1 = \u03bc \u2212 + \u03b1 + \u03b1 \u03b1 + \u03b1 = \u2212 \u03b1 + \u2212 \u03bc + \u03bc \u2212 \u03b1 \u03bc + \u03bc \u2212 \u03b1 = \u03bc \u2212 \u03b1 \u2212 + (4) The interpolation function N* m(x), the so called, function of form, represents the elastic line of a semi-rigidly fixed member at both ends, due to the generalized displacement qm=1, m = 1, 2, 3, 4, while all other generalized displacements are qn=0, n \u2260 m. Interpolation functions given by the terms (4) represent the Hermite's polynomials of the first order, and their diagrams are displayed in the Fig. 1. In the boundary cases, when the member is rigidly fixed at the ends i and k ( 1ik ki\u03bc = \u03bc = ) or when it is rigid at one end and with the joint on the other ( 1 0ik ki,\u03bc = \u03bc = ) the terms (4) assume their well known values [3]. The rigidity matrix of a member with semi-rigid joints, exposed to bending in the plane has the following form: 11 12 13 14 22 23 24 33 34 44 k k k k k k k . k k sim k \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u23a1 \u23a4 \u23a2 \u23a5 \u23a2 \u23a5 = \u23a2 \u23a5 \u23a2 \u23a5 \u23a2 \u23a5 \u23a2 \u23a5\u23a3 \u23a6 k (5) The elements of this matrix are determined with the aid of derivations of other interpolation functions, such as defined by the term (6), and they are in the function of the joints rigidity degree: 1 2 1 2 3 4 30 4 ( ) ( ) EI ( ) ( ) ( ) ( ) d ( ) ( ) l N x N x N x N x N x N x x, N x N x \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2217 \u2033\u23a7 \u23ab \u23aa \u23aa \u2033\u23aa \u23aa\u23aa \u23aa \u2033 \u2033 \u2033 \u2033\u23a1 \u23a4= \u23a8 \u23ac \u23a2 \u23a5\u23a3 \u23a6\u2033\u23aa \u23aa \u23aa \u23aa\u2033\u23aa \u23aa\u23a9 \u23ad \u222bk (6) Such as, for example: 2 2 11 2 12 2 2 13 11 4EI 2EI 2( ) 4EI ik ik ki ki ik ik ki ki ki ik ki ik ki ki ik ik ik ki ki k , k , k k ", + " In the case when the beam is elevated from the foundations, the model can be easily adapted by assuming the values of k1 and k2 are zero. By comparison of experimental and analytically obtained results, Bowles proposes that for the end springs, twice as high values are adopted for k1 and k2. In the Fig. 2(b) the model of the beam on the elastic foundations with springs continuously arranged along the length of the member. The starting point for determination of the rigidity matrix on the elastic foundations according to [3] are functions of form (4), Fig. 1. If v(x) is presented in the usual way with the products of interpolation functions and parameters of displacement (q) the term (10) becomes: ( )rp x c N q.= (14) On the basis of the virtual displacement principle, the continuously distributed transversal load along the axis of the member pr(x) is equivalent to the load on the ends of the member Rm, m=1, 2, 3, 4, which, taking into consideration (14) can be presented in the form: 0 0 d dT T rR N p x c N N q x C q,= = =\u222b \u222b l l (15) Where: 0 dTC c N N x,= \u222b l (16) Is the rigidity matrix of the elastic foundations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004367_5_phys-2022-0223_pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004367_5_phys-2022-0223_pdf-Figure6-1.png", + "caption": "Figure 6: (a) Magnet skew structure motor. (b) Original structure motor.", + "texts": [ + " Subsequently, as the skew angle of the magnet increases, the peak-to-peak value of the cogging torque increases gradually. This result shows that formula (7) is suitable for the calculation of the magnet skew angle in the trapezoidal magnetic pole structure. This magnetic pole structure can be used to optimize the cogging torque of permanent magnet motors. Contrast trapezoidal magnetic pole structure with magnet skew structure and original structure (traditional fourpole structure) motors. As shown in Figure 6, (a) is the schematic diagram of the magnet skew structure motor when the magnet skew angle is 30\u00b0. (b) is the original structure motor. The comparison between the cogging torque and the output torque of the three types of magnetic pole structure motors is shown in Figure 7 below. It can be seen from Figure 7(a) that the motor with trapezoidal magnetic pole structure can effectively reduce the cogging torque. It can be seen from Figure 7(b) that the torque ripple is significantly reduced, and the output torque is slightly decreased" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003966__130_1_130_1_84__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003966__130_1_130_1_84__pdf-Figure2-1.png", + "caption": "Fig. 2. Diagram of in near-field", + "texts": [ + " Therefore, this study focuses on defining the exact frequency and efficiency required for electromagnetic coupling on the basis of the antenna theory, circuit theory, experimental observations, and electromagnetic computations. In particular, the structure of equivalence circuits is described in detail. Fig. 1 shows magnetic and helical antennas, which are loop antennas used to generate a strong magnetic field. One antenna is made the transmitting antenna, and the other is made the receiving Fig. 3. Equivalent circuit with two magnetically coupled antennas antenna. Fig. 2 shows the magnetic field at two different resonant frequencies. At the resonant frequency, amplitudes of current are the same in the transmitting antenna and receiving antenna for each resonance. However, the current phase is different at two different frequencies. The equivalent circuit of this magnetic antenna is shown in Fig. 3. Thus, this figure provides information on the efficiency of power transfer. Similarly, electric antennas are shown in Fig. 4, Fig. 5 and Fig. 6. In this paper, we clarify why the efficiency at the two resonant frequencies is high and propose a method for deriving an equivalent circuit to be used in electromagnetic computations and experiments", + " \u306f\u3058\u3081\u306b \u8fd1\u5e74\uff0c\u30ef\u30a4\u30e4\u30ec\u30b9\u96fb\u529b\u4f1d\u9001\u306e\u6ce8\u76ee\u304c\u96c6\u307e\u3063\u3066\u3044\u308b\u3002\u30ef\u30a4 \u30e4\u30ec\u30b9\u3067\u96fb\u529b\u4f1d\u9001\u304c\u51fa\u6765\u308c\u3070\uff0c\u5c0f\u578b\u306e\u7269\u3067\u306f\u643a\u5e2f\u96fb\u8a71\u3084\u30ce\u30fc \u30c8 PC\uff0c\u5927\u578b\u306e\u3082\u306e\u3067\u306f\u96fb\u52d5\u81ea\u8ee2\u8eca\u3084\u96fb\u6c17\u81ea\u52d5\u8eca\u306a\u3069\u306e\u96fb\u6c60 \u3092\u5185\u8535\u3057\u305f\u6a5f\u5668\u3084\uff0c\u4e57\u308a\u7269\u3078\u624b\u8efd\u306b\u5145\u96fb\u3059\u308b\u3053\u3068\u304c\u51fa\u6765\u308b\u3002 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3\u306b\u793a\u3059\u3002 \u30d8\u30ea\u30ab\u30eb\u30a2\u30f3\u30c6\u30ca\u306e\u7279\u6027\u3092\u30e2\u30fc\u30e1\u30f3\u30c8\u6cd5\u306b\u3088\u308b\u96fb\u78c1\u754c\u89e3\u6790 \u3067\u793a\u3059\u3002\u53cd\u5c04\u4fc2\u6570 S 11\uff0c\u900f\u904e\u4fc2\u6570 S 21 \u306b\u5bfe\u3057\uff0c\u53cd\u5c04\u96fb\u529b\u306e \u52b9\u7387\u3092 \u03b711\uff0c\u900f\u904e\u96fb\u529b\u306e\u52b9\u7387\u3092 \u03b721 \u3068\u3059\u308b\u3068\uff0c(1)\uff0c(2)\u5f0f\u306e \u3088\u3046\u306b\u793a\u305b\u308b\u3002 \u03b711 = |S 11|2 \u00d7 100 [%] \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (1) \u03b721 = |S 21|2 \u00d7 100 [%] \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (2) \u30a2\u30f3\u30c6\u30ca\u304c 1\u7d20\u5b50\u306e\u5834\u5408\u3068\u9001\u53d7\u4fe1\u30a2\u30f3\u30c6\u30ca\u306e\u8a08 2\u7d20\u5b50\u306e \u5834\u5408\u306b\u304a\u3051\u308b\uff0c\u5468\u6ce2\u6570\u306b\u5bfe\u3059\u308b \u03b711\uff0c\u03b721 \u3092 Fig. 4\u306b\u793a\u3059\u3002 1\u7d20\u5b50\u306e\u5834\u5408\u306f\u3069\u306e\u5468\u6ce2\u6570\u3067\u3082\u307b\u307c\u5168\u53cd\u5c04\u3092\u8d77\u3053\u3057\u3066\u304a\u308a\uff0c \u96fb\u6e90\u5074\u306b\u96fb\u529b\u304c\u623b\u3063\u3066\u3044\u308b\u3002\u5171\u632f\u5468\u6ce2\u6570\u306e\u6642\u306b\u95a2\u3057\u3066\u306f\u50c5 \u304b\u306b\u640d\u5931\u304c\u767a\u751f\u3057\u3066\u3044\u308b\u3002\u672c\u7a3f\u3067\u63d0\u6848\u3059\u308b\u30a2\u30f3\u30c6\u30ca\u5f62\u72b6\u306f \u6ce2\u9577\u306b\u5bfe\u3057\u975e\u5e38\u306b\u5c0f\u3055\u3044\u3002\u305d\u306e\u305f\u3081\uff0c\u5171\u632f\u72b6\u614b\u306b\u304a\u3044\u3066\u3082 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\u30ae\u30e3\u30c3\u30d7\u3092\u5909\u5316\u3055\u305b\u305f\u6642\u306e\u5468\u6ce2\u6570 \u306b\u5bfe\u3059\u308b \u03b711\uff0c\u03b721 \u3092 Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003069_df_ru_2024_02_07.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003069_df_ru_2024_02_07.pdf-Figure3-1.png", + "caption": "Figure 3 \u2014 Finite-volume grid of the flow area:", + "texts": [], + "surrounding_texts": [ + "\u0441\u0442\u0432\u0435\u043d\u043d\u043e\u0435 \u0432\u043b\u0438\u044f\u043d\u0438\u0435 \u043d\u0430 \u0432\u043e\u0437\u0434\u0443\u0448\u043d\u044b\u0439 \u043f\u043e\u0442\u043e\u043a, \u0432\u044b\u0445\u043e\u0434\u044f\u0449\u0438\u0439 \u0438\u0437 \u0432\u0435\u043d\u0442\u0438\u043b\u044f\u0442\u043e\u0440\u0430, \u0441\u043b\u0435\u0434\u043e\u0432\u0430\u0442\u0435\u043b\u044c\u043d\u043e, \u0432\u043e\u0437\u0434\u0443\u0448\u043d\u043e-\u0440\u0435\u0448\u0435\u0442\u043d\u0443\u044e 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\u043f\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u043e 2D-\u0441\u0435\u0447\u0435\u043d\u0438\u0435 \u043f\u0440\u043e\u0442\u043e\u0447\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 (\u0441\u043c. \u0440\u0438\u0441\u0443\u043d\u043e\u043a 1), \u043d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u043a\u043e\u0442\u043e\u0440\u043e\u0433\u043e \u0441\u0444\u043e\u0440\u043c\u0438\u0440\u043e\u0432\u0430\u043d\u0430 \u043a\u043e\u043d\u0435\u0447\u043d\u043e-\u043e\u0431\u044a\u0435\u043c\u043d\u0430\u044f \u0441\u0435\u0442\u043a\u0430 (\u0440\u0438\u0441\u0443\u043d\u043e\u043a 3).\n\u0414\u043b\u044f \u043f\u043e\u043b\u0443\u0447\u0435\u043d\u0438\u044f \u0431\u043e\u043b\u0435\u0435 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435\u043d\u043d\u043e\u0439 \u043a\u0430\u0440\u0442\u0438\u043d\u044b \u0442\u0435\u0447\u0435\u043d\u0438\u044f \u0432\u0431\u043b\u0438\u0437\u0438 \u0441\u0442\u0435\u043d\u043e\u043a \u044d\u043b\u0435\u043c\u0435\u043d\u0442\u043e\u0432 \u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0430\u0441\u044c \u0441\u0442\u0440\u0443\u043a\u0442\u0443\u0440\u0438\u0440\u043e\u0432\u0430\u043d\u043d\u0430\u044f \u043f\u0440\u0438\u0437\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0430\u044f \u0441\u0435\u0442\u043a\u0430, \u043f\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u043d\u0430\u044f \u0441 \u043f\u043e\u043c\u043e\u0449\u044c\u044e \u0444\u0443\u043d\u043a\u0446\u0438\u0438 Inflation [6, 7].\n\u041d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u043f\u043e\u043b\u0435\u0439 \u0442\u0435\u0447\u0435\u043d\u0438\u044f, \u043f\u0440\u0435\u0434\u0432\u0430\u0440\u0438\u0442\u0435\u043b\u044c\u043d\u043e \u043f\u043e\u043b\u0443\u0447\u0435\u043d\u043d\u044b\u0445 \u043d\u0430 \u0431\u043e\u043b\u0435\u0435 \u0433\u0440\u0443\u0431\u043e\u0439 \u0441\u0435\u0442\u043a\u0435, \u0431\u044b\u043b\u0430 \u0432\u044b\u043f\u043e\u043b\u043d\u0435\u043d\u0430 \u0435\u0435 \u043b\u043e\u043a\u0430\u043b\u044c\u043d\u0430\u044f \u0430\u0434\u0430\u043f\u0442\u0430\u0446\u0438\u044f, \u0432 \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0435 \u043a\u043e\u0442\u043e\u0440\u043e\u0439 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u0435 \u0431\u0435\u0437\u0440\u0430\u0437\u043c\u0435\u0440\u043d\u043e\u0439 \u043f\u0435\u0440\u0435\u043c\u0435\u043d\u043d\u043e\u0439 y+, \u043e\u043f\u0438\u0441\u044b\u0432\u0430\u044e\u0449\u0435\u0439 \u043f\u0440\u043e\u0444\u0438\u043b\u044c \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0438 \u043f\u0440\u0438\u0441\u0442\u0435\u043d\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438, \u043d\u0435 \u043f\u0440\u0435\u0432\u044b\u0448\u0430\u0435\u0442 10, \u0447\u0442\u043e \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0443\u0435\u0442 \u0440\u0435\u043a\u043e\u043c\u0435\u043d\u0434\u043e\u0432\u0430\u043d\u043d\u043e\u0439 \u0432\u0435\u043b\u0438\u0447\u0438\u043d\u0435 [6]. \u041f\u0440\u0438\u0437\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0438\u0439 \u0441\u043b\u043e\u0439 \u043f\u0440\u0438\u0441\u0442\u0435\u043d\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u0441\u043e\u0434\u0435\u0440\u0436\u0438\u0442 10\u202615 \u044f\u0447\u0435\u0435\u043a \u0432 \u043d\u043e\u0440\u043c\u0430\u043b\u044c\u043d\u043e\u043c \u043d\u0430\u043f\u0440\u0430\u0432\u043b\u0435\u043d\u0438\u0438 \u043a \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044e \u043f\u043e\u0442\u043e\u043a\u0430. \u041a\u043e\u044d\u0444\u0444\u0438\u0446\u0438\u0435\u043d\u0442 \u0440\u043e\u0441\u0442\u0430 (Expansion Factor) \u0440\u0430\u0437\u043c\u0435\u0440\u043e\u0432 \u044f\u0447\u0435\u0435\u043a \u0441\u0435\u0442\u043a\u0438 \u0441\u043e\u0441\u0442\u0430\u0432\u0438\u043b 1,2. \u041f\u043e \u0438\u0442\u043e\u0433\u0443 \u043f\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u043d\u0430\u044f \u0441\u0435\u0442\u043a\u0430 \u0438\u043c\u0435\u0435\u0442 \u0441\u043b\u0435\u0434\u0443\u044e\u0449\u0438\u0435 \u043f\u043e\u043a\u0430\u0437\u0430\u0442\u0435\u043b\u0438 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0430: \u043e\u0440\u0442\u043e\u0433\u043e\u043d\u0430\u043b\u044c\u043d\u043e\u0441\u0442\u044c (Mesh Orthogonality) \u2014 \u043d\u0435 \u043c\u0435\u043d\u0435\u0435 0,7; \u043a\u043e\u044d\u0444\u0444\u0438\u0446\u0438\u0435\u043d\u0442 \u043f\u0440\u043e\u043f\u043e\u0440\u0446\u0438\u043e\u043d\u0430\u043b\u044c\u043d\u043e\u0441\u0442\u0438 (Aspect Ratio) \u2014 \u043d\u0435 \u0431\u043e\u043b\u0435\u0435 50.\n\u0412 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u0440\u0430\u0431\u043e\u0447\u0435\u0433\u043e \u0442\u0435\u043b\u0430 \u043f\u0440\u0438\u043c\u0435\u043d\u0435\u043d\u0430 \u043c\u043e\u0434\u0435\u043b\u044c \u0432\u043e\u0437\u0434\u0443\u0445\u0430 (air) \u0441 \u043f\u043b\u043e\u0442\u043d\u043e\u0441\u0442\u044c\u044e 1,225 \u043a\u0433/\u043c3 \u0438 \u0432\u044f\u0437\u043a\u043e\u0441\u0442\u044c\u044e 1,7894\u00b710\u20135 \u043a\u0433/(\u043c\u00b7\u0441) \u043f\u0440\u0438 \u0442\u0435\u043c\u043f\u0435\u0440\u0430\u0442\u0443\u0440\u0435 20 \u00b0C.\n\u041d\u0430 \u0433\u0440\u0430\u043d\u0438\u0446\u0435 \u0432\u0445\u043e\u0434\u0430 \u0438 \u0432\u044b\u0445\u043e\u0434\u0430 \u0438\u0437 \u0440\u0430\u0441\u0447\u0435\u0442\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u043e\u043f\u0438\u0441\u0430\u043d\u044b \u0433\u0440\u0430\u043d\u0438\u0447\u043d\u044b\u0435 \u0443\u0441\u043b\u043e\u0432\u0438\u044f pressure-inlet \u0438 pressure-outlet \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0435\u043d\u043d\u043e \u0441 \u043e\u0442\u043d\u043e\u0441\u0438\u0442\u0435\u043b\u044c\u043d\u044b\u043c \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u0435\u043c p = 0 \u041f\u0430 (\u0430\u0442\u043c\u043e\u0441\u0444\u0435\u0440\u043d\u043e\u0435 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u0435 101 325 \u041f\u0430).\n\u0412 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u043c\u043e\u0434\u0435\u043b\u0438 \u0442\u0443\u0440\u0431\u0443\u043b\u0435\u043d\u0442\u043d\u043e\u0433\u043e \u0442\u0435\u0447\u0435\u043d\u0438\u044f \u0432\u044b\u0431\u0440\u0430\u043d\u0430 SST k-\u03c9-\u043c\u043e\u0434\u0435\u043b\u044c \u0441 \u0434\u0432\u0443\u043c\u044f \u0434\u0438\u0444\u0444\u0435\u0440\u0435\u043d\u0446\u0438\u0430\u043b\u044c\u043d\u044b\u043c\u0438 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044f\u043c\u0438, \u043f\u0440\u0435\u0434\u0441\u0442\u0430\u0432\u043b\u044f\u044e\u0449\u0430\u044f \u0441\u043e\u0431\u043e\u0439 \u043a\u043e\u043c\u0431\u0438\u043d\u0430\u0446\u0438\u044e k-\u03b5- \u0438 k-\u03c9-\u043c\u043e\u0434\u0435\u043b\u0435\u0439 \u0442\u0443\u0440\u0431\u0443\u043b\u0435\u043d\u0442\u043d\u043e\u0441\u0442\u0438: \u0434\u043b\u044f \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0442\u0435\u0447\u0435\u043d\u0438\u044f \u0432 \u0441\u0432\u043e\u0431\u043e\u0434\u043d\u043e\u043c \u043f\u043e\u0442\u043e\u043a\u0435 \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u0443\u044e\u0442\u0441\u044f \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044f k-\u03b5-\u043c\u043e\u0434\u0435\u043b\u0438, \u0430 \u0432 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u0432\u0431\u043b\u0438\u0437\u0438 \u0441\u0442\u0435\u043d\u043e\u043a \u2014 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044f k-\u03c9-\u043c\u043e\u0434\u0435\u043b\u0438. \u042d\u0442\u0430 \u043c\u043e\u0434\u0435\u043b\u044c \u0434\u043e\u0432\u043e\u043b\u044c\u043d\u043e \u0441\u0442\u0430\u0431\u0438\u043b\u044c\u043d\u0430, \u043f\u043e\u0434\u0445\u043e\u0434\u0438\u0442 \u0434\u043b\u044f \u0440\u0435\u0448\u0435\u043d\u0438\u044f \u0440\u0435\u0430\u043b\u044c\u043d\u044b\u0445 \u0438\u043d\u0436\u0435\u043d\u0435\u0440\u043d\u044b\u0445 \u0437\u0430\u0434\u0430\u0447 \u0438 \u0432\u043e \u043c\u043d\u043e\u0433\u0438\u0445 \u0441\u043b\u0443\u0447\u0430\u044f\u0445 \u043f\u0440\u0435\u0434\u043b\u0430\u0433\u0430\u0435\u0442 \u0445\u043e\u0440\u043e\u0448\u0438\u0439 \u043a\u043e\u043c\u043f\u0440\u043e\u043c\u0438\u0441\u0441 \u0441 \u0442\u043e\u0447\u043a\u0438 \u0437\u0440\u0435\u043d\u0438\u044f \u0442\u043e\u0447\u043d\u043e\u0441\u0442\u0438 [8].\n\u0422\u0430\u043a \u043a\u0430\u043a \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e\u0442\u043e\u043a\u0430 \u0432\u043e\u0437\u0434\u0443\u0445\u0430 \u0432 \u0441\u0438\u0441\u0442\u0435\u043c\u0435 \u0433\u043e\u0440\u0430\u0437\u0434\u043e \u043d\u0438\u0436\u0435 \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0438 \u0437\u0432\u0443\u043a\u0430, \u043f\u0440\u0438 \u0442\u0430\u043a\u0438\u0445 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u044f\u0445 \u0441\u0436\u0438\u043c\u0430\u0435\u043c\u043e\u0441\u0442\u044c \u0441\u0440\u0435\u0434\u044b \u043d\u0435\u0437\u043d\u0430\u0447\u0438\u0442\u0435\u043b\u044c\u043d\u0430 \u0438 \u0435\u0439 \u043c\u043e\u0436\u043d\u043e \u043f\u0440\u0435\u043d\u0435\u0431\u0440\u0435\u0447\u044c [9, 10]. \u0412 \u0441\u0432\u044f\u0437\u0438 \u0441 \u044d\u0442\u0438\u043c \u0434\u043b\u044f \u0440\u0435\u0448\u0435\u043d\u0438\u044f \u0441\u0438\u0441\u0442\u0435\u043c\u044b \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0439, \u043e\u043f\u0438\u0441\u044b\u0432\u0430\u044e\u0449\u0438\u0445 \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044f \u0441\u0440\u0435\u0434\u044b, \u0431\u044b\u043b \u043f\u0440\u0438\u043c\u0435\u043d\u0435\u043d \u0440\u0435\u0448\u0430\u0442\u0435\u043b\u044c \u043d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f Pressure-Based [11].\n\u0412 \u0432\u043e\u0437\u0434\u0443\u0448\u043d\u043e\u043c \u043f\u043e\u0442\u043e\u043a\u0435 \u0440\u0430\u0441\u0441\u043c\u0430\u0442\u0440\u0438\u0432\u0430\u0435\u043c\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u0438\u0437\u043c\u0435\u0440\u0435\u043d\u0438\u0439 \u0438\u043c\u0435\u0435\u0442 \u043c\u0435\u0441\u0442\u043e \u043f\u0440\u043e\u0442\u0435\u043a\u0430\u043d\u0438\u0435 \u0432\u0438\u0445\u0440\u0435\u0432\u044b\u0445 \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u043e\u0432, \u0438 \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432 \u0438\u0437\u043c\u0435\u043d\u0435\u043d\u0438\u0435 \u0432\u0435\u043b\u0438\u0447\u0438\u043d \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0435\u0439 \u043f\u043e\u0442\u043e\u043a\u0430 \u0432 \u043a\u043e\u043d\u0442\u0440\u043e\u043b\u044c\u043d\u044b\u0445 \u0442\u043e\u0447\u043a\u0430\u0445 \u0434\u043e\u0441\u0442\u0438\u0433\u0430\u0435\u0442 30 %, \u043f\u043e\u044d\u0442\u043e\u043c\u0443 \u043f\u043e\u0441\u0442\u0430\u043d\u043e\u0432\u043a\u0430 \u0437\u0430\u0434\u0430\u0447\u0438 \u0442\u0440\u0435\u0431\u0443\u0435\u0442 \u043d\u0435\u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0433\u043e \u0440\u0435\u0448\u0435\u043d\u0438\u044f. \u0414\u043b\u044f \u0440\u0435\u0448\u0430\u0442\u0435\u043b\u044f \u0431\u044b\u043b\u0430 \u0432\u044b\u0431\u0440\u0430\u043d\u0430 \u0444\u043e\u0440\u043c\u0443\u043b\u0438\u0440\u043e\u0432\u043a\u0430 \u0441 \u0432\u0440\u0435\u043c\u0435\u043d\u043d\u043e\u0439 \u0430\u043f\u043f\u0440\u043e\u043a\u0441\u0438\u043c\u0430\u0446\u0438\u0435\u0439 Transient Formulation, \u0430 \u0434\u043b\u044f \u043e\u043f\u0438\u0441\u0430\u043d\u0438\u044f \u0432\u0437\u0430\u0438\u043c\u043e\u0434\u0435\u0439\u0441\u0442\u0432\u0438\u044f \u043c\u0435\u0436\u0434\u0443 \u043f\u043e\u0434\u0432\u0438\u0436\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u044c\u044e \u0432\u0435\u043d\u0442\u0438\u043b\u044f\u0442\u043e\u0440\u0430 \u0438 \u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u044c\u044e \u0441\u0438\u0441\u0442\u0435\u043c\u044b \u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043d\u0430 \u043c\u043e\u0434\u0435\u043b\u044c \u0441\u043a\u043e\u043b\u044c\u0437\u044f\u0449\u0435\u0439 \u0441\u0435\u0442\u043a\u0438 Sliding Mesh Model.\n\u0420\u0430\u0437\u043c\u0435\u0440 \u0448\u0430\u0433\u0430 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u043f\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u0438 \u0394t \u043f\u0440\u0438 \u043d\u0430\u043b\u0438\u0447\u0438\u0438 \u0441\u043a\u043e\u043b\u044c\u0437\u044f\u0449\u0435\u0439 \u0441\u0435\u0442\u043a\u0438 \u0431\u044b\u043b \u0432\u044b\u0447\u0438\u0441\u043b\u0435\u043d \u0441\u043e\u0433\u043b\u0430\u0441\u043d\u043e \u0440\u0435\u043a\u043e\u043c\u0435\u043d\u0434\u0430\u0446\u0438\u044f\u043c [12]:\n\u0433\u0434\u0435 \u0394s \u2014 \u0440\u0430\u0437\u043c\u0435\u0440 \u044d\u043b\u0435\u043c\u0435\u043d\u0442\u0430 \u0441\u0435\u0442\u043a\u0438 \u0432 \u0441\u043a\u043e\u043b\u044c\u0437\u044f\u0449\u0435\u043c \u0438\u043d\u0442\u0435\u0440\u0444\u0435\u0439\u0441\u0435; \u03c5m \u2014 \u043e\u0442\u043d\u043e\u0441\u0438\u0442\u0435\u043b\u044c\u043d\u0430\u044f \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u0434\u0432\u0438\u0436\u0443\u0449\u0435\u0439\u0441\u044f \u0437\u043e\u043d\u044b.\n1 \u2014 fan inlet; 2 \u2014 exit from the flow area; 3 \u2014 entrance from the threshing and separating device", + "\u0414\u043b\u044f \u0443\u043b\u0443\u0447\u0448\u0435\u043d\u0438\u044f \u0441\u0445\u043e\u0434\u0438\u043c\u043e\u0441\u0442\u0438 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0432 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u0441\u0445\u0435\u043c\u044b \u0438\u043d\u0442\u0435\u0440\u043f\u043e\u043b\u044f\u0446\u0438\u0438 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u043f\u0440\u0438\u043d\u044f\u0442\u0430 \u043e\u043f\u0446\u0438\u044f PRESTO! (PREssure STaggering Option).\n\u0421 \u0446\u0435\u043b\u044c\u044e \u0443\u0441\u043a\u043e\u0440\u0435\u043d\u0438\u044f \u0432\u044b\u043f\u043e\u043b\u043d\u0435\u043d\u0438\u044f \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0432 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u0434\u0430\u043d\u043d\u044b\u0445 \u0434\u043b\u044f \u0438\u043d\u0438\u0446\u0438\u0430\u043b\u0438\u0437\u0430\u0446\u0438\u0438 \u043d\u0435\u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0433\u043e \u0440\u0435\u0448\u0430\u0442\u0435\u043b\u044f \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0438\u0441\u044c \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0433\u043e \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u0441 \u0444\u043e\u0440\u043c\u0443\u043b\u0438\u0440\u043e\u0432\u043a\u043e\u0439 Steady Formulation \u0438 \u043c\u043e\u0434\u0435\u043b\u044c\u044e \u043e\u043f\u0438\u0441\u0430\u043d\u0438\u044f \u0432\u0437\u0430\u0438\u043c\u043e\u0434\u0435\u0439\u0441\u0442\u0432\u0438\u044f \u043c\u0435\u0436\u0434\u0443 \u0437\u043e\u043d\u0430\u043c\u0438 Multiple Reference Frames.\n\u0414\u043b\u044f \u0441\u043e\u0445\u0440\u0430\u043d\u0435\u043d\u0438\u044f \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u043e\u0432 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u043d\u0435\u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0433\u043e \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u0430, \u0430 \u0442\u0430\u043a\u0436\u0435 \u0438\u0445 \u0434\u0430\u043b\u044c\u043d\u0435\u0439\u0448\u0435\u0439 \u043e\u0431\u0440\u0430\u0431\u043e\u0442\u043a\u0438 \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0430\u0441\u044c \u043e\u043f\u0446\u0438\u044f \u0432\u044b\u0431\u043e\u0440\u043a\u0438 \u0434\u0430\u043d\u043d\u044b\u0445 Data Sampling for Time Statistics \u0441 \u0447\u0430\u0441\u0442\u043e\u0442\u043e\u0439 \u0437\u0430\u043f\u0438\u0441\u0438 \u043d\u0430 \u043a\u0430\u0436\u0434\u043e\u0439 \u0438\u0442\u0435\u0440\u0430\u0446\u0438\u0438 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0432 \u0442\u0435\u0447\u0435\u043d\u0438\u0435 2 \u0441. \u0417\u0430\u043f\u0438\u0441\u044c \u0432\u044b\u043f\u043e\u043b\u043d\u044f\u043b\u0430\u0441\u044c \u043f\u043e\u0441\u043b\u0435 \u0443\u0441\u0442\u0430\u043d\u043e\u0432\u0438\u0432\u0448\u0435\u0433\u043e\u0441\u044f \u043a\u043e\u043b\u0435\u0431\u0430\u043d\u0438\u044f \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0435\u0439 \u0432\u043e\u0437\u0434\u0443\u0448\u043d\u043e\u0433\u043e \u043f\u043e\u0442\u043e\u043a\u0430 \u0432 \u043a\u043e\u043d\u0442\u0440\u043e\u043b\u044c\u043d\u044b\u0445 \u0442\u043e\u0447\u043a\u0430\u0445.\n\u0420\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u0438\u0441\u0441\u043b\u0435\u0434\u043e\u0432\u0430\u043d\u0438\u044f, \u043f\u043e\u0434\u0442\u0432\u0435\u0440\u0436\u0434\u0435\u043d\u0438\u0435 \u0430\u0434\u0435\u043a\u0432\u0430\u0442\u043d\u043e\u0441\u0442\u0438 \u043c\u043e\u0434\u0435\u043b\u0438. \u0412 \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0435 \u0437\u0430\u043c\u0435\u0440\u043e\u0432 \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0438\u0441\u0441\u043b\u0435\u0434\u043e\u0432\u0430\u043d\u0438\u0439 \u0438 \u0440\u0430\u0441\u0447\u0435\u0442\u043e\u0432 \u0441\u043e\u0441\u0442\u0430\u0432-\n\u043b\u0435\u043d\u043d\u043e\u0439 \u043c\u043e\u0434\u0435\u043b\u0438 \u0431\u044b\u043b\u0438 \u043f\u043e\u043b\u0443\u0447\u0435\u043d\u044b \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u044f \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0435\u0439 \u043f\u043e\u0442\u043e\u043a\u0430 \u0432\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u043d\u043e\u043c \u0438\u043d\u0442\u0435\u0440\u0432\u0430\u043b\u0435. \u0414\u043b\u044f \u0441\u043e\u043f\u043e\u0441\u0442\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430 \u0438 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u0431\u044b\u043b\u0438 \u043f\u043e\u0434\u0432\u0435\u0440\u0433\u043d\u0443\u0442\u044b \u0441\u0440\u0435\u0434\u043d\u0435\u043a\u0432\u0430\u0434\u0440\u0430\u0442\u0438\u0447\u043d\u043e\u043c\u0443 \u0443\u0441\u0440\u0435\u0434\u043d\u0435\u043d\u0438\u044e. \u0412 \u0441\u0432\u044f\u0437\u0438 \u0441 \u0442\u0435\u043c, \u0447\u0442\u043e \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0435 \u0438\u0437\u043c\u0435\u0440\u0435\u043d\u0438\u044f \u043f\u0440\u043e\u0432\u043e\u0434\u0438\u043b\u0438\u0441\u044c \u0432 \u0442\u0440\u0435\u0445\u043c\u0435\u0440\u043d\u043e\u043c \u043f\u0440\u043e\u0441\u0442\u0440\u0430\u043d\u0441\u0442\u0432\u0435 (\u043f\u043e \u0448\u0438\u0440\u0438\u043d\u0435 \u043e\u0447\u0438\u0441\u0442\u043a\u0438), \u0430 \u043c\u043e\u0434\u0435\u043b\u044c \u0438\u043c\u0435\u0435\u0442 \u0434\u0432\u0443\u043c\u0435\u0440\u043d\u0443\u044e \u043f\u043e\u0441\u0442\u0430\u043d\u043e\u0432\u043a\u0443, \u0438\u0445 \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u0442\u0430\u043a\u0436\u0435 \u0431\u044b\u043b\u0438 \u0430\u0440\u0438\u0444\u043c\u0435\u0442\u0438\u0447\u0435\u0441\u043a\u0438 \u0443\u0441\u0440\u0435\u0434\u043d\u0435\u043d\u044b \u0438 \u043f\u043e \u0440\u044f\u0434\u0430\u043c. \u0420\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u0438\u0441\u0441\u043b\u0435\u0434\u043e\u0432\u0430\u043d\u0438\u044f \u043f\u0440\u0438\u0432\u0435\u0434\u0435\u043d\u044b \u0432 \u0442\u0430\u0431\u043b\u0438\u0446\u0435.\n\u041f\u043e \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u043c \u0437\u0430\u043c\u0435\u0440\u0430\u043c \u0432\u0438\u0434\u043d\u043e, \u0447\u0442\u043e \u0440\u0430\u0437\u0431\u0440\u043e\u0441 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u0439 \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0435\u0439 \u043f\u043e\u0442\u043e\u043a\u0430 \u043f\u043e \u0448\u0438\u0440\u0438\u043d\u0435 \u043e\u0447\u0438\u0441\u0442\u043a\u0435 \u043d\u0435\u0437\u043d\u0430\u0447\u0438\u0442\u0435\u043b\u0435\u043d \u0438 \u0441\u043e\u0441\u0442\u0430\u0432\u043b\u044f\u0435\u0442 \u043e\u0442 3 \u0434\u043e 22 %. \u041f\u043e\u043b\u0443\u0447\u0435\u043d\u043d\u0430\u044f \u0440\u0430\u0437\u043d\u0438\u0446\u0430 \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0435\u0439 \u043f\u043e\u0442\u043e\u043a\u0430 \u043f\u043e \u0448\u0438\u0440\u0438\u043d\u0435 \u043a\u043e\u043c\u0431\u0430\u0439\u043d\u0430 \u043d\u0435 \u043f\u0440\u043e\u0442\u0438\u0432\u043e\u0440\u0435\u0447\u0438\u0442 \u043f\u0440\u0438\u043d\u044f\u0442\u044b\u043c \u0443\u0441\u043b\u043e\u0432\u0438\u044f\u043c \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435\u043d\u043d\u043e\u0439 \u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u0437\u0435\u0440\u043d\u0430, \u0438\u0437 \u0447\u0435\u0433\u043e \u043c\u043e\u0436\u043d\u043e \u0441\u0434\u0435\u043b\u0430\u0442\u044c \u0432\u044b\u0432\u043e\u0434, \u0447\u0442\u043e \u0434\u0430\u043d\u043d\u0443\u044e \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0446\u0438\u044e \u0441\u0438\u0441\u0442\u0435\u043c\u044b \u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u043c\u043e\u0436\u043d\u043e \u043f\u0440\u0438 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u0438 \u043f\u0440\u0435\u0434\u0441\u0442\u0430\u0432\u0438\u0442\u044c \u0432 \u0434\u0432\u0443\u043c\u0435\u0440\u043d\u043e\u043c \u043f\u0440\u043e\u0441\u0442\u0440\u0430\u043d\u0441\u0442\u0432\u0435.\n\u2116 \u043a\u043e\u043d\u0442\u0440\u043e\u043b\u044c\u043d\u043e\u0439 \u0442\u043e\u0447\u043a\u0438\n\u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e\u0442\u043e\u043a\u0430, \u0443\u0441\u0440\u0435\u0434\u043d\u0435\u043d\u043d\u0430\u044f \u043f\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u0438, \u043c/\u0441 \u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432\n\u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f\u0420\u044f\u0434 \u0437\u043e\u043d\u0434\u043e\u0432* \u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c, \u0443\u0441\u0440\u0435\u0434-\n\u043d\u0435\u043d\u043d\u0430\u044f \u043f\u043e \u0440\u044f\u0434\u0430\u043c1 2 3 4 5 6 \u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0441 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u043e\u043c\n\u0442. 1 3,2 2,8 2,7 2,8 2,9 3,1 2,9 3,2 \u0442. 2 2,8 2,6 2,4 2,3 2,8 2,9 2,6 2,8 \u0442. 3 2,9 2,7 2,4 2,4 2,7 2,8 2,7 2,9 \u0442. 4 2,8 2,8 2,4 2,4 2,6 2,9 2,7 2,9 \u0442. 5 4,0 3,4 3,2 3,3 3,5 3,9 3,6 3,8 \u0442. 6 3,8 3,3 3,2 3,3 3,5 3,7 3,5 3,4 \u0442. 7 3,3 3,0 2,9 2,8 2,8 3,0 3,0 3,2 \u0442. 8 3,1 3,0 2,5 2,4 3,1 3,0 2,9 3,1 \u0442. 9 3,7 3,6 3,2 3,3 3,7 3,8 3,6 3,8 \u0442. 10 3,1 3,2 3,1 3,0 3,4 3,3 3,2 3,3 \u0442. 11 3,2 2,8 3,0 3,1 3,1 3,3 3,1 3,3 \u0442. 12 6,1 6,1 6,0 6,1 6,0 6,2 6,1 6,6 \u0442. 13 8,2 8,2 8,0 7,9 8,0 8,1 8,1 8,5\n\u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0431\u0435\u0437 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u0430 \u0442. 1 3,9 3,8 3,7 3,5 3,6 4,0 3,8 4,1 \u0442. 2 2,8 2,6 2,6 2,7 2,9 3,1 2,8 3,0 \u0442. 3 3,0 3,0 2,9 3,0 3,2 3,4 3,1 3,2 \u0442. 4 3,1 3,0 2,8 2,9 3,0 3,2 3,0 3,2 \u0442. 5 3,2 3,1 2,7 2,8 3,0 3,1 3,0 3,2 \u0442. 6 3,0 3,0 2,9 2,7 2,7 2,9 2,9 3,1 \u0442. 7 3,2 3,1 2,6 2,5 3,1 3,0 2,9 3,2 \u0442. 8 3,1 3,2 2,8 2,8 3,0 2,9 3,0 3,1 \u0442. 9 3,2 3,2 2,7 3,0 3,2 3,3 3,1 3,3 \u0442. 10 2,8 2,9 2,6 2,6 2,9 3,0 2,8 3,1 \u0442. 11 3,1 2,9 2,8 2,9 3,2 3,0 3,0 3,3 \u0442. 12 3,7 3,5 3,3 3,6 3,4 3,5 3,5 3,8 \u0442. 13 6,6 6,1 5,9 6,3 6,5 6,2 6,3 6,8\n\u041f\u0440\u0438\u043c\u0435\u0447\u0430\u043d\u0438\u0435: *\u043e\u0442\u0441\u0447\u0435\u0442 \u0432\u0435\u0434\u0435\u0442\u0441\u044f \u043e\u0442 \u043f\u0440\u0430\u0432\u043e\u0439 \u0431\u043e\u043a\u043e\u0432\u0438\u043d\u044b \u043f\u043e \u0445\u043e\u0434\u0443 \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044f \u043a\u043e\u043c\u0431\u0430\u0439\u043d\u0430.\n\u0422\u0430\u0431\u043b\u0438\u0446\u0430 \u2014 \u0420\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432 \u0438 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f Table \u2014 Results of experimental measurements and modeling" + ] + }, + { + "image_filename": "designv8_17_0001135_cle_download_672_566-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001135_cle_download_672_566-Figure6-1.png", + "caption": "Fig. 6. Pump housing design options: a \u2013 the pump casing with a vertical inlet pipe; \u0431 \u2013 pump casing with horizontal inlet branch pipe", + "texts": [], + "surrounding_texts": [ + "SUPPORT IN CARDIAC SURGERY (REVIEW)" + ] + }, + { + "image_filename": "designv8_17_0004606__Coupled_Stacked.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004606__Coupled_Stacked.pdf-Figure2-1.png", + "caption": "Fig. 2. (a) Geometry of the Proposed Model. (b) Geometry Parameters of the Proposed Antenna.", + "texts": [ + " To enhance proper impedance matching, two overlapped annular rings are coupled the stacked psi shaped with outer radii of Ro and Inner radii or Ri. The separation between the two centers of 447 | P a g e www.ijacsa.thesai.org the coupled rings is maintained as 3*Ri so the two rings will coincide to their widths which can be etched in further design process. A circular ring slot was introduced in each coupled ring to increase the capacitive effect which further improves the coupling phenomena. The geometry of the proposed antenna is shown in Fig. 2(a). The geometry variables are represented in Fig. 2(b) and their optimized values are tabulated in Table I. TABLE I. GEOMETRY PARAMETER VALUES OF THE PROPOSED MODEL Parameter Value(cm) Parameter Value(cm) L 3.5 Wf 0.09 W 2 W1 0.18 \u2107r 2 Lg 0.4 h 0.127 Wg 0.85 R0 0.812 Xp 0.18 Ri 0.406 Xp1 0.09 R01 0.67 Xp2 0.1 Ri1 0.6 Yp 0.27 Lf 1.31 Yp1 0.27 The equivalent circuit of the proposed model was determined based on the transmission line model technique. The total structure of the patch antenna is represented in its equivalent electrical lumped parameters" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.11-1.png", + "caption": "Figure 3.11: Test Material Pieces", + "texts": [ + " A schematic of the experiment is shown in Figure 3.10(a) and the loading of the shaft via the cantilever is shown in Figure 3.10(b). 36 37 The test pieces are made from polytetrafluoroethylene (PTFE), bearing grade polyether- etherketone (PEEK) and chrome steel with an internal diameter of 10 mm and a depth of 15 mm. The hole size is larger than that of the shaft so that the same piece can be used for multiple runs (up to four) involving different conditions, each on a different surface. These test pieces are shown in Figure 3.11. Note that there are four grooves on each test piece for mounting the test piece onto the cantilever. For the testing and evaluation for each of the materials, the various operating conditions for the experiment are presented in Table 3.4. The sliding speeds of the test pieces against the shafts that correspond to the rotation speeds of 250 rev min-1 and 500 rev min-1 would be at 0.105 m s-1 and 0.209 m s-1, respectively. Each run lasted for two hours to ensure that the material had sufficient time to run-in and obtain the steady state coefficient of friction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure63-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure63-1.png", + "caption": "FIGURE 63. Configuration of the antenna element (a): simulated model, (b): fabricated prototype [42].", + "texts": [ + " VOLUME 9, 2021 98853 Finally, to further excite the small slot, a long slot representing another magnetic current parallel to the short one is etched on the ground plane, as shown in Fig. 62(a). The MSs of first four characteristic modes for the double-slotted metasurface are plotted in Fig. 62(b). Modes 1, 2, 3 and 4 are resonant at 3.5 GHz, 6.0 GHz, 5.85 GHz, and 6.4 GHz, respectively. Another study designed a dual-wideband, dual-polarized antenna using metasurface for millimeter-wave (mm-wave) communications using CMA [42]. The proposed metasurface is mainly composed of a 3 \u00d7 3 square-patch, as shown in Fig. 63, with four of its corner patches further sub-divided into a 4 \u00d7 4 sub-patch array. On the other hand, the size of the other four edge patches is reduced and the center patch is etched with a pair of orthogonal slots. The design of the metasurface in this study was performed as follows: i. The original metasurface consists of three types of patches: center patch (patch 1), edge patch (patch 2), and corner patch (patch 3), as illustrated in Fig. 64(a). ii. By etching a quasi-cross slot on patch 1, reducing the size of patch 2, and splitting patch 3 into a 4\u00d74 sub-array, an initial modified metasurface with dual-band and suitable radiation patterns is achieved, as depicted in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001135_cle_download_672_566-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001135_cle_download_672_566-Figure2-1.png", + "caption": "Fig. 2. Passively suspended Tesla pump. \u0430 \u2013 pump; \u0431 \u2013 appearance of the pump", + "texts": [], + "surrounding_texts": [ + "SUPPORT IN CARDIAC SURGERY (REVIEW)" + ] + }, + { + "image_filename": "designv8_17_0000007_e_download_1546_1132-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000007_e_download_1546_1132-Figure4-1.png", + "caption": "Figure 4. Experimentation. a) Axonometric view of opener through soil bin; b) test process; c) soil cover thickness measurement crosssection.", + "texts": [ + "7 meters in depth, and consisted of fluvo-aquic soil with an added appropriate amount of corn straw to simulate a straw-soil mixed environment. The soil moisture content was measured at 15.8% using the drying method, ensuring consistent test conditions throughout the plot. Based on actual field environments, a two-layer soil model was established consisting of a bottom layer of pure soil particles with a depth of 150mm and a tillage layer mixed with soil and straw particles, having a depth of 50mm and a straw content of 30%. The depth of entry of the opener is 50 mm (Figure 4b). The operating conditions of the soil bin experiment were set to be the same as the simulation experiment, with the forward velocity of the opener being 5 km/h, the endpoint tangent angle being 108\u00b0, and the soil entry angle being 5\u00b0. The simulation results were compared with the actual data of the soil bin for the soil cover thickness and the straw ratio of the seed furrow. The furrow side pick-up blade utilized in the experiment was fabricated using 3D printing technology and made of PLA material, with a manufacturing accuracy of 0.1mm. The remaining test equipment included a chisel opener, TYD-2 soil compaction meter, vernier caliper, tape measure, electronic scale, soil sampling ring knife, and drying oven. Five locations were randomly selected observation areas in the operational travel stability zone of the test area (Figure 4c) and the soil height above the wheat seeds was measured using digital vernier calipers (resolution 0.02 mm) and the average value was obtained as the soil cover thickness. The results of the simulated test soil cover thickness were measured by measuring the height difference between the coordinates of wheat seeds and surface soil [page 30] [Journal of Agricultural Engineering 2024; LV:1546] particles in the corresponding area selected by the EDEM postprocessing module. The proportion of straw in the seed furrow, i", + ", the proportion of straw mass in the sampling area to all soil mass in the area, is the proportion of straw in the seed furrow, and the expression for the proportion of straw in the seed furrow is: (7) In the formula, \u03c1 is the proportion of straw in the seed furrow, % W1 = Straw quality, g W = the total mass of soil in the sampling area, g After ditching in the test area, five sampling areas with the size of 300mm\u00d7200mm were randomly selected. The quality of soil and straw in the area was measured using a JA2003 electronic precision balance, and the five measurements were averaged. The straw mass and the total mass of the soil-straw complex in the selected area were derived from the EDEM post-processing module for calculation. Experiment on optimal parameters of the furrow side pick-up blade To further investigate the performance of the furrow side pickup blade, the EDEM simulation model (Figure 4a) was used to determine the machine the forward velocity (v), the endpoint tangent angle (\u03c9), and the soil entry angle (\u03b5) as the test factors. The thickness of the covering soil and the ratio of straw in the seed fur- row were used as evaluation indicators of the test. The optimal parameter combination for the furrow side pick-up blade was determined through a cross-rotation regression combination optimization test method. The codes for the test factors are presented in Table 4. DEM simulations were carried out using the software EDEM, 2020", + "7 meters in depth, and consisted of fluvo-aquic soil with an added appropriate amount of corn straw to simulate a straw-soil mixed environment. The soil moisture content was measured at 15.8% using the drying method, ensuring consistent test conditions throughout the plot. Based on actual field environments, a two-layer soil model was established consisting of a bottom layer of pure soil particles with a depth of 150mm and a tillage layer mixed with soil and straw particles, having a depth of 50mm and a straw content of 30%. The depth of entry of the opener is 50 mm (Figure 4b). The operating conditions of the soil bin experiment were set to be the same as the simulation experiment, with the forward velocity of the opener being 5 km/h, the endpoint tangent angle being 108\u00b0, and the soil entry angle being 5\u00b0. The simulation results were compared with the actual data of the soil bin for the soil cover thickness and the straw ratio of the seed furrow. The furrow side pick-up blade utilized in the experiment was fabricated using 3D printing technology and made of PLA material, with a manufacturing accuracy of 0.1mm. The remaining test equipment included a chisel opener, TYD-2 soil compaction meter, vernier caliper, tape measure, electronic scale, soil sampling ring knife, and drying oven. Five locations were randomly selected observation areas in the operational travel stability zone of the test area (Figure 4c) and the soil height above the wheat seeds was measured using digital vernier calipers (resolution 0.02 mm) and the average value was obtained as the soil cover thickness. The results of the simulated test soil cover thickness were measured by measuring the height difference between the coordinates of wheat seeds and surface soil [page 30] [Journal of Agricultural Engineering 2024; LV:1546] particles in the corresponding area selected by the EDEM postprocessing module. The proportion of straw in the seed furrow, i", + ", the proportion of straw mass in the sampling area to all soil mass in the area, is the proportion of straw in the seed furrow, and the expression for the proportion of straw in the seed furrow is: (7) In the formula, \u03c1 is the proportion of straw in the seed furrow, % W1 = Straw quality, g W = the total mass of soil in the sampling area, g After ditching in the test area, five sampling areas with the size of 300mm\u00d7200mm were randomly selected. The quality of soil and straw in the area was measured using a JA2003 electronic precision balance, and the five measurements were averaged. The straw mass and the total mass of the soil-straw complex in the selected area were derived from the EDEM post-processing module for calculation. Experiment on optimal parameters of the furrow side pick-up blade To further investigate the performance of the furrow side pickup blade, the EDEM simulation model (Figure 4a) was used to determine the machine the forward velocity (v), the endpoint tangent angle (\u03c9), and the soil entry angle (\u03b5) as the test factors. The thickness of the covering soil and the ratio of straw in the seed fur- row were used as evaluation indicators of the test. The optimal parameter combination for the furrow side pick-up blade was determined through a cross-rotation regression combination optimization test method. The codes for the test factors are presented in Table 4. DEM simulations were carried out using the software EDEM, 2020" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004385_aper_ETC2017-356.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004385_aper_ETC2017-356.pdf-Figure9-1.png", + "caption": "Figure 9: STARTREC concept (left) and STARTREC tubes alignment in relation to the main flow direction (right)", + "texts": [ + " The upstream region of the installation right before the HEX was redesigned in relation to the NEWAC nozzle configuration (including various modifications in the guiding walls and aerodynamic cone) in order to eliminate the size of the recirculation region which was developed there in the previous recuperation installations (reference, NEWAC) as much as possible. Two CORN versions, presented in Figs. 7 and 8, were investigated where the collectors of the cold air are placed circumferentially either every 45o or every 90o leading to a total of 8 or 4 collectors, respectively for the 360o of the Nozzle. The second of the two alternative concepts was named as STARTREC (STraight AnnulaR Thermal RECuperator). The STARTREC concept is following a straight annular design, presented in Fig. 9. Two STARTREC versions were investigated consisting of two and three banks respectively, which are presented in Figs. 10 and 11. In these versions, the gap spacing between the elliptic tubes was altered in relation to the initial MTU design, in order to reduce the pressure losses. All banks were having a 4/3/4 elliptic tubes arrangement with the gap spacing being coarser at the front banks and sparser at the back banks which, due to the gradual cooling of the hot-gas, operated with higher density values and lower flow velocities. In addition, the upstream region of the installation right before the HEX was redesigned (including various modifications in the guiding walls and aerodynamic cone) in order to reduce the size of the recirculation region which was developed there as much as possible. The distribution of the inner flow (cold air) through the collectors is presented in Figs. 10 and 11. The orientation of the elliptic tubes in relation to the main axis of the installation is shown in Fig. 9 (right), where it can be seen that the elliptic tubes are aligned to the main flow direction in the installation in order to ease the flow guidance through the HEX. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. Additionally, the elliptic tubes are aligned to the main flow direction in the installation in order to ease the flow guidance through the HEX. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000847_853_83_17-00194__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000847_853_83_17-00194__pdf-Figure2-1.png", + "caption": "Fig. 2 Simulation model : roll angle \u03b1", + "texts": [], + "surrounding_texts": [ + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u5fa1\u3092\u884c\u3046\u7814\u7a76\uff08\u5927\u5185\u4ed6\uff0c2015\uff09\u3067\u306f\uff0c\u7dda\u5f62\u8fd1\u4f3c\u30e2\u30c7\u30eb\u306b\u5bfe\u3057\u3066\u6700\u9069\u30ec\u30ae\u30e5\u30ec\u30fc\u30bf\u3092\u8a2d\u8a08\u3057\u3066\u304a\u308a\uff0c\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\n\u30f3\u3068\u5b9f\u9a13\u306b\u3088\u308a\u305d\u306e\u52b9\u679c\u304c\u78ba\u8a8d\u3055\u308c\u3066\u3044\u308b\uff0e\uff12\u8f2a\u8eca\u306e\u50be\u304d\u89d2\u5ea6\u306b\u6bd4\u4f8b\u3057\u305f\u7c21\u6613\u306a\u30d5\u30a3\u30fc\u30c9\u30d0\u30c3\u30af\u3092\u65bd\u3057\u30b8\u30f3\u30d0\u30eb \u6a5f\u69cb\u306b\u5236\u5fa1\u30c8\u30eb\u30af\u3092\u52a0\u3048\u308b\u624b\u6cd5 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\u5236 \u5fa1 \u5bfe \u8c61\n\u56f3 1\u306b\u672c\u7814\u7a76\u3067\u7528\u3044\u305f\u5b9f\u9a13\u88c5\u7f6e\u3092\u793a\u3059\uff0e\u3053\u308c\u306f 2\u8f2a\u8eca\u3092\u60f3\u5b9a\u3057\u3066\u3044\u308b\u304c\uff0c\u8eca\u8f2a\u3092\u8a2d\u3051\u3066\u304a\u3089\u305a 2\u3064\u306e\u811a\uff08\u30ea\u30f3 \u30af\uff09\u3067\u4ee3\u7528\u3057\u3066\u3044\u308b\uff0e\u3053\u308c\u3089\u306e\u811a\u3068\u30b8\u30f3\u30d0\u30eb\u3092\u56fa\u5b9a\u3057\u3066\u3044\u308b\u67a0\u3092\u5408\u308f\u305b\u3066\u53f0\u8eca\u3068\u547c\u3076\uff0e\u811a\u306e\u4ee3\u308f\u308a\u306b 2\u8f2a\u8eca\u306e\u69cb \u6210\u306b\u3059\u308c\u3070\u3053\u306e\u53f0\u8eca\u304c\u56f3 1\u306e\u5de6\u53f3\u65b9\u5411\u306b\u8d70\u884c\u3059\u308b\uff0e\n\u56f3 2\u306b\u793a\u3059\u53f0\u8eca\u306e\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\u306e\u6a2a\u63fa\u308c\u89d2\u3092 \u03b1 \u3067\u8868\u3059\uff0e\u53f0\u8eca\u306b\u306f 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DC\u30e2\u30fc\u30bf\u3092\u914d\u7f6e\u3057\u3066\u3044\u308b\uff0e\n\u53f0\u8eca\u306f\u4e0d\u5b89\u5b9a\u7cfb\u3067\u3042\u308b\u305f\u3081\u3044\u305a\u308c\u8ee2\u5012\u3059\u308b\uff0e\u305d\u3053\u3067\u53f0\u8eca\u3084\u30b8\u30f3\u30d0\u30eb\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u8a2d\u8a08\u6761\u4ef6\u3092\u5909\u5316\u3055\u305b\u305f\u3068\u304d\u306b\uff0c\n\u8ee2\u5012\u307e\u3067\u306e\u6642\u9593\u3092\u3067\u304d\u308b\u3060\u3051\u9577\u304f\u3059\u308b\u3088\u3046\u306a\u6700\u9069\u8a2d\u8a08\u304c\u3067\u304d\u308b\u3053\u3068\u304c\u671b\u307e\u3057\u3044\uff0e\u8a2d\u8a08\u6761\u4ef6\u3068\u3057\u3066\u56f3 4\u306b\u793a\u3059\u3088\u3046 \u306b\u30b8\u30f3\u30d0\u30eb\u56de\u8ee2\u8ef8\u304b\u3089\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3\u307e\u3067\u306e\u8ddd\u96e2 a\u3068\u5730\u9762\u304b\u3089\u30b8\u30f3\u30d0\u30eb\u56de\u8ee2\u8ef8\u307e\u3067\u306e\u9ad8\u3055\uff08\u53f0\u8eca\u306e\u811a\u306e\u9577\u3055\uff09b\u306b \u7740\u76ee\u3057\uff0c\u305d\u308c\u305e\u308c a = 0.11,6.11,12.11[mm], b = 92.10,102.05,112.0[mm]\u3068\u5909\u5316\u3067\u304d\u308b\u3088\u3046\u306a\u69cb\u9020\u3068\u3057\u305f\uff0e\n\u30db\u30a4\u30fc\u30eb\u3092\u9664\u304f\u53f0\u8eca\u3068\u30b8\u30f3\u30d0\u30eb\u306f\u30a2\u30eb\u30df\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u307f\u9244\u88fd\u3068\u3057\u3066\u3044\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f\u534a\u5f84 40[mm]\uff0c\u539a\u3055 15[mm] \u3067\uff0c\u8cea\u91cf\u306f\u7d04 0.61[kg]\uff0c\u56de\u8ee2\u8ef8\u307e\u308f\u308a\u306e\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306f\u7d04 0.472\u00d710\u22123[kg m2]\u3067\u3042\u308b\uff0e\u3053\u306e\u30db\u30a4\u30fc\u30eb\u3092DC\u30e2\u30fc", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30bf\u3067\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3055\u305b\u308b\uff0e\u305f\u3060\u3057\uff0c2\u3064\u306e\u30db\u30a4\u30fc\u30eb\u89d2\u901f\u5ea6\u306e\u5927\u304d\u3055\u306f\u540c\u3058\u3067\u65b9\u5411\u3092\u9006\u306b\u3059\u308b\uff0e\u4e8b\u524d\u306b\u884c\u3063\u305f\u4e88 \u5099\u5b9f\u9a13\u3067\u306f\uff0c\u56de\u8ee2\u6570\u3092 7000[rpm]\u7a0b\u5ea6\u306b\u3059\u308b\u3068\uff0c\u30b8\u30f3\u30d0\u30eb\u3068\u53f0\u8eca\u304c\u3068\u3082\u306b\u63fa\u308c\u306a\u304c\u3089\u6b73\u5dee\u904b\u52d5\u3092\u884c\u3044\u9577\u6642\u9593\u306b\u308f 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7000[rpm]\u4ee5\u4e0a\u306b\u3059\u308b\u3068\u56de\u8ee2\u8ef8\u306e\u89e6\u308c\u56de\u308a\u632f\u52d5\n\u304c\u5927\u304d\u304f\u306a\u308a\uff0c\u9a12\u97f3\u3082\u6fc0\u3057\u304f\u306a\u3063\u305f\uff0e\n\u305d\u3053\u3067\uff0c\u672c\u7814\u7a76\u3067\u306f\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u6570\u3092\u3042\u307e\u308a\u5927\u304d\u304f\u3057\u306a\u304f\u3068\u3082\u5b89\u5b9a\u6027\u3092\u826f\u597d\u306b\u4fdd\u3064\u3053\u3068\u304c\u3067\u304d\u308b\u3088\u3046\u306a\u8a2d\u8a08 \u6307\u91dd\u3092\u691c\u8a0e\u3059\u308b\uff0e\u306a\u304a\u56f3 1\u306b\u793a\u3059\u5b9f\u9a13\u88c5\u7f6e\u3092\u3082\u3068\u306b\u56f3 2,3\u3067\u793a\u3057\u305f\u30e2\u30c7\u30eb\u3092 SolidWorks\u4e0a\u3067\u4f5c\u6210\u3057\uff0c\u5404\u525b\u4f53\u306e\u8cea\n\u91cf\u3084\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306a\u3069\u306e\u7279\u6027\u3092\u6c42\u3081\u3066\u304a\u308a\uff0c\u6b21\u7ae0\u4ee5\u964d\u306e\u7406\u8ad6\u89e3\u6790\u3084\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u4f7f\u7528\u3057\u3066\u3044\u308b\uff0e\n3. \u904b \u52d5 \u30e2 \u30c7 \u30eb\n3\u00b71 \u5ea7\u6a19\u7cfb\n\u56f3 5\u306b\u5bfe\u8c61\u3068\u3059\u308b 2\u8f2a\u53f0\u8eca\u3092\u793a\u3059\uff0e\u56f3 5\u306f\u5ea7\u6a19\u7cfb\u306e\u8aac\u660e\u3092\u660e\u78ba\u306b\u3059\u308b\u305f\u3081\u306b\uff0c\u30b8\u30f3\u30d0\u30eb\u6a5f\u69cb\u3092 1\u3064\u306e\u307f\u63cf\u3044\u3066\n\u3044\u308b\uff0e\u53f0\u8eca\u306b\u306f\u30b8\u30f3\u30d0\u30eb\u304c\u53d6\u308a\u4ed8\u3051\u3089\u308c\uff0c\u53d6\u308a\u4ed8\u3051\u8ef8\u5468\u308a\u306b\u81ea\u7531\u306b\u56de\u8ee2\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306b\u306f\u30db\u30a4\u30fc\u30eb\u3092\u56de\u8ee2\u3055\u305b\n\u308b\u30e2\u30fc\u30bf\u304c\u56fa\u5b9a\u3055\u308c\uff0c\u30e2\u30fc\u30bf\u306b\u3088\u308a\u30db\u30a4\u30fc\u30eb\u304c\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3057\u3066\u3044\u308b\uff0e\n\u03a3B \u3092\u5730\u9762\u4e0a\u306b\u56fa\u5b9a\u3057\u305f\u57fa\u6e96\u5ea7\u6a19\u7cfb\u3068\u3059\u308b\uff0ez\u8ef8\u306f\u925b\u76f4\u4e0a\u5411\u304d\uff0cx\u8ef8\u306f\u53f0\u8eca\u9032\u884c\u65b9\u5411\u3092\u6b63\u9762\u3068\u3059\u308b\u3068\u304d\u53f3\u624b\u3068\u306a\u308b \u5411\u304d\uff0cy\u8ef8\u306f\u6c34\u5e73\u65b9\u5411\u3067\u53f0\u8eca\u306e\u9032\u884c\u3059\u308b\u5411\u304d\u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f\u8d77\u4f0f\u306e\u3042\u308b\u9762\u3092\u4e0a\u308a\u4e0b\u308a\u3059\u308b\u3053\u3068\u3092\u60f3\u5b9a\u3059\u308b\uff0e\u53f0\u8eca\u306e \u5e95\u9762\u306b\u539f\u70b9\u3092\u3068\u308a\uff0c\u03a3B \u3092 x\u8ef8\u56de\u308a\u306b\u5730\u9762\u306e\u50be\u304d\u89d2\u5ea6 \u03d5 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u5ea7\u6a19\u7cfb\u3092 \u03a3A \u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f 2\u8f2a\u3067\u8d70\u884c\u3059 \u308b\u305f\u3081\uff0c\u9032\u884c\u65b9\u5411\u306b\u5bfe\u3057\u3066\u5de6\u53f3\u65b9\u5411\uff08\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\uff09\u306b\u5012\u308c\u3088\u3046\u3068\u3059\u308b\uff0e\u3053\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03a3A\u306e y\u8ef8\u56de\u308a\u306b \u03b1 \u3068\u8868 \u3059\uff0e\u539f\u70b9\u3092\u53f0\u8eca\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3A\u3092 y\u8ef8\u56de\u308a\u306b \u03b1 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u53f0\u8eca\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3C \u3068\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u56de \u8ee2\u89d2\u5ea6\u3092 \u03a3C \u306e x\u8ef8\u56de\u308a\u306b \u03b2 \u3068\u8868\u3059\uff0e\u539f\u70b9\u3092\u30b8\u30f3\u30d0\u30eb\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3C \u3092 x\u8ef8\u56de\u308a\u306b \u03b2 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30b8\u30f3\u30d0", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3G \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f \u03a3G \u306e z\u8ef8\u56de\u308a\u306b\u56de\u8ee2\u3059\u308b\uff0e\u305d\u306e\u89d2\u5ea6\u3092 \u03b3 \u3068\u3059\u308b\uff0e\u539f\u70b9\u3092\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3 \u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3G \u3092 z\u8ef8\u56de\u308a\u306b \u03b3 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30db\u30a4\u30fc\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3W \u3068\u3059\u308b\uff0e\n\u4ee5\u964d\u6570\u5f0f\u4e2d\u3067\u306f cos\u03b8 =C\u03b8 , sin\u03b8 = S\u03b8 \u3068\u7565\u8a18\u3059\u308b\uff0e\n3\u00b72 \u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\n\u307e\u305a\uff0c\u56de\u8ee2\u904b\u52d5\u3092\u8868\u3059\u305f\u3081\u306e\u5404\u525b\u4f53\u306e\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092\u660e\u3089\u304b\u306b\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u901f\u5ea6\u306f\u56de\u8ee2\u89d2\n\u03d5 ,\u03b1,\u03b2 ,\u03b3 \u306e\u6642\u9593\u5909\u5316\u306b\u3088\u3063\u3066\u8868\u3059\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u3053\u308c\u3092 \u03a3W \u3067\u8868\u3057\u305f\u3068\u304d W \u03c9W \u3068\u8a18\u3059\u3068\uff0c\nW \u03c9W = C\u03b3 S\u03b3 0 \u2212S\u03b3 C\u03b3 0\n0 0 1\n C\u03b1 \u03d5\u0307 + \u03b2\u0307\nS\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307\n (1)\n\u3068\u306a\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3G \u3067\u8868\u3057\u305f\u3082\u306e\u3092 G\u03c9G \u3068\u8a18\u3059\u3068\uff0c\u5f0f (1) \u306b\u304a\u3044\u3066 \u03b3 = 0, \u03b3\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u307e\u305f\u53f0\u8eca\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092 C\u03c9C \u3068\u8a18 \u3059\u3068\uff0c G\u03c9G \u306b\u5bfe\u3057\u3066 \u03b2 = 0, \u03b2\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u3086\u3048\u306b\uff0c\u305d\u308c\u305e\u308c\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u306a\u308b\uff0e\nG\u03c9G = C\u03b1 \u03d5\u0307 + \u03b2\u0307 S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 C\u03c9C = C\u03b1 \u03d5\u0307 \u03b1\u0307 S\u03b1 \u03d5\u0307 (2)\n3\u00b73 \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae \u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e\u6163\u6027\u30c6\u30f3\u30bd\u30eb\u3092\u305d\u308c\u305e\u308c \u03a3W ,\u03a3G,\u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092\nIW = IWX 0 0 0 IWY 0\n0 0 IWZ\n , IG = IGX 0 0 0 IGY 0\n0 0 IGZ\n , IC = ICX 0 0 0 ICY 0\n0 0 ICZ\n (3)\n\u3068\u3059\u308b\uff0e\u305f\u3060\u3057\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u5bfe\u79f0\u6027\u304b\u3089 IWX = IWY \u3067\u3042\u308a\uff0c\u3053\u306e\u5024\u3092 IWXY \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TWR,TGR,TCR \u306f\u305d\u308c\u305e\u308c\u5f0f (1)(2)\u3092\u7528\u3044\u3066\uff0c\nTWR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 } + IWZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307 )2 ]\n(4)\nTGR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03d5\u0307) = 1 2\n{ IGX ( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + IGY ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 + IGZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 )2 }\n(5)\nTCR(\u03b1, \u03b1\u0307, \u03d5\u0307) = 1 2 ( ICXC2 \u03b1 \u03d5\u0307 2 + ICY \u03b1\u03072 + ICZS2 \u03b1 \u03d5\u0307 2) (6)" + ] + }, + { + "image_filename": "designv8_17_0000887__10.1145_66617.66663-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000887__10.1145_66617.66663-Figure3-1.png", + "caption": "Figure 3. Complexity Index values for assembly components.", + "texts": [ + " Feedback of an inspection plan could reveal problems with access to inspection points by the probe of the coordinate measuring machine. Feedback of inspection plans for assembled devices may also be useful. Example of a Component \"Rough\" Planner The most advanced part of our ICE project is our Complexity Analysis Tool, described above. To test it, we applied it to a small, precision device which feeds coolant through the walls of an ion beam milling machine and allows orientation of the target bolder inside. Figure 3 shows the parts as an exploded solid model, along with their Complexity Indexes (CI's). Table 2 lists the contributions to the CI of the lowest part (1) of this model in Fig. 3 for two materials: titanium 6A1-4V and 6061 A1 alloy. This device was actually quite well designed. To add some complexity, and to further test our tool's analysis capabilities, we combined parts 1 and 3, specified titanium alloy as the material, and added unnecessary detail at three levels, as shown in Fig. 4. The associated CI's, also shown in Fig. 4, track the increase in fabrication complexity, as determined by Martin Marietta Laboratories' machine shop superintendent. The large step in CI from level 2 to 3 is real, even though there is not much change in geometric complexity: to create the splines, the part must be taken out of the lathe and put into a special machine" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure86-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure86-1.png", + "caption": "Figure 86. Finished specimen, pin and side plate", + "texts": [], + "surrounding_texts": [ + "1 = variable 1 2 = variable 2 3 = variable 3 br = bearing comp = compressive extes = extensometer i = at ith data point long = longitudinal direction max = maximum xxii min = minimum pin = pin location s = symmetric spec = specimen ten = tensile trans = transverse direction ult = ultimate x = x-direction xx = in the axial direction for the +/-45\u00b0 shear tensile test y = y-direction xy = xy-direction (plane) 1 CHAPTER 1: INTRODUCTION In this chapter, previous and current thesis work is introduced. Section 1.1 introduces the different two different types of aircraft structures. In Section 1.2, the differences between an adhesively bonded joint and a mechanically fastened joint are explained. In Section 1.3, previous work is mentioned, considerations are made in order to avoid testing parameters, which have already been tested, and the three different failure mechanisms are explained. Section 1.4 explains the thesis goal and the thesis scope. 1.1 Introduction to Conventional & Advanced Composite Structures When you think of an aircraft\u2019s wing, it is composed of multiple panels and not usually made as a single piece. The use of joints becomes essential in an aircraft\u2019s wing (since joints serve to attach multiple structural components together to form one part). Ideally, the designer wants to avoid using them, since they can contribute a significant amount of weight to the overall aircraft\u2019s structure. Current aircraft manufactures are transitioning from a conventional aircraft structure to an advanced composite structure since the advantage of switching to an advanced composite structure is the significant reduction in parts and joints. Composite materials have desirable characteristics such as being: very stiff, extremely strong, and extremely light. For example, the Airbus\u2019 A350 aircraft structure is made up of 53% composite materials [1]. Even though the total amount of joints can be significantly reduced, that does not mean they can be avoided altogether. 2 As composites become more widely used in the Aerospace Industry, there still lies limited research in their ability to perform as joints. Their main flaw is their poor behavior in redistributing stress concentrations. Even though there has been a lot of research in composite joints, not enough advancement has been made compared to its metal counterpart. Metal joints (in particular, Aluminum joints) have been used for years in the Aerospace Industry. Currently, composite joints are overdesigned (made a lot thicker than they need to be) which leads to weight penalties. Design that is more detailed needs to done on composite joints in order to improve its ultimate bearing strength. 1.2 Introduction to Adhesively Bonded Joints & Mechanically Fastened Joints Two types of joints exist: one is the mechanically fastened joint, and the other is the adhesively bonded joint. In Figure 1, one can see an adhesively bonded single shear joint, a mechanically fastened single shear joint and a mechanically fastened double shear joint. The region between the two plates, in the adhesively bonded double shear joint, is the thin layer of structural adhesive used to bond both structural components together. Adhesively bonded joints are typically lighter but are often more difficult to design. No holes need to be made in an adhesively bonded joint. Reduction of holes reduces the amount of stress concentrations. Adhesively bonded joints can be problematic since the surface finish needs to be accounted for to achieve a strong bond between two surfaces. Another issue with adhesively bonded joints is that they cannot be removed as easily as a mechanical joint. 3 Mechanically fastened joints are widely used in the Aerospace Industry since they are more practical in the sense that they can be easily removed if a part needs to be replaced, repaired, or checked. Two types of mechanically fastened joints exist: single shear and double shear. In addition, a mechanically fastened joint can contain many fasteners. Mechanically fastened joints require a hole through both structural components, which creates stress concentrations. Both of the structural assemblies are held together by a bolt, and nut. 4 1.3 Previous Literature on Mechanically Fastened Composite Joints Numerous papers have been made on mechanically fastened composite joints, and in this section, the most important finds will be mentioned. According to Alan Baker[3], for a mechanically fastened double shear joint, load is transferred mainly through compression on the internal face of the fastener holes and as well as on a component of shear on the outer faces of the plate due to friction. Mechanically fastened composite joints can be made very durably but the designer needs to spend a longer time in the design process. According to Okutan [4], problems arise when the designer wants to analyze them since they have an anisotropic and heterogeneous nature. According to Chen [5], the behavior of a composite joint could be influenced by four parameters. The first is the material parameter. The material parameter includes fiber types, form, resin type, fiber orientation, laminate stacking sequence, material cure cycle, etc. The second is the geometric parameter. This includes the specimen width (W) and the hole edge distance (e). These are usually reported as W/D and e/D ratios where D is the diameter of the hole. A huge contributor to the strength of the specimen is the specimen thickness (t). The pitch is the distance between two or more holes in a multiple hole composite joint. The third (also very important) is the fastener parameter. This includes fastener type, fastener size, washer size, hole size, and tolerance. The last is the design parameter. The design parameter includes loading type (tension, compression, fatigue), loading direction, loading speed, hydraulic clamping pressure, joint type (single lap, double lap), environment, etc. 5 The lay-up sequence also played a significant role in the overall strength of the double shear joint, as well. Quinn & Matthews [6] studied in detail the effect of stacking sequences on the pin bearing strength in glass-reinforced plastics. They concluded that placing a 90\u00b0 layer ply on the outer surface of the laminate increased the overall bearing strength. Liu [7] tested different laminate thicknesses by varying the bolt diameter. He concluded that thick laminates with smaller diameter holes and thin laminates with larger diameter holes were a lot weaker than laminates with similar hole and laminate thicknesses. Stockdale & Matthews [8] studied the effects of bolt clamping pressure and found that boltclamping pressure played a huge role in the overall strength of the composite joint. Kim [9] tested to see the effects of temperature and moisture on the strength of graphite-epoxy laminates. From this experiment, the actual stress distribution of the joint is very difficult to find since the region is so small. The use of strain gages is impractical because that region is under a very high stress so any kind of strain gage applied would crush because of the force. That is why numerous researchers have been working on methods of modeling composite joints with the help of various finite element programs. The load capacity of a laminate is severely degraded due to the effects of hole clearance and friction. Hyer & Klang [10] investigated this phenomenon with a pin-loaded orthotropic plate. Pierron [11] used Abaqus to calculate the stress distribution around the hole of a woven composite joint. Most finite element modeling was done using 2D shell elements and recently there has been an increased amount of 3D modeling of composite joints. Previous researchers mention that the joint strength depends mainly on the failure criterion. 6 Only a small section of the bearing stress vs. bearing strain curve is linear, and then after, it becomes nonlinear. Stress concentrations cause crushing in a small section of the geometry, making it a very difficult nonlinear problem. Chang [12] created a 2D finite element model and assumed a frictionless contact with a rigid pin and a cosine normal load distribution in the pin-hole boundary. Another difficulty in modeling the composite joint requires the user to combine the failure criteria with a property degradation model. As the composite takes more load, the actual material properties are degrading over time, which would mean the modulus is decreased after each new load is applied. Lessard [2] used a 2D linear model along with a non-linear model to predict the strength of the composite joint. There are five different kinds of failure, which can occur in a laminate: matrix tensile, compressive failure, fiber/matrix shearing, fiber tensile, and fiber compressive failure. The Hashin failure criterion is an important criterion used to characterize failure within a laminate. 1.3.1 Previous Literature on Loading Rate Effects on Mechanically Fastened Composite Joints In flight, the aircraft might experience various dynamic loading conditions, so not only do composites need to be tested in quasi-static loading case, but also in a dynamic load case. Metals are not as load rate dependent as composite materials. Ger [13] tested a number of carbon and carbon fiber glass hybrid composites at dynamic loading rates of 6 to 7 m/s. The double shear joint configuration carried more load at high loading rates. It was also noted that for all joint configurations the stiffness of the joint increased significantly with 7 loading rate. In addition, what was noted was that the total energy absorption of the joint decreased significantly in the dynamic tests. Contradictory to Ger [13], Li [14] tested different types of joint configurations subject to a bearing load and found that energy absorption increased. Li [14] tested at higher rates of 4-8 m/s and found this interesting trend. The dynamic behavior of composite joints is much more complicated than its behavior for the quasi-static condition due to the involvement of strain rate and inertial effects. Li [14] concluded that crashworthiness design of tested composite joints could be based on their tensile strength design. Ger [13] mentioned there must be a significant safety factor applied to take into account bearing strength variations with loading rate. The failure modes might also be affected due to an increased loading rate. 1.3.2 Types of Failure in Mechanically Fastened Composite Joints According to Larry Lessard [2], it has been observed experimentally that mechanically fastened composite joints fail under three basic mechanisms: net-tension, shear-out, and bearing (in addition, combinations of these mechanisms are often given separate names). Typical damage mechanism is shown below in Figure 2. Looking at previous work, a net-tension and a shear-out failure are more catastrophic than a bearing failure. The best way to see if a bearing failure has occurred is to look at the bearing stress vs. bearing strain plot. Once the stress gets to its peak value and suddenly drops off to zero, then one can conclude it was a shear-out or a net-tension failure. If after the ultimate bearing stress, the specimen continues to carry load but deforms as a result, this means that the joint was designed very safely. According to Okutan [4], the optimum orientation for a bearing type of failure is a quasi-isotropic laminate orientation. A quasi-isotropic laminate 8 orientation means the laminate has the isotropic properties in plane. According to USNA [15], a quasi-isotropic part has either randomly oriented fiber in all directions, or has fibers oriented such that equal strength is developed all around the plane of the part. The geometry of a mechanically fastened composite joint is quite complex since it can affect the failure mode of the double shear joint specimen. Kretsis [16] & Matthews [16] tested fiber glass and carbon fiber reinforced plastics and found that the width(W), end distance(e), diameter of hole(D), and laminate thickness(h) all contribute to the overall mechanically fastened double shear joint strength. The most interesting aspect is that as the width of the specimen decreases to a specific amount, the mode of failure changes from bearing to net-tension. The W/D (width to hole diameter ratio of the composite double shear joint specimen) must be at least 5 order to avoid the net tensile type failure. Another interesting thing to note is when the end distance of the hole is a certain distance from the edge of the plate, the failure turned from bearing to shear-out (where shear-out is considered a special case of bearing failure). 9 1.4 Thesis Goals & Scope In the preceding sections of this thesis paper, the word double shear specimen will be used to represent one test specimen with a mechanically fastened double shear joint configuration. The goal of the thesis is to determine how the strength of a composite double shear joint is affected by two different cure cycles and five different loading rates. The composite joint will be tested in the double shear case and the laminate orientation was decided to be a quasi-isotropic laminate (based upon based on Yeole\u2019s double shear experimental results [17]). Yeole [17] tested three different laminate orientations in his thesis, and concluded that a quasi-isotopic laminate took the highest stress. Yeole [17] also mentioned that the testing of composite materials at fast loading rates could be an interesting topic to explore. ASTM 5961[18], which is the ASTM for bearing response of composite materials, required an extensometer to measure the relative pin displacement since using crosshead displacement is not an accurate method. A fixture was designed and manufactured in order to accommodate an extensometer. Finally, the numerical model was made to validate only the linear elastic portion of the experimental results. There are seven chapters in this thesis. Chapter 1, the introduction, includes a brief introduction to: composite materials, the difference between adhesively bonded joints and mechanically fastened composite joints, and the loading rate effects on mechanically fastened composite double shear joint bearing strengths. It also includes a brief literature review, the statement of the problem and the objective and organization of thesis. Chapter 2 focuses on manufacturing of the double shear specimens and the tensile specimens. Chapter 3 focuses on the experimental material testing 10 procedure conducted on the MTM49 Unidirectional Carbon Fiber pre-preg. It also explains the double shear fixture used for the testing. Chapter 4 focuses on the equations used in the experimental and theoretical calculations. Chapter 5 introduces the experimental result validation and then discusses the experimental results. Chapter 6 introduces: the numerical model, which was created using Abaqus 6.14 software, the convergence plot, and lastly, what, influences the numerical results. Chapter 7 is where the experimental results are compared to the numerical finite element results. Lastly, Chapter 8 is where the conclusions are drawn and different recommendations are made for the future work. In the reference section, one can find most of the related topics in the form of theses, books, reports and even papers published in numerous journals. In the appendix section, one find: drawings of the fixture, a tutorial on setting up the Bluehill2 double shear test method, a tutorial on finding the unknown engineering constants with the Autodesk software, a tutorial on outputting the force vs. hole deformation in Abaqus, and a tutorial on the composite double shear specimen Abaqus model. 11 CHAPTER 2: MANUFACTURING & PREPARING OF THE SPECIMENS This chapter will introduce the type of specimens that were manufactured and tested in the Instron machine along with their dimensions. All the dimensions were based on published ASTM test standards. ASTM is an international standards organization, which develops and publishes voluntary consensus technical standards for a wide range of materials, products, systems and services. 2.1 Tensile Specimen & Double Shear Specimen Dimensions The dimensions for the 0\u00b0 tensile specimens and the 90\u00b0 tensile specimens were found in ASTM D3039 [19] Standard test method for tensile properties of fiber-resin composites. The dimensions used for the shear modulus +/- 45\u00b0 were found in ASTM D3518 [20]. Below in Figure 3, one can see all of the tensile specimen dimensions for each specific fiber orientation angle. Figure 4 shows a drawing of all four different fiber orientation tensile specimens. The +/- 45\u00b0 shear specimens and the quasi-isotropic laminate specimens had the same dimensions. Figure 5 shows the dimensions, based on ASTM D5961 [18], of the composite double shear specimens. The quasiisotropic tensile specimens were tested to see how the theoretical material properties matched. 12 13 2.2 Manufacturing Process In the Cal Poly\u2019s Aerospace Engineering Composites Lab, there are two ways to manufacture a composite. One can use pre-preg material or apply a wet layup process. Pre-preg material is a lot easier to use since it already has the resin infused inside the material. In order to preserve the resin in the pre-preg material, it needed to be stored in a freezer at low temperatures. Once the pre-preg material is thawed, then the user is able to apply it to a mold or create a plate out of it. The second way, the wet-layup process, consisted of having the fibers in their pure form, which usually come in a roll, and having a two-part epoxy. Once the fibers were cut out from the roll, the two-part epoxy is mixed with the correct ratio and then applied to the dry fibers. The part is then sealed, with a vacuum bag (where all the air is removed from the part). Then the cure cycle of the 14 resin is applied to the vacuum-bagged part. All of the tensile and double shear specimens were made on the heat press. When making a composite plate in the heat press, the user needed to sandwich the laminate between two nonporous sheets and two 0.25 in. thick Steel plates. Figure 6 shows how the heat press cure process was set-up. The non-porous sheets served to prevent the resin from sticking to the steel plates. The composite plate, the steel plates and the non-porous sheets were placed inside the heat press and then the cure cycle was programmed. Once cured, the composite plate was cut into various size specimens. 2.2.1 Double Shear Specimens All the composite double shear specimens were made with the quasi-isotropic laminate orientation. The quasi-isotropic laminate orientation, [0 0 +45 -45 +45 -45 90 90]s, is short hand for [0 0 +45 -45 +45 -45 90 90//90 90 -45 +45 -45 +45 0 0]. The subscript s means that the laminate 15 is symmetrical about the last ply (which in this case is a 90\u02da ply). The alternate cure cycle was the Cytec\u2019s MTM 49 cure cycle and the datasheet cure cycle was the Umeco\u2019s MTM 49 cure cycle.. The material was first thawed since according to the Umeco\u2019s [22] MTM 49 datasheet, if the roll is open to the environment, condensation will occur on the pre-preg material, which will degrade the quality and the aesthetic look of the material. Sixteen 12 in. by 12 in. plies were cut out and orientated in the quasi-isotropic laminate orientation of [0 0 +45 -45 +45 -45 90 90]s. All the respective angles within each ply of the laminate were carefully kept within \u00b1 1\u00b0. Shown in Figure 7, a protractor was used to make sure each ply in the laminate was within \u00b1 1\u00b0. Once all the plies were stacked very carefully (in order to prevent air pockets from occurring within the laminate), the cure cycle was programmed into the heat press. Air pockets create areas where delamination can occur, which leads to the formation of cracks. Cracks can severely weaken composite structures. The second step consisted of programming the cure cycle into the heat press. Shown in Figure 16 8, is Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22]. Two different cure cycles were tested to see its effects on the material\u2019s double shear bearing stress. Increasing the dwell temperature from 248\u00b0F to 275\u00b0F and increasing the dwell time from 60 minutes to 90 minutes both affect the mechanical characteristics of the resin. The dwell temperature is the temperature which is held constant in the cure process (for this material, it occurs after the temperature ramp up stage). The dwell time is the duration of the dwell temperature stage. Each different carbon fiber matrix system will have its own recommended cure cycle printed in its specific datasheet. In the experimental section, one can see the difference in mechanical properties of the material based on the two different cure cycles. The first cure cycle was Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22] (also known as the alternate cure cycle). The heat press was adjusted to the specific cure cycle. First, the cure cycle temperature ramped up from room temperature of 77\u00b0F to 275\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 275\u00b0F for 90 minutes. After the 90 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. A uniform pressure of 2 psi was applied on top and bottom of the plate. 17 The second cure cycle was Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [21], shown in Figure 9 (also known as the datasheet cure cycle). The heat press was adjusted to the specific cure cycle. First, the press ramped the temperature up from the room temperature to 248\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 248\u00b0F for 60 minutes. After the 60 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. The pressure was held constant between both cure cycles. 18 The third step consisted of preparation of the test specimens. Once the composite laminate finished curing, the material was removed from the press and was cut with a tile saw, which had a diamond-coated blade. The tile saw had an adjustable clamp that helped keep the cuts within 0.1 of an inch. Figure 10 shows the tile saw used to cut the specimens. A straight cut was made on the composite laminate, in order to clean up the edge of the plate. Next, the top side of the plate was aligned to the straight section of the small tile saw. The cuts were made carefully in order to keep a 90\u00b0 angle on the side of the cured laminate. Once all the cuts were made, and the zero direction of the laminate was located accordingly, specimens were cut to the correct width. Based on ASTM D5961 [18], a W/D (specimen width to hole diameter ratio of the composite double shear joint specimen) of 6 and e/D (hole edge distance to diameter of hole ratio) of 3 were used. These geometric conditions guaranteed the double shear composite specimens failed in bearing and not in net-tension or shear-out. Based on these geometric conditions, the specimens needed to be 1.5 in. wide by 5.5 in. in length. The tile saw 19 was used to trim the long 1.5 in. wide specimens to their final length of 5.5 in. A small aluminum block was clamped to the tile saw, which helped minimize variations in the length of all the specimens and allowed multiple specimens to be cut at the same time. After the specimens were cut to their specified length and width, they were grouped into sets of five. A mini microfiber-board fixture was created in order for five holes to be drilled at the same time. The fixture was clamped into the drill press. Five composite double shear specimens were stacked onto the drill fixture and the top left corner of each composite double shear specimen was aligned to the top left corner of the fixture. An Aluminum template was placed on top of the composite double shear specimens and was used to align the 0.25 in. diamond coated end mill bit. Once the composite double shear specimens were aligned accordingly, a small c-clamp was used to constrain the specimens along with the Aluminum template from moving/rotating during the drilling process. In Figure 11, one can see the fixture, the Aluminum template and the end mill bit used for the hole drilling process. 20 Once the holes were created for all the composite double shear specimens, there needed to be a 0.5 in. wide horizontal slit on each face of the composite double shear specimens. A thin Aluminum template was created to assist in locating a specific distance from the hole. This slit needed to be placed accurately within a tolerance of 0.01 in. The template is shown below in Figure 12, and the flat edge of the Aluminum template was used to locate the slit location. The slit needed to be as horizontal as possible and deep enough to catch the moveable knife-edge of the extensometer. 21 Emery cloth helped distribute the high clamping pressure (which is applied by the hydraulic clamps) which occurred at the bottom of the double shear specimen and the emery cloth prevented the composite double shear specimen from slipping during the test. Aluminum tabs were not needed for the double shear test because the specimens failed before reaching 7,000 lbs. The emery cloth works up to a maximum load of 7,000 lbs. The emery cloth was 1.5 in. wide and had a grit level of 120, which is shown in Figure 13. Each specimen only needed emery cloth on one end. Only a 3 in. long piece was needed to cover all of the specimen\u2019s width. A small portion of painters tape served to hold the emery cloth in position. The emery cloth was also reusable; so one piece of emery cloth could be used on two or more specimens. In Figure 13, on the right, shows the ready-to-test composite double shear specimen. 22 2.2.2 Tensile Specimens The same method was applied for the composite tensile specimens, except that these specimens did not have a hole. Stacking the layers needed to be done in a very careful manner in order to prevent misalignment. Once the composite shear modulus specimens and the 90\u00b0 composite tensile specimens were cut to 10 in. by 1 in., then all that was needed was to apply the emery cloth to the ends. Painters tape was used to secure the emery cloth in position. Then, the composite shear modulus specimens and the 90\u00b0 specimens were ready for testing. The 0\u00b0 unidirectional carbon fiber composite tensile specimens required 2 in. long aluminum tabs (as specified by ASTM 3039 [19]). Sandpaper was used on the surface, near the ends of the 0\u00b0 unidirectional carbon fiber composite tensile specimens. A small section of the surface was 23 abraded, and then, acetone was used to clean the surface. Structural adhesive was used to bond the Aluminum tabs to the 0\u00b0 unidirectional carbon fiber composite tensile specimens. After a full day of curing, the 0\u00b0 unidirectional carbon fiber composite tensile specimens were ready to be tested in the Instron 8801 machine. In Figure 14, one can see the ready-to-test 0\u02da unidirectional carbon fiber composite tensile specimens and the +/-45\u02da composite shear modulus specimens. 24 CHAPTER 3: TESTING PREPARATION & PROCEDURE In this chapter, the test preparation and procedure are explained thoroughly. Section 3.1 introduces the type of testing machine used for the experiment. Various test recommendations are made and included inside the preceding subsection. The Auto-Loop tuning feature is explained in detail and an example is made to assist the user in using this feature. The Specimen Protect feature in Bluehill2 is explained with full detail, which helped produce very consistent experimental results. Finally, in Section 3.3, the tensile double shear test and tensile test procedures are explained. The design and set-up of the double shear fixture is shown in detail as well. In the Appendix, the Bluehill2 test method creation was explained for a double shear tensile test. 3.1 Intro to Uniaxial Testing Using the Instron 8801 Servo-hydraulic Test Machine All the material tests were conducted on an Instron 8801. This machine is a dual column servohydraulic testing system. It meets the challenging demands of various dynamic and static testing requirements. The machine allows the user to hook up external force or strain transducers. A dynamic knife-edge extensometer was used for both, the tensile and double shear tests. The machine works in conjunction with a controller, which can be used to control the machine without the use of a computer. A servo-hydraulic system is composed of an actuator, which can apply a tremendous amount of load onto a test specimen. The load cell has a +/- 100 kN limit which means it can measure accurately up to +/- 22,000 lbs. axial force (in compression/tension). For the tensile double shear test, the maximum load that was seen during the test was around 1,700 lbs. and for 25 the tensile test, a maximum load of 7,000 lbs. was seen. The thicker the laminate, the higher the load the specimen could take before failure. Shown in Figure 15, one can see the Instron 8801 testing setup. The machine\u2019s crossheads contain metal jaws, which (powered by a hydraulic system) are able to clamp the specimen. The hydraulic clamping pressure is adjustable so for standard tensile testing, the pressure is set to 160 bar and for testing fragile composite resins, one would want to drop the pressure to 80 bar. Lowing the hydraulic pressure helped reduce premature specimen cracking. The crosshead mechanism loaded with a specimen is shown below in Figure 16. The specimen is placed carefully between two the hydraulically powered metal clamps which secure 26 the specimen in place. 3.1.1 Instron Servo-hydraulic Test Machine Recommendations For determining the modulus of elasticity along with the modulus of rigidity, the most accurate measuring tools were the extensometer and the strain gage. The crosshead displacement was not very accurate since the system displaces due to the compliance in the grips, and the actuator assembly. This displacement of the crosshead can cause unreliable results in the modulus of elasticity where accuracy is very important. The Instron crosshead and the extensometer both yielded slightly different stress/strain curves. This difference in stress/strain curves is due to the Instron crossheads displacing a little more than the extensometer. The extensometer measured only the deflection of the specimen relative to both of the extensometer knife-edges. The extensometer 27 had a gage length of 0.5 in. and a knife-edge width of 0.5 in. The dynamic extensometer, catalog no. 2620-826, can be seen in Figure 17. The top knife-edge is fixed and the bottom knife-edge records precise deflections. The extensometer was attached using two rubber bands. The rubber bands were wrapped multiple times around the specimen to prevent the knife-edges from slipping. Whenever the extensometer was handled, the safety pin was in place at all times. If the user wants to run a three-point or 4-point bend test, the crosshead displacement is accurate enough to capture the vertical displacement accurately. If the user wants even more accuracy, they are able to hook up an extensometer to the three-point bend fixture and record vertical displacement with that device rather than the crosshead displacement. The Instron 8801 machine has a few features, which need to be utilized in order to minimize testing errors. The load and position calibration should never be changed or conducted. Before any 28 test is conducted, the user should Auto-loop tune the load cell only once. Each time a new material is being tested; for example, carbon fiber compared to Aluminum, the load cell should be Autoloop tuned. A list of load cell control gains should be recorded in a separate table for each material, to avoid having inexperienced individuals auto-loop tune the machine. Some precautions in the auto-loop tuning process include to never auto-loop tune a material that will fails under 120 lbs. and to never set the force amplitude above 500 lbs. This may cause the machine to cycle through very rapidly. 3.1.2 Tutorial on Auto-Loop Tuning of the Load Cell for an 1 in. wide By 1/16 in. Thick Aluminum Specimen Each time a new type of material is tested in the machine the load cell needs to be auto-loop tuned whether it be Aluminum, Steel, carbon fiber, hemp composite, fiberglass or any other composite material. Auto-loop tuning the force insured that the load cell is set up to perform accurately for each specific material. The auto-loop tuning tool adjusted various gains on the load cell controller. This was done through the Bluehill2 console (under the load cell menu). Measure the cross-sectional area of the tensile specimen and note its yield stress (if a metal) or ultimate stress (if a brittle material). For example, for Aluminum, the yield stress is around 35 ksi and the tensile specimen had a cross-sectional area of 0.062 in.2. Make sure to apply a force which keeps the material well under its yield or ultimate stress (so 25 ksi was applied to the Aluminum specimen). 29 Insert the Aluminum tensile specimen into the hydraulic clamps and load the specimen to 1,500 lbs. Also, set the amplitude force to 500 lbs. In the auto-loop tuning wizard, the Proportional gain (P) needs to be set to one before any auto-loop tuning is conducted. The specimen will be exposed to a cyclic load of 1,500 lbs. \u00b1 500 lbs. After the auto-loop tuning completes, it will say Auto-loop tuning completed successfully and then, in the next window record the P, I, D and L values. The P value should be 12.564, the I value should be 0.56, the D value should be 0.49 and the L value should be 0.8. These gain values are essential to the auto-loop tuning process. Each time a new material is tested, it is advised to specify the correct P, I, D and L values in the console and only if those values are unknown then the material needs to be auto-loop tuned. After running the auto-loop tuning tool on the MTM 49 unidirectional carbon fiber material, the P (proportional gain) equaled 13.481 and I (integral gain) equaled 0.578. Both D and L equaled zero. Typically, the material needs to be auto-loop tuned in a load range where accuracy is needed. This range is typically, where the modulus of elasticity is measured in between 25% to 50% of ultimate stress as stated by ASTM D3039 Tensile Properties of Polymer Matrix Composite Materials [19]. If the material fails during the auto-loop tuning process, the actuator will shake violently and will not stop itself. Hit the red emergency stop button on the control panel or hit the red button on the Instron servo-hydraulic machine to power off the actuator. Start back up the machine and run the auto-loop tuning tool again at a lower force. 30 3.1.3 Tutorial on Specimen Protect The specimen is prone to premature failure due to high clamping forces exerted by the hydraulic clamps. Instron's Specimen Protect feature protects a specimen against this phenomenon. This feature is found inside the console, it is labeled Specimen Protect, and the symbol looks like small shield. Before using the Specimen Protect feature, go into the console, enter the Specimen Protect option menu and make sure the load threshold is set to 44 lbs. Clamp the bottom of the test specimen. Once the bottom of the specimen is clamped, move the actuator up until the top of the specimen sits in between the top crosshead's clamps. Turn on the Specimen Protect feature in the console and this will automatically move the bottom crosshead slightly up or down in order to prevent the specimen from experiencing more than 44 lbs. After both the top and bottom of the specimen are clamped, turn off the Specimen Protect feature and continue with the test. Every time a new specimen is inserted into the hydraulic clamps, this feature needs to be utilized in order to prevent premature failure. 3.2 Bluehill2 Test Preparation The machine was connected to a Windows desktop and from there Bluehill2 and the console were used to monitor machine inputs and outputs. According to Instron, the console software provides full system control from a PC: including waveform generation, calibration limit set up, and status monitoring. In real-time, Bluehill2 outputted various experimental results: strain values, load values, displacement values, and exc. All the raw data was outputted into an Excel file, which 31 could be used for post-processing calculations. 3.2.1 Bluehill2 Test Parameter Setup The main software of interest was the Bluehill2 software. In Bluehill2, the user has options of changing various testing parameters. Each test can be created and saved to a separate testing file, which can later be accessed when the user needs to conduct that type of test. Three different tests were created in the Bluehill2 software. The tensile test and tensile double shear test were created with the Bluehill2 software. Before a test file is created, it is required of the user to know what values are of interest for a specific structural test. The ASTM should exactly specify which the testing parameters should be used for the specific test. ASTM D5961 [18] suggested to test at a load rate of 0.05 in./min., to sample at a rate of at least 2 samples per second, and to output the extensometer displacement instead of the crosshead displacement. It also specified to run the test until a maximum force is reached and until the maximum force decreased by 30%. If the force didn\u2019t drop to 30% of the maximum; run the test until the pin displacement is equal to half of the hole diameter. For the pin displacement, the test ended once the extensometer read a displacement of 0.1 in. since that was the maximum range of the extensometer. The test specimen slipped in the grips when the force in the force vs. time plot flattens out, with respect to time, the specimen was slipping. The hydraulic pressure was manually set to 160 bar on the side of the machine. The fastener, which secured the Steel collars to the sides of the specimen, was hand tightened. Five different loading rates were 32 applied and adjusted accordingly inside the Bluehill2 software. 3.3 Instron Experimental Test Procedure The Instron start-up checklist was followed in the lab in order to start the machine safely. The first step of the checklist was to turn on the main power switch in the back of the lab. After turning on the main power switch, the next step was to turn on the Instron controller by pressing the power switch in the back of the Instron controller. Once the controller warmed up fully, a small blinking light appeared on the load calibration section of the controller. The calibrate button was pressed on the load menu of the controller. Next, the Cal button was pressed. Once the Restore button was pressed, the machine was fully calibrated even though it read \u201cCalibration not restorable.\u201d The desktop was turned on, and once the system booted up, the Bluehill2 software was started. As the software started up, it automatically started the console. The console is how the computer communicates with the Instron machine. The extensometer was plugged into the back of the Instron machine and it showed up under Strain 1 (in the Bluehill2 software). Once the extensometer was plugged in, it flashed in the console screen reminding the user that it needed to be calibrated. The extensometer\u2019s calibration was restored to a previous calibration. From this point on, the tensile test, or the double shear bearing test could be started. 3.3.1 Tensile Testing Procedure Before starting any ordinary tensile test, the user needed to have at least six tensile specimens 33 prepared for the test. For each tensile specimen, the thickness, width and gage length (distance between the tabs) were recorded. The Specimen Protect feature was also used when initially clamping the specimens. The first composite tensile specimen was tested to failure (without the extensometer), in order to find its ultimate failure load. A limit load was created for the extensometer and was decided based on the ASTM D3039 [19]. As stated in ASTM D3039 [19], the material's modulus of elasticity can be measured anywhere between 25% and 50% of its ultimate load or yield load (if it is a metal). The limit load was calculated by multiplying the 1st specimen\u2019s ultimate load by 0.25 and this value was specified in Bluehill2\u2019s end of test criteria. In Bluehill2 software, there is an option of recording the strain using an extensometer and once the limit load is reached, the test will pause allowing the user to remove the extensometer. Next, the remaining five composite tensile specimens were tested. The next composite tensile specimens were loaded in the machine and the extensometer was attached for each specimen. Figure 18 shows a composite tensile specimen (with an extensometer mounted on its surface). Once at the limit load, the extensometer was removed, and the test continued up to the ultimate load. Note that the initial modulus recorded by the extensometer was very accurate, and after removal of the extensometer, the crosshead took over and the accuracy declined. 34 3.3.2 Double Shear Testing Procedure Once the standard Instron startup procedure was completed, the tensile double shear Bluehill2 test method was started. In the Appendix, one can find a detailed tutorial on the tensile double shear Bluehill2 test method. Procedure A double shear tension, in ASTM 5961 [18], was followed closely. The user needed to make sure that all the dimensions were recorded such as specimen width, specimen length, and specimen thickness and distance between the edge of the specimen to the hole edge. The fixture used for the double shear test consisted of an assembly made up of three cold drawn Steel plates with two bolts and nuts connecting all three plates. The double shear fixture is shown in between the clamps on the left in Figure 19. The double shear fixture is shown, in the center, in Figure 19. The close-up of the collar-specimen assembly is shown, on the right side, in 35 Figure 19 as well. Each double shear joint specimen was sandwiched between two Steel plates, two Steel collars, four washers and a nut, which can be seen on the left and the center in Figure 20. The extensometer, as required by the ASTM 5961 [18], is fixed on the fixture with a small steel plate and two bolts, shown on the right in Figure 20. The extensometer's knife edge was carefully placed inside the slit of the specimen and secured with a rubber band. The nut which held the screw assembly together with the specimen was only hand tightened. In the Bluehill2 software, as stated earlier, the end of test occured if the maximum force droped by 30% or if the maximum extensometer displacement was 0.1 in. This end of test criteria worked perfectly for the 0.05 in./min., 0.1 in./min. and 1 in./min. loading rates. But for the 2 in./min. and 6in./min. loading rates, the maximum extensometer displacement was lowered to 0.05 in. At faster loading rates (above 2 in./min.), the actuator had problems stopping immediately at very small deflections (0.1 in.) so applying this adujstment prevented the extensometer from accidently breaking due to over-deflection of the crossheads. 36 37 CHAPTER 4: THEORETICAL SOLUTION METHOD In this chapter, information is given on the equations that were used to find all of the mechanical properties of the material used. The theoretical equations used to come up with the macromechanical behavior of a lamina and laminate are included as well. 4.1 Experimental Equations 4.1.1 Equations Used for Unidirectional Carbon Fiber and Aluminum Double Shear Specimens The width to diameter ratio of the specimens needed to be measured and recorded. Below, W, is the specimen width, and D is the diameter of the hole. \ud835\udc4a \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc4a/\ud835\udc37 The edge to diameter ratio of the specimens needed to be measured and recorded. \ud835\udc38 \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = (\ud835\udc54 + \ud835\udc37/2)/\ud835\udc37 The diameter to thickness ratio of the specimens was measured and recorded. Below h is specified as the thickness of the specimen. \ud835\udc37 \u210e \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc37/\u210e The bearing stress was calculated by dividing the force, P, by the force per hole factor, k (equal (1) (2) (3) 38 to 1 for double shear test), with the diameter of the whole, D and by the thickness of the specimen, h. \ud835\udf0e\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strength was calculated by dividing the maximum force, Pmax, by the force per hole factor, k, with the diameter of the hole, D and by the thickness of the specimen, h. \ud835\udc39\ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strain was determined from the extensometer displacement, \ud835\udeff\ud835\udc56 divided by the k, force per hole factor, and the diameter of the hole, D. \ud835\udf16\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udeff\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37) The bearing chord stiffness was only reported if there existed an offset bearing strength. The linear portion, where the bearing stress ranges from 25 \u2013 40 ksi, is the bearing chord stiffness region. \ud835\udc38\ud835\udc4f\ud835\udc5f = \u2206\ud835\udf0e\ud835\udc4f\ud835\udc5f/\u2206\ud835\udf16\ud835\udc4f\ud835\udc5f 4.1.2 Equations Used for Tensile Testing of Unidirectional Carbon Fiber and Aluminum Specimens The maximum tensile strength F, was calculated by dividing the maximum force by the cross- (7) (6) (5) (4) 39 sectional area A. \ud835\udc39 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/\ud835\udc34 The tensile stress, \ud835\udf0e, was calculated by dividing the force by the cross-sectional area, A. \ud835\udf0e\ud835\udc56 = \ud835\udc43\ud835\udc56/\ud835\udc34 The chord modulus of elasticity, E, was calculated by the difference two tensile stress points and their equivalent tensile strain points. \ud835\udc38 = \u0394\ud835\udf0e/\u0394\u03b5 The extensometer strain, \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 , was calculated by dividing the extensometer displacement, \ud835\udeff\ud835\udc56, by the extensometer\u2019s gage length, \ud835\udc3f\ud835\udc54. The gage length of the extensometer was always 0.5 in. \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 = \ud835\udeff\ud835\udc56/\ud835\udc3f\ud835\udc54 The axial and transverse strains were plotted with respect to axial force. The slope of the transverse strain vs. axial load, \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 , was divided by the slope of the axial strain vs. axial load, \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 , and this equaled the Poisson\u2019s ratio of the material. \ud835\udf10 = \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 / \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 (8) (9) (10) (11) (12) 40 4.1.3 Equations Used with the Rosette Strain Gage Using the Equations (13) \u2013 (15), one can find the principle strains in the x-direction, \ud835\udf16\ud835\udc65, y- direction, \ud835\udf16\ud835\udc66 and finally the shear strain in the xy-direction, \ud835\udefe\ud835\udc65\ud835\udc66 . The three different theta values, \u03b81, \u03b82, \u03b83 were all angles relative to the axial strain gage. The strain rosette was placed on the composite quasi-isotropic specimen's surface so that each strain gage was in 0\u00b0, +45\u00b0 and 90\u00b0. So \u03b81 equaled 0\u00b0, \u03b82 equaled +45\u00b0, and lastly \u03b83 equaled 90\u00b0. The principle plane stresses were also transformed with a transformation matrix to the desired angle, \u03b8. In the transformation matrix c = cos \u03b8 and s = sin \u03b8. Where A is considered the transformation matrix below. The transformed plane stresses, \ud835\udf0e\u2032, equaled the transformation matrix, A times the plane stresses, \ud835\udf0e. (13) (14) (15) (16) (17) 41 Once the three principle strains were calculated then a transformation matrix was used to transform each of the three strains to the desired angle, \u03b8. The transformed plane strains, \ud835\udf16\u2032, equals Reuter's Matrix, R, times the transformation matrix, A, by the inverse of the R matrix, and lastly times the plane strains. The modulus of rigidity, G, was found by dividing the modulus of elasticity, \ud835\udc38, by 2 times Poisson\u2019s ratio, \ud835\udf10, plus 1. \ud835\udc3a = \ud835\udc38 2(1+\ud835\udf10) 4.1.4 Equations Used for In-Plane Shear Modulus Testing of Unidirectional Carbon Fiber Specimens The maximum shear stress, \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 (18) (19) (20) (21) 42 divided by the cross-sectional area times two. \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 2\ud835\udc34 The shear stress, \ud835\udf0f12, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65divided by the cross- sectional area times two. \ud835\udf0f12,\ud835\udc56 = \ud835\udc43\ud835\udc56 2\ud835\udc34 The modulus of elasticity in the +/- 45\u00b0 shear modulus test, \ud835\udc38\ud835\udc65\ud835\udc65, was calculated by the difference two stress points and their equivalent strain points. \ud835\udc38\ud835\udc65\ud835\udc65 = \u2212\u0394\ud835\udf0e \u0394\u03b5 The shear chord modulus of elasticity, \ud835\udc3a12, was calculated by the Equation (25). \ud835\udc3a12 = 1/( 4/\ud835\udc38\ud835\udc65\ud835\udc65 \u2212 1/\ud835\udc381 \u2212 1/\ud835\udc382 + 2\ud835\udf1012/\ud835\udc381 ) Converting normal strain to shear strain is done by dividing the shear strain by 2. \ud835\udf16 = 1/2 \u2217 \ud835\udefe 4.1.5 Equations Used for Volume Fraction Testing of Cured Reinforced Resins The ignition loss of the specimen in weight percent is calculated by subtracting the weight of the specimen, W1, and the weight of the residue, W2. (22) (23) (24) (25) (26) 43 Ignition lost, weight % = [(\ud835\udc4a1 \u2212 \ud835\udc4a2)/\ud835\udc4a1 ] \u2217 100 4.2 Theoretical Equations 4.2.1 Equations Used to Find Laminate In-Plane Engineering Constants The NASA Composite Laminate Report [24] was used to find all the laminate in-plane engineering constants (or also known as in-plane laminate material properties). Before finding the laminate in-plane engineering constants, the assumptions must be stated. The quasi-isotropic laminate, with a layup sequence of [0 0 +45 -45 +45 -45 90 90]s, meant that it\u2019s symmetrical and balanced. A symmetrical laminate simplifies the calculations since all that is needed to determine the in-plane engineering constants is the A matrix since the B matrix is composed of all zeros. But for asymmetrical laminates, one would need A, B, and D matrices. The subscripted numbers after the matrix, for example, the 1 and 2 in A12, which is in the number in the first row and second column of the matrix. The theoretical method of finding the laminate in-plane engineering constants required knowledge of Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material properties [21]. The experimental datasheet material properties were used inside the theoretical method. In Equation (28), to find the modulus in the x-direction, the stress in the x-direction is divided by the strain in the x-direction. Which can be also written as force per length in the x-direction, Nx , divided by the laminate thickness, h all over the strain. (27) 44 The A matrix simplifies to the one below since the Bij matrix is all zeros. For each layer in the laminate one needs to solve for a unique Q matrix. If a laminate has 16 different layers then there will be 16 Q matrices and after they are all solved they need to be summed together to form the A matrix. Equations (29) \u2013 (40) will be needed in order to solve for each value in the Q matrix. For any angled ply, one uses Equations (33) \u2013 (40). (32) (31) (30) (29) (33) (34) (28) 45 There is no force (or stress in the other two directions) so those are set to zero. This further simplifies the equations. (35) (36) (37) (41) (40) (39) (38) 46 After further simplification of the Equations (42) \u2013 (44), Equation (46) was equal to our modulus in the x-direction, Ex , only after this number was divided by the laminate thickness, h. \ud835\udc38\ud835\udc65 = \ud835\udc41\ud835\udc65/(\ud835\udf16\ud835\udc65 0 ) \u2217 1/\u210e Next, the same exact method is applied to the y-direction. The modulus in the y-direction, Ey equaled Equation (48). \ud835\udc38\ud835\udc66 = \ud835\udc41\ud835\udc66/(\ud835\udf16\ud835\udc66 0 ) \u2217 1/\u210e Next, the same exact method is applied to the xy-direction. The shear modulus in the xy- direction was found, in Equation (50), Gxy , only after divided by the laminate thickness, h. (42) (43) (44) (45) (46) (48) (47) 47 \ud835\udc3a\ud835\udc65\ud835\udc66 = \ud835\udc41\ud835\udc65\ud835\udc66/(\ud835\udefe\ud835\udc65\ud835\udc66 0 ) \u2217 1/\u210e Poisson\u2019s ratio, \u03c5xy , of the laminate was calculated using Equation (51). Poisson\u2019s ratio, \u03c5yx , of the laminate can was calculated using Equation (52). (51) (52) (50) (49) 48 CHAPTER 5: EXPERIMENTAL RESULTS In this chapter, the experimental results are explained in detail. Section 5.1 explained the validation process, which was conducted, on all the strain measurement devices. The axial modulus of elasticity and Poisson\u2019s ratio of Aluminum were validated. Section 5.2 summarized the material testing which was conducted on the unidirectional carbon fiber material. Section 5.3 explained the unidirectional carbon fiber material property testing. Section 5.4 explained the quasiisotropic carbon fiber laminate material property testing. Section 5.5 explained the experimental results found for the Aluminum double shear specimens. Section 5.6 explained the quasi-isotropic carbon fiber double shear specimens\u2019 experimental results. 5.1 Experimental Measurement Device Validation Before any strain measurement device was used on a composite material, its accuracy needed to be validated with commonly known material. In this case, an Aluminum specimen was tensile tested with a strain gage orientated in the axial direction, and another strain gage orientated in the transverse direction. Since the axial strain gage, the extensometer and the crosshead were measuring axial strain, their readings were compared. In the past theses, students were using the crosshead displacement to measure the modulus of elasticity. Using the crosshead displacement was very unreliable and it is explained in more detail in the next sub section. 49 5.1.1 Extensometer vs. Axial Strain Gage vs. Crosshead Displacement The test set-up of the Aluminum specimen is shown in Figure 21. The three principle directions and the clamped sections of a standard uniaxial tensile specimen are shown in Figure 21. Below in Table 1, an Aluminum sample was loaded and unloaded three times up to a tensile stress of 25 ksi. The tensile stress was calculated using Equation (9). A tensile stress of 25 ksi lies in the material\u2019s linear elastic region and it is far away from materials yield stress of 35 ksi. Table 1 shows the comparison of experimental results between the extensometer, strain gage and crosshead. Table 1 also shows the dimensions of the Aluminum specimen. The strain gage and extensometer experimental results were validated with the Aluminum 2024-T4 datasheet mechanical properties [25]. The moduli of elasticity, in Table 1, are in msi (10E6 lbs./in.2) and were calculated using Equation (10). There was less than 1% error between the extensometer and the strain gage when compared to the Aluminum 2024\u2019s modulus of elasticity. When comparing to the crosshead, there was an error of 64%. The crosshead displacement is not as accurate as an extensometer or a strain gage, because the crossheads have compliance (inside the actuator assembly) which elongates as load is applied. The actuator assembly starts to elongate, which significantly affects the experimental strain results. The small standard deviation showed how consistent the results were when using the three different measurement tools and the testing machine. 50 showing the clamped sections and the 3 principle directions (right) 51 Below in Figure 22, one can see the three runs that were done using the extensometer and the axial strain gage. The crosshead displacement was excluded from Figure 22, since the experimental strain varied so drastically from the extensometer and the axial strain gage. The strain gage and the extensometer read very similar moduli of elasticity. The extensometer and strain gage proved to be reliable, so both measurement tools were used on the composite specimens. 52 5.1.2 Poisson\u2019s Ratio Validation Using Axial and Transverse Strain Gages The Poisson's ratio of the Aluminum 2024-T4 needed to be validated. In Figure 23, one can see the axial and transverse strains plotted with respect to the axial force. The axial strain gage output is shown in blue and the transverse strain gage is shown in red. A linear curve fit was applied to both sets of strain gage data and their respective linear equations are shown, as well. Poisson's Ratio equaled to a value of 0.26, for the Aluminum specimen, using Equation (13). 53 5.2 Summary of Carbon Fiber Material Properties Below in Table 2, the results accumulated from Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg material datasheet [21] are summarized. The values which have a (-) dash meant that they were not given in the material's datasheet. The strengths were specified in ksi, which is 10E^3 lbs./in. Table 3 shows the experimental material properties of the Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material, which were experimentally tested in the Cal Poly\u2019s Aerospace Composites Lab. Table 4 shows the experimentally tested and calculated quasi-isotropic laminate properties. Poisson's ratio, for Umeco\u2019s MTM49 Unidirectional pre-preg material was used from a previous report\u2019s value [26] of 0.25. All these material properties are further explained in the next few sections. Looking at Table 2 and Table 3, the 0\u00b0 compressive modulus is 22.3 msi and the 0\u00b0 tensile modulus is 26.6 msi. All of the tensile axial moduli of elasticity were similar but they were slightly higher than the compressive modulus specified in the datasheet. The tensile and compressive modulus should be very similar since the fibers are assumed to behave like an isotropic material. This material was not tested in compression since compression specimens need to be a lot shorter, in length (ideally have less than 0.5in. in gage length). An extensometer could not be mounted on the surface of the compression specimen since there is not enough room between the grips. The best way to measure, the compressive modulus of elasticity would be to use an optical high-speed camera, which records the relative motion through optics. 55 5.3 Unidirectional Carbon Fiber Material Property Testing 5.3.1 Test for 0\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens A laminate of 8 plies, [0]8T, was laid up and tested along the fiber direction. The 0\u00b0 direction is always the direction of the applied load in a uni-axial test. The ASTM 3039 [19] required a minimum of five specimens per test, and having more than five specimens helped improve the 56 consistency of the results. Each specimen was 10 in. long by 0.5 in. wide and with a thickness of 0.046 in. The ASTM 3039 [19] required curing 2 in. long by 0.5 in. wide Aluminum tabs on the specimens to prevent premature failures from occurring. The grip pressure was set to 160 bar. The tensile test began with testing one 0\u00b0 unidirectional carbon fiber composite tensile specimen (without an extensometer) to failure, to find its ultimate load. The limit load of 2,000 lbs. was chosen since the ultimate load was 4,600 lbs. The last six 0\u00b0 unidirectional carbon fiber composite tensile specimens were loaded to 2,000 lbs., and at 2,000 lbs., the test was paused so that the extensometer could be removed safely. Once the extensometer was removed, the Instron machine's crossheads took over in measuring the tensile strain. The load cell accurately measured the ultimate load up to an accuracy of +/- 45 lbs. In Figure 24, the 0\u00b0 unidirectional carbon fiber composite tensile specimens are shown to the left and one of the clamped post-test 0\u00b0 unidirectional carbon fiber composite tensile specimen is shown on the right. Figure 25 shows all seven of the tested 0\u00b0 unidirectional carbon fiber composite tensile specimens (each color represents a different specimen). Figure 26 shows the extensometer mounted on the 0\u02da unidirectional carbon fiber composite tensile specimen with two rubber bands. The compressive modulus was specified in the datasheet and the tensile modulus was not specified in the datasheet. The experimental tensile modulus was compared to the compressive modulus and the difference between the two values was 19%. A 17% difference between the tensile strength when compared to the datasheet values. 57 58 60 5.3.2 Test for 90\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens Next, a laminate of 14 plies, [90]14T, was laid up and tested along the matrix direction. A couple extra test specimens were tested to find the optimum hydraulic clamping pressure. The clamping pressure was initially set to 160 bar and once the specimen was clamped, it cracked. The hydraulic clamp pressure was reduced to 60 bar in order to prevent this premature failure from occurring. Eight specimens were tested since the material is very brittle and unpredictable. When examining the stress-strain plot of the 90\u00b0 unidirectional carbon fiber composite tensile specimens, the ultimate tensile stress determined the location of where the specimen would fail. As one can see in Figure 27, the four 90\u02da unidirectional carbon fiber composite specimens, which failed at an ultimate tensile stress of around 5 ksi, ended up breaking in the center. Whereas, the specimens which failed at a lower ultimate tensile stress failed near the emery cloth. The experimental results (between all the specimens) showed a very consistent modulus of elasticity. The ultimate tensile strength of the material varied, due to the matrix is very brittle. The failure of a brittle material is very unpredictable which one can see in the Figure 28. There was 17% difference between the datasheet 90\u00b0 modulus of elasticity and a 29% difference between the 90\u00b0 tensile strength when compared to the datasheet values. The ultimate tensile strength variations might have been due to the low accuracy of the load cell, which typically occurs at low loads (around 100 lbs.) since the accuracy of the load cell is +/- 45 lbs. Table 6 shows the experimental results of all the 90\u00b0 unidirectional carbon fiber composite tensile specimens. 61 63 5.3.3 Test for +/-45\u00b0 Shear Modulus Specimens After following ASTM D3518 [20], a laminate was created with an orientation of [+/- 45]4S which is a symmetric laminate with alternating positive and negative 45\u00b0 plies. Another way to write this is [+45 -45 +45 -45 +45 -45 +45 \u2013 45]s. The extensometer was placed at 0\u00b0 relative to the specimen. The axial modulus of elasticity, Exx, was recorded and Equation (25) was used to find G12. Equation (25) requires knowledge of E1, E2, and \u03c512. Eight shear modulus specimens, for consistency, were tested since ASTM D3518 [20] required a minimum of five shear modulus specimens. The shear modulus specimens are shown in Figure 29. The post-tested shear modulus specimens looked the same as the pre-tested shear modulus specimens (since the failure occurred in the matrix and not in the fiber). Figure 30 shows the highly consistent shear specimen results. Table 7 showed the detailed experimental results. There was 35% difference between the in-plane shear modulus and a 43% difference between the in-plane shear strength when compared to the datasheet values. Testing for the shear strength is not an easy task since the shear modulus specimen has to be in full shear state at failure. The tabs on the ends of the specimen create stress concentrations on the ends, which cause the specimen to fail prematurely. 64 66 5.4 Quasi-Isotropic Laminate Material Testing 5.4.1 Test for Quasi-isotropic Tensile Specimens The same test method used for the 0\u00b0 and 90\u00b0 specimens was used to test the carbon fiber quasi-isotropic tensile specimens. Once one quasi-isotropic tensile specimen was tested to failure, the ultimate load was recorded to be 6,500 lbs. The next six quasi-isotropic tensile specimens were tested with the extensometer up to a force of 2,000 lbs. The test paused once the force reached 2,000 lbs. and then the extensometer was removed. Figure 31 shows the quasi-isotropic tensile specimens before (on left) and after (on right) they were tested. The region circled in red showed the area where there was a fiber failure. Figure 32 showed a close-up of the tensile failure. In Figure 32, looking at the picture on the right, one can see the 0\u00b0 fibers on the outer layer held together, while in the center of the laminate, a crack began to form. The crack, in Figure 32, is circled in red. 67 68 From Figure 33, one can see a close-up of the strain rosette, which was on Specimen #1. Shown in Figure 34, a rectangular strain rosette (CEA- 06-120CZ-120 made by VishayPG) produced very accurate results. The rosette was placed on the quasi-isotropic tensile specimen at a 0\u00b0-45\u00b0-90\u00b0 orientation and the wires were soldered very accurately. Each strain gage resistance was checked (with a voltmeter) and read 120 Ohms. The strain gage worked correctly if the resistance across the strain gage read the correct resistance specified in the user manual. The quasi-isotropic tensile specimen #1 was tested one time by recording the strains in the 0\u00b0 direction, 45\u00b0 direction and 90\u00b0 direction. In addition, when the strain gage was being applied to the surface, an 80-grit sandpaper was applied to the surface of the quasi-isotropic tensile specimen. The sanding of the outer 0\u00b0 layer might have affected the material\u2019s mechanical properties. Table 8 shows this 8% difference in modulus of elasticity between the extensometer and the strain gage. From Figure 35, one can see the slight drop in stress (at 20 ksi) due to the pause in the test. The different line colors show the seven different quasi-isotropic tensile specimens that were tested. The main thing to note is the percentage difference between the modulus of elasticity found with the strain rosette and the extensometer. The ultimate tensile strengths were very consistent which showed from a very low standard deviation of 3.87 ksi. 69 70 72 5.4.2 Quasi-Isotropic Tensile Specimen #1 In-Plane Experimental Material Properties Figure 36 shows experimental strain values of the extensometer, the axial strain gage, the +45\u00b0 strain gage and the transverse strain gage. A slight variation exists between the axial strain gage and the extensometer because the extensometer was not placed in the same location as the strain gage. The sanding error, like stated in the previous section, might have also contributed to the error of 8%. The test was stopped at a force of 2,000 lbs. A linear curve fit was applied to all of the three separate strain gage readings and are shown in Figure 36. Next, the Poisson\u2019s ratio of the quasiisotropic tensile specimen was found using Equation (12) and in-plane shear modulus of the quasiisotropic laminate was found using Equation (23). The axial modulus of elasticity was found using Equation (10). 73 5.4.3 Quasi-Isotropic Laminate In-Plane Theoretical Material Properties The theoretical material properties were found using the NASA report on Basic Mechanics of Laminated Composite Plates [24]. In Section 4.2.1, one can find the equations used to calculate the theoretical material properties. Before these equations could be used, a few assumptions were made: (1) The material to be examined is made of up of one or more plies (layers), each ply consisting of fibers that are all uniformly parallel and continuous across the material. The plies do not have to be of the same thickness or the same material. [23] (2) The material to be examined is in a state of plane stress, i.e., the stresses and strains in the through-the-thickness direction are ignored. [23] (3) The thickness dimension is much smaller than the length and width dimensions. [23] The values in Table 9 were needed in order to come up with the theoretical material properties. Table 9 shows the values that were applied into the laminate theory since the laminate theory required knowledge of the material properties of one layer of the unidirectional carbon fiber material. With the help of a strain rosette and the use of Equations (13) - (15), all the in-plane principle strains could be found. 74 Below in Table 10, one can see the calculated experimental material properties using the strain gage rosette. Three different in-plane laminate material properties were calculated based on three different force values (1500 lbs., 1750 lbs. and 1900 lbs.). The theoretical material properties were in agreement with the experimental material properties since the error between the modulus of elasticity was only around 10% and only 2% for the Poisson\u2019s ratio. The low standard deviation showed the reliability of the testing equipment and the strain measurement devices. 75 5.5 Fiber Volume Fraction Test ASTM D2584 [27], Standard Test Method for Ignition Loss of Cured Reinforced Resins, was followed closely. Three volume fraction specimens were tested inside the furnace shown on the right in Figure 37. On the left of Figure 37, one can see a fiber volume fraction test specimen. The fiber volume fraction specimen was placed on top of an Aluminum plate. While the furnace was preheated to a temperature of 1000\u00b0F, the Aluminum plate was weighed and each fiber volume fraction specimen was weighed in grams and then converted to lbs. in order to keep the units consistent. The measuring scale had a least scale reading of 0.1 g. The dimensions of each fiber 76 volume fraction specimens were carefully measured and recorded. Each specimen was placed on the Aluminum plate and left inside the furnace for one hour. Once all the epoxy burned off, the fiber volume fraction specimen was weighed and this was weight of the fibers. The initial weight of the fiber volume fraction specimen minus the final weight of the fiber volume fraction specimen was the weight of the resin (matrix). After doing some simple calculations, along with using the cured resin matrix density of 1.24 g/cm3(from the material\u2019s datasheet); the fiber weight fraction along with the fiber volume fraction was calculated and compared to the datasheet. In Table 11, one can see the three different fiber volume fractions along with the fiber weight fractions. The fiber volume fraction specimen dimensions are crucial to the determination of the fiber volume fraction. The measured thickness of the fiber volume fraction specimen varied from 0.1 in. to 0.103 in., which meant that the heat press cooked unevenly. The slight variation of the specimen\u2019s thickness affected the volume fraction by 4%. The 8.3% difference between the experimental fiber volume fraction and the datasheet fiber volume fraction varied because not enough pressure was applied to the laminate during the curing process. The lower fiber volume fraction of 0.55 compared to 0.6 meant that there was more resin in the laminate. Not enough resin was squeezed out in the cure process. The pressure applied by the heat press was limited, so achieving the optimum fiber volume fraction (of 0.6) was difficult. The fiber volume fraction significantly affected all of the material property testing which was conducted on the Umeco MTM 49 unidirectional material. A low standard deviation showed that the data was very consistent. 78 Section 5.6 was conducted in order to validate the numerical model with the experimental data. Modeling a metal before modeling a composite is very important because metals behave in a more predictable fashion. Metals are a lot simpler to model since they exhibit isotropic behavior whereas composites exhibit orthotropic behavior. The material property inputs for an isotropic material are much less than for a composite material. For a composite, the user has to input three different moduli of elasticity, three moduli of rigidity, and three Poisson\u2019s ratios. For metals, the user only inputs the modulus of elasticity and the Poisson\u2019s ratio. In this validation, Aluminum 2024-T4 was used as the material of choice. Once the linear elastic model was validated with a metal, then any other material should be validated as well, but only for the linear elastic region of the material. This also validates the boundary conditions and any interactions, which were used in the numerical model. 5.6 Aluminum 2024-T4 Double Shear Test The Aluminum 2024-T4 double shear specimens were tested on the same double shear fixture as the composite double shear specimens. From Figure 38, one can see the bearing stress vs. bearing strain response of the five tested Aluminum double shear specimens. The first section of the bearing stress vs. bearing strain plot (the flat initial region) is the strain correction region. Compliance between the Instron parts, along with the clamps, occurred upon initial loading of the specimen. The deformation of all the internal parts of the Instron machine in the strain correction region. The linear elastic region, (shown inside the red square in Figure 38) for the Aluminum, was between 5 ksi and 40 ksi and after this region; the material experienced a non-linear behavior 79 up to its ultimate bearing strength. The strain correction region and the non-linear region were removed, which can be seen in Figure 39. The non-linear region and the strain correction region were not part of the numerical model. Figure 38 showed that specimen #5 failed at an ultimate bearing stress of 130 ksi and the other four specimens failed around 114 ksi. The extensometer\u2019s knife-edge slipped on the face of specimen #1 through #4, but for specimen #5, the extensometer did not slip. The linear elastic region can be seen in Figure 39. The specimen alignment might have caused the variations in the linear elastic strain values. The ultimate bearing strength matched up the Aluminum 2024-T4 material\u2019s datasheet [25]. Table 12 shows the experimental results of the Aluminum double shear specimens. Both the yield and ultimate strengths were calculated in the Table 12. Figure 40 shows a bearing type of failure, which occurred in all the Aluminum double shear specimens. Figure 41 shows the Aluminum double shear specimens before and after they were tested. The region circled in red shows the area where the failure occurred. Each specimens\u2019 hole diameter increased in size and also each specimens\u2019 hole diameter did not go back to its original shape once the load was removed, which showed that the material reached a plastic deformation. 80 82 5.7 Composite Double Shear Test As one can see in Figure 42 (from a paper by Yi Xiao [28]), the composite double shear specimens behaved differently than Aluminum double shear specimens. Recall, all the composite double shear specimens were manufactured with a quasi-isotropic laminate orientation of [0 0 +45 83 -45 +45 -45 90 90]s. The 4%D is considered the bearing strength of the material. The composite double shear specimens held load (without failing) up to the knee point. At the knee point, the first ply failed (after this point, the material properties started to degrade) and the slope of the curve was reduced. The load increased up to the final point, also known as the ultimate bearing strength of the material, where it maxed out. One positive thing about designing a structure to fail in bearing, as opposed to net-tension or shear-out, is that the force dropped 30% of the maximum load. Whereas, in net-tension or shear-out failure, the load dropped down to zero. Figure 43 shows a close-up of the bearing failure, which occurred on the composite double 84 shear specimens. As one can see, there is an excessive amount of damage near the pin location. All of the specimens exhibited a similar type of failure, so there was no need to take a picture of each of the failed specimens. Figure 44 shows ASTM 5961\u2019s [18] failure codes used to characterize any of the failure modes seen in a composite double shear test. The failure code, B1I, is used throughout the rest of the experimental section, which signifies a bearing type of failure. 85 86 5.7.1 Curing Cycle 1 (Cytec\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test Figure 45 shows the composite double shear specimens before and after the double shear test. In Figure 45, on the right, highlights the crushing regions, in red. All the failures are consistent. Eight specimens were tested for each of the five loading rates. For load rate 0.1 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. When looking at the alternate cure cycle experimental data, in Tables 13 & 14, an interesting 87 trend appeared. At slower loading rates, the composite double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min. the composite double shear specimens failed at an average stress of 64.4 ksi and 63.5 ksi whereas at 1 in./min., 2 in./min. and 6 in./min. the composite double shear specimens failed around 52.3 ksi. Looking at all the different loading rates, it seemed as if all the composite double shear specimens had a similar knee point. 2 in./min. and 6in./min. showed a greater drop in load after the composite double shear specimens reached their ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. did not show a huge drop in load after the specimens reached the ultimate load. 89 The maximum values of all the plots, in Figure 46, were the ultimate bearing strengths. When looking at Figure 46, one can see that as the loading rate increased the non-linear region decreased in size. The red-circled sections, in Figure 46, show how the non-linear region decreased in size. The linear region does not change as drastically as the non-linear region. As the load rate increased, the rate of damage also increased which explained the reduction, in size, of the non-linear region. 90 Looking at all of the load rates, the moduli in the non-linear regions are lower than the linear elastic regions. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. 91 5.7.2 Curing Cycle 2 (Umeco\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test When looking at the datasheet cure cycle experimental data, in Tables 15 & 16, a similar trend appeared. At slower loading rates, the double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min., the specimens failed at an average stress of 62.7 ksi and 67.7 ksi, whereas at 1.0 in./min., 2 in./min. and 6 in./min., the specimens failed around or under 52.0 ksi. It also looks like at 2 in./min. and 6in/min. show a greater drop in bearing strength after the specimen reaches its ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. do not show a huge drop in strength after the specimens reach the ultimate load. In general, fast loading causes more damage to the specimen which overall reduces the specimen's ability to carry load. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. Eight specimens were tested for each of the five loading rates. For load rates 2 & 6 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. 93 When looking at Figure 47, one can see that as the loading rate increased the non-linear region decreased in size. In Figure 47, the red-circled section also showed the non-linear region decreased, in size, with increased loading rate. 94 5.7.3 Comparison between Cure 1 & Cure 2 In Figure 48, it is very clear that as loading rate increased, the ultimate bearing strength of the 95 material decreased regardless of the cure cycle. Further research can be done on how different cure cycles can affect the bearing response of a composite double shear specimen. Making the matrix less brittle and more ductile might improve the ultimate bearing strength of the material. Cure cycle 2 (Umeco\u2019s cure cycle) was 2% stronger in bearing when compared to the cure cycle 1 (Cytec\u2019s cure cycle). The MTM 49 Unidirectional carbon fiber pre-preg material was very sturdy by not being affected by an alternate cure cycle. 5.7.4 Comparison Between The Aluminum Double Shear Specimens & Quasi-Statically Loaded (0.05 in./min.) Composite Double Shear Specimens Aluminum is standardly tested at quasi-static load rate of 0.05 in./min, since it\u2019s strain rate independent [30] (not affected by different loading rates). The Aluminum double shear specimens 96 performed a lot better in bearing than the composite double shear specimens. Since the carbon fiber is more brittle by nature, its ultimate bearing strength is significantly lower than Aluminum. of the Aluminum double shear specimens was around 118 ksi and the ultimate bearing strength of the composite double shear specimens was around 63 ksi. That means that carbon fiber is 53% weaker than Aluminum 2024-T4 in a double shear joint configuration. The Aluminum double shear specimens yielded at around 40 ksi compared to the composite double shear specimens, which yielded at 30 ksi. As one can see from the bearing stress vs. bearing strain graphs, there is a huge difference in ultimate bearing strength between of both materials. It is interesting to note that both materials showed a strain correction region. The Aluminum double shear specimens and the composite double shear specimens did not catastrophically fail (they deformed without significantly dropping the applied load). 97 CHAPTER 6: NUMERICAL ANALYSIS Chapter 6 explains the overall finite element approach. Section 1 introduces the finite element model and different considerations, which were applied to the model. Section 2 explains the idea behind a convergence plot and its importance. Section 2 explains what factors influenced the numerical results. 6.1 Finite Element Analysis Introduction Once a Finite Element Analysis model is validated with experimental results, it can then be used in the design process. Abaqus 6.14-1 was used to model the double shear bearing test experiment conducted. All the different Finite Element software work very similarly and the only difference between them is their program interface. However, they all essentially break up the model into small elements and calculate the stress state on each element. The material properties are assigned to the elements and then, the boundary conditions and loads are applied to the model. In some cases when there are two or more parts, one might have to define different types of interactions or constraints for the model (for example, how those parts move relative to each other). The numerical software also predicts non-linear behavior, which requires a lot more material properties. Plasticity required the user to model the damage done on the material as load increased, which meant, implementing a degradation model. First, a numerical model was created and validated for the Aluminum 2024-T4 double shear 98 specimen. The Aluminum numerical model was only validated through the linear elastic region of the experimental data, which was shown in Figure 39. The Aluminum numerical model was adjusted for the composite specimen and the experimental results were compared to the numerical results. Abaqus keeps the units consistent, so when working with US Customary units make sure to stay consistent with the units, if using inches, stick to using inches. The displacement plots should be in the same units as one started with, and the stresses should be in pounds per square inch (psi). 6.1.1 Geometric Definitions The numerical model contained four parts. The two side plates, double shear specimen, and pin were modeled as deformable 3D solids. Both steel plates along with the double shear specimen were partitioned. The steel collars and center middle plate were neglected for simplicity. All the bolts, nuts and washers were also neglected in the model for simplicity reasons. 6.1.2 Material Creation, Section Assignments, & Meshing All the dimensions were defined in English units and the dimensions for each of the parts came from the fixture design. The fixture used in the numerical model was simplified. All the composite material properties were inputted in the elastic engineering constants. Table 17 showed the material properties, which were, applied to the Aluminum numerical model. A Steel solid homogeneous section and an Aluminum solid homogeneous section were created. 99 A composite layup section was applied to the composite double shear specimen and the element type was set to solid. Table 18 shows the material properties that were applied to the composite double shear specimen. In the composite layup section, the user is able to set the element stacking direction, the coordinate system, and the rotation axis. The user can also specify the laminate orientation and select the region for each ply within the model. In the Appendix, there is a tutorial of how the Abaqus composite double shear specimen was modeled. A single layer of unidirectional carbon fiber material is considered a transversely orthotropic material, where E2 is equal to E3 and G12 is equal to G13. E2 and E3 are both considered the matrix and E1 is considered the fiber. One thing to note was that the compressive modulus in the 1- direction (axial) was slightly lower than the tensile modulus, which was found in the Experimental section of the report. The Poisson\u2019s ratio in the 23-direction and the shear modulus in the 23- direction are usually very difficult to find experimentally. Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager was used to find some of the material properties that could not 100 be found experimentally. In the Appendix, one can find the tutorial on how to use Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager. One can also find a step-by-step Abaqus tutorial on the composite double shear specimen. Parts of the step-by-step tutorial were found from D.S. Mane [29] . The parts were individually partitioned which made meshing them very simple. Once the partition was created, the user needed to use the Seed Edge command, then select whole part, and for method select \u201cby number\u201d. As indicated below in sizing control, the user is able to assign the number of elements from one to however many. The convergence plot was constructed using four different nodes per element. The element\u2019s relative thickness was set to 0.5 since there were only two elements that made up the thickness of the part. 101 6.1.3 Assembly, Interactions & Steps The whole assembly was modeled very similarly to the experiment. Each part was given a dependent instance and no tie constraints were used in the model. A contact step and a load step were added to the analysis. The contact step initiated the contact between the pin and the steel plates and also the pin and the specimen. The load step served to apply load to the analysis once full contact was established. The pin was not constrained to the specimen with a tie constraint because that implied a condition similar to being welded. So in contrast, a surface-to-surface interaction was established between the pin, the steel plates and the specimen. The sliding formulation selected was finite sliding. The pin was set as the master surface and the slave surface consisted of two surfaces. One was the surface in contact with the pin and the inner side of the specimen and the other was the surface in contact with the pin and the inner side of both steel plates. The slave adjustment was set to a value of 0.007 in. A contact property with a tangential behavior (the friction formulation was set to penalty and the friction coefficient was set to 0.46). In addition, a normal behavior contact property with the pressure-overclosure was set to \u201cHard\u201d Contact; constraint enforcement method was set to default, and allowed separation after contact. 6.1.4 Boundary Conditions & Loads The boundary conditions applied to the model needed to be assigned carefully. The top face of the specimen (opposite face with the hole) was fully fixed in the x, y and z directions. This was 102 similar to the clamped condition, which is applied by Instron\u2019s crossheads. The second boundary condition that was applied was on the outer pin surface and the inner hole surfaces of the steel plates and the bearing specimen. In the contact step, the pin, steel plates and specimen were not allowed to move in the x, y and z directions. The load step was modified to allow the side plates, pin and specimen to move in only the y-direction. The combined load of 600 lbs. was applied to both of the bottom faces of the steel plates. This was done by applying the load, in the load step, as a total force distribution pressure load. The loading condition used in the model was similar to the experimental loading condition, where a fraction of the force is applied at each time interval. Some elements in the model experienced plastic deformation only when the applied load was over 800 lbs. This meant that certain elements were in stress state beyond their linear elastic limit. The ultimate force was not predicted, by the numerical analysis, since that occurred in the non-linear region. 6.2 Numerical Results This section provides the explanation of the convergence plot and talks about the factors, which influenced the numerical results. In Chapter 7, the numerical results are explained in detail. 6.2.1 Convergence Plot For the numerical model, a partition was created on the face of the specimen. Taking time to draw a symmetrical and neat partition prevented the mesh from becoming unsymmetrical and 103 prevented unusual results. The partitioned double shear specimen is shown in Figure 49. In Figure 50, one can see a close up of the partitioned region around the hole. After a partition was created, the user was able to assign a specific amount of elements using the Seed Edge command. Here the user is able to set the total amount of nodes per element to any value. For the convergence plot, 2, 6, 8, and 10 nodes per element were chosen, and the final vertical deflection at the pin was compared. A convergence plot was created to see if adding more elements to the model actually improved accuracy. Knowing the optimum amount of elements for the least amount of time for the model to complete is very important in the design process. As one can see from Figure 51, as the total amount of nodes per element increased, the deflection did not change significantly. Using more than six elements per node did not significantly improve accuracy, but it did take longer to run. 6.2.2 Factors That Influenced the Numerical Results Increasing the total amount of elements through the thickness of the part, did not significantly affect the pin deflection results. Changing the axial modulus (from tensile to compressive) significantly affected the pin deflection results. The compressive axial modulus was imported into Abaqus rather than the tensile modulus, because the double shear test is mainly a compression type of loading. The fibers are in compression around the hole. When initially assuming a frictionless contact (when the frictional coefficient equaled zero) the specimen ended up colliding with one of the side plates. Changing the frictionless coefficient 104 from zero to 0.46 helped prevent the specimen from colliding with one of the side plates. 105 106 CHAPTER 7: COMPARISON BETWEEN EXPERIMENTAL & NUMERICAL DOUBLE SHEAR RESULTS The slope of the reaction force vs. pin displacement was compared between both the experiment data and the numerical model. First, the numerical Aluminum model was validated. Then the numerical composite model was validated. 7.1 Numerical Aluminum Model Comparison to Experimental Results Looking at Figure 59, the region highlighted in red was due to the compliance in the testing assembly. The bearing stress vs. bearing strain plot was then converted to a load (reaction force in the y-direction) vs. pin displacement plot. All of the specimens were plotted up until the linear region. Looking at Figure 60, of the five tested Aluminum double shear specimens, the numerical results only matched up with one. The four other Aluminum double shear specimens might have slipped with respect to the extensometer\u2019s knife-edge. One way to tell is by the lower load (reaction force in the y-direction) vs. pin displacement slopes. In Table 19, the total error when comparing the experimental slope to the numerical slope was 16%. Misalignment of the specimen might have caused this significant error to occur. 107 108 7.2 Composite Numerical Model Comparison to Experimental Results Figure 54 showed the load (reaction force in y-direction) vs. pin displacement response of the 0.05 in./min. composite double shear specimens that were cured to the recommended datasheet cure cycle. Three of the eight tested composite double shear specimens at 0.05 in./min. did not slip. The strain was corrected using the same method that was applied to the Aluminum double shear specimens. Of the eight carbon fiber specimens that were tested, only three of them closely matched up to the numerical results. The numerical model was loaded to 600 lbs., which was still within linear elastic limit of the material. The load (reaction force in y-direction) vs. pin displacement slopes between all the experimental specimens shown were compared to the numerical model. In Table 20, the average error between the numerical slope and the experimental slopes was about 7.1%. Alignment is a huge factor, which can affect experimental results quite significantly. There will always be error between the experimental and numerical results. The numerical 109 results are the idealized results and the experimental results have so many factors, which can influence their results. Errors from 7% to 16%, for both the aluminum double specimens and the composite double shear specimens, are actually quite reasonable because there is always error in the manufacturing process, displacement measuring equipment, load cell, specimen alignment exc. 111 CHAPTER 8: CONCLUSION The first important contribution of this study was to see how different loading rates affected the ultimate bearing strength of a composite material. One can see that at 0.05 in./min. and 0.1 in./min. (for both cure cycles) the composite double shear specimens carried more load compared to higher load rates of 1 in./min., 2 in./min. and 6 in./min.. All of the specimens failed in bearing and not in net-tension or shear-out. The second important contribution of this study was to see how the recommended datasheet cure cycle and the alternate cure cycle affected the ultimate bearing strength. The two different cure cycles behaved very similarly under the five different loading rates. The average ultimate bearing strength of the Aluminum double shear specimens was 118 ksi and for the composite double shear specimens it was 65 ksi. The experiment showed that carbon fiber material is significantly weaker, in a double shear tensile loading configuration, compared to Aluminum. Ductile materials, like Aluminum for example, handle the double shear tensile loading configuration a lot better than the carbon fiber material, which is brittle. Each carbon fiber sheet is relatively thin which is also very poor for carrying bearing stress. Usually what designers do is use inserts inside and around the hole if they need to improve the bearing strength of a composite joint. The inserts help redistribute the stress concentrations (which are caused by mechanical fasteners) and prevent the brittle material from cracking. The inserts are usually made from ductile materials, like fiberglass or Aluminum. 112 8.1 Recommendations The experiments were carried out using carbon fiber unidirectional pre-preg tape. Similar research can be done using various other materials like: kevlar, fiberglass, or even hemp. Similar testing can be done using a single shear joint configuration. Various carbon fiber types can be tested as well. MTM-28 material is a thicker type of unidirectional fiber, which would be very interesting to test. A high-speed video camera would be a more efficient way to monitor deflection since the extensometer's range was the limiting factor in the data capture. A more in depth case study can be conducted on different cure cycles of composite resins. The pre-load function in the Bluehill2 software can be utilized in order to try to eliminate some of the strain correction region. In addition, a more in-depth experimental analysis can be conducted on the knee point region of the composite (carbon fiber) double shear specimen. 113 REFERENCES 1. Airbus Versus Boeing-Composite Materials: The sky's the limit. http://www.lemauricien.com/article/airbus-versus-boeing-composite-materials-sky-slimit. 2. Lessard, L.B. (1995). Computer aided design for polymer-matrix composite structures. In S.V. Hoa (Eds.), Design of joints in composite structures. New York: Marcel Dekker. 3. Baker, A. (1997). Composites engineering handbook. In P.K. Mallick (Eds.), Joining and repair of aircraft composite structures. New York: Marcel Dekker. 4. Okutan, B. (2001). Stress and Failure Analysis of Laminated Composite Pinned Joints. Journal of Composite Materials, 19. 5. Chen, J.C., Lu, C.K., Chiu, C.H., & Chin, H. (1994). On the influence of weave structure on pin-loaded strength of orthogonal 3D composites. Composites, 25, No: 4, 251-262. 6. Quinn, W.J., & Matthews F.L. (1977, April). The effect of stacking sequence on the pin- bearing strength in glass fiber reinforced plastic. Journal of Composite Materials, 11, 139- 145. 7. Liu, D., Raju, B.B., & You, J. (1999). Thickness effects on pinned joints for composites. Journal of Composite Materials, 33, 2-21. 8. Stockdale, J.H., & Matthews, F.L. (1976, January). The effect of clamping pressure on bolt bearing loads in glass fiber-reinforced plastics. Composites, 34-39. 114 9. Kim, S.J., & Kim, J.H. (1995). Effects of geometries, clearances, and friction on the composite multi-pin joints. AIAA Journal, 34, No: 4, 862-864. 10. Hyer, M.W., & Klang, E.C. (1985). Contact stresses in pin-loaded orthotropic plates. Journal of Solids and Structures, 21, No: 9, 957-975. 11. Pierron, F., Cerisier, F., & Lermes, M.G. (2000). A numerical and experimental study of woven composite pin-joints. Journal of Composite Materials, 34, No: 12, 1028-1053. 12. Chang, Fu-Kuo, Scott, R.A., & Springer, G.S. (1982, November). Strength of mechanically fastened composite joints. Journal of Composite Materials, 16, 470-494. 13. Ger, G.S., Kawata, K., Itabashi, M.: Dynamic tensile strength of composite laminate joints fastened mechanically. Theor. Appl. Fract. Mech. 24(2), 147\u2013155 (1996). 14. Li, Q.M., Mines R.A.W., Birch R.S. (2000, September). Static and dynamic behavior of composite riveted joints in tension. 15. United States Naval Academy (USNA). (2003). Composite Orientation Code. http://www.usna.edu/Users/mecheng/pjoyce/composites/Short_Course_2003/7_PAX_Sh ort_Course_Laminate-Orientation-Code.pdf 16. Kretsis, G., & Matthews, F.L. (1985, April). The strength of bolted joints in glass fiber/epoxy laminates. Journal of Composite Materials, 16, 92-102. 17. Yeole, Amit. (2006, December). Experimental Investigation and Analysis for Bearing Strength Behavior of Composite Laminates. 115 18. Anonymous, \u201cStandard Test Method for Bearing Response of Polymer Matrix composite Laminates,\u201d ASTM Standards, Designation: 5961/5961M-05. 19. Anonymous, \u201cStandard test method for tensile properties of fiber-resin composites,\u201d ASTM Standards, Designation: 3039-76. 20. Anonymous, \u201cStandards. In-plane shear stress-strain response of unidirectional reinforced plastics,\u201d ASTM Standards, Designation: 3518-76. 21. Umeco, \u201cMTM 49 Series Pre-preg System \u2013 Unidirectional Material Properties.\u201d 22. Cytec, \u201cMTM 49-3 \u2013Unidirectional Material Properties.\u201d 23. Instron, \u201cInstron 8801 Servo-hydraulic Machine Photo.\u201d http://www.instron.us/en-us/ 24. Nettles, A.T., (1994, October) \u201cBasic Mechanics of Laminated Composite Plates.\u201d 25. ASM Aerospace Specification Metals Inc., \u201cDatasheet Mechanical Properties of Aluminum 2024-T4.\u201d 26. Anonymous, \u201cProject 1 Report\u201d ME-412. 27. Anonymous, \u201cStandard test method for ignition loss of cured reinforced resins,\u201d ASTM Standards, Designation: 2584-02. 28. Xiao, Yi. \u201cBearing strength and failure behavior of bolted composite joints (part II: modeling and simulation). 29. De, S. MANE 4240/CIVL 4240: Introduction to Finite Element. Abaqus Handout. 30. Semb, Evind. \u201cBehavior of Aluminum at Elevated Strain Rates and Temperatures.\u201d 116 APPENDICES A.1. Drawings for the Fixture Assembly 117 118 A.2. Tutorial on Bluehill2 Test File Setup Various settings were changed inside the BlueHill2 software. Below, I will show a couple of the parameters that were changed. Navigating through the menus is self-explanatory. In the Control submenu, the load rate was changed for each test. The quasi-static case was tested first at a load rate of 0.05 in./min. The second load rate, which was tested, was 0.1 in./min., the third was 1 in./min., the fourth was 2 in./min. and the fifth speed, which was tested, was 6 in./min. 119 The end of test criteria was changed to the ASTM specification. End of test 1 specifies the drop in the load of 30% the peak value and end of test 2 is specified as an extensometer displacement of 0.1 in. The extensometer shows up at Displacement (Strain 1) as a separate channel. 120 In the Control submenu, the sampling rate was changed from the default rate of 10 samples/sec to 3 samples/sec as required by ASTM D5961. This change showed a significant reduction of noise within the extensometer displacement readings. A value of 500 ms was adjusted for the time channel and the load sampling rate was left to default interval of 56 lbf. 121 Below in the Control submenu, the source of tensile strain was changed from the BlueHill2 default channel of \u201cTensile Strain\u201d to the \u201cStrain 1\u201d. The extensometer shows up as \u201cStrain 1\u201d. 122 Bluehill2 also has the option of calculating numerous parameters. In my experimental testing, I needed to calculate the ultimate bearing strength so I picked User Calculation. Then Bluehill2 gives you an option to define various variables like: D (diameter of hole), k (calculation factor for double shear k = 1), Pmax (maximum force carried by the specimen prior to failure), and t (defined as the thickness of the laminate). After all of your variables are defined, the equation designer tool 123 is used to create your equation of interest. In the Results submenu, the user is able to pick exactly which values he/she wants to output while in the test screen. The results are outputted as a column of values for each of the different test specimens. I wanted to output all of these parameters below while I was conducting my tests. 124 In the Graph submenu, the user is able to output two real-time changing graphs. For graph 1, I chose to output Instron crosshead displacement vs. load and for graph 2 I chose to output extensometer displacement vs. load. The X-Data was set to either Extension (for Instron crosshead displacement) or Displacement (Strain 1) (for extensometer displacement. The Y-Data was set to Load for both graph 1 and graph 2. 125 In the Raw Data submenu, Bluehill2 has a great function, which allows the user to export any given output of experimental data into a .csv file. This file can later be opened up with Excel and used to calculate various experimental stresses, strains and other parameters of interest. For my experimental testing, I was interested in outputting: time, crosshead displacement, extensometer 126 displacement, load and corrected position. The last bit of raw data, which needed to be outputted, is shown below. This set of data is saved onto the same .CSV file as the one specified in the previous screen. This set of data is located in its own set of two columns in the .CSV file. 127 A.3. Tutorial on Finding the Unknown Engineering Constants Autodesk created a very powerful tool, which can help the user figure out unknown engineering constants of a ply. For example from the experimental results, the user is able to experimentally determine E1, E2, G12 and \u03c512. Shown below are all the values, which the user inputs into the Autodesk Simulation Composite Analysis 2015 Material Manager. Make sure to label the 128 material a unique name and choose the correct units. The fiber type should be carbon intermediate for the MTM 49 since it is not the ultra-high fiber modulus. The volume fraction should be the one, which was found experimentally in the Results chapter, of 0.55. In Figure 67, in the first row of the Ultimate Lamina Strengths the user inputs the tensile strength in the 0\u00b0 and the 90\u00b0 directions. In the second row, the user inputs the compressive strength in the 0\u00b0 and 90\u00b0 directions and finally, in the last row, the user the user inputs the in-plane shear strengths. 129 In Figure 68, the user will input the known modulus of elasticity into the Lamina Elastic Constants section. The in-plane Poisson's ratio, which was assumed to be around 0.244, was used from a previous paper, which found the material property experimentally on the same MTM 49 Unidirectional material. The in-plane shear modulus was inputted from the experimental testing. 130 The key is to assume a value if you do not know what it is. After all the values have been inserted into the program go into the File, menu and then click optimize. It will ask you if you want to save the material properties somewhere and all you do is specify where you want to save the data. It will take a couple seconds to optimize the values accordingly. A.4. Tutorial on Outputting Force vs. Pin Deflection from Abaqus The pin deflection needed to be monitored for one node on the specimen. The area of interest is shaded in dark blue and the red dot signifies which node was monitored for its vertical deflection. In Figure 70, one can see the deflection in the y-direction, which occurs around the hole. This hole 131 is a localized compression zone. 132 Next what was needed was to have a force vs. time graph. The top most nodes on the specimen were fixed using the encastre boundary condition. The reaction force in the y-direction was captured for all the nodes that make up the top of the specimen. Once all the reactions at each nodes were captured, the whole region was summed up. Under create XY plot click ODB field output and then click continue. Under the Variables tab, find the Output variable box, and in the position menu, click Unique Nodal and then go into RF: Reaction Force and check the RF2 button. Since we are interested in the reaction force in the y-direction (2 direction). Next, click the Elements/Nodes tab and then pick the from viewport button and then click Edit Selection. Once all the fixed nodes are selected, as shown in Figure 72 below, click the Done button in the viewport. Lastly, go into Active Steps/Frames; make sure All steps are selected and set it to Frame. In the bottom of the window, make sure a green checkmark is applied to both the Contact and the Load steps. 133 Using the Create XY Data option in Abaqus, the user is able to go into Operate on XY data. In the Operators window, pick sum((A,A,...)), then under XY data, select all the Reaction Force nodes, which show up as _RF:RF2 and then click Add to Expression. Once all the nodes are inside the Sum operator, hit the Plot Expression button. This will output a force vs. time graph. 134 Once both the force vs. time graph and deflection vs. time graph are created, one needs to combine both graphs. In the Create XY Data, click Operate on XY Data and then press Continue. Under the operator tab, find combine(X,X) and then click it once. The combine operator requires two variables for the plot. For the first variable, click the deflection XY data, and for the second variable, click the Reaction Force 2 XY data. Make sure a comma separates both variables. Once done click the plot expression button and this should bring up a Force vs. Pin Deflection plot as shown in Figure 74. 135 A.5. Tutorial on Modeling the Double Shear Bearing Specimen Assembly Open up Abaqus 6.14. The numerical model should look like something like this. The complete assembly, the pin and one of the side plates modeled with Abaqus 6.14. 136 A.5.1. Model Creation Create a new model by right clicking the Models category. Name it DoubleShear. Then press Ok. 137 A.5.2. Part Creation Next, we have to create the parts for the model, after that, we partition each of the parts. Click on the + button to expand the options inside the DoubleShear model. Right click on Parts and press Create. A menu will appear like the one shown below. Name the part SteelPin. Keep the modeling space: 3D, the type: deformable, the base feature shape: Solid and for the base feature type: Extrusion. Click continue. 138 Click the Create Circle button. Using the dimension tool below set the radius to 0.125 in. Always be consistent with your units (I am using inches). 140 Next, we need to create the double shear specimen. Copy the step above and only change the name of the part to Specimen. Use the rectangle tool (to the right of the circle tool) and make a basic rectangle. 141 Using the dimension tool set the width of the part to 1.5 in. and the length of the part to 5.5 in. Create a Line down the middle of the part. Locate the center of hole 0.75 in. from the bottom edge of the specimen and make sure the hole is centered along the specimen\u2019s width. 142 Now, delete the centerline with the eraser tool, which is highlighted and then click on the centerline (which should highlight in red) and click done. Click the eraser tool to disable it. 143 In the bottom of the drawing window, it should read, \u201cSketch the section for the solid extrusion\u201d. Click the Done button. Set the depth to 0.1 in. Since the carbon fiber specimen\u2019s thickness was 0.1 in. Next, we need to create the side steel plate. Copy the step above and only change the name of the part to SidePlate. Use the rectangle tool (to the right of the circle tool), make a basic rectangle, and use the circle tool to create a hole in the plate. The side steel plate should be 2 in. by 4 in. and it should have a 0.141 in. radius hole. Which is located 1.0 in. from the top of the side plate. Lastly, remove the centerline and then set the depth to 0.25 in. Since the side steel plates had a thickness of 0.25 in. The three parts should look like this once they are completed. 144 A.5.3. Partition Creation A partition was created on the side plates and on the specimen. This made sure that when the mesh was generated all the elements stayed symmetrical. One major source of error in finite element analysis is due to elements not being symmetrical and the same size. One way to avoid this problem is to create your own mesh, which requires the user to partition the part based on what is of interest to him/her. Pick Tools, in the top drop down menu, and choose Partition. Click Face for the partition type and then click on the side plate face highlighted in orange. 145 Click Done and then it will ask to click a line vertical and to the right. Shown below, the highlighted edge is shown in pink, and the non-highlighted edges are shown in red. The part will switch from 3D to 2D and then here the user is able to create the partition desired. Create the partition below with these dimensions using the circle and line tools. It is important to keep the mesh coarse on parts which are not of main interest. 146 Apply the same method to the double shear specimen. The partition on this specimen was a lot more detailed than on the steel side plate. There are six circles, which are all equally spaced apart. The three outer radii were 0.5 in., 0.375 in., and 0.625 in. The three inner radii were 0.1875 in., 0.25 in., and 0.3125 in. A finer partition was created on the three inner radii where the circle was segmented into 64 equally spaced smaller sections. 147 The final partitioned parts should look like this. 148 A.5.4. Material Creation The material properties need to be created. Two materials were used in the analysis: steel and a unidirectional carbon fiber material. Under the Parts category, right click and click create. Name the material Steel. Go into the Mechanical option, then press elasticity, then elastic. Keep the type set to a default isotropic setting. Set the Young\u2019s Modulus to 34e6 and set the Poisson\u2019s ratio to 0.3. Follow the step right above, and create a new material and name it Uni. For the type, select 149 Engineering Constants. Include the material properties in the Table below (remember that msi is 106 psi)." + ] + }, + { + "image_filename": "designv8_17_0003238_f_version_1584177316-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003238_f_version_1584177316-Figure3-1.png", + "caption": "Figure 3. Piezoelectric stator.", + "texts": [ + "\u00a0In\u00a0Figure\u00a02b,\u00a0the\u00a0force\u00a0generated\u00a0by\u00a0 rotating\u00a0the\u00a0pre\u2010pressure\u00a0lever\u00a0is\u00a0converted\u00a0into\u00a0the\u00a0pressure\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0on\u00a0the\u00a0rotor\u00a0 spherical\u00a0 shell.\u00a0When\u00a0 the\u00a0 pre\u2010pressure\u00a0 bar\u00a0moves\u00a0 upward,\u00a0 the\u00a0 pre\u2010pressure\u00a0 slider\u00a0moves\u00a0 in\u00a0 a\u00a0 direction\u00a0close\u00a0to\u00a0the\u00a0rotor\u00a0case.\u00a0In\u00a0this\u00a0way,\u00a0the\u00a0pre\u2010pressure\u00a0between\u00a0the\u00a0piezoelectric\u00a0stators\u00a0and\u00a0 rotor\u00a0is\u00a0applied.\u00a0 \u00a0 (a)\u00a0 (b)\u00a0 Figure\u00a0 2.\u00a0Pre\u2010pressure\u00a0 regulating\u00a0 system:\u00a0 (a)\u00a0 Schematic\u00a0diagram\u00a0of\u00a0pre\u2010pressure\u00a0 system\u00a0 (b)\u00a0Pre\u2010 pressure\u00a0regulating\u00a0diagram.\u00a0 As\u00a0shown\u00a0in\u00a0Figure\u00a03,\u00a0the\u00a0piezoelectric\u00a0stator\u00a0is\u00a0composed\u00a0of\u00a0the\u00a0piezoelectric\u00a0base\u00a0body\u00a0and\u00a0the\u00a0 piezoelectric\u00a0 ceramic\u00a0 sheets.\u00a0Alternating\u00a0voltages\u00a0with\u00a0 the\u00a0 same\u00a0 frequency\u00a0 and\u00a0 amplitude,\u00a0but\u00a0 a\u00a0 phase\u00a0difference\u00a0of\u00a090\u00b0\u00a0is\u00a0applied\u00a0to\u00a0the\u00a0two\u00a0phases\u00a0of\u00a0the\u00a0piezoelectric\u00a0ceramic\u00a0sheets.\u00a0 \u00a0 The\u00a0piezoelectric\u00a0stator\u00a0responds\u00a0to\u00a0a\u00a0pulsating\u00a0wave\u00a0with\u00a0a\u00a0phase\u00a0difference\u00a0of\u00a090\u00b0\u00a0in\u00a0both\u00a0time\u00a0 and\u00a0space,\u00a0which\u00a0 is\u00a0 in\u00a0accordance\u00a0with\u00a0 the\u00a0principle\u00a0of\u00a0a\u00a0piezoelectric\u00a0 inverse\u00a0effect.\u00a0A\u00a0circularly\u00a0 traveling\u00a0wave\u00a0 is\u00a0 formed\u00a0by\u00a0 the\u00a0 superposition\u00a0of\u00a0 the\u00a0 two\u2010phase\u00a0 standing\u00a0waves", + "\u00a0In\u00a0Figure\u00a02b,\u00a0the\u00a0force\u00a0generated\u00a0by\u00a0 rotating\u00a0the\u00a0pre\u2010pressure\u00a0lever\u00a0is\u00a0converted\u00a0into\u00a0the\u00a0pressure\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0on\u00a0the\u00a0rotor\u00a0 spherical\u00a0 shell.\u00a0When\u00a0 the\u00a0 pre\u2010pressure\u00a0 bar\u00a0moves\u00a0 upward,\u00a0 the\u00a0 pre\u2010pressure\u00a0 slider\u00a0moves\u00a0 in\u00a0 a\u00a0 direction\u00a0close\u00a0to\u00a0the\u00a0rotor\u00a0case.\u00a0In\u00a0this\u00a0way,\u00a0the\u00a0pre\u2010pressure\u00a0between\u00a0the\u00a0piezoelectric\u00a0stators\u00a0and\u00a0 rotor\u00a0is\u00a0applied.\u00a0 \u00a0 (a)\u00a0 (b)\u00a0 Figure\u00a0 2.\u00a0Pre\u2010pressure\u00a0 regulating\u00a0 system:\u00a0 (a)\u00a0 Schematic\u00a0diagram\u00a0of\u00a0pre\u2010pressure\u00a0 system\u00a0 (b)\u00a0Pre\u2010 pressure\u00a0regulating\u00a0diagram.\u00a0 As\u00a0shown\u00a0in\u00a0Figure\u00a03,\u00a0the\u00a0piezoelectric\u00a0stator\u00a0is\u00a0composed\u00a0of\u00a0the\u00a0piezoelectric\u00a0base\u00a0body\u00a0and\u00a0the\u00a0 piezoelectric\u00a0 ceramic\u00a0 sheets.\u00a0Alternating\u00a0voltages\u00a0with\u00a0 the\u00a0 same\u00a0 frequency\u00a0 and\u00a0 amplitude,\u00a0but\u00a0 a\u00a0 phase\u00a0difference\u00a0of\u00a090\u00b0\u00a0is\u00a0applied\u00a0to\u00a0the\u00a0two\u00a0phases\u00a0of\u00a0the\u00a0piezoelectric\u00a0ceramic\u00a0sheets.\u00a0 \u00a0 The\u00a0piezoelectric\u00a0stator\u00a0responds\u00a0to\u00a0a\u00a0pulsating\u00a0wave\u00a0with\u00a0a\u00a0phase\u00a0difference\u00a0of\u00a090\u00b0\u00a0in\u00a0both\u00a0time\u00a0 and\u00a0space,\u00a0which\u00a0 is\u00a0 in\u00a0accordance\u00a0with\u00a0 the\u00a0principle\u00a0of\u00a0a\u00a0piezoelectric\u00a0 inverse\u00a0effect.\u00a0A\u00a0circularly\u00a0 traveling\u00a0wave\u00a0 is\u00a0 formed\u00a0by\u00a0 the\u00a0 superposition\u00a0of\u00a0 the\u00a0 two\u2010phase\u00a0 standing\u00a0waves.\u00a0Then\u00a0 the\u00a0 rotor\u00a0 Rotor Piezoelectric stator Pre-pressure slider Pre-pressure rod Figure 2. Pre-pressure regulating system: (a) Schematic diagram of pre-pressure system (b) Pre-pressure regulating diagram. As shown in Figure 3, the piezoelectric stator is composed of the piezoelectric base body and the piezoelectric ceramic sheets. Alternating voltages with the same frequency and amplitude, but a phase difference of 90\u25e6 is applied to the two phases of the piezoelectric ceramic sheets. Sensors 2020, 20, 1621 4 of 18 The piezoelectric stator responds to a pulsating wave with a phase difference of 90\u25e6 in both time and space, which is in accordance with the principle of a piezoelectric inverse effect. A circularly traveling wave is formed by the superposition of the two-phase standing waves. Then the rotor rotates along the tangential direction of the particle surface of the piezoelectric stator surface, and the direction of rotor rotation is opposite to the direction of the traveling wave. Sensors\u00a02020 \u00a020,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 4\u00a0of\u00a018\u00a0 r tates\u00a0along\u00a0the\u00a0tangential\u00a0direction\u00a0of\u00a0the\u00a0particle\u00a0surface\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0surface,\u00a0and\u00a0the\u00a0 direction\u00a0of\u00a0r tor\u00a0r tation\u00a0is\u00a0 pposite\u00a0to\u00a0the\u00a0direction\u00a0of\u00a0the\u00a0traveling\u00a0wave.\u00a0 Figure\u00a03.\u00a0Piezoelectric\u00a0stator.\u00a0 As\u00a0shown\u00a0in\u00a0Figure\u00a04a,b,\u00a0the\u00a0line\u00a0passing\u00a0through\u00a0the\u00a0No.\u00a02\u00a0stator\u00a0(S2)\u00a0is\u00a0defined\u00a0as\u00a0the\u00a0Y\u2010axis,\u00a0 the\u00a0axis\u00a0perpendicular\u00a0to\u00a0the\u00a0Y\u2010axis\u00a0is\u00a0the\u00a0X\u2010axis,\u00a0and\u00a0the\u00a0line\u00a0perpendicular\u00a0to\u00a0the\u00a0X\u2010Y\u00a0plane\u00a0and\u00a0 passing\u00a0through\u00a0the\u00a0origin\u00a0is\u00a0defined\u00a0as\u00a0the\u00a0Z\u2010axis.\u00a0The\u00a0angle\u00a0between\u00a0the\u00a0piezoelectric\u00a0stators\u00a0and\u00a0 the\u00a0X\u2010Y\u00a0plane\u00a0is\u00a0\u03b1\u00b0.\u00a0 As\u00a0shown\u00a0in\u00a0Figure\u00a04c,\u00a0the\u00a0electromagnetically\u2010driven\u00a0stator\u00a0is\u00a0mounted\u00a0outside\u00a0the\u00a0spherical\u00a0 rotor.\u00a0 The\u00a0 rotor\u00a0 torque\u00a0 is\u00a0 generated\u00a0 by\u00a0 the\u00a0 interaction\u00a0 between\u00a0 the\u00a0 energized\u00a0 coil\u00a0 and\u00a0 the\u00a0 PM\u00a0 magnetic\u00a0field", + " 2 stator (S2) is defined as the Y-axis, the axis perpendicular to the Y-axis is the X-axis, and the line perpendicular to the X-Y plane and passing through the origin is defined as the Z-axis. The angle between the piezoelectric stators and the X-Y plane is \u03b1\u25e6. Sensors\u00a02020,\u00a020,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 4\u00a0of\u00a018\u00a0 rotates\u00a0along\u00a0the\u00a0tangential\u00a0direction\u00a0of\u00a0the\u00a0particle\u00a0surface\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0surface,\u00a0and\u00a0the\u00a0 direction\u00a0of\u00a0rotor\u00a0rotation\u00a0is\u00a0opposite\u00a0to\u00a0the\u00a0direction\u00a0of\u00a0the\u00a0traveling\u00a0wave.\u00a0 \u00a0 Figure\u00a03.\u00a0Piezoelectric\u00a0stator.\u00a0 A \u00a0shown\u00a0in\u00a0Figure\u00a04a,b,\u00a0the\u00a0li e\u00a0passing\u00a0through\u00a0th \u00a0No.\u00a02\u00a0stator\u00a0(S2)\u00a0is\u00a0defined\u00a0as\u00a0the\u00a0Y\u2010axis,\u00a0 the\u00a0axis\u00a0perpendicular\u00a0to\u00a0the\u00a0Y\u2010axis\u00a0is\u00a0the\u00a0X\u2010axis,\u00a0a d\u00a0the\u00a0line\u00a0perpendicular\u00a0to\u00a0the\u00a0X\u2010Y\u00a0plane\u00a0and\u00a0 4321 32 1 212 1 32 3 12 3 sinsinsin coscoscos coscos \u03c9\u03b1\u03c9\u03b1\u03c9\u03b1\u03c9 \u03b1\u03c9\u03b1\u03c9\u03b1\u03c9 \u03b1\u03c9\u03b1\u03c9 \u03c9 \u03c9 \u03c9 z y x \u03c9 \u00a0 (1)\u00a0 \u00a0 (a)\u00a0 (b)\u00a0 (c)\u00a0 Figure\u00a0 4.\u00a0Motor\u00a0 structure:\u00a0 (a)\u00a0Top\u00a0view\u00a0of\u00a0piezoelectric\u00a0 stators/rotor\u00a0 structure,\u00a0 (b)\u00a0Front\u00a0view\u00a0of\u00a0 piezoelectric\u00a0stators/rotor\u00a0structure,\u00a0and\u00a0(c)\u00a0Structure\u00a0of\u00a0electromagnetic\u00a0stator/rotor", + "33 7600 Piezoelectric base body Phosphor bronze 8 \u00d7 109 0.3 8800 Rotor material Hard aluminum 72 \u00d7 109 0.33 2700 Rotor PM NdFeB35 16 \u00d7 1010 0.3 7500 Electromagnetic stator coil Copper 11 \u00d7 1010 0.35 8960 Electromagnetic stator core Silicon steel 2 \u00d7 1011 0.25 7600 The outer radius of the piezoelectric stators is 30 mm, the tooth height of the piezoelectric stators is 2 mm, the thickness of the piezoelectric ceramics is 0.5 mm and the thickness of the intermediate elastic body is 2.5 mm. The model of a piezoelectric stator is shown in Figure 3. Each tooth occupies a tooth height of 2 mm, a groove angle of 5\u25e6 between the teeth, a circumferential angle of 3\u25e6, a tooth gap width of 5.5 mm, an elastic base thickness of 2.5 mm, and a piezoelectric ceramic thickness of 0.5 mm. The outer radius of the electromagnetic stator is 93.6 mm. The air gap between the electromagnetic stator and rotor is 1.5 mm. The inner radius of the rotor is 49 mm. The PM thickness is 10 mm. In order to predict the dynamic characteristics of the motor structure, the modal analysis of the stators and rotor is carried out", + "3\u00a0 8800\u00a0 Rotor\u00a0material\u00a0 Hard\u00a0aluminum\u00a0 72\u00a0\u00d7\u00a0109\u00a0 0.33\u00a0 2700\u00a0 Rotor\u00a0PM\u00a0 NdFeB35\u00a0 16\u00a0\u00d7\u00a01010\u00a0 0.3\u00a0 7500\u00a0 Electromagnetic\u00a0stator\u00a0coil\u00a0 Copper\u00a0 11\u00a0\u00d7\u00a01010\u00a0 0.35\u00a0 8960\u00a0 Electromagnetic\u00a0stator\u00a0core\u00a0 Silicon\u00a0steel\u00a0 2\u00a0\u00d7\u00a01011\u00a0 0.25\u00a0 7600\u00a0 The\u00a0outer\u00a0radius\u00a0of\u00a0the\u00a0piezoelectric\u00a0stators\u00a0is\u00a030\u00a0mm,\u00a0the\u00a0tooth\u00a0height\u00a0of\u00a0the\u00a0piezoelectric\u00a0stators\u00a0 is\u00a02\u00a0mm,\u00a0the\u00a0thickness\u00a0of\u00a0the\u00a0piezoelectric\u00a0ceramics\u00a0is\u00a00.5\u00a0mm\u00a0and\u00a0the\u00a0thickness\u00a0of\u00a0the\u00a0intermediate\u00a0 elastic\u00a0body\u00a0is\u00a02.5\u00a0mm.\u00a0The\u00a0model\u00a0of\u00a0a\u00a0piezoelectric\u00a0stator\u00a0is\u00a0shown\u00a0in\u00a0Figure\u00a03.\u00a0Each\u00a0tooth\u00a0occupies\u00a0 a\u00a0tooth\u00a0height\u00a0of\u00a02\u00a0mm,\u00a0a\u00a0groove\u00a0angle\u00a0of\u00a05\u00b0\u00a0between\u00a0the\u00a0teeth,\u00a0a\u00a0circumferential\u00a0angle\u00a0of\u00a03\u00b0,\u00a0a\u00a0tooth\u00a0 gap\u00a0width\u00a0of\u00a05.5\u00a0mm,\u00a0an\u00a0elastic\u00a0base\u00a0thickness\u00a0of\u00a02.5\u00a0mm,\u00a0and\u00a0a\u00a0piezoelectric\u00a0ceramic\u00a0thickness\u00a0of\u00a00.5\u00a0 mm.\u00a0 The\u00a0 outer\u00a0 radius\u00a0 of\u00a0 the\u00a0 electromagnetic\u00a0 stator\u00a0 is\u00a0 93.6\u00a0 mm.\u00a0 The\u00a0 air\u00a0 gap\u00a0 between\u00a0 the\u00a0 electromagnetic\u00a0stator\u00a0and\u00a0rotor\u00a0is\u00a01.5\u00a0mm.\u00a0The\u00a0inner\u00a0radius\u00a0of\u00a0the\u00a0rotor\u00a0is\u00a049\u00a0mm.\u00a0The\u00a0PM\u00a0thickness\u00a0 is\u00a010\u00a0mm.\u00a0In\u00a0order\u00a0to\u00a0predict\u00a0the\u00a0dynamic\u00a0characteristics\u00a0of\u00a0the\u00a0motor\u00a0structure,\u00a0the\u00a0modal\u00a0analysis\u00a0 of\u00a0the\u00a0stators\u00a0and\u00a0rotor\u00a0is\u00a0carried\u00a0out" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000046_cle_download_743_255-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000046_cle_download_743_255-Figure4-1.png", + "caption": "Figure 4: The detailed mesh and boundary conditions of chip Q1", + "texts": [ + "5Cu: In the actual power-driven transient thermal analysis, the chipset is repeatedly powered on and off, and both the dwell times are 3 minutes. The transient thermal conduction analysis of the whole chipset is carried out at first, then followed by thermal stress submodel analysis of each chip according to the temperature fields obtained from the thermal conduction analysis of the whole chipset, to get the stress and strain distributions at the solder/substrate interfaces. The boundary conditions in the submodel of each chip are obtained by automatic interpolation of the ANSYS software, as shown in Fig. 4. Fig. 5 shows the temperature and strain rate at the center of material 2 (solder Pb5Sn) and 4 (solder Sn3Ag0.5Cu). Due to the shock of power on, high temperature gradient and stress appear in solder Pb5Sn since it is just beneath the power layer. The high stress is presently relaxed because the strain rate reaches a balanced state. After the temperature gets to a saturated state, the strain rate decreases. Because the heat flux is difficult to pass through the thermal insulate layer (material 6) beneath it, the temperature gradient and stress in Sn3Ag0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000211_mtime_20231027201738-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000211_mtime_20231027201738-Figure6-1.png", + "caption": "Figure 6: (3D) views of FEM modelling of linear dissipative device (a) side view; (b) top View", + "texts": [ + " By analyzing the results, it can be observed that, unlike thermal sprayed aluminium plates, for the brass plates during cyclic testing, a large fluctuation of the bolt load was obtained in the second test, and consequently a large fluctuation of the friction coefficient was found, both due to the relevant amplitude of the stick and slip phenomenon, that was not adequately compensated by the disc spring. The resulting large fluctuation of the sliding force, even characterized by a constant mean value, proves that the coupling of brass and steel is not as performing as coupling of steel and thermal sprayed aluminium for friction devices. The Linear friction device was modelled in ABAQUS software as consistent with the experimental specimen shown in Figure 6. In the FEM analysis, to understand the effect of the thickness of friction pads and cover plates on the functioning of the friction device, three different configurations were adopted. In the first configuration, the thickness of thermal sprayed aluminium and outer cover plates were 10 mm and 5mm same as of the experimental specimen. In the second configuration friction shims and outer cove plates were taken thinner 5mm and 2.5mm while for third configuration, taken as thicker of thicknesses 20mm and 10mm respectively as shown in table 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-15-1.png", + "caption": "Figure 2-15. Exemples d'antennes PIFA pr\u00e9sentes dans des t\u00e9l\u00e9phones portables", + "texts": [], + "surrounding_texts": [ + "L'objectif de cette partie est de pr\u00e9senter les structures de base que l'on retrouve g\u00e9n\u00e9ralement dans les objets communicants. Ainsi nous pr\u00e9senterons les antennes filaires dont l'antenne dip\u00f4le qui sert tr\u00e8s souvent de r\u00e9f\u00e9rence, nous aborderons \u00e9galement les antennes patchs et PIFA (Planar Inverted F Antenna). L'objectif de cette partie \u00e9tant \u00e9galement d'introduire les antennes que nous aborderons par la suite, de ce fait nous pr\u00e9senterons \u00e9galement les antennes directives de type Yagi-Uda et les antennes \u00e0 ouverture de type cornet tr\u00e8s utilis\u00e9es dans la m\u00e9trologie des antennes. Il ne serait pas raisonnable de pr\u00e9senter toutes les diff\u00e9rentes structures d'antennes existantes car la \"zoologie\" d'antenne est trop vaste et elle ne cesse d'augmenter. Cette partie ne constitue donc pas une \u00e9num\u00e9ration exhaustive de tous les types d'antennes. Dans cette partie, nous faisons \u00e9galement le choix de ne pas pr\u00e9senter les r\u00e8gles de conception ainsi que les formules th\u00e9oriques permettant le dimensionnement d'une antenne \u00e0 une 45 fr\u00e9quence choisie. En effet, dans la plupart des cas l'obtention d'une antenne avec des caract\u00e9ristiques pr\u00e9cises ne peut pas s'obtenir qu'avec des r\u00e8gles de conception empirique. L'exp\u00e9rience du concepteur d'antenne ainsi qu'une succession de simulations \u00e9lectromagn\u00e9tiques permettent de faire converger la structure vers une antenne optimale r\u00e9pondant au cahier des charges. 2.4.1 Les antennes filaires Les antennes filaires sont les plus anciennes des antennes et ce sont des antennes \u00e9l\u00e9mentaires qui servent de r\u00e9f\u00e9rence. Les concepts th\u00e9oriques de ces antennes sont r\u00e9gis par la th\u00e9orie du doublet de Hertz qui est constitu\u00e9 de deux conducteurs aliment\u00e9s par une source radiofr\u00e9quence en diff\u00e9rentiel. La dimension de ces conducteurs est tr\u00e8s petite devant la longueur d'onde ( 10\u03bb< ). La distribution du courant pr\u00e9sent le long du fil est d\u00e9termin\u00e9e par la dimension de la structure par rapport \u00e0 la longueur d'onde du signal \u00e0 \u00e9mettre ou \u00e0 recevoir. C'est \u00e0 partir de cette th\u00e9orie qu'ont \u00e9t\u00e9 \u00e9labor\u00e9es les th\u00e9ories du dip\u00f4le demi-onde et du monopole quart d'onde. Le dip\u00f4le demi-onde ou 2\u03bb est un cas particulier du doublet de Hertz dont la longueur est sensiblement \u00e9gale \u00e0 la moiti\u00e9 de la longueur d'onde du signal ou \u00e0 \u00e9mettre. En effet, si l'on consid\u00e8re la distribution de courant le long d'un dip\u00f4le de longueur d en fonction du rapport d \u03bb , on constate que l'intensit\u00e9 maximale du courant se retrouve sur les points de l'excitation diff\u00e9rentielle comme le montre la Figure 2-10. 46 Le dip\u00f4le 2\u03bb est tr\u00e8s simplement r\u00e9alisable \u00e0 partir de conducteur rigide et ses propri\u00e9t\u00e9s th\u00e9oriques sont tr\u00e8s bien d\u00e9finies ce qui fait que cette antenne peut servir de r\u00e9f\u00e9rence. De plus, elle a l'avantage de pr\u00e9senter un diagramme de rayonnement omnidirectionnel de forme torique et une polarisation lin\u00e9aire parall\u00e8le \u00e0 la direction des conducteurs. La Figure 2-11 repr\u00e9sente le diagramme de rayonnement d'une antenne dip\u00f4le. Dans la suite de la th\u00e8se lorsque nous emploierons le terme de dip\u00f4le sans en pr\u00e9ciser la longueur, cela sous entend que nous faisons r\u00e9f\u00e9rence \u00e0 un dip\u00f4le demi-onde. 47 L'antenne dip\u00f4le est tr\u00e8s rarement mise en \u0153uvre dans les objets communicants, ce type d'antenne est g\u00e9n\u00e9ralement soit utilis\u00e9 pour des longueurs d'onde d\u00e9cam\u00e9triques par les radioamateurs soit dans des structures d'antennes plus complexes comme les antennes Yagi-Uda que nous pr\u00e9senterons apr\u00e8s. Ce n'est pas le cas de l'antenne monopole quart d'onde que l'on retrouve fr\u00e9quemment dans des objets communicants. Cette antenne filaire est aliment\u00e9e en 48 mode commun contrairement au dip\u00f4le, elle est donc r\u00e9f\u00e9renc\u00e9e par rapport \u00e0 un plan de masse. Ce plan de masse introduit un effet d'image qui fait que la longueur du monopole est per\u00e7ue double et revient donc \u00e0 un dip\u00f4le de longueur 2\u03bb . Ainsi pour une longueur de 4\u03bb , le gain obtenu est comparable \u00e0 celui d'un dip\u00f4le. Les gains sont th\u00e9oriquement \u00e9gaux entre ces deux antennes dans le cas o\u00f9 le plan de masse est infini. Lorsque le plan de masse n'est pas infini, ce qui est le cas dans la pratique, la diagramme de rayonnement est modifi\u00e9 mais reste omnidirectionnel. La Figure 2-12 repr\u00e9sente un monopole sur un plan de masse et expose l'image du monopole obtenue gr\u00e2ce au plan de masse. Le monopole \u00e9tait utilis\u00e9 comme antenne dans les premi\u00e8res g\u00e9n\u00e9rations de t\u00e9l\u00e9phone mobile mais il a \u00e9t\u00e9 remplac\u00e9 par d'autres structures plus compactes et multi-bandes. Aujourd'hui ce type d'antenne reste employ\u00e9 notamment au niveau des routeurs ou des cartes r\u00e9seau Wifi o\u00f9 la contrainte d'encombrement est moins forte et o\u00f9 un rayonnement omnidirectionnel est souhaitable. Dans le cas de l'utilisation de monopole dans des objets communicants, le circuit imprim\u00e9 de l'objet constitue g\u00e9n\u00e9ralement le plan de l'antenne ; ceci permet d'obtenir des syst\u00e8mes d'antenne efficaces. 49 2.4.2 Les PIFA - Planar Inverted F Antennas Les antennes PIFA pour Planar Inferted F Antenna sont tr\u00e8s certainement les antennes les plus utilis\u00e9es dans la t\u00e9l\u00e9phonie mobile, aujourd'hui. En effet comme nous l'avons expliqu\u00e9 pr\u00e9c\u00e9demment les antennes de type monopole initialement \u00e0 l'ext\u00e9rieur des premi\u00e8res g\u00e9n\u00e9rations de t\u00e9l\u00e9phones mobiles ont \u00e9t\u00e9 int\u00e9gr\u00e9es au corps du t\u00e9l\u00e9phone pour des questions d'esth\u00e9tisme, elles ont g\u00e9n\u00e9ralement \u00e9t\u00e9 remplac\u00e9es par des antennes de type PIFA qui offrent un degr\u00e9 d'int\u00e9gration sup\u00e9rieur mais \u00e9galement d'autres avantages que nous allons voir. Les antennes PIFA sont constitu\u00e9es d'un plateau m\u00e9tallique rayonnant parall\u00e8le au plan de masse. Un des bords du plateau est reli\u00e9 \u00e0 la masse par un plan de court circuit qui constitue la particularit\u00e9 de cette antenne. Le plan de court circuit peut \u00eatre plus ou moins large en fonction des propri\u00e9t\u00e9s recherch\u00e9es. Le plateau rayonnant est excit\u00e9 par une alimentation verticale en un point adapt\u00e9. Le di\u00e9lectrique entre le plan de masse et le plateau rayonnant est tr\u00e8s souvent de l'air m\u00eame si il est possible d'utiliser un autre mat\u00e9riau pour assurer un meilleur maintien m\u00e9canique de la structure. Il est \u00e0 noter que bien souvent l'utilisation d'un autre di\u00e9lectrique que l'air entraine des pertes suppl\u00e9mentaire et r\u00e9duit l'efficacit\u00e9 totale de l'antenne. 50 Ces antennes en trois dimensions sont compactes et leur cout de fabrication est limit\u00e9. Elles sont le plus souvent r\u00e9alis\u00e9es en m\u00e9tal d\u00e9coup\u00e9 et pli\u00e9, en mati\u00e8re plastique m\u00e9tallis\u00e9e ou sur circuit souple. Afin de r\u00e9duire, encore les dimensions du plateau rayonnant il est possible de le replier. En ins\u00e9rant des fentes dans ce dernier, il est possible de faire appara\u00eetre d'autres fr\u00e9quences de r\u00e9sonnance, ce qui est tr\u00e8s int\u00e9ressant dans le cas de la t\u00e9l\u00e9phonie mobile o\u00f9 les bandes de fr\u00e9quence utilis\u00e9es changent en fonction du r\u00e9seau utilis\u00e9 ou du pays dans lequel on se trouve. Seule la forme de base de cette antenne est r\u00e9gie par des formules empiriques [2.7]. D\u00e8s que la structure est complexifi\u00e9e, seule l'exp\u00e9rience du concepteur permet d'obtenir l'antenne avec les performances et caract\u00e9ristiques voulues. Le rayonnement de ce type d'antenne d\u00e9pendra beaucoup de la forme du plateau rayonnant mais g\u00e9n\u00e9ralement le rayonnement s'effectue dans toute les directions de l'espace, il est parfois possible de se rapprocher du rayonnement isotrope. Il n'y a donc pas de direction de rayonnement privil\u00e9gi\u00e9e ce qui est int\u00e9ressant car dans le cas d'objet communiquant l'orientation de l'objet peut \u00eatre quelconque. La polarisation de ce type d'antenne est tr\u00e8s li\u00e9e \u00e0 la forme du plateau et sera \u00e9galement diff\u00e9rente en fonction de la direction consid\u00e9r\u00e9e. 51 L'antenne PIFA poss\u00e8de une variante planaire appel\u00e9e IFA pour Inverted F Antenna r\u00e9alisable sur circuit imprim\u00e9. Le principe reste le m\u00eame que pour la PIFA mais en deux dimensions. Il y a un brin rayonnant aliment\u00e9 auquel on applique une condition de court circuit \u00e0 l'une de ces extr\u00e9mit\u00e9s comme le montre la Figure 2-16. Il y a moins de degr\u00e9 de libert\u00e9 dans le design qu'avec une PIFA mais cette structure est int\u00e9ressante car elle peut facilement \u00eatre r\u00e9alis\u00e9e sur des circuits imprim\u00e9s et aliment\u00e9e par une ligne microruban. La contrainte de la r\u00e9alisation m\u00e9canique en trois dimensions est alors supprim\u00e9e. 52 Dans nos travaux nous nous sommes largement int\u00e9ress\u00e9s \u00e0 ces structures car elles r\u00e9pondent \u00e0 de tr\u00e8s nombreuses contraintes propres aux objets communicants. Comme nous les verrons, nos travaux nous ont conduits \u00e0 d\u00e9poser un brevet proposant de rendre agile en fr\u00e9quence et en polarisation une antenne PIFA. 2.4.3 Les antennes Patch Les antennes patch sont des antennes planaires g\u00e9n\u00e9ralement r\u00e9alis\u00e9es sur des circuits imprim\u00e9s, cela les rend faibles co\u00fbt et facilement int\u00e9grables dans les objets communicants o\u00f9 elles sont couramment employ\u00e9es. Ces antennes ont trois \u00e9l\u00e9ments constitutifs comme le montre la Figure 2-18. Il y a n\u00e9cessairement un plan de masse, un patch et entre les deux un substrat di\u00e9lectrique. C'est cet empilement qui rend ce type d'antenne compatible avec les techniques de r\u00e9alisation des circuits imprim\u00e9s. Le patch qui est l'\u00e9l\u00e9ment rayonnant peut prendre diverses formes en fonctions des propri\u00e9t\u00e9s recherch\u00e9es. Il est possible de trouver des patchs de forme carr\u00e9, rectangulaire, circulaire, ovale ou m\u00eame triangulaire. Le patch peut \u00eatre excit\u00e9 soit \u00e0 l'aide d'une ligne microruban soit par un acc\u00e8s coaxial en un point du patch. 53 Les antennes patch offrent de nombreux avantages, elles ont un encombrement r\u00e9duit et une configuration planaire, leur r\u00e9alisation est simple et de faible cout. De plus, il est possible de rendre ces structures multi-bandes et d'obtenir des polarisations lin\u00e9aires ou circulaires en fonction du mode d'alimentation. Nous verrons \u00e9galement par la suite qu'il est possible \u00e0 partir d'un seul patch de r\u00e9cup\u00e9rer des signaux dont les polarisations sont orthogonales et donc fortement d\u00e9corr\u00e9l\u00e9es. Mais l'antenne patch n'a pas que des avantages, elle ne rayonne que dans une demi-espace dont la fronti\u00e8re est constitu\u00e9e par le plan de masse et elle souffre d'une bande passante g\u00e9n\u00e9ralement r\u00e9duite (inf\u00e9rieure \u00e0 5% \u00e0 -10dB). La bande passante peut cependant \u00eatre \u00e9largie par l'utilisation de patchs parasites empil\u00e9s ou dispos\u00e9s dans le plan du patch comme le montre la Figure 2-19. 54 2.4.4 Les antennes directives Comme nous l'avons mentionn\u00e9 pr\u00e9c\u00e9demment, les antennes directives sont g\u00e9n\u00e9ralement utilis\u00e9es dans des r\u00e9seaux point \u00e0 point ou point \u00e0 multipoint. Ces structures permettent de concentrer la puissance dans une direction d\u00e9termin\u00e9e afin de cr\u00e9er un lien radio privil\u00e9gi\u00e9. Parmi les structures d'antennes directives, les plus connues du public sont certainement les antennes paraboliques largement utilis\u00e9es dans les communications satellitaires ainsi que les antennes Yagi-Uda utilis\u00e9es pour la r\u00e9ception des signaux de t\u00e9l\u00e9vision hertzienne. Ainsi la majorit\u00e9 des foyers fran\u00e7ais dispose d'une antenne directive sur son toit. Ces deux structures ne sont pas les seules \u00e0 rentrer dans la cat\u00e9gorie des antennes directives, par exemple les antennes h\u00e9lices utilis\u00e9es dans un certain mode pr\u00e9sentent une directivit\u00e9 \u00e9lev\u00e9e, de m\u00eame que les antennes \u00e0 ouverture comme les antennes cornet que nous pr\u00e9senterons apr\u00e8s. La mise en r\u00e9seau d'antennes ne pr\u00e9sentant pas n\u00e9cessairement une directivit\u00e9 \u00e9lev\u00e9e comme des antennes patch permet d'obtenir des structures tr\u00e8s directives. Nous faisons le choix dans nos travaux de ne pas pr\u00e9senter la th\u00e9orie de la mise en r\u00e9seau d'antenne. En effet nos travaux se situent au niveau des objets communicants et la mise en r\u00e9seau d'antenne n'est g\u00e9n\u00e9ralement utilis\u00e9e qu'au niveau des stations de base car l'encombrement de ces r\u00e9seaux d'antenne n'est pas compatible avec les contraintes d'encombrement des objets communicants. La figure ci-dessous pr\u00e9sente un exemple de mise en r\u00e9seau d'antenne patch dans le but d'obtenir un syst\u00e8me d'antenne tr\u00e8s directif, la directivit\u00e9 obtenue est de l'ordre de 21 dBi dans cet exemple. 55 Durant la th\u00e8se, nous avons \u00e9t\u00e9 amen\u00e9s \u00e0 travailler sur une structure directive, l'antenne Yagi-Uda. Cette structure porte le nom de ces deux inventeurs japonais, Hidetsugu Yagi et Shintaro Uda. Cette antenne repose sur le fait que l'adjonction d'\u00e9l\u00e9ments parasites non aliment\u00e9s \u00e0 proximit\u00e9 d'un dip\u00f4le peut modifier consid\u00e9rablement son diagramme de rayonnement. Deux facteurs doivent \u00eatre contr\u00f4l\u00e9s avec pr\u00e9cision, il s'agit de la distance entre les diff\u00e9rents \u00e9l\u00e9ments et leurs dimensions. Le dip\u00f4le aliment\u00e9, appel\u00e9 radiateur, est entour\u00e9 d'un cot\u00e9 par un r\u00e9flecteur, \u00e9l\u00e9ment l\u00e9g\u00e8rement plus long que le radiateur et de l'autre cot\u00e9 par au moins un directeur, \u00e9l\u00e9ment l\u00e9g\u00e8rement plus court que le radiateur. La Figure 2-22 pr\u00e9sente un exemple d'antenne Yagi-Uda de cinq \u00e9l\u00e9ments qui a trois directeurs, un radiateur et un r\u00e9flecteur. Il est important de noter que plus le nombre d'\u00e9l\u00e9ments \"parasites\" est important plus la directivit\u00e9 obtenue est importante. 56 2.4.5 Les antennes \u00e0 ouverture Les antennes \u00e0 ouverture sont des antennes qui reposent sur l'une des id\u00e9es les plus simples pour r\u00e9aliser une interface entre une onde \u00e9lectromagn\u00e9tique guid\u00e9e et une onde rayonn\u00e9e. Pour r\u00e9aliser ceci, il suffit de pratiquer une ouverture dans un guide d'ondes en r\u00e9alisant une ou plusieurs fentes dans celui-ci ou en le laissant ouvert \u00e0 son extr\u00e9mit\u00e9. Cette derni\u00e8re solution conduit \u00e0 une rupture d'imp\u00e9dance dont la transition peut \u00eatre adoucie en \u00e9vasant progressivement les bords du guide d'ondes. Ceci conduit \u00e0 obtenir une antenne cornet. Les antennes cornets, relativement volumineuses dans la bande de fr\u00e9quence UHF, sont essentiellement utilis\u00e9es pour de la m\u00e9trologie. Elles ont le plus souvent une forme de pyramide ou de c\u00f4ne tronqu\u00e9. La forme de cornet assure simplement l'adaptation progressive de l'onde \u00e9lectromagn\u00e9tique entre le point de couplage et la surface de rayonnement. En fonction de la fr\u00e9quence, l'attaque de la structure se fait soit par une guide d'onde soit par une source ponctuelle amen\u00e9e par un coaxial. La structure de l'antenne fait qu'il est simple d'obtenir des antennes tr\u00e8s large bande avec une polarisation contr\u00f4l\u00e9e et un fort gain dans la direction de l'ouverture. Ces propri\u00e9t\u00e9s font de l'antenne cornet une antenne id\u00e9ale pour la mesure d'autres antennes, d'autant plus qu'elles sont g\u00e9n\u00e9ralement calibr\u00e9es et le gain en fonction de la fr\u00e9quence est donc connu. Nous avons utilis\u00e9 des antennes cornets dans nos travaux de th\u00e8se, notamment lors de mesures effectu\u00e9e dans la chambre an\u00e9cho\u00efde de l'ESISAR \u2013 LCIS. Elles peuvent \u00e9galement se r\u00e9v\u00e9ler utile pour mesurer grossi\u00e8rement le gain d'une autre antenne directive ou \u00e9valuer un environnement \u00e9lectromagn\u00e9tique. La Figure 2-23 pr\u00e9sente le cornet utilis\u00e9 dans la chambre an\u00e9cho\u00efde de l'ESISAR et un cornet utilis\u00e9 \u00e0 France T\u00e9l\u00e9com R&D \u00e0 Meylan. 57 L'antenne cornet n'est pas la seule antenne \u00e0 ouverture m\u00eame si c'est elle qui en symbolise le mieux le principe. Parmi les antennes \u00e0 ouverture, il y a les antennes \u00e0 fente planaire. Le principe de ces antennes est la cr\u00e9ation d'une fente dans un plan de masse qui est excit\u00e9 par une ligne micro ruban, la fente rayonne alors. Ce ph\u00e9nom\u00e8ne est d\u00e9crit par le principe de Babinet qui indique que le rayonnement d'une fente peut \u00eatre le m\u00eame que celui d'un dip\u00f4le \u00e9quivalent \u00e0 la fente." + ] + }, + { + "image_filename": "designv8_17_0000677_ejjia_4_3_4_196__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000677_ejjia_4_3_4_196__pdf-Figure2-1.png", + "caption": "Fig. 2. General view of WFSM", + "texts": [ + " In the proposed drive system, however, a difficulty lies in its control since the voltage boost-up and field current regulation required for a given operating condition must be satisfied harmoniously. Therefore, the control algorithm for the proposed system is examined as a main objective in this paper. Some experimental studies using a test drive system are conducted and verify that the proposed control algorithm can operate the proposed drive system properly. c\u00a9 2015 The Institute of Electrical Engineers of Japan. 196 2. Basic Working Principle of WFSM under Proposed Integrated Drive System 2.1 Structure and Basic Working Principle of WFSM Figure 2 illustrates a general view of a 20-pole/24slot WFSM employing fractional-slot concentrated windings. The main machine part in the middle of the figure is composed of a laminated rotor core with 10 salient poles and a laminated stator core with three-phase armature concentrated windings accommodated in 24 slots. The back yoke core is made of soft magnetic composites (SMC) and forms axial field flux paths flowing into the field pole SMC cores located at both ends of the motor. Each field pole SMC core located at each end of the motor in the axial direction has the toroidal field coil" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000357_2015_60_2015_29__pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000357_2015_60_2015_29__pdf-Figure10-1.png", + "caption": "Fig. 10 Coordinate system for damper friction test.", + "texts": [], + "surrounding_texts": [ + "32\n\u3057\u3066\u3044\u308c\u3070\uff0cUSPG2013\u306f\u6b63\u3057\u3044FLP\u3092\u751f\u6210\u3057\u3066\u3044\u308b\u3053\u3068 \u306b\u306a\u308b\uff0e \u4e21FLP\u306e\u6bd4\u8f03\u3092Fig. 6\u306b\u793a\u3059\uff0e\u30b9\u30c8\u30e9\u30c3\u30c8\u8ef8\u5468\u308a\u03c680mm \u306e\u7bc4\u56f2\u306b\u304a\u3044\u3066\u6700\u5927\u8aa4\u5dee\u306f\uff0c1.1mm\u306b\u53ce\u307e\u3063\u3066\u304a\u308a\uff0c\u8eca\u4e21 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\u8a66\u9a131\u3068\u8a66\u9a132\u306e\u7d50\u679c\u306f\uff0c\u7b49KPM\u7dda\u30de\u30c3\u30d7[Nm]\u3068\u3057\u3066\uff0c Fig. 13(a), (b)\u306b\u793a\u3057\u305f\uff0e 5.3 \u691c\u8a0e \u8377\u91cd\u8ef8\u4e0a\u306e2\u70b9\u3068\u30ad\u30f3\u30b0\u30d4\u30f3\u8ef8\u4e0a\u306e2\u70b9\u304c\u540c\u4e00\u5e73\u9762\u4e0a\u306b\u4f4d \u7f6e\u3059\u308c\u3070\uff0cKPM\u306f\u7406\u8ad6\u4e0a\u30bc\u30ed\u3068\u306a\u308b5\uff09\uff0e\u5b9f\u65bd\u3057\u305f2\u3064\u306e\u8a66 \u9a13\u3067\u306f\uff0c\u3053\u306e4\u70b9\u306e\u3046\u30613\u70b9\u3092\u56fa\u5b9a\u3057\uff0c\u6b8b\u308a1\u70b9\u3092\u8d70\u67fb\u3057\u3066 \u3044\u308b\u3053\u3068\u306b\u306a\u308a\uff0cKPM\u304c\u30bc\u30ed\u3068\u306a\u308b\u8d70\u67fb\u70b9\u4f4d\u7f6e\u306f\uff0c\u8d70\u67fb \u5e73\u9762\u3068\u524d\u8ff0\u306e\u540c\u4e00\u5e73\u9762\u3068\u306e\u4ea4\u7dda\u4e0a\u306b\u304f\u308b\u3053\u3068\u304c\u5bb9\u6613\u306b\u60f3\u50cf 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"designv8_17_0003946_al-04249580_document-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003946_al-04249580_document-Figure8-1.png", + "caption": "Fig. 8: Engineering model RA.", + "texts": [ + " The panels are separated by a gap of 10mm, with 5mm coplanar alignment for each panel. The offset distance has been reduced from 5300 mm to 3100 mm, resulting in a corresponding decrease in the offset angle. The same feed used for the nine-panel RA is retained, but to achieve an almost uniform taper at the panel borders, the feed is directed towards the junction between the two panels, introducing two additional consecutive feed reference frame rotations. The two selected reflective surfaces (Figure 8a) consist of a total of 88 \u00d7 52 \u00d7 2 cells, with approximately 2.5% of the active physical aperture being occupied by mechanical inclusions (such as hinges and HRM) shown in Figure 8b. The mechanical inclusions are considered as short-circuited cells in the model, and their detrimental effects are taken into account and compensated for at the global level through the direct optimization process. The selected coverage region for the EM corresponds to the CONUS region, as defined in Section III-A, without specific city requirements. Therefore, the design and optimization 41st ESA Antenna Workshop on Large Deployable Antennas 25 - 28 September 2023 at ESA-ESTEC in Noordwijk, The Netherlands", + "3 16.9 23.3 23.6 23.7 requirements for the EM are less stringent compared to the full-size RA. For the EM design and optimization, the same unit cell geometry and methodology presented in Section III are employed. The properties of the dielectric substrate and honeycomb structure have been updated with experimental data provided by ESA. Similar to the 7m aperture RA, a reference shaped reflector with the same optics and feed, optimized using Ticra POS, was utilized for performance benchmarking. Figure 8c illustrates the layout of the optimized EM. The resulting radiation pattern footprint on Earth in terms of copolarization and XPD is shown in Figure 9. Table IV provides the performances in a 1% bandwidth, as well as in a 10% bandwidth. In the latter case, LHCP and RHCP Gaussian feed illumination was used for the reflector, RA PO, and RA DO, as the supplied real feed was optimized for a 1% bandwidth and not suitable for a larger bandwidth. The direct optimization process was performed at three frequencies within a 1% bandwidth, resulting in far-field performances that comply with the specifications" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002450_9668973_09729868.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002450_9668973_09729868.pdf-Figure3-1.png", + "caption": "FIGURE 3. Trajectory of the track grouser with a slippage coefficient \u03c3p.", + "texts": [ + " (12) and (13) yields the following system of equations: dXp (t) d (t) = ( Upt /( 1\u2212 \u03c3p ) \u2212 yp0 ) \u03c9 cos\u03c9t \u2212 ( xp0\u03c9 \u2212 Up /( 1\u2212 \u03c3p )) sin\u03c9t dYp (t) d (t) = ( Upt /( 1\u2212 \u03c3p ) \u2212 yp0 ) sin\u03c9t + ( xp0\u03c9 \u2212 Upt /( 1\u2212 \u03c3p )) cos\u03c9t (14) Eq. (14) is the trajectory equation of an arbitrary point M on the track plate with slippage. In this section, it is intended to establish a mathematical model of the relationship between vehicle steering time t and slippage coefficient \u03c3p based on the steering trajectory equation of tracked vehicle during slippage. Fig. 3 shows the displacement of an arbitrary track grouser on the P-side track that contacts the ground with a slippage coefficient of \u03c3p. When the track is at the initial position t = 0, the track grouser A0C0 at the front end of the track is in contact with the ground, and the track grouser A20C20 is at the last end of the track. When the vehicle steering time reaches t = t1, the corresponding track steering angle reaches \u03b1. Meanwhile, track grouser A0C0 leaves the ground, while track grouser A20C20 touches the ground" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001566_.5_0_2010.5_669__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001566_.5_0_2010.5_669__pdf-Figure8-1.png", + "caption": "Fig. 8 Definition of HRM parameters", + "texts": [ + " 0tan =b\u03b8 , ac \u03b8\u03b8 coscos = , 0tan =d\u03b8 (6) This result show that a driving link b can't move with a fixed link a, and a driven link d can't move with a connecting rod c in the spherical quadric crank chain mechanism shown in Fig. 3. It means that the link a and the link b drive together, which is the same as the movement of the hinge relocation in the cross-link mechanism. Therefore, requirement of the hinge relocation in the 3D space is to make all \u03b1 \u03c0 /2 with spherical quadric crank chain mechanism. Fig. 7 shows HRM (Hinge Relocation Mechanism). The design requirement of adjusting the central angle derived in Chapter 2 was filled HRM. The all rotation axis has gathered in the center in Fig.8, which is the same as Fig. 5. In Fig. 7, the two rotation axis are controlled in singular configuration (closed state) by using plates: the closed state in Fig. 7(b) is the position where all links are same positions, and hinge relocation can be realized in this state. There are rotation axis a and b at the same time, because revolute joint # 1 and #2 are lined up respectively #3 and #4 on two rotation axes as shown in Fig. 7(b) at the closed state shown in Fig. 9(a). Fig. 9(a) changes into Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004319_echaterobot_download-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004319_echaterobot_download-Figure8-1.png", + "caption": "Figure 8. Parts of the wrist structure", + "texts": [ + " P \u2013 total number of points i \u2013 criterion number j \u2013 number of the alternative p \u2013 criterial number of points n \u2013 number of rating criteria The alternative no. 3 scored the highest (13 points) and according to the ranking by the selected scoring method, this alternative is an optimum one. The alternative no. 3, Fig. 7, has been selected as another solution. MM SCIENCE JOURNAL I 2020 I MARCH The selected variant and the model\u2019s design in the CAD system are adjusted to the given servomotors. To maximize the required firmness of the structure, the relief holes were filled. PARTS OF THE SELECTED VARIANT\u2019S STRUCTURE Figure 8, part \u201ca\u201d shows the first segment of a kinematic chain, that can be bolted to any platform. This segment was specifically designed and dimensioned for the parameters of the selected and used servomotor. Figure 8, part \u201cb\u201d captures the second segment of the kinematic chain. A servomotor will be positioned onto its lower part to ensure the rotating movement of the third segment. Figure 8, part \u201cc\u201d represents the third segment of the chain. The bottom has a circular groove in which the third segment rotates on a tooth. A greater stability is thus achieved. The last, end segment, on Figure 8, part \u201cd\u201d has a storage space (a clip) for fastening of the robotic hand. The printing process started with conversion of the CAD models into a required format (*.stl) and its subsequent uploading into the printer-compatible program. The program enables the user to watch the process and the estimated time of printing completion, Fig. 9. Figure no. 10 shows the program\u2019s interface After the wrist was printed on a 3D printer, it was fitted with the Mechate Robot robotic hand and its functionality and overall firmness were tested, Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000642_download_16767_17232-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000642_download_16767_17232-Figure4-1.png", + "caption": "Figure 4 Representation of the transmission", + "texts": [], + "surrounding_texts": [ + "For the transmission-tires set, the torque provided to the load \u03c4L (EV in this case) by the electric motor is considered as input, and the output is the traction force Fte on the tires. If a simple transmission is considered, shown in the fi gure 4, where r is the radius of the tire, \u03b7g is the transmission effi ciency, and G is the ratio of angular speed reduction. The equations (7a) and (7b) model this type of transmission. Equation (7a) is used when the electrical machine delivers mechanical power, i.e. functions as motor (normal operation) and equation (7b) is used when the electrical machine receives mechanical power, i.e. functions as a generator (regenerative braking). (7a) (7b) Likewise, in equation (8) the relation between the linear velocity v of the EV and the angular velocity \u03c9r of the motor is shown. (8) Vehicle dynamics The forces acting on the EV moving on a slope with angle \u03b3, are shown in fi gure 5. The friction force Frr between the tires and the surface on which the vehicle moves is given by the equation (9). (9) where \u03bcrr is the friction coefficient, m is the EV total mass, g is the acceleration due to gravity, sign(\u00b7) is the sign function and v is velocity. The force of friction with the wind is the equation (10). (10) Where \u03c1 is the air density, A is the EV frontal area and Cd is the drag coefficient. The equation (11) is the force Fhc required to move up the EV over a slope, is the component of weight along the slope. (11) Applying Newton\u2019s second law to the EV and using equations (9), (10) and (11), the equation (12) that relates the traction force Fte with speed v is obtained: (12) where a is the EV acceleration. Considering the equation (13) of torques of IM. (13) where: \u03c4e is the electromagnetic torque, J is the total inertia (rotor and EV), B is the viscous friction coefficient of IM, \u03c9r is the rotor mechanical angular velocity, and \u03c4L is the load torque. In this case the motor load torque is the EV, therefore, it is possible to use equations (7a), (7b), (8), (12) and (13) to obtain the model of the mechanical part of the EV, equations (14a) and (14b). (14a) (14b) So the EV model is given by the equations (1), (2) for the electric part, (5) for the torque developed by the motor and (14a), (14b) for the mechanic part. Direct torque control The DTC allows precise and fast control of flux and torque of the IM required by the EV dynamics. This control strategy is widely used in EV [12]. With this control technique fast dynamic response, low switching frequency, and reduced harmonics are achieved [13]. Flux-linkage and torque Estimator For the DTC is necessary to estimate both the magnitude and angle of the stator flux-linkage space vector, as well as the electromagnetic torque. The estimation is based on the equation (2). The estimated stator flux-linkage space vector, equation (15), is obtained from the stator voltage equation [21]. (15) is the estimated stator flux-linkage space vector. To make this estimation the measurements of voltages and currents in the stator are used. This estimation also depends on the stator resistance. Already known (by estimation) the value of the stator fl ux-linkage space vector, it is possible to estimate the electromagnetic torque by the equation (16). (16) Direct torque control switching table The DTC is based on the electromagnetic torque, equation (5), by expressing the torque in terms of the modulus and and the angles \u03c1s and \u03c1r, of the stator and rotor fl ux-linkage space vectors equation (17) is obtained [ 22]. (17) Figure 6 shows the space vectors involved in the production of the torque. The rotor time constant of a standard squirrelcage IM is large; thus the rotor fl ux-linkage changes only slowly compared to the stator fl uxlinkage [22], and can be assumed that the rotor fl ux-linkage are constant. Therefore, the torque control can be carried out using the stator fl uxlinkage space vector. From (17) we can see that, holding constant and , the torque can be changed quickly by \u03c1s\u2013\u03c1r. Thus, in the DTC drive instantaneous torque control can be achieved by quickly changing the position or the stator fl ux-linkage space vector relative to the rotor fl ux-linkage space vector, which moves slowly. Moreover, the fl ux-linkage space vector (both its modulus and its angle) can be changed by the stator voltage space vector. This can be seen from the stator voltage equation (18). (18) If the stator ohmic drop are neglected, (Rsis = 0), the equation (19) is obtained. (19) If a short \u0394t time is consider (which tends to zero), when the voltage vector is applied, the equation (20) is obtained. (20) Thus the stator fl ux-linkage space vector can be changed directly by the stator voltage space vector. The inverter, shown in fi gure 2, can provide six active and two zero voltage space vectors, as shown in fi gure 7. Numbers in parentheses represent the inverter modulation signals Sa, Sb and Sc for each voltage space vector. Figure 7 also shows the six sectors of \u03c0/3 rad in which the plane is divided for the conventional DTC. The inverter voltage space vector can be expressed as shown in equation (21). (21) Figure 8 shows a block diagram of conventional DTC. The subscript ref indicates the reference values for the variables. The DTC uses two comparators: a two levels hysteresis comparator for the fl ow error (Figure 9a) and a three levels hysteresis comparator for the torque error (Figure 9b). Tolerance bands \u0394\u03c8 y \u0394\u03c4e set the allowable values for the fl ux and torque errors. If the output of fl ux comparator d\u03c8 is: 1 a stator fl ux increase is required, and 0 a stator fl ux decrease is required. For the torque comparator, if its output d\u03c4e is: 1 a torque increase is required, 0 no change in the torque is required, and \u20131 a torque decrease is required. According to the output of the fl ux and torque comparators, and the sector in which the stator fl ux-linkage space vector is located (see Figure 7), are the values that are sent to the inverter modulation signals Sa, Sb y Sc, see table 1. Direct torque control with stator ohmic drop compensation As mentioned in the previously, torque and flux control can be achieved by the stator flux-linkage space vector. If , is substituted in stator equation of the electrical subsystem of squirrel cage IM model, equation (22). (22) where the derivative of the modulus and the derivative of the angle of the stator flux-linkage space vector appear explicitly. Hence, the stator flux-linkage space vector can be directly manipulated by the stator voltage space vector. Equation (22) also shows the stator ohmic drop. Therefore, the compensation of this voltage drop is made if this equation is used to calculate the stator voltage space vector applied to the IM. To perform flux control, the derivative of the modulus of the stator flux-linkage is equaled to the flux error multiplied by a constant, equation (23). (23) Where k\u03c8 is the gain of flux controller, and e\u03c8 is the flux error. From this, equation (24) can be obtained. (24) Therefore, the controller defined by equation (23) is equivalent to an integral controller that acts directly on the flux. Moreover, the electromagnetic torque developed by the IM is proportional to the product of the modulus of the stator flux-linkage space vector and to the change of its position with respect to time (i.e. its time derivative), equation (25). (25) Therefore, the torque controller can be defined by the equation (26). (26) where k1 and k2 are the constants of torque controller, and et is the torque error. Equation (26) is equivalent to a proportionalintegral controller that acts directly on the torque developed by the IM. Substituting flux and torque controllers, equations (23) and (26), in equation (22). The direct flux and torque control with stator ohmic drop compensation is obtained in equation (27). (27) The ohmic drop is an important term in the voltage equation, principally at low speeds. In EV the speed of IM varies in a wide range including low speeds. Figure 10 shows the block diagram of the proposed controller, which is very similar to the block diagram of conventional DTC (Figure 8). The main difference is the way in that the stator voltage space vector is calculated: in the case of conventional DTC is calculated using table 1, and in the proposed controller is calculated by equation (27). Another difference is the way in which inverter modulation signals (Sa, Sb y Sc) are generated: in the conventional DTC these come directly from table 1, and in the proposed controller SVM technique is used. Also in the proposed controller, unlike the conventional DTC, hysteresis comparators are not used. Simulations This section presents simulations to evaluate the performance of conventional DTC and the proposed controller. For both torque controllers were used: the same PI controller for speed regulation, the same desired speed profi le, and the desired fl ux constant and equal to 0.8 Wb. The desired torque is the output of speed controller. The DC bus voltage is 360 V. EV parameters are given in table 2. The values of the hysteresis band used are \u0394\u03c8= 0.01 Wb\u00b7and \u0394te = 2.5 N\u00b7m. With these values a maximum switching frequency of approximately 30 kHz was obtained. The desired speed and the speed developed by the EV are shown in fi gure 11a and in fi gure 11b is presented the speed error which fl uctuates between \u00b10.0268 m/s. The desired torque (i.e. the output of speed controller) and the estimated torque are shown in fi gure 12a. The torque error, presented in fi gure 12b, do not remain at all times within the hysteresis band \u0394\u03c4e = 2.5 N\u00b7m. The estimated fl ux has a good track on to the desired fl ux (Figure 13) during the interval of time 0.5s < t < 15.5s. From 0 to 0.5 s and at the last 0.5 s simulation, fl ux tracking is not good because during this time the torque error is practically zero and, according to table 1, the inverter voltage is zero. The magnitude of the currents in the stator windings is closely related with the electromagnetic torque developed; hence its value varies along the simulation time as shown in fi gure 14a. A close to the currents during the interval of time from 8 to 8.1s is shown in fi gure 14b. DTC with stator ohmic drop compensation Figure 15 presents the desired speed and the speed developed by the EV, as well as the speed error. The desired speed is the same as for conventional DTC likewise the speed developed by the EV and speed error are very similar to those obtained in the simulation of conventional DTC (Figure 11), this is because the speed controller is the same for both simulations. The desired torque and estimated torque are shown in fi gure 16a. The torque error presented in fi gure 16b is lower than that obtained for conventional DTC. For the proposed controller torque error does not exceed \u00b11.3 N\u00b7m. Although both controllers have a suitable tracking of torque, the torque ripple is smaller in the proposed controller. As shown in fi gure 17, fl ux control also has better performance in the proposed controller that in the conventional DTC. The fl ux error, after passing the transitory is very small, it oscillates between \u00b13x10\u20133 Wb. Stator currents are shown in fi gure 18, its magnitude is very similar to those obtained with conventional DTC. However, as shown in fi gure. 18b, its distortion is much lower in the proposed controller. Conclusion The conventional DTC is a good option for torque control of IM that impulse EV. It is simple to implement. It has fast response and good dynamic performance. However, it has some drawbacks: high torque ripple, and variable inverter switching frequency. The values of the hysteresis bands for fl ux and torque controllers play a key role in the performance of the conventional DTC. If very large values are using, shall be poor performance, while resulting in low switching frequency. Instead, if too small values are used signifi cantly improves performance, but also increases the switching frequency and the limit imposed by semiconductor devices could be exceeded. Based on the principle of DTC, it follows that the torque and fl ux control can be carried out through the stator fl ux-linkage space vector. Moreover, the stator fl ux-linkage space vector can be modifi ed directly by the stator voltage space vector. A new improvement direct fl ux and torque control with stator ohmic drop compensation were obtained. The ohmic drop is an important term in the voltage equation, principally at low speeds. Based on the simulation results for: torque and fl ux errors, and distortion in the stator currents, it is shown that the performance of the proposed controller is higher that the performance of conventional DTC. References 1. C. Chan. \u201cPresent status and future trends of electric vehicles\u201d. Advances in Power System Control, Operation and Management. Vol. 1. 1993. pp 456-469. 2. D. Naunin. Electric vehicles. Proceedings of the IEEE International Symposium on Industrial Electronics. Warsaw, Poland. Vol. 1. 1996. pp. 11-24. 3. J. Larminie, J. Lowry. Electric Vehicle Technology Explained. 1st ed. Ed. John Wiley & Sons Ltd. Great Britain, RU. 2003. pp. 7-21. 4. S. Sallem, M. Chaabene, Be. Kamoun. A robust nonlinear of an Electric Vehicle in traction. Systems. Proceedings of the Signals and Devices. Djerba, T\u00fanez. 2009. pp. 1-6. 5. A. Foley, B. Gallachoir, P. Leahy, E. McKeogh. Electric Vehicles and energy storage - a case study on Ireland. Proceedings of the Vehicle Power and Propulsion Conference. Dearborn, USA. 2009. pp. 524-530. 6. R. Chicurel, G. Carmona, E. Chicurel, F. Gutierrez. Contribution of the National University of Mexico to Electric Vehicle Technology. Proceedings of the Electronics, Robotics and Automotive Mechanics Conference. Cuernavaca, M\u00e9xico. 2006. pp. 123-130. 7. F. Perez, G. Nu\u00f1ez, R. Alvarez, M. Gallegos. Step by step design procedure of an Independent-Wheeled Small EV applying EVLS. Proceedings of the IEEE Annual Conference on Industrial Electronics. Paris, Francia. 2006. pp. 1176-1181. 8. I. Alcal\u00e1, A. Claudio, G. Guerrero. Analysis of propulsion systems in electric vehicles. Proceedings of the International Conference on Electrical and Electronics Engineering. 2005. pp. 309-313. 9. O. Diaz. Environmental friendly electric transport for large cities. The case of Mexico City. Proceedings of the International Symposium on Industrial Electronics. Cholula, M\u00e9xico. Vol. 1. 2000. pp. 1-4. 10. L. Takahashi, T. Noguchi. \u201cA new quick-response and high efficiency control strategy of an induction motor\u201d. IEEE Trans. Ind. Appl. Vol. IA-22. 1986. pp. 820\u2013827. 11. M. Depenhrock. \u201cDirekte Selbstregelung (DSR) fiir hochdynamische Drehfeld-antriebe mit Stromrichterschaltung\u201d. ETZ A 7. Germany. 1985. pp. 211-18. 12. B. Singh, P. Jain, A. Mittal, J. Gupta. Direct torque control: a practical approach to Electric vehicle. Proceedings of the IEEE Power India Conference. New Delhi, India. 2006. pp. 1-6. 13. A. Bazzi, A. Friedl, S. Choi, P. Krein. Comparison of induction motor drives for electric vehicle applications: Dynamic performance and parameter sensitivity analyses. Proceedings of the IEEE International Electric Machines and Drives Conference. Florida, USA. 2009. pp. 639-646. 14. J. Faiz, M. Sharifian, A. Keyhani, A. Proca. \u201cSensorless Direct Torque Control of Induction Motors Used in Electric Vehicle\u201d. IEEE Transactions on Energy Conversion. Vol. 18. 2003. pp. 1-10. 15. N. Idris, C. Toh, M. Elbuluk. \u201cA New Torque and Flux Controllers for Direct Torque Control of Induction Motors\u201d. IEEE Transactions on Industry Applications. Vol. 42. 2006. pp. 1358-1366. 16. A. Haddoun, M. Benbouzid, D. Diallo, R. Abdessemed, J. Ghouili, K. Srairi. Comparative Analysis of Control Techniques for Efficiency Improvement in Electric Vehicles. Proceedings of the IEEE Vehicle Power Propulsion Conf. Arlington, USA. 2007. pp. 629-634. 17. E. Hassankhan, D. Khaburi. \u201cDTC-SVM Scheme for Induction Motors Fed with a Three-level Inverter\u201d. World Academy of Science, Engineering and Technology. Vol. 2. 2008. pp. 168-172. 18. M. Vasudevan, R. Arumugam. Simulation of Viable Torque Control Schemes of Induction Motor for Electric Vehicles. Proceedings of the Asian Control Conference. Greensboro, USA. 2004. pp. 1377-1383. 19. A. Trzynadlowski. Control of Induction Motors. 1st ed. Ed. Academic Press. USA. 2001. pp 64-81. 20. C. Ong. Dynamic Simulation of Electrical Machinery: Using Matlab/Simulink. 1st ed. Ed. Prentice Hall. New Jersey, USA. 1998. pp. 167-243. 21. J. Faiz, M. Sharifian. \u201cDifferent techniques for real time estimation of an induction motor rotor resistance in sensorless direct torque control for electric vehicle\u201d. IEEE Trans. on Energy Conversion. Vol. 16. 2001. pp. 104-109. 22. P. Vas. Sensorless Vector and Direct Torque Control. 1st ed. Ed. Oxford University Press. Oxford, UK. 1998. pp. 505-559." + ] + }, + { + "image_filename": "designv8_17_0000229_om_article_22311_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000229_om_article_22311_pdf-Figure2-1.png", + "caption": "Fig. 2. Meshed spur gear with tetrahedron meshing", + "texts": [], + "surrounding_texts": [ + "Vibration response as discussed in the above section has been applied to a pair of spur gears. As stated in earlier section, vibration response has been calculated for a multiple cracked gear. The plots thus obtained are shown in Fig. 3-5. The signal processing procedure is applied to the defect induced gears in form of crack and vibration response. The other signals have also been processed following the same procedure. More distortions and fluctuations in amplitude is clearly observed in multiple cracked gears. 46 VIBROENGINEERING PROCEDIA. DECEMBER 2021, VOLUME 39 The plots reestablish the fact that the choice of decomposition has strong influence on modeling performance reflecting the importance of accurate wavelet-based data pre-processing practice. The best decomposition level selected from results is same for two decomposition types which means choice of suitable decomposition level is determined by time series analyzed but has no relation to decomposition type used. Level 5 decomposition gives better results for multiple cracks. Higher level of decomposition increases the accuracy of de-noising to a very high extent. More fluctuations in amplitude are clearly observed in multiple cracked gears as compared to single cracked gears as seen in Fig. 4 and Fig. 5." + ] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureB.14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureB.14-1.png", + "caption": "Figure B.14: WPI, contact-aided compliant mechanism [4].", + "texts": [ + " Compared to the University of Coimbra design, the material used for the endoskeleton structure is urethane instead of a material with a higher Youngs modulus. Even though a compliance and performance analysis of the fingers/joints was missing, it Page 42 can be expected that the fingers have higher compliance in all directions. B.4 Other Compliant Mechanisms B.4.1 Worcester Polytechnic Institute (WPI) [4] A design methodology to translate from a crossed four-bar mechanism, used in prosthetic hands [37] to a flexible mechanism was presented by the Worcester Polytechnic Institute, see Fig. B.14. A similar mechanism was conceptually presented by Lotti and Vassura (University of Bologna) [13], where two rigid bodies were kept in contact by a ligament. In this case, two cross-curved leafsprings act as the ligaments. The trajectory of the mechanism was determined and used to create a contactaided mechanism. The design presents advantages as reduced compliance in the unwanted directions. However, it lessens some of the advantages of flexure mechanism, like frictionless and backlash after wear" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000752_el-04725201_document-FigureB.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000752_el-04725201_document-FigureB.1-1.png", + "caption": "FIGURE B.1 : Photo de la Biqu SE+ avec le kit Idex.", + "texts": [ + " XI XII ANNEXE B Processus de fabrication de circuit RF en impression 3D par DFF avec du PLA et de l\u2019Electrifi XIII Pour fabriquer des antennes ou des circuits RF, il est essentiel de pouvoir utiliser 2 mat\u00e9riaux : un di\u00e9lectrique (isolant) et un conducteur. En impression 3D par DFF, il y a deux techniques pour imprimer un objet avec deux filaments diff\u00e9rents. La premi\u00e8re technique est l\u2019utilisation d\u2019une imprimante poss\u00e9dant 2 t\u00eates d\u2019impressions. Au laboratoire Energy Lab, nous poss\u00e9dons une BIQU SE+ (figure B.1) et une makerbot (figure B.2) qui permettent directement d\u2019utiliser deux filaments. Imprimante 3D \u00e0 2 buses La Biqu SE+ (Idex) poss\u00e8de deux buses ind\u00e9pendantes. La makerbot quant \u00e0 elle poss\u00e8de deux buses mais une seule t\u00eate d\u2019impression. Ces imprimantes sont capables d\u2019imprimer deux filaments sans n\u00e9cessit\u00e9 de purge. L\u2019avantage est de pouvoir imprimer 2 mat\u00e9riaux sur une m\u00eame couche sans purge et sans changement de filament. Le principale inconv\u00e9nient de ces deux imprimantes est la pr\u00e9cision de r\u00e9alisation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004385_aper_ETC2017-356.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004385_aper_ETC2017-356.pdf-Figure6-1.png", + "caption": "Figure 6: CORN concept and tubes setup", + "texts": [ + " In addition, the numerical tool included the effect of the most important and deterministic HEX design decisions such as: dimensions and positioning of the tubes collectors, tubes geometrical characteristics (diameter, length, profile) and arrangement, modifications in the inner-outer flow currents relative orientation and HEX material selection among others. Additional details about the customizable numerical tool can be found in Yakinthos et al. (2015). The first of the two alternative concepts was named as CORN (COnical Recuperative Nozzle). The CORN concept is following a conical design with a 6/5/6 elliptic tubes arrangement, presented in Fig. 6. The elliptic tubes are bent as also shown in Fig. 6, in order to be aligned to the flow direction through the HEX and minimize inner pressure losses since the hot-gas mass flow encounters a much larger recuperator inlet region, thus entering inside the recuperator with significantly reduced flow velocity resulting in reduced outer pressure losses. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. The upstream region of the installation right before the HEX was redesigned in relation to the NEWAC nozzle configuration (including various modifications in the guiding walls and aerodynamic cone) in order to eliminate the size of the recirculation region which was developed there in the previous recuperation installations (reference, NEWAC) as much as possible" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003169_1_1_article-p624.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003169_1_1_article-p624.pdf-Figure3-1.png", + "caption": "Fig. 3. Single-row cross roller slewing bearings", + "texts": [ + " Its load capacity often determines the load capacity of the entire device (\u015apiewak, 2016). Therefore, improper operation of the crane may damage the bearing and contribute to the loss of boom stability (Fig. 2b) (Krynke and Mielczarek, 2016). The object of considerations is the slewing ring bearing used in the rotation mechanism of the DST - 5050 self-moving crane. In the case of the above crane, a cross roller bearing with a rolling diameter of 1400 mm and catalog symbol 1.KW.Z.T.50.1390.3.3.01 (Fig. 3) was used. The crane load characteristics are shown in Figure 4. The ADINA (2009) software was used to build the numerical model. The bearing rings and frames of the body and chassis were discredited by eight-nodes solid elements of 3D-solid type (Yu, 2017). Teeth of outer ring, holes for the bolts and small constructional details were omitted in the model of a bearing. Contact conditions were defined between adequate surfaces of the bearing rings and surfaces of its mounting (Kania et al., 2016; Wang et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004809_86_s13362-015-0015-z-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004809_86_s13362-015-0015-z-Figure1-1.png", + "caption": "Figure 1 MOS structure: Left: 3D tetrahedral mesh. Right: Doping profile in the case of the n-channel device.", + "texts": [], + "surrounding_texts": [ + "To evaluate the simulation performance of the methods for current calculation introduced in Section we have firstly considered a diode structure with a p-n junction geometrically represented by the cubic region = (, .) \u03bcm (see Figure (a)). A Gaussian implantation of donors with a peak of cm\u2013 and a depth of . \u03bcm (see Figure (b)) is made over a p-type region with a constant acceptor profile of cm\u2013 magnitude. One contact is defined for each of the doped regions: for the n-type part a rounded-shape contact is used (Top), while the p-type part is contacted at the bottom face (Body). As mentioned in Section ., contacts are considered of pure Ohmic-type with appropriate Dirichlet (a) FEMOS (b) Ref. [] Figure 3 n-MOSFET electron concentration at VGate = 2 V and VDrain = 0.1 V. Left: FEMOS calculation. Right: Ref. [30] calculation. boundary conditions: the Top is maintained at ground while the Body is ramped at . V. In Figure the results of the calculation of the current density vector field for electrons and holes in the semiconductor bulk are represented through streamlines connecting the Body with the Top contact. As expected the current calculation obtained with method DDFE (eq. (a) and (b)) is affected by a critical behavior, in particular close to and inside the n-junction as shown in Figure (a) and Figure (b) where instability has to be ascribed to numerical cancellation of the drift and diffusion contributions. Results get definitely better by employing method B using Eqs. (j) and (k) where the improvement can be appreciated in Figure (e) and Figure (f ). However, a careful inspection of the hole current density reveals that some numerical instability is still evident inside the n-junctions. The extension of the D SG scheme to D provided by method A in Eq. (h) and (p) results in the streamlines presented in Figure (c) and Figure (d): no spurious instability can be observed anymore and our calculations are in excellent agreement with the results of a commercial code (not shown here). The comparison between the different current computational methods has also been carried out on a p-channel MOSFET. The doping profiles have been obtained by using a -D process simulator with implantation and diffusion steps [] with the purpose to have a realistic doping as reported in Figure (a) with a GateLength : nm and a GateOx : . nm. The presence of floating non-compensated p-type regions in the channel body increases the computational difficulties. The D doping profile has been then extruded in three spatial dimensions, and the generated mesh is shown in Figure (b) where the device contact has been highlighted with purple color (the body contact is not shown in the picture but is located in the bottom face of the sili- con region). Regarding the calculation of Jp, the numerical difficulties found with method DDFE are still confirmed as clearly depicted in Figure (a) not only inside the p-type region but also around the floating regions present in the body (the visualization are referred to the bias conditions VG = \u2013 V and VD = \u2013. V). The marginality found using formula (k) is increased as reported in Figure (c): this comes by the fact that the evaluation of the coefficient in (i) is again undergoing numerical problems related to roundoff error. However method B is giving a much better current density evaluation with respect to the pure application of the Drift-Diffusion approach at the element level. We conclude this section by noting that, again, the best description of the expected physical behavior of the device is obtained by adopting method A, that turns out to provide an accurate and stable D extension of the D SG formula, as clearly demonstrated by Figure (b)." + ] + }, + { + "image_filename": "designv8_17_0002033_9858037_09858056.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002033_9858037_09858056.pdf-Figure4-1.png", + "caption": "Figure 4. Synchronous reluctance motor developed for electric railway trains by Mitsubishi Electric and its inside. (With the permission of Mitsubishi Electric Corporation.)", + "texts": [ + " It is desirable from a viewpoint of avoiding geopolitical risks to develop synchronous reluctance motors without using rare-earth metals. With such a background, Mitsubishi Electric announced that it had developed a high-efficiency synchronous reluctance motor with the world\u2019s-highest output power on November 26, September / October \u2014 Vol. 38, No. 5 45 2020 [4]. This new design is suitable for the traction motors in electric trains, and its inverter system is capable of variable speed control of the motor for the first time. Figure 4 shows the motor together with a cut-away image picture of its inside. The maximum output power of the motor developed for this purpose is 450 kW, whereas its continuous operable output power without causing heat elevation is 200 kW. The motor can reduce the power loss by about 50% compared with the company\u2019s conventional induction motor of a similar class [4]. Furthermore, the company conducted a verification test of the motor and its traction system in cooperation with Tokyo Metro Co. Ltd., a private electric subway company, from March 24 to April 14, 2021 [5]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004553_ai.7-12-2021.2314491-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004553_ai.7-12-2021.2314491-Figure7-1.png", + "caption": "Fig. 7 \u2018I\u2019- section model with ribs", + "texts": [ + " e developed concept should have the capability Model with twists at both the ends orientation as -time In this concept, double twist present at the bottom and one twist at the top as shown in figure 4. Frame is welded to the seat at one end and bolted at the bottom. In this concept, multiple twists are present at the bottom and one twist is at the top as shown in figure 5. Frame is welded to the seat at one end and bolted at the bottom. In this concept, \u2018I\u2019 section structure is used to support the seat as shown in figure 6. Frame is welded to the seat at one end and bolted at the In this concept, \u2018I\u2019 section structure with ribs as shown in figure 7 is used to support the seat structure. Frame is welded to the seat at one end and bolted at the bottom. I\u2019- section model to support the seat bottom. I\u2019- Section model with cross ribs In this concept, \u2018I\u2019 section structure with cross ribs as shown in figure 8 is used to support the seat structure. Frame is welded to the seat at one end and bolted at the bottom. Rapid Upper Limb Assessment (RULA) analysis was carried out in CATIA package and score for the body at different regions include upper arm, lower arm, wrist, neck, trunk, and legs are obtained [7]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004739_e_1023_context_ijaaa-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004739_e_1023_context_ijaaa-Figure4-1.png", + "caption": "Figure 4. Aero-diesels offer increased reliability, safety, performance, and lowest BSFC of all existing heat-engines.", + "texts": [ + " Gasoline engines are typically lighter in construction, but the new diesels can be all made of Published by Scholarly Commons, 2014 advanced lightweight aluminum alloys and there is additional space to up horsepower (performance tuning) without major modifications \u2013 something that would be impossible in an Otto engine. Existing enabling technologies when employed would make aero-diesel superior to gasoline engine and a tough competitor to light-to-medium turboshafts and turboprops. A color illustration of a modern aero-diesel with propeller attached is shown in Figure 4. Diesel engines are typically, 4-stroke or 2-stroke (cycle) with the number of cylinders varying from 1 to 20 depending on the application: marine diesels, railroad diesel-electric, trucks, personal cars, tanks, aero-engines, heavy-duty equipment, etc. (Woodyard, 2010). In the older diesel engines fuel was injected and atomized at a proper moment by using individual high-pressure pumps. A CMR high-pressure (HP) fuel delivery and DI for automotive use was developed in 1980\u2019s although diesels for submarine and marine applications had sort of CMR delivery systems developed in early 1920\u2019s" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003878_7042252_07080869.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003878_7042252_07080869.pdf-Figure2-1.png", + "caption": "FIGURE 2. Photographs of the fabricated water dielectric patch antenna. (a) Whole structure, (b) Side view, (c) Antenna under test.", + "texts": [ + " Therefore, it can be seen from the above analysis that for any requirement of practical applications, a proper height of substrate may be selected to achieve the desirable bandwidth. III. RESULTS AND DISCUSSION In order to demonstrate the correctness of the proposed design, a prototype of design I in Section II was fabricated and measured. The input characteristic of the antenna was measured by applying anAgilent Network Analyzer E5701C, while the radiation performance was measured by a Satimo Starlab near-field measurement system. A. WATER DIELECTRIC PATCH ANTENNA WITH METALLIC GROUND PLANE The fabricated prototype is depicted in Fig. 2. A water valve made of plastic is installed at a corner of the small plexiglass box for water injection. From the side view of the prototype shown in Fig. 2(b), it is seen that the whole antenna structure maintains a low profile. The height of the whole antenna including the thickness of the plexiglass box is 19 mm, corresponding to 0.059 \u03bb0 at 0.93 GHz. The antenna under test is illustrated in Fig. 2(c). In our design, the xoz and yoz planes are the E- and H- planes respectively. The simulated electric field distributions across the antenna are shown in Fig. 3. It can be seen that the electric field in the air substrate between the water patch and the ground plane is much stronger than the field in the water dielectric patch. The field is radiated from the two open ends of the water dielectric patch. Therefore, it is confirmed that the proposed water dielectric patch design works as a patch antenna instead of a DR antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001726_el-01651589_document-Figure1.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001726_el-01651589_document-Figure1.2-1.png", + "caption": "Figure 1.2: Smartphone frame representation.", + "texts": [ + " When a device is held in its default orientation, the X axis is horizontal and points to the right, the Y axis is vertical and points up, and the Z axis points toward the outside of the screen face. In this system, coordinates behind the screen have negative Z values. This coordinate system is used by the following sensors: accelerometer, gyroscope and magnetometer. The device\u2019s natural (default) orientation for smartphones is portrait. However, the natural orientation for many tablet devices is landscape. And the sensor coordinate system is always based on the natural orientation of a device. In Figure 1.2, frame is represented when the smartphone is layed and when smartphone camera is looking forward (AR). The World Geodetic System (WGS) is a standard for use in cartography, geodesy, and navigation including GPS. It comprises a standard coordinate system for the Earth, a standard spheroidal reference surface. The latest revision is WGS84 (EPSG:4326), established in 1984 and last revised in 2004. The WGS 84 datum surface is an ellipsoid with major radius Rmajor = 6378137 m and the polar semi-minor axis Rminor = 6356752" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004951_f_version_1635217587-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004951_f_version_1635217587-Figure13-1.png", + "caption": "Figure 13. CAD design (left) and actual picture (right) of the experimental setup. 1\u2014e-CVT; 2\u2014carrier shaft; 3\u2014MG/2 driver; 4\u2014ICE; 5\u2014ancillaries (hydraulic pump); 6\u2014cooling box.", + "texts": [ + " This figure shows that the engine was fully loaded during the acceleration, reaching peak power of 58 kW at 4000 rpm. The proposed solution has been developed as a full-scale vehicle prototype. The transmission layout is based on the proposed coaxial and concentric arrangement of the MG/1 and MG/2 machines, which are fully integrated with the planetary gear set. All the data of the vehicle, engine transmission, and drives correspond to those given in Appendix A. A picture of the experimental tractor is given in Figure 13. This figure shows the core of the transmission corresponding to the e-CVT layout from Figure 2, which is located at the center of the tractor, under the driver seat. Some important parts of the transmission are also shown in the picture; in particular, the combustion engine, the cooling box, the carrier shaft, one inverter, and additional mechanical loads constituted of hydraulic pumps. The e-CVT transmission is coupled, on the rear side of the tractor, with a standard tractor final driveline. The battery pack is safely installed in a box on the roof of the cabin" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure4-1.png", + "caption": "Figure 4. Joint robot and drive module components.", + "texts": [ + " Additionally, we will examine the various topologies of the AFPM motor and briefly describe the characteristics of the DRAFPM motor. Section 3 designs AFPM motors based on target RFPM motor specifications. Section 4 applies the effect analysis technique, optimizes the integer design variables preferentially, then optimizes the remaining real number design variables based on the progressive meta model. Section 5 utilizes the proposed process to advance the optimal design of the DRAFPM motor for robot joints. Section 6 summarizes the conclusions of this paper. Figure 4 shows the components of the joint robot and the drive module. Currently, RFPM motor for robot joints is mainly used as shown in Figure 5. The motor size has been reduced to a smaller size, and SPMSM\u2019s performance has reached its limit. Therefore, it is necessary to study the high torque of motor for robot joints. The AFPM motor shape is shown in Figure 6. The AFPM motor is thin and proportional to the cubic diameter. Therefore, the AFPM motor can effectively generate torque [21\u201324]. The shorter the axial length of the motor for robot joints, the better" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000372_9312710_09425552.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000372_9312710_09425552.pdf-Figure1-1.png", + "caption": "FIGURE 1. Configurations of two DSAFFSPM machines. (a) 12/10 U-core. (b) 6/10 E-core.", + "texts": [ + " In section III, the influence of E-core and U-core modular stators on air-gap field harmonics is investigated, together with different modular stator design parameters and different stator/rotor pole-number combinations. In addition, the contribution of working harmonics to flux density, EMF and electromagnetic torque is analyzed, taking advantage of FEA. In section IV, two topologies, i.e.,12/10U-core and 6/10 E-core DSAFFSPMmachines are built andmeasured in order to verify the FEA results and the above analysis based on the flux modulation. II. TOPOLOGY AND MODULATION PRINCIPLE The basic structure of DSAFFSPM machines with concentrated tooth-wound windings and U-core/E-core stator modules are presented in Fig. 1(a) and Fig. 1(b), respectively. They contain three parts, namely dual stators and one rotor sandwiched in between. The stator is constituted by the several identical modules, which can be seen in Fig. 2. Stator-side PMs are all circumferentially magnetized in the opposite direction, and circumferentially aligned between adjacent modules. It can be observed that the rotor has salient poles and the rotor-PMs are removed. The stator-side PMs provide a stationary PM MMF, which is modulated by the uneven permeance distribution of the rotatory salient poles" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003220_20JIYE_G1103158C.pdf-Figure2.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003220_20JIYE_G1103158C.pdf-Figure2.8-1.png", + "caption": "Figure 2.8 (a) Damped oscillation (b) Fourier transformation of ( )x t indicates the", + "texts": [ + "3 LOCOS birds beak ..................................................................................... 14 Figure 2.4 Schematic of a fully filled TSV structure near the wafer surface .............. 16 Figure 2.5 Inelastic scattering in Raman Spectroscopy ............................................... 19 Figure 2.6 Simplified Raman spectrometer layout ...................................................... 20 Figure 2.7 Line profile of a spectral line shows the line wings and line kernel .......... 21 Figure 2.8 (a) Damped oscillation (b) Fourier transformation of ( )x t indicates the intensity 2 0( ) ( )I A ....................................................................................... 23 Figure 3.1 Process flow (a) 100 \u00c5 thermal oxide deposition;(b) Boron implantation; (c) 8 k\u00c5 CVD oxide; (d) via formation by DRIE Si etch and using oxide as the hard mask; (e) liner deposition; (f ) Ta barrier/Cu seed deposition, Cu-ECP, Cu-CMP and nitride passivation layer deposition; (g) contact opening; and (h) Al metallization and patterning", + " With this approximation, which is still very accurate for real atoms, we obtain the solution of (2.7) as ( /2) 0 0( ) costx t x e t (2.9) The frequency 0 02 v of the oscillator corresponds to the central frequency ( ) /ik i kE E of an atomic transition i kE E . As the oscillation decreases gradually, the amplitude ( )x t decrease with time t. The emitted radiation is no longer monochromatic. Instead, it shows a frequency distribution related to the function ( )x t in (2.9) by a Fourier transformation (Figure 2.8). 24 Actually, the damped oscillation ( )x t is a superposition of a series monochromatic oscillations exp( )i t with different frequencies and amplitudes ( )A 0 1 ( ) ( ) 2 2 i tx t A e d (2.10) The amplitudes ( )A are calculated from (2.9) and (2.10) as the Fourier transform ( /2) 0 0 0 1 1 ( ) ( ) cos( ) 2 2 i t t i tA x t e dt x e t e dt (2.11) The lower integration limit is taken to be zero because ( ) 0x t for 0t . Equation (2.11) can readily be integrated to give the complex amplitudes 0 0 0 1 1 ( ) ( ) / 2 ( ) / 28 x A i i (2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003211_f_version_1426592263-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003211_f_version_1426592263-Figure2-1.png", + "caption": "Figure 2. Exploded view of the BDRM: (a) stator; (b) claw-pole rotor; (c) permanent-magnet rotor.", + "texts": [ + " Compared with other proposals of double rotor machines, some advantages of the BDRM can be summarized as follows: (1) BDRM\u2019s windings are mounted on the stator which is close to the motor case, so the windings have good heat dissipation; (2) There is no coupling between the stator phases, so the BDRM can be easily designed to be a multiphase structure; (3) It is appropriate that the BDRM is designed to be a multi-pole machine, so the BDRM is suitable for intermediate or high frequency operation; (4) BDRM\u2019s ring shaped windings are simple and the stator processing is convenient. In this paper, the torque characteristics and power factor of the BDRM are investigated. Based on the analysis results, a prototype was manufactured and the experimental results provided. Figure 2 shows the exploded view of the BDRM. It is a synchronous machine with a stator, claw-pole outer rotor and permanent-magnet inner rotor. The stator comprises laminated iron cores and ring-shaped windings, as shown in Figure 2a. The claw-pole rotor has three arrays of claws placed in non-magnetic bracket as shown in Figure 2b. Figure 2c shows the permanent-magnet rotor which is built in a flux-concentrated magnet topology. The flux path in one pole of the BDRM is shown in Figure 3. The flux from the magnet goes radially through the inner air gap into one claw, then across the outer air gap and into the stator, passing axially along the yoke, and once again radially passing the outer air gap into the next claw, and finally returns to the opposite polarity of the magnet, completing a flux loop. Brushless technology for a double-rotor machine is realized, which makes the BDRM a meaningful invention" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure3-1.png", + "caption": "Fig. 3 Coordinate system during turning machining.", + "texts": [ + " The coefficient matrix that transforms the rotating frame \u03a3m1 to the rotating frame \u03a3m2 is presented below: 1 2 2 1 2 2 2 1 2 1 2 2 2 2 21 1 1 cos sin cos sin sin cos sin cos sin sin sin cos sin cos sin cos 0 0 0 0 0 1 A A A Z A Z M \u2212 \u2212 \u2212 \u2212 \u2212 \u2212 \u2212 = (1) As shown in Fig. 2, the parameter u represents the radial distance of the worm. Additionally, the pressure angle of the pinion on both the i and e sides are referred to as \u03b1i and \u03b1e, respectively, and the tooth profile angles are represented by vi and ve. Finally, \u03b4 corresponds to the cone angle of the pinion. Due to the presence of a cone angle in the pinion, there is a difference in displacement along the axial and radial directions when it rotates by a certain angle. Fig. 3 illustrates the displacement in each direction within worm and cutter system. Respectively, the inference frame \u03a3mb (Omb: xmb, ymb, zmb) and \u03a3w (Ow: xw, yw, zw) are consistently linked to the worm and cutter, while the auxiliary coordinate system \u03a3a (Oa: xa, ya, za) has a positioning direction identical to that of \u03a3mb. The symbol \u03c6u represents the magnitude of the pinion's rotational angle around its za axis at a specific moment. p represents the axial helix parameter of the pinion, while pt corresponds to the radial helix parameter" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002838_f_version_1679473059-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002838_f_version_1679473059-Figure6-1.png", + "caption": "Figure 6. Extreme value of the tooth thickness coefficient of the reference circle: (a) maximum value; (b) minimum value.", + "texts": [ + " Tooth Thickness Coefficient of the Reference Circle As shown in Figure 2, in order to determine the shape of the linear tooth profile of the external gear, two parameters must be determined; the tooth profile angle \u03b2 and the vertical distance h can be selected. However, the vertical distance has no intuitive geometric meaning in the actual design; the tooth thickness coefficient of the reference circle is taken as the basic design parameter, and its geometric meaning is the ratio between the tooth thickness and pitch of the reference circle. The larger the coefficient, the larger the central angle corresponding to the tooth thickness of the reference circle, and the greater the bending strength of the tooth. As shown in Figure 6a, with the increase of the tooth thickness coefficient ks, the intersection H gradually moves to the right, and the corresponding tooth profile of the dedendum circle gradually decreases. When the tooth thickness coefficient reaches ks_max, the central angle corresponding to the tooth thickness reaches \u03b8max, and the dedendum circle will disappear. According to the geometric relationship, the following can be obtained:{ h = r1 sin(\u03b2 + \u03b8max/2) h = r f 1 sin(\u03b2 + \u03c0/z1) (37) Substituting the relationship between the design parameters in Table 2 into Equation (37), the following can be calculated: ks_max = z1 \u03c0 ( arcsin [ r f 1 r1 sin ( \u03b2 + \u03c0 z1 )] \u2212 \u03b2 ) (38) As shown in Figure 6b, with the decrease of the tooth thickness coefficient ks, the intersection H gradually moves to the left, and the corresponding tooth profile of the addendum circle gradually decreases. When the tooth thickness coefficient reaches ks1, the central angle corresponding to the tooth thickness reaches \u03b81, and the addendum circle will disappear. According to the geometric relationship, the following can be obtained: ra1 sin(\u03c0 \u2212 \u03b81/2\u2212 \u03b2) = r1 sin \u03b2 (39) Similarly, the following can be calculated from Equation (39): ks1 = z1 \u03c0 ( arcsin ( ra1 r1 sin \u03b2 ) \u2212 \u03b2 ) (40) It is assumed that the meshing point is at the vertex B of the linear tooth profile" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002827_eira_Unprotected.pdf-Figure2.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002827_eira_Unprotected.pdf-Figure2.3-1.png", + "caption": "Figure 2.3 \u2013 Geometric detail of the considered parts of the TET transformer.", + "texts": [ + " In addition, when the axes are displaced, the TET system behaves similarly at any direction of displacement due to the symmetry. A square core, on the other hand, has symmetry only if the relative rotational angle between the cores is a multiple of 90o. Thus, the behavior of this type of TET system with respect to the displacements between the coils is different if the coil axes displace in different directions. Besides, even if the central axes are lined up, a square TET core would change its behavior at any rotation different than 90o. In order to clarify the considered TET coils, Figure 2.3 details all the parts of the transformer considered during the project. 28 2 \u2013 Transcutaneous Energy Transfer and its Effects Observe that the primary core, external to the body, is surrounded mainly by air while the secondary core, underneath the skin, is surrounded mainly by fat. As mentioned in APPENDIX A, the thickness of the skin could vary between 5 and 30 mm, thus the value of the coil gap (between primary and secondary coils) affects the TET system design. During this research, this geometry was used in different configurations considering ferrite cores or coreless coils", + " Then, virtual prototypes were implemented in FE applications in order to continue with further analyses. Using the parametric tool of Flux-2D, the same simulation can be executed repeatedly while varying different parameters to make a sensitivity analysis and observe the response of the efficiency, regulation and SAR according to the parameters. Moreover, the simulations can be performed with different core materials as well as considering configurations with and without SRCs. Hence, the geometry of Figure 2.3 was simulated in Flux-2D with the default dimensions and the same properties as described in Section 3.5.1., and several scenarios were created in Preflu (input modulus of Flux-2D), varying individual geometrical and physical parameters as shown in Table 4.5. Each scenario was changing one of the parameters at a time while keeping the remaining parameters fixed. In order to obtain the equivalent circuit of the TET transformer, each scenario was simulated with different load conditions, representing short-circuit, nominal load (18", + " 4 \u2013 Sensitivity Analysis 129 130 4 \u2013 Sensitivity Analysis In order to make a more specific analysis of the efficiency and relative current density, the TET coils were implemented in Flux-2D considering coreless coils as well as cores with the five different geometries shown in Figure 4.25. The Flux-2D software performed a set of simulations with the coils aligned for the range of dimensions shown in Table 4.7 and with the same properties as described in Section 3.5.1. All the geometrical parameters are shown in Figure 2.3. 4 \u2013 Sensitivity Analysis 131 The simulation of the different core types was performed using Flux2D with both coils aligned while varying the geometry according to Table 4.7. The results are explicit in Figure 4.25, which shows the efficiency and the relative current density as functions of each dimension for all core types. Note that the worst configuration is when the coil has no magnetic core \u2013 the relative current density is the highest and the efficiency is one of the smallest. The configuration with core type V is as bad as coreless since this type of core entails in low efficiency (some cases even lower than coreless) and the relative current density induced in the skin from this kind of core is one of the worst", + " Therefore, the model is consistent and can be used to support the objective function in the optimization process. After the model was created, the multiobjective genetic algorithm (MGA) from Matlab was used to optimize the efficiency, regulation and SAR with less computational cost. Here, constraints such as minimal load power and coil area were inserted by the use of penalty functions as in (VIEIRA et al., 2004): 1. the load power should always be bigger than 12 W; 2. the region reserved to allocate the primary and secondary coils (the green region in Figure 2.3) should have space enough to fit all the turns of the coils. Thus, the objective functions of the MGA were to minimize: \ufffd \ud835\udc391 = \u2212\ud835\udc38\ud835\udc53\ud835\udc53\ud835\udc56\ud835\udc50\ud835\udc56\ud835\udc52\ud835\udc5b\ud835\udc50\ud835\udc66 \ud835\udc40\ud835\udc5c\ud835\udc51\ud835\udc52\ud835\udc59 + 10. (\ud835\udc43\ud835\udc52\ud835\udc5b\ud835\udc4e\ud835\udc59\ud835\udc61\ud835\udc66 \ud835\udc39\ud835\udc62\ud835\udc5b\ud835\udc50\ud835\udc61\ud835\udc56\ud835\udc5c\ud835\udc5b) \ud835\udc392 = \ud835\udc45\ud835\udc52\ud835\udc54\ud835\udc62\ud835\udc59\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c\ud835\udc5b \ud835\udc40\ud835\udc5c\ud835\udc51\ud835\udc52\ud835\udc59 + 10. (\ud835\udc43\ud835\udc52\ud835\udc5b\ud835\udc4e\ud835\udc59\ud835\udc61\ud835\udc66 \ud835\udc39\ud835\udc62\ud835\udc5b\ud835\udc50\ud835\udc61\ud835\udc56\ud835\udc5c\ud835\udc5b) \ud835\udc393 = \ud835\udc46\ud835\udc34\ud835\udc45 \ud835\udc40\ud835\udc5c\ud835\udc51\ud835\udc52\ud835\udc59 + 10. (\ud835\udc43\ud835\udc52\ud835\udc5b\ud835\udc4e\ud835\udc59\ud835\udc61\ud835\udc66 \ud835\udc39\ud835\udc62\ud835\udc5b\ud835\udc50\ud835\udc61\ud835\udc56\ud835\udc5c\ud835\udc5b) (6.2) In (6.2), the efficiency, regulation and SAR models are the respective models attained from the Kriging method and the penalty function is the sum of the following functions: \u2022 Penalty function for the load power: if the estimated modeled load power was smaller than the desired power (12 W), the difference between both was the penalty function. Otherwise, the penalty function was zero. This value was normalized by dividing it by 12. \u2022 Penalty function for the available region to allocate the primary coil (the top green region in Figure 2.3): the available area ((core inner diameter \u2013 core central diameter)*coil thickness) should be bigger than the number of turns times the cross-section of the considered wire (0.08 mm2). Hence, if the available area is smaller than the coil area, the difference between both areas was the penalty function. Otherwise, the penalty function was zero. This function was also normalized by dividing its value by the area of the coil. 6 \u2013 Optimization 179 \u2022 Penalty function for the available region to allocate the secondary coil (the bottom green region in Figure 2.3): the same procedure used for the primary coil was used here by considering the parameters from the secondary coil instead the primary coil. Moreover, since the regulation values were extremely high, an extra penalty function was added in order to strength its minimization. If the estimated modeled regulation was bigger than 100 %, this penalty function was the excess of 100 %; otherwise, it was zero. Thereby, a set of 32 different configurations for TET systems with and without SRCs was the result from the MGA technique" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure2-1.png", + "caption": "Figure 2: Load and Boundary Conditions of 4 Bar Mechanism.", + "texts": [ + " 36 iv Nomenclature \ud835\udc3a\ud835\udc5b Shear Modulus \ud835\udc3e\ud835\udc5b Bulk Modulus \ud835\udf0f\ud835\udc5b Relaxation time \ud835\udc62\ud835\udc56\ud835\udc5b Input displacement \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 Output displacement PRBM Pseudo-rigid-body model \ud835\udc58 Stiffness of PRBM \ud835\udc38 Elastic Modulus \ud835\udc61 Smallest width of compliant joint \ud835\udc45 Radius of compliant joint cutout \ud835\udc4f Thickness of compliant joint \ud835\udf03 Angle of deflection of complaint mechanism \ud835\udefe Drone landing slope angle \ud835\udefe\ud835\udc5f Characteristic radius factor \ud835\udc40 Moment imposed on compliant joint \ud835\udc3c Second area moment of inertia \ud835\udc50 Perpendicular distance from neutral point to furthest point on cross section v Figure 1: Mechanical model comprising of Hooke\u2019s element and \u201cn\u201d Maxwell Elements [4]. .... 3 Figure 2: Load and Boundary Conditions of 4 Bar Mechanism. ................................................... 4 Figure 3: Deflection distribution over time. .................................................................................. 4 Figure 4: Compliant 4 bar mechanism. .......................................................................................... 5 Figure 5: Maximum deformation 33.78 mm in -x at 120 seconds. ............................................... 7 Figure 6: Deformation profile over 2000 seconds of 4 bar compliant mechanism" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-8-1.png", + "caption": "Figure 2-8. Repr\u00e9sentation de la rotation du vecteur champ \u00e9lectrique E dans le plan xy", + "texts": [ + "....................... 35 Figure 2-4. Exemples de diagramme de rayonnement d'antenne ................................................. 37 Figure 2-5. Illustration de l'angle d'ouverture............................................................................... 37 Figure 2-6. Illustration de la conservation de l'\u00e9nergie dans une antenne .................................... 39 Figure 2-7. Composantes orthogonales du champ \u00e9lectrique ....................................................... 41 Figure 2-8. Repr\u00e9sentation de la rotation du vecteur champ \u00e9lectrique E dans le plan xy ......... 42 Figure 2-9. Polarisation en fonction du rapport Ey/Ex et du d\u00e9phasage\u03c6 .................................... 43 xvi Figure 2-10. Distribution du courant le long d'un dip\u00f4le en fonction du rapport d/\u03bb ................... 46 Figure 2-11. Diagramme de rayonnement d'un dip\u00f4le.................................................................. 47 Figure 2-12. Monopole quart d'onde et repr\u00e9sentation de son image...", + "18): ( ) ( ) ( ), , ,x x y yE z t E z t u E z t u= \u22c5 + \u22c5 (2.18) O\u00f9 ( )( ) ( )0 0( , ) Re cosj t kz x x xE z t E e E t kz\u03c9 \u03c9\u2212= = \u2212 (2.19) ( )( ) ( )0 0( , ) Re cosj t kz y y yE z t E e E t kz\u03c9 \u03c9 \u03c6\u2212= = \u2212 + (2.20) Avec 0xE et 0yE , les magnitudes maximum des composantes en x et en y du champ \u00e9lectrique. \u03b4 repr\u00e9sente la diff\u00e9rence de phase entre les deux composantes et xu et yu les vecteurs unitaires. Dans le cas g\u00e9n\u00e9ral, le vecteur champ \u00e9lectrique d\u00e9crit une ellipse dans le plan d'onde, comme le propose la Figure 2-8. A partir des expressions pr\u00e9c\u00e9dentes, nous pouvons d\u00e9finir le taux d'ellipticit\u00e9 ou rapport axial (AR) qui est le rapport de l'axe majeur, b, sur l'axe mineur, a et qui s'exprime selon l'expression (2.21) : 42 ( )0 0 2 2 0 0 1 2 sin1 tan arcsin 2 x y x y b AR a E E E E \u03c6 = = \u22c5 \u22c5 \u22c5 \u22c5 + (2.21) On distingue trois types de polarisation en fonction du taux d'ellipticit\u00e9 : - la polarisation lin\u00e9aire - la polarisation circulaire - la polarisation elliptique La polarisation est consid\u00e9r\u00e9e comme lin\u00e9aire si \u00e0 chaque instant, le champ \u00e9lectrique est orient\u00e9 selon une m\u00eame direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003644_article_25839670.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003644_article_25839670.pdf-Figure5-1.png", + "caption": "Fig. 5 Magnetic pole with unequal thickness", + "texts": [ + "8mm separately. From Fig. 4 we can see that a less slot opening width leads to a less cogging torque. But the slot opening width can not be designed too less because a narrow slot opening width is difficult for winding inserting. 0 0.5 1 1.5 2 2.5 3 -500 -400 -300 -200 -100 0 100 200 300 400 500 relative position/tooth pitch co gg in g to rq ue /m N *m Bs0=2.5mm Bs0=2.2mm Bs0=2.0mm Bs0=1.8mm Fig.4 Waveform of cogging torque with different slot opening widths Unequal thickness of magnetic pole. As shown in Fig. 5, the center of outer arc of magnetic pole with unequal thickness is at O, and that of the inner arc is at O\u2019. The thickness of magnetic pole h\u2019m(\u03b8) and the air-gap length \u03b4\u2019 (\u03b8) vary with the position angle. The eccentricity h is the distance between O and O\u2019. Different h determines different distribution of radial component of air-gap magnetic density. The radial component of air-gap magnetic density with no eccentricity is of the form ( ) ( ) ( ) m r m hB B h \u03b8 \u03b8 \u03b4 \u03b8 = + (8) The radial component of air-gap magnetic density with eccentricity is of the form Br(nz/2p) is derived from Fourier decomposition of Br 2(\u03b8), and the cogging torque can be analyzed with Eqn" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004399_.srce.hr_file_276795-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004399_.srce.hr_file_276795-Figure16-1.png", + "caption": "Fig. 16 The main parameters of the digging trajectory.", + "texts": [ + " TRANSACTIONS OF FAMENA XLI-3 (2017) 73 74 TRANSACTIONS OF FAMENA XLI-3 (2017) TRANSACTIONS OF FAMENA XLI-3 (2017) 75 Co-simulation of digging processes was performed by using the virtual excavator prototype model. The model was subjected to various working conditions to obtain adaptive joint trajectories. Table 4 describes the system parameters and digging behaviours of simulation scenarios, in which A, H, B, and \u03b1 represent the initial point, the lowest point, the final point, and the attack angle (Fig. 16). Table 5 lists the values of the ASMPIDF controller. The values of the excavator joints computed by means of kinematic equations were presented in Table 6. Scenario 1: The digging trajectory for soft soil was used, and the two control tasks of penetration and curl were executed (Fig. 17). First, the boom was rotated to press the bucket tip into the ground in the penetration segment. Subsequently, the sheared soil was curled at the desired depth. Scenario 2: This scenario was similar to Scenario 1 but with an increase in the penetration depth (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000637_f_version_1649326514-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000637_f_version_1649326514-Figure5-1.png", + "caption": "Figure 5. Simplified drawing of the SynRM with \u201ctrapezoidal-shape\u201d slot.", + "texts": [ + " The torque of an electric machine can be expressed as [35]: T = \u03c0D2Lstk 4 K\u0302s B\u0302g (1) where Lstk is the stack length, B\u0302g is the amplitude of the fundamental harmonic of airgap flux density, and K\u0302s is the linear current density, which is represented as: K\u0302s = kwQsncs I\u0302 \u03c0D (2) where kw is the winding factor, Qs is the number of stator slots, ncs is the number of series conductors per slot and I\u0302 is the phase current peak value. Therefore, the torque equation can be expressed as: T = 1 4 kwQsncs I\u0302 B\u0302gLstkDe\u03c7 (3) It is observed that the output torque is affected by the split ratio when the stator outer diameter De is fixed. The focus of this optimization lies in finding the optimal split ratio that achieves the highest torque. In this analysis, the rotor parameters (flux barrier number, barrier end angles and kair) remain the same. The stator slot is simplified to a trapezoidal shape, as shown in Figure 5. The slot opening is calculated from the slot pitch and stator tooth width, while the slot wedge is neglected. The flux density ratio \u03b2 is defined as the ratio of airgap flux density B\u0302g and stator teeth flux density Bt. Then, the stator teeth width wt is computed as [36]: wt = B\u0302g Bt \u03c0D Qs = \u03b2 \u03c0De Qs \u03c7 (4) This equation is also valid for non-linear conditions only if the leakage flux is neglected. The flux passing through the stator\u2019s back iron accounts for half of the main flux in the air gap, which is [36]: \u03a6bi = BbihbiLstk = 1 2 B\u0302g DLstk p (5) where Bbi is the flux density of the stator\u2019s back iron, p is the number of pole pairs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000403_citation-pdf-url_382-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000403_citation-pdf-url_382-Figure13-1.png", + "caption": "Figure 13. ADAMS Simulation Model for Two-Arm Test Platform", + "texts": [], + "surrounding_texts": [ + "The parallel robotic configuration for translational motion has a higher stiffness compared to the serial robotic configuration. It also has the following features: Large workspace, 360 degree around its base axis like a serial robot, analytic kinematic solution and analytic rigid-body dynamic solution. Applications and Design Requirements With these new features, the robot has the possibility to work with several conveyors and feeders placed around the robot. This is just one example of how a SCARA like parallel arm robot could be used to increase the productivity in an existing production line just by replacing conventional SCARA robots used today with its parallel arm cousins. 588 Industrial Robotics: Theory, Modelling and Control Typical Applications Spot welding and painting are among the earliest application for industrial robot. Their payload is usually less than 50 kg. Repeatability requirement is in the range of 100 \u03bcm. Pick and place and packaging have relatively low requirement on repeatability and stiffness. Payload varies from 1 to 500 kg. High speed is preferred for high productivity. Machining or material removal including deburring, grinding, milling and sawing, requires high stiffness. Stiffness and accuracy of the robot decide the quality of the machined product. Potential Applications Laser cutting or welding, as a non-contact process requires an accu- racy/repeatability less than 100 \u03bcm. Payload, which is the laser gun and accessories, is usually less than 50 kg. Speed required is not high in such applications. Coordinate measuring function is typically performed by a CMM. It has a strict accuracy requirement of less than 50 \u03bcm for both static and path following at a low speed. Fine material removal is as precision machining application now dominated by CNC machines. It requires the highest stiffness and system accuracy. Error Modeling and Accuracy of Parallel Industrial Robots 589 Table 2 shows the performance comparison between the TAU robot and the gantry robot currently used in laser cutting application, which indicates the potential applications instead of using linear gantry robot. The performance of TAU covers all advantages of the Linear Motor Gantry. Figure 12. Single Arm Test Platform for Drive Motor Error Analysis Displacement sen- Direct drive acCarbon fiber composite arm Error Modeling and Accuracy of Parallel Industrial Robots 591 3. Kinematics of Tau configuration 592 Industrial Robotics: Theory, Modelling and Control For Point D1: 4 )120sin()sin( )120cos()cos( 111 1333111 1333111 ddD aaD aaD z y x \u2212= +\u2212= +\u2212= \u03b8\u03b8 \u03b8\u03b8 121 )( aPDdist =\u2212 For Point D2: 23212 1212 1212 )sin( )cos( ddD aD aD z y x += = = \u03b8 \u03b8 222 )( aPDdist =\u2212 For Point D3: 313 1332313 1332313 )120sin()sin( )120cos()cos( dD aaD aaD z y x = +\u2212= +\u2212= \u03b8\u03b8 \u03b8\u03b8 323 )( aPDdist =\u2212 Basic equations 2 1 2 1 2 1 2 12 )()()( PzDpyDPxDa zyx \u2212+\u2212+\u2212= (1) 2 2 2 2 2 2 2 22 )()()( PzDPyDPxDa zyx \u2212+\u2212+\u2212= (2) 2 3 2 3 2 3 2 32 )()()( PzDPyDPxDa zyx \u2212+\u2212+\u2212= (3)" + ] + }, + { + "image_filename": "designv8_17_0003239_haped_Microstrip.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003239_haped_Microstrip.pdf-Figure1-1.png", + "caption": "Fig. 1. Proposed design of the E-shaped microstrip patch antenna.", + "texts": [ + " It is noted that the existing work has discussed the antennas for ITS with larger in size and provided results are not up to mark can be utilized for tolling. The aim of this paper is more especially to design a compact size antenna with better and efficient results. We have designed the E-shaped microstrip patch antenna for the intelligent transportation systems application. III. PROPOSED ANTENNA DESIGN Transmission-line model is used for analyzing the suggested E-shaped microstrip patch antenna design [22]. The design of the suggested E-shaped microstrip patch antenna is illustrated in Fig. 1, where pW and pL represents the patch width and patch length respectively, therefore, the size of the metallic radiating patch of the proposed antenna is p pW L . Furthermore, sW , sL and h represents the width, length, and height of dielectric substrate respectively, therefore, the size of the dielectric substrate of the suggested antenna is s sW L h . Moreover, fW , fL , g and oy represents the feed line width, feedline length, inset gap and inset length, respectively. The proposed antenna operating frequency of , the dielectric constant of the substrate r and the height (thickness) of the dielectric substrate are 960 MHZ, 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000403_citation-pdf-url_382-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000403_citation-pdf-url_382-Figure10-1.png", + "caption": "Figure 10. Useful 2/2/2 Clustering Strategies when the Links of Type A are Attached to the Actuator Platform in a 3-D pattern. (Courtesy of Brogardh, T, 2000).", + "texts": [], + "surrounding_texts": [ + "A new class of parallel robot, namely, TAU robot, has been created based on the 3/2/1 configuration. It combines the performance advantages of parallel arm mechanism (e.g., high stiffness, high accuracy) with the large workspace of serial robot. As shown in Figure 11, the primary design of the TAU prototype robot has three actuators mounted on the base fixture and arranged in a line, which is called an I-configuration TAU. From bottom to top, actuators and upper arms (type B link) are numbered as 1, 2 and 3, and connected with 3, 2 and 1 lower arm(s) (type A link) respectively. This configuration basically performs a 3- DOF motion in its workspace. The 3-DOF parallel robot has a small footprint but with an enhanced stiffness. The six links (lower arms) connected to the tool plate are driven by the three upper arms rotating around Z-axis. This structure has 3 DOFs in its workspace. With its geometric constraint, the DOF of a TAU robot is equal to (Tsai, 1999) DOF = = +\u2212\u2212 1 )1( i ifjn\u03bb \u03bb : degree of freedom of the space in which a mechanism is intended to function Error Modeling and Accuracy of Parallel Industrial Robots 587 n: number of links in a mechanism, including the fixed link j: number of joints in a mechanism, assuming that all the joints are binary. if : degree of relative motion permitted by joint i." + ] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure14-1.png", + "caption": "Figure 14. Bar chart of calculated stator total losses for Motor #1 and Motor #2; rotational torque is treated as input quantity and is identical for both motors.", + "texts": [ + " Losses in Motor #2 core are greater than those of Motor #1 on account of higher values of flux density (produced by permanent magnets) in the electromagnetic circuit (see Figure 5) and higher supply currents (Figure 11). We may observe in these curves that core losses increase as rotational speed increases and then they stabilize at more or less constant levels; this is due to field weakening and operation in the second control zone. The field weakening zone for Motor #1 is commenced somewhat earlier. Characteristics of calculated stator total losses are presented in Figure 14; this is the sum of losses shown in Figures 11 and 13. It must be noted that these losses determine temperature distribution in the stator core. The stator core is heated by its own losses and winding losses, which are transferred through the core to the coolant. In the case of lowest loads (rotational torque Tm = 50 Nm) losses of Motor #2 are higher over the entire range of rotational speed. These are mostly losses generated in the stator\u2019s magnetic core; throughout the entire operational range, these losses are higher in Motor #2 (Figure 14). As the load increases, winding losses increase in both motors, but winding losses in Motor #1 increase at a much higher rate (see Figure 11), while stator core losses do not vary much with changes in the current. When charts for different losses are compared, we observe that while load increases, the area where Motor #2 losses are lower than Motor #1 losses moves away from lower speeds towards maximum speed. In the case of rotational torque equal to Tm = 450 Nm, total losses generated in the motor stator are higher in Motor #1 over the entire rotational speed range", + " Temperature rise in motor elements is influenced by the ratio of existing power losses to the area of heat removal. Design of Motor #2, with respect to Motor #1, is characterized by greater stator diameter and diameter of structure containing a water-cooling system. Thus, while lengths of both motors are identical, the area of heat removal is greater in Motor #2. Bar charts showing the ratio of stator total losses to area of structure, where stator is positioned, are presented in Figure 17. If we compare losses shown in Figure 14 charts, with charts showing the ratio of these losses to the heat removal area (Figure 17), then we see that Motor #2 is much more promising; this is especially noticeable in the case of maximum speed at load torque equal to Tm = 450 Nm and Tm = 350 Nm. A similar comparison was performed for winding losses in Figure 18. Total slot area is much greater in Motor #2 (SQ = 3389.4 cm2) than in Motor #1 (SQ = 235.6 cm2). Ratio of power losses generated in permanent magnets to the rotor surface area where magnets are mounted is shown in Figure 19" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004360_rticle_125987571.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004360_rticle_125987571.pdf-Figure4-1.png", + "caption": "Fig. 4. Horizontal movement.", + "texts": [ + " The limited working height of the existing equipment did not allow tests with a standardized dummy. For testing complete car seats with full loading, it is necessary to increase this height to a minimum of 2000 mm. Also, according to current standards [2] prescribing the testing of car seats in laboratory conditions, it is necessary to add the horizontal movement of the seat during testing, i.e. forward and backward. The testing device was increased to 2400 mmworking height (Fig. 2). The horizontal movement of the platform was designed from the existing two horizontal plates (Fig. 4), between which the linear servo motor actuator series GSM40 was placed. The linear motor servo actuator GSX60 ensures vertical movement. The new test equipment offers the possibility of both how vertical and so horizontal loading of the car seat, as well as their combination while moving. Themethodology of testing car seats is based on the conditions of the corresponding standards. It will be evaluated by comparing how to change the properties seats when loaded only vertically and when loaded vertically and so at the same time horizontally" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000046_cle_download_743_255-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000046_cle_download_743_255-Figure8-1.png", + "caption": "Figure 8: Equivalent creep strain at 30 s", + "texts": [ + " At the edges around the interface, the heat flux comes from the directions that are not blocked by the thermal insulate layer, as a result, the thermal shock appears. The instant thermal stress and strain distribution in the symmetry plane of chip Q1 at 30 s are shown in Fig. 6, it can be seen obvious stress and strain concentration at the interfacial edge between wafer and Pb5Sn (denoted by E12 in follows), and SnAg3Cu0.5 and Cu (denoted by E45 in follows). Fig. 7 shows the equivalent stress distribution in materials 1, 2 and 3 near the interfacial edges. The stress concentration is found at the interfacial edge between materials 1 and 2. Fig. 8 depicts the equivalent strain distribution in materials 3, 4 and 5, and we can also see a severe strain concentration appearing at the interfacial edge between materials 4 and 5. Here the failures of solder joints are mainly concerned, it can be understood from the stress and strain distributions that the failures may occur at the interfacial edges of either E12 or E45. Therefore, the singular stress and strain near these interfacial edges need to be investigated carefully. For this purpose, two data points A and B at E12 and E45 are selected, respectively, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000812_wnload_266261_262421-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000812_wnload_266261_262421-Figure7-1.png", + "caption": "Fig. 7. Deformation contour helix angle: a \u2013 20 degree; b \u2013 30 degrees; c \u2013 14.5 degrees", + "texts": [ + " 6 that the pressure angle of 20 degrees is better in terms of bearing stress compared to the other angles. 5. 3. Effect of helix angle on stress and deformation values The study of this research paper depends on helical gears. It is necessary to study the angles of the helical teeth, as it gives a clear idea of the contact area of the meshed gears. It is known that the increase in the angles of the helical teeth increases the large contact area between two gears and reduces the resulting noise. In Fig. 7 of the resulting deformation values, it is noted that the deformation value is 4.26\u00d710-6 m when the helix angle is 20 degrees and 3.47\u00d710-6 m when the helix angle is 30 degrees, 3.1\u00d710-6 m when the helix angle is 30 degrees, and 3.1\u00d710-6 m when the helix angle is 45 degrees. Figs show that the increase in the angle of the helix increases the contact area and thus increases the ability of the gear to withstand deformations, as in the angle of the helix of 45 degrees. Along the length of the tooth in contact, a fluctuation in the range of values is seen", + " Helical gears are a key component of this research paper\u2019s analysis. The enormous contact area between two gears is known to rise as the angles of the helical teeth increase. The deformation value is 4.26\u00d710-6 m when the helix angle is 20 degrees, according to the calculated deformation values. Knowing the stresses\u2019 values can help to determine how much contact there is between the gears. It should be mentioned that for helix angles of 20 and 30, respectively, the stress value was 1.93\u00d7108 Pa and 1.86\u00d7108 (Fig. 7, 8). Because of the lack of such research studies, this encouraged us to do such work, and it was not easy to compare it with other works that were somewhat far from our work, so we just are content with mesh independency. One of the most important problems encountered is the inability to connect multiple gears to a large extent because the meshing feature is limited in the program. We do not have supercomputers to solve complex problems, as the multiplicity of gears increases the value of the mesh, and therefore we need supercomputers to solve it" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004103_advpub_21-00160__pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004103_advpub_21-00160__pdf-Figure6-1.png", + "caption": "Fig. 6 Attachment angle of a rigid and small subsystem A onto the main system B. The z-axis of the principal axis of inertia corresponds to an axis obtained by inclining the Z-axis of the global coordinates by \ud835\udf03\ud835\udc4b [rad] around the X-axis.", + "texts": [], + "surrounding_texts": [ + "\u00a9 The Japan Society of Mechanical Engineers\n\u63a1\u7528\u3059\u308b\u5358\u4f4d\u7cfb\u3092\u9593\u9055\u3048\u308b\u3068\uff0c\u5171\u632f\u767a\u751f\u4e88\u6e2c\u5e2f\u57df\u306e\u5e45\u304c\u5927\u304d\u3059\u304e\u3066\uff0c\u7b2c 3\u30fb2 \u7bc0\u3068\u7b2c 3\u30fb3 \u7bc0\u306b\u63d0\u6848\u3057\u305f\u65b9\u6cd5\u306e\u5229 \u7528\u306b\u56f0\u96e3\u3092\u4f34\u3046\uff0e\u9069\u5207\u306a\u5358\u4f4d\u7cfb\u3092\u63a1\u7528\u3059\u308b\u5de5\u592b\u304c\u5fc5\u8981\u3067\u3042\u308b\uff0e\n\u8457\u8005\u3089\u304c\u7528\u3044\u3066\u3044\u308b\u5358\u4f4d\u7cfb\u306e\u9078\u629e\u65b9\u6cd5\u3092\u7d39\u4ecb\u3059\u308b\uff0e\u524d\u6bb5\u843d\u3067\u8ff0\u3079\u305f\u7406\u7531\u306b\u57fa\u3065\u3051\u3070\uff0c\u5f0f\uff0817\uff09\u306e\u4e0a\u9650\u3068\u4e0b\u9650\u3092\n\u72ed\u3081\u308b\u306b\u306f\uff0c\u5358\u4f4d\u7cfb\u3092\u5de5\u592b\u3057\u3066\u5f0f\uff088\uff09\u306e\u5404\u6210\u5206\u306e\u6bd4\u7387\u3092\u5c0f\u3055\u304f\u3059\u308b\u3053\u3068\u304c\u809d\u8981\u3067\u3042\u308b\u3068\u308f\u304b\u308b\uff0e\u305d\u3053\u3067\uff0c\u8cea\u91cf\uff0c \u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u5024\u3092\u306a\u308b\u3079\u304f\u540c\u3058\u5927\u304d\u3055\u306b\u3059\u308b\u3088\u3046\u306b\u5358\u4f4d\u7cfb\u3092\u9078\u629e\u3059\u308b\u3053\u3068\u304c\u4e00\u3064\u306e\u89e3\u6c7a\u7b56\u3068\u306a\u308b\uff0e\u4f8b\u3048\u3070\uff0c \u5206\u7cfb A \u304c\u5bf8\u6cd5 50\u00d750\u00d750 mm\uff0c\u4f53\u7a4d\u5bc6\u5ea6 \ud835\udf0c = 8000 kg/m3\u306e\u76f4\u65b9\u4f53\u3068\u3059\u308b\uff0e\u3053\u306e\u3068\u304d\uff0c\u8868 1 \u306b\u793a\u3059\u3088\u3046\u306b\uff0cMKS \u5358\u4f4d\u7cfb\u3067\u306e\u8cea\u91cf\u306f\ud835\udc5a = 1 kg\uff0c\u6163\u6027\u4e3b\u8ef8\u3067\u306e\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306f\ud835\udc3c\ud835\udc65 = \ud835\udc3c\ud835\udc66 = \ud835\udc3c\ud835\udc67 \u2245 4 \u00d7 10\u22124 kg\u30fbm2\u3067\u3042\u308a\uff0c\u305d\u306e\u6bd4\ud835\udc3c\ud835\udc65/\ud835\udc5a \u306f\u7d041/2500\u500d\u3067\u3042\u308b\uff0e\u4e00\u65b9\uff0cCGS \u5358\u4f4d\u7cfb\u3067\u306e\u8cea\u91cf\u306f\ud835\udc5a = 1 \u00d7 103 g\uff0c\u6163\u6027\u4e3b\u8ef8\u3067\u306e\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306f\ud835\udc3c\ud835\udc65 = \ud835\udc3c\ud835\udc66 = \ud835\udc3c\ud835\udc67 \u2245 4 \u00d7 103 g\u30fbcm2\u3067\u3042\u308a\uff0c\u305d\u306e\u6bd4\u306f\u7d04 4 \u500d\u3068\u5c0f\u3055\u3044\uff0e\u305f\u3060\u3057\uff0c\u5206\u7cfb A \u306e\u5bf8\u6cd5\u304c 500\u00d7500\u00d7500 mm \u306b\u306a\u308b\u3068\uff0c MKS \u5358\u4f4d\u7cfb\u3067\u306e\u6bd4\ud835\udc3c\ud835\udc65/\ud835\udc5a\u306f\u7d041/25\u500d\uff0cCGS \u5358\u4f4d\u7cfb\u3067\u306e\u6bd4\u306f\u7d04400\u500d\u3067\u3042\u308b\uff0e\u5206\u7cfb A \u306e\u5bf8\u6cd5\u304c 50\u00d750\u00d750 mm \u306e\u5834 \u5408\u306f CGS \u5358\u4f4d\u7cfb\u3092\u9078\u3073\uff0c500\u00d7500\u00d7500 mm \u306e\u5834\u5408\u306f MKS \u5358\u4f4d\u7cfb\u3092\u9078\u3076\u3053\u3068\u3067\uff0c\u5f0f\uff088\uff09\u306e\u5404\u6210\u5206\u306e\u6bd4\u7387\u304c\u8fd1\u3065 \u304d\uff0c\u5f0f\uff0817\uff09\u306e\u4e0d\u7b49\u5f0f\u306e\u7bc4\u56f2\u304c\u72ed\u307e\u308b\uff0e\u3053\u306e\u3088\u3046\u306b\uff0c\u8a2d\u8a08\u5bfe\u8c61\u306e\u5206\u7cfb\u306e\u8cea\u91cf\u3068\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u5024\u306e\u5dee\u304c\u5168\u4f53\u306b \u5c0f\u3055\u304f\u306a\u308b\u5358\u4f4d\u7cfb\u3092\u63a1\u7528\u3059\u308b\u3053\u3068\u3067\uff0c\u5f0f\uff0817\uff09\u306b\u3088\u308b\u5171\u632f\u767a\u751f\u4e88\u6e2c\u5e2f\u57df\u3092\u72ed\u3081\u3089\u308c\u308b\uff0e\n\u306e\u30e9\u30fc\u30e1\u30f3\u69cb\u9020\u3068\u3057\u305f\uff0ex\u65b9\u5411\u306b\u6a2a\u305f\u308f\u308b\u9577\u3055 1000 mm\uff0c\u5e45 20 mm\uff0c\u539a\u3055 10 mm\u306e\u5747\u8cea\u4e00\u69d8\u306a\u4e2d\u5b9f\u306f\u308a\u306e\u4e0a\u306b\uff0c \u9ad8\u3055 50 mm\uff0c\u5e45 20 mm\uff0c\u539a\u3055 5 mm\u306e\u5747\u8cea\u4e00\u69d8\u306a\u4e2d\u5b9f\u306f\u308a\u306e\u652f\u67f1 2\u672c\u304c\u525b\u7d50\u5408\u3055\u308c\uff0c\u305d\u306e\u4e0a\u306b\uff0c\u9577\u3055 250 mm\uff0c\u5e45 20 mm\uff0c\u539a\u3055 2 mm \u306e\u5747\u8cea\u4e00\u69d8\u306a\u4e2d\u5b9f\u306f\u308a\u306e\u5929\u677f\u304c\u525b\u7d50\u5408\u3055\u308c\u305f\u69cb\u9020\u3067\u3042\u308b\uff0e\u4e0a\u90e8\u306e\u30b3\u306e\u5b57\u69cb\u9020\u306e\u652f\u67f1\u306f\uff0c\u4e0b\u90e8 \u306e\u306f\u308a\u306e\u5de6\u7aef\u304b\u3089 225 mm \u304a\u3088\u3073 475 mm \u306e\u4f4d\u7f6e\u3067\u525b\u7d50\u5408\u3055\u308c\u3066\u3044\u308b\uff0e\u56f3 5 \u306b\u793a\u3059\u3068\u304a\u308a\uff0c\u30b3\u306e\u5b57\u69cb\u9020\u306e\u5929\u677f\u4e2d \u592e\u306b\u5fae\u5c0f\u5206\u7cfb A\u306e\u53d6\u4ed8\u70b9\u304c\u3042\u308b\uff0e\u53f3\u624b\u7cfb\u306e\u30b0\u30ed\u30fc\u30d0\u30eb\u5ea7\u6a19\ud835\udc4b, \ud835\udc4c, \ud835\udc4d, \ud835\udf03\ud835\udc4b, \ud835\udf03\ud835\udc4c , \ud835\udf03\ud835\udc4d\u306e\u65b9\u5411\u3082\u56f3 5 \u306b\u793a\u3059\u3068\u304a\u308a\u3068\u3059\u308b\uff0e\n\u5fae\u5c0f\u5206\u7cfb A \u3092\u4e3b\u7cfb B \u306b\u53d6\u308a\u4ed8\u3051\u308b\u65b9\u6cd5\u3092\u8aac\u660e\u3059\u308b\uff0e\u5fae\u5c0f\u5206\u7cfb A \u306f\u8a2d\u8a08\u5bfe\u8c61\u3067\u3042\u308b\u306e\u3067\uff0c\u5f62\u72b6\u3084\u5bf8\u6cd5\u306f\u63d0\u6848\u6cd5 \u306b\u3088\u308a\u5b9a\u3081\u3066\u3044\u304f\u304c\uff0c\u3053\u306e\u6570\u5024\u4f8b\u3067\u306e\u53d6\u4ed8\u89d2\u306b\u306f\uff0c\u56f3 6(a)\u306b\u793a\u3059\u3088\u3046\u306b\uff0c\u30b0\u30ed\u30fc\u30d0\u30eb\u5ea7\u6a19\u306e\ud835\udc4d\u8ef8\u304b\u3089\ud835\udc4c \u2212 \ud835\udc4d\u9762\u5185\u3067 \ud835\udf03\ud835\udc4b [rad] \u3060\u3051\u6b63\u65b9\u5411\u306b\u56de\u8ee2\u3055\u305b\u305f\u65b9\u5411\u304c\uff0c\u6163\u6027\u4e3b\u8ef8\u306e\u5ea7\u6a19\u7cfb\ud835\udc65, \ud835\udc66, \ud835\udc67, \ud835\udf03\ud835\udc65, \ud835\udf03\ud835\udc66 , \ud835\udf03\ud835\udc67\u306e\ud835\udc67\u8ef8\u306b\u306a\u308b\u3068\u3044\u3046\u5236\u7d04\u3092\u8a2d\u3051\u305f\uff0e\u30b0 \u30ed\u30fc\u30d0\u30eb\u5ea7\u6a19\u3068\uff0c\u6163\u6027\u4e3b\u8ef8\u306e\u5ea7\u6a19\u7cfb\u306e\u95a2\u4fc2\u306f\uff0c\u56f3 6(b)\u306b\u793a\u3059\u3088\u3046\u306b\ud835\udc4c, \ud835\udc4d\u8ef8\u3060\u3051\u304c\u56de\u8ee2\u3059\u308b\u95a2\u4fc2\u3068\u3057\u3066\u5f97\u3089\u308c\u308b\uff0e\n\u521d\u671f\u69cb\u9020\u306e\u5206\u7cfb A \u3092\u56f3 7 \u306b\u793a\u3059\uff0eCGS \u5358\u4f4d\u7cfb\u3067\u5bf8\u6cd5 3 \u00d7 3 \u00d7 3 cm\uff0c\u4f53\u7a4d\u5bc6\u5ea6 \ud835\udf0c = 8 g/cm3\u3068\u3057\uff0c\u53d6\u4ed8\u89d2\u306f\n\ud835\udf03\ud835\udc4b = \ud835\udf0b 6\u2044 rad \u3068\u3057\u305f\uff0e\u8cea\u91cf\u3084\u30b0\u30ed\u30fc\u30d0\u30eb\u5ea7\u6a19\u53ca\u3073\u6163\u6027\u4e3b\u8ef8\u7cfb\u3067\u306e\u6163\u6027\u30c6\u30f3\u30bd\u30eb\u306f\u56f3\u4e2d\u306b\u793a\u3059\u3068\u304a\u308a\u3067\u3042\u308b\uff0e", + "\u00a9 The Japan Society of Mechanical Engineers\n4\u30fb2 \u691c \u8a3c \u7b2c 3\u30fb2 \u7bc0\u306b\u63d0\u6848\u3057\u305f\u5206\u6790\u6cd5\u306e\u3068\u304a\u308a\uff0c\u5168\u7cfb\u306e\u5171\u632f\u5468\u6ce2\u6570\u304c\u5171\u632f\u767a\u751f\u4e88\u6e2c\u5e2f\u57df\u5185\u306b\u751f\u3058\u308b\u304b\u3092\u691c\u8a3c\u3059\u308b\uff0e\u4ee5\u4e0b\u306e \u691c\u8a3c\u3067\u306f CGS\u5358\u4f4d\u7cfb\u3092\u7528\u3044\u308b\u3053\u3068\u3068\u3057\u305f\uff0eCGS\u5358\u4f4d\u7cfb\u3092\u9078\u629e\u3057\u305f\u7406\u7531\u306f\uff0c\u56f3 7 \u306e\u5206\u7cfb A\u306e\u5834\u5408\uff0c\u7b2c 3\u30fb4 \u7bc0\u3067\u8aac \u660e\u3057\u305f\u3088\u3046\u306b\uff0c\u8cea\u91cf\u3068\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u5024\u304c\u8fd1\u3065\u304f\u3053\u3068\u306b\u3088\u308b\uff0e\u691c\u8a3c\u306f\uff0c\u6163\u6027\u4e3b\u8ef8\u3067\u5f0f\uff0817\uff09\u3092\u56f3\u793a\u3057\u3066\u5f97\u305f\u5171 \u632f\u767a\u751f\u4e88\u6e2c\u5e2f\u57df\u306b\uff0c\u30b0\u30ed\u30fc\u30d0\u30eb\u5ea7\u6a19\u3067\u6c42\u3081\u305f\u5168\u7cfb\u306e\u5468\u6ce2\u6570\u5fdc\u7b54\u95a2\u6570\u304b\u3089\u8aad\u307f\u53d6\u308c\u308b\u5171\u632f\u5468\u6ce2\u6570\u304c\u5b58\u5728\u3059\u308b\u304b\u3092\u78ba \u8a8d\u3059\u308b\u3053\u3068\u3067\u884c\u3046\uff0e\n\u56f3 8(a)\u306b\uff0c\u5206\u7cfb A\uff0cB \u306e\u56fa\u6709\u5024\u306e\u5468\u6ce2\u6570\u4f9d\u5b58\u6027\u3092\u56f3\u793a\u3057\u305f\uff0e\u89e3\u6790\u5468\u6ce2\u6570\u7bc4\u56f2\u306f 0\uff5e200 Hz\uff0c\u89e3\u6790\u5468\u6ce2\u6570\u523b\u307f\u306f\n0.005 Hz\u306b\u8a2d\u5b9a\u3057\u305f\uff0e\u51e1\u4f8b\u306e\u3068\u304a\u308a\uff0c\u9752\u5b9f\u7dda\u306f?\u0303?cc A \u306e\uff0c\u8d64\u4e38\u306f?\u0303?cc B \u306e\u56fa\u6709\u5024\u306e\u5468\u6ce2\u6570\u4f9d\u5b58\u6027\u3092\u8868\u3059\uff0e\u3053\u3053\u306b\uff0c?\u0303?cc A \u306e \u56fa\u6709\u5024\u306f\u5206\u7cfb A \u306e\u8cea\u91cf\u884c\u5217\u3092\u4eee\u6c7a\u3081\u3059\u308b\u3053\u3068\u3067\u7406\u8ad6\u7684\u306b\u5b9a\u307e\u308b\u5024\u3067\u3042\u308b\u306e\u3067\u30e9\u30a4\u30f3\u3067\u63cf\u3044\u305f\u304c\uff0c?\u0303?cc B \u306e\u56fa\u6709\u5024\u306f \u89e3\u6790\u5468\u6ce2\u6570\u30e9\u30a4\u30f3\u6bce\u306b\u8a08\u7b97\u3057\u3066\u6c42\u3081\u308b\u3082\u306e\u3067\u3042\u308b\u306e\u3067\u30de\u30fc\u30ab\u30fc\u3067\u63cf\u3044\u305f\uff0e\u56f3\u4e2d\u306b\u00d7\u5370\u3067\u793a\u3055\u308c\u305f\u7b87\u6240\u3092\u4e0a\u4e0b\u9650\u3068 \u3057\u3066\u5f0f\uff0817\uff09\u304c\u6210\u7acb\u3057\uff0c\u305d\u306e\u5e2f\u57df\u306e\u80cc\u666f\u3092\u8272\u4ed8\u3051\u3057\u3066\u793a\u3057\u305f\uff0e\u3053\u306e\u5e2f\u57df\u306e\u4e0a\u4e0b\u9650\u306f\uff0c\u56f3\u306e\u4e0a\u90e8\u306b 4 \u6841\u306e\u7cbe\u5ea6\u3067\u8a18 \u3057\u305f\uff0e\u672c\u56f3\u3088\u308a\uff0c\u5168\u7cfb\u306e\u8907\u6570\u306e\u5171\u632f\u304c\u767a\u751f\u3059\u308b\u5e2f\u57df\u3092\u4fef\u77b0\u3067\u304d\u308b\uff0e\n\u307e\u305f\uff0c\u7b2c 3\u30fb2\u30fb2 \u9805\u306b\u8ff0\u3079\u305f\u5224\u5b9a\u65b9\u6cd5\u306b\u5f93\u3048\u3070\uff0c?\u0303?cc B \u306e\u56fa\u6709\u5024\u306e\u5468\u6ce2\u6570\u4f9d\u5b58\u6027\u306e\u50be\u304d\u304b\u3089\uff0c\u5206\u7cfb A \u306e\u8cea\u91cf\u884c\u5217 \u306e\u5909\u66f4\u306b\u3088\u308b\u53ef\u5236\u5fa1\u6027\u3082\u5224\u65ad\u3067\u304d\u308b\uff0e\u4f8b\u3048\u3070\uff0c1 \u6b21\u5171\u632f\u306e\u3042\u305f\u308a\u3067\u306f\uff0c?\u0303?cc B \u306e\u56fa\u6709\u5024\u306e\u5468\u6ce2\u6570\u4f9d\u5b58\u6027\u306e\u50be\u304d\u304c\u6025\u5cfb \u3067\u3042\u308a\uff0c\u5206\u7cfb A \u306e\u8cea\u91cf\u884c\u5217\u3092\u5c11\u3057\u5909\u3048\u305f\u3068\u3057\u3066\u3082\uff0c\u5168\u7cfb\u306e\u5171\u632f\u5468\u6ce2\u6570\u3092 1 Hz \u5909\u5316\u3055\u305b\u308b\u3053\u3068\u3067\u3055\u3048\u96e3\u3057\u3044\u3068\u308f \u304b\u308b\uff0e4 \u6b21\u5171\u632f\u3082\u6025\u5cfb\u3067\u306f\u3042\u308b\u304c\uff0c1 \u6b21\u5171\u632f\u307b\u3069\u3067\u306f\u306a\u3044\uff0e\u4e00\u65b9\uff0c2\uff0c3 \u6b21\u5171\u632f\u306b\u4fc2\u308b\u5171\u632f\u767a\u751f\u4e88\u6e2c\u5e2f\u57df\u306f\uff0c?\u0303?cc B \u306e \u56fa\u6709\u5024\u306e\u5468\u6ce2\u6570\u4f9d\u5b58\u6027\u306e\u50be\u304d\u304c\u7de9\u3084\u304b\u3067\uff0c\u53ef\u5236\u5fa1\u6027\u304c\u9ad8\u3044\u3068\u8003\u3048\u5f97\u308b\uff0e\n\u305f\u3060\u3057\uff0c\u3053\u308c\u306f\u6570\u5b66\u7684\u306b\u8a3c\u660e\u3067\u304d\u3066\u3044\u306a\u3044\u304c\uff0c2\uff0c3\u6b21\u5171\u632f\u306b\u4fc2\u308b\u5171\u632f\u767a\u751f\u4e88\u6e2c\u5e2f\u57df\u306f\uff0c\u5f0f\uff0817\uff09\u304b\u3089\u5c0e\u3044\u3066\u56f3 8(a)\u306b\u793a\u3057\u305f\u7bc4\u56f2\u306b\u52a0\u3048\u3066\uff0c\u4ee5\u4e0b\u306b\u8a18\u3059\u3053\u3068\u3092\u52d8\u6848\u3057\u3066\u7406\u89e3\u3059\u3079\u304d\u3068\u8003\u3048\u3066\u3044\u308b\uff0e\u307e\u305a\uff0c\u56f3 8(a)\u3067?\u0303?cc B \u306e\u56fa\u6709\u5024\u306e \u30e9\u30a4\u30f3\u3092\u89b3\u5bdf\u3059\u308b\u3068\uff0c\u56fa\u6709\u5024\u306e\u5468\u6ce2\u6570\u4f9d\u5b58\u6027\u306f\u9023\u7d9a\u7684\u3067\u3042\u308b\u304c\uff0c105 Hz\u4ed8\u8fd1\u3067\u306f\u6607\u9806\u3067 5 \u756a\u76ee\u3068 6 \u756a\u76ee\u306e\u56fa\u6709\u5024 \u306e\u9023\u7d9a\u7dda\u304c\u4ea4\u5dee\u3057\u3066\u3044\u308b\uff0e105 Hz\u3088\u308a\u4e0b\u306e\u5468\u6ce2\u6570\u3067 6\u756a\u76ee\u306e\u56fa\u6709\u5024\u306e\u9023\u7d9a\u7dda\u306f\uff0c\u305d\u306e\u7269\u7406\u7684\u610f\u5473\u304b\u3089\u3059\u308b\u3068\uff0c105 Hz\u3088\u308a\u4e0a\u306e\u5468\u6ce2\u6570\u3067\u306f 5 \u756a\u76ee\u306e\u56fa\u6709\u5024\u306e\u9023\u7d9a\u7dda\u3068\u306a\u3081\u3089\u304b\u306b\u3064\u306a\u304c\u3063\u3066\u3044\u308b\u3068\u8003\u3048\u3089\u308c\u308b\uff0e\u3057\u304b\u3057\u306a\u304c\u3089\uff0c\u5358\u306b \u6570\u5024\u7684\u306a\u6607\u9806\u3068\u3044\u3046\u89b3\u70b9\u3067\u306f\uff0c6 \u756a\u76ee\u306e\u56fa\u6709\u5024\u306e\u9023\u7d9a\u7dda\u306f 105 Hz \u4ed8\u8fd1\u3067\u6298\u308c\u66f2\u304c\u308b\uff0e\u3053\u306e\u3088\u3046\u306b\uff0c?\u0303?cc B \u306e\u56fa\u6709\u5024 \u306e\u30e9\u30a4\u30f3\u304c\u4ea4\u5dee\u3057\uff0c\ud835\udc56 \u756a\u76ee\u3068 \ud835\udc56 + 1 \u756a\u76ee\u306e\u56fa\u6709\u5024\u306b\u95a2\u3059\u308b\u9023\u7d9a\u7dda\u306e\u50be\u304d\u304c\u6025\u6fc0\u306b\u6298\u308c\u66f2\u304c\u3063\u305f\u3068\u3057\u3066\u3082\uff0c\u8457\u8005\u3089", + "\u00a9 The Japan Society of Mechanical Engineers" + ] + }, + { + "image_filename": "designv8_17_0003512_e_download_9236_8414-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003512_e_download_9236_8414-Figure9-1.png", + "caption": "Figure 9: Third Re-designed model with FEA results", + "texts": [], + "surrounding_texts": [ + "2.1. Assembly of Radial Engine The objective of this work is to redesign the articulated rod from the radial engine by using generative method. A reciprocating type internal combustion engine is known as a radial engine. Prior to the invention of gas turbine engines, the radial configuration was widely used for aircraft engines. Since the axes of the cylinders are coplanar, connecting rods cannot always be directly linked to the crankshaft, so the pistons are connected to the crankshaft by a master-and-articulating-rod assembly. The model of the radial engine that was produced using solid edge software can be observed in the Figure 1 and the details of individual parts are given in Table 1. 2.2. Articulated Rod The part that is focused for the design optimization is Articulated Rod. The model of Articulated Rod can be seen in the Figure 2. As mentioned earlier, the material of this part is Steel 4340, and its properties can be seen in Table 2. 2.3. Applied force calculation: In this work, the applied force on the model is the force that is acting on the connecting rod in the engine. The force that is acted on the connecting rod is involved with 3 other forces, which are force on piston due to gas pressure, force that is caused by inertia of reciprocating mass and connecting rod, and force due to friction of piston and of piston ring. The calculation method is obtained from [16]. The relevant parameters can be observed in the Table 3. Force on piston from gas pressure (Fa) can be calculated using the formulae below: \ud835\udc39\ud835\udc4e = \ud835\udf0b \u2146 2 \ud835\udc5d\ud835\udc52 4 (1) From (1), we then obtain Fa = 11545.35 N Force that is caused by inertia of reciprocating mass and connecting rod (Fi) can be found by the following equation: \ud835\udc39\ud835\udc56 = \ud835\udc40\ud835\udc642\ud835\udc5f (\ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udf03 + \ud835\udc5f \u2217 \ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udf03 \ud835\udc59 ) (2) Hence, from (2), Fi = 16614.04 N Force due to friction of piston and of piston ring (Ff) From the research paper [7], Ff = 4000 N Force acting on piston (Fp) is equal to three forces combined as follows: Fp = Fa + Fi + Ff = 24159.39 N Force acting on connecting rod (F) can be known by the following equation. \ud835\udc39 = ( \ud835\udc39\ud835\udc5d \ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udefd ) (3) From (3), F = 24159.39 ~ 25000 N 2.4. Method There are three main parts of the methodology, which are finite element analysis, generative design, and conventional redesigning shape of the model. Solid Edge was used to create the part model to conduct the finite element analysis, also it was used to do generative design and redesign of the component as well. First, the articulated rod, which is the focused part for improvement, was created. Then, the boundary conditions are applied to the model. The fix constraint was applied to the smaller circular ring. The force of 25000 N was given to the inner surface of the bigger cylinder. The boundary conditions of articulated rod model can be seen in the Figure 3 (left). After that, in order to observe the stress and displacement distribution in the model, finite element analysis was run. Also, mesh analysis was conducted to observe the change in the maximum stress, maximum displacement, and elapse time of the different subjective mesh size in order to select the most reasonable mesh size for the finite element analysis. In the mesh analysis, 10 different mesh sizes were applied to the model. Figure 3 (right) also shows the preserved region of the rod which will not undergo any changes during generative design so that the connecting parts doesn\u2019t need any changes after the generative design results are obtained. Next, the generative design of the part was started. The goal is to reduce the mass of the rod while the stress and displacement is within the acceptable range. The bigger and smaller cylinder were selected to be a preserved region, which will not change in shape after the new design is finished so that compatibility with existing parts remains unchanged. The chosen safety factor is 1.4. The boundary conditions of generative design can be observed in the generative design was run with different chosen mass reduction from 10-50% of the rod\u2019s original mass to observe the various shape of the design. Finally, the conventional redesign was conducted to redesign the genitive designs shape to be manufacturable in the regular process. 2.5. Results and discussions First of all, the different mesh sizes were applied to observe the maximum stress, maximum displacement, and solving time of the part. The results are illustrated in Table 4; Figure 4 represents the plot between mesh size versus maximum stress and mesh size versus maximum displacement. After analysing mess sensitivity it is concluded that the 1.10 mm of mesh size is most suitable one for our purpose because the results of stress and displacement are really good and the elapse time is not much higher. Figure 5 provides the FEA results, which show the stress and displacement distribution of the model. Once required mesh size has been finalised then generative designs can be obtained by varying different parameters, generative design of Articulated Rod of Radial Engine is created using Solid Edge CAD software. The designs are obtained in the various shapes, depending upon the constraints provided such as mass reduction percentage, elapse time and quality of the generated design. Mass reduction of the rod is observed within the range of 10-50% minimization of the original mass. The execution time varied from 20-30 minutes. Furthermore, factor of safety has been fixed as 1.4, considering the dynamic load of the rod. Figure 6 (a) and (b) shows the different designs obtained after the process along with the processing time and resultant weight of the rod. Next step is conventional or practically possible redesigning of our product inspired by generative design results. We redesigned three different types of models in a way that it can be produce by conventional methods or CAM (Computer Aided Manufacturing). Thereafter, FEA is performed once again to check the feasibility of the redesigned models, results along with model designs can is shown in Figure 7-9. Once all completed, the design will be subjected to practical load testing to cross-check the real life feasibility of the models." + ] + }, + { + "image_filename": "designv8_17_0003045_1044-019-09680-6.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003045_1044-019-09680-6.pdf-Figure3-1.png", + "caption": "Fig. 3 Initial FE configuration (IC) of a square-sectioned steel beam and the nine corresponding generalized rotational component modes \u03c6rkl according to Eq. (13); visualized with appropriate scaling factors for presentation purposes (Color figure online)", + "texts": [ + " In this section, a simple example of a 60 mm square-sectioned 900 mm long steel beam should illustrate the generalized component modes, as well as the inherent problem of linear dependencies, to gain a deeper understanding of the formulation and to show the significance of the current contribution, respectively. Figure 2 illustrates the generalized translational component modes; all nodes are displaced the same amount in the x-, y- or z-direction. Hence, any rigid body translation of the discretized body can be represented by a proper linear combination of the generalized translational component modes. The generalized rotational component modes of the square beam are depicted in Fig. 3 and, as already addressed in Sect. 2.2 and Appendix A, contain in addition to rotational rigid body motion in general stretch and shear deformations, as may be seen in the figure, i.e., only the right linear combination, Eq. (36), of generalized rotational component modes would exclusively rotate the body. Finally, Fig. 4 depicts the first two bending eigenmodes of vibration with their nine corresponding generalized flexible component modes. It is verified numerically (see Fig. 5), but may be also seen in the figure that the first three generalized component modes of the first and second bending eigenmodes are identical, i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.8-1.png", + "caption": "Figure 3.8: Vane Slot Construction Lines", + "texts": [ + " In addition, the calculation assumes that the vane is of a uniform rectangular shape \u2013 with the additional fillet at the sides, the actual vane would actually be able to withstand higher bending moment stresses. 31 \ud835\udf0e\ud835\udc63 = \ud835\udc40\ud835\udc63\ud835\udc64\ud835\udc63 2\ud835\udc3c\ud835\udc63 < \ud835\udf0e\ud835\udc66\ud835\udc56\ud835\udc52\ud835\udc59\ud835\udc51 (3.6) \ud835\udc64\ud835\udc63 > \u221a 6\ud835\udc5b\ud835\udc40\ud835\udc63 \ud835\udc59\ud835\udc50\ud835\udf0e\ud835\udc66\ud835\udc56\ud835\udc52\ud835\udc59\ud835\udc51 (3.7) where \ud835\udc3c\ud835\udc63 = 1 12 (\ud835\udc59\ud835\udc50\ud835\udc64\ud835\udc63 3) (3.8) Based on the preliminary design dimensions in Table 3.1, the calculation for the minimum vane width is presented in Table 3.2 along with its assumed parameters. now be determined. The construction lines for the vane slot are drawn as shown in Figure 3.8 in which some of the dimensions have been exaggerated for clarity. 32 To this end, the geometric relations for the vane with respect to the rotor can be derived as shown in Equations (3.9)\u2013(3.13). \ud835\udc5f\ud835\udc63\ud835\udc5f = \u221a\ud835\udc5f\ud835\udc63\ud835\udc50 2 + \ud7002 \u2212 2\ud700\ud835\udc5f\ud835\udc63\ud835\udc50 cos \ud703\ud835\udc50 (3.9) sin \ud703\ud835\udc63 = \ud700 \ud835\udc5f\ud835\udc63\ud835\udc5f sin \ud703\ud835\udc50 (3.10) \ud835\udc5f\ud835\udc5f sin \ud835\udefe = \ud700 sin \ud703\ud835\udc63 \u2212 \ud835\udc64\ud835\udc63 2 (3.11) \ud835\udc4f\ud835\udc43 = \ud835\udc5f\ud835\udc5f sin(\ud703\ud835\udc63 \u2212 \ud835\udefe) (3.12) \ud835\udc59\ud835\udc53\ud835\udc61 = \ud835\udc59\ud835\udc63 + \ud700 cos \ud703\ud835\udc50 + \ud835\udc5f\ud835\udc5f cos \ud835\udefe \u2212 \ud835\udc5f\ud835\udc50 (3.13) The derivative of Equation (3.10) is presented in Equation (3.14). At the maximum swivel angle \u03b8v, the perpendicular distance bP of the vane edge at the rotor circumference to the slot centreline would dictate the vane slot width and also the maximum allowable fillet height lft" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001764_f_version_1701758188-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001764_f_version_1701758188-Figure8-1.png", + "caption": "Figure 8. Experimental setup: (1) video camera; (2) source of a dye or colloidal particles; (3) automatic drive for control of vortex ring formation; (4) propagating vortex ring; (5) outlet of the injection tube; (6) UV flashlight.", + "texts": [ + " Since we operate in a 2D space, the concentration is measured in [1/m2]. Then, the amount of particles at the moment t is: N(t) = \u222b S |curlv|N (t)dS = \u222b S a b \u2223\u2223\u2223\u2223\u2223 exp { \u2212 [ (x\u2212 x1) 2 + y2]c/2 b }{ 2b\u2212 c [ (x\u2212 x1) 2 + y2 ]c/2 } + exp { \u2212 [ (x + x1) 2 + y2]c/2 b }{ c [ (x + x1) 2 + y2 ]c/2 \u2212 2b }\u2223\u2223\u2223\u2223\u2223N (t)dS. (10) This integral can be efficiently evaluated numerically. In the following, we compare this formula, simulation results, and experimental data. The scheme of the experimental setup is shown in Figure 8. The main tank made of dense organic glass with a height of h = 0.3 m and width d = 0.11 m was filled with water. The rings themselves were generated with a plastic syringe with a diameter of 2 cm, a height of 8 cm, and an outlet with a diameter varied from 2 to 6 mm. The tank size was selected in such a way as to avoid the significant influence of wave reflection from the walls. Since the outlet size is in millimeters and the tank diameter is 10 centimeters, the influence of the walls on propagating rings can be neglected based on the results of velocity field modeling for a large vortex ring (see Figure 4)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000931_nf_efm2014_02064.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000931_nf_efm2014_02064.pdf-Figure4-1.png", + "caption": "Figure 4. FEM model of the easiest kind of exchanger with the straight tubes and inlet / outlet parts.", + "texts": [ + " When comparing the specific energy losses depending on the Reynolds number showed that the FEM model a very good agreement with the experiment (Figure12,13). In Figure 12 is showing a comparison of the values for the temperature of 23\u00b0C on the FEM model. It can be concluded that the FEM model works with the calculation error within 5% as is shown in Table 2. The distribution of pressure losses in the construction geometry of the heat exchanger in the FEM model for the flow velocity of 0.2 m/s is at Figure 4-6. It is obvious that with the increasing velocity, the pressure loss increases as well. For the flow velocity of 0.05 m/s, the pressure loss is approximately 400 Pa, but for four times larger velocity of 0.2 m/s it is already approximately 5000 Pa. Therefore there is a significant exponential increase of the pressure loss. In the Figure 11 one can see the relation of the ez (6) on the actual value of Reynolds number (4) for each temperature 9, 23, 40 and 60\u00b0C. , (6) where ez is the specific energy losses, J\u00b7Kg-1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003279__17_17.20190714__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003279__17_17.20190714__pdf-Figure4-1.png", + "caption": "Fig. 4. Exploded view of LTCC 3D T/R module.", + "texts": [ + " According to the calculations, the noise figure of the receive chain is 2.84 dB. The calculation formulas of the gain and the noise figure are as follows. GSYS \u00bc G1 \u00fe G2 \u00fe \u00fe Gn \u00f01\u00de FSYS \u00bc F1 \u00fe \u00f0F2 1\u00de G1 \u00fe \u00f0F3 1\u00de G1G2 \u00fe \u00fe \u00f0Fn 1\u00de G1G2 . . .Gn 1 \u00f02\u00de The transmission power of the T/R module mainly depends on the last stage power amplifier. The last stage power amplifier is stimulated by 19 dBm input signal, therefor the output power of the power amplifier is 44.6 dBm, and the final output power is 43.8 dBm. Fig. 4 shows the exploded view of the assembled T/R module. The multilayer board is inserted and fixed to the cavity, and a metal plate is placed on top of it for mechanical protection. Four SMP connectors and a 21-pin low-frequency socket are designed at the two sides of the module. According to the overall technical requirements of the system, the antenna array is H polarized, with the signal bandwidth of 600MHz. In order to realize the beam scanning and keep a higher radiation efficiency, the waveguide radiation array is used to optimize the input VSWR and realize the average in-band radiation efficiency of more than 80%" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001232_f_d2me2017_02004.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001232_f_d2me2017_02004.pdf-Figure4-1.png", + "caption": "Figure 4. Platform", + "texts": [ + " The minimum work angle of balance-bar is 7\u00b0, maximum is 87.5\u00b0. 4 3 5 1 2 1- Balance-arm, 2-Connect rod, 3-Platform, 4-Luffing mechanism, 5-Balance-weight Figure 2. Rotatable parallelogram balance-arm Shown as Figure 3, the upper truss is designed with opening downwards to assure the balance-arm not impact with the crane head. The lower truss has enough blank in the end to make the balance-weight pass through. (a) upper truss (b) lower truss Figure 3. Balance-arm truss 2.3 Platform of balance-arm and balance-weight D2ME 2017 The platform (shown as Figure 4) is box-type structure. The luffing mechanism of balance-arm installed on the platform generates the backward torque with weight block under platform together. The head is latticed structure located in the center of rotational support. There is a limit putter on the head to avoid the impact of lifting-arm and balance-arm. The rotational assembly is shown as in Figure 5. The rotational upper support is shown in Figure 6, and the hinged joint of lifting-arm end is arranged on the edge of rotational support" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure17-1.png", + "caption": "Fig. 17. The von Mises stress distribution in the assembly of the modelled rims for the case of transport of pallets with paving stones during stop of the tipper-truck. Average Element Size (as a fraction of bounding box length): a) 0.1; b) 0.05; c) 0.03; d) 0.02; e) 0.01; f) 0.005", + "texts": [ + "5% fraction of bounding box length were the optimal choices for the comparative analysis under the small costs of computation time and involvement of the computer RAM. It facilitated satisfying the important rule for grid generation that at least two finite elements per thickness, particularly that of the rims, should be applied to properly simulate the bending. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during a stop of a tipper-truck were shown in Fig. 17. They hardly exceeded values of 57 MPa. In this case, both tires of each twin wheel of the rear axle were in contact with the road. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during driving on the asphalt road were shown in Fig. 18. They did not exceed values of 61 MPa. In this case, both tires of each twin wheel of the rear axle were in contact with the road. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during driving on the dirt road were shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure4-1.png", + "caption": "Fig. 4 (a) Double rocker mechanism in modified polycentric knee prosthesis (b) ICOR of the polycentric knee during extension (x = 12 mm)", + "texts": [ + " The components of 4-bar knee is designed and assembled independently. The major design changes incorporated in the modified polycentric knee are based on simulation-based failure analysis reports and reported cases of damage from clinical observations as summarized in Table 3. Different transparent perspective views of the CAD model of the modified polycentric prosthetic knee have been shown in Fig. 3. The kinematic evaluation of a 4-bar polycentric knee is based on Grashof\u2019s law double rocker with length bar condition ( dcba ) as shown in Fig. 4(a), where a, b are the longest and shortest link respectively and c, d are the other links. The optimal dimensions of the polycentric knee mechanism is based on the data of the trajectory of the instantaneous center of rotation (ICOR) calculated from the kinematic analysis of the four-bar polycentric knee. This verifies the stability to set the ICOR behind the load line (x = 12 mm) as shown in Fig. 4(b). In this scenario, the initial elevation of the ICOR is situated at less height from the center and the downward course of the instant center remains relatively elevated and within the zone of stability for the first few degrees of knee flexion. The instant center is approximately 100 mm above and 12 mm behind the vertical reference line (load line). The kinematic analysis of the modified polycentric knee has been performed in CATIA V5 as shown in Fig. 5. The digital mockup result has revealed smooth motion in the joint assembly without any interference" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000920_f_version_1693378799-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000920_f_version_1693378799-Figure2-1.png", + "caption": "Figure 2. Schematic representation of the three-element slotted waveguide array for the off-body mode of operation (a) and of the waveguide array with a pair of slots in the narrow waveguide walls for the on-body mode of operation (b).", + "texts": [ + " Conversely, off-body antennas require a wide beam around the human body to establish communication between a central node on the human body and access points positioned at arbitrary locations. Lastly, in-body antennas are optimized to efficiently radiate electromagnetic waves into the human body, enabling reliable communication between central nodes and implantable sensors, as well as facilitating power transfer to these devices. Therefore, the actual realization of a slotted waveguide antenna depends on the specific application. As examples, two different antenna designs are presented in Figure 2 for off-body and on-body types of communication. In the first case, the array contains three slots that are half the guided wavelength apart and approximately half a wavelength long. The waveguide is short-circuited at a distance of three-quarters of the guided wavelength from the center of the third slot. By doing so, each slot radiates a portion of both a forward and backward propagating wave, resulting in increased radiated EM power per slot. Note that most of the energy is radiated out from the body; thus, the regulations concerning the body specific absorption rate (SAR) values are easily satisfied", + " Additionally, the penetration depth of EM fields into the human body is very small, fulfilling the safety requirements. For both cases, the calculated SAR values and the corresponding maximum input antenna powers are given in [18]. In order to investigate the properties of the proposed textile slotted waveguide antenna, we designed and experimentally verified several textile waveguide antennas operating in the 5.8 GHz ISM band. A schematic representation of the considered textile antennas is shown in Figure 2. In principle, the antenna is made of a piece of waveguide on which slots are cut out and which is short-circuited at the end. The waveguide walls were made of conductive textile, and all connections of the walls were realized by a classical sewing procedure. The radiating slots were cut out, and the borders were sewn to fix the dimensions and prevent tearing. The sewn slotted waveguide, with a shape resembling that of a sock, was pulled over a mold (i.e., over an appropriate supporting structure) in order to keep the desired cross section of the antenna", + " In the second step, the antenna is excited with a waveguide-dominant mode using a waveguide port in a general electromagnetic solver (CST in our case [23]). In the final step, the two designed structures are joined together, and the antenna dimensions are fine-tuned. One could also design the feeding structure and the antenna part together. However, in such a case, there is a non-negligible possibility of designing the antenna as a resonator loaded with radiating slots (note that the considered waveguide section is short-circuited at both sides; see Figure 2), leading to narrow operating bandwidth design. In this section, we discuss three different types of feeding transitions, as shown in Figure 3: \u2022 Transition A: Top- or bottom-mounted coax-to-waveguide transition; \u2022 Transition B: Edge-mounted coax-to-waveguide transition; \u2022 Transition C: Microstrip line-to-waveguide transition. The width and height of the waveguide are denoted as a and b, respectively, while the permittivity of the waveguide filling is denoted as \u03b5r. Two types of molds were considered: a rigid mold with a height of b = 15" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.6-1.png", + "caption": "Figure 2.6: Predicted Fluid Flow in Revolving Vane Working Chamber [16]", + "texts": [ + " To this end, they attributed the discrepancy to the absence of a heat transfer model within the working chamber. Tan and Ooi [16] proceeded to explore different convective heat transfer correlations in their RV model, namely those by Adair et al. [31], Benson et al. [32], Liu and Zhou [33]. As these correlations were intended for use in reciprocating compressors, Tan and Ooi had to adapt the heat transfer parameters of the RV mechanism for use in these correlations. The flow prediction of the fluid in the working chamber by Tan and Ooi [16] is depicted in Figure 2.6. 11 With this flow prediction, they then proceeded to define the hydraulic diameter, average flow velocity for calculating the Reynolds number and subsequently the heat transfer coefficient. Amongst the three different heat transfer correlations tested, it was concluded that the correlation by Liu and Zhou [16] is most suitable for modelling the heat transfer effect in the RV compressor as it offers the most accurate prediction for the experimental results. This correlation would be useful for modelling the heat transfer effects in the working chamber for the lubricant-free RV compressor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002886_nal_Thesis_Suren.pdf-Figure5.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002886_nal_Thesis_Suren.pdf-Figure5.1-1.png", + "caption": "Figure 5.1: Three graphite RVE model and the model dimensions (all dimensions are in \u00b5m).", + "texts": [ + " However, other factors like nodules shape were not incorporated in the current RVE model. Formulation of three graphite RVE model is explained systematically in the following section. Beginning from the RVE model geometry, material properties, constitutive equations used and boundary conditions are detailed. With the model implemented the RVE model was verified for the stress-strain evolution, interface properties, and finally X-FEM crack initiation and propagation was simulated. The two-dimensional plane stress RVE model and dimensions are illustrated in Figure 5.1. In the RVE model, the sizes of the graphite circles were based on the microstructural characterization result in chapter 3. With the average graphite particles diameter of 27\u00b18 \u00b5m, three graphite particles of size 20 \u00b5m, 27 \u00b5m and 35 \u00b5m were represented in the RVE. The overall size of the RVE model (square) was then evaluated considering total area of three graphite particles equal to 10 % of the model size, which was identified to be a square plate of 136 \u00b5m with graphite particles as showed in Figure 5.1. This model size estimation was established from the microstructure characterization result for EN-GJS-500-14 demonstrating 9\u2013 10 % of graphite area in the 2D micrograph. Another important information to finalize RVE model was the distance between the graphite particle centers and their orientation termed as Nearest Neighbor Distance (NND). NND was roughly estimated to be around 70 \u00b5m, so the graphite circles were retained 70 \u00b5m apart Nanyang Technological University Singapore Ch. 5. SGI Microstructure Modeling 5.2. Homogenized RVE Approach Page : 157 from each other. The orientation of the graphite network was placed in the center of the RVE model to help minimize the effect of the edge boundary conditions. So, the final design of the RVE model consists of a three graphite networks forming an equilateral triangle of 70 \u00b5m side. The boundary conditions prescribed in the RVE model are illustrated in Figure 5.1. Periodic Boundary Conditions (PBC) was used on the left and right vertical edges to eliminate the existence of free surface. PBC are a set of boundary conditions that forms an infinite model by simply repeating the RVE cell throughout the space. The periodic boundary conditions were defined using *\u0302Equations constrains in ABAQUS. The bottom edge of the RVE model was constrained to move in y-direction and translation boundary condition was defined along x-direction. Then, the top edge of the model was prescribed with a uniform displacement boundary along y-direction to apply load on the RVE model" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001449_2_2_12_22004614__pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001449_2_2_12_22004614__pdf-Figure6-1.png", + "caption": "Fig. 6. Model of bilateral system using elastic structure", + "texts": [ + "2, 2023 (\u03b8m: motor-side angle, \u03b8l: load-side angle, \u03c4ext l : external torque, Dm: viscosity of the motor, Df : viscosity coefficient) tor to make reliable contact with the environment, we should design the controller so that it suppresses resonance vibration and compensates for distortion. Section 3.2 illustrates the modeling of the bilateral system with elasticity. Section 3.3 proposes the design of MSC. 3.2 Modeling of Bilateral System with Elasticity In this paper, the bilateral system is modeled as a pair of twomass resonant systems as shown in Fig. 6. A master system interacts on its load side with an operator. Similarly, a replica system interacts on its load side with the environment. Since the point of action is not each motor position, but each load position, the control goals for the bilateral system modeled as a pair of two-mass resonant systems are expressed as \u03c4h + \u03c4e = 0 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (12) \u03b8Ml \u2212 \u03b8Rl = 0 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (13) where \u03b8Ml and \u03b8Rl denote the load-side rotational angles of the master and the replica, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure33-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure33-1.png", + "caption": "Figure 33 P-POD Mk. III Rev. E Top Panel", + "texts": [ + "6 lbf was applied to components loaded in the Z-axis, primarily the P-POD Door, NEA bracket, and collar. P-POD Mk. IV Part Design and Analysis This section describes the part by part design changes and analysis to show that the P-POD Mk. IV will survive the expected loads. P-POD Mk. IV Top Panel The P-POD top panel is never used as a mounting surface but is still a structural component in contain CubeSat loads. Additionally, the release mechanism bracket attaches to the Top Panel. The P-POD Mk. III Rev. E Top Panel is shown below in Figure 33. The four Bracket mounting holes at the top were moved outward 0.150 inches in order to accommodate through holes on the Bracket that are properly centered, as the previous design had off center through-holes. The two ribs running down the length of Page 51 the panel are currently sized to accommodate the mounting holes with both adequate width and thickness. These ribs were increased for Rev. E but are suspected to be excessive for the design intent of the Top Panel. Additionally, as discussed in Chapter II, a venting hole array designed to shield EMI/RFI was added as a non-standard mission specific case" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001703_v.org_pdf_2411.02953-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001703_v.org_pdf_2411.02953-Figure1-1.png", + "caption": "Fig. 1 a) Schematic representation of a DMGGs, where passive diffusion within the mixing microchannel creates a concentration gradient \ud835\udc50(\ud835\udc65), dictated by the boundary conditions \ud835\udc36\ud835\udc3b and \ud835\udc36\ud835\udc3f and parasitic flow \ud835\udc62. b) Reference design without mechanisms to mitigate parasitic pressure, consisting of two inlet channels leading to an array of mixing microchannels and branching out into two discharge channels. c) New H-junction design with a bypass channel immediately following the mixing microchannels, aimed at redirecting parasitic flow. d) New Y-junction design further advanced by incorporating a shared discharge channel, which allows for the dissipation of parasitic pressure as two d ischarge streams converge.", + "texts": [ + " The convection-free condition in DMGGs is achieved at the expense of losing the speed of gradient formation.7,8,22 This significantly hinders the application of DMGGs in dynamic and time-sensitive studies such as chemotaxis of highly motile invasive cells, where rapid gradient formation is crucial.2,19,24 One practical way to address this technical trade-off in DMGGs is to replace the traditional flow-resistan t membrane with a mixing microchannel connecting the sink and source side channels (see Fig. 1a).19 Although such a membraneless DMGG facilitates rapid gradient formation, it remains prone to the development of parasitic flows due to the lower hydraulic resistance of the mixing microchannel compared to the membrane.25 Here, we address this issue by introducing two new designs in the present study: the H-junction and the Yjunction (see Fig. 1c, d). Our designs effectively manage pressure differences between the sink and source side channels, thereby minimizing parasitic flows within the mixing microchannel. The H-junction design incorporates a bypass channel, which effectively redirects parasitic flows away from the mixing microchannel and releases excess pressure. The Y-junction, on the other hand, features a shared discharge channel, allowing for smooth flow convergence to reduce pressure differentials. Both configurations are positioned downstream of the mixing microchannel, ensuring that parasitic pressure is dissipated and the associated parasitic flow and shear stress within the gradient region are suppressed", + " The model is subsequently meshed automatically (physics-controlled mesh) with normal size, and the results are collected using a MATLAB script. Upon completion of the simulation, this MATLAB script initiates the next round of simulation by updating the geometry and boundary conditions in the applied model. Theoretical models for DMGGs with parasitic flow In this study, the mechanism for generating gradients relies on the diffusion of substances of interest through a mixing microchannel. This mixing microchannel, positioned centrally as depicted in Fig. 1a, connects two side channels. The dimensions of the microchannel are 2 \u00b5m \u00d7 5 \u00b5m \u00d7 100 \u00b5m (height, width, and length). The side channels, significantly larger with a height of 200 \u00b5m and a width of 500 \u00b5m, are constantly filled with the solutions at varying solute concentrations, as denoted by \ud835\udc36\ud835\udc3b and \ud835\udc36\ud835\udc3f. The essential role of these side channels is to regulate the concentration gradient, guaranteeing that the ends of the mixing microchannel preserve constant preset concentrations. The established steady-state gradient along the length of the mixing microchannels, in the xdirection, conforms to the convection-diffusion equation for incompressible flow, assuming no sinks and sources are present. This equation relates the concentration of the substances of interest, denoted by \ud835\udc50(\ud835\udc65,\ud835\udc61), to the diffusion coefficient, \ud835\udc37 , and parasitic flow velocity, \ud835\udc62, towards the gradient direction as47 \ud835\udf15\ud835\udc50 \ud835\udf15\ud835\udc61 = \ud835\udf15 \ud835\udf15\ud835\udc65 (\ud835\udc62\ud835\udc50) + \ud835\udc37 \ud835\udf152 \ud835\udf15\ud835\udc652 \ud835\udc50. (2) For a constant parasitic flow velocity and with boundary conditions of constant concentrations as illustrated in Fig. 1a, the steady state solution can be expressed as \ud835\udc50(\ud835\udc65\u2217) = \ud835\udc36\ud835\udc3b \u2212 (\ud835\udc36\ud835\udc3b \u2212 \ud835\udc36\ud835\udc3f) (1 \u2212 \ud835\udc52\u2212P\u00e9) (1 \u2212 \ud835\udc52\u2212P\u00e9\ud835\udc65\u2217 ). (3) Here, \ud835\udc65\u2217 = \ud835\udc65 \ud835\udc3f\u2044 , where \ud835\udc3f denotes the length of the microchannel, and P\u00e9 = \ud835\udc62\ud835\udc3f/\ud835\udc37 is the dimensionless P\u00e9clet number. The P\u00e9clet number compares the magnitude of convective transport, described by the convection time along the channel \ud835\udc3f/\ud835\udc62, with diffusive transport, represented by diffusion time \ud835\udc3f2 /\ud835\udc37. A P\u00e9clet number considerably greater than unity (P\u00e9 \u226b 1) indicates that convection is the dominant transport mechanism, whereas a negligible P\u00e9clet number (P\u00e9 \u2248 0) signifies a dominance of diffusion", + " This approach allows for considering specific P\u00e9max thresholds that align with the acceptable level of deviation from the ideal gradient profile, ensuring the integrity and reliability of the experimental outcomes. In this study, we enhanced the design of DMGGs by introducing features that minimize parasitic pressure flow and the resulting shear stress within the gradient region . These improvements focus on controlling parasitic pressure, which primarily arises from geometric mismatch and flow imbalances, such as varying flow rates between downstream side channels of the mixing microchannels (as shown in Fig. 1a). By modifying the downstream region, we achieved a substantial reduction in parasitic pressure within the mixing microchannel. Building on this concept, we introduce two new designs to minimize parasitic flow within the gradient domain: 1. The H-junction design: This design incorporates a bypass channel with significantly lower hydraulic resistance than the mixing microchannel, positioned immediately after the gradient region (as shown in Fig. 1c). 2. The Y-junction design: In this design, a shared discharge channel replaces individual discharge channels, allowing the combined flow of two discharge streams toward the outlet. This configuration is depicted in Fig. 1d. Both approaches build on the principle of parallel flow control.48,49 Specifically, a larger bypass or common discharge channel is placed parallel to a mixing channel with a smaller cross-section and much lower hydraulic resistance. This arrangement reduces flow in the mixing channel proportionally to the ratio of hydraulic resistances between the two parallel channels.50 To evaluate the effectiveness of these designs, we also use a Reference design that shares the same geometry but lacks specialized features to mitigate pressure differences. This baseline design, shown in Fig. 1a and b, serves as a benchmark for comparison with the H-junction and Yjunction designs. Fig. 3 presents the equivalent hydraulic circuit diagrams for the Reference, H-junction, and Y-junction designs, illustrating the mechanisms to minimize parasitic pressure within the mixing microchannels. In these diagrams, syringe pumps act as controllable fluid-flow sources, precisely introducing solutions at constant flow rates. The system components\u2014microfluidic channels and inlet/outlet tubing\u2014are modelled as hydraulic resistors, each impeding the flow passing through them" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.1-1.png", + "caption": "Figure 2.1: Rolling Piston Compressor [10]", + "texts": [ + " The operating principles, design and engineering aspects of the compressor such as leakage analysis [22, 23], thermodynamics [24], tribological [25, 26] and vibration [27] are well understood. Its usage is ubiquitous in air-conditioning applications today. The compressor has high volumetric efficiency, and due to the simplicity of its design, it can be very compact as well. However, it is not without its shortcomings such as high vane contact friction which causes wear and tear at the interface [28\u201330]. A schematic of the rolling piston compressor is provided by Yanagisawa et al. [10] in Figure 2.1. 6 The rolling piston mechanism, as its name suggests, consists of a piston mounted onto the eccentric of a driving shaft in a cylinder. The vane is an integral component since it forms the partition separating the suction chamber from the compressor chamber. The action of the piston scrolling around the inner cylinder would cause the suction and subsequently, the compression of the fluid every two revolutions. The vane is actually attached to a spring that provides a downward force onto the rotor to reduce leakage across the chambers" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000475_cle_download_209_208-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000475_cle_download_209_208-Figure6-1.png", + "caption": "Figure 6: First Design Iteration.", + "texts": [ + " Since the stability of the device will also depend on the dexterity of the user, a smaller learning curve will make for a more stable device. Lastly, the toes of a human\u2019s foot help provide stability. They essentially grab the floor and provide a stable platform when ground surfacing is uneven. The prosthetic foot chosen for this project contains a splittoe feature that helps the user grip the floor when standing on the device. This helps provide lateral stability. The first iteration of the design can be seen in Figure 6. Marginal improvements were made to enhance key areas. The manufacturability of the leg attachment was improved to lower production times and weight-bearing components were adjusted to increase the strength and fatigue life of the device. The four-bar linkages in the knee joint were optimized using an algorithm developed by Robson et al. [8] to allow the device to more accurately mimic the natural walking gait. The prototype of the device can be seen in Figure 7 on the left. For validation, the Exo-Limb project was tested to determine if the design requirements and project goals are met" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000171_pdf_64FFEE170012.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000171_pdf_64FFEE170012.pdf-Figure1-1.png", + "caption": "Figure 1. A vertical spikes shelling machine for Bambara groundnuts. Source: Author", + "texts": [ + " Description of the vertical-spikes shelling machine A shelling machine with vertical spikes as the shelling mechanism was used in this research. The prototype consisted of hopper, spikes, shaft, electrical motor and frame. The hopper had a triangular prism shape to allow the groundnuts to slide down to the shelling mechanism. During operation, Bambara groundnuts were temporarily stored in an inclined hopper before moving into the drum where they fell by gravity onto the rotating shelling shaft with spikes. This process created an impact force that broke the pods. To drive the shaft, a motor, pulleys and belts were used. Figure 1 shows the completed vertical spikes shelling machine prototype. This section summarizes the design analysis for the hopper, shelling shaft, frame and power transmission systems. The machine was designed specifically for use by small scale farmers in South Africa as they are the main growers of Bambara groundnuts (DAFF, 2016). The study specifications were to design a: 1. Bambara groundnut shelling machine with a capacity of at least 100 kg hour -1 2. Prototype with a shelling efficiency of at least 80 %, and 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002813_f_version_1620293073-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002813_f_version_1620293073-Figure1-1.png", + "caption": "Figure 1. (a) Specimen geometry for the fatigue tests (b) Geometry and load case of the analyzed generic shaft. All dimensions in mm.", + "texts": [ + " In case of the mold cast GJS-500-7 only two specimens were tested. Furthermore, for each continuous cast grade the tension compression fatigue strength \u03c3W (R = \u22121) was quantified in a fatigue test with at least 15 specimens by the stair step procedure. The ultimate number of load cycles was set to be 107. In case of the mold cast grade, the fatigue strength was estimated from the tensile strength. Therefore, the ratio of \u03c3W over the UTS was calculated for each continuous cast grade and consequently plotted as a function of the pearlite fraction cP. (Figure 1a) displays the geometry of the specimens used for the fatigue tests. Materials 2021, 14, x FOR PEER REVIEW 6 of 16 Figure 1. (a) Specimen geometry for the fatigue tests (b) Geometry and load case of the analyzed generic shaft. All dimensions in mm. (a) In order to show the potential of intentionally produced metallurgical gradients in highly loaded areas of a component, an exemplary case study has been carried out Materials 2021, 14, 2411 6 of 15 on a drive shaft with a flanged gear. This generic part has been chosen, since it is a typical and widespread component, multiaxially loaded and used in many technical applications. By assuming a local MG, expressed as the pearlite fraction in the matrix. A global performance increase of the component is expected. The case study is performed using finite element (FE) modeling. The geometry of the model and the kinematic and static boundary conditions are shown in Figure 1b). The generically selected shaft with a circumferential notch is cyclically loaded by a torsional moment MT and a radial load FB. This loading is relevant for the fatigue strength of the component. In the case of single extreme load events the cyclic loading is superimposed by a radial displacement Uy applied at the centered load application point and projected on the outer surface in the gear area. This displacement generates a bending load on the shaft. Regarding the design of the shaft, it has to be ensured that it can withstand a sudden failure caused by this extreme bending load" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.1-1.png", + "caption": "Figure 6.1: Vane Attached to Cylinder Geometric Relations", + "texts": [ + "27: Rotor Endface Leakage Curve Fit ..................................................................... 85 Figure 5.28: Rotor Endface Leakage Mass Flow Rate with Different Pressure Ratios ......... 86 Figure 5.29: Equivalent Channel Width for Rotor Endface Leakage .................................... 87 Figure 5.30: Vane Endface Leakage Mass Flow Rate with Pslot = Psuc ................................. 88 Figure 5.31: Rotor Endface Leakage with Different Pressure Ratios at 120\u00b0 Vane Angle ... 89 Figure 6.1: Vane Attached to Cylinder Geometric Relations ................................................ 95 Figure 6.2: Vane Attached to Rotor Geometric Relations ..................................................... 97 Figure 6.3: Compressor Housing Cross-section and Friction Losses .................................... 99 Figure 6.4: RV Prototype Cyliner-Rotor Assembly Cross-Section ..................................... 100 Figure 6.5: Motor Load Curve ..................................................", + " Assuming that the RV components undergo purely rotational motion with no translational motion within the bearings, the Lagrange equation in Equation (6.5) can be adapted for a rotational system as shown in Equation (6.6) by replacing the non-conservative 95 force term with that of a torque term. For the RV compressor, these non-conservative torques arise from the work done to the fluid, friction losses and motor work input. \ud835\udc51 \ud835\udc51\ud835\udc61 ( \ud835\udf15\ud835\udc3f \ud835\udf15?\u0307?\ud835\udc57 ) \u2212 \ud835\udf15\ud835\udc3f \ud835\udf15\ud835\udc5e\ud835\udc57 = \ud835\udc47\ud835\udc57 + \u2211\ud706\ud835\udc58(\ud835\udc61) \ud835\udc5b \ud835\udc58 \ud835\udf15\ud835\udc53\ud835\udc58 \ud835\udf15\ud835\udc5e\ud835\udc57 { \ud835\udc57 = 1,2, \u2026 ,\ud835\udc5a \ud835\udc58 = 1,2, \u2026 , \ud835\udc5b (6.6) Figure 6.1 illustrates the geometric relations between the cylinder, rotor and bush components for the generic RV mechanism in which the vane is attached to the cylinder. The rotation angles of each of the components and the displacement angle of the bush component due to rotational translation are designated as the generalised coordinates for the RV mechanism. They are represented by \u03b8c, \u03b8r, \u03b8b, \u03d5b for the cylinder, rotor, bush and displacement angle respectively. The Lagrangian of the system is expressed as shown in Equation (6", + "7) with no potential energy as the bush component undergoes rotational translation in the horizontal plane. \ud835\udc3f = 1 2 (\ud835\udc3c\ud835\udc50\ud703\u0307\ud835\udc50 2 + \ud835\udc3c\ud835\udc5f\ud703\u0307\ud835\udc5f 2 + \ud835\udc3c\ud835\udc4f\ud703\u0307\ud835\udc4f 2 + \ud835\udc5a\ud835\udc4f\ud835\udc51\ud835\udc4f?\u0307? 2) (6.7) 96 The non-conservative torques acting on each component are summarised as shown in Equation (6.8). Note that there is a set of separate friction torques for each generalised coordinate rather than for each component. The fluid torque and motor torque acts on the cylinder since the cylinder is the main driving component. \ud835\udc47\ud835\udc5b,\ud835\udf03\ud835\udc50 = \ud835\udc47\ud835\udc5a + \ud835\udc47\ud835\udc54 \u2212 \ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc50 \ud835\udc47\ud835\udc5b,\ud835\udf03\ud835\udc5f = \u2212\ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc5f \ud835\udc47\ud835\udc5b,\ud835\udf03\ud835\udc4f = \u2212\ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc4f \ud835\udc47\ud835\udc5b,\ud835\udf19 = \u2212\ud835\udc47\ud835\udc53,\ud835\udf19 } (6.8) Based on the geometric relations in Figure 6.1, the set of holonomic constraints for the system in Equation (6.9) are obtained. sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc5f = sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc5f\ud835\udc50 , \u2192 \ud835\udc531 = sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc5f \u2212 sin \ud703\ud835\udc5f \ud835\udc5f\ud835\udc5f\ud835\udc50 = 0 sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc4f = sin\ud835\udf19 \ud835\udc5f\ud835\udc4f\ud835\udc50 , \u2192 \ud835\udc532 = sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc4f \u2212 sin\ud835\udf19 \ud835\udc5f\ud835\udc4f\ud835\udc50 = 0 sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc4f = sin \ud703\ud835\udc4f \ud700 , \u2192 \ud835\udc533 = sin \ud703\ud835\udc50 \ud835\udc5f\ud835\udc4f \u2212 sin \ud703\ud835\udc4f \ud700 = 0 } (6.9) The set of Lagrange equations for the vane on cylinder RV mechanism can then be formulated as shown in Equation (6.10) which describe the motion for each of the generalised coordinate. \ud835\udc3c\ud835\udc50\ud703\u0308\ud835\udc50 = \ud835\udc47\ud835\udc5a + \ud835\udc47\ud835\udc54 \u2212 \ud835\udc47\ud835\udc53,\ud835\udc50 + \ud7061 \ud835\udf15\ud835\udc531 \ud835\udf15\ud703\ud835\udc50 + \ud7062 \ud835\udf15\ud835\udc532 \ud835\udf15\ud703\ud835\udc50 + \ud7063 \ud835\udf15\ud835\udc533 \ud835\udf15\ud703\ud835\udc50 \ud835\udc3c\ud835\udc5f\ud703\u0308\ud835\udc5f = \u2212\ud835\udc47\ud835\udc53,\ud835\udc5f + \ud7061 \ud835\udf15\ud835\udc531 \ud835\udf15\ud703\ud835\udc5f \ud835\udc3c\ud835\udc4f\ud703\u0308\ud835\udc4f = \u2212\ud835\udc47\ud835\udc53,\ud835\udf03\ud835\udc4f + \ud7063 \ud835\udf15\ud835\udc533 \ud835\udf15\ud703\ud835\udc4f \ud835\udc5a\ud835\udc4f\ud835\udc51\ud835\udc4f" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000310_9668973_09745136.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000310_9668973_09745136.pdf-Figure17-1.png", + "caption": "FIGURE 17. Pitch angle tracking history.", + "texts": [ + " Task 2: Three-DOF coupled oscillatory maneuver at high angles of attack in the pitch direction with a central pitch angle 20\u25e6, an amplitude of 30\u25e6, and an angular frequency of 0.5; and in the roll direction with a phase \u03c0 /6, an amplitude of 5\u25e6, and an angular frequency of 0.6; in the yaw direction with an amplitude of 6\u25e6 and an angular frequency of 0.6. \u03b8 = 20 \u25e6 + 30 \u25e6 \u00d7 cos (0.5t) , 36380 VOLUME 10, 2022 and the trajectory function of roll direction is, \u03c6 = 5 \u25e6 \u00d7 sin ( 0.6t + \u03c0 / 6 ) , and the trajectory function of yaw direction is, \u03c8 = 6 \u25e6 \u00d7 cos (0.6t) Initial yaw angle is limited to \u221210\u25e6 \u2212 10\u25e6. The simulation results are shown below. As shown in Fig. 17 and Fig. 19, when the aircraft model moves with two-DOF in the pitch and roll directions, three different controllers are used to make a comparison. As for pitch motion, computed-torque+DDPG controller manages to track the corresponding trajectory at around 3.2s, and 3.6s for computed-torque controller, 3.9s for DDPG controller; as for roll motion, computed-torque+DDPG controller spends 3.9s managing to track the trajectory, and 4.1s for computedtorque controller, 5.2s for DDPG controller. As can be seen from Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003069_df_ru_2024_02_07.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003069_df_ru_2024_02_07.pdf-Figure7-1.png", + "caption": "Figure 7 \u2014 Air flow current lines by velocity in the flow area with belting", + "texts": [], + "surrounding_texts": [ + "\u0414\u043b\u044f \u0443\u043b\u0443\u0447\u0448\u0435\u043d\u0438\u044f \u0441\u0445\u043e\u0434\u0438\u043c\u043e\u0441\u0442\u0438 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0432 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u0441\u0445\u0435\u043c\u044b \u0438\u043d\u0442\u0435\u0440\u043f\u043e\u043b\u044f\u0446\u0438\u0438 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u043f\u0440\u0438\u043d\u044f\u0442\u0430 \u043e\u043f\u0446\u0438\u044f PRESTO! 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\u043c\u043e\u0434\u0435\u043b\u044c\u044e \u043e\u043f\u0438\u0441\u0430\u043d\u0438\u044f \u0432\u0437\u0430\u0438\u043c\u043e\u0434\u0435\u0439\u0441\u0442\u0432\u0438\u044f \u043c\u0435\u0436\u0434\u0443 \u0437\u043e\u043d\u0430\u043c\u0438 Multiple Reference Frames.\n\u0414\u043b\u044f \u0441\u043e\u0445\u0440\u0430\u043d\u0435\u043d\u0438\u044f \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u043e\u0432 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u043d\u0435\u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0433\u043e \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u0430, \u0430 \u0442\u0430\u043a\u0436\u0435 \u0438\u0445 \u0434\u0430\u043b\u044c\u043d\u0435\u0439\u0448\u0435\u0439 \u043e\u0431\u0440\u0430\u0431\u043e\u0442\u043a\u0438 \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0430\u0441\u044c \u043e\u043f\u0446\u0438\u044f \u0432\u044b\u0431\u043e\u0440\u043a\u0438 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\u043f\u0440\u043e\u0441\u0442\u0440\u0430\u043d\u0441\u0442\u0432\u0435.\n\u2116 \u043a\u043e\u043d\u0442\u0440\u043e\u043b\u044c\u043d\u043e\u0439 \u0442\u043e\u0447\u043a\u0438\n\u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e\u0442\u043e\u043a\u0430, \u0443\u0441\u0440\u0435\u0434\u043d\u0435\u043d\u043d\u0430\u044f \u043f\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u0438, \u043c/\u0441 \u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432\n\u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f\u0420\u044f\u0434 \u0437\u043e\u043d\u0434\u043e\u0432* \u0421\u043a\u043e\u0440\u043e\u0441\u0442\u044c, \u0443\u0441\u0440\u0435\u0434-\n\u043d\u0435\u043d\u043d\u0430\u044f \u043f\u043e \u0440\u044f\u0434\u0430\u043c1 2 3 4 5 6 \u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0441 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u043e\u043c\n\u0442. 1 3,2 2,8 2,7 2,8 2,9 3,1 2,9 3,2 \u0442. 2 2,8 2,6 2,4 2,3 2,8 2,9 2,6 2,8 \u0442. 3 2,9 2,7 2,4 2,4 2,7 2,8 2,7 2,9 \u0442. 4 2,8 2,8 2,4 2,4 2,6 2,9 2,7 2,9 \u0442. 5 4,0 3,4 3,2 3,3 3,5 3,9 3,6 3,8 \u0442. 6 3,8 3,3 3,2 3,3 3,5 3,7 3,5 3,4 \u0442. 7 3,3 3,0 2,9 2,8 2,8 3,0 3,0 3,2 \u0442. 8 3,1 3,0 2,5 2,4 3,1 3,0 2,9 3,1 \u0442. 9 3,7 3,6 3,2 3,3 3,7 3,8 3,6 3,8 \u0442. 10 3,1 3,2 3,1 3,0 3,4 3,3 3,2 3,3 \u0442. 11 3,2 2,8 3,0 3,1 3,1 3,3 3,1 3,3 \u0442. 12 6,1 6,1 6,0 6,1 6,0 6,2 6,1 6,6 \u0442. 13 8,2 8,2 8,0 7,9 8,0 8,1 8,1 8,5\n\u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0431\u0435\u0437 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u0430 \u0442. 1 3,9 3,8 3,7 3,5 3,6 4,0 3,8 4,1 \u0442. 2 2,8 2,6 2,6 2,7 2,9 3,1 2,8 3,0 \u0442. 3 3,0 3,0 2,9 3,0 3,2 3,4 3,1 3,2 \u0442. 4 3,1 3,0 2,8 2,9 3,0 3,2 3,0 3,2 \u0442. 5 3,2 3,1 2,7 2,8 3,0 3,1 3,0 3,2 \u0442. 6 3,0 3,0 2,9 2,7 2,7 2,9 2,9 3,1 \u0442. 7 3,2 3,1 2,6 2,5 3,1 3,0 2,9 3,2 \u0442. 8 3,1 3,2 2,8 2,8 3,0 2,9 3,0 3,1 \u0442. 9 3,2 3,2 2,7 3,0 3,2 3,3 3,1 3,3 \u0442. 10 2,8 2,9 2,6 2,6 2,9 3,0 2,8 3,1 \u0442. 11 3,1 2,9 2,8 2,9 3,2 3,0 3,0 3,3 \u0442. 12 3,7 3,5 3,3 3,6 3,4 3,5 3,5 3,8 \u0442. 13 6,6 6,1 5,9 6,3 6,5 6,2 6,3 6,8\n\u041f\u0440\u0438\u043c\u0435\u0447\u0430\u043d\u0438\u0435: *\u043e\u0442\u0441\u0447\u0435\u0442 \u0432\u0435\u0434\u0435\u0442\u0441\u044f \u043e\u0442 \u043f\u0440\u0430\u0432\u043e\u0439 \u0431\u043e\u043a\u043e\u0432\u0438\u043d\u044b \u043f\u043e \u0445\u043e\u0434\u0443 \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044f \u043a\u043e\u043c\u0431\u0430\u0439\u043d\u0430.\n\u0422\u0430\u0431\u043b\u0438\u0446\u0430 \u2014 \u0420\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432 \u0438 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f Table \u2014 Results of experimental measurements and modeling", + "\u041f\u0430\u0434\u0435\u043d\u0438\u0435 \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0438 \u043f\u043e\u0442\u043e\u043a\u0430 \u043d\u0430\u0431\u043b\u044e\u0434\u0430\u0435\u0442\u0441\u044f \u043f\u043e \u0446\u0435\u043d\u0442\u0440\u0443 \u043e\u0447\u0438\u0441\u0442\u043a\u0438 (\u0441\u043c. 3 \u0438 4 \u0440\u044f\u0434\u044b \u0437\u043e\u043d\u0434\u043e\u0432 \u0432 \u0442\u0430\u0431\u043b\u0438\u0446\u0435), \u0447\u0442\u043e \u043e\u0431\u044a\u044f\u0441\u043d\u044f\u0435\u0442\u0441\u044f \u0437\u0430\u0442\u0440\u0443\u0434\u043d\u0438\u0442\u0435\u043b\u044c\u043d\u044b\u043c \u0437\u0430\u0431\u043e\u0440\u043e\u043c \u0432\u043e\u0437\u0434\u0443\u0445\u0430 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\u043c\u0430\u0442\u0435\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f, \u0432\u044b\u0448\u0435 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u0439 \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u0440\u0435\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432, \u043d\u043e \u0440\u0430\u0441\u0445\u043e\u0436\u0434\u0435\u043d\u0438\u044f \u043d\u0435 \u043f\u0440\u0435\u0432\u044b\u0448\u0430\u044e\u0442 10 % (\u0441\u043c. \u0442\u0430\u0431\u043b\u0438\u0446\u0443). \u042d\u0442\u043e \u043f\u043e\u043a\u0430\u0437\u044b\u0432\u0430\u0435\u0442 \u0430\u0434\u0435\u043a\u0432\u0430\u0442\u043d\u043e\u0441\u0442\u044c 2D-\u043c\u043e\u0434\u0435\u043b\u0438 \u0438 \u043f\u043e\u0437\u0432\u043e\u043b\u044f\u0435\u0442 \u043f\u0440\u043e\u0432\u043e\u0434\u0438\u0442\u044c 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\u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u0437\u0435\u0440\u043d\u0430.\n\u0421\u043f\u0438\u0441\u043e\u043a \u043b\u0438\u0442\u0435\u0440\u0430\u0442\u0443\u0440\u044b 1. \u0424\u0440\u043e\u043b\u043e\u0432, \u041a.\u0412. \u041c\u0430\u0448\u0438\u043d\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u0438\u0435. \u042d\u043d\u0446\u0438\u043a\u043b\u043e\u043f\u0435\u0434\u0438\u044f: \u0432 40 \u0442. /\n\u041a.\u0412. \u0424\u0440\u043e\u043b\u043e\u0432. \u2014 \u041c.: \u041c\u0430\u0448\u0438\u043d\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u0438\u0435, 2002. \u2014 \u0422. IV-16: \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0448\u0438\u043d\u044b \u0438 \u043e\u0431\u043e\u0440\u0443\u0434\u043e\u0432\u0430\u043d\u0438\u0435. \u2014 720 \u0441. 2. Experimental study on the influence of working parameters of centrifugal fan on airflow field in cleaning room / C. Zhang [et al.] // Agriculture. \u2014 2023. \u2014 Vol. 13, iss. 7. \u2014 DOI: https://doi.org/10.3390/agriculture13071368. 3. Operation technological process research in the cleaning system of the grain combine / I. Badretdinov [et al.] // Journal of Agricultural Engineering. \u2014 2021. \u2014 Vol. 52, no. 2. \u2014 DOI: https://doi.org/10.4081/jae.2021.1129. 4. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0418.\u0414. \u041d\u0430\u0443\u0447\u043d\u043e\u0435 \u043e\u0431\u043e\u0441\u043d\u043e\u0432\u0430\u043d\u0438\u0435 \u0438 \u0441\u043e\u0432\u0435\u0440\u0448\u0435\u043d\u0441\u0442\u0432\u043e\u0432\u0430\u043d\u0438\u0435 \u043f\u043d\u0435\u0432\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0438\u0445 \u0441\u0438\u0441\u0442\u0435\u043c \u0441\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0445 \u043c\u0430\u0448\u0438\u043d \u043d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u0442\u0435\u0445\u043d\u043e\u043b\u043e\u0433\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u0430 / \u0418.\u0414. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0421.\u0413. \u041c\u0443\u0434\u0430\u0440\u0438\u0441\u043e\u0432 // \u0412\u0435\u0441\u0442\u043d. \u041d\u0413\u0418\u042d\u0418. \u2014 2019. \u2014 \u2116 9(100). \u2014 \u0421. 5\u201316. 5. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u041d.\u0413. \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0442\u0435\u0440\u0438\u0430\u043b\u044b (\u0432\u0438\u0434\u044b, \u0441\u043e\u0441\u0442\u0430\u0432, \u0441\u0432\u043e\u0439\u0441\u0442\u0432\u0430) / \u041d.\u0413. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u0413.\u0410. \u0425\u0430\u0439\u043b\u0438\u0441, \u041c.\u041c. \u041a\u043e\u0432\u0430\u043b\u0435\u0432. \u2014 \u041c.: \u0418\u041a \u00ab\u0420\u043e\u0434\u043d\u0438\u043a\u00bb, \u0436\u0443\u0440\u043d\u0430\u043b \u00ab\u0410\u0433\u0440\u0430\u0440\u043d\u0430\u044f \u043d\u0430\u0443\u043a\u0430\u00bb, 1998. \u2014 208 \u0441." + ] + }, + { + "image_filename": "designv8_17_0002155_ulture2024_02028.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002155_ulture2024_02028.pdf-Figure6-1.png", + "caption": "Fig. 6. Diaphragm type throttle flow divider with variable input resistances of the flat valve type", + "texts": [ + " However, the adjustable pressure drop in them, as in dividers manufactured according to the scheme shown in Figure 4, affects the shut-off and control element, causing an increased synchronization error. The main disadvantage of membrane flow dividers with variable resistances of the flat valve type is that the pressure drop that occurs at the output resistances during operation of the divider affects the membrane element during regulation. This is the reason for their very unsatisfactory operation in the steady state. Figure 6 shows a flow divider, in which the sensing element is made not in the form of permanent chokes, but in the form of variable resistances of the flat valve type, which makes it possible to compensate for the effect of an adjustable pressure drop on the shut-off and control element, which significantly improves operation in static mode, but leads to complication of its manufacture, since it requires the use of membrane elements with strictly specified elastic properties. Another way to exclude the influence of an adjustable pressure drop on the executive control element is used in the design of the flow divider [20-22] shown in Figure 7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001810_2478_bipcm-2023-0030-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001810_2478_bipcm-2023-0030-Figure1-1.png", + "caption": "Fig. 1 \u2013 Geometry definition of the models and the areas of investigation.", + "texts": [ + " For the investigation of the elastic behavior of a bimetal the use of Finite Element Analysis, FEA is an important tool. The paper presents a CAD and FEA study on the influence of the variation of the bimetal layers thickness on the stress and deformation field, performed with FreeCAD, (FreeCAD, 2023) and some other open-source applications, included in various CAELINUX releases, (CAELINUX, 2023). 2. FEA Study The geometric shape and characteristics of the CAD models of the studied bimetals are described in Fig. 1 and Table 1. The top layer, with h1 thickness, is made from Invar and the bottom layer, with h2 thickness, from Copper. Fig. 1 defines the position of the following important lines: AB is longitudinal symmetry line on the top surface. It is used for FEA investigation. CD is longitudinal symmetry line on the interface surface between the two layers of the bimetal. It is used for FEA investigation. EF is longitudinal symmetry line on the bottom surface. It is used for positioning of the point G. GH is transversal symmetry line on the transversal symmetry plane. It is used for FEA investigation. chosen considering the following aspects: - Some theoretical or practical applications encountered in literature consider a bimetal with layers of equal thickness of the two layers", + " The CAD models were meshed automatically, imposing conditions for finer mesh in the vicinity of the interface surface, Figs. 3-5. The models were considered encastred at the left end, Fig. 2. A variation of temperature of 100\u00b0C was applied to all studied cases. The physical proprieties for Invar and Copper were included from the library of materials available in FreeCAD. The investigation of the FEA results focussed on the following directions: a) Deformations Uz represents the deformation along Oz axis of the points situated on line AB, Fig. 1. For the D case, the Uz maximum value, at the right end, from FEA simulation is: UzMAX(FEA results) = 5.74 mm. In the D case, the value for UzMAX, at the right end was also calculated by use of analytical formulas recommended by (Young et al., 2011): UzMAX(Analytic) = 5.709 mm. The variation of Uz along AB line is presented in Fig. 6. It presents, by comparison the variation of Uz for all the study cases. b) Stresses The distribution of stresses was investigated along: - CD line for von Mises , Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003459_le_download_1267_703-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003459_le_download_1267_703-Figure2-1.png", + "caption": "Figure 2: Scheme for the calculation", + "texts": [ + " We set up the equilibrium equations of the moments of forces acting on elements 3 and 5 relative to the corresponding points B and C, and receive { P x 3 \u00b7 lBS3 \u00b7 sin\u03d53 \u2212 P y 3 \u00b7 lBS3 cos\u03d53 + Ny3 34 \u00b7 lBD = 0, P x 5 \u00b7 lCS5 \u00b7 sin\u03d55 \u2212 P y 5 \u00b7 lCS5 cos\u03d55 + Ny5 54 \u00b7 lEC = 0. (1) These equations are easily solvable with respect to unknowns Ny3 34 , N y5 54 provided that lBD and lEC are non-zero. Then we introduce auxiliary points, the so-called Assur \u2013 Dzholdasbekov critical points Q15, Q53, Q13 and determine their coordinates (Q,Q) as the coordinates of the intersection points of the corresponding right lines passing along the pinion carriers O1A, EC, BD (Figure 2). Using the equations of the right lines passing through the given points C and B with known angles of inclination \u03d55 and \u03d53, we obtain the following system of equations: { YQ53 \u2212XQ53 \u00b7 tg\u03d55 = YC \u2212 tg\u03d55, YQ53 \u2212XQ53 \u00b7 tg\u03d53 = YB \u2212 tg\u03d53. (2) This system of equations has a unique solution by definition (XQ53 , YQ53), if tg5\u2212 tg3 6= 0. The coordinates XQ13 , YQ13 , XQ15 , YQ15 of the critical points Q13 and Q15 are determined similarly. Next, we draw up the equilibrium equations of the moments of all forces acting on the Assur group as a whole relative to the singular point Q53 P x 5 \u00b7 lQ53S5 \u00b7 sin\u03d55 \u2212 P y 5 \u00b7 lQ53S5 \u00b7 cos\u03d55 \u2212 P x 2 \u00b7 lQ53S2 \u00b7 sin\u03d5S2\u2212 \u2212P y 2 \u00b7 lQ53S2 \u00b7 cos\u03d5S2 \u2212 P x 3 \u00b7 lQ53S3 \u00b7 sin\u03d53+ +P y 3 \u00b7 lQ53S3 \u00b7 cos\u03d53 + P x 1 \u00b7 lQ53S1 \u00b7 sin\u03d5S1 \u2212 P y 1 \u00b7 lQ53S1 \u00b7 cos\u03d5S1+ +Ny5 54 \u00b7 lQ53E \u2212Ny3 34 \u00b7 lQ53D + Ny1 10 \u00b7 lQ53S1 \u00b7 cos\u03d5s2 = 0, (3) where \u03d5Si = arctg ( yi \u2212 yQ53 Xi \u2212XQ53 ) \u2013 angular coordinate of vector \u2212\u2212\u2212\u2212\u2212\u2212\u2192 Q53Si=1,2; \u03d5O1 = arctg ( yO1 \u2212 yQ53 XO1 \u2212XQ53 ) \u2013 angular coordinate of vector \u2212\u2212\u2212\u2212\u2192 Q53O1; \u03d5A1 = arctg ( yA1 \u2212 yQ53 XA1 \u2212XQ53 ) \u2013 angular coordinate of vector \u2212\u2212\u2212\u2192 Q53Ai. This equation has one unknown NY1 10 . Next, the unknowns NX3 34 and N X5 54 are determined similarly. To determine the reaction in the hinge (Figure 2) we draw up the equilibrium equations of element 5 in projections to coordinate systems EX5,Y5 { NX5 54 + PX 5 \u00b7 cos\u03d55 + P y 5 \u00b7 sin\u03d55 + NX5 52 = 0, NY5 54 \u2212 PX 5 \u00b7 sin\u03d55 + P Y 5 \u00b7 cos\u03d55 + NY5 52 = 0. (4) These equations are always solvable with respect to the desired N X5 52 and N Y5 52 . The reactions in other hinges are determined similarly. For the equilibrium of the conventional leading element 4, the following conditions must be met: NX 40 = NX 45 + NX 43 + PX 4 , NY 40 = NY 45 + NY 43 + P Y 4 , M40 = NX 45(Y0 \u2212 YE) + NY 45(X0 \u2212XE) + NX 43(Y0 \u2212 YD) + NY 43(X0 \u2212XD)+ +PX 5 (Y0 \u2212 YS4) + P Y 5 (X0 \u2212XS4)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002672_05.2019.91.20_175779-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002672_05.2019.91.20_175779-Figure4-1.png", + "caption": "Figure 4 \u2013 The electronic level LE051 type", + "texts": [ + " The form correction is performed using the perpendicular support with defined virtual axis. Resolution of the device is 0.001 mm. The third unit is a MARPOSS MONITORING equipped with the ultrasonic microphones. It is designed to monitor the slot between grinding disc and grinded material (the GAP function) in order to control the contact between the tool and the ground material. In order to maintain the consistent performance of the grinding machine, it was checked regularly with additional devices. Figure 4 presents the electronic level LE051 type produced by MICROPLAN. It is equipped with a digital/analog display, and its internal mechanism is submerged in an oil-bath box. Achievable sensitivity of the level LE051 is 1 \u03bcm/m or 0.2 second of arc. It has 5 measuring scales providing resolutions from 250 \u03bcm/m per division down to 1 \u03bcm/m per division. The data can be transferred to a PC through the serial connections RS-232. Linearity of the bed with the fixed headstocks of the grinding machine was inspected using the collimator device with a string and measuring magnifier, presented in Figure 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004878_1_1_article-p394.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004878_1_1_article-p394.pdf-Figure2-1.png", + "caption": "Fig. 2. Flow domains of flow control valve.", + "texts": [ + " Numerical simulations of fluid flow inside hydraulic valves are conducted for various goals, to investigate flow forces (Domagala, 2008; Lisowski et al., 2015; Lisowski et al., 2016; Lisowski et al., 2018) or to investigate dynamic behavior of valve components (Beune et al., 2012; Domagala, 2016). Fluid flow inside the flow control valve is determined by position of spools, the left side spool position is set by solenoid while position of the second depends on flow conditions on inlet and outlet. Therefore, the flow simulation was conducted for two models as it is presented in Fig. 2. Results of numerical simulation of the part which includes spool set by solenoid are used as input data for the second model. CFD simulation was performed in ANSYS CFX code for fixed component position for steady state conditions and for the following assumptions: (a) fluid (hydraulic oil) is homogeneous and has a constant properties: density 880 [kg/m3], viscosity \u03c5 =40 [mm2/s]; (b) flow is turbulent: k-\u03d6 turbulence model was used; (c) model is in thermodynamics equilibrium, heat transfer is not included; (d) half of the geometrical model was used in simulations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001734_e_download_2825_3901-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001734_e_download_2825_3901-Figure2-1.png", + "caption": "Figure. 2. Shaft turbocharger ABB type VTR 354 Model", + "texts": [ + " This research using secondary data from Soetresno\u2019s research [1] that discuss retrofitting between Niigata 8MG40X engine with turbocharger ABB type 321 and VTR 354. Actually, these engine using turbocharger VTR 401. Because some data about surging is needed in this research, thus the result of retrofitting turbocharger VTR 354 is taken. Some required data is shown in Table 1 and Table 2. Furthermore for turbocharger VTR 354, the needed data such as general specification (Table 3), data of turbocharger performance for torque calculation (Table 4), and shaft turbocharger dimension (Figure 2 and Table 5) for modeling on FEM software and the material properties of the shaft. Several calculations are needed to calculate the compressor or turbine torque. At the beginning is the calculation of compressor efficiency (\u03b7 \ud835\udc50 ) (Eq.1) [2]. Where \u03c0\ud835\udc50 is the compressor pressure ratio, Tin is the inlet air temperature (\u00b0K), Tout is the air temperature after compressor (\u00b0K), and k is 1.325. \u03b7 \ud835\udc50 = \u03c0\ud835\udc50 (k-1) k\u2044 - 1 T\ud835\udc5c\ud835\udc62\ud835\udc61 T\ud835\udc56\ud835\udc5b\u2044 - 1 (1) Then, determining the compressor power value, with following Eq.2 [2]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.1-1.png", + "caption": "Figure 10.1: The Silverstein\u2013Hall subsonic bomber concept, which used liquid hydrogen tanks in both the wing and fuselage [270]", + "texts": [ + " I do not claim to have designed a feasible or desirable airplane at the top level (e.g., I do not consider fuselage design or propulsor design). I also do not claim that design trends observed on this test case are generalizable to other potential hydrogen aircraft configurations. Hydrogen fuel in aviation has a surprisingly long history. Soon after liquid hydrogen was first produced for the space program, the NACA experimented with hydrogen combustion aircraft concepts. Silverstein and Hall [270] proposed using hydrogen fuel for a subsonic high-altitude bomber (Figure 10.1) in a declassified 1955 NACA research memo. Even then, it was apparent that integrating the enormous hydrogen tanks into the aircraft would be a significant challenge. From 1957 to 1959, NACA flew a B-57 Canberra bomber (Figure 10.2) converted to run one engine using liquid hydrogen fuel [271]. The airplane was able to transition from jet fuel to hydrogen and back again on numerous successful flights. The pilots noted that the hydrogen-powered engine tended to leave contrails even when the kerosene-powered engine did not" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000976_ticle_1705029901.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000976_ticle_1705029901.pdf-Figure1-1.png", + "caption": "Figure 1: Degrees of freedom for lower limb exoskeletons", + "texts": [ + " The knee joint is set with one degree of freedom which enables the bending motion between the lower leg and the thigh, disregarding the small rotational motion after the calf is flexed. Three degrees of freedom can be established at the ankle joint of the exoskeleton which enables up and down rotation of the foot around the ankle joint, abduction/adduction, and rotation, respectively [6]. The lower limb exoskeleton has seven degrees of freedom for each leg, plus one on the foot for a total of eight degrees of freedom. Figure 1 displays the ideal degree of freedom for the lower limb exoskeleton configuration. As the fitness equipment shape is designed in the form of the human exoskeleton, the dimensions of its parts need to match the human body, so the parameters needed are: (1) The measured human body dimensions are selected and the approximate dimensions of each structural part of the mechanical exoskeleton are obtained, as shown in Table 1. Illustration: Hip and knee joints: forward motion as flexion, backward motion as extension; Ankle joint: the movement of the foot from the neutral position to the top is dorsiflexion, and the movement of the foot to the bottom is stumbling flexion" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004264___lang_en_format_pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004264___lang_en_format_pdf-Figure6-1.png", + "caption": "Fig. 6 The equivalent electric circuit for, a. Area equivalent impedance, b. Solid BBS, c. Cylindrical BBS, d. Modified Cylindrical BBS", + "texts": [ + " This method transforms the electric circuit into a matrix to calculate the required voltages (electric field) and the currents (magnetic field) passing through the structure under analysis [8]. Three different BBS are proposed for purpose of study as shown in Fig. 5.The analysis given previously will be used to represent each BBS by an equivalent electric circuit. (a) (b) (c) Fig.5 The BBS shapes, a. Solid BBS, b. Cylindrical BBS, c. Modified Cylindrical BBS For the three BBSs, the length of their edges is l=12.25 mm. The solid BBS has four surfaces with an area equals to A. It can be divided into three equal parts. Each part can be replaced by an equivalent Y as shown in Fig. 6.a. The edges of the four surfaces are connected in parallel yielding an equivalent admittance 2Y. By applying the same approach in [24, 30] we have the equivalent electric circuit shown in Fig. 6b. For the cylindrical BBS, the diameter d is set to 0.56 mm to ensure that its surface area equals to A/3 in order to be replaced by an admittance Y. The equivalent electric circuit is shown in Fig. 6c. For the modified cylindrical BBS, the added elements are passing through the middle of each two adjacent edges; hence, their length equals to l/2. Therefore, the admittance of these elements is 2Y. The equivalent electric circuit is shown in Fig. 6d. Let us assume that the system is working at maximum power transfer condition then YL=Yint, where Yint is the source internal admittance and YL is the load admittance (ZL=50 \u2126). By using the nodal analysis, the Y matrix for each BBS is given by Eq.4, Eq.5 and Eq.6. For the solid BBS IY L YY + \u2212\u2212\u2212 \u2212\u2212\u2212 \u2212\u2212\u2212 \u2212\u2212\u2212 = 6222 2622 2262 2226 (4) l Journal of Microwaves, Optoelectronics and Electromagnetic Applications, Vol. 11, No. 1, June 2012 Brazilian Microwave and Optoelectronics Society-SBMO received 6 Jan", + " 2012; accepted 15 June 2012 Brazilian Society of Electromagnetism-SBMag \u00a9 2012 SBMO/SBMag ISSN 2179-1074 166 where I is a square identity matrix and YLI represents the grounded admittances part. For the cylindrical BBS, we have IY L YY + \u2212\u2212\u2212 \u2212\u2212\u2212 \u2212\u2212\u2212 \u2212\u2212\u2212 = 3111 1311 1131 1113 (5) And for the modified cylindrical BBS, we have IY L YY + \u2212\u2212\u2212\u2212 \u2212\u2212\u2212\u2212 \u2212\u2212\u2212\u2212 \u2212\u2212\u2212 \u2212\u2212\u2212 \u2212\u2212\u2212 \u2212\u2212\u2212 = 8222002 2820202 2280022 2004110 0201410 0021140 2220006 (6) The source current Is vector for the solid and cylindrical BBS (Fig.6b, c) is given in Eq.7 = 0 0 0 s s I I (7) While for the modified cylindrical BBS (Fig.6.d) is = 0 0 0 0 0 0 s s I I (8) Using Ohm's law, we can find the voltages at each node as follows: i. For the solid BBS + + + + + = \u21d2= \u2212 LL LL LL LL L ss YYY Y YYY Y YYY Y YYY YY I v v v v 8 2 8 2 8 2 8 2 2 2 2 2 3 2 1 0 1IYV (9) ii. For the cylindrical BBS Journal of Microwaves, Optoelectronics and Electromagnetic Applications, Vol. 11, No. 1, June 2012 Brazilian Microwave and Optoelectronics Society-SBMO received 6 Jan. 2012; for review 2 Feb" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004768_9668973_09764722.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004768_9668973_09764722.pdf-Figure2-1.png", + "caption": "FIGURE 2. Configuration of the target IPMSM.", + "texts": [ + " Therefore, in order to improve the performance of the IPMSM, it is critical to properly place the GO where the magnetic flux flows in the rolling direction. B. TARGET IPMSM FOR HEV APPLICATION The IPMSM is a suitable type of motor for the traction motor for the HEV applications, as the IPMSM satisfies the requirements on high torque density, superior power factor, and high efficiency [21]\u2013[24]. The target model benchmarked the model of the [25]. The specifications and requirements of the IPMSM are tabulated in Table 1, and configuration of the target model is shown in Fig. 2. 46600 VOLUME 10, 2022 To determine where to apply the GO, FEA is conducted to confirm the magnetic flux path of the target model. The JMAG, which is the commercial FEA analysis tool, is used to analyze the load and no-load conditions of the IPMSM. Fig. 3 shows the load condition flux path on the core according to the rotor position. The flux path on the rotor core is uniform regardless of the rotor position. However, the rotor is not suitable for GO application, as the flux path highly relies on the array of the magnet, and there is a mechanical stability problem at high-speed rotation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001921_le_2017_4_art_03.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001921_le_2017_4_art_03.pdf-Figure3-1.png", + "caption": "Fig. 3. Map of the reduced stress for stent made of PtCr alloy", + "texts": [ + " Furthermore, an insignificant diameter reduction protects from the possibility of removing from the catheter surface. The aim of the study is to evaluate the stent compression strength. It was adopted that the surgeon acts with a specific force on the external stent surface. At the time of surgery the doctor uses force 10\u00f715 N. Therefore, the stent model was loaded on both ends with the force of 10 N on four external walls. Figure 2 presents stent model with applied forces and stent fixation. For this stent model, stresses, strain and displacement area were determined. 1. Distribution of reduced stresses - Figure 3 For the coronary stent model made of PtCr alloy with applied forces, distribution of stresses was varied. The maximal value of reduced stresses was observed at the end of the external wall in the locations where the was stent fixation. The maximal value of stresses was 29.86 MPa, whereas minimal stresses were around 1.533 MPa. 2. Distribution of plastic strains - Figure 4a The plastic strains generated during the strength test are permanent displacements which do not yield even after removing the load they were caused by" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure9.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure9.1-1.png", + "caption": "Figure 9.1. Geometry of the R-S link.", + "texts": [ + " A great example is the rear suspension on the 1990\u20132000 BMW 3 Series (E36 chassis code). Called the Z-axle, this replaced the R joint (semi-trailing arm) suspension used by the previous 3 Series (E30). 129 130 131 132 Chapter 9 The R-S Link The R-S link indirectly connects the wheel carrier to the vehicle body. The R joint is located on the body-side and can be given by a coordinate vector x0 \u2208 R3 and a column vector u0 \u2208 R3. The S joint attaches to the wheel and has geometry given by a coordinate vector x1 \u2208 R3. See Figure 9.1. The line defining the R joint does not have the six independent design variables suggested by column vector u0 \u2208 R3 and coordinate vector x0 \u2208 R3. One way to see this is to note that u0 can be a unit vector, u0 \u00b7 u0 = 1, (9.1) and that x0 can be the point on the R joint axis that is closest to x1, meaning that (x1 \u2212 x0) \u00b7 u0 = 0. (9.2) When the wheel is moved from Position 1 (design) to Position i by an isometry given by Ai \u2208 SO(3) and bi \u2208 R3, the distance between xi := Aix1 + bi and x0 must remain equal to the initial distance between x1 and x0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000056_tation-pdf-url_54247-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000056_tation-pdf-url_54247-Figure7-1.png", + "caption": "Figure 7. Geometry of a reconfigurable link mechanism.", + "texts": [ + " After applying gentle brake to the large wheels of a wheelchair for reducing an impact of landing on the ground, the wheelchair starts to descend a step by maintaining the static wheelie situation (Figure 6(c)). The breaks are unlocked after the large wheel lands on the ground, the front casters can then be landed on the ground using the linear actuator motion (Figure 6(d)). The drive wheel lands on the ground after the forward movement of the wheelchair (Figure 6(e)). Thus, the step-descending motion of the wheelchair is completed. In this section, we derive a geometry model of the proposed link mechanism. Figure 7 shows a schematic side view of the reconfigurable link mechanism with a manual wheelchair. We define a coordinate system of the wheelchair \u03a3-X w Z w , where the origin of the coordinate is at the point of contact between the large wheel and the ground as shown in Figure 7. The linear actuator on the link mechanism is attached at the back of the wheelchair frame at an angle \u03b1. Other links are connected to the linear actuator body, point B, and a top of the cylinder, point A. Coordinates of points A, C, and D are derived as the relative position from point B. [ x a z a ] \u2007=\u2007 [ cos \u03b1 \u2212 sin \u03b1 sin \u03b1 cos \u03b1 ] [ 0 u L ] + [ x b z b ] (4) [ x c z c ] \u2007=\u2007 [ cos \u03b1 \u2212 sin \u03b1 sin \u03b1 cos \u03b1 ] [ \u2212 l 0 sin \u03b2 u L \u2212 l 0 cos \u03b2 ] + [ x b z b ] (5) [ x d z d ] \u2007=\u2007 [ cos \u03b1 \u2212 sin \u03b1 sin \u03b1 cos \u03b1 ] [ \u2212 l 1 sin \u03b2 u L \u2212 l 1 cos \u03b2 ] + [ x b z b ] (6) Five-Wheeled Wheelchair with an Add-On Mechanism and Its Semiautomatic" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.14-1.png", + "caption": "Figure 1.14. Citroen IFS, using a torsion spring and a hydraulic shock absorber [2].", + "texts": [ + " A drawing of this type is seen in Figure 1.11. Another early independent suspension approach was the swing axle. This amounted to allowing each \u201chalf\u201d of the axle to swing independently, Figure 1.12. Some designs of this type were even employed as rear suspensions, and used the drive axle as one of the arms. The design favored by GM was the double wishbone, also known as the short-long-arm (SLA), seen in Figure 1.13. In addition to leaf springs and coil springs, torsion springs were also in use. An example can be seen in Figure 1.14. In this figure, there is also a hydraulic shock absorber. As the century went along, the MacPherson strut suspension, Figure 1.15, introduced in the late 1940s, became an increasingly popular IFS. This was due to its relatively few number of components, especially when the spring is placed over the strut, and its ability to provide a steer DOF. The rack and pinion steering system, seen in Figure 1.2, in use in Europe by the 1930s, found its way to American cars in the 1970s. While the shimmy problem and styling demands led to the almost total extinction of the traditional front axle in favor of the double wishbone and MacPherson suspensions, there was no similarly urgent reason to discard the rear axle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000644_8948470_09064511.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000644_8948470_09064511.pdf-Figure5-1.png", + "caption": "FIGURE 5. A dual-band antenna with two C-shaped radiating strips: (a) geometry with highlighted design parameters and (b) visualization of the antenna high-fidelity model.", + "texts": [ + " For the sake of comparison, the antenna was re-designed using the non-sensitivity-based inverse surrogates [25]. It can be observed, also in Fig. 4, that the design quality is comparable for both methods. However, as mentioned before, 75158 VOLUME 8, 2020 the non-sensitivity-based approach required 27 reference designs. Thus, the computational benefits of the proposed methodology are evident. B. EXAMPLE 2: TRIPLE-BAND UNIPLANAR DIPOLE ANTENNA As the second example, consider a dual-band monopole antenna shown in Fig. 5. The structure is based on the radiator of [28]. It consists of a driven element in the form of two C-shaped structures interconnected by a central strip and fed through a stepped impedance microstrip line. The vector of geometry parameters is x = [l1 l2 l3 l4 l5 w o1r o2r]T . The relative variables are o1 = (0.5l1 \u2013 w)o1r , o2 = o1 + w+ (l1 \u2013 o1 \u2013 w)o2r , ls1 = 0.2(l4+ 2w), ls2 = 0.2(l5+ 2w), whereas o = 5 remains fixed. Parameter w0 is calculated based on the transmission line theory for the given values of substrate permittivity \u03b5r and thickness h [24]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002715_200-1-PB.pdf_id_3300-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002715_200-1-PB.pdf_id_3300-Figure2-1.png", + "caption": "Fig. 2. Dynamic model of the boom", + "texts": [ + " An analogous approach was applied in the investigation of the dynamic behaviour of the reloading bridge. It is shown in [15]. 2 DYNAMIC MODEL OF THE BOOM 2.1 Model Description The boom is a constituent part of the portal-rotating crane. The subsystem of the boom consists of the carrying structure and the rope system. The carrying structure of the boom is connected to the platform by joints. In the system of the portal crane, the boom is observed, by idealization, as an independent subsystem. Accordingly, Fig. 2 presents a dynamic equivalent model of the portal crane boom. The model was formed for the needs of determination of dynamic loads. The boom is observed as an independent subsystem which oscillates. A dynamic equivalent model is formed in such a way that it both keeps the main dynamic characteristics of the boom and that the defined problem could be mathematically solved. From Fig. 2 it is seen that the subsystem of the boom with a load is represented with two lumped masses, two lightweight bars, and a circular disc. 593Parameters Influencing the Dynamic Behaviour of the Carrying Structure of a Type H Portal Crane Discretization of the carrying structure of the boom was performed on a lightweight bar with a reduced mass on the tip. In other words, the carrying structure of the boom is represented by a lightweight bar with the length Lb and the mass m1, which is reduced to the tip of the boom", + " The distance between the boom joint and the column axis is r. Based on the recommendations in [15], the reduced mass m1 can be determined according to the following relation: m = mb1 1 4 1 3 , (1) where mb is the boom mass. 2.2 Mathematical Formulation The Lagrange equations of the second kind will be used for the setting of the mathematical formulation of the formed dynamic model of the boom. The equations of motion of the boom elements are set based on the dynamic equivalent model presented in Fig. 2. The dynamic equations of motion of the system read: \u03b8 \u03c9 \u03b8 \u03d5t t = L x tl r ( ) + ( ) \u2212 ( )2 1 sin cos , (2a) \u03c8 \u03c9 \u03c8 \u03d5t t = L x t r ( ) + ( ) \u2212 ( )2 1 sin sin , (2b) J t T\u03d5 ( )= , (2c) where \u03b8 is the angle of oscillation of load in the longitudinal direction, \u03c8 is the angle of oscillation of load in the side (lateral) direction, \u03c6 is the angle of rotation of the column, i.e. the boom, x is the rectilinear motion of the boom, and \u03c9 is the circular frequency of load oscillation. 2.2.1 Load Oscillation The laws of non-attenuated oscillations of the load as a function of time along the generalized coordinates \u03b8 and \u03c8 due to the crane acceleration given by the diagram according to Fig", + " In other words, this holds because the second and the third steps have the same sign so that the change of phase by 2\u03c0 requires that the second and the third steps should be in phase. 2.2.2 Dynamic Loads of the Portal In accordance with the adopted generalized coordinates of oscillation of the dynamic model of the boom, the dynamic moment of bending occurs in two directions: \u2022 in the longitudinal direction, and \u2022 in the side (lateral) direction. The dynamic moment of bending in the longitudinal direction reads, Fig. 2: M m g L r m g L L L r m L dyn,l b r r b r = 1 cos cos sin cos \u03b1 \u03b8 \u03b8 \u03b8 \u03b1 +( ) + +( ) + +( ) + 2 2 2 \u03b8 \u03b8 \u03b1 \u03b8 \u03c8 \u03c8 \u03b1 2 2 2 sin sin cos cos cos . L L m L L r b r r r \u2212( ) + +( ) (14) The dynamic moment of bending in the side direction reads, Fig. 2: M m g L L m L L L dyn,s r r r b r = 2 2 2 2 +( ) + \u2212( ) \u03c8 \u03c8 \u03c8 \u03c8 \u03c8 \u03b1 \u03c8 cos sin sin sin cos . (15) 3 FINITE ELEMENT MODEL OF THE STRUCTURE 3.1 Model Description The whole portal-rotating crane is divided into two subsystems: the moving structure, and the boom. The relationship between the structure and the boom is simplified in such a way that the influence of load and the dead weight of the boom is reduced to the points of the upper and lower supports of the boom. The type \u0397 carrying structure of the considered portal crane is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003506_8355919_08355939.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003506_8355919_08355939.pdf-Figure1-1.png", + "caption": "Fig. 1 Dual angle", + "texts": [ + ": Integrated modeling of spacecraft relative motion dynamics using dual quaternion 369 where a and b are respectively the real and dual parts of a\u0302. \u03b5 is the dual operator, which satisfies \u03b52 = 0 and \u03b5 = 0. The dual number set is denoted by Hs d . In 1901, Study extended the concept of the dual number to space geometry to express the relationship between two lines, which is represented by dual angle \u03b8\u0302 = \u03b8 + \u03b5d (11) where the real part \u03b8 and the dual part d respectively represent the angle and distance between two lines, as Fig. 1 shows. According to dual quaternion algebra, the dual function can be expanded into Taylor series. As for dual angle \u03b8\u0302 = \u03b8 + \u03b5d, there are{ sin \u03b8\u0302 = sin(\u03b8 + \u03b5d) = sin \u03b8 + \u03b5d cos \u03b8 cos \u03b8\u0302 = cos(\u03b8 + \u03b5d) = cos \u03b8 \u2212 \u03b5d sin \u03b8 . (12) A dual vector is composed by three dual numbers, whose set is denoted by Hv d . The dual vector is often called motor and written as a\u0302 = \u23a1\u23a3 a1 + \u03b5b1 a2 + \u03b5b2 a3 + \u03b5b3 \u23a4\u23a6 = a + \u03b5b. (13) Operation rules of the dual number and motor are similar to those of the real number and vector in linear algebra" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001057_e_download_8708_7253-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001057_e_download_8708_7253-Figure2-1.png", + "caption": "Figure 2. 3D Contact Gear", + "texts": [], + "surrounding_texts": [ + "ANSYS 6.5, Structural Analysis Guide. C. H. Wink and A. L. Serpa. (2005). Investigation of Tooth Contact Deviations from the Plane of Action and Their Effects on Gear Transmission Error, State University of Campinas, Brazil, I. Mech. E. Vol. 219 Part C: J. Mechanical Engineering Science, PP.501-509. Faydor L. Litvin, Alfonso Fuentes, J. Matthew Hawkins and Robert F.handschuh. (2001). Design, Generation and Tooth Contact Analysis (TCA) of Asymmetric Face Gear Drive With Modified Geometry, NASA Center for Aerospace Information. Jiande Wang. (2003). Numerical and Experimental Analysis of Spur Gears in Mesh, PhD Curtin University of Technology September. K. L. Johnson. (2003). Contact Mechanics, Cambridge University Press, Ninth prints. M., Amabili and A. Rivola. (June 2008). Dynamic Analysis of Spur Gear Pairs: Study-State Response and Stability of the SDOF Model with Time-Varying Meshing Damping, University of Bologna, Italy, Mechanical Systems and Signal Processing, PP.375-390. Nilanjan Sarkar, Randy E. Ellis, Thomas N. Moore. (2006). Backlash Detection in Geared Mechanisms: Modeling, Simulation, and Experimentation, Queen's University, Kingston, Canada, I. Mech. E. Vol. 220 Part K: J. Multi-body Dynamics, PP.273-282. Ramamurti, V., and Ananda, M. (1988). Dynamic Analysis of Spur Gear Teeth, Indian Institute of Technology, India, Journal of Computers and Structures, Vol.29, No.5, PP.831-843. Spitas. G. A. Papadopoulos. C. Spitas and T.Costopoulos. (2009), Experimental Investigation of Load Sharing in Multiple Gear Tooth Contact Using the Stress-Optical Method of Caustics, Journal Compilation, doi:10.1111/j.PP.1475-1305.2008.00558.x. V. Atanasiu, I. Doroftei. (2009). Dynamic Contact Loads of Spur Gear Pairs with Addendum Modifications, Technical University of Lasi, Romania, Journal of Mechanical and Environmental Engineering. Zeping Wei. (2004). Stresses and Deformations in Involutes Spur Gears by Finite Element Method, M.Sc University of Saskatchewan, Canada. ISSN 1913-1844 E-ISSN 1913-1852 260 Published by Canadian Center of Science and Education 261 Published by Canadian Center of Science and Education 263" + ] + }, + { + "image_filename": "designv8_17_0001685_11044-016-9555-2.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001685_11044-016-9555-2.pdf-Figure14-1.png", + "caption": "Fig. 14 2D car pendulum model", + "texts": [ + " None of the investigated cases shows a qualitatively different result in terms of numerical efficiency than the averaged results shown in Fig. 13. As a result of the findings summarized in Table 3 and the numerical investigations on the multimass oscillator, the three-parameter Coloumb-type friction model (reference model) seems to be the best choice for the modeling of dry friction inside jointed structures although it is not continuous. A 2D car pendulum model including an additional point mass at one end of the pendulum as shown in Fig. 14 is used to demonstrate the method described in Sect. 3 and Sect. 4. The pendulum is designed as a flexible multilayer sheet structure with three metal sheets rotationally fixed to the car. The two outer metal sheets (300 mm \u00d7 20 mm \u00d7 1 mm) are connected via beams at two locations. The central metal sheet (400 mm\u00d720 mm\u00d71 mm) is not directly connected to the outer sheets but connected through contact and friction forces. The flexible structure has been modeled out of steel in the FE software Abaqus [41], and the resulting mass and stiffness matrices have been imported into Scilab [54] for all following computations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003283_tation-pdf-url_13336-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003283_tation-pdf-url_13336-Figure6-1.png", + "caption": "Fig. 6. Compacting footprint by twisting joint axes positions from the classic delta (left) to the twisted delta (right) configuration", + "texts": [], + "surrounding_texts": [ + "After a screening of machine concepts that would fulfill the requirements, especially the small footprint and the fact that the TCP will have to move outside the footprint, posed a challenge. It became obvious that the combination of requirements called for a parallel kinematic machine (PKM) concept, but none of the known kinematics became an obvious candidate." + ] + }, + { + "image_filename": "designv8_17_0004397_jeee.2013.010305.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004397_jeee.2013.010305.pdf-Figure9-1.png", + "caption": "Figure 9. Slab mode antenna design for the 60-GHz frequency range", + "texts": [ + " The slab mode antenna was built for operation at 12 GHz to prove the operating principle and to confirm the simulated antenna characteristics. It was not optimized for compactness. The advantages of this type of antenna, in particular the high radiation efficiency, become apparent at higher frequencies only, where conductor losses are generally more dominant. For this reason, an example antenna design was studied theoretically at 60 GHz. Results are presented in the following section. Another slab mode antenna was designed for operation in the unlicensed 60-GHz band. (Figure 9) In this case, the design parameters were (description see Table 1): a = 18 mm; b = 10 mm; d = 0.508 mm; h = 0.05 mm; t = 0.254 mm; D = 8 mm; r = 8 mm; l = 7 mm. The air gap of the previous prototype antenna was replaced by a PTFE insulation film (\u03b5r = 2.08; tan\u03b4 = 0.001). Again, Duroid\u00ae6010LM laminate was used for the slab and the lens, having a loss tangent tan\u03b4 = 0.003. All conductors were modeled with specific conductivity \u03c3 = 2.0\u00b7107 S/m. Good input return loss > 15 dB was achieved for an operating bandwidth of more than 20 %" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002524_O201020065114094.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002524_O201020065114094.pdf-Figure6-1.png", + "caption": "Fig. 6 Internal flow at main section", + "texts": [ + "5, the fluid energized by the impeller rotation flows backward from the volute to the inlet through the gap, and then re-enters the impeller. Therefore, the amount of flow going through the impeller increases by the amount of gap flow which flows back, compared to the amount of outlet flow. Therefore, it can be thought that the generated pressure is greater with a gap due to the increased amount of the internal flow of the impeller compared to the system without the gap (See the following Chapter 5and 7). The followings are described in Fig.6: (a) velocity distribution, (b) pressure distribution, (c) vorticity distribution of the internal flow of the impeller at Q=5.0 L/min of type-A and (d) velocity distribution of the internal flow of the impeller at Q=5.0 L/min of type-B. In Figures 6 (a) and (d), absolute velocity is described at the inlet and volute, and relative velocity is described at impeller, taking the rotation into consideration. The flow patterns are shown with the thick arrows and the letters. The blade closest to the upper tongue is marked 1, and the numbering continues counterclockwise. The flow from the inlet to the volute inside the impeller is referred to as the forward current, and the flow from the volute to the inlet is referred to as the backward current. In vorticity distribution of Fig.6 (c), the positive values in the concentration map indicate the counterclockwise vorticity and the negative values indicate the clockwise vorticity. The black line in the figure represents equivorticity where the vorticity becomes zero. All of these figures show the central section in the direction of the height of the blade. The velocity distribution of Fig.6 (a) shows that the forward current and backward current develop inside the impeller, and the flow condition varies in between all blades depending on each position. This occurs since the flow path is broader than necessary with the height of the blade b (3.5 mm), which is larger than that of the ordinary design, and the inlet and outlet angles of the blades are 90\u00b0. In the deeper observation, the forward current develops in the broad area by the pump action in between 1 and 2, but due to the effect of the clockwise vortex (around \u201ca\u201d) which developed when the blade passed the upper tongue, the flow no longer goes along the blade but leaves from the anterior surface of the blade around the tip (b\u2192 b\u2019). In between 2-3, the vortex (a) which used to be present at the tip of the blade between 1 and 2 flows out to the volute, and the forward current starts flowing along the anterior surface of the blade (c\u2192 c\u2019). Furthermore, on the posterior surface of the blade 3, the forward current induces development of a counterclockwise vortex (d). In between 3-4, as seen in the pressure distribution in Fig.6 (b), the pressure at the volute increases as the volute area increases. As it becomes more difficult to flow toward the volute, the area where the forward current develops becomes smaller (e\u2192 e\u2019); therefore, it becomes more likely that the forward current develops only on the anterior surface of the blade. The vortex (d) in between 2-3 grows into another vortex (f), which is even larger, in between 3-4. Since then, the backward current starts to develop from the volute to the impeller. The backward current develops more prominently in between 4-5 than in between other blades (g\u2192 g\u2019)", + " This occurs since the increased pressure at the volute induces the backward current of the fluid, which cannot flow out to the volute side, to the impeller side where the pressure is low. The vortex (h) is thought to develop when the part of the fluid, which has flowed backward, is flowing toward the internal volute side starting from the lower tongue. The internal flow of the impeller on the internal volute side of 5-1 is axially symmetrical to that on the external volute side. Further explanations are not provided here since the tendency of the flow is similar to that developed in between 1-5 blades. The pressure distribution in Fig.6 (b) shows that higher pressure is observed in the area where the forward current develops along the anterior surface of the blades (2, 3 and 6) compared to the area on the anterior surface of the other blades. On the other hand, the pressure is low in the area where the flow stops or a vortex develops (around the inlet on the posterior surface of the blades 2, 3, 6, and 7). Furthermore, the condition of the internal flow of impeller can be more clarified by studying not only the velocity distribution but also the vorticity distribution presented in Fig.6 (c). The vorticity distribution suggests that the forward current and backward current pass around the equivorticity line where the vorticity is 0, and the former current flows toward the volute and the latter the inlet, respectively. The comparison of velocity distributions between (a) and (d) of Fig.6 reveals that the area where the forward current develops is greater in type-A, which has a gap, than type-B, with no gap. This is because both forward and backward currents develop only inside the impeller in type-B since there is no gap, while in type-A backward current develops in the gap from the volute toward the inlet, and therefore the amount of backflow which goes through the impeller is reduced. Further details are shown in the following chapter. The amount of flow at Q=5.0 L/min in between each blade around the periphery of the impeller and the amount of outflow from the impeller QI are shown in Table 1. This value is the mean amount of flow in between each blade when the blades rotate by 1 pitch from the position shown in Fig.6, while QI is the mean amount of flow around the entire impeller outlet. The positive value indicates a forward current, and the negative value indicates a backward current. The findings suggest that the amount of the forward current increases after the tongue and decreases as it approaches toward the tongue in both type-A and type-B. A negative value is reported in between 3-4 in type-B, suggesting that a certain amount of backward current has been equally developed. The value of QI in type-A, which has a gap, is 7", + "0 L/min (the flow from inside to outside is defined positive), (b) pressure distribution, and (c) path lines. Each figure shows the result of computation at the central section in the direction of the height of the gap indicated as A-A\u2019 in Fig.8 (d). According to Fig.8 (a), the radial velocity is negative for the entire circumference of the gap; the fluid flows in from the volute to the inlet, and the flow-in velocity is high especially around \u03b8 =110\u00b0-190\u00b0 (area A) and 310\u00b0- 10\u00b0 (area B). This is because the high pressure at the volute around the tongue as in Fig.6 (b) induces an increase of pressure in the areas A and B in the gap as in Fig.8 (b), resulting in high radial pressure gradient in these areas which makes it easier for the fluid to flows in. The flow paths in (c) show that the fluid in the gap flows (backward) to the inlet without causing stagnation while circulating in the same direction as the impeller rotation. Hence, it seems that an adequate \u201cwash-out\u201d effect has been achieved in prevention of thrombosis formation inside the narrow gap, which is one of the most significant elements of the blood pump" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002325_16.99.108_linkid_pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002325_16.99.108_linkid_pdf-Figure7-1.png", + "caption": "Fig. 7(a-d): Magnetic flux density equivalent nephogram (a) d = 5 mm (Bmax = 1.652T), (b) d = 7 mm (Bmax = 1.714T), (c) d = 11 mm (Bmax = 2.001T) and (d) d = 13 mm (Bmax = 1.978T)", + "texts": [ + " Therefore, in order to improve the utilization rate of the permanent magnets, hM should not be too large. Relationship between thickness of rotor core d and the maximum output torque Tmax: Rotor core is used to prevent the interference of external magnetic fields. The distribution of magnetic flux density is changable, thus it will distribute in some places where they are most needed in the design of rotor. When P = 4, the magnetic flux density equivalent nephogram in thickness of different rotor cores is shown in Fig. 7. As shown in Fig. 7, when the thickness of rotor iron core varies from 7-5 mm, the magnetic saturation of core becomes more and more obvious. As shown in Fig. 8, the magnetic saturation makes reluctance increasing and the air gap flux density decreasing. Finally, the output torque is reduced, when increasing the thickness of core, the reluctance will be reduced and the air gap flux density and the output the torque will be increased. When the thickness of iron core increases to a certain value and then increase the thickness of iron core again, the torque output begins to decline" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure22-1.png", + "caption": "Figure 22. Temperature (\u25e6K) contour for both rotor and stator of the motor representing the thermal distribution. (a) Stator. (b) Rotor.", + "texts": [ + " In ANSYS-FLUENT, the flow equations and the energy equation are solved separately: once the flow and turbulence equations converged, the energy equation is solved on the basis of obtained flow field. This method resulted in faster convergence. Simulations were run in ANSYS-FLUENT by using the (RANS) equations. The realizable \u03ba-\u03b5 turbulent model was used for the closure of the system equations. The Enhanced Wall Treatment (EWT) which uses a twolayer approach was applied in FLUENT to model the near wall regions. This approach requires the non-dimensional wall distance y+ to be \u223c 1 in the whole domain, although values of y+ < 5 are considered to be acceptable. Figure 22 shows the temperature contour for both rotor and stator of the motor under full load condition, representing their thermal distribution. Heat dissipation of rotor and stator is possible through both conduction and convection. The heat generated in winding transfers linearly to the stator through conduction and is then conducted to the motor\u2019s body where the body surface cools by the environment. The convection is due to the air movement inside the air-gap because of skew permanent magnets mounted on the rotor surface acting like a fan. The amount of heat transfer on stator surface is almost fixed and is less than rotor\u2019s surface heat transfer amount. Fig. 22(a) shows the difference between the lowest and the highest temperatures are limited to 12\u25e6K and 360\u25e6K respectively. The significant temperature discrimination over the entire stator is due to lamination. However, the rotor small size and high metal conductivity cause the rotor temperature to have a low discrimination over the entire area as shown in Fig. 22(b): the difference between the lowest and the highest temperatures is limited to 4\u25e6K. There is no heat source on the rotor and the heat transfer is via convection through heated air in the motor air-gap. In steady-state rotation the rotor heating is uniform, except where there are juts on the rotor surfaces and exposed to more heated air flow. Therefore, temperature discrimination as the result of this phenomenon is very small. It is obvious that a temperature increase occurs proceeding from the inner radius towards the running clearance outlet" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004002_c_free.html_id_10138-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004002_c_free.html_id_10138-Figure4-1.png", + "caption": "Figure 4: Topology optimization result in terms of element density.", + "texts": [ + " Objective of the simulation was the minimization of the weighted compliance, while it was imposed a constraint condition on the mass fraction of the system. In addition, a condition on the maximum mean stress was included. Several runs of numerical simulation were carried out, including all the load conditions and combining them with different settings to study the impact on the final design. While for the longitudinal parts (along X axis) a common geometry was obtained, for the transversal beam different types of shapes were observed. Then, according to the simulation settings, its shape could change. Figure 4 illustrates the density distribution resulted from a topology optimization run. Once completed the optimization process, resulting solid was introduced in a CAD software. At this point, mass and inertial characteristics of the optimized bogie frame were imported in the multibody software exploiting the automatic tool created with Python code. In the present research project, multibody model included only rigid bodies. According to the objectives of the work, two types of tracks were analysed: a straight track with a simple discontinuity and a curve of 100 metres" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002593_9312710_09335981.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002593_9312710_09335981.pdf-Figure7-1.png", + "caption": "FIGURE 7. The relationship between the torque of MPMA-SynRM motor and IPM motor with the internal power angle.", + "texts": [ + " 6 and based on the above rotor coordination mode, the torque of the synthetic motor and IPM permanent magnet motor changes with the internal power factor angle torque. 19950 VOLUME 9, 2021 Since the MPMA-SynRM rotors are all synchronous rotors, the motor analysis uses space vector diagrams. Therefore, it is particularly important to establish the spatial vector diagram of the MPMA-SynRM motor. Because the d-axes of the different rotor modules of MPMA-SynRM are not parallel in space but are all under the same stator excitation, the stator excitation current is is used as the reference. The MPMA-SynRM establishment space vector diagram is shown in Fig. 7. In the vector diagram, is is the stator current space vector, id and iq are the alternating and direct axis components from the decomposition of the stator current are to the permanent magnet synchronous rotor module, respectively, LdPM and LqPM are the alternating and direct axis inductances of the permanent magnet synchronous rotor module, respectively, 9PM is the flux linkage generated by the permanent magnets of the permanent magnet synchronous rotor module, 9PMA\u2212SynRM is the flux linkage generated by the permanent magnets of the permanent magnet synchronous rotor module, \u03b2 is the angle between is, the permanent magnet synchronous rotor and the d-axis, and p is the number of pole pairs of the motor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001212_f_version_1605160399-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001212_f_version_1605160399-Figure7-1.png", + "caption": "Figure 7. Stress distribution and deformation evolution of unit cell for specimen HTSW.", + "texts": [ + " The internal microstructures of specimen HTSJ reinforce the joint regions (non-weak regions of the cell), and the stress concentration also occurs in the hollow struts as shown in Figure 6b. From the failure mechanism of specimens HT and HTSJ, it can be concluded that the structural weaknesses (the middle of hollow struts) parallel to the loading directi cause he stress concentration and l ad to the collapse of hollow struts. Actually, the collapse position is largely dete mined by the structural weakness in the loading direction. Figure 7 displays the deformation evolution of the unit cell for specimen HTSW. It intuitively shows that the stress concentration mainly occurs at the joint region of the cell, which can be clearly observed at the strain of 0.04. Compared to the hollow struts of specimen HT, the hollow struts of specimen HTSW are strengthened by internal microstructures. The joint region of specimen HTSW becomes the structural weakness, and the stress concentration mainly occurs in the region marked by the black arrow in Figure 7. With the compressive strain increasing, the joint region gradually collapses. Then, the hollow strut inserts into the abdomen of the joint region, and the collapsed cell extends around the loading direction. Therefore, it can be summarized that the failure mechanism of hollow truss structures is closely related to the structural weaknesses parallel to the loading direction. Different internal microstructures change the structural weaknesses inside the cells, cause the different stress concentrations and affect the collapse position of truss structures. In fact, the collapse of the cell around the loading direction is conducive to obtaining better compressive stability of the specimens during the collapse, which can be confirmed by the aforementioned stress drop coefficient. Moreover, the internal microstructures affect the characteristics of the fracture surfaces of the specimens. The fracture surfaces of the struts for specimens HT and HTSJ show the angle of 45\u00b0 from Materials 2020, 13, 5094 10 of 14 Figure 7 displays the deformation evolution of the unit cell for specimen HTSW. It intuitively shows that the stress concentration mainly occurs at the joint region of the cell, which can be clearly observed at the strain of 0.04. Compared to the hollow struts of specimen HT, the hollow struts of specimen HTSW are strengthened by internal microstructures. The joint region of specimen HTSW becomes the structural weakness, and the stress concentration mainly occurs in the region marked by the black arrow in Figure 7. With the compressive strain increasing, the joint region gradually collapses. Then, the hollow strut inserts into the abdomen of the joint region, and the collapsed cell extends around the loading direction. Therefore, it can be summarized that the failure mechanism of hollow truss structures is closely related to the structural weaknesses parallel to the loading direction. Different internal microstructures change the structural weaknesses inside the cells, cause the different stress concentrations and affect the collapse position of truss structures" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003064_citation-pdf-url_775-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003064_citation-pdf-url_775-Figure7-1.png", + "caption": "Fig. 7. Initial Position Mechanism Sketch", + "texts": [ + " 2 m$ with 0 2 \u2260mh deviates from the normal direction of m$ . Therefore, the three principal screws, m$ , 1 m$ and 2 m$ , also form a seventh special three-system. Therefore, the formation of all linear combinations of m$ , 1 m$ and 2 m$ in three-dimensional space, as shown in Fig.6, is a hyperbolic paraboloid. Fig. 6. The spatial distribution of the screws in General configuration In this section we discuss an interesting 3-DOF special 3-UPU mechanism. It has some special inconceivable characteristics. The 3-UPU mechanism, as shown in Fig. 7a, consists of a fixed pyramid A1A2A3, a moving pyramid a1a2a3 and three UPU kinematic chains. Three centrelines of the three prismatic pairs in the initial position are mutually perpendicular. The middle two revolute pairs, 2$ and 4$ , Fig. 7b, adjacent to the prismatic pair in every branch, are mutually perpendicular, moreover they both are perpendicular to the prismatic pair. This is different with general 3- D translational 3-UPU parallel mechanism (Tsai & Stamper, 1996). The base coordinate system is O-XYZ. The length of each side of the cubic mechanism is m. For this special 3-UPU mechanism, each branch of the mechanism has equivalent five singleDOF kinematic pairs. According to the imaginary-mechanism method mentioned in Section 3, an imaginary link and an imaginary revolute pair denoted by a screw with zero pitch, $0i, are added to each branch, as shown in Fig. 7c. Then, each branch has six single-DOF kinematic pairs. Note that it is necessary to let the angular velocity amplitude of $0 for each branch always be zero. Principal Screws and Full-Scale Feasible Instantaneous Motions of Some 3-DOF Parallel Manipulators 367 For each six-DOF serial branch, the motion of the end-effector of the 3-UPU mechanism can be represented as ( )\u03c6\u23a1 \u23a4= =\u23a3 \u23a6 0 1 , 2 , 3i H iG iV (48) Based on the Eq. (48) and Section 3, the matrix equation as well as [ ]G \u2032 and [ ]G can be [ ]=p GV q [ ]\u2032= G\u03c9 q (50) where [ ]\u2032G is the first three rows of \u23a1 \u23a4\u23a3 \u23a6 H LG ; [ ]G is the last three rows of \u23a1 \u23a4\u23a3 \u23a6 H LG . They both are \u00d73 3 matrices. Fig. 7a shows the initial configuration of the mechanism, m = 1.0 m, l = 0.3 m, and = =1 2 3d d d . For each branch of the mechanism ( )\u03c6 \u03c6 =0 0, 0i i , and iq , ( )= 1 , 2 , 3i , are denoted as inputs. Assume the three lengths from the origin O to the centers of three imaginary pairs all to be = \u2212 il m d , which lie on the X-axis, Y-axis and Z-axis, respectively. di is the distance between the first two kinematic pairs including the imaginary pair. The first-order influence coefficient matrices of the three branches are ( )\u23a1 \u23a4 =\u23a3 \u23a6 0 0 1 3 4 5iG $ $ $ $ $ ( )=, 1 , 2 , 3i According to Eq", + " Obviously, along any direction in space there also exists an instant translational motion by linear combination of the three screws. However, by further analysis we find that only three feasible translational motions can continue along the three coordinate axes, respectively. The feasible translational motions along all other directions in 3-D space are only instantaneous. It is easy to recognize, that when a small finite translation occurs not along the coordinate axis from the initial mechanism configuration, all three UPU chains are not the same as the configuration shown in Fig. 7b, and the three constraint screws will change and not similar that in the first configuration. Not all constrained motions are rotational. Therefore, the finite translation can occur only independently along each one of the three coordinate axes. In other words, three twists with \u221e pitch cannot be linearly combined at this initial position and the mechanism is not the same as the general 3D translational parallel mechanism proposed by Tsai & Stamper, (1996). The mechanism has such a very unusual characteristic" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001925__download_6201_3610_-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001925__download_6201_3610_-Figure6-1.png", + "caption": "Fig. 6 - Surface current distribution at the frequency 5.5GHz for UWB planar antenna with band rejection for 5 to 6GHz", + "texts": [ + "7 and 5 to 6GHz are rejected due to the impedance mismatching in the UWB planar antennas. Slits are considered to interrupt the polarization of exterior current circulation and thus impedance mismatching is realized. The exterior current circulations for the UWB planar antenna with band rejections are presented in the next section. Further exterior current allocations on the conductor surfaces are investigated. The exterior current distributions of the reference and UWB planar antenna comprising slits in the conductor elements are illustrated as in Fig. 6 and 7, consecutively. The exterior current is highly condensed in the radiator and edges of the ground conductor for the reference antenna. The exterior current is distributed vertically from the feed and spread into the conductor element surfaces. The flow of the exterior current is reflected at the edges of the conductor elements. The exterior current polarization is in symmetric for the reference antenna. However, slits existence in the radiator and ground element have resulted the changes in the polarizations of the exterior current distribution on the conductor surfaces" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003380_ownload_article_5098-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003380_ownload_article_5098-Figure2-1.png", + "caption": "Figure 2 Ansys Workbench model of honeycomb sandwich panel (a) Straight-line fiber, (b) Curving fiber", + "texts": [ + " The number on the left indicates the unidirectional orientation fibers content, while on the right indicates the curving orientation fibers content. Table 1 shows the complete fiber content and orientation types. A three-dimensional nonlinear elastoplastic finite element model of Three-Point Bending (TPB) was implemented using the commercial software Ansys Workbench Dynamic to investigate the dynamic mechanical behavior of sandwich panels with honeycomb core. The honeycomb sandwich panel under considered here is constituted by the top and bottom sheet plate panel and a regular hexagon aluminum honeycomb core, as illustrated in Figure 2;1(a) is shown for unidirectional orientation fiber while 2(b) is shown for chopped fiber orientation. For both cases, the sheet panel plate polyethylene and aluminum honeycomb core were bonded as a sandwich while the natural fibers were imported from MATLAB software by introducing the coordinate points using a text document file. In this simulation, the sandwich model's geometrical parameters are defined as follows: The thicknesses of the face sheets and aluminum honeycomb core were defined as 23 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000261_f_version_1481286274-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000261_f_version_1481286274-Figure3-1.png", + "caption": "Figure 3. Ring-shaped RBR: (a) schematic view; (b) simulation model.", + "texts": [ + " 2 2 222 2 )1(||,1 C LCRXRZ C LCjRZ LL (4) ) )1( 12 arctan( 2 0 2 2 2 2 0 Z C LCR C LCZ L (5) 2 2 2 0 2 2 2 0 1( ) ( ) | \u0393 | 1( ) ( ) L LCR Z C LCR Z C (6) From the above discussion, it is possible to use a resonator as a reflector to achieve constructive radiations with the reflecting wave (from the reflector) and the antenna direct radiating wave in a wide frequency band. rw is the width. The ring is printed on a substrate (named F4B-M and from a local factory) with relative permittivity \u03b5r = 2.65 and thickness of 1 mm. With the help of a commercial electromagnetic full-wave simulation software named CST Microwave Studio [26], the simulation model utilized to reveal the characteristics of the RBR is depicted in Figure 3b. PMC boundaries were assumed to be at opposite sides, PEC boundaries were assumed to be at the other opposite sizes, and the top and the bottom sides were assumed to be wave ports that imitate infinitely long waveguides for excitation and absorption. Assigning rg = 25.8 mm and rw = 2 mm, then, the surface current distributions at the resonant frequency fr = 1.72 GHz of the ring were plotted, as shown in Figure 4a. As shown in the figure, the currents originate from the bottom of the ring and flow along the two half-rings to the top", + " By substituting Equation (4) into Equation (2), the value of the reflection coefficient can be obtained as Equation (6), and the power above the resonance is reflected. ZL = R + j \u03c92LC\u2212 1 \u03c9C , |ZL| = \u221a R2 + X2 = \u221a R2 + ( \u03c92LC\u2212 1 \u03c9C )2 (4) \u03d5L = arctan( 2Z0 \u03c92LC\u22121 \u03c9C R2 + (\u03c92LC\u22121 \u03c9C ) 2 \u2212 Z2 0 ) (5) |\u0393L| = \u221a\u221a\u221a\u221a\u221a (R\u2212 Z0) 2 + (\u03c92LC\u22121 \u03c9C ) 2 (R + Z0) 2 + (\u03c92LC\u22121 \u03c9C ) 2 (6) From the above discussion, it is possible to use a resonator as a reflector to achieve constructive radiations with the reflecting wave (from the reflector) and the antenna direct adi ting wave in a w d frequency band. A ring-shaped RBR was proposed as shown in Figure 3a, where rg is the radius of the ring and rw is the width. The ring is printed on a substrate (named F4B-M and from a local factory) with relative permittivity \u03b5r = 2.65 and thickness of 1 mm. With the help of a commercial electromagnetic full-wave simulation software named CST Microwave Studio [26], the simulation model utilized to reveal the characteristics of the RBR is depicted in Figure 3b. PMC boundaries were assumed to be at opposite sides, PEC boundaries were assumed to be at the other opposite sizes, and the top and the bottom sides were assumed to be wave ports that imitate infinitely long waveguides for excitation and absorption. Assigning rg = 25.8 mm and rw = 2 mm, t en, the surface current distributions at the resonant frequency fr = 1.72 GHz of the ring were plotted, as shown in Figure 4a. As shown in the figure, the currents originate from the bottom of the ring and flow along the two half-rings to t e top" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003809_el-03253472_document-Figure3.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003809_el-03253472_document-Figure3.6-1.png", + "caption": "Figure 3.6 : Circuit \u00e9quivalent semi-localis\u00e9 d\u2019une cellule d\u2019une ligne CRLH en T (a) et en \u03a0 (b)", + "texts": [ + " Cette \u00e9tude param\u00e9trique est illustr\u00e9e Figure 3.21 et Figure 3.22. DECRIPTION DE LA METHODE DE DESIGN DE DEPHASEURS CRLH-TL 98 La longueur de capacit\u00e9 MIM correspondant au circuit \u00e9quivalent est de 0.22mm. La diff\u00e9rence avec la valeur estim\u00e9e provient sans doute de l\u2019influence de la surface de contact de longueur lvia o\u00f9 doit \u00e9galement se produire un effet capacitif avec la ligne. Nous pouvons \u00e9galement nous int\u00e9resser aux capacit\u00e9s MIM d\u2019un circuit en T qui sont alors au nombre de 2 et chacune du double de la valeur de CL (voir Figure 3.6). La longueur de la structure compos\u00e9e de ces deux capacit\u00e9s MIM est alors quatre fois plus \u00e9lev\u00e9e que dans le circuit en T. Comme nous pouvons le voir dans la Figure 3.23, la capacit\u00e9 prend toute la longueur de la cellule, ainsi les circuits en T se r\u00e9v\u00e8lent plus difficiles \u00e0 concevoir pour ces valeurs de capacit\u00e9s. Les circuits en \u03a0 seront alors privil\u00e9gi\u00e9s pour la ligne 2- LH et la ligne 4-LH, qui ont une longueur de cellule plus faible. Nous pouvons alors d\u00e9terminer la longueur de chaque capacit\u00e9 en cherchant la longueur correspondante \u00e0 une capacit\u00e9 de valeur 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000138_f_version_1712826389-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000138_f_version_1712826389-Figure2-1.png", + "caption": "Figure 2. Structure of the initial mesh of the slab considering developing temperature gradients at the free surfaces, the material flow, pronounced in the rolling direction, and a moving contact patch. Due to regular meshing, potential symmetry planes are equipped with nodes to be constrained by boundary conditions. In the case of prevailing symmetry, these boundary conditions substitute redundant areas of the plate (not shown in this figure). The convention for using the terms head, tail, left, and right within this article is outlined.", + "texts": [ + " Parameters that control the structure of the initial mesh are the base element edge length and three bias factors (one in each edge direction of the cuboid slab). Since the material flow is predominant in the rolling direction and the contact patch moves longitudinally, rolling direction-dependent meshing is implemented in the model. Except for the edge zones, the discretization in the current width direction is coarsened by a factor of four. The structure of the slab\u2019s initial mesh is shown in Figure 2. On the one hand, the length and width bias factors refer to a local coordinate system linked with the plate. Hence, a rotation of the plate does not affect this material-fixed assignment. On the other hand, a rotation of the plate changes the orientation of the rolling direction; therefore, the former coarse-meshed direction turns to the fine-meshed direction and vice versa. Mesh refinement demands the generation of intermediate nodes, including a linear interpolation of coordinates and temperatures at these nodes", + " Degenerate elements are identified and rehabilitated using an angle criterion. Suppose the angle \u03b2 between two element edges of the examined element is outside the tolerable range of 30\u25e6 to 150\u25e6. In this case, the node located at the vertex is slightly moved to bring the angle back into the fair range. The temperature at such nodes is interpolated accordingly. An abstraction of this procedure is outlined in Figure 3c. Metals 2024, 14, 444 7 of 16 Metals\u00a02024,\u00a014,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 6\u00a0 of\u00a0 17\u00a0 \u00a0 \u00a0 \u00a0 Figure\u00a02.\u00a0Structure\u00a0of\u00a0the\u00a0initial\u00a0mesh\u00a0of\u00a0the\u00a0slab\u00a0considering\u00a0developing\u00a0temperature\u00a0gradients\u00a0at\u00a0 the\u00a0free\u00a0surfaces,\u00a0the\u00a0material\u00a0flow,\u00a0pronounced\u00a0in\u00a0the\u00a0rolling\u00a0direction,\u00a0and\u00a0a\u00a0moving\u00a0contact\u00a0patch.\u00a0 Due\u00a0to\u00a0regular\u00a0meshing,\u00a0potential\u00a0symmetry\u00a0planes\u00a0are\u00a0equipped\u00a0with\u00a0nodes\u00a0to\u00a0be\u00a0constrained\u00a0by\u00a0 boundary\u00a0 conditions.\u00a0 In\u00a0 the\u00a0 case\u00a0of\u00a0prevailing\u00a0 symmetry,\u00a0 these\u00a0boundary\u00a0 conditions\u00a0 substitute\u00a0 redundant\u00a0areas\u00a0of\u00a0the\u00a0plate\u00a0(not\u00a0shown\u00a0in\u00a0this\u00a0figure).\u00a0The\u00a0convention\u00a0for\u00a0using\u00a0the\u00a0terms\u00a0head,\u00a0 tail,\u00a0left,\u00a0and\u00a0right\u00a0within\u00a0this\u00a0article\u00a0is\u00a0outlined", + "\u00a0 In\u00a0the\u00a0temperature\u00a0assessment,\u00a0the\u00a0position\u00a0on\u00a0the\u00a0top\u00a0of\u00a0the\u00a0fillet\u00a0of\u00a0the\u00a0slab\u00a0serves\u00a0 as\u00a0a\u00a0reference,\u00a0as\u00a0this\u00a0temperature\u00a0may\u00a0be\u00a0available\u00a0for\u00a0validation.\u00a0Additional\u00a0references\u00a0 at\u00a0this\u00a0fillet\u00a0position\u00a0are\u00a0the\u00a0numerically\u00a0evaluated\u00a0temperatures\u00a0at\u00a0the\u00a0quarter-thickness\u00a0 and\u00a0 the\u00a0plate\u2019s\u00a0 core.\u00a0 Four\u00a0 further\u00a0positions\u00a0 (material\u00a0fixed\u00a0 in\u00a0 the\u00a0 thickness\u00a0direction)\u00a0 included\u00a0in\u00a0the\u00a0investigation\u00a0are\u00a0offset\u00a0equidistantly\u00a0inwards\u00a0in\u00a0the\u00a0longitudinal\u00a0direction\u00a0 from\u00a0the\u00a0slab\u2019s\u00a0head,\u00a0as\u00a0seen\u00a0in\u00a0Figure\u00a02.\u00a0The\u00a0total\u00a0offset\u00a0amount\u00a0corresponds\u00a0to\u00a0400\u00a0mm\u00a0 on\u00a0 the\u00a0 rolled\u00a0plate\u00a0 (after\u00a0 the\u00a0 last\u00a0pass).\u00a0This\u00a0offset\u00a0was\u00a0 chosen\u00a0because\u00a0 it\u00a0needs\u00a0 to\u00a0be\u00a0 examined\u00a0whether\u00a0 the\u00a0 temperature\u00a0gradient\u00a0 in\u00a0 the\u00a0 longitudinal\u00a0direction\u00a0has\u00a0decayed\u00a0 sufficiently\u00a0and,\u00a0hence,\u00a0a\u00a0sample\u00a0taken\u00a0from\u00a0this\u00a0position\u00a0is\u00a0representative\u00a0of\u00a0the\u00a0rolled\u00a0 heavy\u00a0plate\u00a0in\u00a0terms\u00a0of\u00a0its\u00a0material\u00a0properties.\u00a0In\u00a0other\u00a0words,\u00a0the\u00a0model\u00a0can\u00a0be\u00a0used\u00a0to\u00a0 In the temperature assessment, the position on the top of the fillet of the slab serves as a reference, as this temperature may be available for validation. Additional references at this fillet position are the nu erically evaluated te peratures at the quarter-thickness and the plate\u2019s core. Four further positions (material fixed in the thickness directi n) included in the investigation are offset equidistantly inwards in the longitudinal direction from the slab\u2019s head, as seen in Figure 2. The total offset amount corresponds to 400 mm on the rolled plate (after the last pass). This offset was chosen because it needs to be examined whether the temperature gradient in the longitudinal direction has decayed sufficiently and, hence, a sample taken from this position is representative of the rolled heavy plate in terms of its material properties. In other words, the model can be used to predict and, hence, minimize the crop lengths at the heavy plate\u2019s head and tail ends that have to be cut off as scrap since these parts might violate specified temperat re ranges during rolling", + " The surface, quarter-thickness, and core temperatures after the last pass at position 1 are reduced by 77 \u25e6C, 104 \u25e6C, and 127 \u25e6C compared to corresponding temperatures at the reference (fillet) position. Evaluation of the three vertical positions at position 2, shown in Figure 6c, delivers temperature drops of 38 \u25e6C, 55 \u25e6C, and 67 \u25e6C relative to the reference position. Positions 1 and 2 belong to the cut-off scrap [32]. Positions 3 and 4, shown in Figure 6d,e, have temperature differences of 20 \u25e6C, 32 \u25e6C, and 38 \u25e6C and 9 \u25e6C, 17 \u25e6C, and 22 \u25e6C, respectively. This shows that at positions 3 and 4, the influence of the head side surface (Figure 2) has almost subsided since the temperatures reach \u226596% of the corresponding fillet temperatures. In conclusion, forming in the vicinity of positions 3 and 4 proceeds under thermal conditions very close to those prevailing in the fillet. In addition to the time course, the temperature profile in the longitudinal direction is relevant to assess the thermal conditions during forming. Figure 7 shows the temperature profiles after the ninth and the final pass. The areas of homogeneous temperature can easily be identified from this representation, thus indirectly indicating the potential size of the scrap that may need to be discarded", + " As depicted in Figure 6a, the calculated temperature at the surface of the plate matches well with the measured temperatures given in Table 1. This is especially true for the last three measurement points to which the model is tuned (in terms of radiation and convection). Hence, considering unavoidable measurement inaccuracies, the validation can be assessed positively for this model, which aims to evaluate the temperature field inside the plate. Metals 2024, 14, 444 14 of 16 Metals 2024, 14, x FOR PEER REVIEW 14 of 17 surface (Figure 2) has almost subsided since the temperatures reach \u226596% of the corresponding fillet temperatures. In conclusion, forming in the vicinity of positions 3 and 4 proceeds under thermal conditions very close to those prevailing in the fillet. In addition to the time course, the temperature profile in the longitudinal direction is relevant to assess the thermal conditions during forming. Figure 7 shows the temperature profiles after the ninth and the final pass. The areas of homogeneous temperature can easily be identified from this representation, thus indirectly indicating the potential size of the scrap that may need to be discarded" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001563_f_eems2017_02002.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001563_f_eems2017_02002.pdf-Figure3-1.png", + "caption": "Fig. 3. The geometry of the precalcinator and numerical mesh.", + "texts": [ + " According to the laws on the reactions rate, the formation of NOx by means of transition mechanism can be written as: [ ] [ ][ ]( )22,r22,f ]NO[kOONk2 dt NOd \u2212= (13) It is assumed that N2O is in a quasi-stationary state, which implies dependence: [ ] [ ][ ][ ] [ ] [ ] [ ]OkMk NOkMONk ON 2,f1,r 2 2,r21,f 2 + + = (14) In this work mathematical model based on Euler's method to describe the motion of the gas phase and the Lagrange method to describe the motion of particles [22-26]. Numerical calculations were made on pregenerated computational meshes, as shown in Fig.3. In order to take into account the combustion process, it was necessary to add carbon fuel data as used in the precalcinator in the program. The following parameters were used: \u2022 calorific value \u2013 24.6 MJ/kg, \u2022 chemical composition as molar proportions: C \u2013 0.409, H \u2013 0.573, O \u2013 0.014, N \u2013 0.004, \u2022 10 fractional RRS distributions were used for: minimum diameter 10-6 m, maximum diameter 250\u00b710-6 m, main 100\u00b710-6 m and separation factor 3.5. The scheme analyzed in the calculation of the precalcinator is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001448__for_Controlling.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001448__for_Controlling.pdf-Figure2-1.png", + "caption": "Fig. 2. Angle of attack and the direction of relative wind", + "texts": [ + " ANGLE OF ATTACK CONTROL SYSTEM Figure 1 below depicts the block diagram representation of the angle of attack with disturbance and controller. In this diagram input is the elevator deflection and output is the angle of attack. G s Transfer function of angle of attack C s Fuzzy PI controller Transfer Function 1G s G s Disturbance where, E s The elevator deflection The angle of attack 139 | P a g e www.ijacsa.thesai.org Angle of attack is defined as the angle between the chord line of the wing and the relative motion between aircraft and atmosphere. It is controlled by the elevator deflection. Figure 2 below illustrates the angle of attack and the direction of relative wind. Considering the short period approximation (speed of the aircraft u=constant) the longitudinal dynamics [5] of the aircraft reduces to elevator deflection, then using vector matrix notation, Equation (1) and Equation (2) may be written as 0 Ew Ew Z w U q Z (1) 0 E E E w w q E w w w q w w E q M w M w M q M M M Z w M U M q M Z M (2) If w x q the state vector and u= the control vector = x Ax Bu (3) where, 0 0 w w w w q w Z U A M M Z M U M E E E w Z B M Z M Now 0 0 1 0 0 1 w w w w q w Z U sI A s M M Z M U M 0 0 0 0 w w w w q w Z Us M M Z M U Ms 0 0 w w w w q w s Z U M M Z s M U M (4) Again, 2 0 0detsp w q w w q ws sI A s Z M U M s Z M U M 2 22 sp sp sps s (5) The transfer function is given by 0 0 1 1 1 E qE E qE E w E sp sp Z U M M Z s U M M Zw s K sT s s s (6) where, 0 E Ew qK U M M Z 1 E w Z T K " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002046_O201336447759533.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002046_O201336447759533.pdf-Figure4-1.png", + "caption": "Fig. 4 \u223c Fig. 10\uc740 \ud574\uc11d\uacb0\uacfc\ub97c \ub098\ud0c0\ub0b8\ub2e4.", + "texts": [ + " 3] Mesh generation \uace0\uc555\uc138\ucc99\uae30 \ub0b4\ubd80\uc640 \uc678\ubd80\uc758 \uc720\uccb4 \ud750\ub984\uc744 \uc54c\uc544\ubcf4\uae30 \uc704\ud558 \uc5ec \uac01\uac01 100, 120, 150, 160, 180, 200, 250bar\uc758 \uc555\ub825\uc744 \uc8fc\uc5b4 \uc720\ub3d9\ud574\uc11d[4-7]\uc744 \uc2e4\uc2dc\ud558\uc600\ub2e4. Table 2\ub294 \ud574\uc11d\uc870\uac74\uc774\ub2e4. [Table 2] Physics conditions Domain-Default Domain Type Fluid Location B564, B732, B803 Materials Water Fluid Definition Material Library Morphology Continuous Fluid Settings Buoyancy Model Non Buoyant Domain Motion Stationary Reference Pressure 100.0000e+00[bar] ~ 2500.0000e+00[bar] Heat Transfer Model Isothermal Fluid Temperature 2.5000e+01[C] Turbulence Model kepsilon Turbulent wall functions scalable Mass Flow rate 0.250 [kg/s] [Fig. 4] Flow Speed(100bar) [Fig. 5] Flow Speed(120bar) [Fig. 6] Flow Speed(150bar) [Fig. 7] Flow Speed(160bar) [Fig. 8] Flow Speed(180bar) [Fig. 9] Flow Speed(200bar) [Fig. 10] Flow Speed(250bar) Table 3\ub294 \uace0\uc555\uc138\ucc99\uae30\uc758 \uc555\ub825\uc5d0 \ub300\ud55c \ub0b4\ubd80 \uc720\uc18d \uac12\uc774 \ub2e4. \uace0\uc555\uc138\ucc99\uae30\uc758 \ud615\ud0dc\ub85c \uc778\ud558\uc5ec \uc555\ub825\uc774 \ub192\uc544\uc9c0\uba74 \uc720\uc18d\uc774 \uc0c1\uc2b9\ud558\ub294 \uac83\uc73c\ub85c \ub098\ud0c0\ub0ac\ub2e4. [Table 3] Internal flow speed Pressure(bar) Flow Speed(m/s) 100 25.75 120 31.68 150 36.25 160 37.94 180 40.96 200 43.54 250 46.83 3. \uacb0\ub860 \ubcf8 \ub17c\ubb38\uc740 \uace0\uc555\uc138\ucc99\uae30\uc758 \uc131\ub2a5\uc744 \ud5a5\uc0c1\uc2dc\ud0a8 \uc81c\ud488\uac1c\ubc1c\uc744 \uc704\ud558\uc5ec \ud604\uc7a5\uc5d0\uc11c \uc0ac\uc6a9\ub418\ub294 \uc81c\ud488\uc744 \ubd84\ud574 \uce21\uc815\ud558\uc600\uc73c\uba70 CATIA\ub97c \uc0ac\uc6a9\ud558\uc5ec \ubaa8\ub378\ub9c1\ud558\uc600\ub2e4. \uc774\ub7ec\ud55c \uace0\uc555\uc138\ucc99\uae30\uc5d0 \ub300\ud558\uc5ec \uc720\ub3d9\ud574\uc11d\uc744 \uc2e4\uc2dc\ud558\uc5ec \ub2e4\uc74c\uacfc \uac19\uc740 \uacb0\ub860\uc744 \uc5bb\uc5c8\ub2e4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.8-1.png", + "caption": "Figure 6.8: RV Endface Configurations", + "texts": [ + "27) must be used depending on the orientation and affected flange with the appropriate flange dimensions. \ud835\udc47\ud835\udc53,\ud835\udc4f\ud835\udc53 = \u222b \u222b (\ud835\udc53\ud835\udc4f\ud835\udc53\ud835\udc5f) \u2219 \ud835\udc5f\ud835\udc51\ud703\ud835\udc51\ud835\udc5f 2\ud835\udf0b 0 \ud835\udc5f\ud835\udc4f\ud835\udc53,2 \ud835\udc5f\ud835\udc4f\ud835\udc53,1 = 2\ud835\udf0b 3 \ud835\udc53\ud835\udc4f\ud835\udc53(\ud835\udc5f\ud835\udc4f\ud835\udc53,2 3 \u2212 \ud835\udc5f\ud835\udc4f\ud835\udc53,3 3 ) (6.31) Due to the plane rotation of the rubbing surface at the endfaces, the method of analysis for the endface friction would be similar to that employed by Subiantoro and Ooi [117]. Instead of fluid shear force from the lubricant acting on the rotor and cylinder, the RV compressor prototype is affected by Coulomb friction instead. Figure 6.8 shows the different endface configurations for the RV mechanism in which the shaded regions show the overlapping endface areas affected by friction. 106 For an arbitrary point in the shaded regions for any configuration, the velocity of the cylinder and rotor endfaces are expressed as shown in Equations (6.32) and (6.33) respectively. The relative velocity is then calculated as shown in Equation (6.34). \ud835\udc97\ud835\udc50 = \ud835\udf4e\ud835\udc50\u00d7\ud835\udc93\ud835\udc51,\ud835\udc50 = ( 0 0 \u2212\ud835\udf14\ud835\udc50 )\u00d7( \u2212\ud835\udc4f\ud835\udc50 sin \ud703\ud835\udc50 \u2212\ud835\udc4f\ud835\udc50 cos \ud703\ud835\udc50 0 ) = \u2212\ud835\udf14\ud835\udc50\ud835\udc4f\ud835\udc50 cos \ud703\ud835\udc50 ?\u20d1? + \ud835\udf14\ud835\udc50\ud835\udc4f\ud835\udc50 sin \ud703\ud835\udc50 ?\u20d1? (6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001092_2_1_12_22004507__pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001092_2_1_12_22004507__pdf-Figure7-1.png", + "caption": "Fig. 7. Magnetic flux distribution of the jigsawpuzzle-shaped magnet", + "texts": [ + " An additional process for installing the plug is included, and the geometrical structure of the fixed magnets in the motor is shown in Fig. 5. Here A, B and C are the Magnet thickness, Magnet angle of spread and Frame thickness. Figure 6 is a color block representation of the magnetic flux density of the spliced magnets. The rated saturation magnetic flux density is 2.2 T. The areas where the maximum magnetic saturation occur after applying the new improvement strategy are clearly seen. Compared with the traditional design, the dovetail grooves are more evenly distributed. Figure 7 depicts the distribution of the magnetic field lines for the spliced configuration that relieves magnetic saturation. The simulation condition for the test includes a rotation speed of 3,400 rpm, and the material used for the pin is the same as that of the pole core of the prototype, which is S10C. The results shown in Table 3 indicate that under the conditions of identical thickness and development angle, even though the volume of the spliced magnet is slightly higher, 66 IEEJ Journal IA, Vol.12, No" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004479_tation-pdf-url_11272-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004479_tation-pdf-url_11272-Figure4-1.png", + "caption": "Fig. 4. (a) TA, (b) CM and (c) BM Dimming Methods", + "texts": [ + " Therefore, dimming control is an important design consideration for LED backlight applications. We studied three dimming methods for current regulation of the parallel connected LED arrays: the transconductance-amplifier (TA) dimming, the current-mirror (CM) dimming and the burst- mode (BM) dimming. www.intechopen.com Introduction to LED Backlight Driving Techniques for Liquid Crystal Display Panels 209 Fig. 2. Block Diagram of an LCD TV Power Supply. Fig. 3. RGB LED Backlight Driving Circuit Figure 4(a) shows the TA dimming circuit. The LED current can be expressed as Equation (1). R V I d LED = , (1) Figure 4(b) shows the CM dimming circuit. The LED current can be expressed as Equation (2). R V-V VVKII GSd TNGSnrLED =\u2212=\u2248 2)( , (2) where Kn and VTN are the conduction parameter and threshold voltage of the dimming transistors Qr and Qd, respectively. By using the TA dimming and CM dimming circuits, the www.intechopen.com New Developments in Liquid Crystals 210 current regulation of paralleled LED arrays can be achieved. However, the conduction losses of the dimming transistors will be difficult to solve [17]. An adaptive voltage output for the DC-DC converter is usually designed to retain the minimum drain-source voltage on the dimming transistors. As shown in Figure 4(c), the backlight LED current can be also controlled with a BM dimming circuit. Considering the switching loss for the dimming transistors, the burst-mode frequency fb is designed at 400Hz that are unperceivable to the human eye. The duty ratios of the dimming transistors are varied to regulate the LED average current that can be represented as Equation (3). \u03b4 mLED(av) II = , (3) where Im denotes the peak value of the LED array current. The dimming transistors are operated as low-frequency switches, the thermal problem on the dimming transistors can be improved significantly" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure78-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure78-1.png", + "caption": "FIGURE 78. Geometry and dimensions of the naval ship [45].", + "texts": [ + " Mode X (Y ) represents the x-polarized (y-polarized) mode with current flowing along the x(y)-direction. Fig. 77 shows the MS values of Modes X and Y from 3 to 10 MHz in these different environments. It is observed that MS values with the presence of dry earth, wet earth, and seawater are larger than those in free space, due to additional conductive ground in the vicinity of the AAV. Another study in [45] presented an efficient CM-based approach in designing a platform-embedded HF shipboard antenna system. The CMs of the entire ship platform shown in Fig. 78 is calculated to synthesize the desired radiation patterns. Moreover, the localization of the synthesized currents on a small part of the existing platform makes the CM-based structural antenna concept suitable for electrically medium or large platforms. The CMs are first solved to understand the resonant behavior of the ship platform. The radiating currents are then synthesized to produce the desired radiation patterns using CMs on the ship platform. This is made more efficiently by the modal solutions in CM theory" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003708_19_ms-10-47-2019.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003708_19_ms-10-47-2019.pdf-Figure2-1.png", + "caption": "Figure 2. Kinematic sketch of the novel transmission configuration with globe and local axes: (a) vertical view; (b) side view.", + "texts": [ + " The rotary stiffness would increase as the number of steel cable increase, and as the number of input shafts increase. At last, this configuration has better security and lower probability of failure. If multiple drive shafts are employed, and one should fail, the other shafts will work as usual. The main drawback of this configuration can be considered as a fundamental limited roll rotation, which bars their general use in power trains, but it is enough for the fields of stabilized sighting system or infrared imaging seeker. It is clearly seen in Fig. 2, the motion of the output pulley (\u03b8o) is transmitted from the two motors (\u03b8ml, \u03b8mr). The guide pulley (\u03b8g) is used to change the direction of motion. The four colored curves represent the cables utilized in this transmission configuration. The cables are all terminated in the input pulleys at one end and pretensioned in the output drum at the other. It is defined as \u03b8o = 0 when the Z axis of output pulley is parallel with the Z axis of the others. It is also defined as \u03b8g = 0, \u03b8ml = 0, \u03b8mr = 0 when the Y axis of guide pulley, or left input pulley, or right input pulley is parallel with the Y axis of output drum, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003283_tation-pdf-url_13336-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003283_tation-pdf-url_13336-Figure8-1.png", + "caption": "Fig. 8. Flexible Gripper Examples T-pod based (left) and hybrid linear module based attached to a handling robot (right)", + "texts": [ + " As for the handling of underbodies/car bodies it is also necessary to find a new solution for the part handling in the cell. Today mostly geometric grippers are used, which can already have a modular structure but are restricted to a fixed geometric shape for only one part. To achieve the required flexibility to adapt to different sizes of parts for different car models, it is possible in the same way as for the skids to replace the fixed locators off the geometric grippers with programmable positioners. Fig. 8 shows examples for such a type of highly flexible geometric gripper with different types of flexible positioners that will be mounted on robots. Since all them use robot technology they can be programmed and controlled like the conventional robots integrated in each car body assembly cell. The obvious approach to build a 3-axis positioner for carrying the pin locators and clamping tools typically used for positioning and fixing car body parts is based on a Cartesian arrangement of single linear axis modules", + " The advantage of this machine is the reduced footprint in one direction, so that it can be place in very narrow spaces, but in particular the possibility to remove the synchronization and add an extra motor to the perpendicular parallelogram, so that an optional tilt motion around the symmetry axis can be introduced leading to the T-pod4 configuration. This can be particular useful when fixturing buckled car body parts. The T-pod4 is somewhat related to the Kanuk (Rolland, 1999), even though the drive mechanism is different. Combining e.g. four of those T-POD positioners to a common backbone attached to a powerful handling robot a flexible programmable gripper can be achieved which provides an excellent payload compared to its own mass (see Fig. 8). By use of flexible grippers the part logistics within highly flexible car body assembly lines which is another big issue become addressed. With flexible grippers\u2019 space and cycle time consuming tool changing of different grippers as well as additional grippers themselves can www.intechopen.com New Trends and Developments in Automotive Industry 216 be abandoned. Different from typical tool (gripper) changing a flexible gripper will be reconfigured according to the part geometry of the successive car model during the transfer motion of the handling robot without affecting the primary processing time" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001585_9312710_09370131.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001585_9312710_09370131.pdf-Figure1-1.png", + "caption": "FIGURE 1. The structure of the RC. Two Z-shaped mode stirrers are installed at the corner of the chamber. A turn-table platform is placed beside the vertical stirrer. The mechanical controller, power supplier and the cable connectors are fixed on the wall respectively.", + "texts": [ + " C. STIRRERS AND TURN-TABLE PLATFORM Themost important mechanical part in RC is the mode stirrer. The kind of stirrer as well as its position needs to be carefully designed, which is related to the field uniformity and the volume of the uniform field. The shape and the motion model were discussed in [23], [24], where a Z-shape stirrer and rotating motion are proved to provide a better uniform field in a rectangular RC. The size, bending angle and number of plates are also considered. As shown in Fig. 1, there are two mechanical stirrers installed in the RC: one is horizontally installed on the top of the cavity, and the other is vertically installed beside the wall. The positions of the stirrers are determined by the \u03bb/4 principle, where \u03bb is the wavelength of the LUF. The stirrers need to be at least \u03bb/4 away from the chamber, DUT, antennas, and turn-table platform. The stirrers can rotate continuously or step by step. The turn-table platform has been previously employed as a type of source stirrer to increase the uniformity of a field [3]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001411_de_Rooij-Lohmann.pdf-Figure1.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001411_de_Rooij-Lohmann.pdf-Figure1.4-1.png", + "caption": "Figure 1.4. Schematic representation of the 10-mirror optics in an EUV lithography tool.", + "texts": [ + " Debris from the light source and hydrocarbons from the photoresist contaminate the surface, which results in a decreased reflectance. The reflectance can be largely recovered by certain cleaning procedures, but the associated downtime of the lithography tool makes that a costly affair. Moreover, cleaning procedures can have negative side-effects, viz. sputter removal or oxidation of the top layer, or enhanced interdiffusion (see Section 1.3) if e.g. cleaning goes along with a large heat load. Secondly, EUVL imposes high demands on the reflectance of the mirrors, because, as shown in Figure 1.4, typically as many as ten mirrors and one reflective mask are needed for aberration-free demagnification and projection of the pattern on a mask onto the chip in the making. The EUV radiation power that arrives at the substrate after eleven reflections (ten mirrors and one mask) determines to a large extent the throughput of a lithography tool. Knowing that, it is easily seen that every possible improvement of the multilayer reflectance is necessary. This is even more true as long as state-ofthe-art EUV light sources are not (yet) powerful enough to facilitate a sufficiently high throughput for commercial exploitation of lithography tools" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001712_8948470_08963975.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001712_8948470_08963975.pdf-Figure2-1.png", + "caption": "FIGURE 2. 1D pendulum hardware and corresponding notation.", + "texts": [ + " The proposed observers are experimentally compared with a linearization-based Luenberger observer. In Section IV we consider bias estimation based on low-pass filtering and show the limitations of this approach. A reduced-order bias observer augmenting the previously designed control law is proposed and analyzed in Section V, where experimental results and comparison with the low-pass filtering are also given. Finally, possible further research directions are discussed in the concluding Section VI. II. MODEL DESCRIPTION AND STATE-FEEDBACK CONTROL LAW The hardware for the tests (shown in Figure 2) is assembled from off-the-shelf components. A 70W Maxon EC 45 flat brushless DC motor is used to drive the reaction wheel (a bicycle brake rotor). The motor is controlled using Maxon EPOS2 50/5 controller running in torque mode; the controller measures the current as well as the rotor angle. A STM32F407 discovery board was chosen as the main computing unit, where the board communicates with the motor controller via CANopen protocol. A. MODEL DESCRIPTION In our model the main variables are \u03b8 and \u03b8r , where \u03b8 is the angle between the pendulum and the vertical, and \u03b8r is the angle of the reaction wheel with respect to the pendulum. VOLUME 8, 2020 19451 It is worth noting that the notation follows [2] with one exception: we measure \u03b8r with respect to the pendulum body and not with respect to the vertical. Refer to Figure 2 for an illustration; Table 1 provides all parameters and notation used in the paper. The values of the parameters were obtained by direct measurements. We use Lagrange\u2019s approach to derive the equations of motion. The Lagrangian is given by L = Tp + Tr \u2212 P = 1 2 J \u03b8\u03072 + 1 2 Jr (\u03b8\u0307r + \u03b8\u0307 )2 \u2212 mlg cos \u03b8, where ml := mplp + mr lr , J := Jp + mpl2p + mr l 2 r , and Tp = 1 2 (mpl2p + Jp)\u03b8\u0307 2, Tr = 1 2 mr l2r \u03b8\u0307 2 + 1 2 Jr (\u03b8\u0307r + \u03b8\u0307 )2, P = (mplp + mr lr )g cos \u03b8, are the kinetic energy of the pendulum, the kinetic energy of the reaction wheel, and the potential energy, respectively; all the symbols are as defined in Table 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure16-1.png", + "caption": "Fig. 16, The shaft under torsion and the associated dimensional parameters", + "texts": [ + " TORSIONAL MODES OF A UNIFORM SHAFT In engineering applications, shafts and particularly shafts with a uniform cross section are the most common components for transferring power. Shafts have the important property that their circular cross sections remain planar and do not warp in torsion. Due to their widespread applications, the twisting vibration of such parts is of great significance. The part under consideration is a shaft of length \ud835\udc3f = 150 \ud835\udc5a\ud835\udc5a with a circular cross section of radius \ud835\udc45 = 10 \ud835\udc5a\ud835\udc5a. This is displayed in Fig. 16. The plan is to model the first \ud835\udc3f\ud835\udc40\ud835\udc43 = 100 \ud835\udc5a\ud835\udc5a of the shaft with linear tetrahedron elements. The subscript \u201cMP\u201d refers to the \u201cModelled Part\u201d. The end \ud835\udc3f\ud835\udc49\ud835\udc43 = 50 \ud835\udc5a\ud835\udc5a is to be consisting of the Virtual Part, or \u201cVP\u201d. The exact location of the handler point is not relevant if \u201cRigid\u201d or \u201cRigid Spring\u201d is employed and the deformation is purely torsional. Regardless, for the sake of consistency, the handler point is positioned at the centroid of the portion which is not modelled. The theoretical torsional natural frequencies are computed from the expression \ud835\udc5b = (2\ud835\udc5b\u22121) 4\ud835\udc3f \u221a \ud835\udc3a \ud835\udf0c where \ud835\udc5b = 1 2 3 \u2026 The frequency \ud835\udc5b has been normalized to have the units of Hz" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000691_f_version_1607615822-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000691_f_version_1607615822-Figure3-1.png", + "caption": "Figure 3. Seed distributor: (a) Schematic diagram with 1/7 removed to show the internal structure; (b) Real device.", + "texts": [ + " Considering the load and volume restrictions of the aircraft, a small but powerful fan (model: WS9250-24-240-X200, Wonsmart Co. Ltd., Ningbo, China) was chosen as the main power source of airflow, which needs a work voltage of 24 V DC with a 6.5 A current. Weighing 400 g, it can generate 42 m3/h airflow and 8 kPa air pressure in nominal. The function of the distributor is to split the single seed stream into multiple strands equally via the airflow. A small-scale distributor with seven channels was designed as shown in Figure 3, according to the conventional air assisted centralized metering device of the ground planter. This was fabricated by 3D printing based on FDM (Fused deposition modeling) with PLA material. Appl. Sci. 2020, 10, x FOR PEER REVIEW 6 of 14 Shenzhen, China) was chosen as the feeding motor. This is a serial bus servo motor that can work continuously a d stably at 25~45 r/min with a torque range of 15~20 kg\u00b7cm. We chose N as 35 r/min f r he average speed. The measured seed bulk density \u03c1 was 674.5 kg/m3 [19]", + " Considering the load and volume restrictions of the aircraft, a small but powerful fan (model: WS9250-24-240-X200, Wonsmart Co. Ltd., Ningbo, China) was chosen as the main power source of airflow, which needs a work voltage of 24 V DC with a 6.5 A current. Weighing 400 g, it can generate 42 m3/h airflow and 8 kPa air pressure in nominal. The function of the distributor is to split the single seed stream into multiple strands equally via the airflow. A small-scale distributor with seven channels was designed as shown in Figure 3, according to the conventional air assisted centralized metering device of the ground planter. This was fabricated by 3D printing based on FDM (Fused deposition modeling) with PLA material. carried out following a step by step procedure. The rapeseed variety used in the experiments was \u201cHuayouza-62\u201d, a winter Brassica napus variety developed by researchers at Huazhong Agricultural University in 2011 and is now widely planted in central China. The first experiment was an orthogonal experiment [21]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004281__9_6_9_19012601__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004281__9_6_9_19012601__pdf-Figure8-1.png", + "caption": "Fig. 8. Experimental system", + "texts": [ + " Experiment In this section, the virtual acoustic impedance at a desired position is made equal to the acoustic impedance of the desired medium by controlling the sound pressure emitted by the secondary sound source represented by (27). Subsequently, the generation of a virtual wall is confirmed through simulation. 4.1 Experimental Setup Two experiments were conducted for comparing the real wall with the virtual one. Experimental system used is acoustic system composed of microphone, acoustic tube, and speakers as sound source and secondary sound source. Figure 8 shows experimental system. Table 1 presents the parameters of the experiments. The parameters used by the model in (16) are the sound velocity c = 340 m/s and the position of the virtual wall x. In experiment A, the real wall is placed at the end of acoustic tube, i.e. x = l. Figure 9 shows the situation in experiment A. Sound source that is speaker driven current emittes sound wave. At this time, the sound pressure is observed at x = l 2 and l 3 by microphone. In experiment B, the virtual wall is placed at the end of the acoustic tube i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004706_el-04657928_document-Figure3.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004706_el-04657928_document-Figure3.3-1.png", + "caption": "Figure 3.3 Quadcopter in climbing forward flight. Side view.", + "texts": [ + " Thrust-to-weight ratios Thrust-to-weight ratios are used to size the propulsion system for different flight scenarios. The calculation of the thrust to be provided by the rotors in each scenario is distinct for multirotor systems and fixed-wing UAVs. For multirotor UAVs, the thrust calculation involves the equilibrium of forces acting on the vehicle, namely the weight (W ), the aerodynamic forces (drag Df and downward force Lf ), and the thrust of the rotors (Fi). The parameters involved in the equilibrium equations are shown in Figure 3.3, where V\u221e is the free stream velocity and Vh the vertical speed, so 3.3 Models for the preliminary design of UAVs 45 that \u03b8F P is the flight path angle of the drone [112]. Some assumptions are made here for simplicity. The rotors are assumed to be identical and symmetrical with respect to the center of gravity of the UAV. They are also assumed to be in the same plane, i.e. horizontal with respect to the UAV body frame. As a result, the tilting moment can be neglected and the rotors are treated as operating under the same conditions (F1 = F2 = ", + "1235J2 axial These aerodynamic coefficients are corrected to take into account non-zero incidence angles for the propeller. Leng et al. [113] propose an analytical model to express the thrust and power coefficients at non-zero incidence angle as ratios to their respective values in axisymmetric conditions. For a given blade geometry the authors suggest the following expressions: CT,P (\u03b1, J) = \u03b7T,P (\u03b1, J)Caxial T,P (Jaxial) (3.11a) \u03b7T,P (\u03b1, J) = 1 + (J cos\u03b1/\u03c0r\u2032)2 2(1 \u2212 J sin\u03b1/Jaxial 0T,P ) \u03b4(\u03b1) (3.11b) Where: \u2022 \u03b1 is the angle of attack as defined in Figure 3.3. \u2022 J = V\u221e n.dpro is the advance ratio. \u2022 Jaxial = V\u221e sin \u03b1 n.dpro is the axial advance ratio. \u2022 Jaxial 0T,P are the axial advance ratios where the thrust and power coefficients reach zero respectively. These ratios can be obtained by solving Equation 3.10 for Caxial T = 0 and Caxial P = 0. 1https://www.apcprop.com/technical-information/performance-data/ 50 Efficient sizing and optimization of multirotor, fixed-wing and fixed-wing VTOL UAVs \u2022 r\u2032 is the position of the representative section of the blade, in percentage radius (taken as 75%)", + "5 Aerodynamics The calculations of the wing loading and thrust-to-weight ratios introduced in Section 3.3.1 require the determination of the aerodynamic forces applying to the UAV. The following equations distinguish between the aerodynamics of multirotor UAVs and those of fixed-wing and FW-VTOL UAVs. Multirotor UAVs For multirotor UAVs in climbing or cruising conditions, the airframe drag Df and lift Lf are expressed as: Df = 1 2CD\u03c1airV 2 \u221eSref (3.28a) Lf = 1 2CL\u03c1airV 2 \u221eSref (3.28b) As depicted in Figure 3.3, Lf acts as a downward force when the drone moves forward \u2014 the aerodynamic surfaces on a multirotor UAVs are mostly disadvantageous. The effective area Sref varies with the angle of attack and the surfaces facing the relative wind: Sref = Stop sin\u03b1+ Sfront cos\u03b1 (3.29) The drag coefficient CD and the lift coefficient CL are highly dependent on the shape of the frame. Other parameters such as Reynold\u2019s number affect their value. Since the shape of the airframe is highly dependent on the application and payload, a generic model would 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure8-1.png", + "caption": "Figure 8. Equivalent process of the windings.", + "texts": [ + " In 3-D modeling process of the CS-PMSM, to build an accurate model of the windings is quite difficult. This is mainly because the conductors in each coil are randomly distributed inside the slots. The random distribution of the conductors in the slots has a certain influence on the maximum temperature of the windings [47]. Besides, the insulation layer of the conductor is thin, which will bring us a big problem in the model meshing. An effective equivalent method of the distributed conductors is normally used in the 2-D thermal field analysis [48], as shown in Figure 8. An equivalent copper conductor, whose area equals the sum of all copper conductor areas, is put in the center of the slot. And an equivalent insulation, which consists of the slot insulation, the equivalent air gap layer and the equivalent insulation varnish layer, is evenly put outside the equivalent copper conductor. On the basis of this method, the 3-D winding models in the slots, considering both radial and axial heat transfer effect, are built in this paper. In Figure 8, the thermal conductivity of the equivalent insulation \u03bbeq is given by: 1 2 3 eq 31 2 1 2 3 \u03bb \u03bb \u03bb \u03bb d d d dd d + + = + + (4) where d1 is the thickness of the slot insulation; d2 is the thickness of the air gap layer; d3 is the thickness of the equivalent insulation varnish layer; and \u03bb1, \u03bb2, \u03bb3 are the corresponding thermal conductivities. In the CS-PMSM, these parameters have the following values for the stator windings: d1 = 0.3 mm, d2 = 0.7 mm, d3 = 0.6 mm, \u03bb1 = 0.15 W/m\u00b7K, \u03bb2 = 0.0242 W/m\u00b7K, \u03bb3 = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003650_cle_8976_context_etd-Figure2.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003650_cle_8976_context_etd-Figure2.11-1.png", + "caption": "Figure 2.11: (a) Pulsed programming (b) Continuous programming.", + "texts": [ + " Pulsed programming is a simple method to program a floating-gate to a certain voltage. In pulsed programming, short programming and reading intervals are applied alternatively until a target current is read through read interval. The programming process is ended when the target current or voltage is observed. In the programming interval, the FG transistor is being programmed for a short time while in read interval and the output current or voltage is measured to evaluate the effect of the preceding programming interval. Pulsed programming is shown in Fig. 2.11a. Programming pulse duration and programming voltage Vsd control Pulsed Programming Continuous-Time Programming the injection rate during programming intervals. Pulsed-based programming has high accuracy programming as the length of the programming interval can be changed, and thus the amount of charge (injection rate) in the programming interval can be adjusted. Additionally, current measurement in read mode is done in conditions similar to run-mode (i.e. nominal Vsd voltage); this will further improve programming accuracy", + " In this approach, calibration mode is used first to characterize the injection rate, and then a mathematical model is used to summarize the characterization data into few parameters required to choose the optimal Vsd for programming. The calibration mode makes this approach complicated and not suitable for large FG arrays. Furthermore, this approach is not suitable for portable applications as high-precision converters and wide-range current measurements are required. Continuous programming is performed in one single programming period as shown in Fig. 2.11(b); after which the FG cell is placed in run mode to read the programmed current/voltage. Programming process length is controlled using a negative feedback path and is stopped when the floating-gate transistor reaches its target. Using negative feedback is also beneficial to ensure a constant Vsd that linearizes the injection process which provides the condition for predictable injection rate. With the use of the single programming period and linear injection process, continuous programming is faster than pulsed programming and provides predictable injection results, which makes it the more favorable injection method" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002189_f_version_1500114111-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002189_f_version_1500114111-Figure1-1.png", + "caption": "Figure 1. (a) CAD drawing of a fully assembled flapping wing; (b) flapping mechanism; and (c) output flapping angle of the flapper at flapping frequency of 15 Hz.", + "texts": [ + " Multidisciplinary experiments were conducted to provide the natural frequency, force production, and three-dimensional wing kinematics as well as the effects of wing flexibility experienced Aerospace 2017, 4, 37 3 of 26 by the flexible wings. The aerodynamic performance of the present flapping wing MAV was carried out in the hovering condition. Stereoscopic digital particle image velocimetry (SDPIV) was used to obtain the flow structures around the wing at the Reynold number of approximately 3500. The results of unsteady aerodynamics of the flexible wings presented in this work can be used in the efficient wing design for the flapping wing MAV. The flapping mechanism consists of a Scotch-yoke and crank-slider mechanism (Figure 1). The rotating output from the motor is first converted into linear motion with a crank slider mechanism. The flapping wing mechanism can achieve a maximum stroke amplitude of 92\u25e6, which is within the flapping angle range of insect flight. The kinematics of the flapping mechanism are close to the sinusoidal kinematic profile as shown in Figure 1c. The flapper is powered by a DC power supply and can flap at flapping frequency of 10 to 25 Hz. The flapping mechanism was mounted on a Nano 17 (Nano 17 IP68, ATI Industrial Automation, Apex, NC, USA) six-component force balance and a supporting frame. The wings were aligned vertically and flapped in the horizontal plane. The support frame was mounted on a rotating mount and a translation stage (Figure 1). The total height of the flapping wing system was 484 mm. This was designed to isolate the apparatus from outside disturbance, whilst minimizing the wall interference effects in the experiment. The linkages and the supporting frame of the flapper were fabricated by a precision computer numerical control (CNC) machining of acrylic sheet. Aerospace 2017, 4, 37 3 of 26 wing MAV was carried out in the hovering condition. Stereoscopic digital particle image velocimetry (SDPIV) was used to obtain the flow structures around the wing at the Reynold number of approximately 3500. The results of unsteady aerodynamics of the flexible wings presented in this work can be used in the efficient wing design for the flapping wing MAV. he flapping mechanism consi t of a Scot h-yoke and crank-slider mechanism (Figure 1). The rotating output from the motor is first convert d into linear motion with a crank slider mechanism. e flapping wing mechanism can achieve a maximum stroke amplitude of 92\u00b0, which s within the flapping a le range of insect flight. The kinematics of the flap ing mechanism are close to t e si s i r file as shown in Figure 1c. The flapper is powered by a DC power supply and can flap t flapping frequency of 10 to 25 Hz. e fla i ec a is as ounte on a Nano 17 (Nano 17 IP68, ATI Industrial Automation, ex, , ) e t f . The ings ere li e rtic ll fl i t ri t l l . he support fra e as ounted on a rotati g o nt a a tra slati st ( i ). e total hei t of the fla i i s st . This as esigned to isolate t e a arat s fr tsi e ist r a ce, ilst i i izi g t e all i terfere ce effects i t e eri e t. The linkages and the supporting fra e of the flapper ere fabricated by a r i i i l l i i li ", + " The cured wings were released from the base and taped on the mold. The artificial wing shapes were then cut following the designed shape. Figure 6. Wing manufacturing: (a) the composite laminate; and (b) cured in autoclave. A six-axis force/torque sensor (Nano17, ATI industrial Automation Inc., Apex, NC, USA) is used to measure the instantaneous aerodynamic forces on the flapping wing mechanism. The force sensor (17 mm diameter, 20.1 mm length) is attached to the base of the flapping mechanism (Figure 1a). Using a data-acquisition board and programs written in LabView (National Instruments, Austin, TX, USA) (A/D conversion), the force data are recorded at the sampling rate of 3000 Hz. The LabView program collects raw voltages from the sensor during testing. These voltages are later post-processed with the ATI-supplied calibration matrices to generate the forces and moments. The LabView program is synchronized with the flapping motion. The force signal is filtered offline with a zero phase delay low-pass digital Butterworth filter", + " The variation of the angle of attack of the wing during sweeping motion plays an important role in force production [17]. It can be seen from the section profile that the W1 performed a non-uniform movement. Note that the dot lines represented wing profiles in the downstroke. It is clear that for the W1, there is mostly no angle Figure 10. Photographs of ing defor ation of six odel wings at the iddle of the do nstroke and upstroke. The movie of images is available as Supplementary Material Movie 1. Figure 1 shows the diagram of the instantaneous wing profiles at the middle of the wing span of all six wings through one wing beat cycle with a fl pping frequency of 15 Hz. The 3D deformation f six wings can be seen clearly in the movies in Supplem ntary Materials. The variation f the angle of attack of the wing during sweeping motion plays an important role in force production [17]. It can be seen from th section profile that the W1 performed a non-uniform movem nt. Note that the dot lines represented wing profiles in the downstroke" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000882_article-file_1157957-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000882_article-file_1157957-Figure2-1.png", + "caption": "Fig. 2. An example of driveshaft configurations; one piece, two and three pieces in descending order.", + "texts": [ + " Driveshaft, one of these components of powertrain, is the most important component in motor vehicles, for transmitting torque and rotation. It is used as an intermediate element that provides connection between other components of the drivetrain such as transmission and differential. In this way, it allows for relative movement between them [1]. Driveshaft basically comprises of one or more universal joints, yoke parts, splined parts and center support bearing depending on what the driving and driven components are used. Fig. 2 shows an example of configurations of driveshaft and its sub-components. Each component on the driveshaft performs different functions such as angular and axial movement. All these components, composing the driveshaft, have various geometrical and structural features to perform their basic functions. Driveshaft therefore its sub-components are subjected to torsion between driving and driven components of the vehicle. Thus, they must be strong enough to withstand the stress Driveshaft used for transmitting torque and rotation, is one of the most important components in motor vehicles" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003882_f_version_1645520937-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003882_f_version_1645520937-Figure11-1.png", + "caption": "Figure 11. Physical prototype.", + "texts": [ + " The spinning accelerates swiftly then decelerates markedly because of the separate actions for each part during ejection of the pole. This spinning then decelerates slowly during the in-air process. To have a jump that is gentle in damage but strong in displacement, a larger value of k should be set, the surfaces of the sliders should be polished to reduce friction, and the strings must be long enough to avoid inducing intense interior pulse forces. Based on the chosen scheme of virtual prototype, a physical prototype (Figure 11) was built using three-dimensional printing. Fishing wire was used for the upper and lower strings, and the total stiffness of the serried springs was measured to be 1.28 N/mm. The motor adopted is in the GA12-N20 type, with an output shaft in the length of 55 mm. The Li-ion battery is with an output voltage of 12 V. To deal with uneven terrain and vibration of the motor while running, a PVC slice was attached to the pole through nut\u2013bolt pairs, thereby enlarging the supported area and preventing the mechanism from falling over" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003997_e_download_7367_3540-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003997_e_download_7367_3540-Figure4-1.png", + "caption": "Figure 4. Horizontal forces for tractor wheels [11]", + "texts": [ + " The design of CDD type anti-skid truck wheel shoes from several necessary components, namely: (1) traction rods/wheel fins (as the focus of this study), (2) traction rod connecting and (3) fastening components, plates (2 and 3 are not discussed), as shown in Figure 3. (a) (a) Sketch of an anti-slip shoe mounted on the rear wheel of a CDD type truck (front view position). (b) Sketch of 3-dimensional anti-slip shoes on CDD type truck wheels To design the anti-slip shoes on a palm oil hauling truck, the assumption of traction calculation on the tractor wheels relates to the forces acting under the wheels and the ground, as shown in Figure 4. The study uses a tractor wheel design as a guideline because of the availability references with scientific discussion, especially in the agricultural technology journals. The vehicle tire traction enhancer products are already widely available in world markets, but there is not in the scientific journal yet that discusses them. There are only patent documents that can be found for such similar products [10][11]. 216 D.T.Wahyudi and D.S.Khaerudini, Design of Anti-Slip Shoes for 12 Ton Palm Oil Truck \u2026 Traction is the force produced by the torque of the wheel into an overall straight motion. Conversely, if the torque of the wheel does not produce an overall straight motion, then the slippage occurs [12]. A tractor can move if the horizontal ground reaction force (Fh) must be greater than the sum of half drawbar pull (DBP) and rolling resistance, as shown in Figure 4, or \u03a3 Fh \u2265 0. 5 (DBP + R) [11]. Thus, the DBP formula can be expressed as: DBP = Fh \u2013R (1) DBP = draw bar pull (kg), Fh = traction or thrust (kg), R = rolling resistance(kg). Because the truck is not pulling the load then DBP = 0, so Fh - R = 0, or Fh=R (2) Thus the truck can move forward if: \u03a3 Fh \u2265R (3) The weight of the tractor used will directly affect the amount of rolling resistance which is estimated to be proportional to the dynamic weight on the cogs, so that: R = CR.W (4) Where CR = coefficient of rolling resistance, with the values as shown in Figure 5, W = dynamic weight on the wheel drive (kg)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure39-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure39-1.png", + "caption": "Figure 39 : G\u00e9om\u00e9trie du r\u00e9seau utilis\u00e9 par Magill et Wheeler [36].", + "texts": [ + " Page 34 sur 182 Quand une source est utilis\u00e9e dans un r\u00e9seau \u00e0 balayage, elle se d\u00e9sadapte \u00e0 mesure que l\u2019on augmente l\u2019angle de d\u00e9pointage, son coefficient de r\u00e9flexion actif, qui est le coefficient de r\u00e9flexion vu quand toutes les sources du r\u00e9seau sont aliment\u00e9es, se d\u00e9t\u00e9riore. L\u2019objectif est donc de trouver un moyen de compenser cette d\u00e9t\u00e9rioration. Une m\u00e9thode classique est l\u2019utilisation des Wide-Angle Impedance Matching (WAIM). Ce sont Magill et Wheeler qui, en 1966 proposent les premiers dans [36] (Figure 39), cette m\u00e9thode nomm\u00e9e WAIM. Ils proposent de placer une fine couche de substrat di\u00e9lectrique au-dessus du r\u00e9seau d\u2019antennes. Cette fine couche di\u00e9lectrique fait varier l\u2019admittance du r\u00e9seau en fonction de la constante di\u00e9lectrique et de l\u2019\u00e9paisseur du substrat di\u00e9lectrique mais aussi en fonction de sa position au-dessus du r\u00e9seau. En choisissant bien ces trois param\u00e8tres, il est possible d\u2019obtenir une meilleure adaptation d\u2019imp\u00e9dance du r\u00e9seau \u00e0 un ou plusieurs angles de d\u00e9pointage. Ainsi, une am\u00e9lioration \u00e0 trois angles, un dans chacun des plans D, E et H (D \u00e9tant le plan diagonal entre les plans E et H) est obtenue" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003169_1_1_article-p624.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003169_1_1_article-p624.pdf-Figure2-1.png", + "caption": "Fig. 2. Mobile crane stability: loss of crane in stability (a), slewing bearing damage (b)", + "texts": [ + " Depending on the type of chassis (or mounting method) of the crane, these edges are as follows: tracked chassis - the tipping edges are the axles of the first pair of rollers at the front and the drive wheel at the rear for the longitudinal position of the crane and the symmetry axes of the rollers cooperating with the track plates at the transverse position, wheeled chassis, work without supports (if possible) - the tipping edges are both in the longitudinal and lateral position of the wheel symmetry axes, wheeled chassis, work with supports - the tipping edges run in this case through the centers of the support legs (Fig. 2a). In addition to stability, the critical element of the crane is a slewing bearing that acts as a turning node for the boom. Its load capacity often determines the load capacity of the entire device (\u015apiewak, 2016). Therefore, improper operation of the crane may damage the bearing and contribute to the loss of boom stability (Fig. 2b) (Krynke and Mielczarek, 2016). The object of considerations is the slewing ring bearing used in the rotation mechanism of the DST - 5050 self-moving crane. In the case of the above crane, a cross roller bearing with a rolling diameter of 1400 mm and catalog symbol 1.KW.Z.T.50.1390.3.3.01 (Fig. 3) was used. The crane load characteristics are shown in Figure 4. The ADINA (2009) software was used to build the numerical model. The bearing rings and frames of the body and chassis were discredited by eight-nodes solid elements of 3D-solid type (Yu, 2017)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001163_O201110441050686.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001163_O201110441050686.pdf-Figure1-1.png", + "caption": "Fig. 1 View of the vine crusher for sweet potato.", + "texts": [], + "surrounding_texts": [ + "9 The article was submitted for publication on 2010-11-16, reviewed on 2011-01-19, and approved for publication by editorial board of KSAM on 2011-01-31. The authors are Sung Il Kang, Graduate Student, Soo Nam Yoo, Professor, Chonnam National University, Gwangju, Korea, Yong Choi, Agricultural Researcher, National Academy of Agricultural Science, RDA, Suwon Korea, and Young Joo Kim, Senior Researcher, KSAM member, Environmental Materials & Components Center, Korea Institute of Industrial Technology, Jeonju, Korea. Corresponding author: S. N. Yoo, Professor, Department of Rural and Bio-systems Engineering and College of Agricultural and Life Sciences, Chonnam National University, Gwangju, 500-757, Korea; Tel: +82-62-530-2155; Fax: +82-62-530-2159; E-mail: .\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uac15\uc131\uc77c \uc720\uc218\ub0a8 \ucd5c \uc6a9 \uae40\uc601\uc8fc\nDevelopment of a Vine Crusher for Harvesting Sweet Potato\nS. I. Kang S. N. Yoo Y. Choi Y. J. Kim\nThis study was carried out to develop a vine crusher for harvesting sweet potato. The experimental two-row vine crusher attachable to agricultural tractor composed of vine crushing part with frail type vine crushing blades and vine lifting blades, power transmission part with chain and gear transmission mechanism, crushing height control part with two control wheels and manual levers, and implement frames, was designed and fabricated. And this vine crushing performance was also analyzed.\nFrom vine crushing tests, backward travel direction (i.e., rotational direction of the vine crushing blades) showed better vine crushing performance than forward travel direction. Crushing ratio of remained vine was increased, and length of remained vine and length of crushed vine were decreased as working speed was decreased and rotational speed of vine crushing blades was increased. At a working speed of 0.27 m/s and rotational speed of vine crushing blades of 800 rpm, crushing ratio of remained vine was 98%, length of remained vine was 104 mm, and length of crushed vine was 327 mm. But, when crushing vine on irregular ridges, vines and mulching vinyl were wound in the vine crushing part. Therefore, change of location of power transmission chain mechanism, and an automatic control device for controlling crushing height were needed.\nKeywords : Vine crusher, Sweet potato, Frail blade\n1. \uc11c \ub860\n\uc77c\ubc18\uc801\uc73c\ub85c \uad6d\ub0b4\uc758 \uace0\uad6c\ub9c8 \uc7ac\ubc30\ubc29\ubc95\uc740 \ubcd1\ud574\ucda9 \ubc29\uc9c0, \uc218\ud655 \ub7c9 \uc99d\uac00 \ub4f1\uc758 \uc7a5\uc810\uc73c\ub85c \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\uac00 \ub9ce\uc740 \ubc18\uba74, \uc678\uad6d\uc758\n\uacbd\uc6b0 \uc7ac\ubc30\uba74\uc801\uc774 \ub300\uaddc\ubaa8\ub85c \uac70\uc758 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\ub97c \ud558\uc9c0 \uc54a\uc73c \uba70, \ubcc4\ub3c4\uc758 \ub369\uad74\ucc98\ub9ac\uc791\uc5c5 \uc5c6\uc774 \uc218\ud655\uc791\uc5c5 \ud6c4 \ub369\uad74 \ubc0f \ud611\uc7a1\ubb3c\ub85c \ubd80\ud130 \uace0\uad6c\ub9c8\ub97c \uc120\ubcc4\ud558\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \uad6d\uc678\uc758 \uacbd\uc6b0 \uace0\uad6c\ub9c8 \ub369 \uad74\ucc98\ub9ac\uae30\uc5d0 \uad00\ud55c \uc5f0\uad6c\ub294 \uac70\uc758 \uc5c6\ub294 \uc2e4\uc815\uc774\ub2e4. \uace0\uad6c\ub9c8 \uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \uc904\uae30\uc808\ub2e8\uae30\uc640 \ube44\ub2d0\uc81c\uac70 \uae30\uc758 \uc774\uc6a9\uc73c\ub85c ha\ub2f9 \uc791\uc5c5\uc2dc\uac04\uc740 \uc57d 8\uc2dc\uac04\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4 (Namerikawa, 1989). \ub610\ud55c \uc904\uae30\uac77\uc5b4\uc62c\ub9bc\ubd09\uacfc \ud504\ub808\uc77c type \ud68c\n\uc804\ub0a0 \uc808\ub2e8\ubc29\uc2dd\uc744 \uc774\uc6a9\ud55c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 1\uc870 \uace0\uad6c\ub9c8 \uacbd\uc5fd\ucc98\ub9ac \uc7a5\uce58\ub97c \uc774\uc6a9\ud558\uc5ec \uc8fc\ud589\uc18d\ub3c4 0.35\uff5e0.46 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 28.6 m/s\uc5d0\uc11c \uacbd\uc5fd\ucc98\ub9ac\uc728 91.7\uff5e92%, \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774 38\uff5e43 cm\ub85c \uacbd\uc5fd\ucc98\ub9ac \uc815\ub3c4\uac00 \uc591\ud638 \ud558\uc600\ub2e4\uace0 \ubcf4\uace0\ud558\uc600\uc73c\uba70 (Park and Choi, 1995), \uae30\uc874 \ub369\uad74\uc808\ub2e8\uc7a5\uce58 \ub4a4\uc5d0 \ub514\uc2a4\ud06c\ud615 \ub369 \uad74\uc808\ub2e8\uc7a5\uce58\ub97c \ucd94\uac00\ub85c \ubd80\ucc29, \uac1c\ub7c9\ud558\uc5ec \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774\uac00 15.4 cm\ub85c \ub0ae\uc544\uc84c\uc74c\uc744 \ubcf4\uace0\ud558\uc600\ub2e4(Park and Choi, 1997). Ha(2006)\ub294 \ub3d9\ub825 \uacbd\uc6b4\uae30\ub97c \uc774\uc6a9, \uacbd\uc6b4\uae30 \ud6c4\ubc29\uc5d0 1\uc870\uc6a9 \ub369 \uad74\ucc98\ub9ac\uc7a5\uce58\ub97c \ubd80\ucc29\ud558\uc5ec 92%\uc758 \ub369\uad74\ucc98\ub9ac\uc728, 2.5 h/10a \uc791\uc5c5 \uc2dc\uac04\uc73c\ub85c \uad00\ud589 \uc778\ub825\uc758 \uc791\uc5c5\uc2dc\uac04\uc778 26 h/10a \ubcf4\ub2e4 \uc57d 1/10\ub85c \uc791\uc5c5\uc2dc\uac04\uc744 \uc808\uc57d\ud560 \uc218 \uc788\ub294 \uac83\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub9c8\ub298\n\ubc14\uc774\uc624\uc2dc\uc2a4\ud15c\uacf5\ud559 (J. of Biosystems Eng.) Vol. 36, No. 1, pp.9~14 (2011. 2) DOI:10.5307/JBE.2011.36.1.9\nOpen AccessResearch Article", + "\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 \uc904\uae30\uc808\ub2e8 \ubc0f \ube44\ub2d0\ud53c \ubcf5 \uc81c\uac70\uae30\ub97c \uc774\uc6a9\ud558\uc5ec \uc808\ub2e8\ub192\uc774 100 mm, \uc8fc\ud589\uc18d\ub3c4 0.53 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 67.86 m/s\uc5d0\uc11c \uc808\ub2e8\uc815\ub3c4 95.5%\ub85c \ubcf4\uace0\ud55c \ubc14 \uc788\ub2e4(Noh et al., 1999). \uc6b0\ub9ac\ub098\ub77c\uc758 \uace0\uad6c\ub9c8\uc758 \ucd1d \uc7ac\ubc30\uba74\uc801\uc740 2003\ub144\ub3c4 14,161 ha\uc5d0 \uc11c 2007\ub144 21,093 ha\ub85c \uafb8\uc900\ud55c \uc99d\uac00 \ucd94\uc138\uc5d0 \uc788\uc73c\ub098(MFAFF, 2009), \uc9c0\uae08\uae4c\uc9c0 \uae30\uc874\uc758 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc5d0 \ub300\ud55c \uc5f0\uad6c\ub294 1 \uc870\uc6a9\uc73c\ub85c \uc791\uc5c5\ub2a5\ub960\uc774 \ub5a8\uc5b4\uc9c0\uace0 \uc0ac\ub78c\uc774 \uc9c1\uc811 \ub530\ub77c\ub2e4\ub140\uc57c \ud558\ub294 \ub2e8\uc810\uc774 \uc788\uc73c\uba70 \ud604\uc7ac \ub18d\uac00\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8\uc218\ud655\uae30\uac00 \ubcf4\uae09 \ub418\uc5b4 \uc0ac\uc6a9\ub418\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8 \uc218 \ud655\uae30\uc5d0 \uc801\ud569\ud558\uace0 \uae30\uc874 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ubcf4\ub2e4 \ud6a8\uc728\uc801\uc778 2\uc870 \uc6a9 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ub97c \uac1c\ubc1c\ud558\uace0\uc790 \ud558\uc600\ub2e4.\n2. \uc7ac\ub8cc \ubc0f \ubc29\ubc95\n\uac00. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc124\uacc4\uff65\uc81c\uc791\n1) \uc8fc\uc694 \uad6c\uc870 \ubc0f \uc81c\uc6d0\n\uadf8\ub9bc 1\uc5d0\uc11c\uc640 \uac19\uc774 \ud2b8\ub799\ud130 PTO\ub97c \uc774\uc6a9\ud558\uc5ec \ub3d9\ub825\uc774 \uc804\ub2ec\ub418 \ub294 \ud2b8\ub799\ud130 \ubd80\ucc29\ud615\uc73c\ub85c 2\uc870\uc758 \ub450\ub451 \ub369\uad74 \ud30c\uc1c4\uac00 \uac00\ub2a5\ud558\ub3c4\ub85d \uc81c\uc791\ud558\uc600\ub2e4. \uc8fc\uc694\uad6c\uc870\ub294 \ub369\uad74 \ud30c\uc1c4\ub0a0\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\ub85c \uad6c\uc131\ub418\uc5b4 \uc788\ub294 \ub369\uad74 \ud30c\uc1c4\ubd80, \ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc744 \ub369\uad74 \ud30c\uc1c4\ubd80 \uad6c\ub3d9\ucd95\uc73c\ub85c \uc804\ub2ec\ud574\uc8fc\ub294 \uae30\uc5b4\ubc15\uc2a4, \uc2a4\ud504\ub85c\ucf13, \uccb4 \uc778, \uae30\uc5b4 \ub4f1\uc73c\ub85c \uad6c\uc131\ub41c \ub3d9\ub825 \uc804\ub2ec\ubd80, \ub369\uad74 \ud30c\uc1c4\uc791\uc5c5 \uc2dc \ub450\ub451\n\uc758 \ub192\uc774\uc5d0 \ub530\ub77c \ubbf8\ub95c\uc758 \ub192\ub0ae\uc774\ub97c \uc870\uc808\ud568\uc73c\ub85c\uc11c \ub369\uad74 \ud30c\uc1c4\ubd80 \uc758 \ub192\uc774\ub97c \uc870\uc808\ud560 \uc218 \uc788\ub294 \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80, \ud2b8\ub799\ud130 \ubd80\ucc29\uc7a5\uce58 \ubc0f \ud504\ub808\uc784 \ub4f1\uc73c\ub85c \uc8fc\uc694\ubd80\ub97c \uad6c\uc131 \uc124\uacc4\uff65\uc81c\uc791\ud558\uc600\ub2e4.\n2) \ub369\uad74 \ud30c\uc1c4\ubd80\n\ub369\uad74 \ud30c\uc1c4\ubd80\ub294 \uadf8\ub9bc 2\uc5d0\uc11c\ucc98\ub7fc \ud68c\uc804\ub0a0 \ud30c\uc1c4\uc2dd\uc73c\ub85c \ub369\uad74 \ud30c \uc1c4\ub0a0, \ud30c\uc1c4\ub0a0 \ubd80\ucc29 \ube0c\ub77c\ucf13, \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5 \ucd95, \ub369\uad74 \uac77\uc5b4\uc62c \ub9bc\ub0a0, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ubd80\ucc29 \uc6d0\ud310, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95, \uc9c0\uc9c0 \ubca0\uc5b4\ub9c1 \ub4f1 \uc73c\ub85c \uad6c\uc131 \uc81c\uc791\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0\uc740 \uadf8\ub9bc 3\uc5d0\uc11c\ucc98\ub7fc \uc81c\ucd08\n\uc6a9\uc73c\ub85c \ub9ce\uc774 \uc4f0\uc774\ub294 \uae38\uc774 120 mm, \ub450\uaed8 5 mm\uc758 \ud504\ub808\uc77c\ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \ud53c\uce58 70 mm \ub098\uc120\uc73c\ub85c \uc88c\uff65\uc6b0 \uac01\uac01 48\uac1c, \ucd1d 96\uac1c\ub97c \ubc30\uce58\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub0b4\uacbd 75 mm \uc911\uacf5\ucd95\uc778 \ud30c\uc1c4\ub0a0 \ucd95 \uc744 \ubca0\uc5b4\ub9c1\uc73c\ub85c \ub07c\uc6cc \ub9de\ucda4\ud558\uc5ec \uc88c, \uc6b0 \ud30c\uc1c4\ub0a0\ub4e4\uc744 \uac01\uac01 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ubd84\ub9ac \uad6c\ub3d9\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc740 \uadf8\ub9bc 4\uc5d0\uc11c\ucc98\ub7fc \ub05d\uc774 \ubfb0\uc871\ud55c \uae38\uc774 250 mm 6\uac1c \uc9c1\uc120\ub0a0\uc744 \uc6d0\uc8fc \ud53c\uce58\uac01 60\u00b0 \uac04\uaca9\uc73c\ub85c \ub192\uc774 \uc870\uc808\uc774 \uac00 \ub2a5\ud55c \ube0c\ub77c\ucf13\uc5d0 \ubd80\ucc29\ud558\uace0 \ube0c\ub77c\ucf13\uc744 \uc6d0\ud310\uc5d0 \uace0\uc815\ud558\uc600\ub2e4. \uc88c\uff65 \uc6b0\uff65\uc911\uc559 3\uacf3 6\uac1c\uc529 \ubaa8\ub450 18\uac1c\uc758 \ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \uccb4\uc778 \uc804 \ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5\ucd95 \uc548\uc758 \uc9c1\uacbd 35 mm \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\uc5ec \uac77\uc5b4\uc62c\ub9bc \uc791\uc6a9\uc744 \ud558\ub3c4\ub85d \ud558 \uc600\ub2e4.\n3) \ub3d9\ub825 \uc804\ub2ec\ubd80\n\ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc774 \uae30\uc5b4\ubc15\uc2a4\uc5d0\uc11c 2.5\ubc30\ub85c \uc99d \uc18d\ub418\uc5b4 \uad6c\ub3d9\ucd95 \uc88c\uff65\uc6b0\ub85c \ub098\ub258\uc5b4\uc838 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77 \uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\ub294 \uacfc\uc815\uc744 \uadf8\ub9bc 5\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \uad6c\ub3d9\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc6b0\uce21\uc758 \uad6c\ub3d9\ucd95\uc73c\ub85c", + "J. of Biosystems Eng. Vol. 36, No. 1.\n\ubd80\ud130 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95 \uc548\uc5d0 \uc788\ub294 \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uc9c1\uc811 \uad6c\ub3d9\uc2dc\ud0a8\ub2e4. \uadf8\ub9bc 6\uc740 \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\ucd95\uc758 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \uc2dc\uc758 \ub3d9\ub825 \uc804\ub2ec \ubc29\ubc95\uc744 \ub098\ud0c0\ub0b8 \uac83\uc774\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \uc804\uc9c4\ubc29 \ud5a5 \ud68c\uc804(\uc815\ud68c\uc804)\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c \ucf13\uacfc \uae30\uc5b4\uac00 \uc870\ud569\ub41c 2\uac1c\uc758 \ubc29\ud5a5\uc804\ud658 \ucd95\uacfc \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\n\ucd95\uc744 \uac70\uccd0 \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc \ud0a4\uace0, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \ud6c4\uc9c4\ubc29\ud5a5 \ud68c\uc804(\uc5ed\ud68c\uc804)\uc740 \uae30\n\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c\ucf13\uacfc \ud150\uc158 \uc2a4\ud504\ub85c\ucf13\uc744\n\uac70\uccd0 \uc911\uacf5\uc758 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc\ud0a4\ub3c4\ub85d \ud558 \uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \ud68c\uc804\uc18d\ub3c4\ube44\ub294 9 : 1\ub85c \uace0\ub791\uc5d0 \uc788\ub294 \ub3cc\uc5d0 \uc758\ud55c \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \uc190\uc0c1 \ubc0f \ub369\n\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc5d0 \uc758\ud55c \ube44\ub2d0\ud53c\ubcf5 \uc190\uc0c1 \ub4f1\uc758 \ubb38\uc81c\uc810\uc774 \ubc1c\uc0dd\ub420 \uc218\ub3c4 \uc788\uae30 \ub54c\ubb38\uc5d0 \ud68c\uc804\uc18d\ub3c4\uc758 \ucc28\uc774\uac00 \uc788\ub3c4\ub85d \ud558\uc600\ub2e4.\n4) \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80\n\ub369\uad74\ucc98\ub9ac \uc791\uc5c5 \uc2dc \ub369\uad74 \ud30c\uc1c4\ubd80\uc758 \ud30c\uc1c4\ub192\uc774\ub97c \uc81c\uc5b4\ud558\uba70, \uace0 \ub791\uc744 \uc774\ud0c8\ud558\uc9c0 \uc54a\uace0 \uc791\uc5c5\uae30\uc758 \uc8fc\ud589 \uc548\uc815\uc131\uc744 \ub192\uc774\uae30 \uc704\ud558\uc5ec \uc124\uce58\ud55c \ubbf8\ub95c\uc758 \uad6c\uc870\ub97c \uadf8\ub9bc 7\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ubbf8\ub95c\uc740 \uc9c1\uacbd 400 mm, \ud3ed 100 mm\ub85c \ub450\ub451\uc758 \ud615\uc0c1\uc5d0 \ub530\ub77c \ub369\uad74\ud30c\uc1c4\ubd80\uc758\n\ub192\ub0ae\uc774\ub97c \uc704\ucabd\uc758 \ub808\ubc84\ub97c \ud68c\uc804\uc2dc\ucf1c \uc870\uc808\ud560 \uc218 \uc788\ub3c4\ub85d \ud558\uc600\uc73c \uba70, \ub192\uc774 \uc870\uc808\uc740 300 mm\uae4c\uc9c0 \uac00\ub2a5\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ubbf8\ub95c\uc758 \uc124 \uce58 \uc704\uce58\ub294 \uc791\uc5c5\uae30 \ud6c4\ubc29 \uc791\uc5c5\uae30\ub97c \uc911\uc2ec\uc73c\ub85c \uc88c\uc6b0 2\uac1c, \ubbf8\ub95c \uc911 \uc2ec\uac04 \uac70\ub9ac\uac00 1400 mm\uac00 \ub418\ub3c4\ub85d \ubd80\ucc29\ud558\uc600\ub2e4.\n\ub098. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc131\ub2a5\uc2e4\ud5d8\n1) \uc2e4\ud5d8\ud3ec\uc7a5 \ubc0f \uc7ac\ub8cc\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc758 \uc2e4\ud5d8 \uc911 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc5d0 \ub530\ub978 \ud30c\n\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c\ub9c8\ub294 \uc728\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758 \ud3c9 \uade0 \ud568\uc218\uc728\uc740 83.0%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \uc2e4\ud5d8\ud3ec\uc7a5\uc758 \ud1a0\uc131\uc740 \uc0ac\uc591 \ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 30 cm, \ub450\ub451\ub192 \uc774 25 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4. \uc8fc\ud589\uc18d\ub3c4 \ubc0f \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c \ub9c8\ub294 \uc2e0\ud669\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758\ud3c9\uade0 \ud568\uc218\uc728\uc740 79.1%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \ud1a0\uc131\uc740 \uc0ac\uc9c8\ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 40 cm, \ub450\ub451\ub192\uc774 30 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4.\n2) \uc2e4\ud5d8\ub0b4\uc6a9 \ubc0f \ubc29\ubc95\n\uac00) \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8\n\ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ud30c\uc1c4\uc131\ub2a5\uc758 \ucc28\uc774\ub97c \uc870\uc0ac\ud558\uae30 \uc704\n\ud558\uc5ec \uc2e4\uc2dc\ud55c \uc2e4\ud5d8\uc73c\ub85c \ud2b8\ub799\ud130 \uc5d4\uc9c4 \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uc5d0 \ub530\ub77c \uc8fc \ud589\uc18d\ub3c4, PTO \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uac00 \uc5c6\ub3c4\ub85d \ud2b8\ub799\ud130 \uc5d4\uc9c4\uc18d\ub3c4\ub97c 2000 rpm\uc73c\ub85c \uace0\uc815\ud558\uace0, \uc8fc\ud589 \ubcc0\uc18d\ub2e8\uc218\ub97c Park and Choi (1995)\uac00 \ubcf4\uace0\ud55c \uc8fc\ud589\uc18d\ub3c4 0.35, 0.46 m/s\uc5d0\uc11c \uc8fc\ud589\uc18d\ub3c4\uac00 \ub0ae \uc744\uc218\ub85d \ub369\uad74 \ud30c\uc1c4\uc728\uc774 \ub192\uc558\uc73c\uba70, \ub18d\uac00\uc5d0\uc11c \uc8fc\ub85c \uc800\uc18d 1, 2\ub2e8 \uc744 \uc0ac\uc6a9\ud558\ub294 \uac83\uc744 \uace0\ub824\ud558\uc5ec \ubcf8 \uc2e4\ud5d8\ub3c4 \uc800\uc18d 1, 2\ub2e8\uc5d0 \ub9de\ucd94\uc5b4 \uc8fc\ud589\uc18d\ub3c4\ub97c \uac01\uac01 0.27, 0.37 m/s\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \ubcc0\uacbd\uc740 \uadf8\ub9bc 6\uc5d0\uc11c" + ] + }, + { + "image_filename": "designv8_17_0000470_onf_eece18_07007.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000470_onf_eece18_07007.pdf-Figure4-1.png", + "caption": "Fig. 4. Variable points of the front (a) and rear (b) suspension.", + "texts": [ + " 2a, for the rear suspension - points 1,2,4,5,9 in Fig. 2b. In fact to find the critical displacements of the suspension points, changes in their coordinates by \u00b1 5 mm along one axis were considered. Changes occur in two directions: Y or Z. The displacement along the longitudinal axis X was not considered due to the small effect on the K&C parameters. Thus, for each point, 5 possible positions are determined: initial, shifted to the left (y-5), shifted to the right (y+5), raised vertically (z + 5), dropped vertically (z-5). In Fig. 4 below are selected suspension points and their displacements are illustrated. Thus, for the front suspension, 125 options for the relative positioning of hardpoints are considered, and for the rear suspension - 3125. As a result, options for changing the position of hardpoints were selected, which led to the K&C parameters exceeding the indicated limits in Table 2. For the front suspension, these are 37 options for changing the position of the points, for the rear suspension - 2641. Critical point distributions were selected according to groups of options that correlate with each other in the direction of the points' movements. Thus, correlations were found between the direction of movement of the suspension points and the deterioration of the K&C parameters. As a result, the following dependences of the deterioration of the K&C parameters on the direction of displacement of the hardpoints were obtained for the front suspension (point numbers are indicated according to Fig. 4): \u2212 simultaneous displacement more than two hardpoints leads to going beyond a large number of K&C parameters specified limits; \u2212 shifting the angle of inclination of the axis in the horizontal plane (1: Y-5; 2: Y + 5) leads to a deterioration in the anti-dive parameter; \u2212 simultaneous horizontal displacement of the lever front point (1: Y-5) and the lever vertical point of the lever (2: Z + 5) leads to a critical change in the bump steer, roll steer, anti-dive parameters; \u2212 simultaneous shift of the front point of the lever vertically (1: Z \u00b1 5) and the rear point of the lever horizontally (2: Y \u00b1 5) leads to a critical change in the bump steer, roll steer, anti-dive, anti-lift parameters" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001203_el-01058504_document-Figure2.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001203_el-01058504_document-Figure2.6-1.png", + "caption": "Figure 2.6 STT switching approach structure.", + "texts": [ + "1 Two channel model to describe giant magnetoresistance (GMR) effect. ..................... 13 Figure 2.2 Magnetic tunnel junction (MTJ) structure .................................................................... 14 Figure 2.3 Schematic illustration of electron tunneling in MTJ .................................................... 16 Figure 2.4 Field-induced magnetic switching (FIMS) approach structure. ................................... 17 Figure 2.5 Thermally assisted switching (TAS) approach structure. ............................................. 17 Figure 2.6 Spin transfer torque (STT) switching approach structure. ............................................ 18 Figure 2.7 Tunnel magnetoresistance (TMR) and current-induced magnetization switching for Ta/CoFeB/MgO structure MTJ with PMA [38] ............................................................................. 21 Figure 2.8 Recent progress of MTJ ................................................................................................ 23 Figure 2.9 Current-induced domain wall (CIDW) in Pt/Co/AlOx nanowire [67] " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000727_com_article_6089.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000727_com_article_6089.pdf-Figure1-1.png", + "caption": "Fig. 1 Use the Slice command to split the 3D entity", + "texts": [ + " Computer graphics data input has many advantages such as simple, easy to use, fast speed, less memory space, strong controllability and expressive force, and is conducive to teachers to operate actively according to the teaching requirements. AutoCAD, UG, Solid Works, CAD, CAXA electronic drawing board are Common software. The biggest advantage of computer graphics is to exhibit complex parts with animation and three-dimensional graph. For example, when explaining expression method, we can use sectional-tangental drawing in AutoCAD to make presentation shown in fig. 1: In Fig.1 we can see the cutting position, the section plane and the take-away part visually. And in this way when we draw the two-dimensional graphics the label of the section plane, profile line position and drawing are all very clear [1] . Engineering graphics knowledge lays the necessary foundation of computer graphics and facilitates students to understand and master in learning drawing software while the introduction of computer graphics solves a lot of tedious work in engineering graphics such as standard parts, the title bar and map calls, so the two are complementary to each other" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002123_le_download_3242_pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002123_le_download_3242_pdf-Figure4-1.png", + "caption": "Fig. 4. Clutch damper disc operation behavior", + "texts": [ + " The importance Corresponding author: M. O. Genc www.etasr.com Genc & Kaya: Vibration Damping Optimization using Simulated Annealing Algorithm for Vehicle \u2026 of the stiffness behavior can be observed on the model analysis of the powertrain system [6]. Damper torque is applied on the clutch disc to get damper torque capacity which has high importance on the powertrain system optimization. Damper torque\u2019s graph indicates an hysteresis, due to the internal friction which has effect on the dampening ability (Figure 3). Figure 4 shows the loading and unloading phases of the clutch damper disc in operational condition. In this study, the clutch disc assembly can be compressed up to 6.5\u00b0 radial travel. III. MODELING OF THE POWERTRAIN SYSTEM The powertrain system model belongs to a specific type of passenger vehicle. Simcenter AMESim was utilized to analyze the model (Figure 5). The metallic spring was selected from the library of AMESim. The stiffness value 16Nm/\u00b0, according to the results of experimental disc measurements, was provided as input to the model interface (Figure 6)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002304__06_rvol23no1p14.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002304__06_rvol23no1p14.pdf-Figure3-1.png", + "caption": "Fig. 3. CDFIM: reference frame and angles.", + "texts": [ + " The negative sequence phase connection does not have real use in industrial applications [8]. The CDFIM dynamic model can be written in a general reference frame (\"g\"). To describe this model, it is necessary to move all space vectors from their own reference frame to a general one. The reference frame for the Power Machine is stationary and the reference frame for the Control Machine is moving in positive direction relative to Power Machine frame with the mechanical rotor speed (\u03c9ep) in electrical radians por second. The reference frame system of CDFIM is shown in Figure 3 [9], where \u03c9epc = (Pp +Pc)\u03c9r and \u03c9ep = Pp\u03c9r. sd gd rd g estator rotor gen\u00e9rico r g r lreferencia lreferencia lreferencia Considering a general reference frame, the CDFIM model is given by [10], [11]: dt The flux linkages in a general reference frame can be expressed as: \u03c8g sp = Lspigsp +Mpigr (11) \u03c8g r = Mpigsp +Lri g r \u2212Mcigsc (12) \u03c8g sc = Lscigsc \u2212Mcigr . (13) The total eletromagnetic torque in the CDFIM shaft produced by both machines is calculated from mepc = mep \u2212mec. (14) Eletr\u00f4n. Pot\u00ean., Campo Grande, v", + " The negative sequence phase connection does not have real use in industrial applications [8]. The CDFIM dynamic model can be written in a general reference frame (\"g\"). To describe this model, it is necessary to move all space vectors from their own reference frame to a general one. The reference frame for the Power Machine is stationary and the reference frame for the Control Machine is moving in positive direction relative to Power Machine frame with the mechanical rotor speed (\u03c9ep) in electrical radians por second. The reference frame system of CDFIM is shown in Figure 3 [9], where \u03c9epc = (Pp +Pc)\u03c9r and \u03c9ep = Pp\u03c9r. sd gd rd sq gq rq g estator rotor gen\u00e9rico r g r lreferencia lreferencia lreferencia gq gd frame reference general g rotor Pstator Cstator spd rd scd epc ep ec epc ep spq rq scq Fig. 3. CDFIM: reference frame and angles. Considering a general reference frame, the CDFIM model is given by [10], [11]: ug sp = Rspigsp + d\u03c8g sp dt + j\u03c9g\u03c8g sp (8) ug r = Rri g r + d\u03c8g r dt + j(\u03c9g \u2212\u03c9ep)\u03c8g r (9) ug sc = Rscigsc + d\u03c8g sc dt + j(\u03c9g \u2212\u03c9epc)\u03c8g sc. (10) The flux linkages in a general reference frame can be expressed as: \u03c8g sp = Lspigsp +Mpigr (11) \u03c8g r = Mpigsp +Lri g r \u2212Mcigsc (12) \u03c8g sc = Lscigsc \u2212Mcigr . (13) The total eletromagnetic torque in the CDFIM shaft produced by both machines is calculated from mepc = mep \u2212mec" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001121_.uk_9034_1_TQE15.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001121_.uk_9034_1_TQE15.pdf-Figure2-1.png", + "caption": "Figure 2: Leakproof probe handle and encapsulated sensing element. This figure defines the quantities z, zm and zo. Asterisks are added to z and zm (i.e. they become z\u2217 and z\u2217m) when they refer to measurements in the reference phantom", + "texts": [ + " The permittivity \u03b5\u2032 and conductivity \u03c3 of phantoms are checked by using a coaxial sensor [7]. The electric field in the phantom decays with distance from the top of the dielectric window. The E-field magnitude E(z) on the centre axis is given by [3] E2(z) = 4PWG ab\u03b4\u03c3 exp ( \u22122z \u03b4 ) , (1) where PWG is the power flowing in the waveguide at the interface between the liquid and the window, ab is the area of the waveguide, \u03b4 is the penetration depth in the phantom liquid, and z is the distance from the sensing element inside the probe to the top of the dielectric window (see Figure 2). The penetration depth can be determined from measurement of decay curves in the waveguide cell, but in the work reported here it is calculated from the conductivity measured by using a coaxial sensor. For propagation in Page 3 of 33 NPL Report TQE 15 Page 4 of 33 NPL Report TQE 15 Page 5 of 33 NPL Report TQE 15 the waveguide cell at frequency f , [5] \u03c9 = 2\u03c0f, \u03b1 = Re {\u221a (\u03c0/a)2 + j\u03c9\u00b5o (\u03c3 + j\u03c9\u03b5o\u03b5\u2032) } , \u03b4 = 1/\u03b1. (2) For propagation in the phantom tank (which can be considered to be an unbounded medium) [8], \u03b5\u2032\u2032 = \u03c3/ (2\u03c0f\u03b5o) , v = \u221a 1 + (\u03b5\u2032\u2032/\u03b5\u2032)2, \u03b1 = \u03c9 \u221a \u03b5o\u03b5\u2032\u00b5o (v \u2212 1) /2, \u03b4 = 1/\u03b1", + " The power level at the coupler output PCO is also recorded as it is used as the reference level for subsequent measurements of E-field in phantoms. It is chosen (by using the VNA\u2019s controls or the setting of the power amplifier that is used to boost the signal) to give acceptable sensitivity while not causing excessive heating in the phantom liquid. Page 7 of 33 NPL Report TQE 15 The separation between the probe handle and the window in the waveguide (zm) is set by the experimenter, but the E-field is measured in the plane of the sensing element (see Figure 2). The offset distance zo must therefore be estimated. One method of estimating zo is to measure the manner (an exponential decay) in which the detected power [E2(zm + zo)] varies with zm. The value of zo can then be obtained by fitting. In the work described, however, zo was determined using data supplied by the manufacturer of the probe and from the measured dimensions of the probe handle. In subsequent measurements of E-field in phantoms, F is taken to apply to all measured electric field values, i", + " PCO in equation (5) is related to the side arm power meter reading by PCO = Pside arm \u00d7 C. (12) Measurements of F for a range of z (on which it is observed to depend \u2014 see Figures 4 and 5) are taken. These are required in the uncertainty evaluation. Traceable measurements of the following quantities are needed: zm The separation (m) between the tip of the probe handle and the window in the waveguide cell. Page 16 of 33 NPL Report TQE 15 zo The offset (m) between the dipole element and the tip of the probe handle (see Figure 2). C The calibration constant of the coupler/side-arm power meters (see Section 4.1). WT The transmission coefficient of the connecting cable and the waveguide cell combined (see equation (5)). It is measured from the cable connection at the coaxial output of the coupler, and the interface between the liquid-filled section and the waveguide matching window (see Section 4.2). Pside arm The reading of the forward power meter (W). This does not vary significantly with z and is taken to be a constant for each calibration in the waveguide cell", + " As F is a scalar quantity, the measured phase for a vector probe is uncalibrated; nevertheless changes in the phases of measured E-field components fields can be measured. The data required is as follows: z\u2217m The separation (m) between the tip of the probe handle and the bottom of the reference phantom tank. An asterisk is added to distinguish it from zm measured in the waveguide cell. Page 17 of 33 NPL Report TQE 15 zo The offset (m) between the dipole element and the tip of the probe handle (see Figure 2). PCO/Pant The ratio of the power flow to the waveguide cell (for determination of F (z) by calibration) and the reference antenna. S21 The measured vector transmission coefficient. F The calibration factor, determined in liquid phantom in the waveguide cell (V/m per S-parameter unit). measured E-fields in the reference phantom The desired outputs from this work are maps of the Ex and Ey vector field E-field components inside the reference phantom. The power source is a reference antenna placed a specified distance below the reference phantom", + " E-field maps are shown in Figure 11 for the ART-250 antenna at 900 MHz, and in Figure 12 for the ART-219 antenna at 2 450 MHz. Since the signal to noise ratio at 5 200 MHz was very poor, satisfactory measurements of the E-field in the reference phantom were not obtainable. This deficiency is a consequence of the short penetration depth (7 mm). The height of the waveguide used at this frequency (WG12) is only a few times greater than the diameter of the probe which will increase the perturbing effect of the probe (Figure 2) on the E-field, which in turn will cause an error in the value of F . It was not possible to quantify this error with the available resources. For these reasons, measurements made with the ART-220 antenna (5200 MHz) are not presented. Scanned measurements on the reference phantom illuminated by each antenna were performed three times to allow the Type A uncertainty evaluation. Tables 10 and 11 show subsets of the data at 900 MHz in locations close to the maximum and minimum of |Ex|. At each (X, Y ) location, the variance of the measurements was determined" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001217_7419931_07372383.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001217_7419931_07372383.pdf-Figure3-1.png", + "caption": "FIGURE 3. Global Cartesian coordinates and local cylindrical coordinates.", + "texts": [ + " \u2022 Haptic rendering, which produces magnetic force against the user magnets under the control of a designed algorithm based on the properties of the model and the simulation results. Having the system structure determined, our main tasks falls into two parts: electromagnet array actuator design and control methods development. In this section, the design concerns and methods of the whole electromagnet array will be introduced. The control methods based on the properties of the actuator model are introduced in Section IV. For the following discussions, two sets of coordinates are used for the overall array and individual element respectively as shown in Fig. 3. The Cartesian coordinates (Ex, Ey, Ez) are used for describing the locations of the elements in the array, and the cylindrical coordinates (Er, E\u03b8, Ez) are used for magnetic field derivations for individual electromagnet. For haptic rendering devices, the repulsive magnetic force generated is the most important criterion when VOLUME 4, 2016 301 making decisions, besides which there is also stiffness which is the rigidity of the virtual object. In the simulation step, magnetic flux density B is solved by FEM simulation", + " The mechanism of the concentrator is that it contributes the current density in the form ofmagnetization currents that flow both within the volume and on the surface of the concentrator. The detailed statement and proof is shown as follows. Theorem 1: Given a cylinder ring uniformly radially magnetized with the north pole pointing to its central axis, the volume magnetization can be replaced by surface current on the top and bottom when calculating the magnetic field. Proof: The equivalent volume and surface currents of a volume magnetization under the cylindrical coordinates is shown in Fig. 3, which are calculated by JVM = \u2207 \u00d7M (Er, E\u03b8, Ez) (1) JSM = M (Er, E\u03b8, Ez)\u00d7 En (2) where JVM is the volumemagnetization current and JSM is the surface magnetization current [27].M (Er, E\u03b8, Ez) is the magnetization vector field expressed in cylindrical coordinate system, and En denotes the unit normal vector to the surface of the magnetized object. \u2207 \u00d7 M (Er, E\u03b8, Ez) is the curl of the vector field, which can be written explicitly in cylindrical coordinate system as \u2207\u00d7M (Er, E\u03b8, Ez) , 1 r ( \u2202Mz \u2202\u03b8 \u2212 \u2202M\u03b8 \u2202z )Er + ( \u2202Mr \u2202z \u2212 \u2202Mz \u2202r )E\u03b8+ 1 r ( \u2202(rM\u03b8 ) \u2202r \u2212 \u2202Mr \u2202\u03b8 )Ez (3) By assuming the magnetization is uniform and radial, the magnetization vector field can be described as M (Er, E\u03b8, Ez) = \u2212McEr (4) whereMc is a positive constant representing the magnitude of the magnetization" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure18-1.png", + "caption": "Figure 18. The maximum stress simulation results for the front body mount are 4.07 MPa.", + "texts": [ + "17 MPa, and 0.00006 mm. Figure 17 shows the simulation results of the maximum stress value on the driver's footrest. 6. Rollbar body mount The rollbar body mount receives a load of 16.8 kg acting in the y-axis direction. A horizontal bar profile is in the direction of the z axis. This part only consists of one rod to support the rollbar body. The results of the simulation obtained are bending moment, maximum stress, and displacement, respectively, the values are 8552.96 N.mm, 4.07 MPa, and 0.041 mm. Figure 18 shows the simulation results of the maximum stress value on the rollbar body mount. 7. Rear body mount The rear body mount receives a load of 68.67 N, which acts in the y-axis direction. This part only consists of one rod to support the rear body. The simulation results obtained are bending moment, maximum stress, and displacement, respectively, the values are 3505.57 N.mm, 1.10 MPa, and 0.0044 mm. Figure 19 shows the simulation results of the maximum stress value on the driver's footrest. 8. Main rod The force on the main rod is caused by the reaction force acting on the seven supporting rods" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure14-1.png", + "caption": "Fig. 14, Model used for Case (d), \u201cRigid Spring\u201d virtual part, bending", + "texts": [ + " Case (d) Rigid Spring Virtual Part, Bending Vibration: Geometrically speaking this is the same problem considered in case (c) except that the \u201cRigid Spring\u201d virtual part is used. In order to use this feature, the transverse stiffness of the \u201cVP\u201d has to be calculated. This is easily estimated from the expression \ud835\udc58\ud835\udc49\ud835\udc43 = 3\ud835\udc38\ud835\udc3c (0.5\ud835\udc3f\ud835\udc49\ud835\udc43) 3 \ud835\udc58\ud835\udc49\ud835\udc43 \ud835\udf03\ud835\udc66 = \ud835\udc38\ud835\udc3c 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 readily available in strength of materials textbooks. The mass is the translational mass of the virtual part as discussed earlier. This can also be seen in Fig. 14. The translational spring stiffness in the \u201cX\u201d direction is calculated as \ud835\udc58\ud835\udc49\ud835\udc43 = 3\ud835\udc38\ud835\udc3c (0.5\ud835\udc3f\ud835\udc49\ud835\udc43) 3 = 3.2\ud835\udc38 + 7 \ud835\udc41/\ud835\udc5a The rotational spring stiffness about the \u201cY\u201d axis is given by \ud835\udc58\ud835\udc49\ud835\udc43 \ud835\udf03\ud835\udc66 = \ud835\udc38\ud835\udc3c 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 = 6.67\ud835\udc38 + 3 \ud835\udc41.\ud835\udc5a/\ud835\udc5f\ud835\udc4e\ud835\udc51 The above values are inputted as shown in Fig. 15. As far as a theoretical solution, it can be found in standard vibration textbooks [9], [10], The first three transverse frequencies are given by: \ud835\udc5b = (\ud835\udefd\ud835\udc5b\ud835\udc3f) 2 2\ud835\udf0b \u221a \ud835\udc38\ud835\udc3c \ud835\udf0c \ud835\udc3f4 Where \ud835\udefd1\ud835\udc3f = 1.875 \ud835\udefd2\ud835\udc3f = 4.694 \ud835\udefd3\ud835\udc3f = 7.855 The length L is the total length, namely \ud835\udc3f = \ud835\udc3f\ud835\udc40\ud835\udc43 + \ud835\udc3f\ud835\udc49\ud835\udc43 = 150 \ud835\udc5a\ud835\udc5a " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003234__download_10867_8614-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003234__download_10867_8614-Figure3-1.png", + "caption": "Fig. 3. Structure of rail and levitation electromagnet", + "texts": [ + "17816/transsyst201844129-137 cities, CRRC ZELC has designed and manufactured version 2.0 commercial maglev train with the speed grade of 160 km/h based on version 1.0 commercial maglev train. As the increase of the speed, the eddy current effect at the end of the train increases heavily. Because the version 2.0 commercial maglev train is still under commissioning, we only get the analysis results of the drop of levitation force when the speed of the train reaches 160 km/h. The structure of rail and levitation electromagnet in Changsha is shown in Fig. 3. They both made of steel Q235, with the conductivity of 5\u00d7106 S/m, saturated magnetic density of 1.4 T and the density of 7850 kg/m3. The B-H curve of steel Q235 is shown in Fig. 4. 133 \u0422\u0420\u0410\u041d\u0421\u041f\u041e\u0420\u0422\u041d\u042b\u0415 \u0421\u0418\u0421\u0422\u0415\u041c\u042b \u0418 \u0422\u0415\u0425\u041d\u041e\u041b\u041e\u0413\u0418\u0418 TRANSPORTATION SYSTEMS AND TECHNOLOGY \u041e\u0420\u0418\u0413\u0418\u041d\u0410\u041b\u042c\u041d\u042b\u0415 \u0421\u0422\u0410\u0422\u042c\u0418 ORIGINAL STUDIES Received: 20.10.2018. Revised: 16.11.2018. Accepted: 17.12.2018. This article is available under license Transportation Systems and Technology. 2018;4(4):129-137 doi: 10.17816/transsyst201844129-137 Combining the above structure and material properties, we use the threedimensional electromagnetic field finite element analysis to shows that the levitation force of the forefront electromagnet drops by nearly 40 % at a speed of 160 km/h, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.11-1.png", + "caption": "Figure 10.11: Structural failure criterion at the optimum (with tank weight, 2.4 m3 fuel volume)", + "texts": [ + " While the OML only changes subtly at the lower trailing edge, the changes allow the tanks to become much longer and narrower, reducing hoop stress and tank weight. This is a complex tradeoff between the structural weight of a component and the structural weight and drag at the airplane level. It is a good illustration of MDO\u2019s potential to find non-obvious solutions in airplane trade studies rapidly. Figure 10.10 shows the structural sizing variables for this case. Some of the structural zones are minimum gauged, such as the ribs and some spar web zones. Figure 10.11 shows the structural 2https://gist.github.com/bbrelje/b599102f2d83749df681dd5c2c0865e1 3https://gist.github.com/bbrelje/947ef6ff401a201812fde465518b74ff 223 failure criterion at the 2.5 g maneuver case. We can see that the optimizer has removed material almost everywhere until most of the wingbox is nearly at failure at ultimate load (2.5 g plus 1.5 safety factor). 224 225 In the previous example, I relied on a composite objective function in the absence of an airplane-level performance model and assumed a given fuel volume" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002757_f_version_1651162875-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002757_f_version_1651162875-Figure2-1.png", + "caption": "Figure 2. A representation of the bicycle model in 2D space for deriving the equations of motion. The vehicle schematic shows the inertial frame (O), the center of gravity (CoG) frame (C) attached to the center of gravity of the vehicle. The forces Frx and Fry on the rear wheel are the longitudinal and lateral force, respectively. The front wheel forces Ff long and Ff lat are the longitudinal and lateral forces, respectively, the forces Ff x and Ff y are the result of these forces in frame C. The lengths l f and lr are the distance from CoG to the front wheel and rear wheel, respectively.", + "texts": [ + " The rough position of the vehicle can be obtained using the scan end-point matching algorithm and orientation from IMU. Figure 1 shows the high-level scheme of the proposed pipeline which includes a model-predictive controller (MPC) in the loop. We do not provide further details about the MPC algorithm, as this is not the focus of this work. We assume that the control of the car and the track plan can be obtained. As the estimator is based on a system model, the dynamics of the system are derived using the bicycle model [17] representation shown in Figure 2. The vehicle model includes kinematic as well as dynamic equations, represented by: v\u0307x = 1 m (Frx \u2212 Ff lat sin(\u03b4) + mvy\u03c9) v\u0307y = 1 m (Ff lat cos(\u03b4) + Fry \u2212mvx\u03c9) \u03c9\u0307 = 1 Iz (l f Ff lat cos(\u03b4)\u2212 lrFry) (1) X\u0307 = vxcos(\u03b8)\u2212 vysin(\u03b8) Y\u0307 = vxsin(\u03b8) + vycos(\u03b8) \u03b8\u0307 = \u03c9 where vx, vy, \u03c9 are the longitudinal, lateral, and angular velocity of the vehicle, respectively. X, Y, \u03b8 are the global pose of the vehicle in a fixed inertial frame. The available sensors are able to measure, directly or indirectly, [vx, \u03c9, X, Y, \u03b8] states, with some errors" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004698_e_download_3551_3389-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004698_e_download_3551_3389-Figure4-1.png", + "caption": "Fig. 4. Sub-networks for different networks", + "texts": [ + " In this paper, we have targeted FPGAs with 6-input LUTs as basic logic elements. Thus the mapping should ensure a proper utilization of this basic element. For efficient mapping each network in figure 3 is divided into sub-networks. This is again done by traversing through the network and dividing it at output nodes. Thus the network of figure 3(a) is divided into three sub-networks corresponding to outputs X0, X1 and Z0. Similarly networks in 3(b), 3(c) and 3(d) are divided into different sub-network as per their fan-out. This is shown in figure 4. A straight forward approach to mapping would be to assign the logic implemented by each sub-network to a separate LUT. This, however, leads to under utilization of the resources. For efficient mapping, therefore, the entire assembly of subnetworks is re-structured. This requires transferring some subnetworks from their original networks to sub-networks that belong to different networks. For example sub-network X0 that originally belonged to 4(a) is now transferred to 4(b) and included with sub-networks X2 and Z1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure13-1.png", + "caption": "Figure 13. The early Elka1Q fuselage mainly was made of carbon-fibre elements, but it was still not rigid enough.", + "texts": [], + "surrounding_texts": [ + "The overall shape of the drone (as seen in Figures 8 and 9) is a compromise among the general assumptions (described in Section 1), size and weight of significant components (such as the battery pack), and smart usage of available materials. 2.3.1. Wings Typically, drone arms are made of carbon-fibre tubes because they are very stiff and lightweight at the same time. However, such a single tube could have a too big a diameter to fit into the drone\u2019s wing. Instead, we decided to use double 6 \u00d7 2 mm carbon-fibre flat bars as wing spars. Additionally, the space between them forms a convenient tunnel for electric wires. The wings are built of two matching full-balsa wood elements: a bottom and a top half, both CNC 3D milled and glued together. The leading and trailing edges of a wing are usually prone to accidental damage (especially a very thin trailing edge); therefore, both edges are reinforced with carbon-fibre 4\u00d7 1 mm flat bars. The carbon-fibre wing spars at the wingtips support the main motor holders (CNC milled from a 3mm-thick aluminium sheet). The two elements of the holders are screwed together to catch protruding wing spars tightly. Finally, the surface of the wing is covered by Oracover [32] film. The wing construction proves to be light and very durable. We could say it is a perfect balance between stiffness and elasticity. Initially, we chose a wing profile (an airfoil) optimized for high-speed flight: the P-51D tip (BL215) airfoil (see Figure 10). Generally speaking, high-speed airfoils have low drag, but, on the other hand, have a low lift coefficient, which results in a high stall speed, and that means the plane has to maintain high enough speed to stay airborne in a level flight. That should not be an issue if the pusher motor can accelerate the drone to that speed. Due to safety reasons, we decided to modify the original wings\u2014we made them much thicker (see Figure 11). Such a thick airfoil (thickness increased from 12% to 25% of the airfoil chord) gives us a much higher lift coefficient (resulting in a lower stall speed) at the cost of lowering the top speed. Nevertheless, lower stall speed means we could perform the in-flight experiments of switching between quadcopter and plane mode at lower (i.e., safer) speed, and we could do that in a less spacious airfield. The wing configuration used in the drone is called a \u201ctandem-wing\u201d or sometimes a \u201clifting-tail plane\u201d. Those names refer to the fact that the aft wing is not just a horizontal stabilizer, like in a classic \u201ctailplane\u201d configuration, but it contributes to the total lift force produced by the plane. It is a rare configuration due to possible stability and controllability issues [34,35]. Sometimes, quite the opposite statements can be found\u2014tandem-wing planes are easier to pilot because of safer stall behaviour [36]. However, there were at least a few successful tandem-wing planes, e.g., Quickie designed by Elbert Leander \u201cBurt\u201d Rutan (and later QAC Quickie Q2) [36,37] and the Proteus [38] built by Scaled Composites (Rutan\u2019s company). Another famous tandem-wing plane is the \u201cFlying Flea\u201d (French name: \u201cPou du Ciel\u201d), designed by Henri Mignet in 1933. A thorough study of many more historical and modern tandem-wing planes and UAVs, as well as their aerodynamic and stability studies, can be found in [34]. A wing that produces lift force also generates a downwash, i.e., the airflow direction behind the trailing edge of the wing is deflected down by the aerodynamic action of the wing. That phenomenon changes the effective Angle of Attack (AoA) of the rear wing in the tandem-wing configuration. Most tandem-wing planes have the front wing mounted lower than the rear wing to minimize the downwash effect of the front wing [34,35]. Additionally, it is recommended to set a higher AoA of the front wing than the aft wing\u2014such a wing setup affects the stall behaviour of the tandem-wing plane. The front wing with a higher AoA will stall first while the aft wing still produces lift force\u2014that situation will cause the plane to pitch down, increase the speed, and ultimately, end the front wing\u2019s stall (bring back its lift force) [36]. Following the suggestions, the front wing of the Elka1Q drone was mounted at ca. 4\u25e6 AoA and the aft wing at ca. 2\u25e6 AoA. Finally, there is at least one more critical aspect of every aircraft having wings: Centre of Gravity (CG, CoG). It is crucial to keep the longitudinal stability of an aircraft. We used a CG calculator from the eCalc toolset [30]. The results of the calculation are presented in Figure 12. 2.3.2. Fuselage The final fuselage design was based on a rigid PVC tube (100 mm diameter and 1 mm wall) and a lighter, but still solid plywood structure (Figures 15\u201317). The PVC tube acts similarly to a monocoque structure, eliminating the twisting about the longitudinal axis. The landing gear is non-retractable\u2014we made four fixed legs of 3 mm spring steel wire supported by pinewood blocks at the bottom of the fuselage. The overall structure of the wings and the fuselage proved to be very rigid and robust, surviving a few serious crash landings. The most significant disadvantage of such a compact construction is complicated maintenance of internal components, e.g., access to electronic boards, wires, and connectors." + ] + }, + { + "image_filename": "designv8_17_0001274_le_1693_context_etdr-FigureC.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001274_le_1693_context_etdr-FigureC.1-1.png", + "caption": "Figure C.1: Representation of reciprocal lattice in terms of the axes B1B2 and B3. The standard lattice point, HoKoLo, is represented by R and the shifted point represented by R\u2019. The B2 axis is pointing into the paper.8 The distribution of power in real space is given by the powder pattern theorem, calculated as Equation C.2. Using equation C.1, we can express the \ud835\udc51\u210e3 term in terms of the reciprocal space shift, thus giving the adjusted power distribution in real space in Equation C.3.", + "texts": [ + "17 can be combined to further simplify to: I = \u03c82 \u2211 NmZ|m| [cos 2\u03c0m ( h3\u2212Lo 3 \u2212 (\u00b1) \u221a3\u03b1 4\u03c0 ) \u00b1 \u03b2 \u221a3 sin 2\u03c0 |m| ( h3\u2212Lo 3 \u2212 (\u00b1) \u221a3\u03b1 4\u03c0 )]m (B.18) Equation B.18 is the final form of the intensity distribution in reciprocal space, as a function of the continuous variables, h1h2h3. 64 Appendix C: Real Space Power Distribution and Stacking Fault Probability To interpret measured diffraction powder patterns, the reciprocal intensity distribution must be translated to real space (2\u03b8) with an integration over all the crystallites in the sample. This will give the power distribution in real space. Figure C.1 illustrates the variation in reciprocal space that corresponds to a change in the diffraction vector, which can be finally translated to real space. The intensity in reciprocal space is spread around the point R (HoKoLo), in Figure C.1, where it is spread parallel on the B3 axis due to the faulting because the Fourier coefficients Z|m| increase with increased faulting levels. It also spreads parallel along the B1 and B2 axes dependent on the layer dimensions, N1A1 and N2A2, however taking the assumption that the faulting is throughout the layer in the crystallite and that the crystallites are of sufficient size that size broadening (the spread of intensity parallel to the B1 and B2 axes) is not significant. Therefore, the intensity can be assumed to only spread parallel along the B3 axis", + "27 and the constant term in front of the integrals in Equation 1.31. To remove the M term in the constant (number of crystallites), we can let the N3 term be the average number of (111) layers in a single crystallite and calculate the total number of atoms in the entire sample from \ud835\udc41\ud835\udc61 = \ud835\udc40\ud835\udc411\ud835\udc412\ud835\udc413. Therefore, the unit cell volume (\u03c5a) must be converted to the volume per atom (layer) as \u03c5a/3. This constant now becomes: G = NoR\u03bbIef2 16\u03c0vo sin2 \u03b8 (C.6) In addition to this constant, an additional translation is derived from Figure C.1 to combine the affected and unaffected components into one power distribution function. If we assume that the line RO is along the b3 axis in an orthorhombic unit cell, then the diffraction vector can also be represented in terms of a new continuous variable, h3 \u2032 , along with a new index replacing Lo, l\u2032. Therefore, any (hkl) peak measured from the real sample is related to an equivalent (00l\u2019) reflection in an orthorhombic unit cell. Following the first representation in Equation C.1, it is also represented by the portion in bold: B3\u2206h3 sin \u03d5 = \u2206 ( 2 sin \u03b8 \u03bb ) = (\ud835\udc21\ud835\udfd1 \u2032 \u2212 \ud835\udc25\u2032)\ud835\udc1b\ud835\udfd1 \u2032 (C", + " To calculate the real-space 2\u03b8 shift that occurs from the presence of stacking faults, the relation established with Equation C.1 is used to represent the change in diffraction vector in terms of the delta term given in Equation C.21. \u2206 ( 2 sin \u03b8 \u03bb ) = (h3 \u2032 \u2212 l\u2032)b3 \u2032 \u2192 \u22062\ud835\udf03 = \ud835\udf06b3 \u2032 \ud835\udeff cos \ud835\udf03 (C.22) Inserting the displacement term (Equation C.21) we obtain a general form for the peak shift as a function of stacking fault probability \u22062\u03b8 = [ 3\u221a3\u03b1B3\u03bb 4\u03c0(u+a) cos \u03b8 ] \u2211 (\u00b1)a sin \u03d5 (C.23) 70 Following Figure C.1, the reciprocal space terms can be related to the real space lattice dimensions and indices. The sin \u03d5 term can be directly related to the interplanar spacing, d, of the material with sin \u03d5 = B3Lod. This modified equation is now equal to: \u22062\u03b8 = [ 3\u221a3\u03b1\ud835\udc353 2\u03bbd 4\u03c0(u+a) cos \u03b8 ] \u2211 (\u00b1)a Lo (C.24) With the \ud835\udc353 2 term (reciprocal space vector) being equivalent to Equation C.25, with a being the cubic cell lattice parameter. By also replacing \u03bb with 2dsin\u03b8 (Bragg law) we obtain Equation C.26. \ud835\udc353 2 = 1 \ud835\udc343 2 = 1 3\ud835\udc4e2 (C", + "10) \u2202\u03b2 \u2202\u03b8111 = 11(\u2206(2\u03b8111 CG \u22122\u03b8111 max)\u2212\u2206(2\u03b8200 CG \u22122\u03b8200 max)) sec2 \u03b8111 (11 tan \u03b8111+14.6 tan \u03b8200)2 (A.11) \u2202\u03b2 \u2202\u03b8200 = \u221214.6(\u2206(2\u03b8111 CG \u22122\u03b8111 max)\u2212\u2206(2\u03b8200 CG \u22122\u03b8200 max)) sec2 \u03b8200 (11 tan \u03b8111+14.6 tan \u03b8200)2 (A.12) 77 Appendix F: Copyright Clearance Agreements Copyright agreement for Figure 1.2 in Section 1.1 78 79 80 Copyright agreement for Figure 1.4 in Section 1.2.1 81 82 83 84 85 Copyright agreement for Figure 1.6 in Section 1.2.2 86 87 88 Copyright agreement for Figure A.1 in Appendix A (pg. 53), Figure B.1 in Appendix B (pg. 57) and Figure C.1 in Appendix C (pg. 63)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure15-1.png", + "caption": "Figure 15. The final design of Elka1Q fuselage\u2014a PVC tube with internal plywood structure.", + "texts": [], + "surrounding_texts": [ + "The overall shape of the drone (as seen in Figures 8 and 9) is a compromise among the general assumptions (described in Section 1), size and weight of significant components (such as the battery pack), and smart usage of available materials. 2.3.1. Wings Typically, drone arms are made of carbon-fibre tubes because they are very stiff and lightweight at the same time. However, such a single tube could have a too big a diameter to fit into the drone\u2019s wing. Instead, we decided to use double 6 \u00d7 2 mm carbon-fibre flat bars as wing spars. Additionally, the space between them forms a convenient tunnel for electric wires. The wings are built of two matching full-balsa wood elements: a bottom and a top half, both CNC 3D milled and glued together. The leading and trailing edges of a wing are usually prone to accidental damage (especially a very thin trailing edge); therefore, both edges are reinforced with carbon-fibre 4\u00d7 1 mm flat bars. The carbon-fibre wing spars at the wingtips support the main motor holders (CNC milled from a 3mm-thick aluminium sheet). The two elements of the holders are screwed together to catch protruding wing spars tightly. Finally, the surface of the wing is covered by Oracover [32] film. The wing construction proves to be light and very durable. We could say it is a perfect balance between stiffness and elasticity. Initially, we chose a wing profile (an airfoil) optimized for high-speed flight: the P-51D tip (BL215) airfoil (see Figure 10). Generally speaking, high-speed airfoils have low drag, but, on the other hand, have a low lift coefficient, which results in a high stall speed, and that means the plane has to maintain high enough speed to stay airborne in a level flight. That should not be an issue if the pusher motor can accelerate the drone to that speed. Due to safety reasons, we decided to modify the original wings\u2014we made them much thicker (see Figure 11). Such a thick airfoil (thickness increased from 12% to 25% of the airfoil chord) gives us a much higher lift coefficient (resulting in a lower stall speed) at the cost of lowering the top speed. Nevertheless, lower stall speed means we could perform the in-flight experiments of switching between quadcopter and plane mode at lower (i.e., safer) speed, and we could do that in a less spacious airfield. The wing configuration used in the drone is called a \u201ctandem-wing\u201d or sometimes a \u201clifting-tail plane\u201d. Those names refer to the fact that the aft wing is not just a horizontal stabilizer, like in a classic \u201ctailplane\u201d configuration, but it contributes to the total lift force produced by the plane. It is a rare configuration due to possible stability and controllability issues [34,35]. Sometimes, quite the opposite statements can be found\u2014tandem-wing planes are easier to pilot because of safer stall behaviour [36]. However, there were at least a few successful tandem-wing planes, e.g., Quickie designed by Elbert Leander \u201cBurt\u201d Rutan (and later QAC Quickie Q2) [36,37] and the Proteus [38] built by Scaled Composites (Rutan\u2019s company). Another famous tandem-wing plane is the \u201cFlying Flea\u201d (French name: \u201cPou du Ciel\u201d), designed by Henri Mignet in 1933. A thorough study of many more historical and modern tandem-wing planes and UAVs, as well as their aerodynamic and stability studies, can be found in [34]. A wing that produces lift force also generates a downwash, i.e., the airflow direction behind the trailing edge of the wing is deflected down by the aerodynamic action of the wing. That phenomenon changes the effective Angle of Attack (AoA) of the rear wing in the tandem-wing configuration. Most tandem-wing planes have the front wing mounted lower than the rear wing to minimize the downwash effect of the front wing [34,35]. Additionally, it is recommended to set a higher AoA of the front wing than the aft wing\u2014such a wing setup affects the stall behaviour of the tandem-wing plane. The front wing with a higher AoA will stall first while the aft wing still produces lift force\u2014that situation will cause the plane to pitch down, increase the speed, and ultimately, end the front wing\u2019s stall (bring back its lift force) [36]. Following the suggestions, the front wing of the Elka1Q drone was mounted at ca. 4\u25e6 AoA and the aft wing at ca. 2\u25e6 AoA. Finally, there is at least one more critical aspect of every aircraft having wings: Centre of Gravity (CG, CoG). It is crucial to keep the longitudinal stability of an aircraft. We used a CG calculator from the eCalc toolset [30]. The results of the calculation are presented in Figure 12. 2.3.2. Fuselage The final fuselage design was based on a rigid PVC tube (100 mm diameter and 1 mm wall) and a lighter, but still solid plywood structure (Figures 15\u201317). The PVC tube acts similarly to a monocoque structure, eliminating the twisting about the longitudinal axis. The landing gear is non-retractable\u2014we made four fixed legs of 3 mm spring steel wire supported by pinewood blocks at the bottom of the fuselage. The overall structure of the wings and the fuselage proved to be very rigid and robust, surviving a few serious crash landings. The most significant disadvantage of such a compact construction is complicated maintenance of internal components, e.g., access to electronic boards, wires, and connectors." + ] + }, + { + "image_filename": "designv8_17_0003539_O200921140047629.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003539_O200921140047629.pdf-Figure1-1.png", + "caption": "Fig. 1. Structure of langevin vibrator and horn.", + "texts": [ + " \ud558\uc9c0\ub9cc \uae30\uc874\uc5d0 \uac1c\ubc1c\ub41c \ub300\ubd80\ubd84\uc758 \uc561\ucd94\uc5d0\uc774\ud130\ub4e4\uc740 \ub2e8\uc77c \uc790\uc720\ub3c4\ub97c \uac00\uc9c0 \uace0 \ub2e4\uc790\uc720\ub3c4\ub97c \uac16\ub294 \uc2dc\uc2a4\ud15c\uc740 \uc5ec\ub7ec \uac1c\uc758 \uc561\ucd94\uc5d0\uc774\ud130\ub97c \uc0ac\uc6a9\ud558\uc5ec\uc57c \ud558\ubbc0\ub85c \uc2dc\uc2a4\ud15c\uc774 \ubcf5\uc7a1\ud574\uc9c0\uace0 \uc81c\uc5b4\uac00 \uc5b4\ub824 \uc6cc\uc9c0\ub294 \ub2e8\uc810\uc744 \uac00\uc9c4\ub2e4[1-4]. \ub530\ub77c\uc11c, \ubcf8 \ub17c\ubb38\uc5d0\uc11c\ub294 \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\ub97c \uc774\uc6a9\ud558\uace0 \ud558\ub098\uc758 \uc561\ucd94\uc5d0\uc774\ud130\ub97c \uc0ac\uc6a9\ud55c \uc804\ubc29\ud5a5\uc131 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \uc6d0\ub9ac, \ubd84\uc11d \ubc0f \ubaa8\ub378\ub9c1 \ub4f1\uc5d0 \ub300\ud574\uc11c \ub2e4\ub8e8\uace0\uc790 \ud55c\ub2e4. 2. \uc6d0\ub9ac\uc640 \uad6c\uc870 \uc120\ud615 \ucd08\uc74c\ud30c \ubaa8\ud130\ub294 \uad74\uace1\ud30c\uc5d0 \uc758\ud574 \ubc1c\uc0dd\ub41c \uc9c4\ud589\ud30c\ub85c \uad6c\ub3d9\ud558\ub294 \ubc29\ubc95\uacfc \uc885\uc9c4\ub3d9\uacfc \ud6a1\uc9c4\ub3d9\uc744 \uc561\ucd94\uc5d0\uc774\ud130\ub97c \uacb0\ud569 \ud558\uc5ec \uc218\uc9c1\uacfc \uc218\ud3c9\uc6b4\ub3d9\uc744 \ubc18\ubcf5\uc801\uc73c\ub85c \ubc1c\uc0dd\uc2dc\ucf1c \uc774\ub3d9\uc790\ub97c \uad6c\ub3d9\ud558\ub294 \uc815\uc7ac\ud30c\ud615 \ubc29\ubc95\uc774 \uc54c\ub824\uc838 \uc788\ub2e4. \ub610\ud55c \ud55c \uc810 \ub610 \ub294 \ub450 \uc810 \uc774\uc0c1\uc774 \uc774\ub3d9\uc790\uc640 \uc811\ucd09\ud558\uace0 \uc788\uace0 \uc811\ucd09\ubd80\uc5d0\uc11c\uc758 \ub2e4\uc591\ud55c \uc9c4\ub3d9\uc744 \ud1b5\ud574 \uc774\ub3d9\uc790\ub97c \uc6c0\uc9c1\uc774\uac8c \ud558\ub294 \ubc29\ubc95\uc73c\ub85c \ub098\ub20c \uc218 \uc788\ub2e4. \uc81c\uc548\ub41c \uc804\ubc29\ud5a5\uc131 \uc120\ud615 \uc555\uc804 \ubaa8\ud130\ub294 \uc774\ub3d9 \uc790\uc640 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \ud55c \ubd80\ubd84\uc774 \uc811\ucd09\uacfc \ub9c8\ucc30\uc744 \ud1b5\ud574 \uc120\ud615 \uc6b4\ub3d9\uc744 \ud558\ub294 \ubaa8\ud130\uc774\uba70 \uc811\ucd09 \ubd80\uc704\uc5d0\uc11c\uc758 \ud0c0\uc6d0 \uc6b4\ub3d9\uc744 \ud568 \uc73c\ub85c\uc368 \uc774\ub3d9\uc790\uac00 \uc120\ud615 \uc6b4\ub3d9\uc744 \uac00\ub2a5\ud558\uac8c \ud55c\ub2e4.[5-9] 2.1. \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790 \uc124\uacc4\ub41c \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\ub294 \ub780\uc96c\ubc18(langevin) \uc9c4\ub3d9\uc790 2 \uac1c\ub97c \ud0c4\uc131\uccb4 \uc0ac\uc774\uc5d0 \ub123\uc5b4 \ubcfc\ud2b8\ub85c \uacb0\ud569\ud55c \uad6c\uc870\ub85c Fig. 1 \uacfc \uac19\uace0 \u03bb /2 \ubaa8\ub4dc\ub85c \ub3d9\uc791\uc744 \ud558\uba74 \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\uc5d0\uc11c \ubc1c\uc0dd\ud558\ub294 \uc885\ubc29\ud5a5 \uc9c4\ub3d9\uc774 \ud63c\uc758 \ub05d\uc5d0\uc11c \uc57d 5~10\ubc30 \ud655\ub300 \ud55c\uad6d\uacfc\ud559\uae30\uc220\uc5f0\uad6c\uc6d0(KIST) *\ud638\uc11c\ub300\ud559\uad50(Hoseo University) **\uace0\ub824\ub300\ud559\uad50(Korea University) ***\uc218\uc6d0\ub300\ud559\uad50(Suwon University) \u2020Corresponding author: sjyoon@kist.re.kr (Received : January 16, 2009, Revised : March 13, 2009 Accepted : March 17, 2009) \uc13c\uc11c\ud559\ud68c\uc9c0 \uc81c18\uad8c \uc81c3\ud638, 2009 \u2212 186 \u2212 \uc815\uc6b0\uc11d\u00b7\uac15\uc885\uc724\u00b7\uae40\uc815\ub3c4\u00b7\ubc31\ub3d9\uc218\u00b7\uc870\ubd09\ud76c\u00b7\uae40\uc601\ud638\u00b7\uc724\uc11d\uc9c4 \ub41c\ub2e4. \ub610\ud55c, \ub780\uc96c\ubc18 \uc9c4\ub3d9\uc790\uc640 \ub3d9\uc77c\ud55c \u03bb /4 \uae38\uc774\uc758 \ud63c\uc744 \uc5f0\uacb0\ud558\uba74 \ud63c\uc758 \uc704, \uc544\ub798 \ub2e8\uba74\uc801\uc758 \ube44\uc728\ub9cc\ud07c \uc9c4\ub3d9\uc774 \uc99d \ud3ed\ub418\uba70 \ub3d9\uc791 \uc8fc\ud30c\uc218\uac00 1/2\ub85c \uac10\uc18c\ud558\uace0 \ubc1c\uc0dd\ub825\uc774 \uc99d\uac00 \ud558\uba70 \uc9c4\ub3d9\uc18d\ub3c4\ub294 \uac10\uc18c\ub418\ub294 \ud2b9\uc9d5\uc744 \uac16\ub294\ub2e4. \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\uc758 \ubcc0\uc704\ub97c \uc54c\uae30 \uc704\ud574\uc11c\ub294 \uc5ed\uacc4\uc218 A, \uae30\uacc4 \uc784\ud53c\ub358\uc2a4 Z, \ub4f1\uac00 \uae30\uacc4\uc800\ud56d r \ub4f1\uc744 \uc774\uc6a9\ud558\uc5ec \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\uc758 \uae30\uacc4\uc801 \uc9c4\ub3d9\uc744 \ud655\uc778\ud574\uc57c \ud55c\ub2e4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure6-1.png", + "caption": "Figure 6. Three-dimensional (3-D) finite-element analysis (FEA) model of the CS-PMSM thermal field.", + "texts": [ + " Although radiation heat transfer is always happening, especially when the rotor speed is very low or zero [44], radiation heat transfer is normally neglected when the forced convection is mainly responsible of the motor cooling [45,46]. Hence the following assumptions in the FEA calculation are given by: (1) Only the convective and conduction heat transfer are considered; (2) The heat sources are uniformly distributed on the corresponding regions of the CS-PMSM. According to the symmetrical characteristic of the CS-PMSM structure and cooling system in circumferential direction, a 3-D FEA model with half of the CS-PMSM is built to analyze the thermal field, as shown in Figure 6. The 3-D FEA model of the cooling water channel in the stator is shown in Figure 7. In the machine, modeling of the windings and air gap is very important for the thermal field analysis. Hence the model of the windings and air gap will be illustrated in the following text. In 3-D modeling process of the CS-PMSM, to build an accurate model of the windings is quite difficult. This is mainly because the conductors in each coil are randomly distributed inside the slots. The random distribution of the conductors in the slots has a certain influence on the maximum temperature of the windings [47]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003997_e_download_7367_3540-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003997_e_download_7367_3540-Figure7-1.png", + "caption": "Figure 7. Axis load configuration for truck vehicle types (S=single, D=double) [15][16]", + "texts": [ + "C + W tan \u03c6 (5) Where C is the soil cohesion (kg/cm2), b is the width of the track (cm), l is the length of the track in contact with the soil (cm) as in Figure 6, and \u03c6 is the internal friction angle. The designed tools had to increase the tractor wheels in wet soil condition, especially clay, were carried out by increasing the area of the tangents of the wheels to the ground. As the value of b and l increases, the value of traction automatically increases. The situation is done by using a steel wheel or a cage wheel [14], as shown in Figure 6. For CDD type trucks or 1.2 L (medium) trucks has load distribution on the front wheels (34%) and rear wheels (66%), as shown in Figure 7. Soil cohesion value (C) and soil internal friction angle (\u03c6) Oil palm transport trucks experience such skidding because they have to cross over the wet ground. The slippage occurs due to the soil undergoes such deformation or changes in shape due to the internal tensile forces between particles or soil cohesion that were not strong enough to withstand the shear loads when the movement of truck wheels. On clay soil surfaces and wet clay, soils tend to be slippery and cause the wheel to slip. It is because the soil cohesion value decreases due to the influence of the water mixture", + " Soil roads in oil palm plantations generally experience compaction both when first opened with compaction by heavy equipment and compaction every day when crossed by oil palm transport trucks in the dry season. D.T.Wahyudi and D.S.Khaerudini, Design of Anti-Slip Shoes for 12 Ton Palm Oil Truck \u2026 219 It was simulated a colt diesel truck carrying palm oil with a total load or maximum load of 12 tons or 12000 kg, the truck wheels diameter of 81.6 cm with radius r (0.5 d) of 39.5 cm. Referring to Figure 7, the maximum load on the rear truck wheels to one side or W = 0.66 x 0.5 x 12000 is 3960 kg. The value of rolling resistance coefficient (CR) is shown in Table 1, with a truck wheel diameter of 81.6 cm and running on wet clay mud obtained CR values in the range of 0.15. From Equation (4), rolling resistance R = CR. W = 0.15 x 3960 = 594 kg. So that the truck does not slip by the provisions of Equation (3), the soil reaction force Fh \u2265 R means that the ground reaction force must be higher than 594 kg" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure12.25-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure12.25-1.png", + "caption": "Fig. 12.25. Changes of the structure of vibration during propagation, path No. IV, axis \u2013 longitudinal", + "texts": [], + "surrounding_texts": [ + "142 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260" + ] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure87-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure87-1.png", + "caption": "Figure 87. Partition creation screen (for side plate)", + "texts": [], + "surrounding_texts": [ + "1 = variable 1 2 = variable 2 3 = variable 3 br = bearing comp = compressive extes = extensometer i = at ith data point long = longitudinal direction max = maximum xxii min = minimum pin = pin location s = symmetric spec = specimen ten = tensile trans = transverse direction ult = ultimate x = x-direction xx = in the axial direction for the +/-45\u00b0 shear tensile test y = y-direction xy = xy-direction (plane) 1 CHAPTER 1: INTRODUCTION In this chapter, previous and current thesis work is introduced. Section 1.1 introduces the different two different types of aircraft structures. In Section 1.2, the differences between an adhesively bonded joint and a mechanically fastened joint are explained. In Section 1.3, previous work is mentioned, considerations are made in order to avoid testing parameters, which have already been tested, and the three different failure mechanisms are explained. Section 1.4 explains the thesis goal and the thesis scope. 1.1 Introduction to Conventional & Advanced Composite Structures When you think of an aircraft\u2019s wing, it is composed of multiple panels and not usually made as a single piece. The use of joints becomes essential in an aircraft\u2019s wing (since joints serve to attach multiple structural components together to form one part). Ideally, the designer wants to avoid using them, since they can contribute a significant amount of weight to the overall aircraft\u2019s structure. Current aircraft manufactures are transitioning from a conventional aircraft structure to an advanced composite structure since the advantage of switching to an advanced composite structure is the significant reduction in parts and joints. Composite materials have desirable characteristics such as being: very stiff, extremely strong, and extremely light. For example, the Airbus\u2019 A350 aircraft structure is made up of 53% composite materials [1]. Even though the total amount of joints can be significantly reduced, that does not mean they can be avoided altogether. 2 As composites become more widely used in the Aerospace Industry, there still lies limited research in their ability to perform as joints. Their main flaw is their poor behavior in redistributing stress concentrations. Even though there has been a lot of research in composite joints, not enough advancement has been made compared to its metal counterpart. Metal joints (in particular, Aluminum joints) have been used for years in the Aerospace Industry. Currently, composite joints are overdesigned (made a lot thicker than they need to be) which leads to weight penalties. Design that is more detailed needs to done on composite joints in order to improve its ultimate bearing strength. 1.2 Introduction to Adhesively Bonded Joints & Mechanically Fastened Joints Two types of joints exist: one is the mechanically fastened joint, and the other is the adhesively bonded joint. In Figure 1, one can see an adhesively bonded single shear joint, a mechanically fastened single shear joint and a mechanically fastened double shear joint. The region between the two plates, in the adhesively bonded double shear joint, is the thin layer of structural adhesive used to bond both structural components together. Adhesively bonded joints are typically lighter but are often more difficult to design. No holes need to be made in an adhesively bonded joint. Reduction of holes reduces the amount of stress concentrations. Adhesively bonded joints can be problematic since the surface finish needs to be accounted for to achieve a strong bond between two surfaces. Another issue with adhesively bonded joints is that they cannot be removed as easily as a mechanical joint. 3 Mechanically fastened joints are widely used in the Aerospace Industry since they are more practical in the sense that they can be easily removed if a part needs to be replaced, repaired, or checked. Two types of mechanically fastened joints exist: single shear and double shear. In addition, a mechanically fastened joint can contain many fasteners. Mechanically fastened joints require a hole through both structural components, which creates stress concentrations. Both of the structural assemblies are held together by a bolt, and nut. 4 1.3 Previous Literature on Mechanically Fastened Composite Joints Numerous papers have been made on mechanically fastened composite joints, and in this section, the most important finds will be mentioned. According to Alan Baker[3], for a mechanically fastened double shear joint, load is transferred mainly through compression on the internal face of the fastener holes and as well as on a component of shear on the outer faces of the plate due to friction. Mechanically fastened composite joints can be made very durably but the designer needs to spend a longer time in the design process. According to Okutan [4], problems arise when the designer wants to analyze them since they have an anisotropic and heterogeneous nature. According to Chen [5], the behavior of a composite joint could be influenced by four parameters. The first is the material parameter. The material parameter includes fiber types, form, resin type, fiber orientation, laminate stacking sequence, material cure cycle, etc. The second is the geometric parameter. This includes the specimen width (W) and the hole edge distance (e). These are usually reported as W/D and e/D ratios where D is the diameter of the hole. A huge contributor to the strength of the specimen is the specimen thickness (t). The pitch is the distance between two or more holes in a multiple hole composite joint. The third (also very important) is the fastener parameter. This includes fastener type, fastener size, washer size, hole size, and tolerance. The last is the design parameter. The design parameter includes loading type (tension, compression, fatigue), loading direction, loading speed, hydraulic clamping pressure, joint type (single lap, double lap), environment, etc. 5 The lay-up sequence also played a significant role in the overall strength of the double shear joint, as well. Quinn & Matthews [6] studied in detail the effect of stacking sequences on the pin bearing strength in glass-reinforced plastics. They concluded that placing a 90\u00b0 layer ply on the outer surface of the laminate increased the overall bearing strength. Liu [7] tested different laminate thicknesses by varying the bolt diameter. He concluded that thick laminates with smaller diameter holes and thin laminates with larger diameter holes were a lot weaker than laminates with similar hole and laminate thicknesses. Stockdale & Matthews [8] studied the effects of bolt clamping pressure and found that boltclamping pressure played a huge role in the overall strength of the composite joint. Kim [9] tested to see the effects of temperature and moisture on the strength of graphite-epoxy laminates. From this experiment, the actual stress distribution of the joint is very difficult to find since the region is so small. The use of strain gages is impractical because that region is under a very high stress so any kind of strain gage applied would crush because of the force. That is why numerous researchers have been working on methods of modeling composite joints with the help of various finite element programs. The load capacity of a laminate is severely degraded due to the effects of hole clearance and friction. Hyer & Klang [10] investigated this phenomenon with a pin-loaded orthotropic plate. Pierron [11] used Abaqus to calculate the stress distribution around the hole of a woven composite joint. Most finite element modeling was done using 2D shell elements and recently there has been an increased amount of 3D modeling of composite joints. Previous researchers mention that the joint strength depends mainly on the failure criterion. 6 Only a small section of the bearing stress vs. bearing strain curve is linear, and then after, it becomes nonlinear. Stress concentrations cause crushing in a small section of the geometry, making it a very difficult nonlinear problem. Chang [12] created a 2D finite element model and assumed a frictionless contact with a rigid pin and a cosine normal load distribution in the pin-hole boundary. Another difficulty in modeling the composite joint requires the user to combine the failure criteria with a property degradation model. As the composite takes more load, the actual material properties are degrading over time, which would mean the modulus is decreased after each new load is applied. Lessard [2] used a 2D linear model along with a non-linear model to predict the strength of the composite joint. There are five different kinds of failure, which can occur in a laminate: matrix tensile, compressive failure, fiber/matrix shearing, fiber tensile, and fiber compressive failure. The Hashin failure criterion is an important criterion used to characterize failure within a laminate. 1.3.1 Previous Literature on Loading Rate Effects on Mechanically Fastened Composite Joints In flight, the aircraft might experience various dynamic loading conditions, so not only do composites need to be tested in quasi-static loading case, but also in a dynamic load case. Metals are not as load rate dependent as composite materials. Ger [13] tested a number of carbon and carbon fiber glass hybrid composites at dynamic loading rates of 6 to 7 m/s. The double shear joint configuration carried more load at high loading rates. It was also noted that for all joint configurations the stiffness of the joint increased significantly with 7 loading rate. In addition, what was noted was that the total energy absorption of the joint decreased significantly in the dynamic tests. Contradictory to Ger [13], Li [14] tested different types of joint configurations subject to a bearing load and found that energy absorption increased. Li [14] tested at higher rates of 4-8 m/s and found this interesting trend. The dynamic behavior of composite joints is much more complicated than its behavior for the quasi-static condition due to the involvement of strain rate and inertial effects. Li [14] concluded that crashworthiness design of tested composite joints could be based on their tensile strength design. Ger [13] mentioned there must be a significant safety factor applied to take into account bearing strength variations with loading rate. The failure modes might also be affected due to an increased loading rate. 1.3.2 Types of Failure in Mechanically Fastened Composite Joints According to Larry Lessard [2], it has been observed experimentally that mechanically fastened composite joints fail under three basic mechanisms: net-tension, shear-out, and bearing (in addition, combinations of these mechanisms are often given separate names). Typical damage mechanism is shown below in Figure 2. Looking at previous work, a net-tension and a shear-out failure are more catastrophic than a bearing failure. The best way to see if a bearing failure has occurred is to look at the bearing stress vs. bearing strain plot. Once the stress gets to its peak value and suddenly drops off to zero, then one can conclude it was a shear-out or a net-tension failure. If after the ultimate bearing stress, the specimen continues to carry load but deforms as a result, this means that the joint was designed very safely. According to Okutan [4], the optimum orientation for a bearing type of failure is a quasi-isotropic laminate orientation. A quasi-isotropic laminate 8 orientation means the laminate has the isotropic properties in plane. According to USNA [15], a quasi-isotropic part has either randomly oriented fiber in all directions, or has fibers oriented such that equal strength is developed all around the plane of the part. The geometry of a mechanically fastened composite joint is quite complex since it can affect the failure mode of the double shear joint specimen. Kretsis [16] & Matthews [16] tested fiber glass and carbon fiber reinforced plastics and found that the width(W), end distance(e), diameter of hole(D), and laminate thickness(h) all contribute to the overall mechanically fastened double shear joint strength. The most interesting aspect is that as the width of the specimen decreases to a specific amount, the mode of failure changes from bearing to net-tension. The W/D (width to hole diameter ratio of the composite double shear joint specimen) must be at least 5 order to avoid the net tensile type failure. Another interesting thing to note is when the end distance of the hole is a certain distance from the edge of the plate, the failure turned from bearing to shear-out (where shear-out is considered a special case of bearing failure). 9 1.4 Thesis Goals & Scope In the preceding sections of this thesis paper, the word double shear specimen will be used to represent one test specimen with a mechanically fastened double shear joint configuration. The goal of the thesis is to determine how the strength of a composite double shear joint is affected by two different cure cycles and five different loading rates. The composite joint will be tested in the double shear case and the laminate orientation was decided to be a quasi-isotropic laminate (based upon based on Yeole\u2019s double shear experimental results [17]). Yeole [17] tested three different laminate orientations in his thesis, and concluded that a quasi-isotopic laminate took the highest stress. Yeole [17] also mentioned that the testing of composite materials at fast loading rates could be an interesting topic to explore. ASTM 5961[18], which is the ASTM for bearing response of composite materials, required an extensometer to measure the relative pin displacement since using crosshead displacement is not an accurate method. A fixture was designed and manufactured in order to accommodate an extensometer. Finally, the numerical model was made to validate only the linear elastic portion of the experimental results. There are seven chapters in this thesis. Chapter 1, the introduction, includes a brief introduction to: composite materials, the difference between adhesively bonded joints and mechanically fastened composite joints, and the loading rate effects on mechanically fastened composite double shear joint bearing strengths. It also includes a brief literature review, the statement of the problem and the objective and organization of thesis. Chapter 2 focuses on manufacturing of the double shear specimens and the tensile specimens. Chapter 3 focuses on the experimental material testing 10 procedure conducted on the MTM49 Unidirectional Carbon Fiber pre-preg. It also explains the double shear fixture used for the testing. Chapter 4 focuses on the equations used in the experimental and theoretical calculations. Chapter 5 introduces the experimental result validation and then discusses the experimental results. Chapter 6 introduces: the numerical model, which was created using Abaqus 6.14 software, the convergence plot, and lastly, what, influences the numerical results. Chapter 7 is where the experimental results are compared to the numerical finite element results. Lastly, Chapter 8 is where the conclusions are drawn and different recommendations are made for the future work. In the reference section, one can find most of the related topics in the form of theses, books, reports and even papers published in numerous journals. In the appendix section, one find: drawings of the fixture, a tutorial on setting up the Bluehill2 double shear test method, a tutorial on finding the unknown engineering constants with the Autodesk software, a tutorial on outputting the force vs. hole deformation in Abaqus, and a tutorial on the composite double shear specimen Abaqus model. 11 CHAPTER 2: MANUFACTURING & PREPARING OF THE SPECIMENS This chapter will introduce the type of specimens that were manufactured and tested in the Instron machine along with their dimensions. All the dimensions were based on published ASTM test standards. ASTM is an international standards organization, which develops and publishes voluntary consensus technical standards for a wide range of materials, products, systems and services. 2.1 Tensile Specimen & Double Shear Specimen Dimensions The dimensions for the 0\u00b0 tensile specimens and the 90\u00b0 tensile specimens were found in ASTM D3039 [19] Standard test method for tensile properties of fiber-resin composites. The dimensions used for the shear modulus +/- 45\u00b0 were found in ASTM D3518 [20]. Below in Figure 3, one can see all of the tensile specimen dimensions for each specific fiber orientation angle. Figure 4 shows a drawing of all four different fiber orientation tensile specimens. The +/- 45\u00b0 shear specimens and the quasi-isotropic laminate specimens had the same dimensions. Figure 5 shows the dimensions, based on ASTM D5961 [18], of the composite double shear specimens. The quasiisotropic tensile specimens were tested to see how the theoretical material properties matched. 12 13 2.2 Manufacturing Process In the Cal Poly\u2019s Aerospace Engineering Composites Lab, there are two ways to manufacture a composite. One can use pre-preg material or apply a wet layup process. Pre-preg material is a lot easier to use since it already has the resin infused inside the material. In order to preserve the resin in the pre-preg material, it needed to be stored in a freezer at low temperatures. Once the pre-preg material is thawed, then the user is able to apply it to a mold or create a plate out of it. The second way, the wet-layup process, consisted of having the fibers in their pure form, which usually come in a roll, and having a two-part epoxy. Once the fibers were cut out from the roll, the two-part epoxy is mixed with the correct ratio and then applied to the dry fibers. The part is then sealed, with a vacuum bag (where all the air is removed from the part). Then the cure cycle of the 14 resin is applied to the vacuum-bagged part. All of the tensile and double shear specimens were made on the heat press. When making a composite plate in the heat press, the user needed to sandwich the laminate between two nonporous sheets and two 0.25 in. thick Steel plates. Figure 6 shows how the heat press cure process was set-up. The non-porous sheets served to prevent the resin from sticking to the steel plates. The composite plate, the steel plates and the non-porous sheets were placed inside the heat press and then the cure cycle was programmed. Once cured, the composite plate was cut into various size specimens. 2.2.1 Double Shear Specimens All the composite double shear specimens were made with the quasi-isotropic laminate orientation. The quasi-isotropic laminate orientation, [0 0 +45 -45 +45 -45 90 90]s, is short hand for [0 0 +45 -45 +45 -45 90 90//90 90 -45 +45 -45 +45 0 0]. The subscript s means that the laminate 15 is symmetrical about the last ply (which in this case is a 90\u02da ply). The alternate cure cycle was the Cytec\u2019s MTM 49 cure cycle and the datasheet cure cycle was the Umeco\u2019s MTM 49 cure cycle.. The material was first thawed since according to the Umeco\u2019s [22] MTM 49 datasheet, if the roll is open to the environment, condensation will occur on the pre-preg material, which will degrade the quality and the aesthetic look of the material. Sixteen 12 in. by 12 in. plies were cut out and orientated in the quasi-isotropic laminate orientation of [0 0 +45 -45 +45 -45 90 90]s. All the respective angles within each ply of the laminate were carefully kept within \u00b1 1\u00b0. Shown in Figure 7, a protractor was used to make sure each ply in the laminate was within \u00b1 1\u00b0. Once all the plies were stacked very carefully (in order to prevent air pockets from occurring within the laminate), the cure cycle was programmed into the heat press. Air pockets create areas where delamination can occur, which leads to the formation of cracks. Cracks can severely weaken composite structures. The second step consisted of programming the cure cycle into the heat press. Shown in Figure 16 8, is Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22]. Two different cure cycles were tested to see its effects on the material\u2019s double shear bearing stress. Increasing the dwell temperature from 248\u00b0F to 275\u00b0F and increasing the dwell time from 60 minutes to 90 minutes both affect the mechanical characteristics of the resin. The dwell temperature is the temperature which is held constant in the cure process (for this material, it occurs after the temperature ramp up stage). The dwell time is the duration of the dwell temperature stage. Each different carbon fiber matrix system will have its own recommended cure cycle printed in its specific datasheet. In the experimental section, one can see the difference in mechanical properties of the material based on the two different cure cycles. The first cure cycle was Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22] (also known as the alternate cure cycle). The heat press was adjusted to the specific cure cycle. First, the cure cycle temperature ramped up from room temperature of 77\u00b0F to 275\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 275\u00b0F for 90 minutes. After the 90 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. A uniform pressure of 2 psi was applied on top and bottom of the plate. 17 The second cure cycle was Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [21], shown in Figure 9 (also known as the datasheet cure cycle). The heat press was adjusted to the specific cure cycle. First, the press ramped the temperature up from the room temperature to 248\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 248\u00b0F for 60 minutes. After the 60 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. The pressure was held constant between both cure cycles. 18 The third step consisted of preparation of the test specimens. Once the composite laminate finished curing, the material was removed from the press and was cut with a tile saw, which had a diamond-coated blade. The tile saw had an adjustable clamp that helped keep the cuts within 0.1 of an inch. Figure 10 shows the tile saw used to cut the specimens. A straight cut was made on the composite laminate, in order to clean up the edge of the plate. Next, the top side of the plate was aligned to the straight section of the small tile saw. The cuts were made carefully in order to keep a 90\u00b0 angle on the side of the cured laminate. Once all the cuts were made, and the zero direction of the laminate was located accordingly, specimens were cut to the correct width. Based on ASTM D5961 [18], a W/D (specimen width to hole diameter ratio of the composite double shear joint specimen) of 6 and e/D (hole edge distance to diameter of hole ratio) of 3 were used. These geometric conditions guaranteed the double shear composite specimens failed in bearing and not in net-tension or shear-out. Based on these geometric conditions, the specimens needed to be 1.5 in. wide by 5.5 in. in length. The tile saw 19 was used to trim the long 1.5 in. wide specimens to their final length of 5.5 in. A small aluminum block was clamped to the tile saw, which helped minimize variations in the length of all the specimens and allowed multiple specimens to be cut at the same time. After the specimens were cut to their specified length and width, they were grouped into sets of five. A mini microfiber-board fixture was created in order for five holes to be drilled at the same time. The fixture was clamped into the drill press. Five composite double shear specimens were stacked onto the drill fixture and the top left corner of each composite double shear specimen was aligned to the top left corner of the fixture. An Aluminum template was placed on top of the composite double shear specimens and was used to align the 0.25 in. diamond coated end mill bit. Once the composite double shear specimens were aligned accordingly, a small c-clamp was used to constrain the specimens along with the Aluminum template from moving/rotating during the drilling process. In Figure 11, one can see the fixture, the Aluminum template and the end mill bit used for the hole drilling process. 20 Once the holes were created for all the composite double shear specimens, there needed to be a 0.5 in. wide horizontal slit on each face of the composite double shear specimens. A thin Aluminum template was created to assist in locating a specific distance from the hole. This slit needed to be placed accurately within a tolerance of 0.01 in. The template is shown below in Figure 12, and the flat edge of the Aluminum template was used to locate the slit location. The slit needed to be as horizontal as possible and deep enough to catch the moveable knife-edge of the extensometer. 21 Emery cloth helped distribute the high clamping pressure (which is applied by the hydraulic clamps) which occurred at the bottom of the double shear specimen and the emery cloth prevented the composite double shear specimen from slipping during the test. Aluminum tabs were not needed for the double shear test because the specimens failed before reaching 7,000 lbs. The emery cloth works up to a maximum load of 7,000 lbs. The emery cloth was 1.5 in. wide and had a grit level of 120, which is shown in Figure 13. Each specimen only needed emery cloth on one end. Only a 3 in. long piece was needed to cover all of the specimen\u2019s width. A small portion of painters tape served to hold the emery cloth in position. The emery cloth was also reusable; so one piece of emery cloth could be used on two or more specimens. In Figure 13, on the right, shows the ready-to-test composite double shear specimen. 22 2.2.2 Tensile Specimens The same method was applied for the composite tensile specimens, except that these specimens did not have a hole. Stacking the layers needed to be done in a very careful manner in order to prevent misalignment. Once the composite shear modulus specimens and the 90\u00b0 composite tensile specimens were cut to 10 in. by 1 in., then all that was needed was to apply the emery cloth to the ends. Painters tape was used to secure the emery cloth in position. Then, the composite shear modulus specimens and the 90\u00b0 specimens were ready for testing. The 0\u00b0 unidirectional carbon fiber composite tensile specimens required 2 in. long aluminum tabs (as specified by ASTM 3039 [19]). Sandpaper was used on the surface, near the ends of the 0\u00b0 unidirectional carbon fiber composite tensile specimens. A small section of the surface was 23 abraded, and then, acetone was used to clean the surface. Structural adhesive was used to bond the Aluminum tabs to the 0\u00b0 unidirectional carbon fiber composite tensile specimens. After a full day of curing, the 0\u00b0 unidirectional carbon fiber composite tensile specimens were ready to be tested in the Instron 8801 machine. In Figure 14, one can see the ready-to-test 0\u02da unidirectional carbon fiber composite tensile specimens and the +/-45\u02da composite shear modulus specimens. 24 CHAPTER 3: TESTING PREPARATION & PROCEDURE In this chapter, the test preparation and procedure are explained thoroughly. Section 3.1 introduces the type of testing machine used for the experiment. Various test recommendations are made and included inside the preceding subsection. The Auto-Loop tuning feature is explained in detail and an example is made to assist the user in using this feature. The Specimen Protect feature in Bluehill2 is explained with full detail, which helped produce very consistent experimental results. Finally, in Section 3.3, the tensile double shear test and tensile test procedures are explained. The design and set-up of the double shear fixture is shown in detail as well. In the Appendix, the Bluehill2 test method creation was explained for a double shear tensile test. 3.1 Intro to Uniaxial Testing Using the Instron 8801 Servo-hydraulic Test Machine All the material tests were conducted on an Instron 8801. This machine is a dual column servohydraulic testing system. It meets the challenging demands of various dynamic and static testing requirements. The machine allows the user to hook up external force or strain transducers. A dynamic knife-edge extensometer was used for both, the tensile and double shear tests. The machine works in conjunction with a controller, which can be used to control the machine without the use of a computer. A servo-hydraulic system is composed of an actuator, which can apply a tremendous amount of load onto a test specimen. The load cell has a +/- 100 kN limit which means it can measure accurately up to +/- 22,000 lbs. axial force (in compression/tension). For the tensile double shear test, the maximum load that was seen during the test was around 1,700 lbs. and for 25 the tensile test, a maximum load of 7,000 lbs. was seen. The thicker the laminate, the higher the load the specimen could take before failure. Shown in Figure 15, one can see the Instron 8801 testing setup. The machine\u2019s crossheads contain metal jaws, which (powered by a hydraulic system) are able to clamp the specimen. The hydraulic clamping pressure is adjustable so for standard tensile testing, the pressure is set to 160 bar and for testing fragile composite resins, one would want to drop the pressure to 80 bar. Lowing the hydraulic pressure helped reduce premature specimen cracking. The crosshead mechanism loaded with a specimen is shown below in Figure 16. The specimen is placed carefully between two the hydraulically powered metal clamps which secure 26 the specimen in place. 3.1.1 Instron Servo-hydraulic Test Machine Recommendations For determining the modulus of elasticity along with the modulus of rigidity, the most accurate measuring tools were the extensometer and the strain gage. The crosshead displacement was not very accurate since the system displaces due to the compliance in the grips, and the actuator assembly. This displacement of the crosshead can cause unreliable results in the modulus of elasticity where accuracy is very important. The Instron crosshead and the extensometer both yielded slightly different stress/strain curves. This difference in stress/strain curves is due to the Instron crossheads displacing a little more than the extensometer. The extensometer measured only the deflection of the specimen relative to both of the extensometer knife-edges. The extensometer 27 had a gage length of 0.5 in. and a knife-edge width of 0.5 in. The dynamic extensometer, catalog no. 2620-826, can be seen in Figure 17. The top knife-edge is fixed and the bottom knife-edge records precise deflections. The extensometer was attached using two rubber bands. The rubber bands were wrapped multiple times around the specimen to prevent the knife-edges from slipping. Whenever the extensometer was handled, the safety pin was in place at all times. If the user wants to run a three-point or 4-point bend test, the crosshead displacement is accurate enough to capture the vertical displacement accurately. If the user wants even more accuracy, they are able to hook up an extensometer to the three-point bend fixture and record vertical displacement with that device rather than the crosshead displacement. The Instron 8801 machine has a few features, which need to be utilized in order to minimize testing errors. The load and position calibration should never be changed or conducted. Before any 28 test is conducted, the user should Auto-loop tune the load cell only once. Each time a new material is being tested; for example, carbon fiber compared to Aluminum, the load cell should be Autoloop tuned. A list of load cell control gains should be recorded in a separate table for each material, to avoid having inexperienced individuals auto-loop tune the machine. Some precautions in the auto-loop tuning process include to never auto-loop tune a material that will fails under 120 lbs. and to never set the force amplitude above 500 lbs. This may cause the machine to cycle through very rapidly. 3.1.2 Tutorial on Auto-Loop Tuning of the Load Cell for an 1 in. wide By 1/16 in. Thick Aluminum Specimen Each time a new type of material is tested in the machine the load cell needs to be auto-loop tuned whether it be Aluminum, Steel, carbon fiber, hemp composite, fiberglass or any other composite material. Auto-loop tuning the force insured that the load cell is set up to perform accurately for each specific material. The auto-loop tuning tool adjusted various gains on the load cell controller. This was done through the Bluehill2 console (under the load cell menu). Measure the cross-sectional area of the tensile specimen and note its yield stress (if a metal) or ultimate stress (if a brittle material). For example, for Aluminum, the yield stress is around 35 ksi and the tensile specimen had a cross-sectional area of 0.062 in.2. Make sure to apply a force which keeps the material well under its yield or ultimate stress (so 25 ksi was applied to the Aluminum specimen). 29 Insert the Aluminum tensile specimen into the hydraulic clamps and load the specimen to 1,500 lbs. Also, set the amplitude force to 500 lbs. In the auto-loop tuning wizard, the Proportional gain (P) needs to be set to one before any auto-loop tuning is conducted. The specimen will be exposed to a cyclic load of 1,500 lbs. \u00b1 500 lbs. After the auto-loop tuning completes, it will say Auto-loop tuning completed successfully and then, in the next window record the P, I, D and L values. The P value should be 12.564, the I value should be 0.56, the D value should be 0.49 and the L value should be 0.8. These gain values are essential to the auto-loop tuning process. Each time a new material is tested, it is advised to specify the correct P, I, D and L values in the console and only if those values are unknown then the material needs to be auto-loop tuned. After running the auto-loop tuning tool on the MTM 49 unidirectional carbon fiber material, the P (proportional gain) equaled 13.481 and I (integral gain) equaled 0.578. Both D and L equaled zero. Typically, the material needs to be auto-loop tuned in a load range where accuracy is needed. This range is typically, where the modulus of elasticity is measured in between 25% to 50% of ultimate stress as stated by ASTM D3039 Tensile Properties of Polymer Matrix Composite Materials [19]. If the material fails during the auto-loop tuning process, the actuator will shake violently and will not stop itself. Hit the red emergency stop button on the control panel or hit the red button on the Instron servo-hydraulic machine to power off the actuator. Start back up the machine and run the auto-loop tuning tool again at a lower force. 30 3.1.3 Tutorial on Specimen Protect The specimen is prone to premature failure due to high clamping forces exerted by the hydraulic clamps. Instron's Specimen Protect feature protects a specimen against this phenomenon. This feature is found inside the console, it is labeled Specimen Protect, and the symbol looks like small shield. Before using the Specimen Protect feature, go into the console, enter the Specimen Protect option menu and make sure the load threshold is set to 44 lbs. Clamp the bottom of the test specimen. Once the bottom of the specimen is clamped, move the actuator up until the top of the specimen sits in between the top crosshead's clamps. Turn on the Specimen Protect feature in the console and this will automatically move the bottom crosshead slightly up or down in order to prevent the specimen from experiencing more than 44 lbs. After both the top and bottom of the specimen are clamped, turn off the Specimen Protect feature and continue with the test. Every time a new specimen is inserted into the hydraulic clamps, this feature needs to be utilized in order to prevent premature failure. 3.2 Bluehill2 Test Preparation The machine was connected to a Windows desktop and from there Bluehill2 and the console were used to monitor machine inputs and outputs. According to Instron, the console software provides full system control from a PC: including waveform generation, calibration limit set up, and status monitoring. In real-time, Bluehill2 outputted various experimental results: strain values, load values, displacement values, and exc. All the raw data was outputted into an Excel file, which 31 could be used for post-processing calculations. 3.2.1 Bluehill2 Test Parameter Setup The main software of interest was the Bluehill2 software. In Bluehill2, the user has options of changing various testing parameters. Each test can be created and saved to a separate testing file, which can later be accessed when the user needs to conduct that type of test. Three different tests were created in the Bluehill2 software. The tensile test and tensile double shear test were created with the Bluehill2 software. Before a test file is created, it is required of the user to know what values are of interest for a specific structural test. The ASTM should exactly specify which the testing parameters should be used for the specific test. ASTM D5961 [18] suggested to test at a load rate of 0.05 in./min., to sample at a rate of at least 2 samples per second, and to output the extensometer displacement instead of the crosshead displacement. It also specified to run the test until a maximum force is reached and until the maximum force decreased by 30%. If the force didn\u2019t drop to 30% of the maximum; run the test until the pin displacement is equal to half of the hole diameter. For the pin displacement, the test ended once the extensometer read a displacement of 0.1 in. since that was the maximum range of the extensometer. The test specimen slipped in the grips when the force in the force vs. time plot flattens out, with respect to time, the specimen was slipping. The hydraulic pressure was manually set to 160 bar on the side of the machine. The fastener, which secured the Steel collars to the sides of the specimen, was hand tightened. Five different loading rates were 32 applied and adjusted accordingly inside the Bluehill2 software. 3.3 Instron Experimental Test Procedure The Instron start-up checklist was followed in the lab in order to start the machine safely. The first step of the checklist was to turn on the main power switch in the back of the lab. After turning on the main power switch, the next step was to turn on the Instron controller by pressing the power switch in the back of the Instron controller. Once the controller warmed up fully, a small blinking light appeared on the load calibration section of the controller. The calibrate button was pressed on the load menu of the controller. Next, the Cal button was pressed. Once the Restore button was pressed, the machine was fully calibrated even though it read \u201cCalibration not restorable.\u201d The desktop was turned on, and once the system booted up, the Bluehill2 software was started. As the software started up, it automatically started the console. The console is how the computer communicates with the Instron machine. The extensometer was plugged into the back of the Instron machine and it showed up under Strain 1 (in the Bluehill2 software). Once the extensometer was plugged in, it flashed in the console screen reminding the user that it needed to be calibrated. The extensometer\u2019s calibration was restored to a previous calibration. From this point on, the tensile test, or the double shear bearing test could be started. 3.3.1 Tensile Testing Procedure Before starting any ordinary tensile test, the user needed to have at least six tensile specimens 33 prepared for the test. For each tensile specimen, the thickness, width and gage length (distance between the tabs) were recorded. The Specimen Protect feature was also used when initially clamping the specimens. The first composite tensile specimen was tested to failure (without the extensometer), in order to find its ultimate failure load. A limit load was created for the extensometer and was decided based on the ASTM D3039 [19]. As stated in ASTM D3039 [19], the material's modulus of elasticity can be measured anywhere between 25% and 50% of its ultimate load or yield load (if it is a metal). The limit load was calculated by multiplying the 1st specimen\u2019s ultimate load by 0.25 and this value was specified in Bluehill2\u2019s end of test criteria. In Bluehill2 software, there is an option of recording the strain using an extensometer and once the limit load is reached, the test will pause allowing the user to remove the extensometer. Next, the remaining five composite tensile specimens were tested. The next composite tensile specimens were loaded in the machine and the extensometer was attached for each specimen. Figure 18 shows a composite tensile specimen (with an extensometer mounted on its surface). Once at the limit load, the extensometer was removed, and the test continued up to the ultimate load. Note that the initial modulus recorded by the extensometer was very accurate, and after removal of the extensometer, the crosshead took over and the accuracy declined. 34 3.3.2 Double Shear Testing Procedure Once the standard Instron startup procedure was completed, the tensile double shear Bluehill2 test method was started. In the Appendix, one can find a detailed tutorial on the tensile double shear Bluehill2 test method. Procedure A double shear tension, in ASTM 5961 [18], was followed closely. The user needed to make sure that all the dimensions were recorded such as specimen width, specimen length, and specimen thickness and distance between the edge of the specimen to the hole edge. The fixture used for the double shear test consisted of an assembly made up of three cold drawn Steel plates with two bolts and nuts connecting all three plates. The double shear fixture is shown in between the clamps on the left in Figure 19. The double shear fixture is shown, in the center, in Figure 19. The close-up of the collar-specimen assembly is shown, on the right side, in 35 Figure 19 as well. Each double shear joint specimen was sandwiched between two Steel plates, two Steel collars, four washers and a nut, which can be seen on the left and the center in Figure 20. The extensometer, as required by the ASTM 5961 [18], is fixed on the fixture with a small steel plate and two bolts, shown on the right in Figure 20. The extensometer's knife edge was carefully placed inside the slit of the specimen and secured with a rubber band. The nut which held the screw assembly together with the specimen was only hand tightened. In the Bluehill2 software, as stated earlier, the end of test occured if the maximum force droped by 30% or if the maximum extensometer displacement was 0.1 in. This end of test criteria worked perfectly for the 0.05 in./min., 0.1 in./min. and 1 in./min. loading rates. But for the 2 in./min. and 6in./min. loading rates, the maximum extensometer displacement was lowered to 0.05 in. At faster loading rates (above 2 in./min.), the actuator had problems stopping immediately at very small deflections (0.1 in.) so applying this adujstment prevented the extensometer from accidently breaking due to over-deflection of the crossheads. 36 37 CHAPTER 4: THEORETICAL SOLUTION METHOD In this chapter, information is given on the equations that were used to find all of the mechanical properties of the material used. The theoretical equations used to come up with the macromechanical behavior of a lamina and laminate are included as well. 4.1 Experimental Equations 4.1.1 Equations Used for Unidirectional Carbon Fiber and Aluminum Double Shear Specimens The width to diameter ratio of the specimens needed to be measured and recorded. Below, W, is the specimen width, and D is the diameter of the hole. \ud835\udc4a \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc4a/\ud835\udc37 The edge to diameter ratio of the specimens needed to be measured and recorded. \ud835\udc38 \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = (\ud835\udc54 + \ud835\udc37/2)/\ud835\udc37 The diameter to thickness ratio of the specimens was measured and recorded. Below h is specified as the thickness of the specimen. \ud835\udc37 \u210e \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc37/\u210e The bearing stress was calculated by dividing the force, P, by the force per hole factor, k (equal (1) (2) (3) 38 to 1 for double shear test), with the diameter of the whole, D and by the thickness of the specimen, h. \ud835\udf0e\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strength was calculated by dividing the maximum force, Pmax, by the force per hole factor, k, with the diameter of the hole, D and by the thickness of the specimen, h. \ud835\udc39\ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strain was determined from the extensometer displacement, \ud835\udeff\ud835\udc56 divided by the k, force per hole factor, and the diameter of the hole, D. \ud835\udf16\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udeff\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37) The bearing chord stiffness was only reported if there existed an offset bearing strength. The linear portion, where the bearing stress ranges from 25 \u2013 40 ksi, is the bearing chord stiffness region. \ud835\udc38\ud835\udc4f\ud835\udc5f = \u2206\ud835\udf0e\ud835\udc4f\ud835\udc5f/\u2206\ud835\udf16\ud835\udc4f\ud835\udc5f 4.1.2 Equations Used for Tensile Testing of Unidirectional Carbon Fiber and Aluminum Specimens The maximum tensile strength F, was calculated by dividing the maximum force by the cross- (7) (6) (5) (4) 39 sectional area A. \ud835\udc39 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/\ud835\udc34 The tensile stress, \ud835\udf0e, was calculated by dividing the force by the cross-sectional area, A. \ud835\udf0e\ud835\udc56 = \ud835\udc43\ud835\udc56/\ud835\udc34 The chord modulus of elasticity, E, was calculated by the difference two tensile stress points and their equivalent tensile strain points. \ud835\udc38 = \u0394\ud835\udf0e/\u0394\u03b5 The extensometer strain, \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 , was calculated by dividing the extensometer displacement, \ud835\udeff\ud835\udc56, by the extensometer\u2019s gage length, \ud835\udc3f\ud835\udc54. The gage length of the extensometer was always 0.5 in. \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 = \ud835\udeff\ud835\udc56/\ud835\udc3f\ud835\udc54 The axial and transverse strains were plotted with respect to axial force. The slope of the transverse strain vs. axial load, \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 , was divided by the slope of the axial strain vs. axial load, \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 , and this equaled the Poisson\u2019s ratio of the material. \ud835\udf10 = \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 / \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 (8) (9) (10) (11) (12) 40 4.1.3 Equations Used with the Rosette Strain Gage Using the Equations (13) \u2013 (15), one can find the principle strains in the x-direction, \ud835\udf16\ud835\udc65, y- direction, \ud835\udf16\ud835\udc66 and finally the shear strain in the xy-direction, \ud835\udefe\ud835\udc65\ud835\udc66 . The three different theta values, \u03b81, \u03b82, \u03b83 were all angles relative to the axial strain gage. The strain rosette was placed on the composite quasi-isotropic specimen's surface so that each strain gage was in 0\u00b0, +45\u00b0 and 90\u00b0. So \u03b81 equaled 0\u00b0, \u03b82 equaled +45\u00b0, and lastly \u03b83 equaled 90\u00b0. The principle plane stresses were also transformed with a transformation matrix to the desired angle, \u03b8. In the transformation matrix c = cos \u03b8 and s = sin \u03b8. Where A is considered the transformation matrix below. The transformed plane stresses, \ud835\udf0e\u2032, equaled the transformation matrix, A times the plane stresses, \ud835\udf0e. (13) (14) (15) (16) (17) 41 Once the three principle strains were calculated then a transformation matrix was used to transform each of the three strains to the desired angle, \u03b8. The transformed plane strains, \ud835\udf16\u2032, equals Reuter's Matrix, R, times the transformation matrix, A, by the inverse of the R matrix, and lastly times the plane strains. The modulus of rigidity, G, was found by dividing the modulus of elasticity, \ud835\udc38, by 2 times Poisson\u2019s ratio, \ud835\udf10, plus 1. \ud835\udc3a = \ud835\udc38 2(1+\ud835\udf10) 4.1.4 Equations Used for In-Plane Shear Modulus Testing of Unidirectional Carbon Fiber Specimens The maximum shear stress, \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 (18) (19) (20) (21) 42 divided by the cross-sectional area times two. \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 2\ud835\udc34 The shear stress, \ud835\udf0f12, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65divided by the cross- sectional area times two. \ud835\udf0f12,\ud835\udc56 = \ud835\udc43\ud835\udc56 2\ud835\udc34 The modulus of elasticity in the +/- 45\u00b0 shear modulus test, \ud835\udc38\ud835\udc65\ud835\udc65, was calculated by the difference two stress points and their equivalent strain points. \ud835\udc38\ud835\udc65\ud835\udc65 = \u2212\u0394\ud835\udf0e \u0394\u03b5 The shear chord modulus of elasticity, \ud835\udc3a12, was calculated by the Equation (25). \ud835\udc3a12 = 1/( 4/\ud835\udc38\ud835\udc65\ud835\udc65 \u2212 1/\ud835\udc381 \u2212 1/\ud835\udc382 + 2\ud835\udf1012/\ud835\udc381 ) Converting normal strain to shear strain is done by dividing the shear strain by 2. \ud835\udf16 = 1/2 \u2217 \ud835\udefe 4.1.5 Equations Used for Volume Fraction Testing of Cured Reinforced Resins The ignition loss of the specimen in weight percent is calculated by subtracting the weight of the specimen, W1, and the weight of the residue, W2. (22) (23) (24) (25) (26) 43 Ignition lost, weight % = [(\ud835\udc4a1 \u2212 \ud835\udc4a2)/\ud835\udc4a1 ] \u2217 100 4.2 Theoretical Equations 4.2.1 Equations Used to Find Laminate In-Plane Engineering Constants The NASA Composite Laminate Report [24] was used to find all the laminate in-plane engineering constants (or also known as in-plane laminate material properties). Before finding the laminate in-plane engineering constants, the assumptions must be stated. The quasi-isotropic laminate, with a layup sequence of [0 0 +45 -45 +45 -45 90 90]s, meant that it\u2019s symmetrical and balanced. A symmetrical laminate simplifies the calculations since all that is needed to determine the in-plane engineering constants is the A matrix since the B matrix is composed of all zeros. But for asymmetrical laminates, one would need A, B, and D matrices. The subscripted numbers after the matrix, for example, the 1 and 2 in A12, which is in the number in the first row and second column of the matrix. The theoretical method of finding the laminate in-plane engineering constants required knowledge of Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material properties [21]. The experimental datasheet material properties were used inside the theoretical method. In Equation (28), to find the modulus in the x-direction, the stress in the x-direction is divided by the strain in the x-direction. Which can be also written as force per length in the x-direction, Nx , divided by the laminate thickness, h all over the strain. (27) 44 The A matrix simplifies to the one below since the Bij matrix is all zeros. For each layer in the laminate one needs to solve for a unique Q matrix. If a laminate has 16 different layers then there will be 16 Q matrices and after they are all solved they need to be summed together to form the A matrix. Equations (29) \u2013 (40) will be needed in order to solve for each value in the Q matrix. For any angled ply, one uses Equations (33) \u2013 (40). (32) (31) (30) (29) (33) (34) (28) 45 There is no force (or stress in the other two directions) so those are set to zero. This further simplifies the equations. (35) (36) (37) (41) (40) (39) (38) 46 After further simplification of the Equations (42) \u2013 (44), Equation (46) was equal to our modulus in the x-direction, Ex , only after this number was divided by the laminate thickness, h. \ud835\udc38\ud835\udc65 = \ud835\udc41\ud835\udc65/(\ud835\udf16\ud835\udc65 0 ) \u2217 1/\u210e Next, the same exact method is applied to the y-direction. The modulus in the y-direction, Ey equaled Equation (48). \ud835\udc38\ud835\udc66 = \ud835\udc41\ud835\udc66/(\ud835\udf16\ud835\udc66 0 ) \u2217 1/\u210e Next, the same exact method is applied to the xy-direction. The shear modulus in the xy- direction was found, in Equation (50), Gxy , only after divided by the laminate thickness, h. (42) (43) (44) (45) (46) (48) (47) 47 \ud835\udc3a\ud835\udc65\ud835\udc66 = \ud835\udc41\ud835\udc65\ud835\udc66/(\ud835\udefe\ud835\udc65\ud835\udc66 0 ) \u2217 1/\u210e Poisson\u2019s ratio, \u03c5xy , of the laminate was calculated using Equation (51). Poisson\u2019s ratio, \u03c5yx , of the laminate can was calculated using Equation (52). (51) (52) (50) (49) 48 CHAPTER 5: EXPERIMENTAL RESULTS In this chapter, the experimental results are explained in detail. Section 5.1 explained the validation process, which was conducted, on all the strain measurement devices. The axial modulus of elasticity and Poisson\u2019s ratio of Aluminum were validated. Section 5.2 summarized the material testing which was conducted on the unidirectional carbon fiber material. Section 5.3 explained the unidirectional carbon fiber material property testing. Section 5.4 explained the quasiisotropic carbon fiber laminate material property testing. Section 5.5 explained the experimental results found for the Aluminum double shear specimens. Section 5.6 explained the quasi-isotropic carbon fiber double shear specimens\u2019 experimental results. 5.1 Experimental Measurement Device Validation Before any strain measurement device was used on a composite material, its accuracy needed to be validated with commonly known material. In this case, an Aluminum specimen was tensile tested with a strain gage orientated in the axial direction, and another strain gage orientated in the transverse direction. Since the axial strain gage, the extensometer and the crosshead were measuring axial strain, their readings were compared. In the past theses, students were using the crosshead displacement to measure the modulus of elasticity. Using the crosshead displacement was very unreliable and it is explained in more detail in the next sub section. 49 5.1.1 Extensometer vs. Axial Strain Gage vs. Crosshead Displacement The test set-up of the Aluminum specimen is shown in Figure 21. The three principle directions and the clamped sections of a standard uniaxial tensile specimen are shown in Figure 21. Below in Table 1, an Aluminum sample was loaded and unloaded three times up to a tensile stress of 25 ksi. The tensile stress was calculated using Equation (9). A tensile stress of 25 ksi lies in the material\u2019s linear elastic region and it is far away from materials yield stress of 35 ksi. Table 1 shows the comparison of experimental results between the extensometer, strain gage and crosshead. Table 1 also shows the dimensions of the Aluminum specimen. The strain gage and extensometer experimental results were validated with the Aluminum 2024-T4 datasheet mechanical properties [25]. The moduli of elasticity, in Table 1, are in msi (10E6 lbs./in.2) and were calculated using Equation (10). There was less than 1% error between the extensometer and the strain gage when compared to the Aluminum 2024\u2019s modulus of elasticity. When comparing to the crosshead, there was an error of 64%. The crosshead displacement is not as accurate as an extensometer or a strain gage, because the crossheads have compliance (inside the actuator assembly) which elongates as load is applied. The actuator assembly starts to elongate, which significantly affects the experimental strain results. The small standard deviation showed how consistent the results were when using the three different measurement tools and the testing machine. 50 showing the clamped sections and the 3 principle directions (right) 51 Below in Figure 22, one can see the three runs that were done using the extensometer and the axial strain gage. The crosshead displacement was excluded from Figure 22, since the experimental strain varied so drastically from the extensometer and the axial strain gage. The strain gage and the extensometer read very similar moduli of elasticity. The extensometer and strain gage proved to be reliable, so both measurement tools were used on the composite specimens. 52 5.1.2 Poisson\u2019s Ratio Validation Using Axial and Transverse Strain Gages The Poisson's ratio of the Aluminum 2024-T4 needed to be validated. In Figure 23, one can see the axial and transverse strains plotted with respect to the axial force. The axial strain gage output is shown in blue and the transverse strain gage is shown in red. A linear curve fit was applied to both sets of strain gage data and their respective linear equations are shown, as well. Poisson's Ratio equaled to a value of 0.26, for the Aluminum specimen, using Equation (13). 53 5.2 Summary of Carbon Fiber Material Properties Below in Table 2, the results accumulated from Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg material datasheet [21] are summarized. The values which have a (-) dash meant that they were not given in the material's datasheet. The strengths were specified in ksi, which is 10E^3 lbs./in. Table 3 shows the experimental material properties of the Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material, which were experimentally tested in the Cal Poly\u2019s Aerospace Composites Lab. Table 4 shows the experimentally tested and calculated quasi-isotropic laminate properties. Poisson's ratio, for Umeco\u2019s MTM49 Unidirectional pre-preg material was used from a previous report\u2019s value [26] of 0.25. All these material properties are further explained in the next few sections. Looking at Table 2 and Table 3, the 0\u00b0 compressive modulus is 22.3 msi and the 0\u00b0 tensile modulus is 26.6 msi. All of the tensile axial moduli of elasticity were similar but they were slightly higher than the compressive modulus specified in the datasheet. The tensile and compressive modulus should be very similar since the fibers are assumed to behave like an isotropic material. This material was not tested in compression since compression specimens need to be a lot shorter, in length (ideally have less than 0.5in. in gage length). An extensometer could not be mounted on the surface of the compression specimen since there is not enough room between the grips. The best way to measure, the compressive modulus of elasticity would be to use an optical high-speed camera, which records the relative motion through optics. 55 5.3 Unidirectional Carbon Fiber Material Property Testing 5.3.1 Test for 0\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens A laminate of 8 plies, [0]8T, was laid up and tested along the fiber direction. The 0\u00b0 direction is always the direction of the applied load in a uni-axial test. The ASTM 3039 [19] required a minimum of five specimens per test, and having more than five specimens helped improve the 56 consistency of the results. Each specimen was 10 in. long by 0.5 in. wide and with a thickness of 0.046 in. The ASTM 3039 [19] required curing 2 in. long by 0.5 in. wide Aluminum tabs on the specimens to prevent premature failures from occurring. The grip pressure was set to 160 bar. The tensile test began with testing one 0\u00b0 unidirectional carbon fiber composite tensile specimen (without an extensometer) to failure, to find its ultimate load. The limit load of 2,000 lbs. was chosen since the ultimate load was 4,600 lbs. The last six 0\u00b0 unidirectional carbon fiber composite tensile specimens were loaded to 2,000 lbs., and at 2,000 lbs., the test was paused so that the extensometer could be removed safely. Once the extensometer was removed, the Instron machine's crossheads took over in measuring the tensile strain. The load cell accurately measured the ultimate load up to an accuracy of +/- 45 lbs. In Figure 24, the 0\u00b0 unidirectional carbon fiber composite tensile specimens are shown to the left and one of the clamped post-test 0\u00b0 unidirectional carbon fiber composite tensile specimen is shown on the right. Figure 25 shows all seven of the tested 0\u00b0 unidirectional carbon fiber composite tensile specimens (each color represents a different specimen). Figure 26 shows the extensometer mounted on the 0\u02da unidirectional carbon fiber composite tensile specimen with two rubber bands. The compressive modulus was specified in the datasheet and the tensile modulus was not specified in the datasheet. The experimental tensile modulus was compared to the compressive modulus and the difference between the two values was 19%. A 17% difference between the tensile strength when compared to the datasheet values. 57 58 60 5.3.2 Test for 90\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens Next, a laminate of 14 plies, [90]14T, was laid up and tested along the matrix direction. A couple extra test specimens were tested to find the optimum hydraulic clamping pressure. The clamping pressure was initially set to 160 bar and once the specimen was clamped, it cracked. The hydraulic clamp pressure was reduced to 60 bar in order to prevent this premature failure from occurring. Eight specimens were tested since the material is very brittle and unpredictable. When examining the stress-strain plot of the 90\u00b0 unidirectional carbon fiber composite tensile specimens, the ultimate tensile stress determined the location of where the specimen would fail. As one can see in Figure 27, the four 90\u02da unidirectional carbon fiber composite specimens, which failed at an ultimate tensile stress of around 5 ksi, ended up breaking in the center. Whereas, the specimens which failed at a lower ultimate tensile stress failed near the emery cloth. The experimental results (between all the specimens) showed a very consistent modulus of elasticity. The ultimate tensile strength of the material varied, due to the matrix is very brittle. The failure of a brittle material is very unpredictable which one can see in the Figure 28. There was 17% difference between the datasheet 90\u00b0 modulus of elasticity and a 29% difference between the 90\u00b0 tensile strength when compared to the datasheet values. The ultimate tensile strength variations might have been due to the low accuracy of the load cell, which typically occurs at low loads (around 100 lbs.) since the accuracy of the load cell is +/- 45 lbs. Table 6 shows the experimental results of all the 90\u00b0 unidirectional carbon fiber composite tensile specimens. 61 63 5.3.3 Test for +/-45\u00b0 Shear Modulus Specimens After following ASTM D3518 [20], a laminate was created with an orientation of [+/- 45]4S which is a symmetric laminate with alternating positive and negative 45\u00b0 plies. Another way to write this is [+45 -45 +45 -45 +45 -45 +45 \u2013 45]s. The extensometer was placed at 0\u00b0 relative to the specimen. The axial modulus of elasticity, Exx, was recorded and Equation (25) was used to find G12. Equation (25) requires knowledge of E1, E2, and \u03c512. Eight shear modulus specimens, for consistency, were tested since ASTM D3518 [20] required a minimum of five shear modulus specimens. The shear modulus specimens are shown in Figure 29. The post-tested shear modulus specimens looked the same as the pre-tested shear modulus specimens (since the failure occurred in the matrix and not in the fiber). Figure 30 shows the highly consistent shear specimen results. Table 7 showed the detailed experimental results. There was 35% difference between the in-plane shear modulus and a 43% difference between the in-plane shear strength when compared to the datasheet values. Testing for the shear strength is not an easy task since the shear modulus specimen has to be in full shear state at failure. The tabs on the ends of the specimen create stress concentrations on the ends, which cause the specimen to fail prematurely. 64 66 5.4 Quasi-Isotropic Laminate Material Testing 5.4.1 Test for Quasi-isotropic Tensile Specimens The same test method used for the 0\u00b0 and 90\u00b0 specimens was used to test the carbon fiber quasi-isotropic tensile specimens. Once one quasi-isotropic tensile specimen was tested to failure, the ultimate load was recorded to be 6,500 lbs. The next six quasi-isotropic tensile specimens were tested with the extensometer up to a force of 2,000 lbs. The test paused once the force reached 2,000 lbs. and then the extensometer was removed. Figure 31 shows the quasi-isotropic tensile specimens before (on left) and after (on right) they were tested. The region circled in red showed the area where there was a fiber failure. Figure 32 showed a close-up of the tensile failure. In Figure 32, looking at the picture on the right, one can see the 0\u00b0 fibers on the outer layer held together, while in the center of the laminate, a crack began to form. The crack, in Figure 32, is circled in red. 67 68 From Figure 33, one can see a close-up of the strain rosette, which was on Specimen #1. Shown in Figure 34, a rectangular strain rosette (CEA- 06-120CZ-120 made by VishayPG) produced very accurate results. The rosette was placed on the quasi-isotropic tensile specimen at a 0\u00b0-45\u00b0-90\u00b0 orientation and the wires were soldered very accurately. Each strain gage resistance was checked (with a voltmeter) and read 120 Ohms. The strain gage worked correctly if the resistance across the strain gage read the correct resistance specified in the user manual. The quasi-isotropic tensile specimen #1 was tested one time by recording the strains in the 0\u00b0 direction, 45\u00b0 direction and 90\u00b0 direction. In addition, when the strain gage was being applied to the surface, an 80-grit sandpaper was applied to the surface of the quasi-isotropic tensile specimen. The sanding of the outer 0\u00b0 layer might have affected the material\u2019s mechanical properties. Table 8 shows this 8% difference in modulus of elasticity between the extensometer and the strain gage. From Figure 35, one can see the slight drop in stress (at 20 ksi) due to the pause in the test. The different line colors show the seven different quasi-isotropic tensile specimens that were tested. The main thing to note is the percentage difference between the modulus of elasticity found with the strain rosette and the extensometer. The ultimate tensile strengths were very consistent which showed from a very low standard deviation of 3.87 ksi. 69 70 72 5.4.2 Quasi-Isotropic Tensile Specimen #1 In-Plane Experimental Material Properties Figure 36 shows experimental strain values of the extensometer, the axial strain gage, the +45\u00b0 strain gage and the transverse strain gage. A slight variation exists between the axial strain gage and the extensometer because the extensometer was not placed in the same location as the strain gage. The sanding error, like stated in the previous section, might have also contributed to the error of 8%. The test was stopped at a force of 2,000 lbs. A linear curve fit was applied to all of the three separate strain gage readings and are shown in Figure 36. Next, the Poisson\u2019s ratio of the quasiisotropic tensile specimen was found using Equation (12) and in-plane shear modulus of the quasiisotropic laminate was found using Equation (23). The axial modulus of elasticity was found using Equation (10). 73 5.4.3 Quasi-Isotropic Laminate In-Plane Theoretical Material Properties The theoretical material properties were found using the NASA report on Basic Mechanics of Laminated Composite Plates [24]. In Section 4.2.1, one can find the equations used to calculate the theoretical material properties. Before these equations could be used, a few assumptions were made: (1) The material to be examined is made of up of one or more plies (layers), each ply consisting of fibers that are all uniformly parallel and continuous across the material. The plies do not have to be of the same thickness or the same material. [23] (2) The material to be examined is in a state of plane stress, i.e., the stresses and strains in the through-the-thickness direction are ignored. [23] (3) The thickness dimension is much smaller than the length and width dimensions. [23] The values in Table 9 were needed in order to come up with the theoretical material properties. Table 9 shows the values that were applied into the laminate theory since the laminate theory required knowledge of the material properties of one layer of the unidirectional carbon fiber material. With the help of a strain rosette and the use of Equations (13) - (15), all the in-plane principle strains could be found. 74 Below in Table 10, one can see the calculated experimental material properties using the strain gage rosette. Three different in-plane laminate material properties were calculated based on three different force values (1500 lbs., 1750 lbs. and 1900 lbs.). The theoretical material properties were in agreement with the experimental material properties since the error between the modulus of elasticity was only around 10% and only 2% for the Poisson\u2019s ratio. The low standard deviation showed the reliability of the testing equipment and the strain measurement devices. 75 5.5 Fiber Volume Fraction Test ASTM D2584 [27], Standard Test Method for Ignition Loss of Cured Reinforced Resins, was followed closely. Three volume fraction specimens were tested inside the furnace shown on the right in Figure 37. On the left of Figure 37, one can see a fiber volume fraction test specimen. The fiber volume fraction specimen was placed on top of an Aluminum plate. While the furnace was preheated to a temperature of 1000\u00b0F, the Aluminum plate was weighed and each fiber volume fraction specimen was weighed in grams and then converted to lbs. in order to keep the units consistent. The measuring scale had a least scale reading of 0.1 g. The dimensions of each fiber 76 volume fraction specimens were carefully measured and recorded. Each specimen was placed on the Aluminum plate and left inside the furnace for one hour. Once all the epoxy burned off, the fiber volume fraction specimen was weighed and this was weight of the fibers. The initial weight of the fiber volume fraction specimen minus the final weight of the fiber volume fraction specimen was the weight of the resin (matrix). After doing some simple calculations, along with using the cured resin matrix density of 1.24 g/cm3(from the material\u2019s datasheet); the fiber weight fraction along with the fiber volume fraction was calculated and compared to the datasheet. In Table 11, one can see the three different fiber volume fractions along with the fiber weight fractions. The fiber volume fraction specimen dimensions are crucial to the determination of the fiber volume fraction. The measured thickness of the fiber volume fraction specimen varied from 0.1 in. to 0.103 in., which meant that the heat press cooked unevenly. The slight variation of the specimen\u2019s thickness affected the volume fraction by 4%. The 8.3% difference between the experimental fiber volume fraction and the datasheet fiber volume fraction varied because not enough pressure was applied to the laminate during the curing process. The lower fiber volume fraction of 0.55 compared to 0.6 meant that there was more resin in the laminate. Not enough resin was squeezed out in the cure process. The pressure applied by the heat press was limited, so achieving the optimum fiber volume fraction (of 0.6) was difficult. The fiber volume fraction significantly affected all of the material property testing which was conducted on the Umeco MTM 49 unidirectional material. A low standard deviation showed that the data was very consistent. 78 Section 5.6 was conducted in order to validate the numerical model with the experimental data. Modeling a metal before modeling a composite is very important because metals behave in a more predictable fashion. Metals are a lot simpler to model since they exhibit isotropic behavior whereas composites exhibit orthotropic behavior. The material property inputs for an isotropic material are much less than for a composite material. For a composite, the user has to input three different moduli of elasticity, three moduli of rigidity, and three Poisson\u2019s ratios. For metals, the user only inputs the modulus of elasticity and the Poisson\u2019s ratio. In this validation, Aluminum 2024-T4 was used as the material of choice. Once the linear elastic model was validated with a metal, then any other material should be validated as well, but only for the linear elastic region of the material. This also validates the boundary conditions and any interactions, which were used in the numerical model. 5.6 Aluminum 2024-T4 Double Shear Test The Aluminum 2024-T4 double shear specimens were tested on the same double shear fixture as the composite double shear specimens. From Figure 38, one can see the bearing stress vs. bearing strain response of the five tested Aluminum double shear specimens. The first section of the bearing stress vs. bearing strain plot (the flat initial region) is the strain correction region. Compliance between the Instron parts, along with the clamps, occurred upon initial loading of the specimen. The deformation of all the internal parts of the Instron machine in the strain correction region. The linear elastic region, (shown inside the red square in Figure 38) for the Aluminum, was between 5 ksi and 40 ksi and after this region; the material experienced a non-linear behavior 79 up to its ultimate bearing strength. The strain correction region and the non-linear region were removed, which can be seen in Figure 39. The non-linear region and the strain correction region were not part of the numerical model. Figure 38 showed that specimen #5 failed at an ultimate bearing stress of 130 ksi and the other four specimens failed around 114 ksi. The extensometer\u2019s knife-edge slipped on the face of specimen #1 through #4, but for specimen #5, the extensometer did not slip. The linear elastic region can be seen in Figure 39. The specimen alignment might have caused the variations in the linear elastic strain values. The ultimate bearing strength matched up the Aluminum 2024-T4 material\u2019s datasheet [25]. Table 12 shows the experimental results of the Aluminum double shear specimens. Both the yield and ultimate strengths were calculated in the Table 12. Figure 40 shows a bearing type of failure, which occurred in all the Aluminum double shear specimens. Figure 41 shows the Aluminum double shear specimens before and after they were tested. The region circled in red shows the area where the failure occurred. Each specimens\u2019 hole diameter increased in size and also each specimens\u2019 hole diameter did not go back to its original shape once the load was removed, which showed that the material reached a plastic deformation. 80 82 5.7 Composite Double Shear Test As one can see in Figure 42 (from a paper by Yi Xiao [28]), the composite double shear specimens behaved differently than Aluminum double shear specimens. Recall, all the composite double shear specimens were manufactured with a quasi-isotropic laminate orientation of [0 0 +45 83 -45 +45 -45 90 90]s. The 4%D is considered the bearing strength of the material. The composite double shear specimens held load (without failing) up to the knee point. At the knee point, the first ply failed (after this point, the material properties started to degrade) and the slope of the curve was reduced. The load increased up to the final point, also known as the ultimate bearing strength of the material, where it maxed out. One positive thing about designing a structure to fail in bearing, as opposed to net-tension or shear-out, is that the force dropped 30% of the maximum load. Whereas, in net-tension or shear-out failure, the load dropped down to zero. Figure 43 shows a close-up of the bearing failure, which occurred on the composite double 84 shear specimens. As one can see, there is an excessive amount of damage near the pin location. All of the specimens exhibited a similar type of failure, so there was no need to take a picture of each of the failed specimens. Figure 44 shows ASTM 5961\u2019s [18] failure codes used to characterize any of the failure modes seen in a composite double shear test. The failure code, B1I, is used throughout the rest of the experimental section, which signifies a bearing type of failure. 85 86 5.7.1 Curing Cycle 1 (Cytec\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test Figure 45 shows the composite double shear specimens before and after the double shear test. In Figure 45, on the right, highlights the crushing regions, in red. All the failures are consistent. Eight specimens were tested for each of the five loading rates. For load rate 0.1 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. When looking at the alternate cure cycle experimental data, in Tables 13 & 14, an interesting 87 trend appeared. At slower loading rates, the composite double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min. the composite double shear specimens failed at an average stress of 64.4 ksi and 63.5 ksi whereas at 1 in./min., 2 in./min. and 6 in./min. the composite double shear specimens failed around 52.3 ksi. Looking at all the different loading rates, it seemed as if all the composite double shear specimens had a similar knee point. 2 in./min. and 6in./min. showed a greater drop in load after the composite double shear specimens reached their ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. did not show a huge drop in load after the specimens reached the ultimate load. 89 The maximum values of all the plots, in Figure 46, were the ultimate bearing strengths. When looking at Figure 46, one can see that as the loading rate increased the non-linear region decreased in size. The red-circled sections, in Figure 46, show how the non-linear region decreased in size. The linear region does not change as drastically as the non-linear region. As the load rate increased, the rate of damage also increased which explained the reduction, in size, of the non-linear region. 90 Looking at all of the load rates, the moduli in the non-linear regions are lower than the linear elastic regions. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. 91 5.7.2 Curing Cycle 2 (Umeco\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test When looking at the datasheet cure cycle experimental data, in Tables 15 & 16, a similar trend appeared. At slower loading rates, the double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min., the specimens failed at an average stress of 62.7 ksi and 67.7 ksi, whereas at 1.0 in./min., 2 in./min. and 6 in./min., the specimens failed around or under 52.0 ksi. It also looks like at 2 in./min. and 6in/min. show a greater drop in bearing strength after the specimen reaches its ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. do not show a huge drop in strength after the specimens reach the ultimate load. In general, fast loading causes more damage to the specimen which overall reduces the specimen's ability to carry load. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. Eight specimens were tested for each of the five loading rates. For load rates 2 & 6 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. 93 When looking at Figure 47, one can see that as the loading rate increased the non-linear region decreased in size. In Figure 47, the red-circled section also showed the non-linear region decreased, in size, with increased loading rate. 94 5.7.3 Comparison between Cure 1 & Cure 2 In Figure 48, it is very clear that as loading rate increased, the ultimate bearing strength of the 95 material decreased regardless of the cure cycle. Further research can be done on how different cure cycles can affect the bearing response of a composite double shear specimen. Making the matrix less brittle and more ductile might improve the ultimate bearing strength of the material. Cure cycle 2 (Umeco\u2019s cure cycle) was 2% stronger in bearing when compared to the cure cycle 1 (Cytec\u2019s cure cycle). The MTM 49 Unidirectional carbon fiber pre-preg material was very sturdy by not being affected by an alternate cure cycle. 5.7.4 Comparison Between The Aluminum Double Shear Specimens & Quasi-Statically Loaded (0.05 in./min.) Composite Double Shear Specimens Aluminum is standardly tested at quasi-static load rate of 0.05 in./min, since it\u2019s strain rate independent [30] (not affected by different loading rates). The Aluminum double shear specimens 96 performed a lot better in bearing than the composite double shear specimens. Since the carbon fiber is more brittle by nature, its ultimate bearing strength is significantly lower than Aluminum. of the Aluminum double shear specimens was around 118 ksi and the ultimate bearing strength of the composite double shear specimens was around 63 ksi. That means that carbon fiber is 53% weaker than Aluminum 2024-T4 in a double shear joint configuration. The Aluminum double shear specimens yielded at around 40 ksi compared to the composite double shear specimens, which yielded at 30 ksi. As one can see from the bearing stress vs. bearing strain graphs, there is a huge difference in ultimate bearing strength between of both materials. It is interesting to note that both materials showed a strain correction region. The Aluminum double shear specimens and the composite double shear specimens did not catastrophically fail (they deformed without significantly dropping the applied load). 97 CHAPTER 6: NUMERICAL ANALYSIS Chapter 6 explains the overall finite element approach. Section 1 introduces the finite element model and different considerations, which were applied to the model. Section 2 explains the idea behind a convergence plot and its importance. Section 2 explains what factors influenced the numerical results. 6.1 Finite Element Analysis Introduction Once a Finite Element Analysis model is validated with experimental results, it can then be used in the design process. Abaqus 6.14-1 was used to model the double shear bearing test experiment conducted. All the different Finite Element software work very similarly and the only difference between them is their program interface. However, they all essentially break up the model into small elements and calculate the stress state on each element. The material properties are assigned to the elements and then, the boundary conditions and loads are applied to the model. In some cases when there are two or more parts, one might have to define different types of interactions or constraints for the model (for example, how those parts move relative to each other). The numerical software also predicts non-linear behavior, which requires a lot more material properties. Plasticity required the user to model the damage done on the material as load increased, which meant, implementing a degradation model. First, a numerical model was created and validated for the Aluminum 2024-T4 double shear 98 specimen. The Aluminum numerical model was only validated through the linear elastic region of the experimental data, which was shown in Figure 39. The Aluminum numerical model was adjusted for the composite specimen and the experimental results were compared to the numerical results. Abaqus keeps the units consistent, so when working with US Customary units make sure to stay consistent with the units, if using inches, stick to using inches. The displacement plots should be in the same units as one started with, and the stresses should be in pounds per square inch (psi). 6.1.1 Geometric Definitions The numerical model contained four parts. The two side plates, double shear specimen, and pin were modeled as deformable 3D solids. Both steel plates along with the double shear specimen were partitioned. The steel collars and center middle plate were neglected for simplicity. All the bolts, nuts and washers were also neglected in the model for simplicity reasons. 6.1.2 Material Creation, Section Assignments, & Meshing All the dimensions were defined in English units and the dimensions for each of the parts came from the fixture design. The fixture used in the numerical model was simplified. All the composite material properties were inputted in the elastic engineering constants. Table 17 showed the material properties, which were, applied to the Aluminum numerical model. A Steel solid homogeneous section and an Aluminum solid homogeneous section were created. 99 A composite layup section was applied to the composite double shear specimen and the element type was set to solid. Table 18 shows the material properties that were applied to the composite double shear specimen. In the composite layup section, the user is able to set the element stacking direction, the coordinate system, and the rotation axis. The user can also specify the laminate orientation and select the region for each ply within the model. In the Appendix, there is a tutorial of how the Abaqus composite double shear specimen was modeled. A single layer of unidirectional carbon fiber material is considered a transversely orthotropic material, where E2 is equal to E3 and G12 is equal to G13. E2 and E3 are both considered the matrix and E1 is considered the fiber. One thing to note was that the compressive modulus in the 1- direction (axial) was slightly lower than the tensile modulus, which was found in the Experimental section of the report. The Poisson\u2019s ratio in the 23-direction and the shear modulus in the 23- direction are usually very difficult to find experimentally. Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager was used to find some of the material properties that could not 100 be found experimentally. In the Appendix, one can find the tutorial on how to use Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager. One can also find a step-by-step Abaqus tutorial on the composite double shear specimen. Parts of the step-by-step tutorial were found from D.S. Mane [29] . The parts were individually partitioned which made meshing them very simple. Once the partition was created, the user needed to use the Seed Edge command, then select whole part, and for method select \u201cby number\u201d. As indicated below in sizing control, the user is able to assign the number of elements from one to however many. The convergence plot was constructed using four different nodes per element. The element\u2019s relative thickness was set to 0.5 since there were only two elements that made up the thickness of the part. 101 6.1.3 Assembly, Interactions & Steps The whole assembly was modeled very similarly to the experiment. Each part was given a dependent instance and no tie constraints were used in the model. A contact step and a load step were added to the analysis. The contact step initiated the contact between the pin and the steel plates and also the pin and the specimen. The load step served to apply load to the analysis once full contact was established. The pin was not constrained to the specimen with a tie constraint because that implied a condition similar to being welded. So in contrast, a surface-to-surface interaction was established between the pin, the steel plates and the specimen. The sliding formulation selected was finite sliding. The pin was set as the master surface and the slave surface consisted of two surfaces. One was the surface in contact with the pin and the inner side of the specimen and the other was the surface in contact with the pin and the inner side of both steel plates. The slave adjustment was set to a value of 0.007 in. A contact property with a tangential behavior (the friction formulation was set to penalty and the friction coefficient was set to 0.46). In addition, a normal behavior contact property with the pressure-overclosure was set to \u201cHard\u201d Contact; constraint enforcement method was set to default, and allowed separation after contact. 6.1.4 Boundary Conditions & Loads The boundary conditions applied to the model needed to be assigned carefully. The top face of the specimen (opposite face with the hole) was fully fixed in the x, y and z directions. This was 102 similar to the clamped condition, which is applied by Instron\u2019s crossheads. The second boundary condition that was applied was on the outer pin surface and the inner hole surfaces of the steel plates and the bearing specimen. In the contact step, the pin, steel plates and specimen were not allowed to move in the x, y and z directions. The load step was modified to allow the side plates, pin and specimen to move in only the y-direction. The combined load of 600 lbs. was applied to both of the bottom faces of the steel plates. This was done by applying the load, in the load step, as a total force distribution pressure load. The loading condition used in the model was similar to the experimental loading condition, where a fraction of the force is applied at each time interval. Some elements in the model experienced plastic deformation only when the applied load was over 800 lbs. This meant that certain elements were in stress state beyond their linear elastic limit. The ultimate force was not predicted, by the numerical analysis, since that occurred in the non-linear region. 6.2 Numerical Results This section provides the explanation of the convergence plot and talks about the factors, which influenced the numerical results. In Chapter 7, the numerical results are explained in detail. 6.2.1 Convergence Plot For the numerical model, a partition was created on the face of the specimen. Taking time to draw a symmetrical and neat partition prevented the mesh from becoming unsymmetrical and 103 prevented unusual results. The partitioned double shear specimen is shown in Figure 49. In Figure 50, one can see a close up of the partitioned region around the hole. After a partition was created, the user was able to assign a specific amount of elements using the Seed Edge command. Here the user is able to set the total amount of nodes per element to any value. For the convergence plot, 2, 6, 8, and 10 nodes per element were chosen, and the final vertical deflection at the pin was compared. A convergence plot was created to see if adding more elements to the model actually improved accuracy. Knowing the optimum amount of elements for the least amount of time for the model to complete is very important in the design process. As one can see from Figure 51, as the total amount of nodes per element increased, the deflection did not change significantly. Using more than six elements per node did not significantly improve accuracy, but it did take longer to run. 6.2.2 Factors That Influenced the Numerical Results Increasing the total amount of elements through the thickness of the part, did not significantly affect the pin deflection results. Changing the axial modulus (from tensile to compressive) significantly affected the pin deflection results. The compressive axial modulus was imported into Abaqus rather than the tensile modulus, because the double shear test is mainly a compression type of loading. The fibers are in compression around the hole. When initially assuming a frictionless contact (when the frictional coefficient equaled zero) the specimen ended up colliding with one of the side plates. Changing the frictionless coefficient 104 from zero to 0.46 helped prevent the specimen from colliding with one of the side plates. 105 106 CHAPTER 7: COMPARISON BETWEEN EXPERIMENTAL & NUMERICAL DOUBLE SHEAR RESULTS The slope of the reaction force vs. pin displacement was compared between both the experiment data and the numerical model. First, the numerical Aluminum model was validated. Then the numerical composite model was validated. 7.1 Numerical Aluminum Model Comparison to Experimental Results Looking at Figure 59, the region highlighted in red was due to the compliance in the testing assembly. The bearing stress vs. bearing strain plot was then converted to a load (reaction force in the y-direction) vs. pin displacement plot. All of the specimens were plotted up until the linear region. Looking at Figure 60, of the five tested Aluminum double shear specimens, the numerical results only matched up with one. The four other Aluminum double shear specimens might have slipped with respect to the extensometer\u2019s knife-edge. One way to tell is by the lower load (reaction force in the y-direction) vs. pin displacement slopes. In Table 19, the total error when comparing the experimental slope to the numerical slope was 16%. Misalignment of the specimen might have caused this significant error to occur. 107 108 7.2 Composite Numerical Model Comparison to Experimental Results Figure 54 showed the load (reaction force in y-direction) vs. pin displacement response of the 0.05 in./min. composite double shear specimens that were cured to the recommended datasheet cure cycle. Three of the eight tested composite double shear specimens at 0.05 in./min. did not slip. The strain was corrected using the same method that was applied to the Aluminum double shear specimens. Of the eight carbon fiber specimens that were tested, only three of them closely matched up to the numerical results. The numerical model was loaded to 600 lbs., which was still within linear elastic limit of the material. The load (reaction force in y-direction) vs. pin displacement slopes between all the experimental specimens shown were compared to the numerical model. In Table 20, the average error between the numerical slope and the experimental slopes was about 7.1%. Alignment is a huge factor, which can affect experimental results quite significantly. There will always be error between the experimental and numerical results. The numerical 109 results are the idealized results and the experimental results have so many factors, which can influence their results. Errors from 7% to 16%, for both the aluminum double specimens and the composite double shear specimens, are actually quite reasonable because there is always error in the manufacturing process, displacement measuring equipment, load cell, specimen alignment exc. 111 CHAPTER 8: CONCLUSION The first important contribution of this study was to see how different loading rates affected the ultimate bearing strength of a composite material. One can see that at 0.05 in./min. and 0.1 in./min. (for both cure cycles) the composite double shear specimens carried more load compared to higher load rates of 1 in./min., 2 in./min. and 6 in./min.. All of the specimens failed in bearing and not in net-tension or shear-out. The second important contribution of this study was to see how the recommended datasheet cure cycle and the alternate cure cycle affected the ultimate bearing strength. The two different cure cycles behaved very similarly under the five different loading rates. The average ultimate bearing strength of the Aluminum double shear specimens was 118 ksi and for the composite double shear specimens it was 65 ksi. The experiment showed that carbon fiber material is significantly weaker, in a double shear tensile loading configuration, compared to Aluminum. Ductile materials, like Aluminum for example, handle the double shear tensile loading configuration a lot better than the carbon fiber material, which is brittle. Each carbon fiber sheet is relatively thin which is also very poor for carrying bearing stress. Usually what designers do is use inserts inside and around the hole if they need to improve the bearing strength of a composite joint. The inserts help redistribute the stress concentrations (which are caused by mechanical fasteners) and prevent the brittle material from cracking. The inserts are usually made from ductile materials, like fiberglass or Aluminum. 112 8.1 Recommendations The experiments were carried out using carbon fiber unidirectional pre-preg tape. Similar research can be done using various other materials like: kevlar, fiberglass, or even hemp. Similar testing can be done using a single shear joint configuration. Various carbon fiber types can be tested as well. MTM-28 material is a thicker type of unidirectional fiber, which would be very interesting to test. A high-speed video camera would be a more efficient way to monitor deflection since the extensometer's range was the limiting factor in the data capture. A more in depth case study can be conducted on different cure cycles of composite resins. The pre-load function in the Bluehill2 software can be utilized in order to try to eliminate some of the strain correction region. In addition, a more in-depth experimental analysis can be conducted on the knee point region of the composite (carbon fiber) double shear specimen. 113 REFERENCES 1. Airbus Versus Boeing-Composite Materials: The sky's the limit. http://www.lemauricien.com/article/airbus-versus-boeing-composite-materials-sky-slimit. 2. Lessard, L.B. (1995). Computer aided design for polymer-matrix composite structures. In S.V. Hoa (Eds.), Design of joints in composite structures. New York: Marcel Dekker. 3. Baker, A. (1997). Composites engineering handbook. In P.K. Mallick (Eds.), Joining and repair of aircraft composite structures. New York: Marcel Dekker. 4. Okutan, B. (2001). Stress and Failure Analysis of Laminated Composite Pinned Joints. Journal of Composite Materials, 19. 5. Chen, J.C., Lu, C.K., Chiu, C.H., & Chin, H. (1994). On the influence of weave structure on pin-loaded strength of orthogonal 3D composites. Composites, 25, No: 4, 251-262. 6. Quinn, W.J., & Matthews F.L. (1977, April). The effect of stacking sequence on the pin- bearing strength in glass fiber reinforced plastic. Journal of Composite Materials, 11, 139- 145. 7. Liu, D., Raju, B.B., & You, J. (1999). Thickness effects on pinned joints for composites. Journal of Composite Materials, 33, 2-21. 8. Stockdale, J.H., & Matthews, F.L. (1976, January). The effect of clamping pressure on bolt bearing loads in glass fiber-reinforced plastics. Composites, 34-39. 114 9. Kim, S.J., & Kim, J.H. (1995). Effects of geometries, clearances, and friction on the composite multi-pin joints. AIAA Journal, 34, No: 4, 862-864. 10. Hyer, M.W., & Klang, E.C. (1985). Contact stresses in pin-loaded orthotropic plates. Journal of Solids and Structures, 21, No: 9, 957-975. 11. Pierron, F., Cerisier, F., & Lermes, M.G. (2000). A numerical and experimental study of woven composite pin-joints. Journal of Composite Materials, 34, No: 12, 1028-1053. 12. Chang, Fu-Kuo, Scott, R.A., & Springer, G.S. (1982, November). Strength of mechanically fastened composite joints. Journal of Composite Materials, 16, 470-494. 13. Ger, G.S., Kawata, K., Itabashi, M.: Dynamic tensile strength of composite laminate joints fastened mechanically. Theor. Appl. Fract. Mech. 24(2), 147\u2013155 (1996). 14. Li, Q.M., Mines R.A.W., Birch R.S. (2000, September). Static and dynamic behavior of composite riveted joints in tension. 15. United States Naval Academy (USNA). (2003). Composite Orientation Code. http://www.usna.edu/Users/mecheng/pjoyce/composites/Short_Course_2003/7_PAX_Sh ort_Course_Laminate-Orientation-Code.pdf 16. Kretsis, G., & Matthews, F.L. (1985, April). The strength of bolted joints in glass fiber/epoxy laminates. Journal of Composite Materials, 16, 92-102. 17. Yeole, Amit. (2006, December). Experimental Investigation and Analysis for Bearing Strength Behavior of Composite Laminates. 115 18. Anonymous, \u201cStandard Test Method for Bearing Response of Polymer Matrix composite Laminates,\u201d ASTM Standards, Designation: 5961/5961M-05. 19. Anonymous, \u201cStandard test method for tensile properties of fiber-resin composites,\u201d ASTM Standards, Designation: 3039-76. 20. Anonymous, \u201cStandards. In-plane shear stress-strain response of unidirectional reinforced plastics,\u201d ASTM Standards, Designation: 3518-76. 21. Umeco, \u201cMTM 49 Series Pre-preg System \u2013 Unidirectional Material Properties.\u201d 22. Cytec, \u201cMTM 49-3 \u2013Unidirectional Material Properties.\u201d 23. Instron, \u201cInstron 8801 Servo-hydraulic Machine Photo.\u201d http://www.instron.us/en-us/ 24. Nettles, A.T., (1994, October) \u201cBasic Mechanics of Laminated Composite Plates.\u201d 25. ASM Aerospace Specification Metals Inc., \u201cDatasheet Mechanical Properties of Aluminum 2024-T4.\u201d 26. Anonymous, \u201cProject 1 Report\u201d ME-412. 27. Anonymous, \u201cStandard test method for ignition loss of cured reinforced resins,\u201d ASTM Standards, Designation: 2584-02. 28. Xiao, Yi. \u201cBearing strength and failure behavior of bolted composite joints (part II: modeling and simulation). 29. De, S. MANE 4240/CIVL 4240: Introduction to Finite Element. Abaqus Handout. 30. Semb, Evind. \u201cBehavior of Aluminum at Elevated Strain Rates and Temperatures.\u201d 116 APPENDICES A.1. Drawings for the Fixture Assembly 117 118 A.2. Tutorial on Bluehill2 Test File Setup Various settings were changed inside the BlueHill2 software. Below, I will show a couple of the parameters that were changed. Navigating through the menus is self-explanatory. In the Control submenu, the load rate was changed for each test. The quasi-static case was tested first at a load rate of 0.05 in./min. The second load rate, which was tested, was 0.1 in./min., the third was 1 in./min., the fourth was 2 in./min. and the fifth speed, which was tested, was 6 in./min. 119 The end of test criteria was changed to the ASTM specification. End of test 1 specifies the drop in the load of 30% the peak value and end of test 2 is specified as an extensometer displacement of 0.1 in. The extensometer shows up at Displacement (Strain 1) as a separate channel. 120 In the Control submenu, the sampling rate was changed from the default rate of 10 samples/sec to 3 samples/sec as required by ASTM D5961. This change showed a significant reduction of noise within the extensometer displacement readings. A value of 500 ms was adjusted for the time channel and the load sampling rate was left to default interval of 56 lbf. 121 Below in the Control submenu, the source of tensile strain was changed from the BlueHill2 default channel of \u201cTensile Strain\u201d to the \u201cStrain 1\u201d. The extensometer shows up as \u201cStrain 1\u201d. 122 Bluehill2 also has the option of calculating numerous parameters. In my experimental testing, I needed to calculate the ultimate bearing strength so I picked User Calculation. Then Bluehill2 gives you an option to define various variables like: D (diameter of hole), k (calculation factor for double shear k = 1), Pmax (maximum force carried by the specimen prior to failure), and t (defined as the thickness of the laminate). After all of your variables are defined, the equation designer tool 123 is used to create your equation of interest. In the Results submenu, the user is able to pick exactly which values he/she wants to output while in the test screen. The results are outputted as a column of values for each of the different test specimens. I wanted to output all of these parameters below while I was conducting my tests. 124 In the Graph submenu, the user is able to output two real-time changing graphs. For graph 1, I chose to output Instron crosshead displacement vs. load and for graph 2 I chose to output extensometer displacement vs. load. The X-Data was set to either Extension (for Instron crosshead displacement) or Displacement (Strain 1) (for extensometer displacement. The Y-Data was set to Load for both graph 1 and graph 2. 125 In the Raw Data submenu, Bluehill2 has a great function, which allows the user to export any given output of experimental data into a .csv file. This file can later be opened up with Excel and used to calculate various experimental stresses, strains and other parameters of interest. For my experimental testing, I was interested in outputting: time, crosshead displacement, extensometer 126 displacement, load and corrected position. The last bit of raw data, which needed to be outputted, is shown below. This set of data is saved onto the same .CSV file as the one specified in the previous screen. This set of data is located in its own set of two columns in the .CSV file. 127 A.3. Tutorial on Finding the Unknown Engineering Constants Autodesk created a very powerful tool, which can help the user figure out unknown engineering constants of a ply. For example from the experimental results, the user is able to experimentally determine E1, E2, G12 and \u03c512. Shown below are all the values, which the user inputs into the Autodesk Simulation Composite Analysis 2015 Material Manager. Make sure to label the 128 material a unique name and choose the correct units. The fiber type should be carbon intermediate for the MTM 49 since it is not the ultra-high fiber modulus. The volume fraction should be the one, which was found experimentally in the Results chapter, of 0.55. In Figure 67, in the first row of the Ultimate Lamina Strengths the user inputs the tensile strength in the 0\u00b0 and the 90\u00b0 directions. In the second row, the user inputs the compressive strength in the 0\u00b0 and 90\u00b0 directions and finally, in the last row, the user the user inputs the in-plane shear strengths. 129 In Figure 68, the user will input the known modulus of elasticity into the Lamina Elastic Constants section. The in-plane Poisson's ratio, which was assumed to be around 0.244, was used from a previous paper, which found the material property experimentally on the same MTM 49 Unidirectional material. The in-plane shear modulus was inputted from the experimental testing. 130 The key is to assume a value if you do not know what it is. After all the values have been inserted into the program go into the File, menu and then click optimize. It will ask you if you want to save the material properties somewhere and all you do is specify where you want to save the data. It will take a couple seconds to optimize the values accordingly. A.4. Tutorial on Outputting Force vs. Pin Deflection from Abaqus The pin deflection needed to be monitored for one node on the specimen. The area of interest is shaded in dark blue and the red dot signifies which node was monitored for its vertical deflection. In Figure 70, one can see the deflection in the y-direction, which occurs around the hole. This hole 131 is a localized compression zone. 132 Next what was needed was to have a force vs. time graph. The top most nodes on the specimen were fixed using the encastre boundary condition. The reaction force in the y-direction was captured for all the nodes that make up the top of the specimen. Once all the reactions at each nodes were captured, the whole region was summed up. Under create XY plot click ODB field output and then click continue. Under the Variables tab, find the Output variable box, and in the position menu, click Unique Nodal and then go into RF: Reaction Force and check the RF2 button. Since we are interested in the reaction force in the y-direction (2 direction). Next, click the Elements/Nodes tab and then pick the from viewport button and then click Edit Selection. Once all the fixed nodes are selected, as shown in Figure 72 below, click the Done button in the viewport. Lastly, go into Active Steps/Frames; make sure All steps are selected and set it to Frame. In the bottom of the window, make sure a green checkmark is applied to both the Contact and the Load steps. 133 Using the Create XY Data option in Abaqus, the user is able to go into Operate on XY data. In the Operators window, pick sum((A,A,...)), then under XY data, select all the Reaction Force nodes, which show up as _RF:RF2 and then click Add to Expression. Once all the nodes are inside the Sum operator, hit the Plot Expression button. This will output a force vs. time graph. 134 Once both the force vs. time graph and deflection vs. time graph are created, one needs to combine both graphs. In the Create XY Data, click Operate on XY Data and then press Continue. Under the operator tab, find combine(X,X) and then click it once. The combine operator requires two variables for the plot. For the first variable, click the deflection XY data, and for the second variable, click the Reaction Force 2 XY data. Make sure a comma separates both variables. Once done click the plot expression button and this should bring up a Force vs. Pin Deflection plot as shown in Figure 74. 135 A.5. Tutorial on Modeling the Double Shear Bearing Specimen Assembly Open up Abaqus 6.14. The numerical model should look like something like this. The complete assembly, the pin and one of the side plates modeled with Abaqus 6.14. 136 A.5.1. Model Creation Create a new model by right clicking the Models category. Name it DoubleShear. Then press Ok. 137 A.5.2. Part Creation Next, we have to create the parts for the model, after that, we partition each of the parts. Click on the + button to expand the options inside the DoubleShear model. Right click on Parts and press Create. A menu will appear like the one shown below. Name the part SteelPin. Keep the modeling space: 3D, the type: deformable, the base feature shape: Solid and for the base feature type: Extrusion. Click continue. 138 Click the Create Circle button. Using the dimension tool below set the radius to 0.125 in. Always be consistent with your units (I am using inches). 140 Next, we need to create the double shear specimen. Copy the step above and only change the name of the part to Specimen. Use the rectangle tool (to the right of the circle tool) and make a basic rectangle. 141 Using the dimension tool set the width of the part to 1.5 in. and the length of the part to 5.5 in. Create a Line down the middle of the part. Locate the center of hole 0.75 in. from the bottom edge of the specimen and make sure the hole is centered along the specimen\u2019s width. 142 Now, delete the centerline with the eraser tool, which is highlighted and then click on the centerline (which should highlight in red) and click done. Click the eraser tool to disable it. 143 In the bottom of the drawing window, it should read, \u201cSketch the section for the solid extrusion\u201d. Click the Done button. Set the depth to 0.1 in. Since the carbon fiber specimen\u2019s thickness was 0.1 in. Next, we need to create the side steel plate. Copy the step above and only change the name of the part to SidePlate. Use the rectangle tool (to the right of the circle tool), make a basic rectangle, and use the circle tool to create a hole in the plate. The side steel plate should be 2 in. by 4 in. and it should have a 0.141 in. radius hole. Which is located 1.0 in. from the top of the side plate. Lastly, remove the centerline and then set the depth to 0.25 in. Since the side steel plates had a thickness of 0.25 in. The three parts should look like this once they are completed. 144 A.5.3. Partition Creation A partition was created on the side plates and on the specimen. This made sure that when the mesh was generated all the elements stayed symmetrical. One major source of error in finite element analysis is due to elements not being symmetrical and the same size. One way to avoid this problem is to create your own mesh, which requires the user to partition the part based on what is of interest to him/her. Pick Tools, in the top drop down menu, and choose Partition. Click Face for the partition type and then click on the side plate face highlighted in orange. 145 Click Done and then it will ask to click a line vertical and to the right. Shown below, the highlighted edge is shown in pink, and the non-highlighted edges are shown in red. The part will switch from 3D to 2D and then here the user is able to create the partition desired. Create the partition below with these dimensions using the circle and line tools. It is important to keep the mesh coarse on parts which are not of main interest. 146 Apply the same method to the double shear specimen. The partition on this specimen was a lot more detailed than on the steel side plate. There are six circles, which are all equally spaced apart. The three outer radii were 0.5 in., 0.375 in., and 0.625 in. The three inner radii were 0.1875 in., 0.25 in., and 0.3125 in. A finer partition was created on the three inner radii where the circle was segmented into 64 equally spaced smaller sections. 147 The final partitioned parts should look like this. 148 A.5.4. Material Creation The material properties need to be created. Two materials were used in the analysis: steel and a unidirectional carbon fiber material. Under the Parts category, right click and click create. Name the material Steel. Go into the Mechanical option, then press elasticity, then elastic. Keep the type set to a default isotropic setting. Set the Young\u2019s Modulus to 34e6 and set the Poisson\u2019s ratio to 0.3. Follow the step right above, and create a new material and name it Uni. For the type, select 149 Engineering Constants. Include the material properties in the Table below (remember that msi is 106 psi)." + ] + }, + { + "image_filename": "designv8_17_0000292_download_70511_39859-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000292_download_70511_39859-Figure1-1.png", + "caption": "Figure 1. a CB subjected to concentrated end load and tip moment", + "texts": [ + " However, the ADM needs too many algebraic computations to achieve the required accuracy for more complicated loading conditions. Consider an inextensible slender CB of length L with a constant flexural stiffness EI subjected to a concentrated non-follower end load P inclined with an angle \u03b4 measured from the positive x-axis and tip-moment M(L). These loading conditions are presented in the global (x, y) coordinate-system, where the curved coordinate along the deflected axis of the beam is denoted by the arc length , as shown in Fig. 1. The concentrated end force P is decomposed into two components Fx and Fy. Considering the free body diagram of the right segment of the beam, where the length of this segment becomes (L-s), as shown in Fig. 2. Since the beam weight is assumed to be neglected, the horizontal and vertical static equilibrium equations lead that the components Fx and Fy are independent of the arc length . However, the internal bending moment is a function of the arc length , as shown in Fig. 3. In this figure, \u03b8 represents the angle of rotation of the beam with respect to the positive x-axis and ds denotes the length of infinitesimal element of the beam", + " Hence, the moment equilibrium equation of the beam can be written as dM dy dx F Fx yds ds ds = \u2212 \u2212 (1) where sin( ( )), cos( ( )) dy dx s s ds ds \u03b8 \u03b8= = (2) ( ) ( ) d s M s EI ds \u03b8 = (3) s s s Differentiating both sides of Eq. (3) with respect to the arc length and substituting the resultant relation into Eq. (1) lead to 2 ( ) sin( ( )) cos( ( ))2 d s EI F s F sx y ds \u03b8 \u03b8 \u03b8= \u2212 \u2212 (4) This differential equation governs the large deflection of the prismatic CB in terms of the slope of the beam ( )s\u03b8 and the arc length , as shown in Fig. 1. The components of the inclined load P can be written as cos( ), sin( )F P F Px y\u03b4 \u03b4= = (5) Substituting Eq. (5) into Eq. (4) yields 2 ( ) 2 sin( ( ) )2 d s s ds \u03b8 \u03c9 \u03b8 \u03b4= \u2212 + (6) where 2 P EI \u03c9 = (7) The beam under consideration is associated with the following boundary conditions (0) 0\u03b8 = (8) ( ) ( ) s L d s M L ds EI \u03b8 = = (9) Where M(L) is the external moment applied at the free end of the beam. Although Eq. (6) is straightforward in appearance, it is in fact rather difficult to solve because of the nonlinearity term sin( ( ))s\u03b4 \u03b8+ " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003300_1.27.477984.full.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003300_1.27.477984.full.pdf-Figure4-1.png", + "caption": "Fig. 4 Instantaneous PECT and SUPRA force vectors over a flapping cycle. Results of wrist-centered 237\u00a0 model variations (median of the forces obtained for the four wrist-centered model variations, estimated at 238\u00a0 each time instant) are shown as an example. (a) Summary of four views, where PECT (blue) and SUPRA 239\u00a0 (red) force vectors are shown in (b) Dorsal (back) view towards the ventral body side, illustrating wing 240\u00a0 deviation torque creation (approximately); (c) Wing tip view in wing fixed frame from wing wrist towards the 241\u00a0 shoulder, illustrating wing pitching torque creation; (d) Caudal (bottom) view towards the bird\u2019s head from 242\u00a0 tail, illustrating wing stroking torque creation; and (e) Left view, illustrating PECT force directions on the 243\u00a0 sagittal plane. Total ten time instants of the flapping cycle are shown (0% corresponds to the start of 244\u00a0 upstroke and 50% corresponds to the start of downstroke). Points O (black), SB (red), and PB (blue) 245\u00a0 represent the shoulder joint, insertion points of SUPRA and PECT on the body skeleton, respectively. Also 246\u00a0 shown are the trajectories of the humerus insertion points of PECT (blue) and SUPRA (red), progressing 247\u00a0 over the flapping cycle, where PH and SH represent the corresponding insertion points at the mid-248\u00a0 downstroke instant. The dotted grey lines PH-PB and SH-SB in (d) and (e) represent the straight line 249\u00a0 connecting muscle insertion points on the wing skeleton and body skeleton during mid-downstroke. Note 250\u00a0 that the insertion point trajectories and skeletons in (b), (c), (d), and (e) (unmagnified) are scaled as per the 251\u00a0 1 mm scale. The silhouette of the wing skeleton represents the mid-downstroke position (approximately 252\u00a0 75% of the flapping cycle). The force vectors are scaled so that their length is proportional to their 253\u00a0 magnitude. The magnified illustrations are exactly twice the size of the unmagnified illustrations. 254\u00a0 255\u00a0", + "texts": [ + " Hummingbird 221\u00a0 pectoralis, instead, starts to produce force towards the end of the muscle lengthening phase with a short 222\u00a0 active lenthening, followed rapidly by the force peak in the beginning of muscle shortening phase. 223\u00a0 PECT and SUPRA instantaneous force vectoring 224\u00a0 In all hypothesized wing-actuation model variations, both PECT and SUPRA force directions were allowed 225\u00a0 to rotate linearly (with respect to the instantaneous straight-line PH-PB connecting muscle insertion points 226\u00a0 on the wing skeleton and body skeleton, Fig. 4d-e) with the progression in the flapping cycle, in accordance 227\u00a0 with the anatomical features. Results show that at the beginning of downstroke, PECT force direction was 228\u00a0 oriented ventrally by 46o (median, range 38o to 48o) from the straight-line PH-PB (Fig. 4d-e, see Appendix 229\u00a0 and Movies S1, S2, and S3). During downstroke, PECT force rotated dorsally and became almost aligned 230\u00a0 with PH-PB towards the end. Similarly, at the beginning of upstroke, SUPRA force was oriented dorsally by 231\u00a0 57o (median, range 39o-88o) from SH-SB (Fig. 4d-e) and became more aligned with SH-SB (median 9o, 232\u00a0 range 0o-44o) at the end of upstroke. Overall, the vectoring of PECT and SUPRA forces show highly 233\u00a0 elaborated spatiotemporal patterns (Fig. 4), which are more prominent than those observed in other birds 234\u00a0 such as pigeons [31]. As a result, they lead to highly three-dimensional wing actuation torque described 235\u00a0 below. 236\u00a0 .CC-BY 4.0 International licenseavailable under a (which was not certified by peer review) is the author/funder, who has granted bioRxiv a license to display the preprint in perpetuity. It is made The copyright holder for this preprintthis version posted January 28, 2022. ; https://doi.org/10.1101/2022.01.27.477984doi: bioRxiv preprint \u00a0\u00a010\u00a0 ", + " The hummingbird pectoralis can pull the 376\u00a0 humerus more caudally (tailward) and dorsally compared with, for example, pigeons [26,56], thereby 377\u00a0 directing the pectoralis force more tailward for larger wing depression (deviation) torque (Movie S3). This 378\u00a0 appears to be enabled by a more caudal orientation of the pectoralis muscle fibers or a more caudal 379\u00a0 insertion of the pectoralis on the sternum. Such anatomy is necessary to balance the larger lift-induced 380\u00a0 wing elevation torque, as hummingbirds hover with an upright body posture. On the other hand, the bicipital 381\u00a0 crest on humerus, where the pectoralis aponeurosis wraps around, prevents an excessive caudal 382\u00a0 redirection of the force (Fig. 4e), ensuring proper distribution of the force into creating both stroking and 383\u00a0 deviation torque (a direct connection between the pectoralis insertion points on the humerus and sternum 384\u00a0 .CC-BY 4.0 International licenseavailable under a (which was not certified by peer review) is the author/funder, who has granted bioRxiv a license to display the preprint in perpetuity. It is made The copyright holder for this preprintthis version posted January 28, 2022. ; https://doi.org/10.1101/2022.01.27", + " 554\u00a0 4d). We used two variables (\ud835\udf03 and \ud835\udf03 , see Appendix) to represent the overall 3D rotation of PECT force 555\u00a0 .CC-BY 4.0 International licenseavailable under a (which was not certified by peer review) is the author/funder, who has granted bioRxiv a license to display the preprint in perpetuity. It is made The copyright holder for this preprintthis version posted January 28, 2022. ; https://doi.org/10.1101/2022.01.27.477984doi: bioRxiv preprint \u00a0\u00a022\u00a0 vector from its nominal direction (PH-PB, Fig. 4d). Similar to PECT, SUPRA force vector was assumed to 556\u00a0 lie tangent to the muscle tendon at the humerus insertion point (red vector in Fig. 1ci) and that the tendon 557\u00a0 has non-zero bending. The final force vector was found by rotating the nominal vector SH-SB (Fig. 4d) in 558\u00a0 the tendon plane by \ud835\udf03 (see Fig. A3 and Appendix). Both the muscles were modeled using arcs along their 559\u00a0 aponeurosis connecting their two insertion points on the body and humerus, being tangent to their muscle 560\u00a0 force direction at the humerus. Accordingly, the muscle length was then calculated as the arc length (see 561\u00a0 Appendix), which was also used as a length measure for calculating the passive muscle force due to the 562\u00a0 parallel spring. Note that the length of muscle fascicles is proportional to this estimated muscle length, 563\u00a0 assuming that the pennation angle of the fascicles with respect to aponeurosis remains constant throughout 564\u00a0 the flapping cycle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004419_f_version_1590033766-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004419_f_version_1590033766-Figure4-1.png", + "caption": "Figure 4. Bending moments generated by the axial and radial force.", + "texts": [ + " Bearing Function in IWM Integration of a hub bearing unit into the in-wheel motor is objected to ensure the rotation whereas offering required stiffness to support axial and vertical loads as shown in Figure 3. Figure 3. Axial and radial loads acting on rear wheels of a vehicle. Vertical loads are directed opposite to gravitational force, whereas axial loads occur in the cornering direction. The bearing is most affected by the bending moment resulting from the lateral (cornering) force, defined as MX-Y, which acts via pneumatic tire\u2019s effective rolling radius and rim, as shown in Figure 4. FY is shown as an example for left cornering shown as FY-L in Figure 3. Figure 4. Bending moments generated by the axial and radial force. Moment MX-Z is much smaller since it is resulting from the vertical force and the small distance from the tire center to the point of rotational deflection. As identified, the most critical loads are severe braking, cornering and driving over a road pothole/obstacle causing an impact load. MX-Z from vertical impacts or MX-Y from severe cornering can reach values that result in large deflection angles and should be anticipated during the design stage", + " The objective of every brake manufacturer is to design a braking assembly, which will be functional and not affect wheel rotation during severe cornering. Figure 3. Axial and radial loads acting on rear wheels of a vehicle. Sustainability 2020, 12, 4070 3 of 18 Vertical loads are directed opposite to gravitational force, whereas axial loads occur in the cornering direction. The bearing is most affected by the bending moment resulting from the lateral (cornering) force, defined as MX-Y, which acts via pneumatic tire\u2019s effective rolling radius and rim, as shown in Figure 4. FY is shown as an example for left cornering shown as FY-L in Figure 3. Sustainability 2020, 12, x FOR PEER REVIEW 3 of 18 The following chapters deal with the identification of bearing function, loads acting on it, stiffness evaluation with numerical and experimental approach as well as validation on bearings and assembled IWM. 2. Bearing Function in IWM Integration of a hub bearing unit into the in-wheel motor is objected to ensure the rotation whereas offering required stiffness to support axial and vertical loads as shown in Figure 3. Figure 3. Axial and radial loads acting on rear wheels of a vehicle. Vertical loads are directed opposite to gravitational force, whereas axial loads occur in the cornering direction. The bearing is most affected by the bending moment resulting from the lateral (cornering) force, defined as MX-Y, which acts vi pneumatic tire\u2019s effective rolling radius and rim, a shown in Figure 4. FY is shown as an example f left cornering shown as FY-L in Figure 3. Moment MX-Z is much smaller since it is resulting from the vertical force and the small distance from the tire center to the point of rotational deflection. As identified, the most critical loads are severe braking, cornering and driving over a road pothole/obstacle causing an impact load. MX-Z from vertical impacts or MX-Y from severe cornering can reach values that result in large deflection angles and should be anticipated during the design stage. Hub bearing deflection is less problematic for conventional vehicle corners, where the deflection acts on the movement of disc brake towards braking pads inside the caliper (Figure 5). The objective of every brake manufacturer is to design a braking assembly, which will be functional and not affect wheel rotation during severe cornering. Figure 4. Bending moments generated by the axial and radial force. Moment MX-Z is much smaller since it is resulting from the vertical force and the small distance from the tire center to the point of rotational deflection. As identified, the most critical loads are severe braking, cornering and driving over a road pothole/obstacle causing an impact load. MX-Z from vertical impacts or MX-Y from severe cornering can reach values tha result in large deflection angles and should be anticipated during the design stage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure4.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure4.2-1.png", + "caption": "Figure 4.2 : Electric Motor 3D section view (from WP1).", + "texts": [ + " This joint work of both Work-Packages allowed the determination of a maximum value of this equivalent thermal constraint according to cooling configurations to design high-specific motors (EM2025 and EM2035). The proposed cooling for EM2025 and EM2035 respectively enabled the design of a high specific power electric motor with 2\u00d71012 A2\u00b7m3 and 5\u00d71012 A2\u00b7m3 as thermal constraint values. 4.2.2 Motor Design and Sizing A three-dimensional (3D) section of the Electric Motor for 2025 (EM2025) designed for the first target provided by WP1 is depicted in Figure 4.2. The electric motor design is of SMPMSM type with distributed windings forming a wreath at each extremity. The motor section shows the core geometry of the e-motor with its components. E-motor data are presented thereafter. 4.2.2.1 Electric Motor Characteristics Developed by the WP1 group, the electrical design of the motor and corresponding data with their maximum values are gathered in Table 5.1. The losses values in Table 5.1 are the maximum level of heat sources in the thermal model. For a steady-state simulation, they can be used to estimate a continuous full-power operating motor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000752_el-04725201_document-Figure2.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000752_el-04725201_document-Figure2.5-1.png", + "caption": "FIGURE 2.5 : Sch\u00e9ma du r\u00e9sonateur T-line.", + "texts": [ + " La technique du T-r\u00e9sonateur n\u2019est pas applicable sur une large plage de fr\u00e9quences, ce qui implique la non possibilit\u00e9 de caract\u00e9riser les mat\u00e9riaux di\u00e9lectriques sur une gamme \u00e9tendue de fr\u00e9quences. Il est uniquement possible de d\u00e9terminer \u03f5r et tan\u03b4 aux fr\u00e9quences de r\u00e9sonance visibles sur le coefficient de transmission. \u00c9tant donn\u00e9 que notre utilisation est majoritairement ax\u00e9e sur des antennes et des circuits microruban dans la bande Wi-Fi, cette m\u00e9thode est donc appropri\u00e9e. Pour maintenir une coh\u00e9rence avec les futures r\u00e9alisations, la structure sera compos\u00e9e d\u2019un substrat en PLA, d\u2019un plan de masse en cuivre et d\u2019un conducteur en filament Electrifi (figure 2.5). Notons que le plan de masse en ruban adh\u00e9sif de cuivre est utilis\u00e9 pour des raisons \u00e9conomique et d\u2019efficacit\u00e9. De plus, \u00e9tant donn\u00e9 que les plans de masse ne comporterons aucune structure complexe, il n\u2019est pas n\u00e9cessaire d\u2019utiliser l\u2019imprimante 3D pour le r\u00e9aliser en filament Electrifi. Il est important de prendre en compte la sensibilit\u00e9 aux interf\u00e9rences externes lors des mesures. Les variations de temp\u00e9rature, d\u2019humidit\u00e9 et d\u2019autres conditions environnementales peuvent alt\u00e9rer les mesures de r\u00e9sonance, entra\u00eenant ainsi des erreurs dans les r\u00e9sultats de mesure", + "5 pour calculer la longueur du stub. Il est \u00e0 noter que la premi\u00e8re r\u00e9sonance influence la densit\u00e9 des donn\u00e9es sur la plage de fr\u00e9quences, puisque les fr\u00e9quences de r\u00e9sonance suivantes seront des harmoniques de celle-ci. 47 CHAPITRE 2 - M\u00c9THODOLOGIE DE CONCEPTION D\u2019UNE RECTENNA EN IMPRESSION 3D L = c 4f \u221a \u03f5eff (2.5) Pour notre structure de substrat, nous reprenons la longueur du stub utilis\u00e9 dans les travaux de F. Pizarro [89] car ils utilisent la m\u00eame structure (PLA et Electrifi) et travaille \u00e0 une fr\u00e9quence proche (2,5 GHz) (figure 2.5). Les param\u00e8tres d\u2019impression sont d\u00e9crits dans le tableau 2.5 et seront utilis\u00e9s dans toute la suite des travaux. Pour le PLA, les informations fournies par le constructeur ont \u00e9t\u00e9 utilis\u00e9es. En ce qui concerne le filament Electrifi, plusieurs tests d\u2019impression ont \u00e9t\u00e9 effectu\u00e9s, conform\u00e9ment aux travaux de Striker et al. [117]. Les dimensions du dispositif r\u00e9alis\u00e9 sont : Wsub = Lsub = Lligne = 100mm, Wligne = 4, 5mm, LT \u2212ligne = 58, 5mm, hcond = 1mm et hsub = 2, 1mm. Apr\u00e8s r\u00e9alisation, une mesure du coefficient de transmission |S21| est effectu\u00e9e \u00e0 l\u2019aide du PNA-X N5241A" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004034_f_version_1579780510-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004034_f_version_1579780510-Figure3-1.png", + "caption": "Figure 3. Schematic diagram of auxiliary slot in rotor.", + "texts": [ + " A PMSM with this kind of magnetic pole usually has the disadvantages of large cogging torque, large leakage and poor flux weakening capability [16]. Therefore, a novel SIPMSM is developed, as shown in Figure 2. The permanent magnet in the novel SIPMSM is an unequal thickness magnetic pole with different inner and outer radians, which results in the uneven distribution of the radial air-gap flux density and remarkable magnetic congregate effect. In order to reduce the leakage flux and the high harmonic content in the air-gap, an auxiliary slot is notched in the rotor, as shown in Figure 3. Symmetry 2020, 12, x FOR PEER REVIEW 3 of 14 2. The Proposed SIPMSM 2.1. Structure Design The shape of magnetic pole effects the output characteristics of PMSM directly. The permanent magnet of typical SIPMSM is a tile shape with inner and outer arc centers at the same point\u2014as shown in Figure 1. A P SM with this kind of magnetic pole usually has the disadvantages of large cogging torque, large leakage and poor flux weakening capability [16]. Therefore, a novel SIPMSM is developed, as shown in Figure 2. The permanent magnet in the novel SIPMSM is an unequal thickness magnetic pole with different inner and outer radians, which results in the uneven distribution of the radial air-gap flux density and remarkable magnetic congregate effect. In order to reduce the leakage flux and the high harmonic content in the air-gap, an auxiliary slot is notched in the rotor, as shown in Figure 3. Figure 1. Schematic diagram of typical SIPMSM and tile shape magnetic poles. (a) Schematic diagram of traditional SIPMSM; (b) Schematic diagram of tile shape magnetic poles. (a) (b) Figure 2. Schematic diagram of the novel SIPMSM and unequal thickness magnetic poles. (a) Schematic diagram of the novel SIPMSM; (b) Schematic diagram of unequal thickness magnetic poles. i re 1. Schematic diagram of typical SIPMSM and tile shape magnetic pol s. (a) Schematic diagr m of traditional SIPMSM; (b) Schematic diagr m of tile shape magnetic poles", + " A PMSM with t is kind of magnetic pole usually has the disadvantages of large cogging torque, large leakage and po r flux weakening capability [16]. Therefore, a n vel SIPMSM is developed, as shown in Figure 2. Th perm nent magnet in the novel SIPMSM is an unequal thickness magnetic pole with different inner and outer radians, which results in the uneven distribution of the radial air-gap flux density and remarkable magnetic congregate effect. In order to reduce the leakage flux and the high harmonic content in the air-gap, an auxiliary slot is notched in t rotor, s shown in Figure 3. (a) (b) Figure 2. Schematic diagram of the novel SIPMSM and unequal thickness magnetic poles. (a) Schematic diagram of the novel SIPMSM; (b) Schematic diagram of unequal thickness magnetic poles. i re 2. Schematic diagram of the novel SIPMSM and unequal thickness magnetic poles. (a) Schematic diagram of the novel SIPMSM; (b) Schematic diagram of unequal thickness magnetic poles. Symmetry 2020, 12, 179 4 of 14 Symmetry 2020, 12, x FOR PEER REVIEW 4 of 14 According to the performance requirements of PMSM for electric vehicles, the structure parameters of the novel SIPMSM are determined by using the empirical formula (see Table 1)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004625_16_01_smdo160007.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004625_16_01_smdo160007.pdf-Figure14-1.png", + "caption": "Figure 14. Graph showing the evolution of the load on bolt when tightening with a tensioner.", + "texts": [], + "surrounding_texts": [ + "This is the most accurate way to obtain the real final tightening load Fo (Figure 16). However, it is also the most expensive. It requires time, additional equipment, calibration tests, further machining and must be carried out by specialists. Possibly, not all the requirements could be implemented." + ] + }, + { + "image_filename": "designv8_17_0002436_3272-023-00710-w.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002436_3272-023-00710-w.pdf-Figure12-1.png", + "caption": "Fig. 12 Vertical profiles and CAS", + "texts": [ + " In addition, the idle descent regime can be clearly seen here. Figure\u00a011 depicts the impact of varying wind shear. The linear wind gradient assumed here has no effect on the minimum flight time. However, it significantly affects the fuel consumption, with negative wind shear (meaning stronger headwind at higher altitude) resulting in higher fuel consumption than positive wind shear (meaning stronger headwind at lower altitude) for this descent segment. The effect is more pronounced at high speeds than at low speeds. Figure\u00a012 shows the vertical profiles of a set of 167,571 fuel-minimal trajectory segments, color-coded by CAS. We ask the sophisticated reader to excuse the rasterized nature of this depiction, which makes it impossible to discern all individual lines but occupies less storage, and point out the diversity of the flight paths resulting from parameter variation. These range from almost straight to stepwise climb and descent profiles; the latter are in principle undesirable as CCO/CDO can yield higher efficiency [5], but the prescribed variation of the flight duration forces the trajectories to assume such shapes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003142_0245-024-10117-6.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003142_0245-024-10117-6.pdf-Figure3-1.png", + "caption": "Fig. 3 Representation of the computed optimal deformation (indistinguishable from the target configuration) and the contour plot distribution of \u03bb\u03021 ( \u22121(x) ) , for the beam with rectangular section in Fig. 2a for target configurations: a equation (5.14); b equation (5.15). The translucid configuration represents the undeformed configuration 0", + "texts": [ + "14) (ii) Shapemorphing configuration 2: rectangular cross-section beamwith target configuration given by d(X) = [ L 2\u03c0 sin ( 2\u03c0X1 L ) , X2, \u2212 L 2\u03c0 cos ( 2\u03c0X1 L )]T . (5.15) (iii) Shape morphing configuration 3: circular cross-section beam with target configuration given by d(X) = \u23a1 \u23a2\u23a2\u23a3 \u2212(R f + cos \u03b8)r cos ( 2\u03c0X1 L f + \u03c0L 4 ) (R f + cos \u03b8)r sin ( 2\u03c0X1 L f + \u03c0L 4 ) \u2212 6 r sin \u03b8 + X1L f L + 2 \u23a4 \u23a5\u23a5\u23a6 , (5.16) with R f = 6 and L f = 4, and with (r , \u03b8) given by r = \u221a X2 2 + X2 3, tan \u03b8 = X3 X2 . For the case of the rectangular cross-section beam in Fig. 2a, the final configurations attained at convergence are depicted in Fig. 3, correspondingwith the optimal solutions that yield the closest growth-driven configurations to the target configurations denoted as shape morphing configurations 1 and 2. In addition, Fig. 4 depicts the evolution of the cost function for the case of the shape morphing configuration 1. The interior-point algorithm has been used as the optimization method. With regard to the circular cross-section beam in Fig. 2b, with target configuration given in Eq. (5.16), the final growth-driven configuration is displayed in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004765_-IJERTV9IS080317.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004765_-IJERTV9IS080317.pdf-Figure5-1.png", + "caption": "Fig. 5 Analysis of knuckle ( Total deformation)", + "texts": [], + "surrounding_texts": [ + "There are many reasons for a vehicle to lose its controllability: unfavorable weather and road conditions, lack of regular vehicle care, maintenance and repair, the driver\u2018s inexperience, sharp cornering (when passing an obstacle or underestimating a curve). A vehicle will react in a different way when the driver steers smoothly, or when the vehicle slightly declines from the lane. Loss of stability of a vehicle may cause its skidding on the road.In above mention conditions for the safety and comfort of an automobile as well as driver, stability is the major concern which needs to be considered. II. INTRODUCTION Variable Roll Stiffness System of an Automobile is a system which provides varying roll stiffness, adequate stability as well as prevents the rolling of vehicle while excessive turning. By observing the current road scenario it becomes mandatory to understand vehicle behavior in accordance with respective road conditions. Imperative condition to co-relate the vehicle behavior with different road condition is that, vehicle stiffness must vary as per various road condition. Successful implementation of this system will decreases the chances of vehicle getting rolled over. This system includes anti-roll bar, pneumatic system, coil spring, electronic control unit, bevel gears, suspensions and wheel. Anti-roll bar is connected to the suspension strut. Anti-roll bar and suspension strut are interconnected through a ball jointed link. Combination of three mitre type bevel gear mechanism is placed in centered section of antiroll bar. Which provides opposite rotational motion relatively. We have double acting cylinder with 3/2 DCV which controls engage and disengage of gear mechanism.Shape of anti-roll bars for automobile suspension systems are usually designed from a standpoint of avoiding physical interference with other components mounted on the bottom of a vehicle. Also the diameter of the bar is usually pre-selected and fixed to achieve a desired anti-roll stiffness. After having this much amount of constraints in shape and dimensions there is little design flexibility for engineers/designers. So in present invention we have configured the mechanism consisting of three mitre type bevel gears which can be engaged and disengaged. In engaged position of gears Anti-Roll bar will provide continuous traction while cornering, in disengaged position of gears it will flourish the riding comfort during uneven road conditions. International Journal of Engineering Research & Technology (IJERT) ISSN: 2278-0181http://www.ijert.org IJERTV9IS080317 (This work is licensed under a Creative Commons Attribution 4.0 International License.) Published by : www.ijert.org Vol. 9 Issue 08, August-2020 916 III. DESIGN & CALCULATION Fig. 4 Analysis of Chassis ( Total deformation) A. Design International Journal of Engineering Research & Technology (IJERT) ISSN: 2278-0181http://www.ijert.org IJERTV9IS080317 (This work is licensed under a Creative Commons Attribution 4.0 International License.) Published by : www.ijert.org Vol. 9 Issue 08, August-2020 917" + ] + }, + { + "image_filename": "designv8_17_0002141_ngRunqiG1000407F.pdf-Figure4-9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002141_ngRunqiG1000407F.pdf-Figure4-9-1.png", + "caption": "Figure 4-9. (a) Even-mode network of the prototype III. (b) Odd-mode network of the prototype III.", + "texts": [ + "5o and \u03b82= 144o). ................................................................... 71 Figure 4-7. (a) Even-mode network of the prototype II. (b) Odd-mode network of the - XI - prototype II..................................................................................................................... 73 Figure 4-8. Frequency responses of the prototype II under different values of tz1 (other design specifications: tz2= 30, \u03b81= 112.5o and \u03b82= 144o). ......................................... 74 Figure 4-9. (a) Even-mode network of the prototype III. (b) Odd-mode network of the prototype III. .................................................................................................................. 75 Figure 4-10. Frequency responses of the prototype III under different values of \u025b (other design specifications: tz1= -1.5, tz2= 50, \u03b81= 119.25o and \u03b82= 135o). ...................... 77 Figure 4-11. Frequency responses of the prototype III under different values of tz1 (other design specifications: \u03b5= 0", + "3, the rejection for the lower/upper side of the 1st/2nd passband improves slightly, while the rejection between the two passbands drops. Figure 4-11 shows the variation of the TZs in the imaginary frequency plane (as the variation of tz1) with fixing the other design specifications. As tz1 changes from -1 to -5, there is little change of the filtering responses as seen in Figure 4-11(a), while there is an obvious change for the group delay as seen in Figure 4-11(b). In a summary of the three circuit prototypes as tabulated in Table 4.1, according to Figure 4-5, Figure 4-7 and Figure 4-9, these circuit schematics share the similar circuit structure and the design principle, while prototype II has an additional degree of freedom in controlling the group delay and prototype III having the capability in further adjusting the in-band ripple factor. Therefore, it can be concluded that the proposed structure and the synthesis procedure has the capability in effectively controlling the in-band ripple factor (\u025b) and the dual-band isolation. 77 Table 4.4 Design Parameters of Prototype III under Different \u025b Characteristic Impedance (\u03a9) \u025b Z1e Z1o Z2 Z3 Zs1 Zs2 160" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004590_O201319947248395.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004590_O201319947248395.pdf-Figure18-1.png", + "caption": "Fig. 18. Possible domain decomposition of two aircrafts: F16 Falcon fighter jet (left) and Predator Drone UAV (right) for scattering-reduction treatment.", + "texts": [ + " We note that the modified slab does introduce additional scattering, and that the absorber does help reduce the same. We also note that the modified absorber improves the performance over the initial one, but only slightly, which shows that the planar version of the cloak is not all that inferior to the one modified for this type of geometry. Additional optimization of the modified cloak is expected to improve the performance even further, if so desired. For an arbitrary target, we can first decompose the geometry of the target in a manner illustrated in Fig. 18, and wrap each part of the target with an absorber, designed by using the approach based on shape perturbation of a related smooth object, and then follow the methodology we have described above to determine the material parameters of the shroud. It should be evident that this is a far more realistic approach than transforming the geometries of these complex objects into an infinitesimally small-size target, as called for by the TO algorithm for cloak designs, and following the TO recipe corresponding to such a geometry transformation, which is bound to lead to unrealistic and impractical designs. Finally, we mention that we need to extend the procedure outlined above when dealing with an arbitrary target, though the basic philosophy of the design procedure remains the same. Reduction of RFI, another important application for the absorber-wrapping is to mitigate the problem of antenna blockage in a shared-platform environment, as shown in Fig. 18, in which the introduction of the aggressor antenna can raise the far-end sidelobe levels of the parabolic dish significantly. To mitigate this effect, we can wrap the monopole by using a multilayer absorber which has been optimized for a planar geometry, as we have done in the past, or we can optimize the layer thicknesses and material parameter for the circular cylinder geometry. Alternatively, we can use a conducting saucer-like structure wrapped around the monopole, as proposed in [25-27]. Figs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000466_f_version_1668679703-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000466_f_version_1668679703-Figure5-1.png", + "caption": "Figure 5. Longitudinal section cross-sectional images of the extrusion: (a) mirror surface, (b) millimeter-textured, (c) 10 \u03bcm-textured, (d) 5 \u03bcm-textured, and (e) nanometer-textured punches.", + "texts": [ + " tr si rce tr e i r et l l ri c r icr e tr si i s s t e extr sio force\u2013str ia ra s for the i ror punch, millimetert r , , , iffere t surface properties of the nanotexture. The maxi um extrusion load is 5.2 kN for the (a) mirro surface punch, wh ch is the ighest, compared to 3.8 kN for the (b) millime r-textured punch; the force is reduced by the addition of texture. Based on the comparison of the micrometer-scale forces, that is, (c) 4.1 kN for the 10 \u00b5m texture and (d) 3.0 kN for the 5 \u00b5m texture, the force is reduced by d creasing exture size. Figure 5 shows the cross-sectional shape of each punch after micro backward extrusion and the backward extrusion length (lb) for each product at a ram stroke of 1.5 mm. The lb values are 1.95, 2.21, 2.19, 2.64, and 2.60 mm for (a) mirror, (b) millimeter-textured, (c) 10 \u00b5m-textured, (d) 5 \u00b5m-textured, and (e) nanotextured punches, respectively. The lb is similar in length; however, the reduction in the textured true contact area possibly Micromachines 2022, 13, 2001 6 of 11 reduces friction and increases lb by facilitating appropriate material flow", + " The shorter backward extrusion length of the millimeter-textured and 10 \u00b5m-textured punches than that of the 5 \u00b5m-textured punch may be explained using millimeter-sized grooves in microscale machining generating two flows: one in the backward extrusion direction and another that enters the tool groove. By reducing the texture depth, the Al adhesion of the punch was broken, and friction was reduced, thereby resulting in smoother plastic flow and a longer backward extrusion length. Therefore, a friction reduction effect can be obtained by reducing the texture depth in the microscale plastic forming. Micromachines 2022, 13, x 6 of 11 Figure 4. Extrusion force\u2013ram stroke curve in each punch. Figure 5 shows the cross-sectional shape of each punch after micro backward extru- sion and the backward extrusion length (lb) for each product at a ram stroke of 1.5 mm. The lb values are 1.95, 2.21, 2.19, 2.64, and 2.60 mm for (a) mirror, (b) millimeter-textured, (c) 10 \u00b5m-textured, (d) 5 \u00b5m-textured, and (e) nanotextured punches, respectively. The lb is similar in length; however, the reduction in the textured true contact area possibly re- duces friction and increases lb by facilitating appropriate material flow. The shorter back- ward extrusion length of the millimeter-textured and 10 \u00b5m-textured punches than that of the 5 \u00b5m-textured punch may be explained using millimeter-sized grooves in mi- croscale machining generating two flows: one in the backward extrusion direction and another that enters the tool groove. By reducing the texture depth, the Al adhesion of the punch was broken, and friction was reduced, thereby resulting in smoother plastic flow (a) (b) (c) (d) (e) Figure 5. Longitudinal section cross-sectional images of the extrusion: (a) mirror surface, (b) millimeter-textured, (c) 10 \u03bcm-textured, (d) 5 \u03bcm-textured, and (e) nanometer-textured punches. Figure 4. Extrusion force\u2013ra str e c r e i ac . Micromachines 2022, 13, x 6 of 11 Figure 4. Extrusion force\u2013ram stroke curve in each punch. Figure 5 shows the cross-sectional shape of each punch after micro backward extru- sion and the backward extrusion length (lb) for each product at a ram stroke of 1.5 mm. The lb values are 1.95, 2.21, 2.19, 2.64, and 2.60 mm for (a) mirror, (b) millimeter-textured, (c) 10 \u00b5m-textured, (d) 5 \u00b5m-textured, and (e) nanotextured punches, respectively. The lb is similar in length; however, the reduction in the textured true contact area possibly re- duces friction and increases lb by facilitating appropriate material flow", + " The shorter back- ward extrusion length of the millimeter-textured and 10 \u00b5m-textured punches than that of the 5 \u00b5m-textured punch may be explained using millimeter-sized grooves in mi- croscale machining generating two flows: one in the backward extrusion direction and another that enters the tool groove. By reducing the texture depth, the Al adhesion of the punch was broken, and friction was reduced, thereby resulting in smoother plastic flow and a longer backward extrusion length. Therefore, a friction reduction effect can be ob- tained by reducing the t xture depth in the microscale plastic forming. (a) (b) (c) Figure 5. Longitudinal section cross-sectional i ages of the extrusion: (a) mirror surface, (b) millimetertextured, (c) 10 \u00b5m-textured, (d) 5 \u00b5m-textured, and (e) nanometer-textured punches. Figure 6 shows the amount of adhesion on the punch surface after processing with punches with different surface properties: (a) mirror punch, (b) millimeter-textured punch, Micromachines 2022, 13, 2001 7 of 11 (c) 10 \u00b5m-textured punch, (d) 5 \u00b5m-textured punch, and (e) nanotextured punch. EPMA was used to analyze the punch surface" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002044_8948470_09078103.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002044_8948470_09078103.pdf-Figure1-1.png", + "caption": "FIGURE 1. Exploded view of the axial-radial combined permanent magnet eddy current coupler mechanical structure.", + "texts": [ + " Other significant advantages of permanent magnet eddy current couplers are isolated protection, no ripple torque, and excellent tolerance to shaft misalignment [6]\u2013[8]. As a novel transmission device, the axial-radial combined permanent magnet eddy current coupler has a unique double The associate editor coordinating the review of this manuscript and approving it for publication was Xue Zhou . rotor structure [9], [10]. It mainly consists of a conductor rotor, a permanent magnet rotor and an adjustment device; the exploded view of the mechanical structure is shown in Fig. 1. The motor shaft and load shaft are connected to the conductor rotor and permanent magnet rotor, respectively [11]. The conductor rotor rotates together with the drive motor and cuts the magnetic line produced by the permanent VOLUME 8, 2020 This work is licensed under a Creative Commons Attribution 4.0 License. For more information, see https://creativecommons.org/licenses/by/4.0/ 78367 magnet rotor [12]. An alternating eddy current field is generated in the conductor rotor and excites the induced magnetic field according to Faraday\u2019s law [13]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure1-1.png", + "caption": "Fig. 1. The prototype of a Martian rover [6] [13]", + "texts": [ + " Due to the delay in the transmission of radio waves, designers strive to ensure as much autonomous control as possible. Application of composite materials allows for better optimization of the shape and weight, which might improve the vehicle\u2019s functionality and the light laminate structure is less sensitive magnetically. The frame presented in the article was designed for a Martian rover taking part in the European Rover Challenge competition. For the sake of stability, a six-wheel rocker-bogie suspension was selected for the design (Fig. 1). By definition, a \u201cdouble tripod\u201d is more stable than the standard suspension of a four-wheeled off-road vehicle. Additional advantages of such a suspension include evenly distributed pressure of the wheels on the ground and reduction of the frequency of vibrations in the frame where the vehicle electronic components are located. This effect was achieved by a pivoting mounting of the frame in relation to two support points \u2013 1 and 2 (Fig.2). The ERC competition takes place in terrestrial conditions, on a specially prepared track, so the rover\u2019s structure has to be characterised by greater strength" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003993_e_download_5418_2394-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003993_e_download_5418_2394-Figure2-1.png", + "caption": "Fig. 2 \u2014 Three-point bending test rig: (a) Physical model on TMS-Protexture analyzer and (b) CAD model of bending test rig", + "texts": [ + "7 To evaluate the moisture content of paddy straw, the oven drying method was used. The samples were collected from the field on 0th, 5th and 10th day after harvesting.17 Three different levels of moisture content of straw (10.8 \u00b1 1.2, 13.5 \u00b1 1.1, and 18.4 \u00b1 1.4% w.b.) and LR (25, 30 and 35 mm/min) were considered during the study. A three-point bending test was used to determine the maximum force to bend up to a certain deformation. The length of the straw was 80 mm, and its two ends were rested on steel supports with contact arc lengths of 3 mm, as shown in Fig. 2. A Texture Profile Analyzer (TPA) (TA-XT Plus, Stable Micro Systems Ltd., Surrey, UK) was used to conduct the experiments using A/3PB probe. The TPA was set to the following parameters: pre-test speed: 1 mm/s; post-test speed: 3.33 mm/s; trigger force: 5 g; test speed: 0.42 mm/s; target mode distance: 15 mm; trigger type: auto and 200 Points Per Second (PPS) as data acquisition rate. The TPA analysis was carried out at room temperature (27 \u2103) and took 100 s for the process. Three different moisture content and load rates were used to examine the samples. Every specimen in the same lot underwent three measurements, and mean value was recorded. Three loading rates (25, 30 and 35 mm/min) were used for the bending test to assess the force in the failure region of straw. By using the measured force, the YM and BS was computed. The straw was placed on two metallic supports that were rounded and spaced 80 mm apart, and a loading plate generated the load in the middle of the supports (Fig. 2b).10,13 The straw samples were a little oval in cross-section and the second instant of area during the bending, denoted by the symbol Ib, explained as below.18 Ib= \u03c0 4 [ab3-(a-b)(b-t) 3 ] \u2026 (1) (BS) \u03c3b= \u03c0 4 [ Fb 4Ib ] \u2026 (2) where, Fb = Bending force (N), Ib = Second moment of area (mm4), a = Semi-major axis (mm), b = Semiminor axis (mm), \u03b4 = Deflection length of straw (mm), l = Distance between supports (mm), t = thickness (mm), BS = bending strength (MPa) A force-time deformation graph was generated with respect to the experiment time, and shear force (SF) was determined with the help of above mentioned bending test procedure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000615_.1117_12.2308193.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000615_.1117_12.2308193.pdf-Figure11-1.png", + "caption": "Fig. 11 Thermal stress on the wheel", + "texts": [ + " Filter Wheel acts as a support structure for 18 filters, and is connected to the FRP shaft. It is designed for stiffness of more than 100 Hz. This will be cooled in radiating mode by top and bottom casings, which house the wheel. Wheel should be as compact as possible to prevent thermal loss. This should not deform by more than 5 arc-minutes under thermal loads. Eigen value analysis in Fig. 10 shows that first wheel mode with soft mount is at 134 Hz. This is bending mode for the wheel. Thermal analysis as shown in Fig. 11 gives the stress experienced by the wheel for 100K temperature range which is within the yield strength of aluminium. Proc. of SPIE Vol. 10566 105662O-6 ICSO 2008 International Conference on Space Optics Toulouse, France 14 - 17 October 2008 Soft mount was realized and integrated as shown in Fig.5. Component details are as under. 3 mm thick Aluminum 6061-T651 plate as base simulating filter wheel material Aluminum 6061-T651 clamps on the two ends of the germanium filter, fixed with the base RTV sandwiched between the filter and the clamps Rectangular germanium piece 80mm long x 25 mm wide x 5 mm thick" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.11-1.png", + "caption": "Figure 6.11: Taylor-Couette Flow [118]", + "texts": [ + "65) The design of the RV mechanism results in the cylinder-rotor assembly rotating in the housing shell in which the compressed fluid is discharged to. This creates a drag force on the cylinder assembly caused by the shearing of the gas between the cylinder and the housing, resulting in an excitation force on the housing shell. Due to the high speed rotation of the cylinder in the housing shell, the flow profile of the discharged fluid in the housing shell can be characterised as that of a Taylor-Couette flow [118, 119]. An illustration of this flow is shown in Figure 6.11. Dou, et al. [118, 119] have provided the analytical solution for the calculation of the fluid shear but this solution is not applicable in the case of the RV compressor prototype as the ratio of the cylinder length to the gap between the cylinder-rotor assembly and housing shell is small. In the assumptions used to formulate the analytical solution, the lengths of the cylinders are considered to be infinite compared to the dimension of the concentric gap between them. Therefore, a more comprehensive two-dimensional computational fluid dynamics (CFD) analysis using the commercially available computational code ANSYS Fluent is used to estimate the fluid shear in the compressor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001922_1044-023-09952-2.pdf-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001922_1044-023-09952-2.pdf-Figure19-1.png", + "caption": "Fig. 19 Successive iterations of the first contact-cage model: (a) 3-plane version (C2); (b) 5-plane version (C3)", + "texts": [ + " Regarding the dynamic behaviour of this model, the results depicted in Fig. 17 and Fig. 18, respectively, are consistent with those obtained from the non-contact cage models. Both figures exhibit slight vibrations in their magnitudes, reflecting the unrestricted motion of the rolling elements. To enhance the design and eliminate the need for a revolute joint to hold the cage, more advanced modelling approaches were developed. The two proposed designs, referred to as C2 and C3, are illustrated in Fig. 19. In this case, the planes were defined by establishing a circle within the pocket with a certain clearance with respect to the ball radius. Then an angle of 45\u00b0 (C2) or 30/60\u00b0 (C3) was defined to set the points for the additional planes, PJ1 up to PJ5. Thus, the C2 incorporated three planes on each side of the cage, while the C4 utilised five planes. The increased number of planes aimed to maintain the cage in its typical position. However, the greater the number of planes, the larger the number of circle\u2013plane interactions to be defined and solved during the dynamic simulation in each time step" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002838_f_version_1679473059-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002838_f_version_1679473059-Figure3-1.png", + "caption": "Figure 3. Motion trajectories of the addendum and dedendum.", + "texts": [ + " From Equation (19), it can be deduced that the tooth profiles of the external gear and rack cutter need to meet Equation (20) during the meshing process [4]: f (x1, \u03d51) = dy1 dx1 (r1 cos \u03d51 \u2212 y1)\u2212 dx1 dx1 (x1 \u2212 r1 sin \u03d51)= 0 (20) By combining Equations (4), (14), (18), and (19), the mathematical model of the tooth profile of the internal ring can be obtained. Basic design parameters are the basis of modeling the tooth profile of the gear pair and its cutting tool. Unreasonable parameters will directly lead to the failure of design. Therefore, based on the meshing principle and the geometrical relations of the tooth profile, the constraint ranges of basic design parameters were derived. 3.1.1. Addendum Coefficient, Dedendum Coefficient As shown in Figure 3, in the coordinate Sg, the motion trajectories of the addendum and dedendum of the external gear are circles centered on O1, with radius ra1 and r f 1, respectively, and the motion trajectories of the addendum and dedendum of the internal gear ring are circles centered on O2, with radius ra2 and r f 2, respectively. In the transmission process of the gear pair, it is necessary to ensure that there is no interference collision between the addendum of the external gear and the dedendum of the internal gear ring or between the dedendum of the external gear and the addendum of the internal gear ring" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001024_5_27_2_27_2_192__pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001024_5_27_2_27_2_192__pdf-Figure12-1.png", + "caption": "Fig. 12 An example of the simulation results (attitude sensor off, new feedback law on)", + "texts": [], + "surrounding_texts": [ + "\u5927\u5cf6 \u30fb\u4e8c\u5bae:\u78c1 \u6c17\u8ef8\u53d7\u89d2\u904b\u52d5\u91cf\u30db \u30a4\u30fc\u30eb\u3092\u642d \u8f09 \u3057\u305f\u4eba\u5de5\u885b\u661f\u306e\u59ff\u52e2\u904b\u52d5\u306e\u5b89\u5b9a \u5316 197\n\u3055\u308c \u308b.\u3057 \u305f \u304c\u3063\u3066,(9)\u5f0f \u306f,\u8a2d \u8a08 \u306e\u969b\u306e\u76ee\u5b89 \u3092\u4e0e \u3048 \u308b\u5f0f \u3068\u3057\u3066\u6709\u5229\u3067\u3042 \u308d\u3046.\u307e \u305f,\u03c9 \u306b\u3064\u3044\u3066\u306f,\u885b \u661f\u306e \u30cb\u30e5\u30fc \u30c6\u30fc\u30b7 \u30e7\u30f3\u904b\u52d5\u306e\u89d2\u901f\u5ea6\u3092\u8a2d\u8a08 \u306e\u76ee\u5b89 \u3068\u3059 \u308c\u3070 \u3088\u3044.\u3057 \u305f\u304c \u3063\u3066,\u8a2d \u8a08\u6cd5 \u3068 \u3057\u3066 \u306f,\u307e \u305a,\u885b \u661f \u306e\u30cb \u30e5\u30fc\u30c6 \u30fc\u30b7 \u30e7\u30f3\u904b\u52d5 \u306e\u89d2\u901f\u5ea6 \u3092\u6c42 \u3081\u3066,\u305d \u308c\u3092\u53c2\n\u8003\u306bLPF\u306e \u03c9\u3092\u6c7a\u3081,\u3064 \u304e\u306b(9)\u5f0f \u304b \u3089 \u70ba\u3092\u6c7a\u3081\u308c \u3070\u3088\u3044.\n\u307e\u305f,(11)\u5f0f \u306b\u304a\u3044\u3066,s\u21920\u3068 \u3059 \u308b\u3068,\n-1 (13)\n\u3068\u306a \u308b\u3053\u3068\u304b \u3089\u308f\u304b \u308b\u3088 \u3046\u306b,\u03b8*\u304c \u5897 \u3048\u305f\u5206 \u3060\u3051, \u03c6 \u304c\u6e1b\u5c11\u3059 \u308b.\u3053 \u308c \u306f,\u89d2 \u904b \u52d5\u91cf\u4fdd\u5b58\u5247 \u304b \u3089\u51fa\u3066 \u304f\n\u308b\u5f53\u7136 \u306e\u7d50\u679c\u3067\u3042 \u308b.\n4. \u30b3 \u30f3 \u30d4 \u30e5\u30fc \u30bf \u30b7 \u30df \u30e5 \u30ec\u30fc \u30b7 \u30e7\u30f3\n\u306b \u3088 \u308b\u5b9f \u8a3c\n4.1 \u30b7\u30df\u30e5 \u30ec\u30fc\u30b7 \u30e7\u30f3\u306e\u65b9\u6cd5\n\u30db\u30a4\u30fc\u30eb \u30fb\u885b\u661f\u306e\u904b\u52d5\u65b9\u7a0b\u5f0f \u3068 \u3057\u3066 \u306f,(1a), (1 b)\u5f0f \u3068(2a), (2b)\u5f0f \u3092 \u7528 \u3044,\u3053 \u308c\u30924\u6b21 \u30eb \u30f3\u30b2 \u30af\n\u30c3\u30bf\u6cd5 \u306b\u3088\u308a\u6570\u5024\u7684 \u306b\u89e3 \u3044\u305f.\u3053 \u3053\u3067,\u885b \u661f\u306ex, z\n\u8ef8\u56de \u308a\u6163\u6027 \u30e2\u30fc\u30e1\u30f3 \u30c8\u306f12=Iz=200kgm2,\u30db \u30a4 \u30fc\u30eb \u306e\u534a\u5f84\u8ef8\u56de \u308a\u6163\u6027 \u30e2\u30fc\u30e1 \u30f3 \u30c8\u306f,J=0.01kgm2,\u30db \u30a4 \u30fc\u30eb\u306e\u89d2\u904b\u52d5\u91cf \u306f,h=20Nms\u3068 \u3057\u305f.\u307e \u305f,\u885b \u661f \u5236\n\u5fa1\u5247 \u306ePID\u4fc2 \u6570 \u306f,K\u03c1=1.5, Ki=0.025, K4=30 \u3068 \u3057\u305f.\n4.2 \u30b7\u30df\u30e5\u30ec\u30fc \u30b7\u30e7\u30f3\u7d50\u679c \u3068\u8003\u5bdf\n\u885b\u661f\u306e\u521d\u671f\u59ff\u52e2\u89d2\u304c \u03c6=Odeg, \u03c6=0.4deg\u3067 \u3042\u308b \u3068\u3057\u3066 \u30b7 \u30df\u30e5\u30ec\u30fc \u30b7\u30e7\u30f3\u3092\u884c \u3063\u305f.\u885b \u661f\u5168\u4f53(\u30db \u30a4\u30fc \u30eb\u3092\u542b \u3080)\u306e \u89d2\u904b \u52d5\u91cf\u30d9\u30af \u30c8\u30eb\u306f,\u57fa \u6e96\u5ea7\u6a19\u7cfb\u306e-Y\n\u8ef8 \u306b\u4e00\u81f4 \u3057\u3066\u3044\u308b \u3068\u3057\u305f.\u307e \u305f,\u30db \u30a4 \u30fc\u30eb\u306e\u521d\u671f \u30b8 \u30f3 \u30d0 \u30eb\u89d2 \u306f,\u30bc \u30ed\u3067\u3042\u308b\u3068 \u3057\u305f.\u3053 \u306e\u5834\u5408,\u885b \u661f \u306f,\u521d\n\u671f\u72b6\u614b \u3067\u306f\u30cb\u30e5\u30fc\u30c6\u30fc\u30b7 \u30e7\u30f3\u904b\u52d5 \u3092 \u3057\u3066\u3044 \u308b.\n\u307e\u305a,\u885b \u661f\u59ff\u52e2 \u30bb \u30f3\u30b5\u304b \u3089\u306e\u60c5\u5831 \u304c\u5f97 \u3089\u308c\u3066\u3044 \u308b\u5834 \u5408 \u306e,\u885b \u661f\u5236\u5fa1 \u30eb\u30fc\u30d7\u5358\u72ec \u306e\u5236\u5fa1\u7279\u6027 \u306e \u30b7\u30df\u30e5\u30ec\u30fc\u30b7\n\u30e7\u30f3\u3092Fig. 10\u306b \u793a\u3059.\u826f \u3044\u5236\u5fa1\u7279\u6027 \u304c\u5f97 \u3089\u308c\u3066\u3044 \u308b \u3053\u3068\u304c\u308f\u304b \u308b.\u306a \u304a,\u53f3 \u4e0b\u306e\u56f3 \u306f,\u885b \u661f \u59ff\u52e2\u89d2,\u30db \u30a4 \u30fc\u30eb \u30b8 \u30f3\u30d0\u30eb\u89d2 ,\u8ef8 \u53d7 \u30c8\u30eb \u30af\u306e\u4f4d\u76f8\u9762\u8ecc\u8de1 \u3092\u91cd\u306d\u66f8 \u304d \u3057\u305f \u3082\u306e\u3067\u3042 \u308b.\n\u3064 \u304e\u306b,Fig. 10\u3068 \u540c \u3058\u6761 \u4ef6\u4e0b\u3067\u885b\u661f \u306e\u59ff \u52e2\u30bb \u30f3\u30b5\n\u304b \u3089\u306e\u60c5\u5831\u304c\u5f97 \u3089\u308c\u306a\u3044\u5834\u5408 \u306e \u30b7 \u30df\u30e5 \u30ec\u30fc \u30b7 \u30e7 \u30f3\u3092 Fig. 11\u306b \u793a\u3059.\u3053 \u306e\u307e\u307e\u3067\u306f\u885b\u661f \u306e\u30cb\u30e6\u30fc\u30c6\u30fc\u30b7 \u30e7\n\u30f3\u904b \u52d5\u304c\u6e1b\u8870 \u3057\u306a\u3044 \u3053\u3068\u304c\u308f\u304b \u308b.\u307e \u305f,\u8ef8 \u53d7 \u30c8\u30eb \u30af \u306e\u5909\u5316\u3092\u898b \u308b\u3068,\u305d \u308c\u304c\u885b\u661f \u306e\u30cb \u30e5\u30fc\u30c6\u30fc\u30b7 \u30e7\u30f3\u904b\u52d5\n\u306e\u60c5\u5831 \u3092\u542b\u3093\u3067\u3044 \u308b\u3053\u3068\u304c\u308f\u304b\u308b.\nFig. 12\u306f,Fig. 11\u3068 \u540c \u3058\u6761 \u4ef6\u4e0b\u3067\u885b\u661f\u5b89\u5b9a\u5316 \u30d5\n\u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u3092\u4f7f\u7528 \u3057\u305f\u5834\u5408\u3067 \u3042 \u308b.\u885b \u661f\u306e\u59ff\u52e2\u60c5\u5831 \u3092\u7528 \u3044\u3066\u3044\u306a\u3044\u306b \u3082\u304b\u304b \u308f \u3089\u305a,\u885b \u661f \u306e\u30cb \u30e5\u30fc\u30c6\u30fc \u30b7\n\u30e7\u30f3\u904b \u52d5\u306f\u6e1b \u8870 \u3057\u3066 \u3044\u308b.\nFig. 13\u306f,\u59ff \u52e2 \u30bb \u30f3\u30b5\u304b \u3089\u60c5\u5831 \u304c \u5f97 \u3089\u308c \u308b \u3068 \u3057\nnew feedback law off)", + "\u5927\u5cf6 \u30fb\u4e8c\u5bae:\u78c1 \u6c17\u8ef8\u53d7\u89d2\u904b\u52d5\u91cf\u30db\u30a4 \u30fc\u30eb\u3092\u642d\u8f09 \u3057\u305f\u4eba\u5de5\u885b\u661f\u306e\u59ff\u52e2\u904b\u52d5 \u306e\u5b89\u5b9a \u5316 199\n\u3066,\u885b \u661f\u59ff\u52e2 \u5236\u5fa1\u5247 \u3068\u885b\u661f\u5b89\u5b9a\u5316 \u30d5\u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u3092\u4f75\n\u7528 \u3057\u305f\u5834\u5408 \u3067\u3042 \u308b.\u9006 \u632f\u308c\u304c\u8d77 \u304d\u3066 \u3044\u308b\u304c,\u5341 \u5206\u5b89\u5b9a \u3067\u3042 \u308a,\u5b9f \u7528\u4e0a \u554f\u984c \u306f\u306a \u3044\u3067\u3042 \u308d\u3046.\n\u307e\u305f,\u3053 \u306e\u307b\u304b \u306b\u6bd4\u8f03\u7684\u5e83 \u3044\u7bc4\u56f2 \u306b\u8af8\u30d1 \u30e9\u30e1\u30fc\u30bf\u3092 \u5909\u5316 \u3055\u305b \u305f\u30b7 \u30df\u30e5\u30ec\u30fc \u30b7 \u30e7\u30f3\u3067 \u3082,\u3059 \u3079\u3066\u306e\u5834\u5408 \u306b\u5341\n\u5206\u5b89\u5b9a \u3067\u3042 \u308b\u3068\u3044 \u3046\u7d50 \u679c\u304c\u5f97 \u3089\u308c\u3066\u3044\u308b.\n5. \u307e \u3068 \u3081\n\u8ef8 \u53d7 \u30c8\u30eb \u30af\u304b \u3089\u885b\u661f \u306e\u30cb\u30e5\u30fc\u30c6\u30fc\u30b7 \u30e7\u30f3\u904b\u52d5\u3092\u691c\u51fa\n\u3057\u3066,\u305d \u308c\u3092\u6e1b\u8870 \u3055\u305b \u308b\u30d5\u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u5247\u3092\u63d0\u6848 \u3057, \u305d\u306e \u30d5\u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u5247 \u306e\u6709\u52b9\u6027\u3092\u7c21\u5358\u306a\u89e3\u6790\u7684\u8a3c \u660e \u3068 \u30b7\u30df\u30e5 \u30ec\u30fc \u30b7\u30e7\u30f3\u306b\u3088 \u3063\u3066\u793a \u3057\u305f.\u3053 \u306e\u3088 \u3046\u306b,\u30db \u30a4 \u30fc\u30eb\u5236\u5fa1\u7cfb \u81ea\u4f53 \u306b\u885b\u661f\u306e \u30cb\u30e5\u30fc\u30c6 \u30fc\u30b7\u30e7\u30f3\u904b \u52d5\u3092\u6e1b\u8870\n\u3055\u305b \u308b\u6027\u8cea \u3092\u4ed8\u52a0 \u3059 \u308b\u3053\u3068\u306b\u3088\u308a,\u30b5 \u30d6 \u30b7\u30b9\u30c6\u30e0\u3068 \u3057 \u3066\u306e\u78c1\u6c17\u8ef8\u53d7 \u30db\u30a4\u30fc\u30eb\u306e\u5b89\u5168 \u6027\u3092\u5897\u3059 \u3053\u3068\u304c\u3067\u304d\u308b.\n\u306a \u304a,\u672c \u7a3f\u3067\u8ff0 \u3079\u305f\u5236\u5fa1\u7cfb\u306f,\u30db \u30a4\u30fc\u30eb \u306e\u56de\u8ee2\u6570 \u306b\n\u5fdc \u3058\u3066 \u30db\u30a4 \u30fc\u30eb\u5236\u5fa1\u5247 \u306e \u30d5\u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u4fc2 \u6570\u3092\u5909\u5316 \u3055 \u305b \u308b\u306a \u3069\u306e,\u6bd4 \u8f03\u7684\u8907\u96d1 \u306a\u64cd\u4f5c \u3092\u5fc5\u8981 \u3068\u3059 \u308b.\u305d \u306e\u305f \u3081,\u8a08 \u7b97\u6a5f\u3092\u7528 \u3044\u305f \u30c7\u30a3\u30b8\u30bf\u30eb\u5236\u5fa1\u7cfb \u3068 \u3057\u3066\u5b9f\u73fe\u3059 \u308b\n\u5fc5\u8981\u304c\u3042 \u308b.\u305d \u306e\u969b,\u30db \u30a4\u30fc\u30eb\u5236\u5fa1\u7cfb\u3067\u306f\u77ed\u3044\u30b5 \u30f3\u30d7\n\u30ea\u30f3\u30b0\u30bf\u30a4\u30e0\u304c\u5fc5\u8981 \u3068\u3055\u308c \u308b\u306e \u3067,DSP\u306a \u3069\u306e\u9ad8\u901f\n\u306e\u6f14\u7b97\u7d20 \u5b50\u3092\u7528\u3044 \u308b\u3079 \u304d\u3067\u3042 \u308d\u3046.\n\u4eca\u5f8c \u306f,\u3053 \u306e \u30d5\u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u5247\u306e\u6709\u52b9\u6027 \u3092,3\u8ef8 \u30e2 \u30fc\u30b7 \u30e7\u30f3\u30c6\u30fc\u30d6\u30eb\u3092\u5229 \u7528 \u3057\u305f\u5b9f\u9a13\u306a\u3069\u305f\u3088 \u308a\u691c\u8a3c \u3057\u3066\n\u3044 \u304f\u4e88\u5b9a \u3067\u3042\u308b.\n\u53c2 \u8003 \u6587 \u732e\n1) G. Heimbold: Impact of Magnetic Bearing Rotor\nDesign on Satellite Nutational Stability, Journal of Guidance and Control, 7-3, 279/285 (1984)\n2) A. Nakajima and C. Murakami: Active Nutation\nControl of Spacecraft Using a Magnetic Bearing Momentum Wheel with Venier Gimballing Capability, Technical Report of National Aerospace Labo-\nratory, TR-820T (1984) 3) T. Lange: Optimal Magnetic Bearing Control for\nHigh-Speed Momentum Wheels, Journal of Guidance and Control, 8-6, 737/742 (1985)\n4) M. Inoue, K. Tsuchiya, C. Murakami and A.\nNakajima: Nutational Stability of a Satellite Equipped with an Active Magnetic Momentum Wheel, Pasific Basin International Symposium on Advances in Space Science Technology and Its Applications, 127/136 (1987) 5) D.B. Eisenhaure, J.R. Downer, T.E. Bliamptis and\nS.D. Hendrie: A Combined Attitude, Reference, and Energy Storage System for Satellite Applications, AIAA-84-0565 (1984)\n6) J.W. Weissberg: Application of a Magnetically Suspended Momentum Wheel to Satellite Guidance and Control, Master's Thesis, Department of\nElectrical Engineering, the University of Tokyo\n(1988) 7) \u4e95\u4e0a,\u4e8c \u5bae:\u78c1 \u6c17 \u8ef8\u53d7\u30db\u30a4 \u30fc\u30eb \u3092\u642d\u8f09 \u3057\u305f\u4eba\u5de5\u885b\u661f \u306e\u59ff\n\u52e2\u904b \u52d5\u306e\u5b89\u5b9a\u6027\u3068\u5236\u5fa1,\u8a08 \u6e2c \u81ea\u52d5 \u5236 \u5fa1 \u5b66 \u4f1a \u8ad6 \u6587 \u96c6, 25- 10, 74/80 (1989) 8) U. Bicher and T. Eckardt: A 3 (5) Degree of Free-\ndom Electrodynamic Bearing Wheel for 3-Axis Spacecraft Attitude Control Applications, Magnetic Bearings (Proceedings of First International Symposium), 13/22, ETH Zurich, Switzerland (1988)" + ] + }, + { + "image_filename": "designv8_17_0003768_tation-pdf-url_12705-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003768_tation-pdf-url_12705-Figure21-1.png", + "caption": "Fig. 21. The FEM model of a train coach", + "texts": [], + "surrounding_texts": [ + "Simulating the Response of Structures to Impulse Loadings\n301\nOne of the obtained results, for example, is that shown in Fig. 20, which refers to the previous impact case against the handle; four curves are shown, i.e. the experimental one, together with \u00b115% curves, which bound the admissible errors, and that which comes from numerical simulations; as it can be observed, the numerical values are all inside the admissible range, but for a later time, which comes when the headform has left the obstacle and is moving free in the compartment, which is of no interest.", + "Numerical Simulations - Applications, Examples and Theory 302\nThe first phase of the analysis has regarded the estimation of the deformations of the vehicle as a whole, with the aim to evaluate the reduction of the occupants/driver survival space and the probable disengagement of the bogie wheels from the rail. Stated the respect of these standard requirements, the successive phase has regarded the analysis of the energies involved in the phenomenon (Fig. 22); the value of the initial kinetic energy of the vehicle is 851,250 J, which at the end of the impact is fully converted into internal energy of the system. It should be considered that the internal energy includes the elastic energy stored by the buffer spring, which is recovered in terms of kinetic energy during the \"bounce\" of the vehicle. As it can be seen in Fig. 22, about 50,000 J are absorbed in the first phase of the impact by the buffer; once the buffer spring has been fully compressed, about 600,000 J are absorbed by the two absorbers, proportionally to their characteristics. The next analyzed resulting parameter is the acceleration, which in this case has been evaluated on the \u201crigid\u201d pin linking the structure to the forward bogie. As it can be seen from the plot in the lower left of Fig. 22, which will be the \"pulse\" for the Multibody analysis, during the absorption of the impact energy by the buffer/absorbers group, the maximum acceleration value is about 5g, to grow up to about 15g when the frame is involved in the collision. Finally, it has been evaluated the interface reaction between the vehicle and the barrier (Fig. 22): it is almost constant, with acceptable maximum value, until the frame is involved in the collision.\nwww.intechopen.com", + "The main objective of the work is to develop a complete multibody model of a critical area inside a train unit, including the model of an anthropomorphic dummy, which allows to develop fast simulations of secondary impact scenarios from which to obtain biomechanical results; moreover, by proceeding in this way, it is also possible to quickly evaluate the changes in biomechanical performances of the interiors that characterize different configurations (stiffness of the panels, thickness and arrangement of the reinforcement, etc.). In order to characterize the contact reaction between the dummy and the interiors in a\nmultibody environment, the panels are modelled as rigid bodies, but their impact surfaces\nreact to the impact by following an assigned law of the reaction forces vs. displacement\nthrough the contact surface. This law must be evaluated either by considering experimental\ncompression tests of the panel, or by developing a local finite element analysis by modelling\nthe real properties of the materials of the panels.\nThe advantages in the use of this hybrid methodology are briefly described below: \u2022 a full multibody model (free from FE surfaces) requires very short calculation time; \u2022 the multibody model is a very flexible one, in which it is possible to change the \u201cresponse of the material\u201d by acting only on the characteristics of stiffness at the contact interface; \u2022 the change in geometry of the multibody model is very simple and fast. In Figs. 23 and 24, we show some images related to the preliminary multibody analysis\nperformed by using Madymo\u00ae MB commercial code, by considering as perfectly rigid the\nsurfaces representing all the components of the considered scenario. This analysis provides\ninformation about the kinematic of the secondary impacts involving a generic seated\npassenger (Dummy \"Hybrid_III_95% ile\") and a composite panel positioned in front of him.\nWe also introduced the hypothesis that the effective stiffness of the impacted panels doesn\u2019t\ninfluence the relative kinematic between the panels and the passengers.\nwww.intechopen.com" + ] + }, + { + "image_filename": "designv8_17_0004152_6514899_10445465.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004152_6514899_10445465.pdf-Figure3-1.png", + "caption": "FIGURE 3. Evenly distributed surface current mode under Port 1 Excitation: (a) vector surface current (Jx , Jy), (b) magnitude of x-pol the surface current component (Jx), and (c) magnitude of y-pol the surface current component (Jy).", + "texts": [ + " The unbalanced feed lines, like two electrodes, induce a surface current circulating on the peripheral patch with odd symmetry. More importantly, due to proximity coupling, the surface TEx mode will be excited on the center patch by Port 2, which is orthogonal to the surface TEy mode from Port 1. Therefore, the mode orthogonality allows isolation of Port 1 from Port 2 even with strong proximity coupling. On the other hand, the surface current distribution will alternate upon the excitation of Port 1, as shown in Fig. 3. As shown by Fig. 3(b) and (c), due to geometrical symmetry, the surface current magnitude of the x- and y-component are still identical between the left and right half of the antenna. However, Jy in the right half is now in-phase with the left half, while Jx is 180 degrees out of phase between the right and left halves. \ud835\udc3d\ud835\udc66(\ud835\udc65) = \ud835\udc3d\ud835\udc66(\u2212\ud835\udc65) \ud835\udc3d\ud835\udc65(\ud835\udc65) = \u2212\ud835\udc3d\ud835\udc65(\u2212\ud835\udc65) (2) In other words, the phase profile reverses as the excitation switches from Port 2 to Port 1 as shown by Eq. (2). Therefore, a symmetric (or even symmetric) surface current mode profile is exhibited upon the excitation of Port 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure20-1.png", + "caption": "Fig. 20. Characteristic design solution of position and way of mounting of shaft-mounted single-stage gear reducer by using special mounts (Dodge solution) [19].", + "texts": [ + " The design of the housing is quite complex, taking into account the cost savings of the material as well as the reinforcement of the housing. The form is simple and attractive (Fig. 18). [5] * Corresponding author: racmil@uns.ac.rs Single-stage gear reducer with free shaft arrangement, ie. shaft-mounted gear units are mounted directly to the driving shaft and the shaft position itself adapts to the specific mounting conditions (Fig. 19). Using special mounts this position can be adapted to different positions and ways of mounting (Fig. 20), but these solutions are somewhat expensive than usual footmounted or flange-mounted solutions. * Corresponding author: racmil@uns.ac.rs Based on the performed design solutions of single-stage gear reducers produced by leading manufacturers of gear units, it can be concluded that further intensive development of all types of these reducers can be expected. Gear reducer with horizontal shaft arrangement, with the housings with feet on all four sidewise surfaces and with connected flanges (Fig. 10 and 15) presents the most universal gear reducer" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003235_8948470_09084153.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003235_8948470_09084153.pdf-Figure3-1.png", + "caption": "FIGURE 3. Realization of helical PMs. (a) Resultant PM segments. (b) Front view. (c) Side view.", + "texts": [ + " And the thrust force and torque on screw can be approximated as T \u2248 Tm sin \u03b4 (3) F = G \u00b7 T \u2248 G \u00b7 Tm sin \u03b4 (4) where Tm is the pull-out torque. B. DETENT EFFECT One of the challenges to popularize the MLS lies in the realization of radially magnetized helical PMs. To achieve high force density, sintered NdFeB PMs are usually adopted in the MLS. However, it\u2019s hard to manufacture continuous sintered NdFeB PMs with standard radial magnetization. Anyhow, discretized helical NdFeB PM segments could be regarded as an alternative solution. Fig. 3 depicts the interior and exterior turns of PM helixes composed by 12 helical segments. Compared to the radial magnetization, parallel magnetization for 84178 VOLUME 8, 2020 NdFeB PM segments is more cost-effective. Therefore, the MLS investigated in this paper is confined to those equipped with the parallel magnetized PM segments. Operating on the principle of minimum magnetic reluctance, PM segments on screw and nut tend to be aligned with each other in angular direction, as shown in Fig. 4 (a), even in the case that the load angle \u03b4 is zero" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002390_0430-022-03535-6.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002390_0430-022-03535-6.pdf-Figure5-1.png", + "caption": "Fig. 5 Peening function of the ultrasonic tool illustrated by Abbasi et\u00a0al. [1] (Redrawn by referring to the work by Abbasi et\u00a0al. [1]", + "texts": [ + " mech4 study. com/ 2016/ 06/ diffe rence- betwe en- cold- worki ng- and- hot- worki ng. html). As the various approaches which are broadly applied for efficient upgrading of the mechanical behavior of materials in their microstructural characteristics, in the ultrasonic cold deformation technology, as one of the common cold deformation processes, a substantial modification can arise in the mechanical properties of the material such as surface hardness and smoothness from the flattening of surfaces (Fig.\u00a05). In this case, Eq.\u00a0(1) shows the total energy, Et , which is required for the UCFT process; where Es and Ed indicate the input static energy behind the ultrasonic head or the static energy overall value, and the dynamic energy (Eq.\u00a0(2)), which is equaled to the amplitude product of the dynamic load, Fd , and the sinusoidal function of the vibration wave, respectively. As a typical mechanism, a pneumatic system is considered in order to avoid backlash on the return stroke by the tool which tolerates the reaction force" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004247_.1117_12.2304063.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004247_.1117_12.2304063.pdf-Figure2-1.png", + "caption": "Fig. 2: Main Bench Assembly Components", + "texts": [ + " 1, and it is divided in three main components: \u2022 Mechanical Bench Assembly (MBA) and main thermo-structural element developed by LIDAX \u2022 Proximity Electronics (PE) that contains the required electronics connected to the MCCD (CFI manufactured by e2v) by means of a Flexible PCB (Printed Circuit Board) and developed by CRISA \u2022 Optical Assembly (OA) that holds the optics (beam splitter, filter and lens) and developed by Bertin Technologies The whole assembly is supported by means of three bipods to get the appropriate relation between stiffness and loads induced at the interface. Mechanical Bench Assembly shown in Fig. 2 is the main thermo-structural component of CAS and it is composed of different thermo-mechanical components such as: \u2022 Main Bracket \u2022 Bipods \u2022 MCCD and Proximity Electronics Thermal Straps Proc. of SPIE Vol. 10563 105634P-3 Main Bracket The Main Bracket is a Ti6Al4V bracket of complex geometry, which is the main structural element of CAS, and its complex shape provides the following functionalities: \u2022 It provides support and mechanical tolerances for relative positioning of optical sensitive elements: o Bipods o MCCD (mounted on dedicated assembly) o Optical Assembly \u2022 Stiffness and structural strength to support the above assemblies Titanium choice (with respect to invar) is based on its lower mass density, high strength and better machining capabilities in spite of a higher thermal expansion coefficient (worst thermal performance)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002759_f_version_1705227457-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002759_f_version_1705227457-Figure9-1.png", + "caption": "Figure 9. (a) Fabricated sample. (b) Measurement setup. (c) The simulated and measured results of the co- and cross-polarized reflection coefficients. (d) Axial ratio.", + "texts": [ + " The findings of the study suggest that these elements reveal the reasons behind the attainment of outstanding performance and the ultra-wideband LTC polarization conversion. The proposed design and the state of the art as already published are compared in Table 1. With the aim of verifying the accuracy of the numerical simulation outcomes, a physical prototype of the proposed polarization rotator was fabricated using a 120 mm \u00d7 120 mm \u00d7 1.6 mm FR-4 sheet. Subsequently, a series of experimental measurements were performed. The prototype, illustrated in Figure 9a, was fabricated using well-known PCB techniques. The sheet underwent selective etching, forming a well-defined pattern of 20 mm \u00d7 20 mm unit cells on one side while keeping the metallic cladding unchanged on the other side. To determine both the co-polarized and cross-polarized reflection coefficients, we placed the fabricated design in front of two horn ports (antennas): port 1 for transmission and port 2 for receiving the reflection of the electromagnetic waves. The amplitude and phase of the reflected signal from the metasurface were obtained by connecting the ports to a vector network analyzer. The measurement setup is illustrated in Figure 9b. To obtain the co-polarized reflection coefficients, the two ports were aligned in the same orientation, either horizontally or vertically. Conversely, for measuring the cross-polarized reflection coefficients, the ports were set in a perpendicular configuration to one another. The results obtained from the measurements and simulations of an incident wave for the x-polarized situation are shown in Figure 9c,d. Figure 9c presents the magnitude of both the co-polarized as well as the crosspolarized reflection coefficients, while Figure 9d shows the AR. Both the simulated and measured AR consistently remain below 3 dB within the frequency range 15.41\u201325.23 GHz, showing reasonable agreement. The slight variations may be attributed to fabrication imperfections and experimental tolerances. This paper proposes a simple reflective dipole-shaped ultra-wideband LTC polarization converter. The proposed polarization converter successfully performed ultra-wideband LTC conversions and achieved an efficiency of 98% for frequencies ranging from 15" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001191_8948470_09252143.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001191_8948470_09252143.pdf-Figure1-1.png", + "caption": "FIGURE 1. Configuration of a NFF slotted waveguide antenna with four-corner feed.", + "texts": [ + " As far as we know, the focus\u2019s position was generally selected to be at least 3\u03bb away from the antenna aperture [17]. Because the closer the focus is, the more critical phase compensation, which brings a more significant challenge to the feeding network design, is required. However, a closer focus means a higher focusing gain, which can lead to the size reduction in wireless charging and RFID systems and to the enhancement of focusing effects. In this article, a 3D-printed NFF slotted waveguide array antenna with a focal distance of only 1.5\u03bb is presented, as illustrated in Fig. 1. We propose a four-corner-feed structure to realize the quadratic phase distribution naturally. In this case, the waveguide width can be optimized to achieve the desired phase distribution. In addition, the high sidelobe and the grating lobes on the focal plane, caused by the close focus and the residue phase error, can be eliminated by introducing the sparse array based on the particle swarm optimization. Simulation and measurement results verify that we achieved a desirable focusing effect on the focal plane 45 mm away from the antenna aperture at 10 GHz", + " 4, when the focus approaching the array aperture, the FG increases, and the FS, as well as the DoF, decreases. This phenomenon is essential for some near-field applications. On the other hand, the smaller the FD is, the higher the SLL will be, and more phase compensation is required. Therefore, it is very challenging to realize an NFF antenna with a close focus and low sidelobes. III. ANTENNA STRUCTURE To realize a close focus, we introduce a unique four-cornerfeed structure [37] instead of the traditional center-feed structure [38] in this article. Fig. 1 illustrates the overall structure of the proposed array antenna. It is composed of two layers: the upper radiating part and the lower feeding part, which is fed by a coaxial probe at the bottom. Through an H-shaped power divider, the input power is equally and simultaneously transmitted into four corners without frequency dependence. The design principle of coupling and radiating slots is explained in the following paragraphs. The center-inclined coupling slots couple the incident wave from the lower feeding waveguide into the upper radiating waveguide", + " Unfortunately, the guidedwavelength in a rectangular waveguide is usually longer than the wavelength in the free space, and leads to the generation of grating lobes. Since the element spacings in both feeding and radiating waveguides are half guided-wavelength in common, the internal phase delays happening in a four-cornerfeed structure can be estimated straightforwardly. The values listed in Table 1 are simply the multiples of \u2212180 degrees. IV. ARRAY SYNTHESIS A. DETERMINATION OF WAVEGUIDE DIMENSIONS As an example, the proposed antenna illustrated in Fig. 1 is designed at 10 GHz with a focus at (0, 0,z = r0). It is noteworthy that a focus even with the FD as close as \u03bb/10 can be achieved by adopting the proposed antenna structure. Nevertheless, there is a tradeoff between the FG and the SLL as mentioned above. Therefore, to enhance the FG as well as to suppress the SLL to some extent, we fix r0 at 45 mm (1.5\u03bb) as a more moderate value. In order to focus along the central z-axis, the internal phase delay \u03d5ij compensating for the external phase delay should satisfy the following equation with fourfold symmetry" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004696_f_2018_cc_c7cc09133h-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004696_f_2018_cc_c7cc09133h-Figure4-1.png", + "caption": "Fig. 4 A molecular rotary motor driven by light attached to gold surface.24 Adapted by permission from ref. 24. Copyright 2005 Nature Publishing Group.", + "texts": [ + " In particular, it highlights stimuli-responsive molecular rotors working on solid surfaces that undergo rotational motion to perform useful functions, for example, moving a molecular car or gating the release of cargoes. The stimuli include chemical, light and electricity. Feringa et al. reported the first example of surface bound molecular rotary motors in 2005.24 The rotary motion of this motor is similar to the one discussed in Fig. 3, but the rotary motion does not induce any subsequent translational motion. The rotary motor design has four parts: a rotor, a stator, an axle and legs (Fig. 4). A chiral helical alkene with an upper half that serves as a rotor and is connected through a carbon\u2013carbon double bond (axle) to a lower half that serves as a stator. The stator at the bottom is derivatised with two thiol-functionalised legs. These thiol legs attach the whole system onto the gold surface and the two-point attachment avoids uncontrollable rotation of the motor. Input sequences such as shining light and subsequent heating rotate the upper half of the molecule in an anticlockwise fashion to 1801 with respect to the bottom half" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure1-1.png", + "caption": "Fig. 1 Coordinate systems for transmission pairs\u2019 relative position.", + "texts": [ + " This study establishes an analytical model for the face worm gear drive, and strictly derives the equations for three main indicators evaluating meshing performance in a given coordinate system. The changes in meshing performance on the i and e sides of the spiroid gear are analyzed as the spiroid worm angle decreases from 5\u00b0 to 0\u00b0. The accuracy of the analytical results is verified by using statics simulation. As shown in the coordinate system below, the pinion offset is placed on the face worm gear: Figure 1 describes that the initial position of the pinion is indicated by a static reference frame \u03a3(os: xs, ys, zs) established on the pinion and the worm wheel, as well as by \u03a3p(op: xp, yp, zp). The pinion and the worm wheel rotate around axes z1 and z2 with angular velocity vectors \u03c91 and \u03c92, respectively. The dynamic coordinate system \u03a3m1 (om1: 2 \u00a9 2023 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2023jamdsm0073] xm1, ym1, zm1) is consistently linked to the pinion, whereas \u03a3m2 (om2: xm2, ym2, zm2) is firmly attached to the worm gear" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001462_cle_download_248_154-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001462_cle_download_248_154-Figure6-1.png", + "caption": "Fig. 6. The layout of the MTM-loaded two-element microstrip array antenna: (a) Top layer (b) bottom layer.", + "texts": [ + "248 Vol 4 | Issue 5 | October 2020 3 By the following expressions, Permittivity (\u03b5) and Permeability (\u00b5) are related to refractive index and the impedance [21]: \ud835\udc67 = \u00b1\u221a (1+\ud835\udc4611)2\u2212\ud835\udc4621 2 (1\u2212\ud835\udc4611)2\u2212\ud835\udc4621 2 , (1) \ud835\udc52\ud835\udc57\ud835\udc5b\ud835\udc580\ud835\udc51 = \ud835\udc4621 1\u2212\ud835\udc4611 \ud835\udc67\u22121 \ud835\udc67+1 , (2) \ud835\udc5b = 1 \ud835\udc580\ud835\udc51 [{\ud835\udc3c\ud835\udc5a[\ud835\udc59\ud835\udc5b(\ud835\udc52\ud835\udc57\ud835\udc5b\ud835\udc580\ud835\udc51)] + 2\ud835\udc5a\ud835\udf0b} \u2212 \ud835\udc57 [\ud835\udc45\ud835\udc52[\ud835\udc59\ud835\udc5b(\ud835\udc52\ud835\udc57\ud835\udc5b\ud835\udc580\ud835\udc51)]]], (3) \ud835\udf00 = \ud835\udc5b \ud835\udc67 , (4) \ud835\udf07 = \ud835\udc5b\ud835\udc67 (5) where n is the refractive index, d is the maximum length of the unit element, m is the branch due to the periodicity of the sinusoidal function, k0 is the wavenumber and z is the input impedance. Finally, the complex permittivity and permeability curves were obtained using a MATLAB script which used the presented formulations [1], [18] (Fig. 5(a) and (b)). Also, the refractive index and the impedance of the MTM unit cell are shown in Figs. 5(c) and 5(d). As shown in Figure 5, the MTM unit cell has a negative refractive index around the resonant frequency. As show in Fig. 6a, a microstrip monopole patch antenna that was loaded by the MTM unit cell, utilized to design a two-element microstrip array antenna. A dual-shaped feed structure utilized in the array antenna design to excitation of the MTM-loaded monopoles and promote an even field distribution. The dimension of the top layer of the array antenna is 21\u00d721 mm2. Other dimensions of the array antenna structure as shown in Fig. 6(a), are as follows: (in millimeter: mm): W1=10.5, W2=2, W3=3.5, W4=2.75, W5=11.2, W6=1, W7=2.85, W8=3, and d=9.2. The impedance bandwidth of the Structures with low energy storage, are wider due to their low Q factor. So, in order to increase the bandwidth of the array antenna and improve matching, a partial ground plane with WGP= 7.5 mm was utilized. Furthermore, a slot with dimension 5\u00d73 mm2 (Ls\u00d7Ws) was introduced to the partial ground plane, in order to gain more improvements. In order to obtain the wideband matching, the LS and WS parameters were optimized. The layout of the bottom layer of the array antenna is shown in Fig. 6 (b). DOI: http://dx.doi.org/10.24018/ejece.2020.4.5.248 Vol 4 | Issue 5 | October 2020 4 HFSS Software was used to analyze the UWB MTMloaded two-element array antenna schematic. The substrate is FR4 with thickness 1.6 mm, loss tangent of about 0.025, and a dielectric constant \u03b5r =4.3. The simulation results of the impedance bandwidth of the MTM-loaded two-element array antenna is shown in Fig. 7. It can be seen that the -10 dB impedance bandwidth is 3.36~9.48 GHz. However, the simulated return loss is a little above than -10 dB at frequency around 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000475_cle_download_209_208-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000475_cle_download_209_208-Figure9-1.png", + "caption": "Figure 9: Displacement on the Foot Support.", + "texts": [], + "surrounding_texts": [ + "Commercialization of the Exo-Limb project can be made possible by developing large-scale production methods. The scope of this project focuses mainly on research and design, which is a major component of the overall budget. Future goals for the project, if continued, would be to develop large-scale production methods. The raw materials for the Exo-Limb are relatively cheap. The cost for the metal components totals about $40 for one device. Other materials, such as the straps, padding, and miscellaneous components, total at about $20. The Exo-Limb uses a clinical prosthetic foot made by \u00d6ssur to assist in the research and development of the natural walking gait. If large-scale production methods were to be developed in the future, an alternative would be to design a cost effective foot attachment. The groundwork has been laid for the research and development of a hands-free crutch. If the project were to continue, the planning and implementation of largescale production methods would certainly decrease the cost to produce the Exo-Limb." + ] + }, + { + "image_filename": "designv8_17_0002525_127_4_127_4_589__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002525_127_4_127_4_589__pdf-Figure5-1.png", + "caption": "Fig. 5. Structural drawing of radial coreless synchronous generator.", + "texts": [], + "surrounding_texts": [ + "\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u767a\u96fb\u6a5f\u306e\u63d0\u6848\n\u306f\u5c0e\u4f53\u306e\u9577\u3055\u3092\u8868\u3059\u3002\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e \u5834\u5408\uff0c\u767a\u96fb\u6a5f\u306e\u4e2d\u5fc3\u90e8\u5206\u304b\u3089\u306e\u8ddd\u96e2\u306b\u3088\u3063\u3066\u78c1\u675f\u5909\u5316\u306e\u901f \u5ea6\u304c\u5909\u308f\u308b\u304c\uff0c\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e\u5834\u5408\u3067\u306f\uff0c \u4e2d\u5fc3\u304b\u3089\u306e\u8ddd\u96e2\u306b\u304b\u304b\u308f\u3089\u305a\uff0c\u78c1\u675f\u5909\u5316\u306e\u901f\u5ea6\u304c\u4e00\u5b9a\u3067\u3042 \u308b\u305f\u3081\uff0c\u305d\u308c\u305e\u308c\u306e\u5c0e\u4f53 1\u672c\u5f53\u308a\u306e\u56de\u8ee2\u901f\u5ea6 n [min\u22121]\u306b \u304a\u3051\u308b\u901f\u5ea6\u8d77\u96fb\u529b\u306e\u5b9f\u52b9\u5024 Eax\uff0cEra [V]\u306f\uff0c\u4ee5\u4e0b\u306e\u5f0f\u3067\u8868 \u3059\u3053\u3068\u304c\u3067\u304d\u308b\u3002\nEax = 1\u221a 2\n\u222b r2\nr1\n2\u03c0r ( n 60 ) B dr\n= 1\u221a 2 \u03c0 ( r2 2 \u2212 r2 1 ) ( n 60 ) B \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (2)\nEra = 1\u221a 2 2\u03c0r ( n 60 ) B \u00d7 h\n= 2\u221a 2 \u03c0r ( n 60 ) Bh \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (3)\n\u3053\u3053\u3067\uff0cr1 [m]\u306f\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e\u5185 \u90e8\u78c1\u77f3\u306e\u4e2d\u5fc3\u304b\u3089\u306e\u5185\u5f84\uff0cr2 [m]\u306f\u305d\u306e\u5916\u5f84\uff0cr [m]\u306f\u30e9\u30b8 \u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e\u5185\u90e8\u78c1\u77f3\u306e\u56de\u8ee2\u534a\u5f84\uff0ch [m]\u306f \u305d\u306e\u9ad8\u3055\u3092\u8868\u3057\u3066\u3044\u308b\u3002(2)\uff0c(3)\u5f0f\u3088\u308a\u5185\u90e8\u78c1\u77f3\u306e\u9762\u7a4d\u304c \u5171\u306b\u540c\u3058\u3067\u3042\u308b\u306a\u3089\u3070\u57fa\u672c\u7684\u306a\u51fa\u529b\u306f\u5909\u308f\u3089\u306a\u3044\u3053\u3068\u304c\u5206 \u304b\u308b\u3002 \u4eca\u56de\u63d0\u6848\u3059\u308b\u767a\u96fb\u6a5f\u306f\u4e09\u76f8\u51fa\u529b\u767a\u96fb\u6a5f\u3067\u3042\u308a\uff0c\u8a66\u4f5c\u6a5f\u3067 \u306f\u5185\u90e8\u7d50\u7dda\u3092 3\u76f4\u5217\uff0c2\u4e26\u5217\u3067Y\u7d50\u7dda\u3057\u3066\u3044\u308b\u305f\u3081\uff0c(3)\u5f0f \u3088\u308a\u4e09\u76f8\u5dfb\u7dda\u306e\u7dda\u9593\u96fb\u5727\u306e\u5b9f\u52b9\u5024 E\u2032ra [V]\u3092\u6c42\u3081\u308b\u3068\uff0c\nE\u2032ra = 2 \u221a 3sNEra = \u221a 6sN\u03c0rhB ( n 30 ) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (4)\n\u3067\u8868\u3059\u3053\u3068\u304c\u3067\u304d\u308b\u3002\u3053\u3053\u3067\uff0cs\u306f\u30b3\u30a4\u30eb\u76f4\u5217\u6570\uff0cN \u306f\u30b3 \u30a4\u30eb\u5dfb\u304d\u6570\u3092\u8868\u3059\u3002\u307e\u305f\uff0c\u78c1\u6975\u6570\u3068\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u6570\u306e\u6bd4 \u304c m : n\u3068\u3057\u305f\u5834\u5408\uff0c1 : 1\u3067\u3042\u308b\u5834\u5408\u3068\u6bd4\u3079\uff0c\u51fa\u529b\u306b\u5dee\u304c \u51fa\u308b\u3082\u306e\u3068\u8003\u3048\u3089\u308c\u308b\u3002\u3053\u3053\u3067\u306f\u305d\u306e\u4fc2\u6570\u3092 \u03b1\u3068\u7f6e\u304f\u3002\u3057 \u305f\u304c\u3063\u3066\uff0c\u5b9f\u969b\u306e\u96fb\u5727\u306e\u5b9f\u52b9\u5024\u306f\uff0c\nE\u2032\u2032ra = \u03b1E\u2032ra = \u221a 6\u03b1sN\u03c0rhB ( n 30 ) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (5)\n\u3068\u306a\u308b\u3002\u306a\u304a\uff0c\u7b46\u8005\u3089\u306e\u89e3\u6790 (13) \u306b\u3088\u308b\u3068\uff0c\u78c1\u6975\u6570\uff1a\u30b3\u30a4\u30eb \u30b9\u30ed\u30c3\u30c8\u6570\u306e\u6bd4\u304c 4 : 3\u306e\u5834\u5408\uff0c\u03b1\u306f 1.2\u3067\u3042\u308b\u3053\u3068\u304c\u78ba\u8a8d \u3055\u308c\u3066\u3044\u308b\u3002\n\u307e\u305f\uff0c\u30c0\u30a4\u30aa\u30fc\u30c9\u30d6\u30ea\u30c3\u30b8\uff0c\u7d14\u62b5\u6297\u8ca0\u8377\u3092\u63a5\u7d9a\u3057\u305f\u5834\u5408\u306e \u51fa\u529b\u96fb\u5727 Eout [V]\uff0c\u51fa\u529b\u96fb\u6d41 Iout [A]\uff0c\u51fa\u529b\u96fb\u529b Pout [W]\u306f\nEout = 3 \u221a\n2 \u03c0 E\u2032\u2032ra Z Zin + Z \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (6)\nIout = Eout/Z \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (7) Pout = Eout/Z 2 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (8)\n\u3067\u6c42\u3081\u308b\u3053\u3068\u304c\u3067\u304d\u308b\u3002\u3053\u3053\u3067\uff0cZin [\u2126]\u306f\u5185\u90e8\u62b5\u6297\u5024\uff0cZ [\u2126] \u306f\u8ca0\u8377\u62b5\u6297\u5024\u3092\u8868\u3057\u3066\u3044\u308b\u3002\n\u30082\u30fb3\u3009 \u591a\u6975\u6a5f\u5316\u306e\u969b\u306e\u512a\u4f4d\u70b9 \u4eca\u56de\u63d0\u6848\u3059\u308b\u767a\u96fb\u6a5f\u306e \u5229\u70b9\u3068\u3057\u3066\uff0c\u307e\u305a\u767a\u96fb\u6a5f\u306e\u5f84\u3068\u9ad8\u3055\u3092\u72ec\u7acb\u3055\u305b\u3066\u8a2d\u5b9a\u3067\u304d \u308b\u70b9\u304c\u6319\u3052\u3089\u308c\u308b\u3002\u767a\u96fb\u5bb9\u91cf\u3092\u5897\u52a0\u3055\u305b\u308b\u305f\u3081\u306b\u306f\uff0c\u901f\u5ea6 \u3082\u3057\u304f\u306f\u78c1\u675f\u5bc6\u5ea6\u306e\u5897\u52a0\u304c\u5fc5\u8981\u3067\u3042\u308a\uff0c\u5b9f\u969b\u306b\u306f\u78c1\u77f3\u8868\u9762\n\u7a4d\u3084\u78c1\u675f\u5bc6\u5ea6\uff0c\u30b3\u30a4\u30eb\u5dfb\u6570\u3092\u5897\u52a0\u3055\u305b\u308b\u5fc5\u8981\u304c\u3042\u308b\u3002\u3064\u307e \u308a\uff0c\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3067\u3042\u308b\u5834\u5408\uff0c\u69cb\u9020\u7684\u306b \u78c1\u77f3\u306e\u8868\u9762\u7a4d\u306a\u3069\u3092\u5897\u52a0\u3055\u305b\u3088\u3046\u3068\u3059\u308b\u3068\uff0c\u767a\u96fb\u6a5f\u306e\u5f84\u65b9 \u5411\u306b\u3057\u304b\u4f59\u88d5\u304c\u306a\u304f\uff0c\u767a\u96fb\u5bb9\u91cf\u3092\u5897\u52a0\u3055\u305b\u308b\u305f\u3081\u306b\u306f\uff0c\u767a\u96fb \u6a5f\u306e\u5f84\u3092\u5927\u304d\u304f\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\u3002\u3064\u307e\u308a\uff0c\u767a\u96fb\u5bb9\u91cf\u306f\u767a\u96fb \u6a5f\u306e\u5f84\u306b\u4f9d\u5b58\u3059\u308b\u3053\u3068\u306b\u306a\u308b\u3002\u3055\u3089\u306b\uff0c\u767a\u96fb\u6a5f\u306e\u5f84\u304c\u5927\u304d \u304f\u306a\u308b\u306b\u3064\u308c\u9060\u5fc3\u529b\u3082\u5927\u304d\u304f\u306a\u308b\u305f\u3081\uff0c\u30d9\u30a2\u30ea\u30f3\u30b0\u306b\u639b\u304b \u308b\u5076\u529b\u304c\u5927\u304d\u304f\u306a\u308a\uff0c\u5f37\u5ea6\u306e\u70b9\u306b\u304a\u3044\u3066\u554f\u984c\u304c\u51fa\u3066\u304f\u308b\u53ef \u80fd\u6027\u304c\u3042\u308b\u3002\u3057\u304b\u3057\uff0c\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3067\u306f \u754c\u78c1\u6975\u304c\u8ef8\u306b\u5e73\u884c\u306b\u306a\u308b\u3088\u3046\u306b\u8a2d\u8a08\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u56f3 2(b) \u304a\u3088\u3073 (3)\u5f0f\u3088\u308a\uff0c\u767a\u96fb\u6a5f\u672c\u4f53\u306e\u9ad8\u3055\u3092\u5927\u304d\u304f\u3059\u308b\u3053\u3068\u3067\u5185 \u90e8\u306e\u78c1\u77f3\u3084\u30b3\u30a4\u30eb\u306e\u9ad8\u3055\u3082\u5927\u304d\u304f\u306a\u308b\u3053\u3068\u304c\u5206\u304b\u308b\u3002\u3057\u305f \u304c\u3063\u3066\uff0c\u767a\u96fb\u6a5f\u5185\u90e8\u306e\u78c1\u77f3\u8868\u9762\u7a4d\u3092\u5897\u52a0\u3055\u305b\u308b\u5834\u5408\uff0c\u767a\u96fb \u6a5f\u306e\u5f84\u3068\u9ad8\u3055\u3092\u72ec\u7acb\u3055\u305b\u3066\u8003\u616e\u3067\u304d\u308b\u305f\u3081\uff0c\u767a\u96fb\u6a5f\u306e\u5f84\u3060 \u3051\u306b\u4f9d\u5b58\u3059\u308b\u3053\u3068\u306a\u304f\u767a\u96fb\u5bb9\u91cf\u3092\u5897\u52a0\u3055\u305b\u308b\u3053\u3068\u304c\u3067\u304d\u308b\u3002 \u3055\u3089\u306b\uff0c\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u5f62\u72b6\u304c\u5fc5\u305a\u9577\u65b9\u5f62\u306b\u306a\u308b\u305f\u3081\uff0c \u591a\u6975\u6a5f\u5316\u304c\u5bb9\u6613\u3067\u3042\u308b\u70b9\u3082\u5927\u304d\u306a\u512a\u4f4d\u70b9\u3068\u3057\u3066\u6319\u3052\u3089\u308c\u308b\u3002 \u90fd\u5e02\u578b\u98a8\u529b\u767a\u96fb\u3067\u306f\u4f4e\u98a8\u901f\u3067\u3042\u308b\u3053\u3068\u304b\u3089\uff0c\u4f4e\u56de\u8ee2\u3067\u3082\u9ad8 \u3044\u96fb\u5727\u3092\u51fa\u529b\u3059\u308b\u3053\u3068\u304c\u671b\u307e\u3057\u3044\u3002\u305d\u306e\u5bfe\u7b56\u306e 1\u3064\u3068\u3057\u3066 \u591a\u6975\u6a5f\u5316\u304c\u8003\u3048\u3089\u308c\u308b\u306e\u3060\u304c\uff0c\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f \u767a\u96fb\u6a5f\u306e\u5834\u5408\uff0c\u56f3 3\u306e\u3088\u3046\u306b\u30b3\u30a4\u30eb\u5f62\u72b6\u304c\u69cb\u9020\u4e0a\u6247\u5f62\u307e\u305f \u306f\u4e09\u89d2\u5f62\u306b\u306a\u3089\u3056\u308b\u3092\u5f97\u306a\u3044\u305f\u3081\uff0c\u767a\u96fb\u6a5f\u306e\u5f84\u306b\u5bfe\u3057\u3066\u4e00 \u5b9a\u4ee5\u4e0a\u306e\u591a\u6975\u6a5f\u5316\u304c\u88fd\u4f5c\u4e0a\u56f0\u96e3\u3068\u306a\u308b\u3002\u3057\u304b\u3057\uff0c\u30e9\u30b8\u30a2\u30eb \u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e\u5834\u5408\uff0c\u69cb\u9020\u4e0a\u30b3\u30a4\u30eb\u5f62\u72b6\u304c\u5fc5\u305a\u9577 \u65b9\u5f62\u306b\u306a\u308b\u305f\u3081\uff0c\u88fd\u4f5c\u4e0a\u591a\u6975\u6a5f\u5316\u304c\u5bb9\u6613\u3067\uff0c\u5c06\u6765\u306e\u91cf\u7523\u5316 \u3084\u4f4e\u30b3\u30b9\u30c8\u5316\u304c\u53ef\u80fd\u3067\u3042\u308b\u3068\u8003\u3048\u3089\u308c\u308b\u3002 \u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8 nc\u500b\u3092\u6301\u3064\u767a\u96fb\u6a5f\u3092\u8a2d\u8a08\u3057\u3088\u3046\u3068\u3057\u305f\u5834 \u5408\uff0c\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3068\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec \u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e 1\u500b\u3042\u305f\u308a\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u9762\u7a4d\u306f\u305d\u308c\u305e\u308c\uff0c \u4ee5\u4e0b\u306e\u5f0f\u306e\u3088\u3046\u306b\u306a\u308b\u3002\nS ax = \u03c0\nnc\n( r2\n2 \u2212 r2 1\n) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (9)\nS ra = 2\u03c0rh\nnc \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (10)\n\u96fb\u5b66\u8ad6 B\uff0c127 \u5dfb 4 \u53f7\uff0c2007 \u5e74 591", + "\u305f\u3060\u3057\uff0cr1 [m]\uff0cr2 [m]\u306f\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f \u306e\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u306e\u5185\u5f84\u304a\u3088\u3073\u5916\u5f84\uff0cr [m]\uff0ch [m]\u306f\u30e9\u30b8\u30a2 \u30eb\u578b\u306e\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u306e\u56de\u8ee2\u534a\u5f84\u304a\u3088\u3073\u9ad8\u3055\u3092\u8868\u3057\u3066\u304a\u308a\uff0c \u3053\u306e\u3067\u306f\u8a08\u7b97\u306e\u7c21\u5358\u5316\u306e\u305f\u3081\uff0c\u524d\u8ff0\u306e\u78c1\u77f3\u5bf8\u6cd5\u3068\u540c\u4e00\u306b\u8a2d \u5b9a\u3057\u3066\u3044\u308b\u3002\u307e\u305f\uff0c\u4e21\u8005\u306e\u30b3\u30a4\u30eb\u9762\u7a4d S xa \u304a\u3088\u3073 S ra \u304c\u540c \u3058\u306b\u306a\u308b\u3088\u3046\u306b\u8a2d\u8a08\u3057\u305f\u5834\u5408\uff0c\u4ee5\u4e0b\u306e\u95a2\u4fc2\u5f0f\u304c\u6210\u308a\u7acb\u3064\u3002\nh = 1 2\nr2 2 \u2212 r2 1\nr \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (11)\n\u3053\u3053\u3067\uff0c\u30b3\u30a4\u30eb\u675f\u306e\u65ad\u9762\u7a4d wc [mm]\u3092\u8003\u616e\u3059\u308b\u3068\uff0c1\u3064 \u306e\u30b3\u30a4\u30eb\u675f\u3092\u91cd\u306a\u3089\u306a\u3044\u3088\u3046\u306b\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u5185\u306b\u57cb\u3081\u8fbc \u3080\u306b\u306f\uff0c\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u306e\u5834\u5408\u3067\u306f\uff0c\u6b21\u306e\u3088\u3046\u306a\u5236\u7d04\u6761\u4ef6\u304c \u5b58\u5728\u3059\u308b\u3002\nnc < \u03c0r1\nwc + 1 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (12)\n\u4e00\u65b9\uff0c\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e\u5834\u5408\u3067\u306f\uff0c\u5236\u7d04\u6761 \u4ef6\u306f\uff0c\nnc < \u03c0r wc \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (13)\n\u3068\u306a\u308b\u3002 \u4f8b\u3048\u3070\uff0cr2 = 75 mm\uff0cr1 = 55 mm\u306e\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec \u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3092\u60f3\u5b9a\u3057\u305f\u5834\u5408\uff0c\u540c\u4e00\u6027\u80fd\u306e\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2 \u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3092\u4f5c\u88fd\u3059\u308b\u305f\u3081\uff0cr = 75 mm\u3068\u3059\u308b\u3068 (11) \u5f0f\u306e\u95a2\u4fc2\u5f0f\u304b\u3089 h = 17.3 mm \u3068\u306a\u308b\u3002\u3053\u3053\u3067\u30b3\u30a4\u30eb\u675f\u3092 wc = 4 mm\uff08\u7dda\u5e45 0.2 mm\u306e\u30b3\u30a4\u30eb\u9285\u7dda 400\u5dfb\u304d\u306b\u76f8\u5f53\uff09\u3068 \u4eee\u5b9a\u3059\u308b\u3068\uff0c\u30a2\u30ad\u30b7\u30e3\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3067\u306f (12)\u5f0f \u3088\u308a 44\u6975\u307e\u3067\u3057\u304b\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u3092\u4f5c\u88fd\u3067\u304d\u306a\u3044\u3002\u5bfe\u3057 \u3066\uff0c\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3067\u306f (13)\u5f0f\u304b\u3089 58\u500b\u307e \u3067\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u3092\u4e26\u3079\u308b\u3053\u3068\u304c\u3067\u304d\u308b\u3002\u3057\u305f\u304c\u3063\u3066\uff0c\u540c \u4e00\u767a\u96fb\u6a5f\u534a\u5f84\u3067\u3067\u304d\u308b\u3060\u3051\u591a\u6975\u6a5f\u5316\u3055\u305b\u308b\u3088\u3046\u306a\u8a2d\u8a08\u3092\u8003 \u3048\u305f\u5834\u5408\uff0c\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u306e\u65b9\u304c\u30a2\u30ad\u30b7\u30e3 \u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u540c\u671f\u767a\u96fb\u6a5f\u3088\u308a\u6709\u5229\u3067\u3042\u308b\u3053\u3068\u304c\u5206\u304b\u308b\u3002\n3. \u7406\u8ad6\u8a08\u7b97\u5024\u3068\u8a66\u4f5c\u6a5f\u5b9f\u6e2c\u5024\u306e\u6bd4\u8f03\n\u672c\u7ae0\u3067\u306f (5)\uff5e(8)\u5f0f\u3092\u5b9f\u8a3c\u3059\u308b\u305f\u3081\u306b\u534a\u5f84 75 mm\u306e\u5c0f\u578b\n\u8a66\u4f5c\u6a5f\u3092\u4f5c\u88fd\u3057\u305f\u3002\u305d\u306e\u8a66\u4f5c\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9\u767a\u96fb\u6a5f\u306e \u5916\u89b3\u5199\u771f\u3092\u56f3 4\u306b\uff0c\u56f3 5\u306b\u306f\u305d\u306e\u69cb\u9020\u56f3\u3092\u793a\u3059\u3002\u307e\u305f\u767a\u96fb \u6a5f\u306e\u8af8\u69cb\u6210\u3092\u8868 1\u306b\u793a\u3059\u3002 \u30083\u30fb1\u3009 \u5b9f\u9a13\u65b9\u6cd5 \u4eca\u56de\u63d0\u6848\u3057\u305f\u30e9\u30b8\u30a2\u30eb\u578b\u30b3\u30a2\u30ec\u30b9 \u540c\u671f\u767a\u96fb\u6a5f\u306e\u8a66\u4f5c\u6a5f\u3092\u7528\u3044\u3066\uff0c\u5ba4\u5185\u306b\u3066\u7279\u6027\u5b9f\u9a13\u3092\u884c\u306a\u3063\n\u8868 1 \u767a\u96fb\u6a5f\u69cb\u6210\nTable 1. Construction of prototype.\n592 IEEJ Trans. PE, Vol.127, No.4, 2007", + "\u305f\u3002\u56f3 6\u306b\u5b9f\u9a13\u56de\u8def\u3092\u793a\u3059\u3002\u5b9f\u9a13\u65b9\u6cd5\u3068\u3057\u3066\u306f\uff0c\u30a4\u30f3\u30d0\u30fc \u30bf\u5236\u5fa1\u306e\u3067\u304d\u308b\u96fb\u52d5\u6a5f\u3092\u7528\u3044\uff0c\u30ab\u30c3\u30d7\u30ea\u30f3\u30b0\u306b\u3066\u767a\u96fb\u6a5f\u3068 \u63a5\u7d9a\u3057\u3066\u767a\u96fb\u6a5f\u3092\u56de\u8ee2\u3055\u305b\u305f\u3002\u305d\u306e\u5f8c\uff0c\u6574\u6d41\u56de\u8def\u3092\u901a\u3057\u3066 \u76f4\u6d41\u306b\u6574\u6d41\u3057\uff0c\u30e1\u30bf\u30eb\u30af\u30e9\u30c3\u30c9\u62b5\u6297\u306b\u63a5\u7d9a\u3057\u305f\u3002\u6e2c\u5b9a\u306b\u306f YOKOGAWA\u88fdWT230\u30c7\u30a3\u30b8\u30bf\u30eb\u30de\u30eb\u30c1\u30e1\u30fc\u30bf\u3092\u7528\u3044\u3066 \u4e09\u76f8\u4ea4\u6d41\u96fb\u5727\uff0c\u96fb\u6d41\uff0c\u51fa\u529b\u96fb\u529b\u306e\u5024\u3092\u6e2c\u5b9a\u3057\u305f\u3002\u307e\u305f\uff0c\u56de \u8ee2\u6570\u306e\u6e2c\u5b9a\u306b\u306fYOKOGAWA\u88fd 3632\u30c7\u30b8\u30bf\u30eb\u56de\u8ee2\u8a08\u3092\u7528 \u3044\u3066\u975e\u63a5\u89e6\u6e2c\u5b9a\u3092\u884c\u306a\u3063\u305f\u3002\u3053\u306e\u72b6\u614b\u306b\u304a\u3044\u3066\u8a66\u4f5c\u767a\u96fb\u6a5f \u306e\u7279\u6027\u3092\u8abf\u3079\u305f\u3002 \u30083\u30fb2\u3009 \u5b9f\u9a13\u7d50\u679c (4)\uff0c(5)\u5f0f\u304b\u3089\u5f97\u3089\u308c\u305f\u8a08\u7b97\u7d50\u679c\u3068 \u5b9f\u9a13\u3067\u5f97\u3089\u308c\u305f\u7121\u8ca0\u8377\u8d77\u96fb\u529b\u3092\u56f3 7\u306b\u793a\u3059\u3002\u306a\u304a\uff0c\u4eca\u56de\u306e \u8a66\u4f5c\u6a5f\u3067\u306f\uff0c\u8868 1\u3088\u308a\u78c1\u6975\u6570\u304c 24\uff0c\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\u30c8\u6570\u304c 18 \u3067\u3042\u308a\uff0c\u7b46\u8005\u3089\u306e\u89e3\u6790 (13)\u306b\u3088\u308b\u3068\uff0c\u78c1\u6975\u6570\uff1a\u30b3\u30a4\u30eb\u30b9\u30ed\u30c3\n\u56f3 9 \u96fb\u6d41\u7279\u6027\nFig. 9. Current characteristics.\n\u56f3 10 \u51fa\u529b\u7279\u6027\nFig. 10. Output power characteristics.\n\u30c8\u6570\u306e\u6bd4\u304c 4 : 3\u306e\u5834\u5408\uff0c(5)\u5f0f\u306e \u03b1\u306f 1.2\u3067\u3042\u308b\u3053\u3068\u304c\u78ba \u8a8d\u3055\u308c\u3066\u3044\u308b\u3002\u56f3 7\u304b\u3089\u5206\u304b\u308b\u3088\u3046\u306b\u6e2c\u5b9a\u5024\u3068 (5)\u5f0f\u304b\u3089 \u5f97\u3089\u308c\u308b\u8a08\u7b97\u5024\u304c\u307b\u307c\u4e00\u81f4\u3057\u3066\u3044\u308b\u3053\u3068\u304c\u78ba\u8a8d\u3067\u304d\u305f\u3002 \u6b21\u306b\uff0c\u8ca0\u8377\u62b5\u6297 90\u2126\u306e\u5834\u5408\u306e (6)\u5f0f\u304b\u3089\u5f97\u3089\u308c\u305f\u8a08\u7b97\u7d50 \u679c\u3068\u5b9f\u9a13\u3067\u5f97\u3089\u308c\u305f\u96fb\u5727\u7279\u6027\u3092\u56f3 8\u306b\u793a\u3059\u3002\u307e\u305f\u540c\u69d8\u306b\uff0c (7) \u5f0f\u304b\u3089\u5f97\u3089\u308c\u305f\u8a08\u7b97\u7d50\u679c\u3068\u5b9f\u9a13\u3067\u5f97\u3089\u308c\u305f\u96fb\u6d41\u7279\u6027\u3092 \u56f3 9\u306b\uff0c(8)\u5f0f\u304b\u3089\u5f97\u3089\u308c\u305f\u8a08\u7b97\u7d50\u679c\u3068\u5b9f\u9a13\u3067\u5f97\u3089\u308c\u305f\u51fa \u529b\u7279\u6027\u3092\u56f3 10\u306b\u305d\u308c\u305e\u308c\u793a\u3059\u3002\u305f\u3060\u3057\uff0c10\u2126\uff0c50\u2126\u306e\u5834 \u5408\uff0c\u30b3\u30a4\u30eb\u306e\u5c0e\u4f53\u7dda\u5f84\u306b\u3088\u308b\u96fb\u6d41\u5236\u9650\uff082.0 A\uff09\u306b\u3088\u308a\uff0c\u305d\u308c \u305e\u308c 300 min\u22121\uff0c700 min\u22121\u3067\u6e2c\u5b9a\u3092\u7d42\u4e86\u3057\u3066\u3044\u308b\u3002\u56f3 8\u3088 \u308a\uff0c1000 min\u22121\u306b\u304a\u3044\u3066 90\u2126\u6642\u306b\u6700\u5927\u3067 161 V\u306e\u96fb\u5727\u304c\uff0c \u56f3 9\u3088\u308a 300 min\u22121 \u306b\u304a\u3044\u3066 10 \u2126\u6642\u306b\u6700\u5927 2.03 A\u306e\u96fb\u6d41 \u304c\u305d\u308c\u305e\u308c\u5f97\u3089\u308c\u3066\u3044\u308b\u3002\u540c\u69d8\u306b\u56f3 10\u3088\u308a\uff0c\u6700\u5927 283 W \u306e\u51fa\u529b\u304c\u5f97\u3089\u308c\u3066\u3044\u308b\u3053\u3068\u304c\u5206\u304b\u308b\u3002\u52a0\u3048\u3066\uff0c\u305d\u308c\u305e\u308c\u306e \u7279\u6027\u306b\u304a\u3044\u3066\u8a08\u7b97\u5024\u3068\u6e2c\u5b9a\u5024\u304c\u307b\u307c\u4e00\u81f4\u3057\u3066\u3044\u308b\u3053\u3068\u3082\u78ba \u8a8d\u3067\u304d\u308b\u3002 \u90fd\u5e02\u578b\u98a8\u529b\u767a\u96fb\u3067\u306f\u4f4e\u98a8\u901f\u3067\u3042\u308b\u3053\u3068\u304c\u591a\u3044\u305f\u3081\uff0c\u57fa\u672c \u7684\u306b\u56de\u8ee2\u6570\u304c\u4f4e\u3044\u72b6\u614b\u304c\u7d9a\u304f\u3002\u305d\u3053\u3067\uff0c\u56f3 11\uff0c\u56f3 12 \u306b 200 min\u22121 \u4ee5\u4e0b\u306e\u4f4e\u56de\u8ee2\u9818\u57df\u3067\u306e\u96fb\u5727\u7279\u6027\uff0c\u51fa\u529b\u7279\u6027\u3092\u305d \u308c\u305e\u308c\u793a\u3059\u3002\u56f3 11\u306e\u96fb\u5727\u7279\u6027\u3088\u308a\uff0c100 min\u22121\u4ed8\u8fd1\u3067\u4e00\u822c \u7684\u306a\u84c4\u96fb\u6c60\u306e\u52d5\u4f5c\u96fb\u5727\u3067\u3042\u308b 12 V \u3092\u8d85\u3048\u308b\u305f\u3081\uff0c\u5145\u5206\u90fd \u5e02\u90e8\u306e\u4f4e\u98a8\u901f\u306b\u5bfe\u5fdc\u304c\u53ef\u80fd\u3067\u3042\u308b\u3068\u8003\u3048\u3089\u308c\u308b\u3002\u307e\u305f\u56f3 12 \u306e\u51fa\u529b\u7279\u6027\u3088\u308a\uff0c10\u2126\u306b\u304a\u3044\u3066 19 W\u306e\u51fa\u529b\u304c\u5f97\u3089\u308c\u3066\u304a\n\u96fb\u5b66\u8ad6 B\uff0c127 \u5dfb 4 \u53f7\uff0c2007 \u5e74 593" + ] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure17-1.png", + "caption": "Figure 17. Bar chart of the calculated ratio of stator total losses to the area of the supporting structure containing the water cooling system for Motor #1 and Motor #2; rotational torque is treated as input quantity and is identical for both motors.", + "texts": [ + " Rotor magnetic core losses are higher in Motor #2; still, value of these losses in relation to remaining rotor power losses, including PM losses, is very small. Temperature rise in motor elements is influenced by the ratio of existing power losses to the area of heat removal. Design of Motor #2, with respect to Motor #1, is characterized by greater stator diameter and diameter of structure containing a water-cooling system. Thus, while lengths of both motors are identical, the area of heat removal is greater in Motor #2. Bar charts showing the ratio of stator total losses to area of structure, where stator is positioned, are presented in Figure 17. If we compare losses shown in Figure 14 charts, with charts showing the ratio of these losses to the heat removal area (Figure 17), then we see that Motor #2 is much more promising; this is especially noticeable in the case of maximum speed at load torque equal to Tm = 450 Nm and Tm = 350 Nm. A similar comparison was performed for winding losses in Figure 18. Total slot area is much greater in Motor #2 (SQ = 3389.4 cm2) than in Motor #1 (SQ = 235.6 cm2). Ratio of power losses generated in permanent magnets to the rotor surface area where magnets are mounted is shown in Figure 19. The ratio of PM loss to heat removal area again underlines the advantages displayed by Motor #2, with respect to Motor #1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004142_tation-pdf-url_20709-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004142_tation-pdf-url_20709-Figure7-1.png", + "caption": "Fig. 7. The power network", + "texts": [ + "com Power Quality \u2013 Monitoring, Analysis and Enhancement 266 With the availability of , ,o ud d chT , and by using the Embedded MATLAB Functions shown in Fig. 6, the various modes of the chopper (CM, FCM, DM, and FDM) can be determined. Finally using these modes, the corresponding switching strategies are applied to the chopper switches based on Table 5. In this section, the strategies presented in sections 2 through 4 are simulated using MATLAB\u00ae software. The power network to which the SMES is connected is shown in Fig. 7 and was modeled using the M-file in MATLAB\u00ae. The power network and the SMES parameters are given in Appendix I. In Fig. 8, the SMES performance using the developed approaches is compared with that of the SMES when the capacitors of the three-level NPC inverter are replaced with equal and ideal voltage sources (SMES with ideal VSI). These comparisons are from the perspective of the THD and the DF of the inverter output line voltage. As seen in this figure, the www.intechopen.com Using Superconducting Magnetic Energy Storage System 267 performance of the SMES using the chopper duty cycle controller is the same as that of the SMES with an ideal VSI", + " 18, using which, the following equations can be obtained: 1 sin sin tan cos cos \u2212 \u2212 = \u2212 p p n n smes p p n n g \u03bd \u03d5 \u03bd \u03d5 \u03d5 \u03bd \u03d5 \u03bd \u03d5 (14) ( )cos cos cos= \u2212smes p p n n smes\u03bd \u03bd \u03d5 \u03bd \u03d5 \u03d5 (15) By calculating smes\u03d5 and smesv from (14) and (15), and by using the power flow that considers only the effect of the SMES system, the values of the am and inv\u03d5 for applying to the threelevel NPC inverter can be calculated. The power network shown in Fig. 17 was simulated using MATLAB software; the parameters used in this figure are the same as those defined in Fig. 7, and the parameters for the generators are provided in Appendix I; in addition, the sag compensation of the voltage for load 2 using the SMES is shown in Fig. 19. In this study, the voltage of the generator drops to 0.5 [ . .]p u ; in Fig. 19a, the voltage immediately decreases at 0.5=t [sec] from its full value to the sag value in essentially zero time, while in Fig. 19b, the same observation occurs during one cycle in ramp rate. In Figs. 19a and b, the Compensator begins sampling the magnitude and phase of the voltage of load 2 after one cycle and again after three cycles of voltage sag, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002971_pdf_AD1BCDE66371.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002971_pdf_AD1BCDE66371.pdf-Figure9-1.png", + "caption": "Figure 9. Specific absorption rate (SAR) at 897MHz on human phantom model with input power of 1W: (a) SAR distribution for 1 g and (b) SAR distribution for 10 g.", + "texts": [ + " The measured with body resonant frequency was 858 MHz at -43.4 dB and bandwidth (805-936 MHz) of 15.26%. The measurements for simulation without flat Phantom was 907 MHz at -16.94 and -10 bandwidth (858-956 MHz) while for simulation with flat Phantom was 868 MHz at - 22.52dB and -10 dB bandwidth (805-907 MHz). The designed antennas are to operate in proximity to the human body, when they are placed on layers of a garment. The antenna was simulated in CST Microwave Studio using flat body Phantom (Figure 9) considering separation distances from the human body. The antenna was simulated in free space. For this, pocket antenna simulation and average clothing thickness of was considered. The air gap between the felt fabric substrate and the human body was 3 mm. The properties and parameters of the flat body Phantom are: Muscle skin and fat (Ali et al., 2017). Pocket B antenna simulation was performed on the human phantom using CST Microwave Studio. The CST uses the IEEE C95.3 standard averaging method. The referenced input power of 0.25 W produced a SAR distribution (Figure 9). The simulated results are 2.401 W/kg for 1 g of tissue and 1.57 W/kg for 10 g of tissue. The lossy nature of human tissues causes energy to be absorbed when electromagnetic waves are propagating. At lower input power, the SAR limit is within the acceptable limit (ICNIRP 1998). For the chest measurements; the antenna was mounted directly on a shirt of about 3 mm thickness (measured). The antenna was placed near the body which may account for slightly significant detuning effects because of the lossy nature of the human body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001467_v.org_pdf_2409.04961-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001467_v.org_pdf_2409.04961-Figure1-1.png", + "caption": "Figure 1. Multi-Sensor Devices and Data Collection Platforms. (a) SolidWorks models of our sensor rig on three data collection devices, with the coordinate axes color-coded: red for the X-axis, green for the Y -axis, and blue for the Z-axis. This representation illustrates the transformation of sensor coordinates for each device. The multi-sensor rig mounted on (b) a handheld platform, (c) a sailboat, and (d) an UGV. The images in (b) through (d) demonstrate the diverse range of the GEODE dataset across various data collection platforms.", + "texts": [ + " In summary, our dataset exhibits enhanced comprehensiveness in four key aspects: 1) Extensive sensory measurements derived from diverse LiDAR, providing additional channels for LiDAR data; 2) Inclusion of multiple scenarios encompassing varying levels of degradation, enhancing the performance of degeneracy detection and mitigation; 3) Comprehensive data collection incorporating a wide range of motion patterns to facilitate algorithm design for generalpurpose applications; and 4) Simulation of potential realworld sensor failures to improve adaptive algorithm switching and failure detection and recovery. The dataset\u2019s design aims to facilitate the development of LiDAR SLAM algorithms, independent of scanning modalities and FoV characteristics. To achieve this objective, we have developed three acquisition devices that share a common IMU and stereo camera but are equipped with distinct LiDAR sensors. The sensor parameters and layout are detailed in Table 2 and Figure 1a. Our versatile acquisition system can be easily mounted on various platforms, as demonstrated in Figure 1b,1c,1d, showcasing its adaptability to a handheld, sailboat, and UGV device, respectively. Our FPGA-based synchronization module facilitates multichannel sensor synchronization, as illustrated in Figure 2. The module is capable of achieving outdoor time synchronization through the reception of GNSS signals during initialization. By utilizing TIME OF DAY (TOD) and PPS signals from the GNSS, it generates synchronized signals at frequencies of 1, 10, and 100 Hz for LiDAR, cameras, and the Xsens MTi-30 IMU, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002053_e_download_2200_1306-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002053_e_download_2200_1306-Figure8-1.png", + "caption": "Figure 8: 2D model of new outer shell structure (a) inside, (b) outside", + "texts": [ + " Thus, the system can easily break under high amounts of pressure or force, meaning it will not be able to provide the necessary levels of assistive torque to the knee joint. Final Design: To counteract the weakness of the 3D-printed plastic, the material of the outer shell was replaced with steel, which can withstand significantly higher levels of force. However, as steel products are much harder to manufacture in comparison to 3D-printed products, the exact structure of the outer shell was modified into a simpler one while still maintaining the routing system and the flexibility of the 5 segments. As seen from figure 8, the new structure is much simpler overall while maintaining the correct routing system. This improvement means that it can be made in adequate time while also improving the overall solidity of the structure. ISSN: 2167-1907 www.JSR.org 7 From figure 9, it can be seen that the 5 segments are connected together with the use of stop bolts and locknuts in order to secure them tightly together. The stop bolts and locknuts work together to reduce the force of friction acting on the system, while also ensuring stability throughout, meaning the segments are able to flex smoothly according to the user\u2019s movements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003421_agritech-x_06001.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003421_agritech-x_06001.pdf-Figure5-1.png", + "caption": "Fig. 5. Sketch of inner gear", + "texts": [], + "surrounding_texts": [ + "2( ) sin( )2 2 Da yDa (17)\nWe will find the area of the sector limited by the engagement profile, the integration limits - the angles of coverage of the working camera at the maximum volume [8]:\n 4,32\n1 1 1 3,534\nd S x y d\nd \n(18)\n 4,32\n1 2 2 3,534\nd S x y d\nd \n(19)\n 24,321\n11 13,5342 S R d (20)\n 24,321\n22 23,5342 S R d (21)\n 24,321\n22 23,5342 S R d (22)\nFind the geometric volume of the hydraulic machine: 2310 2 2 1 z Vg b e Da z (23) Based on the calculations, we build a sketch of the impeller.\n cos( ) cos( 2 ) 1 ( ) 21 2 cos( 1 ) 11 2 cos( ) 11 cos( 2 ) 11 z x e z R z R z r (24)", + "4 Conclusion\nThe design of heroic programs requires the use of various methods and tools. They include evolute construction methods, reverse engineering, finite element method, and computer modeling.\nThese methods make it possible to optimize the design of gerotor transmissions in order to achieve high efficiency and reliability. They help determine optimal transmission parameters, such as tooth shape, radii and profiles, and analyze its strength and deformations.\nComputer simulations and simulations allow virtual transmission tests, reducing the risks and costs of physical prototyping. This allows designers to develop transmissions faster and more efficiently.\nThe optimal design of heroic transmission depends on the requirements and conditions of a particular application. Designers must consider factors such as required torque, rotational speed, loads and operating conditions to create a gear that will perform its functions optimally.\nReferences\n1. I.V. Karnaukhov, E.A. Sorokin, A.A. Nikitin, V.V. Abramov, M.D. Pankiv, IOP Conference Series: Earth and Environmental Science 981, 042054 (2022)\n2. V.I. Posmetev, V.O. Nikonov, V.V. Posmetev, IOP Conference Series: Earth and Environmental Science 392, 012038 (2019)\n3. V.O. Nikonov, V.I. Posmetev, V.V. Posmetev, IOP Conference Series: Earth and Environmental Science 392, 012039 (2019)\n4. I.I. Gabitov, A.V. Negovora, M.M. Razyapov, A.A. Kozeev, R.J. Magafurov, IOP Conference Series: Materials Science and Engineering 632, 012048 (2019)\n5. Wen Jing Hu, Zheng Meng, Journal of Physics: Conference Series 1574, 012028 (2022) 6. Yuanzhi Huang, Journal of Physics: Conference Series 2143, 012048 (2021) 7. C. Khamnounsak, S. Likit, Journal of Physics: Conference Series 1380, 012018 (2019) 8. R.T. Emelyanov, A.S. Klimov, K.S. Kravtsov, I.B. Olenev, E.S. Turysheva, Journal of\nPhysics: Conference Series 1515, 042078 (2020)" + ] + }, + { + "image_filename": "designv8_17_0004121_8_14_8_14_8_387__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004121_8_14_8_14_8_387__pdf-Figure4-1.png", + "caption": "Fig. 4 Configuration of the experimental system", + "texts": [], + "surrounding_texts": [ + "\u85e4 \u672c \u30fb\u77f3\u5ddd \u30fb\u6749 \u6c5f:\u4e00 \u822c \u5316\u6b63 \u6e96\u5909 \u63db \u3092\u7528 \u3044\u305f\u5b89 \u5b9a\u5316 \u6cd5\u306e \u30ed\u30d0 \u30b9 \u30c8\u6027 \u306b\u95a2\u3059 \u308b\u8003\u5bdf 391\n\u5b9a \u3059 \u308b \u3068,(28)\u5f0f \u306e \u3088 \u3046 \u306b\u8a18 \u8ff0 \u3067 \u304d,\u5b9f \u969b \u306e \u30e2 \u30c7 \u30eb\u5316 \u8aa4 \u5dee \u3092\u6301 \u3064 \u30b7 \u30b9 \u30c6 \u30e0 \u306e \u591a \u304f\u306f \u3053\u306e \u5f62 \u3067 \u8868 \u3055 \u308c \u3066 \u3044 \u308b \u3068\u8003 \u3048 \u3089 \u308c \u308b.\n\u3044 \u307e,(28)\u5f0f \u306b(6)\u5f0f \u306b\u5bfe \u3057\u3066\u6c42 \u307e \u308b \u30d5 \u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u5247\n(10)\u5f0f \u3092\u7528 \u3044,\u3055 \u3089 \u306bq=S(\u2202H/\u2202P)T=S(\u2202H/\u2202P)T \u306e \u95a2 \u4fc2 \u304b \u3089q, p\u305d \u308c \u305e \u308c \u306b\u3064 \u3044 \u3066 \u66f8 \u304d\u4e0b \u3059.\n(30)\n\u305f \u3060 \u3057S\u2020:=(STS)-1ST\u306fS\u306e \u7591 \u4f3c \u9006 \u884c \u5217 \u3067 \u3042 \u308b.\u307e \u305fU\u306fq\u306e \u307f \u306b\u4f9d \u5b58 \u3059 \u308b \u95a2 \u6570 \u306a \u306e \u3067H+U\u306f,\n(31)\n\u3067\u3042\u308b.\u3053 \u3053\u3067\u30e2\u30c7\u30eb\u5316\u8aa4\u5dee\u304c\u306a\u3051\u308c\u3070,(31)\u5f0f \u306e\u53f3\u8fba\n\u7b2c\u4e00\u9805\u306f\u8ca0 \u307e\u305f\u306f\u96f6,\u53f3 \u8fba\u7b2c\u4e8c\u9805\u304c\u96f6 \u3088\u308a,H+U\u22660\n\u3068\u306a \u308a,\u30d5 \u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u7cfb\u306f\u5b89\u5b9a\u3067\u3042\u308b.\u3057 \u304b\u3057,\u30e2 \u30c7 \u30eb\u5316\u8aa4\u5dee\u304c\u3042\u308b\u5834\u5408\u306b\u306f,H+U\u22660\u3068 \u306a\u3089\u306a\u3044.\n4.2.1 \u5b89\u5b9a\u6027\u306e\u5341\u5206\u6761\u4ef6 \u30e2\u30c7\u30eb\u5316\u8aa4\u5dee\u304c\u3042\u308b\u30b7\u30b9\u30c6\u30e0\u306b\u5bfe \u3057\u3066,\u516c \u79f0\u30e2\u30c7\u30eb \u3068\n\u540c\u3058U,\u03b2 \u3067\u6b63\u6e96\u5909\u63db\u3092\u65bd \u3057\u305f \u3068\u3059\u308b.\u3044 \u307e,\u3053 \u306eU,\n\u03b2\u304c\u5b9f\u969b\u306e\u7cfb\u306b\u5bfe \u3057\u3066\u3082\u6642\u4e0d\u5909 \u306a\u5ea7\u6a19\u5909\u63db \u3092\u6301\u3064\u4e00\u822c\u5316 \u6b63\u6e96\u5909\u63db\u3067\u3042\u308b\u3068\u4eee\u5b9a\u3059\u308b,\u3059 \u306a\u308f\u3061(3)\u5f0f \u304c\u6642\u4e0d\u5909\u306a \u5ea7\u6a19\u5909\u63db \u3092\u6301\u3064\u3068\u3059\u308b.\u3053 \u306e\u4eee\u5b9a\u306f,\u516c \u79f0\u30e2\u30c7\u30eb\u3068\u540c\u69d8 H+U\u304c \u5b9f\u969b\u306e\u7cfb\u306b\u5bfe \u3057\u3066\u3082storage\u95a2 \u6570\u3068\u306a\u308b\u3053\u3068\u3092 \u610f\u5473\u3059\u308b.\u3053 \u306e\u6761\u4ef6\u306f(3)\u5f0f \u3088\u308a\n(32)\n\u3068\u306a\u308b.\u3053 \u308c\u3092(31)\u5f0f \u306b\u4ee3\u5165\u3059\u308b\u3068\u53f3\u8fba\u7b2c\u4e8c\u9805 \u76ee\u304c0\u3068\n\u306a\u308a,H+U\u3092storage\u95a2 \u6570 \u3068\u3057\u3066\u53d7\u52d5\u7684\u3068\u306a\u308b\u3053\u3068\u304c\n\u78ba\u8a8d\u3067\u304d\u308b.\u3088 \u3063\u3066\u516c\u79f0\u30e2\u30c7\u30eb \u3068\u540c\u3058\u88dc\u511f\u5668\u3092\u7528\u3044\u305f\u5834 \u5408\u3067\u3082\u5b89\u5b9a\u6027\u304c\u4fdd\u8a3c\u3055\u308c\u308b.\n\u3064\u304e\u306b\u30b7\u30b9\u30c6\u30e0\u306e\u6f38\u8fd1\u5b89\u5b9a\u6027\u306b\u3064\u3044\u3066\u8003\u5bdf\u3059\u308b.\u672c \u624b\n\u6cd5\u3067\u306f\u4e00\u822c\u5316\u6b63\u6e96\u5909\u63db\u3059\u308b\u969b,\u88dc \u984c1\u3092 \u9069\u7528 \u3057\u5165\u51fa\u529b\u96f6 \u5316\u96c6\u5408 \u3092\u7279\u5b9a \u3057\u3066\u305d\u306e\u9818\u57df \u3092\u4e0d\u5b89\u5b9a\u5316\u3059\u308b\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\n\u3092\u7528\u3044\u3066\u6f38\u8fd1\u5b89\u5b9a\u5316\u3092\u9054\u6210 \u3057\u3066\u3044\u308b.\u3044 \u307e,\u30e2 \u30c7\u30eb\u5316\u8aa4 \u5dee\u304c\u3042\u308b\u30b7\u30b9\u30c6\u30e0\u306b\u5bfe \u3057\u3066,\u516c \u79f0\u30e2\u30c7\u30eb\u3068\u540c\u3058\u5ea7\u6a19\u5909\u63db \u3092\u6301\u3064\u4e00\u822c\u5316\u6b63\u6e96\u5909\u63db\u3092\u65bd\u3059\u3068\u5165\u51fa\u529b\u96f6\u5316\u96c6\u5408\u304c\u516c\u79f0\u30e2\n\u30c7\u30eb \u3068\u306f\u7570\u306a\u3063\u305f\u96c6\u5408\u306b\u306a \u308a,\u540c \u3058\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u3067\u306f\u6f38 \u8fd1\u5b89\u5b9a\u5316\u3067\u304d\u306a\u304f\u306a\u308b\u53ef\u80fd\u6027\u304c\u3042\u308b.\u3057 \u304b \u3057\u305d\u306e\u5834\u5408\u3067 \u3082,(28)\u5f0f \u306b\u516c\u79f0\u30e2\u30c7\u30eb\u3068\u540c \u3058\u5ea7\u6a19\u5909\u63db \u3092\u65bd \u3057\u3066\u69cb\u6210\u3055 \u308c\u305fS(\u03be)\u304c(7)\u5f0f \u306e\u3088\u3046\u306b\u5206\u5272\u3067 \u304d,\u3055 \u3089\u306b\u305d\u306e\u3068\u304d\u69cb\n\u6210 \u3055\u308c\u308bS2(\u03be)\u304c(8)\u5f0f \u3092\u6e80\u305f\u305b\u3070\u5165\u51fa\u529b\u96f6\u5316\u96c6\u5408\u304c\u4e00 \u81f4 \u3057,\u540c \u3058\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u3067\u6f38\u8fd1\u5b89\u5b9a\u5316\u304c\u9054\u6210 \u3055\u308c\u308b.\n\u4ee5\u4e0a\u306e\u8b70\u8ad6 \u3092\u307e\u3068\u3081\u308b\u3068\u6b21\u306e\u3088\u3046\u306b\u306a\u308b.\n\u3010\u547d\u984c1\u3011(28)\u5f0f \u306e\u30b7\u30b9\u30c6\u30e0\u304c\u6b21\u306e\u4e8c\u6761\u4ef6 \u3092\u6e80 \u305f\u3059\n\u3068\u4eee\u5b9a\u3059\u308b.\n(33)\n(34)\n\u305f\u3060\u3057S2\u306f \u4e00\u822c\u5316\u6b63\u6e96\u5909\u63db \u3057\u305f\u5f8c\u306e\u30b7\u30b9\u30c6\u30e0\u3092(7)\u5f0f \u306e \u3088\u3046\u306b\u5206\u89e3\u3059\u308b\u3053\u3068\u306b\u3088\u308a\u5f97 \u3089\u308c\u308b.\u3053 \u306e\u6642,(10)\u5f0f \u306e\n\u88dc\u511f\u5668\u306f(28)\u5f0f \u306e\u7cfb\u306e\u539f\u70b9 \u3092\u6f38\u8fd1\u5b89\u5b9a\u5316\u3059\u308b.\n4.2.2 \u4e8c\u8f2a\u8eca\u4e21\u306e\u30e2\u30c7\u30eb\u5316\u8aa4\u5dee\u3078\u306e\u9069\u7528 \u4e0a\u8a18 \u306e\u547d\u984c \u3092\u4e8c\u8f2a\u8eca\u4e21 \u306b\u9069\u7528\u3059\u308b.\u3053 \u3053\u3067\u306f\u8a2d\u8a08\u6642\n\u306b\u306f\u5b9a\u6570\u30d1 \u30e9\u30e1\u30fc\u30bf\u3092\u5de6\u53f3\u5bfe\u79f0 \u306b\u3057\u3066\u3044\u308b(rr=rl=r \u306a\u3069).\u5b9f \u30e2\u30c7\u30eb\u306e\u5b9a\u6570\u30d1 \u30e9\u30e1\u30fc\u30bf\u3092\u52b4.\u306a \u3069\u3013\u3067\u8868 \u3057, \u30ce\u30df\u30ca\u30eb\u5024 \u3068\u771f\u306e\u5024 \u3068\u306e\u6bd4 \u3092\u8868\u3059\u5b9a\u6570(a1\uff5ea8)\u3092 \u7528\u3044\n\u3066,rr=a1r, rl=a2r, wr=a3w, wl=a4w,m=a5m,\nj=a6j,ir=a7i,il=a8i,\u3067 \u3042 \u308b \u3068\u3059 \u308b.\n\u307e\u305a \u547d \u984c1\u306e(33)\u5f0f \u306e \u6761 \u4ef6 \u3092 \u4e8c\u8f2a \u8eca \u4e21 \u7cfb \u306b \u9069 \u7528 \u3059 \u308b. \u4e8c \u8f2a \u8eca \u4e21 \u306e \u5834 \u5408S=ST1, G=T2G\u3068 \u66f8 \u3051 \u308b \u306e \u3067 \u3053\u306e \u95a2\n\u4fc2 \u5f0f \u3092\u7528 \u3044 \u3066\u5b89 \u5b9a \u6027 \u306e \u6761 \u4ef6 \u3092\u66f8 \u304d\u76f4 \u3059 \u3068\n(35)\n\u3068 \u306a \u308b.\u305f \u3060 \u3057,\n(36)\n\u3067\u3042\u308b.\u3053 \u306e\u6761\u4ef6 \u3092\u5b9f\u969b\u306b\u8a08\u7b97 \u3057\u3066\u307f\u308b\u3068,\n(37)\n\u3068\u306a\u308b.\n\u6b21\u306b\u547d\u984c1\u306e(34)\u5f0f \u306e\u6761\u4ef6\u3092\u4e8c\u8f2a\u8eca\u4e21\u7cfb \u306b\u9069\u7528\u3059\u308b\u3068,\n(38)\n\u3057\u305f\u304c\u3063\u3066(34)\u5f0f \u306f\u5e38\u306b\u6210\u7acb\u3059\u308b.\u3088 \u3063\u3066\u3053\u306e\u7bc4\u56f2\u306e \u3069\u3093\u306a\u30d1 \u30e9\u30e1\u30fc\u30bf\u8aa4\u5dee\u304c\u3042\u308b\u5834\u5408\u3067\u3082\u5165\u51fa\u529b\u96f6\u5316\u96c6\u5408\u306f \u30ce\u30df\u30ca\u30eb\u30e2\u30c7\u30eb\u3068\u4e00\u81f4\u3059\u308b\u306e\u3067(24)\u5f0f \u306e\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u3092\n\u4ed8\u52a0\u3059\u308b\u3053\u3068\u3067\u6f38\u8fd1\u5b89\u5b9a\u5316\u3055\u308c\u308b.\n\u4ee5 \u4e0a\u304b\u3089\u4e8c\u8f2a\u8eca\u4e21\u306e\u7269\u7406\u30d1 \u30e9\u30e1\u30fc\u30bf\u306b\u8aa4\u5dee\u304c\u3042\u308b\u5834\u5408 \u3067\u3082,(37)\u5f0f \u304c\u6e80\u305f\u3055\u308c\u308b\u7bc4\u56f2\u3067\u3042\u308c\u3070\u6f38\u8fd1\u5b89\u5b9a\u6027\u304c\u4fdd\n\u8a3c\u3055\u308c\u308b.\u3053 \u306e\u6761\u4ef6\u5f0f \u306b\u306f,\u5e7e \u4f55\u5b66\u7684\u306a\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u307f \u3067,\u4e8c \u8f2a\u8eca\u306e\u8cea\u91cf,\u6163 \u6027\u30e2\u30fc\u30e1\u30f3 \u30c8,\u8eca \u8f2a\u306e\u8cea\u91cf,\u6163 \u6027 \u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u304c\u542b \u307e\u308c\u3066\u3044\u306a\u3044.\u3064 \u307e\u308a,\u5e7e", + "392 \u30b7\u30b9 \u30c6\u30e0\u5236\u5fa1 \u60c5 \u5831\u5b66 \u4f1a\u8ad6 \u6587\u8a8c \u7b2c14\u5dfb \u7b2c8\u53f7(2001)\n\u4f55\u5b66\u7684\u306a\u69cb\u9020\u3055\u3048\u6b63\u78ba \u306b\u8a2d\u8a08 \u3057\u3066\u304a\u3051\u3070,\u4ed6 \u306e\u8aa4\u5dee\u306f\u8a31 \u5bb9\u3067\u304d\u308b\u3068\u3044\u3046\u3053\u3068\u3067\u3042\u308b.\n5. \u5b9f \u9a13\n5.1 \u5b9f\u9a13\u88c5\u7f6e\u306e\u6982\u7565 \u672c\u5b9f\u9a13\u306b\u7528\u3044\u308b\u88c5\u7f6e\u306e\u69cb\u6210\u3092Fig. 4\u306b,\u4e8c \u8f2a\u8eca\u4e21\u306e\u5199\n\u771f\u3092Fig. 5\u306b \u793a\u3059.\u4e8c \u8f2a\u8eca\u4e21\u306e\u4f4d\u7f6e\u3068\u59ff\u52e2\u89d2\u306f,\u8eca \u4e21\u672c \u4f53\u306b\u4ed8\u3051\u305f\u4e8c\u3064\u306eLED\u306e \u4f4d\u7f6e\u3092\u7d043[m]\u306e \u9ad8\u3055\u306b\u53d6 \u308a\u4ed8 \u3051\u305f\u30dd\u30b8\u30b7\u30e7\u30f3\u30bb\u30f3\u30b5\u3067\u8aad\u307f\u53d6\u308b\u3053\u3068\u306b\u3088\u3063\u3066\u6e2c\u5b9a\u3059\u308b. \u5206\u89e3\u80fd\u306f2.5[mm], LED\u9593 \u306e\u8ddd\u96e2\u306f22[cm]\u3067 \u3042\u308b.\u4e8c \u3064\u306e\u8eca\u8f2a(\u8eca \u8f2a\u9593\u306e\u8ddd\u96e215[cm])\u306b \u306f\u305d\u308c\u305e\u308c\u72ec\u7acb \u3057\u305f \u30e2\u30fc\u30bf\u3068\u30a8 \u30f3\u30b3\u30fc\u30c0\u3092\u53d6 \u308a\u4ed8 \u3051,\u305d \u308c\u305e\u308c\u306e\u8eca\u8f2a(\u534a \u5f84\n4[cm])\u306e \u56de\u8ee2\u89d2\u3092\u6e2c \u308a,\u307e \u305f \u30c8\u30eb\u30af\u3092\u4e0e\u3048\u308b.\u901f \u5ea6\u60c5\u5831 \u306f\u30dd\u30b8\u30b7\u30e7\u30f3\u30bb\u30f3\u30b5\u306e\u60c5\u5831\u3092\u6570\u5024\u5fae\u5206 \u3057\u305f\u3082\u306e\u3067\u3042\u308b. \u306a\u304a,\u30b5 \u30f3\u30d7\u30ea\u30f3\u30b0\u30bf\u30a4\u30e0\u306f5[ms]\u3067 \u3042\u308b.\u3053 \u308c\u306f,\u30dd \u30b8\u30b7\u30e7\u30f3\u30bb\u30f3\u30b5\u306e\u4fe1\u53f7\u304c300[Hz]\u3067 \u9001 \u3089\u308c\u3066 \u304f\u308b\u305f\u3081\u306e\n\u5236\u7d04\u3067\u3042\u308b.\u307e \u305f,\u5165 \u529b\u5236\u7d04\u3068,\u8eca \u8f2a\u306e\u6ed1 \u308a\u3092\u304a\u3055\u3048\u308b \u305f\u3081\u901f\u5ea6\u306e\u5236\u7d04 \u3092\u4e0e\u3048\u3066\u3044\u308b.\n5.2 \u5b9f \u9a13 \u7d50 \u679c \u3068\u8003 \u5bdf\n\u5b9f \u9a13 \u3067 \u306f\u7279 \u306b\u89b3 \u6e2c \u30ce \u30a4 \u30ba \u306b\u5bfe \u3059 \u308b \u30ed\u30d0 \u30b9 \u30c8\u6027 \u306b\u3064 \u3044 \u3066\n\u691c \u8a3c \u3059 \u308b.\n5.2.1 \u5b9f \u9a131\n(24)\u5f0f \u306e\u4ed8 \u52a0 \u3059 \u308b \u30dd \u30c6 \u30f3\u30b7 \u30e3\u30eb \u306e\u30d1 \u30e9 \u30e1 \u30fc \u30bf \u3092C1=1,\nC2=1, C3=4, C4=1,\u72b6 \u614b \u30d6\u30a4\u30fc \u30c9\u30d0 \u30c3\u30af \u306e\u30d1 \u30e9 \u30e1 \u30fc\n\u30bf \u3092P=50I\u3068 \u3057\u3066,\u03b3 \u30920\uff5e3\u3068 \u5909 \u5316 \u3055\u305b \u5b9f \u9a13 \u3092\u884c \u3063 \u305f.\u03b3=0,3\u306b \u5bfe \u3059 \u308b\u7cfb \u306e \u5fdc \u7b54 \u306ez1-z2\u30b0 \u30e9 \u30d5(\u6a2a \u8ef8z1\n\u5ea7 \u6a19,\u7e26 \u8ef8z2\u5ea7 \u6a19 \u5358 \u4f4d[cm])\u3092 \u305d \u308c \u305e \u308cFig. 6, Fig. 7 \u306b, q\u306e \u6642 \u9593 \u5fdc \u7b54(\u6a2a \u8ef8 \u6642 \u9593[s],\u7e26 \u8ef8 \u914d \u4f4d \u5ea7 \u6a19,\u03b8:\u5b9f \u7dda 0.1[rad], z1:\u9396 \u7dda, z2:\u7834 \u7dda[cm])\u3092Fig. 8, Fig. 9\u306b\n\u793a \u3059.\n\u3053 \u308c \u3089\u306e \u7d50 \u679c \u304b \u3089, 4.1\u3067 \u884c \u3063 \u305f\u5916 \u4e71 \u306b\u5bfe \u3059 \u308b \u30ed\u30d0 \u30b9\n\u30c8\u6027 \u306e \u8003 \u5bdf \u306e \u3068\u304a \u308a \u03b3 \u304c\u5897 \u3059 \u3068\u89b3 \u6e2c \u30ce \u30a4\u30ba \u306e\u5f71 \u97ff \u3068\u601d \u308f\n\u308c \u308b\u539f \u70b9 \u8fd1 \u508d \u3067 \u306e \u632f \u52d5 \u304c\u5c0f \u3055 \u304f\u306a \u3063\u3066 \u3044 \u308b.\u306a \u304a \u03b3 \u304c3 \u4ee5 \u4e0a \u3067 \u306f \u3042 \u307e \u308a\u5909 \u5316 \u304c \u306a\u304b \u3063 \u305f.\n5.2.2 \u5b9f \u9a132 \u3064 \u304e \u306b\u5b9f \u6a5f \u3067\u4ed6 \u306e \u624b \u6cd5 \u3068\u306e \u6bd4 \u8f03 \u3092 \u304a \u3053 \u306a \u3063 \u305f .\u6bd4 \u8f03 \u3059 \u308b\u5bfe \u8c61 \u3068 \u3057\u3066 \u306f, Astolfi\u306e \u624b \u6cd5[8]\u306b \u30d0 \u30c3\u30af \u30b9 \u30c6 \u30c3 \u30d4 \u30f3\n3)", + "\u85e4\u672c \u30fb\u77f3\u5ddd \u30fb\u6749\u6c5f:\u4e00 \u822c\u5316\u6b63\u6e96\u5909\u63db\u3092\u7528\u3044\u305f\u5b89\u5b9a\u5316\u6cd5\u306e\u30ed\u30d0\u30b9 \u30c8\u6027\u306b\u95a2\u3059\u308b\u8003\u5bdf 393\n\u9593\u5fdc\u7b54 \u3092,\u305d \u308c\u305e\u308cFig. 10, Fig. 11\u306b \u793a\u3059.\u3053 \u306e\u6642\u306e \u30d1\u30e9\u30e1\u30fc\u30bf\u306f\u5b9f\u9a13\u3067\u306e\u8a66\u884c\u932f\u8aa4\u306b\u3088\u308b\u8abf\u6574\u3067\u6c7a\u5b9a \u3057\u305f.\n\u304b \u3057\u03b3\u304c3\u4ee5 \u4e0a\u3067\u306f\u3042\u307e\u308a\u5909\u5316\u304c\u306a\u304b\u3063\u305f\u306e\u306f, Fig. 3 \u3067\u4e0e \u3048\u3089\u308c\u308b\u3088\u3046\u306a(27)\u5f0f \u306e \u03c6\u306e\u5f62\u304c,\u03b3 \u304c3\u4ee5 \u4e0a\u3067 \u306f\u5927 \u304d\u304f\u5909\u5316 \u3057\u306a\u3044\u305f\u3081\u3060\u3068\u8003\u3048\u3089\u308c\u308b.\u5b9f \u9a132\u3067 \u306f, Astolfi\u306e \u624b\u6cd5\u306f\u539f\u70b9\u4ed8\u8fd1\u3067\u304b\u306a\u308a\u5fdc\u7b54\u304c\u66b4\u308c,\u89b3 \u6e2c\u30ce\u30a4 \u30ba\u306b\u5f31\u3044\u3053\u3068\u304c\u308f\u304b\u308b.\u3053 \u306e\u7d50\u679c\u306f,\u53c2 \u8003\u6587\u732e[7]\u306b \u8ff0 \u3079 \u3089\u308c\u3066\u3044\u308b\u4e0d\u9023\u7d9a\u88dc\u511f\u5668\u306f\u89b3\u6e2c\u30ce\u30a4\u30ba\u306b\u5f31\u3044\u3068\u3044\u3046\u7d50\n\u679c\u3068\u4e00\u81f4\u3059\u308b\u304c,\u672c \u624b\u6cd5\u3067\u306f\u3053\u306e\u6b20\u70b9\u304c\u6539\u5584\u3055\u308c\u3066\u3044\u308b\n\u3053\u3068\u304c\u308f\u304b\u308b.\u307e \u305fAstolfi\u306e \u624b\u6cd5\u3067\u306f\u304b\u306a \u308a\u306e\u504f\u5dee\u304c\n\u6b8b\u3063\u3066\u3044\u308b.\u3068 \u304f\u306b\u59ff\u52e2\u89d2\u306e\u504f\u5dee\u304c\u672c\u624b\u6cd5\u306b\u6bd4\u3079\u3066\u9855\u8457 \u3067\u3042\u308b.\u3055 \u3089\u306b,\u672c \u624b\u6cd5\u3067\u306fAstolfi\u306e \u624b\u6cd5\u306b\u6bd4\u3079\u53ce\u675f \u306e\u901f \u3055\u306b\u304a\u3044\u3066\u905c\u8272 \u306f\u306a\u3044.\u4ee5 \u4e0a\u306e\u3053\u3068\u304b \u3089,\u672c \u624b\u6cd5\u306f \u30ed\u30d0\u30b9 \u30c8\u6027\u306b\u512a\u308c\u304b\u3064\u5b9f\u7528\u4e0a\u53ce\u675f \u3082\u901f\u3044\u5b89\u5b9a\u5316\u624b\u6cd5\u3067\u3042\n\u308b\u3068\u8003 \u3048\u3089\u308c\u308b.\n6. \u304a \u308f \u308a\u306b\n\u672c\u8ad6\u6587\u3067\u306f\u5f93\u6765\u3088\u308a\u7b46\u8005\u3089\u304c\u63d0\u6848 \u3057\u3066\u3044\u308b\u4e00\u822c\u5316\u6b63\u6e96 \u5909\u63db \u306b\u57fa\u3065 \u304f\u975e\u30db\u30ed\u30ce\u30df\u30c3\u30af\u306a\u30cf \u30df\u30eb \u30c8\u30cb\u30a2\u30f3\u30b7\u30b9\u30c6\u30e0 \u306e\u5b89\u5b9a\u5316\u624b\u6cd5\u306e\u6709\u52b9\u6027\u306b\u3064\u3044\u3066,\u4e8c \u8f2a\u8eca\u4e21\u7cfb\u3092\u5bfe\u8c61\u3068\u3057\n\u3066\u30ed\u30d0\u30b9 \u30c8\u6027\u306e\u89b3\u70b9\u304b\u3089\u306e\u89e3\u6790 \u3068\u305d\u306e\u5b9f\u9a13\u691c\u8a3c\u3092\u884c\u3063\u305f. \u307e\u305a\u8a2d\u8a08\u30d1\u30e9\u30e1\u30fc\u30bf\u3067\u3042\u308b\u4e0d\u53ef\u5fae\u5206\u306a\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u306e\u6982\n\u5f62 \u3068\u89b3\u6e2c\u5916\u4e71\u7b49 \u306b\u3088\u308b\u72b6\u614b\u306e\u6442\u52d5\u306b\u5bfe\u3059\u308b\u611f\u5ea6 \u3068\u306e\u95a2\u4fc2 \u3092\u8003\u5bdf \u3057\u305f.\u307e \u305f\u5236\u5fa1\u5bfe\u8c61\u306e\u53d7\u52d5\u6027 \u3092\u7528\u3044\u305f\u8003\u5bdf\u306b\u3088\u308a \u7269\u7406\u30d1\u30e9\u30e1\u30fc\u30bf\u5909\u52d5\u306b\u5bfe\u3059\u308b\u30ed\u30d0\u30b9 \u30c8\u5b89\u5b9a\u6027\u306e\u5341\u5206\u6761\u4ef6 \u3092\u4e0e \u3048\u305f.\u3055 \u3089\u306b\u5b9f\u9a13\u3092\u884c\u3044,\u4ed6 \u306e\u624b\u6cd5\u3068\u306e\u6bd4\u8f03 \u3092\u307e\u3058 \u3048\u3066\u63d0\u6848\u624b\u6cd5\u306e\u6709\u52b9\u6027\u3092\u691c\u8a3c \u3057\u305f.\n\u6700\u5f8c\u306b,\u672c \u8ad6\u6587\u306b\u5bfe \u3057\u3066\u6709\u76ca\u306a\u610f\u898b\u3092\u4e0b \u3055\u3063\u305f\u533f\u540d\u306e\n\u67fb\u8aad\u8005\u306e\u65b9\u3005\u306b\u611f\u8b1d\u306e\u610f \u3092\u8868 \u3057\u307e\u3059.\n\u53c2 \u8003 \u6587 \u732e\n[1] A.J. van der Schaft: L2-gain and passivity techniques in nonlinear control; Vol. 218 Lecture Notes in Control and Information Sciences, Springer-Verlag\n(1996) [2] \u85e4 \u672c,\u6749 \u6c5f:\u4e00 \u822c \u5316\u6b63\u6e96 \u5909\u63db \u3092\u7528 \u3044\u305f\u3042 \u308b\u30af \u30e9\u30b9 \u306e\u975e \u30db \u30ed\n\u30ce \u30df\u30c3\u30af\u7cfb \u306e\u5b89\u5b9a\u5316;\u8a08 \u6e2c \u81ea\u52d5 \u5236\u5fa1\u5b66 \u4f1a\u8ad6\u6587 \u96c6, Vol. 36, No. 9, pp. 749-756 (2000)\n[3] \u85e4 \u672c,\u6749 \u6c5f:\u4e00 \u822c\u5316 \u30cf \u30df\u30eb \u30c8\u30cb \u30a2 \u30f3\u30b7\u30b9 \u30c6\u30e0 \u306e\u5b89\u5b9a \u5316 \u2015\n\u6b63\u6e96\u5909 \u63db \u306b \u3088\u308b \u30a2\u30d7 \u30ed\u30fc\u30c1;\u30b7 \u30b9 \u30c6\u30e0\u5236\u5fa1 \u60c5\u5831 \u5b66\u4f1a\u8ad6 \u6587 \u8a8c, Vol. 11, No. 11, pp. 616-622 (1998)\n[4] K. Fujimoto and T. Sugie: Stabilization of Hamiltonian systems with nonholonomic constraints via canonical transformations; Proc. ECC (1999) [5] K. Fujimoto, K. Ishikawa and T. Sugie: Stabilization of a class of hamiltonian system with nonholonomic constraints and its experimental evaluation; Proc. IEEE CDC'99, pp. 3478-3483 (1999) [6] K. Fujimoto and T. Sugie: Canonical transformation and stabilization of generalized hamiltonian systems; Systems and Control Letters, 42, pp. 217-227 (2001)\n[7] \u4e09 \u5e73:\u975e \u30db \u30ed \u30ce \u30df \u30c3 \u30af\u7cfb \u306e \u30d5 \u30a3 \u30fc \u30c9\u30d0 \u30c3 \u30af\u5236 \u5fa1;\u8a08 \u6e2c \u3068\n\u5236 \u5fa1, Vol. 36, No. 6, pp. 396-403 (1997)\n[8] A. Astolfi: Discontinuous control of nonholonomic systems; Systems and Control Letters, 27, pp. 37-45\n(1996) [9] \u4e2d\u6751:\u975e \u30db \u30ed \u30ce \u30df \u30c3 \u30af \u30ed \u30dc \u30c3 \u30c8\u30b7 \u30b9 \u30c6 \u30e01-5\u56de;\u65e5 \u672c\n\u30ed \u30dc \u30c3 \u30c8\u5b66 \u4f1a \u8a8c, Vol. 11, Nos. 4, 5, 6, 7 (1993),\nVol. 12, No. 2 (1994)\n[10] R. Fierro and F.L. Lewis: Control of a nonholonomic mobile robot: Backstepping kinematics into dynam-" + ] + }, + { + "image_filename": "designv8_17_0003238_f_version_1584177316-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003238_f_version_1584177316-Figure1-1.png", + "caption": "Figure 1. Structure of electromagnetic-piezoelectric hybrid drive motor.", + "texts": [ + " The air gap magnetic field characteristics of the motor are analyzed by analytical method, and the rationality of the results is verified by the finite element method. The contact pressure and contact displacement between the piezoelectric stator and the rotor are analyzed through the analytical method, and the motor drive model is established. Finally, a motor prototype and its motor test platform are built. The design rationality of the motor is proven by the experimental results on the prototype. As shown in Figure 1, the electromagnetic-piezoelectric hybrid drive three-DOF motor is mainly composed of the motor base, pre-pressure regulating system, PMs, electromagnetic stator core, electromagnetic stator coils, piezoelectric stators (No.1 stator, No.2 stator and No.3 stator) and rotor. The number of permanent magnets is four, two of which are N poles and two are S poles, which are alternately arranged. Sensors 2020, 20, 1621 3 of 18 The permanent magnet is a spherical structure, which is attached to the rotor", + " The included angle of the central axis of each stator is 120\u25e6. There are four spherical permanent magnets attached to the rotor. The pre-pressure between the stator and the rotor is adjusted by a pre-pressure regulating system. Sensors\u00a02020,\u00a020,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 3\u00a0of\u00a018\u00a0 included\u00a0angle\u00a0of\u00a0the\u00a0central\u00a0axis\u00a0of\u00a0each\u00a0stator\u00a0is\u00a0120\u00b0.\u00a0There\u00a0are\u00a0four\u00a0spherical\u00a0per anent\u00a0 agnets\u00a0 attached\u00a0to\u00a0the\u00a0rotor.\u00a0The\u00a0pre\u2010pressure\u00a0bet een\u00a0the\u00a0stator\u00a0and\u00a0the\u00a0rotor\u00a0is\u00a0adjusted\u00a0by\u00a0a\u00a0pre\u2010pressure\u00a0 regulating\u00a0syste .\u00a0 Figure\u00a01.\u00a0Structure\u00a0of\u00a0electromagnetic\u2010piezoelectric\u00a0hybrid\u00a0drive\u00a0motor.\u00a0 As\u00a0shown\u00a0in\u00a0Figure\u00a02a,\u00a0the\u00a0pre\u2010pressure\u00a0regulating\u00a0system\u00a0is\u00a0mainly\u00a0composed\u00a0of\u00a0a\u00a0pre\u2010pressure\u00a0 base,\u00a0a\u00a0pre\u2010pressure\u00a0bracket,\u00a0a\u00a0pre\u2010pressure\u00a0rod,\u00a0a\u00a0pre\u2010pressure\u00a0sleeve\u00a0and\u00a0a\u00a0pre\u2010pressure\u00a0slider.\u00a0The\u00a0 pre\u2010pressure\u00a0sleeve\u00a0and\u00a0the\u00a0motor\u00a0base\u00a0are\u00a0connected\u00a0by\u00a0a\u00a0screw,\u00a0and\u00a0the\u00a0bottom\u00a0of\u00a0the\u00a0pre\u2010pressure\u00a0 rod\u00a0and\u00a0the\u00a0pre\u2010pressure\u00a0sleeve\u00a0are\u00a0connected\u00a0by\u00a0another\u00a0screw.\u00a0In\u00a0Figure\u00a02b,\u00a0the\u00a0force\u00a0generated\u00a0by\u00a0 rotating\u00a0the\u00a0pre\u2010pressure\u00a0lever\u00a0is\u00a0converted\u00a0into\u00a0the\u00a0pressure\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0on\u00a0the\u00a0rotor\u00a0 spherical\u00a0 shell" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002798_e_download_5515_3621-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002798_e_download_5515_3621-Figure4-1.png", + "caption": "Figure 4. The air gap between microstrip antenna and reflector", + "texts": [ + " This is shown in Figure 2(a) for the top layer and Figure 2(b) for the bottom layer. This design was selected due to a directive and high gain of the antenna and compact in size. The fed slot with a complementary stub (wx, lx, we and le) is a slot radiating element (SRE) that was reported in [20]. As depicted in Figure 3, a reflecting ground plane was employed to achieve a unidirectional radiation pattern and also to increase the gain. This reflector was placed at the bottom of microstrip antenna as shown in Figure 4 with the air gap height (hair). There are several research works on the study of air gap between antenna and reflector for the high gain antenna [21]\u2013[25]. Thus, some of these parameters in Figures 2 and 3 are simulated, analyzed and discussed in section 3. Microstrip antenna with reflector and air gap for short range communication in \u2026 (Noor Azwan Shairi) The microstrip antenna part was fabricated as shown in Figure 5(a) for top layer and Figure 5(b) for bottom layer using FR4 substrate (dielectric constant=4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000854_e_download_6985_1865-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000854_e_download_6985_1865-Figure9-1.png", + "caption": "Figure 9. (a) Temperature distribution at maximum laser beam condition. (b) von Mises stress distribution at midsection of plate; (c)von Mises stress distribution at the completion of cooling period (d) Deformation at the completion of cooling period.", + "texts": [ + " To reduce the stress concentration, efforts have been made to achieve a favourable weld bead shape by welding process design and process control. The melting of the metal is used as part of the absorbed energy. The heat conduction is the primary mode 9718 journal.ump.edu.my/ijame \u25c4 of heat transfer at the initial stage. At the intermediate point, the friction causes the free surface of the welding pool to deform. The temperature variation on the sample during the welding process for one of the laser conditions, i.e., 2 kW, 600 mm/min, and 2 mm, is shown in Figure 9. From Figure 9(a), it can be clearly observed that maximum temperature occurs in the vicinity of the laser beam and the arc gets stabilised at the centre of the plate at a temperature reaching 1487 \u00b0C, which indicates that the cooling temperature zone of the specimen is away from the heat source. Residual stresses developed were also predicted because of thermal input during welding. The deformation due to the welding process is primarily due to developed residual stresses. The von Mises stress distribution predicted at the mid-section of the plate and also after completion of the cooling period are presented. Figure 9(b), 9(c), and 9(d) present the von-Mises stress distribution at the mid-section of the plate, von Mises stress distribution after complete cooling and deformation corresponding to the complete cooling period, respectively. The magnitude of von Mises stress is 1140 MPa, and the value corresponding to complete cooling is 960 MPa. Following the cooling phase, the thermal deformation is calculated using the original requirements of maraging steel. According to the data, the largest distortion occurred at 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure14-1.png", + "caption": "Figure 14. Thermal field distribution of three cross-sections: (a) the windward side; (b) the middle cross-section; and (c) the leeward side.", + "texts": [ + " However, the heat dissipation capacity of inner rotor windings in the core is poor for the inner rotor windings, so the temperature of inner rotor windings in the core is higher than that of end windings. When both the SM and the DRM are running at the rated speed and rated load, the 3-D thermal field distribution is calculated under condition of water cooling used in the casing and axial forced air, as shown in Figure 13. the windward side, middle cross-section, and the leeward side of the CS-PMSM are shown in Figure 14. In order to eliminate the effects of end face boundary conditions, the selected windward and leeward cross-sections are 2.5 mm away from the corresponding end face, respectively. The highest temperature of different parts in the above three cross-sections is shown in Table 7. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 7. From the temperature distribution of each cross-section in Table 7, it can be seen that the temperatures of the stator and inner rotor are very low, indicating that the axial force air have a good cooling effect on the CS-PMSM, especially for the inner rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002652_e_download_2375_2070-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002652_e_download_2375_2070-Figure1-1.png", + "caption": "Fig. 1. General view of the device for grain drying", + "texts": [], + "surrounding_texts": [ + "parameters of a mobile grain dryer" + ] + }, + { + "image_filename": "designv8_17_0000232_11837-016-1997-8.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000232_11837-016-1997-8.pdf-Figure2-1.png", + "caption": "Fig. 2. Schematic diagram of experimental apparatus.", + "texts": [ + " The resulting iron would contain slag stringers in an iron matrix and have virtually the same microstructure as that of modern wrought iron. Because the early smiths had to heat the bloomery iron in order to forge it into useful shapes, it seems quite reasonable that at least some of them used the same bloomery furnaces to heat the iron to forging temperatures. Therefore, these experiments on evaluating carburization of iron were done in hot charcoal contained in a cylindrical furnace that has been used to successfully produce bloomery iron from iron ore. Figure 2 presents a schematic view of the arrangement of the present experiments. An air blower was used to supply air to the two tuyeres at an equal and adjustable rate. The first experiment ran 2 bars and began by filling the furnace with crushed charcoal to a level of 3 inches (76 mm) below the top. Four thermocouples extended vertically into the chamber, one from below and three from above as shown in Fig. 2. They consisted of ceramic-insulated type K wire contained in 3/16-in\u2013diameter (4.8 mm) Inconel sheath. The experiment began by adding propane to the air for a short time to ignite the charcoal and then turning off the propane and controlling the air flow to heat the charcoal bed. The temperature was cycled between 1050 C and 950 C on the bottom thermocouple, tc 1, by turning the air on and off with charcoal being periodically added to the top. After 80 min, which included 3 cycles, two wrought iron plates, marked A and B, were inserted into the charcoal such that the bottom of the plates were located at the tip of thermocouple 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure15-1.png", + "caption": "Fig. 15 Gradual transition from hunting motion stability to instability hunting oscillation when \u03bbe = 0.16. (a) 877 Influence of vehicle speed on distribution characteristics of wheel wear index in tangent line operations. (b) 878 Lateral acceleration PSD of bogie frame changes gradually into forced resonance, ca. 6.0 Hz, when v=600 879 km/h. (c \u2013 d) Variation patterns of wheel spin and longitudinal creepage. 880", + "texts": [ + " Most scholars believe that the flat scar wheel is likely to 861 become one of the direct inducements for the longitudinal uneven wear formation of 862 wheel-rail rolling contact. 863 Relatively speaking, considering the primary hunting phenomenon existed in 864 German ICE3 prototype, the limit speed will be reduced to ca. 400 km/h or a little higher, 865 which is the main reason why the central hollow tread wear has become an exclusive 866 event with high occurrence probability in duration of the long-term operations on 867 dedicated lines. 868 (3) Stable wear at high conicity with tight track gauge effects. When \u03bbe=0.16, as 881 shown in Fig. 15, the negative influences of wheel spin creepage on instability hunting 882 oscillation is enhanced to some extent. Besides, the trailer bogie frame will also have the 883 process of gradual-enhanced lateral resonances due to the tight track gauge effects. 884 When \u03bbe > 0.16, as shown in Fig. 12 (b, d), the tight track gauge effects will grow 885 stronger so that the instability hunting oscillation becomes the dominant behaviour, 886 resulting in the terrible problems of wheel-rail dynamic interaction and noises" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001987_jmrsp.2023.15.26.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001987_jmrsp.2023.15.26.pdf-Figure1-1.png", + "caption": "Fig. 1: Cam mechanism with spring assuming the contact between the cam and the roller follower ensuring vertical displacements", + "texts": [ + " The design of the cam of high-speed production machines, which have different operating criteria, has certain requirements not only for the entire curve of the cam profile but also for specific zones. For example, it is necessary to lift, stop and return the follower, to respect the positions of the follower at the control points. At the same time, to ensure the continuity of the acceleration at all the control points, to maintain the permanent contact between the cam and the follower roller, to ensure minimum contact force in certain areas, to reduce the maximum Hertz pressure, to assume the continuity of the acceleration jerk, the minimum pressure angle, the minimum return time, etc. Figure 1 and 2 allow the comprehension of the mechanism. The studied mechanism is composed of a main console, a support, and a follower. The follower rolls on the cam (it is not shown), is open and cylindrical. There are 4 characteristic points: \u2022 The center of the follower moving according to the motion law \u2022 The center of the prismatic link \u2022 The center of the mass of the support \u2022 The application point of the resultant spring\u2019s forces The main effort applied to the support are: \u2022 Inertial force due to the acceleration \u2022 Spring elastic force \u2022 Cam roller force \u2022 Force in the prismatic joint It is conspicuous that we can observe these conflicting objectives", + " Such an objective function is the sum of all goal values. Thus, the problem can be considered a mono-objective problem with the use of algorithms based on the gradient method. Let us consider an illustrative example based on an industrial cam profile to better understand the proposed optimization approach. In order to show the efficiency of the suggested method, in this section, an optimization of a production machine\u2019s cam profile is considered the profile is shown in Fig. 4. The examined cam system is similar to the mechanism given in Fig. 1. The roller follower carried out rise, dwell, and return motions. To ensure the exact operation of the cam mechanism, the roller follower must go through precise checkpoints shown in Fig. 4. point \"a\" is the beginning of the movement. Point \"b\" is the end of a linear part that ensures a good fit between the cam and the follower when it arrives; this part is useful to make up the variable gap between each unit. Point \"c\" guarantees that the links of mechanisms will not collide during their various movements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004548_0820-023-01017-5.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004548_0820-023-01017-5.pdf-Figure1-1.png", + "caption": "Fig. 1 (a) Schematic illustration of the fabrication process of the GCMCP aerogel frame. (b) Schematic diagram of EMI shielding mechanism of GCMCP aerogel frame and its application in the EMI shielding to reduce electromagnetic radiation pollution", + "texts": [ + " The EMI shielding characteristics of aerogels were evaluated by the vector network analyzer (ZNB40, China) in X-band frequency range (8.2\u201312.4\u00a0GHz). The EMI shielding parameters are as follows: scattering parameters (S11 and S21), reflection coefficient (R), transmission coefficient (T), absorption coefficient (A), total EMI shielding effectiveness (SET), electromagnetic waves reflection (SER), electromagnetic waves absorption (SEA), and the calculation formula is as follows [15, 19]: The fabrication process of 3D printed gradient-conductive MXene/CNT/PI (GCMCP) aerogel frame is schematically exhibited in Fig.\u00a01a. Briefly, a homogeneous MXene/ CNT/PAA ink is obtained by dispersing the MXene, CNT and PAA in deionized water with magnetic stirring. Then, MXene/CNT/PAA inks with different CNT contents (1) = l Rwd (2)R = ||S11|| 2 (3)T = ||S21|| 2 (4)A = 1 \u2212 (R + T) (5)SET = 10 log ( 1 T ) (6)SER = 10 log ( 1 1 \u2212 R ) (7)SEA = 10 log ( 1 \u2212 R T ) are placed in the multiple feed system, and continuously deposited layer by layer on the plate through a 3D printer to prepare the gradient-conductive MXene/CNT/PAA gel frames", + " The average conductivity of MXene/ CNT/PAA is 38.1 S cm\u22121, which slightly increases to 40 S cm\u22121 after thermal imidization. The increase in conductivity is attributed to the removal of inserted water and other molecules during imidization, thus reducing the interlayer spacing of MXene nanosheets. The strategy achieves the accurate construction and integrated molding of gradientconductive structure and imparts hierarchical porous structure (lattice macrostructure and aerogel porous microstructure) to GCMCP aerogel frame (Fig.\u00a01b). In the GCMCP aerogel frame, the conductivity gradually increases from top to bottom, where the top layer serving as the absorbing layer (impedance match layer) and the bottom layer as the high reflective layer (impedance mismatch layer), forming an absorption-reflection-reabsorption interface [36]. Moreover, the middle layer acts as the transition layer that can enable GCMCP aerogel frame to reflect and dissipate electromagnetic waves through multi-interface reflection. In addition, the lattice structure of GCMCP aerogel frame extends the transmission path of electromagnetic waves and increases the multiple reflections inside aerogel pore walls, which greatly improves the EMI shielding performance [37, 38]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure21-1.png", + "caption": "Figure 21. Thermal field distribution under condition of water cooling used in the casing and the inner rotor when both the SM and the DRM run at the low speed and rated load.", + "texts": [ + " Meanwhile, due to the use of axial forced air, the temperature of the end windings at the windward side is much lower than that at the leeward side. By comparison of Tables 10 and 9, it shows that the CS-PMSM can run safely when the water cooling used in the casing and axial forced air are simultaneously adopted in the CS-PMSM. When both the SM and the DRM are running at the low speed and rated load, the 3-D thermal field distribution is calculated under condition of water cooling used in the casing and the inner rotor, as shown in Figure 21. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the water inlet side, middle cross-section, and the water outlet side of the CS-PMSM are shown in Figure 22. The selected water inlet, middle and water outlet cross-sections are the same as those in Section 4.1. The highest temperature of each part in the above three cross-sections is shown in Table 11. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 11" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure36-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure36-1.png", + "caption": "Figure 36 P-POD Mk. III Rev. E Bottom Panel", + "texts": [ + "8, which is still very high. The Top Panel was not expected to be the limiting factor in considering P-POD strength, even after mass reduction. Page 53 P-POD Mk. IV Bottom Panel The next part considered was the P-POD Bottom Panel. The Bottom Panel is similar to the Top Panel but lacks the bracket interface and venting holes. Addtionally, the Bottom Panel is commonly used as a mounting surface, and therefore needs to accommodate the mounting holes. The P-POD Mk. III Rev. E Bottom Panel is shown below in Figure 36. The original design features very thick ribs along the entire length of Page 54 the part. These ribs are necessary at the mounting hole locations but excessive any where else. This was the primary method of reducing the mass of the Bottom Panel. Sections where the standard mounting pattern resides were left alone, and all other locatons had material removed. The resulting design is shown below in Figure 37. A thin rib was left on the exterior for retained stiffness, but material was cutout on both the inside and outside of the panel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000364_f_zkwe2018_01032.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000364_f_zkwe2018_01032.pdf-Figure1-1.png", + "caption": "Fig. 1. Cooling and heating system with: a) heat sink and water block, b) two heat sinks.", + "texts": [ + " The proposed solution may be an alternative to using large and expensive air conditioning systems in buildings. In order to test the cooling and heating capacities of systems with Peltier modules, an algorithm and software for determination of the cell parameters, as well as for analysis and design of cooling/heating systems, have been developed. The algorithm and software have been verified by carrying out tests of the designed system on the built-in measuring stand. The developed prototype of a cooling and heating system is shown in Fig. 1. It provides for the possibility of cooling the hot side of the cell using a water block or a heat sink. In order to increase the thermal reaction speed of the system, low heat capacity heat sinks used in computer equipment for cooling the processors were applied. Two auxiliary copper blocks were placed on the built-in test stand to measure the thermal power consumed by and extracted from the Peltier cell. Temperature sensors PT 100 and the LabVIEW measuring system were used for temperature measurement", + "0[2 12 2 1 TTIbTIkPi (1) where: b=-1 for Pi =Pc, b=1 for Pi =Ph, I is the current, T2, T1 represent the temperature of the hot and cold surface of the cell, respectively, \u03c3 is the cell geometric factor, k is the number of pairs of semiconductor columns in the cell, \u03b1 is the Seebeck coefficient, \u03bb is the thermal conductivity, \u03c1 is the resistivity. The values of the last three parameters depend on temperature. To determine the temperature of both sides of the cell and selected components of the system, a circuit model of thermal phenomena has been used. The developed equivalent thermal circuit of the systems from Fig. 1 is shown in Fig. 2, where Pc, Ph represent the thermal power of the cold and hot cell sides, respectively; RthP, RthCu, RthR, RthWB, RthPar are the thermal resistances of the thermal paste, copper block, heat sink, water block, thermal insulation of the sidewalls of the copper block, 2 ITM Web of Conferences 19, 01032 (2018) https://doi.org/10.1051/itmconf/20181901032 ZKwE\u20192018 respectively; T1, T2, TA, Tc show the temperature of the Peltier cell surfaces, the temperature of the ambience and of the cold air at the output of the system, respectively", + " The simulation and experimental tests of the cooling/ heating system with Peltier modules of such types as TEC127085, TES1-24106, TEC1-12726 have been carried out. Due to the limited volume of the article, only selected research results have been presented. Fig. 4 shows the comparison of the calculated and measured temperature dependences T1(I) and T2(I) on the cold and hot areas of the cell surface. During the tests, in the process of being cooled, the radiator was placed in the closed thermal chamber, and the hot side of the cell was cooled with a water block (Fig. 1a). Fig. 5 shows the cooling capacity of the same system, but with the air inlet and outlet of the thermal chamber being open. The influence of vp air velocity on the temperature at the output of the system was investigated. The air speed at the output of the system was adjusted by changing the rotational speed of the fan. The measurements were repeated for two ways of cooling the hot side of the cell and the selected module types. Fig. 4. Comparison of the calculated and measured temperatures T1 and T2 on the cold and hot sides of a TEC-127085 type cell" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004756_e_download_7008_6354-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004756_e_download_7008_6354-Figure6-1.png", + "caption": "Figure 6: Axis of wheel camber", + "texts": [ + " In this concept the goal is to improve driver performances using a driver assistance system: the driver steers the front wheels and a controller assists the driver during the rear wheel toe angle modification. 3.3 Double effect: camber & toe angles The geometry of the suspension determines the rotation of the wheel at camber modification. In the case of double wishbone suspension at camber modification the wheel rotates around an axis, which is determined by the steering track-rod end and the connection point of the lower arm, see Figure 6. It means that the position of the track-rod end has an important role in the rotation of the wheel. Angle \u03b5 represents the angle of the xis, around which the wheel rotates at actuation. The consequence of angle \u03b5 is the relationship between the camber angle and the toe angle. During actuation there is camber angle modification and an additional toe angle. It means that a suitable suspension geometry can improve the lateral force on the tire not only by the camber angle, but also by the toe angle", + " The angle \u03b5 is determined by the position of the trackrod end and connection point of the lower arm. The lower arm position can be determined by other suspension construction performances [1], therefore it is necessary to influence the height and length of the track-rod. The length of track-rod plays a role in steering design [5], therefore the height of track-rod is chosen to influence wheel rotation. An appropriate choice of this height can improve the lateral force in the tire-road contact with the common camber and toe angle. Figure 6: Axis of wheel camber 3.4 Actuator forces The control input of the system is the lateral movement of a suspension point in the given construction. In a real implementation this movement is realized using a hydraulic actuator [11, 10, 2] or an electric motor [3]. In both systems it is necessary to determine force resistances, which influence the necessary power of the actuator. The in-built hydraulic actuator must compensate for different resistances at the generation of the wheel camber angle. In order to modify the camber angle of the rotated wheels it is necessary to generate energy against the gyroscopic effect", + " Since in most cases the tire can not be pushed into the road (except sand), the vertical movement of the tire-road contact point induces the movement of the chassis. It means that the hydraulic cylinder must increase the potential energy of the system and compensate for the energy dissipation of the damper. The formulation of this resistance depends on vehicle roll dynamics, see [15]. The lateral movement of actuator cylinder can result in a lateral movement of tire-road contact area in the plane of the road, see Figure 6. In Section 3.3 the importance of \u03b5 is established in the aspect of lateral forces. The rotation of the wheel also induces the movement of the tire-road contact area, which results in increased tire wear. The position of the rotation axis influences the position of the wheel, and during it the movement of the 4 Fig. 5. Estimation of parameters C\u03b3 There is another aspect of suspension control on the rear wheels. [11] proposes a system architecture in which the suspension geometry is modified to realize active toe angle on real wheels", + " In this concept the goal is to improve driver performances using a driver assistance system: the driver steers the front wheels and a controller assists the driver during the rear wheel toe angle modification. 3.3 Double effect: camber & toe angles The geometry of the uspension determines the rotation of the wheel at camber modification. In the case of double wishbone suspension at camber modification the wheel rotates around an axis, which is determined by the steering track-rod end and the connection point of the lower arm, see Fig. 6. It means that the position of the track-rod end has an important role in the rotation of the wheel. Angle \u03b5 represents the angle of the axis, around which the wheel rotates at actuation. The consequence of angle \u03b5 is the relationship between the camber angle and the toe angle. During actuation ther is camber angle odification and an additional toe angle. It means that a suitable suspension geometry can improve the lateral force on the tire not only by the camber angle, but also by the toe angle", + " In this concept the goal is to improve driver performances using a driver assistance system: the driver steers the front wheels and a controller assists the driver during the rear wheel toe angle modification. 3.3 Double effect: camber & toe angles The geometry of the suspension determines the rotation of the wheel at camber modification. In the case of double wishbone suspension at camber modification the wheel rotates around an axis, which is determined by the steering track-rod end and the connection point of the lower arm, see Figure 6. It means that the position of the track-rod end has an important role in the rotation of the wheel. Angle \u03b5 represents the angle of the axis, around which the wheel rotates at actuation. The consequence of angle \u03b5 is the relationship between the camber angle and the toe angle. During actuation there is camber angle modification and an additional toe angle. It means that a suitable suspension geometry can improve the lateral force on the tire not only by the camber angle, but also by the toe angle", + " Since in most cases the tire can not be pushed into the road (except sand), the vertical movement of the tire-road contact point induces the movement of the chassis. It means that the hydraulic cylinder must increase the potential energy of the system and compensate for the energy dissipation of the damper. The formulation of this resistance depends on vehicle roll dynamics, see [15]. The lateral movement of actuator cylinder can result in a lateral movement of tire-road contact area in the plane of the road, see Figure 6. In Section 3.3 the importance of \u03b5 is established in the aspect of lateral forces. The rotation of the wheel also induces the movement of the tire-road contact area, which results in increased tire wear. The position of the rotation axis influences the position of the wheel, and during it the movement of the 4 3.4 Actuator forces The control input of the system is the lateral move ent of a suspension oint in the given construction. In a real implementation this movement is realized using a hydraulic actuator [11], [10],[2] or an electric motor [3]", + " Since in most cases the tire can not be pushed into the road (except sand), the vertical movement of the tire-road contact point induces the movement of the chassis. It means that the hydraulic cylinder must increase the potential energy of the system and compensate for the energy dissipation of the damper. The formulation of this resistance depends on vehicle roll dynamics, see [15]. The lateral movement of actuator cylinder can result in a lateral movement of tire-road contact area in the plane of the road, see Fig. 6. In Section 3.3 the importance of \u03b5 is established in the aspect of lateral forces. The rotation of the wheel also induces the movement of the tire-road contact area, which results in increased tire wear. T p si of the rotation axis influences the position of the wheel, and during it the movement of the tire-road contact. An increased lateral movement of the contact area requires increased frictional energy E f ric, which must be generated by an actuator force. E f ric depends on the position of the wheel rotation axis: E f ric = f (\u03b5) (4) In this section several factors of variable geometry suspension actuator forces have been proposed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure8.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure8.8-1.png", + "caption": "Fig. 8.8. Time-frequency distribution of the vibration of upper mounting of shock absorber", + "texts": [], + "surrounding_texts": [ + "82 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260" + ] + }, + { + "image_filename": "designv8_17_0000489_e_download_8889_8047-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000489_e_download_8889_8047-Figure1-1.png", + "caption": "Fig. 1. a \u2013 dual band helical antenna structure; b \u2013 dual band Eshaped PIFA structure", + "texts": [ + " The purpose of this investigation is to compare the effects of substrate materials on EM absorption between external and internal handset antennas. A PIFA and a helical antenna are used as internal and external antenna of mobile phone respectively. Both antennas have dual band characteristics operating at GSM 900 MHz and DCS 1800 MHz. The peak SAR values in the human head and total absorbed power are evaluated for both antennas with varying antenna substrate materials. The geometry of the dual band helical antenna mounted on a conducting box is presented in Fig. 1 a. The design of helix is collected from [12]. The length and diameter of the helix are 18 mm and 5 mm respectively. For the dual band behavior of helical antenna is achieved using non-linear pitch along helix length. The helix is made of perfect electric conductor (PEC). The dimensions of conducting box are 100 mm \u00d7 40 mm \u00d7 20 mm. Fig. 1 b demonstrates detailed geometry of E-shaped PIFA, which is designed for dual band operation. The dimension of the substrate is 100 mm \u00d7 40 mm \u00d7 0.8 mm. The distance between the ground plane and patch is 8 mm. The dimension of shorting plane and feed are 8 mm \u00d7 1 mm \u00d7 0.2 mm and 4 mm \u00d7 1 mm \u00d7 0.2 mm respectively. The E-shaped patch dimension is 40 mm \u00d7 20 mm \u00d7 0.2 mm. The PEC material is also used for PIFA patch, feed and shorting wall. For both PIFA and helical antenna, five different dielectric substrate materials-Bakelite, FR4 glass epoxy, Rogers RO4003, and Taconic TLC are used to take effects of substrate materials" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000107_e_download_6617_5459-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000107_e_download_6617_5459-Figure3-1.png", + "caption": "Fig. 3. Sketches of a mock-up sample of the manual self-cleaning fork (version 1).", + "texts": [ + " Cleaning of the tines 3 is performed by the cleaning plate 4, which is moved along the tines 3. To do this, the user withdraws the movable handle 4, overcoming the resistance of the spring 6. By doing so, the frame 2 passes through the longitudinal grooves 7 and serves as one guide for the movable handle 5, and the handle 1 serves as the second guide. The fork returns to its original state by releasing the spring 6 after the user releases the movable handle 5. In the course of the experimental design work, the author of the device modeled two versions of mock-up samples (Fig. 3 and Fig. 4). Each of these versions differs in the direction of distribution of the user's force on the cleaning plate: above a plane of the tines (version 1) and below this plane (version 2). The results of the evaluation of the comparative effectiveness of the use of the design solutions will be presented based on the test results. In general, the technical result of the claimed utility device is an increase in the operational characteristics of the self-cleaning fork, reduction in the time and effort spent on cleaning of the tines" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002052_9312710_09380129.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002052_9312710_09380129.pdf-Figure2-1.png", + "caption": "FIGURE 2. The 3D configuration of the S-band transceiver board.", + "texts": [ + " Although the Bit Error Rate (BER) increases with the decreasing of the power in the back direction, successful link budget is still existing. Moreover, The CubeSat has six faces, if the antenna is in one face only, the probability of successful communication during the tumbling process may be a sextant, but if two sets of antennas on opposite directions are used the probability will be doubled. So, the use of two sets of antennas will enhance the communication between the CubeSat and the earth station, and decrease the probability of communication interruption. Fig. 2 depicts a 3Dmodel for the proposed S-band CubeSat communication subsystems structure illustrating the position, and the relationship of each board with its contiguous boards. In the following section, the antenna design, and configuration are explained in detail with its results, and discussions. In section IV, the filter design is illustrated with detailed results and discussions. Other boards are briefly explained in section V. Finally, the conclusion is introduced in section VI. III. ANTENNA DESIGN AND CONFIGURATION A" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004184_e_download_5667_4634-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004184_e_download_5667_4634-Figure1-1.png", + "caption": "Figure 1. Shows the winding and offset angles", + "texts": [ + " The closing section shall encompass a set of remarks and a conclusion statement. This paper is organized as follows. First, DTC theory algorithm is introduced in Section 2. Then, the fuzzy logic technique used in DTC, after that, a proposed neural rotor speed estimation use the voltage and current of the first start, is presented in Section 3. In the Section 4, some simulation results are presented. Finally, some concluding remarks are stated in the last Section. The dual star asynchronous machine. Whose Figure 1 expresses the windings of the double star induction machine and the offset angle between the two stars windings [1]. -A1, B1, C1: Winding of stator 01. -A2, B2, C2: Winding of stator 02 -\u03b1: offset angle between two stators. -\u03b8: offset angle between the rotative part and the stators 01&02. The mathematical model of the machine is can be expressed by the following set of electrical/mechanical equations The first star: Vabc, s1 Rs abc, s d \u03c6abc, s dt (1) The second start: Vabc, s2 Rs abc, s d \u03c6abc, s dt 2 For the rotative part: IJECE ISSN: 2088-8708 Contribution to the Artifical Neural Network Speed Estimator in a Degraded Mode for \u2026 (A" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure4-9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure4-9-1.png", + "caption": "Figure 4-9. Vues de l'antenne PIFA miniature", + "texts": [ + "......................................................... 107 Figure 4-6. Dimensions des syst\u00e8mes d'antenne \u00e0 deux monopoles triangulaires...................... 108 Figure 4-7. Photographies des quatre syst\u00e8mes d'antennes \u00e0 deux monopoles r\u00e9alis\u00e9s ............. 109 Figure 4-8. Coefficients de r\u00e9flexion simul\u00e9s et mesur\u00e9s des syst\u00e8mes \u00e0 deux monopoles pour diff\u00e9rents \u00e9cartements ................................................................................................................. 110 Figure 4-9. Vues de l'antenne PIFA miniature ........................................................................... 112 Figure 4-10. Vue de l'antenne PIFA sur substrat de type FoamClad.......................................... 113 Figure 4-11. Bande passante obtenue pour l'antenne PIFA miniature en fonction du substrat .. 113 Figure 4-12. Dimensions d'un syst\u00e8me \u00e0 diversit\u00e9 spatiale utilisant deux antennes miniatures. 114 Figure 4-13 Sch\u00e9ma de l'antenne PIFA agile en polarisation et en fr\u00e9quence.....", + " Nous avons donc essay\u00e9 de concevoir une structure d'antenne compacte dans le but de l'utiliser comme un composant discret que l'on viendrait souder sur le PCB de l'objet communicant, d'o\u00f9 le terme de \"chip antenna\" en anglais Compte tenu des moyens de r\u00e9alisation \u00e0 notre disposition, nous avons fait le choix de ne pas utiliser des mat\u00e9riaux \u00e0 forte permittivit\u00e9, comme la c\u00e9ramique. Nous avons travaill\u00e9 sur des structures PIFA dont le plateau sup\u00e9rieur est repli\u00e9 pour obtenir une antenne miniature. Dans un premier temps, nous avons utilis\u00e9 le m\u00eame substrat que celui utilis\u00e9 dans le syst\u00e8me \u00e0 deux patchs \u00e0 double polarisation, c'est-\u00e0-dire du CLTE de Arlon avec une permittivit\u00e9 de 2.98 et une \u00e9paisseur de 3,8 mm. Nous sommes arriv\u00e9s \u00e0 une antenne de faibles dimensions comme le montre la Figure 4-9.a. 112 Lorsque que cette antenne miniature est plac\u00e9e sur un plan de masse de relativement grande dimension comme sur la Figure 4-9.b, nous obtenons une bande passante \u00e0 -10 dB de 38MHz centr\u00e9e sur 2,45 GHz. L'efficacit\u00e9 totale de l'antenne est de 0,91 \u00e0 la fr\u00e9quence de r\u00e9sonnance, mais elle chute \u00e0 0,53 et 0,66 aux fr\u00e9quences de 2,4 GHz et 2,484 GHz respectivement qui repr\u00e9sentent les limites de la bande ISM que l'on cherche \u00e0 couvrir. Normalement les PIFA utilisent l'air comme di\u00e9lectrique entre le plateau sup\u00e9rieur et le plan de masse. L'utilisation d'un substrat \u00e0 base de t\u00e9flon nous a permis de r\u00e9duire la taille et d'assurer un bon maintien m\u00e9canique du plateau sup\u00e9rieur" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001612_jassp.2016.73.79.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001612_jassp.2016.73.79.pdf-Figure5-1.png", + "caption": "Fig. 5. The longitudinal body segment smart needle design (Podder et al., 2010)", + "texts": [ + " (2013) proposed to improve the controllability of a needle and to increase the curvature of the trajectory by giving a degree of freedom to asymmetrical tip of the needle placing nitinol wires along the needle (Fig. 4). A degree of freedom of the tip allows increasing the angle of deviation, therefore increasing maneuverability of the needle and its controllability resulting in potentially less tissue damage. Podder et al. (2010) proposed another construction of a steerable needle with nitinol wires on its outer side in the special clamping sleeve (Fig. 5). This construction provides a direct contact of the tissue with wires which have the property of shape memory with a temperature increase. To create a robotic system for brachytherapy it is important not only to develop special needles and optimal insertion trajectory, but also to establish the methods to control the needle behavior in the body during brachytherapy. Over the past 20 years, several attempts to control the steerable needles have been made. Abolhassani et al. (2007b) proposed a model for the control of a needle deflection from a target using ultrasound guidance as a feedback" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004900_9312710_09432829.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004900_9312710_09432829.pdf-Figure3-1.png", + "caption": "FIGURE 3. (a) Configuration and electric field distribution diagrams of (b) patch and (c) surface of the X-band embedded single elliptical patch reflecting element.", + "texts": [ + " The obtained electric field distribution diagram of the element is shown in Fig. 2 (b). The maximum electric field is lower than that in [14], but is still higher than that of the high power element [7]. The design with no triple junction can improve the power capacity [16]. So the traditional single elliptical patch reflecting element is modified with the patch embedded into substrate. The configurations of the embedded single elliptical patch reflecting element and the obtained electric field distribution are shown in Fig. 3. It can be found that the maximum electric field strength of the embedded patch is about half of that of the traditional element, and the electric field on the surface is significantly reduced. The compared results prove that the proposed embedded elliptical patch reflecting element shows high power capacity feature. It should be pointed out that the electric field on the surface would further reduce with a thicker substrate, but the available bandwidth would be changed. The reflected amplitude of the dual-band reflecting element with different commercially available thicknesses of upper substrate H1 are shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-FigureB-2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-FigureB-2-1.png", + "caption": "Figure B-2: Three sequential differential rotations.", + "texts": [ + " From the solutions for the joint rates it can be seen th a t for a given velocity of the end-effector, as the m anipulator approaches the singular configuration the joint input ra te goes to infinity. A P P E N D IX B D eriv a tiv e o f R o ta tio n a l U n it V ector T ran sform ation Fig.B-1 shows an increm ental configuration of the coordinate frame. \u00b0RM = ro tational unit vector transform ation between frame 0 and moving coordinate frame M d\u00b0RM \u00b0Rm = dt = linist-, o[ \u00b0RM(t + 8 t ) - \u00b0 R M{t)} 6t J .\u00b0RM(t)(M8R \u2014 I) = h m st^ 0{-----------\u2014----------- J MSR is defined as three increm ental sequential ro tational transform ations From Fig. B-2 and using CS \u2014> 1 and SS \u2014* S, MSR = R O T (M u 8l ) R O T (M 2,82) ROT{M 3,83) = 1 \u2014 83 82 ^3 1 - 8 2 8t 1 M8 R - - ] = M8t 0 \u2014Wm , 3 Wm ,2 - W m aWm , 3 0 \u2014Wm, 2 WMil 0 _ where W{ is the component of the infinitesimal angular velocity. Therefore, 201 2 0 2 \u00b0r m = \u00b0 r m Mn M In vector notation, 0 pM M p __0 yy ^ 0 pM M p Also m \u00a3Im can be represented as a ro tation with respect to an arb itrary axis. Ap pendix C shows the analytic in terpretation using Cayley-Ham ilton\u2019s theorem. A P P E N D IX C A n a ly tic a n d G e o m e tr ic I n te r p r e ta t io n o f a R o ta t io n a l T ra n s fo rm a tio n a ro u n d a n A r b i t r a r y A x is A ro ta tion with respect to an arb itrary axis is represented as e A* = I C $ + a *r ( 1 a = [ ax CLy &z ]T a r =- transpose of a A = \u2022 0 dz dy az 0 ~ay a* 0 ^ [CM] This is proved as follows: Caley H am ilton\u2019s Theorem [Ref" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure24-1.png", + "caption": "Figure 24: von-Misses stress of final design.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0002543_apers_D_N010104f.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002543_apers_D_N010104f.pdf-Figure7-1.png", + "caption": "Figure 7: (a) The bending moment on the VB. (b) Plan view at the section BB (i.e. at the waist circle).", + "texts": [ + " 6, the equivalent resultant compressive force Fc in a fibre (generator of the hyperboloid surface) is given by F2 c = [ N\u03c6 ( \u03c0a n )]2 + [ N\u03b8 ( \u03c0b n )]2 . (15) Substituting eqns (13) and (14) into eqn (15), we have Fc = C 2n cos \u03b2 = C \u221a H 2 + R2 \u2212 a2 2nH . (16) Thus the total axial loading is transmitted into the hyperboloid shell\u2019s straight generators as compressive forces. 3.2 VB stress analysis under bending moment When the VB is subjected to a bending moment (M ), normal stresses (\u03c3y) are developed at the waist circle (r0 = a) cross-section, as shown in Fig. 7. The bending moment sustained at the waist circle is given by M = 2 \u222b a 0 \u03c3y [ 2 t cos \u03b1 dy ] y, (17) where \u03c3y is the compressive stress normal to the cross section (due to the bending moment M ) acting on the two rectangular elements of length 2(t/ cos \u03b1) and width dy. In addition, \u03c3y = y a \u03c3a, (18) where \u03c3a is the stress at y = a. Combining eqns (17) and (18), we have M = 4 \u222b a 0 y2 a \u03c3a t cos \u03b1 dy M = 4t\u03c3a \u222b a 0 y2 a cos \u03b1 dy. (19) Substituting for y = a sin \u03b1 and dy = a cos \u03b1 d\u03b1, eqn (19) can be rewritten as M = 4t\u03c3a \u222b \u03c0/2 0 a2 sin2 \u03b1 a cos \u03b1 a cos \u03b1 d\u03b1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000403_citation-pdf-url_382-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000403_citation-pdf-url_382-Figure21-1.png", + "caption": "Figure 21. Configuration of the IRB 4400 Robot", + "texts": [], + "surrounding_texts": [ + "From Equation (69), the stiffness if the robot can be obtained, including the component or joint stiffness Ki . In order to obtain the total stiffness of the robot, the joint stiffness has to be measured. From Equation (68), the following Equation (70) can be obtained by finding the inverse of the matrix 1\u2212\u2212 kJJ T as . 1 \u03c4Ti JJKp \u2212 =\u0394 (70) Equation (70) is very important for measuring the joint stiffness. Many different equations can be obtained by applying different force \u03c4 with different directions then measuring the deflections p\u0394 . Least square method is applied to solve Equation (70). As variable 1/Ki is the unknown, one can simplify Equation (70) as linear equations since [ ]ii kK /1 1 = \u2212 is a diagonal matrix." + ] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure2-2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure2-2-1.png", + "caption": "Figure 2-2: Relative joint motion description.", + "texts": [ + " Joint axes are defined by lines in space. The geometric relation between the two neighboring joint axes can be specified using two param eters, link length a, and tw ist angle c^. Link length a, is the distance m easured along a line which is m utually perpendicular to both axes. Link twist angle is the angle m easured from axis i to axis i + 1 in the right-hand sense about x* (Fig. 2-1). The relative joint motion of link i + 1 is described by the joint variable 0i+1 which is an angle between Xj and x;+:t m easured around zI+ 1 (Fig. 2-2). Any mechanism can be described kinematically using a*, a,-, dj+i, and $i+i link param eters defined above, referred to as DH param eters. The corresponding joint transform ation is defined by the homogeneous coordi nate description using DH link param eters (Fig. 2-3). The homogeneous coordi nate representation allows one to express the relative spatial motion of several rigid bodies analytically in a compact form. The modeling index used in this work is different from the usual [Ref. 2]. However, it follows the conventional kinematic 12 13 description of a linkage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002807_118_4_118_4_444__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002807_118_4_118_4_444__pdf-Figure1-1.png", + "caption": "Fig. 1. Structure of a cylindrical moving coil type LDM (unit is mm).", + "texts": [], + "surrounding_texts": [ + "\u8ad6 \u6587\n\u5186\u7b52\u72b6 \u30b3\u30a4\u30eb\u53ef\u52d5\u5f62 \u30ea\u30cb\u30a2\u76f4\u6d41\u30e2\u30fc\u30bf\u306e\n\u63a8\u529b/\u5165 \u529b\u6bd4 \u306b\u95a2\u3059\u308b\u8003\u5bdf\n\u6b63 \u54e1 \u6c34 \u91ce \u52c9(\u4fe1 \u5dde \u5927)\n\u6b63 \u54e1 \u5bae \u4e0b \u5229 \u4ec1(\u5c71 \u6d0b\u96fb\u6c17)\n\u5b66\u751f\u54e1 \u77e2 \u5cf6 \u4e45 \u5fd7(\u4fe1 \u5dde \u5927)\n\u5b66\u751f\u54e1 \u5510 \u7389\u742a(\u4fe1 \u5dde \u5927)\n\u6b63 \u54e1 \u5c71 \u672c \u79c0 \u592b(\u677e \u4e0b\u51b7\u6a5f)\n\u6b63 \u54e1 \u6e0b \u8c37 \u6d69 \u6d0b(\u677e \u4e0b\u51b7\u6a5f)\n\u6b63 \u54e1 \u5c71 \u7530 \u4e00(\u4fe1 \u5dde \u5927)\nConsiderations on Thrust-to-Input Ratio of a Cylindrical Moving Coil Type\nLinear DC Motor\nTsutomu Mizuno, Member, (Shinshu University), Toshihito Miyashita, Member (Sanyo Denki), Hisashi Yajima, Student Member, Yu Qi Tang, Student Member (Shinshu University), Hideo Yamamoto, Member, Koyo Shibuya, Member (Matsushita Refrigeration), Hajime Yamada, Mamber (Shinshu University)\nLinear DC motors (LDMs) are widely used for servo-actuator, compressor and so on. High-efficiency LDMs are strongly desired for compressors. To realize the LDMs with high-efficiency characteristics, decreasing the copper losses, namely, thrust-to-input ratio, F/P, must be increased. This paper describes an optimization method for the F/P of a moving coil type LDM. The following results are obtained :\n(1) Simplified expression for the F/P of the LDM is derived from the permeance analysis method. The\neffects that dimensions of the LDM influence the F/P of the LDM are investigated through the simplified expression for the F/P. As a result, the optimum dimension of the LDM for maximizing the F/P exists. (2) When the static thrust is 100 N, the measured F/P of the initial LDM is 7.9 N/W, and the errors by using the simplified expression for the F/P and the finite element method (FEM) are 33 % and 8 %, respectively. Derived simplified expression for the F/P is useful because the F/P can be calculated easily. (3) An improved LDM, which has 26 % higher F/P than those of the initial LDM, is designed by using the permeance analysis method and the FEM.\n\u30ad \u30fc \u30ef \u30fc \u30c9:\u30ea \u30cb \u30a2 \u30e2 \u30fc \u30bf,\u30b3 \u30a4\u30eb \u53ef \u52d5 \u5f62 \u30ea\u30cb \u30a2\u76f4 \u6d41 \u30e2 \u30fc \u30bf,\u63a8 \u529b/\u5165 \u529b \u6bd4,\u30e2 \u30fc \u30bf\u5b9a \u6570,\u9285 \u640d\n1.\u307e \u3048 \u304c \u304d\n\u5f93 \u6765 \u304b \u3089\u6b27\u7c73 \u3067 \u306f,\u5b87 \u5b99 \u7a7a \u9593\u3067 \u7528 \u3044 \u308b\u30b9 \u30bf\u30fc \u30ea\u30f3\u30b0\u30a8 \u30f3 \u30b8 \u30f3 \u7528 \u306e \u30a2 \u30af \u30c1 \u30e5\u30a8\u30fc \u30bf \u3068 \u3057 \u3066 \u30ea\u30cb \u30a2 \u76f4 \u6d41 \u30e2 \u30fc \u30bf\n(LDM)\u306e \u7814\u7a76 \u304c \u71b1 \u5fc3 \u306b\u884c \u308f\u308c \u3066 \u304d\u305f\u3002 \u30ea\u30cb \u30a2 \u30b3\u30f3 \u30d7 \u30ec \u30c3 \u30b5 \u306b\u7528 \u3044 \u308bLDM\u306b \u306f\u9ad8\u52b9 \u7387 \u3067 \u3042 \u308b \u3053 \u3068\u304c \u671b \u307e\u308c \u3066 \u304a \u308a, \u3053\u308c \u3092\u5b9f\u73fe \u3059 \u308b\u305f \u3081 \u306b\u306f,\u9285 \u640d \u3084\u9244 \u640d \u306a \u3069\u306e\u640d \u5931 \u3092\u4f4e \u6e1b \u3059\n\u308b\u5fc5\u8981 \u304c \u3042 \u308b\u3002Jonge\u3089 \u306f,\u78c1 \u6975(\u30dd\u30fc \u30eb \u30d4\u30fc \u30b9)\u3092 \u7db2 \u3044 \u3066 \u30b3\u30a4\u30eb \u306b\u4f5c \u7528 \u3059 \u308b\u78c1 \u675f \u5bc6 \u5ea6 \u3092\u5927 \u304d \u304f\u3059 \u308b\u69cb\u9020 \u306e \u30b3\u30a4\u30eb\u53ef\n\u52d5 \u5f62LDM\u306e \u52b9 \u7387 \u306b \u95a2 \u3059 \u308b\u691c \u8a0e \u3092 \u884c \u3063 \u3066 \u3044 \u308b(1)\u3002\u307e \u305f Clark\u3089 \u306f.\u78c1 \u77f3 \u53ef\u52d5 \u5f62LDM\u306e \u9285\u640d \u306e\u6700 \u5c0f\u5316 \u306b \u3064 \u3044\u3066\u691c\n\u8a0e \u3057\u3066 \u3044 \u308b(2)\u3002\n\u8fd1 \u5e74 \u306e\u6c38 \u4e45\u78c1 \u77f3 \u306e\u9ad8\u6027 \u80fd\u5316 \u306b \u3068 \u3082\u306a \u3063\u3066\u78c1\u6975 \u3092\u7528 \u3044 \u308b \u3053 \u3068\u306a \u304f\u30b3\u30a4\u30eb \u306b\u4f5c \u7528\u3059 \u308b\u78c1 \u675f\u5bc6 \u5ea6 \u3092\u5927 \u304d \u304f\u3067 \u304d\u308b \u3088\u3046\u306b\u306a \u3063\u3066 \u304d\u305f\u3002 \u305d \u3053\u3067\u8457 \u8005 \u3089\u306f,\u6c38 \u4e45\u78c1 \u77f3 \u304c \u30b3 \u30a4\u30eb \u306b\u5bfe \u9762\u3059 \u308b\n\u69cb \u9020 \u306e \u30b3\u30a4\u30eb\u53ef \u52d5\u5f62LDM\u306e \u640d\u5931 \u7279 \u6027 \u306b\u95a2 \u3059 \u308b\u691c \u8a0e \u3092\u884c \u3063 \u3066 \u304d\u305f(3)(4)\u3002\n\u672c \u8ad6 \u6587 \u306f,\u63a8 \u529b/\u5165 \u529b\u6bd4 \u306b\u7740 \u76ee \u3057\u3066\u63a8 \u529b/\u5165 \u529b\u6bd4 \u3092\u6700\u5927,\n\u3059 \u306a\u308f \u3061\u9285 \u640d \u3092\u6700\u5c0f \u3068\u3059 \u308b \u3053 \u3068\u3067 \u9ad8\u52b9 \u7387 \u5316 \u3092\u5b9f\u73fe \u3059 \u308b\u305f\u3081 \u306eLDM\u306e \u69cb \u9020 \u306b \u3064\u3044 \u3066\u8003\u5bdf \u3057\u3066 \u304a \u308a,\u4ee5 \u4e0b \u306e\u9805 \u76ee \u306b\u3064\u3044 \u3066\u8ff0 \u3079 \u308b\u3002\n(1)\u30d1 \u30fc \u30df\u30a2 \u30f3\u30b9\u6cd5 \u3092\u7528 \u3044\u305f \u63a8\u529b/\u5165 \u529b\u6bd4 \u306e\u8868\u73fe \u5f0f \u306e\u5c0e\u51fa\n444 T. IEE Japan, Vol. 118-D, No.4, '98", + "\u8868i \u5186\u7b52\u72b6\u30b3\u30a4\u30eb\u53ef\u52d5\u5f62LDM\u306e \u57fa\u672c\u4ed5\u69d8\n(2)\u63a8 \u529b/\u5165 \u529b\u6bd4 \u306e\u5b9f \u6e2c \u5024 \u3068,\u30d1 \u30fc \u30df\u30a2 \u30f3\u30b9 \u6cd5 \u304a \u3088 \u3073\u6709 \u9650 \u8981\u7d20\u6cd5(FEM)\u3092 \u7528 \u3044\u305f\u8a08 \u7b97\u5024 \u3068\u306e\u6bd4 \u8f03 (3)\u4e00 \u5b9a \u306e \u5916 \u5f62 \u5bf8 \u6cd5 \u306e \u4e0b \u3067 \u5927 \u304d \u306a\u63a8 \u529b/\u5165 \u529b \u6bd4 \u3092\u6709 \u3059 \u308b LDM\u306e \u691c \u8a0e\n2. \u30ea\u30cb \u30a2 \u76f4\u6d41 \u30e2 \u30fc \u30bf \u306e\u69cb \u9020\n\u56f31\u306f \u5186\u7b52 \u72b6 \u30b3 \u30a4 \u30eb \u53ef\u52d5 \u5f62LDM\u306e \u8a66 \u4f5c \u6a5f \u306e \u69cb \u9020 \u3067 \u3042\n\u308a,LDM\u306e \u5916\u5f84 \u5bf8 \u6cd5 \u306f \u03c6170\u00d7120 mm,\u5185\u5f84 \u03c650 mm\u304c\n\u8ef8\u53d7 \u306e\u30b9\u30da \u30fc \u30b9 \u3068\u306a \u3063\u3066 \u3044 \u308b\u3002 \u307e\u305f16\u500b \u306e\u6c38 \u4e45\u78c1 \u77f3 \u304c \u5916 \u5074 \u30e8\u30fc \u30af \u306b\u914d \u7f6e \u3055\u308c \u3066 \u304a \u308a,\u5185 \u5074 \u30e8\u30fc \u30af \u306f \u30b3\u30a4\u30eb \u30dc \u30d3\u30f3\u304c \u633f\u5165 \u3055\u308c \u308b\u305f \u3081\u306b\u56db \u3064 \u306b\u5206\u5272 \u3055\u308c \u3066 \u3044 \u308b\u3002\n\u88681\u306bLDM\u306e \u57fa \u672c \u4ed5\u69d8 \u3092\u793a \u3057\u3066 \u3042 \u308a,\u30b3 \u30a4 \u30eb\u306e \u62b5\u6297 \u306f 11.6\u03a9,Nd-Fe-B\u78c1 \u77f3 \u306e \u8cea \u91cf \u306f1.2kg,\u30e8 \u30fc \u30af \u306b \u306f\u7d14 \u9244\n(SUY)\u3092 \u4f7f \u7528 \u3057\u3066 \u3044 \u308b\u3002\n3,\u5186 \u7b52 \u72b6 \u30b3 \u30a4 \u30eb \u53ef \u52d5 \u5f62LDM\u306e \u78c1 \u6c17 \u56de \u8def \u89e3 \u6790\nLDM\u306e \u69cb \u9020\u5bf8 \u6cd5 \u304c\u63a8 \u529b/\u5165 \u529b \u6bd4 \u306b\u4e0e \u3048 \u308b\u5f71 \u97ff \u3092\u691c \u8a0e \u3059\n\u308b\u305f \u3081\u306b \u306f\u7c21\u6613 \u306a\u89e3\u6790 \u624b \u6cd5 \u304c\u671b \u307e\u308c \u308b\u3002 \u305d \u3053\u3067\u672c\u7ae0 \u3067\u306f,\n\u307e\u305a \u30d1\u30fc \u30df\u30a2 \u30f3\u30b9\u6cd5 \u3092\u7528 \u3044 \u305f\u78c1 \u6c17 \u56de\u8def \u89e3 \u6790 \u306b \u3088 \u308a\u63a8 \u529b/\u5165\n\u529b \u6bd4 \u306e\u8868\u73fe \u5f0f \u3092\u5c0e \u51fa\u3059 \u308b\u3002 \u3053\u306e\u8868 \u73fe \u5f0f \u306b\u57fa\u3065 \u3044\u3066\u4e00 \u5b9a \u306e\u5916 \u5f62 \u5bf8 \u6cd5(LDM\u306e \u9577 \u30551,\u5916 \u5f84 \u534a \u5f84 \u03b3)\u306e \u6761 \u4ef6 \u306e\u4e0b \u3067,\u30e8 \u30fc \u30af\u306e\u539a \u3055\u3084\u78c1 \u77f3 \u306e\u539a \u3055\u304c\u63a8 \u529b/\u5165 \u529b\u6bd4 \u306b\u4e0e \u3048 \u308b\u5f71\u97ff \u306b \u3064\n\u3044 \u3066 \u8003 \u5bdf \u3059 \u308b\u3002 \u66f4 \u306b \u30d1 \u30fc \u30df\u30a2 \u30f3 \u30b9 \u6cd5 \u3067\u5f97 \u3089\u308c \u305f \u6210 \u679c \u3068\nFEM\u306b \u3088 \u308b\u6570 \u5024\u89e3 \u6790 \u7d50\u679c \u3068\u3092\u6bd4 \u8f03\u691c \u8a0e \u3059 \u308b\u3002\n\u30083\u30fb1>LDM\u306e \u89e3 \u6790 \u30e2 \u30c7 \u30eb \u56f32\u306f \u5186\u7b52 \u72b6 \u30b3\u30a4 \u30eb \u53ef\n\u52d5 \u5f62LDM\u306e \u89e3 \u6790 \u30e2 \u30c7 \u30eb \u3067 \u3042 \u308b\u3002 \u540c \u56f3 \u4e2d \u306b \u304a \u3044 \u3066,1: LDM\u306e \u9577 \u3055(=120mm\u4e00 \u5b9a),lm:\u6c38 \u4e45 \u78c1 \u77f3 \u306e \u9577 \u3055\n(m),hs:\u7aef \u90e8 \u30e8 \u30fc \u30af \u306e \u539a \u3055(m),lc:\u30b3 \u30a4 \u30eb \u306e \u9577 \u3055 (m),s:\u30b9 \u30c8\u30ed\u30fc \u30af(\u4e8c20 mm\u4e00 \u5b9a), ho:\u5916 \u5074 \u30e8\u30fc \u30af \u306e\u539a \u3055(m),hm:\u6c38 \u4e45\u78c1 \u77f3 \u306e \u539a \u3055(m),\u03b4:\u30e1 \u30ab \u30cb \u30ab \u30eb \u30ae \u30e3 \u30c3 \u30d7 \u306e \u9577 \u3055(=0.55mm\u4e00 \u5b9a),hc:\u30b3 \u30a4 \u30eb \u306e \u539a \u3055\n(m),hi:\u5185 \u5074 \u30e8\u30fc \u30af \u306e\u539a \u3055(m),\u03b3f:\u5185 \u5074 \u30e8\u30fc \u30af\u306e \u5185\u5f84\n\u534a \u5f84(=25mm\u4e00 \u5b9a),\u03b3:LDM\u306e \u5916 \u5f84 \u534a \u5f84(=85 mm \u4e00 \u5b9a)\u3067 \u3042 \u308b \u3002 \u307e\u305f\u6c38 \u4e45\u78c1 \u77f3 \u304b \u3089\u7aef\u90e8 \u30e8\u30fc \u30af\u3078 \u306e\u6f0f\u308c\u78c1 \u675f\n\u3092\u4f4e\u6e1b \u3059 \u308b\u305f \u3081\u306b,\u6c38 \u4e45 \u78c1\u77f3 \u306e\u7aef \u90e8 \u3068\u7aef \u90e8 \u30e8\u30fc \u30af \u3068\u306e\u9593 \u306b\n\u6c38 \u4e45\u78c1 \u77f3 \u306e \u539a \u3055 \u3068\u540c \u3058\u9577 \u3055hm\u3092 \u8a2d \u3051 \u308b \u3053 \u3068\u306b\u3059 \u308b\u3002 \u66f4 \u306b \u540c\u56f3 \u4e2d \u306b\u6c38\u4e45 \u78c1\u77f3 \u306e\u78c1 \u675f \u03c6m\u3092 \u793a \u3057\u305f\u3002\n\u672c \u30e2 \u30c7\u30eb \u3067 \u306f,\u89e3 \u6790 \u306e\u7c21\u4fbf \u5316 \u3092\u56f3 \u308b\u305f \u3081\u306b \u5185\u5074 \u30e8\u30fc \u30af \u3092\n\u96fb\u5b66\u8ad6D,118\u5dfb4\u53f7,\u5e73 \u621010\u5e74 445", + "\u56db \u3064 \u306b\u5206 \u5272 \u3057\u305f \u3053 \u3068\u304c\u63a8 \u529b/\u5165 \u529b\u6bd4 \u306b\u4e0e \u3048 \u308b\u5f71 \u97ff \u3092\u7121 \u8996 \u3057 \u3066 \u304a \u308a,\u5185 \u5074 \u30e8\u30fc \u30af\u304c\u5206\u5272 \u3055\u308c \u3066 \u3044\u306a \u3044 \u3082\u306e \u3068 \u3057\u3066\u89e3\u6790 \u3059 \u308b\u3002\n\u30083\u30fb2>\u63a8 \u529b/\u5165 \u529b\u6bd4 \u306e\u8868 \u73fe \u5f0f\u306e \u5c0e\u5165 \u30d1 \u30fc \u30df\u30a2 \u30f3\u30b9\u6cd5 \u3092\u7528 \u3044\u305fLDM\u306e \u78c1 \u6c17 \u56de\u8def\u89e3 \u6790 \u306b \u3042\u305f \u308a,\u4ee5 \u4e0b \u306e\u4eee \u5b9a \u3092\u8a2d \u3051 \u308b\u3002\n(\u306e \u6c38\u4e45\u78c1 \u77f3 \u304b \u3089\u7aef\u90e8 \u30e8\u30fc \u30af\u3078 \u306e\u6f0f \u308c\u78c1 \u675f \u306f \u306a\u3044 (ii)\u30e8 \u30fc \u30af\u306e\u900f\u78c1 \u7387 \u306f\u7121 \u9650\u5927 \u3068\u3057,\u30e8 \u30fc \u30af\u306e\u78c1 \u6c17\u62b5 \u6297 \u306f\n\u8003 \u616e \u3057\u306a\u3044\n\u4e0a \u8a18 \u306e\u4eee \u5b9a \u306b\u57fa \u3065 \u304dLDM\u306e \u78c1 \u6c17 \u7b49\u4fa1 \u56de\u8def \u306f,\u56f33\u306e \u3088\n\u3046\u306b \u306a \u308b\u3002 \u540c \u56f3 \u306b \u304a \u3044 \u3066F'm\u306f \u6c38 \u4e45\u78c1 \u77f3 \u306e\u8d77 \u78c1 \u529b,Rm\u306f \u6c38\u4e45 \u78c1\u77f3 \u306e\u5185\u90e8 \u78c1\u6c17 \u62b5 \u6297,RS\u306f \u30ae \u30e3 \u30c3\u30d7\u306e\u78c1 \u6c17 \u62b5 \u6297,\u59ac \u306f\u6c38 \u4e45\u78c1 \u77f3 \u306b \u3088 \u308b\u78c1 \u675f \u3067 \u3042 \u308b\u3002\n\u56f33\u306e \u78c1\u6c17 \u7b49 \u4fa1 \u56de\u8def \u3068\u56f32\u306b \u793a \u3057\u305fLDM\u306e \u89e3\u6790 \u30e2 \u30c7\u30eb\n\u304b \u3089\u6b21\u5f0f \u304c\u6210 \u7acb \u3059 \u308b(4)\u3002\n(1)\n(2)\n(3)\n(4)\n\u3053\u3053 \u306b,H\u3002:\u6c38 \u4e45 \u78c1 \u77f3 \u306e\u4fdd \u78c1 \u529b(A/m),\u03bc \u3002:\u771f\n\u7a7a \u306e\u900f\u78c1 \u7387(\u7f754\u03c0 \u00d710\u4e00'H/m)\n\u6b21 \u306bLDM\u306e \u9759 \u63a8 \u529bF\u306f \u30d5 \u30ec \u30df\u30f3 \u30b0\u306e \u5de6\u624b \u5247 \u3088 \u308a\u4e0b \u5f0f\n\u3067\u4e0e \u3048 \u3089\u308c \u308b\u3002\n(5)\n\u3053 \u3053 \u306b,N:\u30b3 \u30a4 \u30eb \u306e \u5dfb \u6570(\u56de), L:1\u5dfb \u5f53 \u305f \u308a\u306e\u9285 \u7dda \u306e \u5e73\u5747 \u306e\u9577 \u3055(m),B:\u30b3 \u30a4\u30eb \u306b\u4f5c \u7528 \u3059 \u308b \u78c1 \u675f \u5bc6 \u5ea6 \u306e \u5e73 \u5747 \u5024(T),I:\u52b1 \u78c1 \u96fb \u6d41(A), Kf:\u63a8 \u529b \u5b9a\u6570(=NLB)(N/A)\n\u4e0a \u5f0f \u306e\u53f3 \u8fba \u306e\u5404 \u5909\u6570 \u306f,\u305d \u308c \u305e\u308c \u6b21\u5f0f \u3067\u6c42 \u3081 \u308b\u3053 \u3068\u304c \u3067\n\u304d\u308b(4)\u3002\n(6)\n(7)\n(8)\n\u3053 \u3053 \u306b,\u03b6:\u30b3 \u30a4 \u30eb \u306e \u5360 \u7a4d \u7387(=0.78),Ac:\u30b3 \u30a4\n\u30eb \u306e\u65ad \u9762\u7a4d(=lchc)(m2), d:\u9285 \u7dda \u306e\u76f4\u5f84(m)\n\u307e\u305f \u30b3 \u30a4\u30eb \u306e\u62b5 \u6297R\u306f \u4e0b \u5f0f \u3067\u6c42 \u3081 \u3089\u308c \u308b(4)\u3002\n(9)\n\u3053 \u3053\u306b,\u03c1:\u9285 \u306e\u62b5 \u6297 \u7387(\u51a81.673\u00d710-8\u03a9m)\n\u66f4 \u306bLDM\u306b \u76f4 \u6d41 \u306e\u52b1\u78c1 \u96fb \u6d41 \u3092\u6d41 \u3057,\u304b \u3064\u53ef \u52d5 \u5b50 \u3092\u62d8\u675f\n\u3057\u305f\u5834 \u5408 \u306e \u5165\u529bP\u306f \u9285\u640dWc\u3068 \u7b49 \u3057 \u304f\u6b21\u5f0f \u3067 \u793a \u3055\u308c \u308b\u3002\n(10)\n(11)\n\u3053 \u3053\u306b,Vc:\u30b3 \u30a4 \u30eb\u306e\u4f53 \u7a4d(m3)\n\u5f93 \u3063\u3066,(10)\u5f0f \u304b \u3089\u63a8 \u529b/\u5165 \u529b \u6bd4F/P\u306e \u8868 \u73fe \u5f0f \u306f\u6b21 \u306e\n\u5f62 \u3068\u306a \u308b\u3002\n(12)\n\u4e0a \u5f0f \u306f,\u63a8 \u529b/\u5165 \u529b\u6bd4 \u304cLDM\u306e \u767a\u751f \u3059 \u308b\u9759\u63a8 \u529bF\u306b \u53cd\n\u6bd4\u4f8b \u3057\u3066\u3044 \u308b \u3053 \u3068\u3092\u793a \u3057\u3066 \u304a \u308a,F/P\u3092 \u7b97 \u51fa\u3059 \u308b\u969b \u306eF \u306e \u5024 \u306b \u3088 \u3063 \u3066F/P\u304c \u5909 \u5316 \u3059 \u308b \u305f \u3081\u6ce8 \u610f \u3092\u8981 \u3059 \u308b\u3002F/P\n\u3092\u6c42 \u3081 \u308b\u969b \u306eF\u3068 \u3057\u3066,(1)\u9759 \u63a8 \u529b \u306e\u98fd \u548c \u5024,(2)\u5b9a \u683c\n\u63a8 \u529b(\u71b1 \u5b9a \u683c),\u3092 \u7528 \u3044 \u308b\u65b9\u6cd5 \u304c\u8003 \u3048 \u3089\u308c \u308b\u3002\u672c \u8ad6 \u6587 \u306b\u304a \u3044 \u3066\u63a8 \u529b/\u5165 \u529b \u6bd4 \u3092\u7b97 \u51fa\u3067 \u304d\u308b\u7bc4 \u56f2 \u306f,\u89e3 \u6790 \u306e\u4eee \u5b9a \u3067\u8ff0 \u3079\n\u305f \u3088 \u3046\u306b \u30e8\u30fc \u30af\u306e\u78c1\u6c17 \u62b5 \u6297\u304c \u7121\u8996 \u3067 \u304d\u308b\u7bc4 \u56f2,\u3059 \u306a\u308f \u3061\u63a8\n\u529b \u304c\u52b1 \u78c1 \u96fb\u6d41 \u306b\u6bd4 \u4f8b \u3059 \u308b\u7bc4\u56f2 \u3067 \u3042 \u308b\u3002 \u305d \u3053\u3067,\u63a8 \u529b\u304c\u52b1\u78c1 \u96fb \u6d41 \u306b\u6bd4 \u4f8b \u3059 \u308b\u9759 \u63a8 \u529b \u3092\u7528 \u3044\u3066\u63a8 \u529b/\u5165 \u529b\u6bd4 \u3092\u7b97 \u51fa \u3059 \u308b\u3053\n\u3068\u306b\u3059 \u308b\u3002 \u63a8 \u529b\u304c\u52b1 \u78c1 \u96fb \u6d41 \u306b\u6bd4 \u4f8b \u3059 \u308b\u7bc4 \u56f2 \u306e\u9759\u63a8 \u529b \u3092\u7528 \u3044 \u3066 \u3082,\u5f8c \u8ff0 \u3059 \u308b \u3088 \u3046 \u306bLDM\u306e \u30e8\u30fc \u30af \u306e\u539a \u3055\u304c \u63a8\u529b/\u5165 \u529b \u6bd4 \u306b\u4e0e \u3048\u308b\u5f71\u97ff \u3092\u691c \u8a0e \u3059 \u308b\u5834\u5408 \u306b\u306f\u4e00 \u822c\u6027 \u3092\u5931\u308f \u306a\u3044\u3002\n\u307e\u305f\u56de \u8ee2\u5f62 \u30e2\u30fc \u30bf\u3067\u5b9a \u7fa9 \u3055\u308c \u3066\u3044 \u308b\u30e2\u30fc \u30bf Km(5}\u3092\n\u672cLDM\u306b \u9069 \u5fdc \u3059 \u308b \u3068\u6b21 \u5f0f\u304c \u5f97 \u3089\u308c \u308b\u3002\n(13)\n(12)\u5f0f,(13)\u5f0f \u304b \u3089\u63a8 \u529b/\u5165 \u529b \u6bd4F/P\u3068 \u30e2\u30fc \u30bf\u5b9a \u6570Km\n\u3068\u306f,Vc=AIL\u3092 \u7528 \u3044 \u308b \u3068\u4ee5\u4e0b \u306e\u95a2\u4fc2 \u304c \u3042 \u308b\u3002\n(14)\n\u4e0a \u5f0f \u306f,\u5c0f \u5f62 \u30e2 \u30fc \u30bf\u3067\u8981\u6c42 \u3055\u308c \u3066\u3044 \u308b\u30e2\u30fc \u30bf\u5b9a\u6570 \u3092\u5927 \u304d \u304f\u3059 \u308b \u3053 \u3068 \u3068,\u63a8 \u529b/\u5165 \u529b\u6bd4 \u3092\u5897\u52a0 \u3055\u305b \u308b \u3053 \u3068\u304c \u540c \u3058\u610f \u5473\n\u3092 \u3082\u3064 \u3053\u3068 \u3092\u793a \u3057\u3066\u3044 \u308b\u3002\n\u66f4 \u306b(5)\u5f0f \uff5e(12)\u5f0f \u306f,LDM\u306e \u8a2d \u8a08 \u4e0a \u306e \u91cd \u8981 \u306a\u6307\u91dd \u3092 \u4e0e \u3048\u3066 \u3044 \u308b\u3002 \u3059 \u306a \u308f \u3061(5)\u5f0f \u306b\u793a \u3057\u305f \u63a8\u529b \u5b9a \u6570Kj\u306f \u30b3\u30a4 \u30eb \u306e\u5dfb\u6570N\u306b \u6bd4 \u4f8b \u3059 \u308b\u305f \u3081,\u9285 \u7dda \u306e\u76f4 \u5f84d\u3092 \u9078 \u5b9a \u3057\u3066 \u81ea\n\u7531 \u306b\u63a8 \u529b \u5b9a \u6570 \u3092\u8a2d \u8a08 \u3067 \u304d\u308b \u3053 \u3068 \u3092\u793a \u3057 \u3066 \u3044 \u308b\u3002 \u3057\u304b \u3057,\n(12)\u5f0f \u306b \u793a \u3057\u305f\u63a8 \u529b/\u5165 \u529b \u6bd4F/P\u306f,\u9285 \u7dda \u306e \u76f4 \u5f84 \u306b\u4f9d \u5b58 \u3059 \u308b \u5360\u7a4d \u7387 \u03b6,\u30b3 \u30a4 \u30eb \u306b\u4f5c \u7528 \u3059 \u308b\u78c1 \u675f \u5bc6 \u5ea6B\u3068 \u30b3 \u30a4\u30eb\u306e\n\u4f53 \u7a4d \u8107 \u304a \u3088\u3073LDM\u304c \u767a \u751f \u3059 \u308b\u9759\u63a8 \u529bF\u306b \u3088 \u3063\u3066\u6c7a\u5b9a \u3055 \u308c \u308b \u3053 \u3068\u3092\u793a \u3057\u3066 \u304a \u308a,\u30b3 \u30a4\u30eb \u306e \u5dfb \u6570N\u306b \u306f\u4f9d \u5b58 \u3057\u3066 \u306a \u3044\u3002 \u3059 \u306a\u308f \u3061,\u9285 \u7dda \u306e\u76f4 \u5f84 \u3092\u5909 \u3048 \u3066 \u30b3\u30a4\u30eb \u306e\u5dfb \u6570 \u3092\u5909\u5316 \u3055\n\u305b \u3066 \u3082\u5360\u7a4d \u7387 \u304c\u4e00 \u5b9a \u306e\u5834 \u5408 \u306b \u306f\u63a8 \u529b/\u5165 \u529b \u6bd4 \u306e \u5411\u4e0a \u306f\u671f\u5f85\n446 T. lEE Japan, Vol. 118-D, No.4, '98" + ] + }, + { + "image_filename": "designv8_17_0002722_download_58477_60372-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002722_download_58477_60372-Figure3-1.png", + "caption": "Figure 3: Third angle orthographical projection", + "texts": [], + "surrounding_texts": [ + "The result obtained from the experimentation of the cylinder block on the engine test bed is shown on Table 4. Vol.12, No.1, 2022 The developed mathematical model from the application of the multiple linear regression technique is shown in eqaution (9) \ud835\udc4c = 1.993 \u2212 0.07583\ud835\udc34 + 0.03375\ud835\udc35 + 0.0225\ud835\udc36 (9) Where Y=Specific Fuel Consumption (SFC) in kg/kwh A=injection pressure in Mpa B=Load in N C= consumption ratio The optimal levels of the input parameters obtained from the Taguchi Design and Signal-tonoise are shown on Table 5 and Figure 4 respectively. The predicted value for the response parameter (Specific fuel consumption) is 0.680 kg/Kwh. The developed mathematical model was found to be statistically adequate with a p-value lesser than 0.05 using a significant level of 0.05. Also, the 3 input parameters were found to be significant as a result of them having a p-value that is less than 0.05 as shown on Table 6. Vol.12, No.1, 2022" + ] + }, + { + "image_filename": "designv8_17_0004583___lang_en_format_pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004583___lang_en_format_pdf-Figure8-1.png", + "caption": "Fig. 8. ME Dipole antenna attached to the CubeSat 6U chassis.", + "texts": [ + " 7 (b) shows the antenna\u2019s front-to-back-ratio (FBR), where the model shows an FBR greater than 20 dB difference between the right-hand circular polarization (RHCP) and left-hand circular polarization (LHCP) gains. which shows a low lower lobe pattern, as expected for a ME dipole antenna and the radiation efficiency was simulated, obtaining an efficiency greater than 90%. Brazilian Microwave and Optoelectronics Society-SBMO received 28 Nov 2023; for review 15 Jan 2024; accepted 28 May 2024 Brazilian Society of Electromagnetism-SBMag \u00a9 2024 SBMO/SBMag ISSN 2179-1074 Fig. 8 shows the ME dipole antenna attached to the CubeSat 6U (20mm \u00d7 10mm \u00d7 30mm). We are interested in showing the performance of the antenna considering the entire operating structure, in this case the chassis of this nanosatellite, which was modeled in aluminum and simulated in ANSYS HFSS. Fig. 9 (a) shows the radiation pattern obtained for 1.57 GHz, which corresponds to the central frequency of the GPS L1, Beidou B1 and Galileo E1 bands. It can be seen that the maximum gain obtained considering the chassis losses is 8" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001203_el-01058504_document-Figure5.14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001203_el-01058504_document-Figure5.14-1.png", + "caption": "Figure 5.14 Sectional view of the structure: Tw is the thickness of the metal wire, Lw is the distance between the metal wire and racetrack memory, Dw is the interval between the metal wire and racetrack memory.", + "texts": [ + " As the racetrack memory is a linear system, placing metal lines is easier for realization and more beneficial for the CHAPTER 5 DESIGN OPTIMIZATION FOR STT-MRAM AND PMA RACETRACK MEMORY 137 miniaturization. Nevertheless, it should be under some constraints: firstly, as the relatively high current (e.g. 15-20 mA) is required, we should use thick metal in the back-end integration process to pass through these currents so as to prevent the electromigration issues; secondly, the generation of magnetic field coherent to magnetization orientation of domains requires an interval between magnetic nanowire and metal wire. Figure 5.14 illustrates sectional view of the structure of racetrack memory with magnetic field assistance, we can deposit an insulator layer (e.g. MgO) to separate magnetic and metal wires. wT is the thickness of thick metal wire (160 nm in our design). wL and wD represent the distance and interval length between magnetic nanowire and metal wire ( wL is supposed to be equal to wD in the following analysis). According to Biot-Savart-Laplace law, the magnetic field will scale with the current if heating is not considered; meanwhile the distance has a great impact to the generation of magnetic field (see Figure 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000764_f_version_1633592417-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000764_f_version_1633592417-Figure1-1.png", + "caption": "Figure 1. Payload swing angle sensor [7]. (1.) Flexible elements. (2.) Strain gauges. (3.) Device holder mounted on the crane trolley. (4.) An intermediate member performing a spherical motion. (5.) The part of the device performing the movement according to the rope. (6.) Pulleys touching the rope. (7.) Crane rope.", + "texts": [ + " We know several technologies of additive production and each of them requires specific materials. These technologies are constantly evolving, and more of them are added. A basic overview of technologies is given in [25]. Another intention with the design was to optimize the mechanism in terms of shape, rigidity, and weight. DfAM and additive manufacturing allow the designer to use shapes obtained through topological optimization [26] or the Generative design method, which mimics nature\u2019s evolutionary approach to creating structures and objects. The device designed by us is presented in Figure 1. The aim with this solution was to construct a simple, robust, easy to use, and at the same time sufficiently accurate device for measuring the swing angle. That is, the device can be used as a measuring element in connection with feedback control. The original idea was to use a strain gauge, a component which allows for very small displacements to be measured. First, a simple experiment was performed on an embedded beam made by an additive thermoplastic manufacturing technology. A strain gauge was placed at the inlet where the bend is the largest", + " When moving the free end of the beam, the strain gauge connected to the transducer provided a voltage output proportional to the deflection of the end, which is proportional to the lengthening or shortening of the beam surface. If one end of the beam was to run parallel to the rope, and the free end of the beam was connected to the rope by means of a guide, the swing angle would correspond to a lengthening or shortening of the strain gauge. The described device is based on these considerations. The part marked 3 in Figure 1 is firmly connected to the crane cat. This is connected to part 4 by means of a pair of parallel elastic elements 1, on which the strain gauges 2 are placed. Part 4 serves to keep the elastic elements 1 at the same height and to bend each pair only along one of the axes. x or y. Therefore, it is a sort of boundary. Part 5 is connected directly to the rope of the crane 7 by means of pulleys 6. The device designed in this way ultimately represents the attachment of part 5 at one point. Part 5 thus performs a spherical movement in connection with the end of the rope", + " x ( \u03d5x, \u03d5y ) = l sin \u03d5x cos \u03d5y y ( \u03d5x, \u03d5y ) = l sin \u03d5y cos \u03d5x (1) Assuming that the angles \u03d5x and \u03d5y are small, the relations (1) are simplified to an approximate shape (2). x(\u03d5x) = l\u03d5x y ( \u03d5y ) = l\u03d5y (2) The entire functional prototype of this device was created using additive manufacturing technologies, thus it was printed on a conventional 3D printer. This approach makes it possible to produce components that cannot be produced in any other way. The parts were very strong and the equipment showed no signs or excessive wear during the tests. A more interesting version of the device is in Figure 3. The shape of the device of Figure 1 has been optimized using the Generative Design module so the voltage is the same at each point of the device. Of course, except for the flexible elements with strain gauges, which are the sensitive part of the sensor. At first glance, a highly peculiar shape is, of course, unproducible by conventional chip machining. However, this is not a problem with additive manufacturing technologies. The second prototype of the device was made the same as this. For more information on optimizing the design of this device using the generative design module, see [8]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001203_el-01058504_document-Figure2.17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001203_el-01058504_document-Figure2.17-1.png", + "caption": "Figure 2.17 (a) Example of all spin logic circuits: the output is determined by the spin currents injected into the channel by the inputs. (b) Schematic of a neuromorphic with memristor synapses in a crossbar configuration.", + "texts": [ + " In 2008, teams from NEC and Hitachi/Tohoku University presented the prototypes of a non-volatile latch and a STT-MRAM based magnetic full adder [133-134]. In 2010, the HP lab presented an advanced scheme in which logical computing was implemented in a unit consisting of only two memristors [135]. All spin logic (ASL) circuits [137] employ nanomagnets as digital spin capacitors to store data information and spin currents (through STT) to communicate, realizing logic gates based on a spin majority evaluation. Figure 2.17(a) shows an example to demonstrate the possible layout for constructing cascadable ASL logic gates. The magnetization directions of the nanomagnets can be switched between the stable states if enough torque is exerted on them. Information stored in the input magnet is used to generate a spin current that can be routed along a spin-coherent channel to the output magnet, determining its state based on the STT effect. The key features of ASL circuits are their compactness and completeness, because no MOS transistor is needed for the logic operations and all the logic functions can be constructed with a minimal set of Boolean logic gates. With such a design, a full spin computing system can be expected with extremely low switching power. However this is still a theoretical prospect currently and many issues, such as reliability and clock control, remain unresolved. Spintronics may also allow the emergence of radically novel computing paradigms in electronics. In particular, for several years, researchers have been designing \u201cneuromorphic\u201d circuits that work analogously to the brain (see Figure 2.17(b)) [138]. Such circuits could allow a form of intelligent and ultra-low power computing (the brain can solve problems inaccessible to supercomputers with only 20 W). However, as fabricating neuromorphic system with pure CMOS has severe limitations, they require massive and ideally non-volatile memory for their \u201csynapses\u201d. Several groups have thus proposed to use spintronic memristors as synapses [139], in CHAPTER 2 STATE OF THE ART 40 particular relying on DW motion [140]. The associated computing units (neurons) may be realized by CMOS, but in some situations may also be implemented by multiple input spin valves" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002849_tation-pdf-url_69105-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002849_tation-pdf-url_69105-Figure4-1.png", + "caption": "Figure 4. Magnetic flux distribution and flux density in the switched reluctance machine for the unaligned rotor position.", + "texts": [], + "surrounding_texts": [ + "DOI: http://dx.doi.org/10.5772/intechopen.89097 Using the same reasoning as above; Eq. (2) will apply for the unaligned rotor position as well as for the aligned case as shown in Figures 4 and 5. In fact Eq. (2) is used to compute the flux-linkage for any rotor angular position with respect to the stationary stator. One further outcome we are able to accomplish\u2014in addition to varying the rotor angular position to compute the flux-linkage for that rotor position\u2014is to vary the phase current that is being circulated in the concentrated winding of the stator pole. Therefore, if we increase the current from zero to its full rated peak value (see Table 1), for each of the rotor positions from the fully aligned to the fully unaligned, in steps of 1 mechanical degree, the complete flux-linkage map of the 18/12 SR machine will result, as plotted in Figure 6. Some highly notable observations of Figure 6a are that for the aligned rotor position, the flux-linkage builds up very quickly for the range of currents, after which it levels off considerably; this occurs in the region of 80 (amps) called the magnetic saturation point. The unaligned rotor position flux-linkage is fairly linear Modeling and Control of Switched Reluctance Machines aligned position. The intermediate rotor position flux-linkage curves, generally speaking, become highly nonlinear as the rotor tends toward the fully aligned position. If the flux-linkage curves with respect to the rotor position are examined taking the phase current as a parameter, as in Figure 6b, it may be seen that linearity is not present at all, and for a given current value, the flux-linkage value will vary with respect to all rotor positions from the fully unaligned to the fully aligned. This is true irrespective of the rotor rotation in clockwise or counterclockwise direction, as in Figure 6b. The torque production of the SR machine can be described in terms of the fluxlinkage map shown in Figure 6a. If we were to consider only the fully aligned and unaligned rotor position flux-linkage curves, as in Figure 7, then it would follow that as the rotor tends toward the fully aligned position, the current build-up in the phase winding would increase the stored magnetic field energy Wf. The phase current would then follow the same profile as in Figure 3, yet this time it is shown with respect to the flux-linkage curves in Figure 7 (red dashed). As can be seen from the graphical representation, the magnetic co-energy W0 is represented by the area bound by the aligned and the unaligned flux-linkage curves and therefore is given by Eq. (3) in terms of the aligned flux-linkage: W 0 \u00bc \u00f0i 0 \u03a8di\u00a0\u00f0Joules\u00de (3) Thus, generally, if the magnetic field co-energy is created as a result of the rotor moving from the unaligned to the aligned position, while the phase current is kept constant, the torque generated,T, can be computed as in Eq. (4): T \u00bc \u2202W 0 \u2202\u03b8 i\u00bcconstant N m\u00f0 \u00de (4)" + ] + }, + { + "image_filename": "designv8_17_0001991_r.asee.org_33447.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001991_r.asee.org_33447.pdf-Figure3-1.png", + "caption": "Figure 3. Top-down assembly of forearm, wrist and hand", + "texts": [ + " Therefore, the ability to add custom geometry to the base design will enable highly customized, fully functional solutions for almost any user. Finding users who would benefit from these devices requires engaging with the local community. Reaching out to local elementary schools has been a primary approach. Children, since they are continually growing, often can\u2019t afford to get a new prosthetic every time they grow. Thus, a customizable, yet affordable, solution is very beneficial. Results After many hours of learning, investigation, and effort, the design shown in Figure 3 was produced in SolidWorks. The design, inspired by Unlimbited\u2019s foundational work, currently can be configured with an arm length of 250 to 300 mm, an elbow width of 30 to 100+ mm, a hand length of 135 to 235 mm and a wrist angle of -15\u00b0 to +5\u00b0. Customizing the CAD database takes less than three minutes once the end user size requirements have been determined. The designer simply opens the assembly, creates configurations, edits 4 global variables, and rebuilds the newly sized parts. After some final tweaks, the build and validation phases will begin" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000931_nf_efm2014_02064.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000931_nf_efm2014_02064.pdf-Figure6-1.png", + "caption": "Figure 6. FEM model of the heat exchanger distribution of pressure losses in the geometry of the heat convector during the liquid flow velocity 0.2 m s-1 at 23 \u00b0C.", + "texts": [], + "surrounding_texts": [ + "The numerical model for calculating the pressure loss of the heat convector was carried out in the finite element (FEM) Fluid Dynamics module of COMSOL Multiphysics. COMSOL Multiphysics is suitable for modeling various physical phenomena by electrostatics and electrokinetics through dynamic processes up to the fluid flow and compression of isotropic or anisotropic materials [9]. This software includes a number of tools designed to solve a wide range of problems that are described by partial differential equations as specifically in this case used Navier-Stokes equation (2). COMSOL was used to compute the implicit algorithm where at each time instants velocity gradually updated in time t with a time increment t + dt according to equation (3) as opposed to explicit algorithm that is suitable for other types of dynamic analyzes as said Petr#, Nov\u00e1k, Her\u00e1k and Simanjuntak [10-11]. tt i tt ii uuu \u0394+\u0394+ ++ \u2212= 11\u03b4 , (3) where tt iu \u0394+ is the vector of nodal displacement for the i-iteration in the time tt \u0394+ . The numerical model allows the modeling of the vector momentum distribution of the fluid flowing in the coil. The results affect the corresponding initial and boundary conditions that are particularly difficult due to the complicated geometry of the heat exchanger, through which flows the driving medium. The boundary conditions were defined the same way as with the real devices, for the selected observed temperature (12, 23, 40 and 60 \u00b0 C) and for the selected flow velocity. The input parameters of the numerical model for analysis of the pressure loss are shown in Table 1. The model itself was based on the modified 3D CAD data model of the heat exchanger with a real dimensional geometry. The suitable variant of the calculation depending on the size of the Reynolds number was chosen in the simulation. This is a laminar flow, turbulent flow with a low Re number called \"transitional region\" and turbulent flow. \u2022 The Reynolds number (4) where \u03b7 is the dynamic viscosity (1), N\u00b7s\u00b7m-\u00b2; \u03c1 is the density of the fluid, kg\u00b7m-3; D is the inner diameter of the round pipe and v is the mean velocity of the fluid, m\u00b7s-1. During the model simulation of process like this, problems arrise in the convergence of solutions. Sometimes the finite solution can despite very sophisticated procedures Gauss elimination iterate with unacceptable error. Therefore, it is necessary already when drawing up the model that there will be close to the real behavior. This suggests a suitable design adaptive finite element mesh that meets the criteria of flow, boundary and initial conditions, etc. These are a primary target in order to appropriate numbers of iterations already in the beginning of the calculation (Figure 2) to a sufficient degree for minimize the resulting residue defined by equation (5). The calculation is shown in Figure 2. and in Table 2. The resulting dependence of the convergence calculation, which is given by the expression, sizes residues and the number of iterations (linear or nonlinear). [ ] zkz n k c zfsdzzfia == \u2212 == 1 1 )(Re)( 2 1 \u03c0 , (5) where a-1 is rezidium of the function f (z) at the nodal point z0 and f(z) represents a function meromorphic Laurent series around the isolated singular point (node), and must pay (z0 & z). Res [f (z)] z = zk is called the rezidium of function f (z) in the k-th nodal point zk. 02064-p.3 When using the adaptive techniques, it may happen that even though the critical threshold will significantly soften, the stiffness matrix becomes badly definite. Therefore the use of the multi-network methods (multigrid method), which essentially combines a finite iterative method [12]. The error of the solution can be divided into singular (local) and global. Singular is the high frequency error that is not locally extensive, but can be reduced with the iterative process. Global lowfrequency error, has the nature of a smooth function and affects virtually all of the solutions in the areas. The finite element mesh was therefore created from 3D Solid tetrahedron (10-node elements) with the total numbers of degrees of freedom specified in the Table 2. For a sufficiently and accurate solution in geometrically complex areas (radius, knees), adaptive technique were developed in elements of 0.002 mm size. Detail of the proposed finite element mesh is shown in Figure 3. 02064-p.4" + ] + }, + { + "image_filename": "designv8_17_0001921_le_2017_4_art_03.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001921_le_2017_4_art_03.pdf-Figure4-1.png", + "caption": "Fig. 4. Distribution of plastic strain (a) and displacement (b) for stent", + "texts": [ + " Figure 2 presents stent model with applied forces and stent fixation. For this stent model, stresses, strain and displacement area were determined. 1. Distribution of reduced stresses - Figure 3 For the coronary stent model made of PtCr alloy with applied forces, distribution of stresses was varied. The maximal value of reduced stresses was observed at the end of the external wall in the locations where the was stent fixation. The maximal value of stresses was 29.86 MPa, whereas minimal stresses were around 1.533 MPa. 2. Distribution of plastic strains - Figure 4a The plastic strains generated during the strength test are permanent displacements which do not yield even after removing the load they were caused by. The biggest plastic strain was observed on the external stent walls, next to its fixation and accounted for 9.7%. 3. Distribution of displacements - Figure 4b Apart from distribution of stresses, strain and displacements were also observed for the stent made of platinum-chromium alloy. The highest value of displacement was 0.303 mm, wheras the smallest was 0 mm. The biggest displacement was located on the external stent walls, next to its fixation and force application the model. Statistical analysis performed using the finite element method allowed for the evaluation of stent strength. Furthermore, based on its value, the percentage foreshortening and relative narrowing caused by plastic strain was determined" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002204_00161-018-0660-8.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002204_00161-018-0660-8.pdf-Figure13-1.png", + "caption": "Fig. 13 \u201cOlivia\u201d Sports Arena, single lenticular girder, load cases\u2014load tests in 1969", + "texts": [ + " Since [61] manual does not provide information, a detailed study of element properties was undertaken revealing that these are Timoshenko-type beam elements accounting for shear effect and axis eccentricity, \u2022 632 2\u2014node C0 spatial truss-cable elements with no-tension feature. In all calculations, the value of Young\u2019s modulus was assumed as 205 GPa and Poisson\u2019s ratio 0.3. The following load cases were studied: \u2022 gravity load, \u2022 pre-tension force 1030 kN in cables of a single-channel bar in the lower cord, \u2022 pre-tension force 1.96 kN of X bracing, \u2022 concentrated forces 5 kN on the upper cord at every node connecting the chord and vertical post along the total chord length (Fig. 13, case A), \u2022 as above, however along half of the total chord length (Fig. 13, case B). All calculations were carried out in geometrically nonlinear range. The obtained results are presented in Fig. 14, where comparison is given to the original in situ measurements taken in 1969. The curves show a good qualitative agreement. The quantitative assessment revealed the 9% discrepancy between in situ and numerical results which is also fine. Table 3 presents some representative values to support this observation. In the next step, the natural frequency extraction was performed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure2.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure2.13-1.png", + "caption": "Figure 2.13: Multilayer human body model in CST", + "texts": [ + " Therefore, in our analysis, as the propagation is confined in the skin, we will consider three different skin thicknesses to study its effect on the propagation. The most important propagation features of the human body channel are the dispersion and attenuation in the direction of propagation, which can be easily deduced from our TRM codes. To validate our TRM calculations, numerical simulations were performed using CST Microwave Studior for selected frequencies. A similar planar multilayer human body structure was established in the simulation and a waveguide port was set to excite the propagation modes into the model, as shown in figure 2.13. In this demonstration model, the skin thickness is configured to be 1 mm and the fat is 13 mm. Periodic boundary conditions were applied on the two xz-surfaces to simulate the infinite y-axis dimension. The other boundaries were set as absorbent conditions (PML), which can practically simulate the semi-infinite dimension feature of the air and muscle layers. The muscle thickness was chosen as 1 mm to reduce the undesirable modes found in CST and the air thickness was chosen as 3 mm. It should be noted that the heights of the muscle and air layers should be large enough so that the absorbent condition does not disturb the modes under investigation exhibiting an exponential decay within these layers", + " Ignoring the dielectric loss in the tissues allows us to observe more easily the field distribution feature and the essential confinement behavior of the propagating wave. To do so, for the previous 1 mm-thickness skin and 13 mm-thickness fat human body model (figure 2.15(b)), the electromagnetic field distributions of the fundamental TE mode and the TM(1) mode are calculated at 60 GHz in Matlab using equations (2-79) and (2-82), and the linearly plotted results are shown in figure 2.22 and figure 2.23, respectively. For comparison, the CST port mode calculations performed with the frequency solver (figure 2.13) for the respective modes are shown in the captions of figures 2.22 and 2.23. As can be observed, the field distributions deduced from our code have the same form as the CST port mode distribution. It can also be seen that the TE mode field is slightly better confined in the skin layer. For the TM mode, more penetration in fat and less penetration in air of the magnetic field can be observed (figure 2.23). To analyze the attenuation along the direction of propagation, it is more convenient to consider the power distribution" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004590_O201319947248395.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004590_O201319947248395.pdf-Figure5-1.png", + "caption": "Fig. 5. Cloak problem with mesh schematics: (a) physical and (b) virtual domains.", + "texts": [ + " The method we propose to relate the material parameters in the two domains is very general and is applicable to the case where the two geometries have arbitrary shapes, and are not simply related to each other by a scale factor, as we will discuss later in Section III. To derive the material properties of the physical domain, from the assumed parameters in the virtual domain (\u03b50, \u03bc0 for free-space in this example), we turn to Fig. 4 and Eq. (2). The next step, which is key to the TO-based algorithm, is to impose the condition that the fields (E1, H1) in the physical domain be \u201cidentical\u201d to those in the virtual domain, i.e., (E2, H2). To facilitate the imposition of this condition, we now discretize the two domains, as shown in Fig. 5, by setting up a mesh to discretize the regions 2 and 3 in both domains. We take advantage of the circular symmetry of the geometries in the two domains, and of the fact that the geometry of the PEC cylinder, located in region-2 in the virtual domain is simply a scaled-down version of the one in the physical domain (region-1), and note that this transformation preserves the azimuthal symmetries of the two domains. In view of this, we use the same angular increments of \u0394\u03d5 in both domains, although we follow a different strategy in the radial direction, along which we impose the following three conditions: (i) The number of radial cells be identical in region-2 of the domains, which spans the radial distance b 0 if test article is longitudinally stable It is worth to remark that the CG position and excursion shown in Figure 4 are a desired result obtained with a proper wing longitudinal position. The excursion is typical of canard or three-lifting surface configuration, while it is largely unusual for the classical wing and aft tail configurations, where the typical CG excursion is within 15\u201330% [31]. The design loop 1 configuration has been shown in Figure 1. Wind tunnel data highlighted unsatisfactory static stability characteristics, leading to a design review of the canard position and of the empennage layout. In fact, the interaction of the wing and canard wakes was such to provide a neutral longitudinal stability at low lift coefficients, with a tendency to instability at moderate lift coefficients. To keep the aircraft naturally stable in pitch, it was decided to increase the vertical stagger between the canard and the wing. By design constraint imposed by the IRON project leader, the only way to purse this was to shift the canard as high as possible" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002838_f_version_1679473059-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002838_f_version_1679473059-Figure13-1.png", + "caption": "Figure 13. Analysis of radial interference.", + "texts": [ + " Therefore, the radial interference is a constraint that must be satisfied when the gear pair is machined by the generating method, but not when the gear pair is designed. In the coordinate Sg, the conjugate tooth profiles on the right are still taken as an example. The initial meshing position is located at pitch point P. At this time, the included angles between the radius of the tooth apexes B and C\u2032 of the gear pair and the axis Yg are \u03c31 and \u03c32, respectively. The following can be obtained from the geometric relationship in Figure 13: d1 = ra1 sin \u03c31 = ra1 sin(\u03d51 \u2212 \u03c41) (73) d2 = ra2 sin \u03c32 = ra2 sin(\u03d52 + \u03c42) (74) where d1 and d2 are the distance from the apexes B and C\u2032 of the gear pair to the axis Yg, respectively. \u03c41 and \u03c42 are the included angles between the radius on the pitch circles and the radius of the apexes B and C\u2032 at the tooth profile on the same side, respectively. As can be seen from Figure 2, the coordinate of the intersection L of the reference circle of the external gear and the straight-line segment BC is (xL = r1 sin(\u03b8/2), yL = r1 cos(\u03b8/2)); combined with Equations (7) and (11), the length of the straight-line segment BL is as follows: dBL = \u221a (xB \u2212 xL) 2 + (yB \u2212 yL) 2 (75) In \u2206BO1L, the following is obtained according to the law of cosines: \u03c41 = arccos ( r2 a1 + r2 1 \u2212 d2 BL 2ra1r1 ) (76) Since the conjugate tooth profile of the internal gear ring is an irregular curve, the point coordinates on the tooth profile cannot be directly solved through geometric relationships", + " Based on the mathematical model of the tooth profile of the internal gear ring in Section 2.3, MATLAB\u00ae programming is used to solve the coordinates of the intersections M and C\u2032 of the conjugate tooth profile of the internal gear ring with its reference circle and addendum circle, and then the length of the straight-line segment MC\u2032 is as follows: dMC\u2032 = \u221a (xM \u2212 xC\u2032) 2 + (yM \u2212 yC\u2032) 2 (77) In \u2206C\u2032O2M, the following is obtained according to the law of cosines: \u03c42 = arccos ( r2 a2 + r2 2 \u2212 d2 MC\u2032 2ra2r2 ) (78) In Figure 13, when d1 < d2, the radial interference of the gear pair will occur at the angle \u03d51; on the contrary, when d1 \u2265 d2, the radial interference of the gear pair will not occur. Thus, the constraint that there is no radial interference of the conjugated straight-line internal gear pair can be written in the following form: G2(m, z1, z2, \u03b2, ks, h\u2217a1, h\u2217a2, \u03d51) = d1 \u2212 d2 \u2265 0 (79) where G2 is the decision function of radial interference. A set of design parameters used in the gear pump in Table 3 is taken as an example" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.28-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.28-1.png", + "caption": "Figure 1.28. Layout of a trailing link suspension to achieve one-axis velocity specification [12].", + "texts": [ + " The vertical component of the wheel angular velocity is given directly as the parameter kinematic toe change (KTC, radians per millimeter), Figure 1.27. All of these wheel-motion characteristics correlate to the vehicle-level targets. 26 27 Gerrard considers two cases of the velocity specification. In the first case, the velocity of the chosen point is perpendicular to the angular velocity. Consequently, the motion can be considered as the result of instantaneous rotation about an axis. Gerrard shows how to orient links and locate joints to achieve this velocity specification. For example, a trailing link suspension is shown in Figure 1.28. In the second velocity specification case, the velocity is a general rigid body velocity, which is often interpreted as the result of instantaneous rotation about a screw axis. In this second case, Gerrard finds it more useful to consider this velocity as the result of two instantaneous rotation axes that are interrelated by a gear link. Gerrard shows how to compute the two axes from the velocity specification and locate the gear link. The designer is able to select one of the axes at will, allowing it to be used as a steering axis, for example, and there is considerable flexibility in locating the gear link, making it suitable for use as the tie rod of a steering system, for example" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004026_v.org_pdf_2410.23640-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004026_v.org_pdf_2410.23640-Figure4-1.png", + "caption": "Fig. 4. Robot arm system for actual machine verification. (a) Outline of the robot arm system, (b) Suction-gripper-based end-effector.", + "texts": [ + " The algorithm employs vision-based inputs and visual prompts in an iterative process to refine its grasping actions, thereby providing an adaptable framework for suction-based robotic manipulation tasks. This adaptability ensures that the algorithm can be applied to diverse functions, thereby instilling confidence in its versatility. The primary goal was to develop a picking system that can handle a wide variety of items, including previously unseen objects. To validate and analyze the execution of our system, we focused on scenarios in a retail store. 1) Hardware Setup: An overview of the proposed system is shown in Fig. 4, which consists of a robot arm, suction gripper with an RGB-D camera, and serial controller. The details are as follows. Suction Gripper We employed a suction gripper, which is suitable for grasping objects with different shapes, materials, and surface properties, such as flat or curved surfaces and soft objects. The versatile gripping capabilities of the suction gripper were aligned with the objective of picking diverse items. Moreover, because the system selects actions from a discrete set of behaviors, the ability of the suction gripper to adapt to object shape and position variations without requiring precise alignment makes it particularly advantageous for our use case" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000437_-ijaefea20210709.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000437_-ijaefea20210709.pdf-Figure1-1.png", + "caption": "Figure 1. 3D model of sorting machine", + "texts": [], + "surrounding_texts": [ + "To select dc motor, we need to calculate total weight which need to slide from motor on frame, Factor considered for weight 1. Tray weight 2. Nut, bolts weight 3. Frame weight 1. Tray weight Tray weight from cad model = 1.3 kg x 3 Tray = 3.9 kg = 4kg round off (1) Assume 15 nuts, M6 \u00d7 15 nuts = 2.50gm \u00d7 15 = 37.5 grams M8 \u00d7 15 nuts =5.1 gm \u00d715 = 76.5 grams M10 \u00d7 15 nuts = 11.6 gm \u00d715 = 174 grams Overall Weight of Nuts, Total weight = 37.5 +76.5+174 Design and Analysis of Nut and Bolt Separating Machine 99 Int. J. of Analytical, Experimental and Finite Element Analysis www.rame.org.in Total weight of nut = 288 grams Total weight of Bolts (15 \u00d7 M6) + (15 \u00d7 M8) + (15 \u00d7 M10) bolts = 4 kg weight Frame weight; From cad by assign mild steel material density to frame = 7.8 kg. Overall Weight, Tray = 4kg round off. (2) Total weight of nut = 288 grams (3) Total weight of bolts= 4 kg weight (4) Frame = 7.8 kg (5) Overall Weight = A +B+C+D = 16 Kg Consider factor of safety and other factors = 16 + 4 kg extra wright 20 kg, Total weight with factor of safety = 20 kg Power = Force \u00d7 Velocity Here, assuming we are lifting the weight at a constant speed, the force applied by the motor is equal and opposite to the force applied by gravity, which is F=m g =20kg (10m/s2) = 200N Velocity V= 1m/60Sv =1m/60s Power P=F V =200N (1m/60s) =3.33watt From market we got below dc motor suitable for our project with 12V power. \u2022 Speed in rpm = 600 \u2022 Number of poles = 4 \u2022 Shaft Length = 30 mm \u2022 Motor Diameter = 28.5 mm \u2022 Gearbox Diameter = 37mm Now for calculating Working Frequency we use the formula, N = 120f /P Where, N= Rpm and P = No. of Poles. 600 = 120f/4 f = 20 Hz Hence our working frequency is 20 Hz. IV. FEA ANALYSIS Finite Element Analysis or FEA is the simulation of a physical phenomenon using a numerical mathematic technique referred to as the Finite Element Method, or FEM. This process is at the core of mechanical engineering, as well as a variety of other disciplines. It also is one of the key principles used in the development of simulation software. Engineers can use these FEM to reduce the number of physical prototypes and run virtual experiments to optimize their designs. Meshing is the process in which the continuous geometric space of an object is broken down into thousands or more of shapes to properly define the physical shape of the object. The more detailed a mesh is, the more accurate the 3D CAD model will be, allowing for high fidelity simulations. Details of meshing used \u2022 Element Size: 5.0 mm \u2022 Minimum Edge Length: 0.41406 mm 100 Int. J. of Analytical, Experimental and Finite Element Analysis \u2022 Nodes: 159258 \u2022 Elements: 73740 Figure 4. load apply Figure 5. Equivalent Stress TABLE1" + ] + }, + { + "image_filename": "designv8_17_0003777_._12,_No._2_5-14.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003777_._12,_No._2_5-14.pdf-Figure9-1.png", + "caption": "Fig. 9. 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Structurally changed spool: a) 3D-model; b) manufactured spool.\n\u0415\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u0456 \u0434\u043e\u0441\u043b\u0456\u0434\u0436\u0435\u043d\u043d\u044f \u0440\u0435\u0436\u0438\u043c\u0456\u0432 \u0440\u0443\u0445\u0443 \u043b\u0430\u043d\u043e\u043a \u0441\u0442\u0440\u0456\u043b\u043e\u0432\u043e\u0457 \u0441\u0438\u0441\u0442\u0435\u043c\u0438 \u043f\u0440\u043e\u0432\u043e\u0434\u0438\u043b\u0438\u0441\u044c \u043d\u0430 \u0432\u043b\u0430\u0441\u043d\u043e\u0440\u0443\u0447 \u0441\u043f\u0440\u043e\u0435\u043a\u0442\u043e\u0432\u0430\u043d\u0456\u0439 \u0442\u0430 \u0432\u0438\u0433\u043e\u0442\u043e\u0432\u043b\u0435\u043d\u0456\u0439 \u0435\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u0456\u0439 \u0443\u0441\u0442\u0430\u043d\u043e\u0432\u0446\u0456 \u043a\u0440\u0430\u043d\u0430-\u043c\u0430\u043d\u0456\u043f\u0443\u043b\u044f\u0442\u043e\u0440\u0430 \u0437 \u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u0438\u043c \u043f\u0440\u0438\u0432\u043e\u0434\u043e\u043c (\u0440\u0438\u0441. 8).\n\u0420\u0438\u0441. 8. \u0420\u043e\u0437\u0440\u043e\u0431\u043b\u0435\u043d\u0430 \u0435\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u0430 \u0443\u0441\u0442\u0430\u043d\u043e\u0432\u043a\u0430\n\u043a\u0440\u0430\u043d\u0430-\u043c\u0430\u043d\u0456\u043f\u0443\u043b\u044f\u0442\u043e\u0440\u0430.\nFig. 8. The experimental installation of the loader crane is developed.", + "\u0415\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u0456 \u0434\u043e\u0441\u043b\u0456\u0434\u0436\u0435\u043d\u043d\u044f \u043e\u0434\u043d\u043e\u0447\u0430\u0441\u043d\u043e\u0433\u043e \u043a\u0443\u0442\u043e\u0432\u043e\u0433\u043e \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u044f \u0441\u0442\u0440\u0456\u043b\u0438 \u0442\u0430 \u0440\u0443\u043a\u043e\u044f\u0442\u0456 \u043f\u0440\u043e\u0432\u043e\u0434\u0438\u043b\u0438\u0441\u044c \u0437\u0430 \u0442\u0430\u043a\u0438\u0445 \u043f\u043e\u0447\u0430\u0442\u043a\u043e\u0432\u0438\u0445 \u0443\u043c\u043e\u0432:\n- \u041f\u043e\u0447\u0430\u0442\u043e\u043a \u0440\u0443\u0445\u0443 \u0441\u0442\u0440\u0456\u043b\u0438 \u0442\u0430 \u0440\u0443\u043a\u043e\u044f\u0442\u0456 \u0432\u0456\u0434\u0431\u0443\u0432\u0430\u0432\u0441\u044f\n\u043e\u0434\u043d\u043e\u0447\u0430\u0441\u043d\u043e;\n- \u043f\u043e\u0447\u0430\u0442\u043e\u043a \u0440\u0443\u0445\u0443 \u0441\u0442\u0440\u0456\u043b\u0438 \u043f\u043e\u0447\u0438\u043d\u0430\u0432\u0441\u044f \u0456\u0437 \u043f\u043e\u043b\u043e\u0436\u0435\u043d\u043d\u044f \u0448\u0442\u043e\u043a\u0443 \u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u043e\u0433\u043e \u0446\u0438\u043b\u0456\u043d\u0434\u0440\u0443 \u043f\u0440\u0438\u0432\u043e\u0434\u0443 \u0441\u0442\u0440\u0456\u043b\u0438\n\u043cU 73,01 , \u0449\u043e \u0432\u0456\u0434\u043f\u043e\u0432\u0456\u0434\u0430\u0454 \u043a\u0443\u0442\u043e\u0432\u0456\u0439 \u043a\u043e\u043e\u0440\u0434\u0438\u043d\u0430\u0442\u0456 \u0440\u0430\u043401,0 ;\n- \u043f\u043e\u0447\u0430\u0442\u043e\u043a \u0440\u0443\u0445\u0443 \u0440\u0443\u043a\u043e\u044f\u0442\u0456 \u043f\u043e\u0447\u0438\u043d\u0430\u0432\u0441\u044f \u0456\u0437 \u043f\u043e\u043b\u043e\u0436\u0435\u043d\u043d\u044f \u0448\u0442\u043e\u043a\u0443 \u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u043e\u0433\u043e \u0446\u0438\u043b\u0456\u043d\u0434\u0440\u0443 \u043f\u0440\u0438\u0432\u043e\u0434\u0443 \u0440\u0443\u043a\u043e\u044f\u0442\u0456\n\u043cU 81,02 , \u0449\u043e \u0432\u0456\u0434\u043f\u043e\u0432\u0456\u0434\u0430\u0454 \u043a\u0443\u0442\u043e\u0432\u0456\u0439 \u043a\u043e\u043e\u0440\u0434\u0438\u043d\u0430\u0442\u0456 .79,0 \u0440\u0430\u0434\n\u041d\u0430 \u0440\u0438\u0441. 9 \u043d\u0430\u0432\u0435\u0434\u0435\u043d\u043e \u0442\u0430\u043a\u0456 \u043f\u043e\u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f: l1 \u2013 \u0434\u043e\u0432\u0436\u0438\u043d\u0430 \u0441\u0442\u0440\u0456\u043b\u0438; l2 \u2013 \u0434\u043e\u0432\u0436\u0438\u043d\u0430 \u0440\u0443\u043a\u043e\u044f\u0442\u0456; l3 \u2013 \u0434\u043e\u0432\u0436\u0438\u043d\u0430 \u0448\u0430\u0440\u043d\u0456\u0440\u043d\u043e\u0433\u043e \u043f\u0456\u0434\u0432\u0456\u0441\u0443; m1 \u2013 \u043c\u0430\u0441\u0430 \u0441\u0442\u0440\u0456\u043b\u0438; m2 \u2013 \u043c\u0430\u0441\u0430 \u0440\u0443\u043a\u043e\u044f\u0442\u0456; m3 \u2013 \u043c\u0430\u0441\u0430 \u0442\u0435\u043b\u0435\u0441\u043a\u043e\u043f\u0456\u0447\u043d\u043e\u0457 \u0441\u0435\u043a\u0446\u0456\u0457; m4 \u2013 \u043c\u0430\u0441\u0430 \u0432\u0430\u043d\u0442\u0430\u0436\u0443; 54321 ,,,, \u2013 \u043a\u0443\u0442\u0438, \u0449\u043e \u0443\u0442\u0432\u043e\u0440\u0435\u043d\u0456 \u0433\u0435\u043e\u043c\u0435\u0442\u0440\u0438\u0447\u043d\u0438\u043c\u0438 \u043f\u0430\u0440\u0430\u043c\u0435\u0442\u0440\u0430\u043c\u0438 \u0435\u043b\u0435\u043c\u0435\u043d\u0442\u0456\u0432 \u0441\u0442\u0440\u0456\u043b\u043e\u0432\u043e\u0457 \u0441\u0438\u0441\u0442\u0435\u043c\u0438 \u0442\u0430 \u043f\u0440\u0438\u0432\u043e\u0434\u043d\u0438\u0445 \u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u0438\u0445 \u0446\u0438\u043b\u0456\u043d\u0434\u0440\u0456\u0432 \u043a\u0440\u0430\u043d\u0430\u043c\u0430\u043d\u0456\u043f\u0443\u043b\u044f\u0442\u043e\u0440\u0430; \u04451, \u04452, \u04453, \u04454 \u2013 \u0433\u043e\u0440\u0438\u0437\u043e\u043d\u0442\u0430\u043b\u044c\u043d\u0456 \u043a\u043e\u043e\u0440\u0434\u0438\u043d\u0430\u0442\u0438 \u0446\u0435\u043d\u0442\u0440\u0456\u0432 \u043c\u0430\u0441 \u0441\u0442\u0440\u0456\u043b\u0438, \u0440\u0443\u043a\u043e\u044f\u0442\u0456, \u0442\u0435\u043b\u0435\u0441\u043a\u043e\u043f\u0456\u0447\u043d\u043e\u0457 \u0441\u0435\u043a\u0446\u0456\u0457 \u0442\u0430 \u0432\u0430\u043d\u0442\u0430\u0436\u0443; \u04431, \u04432, \u04433, \u04434 \u2013 \u0432\u0435\u0440\u0442\u0438\u043a\u0430\u043b\u044c\u043d\u0456 \u043a\u043e\u043e\u0440\u0434\u0438\u043d\u0430\u0442\u0438 \u0446\u0435\u043d\u0442\u0440\u0456\u0432 \u043c\u0430\u0441 \u0432\u0456\u0434\u043f\u043e\u0432\u0456\u0434\u043d\u043e \u0441\u0442\u0440\u0456\u043b\u0438, \u0440\u0443\u043a\u043e\u044f\u0442\u0456, \u0442\u0435\u043b\u0435\u0441\u043a\u043e\u043f\u0456\u0447\u043d\u043e\u0457 \u0441\u0435\u043a\u0446\u0456\u0457 \u0442\u0430 \u0432\u0430\u043d\u0442\u0430\u0436\u0443; ,, \u2013 \u043a\u0443\u0442\u043e\u0432\u0456 \u043a\u043e\u043e\u0440\u0434\u0438\u043d\u0430\u0442\u0438 \u043f\u043e\u043b\u043e\u0436\u0435\u043d\u043d\u044f\n\u0441\u0442\u0440\u0456\u043b\u0438, \u0440\u0443\u043a\u043e\u044f\u0442\u0456 \u0442\u0430 \u0432\u0430\u043d\u0442\u0430\u0436\u0443; U3 \u2013 \u043b\u0456\u043d\u0456\u0439\u043d\u0430 \u043a\u043e\u043e\u0440\u0434\u0438\u043d\u0430\u0442\u0430 \u043f\u043e\u043b\u043e\u0436\u0435\u043d\u043d\u044f \u0442\u0435\u043b\u0435\u0441\u043a\u043e\u043f\u0456\u0447\u043d\u043e\u0457 \u0441\u0435\u043a\u0446\u0456\u0457.\n\u041e\u0442\u0440\u0438\u043c\u0430\u043d\u0456 \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0438 \u0435\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u043e\u0433\u043e \u0434\u043e\u0441\u043b\u0456\u0434\u0436\u0435\u043d\u043d\u044f \u0440\u0435\u0436\u0438\u043c\u0456\u0432 \u0440\u0443\u0445\u0443 \u0441\u0442\u0440\u0456\u043b\u043e\u0432\u043e\u0457 \u0441\u0438\u0441\u0442\u0435\u043c\u0438 \u043f\u0440\u0438 \u043f\u043e\u0454\u0434\u043d\u0430\u043d\u043d\u0456 \u043e\u0434\u043d\u043e\u0447\u0430\u0441\u043d\u043e\u0433\u043e \u043a\u0443\u0442\u043e\u0432\u043e\u0433\u043e \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u044f \u0441\u0442\u0440\u0456\u043b\u0438\n\u0442\u0430 \u0440\u0443\u043a\u043e\u044f\u0442\u0456 \u0437 \u0432\u0438\u043a\u043e\u0440\u0438\u0441\u0442\u0430\u043d\u043d\u044f\u043c \u0431\u0430\u0437\u043e\u0432\u043e\u0433\u043e \u0442\u0430 \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u043e\u0433\u043e \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0456\u0432 \u043d\u0430\u0432\u0435\u0434\u0435\u043d\u043e \u0432 \u0433\u0440\u0430\u0444\u0456\u0447\u043d\u043e\u043c\u0443 \u0432\u0438\u0433\u043b\u044f\u0434\u0456 \u043d\u0430 \u0440\u0438\u0441. 11 \u2013 \u0440\u0438\u0441. 16.\n\u0430)\n\u0431)\n\u0420\u0438\u0441. 10. \u0413\u0440\u0430\u0444\u0456\u043a \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u044f\u043a\u0435 \u0440\u043e\u0437\u0432\u0438\u0432\u0430\u0454 \u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u0438\u0439 \u0446\u0438\u043b\u0456\u043d\u0434\u0440 \u043f\u0440\u0438\u0432\u043e\u0434\u0443 \u0441\u0442\u0440\u0456\u043b\u0438: \u0430) \u0431\u0430\u0437\u043e\u0432\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a; \u0431) \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a.\nFig. 10. The schedule of effort which develops the hydraulic cylinder of the drive of the boom: a) a factory spool; b) structurally changed spool.\n\u0410\u043d\u0430\u043b\u0456\u0437\u0443\u044e\u0447\u0438 \u0433\u0440\u0430\u0444\u0456\u043a\u0438 \u0437\u0443\u0441\u0438\u043b\u043b\u044f (\u0440\u0438\u0441. 10 \u0430), \u0432\u0438\u0434\u043d\u043e, \u0449\u043e \u043d\u0430 \u043f\u043e\u0447\u0430\u0442\u043a\u0443 \u0440\u0443\u0445\u0443 \u0441\u0442\u0440\u0456\u043b\u0438 \u0456\u0437 \u0432\u0438\u043a\u043e\u0440\u0438\u0441\u0442\u0430\u043d\u043d\u044f\u043c \u0431\u0430\u0437\u043e\u0432\u0438\u0445 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0456\u0432 \u0432\u0438\u043d\u0438\u043a\u0430\u0454 \u043c\u0438\u0442\u0442\u0454\u0432\u0435 \u0437\u0440\u043e\u0441\u0442\u0430\u043d\u043d\u044f \u0432\u0456\u0434\u043f\u043e\u0432\u0456\u0434\u043d\u043e\n\u0437\u0443\u0441\u0438\u043b\u043b\u044f, \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u044f\u043a\u043e\u0433\u043e \u0440\u0456\u0432\u043d\u0435 311491 F \u041d. \u041f\u0440\u0438 \u043f\u043e\u0434\u0430\u043b\u044c\u0448\u043e\u043c\u0443 \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u0456 \u0441\u043f\u043e\u0441\u0442\u0435\u0440\u0456\u0433\u0430\u044e\u0442\u044c\u0441\u044f \u043a\u043e\u043b\u0438\u0432\u0430\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0437\u0430\u0442\u0443\u0445\u0430\u044e\u0447\u043e\u0433\u043e \u0445\u0430\u0440\u0430\u043a\u0442\u0435\u0440\u0443, \u0440\u043e\u0437\u043c\u0430\u0445 \u044f\u043a\u043e\u0433\u043e\n\u0441\u0442\u0430\u043d\u043e\u0432\u0438\u0442\u044c 51241 F \u041d, \u043f\u0440\u043e\u0442\u044f\u0433\u043e\u043c 2,5 \u0441.\n\u041f\u0440\u0438 \u0433\u0430\u043b\u044c\u043c\u0443\u0432\u0430\u043d\u043d\u0456 \u0440\u043e\u0437\u043c\u0430\u0445 \u043a\u043e\u043b\u0438\u0432\u0430\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f\n\u0441\u0442\u0430\u043d\u043e\u0432\u0438\u0442\u044c: 55261 F \u041d, \u043f\u0440\u043e\u0442\u044f\u0433\u043e\u043c 4 \u0441. \u041f\u0440\u0438 \u0433\u0430\u043b\u044c\u043c\u0443\u0432\u0430\u043d\u043d\u0456 \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u0440\u043e\u0437\u043c\u0430\u0445\u0443 \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u043d\u0430 7% \u0431\u0456\u043b\u044c\u0448\u0456 \u043d\u0456\u0436 \u043f\u0440\u0438 \u043f\u0443\u0441\u043a\u0443.\n\u0417\u0430 \u0443\u043c\u043e\u0432\u0438 \u0432\u0438\u043a\u043e\u0440\u0438\u0441\u0442\u0430\u043d\u043d\u044f\u043c \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0445 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0456\u0432 \u0437 \u0433\u0440\u0430\u0444\u0456\u043a\u0443 \u0437\u0443\u0441\u0438\u043b\u043b\u044f (\u0440\u0438\u0441. 10 \u0431) \u0432\u0438\u0434\u043d\u043e, \u0449\u043e \u043d\u0430 \u043f\u043e\u0447\u0430\u0442\u043a\u0443 \u0440\u0443\u0445\u0443 \u0441\u0442\u0440\u0456\u043b\u0438 \u0432\u0438\u043d\u0438\u043a\u0430\u0454 \u043c\u0438\u0442\u0442\u0454\u0432\u0435 \u0437\u0440\u043e\u0441\u0442\u0430\u043d\u043d\u044f\n\u0437\u0443\u0441\u0438\u043b\u043b\u044f, \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u044f\u043a\u043e\u0433\u043e \u0440\u0456\u0432\u043d\u0435 283851 F \u041d. \u041f\u0440\u0438 \u043f\u043e\u0434\u0430\u043b\u044c\u0448\u043e\u043c\u0443 \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u0456 \u0441\u043f\u043e\u0441\u0442\u0435\u0440\u0456\u0433\u0430\u044e\u0442\u044c\u0441\u044f \u043a\u043e\u043b\u0438\u0432\u0430\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0437\u0430\u0442\u0443\u0445\u0430\u044e\u0447\u043e\u0433\u043e \u0445\u0430\u0440\u0430\u043a\u0442\u0435\u0440\u0443, \u0440\u043e\u0437\u043c\u0430\u0445 \u044f\u043a\u043e\u0433\u043e\n\u0441\u0442\u0430\u043d\u043e\u0432\u0438\u0442\u044c 32651 F \u041d, \u043f\u0440\u043e\u0442\u044f\u0433\u043e\u043c 4 \u0441.\n\u041f\u0440\u0438 \u0433\u0430\u043b\u044c\u043c\u0443\u0432\u0430\u043d\u043d\u0456 \u0440\u043e\u0437\u043c\u0430\u0445 \u043a\u043e\u043b\u0438\u0432\u0430\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f\n\u0441\u0442\u0430\u043d\u043e\u0432\u0438\u0442\u044c: 47731 F \u041d, \u043f\u0440\u043e\u0442\u044f\u0433\u043e\u043c 4 \u0441. \u0422\u0430 \u0432\u0456\u0434\u043f\u043e\u0432\u0456\u0434\u043d\u043e \u043f\u0456\u0434 \u0447\u0430\u0441 \u0433\u0430\u043b\u044c\u043c\u0443\u0432\u0430\u043d\u043d\u044f \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u0440\u043e\u0437\u043c\u0430\u0445\u0443 \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u043d\u0430 32% \u0431\u0456\u043b\u044c\u0448\u0456 \u043d\u0456\u0436 \u043f\u0440\u0438 \u0441\u0442\u0430\u0440\u0442\u0456.\n\u041f\u0440\u0438 \u043f\u043e\u0440\u0456\u0432\u043d\u044f\u043d\u043d\u0456 \u043c\u0456\u0436 \u0441\u043e\u0431\u043e\u044e \u043e\u0431\u043e\u0445 \u0440\u0435\u0436\u0438\u043c\u0456\u0432 \u0440\u0443\u0445\u0443", + "\u0432\u0438\u0434\u043d\u043e, \u0449\u043e \u043f\u0440\u0438 \u0432\u0438\u043a\u043e\u0440\u0438\u0441\u0442\u0430\u043d\u043d\u0456 \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0445 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0456\u0432 \u043f\u0456\u043a\u043e\u0432\u0456 \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u044c \u043d\u0430 \u043f\u043e\u0447\u0430\u0442\u043a\u0443 \u0440\u0443\u0445\u0443 \u043c\u0435\u043d\u0448\u0456 \u043d\u0430 9%, \u0430 \u0440\u043e\u0437\u043c\u0430\u0445 \u0437\u043d\u0430\u0447\u0435\u043d\u044c \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0437\u043c\u0435\u043d\u0448\u0438\u0432\u0441\u044f \u043d\u0430 36%. \u041f\u0440\u0438 \u0433\u0430\u043b\u044c\u043c\u0443\u0432\u0430\u043d\u043d\u0456 \u0440\u043e\u0437\u043c\u0430\u0445 \u0437\u043d\u0430\u0447\u0435\u043d\u044c \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0437\u043c\u0435\u043d\u0448\u0438\u0432\u0441\u044f \u043d\u0430 14%.\n\u0430)\n\u0431)\n\u0420\u0438\u0441. 11. \u0413\u0440\u0430\u0444\u0456\u043a \u0437\u0443\u0441\u0438\u043b\u043b\u044f, \u044f\u043a\u0435 \u0440\u043e\u0437\u0432\u0438\u0432\u0430\u0454\n\u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u0438\u0439 \u0446\u0438\u043b\u0456\u043d\u0434\u0440 \u043f\u0440\u0438\u0432\u043e\u0434\u0443 \u0440\u0443\u043a\u043e\u044f\u0442\u0456: \u0430) \u0431\u0430\u0437\u043e\u0432\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a; \u0431) \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a.\nFig. 11. Graph of the force that develops the hydraulic cylinder of the drive of the jib: a) factory spool; b) structurally changed spool.\n\u0412 \u043f\u043e\u0447\u0430\u0442\u043a\u043e\u0432\u0438\u0439 \u043c\u043e\u043c\u0435\u043d\u0442 \u0440\u0443\u0445\u0443 \u0440\u0443\u043a\u043e\u044f\u0442\u0456 \u043f\u0440\u0438 \u0432\u0438\u043a\u043e\u0440\u0438\u0441\u0442\u0430\u043d\u043d\u0456 \u0431\u0430\u0437\u043e\u0432\u0438\u0445 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0456\u0432 \u0432\u0438\u043d\u0438\u043a\u0430\u0454 \u043c\u0438\u0442\u0442\u0454\u0432\u0435 \u0437\u0440\u043e\u0441\u0442\u0430\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f (\u0440\u0438\u0441. 11, \u0430), \u044f\u043a\u0435 \u043d\u0430\u0431\u0443\u0432\u0430\u0454 \u043f\u0456\u043a\u043e\u0432\u043e\u0433\u043e\n\u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f 122462 F \u041d. \u041d\u0430\u0434\u0430\u043b\u0456 \u043f\u0440\u0438 \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u0456 \u0440\u0443\u043a\u043e\u044f\u0442\u0456 \u043d\u043e\u043c\u0456\u043d\u0430\u043b\u044c\u043d\u0435 \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0441\u0442\u0430\u043d\u043e\u0432\u0438\u0442\u044c\n101742 F \u041d. \u0420\u0456\u0437\u043d\u0438\u0446\u044f \u043c\u0456\u0436 \u043f\u0456\u043a\u043e\u0432\u0438\u043c \u0442\u0430 \u043d\u043e\u043c\u0456\u043d\u0430\u043b\u044c\u043d\u0438\u043c\n\u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f\u043c \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0441\u043a\u043b\u0430\u0434\u0430\u0454 17%.\n\u041f\u0440\u043e\u0446\u0435\u0441 \u0433\u0430\u043b\u044c\u043c\u0443\u0432\u0430\u043d\u043d\u044f \u0432\u0456\u0434\u0431\u0443\u0432\u0430\u0454\u0442\u044c\u0441\u044f \u043c\u0438\u0442\u0442\u0454\u0432\u043e, \u043f\u0456\u0441\u043b\u044f \u0447\u043e\u0433\u043e \u0441\u043f\u043e\u0441\u0442\u0435\u0440\u0456\u0433\u0430\u044e\u0442\u044c\u0441\u044f \u044f\u0432\u043d\u043e \u0432\u0438\u0440\u0430\u0436\u0435\u043d\u0456 \u043a\u043e\u043b\u0438\u0432\u0430\u043d\u043d\u044f \u0432\u0430\u043d\u0442\u0430\u0436\u0443 (\u0440\u0438\u0441. 14, \u0430)\n\u041f\u0440\u0438 \u0432\u0438\u043a\u043e\u0440\u0438\u0441\u0442\u0430\u043d\u0456 \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0445 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0456\u0432 \u0437\u0440\u043e\u0441\u0442\u0430\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u043d\u0430 \u043f\u043e\u0447\u0430\u0442\u043a\u0443 \u0440\u0443\u0445\u0443 (\u0440\u0438\u0441. 11 \u0431) \u0432\u0456\u0434\u0431\u0443\u0432\u0430\u0454\u0442\u044c\u0441\u044f \u043f\u043b\u0430\u0432\u043d\u043e, \u043d\u0430\u0431\u0443\u0432\u0430\u044e\u0447\u0438 \u043f\u0456\u043a\u043e\u0432\u043e\u0433\u043e \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f\n131882 F \u041d. \u041d\u0430\u0434\u0430\u043b\u0456 \u043f\u0440\u0438 \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u0456 \u0440\u0443\u043a\u043e\u044f\u0442\u0456\n\u043d\u043e\u043c\u0456\u043d\u0430\u043b\u044c\u043d\u0435 \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0441\u043a\u043b\u0430\u0434\u0430\u0454 128112 F \u041d. \u0420\u0456\u0437\u043d\u0438\u0446\u044f \u043c\u0456\u0436 \u043f\u0456\u043a\u043e\u0432\u0438\u043c \u0442\u0430 \u043d\u043e\u043c\u0456\u043d\u0430\u043b\u044c\u043d\u0438\u043c \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f\u043c \u0437\u0443\u0441\u0438\u043b\u043b\u044f \u0441\u043a\u043b\u0430\u0434\u0430\u0454 3%. \u041f\u0440\u043e\u0446\u0435\u0441 \u0433\u0430\u043b\u044c\u043c\u0443\u0432\u0430\u043d\u043d\u044f \u0432\u0456\u0434\u0431\u0443\u0432\u0430\u0454\u0442\u044c\u0441\u044f \u043f\u043b\u0430\u0432\u043d\u043e, \u043f\u0456\u0441\u043b\u044f \u0447\u043e\u0433\u043e \u043c\u0430\u044e\u0442\u044c \u043c\u0456\u0441\u0446\u0435 \u0432\u0438\u0440\u0430\u0436\u0435\u043d\u0456 \u043d\u0435\u0437\u043d\u0430\u0447\u043d\u0456 \u043a\u043e\u043b\u0438\u0432\u0430\u043d\u043d\u044f \u0432\u0430\u043d\u0442\u0430\u0436\u0443 (\u0440\u0438\u0441. 14, \u0431)\n\u041f\u0440\u0438 \u043f\u043e\u0440\u0456\u0432\u043d\u044f\u043d\u043d\u0456 \u043c\u0456\u0436 \u0441\u043e\u0431\u043e\u044e \u043e\u0431\u043e\u0445 \u0440\u0435\u0436\u0438\u043c\u0456\u0432 \u0440\u0443\u0445\u0443 \u0432\u0438\u0434\u043d\u043e, \u0449\u043e \u043f\u0440\u0438 \u0432\u0438\u043a\u043e\u0440\u0438\u0441\u0442\u0430\u043d\u043d\u0456 \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0445 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0456\u0432 \u043f\u0456\u043a\u043e\u0432\u0456 \u0437\u043d\u0430\u0447\u0435\u043d\u043d\u044f \u0437\u0443\u0441\u0438\u043b\u044c \u043d\u0430 \u043f\u043e\u0447\u0430\u0442\u043a\u0443 \u0440\u0443\u0445\u0443 \u0437\u043c\u0435\u043d\u0448\u0438\u043b\u0438\u0441\u044c \u043d\u0430 82% \u0432 \u043f\u043e\u0440\u0456\u0432\u043d\u044f\u043d\u043d\u0456 \u0437 \u0431\u0430\u0437\u043e\u0432\u0438\u043c\u0438\n\u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a\u0430\u043c\u0438.\n\u0430)\n\u0431)\n\u0420\u0438\u0441. 12. \u0413\u0440\u0430\u0444\u0456\u043a \u0448\u0432\u0438\u0434\u043a\u043e\u0441\u0442\u0456 \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u044f \u0448\u0442\u043e\u043a\u0443 \u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u043e\u0433\u043e \u0446\u0438\u043b\u0456\u043d\u0434\u0440\u0430 \u043f\u0440\u0438\u0432\u043e\u0434\u0443 \u0441\u0442\u0440\u0456\u043b\u0438: \u0430) \u0431\u0430\u0437\u043e\u0432\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a; \u0431) \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a.\n\u0420\u0438\u0441. 13. \u0413\u0440\u0430\u0444\u0456\u043a \u0448\u0432\u0438\u0434\u043a\u043e\u0441\u0442\u0456 \u043f\u0435\u0440\u0435\u043c\u0456\u0449\u0435\u043d\u043d\u044f \u0448\u0442\u043e\u043a\u0443 \u0433\u0456\u0434\u0440\u0430\u0432\u043b\u0456\u0447\u043d\u043e\u0433\u043e \u0446\u0438\u043b\u0456\u043d\u0434\u0440\u0430 \u043f\u0440\u0438\u0432\u043e\u0434\u0443 \u0440\u0443\u043a\u043e\u044f\u0442\u0456: \u0430) \u0431\u0430\u0437\u043e\u0432\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a; \u0431) \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0442\u0438\u0432\u043d\u043e \u0437\u043c\u0456\u043d\u0435\u043d\u0438\u0439 \u0437\u043e\u043b\u043e\u0442\u043d\u0438\u043a.\nFig. 13. Graph of the speed of movement of the rod of the hydraulic cylinder of the drive of the jib: a) factory spool; b) structurally changed spool." + ] + }, + { + "image_filename": "designv8_17_0000209__titds2023_04004.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000209__titds2023_04004.pdf-Figure1-1.png", + "caption": "Fig. 1. Scheme of forces acting on the bogie of the transport device: 1 \u2013 driving wheels; 2 \u2013 bogie with an electric motor; 3 \u2013 electromagnet; 4 \u2013 ferromagnetic surface.", + "texts": [ + " It has been proven that the most effective is the structural arrangement of the transport device, which is a platform on which two wheel propulsors are pivotally fixed \u2013 bogies with an integrated electromagnet and an electric motor driving a pair of wheels. The purpose of the current study is to develop a computational scheme and mathematical models that allow to describe and analyze the effects of various geometric and power parameters on the conditions of movement of magnetic transport devices with a wheel propulsor on ferromagnetic surfaces with different orientations \u2013 horizontal, inclined, and vertical. Figure 1 shows a computational diagram of the interaction of a wheeled propulsor of a transport device with a ferromagnetic surface, the position of which relative to the horizon is determined by an angle of inclination that varies in the range from 0 to 180 degrees. Let us assume that the point of application of all forces coincides with the point O of hinging of the propulsor to the platform. We introduce the following designations: \ud835\udc39\ud835\udc39\ufffd \u2013 is the gravity of the transport device (transmitted through the hinge attachment of the bogie to the platform); \ud835\udc39\ud835\udc39\ufffd \u2013 is the reaction from the processing equipment (also transmitted through the hinge attachment); \ud835\udc39\ud835\udc39\ufffd \u2013 is the force of traction between the driving wheels of the bogie and the ferromagnetic surface; \ud835\udc39\ud835\udc39\ufffd \u2013 is the normal reaction from the ferromagnetic surface to the driving wheels; EF \u2013 is the force of attraction developed by the electromagnet. Consider the sum of forces relative to the axes X and Y (Figure 1). 0X ; 0sinsin WGT FFF ; (1) 0Y ; 0coscos WGE FFF , (2) where \ud835\udefc\ud835\udefc \u2013 is the angle of inclination of the ferromagnetic surface; \ud835\udefd\ud835\udefd \u2013 is the angle that determines the direction of the reaction from the processing equipment to the normal of the ferromagnetic surface. on the ceiling surface; \ud835\udefc\ud835\udefc =90\u00ba \u2013 vertical surface; \ud835\udefc\ud835\udefc =180\u00ba \u2013 horizontal (floor) surface. As is known, the maximum traction \ud835\udc39\ud835\udc39\ufffd\ufffd\ufffd\ufffd in the contact zone is determined by the traction coefficient \ud835\udf13\ud835\udf13 and the pressure \ud835\udc39\ud835\udc39\ufffd of the wheels on the ferromagnetic surface: PT FF max , (3) Here \ud835\udc39\ud835\udc39\ufffd \ufffd \ud835\udc39\ud835\udc39\ufffd \ufffd \ud835\udc39\ud835\udc39\ufffd \ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50 \ud835\udefc\ud835\udefc \ufffd \ud835\udc39\ud835\udc39\ufffd \ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50\ud835\udc50 \ud835\udc50\ud835\udc50 \ufffd \ud835\udc39\ud835\udc39\ufffd" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.4-1.png", + "caption": "Figure B.4: Change in wind speed due to yaw rate (26)", + "texts": [ + "32) Yawing moment increment due to change in axial force from a pair of chord-wise strip elements is: ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) 1 1 1 1 1 2 1 1 2 2 y y y y y y A r l r rr l r l e y D L er l e y D L e e e D L e y n X y X y X y X y X X y U c dy C C y py U c dy C C y U U p C C y c dy \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b1 \u03b4 \u03b4 \u03b4 \u03b4 \u03b4 \u03b4 \u03b4 \u03c1 \u03b1 \u03b1 \u03c1 \u03b1 \u03c1 \u03b1 = \u2212 \u2212 = \u2212 + = \u2212 \u2212 = \u2212 = \u2212 = \u2212 (B.33) Then the total yawing moment due to roll rate is given by: ( ) ( ) ( ) 1 1 2 0 2 0 y y ee s A A e D L e y s s e D L y n n U p C C y c dy U p C C y c dy \u03b1 \u03b1 \u03b1 \u03b4 \u03c1 \u03b1 \u03c1 = = \u2212 \u2248 \u2212 \u222b \u222b \u222b (B.34) Referring to Figure B.4 below, let\u2019s consider a pair of symmetric chord-wise strip elements of the wing. Each pair of elements has the following characteristics: - Located at a distance y from the center line - Length of yc (chord at y ), width of y\u2202 - Lift coefficient of yL C and drag coefficient of yD C 105 When the aircraft experiences a positive yaw rate perturbation r , the right wing strip element will have a decrement in wind speed of ry , and the resultant wind speed at that element is: ( )r eV U ry= \u2212 (B.35) Lift and drag in steady state for each wing strip element were calculated in Equations (B" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003398_1_4_article-p313.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003398_1_4_article-p313.pdf-Figure5-1.png", + "caption": "Fig. 5. Test set-up a) grips of the MTS strength tester including the test assembly and alignment jig, b) cross-section of the test assembly 1 \u2013 cylindrical extrusion tube, 2 \u2013 base of the test assembly,", + "texts": [ + " The test apparatus was MTS strength tester, model Insight 50 kN which allowed recording the force and displacement values at 10 Hz frequency. 3 \u2013 piston, 4 \u2013 multi-channel die plate 5 \u2013 right-angle jig, 6 \u2013 grips of the strength tester, 7 \u2013 spacing ring, P \u2013 compressed dry ice snow (G\u00f3recki et al., 2013) DOI 10.1515/ama-2017-0048 acta mechanica et automatica, vol.11 no.4 (2017) Fig. 6. Dry ice snow compression curve in a multi-channel die extrusion system A special test assembly was used in the tests (Fig. 5). In or- der to minimize the measurement error due to eccentric mounting of the compression head, the grips were equipped with a right- angle jig to align the compression force in the direction perpendic- ular to the specimen cross-section 5. Before starting the test the compression chamber 1 was filled with crushed dry ice. Subsequently the piston 3 was inserted into the extrusion chamber 2. The test set-up was complete with the test assembly fitted in the grips of the strength tester. The scale was zeroed and the procedure was started by lowering the piston 3 downwards at a constant speed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003768_tation-pdf-url_12705-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003768_tation-pdf-url_12705-Figure5-1.png", + "caption": "Fig. 5. Residual pressure for min clearance", + "texts": [], + "surrounding_texts": [ + "The load transfer mechanism of joints equipped with fasteners has been recognized for a long time as one of the main causes which affect both static resistance as well as fatigue life of joints; unfortunately, such components, which are often considered as very simple, exhibit such a complex behaviour that it is far from being deeply understood and only in recent times the coupling of experimental tests with numerical procedures has let researchers begin to obtain some knowledge about the effects which come from assuming one of the available designs. Starting from the very simple hypothesis about load transfer mechanisms which are used in the most common and easy cases, a real study of such joints has started just after Second World War, mainly because from those years onward the use of bolted or riveted sheets has been increasingly spreading and several formulae were developed with various means; also in those years the \u201cneutral line method\u201d was introduced to study the behaviour of the whole joint, with the consequence that the need of a sound evaluation of fasteners stiffness and contribution to the overall behaviour was strictly required. A wide spectrum of results and theories have appeared since then, each one with some peculiarities of its own and the analysis of bolted and riveted joints appears now as to be analysed by different methods. The requirement of a wide range of different studies is to be found in the large number of variables which can affect the response of such joints, among which we can quote, from a general but not exhaustive standpoint: \u2022 general parameters: geometry of the joint (single or several rows, simple- or double-lap joints, clamping length, fastener geometry); characteristics of the sheets (metallic, non metallic, degree of anisotropy, composition of laminae and stacking order for laminates); friction between sheets, interlaminar resistance between laminae, possible presence of adhesive; \u2022 parameters for bolted joints: geometry of heads and washers; assembly axial load; effective contact area between bolts and holes; fit of bolts in holes; \u2022 parameters for riveted joints: geometry of head and kind of fastener (solid, blind \u2013 or cherry \u2013 and self-piercing rivets, besides the many types now available); amplitude of clearance before assembly; mounting axial load; pressure effects after manufacture. From all above it follows that today a great interest is increasingly being devoted to the problem of load transfer in riveted joints, but that no exhaustive analysis has been carried out insofar: the many papers which deal with such studies, in fact, analyze peculiar aspects of such joints, and little efforts have been directed to the connection between riveting operation and response of the joint, especially with regard to the behaviour in presence of damage. Therefore, the activity which we are referring to dealt with modelling of the riveting operation, in order to define by numerical methods the influence of the assembly conditions and parameters on the residual stress state and to the effective compression zone between sheets; another aspect to be investigated was the detection of the relevant parameters of the previous operation to be taken into account in the analysis of the joint strength. As we wished to analyse the riveting operation and its consequences on the residual stresses between plates, the obvious choice was to use a dynamic explicit FEM code, namely Ls- Dyna\u00ae, whose capabilities make it most valuable to model high-speed transients without much time consumption. www.intechopen.com Numerical Simulations - Applications, Examples and Theory 288 www.intechopen.com Simulating the Response of Structures to Impulse Loadings 289 A finer mesh \u2013 with a 0.2 mm average length \u2013 was adopted to model the stem of the rivet (fig. 2) and those parts of the sheets which, around the hole and below the rivet head, are more interested by high stress gradients; a coarser mesh was then adopted for the other zones, as the rivet head and the parts of the sheets which are relatively far from the rivet. The whole model was composed, in the basic reference case, of 101,679-109,689 nodes and 92,416-100,096 brick elements, according to the requirements of single cases, which is quite a large number but also in that case runtimes were rather long, as they resulted to be around 9-10 hours on a common desktop; more complex cases were run on a single blade of an available cluster, equipped with 2 Xeon 3.84 GHz - 4 GB RAM - and of course comparatively shorter times were obtained. The main reason of such times is to be found in the very short time-step to be used for the solution, about 1.0E-08 s, because of the small edge length of the elements. The solid part of rivet and sheets were modelled following a material 3 from Ls-Dyna library, which is well suited to model isotropic and kinematic hardening plasticity, with the option of including strain rate effects; values were assigned with reference to 2024 aluminium alloy; the shells corresponding to the contact surfaces were then modelled with a material 9, which is the so-called \u201cnull material\u201d, in order to take into account the fact that those shells are not a part of the structure, but they are only needed to \u201csoften out\u201d contact conditions; for that material shells are completely by-passed in the element stiffness processing, but not in the mass processing, implying an added mass, and for that reason one has to manually assign penalty coefficients in the input file. Some calibration was required to choose the thickness of those elements, looking for a compromise between the influence of added mass \u2013 which results from too large a thickness \u2013 and the negative effect with regard to contact, which comes in presence of a thickness too small, as in that case Ls-Dyna code doesn\u2019t always detect penetration. The punching part was modelled as a rigid material (mat. no. 20 from Ls-Dyna library); such a material is very cost effective, as they, too, are completely bypassed in element processing and no space is allocated for storing history variables; also, this material is usually adopted when dealing with tooling in a forming process, as the tool stiffness is some order larger than that of the piece under working. In any case, for contact reasons Ls-Dyna code expects to receive material constants, which were assumed to be about ten times those of steel. For what concerns the size of the rivet, it was assumed to be a 4.0 mm diameter rivet, with a stem at least 8.0 mm long; as required by the general standards, considering the tolerance range, the real diameter can vary between 3.94 and 4.04 mm, while the hole diameter is between 4.02 and 4.11 mm, resulting in diametral clearances ranging from 0.02 to 0.17 mm; three cases were then examined, corresponding to 0.02-0.08-0.17 mm clearances. The sheets, also made of aluminium alloy, were considered to range from 1.0 to 4.0 mm thickness, given the diameter of the rivet; the extension examined for the sheets was assumed to correspond to a half-pitch of the rivets and, in particular, it was assigned to be 12.5 mm; along the thickness, a variable number of elements could be assigned, but we considered it to be the same of the elements spacing along the stem of the rivet: that was because contact algorithms give the best results if such spacing is the same on the two sides of the contact region. In general, we introduced a 0.2 mm edge length for those elements, which resulted in 5 elements along the thickness, but also case of 10 and 20 elements were investigated, in order to check the convergence of the solution. At last, for what concerns the loads, they were applied imparting an assigned speed to the rigid wall, and recovering a posteriori the resulting load; that was because previous www.intechopen.com Numerical Simulations - Applications, Examples and Theory 290 Fig. 4. Von Mises stress during riveting for min clearance www.intechopen.com Also the extension of the volume interested by plasticity increases; in particular we obtained that in presence of a larger gap only a part of the first sheet is plastically deformed, but, at the same time, that the corresponding deformation reaches higher values, all in correspondence of the external edge or immediately near to it; as clearance reduces the max plastic deformation becomes smaller, but plasticity reaches the edge of the second sheet and that effect is still larger in correspondence of the min clearance, where a larger part of the second sheet is plastically deformed; at the same time the largest values of the plastic deformation in correspondence of the first edge becomes moderately higher for the constraint effect exerted by the inner surface of the hole and above noted. It is interesting to notice that the compression load is no much altered by varying the riveting velocity, as it can be observed from fig. 6 for 1.00 mm thick plates; what is more noteworthy is the large decrease from the peak to the residual load, which is, more or less, the same for all cases. On the other hand, the increase of thickness produces larger compression loads (fig. 7), as it was to be expected, because of the larger stiffness of the elements. It must be noted, for comparison reasons, that for the plots above the load is the one which acts on the whole rivet and not on the quarter model. www.intechopen.com Numerical Simulations - Applications, Examples and Theory 292 Fig. 7. Influence of thickness on compression load Aiming to evaluate the consequences of the riveting operation on the behaviour of a general joint, because of the residual stress state which has been induced in the sheets, the effect of an axial load was investigated, considering such high loads as to cause a bulging effect. As a first step, using an apparatus (Zwick Roell Z010-10kN) which was available at the laboratories of the Second University of Naples, a series of bearing experimental tests (ASTM E238-84) have been carried out on a simple aluminium alloy 6xxx T6 holed plate (28.5 x 200 x 3 mm3, hole diam. 6 mm), equipped with a 6 mm steel pin (therefore different from that for which we presented the results in the previous pages) obtaining the response curves shown in Fig. 8. In the same graph numerical results have been illustrated, carried out from non linear static FE simulations developed by using ANSYS\u00ae ver. 10 code. As it is www.intechopen.com Simulating the Response of Structures to Impulse Loadings 293 possible to observe the agreement between numerical and experimental results is very good. This experimental activity allowed to setup and develop the FE model (Fig. 9) of each single sheet of the joint and, in particular, their elastic-plastic material behaviour. www.intechopen.com Numerical Simulations - Applications, Examples and Theory 294 those previously obtained from the analysis of the same joint without taking into account the riveting effect: it is possible to observe that the riveting operation effects cause a reduction of the bearing resistance of the joint of about 10%. On the same plot also the results obtained by analysing also the axial loading by means of the explicit codes are illustrated: this procedure obviously proved to be very time consuming compared to the use of an explicit to implicit scheme, without giving relevant advantages in terms of results and therefore it is clear that the explicit-implicit formulation can be adopted for such analyses." + ] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure1-1.png", + "caption": "Figure 1. Test stand: 1\u2014transmission, 2\u2014motor, 3\u2014running rail, 4\u2014bowl, 5\u2014sample holder, 6\u2014supporting frame, 7\u2014compacting roller, 8\u2014bowl frame, 9\u2014main frame, 10\u2014wetting system [12].", + "texts": [ + " The proper determination of the forces and torques acting on the tool operating in the soil is very important, both in the design and operational context. It makes it possible to choose the right tractor power and determine fuel consumption [30\u201333]. On the other hand, in the design aspect, it prevents the structure from being oversized by supporting decisions regarding the selection of the construction materials depending on the occurring variable strains or deformations [34,35]. Therefore, the construction of a new test stand (Figure 1), developed in the Institute of Machine Design at the Poznan University of Technology, included a number of innovative design solutions. The test stand enables the use of advanced measurement systems, including complex measuring tracks, which make it possible to track the patterns of changing loads in the tested tools. The basic element of such solutions can be a transducer for measuring component loads acting on the tools operating in the ground. The number of literature references discussing methods of recording loads acting on components operating in the soil, especially on coulters, is relatively small [26]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003278_le_download_510_1021-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003278_le_download_510_1021-Figure4-1.png", + "caption": "Fig. 4. Cross sectional view of developed sub baric storage bin", + "texts": [ + " A thermocouple is inserted at one side of subbaric storage bin in such a way that the sensing front of thermocouple should touch grains to sense temperature of food grains. Control panel has main switch of developed storage bin and also includes switches of suction blower, vacuum pump, light, agitator and agitator speed regulator. Agitator is provided in the center of storage chamber for mixing of food grains which are stored in the bin to prevent the accumulation of respiratory gases released by insects, food grains and also used in easy unloading of food grains as shown in Fig. 4. It is having 1500 mm length and 25 mm diameter and it has two attached plates with dimensions 300 \u00d7 100 mm (L \u00d7 W) for proper rotations of the grains. A motor with 0.5 Hp capacity was placed at the top of bin to provide power. The sub-baric storage bin has two inlet valves for impregnation of gases which can be used in modified atmospheric storage for future use by providing a gas mixer for mixing of desired gases. The various manufacturing processes involved in fabrication are: Selection of material of construction; Testing of stainless steel for different grades; Development of geometry; SS Sheet cutting; Sheet rolling to form cylinder; TIG welding and DP testing; Nozzle cutting (Door, Sight Glass, Light Glass etc" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003944_6514899_10305151.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003944_6514899_10305151.pdf-Figure12-1.png", + "caption": "FIGURE 12. (a) Metasurface of the proposed 1\u00d72 ME-dipole antenna with metasurface. (b) S-parameters of the proposed 1\u00d72 ME-Dipole Antenna Structure by displacing the unit cells on the top and bottom of the superstrate by c. (Thick black line = S11 when c= 0.5 mm, Thick blue line = S11 when c= 2 mm, Thick red line = S11 when c= 4 mm, Thick dark yellow line = S11 proposed, dotted black line = S21 when c= 0.5 mm, dotted blue line = S21 when c= 2 mm, dotted red line = S21 when c= 4 mm, dotted dark yellow line = S21 proposed).", + "texts": [ + " For more information, see https://creativecommons.org/licenses/by-nc-nd/4.0/ Oludayo Sokunbi and Ahmed Kishk: Millimeter-wave ME-Dipole Array Antenna Decoupling Using a Novel Metasurface Structure V. PARAMETRIC ANALYSIS To further confirm the effectiveness of this simple design with wideband coupling reduction, some antenna parameters are tuned, and their results are discussed. First, the 2\u00d75 unit cells on the superstrate\u2019s top and bottom were moved by a factor of c on the y-axis, as shown in Fig. 12(a). As seen from Fig. 12(b), it is clear that the matching and mutual coupling are degraded as c increases and the best result is obtained when c is zero (proposed). Next, the unit cells on the bottom of the superstrate are displaced by the same factor c while the top unit cells are undisturbed. As seen from Fig. 13(a), the antenna\u2019s bandwidth and coupling are also degraded as c increases, and the best result is observed at c = 0 (Proposed). Also, the number of unit cells on the top and bottom of the superstrate is increased from 2-column resonator rings to 5-column resonator rings and the S-parameters are extracted as seen in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure55-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure55-1.png", + "caption": "Figure 55 EMI Access Port Cover", + "texts": [ + " This is significantly lower than other components of the P-POD, but the previous design exhibited a negative margin, so this was considered a Page 69 significant improvement. The changes to the door resulted in a 18 gram mass increase, which was worth the improvement. P-POD Mk. IV Access Port Covers The access port covers were also redesigned to accommodate the EMI Gasket, as well as the changes to the mounting method described in Chapter 2. Through incorporating the flanged interface with gasket groove, the access port covers gained significant stiffness, such that all six screws were not necessary. A recap of the basic access port cover design is shown below in Figure 55. The access port covers are not intended to withstand any load from the CubeSat, and simply have to withstand the gravity load of their own weight. As expected, under the X/Y gravity load factor the margin of safeties for each size were well over 10. It was important to also consider the load of part of the CubeSat resting on the access port during launch, should the CubeSat structure fail. In order to simulate part of the CubeSat resting against the access port cover, a load consisting of 1 kg at the X-axis load factor was applied to the access port Page 70 cover" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000379_f_version_1387215492-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000379_f_version_1387215492-Figure1-1.png", + "caption": "Figure 1. The structure diagram of LPDA.", + "texts": [ + " The log-periodic dipole antenna (LPDA) could be used as the conformal antenna mounted on the carrier [1]. The Vivaldi antenna is also a good choice. LPDA does not merely possess wide bandwidth and its gain is higher than the ordinary planar spiral antenna. The LPDA is a kind of frequency-invariant-dependent ultra-wideband antenna. Generally, its electrical properties remain stable in the frequency band of 10:1 or even higher because of its self-similar structure. In addition, the antenna installation is simplified, which does not destroy the mechanical structure of the carrier. Figure 1 shows the structure diagram of LPDA, which consists of N parallel linear oscillators. The length is in proportion to the spacing of the oscillators and its definition is: \u03c4 = dp dp+1 = Lp Lp+1 = Rp Rp+1 , p = 1, 2, \u00b7 \u00b7 \u00b7 , N (1) where dp is the distance between pth and p + 1th unit oscillator; Lp is the length of pth unit oscillator; and Rp is the distance from pth unit oscillation to the antenna void vertex. The entire structure of LDPA depends on the scale factor \u03c4 and the structure angle \u03b7. When \u03c4 and \u03b7 are decided, the geometric structure of the LPDA is fixed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002417_rc58_07.15051402.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002417_rc58_07.15051402.pdf-Figure8-1.png", + "caption": "Figure 8. Photographs showing: (a) bottom and (b) top views of the realized coupled SRRs; (c) the filtering module fixed in the horn antenna.", + "texts": [ + " As shown in the previous section, the use of two identical SRRs allows widening the bandwidth of a metamaterial-inspired notch filter. To experimentally validate this result, the coupled SRRs in the configuration reported in Figure 4 have been manufactured by using a LPKF Protomat-S milling machine. Then, a prototype of the overall structure (antenna + filter) has been assembled and experiments were carried out to measure the antenna performance. A photograph of the assembled structure and its elements is shown in Figure 8. Please note that the filtering module has been fixed inside the horn by using a small foam block that does not affect the performance of the overall structure. First, we have measured the reflection coefficient amplitude at the input port, which is in a good agreement with the simulations (see Figure 9). In particular, although there is a slight shift in frequency due to a positioning error of the filtering module along the x-axis (around 0.5 mm, according to a proper set of full-wave simulations), the antenna exhibits the required broadband rejection at around 10 GHz, while it is well matched in the rest of the frequency band of operation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002544_mtime_20210910085626-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002544_mtime_20210910085626-Figure1-1.png", + "caption": "Figure 1: (a) Schematic representation of the analytical model, (b) geometric configuration of a typical kinematic bearing.", + "texts": [ + " [13] highlighted the critical effect of the higher vibration modes on the dynamic response of RPSs consisted of multiple degree of freedom (mdof) elastic superstructure. Experimental investigation of RPSs consisted of sdof superstructure has been also conducted [14]. The presence of curved extensions at the base of the rocking columns results in rolling and rocking rocking response [15]. The idealization of the model of mdof elastic oscillator fixed on the top of a rocking frame which is comprised of kinematic bearings is illustrated in Figure 1(a). Moreover, a typical configuration of the kinematic bearings is presented in Figure 1(b). The rigid frame consists of a cap beam with mass mb and N freestanding columns with mass mc, semi-diagonal length 2 2R H B , rotational moment of inertia around its center of mass Icm, In case of kinematic bearings with curved wedges and total slenderness tan ' = B'/H, the post uplift stiffness during rolling response depends on the radius of curvature r of rocking response. The superstructure is determined by the mass matrix M, the stiffness matrix K and the damping matrix C. The equations of motion of the examined structural system are presented in the aforementioned literature" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002917_f_version_1639712776-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002917_f_version_1639712776-Figure11-1.png", + "caption": "Figure 11. Surface current distribution of 4 \u00d7 4 MIMO array (a) without and (b) with decoupler.", + "texts": [ + " For a better understanding of the decoupler\u2019s necessity, a comparison of the isolation performance between the antenna elements with and without decoupler is presented in Figure 10. In the figure, Sij refers to the isolation between adjacent antenna elements and Sik represents the isolation between diagonal antenna elements. From the results, it can be concluded that the isolation between antenna elements improves when decoupler is introduced, shown in Figure 10, without affecting other parameters. Furthermore, this effect can also be verified from Figure 11 where the surface current distribution of 4 \u00d7 4 MIMO array is plotted without and with decoupler. To understand the coupling behavior between antenna elements, only port-1 of the array is excited while the other ports are terminated with a matched load. The corresponding surface current results are shown in Figure 11. It can be observed from Figure 11a that without decoupler, the surface current generated by antenna 1 is influencing adjacent antenna elements, which corresponds to high mutual coupling. On the contrary, when the decoupler is inserted, shown in Figure 11b, this effect reduces and the isolation performance of the array improves. In addition, the utilization of a decoupler improves the radiation properties of the MIMO antenna. In Figure 12, three-dimensional (3D) radiation characteristics of the MIMO antenna are presented. From Figure 12a, one can observe that without a decoupler, the MIMO antenna exhibits a bi-directional radiation pattern but with high sidelobe levels (SLLs). On the other hand, when the decoupler is printed on the other side of the substrate, the pattern becomes more directional in both directions (0\u25e6 and 180\u25e6) as shown in Figure 12b" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002975_f_version_1683293668-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002975_f_version_1683293668-Figure1-1.png", + "caption": "Figure 1. Proposed UWB microstrip monopole antenna. (a) Antenna layer (top view). (b) Ground plane layer (bottom view).", + "texts": [ + " The obtained notch bands have very high selectivity at the beginning and the end of the notch bands. The MIMO configuration circuit has one connected ground plane. High isolations were obtained between the four radiators by using the defective ground structure (DGS) technique. The article is arranged as follows. The design of a UWB antenna element is explained in Section 2. In Section 3, the design of the UWB-MIMO antenna is introduced. The results and discussion are given in Section 4. Finally, Section 5 provides the conclusions. Figure 1 shows the geometry and parameters of the proposed UWB monopole microstrip antenna element. Table 1 shows the values for the proposed antenna design. The proposed UWB microstrip antenna was designed on FR-4 dielectric substrate material with relative permittivity of \u03b5r = 4.5, a dielectric loss tangent of 0.025, and a substrate height of h = 1.5 mm. The proposed UWB antenna element consists of three sections placed on the top layer of the dielectric substrate. The first one is a 50 \u2126 microstrip feeding line with a width of 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002703_1334-022-00450-w.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002703_1334-022-00450-w.pdf-Figure1-1.png", + "caption": "Fig. 1 GTS for robot r2. The labels of the states denote the output of the TS in the respective state", + "texts": [ + " Intuitively, a valid historywith respect to a setGi ofGTS is a finite sequence that is a prefix of a computation of all GTS in Gi . Thus, a valid history can be produced by the parallel composition of the GTS. Note that since strategies cannot look into the future, a finite word satisfies the requirements of a valid history either for all of its infinite extensions or for none of them. Running example Suppose that robot r2 guarantees to give priority to r1 at crossings and to move forward if r1 is not at the crossing. A GTS g2 for r2 is depicted in Fig. 1. Since r2 never outputs go2 if r1 is at the crossing (left state), the finite sequence {at_c1}{go2} is no valid history with respect to {g2}. Since r2 outputs go2 otherwise (right state), e.g., {at_c2}{go2} is a valid history with respect to {g2}. Since valid histories determine whether the other processes deviate from their certificates, a strategy is required to locally satisfy the specification in certifying synthesis with GTS if its computation is a valid history respecting the GTS of the other processes: Definition 5", + " A strategy si for pi \u2208 P\u2212 locally satisfies an LTL formula \u03d5i with respect to Gi , denoted si | Gi \u03d5i , if comp(si , \u03b3 ) \u222a \u03b3 \u2032 | \u03d5i holds for all \u03b3 \u2208 (2Ii )\u03c9 and \u03b3 \u2032 \u2208 (2V \\Vi )\u03c9 with comp(si , \u03b3 )|t \u222a \u03b3 \u2032|t \u2208 Ht Gi for all t . Intuitively, requiring a strategy to locally satisfy a specification allows us to formulate the implication i \u2192 \u03d5i used in certifying synthesis with LTL certificates also for certificates represented by GTS. Running example If r2 sticks to its certificate g2 depicted in Fig. 1, r1 can enter crossings regardless of r2. Such a strategy s1 for r1 is shown in Fig. 2. Since neither \u03c3 : = {at_c1}{go2} nor any finite sequence containing \u03c3 is a valid history with respect to g2, no transition for input go2 has to be considered for local satisfaction when r1 is at the crossing (left state). Therefore, these transitions are depicted in gray. Similarly, no transition for \u00acgo2 has to be considered when r1 is not at the crossing (right state). The other transitions match valid histories and thus they are taken into account" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003127_0.1145_240518.240656-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003127_0.1145_240518.240656-Figure1-1.png", + "caption": "Figure 1 Decomposition of node v (K = 3). (a) initial network, (b) decomposition yielding mapping depth = 3, (c) decomposition yielding mapping depth = 2.", + "texts": [ + " However, FlowMap can not be applied directly to unbounded networks. Gate decomposition can be classified into structural decomposition and Boolean decomposition. The structural decomposition replaces multi-fanin (simple) gates by fanin trees while the Boolean decomposition decomposes the functionality of gates. This paper focuses on structural decomposition for depth minimization in LUT mapping. Gate decomposition affects the mapping solution depth significantly. For example, assume K = 3. The network N in Figure 1(a) is not K-bounded. If node v is decomposed in the way shown in Figure 1(b), there is no way to obtain a mapping solution of depth less than 3. However, if the decomposition shown in Figure 1(c) is carried out for node v, a mapping solution of depth equal to 2 can be obtained. Even for K-bounded networks, the depth of mapping solutions computed by FlowMap may decrease if gates are further decomposed before mapping [4]. Several gate decomposition routines have been used for LUT-mapping. The tech_decomp and the speed_up in SIS [10] and the dmig in [1] focus on minimizing the number of levels in the decomposed network. They do not directly minimize the depth of the mapping solution. Chortle-d [6] computes depth-optimal gate decomposition and mapping solutions for tree networks (may be unbounded) but produces suboptimal results for general networks" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004153_00502-017-0569-0.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004153_00502-017-0569-0.pdf-Figure10-1.png", + "caption": "Fig. 10. SPNMOS response to 100 ns long TLP-like current pulse with 10 ns rise time simulated with TCAD. (A) At the beginning of 100 ns plateau with MOS action of M2, (B) At the end of the 100 ns plateau with bipolar action of M1 and M2", + "texts": [ + " For the proposed test-chip several versions of SPNMOS were implemented with different ratios of M1 and M2: 16:1 and 8:1 (in terms of W/L dimensions), as well as with linear and with enclosed NMOS layout (both shown in Fig. 8). 2D TCAD simulations were performed in order to optimize the geometry of the cross section and electrical parameters for a wide range of ESD pulse rise times. Fig. 9 shows response to TLP pulses of rise time ranging from 0.1 ns to 10 ns. This spread should cover rise times of real ESD events [16]. Figure 10 shows the SPNMOS current density in response to the 10 ns rise time TLP. After 10 ns the channel is built under M2 indicating MOS action (Fig. 10A). At the end of the 100 ns long plateau the MOS action has vanished (Fig. 10B), since the M2 gate voltage has returned to zero volts (as shown in Fig. 9 waveforms). At this point in time both transistors M1 and M2 are in the bipolar mode, efficiently conducting the test-pulse current with low on-resistance. For all discussed above NMOS-based ESD devices, the N+ drain area was designed to be 32 \u00b5m2 like for diodes described in section 2. Table 3 summarizes the NMOS-based devices with their capacitance including parasitics from Cadence layout extraction. The summary includes also special-purpose ESD devices based on the enclosed-layout MOS transistors, for which the layout capacitance extraction was not possible, because of software limitations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004916_id_0353-36702204619L-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004916_id_0353-36702204619L-Figure1-1.png", + "caption": "Fig. 1 (a) Top-view layout of TG SOI FinFET [21], (b) 3D schematic view of TG SOI FinFET", + "texts": [], + "surrounding_texts": [ + "Most of the reported FinFETs are fabricated with a silicon channel, they present different advantages such as: i) reduced SCEs and a low leakage current, ii) superior electrostatic control through tri-gate structures, iii) reduced effect of substrate bias on the threshold voltage and excellent carrier transport properties along with more aggressive channel length scaling possibilities [1].\nThe conventional FinFET technology has to face the competition from other technology options because of its high access channel resistance due to its extremely thin body. To improve FinFET performance, one must address the quantum confinement problem. Hence, the use of the BQP algorithm, which is based on the Bohm interpretation of quantum mechanics [8], may become more important.\nN.P. Maity et al. in 2017 [22] have explored the application of the promising high-k dielectric material, HfO2, on MOS devices. They observed that the tunneling current is inversely proportional to the dielectric constant of the oxide material.\nNiladri Pratap Maity et al. in 2016 [23] have developed an analytical model to evaluate the impacts of the HfO2 on the current density model with a comparison between the theoretical model and the experimental measurements.\nLazzaz et al. in 2022 [27] have demonstrated that quantum effects play a dominant role in nanostructures. They used the BQP method to fit experimental measurement of the IDS-VDS characteristics for 14 nm TG N-FinFET.\nNeha Gupta et al. in 2020 [28] have explored the performance evaluation of high-k gate stack on the analog and RF figure of merits (FOMs) of 9 nm SOI FinFET. The results of their simulation confirm that the limitations of the transistor device such as SCEs, leakage current and parasitic capacitance have been reduced and pave the way for high-speed switching and RF application due to the use of high-k dielectric material with SiO2 between gate and fin.\nAnisur Rahman et al. in 2018 [29] found that Intel\u2019s 10 nm technology achieved scaling\nbenefits over its preceding 14 nm generation at matched or better transistor reliability.\nMarupaka Aditya et al. in 2021 [30] have confirmed that using high-k dielectric\nmaterials increase the ON current and improve the device performance.\nSanghamitra Das et al. in 2021 [31] have studied the effect of FinFET geometric parameters (channel length and fin height) on the RF FOMs by using TCAD simulations. Their results confirm that decreasing the channel length or increasing the fin height improves the RF parameters.\nMostak Ahmed et al. in 2021 [31] have simulated the electrical characteristics of a 3- D TG N-channel SOI FinFET with a channel length of 5 nm using different gate dielectric materials. The results of their simulation confirm that high-k dielectric materials are the better option in the fabrication for future TG FinFET devices.\nThe above literature survey indicates the importance of using high-k dielectrics in FinFET devices to reduce SCEs. In this paper, the transfer and the transconductance characteristics have been computed in order to find the electrical response of TG N- and Pchannel SOI FinFETs with 10 nm channel length. The BQP algorithm has been used from Silvaco ATLAS TCAD software to simulate the I-V characteristics.\nThe simulated devices have been optimized in terms of geometry to have optimal\nvoltage transfer characteristics (VTC) for a CMOS inverter [14], [15].", + "2. DEVICE STRUCTURE\nThe hafnium-based oxide is extensively used because of its low leakage property and its high thermal stability with silicon [25]. The geometric parameters used in this simulation are represented in Table 1 and the operating parameters of the two structures are presented in Table 2.\nTG FinFET technology is based on the following fin geometry: fin length (L), fin width,\nWfin, fin Height, Hfin, and oxide thickness, tox.\nThe numerical resolution, which includes the gate work function and the choice of physical models, represents one of the two main steps in the Silvaco ATLAS tools. The Shockley-Read-Hall (SRH) theory has been used.\nFigure (1a) shows the top-view layout of TG SOI FinFET with 10 nm gate length, and Figure (1b) illustrates the 3D schematic view of FinFET. The gate oxide thickness is the same for all three sides of the fin. The Hfin is considered as the distance between the top gate and the bottom gate oxides. The Wfin is represented as the distance between front gate and back gate. LG is the gate length and BOX is buried oxide.", + "All simulations have been performed using ATLAS and DEVEDIT 3D device simulator and different operating parameters such as the supply voltage, are extracted from the predictive technology model (PTM) [32].\n3.DRAIN CURRENT MODEL OF THE TG FINFET\nThe device electrostatics is governed by the 3-D Poisson\u2019s equation [5][19]:\nSi\nzyxqn\ndz\nzyxd\ndy\nzyxd\ndx\nzyxd\n\n ),,(\n\u00b2\n),,(\u00b2\n\u00b2\n),,(\u00b2\n\u00b2\n),,(\u00b2 =++ (1)\n : Electrostatic potential; q: electron charge; \u03b5Si: silicon permittivity, n(x,y,z): electron density.\nQuantum effects become more dominant and are difficult to control in the device. Hence,\nin this study, one must consider them by selecting the appropriate model such as the BQP.\nThe BQP model can also be used with the energy balance and hydrodynamic models, where the semi-classical potential is modified by the quantum potential in a similar way as for the continuity equations [20].\nAccording to the Bohm interpretation of quantum mechanics, the wave function can be\nrepresented in polar coordinates by the following expression [8]:\n\ud835\udf13 = \ud835\udc45\ud835\udc52\ud835\udc65\ud835\udc5d( \ud835\udc56\ud835\udc46\n\u210f ) (2)\nThe Schr\u00f6dinger equation can be written as:\n)(Re)(Re)(Re 2\n\u00b2 1\n\n iS xpE iS xpV iS xpM =+ \u2212 \u2212\n(3)\nM-1\u2207S: The local velocity of the particle associated with the wave function. E is conserved and equal to the sum of the potential energy and V is the kinetic energy [8].\nThe quantum potential is derived from the use of the Bohm interpretation of quantum\nmechanics and it is described by the following equation [8][20]:\nR\nRM Q )(\n2\n\u00b2 1 \u2212= \u2212 (4)\nThe threshold voltage expression in the case of a FinFET structure can be defined by [18]:\ndsdsbBSD\nox\nb Bfbth VqN\nC VV \n \u2212+++= ))2(2(2 (5)\nVfb: Flat band voltage; \u2205B: Body potential; Cox: Gate oxide capacitance; q: electron charge; NS: Doping concentration; \u03b5s: dielectric constant of the semiconductor; Vsb: the reverse bias between the source and the body; \u03bbd: drain-induced barrier lowing (DIBL) coefficient; \u03bbds: channel length modulation; \u03bbb: barrier variation coefficient." + ] + }, + { + "image_filename": "designv8_17_0004512_servlets_purl_771234-Figure23-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004512_servlets_purl_771234-Figure23-1.png", + "caption": "Figure 23 Midplane Cross Section of Guard Heater, PX Cell, and Thermocouple Wells", + "texts": [ + " Four are used to measure and control the temperatures of the four zones of the guard heater. Seven are spot-welded in place at various locations on the converter and the hot end heater; two of these are used to control the cold end heater and the hot end heater. There are also two built-in thermocouple \u201cwells\u201d leading to points inside the BASE tube and in the throat of the evaporator. The remaining eight are mounted to a moveable stage and are inserted into eight wells made &om 1.6 mm O.D. x 0.812 mm LD. tubing (see Figure 23). Four of these wells are fastened to the wall of the AMTEC converter to insure good thermal contact with the walls; the other four are fastened to the guard heater so that they lie on the same radial line as the four on the cell. The moveable stage is supported on a threaded rod, and by turning this, the stage and all eight thermocouples move lengthwise along the cell/guard. The threadedrod has 7.09 threads per cm, giving a locating accuracy of 0.35 mm. The experimental data taken with this device indicate that the data is highly repeatable" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure15-1.png", + "caption": "Fig. 15 Radial blades impeller (pressure contour at +5 mm along +Z-axis)", + "texts": [], + "surrounding_texts": [ + "The results obtained from the suggested modifications will be discussed in details by comparing the pressure delivered from the modified impeller, DFB, with that from the standard one, RB. The pressure contours are plotted in each case at 5 mm apart from X-Y plane towards the positive direction of Z-axis. \u03b2 \u03b2=+15\u00b0 \u03b1 \u03b1=+15\u00b0 5-1 Effect of double forward angle modification on the performance of regenerative impeller The suggested modification applied is the double forward impeller, DFB, with chevron angle \u03b1=+15o and inclination angle \u03b2=+15o (see Fig. 14). Figures 15 and 16 show the 2D color contours of pressure of the flow fields for the standard case with radial angles, RB, and a case with double forward angles, DFB, respectively. It can be observed that the suggested modification increases the range of discharged pressure (pressure coefficient), about 50% more than that discharged from the simple radial impeller (standard one). . 5-2 Assessment of the suggested modifications By comparing, both Figs 15 and 16, it can be observed that the pressure of the flow field around the blades in case of double forward blade modification, DFB, is larger than that of the radial blade, RB. Figures 17 shows the instantaneous discharge flow pressure at the outlet pipe ports after three complete revolutions of impeller for both cases: radial blades and double forward blades. It is also observed from Fig. 17 that the discharged local pressure range for the double forward blade, DFB, is higher than the standard radial impeller, RB. This means that the DFB produces largest discharge pressure compared with that of RB one. This result can be also be concluded from tracking the pressure developing between each blade of the double forward, DFB, and the radial blades, RB, through a flow path located +5 mm from the X-Y plan. Figure 18 shows the velocity vectors and the direction of the flow at the tracked path for the radial pump. The tracked flow path for the double forward pump is done with the same criteria of the radial one. The pressure tracking across this flow path is presented in Fig. 19 showing the evidence of local pressure variation between each blade of impeller for the two investigated cases. Moreover, it can be observed that the local pressure in case of the double forward impeller is greater than that in the radial impellers case for all angles \u201cfrom Y-Axis\u201d greater than 60. In order to quantify the performance of the pumps, the pressure (head) coefficient \u03c8 (Eq. 1), pump efficiency \ud835\udf02 and torque coefficient \u03c4, are considered, \ud835\udf02 = \ud835\udf13.\u00d8 2.\ud835\udf0f , (3) where the torque coefficient \u03c4 is calculated as a function of the torque T generated by the impeller blades on the fluid flow through the pump and rotational speed , \ud835\udf0f = \ud835\udc47.\ud835\udf14 \ud835\udf0c.\ud835\udc34\ud835\udc50.\ud835\udc48\ud835\udc47 3 . (4) Figure 20 shows the head coefficient versus the flow coefficient (-\u00d8) and efficiency versus the flow coefficient (-\u00d8) for the simple radial impeller RB, and the double forward impeller, DFB. It is found that the pressure coefficient and pump efficiency of double forward angle case are greater than those of the standard radial impeller. It is observed from Fig. 20 that at the flow coefficient around 0.25, the design condition, the percentage of improvement in the pump head is 70% in case of the double forward impeller compared to the standard radial impeller. As the flow coefficient decreases, the percentage of improvement of the pump head of DFB is decreases and tends to 40% larger than the standard radial impeller. Also, the percentage of efficiency improvement in DFB case is highlighted at the design condition (flow coefficient around 0.25) and reaches 14%higher than the standard radial impeller. 5-3 Double angle modifications versus single one In this section, the pump performance in the present case with simultaneous change of the two angles (referred as a double modification) is compared to the cases interpreted by many researches where the change is confined to one angle, while keeping the other unchanged (referred as a single modification) as suggested previously by many researches, (Nejad et al. 2017 [9]; Horiguchi et al. 2009 [7]; Nejadrajabali et al. 2016 [11]). In total, four cases are investigated and compared with the radial standard impeller in Fig. 21: (1) DFB (\u03b1=+15, \u03b2=+15), (2) RB (\u03b1=0, \u03b2=0), (3) changing the inclination angle only, SFI (\u03b1=0, \u03b2=+15), and (4) changing the chevron angle only, SFC (\u03b1=+15, \u03b2=0). It is obvious that the double forward modification, DFB, (\u03b1=+15, \u03b2=+15) is the best among all the cases. The improvement is among 70% in head pump at the max. efficiency point." + ] + }, + { + "image_filename": "designv8_17_0001490_f_version_1674895715-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001490_f_version_1674895715-Figure1-1.png", + "caption": "Figure 1. Constant pressure relief circuit of inlet throttle speed-control system. Figure 1. Constant pressure relief circuit of inlet throttle speed-control system.", + "texts": [ + " Keywords: SVTDARVWEO; AMESim; response characteristics; influencing factors The direct-acting relief valve (DARV) relies on the pressure oil in the hydraulic system to directly act on the valve element to balance it with the spring force, so as to control the opening and closing of the overflow port in order to keep the hydraulic pressure of the controlled system or circuit constant, and to realize the functions of pressure stabilization, pressure regulation or pressure limitation. The application of the DARV mainly includes constant pressure overflow, safety protection, back-pressure generation, remote pressure regulation and multi-stage pressure control. (1) Constant pressure relief. Figure 1 is a typical inlet throttle speed-control system. When the system pressure is lower than the opening pressure of the DARV, the DARV will close. At this time, the system pressure depends on the load. When the system pressure reaches the set value of the DARV, the DARV is Processes 2023, 11, 397. https://doi.org/10.3390/pr11020397 https://www.mdpi.com/journal/processes Processes 2023, 11, 397 2 of 28 normally open and the system pressure is limited. When the load speed change of the actuator causes the flowrate change, the regulating function of the DARV keeps the system pressure essentially constant, and overflows the excess oil back to the tank, thus realizing constant pressure overflow" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure4-13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure4-13-1.png", + "caption": "Figure 4-13 Sch\u00e9ma de l'antenne PIFA agile en polarisation et en fr\u00e9quence", + "texts": [ + "............................................................... 110 Figure 4-9. Vues de l'antenne PIFA miniature ........................................................................... 112 Figure 4-10. Vue de l'antenne PIFA sur substrat de type FoamClad.......................................... 113 Figure 4-11. Bande passante obtenue pour l'antenne PIFA miniature en fonction du substrat .. 113 Figure 4-12. Dimensions d'un syst\u00e8me \u00e0 diversit\u00e9 spatiale utilisant deux antennes miniatures. 114 Figure 4-13 Sch\u00e9ma de l'antenne PIFA agile en polarisation et en fr\u00e9quence............................ 116 Figure 4-14. Tableau de correspondance entre les \u00e9tats de l'antenne agile et les \u00e9tats des diodes PIN .............................................................................................................................................. 117 Figure 4-15. Antenne dans un rep\u00e8re sph\u00e9rique et cart\u00e9sien ...................................................... 118 Figure 4-16. Champ \u00e9lectrique total en dBV/m et ellipses de polarisation \u00e0 3,53 GHz lorsque le plan de cour-circuit 1 est connect\u00e9", + " Ceci limite cependant le traitement d'antenne \u00e0 des techniques de s\u00e9lection. Nous avons voulu appliquer ce principe d'agilit\u00e9 en polarisation \u00e0 des structures plus compactes que des antennes planaires. Notre travail a abouti \u00e0 la d\u00e9finition d'une nouvelle structure d'antenne PIFA agile en polarisation mais \u00e9galement agile en fr\u00e9quence [4.1]. Ce travail fait l'objet d'un brevet \u00e9tendu \u00e0 l'international et r\u00e9compens\u00e9 par un prix IEEE France. La structure de l'antenne propos\u00e9e est repr\u00e9sent\u00e9e sur la Figure 4-13. C'est une antenne de type PIFA con\u00e7ue pour r\u00e9pondre au cahier des charges \u00e9nonc\u00e9 pr\u00e9c\u00e9demment en termes de dimensions et elle peut \u00eatre utilis\u00e9e pour des applications utilisant soit la bande ISM \u00e0 2,45 GHz soit la bande d\u00e9finie pour le WiMax autour de 3,5 GHz. 116 L'antenne utilise un substrat en mousse (FoamClad RF de Arlon) pr\u00e9sentant une permittivit\u00e9 proche de celle du vide (\u03b5r=1,1) avec une tangente de perte de 0,002 pour une \u00e9paisseur de 6,75 mm. Le plan de masse est un carr\u00e9 de 42 mm de c\u00f4t\u00e9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure38-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure38-1.png", + "caption": "Figure 38: Final pantograph design.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0004668_8600701_08618309.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004668_8600701_08618309.pdf-Figure6-1.png", + "caption": "FIGURE 6. The structure of the proposed FSRs. (a) A-T FSR using CBSR. (b) T-A FSR using M-CBSR. (The geometrical parameters of the unit cell are optimized as: Px = 18pmm, Py = 9mm, l1 = 12.5mm, l2 = 5.75mm, l3 = 4.6mm, l4 = 1.9mm, l5 = 6.0mm, w1 = 0.5mm, w2 = 0.8mm, w3 = 0.15mm, w4 = 0.3mm, w5 = 1.0mm, w6 = 0.3mm, h = 5mm, R = 160ohm.)", + "texts": [ + " In summary, the M-CBSR can be designed by connecting two arms of the CBSR. The size of the two CBSRs is 1.5mm\u00d76.0mm. Although the size of the resonance structure is same. The resonance frequency of M-CBSR can shift to lower frequency. Comparing with the previous resonance structure, the resonance frequency of the proposed CBSR could shift to the lower frequency without enlarging the resonator. IV. DESIGN AND ANALYSIS OF THE PROPOSED FSRS USING CBSR AND M-CBSR The unit cell of the proposed FSRs is shown in Fig.6. It includes two kinds FSRs using CBSR and M-CBSR which have different transmission band. The transmission band of one FSR using CBSR is above the absorption band. It belongs to A-T FSR. The transmission band of the other FSR using M-CBSR is below the absorption band. It belongs to T-A FSR. Each FSR consists of a resistive layer and an FSS layer. Both layers are printed on a dielectric substrate Rogers 4350B with a thickness of 0.508mm. These layers are separated by an air spacer. In the resistive sheet layers, two resonance structures are designed to get low insertion loss at the two transmission bands" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003781_f_version_1680255727-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003781_f_version_1680255727-Figure10-1.png", + "caption": "Figure 10. Grid model of seedling picking mechanism.", + "texts": [ + " Modal Analysis of Seedling Picking Mechanism For the finite element analysis of the drive mechanism (gears, connecting rods, cams, etc.) in the seedling picking mechanism, the 3D model created using SW was imported into Ansys in stp format. To reduce the calculation volume, the mechanism was simplified and the constraints were redefined while ensuring the calculation accuracy. After that, the structure was meshed, and the meshed mechanism comprised 230,927 cells and 1,049,484 nodes; the meshed model is shown in Figure 10. The overall quality of the mesh of the seedling picking mechanism was in the range of 0.85\u20131, indicating that the mesh quality was up to standard and satisfied the requirements. Based on the parameters listed in Table Figure 9. Comparison of trajectory curves: (a) Theoretical trajectory; (b) Simulation Trajectory. 3.2. odal nalysis of Seedling Picking echanis For the finite ele ent analysis of the drive echanis (gears, connecting rods, ca s, etc.) in the seedling picking mechanism, the 3D model created using SW was imported into Agriculture 2023, 13, 810 12 of 18 Ansys in stp format. To reduce the calculation volume, the mechanism was simplified and the constraints were redefined while ensuring the calculation accuracy. After that, the structure was meshed, and the meshed mechanism comprised 230,927 cells and 1,049,484 nodes; the meshed model is shown in Figure 10. The overall quality of the mesh of the seedling picking mechanism was in the range of 0.85\u20131, indicating that the mesh quality was up to standard and satisfied the requirements. Based on the parameters listed in Table 2, the parts of the seedling picking mechanism were set, and the frame fixing plate was set to be fixed to the ground. Agriculture 2023, 13, x FOR PEER REVIEW 13 f 18 2, the parts of the seedling picking mechanism were set, and the frame fixing plate was set to be fixed to the ground. Figure 10. Grid model of seedling picking mechanism. In this study, the modal analysis of the seedling picking mechanism was carried out by means of finite element analysis, and the first six orders of modal vibration and modal frequencies of the seedling picking mechanism were simulated, and the modal frequencies were compared with the engagement frequencies of the planetary gear system to determine whether resonance would occur. Table 3 shows the first six-order modal frequencies of the seedling picking mechanism in the working process", + " From Table 3, it is evident that the first six orders of the inherent frequencies of the seedling picking mechanism were in the range of 181.43\u2013678.14 Hz, which were much larger than the meshing frequencies of the planetary gear system. Thus, the resonance phenomenon did not occur during the efficiency of seedling picking at less than 120 plants/min. Agriculture 2023, 13, 810 13 of 18 Agriculture 2023, 13, x FOR PEER REVIEW 13 of 18 2, the parts of the seedling picking mechanism were set, and the frame fixing plate was set to be fixed to the ground. Figure 10. Grid model of seedling picking mechanism. In this study, the modal analysis of the seedling picking mechanism was carried out by means of finite element analysis, and the first six orders of modal vibration and modal frequencies of the seedling picking mechanism were simulated, and the modal frequencies were compared with the engagement frequencies of the planetary gear system to determine whether resonance would occur. Table 3 shows the first six-order modal frequencies of the seedling picking mechanism in the working process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000668__imane2017_06024.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000668__imane2017_06024.pdf-Figure4-1.png", + "caption": "Fig. 4. Solid Edge PMI editor dialog.", + "texts": [ + " Unlike this case, the synchronous method offers the designer a new tool called PMI (Product Manufacturing Information) particularly strong and fast because it causes the change through direct action on the dimensions displayed on the screen, due to the fact that they no longer are to be found at the sketch, they are actually moved in the three-dimensional solid. Thus, the synchronous method causes the parentchild link to break but also add this new changing instrument called PMI that, when selecting a size of the solid, enables the designer to intervene directly on the solid by requiring application of the modification to the left, centre or right side, as shown in Figure 4. At the same time it enables blocking the dimensional value by selecting the lock in the new working window. The steering wheel is an extremely powerful tool made available to the designer by the synchronous technology, by which one may select a particular surface, followed by its orientation in space and the choice of how to implement the change, meaning selecting a travel axis or the plan containing the tor axis of rotation. This tool determines the movement or rotation of the following elements: Reference planes (except the base reference planes) Coordinate systems (except the base coordinate system), Sketches, Sketch elements, Curves, Faces, Features and Design Bodies" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure21-1.png", + "caption": "Figure 21. Estimation of Sink marks.", + "texts": [ + " The larger the principal value, the stronger is the alignment in the corresponding principal direction. 4.3.1. Estimated Sink Mark Figure 20 shows the presence and location of sink marks and voids likely to be caused by features on the opposite face of the surface. Sink marks typically occur in moldings with thicker sections or at locations opposite ribs, bosses, or internal fillets. These results do not indicate sink marks caused by locally thick regions. From the analysis, along the shaft where the thickness variations are prominent, possible sinks are predicted (Figure 21). 4.3.2. Deflection and Warpage The deflection and warpage results (Figure 22) show how the part deflects from the originally designed shape. These mainly occur due to drastic differences in temperature at different part locations. This result helps design an appropriate cooling system and vary the design of the part to minimize defects during fabrication. Along the edge region, more even cooling is desired. 4.3.3. Volumetric Shrinkage at Ejection The volumetric shrinkage at ejection (Figure 23) decreases local volume from the end of the cooling stage to when the part has cooled to the ambient reference temperature, which shows the volumetric shrinkage for each area expressed as a percent of the original modeled volume" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001044_a8fa772056d4fd55d520-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001044_a8fa772056d4fd55d520-Figure5-1.png", + "caption": "Fig. 5. Main plate support frame configuration. (Color online only) Fig. 6. M2 struts frame configuration. (Color online only)", + "texts": [ + " After curing in the autoclave, the sandwich panel is machined to the designed configurations and the inserts are potted into the panel with EA9394 adhesive glue. The Main Plate and M2 Support Ring honeycomb panel manufacturing process is illustrated in Fig. 4. The Main Plate Support Frame is the mechanical interface for the telescope structure and Top Panel. This frame supports the Main Plate at two edge interfaces, left and right hand sides, and is made of CFRP tubes with glued INVAR material end fittings and angle brackets at the Main Plate interface. The Main Plate Support Frame is mounted onto the Top Panel. This configuration is shown in Fig. 5. There are two INVAR material supporters to support the M2 Support Ring due to RSI stiffness considerations. There are six (6) CFRP tubes that compose the M2 Struts Frame. Each tube is equipped with two titanium interface fittings on both ends. There are twelve (12) interface fittings in the M2 Struts Frame. This frame is mounted onto the Main Plate with three (3) interface fittings and M2 Support Ring supports through three (3) interface brackets. The M2 Struts Frame configuration is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003536_830_81_15-00138__pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003536_830_81_15-00138__pdf-Figure7-1.png", + "caption": "Fig. 7 Summary of the bearing and preload ring, showing", + "texts": [], + "surrounding_texts": [ + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n4\u30fb2 \u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5916\u5f84\u306e\u8a2d\u8a08 \u76ee\u6a19\u30c8\u30eb\u30af 20[N\u30fbm]\u3092\u4f1d\u9054\u3059\u308b\u305f\u3081\u306e\u30c8\u30e9\u30af\u30b7\u30e7\u30f3\u529b\u3092\u5f97\u308b\u305f\u3081\u306b\uff0c\u5916\u8f2a\u713c\u5d4c\u3081\u306b\u3088\u308a\u8ef8\u53d7\u5185\u90e8\u306b\u4e88\u5727\u3092\u52a0\u3048 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\u306f\u30e9\u30b8\u30a2\u30eb\u8377\u91cd\u3067\u3042\u308a\uff0cd=30.0[mm]\uff0cD=72.0[mm]\uff0cB=19.0[mm]\uff0cFr=213[N]\u3067\u3042\u308b\uff0e\u307e \u305f\uff0c\u56f3 7\u306b\u305d\u306e\u5b9a\u7fa9\u3092\u793a\u3059\uff0e\na 3 D D\nD D \n \uff0812\uff09\nia DDD \uff0813\uff09\n3 rF 1008.0 F\nB\nd D \uff0814\uff09\nFeff DDD \uff0815\uff09\n\u4e88\u5727\u30ea\u30f3\u30b0\u3068\u8ef8\u53d7\u5916\u8f2a\u9593\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394Deff\u304b\u3089\uff0c\u8ef8\u53d7\u5185\u5916\u8f2a\u3068\u8ee2\u52d5\u4f53\u9593\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394 \u306e\u8a08\u7b97\u3092\u884c\u3063\u305f\uff0e\u305d \u306e\u969b\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u713c\u5d4c\u3081\u306b\u3088\u308b\u8ef8\u53d7\u5916\u8f2a\u8ecc\u9053\u5f84\u306e\u53ce\u7e2e\u91cf \u03b4f\u3092\u5f0f(16)\u3088\u308a\uff0c\u904b\u8ee2\u6642\u306e\u8ef8\u53d7\u5185\u5916\u8f2a\u306e\u6e29\u5ea6\u5dee\u306b\u3088\u308b \u8ef8\u53d7\u5185\u90e8\u3059\u304d\u307e\u306e\u6e1b\u5c11\u91cf \u03b4t\u3092\u5f0f(17)\u3088\u308a\u8a08\u7b97\u3057\uff0c\u305d\u3053\u304b\u3089\u8ef8\u53d7\u5185\u5916\u8f2a\u3068\u8ee2\u52d5\u4f53\u9593\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u3092\u5f0f(18)\u3088\u308a\u8a08\u7b97 \u3092\u3057\u305f\uff0e\u3053\u3053\u3067De\u306f\u8ef8\u53d7\u5916\u8f2a\u8ecc\u9053\u5f84\uff0ch\u306f\u8ef8\u53d7\u5916\u8f2a\u8ecc\u9053\u5f84 De\u3068\u8ef8\u53d7\u5916\u8f2a\u5916\u5f84D\u306e\u6bd4\uff0cho\u306f\u8ef8\u53d7\u5916\u8f2a\u5916\u5f84D\u3068\u4e88 \u5727\u30ea\u30f3\u30b0\u5916\u5f84 Do\u306e\u6bd4\uff0c\u03b1 \u306f\u8ef8\u53d7\u92fc\u306e\u7dda\u81a8\u5f35\u4fc2\u6570\uff0c\u0394t \u306f\u904b\u8ee2\u6642\u306e\u8ef8\u53d7\u5185\u5916\u8f2a\u306e\u6e29\u5ea6\u5dee\uff0c\u03940\u306f\u8ef8\u53d7\u306e\u5143\u3005\u306e\u8ef8\u53d7\u5185 \u90e8\u3059\u304d\u307e\u3067\u3042\u308a\uff0c\u305d\u308c\u305e\u308cDe=62.5[mm]\uff0ch=De/D\uff0cho=D/Do\uff0c\u0394o=0.03175[mm]\uff0c\u03b1=12.5\u00d710-6 [1/\u2103](\u65e5\u672c\u7cbe\u5de5\u682a\u5f0f \u4f1a\u793e\uff0c2013)\u3067\u3042\u308a\uff0c\u0394t=5[\u2103]\u3068\u4eee\u5b9a\u3057\u3066\u8a08\u7b97\u3057\u305f\uff0e\u307e\u305f\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84 Di\u3068\u4e88\u5727\u30ea\u30f3\u30b0\u5916\u5f84 Do\u3092\u5909\u5316\u3055\u305b\u308b \u3053\u3068\u3067\uff0c\u8ef8\u53d7\u5185\u90e8\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\uff08\u4e88\u5727\u91cf\uff09\u306e\u8a2d\u8a08\u3092\u884c\u3046\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\n2 o 2\n2 o\nefff 1\n1\nhh\nh hD\n\n \uff0816\uff09\net tD \uff0817\uff09\n tf0 \uff0818\uff09\n\u5916\u8f2a\u713c\u5d4c\u3081\u306b\u3088\u3063\u3066\u8ef8\u53d7\u5916\u8f2a\u306b\u306f\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03b6t max\u304c\u767a\u751f\u3059\u308b\uff0e\u8ef8\u53d7\u306e\u7cbe\u5ea6\u3084\u5f37\u5ea6\u306e\u95a2\u4fc2\u304b\u3089\u8ef8\u53d7\u5916\u8f2a\u306b\u52a0\u308f \u308b\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03b6t max\u306f\u7d04 127[MPa]\u4ee5\u4e0b\u306b\u6291\u3048\u308b\u306e\u304c\u597d\u307e\u3057\u3044\u3068\u3055\u308c\u3066\u3044\u308b (\u65e5\u672c\u7cbe\u5de5\u682a\u5f0f\u4f1a\u793e\uff0c2013)\uff0e\u305d\u3053\u3067 \u672c\u7814\u7a76\u3067\u306e\u5916\u8f2a\u713c\u5d4c\u3081\u306b\u3088\u3063\u3066\u8ef8\u53d7\u5916\u8f2a\u306b\u767a\u751f\u3059\u308b\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03b6t max\u3092\u4ee5\u4e0b\u306e\u5f0f(19)\u3068(20)\u3088\u308a\u8a08\u7b97\u3057\u305f(\u65e5\u672c\u7cbe \u5de5\u682a\u5f0f\u4f1a\u793e\uff0c2013)\uff0e\u3053\u3053\u3067\uff0cEe\u3068 Eh\u306f\u8ef8\u53d7\u92fc\u3068\u30af\u30ed\u30e0\u30e2\u30ea\u30d6\u30c7\u30f3\u92fc\uff08\u4e88\u5727\u30ea\u30f3\u30b0\uff09\u306e\u7e26\u5f3e\u6027\u4fc2\u6570\uff0cme\u3068 mh\u306f\u8ef8 \u53d7\u92fc\u3068\u30af\u30ed\u30e0\u30e2\u30ea\u30d6\u30c7\u30f3\u92fc\u306e\u30dd\u30a2\u30bd\u30f3\u6570\u3067\uff0c\u305d\u308c\u305e\u308c Ee=Eh=208000[MPa]\uff0cme=mh=3.33 \u3092\u7528\u3044\u305f\uff0e", + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n \n \n2 oh 2 e\n2\nhh\nh\nee\ne\nm\n1\n1\n1 2\n11\n1\nhEhE\nh\nEm\nm\nEm\nmD\nD p \uff0819\uff09\n2mmaxt 1\n2\nh p \uff0820\uff09\n\u4e88\u5727\u30ea\u30f3\u30b0\u5916\u5f84Do=86.0[mm]\u306e\u3068\u304d\u306e\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84Di\u3068\u5916\u8f2a\u5185\u5f84\u9762\u306e\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03c3t max\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u306e\u95a2 \u4fc2\u3092\u56f3 8\u306b\u793a\u3059\uff0e\u3053\u3053\u3067\uff0c\u56f3 8\u306e a\uff0cA\u306f\u88fd\u4f5c\u6642\u306e\u516c\u5dee\u304c\u7121\u3044\u5834\u5408\u306e\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03c3t max\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u3067\u3042\u308a\uff0cb\uff0c B\u306f\u88fd\u4f5c\u6642\u306e\u516c\u5dee\u306b\u3088\u308a\u4e88\u5727\u91cf\u304c\u904e\u5927\u3068\u306a\u308b\u5834\u5408\uff0cc\uff0cC\u306f\u88fd\u4f5c\u6642\u306e\u516c\u5dee\u306b\u3088\u308a\u4e88\u5727\u91cf\u304c\u904e\u5c0f\u3068\u306a\u308b\u5834\u5408\u306e\u5186\u5468\u65b9 \u5411\u5fdc\u529b \u03c3t max\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u3092\u793a\u3059\uff0e\u307e\u305f\uff0c\u56f3 8\u4e2d\u3067\u306f\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03c3t max \u3092\u793a\u3059 a\u3068 b\u304c\u91cd\u306a\u3063\u3066\u3044\u308b\uff0e\n\u307e\u305a\uff0c\u516c\u5dee\u304c\u7121\u3044\u5834\u5408\uff0c\u76ee\u6a19\u30c8\u30eb\u30af 20[N\u30fbm]\u3092\u4f1d\u9054\u3059\u308b\u306b\u306f\u56f3 6\u3088\u308a\u6709\u52b9\u7de0\u3081\u4ee3 \u0394=-0.0077[mm]\u4ee5\u4e0b\u3067\u3042\u308c\u3070 \u3088\u3044\u306e\u3067\uff0c\u56f3 8 \u4e2d\u306e a\uff0cA(\u5b9f\u7dda\u90e8)\u3088\u308a\u4e88\u5727\u30ea\u30f3\u30b0\u5916\u5f84 Do\u304c 86.0[mm]\u3067\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84 Di\u304c 71.93[mm]\u3067\u3042\u308c\u3070 \u826f\u3044\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84 Di\u3092 71.93[mm]\u3068\u3059\u308b\u3068\u6700\u7d42\u7684\u306b\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394=-0.0084[mm]\u3068\u306a\u3063\u305f\uff0e\u3053 \u306e\u3068\u304d\u306e\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03c3t max\u306f 123.3[MPa]\u3067\u304b\u3064\u5727\u7e2e\u5fdc\u529b\u306b\u306a\u308b\u306e\u3067\uff0c\u8ef8\u53d7\u306e\u53c2\u8003\u8a31\u5bb9\u5024 127[MPa]\u4ee5\u4e0b\u3092\u6e80\u305f\u3059 \u3053\u3068\u3082\u3067\u304d\u308b\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u672c\u7814\u7a76\u3067\u306f\u4f7f\u7528\u3059\u308b\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u5185\u5916\u5f84\u306f\uff0cDi=71.93[mm]\uff0cDo=86.0[mm]\u3068\u3057\u305f\uff0e \u307e\u305f\uff0c\u672c\u5b9f\u9a13\u3067\u4f7f\u7528\u3057\u305f\u8ef8\u53d7\u5bf8\u6cd5\u3067\u306f\uff0c\u4e00\u822c\u7684\u306b\u8ef8\u53d7\u5185\u90e8\u3059\u304d\u307e \u0394o\u306e\u516c\u5dee\u306f\u00b12[\u00b5m]\uff0c\u8ef8\u53d7\u5916\u8f2a\u5916\u5f84 D\u306e\u516c\u5dee\u306f \uff0d7\uff5e0[\u00b5m]\u7a0b\u5ea6\u3068\u8a00\u308f\u308c\u3066\u3044\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u516c\u5dee\u306b\u3088\u308a\u4e88\u5727\u91cf\u304c\u904e\u5927\u3068\u306a\u308b\u5834\u5408(\u8ef8\u53d7\u5185\u90e8\u3059\u304d\u307e\u0394o=0.02975[mm]\uff0c \u8ef8\u53d7\u5916\u8f2a\u5916\u5f84D=72[mm])\u3067\u306f\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03c3t max\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u306f b\uff0cB(\u7834\u7dda\u90e8)\u3068\u306a\u308a\uff0c\u4e88\u5727\u91cf\u304c\u904e\u5c0f\u3068\u306a\u308b\u5834\u5408 (\u8ef8\u53d7\u5185\u90e8\u3059\u304d\u307e \u0394o=0.03375[mm]\uff0c\u8ef8\u53d7\u5916\u8f2a\u5916\u5f84 D=71.993[mm])\u3067\u306f c\uff0cC(\u70b9\u7dda\u90e8)\u3068\u306a\u308b\uff0e\u3053\u308c\u3088\u308a\uff0c\u4f8b\u3048\u3070\u6709\u52b9 \u7de0\u3081\u4ee3 \u0394=\uff0d0.0077[mm]\u4ee5\u4e0b\u3092\u6e80\u305f\u3059\u305f\u3081\u306b\u306f\uff0c\u4e88\u5727\u91cf\u304c\u904e\u5927\u3068\u306a\u308b\u5834\u5408\u306f 71.93mm\uff0c\u4e88\u5727\u91cf\u304c\u904e\u5c0f\u3068\u306a\u308b\u5834\u5408 \u306f 71.92mm\u306e\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84 Di\u3092\u9078\u5b9a\u3059\u308c\u3070\u826f\u3044\uff0e\u306a\u304a\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84 Di\u306e\u516c\u5dee\u7bc4\u56f2\u306f\u7814\u78e8\u52a0\u5de5\u3067\u00b10.01[mm] \u3067\u3042\u308b\uff0e\nthe dimensions of the inner and outer rings of the bearing and preload ring. A difference between the outer diameter of the outer ring of the bearing and the inner diameter of the preload ring will interfere with the appearance.\ninterference; the relationship between the inner diameter of the preload ring and the circumferential stress is shown. The relationship between the inner diameter of the preload ring and the effective interference is also indicated. The effective interference must be less than \u22120.008 mm to transmit the target torque. Then, the preload ring inner diameter will be 71.93 mm and the circumferential stress will be 122.5 MPa when there is no tolerance.", + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\ni\na\n'\n03.0\nD\nD T\n\n \uff0821\uff09\n\u8a08\u7b97\u3092\u884c\u3063\u305f\u7d50\u679c\uff0c\u5916\u8f2a\u713c\u5d4c\u3081\u6642\u306b\u5fc5\u8981\u306a\u5186\u7b52\u3053\u308d\u8ef8\u53d7\u3068\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u6e29\u5ea6\u5dee\u306f\u0394T=124.1[\u2103]\u3067\u3042\u308b\u3053\u3068\u304c\u308f \u304b\u3063\u305f\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u672c\u7814\u7a76\u3067\u306f\u5186\u7b52\u3053\u308d\u8ef8\u53d7\u6e29\u5ea6\u306f\u5e38\u6e29\u306e\u307e\u307e\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u307f\u3092\u7d04 150[\u2103]\u307e\u3067\u52a0\u71b1\u3057\u3066\u5916\u8f2a \u713c\u5d4c\u3081\u3092\u884c\u3063\u305f\uff0e\u3053\u306e\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u307f\u3092\u52a0\u71b1\u3059\u308b\u65b9\u6cd5\u3067\u3042\u308b\u3068\u5186\u7b52\u3053\u308d\u8ef8\u53d7\u81ea\u4f53\u306f\u52a0\u71b1\u3059\u308b\u5fc5\u8981\u304c\u306a\u3044\u306e\u3067\uff0c\u5186 \u7b52\u3053\u308d\u8ef8\u53d7\u81ea\u4f53\u306e\u7cbe\u5ea6\u3092\u7dad\u6301\u3057\u306a\u304c\u3089\u88c5\u7f6e\u3092\u7d44\u7acb\u3066\u308b\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\n5. \u8a66\u9a13\u88c5\u7f6e\u8a2d\u8a08\n5\u30fb1 \u4fdd\u6301\u5668\u30fb\u51fa\u529b\u8ef8\u306e\u5f37\u5ea6\u8a2d\u8a08 \u51fa\u529b\u8ef8\u3068\u4e00\u4f53\u5316\u3057\u305f\u4fdd\u6301\u5668\u306f\uff0c\u5143\u3005\u8ef8\u53d7\u306b\u88c5\u7740\u3055\u308c\u3066\u3044\u308b\u4fdd\u6301\u5668\u3092\u53d6\u308a\u5916\u3057\u305f\u5f8c\uff0c\u8ef8\u53d7\u306b\u5dee\u3057\u8fbc\u3080\u3060\u3051\u3067\u4f7f\u7528 \u3067\u304d\u308b\u3088\u3046\u306b\u7247\u5074\u306e\u7a7a\u9593\u306f\u958b\u653e\u3057\u305f\uff0e\u6750\u8cea\u306f\u8ee2\u52d5\u4f53\u3068\u4fdd\u6301\u5668\u90e8\u5206\u304c\u3059\u3079\u308a\u63a5\u89e6\u3059\u308b\u3053\u3068\u3092\u8003\u616e\u3057\uff0c\u306a\u3058\u307f\u6027\u306e\u826f \u3044\u30ea\u30f3\u9752\u9285\u3092\u9078\u5b9a\u3057\u305f\uff0e\u5f37\u5ea6\u8a08\u7b97\u3068\u3057\u3066\uff0c\u4fdd\u6301\u5668\u722a\u90e8\u306e\u66f2\u3052\uff0c\u8ef8\u306e\u306d\u3058\u308c\u306b\u3088\u308b\u6700\u5c0f\u8ef8\u5f84\u306a\u3069\u3092\u8a08\u7b97\u3057\u305f\uff0e\u307e\u305a\uff0c \u4fdd\u6301\u5668\u306e\u722a\u90e8\u306b\u306f\u56f3 9\u306b\u793a\u3059\u3088\u3046\u306b\u8377\u91cd\u304c\u4f5c\u7528\u3057\u3066\u3044\u308b\u3068\u3057\u3066\uff0c\u56f3 10\u306e\u3088\u3046\u306b\u4fdd\u6301\u5668\u722a\u90e8\u306e\u5f62\u72b6\u3092\u7c21\u7565\u5316\u3057\uff0c\u7247 \u6301\u3061\u6881\u306e\u8a08\u7b97\u5f0f\u304b\u3089\u66f2\u3052\u5fdc\u529b\u3092\u8a08\u7b97\u3057\u305f\uff0e\u56fa\u5b9a\u7aef\u304b\u3089\u8ddd\u96e2 L1 \u96e2\u308c\u305f\u8377\u91cd\u304c\u4f5c\u7528\u3059\u308b\u66f2\u3052\u30e2\u30fc\u30e1\u30f3\u30c8 M \u3092\u5f0f(22) \u304b\u3089\u7b97\u51fa\u3059\u308b\uff0e\u5f0f\u4e2d\u306e\u8377\u91cd Q \u306f\u51fa\u529b\u30c8\u30eb\u30af 20[N\u30fbm]\u3067\u904b\u8ee2\u3057\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394=-0.0084[mm]\u4e0e\u3048\u305f\u5834\u5408\u306e Qmax\u306e \u5024 595.2[N]\u3092\u7528\u3044\u3066\u5f0f(23)\u304b\u3089\u7b97\u51fa\u3057\u305f\uff0e\u3053\u3053\u3067\uff0c\u8ee2\u52d5\u4f53\u304c\u4fdd\u6301\u5668\u722a\u90e8\u3092\u62bc\u3059\u529b Q \u306f\u4e00\u822c\u7684\u306a\u30c8\u30e9\u30af\u30b7\u30e7\u30f3\u4fc2\u6570 \u03bc=0.1\u3092\u4ee3\u5165\u3057\u3066 119.0[N]\u3067\u3042\u308a\uff0c\u307e\u305f\u30dd\u30b1\u30c3\u30c8\u6570 Z\u306f 8\u500b\u3067\uff0c\u56fa\u5b9a\u7aef\u304b\u3089\u306e\u8ddd\u96e2 L1=9.5[mm]\u3068\u3057\u305f\uff0e\n1LQM \uff0822\uff09\nmax2 QQ \uff0823\uff09\nwhen the rolling element pushes the retainer bar is 111.9 N. The traction coefficient at that time is 0.1. The distance from the fixed end of the cantilever is 9.5 mm, the width \u201cb\u201d is 4 mm, and the height \u201ch\u201d is 8 mm.\n4\u30fb3 \u88fd\u4f5c\u6642\u306e\u713c\u5d4c\u3081\u6e29\u5ea6 \u5916\u8f2a\u713c\u5d4c\u3081\u6642\u306b\u4e88\u5727\u30ea\u30f3\u30b0\u3092\u52a0\u71b1\u3057\u3066\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84\u3092\u81a8\u5f35\u3055\u305b\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\u305d\u3053\u3067\uff0c\u305d\u306e\u969b\u306b\u5fc5\u8981\u306a\u5186\u7b52 \u3053\u308d\u8ef8\u53d7\u3068\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u6e29\u5ea6\u5dee \u0394T \u3092\u4ee5\u4e0b\u306e\u5f0f(21)\u3088\u308a\u8a08\u7b97\u3092\u884c\u3063\u305f\uff0e\u3053\u3053\u3067\uff0c\u03b1'\u306f\u30af\u30ed\u30e0\u30e2\u30ea\u30d6\u30c7\u30f3\u92fc\u306e\u7dda\u81a8\u5f35 \u4fc2\u6570\u3067\u3042\u308a\uff0c\u03b1'=11.2\u00d710-6[1/\u2103]\u3067\u3042\u308b(\u65e5\u672c\u91d1\u5c5e\u5b66\u4f1a\u7de8\uff0c2004)\uff0e\n\u56f3 10 \u306b\u793a\u3057\u305f\u4fdd\u6301\u5668\u722a\u90e8\u306e\u5f62\u72b6\u304b\u3089\u5f0f(24)\u3092\u7528\u3044\u3066\u65ad\u9762\u4fc2\u6570 Z '\u3092\u6c42\u3081\uff0c\u66f2\u3052\u30e2\u30fc\u30e1\u30f3\u30c8 M \u3068\u65ad\u9762\u4fc2\u6570 Z '\u304b\u3089 \u5f0f(25)\u3088\u308a\u516c\u79f0\u66f2\u3052\u5fdc\u529b \u03b6M\u3092\u8a08\u7b97\u3057\u305f\uff0e\u3053\u3053\u3067\uff0c\u9577\u65b9\u5f62\u306e\u5e45 b \u3068\u9ad8\u3055 h \u306f\uff0c\u305e\u308c\u305e\u308c b=4[mm]\uff0ch=8[mm]\u3067\u3042\u308b\uff0e" + ] + }, + { + "image_filename": "designv8_17_0004121_8_14_8_14_8_387__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004121_8_14_8_14_8_387__pdf-Figure5-1.png", + "caption": "Fig. 5 Picture of the two-wheeled vehicle", + "texts": [], + "surrounding_texts": [ + "\u85e4 \u672c \u30fb\u77f3\u5ddd \u30fb\u6749 \u6c5f:\u4e00 \u822c \u5316\u6b63 \u6e96\u5909 \u63db \u3092\u7528 \u3044\u305f\u5b89 \u5b9a\u5316 \u6cd5\u306e \u30ed\u30d0 \u30b9 \u30c8\u6027 \u306b\u95a2\u3059 \u308b\u8003\u5bdf 391\n\u5b9a \u3059 \u308b \u3068,(28)\u5f0f \u306e \u3088 \u3046 \u306b\u8a18 \u8ff0 \u3067 \u304d,\u5b9f \u969b \u306e \u30e2 \u30c7 \u30eb\u5316 \u8aa4 \u5dee \u3092\u6301 \u3064 \u30b7 \u30b9 \u30c6 \u30e0 \u306e \u591a \u304f\u306f \u3053\u306e \u5f62 \u3067 \u8868 \u3055 \u308c \u3066 \u3044 \u308b \u3068\u8003 \u3048 \u3089 \u308c \u308b.\n\u3044 \u307e,(28)\u5f0f \u306b(6)\u5f0f \u306b\u5bfe \u3057\u3066\u6c42 \u307e \u308b \u30d5 \u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u5247\n(10)\u5f0f \u3092\u7528 \u3044,\u3055 \u3089 \u306bq=S(\u2202H/\u2202P)T=S(\u2202H/\u2202P)T \u306e \u95a2 \u4fc2 \u304b \u3089q, p\u305d \u308c \u305e \u308c \u306b\u3064 \u3044 \u3066 \u66f8 \u304d\u4e0b \u3059.\n(30)\n\u305f \u3060 \u3057S\u2020:=(STS)-1ST\u306fS\u306e \u7591 \u4f3c \u9006 \u884c \u5217 \u3067 \u3042 \u308b.\u307e \u305fU\u306fq\u306e \u307f \u306b\u4f9d \u5b58 \u3059 \u308b \u95a2 \u6570 \u306a \u306e \u3067H+U\u306f,\n(31)\n\u3067\u3042\u308b.\u3053 \u3053\u3067\u30e2\u30c7\u30eb\u5316\u8aa4\u5dee\u304c\u306a\u3051\u308c\u3070,(31)\u5f0f \u306e\u53f3\u8fba\n\u7b2c\u4e00\u9805\u306f\u8ca0 \u307e\u305f\u306f\u96f6,\u53f3 \u8fba\u7b2c\u4e8c\u9805\u304c\u96f6 \u3088\u308a,H+U\u22660\n\u3068\u306a \u308a,\u30d5 \u30a3\u30fc \u30c9\u30d0 \u30c3\u30af\u7cfb\u306f\u5b89\u5b9a\u3067\u3042\u308b.\u3057 \u304b\u3057,\u30e2 \u30c7 \u30eb\u5316\u8aa4\u5dee\u304c\u3042\u308b\u5834\u5408\u306b\u306f,H+U\u22660\u3068 \u306a\u3089\u306a\u3044.\n4.2.1 \u5b89\u5b9a\u6027\u306e\u5341\u5206\u6761\u4ef6 \u30e2\u30c7\u30eb\u5316\u8aa4\u5dee\u304c\u3042\u308b\u30b7\u30b9\u30c6\u30e0\u306b\u5bfe \u3057\u3066,\u516c \u79f0\u30e2\u30c7\u30eb \u3068\n\u540c\u3058U,\u03b2 \u3067\u6b63\u6e96\u5909\u63db\u3092\u65bd \u3057\u305f \u3068\u3059\u308b.\u3044 \u307e,\u3053 \u306eU,\n\u03b2\u304c\u5b9f\u969b\u306e\u7cfb\u306b\u5bfe \u3057\u3066\u3082\u6642\u4e0d\u5909 \u306a\u5ea7\u6a19\u5909\u63db \u3092\u6301\u3064\u4e00\u822c\u5316 \u6b63\u6e96\u5909\u63db\u3067\u3042\u308b\u3068\u4eee\u5b9a\u3059\u308b,\u3059 \u306a\u308f\u3061(3)\u5f0f \u304c\u6642\u4e0d\u5909\u306a \u5ea7\u6a19\u5909\u63db \u3092\u6301\u3064\u3068\u3059\u308b.\u3053 \u306e\u4eee\u5b9a\u306f,\u516c \u79f0\u30e2\u30c7\u30eb\u3068\u540c\u69d8 H+U\u304c \u5b9f\u969b\u306e\u7cfb\u306b\u5bfe \u3057\u3066\u3082storage\u95a2 \u6570\u3068\u306a\u308b\u3053\u3068\u3092 \u610f\u5473\u3059\u308b.\u3053 \u306e\u6761\u4ef6\u306f(3)\u5f0f \u3088\u308a\n(32)\n\u3068\u306a\u308b.\u3053 \u308c\u3092(31)\u5f0f \u306b\u4ee3\u5165\u3059\u308b\u3068\u53f3\u8fba\u7b2c\u4e8c\u9805 \u76ee\u304c0\u3068\n\u306a\u308a,H+U\u3092storage\u95a2 \u6570 \u3068\u3057\u3066\u53d7\u52d5\u7684\u3068\u306a\u308b\u3053\u3068\u304c\n\u78ba\u8a8d\u3067\u304d\u308b.\u3088 \u3063\u3066\u516c\u79f0\u30e2\u30c7\u30eb \u3068\u540c\u3058\u88dc\u511f\u5668\u3092\u7528\u3044\u305f\u5834 \u5408\u3067\u3082\u5b89\u5b9a\u6027\u304c\u4fdd\u8a3c\u3055\u308c\u308b.\n\u3064\u304e\u306b\u30b7\u30b9\u30c6\u30e0\u306e\u6f38\u8fd1\u5b89\u5b9a\u6027\u306b\u3064\u3044\u3066\u8003\u5bdf\u3059\u308b.\u672c \u624b\n\u6cd5\u3067\u306f\u4e00\u822c\u5316\u6b63\u6e96\u5909\u63db\u3059\u308b\u969b,\u88dc \u984c1\u3092 \u9069\u7528 \u3057\u5165\u51fa\u529b\u96f6 \u5316\u96c6\u5408 \u3092\u7279\u5b9a \u3057\u3066\u305d\u306e\u9818\u57df \u3092\u4e0d\u5b89\u5b9a\u5316\u3059\u308b\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\n\u3092\u7528\u3044\u3066\u6f38\u8fd1\u5b89\u5b9a\u5316\u3092\u9054\u6210 \u3057\u3066\u3044\u308b.\u3044 \u307e,\u30e2 \u30c7\u30eb\u5316\u8aa4 \u5dee\u304c\u3042\u308b\u30b7\u30b9\u30c6\u30e0\u306b\u5bfe \u3057\u3066,\u516c \u79f0\u30e2\u30c7\u30eb\u3068\u540c\u3058\u5ea7\u6a19\u5909\u63db \u3092\u6301\u3064\u4e00\u822c\u5316\u6b63\u6e96\u5909\u63db\u3092\u65bd\u3059\u3068\u5165\u51fa\u529b\u96f6\u5316\u96c6\u5408\u304c\u516c\u79f0\u30e2\n\u30c7\u30eb \u3068\u306f\u7570\u306a\u3063\u305f\u96c6\u5408\u306b\u306a \u308a,\u540c \u3058\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u3067\u306f\u6f38 \u8fd1\u5b89\u5b9a\u5316\u3067\u304d\u306a\u304f\u306a\u308b\u53ef\u80fd\u6027\u304c\u3042\u308b.\u3057 \u304b \u3057\u305d\u306e\u5834\u5408\u3067 \u3082,(28)\u5f0f \u306b\u516c\u79f0\u30e2\u30c7\u30eb\u3068\u540c \u3058\u5ea7\u6a19\u5909\u63db \u3092\u65bd \u3057\u3066\u69cb\u6210\u3055 \u308c\u305fS(\u03be)\u304c(7)\u5f0f \u306e\u3088\u3046\u306b\u5206\u5272\u3067 \u304d,\u3055 \u3089\u306b\u305d\u306e\u3068\u304d\u69cb\n\u6210 \u3055\u308c\u308bS2(\u03be)\u304c(8)\u5f0f \u3092\u6e80\u305f\u305b\u3070\u5165\u51fa\u529b\u96f6\u5316\u96c6\u5408\u304c\u4e00 \u81f4 \u3057,\u540c \u3058\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u3067\u6f38\u8fd1\u5b89\u5b9a\u5316\u304c\u9054\u6210 \u3055\u308c\u308b.\n\u4ee5\u4e0a\u306e\u8b70\u8ad6 \u3092\u307e\u3068\u3081\u308b\u3068\u6b21\u306e\u3088\u3046\u306b\u306a\u308b.\n\u3010\u547d\u984c1\u3011(28)\u5f0f \u306e\u30b7\u30b9\u30c6\u30e0\u304c\u6b21\u306e\u4e8c\u6761\u4ef6 \u3092\u6e80 \u305f\u3059\n\u3068\u4eee\u5b9a\u3059\u308b.\n(33)\n(34)\n\u305f\u3060\u3057S2\u306f \u4e00\u822c\u5316\u6b63\u6e96\u5909\u63db \u3057\u305f\u5f8c\u306e\u30b7\u30b9\u30c6\u30e0\u3092(7)\u5f0f \u306e \u3088\u3046\u306b\u5206\u89e3\u3059\u308b\u3053\u3068\u306b\u3088\u308a\u5f97 \u3089\u308c\u308b.\u3053 \u306e\u6642,(10)\u5f0f \u306e\n\u88dc\u511f\u5668\u306f(28)\u5f0f \u306e\u7cfb\u306e\u539f\u70b9 \u3092\u6f38\u8fd1\u5b89\u5b9a\u5316\u3059\u308b.\n4.2.2 \u4e8c\u8f2a\u8eca\u4e21\u306e\u30e2\u30c7\u30eb\u5316\u8aa4\u5dee\u3078\u306e\u9069\u7528 \u4e0a\u8a18 \u306e\u547d\u984c \u3092\u4e8c\u8f2a\u8eca\u4e21 \u306b\u9069\u7528\u3059\u308b.\u3053 \u3053\u3067\u306f\u8a2d\u8a08\u6642\n\u306b\u306f\u5b9a\u6570\u30d1 \u30e9\u30e1\u30fc\u30bf\u3092\u5de6\u53f3\u5bfe\u79f0 \u306b\u3057\u3066\u3044\u308b(rr=rl=r \u306a\u3069).\u5b9f \u30e2\u30c7\u30eb\u306e\u5b9a\u6570\u30d1 \u30e9\u30e1\u30fc\u30bf\u3092\u52b4.\u306a \u3069\u3013\u3067\u8868 \u3057, \u30ce\u30df\u30ca\u30eb\u5024 \u3068\u771f\u306e\u5024 \u3068\u306e\u6bd4 \u3092\u8868\u3059\u5b9a\u6570(a1\uff5ea8)\u3092 \u7528\u3044\n\u3066,rr=a1r, rl=a2r, wr=a3w, wl=a4w,m=a5m,\nj=a6j,ir=a7i,il=a8i,\u3067 \u3042 \u308b \u3068\u3059 \u308b.\n\u307e\u305a \u547d \u984c1\u306e(33)\u5f0f \u306e \u6761 \u4ef6 \u3092 \u4e8c\u8f2a \u8eca \u4e21 \u7cfb \u306b \u9069 \u7528 \u3059 \u308b. \u4e8c \u8f2a \u8eca \u4e21 \u306e \u5834 \u5408S=ST1, G=T2G\u3068 \u66f8 \u3051 \u308b \u306e \u3067 \u3053\u306e \u95a2\n\u4fc2 \u5f0f \u3092\u7528 \u3044 \u3066\u5b89 \u5b9a \u6027 \u306e \u6761 \u4ef6 \u3092\u66f8 \u304d\u76f4 \u3059 \u3068\n(35)\n\u3068 \u306a \u308b.\u305f \u3060 \u3057,\n(36)\n\u3067\u3042\u308b.\u3053 \u306e\u6761\u4ef6 \u3092\u5b9f\u969b\u306b\u8a08\u7b97 \u3057\u3066\u307f\u308b\u3068,\n(37)\n\u3068\u306a\u308b.\n\u6b21\u306b\u547d\u984c1\u306e(34)\u5f0f \u306e\u6761\u4ef6\u3092\u4e8c\u8f2a\u8eca\u4e21\u7cfb \u306b\u9069\u7528\u3059\u308b\u3068,\n(38)\n\u3057\u305f\u304c\u3063\u3066(34)\u5f0f \u306f\u5e38\u306b\u6210\u7acb\u3059\u308b.\u3088 \u3063\u3066\u3053\u306e\u7bc4\u56f2\u306e \u3069\u3093\u306a\u30d1 \u30e9\u30e1\u30fc\u30bf\u8aa4\u5dee\u304c\u3042\u308b\u5834\u5408\u3067\u3082\u5165\u51fa\u529b\u96f6\u5316\u96c6\u5408\u306f \u30ce\u30df\u30ca\u30eb\u30e2\u30c7\u30eb\u3068\u4e00\u81f4\u3059\u308b\u306e\u3067(24)\u5f0f \u306e\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u3092\n\u4ed8\u52a0\u3059\u308b\u3053\u3068\u3067\u6f38\u8fd1\u5b89\u5b9a\u5316\u3055\u308c\u308b.\n\u4ee5 \u4e0a\u304b\u3089\u4e8c\u8f2a\u8eca\u4e21\u306e\u7269\u7406\u30d1 \u30e9\u30e1\u30fc\u30bf\u306b\u8aa4\u5dee\u304c\u3042\u308b\u5834\u5408 \u3067\u3082,(37)\u5f0f \u304c\u6e80\u305f\u3055\u308c\u308b\u7bc4\u56f2\u3067\u3042\u308c\u3070\u6f38\u8fd1\u5b89\u5b9a\u6027\u304c\u4fdd\n\u8a3c\u3055\u308c\u308b.\u3053 \u306e\u6761\u4ef6\u5f0f \u306b\u306f,\u5e7e \u4f55\u5b66\u7684\u306a\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u307f \u3067,\u4e8c \u8f2a\u8eca\u306e\u8cea\u91cf,\u6163 \u6027\u30e2\u30fc\u30e1\u30f3 \u30c8,\u8eca \u8f2a\u306e\u8cea\u91cf,\u6163 \u6027 \u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u304c\u542b \u307e\u308c\u3066\u3044\u306a\u3044.\u3064 \u307e\u308a,\u5e7e", + "392 \u30b7\u30b9 \u30c6\u30e0\u5236\u5fa1 \u60c5 \u5831\u5b66 \u4f1a\u8ad6 \u6587\u8a8c \u7b2c14\u5dfb \u7b2c8\u53f7(2001)\n\u4f55\u5b66\u7684\u306a\u69cb\u9020\u3055\u3048\u6b63\u78ba \u306b\u8a2d\u8a08 \u3057\u3066\u304a\u3051\u3070,\u4ed6 \u306e\u8aa4\u5dee\u306f\u8a31 \u5bb9\u3067\u304d\u308b\u3068\u3044\u3046\u3053\u3068\u3067\u3042\u308b.\n5. \u5b9f \u9a13\n5.1 \u5b9f\u9a13\u88c5\u7f6e\u306e\u6982\u7565 \u672c\u5b9f\u9a13\u306b\u7528\u3044\u308b\u88c5\u7f6e\u306e\u69cb\u6210\u3092Fig. 4\u306b,\u4e8c \u8f2a\u8eca\u4e21\u306e\u5199\n\u771f\u3092Fig. 5\u306b \u793a\u3059.\u4e8c \u8f2a\u8eca\u4e21\u306e\u4f4d\u7f6e\u3068\u59ff\u52e2\u89d2\u306f,\u8eca \u4e21\u672c \u4f53\u306b\u4ed8\u3051\u305f\u4e8c\u3064\u306eLED\u306e \u4f4d\u7f6e\u3092\u7d043[m]\u306e \u9ad8\u3055\u306b\u53d6 \u308a\u4ed8 \u3051\u305f\u30dd\u30b8\u30b7\u30e7\u30f3\u30bb\u30f3\u30b5\u3067\u8aad\u307f\u53d6\u308b\u3053\u3068\u306b\u3088\u3063\u3066\u6e2c\u5b9a\u3059\u308b. \u5206\u89e3\u80fd\u306f2.5[mm], LED\u9593 \u306e\u8ddd\u96e2\u306f22[cm]\u3067 \u3042\u308b.\u4e8c \u3064\u306e\u8eca\u8f2a(\u8eca \u8f2a\u9593\u306e\u8ddd\u96e215[cm])\u306b \u306f\u305d\u308c\u305e\u308c\u72ec\u7acb \u3057\u305f \u30e2\u30fc\u30bf\u3068\u30a8 \u30f3\u30b3\u30fc\u30c0\u3092\u53d6 \u308a\u4ed8 \u3051,\u305d \u308c\u305e\u308c\u306e\u8eca\u8f2a(\u534a \u5f84\n4[cm])\u306e \u56de\u8ee2\u89d2\u3092\u6e2c \u308a,\u307e \u305f \u30c8\u30eb\u30af\u3092\u4e0e\u3048\u308b.\u901f \u5ea6\u60c5\u5831 \u306f\u30dd\u30b8\u30b7\u30e7\u30f3\u30bb\u30f3\u30b5\u306e\u60c5\u5831\u3092\u6570\u5024\u5fae\u5206 \u3057\u305f\u3082\u306e\u3067\u3042\u308b. \u306a\u304a,\u30b5 \u30f3\u30d7\u30ea\u30f3\u30b0\u30bf\u30a4\u30e0\u306f5[ms]\u3067 \u3042\u308b.\u3053 \u308c\u306f,\u30dd \u30b8\u30b7\u30e7\u30f3\u30bb\u30f3\u30b5\u306e\u4fe1\u53f7\u304c300[Hz]\u3067 \u9001 \u3089\u308c\u3066 \u304f\u308b\u305f\u3081\u306e\n\u5236\u7d04\u3067\u3042\u308b.\u307e \u305f,\u5165 \u529b\u5236\u7d04\u3068,\u8eca \u8f2a\u306e\u6ed1 \u308a\u3092\u304a\u3055\u3048\u308b \u305f\u3081\u901f\u5ea6\u306e\u5236\u7d04 \u3092\u4e0e\u3048\u3066\u3044\u308b.\n5.2 \u5b9f \u9a13 \u7d50 \u679c \u3068\u8003 \u5bdf\n\u5b9f \u9a13 \u3067 \u306f\u7279 \u306b\u89b3 \u6e2c \u30ce \u30a4 \u30ba \u306b\u5bfe \u3059 \u308b \u30ed\u30d0 \u30b9 \u30c8\u6027 \u306b\u3064 \u3044 \u3066\n\u691c \u8a3c \u3059 \u308b.\n5.2.1 \u5b9f \u9a131\n(24)\u5f0f \u306e\u4ed8 \u52a0 \u3059 \u308b \u30dd \u30c6 \u30f3\u30b7 \u30e3\u30eb \u306e\u30d1 \u30e9 \u30e1 \u30fc \u30bf \u3092C1=1,\nC2=1, C3=4, C4=1,\u72b6 \u614b \u30d6\u30a4\u30fc \u30c9\u30d0 \u30c3\u30af \u306e\u30d1 \u30e9 \u30e1 \u30fc\n\u30bf \u3092P=50I\u3068 \u3057\u3066,\u03b3 \u30920\uff5e3\u3068 \u5909 \u5316 \u3055\u305b \u5b9f \u9a13 \u3092\u884c \u3063 \u305f.\u03b3=0,3\u306b \u5bfe \u3059 \u308b\u7cfb \u306e \u5fdc \u7b54 \u306ez1-z2\u30b0 \u30e9 \u30d5(\u6a2a \u8ef8z1\n\u5ea7 \u6a19,\u7e26 \u8ef8z2\u5ea7 \u6a19 \u5358 \u4f4d[cm])\u3092 \u305d \u308c \u305e \u308cFig. 6, Fig. 7 \u306b, q\u306e \u6642 \u9593 \u5fdc \u7b54(\u6a2a \u8ef8 \u6642 \u9593[s],\u7e26 \u8ef8 \u914d \u4f4d \u5ea7 \u6a19,\u03b8:\u5b9f \u7dda 0.1[rad], z1:\u9396 \u7dda, z2:\u7834 \u7dda[cm])\u3092Fig. 8, Fig. 9\u306b\n\u793a \u3059.\n\u3053 \u308c \u3089\u306e \u7d50 \u679c \u304b \u3089, 4.1\u3067 \u884c \u3063 \u305f\u5916 \u4e71 \u306b\u5bfe \u3059 \u308b \u30ed\u30d0 \u30b9\n\u30c8\u6027 \u306e \u8003 \u5bdf \u306e \u3068\u304a \u308a \u03b3 \u304c\u5897 \u3059 \u3068\u89b3 \u6e2c \u30ce \u30a4\u30ba \u306e\u5f71 \u97ff \u3068\u601d \u308f\n\u308c \u308b\u539f \u70b9 \u8fd1 \u508d \u3067 \u306e \u632f \u52d5 \u304c\u5c0f \u3055 \u304f\u306a \u3063\u3066 \u3044 \u308b.\u306a \u304a \u03b3 \u304c3 \u4ee5 \u4e0a \u3067 \u306f \u3042 \u307e \u308a\u5909 \u5316 \u304c \u306a\u304b \u3063 \u305f.\n5.2.2 \u5b9f \u9a132 \u3064 \u304e \u306b\u5b9f \u6a5f \u3067\u4ed6 \u306e \u624b \u6cd5 \u3068\u306e \u6bd4 \u8f03 \u3092 \u304a \u3053 \u306a \u3063 \u305f .\u6bd4 \u8f03 \u3059 \u308b\u5bfe \u8c61 \u3068 \u3057\u3066 \u306f, Astolfi\u306e \u624b \u6cd5[8]\u306b \u30d0 \u30c3\u30af \u30b9 \u30c6 \u30c3 \u30d4 \u30f3\n3)", + "\u85e4\u672c \u30fb\u77f3\u5ddd \u30fb\u6749\u6c5f:\u4e00 \u822c\u5316\u6b63\u6e96\u5909\u63db\u3092\u7528\u3044\u305f\u5b89\u5b9a\u5316\u6cd5\u306e\u30ed\u30d0\u30b9 \u30c8\u6027\u306b\u95a2\u3059\u308b\u8003\u5bdf 393\n\u9593\u5fdc\u7b54 \u3092,\u305d \u308c\u305e\u308cFig. 10, Fig. 11\u306b \u793a\u3059.\u3053 \u306e\u6642\u306e \u30d1\u30e9\u30e1\u30fc\u30bf\u306f\u5b9f\u9a13\u3067\u306e\u8a66\u884c\u932f\u8aa4\u306b\u3088\u308b\u8abf\u6574\u3067\u6c7a\u5b9a \u3057\u305f.\n\u304b \u3057\u03b3\u304c3\u4ee5 \u4e0a\u3067\u306f\u3042\u307e\u308a\u5909\u5316\u304c\u306a\u304b\u3063\u305f\u306e\u306f, Fig. 3 \u3067\u4e0e \u3048\u3089\u308c\u308b\u3088\u3046\u306a(27)\u5f0f \u306e \u03c6\u306e\u5f62\u304c,\u03b3 \u304c3\u4ee5 \u4e0a\u3067 \u306f\u5927 \u304d\u304f\u5909\u5316 \u3057\u306a\u3044\u305f\u3081\u3060\u3068\u8003\u3048\u3089\u308c\u308b.\u5b9f \u9a132\u3067 \u306f, Astolfi\u306e \u624b\u6cd5\u306f\u539f\u70b9\u4ed8\u8fd1\u3067\u304b\u306a\u308a\u5fdc\u7b54\u304c\u66b4\u308c,\u89b3 \u6e2c\u30ce\u30a4 \u30ba\u306b\u5f31\u3044\u3053\u3068\u304c\u308f\u304b\u308b.\u3053 \u306e\u7d50\u679c\u306f,\u53c2 \u8003\u6587\u732e[7]\u306b \u8ff0 \u3079 \u3089\u308c\u3066\u3044\u308b\u4e0d\u9023\u7d9a\u88dc\u511f\u5668\u306f\u89b3\u6e2c\u30ce\u30a4\u30ba\u306b\u5f31\u3044\u3068\u3044\u3046\u7d50\n\u679c\u3068\u4e00\u81f4\u3059\u308b\u304c,\u672c \u624b\u6cd5\u3067\u306f\u3053\u306e\u6b20\u70b9\u304c\u6539\u5584\u3055\u308c\u3066\u3044\u308b\n\u3053\u3068\u304c\u308f\u304b\u308b.\u307e \u305fAstolfi\u306e \u624b\u6cd5\u3067\u306f\u304b\u306a \u308a\u306e\u504f\u5dee\u304c\n\u6b8b\u3063\u3066\u3044\u308b.\u3068 \u304f\u306b\u59ff\u52e2\u89d2\u306e\u504f\u5dee\u304c\u672c\u624b\u6cd5\u306b\u6bd4\u3079\u3066\u9855\u8457 \u3067\u3042\u308b.\u3055 \u3089\u306b,\u672c \u624b\u6cd5\u3067\u306fAstolfi\u306e \u624b\u6cd5\u306b\u6bd4\u3079\u53ce\u675f \u306e\u901f \u3055\u306b\u304a\u3044\u3066\u905c\u8272 \u306f\u306a\u3044.\u4ee5 \u4e0a\u306e\u3053\u3068\u304b \u3089,\u672c \u624b\u6cd5\u306f \u30ed\u30d0\u30b9 \u30c8\u6027\u306b\u512a\u308c\u304b\u3064\u5b9f\u7528\u4e0a\u53ce\u675f \u3082\u901f\u3044\u5b89\u5b9a\u5316\u624b\u6cd5\u3067\u3042\n\u308b\u3068\u8003 \u3048\u3089\u308c\u308b.\n6. \u304a \u308f \u308a\u306b\n\u672c\u8ad6\u6587\u3067\u306f\u5f93\u6765\u3088\u308a\u7b46\u8005\u3089\u304c\u63d0\u6848 \u3057\u3066\u3044\u308b\u4e00\u822c\u5316\u6b63\u6e96 \u5909\u63db \u306b\u57fa\u3065 \u304f\u975e\u30db\u30ed\u30ce\u30df\u30c3\u30af\u306a\u30cf \u30df\u30eb \u30c8\u30cb\u30a2\u30f3\u30b7\u30b9\u30c6\u30e0 \u306e\u5b89\u5b9a\u5316\u624b\u6cd5\u306e\u6709\u52b9\u6027\u306b\u3064\u3044\u3066,\u4e8c \u8f2a\u8eca\u4e21\u7cfb\u3092\u5bfe\u8c61\u3068\u3057\n\u3066\u30ed\u30d0\u30b9 \u30c8\u6027\u306e\u89b3\u70b9\u304b\u3089\u306e\u89e3\u6790 \u3068\u305d\u306e\u5b9f\u9a13\u691c\u8a3c\u3092\u884c\u3063\u305f. \u307e\u305a\u8a2d\u8a08\u30d1\u30e9\u30e1\u30fc\u30bf\u3067\u3042\u308b\u4e0d\u53ef\u5fae\u5206\u306a\u30dd\u30c6\u30f3\u30b7\u30e3\u30eb\u306e\u6982\n\u5f62 \u3068\u89b3\u6e2c\u5916\u4e71\u7b49 \u306b\u3088\u308b\u72b6\u614b\u306e\u6442\u52d5\u306b\u5bfe\u3059\u308b\u611f\u5ea6 \u3068\u306e\u95a2\u4fc2 \u3092\u8003\u5bdf \u3057\u305f.\u307e \u305f\u5236\u5fa1\u5bfe\u8c61\u306e\u53d7\u52d5\u6027 \u3092\u7528\u3044\u305f\u8003\u5bdf\u306b\u3088\u308a \u7269\u7406\u30d1\u30e9\u30e1\u30fc\u30bf\u5909\u52d5\u306b\u5bfe\u3059\u308b\u30ed\u30d0\u30b9 \u30c8\u5b89\u5b9a\u6027\u306e\u5341\u5206\u6761\u4ef6 \u3092\u4e0e \u3048\u305f.\u3055 \u3089\u306b\u5b9f\u9a13\u3092\u884c\u3044,\u4ed6 \u306e\u624b\u6cd5\u3068\u306e\u6bd4\u8f03 \u3092\u307e\u3058 \u3048\u3066\u63d0\u6848\u624b\u6cd5\u306e\u6709\u52b9\u6027\u3092\u691c\u8a3c \u3057\u305f.\n\u6700\u5f8c\u306b,\u672c \u8ad6\u6587\u306b\u5bfe \u3057\u3066\u6709\u76ca\u306a\u610f\u898b\u3092\u4e0b \u3055\u3063\u305f\u533f\u540d\u306e\n\u67fb\u8aad\u8005\u306e\u65b9\u3005\u306b\u611f\u8b1d\u306e\u610f \u3092\u8868 \u3057\u307e\u3059.\n\u53c2 \u8003 \u6587 \u732e\n[1] A.J. van der Schaft: L2-gain and passivity techniques in nonlinear control; Vol. 218 Lecture Notes in Control and Information Sciences, Springer-Verlag\n(1996) [2] \u85e4 \u672c,\u6749 \u6c5f:\u4e00 \u822c \u5316\u6b63\u6e96 \u5909\u63db \u3092\u7528 \u3044\u305f\u3042 \u308b\u30af \u30e9\u30b9 \u306e\u975e \u30db \u30ed\n\u30ce \u30df\u30c3\u30af\u7cfb \u306e\u5b89\u5b9a\u5316;\u8a08 \u6e2c \u81ea\u52d5 \u5236\u5fa1\u5b66 \u4f1a\u8ad6\u6587 \u96c6, Vol. 36, No. 9, pp. 749-756 (2000)\n[3] \u85e4 \u672c,\u6749 \u6c5f:\u4e00 \u822c\u5316 \u30cf \u30df\u30eb \u30c8\u30cb \u30a2 \u30f3\u30b7\u30b9 \u30c6\u30e0 \u306e\u5b89\u5b9a \u5316 \u2015\n\u6b63\u6e96\u5909 \u63db \u306b \u3088\u308b \u30a2\u30d7 \u30ed\u30fc\u30c1;\u30b7 \u30b9 \u30c6\u30e0\u5236\u5fa1 \u60c5\u5831 \u5b66\u4f1a\u8ad6 \u6587 \u8a8c, Vol. 11, No. 11, pp. 616-622 (1998)\n[4] K. Fujimoto and T. Sugie: Stabilization of Hamiltonian systems with nonholonomic constraints via canonical transformations; Proc. ECC (1999) [5] K. Fujimoto, K. Ishikawa and T. Sugie: Stabilization of a class of hamiltonian system with nonholonomic constraints and its experimental evaluation; Proc. IEEE CDC'99, pp. 3478-3483 (1999) [6] K. Fujimoto and T. Sugie: Canonical transformation and stabilization of generalized hamiltonian systems; Systems and Control Letters, 42, pp. 217-227 (2001)\n[7] \u4e09 \u5e73:\u975e \u30db \u30ed \u30ce \u30df \u30c3 \u30af\u7cfb \u306e \u30d5 \u30a3 \u30fc \u30c9\u30d0 \u30c3 \u30af\u5236 \u5fa1;\u8a08 \u6e2c \u3068\n\u5236 \u5fa1, Vol. 36, No. 6, pp. 396-403 (1997)\n[8] A. Astolfi: Discontinuous control of nonholonomic systems; Systems and Control Letters, 27, pp. 37-45\n(1996) [9] \u4e2d\u6751:\u975e \u30db \u30ed \u30ce \u30df \u30c3 \u30af \u30ed \u30dc \u30c3 \u30c8\u30b7 \u30b9 \u30c6 \u30e01-5\u56de;\u65e5 \u672c\n\u30ed \u30dc \u30c3 \u30c8\u5b66 \u4f1a \u8a8c, Vol. 11, Nos. 4, 5, 6, 7 (1993),\nVol. 12, No. 2 (1994)\n[10] R. Fierro and F.L. Lewis: Control of a nonholonomic mobile robot: Backstepping kinematics into dynam-" + ] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure17-1.png", + "caption": "Figure 17. The maximum stress simulation results for the front body mount are 0.17 MPa", + "texts": [ + " The simulation results obtained in bending moment, maximum stress, and displacement, respectively, have 893.86 N.mm, 0.19 MPa, and 0.00008 mm values. Figure 16 shows the simulation results of the maximum stress value on the driver's footrest. 5. Front body mount The front body mount receives a load of 4.2 kg acting in the y-axis direction. This part only consists of one rod to support the front body. The simulation results obtained are bending moment, maximum stress, and displacement, respectively, the values are 786.79 N.mm, 0.17 MPa, and 0.00006 mm. Figure 17 shows the simulation results of the maximum stress value on the driver's footrest. 6. Rollbar body mount The rollbar body mount receives a load of 16.8 kg acting in the y-axis direction. A horizontal bar profile is in the direction of the z axis. This part only consists of one rod to support the rollbar body. The results of the simulation obtained are bending moment, maximum stress, and displacement, respectively, the values are 8552.96 N.mm, 4.07 MPa, and 0.041 mm. Figure 18 shows the simulation results of the maximum stress value on the rollbar body mount" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004255_cle_download_175_155-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004255_cle_download_175_155-Figure7-1.png", + "caption": "Figure 7 Mesh distribution of aircraft and pneumatic impellers", + "texts": [ + " According to the structural characteristics of the aircraft and the impeller, the triangular mesh of the unstructured mesh is used and locally refined. When dividing, the whole computing domain is divided into two parts: one part is the rotation domain, which is the rotating region of the impeller, and the mesh number is 470,000; the other part is the static region, which is excluding the pneumatic impeller all the area, the grid number is 2.8 million. The static domain and the rotating domain transfer the data between the grids through the interface, and the distribution after mesh division is shown in Figure 7. To ensure accuracy, boundary conditions need to be set with velocity-inlet, outflow, wall (wind impeller is rotating wall, aircraft fuselage is stationary wall), and interface. The distance between the inlet surface and the aircraft is one length of fuselage, and the distance between the outlet surface and the aircraft is five lengths of fuselage. The speed and direction of wind energy are set on the velocity inlet surface, the rotating speed and direction of the impeller are set on the wall of the impeller, and the flow medium is set according to the ideal air" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003588_O201305740751996.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003588_O201305740751996.pdf-Figure6-1.png", + "caption": "Fig. 6. Effect of Slip stream", + "texts": [], + "surrounding_texts": [ + "QTW \ube44\ud589\uccb4\uc758 \ub3d9\uc5ed\ud559 \ubaa8\ub378\ub9c1\uc744 \uc704\ud574\uc11c\ub294 \ud56d \uacf5\uae30\uc758 \uc9c8\ub7c9\ubcc0\ud654\ub098 \uc9c8\ub7c9\ubd84\ud3ec\uc758 \ubcc0\ud654\uac00 \uc5c6\ub2e4\uace0 \uac00 \uc815\ud558\uace0 \ud56d\uacf5\uae30\uc5d0 \uc791\uc6a9\ud558\ub294 \uacf5\uae30\uc5ed\ud559\uc801 \ud798, \ucd94\ub825 \uc5d0 \uc758\ud55c \ud798, \uc911\ub825\uc5d0 \uc758\ud55c \ud798 \ub4f1\uc744 \uace0\ub824\ud55c\ub2e4. \ud56d\uacf5 \uae30\uc5d0 \uace0\uc815\ub418\uc5b4 \uc788\ub294 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\uac00 \uad00\uc131\uc88c\ud45c \uacc4\uc5d0 \ub300\ud574 \ud68c\uc804\ud558\uace0 \uc788\ub2e4\uace0 \uac00\uc815\ud558\uace0 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\uc5d0 \ub300\ud558\uc5ec \uac01\uc131\ubd84\ubcc4\ub85c \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc744 \uc815\ub9ac \ud558\uba74, Fig. 3\uacfc \uac19\uc774 \uc124\uacc4\ub41c \ube44\ud589\uccb4 \ud615\uc0c1\uc5d0 \ub300\ud574 6\uc790\uc720\ub3c4 \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc744 \uc5bb\uc744 \uc218 \uc788\ub2e4[6]. (1) (2) (3) (4) (5) (6) \uc704\uc758 \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc5d0\uc11c \ubaa8\ub4e0 \ud798\uacfc \ubaa8\uba58\ud2b8\ub294 \ud56d\uacf5\uae30 \uc5d0 \uc791\uc6a9\ud558\ub294 \uac01 \ubd80\ubd84\uc758 \ud798\uacfc \ubaa8\uba58\ud2b8\uc758 \ud569\uc73c\ub85c \ud45c \ud604\ud560 \uc218 \uc788\ub2e4. \u2211 (7) \u2211 (8) \uc5ec\uae30\uc11c \uc544\ub798\ucca8\uc790 \ub294 \uac01\uac01 \ud504\ub85c \ud3a0\ub7ec \ud6c4\ub958 \ubd80\ubd84\uc5d0\uc11c\uc758 Slip stream \ud6a8\uacfc\uc5d0 \uc758\ud574 \ubc1c\uc0dd\ub418\ub294 \uacf5\uae30\uc5ed\ud559\uc801 \ud798, \ud6c4\ub958\uc5d0 \uc7a0\uae30\uc9c0 \uc54a\ub294 \uc8fc \uc775 \uba74\uc801\uc5d0 \ub300\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798, \uadf8\ub9ac\uace0 \ud504\ub85c\ud3a0\ub7ec \uc5d0 \uc758\ud574 \ubc1c\uc0dd\ub418\ub294 \ucd94\ub825 \ubc0f \uc911\ub825\uc5d0 \uc758\ud55c \ud798\uc744 \ub098 \ud0c0\ub0b8\ub2e4. Fig. 4\ub294 \ud504\ub85c\ud3a0\ub7ec \ud6c4\ub958\uc5d0 \uc7a0\uae30\ub294 \uc8fc\uc775 \uba74\uc801\uacfc \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84\uc744 \ubcf4\uc5ec\uc8fc\uace0 \uc788\ub2e4. \uc774\ub7ec\ud55c \ubcf5\uc7a1\ud55c \ub3d9\uc5ed\ud559\uc801 \ud2b9\uc131\uc744 \ubd84\uc11d\ud558\uae30 \uc704 \ud558\uc5ec \ubcf8 \ub17c\ubb38\uc5d0\uc11c\ub294 QTW\uc758 \uc885\ucd95 \ubc18\uc751\ub9cc\uc744 \uace0\ub824 \ud558\uc600\uc73c\uba70 \ub864 \uc6b4\ub3d9\uacfc \uc694 \uc6b4\ub3d9\uc740 \uace0\uc815\ub418\uc5b4 \uc788\ub2e4\uace0 \uac00\uc815\ud558\uc600\ub2e4. \ub610\ud55c \ud68c\uc804\uc775 \ubaa8\ub4dc\uc640 \ucc9c\uc774\ubaa8\ub4dc \uc601\uc5ed \uc5d0\uc11c\uc758 \ud574\uc11d\uc744 \uc218\ud589\ud558\uc600\ub2e4. \ud504\ub85c\ud3a0\ub7ec\uc5d0 \uc758\ud55c \ucd94\ub825 \uac01 \ud504\ub85c\ud3a0\ub7ec\uc5d0 \ubc1c\uc0dd\ub418\ub294 \ucd94\ub825\uc740 Momentum Theory\ub97c \uae30\ucd08\ub85c \ud55c\ub2e4. Fig. 5\uc5d0\uc11c \ud504\ub85c\ud3a0\ub7ec\ub97c \uc9c0\ub098\ub294 \uacf5\uae30\ud750\ub984\uc744 \ud45c\ud604\ud558\uace0 \uc788\ub2e4. Momentum Theory\uc640 Bernoulli's Equation\uc744 \uc774\uc6a9\ud558\uc5ec \uc720\ub3c4\uc18d\ub3c4\uc640 \ucd94\ub825\uc744 \uacc4\uc0b0\ud55c\ub2e4. \ud504\ub85c\ud3a0\ub7ec \uae30\uc900\uc73c\ub85c z\ucd95\uc758 \uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \uae43 \ud615\uc0c1 \ub4f1\uc744 \uace0\ub824\ud55c \uc18d\ub3c4\uc640 \ucd94\ub825\uc740 \ub2e4\uc74c\uacfc \uac19\uc774 \ud45c\ud604\ub41c\ub2e4[7]. (9) \u221e (10) \uc2dd(9)\uc5d0\uc11c \ub294 \uac01\uac01 \ud504\ub85c\ud3a0\ub7ec\uc758 \ud68c\uc804\ub514\uc2a4\ud06c\uc5d0 \uc218\uc9c1\uc778 \ubc29\ud5a5\uc758 \uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \uac01\uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \ud68c\uc804\ub514\uc2a4\ud06c \ubc18\uc9c0\ub984, \ud504\ub85c\ud3a0\ub7ec \ub4a4\ud2c0\ub9bc \uc815\ub3c4\ub97c \ub098\ud0c0\ub0b4\ub294 \uc0c1\uc218\uc774\uba70 \uc2dd(10)\uc5d0\uc11c\uc758 \u221e \uc740 \uac01\uac01, \ud504\ub85c\ud3a0\ub7ec\ub97c \uc9c0\ub09c \ud6c4\ub958\uc758 \uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \uc591\ub825 \uae30\uc6b8\uae30, \ud504\ub85c\ud3a0\ub7ec\uc758 \ube14\ub808 \uc774\ub4dc \uc218, \ud504\ub85c\ud3a0\ub7ec \ucf54\ub4dc\uc758 \uae38\uc774\ub97c \ub098\ud0c0\ub0b8\ub2e4. \ud504\ub85c\ud3a0\ub7ec\ub97c \uc9c0\ub09c \uc720\ub3c4\uc18d\ub3c4 \ub294 \uc2dd(11)\uc640 \uac19\uc774 \ud45c\ud604\ub41c\ub2e4. \u221e \u2032 (11) \uc5ec\uae30\uc11c \u2032\ub294 \uc6d0\uac70\ub9ac \uc18d\ub3c4(Far-Field Velocity)\ub85c \uc2dd(12)\uc640 \uac19\uc774 \ub098\ud0c0\ub0bc \uc218 \uc788\ub2e4. \u2032 (12) \uc2dd(11)\ub97c \uc2dd(13)\uc758 Newton-Raphson method \ubc18 \ubcf5 \uae30\ubc95\uc744 \uc0ac\uc6a9\ud558\uc5ec \uc720\ub3c4\uc18d\ub3c4\ub97c \uad6c\ud560 \uc218 \uc788\ub2e4. (13) \uc5ec\uae30\uc11c \ub294 \uc2dd(14)\uc640 \uac19\ub2e4. \u221e \u221e (14) \uc218\ub834\uc2dc\uae4c\uc9c0 \ubc18\ubcf5 \uacc4\uc0b0\ud558\uc5ec \uad6c\ud55c \uc720\ub3c4\uc18d\ub3c4 \ub97c \uc2dd(15)\uc5d0 \uc801\uc6a9\ud558\uba74 \ub2e4\uc74c\uacfc \uac19\uc774 \ucd94\ub825\uc744 \uad6c\ud560 \uc218 \uc788\ub2e4. \u221e (15) Slip stream \ud6a8\uacfc Slip stream\uc774\ub780 \ud504\ub85c\ud3a0\ub7ec\uac00 \ucd94\ub825\uc744 \uc77c\uc73c\ud0a4\uba74 \uc11c \ud68c\uc804\ud560 \ub54c \uadf8 \ud68c\uc804\uba74\uc758 \ub4a4\ucabd\uc5d0 \ud504\ub85c\ud3a0\ub7ec\uc758 \uc804 \uc9c4 \uc18d\ub3c4\ubcf4\ub2e4 \ud070 \uc720\uc18d\uc758 \uae30\ub958\uac00 \uc0dd\uae30\ub294 \uac83\uc744 \ub9d0\ud55c \ub2e4. QTW\ub294 \ud504\ub85c\ud3a0\ub7ec\uac00 \uc8fc\uc775\uc5d0 \uace0\uc815\ub418\uc5b4 \ud2f8\ud2b8\uc2dc \uac19\uc774 \uc6c0\uc9c1\uc774\uae30 \ub54c\ubb38\uc5d0 Slip stream \ud6a8\uacfc\ub85c \uc778\ud574 \ud6c4\ub958\uc5d0 \uc7a0\uae30\ub294 \ubd80\ubd84\uc5d0 \ub300\ud574 \uc77c\uc815\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc774 \ubc1c\uc0dd\ud558\uac8c \ub41c\ub2e4. Fig. 6\uc740 \ub85c\ud130\uc5d0 \uc758\ud574 \ubc1c\uc0dd \ub418\ub294 \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud574 \ubc1c\uc0dd\ub418\ub294 \uc5d0\uc5b4\ud3ec\uc77c\uc758 \uc591\ub825\uacfc \ud56d\ub825\uc744 \uc124\uba85\ud55c \uadf8\ub9bc\uc774\ub2e4. Fig. 6\uc5d0\uc11c \uc8fc\uc775\uc758 \uc591\ub825\uacc4\uc218\ub294 \uc2dd(16)\uc73c\ub85c \ub098\ud0c0\ub0bc \uc218 \uc788\uc73c\uba70, \uc774 \ub54c \ubc1b\uc74c\uac01\uc5d0 \ub530\ub978 \uc591\ub825\uacc4\uc218 \ub294 \ud1b5\uc0c1\uc801\uc778 \uac12\uc778 0.1/deg\ub85c \uc124\uc815\ud558\uc600\ub2e4. (16) \ub294 \ud504\ub85c\ud3a0\ub7ec \ud6c4\ub958\uc5d0 \ub300\ud55c \uc8fc\uc775\uc758 \ubd99 \uc784\uac01\uacfc \uac19\uc740 \ud6a8\uacfc\uc640 \ucea0\ubc84\ub97c \uac00\uc9c4 \uc5d0\uc5b4\ud3ec\uc77c\uc774\ub77c\ub294 \uc810\uc744 \uace0\ub824\ud558\uc5ec 3\ub3c4\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub294 \uc870\uc885\uba85 \ub839\uc778 \ud50c\ub7a9\uac01\ub3c4\uc5d0 \ub530\ub978 \uc591\ub825\uacc4\uc218 \uc99d\uac00\ub97c \uace0\ub824\ud55c \ud56d\uc73c\ub85c 0.02\ub85c \uac00\uc815\ud588\uc73c\uba70 \ub294 \ud50c\ub7a9\uc758 \ubcc0\uc704\uc774 \ub2e4. (17) \uc2dd(17)\uacfc \uac19\uc774 \uc591\ub825\uacc4\uc218\ub97c \uc801\uc6a9\ud558\uc5ec \ud6c4\ub958\uc5d0 \uc7a0 \uae30\ub294 \ubd80\ubd84\uc5d0 \ub300\ud55c \uc591\ub825\uacfc \ud56d\ub825\uc744 \uad6c\ud560 \uc218 \uc788\uc73c \uba70, Fig. 4\uc640 \uac19\uc774 \ud6c4\ub958\uc5d0 \uc7a0\uae30\ub294 \ubd80\ubd84\uc758 \uba74\uc801\uc774 \uc77c\uc815\ud558\uc9c0 \uc54a\uc740 \uc810\uacfc \uc124\uacc4\ub41c QTW \ube44\ud589\uccb4\uc758 \uae30\ud558 \ud559\uc801 \ud615\uc0c1\uc744 \uace0\ub824\ud558\uc5ec \ud504\ub85c\ud3a0\ub7ec \uc9c0\ub984\uc758 70%\ub97c \ud3c9\uade0\uc801\uc73c\ub85c \uc7a0\uae30\ub294 \uc601\uc5ed\uc758 \uc2a4\ud32c\uc73c\ub85c \uac00\uc815\ud558\uace0 \uba74\uc801 \ub97c \uacc4\uc0b0\ud558\uc600\ub2e4. \ud56d\ub825\ubd80\ubd84\uc5d0\uc11c\ub294 QTW \ud615\uc0c1\uc758 \ud2b9\uc131\uc0c1 \ud504\ub85c\ud3a0\ub7ec\uc758 \ud6c4\ub958\uac00 \uc8fc\uc775 \ub05d\ub2e8\uae4c \uc9c0 \uc7a0\uae30\uae30 \ub54c\ubb38\uc5d0 \uc720\ud55c\ud55c \ub0a0\uac1c\uc758 \ud2b9\uc131\uc778 Vortex\uc5d0 \uc758\ud55c Downwash\uc640 Downwash\uc5d0 \uc758 \ud55c \uc720\ub3c4\ud56d\ub825\uc744 \ubb34\uc2dc\ud558\uace0 \ud615\uc0c1\ud56d\ub825\ub9cc\uc744 \uace0\ub824\ud558 \uc600\ub2e4. \uc2dd(17)\uc5d0\uc11c \ub3d9\uc555\uc740 \uc2dd(18)\uacfc \uac19\uc73c\uba70, \uc5ec\uae30 \uc11c \uc720\ub3c4\uc18d\ub3c4\ub294 \uc2dd(14)\uc5d0\uc11c \uacc4\uc0b0\ub41c \ud504\ub85c\ud3a0\ub7ec\uc758 \ud6c4\ub958\uc18d\ub3c4\uc5d0 \ud574\ub2f9\ub41c\ub2e4. (18) Slip stream\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\ub4e4\uc740 \ud2f8\ud2b8 \uac01\uc774\ub098 \ube44\ud589\uccb4 \uc790\uc138\uac01\uc5d0 \ubb34\uad00\ud558\uba70 \ud504\ub85c\ud3a0\ub7ec\uc5d0 \uc758 \ud574 \ubc1c\uc0dd\ub418\ub294 \ud6c4\ub958 \uc720\ub3c4\uc18d\ub3c4\uc640 \ud50c\ub7a9\ubcc0\uc704\uc5d0\ub9cc \uc601\ud5a5 \uc744 \ubc1b\uac8c \ub41c\ub2e4. Total force and Moment \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc740 Fig. 7\uacfc \uac19\uc774 \ud2f8\ud2b8 \uac01\ub3c4\uc5d0 \ub530\ub77c \uac01 \ud798\uc758 \ubc29\ud5a5\uc774 \ub2ec\ub77c\uc9c0\uae30 \ub54c\ubb38\uc5d0 \uac01 \ucd95 \ubc29\ud5a5\uc758 \ud798\uc758 \ud06c\uae30\ub97c \uacc4\uc0b0\ud560 \ub54c \ud2f8 \ud2b8 \uac01\ub3c4\ub97c \uace0\ub824\ud558\uc5ec\uc57c \ud55c\ub2e4. \uacc4\uc0b0\ub41c \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801\uc778 \ud798\uacfc \ubaa8\uba58\ud2b8\ub294 \ub2e4\uc74c\uacfc \uac19\uc774 \uae30\uccb4 \uace0\uc815 \uc88c\ud45c\uacc4\ub85c \ud45c\ud604 \ub420 \uc218 \uc788\ub2e4. sin (19) cos (20) cos sin cos (21) \uac01 \ub0a0\uac1c\uc5d0\uc11c \uc5bb\uc5b4\uc9c4 \ud798\ub4e4\uc744 \uc131\ubd84\ubcc4\ub85c \ub2e4\uc2dc \uc815\ub9ac \ud574 \ubcf4\uba74 \ub2e4\uc74c\uacfc \uac19\ub2e4. cossin (22) sin (23) sincos (24) cos (25) \ud2f8\ud2b8 \uac01\ub3c4\uc5d0 \ub530\ub77c \uac01 \ud798 \uc131\ubd84\ub4e4\uc744 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\ub85c \ubcc0\ud658\ud558\uc600\uc73c\uba70, \uac01 \ucd95\ubc29\ud5a5\uc758 \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc5d0 \ud6c4\ub958\uc5d0 \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84\uc5d0 \ub300\ud55c \ud798\uc744 \ucd94\uac00 \ud574 \uc8fc\uc5c8\ub2e4. \ud68c\uc804\uc775\ubaa8\ub4dc\uc5d0\uc11c\ub294 \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84 \uc774 \ud56d\ub825\uc73c\ub85c \uc791\uc6a9\ud558\uac8c \ub418\uace0 \ucc9c\uc774\ubaa8\ub4dc\ub97c \uac70\uccd0 \uace0 \uc815\uc775\ubaa8\ub4dc\ub85c \ud2f8\ud2b8\ub428\uc5d0 \ub530\ub77c \ud56d\ub825\uc740 \uc904\uace0 \uc591\ub825\uc740 \uc99d\uac00\ud558\uac8c \ub41c\ub2e4. \uc2dd(21)\uc758 \ud53c\uce6d\ubaa8\uba58\ud2b8\ub294 \uc804\ubc29\uc8fc\uc775 \uacfc \ud6c4\ubc29\uc8fc\uc775\uc758 \ucd94\ub825, \uc591\ub825 \ubc0f \ud56d\ub825\uc758 \ucc28\uc774\uc5d0 \uc758 \ud574 \ud06c\uae30\uac00 \uacb0\uc815\ub41c\ub2e4." + ] + }, + { + "image_filename": "designv8_17_0000437_-ijaefea20210709.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000437_-ijaefea20210709.pdf-Figure2-1.png", + "caption": "Figure 2. Geometry", + "texts": [], + "surrounding_texts": [ + "To select dc motor, we need to calculate total weight which need to slide from motor on frame, Factor considered for weight 1. Tray weight 2. Nut, bolts weight 3. Frame weight 1. Tray weight Tray weight from cad model = 1.3 kg x 3 Tray = 3.9 kg = 4kg round off (1) Assume 15 nuts, M6 \u00d7 15 nuts = 2.50gm \u00d7 15 = 37.5 grams M8 \u00d7 15 nuts =5.1 gm \u00d715 = 76.5 grams M10 \u00d7 15 nuts = 11.6 gm \u00d715 = 174 grams Overall Weight of Nuts, Total weight = 37.5 +76.5+174 Design and Analysis of Nut and Bolt Separating Machine 99 Int. J. of Analytical, Experimental and Finite Element Analysis www.rame.org.in Total weight of nut = 288 grams Total weight of Bolts (15 \u00d7 M6) + (15 \u00d7 M8) + (15 \u00d7 M10) bolts = 4 kg weight Frame weight; From cad by assign mild steel material density to frame = 7.8 kg. Overall Weight, Tray = 4kg round off. (2) Total weight of nut = 288 grams (3) Total weight of bolts= 4 kg weight (4) Frame = 7.8 kg (5) Overall Weight = A +B+C+D = 16 Kg Consider factor of safety and other factors = 16 + 4 kg extra wright 20 kg, Total weight with factor of safety = 20 kg Power = Force \u00d7 Velocity Here, assuming we are lifting the weight at a constant speed, the force applied by the motor is equal and opposite to the force applied by gravity, which is F=m g =20kg (10m/s2) = 200N Velocity V= 1m/60Sv =1m/60s Power P=F V =200N (1m/60s) =3.33watt From market we got below dc motor suitable for our project with 12V power. \u2022 Speed in rpm = 600 \u2022 Number of poles = 4 \u2022 Shaft Length = 30 mm \u2022 Motor Diameter = 28.5 mm \u2022 Gearbox Diameter = 37mm Now for calculating Working Frequency we use the formula, N = 120f /P Where, N= Rpm and P = No. of Poles. 600 = 120f/4 f = 20 Hz Hence our working frequency is 20 Hz. IV. FEA ANALYSIS Finite Element Analysis or FEA is the simulation of a physical phenomenon using a numerical mathematic technique referred to as the Finite Element Method, or FEM. This process is at the core of mechanical engineering, as well as a variety of other disciplines. It also is one of the key principles used in the development of simulation software. Engineers can use these FEM to reduce the number of physical prototypes and run virtual experiments to optimize their designs. Meshing is the process in which the continuous geometric space of an object is broken down into thousands or more of shapes to properly define the physical shape of the object. The more detailed a mesh is, the more accurate the 3D CAD model will be, allowing for high fidelity simulations. Details of meshing used \u2022 Element Size: 5.0 mm \u2022 Minimum Edge Length: 0.41406 mm 100 Int. J. of Analytical, Experimental and Finite Element Analysis \u2022 Nodes: 159258 \u2022 Elements: 73740 Figure 4. load apply Figure 5. Equivalent Stress TABLE1" + ] + }, + { + "image_filename": "designv8_17_0004319_echaterobot_download-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004319_echaterobot_download-Figure7-1.png", + "caption": "Figure 7. Selected variant fitted with servomotors", + "texts": [ + " Selected servomotor\u2019s torque at the first (most impacted) servomotor: Mk = F x l, Mk = ( m x g ) x l, where: F \u2013 force affecting the end segment of the arm l \u2013 effector arm \u2018s length m \u2013 total structure and effector weight g \u2013 gravitational acceleration The effector structure\u2019s total weight was calculated according to the formula where: m1 \u2013 weight of the interface structure m2 \u2013 weight of all servomotors m3 \u2013 weight of supporting parts of the robotic hand m = 70 + (3 x 60) + 600 m = 70 + 180 + 600 = 850 Upon fitting the above to the formula Mk = ( m x h ) x l Mk = (0.85 x 9.1 ) x 0.143 Mk = 1.1 Nm Maximum torque of this servomotor is 1.2 Nm. Therefore, the torque at the 1st servomotor that operates the hand and arm meets the requirements. P \u2013 total number of points i \u2013 criterion number j \u2013 number of the alternative p \u2013 criterial number of points n \u2013 number of rating criteria The alternative no. 3 scored the highest (13 points) and according to the ranking by the selected scoring method, this alternative is an optimum one. The alternative no. 3, Fig. 7, has been selected as another solution. MM SCIENCE JOURNAL I 2020 I MARCH The selected variant and the model\u2019s design in the CAD system are adjusted to the given servomotors. To maximize the required firmness of the structure, the relief holes were filled. PARTS OF THE SELECTED VARIANT\u2019S STRUCTURE Figure 8, part \u201ca\u201d shows the first segment of a kinematic chain, that can be bolted to any platform. This segment was specifically designed and dimensioned for the parameters of the selected and used servomotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002992_M-2018-3-02-Dyja.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002992_M-2018-3-02-Dyja.pdf-Figure4-1.png", + "caption": "Fig. 4. Hexagonal (a) and dioctahedral (b) working roll pass", + "texts": [ + " Diameter of stock material which was manufactured on the piercing mill was equal to D0 = 166 mm in all the experiments, and the shell wall thickness was different S0 = 10, 11, 12, 13 and 14 mm. Mandrel diameter was Dman1 = 146 mm. Diameter of tubes after rolling on PRM-1 was D0 = 160 mm in all the experiments. Therefore, elongation ratio \u03bb at the first pass was: 1.46; 1.6; 1.73; 1.86; 1.99. The study of metal forming was carried out for two options of working rolls pass design: hexagonal and dioctahedral (Fig. 4). When simulating the rolling process is running operating roll pass designs on PRM-140 were applied. The study of metal forming consisted of determination of the principles of elongation ratio influence to dimensionless ratios, which characterize pipe deformation in the groove taper: S1/S2; \u03b4/S2; C/S2. Where: S1 \u2013 pipe wall thickness in the groove taper; S2 \u2013 pipe wall thickness in the upper part of the groove; \u03b4 \u2013 clearance between mandrel and the internal surface of the pipe; \u0421 \u2013 spreading of a free mandrel surface (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002703_1334-022-00450-w.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002703_1334-022-00450-w.pdf-Figure5-1.png", + "caption": "Fig. 5 Parallel composition of the strategies s1 and s2 for r1 and r2, depicted in Figs. 2 and 3, respectively. The labels of the states denote the output of the TS in the respective state", + "texts": [ + " Since goi is an output variable of robot ri , we obtain the subspecifications \u03d5i = \u03d5safe\u2227\u03d5crossi . A solution of certifying synthesis is then given by the strategies depicted in Figs. 2, 3 and GTS depicted in Figs. 1 and 4. Note that s2 only locally satisfies \u03d5cross2 with respect to g1 when assuming that r1 is not immediately again at the intersection after crossing it. However, there are solutionswith slightlymore complicated certificates that do not need this assumption. The parallel composition of s1 and s2 is depicted in Fig. 5. It is a strategy that allows r1 to move forwards if it is at the crossing and that allows r2 to move forwards otherwise. Both variants of certifying synthesis introduced in the previous sections consider the certificates of all other system processes in the local objective of a process pi . This is not always necessary since \u03d5i might be satisfiable even if another process deviates from its guaranteed behavior. In this section, we present an optimization of certifying synthesis that reduces the number of considered certificates" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001404_22_Vol._51_59-73.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001404_22_Vol._51_59-73.pdf-Figure2-1.png", + "caption": "Figure 2. Scheme of dynamic loading of the load device when lifting the load \u201cwith pickup\u201d", + "texts": [ + " In calculation in the case of dynamic loading of the crane loading device when lifting the load \u201cwith pickup\u201d (\u201cfrom the base\u201d), other approaches can be used [1]. In particular, it allows neglecting the stiffness of one of the elements (ropes, since the elasticity of the metal structure of the crane is much higher than that of the ropes themselves, and the oscillations of the latter quickly damped) and consider only the elasticity of the second element of stiffness \u2013 the crane structure, that is, the mass of the crane m\u043a and the load ml are considered as one mass m (Fig. 2). Note: a) on overhead cranes; b) and c) design schemes of single- and double-mass systems Source: [1; 2] Under the assumptions made, it can be considered that the load is lifted as follows. In the first stage, after turning on the engine. The rope slack is selected, in the second stage \u2013 elastic deformation of all structural elements (Fig. 2). The second stage continues until the force P0 on the load-gripping devices, increasing from zero, becomes equal Ql = ml\u22c5g. Only after that, in the third stage, the lifting of the load begins [18]. When moving x\u043a the mass of the crane m\u043a with rigidity C\u043a (more precisely, the crane beam as part of the metal structure of the crane) kinetic energy: \ud835\udc4a\ud835\udc4a\ud835\udc4a\ud835\udc4a = \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ufffd\u043a \u22c5 ?\u0307?\ud835\udc65\ud835\udc65\ud835\udc65\u043a 2 2 ,\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ufffd\u043a = \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc59\ud835\udc59\ud835\udc59\ud835\udc59 + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\u043a, (66) but potential energy: \ud835\udc48\ud835\udc48\ud835\udc48\ud835\udc48 = \ud835\udc36\ud835\udc36\ud835\udc36\ud835\udc36\u043a \u22c5 \ud835\udc65\ud835\udc65\ud835\udc65\ud835\udc65\u043a2/2. (67) The driving force here P, varies for different stages of lifting the load", + "\ud835\udc65\ud835\udc65\ud835\udc65\u043a \ud835\udc54\ud835\udc54\ud835\udc54\ud835\udc54 = 1 + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\u043a (\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\u043a+\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc59\ud835\udc59\ud835\udc59\ud835\udc59) \u22c5 \ufffd1 \u2212 2\ud835\udc61\ud835\udc61\ud835\udc61\ud835\udc61 \ud835\udf0f\ud835\udf0f\ud835\udf0f\ud835\udf0f\ud835\udc5d\ud835\udc5d\ud835\udc5d\ud835\udc5d \ufffd. (89) Note that its maximum value Kd reaches at the initial moment of time t = 0: \u041a\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51 (\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a)(\ud835\udc61\ud835\udc61\ud835\udc61\ud835\udc61)\ufffd \ud835\udc61\ud835\udc61\ud835\udc61\ud835\udc61=0 = 1 + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\u043a (\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\u043a+\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc59\ud835\udc59\ud835\udc59\ud835\udc59) . (90) The obtained formulas (in the approximation of a single-mass model of lifting a load \u201cwith a pickup\u201d) are quite simple and can be used in practical calculations, although, they do not consider the influence of the second stiffness element that exists in the system under consideration (Fig. 2). Accounting for it, the system should be considered as a biaxial system with two elastic couplings and, accordingly, as having two degrees of freedom of motion, with the corresponding superposition of oscillations at each of the frequencies and finding the maximum during several periods of oscillations. Using the Lagrange function for this problem allows writing in this case the following system of equations for xl and x\u043a: \ud835\udc43\ud835\udc43\ud835\udc43\ud835\udc43\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51 = \ufffd\u2212\ud835\udc44\ud835\udc44\ud835\udc44\ud835\udc44\ud835\udc59\ud835\udc59\ud835\udc59\ud835\udc59 \ud835\udc54\ud835\udc54\ud835\udc54\ud835\udc54 \ufffd \u22c5 \ufffd\ufffd\ud835\udc63\ud835\udc63\ud835\udc63\ud835\udc6302 \u22c5 \ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f2 + \ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f4 \u22c5 \ud835\udc66\ud835\udc66\ud835\udc66\ud835\udc66\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc462 \u22c5 \ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60\ud835\udc60( \ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f + \ud835\udefc\ud835\udefc\ud835\udefc\ud835\udefc)\ufffd,\ud835\udefc\ud835\udefc\ud835\udefc\ud835\udefc = \ud835\udc4e\ud835\udc4e\ud835\udc4e\ud835\udc4e\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc4e\ud835\udc4e\ud835\udc4e\ud835\udc4e\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc4e\ud835\udc4e\ud835\udc4e\ud835\udc4e \ufffd\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\u22c5\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46\ud835\udc46 \ud835\udc63\ud835\udc63\ud835\udc63\ud835\udc630 \ufffd" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure9.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure9.3-1.png", + "caption": "Figure 9.3: Multi-point optimized battery geometry and aerodynamic data compared to baseline", + "texts": [ + " I used the same set of 96 FFD control points illustrated in Figure 9.1 to parameterize the battery (although its optimizer design variable values are independent of the wing). I then optimized the wing and battery using the multi-point problem formulation listed above. The optimization was considered converged once SNOPT\u2019s optimality metric was reduced three orders of magnitude. Table 9.2 shows high-level results from the optimization run, which took 68.7 hours on one TACC Skylake node. The range quantity increased by 62.7% compared to the baseline design. Figure 9.3 shows a before-and-after comparison of pressure, lift, and twist distribution, airfoil section geometry, and battery section geometry. The optimizer greatly increased inboard wing thickness. Outboard of the battery pack end, the wing was reduced to minimum thickness. 200 The battery, although parameterized independently from the wing, fits tightly to the wing upper and lower surfaces with very small gaps. Because today\u2019s batteries are generally composed of cylindrical cells of finite size, it is likely that arbitrary battery curvatures cannot be achieved" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure94-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure94-1.png", + "caption": "Figure 94 : Pr\u00e9sentation du r\u00e9seau lin\u00e9aire bande X surmont\u00e9 de rubans infinis.", + "texts": [ + " En effet, la simulation sans dip\u00f4les montre que les sources du r\u00e9seau bande X poss\u00e8dent des coefficients de r\u00e9flexion actifs relativement diff\u00e9rents les uns des autres, or, sans dip\u00f4les, toutes les sources bande X devraient pr\u00e9senter la m\u00eame adaptation. Afin de simplifier l\u2019\u00e9tude des effets des sources bande L sur les sources bande X, nous d\u00e9cidons de consid\u00e9rer une structure plus simple, mais tout de m\u00eame repr\u00e9sentative. Nous choisissons de simuler un r\u00e9seau lin\u00e9aire bande X surmont\u00e9 de deux rubans infinis qui repr\u00e9sentent les deux dip\u00f4les bande L. Le r\u00e9seau lin\u00e9aire bande X correspondrait globalement \u00e0 la ligne centrale du r\u00e9seau bande X au sein de la maille hexagonale bande L. Page 88 sur 182 La Figure 94 pr\u00e9sente la structure simul\u00e9e. Un r\u00e9seau lin\u00e9aire bande X surmont\u00e9 de deux rubans infinis, repr\u00e9sentant les deux dip\u00f4les bande L, est consid\u00e9r\u00e9 afin d\u2019\u00e9tudier les effets des dip\u00f4les bande L sur les sources bande X. Encore une fois, il s\u2019agit de simulations en r\u00e9seau infini-p\u00e9riodiques r\u00e9alis\u00e9es gr\u00e2ce aux conditions de simulations Master/Slave du logiciel HFSS. Comme des d\u00e9pointages dans le plan E et dans le plan H vont \u00eatre r\u00e9alis\u00e9s, l\u2019utilisation d\u2019une sym\u00e9trie comme dans la partie pr\u00e9c\u00e9dente 7", + " Celle en bande L avec deux dip\u00f4les, permettent un d\u00e9pointage jusque 48\u00b0 dans le plan H, et 26\u00b0 dans le plan E sur les deux bandes IFF souhait\u00e9es (pr\u00e9sent\u00e9e sur la Figure 87 dans la partie 6.4). Nous nous int\u00e9ressons dans un premier temps aux effets sur l\u2019adaptation des sources bande X, ensuite, nous \u00e9tudions les effets sur le diagramme de rayonnement. 4.7.2.2 \u00c9tude des effets des rubans sur l\u2019adaptation des sources bande X La structure consid\u00e9r\u00e9e est celle pr\u00e9sent\u00e9e dans la partie pr\u00e9c\u00e9dente, sur la Figure 94. Ce qui change, ce sont les valeurs des param\u00e8tres des sources bande X et bande L, qui sont maintenant, les derni\u00e8res optimis\u00e9es. Comme pr\u00e9c\u00e9demment, les rubans ont des largeurs uniformes not\u00e9es w3r et w4r. Cependant, \u00e0 pr\u00e9sent, nous choisissons pour les largeurs des rubans, celles aux extr\u00e9mit\u00e9s des dip\u00f4les, et non pas celles au centre. On a alors w3r = w3 et w4r = w4. Ce choix est fait car nous nous int\u00e9ressons aux effets des sources bande L sur toutes les sources bande X, et non pas seulement sur celles au centre du r\u00e9seau" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002508_941f68ffd804d767.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002508_941f68ffd804d767.pdf-Figure2-1.png", + "caption": "Fig. 2: Schematic diagram for modified thresher (EL-SHAMS) type", + "texts": [], + "surrounding_texts": [ + "This study was conducted to develop local thresher (El-Shams) type, tangential axial \u2013 flow cereal crops thresher, to be suitable for threshing of caraway crop." + ] + }, + { + "image_filename": "designv8_17_0004125_f_version_1625137414-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004125_f_version_1625137414-Figure10-1.png", + "caption": "Figure 10. Schematic diagram of hybridization of a woven kenaf with synthetic fibers mat-reinforced polymer composite. Reproduced from ref. [159].", + "texts": [ + " [156] Hybrid composites have been developed by various researchers, combining fibers with epoxy, unsaturated polyester, phenolic, vinyl ester, and thermosetting type polyurethane resins. When, two or more fibers are used for making composites, they are called hybrid composites, for example, carbon fiber/glass fiber, glass fiber/Kevlar hybrid, etc. These type of combination gives an advantage of good strength at lower cost, which can be used for applications that were not possible by using the pure composite. So, the hybridization of composite fibrous material is the key to designing new components having good strength at relatively lower cost [157,158]. Figure 10 shows examples of the hybridization of a woven kenaf with carbon fibers mat-reinforced epoxy composite conducted by Aisyah et al. [159]. Khalil et al. [160] reported on the mechanical properties of EFB/glass hybrid reinforced unsaturated polyester composites. Different ratios of glass and EFB fibers\u20143:7, 5:5, 7:3, and 9:1\u2014were prepared using resin transfer molding (RTM) with a thickness of 1 mm and a pressure of 5 bar. As a result of the great dispersion of the fiber and the efficient load transmission mechanism of this composition, the mechanical study indicates that the composite with 35% fiber loading exhibited the best value mechanical performance" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003248_jees-2021-4-r-36.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003248_jees-2021-4-r-36.pdf-Figure4-1.png", + "caption": "Fig. 4. Structure of canonical triple sleeve antenna.", + "texts": [ + " Variation in the reactance of input impedance is observed to be more for canonical antenna and canonical single sleeve antenna, and less for canonical dual sleeve and canonical triple sleeve antennas. The comparison of simulated voltage standing wave ratio (VSWR) of these antenna configurations is shown in Fig. 3. It can be observed from Figs. 2 and 3 that the canonical triple sleeve antenna has the best impedance matching and hence VSWR performance in the broadband scenario from 370\u20135,000 MHz. The structure of the proposed antenna the, canonical triple sleeve antenna is shown in Fig. 4. The performance of the canonical triple sleeve antenna was simulated with respect to the dimensions and placement of the sleeve. Initially, parametric analysis was performed for the first/central sleeve. The diameter of the first sleeve, j, varied from 50 to 150 mm in seven steps; the results are presented in Fig. 5(a). Table 1. Canonical triple sleeve antenna parameters No. Parameter of antenna Value (mm) 1 Diameter of top cover, a 113.57 2 Length of cylindrical extension, b 19.02 3 Length of second sleeve, c 13", + "56 wavelengths at 5,000 MHz. A conventional dipole of this length would have multiple lobes. The simulation model and the photograph of the realized canonical triple sleeve antenna are shown in Fig. 7. The metallic portions of this antenna were fabricated using aluminum alloy. Poly-urethane foam (PUF) supports were used for the assembly of the antenna. The antenna was fed using a semi-rigid coaxial cable of 0.141-inch diameter. The coaxial cable was assembled with an SMA connector at one end as shown in Fig. 4. The VSWR measurement of canonical triple sleeve antenna is performed using a Vector Network Analyzer. The comparison of simulated and measured VSWR is given in Fig. 8. The antenna has VSWR \u2264 1.9:1 in the frequency bands 415\u2013530 MHz, 1,630\u20132,500 MHz and 4,560\u20135,000 MHz and VSWR \u2264 3:1 over the operating frequency range 370\u20135,000 MHz. The measured and simulated E-plane and H-plane patterns of canonical triple sleeve antenna are shown in Fig. 9. It can be seen from Fig. 9 that the canonical triple sleeve antenna exhibits good omnidirectional characteristics" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure16-1.png", + "caption": "Figure 16. The final design of the Elka1Q fuselage\u2014the internal plywood structure.", + "texts": [], + "surrounding_texts": [ + "The overall shape of the drone (as seen in Figures 8 and 9) is a compromise among the general assumptions (described in Section 1), size and weight of significant components (such as the battery pack), and smart usage of available materials. 2.3.1. Wings Typically, drone arms are made of carbon-fibre tubes because they are very stiff and lightweight at the same time. However, such a single tube could have a too big a diameter to fit into the drone\u2019s wing. Instead, we decided to use double 6 \u00d7 2 mm carbon-fibre flat bars as wing spars. Additionally, the space between them forms a convenient tunnel for electric wires. The wings are built of two matching full-balsa wood elements: a bottom and a top half, both CNC 3D milled and glued together. The leading and trailing edges of a wing are usually prone to accidental damage (especially a very thin trailing edge); therefore, both edges are reinforced with carbon-fibre 4\u00d7 1 mm flat bars. The carbon-fibre wing spars at the wingtips support the main motor holders (CNC milled from a 3mm-thick aluminium sheet). The two elements of the holders are screwed together to catch protruding wing spars tightly. Finally, the surface of the wing is covered by Oracover [32] film. The wing construction proves to be light and very durable. We could say it is a perfect balance between stiffness and elasticity. Initially, we chose a wing profile (an airfoil) optimized for high-speed flight: the P-51D tip (BL215) airfoil (see Figure 10). Generally speaking, high-speed airfoils have low drag, but, on the other hand, have a low lift coefficient, which results in a high stall speed, and that means the plane has to maintain high enough speed to stay airborne in a level flight. That should not be an issue if the pusher motor can accelerate the drone to that speed. Due to safety reasons, we decided to modify the original wings\u2014we made them much thicker (see Figure 11). Such a thick airfoil (thickness increased from 12% to 25% of the airfoil chord) gives us a much higher lift coefficient (resulting in a lower stall speed) at the cost of lowering the top speed. Nevertheless, lower stall speed means we could perform the in-flight experiments of switching between quadcopter and plane mode at lower (i.e., safer) speed, and we could do that in a less spacious airfield. The wing configuration used in the drone is called a \u201ctandem-wing\u201d or sometimes a \u201clifting-tail plane\u201d. Those names refer to the fact that the aft wing is not just a horizontal stabilizer, like in a classic \u201ctailplane\u201d configuration, but it contributes to the total lift force produced by the plane. It is a rare configuration due to possible stability and controllability issues [34,35]. Sometimes, quite the opposite statements can be found\u2014tandem-wing planes are easier to pilot because of safer stall behaviour [36]. However, there were at least a few successful tandem-wing planes, e.g., Quickie designed by Elbert Leander \u201cBurt\u201d Rutan (and later QAC Quickie Q2) [36,37] and the Proteus [38] built by Scaled Composites (Rutan\u2019s company). Another famous tandem-wing plane is the \u201cFlying Flea\u201d (French name: \u201cPou du Ciel\u201d), designed by Henri Mignet in 1933. A thorough study of many more historical and modern tandem-wing planes and UAVs, as well as their aerodynamic and stability studies, can be found in [34]. A wing that produces lift force also generates a downwash, i.e., the airflow direction behind the trailing edge of the wing is deflected down by the aerodynamic action of the wing. That phenomenon changes the effective Angle of Attack (AoA) of the rear wing in the tandem-wing configuration. Most tandem-wing planes have the front wing mounted lower than the rear wing to minimize the downwash effect of the front wing [34,35]. Additionally, it is recommended to set a higher AoA of the front wing than the aft wing\u2014such a wing setup affects the stall behaviour of the tandem-wing plane. The front wing with a higher AoA will stall first while the aft wing still produces lift force\u2014that situation will cause the plane to pitch down, increase the speed, and ultimately, end the front wing\u2019s stall (bring back its lift force) [36]. Following the suggestions, the front wing of the Elka1Q drone was mounted at ca. 4\u25e6 AoA and the aft wing at ca. 2\u25e6 AoA. Finally, there is at least one more critical aspect of every aircraft having wings: Centre of Gravity (CG, CoG). It is crucial to keep the longitudinal stability of an aircraft. We used a CG calculator from the eCalc toolset [30]. The results of the calculation are presented in Figure 12. 2.3.2. Fuselage The final fuselage design was based on a rigid PVC tube (100 mm diameter and 1 mm wall) and a lighter, but still solid plywood structure (Figures 15\u201317). The PVC tube acts similarly to a monocoque structure, eliminating the twisting about the longitudinal axis. The landing gear is non-retractable\u2014we made four fixed legs of 3 mm spring steel wire supported by pinewood blocks at the bottom of the fuselage. The overall structure of the wings and the fuselage proved to be very rigid and robust, surviving a few serious crash landings. The most significant disadvantage of such a compact construction is complicated maintenance of internal components, e.g., access to electronic boards, wires, and connectors." + ] + }, + { + "image_filename": "designv8_17_0003944_6514899_10305151.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003944_6514899_10305151.pdf-Figure17-1.png", + "caption": "FIGURE 17. Top view of the proposed 1\u00d74 ME-dipole antenna with metasurface.", + "texts": [], + "surrounding_texts": [ + "This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License. For more information, see https://creativecommons.org/licenses/by-nc-nd/4.0/ Oludayo Sokunbi and Ahmed Kishk: Millimeter-wave ME-Dipole Array Antenna Decoupling Using a Novel Metasurface Structure and H-planes. Also, the measured and simulated results are close to each other except the differences due to the antenna mounting structures. VI. MIMO CONFIGURATION To further confirm the capability of this new unit cell, we have extended the number of antenna elements to 4 in the H-plane and have also used 11\u00d72 resonator structures as the superstrate. The edge-to-edge difference of antenna elements is still 1.6 mm (0.32\u03bb at 60 GHz) as shown in Figs. 17 and 18. Two extra MGW extensions are also simulated and used to extend the feedline. Fig. 19 shows the simulated reflection coefficient of the antenna with and without the MS. The antenna exhibits good reflection coefficient between 52-66 GHz. Fig. 20 compares the coupling between the antenna elements. The simulated mutual coupling between the elements is reduced by a maximum of 40 dB over the intended bandwidth. This indicates the efficacy of the proposed metasurface. The simulated and measured S-parameters of the 1\u00d74 array is shown in Fig. 21. There is a good agreement between the simulated and measured S-parameters of the array with and without the Metasurface. The simulated and measured mutual coupling between the antenna elements without metasurface is also shown in Fig. 22, with very good agreement. FIGURE 18. Back view of the 1\u00d74 ME-dipole antenna with metasurface. 50 52 54 56 58 60 62 64 66 68 70 -30 -20 -10 0 S11 Without_MS S44 Without_MS S11 With_MS S44 With_MS SPa r. (d B ) Freq. (GHz) FIGURE 19. Simulated reflection coefficient of the proposed 1\u00d74 ME-dipole antenna with and without Metasurface. The simulated and measured radiation pattern of the 1\u00d74 of the proposed antenna in E- and H-plane is shown in Fig. 23. It is clear that the radiation pattern is relatively stable over the bandwidth, with very good agreement. The surface current and E-field distribution of the 1\u00d74 antenna by exciting one port and terminating the other ports with a matching loads are shown in Figs 24 and 25, respectively. Comparing Fig 24(a) and Fig24(b), the surface currents on the antenna substrate have been mitigated by the addition of the 11\u00d72 metasurface unit cells as evidenced by the concentration of surface currents. Also, the E-Field distribution on the surface of the antenna as shown in Figs 25(a) compared to Figs 25(b) shows a great reduction of VOLUME 4, 2016 7 This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License. For more information, see https://creativecommons.org/licenses/by-nc-nd/4.0/ Oludayo Sokunbi and Ahmed Kishk: Millimeter-wave ME-Dipole Array Antenna Decoupling Using a Novel Metasurface Structure 50 52 54 56 58 60 62 64 66 68 70 -80 -70 -60 -50 -40 -30 -20 -10 S21 Without_MS S21 With_MS S32 Without_MS S32 With_MS S43 Without_MS S43 With_MS SPa r. (d B ) Freq. (GHz) FIGURE 21. Simulated and Measured S-parameters of the proposed 1\u00d74 ME-Dipole Antenna Structure: (a) Reflection coefficients With and Without Metasurface (Thick black line = Simulated S11 Without MS, Thick blue line = Simulated S44 Without MS, Thick red line = Simulated S11 With MS, Thick wine line = Simulated S44 With MS, dotted black line = Measured S11 Without MS, dotted blue line = Measured S44 Without MS, dotted red line = Measured S11 With MS, dotted wine line = Measured S44 With MS) (b) mutual coupling between the antenna elements with Metasurface (Thick black line = Simulated S21 With MS, Thick blue line = Simulated S32 With MS, Thick red line = Simulated S43 With MS, dotted black line = Measured S21 With MS, dotted blue line = Measured S32 With MS, dotted red line = Measured S43 With MS). 50 52 54 56 58 60 62 64 66 68 70 -70 -60 -50 -40 -30 -20 -10" + ] + }, + { + "image_filename": "designv8_17_0004765_-IJERTV9IS080317.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004765_-IJERTV9IS080317.pdf-Figure2-1.png", + "caption": "Fig. 2 Anti-roll bar designed in present invention", + "texts": [], + "surrounding_texts": [ + "There are many reasons for a vehicle to lose its controllability: unfavorable weather and road conditions, lack of regular vehicle care, maintenance and repair, the driver\u2018s inexperience, sharp cornering (when passing an obstacle or underestimating a curve). A vehicle will react in a different way when the driver steers smoothly, or when the vehicle slightly declines from the lane. Loss of stability of a vehicle may cause its skidding on the road.In above mention conditions for the safety and comfort of an automobile as well as driver, stability is the major concern which needs to be considered. II. INTRODUCTION Variable Roll Stiffness System of an Automobile is a system which provides varying roll stiffness, adequate stability as well as prevents the rolling of vehicle while excessive turning. By observing the current road scenario it becomes mandatory to understand vehicle behavior in accordance with respective road conditions. Imperative condition to co-relate the vehicle behavior with different road condition is that, vehicle stiffness must vary as per various road condition. Successful implementation of this system will decreases the chances of vehicle getting rolled over. This system includes anti-roll bar, pneumatic system, coil spring, electronic control unit, bevel gears, suspensions and wheel. Anti-roll bar is connected to the suspension strut. Anti-roll bar and suspension strut are interconnected through a ball jointed link. Combination of three mitre type bevel gear mechanism is placed in centered section of antiroll bar. Which provides opposite rotational motion relatively. We have double acting cylinder with 3/2 DCV which controls engage and disengage of gear mechanism.Shape of anti-roll bars for automobile suspension systems are usually designed from a standpoint of avoiding physical interference with other components mounted on the bottom of a vehicle. Also the diameter of the bar is usually pre-selected and fixed to achieve a desired anti-roll stiffness. After having this much amount of constraints in shape and dimensions there is little design flexibility for engineers/designers. So in present invention we have configured the mechanism consisting of three mitre type bevel gears which can be engaged and disengaged. In engaged position of gears Anti-Roll bar will provide continuous traction while cornering, in disengaged position of gears it will flourish the riding comfort during uneven road conditions. International Journal of Engineering Research & Technology (IJERT) ISSN: 2278-0181http://www.ijert.org IJERTV9IS080317 (This work is licensed under a Creative Commons Attribution 4.0 International License.) Published by : www.ijert.org Vol. 9 Issue 08, August-2020 916 III. DESIGN & CALCULATION Fig. 4 Analysis of Chassis ( Total deformation) A. Design International Journal of Engineering Research & Technology (IJERT) ISSN: 2278-0181http://www.ijert.org IJERTV9IS080317 (This work is licensed under a Creative Commons Attribution 4.0 International License.) Published by : www.ijert.org Vol. 9 Issue 08, August-2020 917" + ] + }, + { + "image_filename": "designv8_17_0003852_download_33379_32633-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003852_download_33379_32633-Figure4-1.png", + "caption": "Figure 4. Normal stress\u2019 distribution on the left tooth side of the worm-wheel\u2019s tooth", + "texts": [ + " The number of used elements was 794618. All of the freedom degrees of the worm-wheels were fixed. The type of the material was structured steel (Table 1). Coordinate systems were adopted to the tooth roots. Table 1 Material properties Material Quality Structured steel Density 7850 kg/m 3 Yield stress 250 MPa Tensile strength 460 MPa Poisson factor 0,3 Young modulus 200 GPa Temperature 22 \u00b0C DOI: 10.14232/analecta.2020.1.82-88 The received normal stress results for the left tooth side could be seen on Figure 4. a) z1=1 b) z1=2 DOI: 10.14232/analecta.2020.1.82-88 The received normal stress results for the right tooth side could be seen on Figure 5. The received normal deformation results for the left tooth side could be seen on Figure 7. DOI: 10.14232/analecta.2020.1.82-88 The received normal deformation results for the right tooth side could be seen on Figure 8. a) z1=1 b) z1=2 DOI: 10.14232/analecta.2020.1.82-88 The fillet radiuses on the tooth roots are the same (r=1.5 mm) for every worm-wheels [10]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003809_el-03253472_document-Figure3.15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003809_el-03253472_document-Figure3.15-1.png", + "caption": "Figure 3.15 : Vue 3D (a) et de dessus (b) de la structure en spirale", + "texts": [ + "30) L\u2019inductance de cette ligne est alors de : 9 NS \u00cbE tan % \u00cbE* \u00cbE (3.31) Une premi\u00e8re approximation de la longueur de stub peut alors \u00eatre obtenue ainsi. L\u2019avantage de cette structure est sa simplicit\u00e9, autant au niveau de la conversion de l\u2019inductance en param\u00e8tres physiques qu\u2019au niveau de sa r\u00e9alisation. L\u2019inconv\u00e9nient majeur de la structure est le peu de param\u00e8tres permettant d\u2019avoir un impact sur la valeur d\u2019inductance, r\u00e9duisant les possibilit\u00e9s de valeurs atteignables. Nous avons \u00e9galement consid\u00e9r\u00e9 comme structure d\u2019inductance la spirale (voir Figure 3.15). Nous avons choisi une spirale de forme carr\u00e9e, car plus simple \u00e0 mod\u00e9liser et simuler sur HFSS que la spirale circulaire. Cette spirale est situ\u00e9e en bout de stub parall\u00e8le court-circuit\u00e9 afin d\u2019\u00e9viter un couplage avec la ligne principale. L\u2019inductance de la spirale est d\u00e9termin\u00e9e [49] ainsi : 9 O- 1.27Y \u00d9 O-6*GDk2 u*W 2.07 J O-\u2044 0.18J O- 0.13J O-6v (3.32) Avec la longueur de spirale moyenne lmoy et le ratio \u03c1moy exprim\u00e9s tels quels : *GDk * O- * O- 2 (3.33) J O- * O- $ * O- * O- * O- (3.34) DECRIPTION DE LA METHODE DE DESIGN DE DEPHASEURS CRLH-TL 93 La longueur de spirale interne lspi0 peut \u00eatre calcul\u00e9e en fonction de la longueur de la spirale lspi, sa largeur et l\u2019espacement entre les lignes Sspi : * O- * O- $ 2\u00d9 O-\u00c9 O- $ 2 \u00d9 O- $ 1 0 O- (3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002184_load.php_id_22112102-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002184_load.php_id_22112102-Figure9-1.png", + "caption": "Figure 9. VFPMVMmagnetic flux distribution with excitation current. (a) Initial position, (b) twentydegree movement.", + "texts": [ + ", namely, the cogging torque is reduced by 19.6% compared with that without the auxiliary slot. It means that the multi-tooth fractional slot structure is beneficial to reducing cogging torque for the proposed machine. The fact that the peak value of the cogging torque when NFMP = 1 is minimum is because the influence by low order harmonics is greatly weakened. When the excitation current is applied, the magnetic field line and magnetic density distribution of the VFMFMM are shown in Fig. 8. It can be seen from Fig. 9 that the magnetic density distribution is greatly affected after the excitation current is applied to the machine. After the excitation current is applied, the distribution of VFPMVM air gap magnetic density is shown in Fig. 10. Compared with Fig. 5, the air gap magnetic density of the machine is significantly reduced compared with that without the excitation winding, which proves the effectiveness of magnetic field weakening control. With the purpose of verifying the correctness of simulations results with the proposed VFMFMM, a 1 kW prototype and its testing platform were established, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004992_O201217653783682.pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004992_O201217653783682.pdf-Figure15-1.png", + "caption": "Fig. 15. Basic dimensions description of proposed", + "texts": [ + " Accordingly, the controller Volt-Amp requirement decreases and output torque increases. The objectives for selecting optimal value for other design ratios such as \u03b1ysts, \u03b1yrtr, \u03b1d are minimizing noise, maximizing utilization of material and insuring a mechanical intensity and critical speed well above the rated speed. Table 2 gives a list of these design radios for the BLSRM design. in which, \u03b1ysts, \u03b1yrtr, \u03b1d are defined as follows: ssty ty ss / (25) rrty ty rr / (26) rosod DD / (27) The basic dimensions of the BLSRM are shown in Fig. 15. Firstly, according to (12), the inner diameter of the stator Dsi can be estimated. So, Rout can be obtained after selecting \u03b1d: d si out g D R 2 (28) Pole widths tr and ts are the lateral length of the rotor and stator pole arcs, respectively. The two values can be achieved after choosing \u03b2st and \u03b2r. The yoke thicknesses ys, yr and rotor pole height hr can be calculated after choosing design ratios \u03b1ysts, \u03b1yrtr, \u03b1hrtr and pole arc enclosures of the stator and rotor. Therefore, shaft radius can be described as follows: rrgsh yhRR (29) when Rout, Rg and ys are known, hs can be obtained as following equation: sgouts yRgRh (30) BLSRM In this section characteristics of the proposed structure are analyzed, including magnetic flux distribution, inductance, torque and radial force vs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000211_mtime_20231027201738-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000211_mtime_20231027201738-Figure1-1.png", + "caption": "Figure 1: (a) Assembly details of friction dissipative device; (b) friction dissipative device during testing; (c); slotted downward central plate (d) friction plates and outer cover plates", + "texts": [ + " The variation of bolt preload during the test was evaluated using load cells, while the evaluation of the friction coefficient was done by a correlation between sliding force and the actual instant value of preload acting on the bolts. FEM analysis has been done to further check the functionality and to deeply analyze the behaviour of aluminium plates with different thicknesses, and the role of disc springs. In the FEM analysis, the same testing protocols and properties were taken into consideration as of the experimental test but with different thicknesses of thermal sprayed aluminium plates. The reference test specimen was similar to that used in [17]. The device shown in Figure 1 is composed of two central steel plates, one with slotted holes and the other with standard clearance holes. Two friction shims of steel coated by thermal sprayed aluminium are sandwiched on both sides between the central plates and steel cover plate. This whole assembly is fastened together using four preloaded bolts of M12 class 10.9 on the sliding side and six on the fixed side. The design of the linear friction device is carried out according to [26]. The design of the sliding force of the device is calibrated on the instrumentation available at the Laboratory of Materials and Structures of the University of Palermo", + " The disc springs were used to keep the bolt preload constant on the friction plates as possible. Three-disc springs arranged in series were added to each bolt. The bolt preload was set at 40% of the preload suggested by the standard (maximum work rate ts, max = 0.4). Thus, the expected experimental sliding force is: ,max ,max 0.5 0.4 2 4 59.4 95.04= = =s s s b pcF t n n F kN (3) Displacement was monitored by a digital length gauge placed between the fixed downward central plate and the outer cover plate (see Figure 1(b)). Two tests were carried out for each group of friction shims. Test 1 was performed using new thermal sprayed aluminium plates as friction pads having significant roughness. The force displacement curve of test 1 is shown in Figure 2(a). Two different trends can be seen in the graph, one is where the sliding force is constant and the other is where is a sudden variation of the sliding force. The sudden variation is due to the \u201cstick and slip\u201d phenomenon. It refers to the non-continuous sliding of friction pads and central plate" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure11-1.png", + "caption": "Fig. 11 The mesh model for two transmission pair.", + "texts": [ + " 10: To reduce the computational load for simulation, these two 3D models were simplified, keeping only the meshed portion of the Spiroid gear. In the calculation module of ANSYS 19.2 Workbench, the static structural analysis was selected after entering a new project, and both models were imported separately. In the engineering data section, material properties were assigned based on the data in Table 2. size of the mesing surfaces to 0.5mm, resulting in a total of 442,000 meshes. The mesh model is shown in Fig. 11. 10 2 \u00a9 2023 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2023jamdsm0073] A fixed constraint was set on the inner cylindrical wall of the worm gear and the cylindrical support is applied to the pinion cylinder, and the tangential direction was kept free. Finally, a torque of 100N\u00b7m was set on the pinion cylinder, as shown in the picture below: After the above Settings are completed, the equivalent stress and contact state of the wormwheel and pinion are calculated and results are shown in the following figures" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000173__download_12380_6543-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000173__download_12380_6543-Figure1-1.png", + "caption": "Fig. 1. A lower limb prosthesis schematic", + "texts": [ + " The first method is building the mechanical model using the several blocks inside the MATLAB Simscape multibody toolbox, such as body elements, revolute joints, and reference frames. On the other side, the second method provides the ability to import the CAD mechanical model from other CAD design software. Subsequently, the second method was used in this study by drawing the lower limb prosthesis with the SolidWorks program because it significantly decreased the model's creation time and the high percentage of mistakes associated with this process. The suggested prosthesis is built with two main parts: the thigh and the leg part, as shown in Figure 1. The thigh part represents the upper part of the prosthesis above the knee joint, with a 15 cm height, a 40 cm maximum diameter, and a weight of 0.45 kg. The second part represents the leg under the knee joint with a 40 cm height, a 20 cm foot size, and a 2 kg net weight. Finally, the MATLAB Simscape model is generated from the original CAD assembly model through the Simscape Multibody Link in (.xml) form. Then, the generated model is imported to MATLAB by using the (Smimport) instruction to transfer it to the final (" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003854_9829337_09829346.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003854_9829337_09829346.pdf-Figure5-1.png", + "caption": "Figure 5. A multilay er model of a human hand: (a) the hand model with the antenna, and (b) the multilayer model including skin, fat, muscle, and cortical bone.", + "texts": [ + " It generated a uniform magnetic fi eld distributed above the open-loop section, with a maximum fi eld at the center of the loop. Here, the folded dipole can be treated as a magnetic open loop. Furthermore, to increase the fi eld along the hand\u2019s fi ngers, a Yagi-like structure was adopted by adding one parasitic element to the rhombus-shaped folded dipole, as shown in Figure 4a. The director element was meandered to keep the size of the structure as compact as possible. An equivalent human-hand model was considered in the numerical analysis (Figure 5), so the lengths of the driven and parasitic elements of the antenna were optimized by considering the electrical properties of the human body. The thicknesses and electrical properties of the multilayer planar human hand model are given in Table 1. A photo of the fabricated prototype is depicted in Figure 4b. A photo of a glove-integrated antenna worn on a hand is shown in Figure 4c. Antennas for smart gloves were made of conductive threads or by plating a non-conductive fabric with metal or alloy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure2.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure2.9-1.png", + "caption": "Figure 2.9. Graphical synthesis of the lower control arm (LCA) and strut of a MacPherson architecture, reproduced from [30].", + "texts": [ + " Gerrard [12] exemplifies the traditional approach, where graphical rules are provided for placing joints and links to achieve a velocity specification. Matschinsky [26] also gives a method involving graphical solution from a velocity specification. Milliken and Milliken [30] provide an in-depth, step-by-step treatment for both the SLA and MacPherson architectures, again using a velocity specification. For example, the Millikens show how to orient the lower control arm (triangular link) and strut (turning-and-sliding link) of a MacPherson architecture in Figure 2.9. Graphical methods are best suited for an interactive design process, on the drawing board or in CAD, where a designer can sketch out a potential architecture and assess its suitability for achieving the motion specification. These methods are cumbersome if the task at hand is automated dimensional synthesis of tens, if not hundreds, of architectures. Fortunately, there is another approach that enables the direct computation of linkage geometry. It also allows for more than one rigid body position to be specified" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure30-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure30-1.png", + "caption": "Figure 30 Power-On Access Port FEA Results", + "texts": [ + " Additionally, the spring was assumed to be compressed twice as much as expected, a total of 0.5\u201d, which would produce a force of 14 lbf. Added to the plate was a 100 g gravity load in the Z-axis, which is higher then any qualification load the P-POD would see. The access port cover was fixed at its mounting holes, but the supporting spar from the second access port spar was ignored to get a worst case load scenario. The FEM analyzed showing constraints and loads is shown below in Figure 29, with Deflection and Stress plots shown in Figure 30. Maximum deflection for the specified load case was 0.004 inches, as shown. The maximum stress was seen on the ribs near the mounting holes, and was calculated to be 5616 psi. It is necessary that the Margin of Safety be calculated for Page 43 clarity. Margin of safety is calculated as shown in \ud835\udc74\ud835\udc7a = \ud835\udc7a\ud835\udc82 \ud835\udc7a \u2212 \ud835\udfcf Equation 2. \ud835\udc74\ud835\udc7a = \ud835\udc7a\ud835\udc82 \ud835\udc7a \u2212 \ud835\udfcf Equation 2 In this case, \ud835\udc46\ud835\udc4e is the material allowable stress, or yield stress when doing yield analysis, and \ud835\udc46 is the stress seen from the applied load. This part exhibited an extremely Page 44 high margin of safety of 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003235_8948470_09084153.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003235_8948470_09084153.pdf-Figure5-1.png", + "caption": "FIGURE 5. Analytical model. (a) Screw model. (b) Nut model.", + "texts": [ + " It should be noted that since the solution format of partial differential equations (PDEs) and the magnetization vector of PMs in both models are essentially identical, the details will be simplified in this paper. A. BOUNDARY VALUE PROBLEMS OF 3-D ANALYTICAL MODEL The air-gap magnetic field is excited together by PMs on the screw and nut. When the numbers of PM segments on the screw and nut are different, the orders of magnetic field harmonics excited by screw and nut are also different from each other. Hence, the fields excited by the screw and nut will be calculated separately in this paper, and then they are added together to obtain the distribution of the resultant airgap magnetic field. Fig. 5 shows the analytical models for calculating the magnetic fields by the screw and nut. In the case of screw model, PMs on the nut are removed. The screw model is divided into two regions, viz. PM region (Region I) and air gap region (Region IIa), as shown in Fig. 5 (a). On the contrary, PMs on the screw are removed in the case of nut model, and the air gap region (Region IIb) and PM region (Region III) are created, as shown in Fig. 5 (b). Ni and Ne denote the quantity of PM segment within one turn of PM helix on screw and nut, respectively. R1, R2, R3 and R4 indicate the boundary radii of the four regions. In order to formulate the analytical model, back irons of screw and nut are assumed to be with infinite permeabilities. And the end effect due to finite length of back irons is also VOLUME 8, 2020 84179 neglected. The magnetic scalar potential \u03d5 is selected to formulate the magnetic field distribution ofMLS. The governing equations are\u22072\u03d5i = 1 \u00b5r \u2207 \u00b7M i (i = I, III) \u2207 2\u03d5IIi = 0 (i = a, b) (5) where\u00b5r denotes the relative recoil permeability of PMs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001613_el-04520421_document-Figure6.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001613_el-04520421_document-Figure6.1-1.png", + "caption": "Figure 6.1: Construction d\u2019un moteur \u00e0 aimant permanent [11].", + "texts": [ + " These electrical machines are composed of two main components: the stationary part known as the stator and the rotating part known as the rotor. These two parts are separated by a small gap. In general, electrical machines can be categorized based on three key factors: \u2022 Stator power source: direct current (DC) or alternating current (AC). \u2022 Rotor structure: whether it uses permanent magnets, has a short-circuited winding, or employs an excited winding, among other possibilities. \u2022 Air gap structure. Figure 6.1 presents the 3D model and construction structure, while Figure 1.2 illustrates the general configuration of frameless brushless PM motors. These motors have a three-phase stator winding, which is constructed similarly to that of an AC induction motor. A three-phase stator winding is wound to produce a trapezoidal or sinusoidal distribution of air-gap flux depending on whether the motor is a BLDC motor or a PMSM one. The rotor of these motors is made up of high-performance permanent magnets firmly attached to the core", + " Ces machines \u00e9lectriques sont compos\u00e9es de deux \u00e9l\u00e9ments principaux: la partie fixe appel\u00e9e stator et la partie tournante appel\u00e9e rotor. Ces deux parties sont s\u00e9par\u00e9es par un petit espace, l\u2019entrefer. En g\u00e9n\u00e9ral, les machines \u00e9lectriques peuvent \u00eatre class\u00e9es en fonction de trois facteurs cl\u00e9s: \u2022 Source d\u2019\u00e9nergie du stator: courant continu (CC) ou courant alternatif (CA). \u2022 Structure du rotor: utilisation d\u2019aimants permanents, enroulement court-circuit\u00e9 ou enroulement excit\u00e9, entre autres possibilit\u00e9s. \u2022 Structure de l\u2019entrefer. La figure 6.1 pr\u00e9sente le mod\u00e8le 3D et la structure d\u2019un moteur \u00e0 aimant permanent. Ces moteurs ont un enroulement statorique triphas\u00e9, dont la construction est similaire \u00e0 celle d\u2019un moteur \u00e0 induction \u00e0 courant alternatif. Un enroulement statorique triphas\u00e9 est bobin\u00e9 pour produire une distribution trap\u00e9zo\u00efdale ou sinuso\u00efdale du flux d\u2019entrefer, selon qu\u2019il s\u2019agit d\u2019un moteur BLDC ou d\u2019un moteur PMSM. Le rotor de ces moteurs est constitu\u00e9 d\u2019aimants permanents \u00e0 haute performance solidement fix\u00e9s au noyau. Il est possible d\u2019obtenir diverses caract\u00e9ristiques de moteur en ajustant la disposition, la forme et le positionnement de ces aimants [10]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002788_f_version_1433318177-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002788_f_version_1433318177-Figure3-1.png", + "caption": "Figure 3. iScan mobile LiDAR system.", + "texts": [ + " \u03b4t is relative to the condition of GNSS environments and the interval of neighbouring control epochs. In environments favourable to GNSS, \u03b4t is set big, while in environments that are harsh, its value is smaller. C0 is relative to the polynomial order fitting, the condition of GNSS environments and the interval of neighbouring control epochs. The significance of \u03b4t and C0 will be detailed in Section 3.1.3 and 3.1.4, respectively. Figure 2 shows the overall flow of the LSC-based accuracy improvement method. Datasets used for validation were collected by an iScan ([28]; Figure 3) in which a set of Span-FSASPOS [29] and several laser scanners are integrated (please note that, in this paper, only the level laser scanner was used). The GNSS frequency was 1 Hz, and the IMU frequency was 200 Hz. The nominal precision of Span-FSAS POS in normal GNSS environments is 2 cm. The first dataset was collected on a rural street where GNSS conditions were relatively good, so that the number of satellites was more than 9 at most epochs. We removed some satellites from the raw data to simulate an urban environment, and the position and orientation solved with raw data were referred to as the ground truth" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure5-1.png", + "caption": "Figure 5. Flux density distribution under rated load condition.", + "texts": [], + "surrounding_texts": [ + "Figure 3 is a schematic diagram of the water flow in the water channels. It indicates that the water\ncooling system is symmetrical about the longitudinal section including the inlet and outlet.\nIn the inner rotor, there are six axial cooling slots along circumferential direction, as shown in Figure 4. They can provide a cooling wind path. On one machine side, an external fan is used to provide the force air.\nFrom the above illustration of the cooling system and mechanical structure of the CS-PMSM prototype, we know that when the cooling water with a certain pressure flows through the cooling water channels of the casing, there must be a temperature difference generated in both the axial and circumferential directions of the CS-PMSM. Besides, a temperature difference along the axial direction also exists when one side of the machine is cooled by the fan. Therefore, the thermal field analysis of the CS-PMSM prototype is a typical 3-D problem. However, 3-D thermal field analysis is much more complicated than 2-D thermal field analysis. In the machine, the high-temperature spots usually happen in the core or the windings; therefore, the 3-D model doesn\u2019t contain the end cover and bearing closure. The influence of the end cover and bearing enclosure on the thermal field in this machine is taken into account by selecting a suitable heat transfer coefficient for the end windings and end regions. The 3-D model contains the effective parts of CS-PMSM, end windings of stator and inner rotor, and the cooling system, which are described in the following text.\nThe copper losses are computed from the currents and the measured resistances, which can be\nexpressed as:", + "2 Cu ph ph3P I R= (1)\nwhere PCu is the copper loss; Rph is the per-phase measured resistance; and Iph is the per-phase current.\nThe core loss in the steel lamination regions are computed by:\n2 2 c e max h max aP K f B K fB= + (2)\nwhere Pc is the core loss; f is the magnetic field frequency; Bmax is the magnetic field amplitude; Ke is the eddy current loss coefficient; Kh is the hysteresis loss coefficient; and a is the coefficient determined by the magnetic field waveform and amplitude. Ke, Kh and a can be obtained from the loss curve versus the magnetic field [43].\nThe Eddy current loss in PMs is computed by: 2 e\npm 0\n1\n\u03c3\nT\nV\nJ P dvdt\nT = (3)\nwhere Je is eddy current density in PMs; and \u03c3 is the PM conductivity.\nUnder the rated load condition, the electrical loading, magnetic loading, current density in the slots\nare listed in Table 2.\nWith the material property changing with temperature considered, the copper resistance and the magnet B/H curve are obtained under a pre-specified temperature, and then they are modified according to the thermal-filed results. Eventually, the losses listed in this paper are the results of the electromagnetic-thermal bi-directional accordance, as shown in Table 3.", + "In this paper, the finite-element analysis (FEA) simulation mainly focuses on the steady-state thermal field analysis under the SM and DRM rated load conditions. According to the previous analysis about the cooling system of the CS-PMSM prototype, it is clear that there are mainly water-cooling, forced-air and natural convective heat transfer and conduction heat transfer in the CS-PMSM. Although radiation heat transfer is always happening, especially when the rotor speed is very low or zero [44], radiation heat transfer is normally neglected when the forced convection is mainly responsible of the motor cooling [45,46]. Hence the following assumptions in the FEA calculation are given by:\n(1) Only the convective and conduction heat transfer are considered; (2) The heat sources are uniformly distributed on the corresponding regions of the CS-PMSM.\nAccording to the symmetrical characteristic of the CS-PMSM structure and cooling system in circumferential direction, a 3-D FEA model with half of the CS-PMSM is built to analyze the thermal field, as shown in Figure 6.\nThe 3-D FEA model of the cooling water channel in the stator is shown in Figure 7. In the machine, modeling of the windings and air gap is very important for the thermal field analysis. Hence the model of the windings and air gap will be illustrated in the following text." + ] + }, + { + "image_filename": "designv8_17_0000976_ticle_1705029901.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000976_ticle_1705029901.pdf-Figure4-1.png", + "caption": "Figure 4: ADAMS simulation: axonometric view", + "texts": [ + " Once the dimensional data collection of each part of the human lower limb was completed, the dimensions of each part of the model were also obtained. Based on this, each part is modeled, and then the basic solid assembly model is established, the engineering structure is optimized, and the assembly structure and the final object are finally determined, as shown in Figure 3. The motions of the human body are mainly reflected by the joints' movements, therefore, it is essential to analyze the hinges that are used in the human model [8]. As shown in Figure 4 left, blue represents connecting rod 1, purple stands for connecting rod 2, white and red is the gas spring, green for the thigh rod, yellow for the calf rod, red for the belt connector, and brown for the belt, silver and white for foot parts, and the rest of Marker points are located as shown in the figure. The 3D model built by Solidworks was saved into x_t format and imported into Adams, after defining the material of each part as STEEL, to facilitate analysis and viewing, the model was then simplified into 8 modules, with the same modules displayed in the same color. After defining the kinematic pair of the given parts, 10 rotating pairs, 1 moving pair, and 1 spherical pair, the belt part is connected to the Earth (fixed pair) to highlight the main parts, and the belt is fixed to the thigh, as shown in Figure 4 right. Motion 1: moving pair, Joint Type: translational; Function(time): 25*sin(time); Motion 2: rotating pair, Joint Type: revolute; Function(time): 25.0d* sin( time). Define damping (including friction) to the moving pair, due to friction F=\u03bcmg, according to the table: 0.1\u2264\u03bc\u22640.4, take \u03bc=0.2, then F=\u03bcmg=0.2\u00d71\u00d79.8\u22482N, set the damping added by the drive is 8N, assign the total damping=10N. The damping is set to 10N, and the damping friction F=1N is defined for each rotating pair. In the postprocessing module, the End time is set to 12 and the Steps are set to 200" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure75-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure75-1.png", + "caption": "Figure 75. Finished parts for numerical model", + "texts": [], + "surrounding_texts": [ + "1 = variable 1 2 = variable 2 3 = variable 3 br = bearing comp = compressive extes = extensometer i = at ith data point long = longitudinal direction max = maximum xxii min = minimum pin = pin location s = symmetric spec = specimen ten = tensile trans = transverse direction ult = ultimate x = x-direction xx = in the axial direction for the +/-45\u00b0 shear tensile test y = y-direction xy = xy-direction (plane) 1 CHAPTER 1: INTRODUCTION In this chapter, previous and current thesis work is introduced. Section 1.1 introduces the different two different types of aircraft structures. In Section 1.2, the differences between an adhesively bonded joint and a mechanically fastened joint are explained. In Section 1.3, previous work is mentioned, considerations are made in order to avoid testing parameters, which have already been tested, and the three different failure mechanisms are explained. Section 1.4 explains the thesis goal and the thesis scope. 1.1 Introduction to Conventional & Advanced Composite Structures When you think of an aircraft\u2019s wing, it is composed of multiple panels and not usually made as a single piece. The use of joints becomes essential in an aircraft\u2019s wing (since joints serve to attach multiple structural components together to form one part). Ideally, the designer wants to avoid using them, since they can contribute a significant amount of weight to the overall aircraft\u2019s structure. Current aircraft manufactures are transitioning from a conventional aircraft structure to an advanced composite structure since the advantage of switching to an advanced composite structure is the significant reduction in parts and joints. Composite materials have desirable characteristics such as being: very stiff, extremely strong, and extremely light. For example, the Airbus\u2019 A350 aircraft structure is made up of 53% composite materials [1]. Even though the total amount of joints can be significantly reduced, that does not mean they can be avoided altogether. 2 As composites become more widely used in the Aerospace Industry, there still lies limited research in their ability to perform as joints. Their main flaw is their poor behavior in redistributing stress concentrations. Even though there has been a lot of research in composite joints, not enough advancement has been made compared to its metal counterpart. Metal joints (in particular, Aluminum joints) have been used for years in the Aerospace Industry. Currently, composite joints are overdesigned (made a lot thicker than they need to be) which leads to weight penalties. Design that is more detailed needs to done on composite joints in order to improve its ultimate bearing strength. 1.2 Introduction to Adhesively Bonded Joints & Mechanically Fastened Joints Two types of joints exist: one is the mechanically fastened joint, and the other is the adhesively bonded joint. In Figure 1, one can see an adhesively bonded single shear joint, a mechanically fastened single shear joint and a mechanically fastened double shear joint. The region between the two plates, in the adhesively bonded double shear joint, is the thin layer of structural adhesive used to bond both structural components together. Adhesively bonded joints are typically lighter but are often more difficult to design. No holes need to be made in an adhesively bonded joint. Reduction of holes reduces the amount of stress concentrations. Adhesively bonded joints can be problematic since the surface finish needs to be accounted for to achieve a strong bond between two surfaces. Another issue with adhesively bonded joints is that they cannot be removed as easily as a mechanical joint. 3 Mechanically fastened joints are widely used in the Aerospace Industry since they are more practical in the sense that they can be easily removed if a part needs to be replaced, repaired, or checked. Two types of mechanically fastened joints exist: single shear and double shear. In addition, a mechanically fastened joint can contain many fasteners. Mechanically fastened joints require a hole through both structural components, which creates stress concentrations. Both of the structural assemblies are held together by a bolt, and nut. 4 1.3 Previous Literature on Mechanically Fastened Composite Joints Numerous papers have been made on mechanically fastened composite joints, and in this section, the most important finds will be mentioned. According to Alan Baker[3], for a mechanically fastened double shear joint, load is transferred mainly through compression on the internal face of the fastener holes and as well as on a component of shear on the outer faces of the plate due to friction. Mechanically fastened composite joints can be made very durably but the designer needs to spend a longer time in the design process. According to Okutan [4], problems arise when the designer wants to analyze them since they have an anisotropic and heterogeneous nature. According to Chen [5], the behavior of a composite joint could be influenced by four parameters. The first is the material parameter. The material parameter includes fiber types, form, resin type, fiber orientation, laminate stacking sequence, material cure cycle, etc. The second is the geometric parameter. This includes the specimen width (W) and the hole edge distance (e). These are usually reported as W/D and e/D ratios where D is the diameter of the hole. A huge contributor to the strength of the specimen is the specimen thickness (t). The pitch is the distance between two or more holes in a multiple hole composite joint. The third (also very important) is the fastener parameter. This includes fastener type, fastener size, washer size, hole size, and tolerance. The last is the design parameter. The design parameter includes loading type (tension, compression, fatigue), loading direction, loading speed, hydraulic clamping pressure, joint type (single lap, double lap), environment, etc. 5 The lay-up sequence also played a significant role in the overall strength of the double shear joint, as well. Quinn & Matthews [6] studied in detail the effect of stacking sequences on the pin bearing strength in glass-reinforced plastics. They concluded that placing a 90\u00b0 layer ply on the outer surface of the laminate increased the overall bearing strength. Liu [7] tested different laminate thicknesses by varying the bolt diameter. He concluded that thick laminates with smaller diameter holes and thin laminates with larger diameter holes were a lot weaker than laminates with similar hole and laminate thicknesses. Stockdale & Matthews [8] studied the effects of bolt clamping pressure and found that boltclamping pressure played a huge role in the overall strength of the composite joint. Kim [9] tested to see the effects of temperature and moisture on the strength of graphite-epoxy laminates. From this experiment, the actual stress distribution of the joint is very difficult to find since the region is so small. The use of strain gages is impractical because that region is under a very high stress so any kind of strain gage applied would crush because of the force. That is why numerous researchers have been working on methods of modeling composite joints with the help of various finite element programs. The load capacity of a laminate is severely degraded due to the effects of hole clearance and friction. Hyer & Klang [10] investigated this phenomenon with a pin-loaded orthotropic plate. Pierron [11] used Abaqus to calculate the stress distribution around the hole of a woven composite joint. Most finite element modeling was done using 2D shell elements and recently there has been an increased amount of 3D modeling of composite joints. Previous researchers mention that the joint strength depends mainly on the failure criterion. 6 Only a small section of the bearing stress vs. bearing strain curve is linear, and then after, it becomes nonlinear. Stress concentrations cause crushing in a small section of the geometry, making it a very difficult nonlinear problem. Chang [12] created a 2D finite element model and assumed a frictionless contact with a rigid pin and a cosine normal load distribution in the pin-hole boundary. Another difficulty in modeling the composite joint requires the user to combine the failure criteria with a property degradation model. As the composite takes more load, the actual material properties are degrading over time, which would mean the modulus is decreased after each new load is applied. Lessard [2] used a 2D linear model along with a non-linear model to predict the strength of the composite joint. There are five different kinds of failure, which can occur in a laminate: matrix tensile, compressive failure, fiber/matrix shearing, fiber tensile, and fiber compressive failure. The Hashin failure criterion is an important criterion used to characterize failure within a laminate. 1.3.1 Previous Literature on Loading Rate Effects on Mechanically Fastened Composite Joints In flight, the aircraft might experience various dynamic loading conditions, so not only do composites need to be tested in quasi-static loading case, but also in a dynamic load case. Metals are not as load rate dependent as composite materials. Ger [13] tested a number of carbon and carbon fiber glass hybrid composites at dynamic loading rates of 6 to 7 m/s. The double shear joint configuration carried more load at high loading rates. It was also noted that for all joint configurations the stiffness of the joint increased significantly with 7 loading rate. In addition, what was noted was that the total energy absorption of the joint decreased significantly in the dynamic tests. Contradictory to Ger [13], Li [14] tested different types of joint configurations subject to a bearing load and found that energy absorption increased. Li [14] tested at higher rates of 4-8 m/s and found this interesting trend. The dynamic behavior of composite joints is much more complicated than its behavior for the quasi-static condition due to the involvement of strain rate and inertial effects. Li [14] concluded that crashworthiness design of tested composite joints could be based on their tensile strength design. Ger [13] mentioned there must be a significant safety factor applied to take into account bearing strength variations with loading rate. The failure modes might also be affected due to an increased loading rate. 1.3.2 Types of Failure in Mechanically Fastened Composite Joints According to Larry Lessard [2], it has been observed experimentally that mechanically fastened composite joints fail under three basic mechanisms: net-tension, shear-out, and bearing (in addition, combinations of these mechanisms are often given separate names). Typical damage mechanism is shown below in Figure 2. Looking at previous work, a net-tension and a shear-out failure are more catastrophic than a bearing failure. The best way to see if a bearing failure has occurred is to look at the bearing stress vs. bearing strain plot. Once the stress gets to its peak value and suddenly drops off to zero, then one can conclude it was a shear-out or a net-tension failure. If after the ultimate bearing stress, the specimen continues to carry load but deforms as a result, this means that the joint was designed very safely. According to Okutan [4], the optimum orientation for a bearing type of failure is a quasi-isotropic laminate orientation. A quasi-isotropic laminate 8 orientation means the laminate has the isotropic properties in plane. According to USNA [15], a quasi-isotropic part has either randomly oriented fiber in all directions, or has fibers oriented such that equal strength is developed all around the plane of the part. The geometry of a mechanically fastened composite joint is quite complex since it can affect the failure mode of the double shear joint specimen. Kretsis [16] & Matthews [16] tested fiber glass and carbon fiber reinforced plastics and found that the width(W), end distance(e), diameter of hole(D), and laminate thickness(h) all contribute to the overall mechanically fastened double shear joint strength. The most interesting aspect is that as the width of the specimen decreases to a specific amount, the mode of failure changes from bearing to net-tension. The W/D (width to hole diameter ratio of the composite double shear joint specimen) must be at least 5 order to avoid the net tensile type failure. Another interesting thing to note is when the end distance of the hole is a certain distance from the edge of the plate, the failure turned from bearing to shear-out (where shear-out is considered a special case of bearing failure). 9 1.4 Thesis Goals & Scope In the preceding sections of this thesis paper, the word double shear specimen will be used to represent one test specimen with a mechanically fastened double shear joint configuration. The goal of the thesis is to determine how the strength of a composite double shear joint is affected by two different cure cycles and five different loading rates. The composite joint will be tested in the double shear case and the laminate orientation was decided to be a quasi-isotropic laminate (based upon based on Yeole\u2019s double shear experimental results [17]). Yeole [17] tested three different laminate orientations in his thesis, and concluded that a quasi-isotopic laminate took the highest stress. Yeole [17] also mentioned that the testing of composite materials at fast loading rates could be an interesting topic to explore. ASTM 5961[18], which is the ASTM for bearing response of composite materials, required an extensometer to measure the relative pin displacement since using crosshead displacement is not an accurate method. A fixture was designed and manufactured in order to accommodate an extensometer. Finally, the numerical model was made to validate only the linear elastic portion of the experimental results. There are seven chapters in this thesis. Chapter 1, the introduction, includes a brief introduction to: composite materials, the difference between adhesively bonded joints and mechanically fastened composite joints, and the loading rate effects on mechanically fastened composite double shear joint bearing strengths. It also includes a brief literature review, the statement of the problem and the objective and organization of thesis. Chapter 2 focuses on manufacturing of the double shear specimens and the tensile specimens. Chapter 3 focuses on the experimental material testing 10 procedure conducted on the MTM49 Unidirectional Carbon Fiber pre-preg. It also explains the double shear fixture used for the testing. Chapter 4 focuses on the equations used in the experimental and theoretical calculations. Chapter 5 introduces the experimental result validation and then discusses the experimental results. Chapter 6 introduces: the numerical model, which was created using Abaqus 6.14 software, the convergence plot, and lastly, what, influences the numerical results. Chapter 7 is where the experimental results are compared to the numerical finite element results. Lastly, Chapter 8 is where the conclusions are drawn and different recommendations are made for the future work. In the reference section, one can find most of the related topics in the form of theses, books, reports and even papers published in numerous journals. In the appendix section, one find: drawings of the fixture, a tutorial on setting up the Bluehill2 double shear test method, a tutorial on finding the unknown engineering constants with the Autodesk software, a tutorial on outputting the force vs. hole deformation in Abaqus, and a tutorial on the composite double shear specimen Abaqus model. 11 CHAPTER 2: MANUFACTURING & PREPARING OF THE SPECIMENS This chapter will introduce the type of specimens that were manufactured and tested in the Instron machine along with their dimensions. All the dimensions were based on published ASTM test standards. ASTM is an international standards organization, which develops and publishes voluntary consensus technical standards for a wide range of materials, products, systems and services. 2.1 Tensile Specimen & Double Shear Specimen Dimensions The dimensions for the 0\u00b0 tensile specimens and the 90\u00b0 tensile specimens were found in ASTM D3039 [19] Standard test method for tensile properties of fiber-resin composites. The dimensions used for the shear modulus +/- 45\u00b0 were found in ASTM D3518 [20]. Below in Figure 3, one can see all of the tensile specimen dimensions for each specific fiber orientation angle. Figure 4 shows a drawing of all four different fiber orientation tensile specimens. The +/- 45\u00b0 shear specimens and the quasi-isotropic laminate specimens had the same dimensions. Figure 5 shows the dimensions, based on ASTM D5961 [18], of the composite double shear specimens. The quasiisotropic tensile specimens were tested to see how the theoretical material properties matched. 12 13 2.2 Manufacturing Process In the Cal Poly\u2019s Aerospace Engineering Composites Lab, there are two ways to manufacture a composite. One can use pre-preg material or apply a wet layup process. Pre-preg material is a lot easier to use since it already has the resin infused inside the material. In order to preserve the resin in the pre-preg material, it needed to be stored in a freezer at low temperatures. Once the pre-preg material is thawed, then the user is able to apply it to a mold or create a plate out of it. The second way, the wet-layup process, consisted of having the fibers in their pure form, which usually come in a roll, and having a two-part epoxy. Once the fibers were cut out from the roll, the two-part epoxy is mixed with the correct ratio and then applied to the dry fibers. The part is then sealed, with a vacuum bag (where all the air is removed from the part). Then the cure cycle of the 14 resin is applied to the vacuum-bagged part. All of the tensile and double shear specimens were made on the heat press. When making a composite plate in the heat press, the user needed to sandwich the laminate between two nonporous sheets and two 0.25 in. thick Steel plates. Figure 6 shows how the heat press cure process was set-up. The non-porous sheets served to prevent the resin from sticking to the steel plates. The composite plate, the steel plates and the non-porous sheets were placed inside the heat press and then the cure cycle was programmed. Once cured, the composite plate was cut into various size specimens. 2.2.1 Double Shear Specimens All the composite double shear specimens were made with the quasi-isotropic laminate orientation. The quasi-isotropic laminate orientation, [0 0 +45 -45 +45 -45 90 90]s, is short hand for [0 0 +45 -45 +45 -45 90 90//90 90 -45 +45 -45 +45 0 0]. The subscript s means that the laminate 15 is symmetrical about the last ply (which in this case is a 90\u02da ply). The alternate cure cycle was the Cytec\u2019s MTM 49 cure cycle and the datasheet cure cycle was the Umeco\u2019s MTM 49 cure cycle.. The material was first thawed since according to the Umeco\u2019s [22] MTM 49 datasheet, if the roll is open to the environment, condensation will occur on the pre-preg material, which will degrade the quality and the aesthetic look of the material. Sixteen 12 in. by 12 in. plies were cut out and orientated in the quasi-isotropic laminate orientation of [0 0 +45 -45 +45 -45 90 90]s. All the respective angles within each ply of the laminate were carefully kept within \u00b1 1\u00b0. Shown in Figure 7, a protractor was used to make sure each ply in the laminate was within \u00b1 1\u00b0. Once all the plies were stacked very carefully (in order to prevent air pockets from occurring within the laminate), the cure cycle was programmed into the heat press. Air pockets create areas where delamination can occur, which leads to the formation of cracks. Cracks can severely weaken composite structures. The second step consisted of programming the cure cycle into the heat press. Shown in Figure 16 8, is Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22]. Two different cure cycles were tested to see its effects on the material\u2019s double shear bearing stress. Increasing the dwell temperature from 248\u00b0F to 275\u00b0F and increasing the dwell time from 60 minutes to 90 minutes both affect the mechanical characteristics of the resin. The dwell temperature is the temperature which is held constant in the cure process (for this material, it occurs after the temperature ramp up stage). The dwell time is the duration of the dwell temperature stage. Each different carbon fiber matrix system will have its own recommended cure cycle printed in its specific datasheet. In the experimental section, one can see the difference in mechanical properties of the material based on the two different cure cycles. The first cure cycle was Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22] (also known as the alternate cure cycle). The heat press was adjusted to the specific cure cycle. First, the cure cycle temperature ramped up from room temperature of 77\u00b0F to 275\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 275\u00b0F for 90 minutes. After the 90 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. A uniform pressure of 2 psi was applied on top and bottom of the plate. 17 The second cure cycle was Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [21], shown in Figure 9 (also known as the datasheet cure cycle). The heat press was adjusted to the specific cure cycle. First, the press ramped the temperature up from the room temperature to 248\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 248\u00b0F for 60 minutes. After the 60 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. The pressure was held constant between both cure cycles. 18 The third step consisted of preparation of the test specimens. Once the composite laminate finished curing, the material was removed from the press and was cut with a tile saw, which had a diamond-coated blade. The tile saw had an adjustable clamp that helped keep the cuts within 0.1 of an inch. Figure 10 shows the tile saw used to cut the specimens. A straight cut was made on the composite laminate, in order to clean up the edge of the plate. Next, the top side of the plate was aligned to the straight section of the small tile saw. The cuts were made carefully in order to keep a 90\u00b0 angle on the side of the cured laminate. Once all the cuts were made, and the zero direction of the laminate was located accordingly, specimens were cut to the correct width. Based on ASTM D5961 [18], a W/D (specimen width to hole diameter ratio of the composite double shear joint specimen) of 6 and e/D (hole edge distance to diameter of hole ratio) of 3 were used. These geometric conditions guaranteed the double shear composite specimens failed in bearing and not in net-tension or shear-out. Based on these geometric conditions, the specimens needed to be 1.5 in. wide by 5.5 in. in length. The tile saw 19 was used to trim the long 1.5 in. wide specimens to their final length of 5.5 in. A small aluminum block was clamped to the tile saw, which helped minimize variations in the length of all the specimens and allowed multiple specimens to be cut at the same time. After the specimens were cut to their specified length and width, they were grouped into sets of five. A mini microfiber-board fixture was created in order for five holes to be drilled at the same time. The fixture was clamped into the drill press. Five composite double shear specimens were stacked onto the drill fixture and the top left corner of each composite double shear specimen was aligned to the top left corner of the fixture. An Aluminum template was placed on top of the composite double shear specimens and was used to align the 0.25 in. diamond coated end mill bit. Once the composite double shear specimens were aligned accordingly, a small c-clamp was used to constrain the specimens along with the Aluminum template from moving/rotating during the drilling process. In Figure 11, one can see the fixture, the Aluminum template and the end mill bit used for the hole drilling process. 20 Once the holes were created for all the composite double shear specimens, there needed to be a 0.5 in. wide horizontal slit on each face of the composite double shear specimens. A thin Aluminum template was created to assist in locating a specific distance from the hole. This slit needed to be placed accurately within a tolerance of 0.01 in. The template is shown below in Figure 12, and the flat edge of the Aluminum template was used to locate the slit location. The slit needed to be as horizontal as possible and deep enough to catch the moveable knife-edge of the extensometer. 21 Emery cloth helped distribute the high clamping pressure (which is applied by the hydraulic clamps) which occurred at the bottom of the double shear specimen and the emery cloth prevented the composite double shear specimen from slipping during the test. Aluminum tabs were not needed for the double shear test because the specimens failed before reaching 7,000 lbs. The emery cloth works up to a maximum load of 7,000 lbs. The emery cloth was 1.5 in. wide and had a grit level of 120, which is shown in Figure 13. Each specimen only needed emery cloth on one end. Only a 3 in. long piece was needed to cover all of the specimen\u2019s width. A small portion of painters tape served to hold the emery cloth in position. The emery cloth was also reusable; so one piece of emery cloth could be used on two or more specimens. In Figure 13, on the right, shows the ready-to-test composite double shear specimen. 22 2.2.2 Tensile Specimens The same method was applied for the composite tensile specimens, except that these specimens did not have a hole. Stacking the layers needed to be done in a very careful manner in order to prevent misalignment. Once the composite shear modulus specimens and the 90\u00b0 composite tensile specimens were cut to 10 in. by 1 in., then all that was needed was to apply the emery cloth to the ends. Painters tape was used to secure the emery cloth in position. Then, the composite shear modulus specimens and the 90\u00b0 specimens were ready for testing. The 0\u00b0 unidirectional carbon fiber composite tensile specimens required 2 in. long aluminum tabs (as specified by ASTM 3039 [19]). Sandpaper was used on the surface, near the ends of the 0\u00b0 unidirectional carbon fiber composite tensile specimens. A small section of the surface was 23 abraded, and then, acetone was used to clean the surface. Structural adhesive was used to bond the Aluminum tabs to the 0\u00b0 unidirectional carbon fiber composite tensile specimens. After a full day of curing, the 0\u00b0 unidirectional carbon fiber composite tensile specimens were ready to be tested in the Instron 8801 machine. In Figure 14, one can see the ready-to-test 0\u02da unidirectional carbon fiber composite tensile specimens and the +/-45\u02da composite shear modulus specimens. 24 CHAPTER 3: TESTING PREPARATION & PROCEDURE In this chapter, the test preparation and procedure are explained thoroughly. Section 3.1 introduces the type of testing machine used for the experiment. Various test recommendations are made and included inside the preceding subsection. The Auto-Loop tuning feature is explained in detail and an example is made to assist the user in using this feature. The Specimen Protect feature in Bluehill2 is explained with full detail, which helped produce very consistent experimental results. Finally, in Section 3.3, the tensile double shear test and tensile test procedures are explained. The design and set-up of the double shear fixture is shown in detail as well. In the Appendix, the Bluehill2 test method creation was explained for a double shear tensile test. 3.1 Intro to Uniaxial Testing Using the Instron 8801 Servo-hydraulic Test Machine All the material tests were conducted on an Instron 8801. This machine is a dual column servohydraulic testing system. It meets the challenging demands of various dynamic and static testing requirements. The machine allows the user to hook up external force or strain transducers. A dynamic knife-edge extensometer was used for both, the tensile and double shear tests. The machine works in conjunction with a controller, which can be used to control the machine without the use of a computer. A servo-hydraulic system is composed of an actuator, which can apply a tremendous amount of load onto a test specimen. The load cell has a +/- 100 kN limit which means it can measure accurately up to +/- 22,000 lbs. axial force (in compression/tension). For the tensile double shear test, the maximum load that was seen during the test was around 1,700 lbs. and for 25 the tensile test, a maximum load of 7,000 lbs. was seen. The thicker the laminate, the higher the load the specimen could take before failure. Shown in Figure 15, one can see the Instron 8801 testing setup. The machine\u2019s crossheads contain metal jaws, which (powered by a hydraulic system) are able to clamp the specimen. The hydraulic clamping pressure is adjustable so for standard tensile testing, the pressure is set to 160 bar and for testing fragile composite resins, one would want to drop the pressure to 80 bar. Lowing the hydraulic pressure helped reduce premature specimen cracking. The crosshead mechanism loaded with a specimen is shown below in Figure 16. The specimen is placed carefully between two the hydraulically powered metal clamps which secure 26 the specimen in place. 3.1.1 Instron Servo-hydraulic Test Machine Recommendations For determining the modulus of elasticity along with the modulus of rigidity, the most accurate measuring tools were the extensometer and the strain gage. The crosshead displacement was not very accurate since the system displaces due to the compliance in the grips, and the actuator assembly. This displacement of the crosshead can cause unreliable results in the modulus of elasticity where accuracy is very important. The Instron crosshead and the extensometer both yielded slightly different stress/strain curves. This difference in stress/strain curves is due to the Instron crossheads displacing a little more than the extensometer. The extensometer measured only the deflection of the specimen relative to both of the extensometer knife-edges. The extensometer 27 had a gage length of 0.5 in. and a knife-edge width of 0.5 in. The dynamic extensometer, catalog no. 2620-826, can be seen in Figure 17. The top knife-edge is fixed and the bottom knife-edge records precise deflections. The extensometer was attached using two rubber bands. The rubber bands were wrapped multiple times around the specimen to prevent the knife-edges from slipping. Whenever the extensometer was handled, the safety pin was in place at all times. If the user wants to run a three-point or 4-point bend test, the crosshead displacement is accurate enough to capture the vertical displacement accurately. If the user wants even more accuracy, they are able to hook up an extensometer to the three-point bend fixture and record vertical displacement with that device rather than the crosshead displacement. The Instron 8801 machine has a few features, which need to be utilized in order to minimize testing errors. The load and position calibration should never be changed or conducted. Before any 28 test is conducted, the user should Auto-loop tune the load cell only once. Each time a new material is being tested; for example, carbon fiber compared to Aluminum, the load cell should be Autoloop tuned. A list of load cell control gains should be recorded in a separate table for each material, to avoid having inexperienced individuals auto-loop tune the machine. Some precautions in the auto-loop tuning process include to never auto-loop tune a material that will fails under 120 lbs. and to never set the force amplitude above 500 lbs. This may cause the machine to cycle through very rapidly. 3.1.2 Tutorial on Auto-Loop Tuning of the Load Cell for an 1 in. wide By 1/16 in. Thick Aluminum Specimen Each time a new type of material is tested in the machine the load cell needs to be auto-loop tuned whether it be Aluminum, Steel, carbon fiber, hemp composite, fiberglass or any other composite material. Auto-loop tuning the force insured that the load cell is set up to perform accurately for each specific material. The auto-loop tuning tool adjusted various gains on the load cell controller. This was done through the Bluehill2 console (under the load cell menu). Measure the cross-sectional area of the tensile specimen and note its yield stress (if a metal) or ultimate stress (if a brittle material). For example, for Aluminum, the yield stress is around 35 ksi and the tensile specimen had a cross-sectional area of 0.062 in.2. Make sure to apply a force which keeps the material well under its yield or ultimate stress (so 25 ksi was applied to the Aluminum specimen). 29 Insert the Aluminum tensile specimen into the hydraulic clamps and load the specimen to 1,500 lbs. Also, set the amplitude force to 500 lbs. In the auto-loop tuning wizard, the Proportional gain (P) needs to be set to one before any auto-loop tuning is conducted. The specimen will be exposed to a cyclic load of 1,500 lbs. \u00b1 500 lbs. After the auto-loop tuning completes, it will say Auto-loop tuning completed successfully and then, in the next window record the P, I, D and L values. The P value should be 12.564, the I value should be 0.56, the D value should be 0.49 and the L value should be 0.8. These gain values are essential to the auto-loop tuning process. Each time a new material is tested, it is advised to specify the correct P, I, D and L values in the console and only if those values are unknown then the material needs to be auto-loop tuned. After running the auto-loop tuning tool on the MTM 49 unidirectional carbon fiber material, the P (proportional gain) equaled 13.481 and I (integral gain) equaled 0.578. Both D and L equaled zero. Typically, the material needs to be auto-loop tuned in a load range where accuracy is needed. This range is typically, where the modulus of elasticity is measured in between 25% to 50% of ultimate stress as stated by ASTM D3039 Tensile Properties of Polymer Matrix Composite Materials [19]. If the material fails during the auto-loop tuning process, the actuator will shake violently and will not stop itself. Hit the red emergency stop button on the control panel or hit the red button on the Instron servo-hydraulic machine to power off the actuator. Start back up the machine and run the auto-loop tuning tool again at a lower force. 30 3.1.3 Tutorial on Specimen Protect The specimen is prone to premature failure due to high clamping forces exerted by the hydraulic clamps. Instron's Specimen Protect feature protects a specimen against this phenomenon. This feature is found inside the console, it is labeled Specimen Protect, and the symbol looks like small shield. Before using the Specimen Protect feature, go into the console, enter the Specimen Protect option menu and make sure the load threshold is set to 44 lbs. Clamp the bottom of the test specimen. Once the bottom of the specimen is clamped, move the actuator up until the top of the specimen sits in between the top crosshead's clamps. Turn on the Specimen Protect feature in the console and this will automatically move the bottom crosshead slightly up or down in order to prevent the specimen from experiencing more than 44 lbs. After both the top and bottom of the specimen are clamped, turn off the Specimen Protect feature and continue with the test. Every time a new specimen is inserted into the hydraulic clamps, this feature needs to be utilized in order to prevent premature failure. 3.2 Bluehill2 Test Preparation The machine was connected to a Windows desktop and from there Bluehill2 and the console were used to monitor machine inputs and outputs. According to Instron, the console software provides full system control from a PC: including waveform generation, calibration limit set up, and status monitoring. In real-time, Bluehill2 outputted various experimental results: strain values, load values, displacement values, and exc. All the raw data was outputted into an Excel file, which 31 could be used for post-processing calculations. 3.2.1 Bluehill2 Test Parameter Setup The main software of interest was the Bluehill2 software. In Bluehill2, the user has options of changing various testing parameters. Each test can be created and saved to a separate testing file, which can later be accessed when the user needs to conduct that type of test. Three different tests were created in the Bluehill2 software. The tensile test and tensile double shear test were created with the Bluehill2 software. Before a test file is created, it is required of the user to know what values are of interest for a specific structural test. The ASTM should exactly specify which the testing parameters should be used for the specific test. ASTM D5961 [18] suggested to test at a load rate of 0.05 in./min., to sample at a rate of at least 2 samples per second, and to output the extensometer displacement instead of the crosshead displacement. It also specified to run the test until a maximum force is reached and until the maximum force decreased by 30%. If the force didn\u2019t drop to 30% of the maximum; run the test until the pin displacement is equal to half of the hole diameter. For the pin displacement, the test ended once the extensometer read a displacement of 0.1 in. since that was the maximum range of the extensometer. The test specimen slipped in the grips when the force in the force vs. time plot flattens out, with respect to time, the specimen was slipping. The hydraulic pressure was manually set to 160 bar on the side of the machine. The fastener, which secured the Steel collars to the sides of the specimen, was hand tightened. Five different loading rates were 32 applied and adjusted accordingly inside the Bluehill2 software. 3.3 Instron Experimental Test Procedure The Instron start-up checklist was followed in the lab in order to start the machine safely. The first step of the checklist was to turn on the main power switch in the back of the lab. After turning on the main power switch, the next step was to turn on the Instron controller by pressing the power switch in the back of the Instron controller. Once the controller warmed up fully, a small blinking light appeared on the load calibration section of the controller. The calibrate button was pressed on the load menu of the controller. Next, the Cal button was pressed. Once the Restore button was pressed, the machine was fully calibrated even though it read \u201cCalibration not restorable.\u201d The desktop was turned on, and once the system booted up, the Bluehill2 software was started. As the software started up, it automatically started the console. The console is how the computer communicates with the Instron machine. The extensometer was plugged into the back of the Instron machine and it showed up under Strain 1 (in the Bluehill2 software). Once the extensometer was plugged in, it flashed in the console screen reminding the user that it needed to be calibrated. The extensometer\u2019s calibration was restored to a previous calibration. From this point on, the tensile test, or the double shear bearing test could be started. 3.3.1 Tensile Testing Procedure Before starting any ordinary tensile test, the user needed to have at least six tensile specimens 33 prepared for the test. For each tensile specimen, the thickness, width and gage length (distance between the tabs) were recorded. The Specimen Protect feature was also used when initially clamping the specimens. The first composite tensile specimen was tested to failure (without the extensometer), in order to find its ultimate failure load. A limit load was created for the extensometer and was decided based on the ASTM D3039 [19]. As stated in ASTM D3039 [19], the material's modulus of elasticity can be measured anywhere between 25% and 50% of its ultimate load or yield load (if it is a metal). The limit load was calculated by multiplying the 1st specimen\u2019s ultimate load by 0.25 and this value was specified in Bluehill2\u2019s end of test criteria. In Bluehill2 software, there is an option of recording the strain using an extensometer and once the limit load is reached, the test will pause allowing the user to remove the extensometer. Next, the remaining five composite tensile specimens were tested. The next composite tensile specimens were loaded in the machine and the extensometer was attached for each specimen. Figure 18 shows a composite tensile specimen (with an extensometer mounted on its surface). Once at the limit load, the extensometer was removed, and the test continued up to the ultimate load. Note that the initial modulus recorded by the extensometer was very accurate, and after removal of the extensometer, the crosshead took over and the accuracy declined. 34 3.3.2 Double Shear Testing Procedure Once the standard Instron startup procedure was completed, the tensile double shear Bluehill2 test method was started. In the Appendix, one can find a detailed tutorial on the tensile double shear Bluehill2 test method. Procedure A double shear tension, in ASTM 5961 [18], was followed closely. The user needed to make sure that all the dimensions were recorded such as specimen width, specimen length, and specimen thickness and distance between the edge of the specimen to the hole edge. The fixture used for the double shear test consisted of an assembly made up of three cold drawn Steel plates with two bolts and nuts connecting all three plates. The double shear fixture is shown in between the clamps on the left in Figure 19. The double shear fixture is shown, in the center, in Figure 19. The close-up of the collar-specimen assembly is shown, on the right side, in 35 Figure 19 as well. Each double shear joint specimen was sandwiched between two Steel plates, two Steel collars, four washers and a nut, which can be seen on the left and the center in Figure 20. The extensometer, as required by the ASTM 5961 [18], is fixed on the fixture with a small steel plate and two bolts, shown on the right in Figure 20. The extensometer's knife edge was carefully placed inside the slit of the specimen and secured with a rubber band. The nut which held the screw assembly together with the specimen was only hand tightened. In the Bluehill2 software, as stated earlier, the end of test occured if the maximum force droped by 30% or if the maximum extensometer displacement was 0.1 in. This end of test criteria worked perfectly for the 0.05 in./min., 0.1 in./min. and 1 in./min. loading rates. But for the 2 in./min. and 6in./min. loading rates, the maximum extensometer displacement was lowered to 0.05 in. At faster loading rates (above 2 in./min.), the actuator had problems stopping immediately at very small deflections (0.1 in.) so applying this adujstment prevented the extensometer from accidently breaking due to over-deflection of the crossheads. 36 37 CHAPTER 4: THEORETICAL SOLUTION METHOD In this chapter, information is given on the equations that were used to find all of the mechanical properties of the material used. The theoretical equations used to come up with the macromechanical behavior of a lamina and laminate are included as well. 4.1 Experimental Equations 4.1.1 Equations Used for Unidirectional Carbon Fiber and Aluminum Double Shear Specimens The width to diameter ratio of the specimens needed to be measured and recorded. Below, W, is the specimen width, and D is the diameter of the hole. \ud835\udc4a \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc4a/\ud835\udc37 The edge to diameter ratio of the specimens needed to be measured and recorded. \ud835\udc38 \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = (\ud835\udc54 + \ud835\udc37/2)/\ud835\udc37 The diameter to thickness ratio of the specimens was measured and recorded. Below h is specified as the thickness of the specimen. \ud835\udc37 \u210e \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc37/\u210e The bearing stress was calculated by dividing the force, P, by the force per hole factor, k (equal (1) (2) (3) 38 to 1 for double shear test), with the diameter of the whole, D and by the thickness of the specimen, h. \ud835\udf0e\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strength was calculated by dividing the maximum force, Pmax, by the force per hole factor, k, with the diameter of the hole, D and by the thickness of the specimen, h. \ud835\udc39\ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strain was determined from the extensometer displacement, \ud835\udeff\ud835\udc56 divided by the k, force per hole factor, and the diameter of the hole, D. \ud835\udf16\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udeff\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37) The bearing chord stiffness was only reported if there existed an offset bearing strength. The linear portion, where the bearing stress ranges from 25 \u2013 40 ksi, is the bearing chord stiffness region. \ud835\udc38\ud835\udc4f\ud835\udc5f = \u2206\ud835\udf0e\ud835\udc4f\ud835\udc5f/\u2206\ud835\udf16\ud835\udc4f\ud835\udc5f 4.1.2 Equations Used for Tensile Testing of Unidirectional Carbon Fiber and Aluminum Specimens The maximum tensile strength F, was calculated by dividing the maximum force by the cross- (7) (6) (5) (4) 39 sectional area A. \ud835\udc39 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/\ud835\udc34 The tensile stress, \ud835\udf0e, was calculated by dividing the force by the cross-sectional area, A. \ud835\udf0e\ud835\udc56 = \ud835\udc43\ud835\udc56/\ud835\udc34 The chord modulus of elasticity, E, was calculated by the difference two tensile stress points and their equivalent tensile strain points. \ud835\udc38 = \u0394\ud835\udf0e/\u0394\u03b5 The extensometer strain, \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 , was calculated by dividing the extensometer displacement, \ud835\udeff\ud835\udc56, by the extensometer\u2019s gage length, \ud835\udc3f\ud835\udc54. The gage length of the extensometer was always 0.5 in. \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 = \ud835\udeff\ud835\udc56/\ud835\udc3f\ud835\udc54 The axial and transverse strains were plotted with respect to axial force. The slope of the transverse strain vs. axial load, \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 , was divided by the slope of the axial strain vs. axial load, \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 , and this equaled the Poisson\u2019s ratio of the material. \ud835\udf10 = \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 / \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 (8) (9) (10) (11) (12) 40 4.1.3 Equations Used with the Rosette Strain Gage Using the Equations (13) \u2013 (15), one can find the principle strains in the x-direction, \ud835\udf16\ud835\udc65, y- direction, \ud835\udf16\ud835\udc66 and finally the shear strain in the xy-direction, \ud835\udefe\ud835\udc65\ud835\udc66 . The three different theta values, \u03b81, \u03b82, \u03b83 were all angles relative to the axial strain gage. The strain rosette was placed on the composite quasi-isotropic specimen's surface so that each strain gage was in 0\u00b0, +45\u00b0 and 90\u00b0. So \u03b81 equaled 0\u00b0, \u03b82 equaled +45\u00b0, and lastly \u03b83 equaled 90\u00b0. The principle plane stresses were also transformed with a transformation matrix to the desired angle, \u03b8. In the transformation matrix c = cos \u03b8 and s = sin \u03b8. Where A is considered the transformation matrix below. The transformed plane stresses, \ud835\udf0e\u2032, equaled the transformation matrix, A times the plane stresses, \ud835\udf0e. (13) (14) (15) (16) (17) 41 Once the three principle strains were calculated then a transformation matrix was used to transform each of the three strains to the desired angle, \u03b8. The transformed plane strains, \ud835\udf16\u2032, equals Reuter's Matrix, R, times the transformation matrix, A, by the inverse of the R matrix, and lastly times the plane strains. The modulus of rigidity, G, was found by dividing the modulus of elasticity, \ud835\udc38, by 2 times Poisson\u2019s ratio, \ud835\udf10, plus 1. \ud835\udc3a = \ud835\udc38 2(1+\ud835\udf10) 4.1.4 Equations Used for In-Plane Shear Modulus Testing of Unidirectional Carbon Fiber Specimens The maximum shear stress, \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 (18) (19) (20) (21) 42 divided by the cross-sectional area times two. \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 2\ud835\udc34 The shear stress, \ud835\udf0f12, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65divided by the cross- sectional area times two. \ud835\udf0f12,\ud835\udc56 = \ud835\udc43\ud835\udc56 2\ud835\udc34 The modulus of elasticity in the +/- 45\u00b0 shear modulus test, \ud835\udc38\ud835\udc65\ud835\udc65, was calculated by the difference two stress points and their equivalent strain points. \ud835\udc38\ud835\udc65\ud835\udc65 = \u2212\u0394\ud835\udf0e \u0394\u03b5 The shear chord modulus of elasticity, \ud835\udc3a12, was calculated by the Equation (25). \ud835\udc3a12 = 1/( 4/\ud835\udc38\ud835\udc65\ud835\udc65 \u2212 1/\ud835\udc381 \u2212 1/\ud835\udc382 + 2\ud835\udf1012/\ud835\udc381 ) Converting normal strain to shear strain is done by dividing the shear strain by 2. \ud835\udf16 = 1/2 \u2217 \ud835\udefe 4.1.5 Equations Used for Volume Fraction Testing of Cured Reinforced Resins The ignition loss of the specimen in weight percent is calculated by subtracting the weight of the specimen, W1, and the weight of the residue, W2. (22) (23) (24) (25) (26) 43 Ignition lost, weight % = [(\ud835\udc4a1 \u2212 \ud835\udc4a2)/\ud835\udc4a1 ] \u2217 100 4.2 Theoretical Equations 4.2.1 Equations Used to Find Laminate In-Plane Engineering Constants The NASA Composite Laminate Report [24] was used to find all the laminate in-plane engineering constants (or also known as in-plane laminate material properties). Before finding the laminate in-plane engineering constants, the assumptions must be stated. The quasi-isotropic laminate, with a layup sequence of [0 0 +45 -45 +45 -45 90 90]s, meant that it\u2019s symmetrical and balanced. A symmetrical laminate simplifies the calculations since all that is needed to determine the in-plane engineering constants is the A matrix since the B matrix is composed of all zeros. But for asymmetrical laminates, one would need A, B, and D matrices. The subscripted numbers after the matrix, for example, the 1 and 2 in A12, which is in the number in the first row and second column of the matrix. The theoretical method of finding the laminate in-plane engineering constants required knowledge of Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material properties [21]. The experimental datasheet material properties were used inside the theoretical method. In Equation (28), to find the modulus in the x-direction, the stress in the x-direction is divided by the strain in the x-direction. Which can be also written as force per length in the x-direction, Nx , divided by the laminate thickness, h all over the strain. (27) 44 The A matrix simplifies to the one below since the Bij matrix is all zeros. For each layer in the laminate one needs to solve for a unique Q matrix. If a laminate has 16 different layers then there will be 16 Q matrices and after they are all solved they need to be summed together to form the A matrix. Equations (29) \u2013 (40) will be needed in order to solve for each value in the Q matrix. For any angled ply, one uses Equations (33) \u2013 (40). (32) (31) (30) (29) (33) (34) (28) 45 There is no force (or stress in the other two directions) so those are set to zero. This further simplifies the equations. (35) (36) (37) (41) (40) (39) (38) 46 After further simplification of the Equations (42) \u2013 (44), Equation (46) was equal to our modulus in the x-direction, Ex , only after this number was divided by the laminate thickness, h. \ud835\udc38\ud835\udc65 = \ud835\udc41\ud835\udc65/(\ud835\udf16\ud835\udc65 0 ) \u2217 1/\u210e Next, the same exact method is applied to the y-direction. The modulus in the y-direction, Ey equaled Equation (48). \ud835\udc38\ud835\udc66 = \ud835\udc41\ud835\udc66/(\ud835\udf16\ud835\udc66 0 ) \u2217 1/\u210e Next, the same exact method is applied to the xy-direction. The shear modulus in the xy- direction was found, in Equation (50), Gxy , only after divided by the laminate thickness, h. (42) (43) (44) (45) (46) (48) (47) 47 \ud835\udc3a\ud835\udc65\ud835\udc66 = \ud835\udc41\ud835\udc65\ud835\udc66/(\ud835\udefe\ud835\udc65\ud835\udc66 0 ) \u2217 1/\u210e Poisson\u2019s ratio, \u03c5xy , of the laminate was calculated using Equation (51). Poisson\u2019s ratio, \u03c5yx , of the laminate can was calculated using Equation (52). (51) (52) (50) (49) 48 CHAPTER 5: EXPERIMENTAL RESULTS In this chapter, the experimental results are explained in detail. Section 5.1 explained the validation process, which was conducted, on all the strain measurement devices. The axial modulus of elasticity and Poisson\u2019s ratio of Aluminum were validated. Section 5.2 summarized the material testing which was conducted on the unidirectional carbon fiber material. Section 5.3 explained the unidirectional carbon fiber material property testing. Section 5.4 explained the quasiisotropic carbon fiber laminate material property testing. Section 5.5 explained the experimental results found for the Aluminum double shear specimens. Section 5.6 explained the quasi-isotropic carbon fiber double shear specimens\u2019 experimental results. 5.1 Experimental Measurement Device Validation Before any strain measurement device was used on a composite material, its accuracy needed to be validated with commonly known material. In this case, an Aluminum specimen was tensile tested with a strain gage orientated in the axial direction, and another strain gage orientated in the transverse direction. Since the axial strain gage, the extensometer and the crosshead were measuring axial strain, their readings were compared. In the past theses, students were using the crosshead displacement to measure the modulus of elasticity. Using the crosshead displacement was very unreliable and it is explained in more detail in the next sub section. 49 5.1.1 Extensometer vs. Axial Strain Gage vs. Crosshead Displacement The test set-up of the Aluminum specimen is shown in Figure 21. The three principle directions and the clamped sections of a standard uniaxial tensile specimen are shown in Figure 21. Below in Table 1, an Aluminum sample was loaded and unloaded three times up to a tensile stress of 25 ksi. The tensile stress was calculated using Equation (9). A tensile stress of 25 ksi lies in the material\u2019s linear elastic region and it is far away from materials yield stress of 35 ksi. Table 1 shows the comparison of experimental results between the extensometer, strain gage and crosshead. Table 1 also shows the dimensions of the Aluminum specimen. The strain gage and extensometer experimental results were validated with the Aluminum 2024-T4 datasheet mechanical properties [25]. The moduli of elasticity, in Table 1, are in msi (10E6 lbs./in.2) and were calculated using Equation (10). There was less than 1% error between the extensometer and the strain gage when compared to the Aluminum 2024\u2019s modulus of elasticity. When comparing to the crosshead, there was an error of 64%. The crosshead displacement is not as accurate as an extensometer or a strain gage, because the crossheads have compliance (inside the actuator assembly) which elongates as load is applied. The actuator assembly starts to elongate, which significantly affects the experimental strain results. The small standard deviation showed how consistent the results were when using the three different measurement tools and the testing machine. 50 showing the clamped sections and the 3 principle directions (right) 51 Below in Figure 22, one can see the three runs that were done using the extensometer and the axial strain gage. The crosshead displacement was excluded from Figure 22, since the experimental strain varied so drastically from the extensometer and the axial strain gage. The strain gage and the extensometer read very similar moduli of elasticity. The extensometer and strain gage proved to be reliable, so both measurement tools were used on the composite specimens. 52 5.1.2 Poisson\u2019s Ratio Validation Using Axial and Transverse Strain Gages The Poisson's ratio of the Aluminum 2024-T4 needed to be validated. In Figure 23, one can see the axial and transverse strains plotted with respect to the axial force. The axial strain gage output is shown in blue and the transverse strain gage is shown in red. A linear curve fit was applied to both sets of strain gage data and their respective linear equations are shown, as well. Poisson's Ratio equaled to a value of 0.26, for the Aluminum specimen, using Equation (13). 53 5.2 Summary of Carbon Fiber Material Properties Below in Table 2, the results accumulated from Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg material datasheet [21] are summarized. The values which have a (-) dash meant that they were not given in the material's datasheet. The strengths were specified in ksi, which is 10E^3 lbs./in. Table 3 shows the experimental material properties of the Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material, which were experimentally tested in the Cal Poly\u2019s Aerospace Composites Lab. Table 4 shows the experimentally tested and calculated quasi-isotropic laminate properties. Poisson's ratio, for Umeco\u2019s MTM49 Unidirectional pre-preg material was used from a previous report\u2019s value [26] of 0.25. All these material properties are further explained in the next few sections. Looking at Table 2 and Table 3, the 0\u00b0 compressive modulus is 22.3 msi and the 0\u00b0 tensile modulus is 26.6 msi. All of the tensile axial moduli of elasticity were similar but they were slightly higher than the compressive modulus specified in the datasheet. The tensile and compressive modulus should be very similar since the fibers are assumed to behave like an isotropic material. This material was not tested in compression since compression specimens need to be a lot shorter, in length (ideally have less than 0.5in. in gage length). An extensometer could not be mounted on the surface of the compression specimen since there is not enough room between the grips. The best way to measure, the compressive modulus of elasticity would be to use an optical high-speed camera, which records the relative motion through optics. 55 5.3 Unidirectional Carbon Fiber Material Property Testing 5.3.1 Test for 0\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens A laminate of 8 plies, [0]8T, was laid up and tested along the fiber direction. The 0\u00b0 direction is always the direction of the applied load in a uni-axial test. The ASTM 3039 [19] required a minimum of five specimens per test, and having more than five specimens helped improve the 56 consistency of the results. Each specimen was 10 in. long by 0.5 in. wide and with a thickness of 0.046 in. The ASTM 3039 [19] required curing 2 in. long by 0.5 in. wide Aluminum tabs on the specimens to prevent premature failures from occurring. The grip pressure was set to 160 bar. The tensile test began with testing one 0\u00b0 unidirectional carbon fiber composite tensile specimen (without an extensometer) to failure, to find its ultimate load. The limit load of 2,000 lbs. was chosen since the ultimate load was 4,600 lbs. The last six 0\u00b0 unidirectional carbon fiber composite tensile specimens were loaded to 2,000 lbs., and at 2,000 lbs., the test was paused so that the extensometer could be removed safely. Once the extensometer was removed, the Instron machine's crossheads took over in measuring the tensile strain. The load cell accurately measured the ultimate load up to an accuracy of +/- 45 lbs. In Figure 24, the 0\u00b0 unidirectional carbon fiber composite tensile specimens are shown to the left and one of the clamped post-test 0\u00b0 unidirectional carbon fiber composite tensile specimen is shown on the right. Figure 25 shows all seven of the tested 0\u00b0 unidirectional carbon fiber composite tensile specimens (each color represents a different specimen). Figure 26 shows the extensometer mounted on the 0\u02da unidirectional carbon fiber composite tensile specimen with two rubber bands. The compressive modulus was specified in the datasheet and the tensile modulus was not specified in the datasheet. The experimental tensile modulus was compared to the compressive modulus and the difference between the two values was 19%. A 17% difference between the tensile strength when compared to the datasheet values. 57 58 60 5.3.2 Test for 90\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens Next, a laminate of 14 plies, [90]14T, was laid up and tested along the matrix direction. A couple extra test specimens were tested to find the optimum hydraulic clamping pressure. The clamping pressure was initially set to 160 bar and once the specimen was clamped, it cracked. The hydraulic clamp pressure was reduced to 60 bar in order to prevent this premature failure from occurring. Eight specimens were tested since the material is very brittle and unpredictable. When examining the stress-strain plot of the 90\u00b0 unidirectional carbon fiber composite tensile specimens, the ultimate tensile stress determined the location of where the specimen would fail. As one can see in Figure 27, the four 90\u02da unidirectional carbon fiber composite specimens, which failed at an ultimate tensile stress of around 5 ksi, ended up breaking in the center. Whereas, the specimens which failed at a lower ultimate tensile stress failed near the emery cloth. The experimental results (between all the specimens) showed a very consistent modulus of elasticity. The ultimate tensile strength of the material varied, due to the matrix is very brittle. The failure of a brittle material is very unpredictable which one can see in the Figure 28. There was 17% difference between the datasheet 90\u00b0 modulus of elasticity and a 29% difference between the 90\u00b0 tensile strength when compared to the datasheet values. The ultimate tensile strength variations might have been due to the low accuracy of the load cell, which typically occurs at low loads (around 100 lbs.) since the accuracy of the load cell is +/- 45 lbs. Table 6 shows the experimental results of all the 90\u00b0 unidirectional carbon fiber composite tensile specimens. 61 63 5.3.3 Test for +/-45\u00b0 Shear Modulus Specimens After following ASTM D3518 [20], a laminate was created with an orientation of [+/- 45]4S which is a symmetric laminate with alternating positive and negative 45\u00b0 plies. Another way to write this is [+45 -45 +45 -45 +45 -45 +45 \u2013 45]s. The extensometer was placed at 0\u00b0 relative to the specimen. The axial modulus of elasticity, Exx, was recorded and Equation (25) was used to find G12. Equation (25) requires knowledge of E1, E2, and \u03c512. Eight shear modulus specimens, for consistency, were tested since ASTM D3518 [20] required a minimum of five shear modulus specimens. The shear modulus specimens are shown in Figure 29. The post-tested shear modulus specimens looked the same as the pre-tested shear modulus specimens (since the failure occurred in the matrix and not in the fiber). Figure 30 shows the highly consistent shear specimen results. Table 7 showed the detailed experimental results. There was 35% difference between the in-plane shear modulus and a 43% difference between the in-plane shear strength when compared to the datasheet values. Testing for the shear strength is not an easy task since the shear modulus specimen has to be in full shear state at failure. The tabs on the ends of the specimen create stress concentrations on the ends, which cause the specimen to fail prematurely. 64 66 5.4 Quasi-Isotropic Laminate Material Testing 5.4.1 Test for Quasi-isotropic Tensile Specimens The same test method used for the 0\u00b0 and 90\u00b0 specimens was used to test the carbon fiber quasi-isotropic tensile specimens. Once one quasi-isotropic tensile specimen was tested to failure, the ultimate load was recorded to be 6,500 lbs. The next six quasi-isotropic tensile specimens were tested with the extensometer up to a force of 2,000 lbs. The test paused once the force reached 2,000 lbs. and then the extensometer was removed. Figure 31 shows the quasi-isotropic tensile specimens before (on left) and after (on right) they were tested. The region circled in red showed the area where there was a fiber failure. Figure 32 showed a close-up of the tensile failure. In Figure 32, looking at the picture on the right, one can see the 0\u00b0 fibers on the outer layer held together, while in the center of the laminate, a crack began to form. The crack, in Figure 32, is circled in red. 67 68 From Figure 33, one can see a close-up of the strain rosette, which was on Specimen #1. Shown in Figure 34, a rectangular strain rosette (CEA- 06-120CZ-120 made by VishayPG) produced very accurate results. The rosette was placed on the quasi-isotropic tensile specimen at a 0\u00b0-45\u00b0-90\u00b0 orientation and the wires were soldered very accurately. Each strain gage resistance was checked (with a voltmeter) and read 120 Ohms. The strain gage worked correctly if the resistance across the strain gage read the correct resistance specified in the user manual. The quasi-isotropic tensile specimen #1 was tested one time by recording the strains in the 0\u00b0 direction, 45\u00b0 direction and 90\u00b0 direction. In addition, when the strain gage was being applied to the surface, an 80-grit sandpaper was applied to the surface of the quasi-isotropic tensile specimen. The sanding of the outer 0\u00b0 layer might have affected the material\u2019s mechanical properties. Table 8 shows this 8% difference in modulus of elasticity between the extensometer and the strain gage. From Figure 35, one can see the slight drop in stress (at 20 ksi) due to the pause in the test. The different line colors show the seven different quasi-isotropic tensile specimens that were tested. The main thing to note is the percentage difference between the modulus of elasticity found with the strain rosette and the extensometer. The ultimate tensile strengths were very consistent which showed from a very low standard deviation of 3.87 ksi. 69 70 72 5.4.2 Quasi-Isotropic Tensile Specimen #1 In-Plane Experimental Material Properties Figure 36 shows experimental strain values of the extensometer, the axial strain gage, the +45\u00b0 strain gage and the transverse strain gage. A slight variation exists between the axial strain gage and the extensometer because the extensometer was not placed in the same location as the strain gage. The sanding error, like stated in the previous section, might have also contributed to the error of 8%. The test was stopped at a force of 2,000 lbs. A linear curve fit was applied to all of the three separate strain gage readings and are shown in Figure 36. Next, the Poisson\u2019s ratio of the quasiisotropic tensile specimen was found using Equation (12) and in-plane shear modulus of the quasiisotropic laminate was found using Equation (23). The axial modulus of elasticity was found using Equation (10). 73 5.4.3 Quasi-Isotropic Laminate In-Plane Theoretical Material Properties The theoretical material properties were found using the NASA report on Basic Mechanics of Laminated Composite Plates [24]. In Section 4.2.1, one can find the equations used to calculate the theoretical material properties. Before these equations could be used, a few assumptions were made: (1) The material to be examined is made of up of one or more plies (layers), each ply consisting of fibers that are all uniformly parallel and continuous across the material. The plies do not have to be of the same thickness or the same material. [23] (2) The material to be examined is in a state of plane stress, i.e., the stresses and strains in the through-the-thickness direction are ignored. [23] (3) The thickness dimension is much smaller than the length and width dimensions. [23] The values in Table 9 were needed in order to come up with the theoretical material properties. Table 9 shows the values that were applied into the laminate theory since the laminate theory required knowledge of the material properties of one layer of the unidirectional carbon fiber material. With the help of a strain rosette and the use of Equations (13) - (15), all the in-plane principle strains could be found. 74 Below in Table 10, one can see the calculated experimental material properties using the strain gage rosette. Three different in-plane laminate material properties were calculated based on three different force values (1500 lbs., 1750 lbs. and 1900 lbs.). The theoretical material properties were in agreement with the experimental material properties since the error between the modulus of elasticity was only around 10% and only 2% for the Poisson\u2019s ratio. The low standard deviation showed the reliability of the testing equipment and the strain measurement devices. 75 5.5 Fiber Volume Fraction Test ASTM D2584 [27], Standard Test Method for Ignition Loss of Cured Reinforced Resins, was followed closely. Three volume fraction specimens were tested inside the furnace shown on the right in Figure 37. On the left of Figure 37, one can see a fiber volume fraction test specimen. The fiber volume fraction specimen was placed on top of an Aluminum plate. While the furnace was preheated to a temperature of 1000\u00b0F, the Aluminum plate was weighed and each fiber volume fraction specimen was weighed in grams and then converted to lbs. in order to keep the units consistent. The measuring scale had a least scale reading of 0.1 g. The dimensions of each fiber 76 volume fraction specimens were carefully measured and recorded. Each specimen was placed on the Aluminum plate and left inside the furnace for one hour. Once all the epoxy burned off, the fiber volume fraction specimen was weighed and this was weight of the fibers. The initial weight of the fiber volume fraction specimen minus the final weight of the fiber volume fraction specimen was the weight of the resin (matrix). After doing some simple calculations, along with using the cured resin matrix density of 1.24 g/cm3(from the material\u2019s datasheet); the fiber weight fraction along with the fiber volume fraction was calculated and compared to the datasheet. In Table 11, one can see the three different fiber volume fractions along with the fiber weight fractions. The fiber volume fraction specimen dimensions are crucial to the determination of the fiber volume fraction. The measured thickness of the fiber volume fraction specimen varied from 0.1 in. to 0.103 in., which meant that the heat press cooked unevenly. The slight variation of the specimen\u2019s thickness affected the volume fraction by 4%. The 8.3% difference between the experimental fiber volume fraction and the datasheet fiber volume fraction varied because not enough pressure was applied to the laminate during the curing process. The lower fiber volume fraction of 0.55 compared to 0.6 meant that there was more resin in the laminate. Not enough resin was squeezed out in the cure process. The pressure applied by the heat press was limited, so achieving the optimum fiber volume fraction (of 0.6) was difficult. The fiber volume fraction significantly affected all of the material property testing which was conducted on the Umeco MTM 49 unidirectional material. A low standard deviation showed that the data was very consistent. 78 Section 5.6 was conducted in order to validate the numerical model with the experimental data. Modeling a metal before modeling a composite is very important because metals behave in a more predictable fashion. Metals are a lot simpler to model since they exhibit isotropic behavior whereas composites exhibit orthotropic behavior. The material property inputs for an isotropic material are much less than for a composite material. For a composite, the user has to input three different moduli of elasticity, three moduli of rigidity, and three Poisson\u2019s ratios. For metals, the user only inputs the modulus of elasticity and the Poisson\u2019s ratio. In this validation, Aluminum 2024-T4 was used as the material of choice. Once the linear elastic model was validated with a metal, then any other material should be validated as well, but only for the linear elastic region of the material. This also validates the boundary conditions and any interactions, which were used in the numerical model. 5.6 Aluminum 2024-T4 Double Shear Test The Aluminum 2024-T4 double shear specimens were tested on the same double shear fixture as the composite double shear specimens. From Figure 38, one can see the bearing stress vs. bearing strain response of the five tested Aluminum double shear specimens. The first section of the bearing stress vs. bearing strain plot (the flat initial region) is the strain correction region. Compliance between the Instron parts, along with the clamps, occurred upon initial loading of the specimen. The deformation of all the internal parts of the Instron machine in the strain correction region. The linear elastic region, (shown inside the red square in Figure 38) for the Aluminum, was between 5 ksi and 40 ksi and after this region; the material experienced a non-linear behavior 79 up to its ultimate bearing strength. The strain correction region and the non-linear region were removed, which can be seen in Figure 39. The non-linear region and the strain correction region were not part of the numerical model. Figure 38 showed that specimen #5 failed at an ultimate bearing stress of 130 ksi and the other four specimens failed around 114 ksi. The extensometer\u2019s knife-edge slipped on the face of specimen #1 through #4, but for specimen #5, the extensometer did not slip. The linear elastic region can be seen in Figure 39. The specimen alignment might have caused the variations in the linear elastic strain values. The ultimate bearing strength matched up the Aluminum 2024-T4 material\u2019s datasheet [25]. Table 12 shows the experimental results of the Aluminum double shear specimens. Both the yield and ultimate strengths were calculated in the Table 12. Figure 40 shows a bearing type of failure, which occurred in all the Aluminum double shear specimens. Figure 41 shows the Aluminum double shear specimens before and after they were tested. The region circled in red shows the area where the failure occurred. Each specimens\u2019 hole diameter increased in size and also each specimens\u2019 hole diameter did not go back to its original shape once the load was removed, which showed that the material reached a plastic deformation. 80 82 5.7 Composite Double Shear Test As one can see in Figure 42 (from a paper by Yi Xiao [28]), the composite double shear specimens behaved differently than Aluminum double shear specimens. Recall, all the composite double shear specimens were manufactured with a quasi-isotropic laminate orientation of [0 0 +45 83 -45 +45 -45 90 90]s. The 4%D is considered the bearing strength of the material. The composite double shear specimens held load (without failing) up to the knee point. At the knee point, the first ply failed (after this point, the material properties started to degrade) and the slope of the curve was reduced. The load increased up to the final point, also known as the ultimate bearing strength of the material, where it maxed out. One positive thing about designing a structure to fail in bearing, as opposed to net-tension or shear-out, is that the force dropped 30% of the maximum load. Whereas, in net-tension or shear-out failure, the load dropped down to zero. Figure 43 shows a close-up of the bearing failure, which occurred on the composite double 84 shear specimens. As one can see, there is an excessive amount of damage near the pin location. All of the specimens exhibited a similar type of failure, so there was no need to take a picture of each of the failed specimens. Figure 44 shows ASTM 5961\u2019s [18] failure codes used to characterize any of the failure modes seen in a composite double shear test. The failure code, B1I, is used throughout the rest of the experimental section, which signifies a bearing type of failure. 85 86 5.7.1 Curing Cycle 1 (Cytec\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test Figure 45 shows the composite double shear specimens before and after the double shear test. In Figure 45, on the right, highlights the crushing regions, in red. All the failures are consistent. Eight specimens were tested for each of the five loading rates. For load rate 0.1 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. When looking at the alternate cure cycle experimental data, in Tables 13 & 14, an interesting 87 trend appeared. At slower loading rates, the composite double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min. the composite double shear specimens failed at an average stress of 64.4 ksi and 63.5 ksi whereas at 1 in./min., 2 in./min. and 6 in./min. the composite double shear specimens failed around 52.3 ksi. Looking at all the different loading rates, it seemed as if all the composite double shear specimens had a similar knee point. 2 in./min. and 6in./min. showed a greater drop in load after the composite double shear specimens reached their ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. did not show a huge drop in load after the specimens reached the ultimate load. 89 The maximum values of all the plots, in Figure 46, were the ultimate bearing strengths. When looking at Figure 46, one can see that as the loading rate increased the non-linear region decreased in size. The red-circled sections, in Figure 46, show how the non-linear region decreased in size. The linear region does not change as drastically as the non-linear region. As the load rate increased, the rate of damage also increased which explained the reduction, in size, of the non-linear region. 90 Looking at all of the load rates, the moduli in the non-linear regions are lower than the linear elastic regions. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. 91 5.7.2 Curing Cycle 2 (Umeco\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test When looking at the datasheet cure cycle experimental data, in Tables 15 & 16, a similar trend appeared. At slower loading rates, the double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min., the specimens failed at an average stress of 62.7 ksi and 67.7 ksi, whereas at 1.0 in./min., 2 in./min. and 6 in./min., the specimens failed around or under 52.0 ksi. It also looks like at 2 in./min. and 6in/min. show a greater drop in bearing strength after the specimen reaches its ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. do not show a huge drop in strength after the specimens reach the ultimate load. In general, fast loading causes more damage to the specimen which overall reduces the specimen's ability to carry load. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. Eight specimens were tested for each of the five loading rates. For load rates 2 & 6 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. 93 When looking at Figure 47, one can see that as the loading rate increased the non-linear region decreased in size. In Figure 47, the red-circled section also showed the non-linear region decreased, in size, with increased loading rate. 94 5.7.3 Comparison between Cure 1 & Cure 2 In Figure 48, it is very clear that as loading rate increased, the ultimate bearing strength of the 95 material decreased regardless of the cure cycle. Further research can be done on how different cure cycles can affect the bearing response of a composite double shear specimen. Making the matrix less brittle and more ductile might improve the ultimate bearing strength of the material. Cure cycle 2 (Umeco\u2019s cure cycle) was 2% stronger in bearing when compared to the cure cycle 1 (Cytec\u2019s cure cycle). The MTM 49 Unidirectional carbon fiber pre-preg material was very sturdy by not being affected by an alternate cure cycle. 5.7.4 Comparison Between The Aluminum Double Shear Specimens & Quasi-Statically Loaded (0.05 in./min.) Composite Double Shear Specimens Aluminum is standardly tested at quasi-static load rate of 0.05 in./min, since it\u2019s strain rate independent [30] (not affected by different loading rates). The Aluminum double shear specimens 96 performed a lot better in bearing than the composite double shear specimens. Since the carbon fiber is more brittle by nature, its ultimate bearing strength is significantly lower than Aluminum. of the Aluminum double shear specimens was around 118 ksi and the ultimate bearing strength of the composite double shear specimens was around 63 ksi. That means that carbon fiber is 53% weaker than Aluminum 2024-T4 in a double shear joint configuration. The Aluminum double shear specimens yielded at around 40 ksi compared to the composite double shear specimens, which yielded at 30 ksi. As one can see from the bearing stress vs. bearing strain graphs, there is a huge difference in ultimate bearing strength between of both materials. It is interesting to note that both materials showed a strain correction region. The Aluminum double shear specimens and the composite double shear specimens did not catastrophically fail (they deformed without significantly dropping the applied load). 97 CHAPTER 6: NUMERICAL ANALYSIS Chapter 6 explains the overall finite element approach. Section 1 introduces the finite element model and different considerations, which were applied to the model. Section 2 explains the idea behind a convergence plot and its importance. Section 2 explains what factors influenced the numerical results. 6.1 Finite Element Analysis Introduction Once a Finite Element Analysis model is validated with experimental results, it can then be used in the design process. Abaqus 6.14-1 was used to model the double shear bearing test experiment conducted. All the different Finite Element software work very similarly and the only difference between them is their program interface. However, they all essentially break up the model into small elements and calculate the stress state on each element. The material properties are assigned to the elements and then, the boundary conditions and loads are applied to the model. In some cases when there are two or more parts, one might have to define different types of interactions or constraints for the model (for example, how those parts move relative to each other). The numerical software also predicts non-linear behavior, which requires a lot more material properties. Plasticity required the user to model the damage done on the material as load increased, which meant, implementing a degradation model. First, a numerical model was created and validated for the Aluminum 2024-T4 double shear 98 specimen. The Aluminum numerical model was only validated through the linear elastic region of the experimental data, which was shown in Figure 39. The Aluminum numerical model was adjusted for the composite specimen and the experimental results were compared to the numerical results. Abaqus keeps the units consistent, so when working with US Customary units make sure to stay consistent with the units, if using inches, stick to using inches. The displacement plots should be in the same units as one started with, and the stresses should be in pounds per square inch (psi). 6.1.1 Geometric Definitions The numerical model contained four parts. The two side plates, double shear specimen, and pin were modeled as deformable 3D solids. Both steel plates along with the double shear specimen were partitioned. The steel collars and center middle plate were neglected for simplicity. All the bolts, nuts and washers were also neglected in the model for simplicity reasons. 6.1.2 Material Creation, Section Assignments, & Meshing All the dimensions were defined in English units and the dimensions for each of the parts came from the fixture design. The fixture used in the numerical model was simplified. All the composite material properties were inputted in the elastic engineering constants. Table 17 showed the material properties, which were, applied to the Aluminum numerical model. A Steel solid homogeneous section and an Aluminum solid homogeneous section were created. 99 A composite layup section was applied to the composite double shear specimen and the element type was set to solid. Table 18 shows the material properties that were applied to the composite double shear specimen. In the composite layup section, the user is able to set the element stacking direction, the coordinate system, and the rotation axis. The user can also specify the laminate orientation and select the region for each ply within the model. In the Appendix, there is a tutorial of how the Abaqus composite double shear specimen was modeled. A single layer of unidirectional carbon fiber material is considered a transversely orthotropic material, where E2 is equal to E3 and G12 is equal to G13. E2 and E3 are both considered the matrix and E1 is considered the fiber. One thing to note was that the compressive modulus in the 1- direction (axial) was slightly lower than the tensile modulus, which was found in the Experimental section of the report. The Poisson\u2019s ratio in the 23-direction and the shear modulus in the 23- direction are usually very difficult to find experimentally. Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager was used to find some of the material properties that could not 100 be found experimentally. In the Appendix, one can find the tutorial on how to use Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager. One can also find a step-by-step Abaqus tutorial on the composite double shear specimen. Parts of the step-by-step tutorial were found from D.S. Mane [29] . The parts were individually partitioned which made meshing them very simple. Once the partition was created, the user needed to use the Seed Edge command, then select whole part, and for method select \u201cby number\u201d. As indicated below in sizing control, the user is able to assign the number of elements from one to however many. The convergence plot was constructed using four different nodes per element. The element\u2019s relative thickness was set to 0.5 since there were only two elements that made up the thickness of the part. 101 6.1.3 Assembly, Interactions & Steps The whole assembly was modeled very similarly to the experiment. Each part was given a dependent instance and no tie constraints were used in the model. A contact step and a load step were added to the analysis. The contact step initiated the contact between the pin and the steel plates and also the pin and the specimen. The load step served to apply load to the analysis once full contact was established. The pin was not constrained to the specimen with a tie constraint because that implied a condition similar to being welded. So in contrast, a surface-to-surface interaction was established between the pin, the steel plates and the specimen. The sliding formulation selected was finite sliding. The pin was set as the master surface and the slave surface consisted of two surfaces. One was the surface in contact with the pin and the inner side of the specimen and the other was the surface in contact with the pin and the inner side of both steel plates. The slave adjustment was set to a value of 0.007 in. A contact property with a tangential behavior (the friction formulation was set to penalty and the friction coefficient was set to 0.46). In addition, a normal behavior contact property with the pressure-overclosure was set to \u201cHard\u201d Contact; constraint enforcement method was set to default, and allowed separation after contact. 6.1.4 Boundary Conditions & Loads The boundary conditions applied to the model needed to be assigned carefully. The top face of the specimen (opposite face with the hole) was fully fixed in the x, y and z directions. This was 102 similar to the clamped condition, which is applied by Instron\u2019s crossheads. The second boundary condition that was applied was on the outer pin surface and the inner hole surfaces of the steel plates and the bearing specimen. In the contact step, the pin, steel plates and specimen were not allowed to move in the x, y and z directions. The load step was modified to allow the side plates, pin and specimen to move in only the y-direction. The combined load of 600 lbs. was applied to both of the bottom faces of the steel plates. This was done by applying the load, in the load step, as a total force distribution pressure load. The loading condition used in the model was similar to the experimental loading condition, where a fraction of the force is applied at each time interval. Some elements in the model experienced plastic deformation only when the applied load was over 800 lbs. This meant that certain elements were in stress state beyond their linear elastic limit. The ultimate force was not predicted, by the numerical analysis, since that occurred in the non-linear region. 6.2 Numerical Results This section provides the explanation of the convergence plot and talks about the factors, which influenced the numerical results. In Chapter 7, the numerical results are explained in detail. 6.2.1 Convergence Plot For the numerical model, a partition was created on the face of the specimen. Taking time to draw a symmetrical and neat partition prevented the mesh from becoming unsymmetrical and 103 prevented unusual results. The partitioned double shear specimen is shown in Figure 49. In Figure 50, one can see a close up of the partitioned region around the hole. After a partition was created, the user was able to assign a specific amount of elements using the Seed Edge command. Here the user is able to set the total amount of nodes per element to any value. For the convergence plot, 2, 6, 8, and 10 nodes per element were chosen, and the final vertical deflection at the pin was compared. A convergence plot was created to see if adding more elements to the model actually improved accuracy. Knowing the optimum amount of elements for the least amount of time for the model to complete is very important in the design process. As one can see from Figure 51, as the total amount of nodes per element increased, the deflection did not change significantly. Using more than six elements per node did not significantly improve accuracy, but it did take longer to run. 6.2.2 Factors That Influenced the Numerical Results Increasing the total amount of elements through the thickness of the part, did not significantly affect the pin deflection results. Changing the axial modulus (from tensile to compressive) significantly affected the pin deflection results. The compressive axial modulus was imported into Abaqus rather than the tensile modulus, because the double shear test is mainly a compression type of loading. The fibers are in compression around the hole. When initially assuming a frictionless contact (when the frictional coefficient equaled zero) the specimen ended up colliding with one of the side plates. Changing the frictionless coefficient 104 from zero to 0.46 helped prevent the specimen from colliding with one of the side plates. 105 106 CHAPTER 7: COMPARISON BETWEEN EXPERIMENTAL & NUMERICAL DOUBLE SHEAR RESULTS The slope of the reaction force vs. pin displacement was compared between both the experiment data and the numerical model. First, the numerical Aluminum model was validated. Then the numerical composite model was validated. 7.1 Numerical Aluminum Model Comparison to Experimental Results Looking at Figure 59, the region highlighted in red was due to the compliance in the testing assembly. The bearing stress vs. bearing strain plot was then converted to a load (reaction force in the y-direction) vs. pin displacement plot. All of the specimens were plotted up until the linear region. Looking at Figure 60, of the five tested Aluminum double shear specimens, the numerical results only matched up with one. The four other Aluminum double shear specimens might have slipped with respect to the extensometer\u2019s knife-edge. One way to tell is by the lower load (reaction force in the y-direction) vs. pin displacement slopes. In Table 19, the total error when comparing the experimental slope to the numerical slope was 16%. Misalignment of the specimen might have caused this significant error to occur. 107 108 7.2 Composite Numerical Model Comparison to Experimental Results Figure 54 showed the load (reaction force in y-direction) vs. pin displacement response of the 0.05 in./min. composite double shear specimens that were cured to the recommended datasheet cure cycle. Three of the eight tested composite double shear specimens at 0.05 in./min. did not slip. The strain was corrected using the same method that was applied to the Aluminum double shear specimens. Of the eight carbon fiber specimens that were tested, only three of them closely matched up to the numerical results. The numerical model was loaded to 600 lbs., which was still within linear elastic limit of the material. The load (reaction force in y-direction) vs. pin displacement slopes between all the experimental specimens shown were compared to the numerical model. In Table 20, the average error between the numerical slope and the experimental slopes was about 7.1%. Alignment is a huge factor, which can affect experimental results quite significantly. There will always be error between the experimental and numerical results. The numerical 109 results are the idealized results and the experimental results have so many factors, which can influence their results. Errors from 7% to 16%, for both the aluminum double specimens and the composite double shear specimens, are actually quite reasonable because there is always error in the manufacturing process, displacement measuring equipment, load cell, specimen alignment exc. 111 CHAPTER 8: CONCLUSION The first important contribution of this study was to see how different loading rates affected the ultimate bearing strength of a composite material. One can see that at 0.05 in./min. and 0.1 in./min. (for both cure cycles) the composite double shear specimens carried more load compared to higher load rates of 1 in./min., 2 in./min. and 6 in./min.. All of the specimens failed in bearing and not in net-tension or shear-out. The second important contribution of this study was to see how the recommended datasheet cure cycle and the alternate cure cycle affected the ultimate bearing strength. The two different cure cycles behaved very similarly under the five different loading rates. The average ultimate bearing strength of the Aluminum double shear specimens was 118 ksi and for the composite double shear specimens it was 65 ksi. The experiment showed that carbon fiber material is significantly weaker, in a double shear tensile loading configuration, compared to Aluminum. Ductile materials, like Aluminum for example, handle the double shear tensile loading configuration a lot better than the carbon fiber material, which is brittle. Each carbon fiber sheet is relatively thin which is also very poor for carrying bearing stress. Usually what designers do is use inserts inside and around the hole if they need to improve the bearing strength of a composite joint. The inserts help redistribute the stress concentrations (which are caused by mechanical fasteners) and prevent the brittle material from cracking. The inserts are usually made from ductile materials, like fiberglass or Aluminum. 112 8.1 Recommendations The experiments were carried out using carbon fiber unidirectional pre-preg tape. Similar research can be done using various other materials like: kevlar, fiberglass, or even hemp. Similar testing can be done using a single shear joint configuration. Various carbon fiber types can be tested as well. MTM-28 material is a thicker type of unidirectional fiber, which would be very interesting to test. A high-speed video camera would be a more efficient way to monitor deflection since the extensometer's range was the limiting factor in the data capture. A more in depth case study can be conducted on different cure cycles of composite resins. The pre-load function in the Bluehill2 software can be utilized in order to try to eliminate some of the strain correction region. In addition, a more in-depth experimental analysis can be conducted on the knee point region of the composite (carbon fiber) double shear specimen. 113 REFERENCES 1. Airbus Versus Boeing-Composite Materials: The sky's the limit. http://www.lemauricien.com/article/airbus-versus-boeing-composite-materials-sky-slimit. 2. Lessard, L.B. (1995). Computer aided design for polymer-matrix composite structures. In S.V. Hoa (Eds.), Design of joints in composite structures. New York: Marcel Dekker. 3. Baker, A. (1997). Composites engineering handbook. In P.K. Mallick (Eds.), Joining and repair of aircraft composite structures. New York: Marcel Dekker. 4. Okutan, B. (2001). Stress and Failure Analysis of Laminated Composite Pinned Joints. Journal of Composite Materials, 19. 5. Chen, J.C., Lu, C.K., Chiu, C.H., & Chin, H. (1994). On the influence of weave structure on pin-loaded strength of orthogonal 3D composites. Composites, 25, No: 4, 251-262. 6. Quinn, W.J., & Matthews F.L. (1977, April). The effect of stacking sequence on the pin- bearing strength in glass fiber reinforced plastic. Journal of Composite Materials, 11, 139- 145. 7. Liu, D., Raju, B.B., & You, J. (1999). Thickness effects on pinned joints for composites. Journal of Composite Materials, 33, 2-21. 8. Stockdale, J.H., & Matthews, F.L. (1976, January). The effect of clamping pressure on bolt bearing loads in glass fiber-reinforced plastics. Composites, 34-39. 114 9. Kim, S.J., & Kim, J.H. (1995). Effects of geometries, clearances, and friction on the composite multi-pin joints. AIAA Journal, 34, No: 4, 862-864. 10. Hyer, M.W., & Klang, E.C. (1985). Contact stresses in pin-loaded orthotropic plates. Journal of Solids and Structures, 21, No: 9, 957-975. 11. Pierron, F., Cerisier, F., & Lermes, M.G. (2000). A numerical and experimental study of woven composite pin-joints. Journal of Composite Materials, 34, No: 12, 1028-1053. 12. Chang, Fu-Kuo, Scott, R.A., & Springer, G.S. (1982, November). Strength of mechanically fastened composite joints. Journal of Composite Materials, 16, 470-494. 13. Ger, G.S., Kawata, K., Itabashi, M.: Dynamic tensile strength of composite laminate joints fastened mechanically. Theor. Appl. Fract. Mech. 24(2), 147\u2013155 (1996). 14. Li, Q.M., Mines R.A.W., Birch R.S. (2000, September). Static and dynamic behavior of composite riveted joints in tension. 15. United States Naval Academy (USNA). (2003). Composite Orientation Code. http://www.usna.edu/Users/mecheng/pjoyce/composites/Short_Course_2003/7_PAX_Sh ort_Course_Laminate-Orientation-Code.pdf 16. Kretsis, G., & Matthews, F.L. (1985, April). The strength of bolted joints in glass fiber/epoxy laminates. Journal of Composite Materials, 16, 92-102. 17. Yeole, Amit. (2006, December). Experimental Investigation and Analysis for Bearing Strength Behavior of Composite Laminates. 115 18. Anonymous, \u201cStandard Test Method for Bearing Response of Polymer Matrix composite Laminates,\u201d ASTM Standards, Designation: 5961/5961M-05. 19. Anonymous, \u201cStandard test method for tensile properties of fiber-resin composites,\u201d ASTM Standards, Designation: 3039-76. 20. Anonymous, \u201cStandards. In-plane shear stress-strain response of unidirectional reinforced plastics,\u201d ASTM Standards, Designation: 3518-76. 21. Umeco, \u201cMTM 49 Series Pre-preg System \u2013 Unidirectional Material Properties.\u201d 22. Cytec, \u201cMTM 49-3 \u2013Unidirectional Material Properties.\u201d 23. Instron, \u201cInstron 8801 Servo-hydraulic Machine Photo.\u201d http://www.instron.us/en-us/ 24. Nettles, A.T., (1994, October) \u201cBasic Mechanics of Laminated Composite Plates.\u201d 25. ASM Aerospace Specification Metals Inc., \u201cDatasheet Mechanical Properties of Aluminum 2024-T4.\u201d 26. Anonymous, \u201cProject 1 Report\u201d ME-412. 27. Anonymous, \u201cStandard test method for ignition loss of cured reinforced resins,\u201d ASTM Standards, Designation: 2584-02. 28. Xiao, Yi. \u201cBearing strength and failure behavior of bolted composite joints (part II: modeling and simulation). 29. De, S. MANE 4240/CIVL 4240: Introduction to Finite Element. Abaqus Handout. 30. Semb, Evind. \u201cBehavior of Aluminum at Elevated Strain Rates and Temperatures.\u201d 116 APPENDICES A.1. Drawings for the Fixture Assembly 117 118 A.2. Tutorial on Bluehill2 Test File Setup Various settings were changed inside the BlueHill2 software. Below, I will show a couple of the parameters that were changed. Navigating through the menus is self-explanatory. In the Control submenu, the load rate was changed for each test. The quasi-static case was tested first at a load rate of 0.05 in./min. The second load rate, which was tested, was 0.1 in./min., the third was 1 in./min., the fourth was 2 in./min. and the fifth speed, which was tested, was 6 in./min. 119 The end of test criteria was changed to the ASTM specification. End of test 1 specifies the drop in the load of 30% the peak value and end of test 2 is specified as an extensometer displacement of 0.1 in. The extensometer shows up at Displacement (Strain 1) as a separate channel. 120 In the Control submenu, the sampling rate was changed from the default rate of 10 samples/sec to 3 samples/sec as required by ASTM D5961. This change showed a significant reduction of noise within the extensometer displacement readings. A value of 500 ms was adjusted for the time channel and the load sampling rate was left to default interval of 56 lbf. 121 Below in the Control submenu, the source of tensile strain was changed from the BlueHill2 default channel of \u201cTensile Strain\u201d to the \u201cStrain 1\u201d. The extensometer shows up as \u201cStrain 1\u201d. 122 Bluehill2 also has the option of calculating numerous parameters. In my experimental testing, I needed to calculate the ultimate bearing strength so I picked User Calculation. Then Bluehill2 gives you an option to define various variables like: D (diameter of hole), k (calculation factor for double shear k = 1), Pmax (maximum force carried by the specimen prior to failure), and t (defined as the thickness of the laminate). After all of your variables are defined, the equation designer tool 123 is used to create your equation of interest. In the Results submenu, the user is able to pick exactly which values he/she wants to output while in the test screen. The results are outputted as a column of values for each of the different test specimens. I wanted to output all of these parameters below while I was conducting my tests. 124 In the Graph submenu, the user is able to output two real-time changing graphs. For graph 1, I chose to output Instron crosshead displacement vs. load and for graph 2 I chose to output extensometer displacement vs. load. The X-Data was set to either Extension (for Instron crosshead displacement) or Displacement (Strain 1) (for extensometer displacement. The Y-Data was set to Load for both graph 1 and graph 2. 125 In the Raw Data submenu, Bluehill2 has a great function, which allows the user to export any given output of experimental data into a .csv file. This file can later be opened up with Excel and used to calculate various experimental stresses, strains and other parameters of interest. For my experimental testing, I was interested in outputting: time, crosshead displacement, extensometer 126 displacement, load and corrected position. The last bit of raw data, which needed to be outputted, is shown below. This set of data is saved onto the same .CSV file as the one specified in the previous screen. This set of data is located in its own set of two columns in the .CSV file. 127 A.3. Tutorial on Finding the Unknown Engineering Constants Autodesk created a very powerful tool, which can help the user figure out unknown engineering constants of a ply. For example from the experimental results, the user is able to experimentally determine E1, E2, G12 and \u03c512. Shown below are all the values, which the user inputs into the Autodesk Simulation Composite Analysis 2015 Material Manager. Make sure to label the 128 material a unique name and choose the correct units. The fiber type should be carbon intermediate for the MTM 49 since it is not the ultra-high fiber modulus. The volume fraction should be the one, which was found experimentally in the Results chapter, of 0.55. In Figure 67, in the first row of the Ultimate Lamina Strengths the user inputs the tensile strength in the 0\u00b0 and the 90\u00b0 directions. In the second row, the user inputs the compressive strength in the 0\u00b0 and 90\u00b0 directions and finally, in the last row, the user the user inputs the in-plane shear strengths. 129 In Figure 68, the user will input the known modulus of elasticity into the Lamina Elastic Constants section. The in-plane Poisson's ratio, which was assumed to be around 0.244, was used from a previous paper, which found the material property experimentally on the same MTM 49 Unidirectional material. The in-plane shear modulus was inputted from the experimental testing. 130 The key is to assume a value if you do not know what it is. After all the values have been inserted into the program go into the File, menu and then click optimize. It will ask you if you want to save the material properties somewhere and all you do is specify where you want to save the data. It will take a couple seconds to optimize the values accordingly. A.4. Tutorial on Outputting Force vs. Pin Deflection from Abaqus The pin deflection needed to be monitored for one node on the specimen. The area of interest is shaded in dark blue and the red dot signifies which node was monitored for its vertical deflection. In Figure 70, one can see the deflection in the y-direction, which occurs around the hole. This hole 131 is a localized compression zone. 132 Next what was needed was to have a force vs. time graph. The top most nodes on the specimen were fixed using the encastre boundary condition. The reaction force in the y-direction was captured for all the nodes that make up the top of the specimen. Once all the reactions at each nodes were captured, the whole region was summed up. Under create XY plot click ODB field output and then click continue. Under the Variables tab, find the Output variable box, and in the position menu, click Unique Nodal and then go into RF: Reaction Force and check the RF2 button. Since we are interested in the reaction force in the y-direction (2 direction). Next, click the Elements/Nodes tab and then pick the from viewport button and then click Edit Selection. Once all the fixed nodes are selected, as shown in Figure 72 below, click the Done button in the viewport. Lastly, go into Active Steps/Frames; make sure All steps are selected and set it to Frame. In the bottom of the window, make sure a green checkmark is applied to both the Contact and the Load steps. 133 Using the Create XY Data option in Abaqus, the user is able to go into Operate on XY data. In the Operators window, pick sum((A,A,...)), then under XY data, select all the Reaction Force nodes, which show up as _RF:RF2 and then click Add to Expression. Once all the nodes are inside the Sum operator, hit the Plot Expression button. This will output a force vs. time graph. 134 Once both the force vs. time graph and deflection vs. time graph are created, one needs to combine both graphs. In the Create XY Data, click Operate on XY Data and then press Continue. Under the operator tab, find combine(X,X) and then click it once. The combine operator requires two variables for the plot. For the first variable, click the deflection XY data, and for the second variable, click the Reaction Force 2 XY data. Make sure a comma separates both variables. Once done click the plot expression button and this should bring up a Force vs. Pin Deflection plot as shown in Figure 74. 135 A.5. Tutorial on Modeling the Double Shear Bearing Specimen Assembly Open up Abaqus 6.14. The numerical model should look like something like this. The complete assembly, the pin and one of the side plates modeled with Abaqus 6.14. 136 A.5.1. Model Creation Create a new model by right clicking the Models category. Name it DoubleShear. Then press Ok. 137 A.5.2. Part Creation Next, we have to create the parts for the model, after that, we partition each of the parts. Click on the + button to expand the options inside the DoubleShear model. Right click on Parts and press Create. A menu will appear like the one shown below. Name the part SteelPin. Keep the modeling space: 3D, the type: deformable, the base feature shape: Solid and for the base feature type: Extrusion. Click continue. 138 Click the Create Circle button. Using the dimension tool below set the radius to 0.125 in. Always be consistent with your units (I am using inches). 140 Next, we need to create the double shear specimen. Copy the step above and only change the name of the part to Specimen. Use the rectangle tool (to the right of the circle tool) and make a basic rectangle. 141 Using the dimension tool set the width of the part to 1.5 in. and the length of the part to 5.5 in. Create a Line down the middle of the part. Locate the center of hole 0.75 in. from the bottom edge of the specimen and make sure the hole is centered along the specimen\u2019s width. 142 Now, delete the centerline with the eraser tool, which is highlighted and then click on the centerline (which should highlight in red) and click done. Click the eraser tool to disable it. 143 In the bottom of the drawing window, it should read, \u201cSketch the section for the solid extrusion\u201d. Click the Done button. Set the depth to 0.1 in. Since the carbon fiber specimen\u2019s thickness was 0.1 in. Next, we need to create the side steel plate. Copy the step above and only change the name of the part to SidePlate. Use the rectangle tool (to the right of the circle tool), make a basic rectangle, and use the circle tool to create a hole in the plate. The side steel plate should be 2 in. by 4 in. and it should have a 0.141 in. radius hole. Which is located 1.0 in. from the top of the side plate. Lastly, remove the centerline and then set the depth to 0.25 in. Since the side steel plates had a thickness of 0.25 in. The three parts should look like this once they are completed. 144 A.5.3. Partition Creation A partition was created on the side plates and on the specimen. This made sure that when the mesh was generated all the elements stayed symmetrical. One major source of error in finite element analysis is due to elements not being symmetrical and the same size. One way to avoid this problem is to create your own mesh, which requires the user to partition the part based on what is of interest to him/her. Pick Tools, in the top drop down menu, and choose Partition. Click Face for the partition type and then click on the side plate face highlighted in orange. 145 Click Done and then it will ask to click a line vertical and to the right. Shown below, the highlighted edge is shown in pink, and the non-highlighted edges are shown in red. The part will switch from 3D to 2D and then here the user is able to create the partition desired. Create the partition below with these dimensions using the circle and line tools. It is important to keep the mesh coarse on parts which are not of main interest. 146 Apply the same method to the double shear specimen. The partition on this specimen was a lot more detailed than on the steel side plate. There are six circles, which are all equally spaced apart. The three outer radii were 0.5 in., 0.375 in., and 0.625 in. The three inner radii were 0.1875 in., 0.25 in., and 0.3125 in. A finer partition was created on the three inner radii where the circle was segmented into 64 equally spaced smaller sections. 147 The final partitioned parts should look like this. 148 A.5.4. Material Creation The material properties need to be created. Two materials were used in the analysis: steel and a unidirectional carbon fiber material. Under the Parts category, right click and click create. Name the material Steel. Go into the Mechanical option, then press elasticity, then elastic. Keep the type set to a default isotropic setting. Set the Young\u2019s Modulus to 34e6 and set the Poisson\u2019s ratio to 0.3. Follow the step right above, and create a new material and name it Uni. For the type, select 149 Engineering Constants. Include the material properties in the Table below (remember that msi is 106 psi)." + ] + }, + { + "image_filename": "designv8_17_0000307__2018jamdsm0123__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000307__2018jamdsm0123__pdf-Figure1-1.png", + "caption": "Fig. 1 Structure of hydraulic drifter", + "texts": [ + " The correctness of the derivation p rocess and the conclusion of this study are experimentally verified. The present findings provide a basis for reasonably match ing the relationships among design parameters and can help improve drifter impact efficiency. Keywords : Hydraulic drifter, Dynamic model, Once vibration, Existence scope, Point transformation Hydraulic d rifter act as a drilling device that use liquid as working medium to convert the pressure energy into the impact energy of the piston. They are widely applied in engineering work on mines and tunnels (Nygren, et al., 2009) (Fig. 1). The operation of the hydraulic drifter comprises propulsion (the hydraulic cy linder applies propulsion to the drifter to ensure that the drill shank is constantly in contact with the rock), impact (the hydraulic pump prov ides fluid pressure energy to the drifter; the impact piston reciprocally impacts the shank adapter; and the drill shank transfers the impact energy to the rock in the form of stress waves, thus causing the rock to rupture), gyration (the torque output by the hydraulic motor causes the drill bit to gyrate to a new position after each impact, and part of the cracked rock surface is removed), and flushing (the auxiliary water pump flushes the broken rock powder in the borehole) (Lin, 2014; Zou, 2017; Song, et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure7-1.png", + "caption": "Fig. 7, The discretized mesh and the zoomed view for case (a)", + "texts": [ + " This particular problem has an analytical solution based on \u201cBar\u201d theory with a lumped mass \ud835\udc5a\ud835\udc49\ud835\udc43 attached to the free end 16th LACCEI International Multi-Conference for Engineering, Education, and Technology: \u201cInnovation in Education and Inclusion\u201d, 19-21 July 2018, Lima, Peru. [9]. The natural frequencies are computed from the equation below, where \ud835\udc50 = \u221a \ud835\udc38 \ud835\udf0c 2\ud835\udf0b\ud835\udc53\ud835\udc5b\ud835\udc3f\ud835\udc40\ud835\udc43 \ud835\udc50 tan 2\ud835\udf0b\ud835\udc53\ud835\udc5b\ud835\udc3f\ud835\udc40\ud835\udc43 \ud835\udc50 = \ud835\udf0c\ud835\udc34\ud835\udc3f\ud835\udc40\ud835\udc43 \ud835\udc5a\ud835\udc49\ud835\udc43 where \ud835\udc5b = 1 2 3 \u2026 The frequency \ud835\udc5b has been normalized to have the units of Hz. The above theoretical frequencies are based on stress wave propagation ie, solving the one-dimensional partial differential equation governing the deformation. Based on a mesh convergence study, an extremely fine mesh of linear tetrahedron elements has been used which is also shown in Fig. 7 below for the sake of completeness. This mesh has been maintained for all other analysis and case studies. The calculated first three natural frequencies associated with the axial vibration are given in the Table I below. The middle column consists of the Catia generated frequencies whereas the third column is the one calculated from the theoretical formula presented earlier. The FEA results are in excellent agreement with theory as reflected in the table. The deformation modes of the FEA calculations are also in good agreement with the theoretical ones but are not displayed due to the space limitations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003548_om_article_19879.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003548_om_article_19879.pdf-Figure3-1.png", + "caption": "Figure 3. Surface tiles pole", + "texts": [], + "surrounding_texts": [ + "Because of the different structure, compared permanent magnet fault-tolerant motor with the traditional permanent magnet synchronous motor, there are many differences in terms of parameter design. In this section, we use a four-phase six-pole permanent magnet fault-tolerant motor as an example, and research the design of motor structure and electromagnetic parameters. The main performance parameters of this motor are as follows: rated power PN=1KW, rated voltage UN=36V, rated speed nN=1200rpm, number of the stator Ns=8, rotor pole pairs p=3, number of phase m=4, rated efficiency \u03b7N=90%, the rated power factor cos\u03c8N=0.8. A. Design of stator inner diameter and core length The main dimensions of the permanent magnet fault-tolerant motor are specified the inside diameter and the effective axial length of stator core which can be determined according to the need of maximum torque and dynamic response indication [10] . When the biggest electromagnetic torque of motor is Temmax(N . m), then the relationship between main dimensions and electromagnetic loads is: 42 11 10 4 2 max ADLBT iefem (1) where B1 is the flux density of fundamental amplitude (T), A is the stator electric load valid value (A/CM). Obtained the relationship between the main dimensions of motor and the electromagnetic loads according to formula (1): AB T LD em efi 1 4 2 1 1022 max (2) p KmNI A dp1 (3) where m is the motor phase, N is the winding turns, I1 is the stator current, p is the rotor pole pairs, Kdp is the winding factor, \u03c4 is the motor pole pitch. Here we take power load A=150A/cm, the flux density of fundamental amplitude B\u03b41=0.8T. Because the dynamic response performance index of a permanent magnet fault-tolerant motor mainly refers to the motor that under the effect of maximum electromagnetic torque Temmax can accelerate linearly from rest to turning speed \u03c9b during time of tb , that is: b b em pt J tp J T max (4) where J is the rotor and load inertia (kg . m 2 ). Therefore, according to formula (4) we can obtain the ratio of maximum electromagnetic torque to the moment of inertia is: b bem ptJ T max (5) The moment of inertia of the motor rotor can approach to: 741 10) 2 ( 2 i efFe D LJ (6) where \u03c1Fe is the mass density of the rotor material iron (g/cm 3 ). We take formula (1) and formula (6) into equation (5), can obtain the stator inner diameter Di1(cm) is: 3 1 1 10 28 Feb b i ABpt D (7) Then according to equation (2), we can obtain the effective axial length of the stator core Lef(cm) is: 22 11 2 1 4 4 101022 maxmax ABpt T ABD T L b Febem i em ef (8) B. Design of groove parameters Fig .1 shows the block diagram of stator slots of permanent magnet fault-tolerant motor after straightening. From Fig .1, we can know that the parameters which need be calculated include: notch thickness Hs0, slot width Bs0, stator tooth width Bt and stator tooth height Hs2. Firstly, according to the magnetic saturation constraint conditions of the stator teeth, we obtained the tooth height and the tooth width. Secondly, according to the design requirements of slot leakage inductance, we derived the notch height and width. Finally, in accordance with the requirements of internal winding current density of stator slot, we calculated the other parameters, like the width of the groove bottom Bs2 and the width of the groove top Bs1. 1) Parameter calculation of stator teeth Assuming all of the air-gap magnetic flux through the main stator teeth, so the stator tooth width is obtained as follows: maxt i t b B B (9) where B\u03b4 is magnetic load, \u03b1i is calculated pole arc coefficient. Because when ferromagnetic material under normal circumstances, the maximum magnetic flux density of the stator teeth btmax equal to 1.4~1.6T, therefore, this article selected btmax=1.5T, and according to formula (9) can derive the stator tooth width Bt. Generally, the height and width ratio of the stator teeth is between 1.5 and 3. Because, if the ratio is small, the stator slot is very shallow, this may cause very high current density that through the inner winding. But if the ratio is large, then the stator slot is very deep, the stator yoke is easy to reach saturation, and the electromagnetic torque may reduce. So in this paper, we take the value of 2, and the stator tooth height is: ts BH 22 (10) 2) Calculation of notch parameter In order to reduce the saturation degree of the stator tooth tip maximum extent, at the same time to improve the slot leakage inductance Ls0\u03c3, the notch thickness Hs0 generally taken to be (0.35~0.5)Bt, this article is taken as 0.4 times, that is: ts BH 4.00 (11) Slot leakage inductance Ls0\u03c3 is: 0 000 2 0 0 ))((2 s sefss s B BLBHN L (12) Because the notch width Bs0 is much smaller than the effective axial length of stator core Lef, therefore, formula (12) can be simplified as: 0 00 2 0 0 )(2 s efss s B LBHN L (13) Rearranging slot width Bs0 is: efs efs s LNL LHN B 2 00 0 2 0 0 2 2 (14) where the slot leakage inductance Ls0\u03b4 taken as 0.33 times of the coil inductance Ls, and has the following formulas: eese s If E I E L 2 00 (15) NNN N e mU P I cos (16) where E0 is the motor back electromotive force (V), \u03c9e is the electrical angular frequency (rad/s), Is is the steady-state short-circuit current (A), Ie is the motor rated current (A), fe is the rated synchronization frequency (Hz). 3) Calculation of armature winding turns and coil diameter The definition of motor no-load back electromotive force(EMF) is: 010 44.4 we NkfE (17) where fe is the rated synchronization frequency(Hz), kw1 is the winding factor, \u03a60 is the fundamental magnetic flux air gap(Wb), and has the following formulas: ef i LB ) 2 sin 4 ( 2 0 (18) So the number of turns of the armature winding N is: )2sin( 18.0 11 0 iefiwe LDBkf pE N (19) According to the dimensions of slot form, we can get the area of stator slots As is: 2 sin)( 221 sss s HBB A (20) where \u03b8 is the mechanical angle that relative to the centerline of the pole (rad), and: Width of the top slot is: t si s B Q HD B )2( 01 1 (21) Width of the bottom slot is: t sssi s B Q HHHD B )(2 2101 2 (22) where Q is the number of stator slots, in order to reduce the degree of magnetic saturation of tooth boots, Hs1 generally taken as 0.5~1mm. 4) Calculation of stator and rotor yoke portion thickness The thickness of the yoke of stator and rotor needs to meet the constraints of magnetic saturation, for the four-phase six-pole permanent magnet fault-tolerant motor in this article, the maximum value of yoke flux density is 1.6~1.8T, which is slightly larger than the maximum limit value of flux density in tooth portion, in this paper the value is 1.6T. Then the thickness of the stator yoke portion Hsy is: sy im sy b b H 2 1 (23) The thickness of the rotor yoke is: ry p ry b B H 2 1 (24) where bsy is the flux density of stator yoke portion (T), bry is the flux density of rotor yoke portion (T). C. Magnetic circuit design Magnetic circuit design includes the determination of overall structure, the determination of sizing and the selection of material, which focuses on the work of choosing permanent magnetic materials and designing the operating point. 1) Permanent magnet material selection In this paper, we chose NdFeB N38H as the permanent magnet material, the remanence density Br20 is 1.23T, the temperature coefficient \u03b1Br is 0.12 %/\u2103, the irreversible demagnetization loss IL is 0.7%, the calculated coercive force of permanent magnet Hc20 is 899kA/m. We can obtain following results according to the selection of NdFeB N38H: (1)Remanent flux density during the operating temperature: 20 [1 ( 20) /100] [1 /100] 1.18 r Br r B t IL B T (2)Calculated coercive force during the operating temperature: mkA HILtH cBrc /7.833 ]100/1[]100/)20(1[ 20 (3)Relative permeability of the permanent magnet: 20 0 20 1.089 1000 r r c B H where 0 is vacuum permeability, 0=410 -7 H/m. 2) Determine the shape of permanent magnet Surface magnetic pole structure can improve the ability of isolation between the windings, in this article we use the surface-type tile-shaped magnetic poles in the permanent magnet fault tolerant motor, shown in Fig .3. The structure of permanent magnet contacting the air gap directly is easy processing and installation. And uses a concentric tile-shaped magnetic poles, i.e., the outer diameter and the inter diameter of the permanent magnets have a common center, it shown as in the Fig .4. 3) Calculate the size of permanent magnet The main size parameters of permanent magnet part include the thickness and the width of permanent magnet, and can be determined by the following formula: The thickness of permanent magnet hM is: i r r M B B h 1 (25) The width of permanent magnet bM is: pM b (26) where \u03bcr is the relative permeability of ferromagnetic material; \u03b4i is the calculating air gap length of motor(cm); Br is the residual magnetic induction intensity of permanent magnet (T); B\u03b4 is the magnetic load (T); \u03b1p is the percentage of pole embrace. Generally Br/B\u03b4 equal to 1.1~1.35. 4) Permanent magnet magnetization way of design In this paper, the arrangement of permanent magnet is in the way of Halbach array [11] , this kind of arrangement can not only enhance the air gap flux of motor, but also can weaken the magnetic flux of rotor yoke, which is particularly suitable for the rotor structure of using surface-mounted permanent magnet. Halbach array is a novel magnetic structure array that combines radial array with tangential array, as Fig .5(a) shows, so that we can make the magnetic field in one side of permanent magnet strengthening and the other side weakening. The rational design of Halbach array can make the air-gap flux density and the no-load back electromotive force having good sinusoidal. Fig .5 (b) shows the distribution of magnetic equipotential line of the permanent magnet motor with Halbach array which is calculated by the ANOSOFT which is one of the finite element analysis software. As we can see, after using Halbach array, the magnetic flux of rotor yoke significantly reduced, while the magnetic flux that across air gap into the stator significantly increased, which increases the magnetic load of permanent magnet motor and the density of force and energy, so Halbach array is very suitable for the ideal for the permanent magnet fault-tolerant motor with the inter rotor structure of permanent magnet posted outside." + ] + }, + { + "image_filename": "designv8_17_0002164_f_version_1560418557-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002164_f_version_1560418557-Figure16-1.png", + "caption": "Figure 16. The selected methods of the distribution of measurement points available in the Calypso software.", + "texts": [ + " In the case of some commercial methods of determining the location of measurement points on curvilinear surfaces, there is a large probability of not detecting deviations that exceed the accepted tolerance. The examples of such methods are: \u2022 the method that enables the distribution of measurement points between two points located on a measured free-form surface and chosen by the operator of a CMM; \u2022 the method of single measurement points, which are randomly selected on a considered curvilinear surface of a measured object by the user of a CMM. Both above mentioned methods are available in the Calypso measurement software as parts of the Free-form surface measurement element. Figure 16 presents the usage of both methods. The vectors illustrated in Figure 16 are perpendicular to the free-form surface and they represent measurement points. The vectors were automatically generated by the Calypso measurement software. Measurement points were randomly chosen by the user of the applied measurement software. Based on the analysis of the distributions of measurement points, which were obtained using those methods, it can be noticed that there is the very big risk of omitting the parts of the measured free-form surface which are characterized by the worst quality of manufacturing when conducting measurements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004995_9_34_5_34_5_443__pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004995_9_34_5_34_5_443__pdf-Figure14-1.png", + "caption": "Fig, 14. Interaction of a transverse or longitudinal crack with regions of {1 11} l> and {1 1l} 112> orientation,", + "texts": [ + " In the first case, a tear in either the T-L or L-T orientations will propagate more-or-less in the {OI I}plane within those parts of the material with the {OOI} I I0> texture, Fig. 13. The {OOI} I0> texture componentis therefore symmetrical with respect to both longitudinal and transverse cracks. The situation is slightly different in the case of the second texture component, the {I I l} fibre. The two possible orientations of the tears are not symmetrical with respect to any of the individual componentswithin the fibre. The situations with respect to the {11l} 1> and {lll} components are shown in Fig. 14. ISIJ International, Vol. 34 (1994), No. 5 ct2. pol MIKET21 ) ~~Il)i-~; (:. ___ _:~ L '~:~L:1::*~' k: ~~~ (~), ,..P . ~-. ...), ~~),,~ , ..~) ~s\"cp,~: ' :~.~, ~~ =b.~ * Ir: * ce)_ o. cl> ~ , 'O IF !' ((),-:: . ~l ;c.~ ~; ~i,'~!: ~T_) o. 2e ,, - 30 ,, s2 ,, e5 ,, 77 ,, eo ,, 430 STAINLESSSTEEL \"Ax - 8.el SAMPLENOT21 Fig. n. ODFPlot for the sample of type 430 staintess-steel. / R.D. stainless-steel. However, the effect of specimenorientation is averaged out over the spread of orientations within the {111}fibre, which was shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000082_article_25839690.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000082_article_25839690.pdf-Figure5-1.png", + "caption": "Figure 5. Analysis result", + "texts": [ + "486 Aluminum alloy former and structural steel riveting Total Deformation Maximum Minimum Design Point 0.03916 65.312 15 10 Equivalent Stress Maximum Minimum Design Point 0.03916 65.312 15 10 In summary, the optimal plan is that Aluminum alloy interest into structural steel welding plan when the diameter of the rivet hole is 15mm, and the distance between the center of the rivet hole and the edge is 25mm. According to the analyzing, the deformation deprogram\u3001stress deprogram\u3001strain deprogram are show in the Figure 5. At last, the system distortion of the selected optimal plan is about 0.034mm which satisfy the requires of stiffness of the electric vehicles frame; and the maximum stress of the system is 43.842Mpa which is much less than the admissible stress of the structure steel (250Mpa) and the admissible stress of the Aluminum alloy (280Mpa), so it can satisfy the requirements well for the electric vehicles. [1] BENEDYK J C. Light metals in automotive applications[J]. Light Metal Age,2000,10(1):34-35. [2] Pedersen P" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure7-1.png", + "caption": "Figure 7. Rotation Mechanism Cross Section", + "texts": [ + " When the motor is actuated, friction between the wheel and the pipe causes the wheel to drive itself around the pipe. This motion rotates the entire Pipe Traveler around the pipe until the unit is aligned with the next pipe. Gussets are used to support the drive wheel cage which houses the drive wheel. The drive wheel cage slides along support ridges along the inside of the gussets. A gusset brace allows the gussets to transfer the moment applied to the Pipe Traveler when the drive wheel is actuated. These components and can be seen in Figure 6 & Figure 7. Page 5 of 15 The pneumatic cylinders are controlled using 4-way 2-position manual valves. A manual return valve is used to control the drive wheel actuation so that the air pressure would continue to be applied until the operator decided to disengage the wheel. The extension cylinders are controlled with a momentary valve to provide the operator with finer control of the extension. The extension cylinders have a single control valve and the drive wheel cylinders have a single control valve since there is no situation where independent control would be required" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001639_6_06_Paper841-46.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001639_6_06_Paper841-46.pdf-Figure1-1.png", + "caption": "Fig. 1 Schematic Diagram of Shot Peening", + "texts": [], + "surrounding_texts": [ + "Proposed work aims to investigate the impact of exploitation express thinker whereas coming up with the experiment to comprehend optimized process parameters for shot-peening. The proposed work is planned to be carried out in following distinct phases, steps in project execution given below; a. Study alternative processes for life improvement b. Study shot peening method c. Development of FE model for shot peening d. Shot peening on component e. Comparison of results f. Recommendations" + ] + }, + { + "image_filename": "designv8_17_0001771_s-3217716_latest.pdf-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001771_s-3217716_latest.pdf-Figure19-1.png", + "caption": "Figure 19 shows that after the optimization of the hollow ball valve sealing ratio distribution cloud map, it can be seen from Figure 20 that the seal ratio of the heart ball valve over the lower heart ball valve is evenly distributed on the entire cover. In the completely closed seal ratio band; the maximum value of the seal ratio is 28.53MPa, less than 37MPa than the obtained material.", + "texts": [ + " After the optimization of the dual elastic slot valve is optimized, the ball valve has a good fatigue resistance performance under the temperature and pressure transition load, and at the same time meets the structural strength and stiffness requirements, and realizes the lightweight design. To ensure that the ball valve has a good deformation compensation effect at a high-temperature difference, the thermal coupling method is used to analyze its sealing performance with the thermal coupling method optimized by the valve seat. Figure 18 shows the sealing ratio of the liquid hydrogen receiving station ball valve in the initial structural parameter. It can be seen from Figure 19 that the seal ratio of the hollow ball valve is evenly distributed on the entire cover surface. The seal ratio pressure is greater than the necessary comparison pressure 12.82MPa, which can form a completely closed seal ratio band. The maximum value of the seal ratio is 21.219MPa, Smaller than the cover material for 37MPa, which can ensure the sealing and the phenomenon of sealing side pressure. (a\uff09Sealing pressure distribution cloud diagram of inlet end sphere and valve seat \uff08b\uff09Sealing surface sealing pressure amplification cloud map Fig.19 Sealing pressure distribution cloud diagram of hollow ball valve after optimization Compared with the cloud diagram of the sealing ratio of the hollow ball valve before optimization, it can be seen that the maximum value of the seal ratio after optimization increased by 34.4%compared with the optimization, but it is still less than the maximum use ratio of 37MPa. Therefore, after the optimization, the valve seat has not only greatly improved its structural performance, but its sealing performance has also increased significantly, indicating that the valve seat has good deformed deformation compensation capabilities under the hydrogen hydrogen hydrogen temperature after the optimization" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure15.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure15.11-1.png", + "caption": "Fig. 15.11. The comparison of energy estimators of vibration of vehicle moving at 50 km/h and 70 km/h speed versus laboratory tested vehicle at the same gear ratio and engine rotational speed (floor panel in location of driver feet)", + "texts": [ + " ISSN 2351-5260 Analysis of distributions of vibration in time, frequency domains and its TFR allows to identify all components of the vibration caused by the road roughness and powertrain system. These presentations enable observing the time of excitation on defined frequencies. For the comparison VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 189 of total energy of vibration transferred into the human organism the distribution of estimators defined in previous chapters are collected in Fig. 15.11. The chapter presents some results of identification of structure and directional distribution of vibration transferred to car-body from road roughness. 190 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260 The method proposed for identification of components of road irregularity induced vibrations for a moving vehicle may be brought down to comprehensive laboratory and road tests of the same vehicle while maintaining identical engine and power transmission operating parameters" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003281_om_article_22266_pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003281_om_article_22266_pdf-Figure4-1.png", + "caption": "Fig. 4. Boundary constraints for stator systems", + "texts": [ + " ISSN PRINT 1392-8716, ISSN ONLINE 2538-8460 1191 This section mainly studies the electromagnetic vibration and noise radiation caused by the radial electromagnetic force generated by the field circuit coupling method. The electromagnetic vibration noise of PMSM is determined by the radial electromagnetic force wave acting on the stator structure and the radial modes of the stator structure. In this paper, the vibration and noise of the motor are carried out on the bench, so the six degrees of freedom of the cross-section bolt holes are constrained according to the actual constraints to simulate the motor installation state, as shown in Fig. 4. Add boundary conditions to simulate the constrained modes of the motor. This article lists the first five radial modes and frequencies of the stator system, which are shown in Fig. 5. The left is the vibration mode of the stator system, and the right is the vibration mode of the stator core. 1192 JOURNAL OF VIBROENGINEERING. SEPTEMBER 2022, VOLUME 24, ISSUE 6 The main radial electromagnetic force frequency of the motor is an even multiple of the current frequency. As can be seen from Fig. 6, when the excitation frequency is close to the modal frequency of the stator system, it will cause the stator system to resonate, especially in 960 Hz and 1280 Hz, the stator modal frequencies are dense, which are easy to cause the resonance of stator system" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure8-1.png", + "caption": "Fig. 8 Distribution of stress (a) Antero-lateral (b) Postero-lateral; (c) Maximum stress under static load condition II", + "texts": [ + " The static strength simulation findings of the modified knee prosthesis are shown in Figs. 7 and 8. It shows prosthetic knee stress under loading conditions I and II. Stresses in front and back joint bars are 85-107 and 42-64 MPa respectively for load condition I (Figs. 7a and 7b) and 81- 101 and 40-60 MPa for load condition II (Figs. 8a and 8b). The maximum von-Mises stress value of 300 MPa is observed at the front link bush for load conditions I (Fig. 7c) and 284 MPa for load conditions II (Fig. 8c). Comparing these results to corresponding material properties, the maximum stresses are sufficiently below the yield strength of AA7075-T6 aluminium alloy (503 MPa) utilized for the front and back joint bars and bush. These results suggest that the modified knee prosthesis will successfully pass the ISO 10328:2016 static strength test. The static strength test results for the modified knee are shown in terms of total deformation in Figs. 9 and 10. Maximum deformation is observed at the load application point which is 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure12-1.png", + "caption": "Figure 12: Third iteration of compliant landing mechanism.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure9-1.png", + "caption": "Fig. 9. Total displacements for the base load", + "texts": [ + " 7): \u2022 point A \u2014 support, \u2022 point B \u2014 support, \u2022 point C \u2014 manipulator 200N (due to the lim- ited budget of the project and difficult to predict dynamic loads, a doubled force value was assumed), \u2022 point D \u2014 battery 75N, \u2022 point E \u2014 computer and electronics 5N, \u2022 point F \u2014 laboratory 29N. The analysis was performed for several variants of the grid in order to verify the convergence of the results. The similarity of the obtained results confirms the appropriate densification of the grid (Table 2). The analysis was carried out iteratively, starting from the base load value up to the dangerous load value (Table 3). The following drawings presented (Fig. 8, Fig. 9, Fig. 10) show the results for the analysis without force multipliers. Figures 11, 12, and 13 shows the results for the analysis with the critical load included. Figure 14 show where the frame joins the rocker-bogie suspension beam. It is possible to identify the point where the reduced stresses reach a value close to the hazardous value for the material used in the structure. Due to the complex state of stresses occurring in this point, potentially dangerous for the structure, additional local laminate layers should be applied to increase the durability of the structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure6-15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure6-15-1.png", + "caption": "Figure 6-15. Syst\u00e8me d'antennes miniatures avant rotation", + "texts": [ + " Repr\u00e9sentation de la g\u00e9om\u00e9trie du syst\u00e8me d'antennes LCIS................................ 194 Figure 6-11. Repr\u00e9sentation des trois orientations dans l'espace du syst\u00e8me LCIS ................... 194 Figure 6-12. Repr\u00e9sentation de la g\u00e9om\u00e9trie du syst\u00e8me d'antennes FTRD .............................. 195 Figure 6-13. Coefficients de r\u00e9flexion (S11) des deux syst\u00e8mes UWB ..................................... 196 Figure 6-14. Antenne miniature utilis\u00e9e dans le syst\u00e8me \u00e0 diversit\u00e9.......................................... 201 Figure 6-15. Syst\u00e8me d'antennes miniatures avant rotation ....................................................... 201 Figure 6-16. Repr\u00e9sentation du dip\u00f4le dans le rep\u00e8re initial ...................................................... 202 Figure 6-17. Vue des antennes patchs de r\u00e9f\u00e9rence avant rotation............................................. 203 Figure 6-18. Coefficients de r\u00e9flexion des antennes patchs polaris\u00e9es verticalement et horizontalement et de l'antenne miniature (\"chip antenna\") .............", + " Les d\u00e9tails de la g\u00e9om\u00e9trie de l'antenne sont rappel\u00e9s sur la Figure 6-14. Le syst\u00e8me est constitu\u00e9 d'un plan de masse rectangulaire de 100 x 50 mm, les antennes \u00e9tant dispos\u00e9es \u00e0 chacune des extr\u00e9mit\u00e9s de ce plan de masse. Ce syst\u00e8me pr\u00e9sente donc une diversit\u00e9 spatiale mais \u00e9galement une part de diversit\u00e9 de diagramme car la position de l'antenne par rapport au plan de masse conditionne fortement la directivit\u00e9 de ces antennes miniatures. Avant rotation, le syst\u00e8me est orient\u00e9 comme repr\u00e9sent\u00e9 sur la Figure 6-15. 202 Le syst\u00e8me pr\u00e9sentant une sym\u00e9trie, les deux antennes ont les m\u00eames propri\u00e9t\u00e9s. La bande passante \u00e0 -10 dB de ces antennes va de 2,426 GHz \u00e0 2,457 GHz, elle ne couvre donc pas la totalit\u00e9 de la bande ISM \u00e0 2,4 GHz. L'efficacit\u00e9 totale de ces antennes varie donc fortement en fonction de la fr\u00e9quence. Les valeurs de cette efficacit\u00e9 sont pr\u00e9sent\u00e9es dans le Tableau 6-13, ce tableau donne \u00e9galement les efficacit\u00e9s des antennes de r\u00e9f\u00e9rence utilis\u00e9es pour calculer les gains de diversit\u00e9 r\u00e9f\u00e9renc\u00e9s Contrairement aux exemples pr\u00e9c\u00e9dents, nous utilisons ici trois antennes de r\u00e9f\u00e9rence, avec lesquelles nous calculerons uniquement les gains de diversit\u00e9 r\u00e9f\u00e9renc\u00e9s pour \u00e9valuer la pertinence d'utiliser un syst\u00e8me d'antennes miniatures pr\u00e9sentant de la diversit\u00e9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004553_ai.7-12-2021.2314491-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004553_ai.7-12-2021.2314491-Figure6-1.png", + "caption": "Fig. 6. \u2018", + "texts": [ + " e developed concept should have the capability Model with twists at both the ends orientation as -time In this concept, double twist present at the bottom and one twist at the top as shown in figure 4. Frame is welded to the seat at one end and bolted at the bottom. In this concept, multiple twists are present at the bottom and one twist is at the top as shown in figure 5. Frame is welded to the seat at one end and bolted at the bottom. In this concept, \u2018I\u2019 section structure is used to support the seat as shown in figure 6. Frame is welded to the seat at one end and bolted at the In this concept, \u2018I\u2019 section structure with ribs as shown in figure 7 is used to support the seat structure. Frame is welded to the seat at one end and bolted at the bottom. I\u2019- section model to support the seat bottom. I\u2019- Section model with cross ribs In this concept, \u2018I\u2019 section structure with cross ribs as shown in figure 8 is used to support the seat structure. Frame is welded to the seat at one end and bolted at the bottom. Rapid Upper Limb Assessment (RULA) analysis was carried out in CATIA package and score for the body at different regions include upper arm, lower arm, wrist, neck, trunk, and legs are obtained [7]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000540_r.asee.org_12263.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000540_r.asee.org_12263.pdf-Figure8-1.png", + "caption": "Figure 8 Power Requirements Main Menu", + "texts": [ + "7 Proceedings of the 2003 American Society for Engineering Education Annual Conference & Exposition Copyright p 2003, American Society for Engineering Education The next section of the spur gear program has the student select a material based on contact stress. This follows a similar procedure that was done for selecting a material based on bending stress. IV. Horsepower Requirements for Machine Design Horsepower requirements for machine design is an important part of the design process. This program allows the student to analyze three different power requirements as shown in figure 8. The student can analyze the power requirements for a rotating roller, conveyor system, or a leadscrew drive system. Selecting one of the three drive analysis command buttons, will take the student through the design process for that selection. The student enters inputs such as speeds, sizes, loads, and other information required to run the calculations. The conveyor system analyzes the power requirements for moving a load on a conveyor and rotating a roller based on speed and the time requirements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003997_e_download_7367_3540-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003997_e_download_7367_3540-Figure3-1.png", + "caption": "Figure 3. The design of CDD", + "texts": [ + " It requires preparation and skills. Therefore, this design is expected to facilitate the installation in emergency conditions or when the truck's wheels are stuck in the mud. Outside the area of the mud trap, this tool must be removed because the use of traction enhancers on the paved road will damage the road surface, hamper the vehicle's speed, wasteful of fuel, and damage the device itself. The design of the anti-slip shoes of the wheels truck can be fitted into the standard size of the Colt diesel-type truck, as shown in Figure 3 (a). The wheel type is 7.50-16-14PR double rear wheels, tubed type with an outer tire, rim 16x6.00GS, and six studs [9]. Tire diameter is 816 mm (81.6 cm) with cross-section width of 211 mm (21.1 cm) and maximum truckload (empty + load) 12 tons. The applied anti-slip shoe material is based on the standard of SNI 07-0052-2006 of D.T.Wahyudi and D.S.Khaerudini, Design of Anti-Slip Shoes for 12 Ton Palm Oil Truck \u2026 215 U channel steel. The calculations of this design are focused on determining the dimensions of the traction rod fins as the main component of the truck wheel anti-slip shoes. The traction rod is mounted on the surface of the rear truck drive wheel, as depicted in Figure 3 (a) of the CDD type. So, it is expected to be having a similar function as in the tractor wheel, as shown in Figure 3(a). The condition is aimed to provide a wheel grip on the muddy ground. The length and depth dimensions of the traction fin will be determining the parameters for the slip less rolling for a wheel. The two dimensions of the traction rod applied as the parameters to get the maximum traction value, which used for the next step of design simulation. Other parameters that required to calculate the maximum traction value of anti-slip shoes are soil cohesion and soil internal friction angle. Data on soil cohesion, soil internal friction angle, and secondary data on the physical properties of soil are taken from several references from the relevant studies. At the same time, the calculation of material strength and selection of supporting components are not discussed further as a limitation of this study. The design of CDD type anti-skid truck wheel shoes from several necessary components, namely: (1) traction rods/wheel fins (as the focus of this study), (2) traction rod connecting and (3) fastening components, plates (2 and 3 are not discussed), as shown in Figure 3. (a) (a) Sketch of an anti-slip shoe mounted on the rear wheel of a CDD type truck (front view position). (b) Sketch of 3-dimensional anti-slip shoes on CDD type truck wheels To design the anti-slip shoes on a palm oil hauling truck, the assumption of traction calculation on the tractor wheels relates to the forces acting under the wheels and the ground, as shown in Figure 4. The study uses a tractor wheel design as a guideline because of the availability references with scientific discussion, especially in the agricultural technology journals", + "5 Refers to the Equation (5), the value of z is determined based on the dimensions of the two sides of the U channel steel in Table 3 and three sizes are selected at once namely U50, U65, and U80 with each side dimension or fin depth (z) 3.8, 4.2 and 4.5 cm. The truck wheel diameter (d) of 81.6 cm is used as a reference to scatter the projections of the fulcrum with the ground (l) (Figure 6). The numerical results by using Solidworks software from all fins (z) 3.8 cm on U50 steel obtained the length of the track in contact with the soil (l), which 36.03 cm based on the design sketch as in Figure 3 (a) is then shown in Figure 11. With the same step fin depth calculation, the length of the track in contact with the soil (l) is then obtained for the sketch design of the U65 and U80 dimensions. The results are shown in Table 4. Table 4. The results of the length of the track in contact with the soil U Channel Steel z (cm) l (cm) U50 3.8 36.03 U65 4.2 37.97 U80 4.5 39.7 220 D.T.Wahyudi and D.S.Khaerudini, Design of Anti-Slip Shoes for 12 Ton Palm Oil Truck \u2026 Determining the maximum traction values (Hmax) By using the reference data as in Table 1, in this study, the length of the traction rod (b) is determined at 30 cm with the dynamic weight factor (W) on the wheel is 3960 kg" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002838_f_version_1679473059-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002838_f_version_1679473059-Figure1-1.png", + "caption": "Figure 1. Movement relations between coordinate systems: (a) external gear and internal gear ring; (b) rack cutter and external gear.", + "texts": [ + " But different from the involute gear pair, the transmission of the conjugated straight-line gear pair is not separable because its profile cannot extend radially indefinitely. When the center distance changes, the tooth profile no longer satisfies the conjugate relation, so the pitch circle of the gear pair coincides with the reference circle. Table 2 shows relevant geometric parameters involved in the mathematical modeling of the gear pair and rack cutter tooth profile. The external gear is machined by rack cutter. The coordinate systems and their movement relations are shown in Figure 1. The fixed coordinate system Sg ( Og \u2212 Xg, Yg, Zg ) is fixedly connected with the ground, and the movable coordinate systems S1(O1 \u2212 X1, Y1, Z1), S2(O2 \u2212 X2, Y2, Z2), and Sc(Oc \u2212 Xc, Yc, Zc) are fixedly connected with the external gear, internal gear ring, and rack cutter, respectively. The Z-axis of each coordinate system is established in accordance with the right-hand rule. The coordinates S1 and S2 rotate with the external gear and internal gear ring, the coordinate Sc moves parallel with the rack cutter, and the counterclockwise direction is defined as the positive direction of rotation. At this time, the axis Z1 and Z2 coincide with the rotation axis of the external gear and internal gear ring, respectively, and the pitch circles of the external gear and internal gear ring are tangent to point P; the axis Xc coincides with the pitch line of the rack cutter and is tangent to the pitch circle of the internal gear ring at point Pc. At the initial position, the coordinates S2 and Sg coincide. Figure 1a,b describes the movement relations between the external gear and internal gear ring, and between the rack cutter and external gear during the meshing process, respectively. Suppose that the external gear and internal gear ring rotate counterclockwise around axis Z1 and Z2 at the angular velocities \u03c91 and \u03c92, respectively, for a period of time, and the rotation angles are \u03d51 and \u03d52. According to the definition of transmission ratio, the transmission ratio i12 of coordinates S1 and S2 can be expressed as follows: i12 = 1/i21 = z2/z1 = \u03c91/\u03c92 = \u03d51/\u03d52 = r2/r1 (1) When the rotation angle of coordinate S1 is \u03d51, the translational displacement of coordinate Sc is d" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001974_f_version_1645516501-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001974_f_version_1645516501-Figure1-1.png", + "caption": "Figure 1. The concept of measuring and grasping the docking ring.", + "texts": [ + " NASA\u2019s OSAM-1 on-orbit service mission plan captures an on-orbit satellite by grabbing the docking ring for fuel replenishment to extend its lifespan. Additionally, it passed ground verification in 2020 [11]. The deorbit plan proposed by the German OHB company is expected to be launched in 2023 to rescue the Envisat satellite, and the target is also the docking ring [12]. Therefore, using the docking ring target to estimate the relative pose has great practical value. The concept of measuring and grasping the docking ring is shown in the Figure 1. Information 2022, 13, 95. https://doi.org/10.3390/info13020095 https://www.mdpi.com/journal/information Miao and Zhu et al. calculated two solutions of the spatial circle pose based on the projection of the spatial circle on the docking ring on the image. They used the distance from a reference point outside the docking ring plane to the center of the circle, which remained unchanged as a constraint to eliminate false solutions and obtain the pose of the docking ring [13]. Cai and Li et al. proposed a pose solution method based on circular features and straight-line features to solve the roll angle and eliminate the ambiguity of the solution [14]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.7-1.png", + "caption": "Figure 3.7: Vane Free Body Diagram", + "texts": [ + "1) \ud835\udc59\ud835\udc63\ud835\udc60 > \ud835\udc59\ud835\udc63 (3.2) The next step would be to determine the thickness of the vane required. The vane must be robust enough to withstand the pressure differential between the chambers and drive the rotor component without yielding. For calculation of the bending moment stresses that the vane 30 would experience during operation, it can be safe to assume that the vane has a uniform rectangular cross-section area since the actual vane design would have a much thicker crosssection due to the addition of fillets. Figure 3.7 shows the cross-section and free body diagram of the vane subject to gas pressure forces between the chamber and the reaction force from the rotor. It is assumed that these forces are at their maximum; the reaction force is acting at the tip of the vane with the maximum magnitude in which the moment arm for the rotor is its shortest at maximum acceleration and the pressure differential across the vane is at its maximum. Based on the diagram, the bending moment exerted on the vane can be summarised as shown in Equation (3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001910_9312710_09348895.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001910_9312710_09348895.pdf-Figure16-1.png", + "caption": "FIGURE 16. Side view of the proposed LTCC LWA with rotated connectors by \u03be from the horizon.", + "texts": [ + " To summarize the parametric study, the corresponding peak realized gain at 28.5 GHz for different parameters are reported in Table 2. Placement the connectors on the antenna structure can bend the ends of the antenna due to the small thickness of the structure. Moreover, the connectors may not be adequately secured at their places due to assembly errors. Overall, the pin may not lie entirely on the signal trace. To simulate such case, we offset the connector pin angle from the horizon by \u03be , as illustrated in Fig. 16. The corresponding S-parameters, radiation patterns, and peak realized gain are reported in Figs. 17-19, respectively. According to Fig. 17, changing \u03be leads to smaller return loss. Fig. 18 indicates that offsetting the connectors increases the SLL and the lobe levels of the beams radiating beneath the antenna. According to Fig. 19, the peak realized gain degrades by changing \u03be . Hence, rotating the connectors causes discrepancies because the pin is not touching the signal trace properly and only a small portion of the input signal transfers to the antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003726_8_agriceng-2022-0005-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003726_8_agriceng-2022-0005-Figure2-1.png", + "caption": "Figure 2. The objective function response surface (a) and its two-dimensional sections (b) for ZAV-25 at \u04452 = 0", + "texts": [], + "surrounding_texts": [ + "Currently, there is no methodology that allows analyzing the effect of electromechanical systems on efficiency of using electrical energy for both for individual production lines and grain cleaning units. At the same time, it was established (Postnikova, 2011) that the most informative indicator for determining energy-saving modes of operation is the specific consumption of electrical energy for the grain cleaning process. The ZAV-25 unit was studied in terms of the influence of its operating modes on its power demand using MEP (Nazar'jan et al., 2012; Kiktev et al., 2021). Based on the review of modern grain cleaning theory and practice, the studied mathemat- ical model was formed as equation (Postnikova, 2011): \ud835\udc4a\ud835\udc60 = \u2211 \ud835\udc43\ud835\udc5b\ud835\udc56\u22c5\ud835\udc3e \ud835\udc5b \ud835\udc56=1 \ud835\udc44\u22c5\ud835\udf02\ud835\udc5b.\ud835\udc4e , (3) where: \u2211 \u0420\ud835\udc5b\ud835\udc56 \ud835\udc5b \ud835\udc56=1 \u2013 total rated power of production line electric motors, (kW) K \u2013 load factor of production line electric motors Q \u2012 production line performance, (t\u00b7h-1) \u03b7n.a \u2013 average rated efficiency of electric motors. The dependence of the optimization parameter Ws can be presented as a function of power consumption of the motors by using equation (3): \ud835\udc4a\ud835\udc60 = \u2211 \ud835\udc431\ud835\udc56\u22c5\ud835\udc3e \ud835\udc5b \ud835\udc56=1 \ud835\udc44 (4) where: \u2211 \ud835\udc431\ud835\udc56 \ud835\udc5b \ud835\udc56=1 \u2013 total consumed or connected power of electric motors, (kW) \u2211 \ud835\udc431\u0456 = \ud835\udc43\ud835\udc5b1 \ud835\udf02\ud835\udc5b1 +\ud835\udc5b \ud835\udc56=1 \ud835\udc43\ud835\udc5b2 \ud835\udf02\ud835\udc5b2 + \ud835\udc43\ud835\udc5b3 \ud835\udf02\ud835\udc5b3 +. . . + \ud835\udc43\ud835\udc5b\ud835\udc5b \ud835\udf02\ud835\udc5b\ud835\udc5b , (i = 1, 2, 3, \u2026, n). (5) The selected variable factors that affect specific power consumption are: Q \u2013 unit performance (tons per hour); \u04201i \u2013 connected power of the electric motor (kW); K \u2013 load factor of the electric motors. The levels and variation intervals of the variables for ZAV-25 grain cleaning unit are given in (Nazar'jan et al., 2012) and are selected in accordance with realistic possibilities of adjusting working elements of the unit line. When solving the problem of optimizing complex research objects for an adequate description of the optimum region, the second-order polynomials of the form are usually used: \u0443 = \ud835\udc4f0 +\u2211 \ud835\udc4f\ud835\udc56 \u22c5 \ud835\udc65\ud835\udc56 +\u2211 \ud835\udc4f\ud835\udc56,\ud835\udc57 \u22c5 \ud835\udc65\ud835\udc56 \u22c5 \ud835\udc65\ud835\udc57 +\u2211 \ud835\udc4f\ud835\udc56\ud835\udc56 \ud835\udc5b \ud835\udc56=1 \ud835\udc5b \ud835\udc56\u227a\ud835\udc57 \ud835\udc5b \ud835\udc56=1 \ud835\udc65\ud835\udc56 2+. .., (6) where \u0443 \u2013 target function; b0, b\u0456, b\u0456j, b\u0456\u0456 \u2013 regression equation coefficients; \u0445\u0456, \u0445j, \u0445\u0456 2 \u2212 normalized factor values. According to (Nazar'jan et al., 2012), second-order central composite design (CCD) is recommended for solving optimization problems. CCD is the experiment planning at five levels, which, in normalized units, can be represented as: 1) \u2013\u03b1; 2) \u22121; 3) 0; 4) +1; 5) +\u03b1, (7) where: \u03b1 \u2013 star point shoulder size. The OCCP matrix for three factors is presented in (Nazar'jan et al., 2012). Statistical data processing has been performed. Regression equations were obtained to calculate the specific power consumption depending on the performance of the grain cleaning unit, the connected power, and the load factor of the electric motors in coded units. \u0443\u0303 = 1.4343 \u2212 0.546\u04451 + 0.489\u04452 + 0.338\u04453 \u2212 0.207\u04451\u04452 \u2212 0.143\u04451\u04453 + +0.123\u04452\u04453 \u2212 0.048\u04451\u04452\u04453 \u2212 0.089\u04451 2 + 0.135\u04452 2 + 0.135\u04453 2. (8) The symbols adopted in equation (8) are: \u0443\u0303, Ws \u2013 specific power consumption; \u04451, \u04201 \u2013 power; \u04452, Q \u2013 production; \u04453, K \u2012 load factor of electrical equipment, respectively, in coded and natural values. After obtaining an adequate second-order mathematical model as in (8), it is necessary to determine the coordinates of the optimum (maximum or minimum, if any) and analyze the response surface properties in the optimum vicinity. Object optimization problems are usually solved by search methods, which are extremely varied. The main methods include the following: gradient method, saddle-point method and its modifications \u2013 steepest ascent, Gauss-Seidel method, simplex method,, random search method and others. There are mathematical transformations that allow obtaining a graphical and analytical interpretation of the optimum area. For these purposes, the mathematical model canonical transformation and the method of two-dimensional sections of the response surface are commonly used. Regression equation (8) was differentiated for each factor: \ud835\udf15?\u0303? \ud835\udf15\ud835\udc651 = \u22120.546 \u2212 0.207\u04452 \u2212 0.143\u04453 \u2212 0.048\u04452\u04453 \u2212 0.178\u04451 = 0; \ud835\udf15?\u0303? \ud835\udf15\ud835\udc652 = 0.489 \u2212 0.207\ud835\udc651 + 0.123\ud835\udc653 \u2212 0.048\u04451\u04453 + 0.27\ud835\udc652 = 0; \ud835\udf15?\u0303? \ud835\udf15\ud835\udc653 = 0.338 \u2212 0.143\ud835\udc651 + 0.123\ud835\udc652 \u2212 0.048\u04451\u04452 + 0.27\ud835\udc653 = 0. The center coordinates were obtained in coded units after solving the system of equations \u04451\ud835\udc46 = 1.0; \u04452\ud835\udc46 = \u22120.4; \u04453\ud835\udc46 = \u22120.827; \u0443\ud835\udc46 = 0.664, which correspond to the following values of factors and objective function in physical units Q = 20 t\u00b7h-1; \u04201 = 26 kW; K = 0.526. The optimal function value corresponds to Ws = 0.6 kWh\u00b7t-1. Possible two-dimensional sections, which are of the greatest practical importance for determining the specific power consumption, depending on the performance of the unit, the connected power and the load factor of the electric motors, are as follows: \u2212 At \u04451 = 0 (Fig. 1a) the response surface of objective function; \u0431) two-dimensional sec- tions for ZAV-25 \ud835\udf15?\u0303? \ud835\udf15\ud835\udc652 = 0.489 + 0.123\ud835\udc653 + 0.27\ud835\udc652 = 0; \ud835\udf15?\u0303? \ud835\udf15\ud835\udc653 = 0.338 + 0.123\ud835\udc652 + 0.27\ud835\udc653 = 0; \u04452\ud835\udc46 = \u22121.566; \u04453\ud835\udc46 = \u22120.534; \u0443\ud835\udc46 = 0.96, which corresponds to factors values and objective function in physical units \u04201 = 14.34 kW; K = 0.57 and Ws = 0.96 kWh\u00b7t-1. Figure 1. The objective function response surface (a) and its two-dimensional sections (b) for ZAV-25 at \u04451 = 0 To find the optimal value of the target function, the system has been solved: \ud835\udc53(\ud835\udc35) = | 0.27 \u2212 \ud835\udc35 0.5 \u22c5 0.123 0.5 \u22c5 0.123 0.27 \u2212 \ud835\udc35 | = (0.27 \u2212 \u0412) \u22c5 (0.27 \u2212 \ud835\udc35) \u2212 0.0038 = 0. As a result, the equation is: \ud835\udc4c \u2212 0.96 = 0.209\ud835\udc4b2 2 + 0.331\ud835\udc4b3 2. \u2212 At \u04452 = 0 (Fig. 2\u0430) the response surface of objective function; \u0431) two-dimensional sec- tions for ZAV-25: \ud835\udf15?\u0303? \ud835\udf15\ud835\udc651 = \u22120.546 \u2212 0.143\ud835\udc653 \u2212 0.178\ud835\udc651 = 0; \ud835\udf15?\u0303? \ud835\udf15\ud835\udc653 = 0.338 \u2212 0.143\ud835\udc651 + 0.27\ud835\udc653 = 0; \u04451\ud835\udc46 = \u22121.446; \u04453\ud835\udc46 = \u22122.018; \ud835\udc66\ud835\udc46 = 1.488, which corresponds to factors values and objective function in physical units: Q = 7.9 t\u00b7h-1; K = 0.35 and Ws = 1.488 kWh\u00b7t-1 To find the optimal value of the target function, the system has been solved as follows: \ud835\udc53(\ud835\udc35) = | \u22120.178 \u2212 \ud835\udc35 \u22120.5 \u22c5 0.143 \u22120.5 \u22c5 0.143 0.27 \u2212 \ud835\udc35 | = (\u22120.178 \u2212 \u0412) \u22c5 (0.27 \u2212 \u0412) \u2212 0.25 \u22c5 0.1432 = 0. As a result of solving the system, the equation is: \ud835\udc4c \u2212 1.488 = \u22120.189\ud835\udc4b1 2 + 0.281\ud835\udc4b3 2. \u2212 At \u04453 = 0 (Fig. 3\u0430) the response surface of objective function; \u0431) two-dimensional sec- tions for ZAV-25: \ud835\udf15?\u0303? \ud835\udf15\ud835\udc651 = \u22120.546 \u2212 0.207\ud835\udc652 \u2212 0.178\ud835\udc651 = 0; \ud835\udf15?\u0303? \ud835\udf15\ud835\udc652 = 0.489 \u2212 0.207\ud835\udc651 + 0.27\ud835\udc652 = 0; \u04451\ud835\udc46 = \u22120.508; \u04452\ud835\udc46 = \u22122.2; \ud835\udc66\ud835\udc46 = 1.035, which corresponds to factors values and objective function in physical units: Q = 14.44 t\u00b7h-1; \u04201 = 8 kW and Ws = 1.035 kWh\u00b7t-1. To find the optimal value of the target function, the system has been solved as follows: \ud835\udc53(\ud835\udc35) = | \u22120.178 \u2212 \ud835\udc35 \u22120.5 \u22c5 0.207 \u22120.5 \u22c5 0.207 0.27 \u2212 \ud835\udc35 | = (\u22120.178 \u2212 \ud835\udc35) \u22c5 (0.27 \u2212 \ud835\udc35) \u2212 0.25 \u22c5 0.2072 = 0. As a result of solving the system, the equation is: \ud835\udc4c \u2212 1.035 = \u22120.201\ud835\udc4b1 2 + 0.293\ud835\udc4b3 2. According to the analysis and solution result of the equations obtained for minimax using a package of specialized mathematical software, the minimum specific power consumption possible values of the ZAV-25 production lines were obtained. The factor change was taken into account." + ] + }, + { + "image_filename": "designv8_17_0001040_77_aoje_2_021025.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001040_77_aoje_2_021025.pdf-Figure6-1.png", + "caption": "Fig. 6 Tile unit curling geometry. Geometry of the tile unit architecture is determined by the height H and the kinematic widthW, and the circular membrane shape determines the tile unit curling geometry under vacuum.", + "texts": [ + " The tiles are assumed to be rigid such that they do not deform under the membrane tension, compression of the atmospheric pressure, or the contact at the inter-tile hard stop. The bladder is assumed airtight such that pressure within the vacuum bladder is uniform. The first principle modeling does not include the hinge stiffness and the bladder effects from friction and end effects, which are captured in the phenomenological terms characterized experimentally. 4.1.2 Geometry Modeling. Curling torques are analyzed using a cross-sectional view as torques per unit length shown in Fig. 6, since the tile unit is uniform along its length. The tile height H and kinematic width W are the two primary dimensions that determine the tile unit actuation. The height H is defined as the distance from the membrane connection point M to the line of the tile base, Table 1 Nomenclature for the unit curling and surface models Varying parameters \u0394p Gauge pressure of the vacuum bladder \u03b8 Curling angle, angle deflection from flat about a hinge \u03c6i Orientation angle from flat of a tile in surface, \u03c6i = \u2211i j=1 \u03b8j (i = 1, " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002029_d.aspx_paperID_79349-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002029_d.aspx_paperID_79349-Figure22-1.png", + "caption": "Figure 22. Bend patch configuration.", + "texts": [ + " The fitted plot has been obtained after deriving the RLC parameters of the equivalent spice circuit. The poles and residues derived from a rational function using Matlab has been shown in Table 4. Figure 20 shows the obtained equivalent spice circuit using ADS tool and the RLC values have been shown in Table 5. DOI: 10.4236/ojapr.2017.53011 146 Open Journal of Antennas and Propagation Patch antenna with and without CSRR loading has been bent with a radius of 20 mm and 40 mm to show the effect of bending. The bend structures have been shown in Figure 21 and Figure 22, while the comparison of the return loss has been plotted in Figure 23. DOI: 10.4236/ojapr.2017.53011 147 Open Journal of Antennas and Propagation The patch configuration as defined in Section 3 has been used for the CSRR loading effect over its resonance frequency. Here the patch element has dimension of 13.9 mm \u00d7 18 mm \u00d7 0.017 mm with its inset feed of 13.05 mm \u00d7 2.8 mm \u00d7 0.017 mm and inset gap of 0.5 mm. This patch element has been laid over 30 mm \u00d7 30 mm \u00d7 1.57 mm Fr4 substrate with its relative permittivity 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003708_19_ms-10-47-2019.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003708_19_ms-10-47-2019.pdf-Figure4-1.png", + "caption": "Figure 4. Shape and configuration of the MBCDM: (a) overall shape; (b) detailed view.", + "texts": [ + " (19), we can obtain the backlash angle of this novel configuration precise cable drive. \u03b8b = (20) Tpre (ro+ ri) AE\u00b5ro [( Mle Ml/2Tprero 2Tprero ( eMl/2Tprero \u2212 1 ) \u2212 1 ) 1+ \u00b5 \u221a L2\u2212 ( rg+ ri )2 ro+ ri \u2212 ln ( Mle Ml/2Tprero 2Tprero ( eMl/2Tprero \u2212 1 ))] In order to validate the design and performance analysis methods of the proposed configuration, the parametric sensitivities would be investigated after determining the specific parameters. Shape and configuration of the designed 1-DOF MISO with bevel gear configuration cable drive mechanism (MBCDM) are shown in Fig. 4. The mechanism includes fixed support, DC motors, input pulleys, guide pulley, output drum, pretension mechanism and encoders. Two DC motors are mounted on the fixed support in parallel to rotate the two input pulleys. www.mech-sci.net/10/47/2019/ Mech. Sci., 10, 47\u201356, 2019 Table 1. The physical properties of the selected cable. Brand Construction Coating Material Nominal diameter (mm) Effective aero A (mm2) Radius ratio \u03c1 FF-081 7\u00d7 7 Uncoated SUS-304 0.81 0.3117 14.8 Table 2. The geometric parameters of the developed MBCDM" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001191_8948470_09252143.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001191_8948470_09252143.pdf-Figure9-1.png", + "caption": "FIGURE 9. Ovearall structure of the NFF antenna designed by HFSS.", + "texts": [ + " The larger the inclined angle of coupling slots is, the larger the coupling factor is. Meanwhile, the lengths of coupling slots function to compensate for the coupling phase to some extent. Step 4: The subarrays of radiating slots, with different configurations shown in Table 3, need to be designed separately. The lengths and widths of radiating slots are optimized to realize the desired radiating power and to satisfy the matching condition simultaneously. The overall structure of the NFF antenna designed by HFSS is illustrated in Fig. 9. VI. ANTENNA FABRICATION AND EVALUATION The antenna presented in this article is fabricated by a special 3-D printing technique. That is the Direct Metal Laser Sintering of the aluminum alloy powder. The photograph of the prototype antenna is shown in Fig. 10. Its overall dimensions are 282.5 mm \u00d7 237 mm \u00d7 25 mm. VOLUME 8, 2020 203053 The reflection of the prototype antenna is measured by using a vector network analyzer. As shown in Fig. 11, the measured and simulated reflections are suppressed below \u221210 dB over the frequency ranges of 9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004625_16_01_smdo160007.pdf-Figure34-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004625_16_01_smdo160007.pdf-Figure34-1.png", + "caption": "Figure 34. Pictures of the example of a set of two flanges fastened by eight bolts.", + "texts": [ + " Check for each set that the resulting load in the bolts is compatible with the admissible load. 4. Update of control variables: load increment, displacement increment and length compatibility. 5. Deduction of the displacements of the flange at other locations of bolts. 6. Deduction of load of other sets bolts. All of this can be summarized by the following simplified model. The solution can be displayed on screen, by example on excel sheets (Figures 32 and 33). Two circular flanges assembled with eight bolts (screws and nuts) (Figure 34). In this example two bolt tensioners are used and the required tightening load is Fo = 100 kN (Figure 35). Three cases are analyzed in terms of maximum load applied Fh to the bolts at hydraulic tension phase. \u2013 No limitation on maximum load applied to the bolts. \u2013 The maximum load applied to the bolts is limited to 160 kN. \u2013 The maximum load applied to the bolts is limited to 120 kN. The results are shown on following the screenshots. As can be seen and obviously, the lower is the limitation on maximum load Fh on bolts, the higher is the number of necessary passes to reach the required tightening load Fo (Figures 36\u201338)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure18-1.png", + "caption": "Fig. 18 Optimization design of rubber hanging parameters for equipment cabin under floor frame based on 952 weak coupling interface is adopted for service car body system, so as to avoid internal lateral coupling 953 resonance of traction converter as much as possible. (a \u2013 c) 1st order lateral bending inherent mode of 954 aluminium alloy car body has evolved into two critical modes, i.e. 1st order lateral bending modes on lower 955 and upper part of service car body. (d) Safety assessment of lateral vibration for traction converter when 956 running in a tangent line approaching to limit speed of 650 km/h under \u03bbe = 0.06 according to specified in 957", + "texts": [ + " (c) Travelling wide light band is formed on top surface of railhead while concentrated wear is 926 evolved on wheel tread. (d) Bogie frame thereby generates forced resonance with dominant frequency of ca. 927 6 Hz and leading frequency is close to or more than 10 Hz. (e) Influence of vehicle speed on lateral 928 acceleration (RMS)2.2\u03c3 of bogie frame. 929 (2) Correlative excitations come from internal lateral resonances. By applying 937 MMRT, the transaction strategy of flexible body to MBS interface was improved, as 938 shown in Fig. 18, so as to remove and eliminate completely the lateral coupling 939 relationship between running gear and service car body. 940 As mentioned above, through the collaborative and innovative efforts of vehicle, rail 941 and passenger transport disciplines, the slight central hollow tread wear provides the 942 necessary conditions for the structural experts to better realize the structural dynamic 943 response design optimization of aluminium alloy car body. In order to ensure the weak 944 coupling interface, the independent design of equipment cabin under floor frame mainly 945 includes the following three points: 946 1) In order to avoid the negative impacts caused by the reciprocating lateral 947 movement of traction converter, e", + " 972 The independent design of the above equipment cabin is based on the following two 973 guidelines to realize the weak coupling interface: 974 1) The improved transaction strategy of flexible body to MBS interface is 975 implemented by applying MMRT. Specifically, considering the low dynamic interaction 976 requirements of both interfaces, including the floor frame under which the equipments 977 like traction converter hanged and the roof on which the pantograph with fairing and the 978 air conditioning unit installed, the constrained DoF set to zero. 979 2\uff09As shown in Fig. 18 (a - c), the 1st lateral bending inherent mode of aluminium 980 alloy car body is transformed into the 1st lateral bending modes of service car body on 981 lower / upper parts, both modal frequencies are ca. 14.0/17.9 Hz. 982 As shown in formula (22), only when the constraint DoF is zero, the corresponding 983 interface stiffness will not be weakened, and the relevant modal mass will be reduced. 984 That is to say, under the strong coupling interface, the central rhombus modal frequency 985 of service car body is ca. 9.7 Hz, which becomes the critical modal vibration. Meanwhile 986 under the weak coupling interface, it changes into the 1st lateral bending mode on lower 987 part, ca. 14.0 Hz. So the lateral coupling relationship is then removed between running 988 gear and service car body. 989 According to the provisions of IEC61373 \u2013 2010, as shown in Fig. 18 (d - h), the 990 simulation analyses of various working conditions show that the traction converter has no 991 lateral coupling resonance and is far below the safety threshold. According to the floating 992 plate effect, the moderate lateral vibration of traction converter releases the 993 corresponding kinetic energy in time, which is beneficial to maintain the ESL safety of 994 aluminium alloy car body. 995 At the same time, it is also confirmed again that the self-adaptive improved design 996 for next generation HSRS can satisfy the higher speed requirements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure3.22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure3.22-1.png", + "caption": "Figure 3.22: Field distribution in absolute value at 60 GHz in xz-plane of the GDSM waveguide (a) the electric field (b) magnetic field", + "texts": [ + "0023), and the metal parts (metasurface patches and the ground) use annealed copper (\u03c3 = 5.8\u00d7107 S/m) as their material. The waveguide port is implemented to excite the propagation mode. However, it should be noted that the CST waveguide port is not able to properly excite the desired propagation mode. The port is placed on the border of the metasurface, which excites a quasiTEM mode, which will then couple into the appropriate GDSM propagation mode. This results in a mismatch that will not exist (or largely reduced) when a tapered transition is added. Figure 3.22 shows the electromagnetic field distribution of the absolute value at 60 GHz in the cross section of xz-plane. The field distribution has a form of TM propagation mode. From the magnetic field distribution in figure 3.22(b), the propagation wavelength \u03bbg can be approximately estimated to be about 3.5 mm. Therefore, the phase constant can be derived as \u03b2 = 2\u03c0/\u03bbg = 1795 rad/m, which is in good agreement with the TRM-calculated 60 GHz phase constant of the GDSM shown in table 3.5 (i.e., \u03b2 = 1758 rad/m). As can be seen from figure 3.22, the simulated GDSM structure radiates 3.9. METASURFACE-BASED ENHANCED-DISPERSION WAVEGUIDE at the beginning (left side) and the end (right side) of the metasurface. This is because, as mentioned earlier, the port mode calculated in the simulation is not the same as the GDSM propagation mode, therefore causing mismatch. Even though the GDSM mode is successfully coupled into the waveguide from the excitation port mode, the waves see discontinuities at the coupling section at the two ports, and thus the structure radiates at these ends. In addition, since the dielectric loss and metal conduction loss are considered in the simulation, the radiation on the end side of the waveguide is comparatively smaller. Figure 3.23 shows the far field patterns of the waveguide in simulation. As anticipated, it can be seen that due to the discontinuities at the edges of the metasurface, the GDSM guide exhibits a 10 dB of radiation from about 20\u25e6 to 40\u25e6 in the forward quadrant as observed in figure 3.22. In further design optimization, this discontinuity at the starting border of the metasurface should be taken into consideration to avoid unwanted radiation. For example, the beginning of the metasurface can be gradually changed to have smoother transition between the GDS propagation mode and the GDSM propagation mode. signed Waveguide With the previously designed dispersion-enhanced waveguide using the 0.254 mm-thickness Rogers substrate RT/duroidr 6010 (\u03b5r = 10.2, tan \u03b4 = 0.0023), a periodic leaky-wave antenna is realized by adding periodicity to the GDSM structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004329_f_version_1614262193-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004329_f_version_1614262193-Figure5-1.png", + "caption": "Figure 5. Strains and the resulting secondary stresses in a cylindrical pressure vessel.", + "texts": [ + " To visualise the consequence of this, strain in both cylinder and dome are calculated using Hooke\u2019s law, Equation (9). \u03b5m = 1 E [\u03c3m \u2212 \u03bd\u03c3t] \u03b5t = 1 E [\u03c3t \u2212 \u03bd\u03c3m] (9) Since both the segments are physically connected, the dome will try to pull the cylinder inwards while the cylinder will try to pull the dome outwards. If both the parts are disjointed, then the difference in the radii can be calculated as (see [21]): \u03b4 = pr2 2hE (10) These two parts are held together by equal but opposite transverse shear forces and bending moments, both of which act on the faces at the dome-cylinder interface, as shown in the Figure 5. In order to design the vessel in such a way that it does not fail at the interface, Equation (9) has to be continuous. This requires that the stresses and in-turn the radii of curvature, pressure, and thickness must be continuous. At the interface of the cylinder and the dome, there is a discontinuity in the radius of curvature, which results in the aforementioned secondary stresses. In addition, in a wound composite pressure vessel, in order to take advantage of the composite, various ply length and winding angle are used: hoop, helical, and polar winding" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000591_f_version_1671613940-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000591_f_version_1671613940-Figure3-1.png", + "caption": "Figure 3. Rotor slot shape of induction motor and its parameters.", + "texts": [ + " The rotor resistance, R2, and rotor reactance, X2, are derived from the rotor slot geometries that also influence the three performance indicators. Rotor resistance determines the copper losses related to IM rotor, reducing its efficiency. Furthermore, breakdown torque depends on rotor-leakage reactance, as given in (8). In addition, rotor reactance also has minor impact on reactive power consumption under typical operating conditions which affect the power factor. The rotor slot design parameters are illustrated in Figure 3. The six-rotor slot parametric geometries are rotor slot opening width (Br1), upper width (Br2), lower width (Br3), opening height (Hr1), wedge height (Hr2), and height (Hr3). In this work, only Br1, Br2, and Hr3 are optimized within the specified limits as in Table 4 to ensure they are not violating the overall design of IM. Similar to the stator slot, the three rotor slot parameters are selected because they highly impact the rotor magnetization characteristics and significantly affect the resistance and reactance of the rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure4-1.png", + "caption": "Figure 4. Models of cross-sections of magnetic circuits: (a) Q = 48, 2p = 32, q = 0.5; (b) Q = 84, 2p = 56, q = 0.5; (c) Q = 63, 2p = 56, q = 0.375.", + "texts": [ + " We must also keep in mind that, when yoke thickness is reduced, the mechanical strength of the rotor also goes down. An additional problem emerges when we try to increase the number of stator slots in proportion to the increased number of poles. For instance, with the number of poles 2p = 32 and number of slots Qs = 48, the number of slots per pole per phase is q = 0.5. If we raise the number of poles up to 2p = 56, then in order to maintain q = 0.5, the number of slots should be increased to Qs = 84 (Figure 4). Since the outer diameter of the machine is constant, such a large number of slots may not be feasible due to the technological limitations of production machines, the strength of the thin stator teeth, or the workability of the winding. In addition, the cost of producing a winding will also increase, as the number of coils is much greater. The area of the active part of the slot winding also decreases, because, with the increase in the number of slots, the share of slot insulation is greater. In this situation, it is possible to reduce the number of sockets per pole per phase, but it should be remembered that, for motors with q < 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004747_article_25861568.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004747_article_25861568.pdf-Figure2-1.png", + "caption": "Fig. 2. The parallel approximate figure of the far field calculation", + "texts": [ + " The schematic diagram is shown as figure 1, \u0394r represents the phase change, D is the diameter of the antenna. \u00a9 2016. The authors - Published by Atlantis Press 379 A. Basic principle Under the condition of far-field distance, spot P radiate electromagnetic field aimed to area J, watch spot is the coordinate original point O, r is path vector from watch point to field point, r is path vector from point O to the point Q in the original area, is the angle of r into r , the distance from point Q to field point P. Figure 2 is the parallel approximate figure of the far field calculation, in globe coordinate, 2 3 2 2 2 1 1 c o s s i n c o s s i n 2 r r R r r r r x \uff081\uff09 Under the condition of far-field distance, since r is mostly more bigger than r , cosr r r , thus, cosrrR \uff082\uff09 The formula (2) is called calculation approximate, path vector R and r can be considered one parallel ray. The deviation due to ignoring the third element of formula (1) is \u03bb/16 [1] , the corresponding phase difference is\uff1a 2 rad 22" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003236_id_0354-51801805953L-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003236_id_0354-51801805953L-Figure6-1.png", + "caption": "Figure 6: Motor speed and torque during steering process Figure 7: Motor speed and torque during return process", + "texts": [ + " \u03c8 \u2208 [\u22121, 1] , with the increase of the rotation angle, it gradually turns from 1 to -1, realizing the adjustment of bilateral motors with different driving states. 3.2 The calculation of direct torque control strategy The steering process requires close coordination between the accelerator pedal or the brake pedal and the steering wheel. The control process is complex which requires further consideration. Firstly, the acceleration condition is considered, at this time \u03be \u2208 [0, 1] . Assume that the speed-torque characteristic curve of the two motors are the same, as shown in Figure 6, at the same speed, the maximum drive torque of the motor is equal to the maximum braking torque. n1 and n2 respectively indicate the speed of outside motor and inside motor, Tmax(n) is the maximum motor torque at speed n . As seen in Figure 6, n1 > n2 and Tmax(n1) < Tmax(n2), the torque difference between the two motors can be expressed by formula (7): T\u20321 \u2212 T\u20322 = \u03be \u00b7 Tmax(n1) \u2212 \u03be \u00b7 \u03c8 \u00b7 Tmax(n2) (7) Where T\u20321 and T\u20322are the demand torque of the two motors. However, when \u03c8 \u2208 [0, 1] , there may be the situation T\u20321 \u2212 T\u20322 \u2264 0. Therefore, it is necessary to revise the torque of the motors, T\u20321 and T\u20322 can be expressed as:{ T\u20321 = \u03be \u00b7 Tmax(n1) T\u20322 = \u03be \u00b7 \u03c8 \u00b7 Tmax(n1) 0 < \u03c8 < 1 (8) When \u03c8 \u2208 [\u22121, 0], in order to form a bigger torque difference and make full use of the braking ability of the inside motor, the demand torque of the motors can be expressed as:{ T\u20321 = \u03be \u00b7 \u03c8 \u00b7 Tmax(n1) T\u20322 = \u03be \u00b7 Tmax(n2) \u22121 \u2264 \u03c8 \u2264 1 (10) Similarly, for the braking condition, the demand torque expression can be derived by the same method" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001562_aper_Jater-4.1.5.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001562_aper_Jater-4.1.5.pdf-Figure1-1.png", + "caption": "Fig. 1. Forces on a sailplane", + "texts": [ + " Gliding is the origin of light, all the early attempts of lying were powerless and mostly depended on wings that emulate the birds. Up to early 1900s, most of these attempts did not last more than few minutes. However, they were the inspiration for present sailplanes, which are capable of lying for tens of hours and hundreds of miles without one millilitre of fuel. This outstanding performance came as a result of incorporating modern technologies and theories in sailplane design. Soaring is heavier-than-air light without the use of thrust. As a result, only three forces act on the sailplane; Lift, Drag and Weight (Figure 1). Although a sailplane is not powered, there is still a need to obtain thrust. It does this by converting the potential energy into kinetic as it glides downward, trading height for distance. *Corresponding author: Ahmed El Ibrahim \u2020email: alibrahim.ahmad88@gmail.com The Author(s). Published by TAF Publishing. This is an Open Access article distributed under a Creative Commons Attribution-NonCommercialNoDerivatives 4.0 International License The performance of sailplane can be evaluated by its maximum range or maximum endurance" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003696_7_10_27_10_1144__pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003696_7_10_27_10_1144__pdf-Figure13-1.png", + "caption": "Fig. 13 Control of cameras corresponding to updown motion of viewer (side view)", + "texts": [ + " 1150 1991\u5e7410\u6708 \u8a08\u6e2c \u81ea\u52d5\u5236\u5fa1\u5b66\u4f1a\u8ad6\u6587\u96c6 \u7b2c27\u5dfb \u7b2c10\u53f7 Fig. 11 Space of display image when the viewer moves rightward (\u03bb=L,\u03b5=E,\u03bc=M=10) \u3044 \u3046\u3053\u3068\u3092\u610f\u5473\u3059 \u308b. 3.3 \u8996 \u8005\u306e\u5de6\u53f3\u79fb\u52d5 Fig. 11\u306f,\u8996 \u8005 \u304c\u53f3 \u306b\u79fb\u52d5 \u3057\u305f \u3068 \u304d \u306e\u7acb\u4f53 \u50cf\u3092 \u793a \u3057\u3066 \u3044 \u308b.Fig. 8\u306e \u6c34\u5e73\u9762\u3092,\u8996 \u8005\u304c\u53f3\u65b9 \u5411\u306b10 (cm)\u79fb \u52d5 \u3057\u305f\u3068\u304d\u306e,\u50cf \u3092\u771f\u4e0a\u304b \u3089\u307f\u305f\u56f3\u3067 \u3042\u308b. \u3053\u308c \u306b\u3088\u308c\u3070,\u6b63 \u9762\u304b \u3089\u898b\u305f \u3068\u304d\u898b \u3048\u3066 \u3044\u305f\u53f3\u5074 \u306e\u90e8 \u5206\u304c\u96a0\u308c,\u898b \u3048\u3066 \u3044\u306a\u304b \u3063\u305f\u3053\u5de6\u5074 \u306e\u90e8\u5206\u304c\u898b \u3048\u3066 \u304f\u308b \u3068\u3044\u3046\u56de \u308a\u8fbc\u307f \u306e\u52b9\u679c\u304c\u5f97 \u3089\u308c\u3066 \u3044\u308b\u3053\u3068\u304c\u308f \u304b\u308b. \u307e\u305f\u8996\u8005 \u304c\u6b63\u9762\u304b \u3089\u898b\u305f \u3068\u304d\u306e\u6b63\u9762\u5965\u884c \u65b9\u5411\u304c \u307b\u307c\u4fdd \u5b58 \u3055\u308c,\u7279 \u306b\u64ae\u5f71\u7a7a\u9593 \u306b\u304a \u3051\u308b\u6b63\u9762\u65b9\u5411 \u306e\u70b9(\u7e26 \u8ef8\u4e0a \u306e\u70b9)\u304c \u8868\u793a\u7a7a\u9593 \u306b\u304a\u3051\u308b\u7e26\u8ef8\u4e0a\u306e\u70b9 \u3068 \u3057\u3066\u5fe0\u5b9f \u306b\u518d \u73fe \u3055\u308c\u3066 \u3044\u308b\u3053\u3068\u304c\u308f\u304b \u308b. \u4e21 \u30ab \u30e1\u30e9\u306e\u5149\u8ef8\u306e\u4ea4\u70b9\u304c\u70b9F\u306b \u306a \u308b\u3088 \u3046\u306b\u4fdd \u3061\u306a\u304c \u3089,\u4e21 \u30ab\u30e1 \u30e9\u306e\u30ec \u30f3\u30ba\u7cfb\u306e\u4e2d\u5fc3\u3092,\u8996 \u8005\u306e\u4e0a\u4e0b\u5de6\u53f3\u306e \u52d5 \u304d\u306b\u5408\u305b\u3066,\u925b \u76f4 \u306a \u5e73\u9762\u4e0a \u3092 \u4e0a\u4e0b\u5de6\u53f3 \u306b \u79fb\u52d5 \u3055\u305b \u308b(Fig. 13).\u672c \u30b7\u30b9 \u30c6\u30e0 \u306b\u304a\u3044\u3066 \u306f,\u70b9F\u3092 \u4e2d\u5fc3 \u3068 \u3057\u3066,\u30ab \u30e1\u30e9\u306e\u79fb\u52d5\u88c5\u7f6e\u5168\u4f53\u3092\u4e0a \u4e0b\u65b9\u5411 \u306b\u56de\u8ee2 \u3055\u305b \u308b \u5fc5\u8981\u304c \u3042\u308b. \u305f\u3060 \u3057,\u8996 \u8005\u304c\u4e0a \u306b\u5927 \u304d \u304f\u79fb\u52d5\u3059 \u308b\u3068\u753b\u9762\u4e0b\u90e8 \u304c, \u4e0b \u306b\u5927 \u304d \u304f\u79fb\u52d5\u3059 \u308b\u3068\u753b\u9762\u4e0a\u90e8\u304c,\u5965 \u306b\u898b\u3048 \u308b\u50be \u5411\u304c \u3042 \u308b\u305f\u3081,\u8996 \u8005\u306e\u6975\u7aef\u306b\u5927 \u304d\u306a\u4e0a\u4e0b \u79fb\u52d5 \u306b\u306f\u5bfe\u5fdc\u3067 \u304d \u306a \u3044. \u91ce \u4e2d \u30fb\u4f0a \u9054:\u4e21 \u773c \u8996 \u3068\u904b \u52d5 \u8996 \u3092\u5fdc \u7528 \u3057\u305f \u30d3\u30c7 \u30aa \u30b7 \u30b9 \u30c6 \u30e0 1151 \u3063\u305f\u611f\u899a \u3092,\u3088 \u308a\u30ea\u30a2\u30eb\u306a\u3082\u306e\u306b\u3059 \u308b\u305f\u3081 \u306b,\u8996 \u8005 \u306e \u524d\u5f8c\u79fb\u52d5 \u306b\u5bfe\u5fdc \u3057\u305f\u30ab\u30e1 \u30e9\u5236\u5fa1\u3092\u4ed8\u52a0\u3059 \u308b \u3053\u3068\u304c\u52b9\u679c \u7684 \u3068\u8003 \u3048 \u3089\u308c \u308b.\u3059 \u306a\u308f\u3061,\u8996 \u8005\u304c \u30c7\u30a3\u30b9\u30d7 \u30ec\u30a4\u306b\u8fd1 \u3065 \u304f\u3068,\u88ab \u5199\u4f53 \u304c\u5927 \u304d\u304f\u306a \u308b\u306e\u3068\u540c\u6642 \u306b,\u8996 \u91ce\u304c\u5e83\u304c \u308b\u3068\u3044\u3046\u52b9\u679c\u3084,\u8996 \u8005 \u304c \u30c7 \u30a3\u30b9 \u30d7 \u30ec\u30a4 \u306b\u8fd1 \u3065\u3044\u305f\u3068 \u304d,\u8fd1 \u304f\u306e\u88ab\u5199\u4f53 \u306f\u8fd1 \u3065\u3044\u3066\u307f\u3048 \u308b\u304c,\u9060 \u666f \u306f\u307b \u3068\u3093 \u3069\u8fd1\u3065 \u304b\u306a\u3044 \u3068\u3044 \u3046\u52b9\u679c \u304c\u5f97 \u3089\u308c\u308b.\u3053 \u306e\u6a5f\u80fd \u3092\u5b9f\u73fe \u3059 \u308b\u305f\u3081\u306b\u306f,\u30ab \u30e1 \u30e9\u306e\u79fb\u52d5 \u3060\u3051\u3067 \u306a \u304f,\u30ba \u30fc \u30df\u30f3\u30b0 \u304c\u5fc5\u8981 \u3068\u306a \u308b.\u4ee5 \u4e0b\u306b\u30ab\u30e1 \u30e9\u306e\u5236\u5fa1 \u306e\u6982\u8981 \u3092\u793a \u3059. \u4e21 \u30ab\u30e1 \u30e9\u306e\u5149 \u8ef8\u306e\u4ea4\u70b9 \u304c\u70b9F\u306b \u306a \u308b\u3088 \u3046\u306b\u4fdd\u3061\u306a\u304c \u3089,\u4e21 \u30ab\u30e1 \u30e9\u306e \u30ec\u30f3\u30ba\u7cfb \u306e\u4e2d\u5fc3\u3092,\u8996 \u8005 \u306e\u524d\u5f8c\u5de6\u53f3 \u306e \u52d5 \u304d\u306b\u5408\u305b \u3066,\u6c34 \u5e73 \u306a\u5e73\u9762 \u5185\u3092\u524d\u5f8c\u5de6\u53f3 \u306b\u79fb\u52d5 \u3055\u305b \u308b (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000882_article-file_1157957-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000882_article-file_1157957-Figure7-1.png", + "caption": "Fig. 7. Boundary conditions for the analysis with loading by moment", + "texts": [ + " For the lower side of the weld yoke where the welding operation is performed, as shown in Fig. 6, the constraint has been defined in a way that does not allow rotation and translation in all axes by using rigid elements. Elasticity modulus of 210 GPa and Poisson\u2019s ratio of 0.3 have been used as input data for the material of weld yoke. Boundary conditions for the analysis with loading by mo- ment: Rigid elements have been created on each yoke branches. And so the moment acting on the weld yoke is distributed equally as shown in Fig. 7. The torque of 4,600 is defined in the middle node of the rigid structure. At the same time, constraint which gives freedom of rotation and translation in the axis of rotation, has been applied on the node of rigid structure. For the lower side of the weld yoke where the welding operation is preformed, as shown in Fig. 7, the constraint has been defined in a way that does not allow rotation and translation in all axes by using rigid elements. Elasticity modulus of 210 GPa and Poisson\u2019s ratio of 0.3 have been used as input data for the material of weld yoke. After the defining load and constraints, the solution process has been implemented by linear static structural method. In solution process OptiStruct has been used as solver. Von Mises stress value on the critical area (Fig. 3 and Fig. 4) which is taken into consideration for the theoretical calculations, has been obtained as 241 MPa for the loading type of force couple, while 240 MPa has been obtained for the loading type of moment as shown Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003263_8600701_08685150.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003263_8600701_08685150.pdf-Figure7-1.png", + "caption": "FIGURE 7. The BWR\u2019 structure.", + "texts": [ + " In addition, this table contains other published results of the same problem using different optimization methods, including the multiplier method [22] and the HS algorithm [23]. By comparison with the data in the Table 2, it is interesting to note that the maximum of the deviation is less than 1%. V. STRUCTURE OPTIMIZATION OF THE BWR BOOM A. STRUCTURAL COMPONENTS OF THE BWR The BWR is a major complex equipment widely used in construction, mining, etc. due to its advantages, such as operation VOLUME 7, 2019 47765 simplicity and high efficiency. As illustrated in Fig. 7, the BWR consists of three major components, including the upper body, the lower body and the attachment. As the basis of entire BWR, the lower body provides a stable base for the machine and includes the proper drive and crawler system. The upper body serves as a platform for the machinery and it is a core part of the BWR to realize the valid operations, such as the digging, the lifting, and the revolving. The attachment is the implementing agencies of the BWR, including boom, bucket-wheel and guy rope" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.1-1.png", + "caption": "Figure 2.1 : Dissociated components of an electric motor [34].", + "texts": [ + " When such problems occur at these levels, there will be no significant impact of optimizing other heat transfer modes (such as convection) on the thermal behavior of electric machines. Changing the materials, their ratios in heterogeneous elements, or even their dimensions would make a difference. However, any change in these characteristics will influence the loads of the machine and can affect its electrical performance. A trade-off decision is required between thermal and electromagnetic constraints. The structure of the electrical machine consists of different parts as presented in Figure 2.1. In this configuration, the main machine components are the following: windings (made of coils), stator laminations, rotor laminations, motor housing (or frame), and eventually the magnets (in electrical machines with permanent magnets) Each component will be described and studied from a thermal point of view. It will help to understand the element composition and structure and will allow figuring out the modeling of the conduction heat transfer in the motor. 2.2.1.1 Windings The windings are formed with metallic coils covered by electrical insulation material(s), which can be generally a coat of insulator around the coil, traditionally a varnish, and lately, other constituents are added such as epoxy resin for impregnation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000171_pdf_64FFEE170012.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000171_pdf_64FFEE170012.pdf-Figure2-1.png", + "caption": "Figure 2. Technical drawing of a triangular prism hopper. Source: Author", + "texts": [ + "01 m 3 per fill meaning that the machine had to be filled 28 times to achieve the design machine capacity. The length (l) and breadth (b) of the hopper were set at 420 and 130 mm respectively. The height of the triangular prism was calculated to be 200 mm from Equation 1. v = 1 2 \u00d7l\u00d7b\u00d7h (1) Where v = volume (m3); l = length (m); b= breadth (m) and h= height (m). The hopper was welded on top of the shelling shaft housing. The technical drawing of the hoper and the semi-circular cylinder are shown in Figure 2. The total shelling power is combination of the required power for cracking kernels (Ps) and the power needed to drive the shelling shaft (PD). Required power for cracking kernels (PS) The average force required for cracking Bambara groundnut pods and nuts at 6% moisture content was 32 \u00b112 and 73.74 \u00b1 16.3 N, respectively based on experiments. The power calculations were based on the physical properties of Bambara groundnuts at 6% moisture content. The assumption made was that the shelling shaft had a diameter of 25 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure11-1.png", + "caption": "Figure 11. Field analysis of the designed AFPM motor by Vector Field Opera 14.0 software [36]. (a) 3D auto-mesh generation. (b) Fluxdensity plot.", + "texts": [ + " The best motor design dimensions are selected based on the proposed candidates from all the methods (genetic algorithm, finite element analysis, and finite volume analysis simulation). However, the final optimized design is made possible with minor changes effectuated by the powerful FEA and FVA, with the strenuous task of changing permanent-magnet thickness, air-gap length, and length of stator yoke and rotor yoke several times. Fig. 10 shows the exploded view of the designed motor which is an inside-out double-rotor single-stator axialflux permanent-magnet motor. Table 7 lists the machine design\u2019s final dimensions and specifications. Figure 11 shows finite element field analysis of the designed 15- stator-slot per pole pair AFPM motor. Fig. 11(a) shows one eighth of the entire motor, the part which is used to model the FEA-designed AFPM motor\u2019s structure: 90\u25e6 of the half motor structure and 1 pole, fulfilling symmetry conditions. It is the portion of the meshed model, a three-dimensional auto-mesh comprising tetrahedral elements with 6 nodes fitting circular layers starting from the shaft to the outer diameter of the AFPM motor, along with entire winding configuration. It is to be noted that the adopted fractional winding (q = 5/4; slot/(pole \u00d7 phase)) necessitate to consider the full periphery (four poles/side), in order to complete the space period. So, the entire winding is used to model the machine. The entire machine comprises 2\u00d7 15 = 30 stator slots and 2 polepairs. Fig. 11(b) shows the magnetic flux density distribution over different AFPM motor parts. The flux density obtained from FEA is somewhat less than theoretically calculated through GA based sizing equation due to neglected core magnetic reluctance. In fact, the flux density of different core parts decreases when the magneto-motive force (MMF) drops in real conditions. Magnetic flux density evaluation for various sections of the designed AFPM machine is essential to detect saturation of either the core or the teeth, which decreases machine efficiency and thus affects operation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004430_.srce.hr_file_311135-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004430_.srce.hr_file_311135-Figure7-1.png", + "caption": "Figure 7 AFPMM model ( a-starting model with 100mm fictitious air gap, b-meshed model with 55 mm fictitious air gap)", + "texts": [ + " The equation for magnetic flux density in the air gap takes its final form: ( ) r d s d r PM 0,5 1 BB d + 2d + h \u00b5 = (18) where Br is permanent magnetic flux density in the air gap, hPM the permanent magnet thickness and \u00b5r the relative recoil permeability of the PMs. Fig. 4 - Fig. 6 and Eq. (18) show that the fictitious air gap has a significant influence on the magnetic flux density. Thicker air gap means smaller magnetic flux density in axial direction. AFPMM model is constructed using Ansys Maxwell 3D software and the data from Tab. 1. Fig. 7a shows the starting model of the study, which consists of two 7 mm thick rotor disks with 10 PMs mounted on each one. Between them, there is a 100 mm air gap with 5 mm layers. Each air gap layer represents a new FEA simulation of air gap flux density (i.e., Fig. 7b shows the meshed model with 55 mm fictitious air gap), which is analyzed on a line that runs through both rotor disks, all the air gaps and 2 PMs. The line is drawn through the centre of the PMs on the average radius, as shown in Fig. 8. FEA simulations are performed for the thickness of fictitious air gap from 5 mm to 100 mm with 5mm steps, which in total represents 20 simulations. The result of each simulation is the axial component of the magnetic flux density on the centerline (Fig. 8) between opposite PMs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003188_d2719ed4543447a7_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003188_d2719ed4543447a7_pdf-Figure2-1.png", + "caption": "Figure 2. Test sled schematic (left) and actual test sled with front suspension subsystem installed (right).", + "texts": [], + "surrounding_texts": [ + "Figure 1 shows a quarter car impact model, where mb is the mass of the body, mw is the mass of the wheel assembly, ks and bs are the stiffness and damping coefficients of the suspension, kt and bt are the stiffness and damping coefficients of the tire, zw is wheel displacement, zb is the body displacement, and h0 is the initial drop height for impact. This height is used to calculate the velocity at impact, vi, which combined with zb and zw represent the initial conditions of the model. \ud835\udc63\ud835\udc56 = \u221a2\ud835\udc54\u210e0 (1) The equations of motion for the model of Figure 1 are: \ud835\udc5a\ud835\udc4f?\u0308?\ud835\udc4f = \ud835\udc58\ud835\udc60(\ud835\udc67\ud835\udc64 \u2212 \ud835\udc67\ud835\udc4f) + \ud835\udc4f\ud835\udc60(?\u0307?\ud835\udc64 \u2212 ?\u0307?\ud835\udc4f) \u2212 \ud835\udc5a\ud835\udc4f\ud835\udc54 (2) \ud835\udc5a\ud835\udc64?\u0308?\ud835\udc64 = \u2212\ud835\udc58\ud835\udc60(\ud835\udc67\ud835\udc64 \u2212 \ud835\udc67\ud835\udc4f) \u2212 \ud835\udc4f\ud835\udc60(?\u0307?\ud835\udc64 \u2212 ?\u0307?\ud835\udc4f) + \ud835\udc58\ud835\udc61\ud835\udc67\ud835\udc64 + \ud835\udc4f\ud835\udc61?\u0307?\ud835\udc64 \u2212 \ud835\udc5a\ud835\udc64\ud835\udc54 (3) From these equations the state space matrices of the model can be solved numerically in MATLAB\u2019s ode23s solver." + ] + }, + { + "image_filename": "designv8_17_0000065_m.C.2010.4.62-67.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000065_m.C.2010.4.62-67.pdf-Figure1-1.png", + "caption": "Fig. 1 Three-dimensional model of TATRA 815 S1 lorry undercarriage and subsidiary ladder frame", + "texts": [], + "surrounding_texts": [ + "The process of fatigue damage (fatigue life) prediction is generally very complicated and contains a lot of uncertain inputs, e.g. material characteristics, randomness of the service loading etc. Our paper aim is to present the selected results of the computer simulation analysis of fatigue damage lorry frames. This simulation concentrates to: the most important aspects which are typical for means of transport working conditions, use of the obtained computational models for a working exciting simulation of a virtual lorry construction, dynamic analysis of the vehicle critical parts stress under the influence of typical working conditions, the fatigue life prediction of the analyzed vehicle most exposed parts. During the computational simulation of the chosen vehicle (TATRA 815 S1) under the modeled conditions of its service, it was necessary to consider that it is a kind of vehicle whose traffic conditions are determined mainly by the influence of the following aspects: roadways and terrain surface undulation, traffic velocity." + ] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure21-1.png", + "caption": "Figure 21. Aluminum specimen between both clamps (left) aluminum specimen with a transverse strain gage, axial strain gage & extensometer (center) tensile specimen", + "texts": [ + " In this case, an Aluminum specimen was tensile tested with a strain gage orientated in the axial direction, and another strain gage orientated in the transverse direction. Since the axial strain gage, the extensometer and the crosshead were measuring axial strain, their readings were compared. In the past theses, students were using the crosshead displacement to measure the modulus of elasticity. Using the crosshead displacement was very unreliable and it is explained in more detail in the next sub section. 49 5.1.1 Extensometer vs. Axial Strain Gage vs. Crosshead Displacement The test set-up of the Aluminum specimen is shown in Figure 21. The three principle directions and the clamped sections of a standard uniaxial tensile specimen are shown in Figure 21. Below in Table 1, an Aluminum sample was loaded and unloaded three times up to a tensile stress of 25 ksi. The tensile stress was calculated using Equation (9). A tensile stress of 25 ksi lies in the material\u2019s linear elastic region and it is far away from materials yield stress of 35 ksi. Table 1 shows the comparison of experimental results between the extensometer, strain gage and crosshead. Table 1 also shows the dimensions of the Aluminum specimen. The strain gage and extensometer experimental results were validated with the Aluminum 2024-T4 datasheet mechanical properties [25]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000274___lang_en_format_pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000274___lang_en_format_pdf-Figure5-1.png", + "caption": "Figure 5. Effective strain distribution in the workpiece after the forming step.", + "texts": [ + " Tests were performed considering five (05) repetitions for each sample, and the mean and standard deviation values were calculated. Prior to the beginning of tests, the open circuit potential (OCP) was determined, characterized by a potential variation of less than 5 mV. The stabilization period was defined as 3600 s. After stabilizing the potential, the polarization test was started, with a scanning range from -1.0 to +0.2 V at a speed of 5 mV/s. Strain distributions along the part at the end of the forming step are shown in Figure 5. It is possible to observe that, in general, deformation levels are relatively low, in the order of 7%, which corresponds to the bluish color of the image. This is natural to occur, since the part has mostly \u201cU\u201d bending strains, which usually result in low deformation values. However, certain regions exhibited considerably higher strain concentration, reaching levels around 45% (yellow color). In these regions, the forming behavior becomes of the deep drawing type, which explains these concentrations" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003536_830_81_15-00138__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003536_830_81_15-00138__pdf-Figure5-1.png", + "caption": "Fig. 5 Explanation for calculating torque. The total load of the rolling element is obtained from the load distribution of the rolling element. When the total load of the rolling element is multiplied by both the pitch radius of bearing Dp/2 and the traction coefficient 0.1, the torque that rotates the output shaft rotate is obtained.", + "texts": [], + "surrounding_texts": [ + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n\u6700\u5927\u8ee2\u52d5\u4f53\u8377\u91cdQmax\u3092\u8a08\u7b97\u3059\u308b\u969b\u306b\uff0cJr(\u03b5)\u306e\u5024\u304c\u5fc5\u8981\u3068\u306a\u308b\u305f\u3081\uff0c\u56f3 4\u306b\u793a\u3059\u3088\u3046\u306a\u30d5\u30ed\u30fc\u30c1\u30e3\u30fc\u30c8\u3067 \u03b5\u3068 Jr(\u03b5)\n\u3092\u6c42\u3081\u305f\uff0e\n 2\n2 pD QT \uff0811\uff09\nNO\nInitial data l, Pd ,Fr ,Z\nCalculation of stiffness\nKn, Kl1, Kl2\nAssumption of load distribution\nfactor \u03b5(old)\nCalculation of radial integral Jr(\u03b5)\nCalculation of max. radial shift \u03bbmax\nCalculation of load distribution\nfactor \u03b5'(new)\n\u03b5=\u03b5'\nDecision radial integral Jr(\u03b5)\nYES\nl\uff1aEffective contact length Pd\uff1aDiametral clearance Fr\uff1aRadial load Z\uff1aNumber of rolling elements Kn\uff1aCombined load \u2013deflection factor Kl1, Kl2\uff1aLoad-deflection factor \u03b5\uff1aLoad distribution factor \u03bbmax\uff1aMax. radial shift Jr(\u03b5)\uff1aRadial integral\n\u5404\u8ee2\u52d5\u4f53\u306b\u304b\u304b\u308b\u8377\u91cd Q(\u03c8)\u304b\u3089\u8ee2\u52d5\u4f53\u5168\u3066\u306e\u7dcf\u8ee2\u52d5\u4f53\u8377\u91cd\uff08\u6b6f\u8eca\u53cd\u529b Fr \u3092\u542b\u3080\u8ee2\u52d5\u4f53\u8377\u91cd\u306e\u5408\u8a08\u5024\uff09\u03a3Q(\u03c8) \u3092\u6c42\u3081\u308b\uff0e\u6c42\u3081\u305f\u7dcf\u8ee2\u52d5\u4f53\u8377\u91cd\u03a3Q(\u03c8)\u3092\u7528\u3044\u3066\uff0c\u5f0f(11)\u304b\u3089\u4fdd\u6301\u5668\u3068\u4e00\u4f53\u5316\u3057\u305f\u51fa\u529b\u8ef8\u3092\u56de\u8ee2\u3055\u305b\u308b\u305f\u3081\u306e\u30c8\u30eb \u30af T \u3092\u6c42\u3081\u308b\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u5f0f\u4e2d\u306e \u03bc\u306f\u4e00\u822c\u7684\u306a\u30c8\u30e9\u30af\u30b7\u30e7\u30f3\u4fc2\u6570 0.1 \u3092\u7528\u3044\u305f\uff0eDp\u306f\u8ef8\u53d7\u30d4\u30c3\u30c1\u5186\u5f84\u3067\uff0c\u8ef8\u53d7 \u5185\u5f84\u3068\u8ef8\u53d7\u5916\u5f84\u306e\u5e73\u5747\u5024\u3067\u6c42\u3081\u305f\uff0e\u56f3 5 \u306b\u305d\u306e\u95a2\u4fc2\u3092\u793a\u3059\uff0e", + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n4. \u4e88\u5727\u30ea\u30f3\u30b0\u306e\u8a2d\u8a08\n4\u30fb1 \u4e88\u5727\u91cf\u306e\u8a2d\u5b9a 3 \u7ae0\u3067\u8ef8\u53d7\u306b\u3042\u308b\u4efb\u610f\u306e\u534a\u5f84\u65b9\u5411\u8377\u91cd Fr\u3068\u713c\u5d4c\u3081\u306b\u3088\u308b\u6cd5\u7dda\u529b\u304c\u4f5c\u7528\u3057\u305f\u5834\u5408\u306b\uff0c\u51fa\u529b\u8ef8\u3067\u4f1d\u9054\u53ef\u80fd\u306a\u30c8\u30eb\u30af \u306e\u89e3\u6790\u6cd5\u3092\u793a\u3057\u305f\uff0e\u3053\u3053\u3067\u306f\uff0c\u4e88\u5727\u306b\u76f8\u5f53\u3059\u308b\u76f4\u5f84\u3059\u304d\u307e Pd\u3092\u30d1\u30e9\u30e1\u30fc\u30bf\u306b\u3057\u3066\u4f1d\u9054\u53ef\u80fd\u30c8\u30eb\u30af\u306e\u63a8\u5b9a\uff0c\u3055\u3089\u306b \u306f Hertz\u306e\u5f3e\u6027\u63a5\u89e6\u7406\u8ad6\u3088\u308a\u8ee2\u52d5\u4f53\u3068\u5185\u8f2a\u9593\u306e\u6700\u5927\u63a5\u89e6\u5fdc\u529b Pmax\u3082\u8a08\u7b97\u3057\u305f(Johnson, 2003)\uff0e\n\u672c\u5b9f\u9a13\u3067\u306f\u4f7f\u7528\u3059\u308b\u30c8\u30eb\u30af\u30e1\u30fc\u30bf\u306e\u8a31\u5bb9\u5024\u304b\u3089\u4f1d\u9054\u30c8\u30eb\u30af\u306e\u76ee\u6a19\u5024\u3092 20[N\u30fbm]\u3068\u3057\u3066\u3044\u308b\u306e\u3067\uff0c\u76ee\u6a19\u306e\u4f1d\u9054\u30c8 \u30eb\u30af\u307e\u3067\u904b\u8ee2\u304c\u3067\u304d\u308b\u3088\u3046\u306b\u76f4\u5f84\u3059\u304d\u307e Pd\u3092\u6c7a\u5b9a\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\u56f3 6\u306b 3\u7ae0\u3067\u793a\u3057\u305f\u8a08\u7b97\u65b9\u6cd5\u3067\u306e\u4f1d\u9054\u53ef\u80fd\u30c8 \u30eb\u30af\u3068\u6700\u5927\u63a5\u89e6\u5fdc\u529b Pmax\u306e\u8a08\u7b97\u7d50\u679c\u3092\u793a\u3059\uff0e\u307e\u305f\uff0c\u672c\u5b9f\u9a13\u3067\u4f7f\u7528\u3057\u305f\u8ef8\u53d7\u8af8\u5143\u3092\u8868 2\u306b\u793a\u3059\uff0e\nFig. 6 Calculation results of NU306E. The calculation result\nof both the output torque and the maximum contact stress between the rolling element and the inner ring when a change in the diametral clearance occurs is indicated. Output torque becomes large when the negative clearance is small, but the contact stress becomes large.\nBearing number NU306E\nInner diameter [mm] 30\nInner race diameter [mm] 40.5\nOuter diameter [mm] 72\nOuter race diameter [mm] 62.5\nBearing width [mm] 19\nNumber of rolling elements 8\nRolling element diameter[mm] 11\nRolling element length[mm] 12\nTable 2 Bearing selecting dimensions\n\u4e0a\u8a18\u306e\u56f3 6 \u3088\u308a\u4f1d\u9054\u30c8\u30eb\u30af\u306e\u76ee\u6a19\u5024 20[N\u30fbm]\u3092\u6e80\u305f\u3059\u305f\u3081\u306b\u306f\u76f4\u5f84\u3059\u304d\u307e Pd=-0.0077[mm] (\u8ca0\u3059\u304d\u307e\u3068\u306a\u308b\u305f \u3081\u4ee5\u5f8c\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u3068\u8a18\u3059)\u4ee5\u4e0b\u306b\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\u3053\u3053\u3067\u306f\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u88fd\u4f5c\u6642\u306e\u52a0\u5de5\u7cbe\u5ea6\u3092\u8003\u616e\u3057\u3066\u6709\u52b9\u7de0 \u3081\u4ee3 \u0394=-0.008[mm]\u3068\u306a\u308b\u3088\u3046\u306b\u8a2d\u8a08\u53ca\u3073\u52a0\u5de5\u3092\u884c\u3063\u3066\u3044\u304f\uff0e\u307e\u305f\uff0c\u6709\u52b9\u7de0\u3081\u4ee3 \u0394=-0.008[mm]\u306e\u3068\u304d\u306e\u8ee2\u52d5\u4f53\u3068 \u5185\u8f2a\u9593\u306e\u6700\u5927\u63a5\u89e6\u5fdc\u529b Pmax\u306f 0.772[GPa]\u3068\u306a\u308b\uff0e", + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n4\u30fb2 \u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5916\u5f84\u306e\u8a2d\u8a08 \u76ee\u6a19\u30c8\u30eb\u30af 20[N\u30fbm]\u3092\u4f1d\u9054\u3059\u308b\u305f\u3081\u306e\u30c8\u30e9\u30af\u30b7\u30e7\u30f3\u529b\u3092\u5f97\u308b\u305f\u3081\u306b\uff0c\u5916\u8f2a\u713c\u5d4c\u3081\u306b\u3088\u308a\u8ef8\u53d7\u5185\u90e8\u306b\u4e88\u5727\u3092\u52a0\u3048 \u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\u5916\u8f2a\u713c\u5d4c\u3081\u3092\u884c\u3046\u305f\u3081\u306b\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u5185\u5916\u5f84\u3092\u8a2d\u8a08\u3057\u3066\uff0cNSK \u30c6\u30af\u30cb\u30ab\u30eb\u30ec\u30dd\u30fc\u30c8(\u65e5\u672c\u7cbe\u5de5\u682a \u5f0f\u4f1a\u793e\uff0c2013)\u3088\u308a\u8ef8\u53d7\u5185\u90e8\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u3092\u8a2d\u8a08\u3057\u305f\uff0e\u307e\u305f\uff0c\u713c\u5d4c\u3081\u306e\u969b\u306b\u8ef8\u53d7\u5916\u8f2a\u306b\u767a\u751f\u3059\u308b\u5186\u5468\u65b9\u5411\u5fdc\u529b\u306b \u3064\u3044\u3066\u3082\u8a08\u7b97\u3057\u305f\uff0e\n\u713c\u5d4c\u3081\u3092\u884c\u3046\u969b\uff0c\u307e\u305a\u4e88\u5727\u30ea\u30f3\u30b0\u3068\u8ef8\u53d7\u5916\u8f2a\u9593\u306e\u898b\u304b\u3051\u306e\u7de0\u3081\u4ee3 \u0394Da\u304b\u3089\u5b9f\u969b\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394Deff\u3092\u6c42\u3081\u308b\u5fc5 \u8981\u304c\u3042\u308b\uff0e\u305d\u306e\u969b\uff0c\u63a5\u89e6\u9762\u306e\u8868\u9762\u7c97\u3055\u306e\u72b6\u614b\u3068\u6b6f\u8eca\u53cd\u529b\u306b\u3088\u308b\u30e9\u30b8\u30a2\u30eb\u8377\u91cd\u306b\u3088\u3063\u3066\uff0c\u898b\u304b\u3051\u306e\u7de0\u3081\u4ee3\u3088\u308a\u5b9f\u969b \u306e\u6709\u52b9\u7de0\u3081\u4ee3\u306f\u6e1b\u5c11\u3059\u308b\uff0e\u8868\u9762\u7c97\u3055\u306b\u3088\u308b\u6e1b\u5c11\u91cf\u3092\u5f0f(12)\u3068(13)\u3088\u308a\uff0c\u30e9\u30b8\u30a2\u30eb\u8377\u91cd\u306b\u3088\u308b\u6e1b\u5c11\u91cf\u3092\u5f0f(14)\u3088\u308a\uff0c \u5b9f\u969b\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394Deff\u3092\u5f0f(15)\u3088\u308a\u8a08\u7b97\u3092\u884c\u3063\u305f\uff0e\u3053\u3053\u3067 d\u306f\u8ef8\u53d7\u5185\u8f2a\u5185\u5f84\uff0cD\u306f\u8ef8\u53d7\u5916\u8f2a\u5916\u5f84\uff0cB\u306f\u8ef8\u53d7\u5e45\uff0c Di \u306f\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84\uff0cFr \u306f\u30e9\u30b8\u30a2\u30eb\u8377\u91cd\u3067\u3042\u308a\uff0cd=30.0[mm]\uff0cD=72.0[mm]\uff0cB=19.0[mm]\uff0cFr=213[N]\u3067\u3042\u308b\uff0e\u307e \u305f\uff0c\u56f3 7\u306b\u305d\u306e\u5b9a\u7fa9\u3092\u793a\u3059\uff0e\na 3 D D\nD D \n \uff0812\uff09\nia DDD \uff0813\uff09\n3 rF 1008.0 F\nB\nd D \uff0814\uff09\nFeff DDD \uff0815\uff09\n\u4e88\u5727\u30ea\u30f3\u30b0\u3068\u8ef8\u53d7\u5916\u8f2a\u9593\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394Deff\u304b\u3089\uff0c\u8ef8\u53d7\u5185\u5916\u8f2a\u3068\u8ee2\u52d5\u4f53\u9593\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394 \u306e\u8a08\u7b97\u3092\u884c\u3063\u305f\uff0e\u305d \u306e\u969b\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u306e\u713c\u5d4c\u3081\u306b\u3088\u308b\u8ef8\u53d7\u5916\u8f2a\u8ecc\u9053\u5f84\u306e\u53ce\u7e2e\u91cf \u03b4f\u3092\u5f0f(16)\u3088\u308a\uff0c\u904b\u8ee2\u6642\u306e\u8ef8\u53d7\u5185\u5916\u8f2a\u306e\u6e29\u5ea6\u5dee\u306b\u3088\u308b \u8ef8\u53d7\u5185\u90e8\u3059\u304d\u307e\u306e\u6e1b\u5c11\u91cf \u03b4t\u3092\u5f0f(17)\u3088\u308a\u8a08\u7b97\u3057\uff0c\u305d\u3053\u304b\u3089\u8ef8\u53d7\u5185\u5916\u8f2a\u3068\u8ee2\u52d5\u4f53\u9593\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\u3092\u5f0f(18)\u3088\u308a\u8a08\u7b97 \u3092\u3057\u305f\uff0e\u3053\u3053\u3067De\u306f\u8ef8\u53d7\u5916\u8f2a\u8ecc\u9053\u5f84\uff0ch\u306f\u8ef8\u53d7\u5916\u8f2a\u8ecc\u9053\u5f84 De\u3068\u8ef8\u53d7\u5916\u8f2a\u5916\u5f84D\u306e\u6bd4\uff0cho\u306f\u8ef8\u53d7\u5916\u8f2a\u5916\u5f84D\u3068\u4e88 \u5727\u30ea\u30f3\u30b0\u5916\u5f84 Do\u306e\u6bd4\uff0c\u03b1 \u306f\u8ef8\u53d7\u92fc\u306e\u7dda\u81a8\u5f35\u4fc2\u6570\uff0c\u0394t \u306f\u904b\u8ee2\u6642\u306e\u8ef8\u53d7\u5185\u5916\u8f2a\u306e\u6e29\u5ea6\u5dee\uff0c\u03940\u306f\u8ef8\u53d7\u306e\u5143\u3005\u306e\u8ef8\u53d7\u5185 \u90e8\u3059\u304d\u307e\u3067\u3042\u308a\uff0c\u305d\u308c\u305e\u308cDe=62.5[mm]\uff0ch=De/D\uff0cho=D/Do\uff0c\u0394o=0.03175[mm]\uff0c\u03b1=12.5\u00d710-6 [1/\u2103](\u65e5\u672c\u7cbe\u5de5\u682a\u5f0f \u4f1a\u793e\uff0c2013)\u3067\u3042\u308a\uff0c\u0394t=5[\u2103]\u3068\u4eee\u5b9a\u3057\u3066\u8a08\u7b97\u3057\u305f\uff0e\u307e\u305f\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u5185\u5f84 Di\u3068\u4e88\u5727\u30ea\u30f3\u30b0\u5916\u5f84 Do\u3092\u5909\u5316\u3055\u305b\u308b \u3053\u3068\u3067\uff0c\u8ef8\u53d7\u5185\u90e8\u306e\u6709\u52b9\u7de0\u3081\u4ee3 \u0394\uff08\u4e88\u5727\u91cf\uff09\u306e\u8a2d\u8a08\u3092\u884c\u3046\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\n2 o 2\n2 o\nefff 1\n1\nhh\nh hD\n\n \uff0816\uff09\net tD \uff0817\uff09\n tf0 \uff0818\uff09\n\u5916\u8f2a\u713c\u5d4c\u3081\u306b\u3088\u3063\u3066\u8ef8\u53d7\u5916\u8f2a\u306b\u306f\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03b6t max\u304c\u767a\u751f\u3059\u308b\uff0e\u8ef8\u53d7\u306e\u7cbe\u5ea6\u3084\u5f37\u5ea6\u306e\u95a2\u4fc2\u304b\u3089\u8ef8\u53d7\u5916\u8f2a\u306b\u52a0\u308f \u308b\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03b6t max\u306f\u7d04 127[MPa]\u4ee5\u4e0b\u306b\u6291\u3048\u308b\u306e\u304c\u597d\u307e\u3057\u3044\u3068\u3055\u308c\u3066\u3044\u308b (\u65e5\u672c\u7cbe\u5de5\u682a\u5f0f\u4f1a\u793e\uff0c2013)\uff0e\u305d\u3053\u3067 \u672c\u7814\u7a76\u3067\u306e\u5916\u8f2a\u713c\u5d4c\u3081\u306b\u3088\u3063\u3066\u8ef8\u53d7\u5916\u8f2a\u306b\u767a\u751f\u3059\u308b\u5186\u5468\u65b9\u5411\u5fdc\u529b \u03b6t max\u3092\u4ee5\u4e0b\u306e\u5f0f(19)\u3068(20)\u3088\u308a\u8a08\u7b97\u3057\u305f(\u65e5\u672c\u7cbe \u5de5\u682a\u5f0f\u4f1a\u793e\uff0c2013)\uff0e\u3053\u3053\u3067\uff0cEe\u3068 Eh\u306f\u8ef8\u53d7\u92fc\u3068\u30af\u30ed\u30e0\u30e2\u30ea\u30d6\u30c7\u30f3\u92fc\uff08\u4e88\u5727\u30ea\u30f3\u30b0\uff09\u306e\u7e26\u5f3e\u6027\u4fc2\u6570\uff0cme\u3068 mh\u306f\u8ef8 \u53d7\u92fc\u3068\u30af\u30ed\u30e0\u30e2\u30ea\u30d6\u30c7\u30f3\u92fc\u306e\u30dd\u30a2\u30bd\u30f3\u6570\u3067\uff0c\u305d\u308c\u305e\u308c Ee=Eh=208000[MPa]\uff0cme=mh=3.33 \u3092\u7528\u3044\u305f\uff0e" + ] + }, + { + "image_filename": "designv8_17_0001948_al-01287745_document-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001948_al-01287745_document-Figure2-1.png", + "caption": "Figure 2. Geometry composition of the footbridge : (a) module, (b) beam assembly, (c) initial deflection, (d) final structure with deck", + "texts": [ + " This problem can be carried out in an exploratory manner in three parts: establishing a set of different configurations with varying geometry and material, designing the selfstress level and the appropriate cross-sections characteristics for each one and evaluating its structural performances, and finally, looking for the optimum solution. We demonstrate this methodology on the case of a footbridge composed of two tensegrity beams generated by replication of 4 bars tensegrity modules. Each beam is deployable in a short time and stiffened by transverse cables added in the upper layer in order to block mechanisms and then limit vertical deflection (Averseng & Dub\u00e9, 2012). A simply supported rigid deck joints the two beams. Curvature is induced by mapping the system on a horizontal axis cylindrical surface (Figure 2). The whole structure is modelled as a space reticulate system in which the deck is represented by a series of transverses bars. So as to avoid torsion in the supporting beams, they are jointed at their ends to a specific reticulate sub-system that distribute the vertical forces to the four lower nodes of each module. The specifications of this footbridge summarize in two parameters: the width and the span, fixed respectively in this study to 2 m and 12 m. The others fixed data are related to the deck, considered as a series of rigid plates (estimated distributed mass of 30 kg/m2), and to the variable load, taken equal to 3 kN/m2", + " The three parameters \ud835\udc40, \ud835\udc36 and \ud835\udc3e represent respectively the mass, the damping factor, and the stiffness of the structure. In this model, actuators are materialized by an 31\u00e8mes Rencontres de l\u2019AUGC, E.N.S. Cachan, 29 au 31 mai 2013 4 3. Etude du comportement dynamique de la structure Nous avons \u00e9tudi\u00e9 deux types de comportements : le comportement passif (sans usage des v\u00e9rins ) et le comportement actif. 3.1. Le comportement passif Pour caract\u00e9riser la r\u00e9ponse passive de la structure, on r\u00e9alise un essai de type balayage sinus \u00e0 l\u2019aide d\u2019un pot vibrant (Fig. 2) situ\u00e9 en un point d\u00e9cal\u00e9 par rapport \u00e0 l\u2019axe longitudinal de la structure afin d\u2019en exciter les modes de flexion et torsion. Les signaux mesur\u00e9s sont la force introduite par le pot en entr\u00e9e et l\u2019acc\u00e9l\u00e9ration verticale en nappe sup\u00e9rieure de la structure. Le comportement est ensuite d\u00e9termin\u00e9 sous la forme de la fonction de transfert acc\u00e9l\u00e9ration sur force (Fig. 3a). Sur ce graphe, on voit apparaitre les pics de r\u00e9sonnance des modes de torsion (13,4 Hz) et de flexion (17,4 Hz). L\u2019objectif du contr\u00f4le actif sera de les attenuer" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001257_v.org_pdf_2404.09765-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001257_v.org_pdf_2404.09765-Figure2-1.png", + "caption": "Fig. 2: Trailblazer\u2019s sensor suite (a) and calibration data collection procedure (b).", + "texts": [ + " However, for most construction-related applications that leverage handheld systems or robots, consistently high-accuracy positioning across various conditions is the key driver of better quality control and human-equivalent task performance for robots in realworld conditions, emphasizing the need for TLS-based GT. In comparison to our previous SLAM Challenge [2] in which we recorded the datasets exclusively with our hand-held device called Phasma1 (Figure 1b), this year\u2019s dataset features additionally recorded trajectories with our robot prototype called Trailblazer (Figure 2), a 700 kg construction robot. In contrast to Phasma, the datasets recorded with Trailblazer include robot-specific behaviors such as strong vibrations when turning, mostly constrained motion to a plane and large extrinsics between sensors. Since we chose to maintain the same hardware and calibration routines for the Phasma prototype as the Hilti SLAM Challenge 2022 [2], this section focuses primarily on the hardware setup of Trailblazer. 1https://github.com/Hilti-Research/hilti-slam-challenge-2023/blob/main/documentation/hardware/Handheld" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure10-1.png", + "caption": "Fig. 10 The Accurate model of two types of transmission pair.", + "texts": [ + " In addition, the change in the relatively entrainment velocity of the e-side is similar to the lubrication angle and under certain parameters, it may also increase and then decrease along the same contact line. According to the parameters outlined in Table 1, a 3D model of spiroid gear and was created in UG software to match the specified parameters. In order to verify the accuracy of the performance analysis of the three types of meshing in Chapter 3, a 3D model of a face worm gear drive that has the parameter values equivalent to those shown in Table 1 and a taper angle \u03b4 of 0\u00b0 was established as a comparison, as shown in the Fig. 10: To reduce the computational load for simulation, these two 3D models were simplified, keeping only the meshed portion of the Spiroid gear. In the calculation module of ANSYS 19.2 Workbench, the static structural analysis was selected after entering a new project, and both models were imported separately. In the engineering data section, material properties were assigned based on the data in Table 2. size of the mesing surfaces to 0.5mm, resulting in a total of 442,000 meshes. The mesh model is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002029_d.aspx_paperID_79349-Figure24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002029_d.aspx_paperID_79349-Figure24-1.png", + "caption": "Figure 24. Patch antenna with CSRR (Top side).", + "texts": [ + "53011 147 Open Journal of Antennas and Propagation The patch configuration as defined in Section 3 has been used for the CSRR loading effect over its resonance frequency. Here the patch element has dimension of 13.9 mm \u00d7 18 mm \u00d7 0.017 mm with its inset feed of 13.05 mm \u00d7 2.8 mm \u00d7 0.017 mm and inset gap of 0.5 mm. This patch element has been laid over 30 mm \u00d7 30 mm \u00d7 1.57 mm Fr4 substrate with its relative permittivity 4.4 and tangent loss of 0.02 while the ground layer has been designed using copper conductor with its dimension of 30 mm \u00d7 30 mm \u00d7 0.017 mm. Figure 12 shows the patch configuration without CSRR loading while Figure 24 (Top view) and Figure 25 (Bottom view) show the same size patch configuration with CSRR loading. The CSRR loading as shown in Figure 26 provides resonance frequency shift where the original patch resonates at 5 GHz while the periodic CSRR array loaded patch resonates at 3.7 GHz. DOI: 10.4236/ojapr.2017.53011 148 Open Journal of Antennas and Propagation Table 6 shows the comparison of antenna parameters when patch is not loaded with CSRR and when patch is loaded with CSRR. The parameter for the bend configuration of these elements has also been shown here" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003036_cmtmte2018_04028.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003036_cmtmte2018_04028.pdf-Figure2-1.png", + "caption": "Fig. 2. Vibrator prototype dynamic model.", + "texts": [ + " In the following, such input parameters of the model as the shaft rotation frequency and eccentric weights are selected based on the initial data. Creation and operation of a vibration system model is based on main dynamics laws and system vibration theory. First, when mechanism shaft loads are known, plain bearings that meet operation requirements and conditions are selected. Then a 3D device model is built using NX 11 CAD graphic editor (Fig. 1). A 3D model is used to determine the vibrator prototype mass-center data. After that a dynamic model is developed in Euler 10.11 Pro software based on the available data (Fig. 2). When the required input parameters and mass-center characteristics have been introduced in the dynamic model, it is possible, by changing free parameters, to obtain set speeds, accelerations and other parameters of the device parts. An example in Fig. 3 shows the relationship between the driving shaft angular speed and operation time of different eccentric weights. After selection of optimal characteristics of the device under design, based on the results obtained from the dynamic model, for example, housing acceleration, spring force in Ansys R18 software system, we determine design peculiarities and operability of vibrator prototype parts" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004425_icle_download_104_97-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004425_icle_download_104_97-Figure5-1.png", + "caption": "Figure 5: (Left): Drawing of an Iwan model as a parallel arrangement of dry friction sliders (Brake, 2016), (Right): Drawing of a typical hysteresis curve for a four parameter Iwan model described by (Brake, 2016)", + "texts": [ + " This requires quality mesh, high computing power and is more time consuming. Discrete models proposed by Iwan (1966) are also used for modelling of jointed structures. This requires the discretization of parameters that takes longer than the analytical representation of Iwan model as presented by Brake (2016). A framework that has potential for providing that balance is due to Iwan (Segalman, 2005). One of his models, the most prominent, has been the parallel system of Jenkins elements, sometimes called the parallel series Iwan model as shown in Figure 5. Such a model consists of spring-slider units arranged in a parallel system. The four parameters defined by Iwan are as follows: FS: Force necessary to cause macro-slip KT: Joint stiffness under small applied load \u03f0: Dissipation parameter at every instant \u03b2: Dissipation parameter for the complete curve of Force vs. Dissipation As a starting point, the four parameter Iwan model developed in Brake (2016): \ud835\udc39\ud835\udc56\ud835\udc64\ud835\udc4e\ud835\udc5b = \u222b \ud835\udf0c (\u0424)(\ud835\udc62(\ud835\udc61) \u2212 \ud835\udc65(\ud835\udc66, \u0424))\ud835\udc51\u0424 (1) \ud835\udc62 \u2212 \ud835\udc65(\ud835\udc61, \u0424) = { \ud835\udc62, \ud835\udc62 < \u0424 (\ud835\udc56\ud835\udc53 \ud835\udc60\ud835\udc59\ud835\udc56\ud835\udc51\ud835\udc52\ud835\udc5f \u0424 \ud835\udc56\ud835\udc60 \ud835\udc60\ud835\udc61\ud835\udc62\ud835\udc50\ud835\udc58) \u0424, \ud835\udc62 \u2265 \u0424 (\ud835\udc56\ud835\udc53 \ud835\udc60\ud835\udc59\ud835\udc56\ud835\udc51\ud835\udc52\ud835\udc5f \u0424 \ud835\udc56\ud835\udc60 \ud835\udc60\ud835\udc59\ud835\udc56\ud835\udc51\ud835\udc56\ud835\udc5b\ud835\udc54) (2) The above equation describes a distribution \u03c1 (\u0424) of dry friction sliders (Jenkins elements) as shown in Figure 5. Note that in Segalman (2005), the global displacement U is used in place of the relative displacement u; in what follows, the relative displacement u is defined to be positive in the slip direction. The four parameter Iwan model of Segalman (2005) is subject to two Masing conditions which are both visible in Brake (2016). The forward and backward curves are reflective of one another and are scaled to fit between the initial loading point and the force for macro-slip. The displacement in the negative direction is the same as a displacement in the positive direction with the change in coordinates" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004706_el-04657928_document-Figure7.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004706_el-04657928_document-Figure7.3-1.png", + "caption": "Figure 7.3.1 Motion variables and control notations of a FW-VTOL UAV concept.", + "texts": [ + ", the position and size of the control surfaces), is further developed in Section 7.4. The control input vector \u03b4 \u2208 Rm in Equation 7.4 contains the effectors\u2019 inputs such as the propeller thrust settings \u03c4 \u2208 [0, 1] and the deflection angles [rad] of the elevators (\u03b7), ailerons (\u03c1), and rudders (\u03b6) [54]: \u03b4 = [\u03c11, \u00b7 \u00b7 \u00b7 , \u03c1i, \u03b71, \u00b7 \u00b7 \u00b7 , \u03b7j , \u03b61, \u00b7 \u00b7 \u00b7 , \u03b6k, \u03c41, \u00b7 \u00b7 \u00b7 , \u03c4l]T (7.5) The detailed scalar equations of motions, derived from the above equalities, can be found in 7.A. The motion variables and control notations introduced above are visually summarized in Figure 7.3.1, where \u03a6 = [\u03d5 \u03b8 \u03c8]T represents the Euler angles (i.e., roll, pitch and yaw). 7.3.2 Linearized state-space model The equations of motion are linearized using the small-disturbance theory applied to a reference flight condition. For example, the longitudinal speed becomes ub = ub0 + \u2206ub, 188 Controllability assessment and fault-tolerant sizing of UAVs where \u2206 represents a deviation from the referenced value. For simplicity, the flight condition of reference consists of a steady, straight and level flight, which implies: vb0 = wb0 = p0 = q0 = r0 = \u03d50 = \u03c80 = 0", + " Control along the y-axis of the UAV is primarily achieved through fixed surfaces such as the wing and horizontal stabilizer. Moreover, there exists a coupling between the y-axis and the other axes, enabling control of the UAV\u2019s vertical motion by acting on these other axes. Therefore, a four-dimensional virtual control vector is considered, denoted as u = [X L M N ]T . The effector control vector, represented as \u03b4 = [\u03c11 \u03c12 \u03b71 \u03b72 \u03b6 \u03c4p \u03c41 \u03c42 \u03c43 \u03c44]T , corresponds to the configuration illustrated in Figure 7.3.1. Note that for most fixed-wing UAVs, the number of elevators is reduced to one, since both sides are mechanically connected to a single actuator. However, for genericity, the case of two independent elevators is covered here. For consistency with the notations introduced in Section 7.3, the effector control vector \u03b4 replaces the rotor thrust vector notation f used in the ACAI computation presented in Section 7.4.1. 7.4 Controllability assessment 195 Drag forces are essential aerodynamic components that introduce cross-coupling effects between control axes in the control surfaces", + " Its design reflects 7.7 Case studies 203 the E-flite Ultra Stick 25e, whose dynamics model, linearized around cruise flight conditions without failures, is provided in [63]. Expressly, this model assumes that the longitudinal and lateral dynamics are decoupled. The second concept consists of a hybrid FW-VTOL UAV Figure 7.7.1 E-flite Ultra Stick 25e. Source: E-flite with similar design specifications, except four VTOL rotors have been added. This concept is representative of the UAV depicted in Figure 7.3.1. On the y-axis, the VTOL rotors are centered on the right and left wings. On the x-axis, they are positioned on either side of the aerodynamic center, with a distance equal to twice the chord of the rectangular wing. The thrust-to-weight ratios for the propulsion and the VTOL rotors are based on market trends. Furthermore, the total masses of both concepts are assumed to be equal. The additional mass introduced by the VTOL propulsion is assumed to be balanced by a lower battery capacity. The VTOL rotors are typically inactive in nominal cruise flight conditions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure21-1.png", + "caption": "Figure 21. 3D auto-mesh generation by GAMBIT software (GAMBIT).", + "texts": [ + " The appropriate boundary conditions are selected so that to simulate the actual heat transfer circumstances of the motor. It should be noted that in the motor design, in contrast with normal electrical machines, outer bearing is used. The mechanical advantages of this structure include improved balancing and cooling capability. It enables air to flow in through the center of rotor hollow and out through the air-gap. A structural multi block meshing is used for all of domains such as stationary and rotational. Fig. 21 illustrates three dimensional meshing of model in Gambit by using cubical elements for calculating the circulations in the passages of the motor [45]. GAMBIT is used only to auto generate the finite volume mesh and simulation is analyzed with ANSYS-FLUENT software. The whole domain has been split into smaller elementary volumes connected to each other by sharing a common face. The grid is made of 3 million hexahedral elements. The clearance between stator and rotor contains about 2.2 million elements in total" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002827_eira_Unprotected.pdf-Figure4.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002827_eira_Unprotected.pdf-Figure4.10-1.png", + "caption": "Figure 4.10 \u2013 Simplified equivalent circuit model without considering Rp.", + "texts": [ + " Making the simulation of these different load conditions with Gmsh/GetDP, the same behavior ensued, as shown in Figure 4.9. Observe that the \u201cPhase\u201d curves in Figure 4.9 have the same phase as the \u201cPhase\u201d curves in Figure 4.7. The difference is that Figure 4.9 shows the phases from 0o to 360o and Figure 4.7 shows the phase from - 180o to 180o. Knowing that -90o is the same as 270o, both figures present the same results in different scale. 4 \u2013 Sensitivity Analysis 107 This behavior is easily explained by the analytical formulation when considering the simplified model of Figure 4.10 with SRCs. From this model, \ud835\udc4d = ?\u0307?1 \ud835\udc3c1\u0307 = \ufffd\ud835\udc5f1 + \ud835\udc57.\ud835\udf14. \ud835\udc3f1 + 1 \ud835\udc57.\ud835\udf14.\ud835\udc361 \ufffd \u2212 \ud835\udc57.\ud835\udf14.\ud835\udc40. \ud835\udc3c2\u0307 \ud835\udc3c1\u0307 (4.5) Then, replacing \ud835\udc3c2\u0307, the equation of the impedance becomes: \ud835\udc4d = \ufffd\ud835\udc5f1 + \ud835\udc57. \ufffd\ud835\udf14. \ud835\udc3f1 \u2212 1 \ud835\udf14.\ud835\udc361 \ufffd\ufffd + \ud835\udf142.\ud835\udc402 \ud835\udc45\ud835\udc3f + \ud835\udc5f2 + \ud835\udc57. \ufffd\ud835\udf14. \ud835\udc3f2 \u2212 1 \ud835\udf14.\ud835\udc362 \ufffd (4.6) These formulas were applied considering: 108 4 \u2013 Sensitivity Analysis \u2022 the joule loss resistance obtained when the coil is magnetically and electrically uncoupled from any other coil; \u2022 the self and mutual inductances when the coil is 5 mm distant from the other coil (as done with the measurements and simulation); \u2022 the use of SRCs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure5-3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure5-3-1.png", + "caption": "Figure 5-3. Repr\u00e9sentation des rotations \u00e9l\u00e9mentaires", + "texts": [ + " Comparaison des diagrammes de rayonnement obtenus en simulation et par la mesure ......................................................................................................................................... 130 Figure 4-28. Photographie du commutateur RF 4 voies r\u00e9alis\u00e9.................................................. 131 Figure 5-1. Exemple d'orientations possibles pour un t\u00e9l\u00e9phone mobile ................................... 145 Figure 5-2. Repr\u00e9sentation des rep\u00e8res cart\u00e9sien et sph\u00e9rique consid\u00e9r\u00e9s ................................. 146 Figure 5-3. Repr\u00e9sentation des rotations \u00e9l\u00e9mentaires ............................................................... 148 Figure 5-4. Repr\u00e9sentation des rep\u00e8res avant et apr\u00e8s rotation .................................................. 149 Figure 5-5. Exemple de rotation du champ \u00e9lectrique total d'un dip\u00f4le, de r\u00e9-\u00e9chantillonnage et d'interpolation de celui-ci dans le rep\u00e8re initial .......................................................................... 150 Figure 5-6. Champs \u00e9lectriques d'un dip\u00f4le avant et apr\u00e8s rotation de 45\u00b0 selon l'axe x ", + " Celle-ci se d\u00e9compose en trois rotations \u00e9l\u00e9mentaires dans le rep\u00e8re cart\u00e9sien afin d'\u00eatre en mesure de consid\u00e9rer l'antenne orient\u00e9e dans n'importe quelle direction. Ainsi si un point P de coordonn\u00e9es ( ), ,p p px y z devient le point M de coordonn\u00e9es ( ), ,m m mx y z apr\u00e8s rotation. Alors ce nouveau point est obtenu par la transformation suivante : PRPRRRM xyz .... == (5.29) Avec \u2206\u2206 \u2206\u2212\u2206 = 100 0cossin 0sincos \u03c6\u03c6 \u03c6\u03c6 zR , \u2206\u2206\u2212 \u2206\u2206 = \u03b8\u03b8 \u03b8\u03b8 cos0sin 010 sin0cos yR et \u2206\u2206 \u2206\u2212\u2206= \u03c4\u03c4 \u03c4\u03c4 cossin0 sincos0 001 xR 148 Rz, Ry, Rx sont les matrices de transformation correspondantes aux rotations \u00e9l\u00e9mentaires d\u00e9crites sur la Figure 5-3. Bien que la rotation du champ \u00e9lectrique total se traduise par une simple rotation d\u00e9finie par la matrice R, ce n'est pas le cas pour les composantes du champ \u00e9lectrique ( ),E \u03b8 \u03b8 \u03c6 et ( ),E \u03c6 \u03b8 \u03c6 qui sont rattach\u00e9es aux vecteurs u\u03b8 et \u03c6u , respectivement. 5.2.4 Repolarisation des champs \u00e9lectriques On consid\u00e8re un champ en un point P d\u00e9fini par deux composantes complexes ( ),E \u03b8 \u03b8 \u03c6 et ( ),E \u03c6 \u03b8 \u03c6 se rapportant respectivement aux vecteurs u\u03b8 et \u03c6u . Si le point P subit une rotation et que l'on nomme P' le point P apr\u00e8s transformation, alors les vecteurs u\u03b8 et \u03c6u subissent \u00e9galement la m\u00eame rotation pour devenir les vecteurs 'u\u03b8 et 'u\u03c6 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004400_e_download_7768_6705-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004400_e_download_7768_6705-Figure14-1.png", + "caption": "Fig 14. Design parameters", + "texts": [ + " The influence of spar circular fitting (Fig 11), skin thickness (Fig 12), spar and web thickness together (Fig 13) and MFC chord-wise length (Fig 6) on torsion angle illustrated lower values. Due to large dimension of the numerical problem to be solved, non-direct optimisation technique should be applied, since the application of direct minimisation algorithms and multiple finite element analysis is too expensive from the computational point of view. For this reason an optimisation methodology is developed employing the method of experimental design and response surface technique. An optimisation problem for the optimum placement of actuators in the helicopter rotor blade (Fig 14) has been formulated on the results of parametric study and taking into account the producers requirements: Objective function: \u03c6 = \u03c6(x). Design parameters:{x} = {l, tskin, tspar, L}, 16 \u2264 l \u2264 24 mm, 0.25 \u2264 tskin \u2264 1.25 mm, 0.50 \u2264 tspar \u2264 2.50 mm, 16 \u2264 L \u2264 100 mm. Constraints: 22\u2264 ycg \u226430, 10\u2264 ycg \u226425, 10\u2264 ycg \u226425, m\u2264 1.35, fT1\u226559.15, where l \u2013 spar circular fitting (mm), tskin \u2013 skin thickness (mm), tspar \u2013 spar thickness and web thickness together (mm), L \u2013 MFC chord-wise length (mm). The length of web is 56 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000882_article-file_1157957-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000882_article-file_1157957-Figure1-1.png", + "caption": "Fig. 1. Powertrain of a motor vehicle.", + "texts": [ + "------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- In a motor vehicle, powertrain covers every component that converts the power from engine into the movement, such as transmission, driveshaft, differential and wheels as seen in Fig. 1. Driveshaft, one of these components of powertrain, is the most important component in motor vehicles, for transmitting torque and rotation. It is used as an intermediate element that provides connection between other components of the drivetrain such as transmission and differential. In this way, it allows for relative movement between them [1]. Driveshaft basically comprises of one or more universal joints, yoke parts, splined parts and center support bearing depending on what the driving and driven components are used" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure75-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure75-1.png", + "caption": "FIGURE 75. AAV model [44].", + "texts": [ + " As the fourth step, the purity of mode excitation is evaluated by calculating the far-field radiation power of each mode, as shown in Fig. 74. G. PLATFORM In this section, advanced systematic procedures for designing platform-integrated antenna systems using the CMs 98856 VOLUME 9, 2021 is presented. The platforms include the likes of naval ships and amphibious assault vehicles and are described as follows. The study in [44] employed CM theory to adapt the metallic platform as the main radiator. Low-profile coupling elements are mounted on different locations of the amphibious assault vehicle (AAV) platform shown in Fig. 75 to excite two orthogonal, horizontally polarized CMs. The systematic design steps of a dual-polarized, platform-based HF antenna system are characterized experimentally. It is intended for Vertical Incidence Skywave (NVIS) applications operating from 3 to 10 MHz. To develop dual-polarized antennas for this application, horizontally polarized modes should be excited on the platform to create strong radiation towards the zenith. The CMs of this platform were analyzed in different environments (corresponding to dry and wet earth as well as the seawater)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000938_.2478_mspe-2020-0039-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000938_.2478_mspe-2020-0039-Figure4-1.png", + "caption": "Fig. 4 Construction of Terra-Max ground rocket 1 \u2013 head of punch, 2 \u2013 piston (ram), 3 \u2013 elastic shock absorber, 4 \u2013 conical housing, 5 \u2013 control sleeve", + "texts": [ + " In the case of uncontrolled, pushing-out ground thickening methods ramming and ground pushing devices, called ground rockets, are used very often. In Poland these devices have a common name \u201cmole\u201d [1, 10]. The first ground rocket was designed in England in 1916. This device consisted of a metal cylinder with a sharpened front. Rams, controlled with compressed air, were installed inside the cylinder. In Fig. 3 a diagram of this ground rocket of Terra-Hammer type, made by Terra Company [19], is presented and in Fig. 4 a solution, developed by the Terra Max Company [17], is shown. Source: [17]. Source: [16]. The schematic diagram of this method, consisting in an implementation of an in-coming installation with the dynamic head is presented in Fig. 5. Source: [10]. It is one of the simplest excavationless methods and it is based on an introduction into the ground of the installation 3 (usually flexible) directly behind the dynamic head, [1, 10]. In the head of a cigar shape there is a ram put into reciprocating motion, which hits the head, relocating it in the ground" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000706_O201332479507885.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000706_O201332479507885.pdf-Figure3-1.png", + "caption": "Fig. 3\uc740 \ubca8\ud2b8 \uc0e4\ud504\ud2b8 \uc9c0\uc9c0\ub300\uc774\ub2e4. \ubca8\ud2b8\ub97c 35\ub3c4 \uc815\ub3c4 \uacbd\uc0ac\uc9c0\uac8c \ub450\uc5b4\uc11c \uc120\ubcc4\ub9dd\uc744 \ud1b5\uacfc\ud55c \ubd80\uc0b0\ubb3c\uacfc \ucf69\uc744 \uc120\ubcc4\ud560 \uc218 \uc788\uac8c \ud558\uc600\ub2e4.", + "texts": [ + " \uc77c\ubcf8 \uc81c\uc870\uc5c5\uccb4 \uc580\ub9c8\uc0ac[3]\uc758 \ud0c8\uace1\uae30\ub294 \ub3c5\ub9bd\uad6c\ub3d9\ubc29\uc2dd\uc73c \ub85c \uace0\uc815\uc2dd\ubcf4\ub2e4\ub294 \uc791\uc5c5 \uc131\ub2a5\uc774\ub098 \ud6a8\uc728 \uba74\uc5d0\uc11c \uc6d4\ub4f1\ud558\uace0, \uc774\ub3d9\ud558\uba74\uc11c \ud0c8\uace1\uc744 \ud558\ubbc0\ub85c \uc791\uc5c5\uc774 \ud3b8\ub9ac\ud558\uace0, \uad6d\ub0b4 \uc81c\ud488\uc5d0 \ube44\ud574 \uba3c\uc9c0\uac00 \ub9ce\uc774 \uc77c\uc5b4\ub098\uc9c0 \uc54a\ub294 \uc6b0\uc218\uc131\uc774 \uc788\uc73c\ub098 \ud310\ub9e4 \uac00\uaca9\uc774 \ub192\ub2e4\ub294 \ub2e8\uc810\uc774 \uc788\ub2e4[3,4]. \uad6d\ub0b4 \uc81c\ud488\ub4e4\uc740 \uae30\uacc4 \uc8fc\ubcc0\uc5d0 \uba3c\uc9c0\uac00 \ub9ce\uc774 \ub098\uace0, \uc791\uc5c5\uc790 \uac00 \ub9c8\uc2a4\ud06c\ub97c \ud544\ud788 \uc368\uc57c \ud558\ub294 \uc0c1\ud669\uc774\ub2e4. \uc131\ub2a5 \uc2dc\ud5d8\uc2dc \uba3c\uc9c0 \ub3c4 \uad6d\ub0b4\uc0b0\uc774 \uba87 \ubc30\ub098 \ub354 \ub9ce\uc774 \ub098\uc624\ub294 \uc2e4\uc815\uc774\ub2e4. 2.2 3\ucc28\uc6d0 \ubd80\ud488 \uc124\uacc4 \ubc0f \uc81c\uc791 \uc544\ub798 \uadf8\ub9bc\ub4e4\uacfc \uac19\uc774 3\ucc28\uc6d0 \uc124\uacc4 \uc18c\ud504\ud2b8\uc6e8\uc5b4 (Pro-Engineer)[5]\ub97c \uc774\uc6a9\ud558\uc5ec \ud0c8\uace1\uae30\uc758 \ubd80\ud488\ub4e4\uc744 \uc124\uacc4\ud558 \uace0 \uc870\ub9bd\ud558\uc600\ub2e4. [Fig. 1] Drum to do the threshing Fig. 1\uacfc \uac19\uc774 \ud0c8\uace1\ud1b5\uc758 \ub0a0\uc744 \ub098\uc120\ud615\uc73c\ub85c \ubc30\uce58\ud558\uc5ec \uc55e \uba74\uc5d0\uc11c \ucf69\uc744 \ud22c\uc785\ud558\uba74 \ub098\uc120\ud615\uc744 \ub530\ub77c \uc774\ub3d9\ud558\uba74\uc11c \ud0c8\uace1\uc744 \ud560 \uc218 \uc788\uac8c \uc124\uacc4\ud558\uc600\ub2e4. \uae30\uc874 \uc81c\ud488\uc758 \ud22c\uc785\uad6c\ub294 \ud0c8\uace1\ud1b5\uc758 \ub0a0\uacfc \ubc14\ub85c \uc811\ud574 \uc788\uc5b4 \uc11c \uc791\uc5c5\uc790\uc758 \uc190\uc774 \ub4e4\uc5b4\uac08 \uc704\ud5d8\uc774 \uc788\ub2e4. \uc774\ub97c \ud574\uacb0\ud558\uae30 \uc704 \ud574 \ud22c\uc785\uad6c\uc5d0 Fig. 2\uc640 \uac19\uc774 \ub0a0\uce74\ub86d\uc9c0 \uc54a\uc740 \ubc14\uc774\ud2b8\ub97c \ub450\uc5b4 \uc11c \uc800\uc18d\uc73c\ub85c \ud68c\uc804\uc744 \uc2dc\ucf1c \ucf69\ub300\ub97c \ubb3c\uace0 \ud0c8\uace1\ud1b5 \uc548\uc73c\ub85c \ub4e4 \uc5b4\uac00\uac8c \uc124\uacc4\ud558\uc5ec \uc791\uc5c5\uc790\uc758 \uc548\uc804\uc744 \ub3c4\ubaa8\ud558\uc600\ub2e4. [Fig. 3] Support of the belt shaft \uc815\uc120\ub41c \ucf69\uc744 \ubc30\ucd9c\uc2dc\ud0a4\uae30 \uc704\ud574 \ubc30\ucd9c \ud32c\uc744 \ud0c8\uace1\uae30\uc758 \ub4a4 \ucabd\uc5d0 \ubc30\uce58\ud558\uc600\ub2e4. Fig. 5\uc640 \uac19\uc774 \ubc30\ucd9c \ud32c\uc758 \uac00\uc6b4\ub370 \ubd80\ubd84\uc5d0 \ub294 \uacf5\uae30\ub97c \ud761\uc785\ud560 \uc218 \uc788\ub3c4\ub85d \uc548\ucabd\uc73c\ub85c \uacbd\uc0ac\ub97c \uc8fc\uc5b4 \ud32c \ub0a0 \uc744 \uc81c\uc791\ud558\uc600\ub2e4. [Fig. 5] Exhaust fan \uc815\uc120\ub41c \ucf69\uc744 \ubc30\ucd9c\uc2dc\ud0a4\uae30 \uc704\ud574 \ubc30\ucd9c\uad6c\ub97c \ub4a4\ucabd\uc5d0 \ubc30\uce58\ud558 \uc600\ub2e4. \ubc30\ucd9c\uad6c \ub05d \ubd80\ubd84\uc744 \uc791\uc5c5\uc790 \uc55e\uc73c\ub85c \uc720\ub3c4\ud558\uc5ec \uc544\ub798\uc5d0 \ub294 \ud3ec\uc7a5\uc744 \ud560 \uc218 \uc788\uac8c \uc790\ub8e8 \ubc1b\uce68\ub300\ub97c \ub450\uc5c8\ub2e4. [Fig. 6] Outlet of a soybean \ud648\uc5d0 \uc815\uc120\ub41c \ucf69\uc774 \ub5a8\uc5b4\uc9c0\uba74 \uc774\uc1a1\uc2a4\ud06c\ub958(Fig. 7)\ub97c \ud0c0\uace0 \ubc30\ucd9c\uad6c\ub85c \ubcf4\ub0b4\uc9c4\ub2e4. \uc774 \ub54c \uc774\uc1a1\ub418\ub294 \ucf69\uc758 \uc591(\uccb4\uc801\uc720\ub3d9\ub7c9) \uc740 \uc2a4\ud06c\ub958\uc758 \ub2e8\uba74\uc801\uacfc \ud68c\uc804\uc18d\ub3c4\uc5d0 \ube44\ub840\ud55c\ub2e4[6]. \uc18d\ub3c4 \uc2a4\ud06c\ub958\uc758\ub2e8\uba74\uc801 [Fig. 7] Outlet of a soybean \uada4\ub3c4\ucc28\ub7c9\uc704\uc5d0 \uc7a5\ucc29\ud558\uae30 \uc804 \ucf69 \ud0c8\uace1\uae30\uc758 \uc870\ub9bd\uacfc\uc815\uc744 \ubcf4 \uc5ec\uc900\ub2e4. [Fig. 14] Assembling the threshing machine \uace0\ubb34\uc7ac\uc9c8\uc758 \ubb34\ud55c\uada4\ub3c4 \uc7a5\ucc29\ud55c \uc644\uc131\ub41c \ucf69 \ud0c8\uace1\uae30\uc758 \ubaa8\uc2b5 \uc774\ub2e4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000765_1740-021-01063-1.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000765_1740-021-01063-1.pdf-Figure1-1.png", + "caption": "Fig. 1 TPRR machine with one supporting roll removed: schematic a and photo b", + "texts": [ + " The implementation of a process control system in the actual rolling machine requires a modification of the machine control system. Moreover, the realization of such tests on a machine in real conditions presents a certain number of challenges (risk of damaging the tools or the machine, etc.). Therefore, first investigations are done as virtual experiments on a digital twin. After successful testing the following methods could be transferred onto an real machine. The machine used in this paper is a retrofitted 1986 \u201cUPWS 31,5.2\u201d from VEB Werkzeugmaschinenfabrik Bad D\u00fcben, today Profiroll Technologies GmbH. Figure\u00a01 presents the different parts of the TPRR machine. The mandrel is supported by two fixed supporting rolls and can rotate freely around its axis. The roll, rotating at a constant speed, is driven against the ring at a given speed (roll speed). The round rolls stabilize the ring rotation. Finally, compressed air can be sprayed on the ring to cool it down. During the process, the ring grows incrementally and the eventual profiles of the tools are impressed on the ring. In this paper, in an effort to reduce the problem complexity, the tools are not profiled, which lead to more homogeneous fields of deformation and temperature" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure3-21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure3-21-1.png", + "caption": "Figure 3-21: Trajectory in joint configuration space from [ -0 .5 ,- 1 .0 ,-1 .0 ] to [0.5,1.0,1.0].", + "texts": [], + "surrounding_texts": [ + "77", + "3 .6 . S u m m ary\nIn this chapter, a dynamic equation of motion was modeled via the Newton-\nEuler and the Lagrange-Euler form uations utilizing the recursion of the kinematic\nvariables from chapter 2. The structural properties and the physical interpretations of the coefficient term s in a dynam ic model were presented.\nThe motion effects and relative significance of the dynamic term s were analyzed\nby comparing m inimum time m otion to straight line motion. From the illustrated results of the three cases and various simulations, a general dynamic behavior of\na m anipulator subject to a m inimum tim e motion can be described from the role of each term . The Coriolis and centrifugal effects play an im portan t role in increasing dynamic performance as well as the direct inertia term . Gravity and direct inertia effects have an intim ate relation to each other. T ha t is, a minimum tim e motion tends to decrease the m agnitude of the direct inertia coefficient which results in a relative increase in acceleration. From the view point of the m anipulator configuration, all links are likely to contract toward the center of the motion and the base joint usually has the largest effect on the contraction. The contraction tends to reduce the gravity effect on each joint. W hen these trends are carried out, the Coriolis and centrifugal effects become large. Each link of a m anipulator tends to move to utilize the Coriolis and centrifugal effects to cause the required nominal joint torque to be in bound. Usually, a dynamically efficient motion is m ade by" + ] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure2.31-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure2.31-1.png", + "caption": "Figure 2.31: Horizontally polarized \u03bb/2 on-skin dipole with the human body model", + "texts": [ + " In contrast, the Zenneck TM modes possess a positive reactance value (inductance feature). It can be noted that the \u201cTM Zenneck Skin/Fat\u201d mode (figure 2.30(b)) exhibits very high surface impedance values in terms of resistance (500 - 700 \u2126). However, this mode is more confined inside the human body and therefore has less impact on the on-body antennas. tion In order to analyze the possibility of the skin-confined propagation mode excitation, a horizontally polarized \u03bb/2 dipole antenna is simulated at 5 GHz with the multilayered human body model in CST (figure 2.31). The thicknesses of the air, skin, fat, muscle layers in the simulation are 30 mm, 1 mm, 13 mm, and 16 mm respectively. The dipole is located on the skin and is in direct contact with the skin. In order to increase the contact area of the dipole with the skin surface, the cross section of the dipole was chosen to be square form rather than cylindrical. As the dipole is horizontally polarized, this is similar to some extent to the galvanic coupling mechanism excitation mentioned in section 1.10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000156_ownload_109198_pdf_6-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000156_ownload_109198_pdf_6-Figure1-1.png", + "caption": "Fig. 1. Scheme of cold forging process with enclosed dies (a) and formed part (b), 1 \u2013 punch, 2 \u2013 billet, 3 \u2013 lower die, 4 \u2013 mandrel, 5 \u2013 formed part", + "texts": [ + " In this paper, to create precision parts in cold forging process, enclosed dies have been used. Based on the finite element simulations, forming characteristics such as deformation patterns (gridlines distortion), distributions of effective strain and stress at several stages of process with different forming parameters and also to predict and avoid folding defect in cold forging process have been investigated by using this theoretical simulation method. The die scheme, die geometries, billet dimensions and the formed part for cold forging process with enclosed dies are shown in Fig. 1. A cylindrical billet is considered. The die geometry parameters, billet dimensions and power mode parameters are as follows: R0 \u2013 the radius of billet (R0= 20mm), R1= 15mm, R2= 27.5mm, R3= 31mm, L0 \u2013 the billet height (L0= 30mm), L1= 8mm, L2= 15mm, L3= 7mm, L4= 2.5mm, L5= 5mm, L6= 15mm, L7= 6mm, L8= 26mm, r \u2013 the punch, lower die and mandrel tip radiuses (r=1mm), V \u2013 punch velocity (V=1mm/s), P \u2013 punch load, The friction factors between the billet and tools are constant (Zibel's law, \u03bc=0.08). In this study, the material used for the simulation is AA 6060 aluminum alloy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004511_cle_download_981_416-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004511_cle_download_981_416-Figure4-1.png", + "caption": "Figure 4: Set up boundary condition for model in ANSYS", + "texts": [], + "surrounding_texts": [ + "Similarly, clearance is also existed in a practical spherical joint which is difference between a radius of ball and radius of socket. The model of a spherical clearance joint as outlined in Figure 3 is used to connect between crank and connecting rod, between the connecting rod and the slider." + ] + }, + { + "image_filename": "designv8_17_0003768_tation-pdf-url_12705-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003768_tation-pdf-url_12705-Figure12-1.png", + "caption": "Fig. 12. Transversal section of the bended frame (dimensions are in mm)", + "texts": [ + " In any case, to simulate these typologies of phenomena explicit FE algorithms can be certainly considered the most suitable, for what concerns both the computational efficiency and the solution accuracy; on the other side, implicit FE algorithms can be considered in the most of applications more effective in the spring-back phase. www.intechopen.com Simulating the Response of Structures to Impulse Loadings 295 The experimental test-case regards a process of stretch-bending of a single frame (3000 mm length) of aluminium alloy 7076, whose transversal section is represented in figure 12; during the process the ends of the frame are clamped and a tensile force, corresponding to the yield force or somewhat higher, is applied to the specimen. Then the frame is bended by fitting it around a die (3300 mm radius) with the mandrel fixed and the arms of the machine rotating. Stretch bending of the frame has been developed after it has been subjected to a quenching treatment. In order to evaluate residual stresses after the stretch bending, experimental hole-drilling measurements have been performed in opportune locations on the frame, as showed in figure 13, where also the test apparatus is illustrated" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004336_s-3941981_latest.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004336_s-3941981_latest.pdf-Figure8-1.png", + "caption": "Fig. 8: Layout of a 12-pole 36-slot PMSM. The geometry is color-coded to identify different materials and properties of subdomains. Red and blue indicate North and South magnets, gray represents the motor core, and pink, yellow, and green represent the 3-phase windings.", + "texts": [ + " First, we present verification results and quantify any existing errors in the proposed method. Next, we 2 https://github.com/LSDOlab/modopt Geometric Design of Electric Motors Using Adjoint-based Shape Optimization 15 conduct a grid independence study to determine reasonable mesh sizing for the geometry. Finally, we demonstrate design optimization results for a motor within an electric aircraft system. All results are generated for a 12-pole, 36-slot radial flux permanent magnet synchronous motor; an example of the geometry is shown in Fig 8. 4.1 Model Validation The FEniCSx electromagnetic solver is verified using the Ansys Maxwell software(Ansys, Accessed 03/20/2021). We begin with a qualitative comparison of the output magnetic flux density fields, shown in Fig 9. The two cases considered here are the no-load (no current) case and the 280A current amplitude case. We see qualitative similarities in the no-load flux density field distributions between the FEniCSx solver in Figure 9a and Ansys Maxwell in Figure 9b. The flux field dissipates in a similar fashion around the boundaries and between stator teeth, and the flux density concentration around the magnets indicates that the modeling approach using Eq 8 for the magnets is accurate" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure9-1.png", + "caption": "Figure 9. (a) Stator winding equivalent model; and (b) inner rotor winding equivalent model.", + "texts": [ + " In the inner rotor windings, the parameters are listed as follows: d1 = 0.3 mm, d2 = 0.7 mm, d3 = 0.4 mm, \u03bb1 = 0.15 W/m\u00b7K, \u03bb2 = 0.0242 W/m\u00b7K, \u03bb3 = 0.35 W/m\u00b7K. Therefore, the thickness of the equivalent insulation is 1.4 mm and its equivalent thermal conductivity is 0.044 W/m\u00b7K for the inner rotor windings. Although the above equivalent method is a method to analyze the radial heat transfer effect, the extrusion 3-D model of the above equivalent model can also analyze the axial heat transfer effect. The 3-D models of the stator and inner rotor windings are shown in Figure 9. To build an accurate model of the end windings is more difficult than the winding model in the slot. This is mainly because the shape of each end winding isn\u2019t exactly the same and is also difficult to ascertain for the distributed-conductor machine. Therefore, this paper presents a simplified model of the end windings, as shown in Figure 10. Each end winding is equivalent to the two linear-structure windings. The axial length sum of the two linear-structure windings equals the length of one end winding" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003827_f_version_1527132471-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003827_f_version_1527132471-Figure2-1.png", + "caption": "Figure 2. Experimental setup: (a) actuator connected to the microcontroller and pneumatic tubes; and (b) actuator applying force against the linear drive for the force and impedance control tests.", + "texts": [ + " Sample cylinders where submerged in a water bath to capture any fragments in the event of failure and cyclically charged and discharged from 0\u2013150 psig (1034 kN/m2) for a period of 10 s for 20 cycles. No part failed or deformed plastically, but a significant increase in interlayer pore leakage was observed as wall thickness was decreased, with the leakage rate for the 0.089-cm wall thickness cylinder approaching 0.056 cubic meters per minute for a 5 cm-long test cylinder. None of the pressure-tested samples possessed post-treated bores. The experimental setup used is shown in Figure 2. The apparatus consisted of four main components: (1) sensors; (2) a pneumatic proportional flow valve; (3) a micro-controller; and (4) a commercially produced lead screw drive. 2.2.1. Sensors The actuator had non-contact position sensors to measure the piston travel. The actuator also had 2 pressure sensors in the actuator chambers that were calibrated to measure the force. The position of the piston was obtained by using Hall effect sensors that measured the magnetic intensity of the neodymium magnet in the piston head", + "4 ms with the Arduino Mega 2560 to 0.2 ms with the Teensy 3.6. The Teensy 3.6 was capable of handling all functions including piston position computation, controller implementation, external positioning (lead-screw) drive and data collection (via serial to an attached desktop computer). 2.2.4. Lead-Screw Linear Drive A lead-screw-driven linear drive (Konmison SFU1605) was utilized to position the piston of the pneumatic cylinder during the force control and impedance control testing phases (see Figure 2b). It was also used to establish a positional base line during calibration of the Hall effect sensor array. Control of the SFU1605 was performed by the Teensy 3.6 through the use of the AccelStepper program library [15]. Figure 5 shows a block diagram of the control system. At the heart of the control system was the micro-controller. The micro-controller sends a voltage signal to the proportional flow valve driver (PFV) (D1 valve driver from Enfield Technologies). The PFV driver controlled the compressed air from the pneumatic supply system through a valve (LS-V15s, proportional pneumatic valve Enfield Technologies)", + " Furthermore, reductions in this delay can be realized by reducing the radial compression of the piston sealing mechanism in order to reduce the required minimum pressure to overcome piston friction, but care must be taken, or leakage will occur past the piston seal. Figure 7 shows results for force control using the pneumatic actuator. The force control test was performed with a regulated 40 psig (275.79 kN/m2) supply pressure. The linear drive was placed in series with the pneumatic actuator such that the linear drive could exert a force on the piston of the pneumatic actuator as shown in Figure 2b. The objective was to maintain a constant compressive force of 44.48 N while moving the linear actuator at a constant speed back and forth as shown in Figure 7a. An external linear drive coupled to the piston of the 3D-printed actuator imposes a constant speed on the device. The constant speed test is done to demonstrate that the 3D-printed actuator is able to maintain constant force throughout its travel distance. The force control was achieved using feedback from the force measured from the pressure sensors" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004358_ation-damage-div.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004358_ation-damage-div.pdf-Figure1-1.png", + "caption": "Figure 1. Schematic of component", + "texts": [ + "isa A. Deibler and Donald F. Susan Sandia National Laboratories, Albuquerque, USA Components with surfaces which must be able to slide freely after a period of use were subjected to vibration testing. After vibration testing, some units locked up and were unable to slide. The component consists of two interlocking pins which ride in a housing, as illustrated in Figure 1. During normal operation, the upper pin is pulled up out of the housing where it is free to disconnect from the lower pin. In the post-vibration locked up condition, the upper pin cannot be pulled out of the sleeve. Several units of varying ages were inspected and it was found that all units which had been subjected to any level of vibration testing showed some amount of wear damage, regardless of whether they locked up after testing. Samples which were not subjected to vibration showed no evidence of similar damage", + " The pin surface was lubricated with molybdenum-disulfide. The use of the same alloy on mating surfaces was an immediate area of concern for galling and wear damage. To determine the cause of the lock-up, housings were cut open to remove the pins and surfaces were visually inspected for signs of damage caused by vibration. Figure 2 shows an example of the type of extensive damage visible in a typical housing. A matching pattern of surface wear damage was also observed on the pins. The areas outlined in yellow, red, and purple in Figure 1 were areas of concern for wear damage. The area outlined in yellow near the tip of each pin where they interlock was found to have the most severe damage. SEM inspection of the wear scars on both the housing and the pins showed the presence of oxide particles, which are indicative of fretting [1]. During fretting, which is often seen on parts subject to vibration, the passive layer on the stainless steel breaks down. This breakdown leads to oxidation and the much harder oxide particles accelerate the wear" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001549_tation-pdf-url_35276-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001549_tation-pdf-url_35276-Figure4-1.png", + "caption": "Fig. 4. Coordinate relationship between the rack cutter and the generated gear", + "texts": [ + " (15), the unit normal vector of region 3 can be obtained as follows (Chang & Tsay, 1998): )cos( )sin( 3 3 3 yc xc c n n n (18) The equations for the right side of the cutter are similar to those of left\u2019s, provided that parameters are calculated according to corresponding pressure angle, and all equations corresponding to cX coordinate are assigned an appropriate sign. To derive the mathematical model for the complete tooth profile of involute spur gears with asymmetric teeth, coordinate systems ),,( nnnn ZYXS , ),,( 1111 ZYXS and ),,( hhhh ZYXS should be set up. The coordinate systems nS , 1S and hS are attached to the rack cutter, involute gear, and gear housing, respectively as shown in Fig. 4. 1Z , nZ and hZ are determined by the right-hand co-ordinate system. During the generation process, the rack cutter translates a distance 11 prS while the gear blank rotates rotates by an angle 1 . The mathematical model of the generated gear tooth surface is a combination of the meshing equation and the locus of the rack cutter surfaces according to gearing theory (Litvin, 1994). Applying the following homogeneous coordinate transformation matrix equation makes it possible to obtain the locus of the cutter represented in coordinate system 1S as follows: www" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000771_1081-023-09833-9.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000771_1081-023-09833-9.pdf-Figure7-1.png", + "caption": "Fig. 7 Design variables related to the straight-topology of the spokes", + "texts": [ + " Stiffness and safety (buckling) constraints are included in the optimization, as well as manufacturing constraints. Design variables describe the main geometric features of the wheel. Wheels with 3, 5 and 7 spokes layout are considered in the optimization. Five distinct spoke topologies are investigated, namely: straight-shape (Fig. 6a), Y-shape (Fig. 6b), X-shape (Fig. 6c), asymmetric Y-shape (Fig. 6d) and double straight-shape (Fig. 6e), each one described by a dedicated set of parameters. As regards the straight spokes, the only design variable is the spoke rotation angle (angle \u03b1 in Fig. 7), namely the angle between the spoke and an axis passing through the hub center and the spoke root (see Fig. 7). Concerning the spokes with Y-topology, two additional angles \u03b2 and \u03b3 determine the location of the spoke-rim connection points and the position of the bifurcation point (see Fig. 8). Likewise, for the X-topology, the angles \u03b2 and \u03b3 define the position of the connection points with the hub and the rim respectively (see Fig. 9). The asymmetric Y spoke has a structure divided into two parts. The main part is parameterized as a straight spoke while the two additional design variables k and \u03b4 determine the location of the bifurcation point and the orientation of the secondary member, as depicted in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002518__cdbme-2018-0012_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002518__cdbme-2018-0012_pdf-Figure1-1.png", + "caption": "Figure 1: Structure of the blood pump", + "texts": [ + " Although the pressurized-air actuating mechanism is simple, it may cause problems due to an uncontrolled air blood contact and the low actuating dynamics of the membrane. The research presented in this paper is based on a novel pump-oxygenator in which a much simpler but very effective pulsatile pump mechanism is integrated in an oxygenator. For actuating the pump mechanism, we propose a fluid coupling system by which the pump can be fully actuated in both, pressure and suction mode. The blood pump in the pump-oxygenator system is based on the displacement pump concept, which was firstly patented in [6]. As shown in Fig. 1, the pump is composed of two concentric hollow cylinders in such a way that the smaller one is placed inside the bigger one. The space between the inner and the outer cylinder, denoted by (3) in Fig. 1, is packed with hollow fibers made of polypropylene. They constitute the gas exchange membrane. The inner cylinder has two separated parts. The upper part has six circular windows (5) which are all covered by a tubular silicone membrane. This membrane is the pumping membrane, and it separates blood from the driving fluid. The inner cylinder is Keywords: Blood Pump, Pump-oxygenator, Pediatric https://doi.org/10.1515/cdbme-2018-0012 To optimize extracorporeal pediatric perfusion systems a low priming volume of the components is an important prerequisite", + " The actuating mechanism of this pump-oxygenator can be either pneumatically or hydraulically. A pneumatic mechanism can only actuate the pump in the pump/pressure mode, while the pumping membrane cannot be actuated actively in the suction mode. To overcome this limitation, we proposed a hydraulic mechanism in which an auxiliary pump was used to actuate the blood pump. Fig. 2 shows the piston pump which served as the auxiliary pump. The piston pump is connected via a tubing system to the actuating port ((4) in Fig. 1) of the blood pump. The driving fluid generates a tight bidirectional coupling between the two pumps. Therefore, the reciprocating motion of the piston in the cylinder causes a synchronized movement of the pumping membrane in the blood pump. In order to generate a directed blood flow, two check valves (artificial heart valves) are necessary, which convert the reciprocating membrane movement in a unidirectional blood stream. The valves are located at the blood inlet and outlet (near (1) and (2) in Fig. 1). During operation, the stroke volume \u2206\ud835\udc49\ud835\udc49\ud835\udc43\ud835\udc43 of the piston pump is transferred to a volume displacement \u2206\ud835\udc49\ud835\udc49\ud835\udc35\ud835\udc35 in the blood pump, which is the stroke volume for blood pumping. With the frequency of motion \ud835\udc53\ud835\udc53\ud835\udc5a\ud835\udc5a, mean blood flow rate ?\u0305?\ud835\udc44\ud835\udc35\ud835\udc35 is ?\u0305?\ud835\udc44\ud835\udc35\ud835\udc35 = \u2206\ud835\udc49\ud835\udc49\ud835\udc35\ud835\udc35 \u2219 \ud835\udc53\ud835\udc53\ud835\udc5a\ud835\udc5a. (1) \u2206\ud835\udc49\ud835\udc49\ud835\udc35\ud835\udc35 is coupled to \u2206\ud835\udc49\ud835\udc49\ud835\udc43\ud835\udc43 by a reduction factor \ud835\udeff\ud835\udeff, which follows from the compliance of the system (0.9 < \ud835\udeff\ud835\udeff < 0,95). With displacement \u2206\ud835\udc65\ud835\udc65 and surface area \ud835\udc34\ud835\udc34 of the piston, blood flow can be expressed as ?\u0305?\ud835\udc44\ud835\udc35\ud835\udc35 = \u2206\ud835\udc49\ud835\udc49\ud835\udc35\ud835\udc35 \u2219 \ud835\udc53\ud835\udc53\ud835\udc5a\ud835\udc5a \u2248 \ud835\udeff\ud835\udeff \u2219 \ud835\udc34\ud835\udc34 \u2219 \u2206\ud835\udc65\ud835\udc65 \u2219 \ud835\udc53\ud835\udc53\ud835\udc5a\ud835\udc5a (2) Hence, the mean flow rate can be controlled in an open-loop mode by the piston position" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004268_f_version_1699339891-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004268_f_version_1699339891-Figure7-1.png", + "caption": "Figure 7. Measurement setup (a) for investigating the pressure-deformation behavior of a pneumatic actuator (PA). The PA is attached to a plate holder (b). A laser triangulator is mounted vertically above and axially aligned with the PA and sends the measurement data as an analog signal to the microcontroller with a 16-bit ADC (c), which also measures the pressure.", + "texts": [ + " Therefore, Equation (11) was set to zero and solved numerically: \u2212wmax ( 2E \u00b7 h \u00b7 \u03c0 \u00b7 w3 max(\u22122791v2 + 4250v + 7505) 19,845a2(v2 \u2212 1) ... \u22124E \u00b7 a2 \u00b7 FD \u00b7 kAM \u00b7 \u03c0 \u00b7 wmax 9H ) \u2212 a2 \u00b7 \u03c0 \u00b7 p \u00b7 wmax 3 = 0 (12) The nonlinear Equation (12) was solved using the MATLAB trust-region-dogleg algorithm (The MathWorks, Inc., Natrick, MA, USA) implemented in the fsolve function. An experiment was performed to validate the mathematical description and investigate the relationship between FD and deflection w. The test rig is shown in Figure 7. The maximum deflection, wmax, was measured using a laser triangulation sensor (HL-G112-S-J, Panasonic, Kadoma, Japan) at pressures of 0 to 8 bar on the actuator. The applied pressure was recorded using a basic board-mounted pressure sensor (ABPDANN010BGAA5, Honeywell International Inc., Charlotte, NC, USA). The sensor signals were recorded with a microcontroller (ArduinoNano, Arduino S.r.l., Monza, Italy), and then evaluated using MATLAB. It was assumed that the deflection changes accordingly by varying FD at the same pressure (see Equation (12))" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004853_0015-022-00744-z.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004853_0015-022-00744-z.pdf-Figure3-1.png", + "caption": "Fig. 3 The offset between the smectic force centre Sm and the hydrodynamic centre H , can result in a change in the agent\u2019s swimming direction, . a If the distance \ud835\udeff = \ud835\udeff+ > 0 , the resultant torque will reduce the angle between and Sm , aligning the swimming direction with the smectic force (red). This is probably the natural sign for most pushers. We adopt this convention in the remainder of this paper. b If \ud835\udeff = \ud835\udeff\u2212 < 0 , the natural sign for most pullers, the swimmer will instead anti-align (blue) (color figure online)", + "texts": [ + " This is where the hydrodynamic force arising through their motion through the (4) Sm = N\u22121\ufffd i=1 \u2212\u2207G( \u2212 i) = FSm \u239b\u239c\u239c\u239d cos sin 0 \u239e\u239f\u239f\u23a0 fluid may be considered to be acting and depends on the particle shape. Any force acting on the swimmer through a point other than H will generate a torque and hence a rotation. The smectic-mediated interaction is, in general, such a force. The torque that it generates Sm = \u2227 Sm where is the (signed) offset between the centres of smectic and hydrodynamic forces, see Fig.\u00a03. This torque acts to increase the angle between and Sm if is negative, and to decrease it if is positive. This is to say, that it acts to align the swimmer with the direction of the smectic force if the swimmer is a pusher, and to anti-align it if a puller, see Fig.\u00a03. The viscous torque due to rotation that balances this smectic torque also depends on the shape of the swimmer. For a spherical swimmer it is given by Faxen\u2019s law = 8\ud835\udf0b\ud835\udf07a3(\u0307 \u2227 ) . However, for a swimmer with more general axisymmetric shape, it takes the form V = c 1 \ud835\udf07(\u0307 \u2227 ) , where is the dynamic viscosity, and c1 is a parameter (with dimensions of volume) that depends on the shape. Following Newton we balance the torques V + Sm = 0 to find Using \u0307 = \ud835\udf15 \ud835\udf15t = ?\u0307? ( \u2212 sin\ud835\udf13 cos\ud835\udf13 ) we can then write The overdamped equation of motion for the particle position is assumed to be (5)\u0307 = \ud835\udeff c1\ud835\udf07 ( \u2227 Sm \u2227 ) " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004113_.aspx_paperID_130953-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004113_.aspx_paperID_130953-Figure1-1.png", + "caption": "Figure 1. Shows the coordinate system of a parabolic.", + "texts": [ + " [2] [5], the thermal deformation of the reflector caused by temperature increase, has effect on the surface accuracy and electrical performance, it impairs performance. Theory of the Parabolic Reflector Antenna The reflector or antenna has two purposes, first they collect power in terms of electrical signals (scintillations) and second, they provide directionality, for propagation of electromagnetic signal [6]. Reflector antennas operate on the principles known long ago from the theory of geometrical optics (GO) [7] [8]. Figure 1 shows an abstraction of the coordinate system of a parabolic antenna while Figure 2 shows the cross section. DOI: 10.4236/ojapps.2024.141014 184 Open Journal of Applied Sciences The parabolic surface of the antenna in Figure 1 is described by: ( )2 4 ,fF F z p a\u03c1\u2032 \u2032\u2212= (1) Here, \u03c1\u2032 is the distance from a point A to the focal point O, where A is the projection of the point R on the reflector surface onto the axis-orthogonal plane (the aperture plane) at the focal point [9] [10]. For a given displacement: \u03c1\u2032 from the axis of the reflector, the point R on the reflector surface is a distance fr away from the focal point O. The position of R can be modeled by a pair of coordinates in either rectangular ( \u03c1\u2032 , fz ) or the polar ( fr , f\u03b8 )" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003981_20_01_smdo200027.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003981_20_01_smdo200027.pdf-Figure3-1.png", + "caption": "Fig. 3. Mesh strategy adopting in CFD calculation with grids of 1.57e6.", + "texts": [ + " With the initiative geometrical parameters, the grid independent verification by means of CFD calculation is carried out at first to decide the right mesh strategy to adopt in the following optimization [12]. With the similar boundary conditions and algorithms settings in previous research [6], three cases varied with the mesh quantities of 1.17e6, 1.57e6 and 2.44e6 at the speed of V=60 km/h are calculated and their results are listed and compared (see Tab. 1). Referring to lift and drag values, that of 1.57e6 is considered as the optimal mesh which has assured the simulation precision with relatively less mesh to reduce process time, that saves as much as 44.3% of total time cost (see Fig. 3), which would also provide virtual results with enough details to describe the flow around the wings [13]. According to previous researches and test experience, this article has choses 5 parameters and 4 parameters respectively to realize the geometrical models of the delta wing and canard wing as followings. In the part of delta wing, the aerofoil shape is selected as FX63-137 as its lift advantage and the thickness to install the fans, thus the value between 4\u00b0 and 6\u00b0 are set for the incident angle ain1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003752_20__20Yan_20Qiao.pdf-Figure3.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003752_20__20Yan_20Qiao.pdf-Figure3.1-1.png", + "caption": "Figure 3.1: Pinhole camera model", + "texts": [ + " Intrinsic calibration refers to the method to find out the correct intrinsic parameters of pinhole camera, the focal length and focal point of x and y axis in image plane while extrinsic calibration refers to regressing real extrinsic parameters which describe the relative pose between two or multiple cameras. In this section, some notations about camera model and camera matrix are briefly explained. 27 As previously stated in Chapter 1, RGBD sensor refers to the stereo camera which consists of two pinhole cameras, or one pinhole camera which provides color image and 3D-laser scanner, which provides depth or distance information. Camera model has already been well-established for years and according to [76], the simplest optical system for modelling camera is pinhole camera. From Fig. 3.1, the focal point is the origin of the coordinate system which is located at the center of the projection and the focal length refers to the distance from the focal point to the image. According to the camera model, camera matrix and camera equation can be established. Using homogeneous coordinates, the relationship between image point under image plane, x, y, and its corresponding point under world plane, X, Y, Z can be expressed as Eq.(3.1), where \u03bb is equal to depth Z. \u03bb x y 1 = fx 0 cx 0 fy cy 0 0 1 X Y Z (3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002729_d.aspx_paperID_27644-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002729_d.aspx_paperID_27644-Figure1-1.png", + "caption": "Figure 1. Circuit outline of broadband feed and uniplanar tapered slot antenna; microstrip line on top metallization, slotline with TSA on bottom metallization.", + "texts": [ + " Therefore, several papers and books on the different components of a TSA system are available and discuss related planar transmission lines (PTLs) [8] and transitions involving microstrip and slotlines [9-14]. It has been demonstrated that the antipodal TSA, with fins on opposite sides of the substrate, is easily fed by a microstrip line over a wide bandwidth [15-17]. However, it is the uniplanar TSA, with both fins on the same substrate side, which is usually employed in large array applications. So far, though, its feed has limited the exploitation of an ultra-wide bandwidth [2,4]. The uniplanar TSA with a microstrip-to-slotline transition as feed is shown in Figure 1. Traditionally, the tran- sition is realized on high-permittivity substrate [8,9] due to the availability of better slotline models. However, a TSA performs best on low-permittivity substrate. On highpermittivity material, its performance is known to be poor unless parts of the substrate in the antenna are removed. This puts an extra effort on fabrication which has to be avoided when TSA arrays are involved [2,4]. Another feed that can be considered is a transition from coplanar waveguide (CPW) to slotline", + " However, the characteristic impedance of the slotline is usually limited to a lower boundary by manufacturing restrictions as will be considered in Section 2.3. Based on these results, microstrip as primary PTL and slotline as secondary PTL are used for the TSA system. An overview over the different TSA types is presented in [7]. To obtain small dimension, as mentioned above, the TSA profile is selected as an exponential taper, as first introduced in [6], which offers the shortest taper for broadband purposes. The taper in Figure 1 is determined by px TSAw Ae (2) where wTSA presents one half of the width between the fins, A adds an offset to the curve determined by the width of the secondary PTL (slotline with wsl = 150 m), and p = 0.125 characterizes the slope of the taper influenced by the overall length (1.5 sl at 6.5 GHz), the operational frequency range and the radiation characteristics of the TSA. Additionally, the sharp edges, which occur when the taper meets the radiating end of the substrate, are rounded to avoid disturbances and reflections in the electromagnetic fields (Figure 1). These features may later be replaced by corrugations [15] to limit the overall height of the antenna for array applications. Moreover, it is found that the advantage of a low- Copyright \u00a9 2013 SciRes. WET permittivity substrate on the radiation characteristics compensates for the loss along the PTLs. The microstrip-to-slotline transition presented in [9] matches the basic requirements for this application. However, it is presented in a back-to-back setup on a highpermittivity substrate. Therefore, the single transition is redesigned on a low-permittivity substrate for which Rogers RT/Duorid 5880 material with r = 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001817_451-41171703218M.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001817_451-41171703218M.pdf-Figure3-1.png", + "caption": "Figure 3: Principle of movement of grain through the elbow [11]", + "texts": [ + " Brittle materials are avoided due to dynamic loading system while , 433 Journal of Applied Engineering Science 15(2017)3 tough and soft (elastomer) because of poor mechanical properties and formability, particularly due to external temperature variations during seasonal changes. According to the laws of movement of grain through the pneumatic system [02, 08], the grain moves turbulent, hitting the walls bend, bouncing off each other and colliding with the consequent slowing of movement and change of continuity of movement. This chaotic movement causes discontinuity of flow and, ultimately, leads to congestion (Figure 3). The consequences of the arrival of the grain mass at the crossings is increased friction between the grain and the walls of the pass due to the direction of movement and effects of centrifugal force. Even according to some studies detected the collision zone of grain coming out of the bend pipe (secondary collision zone) which results in a slowing of movement and potential fracture grain [03]. These are the main causes of deformation and there are multiple solutions: adjustment of the pneumatic system with modern shapes of elbows, installation of the Venturi pipe directly below grain dinspenser in order to obtain sufficient speed at the beginning of movement, precise regulation of air and grain velocity through pipe, etc" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001345_f_version_1621584150-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001345_f_version_1621584150-Figure3-1.png", + "caption": "Figure 3. Mesh of the airfoil.", + "texts": [ + " A density-based solver was applied in ANSYS Fluent, and the Reynolds average Navier\u2013Stokes (RANS) equation and the S\u2013A turbulence model were adopted. The Green\u2013Gauss node-based scheme was selected as the discretization scheme, and the second-order upwind scheme was selected for turbulence equation discretization. The computational domain was 15 times the chord length. The far-field pressure was used as the boundary condition, and the airfoil was set as the wall boundary. The residual value was required to be below 1 \u00d7 10\u22126 to ensure convergence. The mesh of the airfoil is shown in Figure 3. A three-dimensional mesh was generated in ICEM. Figure 4 shows the computational domain, which consisted of two components, an internal rotation domain, and an external static domain. The upstream distance of the static domain was 10 times the diameter of the propeller, the downstream one was 20 times, and the diameter of the static domain was 10 times the diameter of the propeller. The rotation domain\u2019s speed is ns, whereas the static domain is stationary. The interface boundary condition was used as the exchange data between the static and the rotation domains, the velocity inlet and pressure outlet were adopted as the boundary conditions of the static domain, and the surface of the propeller was set as the wall" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003338_f_version_1718161279-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003338_f_version_1718161279-Figure3-1.png", + "caption": "Figure 3. Actuator parts.", + "texts": [ + " The actuator module encompasses key components such as the harmonic drive system, encoder, core motor, and various mechanical housing parts. Notably, the mechanical parts and harmonic drive system are intricately crafted to achieve a reduction in overall weight while simultaneously enhancing performance compared to existing actuators. The core principle of operation entails the amplification of input power generated by the core motor through the harmonic drive system, ultimately manifesting at the load side. Figure 3 provides a comprehensive overview of the various parts comprising the fabricated actuator module. The specifications of the harmonic drive are provided in Table 1. Figure 2. CAD model of the actuator. Figure 1. Actuator system architecture. i icts an articulated view of the d veloped actuator CAD model, meticulo sl si si g SolidWorks. The actuator module encompasses key components suc as t e ar ic drive system, encoder, core m tor, and various mechanical housing parts. otably, the mechanical parts and harmonic drive system are intricately crafted to achieve a reduction in overall weight while simultaneously enhancing perfor ance compared to existing actuators. The core principle of operation entails the amplification of input power generated by the core motor through the harmonic drive system, ultimately manifesting at the load side. Figure 3 provides a comprehensive overview of the various parts comprising the fabricated actuator module. The specifications of the harmonic drive are provided in Table 1. ct ators 2024, 13, x I 5 of 18 . it ct re. . . l i t ti l t ie of the developed actuator CAD model, meticul l li r s. e actuator odule nco pa se key compone ts s i ri s st , e c er, core otor, and various mechanical housing rts. t l , t c ic l rts a ar onic drive syste are intricately crafted to ac ie a re cti i erall ei t ile si ultaneously enhancing performance com- are to existi g act ators. e core ri ciple of operation e tails the amplification f in t r r te by the core otor through the har onic drive system, ultimately a ifesti at t e l a si e. Figure 3 provides a co prehensive overview of the various parts co rising the fabricated actuator odule. The specifications of the harmonic drive are provided in Table 1. Figure 2. CAD model of the actuator. Figure 2. CAD model of the actuator. Actuators 024, 13, x FOR PEER REVIE 5 of 18 Figure 1. rchitecture. 2.2. Actuator Module Figure 2 depicts an articulated view of the developed actuator CAD model, meticulously designed using SolidWorks. The actuator module encompasses key components such as the harmonic drive system, encoder, core motor, and various mechanical housing parts. Notably, the mechanical parts and harmonic drive system are intricately crafted to achieve a reduction in overall weight while simultaneously enhancing performance compared to existing actuators. The core principle of operation entails the amplification of input po er generated by the core motor through the harmonic drive system, ultimately manifesting at the load side. Figure 3 provides a comprehensive overview of the various parts co risi t e fa ricate actuator module. The specifications of the harmonic drive are provi e i l . Figure 2. t e actuator. Actuators 2024, 13, 218 6 of 17 The harmonic drive\u2019s design incorporates a wave generator, circular spline, and flex spline, constituting a three-component system engineered to amplify input power, resulting in an impressive reduction ratio of 1:160 within a compact structure. The characteristics of this system, outlined in Table 1, include a high torque capability of 40 Nm, zero backlash, high position accuracy (1 Arcmin), high stiffness, and co-axial orientation of the input and output", + " The flex spline, a thin cylindrical structure with external teeth at the open end of the cup, is affixed to the wave generator and functions as the output gear. The circular spline, featuring internal teeth and two additional teeth compared to the flex spline, remains constant and is fixed to the housing parts in our configuration. The mechanical parts of the actuator encompass several components, including the output flange, harmonic drive (HD) housing, bearing stopper, wave generator bearing housing, rotor coupler, stator bearing connector, and motor cover. The design of the output flange, depicted in Figure 3, facilitates the mounting of the encoder at one end of the hollow shaft and features flange-holes for attaching various loads and internal housing parts. Similarly, the design of the HD housing and wave-generator bearing housing, as shown in Figure 3, aids in internally mounting the harmonic drive system. Lastly, the rotor coupler, stator bearing connector, and motor cover, also illustrated in Figure 3, were designed in conjunction with the output flange and HD housing to accommodate the core motor within the harmonic drive system. In this research, the core motor utilized for designing the actuator was specified as the Maxon Electronically Commutated (EC) brushless motor. The actuator\u2019s modeling encompassed both electrical and mechanical characteristics. The electrical characteristics of the core motor can be derived by approximating it as a circuit consisting of an inductor, resistor, and back EMF" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure9.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure9.4-1.png", + "caption": "Figure 9.4. Illustration of the Ackermann steering geometry [53].", + "texts": [ + " As an example, consider a rack having width w = 650 mm and the package space (cube) of the earlier S-S link chapter, discretized into points spaced 10 mm apart. This results in 3286 link solutions that fit. Requiring that they fit inside the same rim as the earlier S-S link example reduces the number of solutions to 106, as seen in Figure 9.3. Choosing among the various candidate solutions is made easier by considering a steering system criterion associated with the Ackermann steering geometry. Ackermann steering geometry has all four wheels trace circles around a common center point, Figure 9.4. This geometry reduces the amount of tire slip that occurs when maneuvering at low speeds. At its essence, this means that the inside front wheel steers more than the outside front wheel, with the actual difference in steer angle not strictly set by achieving perfect Ackermann geometry. This is because Ackermann geometry is not particularly relevant at high speeds where the tire slip angles are unavoidably large. In [41, Figure 3.92], a difference of 3\u25e6 when the inside 138 wheel is at 20\u25e6 of steer is given as an example tolerance for Ackermann behavior" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000615_.1117_12.2308193.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000615_.1117_12.2308193.pdf-Figure10-1.png", + "caption": "Fig. 10 Eigen value analysis of the wheel", + "texts": [ + " This in turn will need more radiator area, causing substantial cooler mass increase. Based on these results, Soft mount was selected for mounting filters on the wheel. Filter Wheel acts as a support structure for 18 filters, and is connected to the FRP shaft. It is designed for stiffness of more than 100 Hz. This will be cooled in radiating mode by top and bottom casings, which house the wheel. Wheel should be as compact as possible to prevent thermal loss. This should not deform by more than 5 arc-minutes under thermal loads. Eigen value analysis in Fig. 10 shows that first wheel mode with soft mount is at 134 Hz. This is bending mode for the wheel. Thermal analysis as shown in Fig. 11 gives the stress experienced by the wheel for 100K temperature range which is within the yield strength of aluminium. Proc. of SPIE Vol. 10566 105662O-6 ICSO 2008 International Conference on Space Optics Toulouse, France 14 - 17 October 2008 Soft mount was realized and integrated as shown in Fig.5. Component details are as under. 3 mm thick Aluminum 6061-T651 plate as base simulating filter wheel material Aluminum 6061-T651 clamps on the two ends of the germanium filter, fixed with the base RTV sandwiched between the filter and the clamps Rectangular germanium piece 80mm long x 25 mm wide x 5 mm thick" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001293_O201226935181464.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001293_O201226935181464.pdf-Figure6-1.png", + "caption": "Fig. 6 3D FEM mesh for 3 phase 6/4 SRM", + "texts": [], + "surrounding_texts": [ + "\ubc1c\uc0dd\ud1a0\ud06c Te\ub294 \uad00\uc131, \ub9c8\ucc30\uacc4\uc218 \ubc0f \ubd80\ud558\ud1a0\ud06c\ub97c \uc774\uc6a9\ud558\uc5ec \ub2e4 \uc74c\uacfc \uac19\uc774 \ud45c\ud604\ud560 \uc218 \uc788\ub2e4. (3) \uc5ec\uae30\uc11c J\ub294 \uad00\uc131, B\ub294 \ub9c8\ucc30\uacc4\uc218, TL\uc740 \ubd80\ud558\ud1a0\ud06c\ub97c \ub098\ud0c0\ub0b8\ub2e4. \ubaa8\ub378\ub9c1\ud55c SRM\uc758 \ub3d9\uc801 \ubaa8\ub378\uc744 \uc774\uc6a9\ud558\uc5ec \uc2ac\ub77c\uc774\ub529\ubaa8\ub4dc \uc81c \uc5b4\uae30\ub97c \uc124\uacc4\ud55c\ub2e4. \uc774\ub54c, \ubd80\ud558 \ubc0f \ub9e4\uac1c\ubcc0\uc218 \ubcc0\ub3d9\uc5d0 \ub300\ud574 \uac15 \uc778\ud55c \uc2ac\ub77c\uc774\ub529\ubaa8\ub4dc \uc81c\uc5b4\uae30\ub97c \uc124\uacc4\ud558\uae30 \uc704\ud574 \ub2e4\uc74c\uacfc \uac19\uc774 \uc2dc \uc2a4\ud15c\uc758 \uad00\uc131, \ub9c8\ucc30\uacc4\uc218 \ubc0f \ubd80\ud558\ud1a0\ud06c\uc758 \ubcc0\ud654\ub97c \uac00\uc815\ud55c\ub2e4. Jmin < J < Jmax Bmin < B < Bmax TL,min < TL < TL,max Te J d\u03c9 dt ------ B\u03c9 TL+ += \uc5ec\uae30\uc11c \ucca8\uc790 \u2018min\u2019\uacfc \u2018max\u2019\ub294 \uac01\uac01 \ucd5c\uc18c\uac12\uacfc \ucd5c\ub300\uac12\uc744 \ub098\ud0c0 \ub0b8\ub2e4. \uc704\uc758 \uad00\uacc4\uc2dd\uc744 \uc774\uc6a9\ud558\uba74 \uc2dd (3)\uc740 \ub2e4\uc74c\uacfc \uac19\uc774 \ub098\ud0c0 \ub0bc \uc218 \uc788\ub2e4. (4) \uc2dd (4)\ub85c\ubd80\ud130 f\uac00 \uc2dd (5)\uc640 \uac19\uc774 \uc815\uc758\ub41c\ub2e4. (5) \uc0c1\ud0dc\ubcc0\uc218\ub97c \uc2dd (6)\uacfc \uac19\uc774 \uc815\uc758\ud558\uace0 \uc785\ub825 u\ub97c \ubc1c\uc0dd\ud1a0\ud06c Te\ub85c \uc815\uc758\ud558\uba74 \uc2dd (7)\uacfc \uac19\uc740 \uc624\ucc28 \uc0c1\ud0dc\ubc29\uc815\uc2dd(error state equation) \uc744 \uc5bb\ub294\ub2e4. x = \u03c9r \u2212 \u03c9r * (6) x = a0x + b0u + df + a0\u03c9r * (7) \uc5ec\uae30\uc11c \u03c9 r *\ub294 \uae30\uc900\uc18d\ub3c4, a0 = \u2212B0/J0, b0 = 1/J0, d = \u22121/J0, u = Ts\uc774\ub2e4." + ] + }, + { + "image_filename": "designv8_17_0002195_le_download_1077_452-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002195_le_download_1077_452-Figure3-1.png", + "caption": "Figure 3: Simulated reflection coefficient for various antenna structures shown in Figure 2.", + "texts": [ + " By adjusting the position of the step-shaped feeding underneath the DR (L3), a good impedance matching with a significant coupling can be achieved. The partial ground plane with size of 25\u00d711.5 mm2 is applied on the back side of the dielectric substrate. Figure 1: Geometry of the proposed UWB DRA (a) top view, (b) bottom view, and (c) 3-D view. The design procedure of the proposed DRA is shown in Fig. 2.The simulated reflection coefficients for the different antenna structures shown in Fig. 2, are plotted in Fig. 3 From the Figure 3, we can see that the monopole antenna resonate at two frequencies with an impedance bandwidth from 8.8 to 23.8 GHz. In order to increase the bandwidth and move the lower band toward lower frequencies, a DR is loaded on the monopole as shown in Figure 2(b). From Figure 3, it can be seen that the monopole antenna loaded with the DR, achieves better impedance matching than the basic monopole antenna structure. But the antenna still presents some mismatches at low frequencies band (less than 5.2 GHz), the band (18-19.4 GHz), and the high frequency band (more than 25.2 GHz). To further improve the impedance matching of the antenna, a slot is added to the partial ground plane, as shown in Figure 2(c). From Figure 3, it is clear that the added slot can improve the impedance matching; however, the antenna still has a mismatch at the low frequency less than 5.2 GHz. So, to improve this impedance mismatching at low frequencies, an L-shaped tuning stub is added to truncated ground plane, as shown in Figure 2(d). We can notice from Figure 3 that the monopole antenna loaded with the DR and the added slot in the ground plane and added L-shaped tuning stub shows a better impedance matching than the previous structures. Figure 2: Evolution of the proposed UWB DRA. (a) Monopole antenna. (b) Monopole antenna loaded with the DR. (c) Monopole antenna loaded with the DR and the added slot in the ground plane. (d) Monopole antenna loaded with the DR and the added slot in the ground plane and added L-shaped tuning stub. (e) The proposed DRA. To further improve the impedance matching and get a better reflection coefficient, a parasitic strip is added at the bottom of substrate, as shown in Figure 2(e).From Figure 3, we can notice that the proposed antenna has a better impedance matching over a very wide frequency band from 3.4 GHz to more than 28 GHz, a bandwidth of more than 156.7%; and a reflection coefficient that can reach until about -45dB. (e) (d) (a) (b) (c) HD HD LD1 Hs (c) WD1 X Y Z (a) Lf LP1 LP2 WP1 WS LS WP2 Wf L3 LD2 WD2 (b) LSh WSh LG LST1 WTS2 WTS1 LST2 Wn Ln The proposed DRA was designed, simulated, and optimized using HFSS. The parameters of proposed DRA are as follows: LS=25 mm, WS=25 mm, HS=0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004263_8600701_08725557.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004263_8600701_08725557.pdf-Figure8-1.png", + "caption": "FIGURE 8. Experimental prototype and test equipment. (a) Motor and the test equipment. (b) Test equipment for inductance.", + "texts": [ + " By the above analysis, VOLUME 7, 2019 71179 the best poles polarities arrangement for torque output is NSNNSN, and, the worst poles polarities arrangement is NNNNNN. From table 2, it can be seen that poles polarities arrangement of any adjacent three phases is NSNNSN in NS mode and NNNNNN in 12N mode. For this reason, when SRMs run in three-phase excitation mode, the best connection mode is NS mode and the worst connection mode is 12N. V. EXPERIMENTAL VERIFICATION Experimental prototype and test equipment are shown in figure 8 (a). The structure of the SRM is 12/10, dividing head is used to fix the position of the motor, when the phase winding is connected to the DC current, the torque value will be displayed on the instrument. The measuring range of the torque sensor is 20Nm and the precision is 0.04Nm, reduction of error by means of average of multiple measurements. The key parameters of the six-phase SRM were listed in table 1. A. SELF-INDUCTANCE AND MUTUAL INDUCTANCE From figure 5, when the SRM runs under unsaturated region, the self-inductance under different currents can be assumed as equal. The self-inductance andmutual inductance can be obtained by LCR. The experimental for measuring self-inductance and mutual inductance in SRMs is shown in figure 8(b). The rotor is held standstill at a position using the indexing head and a disk with position marking is mounted on the shaft of the SRM, the self-inductance of each phase at this degree can be measured by the LCR meter. When the motor is unsaturated, the model of the mutual inductance and adjacent phase-windings can be regard as an air-core transformer. The principle of the LCR meter is to use the AC power to test the impedance of the circuit loop. Taking phase A and B as an example, when the rotor is held standstill at a position and phase B is open, the impedance can be expressed as: ZAa = RSA + j\u03c9LSA (6) At the same rotor position, closing the phase B, the equation of the impedance can be expressed as: ZAb = RSA+ RSB R2SB+(\u03c9LSB) 2 +j\u03c9LSA \u2212 j\u03c93M2LSB R2SB+(\u03c9LSB) 2 (7) The imaginary part of equation (6) and (7) can be used to calculate the self-inductance of phase A by the LCR, and the difference of these two values, frequency of the voltage, phase resistance can be used to calculate the mutual inductance, and the equation can be shown as: M = \u221a (LSA \u2212 LAB)(R2SB + (\u03c9LSB)2) \u03c92LSB (8) where LSA is the self-inductance of phase A when phase B is opening, LAB is the self-inductance of phase A when phase B is closure, RSB is the resistance of phase B, LSB is the self-inductance of phase B when other phases are turned-off, \u03c9 is the frequency of the voltage in LCR meter" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001205_f_version_1535538104-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001205_f_version_1535538104-Figure2-1.png", + "caption": "Figure 2. Schematically samples for TMCP simulation (a) and wire-cut for tensile testing (b).", + "texts": [ + "\u00a0 Lastly,\u00a0X\u2010ray\u00a0diffraction\u00a0(XRD)\u00a0was\u00a0used\u00a0to\u00a0quantify\u00a0the\u00a0dislocation\u00a0density\u00a0of\u00a0each\u00a0sample,\u00a0according\u00a0 to\u00a0the\u00a0method\u00a0described\u00a0in\u00a0References\u00a0[5,20].\u00a0The\u00a0XRD\u00a0spectrum\u00a0for\u00a0each\u00a0sample\u00a0was\u00a0obtained\u00a0via\u00a0 scanning\u00a0in\u00a0a\u00a0diffractometer\u00a0(Rigaku\u00a0D/max\u20132500/PC,\u00a0Rigaku,\u00a0Tokyo,\u00a0Japan)\u00a0and\u00a0a\u00a0scanning\u00a0angle\u00a0 (2\u03b8)\u00a0ranging\u00a0from\u00a030\u00b0\u00a0to\u00a0110\u00b0\u00a0and\u00a0a\u00a0step\u00a0size\u00a0of\u00a00.02\u00b0\u00a0were\u00a0used.\u00a0Three\u00a0samples\u00a0were\u00a0tested\u00a0for\u00a0each\u00a0 simulated\u00a0specimen\u00a0and\u00a0the\u00a0average\u00a0value\u00a0was\u00a0reported.\u00a0 The\u00a0tensile\u00a0properties\u00a0of\u00a0the\u00a0samples\u00a0were\u00a0measured\u00a0using\u00a0the\u00a0micro\u2010sample\u00a0tensile\u00a0technique,\u00a0 which\u00a0 is\u00a0 shown\u00a0 in\u00a0 Figure\u00a0 2\u00a0 [16].\u00a0The\u00a0micro\u2010sample\u00a0was\u00a0 cross\u2010sectioned\u00a0 from\u00a0 the\u00a0 sample\u00a0 at\u00a0 the\u00a0 position\u00a0 the\u00a0 thermocouple\u00a0was\u00a0 fixed.\u00a0Lately,\u00a0 the\u00a0 room\u2010temperature\u00a0 tension\u00a0was\u00a0 performed\u00a0 in\u00a0 a\u00a0 After the simulation, the microstructures of different samples were characterized in details. For the optical microscopy (OM) observations, the samples were cross-sectioned at the position of the thermocouple, which was fixed, polished mechanically, etched in a 4% nital, and observed in an optical microscope (Axiover-200MAT, Carl Zeiss Microimaging GmbH, Jena, Germany)", + " Lastly, X-ray diffraction (XRD) was used to quantify the dislocation density of each sample, according to the method described in References [5,20]. The XRD spectrum for each sample was obtained via scanning in a diffractometer (Rigaku D/max\u20132500/PC, Rigaku, Tokyo, Japan) and a scanning angle (2\u03b8) ranging from 30\u25e6 to 110\u25e6 and a step size of 0.02\u25e6 were used. Three samples were tested for each simulated specimen and the average value was reported. The tensile properties of the samples were measured using the micro-sample tensile technique, which is shown in Figure 2 [16]. The micro-sample was cross-sectioned from the sample at the Metals 2018, 8, 677 4 of 16 position the thermocouple was fixed. Lately, the room-temperature tension was performed in a tensile testing machine (Inspekt Table 100, Hegewald & Peschke, Nossen, Germany) with a tension rate of 0.25 mm/min. Twice tensile testing were performed for each sample and their mean value was taken as the tensile properties. The yield strength (YS) was measured as the 0.2% offset stress (Rp0.2). 1 Each sample was tensile tested with the stress-strain curve shown in Figure 3 and the tensile properties indicated in Figure 4, as the function of the cooling path (CP)", + " The YR is a subordinate indicator for the evaluation of a strain hardening capacity. A lowered YR for this low-C V-Ti-N steel could lead to a better strain hardening capacity, according to ref. [16,19]. Metals\u00a02018,\u00a08,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 \u00a0 4\u00a0of\u00a016\u00a0 nsile\u00a0testing\u00a0machin \u00a0(Inspekt\u00a0Table\u00a0100,\u00a0Hegewald\u00a0&\u00a0Peschk ,\u00a0Nossen,\u00a0Germany)\u00a0with\u00a0a\u00a0tension\u00a0 rate\u00a0of\u00a00.25\u00a0mm/m n.\u00a0Twice\u00a0tens le\u00a0testing\u00a0were\u00a0perform d\u00a0for\u00a0each\u00a0sample\u00a0and\u00a0their\u00a0mean\u00a0value\u00a0was\u00a0 taken\u00a0as\u00a0the\u00a0tensil \u00a0properti s.\u00a0The\u00a0yi ld\u00a0strength\u00a0(YS)\u00a0was\u00a0measured\u00a0as\u00a0the\u00a00.2%\u00a0offset\u00a0stress\u00a0(Rp0.2).\u00a0 \u00a0 Figure\u00a02.\u00a0Schematically\u00a0samples\u00a0for\u00a0TMCP\u00a0simulation\u00a0(a)\u00a0and\u00a0wire\u2010cut\u00a0for\u00a0tensile\u00a0testing\u00a0(b).\u00a0 .\u00a0 s lts\u00a0 3.1.\u00a0Tensile\u00a0Properties\u00a0 Each\u00a0sample\u00a0was\u00a0tensile\u00a0tested\u00a0with\u00a0the\u00a0stress\u2010strain\u00a0curve\u00a0shown\u00a0in\u00a0Figure\u00a03\u00a0and\u00a0the\u00a0tensile\u00a0 properties\u00a0indicated\u00a0in\u00a0Figure\u00a04,\u00a0as\u00a0the\u00a0function\u00a0of\u00a0the\u00a0cooling\u00a0path\u00a0(CP).\u00a0As\u00a0displayed\u00a0in\u00a0this\u00a0figure,\u00a0 the\u00a0yield/tensile\u00a0strength\u00a0 (YS/TS)\u00a0decreased\u00a0 from\u00a0436/615\u00a0 to\u00a0355/599\u00a0MPa\u00a0along\u00a0with\u00a0 the\u00a0changes\u00a0 from\u00a0the\u00a0cooling\u00a0path\u00a0A\u00a0(CP\u2010A)\u00a0to\u00a0the\u00a0cooling\u00a0path\u00a0E\u00a0(CP\u2010E).\u00a0The\u00a0yield\u00a0ratio\u00a0(YR),\u00a0which\u00a0is\u00a0equal\u00a0to\u00a0 the\u00a0ratio\u00a0of\u00a0the\u00a0YS\u00a0to\u00a0the\u00a0TS,\u00a0decreased\u00a0evidently\u00a0from\u00a00" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000000_9771273_09667270.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000000_9771273_09667270.pdf-Figure2-1.png", + "caption": "Fig. 2. (a) E-field distributions at even-mode and odd-mode. (b) Simplified equivalent circuit model of the loaded-stub resonator. (c) Even-mode model. (d) Odd-mode model. (Z1 = 49 , Z2 = 65 , Z3 = 80 , Z4 = 56 , Z5 = 68 , \u03b81 = 41\u25e6 , \u03b82 = 78\u25e6, \u03b83 = 15\u25e6, \u03b84 = 30\u25e6 , and \u03b85 = 89\u25e6).", + "texts": [ + " To further investigate the mechanism, the dielectric substrate RT5880 (i.e., \u03b5r = 2.2, h1 = 0.127 mm, and h3 = 0.508 mm), the bounding layer RO4450F (i.e., \u03b5r = 3.52 and h2 = 0.101 mm), and the 3-D EM simulation software HFSS are used. 1) Loaded-Stub SIDGS Resonator: Since the loaded-stub SIDGS resonator is symmetrically designed, the even- and This work is licensed under a Creative Commons Attribution 4.0 License. For more information, see https://creativecommons.org/licenses/by/4.0/ odd-mode analyses can be carried out. Fig. 2(a) depicts the electric field (i.e., E-field) distributions of two resonant modes. The E-fields in the end of the DGSs almost disappear. Thus, the ends are regarded as grounded. Besides, the middle-point E-field at the even mode is continuous, while the middlepoint E-field at the odd mode almost disappears. Therefore, center point of the even mode is open, while the one of the odd mode is short. Here, the simplified equivalent model of the loaded-stub resonator is shown in Fig. 2(b), while the even-mode and odd-mode models are derived in Fig. 2(c) and (d), respectively. The input admittance (i.e., Ya) of the circuit model is derived as Ya = Y a + Y a (1) Y a = \u2212 j 1 Z1 Z1 \u2212 Z2 tan \u03b81 tan \u03b82 Z1 tan \u03b81 + Z2 tan \u03b82 (2) where Y a is calculated by (3) as shown at the bottom of the page. The electrical parameters of the circuit models can be obtained as [39] mentioned and are given in the caption of Fig. 2. Due to the magnetic effect from the surrounding metal vias, Z1 is not equal to Z2. By setting Ya = 0 at the even mode and Ya = \u221e at the odd mode, two fundamental resonant frequencies fa1 and fa2 are calculated. Fig. 3(a) and (b) provides the calculated and simulated resonant frequencies versus l2 and l3, respectively. The analytical solutions are in a good agreement with the EM-simulated resonant frequencies. 2) C-Shape SIDGS Resonator: Fig. 1(d) shows the configuration of the C-shape SIDGS resonator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001092_2_1_12_22004507__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001092_2_1_12_22004507__pdf-Figure3-1.png", + "caption": "Fig. 3. Magnetic flux density of the dovetailshaped magnet", + "texts": [ + " However, as the performance of the current prototype remains insufficient, this study focuses on the prototype structure. To mitigate the performance differences and meet the needs of practical applications, the specifications used in preplanning are shown in Table 2 (7). 3. Magnet Fixation Optimization Design In this study, for the magnet fixation method, a common dovetail groove cut on silicon steel sheet was used first, and the magnet was embedded in the groove to achieve fixation. However, as seen from Fig. 3, the traditional dovetail groove design causes the magnetic flux of the dovetail magnet to saturate easily at the bottom of the groove when flowing through the silicon steel sheet. Figure 4 shows the distribution of the magnetic field lines for the traditional dovetail groove design. Second, because of the design used for magnet fixation, there may be wear and tear of the magnet material during processing; correspondingly, owing to the poor structural stresses at the sharp corners of the magnet, the magnet may break or result in other problems if the assembly is not performed carefully (8)\u2013(22)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003835_f_version_1676453559-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003835_f_version_1676453559-Figure1-1.png", + "caption": "Figure 1. STRATOFLY MR3 layout.", + "texts": [ + " In addition, in order to reduce the complexity associated with the modeling and simulation of such a kind of system, the proposed TMS concept (Section 4) takes into account powerplant cooling only, even if still considers interfaces with the cabin environmental control system (ECS) as an example of external utility (other than the propellant system, whose interface is a pre-requisite for enabling the TMS). Airframe thermal control is instead not included within the analysis, even if theoretically applicable to the concept. From the configuration standpoint, the STRATOFLY MR3 aircraft (Figure 1) follows the layout proposed by LAPCAT II Project for its MR2.4 vehicle [17], with some differences. It is still characterized by a waverider architecture, with a dorsal-mounted propulsion plant duct, a canard and a V-Tail layout for directional stability and control. The main differences between the MR2.4 and MR3 external layouts are related to the overall dimensions, which are slightly extended for the MR3; the shape of the V-Tail; and the upper part of the aft section of the nozzle, as well as the introduction of additional control surfaces (nozzle flaps)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002072_3-319-16178-5_15.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002072_3-319-16178-5_15.pdf-Figure3-1.png", + "caption": "Fig. 3. To estimate the ground distance d between the UAV and the person, we assume a horizontal ground plane and a person height h. The angle \u03d5 is obtained from normalized image coordinate y of the upper edge of the bounding box and the effective focal length f . The UAV altitude z and camera pitch \u03c1 are known. The distance is obtained using simple geometry by considering the larger triangle in the figure.", + "texts": [ + " The process and detection models are xk+1 =Fk+1xk + wk+1 = \u23a1 \u23a3I2 TsI2 02 02 I2 02 02 02 I2 \u23a4 \u23a6xk + wk+1 (7) zk =Hkxk + ek = [ I2 02 02 ] xk + ek, (8) where wk+1 and ek are zero-mean Gaussian noice processes with covariance matrices Qk+1 and Rk, respectively. The visual tracking output is used as input in a Probability Hypothesis Density (PHD) filter [19,20]. Specifically we use a Gaussian mixture implementation [24] with a uniform distribution for the position component of the birth PHD intensity [3]. Controlling the UAV by leashing requires a distance estimate to the target. This is obtained by assuming a horizontal ground plane and a fixed person height h. Figure 3 contains a simple illustration of the scenario. The angle \u03d5 between the optical axis and the projection ray of the top of the target is calculated as \u03d5 = arctan ( y f ) (9) where y is the normalized image top-coordinate of the bounding box and f is the effective focal length. Using the known altitude z and camera pitch angle \u03c1, the distance d can be obtained from simple trigonometry. d = z \u2212 h tan(\u03c1 \u2212 \u03d5) (10) Since we have a camera with a narrow field of view, a small yaw angle of the camera relative the target can be assumed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001789_cle_download_505_375-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure3-1.png", + "caption": "Figure 3. Initial IPMSM motors with M19 silicon steel material (a) 2 kW motor, (b) 5 kW motor and (c) 120 kW motor.", + "texts": [ + " Computer-aided design of IPMSM includes a database of various materials, a selection of design variables, performance estimation and decision-making loops for performance checks. The performance of the motor is estimated according to the calculated dimensions, material properties and assumed design variables [24]. It takes corrective actions if estimated performance deviates from expected performance. Three standard rating IPMSMs of 2 kW, 200 000 rpm; 5 kW, 24 000 rpm and 120 kW, 10 000 rpm are initially designed using M19 cold-rolled silicon steel material. Finite element (FE) models created on the basis of the design details of these ratings are illustrated in Figure 3. Table 1 shows design details of initially designed motors for all three ratings. All three different rating motors are designed with the same number of stator slots and three phases of winding distributed in it. The number of rotor poles is also considered to be the same and made of NdFeB type permanent magnet. Permanent magnets are inserted in the rotor core to obtain interior rotor pole arrangement. Neodymium Iron Boron (NdFeB) permanent magnets of 35th grade (i.e. N35) are used with the magnetization in alternately reversing polarity in a spoke-type arrangement to form rotor poles" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003536_830_81_15-00138__pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003536_830_81_15-00138__pdf-Figure14-1.png", + "caption": "Fig. 14 Detailed drawing of a cross section of the hybrid device tested in this study. The rolling bearing functions as a traction drive by adding preload from the preload ring. The output power is transmitted from the output shaft with retainer.", + "texts": [], + "surrounding_texts": [ + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n6 '\n2hb Z \uff0824\uff09\n' M Z\nM \uff0825\uff09\n\u516c\u79f0\u66f2\u3052\u5fdc\u529b \u03c3M\u306f\uff0c26.5[N/mm 2 ]\u306b\u306a\u308b\u3053\u3068\u3092\u78ba\u8a8d\u3057\u305f\uff0e\u3053\u3053\u3067\uff0c\u5fdc\u529b\u96c6\u4e2d\u4fc2\u6570 \u03b1(Heywood, 1952)\u3092\u4ee5\u4e0b\u306e\u5f0f(26) \u3088\u308a\u8a08\u7b97\u3092\u3057\u305f\uff0e\u5f0f(26)\u4e2d\u306e B\uff0cb\uff0c\u03c1\u306f\u305d\u308c\u305e\u308c 2B=20.0[mm]\uff0c2b=8.0[mm]\uff0c\u03c1=6.0[mm]\u3067\uff0c\u305d\u306e\u5b9a\u7fa9\u3092\u56f3 11 \u306b \u793a\u3059\uff0e\n85.0\n8.437.5\n1\n1\n \n\n \n\n\n\n\n \n b\nb\nB b\nB\n\uff0826\uff09\nMS \uff0827\uff09\n3\na\na\n16 T d \uff0828\uff09\n\u5fdc\u529b\u96c6\u4e2d\u4fc2\u6570 \u03b1\u306f 1.16 \u3068\u306a\u308a\uff0c\u516c\u79f0\u66f2\u3052\u5fdc\u529b 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\u6e1b\u901f\u6a5f\u80fd\u3092\u6709\u3059\u308b\u5186\u7b52\u3053\u308d\u8ef8\u53d7\u90e8\u5206\u306b\u306f\u30c8\u30e9\u30af\u30b7\u30e7\u30f3\u30b0\u30ea\u30fc\u30b9\u3092\u7528\u3044\uff0c\u6b6f\u8eca\u3084\u305d\u306e\u4ed6\u306e\u8ee2\u304c\u308a\u8ef8\u53d7\u90e8\u306b\u306f\uff0c\u30d1\u30e9 \u30d5\u30a3\u30f3\u7cfb\u9271\u7269\u6cb9\u3092\u57fa\u6cb9\u3068\u3057\uff0c\u5897\u3061\u3087\u3046\u5264\u3092\u30ea\u30c1\u30a6\u30e0\u30b3\u30e0\u30d7\u30ec\u30c3\u30af\u30b9\u3068\u3057\u305f\u30b0\u30ea\u30fc\u30b9\u3092\u7528\u3044\u305f\uff0e\u30b0\u30ea\u30fc\u30b9\u306e\u6027\u72b6\u3092 \u8868 4\u306b\u793a\u3059\uff0e\nd '\nFig. 12 Final overview showing an external view of the output shaft with retainer. The material is phosphorus bronze. The torsion strength of the smallest diameter of the shaft was calculated and was confirmed to have no problems.\nMaterial Phosphor bronze\n(Cu 90.3%, Sn 9.3%, P 0.16%)\nNumber of retainer pocket - 8\nNominal bending stress [N/mm 2 ] \u03c3S 30.7\nShaft diameter [mm] d\u00b4 20\nTable 3 Final dimensions of the output shaft with retainer\nfrom the motor is measured by the torque meter and tachometer. Its power is transmitted to a gear pair with a gear reduction ratio of 1. The torque meter and tachometer are also set on the output side, making it possible to measure the power.", + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n6\u30fb1 \u8a55\u4fa1\u6307\u6570\u306e\u5b9a\u7fa9 \u5165\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nin\uff0c\u51fa\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nout\uff0c\u5165\u529b\u5074\u30c8\u30eb\u30af\u306e\u8a08\u6e2c\u5024 Tin\uff0c\u51fa\u529b\u5074\u30c8\u30eb\u30af\u306e\u8a08\u6e2c\u5024 Tout \u3092\u7528\u3044\u3066\uff0c\u5f0f(29)\u304b\u3089\u52d5\u529b\u4f1d\u9054\u52b9\u7387 \u03b7eff\u306e\u7b97\u51fa\u3092\u884c\u3063\u305f\uff0e\u6b21\u306b\uff0c\u7406\u8ad6\u4e0a\u306e\u6e1b\u901f\u6bd4 ith\u3068\u5165\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nin\u3092 \u51fa\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nout\u3067\u5272\u3063\u305f\u5b9f\u6e2c\u6e1b\u901f\u6bd4 iac\u3092\u7528\u3044\u3066\uff0c\u6b21\u306e\u5f0f(30)\u304b\u3089\u3059\u3079\u308a\u7387 S \u306e\u7b97\u51fa\u3092\u884c\u3063\u305f\uff0e\u306a\u304a\uff0c \u5f93\u6765\u7814\u7a76\u3092\u57fa\u306b\uff0c\u672c\u7814\u7a76\u3067\u7528\u3044\u305f\u8ef8\u53d7\u54c1\u756a\u300cNU306E\u300d\u306e\u7406\u8ad6\u4e0a\u306e\u6e1b\u901f\u6bd4 ith\u3092\u8a08\u7b97\u3057\u305f\u7d50\u679c ith=2.543\u3067\u3042\u3063\u305f\uff0e\ninin\noutout eff\nTN\nTN\n\n \uff0829\uff09\n1001 th ac i i S \uff0830\uff09\n6\u30fb2 \u4f1d\u9054\u53ef\u80fd\u30c8\u30eb\u30af\u3068\u6e1b\u901f\u6bd4\u306e\u78ba\u8a8d \u5165\u529b\u56de\u8ee2\u901f\u5ea6\u3092\u305d\u308c\u305e\u308c\uff0c50\uff0c100\uff0c150\uff0c200[rpm]\u306b\u3057\u3066\uff0c\u4f1d\u9054\u53ef\u80fd\u30c8\u30eb\u30af\u3068\u6e1b\u901f\u6bd4\u306e\u78ba\u8a8d\u3092\u884c\u3063\u305f\uff0e\u5b9f\u9a13\u65b9 \u6cd5\u306f\uff0c\u51fa\u529b\u5074\u306e\u8a2d\u5b9a\u30c8\u30eb\u30af\u3092\u5f90\u3005\u306b\u5897\u52a0\u3055\u305b\u3066\uff0c4\u7ae0\u3067\u76ee\u6a19\u3068\u3057\u305f 20[N\u30fbm]\u304c\u904b\u8ee2\u53ef\u80fd\u304b\u3069\u3046\u304b\u306b\u95a2\u3057\u3066\u78ba\u8a8d\u3057 \u305f\uff0e\u56f3 15\uff0c\u56f3 16\uff0c\u306b\u5165\u529b\u56de\u8ee2\u901f\u5ea6\u304c 100\uff0c200[rpm]\u306e\u3068\u304d\u306e\u5b9f\u9a13\u7d50\u679c\u3092\u793a\u3059\uff0e\n\u3044\u305a\u308c\u306e\u56de\u8ee2\u901f\u5ea6\u3067\u3082\uff0c\u524d\u8ff0\u306e\u8a08\u7b97\u901a\u308a\u306e\u51fa\u529b\u30c8\u30eb\u30af 20[N\u30fbm]\u307e\u3067\u904b\u8ee2\u304c\u53ef\u80fd\u3067\u3042\u3063\u305f\uff0e\u3055\u3089\u306b\uff0c\u3059\u3079\u3066\u306e\u904b \u8ee2\u9818\u57df\u3067\u306e\u5b9f\u6e2c\u6e1b\u901f\u6bd4\u306e\u5e73\u5747\u306f\u5165\u529b\u56de\u8ee2\u901f\u5ea6 100[rpm]\u306e\u3068\u304d\u306b\u306f iac=2.539\uff0c200[rpm]\u306e\u3068\u304d\u306b\u306f iac=2.524 \u3068\u7406\u8ad6 \u4e0a\u306e\u6e1b\u901f\u6bd4 ith\u3067\u3042\u308b 2.543 \u306b\u8fd1\u3044\u5024\u3068\u306a\u3063\u305f\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u3092\u7528\u3044\u305f\u4e88\u5727\u65b9\u6cd5\u3067\u3082\u554f\u984c\u306a\u304f\u8a2d\u8a08\u5024\u901a \u308a\u306e\u30c8\u30eb\u30af\u3092\u4f1d\u9054\u3067\u304d\u308b\u3053\u3068\u304c\u78ba\u8a8d\u3067\u304d\u305f\uff0e\u307e\u305f\uff0c\u3044\u305a\u308c\u306e\u56de\u8ee2\u901f\u5ea6\u3067\u3082\u5b9f\u6e2c\u6e1b\u901f\u6bd4\u306f\u5b89\u5b9a\u3057\u305f\u6570\u5024\u3092\u5f97\u3066\u3044\u305f\uff0e" + ] + }, + { + "image_filename": "designv8_17_0001456_18_ms-9-327-2018.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001456_18_ms-9-327-2018.pdf-Figure11-1.png", + "caption": "Figure 11. FEA of the compliant segment.", + "texts": [ + " From this, the link cross-sectional dimensions are determined as t = 1 mm, and b = 30 mm. With these dimensions, the stress of the flexible segment remains in an acceptable range for the complete cycle. The resulting stress values with respect to angular position of the input link (\u03b812) are presented in Fig. 10. The determined maximum and minimum stresses are \u2213311.2 MPa. In order to verify the analytical approach, FEA is performed and equivalent stresses on the compliant link are determined. Mech. Sci., 9, 327\u2013336, 2018 www.mech-sci.net/9/327/2018/ The results are shown in Fig. 11. Neglecting the stress concentration regions, the maximum stress is determined as \u03c3max = 336.2 MPa. This result is in agreement with the analytically calculated stress. Fatigue failure can occur at stresses that are significantly smaller than those causing static failure. Therefore, a fatigue life analysis is essential for all compliant mechanisms. Furthermore, as this mechanism will be used in automotive applications, the fatigue life is critical. The unmodified endurance limit (for the fatigue test specimen), which is the point where failure will not occur regardless of the number of cycles, for this steel is S\u2032e = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001405_f_version_1688450777-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001405_f_version_1688450777-Figure2-1.png", + "caption": "Figure 2. CTRV odel for a oving object.", + "texts": [ + " The UAV dynamics were obtained from the 2D CTRV model [8] for vehicle and pedestrian detection on highways. It is assumed that the possible movements of the elements around the UAV are not completely arbitrary and not holonomous, in which case there will be displacements in a bi-dimensional plane. The curvilinear model (CTRV) includes angular velocities and angular movements in its modeling, which allows a better description of the changes in the direction and velocity of an object in a linear model. The CTRV model is shown in Figure 2. Remote\u00a0Sens.\u00a02023,\u00a015,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 3\u00a0 of\u00a0 14\u00a0 \u00a0 \u00a0 changes\u00a0in\u00a0their\u00a0direction\u00a0and\u00a0trajectory,\u00a0to\u00a0generate\u00a0a\u00a0three-dimensional\u00a0reconstruction\u00a0 w e \u00a0the\u00a0information\u00a0is\u00a0captured\u00a0from\u00a0a\u00a0UAV.\u00a0 2.\u00a0Dynamic\u00a0Model\u00a0of\u00a0UAV\u00a0 The\u00a0UAV\u00a0dynamics\u00a0were\u00a0obtained\u00a0from\u00a0the\u00a02D\u00a0CTRV\u00a0model\u00a0[8]\u00a0for\u00a0vehicle\u00a0and\u00a0pe- destrian\u00a0detection\u00a0on\u00a0highways.\u00a0It\u00a0is\u00a0assumed\u00a0that\u00a0the\u00a0possible\u00a0movements\u00a0of\u00a0the\u00a0elements\u00a0 around\u00a0the\u00a0UAV\u00a0are\u00a0not\u00a0completely\u00a0arbitrary\u00a0and\u00a0not\u00a0holonomous,\u00a0in\u00a0which\u00a0case\u00a0there\u00a0 will\u00a0be\u00a0displacements\u00a0in\u00a0a\u00a0bi-dimensional\u00a0plane.\u00a0The\u00a0curvilinear\u00a0model\u00a0(CTRV)\u00a0includes\u00a0 angular\u00a0velocities\u00a0and\u00a0angular\u00a0movements\u00a0in\u00a0its\u00a0modeling,\u00a0which\u00a0allows\u00a0a\u00a0better\u00a0descrip- tion\u00a0of\u00a0the\u00a0changes\u00a0in\u00a0the\u00a0direction\u00a0and\u00a0velocity\u00a0of\u00a0an\u00a0object\u00a0in\u00a0a\u00a0linear\u00a0model.\u00a0The\u00a0CTRV\u00a0 model\u00a0is\u00a0shown\u00a0in\u00a0Figure\u00a02.\u00a0 Figure\u00a02.\u00a0CTRV\u00a0model\u00a0for\u00a0a\u00a0moving\u00a0object.\u00a0 The\u00a0velocity\u00a0variable\u00a0provides\u00a0the\u00a0system\u00a0model\u00a0the\u00a0ability\u00a0to\u00a0calculate\u00a0the\u00a0target\u2019s\u00a0 lateral\u00a0position\u00a0variations\u00a0for\u00a0a\u00a0correct\u00a0prediction\u00a0of\u00a0the\u00a0future\u00a0position\u00a0of\u00a0the\u00a0target,\u00a0thus\u00a0 starting\u00a0from\u00a0initial\u00a0positions\u00a0x\u00a0and\u00a0y\u00a0and\u00a0projecting\u00a0this\u00a0location\u00a0over\u00a0time,\u00a0defined\u00a0as\u00a0x\u00a0 +\u00a0x\u00a0and\u00a0y\u00a0+\u00a0y\u00a0for\u00a0the\u00a0target\u00a0as\u00a0shown\u00a0in\u00a0Figure\u00a03.\u00a0 Figure\u00a03.\u00a0Position\u00a0prediction\u00a0through\u00a0the\u00a0CTRV\u00a0model.\u00a0 The\u00a0CTRV\u00a0model\u00a0for\u00a0the\u00a0UAV\u00a0system\u2019s\u00a0moving\u00a0target\u00a0in\u00a0the\u00a0three-dimensional\u00a0case\u00a0 determines\u00a0the\u00a0projection\u00a0of\u00a0the\u00a0position\u00a0of\u00a0the\u00a0target\u00a0xi+1\u00a0on\u00a0the\u00a0axis,\u00a0starting\u00a0from\u00a0the\u00a0 The velocity variable provides the syste odel the ability to calculate the target\u2019s lateral position variations for a co rect prediction of the future position of the target, thus starting from initial positions x and y and projecting this location over time, defined as x + \u2206x and y + \u2206y for the target as show in Figure 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001453_article_25887703.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001453_article_25887703.pdf-Figure2-1.png", + "caption": "Figure 2. Finite Frame static analysis of strain cloud", + "texts": [ + " When the frame structure is subjected to a small alternating dynamic load, it can be regarded as a static effect, directly to the static analysis, the initial judgment of the frame by the maximum static effect Is the weight of the pad, the auxiliary rail, the linear motion unit, the motor, the air-cooled system, the target and the attachment, respectively, equally on the four beams. Through the finite element analysis, the results of the static analysis are obtained: the maximum deformation occurs in the middle of the beam, and the deformation is mm, as shown in Fig. 2. 26.86MPa, and the minimum stress occurs at the junction of the middle pillar and the base of the channel. The minimum stress is MPa, as shown in Fig. 3. Modal Analysis. In order to further evaluate whether the design of the overall system can meet the requirements, the following is a special modal analysis and calculation of the dynamic stiffness of the channel structure. Which can be obtained in the channel structure of the ninth-order natural frequency value of Hz, the maximum vibration deformation of 13" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001876_41230-021-0125-8.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001876_41230-021-0125-8.pdf-Figure3-1.png", + "caption": "Fig. 3: Geometry of calculated domain (a) and consumable electrodes location in ESR mould (b)", + "texts": [ + " Each pair of consumable electrodes is connected to each corresponding transformer in a bifilar pattern (designated A1 and A2, B1 and B2, C1 and C2, respectively). The principal electric diagram is presented in Fig. 2 below. The midpoint of each transformer is shown as \u201c0\u201d and all of them are connected to the bottom plate. (3) (4) (5) (6) To simplify the calculation process, the design features of the high current loop and auxiliary units were not taken into account. The 3D model of the studied domain (Fig. 3) was exported to the Comsol Multiphysics software environment for further calculations. In-built mathematical formulas for the electromagnetic analysis and heat release determination (from the point of the current density and electric conductivity of a slag) were used to simulate the electromagnetic phenomena and Joule heating. The electric and magnetic fields in the ESR are interdependent and are determined by Maxwell's equations and Ohm's law: V div div (2)curl (1)curl where, E is the electric field intensity, H is the magnetic field intensity, J is current density, D is the electric flux density, \u03bc is the permeability of a material, \u03c3 is the electrical conductivity and qV is the volumetric power dissipated by Joule effect", + " The following assumptions and simplifications were also adopted at simulation: all consumable electrodes were identical and had an equal mass and density; imbalance between electrodes was absent, and current to the bottom plate didn\u2019t exist. The geometry of the computation domain, electrical parameters and properties of involved materials are given in Table 1. To understand the nature and characteristics of electromagnetic phenomena and the heat releasing features at the threephase ESR bifilar diagram, the following three variants of the location of the consumable electrodes were studied: the uniform distribution in the mould, and distribution in bifilar pairs of two types - maximum closeness and maximum extension. Figure 3 shows a schematic of the geometric arrangement of the electrodes in a melting space of the ESR furnace for the studied variants, and parameters for the considered variants are listed in Table 2. The given potential difference between the electrodes is 80 V, and the voltage between the electrode and the bottom plate equals 40 V. For each of the variants listed in Table 2, the investigation included magnetic flux distribution and the potential differences in the cross-section of the slag bath at 5 mm distance from the tips of the electrodes (penetration from the surface of the slag bath makes 55 mm)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure17-1.png", + "caption": "Fig. 17, Model used for Case (e), \u201cRigid\u201d virtual part, torsion", + "texts": [ + " The exact location of the handler point is not relevant if \u201cRigid\u201d or \u201cRigid Spring\u201d is employed and the deformation is purely torsional. Regardless, for the sake of consistency, the handler point is positioned at the centroid of the portion which is not modelled. The theoretical torsional natural frequencies are computed from the expression \ud835\udc5b = (2\ud835\udc5b\u22121) 4\ud835\udc3f \u221a \ud835\udc3a \ud835\udf0c where \ud835\udc5b = 1 2 3 \u2026 The frequency \ud835\udc5b has been normalized to have the units of Hz. Case (e) Rigid Virtual Part, Torsional Vibration: Here, the 50 mm right end of the bar is replaced with a \u201cRigid\u201d virtual part, as shown in Fig. 17. Since only torsional vibration is considered, the exact location of the handler point is irrelevant. However, it is placed at the centroid of the virtual part as in the previous cases. In the case of pure torsion, the translational mass of the virtual part does not contribute to the analysis, whereas its rotary inertia about the Z-axis is the determining factor. The value of the rotary inertia is calculated below. \ud835\udc49\ud835\udc43 \ud835\udf03\ud835\udc67 = 1 2 \ud835\udc5a\ud835\udc49\ud835\udc43\ud835\udc45 2 = \ud835\udf0b 2 \ud835\udf0c\ud835\udc3f\ud835\udc49\ud835\udc43\ud835\udc45 4 = 6.17\ud835\udc38 \u2212 6 \ud835\udc58\ud835\udc54.\ud835\udc5a2 The theoretical solution of this problem comes from a frequency equation which closely resembles that of \u201cRigid\u201d virtual part in axial vibration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure47-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure47-1.png", + "caption": "Figure 47: The safety mechanical stops (in green color). Left: Inversion/eversion, Right: Dorsiflexion/plantarflexion [131].", + "texts": [ + ".................................................. 67 Figure 45: Using a 45 (Deg) bubble level to assess the accuracy of angular measurements. The reference tool (A: Precision 45\u201d miter with bubble level) was used to set three different refernce angles (B: 0\u00b0, C: 45\u00b0 and D: -45\u00b0) and the data readouts were recorded in the LabVIEW program. ......... 68 Figure 46: The adjustable chair with risers. ................................................................................................ 70 Figure 47: The safety mechanical stops (in green color). Left: Inversion/eversion, Right: Dorsiflexion/plantarflexion [131] ............................................................................................................... 71 Figure 48: The compoenents of vi-RABT. Subject is seated on an adjustable chair (3); His foot is strapped into the the robotic ankle trainer (1); The real-time machine (4) controls the 2-DOF robotic footplate (1); The 3-D display is used to project the virtual reality game (2); The subject is instructed to control the virtual avatar on the screen via moving the footplate (1); Therapist enters the required parameters and objectively monitors the ongoing experiment (5)", + " In order to limit the maximum angle along each axis, mechanical stops have been implemented underneath the corresponding DOF, as depicted in Figures 52-53. These act as a hard-limiter to prevent over rotation of the footplate. Accordingly the maximum rotation on the INEV axis was limited to 40\u00b0 of rotation, shown in Figure 52. The maximum rotation on the DFPF axis is 60\u00b0 of rotation. The stop on this axis was built into the frame using a cross beam from the 8020. The stop for this axis can be seen in Figure 47 and is highlighted in green. This is adjustable based on therapist decision and is a backup protection in case of software failure. As explained in the previous section, the patient\u2019s foot will be strapped into the bindings on the footplate. This is to provide the maximum control over the ankle joint. However having the patient\u2019s foot tight on the footplate will raise the risk of damage to the tissue in uncontrolled 72 situations, such as falls or excessive power. This problem will become more serious by considering the maximum producible torque (300% of the rated toque) of the motors" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureB.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureB.7-1.png", + "caption": "Figure B.7: Flexure-based finger. Top, non-symmetrical elliptic notch hinges; bottom, conceptual notch designs [1].", + "texts": [ + " Page 38 The flexure joints are optimized in the actuation direction with interest in an ellipsis compliance in the contact point. However, the publications did not show special attention for the compliance in the unwanted direction and the influence in the load-carrying capacity. Reported weight: 400 g. [76]. B.2.5 University of Wollongong [1] Researchers presented a flexure-based finger aimed for prosthetic applications. It consisted of three notch joints. Three conceptual notch designs were presented: a leafspring with round corners; a circular notch; and, an elliptical notch (Fig. B.7). The thickness (3 mm) and length of all elements was constant for all hinges. The study is based on the compliance in the actuation direction. A Finite Element Analysis and validation were done with 5% relative error in the displacements of the end effector. Page 39 However, analysis on the stresses were not presented. The selected material was an elastomer, which makes sense for that thickness and the large range of motion. Hysteresis was shown in flexion-extension of the finger, and it was attributed to material hysteresis and friction in the channels of the tendon" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001734_e_download_2825_3901-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001734_e_download_2825_3901-Figure5-1.png", + "caption": "Figure. 5. Displacement at 50% of the engine load", + "texts": [ + "014686 Mpa at 90% of the engine load and 0.014076 Mpa at 100% of the engine load. An object moving from one point to another point caused by a given certain force. It is different between one end with another end called displacement because the forces that work on the turbine is considered 0 Nm but on the compressor side there is still has some value that works and it bigger than 0 Nm. Thus, it leads to a twisting moment. As an example, the result of displacement simulation at 50% of the engine load is in Figure 5. The largest displacement is obtained about 2.70028 x 10-5 mm. Another displacement result of some loads are 2.59675 x 10-5 mm at 60% of the engine load, 2.55532 x 10-5 mm at 70% of the engine load, 2.51391 x 10-5 mm at 80% of the engine load, 2.4932 x 10-5 mm at 90% of the engine load and 2.38966 x 10-5 mm at 100% of the engine load. The strain is closely related to pulling of an object. The greater value of the strain will increasingly stretch the object and opposite. From the simulation result obtained that the maximum strain is located on the compressor seat as same as stress area with the value equal to 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure3-1.png", + "caption": "Figure 3. Shape and name of RFPM and AFPM motor.", + "texts": [ + " Therefore, motors used in collaborative robot joints design elements of miniaturization, high torque, and high control performance [6\u20138]. The axial flux permanent magnet (AFPM) motor proposed in this paper has a higher torque density than the radial flux permanent magnet (RFPM) motor. The AFPM motor is advantageous for torque density, power density, high efficiency, and miniaturization compared to RFPM motor with the same volume and weight [9\u201314]. Machines 2023, 11, 445. https://doi.org/10.3390/machines11040445 https://www.mdpi.com/journal/machines Figure 3 shows the shape and name of the RFPM motor and the AFPM motor [15]. The torque of the RFPM motor is proportional to the square of the motor diameter, as shown in Equation (1). In here, ac is specific electric loading, kw is winding coefficient, and Bg1 is a fundamental of airgap magnetic flux density. Tradial = ( 1 4 ac\u03c0kwBg1cos\u03b2 ) D2Lstk (1) The torque of the AFPM motor is proportional to the cube of the motor diameter, as shown in Equation (2). As the AFPM motor can increase the permanent magnet usage at the same volume, it has high torque and high efficiency characteristics compared to the RFPM motor [16\u201320]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001023_article-file_2203208-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001023_article-file_2203208-Figure13-1.png", + "caption": "Fig. 13: The Limiters", + "texts": [ + " A set of adjustable limit switches is installed on a garage door opener to turn off the motor when the door is in the fully raised or fully lowered position. A numerical control machine such as a lathe should have limit switches to define maximum limits for machine parts or to provide a known reference point for incremental movements. Therefore, in our system, we also used limiters to control movement limits in the system and obtain more useful results. An example of the limiter in the system is shown in Figure 13. Arduino Uno is a microprocessor development board based on ATmega 328 (Figure 14). The card has 14 digital input/output connections (of which 6 can be used as a P W M output), 6 analog inputs, a 16 Mhz crystal oscillator, a USB connection, a power connection, an ICSP connection, and a reset button. Connecting to the computer via the USB port is sufficient for the card to work. In addition, it can also be used with a battery or an adapter. In the machine designed in this study, we used AT mega 328" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004509_i_10.3233_ATDE230467-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004509_i_10.3233_ATDE230467-Figure1-1.png", + "caption": "Figure 1. Structure of a harmonic drive.", + "texts": [ + " This paper provides a technical reference for the optimization and improvement of the lifespan of POM FS. Keywords. Harmonic drive, flexspline, POM, FEM, fatigue life The harmonic drive, also known as a strain wave transmission system, represents a high-precision reduction mechanism that employs a unique gear design, offering exceptional torque capacity and precision, and is the preferred choice for various industrial applications [1]. It is mainly comprised of components such as the wave generator (WG), flexible bearing (FB), flexspline (FS), and circular spline (CS), as presented in figure 1. The FS is a thin-walled cylinder with external teeth that can generate significant radial elastic deformation with the support of WG. It engages with the CS through differential teeth to achieve axial output. These crucial components of the harmonic drive work collaboratively to enable transmission with high precision, high torque, low noise, and high reliability. Plastic gears have advantages of self-lubrication, lightweight construction, low noise, corrosion resistance, and low cost [2]. Advancement in high-strength plastic materials and precision injection molding technology has enabled plastic gears to evolve from simple motion transmission to complex power transmission [3]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004544__39_article-p159.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004544__39_article-p159.pdf-Figure2-1.png", + "caption": "Fig. 2 Spherical triangle of the universal joint", + "texts": [ + " Therefore, use of the kinematic mechanism with one universal joint is possible only for small axis deviation \u03b1. If the axis deviation \u03b1 will increase, then the value of angular velocity and angular acceleration of the driven shaft will also increase during the rotation of the driven shaft. This can lead to the formation of undesirable vibrations that are transferred to the environment (3, 4). The kinematics of the universal joint is described through a spherical triangle which consists of a path of the points on the axes of the universal joint. In the case of the spherical triangle (Fig. 2), cosine theorem is applied cos\ud835\udc4e = cos\ud835\udc4f. cos\ud835\udc50 + sin\ud835\udc4f. sin\ud835\udc50. cos\ud835\udefc1 [1] If \ud835\udc4e = 90\u00b0, \ud835\udc4f = 90\u00b0 + \ud835\udf111 , c = \ud835\udf111 \u2032 then sin\ud835\udf111 .cos\ud835\udf111 \u2032 cos\ud835\udf111 .cos\ud835\udf111 \u2032 = cos\ud835\udf111 .sin\ud835\udf111 \u2032 .cos\ud835\udefc1 cos\ud835\udf111 .cos\ud835\udf111 \u2032 tg\ud835\udf111 = tg\ud835\udf111 \u2032 . cos\ud835\udefc1 [2] From the equations, it is clearly seen that if the angle \ud835\udefc1 is bigger, subsequently the angle \u03c61 will be smaller and the difference between angles \ud835\udf111 \u2032 and \ud835\udf111 will be bigger. The equation for the solution of the angular velocity has been obtained through derivation of the equation [2]. \ud835\udf141 \u2032 = cos\ud835\udefc1 1\u2212sin2\ud835\udefc1 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure4.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure4.1-1.png", + "caption": "Figure 4.1: Cylinder-Rotor Geometry", + "texts": [ + " With the new vane design presented in Chapter 3, the locus of the vane movement has changed since the tip of the vane is now constrained and its centre now slides along the centreline of the slot. The vane geometric relations form the basis for computing the working chamber volume variations and vane kinematics. These are required in the thermodynamics model and heat transfer relations that will be presented in Chapter 5. In addition, these relations will also be used for modelling the dynamics of the compressor components in Chapter 6. These new geometric dimensions are presented in Figure 4.1 with exaggerated dimensions for clarity. Note that some of the relations have been presented in Chapter 3 and are repeated here for comprehensiveness. 47 Based on the new vane design, the expressions for the geometric relations in Figure 4.1 are presented in Equations (4.1)\u2013(4.5). The first order derivatives and second order derivatives of these relations with respect to the cylinder rotation angle can be found in Equations (4.6)\u2013 (4.10) and are used for the kinematics and dynamics modelling in Chapter 6. \ud835\udc5f\ud835\udc63\ud835\udc5f = \u221a\ud7002 + \ud835\udc5f\ud835\udc63\ud835\udc50 2 \u2212 2\ud700\ud835\udc5f\ud835\udc63\ud835\udc50 cos \ud703\ud835\udc50 (4.1) \ud835\udc5f\ud835\udc5f 2 = \ud835\udc5f\ud835\udc5f\ud835\udc50 2 + \ud7002 \u2212 2\ud835\udc5f\ud835\udc5f\ud835\udc50\ud700 cos \ud703\ud835\udc50 \ud835\udc5f\ud835\udc5f\ud835\udc50 = \ud700 cos \ud703\ud835\udc50 + \u221a\ud835\udc5f\ud835\udc5f2 \u2212 (\ud700 sin \ud703\ud835\udc50)2 (4.2) sin \ud703\ud835\udc63 = \ud700 \ud835\udc5f\ud835\udc63\ud835\udc5f sin \ud703\ud835\udc50 (4.3) cos \ud703\ud835\udc63 = \ud835\udc5f\ud835\udc63\ud835\udc50 2 + \ud835\udc5f\ud835\udc63\ud835\udc5f 2 \u2212 \ud7002 2\ud835\udc5f\ud835\udc63\ud835\udc50\ud835\udc5f\ud835\udc63\ud835\udc5f (4.4) \ud703\ud835\udc5f = \ud703\ud835\udc50 + \ud703\ud835\udc63 (4.5) First order derivatives: \ud835\udc51\ud835\udc5f\ud835\udc63\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 = \ud700\ud835\udc5f\ud835\udc63\ud835\udc50 \ud835\udc5f\ud835\udc63\ud835\udc5f sin \ud703\ud835\udc50 (4", + " This would be useful for future design work when miniaturisation of the RV mechanism would cause the thickness of the vane to be significant when compared to the radius of the rotor and cylinder. It is first assumed that the vane is infinitesimally thin [15] and the resulting working chamber volume and dead volume from the vane slot is computed before subtracting the volume of the vane for the exact working volume. Figure 4.2 shows an enlarged section of the vane tip and slot with the geometric features highlighted for the breakdown in volume calculation. 49 From Figure 4.1, the volumes of the working chambers with negligible vane volume are expressed as shown in Equations (4.12) and (4.13) while the variations of the working chambers with respect to the cylinder rotation angle are expressed in Equations (4.14) and (4.15). \ud835\udc49\ud835\udc61\u210e\ud835\udc56\ud835\udc5b,\ud835\udc60\ud835\udc62\ud835\udc50 = \ud835\udc59\ud835\udc50 2 \u222b (\ud835\udc5f\ud835\udc50 2 \u2212 \ud835\udc5f\ud835\udc5f\ud835\udc50 2 ) \ud835\udc51\ud703\ud835\udc50 \ud835\udf03\ud835\udc50 0 = \ud835\udc59\ud835\udc50 2 [(\ud835\udc5f\ud835\udc50 2 \u2212 \ud835\udc5f\ud835\udc5f 2)\ud703\ud835\udc50 \u2212 1 2 \ud7002 sin 2\ud703\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc5f 2\ud835\udefe \u2212 \ud700 sin \ud703\ud835\udc50 \u221a\ud835\udc5f\ud835\udc5f2 \u2212 \ud7002 sin2 \ud703\ud835\udc50] (4.12) \ud835\udc49\ud835\udc61\u210e\ud835\udc56\ud835\udc5b,\ud835\udc50\ud835\udc5c\ud835\udc5a = \ud835\udc59\ud835\udc50 2 \u222b (\ud835\udc5f\ud835\udc50 2 \u2212 \ud835\udc5f\ud835\udc5f\ud835\udc50 2 ) \ud835\udc51\ud703\ud835\udc50 2\ud835\udf0b \ud835\udf03\ud835\udc50 = \ud835\udf0b\ud835\udc59\ud835\udc50(\ud835\udc5f\ud835\udc50 2 \u2212 \ud835\udc5f\ud835\udc5f 2) \u2212 \ud835\udc49\ud835\udc61\u210e\ud835\udc56\ud835\udc5b,\ud835\udc60\ud835\udc62\ud835\udc50 (4.13) Derivatives: \ud835\udc51\ud835\udc49\ud835\udc61\u210e\ud835\udc56\ud835\udc5b,\ud835\udc60\ud835\udc62\ud835\udc50 \ud835\udc51\ud703\ud835\udc50 = \ud835\udc59\ud835\udc50 2 (\ud835\udc5f\ud835\udc50 2 \u2212 \ud835\udc5f\ud835\udc5f\ud835\udc50 2 ) (4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002053_e_download_2200_1306-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002053_e_download_2200_1306-Figure21-1.png", + "caption": "Figure 21: Initial experimental setup", + "texts": [ + " The use of these ESP32 boards is much more effective as the two boards aren\u2019t directly connected to one another, meaning the user doesn\u2019t have to stand right next to the computer in order for the system to work, they just need to be close enough to be visible to the pose detection algorithm. ISSN: 2167-1907 www.JSR.org 16 Experimental Validation Experimental Setup To ensure the safety of the user, while the exoskeleton is being used on the user\u2019s body, the metallic string will remain relaxed throughout, and there will be no force from the reel or the servo. Additionally, the movement of the human joints will be simulated using a setup to determine the experimental results. As seen from figure 21, the initial experimental setup comprises the core elements of the system, which in- clude the servo, reel, outer shell, metallic string, and an elastic element. As aforementioned, in consideration of the experimenting user, a metallic stand is used in place of the human lower body, where a hinge that can turn vertically is used to mimic the human knee joint. As the lower extremities are no longer required, the shin pad is also disregarded in this setup as we don\u2019t need to connect the elastic element with the lower body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001671_O201325954480036.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001671_O201325954480036.pdf-Figure8-1.png", + "caption": "Fig. 8 Frequency responses of amplitude deformations", + "texts": [ + " \uc2e4\uc81c\uc801\uc73c\ub85c \ud558\uc911\uc774 \uc0c1\ub2f9\ud788 \uc791\uc544\uc9c4\ub2e4 \ud558\ub354\ub77c\ub3c4 \ub4f1\uac00\uc751\ub825\uc774\ub098 \ucd5c\ub300\uc751\ub825\uc774 \uadf8\ub2e4 \uc9c0 \uc791\uc544\uc9c0\uc9c0\ub294 \uc54a\uc558\uc73c\uba70, \uacf5\uc9c4\uc758 \uacbd\uc6b0\ub3c4 \uc704\uc5d0 \ub098\ud0c0\ub09c \uacf5\uc9c4\uc218 \uc774\uc0c1 \ub098\ud0c0\ub098\uc9c0 \uc54a\uc558\ub2e4. \ucc28\ub7c9\uc740 \uc8fc\ud589 \uc911 60\uff5e120 cycle/min (1\uff5e2 Hz) \uc758 \uc9c4\ub3d9\uc218\uc5d0\uc11c \uac00\uc7a5 \uc88b\uc740 \uc2b9\ucc28\uac10\uc744 \ubcf4\uc774\uba70 \ud604\uac00\uc7a5\uce58\ub294 \uc774 \ubc94\uc704 \ub0b4 \uc5d0\uc11c \uc124\uacc4\ub41c\ub2e4 [8] . \ub610\ud55c \uc774 \uacb0\uacfc\uc5d0\uc11c \ubcf4\uba74 \uc8fc\ud589 \uc911 157 Hz\uc640 222 Hz\uc5d0\uc11c \uacf5\uc9c4\uc774 \ubc1c\uc0dd\ud558\ub098 \uc2e4\uc81c\uc0c1\uc5d0\uc11c\ub294 \uc774\ubcf4\ub2e4 \ud6e8\uc52c \ub0ae\uc740 \uc9c4\ub3d9\uc218\ub85c \uc6b4\ud589\ub418\uae30 \ub54c\ubb38\uc5d0 \uc2b9\ucc28\uac10\uc774 \uc88b\ub3c4\ub85d \uc124\uacc4\ub97c \ud560 \uc218 \uc788\ub2e4\ub294 \uac80\uc99d \uacb0\uacfc \ub97c \ubcf4\uc600\ub2e4. \uadf8\ub9ac\uace0 \uc2e4\uc81c\uc801\uc73c\ub85c Fig. 2 \ubc0f Fig. 3\uc5d0\uc11c\uc640 \ub611\uac19\uc774 \uc55e \ubc94\ud37c\uc758 \uc55e\uba74\uc5d0 Force\ub97c 2500 N\uc758 \uad6c\uc18d\uc744 \uc8fc\uc5b4, \uc55e \ubc94\ud37c\uc5d0 \uc0dd\uae30\ub294 \ud558\ubaa8\ub2c9 \uc9c4\ub3d9\uc5d0 \ub300\ud558\uc5ec \ud574\uc11d\ud574 \ubcf4\uc558\ub2e4. \uc9c4\ub3d9\uc218\uc758 \ubc94\uc704\ub294 230 Hz\uae4c \uc9c0\ub85c \uc124\uc815\ud558\uc600\ub2e4. \uc55e\uc5d0 Modal \ud574\uc11d\uc758 \uacb0\uacfc\ub97c \ubcf4\uac8c \ub418\uba74 6\ucc28 \ubaa8\ub4dc \uc758 \uace0\uc720\uc9c4\ub3d9\uc218\uac00 230 Hz\ubc94\uc704 \ub0b4\uc5d0 \uc788\uae30 \ub54c\ubb38\uc5d0 \uac00\uc9c4 \uc8fc\ud30c\uc218 \uc601\uc5ed \uc744 \ub9de\ucdb0 \uacf5\uc9c4 \uc8fc\ud30c\uc218\ub97c \ud655\uc778\ud558\uc600\ub2e4. Model 1\uacfc 2\uc5d0 \ub300\ud558\uc5ec \uc9c4\ub3d9\uc218 \uc5d0 \ub300\ud55c \uc9c4\ud3ed \ubcc0\uc704 \uc751\ub2f5\uc744 \uc0b4\ud3b4 \ubcf8 Fig. 8(a), (b)\uc5d0\uc11c \ubcf4\uba74 \uc54c \uc218 \uc788\ub4ef\uc774 Model 1\uc740 159 Hz\uc5d0\uc11c\uc640 Model 2\ub294 110 Hz\uc758 \uc704\ud5d8 \uc9c4 \ub3d9\uc218\ub97c \uac01\uac01 \ub098\ud0c0 \ub0b4\uc5c8\ub2e4. \uc774\ub7ec\ud55c Model 1\uacfc 2\uc5d0 \ub300\ud55c \uc704\ud5d8 \uc9c4\ub3d9 (c) Natural frequency at 3'rd (d) Natural frequency at 4'th Table 3 Maximum total deformation and natural frequency per mode at model 1 Frequency (Hz) Total deformation (mm) 1\u2019st Mode 69.85 18.42 2\u2019nd Mode 77.302 19.189 3\u2019rd Mode 138.95 28.845 4\u2019th Mode 157.88 62.671 5\u2019th Mode 171.46 25.46 6\u2019th Mode 199.68 24.944 Table 4 Maximum total deformation and natural frequency per mode at model 2 Frequency (Hz) Total deformation (mm) 1\u2019st Mode 43", + " \ub530\ub77c\uc11c Model 1\uacfc 2\uc5d0\uc11c\uc758 159 Hz\uc640 110 Hz\uc758 \uc704\ud5d8 \uc9c4\ub3d9\uc218\uc5d0\uc11c Model 1\uacfc 2\uc758 \uc2e4\uc81c\uc801\uc778 \ub4f1\uac00 \uc751\ub825\uacfc \uc804\ubcc0\ud615\ub7c9\uc740 \uac01\uac01 Fig. 9(a), (b) \ubc0f Fig. 10(a), (b)\uacfc \uac19\uc774 \ub098\ud0c0\ub0ac\ub2e4 [9] . 4. \uacb0 \ub860 \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 \uc8fc\ud589 \uc911\uc778 \uc790\ub3d9\ucc28 \uc55e \ubc94\ud37c\uc5d0 \ub300\ud55c \uad6c\uc870 \ubc0f \uc9c4\ub3d9\uc5d0 \ub530\ub978 \uac15\ub3c4 \ub0b4\uad6c\uc131\uc744 \ud574\uc11d\ud558\uc600\ub2e4. \uc774\uc5d0 \ub300\ud574 \uc5f0\uad6c\ud55c \uacb0\uacfc\ub294 \ub2e4\uc74c\uacfc \uac19\ub2e4. \uad6c\uc870\ud574\uc11d \uacb0\uacfc, Mode1\uacfc Mode2 \uc55e \ubc94\ud37c\uc758 \ucd5c\ub300\uc758 \ub4f1\uac00\uc751\ub825\uc774 \uac01\uac01 187.09 MPa \ubc0f 278.4 MPa\uc774\uace0, \ubcc0\ud615\ub7c9\uc774 \uac01\uac01 1.3772 mm \ubc0f 2.675 mm\ub85c\uc11c \ucd5c\ub300\ub85c \ub098\ud0c0\ub0ac\ub2e4. 2\ubc88 \ubaa8\ub378\uc774 1\ubc88 \ubaa8\ub378\ubcf4\ub2e4 \ub354 \ubcc0\ud615\ub418\ub294 \uac83\uc744 \uc54c \uc218 \uc788\ub2e4. \ub610\ud55c Model 1\uacfc Model 2\uc5d0\uc11c \uace0\uc720\uc9c4 \ub3d9\uc218\ub294 \uacf5\ud788 230 Hz\uc774\ub0b4\uc5d0\uc11c \uc77c\uc5b4\ub0a8\uc744 \uc54c \uc218 \uc788\uc73c\uba70 \uc2e4\uc81c\uc801\uc73c\ub85c \ubcc0\ud615\uc774 \uc26c\uc6b0\uba70 \uacf5\uc9c4\uc774 \uc77c\uc5b4\ub0a0 \uac00\ub2a5\uc131\uc774 \ud070 \uac83\uc73c\ub85c \ubcf4\uc774\ub294 Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc758 \uc9c4\ub3d9\uc218\ub294 157.88 Hz\uc774\uace0 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc758 \uc9c4\ub3d9\uc218\ub294 222.41 Hz\uc774\ub2e4. \ub610\ud55c \uc9c4\ub3d9\uc218 \uc751\ub2f5\uc744 \ubcf8 Fig. 8(a), (b)\uc5d0 \uc11c \ubcf4\uba74 \uc54c \uc218 \uc788\ub4ef\uc774 Mode1\uc740 159 Hz\uc5d0\uc11c\uc640 Mode2\uc740 110 Hz \uc5d0\uc11c \ucd5c\ub300\uc758 \uc9c4\ud3ed\ubcc0\uc704\uac00 0.105 mm\uc640 0.154 mm\ub85c \uc0dd\uae40\uc744 \uc54c \uc218 \uc788\ub2e4. \uacf5\uc9c4\uc8fc\ud30c\uc218 \ud074\uc218\ub85d \ubaa8\ub378\uc758 \ub0b4\uad6c\uc131\uc774 \uc591\ud638\ud558\uc5ec Mode1\uc758 \ub0b4 \uad6c\uc131\uc774 Mode2\ubcf4\ub2e4 \ub354 \uc88b\uc740 \uac83\uc744 \ubcfc \uc218 \uc788\ub2e4. \ubcf8 \uc5f0\uad6c\uc758 \uacb0\uacfc\ub97c \uc885\ud569\ud558\uc5ec \uc790\ub3d9\ucc28 \uc55e \ubc94\ud37c\uc758 \uc124\uacc4\uc5d0 \uc751\uc6a9\ud55c\ub2e4\uba74 \uadf8 \uad6c\uc870\uac15\ub3c4 \ubc0f \ub0b4\uad6c\uc131\uc744 \uac80\ud1a0, \uc608\uce21\ud558\ub294\ub370 \ud65c\uc6a9\uc774 \ud074 \uac83\uc73c\ub85c \uc0ac\ub8cc \ub41c\ub2e4. [1] Sohn, I. S., Lee, J. G., 2008, A Study of Electrical Control Kit for Damping Force of Automotive Shock Absorber, Transactions of KSAE., 16:3 1-6. [2] Mariot, J. P., K'nevez, J. Y., Barbedette, B., 2004, Tripod and Ball Joint Automotive Transmission Kinetostatic Model Including Friction, Multibody System Dynamics, 11:2 127-145" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.12-1.png", + "caption": "Figure 1.12. Ballamy swing axle IFS [2].", + "texts": [ + " In contrast, an independent suspension is designed to have a vertical degree-of-freedom (DOF), upon which separate springs and dampers may act. Independent suspensions had actually been around for a number 9 of years prior to GM\u2019s realization of their merits in the 1930s. The first production car to have an IFS was the Decauville, circa 1898, which used a sliding pillar IFS. A drawing of this type is seen in Figure 1.11. Another early independent suspension approach was the swing axle. This amounted to allowing each \u201chalf\u201d of the axle to swing independently, Figure 1.12. Some designs of this type were even employed as rear suspensions, and used the drive axle as one of the arms. The design favored by GM was the double wishbone, also known as the short-long-arm (SLA), seen in Figure 1.13. In addition to leaf springs and coil springs, torsion springs were also in use. An example can be seen in Figure 1.14. In this figure, there is also a hydraulic shock absorber. As the century went along, the MacPherson strut suspension, Figure 1.15, introduced in the late 1940s, became an increasingly popular IFS" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002506_.srce.hr_file_390601-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002506_.srce.hr_file_390601-Figure5-1.png", + "caption": "Figure 5 The size of the contact surface depending on the curvature at the point of contact of the tool with the blade: a) small internal curvature; b) large internal curvature", + "texts": [ + " Typically, the impact of selected, only the most relevant parameters is analyzed and taken into account in the given case. This paper presents the issue of machining a real blade whose shape is complex. The variable curvature of the blade makes the dependence on the contact force more complicated. The desired contact force also depends on the place where the tool is applied to the blade, i.e. the coordinates of the application point of the tool to the blade C: xC, yC, zC. An explanation of this dependence is presented in Fig. 5, which shows an example of a crosssection of a blade. A tool that has a deformable layer is also shown. Depending on the curvature of the blade, the parameter c is changed, which is a measure of the size of the contact surface: in the case of small internal curvatures, the parameter c has a small value which increases with the increase of the curvature of the surface. In the case of external curvatures, the dependence is reversed. In the analyzed bibliography, such an approach to the problem was not encountered" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001293_O201226935181464.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001293_O201226935181464.pdf-Figure11-1.png", + "caption": "Fig. 11 Magnetization curve for SRM", + "texts": [ + " Te J 0 d\u03c9r dt -------- B 0 \u03c9r f+ += f \u2206J d\u03c9r dt -------- \u2206B\u03c9r TL+ += TL RL Rc Rg Ri+ + += RL AR BR VR CR VR 2 \u22c5+\u22c5+= CR VR 2 \u22c5 s x c 1 x t( ) td \u221e t \u222b+ 0= = u ueq \u2206u+= s\u00b7 0= ueq 1 b 0 ---- a 0 c 1 +( )x a 0 \u03c9r * +[ ]\u2013= \u2206u \u03c8 1 x \u03c8 2 += 1 2 -- d dt ---- s 2 ( ) 0< \u03c8 1 \u03b1 1 0 : if sx 0<< \u03b2 1 0 : if sx 0><\u23a9 \u23a8 \u23a7 = \u03c8 2 \u03b1 1 d 0 b 0 ----\u2206f max : if s 0<\u2013> \u03b2 2 d 0 b 0 ----\u2206f min : if s 0>\u2013< \u23a9 \u23aa \u23aa \u23a8 \u23aa \u23aa \u23a7 = Fig. 9\ub294 SRM\uc758 PI \uc81c\uc5b4 \ube14\ub85d\ub3c4\ub97c \ub098\ud0c0\ub0b8\ub2e4. Fig. 9 Block diagram of PI controller for SRM drive SRM\uc740 \uac01 \uc0c1\uc5d0 \uc5f0\uacb0\ub41c \uac01\uac01\uc758 \ucee8\ubc84\ud130\uc5d0 \uc758\ud574 \uc81c\uc5b4\ub41c\ub2e4. \ubcf8 \ub17c\ubb38\uc5d0\uc11c \uc0ac\uc6a9\ud55c 3\uc0c1 \ube44\ub300\uce6d \ucee8\ubc84\ud130\ub97c Fig. 10\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. 5. \uc2dc\ubbac\ub808\uc774\uc158 \uacb0\uacfc \uc774 \uc7a5\uc5d0\uc11c\ub294 2\uc7a5\uc5d0\uc11c \uc5bb\uc740 SRM\uc758 \uc790\uc18d\ud2b9\uc131\uacfc \uc124\uacc4\ubaa8\ub378 \ubc0f 3\uc7a5\uc5d0\uc11c \uc124\uacc4\ud55c \uc81c\uc5b4\uae30\ub97c \ud1b5\ud574 \uc18d\ub3c4 \uc81c\uc5b4 \uc2dc\ubbac\ub808\uc774\uc158\uc744 \uc218\ud589\ud558\uace0 \uadf8 \uacb0\uacfc\ub97c \ube44\uad50\ud55c\ub2e4. PI \uc81c\uc5b4\uae30\uc640 \uc2ac\ub77c\uc774\ub529\ubaa8\ub4dc \uc81c \uc5b4\uae30\ub97c \uc124\uacc4\ud558\uc5ec \uadf8 \ud2b9\uc131\uc744 \ube44\uad50\ud558\uc600\ub2e4. \uc124\uacc4\ub41c SRM\uc744 \uc774\uc6a9\ud558\uc5ec \uc18d\ub3c4 \uc81c\uc5b4 \uc2dc\ubbac\ub808\uc774\uc158\uc744 \uc218\ud589\ud558 \uae30 \uc704\ud574 4.2\uc808\uc5d0\uc11c \uc124\uacc4\ud55c SRM\uc758 \ud68c\uc804\uc790 \uc704\uce58\uc5d0 \ub530\ub978 \uc804 \ub958-\uc790\uc18d\uace1\uc120\uc744 \uc774\uc6a9\ud558\uc5ec SRM \ubaa8\ub378 \ube14\ub85d\uc744 \uad6c\uc131\ud558\uc600\ub2e4. \ud574 \uc11d\ud55c SRM\uc758 \ud68c\uc804\uc790 \uc704\uce58\uc5d0 \ub530\ub978 \uc804\ub958-\uc790\uc18d \uace1\uc120\uc744 Fig. 11 \uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \uc804\ub958\uc5d0 \ub300\ud55c \uc1c4\uad50 \uc790\uc18d\uc740 \uc804\uc555 v, \uc804\ub958 i, \uad8c\uc120\uc758 \uc800\ud56d\uc744 R\uc774\ub77c \ud558\uba74 \uc2dd (17)\uacfc \uac19\uc774 \uad6c\ud560 \uc218 \uc788\ub2e4. (17) SRM\uc758 \ud1a0\ud06c\ub294 \uc2dd (18)\uacfc \uac19\uc774 \ud68c\uc804\uc790\uc758 \uc704\uce58\uc5d0 \ub530\ub978 \ucf54 \uc5d0\ub108\uc9c0\uc758 \ubcc0\ud654\uc728\ub85c \ub098\ud0c0\ub0bc \uc218 \uc788\uc73c\uba70 \uc804\ub958\uc758 \ubd80\ud638\uc640\ub294 \uc0c1\uad00 \uc5c6\uc774 \ud68c\uc804\uc790\uc758 \uc704\uce58 \u03b8\uc5d0 \ub530\ub978 \uc778\ub355\ud134\uc2a4\uc758 \ubcc0\ud654\ub7c9\uc5d0 \ub530\ub77c \uacb0 \uc815\ub41c\ub2e4. (18) Fig. 11\uc758 \ub370\uc774\ud130 \uac12\uacfc \uc2dd (18)\uc744 \uc774\uc6a9\ud558\uc5ec \ud1a0\ud06c\ub97c \uacc4\uc0b0\ud558 \uc600\uc73c\uba70 \uc804\ub3d9\uae30 \ubd80\ud558\ub294 \uc2dd (8)\ub85c \ubaa8\ub378\ub9c1 \ub41c \uc5f4\ucc28 \ubd80\ud558\ub97c \uc774 \uc6a9\ud558\uc5ec \uc2dc\ubbac\ub808\uc774\uc158\uc744 \uc218\ud589\ud558\uc600\ub2e4. Fig. 12\ub294 \uae30\uc900\uc804\ub958 200A\uc77c \ub54c a\uc0c1\uc758 \uc804\ub958\uba85\ub839\uacfc \uc2e4\uc81c \uc804 \ub958 \uc751\ub2f5\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub798\ud504\uc774\ub2e4. \uc124\uc815\ud55c on/off \uc2a4\uc704\uce6d \uac01\ub3c4\uc640 \uae30\uc900\uc804\ub958\uc5d0 \ub530\ub77c \uc0c1\uc804\ub958 \uba85\ub839\uc744 \ub9cc\ub4e4\uace0, \uc2e4\uc81c\uc804\ub958\ub294 \ud788\uc2a4\ud14c \ub9ac\uc2dc\uc2a4 \uc804\ub958 \uc81c\uc5b4\uae30\ub97c \ud1b5\ud574 \uc804\ub958\uba85\ub839\uc5d0 \ucd94\uc885\ud558\ub294 \uac83\uc744 \ud655\uc778 \ud560 \uc218 \uc788\ub2e4. Fig. 13\uc740 \ub3d9\uc77c \uc870\uac74\uc5d0\uc11c 3\uc0c1\uc758 \uc790\uc18d\uacfc \uc804\ub958 \ubc0f \ud569\uc131 \ud1a0\ud06c \ud30c\ud615\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub798\ud504\uc774\ub2e4. \uc124\uc815\ud55c on/off \uc2a4\uc704\uce6d \uac01\uc5d0 \uc758\ud574 3\uc0c1\uc774 \ubc88\uac08\uc544 \uac00\uba70 \uc2a4\uc704\uce6d \ub418\ub294 \uac83\uc744 \ud655\uc778\ud560 \uc218 \u03bb t( ) v iR\u2013( ) td 0 t \u222b= T dWm d\u03b8 ---------- i 2 2 --- dL d\u03b8 -----= = \uc788\uc73c\uba70, \uc774\ub54c\uc758 \uc790\uc18d \ubc0f \uc138 \uc0c1\uc758 \ud569\uc131 \ud1a0\ud06c\uac00 \ub098\ud0c0\ub0a8\uc744 \ubcfc \uc218 \uc788\ub2e4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure7-1.png", + "caption": "Figure 7. 3-D FEA model of the cooling water channel.", + "texts": [ + " Hence the following assumptions in the FEA calculation are given by: (1) Only the convective and conduction heat transfer are considered; (2) The heat sources are uniformly distributed on the corresponding regions of the CS-PMSM. According to the symmetrical characteristic of the CS-PMSM structure and cooling system in circumferential direction, a 3-D FEA model with half of the CS-PMSM is built to analyze the thermal field, as shown in Figure 6. The 3-D FEA model of the cooling water channel in the stator is shown in Figure 7. In the machine, modeling of the windings and air gap is very important for the thermal field analysis. Hence the model of the windings and air gap will be illustrated in the following text. In 3-D modeling process of the CS-PMSM, to build an accurate model of the windings is quite difficult. This is mainly because the conductors in each coil are randomly distributed inside the slots. The random distribution of the conductors in the slots has a certain influence on the maximum temperature of the windings [47]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003981_20_01_smdo200027.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003981_20_01_smdo200027.pdf-Figure2-1.png", + "caption": "Fig. 2. Comparisons of the two conceptual design of hybrid UAV (a) preliminary design with winglet (b) present design with canard configuration.", + "texts": [ + " With massive precedent researches as well as engineering experience in structural optimization and additive manufacture technologies, our team has invented an innovative conception of Tube-Fan drone characterised with the integration of fixed-wing and tube-fan inside in the wing structure [6], where basic flight modes are included in our hybrid-UAV: (1) cruise mode; (2) VTOL mode; (3) transition mode. In the preliminary conception, though the winglet was added into the delta wing structure to improve the poor aerodynamical performance caused by the low aspect-ratio (see Fig. 2a), this article continues to adopt the canard configuration which is widely preferred in the modern fixed-wing plane conception, with a slight modification in the fuselage part [6] (see Fig. 2b). As the canard wing are installed at the front of the fuselage of the tube-fan UAV, it\u2019s supposed that the lift performance would be increased the lift performance dramatically in the cruise flight mode, as well as its manoeuvrability and low trim drag at the occasion of large angle of attack [7]. Besides, the canard wing would enhance the flight security by preventing into stall thanks to the canard wing while energy economy of the drone is improved by omitting the tail wing part, which would inevitably produce negative lift to keep the attitude balance [8]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003752_20__20Yan_20Qiao.pdf-Figure2.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003752_20__20Yan_20Qiao.pdf-Figure2.13-1.png", + "caption": "Figure 2.13: Orthogonal planes features for multi-LiDAR calibration", + "texts": [ + " In [44] lines in image are extracted in pixel level and lines on the accumulated point cloud are reliably extracted by depthcontinuous edge extraction, voxel cutting and plane fitting as shown in Fig. 2.12. It also careful analyzes the physical principles of non-repetitive scanning solid-state LiDAR and elaborates the robustness with accurate calibration parameters. Since edges are rich in natural scenes, this method is easy to implement in both indoor and outdoor for camera-LiDAR calibration in a targetless environment. Three orthogonal planes are extracted from the environment for extrinsic calibration of multi-LiDARs in [45] as shown in Fig. 2.13. Three linearly independent planar surfaces in the surroundings are detected in two LiDARs point cloud data. Firstly a closed-form solver is developed for initialization and then an optimizer is introduced for refinement by minimizing a nonlinear cost function. This calibration method shows a promising result with lower than 0.4 rad rotation error and smaller than 0.1 meter translation error. Even though it is fully online and there is no need to put up artificial calibration targets, users still need to carefully investigate the environment to select ideal three orthogonal planes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004734_za_pdf_rd_v39_02.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004734_za_pdf_rd_v39_02.pdf-Figure3-1.png", + "caption": "Figure 3 Rotor Test Bench (See Appendix D)", + "texts": [ + "1 8 Motor Speed (r/s) 0 6000 Rated Head Speed (r/s) 3000 Blade Pitch Angle (Deg.) - 5.0 (\u00b10.5) +35.0 (\u00b10.5) Thrust Capacity (Kg) 50 (\u00b10.01) **Construction Stainless Steel & Aluminium Gear Ratio 1:1 **Construction is defined as mechanical components, excluding electronics. **B \u2013 Blade Set, \ud835\udc79\ud835\udc79\ud835\udc8e\ud835\udc8e\ud835\udc8e\ud835\udc8e\ud835\udc8e\ud835\udc8e \u2013 Blade length, \ud835\udc79\ud835\udc79\ud835\udc93\ud835\udc93\ud835\udc93\ud835\udc93\ud835\udc93\ud835\udc93\ud835\udc93\ud835\udc93 \u2013 Annulus Root Radius, \ud835\udc6a\ud835\udc6a \u2013 Chord Length, \ud835\udc69\ud835\udc69 \u2013 Chord Thickness, \ud835\udc83\ud835\udc83 \u2013 Distance from leading edge to thickness B, \ud835\udc74\ud835\udc74\ud835\udc83\ud835\udc83 \u2013 Mass of a single blade, \ud835\udc79\ud835\udc79\ud835\udc88\ud835\udc88 \u2013 Mass Centroid about the X-Axis As illustrated in figure 3, the load cell is positioned such thrust force \ud835\udc47\ud835\udc47 (3) is transmitted to the load cell via reactionary force \ud835\udc39\ud835\udc39 (1) along the Z-axis. Bearing guides sliding on rigidly mounted guides isolate residual reactionary forces \ud835\udc39\ud835\udc39\ud835\udc5f\ud835\udc5f (2) or moments \ud835\udc40\ud835\udc40 (4) about X|Y axes to prevent torsional forces acting on the load cell. Three blade sets were tested at constant speed (\ud835\udc41\ud835\udc41\ud835\udc5f\ud835\udc5f = 1000 \u2212 2500 \ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5f\ud835\udc5a\ud835\udc5a) with a collective pitch of \ud835\udf03\ud835\udf03\ud835\udc56\ud835\udc56\ud835\udc56\ud835\udc56 = 0\ud835\udc5d\ud835\udc5d \u2212 14\ud835\udc5d\ud835\udc5d. Sample data was processed and conditioned in MATLAB before being compared to theoretical performance results" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001456_18_ms-9-327-2018.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001456_18_ms-9-327-2018.pdf-Figure3-1.png", + "caption": "Figure 3. Four-bar mechanism at max. and min. transmission angles.", + "texts": [ + " The wiping action is typically performed by mechanisms that are limited to moving between two prescribed positions. In this section, a two-position synthesis method is implemented to determine link proportions for an appropriate rigid fourbar mechanism to be used for the rigid body replacement synthesis. There are numerous two-position mechanism design methods in the literature. Brodell and Soni (1970) described the synthesis of a crank-rocker mechanism with an optimum transmission angle. In this method, the transmission angle between the coupler and output link (shown as \u03b3 in Fig. 3) deviates the same amount from 90\u25e6 for a full rotation of the crank \u2013 Eq. (1). Therefore, if the undeflected position of the compliant segment is set to \u03b3 = 90\u25e6 during the PRBM replacement synthesis, the deflection of the compliant segment will be the same in both directions. In addition, with Mech. Sci., 9, 327\u2013336, 2018 www.mech-sci.net/9/327/2018/ this method, as the transmission angle (Tan\u0131k, 2011; Balli and Chand, 2002; Alt, 1932) is at an optimum, the motion quality of the synthesized mechanism will be satisfactory", + " (15) During the stress calculations, it was observed that the horizontal component of the force (nP in Fig. 7) yields a negligible amount of stress for the full cycle of the mechanism. Therefore, in order to simplify the solution, we neglect the horizontal component of this force, which yields n= 0. The force that causes the deformation on the compliant segment is given in Eq. (16) (Howell, 2001): P = Bx sin\u03b84\u2212By cos\u03b84, (16) where Bx and By are horizontal and vertical reaction forces at the bearing (O4 at Fig. 3) of the compliant segment, respectively. From Eqs. (15) to (16) and the bending stress formula, the critical stress on the compliant segment is \u03c3 = 6Pa bt2 , (17) where b and t are the width and thickness of the compliant segment, respectively. By using Eq. (17), flexible segment thickness and width are determined iteratively, corresponding to the strength of the material. From this, the link cross-sectional dimensions are determined as t = 1 mm, and b = 30 mm. With these dimensions, the stress of the flexible segment remains in an acceptable range for the complete cycle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002146_11044-013-9375-6.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002146_11044-013-9375-6.pdf-Figure4-1.png", + "caption": "Fig. 4 The kinematical chain of the right lower limb, and the open-constraint coordinates and respective reaction forces in the limb", + "texts": [ + " An advantageous feature of using open-constraint coordinates is that they can be introduced only in those joints in which the reaction forces are to be determined; see [27] for the theoretical background and [20, 23, 28] where the approach was applied to biomechanical modeling. For the triple jump analysis, the open-constraint coordinates can be introduced only in the supporting-leg joints\u2014either the right or left lower limb, depending on the case. Instead of all l = 26 coordinates z = [z1 . . . zl]T , one thus use l\u2032\u2032 = 6 coordinates z\u2032\u2032 = [z15 . . . z20]T for the right leg (Fig. 4), while for the left leg these are z\u2032\u2032 = [z21 . . . z26]T . The respective X and Y components of joint reaction forces are either \u03bb\u2032\u2032 = [\u03bb15 . . . \u03bb20]T or \u03bb\u2032\u2032 = [\u03bb21 . . . \u03bb26]T . The final explicit form of joint constraint equations is p = g(q, z\u2032\u2032) (4) Since, by principle, z\u2032\u2032 = 0, the augmented and traditional formulations of explicit constraint equations, p = g(q, z\u2032\u2032) and p = g(q), are virtually equivalent, and the dependence on z\u2032\u2032 is introduced here only to grasp the directions of z\u0307\u2032\u2032, which are also the directions of constraint reactions \u03bb\u2032\u2032 (Fig. 4). Time differentiation of Eq. (4) leads to p\u0307 = ( \u2202g \u2202q )\u2223\u2223 \u2223\u2223 z\u2032\u2032=0 q\u0307 + ( \u2202g \u2202z\u2032\u2032 )\u2223\u2223 \u2223\u2223 z\u2032\u2032=0 z\u0307 = D(q)q\u0307 + E\u2032\u2032z\u0307\u2032\u2032 (5) where the matrices D and E\u2032\u2032 are of dimensions n \u00d7 r and n \u00d7 l\u2032\u2032, respectively, and E\u2032\u2032 is constant (and simple) for the case of hinge joints in planar systems; see [20, 23, 28] for more details. Evidently, the matrix D introduced in Eq. (5) can also be derived from the traditional formulation p = g(q) as p\u0307 = (\u2202g/\u2202q)q\u0307 \u2261 D(q)q\u0307, and it is an orthogonal complement matrix to the constraint matrix C [24\u201326], i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001569__downloads_6969z181x-Figure4.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001569__downloads_6969z181x-Figure4.13-1.png", + "caption": "Figure 4.13: Discrete p-i-n diode dimensions [91]", + "texts": [ + " This experiment aims to use the diodes as photovoltaic devices under ionizing radiation. Silicon as a semi-conductor is used in a range of visible light wavelengths to generate current and hence useful power. However, using it for the same application under ionizing radiation does not seem possible since higher energy photons beyond the absorption of silicon will pass through without any interactions. Experiments were performed on discrete p-i-n diodes manufactured by 105 Luna Optoelectronics as shown in Figure 4.13 [91]. Figure 4.14 shows the responsivity of the diodes. It can be seen that longer wavelengths have a better responsivity than the shorter wavelengths. Silicon p-i-n diodes either would not interact with ionizing radiation or if they do, recombination rates would be high in an unbiased mode to generate a significant current; therefore, three different scintillating material were chosen and used to compare against the case without any scintillating material on it. As the integrated chip technology has found its way into ultra low power wireless sensor applications, using photodiodes as energy-harvesting devices has gained serious attraction and popularity" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000804_le_1878_context_etdr-Figure2.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000804_le_1878_context_etdr-Figure2.5-1.png", + "caption": "Figure 2.5 Step bar casting used for section size and cooling rate analysis.", + "texts": [ + " Each mold contained four blanks that could be easily turned into tensile bars. These blanks are 0.75 inches (19 mm) in diameter and 8 inches (200 mm) in height (Figure 2.3). These molds were made from an air set chemically bonded sand (Figure 2.4). Each mold half required 22 lbs. of sand, resulting in a total mold weight of 44 pounds of sand. The weight of these casting systems was 11 lbs. 8 9 Two step bar molds were also cast for each heat. The bar has steps that were 0.25, 0.5, 0.75, and 2 inches high. This mold was made from green sand and was horizontally parted (Figure 2.5). This casting system weighed 12 lbs. Additional metal was poured into pig mold which can hold up to 120 lb of iron but typically were filled to between 60- 80 lbs for ease of recharging. Alloy Set B was used to cast 5 tensile bar sets and 2 step bars. The tensile bar molds had a 55x55x12.7 mm filter with 2.31 mm diameter holes positioned at the bottom of the pouring cup (Figure 2.6). In addition, 3 y-blocks were cast (Figure 2.7) with a 23.5 mm cross section at the bottom. All three 18 lb y-blocks were cast in the same 106 lb chemically bonded mold (Figure 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure12-1.png", + "caption": "Figure 12. Shape of DRAFPM motor.", + "texts": [ + "21 Vrms and 6.16% for THD. The DRAFPM motor has rotors on both sides so that the stator back-yoke can be removed. The advantage is that removing the Stator back-yoke can reduce the size of the motor. In this paper, while having the same volume, the height of the stator teeth was increased to further wind up the number of turns. The DRAFPM motor was designed as a dual rotor by dividing the thickness of the AFPM motor rotor back-yoke and magnet in half. Accordingly, the same permanent magnet usage is used. Figure 12 shows the DRAFPM motor with the same 20 pole 18 slot as the target RFPM motor. To check the performance according to the combination of pole and slot numbers together, the optimal design was carried out in Section 4 by adding a 24 pole 18 slot model. The optimization based on progressive meta-model constructs the initial meta-model with a minimum number of experimental points. After that, the meta-model is upgraded by adding experimental points that approximate the optimization conditions one by one" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004126_ists29_12_Pc_15__pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004126_ists29_12_Pc_15__pdf-Figure11-1.png", + "caption": "Fig. 11. Experimental setup.", + "texts": [ + "8% by the simultaneous optimization, the effectiveness of the optimum design is verified for the flat rib-stiffened shell antenna. The rib configuration obtained by the optimization is indicated in Fig.10. Additionally, the optimum location of the actuator is xF=320mm and the optimum output force of the actuator is F=8.6N. These optimal parameters are used in the experiments. Fig. 9. Distribution of surface error. Fig. 10. Rib configuration obtained by optimization. The overview of the experimental setup is indicated in Fig.11. The antenna specimen is manufactured by attaching the rib to the 0.5mm flat-triangular shell. The optimized rib is manufactured by machine work. The material of the shell and the rib are aluminum. For the actuator, the tensile force is applied to the rib by nylon cable. The value of the tensile force is adjusted by tuning the length of the cable, where the value is measured by the load cell. The disturbance is applied by loading weights on the rib. The deformed shape of the antenna surface is measured by a laser displacement meter attached on 0 10 20 0 50 100 150 200 250 300 350 400 450 500 Rib thickness, d [mm] Rib coordinate, xr [mm] Pc_20 the XY stage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001251_al-02449247_document-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001251_al-02449247_document-Figure2-1.png", + "caption": "Figure 2: Glide-back configuration with the components of the reusability kit (in black)", + "texts": [ + " It first lifts off from Kourou carrying out the ascent mission and then returns near to the launch site. Concerning the launch vehicle architecture, the first stage is propelled with 7 PROMETHEUS engines using LOx/LCH4 propellant. The second stage is also propelled with another PROMETHEUS engine. An expendable baseline and an example of a glide-back configuration are illustrated in Figure 1. The main wings and rear landing gears are located in a reusability pack located in a case that is attached to the main core at the thrust frame (Figure 2). This kit can be removed for the expendable mission. The front landing gear, nose and canards are attached to a skirt located in front of the first stage. In addition to these specifications, operational constraints on the vehicles are considered. The loads (axial and transverse loads, dynamic pressure and aerothermal flux) during the flights must not exceed a threshold during both the ascent and the return phases. Moreover, safety and visibility constraints near the launch and landing sites are taken into account to ensure the RLV operation safety" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure20-1.png", + "caption": "Fig. 20, the SAE Mini-Baja, engine modeled with \u201cRigid\u201d virtual part", + "texts": [ + " THE RATIONALE FOR THIS STUDY The focus of the material presented in this paper was the functionalities and performance of the \u201cRigid\u201d and \u201cRigid Spring\u201d elements in modal frequency calculations. These elements were discussed in reference to the Catia v5 commercial finite element package. It is important to clarify the need for such studies. At the early stages of the mechanical design, very frequently, there is a need to study the dynamic behavior of the part under a transient/harmonic load. The method of choice for such a purpose is \u201cLinear Dynamics\u201d analysis which can be effectively used for such studies. A concrete example is depicted in Fig. 20 where the SAE Mini-Baja [11], [12] is displayed. This all-train vehicle is widely used by mechanical engineering students in their capstone design project, where they are expected to design, fabricate, and test the vehicle according to the specifications set by the Society of Automotive Engineers (SAE). The use of \u201cStatic\u201d finite element analysis has become fairly standard in this project but \u201cDynamic\u201d calculations is very rare. Part of the reason is the complexity and lack of expertise/code documentation in commercial codes on this topic. Imagine that one of the goals of the analysis is to find the dynamic response (such as stresses) of the Mini-Baja when a wheel experiences an impulsive load. This can happen when the vehicle passes over a speed bump. Based on the material presented in this paper, one way to efficiently model such a problem is to treat the engine unit as a lumped mass placed at the handler point of a \u201cRigid\u201d or \u201cRigid Spring\u201d virtual part as shown in Fig. 20. In terms of a dynamic response, the details including the stiffness of the engine may not be consequential. In the event that the \u201cRigid Spring\u201d virtual part is used, the 6- spring stiffnesses can be easily determined from the \u201cStatic\u201d analysis of the structure, or from the experimental data if available. X. CONCLUDING REMARKS In implementing the ideas (rationales) presented in the previous section and employing \u201cLinear Dynamics\u201d, first, one needs to calculate the vibration frequencies of the different modes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000161_om_article_21583_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000161_om_article_21583_pdf-Figure1-1.png", + "caption": "Fig. 1. Design of the intermittent motion planetary mechanism:", + "texts": [ + " Thus, non-circular planetary gears are one of the most promising mechanisms for converting the rotational motion of the input shaft into the desired type of motion of the output shaft. Therefore, their theoretical and experimental studies are relevant and can be used in the design, manufacture and practical application in industry [25, 26]. The object of research in this article is a two-row planetary gear transmission with two external gears, including a pair of cylindrical gears and a pair of elliptical gears (Fig. 1), which is presented in [27]. 0 \u2013 cover, 1 \u2013 input shaft, 2 \u2013 carrier, 3 \u2013 output shaft, 4 \u2013 sun spur stationary gear, 5 \u2013 elliptical gear, 6 \u2013 spur planet gear, 7 \u2013 elliptical planet gear, 8 \u2013 satellite shaft Planetary transmission (Fig. 1) operates as follows. The input shaft 1 performs rotational movement, which is translated to the carrier 2, thereby the spur gear 6 rotates around a stationary gearwheel 4. The rotational motion of the spur gear 6 transmitted to the satellite shaft 8 and the elliptical gear 7 which drives the elliptical gear 5 and the output shaft 3 respectively. At moment when the gear ratio of elliptical gears pair is equal to the ratio of cylindrical gears pair, the output shaft 3 is stopped. Further, the angular velocity of output shaft increases to a maximum value and then decreases again to zero" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003103_26_tylek_203-215.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003103_26_tylek_203-215.pdf-Figure12-1.png", + "caption": "Fig. 12 Planting module control system", + "texts": [ + " Then the dibble is driven into the soil, with the simultaneous commencement of the movement following the ground: the dibble moves downwards in relation to the carriage and towards the back of the frame. After placing the dibble in the soil, the jaws are opened and the dibble is lifted until the entire plant comes out of the cylinder. At this point, the carriage is moved back to its starting position relative to the robot\u2019s frame, the jaws are clamped again, and a new cycle begins. Elements of the module control system are presented in Fig. 12. The valve coils of the hydraulic actuators, the sensors and additional buttons for operating the module are connected to the controller. The device can be controlled directly from the display by re-setting selected sections or by running the programme in the automatic mode. The operation of the device in the automatic mode is divided into several stages. In the first stage, the condition of compliance of the current position of the device with the initial, transport position is checked: the dibble is raised, the crane is moved to the left, the gripper jaws are clenched", + " In the sixth step, the controller continues sending a signal to the electric valve responsible for inserting the dibble actuator piston rod, lifting the dibble in this way, and a signal is sent to the electric valve which controls the hydraulic valve of the engine crane. Signals to the electric valves are sent until the crane is in the transport position \u2013 moved to the extreme left, while the dibble is raised. In step seven, the controller sends a signal to the electric valve responsible for closing the gripper. After this step, the process starts all over again: the controller returns to the first step and the cycle of planting the next seedling is initiated (Tylek et al. 2021a). A pilot study of the planting module (Fig. 12) shows that operation in the automatic mode in partially prepared terrain (the soil loosened, with a low coefficient of compactness, and a fairly level surface) satisfies the functional requirements. In the case of planting seedlings of coniferous species (pine, spruce), the work efficiency of the planting module was equal to 14.3\u00b12.7 seedlings/min. For deciduous species (oak, beech) it was lower and amounted to 9.1\u00b13.2 seedlings/min. In this case, the performance was characterised by significantly higher variability" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003635_rc55_19.14102808.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003635_rc55_19.14102808.pdf-Figure5-1.png", + "caption": "Figure 5. (a) Computed radiation pattern for a circular patch with shorting pins 5.8 GHz. (b) Computed radiation pattern for a conventional circular patch at 5.8 GHz. (RHCP and LHCP for phi = 0\u25e6).", + "texts": [], + "surrounding_texts": [ + "In our design, we used a RT/Duroid 5870 substrate with a dielectric constant \u03b5r = 2.33 and thickness of 1.575 mm. For the transmitting array, the desired frequency is 5.8 GHz; the patch radius a is then calculated from Equation (3). It is important to note here that the patch radius in our design is electrically larger than in conventional designs (without the shorting pins) since the free space wavenumber k0 (not k) is used to determine the patch radius. This fact results in higher antenna gain for our design when compared to conventional microstrip patches. The required value of ka for our substrate is given by: ka = k0 \u221a \u03b5ra = 2.81 (5) Using this value of ka in Figure 3, the required shorting pin position for a pin radius b/a = 0.055 is r0/a = 0.72. To obtain circular polarization, a diagonal narrow slot at the center of the patch was used. The design for a single patch was optimized in ANSYS HFSS resulting in the following dimensions: slot length L = 10 mm, slot width W = 1 mm, a = 15.15 mm, r0 = 10.9 mm and b = 0.83 mm. The antenna was fabricated using a milling machine. The simulation and measurement results for the reflection coefficient (|S11|dB) are shown in Figure 4. The measured return loss at the resonant frequency (5.76 GHz) is more than 20 dB (it is 18 dB at 5.8 GHz) and the measured 10-dB bandwidth is 240 MHz (5.65 GHz\u20135.89 GHz). The bandwidth is more than 4%, which is better than a conventional patch (less than 2%). The simulated radiation patterns of the patch with shorting pins and a conventional patch at 5.8 GHz are shown in Figures 5(a) and (b). The radiation pattern for the patch with shorting pins has a narrower main beam and shows significantly reduced radiation in the plane of the substrate (about 23 dB below broadside) compared to the conventional patch (about 11.7 dB below broadside). The computed gain and front to back ratio for the patch with shorting pins are also significantly better. Its gain is 7.6 dB, and the front to back ratio is 39 dB, versus 5.4 dB gain and 31 dB front to back ratio for the conventional patch. These features make this antenna an excellent element in antenna arrays to reduce mutual coupling and improve overall gain and efficiency. The single patch was used to design the two-element, circularly polarized transmitting array. A circularly polarized probe-fed conventional microstrip circular patch operating at 2.4 GHz was used as the array element for the receiving array. The complete retrodirective array was constructed using the transmitting array, receiving array, and feed network, consisting of the VCO, mixers, Wilkinson\u2019s power divider, and amplifiers, as shown in Figure 1. A monostatic setup was used to test the performance of the retrodirective system in Figure 6. A fixed 2.4 GHz transmitter and a 5.8 GHz receiving antenna were collocated, and the retrodirective system was mounted on a rotational stage. The radiation pattern (recorded by the fixed 5.8 GHz receiver) was measured to test the system\u2019s capability in steering its beam toward the transmitter. The measurement was repeated using a normal non-retrodirective array. The measured radiation patterns for both cases are shown in Figure 7 (the retrodirective array pattern is the solid curve and the normal antenna arrays is the dotted curve. The figure clearly shows that the received power for the retrodirective array is relatively flat between \u221230\u25e6 to 30\u25e6 (60\u25e6 sector) while the received power starts to drop beyond 5\u25e6 for the normal non-retrodirective antenna array." + ] + }, + { + "image_filename": "designv8_17_0000014_oad_15819_6662_82041-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000014_oad_15819_6662_82041-Figure4-1.png", + "caption": "Fig. 4 DNG loaded proposed antenna(a) Structure I;(b) Structure II; (c) Perspective view of structure II", + "texts": [ + " Here k0 and t are the wave number and substrate thickness respectively. The computed records of nr, \u0190r and\u00b5r of the DNG unit cell have been discussed in Table 2. The active region for double negative metamaterial is 2.0 - 3.0THz, 3.25-3.5 THz, 4.0-6.4 THz which exhibits the double negative characteristics in O-CC unit cell. Once the structure of DNG loaded rhombus-shaped single antenna (Ant.5) is designed in Fig1(e), a single antenna (Ant.5) is transfigured into 2-port MIMO antenna to increase data rate and channel capacity(bps/Hz) as illustrated in Fig.4.Initially,the structure-I of proposed antenna is implanted on a quartz substrate with an optimized physical dimension of 57\u00b5m x 27.65\u00b5m(W_SUB X L_SUB) as illustrated in Fig.4(a).Two radiating elements are placed adjacent at a minimum distance(\u03bb0/4) to maintain compactness of antenna in spatial diversity. Further, for the reduction of coupling effects, two inverse-L stubs with connected ground have been introduced at the ground side as illustrated in Fig.4(a). The minimum distance between antenna elements is 19.5 \u00b5m which utilized to maintain the standard value of isolation (S12/S21\u2264- 15dB) in the frequency region of 1.9 to 18 THz which is depicted in Fig.5a. To improve the isolation and gain, a periodic defected ground structure with DNG characteristics has been implanted at back side of substrate without altering the physical size of antenna structure I as illustrated in Fig.4(b). The top view, bottom view, and perspective view of the SWBMA with physical dimensions are depicted in Fig.4(a)-(c). (a) (b) After designing, simulations of proposed antenna structures (I &II) are done by CST microwave studio 2019 software. Because of similar radiating elements, the simulated reflection coefficients (S11/S22) and transmission coefficients(S12/S21) are the same at port1& port2. The reflection coefficient (S11) of the antenna expresses how much power is reflected from the antenna port1. The value of reflected power at the port should be less than -10dB. As per simulated results in Fig.5(a), the S11/S22 shows an impedance bandwidth of proposed antenna (1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002160_load.php_id_23033110-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002160_load.php_id_23033110-Figure4-1.png", + "caption": "Figure 4. Surface current density at (a) 5GHz, (b) 20GHz, (c) 35GHz, (d) 55GHz.", + "texts": [ + " Finally, for improved matching at lower frequency bands, two parasitic strips are placed on the top side of the substrate, as shown in Figure 2(e). These parasitic strips minimize the effect of spurious radiation caused by the feed line [13, 21, 22] and ultimately lead to enhanced IBW. This modification tends to achieve SWB response from 2.86 to more than 60GHz, as shown in Figure 3(b) (black curve). To gain further insight about the antenna operation, the surface current density at four different frequencies, i.e., 5GHz, 20GHz, 35GHz, and 55GHz, is shown in Figure 4. From the figure, it is evident that the outermost circle is responsible for the resonances at lower frequencies, as shown in Figure 4(a). As the frequency increases, the inner circles start contributing and generating resonances at higher frequencies, as illustrated in Figures 4(b)\u2013(d). This behavior is also in accordance with the conventional antenna theory [19]. To verify the simulated data, a prototype of the designed fractal antenna is fabricated (shown in the inset of Figure 5) using a low-cost photolithography technique and measured using the Agilent Technologies Power Network Analyzer (PNA). Figure 5 illustrates a comparison between the simulated and measured S11, and they are found to be in fair agreement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003341_ment_59_P2E1-16__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003341_ment_59_P2E1-16__pdf-Figure1-1.png", + "caption": "Fig. 1 Motion reconstruction in a 3D human simulator during the lifting phase", + "texts": [ + " Two identical devices recorded the external forces of the hands, each consisting of two three-axis force sensors (USL08-H6, Tec Gihan Co., Ltd., Kyoto, Japan). Data were filtered using a low-pass filter with a 4 Hz cut-off frequency. The required kinematic and force data were used to estimate the lumbar moment using inverse dynamics4). A testing machine was used to record the assistive torque at different trunk angles5). Then, the interpolation method was used to obtain the relationship between the assistive torque and trunk angle. As the assistive torque only acts in the flexion plane (plane xoz in Fig. 1), it is subtracted from the non-assisted torque in this plane to obtain the actual lumbar torque. Lumbar risk probability was estimated by risk assessment benchmark using five key factors: lifting rates, average twisting velocity, maximal lumbar moment, maximal sagittal angle, and maximal lateral velocity3). The overall lumbar risk probability can be estimated by the mean risk probability of all factors. If the estimated risks were smaller than 0.01 or higher than 0.99, they were considered 0.01 and 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001782_f_version_1663924178-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001782_f_version_1663924178-Figure3-1.png", + "caption": "Figure 3. Prototype of ISDR implantable lengthening nail. 1\u2014protective shell, 2\u2014distraction nail, 3\u2014thrust bearing, 4\u2014lead screw nut, 5\u2014lead screw, 6\u2014gearbox, 7\u2014internal permanent magnet, 8\u2014shafting tube. (a) The schematics of implantable lengthening nail; (b) cross-section of implantable lengthening nail; (c) axial load acts on the shafting system in the implantable lengthening nail; (d) cross-section of planetary gearbox and RV gearbox.", + "texts": [ + " This design signifies that the air gap between the permanent magnet and the driver is minor, revealing the driving torque for the bone distraction is much more stable and forceful. Moreover, the transmission component of ISDR has a longer lifespan compared to PRECICE because the transmission of the axial load from the distraction nail towards the thrust bearing and protective shell occurs without passing through the gearbox. Last but not least, the distraction force of ISDR is adjustable and controllable by tuning the electromagnetic driver parameters akin to the Permanent Magnet Brushless Direct Current (PMBLDC) motor model. 2.2.1. Implantable Lengthening Nail Figure 3 illustrates that the proposed implantable lengthening nail distraction mechanism is well-protected by a protective shell. The mechanical stiffness of implantable lengthening nail is guaranteed by a titanium alloy with good bio-compatibility (non-toxic and high resistance to oxidization), lightweight, and rigid characteristics, which is commonly used in surgical transplants [30\u201332]. The implantable lengthening nail adopts a distraction structure design, where the distraction mechanism is placed within the distraction nail" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure7-1.png", + "caption": "Fig. 7 Distribution of stress (a) Antero-lateral (b) Postero-lateral; (c) Maximum stress under static load condition I", + "texts": [ + " Soderberg's theory for fatigue analysis has been used as the design criterion which is related to the yield stress. The static strength simulation findings of the modified knee prosthesis are shown in Figs. 7 and 8. It shows prosthetic knee stress under loading conditions I and II. Stresses in front and back joint bars are 85-107 and 42-64 MPa respectively for load condition I (Figs. 7a and 7b) and 81- 101 and 40-60 MPa for load condition II (Figs. 8a and 8b). The maximum von-Mises stress value of 300 MPa is observed at the front link bush for load conditions I (Fig. 7c) and 284 MPa for load conditions II (Fig. 8c). Comparing these results to corresponding material properties, the maximum stresses are sufficiently below the yield strength of AA7075-T6 aluminium alloy (503 MPa) utilized for the front and back joint bars and bush. These results suggest that the modified knee prosthesis will successfully pass the ISO 10328:2016 static strength test. The static strength test results for the modified knee are shown in terms of total deformation in Figs. 9 and 10. Maximum deformation is observed at the load application point which is 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure3-2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure3-2-1.png", + "caption": "Figure 3-2: Link i under angular motion.", + "texts": [ + " The motion profiles are presented in Cartesian and joint configuration spaces. The simulation results provide valuable inform ation for understanding the com plex behavior of the dynamic m anipulator motion and for improving m anipulator performance. Concepts of this chapter could be extended to determ ine optim um feedforward torque requirem ents for each joint actuator for a specified task. 40 3.2 N ew to n -E u ler F orm u lation Newton\u2019s equation of m otion applied to link i yields (Fig. 3-1) = m i \u2019{% <} Euler\u2019s equation of motion applied to link i yields (Fig. 3-2) * { \u00b0 iV , } = \u00ab U i f W i } +*' { \u00b0 W i } X [ciI i \u2018 { \u00b0 ^ } ] , where \u00b0FCJ- and \u00b0 iV , denote the net force and torque applied to link i. m-i is the mass of link i. ctIi is the m oment of inertia of link i w ith respect to the centroid coordinate frame ci. The fram e ci is located at the centroid of link i and has the same orientaion as joint fram e i resulting in c,/j =* Jj. Appendix D shows the derivation of the above expression and the structure of the inertia tensor \u2019/,\u2022 and transform ation between *1; and \u00b0Ii" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001813_tation-pdf-url_37022-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001813_tation-pdf-url_37022-Figure1-1.png", + "caption": "Fig. 1. Three ideal models of PMC loaded monopole antennas, (a) case I, (b) case II, and (c) case III: L=7.5mm, D=0.5mm and h=3.5mm, h1=2.5mm, h2=3mm, H=2mm, h3=5.5mm, h4=2mm, and r =4mm. From (Jafargholi et al., 2010), copyright \u00a9 2010 by the Institute of Electrical and Electronics Engineers (IEEE).", + "texts": [ + " To this aim, the CLLs are used to realize perfect magnetic conductor behavior. Due to the reverse current effects, the monopole radiation pattern does not remain omnidirectional at the second harmonic of the main resonant frequency (Balanis, 1989). In this section, a monopole antenna loaded with the PMC layer is proposed to increase omnidirectional radiation bandwidth. To make the concept more clear, three ideal models are simulated, all of which are partly covered by a very thin PMC shell, as shown in Fig. 1. As a reference, a conventional monopole antenna is also simulated for comparison. It has the same dimensions as the geometries in Fig. 1, except that the PMC cover is removed. Fig. 2, shows the simulated reflection coefficient of the monopole antennas with and without the PMC cover. The resonant frequencies for case I and II are 18.5GHz and 24GHz, respectively, whereas the resonant frequency for case III remains the same as the conventional monopole antenna. For the conventional monopole antenna, distortion of the omnidirectional radiation pattern occurs at frequencies higher than 20GHz. This upper limit is indicated by dashed line in Fig", + " As is evident from Fig. 4, the directivity curve for the case II is approximately flat while the antenna directivity for the case III significantly improves as compared to that of the conventional monopole antenna. For our discussion on the pattern modification, the results shown in Figs. 2 to 4, need to be considered simultaneously. www.intechopen.com Applications of Artificial Magnetic Conductors in Monopole and Dipole Antennas 579 www.intechopen.com Metamaterial 580 Consequently, the ideal model shown in Fig. 1 (c) (case III) is considered for the practical realization. It should be pointed out that we can always use a shorter monopole antenna to improve the omnidirectional radiation pattern. However, the prices we pay are the higher resonant frequency and lower directivity due to the significant reduction in the monopole length. www.intechopen.com In the previous section, it was revealed that the suppression of phase reversal by incorporating PMC cover has led to the improved radiation pattern, especially at the second harmonic of the main resonant frequency" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002992_M-2018-3-02-Dyja.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002992_M-2018-3-02-Dyja.pdf-Figure3-1.png", + "caption": "Fig. 3. Scheme of the \u201cguide mark\u201d defect formation on the internal surface of the pipe, a) stripe formation in the groove tapers when rolling on plug rolling mill 1, b) pipe having been turned is clamped by the upper part of the groove of plug rolling mill 2, c) jamming at groove filling", + "texts": [ + " 1) on internal surface of the pipe. So far there is no unanimous view about the reasons of this defect appearance and no objective and accurate analysis of this problem has been made. Preventive recommendations of \u201cguide mark\u201d defect appearance are ambiguous and controversial. The study of the process of lengthwise rolling of tubes is presented in [4,5]. This study proposes the model of \u201cguide marks\u201d formation and provides the research of pipe forming at plug rolling mill (Fig. 2). A \u201cguide mark\u201d defect appears as follows, Fig. 3 [6]: 1) when rolling is performed on PRM-1, there is intensive metal flowing into the tapers, it results in a thicker pipe walls * URAL FEDERAL UNIVERSITY NAMED AFTER THE FIRST PRESIDENT OF RUSSIA B.N. YELTSIN, INSTITUTE OF MATERIAL SCIENCE AND METALLURGY, YEKATERINBURG, RUSSIA ** METAL FORMING INSTITUTE, 14 JANA PAWLA II AV., 61-139 POZNAN, POLAND # Corresponding author: dyja.henryk@wip.pcz.pl in the groove tapers than in the upper part of the groove (S1 is a wall thickness of the pipe in the groove taper and S2 is a wall thickness of the pipe in the upper part of the groove) [7-9]. This point causes the stripes on the pipe surface are forming, Fig. 3a; 2) after pipe turning to 90\u00b0, the pipe is rolled in PRM-2, and the stripes get into the tapers, Fig. 3b. When the groove is filled stripes are forming on the mandrel, and the jamming occurs, Fig. 3c; 3) when rolling is performed in a three-roll blooming mill and then in a stretch-reducing or sizing mill, jamming on the internal surface of the pipe turns into a \u201cguide mark\u201d defect. Thus the increase of S1/S2 ratio leads to \u201cguide mark\u201d defect formation on the internal surface of the pipe. The study of pipe forming was carried out using \u00abDEFORM \u2013 3D\u00bb software solution. Following the recommendations of the programmers and taking into account a practical data about pipes rolling on the PRM mill [10,11] the initial conditions included data about temperature of the pipe T = 1200\u00b0C, temperature of roll and mandrel T = 150\u00b0C, air temperature T = 20\u00b0C" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002765_11633-014-0800-y.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002765_11633-014-0800-y.pdf-Figure3-1.png", + "caption": "Fig. 3 The 2-link free-floating manipulator in space", + "texts": [ + " J(q)q\u0307 = x\u0307 (2) where J(q) \u2208 R2\u00d72 is the Jacobian matrix related to the robot manipulator motion, and q = [ q1 q2 ]T is the joint angle vector and x \u2208 R2 is the end position. For the planar 2-link robot manipulator, the dynamic of the space manipulator is derived using the Lagrange formulation. M (q)q\u0308 + B(q, q\u0307)q\u0307 + G(q) = \u03c4 (3) where M (q) \u2208 R2\u00d72 is the inertia matrix; B(q, q\u0307) \u2208 R2\u00d72 is the vector of the Coriolis and centrifugal forces; G(q) \u2208 R2 is the gravity vector; \u03c4 \u2208 R2 is the joint torque. According to the properties that have been assumed previously, the free floating space manipulator is shown in Fig. 3. The freedom of the selected planar manipulator will be added to five for the space manipulator will rotate around its centroid and translate along the axis. When the main body of manipulator moves, a dynamic force or torque will apply on the base and the attitude and position of the base will change. In the figure, B0 is the base of the space manipulator; C0 is the centroid of the base; m0 is the mass of the base; other symbols have been defined in Fig. 1. The kinematic and dynamic equations can be established in the similar method of the ground case" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002562_f_version_1605520280-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002562_f_version_1605520280-Figure5-1.png", + "caption": "Figure 5. One degree of freedom (DoF) pendulum model of the exoskeleton.", + "texts": [ + " Figure 4 illustrates a free body diagram of the exoskeleton and human model. O1, O2, and O3 are the center position of hip, knee, and ankle joint, respectively; \u03b81, \u03b82, and \u03b83 represent angles of hip, knee, and ankle, respectively; l1, l2, and l3 are length of the femur, tibia, and foot, respectively; and lGi is the center of gravity (CoG) of links 1, 2, and 3. In this paper, each link of the exoskeleton and human is modeled as one DoF pendulum model, which replicates one joint of the exoskeleton and human, as shown in Figure 5. The summation of the physical effect of each lower link such as mass and inertia is considered to be Mi [24]. In this study, the Lagrangian formulation of dynamic equation of the pendulum model is expressed as follows: Li = Eki \u2212 Epi , (1) Ti = d dt ( dLi d\u03b8\u0307i )\u2212 dLi d\u03b8i , (2) where i represents number of the links; Li is the Lagrangian function; \u03b8i and \u03b8\u0307i are the angular position and velocity, respectively; Ti is the torque that applies to each joint; and Eki and Epi represent kinetic and potential energy [25], respectively, which are given as follows: Eki = 1 2 Ii \u03b8\u0307i 2 + 1 2 mi( \u02d9xGi 2 + \u02d9yGi 2) + 1 2 Mi(x\u0307i 2 + y\u0307i 2), (3) Epi = migyGi + Migyi , (4) where mi and Ii are the mass and inertia of the link, respectively; Mi is the mass of lower links; g represents gravitational acceleration; xGi, yGi, xi, yi \u02d9xGi, \u02d9yGi x\u0307i, and y\u0307i,represent the position of the CoG, end point of the link, and their velocity, respectively, as follows: xGi = lGisin\u03b8i x\u0307Gi = lGi \u03b8\u0307icos\u03b8i xi = lisin\u03b8i x\u0307i = li \u03b8\u0307icos\u03b8i , (5) yGi = lGicos\u03b8i y\u0307Gi = \u2212lGi \u03b8\u0307isin\u03b8i yi = licos\u03b8i y\u0307i = \u2212li \u03b8\u0307isin\u03b8i , (6) where lGi and li are the length of the CoG and the link i, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000853_9668973_09718336.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000853_9668973_09718336.pdf-Figure3-1.png", + "caption": "FIGURE 3. Computer-aided design (CAD) model of the proposed revolute joint.", + "texts": [ + " The motor cortex is located at approximately \u00b160\u25e6 in the sagittal plane based on the center of the brain. To cover the region, the rotation range of the revolute joint must be greater than\u00b160\u25e6.We chose a rotation range of\u00b170\u25e6 that included a margin of 10\u25e6 on both sides. To achieve this range, s and h were determined to be 133 mm and 24 mm, respectively, based on (1). In the selection process of the above parameters, the sizes of the commercial components were considered. Based on these parameters, the proposed revolute joint was designed as shown in Fig. 3. To change the linear motion to rotational motion, the block of the lead-screw-driven linear guide was connected to a revolute link. Given that both the linear and revolute motion axes were fixed, the distance and VOLUME 10, 2022 24041 angle changes occurred between the block and the revolute link during the motion changing process. The length between the revolute axis and linear guide block as a function of the angle \u03b8 , l\u03b8 , can be obtained as follows, l\u03b8 = h cos\u03b8 . (2) When the angle of the revolute joint changes from 0\u25e6 to 70\u25e6, the length changes from 24 mm to approximately 70 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001550_load.php_id_14120403-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001550_load.php_id_14120403-Figure1-1.png", + "caption": "Figure 1. CBRAM Cell: (a) MIM structure, (b) electrical equivalent circuit.", + "texts": [ + " No complex technological, high temperature process such as photolithography or doping is used. Instead, the approach is simple to implement and compatible with direct integration of the RF switches in conventional RF PCB. The study that follows aims to demonstrate the implementation of these MIM structures on a low cost and versatile substrate, massively used in the electronics manufacturing process for signal switching applications. CBRFS are based on MIM solid state structures (Metal Insulator Metal), i.e., a stack of three layers with no moving parts, as shown in Figure 1(a). By carefully choosing materials and their thicknesses, it is possible to show that such a structure acts as a programmable resistor that keeps its value in the absence of energy to maintain its state. This stack must be composed of an inert electrode (Al, Ni. . .) and the other must be chemically active (Cu, Ag. . .). An equivalent electric diagram of the structure is shown in Figure 1(b). It comprises a variable resistance (relating to the On and Off states) in parallel with a capacitor, which depends on the geometry of the MIM structure and the nature of the dielectric layer. Initially, the structure is not conductive (denoted Off state in Figure 2(a)) because the electrolyte is a good insulator. Under the action of a tension V set between the two electrodes, the insulator allows the migration of Cu ions, which come from the active electrode, towards the inert electrode (see Figure 2(b) [12])" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000847_853_83_17-00194__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000847_853_83_17-00194__pdf-Figure4-1.png", + "caption": "Fig. 4 Height of cart and wheel", + "texts": [], + "surrounding_texts": [ + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 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1996\uff09\uff0e\u3053\u306e\u5b89\u5b9a\u5ea6\u306f\u5bfe\u8c61\u306e\u72b6\u614b\u7a7a\u9593\u30e2\u30c7\u30eb\u306e\u56fa\u6709\u5024\u306e\u5b9f\u90e8\u306e\u6700\u5927\u5024\u3067\u3042\u308b\uff0e\u5b89\u5b9a\u5ea6\u306b\u57fa\n\u3065\u304d\u30b8\u30f3\u30d0\u30eb\u8ef8\u306e\u56de\u8ee2\u3070\u306d\u525b\u6027\u3084\u7c98\u6027\u6e1b\u8870\u4fc2\u6570\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u89d2\u901f\u5ea6\u306e\u6700\u9069\u5316\u3092\u63d0\u6848\u3057\u3066\u3044\u308b\uff0e\n\u672c\u7814\u7a76\u306f 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\u5236 \u5fa1 \u5bfe \u8c61\n\u56f3 1\u306b\u672c\u7814\u7a76\u3067\u7528\u3044\u305f\u5b9f\u9a13\u88c5\u7f6e\u3092\u793a\u3059\uff0e\u3053\u308c\u306f 2\u8f2a\u8eca\u3092\u60f3\u5b9a\u3057\u3066\u3044\u308b\u304c\uff0c\u8eca\u8f2a\u3092\u8a2d\u3051\u3066\u304a\u3089\u305a 2\u3064\u306e\u811a\uff08\u30ea\u30f3 \u30af\uff09\u3067\u4ee3\u7528\u3057\u3066\u3044\u308b\uff0e\u3053\u308c\u3089\u306e\u811a\u3068\u30b8\u30f3\u30d0\u30eb\u3092\u56fa\u5b9a\u3057\u3066\u3044\u308b\u67a0\u3092\u5408\u308f\u305b\u3066\u53f0\u8eca\u3068\u547c\u3076\uff0e\u811a\u306e\u4ee3\u308f\u308a\u306b 2\u8f2a\u8eca\u306e\u69cb \u6210\u306b\u3059\u308c\u3070\u3053\u306e\u53f0\u8eca\u304c\u56f3 1\u306e\u5de6\u53f3\u65b9\u5411\u306b\u8d70\u884c\u3059\u308b\uff0e\n\u56f3 2\u306b\u793a\u3059\u53f0\u8eca\u306e\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\u306e\u6a2a\u63fa\u308c\u89d2\u3092 \u03b1 \u3067\u8868\u3059\uff0e\u53f0\u8eca\u306b\u306f 2\u3064\u306e\u30b8\u30f3\u30d0\u30eb\u304c\u53d6\u308a\u4ed8\u3051\u3089\u308c\u3066\u304a\u308a\uff0c\u56de\u8ee2 \u8ef8\u307e\u308f\u308a\u306b\u81ea\u7531\u306b\u56de\u8ee2\u3059\u308b\uff0e\u56f3 3\u306b\u793a\u3059\u30b8\u30f3\u30d0\u30eb\u306e\u30d4\u30c3\u30c1\u89d2\u65b9\u5411\u306e\u56de\u8ee2\u89d2\u3092 \u03b2 \u3067\u8868\u3059\uff0e2\u3064\u306e\u30b8\u30f3\u30d0\u30eb\u306f\u5bfe\u79f0\u306b\u914d\n\u7f6e\u3055\u308c\uff0c\u305d\u308c\u3089\u306e\u89d2\u5ea6\u304c\u540c\u3058\u5927\u304d\u3055\u306b\u306a\u308b\u3088\u3046\u306b\u30ae\u30a2\u3067\u62d8\u675f\u3057\u3066\u3044\u308b\uff0e\u5404\u30b8\u30f3\u30d0\u30eb\u306b\u306f\u56de\u8ee2\u3059\u308b\u30db\u30a4\u30fc\u30eb\u3068\uff0c\u305d \u306e\u56de\u8ee2\u306e\u305f\u3081\u306e DC\u30e2\u30fc\u30bf\u3092\u914d\u7f6e\u3057\u3066\u3044\u308b\uff0e\n\u53f0\u8eca\u306f\u4e0d\u5b89\u5b9a\u7cfb\u3067\u3042\u308b\u305f\u3081\u3044\u305a\u308c\u8ee2\u5012\u3059\u308b\uff0e\u305d\u3053\u3067\u53f0\u8eca\u3084\u30b8\u30f3\u30d0\u30eb\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u8a2d\u8a08\u6761\u4ef6\u3092\u5909\u5316\u3055\u305b\u305f\u3068\u304d\u306b\uff0c\n\u8ee2\u5012\u307e\u3067\u306e\u6642\u9593\u3092\u3067\u304d\u308b\u3060\u3051\u9577\u304f\u3059\u308b\u3088\u3046\u306a\u6700\u9069\u8a2d\u8a08\u304c\u3067\u304d\u308b\u3053\u3068\u304c\u671b\u307e\u3057\u3044\uff0e\u8a2d\u8a08\u6761\u4ef6\u3068\u3057\u3066\u56f3 4\u306b\u793a\u3059\u3088\u3046 \u306b\u30b8\u30f3\u30d0\u30eb\u56de\u8ee2\u8ef8\u304b\u3089\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3\u307e\u3067\u306e\u8ddd\u96e2 a\u3068\u5730\u9762\u304b\u3089\u30b8\u30f3\u30d0\u30eb\u56de\u8ee2\u8ef8\u307e\u3067\u306e\u9ad8\u3055\uff08\u53f0\u8eca\u306e\u811a\u306e\u9577\u3055\uff09b\u306b \u7740\u76ee\u3057\uff0c\u305d\u308c\u305e\u308c a = 0.11,6.11,12.11[mm], b = 92.10,102.05,112.0[mm]\u3068\u5909\u5316\u3067\u304d\u308b\u3088\u3046\u306a\u69cb\u9020\u3068\u3057\u305f\uff0e\n\u30db\u30a4\u30fc\u30eb\u3092\u9664\u304f\u53f0\u8eca\u3068\u30b8\u30f3\u30d0\u30eb\u306f\u30a2\u30eb\u30df\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u307f\u9244\u88fd\u3068\u3057\u3066\u3044\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f\u534a\u5f84 40[mm]\uff0c\u539a\u3055 15[mm] \u3067\uff0c\u8cea\u91cf\u306f\u7d04 0.61[kg]\uff0c\u56de\u8ee2\u8ef8\u307e\u308f\u308a\u306e\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306f\u7d04 0.472\u00d710\u22123[kg m2]\u3067\u3042\u308b\uff0e\u3053\u306e\u30db\u30a4\u30fc\u30eb\u3092DC\u30e2\u30fc", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30bf\u3067\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3055\u305b\u308b\uff0e\u305f\u3060\u3057\uff0c2\u3064\u306e\u30db\u30a4\u30fc\u30eb\u89d2\u901f\u5ea6\u306e\u5927\u304d\u3055\u306f\u540c\u3058\u3067\u65b9\u5411\u3092\u9006\u306b\u3059\u308b\uff0e\u4e8b\u524d\u306b\u884c\u3063\u305f\u4e88 \u5099\u5b9f\u9a13\u3067\u306f\uff0c\u56de\u8ee2\u6570\u3092 7000[rpm]\u7a0b\u5ea6\u306b\u3059\u308b\u3068\uff0c\u30b8\u30f3\u30d0\u30eb\u3068\u53f0\u8eca\u304c\u3068\u3082\u306b\u63fa\u308c\u306a\u304c\u3089\u6b73\u5dee\u904b\u52d5\u3092\u884c\u3044\u9577\u6642\u9593\u306b\u308f 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7000[rpm]\u4ee5\u4e0a\u306b\u3059\u308b\u3068\u56de\u8ee2\u8ef8\u306e\u89e6\u308c\u56de\u308a\u632f\u52d5\n\u304c\u5927\u304d\u304f\u306a\u308a\uff0c\u9a12\u97f3\u3082\u6fc0\u3057\u304f\u306a\u3063\u305f\uff0e\n\u305d\u3053\u3067\uff0c\u672c\u7814\u7a76\u3067\u306f\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u6570\u3092\u3042\u307e\u308a\u5927\u304d\u304f\u3057\u306a\u304f\u3068\u3082\u5b89\u5b9a\u6027\u3092\u826f\u597d\u306b\u4fdd\u3064\u3053\u3068\u304c\u3067\u304d\u308b\u3088\u3046\u306a\u8a2d\u8a08 \u6307\u91dd\u3092\u691c\u8a0e\u3059\u308b\uff0e\u306a\u304a\u56f3 1\u306b\u793a\u3059\u5b9f\u9a13\u88c5\u7f6e\u3092\u3082\u3068\u306b\u56f3 2,3\u3067\u793a\u3057\u305f\u30e2\u30c7\u30eb\u3092 SolidWorks\u4e0a\u3067\u4f5c\u6210\u3057\uff0c\u5404\u525b\u4f53\u306e\u8cea\n\u91cf\u3084\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306a\u3069\u306e\u7279\u6027\u3092\u6c42\u3081\u3066\u304a\u308a\uff0c\u6b21\u7ae0\u4ee5\u964d\u306e\u7406\u8ad6\u89e3\u6790\u3084\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u4f7f\u7528\u3057\u3066\u3044\u308b\uff0e\n3. \u904b \u52d5 \u30e2 \u30c7 \u30eb\n3\u00b71 \u5ea7\u6a19\u7cfb\n\u56f3 5\u306b\u5bfe\u8c61\u3068\u3059\u308b 2\u8f2a\u53f0\u8eca\u3092\u793a\u3059\uff0e\u56f3 5\u306f\u5ea7\u6a19\u7cfb\u306e\u8aac\u660e\u3092\u660e\u78ba\u306b\u3059\u308b\u305f\u3081\u306b\uff0c\u30b8\u30f3\u30d0\u30eb\u6a5f\u69cb\u3092 1\u3064\u306e\u307f\u63cf\u3044\u3066\n\u3044\u308b\uff0e\u53f0\u8eca\u306b\u306f\u30b8\u30f3\u30d0\u30eb\u304c\u53d6\u308a\u4ed8\u3051\u3089\u308c\uff0c\u53d6\u308a\u4ed8\u3051\u8ef8\u5468\u308a\u306b\u81ea\u7531\u306b\u56de\u8ee2\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306b\u306f\u30db\u30a4\u30fc\u30eb\u3092\u56de\u8ee2\u3055\u305b\n\u308b\u30e2\u30fc\u30bf\u304c\u56fa\u5b9a\u3055\u308c\uff0c\u30e2\u30fc\u30bf\u306b\u3088\u308a\u30db\u30a4\u30fc\u30eb\u304c\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3057\u3066\u3044\u308b\uff0e\n\u03a3B \u3092\u5730\u9762\u4e0a\u306b\u56fa\u5b9a\u3057\u305f\u57fa\u6e96\u5ea7\u6a19\u7cfb\u3068\u3059\u308b\uff0ez\u8ef8\u306f\u925b\u76f4\u4e0a\u5411\u304d\uff0cx\u8ef8\u306f\u53f0\u8eca\u9032\u884c\u65b9\u5411\u3092\u6b63\u9762\u3068\u3059\u308b\u3068\u304d\u53f3\u624b\u3068\u306a\u308b \u5411\u304d\uff0cy\u8ef8\u306f\u6c34\u5e73\u65b9\u5411\u3067\u53f0\u8eca\u306e\u9032\u884c\u3059\u308b\u5411\u304d\u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f\u8d77\u4f0f\u306e\u3042\u308b\u9762\u3092\u4e0a\u308a\u4e0b\u308a\u3059\u308b\u3053\u3068\u3092\u60f3\u5b9a\u3059\u308b\uff0e\u53f0\u8eca\u306e \u5e95\u9762\u306b\u539f\u70b9\u3092\u3068\u308a\uff0c\u03a3B \u3092 x\u8ef8\u56de\u308a\u306b\u5730\u9762\u306e\u50be\u304d\u89d2\u5ea6 \u03d5 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u5ea7\u6a19\u7cfb\u3092 \u03a3A \u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f 2\u8f2a\u3067\u8d70\u884c\u3059 \u308b\u305f\u3081\uff0c\u9032\u884c\u65b9\u5411\u306b\u5bfe\u3057\u3066\u5de6\u53f3\u65b9\u5411\uff08\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\uff09\u306b\u5012\u308c\u3088\u3046\u3068\u3059\u308b\uff0e\u3053\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03a3A\u306e y\u8ef8\u56de\u308a\u306b \u03b1 \u3068\u8868 \u3059\uff0e\u539f\u70b9\u3092\u53f0\u8eca\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3A\u3092 y\u8ef8\u56de\u308a\u306b \u03b1 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u53f0\u8eca\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3C \u3068\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u56de \u8ee2\u89d2\u5ea6\u3092 \u03a3C \u306e x\u8ef8\u56de\u308a\u306b \u03b2 \u3068\u8868\u3059\uff0e\u539f\u70b9\u3092\u30b8\u30f3\u30d0\u30eb\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3C \u3092 x\u8ef8\u56de\u308a\u306b \u03b2 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30b8\u30f3\u30d0", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3G \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f \u03a3G \u306e z\u8ef8\u56de\u308a\u306b\u56de\u8ee2\u3059\u308b\uff0e\u305d\u306e\u89d2\u5ea6\u3092 \u03b3 \u3068\u3059\u308b\uff0e\u539f\u70b9\u3092\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3 \u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3G \u3092 z\u8ef8\u56de\u308a\u306b \u03b3 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30db\u30a4\u30fc\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3W \u3068\u3059\u308b\uff0e\n\u4ee5\u964d\u6570\u5f0f\u4e2d\u3067\u306f cos\u03b8 =C\u03b8 , sin\u03b8 = S\u03b8 \u3068\u7565\u8a18\u3059\u308b\uff0e\n3\u00b72 \u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\n\u307e\u305a\uff0c\u56de\u8ee2\u904b\u52d5\u3092\u8868\u3059\u305f\u3081\u306e\u5404\u525b\u4f53\u306e\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092\u660e\u3089\u304b\u306b\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u901f\u5ea6\u306f\u56de\u8ee2\u89d2\n\u03d5 ,\u03b1,\u03b2 ,\u03b3 \u306e\u6642\u9593\u5909\u5316\u306b\u3088\u3063\u3066\u8868\u3059\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u3053\u308c\u3092 \u03a3W \u3067\u8868\u3057\u305f\u3068\u304d W \u03c9W \u3068\u8a18\u3059\u3068\uff0c\nW \u03c9W = C\u03b3 S\u03b3 0 \u2212S\u03b3 C\u03b3 0\n0 0 1\n C\u03b1 \u03d5\u0307 + \u03b2\u0307\nS\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307\n (1)\n\u3068\u306a\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3G \u3067\u8868\u3057\u305f\u3082\u306e\u3092 G\u03c9G \u3068\u8a18\u3059\u3068\uff0c\u5f0f (1) \u306b\u304a\u3044\u3066 \u03b3 = 0, \u03b3\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u307e\u305f\u53f0\u8eca\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092 C\u03c9C \u3068\u8a18 \u3059\u3068\uff0c G\u03c9G \u306b\u5bfe\u3057\u3066 \u03b2 = 0, \u03b2\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u3086\u3048\u306b\uff0c\u305d\u308c\u305e\u308c\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u306a\u308b\uff0e\nG\u03c9G = C\u03b1 \u03d5\u0307 + \u03b2\u0307 S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 C\u03c9C = C\u03b1 \u03d5\u0307 \u03b1\u0307 S\u03b1 \u03d5\u0307 (2)\n3\u00b73 \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae \u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e\u6163\u6027\u30c6\u30f3\u30bd\u30eb\u3092\u305d\u308c\u305e\u308c \u03a3W ,\u03a3G,\u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092\nIW = IWX 0 0 0 IWY 0\n0 0 IWZ\n , IG = IGX 0 0 0 IGY 0\n0 0 IGZ\n , IC = ICX 0 0 0 ICY 0\n0 0 ICZ\n (3)\n\u3068\u3059\u308b\uff0e\u305f\u3060\u3057\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u5bfe\u79f0\u6027\u304b\u3089 IWX = IWY \u3067\u3042\u308a\uff0c\u3053\u306e\u5024\u3092 IWXY \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TWR,TGR,TCR \u306f\u305d\u308c\u305e\u308c\u5f0f (1)(2)\u3092\u7528\u3044\u3066\uff0c\nTWR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 } + IWZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307 )2 ]\n(4)\nTGR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03d5\u0307) = 1 2\n{ IGX ( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + IGY ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 + IGZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 )2 }\n(5)\nTCR(\u03b1, \u03b1\u0307, \u03d5\u0307) = 1 2 ( ICXC2 \u03b1 \u03d5\u0307 2 + ICY \u03b1\u03072 + ICZS2 \u03b1 \u03d5\u0307 2) (6)" + ] + }, + { + "image_filename": "designv8_17_0004797_f_efsc2021_07023.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004797_f_efsc2021_07023.pdf-Figure1-1.png", + "caption": "Fig. 1. Diagram of the action of forces on the details of the filling section of the fuel pump.", + "texts": [ + " Since the radial unbalanced force arising from the design features can be reduced by using a plunger with two helical cut-off edges, and the unbalanced force caused by the asymmetry of the liner relative to the filling and bypass holes is insignificant, the radially unbalanced force caused by inaccuracy manufacture of parts of the plunger pair. In accordance with the technical documentation defining the geometric shape of precision pairs, ovality and taper of no more than 0.5-1 microns are allowed. The inspection found that of the number of new precision parts manufactured at the Noginsk and Yaroslavl fuel equipment plants, 60% had ovality and cone-shapedness in the range of 1 - 2.3 microns. Let us consider the case of eccentric placement of a plunger with a double-sided cone of its working surface in a bushing (Fig. 1). Because of such a cone, the cross-sectional area of the gap and the fluid pressure gradient along the length of the plunger change according to a curvilinear law. Plane-parallel steady motion of an incompressible fluid is described by the Navier-Stokes equations: + = \u2219 + \u2212 (1) + = \u2219 + \u2212 (2) and the fluid continuity equation: + = 0 (3) where \u2013 the projection of the fluid flow velocity on the X-axis, m/s; \u2013 the same on the Y-axis, m/s; \u2013 kinematic viscosity of the liquid, m2/s; \u2013 density of liquid, kg/m3; p \u2013 fluid pressure along the length of the plunger, N/m2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure3.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure3.8-1.png", + "caption": "Figure 3.8 : Electric motor stator geometry showing slot coils and papers and thermal contact resistance of laminations [138].", + "texts": [ + "26) Where \u2113 denotes the total thickness of all insulator sheets and laminations, \u03bb is the thermal conductivity property, \u2113\ud835\udc56\ud835\udc5b\ud835\udc60 and \u2113\ud835\udc59\ud835\udc4e\ud835\udc5a are the thicknesses of insulator sheets and laminations respectively. 3.6.2 Contact Thermal Resistance It is important to note that the equivalent lumped model of any system depends strongly on physical factors, one of which is the nature of the connection between different elements. In particular, the complex nature of the interface region between two different elements (presence of residual impurities, air\u2026) influences the thermal behavior of the electric motor at some locations in the stator (Figure 3.8) as well as in rotor (for instance, between magnets and rotor core). For an imperfect surface contact, calculating the total conductance between machine elements consists of adding directly or indirectly a contact thermal conductance representing the interface. Bertin [47] suggested some values of the contact conductance at some locations for different electric motor types, depending on the pressure applied to the contact region, surface roughness, materials properties, and connection type and technique" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.12-1.png", + "caption": "Figure 3.12: Wear of Metal Shafts with Chrome Steel Test Piece", + "texts": [ + " This concluded a set of reading for one experiment run. 7. The test piece was then removed using step 2 and weighed to determine the final mass after the experiment. The change in mass would indicate the wear of the material. 8. Steps 1 \u2013 7 were repeated for each condition of the experiment runs listed in Table 3.4. A chrome steel test piece was first used to observe the detrimental effects of metal-on- metal rubbing. In the absence of lubricant, severe wear marks were observed on both the interior of the bearing and the shaft as shown in Figure 3.12 and highlighted by the red circles. The coefficient of friction was recorded to be 0.52 for steel and 0.44 for aluminium at a rotation speed of 250 rev min-1 with a load of 20 N. This result highlights the importance of ensuring that only dissimilar materials should form rubbing pairs and that metal-to-metal rubbing should always be avoided. 40 The results for the runs with PTFE test piece are shown in Figure 3.13. The coefficient of friction ranges between 0.35 and 0.51 for the steel shaft and 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003704_86_s40648-016-0055-1-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003704_86_s40648-016-0055-1-Figure3-1.png", + "caption": "Fig. 3 Mechanical parameters of ring assembly", + "texts": [ + " We consider a mechanical successful condition of ring assembly. Jamming diagram is useful for considering a mechanical successful condition of mating [1]. Jamming diagram describes the successful condition on two-dimensional plane. Although conventional Jamming diagram is considered for the case of assembling a peg (shaft part) into a hole (ring part), we convert the previous case into the case of assembling a ring part into a shaft part in this paper. Mechanical parameters for Jamming diagram is shown in Fig.\u00a0 3. The parameters summarize in Table\u00a02. By approximating \u03b8 \u2248 0 and assuming that the radial thickness of the ring is zero, three equations are given as follows, (1)\u03b8 \u2264 \u03b8m = cos\u22121 ( Rs Rri ) By eliminating f1 and f2 from Eqs. (2), (3) and (4), Eq. (5) is given, In the case that the angle of a ring is negative, Eq. (7) is given, Additionally, a condition of friction is given as follows, According to Eqs. (5), (7) and (8), Jamming diagram for ring assembly is obtained as shown in Fig.\u00a04. If relationship of mechanical parameters are in a closed area (hatching area in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002382_es-auction-logistics-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002382_es-auction-logistics-Figure2-1.png", + "caption": "Figure 2. The conceptual model of cloud auction robot", + "texts": [ + " Therefore, an advanced AL system with high modularity, scalability, agility, and reconfigurability is needed. Mirroring the definition of cloud asset (Xu et al., 2015), CAR refers to a cloud controlled autonomous robot in the auction floor that is augmented with the capability of perception, communication, and mobility. Through utilizing sufficient cloud computing and storage resources, CARs could handle the mass data collected during the whole process of auction execution. Basically, CAR consists of two parts: hardware and software, and its concept model is depicted in Figure 2. The hardware also called \u201csmart transportation unit\u201d consists of industrial robot and smart devices like RFID readers. Each CAR is equipped with sensor, auto-localization, and local Auction trolleys (before consolidation) OUT OUT OUTININ Auction trolleys (after consolidation) Towing vehicle Internal distribution by vehicles Auction studio Pick-up and put-away by workers Worker Auction trolley receiving zone Pre-auction trolley staging zone Figure 1. Typical auction environment 1958 IMDS 117,9 navigation subsystems running independently and informing regularly its execution system about the status of each task (i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001345_f_version_1621584150-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001345_f_version_1621584150-Figure1-1.png", + "caption": "Figure 1. Forces and velocities acting on the blade element.", + "texts": [ + " The prediction parameters are discussed, and a realistic and accurate prediction model is obtained which reduces the calculation amount with respect to the vortex theory, in regard not only to airfoil performance calculation, but also to propeller performance calculation. The blade element theory is typically used to predict the performance of a propeller. The blade is divided into a finite number of tiny segments called blade elements, and the aerodynamic performance of each blade element can be obtained according to the airfoil theory. The blade element is integrated along the radial direction to obtain the total aerodynamic performance of the blade. Figure 1 presents the forces and velocities acting on the blade element, where V\u221e is the free stream speed, Va is the axial induction velocity, Vt is the tangential induction velocity, and V is the total velocity of the actual airflow; ns is the angular velocity of the propeller, and r is the radial position of the blade element; \u03d50 is the induced angle of attack, \u03d5 is the angle of actual airflow, \u03b8 is the pitch angle, and \u03b2 is the interference angle, which is given by: tan \u03b2 = Vi V0 = \u221a V2 a + V2 t V0 (1) The axial and tangential induction factors are defined as follows:{ a = Va V\u221e a\u2032 = Vt 2\u03c0nsr (2) The angle of actual airflow \u03d5 is as follows: tan \u03d5 = V\u221e + Va 2\u03c0nsr\u2212Vt (3) The angle of attack \u03b1, the velocity of the actual airflow V, and the local Reynolds number Re are given by: \u03b1 = \u03b8 \u2212 \u03d5 (4) V = \u221a (V\u221e + Va) 2 + (2\u03c0nsr\u2212Vt) 2 = V\u221e (1 + a)2 sin \u03d5 (5) Re = \u03c1Vb \u00b5 (6) The thrust and torque forces acting on the blade element are as follows:{ dT = 1 2 \u03c1V2CTV bdr dF = 1 2 \u03c1V2CFV bdr (7) where b is the chord length of the blade element. CTV and CFV are obtained from the geometric relationship shown in Figure 1; CL and CL can be determined by Re and \u03b1.{ CTV = CL cos \u03d5\u2212 CD sin \u03d5 CFV = CL sin \u03d5 + CD cos \u03d5 (8) Equation (5) is integrated into Equation (7), and the lift and torque acting on the propeller are given by: dT = 1 2 \u03c1V2 \u221e CTV Nbb (1+a)2 sin2 \u03d5 dr dM = rdF = 1 2 \u03c1V2 \u221e CFV Nbb (1+a)2 sin2 \u03d5 rdr (9) The momentum theory equations are shown below:{ dT = 4\u03c0r\u03c1V2 \u221ea(1 + a)drF dM = 4\u03c0r2\u03c1V\u221e(2\u03c0nsr)a\u2032(1 + a)drF (10) Combining Equations (9) and (10), we obtained: a = ( 4F sin2 \u03d5 \u03c3CTV \u2212 1 )\u22121 a\u2032 = ( 4F sin \u03d5 cos \u03d5 \u03c3CFV + 1 )\u22121 (11) where \u03c3 is the solidity ratio of the propeller, and F is the Prandlt momentum loss factor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004580_article_25837307.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004580_article_25837307.pdf-Figure1-1.png", + "caption": "Figure 1 shows the diagram of the dual-stator toroidal motor. The motor consists of four basic elements: (1) the worm inner stator; (2) radially positioned planets; (3) outer stator; and (4) rotor upon which the planets are mounted. Among them, the inner stator is fixed and the armature coils are mounted in helical slots of its surface. The planets adopt permanent magnets for excitation, the N and S pole permanent magnets mounted alternately on each planet. Outer stator has several helical magnetic steel or alternating NS pole permanent magnets embedded in the bracket.", + "texts": [], + "surrounding_texts": [ + "Dual-stator toroidal motor with hybrid excitation which integrates power and drive can transmit large torque in a small size. The integration of mechanical elements and electromagnetic ones makes control easier, the motor also assemble with the decelerator. So the toroidal motor is suitable for fields such as aviation and space flight[1-3]. The servo system can be substituted by toroidal motor to simplify the structure of an existing electromechanical system. The motor can also be used in robots and other fields that require accurate control. As more and more electrical and control techniques are utilized in engineering field, new-style motors become advancing edge of electromechanical science[4,5]. Thus the dual-stator toroidal motor with hybrid excitation has more expansive application prospect. When a specific relationship is satisfied between the planet pitch, lead angle on the stators and the number of pole pairs, then the N pole of one element will corresponding to S pole of the other elements. A toroidal circular electromagnetic field is formed when the alternating current is connected to the coils of the armature worm. The magnetic forces between N and S poles of \u00a9 2015. The authors - Published by Atlantis Press 423 different elements are the driving force. It drives the planets to rotate about their own axes, and at the same time, the attractive force outside between planets and helical outer stator cause the rotor to rotate about its own axis. So output with a large torque at low speed is generated. In this study, from the electromechanical coupled model of toroidal motor, the transfer function of the speed control for the drive system is derived. In order to improve the speed response of the motor system, a speed feedback control model is presented and a anticipatory controller is designed. The time-domain response of speed control system is simulated and investigated. The results are useful for designing and manufacturing the controller for the novel motor." + ] + }, + { + "image_filename": "designv8_17_0001751_ticle_download_19_31-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001751_ticle_download_19_31-Figure1-1.png", + "caption": "Figure 1 Mass spring system with mass sliding against dry surface.", + "texts": [], + "surrounding_texts": [ + "Damping in any structure is due to several Mechanisms. Coulomb friction damping is because of sliding of two surface against each other. The friction force is F = \u00b5N. where \u00b5 is coefficient of friction which includes dynamic and static friction. Free vibration is a major cause for the motion. As motion starts the friction force becomes independent of velocity and acts always opposite to the direction of motion. The sign of friction force will change when the direction of motion changes. When motion starts the object will move back and forth in either left to right direction or right to left direction. Two equations of motion will be formed. The equation of motion of free vibration when object moves from left to right mu\u0308+ ku = \u2212F (1) When object moves from right to left mu\u0308+ ku = F (2) In discrete modeling mass spring system was created by using slide-plane connection type in ABAQUS. Slide plane connections helps to constrain the position of node to remain on a plane defined by the local normal direction. Coulomb friction in slide plane connection relates the friction forces to the kinematic constraint forces. The frictional effect is written as \u03a6 = p(f) \u2212 \u00b5FN \u2264 0 (3) In the above expression p(f) represents the magnitude of tangential frictional traction and FN is the normal force which produces friction and \u00b5 is the coefficient of static and dynamic friction. In slide plane, frictional stick occurs if \u03a6 < 0 and sliding will occur if \u03a6 = 0. FN , normal force which is the sum of connector force, Fc and internal contact force FC int. FN = Fc + FC int (4) The magnitude of tangential frictional traction p(f) is computed p(f) = \u221a f21 + f22 (5) In continuum modeling two stone blocks were used. To study the contact behavior of two stone blocks Coulomb friction was introduced. Coulomb friction comes whenever two surfaces come in contact with one another." + ] + }, + { + "image_filename": "designv8_17_0000437_-ijaefea20210709.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000437_-ijaefea20210709.pdf-Figure7-1.png", + "caption": "Figure 7. Factor of safety", + "texts": [], + "surrounding_texts": [ + "In addition, the machine's sorting speed is faster than that of a human operator, resulting in a significant reduction in the cost of inventory. When it comes to packaging, the industry where it is made is where it belongs. Used as a large-scale piece of machine hardware (such a machine's construction). Nuts of close dimension are utilized in construction of structures and towers. Structural analysis is done for the sorter machine. Equivalent stresses, total deformation and factor of safety is checked. Design is safe. Design and Analysis of Nut and Bolt Separating Machine 101 Int. J. of Analytical, Experimental and Finite Element Analysis www.rame.org.in" + ] + }, + { + "image_filename": "designv8_17_0000010_es-2018-18-3-199.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000010_es-2018-18-3-199.pdf-Figure1-1.png", + "caption": "Fig. 1. Geometrical structure of the proposed M-SweepSAR mode.", + "texts": [ + " Therefore, antenna length should be larger than twice the satellite speed divided by the PRF, as indicated in [9]. A long antenna length increases the total weight and launching cost of payload. To overcome the disadvantages of resolution degradation due to increased antenna length (i.e., Azimuth resolution (\u03c1A) is proportional to antenna length; for example, \u03c1A = L/2) and the asymmetric beam patterns caused by offset feeding structures, we developed a modified SweepSAR (M-SweepSAR) system with a new imaging scenario. Fig. 1 shows the geometrical structure of M-SweepSAR. In this system, the frequency used is assumed to be the C-band, which is highly applicable to disaster/water-level monitoring, and the number of sub-swaths is assumed to be 12. Table 1 summarizes the main parameters used in the performance evaluation of the proposed SAR system. The total radar swath range is 150 km, and the reflected signals sequentially come from a near range in the order of array. As shown in Fig. 2, two PRF signals higher than 2,500 Hz are simultaneously transmitted into the overall swath area to avoid a blind range, which is the area of overlap between the timing of a transmitted signal and the timing of a signal returned from the nadir flight direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001792_-3_2008_7-3_671__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001792_-3_2008_7-3_671__pdf-Figure4-1.png", + "caption": "Figure 4 Dynamic driving forces", + "texts": [ + "848] Hz The effect of leg inertia on the Stewart platform Comparisons between current model and traditional one are made on the static and dynamic driving forces. In the simulation of static forces, all the velocities and accelerations remain zero, there is no the external force and torque exerted on the platform, and the moving platform moves horizontally along z-axis between -250mm and 250mm. It's obvious that the inertia of the leg especially the piston part influences a lot on the static driving forces In figure 4, the moving platform moves horizontally along z-axis with a sinusoidal motion (100sin(nt) mm), while other velocities and accelerations remain zero. The three lines (N 1, N 2, N 3) are the results with current inertia matrix model, and the other three lines (O_1, O_2, O_3) are with traditional one including only the translational part of the leg. Copyright (C) 2008 by JFPS, ISBN 4-931070-07-X 674 Influence of design parameters on natural frequency The influence of design parameters on natural frequency is shown in figure 5-figure 13" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004255_cle_download_175_155-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004255_cle_download_175_155-Figure15-1.png", + "caption": "Figure 15 Pressure diagram of windward surface of pneumatic impeller at different angles of attack", + "texts": [ + " With the increase of the angle of attack, the area of the minimum pressure surface of the wings of the three types of pneumatic impeller is basically unchanged. a. No impeller b. The front wing Different installation positions of the pneumatic impeller will also have an impact on itself, and the output power of the pneumatic impeller at different installation positions is shown in Figure 14. It can be seen from the figure, no matter where the pneumatic impeller is located, the output torque continues to decrease with the increase of the angle of attack. As shown in Figure 15, the large pressure area on the windward side of the pneumatic impeller at an angle of attack of 0\u00b0 is much larger than that at an angle of attack of 12\u00b0. Therefore, the pneumatic impeller should be opened at a small angle of attack to collect more wind energy to improve the energy conversion efficiency of the pneumatic impeller. But when installed in pneumatic impeller under the wing output torque minimum and different angles of attack, the biggest change in the front wing with maximum output torque and different angles of attack change when the youngest, pneumatic impeller best location for the front wing, both to reduce the influence of aerodynamic characteristics of aircraft pneumatic impeller, in the case of large angle of attack is more conducive to the aircraft flight, at the same time, it reduces the influence of agricultural aircraft on the pneumatic impeller, so that the pneumatic impeller always keeps the appropriate output torque" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000432_s.eu_pliki_art_9564_-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000432_s.eu_pliki_art_9564_-Figure3-1.png", + "caption": "Fig. 3. Trailing vortices behind blades of an eccentrically positioned Rushton turbine (iso-surfaces of Q-criterion (Q = 1500 [s\u20132] coloured by velocity magnitude [m/s], a) e = 0 , b) e = 0.25 R, c) e = 0.5 R", + "texts": [ + " Maximum values of underpressure were determined for the largest shaft eccentricity (e = 0.5R) and differed in comparison with central shaft position (e = 0) by 30%. During the Rushton turbine rotation vortices that differ in shape and scale are generated in the mixing vessel. Some of them have a scale comparable with the apparatus scale [6], the others are smaller and they are inducted in the impeller zone. A location of vortex cores can be visualised in a number of different ways, e.g. Q-criterion, \u03bb \u2013 criterion or iso-surfaces of vorticity or helicity. Figure 3 presents example visualisations of trailing vortices generated behind Rushton turbine blades, created with the use of the Q-criterion. This criterion is defined as: Q S= \u2212 > 1 2 02 2[ ]\u2126 where: S \u2013 the rate-of-strain tensor and \u2126 is the vorticity tensor. Each visualisation is prepared at the same scale (Q = 1500 [s\u20132]). Iso-surfaces are additionally coloured by velocity magnitude. The movement of the impeller blades induces an intense flow in the blade zone. Firstly, liquid swirls are observed on the front side of the blades and close to the blade edges. Next, two separate, longitudinal trailing vortices above and below the impeller disc are generated. They are elongated in a tangential flow field. The biggest scale trailing vortices are seen for the highest impeller eccentricity e = 0.5R (Fig. 3c). For this case the greatest tangential velocities were also determined. The above-presented numerical visualisations of trailing vortices formation were confirmed experimentally, e.g. [1, 2, 8]. As a result of an impeller blade movement the main liquid flow is divided into a tangential flow and a radial one. Figure 4 presents velocity vector maps obtained for the vessel\u2019s vertical cutting plane (XZ), passing through the vessel axis and collinear with the impeller displacement. These maps show the distribution of velocity vectors for a radial-axial direction", + " Displacement of the impeller towards the vessel wall causes a visible deflection of the discharge stream to the bottom and a generation of small-scale vortices in the zone close to the tank wall, under the impeller (Fig. 4b, c). These changes and differences in the flow pattern were caused by the effect of the vessel wall and the generation of unsymmetrical, large-scale vortices, which are initiated in the impeller region [6]. Preliminary comparisons of these maximum values of tangential velocities (Fig. 3) with radial ones showed that tangential components are about 30% greater. One of the parameters that characterise a turbulence flow in mixing vessels is turbulence kinetic energy k (TKE). This quantity is often used for the estimation of impeller performance efficiency, characterisation of turbulence in an impeller discharge stream and also in dispersion processes. The contour maps presented in Figure 5 show changes of k with impeller eccentricity and confirm earlier described observations and tendencies" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000020__ms-13-1011-2022.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000020__ms-13-1011-2022.pdf-Figure2-1.png", + "caption": "Figure 2. Schematic illustration of the tooth profile section and force analysis.", + "texts": [ + " The principle is expounded through theoretical research, and the feasibility is verified by a numerical method. As shown in Fig. 1, coordinate systems S1 and S2 are connected to driving gear and driven gear, and coordinate systems Sf and Sp are fixed with the frame. In initial engagement position, S1 and S2 coincide with Sf and Sp, respectively. \u03d51 and \u03d52 are the rotation angles of the driving and driven gear, respectively. Space curve L1 and L2 exist on the surfaces of the driving gear and driven gear. As shown in Fig. 2, the contact form of the tooth surfaces is concave\u2013convex.R1 is the section radius of surface 1, and R2 is the section radius of surface 2.M1 is a contact point that exists on the forward contact curve, and M2 is a contact point that exists on the reverse contact curve. To avoid interference, the induced normal curvature K12 should be less than 0, which is shown as Eq. (1) (Litvin, 1992). K12 < 0. (1) The surface equations of 1 and 2 are expressed as Eqs. (2) and (3) if contact curves pass through point M1", + " \u03d52PTE = \u03d51 i12 +PTEs (16) im 2 (t,\u00b52)=Xim 2 (t,\u00b52)i+Y im 2 (t,\u00b52)j ++Zim 2 (t,\u00b52) Xim 2 (t,\u00b52)= (xim 2 \u2212 \u221a 2 2 R2)+ xr2 Y im 2 (t,\u00b52)= (yim 2 \u2212 \u221a 2 2 R2)+ yr20\u2264 \u00b52 \u2264 \u03c0 3 (yim 2 \u2212 \u221a 2 2 R1+ \u221a 2 2 R2)+ yr2\u2212\u03c03 \u2264 \u00b52 \u2264 0 Zim 2 (t,\u00b52)= zim 2 . (17) Here, xim 2 , yim 2 and zim 2 are parameters of the improved contact curve of the driven gear. They can be obtained in the same way for obtaining x2, y2 and z2; one just needs to place \u03d52PTE instead of \u03d52 in the formula. While the tooth surface equations are obtained, the maximum contact stress of a loaded gear drive could also be obtained by the application of the Hertz contact theory.Shown in Fig. 2, force of the gear drive can be represented with Eq. (18). F n = F r cos(rr ,n) F r = \u221a 2\u00b7T l rr = ( \u221a 2 2 , \u221a 2 2 ,0) . (18) Here, F n is the force which is acting on the gear tooth surface, l is the arm of the force, T is the torsion load, rr is the unit vector of F r , and cos(rr ,n) is the cosine value of the angle between vector rr and n. Based on the Hertz contact theory, the maximum contact stress can be obtained by putting Eq. (18) into Eq. (19). \u03c3max = 3 |F n| 2\u03c0la lb . (19) la and lb are the long half-axis and short half-axis of the contact ellipse, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure4-15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure4-15-1.png", + "caption": "Figure 4-15. Antenne dans un rep\u00e8re sph\u00e9rique et cart\u00e9sien", + "texts": [ + " Bande passante obtenue pour l'antenne PIFA miniature en fonction du substrat .. 113 Figure 4-12. Dimensions d'un syst\u00e8me \u00e0 diversit\u00e9 spatiale utilisant deux antennes miniatures. 114 Figure 4-13 Sch\u00e9ma de l'antenne PIFA agile en polarisation et en fr\u00e9quence............................ 116 Figure 4-14. Tableau de correspondance entre les \u00e9tats de l'antenne agile et les \u00e9tats des diodes PIN .............................................................................................................................................. 117 Figure 4-15. Antenne dans un rep\u00e8re sph\u00e9rique et cart\u00e9sien ...................................................... 118 Figure 4-16. Champ \u00e9lectrique total en dBV/m et ellipses de polarisation \u00e0 3,53 GHz lorsque le plan de cour-circuit 1 est connect\u00e9.............................................................................................. 119 Figure 4-17. Champ \u00e9lectrique total en dBV/m et ellipses de polarisation \u00e0 3,53 GHz lorsque le plan de court-circuit 2 est connect\u00e9 ................................", + " Cette PIFA pr\u00e9sente donc quatre \u00e9tats diff\u00e9rents r\u00e9sultant de l'association d'une polarisation lin\u00e9aire soit verticale, soit horizontale avec une fr\u00e9quence de r\u00e9sonance basse ou haute. L'\u00e9tat des diodes PIN et les potentiels de chacun des plateaux pour ces quatre \u00e9tats sont d\u00e9crits dans le tableau de la Figure 4-14. Pour l'instant cette structure a seulement \u00e9t\u00e9 simul\u00e9e \u00e0 l'aide de CST Microwave Studio. Les diodes PIN sont mod\u00e9lis\u00e9es comme des \u00e9l\u00e9ments capacitifs de 25fF lorsque les diodes sont bloqu\u00e9es et des \u00e9l\u00e9ments r\u00e9sistifs de 3 \u2126 lorsqu'elles sont passantes. L'antenne est consid\u00e9r\u00e9 dans le rep\u00e8re d\u00e9finit sur la Figure 4-15. 118 L'agilit\u00e9 en polarisation est illustr\u00e9e par la Figure 4-16 et la Figure 4-17 qui repr\u00e9sentent l'\u00e9tat de polarisation et le champ \u00e9lectrique total rayonn\u00e9 \u00e0 3,53 GHz en fonction de l'azimut, Phi, et l'\u00e9l\u00e9vation, Th\u00eata. Ces figures correspondent respectivement \u00e0 la PIFA polaris\u00e9e verticalement (plan de court-circuit 1 connect\u00e9) et \u00e0 la PIFA polaris\u00e9e horizontalement (plan de court-circuit 2 connect\u00e9). Le changement d'\u00e9tat de polarisation est clairement visible l\u00e0 o\u00f9 le rayonnement de l'antenne est le plus fort, c'est-\u00e0-dire pour 130\u00b0 < Phi < 230\u00b0 et 60\u00b0 < Theta <120\u00b0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure30-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure30-1.png", + "caption": "Figure 30: von-Mises stress on compliant joints.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure14-1.png", + "caption": "Figure 14. The simulation results of the maximum stress on the electric motor mount are 0.32 MPa.", + "texts": [ + " Using the frame analysis feature, the simulation results on the electric motor mount are bending moment, maximum stress, and displacement, each with values of 1674.76 N.mm, 0.35 MPa, and 0.0007 mm. Figure 13 shows the simulation results of the maximum stress value on the electric motor mount. 2. Control panel and battery mount The control panel and battery holder receive a weight force of 31.392 N acting in the y-axis direction. This section only has one rod to support the control panel and battery. The simulation results obtained are bending moment, maximum stress, and displacement, values are 1538.65 N.mm, 0.32 MPa, and 0.0007 mm, respectively. Figure 14 shows the simulation results of the maximum stress values at the control panel and battery mounts. 3. Driver body mount The driver's body mount receives a weight force of 466.956 N, which acts in the y-axis direction. This part consists of two rods that support the driver's body. The simulation results for the total of the two driver rods were bending moment, maximum stress, and displacement, respectively, with values of 21683.48 N.mm, 4.63 MPa, and 0.010 mm. Figure 15 shows the maximum stress value simulation results at the driver's body mount" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure13-1.png", + "caption": "Figure 13: Fourth iteration of compliant landing mechanism.", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0004245_SIJINT-2015-088__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004245_SIJINT-2015-088__pdf-Figure2-1.png", + "caption": "Fig. 2. Coordinate system of hot rolling process and cross-section of the strip.", + "texts": [ + " Also, the first assumption was based on the idea that the rotated angle of the strip at the delivery side \u03b82 is reduced to rotated angle at the entry side \u03b81 divided by \u03bb. From the definition of curvature (Eq. (3)), they explained that additional curvature is generated by the rotation of the strip scaled by \u03bb2 because dx2 increases to \u03bbx1, whereas d\u03b82 decreases to d\u03b82/\u03bb. The basis of the first assumption was established in the first study4) of side-slipping which represented the timevarying location of points on the centerline (Fig. 2). If the strip is regarded as a rigid body, the location of a point on its centerline can be represented as a function of time. If the longitudinal direction of the strip is defined as the x-axis, and the transversal direction of the strip as the y-axis, the velocity of the point v(t) at time t can be represented as v t y t v t( ) ( ) ( ),= \u22c5 +\u03c9 1 ......................... (4) u t x t( ) ( ),= \u2212 \u22c5\u03c9 ............................. (5) where v, u are velocity along the x, and y-axis respectively, v1 is the average speed of the strip at the entry side, and \u03c9 is the rotation speed of the strip" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002123_le_download_3242_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002123_le_download_3242_pdf-Figure1-1.png", + "caption": "Fig. 1. Clutch system dampening effect", + "texts": [ + " In this study, the 1-D modeling of powertrain system, including metallic clutch damper springs, was subjected to vibration optimization with the Simulated Annealing (SA) algorithm. This novel methodology accelerates the powertrain system vibration optimization and provides assumptions eliminating cost and time in real vehicle testing. Keywords-clutch damper; simulated annealing; 1-D modeling; damper torque; powertrain system; driving comfort; vibration I. INTRODUCTION Clutch damper springs, used in vehicle powertrain systems, are of great importance as they damp engine vibrations during torque transmission (Figure 1). Prominent studies have been carried out on the optimization of the vibration on vehicles. Torsional mode analysis was carried out in [1] investigating the modeling of powertrain systems, including automated transmission. The hydraulic hybrid powertrain system was analyzed in [2] using 1-D modeling. Analysis using 1-D simulation at stiffness levels of the clutch disc damper were studied in [3]. The natural frequency of vehicle components were studied in [4], assuming on optimal weight values. In [5], an analysis on the vibration frequency level of a 3-cylinder engine proposed improvements to the clutch design" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002350_itation-pdf-url_5336-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002350_itation-pdf-url_5336-Figure8-1.png", + "caption": "Figure 8. Revolute robot scheme", + "texts": [], + "surrounding_texts": [ + "Can be useful to include D-H transformation matrix of equation (24), in camera model (33), in this way it is possible to obtain a perspective representation of the robot in an image plane by means joint coordinates. In homogeneous coordinates, using matrix notation, it is possible to write equation (33): www.intechopen.com Video System in Robotic Applications 231 [ ] \u23aa \u23aa \u23ad \u23aa \u23aa \u23ac \u23ab \u23aa \u23aa \u23a9 \u23aa \u23aa \u23a8 \u23a7 \u22c5= \u23aa \u23aa \u23ad \u23aa \u23aa \u23ac \u23ab \u23aa \u23aa \u23a9 \u23aa \u23aa \u23a8 \u23a7 1 \u251er,w \u251fr,w \u03ber,w K \u251er,w 1 1 0 v u (60) where matrix K is: [ ] \u23a5 \u23a5 \u23a5 \u23a5 \u23a5 \u23a5 \u23a5 \u23a6 \u23a4 \u23a2 \u23a2 \u23a2 \u23a2 \u23a2 \u23a2 \u23a2 \u23a3 \u23a1 \u2212 \u2212 = 0100 0000 00v v\u03b4 f 0 00u0 u\u03b4 f K (61) Considering equation (2), it is possible to write (60) in the frame O,x,y,z, external to images : [ ] [ ] \u23aa \u23ad \u23aa \u23ac \u23ab \u23aa \u23a9 \u23aa \u23a8 \u23a7 \u23aa \u23ad \u23aa \u23ac \u23ab \u23aa \u23a9 \u23aa \u23a8 \u23a7 \u22c5 \u22c5 = 1 zw yw xw TK zwzD 1 1 0 v u (62) Considering equation (9), If we define the vector N: { } { }T,,,N \u03c2 \u03c2\u03c2\u03c2= t zyx (63) (62) becomes: { } { } [ ] [ ] \u23aa \u23ad \u23aa \u23ac \u23ab \u23aa \u23a9 \u23aa \u23a8 \u23a7 \u23aa \u23ad \u23aa \u23ac \u23ab \u23aa \u23a9 \u23aa \u23a8 \u23a7 \u22c5 \u22c5 = 1 zw yw xw TK wN 1 1 0 v u T (64) Equation (64) represents the relation between coordinates (u,v) of an assigned point, (e.g. a robot end-effector point expressed in pixels in the image plane) and the coordinates of the same point in the world (Cartesian) frame. In this equation, it is possible to include D-H transformation matrix, to obtain a model that describes the relation between coordinates (u,v) of robot end-effector expressed in pixels, in image plane, and end-effector coordinates in the robot joints space. The relation that synthetizes the model is following: { } { } { } [ ] [ ] { }nw~0 nTTK nw~0 nTTN 1 vu, \u23a5\u23a6 \u23a4 \u23a2\u23a3 \u23a1\u22c5 \u23a5\u23a6 \u23a4 \u23a2\u23a3 \u23a1\u22c5 = (65) where: \u2022 {u,v}: vector with end-effector coordinates expressed in pixel in image plane; www.intechopen.com Frontiers in Brain, Vision and AI 232 \u2022 { } nw~ : end-effector homogeneous coordinates in robot frame n, for a generic robot with n d.o.f; \u2022 [Tn0]: Denavit-Hartenberg robot transformation matrix from base frame to end-effector frame; www.intechopen.com Video System in Robotic Applications 233" + ] + }, + { + "image_filename": "designv8_17_0002867_anagement_System.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002867_anagement_System.pdf-Figure5-1.png", + "caption": "Fig. 5. Hardware Components of the Homergy Box.", + "texts": [ + " In our implementation, the Firebase Realtime Database was selected due to well-documented libraries available for both Android/iOS/Web platforms and the NodeMCU platform. The streaming feature of the Firebase Realtime Database was used to send commands to Homergy Boxes in real time. Any cloud-based implementation (e.g. MQTT used in [13]) that allows real-time communication between the NodeMCU and the Homergy Mobile App will also work. The exterior of the Homergy Box hardware is shown in Fig. 15. The internal components are shown in Figs. 5 and 6. Below are the properties of the hardware used in the Homergy Box; 1) Four-channel Relay board (Fig. 5-A): There are four of these relay modules in the Homergy Box, totalling sixteen (16) relay channels. The relay module serves as coupling between the high-voltage home circuit and the low-voltage Homergy Box circuit. The module has its internal low-voltage digital signal circuit isolated from the relay through opto-coupling. The relay\u2019s contact capacity is 10A 250V AC / 10A 30V DC, whilst the Digital circuit operates at 5V 20mA (DC). The module is therefore compatible with the Arduino\u2019s 40mA General-Purpose Input/Output (GPIO) pins, and with common household AC appliances. The relays are connected to the appliances as shown in Fig. 7. The Normally Closed (NC) port of the relay is placed between the source and the load. This way, current can still www.ijacsa.thesai.org 725 | P a g e flow when the Homergy Box is off. A \u201cHigh\u201d from the Arduino GPIO pin activates the relay and switches the appliance off. 2) Arduino Mega 2560 (Fig. 5-B): The Arduino\u2019s properties are detailed in Table I. 3) 16x04 I2C LCD (Fig. 5-C): An LCD is included to provide information on the state of the Homergy Box to the user. During initial configuration, the LCD guides the user in step-by-step procedure to configure the Wi-Fi connection (SSID and password). Any errors (such as disconnection from the Wi-Fi or the Cloud) is displayed on the LCD. The LCD is controlled by the NodeMCU. 4) NodeMCU (Fig. 5-D): Table II shows the properties of the NodeMCU module used. There are three main parts of the Homergy system; The Microcontroller (Arduino), the Communications (NodeMCU/ESP8266 and Cloud) and the Homergy Mobile App. Arduino: The Arduino makes use of the SoftwareSerial library to communicate with the NodeMCU over a serial connection. The Arduino has been programmed to always listen to the NodeMCU for instructions. These instructions are received as a JavaScript Object Notation (JSON) objects which are parsed and executed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure4-1.png", + "caption": "Figure 4. Gripper Exploded View", + "texts": [ + " Since the drive screw cannot move, the drive block is pulled toward it. As the block moves back, pins connected to the fingers are pulled back which closes the grippers (See Figure 3). When the gripper closes onto a pipe completely the torque supplied by the motor is turned into a linear force which is transferred through the thrust bearing to the load washer. The load washer is then able to provide force feedback to the motor to shut it off when the desired load on the pipe is obtained. An exploded view of the assembly can be seen in Figure 4. Page 4 of 15 An extension system is incorporated into the Pipe Traveler design to allow the second set of grippers to extend to the next pipe. Also, after a pipe is released, it is necessary for the pipe traveler to retract from a pipe before it rotates to another pipe. To provide the motive force for extension and retraction, two pneumatic cylinders are used (Figure 5). Four commercial linear slides are used to provide linear stability and support the large moment during extension. The rotation mechanism operates by using a pneumatic cylinder to push a drive wheel against the pipe" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004810_9781644902479_83.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004810_9781644902479_83.pdf-Figure1-1.png", + "caption": "Fig. 1. A simplified, rectangular buckled sheet, affected by tension and compression stresses (the ut edge displacement is interpreted along the L direction).", + "texts": [ + " However, when blank holder is applied during a deep drawing process, the optimum of the external work of the blank holder (W) is exactly the same as the difference of the two mentioned energy terms: \ud835\udc4a\ud835\udc4a = \ud835\udc38\ud835\udc380 \u2212 \ud835\udc38\ud835\udc38\ud835\udc4f\ud835\udc4f (1) Assuming that the external work of the blank holder can be mathematically described in the knowledge of the normal force and the buckling deflection, as well as the normal force itself is a non-linear function of the buckled height (\u03b4), the normal pressure can be expressed in the following form, according to [2]: \ud835\udc5d\ud835\udc5d = 3(\ud835\udc38\ud835\udc380\u2212\ud835\udc38\ud835\udc38\ud835\udc4f\ud835\udc4f) 4\ud835\udeff\ud835\udeff\ud835\udeff\ud835\udeff\ud835\udeff\ud835\udeff (2) This is the case of a simplified, rectangular flat blank, which has L length, w width and s thickness (see Fig. 1). Applying the deduction of the energy terms based on [2,3], in which Swift hardening law [12] and Hill48 anisotropic plastic potential [13] was used, each energy members can be obtained according to Eq. 3 and Eq. 4. \ud835\udc38\ud835\udc380 = 1 \ud835\udeff\ud835\udeff\u222c\ud835\udf0e\ud835\udf0e\ufffd \ud835\udc51\ud835\udc51\ud835\udf00\ud835\udf00 \u0305\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51 = \ud835\udc3e\ud835\udc3e\ud835\udeff\ud835\udeff\ud835\udc3e\ud835\udc3e \ud835\udc5b\ud835\udc5b+1 (\ud835\udf00\ud835\udf000 + \ud835\udc50\ud835\udc501\ud835\udf00\ud835\udf0010)\ud835\udc5b\ud835\udc5b+1 (3) \ud835\udc38\ud835\udc38\ud835\udc4f\ud835\udc4f = 2\ud835\udc3e\ud835\udc3e\ud835\udc3e\ud835\udc3e \ud835\udc5b\ud835\udc5b+1 \ufffd\ud835\udc50\ud835\udc502\ud835\udc3e\ud835\udc3e 2 + (\ud835\udf00\ud835\udf000 + \ud835\udc50\ud835\udc503) \ufffd 1 \ud835\udc5a\ud835\udc5a2\ud835\udeff\ud835\udeff + \ud835\udc3e\ud835\udc3e 2 \ufffd\ufffd \ud835\udc5b\ud835\udc5b+1 \u2219 \ufffd 1 \ud835\udc5a\ud835\udc5a2\ud835\udeff\ud835\udeff + \ud835\udc3e\ud835\udc3e 2 \ufffd \u2212\ud835\udc5b\ud835\udc5b \u2219 \ud835\udc61\ud835\udc61\ud835\udc61\ud835\udc61\ud835\udc61\ud835\udc61\u22121(\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a) (4) In these functions, K, \u03b50 and n refer to the constants of the Swift hardening law, while c1, c2 and c3 are material parameters considering the plastic anisotropy and the stress state" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002748_e_download_7184_5916-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002748_e_download_7184_5916-Figure12-1.png", + "caption": "Fig. 12\u2013 Before octagon cutout", + "texts": [], + "surrounding_texts": [ + "---------------------------------------------------------------------------------------------------\nDOI 10.14311/CEJ.2021.01.0014 198\n4\n4\n1\n2\n2 tan 22.5\nE\nE\nX c\nc Y\n\n \n(13)\n5\n5\n1\n2\n2 tan 22.5\nE\nE\nX c\nc Y\n\n \n(14)\n6\n6\n2 tan 22.5\n2\nE\nE\nc X\nc Y\n \n(15)\n7\n7\n2 tan 22.5\n2\nE\nE\nc X\nc Y\n \n(16)\n8\n8\n1\n2\n2 tan 22.5\nE\nE\nX c\nc Y\n\n \n(17)\nA hexagon on the upper chord of the mid-span joint is created according to the above\nmethod, and connected with the joint of the three-direction grid type single-layer grid structure to form a partial web member of the three-direction grid type prestressed giant grid structure. The schematic diagram is as shown in Figure 11, and the length is marked as L4. The length of L4 can be calculated by Formula (18):\nwith the upper part of the inverted quadrangular pyramid truss structure on the outer edge, so that", + "---------------------------------------------------------------------------------------------------\nDOI 10.14311/CEJ.2021.01.0014 199\nthe upper part of the structure forms four complete new out edges, namely the edge of the outermost edge of an upper chord of the whole structure, if it is external, cut it out.\nEach corner point of the polygon after cutting is respectively connected with the joint of the\nthree-direction grid type single-layer grid structure to form the web member of the three-direction grid type prestressed giant grid structure, and the joint connection schematic diagram is shown in Figure 13 below.\nThe web member shown in the above figure is divided into two parts, one part is the corner\npoint of the regular octagon connected with the three-direction grid type prestressed huge grid structure, and the length is marked as l5, the other part is the center point of the regular octagon connected with the joint of the three-direction grid type prestressed huge grid structure, and the length marked as l6 can be calculated by formula (19):\n5\n6\n2sin 22.5\nc l\nl h\n\n \n(19)\nAfter the webs are formed, the center points of the hexagons and the octagons are\nconnected with the corner points of the hexagons and the octagons to form partial top chords. Thus, a three-direction grid type prestressed mega-grid structure is finally formed.\nSelection of structural calculation model\nDetermination of basic geometry size: This paper refers to the geometry size design of\n306m \u00d7 90m hangar roof structure of Capital Airport [48], the control parameter of three-direction grid prestressed reticulated megastructure is set as follows: length 300m, span 150m, structural", + "---------------------------------------------------------------------------------------------------\nDOI 10.14311/CEJ.2021.01.0014 200\nwhole thickness 6m, structural megagrid number in long direction 4, structural megagrid number in span direction 4. The number of interjoint grids of long direction giant component is 10, and the number of interjoint grids of span direction giant component is 8. The number of interjoint grids of oblique giant components is 6. Replace the lower chords on the main diagonal and the middle span with prestressed cables, and finally form a three-direction grid type prestressed mega-grid structure as shown in Figure 14.\nThe modeling of square pyramid space truss structure can be obtained by inputting the\ncorresponding parameters in MSTCAD software; The plane dimensions of square pyramid space grid structure are 300m in length direction, 150m in span direction, 31 grids in length direction, 19 grids in span direction and 6m in thickness. The load and constraint conditions are the same as those of the prestressed mega grid structure. The established model is shown in Figure 16 below:\nAnalysis of natural vibration characteristics of three-direction grid prestressed\nreticulated mega-structure\nThe steel grade of the members is Q345, the nominal diameter of the prestressed cable is\n300mm, and the basic level of the selected pretension is 23000kN. The modal analysis of the three-direction grid type prestressed huge grid structure model is carried out by using sap2000 software, and 1. 0 dead load + 0. 5 times live load is considered as the representative value of gravity load. In order to compare and analyze the dynamic characteristics of two kinds of space truss structures, the orthogonal square pyramid space truss in chapter 4 and chapter 3 are used to" + ] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure15-1.png", + "caption": "Figure 15. Thermal field distribution under condition of water cooling used in the casing and the inner rotor when both the SM and the DRM are running at the rated speed and rated load.", + "texts": [ + " Meanwhile, due to the existence of axial forced air, there is a certain axial temperature difference for each part within the core length; the temperature of the end windings at windward side is much lower than that at leeward side. By comparison of Tables 6 and 7, it shows that the CS-PMSM can run safely when the water cooling used in the casing and axial forced air are simultaneously adopted in the CS-PMSM. When both the SM and the DRM are running at the rated speed and rated load, the 3-D thermal field distribution is calculated under condition of water cooling used in the casing and the inner rotor, as shown in Figure 15. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the water inlet side, middle cross-section, and the water outlet side of the CS-PMSM are shown in Figure 16. The selected water inlet, middle and water outlet cross-sections are the same as those in Section 4.1. The highest temperature of each part in the above three cross-sections is shown in Table 8. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 8" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003902_om_article_21697_pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003902_om_article_21697_pdf-Figure7-1.png", + "caption": "Fig. 7. Pull rope displacement sensor structure and measurement principle", + "texts": [ + " The CKS256 high-precision rope-type displacement sensor is selected as the measurement of the swing angle of the crane. The rope-type displacement sensor can be directly applied to the measurement of the linear guide motion system. The rope displacement sensor is the perfect combination of an angle sensor and a linear displacement sensor. It has the advantages of small installation size, compact structure, large measuring stroke, and high precision. The structure and measurement principle is shown in Fig. 7. The maximum rotation speed of the actual crane slewing mechanism is 0.8 rev/min. The voltage input signal of the proportional and rotary proportional valves is \u00b110 V. In order to make the experimental results compared with the simulation results, the input signal of the rotary proportional valve in the simulation model set in MATLAB is also \u00b110 V and maximum rotational speed of the sway and variable amplitude mechanism is also 0.8 revs/min. Finally, the comparison between the experimental and simulated swing angles can be obtained" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003908_f_version_1694336155-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003908_f_version_1694336155-Figure1-1.png", + "caption": "Figure 1. Characteristics of the Quadrotor with a suspended Single Pendulum. Figure 1. Characteristics of the Quadrotor with a suspended Single Pendulum.", + "texts": [ + " Their performance in different scenarios and with imposition of external disturbances will be presented. An analysis of the results obtained from these simulations will be analyzed in Section 4. Section 5 provides some conclusions. In this section, we define the dynamics of a multirotor and its suspended payload, which are then cascaded together to form a single system. This is the system upon which the proposed controllers will be applied and subsequently compared. The characteristics of the multirotor slung load system are as shown in Figure 1. Let qtrans = [ x y z \u03b8x \u03b8y ] and qrot = [\u03d5 \u03b8 \u03c8] denote the translational and rotational state vectors of the system, such that q = [ qtrans qrot ] represents the overall system state vector, with x, y, and z denoting the multirotor position along their respective co-ordinate axes, \u03d5, \u03b8, and \u03c8 representing the roll, pitch, and yaw about each respective co-ordinate axis, and \u03b8x and \u03b8y being the payload tilt angle about the x-axis and y-axis, respectively. We take the mass of the multirotor to be M and the payload it is carrying to have a mass m", + " Their perfo mance in different scenarios and with imposition of external disturbances will be presented. An analysis of th results obtained from these simulations will be analyzed in Section 4. Section 5 provide some concl sions. 2. Methodology In this section, we define the dynamics of a multirotor and its suspended payload, which are then cascaded together to for a single system. This is the system upon which the proposed controllers will be applied and subsequently compared. The characteristics of the multirotor slung load system are as shown in Figure 1. Let q = x y z \u03b8 \u03b8 and q = [\u03c6 \u03b8 \u03c8] denote the translational and rotational state vectors of the system, such that q = [q q ] represents the overall system state vector, with x, y, and z denoting the multirotor p sition along their respective co-ordinate axes, \u03c6, \u03b8, and \u03c8 representing the roll, pitch, and yaw about each respective co-ordinate axis, and \u03b8 and \u03b8 being the payload tilt angle about the x-axis and y-axis, respectively. We take the mass of the multirotor to be M and the payload it is carrying to have a mass m" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000044__2015jamdsm0037__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000044__2015jamdsm0037__pdf-Figure4-1.png", + "caption": "Fig 4. Camber, caster, kingpin, and toe angle measurement", + "texts": [ + " (5), (6), (16), and (17) as: \u2206\ud835\udc42\ud835\udc3d\u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d7 = (\ud835\udc59 l\ud835\udc52l\u20d1\u20d1 \u20d7 + \ud835\udc59h\ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 + \ud835\udc59hubt \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7 + \ud835\udc45w\ud835\udc52tr\u20d1\u20d1 \u20d1\u20d1 \u20d7) \u2212 (\ud835\udc59 l\ud835\udc52l0 \u20d1\u20d1\u20d1\u20d1\u20d1\u20d7 + \ud835\udc59h\ud835\udc52k0 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d7 + \ud835\udc59hubt0 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d7 + \ud835\udc45w\ud835\udc52tr0 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1\u20d1\u20d7 ) (18) Z-component of the vector given in Eq. (18), OJz is the wheel travel of the suspension. From X-component of this vector the track variation can be determined as 2OJx. Here, OJx is multiplied by two, since the track variat ion is calculated for two wheels. Finally, camber, caster, kingpin, and toe angles are measured as shown in Fig. 4. Camber angle of the suspension system regarding the toe angle variation can be calculated from the angle between the hub direction and Z -axis as: \ud835\udf11 = cos\u22121(\ud835\udc52hub\u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d1\u20d1 \u20d7 \u2219 ?\u20d1\u20d7?) \u2212\ud835\udf0b 2\u2044 (19) Caster angle of the suspension system regarding the toe angle variation can be calcu lated from the angle between the unit vector perpendicular to the projection of the hub direction on XY plane and the unit vector of the knuckle as: \ud835\udf0f = cos\u22121(\ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 \u2219 \ud835\udc52caster\u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d7) \u2212\ud835\udf0b 2\u2044 (20) where \ud835\udc52caster\u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1\u20d1\u20d1 \u20d7 = [\u2213 \ud835\udc52huby \ud835\udc52hubx \u221a 1 ( \ud835\udc52huby \ud835\udc52hubx ) 2 + 1 \u00b1 \u221a 1 ( \ud835\udc52huby \ud835\udc52hubx ) 2 + 1 0] \ud835\udc47 Kingpin angle of the suspension system regarding the toe angle variation can be calculated from the angle between the projection of the hub direction on XY plane and the unit vector of the knuckle as: \ud835\udf0e = cos\u22121(\ud835\udc52k\u20d1\u20d1 \u20d1\u20d7 \u2219 \ud835\udc52hubp\u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7)\u2212\ud835\udf0b 2\u2044 (21) where \ud835\udc52hubp\u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d7 = [\ud835\udc52hubpx \ud835\udc52hubpy 0] \ud835\udc47 /\u221a\ud835\udc52hubpx 2 + \ud835\udc52hubpy 2 Toe angle of the suspension system can be determined from the angle between the project ion of the hub direct ion on XY plane and Y-axis as: 7 \u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000668__imane2017_06024.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000668__imane2017_06024.pdf-Figure5-1.png", + "caption": "Fig. 5. Design Intent.", + "texts": [ + " In case of importing geometry from other 3D design software, the synchronous technology allows the user to add additional information to imported geometry. Design Intent and Advanced Design Intent panel are two tools that together reveal the true power of the synchronous technology. Design Intent dialog box displays the current rules which were associated with a selected geometry. The second level of help is Advanced Design panel. Here, users have full access to see what rules the system has applied for the selected geometry and all the rules on which can intervene to select them. Rules in the lower region of Figure 5 may be enabled or disabled. There are several different options available to users, including control deactivation or stopping all controls. Analysing the references mentioned in the end and those presented in this paper we can draw the following conclusions about the two methods studied, namely the ordered (with history) type and the synchronous type: The classic method (with history) has been applied for more than 25 years in the field of aided design and therefore has created stronger dependent relations among its users, who because of habit, prefer to apply a very well-known method rather than to test and then apply a superior method as the synchronous one" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000882_article-file_1157957-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000882_article-file_1157957-Figure6-1.png", + "caption": "Fig. 6. Boundary conditions for the analysis with loading by force couple", + "texts": [ + " The result of 2D meshing, shell elements has been checked and modified to achieve a good quality of mesh. After this phase, 3D mesh structure was created with first-order tetra 3D elements. After 3D meshing, totally 1,068,883 elements and 231,534 nodes were generated. As mentioned in the introduction, two different analysis were carried out in terms of load condition, respectively force couple and pure moment. Boundary conditions for the analysis with loading by force couple: 1D rigid element has been created inside of each yoke holes as shown in Fig. 6. The force of 49,758 N corresponding to the moment acting on the yoke, has been defined on the nodes of the rigid structures on each yoke\u2019s hole and in the opposite direction as shown in Fig. 6. The definition of constraint has been applied to the nodes of rigid structures in the direction of force and rotation axis, which gives freedom in rotation and translation. For the lower side of the weld yoke where the welding operation is performed, as shown in Fig. 6, the constraint has been defined in a way that does not allow rotation and translation in all axes by using rigid elements. Elasticity modulus of 210 GPa and Poisson\u2019s ratio of 0.3 have been used as input data for the material of weld yoke. Boundary conditions for the analysis with loading by mo- ment: Rigid elements have been created on each yoke branches. And so the moment acting on the weld yoke is distributed equally as shown in Fig. 7. The torque of 4,600 is defined in the middle node of the rigid structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure11-1.png", + "caption": "Fig. 11. The grid of tetrahedral finite elements. Average Element Size (as a fraction of bounding box length): a) 0.1 \u2013 76857 elements, 153109 nodes; b) 0.05 \u2013 93147 elements, 193671 nodes; c) 0.03 \u2013 227881 elements, 470621 nodes; d) 0.02 \u2013 457849 elements, 887356 nodes; e) 0.01 \u2013 2917447 elements, 4841588 nodes, f) 0.005 \u2013 7402836 elements, 11653415 nodes", + "texts": [ + " The maximal drive torque T was symmetrical, half its value, applied to the annular part of the plane of each hub containing the holes for pins/bolts connecting the twin wheels (Fig. 10). Half of the maximum vertical load G on the rear axle of the tipper by one twin wheel of this axle was applied to the same annular fragments of the plane (Fig. 10). The maximum vertical load G reached the value equal to a weight resulting from the permissible rear axle mass m mra\u2212perm, namely 16 0000 N. The grid of the curvilinear 10-node tetrahedral finite elements was shown in Fig. 11. Five options of average element size were utilized to conduct convergence evaluation in terms of the effect of the average element size on the maximum values of calculated von Mises stresses. It was assumed that solution convergence can be obtained when the decrease of average element size results in the stabilizing of the maximum values of von Mises stress calculated for the same geometrical and material parameters, loads, and boundary conditions in the analyzed model. The parts included in the modelled assembly of rims had connected each other by contact elements with the option of 3D planar curvilinear 6-node triangles and the option of their bond behavior" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.9-1.png", + "caption": "Figure 4.9: Comparator offset tolerance in 1.5-bit stage.", + "texts": [ + " 50 ATTENTION: The Singapore Copyright Act applies to the use of this document. Nanyang Technological University Library One advantage of 1.5-bit stage is that it can tolerate large comparator offset errors because of its low stage resolution and reduced interstage amplifier gain. To explain how digital error correction works, consider a 1.5-bit stage followed by a full 2-bit stage to form a 3-bit pipelined ADC. The transfer function of the first stage and the outputs of both stages are shown in Figure 4.9. When an input signal slightly larger than - ~ef /4 is applied to the first stage, if the comparators are ideal, the digital output of the first stage should be 01. From the transfer curve of the 1.5-bit stage, the analog output of the first stage should be within - ~ef /2 to o. The analog output of the first stage is the input of the second stage, and the second stage is a fu1l2-bit ADC. Thus the digital output of the second stage should be 01. Then the total 51 ATTENTION: The Singapore Copyright Act applies to the use of this document. Nanyang Technological University Library output is obtained from: Stagel 0 1 Stage2 + 0 1 ()utput 0 1 1 If the comparator is not ideal and has a threshold voltage larger than both - ~ef /4 and the input signal (as shown in Figure 4.9), then the digital output of the first stage will be 00 and the analog output of the first stage becomes within the range ~ef/2 to ~ef \u2022 Therefore the digital output of the second stage becomes 11. In this case the total output is: Stagel 0 0 Stage2 + 1 1 Output 0 1 1 which is the same as in the ideal condition. With digital error correction, the comparator offset errors can be removed as long as the residue stays in the input range of the following stage. In the I.5-bit stage architecture, an offset error as " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001782_f_version_1663924178-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001782_f_version_1663924178-Figure6-1.png", + "caption": "Figure 6. Geometric parameters of the electromagnetic driver stator core.", + "texts": [ + " In the meantime, the remaining geometric parameters in the stator core are obtainable from the function of three geometric parameters in the slot area. \u03c4slot = 2\u03c0Rsi Nslot , (8) \u03c4c = 2\u03c0 ( Rsi + 1 2 ds ) 1 P , (9) wsb = \u03c4slot \u2212 wt, (10) ds = Rso \u2212 Rsi \u2212 1.5wbi, (11) wst = 2\u03c0(Rsi + ds) Nslot \u2212 wt, (12) where \u03c4slot is the slot pitch, Nslot is the number of slots, \u03c4c is the coil pitch, wt is the tooth width, Rso is the stator outer radius, and wbi is the back iron length. These geometric parameters are presented in Figure 6. In this section, both mechanical stiffness and torques are analyzed and simulated while the driving torque is tested with the torque measurement system. Referring to the characteristics given in Table 1, the implantable lengthening nail is designed according to the parameters listed in Table 3. The implantable lengthening nail starts to distract along with the distal bone after clinicians perform an osteotomy. In our case, the maximal allowable distraction length showed an 80 mm gap between the proximal and distal bone at the end of the distraction period and before the consolidation phase (shown in Figure 7)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002450_9668973_09729868.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002450_9668973_09729868.pdf-Figure2-1.png", + "caption": "FIGURE 2. Velocity diagram of an arbitrary point on the track.", + "texts": [ + " Moreover, \u03b1, r VOLUME 10, 2022 72007 and B denote the vehicle steering angle, radius of the track sprocket, and the track gauge of the tracked vehicle, respectively. t is the running time of tracked vehicle under the vehicle steering angle \u03b1. Under the slip and skid conditions of tracks, the actual steering radius RS and the actual steering angular velocity \u03c9S of the vehicle can be expressed in the form below: Given the slippage factor of tracked vehicles during steering, the trajectory of an arbitrary point on the track during steering can be analyzed. Fig. 2 shows a ground-based static coordinate system XOY and a dynamic coordinate system x1o1y1 rotating with the track chassis. The subscript P = 1 and P = 2 represent the low-speed and high-speed side track, respectively. Considering the correlation between the unit vector in the moving coordinate system and the unit vector in the static coordinate system, the velocity at an arbitrary point on the track in the static coordinate system can be obtained indirectly. Subsequently, integrating the velocity with respect to time t results in the trajectory equation on the track. Fig. 2(a) shows that at the initial state t= 0, the static coordinate system XOY overlaps with the dynamic coordinate system x1o1y1. In this case, the coordinate of a point M on the track of the P side in themoving coordinate system x1o1y1 can be expressed as (xp0, yp0). As the test progresses, point M constantly moves relative to the ground. When the test time reaches 0< t, the steering angle of the tracked vehicle reaches \u03d5, and the coordinate of the point M in the coordinate system x1o1y1 can be expressed as (xp, yp), where components are as follows: xp = xp0 yp = yp0 \u2212 vpt \u03d5 = \u03c9st (6) Fig. 2(b) indicates that the implicated motion velocity of the point, which overlaps with the point M on the body can be calculated from the following expression: EV ep = \u2212yp\u03c9sEi1 + xp\u03c9sEj1 (7) The relative movement speed of the track relative to the vehicle is: EVrp = \u2212VpEj1 (8) where i1 and j1 are two unit vectors in the moving coordinate system x1o1y1. Velocity of the point M relative to the ground is: EVap = EVep + EVrp (9) Substituting Eqs. (6), (7), and (8) into Eq. (9) yields: EVap = ( Vpt \u2212 yp0 ) \u03c9Ei1 + ( xp0\u03c9 \u2212 Vp ) Ej1 (10) On the other hand, the unit vectors i and j in the static coordinate system XOY can be expressed as:{ Ei1 = cos\u03d5Ei+ sin\u03d5Ej Ej1 = cos\u03d5Ej\u2212 sin\u03d5Ei (11) Substituting Eqs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003562_5_agriceng-2019-0036-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003562_5_agriceng-2019-0036-Figure5-1.png", + "caption": "Figure 5. Simplified view of the car body concept in version no. 4", + "texts": [ + " Air inlets were presented in the cover in the side walls to improve thermal exchange of an engine with the surrounding. Air inlets are designed in the final version and they are available in each concept, with the same functions. Due to the methods of lamination of the car body and 3D print, with maintenance of the previously mentioned principles of division of the car body surface, they are effective methods. Concept 4 In concept 4, it was decided to extend the front end of the car body to reduce aerodynamic resistance and improvement of the air flow around the vehicle (Fig. 5) at the expense of the lower manoeuvrability. Driver\u2019s legs, as in concept 1, are hidden under the surface of the car body. The car body presented in concept 4 can be made with all the above-mentioned methods. The above concepts were also analysed on account of distribution of pressure in the vehicle symmetry plane and air trajectory around the car body model using for this purpose SolidWorks Flow Simulation software. The following boundary conditions were assumed: ambient pressure 101325Pa, ambient temperature 20\u00baC, maximum speed 50 km\u2219h-1 and global calculation grid" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001821_f_version_1591065925-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001821_f_version_1591065925-Figure2-1.png", + "caption": "Figure 2. Position of an exemplary track coordinate system and the contact plane using the example of the inner race: (left) spatial presentation; and (right) top view.", + "texts": [ + " Starting from the body-fixed coordinate systems, several coordinate systems are introduced for each track and for each cage window. While the alignment of the coordinate systems in the cage window corresponds to the cage fixed coordinate system, the track coordinate systems tre follow the track orientation with the two track angles \u03b1incl and \u03b2incl . The transformation into the track coordinate system is performed sequentially using the matrix QtrI = 1 0 0 0 cos(\u03b1incl) \u2212sin(\u03b1incl) 0 sin(\u03b1incl) cos(\u03b1incl) \u00b7 cos(\u03b2incl) 0 sin(\u03b2incl) 0 1 0 \u2212sin(\u03b2incl) 0 cos(\u03b2incl) . (8) In Figure 2, the position of the described track coordinate systems is illustrated using the inner race as an example. Based on the defined coordinate systems, various coordinate transformations can be carried out to enable analytical contact determination for the entire joint. This applies to the ball track as well as to the ball cage contact, which is explained in detail in the following. Up to six potential contact points are possible per ball, two per track and two more in the cage window. In the entire joint, therefore, a large number of potential contact points must be evaluated for each time step of the numerical integration, which can lead to high computing times under arbitrary circumstances", + " The analytical contact determination is derived from the joint system plane for both ball track contact and ball cage contact for the undeflected state of the joint. Based on the considered track angles of each track, the balls move out of the joint system plane as a result of the deflection or axial displacement of the inner race. Hence, both the PCD and the distance between the ball centres along the PCD change. This leads to additional transformation steps. For ball track contact, the current ball position is evaluated with respect to the track coordinate system tre, so that a corresponding contact plane Pe (red, Figure 2) can be defined orthogonal to the track axis as a function of the ball position. After the transformation of all necessary coordinates into the contact plane, the two-dimensional contact determination is performed by calculating the distance between the centres of two circles in order to identify the maximum plane penetration d between PC1 and PC2 of the contact bodies along the normal vector Pe1 (see Figure 3a). Subsequently, the identified contact points PC1 on the track and PC2 on the ball surface are transformed into the inertial system and the maximum spatial penetration \u03b4 is determined for further force calculation PC1 = PMtr + Pe1 \u00b7 Rtr , (9) PC2 = PMball + Pe1 \u00b7 Rball , (10) Pe1 = PMball \u2212 PMtr ||PMball \u2212 PMtr|| , (11) d = IC2 \u2212 IC1 , (12) \u03b4 = ||d|| ", + " A detailed description of the ball kinematics with the aid of numerical models offers a suitable potential for performance optimisation and thus for CO2 reduction through the joint by improving material utilisation and efficiency of the overall system. For this purpose, the kinematic curves of the ball were evaluated with respect to the body-fixed track coordinate system tre, which rotates with the inner race. Due to the ideal joint geometry in the simulation, the periodic kinematic curves of all eight balls are the same for one revolution of the inner race. They only have a phase shift. For this reason, only one ball is considered in the following. The orientation of the ball at the initial point in time is illustrated in Figure 2. In Figure 13, the curves of the translational displacements of the ball (see Figure 13a), the translational velocities (see Figure 13b), the rotational velocities (see Figure 13c) and the rotational angles of the ball (see Figure 13d) are shown, which result during the rotation at a constant speed of 300 rpm and a load torque of 2000 Nm at a deflection angle of 2\u25e6. As a characteristic movement of the ball within the track, the oscillation along the track axis can easily be identified (green curves)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002140_5-lajss-15-5-e71.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002140_5-lajss-15-5-e71.pdf-Figure3-1.png", + "caption": "Figure 3: Coordinate frames used in the discussed problem.", + "texts": [ + " Keep in mind that improper set of buffer coefficients leads to rebounding motion between two vehicles and then, unsuccessful capture mission. To formulate a wide range of mechanical problem from very simple to very complex, multibody dynamics tool can be used where a collection of bodies may undergo relative motion with respect to each other. Accurate configuration of such systems is better described by arranging coordinate frames in the suitable position of each component. To provide this, all coordinates are assigned at the centroid of k-th body, as depicted in Figure 3. It is to be noted that subscripts S, C, P and T are, respectively, associated with coordinates for servicing satellite, cylinder, probe and target. The position vectors of Sr , Cr , Pr and Tr can be easily written in the global coordinate frame, as: \u00a0 , , ,k k ku v for k S C P T= + =r i j\u00a0\u00a0 (5) As mentioned earlier, the connection between cylinder and main body of chaser is provided by revolute joint and al- so, the translational motion of probe with respect to cylinder is performed by prismatic joint" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002184_load.php_id_22112102-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002184_load.php_id_22112102-Figure11-1.png", + "caption": "Figure 11. VFPMVM test system with (a) prototype stator lamination, (b) prototype stator with armature winding, (c) prototype test platform and (d) control system.", + "texts": [ + " 9 that the magnetic density distribution is greatly affected after the excitation current is applied to the machine. After the excitation current is applied, the distribution of VFPMVM air gap magnetic density is shown in Fig. 10. Compared with Fig. 5, the air gap magnetic density of the machine is significantly reduced compared with that without the excitation winding, which proves the effectiveness of magnetic field weakening control. With the purpose of verifying the correctness of simulations results with the proposed VFMFMM, a 1 kW prototype and its testing platform were established, as shown in Fig. 11. Figure 12 shows the test waveforms of back-EMF when the excitation currents are 0, 0.5A, \u22120.5A, and machine operation speeds are 100 rpm, 150 rpm, and 200 rpm, respectively. It can be seen from Fig. 11 that the back-EMF values change obviously when the excitation current values are changed. When the excitation current values are 0.5A and \u22120.5A, the average field weakening and increasing amplitudes are 52.9% and 33.7%, respectively, which can meet the needs of wide speed range regulation. It is worth noting that, compared with the traditional hybrid excitation PMSM, the proposed VFMFMM in this paper has more obvious effect in the field weakening, and the magnetic field saturation of the machine is easier to be obtained caused by the increase of magnetic field" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001217_7419931_07372383.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001217_7419931_07372383.pdf-Figure5-1.png", + "caption": "FIGURE 5. Current and magnetization directions settings. (a) Magnetization direction of the concentrator and the magnet disk. (b) Mechanism of the magnetic field concentrator.", + "texts": [ + " Therefore the current range of the electromagnet is from \u22121A to 1A. C. MAGNETIC FIELD CONCENTRATION Inspired by Halbach array [24] and the magnetic arrays with increased magnetic flux [25] introduced in Section II-C where the magnetic field is increased on one pole by special arrangement, in our design, the coil is encased in a cylinder ring permanent magnet acting as a magnetic field concentrator to enhance the magnetic flux on the upward side. The directions of magnetization and corresponding current flow imposed are depicted in Fig. 5. When imposing counter-clockwise current into the coil in the vertical view, the magnetic field lines generated are pointing upward according to the right-hand rule, thus the coil can be viewed as a magnet with north pole on the top. 302 VOLUME 4, 2016 The concentrator, which is a permanent magnet cylinder ring depicted in Fig. 5a is radially magnetized with north pole pointing to the axis. The mechanism of the concentrator is that it contributes the current density in the form ofmagnetization currents that flow both within the volume and on the surface of the concentrator. The detailed statement and proof is shown as follows. Theorem 1: Given a cylinder ring uniformly radially magnetized with the north pole pointing to its central axis, the volume magnetization can be replaced by surface current on the top and bottom when calculating the magnetic field", + " 2, we can obtain the volume magnetization current density as JVM = \u2207 \u00d7 (\u2212McEr) = E0(A/m2) (5) and the surface magnetization current density for the top, bottom, inner side and outer side surfaces as J topSM = (\u2212McEr)\u00d7 Ez = Mc E\u03b8 (A/m) (6) JbottomSM = (\u2212McEr)\u00d7 (\u2212Ez) = \u2212Mc E\u03b8 (A/m) (7) J innerSM = (\u2212McEr)\u00d7 (\u2212Er) = E0(A/m) (8) JouterSM = (\u2212McEr)\u00d7 Er = E0(A/m) (9) where J topSM, JbottomSM , J innerSM and JouterSM are the magnetization surface current on the top, bottom, inner and outer side of the concentrator respectively. Remark 1: From Eq. 6 we can see that when looking down from above, the magnetic concentrator contributes to the top surface current with a counter-clockwise magnetization current and to the bottom surface current with a clockwise magnetization current according to Eq. 7. When visualizing the magnetization current in Fig. 5b, we can see that the directions of the magnetization current and the stimulating current in the coil are the same on the top surface of the concentrator while opposite on the bottom surface. Thus, the magnetic field is augmented on the top and reduced on the bottom. In reality, the magnetization value of a normal bar magnet can be 105A/m while for iron it can be as large as 106A/m. To ensure the electromagnet model and the magnet disks having magnetic field strength of approximately the same orders of magnitude, the magnetization of the concentrator is set to be 5\u00d7 105A/mand that of the diskmagnets is 106A/m" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000804_le_1878_context_etdr-Figure2.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000804_le_1878_context_etdr-Figure2.3-1.png", + "caption": "Figure 2.3 Tensile Bar Blank Casting", + "texts": [ + " An additional heat was added to assess the highest alloy content with less silicon. Set B was inoculated with Topseed as magnesium cover in the ladle and Spherix outside the pocket. These were the only inoculating steps, so the spectroscopy data is representative of all the castings. The mass balances for Alloy Set B are shown in Appendix A. 7 Alloy Set A was cast into 5 vertically parted tensile bar molds. Each mold contained four blanks that could be easily turned into tensile bars. These blanks are 0.75 inches (19 mm) in diameter and 8 inches (200 mm) in height (Figure 2.3). These molds were made from an air set chemically bonded sand (Figure 2.4). Each mold half required 22 lbs. of sand, resulting in a total mold weight of 44 pounds of sand. The weight of these casting systems was 11 lbs. 8 9 Two step bar molds were also cast for each heat. The bar has steps that were 0.25, 0.5, 0.75, and 2 inches high. This mold was made from green sand and was horizontally parted (Figure 2.5). This casting system weighed 12 lbs. Additional metal was poured into pig mold which can hold up to 120 lb of iron but typically were filled to between 60- 80 lbs for ease of recharging" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002722_download_58477_60372-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002722_download_58477_60372-Figure11-1.png", + "caption": "Figure 11: Cylinder block convection output", + "texts": [], + "surrounding_texts": [ + "The designed cylinder block had an engine power of 5.11kw which drove piston through a bore and stroke of 46.10mm and 51.20mm respectively. The determined clearance volume of 9.46cm3 was enclosed in a cylinder wall thickness and block length of 3.04mm and 58.88mm respectively. The designed values were found to be in consonance with recommended values obtained in standard engineering text The parametric optimization yielded an adequate mathematical model with a statistical Coefficient of determination (R2) and Adjusted coefficient of determination (Adj R2) of 98.62% and 97.79% respectively. The Taguchi design and the Genetic algorithm optimization results were found to have optimal values of 19.9995mpa, 1.0001N and 8.0006 for injection pressure, load and compression ratio respectively. The cylinder block was further subjected to temperature and total heat flux output analysis in the Finite element ANSYS software to ascertain the effect of the inputted parameters on the internal combustion engine component. The temperature output result showed that the highest temperature of 100oC occurred around the cylinderical bore axis while the lowest temperature of 51.97oC was found on the cooling fins of the component. Vol.12, No.1, 2022" + ] + }, + { + "image_filename": "designv8_17_0002718_3452-020-00107-0.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002718_3452-020-00107-0.pdf-Figure9-1.png", + "caption": "Fig. 9 Distribution of the critical strain (a) and recrystallized volume fraction (b) in the 3rd pass for the pearlitic steel", + "texts": [ + " The difference in temperature and strains distribution between pearlitic and bainitic steels is small. Contrary, the microstructure evolution is noticeably different, due to high-temperature dynamic recrystallization dominated in the break down passes for both steels. Figures\u00a09 and 10 shows distributions of the critical strain and dynamically recrystallized volume fraction in the 3rd pass for pearlitic and bainitic steels, respectively. Results show that DRX was completed for the pearlitic steel (Fig.\u00a09b) while in bainitic steel only a small volume of metal recrystallized according to dynamic mechanism (Fig.\u00a010b). In the last pass, no 17, partial dynamic recrystallization for the pearlitic steel was observed, but the dominant mechanism of recrystallization was static. For bainitic steel, the value of the critical strain was greater than the value of the effective strain and dynamic recrystallization did not start. Static recrystallization only was observed (Fig.\u00a011). Modelling of the mechanisms of recrystallization (dynamic and static) showed that for pearlitic steel the recrystallization rate is larger than for bainitic steel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001549_tation-pdf-url_35276-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001549_tation-pdf-url_35276-Figure3-1.png", + "caption": "Fig. 3. Geometry of the shaper cutter", + "texts": [ + " The position vector of regions eg and fh are represented in the coordinate system nS as follows (Yang, 2005): )sin( cos 1 1 nynec ne eg n eg neg n mclb l y x R (5) and )sin( cos 2 2 nynfc nf fh n fh nfh n mclb l y x R (6) where el and fl are the design parameters of the rack cutter surface which determine the location of points on the working surface. el and fl are limited by 11 cos/cos/ naena hlh and 22 cos/cos/ nafna hlh for the left- and right-side of the rack cutter respectively. The surface unit normals of the regions ac to fh of the rack cutter surfaces are represented by (Litvin, 1994), )~( )~( faj fhaci l l n j i n n j i n i n k R k R n (7) where nk is the unit vector of the nZ -axis. Pinion-type shaper cutters are designed consists of six generating regions as depicted in Fig.3. Regions 1 and 6 of the involute-shaped curves generate the working regions of involute spur gears, regions 2 and 5 of the circular arcs with centers at E and G generate the fillet surfaces, and regions 3 and 4 of the shaper cutter surfaces generate the bottom lands (Chang & Tsay, 1998). Based on (Figliolini & Angeles, 2003), nongenerating surfaces of the cutter are also shown for visual purposes only. In Fig. 3, coordinates systems ),( sss YXS and ),( ccc YXS represent the reference and the shaper cutter coordinate systems, respectively. According to the relationship between coordinate systems sS and cS , the position vector of region i can be transformed from www.intechopen.com Mechanical Engineering 508 coordinate systems sS to cS by applying the following homogeneous coordinate transformation (Litvin, 1994): i s i s i c i ci c y x y x R sincos cossin (8) where tan2/ sN , sN is the number of shaper cutter teeth and is the pressure angle of the cutter at the pitch point, as depicted in Fig. 1. Supercript i represents regions 1, 2, 3, 4, 5 and 6. For simplicity the mathematical models of the left side generating surfaces of the cutter are given. As shown in Fig. 3., the regions 1 and 6 of the shaper cutter are used are used to generate the different sides of the working tooth surfaces of involute spur gears. is the design parameter of the cutter surface which determines the location of points on the involute region and its effective range is m 0 . The position vector of region 1 is represented in the coordinate system sS as follows (Chang & Tsay, 1998): sincos cossin 1 1 1 bb bb s s s rr rr y x R (9) www.intechopen.com Computer Simulation of Involute Tooth Generation 509 where br is the radius of base circle", + " (8) yields the position vector of region 1 represented in coordinate system cS as follows (Chang & Tsay, 1998): )cos()sin( )sin()cos(1 bb bb c rr rr R (10) Regions 2 and 5 of the shaper cutter generate different sides of the fillet surfaces of spur gears. As shown in Fig. 1, parameter of the cutter surface determines the location of points on the fillet region and its effective range is ))/((tan2/0 1 1 bm r . The tangents of the involute curve and circular arc at point A should be same and continuous. Therefore, the center E of the circular arc is located on the line PA , as depicted in Fig. 3. The position vector of region 2 is represented in the coordinate system sS as follows (Chang & Tsay, 1998): )sin(sinsincos )cos(coscossin 11 112 mmmmbmb mmmmbmb s rr rr R (11) where 1 is the radius tip fillet surface of the generating cutter, and m is the maximum extension angle of the involute curve at point A. Similarly, the position vector of region 2 can be represented in coordinate system cS as follows: )cos()cos()cos()sin( )sin()sin()sin()cos( 11 112 mmmmbmb mmmmbmb c rr rr R (12) As depicted in Fig. 3, the regions 3 and 4 are used to generate the bottomland of the machined gear. represents a design parameter of shaper cutter and its effective range is sm N2/tan2/ . Based on the cutter geometry, equation of region 3, represented in coordinate system sS , can be expressed as (Chang & Tsay, 1998) cos sin 3 3 3 a a s s s r r y x R (13) where 1 2 1 2 )( mbba rrr is the radius of the tip circle of the cutter and ))/((tan2/ 1 1 bm r . Similarly, the position vector of region 3 can be represented in coordinate system cS as follows (Chang & Tsay, 1998): )cos( )sin(3 a a c c c r r y x R (14) Based on the differential geometry, the unit normal vectors of the above mentioned shaper cutter surface represented in coordinate system cS are (Litvin, 1994) www", + "01 and right side radius of rounding As illustrated in Table 2, the shaper cutter of type-1a has different clearances at its different sides. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 35.02 . Figure 12 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. www.intechopen.com As illustrated in Fig. 3. and classifed type-1b in Table 2, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The relationship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 222.02 . Generating and generated surfaces and trochoidal paths are illustrated in Fig 13", + " Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 373.01 and right side radius of rounding m 449.02 . Figure 14 displays the generating cutter of type-2a , generated surface and trochoidal paths of the tip. For visual clearity, only the corresponding halves (of secondary trochoids) that contribute to final formation of the generated tooth shape are shown. The shaper cutter with asymmetric involute teeth and with a single rounded edge can not be designed for constant clearance in case of standard tooth height. As illustrated in Fig. 3., the center of the rounding should be on the pressure line of the cutter. As a result, the geometric varieties of pinion-type tool tip is limited for indirect generation. www.intechopen.com Mechanical Engineering 522 www.intechopen.com Figure 17 displays relative positions of the pinion cutter with symmetric involute teeth and a fully-rounded tip. The trochoidal curves exhibits symmetry according to center line of gear tooth space. Generating with a sharp-edge pinion cutter is depicted in Fig.18" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003023_11n4_8426_lakrit.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003023_11n4_8426_lakrit.pdf-Figure1-1.png", + "caption": "Fig. 1. Geometry of the proposed antenna", + "texts": [ + " The measured results show that the antenna has a bandwidth ranging from 3.26 to 14.23 GHz for S11< -6 dB [1] and from 3.52 to 13.67 GHz for S11< -10dB. Also, the radiation pattern keeps approximately the same shape over the frequency bandwidth. Details of the proposed design are presented and discussed in this paper. The Ansoft High Frequency Structure Simulator (HFSS) was used in the design process. The present work is a more detailed study of our previous papers [18, 19]. II. ANTENNA GEOMETRY AND DESIGN Figure 1 illustrates the configuration of the proposed antenna, which consists of a circular patch, a partial ground plane and a T-shaped slot on the ground plane. This compact antenna, which has a radius a = 5mm, is printed in the front of an FR4 substrate having a thickness 1.58mm with relative permittivity of 4.4 and 0.02 for loss tangent. The dimensions of the partial ground plane, which is printed in the bottom side of the substrate, are chosen to be 12\u00d73.5mm2 in this study. The patch is fed by a 50\u2126 coaxial probe from the side of the antenna through a 50\u2126 microstrip line" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure6-1.png", + "caption": "Figure 6. Axial flux permanent magnet synchronous motor shape.", + "texts": [ + " Section 5 utilizes the proposed process to advance the optimal design of the DRAFPM motor for robot joints. Section 6 summarizes the conclusions of this paper. Figure 4 shows the components of the joint robot and the drive module. Currently, RFPM motor for robot joints is mainly used as shown in Figure 5. The motor size has been reduced to a smaller size, and SPMSM\u2019s performance has reached its limit. Therefore, it is necessary to study the high torque of motor for robot joints. The AFPM motor shape is shown in Figure 6. The AFPM motor is thin and proportional to the cubic diameter. Therefore, the AFPM motor can effectively generate torque [21\u201324]. The shorter the axial length of the motor for robot joints, the better. The AFPM motor is suitable for the motor for robot joints because it has a very short axial length compared to the radial direction. The AFPM motor can be designed in various topologies as shown in Figure 7 depending on the configuration of the rotor and stator, and the permanent magnet arrangement [25]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure4-27-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure4-27-1.png", + "caption": "Figure 4-27. Comparaison des diagrammes de rayonnement obtenus en simulation et par la mesure", + "texts": [ + " Diagramme de rayonnement d'une des antennes du syst\u00e8me................................. 127 Figure 4-24. Dimensions du syst\u00e8me \u00e0 quatre antennes Yagi-Uda imprim\u00e9es .......................... 128 Figure 4-25. Photographie du syst\u00e8me Yagi-Uda imprim\u00e9 avec les deux plaques assembl\u00e9es . 129 Figure 4-26. Coefficients de r\u00e9flexion et de transmission d'une des antennes du syst\u00e8me \u00e0 quatre Yagi-Uda..................................................................................................................................... 129 Figure 4-27. Comparaison des diagrammes de rayonnement obtenus en simulation et par la mesure ......................................................................................................................................... 130 Figure 4-28. Photographie du commutateur RF 4 voies r\u00e9alis\u00e9.................................................. 131 Figure 5-1. Exemple d'orientations possibles pour un t\u00e9l\u00e9phone mobile ................................... 145 Figure 5-2. Repr\u00e9sentation des rep\u00e8res cart\u00e9sien et sph\u00e9rique consid\u00e9r\u00e9s " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003760_le_download_1573_791-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003760_le_download_1573_791-Figure3-1.png", + "caption": "Fig. 3 CDFW process of AA 6061/GNPs (a) Schematics and (b) real images.", + "texts": [ + " Both welded sides were identical in dimensions. Table 1 Chemical compositions of AA 6061 by wet% GNPs in the form of graphene dispersion were supplied by Graphene Laboratories Inc. (760 Koehler Avenue - Suite 2 Ronkonkoma, NY 11779). The product is an ultra-high concen- tration dispersion of graphene with an average GNPs thickness of about 7 nm and 23 wt% total graphene content in N-Butyl acetate solvent. The rods were drilled in a way that the holes circumferential are touching the rod center (see Fig. 3 (a)). The hole has 3 mm diameter and 15 mm depth. After stirring the GNPs dispersion for 30 minutes as illustrated in the data sheet to provide complete homogeneous dispersion. The GNPs dispersion were injected into the holes. The hole was made sure to be fully filled with the GNPs dispersion. The samples were left for a few hours to let dry and then used in the CDFW. Figure 3 (a, b) show schematic and real images for the de- signed test setup with samples fixation within the rotating and fixed sides. The rotating side contains the AA 6061 with GNPs while the sample at the fixed side is AA 6061 only. During the welding process, the GNPs are moving out of the friction plane towards the periphery. The welding procedure was performed next. The AA 6061 rods that were filled with GNPs were welded using our fabricated CDFW machine. The welding parameters for all samples are tabulated in Table 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000904_cle_download_386_285-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000904_cle_download_386_285-Figure3-1.png", + "caption": "Figure 3: (a) Geometry of the proposed PIFA, (b) Dimension of top plane.", + "texts": [ + " The antenna structure consists of two F-shaped patterns nested in the top metal layer. Shorter elements are used for higher frequency bands and longer ones for lower bands. Two via holes with a diameter of 1.27 mm are used to connect the top and bottom metal layers. The Sub-Miniature version A (SMA) connector is attached to the edge of the substrate (shown in Figure 2(b)) used for measurement. The antenna structure occupies a board dimension area of 30 \u00d7 22 \u00d7 1.57 mm3. Vol. 01, No. 01, December 2022 17 Another PIFA antenna is proposed [11], as illustrated in Figure 3(a), which depicts the fabrication structure and geometry of a capacitively coupled dual-band PIFA antenna. The antenna consists of a metal top plane and a ground plane system, It is excited by a single probe feed connected to a square capacitive strip. In the upper plane, the antenna also consists of an L-shaped slotted line, and it is suspended above the ground plane and shortened to the ground plane by a short metal plane. The antenna is designed on an FR-4 dielectric substrate. The optimized antenna design parameters are Wt = 10 mm, Lt = 34.5 mm, Lh = 13.5 mm, Lv = 5 mm, h = 6 mm, Wg = 40 mm, Lg = 100 mm, th = 0.5 mm, tv = 1.2 mm, g = 0.5 mm, s = 4 mm, and t = 4 mm. This antenna is best suited for GPS 1.5 GHz and 2.4 GHz WLAN applications. While Figure 3(b) depicts the dimensions of the top plane and the slot\u2019s edge. After the previous discussion on antenna design, this section will discuss the results of antenna measurements and simulations. A compact Triple-band PILA antenna [6], is simulated using the HFSS simulator. The proposed antenna prototype was made to verify the simulation results. S11 was measured using the 9916A Agilent Network Analyzer. The simulation results and measurements show that parameter S11 is S11 \u00a1 -10dB and the gain variation in each operating band is less than 1dB" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure4-1.png", + "caption": "Figure 4. 0\u00b0 Specimen (left) +/-45\u00b0 specimen & quasi-isotropic laminate specimen (center) 90\u00b0 specimen (right)", + "texts": [ + " ASTM is an international standards organization, which develops and publishes voluntary consensus technical standards for a wide range of materials, products, systems and services. 2.1 Tensile Specimen & Double Shear Specimen Dimensions The dimensions for the 0\u00b0 tensile specimens and the 90\u00b0 tensile specimens were found in ASTM D3039 [19] Standard test method for tensile properties of fiber-resin composites. The dimensions used for the shear modulus +/- 45\u00b0 were found in ASTM D3518 [20]. Below in Figure 3, one can see all of the tensile specimen dimensions for each specific fiber orientation angle. Figure 4 shows a drawing of all four different fiber orientation tensile specimens. The +/- 45\u00b0 shear specimens and the quasi-isotropic laminate specimens had the same dimensions. Figure 5 shows the dimensions, based on ASTM D5961 [18], of the composite double shear specimens. The quasiisotropic tensile specimens were tested to see how the theoretical material properties matched. 12 13 2.2 Manufacturing Process In the Cal Poly\u2019s Aerospace Engineering Composites Lab, there are two ways to manufacture a composite" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000706_O201332479507885.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000706_O201332479507885.pdf-Figure4-1.png", + "caption": "Fig. 4\uc640 \uac19\uc774 \ud0c8\uace1\uae30 \ub36e\uac1c \uc548 \ucabd\uc5d0 \ucf69\ub300 \uc720\ub3c4\ud310\uc744 \ub450 \uc5b4\uc11c \ubc29\ud5a5\uacfc \ud0c8\uace1 \uc18d\ub3c4\ub97c \uc870\uc808\ud560 \uc218 \uc788\uac8c \uac00\uc774\ub4dc\ub97c \uc124\uacc4 \ud558\uc600\ub2e4.", + "texts": [], + "surrounding_texts": [ + "Key Words : Bean, Bean Threshing, Threshing machine, Three dimensional design, Pro-Engineer, Industry University Cooperation\n2012\ub144 \uc911\uc18c\uae30\uc5c5\uccad\uc5d0\uc11c \uc2dc\ud589\ud55c \uc0b0\ud559\uc5f0 \ucee8\uc18c\uc2dc\uc5c4 \uc0ac\uc5c5 \uc9c0\uc6d0(\uacfc\uc81c\ubc88\ud638 C00256890100381053)\uc744 \ubc1b\uc544 \uc218\ud589\ud558\uc600\uae30\uc5d0 \uac10\uc0ac\ub4dc\ub9bd \ub2c8\ub2e4. \ub610\ud55c \ucc38\uc5ec\uae30\uc5c5\uc778 \ub300\ub959\uae30\uacc4 \uad00\uacc4\uc790\ubd84\ub4e4\uaed8 \uac10\uc0ac\ub4dc\ub9bd\ub2c8\ub2e4. *Corresponding Author : BongChoon Jang(Andong National Univ.) Tel: +82-10-5132-4081 email: bjang@andong.ac.kr Received June 21, 2013 Revised August 5, 2013 Accepted September 6, 2013\n1. \uc11c\ub860\n1.1 \uae30\uc220\uac1c\ubc1c\uc758 \ud544\uc694\uc131\n\uad6d\ub0b4 \ucf69 \ud0c8\uace1\uae30 \uc81c\uc870\uc5c5\uccb4\ub85c\ub294 \uc804\uad6d\uc9c0\uc5ed\uc5d0\uc11c \ubd80\ud765\uae30\uacc4 \uacf5\uc5c5\uc0ac, \ubc1c\uc0b0\uacf5\uc5c5, \uc601\uc2e0\ub18d\uae30\uacc4, \uacbd\uc2e0\uae30\uacc4\uacf5\uc5c5\uc0ac \ub4f1 23\uac1c \uc5c5\uccb4\uac00 \uc788\uc73c\uba70 \uaddc\ubaa8\uac00 \uc791\uace0 \ub300\ubd80\ubd84 \uc804\uae30\ubaa8\ud130\uc2dd\uc73c\ub85c \uace0\uc815 \ud615[1,2]\uc774\uba70 \ub3c5\ub9bd\uad6c\ub3d9 \ubc29\uc2dd\uc758 \uc790\uc8fc\ud615\uc740 \uad6d\ub0b4\uc5d0\uc11c \uac70\uc758 \uc0dd\n\uc0b0 \ub418\uc9c0 \uc54a\ub294\ub2e4. \ub113\uc740 \ud3c9\uc9c0\ub97c \uc18c\uc720\ud558\uace0 \uc788\ub294 \ub300\uc9c0\uc8fc\ub294 \ub300 \ub7c9\uc73c\ub85c \ucf69\uc744 \uc218\ud655 \ud6c4 \ucf69 \ud0c8\uace1\uae30 \uc0ac\uc6a9\uc774 \uc808\ub300\uc801\uc73c\ub85c \ud544\uc694 \ud558\uba70, \ub113\uc740 \ubc2d\uc744 \ub3cc\uc544\ub2e4\ub2c8\uba74\uc11c \ud0c8\uace1 \uc791\uc5c5\uc744 \ud560 \uc218 \uc788\ub294 \ub3c5\ub9bd\uad6c\ub3d9\ud615 \uc790\uc8fc\uc2dd \ucf69 \ud0c8\uace1\uae30 \uc0ac\uc6a9\uc744 \uc120\ud638\ud558\uc5ec \ub18d\uc5c5\uc778 \uc218\uc694\uc790 \ub9de\ucda4\ud615 \ucf69 \ud0c8\uace1\uae30 \uac1c\ubc1c\uc774 \uc808\ub300\uc801\uc73c\ub85c \ud544\uc694\ud558\uc600\ub2e4.\n\uc678\uad6d\uc0b0 \uacbd\uc7c1 \uc81c\ud488\uc758 \uacbd\uc6b0\uc5d0\ub294 \uc131\ub2a5\uc774 \uc6b0\uc218\ud558\uace0, \ucf69 \ud0c8 \uace1 \uc791\uc5c5\uc2dc \uba3c\uc9c0\uac00 \ub9ce\uc774 \uc77c\uc5b4\ub098\uc9c0 \uc54a\uc544 \uc791\uc5c5\uc790\uc5d0\uac8c \ud574\ub86d", + "\uc9c0 \uc54a\uc73c\ub098, \uad6d\uc0b0 \uc81c\ud488\ub4e4\uc740 \uba3c\uc9c0\ub97c \ub9ce\uc774 \uc77c\uc73c\ucf1c \ub18d\uc5c5\uc778\ub4e4 \uc5d0\uac8c \uac74\uac15\uc0c1 \ud574\ub97c \ub07c\uce60 \uc218 \uc788\uc5b4 \uc0c8\ub85c\uc6b4 \ud615\ud0dc\uc758 \ud0c8\uace1\uae30 \uac1c \ubc1c\uc774 \ud544\uc694\ud558\uc600\ub2e4. \ub610\ud55c, \uad6d\uc0b0 \uc81c\ud488\uc758 \uc791\uc5c5 \uc131\ub2a5\uc774\ub098 \ud6a8\uc728 \uc744 \uadf9\ub300\ud654\ud558\uc5ec \uacbd\uc7c1\ub825\uc744 \uc81c\uace0\ud560 \uc81c\ud488 \uac1c\ubc1c\uc774 \ud544\uc694\ud558\uba70 \uc678\uad6d\uc0b0 \uc81c\ud488\uc758 \uc218\uc785 \ub300\uccb4 \ud6a8\uacfc\ub97c \uac00\uc838\uc62c \uacbd\uc7c1\ub825\uc788\ub294 \ube44 \ud0c8\ubd80\ucc29\uc2dd \ucf69 \ud0c8\uace1\uae30 \uac1c\ubc1c\uc774 \uc2dc\uae09\ud558\uc5ec \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 3\ucc28 \uc6d0 \uc124\uacc4 \ud6c4 \uc2dc\uc81c\ud488 \uc81c\uc791\uc744 \ubaa9\ud45c\ub85c \ud558\uc600\ub2e4.\n2. \ubcf8\ub860\n2.1 \ud0c8\uace1\uae30\uc758 \uc6d0\ub9ac \ubc0f \uac1c\uc120\uc810\n\ucf69 \ud0c8\uace1\uc758 \ud575\uc2ec\uae30\uc220\uc740 \ud587\ube5b\uc5d0 \ub9d0\ub9b0 \ucf69\uc791\ubb3c\uc744 \ubc2d\uc5d0\uc11c \ubaa8\uc544\uc11c \ud22c\uc785\uad6c\uc5d0 \ub123\uc73c\uba74 \ud0c8\uace1\ucca0\ub9dd(\ub864\ub7ec\ud615\ud0dc)\uc5d0 \ubd80\ucc29\ub41c \ucca0 \uad6c\uc870\ubb3c(\ud30c\uc1c4\uae30\uc758 \uce7c\ub0a0 \uc6d0\ub9ac\uc640 \uac19\uc74c)\uc774 \ucf69 \uc791\ubb3c\uc744 \ud30c\uc1c4 \ud558\uba74\uc11c \ucf69 \uaecd\uc9c8\uc774 \ubc97\uaca8\uc9c0\uace0 \ucf69\ub4e4\uc740 \uc120\ubcc4\ub9dd \uc544\ub798\ub85c \ub5a8\uc5b4 \uc9c4\ub2e4. \uc774 \ub54c \uc120\ubcc4\ub9dd\uc5d0 \uc9c4\ub3d9\uc744 \uac00\ud558\uba74 \ub730\ucc44\uc640 \uac19\uc740 \uc5ed\ud560\uc744 \uc218\ud589\ud558\uba70 \ucf69 \uaecd\uc9c8\uacfc \ucf69\ub300\ub97c \uc120\ubcc4\ud558\uae30 \uc704\ud574 \uc1a1\ud48d\ud32c\uc744 \uc124 \uce58\ud558\uc5ec \ubd80\uc0b0\ubb3c\uc744 \ud1a0\ucd9c\uad6c\ub85c \ubcf4\ub0b4\ub294 \uc5ed\ud560\uc744 \ud55c\ub2e4. \uadf8\ub7ec\ub098 \uad6d\ub0b4\uc0b0 \uc81c\ud488\ub4e4 \ub300\ubd80\ubd84\uc774 \ubd80\uc0b0\ubb3c\ub4e4\uc744 \ubaa8\ub450 \ud1a0\ucd9c\ud558\uc9c0 \ubabb\ud574 \ucf69\uacfc \ud568\uaed8 \uc11e\uc5ec\uc11c \ud638\ud37c\uc5d0 \uc801\uc7ac\ub418\ub294 \ubb38\uc81c\uc810\ub4e4\uc774 \uc788\uc5c8\ub2e4.\n\uc77c\ubcf8 \uc81c\uc870\uc5c5\uccb4 \uc580\ub9c8\uc0ac[3]\uc758 \ud0c8\uace1\uae30\ub294 \ub3c5\ub9bd\uad6c\ub3d9\ubc29\uc2dd\uc73c \ub85c \uace0\uc815\uc2dd\ubcf4\ub2e4\ub294 \uc791\uc5c5 \uc131\ub2a5\uc774\ub098 \ud6a8\uc728 \uba74\uc5d0\uc11c \uc6d4\ub4f1\ud558\uace0, \uc774\ub3d9\ud558\uba74\uc11c \ud0c8\uace1\uc744 \ud558\ubbc0\ub85c \uc791\uc5c5\uc774 \ud3b8\ub9ac\ud558\uace0, \uad6d\ub0b4 \uc81c\ud488\uc5d0 \ube44\ud574 \uba3c\uc9c0\uac00 \ub9ce\uc774 \uc77c\uc5b4\ub098\uc9c0 \uc54a\ub294 \uc6b0\uc218\uc131\uc774 \uc788\uc73c\ub098 \ud310\ub9e4 \uac00\uaca9\uc774 \ub192\ub2e4\ub294 \ub2e8\uc810\uc774 \uc788\ub2e4[3,4].\n\uad6d\ub0b4 \uc81c\ud488\ub4e4\uc740 \uae30\uacc4 \uc8fc\ubcc0\uc5d0 \uba3c\uc9c0\uac00 \ub9ce\uc774 \ub098\uace0, \uc791\uc5c5\uc790 \uac00 \ub9c8\uc2a4\ud06c\ub97c \ud544\ud788 \uc368\uc57c \ud558\ub294 \uc0c1\ud669\uc774\ub2e4. \uc131\ub2a5 \uc2dc\ud5d8\uc2dc \uba3c\uc9c0 \ub3c4 \uad6d\ub0b4\uc0b0\uc774 \uba87 \ubc30\ub098 \ub354 \ub9ce\uc774 \ub098\uc624\ub294 \uc2e4\uc815\uc774\ub2e4.\n2.2 3\ucc28\uc6d0 \ubd80\ud488 \uc124\uacc4 \ubc0f \uc81c\uc791\n\uc544\ub798 \uadf8\ub9bc\ub4e4\uacfc \uac19\uc774 3\ucc28\uc6d0 \uc124\uacc4 \uc18c\ud504\ud2b8\uc6e8\uc5b4 (Pro-Engineer)[5]\ub97c \uc774\uc6a9\ud558\uc5ec \ud0c8\uace1\uae30\uc758 \ubd80\ud488\ub4e4\uc744 \uc124\uacc4\ud558 \uace0 \uc870\ub9bd\ud558\uc600\ub2e4.\n[Fig. 1] Drum to do the threshing\nFig. 1\uacfc \uac19\uc774 \ud0c8\uace1\ud1b5\uc758 \ub0a0\uc744 \ub098\uc120\ud615\uc73c\ub85c \ubc30\uce58\ud558\uc5ec \uc55e \uba74\uc5d0\uc11c \ucf69\uc744 \ud22c\uc785\ud558\uba74 \ub098\uc120\ud615\uc744 \ub530\ub77c \uc774\ub3d9\ud558\uba74\uc11c \ud0c8\uace1\uc744 \ud560 \uc218 \uc788\uac8c \uc124\uacc4\ud558\uc600\ub2e4.\n\uae30\uc874 \uc81c\ud488\uc758 \ud22c\uc785\uad6c\ub294 \ud0c8\uace1\ud1b5\uc758 \ub0a0\uacfc \ubc14\ub85c \uc811\ud574 \uc788\uc5b4 \uc11c \uc791\uc5c5\uc790\uc758 \uc190\uc774 \ub4e4\uc5b4\uac08 \uc704\ud5d8\uc774 \uc788\ub2e4. \uc774\ub97c \ud574\uacb0\ud558\uae30 \uc704 \ud574 \ud22c\uc785\uad6c\uc5d0 Fig. 2\uc640 \uac19\uc774 \ub0a0\uce74\ub86d\uc9c0 \uc54a\uc740 \ubc14\uc774\ud2b8\ub97c \ub450\uc5b4 \uc11c \uc800\uc18d\uc73c\ub85c \ud68c\uc804\uc744 \uc2dc\ucf1c \ucf69\ub300\ub97c \ubb3c\uace0 \ud0c8\uace1\ud1b5 \uc548\uc73c\ub85c \ub4e4 \uc5b4\uac00\uac8c \uc124\uacc4\ud558\uc5ec \uc791\uc5c5\uc790\uc758 \uc548\uc804\uc744 \ub3c4\ubaa8\ud558\uc600\ub2e4.\n[Fig. 3] Support of the belt shaft", + "\uc815\uc120\ub41c \ucf69\uc744 \ubc30\ucd9c\uc2dc\ud0a4\uae30 \uc704\ud574 \ubc30\ucd9c \ud32c\uc744 \ud0c8\uace1\uae30\uc758 \ub4a4 \ucabd\uc5d0 \ubc30\uce58\ud558\uc600\ub2e4. Fig. 5\uc640 \uac19\uc774 \ubc30\ucd9c \ud32c\uc758 \uac00\uc6b4\ub370 \ubd80\ubd84\uc5d0 \ub294 \uacf5\uae30\ub97c \ud761\uc785\ud560 \uc218 \uc788\ub3c4\ub85d \uc548\ucabd\uc73c\ub85c \uacbd\uc0ac\ub97c \uc8fc\uc5b4 \ud32c \ub0a0 \uc744 \uc81c\uc791\ud558\uc600\ub2e4.\n[Fig. 5] Exhaust fan\n\uc815\uc120\ub41c \ucf69\uc744 \ubc30\ucd9c\uc2dc\ud0a4\uae30 \uc704\ud574 \ubc30\ucd9c\uad6c\ub97c \ub4a4\ucabd\uc5d0 \ubc30\uce58\ud558 \uc600\ub2e4. \ubc30\ucd9c\uad6c \ub05d \ubd80\ubd84\uc744 \uc791\uc5c5\uc790 \uc55e\uc73c\ub85c \uc720\ub3c4\ud558\uc5ec \uc544\ub798\uc5d0 \ub294 \ud3ec\uc7a5\uc744 \ud560 \uc218 \uc788\uac8c \uc790\ub8e8 \ubc1b\uce68\ub300\ub97c \ub450\uc5c8\ub2e4.\n[Fig. 6] Outlet of a soybean\n\ud648\uc5d0 \uc815\uc120\ub41c \ucf69\uc774 \ub5a8\uc5b4\uc9c0\uba74 \uc774\uc1a1\uc2a4\ud06c\ub958(Fig. 7)\ub97c \ud0c0\uace0 \ubc30\ucd9c\uad6c\ub85c \ubcf4\ub0b4\uc9c4\ub2e4. \uc774 \ub54c \uc774\uc1a1\ub418\ub294 \ucf69\uc758 \uc591(\uccb4\uc801\uc720\ub3d9\ub7c9) \uc740 \uc2a4\ud06c\ub958\uc758 \ub2e8\uba74\uc801\uacfc \ud68c\uc804\uc18d\ub3c4\uc5d0 \ube44\ub840\ud55c\ub2e4[6].\n \uc18d\ub3c4 \uc2a4\ud06c\ub958\uc758\ub2e8\uba74\uc801\n[Fig. 7] Outlet of a soybean" + ] + }, + { + "image_filename": "designv8_17_0003454_6_61_4_61_4_501__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003454_6_61_4_61_4_501__pdf-Figure4-1.png", + "caption": "Fig. 4 Effect of offset values for pitch circle", + "texts": [], + "surrounding_texts": [ + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\nRg: \u57fa \u790e \u5186 \u7b52 \u534a \u5f84 R0: \u57fa \u790e \u30d4 \u30c3\u30c1 \u5186 \u7b52 \u534a \u5f84\nRx: \u6b6f \u5f62 \u4e0a \u306e \u4efb \u610f \u306e \u534a \u5f84 Tg: \u57fa\u790e\u5186\u7b52\u4e0a\u306e\u5186\u5f27\u6b6f\u539a T0: \u57fa \u6e96 \u30d4 \u30c3\u30c1 \u5186\u7b52 \u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a\nTx: Rx\u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a 2\u03c8g: \u5f27Tg\u306b \u5bfe \u3059 \u308b\u4e2d \u5fc3 \u89d2\n2\u03c80: \u5f27T0\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2\n2\u03c8x: \u5f27Tx\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2 \u03b1x: Rx\u4e0a \u306b \u304a \u3051 \u308b\u304b \u307f \u5408 \u3044 \u5727 \u529b \u89d2 \u03b10: \u5de5 \u5177 \u5727 \u529b \u89d2\n\u3092\u8868 \u3059.\n(a) \u5927 \u7aef \u76f4 \u5f84\n\u56f32\u3067 \u4efb \u610f \u306e \u534a \u5f84Rx\u306b \u304a \u3051 \u308b \u5186\u5f27 \u6b6f \u539aTx\u306f,X\u3092 \u8ee2 \u4f4d\n\u4fc2 \u6570 \u3068 \u3057\u3066\n( 1 )\n\u3067\u8868\u305b\u308b.\u307e \u305f\u57fa\u6e96\u30d4\u30c3\u30c1\u5186\u4e0a\u306e\u5186\u5f27\u6b6f\u539aT0 \u306f\n( 2 )\n\u3068\u306a \u308b.\u5f0f(1)\u306b \u5f0f(2)\u3092 \u4ee3 \u5165\u3059 \u308b \u3068\n( 3 )\n\u3068\u306a \u308b.\u5f93 \u3063\u3066,\u5927 \u7aef \u76f4 \u5f84 \u306f \u6b6f \u5148 \u306e \u3068\u304c \u308a\u3092\u9650 \u754c \u306b\u3059 \u308b \u306b \u306fTx=0\u3068 \u3059 \u308c \u3070 \u3088 \u3044.\u5f0f(3)\u3092inv\u03b1x\u306b \u3064 \u3044 \u3066 \u89e3\n\u304f\u3068\n( 4 )\n\u3068 \u306a \u308b.\u3053 \u3053\u3067\n( 5 )\n( 6 )\n\u3068\u3059 \u308b \u3068,\u76f8 \u5f53 \u5e73 \u6b6f \u8eca \u306e\u6b6f \u6570Zv\u306f,\u03b3 \u3092\u57fa \u790e \u5186 \u7b52 \u306d \u3058\u308c\n\u89d2 \u3068 \u3057\n( 7 )\n\u3068\u306a\u308b.\u307e \u305f\u4efb\u610f\u306e\u534a\u5f84Rx\u4e0a \u306e\u8ee2\u4f4d\u4fc2\u6570X \u306f\n( 8 )\n\u3067 \u8868 \u3055\u308c \u308b.\u3088 \u3063\u3066 \u5927 \u7aef \u534a \u5f84D0 \u306f\n( 9 )\n\u3088 \u308a\u6c7a \u5b9a \u3055 \u308c \u308b.\n(b) \u5c0f \u7aef \u76f4\u5f84\n\u5c0f \u7aef \u76f4 \u5f84 \u306e \u6c7a \u5b9a \u306b \u3064 \u3044 \u3066 \u306f,\u56f33\u306b \u793a \u3059 \u3088 \u3046 \u306b,\u6b6f \u306e\u5207 \u308a\u4e0b \u3052 \u3092 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5e73 \u9762 \u307e \u3067 \u751f \u3058\u3066 \u3082 \u826f\u3044 \u3068\u4eee\n\u5b9a5)\u3059 \u308b.\u8ca0 \u306e \u8ee2 \u4f4d \u304b \u3089,\u57fa \u6e96 \u5727 \u529b \u89d220\u309c \u306e \u5834 \u5408,\u5e73 \u6b6f \u8eca \u306e \u9650 \u754c \u6b6f \u6570 \u306fZmin=17\u3067 \u3042 \u308a,\u8ee2 \u4f4d \u4fc2 \u6570X \u306f\n( 10 )\n\u5f93 \u3063\u3066 \u5c0f \u7aef \u76f4\u5f84Di\u306f \u6b21 \u5f0f \u3088 \u308a\u6c42 \u307e \u308b.\npositive shift\n502 \u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u5893\u3064\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n( 11 )\n\u305f \u3060 \u3057,Z'\u306f \u5207 \u308a\u4e0b \u3052 \u3092 \u3069 \u3053 \u307e \u3067 \u8a31 \u3059 \u304b \u306b \u3088 \u3063\u3066 \u6c7a \u307e \u308b\n\u6b6f \u6570 \u3067,\u56f33\u306e \u5834 \u5408 \u3067 \u306fZ'=6\uff5e8\u306b \u3059 \u308c \u3070 \u3088 \u3044.\n(c) \u30aa \u30d5 \u30bb \u30c3 \u30c8\u4e0b \u3067 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84\n\u56f34\u306b \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3057\u3066 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84 \u306e \u5909 \u5316 \u306e\n\u69d8 \u5b50 \u3092 \u793a \u3059.\u56f3 \u4e2d \u306e \u5404 \u8a18 \u53f7 \u306f \u305d \u308c \u305e \u308c\na: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf Z: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e\u6b6f \u6570 \u03c9: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u89d2 \u901f \u5ea6\n\u03b2: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u89d2 R0: \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84 Ra: \u30aa \u30d5\u30bb \u30c3 \u30c8\u3067 \u5909 \u5316 \u3057\u305f \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84\nV0: \u534a \u5f84R0\u4e0a \u306e \u901f \u5ea6 Va: \u534a\u5f84Ra\u4e0a \u306e \u901f \u5ea6\n\u3092\u8868 \u3059.\u3053 \u308c \u3088 \u308a,\u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306b\u5bfe \u3057\u3066 \u5c0f \u6b6f \u8eca \u304c \u30aa \u30f3\u30bb \u30f3 \u30bf(P\u306e \u4f4d \u7f6e)\u306b \u304a \u3044 \u3066 \u306f,\u5c0f \u6b6f \u8eca \u306e \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84 \u306e \u6bd4 \u306f\u6b6f \u6570 \u306e \u6bd4(\u89d2 \u901f \u5ea6 \u306e \u6bd4)\u306b \u7b49 \u3057 \u304f\u306a \u308b \u304c,\u30aa \u30d5 \u30bb \u30c3 \u30c8 (\nP'\u306e \u4f4d \u7f6e)\u4e0b \u3067 \u306f \u4e21 \u534a \u5f84 \u306e \u6bd4 \u306f,\u306f \u3059 \u3070 \u89d2 \u306e \u5f71 \u97ff \u3092 \u53d7\n\u3051\u3066 \u5fc5 \u305a \u3057\u3082\u6b6f \u6570 \u306e \u9006 \u6bd4 \u306b\u7b49 \u3057 \u304f\u306f \u306a \u3089 \u306a \u3044.\u3059 \u306a \u308f \u3061 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3059 \u308b \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84Ra \u306f\n( 12 )\n\u3068\u306a \u308b.\u307e \u305f,\u5f0f(12)\u3067 \u03b2\u306e \u4ee3 \u308f \u308a\u306b \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf a\n\u3092\u7528 \u3044\u3066 \u8868 \u3059 \u3068\n( 13 )\n\u3068\u306a \u308b.\u305f \u3060 \u3057,\u30aa 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\u306b\u4e21 \u76f4 \u5f84 \u306e \u5dee, \u3064 \u307e \u308a\u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b.\u307e \u305f,\u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u304c \u5927 \u304d \u3044 \u307b\n\u3069\u5927 \u7aef,\u5c0f \u7aef \u76f4\u5f84 \u53ca \u3073 \u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b \u3053 \u3068\u304c \u308f \u304b \u308b.\u3053 \u308c \u306f \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u306e \u5897 \u52a0 \u306b\u4f34 \u3044 \u30d4 \u30c3\u30c1 \u5186 \u76f4\u5f84 \u304c \u5927 \u304d \u304f\u306a \u308b \u304b \u3089\u3067 \u3042 \u308b.\u3057 \u304b \u3057\u306a \u304c \u3089\u6b6f \u6570 \u304c40\u679a,\u30aa \u30d5 \u30bb \u30c3 \u30c8 10\n\u30fbm\u306b \u5bfe \u3057\u6b6f \u5e45 \u306f5mm\u7a0b \u5ea6 \u3067 \u3042 \u308a,\u540c \u3058 \u304f\u6b6f \u6570140 \u679a\n\u3067 \u308210mm\u7a0b \u5ea6 \u3068\u6b6f \u5e45 \u304c \u72ed \u3044.\u3053 \u306e \u3053 \u3068\u306f \u5148 \u306b\u8ff0 \u3079 \u305f \u3088\n\u3046\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e1\u3064 \u306e \u6b20 \u70b9 \u3067 \u3082\u3042 \u308b \u308f \u3051 \u3067 \u3042 \u308b.\u3055 \u3089\npitch plane\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 503", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a8\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n\u306b\u304b \u307f \u5408 \u3044 \u5727 \u529b \u89d2 \u306f \u5c0f \u7aef \u304b \u3089 \u5927\u7aef \u306b \u5411 \u304b \u3063\u3066 \u5927 \u304d \u304f\u306a \u308b5) \u305f\u3081,\u6709 \u52b9 \u306a\u52d5 \u529b \u4f1d \u9054 \u4e0a,\u4eee \u306b \u6b6f \u5e45 \u3092\u6e1b \u5c11 \u3055\u305b \u308b \u306b \u306f, \u5927\n\u7aef \u304b \u3089\u6e1b \u3089\u3059 \u3079 \u304d \u3067 \u3042 \u308b.\n3. \u901a \u5e38 \u306e \u30dc \u30d6 \u76e4 \u306b \u3088 \u308b \u6b6f \u5207 \u308a \u3068\u304b \u307f \u5408 \u3044 \u8a66 \u9a13\n\u4e0a\u8a18 \u306e \u8a08 \u7b97\u7d50 \u679c \u306b \u57fa \u3065 \u3044 \u3066 \u901a \u5e38 \u306e \u30dc \u30d6 \u76e4(HAMAI,H- 102 )\n\u3068\u5e02 \u8ca9 \u30db \u30d6(\u30e2 \u30b8 \u30e5 \u30fc \u30eb1,\u5de5 \u5177 \u5727 \u529b \u89d220\u309c,\u306d \u3058\u308c \u89d21\u309c 57',\n\u5207\u308c \u6b6f \u5217 \u65706)\u3092 \u7528 \u3044 \u3066 \u6b6f \u5207 \u308a\u3092 \u884c \u3063\u305f.\u5f53 \u521d,\u30dc \u30d6 \u3067 \u6b6f \u5207 \u308a \u3057\u305f \u5834 \u5408,\u5185 \u6b6f \u6b6f \u8eca \u306e \u30c8\u30ed \u30b3 \u30a4 \u30c9\u5e72 \u6e09 \u306b\u4f3c \u305f \u3053 \u3068\u304c \u30dc \u30d6 \u3068\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u3068 \u306e \u9593 \u306b\u8d77 \u3053 \u308a,\u6b6f \u5f62 \u306e \u5927 \u304d \u306a \u304f\u305a \u308c \u304c \u4e88\n\u60f3 \u3055 \u308c \u305f \u306e \u3067,\u30dc \u30d6 \u306e \u5207 \u308c \u6b6f \u304c3\u5217(\u5e458mm)\u306b \u306a \u308b \u3088 \u3046 \u306b \u5207 \u65ad \u3057\u305f \u3082\u306e \u3092\u7528 \u3044 \u3066 \u8a66 \u9a13 \u7684 \u306b \u6b6f \u5207 \u308a\u3092 \u884c \u3063\u305f(\u30db \u30d6 \u5e45 \u306b\u3088\n\u308b\u6b6f \u5e45 \u7b49 \u3078 \u306e \u5f71 \u97ff \u306f \u5225 \u5831 \u3067 \u8a73 \u7d30 \u306b \u8ff0 \u3079 \u308b).\n\u56f36\u306b \u5177 \u4f53 \u7684 \u6b6f \u5207 \u308a\u6cd5 \u3068\u6b6f \u5207 \u308a\u5f8c \u306e \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u3092 \u793a \u3059.\n\u6b6f \u5207 \u308a\u306f \u3044 \u308f \u3086 \u308b \u30b3 \u30f3\u30d9 \u30f3 \u30b7 \u30e7\u30ca \u30eb \u6cd5 \u3067 \u3042 \u308a,\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u7d20 \u6750 \u306b \u5bfe \u3057 \u3066,(1)\u30db \u30d6 \u306e \u4e2d \u5fc3 \u3092 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u4e2d\u5fc3 \u304b \u3089\u6a2a \u306b\u79fb \u52d5 \u3055\u305b \u6240 \u5b9a \u306e \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u3092 \u4e0e \u3048 \u308b.(2)\u30dc \u30d6 \u3092 \u3042 \u3089\u304b\n\u3058\u3081 \u5168\u6b6f \u305f \u3051 \u5206 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u8ef8 \u65b9\u5411 \u306b\u9001 \u308a,\u305d 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\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61. No. 4. 1995" + ] + }, + { + "image_filename": "designv8_17_0003173__VALVERDE_ALCALA.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003173__VALVERDE_ALCALA.pdf-Figure10-1.png", + "caption": "Figure 10: Cookie Node Architecture", + "texts": [ + " Run-Time Dynamically-Adaptable FPGA-based Architecture for High-Performance Autonomous Distributed Systems Chapter 2 HW Platform Design: HiReCookie 55 This section shows all the information about the HiReCookie platform design including processing and power supply units, their connections and board designs. The architecture of the HiReCookie platform follows the design proposed by [Portilla\u201910]. The Cookies approach represents a modular design where the functionalities of the node are implemented in physically separated layers or PCBs (Printed Circuit Boards). The four basic functionalities of these layers are: communications, processing, power supply and sensors/actuators (from now on sensor layer) as seen in Figure 10. All the modules are stacked together through vertical connectors that work both as mechanical links and vertical connection buses. These vertical buses take all the signals that are exchanged among layers to all the connected PCBs with independence on whether they are used or not. These signals include analogue, digital and different power rails. In this way, it is possible to increase flexibility by adding new layers in case additional functionalities or extensions are required. The modular design allows changing or updating the functionality of the node by only changing some of its layers, this represents another level of reconfigurability. Besides, since not all the nodes in a network have the same functionality, it is possible to reuse those layers that are common and add specific ones only when they are required. For instance, Figure 10 (d) includes two sensor layers while Figure 10 (a) only includes one. In the same way, Figure 10 (c) includes an additional memory layer to increase the already existent memory in the processing layer. For example, a router node could only include communications and power supply layers and, in case it is necessary, a processing layer. However, a sink node only includes the power supply and communication layers. Since all the signals pass through the vertical connectors to all the layers, the order in which the PCBs are connected is arbitrary. The only considerations to take into account is that, in general, communication and sensor modules are placed on the sides of the node due to interferences and contact with the environment" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000847_853_83_17-00194__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000847_853_83_17-00194__pdf-Figure5-1.png", + "caption": "Fig. 5 Coordinate system", + "texts": [], + "surrounding_texts": [ + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30bf\u3067\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3055\u305b\u308b\uff0e\u305f\u3060\u3057\uff0c2\u3064\u306e\u30db\u30a4\u30fc\u30eb\u89d2\u901f\u5ea6\u306e\u5927\u304d\u3055\u306f\u540c\u3058\u3067\u65b9\u5411\u3092\u9006\u306b\u3059\u308b\uff0e\u4e8b\u524d\u306b\u884c\u3063\u305f\u4e88 \u5099\u5b9f\u9a13\u3067\u306f\uff0c\u56de\u8ee2\u6570\u3092 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7000[rpm]\u4ee5\u4e0a\u306b\u3059\u308b\u3068\u56de\u8ee2\u8ef8\u306e\u89e6\u308c\u56de\u308a\u632f\u52d5\n\u304c\u5927\u304d\u304f\u306a\u308a\uff0c\u9a12\u97f3\u3082\u6fc0\u3057\u304f\u306a\u3063\u305f\uff0e\n\u305d\u3053\u3067\uff0c\u672c\u7814\u7a76\u3067\u306f\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u6570\u3092\u3042\u307e\u308a\u5927\u304d\u304f\u3057\u306a\u304f\u3068\u3082\u5b89\u5b9a\u6027\u3092\u826f\u597d\u306b\u4fdd\u3064\u3053\u3068\u304c\u3067\u304d\u308b\u3088\u3046\u306a\u8a2d\u8a08 \u6307\u91dd\u3092\u691c\u8a0e\u3059\u308b\uff0e\u306a\u304a\u56f3 1\u306b\u793a\u3059\u5b9f\u9a13\u88c5\u7f6e\u3092\u3082\u3068\u306b\u56f3 2,3\u3067\u793a\u3057\u305f\u30e2\u30c7\u30eb\u3092 SolidWorks\u4e0a\u3067\u4f5c\u6210\u3057\uff0c\u5404\u525b\u4f53\u306e\u8cea\n\u91cf\u3084\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306a\u3069\u306e\u7279\u6027\u3092\u6c42\u3081\u3066\u304a\u308a\uff0c\u6b21\u7ae0\u4ee5\u964d\u306e\u7406\u8ad6\u89e3\u6790\u3084\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u4f7f\u7528\u3057\u3066\u3044\u308b\uff0e\n3. \u904b \u52d5 \u30e2 \u30c7 \u30eb\n3\u00b71 \u5ea7\u6a19\u7cfb\n\u56f3 5\u306b\u5bfe\u8c61\u3068\u3059\u308b 2\u8f2a\u53f0\u8eca\u3092\u793a\u3059\uff0e\u56f3 5\u306f\u5ea7\u6a19\u7cfb\u306e\u8aac\u660e\u3092\u660e\u78ba\u306b\u3059\u308b\u305f\u3081\u306b\uff0c\u30b8\u30f3\u30d0\u30eb\u6a5f\u69cb\u3092 1\u3064\u306e\u307f\u63cf\u3044\u3066\n\u3044\u308b\uff0e\u53f0\u8eca\u306b\u306f\u30b8\u30f3\u30d0\u30eb\u304c\u53d6\u308a\u4ed8\u3051\u3089\u308c\uff0c\u53d6\u308a\u4ed8\u3051\u8ef8\u5468\u308a\u306b\u81ea\u7531\u306b\u56de\u8ee2\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306b\u306f\u30db\u30a4\u30fc\u30eb\u3092\u56de\u8ee2\u3055\u305b\n\u308b\u30e2\u30fc\u30bf\u304c\u56fa\u5b9a\u3055\u308c\uff0c\u30e2\u30fc\u30bf\u306b\u3088\u308a\u30db\u30a4\u30fc\u30eb\u304c\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3057\u3066\u3044\u308b\uff0e\n\u03a3B \u3092\u5730\u9762\u4e0a\u306b\u56fa\u5b9a\u3057\u305f\u57fa\u6e96\u5ea7\u6a19\u7cfb\u3068\u3059\u308b\uff0ez\u8ef8\u306f\u925b\u76f4\u4e0a\u5411\u304d\uff0cx\u8ef8\u306f\u53f0\u8eca\u9032\u884c\u65b9\u5411\u3092\u6b63\u9762\u3068\u3059\u308b\u3068\u304d\u53f3\u624b\u3068\u306a\u308b \u5411\u304d\uff0cy\u8ef8\u306f\u6c34\u5e73\u65b9\u5411\u3067\u53f0\u8eca\u306e\u9032\u884c\u3059\u308b\u5411\u304d\u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f\u8d77\u4f0f\u306e\u3042\u308b\u9762\u3092\u4e0a\u308a\u4e0b\u308a\u3059\u308b\u3053\u3068\u3092\u60f3\u5b9a\u3059\u308b\uff0e\u53f0\u8eca\u306e \u5e95\u9762\u306b\u539f\u70b9\u3092\u3068\u308a\uff0c\u03a3B \u3092 x\u8ef8\u56de\u308a\u306b\u5730\u9762\u306e\u50be\u304d\u89d2\u5ea6 \u03d5 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u5ea7\u6a19\u7cfb\u3092 \u03a3A \u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f 2\u8f2a\u3067\u8d70\u884c\u3059 \u308b\u305f\u3081\uff0c\u9032\u884c\u65b9\u5411\u306b\u5bfe\u3057\u3066\u5de6\u53f3\u65b9\u5411\uff08\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\uff09\u306b\u5012\u308c\u3088\u3046\u3068\u3059\u308b\uff0e\u3053\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03a3A\u306e y\u8ef8\u56de\u308a\u306b \u03b1 \u3068\u8868 \u3059\uff0e\u539f\u70b9\u3092\u53f0\u8eca\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3A\u3092 y\u8ef8\u56de\u308a\u306b \u03b1 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u53f0\u8eca\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3C \u3068\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u56de \u8ee2\u89d2\u5ea6\u3092 \u03a3C \u306e x\u8ef8\u56de\u308a\u306b \u03b2 \u3068\u8868\u3059\uff0e\u539f\u70b9\u3092\u30b8\u30f3\u30d0\u30eb\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3C \u3092 x\u8ef8\u56de\u308a\u306b \u03b2 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30b8\u30f3\u30d0", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3G \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f \u03a3G \u306e z\u8ef8\u56de\u308a\u306b\u56de\u8ee2\u3059\u308b\uff0e\u305d\u306e\u89d2\u5ea6\u3092 \u03b3 \u3068\u3059\u308b\uff0e\u539f\u70b9\u3092\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3 \u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3G \u3092 z\u8ef8\u56de\u308a\u306b \u03b3 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30db\u30a4\u30fc\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3W \u3068\u3059\u308b\uff0e\n\u4ee5\u964d\u6570\u5f0f\u4e2d\u3067\u306f cos\u03b8 =C\u03b8 , sin\u03b8 = S\u03b8 \u3068\u7565\u8a18\u3059\u308b\uff0e\n3\u00b72 \u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\n\u307e\u305a\uff0c\u56de\u8ee2\u904b\u52d5\u3092\u8868\u3059\u305f\u3081\u306e\u5404\u525b\u4f53\u306e\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092\u660e\u3089\u304b\u306b\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u901f\u5ea6\u306f\u56de\u8ee2\u89d2\n\u03d5 ,\u03b1,\u03b2 ,\u03b3 \u306e\u6642\u9593\u5909\u5316\u306b\u3088\u3063\u3066\u8868\u3059\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u3053\u308c\u3092 \u03a3W \u3067\u8868\u3057\u305f\u3068\u304d W \u03c9W \u3068\u8a18\u3059\u3068\uff0c\nW \u03c9W = C\u03b3 S\u03b3 0 \u2212S\u03b3 C\u03b3 0\n0 0 1\n C\u03b1 \u03d5\u0307 + \u03b2\u0307\nS\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307\n (1)\n\u3068\u306a\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3G \u3067\u8868\u3057\u305f\u3082\u306e\u3092 G\u03c9G \u3068\u8a18\u3059\u3068\uff0c\u5f0f (1) \u306b\u304a\u3044\u3066 \u03b3 = 0, \u03b3\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u307e\u305f\u53f0\u8eca\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092 C\u03c9C \u3068\u8a18 \u3059\u3068\uff0c G\u03c9G \u306b\u5bfe\u3057\u3066 \u03b2 = 0, \u03b2\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u3086\u3048\u306b\uff0c\u305d\u308c\u305e\u308c\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u306a\u308b\uff0e\nG\u03c9G = C\u03b1 \u03d5\u0307 + \u03b2\u0307 S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 C\u03c9C = C\u03b1 \u03d5\u0307 \u03b1\u0307 S\u03b1 \u03d5\u0307 (2)\n3\u00b73 \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae \u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e\u6163\u6027\u30c6\u30f3\u30bd\u30eb\u3092\u305d\u308c\u305e\u308c \u03a3W ,\u03a3G,\u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092\nIW = IWX 0 0 0 IWY 0\n0 0 IWZ\n , IG = IGX 0 0 0 IGY 0\n0 0 IGZ\n , IC = ICX 0 0 0 ICY 0\n0 0 ICZ\n (3)\n\u3068\u3059\u308b\uff0e\u305f\u3060\u3057\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u5bfe\u79f0\u6027\u304b\u3089 IWX = IWY \u3067\u3042\u308a\uff0c\u3053\u306e\u5024\u3092 IWXY \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TWR,TGR,TCR \u306f\u305d\u308c\u305e\u308c\u5f0f (1)(2)\u3092\u7528\u3044\u3066\uff0c\nTWR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 } + IWZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307 )2 ]\n(4)\nTGR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03d5\u0307) = 1 2\n{ IGX ( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + IGY ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 + IGZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 )2 }\n(5)\nTCR(\u03b1, \u03b1\u0307, \u03d5\u0307) = 1 2 ( ICXC2 \u03b1 \u03d5\u0307 2 + ICY \u03b1\u03072 + ICZS2 \u03b1 \u03d5\u0307 2) (6)", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u3068\u306a\u308b\uff0e\n3\u00b74 \u30c4\u30a4\u30f3\u30b8\u30f3\u30d0\u30eb\u30e2\u30c7\u30eb\u306e\u5fc5\u8981\u6027\n\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae\u5f0f (4)\u306b\u306f\uff0c\u53f0\u8eca\u306e\u50be\u304d\u89d2\u901f\u5ea6 \u03b1\u0307 \u3068\u5730\u9762\u306e\u8d77\u4f0f\u306b\u3088\u308a\u751f\u3058\u308b\u89d2 \u901f\u5ea6 \u03d5\u0307 \u306e\u7a4d\uff0c\u304a\u3088\u3073\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u901f\u5ea6 \u03b2\u0307 \u3068 \u03d5\u0307 \u306e\u7a4d\u304c\u3042\u308b\uff0e\u3053\u308c\u3089\u306e\u305f\u3081\u306b\uff0c\u5bfe\u8c61\u306e\u904b\u52d5\u65b9\u7a0b\u5f0f\u306e\u4e2d\u306b\u5730\u9762\u306e \u8d77\u4f0f\u306b\u3088\u308a\u751f\u3058\u308b\u89d2\u901f\u5ea6 \u03d5\u0307 \u306b\u4f9d\u5b58\u3059\u308b\u30e2\u30fc\u30e1\u30f3\u30c8\u304c\u8907\u96d1\u306b\u4f5c\u7528\u3059\u308b\uff0e\u3055\u3089\u306b\u30db\u30a4\u30fc\u30eb\u306e\u89d2\u901f\u5ea6 \u03b3\u0307 \u3068 \u03d5\u0307 \u306e\u7a4d\u304c\u3042\u308b \u305f\u3081\uff0c\u904b\u52d5\u65b9\u7a0b\u5f0f\u306e\u4e2d\u306b \u03d5\u0307 \u3068 \u03b3\u0307 \u306e\u7a4d\u304b\u3089\u306a\u308b\u30e2\u30fc\u30e1\u30f3\u30c8\u304c\u73fe\u308c\u308b\uff0e\u3053\u308c\u306f\u5730\u9762\u306e\u50be\u304d\u306e\u5909\u5316\u306e\u305f\u3081\u53f0\u8eca\u306e\u59ff\u52e2\u304c \u30d4\u30c3\u30c1\u89d2\u65b9\u5411\u3078\u50be\u304f\u969b\u306b\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\u3078\u767a\u751f\u3059\u308b\u30b8\u30e3\u30a4\u30ed\u30e2\u30fc\u30e1\u30f3\u30c8\u306b\u76f8\u5f53\u3057\uff0c\u53f0\u8eca\u3092\u5012\u305d\u3046\u3068\u3059\u308b\u5916\u4e71\u3068\u306a\u308b\uff0e\n\u3053\u308c\u3089\u306e\u5916\u4e71\u9805\u3092\u6253\u3061\u6d88\u3059\u305f\u3081\u306b\uff0c\u540c\u4e00\u69cb\u9020\u306e\u30db\u30a4\u30fc\u30eb\u3068\u30b8\u30f3\u30d0\u30eb\u3092\u53f0\u8eca\u306e\u524d\u65b9\u3068\u5f8c\u65b9\u306b\u4e00\u7d44\u3065\u3064\u914d\u7f6e\u3059\u308b\u30c4\u30a4 \u30f3\u30b8\u30f3\u30d0\u30eb\u30e2\u30c7\u30eb\u3092\u69cb\u7bc9\u3059\u308b\uff0e\u56f3 6\u306b\u305d\u306e\u69d8\u5b50\u3092\u793a\u3059\uff0e\n\u524d\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u3092\u30b8\u30f3\u30d0\u30eb 1\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3G1 \u3092\u914d\u7f6e\uff0c\u524d\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u3092\u30db\u30a4\u30fc\u30eb 1\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3W1 \u3092\u914d\u7f6e\u3059\u308b\uff0e \u307e\u305f\uff0c\u5f8c\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u3092\u30b8\u30f3\u30d0\u30eb 2\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3G2 \u3092\uff0c\u5f8c\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u3092\u30db\u30a4\u30fc\u30eb 2\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3W2 \u3092\u914d\u7f6e\u3059\u308b\uff0e \u524d\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03b21\uff0c\u524d\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u89d2\u5ea6\u3092 \u03b31\uff0c\u5f8c\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03b22\uff0c\u5f8c\u65b9\u306e\u30db \u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u89d2\u5ea6\u3092 \u03b32 \u3068\u3059\u308b\uff0e\n\u3053\u306e\u3068\u304d\uff0c\u524d\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TW1R \u306f\uff0c\nTW1R(\u03b1,\u03b21, \u03b1\u0307, \u03b2\u03071, \u03b3\u03071, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u03071 )2 + ( S\u03b21S\u03b1 \u03d5\u0307 +C\u03b21 \u03b1\u0307 )2 } + IWZ ( C\u03b21S\u03b1 \u03d5\u0307 \u2212S\u03b21 \u03b1\u0307 + \u03b3\u03071 )2 ]\n(7)\n\u5f8c\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TW2R \u306f\uff0c\nTW2R(\u03b1,\u03b22, \u03b1\u0307, \u03b2\u03072, \u03b3\u03072, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u03072 )2 + ( S\u03b22S\u03b1 \u03d5\u0307 +C\u03b22 \u03b1\u0307 )2 } + IWZ ( C\u03b22S\u03b1 \u03d5\u0307 \u2212S\u03b22 \u03b1\u0307 + \u03b3\u03072 )2 ]\n(8)\n\u3068\u306a\u308b\uff0e\u3053\u3053\u3067\uff0c\u03b21 = \u03b2 , \u03b22 =\u2212\u03b2 , \u03b3\u03071 = \u03b3\u0307, \u03b3\u03072 =\u2212\u03b3\u0307 \u3068\u306a\u308b\u3088\u3046\u306b\uff0c\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u5ea6\u306b\u62d8\u675f\u3092\u304b\u3051\uff0c\u30db\u30a4\u30fc\u30eb \u306e\u56de\u8ee2\u5236\u5fa1\u3092\u884c\u3046\u3053\u3068\u306b\u3059\u308b\u3068\uff0c\u3053\u308c\u3089\u306e\u548c\u306f\nTWR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = TW1R(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307)+TW2R(\u03b1,\u2212\u03b2 , \u03b1\u0307,\u2212\u03b2\u0307 ,\u2212\u03b3\u0307, \u03d5\u0307)\n= IWXY\n( C2\n\u03b1 \u03d5\u0307 2 + \u03b2\u0307 2 +S2 \u03b2 S2 \u03b1 \u03d5\u0307 2 +C2 \u03b2 \u03b1\u03072 ) + IWZ { C2 \u03b2 S2 \u03b1 \u03d5\u0307 2 + ( S\u03b2 \u03b1\u0307 \u2212 \u03b3\u0307 )2 }\n(9)\n\u3068\u306a\u308a\uff0c\u03b1\u0307\u03d5\u0307 , \u03b2\u0307 \u03d5\u0307 , \u03b3\u0307 \u03d5\u0307 \u306e\u9805\u304c\u6253\u3061\u6d88\u3055\u308c\u308b\uff0e \u3057\u304b\u3057\u306a\u304c\u3089\uff0c\u3053\u3053\u3067\u306f\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u5236\u5fa1\u3092\u6b63\u78ba\u306b\u884c\u3046\u3053\u3068\u304c\u56f0\u96e3\u3067\u3042\u308b\u3053\u3068\u3092\u60f3\u5b9a\u3057 \u03b3\u03071 = (1+ \u03b4 )\u03b3\u0307, \u03b3\u03072 = \u2212(1\u2212\u03b4 )\u03b3\u0307 \u3068\u8a18\u8ff0\u3059\u308b\uff0e\u3053\u3053\u3067 \u03b3\u0307 \u306f \u03b3\u03071 \u3068 \u03b3\u03072 \u306e\u5927\u304d\u3055\u306e\u5e73\u5747\u5024\uff0c\u03b4 \u306f\u5e73\u5747\u5024\u304b\u3089\u306e\u3070\u3089\u3064\u304d\u3092\u8868\u3059\u30d1\u30e9\u30e1\u30fc\u30bf\u3067\u3042 \u308b\uff0e\u3053\u306e\u3068\u304d\uff0c\u5f0f (9)\u306f" + ] + }, + { + "image_filename": "designv8_17_0000606_10a-e2a6eb25b194.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000606_10a-e2a6eb25b194.pdf-Figure2-1.png", + "caption": "Fig. 2 - Calculation scheme of a wheeled tractor", + "texts": [ + " a \u2013 tractor with front load; b \u2013 change in the weight of the front load; c \u2013 traction load locking system; d \u2013 sensor with cables for measuring traction load When moving evenly from the tractor side, the following factors affect the ground: the weight of the tractor G, the weight of the front GFL and rear GBL load, the resistance of the tool FTR, the traction on the front FTF and rear FTB wheel. This scheme was supplemented with countermeasures from the soil to the front RF and rear RB axles. The design diagram of the tractor used during the research is shown in Fig. 2. G \u2013 tractor total weight, kN; GFL, GBL \u2013 weight of the front and rear loads, kN, respectively; l \u2013 distance between tractor wheel axles (tractor base), m; lF \u2013 distance from the front wheel axis to the tractor weight application point, m; lFL, \u2013 distance from the front wheel axis to front load center of gravity, m; lBL \u2013 distance from the rear wheel axis to rear load center of gravity, m; rF, rB \u2013 radius of the tractor front and rear wheels, respectively, m; lH \u2013 distance from the rear wheel axis to the hook, m; hH \u2013 hook installation height, m; RF, RB \u2013 reaction at the tractor front and rear wheels contact point with the ground, kN; FTF, FTB \u2013 traction force on the tractor front and rear wheels, respectively, kN; FTR \u2013 resistance force of the tillage tool, kN; \u2013 resistance force action angle, rad", + " By reducing the action of the tractor weight and loads \ud835\udc3a = \ud835\udc3a\ud835\udc39\ud835\udc3f + \ud835\udc3a\ud835\udc39 + \ud835\udc3a\ud835\udc35 + \ud835\udc3a\ud835\udc35\ud835\udc3f to one point and taking into account the distance from the front wheel axis to the application point of the tractor weight lF, based on the moments from the action of the tractor components weight \ud835\udc3a\ud835\udc39\ud835\udc3f(\ud835\udc59\ud835\udc39\ud835\udc3f + \ud835\udc59\ud835\udc39) + \ud835\udc3a\ud835\udc39\ud835\udc59\ud835\udc39 = \ud835\udc3a\ud835\udc35(\ud835\udc59 \u2212 \ud835\udc59\ud835\udc39) + \ud835\udc3a\ud835\udc35\ud835\udc3f(\ud835\udc59\ud835\udc35\ud835\udc3f + \ud835\udc59 \u2212 \ud835\udc59\ud835\udc39) we will get: \ud835\udc59\ud835\udc39 = \ud835\udc3a\ud835\udc35\ud835\udc59\u2212\ud835\udc3a\ud835\udc39\ud835\udc3f\ud835\udc59\ud835\udc39\ud835\udc3f+\ud835\udc3a\ud835\udc35\ud835\udc3f(\ud835\udc59\ud835\udc35\ud835\udc3f+\ud835\udc59) \ud835\udc3a\ud835\udc39\ud835\udc3f+\ud835\udc3a\ud835\udc39+\ud835\udc3a\ud835\udc35+\ud835\udc3a\ud835\udc35\ud835\udc3f (1) In the absence of rear, front, and both loads, this distance will be: \ud835\udc59\ud835\udc39 \ud835\udc35 = \ud835\udc3a\ud835\udc35\ud835\udc59\u2212\ud835\udc3a\ud835\udc39\ud835\udc3f\ud835\udc59\ud835\udc39\ud835\udc3f \ud835\udc3a\ud835\udc39\ud835\udc3f+\ud835\udc3a\ud835\udc39+\ud835\udc3a\ud835\udc35 ; \ud835\udc59\ud835\udc39 \ud835\udc39 = \ud835\udc3a\ud835\udc35\ud835\udc59+\ud835\udc3a\ud835\udc35\ud835\udc3f(\ud835\udc59\ud835\udc35\ud835\udc3f+\ud835\udc59) \ud835\udc3a\ud835\udc39+\ud835\udc3a\ud835\udc35+\ud835\udc3a\ud835\udc35\ud835\udc3f ; \ud835\udc59\ud835\udc39 \ud835\udc35\ud835\udc39 = \ud835\udc3a\ud835\udc35\ud835\udc59 \ud835\udc3a\ud835\udc39+\ud835\udc3a\ud835\udc35 (2) Where GF, GB \u2013 part of the tractor weight transmitted to the front and rear axles of the tractor, kN. From Fig. 2, the sum of the moments of forces acting on the MTA relative to the wheels points of contact with the ground will be: \ud835\udc47\ud835\udc39 = \ud835\udc45\ud835\udc35\ud835\udc59 \u2212 \ud835\udc3a\ud835\udc59\ud835\udc39 + \ud835\udc39\ud835\udc47\ud835\udc39\ud835\udc5f\ud835\udc39 + \ud835\udc39\ud835\udc47\ud835\udc35\ud835\udc5f\ud835\udc35 \u2212 \ud835\udc39\ud835\udc47\ud835\udc45\u210e\ud835\udc3bcos\ud835\udefc \u2212 \ud835\udc39\ud835\udc47\ud835\udc45(\ud835\udc59\ud835\udc3b + \ud835\udc59)\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udefc = 0 (3) \ud835\udc47\ud835\udc35 = \u2212\ud835\udc45\ud835\udc39\ud835\udc59 + \ud835\udc3a(\ud835\udc59 \u2212 \ud835\udc59\ud835\udc39) + \ud835\udc39\ud835\udc47\ud835\udc39\ud835\udc5f\ud835\udc39 + \ud835\udc39\ud835\udc47\ud835\udc35\ud835\udc5f\ud835\udc35 \u2212 \ud835\udc39\ud835\udc47\ud835\udc45\u210e\ud835\udc3bcos\ud835\udefc \u2212 \ud835\udc39\ud835\udc47\ud835\udc45\ud835\udc59\ud835\udc3b\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udefc = 0 (4) Where: TF, TB \u2013 the total moment of forces acting on the MTA relative to the front and rear wheels contact point with the ground, respectively, kN m. The distribution of the traction forces of the front and rear wheels is determined according to the distribution of the tractor weight between the front and rear axles by the expressions: \ud835\udc39\ud835\udc47\ud835\udc39 = \ud835\udc3a\ud835\udc39 \ud835\udc3a \ud835\udc39\ud835\udc47 = \ud835\udc58\ud835\udc47\ud835\udc39\ud835\udc39\ud835\udc47 and \ud835\udc39\ud835\udc47\ud835\udc35 = \ud835\udc3a\ud835\udc35 \ud835\udc3a \ud835\udc39\ud835\udc47 = \ud835\udc58\ud835\udc47\ud835\udc35\ud835\udc39\ud835\udc47, and taking that the total traction force of the tractor as \ud835\udc39\ud835\udc47 = \ud835\udc39\ud835\udc47\ud835\udc45\ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udefc, the soil reactions to the rear and front axles will have the value: \ud835\udc45\ud835\udc35 = [\ud835\udc3a\ud835\udc59\ud835\udc39 \u2212 \ud835\udc58\ud835\udc47\ud835\udc39\ud835\udc39\ud835\udc47\ud835\udc45\ud835\udc5f\ud835\udc39\ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udefc \u2212 \ud835\udc58\ud835\udc47\ud835\udc35\ud835\udc39\ud835\udc47\ud835\udc45\ud835\udc5f\ud835\udc35\ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udefc + \ud835\udc39\ud835\udc47\ud835\udc45\u210e\ud835\udc3bcos\ud835\udefc + \ud835\udc39\ud835\udc47\ud835\udc45(\ud835\udc59\ud835\udc3b + \ud835\udc59)\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udefc]\ud835\udc59\u22121; (5) \ud835\udc45\ud835\udc39 = [\ud835\udc3a(\ud835\udc59 \u2212 \ud835\udc59\ud835\udc39) + \ud835\udc58\ud835\udc47\ud835\udc39\ud835\udc39\ud835\udc47\ud835\udc45\ud835\udc5f\ud835\udc39\ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udefc + \ud835\udc58\ud835\udc47\ud835\udc35\ud835\udc39\ud835\udc47\ud835\udc45\ud835\udc5f\ud835\udc35\ud835\udc50\ud835\udc5c\ud835\udc60\ud835\udefc \u2212 \ud835\udc39\ud835\udc47\ud835\udc45\u210e\ud835\udc3bcos\ud835\udefc \u2212 \ud835\udc39\ud835\udc47\ud835\udc45\ud835\udc59\ud835\udc3b\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udefc]\ud835\udc59\u22121, (6) or: \ud835\udc45\ud835\udc35 = [\ud835\udc3a\ud835\udc59\ud835\udc39 \u2212 \ud835\udc39\ud835\udc47\ud835\udc45((\ud835\udc58\ud835\udc47\ud835\udc39\ud835\udc5f\ud835\udc39 + \ud835\udc58\ud835\udc47\ud835\udc35\ud835\udc5f\ud835\udc35 \u2212 \u210e\ud835\udc3b)cos\ud835\udefc \u2212 (\ud835\udc59\ud835\udc3b + \ud835\udc59)\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udefc)]\ud835\udc59\u22121; (7) \ud835\udc45\ud835\udc39 = [\ud835\udc3a(\ud835\udc59 \u2212 \ud835\udc59\ud835\udc39) + \ud835\udc39\ud835\udc47\ud835\udc45((\ud835\udc58\ud835\udc47\ud835\udc39\ud835\udc5f\ud835\udc39 + \ud835\udc58\ud835\udc47\ud835\udc35\ud835\udc5f\ud835\udc35 \u2212 \u210e\ud835\udc3b)cos\ud835\udefc \u2212 \ud835\udc59\ud835\udc3b\ud835\udc60\ud835\udc56\ud835\udc5b\ud835\udefc)]\ud835\udc59\u22121, (8) Where kTF, kTB \u2013 coefficients of distribution of the tractor total weight between the front and rear axles, respectively, rel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004387_f_version_1673487113-Figure24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004387_f_version_1673487113-Figure24-1.png", + "caption": "Figure 24. Dorsal hand venipuncture model.", + "texts": [ + " The common hyperelastic principal structure models are the following: Mooney Rivlin model, Yeoh model, Ogden model, Valanis Landel model, and Neo Hookean model. By reviewing the data and studying the mechanical properties of biological tissues such as skin, subcutaneous fat, and venous vessels [36], this paper adopts the Yeoh model for skin and venous vessels and the Mooney\u2013Rivlin model for subcutaneous fat and muscle. Firstly, the dorsal hand vein puncture model was established in SolidWorks in layers according to the actual scale and then imported into ANSYS. As shown in Figure 24, this mainly includes five parts: the puncture needle, the skin layer, the subcutaneous fat layer, the vein vessels, and the muscle layer. The material properties of each part are configured by reviewing relevant information to meet the experimental simulation requirements [37,38] including material density, material model and parameters, and failure properties. The mechanical property parameters of each layer organization are shown in Table 5. Sensors 2023, 23, 848 18 of 22 Sensors 2023, 23, x FOR PEER REVIEW 19 of 24 3", + " The common hyperelastic principal structure models are the following: Mooney Rivlin model, Yeoh model, Ogden model, Valanis Landel model, and Neo Hookean model. By reviewing the data and studying the mechanical properties of biological tissues such as skin, subcutaneous fat, and venous vessels [36], this paper adopts the Yeoh model for skin and venous vessels and the Mooney\u2013Rivlin model for subcutaneous fat and muscle. Firstly, the dorsal hand vein puncture model was established in SolidWorks in layers according to the actual scale and then imported into ANSYS. As shown in Figure 24, this mainly includes five parts: the puncture needle, the skin layer, the subcutaneous fat layer, the vein vessels, and the muscle layer. The material properties of each part are configured by reviewing relevant information to meet the experimental simulation requirements [37,38] including material density, material model and parameters, and failure properties. The mechanical property parameters of each layer organization are shown in Table 5. Table 5. Table of mechanical characteristic parameters", + " A binding type of contact was used between the four layers of biological tissues, and a friction type of contact was used between the puncture needle and each biological tissue, with a friction coefficient set to 0.7. The \u201ctetrahedral\u201d method was introduced to divide the mesh to refine the biological tissues on the puncture path locally to improve the accuracy of the simulation. The puncture needle was set to move rigidly along the needle axis at a speed of 5 mm/s. A pressure of 0.7 kPa was applied to the inner wall of the venous vessel model to simulate venous blood pressure. contact pairs between the puncture needle and each tissue separately. Figure 24. Dorsal hand venipuncture model. Table 5. Table of mechanical characteristic parameters. Organization Materials Mechanical Parameters C10 (MPa) C20 (MPa) C01 (MPa) D1 (MPa\u22121) D2 (MPa\u22121) Skin Yeoh model 0.5 \u22120.06 0.01 0.1 S cutaneous fat o ney Rivlin model 0.1 \u22120. 4 0. 1 Venous vascular Yeoh model 0.4 \u22120.05 0.01 0.12 Muscle Mooney Rivlin model 1 \u22120.5 0.1 The LS-DYNA module was used to perform venipuncture simulation experiments. Because the puncture model consists of five parts, the puncture process involves the setting of contact pairs between each part" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003706_6_2_LiXiaobo2006.pdf-Figure5.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003706_6_2_LiXiaobo2006.pdf-Figure5.3-1.png", + "caption": "Fig. 5.3: Simplified output matching design with cascade connection", + "texts": [ + " Furthermore, if the Q of the resonator is high enough, at out of band \"4 Simulation Studies on Notch Filter 1 with Varactor Tuning frequency, the ZE is near to zero, and it is obvious the Gm will be equal to gm. So in band Gm =0, while at out of band Gm ^gm, the bandstop behavior is obvious. 5.2.2 Output Matching Because the resonators are not located at the connector of the input transistor, the output matching design is simplified compared to the bandpass filter in Chapter 4. No output matching stage is needed in this design, because the output impedance of the filter is mainly determined by the loading resistor now (RL in Fig. 5.3). In actual design, to cancel the parasitic capacitive loading at the output, an on chip inductor (Li in Fig. 5.3) is added in series with the loading resistor. Furthermore, at high frequency, to reduce the effect of the resonator on the output impedance of the filter, the input transistor is constructed by two transistors 75 Simulation Studies on Notch Filter 1 with Varactor Tuning in cascade connection, as shown in Fig. 5.3. Transistor Q3 can be viewed as a common base stage. Its output impedance [40, pp. 191] is: Z.\u00ab* I | | ( f i f i kz\u201e ) (5.2) ZE3 is the impedance seen at the emitter of the Q3. From Eqn. (4.2), ZE3 is increased by the factor of gm3r\u00b03 , and RL is in parallel with g m 3 r\u00b03 Z\u00a3 3 , so the effect of ZE3 on Z0 is much reduced. (Notice: ZE3 in Eqn. (5.2) is different from ZE in Eqn. (5.1), which is the impedance at the emitter of Qi. Actually, ZE3 is equal \u00ab o i 5.2.3 Frequency Tuning Scheme In this filter design, varactors are used for frequency tuning", + " The Q-Enhancement circuit employed here is the same as the one presented in section 4.2.3.2. Because the varactors have lower quality factor when it is reverse biased at lower potential, more bias current is needed for the Q-Enhancement circuit at the lower resonant frequency. That is totally reverse to the active inductor presented in Chapter 3, in which the Qenhancement circuit requires more bias current at the higher operating frequency. 5.2.5 Input Matching The input section of the notch filter in Fig. 5.2 is depicted in Fig. 5.6. According to Fig. 5.3 and Eqn. (4.1), the input impedance of the filter is: 8 L 1 jcoL 1 Zjn = r b + ^ = + \u2014\u2022*\u2014. + , (5.5) C\u201e \\-o)2LC \\-co2LC jcoCK and the real part of Eqn. (5.5) is: ZK = Th-\u00a5^L -. . (5.6) Cn \\-co2LC By a simple analysis to Eqn. (5.6), it is obvious that Zre will be a negative or a small positive value when co is larger than co0 = \u2014. \u2022 . And if the difference VLC between co and con - , is small enough, Zre will even be a large negative 4LC 78 Simulation Studies on Notch Filter 1 with Varactor Tuning value" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004544__39_article-p159.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004544__39_article-p159.pdf-Figure11-1.png", + "caption": "Fig. 11 Cardan shaft with variable slope angle of central shaft in range from -40\u00b0 to 40\u00b0", + "texts": [], + "surrounding_texts": [ + "The construction of the universal joints allows transferring torque moment between two rotating abaxial shafts. In some cases, this allows axle shift (2). The most commonly used joint is the universal joint shown in Fig. 4. In the motor vehicles are used universal joints for maximal axes deviation 8\u00b0. Special design allows also greater deviation of the axes (5, 6). Kinematic simulation was made using the CAD/CAM/CAE system CATIA V5 on the model of the cardan shaft which contains two universal joints (Fig. 5). Between all connections with bearings, the revolute type of joint and one prismatic type of connection for central cardan shaft was used, which allows adjustment of the relative position between two parts of the cardan shaft through castellated shaft connection. All degrees of freedom were blocked for the frame. (1- flange, 2 \u2013 universal joint, 3 \u2013 cardan shaft, 4- castellated shaft) In the first case, kinematic analysis of the cardan shaft sloped at an angle 15\u00b0, was simulated. The input and output shafts were parallel during analysis as is shown in Fig. 6. The graphical output of the angular acceleration obtained from the central cardan shaft proves cardan error because the angular acceleration is not zero and the shape of the curve is sinusoidal. The sinusoidal curve shape in Fig. 7 shows two areas with acceleration and two areas with deceleration during one revolution of the input driving shaft. Angular acceleration for the output driven shaft is shown in Fig. 8, where can be clearly seen that angular acceleration during a complete turn of the input driving shaft constant with a zero value. This result obtained through kinematic simulation using the CAD/CAM/CAE system CATIA V5 proves, that using two universal joints in cardan shaft construction with parallel input and output shafts leads to neutralization of cardan error and input and output angular speeds and accelerations for both shafts are constant and equal zero. This theory was confirmed through equations [8]. The second case completed on the same cardan shaft construction but with the central cardan shaft was sloped under a higher angle with the value 25\u00b0. The graph in Fig. 9 shows the obtained values of angular acceleration of the central cardan shaft where it can be seen that the amplitude of angular acceleration has a higher value than in Fig. 7. When the angle \u03b1 between the input driving shaft and central cardan shaft (central cardan shaft and output driven shaft) grows, then the amplitude of angular acceleration grows too. The third case simulates the variable cardan shaft where the angle \u03b1 changes value from -40\u00b0 to 40\u00b0 while the input driving shaft did four turns (1440\u00b0). Fig. 12 shows angular acceleration during the whole kinematic analysis. This type of analysis also proves that if angle \u03b1 is decreasing then angular acceleration is decreasing too and viceversa." + ] + }, + { + "image_filename": "designv8_17_0004680_article_25848203.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004680_article_25848203.pdf-Figure2-1.png", + "caption": "Figure 2. the construction of stewart motion system", + "texts": [], + "surrounding_texts": [ + "Ships and offshore platforms have been widely used in the marine transportation and exploitation of ocean resources. Due to the load of wind, wave, current of sea , The platform will occur oscillating movement, Not only have effects on personnel health and equipment, but do harm to the offshore production. Stewart platform has six degrees of freedom of movement parallel mechanism with advantages about stiffness, bearing capacity, high accuracy. this thesis combine the characteristics of ocean wave motion and parallel institutions\uff0cDesign and analysis a Ship borne compensated stable platform based on 6-SPU Stewart mechanism. The construction of the system show as the Fig.1. According to the space coordinate transformation, the vector R' of the moving coordinate system can be transformed the vector R of static coordinate system. TZcYcXcP ddd ddd ddd T PTRR },,{ ' 333231 232221 131211 = = +=" + ] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure112-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure112-1.png", + "caption": "Figure 112. Boundary condition (for pin)", + "texts": [], + "surrounding_texts": [ + "Inputs E 1 Axial Modulus, msi E 2 Transverse Modulus, msi E 3 Modulus, msi G 12 = G 13 Shear Modulus, msi G 23 Shear Modulus, msi \u03c5 12 = \u03c5 13 Poisson\u2019s Ratio \u03c5 23 Poisson\u2019s Ratio MTM 49-LT Unidirectional 19.9 0.99 0.99 0.302 0.398 0.244 0.257 A.5.5. Isotropic Section Creation One section was created for the steel. To make a new section right click Section category and click create. Name it Isotropic, for the category chooses Solid, and for the type choose 150 Homogeneous. Click continue, and then choose Steel as the material. Apply the steel section to the steel pin part and the steel side plate. In this step, we also want to duplicate the SidePlate part. Right click on the SidePlate and click copy, name it SidePlate2. Expand the SidePlate options by pressing the (+) icon next to the part name, click Section Assignments, click the part and then it should highlight in red. Click done once selected. For the section choose the Isotropic section which was created then hit Ok. 151 Apply this same method to the SteelPin part and the Sideplate2 part. A.5.6. Composite Laminate Section Creation The specimen which was created was a carbon fiber laminate composed of 16 layers with an orientation of [0 0 +45 -45 +45 -45 90 90]s. Abaqus has a Composite layup tool which is found in each individual part. Keep the name default, set the initial ply count to eight and set the element type to solid. 152 A new window appears. In this window, all of the laminate stacking directions along with the rotation axis are specified. 153 Before a layup orientation can be created; a datum coordinate system needs to be defined. Click Create Datum CSYS. Create a rectangular coordinate system and keep the default name. Next, it will ask you to specify a point, click the point in the center of the hole shown below in the figure. Keep the Rotation axis to Axis 3 and keep the Stacking Direction to Element direction 3. Check the box that says, \u201cMake calculated sections symmetric\u201d. Since we are only going to specify eight of the plies, which are part of the orientation. Next, we need to specify where on the part we have this orientation. In the region section, double click it, click on the specimen, and then click the done button. Do that for each layer and then for the material section, choose Uni as the material. The element relative thickness should 154 equal the reciprocal of the amount of elements through the thickness of the part. For example, my mesh consists of two element, which span the thickness of the specimen. My element relative thickness was set to 0.5 (2-1). 155 Last of all, set each ply orientation angle starting with the outermost layer. Keep the integration point to one. The result should look like this. 156 A.5.7. Assembly Creation Under the Assembly submenu, create an Instance. Make each of the parts are set as Dependent also make sure to check the Auto-offset from other instances. 157 The next part requires getting used to Abaqus\u2019 assembly options. This can be tricky, but it takes practice. After moving each part around, the final assembly should look something like this below. Make sure the specimen is centered between both of the side steel plates. The specimen should sit 1 in. into the pin, which is how it was loaded in the experiment. The distance between the two side plates is 0.25 in. Make sure the top of the pin is touching the top of both of the side steel plates. 158 A set needed to be created for a specific node. Abaqus gives you an option to select a specific node of interest and name it whatever you please. Therefore, in my model I wanted to select a node, which is in the middle of the specimen and located at the bottom of the hole. This location is of critical importance to the model because that is the location I want to monitor the vertical 159 deflection. This is the location where we will want to compare the experimental extensometer displacement and the nodal displacement in the numerical model. While in the Assembly module, I created a new set, picked the corresponding node, and named it Monitor. Switch to the Step module and then you will see the main horizontal bar at the top of the screen change accordingly. Now the main horizontal bar should have an Output menu. Click into this menu and click DOF Monitor. There should be an option to toggle on, Monitor a degree of freedom throughout the analysis. Click Edit, and then click Points in the prompt area and choose the node set Monitor from the region selection dialog box. Now we set the Degree of Freedom we want to monitor. In our model, we are interested in the displacement in the Y direction because that is actually, what the extensometer measured in the experiment. As we can see in, we want to monitor the Y-axis displacement so we set the Degree of Freedom to 2. Now we click Ok. 160 Surfaces needed to be created for each specific part. A very important feature is located in the surface option, here the user is able to select and define a surface on any particular part in your model. So what I did was define a surface called InnerSpecimen, this was defined as the inner surface of the specimen\u2019s hole. The second surface I defined was the outer surface of the pin and named it Pin. A.5.8. Step Creation Two steps need to be created one for the contact step and another for the load step. Abaqus runs the steps in order so first we are going to tell Abaqus that there is contact between some of the parts and after that, contact is established the load step can be applied. Create the contact step 161 and make sure all of these match. Create the load step and make sure all of these match. 162 A.5.9. Interaction Creation Next, we need to create an interaction between the pin and the specimen along with the two side plates. Right click the Interactions submenu and click Create. Choose Surface-to-surface contact. Keep the name to default and make sure to make it for the Initial Step. Click the outer surface of the pin as the Master Surface. After this step, go into the assembly and hide the SteelPin part by right clicking on it, and selecting Hide. 163 Once the pin is hidden, selecting the slave surfaces is a lot easier. Select Slave at the bottom menu and then select the inner hole surface of the two steel plates along with the specimen (hold Shift to select more than one at a time). Then click done and that should be all. Keep it at Finite Sliding and keep the Discretization method to Surface-to-Surface. 164 Then click the create Contact interaction property button. Choose Contact and name it NoFric. Then under Mechanical Submenu add Normal and a Tangential Behavior. Pick penalty for Tangential Behavior and choose a friction coefficient of 0.46. For the normal Behavior, Pressure Over-closure \u201cHard\u201d Contact, Constraint enforcement method Default and make sure to allow separation after contact is checked. 165 A.5.10. Defining the Load Next, we need to define a load in the model. Right click the load submenu and click create. Name the load, then apply the load in the load step. Choose a Pressure load for type. Select bottom faces of the two steel plates (shown red in the figure). Select Total Force for the Distribution type, and enter a magnitude of -600 and keep amplitude as ramp. 166 167 A.5.11. Defining the Boundary Conditions Three boundary conditions were applied to the model. One boundary condition was applied to the top face of the specimen and this will simulate the clamps in the Instron machine. The second boundary condition was applied to the side steel plates. For this condition, we want to prevent the plates from moving out from the z-plane. The last boundary condition was initially applied to the contact step and then it became modified from the load step. The last boundary condition dictated how the pin was to move in the model. Right click on the boundary conditions (BCs) submenu and click create. Name it Fixed and apply it to the Contact step. For the category choose Mechanical and for type, choose Symmetry/Antisymmetry/Encastre. Then click Continue. Select all of the outer sections of the steel side plates. Choose Encastre as the type. 168 Right click on the boundary conditions (BCs) submenu and click create. Name it SideFaces and apply it to the Load step. For category choose mechanical and for type choose Displacement/Rotation. Then click continue. Select all of the outer sections of the steel side plates. Set the U3 equal to zero since no deflection is expected to occur in this direction. 169 Right click on the boundary conditions (BCs) submenu and click create. Name it PinBC and apply it to the Contact step. For category, choose mechanical and for type choose Displacement/Rotation. Then click continue. Select all the surfaces of the pin. 170 Right click on the load and press edit. Disable the U2 boundary condition by unchecking the box. A.5.12. Defining the Mesh The partitions that were created for the side plates and the specimen simplified the mesh defining process. The Seed Edges command was used for each part and each part was highlighted. 171 In the options, the number method was chosen and the bias was set to none. The sizing controls options defined how many elements would be assigned to each element of the partition. For my model, I kept the number of elements equal to two. After this, I clicked Ok. Apply the same method to all the parts. Apply these settings under the Mesh Controls options. 172 In the element type settings, make sure all of these are applied to both the pin and side plate parts. All of these settings should be default. For the specimen, only difference was to uncheck the Reduced integration box. 173 A.5.13. Creating the Job Lastly, we need to create a specific job for your model. Once a job is created, you need to right click on the job and submit it. Once submitted, the job will run and once it converges, it will say Completed assuming everything runs smoothly. To see the results, right click on the job and click the results. This should open up another tab where the user is able to see the different displacements and stresses in the different directions." + ] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure8-1.png", + "caption": "Figure 8 Captive Screw Access Port Design.", + "texts": [ + " In addition to their low profile, another benefit of these screws is that the screw itself is contained by the outer sleeve. This simplifies handling and integration operations greatly, as there is no longer a need to keep track of individual screws and also significantly less risk of foreign object debris (FOD) on the inside of the P-POD. The downside of these captive screws is that in the size necessary for this task, the only head style available is a standard flat head, which is typically not a preferred screw head to work with. This access port design is shown below in Figure 8. Page 10 The captive screw design showed promise. However, late in the design process, the captive screw manufacturer strongly recommended using at least a whole diameter of the press-fit sleeve-in material surrounding the sleeve, to prevent the access port cover material from yielding when the sleeve is pressed into the tab. There is simply not enough space on the side panel for such large mounting tabs to be practically implemented. This necessitated the exploration of one final design option, in which the access port design itself was maintained, but the 4-40 Captive Screws were replaced by Torx-head 4-40 button cap screws" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure44-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure44-1.png", + "caption": "Figure 44 P-POD Mk. IV Back Plate Purge Interface", + "texts": [ + " In an effort to save mass, parts of the walls not near Page 59 mounting screws or other features were thinned but remained constant height with the rest of the part. Additionally, four standoffs were added to streamline the implementation of a gaseous purge system or the Power-On system. If either system is required, the part can simply be sent out and have mission specfic holes drilled into it. The amount of material removed was low, saving only 12 grams, but it did not increase the part\u2019s complexity an appreciable amount. The Back Plate following the changes is shown below in Figure 43. Additionally, an example of the purge interface is shown in Figure 44. The part was expected to lose little to no strengh with this Page 60 change, as no direct load path was altered and interfaces to other panels remained unchanged. In order to verify the prediction that the part retained its strength, an FEA was conducted under the Z-axis load case applied to the 4 spring plunger holes, which are the large holes shown in the corners of the figures above. All outer walls were considered fixed. The resulting stress is shown below in Figure 45. Slight stress was seen in each of the 4 corners, but this part exhibited and extremely high margin of safety of 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000107_e_download_6617_5459-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000107_e_download_6617_5459-Figure1-1.png", + "caption": "Fig. 1. Plan view of the manual self-cleaning fork (starting position (a) and working position (b)).", + "texts": [ + " The technical task is achieved by the fact that this manual self-cleaning fork consists of a handle and a frame with many elongated spaced tines, which is fixed at one end of the handle, a cleaning plate with many spaced holes in which the tines are located, a spring, a movable handle. The cleaning plate is fixed to the movable handle which has lateral longitudinal grooves, while the spring is located on top of the handle inside the movable handle. The technical essence of the proposed device \u201cManual self-cleaning fork\u201d is explained on Fig. 1 and Fig. 2. Essentially, the design of this manual self-cleaning fork consists of a handle 1 and a frame 2 with many elongated spaced tines 3, which is fixed at one end of the handle 1, as well as a cleaning plate 4, which is fixed to the movable handle 5, and a spring 6 located on top of the handle 1 inside the movable handle 5. The movable handle 5 has lateral longitudinal grooves 7. The movable handle 5 provides the movement of the cleaning plate 4 relative to the handle 1, and, consequently, the compression and releasing of the spring 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002461_ticle_download_33_42-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002461_ticle_download_33_42-Figure1-1.png", + "caption": "Fig. 1. The holder using CATIA .", + "texts": [], + "surrounding_texts": [ + "such as a flight control system for aircraft. This why an accurate value for moment of inertia is needed. A test rig was designed and made form cardboard and then developed for wood. Experiments were carried out, to get to the final shape and product for the test rig, and it was manufactured with dimensions of 2.7x2.5 meters and with a holder dimension of 60x60 cm that bears up to 10 kg. Moreover, an electronic circuit has been used to measure the period of oscillations. The moment of inertia of a rectangular block of wood and a UAV is found. The moment of inertia was measured analytically and experimentally for the block of wood, and by comparing the values it founds that the error ratio from 1%to5% in X axis and -6% to 7% in Y axis. For the UAV the moment of inertias error ratio in X axis from 2% to 5% and in Y axis from 11% to 14%. It is noticed that the greater the additional weight, the greater the accuracy of the device.\nKey words-Moment of Inertia, Simple Pendulum Theory, Test Rig, Unmanned Aerial Vehicle, Electronic I. INTRODUCTION\nMoment of inertia is the resistance of the rotational acceleration of an object. Its essential characteristic in calculating the aircraft stability and control parameters, and developing a flight control system. It can be determined analytically, experimentally, or by using Computer Aided Design (CAD) software. Analytical method can be used for simple regular shapes, but for the complex shapes it could be more complicated and tedious. Therefore, it is not suitable for shapes like aircrafts[5]. CAD software can give a precise moment of inertia but it consumes time because it needs to include all the details and material types. During decades scientists have conducted many experiments and developed many techniques to obtain a practical technique for obtaining the moment of inertia experimentally, and found that calculating the moment of inertia by using location of center of gravity of the body, based on a simple pendulum theory is the most efficient method for simplicity and high accuracy [1]. The aim of the research is to design and fabricate a device capable of measuring the moment of inertia for any engineering part as general and for UAV (as a case study) in both x and y axes. The research work was divided in to four main stages, designing of the device, fabricating, testing, and developing the technique.\nMeasuring an aircraft\u2019s moment of inertia is not a new concept. It has been found since the beginning of the aviation 1926. NACA used simple pendulum theory in measuring Moment of Inertia and improved and developed it during decades. Russians developed the compound pendulum to get better results [1], and had an experiment to measure moments in pitch, roll, and yaw on HP115 slender wing research aircraft, depending on the pendulum theory with fuel tanks empty and full [2].Additionally, Barnes and Wood field made a device to measure MOI based on spring restrained oscillations and examine it on Delta-2 Fairy\u2019s aircraft. In space craft X-38 Peterson used bifilar pendulum, single point suspension, spring table and dynamic inertia method to calculate the MOI [3]. In addition, A.Shakoorl, A.V. Betin, and D.A. Betin [3], [4] used three different techniques, compound pendulum, physical double pendulum and bifilar tensional pendulum in order to measure Moment of Inertia for light UAV. Compound pendulum has swung and oscillated the UAV in one axis. Physical double pendulum enables to perform the UAV in two simultaneous oscillations in opposite directions about two different axes. The bifilar tensional pendulum determines the MOI by swinging the UAV about axes passing through the Center of Gravity. The results indicated from bifilar tensional pendulum is more accurate than the others and it could be on x, y, and z axis [4]. Michael used an experiment to measure moment of inertia for a model of wooden aircraft and wooden block, using a pendulum theory, by comparison of the experimental and real results. Deviations between the experimental determined moment of inertia ranged from 0.42% to 1.70%. It shows that the experiment can be determined not only for the aircraft but also for irregular shaped objects [5]. Accuracy of the test rig depends on the construction of the pendulum, dimensions and the precision of measurements. To enhance the results, a small angle of oscillation Title", + "angle is used to acquire more precise results [5]\u2013[7].Repeating the measuring process (more than 10 times) and taking into consideration the vertical location of the center of gravity, increases the accuracy [6]\u2013[8].Furthermore, developing measuring techniques, such as using of bifilar pendulum with Kalman filter attached with controller and sensors to measure the period, eliminate unwanted signal and drift noise from measurement, and reduces the human error for more appropriate results [9].\nMeasuring an aircraft\u2019s moment of inertia is not a new concept. It has been found since the beginning of the aviation 1926. NACA used simple pendulum theory in measuring Moment of Inertia and improved and developed it during decades. Russians developed the compound pendulum to get better results [1], and had an experiment to measure moments in pitch, roll, and yaw on HP115 slender wing research aircraft, depending on the pendulum theory with fuel tanks empty and full [2].Additionally, Barnes and Wood field made a device to measure MOI based on spring restrained oscillations and examine it on Delta-2 Fairy\u2019s aircraft. In space craft X-38 Peterson used bifilar pendulum, single point suspension, spring table and dynamic inertia method to calculate the MOI [3], [4]. In addition, A.Shakoorl, A.V. Betin, and D.A. Betin [3]\u2013[5] used three different techniques, compound pendulum, physical double pendulum and bifilar tensional pendulum in order to measure Moment of Inertia for light UAV. Compound pendulum has swung and oscillated the UAV in one axis. Physical double pendulum enables to perform the UAV in two simultaneous oscillations in opposite directions about two different axes. The bifilar tensional pendulum determines the MOI by swinging the UAV about axes passing through the Center of Gravity. The results indicated from bifilar tensional pendulum is more accurate than the others and it could be on x, y, and z axis [4]. Michael used an experiment to measure moment of inertia for a model of wooden aircraft and wooden block, using a pendulum theory, by comparison of the experimental and real results. Deviations between the experimental determined\nmoment of inertia ranged from 0.42% to 1.70%. It shows that the experiment can be determined not only for the aircraft but also for irregular shaped objects [5]. Accuracy of the test rig depends on the construction of the pendulum, dimensions and the precision of measurements. To enhance the results, a small angle of oscillation Title angle is used to acquire more precise results [6], [7].Repeating the measuring process (more than 10 times) and taking into consideration the vertical location of the center of gravity, increases the accuracy [6], [8].Furthermore, developing measuring techniques, such as using of bifilar pendulum with Kalman filter attached with controller and sensors to measure the period, eliminate unwanted signal and drift noise from measurement, and reduces the human error for more appropriate results [9].", + "The test rig was manufactured by dimension (2.7m x 2.5m) with ability to carry maximum weight 10Kg.The side shape was made as triangle (A shape) for its capability to afford weights and to increase the stability of the device. A four steel bars (60cm) welded together to form the holder. Then, wires with 1 meter long welded to the holder edges. Showed in (Fig 4). The holder suspended by hooks to the horizontal beam (Fig 5). The suspension part was made by welding a u-shaped metal hook in the horizontal beam and hangs the holder on it. To make the measuring process clear and easy, an electronic circuit (is shown in Fig 6) has been added to the final model," + ] + }, + { + "image_filename": "designv8_17_0002151_272X.2016.5.02_77271-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002151_272X.2016.5.02_77271-Figure2-1.png", + "caption": "Fig. 2. Phase currents of direct and negative sequence and resulting TG currents", + "texts": [ + "134 ; in the rotor winding the turns number Nr = 224. Theoretical basics of the TG unbalanced operation mode analysis. Unbalanced modes in three-phase TG are results of phase currents difference because of different stator phase windings loadings. These modes are investigated by using the method of symmetrical components [2, 3]. Actually, phase currents of direct IA1, IB1, IC1 and negative IA2, IB2, IC2 sequences as well as resulting currents IA, IB, IC are considered. Their assumed initial system is presented in Fig. 2 by vector diagram. In the correspondence with DSU 533-200 RMS of negative sequence currents are assumed 0.08IsN. Besides, maximal RMS of all resulting phase currents is limited by rated value IsN. On this basis, by calculation it is determined that the phase currents RMS are IA=2170.2 \u0410; IB=2314.7 \u0410; IC=2015.3 \u0410, and more detailed methods of their calculation is presented in [10]. In the calculations of rotating magnetic fields instantaneous values of phase currents are used [7, 8]. In this paper, at unbalanced loading phase currents are defined by their temporal functions: )cos( IamaA tIi ; )cos( IbmbB tIi ; (1) )cos( IcmcC tIi , where =2 fs is the angular frequency; Ima, Imb, Imc are the amplitudes of currents determined by their abovementioned RMS. The initial phase of currents Ia, Ib, Ic determined initially by summing the vectors in Fig. 2 and therefore rigidly connected with each other. They were then turned on all selected by numerical experiments a certain angle so that when = 0 resulting MMF of the stator winding Fs is directed along the longitudinal rotor axis d which is shown in Fig. 1. In such a way the necessary initial phase are received: Ia = 9.15\u00b0; Ib = \u2013117.56\u00b0; Ic = \u2013237.88\u00b0. In (1) additional rotation angle for all currents, respectively, rotates vector Fs of MMF at the same angle with the proviso that when at predetermined stator currents and excitation current to provide the required output 18 ISSN 2074-272X" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000880_242_1_02-Amoskov.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000880_242_1_02-Amoskov.pdf-Figure14-1.png", + "caption": "Figure 14. Schematics of EDS maglev car", + "texts": [ + " 1) reaches its half-maximum at the speed of about 11 m/s. Based on the obtained results [7\u201310], the scaling was made to a realistic flat freight car propelled by a linear induction motor. The initial parameters were taken as follows:\u25cf operation speed 200 km/h;\u25cf load condition 50 tons;\u25cf air resistance coefficient C = 0.6;\u25cf acceleration/slowdown 0.1 m/s2;\u25cf upward/downward grade 70 or 10% ;\u25cf number of bogies 5;\u25cf every bogie is driven with a linear motor module;\u25cf the track and levitation magnet arrangement is shown in Fig. 14;\u25cf EDS configurations under study: \u2014 Option 1. PMs configured in Halbach arrays, \u2014 Option 2. SC racetrack coils (1500\u00d7500 mm), \u2014 Option 3. SC racetrack coils topologically equivalent to the Halbach array. 294 \u0412\u0435\u0441\u0442\u043d\u0438\u043a \u0421\u041f\u0431\u0413\u0423. \u041f\u0440\u0438\u043a\u043b\u0430\u0434\u043d\u0430\u044f \u043c\u0430\u0442\u0435\u043c\u0430\u0442\u0438\u043a\u0430. \u0418\u043d\u0444\u043e\u0440\u043c\u0430\u0442\u0438\u043a\u0430... 2018. \u0422. 14. \u0412\u044b\u043f. 4 The EDS arrangement presented in Fig. 14 corresponds to schematics described in [27]. The guideway tilt of 60\u25cb with respect to the horizontal plane is taken so that to ensure lateral stability. 1 \u2014 guideway; 2 \u2014 track; 3 \u2014 levitation magnet; 4 \u2014 bogie. Dimensions are given in millimeters. A motion scenario from the standstill to the operating speed has been simulated for 3 indicated EDS options. The results include spatial and temporal variations of the magnetic flux, eddy current, Lorentz force, Joule heat and other parameters. Then, evolutions of the integral loads have been calculated for the EDS components", + " Comparative efficiency of EDS maglev with different track concepts (levitated weight 500 kN, propulsion speed 200 km/h) Continuous1 Discrete2 Track concept Conducting band Rutherfordtype cable Conducting band Infinitely thin loop Multiturn coil with finite dimensions Single-turn coil with finite dimensions Levitation magnet type PM PM SC SC SC SC Power consumed by air resistance, MW grade up to 30%}, acceleration up to 0.1 m/s2 1.7 1.7 1.7 1.7 1.7 1.7 Power consumed by electrodynamic drag, MW 8.3 2.6 5 0.6 2.8 4 Levitation efficiency 3.4 20 5.6 46 10 7 Auxiliary power, kW 0 0 50 50 50 50 Initial levitation speed, m/s 3 3 15 \u223c30 \u223c25 \u223c25 1 Tracks and magnets are tilted by 60\u25cb with respect to the horizontal plane (see Fig. 14) to provide lateral stability. 2 Tracks and magnets are tilted by 90\u25cb with respect to the horizontal plane (see Fig. 3) [2]. 296 \u0412\u0435\u0441\u0442\u043d\u0438\u043a \u0421\u041f\u0431\u0413\u0423. \u041f\u0440\u0438\u043a\u043b\u0430\u0434\u043d\u0430\u044f \u043c\u0430\u0442\u0435\u043c\u0430\u0442\u0438\u043a\u0430. \u0418\u043d\u0444\u043e\u0440\u043c\u0430\u0442\u0438\u043a\u0430... 2018. \u0422. 14. \u0412\u044b\u043f. 4 Conclusions. Comparative calculations have revealed that simplified models, particularly, those neglecting the real coil configuration, underestimate the power consumption of EDS maglev systems. At a low speed range up to 300\u2013400 km/h, while the power consumed by the electrodynamic drag remains higher than the one of air dynamic drag, that EDS systems prove to be inefficient" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004963_ng-viscosity-div.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004963_ng-viscosity-div.pdf-Figure12-1.png", + "caption": "Figure 12. Schematic explaining the absence of steady orientations at \u03b1 = 0 and \u03b1 = \u03c0/2 for (a) prolate and (b) oblate spheroids when the external force and viscosity gradient are perpendicular. This schematic is shown in the particle\u2019s frame of reference.", + "texts": [ + " First of all, we note that the results from the symmetry-based theory (solid curve, (5.3)) are virtually indistinguishable from the full numerical simulation (dashed curve), indicating the validity of our theory. Secondly, for all starting conditions, we observe the particle converges to one steady orientation. However, this steady orientation is not \u03b1 = 0, \u03b1 = \u03c0 or \u03b1 = \u03c0/2, which was the case when the force and viscosity gradient vectors were co-linear. We elucidate this point more clearly in figure 12. Here, we observe that neither \u03b1 = 0, \u03c0/2 nor \u03c0 are steady configurations because the counterclockwise torque is different than the clockwise torque at these specific angles. Some general trends are described below for prolate and oblate particles. 983 A28-19 ht tp s: // do i.o rg /1 0. 10 17 /jf m .2 02 4. 13 6 Pu bl is he d on lin e by C am br id ge U ni ve rs ity P re ss (i) For prolate spheroids, we observe from figure 12 that the difference between the counterclockwise and clockwise torques is smaller for \u03b1 = 0 and \u03c0 (where the long axis is along the force direction) compared with \u03b1 = \u03c0/2 (where the long axis is along the viscosity gradient direction). Therefore, the steady orientation is closer to \u03b1 = 0 and \u03c0 than to \u03b1 = \u03c0/2, and continues to approach \u03b1 = 0 or \u03c0 as the aspect ratio increases. In the limiting case of needle-like particles where AR \u2192 \u221e, the steady orientation reaches \u03b1 = n\u03c0. Between the two configurations of \u03b1 = 0 + \u0394 and \u03b1 = \u03c0 \u2212 \u0394 (where \u0394 is a positive constant depending on aspect ratio), \u03b1 = \u03c0 \u2212 \u0394 is the stable configuration, while \u03b1 = 0 + \u0394 is unstable (see figure 11a)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001133_f_version_1569401418-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001133_f_version_1569401418-Figure9-1.png", + "caption": "Figure 9. The relation between suspension frame and track constraint coordinate system.", + "texts": [ + " The reference coordinate systems J0 and T0 of the kinematics equation of the suspension frame are set at the first joint of the anti-rolling beam group (the connection between the left module and the anti-rolling beam) and the last joint (the connection between the right module and the anti-rolling beam). They do not coincide with the track coordinate system TL(i) and TR(i). Therefore, it is necessary to design the transformation matrix so as to transform the train\u2013track constraint relation to the reference system of the inverse kinematics solution. The spatial relationship between the suspension module and the electromagnet corresponding to a suspension frame is shown in Figure 9. It can be seen in Figure 9 that the postures of the reference coordinate system and the terminal coordinate system of the suspension frame are the same as that of the orbit coordinate system, but the origin does not coincide. h0 : The distance from the origin of the track coordinate system TL(i) TR(i) on the center line of the electromagnet polar surface to the cross section of the anti-rolling beam group (x-direction of the reference system); h1 : The vertical distance from the pole surface of the electromagnet to the upper hinge (z-direction of the reference system); l0 : The distance from the polar axis of the electromagnet to the anti-roll beam and the module hinge (y-axis of the reference system); The definitions of l1, l2 and l3 are given in Section 2 of the kinematic modeling of the suspension frame. The parameters of the transition curve and the Maglev train are shown in Table 1. As can be seen from Figure 9, for the right module of the suspension frame, the transformation matrix from the terminal coordinate system T0 of the suspension frame to the track coordinate system TR(i) is as follows: TR(i) T0(i) J = 1 0 0 (\u22121)ih0 0 1 0 l0 0 0 1 h1 \u2212 l2 0 0 0 1 . (52) In Equation (52), the \u2212l2 is the height difference between the terminal coordinate system and the reference coordinate system. On the left module, the transformation matrix from the reference coordinate system J0 to the orbit coordinate system TL(i) is as follows: TL(i) J0(i) J = 1 0 0 (\u22121)ih0 0 1 0 \u2212l0 0 0 1 h1 0 0 0 1 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004576__AME_2009_132087.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004576__AME_2009_132087.pdf-Figure8-1.png", + "caption": "Fig. 8. Rope system", + "texts": [ + " ENERGY OF LOAD AND DRUM OF THE HOISTING WINCH The load is modelled as a particle. The vector of its generalized coordinates is expressed in the following form qL = [ xL,1 xL,2 xL,3 ]T . The angle of rotation of the drum of the hoisting winch is denoted as \u03d5H . Kinetic energy of the load and the drum can then be calculated as: TR = 1 2 mL r\u03072 L + 1 2 IH \u03d5\u03072 H , (23) where IH is the moment of inertia mass of the drum, r\u03072 L = x\u03072 L,1 + x\u03072 L,2 + x\u03072 L,3. Potential energy of the load is determined as: V L g = mL g xL,3. (24) The rope system of the A-frame is presented in Fig. 8. It is assumed that radii of pulleys are small compared to the dimensions of the whole mechanism, and also that the rope passes through points S and H \u2013 centres of the pulley and the drum, respectively. Because the radii of pulleys are small and the length of the rope may be hundreds of meters, this simplification can be seen as admissible. Potential energy of elastic deformation of the rope and its dissipation can be expressed in the following forms: VR = 1 2 cR\u03b4R\u22062 R, (25) DR = 1 2 dR\u03b4R\u2206\u03072 R, (26) where \u03b4R = 0 if \u2206R \u2264 0 1 if \u2206R > 0 , \u2206R = |LS| + |SH | \u2212 l0 \u2212 \u03d5H dH 2 , |LS| = |rL \u2212 rS | , |SH | = |rS \u2212 rH | , cR = ERFR l \u2013 stiffness coefficient of the rope, dR \u2013 damping coefficient of the rope, l0, l \u2013 initial and current length of the rope, respectively, ER \u2013 Young\u2019s modulus of the rope material, FR \u2013 cross-section of the rope, dH \u2013 diameter of the drum" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004878_1_1_article-p394.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004878_1_1_article-p394.pdf-Figure4-1.png", + "caption": "Fig. 4. Velocity distribution (left side, in m/s) and pathlines (right side) for the part with second spool.", + "texts": [ + " CFD simulation was performed in ANSYS CFX code for fixed component position for steady state conditions and for the following assumptions: (a) fluid (hydraulic oil) is homogeneous and has a constant properties: density 880 [kg/m3], viscosity \u03c5 =40 [mm2/s]; (b) flow is turbulent: k-\u03d6 turbulence model was used; (c) model is in thermodynamics equilibrium, heat transfer is not included; (d) half of the geometrical model was used in simulations. An exemplary results of fluid flow inside flow control valve are shown in Fig.3 and Fig.4. Numerical simulations of flow inside the valve allowed also to obtain pressure drop at the first spool (controlled by solenoid) which is presented in Fig.5. Spool position is normalized value, where 0 is initial position (valve is closed) while 1 is fully open valve. Numerical simulations of flow inside valves bring new quality in modelling such components. Information which are obtained during CFD simulation allows to investigate phenomena which appears during fluid flow which might be used during design process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000771_1081-023-09833-9.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000771_1081-023-09833-9.pdf-Figure8-1.png", + "caption": "Fig. 8 Design variables related to the Y-topology of the spokes", + "texts": [ + " 6c), asymmetric Y-shape (Fig. 6d) and double straight-shape (Fig. 6e), each one described by a dedicated set of parameters. As regards the straight spokes, the only design variable is the spoke rotation angle (angle \u03b1 in Fig. 7), namely the angle between the spoke and an axis passing through the hub center and the spoke root (see Fig. 7). Concerning the spokes with Y-topology, two additional angles \u03b2 and \u03b3 determine the location of the spoke-rim connection points and the position of the bifurcation point (see Fig. 8). Likewise, for the X-topology, the angles \u03b2 and \u03b3 define the position of the connection points with the hub and the rim respectively (see Fig. 9). The asymmetric Y spoke has a structure divided into two parts. The main part is parameterized as a straight spoke while the two additional design variables k and \u03b4 determine the location of the bifurcation point and the orientation of the secondary member, as depicted in Fig. 10. For the double straight-topology, the same design variables of the X-topology are used to define the four connection points of the spoke with the hub and rim" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002293_robt.2022.870018_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002293_robt.2022.870018_pdf-Figure2-1.png", + "caption": "FIGURE 2 | Swing-phase model and damper force and angle resolution.", + "texts": [ + " Toe-off and foot strike are the two different occurrences that can distinguish the periodic pattern. One gait cycle is classified into two main phases/ periods: stance and swing (Figure 1, right leg shaded). Stance is the time between when the foot first meets the ground and when it rises from it, and it accounts for 62% of the gait cycle. The rest 38% of the gait cycle is made up of the swing period when the foot leaves the ground and swings in the air (Nandy et al., 2012). The dynamic model of the swing-phase leg model with the prosthetic knee, depicted in Figure 2, is developed based on the following assumptions: \u2022 The ankle is considered rigid and fixed on the shank, and the shank and thigh are assumed to be connected by pin joints. \u2022 The thigh is allowed to have vertical and horizontal movement in two dimensions. \u2022 The swing motion of the two-link rigid body chain is taken as a two-degree-of-freedom double pendulum. The resulting swing-phase representation of the knee by applying Lagrangian formulation will be T M(\u03b8)\u20ac\u03b8 + V(\u03b8, _\u03b8) + G(\u03b8). (1) From this relation, the inertia, Coriolis and centrifugal, and gravitational matrices are as follows: M(\u03b8) ((m1a 2 1 + I1 +m2l 2 1) \u2212(l1a2m2C12) \u2212l1a2m2C12 (m2a 2 2 + I2) ), V(\u03b8, _\u03b8) \u239b\u239d l1a2m2S12 _\u03b8 2 2 l1a2m2S12 _\u03b8 2 1 \u239e\u23a0, G(\u03b8) \u239b\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239d (a1m1 + l1m2)(gS1 + \u20acxH C1 + \u20acyH S1) m2a2(gS2 \u2212 \u20acxHC2 + \u20acyHS2) \u239e\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u23a0 , (2) where m1, I1, m2, and I2 are the masses and moments of inertia of the thigh and shank, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000508_6514899_10356080.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000508_6514899_10356080.pdf-Figure1-1.png", + "caption": "FIGURE 1. Lattice core used for analysis (a) Diamond (b) Octet (c) Star", + "texts": [ + " In section III, we fabricate six structures using a 3-D printer and measure them using the free-space measurement method. In section IV, we compare our results with those from other research studies and discuss our findings. Finally, in section V, we conclude and summarize our study\u2019s findings. II. LATTICE CORE ANALYSIS A. LATTICE CORE The lattice core can be configured in a variety of shapes, including diamond, octet-truss (referred to as octet), and star structures, each characterized by branches with a diameter of w and a periodicity of p. This configuration is shown in Fig. 1. Each shape has unique mechanical properties, and these properties can be optimized by carefully selecting and designing the lattice core. A study by [19] investigated the mechanical properties of 10 different lattice designs. This studies have demonstrated that the star configuration possesses the highest bending load capacity. In contrast, diamond lattices perform exceptionally under compressive and bending loads. However, they are prone to brittleness and lack effective energy absorption, mainly due to limited displacement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003781_f_version_1680255727-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003781_f_version_1680255727-Figure5-1.png", + "caption": "Figure 5. Structure parameters of seedling picking mechanism.", + "texts": [ + " In the ascending phase of the cam and the connecting rod, the sun gear rotated clockwise and increased the clockwise rotation speed of the planetary gear via meshing. In contrast, in the descending phase of the cam, the sun gear rotated counterclockwise and decreased the clockwise rotation speed of the planetary gear via meshing. Thus, the design of the cam profile can be used to achieve the seedling picking trajectory. To facilitate further optimization of the seedling picking mechanism, the displacement equations of each component of the seedling picking mechanism must be established, with the center of the sun gear in Figure 5 as the coordinate origin, and the horizontal and vertical directions as the X- and Y-axes, respectively. Moreover, in the analysis of its motion model, it was assumed that each component was a rigid structure and no elastic deformation occurred. Agriculture 2023, 13, 810 5 of 18 The motor drove the input shaft to rotate counterclockwise, whereas the cam and the casing that were fixed to the input shaft rotated in a counterclockwise direction. The sun gear was oscillated by the influence of the cam-linkage, and the engagement drive of the planetary gear system controlled the variable speed rotation of the seedling picking arm fixed to the planetary shaft to achieve the seedling picking trajectory to satisfy the design requirements", + " In the ascending phase of the cam and the connecting rod, the sun gear rotated clockwise and increased the clockwise rotation speed of the planetary gear via meshing. In contrast, in the descending phase of the cam, the sun gear rotated counterclockwise and decreased the clockwise rotation speed of the planetary gear via meshing. Thus, the design of the cam profile can be used to achieve the seedling picking trajectory. To facilitate further optimization of the seedling picking mechanism, the displacement equations of each component of the seedling picking mechanism must be established, with the center of the sun gear in Figure 5 as the coordinate origin, and the horizontal and vertical directions as the X- and Y-axes, respectively. Moreover, in the analysis of its motion model, it was assumed that each component was a rigid structure and no elastic deformation occurred. Agriculture 2023, 13, x FOR PEER REVIEW 6 of 18 Figure 5. Structure parameters of seedling picking mechanism. In Figure 5, point B is the output shaft axis, C\u2013D is the seedling picking arm, and point O is the input shaft axis. E, F, G, H are the end points of connecting rod FG and connecting rod EH respectively. Where point H is also the axis of the roller. 2.1. Kinematic Equations of the Seedling Picking Mechanism When the seedling picking mechanism begins operation, the planetary frame rotates counterclockwise with an angular velocity of \u03c9. The displacement equation of the planetary gear axis point B is expressed as follows: ( ) ( ) ( ) ( ) 1 2 3 2 1 2 3 2 2 cos 2 sin B B X R R R t Y R R R t \u03c9 \u03b1 \u03c9 \u03b1 = + + + = + + + ", + " Consequently, the planetary gear and planetary frame transmission ratios can be derived as follows: 3 2 3 3 31 1 1 2 1 H H H z z z i z z z \u03c9 \u03c9 \u03c9 \u03c9 \u2212 = = = \u2212 , (2) 3 31 1 31 1 /H Hi i R R= \u2212 = \u2212 . (3) where i3H is the ratio of the planetary gear to planetary carrier speed; z1 is the number of teeth of the sun gear; z2 is the number of teeth of the intermediate gear; z3 is the number of planetary gear teeth; and iH 31 is the transmission ratio of the conversion gear system. To realize the cycle of picking action, the position of the seedling picking arm should be the same as the initial position after one rotation of the planetary frame; thus, the value In Figure 5, point B is the output shaft axis, C\u2013D is the seedling picking arm, and point O is the input shaft axis. E, F, G, H are the end points of connecting rod FG and connecting rod EH respectively. Where point H is also the axis of the roller. 2.1. Kinematic Equations of the Seedling Picking Mechanism When the seedling picking mechanism begins operation, the planetary frame rotates counterclockwis w th an angular velocity of\u03c9. The displacement equation o the plane ary gear axis point B is expressed as follows:{ XB = (R1 + 2R2 + R3) cos(\u03c9t + \u03b12) YB = (R1 + 2R2 3) sin( t + \u03b12) " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003980_n6_IJWMT-V5-N6-5.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003980_n6_IJWMT-V5-N6-5.pdf-Figure1-1.png", + "caption": "Fig. 1 shows the geometry of the proposed antenna. This antenna is built on a FR-4 substrate with a relative permittivity of \u03b5r = 4:4 and a loss tangent of 0.02. The transverse dimension of this antenna is 48\u00d746mm 2 . In designing, the patch antenna is used to cover the UWB range, which is the highest frequency band of the multiband antenna. Initially Bluetooth (2.4-2.48 GHz) and UWB (3.1-10.6 GHz) antenna is obtained by partial grounding technique (DGS) and a Dual notched band characteristic is performed on the UWB antenna without disturbing the Bluetooth and UWB antenna. After that for GSM band (1.710-1.885 GHz), the Quarter wavelength stub of centre frequency 1.797 GHz is added to both side of the radiation patch of the antenna.", + "texts": [ + " Due to interference of the dual band WIMAX (3.3-3.7 GHz) and WLAN (5.15-5.825GHz) is notched in the UWB. The length of slot is half of wavelength at centre frequency of the 3.3 -3.7 GHz. The gap between the radiating patch and the ground plane affects impedance bandwidth because it acts as a matching network. The length of the U-shaped slot can be calculated by, (1) The length of lower and upper slot is Llower= 26.1mm Lupper =19.6mm for WIMAX and WLAN respectively. The U- shaped slot shown in fig 1 which is performing band notch function for WIMAX and WLAN. The effect of the width of Lower slot and upper slot shown in fig.6 & fig.7 correspondingly. In addition, at the desired frequency, only are the corresponding slots active while the others are inactive, approving the independence of the frequency bands. The natural elucidation is that the slots are not the major contributor of antenna performance [5]. The current distribution of the particular rejected band in proposed dual band notched antenna shown in fig.8. Fig.6. Shows Return Loss of Proposed Antenna with Slot of Centre Frequency 3.5 & 5.5 GHz. Finally, half of wavelength stub of centre frequency 1.797 GHz for GSM band to boost the particular frequency band. The stub dimensions are given in table no.1. In proposed band notch antenna the performance of the GSM operation of by optimising the length of stub shown in fig.1. The Simulated return loss of the proposed antenna shown in fig.7. In Fig. 9, it is can be seen that the proposed antenna has an impedance bandwidth of 1.5 GHz to 10.6 GHz for S11 \u226410 dB, except two frequency stop-bands of 3.3-3.7 GHz for Wi-MAX and 5.2-5.825 GHz for WLAN. The proposed GSM integrated, Bluetooth, dual band notched UWB antenna is simulated and shown in fig. Omnidirectional characteristics and radiation bandwidth can be improved if the ground plane length is approximately the same size as that of the radiating structure width [11] and by using a thin substrate or a substrate with low dielectric constant [12]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001023_article-file_2203208-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001023_article-file_2203208-Figure6-1.png", + "caption": "Fig. 6: Nema 17 Motor", + "texts": [], + "surrounding_texts": [ + "The 304 stainless steel plate used for the main lines and chassis of our machine was processed and assembled in accordance with our machine (Figure 2). The features such as being lightweight, giving results that we want in terms of durability, and being suitable for food use were among the main reasons for using this steel plate in our machine. In addition, its low cost stood out as a separate positive factor for us. The fact that the main frame of our machine is durable makes it possible not to be easily affected negatively as a result of any impact that the machine will face during the operation process." + ] + }, + { + "image_filename": "designv8_17_0000439_sd_157_22004_.5m.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000439_sd_157_22004_.5m.pdf-Figure1-1.png", + "caption": "Fig. 1. The USV\u2019s configuration and dynamics", + "texts": [ + " Section 2 specifies the considered USV\u2019s configuration and the governing dynamic and kinematics equations. In Section 3, the guidance law for yaw angle and surge velocity is designed. Section 4 specifies the controller. In Section 5, the simulation results illustrating the proposed controller\u2018s effectiveness are provided. The conclusions are drawn in Section 6. The USV configuration considered in this paper is a twin-hull vessel with two independent motors or thruster attached to each hull (shown in Fig.1). The USV\u2018s dynamic model used in this paper is described by the following linear maneuvering equations [3]: (\ud835\udc74\ud835\udc74\ud835\udc79\ud835\udc79\ud835\udc79\ud835\udc79 + \ud835\udc74\ud835\udc74\ud835\udc68\ud835\udc68)?\u0307?\ud835\udf42 + (\ud835\udc6a\ud835\udc6a\ud835\udc79\ud835\udc79\ud835\udc79\ud835\udc79 + \ud835\udc6a\ud835\udc6a\ud835\udc68\ud835\udc68 + \ud835\udc6b\ud835\udc6b)\ud835\udf42\ud835\udf42 = \ud835\udf49\ud835\udf49 (1) where \ud835\udf42\ud835\udf42 = [\ud835\udc62\ud835\udc62 \ud835\udc63\ud835\udc63 \ud835\udc5f\ud835\udc5f]\ud835\udc47\ud835\udc47 , \ud835\udc62\ud835\udc62, \ud835\udc63\ud835\udc63, \ud835\udc5f\ud835\udc5f denote the surge velocity, sway velocity, and yaw velocity, respectively, \ud835\udf49\ud835\udf49 = [\ud835\udc39\ud835\udc39\ud835\udc65\ud835\udc65 \ud835\udc39\ud835\udc39\ud835\udc66\ud835\udc66 \ud835\udc41\ud835\udc41] denotes the forces and moments applied on the USV, \ud835\udc74\ud835\udc74\ud835\udc79\ud835\udc79\ud835\udc79\ud835\udc79 is the rigid- body mass matrix, \ud835\udc74\ud835\udc74\ud835\udc68\ud835\udc68 is the added mass matrix. \ud835\udc6a\ud835\udc6a\ud835\udc79\ud835\udc79\ud835\udc79\ud835\udc79 is the rigid-body Coriolis and centripetal matrix, \ud835\udc6a\ud835\udc6a\ud835\udc68\ud835\udc68 is the linear hydrodynamic Coriolis and centripetal matrix" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004557_9312710_09416651.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004557_9312710_09416651.pdf-Figure13-1.png", + "caption": "FIGURE 13. Flux density distribution of proposed model.", + "texts": [ + "67 % reduction in cogging torque with almost the same back EMF. The output torque of the basic model is 188.76 Nm while that of the proposed model is 181.55 Nm as shown in Fig. 11. The output torque of the basic model is slightly greater than the proposed model\u2019s output torque but with a high percentage of torque ripples (8.82%). The torque ripples in the proposedmodel are 4.22%, which is the primary objective of this paper, to reduce torque ripples. The basic model has slightly greater power as compared to the proposed model as shown in Fig. 12. Fig. 13 shows the flux density distribution of the proposed model with rated 4.4 A. The core of the proposed model is a maximum of 1.75 T to elude saturation factor. Air gap flux densities of the basic and proposedmodel are almost the same as shown in Fig. 14. IV. MAGNET SHAPE OPTIMIZATION The flow chart of the optimization procedure is shown in Fig. 16. First, design variables and objective function are nominated. In the next phase, sampling is done to design the experiments by using the Latin hyper cube (LHC) sampling technique" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-FigureC.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-FigureC.1-1.png", + "caption": "Figure C.1: CAD model and CFD mesh in undeformed state", + "texts": [ + " 274 The first step in a CAD-based shape optimization is to create a baseline geometry in ESP. The baseline geometry should be consistent with the requirements of the analysis method(s) to be used. For example, geometry to be used with CFD should generally be a \u201cwatertight\u201d enclosed surface. Finite element geometry should include surfaces coincident with the intended location of the idealized elements (e.g. ribs, spars, skins). All points in the baseline computational model must be coincident with a surface in the CAD model. A notional CAD surface is pictured in Figure C.1a. A CFD mesh can be generated using the CAD surface with an external program such as Pointwise or ICEM CFD. Alternatively, if the geometry of an existing CFD mesh is known, a new CAD surface can be created that matches the existing mesh. Figure C.1b illustrates a CFD mesh corresponding to the notional CAD object. The CAD object is segmented into one or more B-spline surfaces. Each spline surface has a two-dimensional parameterization (denoted by the variables u and v). Engineering Sketch Pad typically defines u and v on a range of 0 to 1, but circular or spherical shapes may vary from 0 to 2\u03c0 or multiples thereof. Figure C.2 shows a schematic illustration of the u, v parameterization on a B-spline surface. Each point on the surface can be uniquely defined in u, v coordinates" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002375__2016_0_2016_88__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002375__2016_0_2016_88__pdf-Figure4-1.png", + "caption": "Fig. 4: Schematic drawing of the parallel-structured flexible slave arm.", + "texts": [ + " Then, by considering the mathematical model of the DC motor and the electrical time constant is sufficiently small and applying the inverse Laplace transform, the control torque, \u03c4(t), is derived as follows: \u03c4(t) = k\u03c4KP R {\u03b8com(t)\u2212 \u03b8(t)} + k\u03c4KD R { \u03b8\u0307com(t)\u2212 \u03b8\u0307(t) } \u2212 kek\u03c4 R \u03b8\u0307(t). (4) where k\u03c4 and ke are the torque and the back electromotive force constants, respectively. R is the internal resistance of the coil in the DC motor. This torque controls the flexible slave arm. In this study, the parallel-structured single-link flexible arm is considered as the slave arm (see Fig. 4). As seen in this figure, the parallel-structured single-link flexible arm consists of a pair of uniform Euler-Bernoulli beams. Both ends of each beam clamp a hub unit and a tip-mass. Because of the highly complex nonlinear differential equations, the derivation of the mathematical model of the parallel-structured single-link flexible arm is very difficult. However, because both beams are uniform Euler-Bernoulli beams and both ends are clumped by the unit hub and tip-mass, the displacements of both beams can be considered equal" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001925__download_6201_3610_-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001925__download_6201_3610_-Figure1-1.png", + "caption": "Fig. 1 - (a) side view; (b) reference; (c) UWB planar antenna with a single slit; (d) UWB planar antenna with dual slits", + "texts": [ + " Structure and the performance of the UWB planar antennas are explained in part 2 and 3, respectively. The UWB planar antenna with band rejection for 5 to 6GHz is described in [17-18]. The designed antenna is extended to generate the band rejection for the frequency bandwidth from 3.3 to 3.7GHz, accordingly. The UWB planar antenna performances are described and summarized results are concluded in part 4, accordingly. The reference is known as the UWB planar antenna with an elliptical element as in Fig. 1(a-b) and the dimensions are given in Table 1, respectively. The base used FR4, the permittivity, r and electric conductivity tangent delta, are given as 4.4 and 0.019. Major and minor radiuses are recognized as L1 and L2, respectively. The substrate and conductor planes thickness are identified as hs and hc, respectively. Width and length of the ground element are given as Lg and Wg. Feed F is positioned in the radiator. Ground plane used half ground plane for simplicity and compact structure design. The impedance matching is controlled by the eccentricity e as Eq. 1. e =\u221a1 \u2212 (\ud835\udc3f2) 2 (\ud835\udc3f1) 2 (1) UWB planar antenna with a single band rejection that is for 5 to 6GHz is demonstrated as Fig. 1(c), while for dual band rejection for the frequency bandwidths 3.3 to 3.7 and 5 to 6GHz is illustrated in Fig. 1(d), accordingly. Single slit is known as S1 and is scraped in the +x axis of the radiator and the second slit S2 is etched in the ground plane in the \u2013x axis. Slit configurations and dimensions are illustrated Fig. 2 and Table 2, respectively. Slit S1 is realized to cause band rejection for the frequency bandwidth between 5 and 6GHz, while slit S2 is for rejecting the frequency bandwidth between 3.3 and 3.7GHz. Slit S2 is longer and more slanted compared to slit S1. Width w of slit S2 is bigger than slit S1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003156_1_files_28155276.pdf-Figure4.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003156_1_files_28155276.pdf-Figure4.3-1.png", + "caption": "Figure 4.3: Calibration fixture and setup", + "texts": [ + " The Lauda Proline RP 1845 constant temperature baths in the Advanced Heat Transfer Laboratory were used to provide a stable environment for calibration, and the temperature in them was verified with an Omega DP97 High Accuracy Digital Thermometer accurate to \u00b10.04 \u25e6C and a recently certified liquid-in-glass thermometer. A fixture was constructed to hold a length of wire submerged while the various thermometers were held in place with several clamps mounted to two retort stands. The wire and contact thermometers were adjusted such that the wire just breaks the surface of the water and makes contact with the thermometer just outside the surface. A representation of the calibration setup be seen in Figure 4.3. For the calibration procedure, all of the thermocouples were adjusted to match the correct temperature reading at 25 \u25e6C based on the DP97 thermometer and then the temperature in the water bath was incremented by 5 \u25e6C up to 60 \u25e6C and back down to 25 \u25e6C, with 20 minutes given at each temperature to ensure a stable reading. The data for all of the thermocouples was recorded and plotted. This data was linear in appearance, and Matlab\u2019s Polynomial Fitting Tool was used, with a 1st degree polynomial specified" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003036_cmtmte2018_04028.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003036_cmtmte2018_04028.pdf-Figure4-1.png", + "caption": "Fig. 4. Driven shaft calculation models in Ansys R18 software system: a) deformations b) equivalent stresses", + "texts": [ + " When the required input parameters and mass-center characteristics have been introduced in the dynamic model, it is possible, by changing free parameters, to obtain set speeds, accelerations and other parameters of the device parts. An example in Fig. 3 shows the relationship between the driving shaft angular speed and operation time of different eccentric weights. After selection of optimal characteristics of the device under design, based on the results obtained from the dynamic model, for example, housing acceleration, spring force in Ansys R18 software system, we determine design peculiarities and operability of vibrator prototype parts. An example in Fig. 4 demonstrates results of strength calculations for different vibrator eccentric weight design solutions. Use of the suggested computer-aided design and simulation methods enables reducing labor intensity of designing resonance-free vibration systems with variation of input parameters and design solutions, reducing the design calculation error, optimizing engineer\u2019s work, significantly simplifying the process of designing new systems and modernizing existing structures with account for calculation results obtained during simulation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001751_ticle_download_19_31-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001751_ticle_download_19_31-Figure6-1.png", + "caption": "Figure 6 Discrete model of Single block on rough ground.", + "texts": [ + " The remaining properties like mass, stiffness and density were kept same as the 2D model. Continuum Assembly: Assembly was created by placing part1 above the Part2. Cube stone block was placed at the center of rectangular stone blocks. Spring was connected between RF1 and RF2. The assembly diagram is given below: Friction plays an important role in the dissipation of the energy. Following conclusions were derived from the analysis. The single degree of freedom system was analyzed by using discrete modeling (Figure 6). The free vibration response to initial displacement is shown in Figure 7 as a plot of displacement versus time. From graph it can be seen that in the beginning when the initial displacement given to the Node 2, it starts oscillating back and forth at its position. The time duration of graph is 2 sec. The RF1 starts vibrating at 1 sec rapidly and diminish completely at 2 sec. As friction is present between RF2 and Slide plane, it is creating a damping mechanism by which the energy in the system is dissipating with respect of time" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure12.20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure12.20-1.png", + "caption": "Fig. 12.20. Changes of the structure of vibration during propagation, path No. III, axis \u2013 lateral", + "texts": [], + "surrounding_texts": [ + "VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 137" + ] + }, + { + "image_filename": "designv8_17_0002044_8948470_09078103.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002044_8948470_09078103.pdf-Figure2-1.png", + "caption": "FIGURE 2. Working principle diagram of axial-radial combined permanent magnet eddy current coupler working principle diagram.(a) Principle of axial. (b) Principle of radial.", + "texts": [ + " The conductor rotor rotates together with the drive motor and cuts the magnetic line produced by the permanent VOLUME 8, 2020 This work is licensed under a Creative Commons Attribution 4.0 License. For more information, see https://creativecommons.org/licenses/by/4.0/ 78367 magnet rotor [12]. An alternating eddy current field is generated in the conductor rotor and excites the induced magnetic field according to Faraday\u2019s law [13]. The torque is calculated by superposing the inducedmagnetic field with the excitationmagnetic field. It is transmitted from the power side to the load side [14], [15]. As shown in Fig. 2, the effective contact area between the magnetic field and the rotor can be adjusted by changing the thickness of the air gap to obtain a controllable and adjustable load rotation speed [16]. To study the performance of axial-radial combined permanent magnet eddy current couplers, two different methodologies are used: numerical methods and analytical methods [17]. The finite element method is a representative numerical method that can comprehensively consider the nonlinearity and magnetic flux leakage of the permanent magnetmaterials" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004245_SIJINT-2015-088__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004245_SIJINT-2015-088__pdf-Figure5-1.png", + "caption": "Fig. 5. FEM simulator configuration.", + "texts": [ + " In contrast, the proposed delivery-side curvature model is constructed based on the fact that elongation difference is the cause of a curved strip. \u0394v2 is represented as \u0394v1 and \u0394\u03c8 (Eq. (23)). Because \u0394v1 is related to 1/\u03c11 and is already included in \u0394v2, the inconsistency that was shown in Section 2 is not generated. The FEM is used to build a simulator for the hot roll- ing process to verify the accuracy of the proposed model of delivery-side curvature. To simplify the process and to reduce simulation time, the FEM simulator was composed only of roll, strip, and pusher using mirror symmetry on the lower side of the bar (Fig. 5) with the aid of the commercial Fig. 4. Relation between curvature and velocity difference. \u00a9 2015 ISIJ 1984 FEM software DEFROM 3D. The roll was assumed to be a rigid body, and the strip was assumed to be a rigid plastic body. Consequently, the thickness of the strip was equal to the roll gap. The bar was assumed as AISI 1015 carbon steel, and yield strength of the material was 325 MPa. Shear friction coefficient was set as 0.7.7) More detailed specifications of the simulator are shown in Table 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure5.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure5.3-1.png", + "caption": "Figure 5.3 : E-motor schematic section with specific locations of temperatures.", + "texts": [ + " The command matrix \ud835\udc35\ud835\udc5d can also be split into two matrices as: \ud835\udc35\ud835\udc5d = [\ud835\udc35\ud835\udc3e \ud835\udc35\ud835\udc48]. By defining a vector \ud835\udc49 as: \ud835\udc49 = \ud835\udc35\ud835\udc50\ud835\udc47\ud835\udc52\ud835\udc65\ud835\udc61 + \ud835\udc35\ud835\udc3e\ud835\udc3e, the state space representation takes the following form: { ?\u0307?(\ud835\udc61) = \ud835\udc34\ud835\udc47(\ud835\udc61) + \ud835\udc49(\ud835\udc61) + \ud835\udc35\ud835\udc48\ud835\udc48(\ud835\udc61) \ud835\udc4c(\ud835\udc61) = \ud835\udc36\ud835\udc5c\ud835\udc47(\ud835\udc61) (5.5) (5.6) Where an observation matrix \ud835\udc36\ud835\udc5c (dimension nq,N) allows to select nq temperatures in the whole temperature field \ud835\udc47(\ud835\udc61) and to store them in vector function \ud835\udc4c(\ud835\udc61). In this study, a maximum of nine temperature locations will be used as outputs. These temperatures are depicted in Figure 5.3, and are located in the stator lamination (Ts1, Ts2, and Ts3), in the end-winding (Tw) at the surface of the end-winding (Tsw), on the surface of the stator in the airgap (Ta), in the cavity between the rotor end-cap and the frame (Tc), in the bearings (Tb), and in the magnets (Tm). These locations have been chosen given the heat sources but also considering plausible experimental measurement system positions. The temperature in the static part of the motor could be obtained using thermocouples (Ts1, Ts2, Ts3, Tsw, Ta, Tb, and Tc)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000752_el-04725201_document-Figure1.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000752_el-04725201_document-Figure1.13-1.png", + "caption": "FIGURE 1.13 : Les diff\u00e9rents types de polarisation d\u2019antenne [51].", + "texts": [ + " Les lobes secondaires sont des directions dans lesquelles l\u2019antenne \u00e9met ou capte de l\u2019\u00e9nergie de mani\u00e8re significative en dehors de sa direction principale, tandis que les lobes arri\u00e8re repr\u00e9sentent les directions dans lesquelles l\u2019antenne rayonne ou re\u00e7oit de l\u2019\u00e9nergie dans la direction oppos\u00e9e \u00e0 sa direction principale. La polarisation des antennes est un aspect important de leur conception et de leur fonctionnement dans les syst\u00e8mes de communication sans fil. La polarisation d\u2019une antenne se r\u00e9f\u00e8re \u00e0 l\u2019orientation du champ \u00e9lectrique de l\u2019onde \u00e9lectromagn\u00e9tique \u00e9mise ou re\u00e7ue par l\u2019antenne (voir figure 1.13 [51]). Cette orientation peut \u00eatre lin\u00e9aire ou circulaire, et elle influence la mani\u00e8re dont l\u2019antenne interagit avec les signaux RF. 17 CHAPITRE 1 - L\u2019IMPRESSION 3D ET LA RECTENNA AU SERVICE DE L\u2019IOT Une antenne est dite polaris\u00e9e lin\u00e9airement lorsque le champ \u00e9lectrique de l\u2019onde RF oscille dans une seule direction, parall\u00e8le \u00e0 un plan sp\u00e9cifique. Il existe deux types principaux de polarisation lin\u00e9aire : la polarisation verticale et la polarisation horizontale. La polarisation verticale se produit lorsque le champ \u00e9lectrique est orient\u00e9 verticalement par rapport au sol" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001811_article-file_1690258-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001811_article-file_1690258-Figure7-1.png", + "caption": "Figure 7. Magnetic vector potential distribution (a) Reference motor model (b) 3 slitted motor model (c) 5 slitted motor model.", + "texts": [ + "127 When Figure 5 and Table 2 are examined, it is seen that the torque values obtained from the slitted motor model increase. It was determined that the average torque increased by 12.127 % and the maximum torque by 23.164 %. In addition, for making a healthy verify, a 5 slitted motor model has been solved in transient solver. The magnetic flux density distribution of the reference and different slitted motor models are given in Figure 6 (a), (b) and (c). When the figure is examined, it is seen that the flux density values are approximately the same. In Figure 7, the distribution of magnetic flux lines for reference and different slitted motor models are given. It is seen that flux lines can be directed by using slits. Figure 8 shows the current values obtained from the reference and slitted motor models. A slight increase has been observed in the current values obtained from the 3 slitted motor model. There has no difference between the 3 slitted and 5 slitted motor current waveforms. For this reason, only 3 slitted motor current graph has been given in the text" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure11-1.png", + "caption": "Fig. 11. The characteristic solution of single-stage gear reducer with vertical shafts arrangement (Rossi solution): a) footmounted and b) flange-mounted [17].", + "texts": [ + " Based on the analyzed gearbox housings, it can be noticed that all manufacturers produce the housings from cast iron. Only two of them (Bonfiglioli S, Leroy Somer) use aluminium alloys as material for housings of the low axis heights of reducer [13, 10]. In this way, they achieve a smaller weight of their gear units and thus better technical characteristics of their products. The housing design of single-stage gearbox depends most on the shaft arrangement and mounting method. According to this, there are gearboxes with horizontal (Fig. 6, 7, 8, 9, 10), with vertical (Fig. 11, 12) and with free shaft positions (Fig. 14, 15). Gear reducers with horizontal shaft position are usually manufactured with radial mounting and they present the old type of single-stage units. They passed through extremely intense shape development, from the usual and simple shapes, which insisted only on functionality and reduced material consumption (Fig. 6 and 7) to the very interesting contemporary forms, where great attention has been paid to the appearance of the gearbox (Fig. 9 and 10). If the gear reducer is intended for operation in an environment with high ambient temperature, as well as the higher engine power is used and higher losses can be expected, the housing should be manufactured with ribs (Fig", + " In this way, the gearbox can be mounted with horizontal shaft arrangement, but also in vertical shaft arrangement. The additional opening is added through which the gears are mounted and it is closed by a cover. In order to increase the versatility of this gearbox, an additional flange is created on the front surfaces of the housing (Fig. 10). Single-stage universal gear reducers with vertical shaft arrangement are today more common in practice. They are produced with a different way of connecting: foot-mounted gearbox (Fig. 11a), flange-mounted gearbox (Fig. 11b) and foot and flange-mounted gearbox (Fig. 12). Gear reducers with vertical shaft arrangement have a simpler machining processing, but assembling is a bit complicated. Some manufacturers that produce gear reducers in small series, practice using an universal housing with feet or flange connected by screws. The housings of single-stage gear reducers with free shaft arrangement (but also all other arrangements) are manufactured as rounded (Fig. 13), but also as squared (Fig. 14). When they are assembled with a hollow shaft, they are called shaft-mounted gear units" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003708_19_ms-10-47-2019.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003708_19_ms-10-47-2019.pdf-Figure3-1.png", + "caption": "Figure 3. Development of transmission backlash model of proposed configuration: (a) tension profile and Affected angles of wrap; (b) equivalent model of SISO configuration; (c) equivalent model of proposed configuration.", + "texts": [ + " It is originated from the change in elastic elongation of the cable, which in turn results from the abrupt change in applied load. Determining the cable tension requires the knowledge of the equilibrium tension profile in the contact region, which could be derived by the classical creep theory. This theory assumes that friction is developed due to the relative slip motion between the cable and the pulley, and a Coulomb law describes the cablepulley friction (Kong and Parker, 2005). www.mech-sci.net/10/47/2019/ Mech. Sci., 10, 47\u201356, 2019 Figure 3a shows the tension and affected angles of wrap in SISO configuration when an external load Ml is applied to the output drum. As a result, the cable tension of the free length AH and DE change to Th and Tl from a uniform preload force, Tpre, respectively. The affected slip angles can be divided into three parts on input pulley (radius, ri) \u03b8i_slip1, \u03b8i_nonslip, \u03b8i_slip2, and three parts on output drum (radius, ro) \u03b8o_slip1, \u03b8o_nonslip, \u03b8o_slip2, respectively. Assuming that the output drum rotates in the counterclockwise direction initially. Thus AH and DE become the tight side and the slack side, respectively. The equivalent spring model of SISO configuration is shown in Fig. 3b. The deformations of cable could be divided into two parts due to the variation of the cable tension of free length. The deformation of cable on side1 (\u03b4o_slip1, \u03b4free1, \u03b4i_slip1) is elongated due to the cable tension of the free length AH increases. And the deformation of cable on side2 (\u03b4o_slip2, \u03b4free2, \u03b4i_slip2) is shortened due to the cable tension of the free length DE decreases. As to the proposed configuration, the equivalent model is depicted in Fig. 3c. The two input pulleys bear the external load simultaneously. When the external load applies to the output drum, the deformations of cable on side1 and side4 are both shorten and the deformations of cable on side2 and side3 are both elongated. Based on the torque equilibrium equation, the ca- Mech. Sci., 10, 47\u201356, 2019 www.mech-sci.net/10/47/2019/ ble tension of the free length can be obtained as Ml/2\u2212 (Th\u2212 Tl)ro = 0 (3) The tension in the slip region T (\u03b8 ) and slip angles could be derived as, T (\u03b8 )= Tpree \u00b5\u03b8slip (4) \u03b8o_slip1 = \u03b8i_slip1 = 1 \u00b5 ln ( Th Tpre ) (5) \u03b8o_slip2 = \u03b8i_slip2 = 1 \u00b5 ln ( Tpre Tl ) (6) According to the Hooke\u2019s law (Baser and Konukseven, 2010), the cable deflection in the corresponding slip region and free cable segment, namely \u03b4o_slip1, \u03b4o_slip2, \u03b4i_slip1, \u03b4i_slip2, \u03b4free could be written as, \u03b4o_slip1 = \u03b8o_slip1\u222b 0 ( d\u03b4T \u2212 d\u03b4pre ) (7) = ro AE\u00b5 ( Th\u2212 Tpre\u2212 Tpre ln ( Th/Tpre )) \u03b4o_slip2 = \u03b8o_slip2\u222b 0 ( d\u03b4pre\u2212 d\u03b4T ) (8) =\u2212 ro AE\u00b5 ( Tl\u2212 Tpre\u2212 Tpre ln ( Tl/Tpre )) \u03b4i_slip1 = ri AE\u00b5 ( Th\u2212 Tpre\u2212 Tpre ln ( Th/Tpre )) (9) \u03b4i_slip2 =\u2212 ri AE\u00b5 ( Tl\u2212 Tpre\u2212 Tpre ln ( Tl/Tpre )) (10) \u03b4free1 = 1TAHLfree AE = ( Th\u2212 Tpre ) AE \u221a L2\u2212 ( rg+ ri )2 (11) \u03b4free2 = 1TDELfree AE = ( Tpre\u2212 Tl ) AE \u221a L2\u2212 ( rg+ ri )2 (12) Assuming that the overall length of the cable remains unchanged, the geometric constraint is therefore \u03b4o_slip1+ \u03b4o_slip2+ \u03b4i_slip1+ \u03b4i_slip2+ \u03b4free1+ \u03b4free2 = 0 (13) Substituting the torque equilibrium equation (Eq" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000615_.1117_12.2308193.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000615_.1117_12.2308193.pdf-Figure7-1.png", + "caption": "Fig. 7 Flexure Mount", + "texts": [ + "6 Soft Mount Assembly with gap Force per screw will be, W = T/k.D (6) k= friction factor = 0.2 D = Screw diameter in mm = 3mm W= = 96.21 kg. This offers high margin for vibration loads. Option: 2 Flexure Mount Generally flexure mounts are used to reduce mounting and thermal stresses. [4] Flexures have advantage of flexing more and there by reducing the force on filter. It is a single piece mount having blades for filter interface and three lugs for the filter wheel interface, connected by thin frame, as shown in Fig. 7. Flexure positions are optimized on the frame, for minimum stress on filter. Here, the force P acting on filter will have relationship of, P E I y / h3. E is Modulus of Elasticity, I am Moment of Inertia, y is thickness of the blade and h is the height of the blade. Results of FEA thermal analysis for 100K temperature difference and blade height h of 15mm, are shown in Table 2. Fig. No. 8 and 9 show FEA results for aluminium mount. Table 2 Flexure Mount material Stress in the mount Stress in the filter Aluminium 25" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002466_icle_download_101_66-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002466_icle_download_101_66-Figure6-1.png", + "caption": "Figure 6. Calculation model", + "texts": [], + "surrounding_texts": [ + "- unbalanced mass m of the vibration activator and its center-of-gravity position \u2014 distance L from the body end face \u2014 are determined by the known methods using KOMPAS 3D and other programs; - the centrifugal force resultant is calculated according to the following equation: Q=me\u03c92, where e is the value of crank eccentricity (oscillation amplitude); \u03c9 is the angular velocity of rotation of the drive crank shaft of the vibration activator; - reactive forces R1 and R2 in the rod bearings are determined by means of statics equations; - centrifugal forces from masses of the rod bearing assemblies including the bearing itself and eccentric bushing are determined. Dynamic balancing is carried out in accordance with the calculation model presented in Figure 8. Balancing condition: P1 = 1/2 (R1 - R3), R1>R3 symmetric arrangement of P2 = 1/2 (R2+ R4) counterbalances A geometric shape of counterbalances is chosen according to the recommendations proposed in (Kuzmichev, Verstov, 2017). As an example, results of measurements of the vibration level on the vibration mixer body (A type) are presented in Table 2. These results reflect the dynamic balancing quality. The measurements were taken using the following measuring equipment: vibration meter of 00032 type, No. 4106, Germany. Sensors were installed in two diametrically opposite areas on the vibration mixer cover where the drive was placed. The measurements were taken in two modes: experiment \u2116 1 \u2014 without any mix in the mixer; experiment \u2116 2 \u2014 during mixing. Victor Kuzmichev, Vladimir Verstov\u2014 Pages 20\u201326 VESSEL MIXERS WITH VIBRATION ACTIVATOR IN CONSTRUCTION ENGINEERING DOI: 10.23968/2500-0055-2017-2-2-20-26" + ] + }, + { + "image_filename": "designv8_17_0002992_M-2018-3-02-Dyja.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002992_M-2018-3-02-Dyja.pdf-Figure2-1.png", + "caption": "Fig. 2. Scheme of the plug rolling mill", + "texts": [ + " Application of higher elongation ratio leads to \u201cguide mark\u201d defects appearance (Fig. 1) on internal surface of the pipe. So far there is no unanimous view about the reasons of this defect appearance and no objective and accurate analysis of this problem has been made. Preventive recommendations of \u201cguide mark\u201d defect appearance are ambiguous and controversial. The study of the process of lengthwise rolling of tubes is presented in [4,5]. This study proposes the model of \u201cguide marks\u201d formation and provides the research of pipe forming at plug rolling mill (Fig. 2). A \u201cguide mark\u201d defect appears as follows, Fig. 3 [6]: 1) when rolling is performed on PRM-1, there is intensive metal flowing into the tapers, it results in a thicker pipe walls * URAL FEDERAL UNIVERSITY NAMED AFTER THE FIRST PRESIDENT OF RUSSIA B.N. YELTSIN, INSTITUTE OF MATERIAL SCIENCE AND METALLURGY, YEKATERINBURG, RUSSIA ** METAL FORMING INSTITUTE, 14 JANA PAWLA II AV., 61-139 POZNAN, POLAND # Corresponding author: dyja.henryk@wip.pcz.pl in the groove tapers than in the upper part of the groove (S1 is a wall thickness of the pipe in the groove taper and S2 is a wall thickness of the pipe in the upper part of the groove) [7-9]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000161_om_article_21583_pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000161_om_article_21583_pdf-Figure3-1.png", + "caption": "Fig. 3. Plans of positions and linear velocities of the mechanism links", + "texts": [ + " SEPTEMBER 2020, VOLUME 8, ISSUE 3 The proposed mechanism is characterized by the following main parameters: radius \ud835\udc45 = \ud835\udc51 2\u2044 of the sun spur gear, radius \ud835\udc45 = \ud835\udc51 2\u2044 of the satellite spur gear, semi-major axis \ud835\udc4e, minor axis \ud835\udc4f, eccentricity \ud835\udc52 and focal distance \ud835\udc50 of elliptical gears (Fig. 2). As can be seen from Fig. 2, to ensure intermittent motion of the output link, the dimensions of the cylindrical and elliptical gears are related by the following equations: \ud835\udc45 = \ud835\udc4e + \ud835\udc50, (1)\ud835\udc45 = \ud835\udc4e \u2212 \ud835\udc50. (2) To conduct a kinematic analysis of the proposed mechanism, there is constructed positions and linear velocities plans of mechanism links (Fig. 3) [26, 28]. Intermittent motion of the output link in this case is achieved by the fact that point D on the velocity plan will not intersect the zero line. The vector CC' from the point C lying at the same level as the point C in the mechanism scheme shows the velocity of the carrier point C. Connecting the point C' with the point A, which corresponds to the stationary point A on the axis of the carrier, gives a line C'A showing distribution of the carrier CA linear velocity. For a satellite, there are known the velocities of two points: the point C, which is common for a satellite and a carrier, and the point B, the velocity of which is equal to zero in accordance with the condition of rolling of the initial circle of a gear 6 ISSN PRINT 2335-2124, ISSN ONLINE 2424-4635, KAUNAS, LITHUANIA 125 on the initial circle of a gear 4", + " Consequently, connecting point D' with point A gives the distribution line of linear velocity of an elliptical gear 5 and, thus, that of a output shaft 3. At the moment when the gear ratio of the pair of elliptical wheels is equal to the gear ratio of the pair of cylindrical wheels, the output shaft 3 is stationary (position \ud835\udc4e). Then the velocity of the output shaft increases (position \ud835\udc4f) and reaches its maximum value (position \ud835\udc50), then again decreases (position \ud835\udc51) to zero (position \ud835\udc52). This way provides intermittent movement with stops of the output link. An analogue of the angular velocity of the output link 3, according to Fig. 3, will be determined as: \ud835\udf11\u2032 = \ud835\udf14\ud835\udf14 = \ud835\udc63 \u2219 \ud835\udc34\ud835\udc36\ud835\udc63 \u2219 \ud835\udc37\ud835\udc38 = \ud835\udc35\ud835\udc37 \u2219 \ud835\udc34\ud835\udc36\ud835\udc35\ud835\udc36 \u2219 \ud835\udc37\ud835\udc38 , (3) where \ud835\udf14 and \ud835\udf14 are angular velocities of input and output shafts, respectively; \ud835\udc63 and \ud835\udc63 are linear velocities of points D and C; BD, BC, AC and DE are lengths of the segments in Fig. 3. The distances AC and BC in Eq. (3) are determined as: \ud835\udc34\ud835\udc36 = \ud835\udc45 + \ud835\udc45 , (4)\ud835\udc35\ud835\udc36 = \ud835\udc45 . (5) To determine the segments BD and DE, it is necessary to find the length of the segment CD. It is determined by the equation of the centroid of an elliptical wheel [29, 30]: \ud835\udc36\ud835\udc37 = \ud835\udf0c = \ud835\udc4e \u2219 (1 \u2212 \ud835\udc52 )1 \u2212 \ud835\udc52 \u2219 cos\ud835\udf11 , (6) where \ud835\udf11 = \ud835\udc45 \ud835\udc45\u2044 \u2219 \ud835\udf11 is the angle of rotation of the elliptical wheel 7. Then, according to Fig. 3, the segments BD and DE are defined as: \ud835\udc35\ud835\udc37 = \ud835\udc35\ud835\udc36 \u2212 \ud835\udc36\ud835\udc37 = \ud835\udc45 \u2212 \ud835\udf0c, (7)\ud835\udc37\ud835\udc38 = \ud835\udc45 + \ud835\udc45 \u2212 \ud835\udf0c. (8) By substituting Eqs. (4-8) in Eq. (3), the equation for determining the analogue of the output shaft angular velocity is obtained: \ud835\udf11 = 1 \u2212 \ud835\udc45 \u2219 \ud835\udf0c\ud835\udc45 \u2219 (\ud835\udc45 + \ud835\udc45 \u2212 \ud835\udf0c) . (9) Thus, by integrating Eq. (9) over the generalized coordinate \ud835\udf11 , the function of the mechanism output link angle of rotation can be obtained. Using the study of the position function \ud835\udf11 (\ud835\udf11 ), we verify the adequacy of the developed kinematic model to a real mechanism", + " Geometrical and electrical characteristics of the experimental setup Geometrical parameters of the mechanism \ud835\udc45 , mm \ud835\udc45 , mm \ud835\udc4e, mm \ud835\udc4f, mm \ud835\udc50, mm \ud835\udc52 16 9 12.5 12 3.5 0.28 Parameters of angle sensor Resolution Linearity Update speed Output signal Outside diameter 360\u00b0 / 4096 \u2248 0.088\u00b0 0.3 % 0.6 ms 0-5 V 22 mm The study of the position function was carried out by measuring the rotation angles of the input and output shafts of the planetary mechanism. The theoretical position function and the results of the measurements are shown in Fig. 6. Designations \ud835\udc4e, \ud835\udc4f, \ud835\udc50, \ud835\udc51 and \ud835\udc52 in Fig. 6 correspond to the positions in Fig. 3. Kinematic analysis showed that the output link is stopped every 202.5\u00b0 of the input link rotation. Fig. 6 shows that the kinematics of the mechanism is described correctly, and the maximum deviations of the experimental results from theoretical data did not exceed 5 %. To perform a complete analysis of the experimental data, it is necessary to conduct a statistical analysis of the measurement results. Fig. 7 shows graphs of the absolute errors of the experimental results. ISSN PRINT 2335-2124, ISSN ONLINE 2424-4635, KAUNAS, LITHUANIA 127 Let us construct an interval variational series of the obtained experimental data" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000508_6514899_10356080.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000508_6514899_10356080.pdf-Figure8-1.png", + "caption": "FIGURE 8. Rendered image of lattice core unit cell used for analysis (a, b, c) A sandwich with diamond, octet, and star lattice core (d, e, f) C sandwich with diamond, octet, and star lattice core", + "texts": [ + "5mm and tcore = p = 5 mm), while the total thickness This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License. For more information, see https://creativecommons.org/licenses/by-nc-nd/4.0/ Author et al.: Preparation of Papers for IEEE TRANSACTIONS and JOURNALS of the C-sandwich is 12 mm. At this time, the dielectric constants of diamond, octet, and star are 1.15, 1.35, and 1.21, respectively. As highlighted earlier, the design consists of a single medium, making it compatible with 3-D printing processes, as shown in Fig. 8. Figs. 9 and 10 present the reflection and transmission coefficients for A- and C-type sandwich structures with lattice cores at 10 GHz. In the analysis of each lattice structure, based on incident angle changes, the A-type with octet lattices, particularly in TE polarization, exhibited higher reflectance and lower transmission compared to the diamond and star structures. This indicates that structures with a reduced effective permittivity offer benefits for radome designs. Additionally, the TE polarized light transmission in the A-type structure undergoes a phase shift of up to 25 degrees due to changes in the angle of incidence (See Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure9-1.png", + "caption": "Fig. 9 Lateral coupling resonances in equipment cabin under floor frame and associated influences on 691 fatigue damage of aluminum alloy car body. (a) Rhombus modal coupling resonance in middle of 692 service car body is accompanied by roof twisted modal vibration, ca.17.40 Hz. (b) Crescent notch 693 effect on one side of pantograph fairing and associated influences on fatigue damage at both ends of 694 transverse weldline. (c) Relationship curve of vehicle speed influence on fatigue life at both ends of 695 transverse weldline, in which roof is twisted and resonant when 450 km/h, and stronger resonance 696 occurs again when 650 km/h. (d, e, f) Lateral and vertical vibrations of pantograph fairing and 697 associated influences on fatigue life at both ends of transverse weldline when speed of (300 - 550) 698 km/h. (g, h, i) Lateral and vertical vibrations of pantograph fairing and associated influences on 699 fatigue life at both ends of transverse weldline when speed of (450 - 650) km/h. 700", + "texts": [ + " 669 However, the new rubber hanging elements were mistakenly used to implement the DVA 670 damping technique. If the impact of repeated roll vibration is excluded, as shown in Fig. 671 8, the lateral acceleration of traction converter exceeds the limit specified in IEC61373 \u2013 672 2010, forcing the self-excited vibration of the middle diamond mode for service car body. 673 Consequently, the accompanying vibration of roof twisted mode completely exposed the 674 inherent defects of aluminium alloy car body, as shown in Fig. 9, and the construction 675 speed (or design speed) could not be further promoted anymore. 676 The nonlinear variation in the inner forces of relevant constraints is one of the main 701 reasons for the elastic vibrations of lightweight structures. The vibration fatigue damage 702 assessment based on the master S-N curve of modal structural stress shows that: as shown 703 in Fig. 9 (d, g), the accompanying vibration of roof twisted mode exposes the impacts of 704 crescent notch effects at one side of pantograph on the fatigue lives at both ends of 705 transverse weldline. Specifically, as shown in Fig. 9 (c), when the vehicle speed is 450 706 km/h, the coupling resonance occurs in the roof twisted mode, and the fatigue life of 707 critical nodes decreases to 545\u00d7104 km. When increased to 650 km/h, the more intense 708 coupling resonance occurs, and the fatigue life decreases further to 138\u00d7104 km. 709 When the impact of repeated roll vibration is considered, the actual situation will 710 become worse, e.g. the maximum of lateral / vertical accelerations is 1.4 / 1.7 g 711 respectively due to the unstable vibration of transformer (ca" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure14-1.png", + "caption": "Figure 14. Flight tests revealed that the early Elka1Q fuselage was twisting about the longitudinal axis (see the arrows).", + "texts": [], + "surrounding_texts": [ + "The overall shape of the drone (as seen in Figures 8 and 9) is a compromise among the general assumptions (described in Section 1), size and weight of significant components (such as the battery pack), and smart usage of available materials. 2.3.1. Wings Typically, drone arms are made of carbon-fibre tubes because they are very stiff and lightweight at the same time. However, such a single tube could have a too big a diameter to fit into the drone\u2019s wing. Instead, we decided to use double 6 \u00d7 2 mm carbon-fibre flat bars as wing spars. Additionally, the space between them forms a convenient tunnel for electric wires. The wings are built of two matching full-balsa wood elements: a bottom and a top half, both CNC 3D milled and glued together. The leading and trailing edges of a wing are usually prone to accidental damage (especially a very thin trailing edge); therefore, both edges are reinforced with carbon-fibre 4\u00d7 1 mm flat bars. The carbon-fibre wing spars at the wingtips support the main motor holders (CNC milled from a 3mm-thick aluminium sheet). The two elements of the holders are screwed together to catch protruding wing spars tightly. Finally, the surface of the wing is covered by Oracover [32] film. The wing construction proves to be light and very durable. We could say it is a perfect balance between stiffness and elasticity. Initially, we chose a wing profile (an airfoil) optimized for high-speed flight: the P-51D tip (BL215) airfoil (see Figure 10). Generally speaking, high-speed airfoils have low drag, but, on the other hand, have a low lift coefficient, which results in a high stall speed, and that means the plane has to maintain high enough speed to stay airborne in a level flight. That should not be an issue if the pusher motor can accelerate the drone to that speed. Due to safety reasons, we decided to modify the original wings\u2014we made them much thicker (see Figure 11). Such a thick airfoil (thickness increased from 12% to 25% of the airfoil chord) gives us a much higher lift coefficient (resulting in a lower stall speed) at the cost of lowering the top speed. Nevertheless, lower stall speed means we could perform the in-flight experiments of switching between quadcopter and plane mode at lower (i.e., safer) speed, and we could do that in a less spacious airfield. The wing configuration used in the drone is called a \u201ctandem-wing\u201d or sometimes a \u201clifting-tail plane\u201d. Those names refer to the fact that the aft wing is not just a horizontal stabilizer, like in a classic \u201ctailplane\u201d configuration, but it contributes to the total lift force produced by the plane. It is a rare configuration due to possible stability and controllability issues [34,35]. Sometimes, quite the opposite statements can be found\u2014tandem-wing planes are easier to pilot because of safer stall behaviour [36]. However, there were at least a few successful tandem-wing planes, e.g., Quickie designed by Elbert Leander \u201cBurt\u201d Rutan (and later QAC Quickie Q2) [36,37] and the Proteus [38] built by Scaled Composites (Rutan\u2019s company). Another famous tandem-wing plane is the \u201cFlying Flea\u201d (French name: \u201cPou du Ciel\u201d), designed by Henri Mignet in 1933. A thorough study of many more historical and modern tandem-wing planes and UAVs, as well as their aerodynamic and stability studies, can be found in [34]. A wing that produces lift force also generates a downwash, i.e., the airflow direction behind the trailing edge of the wing is deflected down by the aerodynamic action of the wing. That phenomenon changes the effective Angle of Attack (AoA) of the rear wing in the tandem-wing configuration. Most tandem-wing planes have the front wing mounted lower than the rear wing to minimize the downwash effect of the front wing [34,35]. Additionally, it is recommended to set a higher AoA of the front wing than the aft wing\u2014such a wing setup affects the stall behaviour of the tandem-wing plane. The front wing with a higher AoA will stall first while the aft wing still produces lift force\u2014that situation will cause the plane to pitch down, increase the speed, and ultimately, end the front wing\u2019s stall (bring back its lift force) [36]. Following the suggestions, the front wing of the Elka1Q drone was mounted at ca. 4\u25e6 AoA and the aft wing at ca. 2\u25e6 AoA. Finally, there is at least one more critical aspect of every aircraft having wings: Centre of Gravity (CG, CoG). It is crucial to keep the longitudinal stability of an aircraft. We used a CG calculator from the eCalc toolset [30]. The results of the calculation are presented in Figure 12. 2.3.2. Fuselage The final fuselage design was based on a rigid PVC tube (100 mm diameter and 1 mm wall) and a lighter, but still solid plywood structure (Figures 15\u201317). The PVC tube acts similarly to a monocoque structure, eliminating the twisting about the longitudinal axis. The landing gear is non-retractable\u2014we made four fixed legs of 3 mm spring steel wire supported by pinewood blocks at the bottom of the fuselage. The overall structure of the wings and the fuselage proved to be very rigid and robust, surviving a few serious crash landings. The most significant disadvantage of such a compact construction is complicated maintenance of internal components, e.g., access to electronic boards, wires, and connectors." + ] + }, + { + "image_filename": "designv8_17_0003509_451-20922303415D.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003509_451-20922303415D.pdf-Figure4-1.png", + "caption": "Figure 4. Modification of the supporting surface of the track by transferring the grouser", + "texts": [ + " This direction can be considered promising. 4. The optimization of the arrangement of lugs [35]. Moving the lugs from under the hinge axis to the edge of the link reduces the time when the track roller rolls over the hinge axis and reduces the vertical vibrations of the track. Such modernization, affecting only track design, is characterized by minimal costs for the improvement of the caterpillar and does not affect the weight of the undercarriage system [36]. Moving the lug behind the hinge axis minimizes the turning force arm A (Fig. 4), which helps to reduce losses in propulsion. Improving the movement helps to reduce losses in the propulsion unit while maintaining the high cross-country ability of the vehicle. This met\u2013 hod is most effective when driving on hard ground [37]. The positive displacement of the tracks depends on the geometric dimensions of the undercarriage and the forces acting on its elements. To select dimensions when designing a caterpillar with reduced environ\u2013 mental hazard, it is necessary to study in more detail the mechanics of the interaction of the track with the track roller and the ground" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003878_7042252_07080869.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003878_7042252_07080869.pdf-Figure1-1.png", + "caption": "FIGURE 1. Geometry of the proposed L-probe fed water dielectric patch antenna. (a) Overall geometry, (b) Side view, (c) Top view of the water patch with L-probe.", + "texts": [ + " Personal use is also permitted, but republication/redistribution requires IEEE permission. See http://www.ieee.org/publications_standards/publications/rights/index.html for more information. VOLUME 3, 2015 The rest of the paper is organized as follows. Section II describes the geometry and design considerations of the proposed antenna. The simulated and measured results and the discussions are detailed in Section III. Finally, a conclusion is given in Section IV. II. ANTENNA GEOMETRY AND DESIGN The geometry of the proposed water DDPA with an L-probe feed is shown in Fig. 1. In order to realize the design, two boxes made of plexiglass are stacked together. The plexiglass has a thickness of 4 mm and a dielectric constant of 3.4. The top smaller rectangular box with a width ofWP, a length of LP, and a height ofHP is filled with pure water to construct the water dielectric patch, while the bottom larger square box with a height of HA is empty and is used as a supporting structure. Therefore, the substrate between the water patch and the ground plane is air in this design. A square metallic ground plane of length WG is installed at the bottom surface of the large box, where the L-shaped probe is mounted. The height and length of the L-probe are LV and LH respectively. There is a spacing S between the edge of the water patch and the position of the L-probe. A short section of coaxial cable with an SMA connector is connected to the L-probe for measurement. It should be noted that the dimensions shown in Fig. 1 do not include the thickness of the plexiglass box. It is found in our studies that since the operating mechanism of the proposedwater patch antenna is similar to the conventional metallic patch antenna, they owns analogous design rules as well. The design procedure of the patch antenna has been available in the literature [15], [16]. Besides, a parametric study of the DDPA was also given in [13], so it is not necessary to address them in details here. According to the result in [13], the aperture coupled DDPA with a thin substrate has a narrow bandwidth of 1%" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure41-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure41-1.png", + "caption": "Figure 41: FEA deflection plot after 10 degree input for compliant slider crank [16].", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0002072_3-319-16178-5_15.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002072_3-319-16178-5_15.pdf-Figure1-1.png", + "caption": "Fig. 1. LinkQuad platform with the color camera sensor module", + "texts": [ + " Our experimental results clearly demonstrate that the proposed framework efficiently detects and tracks persons in both indoor and outdoor complex scenarios. Our framework can thus be used for stable virtual leashing. The rest of the paper is organized as follows. Section 2 describes the used Micro UAV platform. Section 3 presents our active vision framework. Experimental results are provided in Section 4. Finally, conclusions are provided in Section 5. The micro UAV platform used for the system evaluation is a LinkQuad, see Figure 1. It is a highly versatile autonomous UAV. The platform\u2019s airframe is characterized by a modular design which allows for easy reconfiguration to adopt to a variety of applications. Thanks to a compact design (below 70 centimeters tip-to-tip) the platform is suitable for both indoor and outdoor use. It is equipped with custom designed optimized propellers which contribute to an endurance of up to 30 minutes. Depending on the required flight time, one or two 2.7 Ah batteries can be placed inside an easily swappable battery module" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003921_3272-021-00517-7.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003921_3272-021-00517-7.pdf-Figure11-1.png", + "caption": "Fig. 11 Entire domain for numerical simulation", + "texts": [ + " This study takes advantage of a mixing plane approach to model interfaces between adjacent domains. According to ANSYS, this approach utilizes a technique to submit circumferentially averaged data between two adjacent domains. Moderate pitch angles are assumed uncritical [16]. Comparing full simulation and single blade passage results, for example, by considering static pressure values, reveals only small discrepancies. Therefore, possibly distorted results appear to be negligible and remaining operation points are investigated by simulating a single passage, as depicted in Fig.\u00a011. The details are discussed in the following section. As a start, Fig.\u00a011 intends to provide an overview of a blade passage domain, consisting of four axially aligned sub domains. The flow enters the domain through the interface marked as \u201cInlet\u201d, which is identical to the inlet station as defined in Fig.\u00a05. The same applies to the outlet station, where the fluid exits the entire domain. Boundary layers are geometrically resolved using prism layers. Turbulence is mathematically modeled by applying the sst-model. To simplify the numeric setup, turbulent inflow conditions are selected" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure28-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure28-1.png", + "caption": "Figure 28 CubeSat Connector Interface", + "texts": [ + " CubeSat Interface Specification The standardized CubeSat interface will consist of the CubeSat connector half mounted to the center of the \u2013Z face of the CubeSat, such that the back plane of the connector housing is flush with the plane created by the \u2013Z rail standoffs. The reason this location was chosen was that it is important to maintain the CubeSat\u2019s useable volume, employing as few limitations to the CubeSat as possible. Connector orientation is less critical, but must be the same every time, so it will required that the connector be mounted such that the long axis of the connector is along the Y-axis of the CubeSat. This interface specification is show below in Figure 28. Page 42 Power-On System Structural Analysis The next step was to show that the design was structurally sound. This was not a significant concern given the loads it was going to see, but it is still important to show launch providers that the entire P-POD is structurally sound and that the access port halves will not gap. A conservative load case was used, assuming the entire load of the connector spring was placed on the access port half that it was mounted too. Additionally, the spring was assumed to be compressed twice as much as expected, a total of 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000432_s.eu_pliki_art_9564_-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000432_s.eu_pliki_art_9564_-Figure1-1.png", + "caption": "Fig. 1. Stirred vessel with an eccentrically positioned impeller: a) stirred vessel geometry: 1 \u2013 cylindrical tank, 2 \u2013 impeller, 3 \u2013 shaft, b) Rushton turbine", + "texts": [ + " An interesting alternative to standard, baffled mixing vessels are unbaffled ones with eccentrically (not in accordance with the tank axis located) impeller [1]. The impeller displacement causes a change in the flow pattern in the vessel. Distinct, asymmetric circulation loops are induced in the apparatus. For identification of liquid flow generated by an eccentrically positioned Rushton turbine, numerical modelling and CFD simulations were applied. This study is a continuation of the research described in [6]. The stirred vessel analysed in the numerical investigations is shown in Figure 1. It consists of an unbaffled cylindrical tank 1 (internal diameter D\u00a0=\u00a00.286\u00a0m) with a flat bottom. Inside the tank a single, standard Rushton turbine 2 was located (Fig. 1b). The impeller has the diameter d = D/3 and the impeller off-bottom clearance was set at h = d. The impeller rotated clockwise at n = 300 [1/min], in the range of fully turbulent flow (Rem \u2248 4,5\u00b7104). Distilled water (\u03c1\u00a0=\u00a0998 kg\u00a0m3, \u03b7\u00a0=\u00a00,001\u00a0Pa\u00b7s (at 20\u00b0C)) was taken as the tested liquid. The liquid height for all simulations was set at H = D. An impeller was located in three different positions inside the tank. Its distance from the tank axis was: e = 0 (central position, in accordance with the tank axis) as well as e = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000548_3_NgTeckChew2009.pdf-Figure2.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000548_3_NgTeckChew2009.pdf-Figure2.1-1.png", + "caption": "Figure 2.1: Trajectory reconstruction-based vehicle following from Stefan [52]. The positions of the lead vehicle are recorded up to time tn. A lookahead distance is imposed for safety purposes.", + "texts": [ + " His model states that a follower will trail the path rather than the current position of the leader. A stereo pair camera is installed in the follower vehicle to estimate the relative position and orientation of the lead vehicle, and a path is reconstructed using the estimated poses of the leader and the follower. A global map is built based on the estimation results. The proposed algorithm [52],[53] uses the time history associated with the lead vehicle over a certain period of time, as shown in Figure 2.1. In this case, the position coordinates of the lead vehicle and the motion parameters of the follower vehicle were stored with the time stamped on the map. From the map, a tracking point for vehicle following in both lateral and longitudinal directions was then selected. The algorithm Chapter 2. Related Work 32 assumes that the lead vehicle moves at such a slow speed that it is manuvering along a straight path within this short period of time. Some experiments were carried out on straight and clothoid paths" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004426_iceesi2017_01022.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004426_iceesi2017_01022.pdf-Figure2-1.png", + "caption": "Fig. 2. Configuration of SIW Coupler (a) Top view (b) Side view", + "texts": [ + " Both metal posts are set symmetrically in order to control the signal flow. Two extra silver epoxy posts that set in every port act as reflection cancelling elements by varying the sections of Substrate Integrated Waveguide (SIW) [14]. Via hole must be shorted to both planes in order to provide vertical current paths, otherwise the propagation characteristics of SIW will be significantly degraded [14]. 2.2 SIW Coupler\u2019s Design The configuration and parameter dimensions of SIW coupler are shown in Fig. 2. (a) As depicted in Fig. 2, the coupling is obtained by two narrow apertures in the common broadside wall of two adjacent SIWs. To accomplish such coupling ratio, Port 1 is defined as the input port, Port 2 as the through port, Port 3 as the coupled port and Port 4 as the isolated port. The transition between SIWs and microstrip line is realized using microstrip taper to match both electrical and magnetic field distributions between the two medias [14]. In this paper, the proposed coupler is designed on photographic paper substrate materials where the metal (conductive) used is copper as a ground plane and metallic via holes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004203_f_version_1598534949-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004203_f_version_1598534949-Figure4-1.png", + "caption": "Figure 4. Motor designs with various interpole iron widths.", + "texts": [ + " The analytical mo ls as umed th t the motors were made of silicon steel (35CS300) and driven by t single-phase square wave Energies 2020, 13, 4445 4 of 11 current of 1 A at a rotational speed of 1000 RPM under a no-load condition. The final motor design was chosen based on its high torque density and low torque ripple. Torque ripple (Tripple) was defined as Tripple = Tmax \u2212 Tmin Tavg \u00d7 100% (1) where Tmax, Tmin, and Tavg are the maximum, minimum, and average torques, respectively. Torque density (TV) was defined as Tv = Tavg Vol (2) where Vol is the volume of the magnet. The preliminary analysis of the motor designs was assessed with interpole iron widths of 0, 0.5, 1, 1.5, and 2 mm, as shown in Figure 4. The torque characteristics and volume of the magnet were obtained as shown in Table 2. The best design can be found in the interpole iron widths between 1 mm and 2 mm. er ies 020, 13, x FOR PEER REVIEW current of 1 A at a rotational speed of 1000 RPM under a no-load condition. The final motor design was chosen based on its high torque density and low torque ripple. Torque ripple (Tripple) was defined as \ud835\udc47 \ud835\udc47 \ud835\udc47\ud835\udc47 100% (1) where Tmax, Tmin, and Tavg are the maximum, minimum, and average torques, respectively. Torque density (TV) was defined as \ud835\udc47 \ud835\udc47\ud835\udc49\ud835\udc5c\ud835\udc59 (2) where Vol is the volume of the magnet. The preliminary analysis of the motor designs was assessed with interpole iron widths of 0, 0.5, 1, 1.5, and 2 mm, as shown in Figure 4. The torque characteristics and volume of the magnet were obtained as shown in Table 2. The best design can be found in the interpole iron widths between 1 mm and 2 mm. Figure 4. Motor designs with various interpole iron widths. from 1.1 mm to 1.9 mm in increments of 0.1 mm. The motor characteristics were calculated as shown in Table 3. The final design was selected with an interpole iron width of 1.6 mm. The motor had an average torque of 3.008 mN-m, a torque ripple of 74.77%, and a torque density of 0.172 mN-m/mm3. d (mm) Tavg (mN-m) Tripple (%) Vol (mm3) Tv (mN-m/mm3) 1.1 3.270 62.96 20.00 0.164 1.2 3.222 62.70 19.49 0.165 1.3 3.172 64.68 18.98 0.167 1.4 3.119 67.25 18" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001044_a8fa772056d4fd55d520-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001044_a8fa772056d4fd55d520-Figure1-1.png", + "caption": "Fig. 1. FS5 RSI configuration. (Color online only)", + "texts": [ + " The secondary mirror, M2 Support Bracket, M2 Spider, and M2 Baffle are supported by the M2 Support Ring, which is connected to the Top Panel by the M2 Support Ring Supporter. The Main Plate Support Frame supports the main plate and connected to the Top Panel. The M2 Strut Frame consists of six struts and interface brackets connecting the M2 Support Ring to the Main Plate. The Top Panel is on the bottom of the Telescope, connected to the satellite bus by top supports. The RSI Cover Assembly is installed directly to the Top Panel and covered by a thermal blanket to maintain the required thermal environment. The overall RSI configuration is shown in Fig. 1. Terr. Atmos. Ocean. Sci., Vol. 28, No. 2, 157-165, April 2017 There are three primary materials used in the RSI structure: CFRP material, honeycomb plate core material, and adhesive bonding material. According to Yang (2009), the properties of these materials are described in sections 2.1 to 2.3. With the advantages of low CTE design and high stiffness, the 350\u00b0F cured 954-3 cyanate resin with high modulus of M55J carbon fibre was selected for honeycomb plate face sheet materials for the Main Plate, M2 Support Ring, and Top Panel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003418_ice_Designed_for.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003418_ice_Designed_for.pdf-Figure5-1.png", + "caption": "Figure 5. Realized prototype of a device for offsetting tensile forces in elevator ropes", + "texts": [ + " The accuracy of determining the actual tensile force in the rope is affected by the reshaping (deformation) of the rope sensor body and depends on the angle of inclination of the rope section and the distance of the gripping points of all contact points. The above mentioned limitations and drawbacks can be eliminated using the device for offsetting tensile forces in elevator ropes described below. FORCE IN A ROPE A specific design and technical solution of the device for detecting and offsetting tensile forces in the elevator carrier ropes is illustrated in Figure 5. The described device is capable of continuously recording the time course of the instantaneous tensile forces, acting on elevator carrier ropes, when one free ends of the carrier ropes are mechanically attached to the openings of the suspension screws, which are mechanically tied to the bearing bracket, see Figure 3. Suspension screw 1, see Figure 6, is threaded through the opening in the bearing bracket 2. On the thread of the suspension screw, above the up- per level of the bearing bracket, a bowl is pushed 3 in a defined direction, into which one end of the compression coil spring is inserted 4", + " Compression or release (given by the purpose of rotation of the suspension screw 9 of the individual screw spindle 8) of the individual compression coil spring 4 are due to the design of the movable mechanical tension off-setter, namely the fixed length distance (at a given moment) between the plane of placement of the cylindrical nut 11 (the link is provided by the pins inserted into the openings created in the end sections of the cylindrical rod 12 and screws with cylindrical head and inner hexagon 13) and the upper surface of the bearing bracket 2. In the lower part of the body 14 of the movable mechanical tension off-setter, there is a mounting (neck- down), into which a centering ring is inserted 24, see Figure 5. The inner diameter of the centering ring 24 thus defines a play between the outer dimensions of the washer 6 and the inner diameter of the body mounting 14. At the moment of rotation (in a given direction) of the double screw 9 of the individual screw spindle 8, there is an extension (shortening) of the distance between the plane of placement of the cylindrical nut 11 (in relation to the body 14) and the upper surface of the bearing bracket 2. The mutual mechanical connection of the hub 23 with the suspension screw 1 and the screw spindle 8, which is through the cylindrical nut 11 mechanically interconnected with the body 14 of the movable mechanical tension off-setter, gains one degree of freedom" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002886_nal_Thesis_Suren.pdf-Figure5.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002886_nal_Thesis_Suren.pdf-Figure5.10-1.png", + "caption": "Figure 5.10: Illustration of microstructure submodel in CT specimen.", + "texts": [ + " Microstructure Submodeling of SGI Material Page : 179 form of failure and life prediction should consider the microstructural features and defects in the material. This explained an admirable reason why submodeling could be appropriate modeling approach to predict microstructure dependent failure in SGI components. To demonstrate microstructure dependent crack growth simulation using submodeling approach, a miniature CT specimen used for FCP test in section 4.3.2 was modeled with microstructure submodel at the notch region as illustrated in Figure 5.10. Both the global CT model and microstructure submodel were modeled with plane stress elements. For the global model, course mesh was used and modeled as bulk SGI material. For the microstructure submodel, the real undeform micrograph at the notch of the CT specimen was used to generate FE representation mesh using image based FEM method OOF2, which is explained in detail in next section. As only submodel was defined as X-FEM enrichment region, cracks can only initiate and grow within the microstructure submodel", + " As the main aim in the simulation was to study microstructure dependent crack initiation and propagation in SGI material, only the ferrite region in the microstructure model was defined as X-FEM enrichment region. The CT sample was not defined with any damage criterion, which significantly reduced computation time. The main are of interest was the microstructure model. The CT sample model was designed with exact dimension to the CT sample used in the experiment, So that the results could be directly compared. The boundary conditions for the CT sample were formulated similar to the experimental constrains as illustrated in Figure 5.10. Both the top and bottom pin holes in the CT were defined as a kinematic coupling with the hole center as the reference control point. The top hole reference point was constrained in x and y direction and allowed rotation DOF about the z-axis (UR3). The load was applied to the bottom hole in the negative y-direction. The out of plane specimen thick- Nanyang Technological University Singapore Ch. 5. SGI Microstructure Modeling 5.3. Microstructure Submodeling of SGI Material Page : 183 ness was used from the actual specimen thickness, and the corresponding force was applied in the simulation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure16-1.png", + "caption": "Figure 16. Thermal field distribution of three cross-sections: (a) the water inlet side; (b) the middle cross-section; and (c) the water outlet side.", + "texts": [ + " By comparison of Tables 6 and 7, it shows that the CS-PMSM can run safely when the water cooling used in the casing and axial forced air are simultaneously adopted in the CS-PMSM. When both the SM and the DRM are running at the rated speed and rated load, the 3-D thermal field distribution is calculated under condition of water cooling used in the casing and the inner rotor, as shown in Figure 15. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the water inlet side, middle cross-section, and the water outlet side of the CS-PMSM are shown in Figure 16. The selected water inlet, middle and water outlet cross-sections are the same as those in Section 4.1. The highest temperature of each part in the above three cross-sections is shown in Table 8. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 8. From the temperature distribution of each cross-section in Table 8, it can be seen that the temperatures of the stator and inner rotor are lower than that of the outer rotor, as the heat of the stator and inner rotor is easily taken away by the water when the water cooling is used in the casing and the inner rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure22-1.png", + "caption": "Figure 22. Results of Deflection and warpage.", + "texts": [ + " Estimated Sink Mark Figure 20 shows the presence and location of sink marks and voids likely to be caused by features on the opposite face of the surface. Sink marks typically occur in moldings with thicker sections or at locations opposite ribs, bosses, or internal fillets. These results do not indicate sink marks caused by locally thick regions. From the analysis, along the shaft where the thickness variations are prominent, possible sinks are predicted (Figure 21). 4.3.2. Deflection and Warpage The deflection and warpage results (Figure 22) show how the part deflects from the originally designed shape. These mainly occur due to drastic differences in temperature at different part locations. This result helps design an appropriate cooling system and vary the design of the part to minimize defects during fabrication. Along the edge region, more even cooling is desired. 4.3.3. Volumetric Shrinkage at Ejection The volumetric shrinkage at ejection (Figure 23) decreases local volume from the end of the cooling stage to when the part has cooled to the ambient reference temperature, which shows the volumetric shrinkage for each area expressed as a percent of the original modeled volume" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003696_7_10_27_10_1144__pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003696_7_10_27_10_1144__pdf-Figure14-1.png", + "caption": "Fig. 14 Control of cameras corresponding to backward and forward motion of viewer (top view)", + "texts": [ + " \u305f\u3060 \u3057,\u8996 \u8005\u304c\u4e0a \u306b\u5927 \u304d \u304f\u79fb\u52d5\u3059 \u308b\u3068\u753b\u9762\u4e0b\u90e8 \u304c, \u4e0b \u306b\u5927 \u304d \u304f\u79fb\u52d5\u3059 \u308b\u3068\u753b\u9762\u4e0a\u90e8\u304c,\u5965 \u306b\u898b\u3048 \u308b\u50be \u5411\u304c \u3042 \u308b\u305f\u3081,\u8996 \u8005\u306e\u6975\u7aef\u306b\u5927 \u304d\u306a\u4e0a\u4e0b \u79fb\u52d5 \u306b\u306f\u5bfe\u5fdc\u3067 \u304d \u306a \u3044. \u91ce \u4e2d \u30fb\u4f0a \u9054:\u4e21 \u773c \u8996 \u3068\u904b \u52d5 \u8996 \u3092\u5fdc \u7528 \u3057\u305f \u30d3\u30c7 \u30aa \u30b7 \u30b9 \u30c6 \u30e0 1151 \u3063\u305f\u611f\u899a \u3092,\u3088 \u308a\u30ea\u30a2\u30eb\u306a\u3082\u306e\u306b\u3059 \u308b\u305f\u3081 \u306b,\u8996 \u8005 \u306e \u524d\u5f8c\u79fb\u52d5 \u306b\u5bfe\u5fdc \u3057\u305f\u30ab\u30e1 \u30e9\u5236\u5fa1\u3092\u4ed8\u52a0\u3059 \u308b \u3053\u3068\u304c\u52b9\u679c \u7684 \u3068\u8003 \u3048 \u3089\u308c \u308b.\u3059 \u306a\u308f\u3061,\u8996 \u8005\u304c \u30c7\u30a3\u30b9\u30d7 \u30ec\u30a4\u306b\u8fd1 \u3065 \u304f\u3068,\u88ab \u5199\u4f53 \u304c\u5927 \u304d\u304f\u306a \u308b\u306e\u3068\u540c\u6642 \u306b,\u8996 \u91ce\u304c\u5e83\u304c \u308b\u3068\u3044\u3046\u52b9\u679c\u3084,\u8996 \u8005 \u304c \u30c7 \u30a3\u30b9 \u30d7 \u30ec\u30a4 \u306b\u8fd1 \u3065\u3044\u305f\u3068 \u304d,\u8fd1 \u304f\u306e\u88ab\u5199\u4f53 \u306f\u8fd1 \u3065\u3044\u3066\u307f\u3048 \u308b\u304c,\u9060 \u666f \u306f\u307b \u3068\u3093 \u3069\u8fd1\u3065 \u304b\u306a\u3044 \u3068\u3044 \u3046\u52b9\u679c \u304c\u5f97 \u3089\u308c\u308b.\u3053 \u306e\u6a5f\u80fd \u3092\u5b9f\u73fe \u3059 \u308b\u305f\u3081\u306b\u306f,\u30ab \u30e1 \u30e9\u306e\u79fb\u52d5 \u3060\u3051\u3067 \u306a \u304f,\u30ba \u30fc \u30df\u30f3\u30b0 \u304c\u5fc5\u8981 \u3068\u306a \u308b.\u4ee5 \u4e0b\u306b\u30ab\u30e1 \u30e9\u306e\u5236\u5fa1 \u306e\u6982\u8981 \u3092\u793a \u3059. \u4e21 \u30ab\u30e1 \u30e9\u306e\u5149 \u8ef8\u306e\u4ea4\u70b9 \u304c\u70b9F\u306b \u306a \u308b\u3088 \u3046\u306b\u4fdd\u3061\u306a\u304c \u3089,\u4e21 \u30ab\u30e1 \u30e9\u306e \u30ec\u30f3\u30ba\u7cfb \u306e\u4e2d\u5fc3\u3092,\u8996 \u8005 \u306e\u524d\u5f8c\u5de6\u53f3 \u306e \u52d5 \u304d\u306b\u5408\u305b \u3066,\u6c34 \u5e73 \u306a\u5e73\u9762 \u5185\u3092\u524d\u5f8c\u5de6\u53f3 \u306b\u79fb\u52d5 \u3055\u305b \u308b (Fig. 14).\u3053 \u306e\u969b,\u8996 \u8005\u304c \u30c7 \u30a3\u30b9\u30d7 \u30ec\u30a4 \u306b\u8fd1\u3065 \u304f\u3068 \u304d\u306f \u30ba \u30fc \u30e0 \u30c0 \u30a6 \u30f3,\u9060 \u3056\u304b \u308b\u3068\u304d\u306f\u30ba \u30fc\u30e0\u30a2 \u30c3\u30d7\u3059 \u308b.\u3053 \u306e \u3053\u3068\u306f,\u8996 \u8005\u304c \u30c7\u30a3\u30b9\u30d7 \u30ec\u30a4\u306b\u8fd1\u3065 \u304f\u3068\u8996\u91ce \u304c\u5e83\u304c \u308a(\u5e83 \u89d2),\u9060 \u3056\u304b \u308b\u3068\u8996\u91ce \u304c\u72ed \u304f\u306a \u308b(\u671b \u9060) \u3053\u3068\u306b\u5bfe\u5fdc\u3059 \u308b. \u672c\u5831\u544a\u306e\u8a66\u4f5c\u306b \u304a\u3044\u3066,\u524d \u5f8c2\u53f0 \u306e\u53f0\u8eca \u306e\u79fb\u52d5\u8ddd\u96e2 \u6bd4 \u3068\u540c \u3058\u6bd4\u7387\u3067,\u524d \u5f8c2\u5bfe \u306e \u30ec\u30fc\u30eb\u3092\u5965\u884c \u65b9\u5411 \u306b\u79fb\u52d5 \u3055\u305b \u308b\u3053\u3068,\u304a \u3088\u3073\u64ae\u5f71\u7cfb \u3068\u8868\u793a\u7cfb \u306e\u753b\u89d2\u3092\u4e00\u81f4 \u3055\u305b \u308b\u3088 \u3046\u306b \u30ec\u30f3\u30ba\u7cfb\u306e\u7126\u70b9\u8ddd\u96e2 \u3092\u5909\u5316 \u3055\u305b \u308b\u3053\u3068\u306b\u3088 \u3063 \u3066,\u3053 \u306e\u30ab\u30e1 \u30e9\u306e\u79fb\u52d5\u304c\u5b9f\u73fe \u3055\u308c\u308b. 5. \u307e \u3068 \u3081 \u672c\u7814\u7a76 \u3067\u306f,\u30d3 \u30c7\u30aa\u753b\u50cf\u8868\u793a \u30b7\u30b9\u30c6\u30e0\u306b\u4e21 \u773c\u8996 \u304a \u3088 \u3073\u904b\u52d5\u8996 \u306e\u6a5f\u80fd \u3092\u4ed8\u52a0\u3059 \u308b\u8a66\u307f\u3092\u884c \u3063\u305f.\u3053 \u308c\u306f,\u8fd1 \u5e74 \u30d3\u30c7\u30aa\u753b \u50cf\u3092\u901a \u3057\u3066,\u3088 \u308a\u6b63\u78ba\u306a\u7a7a\u9593\u60c5 \u5831\u3092\u5f97 \u308b\u624b \u6bb5 \u304c\u5fc5\u8981 \u3068\u306a \u3063\u3066 \u304d\u3066 \u3044\u308b\u3053\u3068\u306b\u5fdc\u3048\u305f \u3082\u306e\u3067\u3042 \u308a, \u30d2\u30e5\u30fc\u30de \u30f3 \u30fb\u30a4 \u30f3\u30bf \u30d5\u30a7\u30fc\u30b9 \u3068 \u3057\u3066\u306e\u6a5f\u80fd \u306e\u5411\u4e0a \u3092\u5b9f \u73fe\u3059 \u308b\u3082\u306e\u3067 \u3042\u308b.\u5e7e \u4f55 \u5b66\u7684\u306a\u65b9\u6cd5\u3067\u64ae\u5f71\u6a5f\u5668 \u306e\u914d \u7f6e \u304a\u3088\u3073\u79fb\u52d5\u5236\u5fa1 \u306e\u8a2d\u5b9a \u3092\u884c \u3046 \u3053\u3068\u306b\u3088\u308a,\u6b6a \u307f\u306e\u5c11 \u306a \u3044\u7acb\u4f53 \u50cf\u304c\u5f97 \u3089\u308c\u305f" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000752_el-04725201_document-Figure2.24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000752_el-04725201_document-Figure2.24-1.png", + "caption": "FIGURE 2.24 : Sch\u00e9ma d\u2019une ligne de transmission microruban.", + "texts": [ + " Les antennes patch se composent g\u00e9n\u00e9ralement d\u2019un \u00e9l\u00e9ment rayonnant m\u00e9tallique plac\u00e9 sur un substrat di\u00e9lectrique, avec un plan de masse sur le c\u00f4t\u00e9 oppos\u00e9 du substrat. Les antennes patch peuvent \u00eatre excit\u00e9es de diff\u00e9rentes mani\u00e8res, en fonction des besoins de l\u2019application et des caract\u00e9ristiques de l\u2019antenne [125]. Nous retenons pour ces travaux l\u2019alimentation de l\u2019antenne patch par une ligne microruban, car c\u2019est la plus simple \u00e0 mettre en \u0153uvre dans notre cas. Le sch\u00e9ma d\u2019une ligne microruban est montr\u00e9 sur la figure 2.24. Nous savons que la propagation des ondes dans une ligne microruban s\u2019effectue \u00e0 la fois dans le milieu di\u00e9lectrique et dans l\u2019air. Du point de vue de la mod\u00e9lisation, les deux milieux sont remplac\u00e9s par un milieu effectif caract\u00e9ris\u00e9 par une constante di\u00e9lectrique exprim\u00e9e par : 66 2.4 - CONCEPTION DE LA RECTENNA Si h w < 1 \u03f5eff = ( \u03f5r + 1 2 ) + ( \u03f5r \u2212 1 2 ) . ( 1 + 12. h w )\u2212 1 2 (2.22) Ainsi, la propagation des signaux d\u00e9pend principalement de la largeur de la ligne w des circuits m\u00e9tallis\u00e9s et des propri\u00e9t\u00e9s du substrat, telles que sa constante di\u00e9lectrique \u03f5r et son \u00e9paisseur h" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000556_load.php_id_08123106-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000556_load.php_id_08123106-Figure2-1.png", + "caption": "Figure 2. 3D Configuration of the horn section. (a) 3D view. (b) Top view. (L = 60 mm, d0 = 1.6mm, dL = 74.0mm).", + "texts": [ + " This approach reduces reflection coefficient and increases matching bandwidth [16]. A Chebyshev tapered structure improves directivity of the antenna, and yields the smallest minor-lobe amplitude for a fixed taper length [20]. In this paper, we use an exponentially tapered structure. Exponential impedance taper is used to match the characteristic impedance at the feed point to the impedance of the free space at the antenna aperture. In fact, the antenna acts as a transformer to match the transmission line and the free space. The configuration of the horn section is shown in Fig. 2. It is divided into ten sections, each section consists of a parallel plate waveguide. Since the exponentially tapered matching technique is used, the characteristic impedance of each section, Z(zi), can be expressed as: Z(zi)=Z0 exp(\u03b1zi), zi = iL N i=1, 2, 3, . . . , N ; \u03b1= 1 L ln ( \u03b7 Z0 ) (1) where Z0 is the characteristic impedance of the feed line (50\u2126), \u03b7 is the intrinsic impedance of the free space (120\u03c0\u2126), L is the antenna length, N is the number of the sections, and \u03b1 is a constant value to be calculated using the intrinsic impedance of the free space, characteristic impedance of the feed line and the antenna length. The separation between two parallel plates d(zi) is determined by an exponential function [16], so it is given by: d(zi) = a exp(bzi) (2) where a and b are constants to be determined using the separation between the plates at input d0 and output aperture dL, shown in Fig. 2(a). a = d0 b = 1 L ln ( dL d0 ) (3) To determine the plate width of the sections w(zi), the characteristic impedance of a parallel plate waveguide Z(zi), given by [21], is used: Z(zi) = d(zi) w(zi) \u03b7 (4) Design parameters of the horn section are calculated and optimized for 2\u201314GHz using Eqs. (1)\u2013(4). The length of the horn section is determined as L = 0.4\u03bb, where \u03bb is the wavelength at the lowest operating frequency and since the lowest operating frequency was selected as 2 GHz, the length of the horn section was determined as 60 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001544_download_20560_13226-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001544_download_20560_13226-Figure1-1.png", + "caption": "Figure 1. Block Diagram of the proposed ANN based energy efficiency optimization control EMDS.", + "texts": [ + " The maximum efficiency of EMDS can be achieved when the minimum input power is obtained with the constant output power required by the load. This proposed approach is based on varying the flux up to the point where the measuring input power is a minimum of one point of operation. The adaptive optimum flux value is predicted by the proposed efficiency optimization ANN based efficiency optimization controller algorithm for any different operation mode, ie, various speed and various load to obtain its optimum flux value corresponding to different cases as shown in Figure 1. The prediction of the flux value can be achieved due to the possession of the online learning ability in the proposed algorithm. The difference between the calculated input and the real input power is fed as input for the neural. [26-28] The proposed ANN based energy efficiency optimization of DTC EMDS, as shown in Figure 1, where it is targeted to maintain the fast dynamic characteristics and better response, and also aimed in getting minimum losses especially for the light load and light speed drive\u2019s operation. The proposed ANN efficiency optimization controller is shown in Figure 2. The error of input power is used as input for the proposed controller while the output of it implemented as the optimum flux reference. Figure 2. Simulink circuit for the proposed ANN efficiency optimization controller. In order to verify the effectiveness of the proposed ANN efficiency optimization controller for the DTC electric drive system, the investigations of the drive system have been carried out for different values of speed and torque" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002707_8948470_09199824.pdf-Figure34-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002707_8948470_09199824.pdf-Figure34-1.png", + "caption": "FIGURE 34. Illustration of the mapping process. The black line around the UAV represent the boundary between free and either unknown or occupied space.", + "texts": [ + " 33. It is therefore necessary to implement a mapping strategy to create a safety set envelope that the vehicle can evolve in. Note, however, that for the first iteration of the algorithm, the vehicle is not inside the safety set, so an assumption must be made that the immediate surroundings of the vehicle are safe for this 1st iteration (cf. Fig. 33). During subsequent iterations, mapping can be performed based only on new sensor data and a safety set can be progressively built as illustrated in Fig. 34. To implement this approach in a way that leverages the precision and efficiency of a point-cloud representation of the safety set, we propose an algorithm that combines pointcloud and voxel representations of the environment. A naive approach would be to just fusion the point-clouds given by the sensor, however this would only define the boundary between free and occupied space, but not between free and unknown space. One could therefore rely on a voxel-based representation of the environment, but this would come at the cost of conservatism on the location of the obstacle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004263_8600701_08725557.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004263_8600701_08725557.pdf-Figure1-1.png", + "caption": "FIGURE 1. Different winding connections in CSRM. (a) NS mode. (b) 12N mode. (c) 3N3S mode. (d) NNSS mode. (e) 6N6S mode. (f) NSSN mode.", + "texts": [ + " Six-phase SRM can be run in two-phase excitation mode and three-phase excitation mode, the poles polarities arrangements of adjacent phases in these two modes are listed, the static characteristics with different poles polarities arrangements are analyzed and compared. Different winding connections are composed by different poles polarities arrangements, the static torque generated by different winding connections is compared. The results are given and verified by the simulation and experiment on the six-phase SRM. II. WINDING CONNECTIONS AND ITS MAGNETIC DISTRIBUTION Different winding connections can result in various poles polarities arrangements, the possible connections in the six-phase 12/10 SRM are shown in figure 1. Magnetic poles polarities N and S are defined as shown in figure 1(a), for example, poles polarities of stator poles A1, B1 is N and S. To explain, the name of the winding connections are simplified. For example, NS mode is the situation when the arrangements of stator poles polarities is NSNSNSNSNSNS as shown in figure.1 (a), and the rest of the winding connections are shown in figure.1(c) \u223c figure.1 (f). Based on the difference of poles polarities arrangements in one phase, the winding connections of the conventional SRM can be divided into two types: reverse series and forward series [18], [22]. In reverse series connections, the polarity of stator poles in the same phase are the same, for example, the polarity of poles A1 and A2 in phase A is N which is shown in figure.1 (a) \u223c figure.1 (c). In forward series connections, the polarity of the poles in the same phase is different, for example, the polarity of pole A1 and A2 is N and S which is shown in figure.1 (d) \u223c figure.1 (f). In one-phase excitation mode, the magnetic fields distribution of these two kinds of winding connections are shown in figure.2 (a) and figure.2 (b), and the magnetic field distributions are different in these two winding connection types. In reverse series connection, when phase A is excited, the magnetic flux flows down the stator pole A1, due to the same polarity of poles A1 and A2, the flux through the rotor yoke and returns via the adjacent stator poles. The flux path in reverse series is short path, and that means the mutual coupling will be occurred between phases, and also, fault tolerance will be reduced", + " TNS and TNNSS are the torque in NS mode andNNSSmode, it can be seen that TNNSS is larger than TNS when the dc current in NS and NNSS mode is equal. IV. COMPARISONS OF STATIC TORQUE A. TWO-PHASE EXCITATION MODE When the SRM runs in two-phase excitation mode, the arrangements of the poles polarities in different connection modes are shown in table 2. For example, when the windings are connected in NNSS mode, the arrangements VOLUME 7, 2019 71177 of poles polarities in adjacent two phases can be NNSS and NSSN, which are shown in figure 1(d). When phase A and phase B are excited simultaneously, the polarity of four poles in these two phases is NNSS (A1 is N, B1 is N, A2 is S, B2 is S), the same to phase C and D, E and F, hence, the number of the poles polarities arrangement NNSS is three. From Table 2, it can be seen that the arrangements of poles polarities in different winding connection modes can be four kinds: NSNS, NNSS, NNNN (SSSS), and NSSN. Taking phase A and phase B as an example, in starting stage of a SRM, the motor is operated in CCC mode (current chopper control), the current of phase A and phase B can be assumed equal with constant" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000765_1740-021-01063-1.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000765_1740-021-01063-1.pdf-Figure3-1.png", + "caption": "Fig. 3 FEM Simulation: a first timestep and b last timestep", + "texts": [ + "01 mm and is therefore not represented in the results. 1 3 The main element of the numerical twin is a thermomechanical FE-simulation using LS-DYNA explicit formulation. To quicken the simulation, time scaling with a factor of two is used. The geometry and kinematics of the real machine tools have been faithfully reproduced. The tools are modeled as rigid parts using shells with a constant temperature. The inertia of the tools was determined using CAD and taken into account as well as the damping of the hydraulic system of the round roll. Figure\u00a03 presents the FE-model parts. The ring is modeled by 6500 brick elements with 8 nodes and one integration point (ELFORM 1 in LS-DYNA). The hourglassing is compensated and it has been verified that the energy dissipated by hourglassing is very low (less than 1% on average) compared to the energy dissipated by the plastic deformation. The model material in this investigation is 16MnCr5 (1.7131, AISI 5115). Determination of mechanical properties is carried out by performing compression tests on cylindrical samples at strain rates in the range of 10\u22122 to 1 s\u22121 and in a temperature range from room temperature to 1000 K" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001194_n_Systems_Latest.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001194_n_Systems_Latest.pdf-Figure1-1.png", + "caption": "Fig. 1. Normal patch antenna", + "texts": [ + " Hence in simple words patch size reduction has been a very common interesting topic among researchers [8-11]. Therefore, in this paper we have proposed a miniaturized fractal shape patch antenna with u-slots on patch and defected ground structure with good impedance bandwidth, gain and directivity. The proposed antenna is showing multi frequency response which can be used for various applications systems. II. ANTENNA DESIGN The basic patch antenna consists of patch, substrate and ground plane. The basic patch antenna with coaxial probe feed (contacting) is given in fig 1. The first important task while designing an antenna is selection of a proper substrate with proper dielectric constant. In proposed antenna design, due its cost effectiveness, moisture withstanding capabilities, FR4 (lossy) is chosen as substrate with dielectric constant of 4.3. In order to derive Patch width, following equation is used. (1). \u221a Whereas c is the speed of light in free space and .f0 is the resounding frequency and \u03b5r is the relative permittivity. In order to derive Patch length, following equation is used" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001484__EEE-THESES_1563.pdf-Figure2.21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001484__EEE-THESES_1563.pdf-Figure2.21-1.png", + "caption": "Fig. 2.21 Case 2 simulation results: SPL distribution using (a) s (12)ynq and (b) s (36)ynq . (The target region is denoted by dashed lines.)", + "texts": [ + " Simulations conducted in free field with sound speed 344c = m/s..................................................................................................61 Fig. 2.18 Case 1 simulation results: Distributions of ..................................................63 Fig. 2.19 Case 1 simulation results: SPL distributions using (a) s (9)ynq and (b) s (36)ynq . (The square target region is highlighted by dashed lines.) ..........65 Fig. 2.20 Case 2 simulation results: Distributions of ..................................................67 Fig. 2.21 Case 2 simulation results: SPL distribution using (a) s (12)ynq and (b) s (36)ynq . (The target region is denoted by dashed lines.) ...........................67 Fig. 3.1 Target region is a point. ...............................................................................75 Fig. 3.2 Illustration of the TD method for hotspot generation. 1O and 2O are the orthocenters of the array and the target region, respectively. ......................77 Fig. 3.3 Configuration for point target simulation ", + " The distributions of the gain, the average square error, the average SPL and the SPL variance with respect to the length, L are shown in Fig. 2.20 (a), (b), (c) and (d), respectively. From Fig. 2.20 (a) and (b), it can be observed that both the gain and the square error decrease with the increase of L. By setting a tolerance of * =0.1J , an optimal length * 12L = is selected by performing the procedures shown in Fig. 2.13. The resulting array patterns, correspondent to L = 12 and 36 are presented in Fig. 2.21 (a) and (b), respectively. As shown in Fig. 2.20 (c), about a 18 dB SPL difference (24.8 against 6.4 dB) in the target region can be achieved by choosing s (12)ynq over s (36)ynq . The average SPL 66 does not constantly decrease when L = 1,...,5, whereas the gain does. This is because a region with a highest gain may not correspond to a highest average SPL in the region. The TOAM property, as proven in Section 2.4.5 guarantees a decreasing gain with the increase of L. Furthermore, the target region is an acoustical hotspot (SPL higher than neighboring region) for s (12)ynq as shown in Fig. 2.21 (a), whereas it is a quiet zone for s (36)ynq as shown in Fig. 2.21 (b). In general, the observations from the simulation results are consistent with the theoretical analysis on the properties of the TOAM series expansion. The TOAM solution can be used to improve the gain for solving inverse problems. In Chapter 4, the application of the TOAM series expansion is extended to the solution of a nonlinear optimization problem in the synthesis of single look-direction and flat-top array patterns. 0 10 20 30 40 70 75 80 85 90 95 93.6 93.0 92.0 89.8 84.6 74.7 73.1 L G ai n g sy n(L ) ( dB ) 0 10 20 30 40 0 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure3.27-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure3.27-1.png", + "caption": "Figure 3.27: Designed leaky-wave antenna with a tapered starting edge of metasurface", + "texts": [ + " Compared to the classical GDS-based antenna, the GDSM-based leaky-wave antenna has about 1 dB smaller directivity and larger beam width. Figure 3.26 shows the electromagnetic field distribution in absolute value of the GDSM-based antenna at 64 GHz in the central xz-plane. The backward leakage wavefront can be well observed despite a disturbance at the feeding edge by the forward radiation of the discontinuity. Several attempts have been made to remove the undesired forward radiation from the discontinuity at the starting edge of the metasurface. One uses a tapered transition at the beginning of the metasurface, as shown in figure 3.27. The tapered transition starts with two patches, and is then made to symmetrically add one patch per side in the y-axis direction every six patches along the z-axis direction. The simulated farfield patterns are shown in figure 3.28, and the detailed parameters are shown in table 3.8. It can be observed that by making a smooth tapered transition between the excited GDS-based propagation mode and the metasurface-based propagation mode, the unwanted forward radiation is significantly reduced. Since the dielectric and metal of the transition create additional losses, the gain of the main beam is smaller compared to the original design" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002182_om_article_19326_pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002182_om_article_19326_pdf-Figure10-1.png", + "caption": "Fig. 10. a) Simulated stress analysis \u2013 verification of safety margins, b) close up of single joint", + "texts": [], + "surrounding_texts": [ + "The completed fully functional prototype retractor is shown in Figs. 1 and 2. The center main part of the handle is the main handle, the section to the left of the handle in Fig. 1 adjusts the opening angle of the tips (shown open) by rotation. The end section to the right of the handle in Fig. 1 adjusts the tip\u2019s flexion (or straightening) by rotation. The total length is about 500 mm and all metal parts are made using SUS304 stainless steel. The handle and internal control mechanisms were 3D printed from ABS resin. Fig. 11(a) and (b). shows the retractors being used to hold part of a porcine lung in place in preparation for surgery on the target tissue outlined in red. In Fig. 11(a) the target tissue is obstructed by a lung segment, in Fig. 11(b) the lung segment is retracted, and the target tissue area is clearly visible and ready for surgery. The fully functional prototype retractors were successful in carrying out this role thus validating the mechanism\u2019s functionality and dynamics in thoracic surgery. By using the multi-joint finger like articulated mechanism, the surgery was able to be carried out in an efficient and effective manner without the need for use of gauze as the mechanisms dynamics are such that they can be inherently adapted to the shape of the organ that it needs to support. Regarding evaluation of prototype laparoscopic instruments in general the current standard is the \u201cRosser station test\u201d [5], handling ergonomics in regard to dynamics confirmed by EMG [6], however in the case of retractors, mechanical simulations and actual tests in regard to fitness for given tasks are more typical [7]. \u00a9 JVE INTERNATIONAL LTD. JOURNAL OF VIBROENGINEERING. MAR 2018, VOL. 20, ISSUE 2. ISSN 1392-8716 1199 This research was overseen by Ikuo Yamamoto (Engineering) and Takeshi Nagayasu (Medical). The research was carried out by and written up by Keiko Kishikawa and Yoshihiro Kondo with the assistance of the other authors. Naoya Yamasaki facilitated the porcine experiment and Keitaro Matsumoto the initial 3D printing. The full metal forceps were arranged by Ikuo Yamamoto. All authors worked together on the conceptual design of the forceps. The English paper was checked, corrected and the revised by Murray Lawn." + ] + }, + { + "image_filename": "designv8_17_0001484__EEE-THESES_1563.pdf-Figure2.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001484__EEE-THESES_1563.pdf-Figure2.1-1.png", + "caption": "Fig. 2.1 Relationship between Cartesian and spherical coordinate systems.", + "texts": [ + " Some basic descriptions on wave field, array categories and the definition of desired array pattern synthesis are briefly presented. Wave field is the medium for signal transmission. A transfer function numerically describes the signal transmission between two points in a wave field. In the following sub-sections, the wave equations, far/near-field definitions and transfer functions are briefly reviewed. 2.1.1.1 Wave field A space-time signal is written as ( , )s tr , where r is the 3-dimensional position of observation at time t. The position, r can be represented in a coordinate system, as shown in Fig. 2.1. Cartesian and spherical coordinate systems can be denoted as ( , , )x y z and ( , , )r \u03b8 \u03c6 , respectively. \u03b8 and \u03c6 are defined as the polar angle and horizontal angle, respectively. Figure 2.1 shows the relationship between the two coordinate systems. 22 Consider a sound wave field, and assume the medium of the wave propagation is homogeneous, dispersion-free and lossless. Homogeneity assures a constant propagation speed throughout space and time. Dispersion happens in a nonlinear medium, where the wave interacts with the medium, and thus changes its amplitude related to its frequency contents. A lossless medium implies that the medium does not influence the amplitude attenuation of the propagating wave" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001143_23_2_pag_55_vela_dg_-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001143_23_2_pag_55_vela_dg_-Figure1-1.png", + "caption": "Fig. 1. The constructive-functional scheme of the prehension device without the workpiece, after [13].", + "texts": [ + " It presents a series of advantages, as follows: - simple construction; - compact design with low weight; - small size; - reduced kinematic errors; - low electrical power consumption; - usable in the construction of devices for workpieces orientation and fixing. This paper shows the way to determine the actuating force of the SMA element required for prehension of a workpiece, knowing the weight of the workpiece and the dimensions of the prehension device elements. 2. The Constructive-Functional Scheme of the Prehension Device The device variant analyzed involves the replacement of the classic motor (electric, hydraulic, etc.) with an SMA actuator. The constructive-functional scheme of the device is shown in Fig. 1 and Fig. 2, in the variant without workpiece (Fig. 1) and in the variant with the prehensed workpiece (Fig. 2). The SMA actuator is solidarized with the fixed element (0). The shape-memory alloy element (1), a cylindrical helical spring, is axially deformed by expansion or compression through a well-defined operating program, developing the actuating force Fa and Kinetostatics of a Robotic Prehension Device Driven by Shape Memory Alloy Elements Robotica Management, 28-2 / 2023 56 the prehension force F2 of the fingers (6), and (7) respectively. The return to the initial position of the SMA spring and the action of the elastic forces (Fspr) of the springs (4) and (5) causes the return of the actuator's driving elements (2) and (3), of the fingers (6) and (7), releasing the working object (10)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003835_f_version_1676453559-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003835_f_version_1676453559-Figure8-1.png", + "caption": "Figure 8. Extension of protected powerplant surfaces (mm).", + "texts": [ + " Downstream, after ATR exhaust flow injection, the remaining part of the common nozzle received an average flux of 500 kW/m2. 4.2.2. Powerplant Geometrical Interfaces The extension of protection by means of cooling jacket includes part of the combustor (from hydrogen injector position towards downstream), the DMR nozzle and part of the common nozzle. This means that the assembly including the combustor and common nozzle is around 15 m, while 39 m out of 42 for the common nozzle are equipped with the cooling jacket. The overall dimensions are shown within Figure 8. The sections view represents the DMR combustor (constant section) and the interface between the DMR nozzle outlet and common nozzle inlet, as well as the common nozzle towards the outlet (where protection ends). The design of the geometrical features of the cooling jacket, originally proposed by [24] and reviewed in [25], led to the layout shown in Figure 9 for the first exchanger (similar for the second one). For the combustor and the DMR nozzle, each segment has an average width (a) of about 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000681_230-1-PB.pdf_id_6201-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000681_230-1-PB.pdf_id_6201-Figure1-1.png", + "caption": "Fig. 1. Compliance addition in a hydraulic force system using a) spring and b) HVE hoses", + "texts": [ + " Direct contact between the cylinder and the load would cause the entire system to be stiffer, and even a small control signal sent to a servovalve could generate large force variations due to the high open-loop gain. Reference [21] emphasizes the advantages of including a spring in a force control system. In [8], the procedure of the spring selection for the SEA was improved by using two types of linear actuators: an electromechanical and a hydraulic actuator. In both cases, the introduction of a compliant element between the actuator and the load decreases the output impedance. Additionally, the measurement of the spring compression is used to calculate indirectly the force applied over the load (Fig. 1a). The use of the spring limits the rate of the force applied by the hydraulic actuator, ensuring some degree of isolation between the hydraulic system and the movement of the load (environment) and maintaining a stable and robust applied force. The use of a hydraulic compliant component instead of a spring is proposed. Fig. 1b shows an option using high volumetric expansion (HVE) hoses between the servovalve and cylinder. The use of accumulators instead of hoses could also be possible for similar purposes. Two mathematical models are explained in this section: a nonlinear model, which is used for simulation in order to obtain force responses; and a linear model, used for the controller design and hose sizing. Both models are based on Fig. 1b. 2.1 Nonlinear Modelling of the Hydraulic System 2.1.1 Servovalve Modelling In the design of the hydraulic circuit, a symmetrical servovalve is used (Fig. 2) [22]. The dynamic relationship between the input control signal (UC) and the spool displacement, represented by an equivalent voltage (UCsp), can be approximated by a secondorder function: U U t U t UC nv Csp v nv Csp Csp d d d d = + + 1 2 2 2 2\u03c9 \u03be \u03c9 , (1) where \u03c9nv is the natural frequency of the valve and \u03bev represents the damping ratio of the valve", + " (22)) and the desired Lho. After that, the proportional gain to achieve the required closed loop response can be calculated by isolating it in Eq. (21). The use of a proportional controller in this design stage allows obtaining a very good approximation for the required hydraulic stiffness. A specific controller design and the system dynamic analysis using a nonlinear model can then be carried out as shown in Sections 5 and 6. 3.3 Example of Hose Selection Consider a Pure Hydro-Elastic Actuator (PHEA), as shown in Fig. 1b, able to apply forces up to 9000 N. The desired tracking control ratio is specified according to Eq. (20) with a time constant \u03c4d equal to 50 ms. The system parameters are according to the Appendix, with KqU0 and Kc0, calculated at null operating based on Eqs. (11) and (12). Considering the maximum flow rate equal to the test rig pump supply (1.6\u00d710\u20134 m3/s) and fluid velocity in the line equal to 2 m/s, a commercial hose diameter of 12.7 mm (1/2 in) was selected using Eq. (22). Analysing HVE hose catalogues, the EATON Synflex \u00ae 3130-08 was selected [25]", + " The hose volumetric expansion is 1.56\u00d710\u20135 m3/m @ 7\u00d7106 Pa (4.7 cc/ft @ 1000 psi), resulting in a static bulk modulus (\u03b2hoSS) of 6.36\u00d7107 Pa. Based on Eq. (26), an r\u03b2 value equal to 5 was considered. As discussed before, the system performance must be determined by a trade-off between KH, Kp, and Lho. In this study, a Lho equal to 1.5 m was specified and using Eq. (28) the resulting KH is 2.24\u00d7106 N/m and, based on Eq. (21), Kp is 2.7 \u00d710\u20134. The hydraulic force control system according to the configuration shown in Fig. 1b was assembled in a test rig as shown in Fig. 4. The system comprises two hoses interconnecting each cylinder chamber with the servovalve. A load cell is fixed at the cylinder rod, and it will be in contact with a metal block attached to the test rig frame. The parameter values of this experimental setup are presented in the Appendix. For the QFT controller design and dynamic simulation, KS equal to 2\u00d7107 N/m was used, corresponding to the 585Force Control of Hydraulic Actuators using Additional Hydraulic Compliance equivalent stiffness resulting from the load cell and environment compliances" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-FigureB.1-1.png", + "caption": "Figure B.1: Side force at vertical tail in rolling flight (26)", + "texts": [ + "7: Vertical/horizontal tail\u2019s drag coefficient vs. angle of attack .............................. 94 Figure A.8: Vertical/horizontal tail\u2019s lift coefficient vs. angle of attack ................................. 94 Figure A.9: Vertical/horizontal tail\u2019s pitching moment coefficient vs. angle of attack .......... 95 Figure A.10: Stators\u2019 drag coefficient vs. angle of attack....................................................... 96 Figure A.11: Stators\u2019 rolling moment coefficient vs. angle of attack ..................................... 96 Figure B.1: Side force at vertical tail in rolling flight (26) ....................................................... 99 Figure B.2: Change in vertical tail's angle of attack due to yaw rate (26) ............................ 100 Figure B.3: Change in wing's angle of attack in rolling flight (26) ........................................ 101 Figure B.4: Change in wind speed due to yaw rate (26) ...................................................... 105 x LIST OF TABLES Table 3.1: Flight conditions for altitude-hold mode and climbing mode ", + "14) 99 Side force derivatives can be derived directly in body axes system, but other derivatives need to be derived in stability axes system first, then transformed to body axes system because the drag and lift data are involved in their derivation. It is assumed that the side force due to roll rate perturbation and yaw rate perturbation is contributed by the vertical tail only. If the vehicle experiences a roll rate perturbation p in body axes system, let\u2019s consider a chord-wise strip element of the vertical tail, with thickness of h\u2202 at coordinate h measured from the body x axis as shown in Figure B.1 below: When there is a roll rate disturbance p applying to the aircraft, the strip element will have a lateral velocity component ph . The resultant velocity V is at angle of attack \u03b1 \u2032 relative to the vertical tail: tan e ph U \u03b1 \u03b1\u2032 \u2032\u2248 = (B.15) 100 The change in angle of attack causes a change in vertical tail lift, which is resolved into a lateral force increment on this strip element. Sum of all these force increments is the resultant side force due to roll rate generated by the vertical tail" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004713_2_7_2_ajme-2-7-2.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004713_2_7_2_ajme-2-7-2.pdf-Figure2-1.png", + "caption": "Figure 2. Model of the operating machine\u2019s arm", + "texts": [ + " the power of a driven aggregate in the chosen tilting mode of the sheet metal coils, and the kinematics values of individual mechanism constituents. The strength calculation of the industrial operating machine\u2019s arm is described in detail in the following part. Machine\u2019s Arm The strength calculation was performed in two stages. In the first stage, the main parameters of the operating machine\u2019s arm parts were designed on the basis of preliminary strength calculations, and approximate and simpler, single calculation methods were used. The model of the operating machine\u2019s arm design is presented in Figure 2 (CAD model). The arm is designed as a weld of steel sheet parts. There are 15 equations (6 geometrical equations, 3 differential equilibrium equations, 6 constitutional equations) to find 15 searched functions (3 displacement functions, 6 functions of the component of strain tensor, 6 functions of the component of stress tensor) in continuum mechanics. Moreover, boundary conditions, namely geometrical, that determines the displacement values on the parts of the body borders and force boundary conditions that determine the stress and pressure values on another part of the body, have to be satisfied" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001369_9fb40a0e36ab0a7e.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001369_9fb40a0e36ab0a7e.pdf-Figure1-1.png", + "caption": "Figure 1. Schematic diagram of the developed prototype.", + "texts": [ + " Kachman and Smith (1995) stated alternative measurements of accuracy in seed placement for seeders. These measurements based on the theoretical seed spacing and include the multiple index, miss index, quality of feed index and the precision in spacing. They recommended using these measurements for summarizing Misr J. Ag. Eng., October 2009 1755 the uniformity of seeder metering rather than meaning or sampling coefficient of variation. MATERIALS AND METHODS Prototype Description A developed single precision vacuum seeder prototype (Figure 1) consists of the following components. 1- seed box The seed box (Figure 2a) has a trapezoidal shaped in the lower part and a rectangular shaped at the upper part. The lower part is inclined 63\u00b0 from the vertical direction. The shape of the seed chamber is triangular shape and it designed to be connected with the seed box for receiving the seeds from seed box and transfer the seeds to the holes on the seed plate. Vertical seed plate and the plate of vacuum flow Three seed plates (Figure 2b) were fabricated with different hole diameters", + ", October 2009 1756 Two rigid brush-off devices were fabricated from rubber material and fixed in the back of the seeder case prated 2 mm from the pitch circle diameters of seed plate for the two rows. The two brush-off devices were curved shape with the radius of curvatures of 88 and 76 mm (Figure 2d). The dimensions of the brush-off device were 70, 75 mm length and 5 mm thickness for the first and the second rows, respectively. Depth control device The depth control device consists of two press wheels with a linkage between them. The diameter of both press wheels is 280 mm. The planting depth is changing by means of a rotating locking mechanism (Figure 1) attached with the front and rear press wheels. Furrow opener A runner-type opener (Figure 2e) with two outlets was used to enable the developed prototype to plant two rows instead of one row. The cutting edge of the opener is 20 mm width and 114 mm length. The total length of the furrow opener was 195 mm and 110 mm height. Blower (vacuum pump) The blower (vacuum pump) was developed according to the design of the Keverneland vacuum seeder blower. It was fabricated from the local plain carbon steel with 3 mm thickness" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003156_1_files_28155276.pdf-Figure3.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003156_1_files_28155276.pdf-Figure3.4-1.png", + "caption": "Figure 3.4: Feeding side of wire movement system", + "texts": [ + " There are also three guiding and tensioning pulleys, as well as an AMACOIL AKI3-15-6 traversing unit and a Shimpo DT-105A tachometer to monitor the wire speed. The pulling system is featured in Figure 3.3. The payoff side has a single spool with a friction brake on it to give appropriate wire tension and ensure it does not freewheel from inertia when the system stops. There is also a Cometo AS574 single plane wire straightener and two guide pulleys to control the entry into the wire straightener. The wire payoff system is featured in Figure 3.4. The parameters of interest in this study are the wire temperature at the bed inlet and outlet, the bed temperature, the wire speed and the fluidizing velocity. There are three systems at work to monitor these parameters. The temperature of the wire is monitored with two Anritsu MW-44K-TC2-ANP moving wire probes, while the bed temperature is monitored by a standard immersion type thermocouple. These three instruments are connected to a Data Translation DT9828 DAQ, which obtains and transmits the values to a computer for logging" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001698_O201411560018329.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001698_O201411560018329.pdf-Figure8-1.png", + "caption": "Fig. 8. Surface current distributions at (a) 2.42 GHz and (b) 5.63 GHz.", + "texts": [ + " The second resonant mode has an impedance bandwidth of 1,020 MHz (5.08\u20136.1 GHz), which satisfies the required bandwidth of the 5.2/5.8-GHz WLAN bands. Clearly, the design prototype of the proposed antenna has sufficient bandwidth to cover the needs of the 2.4- and 5- GHz WLAN bands (2.4\u20132.484 GHz and 5.15\u20135.825 GHz, respectively). Theoretically, HFSS was used to evaluate and verify the two resonant frequencies of 2.42 and 5.63 GHz, which mainly depended on the lengths of the open-ended circular ring. Fig. 8(a) and (b) show the surface current density excitations along the open-ended circular ring antenna in the cases of the two resonant frequencies of 2.42 and 5.63 GHz, respectively. As shown in Fig. 8(a), the 2.4-GHz band surface current density excitations along the open-ended circular ring was observed when the resonant frequency was 2.42 GHz. Thus, it is implied that the excitation of the 2.4- GHz bands is mainly contributed by the open-ended circular ring. As shown in Fig. 8(b), however, larger surface current density excitations flowed along the bottom of the openended circular ring antenna when the resonant frequency was 5.575 GHz. As we can see in this figure, the 5-GHz band is more strongly excited than the 2.4-GHz band in the case of the open-ended circular ring antenna. Fig. 9 shows the measured 2D far-field radiation patterns in the E-plane (x-z plane) and the H-plane (y-z plane) at the 2.4- and 2.45-GHz bands. Fig. 10 shows the measured 2D far-field radiation patterns in the E-plane (x-z plane) and the H-plane (y-z plane) at the 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000056_tation-pdf-url_54247-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000056_tation-pdf-url_54247-Figure13-1.png", + "caption": "Figure 13. Laser sensors for semiautomatic system. (a) Side view. (b) Front view.", + "texts": [ + " The add-on mechanism, which includes the active-caster and the reconfigurable link mechanism with a linear actuator, is attached on the back of a frame of a manual wheelchair. The stroke of the linear actuator is 200 mm and the maximum power is 144 W. To drive the active-caster, two motors are installed, whose capacities are 200 W each. The diameter of the drive wheel is 130 mm with 45 mm caster offset. Two sensors (LRF) are attached on the side of the wheelchair frame to measure the step whose locations are illustrated in Figure 13. For maneuvering the wheelchair around normal environments, a user can operate the wheelchair by using a joystick on an arm rest as same as in the standard electric wheelchair. measured step height and the distance detected by LRFs. Five-Wheeled Wheelchair with an Add-On Mechanism and Its Semiautomatic... http://dx.doi.org/10.5772/67558 37 We propose an add-on electric drive system with a reconfigurable link mechanism for a manual wheelchair. We also propose a semiautomatic system for reducing the user effort to operate a wheelchair to surmount a step" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004930_O201024441466953.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004930_O201024441466953.pdf-Figure7-1.png", + "caption": "Fig. 7 Flux paths in radial HMB", + "texts": [], + "surrounding_texts": [ + "\uae40 \uc6b0 \uc5f0 \u2024\uc774 \uc885 \ubbfc \u2024\ubc30 \uc6a9 \ucc44 \u2024\uae40 \uc2b9 \uc885\n722/\ud55c\uad6d\uc18c\uc74c\uc9c4\ub3d9\uacf5\ud559\ud68c\ub17c\ubb38\uc9d1/\uc81c 20 \uad8c \uc81c 8 \ud638, 2010\ub144\n\uc815\ud655\ud55c \ud574\uc11d\uc744 \ud1b5\ud558\uc5ec \uc124\uacc4 \ubcc0\uc218\ub97c \uc870\uc815\ud558\ub294 \uacfc\uc815 \uc758 \ubc18\ubcf5\uc774 \ud544\uc694\ud558\ub2e4. \uc774\ub97c \uc704\ud558\uc5ec 3\ucc28\uc6d0 FEM \ud574\uc11d \uc18c\ud504\ud2b8\uc6e8\uc5b4\uc778 Maxwell v.11 3D\ub97c \uc774\uc6a9\ud558\uc600\ub2e4. \ud574 \uc11d \uacb0\uacfc, \ub204\uc124 \uc790\uc18d\uacfc \ud504\ub9b0\uc9d5 \ud6a8\uacfc \ub4f1, \uc790\uae30\ud68c\ub85c \ud574\n\uc11d\uc5d0\uc11c \ubb34\uc2dc\ub418\uc5c8\ub358 \ud6a8\uacfc\ub4e4\uc5d0 \uc758\ud574 \uc790\uc18d\ubc00\ub3c4\uac00 \uc57d 15 % \ub0ae\uc740 \uac12\uc73c\ub85c \uc5bb\uc5b4\uc84c\ub2e4. \uc774\ub97c \uc99d\uac00\uc2dc\ud0a4\uae30 \uc704\ud574 \uc11c, \uac01 \uacf5\uadf9\uc758 \ud06c\uae30\ub294 \uc55e \uc808\uc5d0\uc11c \uc120\uc815\ud55c \uac12\uc744 \uc720\uc9c0 \ud55c \ucc44, \uc601\uad6c\uc790\uc11d \ubc0f \ucf54\uc5b4\uc758 \uba74\uc801\uc744 \uc99d\uac00\uc2dc\ucf30\ub2e4. \ucd5c\uc885 \uc124\uacc4\uac12\ub4e4\uc744 Table 1\uc5d0 \uc815\ub9ac\ud558\uc600\ub2e4. Table 1\uc758 \uac12\ub4e4\uc744 \uc774\uc6a9\ud55c FEM \ud574\uc11d \uacb0\uacfc\uc5d0\uc11c, \uacf5\uadf9 gap1\uc5d0\uc11c\uc758 \uc790\uc18d \ubc00\ub3c4 B1\uc740 0.788 T\uc774\uace0, gap2\uce21\uc758 \uc704\ucabd \uacf5\uadf9\uc5d0\uc11c\uc758 \uc815\uc0c1\uc0c1\ud0dc \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d \ubc00\ub3c4 B2\ub294 0.478 T, \uc544\ub798\ucabd \uacf5\uadf9\uc758 B2\ub294 0.399 T\uc774\uc5c8\ub2e4. \ucc38\uace0\ub85c, \ub3d9\uc77c\ud55c \uac12\ub4e4\uc744 \uc2dd (2)\uc640 (3)\uc5d0 \ub123\uc5b4 \uacc4\uc0b0\ud55c \uacb0\uacfc\ub294 B1\uac00 0.898 T, B2\ub294 0.542 T\uc774\uc5c8\ub2e4. \ud55c\ud3b8, gap1\uc5d0\uc11c\uc758 \uc601\uad6c\uc790\uc11d \uc790 \uae30\ub825\uc740 1,466 N\uc73c\ub85c\uc11c \uc790\uc911(140 kgf)\ubcf4\ub2e4 \uc57d 6.8 %\n\ud070 \uac12\uc774\ub2e4. \uc774\ub294 \uc2e4\uc81c \uc81c\uc791\ub41c \uc2dc\uc2a4\ud15c\uc5d0\uc11c \ubc1c\uc0dd\ud558\ub294 \ud798\uc774 FEM \uacb0\uacfc\ubcf4\ub2e4 \ub2e4\uc18c \uc791\uac8c \uc5bb\uc5b4\uc9c0\ub294 \uacbd\ud5d8\uc744 \ubc18 \uc601\ud55c \uac83\uc774\ub2e4. \ucd5c\uc885 \uc124\uacc4\ub41c \ucd95 \ubc29\ud5a5 HMB\uc5d0 \ub300\ud558\uc5ec, \ud68c\uc804\uccb4\uc758\n\ucd95 \ubc29\ud5a5 \ubcc0\uc704 \ubc0f \uc81c\uc5b4 \uc804\ub958\uc758 \ubcc0\ud654\uc5d0 \ub530\ub978 \uc804\uc790\uae30 \ub825\uc758 \ubcc0\ud654\ub97c FEM\uc744 \uc774\uc6a9\ud558\uc5ec \uc608\uce21\ud55c \uacb0\uacfc\ub97c Fig. 5 \uc640 6\uc5d0 \ub3c4\uc2dc\ud558\uc600\ub2e4. \uadf8\ub9bc\uc5d0\uc11c \ubcf4\ub4ef\uc774 \uacc4\uc0b0 \uacb0\uacfc\ub294 \uc120\ud615\uc801\uc73c\ub85c \uadfc\uc0ac\uac00 \uac00\ub2a5\ud55c\ub370, \ub450 \uc9c1\uc120\uc758 \uae30\uc6b8\uae30\ub294\n\uac01\uac01 \uc704\uce58\uac15\uc131\uacc4\uc218\uc640 \uc804\ub958\uac15\uc131\uacc4\uc218\ub85c \uc815\uc758\ub418\ub294 \uc0c1 \uc218\ub4e4\ub85c\uc11c \uadf8 \uac12\uc740 \uac01\uac01 1.801\u00d7106 N/m\uc640 315.9 N/A\ub85c \uacc4\uc0b0\ub418\uc5c8\ub2e4. \ub450 \uadf8\ub9bc\uc5d0\uc11c \ub098\ud0c0\ub0b8 \ud798\uc5d0\ub294 gap1\uc5d0\uc11c\uc758 \uc790\uae30\ub825\uc774 \ud3ec\ud568\ub418\uc5b4 \uc788\uae30\uc5d0 \ubcc0\uc704\uc640 \uc804\ub958 \uac00 \uc5c6\ub294 \uc0c1\ud0dc\uc5d0\uc11c \ubc1c\uc0dd\ud558\ub294 1,466 N\uc774 \uae30\uc900\uc774 \ub418\uc5c8 \ub2e4. \uc798 \uc54c\ub824\uc9c4 \ubc14\uc640 \uac19\uc774, \uc704\uc758 \uc704\uce58\uac15\uc131\uacc4\uc218\ub294 \ubd88 \uc548\uc815\ud55c \uac15\uc131\uc774\ub2e4. \ud53c\ub4dc\ubc31 \uc81c\uc5b4\uae30\ub97c \ud3ec\ud568\ud55c \ud3d0\ub8e8\ud504\n\uc2dc\uc2a4\ud15c\uc758 \uc548\uc815\ub41c \uac15\uc131\uacc4\uc218\ub294 \ud53c\ub4dc\ubc31 \uc81c\uc5b4 \uc774\ub4dd\uc5d0 \ub530\ub77c \uc88c\uc6b0\ub418\uc9c0\ub9cc, \ucd5c\ub300 \ubcc0\uc704 0.3 mm\uc77c \ub54c \ucd5c\ub300 \uc804 \ub958 5 A\uac00 \ud750\ub978\ub2e4\uace0 \uac00\uc815\ud558\uba74, \ub2e4\uc74c\uacfc \uac19\uc774 \ub300\ub7b5 \ucd94 \uc815\ud560 \uc218 \uc788\ub2e4.\n6 3\n6\n5315.9 1.801 10 0.3 10 3.464 10 (N/m) K \u2212= \u00d7 \u2212 \u00d7 \u00d7 = \u00d7 (10)\n\uadf8\ub7ec\uba74, \ud68c\uc804\uccb4\uc758 \ucd95 \ubc29\ud5a5 \uace0\uc720\uc9c4\ub3d9\uc218\ub294 \uc57d 24.5 Hz\ub85c \uc608\uce21\ub41c\ub2e4. \uc81c\uc5b4\uae30 \uc124\uacc4 \ubc0f \uc2dc\uc2a4\ud15c \ub3d9\ud2b9\uc131\uc5d0 \uad00\ud55c \uc790\uc138\ud55c \ub0b4\uc6a9\uc740 \ud6c4\uc18d \ub17c\ubb38\uc5d0 \uae30\uc220\ud558\uae30\ub85c \ud55c\ub2e4.\n3. \ubc18\uacbd \ubc29\ud5a5 HMB \uc124\uacc4\n3.1 \uad6c\uc870 \ubc0f \uc6d0\ub9ac Fig. 7\uc740 \uc774 \ub17c\ubb38\uc5d0\uc11c \uc124\uacc4\ub41c \ubc18\uacbd \ubc29\ud5a5 HMB\uc758 \uad6c\uc870 \ubc0f \uc790\uc18d \uacbd\ub85c\ub97c \ub098\ud0c0\ub0b8\ub2e4. \uc774\uc640 \uac19\uc740 \uad6c\uc870\ub294 \uc798 \uc54c\ub824\uc9c4 \ud638\ubaa8\ud3f4\ub77c(homopolar)\ud615 HMB(3)\ub85c\uc11c \uc678\uc804 \ud615(outer rotor type)\uc774\uace0 \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\uc744 \uc0dd\uc131\ud558\ub294 \uc601\uad6c\uc790\uc11d\uc774 \ud68c\uc804\uccb4 \uce21\uc5d0 \ub07c\uc6cc\uc838 \uc788\ub294 \uacbd\uc6b0\uc774\ub2e4. \ub3d9 \uc77c\ud55c \ucf54\uc77c\uc774 \uac10\uae34 4\uac1c\uc758 \ucf54\uc5b4\uac00 90\u00b0 \uac04\uaca9\uc73c\ub85c \ubc30\uce58 \ub418\uc5b4 \uc788\ub294 \uace0\uc815\uc790 \uc8fc\uc704\uc5d0 \ub9c1(ring) \ud615\uc0c1\uc758 \ud68c\uc804\uc790\uac00 \uc788\ub294 \uad6c\uc870\uac00 \ub450 \uce35\uc744 \uc774\ub8e8\uace0 \uc788\ub294\ub370, \ub450 \ud68c\uc804\uc790 \uc0ac \uc774\uc5d0\ub294 \ucd95 \ubc29\ud5a5\uc73c\ub85c \uc790\ud654\ub41c \uc601\uad6c\uc790\uc11d\uc774 \ub07c\uc6cc\uc9c0\uace0, \ub450 \uace0\uc815\uc790\ub294 \uc790\uc131\uccb4 \uc7ac\uc9c8\uc758 \uc911\uc2ec\ucd95\uc73c\ub85c \uc5f0\uacb0\ub41c \uad6c \uc870\uc774\ub2e4. \uadf8\ub7ec\uba74, \uc601\uad6c\uc790\uc11d\uc5d0\uc11c \ubc1c\uc0dd\ud55c \ubc14\uc774\uc5b4\uc2a4 \uc790 \uc18d\uc740 \uadf8\ub9bc\uc5d0\uc11c \uc2e4\uc120\uc73c\ub85c \ud45c\uc2dc\ub41c \u2018\uc0c1\uce35 \ud68c\uc804\uc790 4", + "\ud50c\ub77c\uc774\ud720 \uc5d0\ub108\uc9c0 \uc800\uc7a5\uc7a5\uce58\ub97c \uc704\ud55c \uc800 \uc804\ub825\uc18c\ubaa8 \ud558\uc774\ube0c\ub9ac\ub4dc \ub9c8\uadf8\ub124\ud2f1 \ubca0\uc5b4\ub9c1\uc758 \uc124\uacc4\n\ud55c\uad6d\uc18c\uc74c\uc9c4\ub3d9\uacf5\ud559\ud68c\ub17c\ubb38\uc9d1/\uc81c 20 \uad8c \uc81c 8 \ud638, 2010\ub144/723\n\uac1c\uc758 \uacf5\uadf9 4\uac1c\uc758 \uc0c1\uce35 \uace0\uc815\uc790 \ucf54\uc5b4 \uc911\uc2ec\ucd95\n4\uac1c\uc758 \ud558\uce35 \uace0\uc815\uc790 \ucf54\uc5b4 4\uac1c\uc758 \uacf5\uadf9 \ud558\uce35 \ud68c\uc804\uc790 \uc601\uad6c\uc790\uc11d S\uadf9\u2019\uc758 \uacbd\ub85c\ub97c \uac16\ub294\ub2e4. \ubc18\uba74\uc5d0 \ucf54\uc77c\uc5d0 \uc758\ud55c \uc81c\uc5b4 \uc790\uc18d\uc758 \uacbd\uc6b0\uc5d0\ub294, \uc11c\ub85c \ubc18\ub300\ubc29\ud5a5\n\uc5d0 \uc704\uce58\ud55c \ucf54\uc77c\ub4e4\uc774 \ub3d9\uc77c\ud55c \ubc29\ud5a5\uc73c\ub85c \uc790\uc18d\uc744 \uc0dd\uc131 \ud558\ub3c4\ub85d \uc5f0\uacb0\ub418\uc5b4 \uc788\uc5b4\uc11c, Fig. 7\uc5d0\uc11c \uc810\uc120\uc73c\ub85c \ud45c\uc2dc \ub41c \ubc14\uc640 \uac19\uc774, \u2018\ud55c \ucabd \ucf54\uc5b4 \uacf5\uadf9 \ud68c\uc804\uc790(\uc591\ucabd \uc73c\ub85c \ubc18\uc6d0\uc744 \uadf8\ub9ac\uba70 \ubc18\ub300\ud3b8\uc73c\ub85c \uc774\ub3d9) \uacf5\uadf9 \ubc18\ub300\ucabd \ucf54\uc5b4 \uace0\uc815\uc790 \uc911\uc2ec\u2019\uc758 \uacbd\ub85c\ub97c \uac16\ub294\ub2e4. \uc0c1\n\uce35\uacfc \ud558\uce35\uc758 \uc81c\uc5b4\uc790\uc18d\uc758 \uacbd\ub85c\ub294 \ub3c5\ub9bd\uc801\uc774\uba70 \ubc29\ud5a5\uc740 \uc11c\ub85c \ubc18\ub300\uc774\ub2e4. \uc774\ub85c\uc368, \uc0c1\ud558\uce35 \uacf5\ud788, \ud55c \ucabd \uacf5\uadf9\uc5d0\n\uc11c\ub294 \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\uacfc \uc81c\uc5b4 \uc790\uc18d\uc758 \ubc29\ud5a5\uc774 \ub3d9\uc77c\ud558\n\uace0 \ubc18\ub300\ucabd \uacf5\uadf9\uc5d0\uc11c\ub294 \ub450 \uc790\uc18d\uc758 \ubc29\ud5a5\uc774 \ubc18\ub300\uac00 \ub41c \ub2e4. \uc608\ub97c \ub4e4\uc5b4, Fig. 7\uc5d0\uc11c \uc88c\uce21\uc758 \uacf5\uadf9\uc5d0\uc11c\ub294 \ub450 \uc790\n\uc18d\uc758 \ubc29\ud5a5\uc774 \uc77c\uce58\ud558\uace0 \uc6b0\uce21 \uacf5\uadf9\uc5d0\uc11c\ub294 \ubc18\ub300 \ubc29\ud5a5 \uc774 \ub418\ubbc0\ub85c, \uc88c\uce21 \uacf5\uadf9\uc5d0\uc11c\uc758 \uc804\uc790\uae30\ub825\uc774 \uc99d\uac00\ud558\uc5ec\n\ud68c\uc804\uccb4\ub294 \uc6b0\uce21(+Y\ubc29\ud5a5)\uc73c\ub85c \uc774\ub3d9\ud55c\ub2e4. \uc774\uc640 \uac19\uc774, \uc81c\uc5b4 \uc804\ub958\uc758 \ubc29\ud5a5\uacfc \ud06c\uae30\ub97c \uc870\uc808\ud558\uc5ec \uc591\ucabd \uacf5\uadf9\uc5d0\n\uc11c\uc758 \uc790\uc18d\uc758 \ud06c\uae30\ub97c \uc81c\uc5b4\ud568\uc73c\ub85c\uc368 \ud68c\uc804\uccb4\ub97c \uc911\uc2ec \uc704\uce58\uc5d0 \ubd80\uc0c1\uc2dc\ud0ac \uc218 \uc788\ub2e4. 3.2 \uc790\uae30\ud68c\ub85c \ud574\uc11d \ubc0f \uc124\uacc4 \ubcc0\uc218 \uc120\uc815 \ubc18\uacbd \ubc29\ud5a5 HMB\uc758 \uc124\uacc4\uacfc\uc815\uc740 \ud68c\uc804\uccb4 \uc790\uc911\uc744 \uac10 \ub2f9\ud558\ub294 \uc815\uc801\uc778 \ud798\uc5d0 \ub300\ud55c \uace0\ub824\ub9cc \uc81c\uc678\ud558\uba74 Fig. 3\uacfc \uc720\uc0ac\ud558\ub2e4. Fig. 8(a)\ub294 \uc601\uad6c\uc790\uc11d\uc5d0 \ub300\ud55c \uc790\uae30\ud68c\ub85c\uc774 \ub2e4. \uc815\uc0c1 \uc0c1\ud0dc\uc5d0\uc11c \ud558\ub098\uc758 \uace0\uc815\uc790 \ucf54\uc5b4\ub97c \uc9c0\ub098\ub294 \ubc14 \uc774\uc5b4\uc2a4 \uc790\uc18d\uc740 \ub2e4\uc74c\uacfc \uac19\uc774 \uc5bb\uc5b4\uc9c4\ub2e4.\n2 4 mr\nc r mr\nR R R \u03c6 \u03c6= +r (11)\n\uc5ec\uae30\uc11c, \ubc18\uacbd \ubc29\ud5a5 \ub0b4\ubd80\uc800\ud56d Rmr\uacfc \ud558\ub098\uc758 \ucf54\uc5b4 \uacf5 \uadf9\uc5d0\uc11c\uc758 \uc790\uae30\uc800\ud56d Rr\uc740\n0\nmr mr\nmr\nlR A\u03bc = , 0 r r r gR A\u03bc = (12)\n\uc640 \uac19\uc774 \ud45c\ud604\ub41c\ub2e4. lmr\uacfc Amr\uc740 \ubc18\uacbd\ubc29\ud5a5 HMB\uc758 \uc601\uad6c\uc790\uc11d \uae38\uc774\uc640 \ub2e8\uba74\uc801\uc774\uace0, gr\uc740 \uacf5\uadf9\uc758 \ud06c\uae30, Ar \uc740 \ucf54\uc5b4 \ud558\ub098\uc758 \ub2e8\uba74\uc801\uc774\ub2e4. \uadf8\ub7ec\uba74, \uacf5\uadf9\uc5d0\uc11c\uc758 \ubc14 \uc774\uc5b4\uc2a4 \uc790\uc18d\ubc00\ub3c4 B\ub294 \uc2dd (13)\uacfc \uac19\uc774 \uc720\ub3c4\ub41c\ub2e4.\n1 2 4 c r rr\nmr mr\nB B g AA l A\n\u03c6 = = \u22c5\n+ r\n(13)\n\ucd95 \ubc29\ud5a5 HMB\uc5d0\uc11c\uc640 \ub9c8\ucc2c\uac00\uc9c0\ub85c \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d \ubc00\ub3c4\uac00 \uc57d 0.5 T\uac00 \ub418\ub3c4\ub85d \ubcc0\uc218\ub4e4\uc744 \uc124\uc815\ud55c\ub2e4. \uba3c\uc800, \uacf5\uadf9\uc740 0.8 mm\ub85c \ud558\uc600\uace0, \uc601\uad6c\uc790\uc11d\uc758 \ub192\uc774\ub294 \uc0c1\ud558 \uce35 \ucf54\uc5b4 \uc0ac\uc774\uc758 \ucf54\uc77c \uad8c\uc120 \uacf5\uac04\uc744 \uace0\ub824\ud558\uc5ec 18 mm \ub85c \uc815\ud558\uc600\ub2e4. \uc601\uad6c\uc790\uc11d\uc758 \ub192\uc774\uac00 \ub108\ubb34 \ud06c\uba74 \uc0c1\ud558 \ucf54\n\uc5b4 \uac04\uaca9\uc774 \uc99d\uac00\ud558\uc5ec \ucd95\uc758 \uae30\uc6b8\uc5b4\uc9d0 \uac70\ub3d9\uc758 \uc81c\uc5b4\uc5d0 \ubd88\ub9ac\ud558\uace0, \ub108\ubb34 \uc791\uc73c\uba74 \uc0c1\ud558 \ucf54\uc5b4 \uc0ac\uc774\uc758 \ub204\uc124 \uc790\uc18d \uc774 \uc99d\uac00\ud55c\ub2e4. \ucf54\uc5b4\uc758 \ub2e8\uba74\uc801 Ar\uc740 \ubc18\uacbd\ubc29\ud5a5 \ucd5c\ub300 \uc804 \uc790\uae30\ub825\uacfc \ub2e4\uc74c\uacfc \uac19\uc740 \uad00\uacc4\uac00 \uc788\ub2e4.\n( ) ( )2 max 6\n,max 0\n2 1.146 10\n2 r r r\nB A F A\n\u03bc = \u2248 \u00d7 (14)\n\ubc18\uacbd\ubc29\ud5a5 \ucd5c\ub300 \uc804\uc790\uae30\ub825\uc740 \ud68c\uc804\uccb4\uc758 \ub3d9\uc801 \ubd80\ud558\ub97c \uace0\ub824\ud558\uc5ec \uc120\uc815\ud55c\ub2e4. \uc989, \ud68c\uc804\uc18d\ub3c4 12,000 rpm\uc5d0\uc11c", + "\uae40 \uc6b0 \uc5f0 \u2024\uc774 \uc885 \ubbfc \u2024\ubc30 \uc6a9 \ucc44 \u2024\uae40 \uc2b9 \uc885\n724/\ud55c\uad6d\uc18c\uc74c\uc9c4\ub3d9\uacf5\ud559\ud68c\ub17c\ubb38\uc9d1/\uc81c 20 \uad8c \uc81c 8 \ud638, 2010\ub144\n\ubc38\ub7f0\uc2f1 \ub4f1\uae09\uc744 G6.3\uc73c\ub85c \uac00\uc815\ud560 \ub54c, \ubd88\uade0\ud615\ub7c9\uc740 \uc57d 5 gmm/kg\uc774\ubbc0\ub85c, \ubd88\uade0\ud615\ub825\uc740 \uc57d 1,100 N\uc774\ub2e4. \uadf8\ub7ec \ubbc0\ub85c \ud558\ub098\uc758 \ubc18\uacbd\ubc29\ud5a5 HMB\uc5d0\uc11c \uc694\uad6c\ub418\ub294 \ucd5c\ub300 \uc804 \uc790 \uae30\ub825\uc740 550 N \uc774\uc0c1\uc774\uba74 \ub418\uc9c0\ub9cc, \ud574\uc11d \uc624\ucc28\uc640 \uc548 \uc804\uc728\uc744 \uace0\ub824\ud558\uc5ec \uadf8 \ub450 \ubc30 \uc815\ub3c4\ub85c \ud558\uc600\ub2e4. \uc124\uacc4\ub41c Ar\uc740 924.25 mm2\uc774\ub2e4. \uadf8\ub7ec\uba74 \uc2dd (13)\uc5d0\uc11c B\u226b0.5 T\uc774\uae30 \uc704\ud574 Amr\uc740 1,472 mm2\ub85c \uacc4\uc0b0\ub41c\ub2e4. \uadf8\ub7ec\ub098 \uc774 \uc124\uacc4\uac12\uc5d0 \ub300\ud574\uc11c FEM \ud574\uc11d\uc744 \uc218\ud589\ud55c \uacb0\uacfc, \uacf5 \uadf9 \uc790\uc18d\ubc00\ub3c4\ub294 \uc57d 0.29 T\uac00 \uc5bb\uc5b4\uc84c\ub2e4. \uc774 \uc624\ucc28\ub294 \uc0c1\n\ud558 \ucf54\uc5b4 \uc0ac\uc774\uc758 \uacf5\uac04\uc744 \ud1b5\ud55c \uc790\uc18d \ub204\uc124\uc774 \uc8fc\uc6d0\uc778\uc77c \uac83\uc73c\ub85c \ud310\ub2e8\ub41c\ub2e4. \uadf8\ub798\uc11c Amr\uc744 \uc99d\uac00\uc2dc\ud0a4\uba74\uc11c FEM \ud574\uc11d\uc744 \uc218\ud589\ud558\uc5ec, \uacf5\uadf9\uc5d0\uc11c\uc758 \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\ubc00\ub3c4 B \uac00 \ub300\ub7b5 0.5 T\uac00 \ub418\ub294 Amr\uc744 \uc120\ud0dd\ud558\uc600\ub2e4. \ucd5c\uc885 \uacb0\uc815 \ub41c \ubc18\uacbd\ubc29\ud5a5 HMB\uc5d0 \ub300\ud55c \uc124\uacc4\ubcc0\uc218\ub4e4\uc744 Table 2\uc5d0 \uc815\ub9ac\ud558\uc600\ub2e4. Fig. 9\ub294 \ucd5c\uc885 \uacb0\uc815\ub41c \uc124\uacc4 \uc548\uc5d0 \ub300\ud55c 3\ucc28\uc6d0 FEM \ud574\uc11d \uacb0\uacfc\ub85c\uc11c, (a)\ub294 \uc601\uad6c\uc790\uc11d \uc8fc\ubcc0\uc758 \uacf5\uac04\uc73c\ub85c \ub204\uc124 \uc790\uc18d\uc774 \ud1b5\uacfc\ud558\uace0 \uc788\uc74c\uc744 \ubcf4\uc5ec\uc8fc\uace0, (b)\ub294 \uc6d0\uc8fc \ubc29\ud5a5\uc73c\ub85c \uacf5\uadf9\uc758 \uc790\uc18d\ubc00\ub3c4 \ubd84\ud3ec\ub97c \ub3c4\uc2dc \ud55c \uadf8\ub9bc\uc774\ub2e4. \ub124 \uac1c\uc758 \ucf54\uc5b4\uc5d0\uc11c \ub3d9\uc77c\ud558\uac8c 0.503 T\uc758 \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\ubc00\ub3c4\uac00 \ubc1c\uc0dd\ud568\uc744 \uc54c \uc218 \uc788\ub2e4. \ucc38\uace0\ub85c, \uc2dd (13)\uc73c\ub85c\ubd80\ud130 \uad6c\ud55c \uac12\uc740 0.858 T\ub85c\uc11c \ud574\uc11d\uac12\uacfc \ube44\uad50\ud560 \ub54c \uc5ec\uc804\ud788 \ud070 \uc624\ucc28\ub294 \uc874\uc7ac\ud55c\ub2e4. \ud55c\ud3b8, Fig. 8(b)\ub294 \ubc18\uacbd \ubc29\ud5a5 \uc804\uc790\uc11d\uc744 \ud3ec\ud568\ud558\ub294 \uc790\uae30\ud68c\ub85c\uc774\uace0, \uc5ec\uae30\uc11c \uacf5\uadf9\uc5d0\uc11c\uc758 \uc81c\uc5b4 \uc790\uc18d\ubc00\ub3c4 Brc\ub294\n0 r r rc\nr\nN IB g \u03bc = (15)\n\uc73c\ub85c \ud45c\ud604\ub41c\ub2e4. \uc55e \uc808\uc5d0\uc11c\uc640 \uc720\uc0ac\ud55c \ubc29\ubc95\uc73c\ub85c, Brc\uc758\nTable 2 Specification of radial HMB\nParameter Value\nPM\nHeight(mm) 18 Outer dia.(mm) 148 Inner dia.(mm) 134 Cross-sectional area(mm2) 3100\nStator core Outer dia.(mm) 116 Thickness(mm) 20\nArea of one core(mm2) 924.25\nRotor core Outer dia.(mm) 156\nInner dia.(mm) 117.6\nAir gap size(mm) 0.8\n\ucd5c\ub300\uac12\uc740 \ubc18\uacbd \ubc29\ud5a5 \ucd5c\ub300 \ubcc0\uc704\uac00 \ubc1c\uc0dd\ud558\uc600\uc744 \ub54c, \uc881\n\uc544\uc9c4 \uacf5\uadf9\uc5d0\uc11c\uc758 \ubc14\uc774\uc5b4\uc2a4 \uc790\uc18d\ubc00\ub3c4\ub97c \uc0c1\uc1c4\ud560 \uc218 \uc788\ub294 \uc218\uc900\uc73c\ub85c \uacb0\uc815\ud55c\ub2e4. \ubc18\uacbd\ubc29\ud5a5 \ube44\uc0c1 \ubca0\uc5b4\ub9c1 \uac04 \uadf9\uc740 \uacf5\uadf9\uc758 1/2\uc778 0.4 mm\ub85c \ud558\uc600\uc73c\ubbc0\ub85c \ucd5c\ub300 \ubcc0\uc704\ub294 0.4 mm\uac00 \ub418\uace0, \uc774\ub54c\uc758 \uacf5\uadf9 \uc790\uc18d\ubc00\ub3c4 \ubd84\ud3ec\ub97c FEM \uc73c\ub85c \uad6c\ud558\uba74 Fig. 10\uacfc \uac19\ub2e4. \uadf8\ub9bc\uc5d0\uc11c A\ub85c \ud45c\uc2dc\ub41c" + ] + }, + { + "image_filename": "designv8_17_0000797_ING_20SZE_20LING.pdf-Figure3.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000797_ING_20SZE_20LING.pdf-Figure3.9-1.png", + "caption": "Figure 3.9 Structure of the outer radius and core radius of ferrite coil", + "texts": [ + " Besides that, the relative permeability of the ferrite coil is varied in order to find out how it affects the S11 performance. This is to aid the understanding of the effects of these parameters on the performance of the current probe feed. The length of the PEC monopole is fixed at L = 2.5 m, the ferrite coil is placed 3 cm above the ground plane, the inner and outer radii of the ferrite toroid will be varied, the number of turns N is 2 and the fo = 28 MHz for the following comparisons. The structure of a ferrite coil is shown below in Figure 3.9. When the outer radius of the ferrite coil changes, it will affect the amount of current induced into the monopole antenna respectively. Comparison of the S11 results for different outer radius values of the ferrite coil when the ferrite coil is being placed 3 cm from the ground of the PEC monopole antenna is shown in Figure 3.10. In this simulation, the outer radius of the ferrite core is varied from 3.7 cm to 6.7 cm with all other parameters kept constant. From the simulated results shown in Figure 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002105_783_77_783_4144__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002105_783_77_783_4144__pdf-Figure3-1.png", + "caption": "Fig. 3 Configuration of the motor", + "texts": [], + "surrounding_texts": [ + "\u5ea7\u5c48\u5e73\u884c\u677f\u3070\u306d\u3092\u7528\u3044\u305f\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306e\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\n\u00a92011 The Japan Society of Mechanical Engineers\n\u3053\u308c\u3089\u306e\u5e73\u677f\u72b6\u632f\u52d5\u5b50\u306f\uff0c\u632f\u52d5\u5b50\u81ea\u4f53\u306f\u5358\u7d14\u306a\u69cb\u9020\u3067\u3042\u308b\u304c\uff0c\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u3068\u3057\u3066\u7528\u3044\u308b\u5834\u5408\uff0c\u3053\u306e\u632f 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\u308b\uff0e\u5b89\u5b9a\u6027\u3084\u4fdd\u6301\u525b\u6027\u3092\u9ad8\u3081\u305f\u65b9\u5f0f\u3068\u3057\u3066\u306f\uff0c\u632f\u52d5\u5b50\u3092\u652f\u6301\u3059\u308b\u7b87\u6240\u3092\u30b4\u30e0\u3084\u6a39\u8102\u306a\u3069\u306e\u5f3e\u6027\u4f53\u306b\u3088\u3063\u3066\u5225\u9014\u8a2d \u3051\u305f\u69cb\u9020(2)(12)\u3084\u632f\u52d5\u5b50\u306e 1 \u9762\u5168\u3066\u3092\u5f3e\u6027\u4f53\u306b\u3088\u3063\u3066\u652f\u6301\u3059\u308b\u69cb\u9020(4)\u3082\u63d0\u6848\u3055\u308c\u3066\u3044\u308b\u304c\uff0c\u652f\u6301\u3057\u305f\u7b87\u6240\u306b\u767a\u751f\u3059 \u308b\u6469\u64e6\u6e1b\u8870\u3084\u6a39\u8102\u306a\u3069\u306e\u6750\u6599\u6e1b\u8870\u306b\u3088\u308a Qm \u5024\u304c\u4f4e\u4e0b\u3059\u308b\u61f8\u5ff5\u304c\u3042\u308b\uff0e\u652f\u6301\u90e8\u306b\u3088\u308b\u632f\u52d5\u5b50\u306e\u632f\u52d5\u4f4e\u4e0b\u3092\u5c0f\u3055\u304f 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3\u306b\u672c\u30e2\u30fc\u30bf\u306e\u69cb\u6210\u3092\u793a\u3059\uff0eL1\u30e2\u30fc\u30c9\u306f\uff0c\u6469\u64e6\u30d8\u30c3\u30c9\u306e\u52a0\u5727\u65b9 \u5411\u306e\u632f\u52d5\u3092\u767a\u751f\u3059\u308b\u30e2\u30fc\u30c9\u3067\u3042\u308a\uff0c\u52a0\u5727\u529b\u3092\u5c48\u66f2\u632f\u52d5\uff08B2\u30e2\u30fc\u30c9\uff09\u3068\u540c\u671f\u3057\u3066\u5909\u5316\u3055\u305b\u308b\u3053\u3068\u3067\u6469\u64e6\u529b\u306e\u5236\u5fa1\u3092 \u884c\u3046\u632f\u52d5\u6210\u5206\u3067\u3042\u308b\uff0eB2\u30e2\u30fc\u30c9\u306f\u30b9\u30e9\u30a4\u30c0\u306e\u9001\u308a\u65b9\u5411\u306e\u632f\u52d5\u6210\u5206\u3092\u6301\u3064\u30e2\u30fc\u30c9\u3067\u3042\u308a\uff0c\u52d5\u529b\u6e90\u306b\u4f7f\u7528\u3055\u308c\u308b\uff0e\u672c \u632f\u52d5\u5b50\u306f\uff0c\u3053\u306e L1\u30e2\u30fc\u30c9\u3068 B2\u30e2\u30fc\u30c9\u3092\u5225\u3005\u306e\u96fb\u6975\u306b\u3088\u308a\u72ec\u7acb\u306b\u5236\u5fa1\u3067\u304d\u308b\u3053\u3068\u304c\u7279\u5fb4\u3067\u3042\u308b\uff0e\n4145\n\u2015 185 \u2015", + "\u5ea7\u5c48\u5e73\u884c\u677f\u3070\u306d\u3092\u7528\u3044\u305f\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306e\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\n\u00a92011 The Japan Society of Mechanical Engineers\nLeaf spring\nFriction head\nTransducer\nCase\nLeaf spring\nAdhesion\nAdhesion\nFig. 4 Holding and preloading mechanism\n\u8d85\u97f3\u6ce2\u30e2\u30fc\u30bf\u3067\u306f\uff0c\u632f\u52d5\u5b50\u3092\u5b89\u5b9a\u306b\uff0c\u304b\u3064\u4e00\u5b9a\u306e\u52a0\u5727\u529b\u3067\u30b9\u30e9\u30a4\u30c0\u306a\u3069\u306e\u79fb\u52d5\u4f53\u306b\u52a0\u5727\u63a5\u89e6\u3055\u305b\u305f\u72b6\u614b\u3067\u4fdd\u6301 \u3059\u308b\u6a5f\u69cb\u304c\u5fc5\u8981\u3068\u306a\u308b\uff0e\u56f3 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\u304d\u308b\u3060\u3051\u5927\u304d\u3044\u65b9\u304c\u671b\u307e\u3057\u3044\uff0e\u8377\u91cd\u304c\u4e00\u5b9a\u306b\u306a\u308b\u73fe\u8c61\u306f\uff0c\u5ea7\u5c48\u306e\u5f71\u97ff\u3068\u66f2\u3052\u525b\u6027\u306e\u5f71\u97ff\u306e\u30d0\u30e9\u30f3\u30b9\u306b\u3088\u3063\u3066\u751f\u3058\n4146\n\u2015 186 \u2015", + "\u5ea7\u5c48\u5e73\u884c\u677f\u3070\u306d\u3092\u7528\u3044\u305f\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306e\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\n\u00a92011 The Japan Society of Mechanical Engineers\n\u308b\uff0e\u305d\u3053\u3067\uff0c\u8377\u91cd\u304c\u4e00\u5b9a\u306b\u306a\u308b\u3070\u306d\u7279\u6027\u3092\u5c0e\u51fa\u3059\u308b\u3053\u3068\u3092\u76ee\u7684\u306b\u677f\u3070\u306d\u306e\u5f62\u72b6\u3068\u3070\u306d\u7279\u6027\u306e\u95a2\u4fc2\u306b\u3064\u3044\u3066\u8abf\u3079\u305f\uff0e \u677f\u3070\u306d\u306e\u5f62\u72b6\u3092\u56f3 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0\u8fd1\u508d\u306b\u306a\u308b\u3068\uff0c\u3070\u306d\u7279\u6027\u306b\u304a\u3051\u308b\u8377\u91cd\u4e00\u5b9a\u306e\u9818\u57df\u304c\u5927\u304d\u304f\u306a\u308b\u3053\u3068\u3092\u610f\u5473\u3059\u308b\uff0e\u306a \u304a\uff0cUO\u8fd1\u508d\u306e\u8377\u91cd\u306e\u50be\u304d\u306f\uff0c\u62bc\u8fbc\u307f\u91cf\u304c UO-0.1 mm\u306e\u3068\u304d\u306e\u8377\u91cd\u3068 UO+0.1 mm\u306e\u3068\u304d\u306e\u8377\u91cd\u306e\u5dee\u304b\u3089\u6c42\u3081\u305f\uff0e UO\uff0cLO \u306e\u5bf8\u6cd5\u6bd4\u3068\u3057\u3066\uff0cLO 2 /UO 3 \u3092\u7528\u3044\u308b\u3053\u3068\u3067\uff0cUO \u306e\u7570\u306a\u308b\u5404\u30c7\u30fc\u30bf\u304c\u307b\u307c\u76f4\u7dda\u72b6\u306b\u30d7\u30ed\u30c3\u30c8\u3055\u308c\u305f\uff0e\u540c \u56f3\u3088\u308a\u8377\u91cd\u306e\u50be\u304d\u304c 0\u306b\u306a\u308b LO 2 /UO 3\u306f\u7d04 0.08\u3067\u3042\u308b\u306e\u3067\uff0c\u3053\u306e\u5024\u3068\u306a\u308b\u3088\u3046\u306b\u677f\u3070\u306d\u306e\u5f62\u72b6\u3092\u8a2d\u8a08\u3059\u308c\u3070\uff0c\u6240 \u671b\u306e\u8377\u91cd\u7279\u6027\u3092\u5f97\u308b\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u5b9f\u969b\u306b\u8a66\u4f5c\u3057\u305f\u4fdd\u6301\u30fb\u52a0\u5727\u69cb\u9020\u306e\u3070\u306d\u7279\u6027\u3092\u56f3 8\u306b\u793a\u3059\uff0eUO\u306f 0.8 mm\uff0cLO\n4147\n\u2015 187 \u2015" + ] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-FigureA-2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-FigureA-2-1.png", + "caption": "Figure A-2: Local coordinate frames of the Euler wrist.", + "texts": [], + "surrounding_texts": [ + "180\n\u00b0T 3 = 'c$iC(e2 + e3) -C9iS(e2 + e2) - s e ! d2C 0XC \u2014d3S0x'\nSOiC{02 + 03) -S9iS(e2 + o3) cex 112S01CO2 + d3C0x \u2014 S{6 2 + $3 ) \u2014C(9 2 + 03) 0 dx \u2014 a2S02\n0 0 0 1 -\n3 rpG __ \u2019ce4ce3cee - se4S0e - c e 4C05se6- S04C06 C04S0 5 0\nS95Cde - s e 5S 06 -CO, \u2014d4 so 4CdsC$9 - C04S0e -S04C06S0e - C04C06 se4se5 0\n0 0 0\n&rpE __ 1\n0\n0\n0\n0\n1\n0\n0\n0\n0\n1\n0\n0\n0 de\n1\nA .2 A n a ly sis o f th e S p h erica l W rist\nTwo types of spherical wrists with three joints intersecting at one point, such as\nEuler and R P Y wrists, are analyzed. Since the range of orientations achieved by the end-effector is at a m axim um when the axes of the last three joints intersect at right\nangles [Ref. 26] and a change of an orientation does not require a drastic change of an arm configuration, most m anipulators follow this structure. The ze and y e axes of an end-effector frame are aligned with the approaching and sliding directions", + "respectively for a convenient analysis of the object handling. The degenerate sta te of the w rist, which is a singular sta te , is obtained from the closed-form solution.\nA .2.1 E uler W rist\nTEuler = ROT(z,) ROT(y ', f i ) R O T (z \",V>)\nwhere rotations are perform ed based on the current moving frames from left to right\n= ROT(z , ) R O T (y , /z) ROT{z, V>)\nwhere rotations are perform ed based on the fixed xyz fram e from right to left.\ncCnCi) - sSip - cCnSi' - scv> cSn S(j)CnC^ + Cs4> - SC[iSrl\u00bb + CC4' S(f>Sfi\n\u2014 S f i C i l \u2019 S f i S i p C f i", + "182\nLink param eters\nLink O f - 1 a i - 1 d i 0 i\n4 0 0 0 e4\n5 -9 0 \u00b0 0 0 6,5 6 90\u00b0 0 0 0 e\n3 r 4 == R OT{z4 ,94) 4T 5 = R O T (x 4, \u201490) R O T (z5,95) 5T 6 = R O T (x 5,9Q)ROT(z6 ,96) 6T E = [/] The above transform ations can be verified such th a t T L UrT E = 3 T E = ROT{z,) R O T {x ,-90 )R O T{z ,n )R O T (x ,9Q ) ROT(z,il>) '-----------------------------------------------v------------------------------------ -----------' ROT(y,n) S o lv in g E u le r a n g les Given trajectories of the end-effector expressed in the fixed inertial frame, the cor responding Euler angles can be obtained as follows: From the specified \u00b0T E = \u00b0RE \u00b0Pe\n0 1\n3T e is com puted such th a t 3T E = [ \u00b0 r 3 ] - 1 \u00b0TE. It will be shown later to obtain \u00b0T3. Since no translation is involved, 3T E = 3 R E. 3R E = [3N e 3S e 3A e }\nwhere 3N E ,3 S E, and 3A E denote the norm al, sliding, and approaching vectors respectively, expressed with respect to frame 3." + ] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.9-1.png", + "caption": "Figure 8.9: Geometry for 3D optimization cases", + "texts": [ + " Floating point errors round the contributions of distant segments to zero in the constraint Jacobian, which becomes sparser as a result. Both of these effects degrade optimizer performance. 186 Revolution For a simple 3D test, I defined single-point (0\u00b0) and multipoint (0\u00b0 and 20\u00b0) drag minimization cases. I created a starting surface mesh consisting of a NACA 0012 airfoil revolved around the streamwise (x) axis (Figure 8.10). The structured surface and volume meshes consisted of 1802 and 237762 cells, respectively. The 3D parameterization consists of 192 FFD points which provide fine shape control along the y-axis (Figure 8.9a), and an additional 17 parameters providing degrees of freedom in the x and z axes. I imposed symmetry in the crossflow (x-y) plane to effectively obtain a \u221220\u00b0 crossflow case without running additional CFD cases. The optimization parameters are described in Table 8.3. Figure 8.11 shows the optimized shape for the single point case. The drag decreased 29.3% 187 188 compared to the baseline single point case. The optimized shape is a long fairing with relatively tight leading edge curvature. The tightly curved leading edge is characteristic of single point aerodynamic shape optimization, since robustness to varying flow conditions is not required", + " Finally, I set up single and multipoint optimization cases where the geometry to be enveloped is that of a person in a seated position, with parameters identical to the previous case (Table 8.3). I exported a high-resolution model of an average U.S. adult in a seated driving position to a 190 stereolithography file (STL) using the University of Michigan Transportation Research Institute\u2019s (UMTRI) online tool6 [260]. I then resized and reduced the complexity of the triangulated mesh using Autodesk Meshmixer7 and imported it directly into the optimization environment; the final mesh (Figure 8.9b) had 626 triangles. Figure 8.13 shows the initial condition of the optimization. Figure 8.14 shows the optimized shape for the single point case. The drag decreased 61.3% compared to the grossly oversized baseline single point case. The optimizer generated a rounded leading edge and an elongated trailing cone with moderate closure angle. In this case, the rotational asymmetry is due to the asymmetric constraint geometry, not the flow condition. Figure 8.15 shows the optimized shape for the multipoint case" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-19-1.png", + "caption": "Figure 2-19. Exemple de mise en \u0153uvre de patchs parasites pour \u00e9largir la bande passante", + "texts": [ + " Nous verrons \u00e9galement par la suite qu'il est possible \u00e0 partir d'un seul patch de r\u00e9cup\u00e9rer des signaux dont les polarisations sont orthogonales et donc fortement d\u00e9corr\u00e9l\u00e9es. Mais l'antenne patch n'a pas que des avantages, elle ne rayonne que dans une demi-espace dont la fronti\u00e8re est constitu\u00e9e par le plan de masse et elle souffre d'une bande passante g\u00e9n\u00e9ralement r\u00e9duite (inf\u00e9rieure \u00e0 5% \u00e0 -10dB). La bande passante peut cependant \u00eatre \u00e9largie par l'utilisation de patchs parasites empil\u00e9s ou dispos\u00e9s dans le plan du patch comme le montre la Figure 2-19. 54 2.4.4 Les antennes directives Comme nous l'avons mentionn\u00e9 pr\u00e9c\u00e9demment, les antennes directives sont g\u00e9n\u00e9ralement utilis\u00e9es dans des r\u00e9seaux point \u00e0 point ou point \u00e0 multipoint. Ces structures permettent de concentrer la puissance dans une direction d\u00e9termin\u00e9e afin de cr\u00e9er un lien radio privil\u00e9gi\u00e9. Parmi les structures d'antennes directives, les plus connues du public sont certainement les antennes paraboliques largement utilis\u00e9es dans les communications satellitaires ainsi que les antennes Yagi-Uda utilis\u00e9es pour la r\u00e9ception des signaux de t\u00e9l\u00e9vision hertzienne" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003743_load.php_id_12051019-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003743_load.php_id_12051019-Figure4-1.png", + "caption": "Figure 4. Simulated normalized CP radiation pattterns within UHF band frequencies: (a) 860 MHz, (b) 910MHz, and (c) 960 MHz.", + "texts": [ + " The surface current distributions on the radiating element are shown in Figure 3 for the middle frequency (910 MHz) at different time frames: t = 0 (0\u25e6), T/4 (90\u25e6), T/2 (180\u25e6), and 3T/4 (270\u25e6). The figure clearly shows surface currents causing circular polarization described by the tip of the current vectors (counter clockwise) with time. The antenna structure shows the same surface current behavior throughout the entire band of interest (840\u2013960 MHz). A difference in rotation (clockwise) can similarly be achieved when the excitation and matched load termination are interchanged at the input ports. (a) (b) Figure 4 shows the normalized simulated CP radiation patterns at 860MHz, 910 MHz, and 960 MHz within the UHF frequency band. It can be seen that around 15 dB front-to-back (F/B) ratio is achieved at these frequencies. The co-polarization RHCP patterns are symmetric at all the frequencies. The maximum cross-polarization LHCP radiation patterns are separated from the co-polarization ones by almost 10 to 16 dB. The 3 dB beamwidths are around 60\u25e6 which suggests wide angular coverage for the reader antenna. The maximum RHCP gain varies between 8 dBic and 5 dBic within the UHF band, where the best gain is happening towards middle of the band" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003562_5_agriceng-2019-0036-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003562_5_agriceng-2019-0036-Figure4-1.png", + "caption": "Figure 4. Simplified view of the car body concept in version no. 3", + "texts": [ + " In the rear part, it was suggested to use spoilers and bending of edges which will reduce turbulence of the air stream behind the vehicle during its motion (Song et al., 2011). In the concept 2 the use of bending and cutting technologies for maintaining an aerodynamic shape will be more labour consuming. Concept 3 In concept 3 an appearance and shape of the front part was completely changed, and the steering system was shielded limiting thus the impact of the wind on a driver. It will be required to use additional mudguards in the front and rear axis (Fig.4). The cover of the engine chamber will also use the bending of edges to reduce air stream turbulences. Air inlets were presented in the cover in the side walls to improve thermal exchange of an engine with the surrounding. Air inlets are designed in the final version and they are available in each concept, with the same functions. Due to the methods of lamination of the car body and 3D print, with maintenance of the previously mentioned principles of division of the car body surface, they are effective methods" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure16-1.png", + "caption": "Figure 16. The maximum stress simulation results for the driver's footrest is 0.19 MPa.", + "texts": [ + " The simulation results for the total of the two driver rods were bending moment, maximum stress, and displacement, respectively, with values of 21683.48 N.mm, 4.63 MPa, and 0.010 mm. Figure 15 shows the maximum stress value simulation results at the driver's body mount. 4. Driver's footrest The driver's footrest receives a load of 8.4 kg acting in the y-axis direction. This part only consists of one rod to support the driver's feet. The simulation results obtained in bending moment, maximum stress, and displacement, respectively, have 893.86 N.mm, 0.19 MPa, and 0.00008 mm values. Figure 16 shows the simulation results of the maximum stress value on the driver's footrest. 5. Front body mount The front body mount receives a load of 4.2 kg acting in the y-axis direction. This part only consists of one rod to support the front body. The simulation results obtained are bending moment, maximum stress, and displacement, respectively, the values are 786.79 N.mm, 0.17 MPa, and 0.00006 mm. Figure 17 shows the simulation results of the maximum stress value on the driver's footrest. 6. Rollbar body mount The rollbar body mount receives a load of 16" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure1-1.png", + "caption": "Figure 1. Pipe Traveler Assembly", + "texts": [ + " However, this type of remote delivery Page 2 of 15 platform may be useful in other places; specifically around the DOE complex for Decontamination & Demolition (D&D) operations where this type of environment may exist. 2 APPROACH Grippers using idler rollers as the contact points and a drive wheel to contact the pipe are used to create the rotational motion around the pipe. The drive wheel is pressed against a pipe by a pneumatic cylinder and is powered by a stepper motor. Four linear slides are used to allow the system to extend while maintaining rigidity. The slides are actuated by two pneumatic extension cylinders. The overall system design is shown in Figure 1. Pipe Traveler Assembly The gripper is used to allow the Pipe Traveler to clamp onto pipes, but still allow the unit to rotate around the pipe. This is achieved by using idler rollers located between fingers as the contact points on the pipe (See Figure 2). The idler rollers allow the grippers to support the weight of the Pipe Traveler while permitting rotation around a pipe. The gripping surface of the rollers is urethane rubber, which allows the grippers to accommodate imperfections in the pipes to be gripped" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure5-1.png", + "caption": "Figure 5 P-POD Mk. III Rev. E. Access Port", + "texts": [ + " In order to gasket the access port covers, a flanged interface needed to be created to house the gasket. This mandated a redesign of the current access port design. Page 7 Sealing EMI/RFI Leaks P-POD components were modified to close the identified sources of EMI/RFI leakage, and incorporate EMI gaskets to any gaps. The access port covers, door/collar interface, and venting hole were all accounted for. The Mk. III access port cover used 6 x 2-56 Socket Cap screws to affix it to the Side Panel of the P-POD. The original access port is shown below in Figure 5. The 2-56 screws used in the original access port design are very small and difficult to work with. While these screws have flight heritage, it would be beneficial to incorporate larger screws into this redesign. Unfortunately, because both the P-POD exterior static envelope and interior volume must stay the same, simply increasing the screw size is impossible, as the head height of the screw cap grows significantly with increased screw sizes. Multiple options were explored in order to determine the best Page 8 design prior to proceeding" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure2.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure2.5-1.png", + "caption": "Figure 2.5. Practical implementations of the turning joint with two rubber bushings (left), and the turning-and-sliding joint as a telescopic damper (right), reproduced from [26].", + "texts": [ + "\u201d This substitution is possible when only one axis of rotation is primarily used by a ball joint, allowing the two orthogonal rotations to occur via bushing compliance. The turning joint, Figure 2.4c, also known as the revolute joint, is another possibility, as is the turning-and-sliding joint, Figure 2.4d, also known as the cylindric joint. Matschinsky notes that the turning joint is often implemented practically with two rubber joints, while the turning-and-sliding joint takes the form of a telescopic damper; see Figure 2.5. Finally, he mentions the ball-and-surface joint, Figure 2.4e, but says it is very rarely found in independent suspensions, discussing it further only in the context of rigid axle suspension linkages. Matschinsky does not construct links combinatorially like Raghavan, instead directly stating the most important types, Figure 2.6. The rod link, Figure 2.6a, has a ball joint (or equivalent rubber joint) at each end. It comes with a superfluous rotation r, which does not affect the wheel carrier motion" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001910_9312710_09348895.pdf-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001910_9312710_09348895.pdf-Figure20-1.png", + "caption": "FIGURE 20. Schematic view of the bent LTCC antenna. (a) 3D view, (b) side view.", + "texts": [ + " 19, the peak realized gain degrades by changing \u03be . Hence, rotating the connectors causes discrepancies because the pin is not touching the signal trace properly and only a small portion of the input signal transfers to the antenna. As stated before, the antenna may bend due to the small thickness of the structure. Moreover, heating the antenna, as part of the fabrication procedure of the LTCC, can curve the board. To investigate such case, we bent the antenna such to deviate gradually up to hb = 6 mm from the horizon, as illustrated in Fig. 20. The S-parameters, radiation patterns, and peak realized gain of the curved antenna are reported 25020 VOLUME 9, 2021 in Figs. 21-23, respectively. According to Figs. 21-23, bending the substrate leads to severe degradation of the antenna responses in terms of return loss, SLL, and gain. Since the LTCC fabrication process involves heating the structure, deviations in via size and spacing, and total width (d , S, W , and Wt ) are quite likely. Meandering the board and deviation in the layer thickness can also occur due to the heating" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000951_f_version_1592539735-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000951_f_version_1592539735-Figure2-1.png", + "caption": "Figure 2. Schematic of a piston-swivelling-cylinder (PSC) pair in HWBHM with SDV: (a) Basic structure of the PSC pair; (b) PSC pair at an arbitrary position; (c) PSC pair at position \u03c6i = 0", + "texts": [ + " For a PSC pair in HWBHM with SDVs, there are mainly two kinds of sealing mode: non-contact sealing (a clearance seal) and contact sealing mode (using a sealing ring). Energies 2020, 13, 3175 4 of 18 For a clearance seal, the friction pairs are under lubricated conditions most of the time, which has the advantage of minor abrasion between friction pair components. Thus, the working life of a friction pair with clearance seal mode would be longer than that in contact seal mode (the clearance would, however, affect the volume efficiency of the HWBHM). The basic structure of a PSC pair is shown in Figure 2a: it consists of a piston and a swivelling cylinder. The diameter of the piston is d, the seal length in the PSC pair is \u03b4lp, and the clearance between piston and swivelling cylinder is hp. Energies 2020, 13, x FOR PEER REVIEW 4 of 19 i it l l l l t t t i t t l (t l l , , ffect t e vol e efficiency of the BH ). i t t f i i i i : it i t f i t i lli li . The diameter of the piston is d, the seal lengt in the PSC pair is \u03b4lp, and the clearance between pi ton and swivelling cylinder is hp. The motion of a piston in its cylinder at an arbitrary position is shown in Figure 2b, O represents the centre of rotation of the crankshaft, O1 represents the eccentricity of the structure on the crankshaft, O2 represents the centre of rotation of the cylinder, e0 represents the distance between O and O1, R0 is the distance between O and O2, \u03b8i represents the angle of rotation of the cylinder, \u03c6i denotes the angle of rotation of the crankshaft, \u03c9 represents the angular velocity of the crankshaft, and li is the distance between O1 and O2. A PSC pair at position \u03c6i = 0 is shown in Figure 2c. For the proposed HWBHM with SDV, the designed displacement q is 189 ml/r, the rated rotation speed is 60 rpm, and maximum rotation speed is 100 rpm. The corresponding basic parameters in Figure 2 are listed in Table 1. piston and swivelling cylinder can be expressed as [18]: 0 0 0sin sini i i iv R R e l (1) 0 0 0 02 cosi il e R e R . Thus, the variation of velocity vi with angular position \u03c6i can be obtained (Figure 3). The maximum relative velocity vi between piston and swivelling cylinder will be less than 0.2 m/s when the working speed of HWBHM is no more than 100 rpm. i 2. Schematic of a piston-swivelling-cylinder (PSC) pair in HWBHM with SDV: (a) Basic structure of the PSC pair; (b) PSC pair at an arbitrary pos ion; (c) PSC pair at position \u03c6i = 0", + " i i i i li i i i i i i , centre of rotation of the crankshaft, O1 represents the eccentricity of the structure on the crankshaft, O2 represents th centre of rotation of the cylinder, e0 represents the distance between O and O1, R0 is the distance between O and O2, \u03b8i represents the angle of rotation of the cylinder, \u03c6i denotes the angle of rotation of the crankshaft, \u03c9 represents the angular v locity of the crankshaft, and li is the distance between O1 and O2. A PSC pair at position \u03c6i = 0 is shown in Figure 2c. For the proposed HWBHM with SDV, the designed displacement q is 189 mL/r, the rated rotation speed is 60 rpm, and maximum otatio speed is 100 pm. The corresponding basic parameters in Figure 2 e listed in Table 1. Table 1. Basic parameters of main structures in designed HWBHM with SDV. As shown in Figure 2b, when the crankshaft is at position \u03c6i, the relative velocity vi between the piston and swivelling cylinder can be expressed as [18]: vi = \u03c9R0 sin\u03b8i = \u03c9R0e0sin\u03c6i/li (1) In Equation (1), li is calculated as: li = \u221a e2 0 + R02 \u2212 2e0R0 cos\u03c6i. Energies 2020, 13, 3175 5 of 18 Thus, the variation of velocity vi with angular position\u03c6i can be obtained (Figure 3). The maximum relative velocity vi between piston and swivelling cylinder will be less than 0.2 m/s when the working speed of HWBHM is no more than 100 rpm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003514__pdf_10.1145_3618396-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003514__pdf_10.1145_3618396-Figure11-1.png", + "caption": "Fig. 11. Our experimental setup for both compression and tensile testing of small tilings of our planar microstructures.", + "texts": [ + " The testing system allows the application of a prescribed displacement and the measurement of the corresponding reaction force (or vice versa). For tensile specimens, clamps are used to grip both ends of the specimens. Prescribed displacements are applied at these boundary edges parallel to the sheets while the lateral displacements are constrained to zero. For compression testing, a sleeve is fabricated using acrylic sheets to sandwich the specimens in between. Two additional acrylic sheets are used to apply prescribed compressive displacements to the specimens (Figure 11). Liquid lubricant is used to minimize the influence of friction. Here, the lateral displacements at the boundaries are unconfined. All experiments are conducted under ambient conditions, and the loading rate is set to 3mm/min. Given that room temperature is significantly below the glass transition temperature of the polymer (\u2248 60 \u25e6C), we assume that the material is in its glassy phase. The results of our large-scale material design experiments described in Section 6.1 are summarized in Figure 13 and Figure 14" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002315_cle_download_253_179-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002315_cle_download_253_179-Figure3-1.png", + "caption": "Figure 3. Bogie Model Applied in Simulation : (a) Bogie Model in 3D Drawing, (b) Simplified Bogie Applied in Simulation.", + "texts": [ + " The ride comfort index can be calculated by [11] [12] \ud835\udc4a\ud835\udc4d = 0.89610\u221a \ud835\udc4e2 \ud835\udc53 \ud835\udc39(\ud835\udc53) (2) where a is vibration amplitude in cm/s, f is the frequency in Hz dan F(f) is different frequency weights for vertical and lateral vibrations. Based on Equation (2), it can be written into \u221a\ud835\udc4e2\ud835\udc3526.67 (3) where B is the vertical and lateral comfort direction factors which are written consecutively as follows; \ud835\udc35\ud835\udc63 = 0.588 [ 1.1911\ud835\udc532+(0.25\ud835\udc532)2 (1\u22120.277\ud835\udc532)2+(1.563\ud835\udc53\u22120.0368\ud835\udc533)2] (4) \ud835\udc35\ud835\udc63 = 0.737 [ 1.1911\ud835\udc532+(0.25\ud835\udc532)2 (1\u22120.277\ud835\udc532)2+(1.563\ud835\udc53\u22120.0368\ud835\udc533)2] (5) Figure 3 shows the bogie model of the SS-NG passenger coach applied in the simulation. Figure 3(a) is the bogie model in the 3D drawing. This bogie model was then simplified as shown in Figure 3(b) in order to analyze the dynamics of the train during operation. The simplification aims to smooth running in computation and provide more accurate results. As shown in the picture, this model consists of six vertical dampers, one lateral damper, four primary suspensions, eight secondary suspensions in the form of metal springs, and four swing links that are used to connect the bogie frame, bolster, spring plank, and wheelset. Figure 4 displays a contact model between the train wheels to the rail line in the simulation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004599_(5)_2017_549-562.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004599_(5)_2017_549-562.pdf-Figure3-1.png", + "caption": "Figure 3. Typical determination of the vehicle length.", + "texts": [ + " In a variable 3D-CAD layout model, the geometrical dimensions are controlled by parameters to enable the creation and analysis of different dimensional constellations and to evaluate their influences onto the vehicle architecture. Depending on the specific design questions, the sequence of development steps for the layout definition of a new car model may vary significantly for one project to the other. Initial car development can be done for instance from inside to outside or vice versa. Another possibility is to start from an existing vehicle platform, where basic dimensions are already defined. As illustrated in Fig. 3, a possible determination of the vehicle length (L103) includes the summation of the overhang front (L104), the wheelbase (L101) and the overhang rear (L105). The wheelbase itself results in this example out of the difference of the wheel center x-coordinates. In terms of a CAD model, the following formulas are required: L103 = L104 + L101 + L105 L101 = xRearWheel \u2212 xFrontWheel (2.1) A modification of one of the input parameters will consequently lead to an automatic evaluation of the defined formulas and provides the output parameter values to be updated" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure5-1.png", + "caption": "Figure 5. Surface-mounted permanent magnet synchronous motor.", + "texts": [ + " Section 3 designs AFPM motors based on target RFPM motor specifications. Section 4 applies the effect analysis technique, optimizes the integer design variables preferentially, then optimizes the remaining real number design variables based on the progressive meta model. Section 5 utilizes the proposed process to advance the optimal design of the DRAFPM motor for robot joints. Section 6 summarizes the conclusions of this paper. Figure 4 shows the components of the joint robot and the drive module. Currently, RFPM motor for robot joints is mainly used as shown in Figure 5. The motor size has been reduced to a smaller size, and SPMSM\u2019s performance has reached its limit. Therefore, it is necessary to study the high torque of motor for robot joints. The AFPM motor shape is shown in Figure 6. The AFPM motor is thin and proportional to the cubic diameter. Therefore, the AFPM motor can effectively generate torque [21\u201324]. The shorter the axial length of the motor for robot joints, the better. The AFPM motor is suitable for the motor for robot joints because it has a very short axial length compared to the radial direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000257_al-02004843_document-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000257_al-02004843_document-Figure1-1.png", + "caption": "Fig. 1. Scheme of an amplifying gate thyristor (AGT) based on SiC.", + "texts": [ + " The fundamental idea behind the concept of amplifying gate turn-on or follow-up triggering is to take the power being necessary for triggering a large emitter periphery from the load circuit of a small integrated auxiliary thyristor rather than from the gate circuit [5]. All technical variants of this concept have in common that \u2013 given the auxiliary (or pilot) thyristor is properly dimensioned \u2013 triggering proceeds in two phases: first, within the integrated auxiliary thyristor which then is followed by the main (or principal) thyristor. Once the latter is turned on it will take over the load current from the pilot thyristor and preserve it against damage by overload. The implementation of such a concept into a SiC device configuration is quite obvious, see Fig. 1. The device configuration reported here is based on an epi-structure having the same layer sequence, namely n+(substrate)/p/p-/n/p+, that is commonly used for asymmetric SiC thyristors. The AGT structure comprises a central gate electrode (G) and \u2013 concentrically arranged \u2013 pilot thyristor (A\u2019), anode (A), and junction termination extension (JTE). Note that the anode of the pilot thyristor (A\u2019) and the gate contact of the main thyristor (G\u2019) are connected with each other and consequently overlap the p+/n-base junction", + " Due to the epitaxial structure, two characteristic features were identified as regards the AGT device: first, the contact bridging auxiliary anode and main gate require a mesa step, and second, the design criterion for realizing an amplifying gate structure must rely on geometrical constraints only, see Ref. 6. While the former was part of the technological hurdles to be cleared the latter is more of fundamental importance for the entire device layout. In order for the AGT device conceptualized to work properly, i.e., trigger the auxiliary thyristor rather than the main thyristor, the voltage drop produced by the gate current when passing through the lateral n-base resistance beneath the auxiliary anode, here, denoted as RP, see Fig. 1, must exceed the threshold voltage and, moreover, the voltage drop across the resistance RM underneath the main anode; in terms of RP and RM this is equivalent to P MR R , (1) which obeys when transferred to a circular device geometry to SA SM EA EM r r r r , (2) where rEA, rSA and rEM, rSM refer to the radial distances from the gate center to the edges of the auxiliary and the main anode (cf. Fig. 1), respectively. The device under investigation is a SiC thyristor with a blocking capability of nominal 1.2 kV and a die size of 10 mm2. The first constraint reflects the fact that the device is aiming at fundamental investigations and thus does not require any advanced performance; the latter is a trade-off between the need for sufficiently large gate periphery and a rather small die size necessary to assure an adequate yield of equally functioning devices. The source material of our devices comprises a 4\u00b0 off-axis n-type 4H-SiC production-grade 100- mm wafer substrate from SiCrystal AG" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.10-1.png", + "caption": "Figure 10.10: Structural sizing variables at the optimum (with tank weight, 2.4 m3 fuel volume)", + "texts": [ + " The problem formulation is summarized in Table 10.4. The resulting geometry is visualized in Figure 10.9 (in blue). While the OML only changes subtly at the lower trailing edge, the changes allow the tanks to become much longer and narrower, reducing hoop stress and tank weight. This is a complex tradeoff between the structural weight of a component and the structural weight and drag at the airplane level. It is a good illustration of MDO\u2019s potential to find non-obvious solutions in airplane trade studies rapidly. Figure 10.10 shows the structural sizing variables for this case. Some of the structural zones are minimum gauged, such as the ribs and some spar web zones. Figure 10.11 shows the structural 2https://gist.github.com/bbrelje/b599102f2d83749df681dd5c2c0865e1 3https://gist.github.com/bbrelje/947ef6ff401a201812fde465518b74ff 223 failure criterion at the 2.5 g maneuver case. We can see that the optimizer has removed material almost everywhere until most of the wingbox is nearly at failure at ultimate load (2.5 g plus 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002506_.srce.hr_file_390601-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002506_.srce.hr_file_390601-Figure6-1.png", + "caption": "Figure 6 The area of the trailing surface of the blade with a grid of points applied", + "texts": [ + " Therefore, the dependence of the grinding force on the most important variable parameters is presented as n C C C, , ,F f Q x y z (2) To avoid the problem of analytical modeling of the complicated relationship between the desired force and the machining allowance Q occurring at the point determined by the coordinates xC, yC, zC, with fixed process parameters vr, vt, the NN was used, which was learned dependence given by Eq. (2). 18 Technical Gazette 29, 1(2022), 15-22\u00a0 The outer surface of the blade, called the trailing surface or the so-called ridge was covered with a regular grid of points located at distances not greater than the width of the machining tool (Fig. 6). For these points the value of the contact force was determined. A detailed description of the neural generator of the set contact force is given in section 3.3. The designed robotic blade grinding station includes an IRB 140 robot manipulating the workpiece, a grinding tool and an IRB 1600 robot with a 3D scanning head installed. The measuring system works with ATOS Professional software and communicates with the IRC5 robot controller using the TCP/IP protocol. The RobotWare robot controller software provides control of two robots and is additionally equipped with a force control option" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000089_65_34_1_34_1_20__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000089_65_34_1_34_1_20__pdf-Figure4-1.png", + "caption": "Fig. 4 Two-wheeled vehicle model", + "texts": [], + "surrounding_texts": [ + "\u8a08\u6e2c \u81ea\u52d5\u5236\u5fa1 \u5b66\u4f1a\u8ad6\u6587\u96c6 \u7b2c34\u5dfb \u7b2c1\u53f7 1998\u5e741\u6708 23\n\u306b\u5e30\u7740 \u3067 \u304d\u308b.\u305f \u3060 \u3057,U\u306e \u5b58\u5728 \u6761\u4ef6 \u3068\u3057\u3066\u5f0f(8)\u4e2d,An12 \u304c\u6b63 \u5247 \u3067\u3042 \u308b\u5fc5\u8981 \u304c \u3042 \u308b\u304c,\u305d \u306e\u884c \u5217\u5f0f \u304c\ndet(An12) = det(Im +72(W T )13Bwf 2) = 1 +,Y2 f 2(W1 T~13Bw\n\u3067 \u4e0e \u3048 \u3089\u308c \u308b \u3053\u3068\u304b \u3089\u3082\u308f \u304b \u308b \u3088 \u3046\u306b \u03b32\u306b \u95a2\u3059 \u308b\u4e00 \u6b21\u5f0f \u3068\n\u306a\u308b \u305f\u3081,\u3082 \u3057\u3042 \u308b \u03b3 \u306b\u5bfe \u3057\u3066\u6b63 \u5247 \u3067 \u306a\u3044 \u3068 \u3057\u3066 \u3082 \u03b3 \u3092 \u308f\n\u305a \u304b \u306b\u5909 \u3048 \u308b\u3060 \u3051 \u56de\u907f \u3067 \u304d\u308b.\u305d \u306e\u305f \u3081,An12\u306f \u6b63\u5247 \u3067\u3042\n\u308a,\u9006 \u884c \u5217 \u304c\u5b58 \u5728 \u3059 \u308b \u3068\u8003 \u3048\u3066 \u3088\u3044.\u3053 \u3053\u3067,(W-T1)13\u306f\nAn\u3068 \u540c\u69d8 \u306bAs\u306e \u69cb \u9020 \u306b\u5408 \u308f\u305b \u3066W-T1\u3092 \u5206\u5272 \u3057\u305fm\u00d7r\n\u884c \u5217\u3067 \u3042 \u308b.\n\u307e\u305f,\u81ea \u7531\u30d1 \u30e9 \u30e1\u30fc \u30bf\u306b\u5bfe \u3059 \u308b \u30ce\u30eb\u30e0\u6761\u4ef6||\u03a6||\u221e<1\u3092 \u6e80 \u8db3 \u3059 \u308b\u5fc5\u8981 \u304c \u3042 \u308b\u304c,\u5f0f(8)\u306b \u6ce8 \u76ee\u3059 \u308b \u3068,b\u03c6., d\u03c6.\u3059 \u3079 \u3066 \u306b \u03b6-1\u306e \u9805 \u304c \u3042 \u308b\u305f \u3081 \u03a6=\u03b6-1\u03a6 \u2032\u3068\u7f6e \u304f\u3053 \u3068\u304c \u3067 \u304d,\u3053 \u306e\n\u6761\u4ef6 \u306f||\u03b6-1\u03a6\u2032||\u221e<1\u3059 \u306a\u308f \u3061||\u03a6\u2032||\u221e<\u03b6(=(\u03b32-1)1/2)\n\u3068\u7f6e \u304d\u63db \u3048 \u308b \u3053\u3068\u304c\u3067 \u304d\u308b.\u03b3 \u2192 \u221e \u306b\u5bfe \u3057\u3066\n\u03b32W-T1=-In (11)\n\u3068\u306a\u308b \u3053 \u3068\u304b \u3089An\u306f \u03b3\u2192 \u221e \u3068\u3059 \u308b \u3068As-ZCTsCs\u306b \u6f38\n\u8fd1 \u3059 \u308b.\u3057 \u305f \u304c \u3063\u3066 \u03b3 \u3092\u5927 \u304d \u304f\u3059 \u308b \u3053 \u3068\u3067,\u5fc5 \u305a \u81ea\u7531\u30d1 \u30e9\n\u30e1\u30fc \u30bf\u306b\u5bfe \u3059 \u308b \u30ce\u30eb \u30e0\u6761\u4ef6 \u3092\u6e80\u8db3 \u3067 \u304d\u308b.\u305f \u3060 \u3057,\u03b3 \u306f,\u9589 \u30eb \u30fc\u30d7 \u4f1d\u9054\u884c \u5217 \u306e\u6574 \u5f62 \u5ea6 \u5408\u3044 \u3092\u8868 \u3057\u3066\u304a \u308a,\u30eb \u30fc\u30d7\u6574 \u5f62 \u306e\u7acb\n\u5834 \u304b \u3089\u3044 \u3048 \u3070\u3042 \u307e \u308a\u5927 \u304d \u304f\u9078 \u5b9a\u3059 \u308b\u3053 \u3068\u306f\u597d \u307e \u3057\u3044 \u3053\u3068\u3067 \u306f \u306a\u3044.\u3082 \u3057,\u6307 \u5b9a \u3057\u305f \u03b3 \u306b\u5bfe \u3057\u3066 \u30ce\u30eb \u30e0\u6761\u4ef6 \u304c\u6e80 \u305f \u3055\u308c \u306a\u3044 \u5834 \u5408 \u306b \u306f,\u81ea \u7531\u30d1 \u30e9 \u30e1\u30fc \u30bf\u306e\u6b21 \u6570 \u3092 \u3088\u308a\u9ad8 \u3044 \u3082\u306e \u306b\u3059 \u308b\u5fc5\u8981 \u304c\u3042 \u308b.\u4ee5 \u4e0a \u304b \u3089,\u9069 \u5f53 \u306aa\u03c6<0, u3\u306e \u9078\u5b9a \u306b \u3088 \u308a,\u5f0f(4)\n\u308a\u62e1\u5927 \u7cfbGs\u306b \u5bfe \u3057\u30661\u6b21 \u5143 \u306e\u5236\u5fa1 \u5668\u304c\u5f97 \u3089\u308c\u308b \u3053 \u3068\u304c \u793a \u3055 \u308c\u305f.\n\u6b21 \u306b \u3053\u306e\u5236 \u5fa1 \u5668(10)\u306e \u69cb\u9020 \u306b\u3064 \u3044\u3066\u691c\u8a0e \u3059 \u308b.\u5f0f(5),\u5f0f\n(9)\u304a \u3088\u3073\u5f0f(10)\u304b \u3089\u5f97 \u3089\u308c \u308b\nu-Fx=xk-Ux (12) hkCs-UAs=-a\u03c6U-(bk-UBs)F\n\u3092\u7528 \u3044 \u3066,\u5f0f(4)\u306e \u62e1 \u5927\u7cfb \u3068\u5f0f(5)\u304b \u3089xk-Ux\u306b \u95a2 \u3059 \u308b\n\u5fae \u5206\u65b9 \u7a0b\u5f0f \u3092\u6c42\u3081 \u308b \u3068\u6b21 \u5f0f\u304c\u5f97 \u3089\u308c \u308b.\nxk-Ux=(a\u03c6+bk-UBs)(xk-Ux) (13)\nu=xk-Ux+Fx\n\u3053\u306e \u5f0f \u3088 \u308a,\u3082 \u3057a\u03c6+bk-UBs<0\u3067 \u3042 \u308c \u3070,limt\u2192\u221exk-\nUx=0,\u3059 \u306a\u308f \u3061u=Fx\u3068 \u306a \u308a,\u62e1 \u5927\u7cfbGs(s)\u306b \u5bfe \u3059 \u308b\n\u6c4e \u95a2\u6570 \u89b3\u6e2c \u5668 \u3067\u3042 \u308b \u3053 \u3068\u304c \u308f\u304b \u308b.\u306a \u304a,\u3053 \u306e\u4e0d \u7b49 \u5f0f\u6761 \u4ef6 \u306f\n\u03b3\u2192 \u221e \u306e \u3068 \u304d,bk=UBs\u3068 \u306a \u308b \u3053 \u3068\u304b \u3089a\u03c6<0\u3068 \u306a\u308b.\n\u4ee5 \u4e0a \u306e \u3088 \u3046\u306b \u3057\u3066\u5f97 \u3089\u308c \u305f \u5236 \u5fa1 \u5668(10)\u306b \u5bfe \u3057\u3066,\u91cd \u307f W, Q\u3092 \u305d \u308c \u305e\u308c \u524d \u5f8c \u304b \u3089\u7d50\u5408 \u3057,\u62e1 \u5927 \u3057\u305f \u91cd \u307f\u4f1d \u9054 \u95a2\u6570 W\u306e \u72b6 \u614b\u91cf \u304c\u5236\u5fa1 \u5668\u5074 \u3067 \u65e2 \u77e5 \u3067 \u3042 \u308b\u3053 \u3068 \u3092\u5229 \u7528 \u3059 \u308b \u3068,\u6b21\n\u5f0f \u306b\u793a \u3059m\u5165 \u529b1\u51fa \u529b \u306e\u5236 \u5fa1 \u5668K(s)\u3092 \u5f97 \u308b.\u305d \u306e\u6b21 \u6570 \u306f 1\u6b21+\u91cd \u307f\u4f1d \u9054 \u95a2\u6570W(s)\u306e \u6b21 \u6570 \u3068\u306a\u308b.\nFthwl = Ak xw Bky . L xk xk\n(14) xw U = ck\nxk\n\u3053 \u3053 \u3067,\nAw BW Ck Ak\n0 ak + bkck\n+ Bwdk 0 Ir 0 hk + bkdk Ir\nBwdk Q B k - h\nk + bkdk 0\nCk = CW 0\n5. \u4e8c \u8f2a \u8eca \u7cfb \u3078 \u306e \u9069 \u7528\n5.1 \u5236 \u5fa1\u5bfe \u8c61\n\u8eab\u8fd1 \u306a\u4e0d\u5b89 \u5b9a\u7cfb \u306e \u4e00\u3064 \u3067\u3042 \u308b\u4e8c \u8f2a\u8eca \u306b\u5bfe \u3057\u3066\u4eba \u9593 \u306f,\u76ee \u3084\n\u8033 \u306a \u3069\u304b \u3089\u306e\u60c5\u5831 \u3092\u5de7 \u307f \u306b \u30d5 \u30a3\u30fc \u30c9\u30d0 \u30c3 \u30af\u3059 \u308b \u3053 \u3068\u3067 \u3046\u307e \u304f \u30d0 \u30e9\u30f3\u30b9 \u3092 \u3068\u3063\u3066 \u3044\u308b.\u3053 \u306e\u4e8c\u8f2a \u8eca \u306e\u5b89 \u5b9a\u5316\u5236\u5fa1 \u306b\u5bfe \u3057\u3066\u306f,\n\u30b8 \u30e3\u30a4\u30ed \u3092\u5229\u7528 \u3057\u305f \u3082\u306e\u304c \u5831\u544a \u3055\u308c\u3066\u3044 \u308b6)\u304c,\u672c \u8ad6 \u6587 \u3067 \u306f\n\u53f0 \u8eca \u306e\u91cd\u5fc3\u79fb \u52d5 \u306b \u3088\u308b\u5b89\u5b9a \u5316 \u5236\u5fa1 \u3092\u8a66 \u307f \u308b.\n\u672c\u8ad6\u6587 \u3067\u5bfe \u8c61 \u3068 \u3057\u305f\u4e8c\u8f2a \u8eca \u306b\u5bfe\u3059 \u308b\u5236 \u5fa1\u7cfb \u306e\u69cb\u6210 \u3092Fig. 3 \u306b\u793a\u3059.\u4e8c \u8f2a \u8eca \u306e\u5e8a \u306b\u5bfe \u3059 \u308b\u50be \u304d\u89d2 \u5ea6 \u304a \u3088\u3073\u53f0\u8eca \u306e\u4f4d\u7f6e \u306e\u8a08\n\u6e2c \u306f\u30a8 \u30f3\u30b3\u30fc\u30c0(\u591a \u6469 \u5ddd\u7cbe \u6a5f(\u682a)TS5320N510 (400C/T)) \u3092\u7528 \u3044\u3066\u884c \u3044,\u305d \u306e\u60c5 \u5831 \u306f \u30ab \u30a6\u30f3 \u30bf\u30dc \u30fc \u30c9\u3092\u901a \u3057\u3066\u8a08\u7b97 \u6a5f \u306b\n\u53d6 \u308a\u8fbc \u307e\u308c\u308b.\u3053 \u3053\u3067,\u4e8c \u8f2a \u8eca \u306e\u50be \u304d\u89d2 \u5ea6 \u306f\u4e8c\u8f2a \u8eca \u3068\u5e8a \u3068\u306e \u9593 \u306b\u8efd \u91cf \u306e\u30a2 \u30fc\u30e0 \u3092\u63a5 \u89e6 \u3055\u305b \u3066\u8a08 \u6e2c \u3057\u3066\u3044 \u308b.\u307e \u305f,\u8a08 \u7b97 \u6a5f \u5185 \u3067\u5f97 \u3089\u308c\u305f\u64cd\u4f5c \u91cf \u306f,D/A\u5909 \u63db \u5668 \u3092\u901a \u3057\u3066\u901f\u5ea6 \u5236\u5fa1 \u7cfb \u3092 \u69cb \u6210 \u3057\u305f\u30b5 \u30fc\u30dc\u30e2 \u30b8\u30e5\u30fc\u30eb(\u30b5 \u30fc\u30dc \u30e9 \u30f3\u30c9(\u682a)SMCM4-AI) \u306b\u4e0e \u3048 \u3089\u308c,\u4e8c \u8f2a \u8eca \u306b\u642d \u8f09 \u3057\u305fDC\u30e2 \u30fc \u30bf(\u5c71 \u6d0b \u96fb\u6c17(\u682a) L406T-011 (60W))\u99c6 \u52d5\u306e\u53f0 \u8eca\u304c\u79fb\u52d5 \u3059 \u308b.\u3053 \u308c \u306b\u3088 \u308a\u4e8c\u8f2a\n\u8eca \u3092\u5b89 \u5b9a\u5316 \u3059 \u308b.\u3055 \u3089\u306b,\u3053 \u306e\u4e8c \u8f2a \u8eca \u306b \u306f\u99c6 \u52d5\u7528 \u304a \u3088\u3073 \u30b9 \u30c6 \u30a2 \u30ea\u30f3\u30b0\u7528DC\u30e2 \u30fc \u30bf(\u5c71 \u6d0b \u96fb\u6c17(\u682a)L406T-011 (60W), L404T-011 (40W))\u304c \u53d6 \u308a\u4ed8 \u3051 \u3066\u3042 \u308a,\u4e8c \u8f2a \u8eca \u3092\u5b89\u5b9a \u5316 \u3057\n\u306a\u304c \u3089\u306e\u8d70\u884c \u304c \u53ef\u80fd \u306a\u69cb \u6210 \u3068\u306a\u3063\u3066 \u3044 \u308b.\nFig. 4\u306b \u793a \u3059\u8a18\u53f7 \u3092\u7528\u3044,\u72b6 \u614b\u91cf \u3092\nx=[d\u03c6d\u03c6]T\n\u3068\u3057\u305f \u3068 \u304d\u672c\u7cfb \u306b\u5bfe \u3059 \u308b\u72b6 \u614b \u7a7a \u9593\u30e2 \u30c7 \u30eb \u306f\u5f0f(1)\u306b \u793a\u3059 \u69cb \u9020\n\u3092 \u3082\u30647).\u3053 \u3053\u3067,", + "24 T. SICE Vol.34 No.1 January 1998\nFig. 3 Schematic diagram of an experimental equipment\n0 0 A21 = _ MMg (MbHb + McHc)g %1 %1 -cs 0 A22 = _ M~ Hccx Cb (15) %1 %1\nB2 = MCHC/3\n+ MCH,2 %1 = MbHb+ A\n\u3067 \u3042 \u308b.\u307e \u305f,\u540c \u5b9a \u5b9f \u9a13 \u306b \u3088\u3063\u3066\u5f97 \u3089\u308c \u305f\u672c \u7cfb \u306e\u7269 \u7406 \u30d1 \u30e9 \u30e1\u30fc \u30bf\u5024 \u3092Table 1\u306b \u793a \u3059.\u306a \u304a,\u3053 \u306e \u30e2\u30c7 \u30eb\u306f \u30b9\u30c6 \u30a2 \u30ea \u30f3\u30b0 \u3092\u56fa\u5b9a \u3057,\u53f0 \u8eca \u306b \u3088\u308b\u5b89 \u5b9a\u5316 \u306e \u307f \u3092\u691c\u8a0e \u3059 \u308b \u305f\u3081\u306e \u3082\u306e\n\u3067 \u3042 \u308b.\n5.2 \u4f4e \u6b21 \u5143\u5236 \u5fa1\u5668 \u306e\u8a2d \u8a08\n\u672c \u7cfb \u306b\u5bfe \u3057\u3066\u524d \u7ae0 \u3067\u63d0 \u6848 \u3057\u305f\u4f4e \u6b21 \u5143 \u5236\u5fa1 \u5668 \u306e\u8a2d \u8a08 \u3092\u884c \u3046.\n\u6700\u521d \u306b\u5b9a \u6570\u91cd \u307fQ,\u91cd \u307f\u4f1d \u9054 \u95a2\u6570W(s)\u3092 \u4ee5 \u4e0b \u306e \u3088\u3046\u306b\u9078\n\u5b9a\u3059 \u308b.\nQ_ 10 of 0 1\nW _ 50 s+50\n\u3053 \u3053\u3067,\u5b9a \u6570 \u91cd \u307fQ\u306f \u4e8c \u8f2a\u8eca \u306b\u53d6 \u308a\u4ed8 \u3051 \u305f \u53f0\u8eca \u306e\u901f \u5fdc \u6027 \u3092\n\u9ad8 \u3081 \u308b \u305f\u3081 \u306b,\u305d \u3057\u3066\u5468 \u6ce2\u6570 \u91cd \u307fW\u306f,50[Hz]\u306e \u96fb\u6e90 \u30ce\u30a4 \u30ba \u306e\u5f71 \u97ff \u3092\u4f4e \u6e1b\u3059 \u308b\u3053 \u3068\u3092\u610f\u8b58 \u3057\u3066\u9078\u5b9a \u3057\u3066 \u3044\u308b.\n\u6b21 \u306b,\u5f0f(10)\u3092 \u7528\u3044 \u3066\u4f4e \u6b21\u5143\u5236\u5fa1 \u5668 \u3092\u69cb\u6210 \u3059 \u308b.\u305d \u306e\u969b \u306b,\n\u03b3=1.05\u03b3min, u3=1\u3068 \u3057\u305f.\u307e \u305f,a\u03c6 \u3067 \u3042\u308b\u304c,\u5b89 \u5b9a\u6027\u3060 \u3051 \u3067 \u306f\u306a \u304f\u81ea\u7531\u30d1 \u30e9 \u30e1\u30fc \u30bf\u306e \u30ce\u30eb\u30e0\u6761\u4ef6 \u3092\u6e80 \u8db3\u3059 \u308b\u3088 \u3046\u306b\u9078\u5b9a\n\u3057\u306a\u3051 \u308c\u3070 \u306a \u3089\u306a\u3044.\u672c \u7cfb \u306b\u5bfe \u3057\u3066\u306f,\u8a08 \u7b97 \u306b \u3088 \u308aa\u03c6>-13 \u3068\u9078 \u3079 \u3070 \u3088\u3044 \u3053 \u3068\u304c \u308f\u304b\u308b.\u4e00 \u65b9,\u3053 \u306e \u6761\u4ef6 \u3092\u6e80\u305f\u3059 \u3044 \u304f\u3064\u304b \u306ea\u03c6 \u306b\u5bfe \u3057\u3066,\u5f0f(13)\u4e2d \u306ea\u03c6+bk-UBs\u3092 \u8a08\u7b97 \u3057\u3066\u307f\u308b \u3068\u307b \u3068\u3093 \u3069\u5dee\u304c\u898b \u3089\u308c\u306a\u3044.\u305d \u3053\u3067,a\u03c6=-10\u3068 \u3057\u305f.\u3053 \u306e \u3068 \u304d,\u03b3=132.6, ||\u03a6||\u221e=0.975, a\u03c6+bk-UBs=-7.06\n\u3067 \u3042 \u308b.\u4ee5 \u4e0a \u306b\u5bfe \u3057\u3066\u5f97 \u3089\u308c\u305f\u5236\u5fa1 \u5668 \u304c\u6b21 \u5f0f \u3067 \u3042\u308b.\n-139 .5 50.0 -3514 6449\nK = -162.6 42.9 -4040 6404 (16)\n1 0 0 0\n\u3053 \u306e\u5236\u5fa1 \u5668 \u306e\u30b2 \u30a4 \u30f3\u7279\u6027(\u5b9f \u7dda)\u3092Fig. 5\u306b \u793a\u3059.\u4e0a \u56f3\u304c\n\u53f0\u8eca\u4f4d \u7f6ed\u304b \u3089\u64cd \u4f5c\u91cf \u307e\u3067 \u306e\u30b2 \u30a4 \u30f3\u7279 \u6027 \u3067\u3042 \u308a,\u4e0b \u56f3 \u304c\u4e8c\u8f2a\n\u8eca \u306e\u50be \u304d\u89d2\u5ea6 \u03c6 \u304b \u3089\u64cd \u4f5c\u91cf \u307e\u3067 \u306e\u30b2 \u30a4\u30f3\u7279\u6027 \u3067 \u3042 \u308b.\u306a \u304a, \u53c2\u8003 \u307e\u3067 \u306b \u03a6(s)=0\u3068 \u3057\u305f\u4e2d\u592e\u89e3(\u3053 \u306e\u5834\u54086\u6b21)\u306e \u30b2 \u30a4 \u30f3\u7279 \u6027 \u3092\u7834 \u7dda \u3067\u793a \u3057\u305f.\u9078 \u5b9a \u3057\u305f \u30ed\u30fc\u30d1 \u30b9 \u30d5 \u30a3\u30eb \u30bfW(s)\u306e\n\u7279\u6027 \u306b \u3088 \u308a\u9ad8 \u5468\u6ce2 \u6570\u5e2f \u57df \u3067\u306e\u30b2 \u30a4\u30f3\u304c\u4f4e \u304f\u306a \u3063\u3066\u3044 \u308b.\u3055 \u3089 \u306b\u9589 \u30eb \u30fc\u30d7\u4f1d \u9054\u884c \u5217 \u306e\u30b2 \u30a4\u30f3\u7279 \u6027\u304c \u9078\u5b9a \u3057\u305f\u91cd \u307f\u4f1d\u9054 \u95a2 \u6570\u3067 \u6574 \u5f62 \u3055\u308c \u3066\u3044 \u308b \u3053 \u3068\u3092\u78ba \u8a8d \u3059 \u308b\u305f \u3081 \u306bK(I-GK)-1\u304a \u3088 \u3073(I-GK)-1\u306e \u30b2 \u30a4 \u30f3\u7279 \u6027(\u5b9f \u7dda)\u3092 \u305d\u308c \u305e \u308cFigs. 6, 7\u306b \u793a\u3059.\u3053 \u3053\u3067,\u03c3(A)\u306f \u4f1d \u9054\u884c \u5217A\u306e \u6700\u5927\u7279 \u7570\u5024,\u03c3(A) \u306f\u6700 \u5c0f \u7279\u7570 \u5024 \u3092\u610f \u5473\u3059 \u308b.Fig. 6\u306b \u304a \u3044 \u3066\u89b3 \u6e2c\u5916 \u4e71 \u304b \u3089\u64cd \u4f5c\n\u91cf \u307e\u3067 \u306b\u76f8 \u5f53 \u3059 \u308bK(I-GK)-1\u306e \u30b2 \u30a4 \u30f3\u7279 \u6027 \u304c \u9ad8\u5468 \u6ce2 \u6570 \u5e2f\u57df \u3067 \u9078\u5b9a \u3057\u305f\u91cd \u307f \u306b \u3088 \u3063\u3066\u6574 \u5f62 \u3055\u308c\u3066 \u304a \u308a,\u3055 \u3089 \u306bFig. 7 \u306b\u304a \u3044 \u3066\u611f \u5ea6 \u95a2\u6570(I-GK)-1\u306e \u30b2 \u30a4 \u30f3\u7279\u6027 \u304c \u4f4e\u5468 \u6ce2 \u6570 \u5e2f\n\u57df\u3067 \u540c\u69d8 \u306b\u6574\u5f62 \u3055\u308c\u3066 \u3044 \u308b\u3053 \u3068\u304c\u308f \u304b \u308b.\u306a \u304a,\u7834 \u7dda \u306f \u4e2d\u592e\n\u89e3 \u3092\u7528 \u3044 \u305f \u3068 \u304d\u306e\u30b2 \u30a4 \u30f3\u7279\u6027 \u3067 \u3042\u308b.\n6. \u5236 \u5fa1 \u5b9f \u9a13\n\u524d \u7ae0 \u3067\u8a2d\u8a08 \u3057\u305f\u5236 \u5fa1\u5668 \u3092\u7528 \u3044 \u3066\u884c \u3063\u305f\u5236 \u5fa1\u5b9f \u9a13\u7d50 \u679c \u3092\u6b21 \u306b\n\u793a \u3059.\u5f0f(16)\u306e \u5236\u5fa1 \u5668 \u3092\u30b5 \u30f3\u30d7 \u30ea\u30f3\u30b0 \u30bf\u30a4\u30e00.1[ms], 0\u6b21 \u30db \u30fc\u30eb \u30c9\u3067\u96e2 \u6563\u5316 \u3057,\u5236 \u5fa1 \u5b9f\u9a13 \u3092\u884c \u3063\u305f.\u5236 \u5fa1 \u5668 \u306e\u5b9f \u88c5 \u306b\u306f DSP-CIT (dSPACE\u793e)\u3092 \u7528\u3044 \u305f.\u5b89 \u5b9a \u306b\u5236\u5fa1 \u3055\u308c\u3066 \u3044 \u308b\u72b6\n\u614b \u3067 \u53f0\u8eca \u306b\u5bfe \u3057\u3066 \u30b9 \u30c6 \u30c3\u30d7 \u5165 \u529b \u3092\u52a0 \u3048 \u305f \u3068 \u304d\u306e \u30b7 \u30df\u30e5 \u30ec\u30fc \u30b7 \u30e7 \u30f3\u306a \u3089\u3073 \u306b\u5b9f \u9a13\u7d50 \u679c \u3092Figs. 8, 9\u306b \u793a\u3059.\u306a \u304a,\u4e8c \u8f2a\n\u8eca \u306e \u56de\u8ee2 \u89d2 \u304c\u6642\u8a08 \u56de \u308a\u304c \u6b63\u65b9 \u5411\u3067 \u3042 \u308b\u306e \u306b\u5bfe \u3057\u3066,\u53f0 \u8eca \u306e\u6b63 \u65b9 \u5411\u304c \u5de6 \u3067\u3042 \u308b \u3053 \u3068\u306b\u6ce8\u610f \u3057\u3066 \u307b \u3057\u3044(Fig. 4\u53c2 \u7167).\u56f3 \u3088\u308a, \u30b7 \u30df\u30e5 \u30ec\u30fc \u30b7 \u30e7\u30f3\u7d50\u679c \u3068\u5b9f \u9a13\u7d50 \u679c\u304c \u826f\u597d \u306b\u4e00\u81f4 \u3057\u3066\u3044 \u308b \u3053 \u3068\n\u304c \u308f \u304b \u308b.\u307e \u305f,\u89b3 \u6e2c \u30ce\u30a4\u30ba \u3092\u4f4e\u6e1b \u3059 \u308b \u76ee\u7684 \u3067\u5c0e\u5165 \u3057\u305f\u91cd \u307f", + "Fig. 5 Gain characteristics of controller\n\u4f1d\u9054\u95a2\u6570W(s)\u306e \u30ed\u30fc\u30d1\u30b9\u30d5\u30a3\u30eb\u30bf\u52b9\u679c\u3067,\u5b9f \u9a13\u7d50\u679c\u306b\u89b3\u6e2c \u30ce\u30a4\u30ba\u306e\u5f71\u97ff\u304c\u73fe\u308c\u3066\u3044\u306a\u3044.\u6b21 \u306b,\u4e8c \u8f2a\u8eca\u304c\u5b89\u5b9a\u306b\u5236\u5fa1\u3055 \u308c\u3066\u3044\u308b\u72b6\u614b\u3067\u30a4\u30f3\u30d1\u30eb\u30b9\u72b6\u306e\u5916\u4e71\u3092\u4e0e\u3048\u305f\u3068\u304d\u306e\u5b9f\u9a13\u7d50\u679c \u3092Fig. 10\u306b \u793a\u3059\u304c,\u826f \u597d\u306b\u5236\u5fa1\u3055\u308c\u3066\u3044\u308b\u3053\u3068\u304c\u308f\u304b\u308b.\n7. \u304a \u308f \u308a \u306b\n\u672c\u8ad6\u6587\u3067\u306f,LSDP\u306b \u57fa\u3065\u304f\u4f4e\u6b21\u5143\u5236\u5fa1\u5668\u306e\u4e00\u8a2d\u8a08\u6cd5\u3092\u63d0\n\u6848\u3057\u305f.LSDP\u306e \u4e2d\u592e\u89e3\u3092\u5229\u7528\u3057\u305f\u5236\u5fa1\u5668\u306e\u6b21\u6570\u306f,\u8a2d \u8a08\u30e2 \u30c7\u30eb\u306e\u6b21\u6570+\u91cd \u307f\u4f1d\u9054\u884c\u5217\u306e\u6b21\u6570 \u00d72\u3068 \u306a\u308b\u306e\u306b\u5bfe\u3057\u3066,\n\u672c\u8a2d\u8a08\u6cd5\u3092\u5229\u7528\u3059\u308b\u3068,\u5f0f(1)\u306e \u8a2d\u8a08\u30e2\u30c7\u30eb\u306b\u5bfe\u3057\u30661\u6b21 +\u91cd \u307f\u4f1d\u9054\u884c\u5217\u306e\u6b21\u6570\u3068\u306a\u308b.\u307e \u305f,\u4f4e \u6b21\u5143\u5316\u306e\u969b\u306b\u8fd1\u4f3c\u6cd5 \u3092\u5229\u7528\u3057\u3066\u3044\u308b\u308f\u3051\u3067\u306f\u306a\u3044\u306e\u3067,LSDP\u306e \u3082\u3064\u6574\u5f62\u6027\u80fd\u304c\n\u640d\u306a\u308f\u308c\u308b\u3053\u3068\u306f\u306a\u3044.\u672c \u8a2d\u8a08\u6cd5\u306e\u6709\u52b9\u6027\u3092\u691c\u8a3c\u3059\u308b\u76ee\u7684\u3067,\n\u4e0d\u5b89\u5b9a\u30e1\u30ab\u30cb\u30ab\u30eb\u30b7\u30b9\u30c6\u30e0\u306e\u4e00\u3064\u3067\u3042\u308b\u4e8c\u8f2a\u8eca\u7cfb\u306e\u5b89\u5b9a\u5316\u5236 \u5fa1\u554f\u984c\u306b\u9069\u7528 \u3057\u826f\u597d\u306a\u7d50\u679c\u3092\u5f97\u305f.\n\u3053\u308c\u307e\u3067,LSDP\u306e \u6b20\u70b9\u3068\u3057\u3066\u5236\u5fa1\u5668\u304c\u6bd4\u8f03\u7684\u9ad8\u6b21\u3068\u306a\u308a\n\u3084\u3059\u3044\u3053\u3068\u304c\u6319\u3052\u3089\u308c\u3066\u304d\u305f\u304c,\u672c \u8a2d\u8a08\u6cd5\u306b\u3088\u308a\u305d\u306e\u6b20\u70b9\u304c \u89e3\u6d88\u3055\u308c\u308b\u53ef\u80fd\u6027\u304c\u898b\u3048\u305f\u3068\u3044\u3048\u308b.\u672c \u8ad6\u6587\u3067\u306f,\u5f0f(1)\u306e\n\u69cb\u9020\u3092\u3082\u3064\u8a2d\u8a08\u30e2\u30c7\u30eb\u306b\u9650\u5b9a\u3057\u3066\u8b70\u8ad6\u3057\u305f\u304c,\u3088 \u308a\u4e00\u822c\u7684\u306a\n\u3082\u306e\u306b\u5bfe\u3057\u3066\u691c\u8a0e\u4e2d\u3067\u3042\u308b.\n\u6700\u5f8c\u306b,\u5b9f \u9a13\u306b\u4f7f\u7528\u3057\u305f\u4e8c\u8f2a\u8eca\u306f\u4f50\u85e4\u62d3\u53f2\u6c0f(\u73fe(\u682a)\u30d6 \u30ea \u30c2\u30b9\u30c8\u30f3)\u88fd\u4f5c\u306e\u3082\u306e\u3067,\u3053 \u3053\u306b\u611f\u8b1d\u306e\u610f\u3092\u8868 \u3057\u305f\u3044.\u307e \u305f,\n\u5b9f\u9a13\u3092\u884c \u3046\u306b\u3042\u305f\u308a\u3054\u5354\u529b\u3044\u305f\u3060\u3044\u305f\u672c\u5b66\u5927\u5b66\u96621\u5e74 \u4e2d\u6751\u4f38 \u541b\u306b\u3082\u611f\u8b1d\u306e\u610f\u3092\u8868 \u3057\u305f\u3044." + ] + }, + { + "image_filename": "designv8_17_0003738_school_dissertations-Figure4.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003738_school_dissertations-Figure4.4-1.png", + "caption": "Figure 4.4: (a) Injected IDDQ and oscillation testable faults. Note: XFIT is an n-MOS faultinjection transistor. XFIT 1 and XFIT 3 are IDDQ testable faults. XFIT 1-7 are oscillation testable faults and (b) fault-injection transistor (FIT).", + "texts": [ + "10: BICS showing PASS/FAIL output from HP1660CS Logic Analyzer corresponding to fault M10DSS (a) VENABLE and VERROR connected to 5 kHz signal at 300k. (b) VENABLE and VERROR connected to 5 kHz signal at 77 K. ..........94 Figure 4.11: BICS showing PASS/FAIL output from HP1600CS Logic Analyzer corresponding to fault M10DSS. (a) VENABLE and VERROR connected to 1 MHz signal at 300 K. (b) VENABLE and VERROR connected to 1 MHz signal at 77 K...........................................................................................................................95 Figure 4.12: Simulated IDDQ of the circuit of Figure 4.4. Note: 77 K plot is nearly same and differs marginally from 300 K plot. ...................................................................97 Figure 4.13: Influence of BICS on VSS. Note: There is insignificant difference between plots at 300 K and 77 K.(a) BICS enable signal (b) Voltage at point EXT of the circuit of Figure 4.3.............................................................................................98 Figure 4.14: A two stage floating gate input CMOS op-amp..................", + " Input signal to the CUT should produce a noticeable amount of difference between the power supply current of each faulty case and fault-free case. In the present work, the tolerance limit for the magnitude of IDDT with no injected faults is defined as \u00b15%, such that it will take into account the deviations of significant technology and design parameters. The magnitude of power supply current, IDDT is determined with every injected fault. If the simulated IDDT value falls out of the tolerance limit the fault is detected. Figure 4.4 (a) shows the CMOS amplifier circuit of Figure 4.1 with fault-injection transistors (FITs) simulating manufacturing defects. Figure 4.4 (b) shows a simple fault- 83 injection transistor [86, 97]. The fault injection transistors are activated by connecting the gate of the transistors to VDD. The use of a fault-injection transistor for the fault simulation prevents permanent damage to the operational amplifier by introduction of a physical metal short. All fault injection transistors embedded are of uniform size 4.5um/1.6um. Eight faults have been introduced into the amplifier circuit of Figure 4.4 (a). Seven faults are injected into the amplifier using fault injection transistors and the eighth fault which is an open fault is introduced by connecting the gate of transistor M11 to VSS. The injected faults in the amplifier are as follows: Fault-1: M10 drain-source short (M10DSS), Fault-2: M5 gate-drain short (M5GDS), Fault-3: M5 drain-source short (M5DSS), Fault-4: M11 drain-source short (M11DSS), Fault-5: compensation capacitor short (CCS), Fault-6: M7 gate-drain short (M7GDS), Fault-7: M6 gate-drain short (M6GDS) and Fault-8: M11 gate to VSS (M11GVSSS). Figure 4.5 and Figure 4.6 shows the layout and microphotograph of the fabricated chip. Figure 4.7 shows the measured gain versus frequency dependence behavior of the CMOS amplifier circuit. It can be observed from Figure 4.7 that the open loop gain has increased from 65.4 dB at 300 K to 69.2 dB at 77 K and the 3 dB bandwidth of the amplifier has increased from 3.5 kHz at 300 K to 9.5 kHz at 77 K. The amplifier circuit of Figure 4.4 (a) has been converted into an oscillator circuit according to Figure 4.2 (b) and has been simulated in SPICE for the injected oscillation-based faults. The Fast-Fourier Transform (FFT) analysis has been performed to determine the natural oscillation frequency and is shown in Figure 4.8. The natural oscillation frequency of the CUT oscillator is 875 kHz at 300 K and 1.858 MHz at 77 K. Figure 4.9 shows the Monte-Carlo simulated results of the parametric (threshold-voltage, Vth of the CUT transistors, R1, R2, R, C) tolerances (5%) gives a deviation of [-2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004054___lang_en_format_pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004054___lang_en_format_pdf-Figure7-1.png", + "caption": "Fig. 7. Physically designed MPAs (Conventional microstrip line edge fed MPA and three compact MPAs) (a) Top View (b) Bottom view.", + "texts": [ + " The corresponding design parameters of Design_3 MPA are L = 29.5 mm, Lc = 13.05 mm, and W1 = 11.7mm. Since Design_2 MPA is resonating exactly at 2.4 GHz with good performance parameters, no optimization is performed. The summary of all the design parameters of three compact MPAs post optimization is listed in Table III. After optimized parameters are obtained, the three compact MPAs and only the microstrip line fed conventional MPA are physically fabricated. These fabricated MPAs are shown in Fig. 7. In Design_1, the patch area has reduced by 70% from 0.29 \u03bb0 \u00d7 0.22 \u03bb0 (Conventional microstrip line edge feed MPA) to 0.15 \u03bb0 \u00d7 0.13 \u03bb0 (proposed Design_1 MPA). The overall volume of this MPA is reduced by 57% from the conventional one. Using the same principle for Design_2 MPA, the patch area reduction and the volume reduction achieved are 35% and 25%, respectively compared to its conventional proximity-coupled fed MPA. Similarly, for Design_3 MPA, the patch area reduction and the volume reduction achieved are 38% and 33%, respectively compared to its conventional aperture-coupled fed MPA" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure28-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure28-1.png", + "caption": "Figure 28: 8 joint compliant mechanism.", + "texts": [ + " This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004801_cle_2630_context_etd-Figure7.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004801_cle_2630_context_etd-Figure7.4-1.png", + "caption": "FIGURE 7.4: TWO ISOTROPIC POINT SOURCES SEPARATED BY A DISTANCE d.", + "texts": [ + "14) where the terms I12/I I and 113/I1 I are less than 1.0 in magnitude. The mutual impedances Z12 and Z3 being inductive, they will make the input impedance of the antenna more inductive, ( or less capacitive) This will have the effect of decreasing the resonant frequency of the antenna, which explains the sizereduction properties of meander antennas. 7.1.3 RADIATED FIELD OF A MEANDER DIPOLE The radiated fields of meander antennas can be explained on the basis of the Array Theory. [4] Refering to Figure 7.4, we have two isotropic sources separated by a distance d. If the two sources are identical in amplitude and of the same phase, and assuming they have the same polarization, the far field is given by: E = E + E 2 ejN (7.15) where: Ei= far electric field at a distance r due to source 1 E2 = far electric field at a distance r due to source 2 V= (2nd/A)cos 9 The quantity yis the phase-angle difference between the fields of the two sources measured along the radius-vector line at the angle 9 13'3 7.2 CONCLUSIONS It has been proven that a meander antenna such as the one designed in this thesis is feasable and can be used in many practical applications" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003576_05_6_2005_6_467__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003576_05_6_2005_6_467__pdf-Figure5-1.png", + "caption": "Figure 5 Test system", + "texts": [ + " The piston changes the direction of its movement to the left. As these steps are continuously repeated, the self reciprocating motion of the piston continues. EXPERIMENTAL METHOD Fundamental characteristics of the motion were tested for the both of the short stroke and the long stroke types. The piston's displacement, speed, force, and the supply flow rate and pressure were measured under steady working conditions. The tests were carried out under the two kinds of load; inertia mass and constant force loads. As shown in Figure 5, the constant force load is given by using a magnetic brake (see (a)), and the inertia mass load was given by stacking iron plates on a plate with wheels (see (b)). The mass of each iron plate is 2 kg. The water is supplied to the actuator through a common nylon tube of 5 m length from a tap water network. The maximum pressure at the tap is about 0.4 MPa. The flow rate is detected by a turbine flow meter, the supply pressure is by a strain gauge type pressure transducer, the displacement of the piston is by a magnetic displacement detector and the force is by a load cell to be available for the both of tension and compression" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002707_8948470_09199824.pdf-Figure26-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002707_8948470_09199824.pdf-Figure26-1.png", + "caption": "FIGURE 26. Simulation environment. The top shows the desired and filtered velocity commands based on the closest point in the point cloud. The bottom shows the drone navigating through the cave.", + "texts": [ + " In practice, feasibility is regained quickly and this is the approach we take for the following simulations. The simulation environment is a ROS-based C++ environment. The point-cloud data is obtained from a modified Velodyne LIDAR sensor inside of the Gazebo simulator at a frequency of 10 hz. The simulation, including visualization in Gazebo and RVIZ, was able to run at a frequency of 300 Hz on a modern laptop computer. The cave environment to explore was a large 240m by 460m structure with one entrance and one exit (cf. Fig. 32 and Fig. 26). The cave height is constant at roughly 3m, but the width is constantly changing, and gets as small as 0.5m with several protruding areas. The quadrotor was able to explore the entire 240m by 460m cave in just under 28 minutes (cf. Fig. 32). The maximum allowable speed from the planner was 5 m/s, which the drone reached during open areas of the cave. The average desired speed sent from the planner was 4.09 m/s, and the average speed of the drone after the safety filter was 3.28 m/s. A positive value of the barrier functions was maintained throughout, meaning the quadrotor never went closer than the minimum allowed distance from a point in the point-cloud, which was set at 1h = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002315_cle_download_253_179-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002315_cle_download_253_179-Figure5-1.png", + "caption": "Figure 5. Two Passenger Coaches Analyzed in Simulation : (a) Passenger Coach Model of SS-2018, (b) Passenger Coach Model of SS-NG.", + "texts": [ + " As shown in the picture, this model consists of six vertical dampers, one lateral damper, four primary suspensions, eight secondary suspensions in the form of metal springs, and four swing links that are used to connect the bogie frame, bolster, spring plank, and wheelset. Figure 4 displays a contact model between the train wheels to the rail line in the simulation. The dimensions of the wheel were 0.387 m for the radius, 1.844 m for axle length, 0.565 m for center distance, 1500 kg for the mass, 1.067 m for the width of the rail gauge, and 1: 40 for the wheel conicity. As shown in this figure, the railroad track has a width of 70 mm and these rail lines would be in contact with the wheels while the train is operating in the simulation. Figure 5 displays two passenger coaches that would Dynamic Analysis on Stainless Steel New Generation Passenger Coach using Multibody Dynamic System (Saka Marga Redi) be analyzed in the simulation; Figure 5(a) is the passenger coach model of SS-2018. Figure 5(b) is the passenger coach model of the SS-NG, the model which is developing in this study. This model has several differences from the old model such as the replacement of rubber springs on the primary suspension, a different bogie frame design, and the addition of a yaw damper. In addition to the passenger train model as described above, several parameters were required in the simulation. Those parameters are car body mass, bogie mass, train mass, the distance between bogie center and car body center, and distance between bogies, each of which is 31186 kg; 9669 kg; 40855 kg; 7 meters; and 14 m" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002247_6514899_10415015.pdf-Figure28-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002247_6514899_10415015.pdf-Figure28-1.png", + "caption": "FIGURE 28. Propagation of waves between two layers", + "texts": [ + " Increased illumination of the reflecting surface can improve antenna directivity or gain; hence, a partially reflecting slab (MTM slab) is positioned in the vicinity of the radiator and parallel to the reflector, which increases the rate of reflection, thus increasing the illumination. The separation distance between the full and partial reflectors is important in achieving maximum reflection, and the two reflectors should be placed in such a way that the rays reflected through the partial slab into the air medium are in phase with the normal direction [28][29]. Assume that the antenna is emitting a wave with the element pattern \ud835\udc53(\ud835\udefc) that is emanating from point P as illustrated in Figure 28. When a metamaterial slab or partially reflecting surface (PRS) is placed at a fixed distance '\u210e' from the patch layer, continuous reflections with reduced amplitudes occur between the surfaces. In general, the reflection coefficient of the PRS is \ud835\udc5d\ud835\udc52\ud835\udc57\ud835\udf13, and for an ideal case, the transmission loss will be 0, thus the magnitude of the ray 0 is equal to \u221a1 \u2212 \ud835\udc5d2, the magnitude of the ray 1 is equal to \ud835\udc5d\u221a1 \u2212 \ud835\udc5d2, and the magnitude of the ray 2 is equal to \ud835\udc5d2\u221a1 \u2212 \ud835\udc5d2, and so on. The E-field density in the Fraunhofer region is the vector summation of these reflected rays, and for an infinite reflecting and partial reflecting surface, the E-field is given by \ud835\udc38 = \u2211 \ud835\udc53(\ud835\udefc) \ud835\udc380\ud835\udc5d\ud835\udc5b\u221a1 \u2212 \ud835\udc5d2\ud835\udc52\ud835\udc57\ud835\udf03\ud835\udc5b (16)\u221e \ud835\udc5b=0 where \ud835\udf03\ud835\udc5b is the phase angle that specifies the phase fluctuations of waves when they propagate across two surfaces, as well as the path difference between two rays" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure19-1.png", + "caption": "Fig. 19. Characteristic design solution of position and way of mounting of shaft-mounted single-stage gear reducer (Dodge solution) [19].", + "texts": [ + " NRW produces gear units with the classic input shaft and with the adapter for IEC motors with flanges B5 and B14. The design of the housing is quite complex, taking into account the cost savings of the material as well as the reinforcement of the housing. The form is simple and attractive (Fig. 18). [5] * Corresponding author: racmil@uns.ac.rs Single-stage gear reducer with free shaft arrangement, ie. shaft-mounted gear units are mounted directly to the driving shaft and the shaft position itself adapts to the specific mounting conditions (Fig. 19). Using special mounts this position can be adapted to different positions and ways of mounting (Fig. 20), but these solutions are somewhat expensive than usual footmounted or flange-mounted solutions. * Corresponding author: racmil@uns.ac.rs Based on the performed design solutions of single-stage gear reducers produced by leading manufacturers of gear units, it can be concluded that further intensive development of all types of these reducers can be expected. Gear reducer with horizontal shaft arrangement, with the housings with feet on all four sidewise surfaces and with connected flanges (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001352_pdf_tmm-18-e2473.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001352_pdf_tmm-18-e2473.pdf-Figure4-1.png", + "caption": "Figure 4. Kingpins: 2-inch with 8 and 12 holes (left) and 3.5-inch with 8 and 12 holes (right).", + "texts": [ + " However, the validation criteria for mechanical tests are not usually reported. Therefore, the present work shows the method validation for fatigue 3/12Tecnol Metal Mater Min. 2021;18:e2473 of the MTS brand FlexText (16 bits) performed the reading of force values by the load cell, equipped with the Station Manager 5.1C software. Thus, Figure 3 shows examples of the force transducers. Kingpin is an automotive component that, along with the fifth wheel, links the horse to the semi-trailer in automotive wagons. There are several kingpin models (two shown in Figure 4) that can be exemplified as: 2 and 8-inch kingpin with 8 and 12 holes and 3.5-inch kingpin with 8 and 12 holes. The kingpin fatigue test consists in applying horizontal forces perpendicularly to the pin axis, with a frequency of less than 30 Hz, during 2,000,000 cycles. In the test, the values of maximum and minimum force are acquired and stored in every 100 cycles for further data analysis. In this work, the criteria (Figure 1) were selected for the method validation. Therefore, criteria are briefly described below" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004385_aper_ETC2017-356.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004385_aper_ETC2017-356.pdf-Figure12-1.png", + "caption": "Figure 12: CFD grid for CORN 90o (left) and CORN 45o (right)", + "texts": [], + "surrounding_texts": [ + "Trying to further optimize the recuperation installation, two alternative designs were conceptualized. For the design and investigations a customizable numerical tool modelling the recuperation system operational heat transfer and pressure loss characteristics was developed. This numerical tool was based on an advanced porosity model approach in which the HEXs macroscopic behaviour was included through the integration of predefined heat transfer and pressure loss correlations which were previously calibrated through detailed 2D and 3D CFD computations in Fluent CFD software (with the use of the Shear Stress Transport (SST) turbulence model of Menter (1994) and experimental measurements. These correlations were incorporated in the CFD computations with the addition of appropriate source terms in the momentum and energy equations, as presented in detail in Fig. 5. More specifically, Fig.5a presents the system of equations (momentum and energy equations) for the hot-gas outer flow. In these equations the effect of the pressure losses on the outer hot-gas flow is included by the addition of source terms in the x, y and z directions. These correlations correspond to modified formulation of the Darcy-Forchheimer equation and take into account the viscous and inertial effects on the hot-gas pressure losses through the coefficients 10 ,aa and 210 ,, bbb . These coefficients were derived by experimental measurements and CFD computations through a trend line curve fitting process, for various heat exchanger conditions. The energy source term is responsible for the linking and the achieved heat exchange between the hot-gas flow and the cold-air. This is achieved by the use of the overall heat transfer coefficient, U. This coefficient is calculated, as shown in Fig.5b, by the independent calculation of the inner (cold-air) and outer (hot-gas) heat transfer coefficients (by neglecting the effect of conduction in the thin tube walls) with the help of specifically derived Nusselt number correlations. These correlations were also derived with the combined use of experimental measurements and CFD computations. Regarding the inner (cold-air) flow, this was modeled by the inclusion of an additional set of equations (Fig.5c) corresponding to the transport of the total specific enthalpy and the inner flow total pressure. The calculation of the inner flow pressure losses was performed with the use of a friction loss coefficient, f . In addition, the numerical tool included the effect of the most important and deterministic HEX design decisions such as: dimensions and positioning of the tubes collectors, tubes geometrical characteristics (diameter, length, profile) and arrangement, modifications in the inner-outer flow currents relative orientation and HEX material selection among others. Additional details about the customizable numerical tool can be found in Yakinthos et al. (2015). The first of the two alternative concepts was named as CORN (COnical Recuperative Nozzle). The CORN concept is following a conical design with a 6/5/6 elliptic tubes arrangement, presented in Fig. 6. The elliptic tubes are bent as also shown in Fig. 6, in order to be aligned to the flow direction through the HEX and minimize inner pressure losses since the hot-gas mass flow encounters a much larger recuperator inlet region, thus entering inside the recuperator with significantly reduced flow velocity resulting in reduced outer pressure losses. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. The upstream region of the installation right before the HEX was redesigned in relation to the NEWAC nozzle configuration (including various modifications in the guiding walls and aerodynamic cone) in order to eliminate the size of the recirculation region which was developed there in the previous recuperation installations (reference, NEWAC) as much as possible. Two CORN versions, presented in Figs. 7 and 8, were investigated where the collectors of the cold air are placed circumferentially either every 45o or every 90o leading to a total of 8 or 4 collectors, respectively for the 360o of the Nozzle. The second of the two alternative concepts was named as STARTREC (STraight AnnulaR Thermal RECuperator). The STARTREC concept is following a straight annular design, presented in Fig. 9. Two STARTREC versions were investigated consisting of two and three banks respectively, which are presented in Figs. 10 and 11. In these versions, the gap spacing between the elliptic tubes was altered in relation to the initial MTU design, in order to reduce the pressure losses. All banks were having a 4/3/4 elliptic tubes arrangement with the gap spacing being coarser at the front banks and sparser at the back banks which, due to the gradual cooling of the hot-gas, operated with higher density values and lower flow velocities. In addition, the upstream region of the installation right before the HEX was redesigned (including various modifications in the guiding walls and aerodynamic cone) in order to reduce the size of the recirculation region which was developed there as much as possible. The distribution of the inner flow (cold air) through the collectors is presented in Figs. 10 and 11. The orientation of the elliptic tubes in relation to the main axis of the installation is shown in Fig. 9 (right), where it can be seen that the elliptic tubes are aligned to the main flow direction in the installation in order to ease the flow guidance through the HEX. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. Additionally, the elliptic tubes are aligned to the main flow direction in the installation in order to ease the flow guidance through the HEX. The heat transfer is taking place between the hot-gas passing through the outer stream of the HEX elliptic tubes and the cold air circulating inside the elliptic tubes. At the next step, 3D CFD models were created for all CORN and STARTREC versions (presented in Figs. 12 and 13) and CFD computations were carried out for Average Cruise conditions (details about the conditions can be found in Schonenborn et al. (2004)) with the use of the SST turbulence model of Menter (1994) and Fluent CFD software. Due to its complexity and the extremely large number of elliptic tubes, the modelling of the precise HEXs geometry could not be afforded since the required size of the computational grid capable of providing grid independent results for a single HEX could easily surpass one hundred millions computational grid points. Figure13: CFD grid for STARTREC two banks (left) and STARTREC three banks (right) As a result, the HEXs were modelled by following a porous media approach, with the use of the customizable numerical tool. In this approach CFD models of approximately two million computational nodes were used and could provide grid independent results. At the inlet of the computational domain the mass flow, flow direction, total temperature and turbulence intensity were defined. At the outlet of the computational domain, average static pressure was imposed. The total pressure losses of the aero engine hot-gas exhaust nozzle installation, together with the inner total pressure losses and the recuperator thermal efficiency (as calculated form the CFD results) were then incorporated as input values in the thermodynamic cycle analysis software GasTurb 11, Kurzke (2011), and the thermodynamic cycle for each CORN and STARTREC version (two and three banks versions) were calculated. An indicative view of the IRA engine thermodynamic cycle is presented in Fig. 14. Comparative performance of the various recuperation concepts which were examined are presented in Table 1 in relation to a conventional non-intercooled and nonrecuperated aero-engine of similar technology level with the IRA engine for the specific fuel consumption, and in relation to the NEWAC nozzle configuration for the recuperator major characteristics (pressure losses, effectiveness and weight) in order to proceed to a state-of-the-art comparison and present a quantification of the recuperator achieved improvement. As it can be seen, for the most beneficial concept (CORN 45o) the strongest effect is due to the pressure losses significant reduction which compensates for a small reduction in recuperator effectiveness. This pressure loss reduction is particularly important for the CORN 45o and is the result of two parameters. More specifically, regarding the outer pressure losses, the conical shape of the CORN 45o hot-gas inlet available area results in a drastic reduction of the hot-gas mean flow velocity. This is the same reason due to which CORN 90o configuration presents also reduced outer pressure losses as shown in Table 1. However, regarding the inner pressure losses the most critical parameter is the use of sufficient number of collectors in order to reduce the cold-air flow velocity inside the feed tubes and at the same reduce the tubes length. Thus, the use of 8 collectors provided a very good combination of tubes inner flow velocity and tubes length, resulting in significantly reduced inner pressure losses for the CORN 45o configuration." + ] + }, + { + "image_filename": "designv8_17_0002053_e_download_2200_1306-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002053_e_download_2200_1306-Figure5-1.png", + "caption": "Figure 5: 3D model of a segment of the routing system", + "texts": [ + " One main benefit of changing this routing system into 5 different segments is the additional flexibility that is allowed. As a human\u2019s leg and knee flexion angle will frequently change when in motion, this design allows the exoskeleton to become more flexible and adaptable to the person\u2019s movement, as well as being more comfortable and natural to the user. For a more ergonomic design, all the corners and straight edges have also been curved in order to minimize any physical harm upon physical contact. Figure 5 is an example of one of the five segments. I cut out the top half\u2019s middle part so that the adjacent segments would be able to fit into the gap and be connected using the holes on either side. Therefore, an alternating pattern was designed in which they would be able to smoothly connect to each other while maintaining the routing system shape. The bottom half (uncut side) of each segment mimics the routing route pattern and is uncut so that the exoskeleton has a basic foundational shape. The holes used to connect the adjacent segments together are placed on the edges of the segment as this ensures maximum flexibility and rotational ability" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001549_tation-pdf-url_35276-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001549_tation-pdf-url_35276-Figure11-1.png", + "caption": "Fig. 11. Trochoidal paths of rack cutter with a fully rounded-tip for constant clearance", + "texts": [], + "surrounding_texts": [ + "Computer graphs of generating and generated surfaces can be obtained by using a programming language and graphic processor. In this study codes are developed by using GW-BASIC language to obtain the coordinates of the surfaces. GRAPHER 2-D Graphing System is used for displaying computer graphs of the cutters and gears. Also the ANSYS Preprocessor module is used for displaying gear generating process. Illustrative examples are given for both rack- and pinion-type cutters for different types of tool tip geometries. For rack-type generation, types of tip fillet geometry are selected from the study proposed by Alipiev (Alipiev, 2009, 2011) and the related geometries displayed in the table are adopted to the present mathematical model. Table 1 displays the variation of tip geometry of the rack cutters. www.intechopen.com As illustrated in Table 1, the rack cutter of type-1a has different clearances at its different sides. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. The tooth semi-thicknesses at pitch line of the cutter are different from each other. Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 2.01 and right side radius of rounding m 3.02 . Figure 8 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. As illustrated in Fig. 2. and classifed type-1b in Table 1, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The tooth semi-thicknesses at pitch line of the cutter are same. This type of cutter is adopted from the standard generating rack to asymmetric gearing. The relation ship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 38.01 and right side radius of rounding m 33.02 . Generating and generated surfaces and trochoidal paths are illustrated in Fig 9. Rack cutters with asymmetric teeth can also be designed with full rounded tips. The rack cutter of type-2a has a single rounded edge. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. As depicted in Table 1 the centers of the rounded tip are at the center line of the cutter tooth. The tooth semi-thicknesses at pitch line of the cutter are same. Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 5.221 , right side pressure angle 152 , left side radius of rounding m 4.01 and right side radius of rounding m 587.02 . Figure 10 displays the generating cutter of type-1a, generated surface and trochoidal paths of the tip. For visual clearity, only the corresponding halves (of secondary trochoids) that contribute to final formation of the generated tooth shape are shown. www.intechopen.com Mechanical Engineering 518 www.intechopen.com www.intechopen.com Mechanical Engineering 520 As classifed type-2b in Table 1, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The tooth semi-thicknesses at pitch line of the cutter are different. The relation ship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 5.221 , right side pressure angle 152 , left side radius of rounding m 514.01 and right side radius of rounding As illustrated in Table 2, the shaper cutter of type-1a has different clearances at its different sides. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 35.02 . Figure 12 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. www.intechopen.com As illustrated in Fig. 3. and classifed type-1b in Table 2, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The relationship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 222.02 . Generating and generated surfaces and trochoidal paths are illustrated in Fig 13. The shaper cutter of type-2a has a single rounded edge. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. As depicted in Table 2 the centers of the rounded tip are at the center line of the cutter tooth. Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 373.01 and right side radius of rounding m 449.02 . Figure 14 displays the generating cutter of type-2a , generated surface and trochoidal paths of the tip. For visual clearity, only the corresponding halves (of secondary trochoids) that contribute to final formation of the generated tooth shape are shown. The shaper cutter with asymmetric involute teeth and with a single rounded edge can not be designed for constant clearance in case of standard tooth height. As illustrated in Fig. 3., the center of the rounding should be on the pressure line of the cutter. As a result, the geometric varieties of pinion-type tool tip is limited for indirect generation. www.intechopen.com Mechanical Engineering 522 www.intechopen.com Figure 17 displays relative positions of the pinion cutter with symmetric involute teeth and a fully-rounded tip. The trochoidal curves exhibits symmetry according to center line of gear tooth space. Generating with a sharp-edge pinion cutter is depicted in Fig.18. In this case, primary trochoids determine the shape of the generated tooth fillet. The secondary trochoids do not exist. Video files displaying generating positions of the cutter can be obtained with a proper software. In this study, ANSYS Parametric Design Language (APDL) is also used for obtaining graphic outputs and animation files displaying the simulated motion path of the generating cutters (ANSYS, 2009). Video files can be seen in the author\u2019s web page: http://www.istanbul.edu.tr/eng2/makina/cfetvaci/gearpage.htm www.intechopen.com Mechanical Engineering 524 www.intechopen.com Computer Simulation of Involute Tooth Generation 525" + ] + }, + { + "image_filename": "designv8_17_0002707_8948470_09199824.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002707_8948470_09199824.pdf-Figure11-1.png", + "caption": "FIGURE 11. Segway vehicle used for experiments.", + "texts": [ + " These two operating systems are able to share information through a shared memory interface. All of the code running on the Segway is written in C++. In order to test the implicit safety filter on the Segway, a model of the dynamics is required. The equations of motion are derived via Newton-Euler method, treating the Segway as a two-wheeled inverted pendulum with torque inputs at each wheel. For this experiment, the planar model is used, consisting of four states: position (p), velocity (p\u0307), pitch angle (\u03c8), and angular rate (\u03c8\u0307) (cf. Fig. 11a). Since themotor controllers command current, the motor torque constant is estimated via system identification. The other necessary parameters, including the mass and inertia properties of the Segway frame 187260 VOLUME 8, 2020 and wheels, were measured directly using various custommade testbeds. The next step is to define the safety set for the test. This is simply defined as bounds on all of the states, with p \u2208 [\u22121, 1] m, and \u03c8 \u2208 [\u2212\u03c06 , \u03c0 6 ] rad. The input bounds are u \u2208 [\u221220, 20]A. After identifying the system dynamics and determining a safety set, a backup set and backup controller must be generated" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000709_.1117_12.2307961.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000709_.1117_12.2307961.pdf-Figure8-1.png", + "caption": "Figure 8: Primary & Secondary blank mirror", + "texts": [], + "surrounding_texts": [ + "3.1 RSI overall configuration The Instrument features two main parts: The push-broom camera which includes the telescope and the Focal Plane Assembly (FPA) attached to the rear side of the telescope: Two Instrument Processing Units (IPU) mounted in cold redundancy inside the Bus and whose functions are to ensure the video data processing, the data compression and the telemetry/telecommand data processing (including thermal acquisition and control). 3.2 RSI Camera Telescope optical concept The camera is based on a compact Cassegrain-type telescope and a four-lenses field corrector Figure 5: Telescope optical concept Focal Length 2896 mm Pupil Diameter 600 mm F/N = 4.83 Field of View +/- 0.8\u00b0 Optical Quality WFE < 40 nm rms Figure 6: Optical Sub-assembly characteristics Silicon carbide for mirrors and structure The RSI design is based on an all-SiC opto-mechanical architecture (telescope structure, mirrors, and focal plane structural elements). This monolithic design approach, combined with the intrinsic SiC100 properties (high stiffness, low density, low thermal expansion, high thermal conductivity) allows to combine a high level of stability together with a low mass. Low mass: telescope mass ~ 60 kg, High Rigidity: first Eigen frequency >100Hz, High mechanical stability: inter mirror stability lower than 5\u03bcm, High thermo-elastic stability: quasi a-thermal configuration. Telescope structure The telescope structure is only featuring three main parts: the main plate (supporting the primary mirror), the secondary mirror support, and the rod connecting those two parts. ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-3 Telescope mirrors SiC mirrors can be light-weighted and polished with a high accuracy. Both mirrors were SiC CVD1 coated before polishing in order to minimize the roughness The Wave-front Error (WFE) was measured below 20 nm rms for each mirror, with a roughness lower than 1.0 nm rms. 1 CVD: Chemical Vapor Deposition Refocusing capability The secondary mirror is fixed on the structure by its interface flange. The primary mirror is fixed on to the structure through three iso-static invar mounts and thus thermally decoupled from the structure. Its temperature is controlled by a heater plate located between the mirror and the mounting plate. Setting different thermal control set points between the telescope structure and the primary mirror leads to a variation of the focal plane position, thanks to the low - but nonnull \u2013 thermal expansion coefficient of silicon carbide. The refocusing capability is +/- 200\u03bcm for a +/- 5\u00b0C thermal set point variation. Focal Plane Assembly (FPA) The focal plane assembly features only two CCD for the 5 required spectral bands. One CCD is dealing with the Panchromatic band and the other one is dealing with the multi-spectral bands. The separation of the entrance optical bean is ensured by an optical field separator. ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-4 A 4-line CCD for Multi-spectral bands ROCSAT2 took benefit of the pre-development performed by Atmel, under a CNES R&D contract. The TH31547 multi-spectral CCD consists of 4 photodetector lines, each line being made of 6000 photodiodes with 13\u03bcm step. The detector is operated at 5 Mpixel/s per video output. Each CCD line is coupled with a spectral band filter. The four slit filters are coated on the same glass substrate glued on the CCD. High speed video processing for the panchro- matic channel The panchromatic detection chain is based on the wellknown TH7834B detector (12000 useful 6.5 x 6.5 \u03bcm\u00b2 pixels). The challenge was to operate the four serial read-out registers at a 10 MHz pixel rate for satisfying the 308\u03bcs integration time required to achieve the 2- meter resolution. Front end electronics Each CCD is connected to a dedicated front-endelectronic board which ensures the clock driver distribution and the video signal pre-amplification. Integrated FPA ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-5 3.3 Integrated Video Processing Function The Instrument Processing Unit (IPU) is gathering the instrument electronics functions in a modular and highly integrated assembly. The IPU is coupled with the Focal Plane Assembly front-end electronics - Panchromatic Electronics Board (PEB) & Multi-spectral Electronics Boards (MEB) \u2013 and also with three Spacecraft main units: the On Board Management Unit (OBMU), the Solid State Recorder (SSR), and the Distribution & regulation Unit (DRU). Each IPU includes the necessary functions: to operate both CCD detectors - through the front end electronics located in the FPA to process the video analogue signal and to condition and to digitise all the pixel values, to compress the data flow with an improved adaptative rate regulated JPEG algorithm, to ensure the instrument thermal control. These functions are split on seven electronics boards racked in the same unit. 3.4 RSI Main Characteristics ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-6" + ] + }, + { + "image_filename": "designv8_17_0001040_77_aoje_2_021025.pdf-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001040_77_aoje_2_021025.pdf-Figure21-1.png", + "caption": "Fig. 21 Surface loaded curling shape. The surface is loaded with a concentrated end load and activated over a range of motion from almost (a) flat to (d ) fully curled, where its shape is measured from photogrammetry (dotted contours) and predicted with the model (solid contours).", + "texts": [ + " While all efforts were made to minimize or characterize these uncertainties, it is expected that they will cause some additional validation error. 5.3 Surface Loaded Shape Validation. To validate the surface model, the surface prototype is loaded with a concentrated end load and curls under increasing vacuum pressure. The surface curling shape is measured through photogrammetry and compared with the surface model prediction using the applied torque and actuation pressure. To apply a concentrated end load, the surface prototype is clamped horizontally at one end with a weight hung on the last tile at the cantilevered end (Fig. 21). As the vacuum pressure increases, the surface curls from almost flat to fully curled against the internal tile-tile hard stop. The surface curling shape is measured via photogrammetry, where the curling angles at each hinge are obtained from the positions of the colored markers placed on Fig. 20 Surface prototype demonstration. A surface prototype with five hinged T-shaped tiles of 0.5 in. height, 0.4 in. kinematic width, 9 in. full width, and 6 in. length is fabricated and demonstrates the curling and straightening functionalities through its fourstate operation cycle: (a) fully straight, (b) curling, (c) fully curled, and (d) straightening", + " The surface internal tile shapes are plotted at four different values of vacuum pressures for a given 0.22 lb (0.1 kg) weight based on the curling angles and the tile geometry. The measured locations (dotted contours) are close to the locations predicted from the surface model (solid contours) over the entire range of motion. The model error accumulates along the hinges, causing the surface shape to appear to deviate more near the loaded end, but the curling angle errors remain relatively small (approximately 1\u20133 deg) at each hinge. Since the curling torque scales with pressure, the results in Fig. 21 also indicate that the 6 in.-long surface prototype can lift up to 7 lb cantilevered end load to 35 deg of surface curling, and 2.5 lb to over 90 deg curling (corresponding to approximately 14 lb and 5 lb distributed load). This is larger than the weight of typical debris. For example, a 6 in. depth of packed snow would weigh 4.7 lb distributed over the 6 in. prototype, and a 2 in. depth of wet leaves would weigh only 0.64 lb [52]. The air surface prototype is run through the full range of curling motion from flat to fully curled under three different weights of 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002707_8948470_09199824.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002707_8948470_09199824.pdf-Figure18-1.png", + "caption": "FIGURE 18. Schematic representation of the Atalante exoskeleton. In red are the joints that will be used for variable assistance.", + "texts": [ + " As we are about to see, the framework presented in this 187264 VOLUME 8, 2020 paper can be used to enable assist-as-needed strategies while guaranteeing coherence of the walking pattern. The method presented here allows users to control their own motions when they are performing well, but intervene when they are not, so as to maintain a functional walking pattern. More details about this method can be found in [44]. The exoskeleton used for this work, named Atalante, was developed by the French startup company Wandercraft. As shown in Fig. 18, this lower-body exoskeleton has 12 actuated joints. The position and velocity of each actuated joint is measured using a digital encoder. Additionally, the exoskeleton has four Inertial Measurement Units (IMUs) that are used to provide additional information about the attitude of the robot with respect to the world. To detect ground contact, four 3-axis force sensors are attached to the bottom of each foot. All of the actuators and sensors are controlled by an embedded computing unit running a real-time operating system", + " As discussed in [43], the correct muscle activation pattern is an important criterion for the spinal learning process. To that end, we utilise the proposed set invariance framework to precisely control how much freedom is granted to the user, as the better the motricity of the patient is, the more he or she can be relied on to execute a stable walking pattern. First, we choose joints that we want to let the user control: the assisted joints. All the other joints will be rigidly controlled. In this work, we choose to only assist the sagittal hip and sagittal knee of the swing leg (cf. Fig. 18). The architecture of the variable assistance framework, as shown in Fig. 19, contains four main components. First, a nominal gait is obtained from a neural network based library built fromPHZD trajectories (cf. [42], [45]\u2013[49]). This trajectory is modulated by a deadbeat mechanism. This deadbeat mechanism is critical in this case because the nominal joint trajectory will not be followed very accurately when the user is in control of the assisted joints. The filtered trajectory qdes(\u00b7) is then fed into two separate controllers" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001752_8600701_08601325.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001752_8600701_08601325.pdf-Figure3-1.png", + "caption": "FIGURE 3. Channel sounder. Description of the transmitter side with the dipole antenna connected to a rotating arm implementing 30 different positions for the transmit antenna. Description of the receiver side including the textile planar array, the 4\u2013channel receiver module, data acquisition card and processing laptop.", + "texts": [ + "2) emulating a scenario where rescuers have the user equipment integrated in their clothing and they are moving. Similarly, in B2 we measure one outdoor position for the BS and 6 indoor positions with the 4 rotations for the UE. Therefore a total of 72 links have been characterized. B. EXPERIMENTAL SETUP The narrow\u2013band MIMO transmitter uses a classic synthetic aperture array [19] where a single element is moved sequentially along the element positions corresponding to the array being synthesize. Specifically, a dipole antenna mounted on a 0.5 m rotating arm (see Fig. 3) and moved in 12\u25e6 angular increments in the horizontal plane, synthesizing circular array with up to 30 elements. The inter-element distance is\u00d72.8 the half wavelength ensuring minimal mutual coupling (MC) and thus, correlation at the transmitter will mostly be dependent on the channel scattering characteristics. At the receiver side, the textile antenna array deployed at the user equipment is composed of individual squared patch antennas of length 3.3 cm using a 0.3 cm thick felt (with permittivity \u03b5r = 1.38) as a dielectric material. Its geometry follows Nh = 2 columns in the horizontal plane and Nv = 6 antenna rows in the vertical plane. Then, the total array size is N = Nv \u00d7 Nh = 12 antennas occupying 15\u00d738 cm2. TominimizeMCbetween antennas at the receiver we selected an inter-element distance of 0.7\u03bb, obtaining simulated MC values below \u221220 dB. The design and characterization of antenna parameters such as MC were performed using CST Microwave Studio. As illustrated in Fig. 3, groups of 4 antennas are connected to 3 SP4T switches, which successively connect one antenna from each group to the input of a 4\u2013channel receiver. The fourth receive channel is used to correct for the phase drift between transmitter and receiver during themeasurement sequence. This way for each transmit antenna position, 12 channels to the respective UE antennas are measured. The channel sounder uses the procedure described in [20] to measure the complex path\u2013gains that form the MIMO channel matrix for each of the L = 72 radio links (each corresponding to a different relative position of the transmitter and receiver)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001892_e_download_4116_2763-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001892_e_download_4116_2763-Figure1-1.png", + "caption": "Fig. 1. The scheme and the model of the damper with a bypass", + "texts": [ + " To assure the proper functioning of the model within the wide range of amplitudes and excitation frequencies, the pressure influence on the oil compressibility modulus is taken into account. The proposed model of the damper is different than the presented in the paper by Lee and Moon (2006) and allows the investigation of the influence of a more number of constructional parameters of the shock absorber within the wide range of their changes. The scheme of the hydraulic shock absorber with a bypass as well as its model is presented in Fig. 1. Two chambers are in the main cylinder: chamber K1 above the piston (rebound chamber) and chamber K2 below the piston (compression chamber). Narrow orifices through which oil flows between both chambers are inside the piston. Some orifices are constantly open while the others are the most often covered by the shim stack. An additional external flow passage connects chambers K1 and K2, and distances h1 and h2 determine placements of the bypass orifices. The shock absorber is rigidly connected with a reserve cylinder, consisting of chamber K3 filled with oil and chamber K4 filled with gas under a high pressure of 2-3MPa" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000020__ms-13-1011-2022.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000020__ms-13-1011-2022.pdf-Figure3-1.png", + "caption": "Figure 3. A pair of gear drive samples produced by a 3D printer.", + "texts": [ + " The parameters are listed in Table 1. The 3D models of the NHGM were established according to Eqs. (10) and (11). 1(t,\u00b51)=X1(t,\u00b51)i+Y1(t,\u00b51)j ++Z1(t,\u00b51)k X1(t,\u00b51)= (30cos(t)\u2212 5 \u221a 2 2 )+ 5cos(\u00b51) Y1(t,\u00b51)= (30sin(t)\u2212 5 \u221a 2 2 )+ 5sin(\u00b51) Z1(t,\u00b51)= 20t \u2212 \u03c0 2 \u2264 \u00b51 \u2264 \u03c0 2 ,0\u2264 t \u2264 \u03c0 2 (10) 2(t,\u00b52)=X2(t,\u00b52)i+Y2(t,\u00b52)j ++Z2(t,\u00b52)k X2(t,\u00b52)= (\u221260cos(t)\u2212 3 \u221a 2)+ 6cos(\u00b52) Y2(t,\u00b52)= (\u221260sin(t)\u2212 3 \u221a 2)+ 6sin(\u00b52)0 \u2264 \u00b52 \u2264 \u03c0 3 (\u221260sin(t)+ \u221a 2 2 )+ 6sin(\u00b52)\u2212 \u03c0 3 \u2264 \u00b52 \u2264 0 Z2(t,\u00b52)= 20t0\u2264 t \u2264 \u03c0 2 . (11) As shown in Fig. 3, they were manufactured with a 3D printer. The 3D printer model is Lite450HD. The resolution is 0.001 mm. The material is a gray high-temperature, photosensitive resin (YGH-5001). The tooth contact analysis (TCA) is the main method to obtain TEs. The equation of TCA is expressed as Eq. (12) (Litvin, 1992).{ f 1(t,\u00b51,\u03d51)= f 2(t,\u00b52,\u03d52) nf 1(t,\u00b51,\u03d51)= nf 2(t,\u00b52,\u03d52) . (12) Here, is the surface equation, and n is the normal vector of the corresponding surface. It is expressed as Eq. (13). n(t,\u00b5)= \u2202 \u2202t \u00d7 \u2202 \u2202\u00b5\u2223\u2223\u2223 \u2202 \u2202t \u00d7 \u2202 \u2202\u00b5 \u2223\u2223\u2223 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000882_article-file_1157957-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000882_article-file_1157957-Figure3-1.png", + "caption": "Fig. 3. Critical areas on the yoke parts (respectively; flange yoke, yoke shaft, weld yoke)", + "texts": [ + " Additionally, in response to the question \"what would happen if moment was applied instead of a force couple?\", the analysis in which moment was applied as the loading type, was carried out. As a result, the effect of both loading types (moment and force couple) on the FEA results was compared and discussed. Yoke parts are subjected to shearing and bending under torque when the driveshaft transmits the torque through the wheel. Depending on the geometry and material of the yoke part, stress values differ regionally. Therefore, the critical area for each different yoke part is also different. Fig. 3 shows the critical areas in terms of stress, for the various yoke parts. In design work, the critical area where the largest stresses occur on the structure, should be taken into consideration. Correspondingly, critical point is selected on the cross section where the stresses reach the largest values. It is possible to determine the critical area for weld yoke, by means of field experiences, finite element analysis, basic strength theories and torsional test simulating the relevant operating conditions. Furthermore, within those cross sections, the points should be selected where either the normal stresses or the shear stresses have their largest values. Weld yoke is usually broken from the critical cross section including the both areas circled in the Fig. 3. While the critical cross section of the weld yoke is shown in Fig. 4, the critical dimensions on the cross section are given in table 1. In addition to keeping the max. stress on the critical section under control, the material selection for weld yoke is another key factor. The properties belonging to steel of C45 grade that is selected for the weld yoke, is shown in Table 2 below. Maximum force on the branch of the weld yoke, Considering the weld yoke on the driveshaft alone, force couple produced by the torque acting on it, is shown in Fig", + " For the lower side of the weld yoke where the welding operation is preformed, as shown in Fig. 7, the constraint has been defined in a way that does not allow rotation and translation in all axes by using rigid elements. Elasticity modulus of 210 GPa and Poisson\u2019s ratio of 0.3 have been used as input data for the material of weld yoke. After the defining load and constraints, the solution process has been implemented by linear static structural method. In solution process OptiStruct has been used as solver. Von Mises stress value on the critical area (Fig. 3 and Fig. 4) which is taken into consideration for the theoretical calculations, has been obtained as 241 MPa for the loading type of force couple, while 240 MPa has been obtained for the loading type of moment as shown Fig. 8. The stress on the lower side of the weld yoke where the welding operation is performed, has been ignored because they occur due to lack of freedom. moment Equivalent stress via Von Mises was calculated to include bending and shear stresses on the critical area. By this way, equivalent stress obtained as 237" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000998_e_1600_context_ijaaa-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000998_e_1600_context_ijaaa-Figure5-1.png", + "caption": "Figure 5 Shaft Surface Temperature Distribution", + "texts": [ + " The ratio of heat flux transferred to the temperature gradient in conduction heat transfer is constant. With the existing preheating parameters, it was determined that the thermal value required for curing the surface of the shaft to be coated was not reached in the oven without a fan. With the current parameters and the way of heating, it has been determined that the area of the shaft that is desired to be coated can reach 193 \u00b0C at most. The temperature distribution obtained at the end of the thermal analysis is presented in Figure 5. https://commons.erau.edu/ijaaa/vol8/iss3/3 DOI: 10.58940/2374-6793.1600 Furnace type T1 T2 Time [sec] Torsion area Temp.[\u00b0C] Coating surface Temp .[\u00b0C] Torsion area Temp. [\u00b0C] Coating surface Temp. [\u00b0C] 72 22 40 25 52 144 26 78 33 89 360 33 112 43 127 720 46 138 53 192 1440 60 159 66 245 1800 67 167 74 259 2400 72 175 83 278 2700 75 178 87 285 3200 79 181 96 287 3600 81 182 102 289 4500 83 187 110 291 5400 84 193 115 293 It was observed that the highest temperature value measured experimentally was at most 186 \u00baC at the end of the whole heating process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004557_9312710_09416651.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004557_9312710_09416651.pdf-Figure4-1.png", + "caption": "FIGURE 4. Drum winding.", + "texts": [ + " The tooth of the first stator faces the slot of the second stator creates unalignment which directs the flux to flow over the entire machine which is different from conventional surface type machines. In conventional surface type machines, the flux loop cover half of the machine. This unaligned two stator arrangement inherently produces a skew effect which lessens machine cogging torque. Conductors of coils are wrapped over the stator yoke to apply drum winding in the open slot arrangement as shown in Fig. 4. The main design parameters of DSAFST-PMVM are tabulated in Table. 1. Magnet pieces with a 7 mm thickness are selected in event of demagnetization. A ratio of stator slot width per slot pitch 0.63 is picked as a result of the optimized design of the open slot in PMVM [28]. C. FLUX FOCUSING The DSAFST PMVM design uses spoke-arranged magnets to have a flux-focusing effect, thus raising the useful magnet flux. The rotor pole directs flux through both the outer and inner airgaps with half teeth pitch shifted dual stators, as seen in Fig", + " DESIGN EQUATIONS The designing of the PMVM is done in [21], [29], in which the magnetic field is analyzed by taking a small section of the DSAFST-PMVM, which includes single pole pair, slot, and tooth. Equation (1-16) are basic design equations presented in [21], [29], for dual stator axial flux topology of PMVM.All the machines in this paper follow the same design equations. From equation (1), we have the number of combinations for rotor pole pair and the number of slots of the DSAFST-PMVM. One selection is adopted for all the machines analysis. Zr = 17, Zs = 18 and p = 1. For a 3-phase machine (m), q = Zs 2pm = 3 (3) The slot per pole per phase is illustrated in Fig.4. Axial field permeance coefficient P is given by: P(\u03b8) = P0 + (\u22121)j \u2211\u221e m=1 Pm cos(mZs\u03b8 ) (4) VOLUME 9, 2021 64181 P0 = \u00b50 ge = \u00b50 kcskcrg kco = \u00b50 kcskcrg (1\u2212 1.6\u03b2 bo \u03c4s ) (5) P1 = 2\u00b50\u03b2 \u03c0g sin(1.6\u03c0 bo \u03c4s ) 1 1\u2212 1.62( bo \u03c4s )2 (6) kcs \u2248 \u03c4s \u03c4s \u2212 b2o 5g+bo (7) kcr \u2248 \u03c4r \u03c4r \u2212 g2m 5g+gm (8) P0 is an average air gap permeance coefficient, Pm is the amplitude of the permeance coefficient (mth harmonic), kcs, and kcr are the Carter coefficients, j is the number of slot shifts of the short pitch windings, \u00b50 is the permeability of air, ge is the equivalent airgap length, g is the mechanical airgap length, gm is the width of PM, b0 is slot width, kc0 is a coefficient linked to airgap and slot, \u03b2 is a function of the ratio b0/g, \u03c4s is stator pole pitch, \u03c4r is rotor pole pitch" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001670_ev_9_1_9_1_1465__pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001670_ev_9_1_9_1_1465__pdf-Figure7-1.png", + "caption": "Fig. 7 Flux density at no-load distribution", + "texts": [ + " 2 21 (5) Iron losses by eddy current:\u2022 2 22 0 2 0 2 2 11 f).(.d d\u03b8 db.\u03b1.dt dt db T .\u03b1P p T pEC (6) Where f is the electric frequency; \u0394B is the peak-topeak value of flux density and kh1, kh2, \u03b1p are constants which are determined from the constructor\u2019s data. .12 2d\u03b1p (7) Where d is the thickness of the electric sheet, r is the specific resistivity and \u03b3 the material density, kh1 = 5 (A.m-1), kh2 = 50 (A.m.V-1.s-1) \u03b1p = 0.042 (A.m.V-1). Of course, the value of flux density is not the same in each part on the stator (Figure 7). The calculation of flux density value of each point on the stator could be a perfect idea but very difficult because of the computation time. Therefore, considering that there are some regions on the stator where flux density values are not too different, also, in order to have a better result, the stator of each machine has been divided into several small subdivisions in which the value of flux density is nearly constant. We have developed \u201caverage value method\u201d. This method is based on the flux density analysis (FEA) of each subdivision on the stator and for the two axes Ox-Oy, and then, on the average analysis on the overall volume of the stator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000020__ms-13-1011-2022.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000020__ms-13-1011-2022.pdf-Figure1-1.png", + "caption": "Figure 1. Coordinate systems of the gear drive.", + "texts": [ + " Based on the line gear theory, a novel helical gear mechanism (NHGM) with a concave\u2013convex meshing form is presented for parallel shaft transmission. The geometry modification of the NHGM is researched to improve the transmission precision. The effect of the center distance error on the TEs is analyzed. The effect of the geometry modification on the maximum contact stresses are studied. The principle is expounded through theoretical research, and the feasibility is verified by a numerical method. As shown in Fig. 1, coordinate systems S1 and S2 are connected to driving gear and driven gear, and coordinate systems Sf and Sp are fixed with the frame. In initial engagement position, S1 and S2 coincide with Sf and Sp, respectively. \u03d51 and \u03d52 are the rotation angles of the driving and driven gear, respectively. Space curve L1 and L2 exist on the surfaces of the driving gear and driven gear. As shown in Fig. 2, the contact form of the tooth surfaces is concave\u2013convex.R1 is the section radius of surface 1, and R2 is the section radius of surface 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000752_el-04725201_document-Figure1.32-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000752_el-04725201_document-Figure1.32-1.png", + "caption": "FIGURE 1.32 : Rectenna flexible [104].", + "texts": [ + " En 2021, Viskadourakis et al. dans [103] ont con\u00e7u et fabriqu\u00e9 la premi\u00e8re rectenna en impression DFF avec le filament conducteur Electrifi (figure 1.31). La rectenna est constitu\u00e9e d\u2019une antenne dip\u00f4le et d\u2019un redresseur en topologie parall\u00e8le et affiche une efficacit\u00e9 de 7 % pour une puissance d\u2019entr\u00e9e de 14,61 dBm \u00e0 une fr\u00e9quence de 2,4 GHz. 34 1.5 - \u00c9TAT DE L\u2019ART DES CIRCUITS RF EN IMPRESSION 3D En 2023, D. D. Patil et al. dans [104] ont con\u00e7u une rectenna avec un substrat flexible r\u00e9alis\u00e9 en impression 3D DFF (figure 1.32). Pour la partie conducteur \u00e9lectrique, un spray conducteur a \u00e9t\u00e9 utilis\u00e9. La rectenna est multi-bande et op\u00e8re aux fr\u00e9quences de 2,4 et 5,2 GHz pour une efficacit\u00e9 respective de 67,29 % et 42,16 % pour une puissance d\u2019entr\u00e9e de 0 dBm. En 2023, Linh et al. dans [105] pr\u00e9sentent une rectenna combinant le DFF \u00e0 la st\u00e9r\u00e9olithographie. La rectenna fonctionne \u00e0 2,45 GHz et affiche une efficacit\u00e9 de 13 % pour une puissance d\u2019entr\u00e9e de -24 dBm. Enfin, en 2023, Linge et al. dans [106] proposent une rectenna en PLA et cuivre (figure 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000095_cle_download_406_813-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000095_cle_download_406_813-Figure3-1.png", + "caption": "Fig. 3. Concept design of the carrot seeder", + "texts": [ + " Initial design criteria were inputted and then were modified after the simulation procedure. In the simulation, stress and load analysis were carried out. Stress analysis was also verified using Equation 7. Suggested construction materials for all components were considered in the final design. = / (7) Where: is the stress, F is the force acting on the member; A is the cross-sectional area of the member. Based on the preference of the farmers, and the data gathered from the field a concept design of a carrot seeder was prepared shown in Fig. 3. The seeder comprises of metering mechanism which is responsible of discharging the seeds into the ground, ground wheels, transmission assembly, furrow opener, clutch assembly, handle and some accessories. The seeder is operated by means of pushing the handle that would cause the ground wheel to rotate. The metering discs which are in synchronous to the ground wheel by means of chain and sprocket will then be rotated. The seed metering assembly, as shown in Fig. 4, comprises of hopper, metering disc, and additional parts such as the seed discharge guide or stopper and furrow opener" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure5.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure5.1-1.png", + "caption": "Figure 5.1. Depiction of an R joint.", + "texts": [ + " Occasionally, when the standard multiset notation is too cumbersome, multisets are written as the \u201cproduct\u201d of their unique elements, with each unique element having a superscript indicating its multiplicity (when said multiplicity is greater than one). For example, the multiset {a, a, b} will be written as a2b. 80 Chapter 5 The R Joint The revolute (R) joint directly connects the wheel carrier to the vehicle body. The R joint\u2019s geometry in the design position can be described by a column vector u0 \u2208 R3, giving the direction of the joint axis, and a coordinate vector x0 \u2208 R3, giving the coordinates of a point on the joint axis. See Figure 5.1 for a picture; the R joint is achieved with two legs having point-connections on each end, as is common practice. As the wheel carrier moves from the design position to the position given by some A \u2208 SO(3) and some b \u2208 R3, the axis remains invariant: Au0 = u0 (5.1) Ax0 + b = x0. (5.2) With, at most, six independent variables to work with, and these six design equations, no more than two wheel positions are possible when working with the R joint. Further, it is not yet known for sure if the design equations are solvable for the two wheel positions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004266_0005208_10013670.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004266_0005208_10013670.pdf-Figure16-1.png", + "caption": "FIGURE 16. Radiation patterns of Monopole radiator#1 and Monopole radiator#2, at (a) 2.5 GHz, E-plane, (b) 4.5 GHz, E-plane, (c) 2.5 GHz, H-plane, and (d) 4.5 GHz, H-plane.", + "texts": [ + " This small deviation may arise from minor fabricating errors or manu- facturing tolerances. Nevertheless, Sub-6 GHz 5G and Wi-Fi 6E dual-band operation is clearly seen in Figure 14. The measured Sub-6 GHz 5G/lower Wi-Fi 6E and higher Wi-Fi 6E band operation exhibit wide 10-dB impedance bandwidths of 7.25% (2.39-2.57 GHz) and 58.12% (3.82-6.95 GHz), respectively, while the mutual coupling better than -15 dB was obtained in the desired bands. B. SIMULATED AND MEASURED FAR-FIELD RADIATION PATTERNS OF TWO-PORT MIMO ANTENNA Figure 16 depicts the schematic for far-field measurement inside an anechoic chamber. The radiation patterns of the VOLUME 11, 2023 5623 two-port MIMO antenna in the E-plane and H-plane are visualized in Figure 16. Figures 16(a) and (b) reveal that the two monopole radiators in the E-plane exhibit approximately omnidirectional patterns and eight-shaped patterns for the co-polar and crosspolar radiation, respectively. Furthermore, it is important to observe that Monopole radiator#1\u2019s radiation patterns are exactly the mirror images of the ones shown in Monopole radiator#2. As for the H-plane equivalents, shown in Figures 16(c) and (d), across the two bands of operation, 2.5 GHz and 4.5 GHz, respectively, the twomonopole radiators exhibit bi-directional patterns (co-polar) and omnidirectional patterns (cross-pol)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure6.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure6.1-1.png", + "caption": "Figure 6.1. Depiction of an S-S link.", + "texts": [ + " Nevertheless, the R joint independent rear suspension is appealing in its simplicity and has had success in the marketplace; notably, it found a long-term home in the 1963 to 1993 Porsche 911. The market for these then, and now, does not seem to mind the design\u2019s compromised ride and handling! 95 Chapter 6 The S-S Link The spherical-spherical (S-S) link indirectly connects the wheel carrier to the vehicle body. In the design position, the body-side S joint is to be located at x0 \u2208 R3, while the wheel-side S joint is to be located at x1 \u2208 R3. For a picture, see Figure 6.1. For a wheel motion from Position 1 (the design position) to Position i given by Ai \u2208 SO(3) and bi \u2208 R3, the distance between the wheel-side point xi := Aix1 +bi and the fixed body-side point x0 must remain constant; equivalently, (xi \u2212 x0) \u00b7 (xi \u2212 x0) = (x1 \u2212 x0) \u00b7 (x1 \u2212 x0). Algebraic manipulation results in the equivalent and useful equation xT1 (I \u2212AT i )x0 + bTi Aix1 \u2212 bTi x0 + bTi bi/2 = 0. For i = 2, 3, . . . , 7, there are six equations in six variables; up to seven wheel positions (includes the design position) can be specified for the S-S link" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002970_cle_download_643_621-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002970_cle_download_643_621-Figure2-1.png", + "caption": "Figure 2. The forming stages of cold heading process of fastener", + "texts": [ + " The process involves applying a force through a punch to the end of a workpiece contained in a die. In order for the workpiece to experience a plastic flow, the applied force should exceed the elastic limit of the metal. Typically, the heading process is often performed in conjunction with other cold forging process, in which consists of two or three different operations; i.e. one or two performing method and one finishing process. The principal stages of the cold heading process of fastener, simulated by FEM-code DEFORMTM F3 v6.0, are shown in Figure 2. The operation consisted of a performing process followed by the head compression. Extensive study for die stress analyses was performed in the area of the latter stage to determine the stresses and deformations on the punch. Figure 3 shows the final geometry of workpiece obtained in the simulation, in which was similar to actual fastener geometry. Table 1 lists the mechanical and physical properties of the model. On the other hand, two different analyses were implemented for the FE study and were specified in Table 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure2-4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure2-4-1.png", + "caption": "Figure 2-4: Coordinate fram e attachm ent of an n d.o.f open kinem atic chain.", + "texts": [ + "re defined along and around the x axis. A m anipulator can be considered as the articulated open kinematic chain of n num ber of rigid links. The links are num bered consecutively from the fixed support (link 0) to the end-effector (link n). Each joint and its fram e is num bered so th a t joint i connects link i \u2014 1 to link i. Even though there is no joint at the end of the end-effector, it is convenient to p u t an end-effector frame (sometimes referred to as a tool fram e) w ithout the joint variable (Fig. 2-4). Fram e 0 is referred to as a Cartesian inertial frame(world, ground , or base fram e). Appendix A .l shows the attachm ent of each joint frame for the PUM A-type arm and corresponding joint transform ations. From the vector transform ation m atrices, the transform ation for the z\u2019th joint coordinate referenced to the base coordinate can be obtained by the successive concatenation of transform ations such th a t \u00b0T l = \u00b0 T l 1T 2...'~1T t a function of (<7i,<72) \u2014>?>)\u2022 Qi is denoted as a generalized joint variable a t the zth jo in t" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure16-1.png", + "caption": "Fig. 16 Prediction of fatigue life (a) Antero-lateral (b) Postero-lateral", + "texts": [ + " The design variation and adoption of stronger materials have substantially improved the strength of knee prostheses. The summarized simulation results showing the comparison between existing and modified knee prostheses are presented in Table 5. To estimate the fatigue life (number of cycles), the stress distribution data is utilized in the MSC fatigue module to plot the S-N curve as depicted in Fig. 15. A visual representation of the fatigue life of knee components under cyclic load circumstances in isometric views is presented in Fig. 16. The prosthetic fatigue life is indicated by the color legend bar. As illustrated in Fig. 16, the Allen screws made up of stainless steel are found to have an average fatigue life of 61010 . On the other hand, it is observed that the average fatigue life of the overall prosthetic knee is 610240 . This research discusses a simulation approach to improve the standard of polycentric knee subjected to static and cyclic loading following recommendation of ISO 10328:2016. The proposed modified design of the polycentric knee has been compared with the existing one in terms of stress distribution, total contour deformation, safety factor, and fatigue life" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.10-1.png", + "caption": "Figure 8.10: 3D ASO starting point: NACA 0012 surface of revolution enclosing a cylinder", + "texts": [ + " A second effect of large \u03c1 is that the KS contribution from nearby facets becomes large compared to distant segments. Floating point errors round the contributions of distant segments to zero in the constraint Jacobian, which becomes sparser as a result. Both of these effects degrade optimizer performance. 186 Revolution For a simple 3D test, I defined single-point (0\u00b0) and multipoint (0\u00b0 and 20\u00b0) drag minimization cases. I created a starting surface mesh consisting of a NACA 0012 airfoil revolved around the streamwise (x) axis (Figure 8.10). The structured surface and volume meshes consisted of 1802 and 237762 cells, respectively. The 3D parameterization consists of 192 FFD points which provide fine shape control along the y-axis (Figure 8.9a), and an additional 17 parameters providing degrees of freedom in the x and z axes. I imposed symmetry in the crossflow (x-y) plane to effectively obtain a \u221220\u00b0 crossflow case without running additional CFD cases. The optimization parameters are described in Table 8.3. Figure 8.11 shows the optimized shape for the single point case" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000706_O201332479507885.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000706_O201332479507885.pdf-Figure9-1.png", + "caption": "Fig. 9\ub294\ud0c8\uace1\ud1b5, \uc120\ubcc4\ub9dd, \uc1a1\ud48d\ud32c, \ubca8\ud2b8, \ud754\ub4e4\ucc44, \uc0e4\ud504\ud2b8 \ucd95, \ud480\ub9ac, \ud22c\uc785\uc758 \uc870\ub9bd \ubc29\ubc95\uc744 \ubcf4\uc5ec\uc900\ub2e4.", + "texts": [], + "surrounding_texts": [ + "\uc9c0 \uc54a\uc73c\ub098, \uad6d\uc0b0 \uc81c\ud488\ub4e4\uc740 \uba3c\uc9c0\ub97c \ub9ce\uc774 \uc77c\uc73c\ucf1c \ub18d\uc5c5\uc778\ub4e4 \uc5d0\uac8c \uac74\uac15\uc0c1 \ud574\ub97c \ub07c\uce60 \uc218 \uc788\uc5b4 \uc0c8\ub85c\uc6b4 \ud615\ud0dc\uc758 \ud0c8\uace1\uae30 \uac1c \ubc1c\uc774 \ud544\uc694\ud558\uc600\ub2e4. \ub610\ud55c, \uad6d\uc0b0 \uc81c\ud488\uc758 \uc791\uc5c5 \uc131\ub2a5\uc774\ub098 \ud6a8\uc728 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\ub3c5\ub9bd\uad6c\ub3d9\ubc29\uc2dd\uc73c \ub85c \uace0\uc815\uc2dd\ubcf4\ub2e4\ub294 \uc791\uc5c5 \uc131\ub2a5\uc774\ub098 \ud6a8\uc728 \uba74\uc5d0\uc11c \uc6d4\ub4f1\ud558\uace0, \uc774\ub3d9\ud558\uba74\uc11c \ud0c8\uace1\uc744 \ud558\ubbc0\ub85c \uc791\uc5c5\uc774 \ud3b8\ub9ac\ud558\uace0, \uad6d\ub0b4 \uc81c\ud488\uc5d0 \ube44\ud574 \uba3c\uc9c0\uac00 \ub9ce\uc774 \uc77c\uc5b4\ub098\uc9c0 \uc54a\ub294 \uc6b0\uc218\uc131\uc774 \uc788\uc73c\ub098 \ud310\ub9e4 \uac00\uaca9\uc774 \ub192\ub2e4\ub294 \ub2e8\uc810\uc774 \uc788\ub2e4[3,4].\n\uad6d\ub0b4 \uc81c\ud488\ub4e4\uc740 \uae30\uacc4 \uc8fc\ubcc0\uc5d0 \uba3c\uc9c0\uac00 \ub9ce\uc774 \ub098\uace0, \uc791\uc5c5\uc790 \uac00 \ub9c8\uc2a4\ud06c\ub97c \ud544\ud788 \uc368\uc57c \ud558\ub294 \uc0c1\ud669\uc774\ub2e4. \uc131\ub2a5 \uc2dc\ud5d8\uc2dc \uba3c\uc9c0 \ub3c4 \uad6d\ub0b4\uc0b0\uc774 \uba87 \ubc30\ub098 \ub354 \ub9ce\uc774 \ub098\uc624\ub294 \uc2e4\uc815\uc774\ub2e4.\n2.2 3\ucc28\uc6d0 \ubd80\ud488 \uc124\uacc4 \ubc0f \uc81c\uc791\n\uc544\ub798 \uadf8\ub9bc\ub4e4\uacfc \uac19\uc774 3\ucc28\uc6d0 \uc124\uacc4 \uc18c\ud504\ud2b8\uc6e8\uc5b4 (Pro-Engineer)[5]\ub97c \uc774\uc6a9\ud558\uc5ec \ud0c8\uace1\uae30\uc758 \ubd80\ud488\ub4e4\uc744 \uc124\uacc4\ud558 \uace0 \uc870\ub9bd\ud558\uc600\ub2e4.\n[Fig. 1] Drum to do the threshing\nFig. 1\uacfc \uac19\uc774 \ud0c8\uace1\ud1b5\uc758 \ub0a0\uc744 \ub098\uc120\ud615\uc73c\ub85c \ubc30\uce58\ud558\uc5ec \uc55e \uba74\uc5d0\uc11c \ucf69\uc744 \ud22c\uc785\ud558\uba74 \ub098\uc120\ud615\uc744 \ub530\ub77c \uc774\ub3d9\ud558\uba74\uc11c \ud0c8\uace1\uc744 \ud560 \uc218 \uc788\uac8c \uc124\uacc4\ud558\uc600\ub2e4.\n\uae30\uc874 \uc81c\ud488\uc758 \ud22c\uc785\uad6c\ub294 \ud0c8\uace1\ud1b5\uc758 \ub0a0\uacfc \ubc14\ub85c \uc811\ud574 \uc788\uc5b4 \uc11c \uc791\uc5c5\uc790\uc758 \uc190\uc774 \ub4e4\uc5b4\uac08 \uc704\ud5d8\uc774 \uc788\ub2e4. \uc774\ub97c \ud574\uacb0\ud558\uae30 \uc704 \ud574 \ud22c\uc785\uad6c\uc5d0 Fig. 2\uc640 \uac19\uc774 \ub0a0\uce74\ub86d\uc9c0 \uc54a\uc740 \ubc14\uc774\ud2b8\ub97c \ub450\uc5b4 \uc11c \uc800\uc18d\uc73c\ub85c \ud68c\uc804\uc744 \uc2dc\ucf1c \ucf69\ub300\ub97c \ubb3c\uace0 \ud0c8\uace1\ud1b5 \uc548\uc73c\ub85c \ub4e4 \uc5b4\uac00\uac8c \uc124\uacc4\ud558\uc5ec \uc791\uc5c5\uc790\uc758 \uc548\uc804\uc744 \ub3c4\ubaa8\ud558\uc600\ub2e4.\n[Fig. 3] Support of the belt shaft", + "\uc815\uc120\ub41c \ucf69\uc744 \ubc30\ucd9c\uc2dc\ud0a4\uae30 \uc704\ud574 \ubc30\ucd9c \ud32c\uc744 \ud0c8\uace1\uae30\uc758 \ub4a4 \ucabd\uc5d0 \ubc30\uce58\ud558\uc600\ub2e4. Fig. 5\uc640 \uac19\uc774 \ubc30\ucd9c \ud32c\uc758 \uac00\uc6b4\ub370 \ubd80\ubd84\uc5d0 \ub294 \uacf5\uae30\ub97c \ud761\uc785\ud560 \uc218 \uc788\ub3c4\ub85d \uc548\ucabd\uc73c\ub85c \uacbd\uc0ac\ub97c \uc8fc\uc5b4 \ud32c \ub0a0 \uc744 \uc81c\uc791\ud558\uc600\ub2e4.\n[Fig. 5] Exhaust fan\n\uc815\uc120\ub41c \ucf69\uc744 \ubc30\ucd9c\uc2dc\ud0a4\uae30 \uc704\ud574 \ubc30\ucd9c\uad6c\ub97c \ub4a4\ucabd\uc5d0 \ubc30\uce58\ud558 \uc600\ub2e4. \ubc30\ucd9c\uad6c \ub05d \ubd80\ubd84\uc744 \uc791\uc5c5\uc790 \uc55e\uc73c\ub85c \uc720\ub3c4\ud558\uc5ec \uc544\ub798\uc5d0 \ub294 \ud3ec\uc7a5\uc744 \ud560 \uc218 \uc788\uac8c \uc790\ub8e8 \ubc1b\uce68\ub300\ub97c \ub450\uc5c8\ub2e4.\n[Fig. 6] Outlet of a soybean\n\ud648\uc5d0 \uc815\uc120\ub41c \ucf69\uc774 \ub5a8\uc5b4\uc9c0\uba74 \uc774\uc1a1\uc2a4\ud06c\ub958(Fig. 7)\ub97c \ud0c0\uace0 \ubc30\ucd9c\uad6c\ub85c \ubcf4\ub0b4\uc9c4\ub2e4. \uc774 \ub54c \uc774\uc1a1\ub418\ub294 \ucf69\uc758 \uc591(\uccb4\uc801\uc720\ub3d9\ub7c9) \uc740 \uc2a4\ud06c\ub958\uc758 \ub2e8\uba74\uc801\uacfc \ud68c\uc804\uc18d\ub3c4\uc5d0 \ube44\ub840\ud55c\ub2e4[6].\n \uc18d\ub3c4 \uc2a4\ud06c\ub958\uc758\ub2e8\uba74\uc801\n[Fig. 7] Outlet of a soybean", + "\uada4\ub3c4\ucc28\ub7c9\uc704\uc5d0 \uc7a5\ucc29\ud558\uae30 \uc804 \ucf69 \ud0c8\uace1\uae30\uc758 \uc870\ub9bd\uacfc\uc815\uc744 \ubcf4 \uc5ec\uc900\ub2e4.\n[Fig. 14] Assembling the threshing machine\n\uace0\ubb34\uc7ac\uc9c8\uc758 \ubb34\ud55c\uada4\ub3c4 \uc7a5\ucc29\ud55c \uc644\uc131\ub41c \ucf69 \ud0c8\uace1\uae30\uc758 \ubaa8\uc2b5 \uc774\ub2e4. \uada4\ub3c4\uc758 \uc7ac\uc9c8\uc774 \uace0\ubb34\ub85c \ub418\uc5b4 \uc788\uc5b4 \uc544\uc2a4\ud314\ud2b8 \uc704\uc5d0\uc11c \uc6b4\ud589\uc744 \ud574\ub3c4 \ubc14\ub2e5\uc5d0 \uc190\uc0c1\uc744 \uc8fc\uc9c0 \uc54a\ub294\ub2e4.\n[Fig. 15] Prototype of the threshing machine\nFig. 16\uc740 \ucf69 \ud0c8\uace1\uae30\uc758 \uc791\uc5c5 \uc6d0\ub9ac\ub97c \uc124\uba85\ud558\uae30 \uc704\ud558\uc5ec \ubc88\ud638\ub97c \uae30\uc785\ud558\uc600\ub2e4. \uc218\ud655\ud55c \ud6c4 \ub9c8\ub978 \ucf69\uc744 \uc88c\uce21\uc55e\ucabd\uc758 \ud22c \uc785\uad6c\u24ea\uc744 \ud1b5\ud574 \ud22c\uc785\ud558\uba74 \ubc14\uc774\ud2b8\u2460\uc774 \ud68c\uc804\uc744 \ud558\uba74\uc11c \ucf69\uae4d \uc9c0\ub97c \ubb3c\uace0 \ud0c8\uace1\uc2e4\ub85c \ubcf4\ub0b8\ub2e4." + ] + }, + { + "image_filename": "designv8_17_0003249_O200932056740446.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003249_O200932056740446.pdf-Figure1-1.png", + "caption": "Fig. 1. Configuration of IPMSM.", + "texts": [ + " In the newly proposed method, the different preprocessing for each analysis program is no longer required by combining field analysis programs in parallel. In other words, the node and element data obtained by the electromagnetic field analysis program is also used in the stress analysis. Therefore, the computing time of the new method is very short in comparison with that of the conventional program while the results of the proposed method are similar to those of the conventional method. In particular, when the repeated analyzes of various models are required, this method is very useful and convenient. Fig.1 shows an analysis model with one magnet layer in the rotor core. Generally, the shape of the layer and length are designed to enhance the capability of the IPMSM such as with high reluctance torque and sinusoidal EMF, etc. In high-speed operations, the center-post and bridge sustaining the magnet have the potential to be broken by the stress caused by centrifugal force. Therefore, the length of the bridge and center-post should have sufficient thickness to prevent the dispersion of the magnets. \u2020 Corresponding Author : School of Electrical Engineering and Computer Science, Seoul National University, Korea" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003809_el-03253472_document-Figure3.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003809_el-03253472_document-Figure3.13-1.png", + "caption": "Figure 3.13 : Principe de la capacit\u00e9 interdigit\u00e9e", + "texts": [ + " Son inconv\u00e9nient majeur est sa fabrication, car une couche de mat\u00e9riau di\u00e9lectrique suffisamment fine doit \u00eatre appliqu\u00e9e entre la ligne microstrip et la plaque de m\u00e9tal apportant l\u2019effet capacitif. Cette couche suppl\u00e9mentaire aura un impact sur l\u2019ensemble du prototype. DECRIPTION DE LA METHODE DE DESIGN DE DEPHASEURS CRLH-TL 90 Une autre structure consid\u00e9r\u00e9e est la capacit\u00e9 interdigit\u00e9e. Elle est compos\u00e9e de part et d\u2019autre de plusieurs lignes m\u00e9talliques tr\u00e8s fines appel\u00e9es doigts, s\u00e9par\u00e9es par un espace vide, ce qui cr\u00e9e l\u2019effet capacitif attendu (voir Figure 3.13). Une valeur estim\u00e9e de la capacit\u00e9 est obtenue [49] \u00e0 l\u2019aide de cette formule : \u00ca\u00d8 FX 1 *SHOHu \u00d9mD- $ 3 \u00aa/ \u00aa6v (3.25) Les expressions A1 et A2 pouvant \u00eatre approxim\u00e9es par ces relations : \u00aa/ 4.409 tanh \u00db0.55 \u210e \u00cbE\u00c9SHOH .\u00ac\u00dd\u00de . 10 \u00df (3.26) \u00aa6 9.92 tanh \u00db0.52 \u210e \u00cbE\u00c9SHOH .\u00dd\u00de . 10 \u00df (3.27) L\u2019avantage principal de cette structure est sa simplicit\u00e9 d\u2019int\u00e9gration dans une ligne microstrip, un de ses inconv\u00e9nients \u00e9tant son mod\u00e8le th\u00e9orique plus complexe. Un autre inconv\u00e9nient de cette structure est la pr\u00e9sence potentielle d\u2019effets parasites pouvant impacter ses performances au sein d\u2019une ligne CRLH, dus principalement \u00e0 la complexit\u00e9 de sa composition et \u00e0 sa taille" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000161_om_article_21583_pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000161_om_article_21583_pdf-Figure4-1.png", + "caption": "Fig. 4. Prototype of the planetary intermittent motion mechanism:", + "texts": [ + " (3), the equation for determining the analogue of the output shaft angular velocity is obtained: \ud835\udf11 = 1 \u2212 \ud835\udc45 \u2219 \ud835\udf0c\ud835\udc45 \u2219 (\ud835\udc45 + \ud835\udc45 \u2212 \ud835\udf0c) . (9) Thus, by integrating Eq. (9) over the generalized coordinate \ud835\udf11 , the function of the mechanism output link angle of rotation can be obtained. Using the study of the position function \ud835\udf11 (\ud835\udf11 ), we verify the adequacy of the developed kinematic model to a real mechanism. For further research, a prototype of the planetary gear was designed and manufactured from ABS plastic using additive technologies (Fig. 4). The rotation angle is measured using absolute encoders mounted on the input and output shafts of the mechanism (Fig. 5). The signal from the sensors is processed using the controller, which performs the function of an analog-to-digital converter, and then transmitted to a personal computer. Further, the obtained data can be easily processed in any computer mathematics system, 126 JOURNAL OF MEASUREMENTS IN ENGINEERING. SEPTEMBER 2020, VOLUME 8, ISSUE 3 for example, MathCAD. 0 \u2013 cover, 1 \u2013 input shaft, 2 \u2013 carrier, 3 \u2013 output shaft, 4 \u2013 sun spur stationary gear, 5 \u2013 elliptical gear, 6 \u2013 spur planet gear, 7 \u2013 elliptical planet gear, 8 \u2013 satellite shaft Brief specifications of the experimental setup are presented in Table 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure11.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure11.1-1.png", + "caption": "Figure 11.1. Illustration of the R-R link.", + "texts": [ + " Support angle becomes increasingly negative with rebound; this is increasing anti-lift behavior. The control blade suspension is an interesting design, but its kinematic performance does not seem to justify its number of links, its packaging issues, and its inability to accommodate a kingpin axis, especially compared to the SLA suspension. Perhaps its elastokinematic performance is why it has become so popular for compact car rear suspensions. 154 155 156 157 Chapter 11 The R-R Link The R-R link indirectly connects the wheel carrier to the vehicle body, as illustrated in Figure 11.1. The body-side R joint is given by column vector u0 and coordinate vector x0, which must satisfy u0 \u00b7 u0 = 1 (x1 \u2212 x0) \u00b7 u0 = 0, while the wheel-side R joint is given by column vector u1 and coordinate vector x1, which must satisfy u1 \u00b7 u1 = 1 (x1 \u2212 x0) \u00b7 u1 = 0. The R joint axes arising from synthesis are expected to be skew ; that is, they do not intersect and are not parallel. In the former case, the wheel will rotate about the fixed point of intersection \u2014 spherical motion. In the latter case, the wheel will move in the plane normal to the shared axes\u2019 direction \u2014 planar motion" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001453_article_25887703.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001453_article_25887703.pdf-Figure1-1.png", + "caption": "Figure 1. Finite Mechanical translation structure", + "texts": [], + "surrounding_texts": [ + "1\u2014Channel steel frame\uff1b2\u2014Base frame\uff1b3\u2014Plate\uff1b4\u2014Wire towline\uff1b 5\u2014Auxiliary rails\uff1b6\u2014motor\uff1b7\u2014Coupling\uff1b8\u2014Y-axis\uff1b9\u2014target\uff1b 10\u2014Z axis\uff1b11\u2014Positioning grating\uff1b12\u2014Base\uff1b13\u2014pillar\uff1b14\u2014Block iron\u3002 The overall layout of the mechanical translation mechanism is shown in Fig .1. According to the movement characteristics of the target, two linear motion systems (composed of rolling guide and lead screw) and two auxiliary rails are used in the axial direction, which are fixed on the frame through the plate. As the rigidity of the guide rail itself is not high, so the installation of the rail base frame to have a high stiffness, to prevent the movement in the process of bending deformation. The four sliders in the axial direction are connected by a linear motion system in the axial direction to achieve axial direction (horizontal) movement with an effective stroke of 4000 mm. There is a linear motion system in the axial direction, and the target is mounted on its slider to achieve axial (vertical) movement with an effective stroke of 4000 mm. Y axial and Z axial use of servo motor and coupling drive linear motion system screw drive load movement, motion positioning is completed by reading the raster in the two directions. The whole frame is made of 100mm \u00d7 100mm \u00d7 10mm channel welded steel, the frame is installed on the floor, the floor is equipped with lifting pillars, you can level the entire frame. Copyright \u00a9 2017, the Authors. Published by Atlantis Press. This is an open access article under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/). 766 measures to design. The first type of non-contact switch. When the axis movement direction to the end of 40mm, the contactless switch to detect the signal and sent to the controller, forced to stop the motor running. The second set of a set of iron, in the axial travel to the end of 20mm, directly blocking the target movement. Axial direction travel The non-contact switch is mounted on the upper side of the upper rail. Axial direction travel The contactless switch is mounted on the left side of the linear motion system. In order to prevent direct collision, the block attached to the thick rubber to play the role of buffer." + ] + }, + { + "image_filename": "designv8_17_0002004___lang_en_format_pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002004___lang_en_format_pdf-Figure4-1.png", + "caption": "Fig. 4. (a) Proposed SRR inverted U-shaped UWB band notch antenna (b) its realized prototype", + "texts": [ + " Here, the SRRs affect Brazilian Microwave and Optoelectronics Society-SBMO received 19 Aug 2023; for review 20 Sep 2023; accepted 23 Jan 2024 Brazilian Society of Electromagnetism-SBMag \u00a9 2024 SBMO/SBMag ISSN 2179-1074 the antenna performance in two ways. They act as a parasitic radiator and then contribute to the overall antenna gain in relation to their resonance frequency. In the other side, their coupling to the antenna, depending on the distance g, affects the input impedance and reflection coefficient. The inverted U-shaped patch antenna depicted in Fig. 4 (a) was prototyped on an FR4 substrate with permittivity of \u03b5r = 4.3, loss tan\u03b4 = 0.0024 and substrate thickness of h = 1.6 mm. Four element array of a rectangular SRR will be placed near the feedline as shown in Fig. 4 (b) Table II presents the geometric parameters of the whole structure results of optimization to control the desired resonance frequency and the features of UWB. When included, the four rectangular SRRs, integrated with the inverted U-shaped antenna, will permit a single band-notched antenna structure inside the WLAN band (5.15-5.85 GHz). The reflection coefficient of the proposed antenna depicted in Fig. 5, shows that the WLAN band contains the single band-notch, and Fig. 6 indicates gain estimated at 5dB" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002569_pdf_234FA5140425.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002569_pdf_234FA5140425.pdf-Figure2-1.png", + "caption": "Figure 2. Apparatus for measuring static coefficient of friction.", + "texts": [ + ", 2006): 100-1 t b (8) The angle of repose (\u03c8) was determined by using a hollow cylindrical mould of 100 mm diameter and 150 mm height. The cylinder was placed on a wooden table, filled with okra seed and raised slowly until it forms a cone of seeds. The diameter (D) and height (H) of the cone were recorded. The angle of repose (\u03c8) was calculated by the fallowing equation (Mullah, 1992): )/2(tan 1 DH (9) Incline plane method was used to measure static coefficient of friction on different structural surfaces including (Figure 2): Aluminum, rubber, plywood, galvanized steel and iron sheet. A hollow metal cylinder (100 mm diameter and 100 mm high) opened at both ends was filled with samples at the specific moisture content. The cylinder was then placed on an adjustable tilting plate without allowing the metal cylinder to touch the inclined surface. The tilting surface was then raised slowly and gradually by a screw mechanism until the cylinder started to slide down. At this point, the angle of tilt was measured and the friction coefficient was calculated as the tangent of that specific tilt angle (Dutta et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003458_2013__G101064-1__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003458_2013__G101064-1__pdf-Figure4-1.png", + "caption": "Fig 4 Statlc analysls result oftUbular frame Flg 5 DyTiamic analysis result oftUbular frame", + "texts": [], + "surrounding_texts": [ + "The Japan Society of Mechanical Engineers\u00a0\nNII-Electronic Library Service\u00a0\nhe apan oclety f echanlcal nglneers\n\u3044 \uff0e\u3057\u304b \u3057\uff0c\u30c1 \u30e5 \u30fc\u30d6 \u30e9 \u30fc \u30d5 \u30ec\u30fc\u30e0 \u306b \u306f \u4ee5 \u4e0b \u306e \u3088\u3046\u306a\u7279\u5fb4\u304c\u3042 \u308a\uff0c\u8d85\u5c0f\u578b\u96fb\u6c17 \u81ea\u52d5\u8eca\u306e \u69cb\u9020\u3068 \u3057\u3066 \u9069\u3057 \u3066 \u3044 \u308b\uff0e \uff081\uff09\u8efd\u91cf \u3067 \u3042 \u308b\uff0e\uff082\uff09\u9ad8\u3044 \u525b\u6027 \u30fb\u5f37\u5ea6\u3092\u6301\u305f\u305b \u308b \u3053 \u3068\u304c \u3067 \u304d \u308b\uff0e\uff083\uff09\u7c21\u6613\u306a\u88fd\u9020\u8a2d\u5099 \u3057\u304b\u306a \u3044 \u5c0f\u898f\u6a21\u306a \u5de5 \u5834 \u3067 \u3082\u751f\u7523 \u3067\n\u304d \u308b\uff0e\uff084\uff09\u8a2d\u8a08\u5909\u66f4\u3084\u4fee\u7406 \u304c\u5bb9\u6613\u306b\u884c\u3048 \u308b\uff0e\n\u4eca\u56de\u8a2d\u8a08 \u3057\u305f \u30c1 \u30e5\u30fc\u30d6 \u30e9\u30fc \u30d5 \u30ec \u30fc\u30e0 \u306e \u7279\u5fb4 \u3068 \u3057\u3066 \u306f \u4e3b \u306b \u4e8c \u3064 \u3042 \u308a\uff0c \u4e00 \u3064 \u76ee\u306f \u30d1 \u30a4 \u30d7\u30d9 \u30f3 \u30c0\u30fc\u3084\u6eb6\u63a5\u6a5f \u306a\u3069\u306e \u7c21\n\u6613\u306a\u88fd\u9020\u8a2d\u5099 \u306e \u307f \u3067\u88fd\u4f5c\u3067\u304d\u308b \u3053 \u3068\u3067\u3042\u308b\uff0e\u96fb\u6c17 \u81ea\u52d5\u8eca\u306f\u5185\u71c3\u6a5f \u95a2 \u81ea\u52d5\u8eca\u3068 \u6bd4 \u307a \uff0c\u90e8\u54c1\u70b9\u6570\u304c\u5c11\u306a \u304f\u69cb\u9020 \u3082\u7c21\u5358\n\u306a\u305f \u3081 \u8a2d\u5099 \u306e \u6574 \u3063 \u3066 \u3044 \u306a\u3044 \u5c0f \u898f\u6a21 \u306a \u5de5 \u5834 \u3067 \u3082\u88fd\u4f5c\u304c \u53ef \u80fd \u3068\u3055\u308c \u3066 \u304a \u308a\uff0c\u8eca\u4f53\u3092\u5c0f\u898f\u6a21\u306a\u5de5 \u5834\u3067 \u88fd\u4f5c\u3067\u304d\u308c \u3070\uff0c\u5730\n\u57df\u5185\u3067\u88fd\u4f5c \u3057\u8ca9\u58f2\u3059\u308b\u3053 \u3068\u3082\u53ef\u80fd\u306b \u306a\u308b\u3068\u8003\u3048 \u3089\u308c \u308b\uff0e\n\u4e8c \u3064 \u76ee\u306f\uff0c\u5c11\u91cf\u591a\u54c1\u7a2e\u751f\u7523 \u3092\u5bb9\u6613\u306b\u3059\u308b\u305f\u3081\u306b\u30e2 \u30b8 \u30e5 \u30fc \u30eb \u6bce\u306b\u8a2d\u8a08\u3057 \u305f \u3053 \u3068 \u3067 \u3042\u308b\uff0e\u3053 \u306e\u8eca\u4e21\u306f\u56f3 2 \u306e \u3088 \u3046\u306b\n\u30b7 \u30e3 \u30b7 \u30d5 \u30ec\u30fc\u30e0 \u30fb\u30d5 \u30ed \u30f3 \u30c8\u30fb\u30ad \u30e3 \u30d3 \u30f3 \u30fb\u30ea\u30a2 \u306e \u56db \u3063 \u306e \u30e2 \u30b8 \u30e5 \u30fc \u30eb \u306b \u5206 \u3051\u3066 \u8a2d\u8a08 \u3055\u308c \u3066 \u3044 \u308b\uff0e\u3053 \u306e \u3088 \u3046\u306b \u30e2 \u30b8 \u30e5 \u30fc \u30eb \u6bce\u306b\u5206\u5272 \u3057\u3066 \u8a2d\u8a08\u3059\u308b \u3053 \u3068\u3067 \uff0c\u8a2d\u8a08\u5909\u66f4\u3084\u30e2 \u30c7 \u30eb \u30c1 \u30a7 \u30f3 \u30b8\u3092\u884c \u3046\u969b\u306b \u4e00 \u90e8\u306e \u30e2 \u30b8 \u30e5 \u30fc \u30eb \u306e \u307f \u3092\u5909\u66f4\u3059\u308b \u3053 \u3068\u3067 \u7528\u9014 \u306b\u5fdc\u3058\u305f \u8eca\u4e21 \u30d5 \u30ec \u30fc\u30e0 \u306e \u958b\u767a\u304c\u53ef\u80fd\u3068\u306a\u3063 \u3066 \u3044 \u308b\uff0e\nFig\uff0e1 Tubular f\u30bbame ofMEV Fig\uff0e2 Division ofmodule\nTable l Speci\u9b5acation ofMEV\nSize ofMEV\n\uff08Leng \u8840xWidthxHei \u5e25t\uff09 2499\uff3bmm \uff3d\u00d71290\uff3bmm \u3011\u00d7 1655\uff3bmm1\nWheelbase 1730\uff3bmm1 \u6b4c\u3015tal maSS 380\uff3bkg\uff3d\nMaximum speed 60\uff3bkm \uff01h\uff3d\nDrive lype Mid\u2212motor Rear \u2212drive\nBa\u6756eries Lead\u30c8acid battely\uff0812V\uff0f42Ah \uff09x6\nLeadracid battery\uff0812V128Ah\uff09x1\n\u8a2d\u8a08\u3057 \u305f\u30c1 \u30e5 \u30fc\u30d6 \u30e9\u30fc\u30d5 \u30ec\u30fc\u30e0 \u306f \uff0c\u9efc \u9f6c \u70ad\u7d20\u8cfc S\u00a0 llA \u03a838\uff0e1\u00d7 1\uff0c6 \u3068\u9efc \u9020\u7528\u7030 \u7ba1 S\u00a0\n29040 \u00d7 40Xl \uff0e6\uff0c STKMMR 29080 \u00d7 40 \u00d7 1\uff0e6 \u3067 \u69cb\u6210 \u3055\u308c \u3066 \u3044 \u308b\uff0e\u89d2\u5f62\u92fc\u7ba1\u306f\u4e3b\u306b\u30ad \u30e3 \u30d3 \u30f3 \u306b\u4f7f\u7528 \u3057\uff0c\u92fc\u7ba1\u306f\u305d \u306e \u4ed6\n\u306e \u7b87\u6240 \u306b\u4f7f\u7528 \u3057\u3066 \u3044 \u308b\uff0e\u89d2\u5f62\u92fc\u7ba1\u3092\u30ad \u30e3 \u30d3 \u30f3 \u306b\u4f7f\u7528\u3057 \u3066 \u3044 \u308b \u7406 \u7531\u3068 \u3057\u3066 \u306f\uff0c\u92fc\u7ba1 \u306e \u76f4\u5f84\u3068\u89d2\u5f62\u92fc\u7ba1 \u306e \u5e45\u304c\u540c \u3058\u5834\n\u5408 \uff0c \u89d2\u5f62\u92fc\u7ba1\u306e \u307b \u3046\u304c\u5f37\u3044 \u66f2\u3052\u5f37\u5ea6\u3092\u6301\u3064 \u305f \u3081 \u3067 \u3042\u308b\uff0e\u305d \u306e \u305f \u3081 \uff0c\u92fc\u7ba1\u3067 \u540c \u3058\u5f37\u5ea6\u3092\u6301 \u3063 \u305f\u30ad\u30e3 \u30d3 \u30f3 \u3092\u88fd\u4f5c\u3059 \u308b\n\u3088 \u308a\u5c45\u4f4f \u30b9 \u30da \u30fc\u30b9 \u3092\u5e83\u304f \u3068 \u308b \u3053 \u3068\u304c \u3067 \u304d\u308b\uff0e\u307e \u305f\uff0c\u30c9\u30a2\u3084\u7a93\u30ac \u30e9 \u30b9 \u3092\u53d6\u308a\u4ed8\u3051 \u308b\u969b\uff0c\u5e73\u9762 \u306e \u3042\u308b\u89d2\u5f62\u92fc\u7ba1 \u306e \u307b \u3046\n\u304c\u5bb9\u6613\u306b\u53d6 \u308a\u4ed8\u3051\u308b \u3053 \u3068\u304c \u3067 \u304d\u308b\u3068\u3044 \u3046\u70b9\u3082\u3042 \u308b\uff0e\n\u30b7 \u30e3 \u30b7 \u30d5 \u30ec \u30fc \u30e0 \u306f\u56f3 3 \u306b \u793a\u3059\u3088 \u3046\u306a\u69cb\u6210\u3092\u3068\u3063 \u3066 \u3044 \u308b\uff0e\u30e2 \u30fc \u30bf\u3092\u5f8c\u8eca\u8ef8\u3088 \u308a\u524d\u65b9\u306b\u914d\u7f6e\u3059\u308b \u30df \u30c3 \u30c9\u30b7 \u30c3 \u30d7\u65b9\u5f0f\n\u3092\u63a1\u7528 \u3057 \uff0c 100\uff3bkg\u3011\u4ee5 \u4e0a \u3042 \u308b\u30d0 \u30c3 \u30c6 \u30ea\u30fc\u3082\u524d\u8f2a\u3068\u5f8c\u8f2a\u306e \u4e2d\u9593 \u306b\u914d\u7f6e\u3057\u3066 \u3044 \u308b\uff0e\u3053 \u3046\u3059 \u308b \u3053 \u3068\u3067 \uff0c\u8eca\u91cd \u306e \u534a\u5206\u8fd1 \u304f\u3092 \u5360\u3081\u308b \u30e2 \u30fc \u30bf \u3068\u30d0 \u30c3 \u30c6 \u30ea \u30fc \u304c\u8eca\u4f53\u4e2d\u592e \u306b\u914d\u7f6e \u3055\u308c \uff0c \u52a0\u6e1b\u901f\u6642\u3084\u65cb\u56de\u6642\u306b\u5b89\u5b9a\u6027\u306e \u5411\u4e0a\u3092\u56f3\u308c\u308b\uff0e\u307e\u305f \uff0c \u30e2 \u30fc \u30bf\u3084 \u30d0 \u30c3 \u30c6 \u30ea \u30fc\uff0c\u30c7 \u30d5 \u30a1 \u30ec \u30f3 \u30b7 \u30e3\u30eb \u30ae\u30a2 \uff0c\u30a4 \u30f3 \u30d0 \u30fc \u30bf \u30fc \uff0c\u30c1 \u30e3 \u30fc\u30b8 \u30e3 \u30fc \u3068\u3044 \u3063 \u305f\u91cd\u91cf\u7269\u3092\u5e8a\u4e0b \u306b\u53ce\u3081 \u308b \u3053 \u3068\u3067 \u91cd\u5fc3 \u3092 \u4e0b\u3052 \uff0c \u8d70\u884c\u6027\u80fd \u306e \u5411\u4e0a\u3084\u6a2a\u8ee2\u306e\u9632\u6b62 \u3092\u56f3 \u3063 \u3066 \u3044 \u308b \u00a0 \uff0e\n\u5de5\u5de5 \u4e00lectronlc lbra y", + "The Japan Society of Mechanical Engineers\u00a0\nNII-Electronic Library Service\u00a0\nhe apan oclety f echamc l nglneers\nFlg 3 Structure ofChass \u826es module\n3\uff0e\u885d\u7a81\u6642\u306e\u5f37\u5ea6\u89e3\u6790\n\u8a2d \u8a08\u3057\u305f \u30d5 \u30ec \u30fc\u30e0 \u306e \u5b89\u5168\u6027\u3092\u691c\u8a3c\u3059\u308b \u305f\u3081 \uff0c\u885d\u7a81\u4e8b\u6545\u3092\u60f3\u5b9a \u3057 \u305f\u8377\u91cd \u3092 \u30d5 \u30ec \u30fc \u30e0 \u306b\u639b \u3051\u308b\u9759\u89e3\u6790 \u3068\u52d5\u89e3\u7948 \u3092\u884c \u3063 \u305f \u885d\u7a81\u4e8b\u6545\u3092\u60f3\u5b9a\u3057\u305f\u8377\u91cd \u306e \u8a08\u7b97\u65b9\u4f1d\u306f\uff0c\u4e57\u54e1\u306e \u91cd\u91cf\u3092\u52a0 \u3048\u305f\u8eca\u4e21\u91cd\u91cf\u3092 M \u885d\u7a81\u6642 \u306e \u8eca\u4e21\u901f\u5ea6 \u3092 v\uff0c\u885d\u7a81 \u6642\u9593\u3092 t \u3068 \u3057 \u305f \u3068\u304d \uff0c \u904b\u52d5\u91cf\u5909\u5316 \u4e8c\u529b\u7a4d \u3088 \u308a\n\u300a4x \u3003\u30c9 F \uff081\uff09\n\u3068 \u3057\u3066\u8a08\u7b97\u3092\u884c\u3063 \u305f\u03c3\uff09\n\u8eca\u4e21\u91cd\u91cf M \u2190380\uff3bkg\u3011\u3068\u3057\uff0c\u885d\u7a81\u6642\u306e \u8eca\u4e21\u901f\u5ea6\u306f \u30d5 \u30eb \u30e9 \u30bd \u30d7\u524d\u9762\u885d\u7a81\u8a66\u9a13\u306e\u901f\u5ea6\u3092\u57fa \u306b \u5339 57\uff3bkrnh\uff3d\uff0c\u885d\u7a81\u6642\u9593\u306f \u30d5 \u30eb \u30e9 \u30ce \u30d6\u524d\u9762\u885d\u7a81\u8a66\u9a13\u306e \u6620\u50cf\u3092\u53c2\u8003 \u306b \u3057\u3066 FO 13\uff3bs\uff3d\u3068 \u3057\u3066 \u8a08\u7b97\u3092\u884c \u3044 \u885d\u7a81\u6642 \u306b \u4f5c\u7528\u3059 \u308b\u8377 \u91cd F46 \uff0c 000\uff3b\u5ca1 \u3092 \u6c42 \u3081 \u305f \u9759\u89e3\u6790\u3066 \u306f Autedesk inventor Professiona1 20 2\u3092\u4f7f\u7528 \u3057\uff0c \u5f8c\u8f2a \u306e \u30ed \u30a2\u30a2 \u30fc\u30e0 \u53d6 \u308a\u4ed8 \u3051\u90e8\u3092\u56fa\u5b9a \u3057\u305f\u72b6\u614b\u3066 \u30d5 \u30ec \u30fc \u30e0 \u306b\u524d\u65b9\u304b \u3089\u8377\u91cd\u3092\u304b \u3051\u305f\n\u52d5\u89e3\u6790 \u3066 \u306f Autodesk SimUlation Multiphysics 20 12\u3092\u4f7f\u7528 \u3057\uff0c\u56fa\u5b9a\u3057\u305f\u58c1 \u306b V\u221257\uff3bkm\uff0fh\u3011\u3066 \u30d5 \u30ec\u30fc\u30e0 \u3092\u885d\u7a81\u3055\u305b \u305f\n\u30d5 \u30ec \u30fc \u30e0 \u306e \u91cd\u91cf\u306f\u7d04 80\uff3bkg\uff3d\u306a \u306e \u3066 \uff0c\u30d0 \u30c3 \u30c6 \u30ea \u30fc\u3084\u30e2 \u30fc \u30bf\uff0c\u5916\u88c5\u306a\u3069 \u306b\u76f8\u5f53\u3059\u308b 300\uff3bkg\uff3d\u306e \u91cd \u308a\u3092\u91cd\u5fc3\u4ed8\u8fd1 \u306b\u642d\u8f09 \u3057\n\u89e3\u6790\u3092\u884c \u3063 \u305f\n\u9759\u89e3\u6790\u306b \u3088 \u308b\u7d50\u679c\u3092pa 4\uff0c\u52d5\u89e3\u6790\u306b\u3088\u308b\u885d\u7a81\u5f8c 007 \u79d2\u5f8c \u306e \u7d50\u679c \u3092\u56f3 5 \u306b\u793a\u3059 \u56f3 4\uff0c\u56f3 5 \u4e2d\u306e \u00a0 \u00a0 \u00a0 \u306e\u7b87\u6240\u306f\n\u5fdc\u529b\u304c\u639b\u304b \u308a\u6613\u3044 \u3053 \u3068\u304b\u8aad\u307f\u53d6\u308c \u308b \u00a0 \u00a0 \u306f\u885d\u7a81 \u3057\u305f\u969b\u306b\u6eb6\u63a5\u500b\u6240\u304b\u7834 \u65ad\u3059 \u308b\u53ef\u80fd \u9678\u304b \u3042 \u308a\uff0c\u00a0 \u306e \u89d2\u5f62\u92fc\u7ba1\u306f \u66f2\n\u3052\u5d29\u58ca\u3092 \u8d77 \u3053\u3059\u53ef \u80fd \u6027\u304c\u3042 \u308b \u305d \u306e \u305f \u3081\uff0c\u3053 \u306e \u70b9 \u306b\u7559\u610f \u3057\u8a2d\u8a08 \u3092\u884c \u3046\u5fc5\u8981\u304b \u3042\u308b \u307e\u305f\uff0c\u9759\u89e3\u6790 \u3068\u52d5\u89e3\u6790\u3067 \u306f\u6700\n\u5927 10\u500d \u306e \u5fdc\u529b\u5024 \u306e \u5dee\u304b \u3042\u308b\u3082\u306e \u306e \uff0c\u5909\u5f62\u306e\u72b6\u614b\u3084\u5fdc\u529b \u306e\u639b\u304b \u308b\u500b\u6240\u306f\u8fd1 \u3044\u5024\u3092\u793a\u3059\u3053 \u3068\u3092\u78ba\u8a8d \u3057\u305f\n\u5de5\u5de5 \u4e00lectronlc lbra y", + "The Japan Society of Mechanical Engineers\u00a0\nNII-Electronic Library Service\u00a0\nhe apan oclety f echanlcal nglneers\n4\uff0e\u7d50 \u8a00\n\u672c\u7a3f\u3067 \u306f \uff0c \u885d\u7a81\u6642 \u306b\u4e57\u54e1\u3092\u5b88 \u308b \u3053 \u3068\u306b\u91cd\u70b9\u3092\u7f6e \u3044 \u305f\u8d85\u5c0f\u578b\u96fb\u6c17 \u81ea\u52d5\u8eca\u306e \u30c1 \u30e5 \u30fc\u30d6\u30e9 \u30fc \u30d5 \u30ec \u30fc\u30e0 \u3092\u63d0\u6848\u3057\u305f\uff0e\u672c\n\u30d5 \u30ec \u30fc \u30e0 \u306f\u7c21\u5358\u306a\u8a2d\u5099\u3067\u88fd\u9020\u3059\u308b \u3053 \u3068\u304c \u3067 \u304d\uff0c\u5c11\u91cf\u591a\u54c1\u7a2e\u751f\u7523 \u306b \u3082\u5bfe\u5fdc \u3067 \u304d\u308b\u3088\u3046\u306b\u8003\u616e \u3055\u308c\u8a2d\u8a08 \u3055\u308c \u3066 \u3044 \u308b\uff0e\n\u307e\u305f\uff0c\u9759\u89e3\u6790 \u3068\u52d5\u89e3\u6790\u3092\u7528 \u3044 \u305f\u885d \u7a81\u6642\u306e \u5f37\u5ea6\u89e3\u6790\u3092\u884c \u3044 \uff0c\u8a2d\u8a08\u6642\u306b\u7559\u610f\u3057\u306a\u3051\u308c \u3070\u306a\u3089\u306a\u3044 \u7b87\u6240\u3092\u78ba\u8a8d\u3057\u305f\uff0e\u4eca \u5f8c \uff0c \u8eca\u4e21 \u306e \u8efd\u91cf\u5316 \u3068\u885d\u7a81\u5b89\u5168\u6027 \u306e \u5411\u4e0a \u3092\u76ee\u6307 \u3057\u3066 \u89e3\u6790\u3092\u9032 \u3081\uff0c\u8d85\u5c0f\u578b\u96fb\u6c17 \u81ea\u52d5\u8eca\u306e \u88fd\u4f5c\u3092\u884c \u3044 \u672c\u30d5 \u30ec\u30fc\u30e0 \u306e\u6709\u52b9 \u6027 \u3092\u78ba\u8a8d\u3059 \u308b\uff0e\n\u6587 \u732e\n\uff081\uff09 \u56fd\u571f\u4ea4\u901a\u7701\u90fd\u5e02\u5c40 \u30fb\u81ea\u52d5\u8eca\u5c40\uff0c \u201c \u8d85\u5c0f\u578b\u30e2 \u30d3 \u30ea\u30c6 \u30a3 \u5c0e\u5165\u306b \u5411\u3051\u305f \u30ac \u30a4 \u30c9\u30e9\u30a4 \u30f3 \u201d \uff082012\uff09\uff0e \uff082\uff09 \u5e73\u702c\u535a\u4eba\uff0c \u201c \u9ad8\u9f62\u8005 \u306b 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] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure47-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure47-1.png", + "caption": "Figure 47 P-POD Mk. IV Bracket", + "texts": [ + " This design had heritage and did not pose a strength issue in the past, but moving forward there was no reason to maintain this odd design. Material was removed from most sections of the part, reducing it to more of a skeleton like structure, as opposed to solid surfaces. Because the Bracket does not need to provide CubeSat containment, there is more liberty allowed in the structural design, unlike the rest of the parts on the P-POD. The resulting Bracket following the mass reduction changes is shown below in Figure 47. The side walls that bear the load from the Door were reduced to two spars, and some material was removed in other sections that did not take any load, such as between the two mounting through holes, and the sections in the front face near the conical cup. Additionally, some material was removed from under the conical cup to accommodate the new Door geometry. Some of these changes reduced the front sections bending stiffness. In order to help rectify this, the lip that protrudes from the top edge of the bracket was heightened, to provide some extra Page 63 stiffness" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000804_le_1878_context_etdr-Figure2.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000804_le_1878_context_etdr-Figure2.6-1.png", + "caption": "Figure 2.6 Tensile bar pattern with filter for 0.75 in diameter by 8 in tall cylinders.", + "texts": [ + " The bar has steps that were 0.25, 0.5, 0.75, and 2 inches high. This mold was made from green sand and was horizontally parted (Figure 2.5). This casting system weighed 12 lbs. Additional metal was poured into pig mold which can hold up to 120 lb of iron but typically were filled to between 60- 80 lbs for ease of recharging. Alloy Set B was used to cast 5 tensile bar sets and 2 step bars. The tensile bar molds had a 55x55x12.7 mm filter with 2.31 mm diameter holes positioned at the bottom of the pouring cup (Figure 2.6). In addition, 3 y-blocks were cast (Figure 2.7) with a 23.5 mm cross section at the bottom. All three 18 lb y-blocks were cast in the same 106 lb chemically bonded mold (Figure 2.8). The y-blocks were open poured and had sand placed on the exposed top after approximately 6 minutes. 10 11 This chemically bonded sand was air set using an ALPHASET\u00ae 9010 resin system mixed in a Tinker Omega TOM. The total addition to the sand was 1.25% by weight with 30% catalyst and 70% resin. Molds were packed up to two weeks ahead of time for each pour with the typical time being 2-5 days" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000087_5_secm-2014-0048_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000087_5_secm-2014-0048_pdf-Figure2-1.png", + "caption": "Figure 2 Concept for a modular driveshaft system with a profiled shaft body: complex drivetrain (A), linearly extruded shaft body (B), and demonstrator part (C).", + "texts": [ + " For example, the layer stiffness can be modified with the aim of achieving an even stress distribution in the driveshaft laminate subjected to shear loads, for which a concept is presented. To enable an application of those concepts, the strength and stiffness parameters of different braided and wound patterns are experimentally investigated. A modular system concept for lightweight driveshafts has been developed at the ILK to reduce the development time and cost. This system consists of a composite shaft body with its profiled cross-section (Figure 2B) and a broad range of functional components such as flanges, gear wheels, universal joints or bearings, which can be chosen from a standardized catalogue. A customized power train component is manufactured by cutting the composite shaft body to length and a subsequent assembling of the functional components at the required positions (see Figure 2A\u2013C) [6, 7]. Here, the profiled cross-section allows an easy assembly by a form fit connection. Although this design is highly flexible and permits the manufacturing of potentially cost-efficient semifinished products, the undulated laminate cross-section reduces the load bearing capacity of the driveshaft when compared to a shaft with cylindrical cross-section. Therefore, in a further work, this modular concept has been adapted to meet the requirements of high-performance applications. The newly developed driveshaft concept focuses on the provision of high-performance semifinished driveshaft bodies, which are equipped with metallic end fittings for concentrated load introduction (Figure 3, top). A basic geometry as depicted in Figure 3 is chosen. It features a profiled inner laminate, the so-called profiled shell (1), for load introduction, supplemented by axial reinforcements (2) and enclosed by a cylindrical laminate, or cylindrical shell (3). This cylindrical shell efficiently transmits loads over the span of the driveshaft, enhancing the performance of the component when compared with the previous design (Figure 2). This novel design recently was successfully patented [10]. In order to maintain the advantage of a continuous manufacturing process, the profile is linearly extruded to constitute the shaft body. Thus, the profiled geometry not only influences the load introduction capabilities but also the mechanical performance of the shaft in the \u201cundisturbed\u201d area between the load introduction zones. Those two features have to be matched in order to develop a viable design. For this, a simulation model was created and a parameter study on favorable geometrical parameters of the profiled cross-section was conducted [11]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure57-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure57-1.png", + "caption": "Figure 57. The control test bed utilizing springs to create intercation torques along INEV & DFPF axes of roration. A: vetical view, B: horizontal view.", + "texts": [ + "........................ 84 Figure 55: The Nyquist diagram of the control system along DFPF (left) and INEV (right) axis with 10% perturbation................................................................................................................................. 85 Figure 56: The time response characterisitcs of the control system along DFPF (left) and INEV axis (right) in regular condition (\u2026), and with 10% perturbation (-). ........................................................ 85 Figure 57: The control test bed utilizing springs to create intercation torques along INEV & DFPF axes of roration. A: vetical view, B: horizontal view. ................................................................................ 86 Figure 58: Controlling vi-RABT along DFPF axis of rotation. The desired torque (top .. red), actual torque (top - blue) and control command (bottom - black) are presented ........................................ 87 Figure 59: Controlling vi-RABT along INEV axis of rotation", + " 85 As shown in time response and frequency analysis in Figures 55-56, the perturbed characteristics of the system also demonstrated stable margins. Accordingly if the coefficients of the linear 86 model were subject to perturbation by 10%, the system is still in safe range of operation. The system is stable both internally as revealed by frequency analysis and bounded as shown in time domain. In order to assess and evaluate the performance of the controllers along each axis, the following test-bed was designed and developed, as shown in Figure 57. Two springs were attached to the front and back part of the footplate to resist the movement of force-plate and create an interaction torque similar to that produced by human subjects. The bench-test was designed to evaluate the torque controllers. Two springs in the anterior lateral and posterior medial of the footplate provided the possibility of applying all combination of torques along both DOF. Using this mechanism, the actuators were controlled to drive the forceplate so as to experience particularly chosen desired torque values along each degree of freedom, i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure24-1.png", + "caption": "Figure 24 : (a) Vue de face, (b) Vue en perspective des anneaux fendus [23].", + "texts": [], + "surrounding_texts": [ + "Dans cette section, qui est la plus fournie en termes de r\u00e9seaux bi-bandes, trois m\u00e9thodes possibles de design ressortent : les structures entrelac\u00e9es, les patchs perfor\u00e9s, et enfin, les structures chevauch\u00e9es ou sandwiches. Ces solutions \u00e9tant plus susceptibles de permettre d\u2019atteindre le cahier des charges, elles seront plus d\u00e9taill\u00e9es que celles des parties pr\u00e9c\u00e9dentes." + ] + }, + { + "image_filename": "designv8_17_0004695_oradea2018_02004.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004695_oradea2018_02004.pdf-Figure12-1.png", + "caption": "Fig. 12. The method of applying the force and defining contacts in ANSYS", + "texts": [ + " The assembly model with finite elements is shown in figure 11, a and in figure 11, b is shown a detail on the bolt meshing. On the elements found in contact there was made a finer meshing, meaning it had more layers of finite elements and nodes in order to have a better convergence of the results and contact from that area. After meshing there were obtained 16234 finite elements and 67696 modes. For this model there are shown two calculation cases, as follows: case 1: guide material PA46, F=5 N and \u03bc=0.28; case 2: guide material PA66, F=5 N and \u03bc=0.28; The method of applying the force is presented in figure 12 being identical for both analyzed cases. For load case 1, of this model, the obtained value of maximum displacement is 0.0005 mm, figure 13 a. If it is made a detailed value on the guide it is observed that the guide is deformed locally and only on the contact zone between the guide and bolt. In figure 13 b, it is shown the guide deformation at a scale 1:1, and in figure 13 c, it is shown the guide deformation at an enlarged scale by 3000 times, only for visualization. The distribution of the contact pressure between guide and bolt, in this case, it is shown in figure 14 and has an uniform distribution with higher values towards the interior of the bolt, the maximum value of the contact pressure being 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003896_l_45_1_45_1_127__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003896_l_45_1_45_1_127__pdf-Figure2-1.png", + "caption": "Fig. 2. Specimen configuration used for crack initiation studies.", + "texts": [ + " Cylindrical specimens of 5 mm gauge diameter and 20 mm gauge length were used for the determination of tensile properties of the steel following ASTM standard E803.18) These tests were carried out using a Universal testing machine (Schimadzu, model: AG-5000G) at a nominal strain rate of 4.2 10 4 s 1 at room temperature. The average yield (sy) and tensile (s t) strength of the material were found to be 94 2 and 238 3 MPa respectively, whereas the uniform and the total elongation were estimated as 35 0.8 and 45 0.5% respectively. The fatigue studies were carried out on small hourglass type flat specimens, made from the as-received material as shown in Fig. 2. One of the flat surfaces of these samples was ground, polished, and etched to reveal the microstructure. The fatigue tests were performed with the help of an Instron machine (model: 8501) using sinusoidal wave at a frequency of 10 Hz at room temperature (approximately 298 K) in the laboratory air. The tests were conducted at various stress ranges keeping the maximum stress as 0.6 to 1.0sy of the steel while maintaining the minimum stress as zero. Each test at different applied stress ranges was carried out for 2 104 cycles" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure11-1.png", + "caption": "Fig. 11. Maximum reduced stresses for the load with a hazardous multiplier", + "texts": [], + "surrounding_texts": [ + "The presented composite frame with sandwich-type walls was analysed using ANSYS Workbench 2020 R2. First-degree solid and shell elements were used in the analysis (Fig. 6). The data on the materials used in the analysis of the frame come from the ANSYS Workbench library. Test samples were made simultaneously with the frame, in order to determine the actual material parameters such as density or equivalent Young\u2019s modulus. The tests conducted, which will be described in the next article, will be used for validating the model. The following frame loads were assumed for analysis (Fig. 7): \u2022 point A \u2014 support, \u2022 point B \u2014 support, \u2022 point C \u2014 manipulator 200N (due to the lim- ited budget of the project and difficult to predict dynamic loads, a doubled force value was assumed), \u2022 point D \u2014 battery 75N, \u2022 point E \u2014 computer and electronics 5N, \u2022 point F \u2014 laboratory 29N. The analysis was performed for several variants of the grid in order to verify the convergence of the results. The similarity of the obtained results confirms the appropriate densification of the grid (Table 2). The analysis was carried out iteratively, starting from the base load value up to the dangerous load value (Table 3). The following drawings presented (Fig. 8, Fig. 9, Fig. 10) show the results for the analysis without force multipliers. Figures 11, 12, and 13 shows the results for the analysis with the critical load included. Figure 14 show where the frame joins the rocker-bogie suspension beam. It is possible to identify the point where the reduced stresses reach a value close to the hazardous value for the material used in the structure. Due to the complex state of stresses occurring in this point, potentially dangerous for the structure, additional local laminate layers should be applied to increase the durability of the structure. Figure 15 show the progress of changes in the value of reduced stresses as a function of the force multiplier and the safety factor as a function of the force multiplier. Despite the linear increase in load, a non-linear decrease of the safety factor can be observed, which may result from the change in the relationship between the values of shear stresses and the values of normal stresses." + ] + }, + { + "image_filename": "designv8_17_0004319_echaterobot_download-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004319_echaterobot_download-Figure2-1.png", + "caption": "Figure 2. Robotic wrist variant no. 1", + "texts": [ + "7 mm in diameter on the back of the hand. This opening allows for its mechanical joining with either the robot\u2019s arm or wrist. ROBOTIC HAND\u2019S WRIST VARIANT PROPOSALS 3 wrist variants were manufactured for the MechateRobot robotic hand [Mecha 2015]. All three variants meet the condition of three degrees of freedom of movement. All variants were created and then rendered in the PTC Creo 2.0. The selected optimum variant was made of plastic on a 3D printer. The first variant was executed as an elementary kinematic chain pictured on the Fig. 2. This design of a kinematic chain is made up of four main parts. The variant\u2019s structure is simple and its advantage is noncomplexity of production and its cost. Its disadvantage is its overall size, which is also one of the main reasons why we did not proceed with manufacturing the prototype. The second variant design was a cylinder-shaped wrist consisting of four parts. Rotation of the central rotating part is ensured by a simple cog and transmission. A disadvantage of this variant and the main reason why it was not selected for the final solution is its more complicated structure and incompatibility of the 3D printer\u2018s technical parameters therewith, so that it would not be possible to proceed with its manufacturing using the printer" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003696_7_10_27_10_1144__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003696_7_10_27_10_1144__pdf-Figure4-1.png", + "caption": "Fig. 4 Motion of two video cameras (top view)", + "texts": [ + " \u91ce \u4e2d \u30fb\u4f0a \u9054:\u4e21 \u773c \u8996 \u3068\u904b \u52d5 \u8996 \u3092\u5fdc \u7528 \u3057\u305f \u30d3\u30c7 \u30aa \u30b7 \u30b9 \u30c6 \u30e0 1147 Table 1 Performance of position measuring methods * Clock: 2 (MHz) Distanse between two microphones: 100 (mm) \u30c8\u306e\u9762\u3067\u512a\u308c\u3066 \u3044\u308b(Table 1). 2.3 \u64ae\u5f71 \u30fb\u8868\u793a\u6a5f\u5668 \u306e\u914d\u7f6e \u3068\u79fb\u52d5\u5236\u5fa1 \u64ae \u5f71\u6a5f\u5668\u304a \u3088\u3073\u8868\u793a\u6a5f\u5668 \u306e\u914d\u7f6e\u306e\u8a2d\u5b9a\u624b \u9806\u306f\u4ee5\u4e0b\u306e \u3068\u304a \u308a\u3067\u3042 \u308b. (1) \u8996 \u8005 \u3068\u30c7 \u30a3\u30b9\u30d7 \u30ec\u30a4\u3068\u306e\u8ddd\u96e2 \u03bb\u3092,\u64ae \u5f71\u7cfb \u3068 \u8868\u793a \u7cfb\u306e\u753b \u89d2\u304c\u4e00\u81f4\u3059 \u308b \u3088 \u3046 \u306b\u8a2d\u5b9a \u3059 \u308b(\u30d3 \u30c7\u30aa\u30ab \u30e1 \u30e9\u306e\u7126\u70b9 \u8ddd\u96e2,\u64ae \u50cf\u7d20\u5b50 \u306e\u5927 \u304d\u3055,\u30c7 \u30a3\u30b9\u30d7 \u30ec\u30a4\u306e \u5927 \u304d\u3055\u306a \u3069\u306b\u5fdc \u3058\u3066 \u03bb\u306e\u5024\u306f\u5909 \u5316\u3059\u308b)(\u6ce82). (2) 2\u53f0 \u306e \u30d3\u30c7\u30aa\u30ab\u30e1 \u30e9\u306e \u30ec\u30f3\u30ba\u7cfb \u306e\u4e2d\u5fc3\u9593 \u306e\u8ddd \u96e2 \u304c\u4e21\u773c \u306e\u5e45 \u3068\u7b49 \u3057\u304f\u306a \u308b\u3088 \u3046\u306b\u914d \u7f6e\u3059 \u308b. (3) \u4e21 \u30ab\u30e1 \u30e9\u306e \u30ec\u30f3\u30ba\u7cfb \u306e\u4e2d\u5fc3 \u306e\u4e2d\u70b9 \u304b \u3089\u524d\u65b9 \u306b \u8ddd\u96e2 \u03bb\u306e\u4e00 \u70b9\u3092F\u3068 \u3059 \u308b.\u3053 \u306e \u3068\u304d\u4e21 \u30ab\u30e1 \u30e9\u306e\u5149\u8ef8 \u304c \u3053\u306e\u4e00\u70b9F\u3067 \u4ea4 \u308f \u308b\u3088 \u3046\u306b\u5411 \u304d\u3092\u8abf\u7bc0\u3059 \u308b. (4) \u4e21 \u30ab\u30e1 \u30e9\u306e\u5149\u8ef8 \u306e\u4ea4\u70b9 \u3092\u70b9F\u306b \u4fdd \u3061\u306a\u304c \u3089, \u8996\u8005 \u306e\u5de6\u53f3 \u306e\u79fb \u52d5\u306b\u4f34 \u3044,\u305d \u306e\u79fb\u52d5\u91cf \u3068\u7b49 \u3057\u3044\u8ddd\u96e2 \u3060 \u3051\u4e21 \u30ab\u30e1\u30e9\u306e \u30ec\u30f3\u30ba\u7cfb \u306e\u4e2d\u5fc3 \u3092\u79fb\u52d5 \u3055\u305b \u308b(Fig. 4). \u672c\u8a66\u4f5c \u306e\u5834\u5408,\u03bb=88.0(cm)\u3068 \u3057\u305f.\u3059 \u306a\u308f \u3061,\u8996 \u8005 \u3068\u30c7\u30a3\u30b9 \u30d7 \u30ec\u30a4\u306e\u8ddd\u96e2 \u309288.0(cm)\u3068 \u3057,\u4e21 \u30ab\u30e1 \u30e9 \u3092,\u305d \u308c\u305e\u308c \u306e\u5149\u8ef8 \u304c\u8ddd\u96e288.0(cm)\u306e \u4e00\u70b9\u3067\u4ea4\u308f \u308b \u3088 \u3046\u306b\u914d\u7f6e \u3057\u305f. \u4e21 \u30ab\u30e1 \u30e9\u306e\u5149\u8ef8\u65b9 \u5411\u306e\u4ea4 \u70b9\u3092\u6240\u5b9a \u306e\u4f4d\u7f6e \u306b\u56fa\u5b9a \u3059\u308b \u305f\u3081\u306b,Fig. 5\u306b \u793a \u3059 \u3088 \u3046\u306a\u6a5f\u69cb \u3092\u63a1\u7528 \u3057\u305f.\u524d \u65b9 \u3068\u5f8c\u65b9\u306b\u305d\u308c\u305e\u308c\u4e00\u5bfe \u306e \u30ec\u30fc\u30eb \u3092\u5e73\u884c \u306b\u6577 \u304d,\u305d \u306e\u4e0a \u306b\u305d\u308c\u305e\u308c\u53f0\u8eca \u3092\u8f09\u305b \u308b.\u53f0 \u8eca \u306f\u30b9\u30c6 \u30c3\u30d4\u30f3\u30b0\u30e2\u30fc\u30bf \u3068\u30e9\u30c3\u30af\u30ae\u30a2\u306b\u3088\u3063\u3066,\u5de6 \u53f3 \u306e\u52d5 \u304d\u3092\u30b3 \u30f3 \u30c8\u30ed\u30fc\u30eb\u3055 \u308c \u308b.\u30ab \u30e1 \u30e9\u306e\u5411\u304d\u304c\u4e0a\u8ff0 \u306e\u70b9F\u3092 \u5411 \u304f\u3088 \u3046\u306b,\u53f0 \u8eca \u306e\u4e0a \u306b2\u53f0 \u306e\u30ab\u30e1 \u30e9\u56fa\u5b9a \u53f0\u3092\u8f09\u305b \u308b.\u305f \u3060 \u3057\u524d\u65b9 \u306e\u53f0 \u8eca \u3068\u306f \u30ea\u30f3\u30af\u3067,\u5f8c \u65b9 \u306e\u53f0\u8eca \u3068\u306f\u3059\u3079 \u308a\u30ea\u30f3\u30af\u3067,\u9023 \u7d50 \u3055\u305b \u308b.\u30d3 \u30c7\u30aa \u30ab\u30e1 \u30e9\u306e \u30ec\u30f3\u30ba\u7cfb\u306e \u4e2d\u5fc3 \u304c,\u524d \u65b9\u306e \u30ea\u30f3\u30af\u306e\u4f4d \u7f6e\u306b\u4e00\u81f4\u3059 \u308b\u3088 \u3046\u306b,\u30d3 \u30c7\u30aa \u30ab\u30e1\u30e9\u3092 \u56fa\u5b9a \u53f0 \u306e\u4e0a \u306b\u56fa\u5b9a\u3059 \u308b. \u4ee5\u4e0a \u306e\u8a2d\u5b9a \u306b\u3088\u308a,\u4e21 \u30ab\u30e1 \u30e9\u306e\u5149\u8ef8 \u306e\u4ea4\u70b9 \u306f,\u30ec \u30fc \u30eb \u3068\u5e73\u884c\u3067 \u304b\u3064\u70b9F\u3092 \u901a \u308b\u76f4\u7dda \u4e0a\u3092\u52d5 \u304f\u3088 \u3046 \u306b \u306a \u308b \u304c,\u3055 \u3089\u306b\u305d\u308c\u305e\u308c\u306e\u53f0\u8eca \u306e\u79fb \u52d5\u8ddd \u96e2\u6bd4\u3092\u6b63 \u3057\u304f\u8a2d\u5b9a \u3059 \u308b\u3053\u3068\u306b\u3088 \u308a,\u4e21 \u30ab\u30e1 \u30e9\u306e\u5149\u8ef8 \u306e\u4ea4 \u70b9\u3092\u4e00\u70b9F\u306b \u56fa \u5b9a\u3059 \u308b\u3053\u3068\u304c\u3067 \u304d\u308b" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000986_ile.php_fileID_37135-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000986_ile.php_fileID_37135-Figure2-1.png", + "caption": "Figure 2 Morphology of the Si-NR FET device. (A) The 3D schematic diagram of the Si-NR FET device; (B) SEM image of the Si-NR FET device; and (C) SEM image of si-Nr. Abbreviations: FET, field-effect transistor; SEM, scanning electron microscopy; si-Nr, si-Nr, silicon nanoribbon.", + "texts": [ + " A Ni/Au (20 nm/100 nm) bilayer was deposited and patterned on the wafer to define the contact area of the source, the drain, and the back gate. Ohmic contact was obtained by using rapid thermal annealing at 400\u00b0C (10\u00b0C/s; Figure 1D). SiO 2 /SiN x (200 nm/200 nm) was deposited as a passivation layer. The Si-NR detection window was opened by using reaction ion etching and BOE. The chamber of the RIE is a vacuum environment, with pressure always below 10\u20133 Pa and operating frequency between 10 and 100 MHz. (Figure 1E). Figure 2 shows the 3D schematic diagram and sectional schematic of Si-NR. The size of a single device is 15\u00d710 mm. There are five parallel Si-NRs on the device that can be observed in the detecting window, as shown in Figure 2A. One of the Si-NRs was characterized by scanning electron microscopy (SEM; Quanta 400 FEG, FEI Company, Hillsboro, OR, USA; Figure 2B and C). An SEM image of Si-NR device (length 30 \u03bcm) is shown in Figure 2B, and a corresponding zoomed-in image, showing the device with width 120 nm and length 25 nm, is shown in Figure 2C. On the device, a passivation layer was deposited by PECVD and patterned by lithography and the RIE process. surface functionalization of the si-Nr Si-NRs should be covalently modified with monoclonal anti-CEA through the surface natural oxidation layer of Si-NRs for the purpose of CEA detection. The method using the linker of APTES bounded with Glu is one of the most well-known chemical covalent methods, wherein an aldehyde terminal is prepared for bonding with the detected protein.30,31 The same method was used in the study for surface functionalization" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001008__caadria2021_133.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001008__caadria2021_133.pdf-Figure7-1.png", + "caption": "Figure 7. structure diagram.", + "texts": [], + "surrounding_texts": [ + "Finite element analysis and simulation of the bridge were carried out to verify the design strategies and get the correct amount of prestressing. The structure diagram is as follow: Supports at both ends of the bridge are hinged. According to related regulation and the test result above, the material properties of the prestressed steel bars and the printed parts were listed as follows: The steel bars were made of finished rolled rebar without longitudinal ribs, connected by rebar nuts on both sides, manually tightened by a torque wrench, and the amount of the tension is controlled by the wrenching torque. The live load of the bridge deck was set as 4.5kPa and calculate with the full span and half span load case." + ] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure13-1.png", + "caption": "Fig. 13. Distribution of the safety factor for the load with a hazardous multiplier", + "texts": [], + "surrounding_texts": [ + "The presented composite frame with sandwich-type walls was analysed using ANSYS Workbench 2020 R2. First-degree solid and shell elements were used in the analysis (Fig. 6). The data on the materials used in the analysis of the frame come from the ANSYS Workbench library. Test samples were made simultaneously with the frame, in order to determine the actual material parameters such as density or equivalent Young\u2019s modulus. The tests conducted, which will be described in the next article, will be used for validating the model. The following frame loads were assumed for analysis (Fig. 7): \u2022 point A \u2014 support, \u2022 point B \u2014 support, \u2022 point C \u2014 manipulator 200N (due to the lim- ited budget of the project and difficult to predict dynamic loads, a doubled force value was assumed), \u2022 point D \u2014 battery 75N, \u2022 point E \u2014 computer and electronics 5N, \u2022 point F \u2014 laboratory 29N. The analysis was performed for several variants of the grid in order to verify the convergence of the results. The similarity of the obtained results confirms the appropriate densification of the grid (Table 2). The analysis was carried out iteratively, starting from the base load value up to the dangerous load value (Table 3). The following drawings presented (Fig. 8, Fig. 9, Fig. 10) show the results for the analysis without force multipliers. Figures 11, 12, and 13 shows the results for the analysis with the critical load included. Figure 14 show where the frame joins the rocker-bogie suspension beam. It is possible to identify the point where the reduced stresses reach a value close to the hazardous value for the material used in the structure. Due to the complex state of stresses occurring in this point, potentially dangerous for the structure, additional local laminate layers should be applied to increase the durability of the structure. Figure 15 show the progress of changes in the value of reduced stresses as a function of the force multiplier and the safety factor as a function of the force multiplier. Despite the linear increase in load, a non-linear decrease of the safety factor can be observed, which may result from the change in the relationship between the values of shear stresses and the values of normal stresses." + ] + }, + { + "image_filename": "designv8_17_0001215_7725587_07783972.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001215_7725587_07783972.pdf-Figure1-1.png", + "caption": "Fig. 1. The quad-rotor modeling", + "texts": [ + " (19) If the mass matrix M in (14) is singular, the UdwadiaPhohomsiri equation is utilized (Udwadia & Phohomsiri 2006) instead of Udwadia-Kalaba equation (Udwadia & Kalaba 2000) to acquire the equation of motion of the constrained system.The equation of motion is given by [29] q\u0308 = [ [I \u2212A+A]M A ]+ [ Q b ] (20) where the superscript \u201c + \u201d denotes the Moore-Penrose generalized inverse (Moore 1920; Penrose 1955). Equation (20) is valid when the matrix [M |A]T is in full rank (Udwadia & Phohomsiri 2006). The full rank condition is essential for the equation of motion of the constrained system to be unique, which can be used to check whether the proposed model is correct. As is shown in Fig. 1, every rotor driven by a DC servo motor produces lift force as well as moment [3], [11]. It is assumed that the body fixed frame B{xb, yb, zb} is created at the mass center of the rigid quad-rotor body where the z-axis is pointing upwards. The frame B has six degrees of freedom with respect to the earth fixed frame I{x, y, z} which is assumed as an inertial frame. Therefore the position and orientation of the quad-rotor can be described as a position vector p = (x y z)T and an orientation vector r = (\u03b8 \u03c8 \u03c6)T " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001081_f_version_1698412750-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001081_f_version_1698412750-Figure2-1.png", + "caption": "Figure 2. Stellar imaging schematic.", + "texts": [ + " Finally, the intensity-weighted centroid formula shown in Equation (5) is used to calculate the stellar centroid: xc = \u2211x\u2208D \u2211y\u2208D xI(x, y) \u2211x\u2208D \u2211y\u2208D I(x, y) ; yc = \u2211x\u2208D \u2211y\u2208D yI(x, y) \u2211x\u2208D \u2211y\u2208D I(x, y) , (5) where xc, yc are the row and column coordinates of the stellar centroid, respectively, and D is the corresponding connected component. Stellar light is focused on the light-sensitive plane through the lens to form an image; thus, the imaging model can be regarded as a pinhole perspective projection model [40], as shown in Figure 2. In Figure 2, Ow \u2212 xwywzw is the world coordinate system and O\u2212 xyz is the camera coordinate system. According to the principle of pinhole imaging, the angle \u03b8i = \u03b8o always holds, and because the star is a point source of light at infinite distance from the camera, \u03b8i does not change with the movement of the camera. According to the above analysis, it can be concluded that the angle between two stars is constant no matter when, where, and in what position they are photographed, making the angle between the stars a good matching feature, which in this paper we call the radial modulus feature (RMF)", + " This variation causes errors in the calculation of the angle; in order to avoid this error and ensure the direct use of twodimensional coordinates to reduce the calculation, the distance between the stars can be used as the RMF instead of the angle between then. It should be noted that while the distance between stars varies at different positions in the image, based on prior analysis this variation is acceptable in image registration for most astronomical telescopes. Letting the field of view angle be f ov and the image size be n pixels, the process of analyzing the amount of variation in combination with Figure 2 is as follows: d2 = (d2 1 + f 2) + (d2 2 + f 2)\u2212 2 \u221a d2 1 + f 2 \u221a d2 2 + f 2 cos \u03b8o = n2 4 cot2 f ov 2 [ (tan2 \u03b81 + 1) + (tan2 \u03b82 + 1)\u2212 2 \u221a tan2 \u03b81 + 1 \u221a tan2 \u03b82 + 1 cos \u03b8o ] , (6) where f ov is the field of view angle and cot is the cotangent function. When \u03b81 = \u03b82 = \u03b8o 2 , the distance between stars takes the minimum value: dmin = n tan \u03b8o 2 cot f ov 2 . (7) When \u03b81 = \u03b82 = f ov 2 , the distance between the stars takes the maximum value: dmax = n sin \u03b8o 2 csc f ov 2 . (8) Then, the maximum value of the variation when the angle is \u03b8o is shown in Equation (9): derr = n sin \u03b8o 2 csc f ov 2 \u2212 n tan \u03b8o 2 cot f ov 2 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000545_4.03.023663.full.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000545_4.03.023663.full.pdf-Figure1-1.png", + "caption": "Fig. 1 Surface rendering of the digital pinna. a) Raw pinna shape representation, and the flap is covered by tragus; b) splitting the pinna with a coronal plane to uncover the hidden flap, which is marked by arrows and dark gray area; c) transverse section of the pinna with flap removed by digital operation and d) transverse section with flap.", + "texts": [ + " According the result of field decomposition, two resonance cavities around the flap is simplified to a dipole, and the mechanism of the scanning side lobes generated by resonance cavities and dipole are analyzed by comparison of the results obtained from the numerical calculation of the real pinna and the analytical solution of the dipole. The pinna sample of a Brown Long-Eared Bat used in this numerical experiment is obtained by the micro-CT scanning and digital processing [5,13], which is show in Fig. 1 a). As shown in Fig.1, both c) and d) is obtained by cutting the pinna model with a transverse plane marked by the frame in b). The finite element method (FEM) is employed in this study to calculate the acoustic near field. The basic computational element used is cuboid-shaped volume [5,6]. By reciprocity, the reception and radiation pattern of the ear is equivalent [14]. Hence, a point acoustic source is put in the canal opening, and then FEM is utilized to calculate the acoustic near field. The Kirchhoff integral formulation is used to calculate the acoustic far field projection", + " Because the wavelength is about in the same size as the flap, the sound can pass around the edge of the flap as the diffraction effect, so the flap has little effect on both near and far field. In addition, the wave of the single source is spherical wave which is isotropic, so it has no effect on directivity gain. As a result, the single source and flap items are not significant in this study. Hence, only the other three items are considered in this study. The cavity surrounded by the pinna wall and tragus is separated into two half-open cavities by flap (see Fig. 1), which are named inner cavity and outer cavity respectively. The layer crossing the center of resonators can be picked up for calculating far-field directivity, and dipole approximation is involved to simulate the frequency-driven sidelobe scanning as the amplitude of sound pressure in both cavities increase much more than other range if resonance occurs. In the acoustic far-field (10m radius in this study), the radiation of the inner resonator can be equalized to point source pi, and the radiation of the outer resonator can be equalized to point source po", + " The Eq. (2) can be written as ]*[ *]**[ 1 )( )()( \u03d5 \u03c9 \u03c9\u03d5\u03d5 j tkrj tkrjkj O j I oir ep r e eepep r ppp OI \u2212\u2212 \u2212\u2212+\u0394 = +\u2248 += (7) where, )cos(***222 IOOIOI kppppp \u03d5\u03d5 \u2212\u0394+++= (8) and, )cos(cos )sin(sin tan 1 OOII OOII kpp kpp \u03d5\u03d5 \u03d5\u03d5\u03d5 +\u0394+ +\u0394+= \u2212 (9) As shown in Eq. (7), when r is constant, pr is determined by the phase difference between the dipole \u03c6O-\u03c6I, wave number k and d*cos( -\u03b80), which is the difference of sound path that the sound travels from far-field to each pole (see Fig. 2 (b)). As shown in Fig. 1, the flap is situated in a half-opened circle, and split one cavity into two cavities. When the two cavities are in resonance, they can be simplified into a dipole (shown as Fig. 2 (b)), and this simplification is investigated in this study. The data obtained from the both cavities are analyzed. The geometrical central points of the cavities are considered as the position of the dipole, and angle between the dipole and the horizontal line is the initial oblique angle \u03b80. The amplitude (pI, pO) and phase (\u03c6I and the outer cavity \u03c6O) of the dipole are calculated for each frequencies and plotted for each items (pinna without flap, flap, interaction), as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001274_le_1693_context_etdr-Figure1.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001274_le_1693_context_etdr-Figure1.6-1.png", + "caption": "Figure 1.6: General diagram of twin deformation in a simple tetragonal lattice, showing", + "texts": [ + " Twin deformation typically occurs in materials with a limited amount of slip systems present (BCC/HCP) or at lower deformation temperatures and generally requires higher levels of stress than slip deformation in FCC materials [1]. In FCC materials, plastic deformation begins with slip and does not begin to twin until the material has been sufficiently work hardened to where the flow stress in the material has reached the stress required for twin deformation. During twin deformation, sections of the lattice are deformed to move to mirror positions across the defined twin boundary or twin plane, as shown in Figure 1.6. The crystallographic orientation of the lattice changes during twin deformation, as compared to slip deformation where the 9 crystallographic orientation stays the same. When compared to slip deformation, where single planes of atoms move, during twin deformation multiple planes of atoms move which involves large overall atomic movement, when compared to slip deformation on a single plane of atoms. Thus, the reason why twin deformation requires more energy than slip deformation. 3 Republished with permission of John Wiley and Sons from Fundamentals of Materials Science and Engineering: An Integrated Approach, 4th Edition, David G Rethwisch, William D", + "6 tan \u03b8200) (A.9) \ud835\udf15\ud835\udefd2 = \u2202\u03b2 \u2202\u2206(2\u03b8200 CG \u22122\u03b8200 max) = \u22121 (11 tan \u03b8111+14.6 tan \u03b8200) (A.10) \u2202\u03b2 \u2202\u03b8111 = 11(\u2206(2\u03b8111 CG \u22122\u03b8111 max)\u2212\u2206(2\u03b8200 CG \u22122\u03b8200 max)) sec2 \u03b8111 (11 tan \u03b8111+14.6 tan \u03b8200)2 (A.11) \u2202\u03b2 \u2202\u03b8200 = \u221214.6(\u2206(2\u03b8111 CG \u22122\u03b8111 max)\u2212\u2206(2\u03b8200 CG \u22122\u03b8200 max)) sec2 \u03b8200 (11 tan \u03b8111+14.6 tan \u03b8200)2 (A.12) 77 Appendix F: Copyright Clearance Agreements Copyright agreement for Figure 1.2 in Section 1.1 78 79 80 Copyright agreement for Figure 1.4 in Section 1.2.1 81 82 83 84 85 Copyright agreement for Figure 1.6 in Section 1.2.2 86 87 88 Copyright agreement for Figure A.1 in Appendix A (pg. 53), Figure B.1 in Appendix B (pg. 57) and Figure C.1 in Appendix C (pg. 63)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001921_le_2017_4_art_03.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001921_le_2017_4_art_03.pdf-Figure2-1.png", + "caption": "Fig. 2. Stent model with applied forces and stent fixation", + "texts": [ + " It is necessary to reduce the initial diameter of the implant in order to ensure proper implantation of the stent in the position of the artery narrowing. Furthermore, an insignificant diameter reduction protects from the possibility of removing from the catheter surface. The aim of the study is to evaluate the stent compression strength. It was adopted that the surgeon acts with a specific force on the external stent surface. At the time of surgery the doctor uses force 10\u00f715 N. Therefore, the stent model was loaded on both ends with the force of 10 N on four external walls. Figure 2 presents stent model with applied forces and stent fixation. For this stent model, stresses, strain and displacement area were determined. 1. Distribution of reduced stresses - Figure 3 For the coronary stent model made of PtCr alloy with applied forces, distribution of stresses was varied. The maximal value of reduced stresses was observed at the end of the external wall in the locations where the was stent fixation. The maximal value of stresses was 29.86 MPa, whereas minimal stresses were around 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004397_jeee.2013.010305.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004397_jeee.2013.010305.pdf-Figure2-1.png", + "caption": "Figure 2. TM0 slab mode launcher and electric field visualization", + "texts": [ + " Dielectric dissipation is usually the dominant loss mechanism due to the absence of field singularities in the slab guide. An advantageous field distribution leads to low current densities and therefore to low conductor losses in the ground plane. The latter are particularly low if a thin low-permittivity insulation film (\u03b5r \u2248 2) is introduced between the substrate and ground. Then, the tangential magnetic field intensity right above the ground plane is lowered and current densities are reduced. The TM0 slab mode is excited by a coplanar wave launcher. (Figure 2) Coplanar waveguide (CPW) was chosen as input line because it is compatible with MMICs and with the relative thick substrate necessary for sufficient field confinement. The substrate thickness d is in the order of one third of a wavelength in the dielectric medium or about 0.5 mm at 60 GHz for the exemplary used Duroid\u00ae6010LM laminate (\u03b5r = 10.2) from Rogers\u00ae Corp. Such a thickness is still good to handle in a manufacturing process. The launcher\u2019s large metallized back-short vias can simultaneously be used as RF or DC ground or for heat dissipation from active MMICs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002878_o_download-file_7242-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002878_o_download-file_7242-Figure2-1.png", + "caption": "Figure 2 - Linear Ergometer for Lower Limbs", + "texts": [ + " The linear ergometer for lower limbs was developed to generated the linear motions for passive and active exercises in humans that require the movement or exercise to recover or increase quality of life according to medical instructions, while the manual motions performed by a physiotherapist or health worker require a large amount of effort to provide the same benefits to the patient\u2019s condition. The linear ergometers allows the linear movement in milimetrically adjusted courses, between 500 and 2100 mm, with potency varying between 120, and up to 1178 N for pneumatic actuation, being composed of the following parts presented in Figure 2: \u2022 Linear Device (1) is a device composed by a tube with a circular or oblong cross section, where a Displacer (3) is draw in place by magnetism, being actuated by pneumatic energy. \u2022 The Linear Device (1) is attached to the Adjustable Beam (2) that can be adapted according to the user\u2019s needs, and it is where Fastening resides (2.1) \u2022 The Fastening (2.1) is composed by a set of parts that allow the Linear Device (1) to be fastened to the bed, floor, or walls, depending on the application. \u2022 Above the Displacer (3) the Fastener\u2019s Adapter (7) is mounted, which has the application of being mounted the Lower Limbs\u2019 Attachments (7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004977__067_ecp09430117.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004977__067_ecp09430117.pdf-Figure6-1.png", + "caption": "Figure 6: equivalent electrical network representation of a thermal system", + "texts": [ + " We have introduced two plane models with the ability to calculate the heat transfer between the connectors\u2019 positions in relation to the position of the connectors. The first option to calculate the thermal properties on the plane and between different points which will be represented by the connectors, we will use the concept of the radial heat conduction on a disc [15] fig.5. Although this method is simple to calculate and use, it would be applicable only if the surface could be supposed unlimited due to the dimensions of the r1 and r2. The other option is to use the equivalent electrical network [16] fig.6, which represent the system with the system with the thermal resistances and capacitors which can be simulated as an electrical network. To simplify the models in the first stage of modeling procedure we suppose the problem as a steady state situation so that we can neglect the C. This will simplify our plane thermal model to a model which has been divided by the smaller cubes which each will be represented by their thermal resistances. Fig. 7 These two thermal models can be used for modeling the plane model including its geometrical equations in DYMOLA" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001910_9312710_09348895.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001910_9312710_09348895.pdf-Figure1-1.png", + "caption": "FIGURE 1. The proposed LTCC antenna. (a) 3D view with an exaggerated view of the cavities, (b) Enlarged non-scaled view of the trapezoid-shape aperture, (c) Top view, (d) side view, and (e) fabricated antenna.", + "texts": [ + " In this paper, similar to [30], the gain of HMSIW LWA is improved by embedding cavities in the structure that is equivalent to tapering the thickness of the structure. The structure of this paper is as follows. The design procedure is discussed in section II. The structure of the antenna is presented in section III. The measured and simulated results are investigated in section IV. II. DESIGN PROCEDURE Assuming single-mode propagation of the fundamental HMSIWmode (TE0.5,0) in the proposed antenna as presented in Fig. 1, the effective width of the HMSIW (w) was calculated by [10], [11] w = c 4 \u221a \u03b5r fc (1) where w, fc, \u03b5r , and c are the transverse distance of via fence from the open side aperture (i.e., the effective width of HMSIW), cut-off frequency, dielectric constant, and velocity of light in free space, respectively. Assuming fc = 27 GHz and \u03b5r = 5.68, the corresponding w is 1.16 mm according to (1). The via fence acts as the waveguide sidewall and confines the fields when the ratio of via spacing (S) to via diameter (d) and the ratio of the d to w be smaller than 3 and 0", + " According to (3)-(7), embedding cavities changes h resulting in the variations of ky, kz, Ex , and Ey. The far-zone electromagnetic fields can be obtained by taking the fast Fourier transform (FFT) of the aperture fields using the well-known equations presented in [42]. As a result, introducing the cavities causes variations in the radiation pattern. The design and optimization process regarding the locations and the sizes of cavities will be investigated in the next section. III. STRUCTURE OF THE ANTENNA The schematic view of the proposed LWA and the fabricated LTCC LWA are demonstrated in Fig. 1. The length, width, and height of the antenna corresponding to 40 mm, 16 mm, and 1 mm, respectively. Some of the important geometrical parameters of the proposed antenna are reported in Table 1. The full-wave optimization was used in conjunction with the physical intuition to find the optimum dimensions. The feed size was optimized to minimize the return loss, while the location and size of the cavities were optimized to maximize the peak realized gain. In the proposed structure, Ferro A6M tape layers were used as the dielectric layers", + " However, it degraded the antenna performance in terms of SLL and gain due to the truncation of the ground plane. Due to this trade-off, the meshing topology was optimized to prevent performance degradation as much as possible while satisfying the design rules of the LTCC technology. To further increase the robustness of the structure, two 0.254 mm dummy layers were added underneath the main antenna. To reduce the SLL and frequency beamsquint, a section of the conducting cladding was tapered in a shape of a trapezoid with a width ofW0 and the longer side\u2019s length of 18mm, as shown in Fig. 1(b). The size of the cavities (Lc and Wc) and their locations (zc and xc) were optimized through full-wave simulations in conjunction with the physical insight to improve the peak realized gain. The peak realized gain diagrams for different cavities\u2019 dimensions and locations are reported in Fig. 2. Embedding cavities into the antenna is similar to loading it with different stubs. Changing the size and location of the cavities/stubs disturb the field distribution and propagation constant of the leaky-wave" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000292_download_70511_39859-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000292_download_70511_39859-Figure3-1.png", + "caption": "Figure 3. Infinitesimal element of the CB", + "texts": [ + " These loading conditions are presented in the global (x, y) coordinate-system, where the curved coordinate along the deflected axis of the beam is denoted by the arc length , as shown in Fig. 1. The concentrated end force P is decomposed into two components Fx and Fy. Considering the free body diagram of the right segment of the beam, where the length of this segment becomes (L-s), as shown in Fig. 2. Since the beam weight is assumed to be neglected, the horizontal and vertical static equilibrium equations lead that the components Fx and Fy are independent of the arc length . However, the internal bending moment is a function of the arc length , as shown in Fig. 3. In this figure, \u03b8 represents the angle of rotation of the beam with respect to the positive x-axis and ds denotes the length of infinitesimal element of the beam. Hence, the moment equilibrium equation of the beam can be written as dM dy dx F Fx yds ds ds = \u2212 \u2212 (1) where sin( ( )), cos( ( )) dy dx s s ds ds \u03b8 \u03b8= = (2) ( ) ( ) d s M s EI ds \u03b8 = (3) s s s Differentiating both sides of Eq. (3) with respect to the arc length and substituting the resultant relation into Eq. (1) lead to 2 ( ) sin( ( )) cos( ( ))2 d s EI F s F sx y ds \u03b8 \u03b8 \u03b8= \u2212 \u2212 (4) This differential equation governs the large deflection of the prismatic CB in terms of the slope of the beam ( )s\u03b8 and the arc length , as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.17-1.png", + "caption": "Figure 1.17. Twist beam semi-rigid rear axle [14].", + "texts": [ + " If one is curious how far designers have taken the independent suspension with respect to ground clearance and robustness, consider that the military Humvee features independent front suspensions front and rear, Figure 1.16. One way to provide some measure of independent rear wheel motion economically is to allow the axle itself to deform, thus requiring the further classification of an axle as rigid or semi-rigid. The primary realization of the semi-rigid axle is the twist beam, introduced in 1974 by Volkswagen. An example of the type is shown in Figure 1.17. This design allows the axle to swing relative to the vehicle body, while independent wheel motion is a result of torsional deformation of the axle itself. On the other hand, more expensive cars did begin to use independent rear suspensions (IRS) shortly after the mid-century mark. Multilink designs, such as Mercedes-Benz\u2019s five link IRS, seen in Figure 1.18, provide the designer with considerable choice over how to guide the wheel\u2019s vertical motion. Recently, even cheaper, compact cars have adopted the IRS" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004364_9312710_09358133.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004364_9312710_09358133.pdf-Figure1-1.png", + "caption": "FIGURE 1. The underwater positioning system.", + "texts": [ + " The node first infers its locations with the motion information, and then the location is corrected using the range estimation by EKF. In this paper, we also adopt an EKF to modify the proposed TDoA-based node localization method when the node to be located only receives two positioning messages or one positioning message from surface beacon(s) within an epoch. III. PROPOSED TDoA-BASED NODE LOCALIZATION METHODS In this section, we present three TDoA-based localization methods of underwater mobile nodes using multiple surface beacons. Fig. 1 shows the underwater positioning system consisting of three surface beacons and an underwater mobile node. Three surface beacons are deployed on the vertexes of a triangle grid, and the distance between two beacons is determined the communication distance of acoustic module installed on beacons. Each surface beacon obtains real-time position through received GPS information. All of the surface beacons maintain clock synchronization. The three surface beacons broadcast their positioning messages synchronously according to the scheduled timing. The underwater mobile node, 31714 VOLUME 9, 2021 such as the UG, localizes itself using received positioning messages and the corresponding arrival times. It is worth noting that Fig. 1 illustrates a minimum scale positioning system. The number of underwater mobile nodes within the common signal coverage area of three surface beacons is unrestricted. In the underwater positioning system, each grid consists of three surface beacons deployed on the vertexes of the triangle grid. If the number of surface beacons increases, we can construct a larger positioning system according to a certain topology. For example, if one more surface beacon is added to the positioning system, two triangle grids can be constructed, and the signal coverage is doubled" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure5.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure5.13-1.png", + "caption": "Figure 5.13: Radial Clearance Geometry", + "texts": [ + " These leakage channels are listed as follows: 1. Radial clearance leakage at the radial contact between the rotor and the cylinder 2. Leakage around the vane tip 3. Vane endface leakage (both endfaces) 4. Rotor endface leakage (both endfaces) Since the revolving vane mechanism shares a similar rotor and cylinder configuration to that of the rolling piston, the leakage through the radial clearance gap is modelled using the same method as that of a rolling piston proposed by Yanagisawa and Shimizu [112]. Figure 5.13 shows the clearance gap at the radial contact and Figure 5.14 shows the leakage path model used for the rolling piston [112], which is modelled as a Fanno flow. 70 According to Yanagisawa and Shimizu [112], the flow is first assumed to be choked at the channel exit. When the channel exit is choked, Equations (5.46)\u2013(5.52) apply to the flow describing the equivalent channel length, pressure and temperature ratios, and the leakage flow rate, respectively [112]. \ud706 \ud835\udc59\ud835\udc53 2\ud835\udeff\ud835\udc5f\ud835\udc4e\ud835\udc51 = 1 \u2212 \ud835\udc40\ud835\udc61 2 \ud705\ud835\udc40\ud835\udc61 2 + \ud705 + 1 2\ud705 ln \ud835\udc40\ud835\udc61 2(\ud705 + 1) 2 + \ud835\udc40\ud835\udc61 2(\ud705 \u2212 1) (5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001133_f_version_1569401418-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001133_f_version_1569401418-Figure1-1.png", + "caption": "Figure 1. The suspension frame and secondary system in the mid-low speed Maglev train.", + "texts": [ + " The solution of vehicle inverse kinematics is introduced in Section 3. In addition, the modeling of the track transition curve and the relationship of the vehicle/track posture is then introduced in Section 4. Section 5 presents the examples of motion based on the theory in the previous sections, which is followed by the conclusions in Section 6. The running mechanism of the Maglev train mainly includes a suspension frame, a secondary suspension system (secondary system), an auxiliary steering mechanism and so on, as shown in Figure 1. Therefore, its kinematics modeling can be divided into two levels: the kinematics of the suspension frame and secondary kinematics. In the kinematics of the suspension frame, the left and right modules of the suspension frame are constrained by the track, so the kinematics mainly analyzes the movement of the anti-rolling beams and hanger rods inside the same suspension frame. The suspension frame in the mid-low speed Maglev train is mainly analyzed in this paper, and the analysis of the secondary system is similar to it" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000218_r.asee.org_21409.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000218_r.asee.org_21409.pdf-Figure2-1.png", + "caption": "Figure 2. Rapid prototype medallion for winners of the inter-class race.", + "texts": [ + " The remainder of this paper is organized as follows: the Methods section will outline the structure of the project as well as the assessment tools used, the Results & Discussion section will cover the student submissions, as well as the results of the grading and surveying outlined in Methods. Next, the results will be summarized and some conclusions drawn and finally some plans for future research will be laid out. Methods Each class of 20-25 students was divided into groups of 3-6 students, depending on class size. Each team was allowed to choose its own name and meet on their own to discuss their strategy toward meeting the goal, which was to win the race at the end of the semester. The reward for winning the race was a small number of bonus points, a \u201cmedallion\u201d (see Figure 2) and bragging rights (the winning cars would be put on display in the trophy case in the department hallway). Winning the race was not required to receive a good grade on the project or in the class, which matches with the strategy put forth in Burguillo. 1 P age 25.652.3 Each student team was given the task of building a race car based on the Pinewood Derby cars made famous by the Boy Scouts of America. Using both in-class and personal time, each team member was required to design and model an individual piece of the car and the cars were required to be made of entirely SLA material (no lead weights could be added) but decals, paint and other \u201cflash\u201d were allowed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001223_d904908b0435a9d9.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001223_d904908b0435a9d9.pdf-Figure1-1.png", + "caption": "Fig. 1. The designed seed pelleting machine", + "texts": [ + " Therefore, the objective of this work is to determine the effect of pelleting process variables on: 1) the physical properties of pelleted seeds (size, shape, volume, sphericity, weight and density); 2) the mechanical properties of pelleted seeds (static coefficient of friction, natural angle of repose, maximum contact stress, cutting strength and pellet hardness), 3) the biological properties (germination and vigor percentages and germination rate) of pelleted seeds processed by pelleting machine, 4) Determining factors that had the most relation with seed quality. MATERIALS AND METHODS Seed material and pelleting machine: All pelleting runs were aimed sesame seeds (Shandweel 3) obtained from Oil Crop Research Inst., Agricultural Research Center. This work was accomplished by using an experimental model of seed pelleting machine which designed, manufactured, and operated through a co-operation between Agronomy Dept. and Agric. Eng. Dept., Fac. of Agric., Ain Shams Univ. Full description of the designed machine for seed pelleting (Fig. 1) was demonstrated in detail previously (Sahhar et al 2006). Investigation procedure: Variables of pelleting process which affect the quality of seed pelleting were investigated by conducting numerous simple experiments. The investigated variables included the rotational speed of the pelleting pan (15, 30, 45 and 60 rpm), the quantity of seeds added per run (100, 250 and 500 g) , the ratio of pelleting solid materials to seed (5, 10 and 20 times), the effect of levels of adhesive concentration (dissolved Arabic gum) (5, 10 and 20% weight/ volume), the quantity of adhesive solution added per pelleting solids (50, 125 and 150 mm3/ 500 g pelleting material) , and substituting varying quantities (0, 25, 50, 75 and 100%) of lime (Calcium carbonate) for Pentonite (Aluminum silicate) to determine which conditions of pelleting process were most susceptible to the hardness of pelleted seeds" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000980_.1007_BF02187878.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000980_.1007_BF02187878.pdf-Figure6-1.png", + "caption": "Fig. 6. Applicability of Rule 4.", + "texts": [ + " Without loss of generality assume r is green. Rule 4 is obviously applicable to r. Let v be the leftmost green vertex that can be reached by an x-monotone edge path as specified in Rule 4. We claim that the left-edges of v form a contiguous subsequence of the current cut and thus Rule 2 is applicable. Since v is leftmost the only way that left-edges of v might not lie in the current cut is for them to intersect e~ or ek (as in Rule 4). But this would contradict the leftmost condition for r (see Fig. 6). Thus all left-edges of v lie in the current cut. They have to be contiguous since otherwise Rule 1 would still be applicable, contrary to assumption. the following information: a double-linked list of the edges in the current cut; for each of these edges a pointer to the next and to the previous edge of the same color in the cut; a set of pairs of adjacent edges in the current cut for which Rule 1 is applicable; for each blue and each green vertex v a counter for how many of its left-edges are not in the current cut, a second counter tallying in the current cut all occurrences of adjacent edge pairs in which exactly one edge is a left-edge of v and a flag telling whether v has been declared safe; finally, a set of vertices for which Rules 2 and 3 are applicable; this set contains all vertices for which the flag is on (i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003710_f_version_1671673147-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003710_f_version_1671673147-Figure2-1.png", + "caption": "Figure 2. Illustration of the employed set-up. (a) Schematic depiction. Current measurement probes were integrated at positions 1 and 2 to measure the RTDL. A three-way valve behind the TCC\u2019s outlet could be used to convey either a circuit back into the feed vessel or a waste container. Operating and design parameters are shown in blue and orange, respectively. (b) Photograph of the TCC. The end plates were held in place by four steel rods. The motor was fixated on one end plate and connected to the rotor by a spring clutch.", + "texts": [ + " It features homogeneous and gentle mixing without local shear peaks, decoupled from the net flow [9,10]. Moreover, the RTDL is adjustable in a wide range by varying the operating and design parameters [11]. However, it should be mentioned that the local mixing intensity and, thus, particle suspension and the RTDL in a TCC cannot be adjusted independently [12]. Concerning these characteristics, the TCC shows remarkable similarities to the continuous oscillatory flow baffled crystallizer [13,14]. A TCC, as shown in Figure 2, consists of two concentric cylinders placed inside each other, of which the inner one rotates (rotor) while the outer one is commonly held sta\u2011 tionary (stator) for technical applications. By surpassing a critical rotation rate, a flow in\u2011 stability leads to a transition from pure azimuthal laminar Couette flow (LCF) to laminar Taylor vortex flow (LTVF) characterized by toroidal counter\u2011rotating Taylor vortices (see Figure 3 and the related Videos S1\u2013S4 in the Supplementary Materials) [10,15]. An essential characteristic of the vortex structure is low intervortex mass transfer across vortex boundaries accompanied by improved local mixing described by the intra\u2011 vortex mass transfer", + " The averaged median particle sizes of the three fractions are listed in Table 1, and exemplary cumulative size distributions are presented in Figure 1, showing that they were approximately equidistant. Moreover, it ca be seen fro the small standard deviations in T ble able 1. veraged edian dia eters of the investigated particle size fractions. Sieve fraction [\u00b5m] 100\u2013200 200\u2013315 315\u2013400 ian particle size \ud835\udc99\ud835\udfd3\ud835\udfce,\ud835\udfd1 [\u00b5m] 199.53 \u00b1 7.41 348.82 \u00b1 5.50 479.64 \u00b1 5.86 Figure 1. Exemplary cumulative PSDs of the employed L-alanine particle fractions after wet sieving. The experimental set-up, depicted in Figure 2a, consisted of a stirred feed vessel (\ud835\udc49 = 5 L) from which either solution or suspension was pumped to the TCC with a peristaltic pump (Ismatec Reglo Digital MS-2/8). The TCC was operated horizontally to prevent gravitational effects on the particles in the axial direction. The inlet and outlet of the TCC were placed tangentially to the stator (cf. Figure 2b), minimizing the inflow\u2019s effect on the vortex structure. To determine the effect of design parameters, differently sized stainless steel rotors and transparent glass and perspex stators, with a length of \ud835\udc3f = 594 mm, were employed. All dimensions investigated, characterized by the radius ratio \ud835\udf02 (Equation (2)), with \ud835\udc5f equaling the rotor radius and \ud835\udc5f the inner stator radius, can be found in Table 2. \ud835\udf02 = \ud835\udc5f\ud835\udc5f (2) Table 2. Employed geometries, defined by the radius ratio \ud835\udf02. The length of the apparatus was held constant at \ud835\udc3f = 594 mm. Stator Radius \ud835\udc93\ud835\udc90 (mm) Rotor Radius \ud835\udc93\ud835\udc8a (mm) 24.2 (Glass) 25 (Perspex) 26.8 (Glass) 13.5 0.56 / 0.50 18.8 0.78 0.75 0.70 i . \u2011 i i . The experimental set\u2011up, depicted in Figure 2a, consisted of a stirred feed vessel (V = 5 L) from which either solution or suspension was pumped to the TCC with a peri\u2011 staltic pump (Ismatec Reglo Digital MS\u20112/8). The TCC was operated horizontally to pre\u2011 vent gravitational effects on the particles in the axial direction. The inlet and outlet of the TCC were placed tangentially to the stator (cf. Figure 2b), minimizing the inflow\u2019s effect on the vortex structure. To determine the effect of design parameters, differently sized stainless steel rotors and transparent glass and perspex stators, with a length of L = 594mm,were employed. All dimensions investigated, characterized by the radius ratio \u03b7 (Equation (2)), with ri equaling the rotor radius and ro the inner stator radius, can be found in Table 2. \u03b7 = ri ro (2) able 2. l t i , fi \u03b7. l t constant at L = 594 mm. Rotor adius ri (m ) Stator Radius ro (mm) 24", + "84 The stator was sealed on both ends with an O-ring (EPDM rubber, hardness 70 Shore Videos were recorded (Canon, EOS M6, 15\u201345 mm lens) in ambient light in the TCC\u2019s center position, from the side, and the underside to evaluate the flow regime and the suspension behavior, respectively. For better contrast, black cardboard was placed behind the TCC. Following the set-up described by L\u00fchrmann et al. [31], self-constructed measuring electrodes consisting of two stainless steel wires with a diameter of 1 mm were used for RTDL measurement. They were installed in T-pieces made by the glassblowing workshop of TU Dortmund University and placed at positions 1 and 2 shown in Figure 2a just in front of the TCC\u2019s inlet and right behind its outlet. The current was measured by multimeters (Voltcraft, VC880) connected to the PC. The voltage supply with a sinusoidal peakto-peak voltage of 20 V and a frequency of 20 kHz was provided by function generators (Toellner, Herdecke, Germany, TCE 7404). Figure 2. Illustration of the employed set\u2011up. (a) Schematic depiction. Current measurement probes ere integrated at positions 1 and 2 tomeasure the RTDL. A three\u2011way valve behind the TCC\u2019s outlet could be used to convey eith r a circuit back nto the feed v ssel or a waste cont iner. Operating and design parameters are shown in blue and orange, respectively. (b) Photograph of the TCC. The end plates were held in place by four steel rods. The motor was fixated on one end plate an connecte to the rotor by a spring clutch", + " \u2011 i , i r ), a t e r t r s s rt si sealedwith a shaft sealing ring (Paulstra Hutchinson, NBR). The rotation rate was set with a stepper motor (TRINAMIC, QSH5718\u201176\u201128\u2011189) via LabVIEW. \u2019 i i , f t si , t e n ersi e to eval ate the flo regi e and the sus\u2011 For better contrast, black cardboar s l i . ll i t t\u2011 i t l. [ ], self\u2011c str ct e s ri l tr s sisti f t st i l ss st l ir s it i t r f r s f r easure ent. They were installed in T\u2011pieces a e by t e lass l i r s of ort undUniversity and placed at positions 1 and 2 shown in Figure 2a just in front of the TCC\u2019s inlet and right behind its outlet. The current was measured by multi eters (Voltcraft, VC880) connected to the PC. The voltage supply with a sinusoidal peak\u2011to\u2011peak voltage of 20 V and a frequency of 20 kHz was provided by function generators (Toellner, Herdecke, Germany, TCE 7404). 2.3.1. Flow Regime Transitions and Particle Suspension The flow transitions and the suspension behavior were investigated using a closed loop to keep the amount of solid necessary to a minimum", + " N = L d (14) For each of the vortex cells, a mass balance is set up in the form of an ordinary differ\u2011 ential equation, which describes the mass transfer of the tracer between the vortices via a mass transfer coefficient \u03b2V . Separate consideration of the bypass flow is omitted in this model, such that it is lumped in both v\u2217D and \u03b2V [21]. The tracer concentration in the entire apparatus is set to zero as the initial condition. Deviating from Richter et al. [21], the normalized amperage measurement signal at posi\u2011 tion 1 (Figure 2a) is set equal to the concentration of the first vortex as a boundary condi\u2011 tion for the entire duration of the measurement. Thus, the model can consider the effect of non\u2011idealities in impulse addition on the outlet signal. The model now simulates the downstream movement of the vortices by having all vortex cells move one position fur\u2011 ther. Accordingly, the last vortex leaves the apparatus and forms the exit concentration. The time between two movements \u2206t corresponds to the ratio of the gap width d and the vortex displacement velocity uD", + " Here, the laminar flow transitioned directly into the turbulent flow. This absence of the WTVF was described by Coles [15] for radius ratios smaller than around \ud835\udf02 = 0.714. Nevertheless, in our investigations, WTVF also occurred for the radius ratio \ud835\udf02 = 0.7. This could have been due to the slight difference between the values and manufacturing tolerances of the glass stator used, which was also observed by Nemri et al. [45] for \ud835\udf02 = 0.687. Increasing rotational Reynolds numbers within the WTVF showed an increasing occurrence of local turbulence (cf. Figure 2a). While further subdivisions of this regime into complementary subcategories can be found in the literature (e.g., [47,48]), the entire Figure 3. Photographs of the flow visualization experiments for wsolid,Mica = 0.05 wt.%, \u03b7 = 0.7, . V = 92 mL\u00b7min\u22121 and Reax = 15.67. (a) Adjustment of the flow regime after a change in rotation rate from n = 25 rpm to n = 80 rpm. Existing wavy vortices retained their pattern and were displaced by newly forming turbulent wavy vortices. (b) Observed flow regimes; LCF is not shown", + " Here, the laminar flow transitioned directly into the turbulent flow. This absence of the WTVF was described by Coles [15] for radius ratios smaller than around \ud835\udf02 = 0.714. Nevertheless, in our investiga- tions, WTVF also occurred for the radius ratio \ud835\udf02 = 0.7. This could have been due to the slight difference between the values and manufacturing tolera ces of the glass stator used, which w s also observed by Nemri et al. [45] for \ud835\udf02 = 0.687. Increasing rotational Reynolds numbers within the WTVF showed an increasing occurrence of loca turbulence (cf. Figure 2a). While fu ther subdivisions of this regime into complem ntary subca egories can be f und in the lit rature (e.g., [47,48]), the ntire Figure 4. Rotational Reynolds nu bers of the flo regi e transitions for the different geo etries. The axial Reynolds number was set constant at Reax = 15.67, resulting in the volume flow rates . V = 99.5, 92, and 82 mL\u00b7min\u22121 for the ratios \u03b7 = 0.84, 0.7, and 0.5, respectively. Increasing rotational Reynolds numbers within the WTVF showed an increasing c\u2011 currence of local turbulence (cf. Figure 2a). While further subdivisions of this regime into complementary subcategories can be found in the literature (e.g., [47,48]), the entire ro\u2011 tational Reynolds number range in wh ch wavy flows occur is referred to h re as WTVF for simplicity. It can be een that theWTVF regionwasm e pronounced for the radius ratio \u03b7 = 0.84, and the TTVF started atmuch higher rotational Reynolds numbers than for the radius ratio \u03b7 = 0.7. Accordingly, the operatin window for achieving minimum disper ion became larger f r large radius ra ios" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003481__097_ecp14096097.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003481__097_ecp14096097.pdf-Figure6-1.png", + "caption": "Figure 6: Contact point detection of the circle-tocylinder contact model", + "texts": [ + " The latter results from the assumption of a thin contact layer. This evaluation is performed in LCS1. On the other hand, the interval | | between and in the longitudinal direction of the cylinder has to be less than or equal to . This is evaluated in BCS1. If both conditions are fulfilled at the same time, the two bodies intrude and the contact force is applied to the contact points (c.f. Section 3.3). ( | \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1| ) (| \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1\u20d1 \u20d1| | | ) (1) The second example is the collision between a cylinder and a circular plane (see Figure 6), which denotes a linear shape of the contact area. As regards the circular plane, the geometry is sufficiently described by the radius . Again, body-fixed coordinate systems (BCS1 and BCS2) are defined in the centroids of the cylinder and of the plane. The -direction of BCS2 represents the vertical direction of the plane and the normal direction for force calculation. According to Figure 2 the contact area has a linear shape. Thus, two potential contact points have to be determined on the surface of the cylinder" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000065_m.C.2010.4.62-67.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000065_m.C.2010.4.62-67.pdf-Figure3-1.png", + "caption": "Fig. 3 Cross-sections of the analyzed critical parts", + "texts": [ + " From these elements, the critical parts from the fatigue life damage accumulation point of view were chosen. Normal stresses in marginal profile points of elements No. 21, 79 and 250 obtained extreme values as ensued from the graphical representation of performed stress analysis results and from the next performed analyses output files [9]. Particular examined elements can be shortly characterized as follows: element 21 \u2013 part of the vehicle bearing spinal frame, specifi- cally the back bearing tube, construction material \u2013 steel STN 41 1523, shape according to Fig. 3a, element 79 \u2013 part of the formed thick-walled bridge tube of the right central half-axle, construction material \u2013 steel STN 41 1523, tube shape according to Fig. 3b, element 250 \u2013 the longitudinal truss part of the subsidiary bearing frame, approximately in the middle between both back axles, \u201cU\u201d shape 250 100 7, construction material \u2013 steel STN 41 1523, element shape according to Fig. 3c. The process of kinematics excitation was considered a cooperation of two basic operating factors: road surface quality (5 road surface quality classifications and difficult terrain specifications), vehicle velocity (4 reference velocities for each road surface quality). As the excitation generator were applied behaviors of the section\u2019s longitudinal height unevenness for different road and terrain surfaces. The method of their acquiring is particularly described for an example in [1, 7]. The experimental obtaining of the height unevenness behavior is time and financially demanding" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.29-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.29-1.png", + "caption": "Figure 2.29 : Electric motor internal Heat Pipes: (a) Electric Motor with Heat Pipes [104]", + "texts": [ + " In 2009, research on Heat Pipes has led to initiate and incite investigations of these cooling devices and their installation inside the motor. The aim is to cool directly the machine's internal part with a more efficient and more compact system. Through the patent [104] with publication number US 7569955 B2 entitled: \u201cElectric Motor with Heat Pipes\u201d, the authors were based on using straight heat pipes and placing the evaporator part in the stator laminated core, and the condenser in a cooling chamber containing a coolant circulating using a pump (Figure 2.29a). In this conception, there are many difficulties to mention. First, the risk of leakage of heat pipes inside the motor, second the possible maintenance that is difficult to perform, and finally the power supply required to circulate the coolant. Later on, the invention of [105] has been granted a patent in this field with publication number US 8368265 B2, entitled: \u201cElectric Motor Having Heat Pipes\u201d also using straight heat pipes. The heat pipes are placed around the motor shaft while the condenser is on the impeller", + " The work of [106] has been granted a patent for the invention entitled: \u201cCooling of an Electric Motor via Heat Pipes\u201d, patent with publication number US 9561716 B2 in which straight heat pipes were used. The evaporator section was installed in the motor housing and the condenser in the cooling tank. Also, [107] considered another model for electric motor cooling with heat pipes under patent number US 9331552 B2 entitled: \u201cRotor Assembly with Heat Pipe Cooling System\u201d. It was based on putting the evaporator in the shaft and the condenser equipped with cooling fins outside the motor (Figure 2.29b). Here also, the drawback is that any leak in heat pipes may cause damage to the motor construction since they are put inside the shaft and a special design is required. (b) Rotor Assembly with Heat Pipe Cooling System [105]. 2.4 Conclusion A review of the existing methods for e-motor thermal management was presented based on the literature. In this review, the basics of heat transfer phenomena in electric machines are assessed and the existing cooling solutions are presented with corresponding descriptions and information" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000754_40396_type_printable-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000754_40396_type_printable-Figure1-1.png", + "caption": "Fig 1. Schematic diagram of fluid end of a reciprocating pump.", + "texts": [ + " And all authors declared that there are no competing interests with commercial company. plunger pump through the optimized design of the spring stiffness and valve quality parameters. The working principle of a plunger pump fluid end depends on a changing medium volume of sealed pump chambers achieved by the reciprocating movement of the plunger, thus realizing the suction and discharge operation of the pump valve. The valve itself consists primarily of spring, valve body, rubber sealing gasket and valve seat, as shown in Fig 1. This analysis primarily investigates the discharge valve motion of the plunger pump. 2.1 Mathematical model of valve motion The structural diagram of the reciprocating pump discharge valve is depicted in Fig 2. According to fluid mechanics and the structure of the valve [17, 18], the continuous flow of valve clearance is given as follows: Qc \u00bc a0Acuc \u00f01\u00de where Qc is the instantaneous flow of valve clearance; a0 is the contraction coefficient of the doi:10.1371/journal.pone.0140396.g001 PLOSONE | DOI:10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002886_nal_Thesis_Suren.pdf-Figure5.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002886_nal_Thesis_Suren.pdf-Figure5.5-1.png", + "caption": "Figure 5.5: Strain concentration at the edge of the decohesed interface after degradation of the cohesive behavior (\u03b5yy = 0.368 %) (deformation scale = 1).", + "texts": [ + " However, the presence of graphite particles and normal contact behavior showed partial separation of the graphite particles. In the RVE model with the cohesive interface, the graphite particles were slightly strained at the region of the compressive, which showed similarity to the experimental observation. The strain distribution in the ferrite matrix were similar, only difference was that the bound interface slightly reduced the strain concentration around smaller graphite nodules, so the high strain band connecting larger graphite nodules became only preferable fracture region. Figure 5.5 presents zoomed view of the the strain concentration around the larger graphite nodules. For the larger graphite particle, the maximum strain point corresponds to the point of ferrite compression and its direction affected by the larger graphite nodules around. The matrix between two larger graphite nodules seemed to be highly strained due to thinner matrix in-between. Such high strain concentrations were observed on either side of the graphite nodules, forming continuous link of high strain band connecting larger graphite particles, which is Nanyang Technological University Singapore Page : 168 Ch" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-Figure1-1.png", + "caption": "Fig. 1: A 3D printed finger developed at the University of Twente, consisting solely out flexure hinges", + "texts": [ + " Furthermore, a comparison is made of the sideways support stiffness over the whole range of motion for the different topologies. Third, an overload-protection mechanism for the sideways force is presented. A FEM analysis is used to obtain the stiffness of the hinge, which is subsequently corroborated with measurements. II. DESIGN METHODOLOGY A. Optimization loadcase A finger is designed to be in a rest position that allows 15\u25e6 of passive extension (ROMpas) and \u221230\u25e6 of active flexion (ROMact). See Fig. 1. This range of motion allows one to grasp objects in the medium wrap range. Since the fingers have high compliance for rotations around the z-axis (Fig. 1), the passive extension is achieved by contact with an object. The contact will open the hand to allow larger objects to be grasped. The extension is actuated by a tendon force Fact which deflects the flexure up to \u221230\u25e6 around the z-axis. The metacarpophalangeal joint (MCP) has been identified as the critical joint [3]. When holding an object, the contact force and weight of the object result in a combination of in- and out-of-plane bending loads of the flexure elements. See Fig. 2. Since it is of interest to study the functionality of hands while power grasping, a contact point common to all hinge topologies is defined (Fig", + " It took until the sixteenth century for the first hinged prosthetic hand to be introduced by Amoroise Par. In the 20th century prosthetic limbs started to become more advanced. Especially with the improvements in 3D printing technologies, the future in prosthetics seems very bright. [1] The chair of Precision Engineering (PE) at the University of Twente (UT) is very innovative with many new developments in this field. The main goal of their research is to design prosthetic fingers with solely flexure hinges (see figure 1). A flexure hinge moves within the elastic limits of a material and does not consist of multiple different parts like conventional hinges. Reasons to design by using flexure hinges are: excellent repeatable motion (no friction, no backlash, low hysteresis), no maintenance and assembly needed due to their monolithic nature, and a strong reduction in the number of parts, mass and cost. This paper will be supporting the developments in the design of prosthetic fingers, by enabling validation and testing of new concepts from the UT", + " This method allows for evaluation of support stiffness at larger deflections, however, it described the compliance matrix only for the 2-dimensional case. For typical loading-conditions, out-of-plane stiffness and load carrying capacity are important also. Furthermore, it only allows for the evaluation of non-planar hinge designs. In this paper, we exploit a flexible multibody method to calculate and optimize several flexure hinge topologies, including non-planar topologies, during a cylindrical medium D.2 Publication Page 66 Fact Tendon Flexure Phalange ROMact x y ROMpas Fig. 1. Passive and active range of motion. power wrap (Fig. 2). This power grasp is identified as one of the most common used grasps [11], [12] and therefore the main focus of this research. First, we developed an optimization strategy to minimize stresses and maximize grasping force for each topology in deflected state. Secondly, several joints are presented and the optimized topologies are compared. The comparison is based on stresses due to grasping force and sideways loads. Furthermore, a comparison of the support stiffnesses over the whole range of motion for the different topologies is done. Third, an overload protection mechanism for the sideways force is presented. An FEM analysis is used to obtain the stiffness of the entire finger, which is subsequently corroborated with measurements. II. DESIGN METHODOLOGY A. Optimization loadcase A finger is designed to be in a rest position that allows 15\u25e6 of passive extension (ROMpas) and \u221230\u25e6 of active flexion (ROMact), Fig. 1. This range of motion allows to grasp objects in the medium wrap range. Since the fingers have high compliance for rotations around the z-axis, the passive extension is achieved by contact with an object. The contact will open the hand to allow bigger objects to be grasped. The extension is actuated by a tendon force Fact which deflects the flexure up to \u221230\u25e6 around the z-axis. The MCP has been identified as the critical joint [3]. When holding an object the contact force and weight of an object result in a combination of in- and out-of-plane bending loads of the flexure elements, Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000961_0.1515_fas-2014-0011-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000961_0.1515_fas-2014-0011-Figure1-1.png", + "caption": "Fig. 1. PZL M28 wing area of rib 15:", + "texts": [ + " In case of the stress level change in the tested area, the fatigue life must be recalculated. Below two cracks in wing structure are presented in detail. The first significant event in the test was a crack in the wing, in the area where wing strut loads are introduced at the rib 15. The crack was caused by the fatigue damage of the wing in the area of the local stress concentration (holes for bolts in the wing strut fitting mounting). The test was terminated before the damage of the tested wing could spread \u2013 see Fig. 1. The subsequent analysis showed that it was possible to repair the critical wing area on the airplane in operation, and in this way significantly extend the airplane\u2019s service life. A careful stress analysis was performed for the PZL M28\u2019s outer wing, in which the most interesting area was the rib 15, where the wing strut loads were introduced. A detailed FEM model covers the wing area from rib 10 (the root rib of the outer wing, with four fittings of the junction with the centerwing) to the rib 19 \u2013 see Fig. 1(c) and Fig. 2. a) b) (a) Sketch of the area of rib 15 with a crack indicated (b) Cracked wing skin after removal of a wing strut fitting (c) The FEM model of the wing, general view The wing area aft of the rib 19 was modeled as a beam. Design changes implemented in the structural beam lying between the front and rear wingspans considerably increased the service life of the wing. These changes can be introduced to the wing taken from the airplane in operation during the repair process. The fatigue test was continued after the repair of the wing critical area, with separate design solutions implemented in the LH outer wing and the RH outer wing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000324_cle_download_348_244-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000324_cle_download_348_244-Figure10-1.png", + "caption": "Fig. 10. VGMF control mechanism for the flaps (Photo: P. Lauk)", + "texts": [ + " With flaps deflected at +15 degrees, the VGMF at the angle of attack of 0 degrees augmented the lift coefficient by 0.669. VG miniflaps are embedded inside the flaps. To let the VGMF to be extended, the lower aft side was covered with a flexible precurved mylar seal. Like Fowler flaps, the VGMF, when extended, enlarge the wing surface area by 6.5%, and can be deflected by 16.7 degrees (Figs 7, 8). To minimize weight, the CFRP panels were sandwiched using a 1.5 mm balsa sheet. The miniflaps were designed at the Department of Aircraft Engineering of the Estonian Aviation Academy (Fig. 10). Most of the miniflap control elements were milled from aluminum alloy 7075. Several smaller elements were made from stainless steel 316R by using metal 3D sintering in the Powder Metal Laboratory at Tallinn University of Technology (Fig. 11). The linkage inside the wing is actuated using the 8x1 CFRP tube close to the flap edge (Figs 12 and 13). The lower aft side of the flaps is coated with elastic precurved mylar sealing (Fig. 14). With the wings rigging, the controls of the miniflaps automatically joined the fuselage controls" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure15-1.png", + "caption": "Figure 15. The maximum stress simulation results for the two driver body support rods are 4.63 MPa.", + "texts": [ + "32 MPa, and 0.0007 mm, respectively. Figure 14 shows the simulation results of the maximum stress values at the control panel and battery mounts. 3. Driver body mount The driver's body mount receives a weight force of 466.956 N, which acts in the y-axis direction. This part consists of two rods that support the driver's body. The simulation results for the total of the two driver rods were bending moment, maximum stress, and displacement, respectively, with values of 21683.48 N.mm, 4.63 MPa, and 0.010 mm. Figure 15 shows the maximum stress value simulation results at the driver's body mount. 4. Driver's footrest The driver's footrest receives a load of 8.4 kg acting in the y-axis direction. This part only consists of one rod to support the driver's feet. The simulation results obtained in bending moment, maximum stress, and displacement, respectively, have 893.86 N.mm, 0.19 MPa, and 0.00008 mm values. Figure 16 shows the simulation results of the maximum stress value on the driver's footrest. 5. Front body mount The front body mount receives a load of 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000044__2015jamdsm0037__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000044__2015jamdsm0037__pdf-Figure1-1.png", + "caption": "Fig. 1. Double wishbone suspension system", + "texts": [ + " Key words : Suspension systems, Double wishbone, RSSR-SS mechanism, Suspension linkage, Suspension kinematics \u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2015jamdsm0037] unequal length of arms. A double wishbone suspension is basically a spatial four-mechanism (Russell, et al., 2009). Each wishbone is connected by two revolute joints to the chassis and by one spherical jo int to the knuckle. Shock absorber and coil spring mount to the wishbones to control vertical movement. In the case of front axle, steering knuckle is connected to chassis by means of tie-rod using spherical jo ints as seen in Fig. 1. Rear suspensions may contain a similar link, called control linkage. Thus, due to this configuration, the whole three-dimensional kinemat ic chain is named RSSR\u2013SSP (R: revolute, S: spherical, P: pris matic). Large number of design parameters necessary to define a double-wishbone suspension system makes it easy to approach the kinemat ic characteristic accurately, but at the same time, it is more d ifficu lt to synthesize due to the large number o f parameters involved in the three -d imensional problem" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003971__2462_context_theses-Figure6-3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003971__2462_context_theses-Figure6-3-1.png", + "caption": "Figure 6-3: Gears of 1st stage", + "texts": [ + " The simulation hardware is for that reason very close to an applied Figure 6-1: Nordex wind turbine (Reference [1]) industrial application and reflects applications in reality. Figure 6-2 shows the gearbox of the Nordex N90/2300 in the nacelle of the wind turbine. Figure 6-2: Inside nacelle of the Nordex wind turbine (Reference [1]) 6.1.2 The Gearbox The used gearbox has following parameters as seen in Table 6-1: The three stage gearbox has 2 planetary gear stages and one spur gear stage. Table 6-2 shows the parameters that have been used for the gear design. 65 Figure 6-3 shows the first stage of the wind turbine gear box. 6.1.3 Input Force Figure 6-4 shows the input values of a Nordex N90/2300 wind turbine which is used in the MBD Simulation. Please see chapter 2.3 on page 14 to find the derivation of this graph. 6.1.4 Relative speeds Relative speeds based on equations of chapter 4.10 on page 38. These values occur with maximum torque at the rotor at wind speeds of 14-25 m/s. 66 6.1.5 The Generator The blue curves in Figure 6-5 shows the power in dependency of the rotor speed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure19-1.png", + "caption": "Figure 19. Predicted fiber orientation.", + "texts": [ + " The temperature of melted polymer changes not only with time and location but also with thickness during the entire injection molding cycle. Figure 18 shows the air traps and weld lines that are likely to occur during the injection molding process. Air traps can be reduced by appropriate venting in the molds, which can be then be used to design vents required to minimize the air traps. The weld lines distribution displays the angle of convergence as the two flow fronts meet. However, the presence of weld lines may indicate a structural weakness and/or a surface blemish. The fiber orientation at skin shown in Figure 19 provides a good indication of how molecules will be oriented on the outside of the part, thereby demonstrating the average principal alignment direction for the whole local area at the end of the filling. Since the melt freezes very quickly upon contact with the mold for the first time, the velocity vector provides the most probable molecular orientation at the skin. Figure 20 shows the orientation of fibers during the injection molding process, averaged over the thickness. To analyze this, the layer-based fiber orientation tensor was calculated at each time-step throughout the duration of the analysis" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004255_cle_download_175_155-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004255_cle_download_175_155-Figure2-1.png", + "caption": "Figure 2 Aircraft flight stress map", + "texts": [ + "87\u00b0, and NACA0012 was used for the vertical tail and flat tail airfoil. The specific design parameters are shown in Table 1. For the convenience of research, the influence of aircraft propeller slipflow is ignored, and the propeller and its accessories are omitted. According to the structure and design parameters of the aircraft, reverse engineering is used to obtain the appearance of the aircraft in SolidWorks, as shown in Figure 1. The aircraft is regarded as a rigid body, and its forces during flight are shown in Figure 2, which mainly include the gravity of the aircraft itself G, the thrust of the engine T, the lift force perpendicular to the velocity direction L, the drag force parallel to the velocity direction D, the side force perpendicular to the flight plane of the aircraft C, and the forces of the landing gear and the ground during take-off and landing. Lift force L, drag force D and side force C are collectively referred to as aerodynamics of the aircraft[8]. The core of aerodynamic analysis of aircraft is to solve the aerodynamic coefficient of aircraft" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001821_f_version_1591065925-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001821_f_version_1591065925-Figure1-1.png", + "caption": "Figure 1. Components of a CVJ.", + "texts": [ + " The present work is intended to close this gap and to provide a tool that complements the design process of CVJ with straight tracks and allows first numerical analyses to be performed focused on a most efficient variant, which is why an analytical contact determination is chosen. Only free bodies are considered, so that the positions of the individual joint bodies result exclusively from the forces acting in the joint. This also allows the use of an ODE solver, which means less numerical effort compared to a DAE solvers. Figure 1 illustrates the basic design of a constant velocity ball joint of this type. The inner race and the outer race are each connected to a rotating shaft and have several tracks, so that a positive transmission of the torque takes place in the joint between the name-giving balls and the tracks. Further, for numerical analysis using multi-body simulation, it is necessary to define fixed coordinate systems for all joint components in addition to the inertial system Ie, which are also shown in Figure 1. For the undeflected state of the joint, all ball centres in the system plane are located on the pitch circle diameter (PCD) of the joint. As the joint rotates, the balls are positioned over the ball cage in the bisecting plane to ensure uniform rotary transmission [12]. For this purpose, it has recesses called cage windows. In addition, the joint is filled with grease to achieve a better tribological behaviour and to reduce wear. Depending on the intended use of the joint, the designs of the track geometries differ", + " After the contact forces for each body have been determined and entered into the vector of the right hand side, the solution of the differential equation can be done by the procedure described above and the state vector can be calculated for the following time step. To analyse the joint kinematics using multi-body simulation, it is first necessary to define suitable coordinate systems. Therefore, a Cartesian inertial system is introduced, whose global z-axis corresponds to the rotational axis of the outer race. In addition, body-fixed coordinate systems are defined on the inner race IRe, the outer race ORe and the cage CAe, whose origins lie in the joint system plane (see Figure 1). Starting from the body-fixed coordinate systems, several coordinate systems are introduced for each track and for each cage window. While the alignment of the coordinate systems in the cage window corresponds to the cage fixed coordinate system, the track coordinate systems tre follow the track orientation with the two track angles \u03b1incl and \u03b2incl . The transformation into the track coordinate system is performed sequentially using the matrix QtrI = 1 0 0 0 cos(\u03b1incl) \u2212sin(\u03b1incl) 0 sin(\u03b1incl) cos(\u03b1incl) \u00b7 cos(\u03b2incl) 0 sin(\u03b2incl) 0 1 0 \u2212sin(\u03b2incl) 0 cos(\u03b2incl) ", + " It can also be seen that the inner race (red line) performs a four times oscillating movement around the zero position during one revolution. When transforming the time signal of the axial movement of the inner race via FFT [28] into the frequency domain, the significant frequencies become obvious. The resulting frequency spectrum is shown in Figure 14b. For the rotational speed of 300 rpm, the first order is 5 Hz. As was already evident from the previous time observation of the inner race movement, the fourth order appears to be the most significant frequency of the movement process. This is due to the geometry of the joint (see Figure 1), which has a 90\u25e6 symmetry due to the alternate track arrangement and the number of balls, so that the joint has an identical starting position after a quarter turn. Further peaks (12th order, 20th order, 28th order, etc.; see Figure 14b) occur starting from the fourth order in addition to an integer multiple of the number of balls (eight). The characteristic frequencies of the axial excitation of the inner race thus depend exclusively on the existing CVJ geometry in form of the track arrangement and the number of balls used" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002288_844f2825d7b64f46.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002288_844f2825d7b64f46.pdf-Figure1-1.png", + "caption": "Fig. 1. Side veiw of thresher.", + "texts": [ + " This was done by replacing the normal concave with a new one with opening of 7\u00d77cm per opening (square shape) The experiments were carried out at Mamdoh Farm, El Delengat district, Behera Governorate during the agriculture season 2020. The developed thresher was locally fabricated at private workshop in wehada Village, El Delengat district, Behera Governorate. The main idea is to develop a local thresher machine to separate the peanut crop pods. The local thresher machine, model tangential axial\u2013flow consists of a group of parts as shown in Fig. 1. The component dimensions, drum diameter of 70 cm, drum length of 115 cm, fixed knives on 4 rows, knives total number of 44 (30 cm. long, 5cm width, and 0.7 cm thickens), and concave (118cm length, 80 cm width and 0.3cm thickens), the front sieve (115 cm length and 40cm width) drum speed ranged from 300 to 450 rpm, and the power was transmitted to thresher machine by belt pulley from 65 hp tractor Developed a local thresher machine to separate the peanut crop; peanut crop mass movement, the pods are separated from peanut plant in the threshing chamber" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003167_ostyka2018_01003.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003167_ostyka2018_01003.pdf-Figure3-1.png", + "caption": "Fig. 3. View of the calculated grid in the longitudinal and transverse planes.", + "texts": [ + "\ud835\udf14 = \u222e[\ud835\udc5f\ud835\udc5f \u2219 (\ud835\udc5d\ud835\udc5d\ud835\udc27\ud835\udc27 + \ud835\udc46\ud835\udc46\ud835\udc27\ud835\udc27)] \ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51 + \ud835\udc40\ud835\udc40, where S \u2013 the stress tensor on the surface of a solid body; n \u2013 surface normal; J \u2013 moment of inertia tensor; \u2013 angular velocity of rotation of the body; M - external torque. As the physical parameters of the working fluid in the simulation were taken: density \u03c1 = 840 \u043a\u0433/\u043c3; molecular viscosity \u03bc = 0.0071 \u043a\u0433/(\u043c\u0441); the flow of the working fluid \u2013 0.1 kg/s; working fluid temperature in the working area \u2013 no more than 120 \u0421; pressure at the inlet of the retarder \u2013 5.5 MPa. The algorithm of finite element analysis was used to solve the given equations [6]. The simulation used a uniform finite element design grid in the plane passing through the wheel rotation axis (figure 3a) and a uniform one in the perpendicular plane (figure 3b). c) Fig. 2. Geometric parameters of the brakes: a) basic version; b) with circular blade system; c) with inclined blades. Simulation of oil flow in the flow part of the brake-retarder is performed within the model of turbulent fluid flow [5]. The equations describing the change in velocity, pressure, turbulent energy, and dissipation have the form: - Navier-Stokes equation \ud835\udf15\ud835\udf15\ud835\udc7d\ud835\udc7d \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udc7d\ud835\udc7d\u2a02 \ud835\udc7d\ud835\udc7d) = \u2212 \u2207\ud835\udc5d\ud835\udc5d \ud835\udf0c\ud835\udf0c + 1 \ud835\udf0c\ud835\udf0c \u2219 \u2207(\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61) \u2219 (\u2207\ud835\udc7d\ud835\udc7d + (\u2207\ud835\udc7d\ud835\udc7d)\ud835\udc47\ud835\udc47) + \ud835\udc54\ud835\udc54, - continuity equation \u2207(\ud835\udc7d\ud835\udc7d) = 0, - equations for turbulent energy and dissipation rate \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 = \ud835\udc50\ud835\udc50\ud835\udf07\ud835\udf07 \u2219 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udc58\ud835\udc582 \ud835\udf00\ud835\udf00 , \ud835\udf15\ud835\udf15(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc58\ud835\udc58) \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc7d\ud835\udc7d \u2219 \ud835\udc58\ud835\udc58) = \u2207 ((\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \ud835\udf0e\ud835\udf0e\ud835\udc58\ud835\udc58 ) \u2219 \u2207\ud835\udc58\ud835\udc58) + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \u2219 \ud835\udc3a\ud835\udc3a \u2212 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf00, \ud835\udf15\ud835\udf15(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf00) \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc7d\ud835\udc7d \u2219 \ud835\udf00\ud835\udf00) = \u2207 ((\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \ud835\udf0e\ud835\udf0e\ud835\udf00\ud835\udf00 ) \u2219 \u2207\ud835\udf00\ud835\udf00) + \ud835\udc50\ud835\udc501 \u2219 \ud835\udf00\ud835\udf00 \ud835\udc58\ud835\udc58 \u2219 \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \u2219 \ud835\udc3a\ud835\udc3a \u2212 \ud835\udc50\ud835\udc502 \u2219 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf002 \ud835\udc58\ud835\udc58 , where V \u2013 the velocity vector; t \u2013 time; p \u2013 pressure; \u03c1 \u2013 the fluid density; \u03bc \u2013 the molecular dynamic viscosity; \u00b5t \u2013 the turbulent dynamic viscosity; g \u2013 the vector of gravitational acceleration; k \u2013 turbulent energy; \u03b5 \u2013 the rate of dissipation of turbulent energy", + "\ud835\udf14 = \u222e[\ud835\udc5f\ud835\udc5f \u2219 (\ud835\udc5d\ud835\udc5d\ud835\udc27\ud835\udc27 + \ud835\udc46\ud835\udc46\ud835\udc27\ud835\udc27)] \ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51 + \ud835\udc40\ud835\udc40, where S \u2013 the stress tensor on the surface of a solid body; n \u2013 surface normal; J \u2013 moment of inertia tensor; \u2013 angular velocity of rotation of the body; M - external torque. As the physical parameters of the working fluid in the simulation were taken: density \u03c1 = 840 \u043a\u0433/\u043c3; molecular viscosity \u03bc = 0.0071 \u043a\u0433/(\u043c\u0441); the flow of the working fluid \u2013 0.1 kg/s; working fluid temperature in the working area \u2013 no more than 120 \u0421; pressure at the inlet of the retarder \u2013 5.5 MPa. The algorithm of finite element analysis was used to solve the given equations [6]. The simulation used a uniform finite element design grid in the plane passing through the wheel rotation axis (figure 3a) and a uniform one in the perpendicular plane (figure 3b). Table 1 presents the results of the calculation of the braking performance of the retarder with straight radial blades. Figure 4 shows the visualization of velocity fields in a plane passing through the axis of rotation of the wheels when nrot=1500 rpm. As can be seen from the figure for the working fluid is turbulent in nature. The meridional component of the liquid flow rate is 53 m/s. Figure 5 shows a visualization of the pressure distribution in the plane passing through the axis of rotation of the wheels at nrot =1500 rpm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004394_j_29_9_29_9_857__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004394_j_29_9_29_9_857__pdf-Figure1-1.png", + "caption": "Fig. 1 Model of front-steering vehicle", + "texts": [], + "surrounding_texts": [ + "\u5b66\u8853\u30fb\u6280\u8853\u8ad6\u6587\n\u679c\u6a39\u5712 UGV \u306e\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u753b\u50cf\u306b\u57fa\u3065\u304f\u5236\u5fa1\n\u6c38 \u7530 \u7d14 \u5e73\u22171 \u958b \u7530 \u5b8f \u4ecb\u22171 \u5009 \u92ea \u572d \u592a\u22171 \u6df1 \u5c3e \u9686 \u5247\u22171\n\u77f3 \u5c71 \u5065 \u4e8c\u22172 \u795e \u8c37 \u525b \u5fd7\u22172 \u6751 \u4e0a \u5247 \u5e78\u22173\nImage-based Control of a UGV in an Orchard using a Central Catadioptric Camera\nJunpei Nagata\u22171, Kosuke Kaida\u22171, Keita Kurashiki\u22171, Takanori Fukao\u22171, Kenji Ishiyama\u22172, Tsuyoshi Kamiya\u22172 and Noriyuki Murakami\u22173\nRecently the necessity of autonomous or highly functional agricultural equipments is increasing because of decrease and aging of labors for farming. The development of autonomous vehicles in an orchard is required as one of the equipments because an orchard is usually on a hill or mountain where it is very tough for farmers to work. In this research, a new design method of an unmanned ground vehicle (UGV) in an orchard is proposed by using image-based control with a central catadioptric camera. A central catadioptric camera is very effective to keep target objects in the camera field of view because of its wide area view. The effectiveness of our proposed method is confirmed by experimental results in an orchard.\nKey Words: Autonomous Vehicle, Orchard, Central Catadioptric Camera, Image-based Control\n1. \u306f \u3058 \u3081 \u306b\n\u6211\u304c\u56fd\u306e\u8fb2\u696d\u3092\u53d6\u308a\u5dfb\u304f\u72b6\u6cc1\u306f\u6df1\u523b\u3067\u3042\u308b\uff0e\u8fb2\u696d\u5f93\u4e8b\u8005\u306e\u6e1b \u5c11\u3068\u9ad8\u9f62\u5316\u304c\u9855\u8457\u3067\u3042\u308a\uff0c\u52b9\u7387\u7684\u306a\u8fb2\u696d\u751f\u7523\u30b7\u30b9\u30c6\u30e0\u306e\u78ba\u7acb\u304c \u6c42\u3081\u3089\u308c\u3066\u3044\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u8fb2\u696d\u306e\u81ea\u52d5\u5316\u30fb\u7701\u529b\u5316\u3092\u76ee\u7684\u3068\u3057 \u305f\u81ea\u5f8b\u578b\u8fb2\u4f5c\u696d\u8eca\u4e21\u306b\u95a2\u3059\u308b\u7814\u7a76\u304c\u76db\u3093\u306b\u884c\u308f\u308c\u3066\u3044\u308b [1]\uff0e\u672c 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\u22172\u30e4\u30de\u30cf\u767a\u52d5\u6a5f \u22173\u8fb2\u696d\u30fb\u98df\u54c1\u7523\u696d\u6280\u8853\u7dcf\u5408\u7814\u7a76\u6a5f\u69cb\u5317\u6d77\u9053\u8fb2\u696d\u7814\u7a76\u30bb\u30f3\u30bf\u30fc \u22171Graduate School of Engineering, Kobe University \u22172Yamaha Motor Co., Ltd. \u22173National Agricultural Research Center for Hokkaido Region\n\u672c\u8ad6\u6587\u306f\u6709\u7528\u6027\u3067\u8a55\u4fa1\u3055\u308c\u307e\u3057\u305f\uff0e\n\u679c\u6a39\u5712\u5185\u3092\u5de1\u56de\u3059\u308b\u3068\u3044\u3046\u307e\u3063\u305f\u304f\u65b0\u3057\u3044\u30b7\u30b9\u30c6\u30e0\u3092\u63d0\u6848\u3059\u308b\uff0e \u30ab\u30e1\u30e9\u3092\u7528\u3044\u305f\u5236\u5fa1\u624b\u6cd5\u306f\uff0c\u30ab\u30e1\u30e9\u306e\u753b\u50cf\u304b\u3089\u8eca\u4e21\u306e\u4f4d\u7f6e\u30fb \u59ff\u52e2\u3092\u7b97\u51fa\u3057\uff0c\u305d\u308c\u306b\u57fa\u3065\u3044\u3066\u5236\u5fa1\u3092\u884c\u3046 Position-based \u5236 \u5fa1\u3068\uff0c\u8eca\u4e21\u306e\u4f4d\u7f6e\u30fb\u59ff\u52e2\u3092\u967d\u306b\u53d6\u308a\u6271\u308f\u305a\uff0c\u753b\u50cf\u5e73\u9762\u4e0a\u306b\u5b9a\u7fa9 \u3057\u305f\u72b6\u614b\u91cf\u3092\u7528\u3044\u3066\u8eca\u4e21\u3092\u5236\u5fa1\u3059\u308b Image-based \u5236\u5fa1\u3068\u306b\u5206 \u3051\u3089\u308c\u308b\uff0e\u3053\u306e\u3046\u3061\u753b\u50cf\u306b\u57fa\u3065\u304f\u5236\u5fa1\u3067\u306f\uff0c\u753b\u50cf\u304b\u3089\u4f4d\u7f6e\u3078\u306e \u5909\u63db\u3092\u884c\u308f\u305a\uff0c\u30ab\u30e1\u30e9\u306e\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u30a8\u30e9\u30fc\u306b\u5bfe\u3059\u308b\u30ed \u30d0\u30b9\u30c8\u6027\u304c\u9ad8\u3044\u3068\u3044\u3046\u7279\u5fb4\u304c\u3042\u308b [6]\uff0e \u672c\u8ad6\u6587\u3067\u306f\uff0c\u8d70\u884c\u6642\u306b\u76ee\u6a19\u3068\u306a\u308b\u6728\u304c\u30ab\u30e1\u30e9\u306e\u8996\u91ce\u304b\u3089\u5916\u308c \u306a\u3044\u3088\u3046\u306b\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u3092\u7528\u3044\u308b\uff0e\u3053\u308c\u307e\u3067\u306b\u3082\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9 \u3092\u7528\u3044\u305f\u753b\u50cf\u306b\u57fa\u3065\u304f\u5236\u5fa1\u304c\u63d0\u6848\u3055\u308c\u3066\u3044\u308b [7] [8]\u304c\uff0c\u3053\u308c\u3089 \u306e\u65b9\u6cd5\u3067\u306f\uff0c\u5236\u5fa1\u306b\u7528\u3044\u308b\u72b6\u614b\u91cf\u3092\u6c42\u3081\u308b\u306e\u306b\u5b9f\u969b\u306b\u8d70\u884c\u9762\u4e0a \u306e\u76f4\u7dda\u3084\u66f2\u7dda\u3092\u5fc5\u8981\u3068\u3057\u3066\u3044\u308b\u306e\u306b\u5bfe\u3057\uff0c\u672c\u63d0\u6848\u624b\u6cd5\u3067\u306f\u8d70\u884c \u8ecc\u9053\u306f\u5186\u8ecc\u9053\u306b\u9650\u3089\u308c\u308b\u304c\uff0c\u4eee\u60f3\u7684\u306a\u76f4\u7dda\u3084\u66f2\u7dda\u3092\u8a2d\u5b9a\u3059\u308b\u3053 \u3068\u306b\u3088\u308a\uff0c\u8d70\u884c\u9762\u4e0a\u306e\u70b9\u306e\u307f\u3092\u7528\u3044\u3066\u5236\u5fa1\u3092\u884c\u3063\u3066\u3044\u308b\uff0e \u4ee5\u4e0a\u306e\u3088\u3046\u306a\u624b\u6cd5\u3092\u7528\u3044\uff0c\u30d0\u30a4\u30ef\u30a4\u30e4\u5316\u3055\u308c\u305f\u8eca\u4e21\u3092\u7528\u3044\u305f\u679c \u6a39\u5712\u3067\u306e\u5b9f\u9a13\u306b\u3088\u308a\u672c\u63d0\u6848\u624b\u6cd5\u306e\u6709\u52b9\u6027\u3092\u793a\u3059\uff0e\u7b2c 2\u7ae0\u3067\u8eca\u4e21\u3068 \u30ab\u30e1\u30e9\u306e\u30e2\u30c7\u30eb\u306b\u3064\u3044\u3066\u8ff0\u3079\uff0c\u7b2c 3\u7ae0\u3067\u5236\u5fa1\u624b\u6cd5\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e \u305d\u3057\u3066\uff0c\u7b2c 4\u7ae0\u3067\u679c\u6a39\u306e\u691c\u51fa\u30ab\u30a6\u30f3\u30c8\u306e\u65b9\u6cd5\uff0c\u7b2c 5\u7ae0\u3067 UGV \u3092\u7528\u3044\u305f\u5b9f\u9a13\u306b\u3064\u3044\u3066\u8ff0\u3079\uff0c\u6700\u5f8c\u306b\u7b2c 6\u7ae0\u3067\u307e\u3068\u3081\u3092\u8ff0\u3079\u308b\uff0e\n2. \u8eca\u4e21\u30e2\u30c7\u30eb\u3068\u30ab\u30e1\u30e9\u30e2\u30c7\u30eb\n\u672c\u7ae0\u3067\u306f\uff0c\u8eca\u4e21\u3068\u30ab\u30e1\u30e9\u306e\u30e2\u30c7\u30eb\u304a\u3088\u3073\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306b\u3088\u308b \u76f4\u7dda\u306e\u5c04\u5f71\u65b9\u7a0b\u5f0f\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 29 \u5dfb 9 \u53f7 \u2014101\u2014 2011 \u5e74 11 \u6708", + "2. 1 \u8eca\u4e21\u30e2\u30c7\u30eb \u8eca\u4e21\u306e\u904b\u52d5\u5b66\u30e2\u30c7\u30eb\u3068\u3057\u3066\u306f\uff0cFig. 1\u306b\u793a\u3059\u524d\u8f2a\u64cd\u8235\u578b\u306e\u30e2 \u30c7\u30eb\u3092\u7528\u3044\u308b [9]\uff0e\u4ee5\u4e0b\u3067\u306f\uff0c\u8eca\u4e21\u306f\u5e73\u9762\u5185\u3092\u904b\u52d5\u3059\u308b\u3082\u306e\u3068 \u3057\uff0c\u30ed\u30fc\u30eb\u30fb\u30d4\u30c3\u30c1\u904b\u52d5\u306f\u8003\u616e\u3057\u306a\u3044\uff0e\u3053\u3053\u3067\uff0c\u30ef\u30fc\u30eb\u30c9\u5ea7\u6a19 \u7cfb Ow\u2013xwyw \u306b\u304a\u3051\u308b\u8eca\u4e21\u5f8c\u8f2a\u8ef8\u4e2d\u5fc3\u306e\u5ea7\u6a19\u3092 [x, y]T\uff0c\u524d\u8f2a \u8ef8\u4e2d\u5fc3\u306e\u5ea7\u6a19\u3092 [x1, y1]\nT\uff0cxw \u8ef8\u306b\u5bfe\u3059\u308b\u8eca\u4e21\u306e\u89d2\u5ea6\uff08\u53cd\u6642\u8a08 \u56de\u308a\u3092\u6b63\u3068\u3059\u308b\uff09\u3092 \u03b8\uff0c\u8eca\u4e21\u306e\u9032\u884c\u65b9\u5411\u901f\u5ea6\u3092 v\uff0c\u64cd\u8235\u89d2\u3092 \u03c6\uff0c \u30db\u30a4\u30fc\u30eb\u30d9\u30fc\u30b9\u3092 L \u3068\u3059\u308b\uff0e\u524d\u5f8c\u8f2a\u304c\u6a2a\u6ed1\u308a\u3057\u306a\u3044\u3068\u3044\u3046\u4eee\u5b9a \u3092\u304a\u304f\u3068\uff0c\u6b21\u306e\u4e8c\u3064\u306e\u901f\u5ea6\u62d8\u675f\u3092\u5f97\u308b\uff0e(\nx\u0307 sin \u03b8 \u2212 y\u0307 cos \u03b8 = 0 x\u03071 sin (\u03b8 + \u03c6) \u2212 y\u03071 cos (\u03b8 + \u03c6) = 0 \uff081\uff09\n\u307e\u305f\uff0c\u9032\u884c\u65b9\u5411\u901f\u5ea6 v \u306b\u95a2\u3057\u3066\u6b21\u306e\u95a2\u4fc2\u304c\u6210\u308a\u7acb\u3064\uff0e\nx\u0307 cos \u03b8 + y\u0307 sin \u03b8 = v \uff082\uff09\n\u4e00\u65b9\uff0c\u5e7e\u4f55\u5b66\u7684\u306a\u95a2\u4fc2\u304b\u3089\u6b21\u5f0f\u304c\u6210\u308a\u7acb\u3064\uff0e( x1 = x + L cos \u03b8\ny1 = y + L sin \u03b8 \uff083\uff09\n\u5f0f\uff081\uff09\uff0c\uff083\uff09\u304b\u3089 x1\uff0cy1 \u3092\u6d88\u53bb\u3057\uff0c\u5f0f\uff082\uff09\u3092\u7528\u3044\u308b\u3068\u6b21\u306e\u95a2 \u4fc2\u3092\u5f97\u308b\uff0e\n\u03b8\u0307 = v\nL tan\u03c6 \uff084\uff09\n\u4ee5\u4e0a\u3088\u308a\uff0c\u8eca\u4e21\u306e\u89d2\u901f\u5ea6\u3092 \u03c9 \u3068\u3059\u308b\u3068\uff0c\u904b\u52d5\u5b66\u30e2\u30c7\u30eb\u306f\u6b21\u5f0f\u3067 \u8868\u3055\u308c\u308b\uff0e\nd dt\n2 64 x y\n\u03b8\n3 75 = 2 64 cos \u03b8 0 sin \u03b8 0\n0 1\n3 75 \" v\n\u03c9\n# \uff085\uff09\n\u305f\u3060\u3057\uff0c\n\u03c9 = v\nL tan \u03c6 \uff086\uff09\n\u3067\u3042\u308b\uff0e 2. 2 \u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u30e2\u30c7\u30eb \u672c\u8ad6\u6587\u3067\u6271\u3046\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306f\uff0cFig. 2\u306e\u3088\u3046\u306b\u30ab\u30e1\u30e9\u306e\u5149\u8ef8 \u3068\u53cc\u66f2\u9762\u30df\u30e9\u30fc\u306e\u5bfe\u79f0\u8ef8\u304c\u4e00\u81f4\u3059\u308b\u3088\u3046\u306b\u4e21\u8005\u3092\u7d44\u307f\u5408\u308f\u305b\u305f \u3082\u306e\u3067\u3042\u308b\uff0e\u30ab\u30e1\u30e9\u306e\u5149\u5b66\u4e2d\u5fc3\u3092 C\uff0c\u30df\u30e9\u30fc\u306e\u7126\u70b9\u3092 M \u3068\u3057\uff0c \u305d\u308c\u3089\u3092\u539f\u70b9\u3068\u3059\u308b\u5ea7\u6a19\u7cfb\u3092\u305d\u308c\u305e\u308c Fc\uff0cFm \u3068\u3059\u308b\uff0e\u3053\u306e\u3068 \u304d\uff0c\u3042\u308b\u70b9\u306e Fm \u306b\u304a\u3051\u308b\u5ea7\u6a19 Pm = [xm, ym, zm]T \u3068\uff0c\u753b\n\u50cf\u5ea7\u6a19 X\u0304 = [X, Y, 1]T \u3068\u306e\u95a2\u4fc2\u306f\u6b21\u5f0f\u3067\u8868\u3055\u308c\u308b [7]\uff0e\nX\u0304 = Kf (Pm) \uff087\uff09\n\u3053\u3053\u3067\uff0c\nf (Pm) = 2 664\nxm zm+\u03be \u221a x2 m+y2 m+z2 m\nym zm+\u03be \u221a x2 m+y2 m+z2 m\n1\n3 775 \uff088\uff09\n\u3067\u3042\u308a\uff0cK \u306f\u8f03\u6b63\u884c\u5217\uff0c\u03be \u306f\u53cc\u66f2\u9762\u30df\u30e9\u30fc\u306e\u5185\u90e8\u30d1\u30e9\u30e1\u30fc\u30bf\u3067 \u3042\u308b\uff0e\u672c\u8ad6\u6587\u3067\u306f\uff0cK \u306f\u5358\u4f4d\u884c\u5217\u3068\u3057\uff0cPm \u3068 X\u0304 \u3068\u306e\u95a2\u4fc2\u306f\nX\u0304 = f (Pm) \uff089\uff09\n\u3067\u8868\u3055\u308c\u308b\u3082\u306e\u3068\u3059\u308b\uff0e 2. 3 \u76f4\u7dda\u306e\u5c04\u5f71\u65b9\u7a0b\u5f0f \u4e09\u6b21\u5143\u7a7a\u9593\u4e0a\u306e\u76f4\u7dda\u304c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306b\u3088\u3063\u3066\u3069\u306e\u3088\u3046\u306b\u753b\u50cf \u5e73\u9762\u306b\u5c04\u5f71\u3055\u308c\u308b\u306e\u304b\u3092\u8ff0\u3079\u308b\uff0e\u53cc\u66f2\u9762\u30df\u30e9\u30fc\u306e\u5ea7\u6a19\u7cfb Fm \u306b \u304a\u3044\u3066\u70b9 P \u3068\u5358\u4f4d\u30d9\u30af\u30c8\u30eb u = [ux, uy , uz]\nT \u306b\u3088\u3063\u3066\u76f4\u7dda \u3092\u8868\u3059\u3082\u306e\u3068\u3059\u308b\uff08Fig. 2\uff09\uff0en = \u2212\u2212\u2192 MP\u00d7 u = [nx, ny , nz]\nT \u3068 \u3044\u3046\u53cc\u66f2\u9762\u30df\u30e9\u30fc\u306e\u7126\u70b9\u3068\u76f4\u7dda\u3092\u542b\u3080\u5e73\u9762\u306e\u6cd5\u7dda\u30d9\u30af\u30c8\u30eb\u3092\u5b9a \u7fa9\u3059\u308b\u3068\uff0c\u6b21\u306e\u5ea7\u6a19\u7cfb Fm \u306b\u304a\u3051\u308b\u76f4\u7dda\u306e\u753b\u50cf\u5ea7\u6a19\u7cfb\u3067\u306e\u95a2\u4fc2 \u5f0f\u304c\u6c42\u307e\u308b [7]\uff0e\nX\u0304T \u03a9X\u0304 = 0 \uff0810\uff09\n\u3053\u3053\u3067\uff0c\u03a9 \u306f\u6b21\u5f0f\u3067\u8868\u3055\u308c\u308b\uff0e\n\u03a9 = 2 64 n2 x ` 1 \u2212 \u03be2 \u00b4 \u2212 n2 z\u03be2 nxny ` 1 \u2212 \u03be2 \u00b4 nxnz nxny ` 1 \u2212 \u03be2 \u00b4 n2\ny\n` 1 \u2212 \u03be2 \u00b4 \u2212 n2 z\u03be2 nynz\nnxnz nynz n2 z\n3 75\n\uff0811\uff09\n\u5f0f\uff0810\uff09\u306e\u95a2\u4fc2\u5f0f\u304b\u3089\uff0c\u6b21\u306e\u4e8c\u6b21\u65b9\u7a0b\u5f0f\u304c\u5b9a\u7fa9\u3055\u308c\u308b\uff0e\nA0X 2 + A1Y 2 + 2A2XY + 2A3X + 2A4Y + A5 = 0\n\uff0812\uff09\nJRSJ Vol. 29 No. 9 \u2014102\u2014 Nov., 2011", + "\u305f\u3060\u3057\uff0cs \u3092\u30b9\u30b1\u30fc\u30eb\u30d5\u30a1\u30af\u30bf\u3068\u3057\u3066\uff0c8>>>>< >>>>>: A0 = s ` n2 x ` 1 \u2212 \u03be2 \u00b4 \u2212 n2 z\u03be2 \u00b4 A1 = s ` n2 y ` 1 \u2212 \u03be2 \u00b4 \u2212 n2 z\u03be2 \u00b4 A2 = snxny ` 1 \u2212 \u03be2 \u00b4 A3 = snxnz A4 = snynz\nA5 = sn2 z\n\uff0813\uff09\n\u3067\u3042\u308b\uff0e\u3059\u306a\u308f\u3061\uff0c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u5834\u5408\uff0c\u76f4\u7dda\u306e\u65b9\u7a0b\u5f0f\u306f\u753b\u50cf\u5ea7 \u6a19\u7cfb\u3067\u306f\u4e8c\u6b21\u65b9\u7a0b\u5f0f\u3067\u8868\u3055\u308c\u308b\u3088\u3046\u306b\u306a\u308b\uff0e\u3053\u3053\u3067\uff0c\u5f0f\uff0812\uff09\u306e \u4e21\u8fba\u3092 A5 \u3067\u9664\u3057\u3066\uff0c\u6b21\u306e\u3088\u3046\u306a\u4e8c\u6b21\u65b9\u7a0b\u5f0f\u306e\u5f62\u306b\u6a19\u6e96\u5316\u3059\u308b\uff0e\nB0X 2 + B1Y 2 + 2B2XY + 2B3X + 2B4Y + 1 = 0\n\uff0814\uff09\n\u305f\u3060\u3057\uff0cBi = Ai/A5 (i = 0, . . . , 4) \u3067\u3042\u308b\uff0enz = 0 \u3068\u306a\u308b \u5834\u5408\uff0c\u4e09\u6b21\u5143\u7a7a\u9593\u4e0a\u306e\u76f4\u7dda\u304c\u753b\u50cf\u5e73\u9762\u306b\u5c04\u5f71\u3055\u308c\u305f\u7dda\u304c\u753b\u50cf\u306e \u4e2d\u5fc3\u3092\u901a\u308b\uff0e\u3053\u306e\u3068\u304d\uff0c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u5834\u5408\u306b\u306f\u7dda\u304c\u898b\u3048\u306a\u304f \u306a\u3063\u3066\u3057\u307e\u3046\u305f\u3081\uff0c\u4ee5\u4e0b\u3067\u306f nz = 0 \u3092\u4eee\u5b9a\u3059\u308b [7]\uff0e\n3. \u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u753b\u50cf\u306b\u57fa\u3065\u304f\u8eca\u4e21\u306e\u5236\u5fa1\n\u672c\u7ae0\u3067\u306f\uff0c\u554f\u984c\u8a2d\u5b9a\u3068\u5236\u5fa1\u5247\u306e\u5c0e\u51fa\u304a\u3088\u3073\u753b\u50cf\u4e0a\u306e\u30d1\u30e9\u30e1\u30fc \u30bf\u306e\u7b97\u51fa\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e\n3. 1 \u554f\u984c\u8a2d\u5b9a\u3068\u5236\u5fa1\u5247\u306e\u5c0e\u51fa \u5236\u5fa1\u76ee\u7684\u306f\uff0c\u8eca\u4e21\u304c\u5730\u9762\u4e0a\u306b\u56fa\u5b9a\u3055\u308c\u305f\u76ee\u6a19\u70b9\u3092\u4e2d\u5fc3\u3068\u3059\u308b \u4e00\u5b9a\u534a\u5f84\u306e\u5186\u8ecc\u9053\u4e0a\u3092\u8d70\u884c\u3059\u308b\u3053\u3068\u3067\u3042\u308b\uff0e\u672c\u7814\u7a76\u30b0\u30eb\u30fc\u30d7\u306e\u5148 \u306e\u7814\u7a76\u3067\u306f\uff0c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u3092\u7528\u3044\u305f\u76f4\u7dda\u304a\u3088\u3073\u66f2\u7dda\u8ffd\u5f93\u5236\u5fa1 [8] \u3092\u63d0\u6848\u3057\u3066\u3044\u308b\u304c\uff0c\u3053\u306e\u65b9\u6cd5\u3067\u306f\u4e09\u6b21\u5143\u7a7a\u9593\u5185\u306e\u7dda\u304c\u753b\u50cf\u5e73\u9762 \u4e0a\u306b\u6295\u5f71\u3055\u308c\u305f\u4e8c\u6b21\u66f2\u7dda\u3068\uff0c\u753b\u50cf\u5ea7\u6a19\u306e\u6a2a\u8ef8\u3068\u306e\u4ea4\u70b9\u306b\u304a\u3051\u308b \u63a5\u7dda\u3092\u6c42\u3081\uff08Fig. 3\uff09\uff0c\u305d\u308c\u3092\u7e26\u8ef8\u3068\u5e73\u884c\u304b\u3064\u4e00\u5b9a\u8ddd\u96e2\u306b\u3059\u308b\u3088 \u3046\u306a\u5236\u5fa1\u3092\u884c\u3063\u3066\u3044\u308b\uff0e\u672c\u8ad6\u6587\u304c\u5bfe\u8c61\u3068\u3059\u308b\u74b0\u5883\u3067\u753b\u50cf\u304b\u3089\u5f97 \u3089\u308c\u308b\u60c5\u5831\u306f\uff0c\u76ee\u6a19\u5186\u8ecc\u9053\u306e\u4e2d\u5fc3\u70b9\u306e\u753b\u50cf\u4e0a\u306e\u5ea7\u6a19\u306e\u307f\u3067\u3042\u308a\uff0c \u4e0a\u8ff0\u306e\u65b9\u6cd5\u3067\u63a5\u7dda\u3092\u6c42\u3081\u308b\u3053\u3068\u306f\u3067\u304d\u306a\u3044\uff0e\u305d\u3053\u3067\uff0c\u5186\u8ecc\u9053\u306e \u307f\u306b\u306a\u308b\u304c\uff0c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u753b\u50cf\u306b\u57fa\u3065\u304f\u5236\u5fa1\u306b\u3088\u308b\u65b0\u3057\u3044\u8a2d \u8a08\u6cd5\u3092\u63d0\u6848\u3059\u308b\uff0e \u307e\u305a\uff0cFig. 4\u306b\u793a\u3059\u3088\u3046\u306b\uff0c\u8eca\u4e21\u306e\u5f8c\u8f2a\u8ef8\u4e2d\u5fc3\u304b\u3089\u5730\u9762\u306b\u4e0b \u308d\u3057\u305f\u5782\u7dda\u3068\u5730\u9762\u3068\u306e\u4ea4\u70b9\u3092\u539f\u70b9\u3068\u3057\uff0c\u8eca\u4e21\u306e\u524d\u5411\u304d\u306b xv \u8ef8\uff0c \u5de6\u5411\u304d\u306b yv \u8ef8\u3092\u3068\u308b\u3088\u3046\u306a\u8eca\u4e21\u5ea7\u6a19\u7cfb O\u2013xvyv \u3092\u8003\u3048\u308b\uff0e\u305f\n\u3060\u3057\uff0c\u5730\u9762\u306f\u5e73\u9762\u3067\u3042\u308b\u3068\u3057\uff0cxwyw \u5e73\u9762\u3068 xvyv \u5e73\u9762\u306f\u540c\u4e00 \u5e73\u9762\u4e0a\u306b\u3042\u308b\uff0e\u5730\u9762\u4e0a\u306b\u56fa\u5b9a\u3055\u308c\u3066\u3044\u308b\u76ee\u6a19\u70b9\u3092 Pt \u3068\u3057\uff0c\u30ef\u30fc \u30eb\u30c9\u5ea7\u6a19\u7cfb Ow\u2013xwyw \u306b\u304a\u3051\u308b\u5ea7\u6a19\u3092 [xr, yr]\nT \u3068\u3059\u308b\uff0e\u4ee5\u4e0b \u3067\u306f\uff0c\u3059\u3079\u3066\u306e\u904b\u52d5\u306f\u3053\u306e\u5e73\u9762\u4e0a\u3067\u8d77\u3053\u3063\u3066\u3044\u308b\u3082\u306e\u3068\u3059\u308b\uff0e \u70b9 Pt \u3092\u901a\u308a\uff0c\u70b9 O \u3068\u70b9 Pt \u3092\u7d50\u3076\u7dda\u5206\u306b\u76f4\u4ea4\u3059\u308b\u4eee\u60f3\u7684 \u306a\u76f4\u7dda\u3092\u5c0e\u5165\u3059\u308b\uff0e\u3053\u306e\u3068\u304d\uff0c\u76ee\u6a19\u72b6\u614b\u3059\u306a\u308f\u3061\u76ee\u6a19\u70b9 Pt \u3092 \u4e2d\u5fc3\u3068\u3059\u308b\u4e00\u5b9a\u534a\u5f84\u306e\u5186\u8ecc\u9053\u4e0a\u3092\u8d70\u884c\u3059\u308b\u3053\u3068\u306f\uff0c\u8eca\u4e21\u5ea7\u6a19\u7cfb O\u2013xvyv \u306b\u304a\u3044\u3066\uff0c\u3053\u306e\u4eee\u60f3\u7684\u306a\u76f4\u7dda\u3092 xv \u8ef8\u306b\u5e73\u884c\u306b\uff0c\u304b\u3064 \u539f\u70b9\u3068\u306e\u8ddd\u96e2\u3092\u4e00\u5b9a\u306b\u4fdd\u3064\u3053\u3068\u3068\u306a\u308b\uff0e\u3053\u306e\u4eee\u60f3\u7684\u306a\u76f4\u7dda\u3092\u76f4 \u7dda A \u3068\u3059\u308b\uff0e\u76f4\u7dda A \u304c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306b\u3088\u308a\u753b\u50cf\u5e73\u9762\u4e0a\u306b\u6295\u5f71 \u3055\u308c\u305f\u66f2\u7dda\u3092 B\u2032 \u3068\u3059\u308b\uff0e\u3053\u3053\u3067\uff0c\u66f2\u7dda B\u2032 \u306f\u5f0f\uff0814\uff09\u3067\u8868\u3055\u308c \u308b\u4e8c\u6b21\u66f2\u7dda\u3067\u3042\u308b\u3068\u3059\u308b\uff0e\u3055\u3089\u306b\uff0c\u753b\u50cf\u5ea7\u6a19\u7cfb\u3067\u306e Pt \u306e\u5c04\u5f71 \u70b9 (Xt, Yt) \u306b\u304a\u3051\u308b\u66f2\u7dda B\u2032 \u306e\u63a5\u7dda\u3092\u76f4\u7dda A\u2032 \u3068\u3059\u308b\uff0e\u3053\u306e\u3068 \u304d\uff0c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u6027\u8cea\u3088\u308a\uff0c\u8eca\u4e21\u5ea7\u6a19\u7cfb\u306b\u304a\u3051\u308b\u76f4\u7dda A \u3068\u753b \u50cf\u5ea7\u6a19\u7cfb\u306b\u304a\u3051\u308b\u76f4\u7dda A\u2032 \u306e\u65b9\u5411\u306f\u4e00\u81f4\u3059\u308b\uff08Fig. 5\uff0c6\uff09\uff0e\u3053\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 29 \u5dfb 9 \u53f7 \u2014103\u2014 2011 \u5e74 11 \u6708" + ] + }, + { + "image_filename": "designv8_17_0000027_6_65_4_65_4_525__pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000027_6_65_4_65_4_525__pdf-Figure16-1.png", + "caption": "Fig. 16 Example of output of spatial layout constraints", + "texts": [], + "surrounding_texts": [ + "\u6a5f \u80fd\u8981 \u7d20 \u9593\u306b\u6210 \u308a\u7acb \u3064\u4f4d\u7f6e \u95a2\u4fc2 \u306b\u3064 \u3044\u3066 \u306e\u5236 \u7d04 \u3092\u5145\u8db3 \u3055\u305b \u308b \u3082 \u306e \u3067\u3042 \u308b.\u3053 \u306e \u30bd\u30eb\u30d0 \u306b \u304a\u3044 \u3066\u306f,\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u30e6\u30cb \u30c3 \u30c8\u304c \u8a2d\n\u8a08\u89e3 \u3092\u751f\u6210 \u3059 \u308b\u524d \u306b,\u6a5f \u80fd \u8981\u7d20\u306e \u4f4d\u7f6e \u306e\u6982 \u7565 \u3092\u6c42 \u3081 \u308b \u3053 \u3068\u3092 \u76ee \u7684 \u3068\u3057\u3066\u3044 \u308b.\u305d \u306e\u305f \u3081,\u3053 \u3053\u3067 \u306f\u6a5f \u80fd\u8981 \u7d20\u306e \u4e2d\u5fc3 \u5ea7 \u6a19 \u306e\u307f \u3092 \u53d6 \u308a\u6271 \u3046.\u3053 \u306e\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb \u30d0 \u306b \u3088\u3063\u3066\u6c42 \u3081 \u3089\u308c \u305f \u4e2d\u5fc3\u5ea7 \u6a19 \u304b \u3089,\u4e0a \u8ff0 \u3057\u305f \u5e7e\u4f55 \u5b66\u7684 \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066\u6c42\u3081 \u3089\u308c \u305f\u5f62\u72b6 \u304c\u751f \u6210\u3059 \u308b\u3053 \u3068\u306b \u306a\u308b.\u5177 \u4f53 \u7684 \u306b\u306f,\u3053 \u306e \u30bd\u30eb \u30d0 \u306f\u5b9f \u6570\u8868 \u73fe \u306e \u67d3 \u8272\u4f53 \u3092 \u3082\u3064GA\u3092 \u5fdc \u7528 \u3057\u3066 \u304a \u308a,VLSI(Very Large Scale Integrated)\u30c1 \u30c3\u30d7 \u306e \u30ec \u30a4\u30a2 \u30a6 \u30c8\u8a2d\u8a08(\u4f8b \u3048\u30709))\u306b \u304a \u3044 \u3066\u7528 \u3044 \u3089\u308c \u3066 \u3044 \u308b \u3082\u306e \u3068\u57fa \u672c \u7684 \u306b\u540c\u69d8 \u306e \u624b \u6cd5 \u30923\u6b21 \u5143 \u306b\u62e1 \u5f35 \u3057\u305f\n\u624b \u6cd5 \u3092\u63a1\u7528 \u3057\u3066\u3044 \u308b.\n\u4e0a\u8ff0 \u3057\u305f2\u3064 \u306e \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066,\u305d \u308c\u305e \u308c\u6a5f \u80fd \u8981\u7d20 \u306e\u6982 \u7565 \u5f62 \u72b6 \u3068\u6982\u7565 \u306e\u4f4d \u7f6e \u3092\u5f97 \u305f\u5f8c \u306b,\u3053 \u306e\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8\u306b \u3088\u3063 \u3066\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u3092\u751f \u6210\u3059 \u308b.\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u30e6 \u30cb \u30c3 \u30c8\u306b\u304a \u3051 \u308b \u30a2\u30eb \u30b4 \u30ea\u30ba \u30e0\u306f,\u5236 \u7d04 \u3092\u5145 \u8db3\u3059 \u308b\u30d7 \u30ed\u30bb \u30b9\u3067 \u306f \u306a \u304f,\u5e7e \u4f55 \u5b66 \u7684 \u5236\u7d04 \u30bd\u30eb\u30d0 \u3068\u7a7a \u9593\u914d \u7f6e \u30bd\u30eb\u30d0\u304c \u751f \u6210 \u3057\u305f\u5236 \u7d04\u5145 \u8db3 \u89e3 \u3092\u7d71 \u5408 \u3057, \u6a5f \u80fd\u8981 \u7d20 \u306e3\u6b21 \u5143 \u5f62 \u72b6 \u3068\u305d\u306e\u7a7a \u9593 \u7684 \u914d\u7f6e \u3092\u540c \u3058\u67a0 \u7d44 \u306e \u4e2d \u3067\u6c42 \u3081 \u308b \u3053 \u3068\u304c \u76ee\u7684\u3067 \u3042 \u308b.\u3053 \u3053\u3067,\u300c\u540c\u3058\u67a0 \u7d44\u306e \u4e2d\u3067 \u300d\u6c42 \u3081 \u308b \u3053 \u3068 \u3068\u306f,\u5e7e \u4f55\u5b66 \u7684\u5236\u7d04 \u30bd\u30eb\u30d0 \u3068\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0\u304c \u751f\u6210 \u3057\u305f\u8a2d \u8a08\u89e3 \u306e\u77db \u76fe\u3059 \u308b\u90e8 \u5206 \u306b\u3064 \u3044\u3066,\u305d \u308c\u305e \u308c \u306b\u5bfe \u3057\u3066 \u300c\u540c \u3058\u67a0 \u7d44 \u306e \u4e2d\u3067 \u300d\u4fee \u6b63 \u3092\u52a0 \u3048,\u5e7e \u4f55 \u5b66\u7684 \u5236\u7d04 \u3068\u7a7a \u9593\u914d \u7f6e\u5236 \u7d04 \u306b \u3088\u3063\u3066 \u751f\u6210 \u3055\u308c \u305f2\u3064 \u306e \u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3 \u306b\u95a2\u3059 \u308b\u8a2d \u8a08 \u89e3\u306e \u59a5\u5354 \u70b9 \u3092\u63a2 \u7d22 \u3057, \u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3 \u89e3 \u3092\u751f\u6210 \u3059 \u308b \u3053 \u3068\u3092\u610f \u5473 \u3057\u3066\u3044 \u308b.\u4ee5 \u4e0b \u306b,\u56f3 \u4e2d \u306e \u756a\u53f7 \u306b\u6cbf \u3044 \u306a\u304c \u3089,\u5404 \u6bb5 \u968e \u306b\u3064 \u3044\u3066 \u8aac \u660e\u3059 \u308b.\n\u56f311(1)\u306b \u304a\u3044\u3066,\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066\u751f \u6210 \u3055\u308c \u305f, \u6a5f \u80fd\u8981\u7d20 \u306e\u5ea7 \u6a19 \u3092\u5f97 \u308b(\u56f312\u306e1).\u6b21 \u306b,\u56f312\u306e2\u306b \u793a\u3059 \u3088 \u3046\u306b,(1)\u306b \u304a \u3044\u3066 \u5f97 \u3089\u308c \u305f\u5ea7 \u6a19 \u3092 \u4e2d\u5fc3 \u306b,\u5f62 \u72b6 \u3092\u751f\u6210 \u3059 \u308b. \u3053\u306e\u6bb5 \u968e\u3067 \u306f,\u6a5f \u80fd\u8981 \u7d20 \u9593\u306b\u5e72\u6e09 \u306f \u306a\u3044 \u305f\u3081,\u66f4 \u306b\u5f62\u72b6 \u306f\u6bb5 \u968e\n\u7684 \u306b\u751f \u6210 \u3055\u308c \u308b(\u56f311(2),(3)) .\u56f312\u306e3\u306b \u793a\u3059 \u3088 \u3046\u306b,\u5f62 \u72b6\u304c \u751f \u6210 \u3055\u308c\u3066 \u3044 \u304f\u306b\u5f93 \u3063\u3066,\u96a3 \u63a5\u3059 \u308b\u6a5f \u80fd \u8981\u7d20\u304c \u5e72 \u6e09 \u3057,\u5171 \u6709 \u90e8\u5206 \u304c\u767a \u751f \u3059 \u308b.\u3053 \u306e\u5834 \u5408,\u56f311(4),(5),(6)\u306b \u793a \u3059 \u3088 \u3046\u306b, \u5f62\u72b6 \u751f\u6210 \u306e \u4e2d\u5fc3\u4f4d \u7f6e \u3068\u5e72 \u6e09 \u3057\u305f\u5f62\u72b6 \u306e\u30eb \u30fc\u30eb \u306b\u3064 \u3044\u3066 \u306e\u8abf \u6574\u304c \u540c \u3058\u67a0 \u7d44 \u306e \u4e2d\u3067\u884c \u308f \u308c \u308b.\n\u5f62\u72b6 \u306e \u4e2d\u5fc3 \u4f4d\u7f6e \u306e\u8abf \u6574 \u306f,\u56f313\u306b \u793a\u3059 \u3088 \u3046\u306b,\u5e72 \u6e09 \u3057\u305f\u6a5f\n\u80fd \u8981\u7d20A,B\u306f,\u305d \u308c\u305e \u308c \u306e\u5f62 \u72b6 \u306e\u751f \u6210 \u306e \u4e2d\u5fc3 \u3092NA,NB\u65b9 \u5411 \u306b\u79fb \u52d5\u3059 \u308b\u3002 \u305d\u306e\u79fb \u52d5 \u8ddd\u96e2 \u306f,\u305d \u306e \u5171\u6709 \u90e8 \u5206 \u306e\u4f53\u7a4d \u3092V;\u3068 \u3059 \u308b \u3068,\u4ee5 \u4e0b \u306e \u3088 \u3046\u306b\u5b9a \u7fa9\u3059 \u308b(\u56f313:\u5de6).\n\u3013(1)\n\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066\u751f\u6210 \u3055\u308c \u305f\u5f62\u72b6 \u751f \u6210\u306e \u4e2d\u5fc3 \u4f4d\u7f6e \u3092NA,NB\u65b9 \u5411\u306b\u79fb \u52d5 \u3055\u305b \u305f\u5834 \u5408,\u8abf \u6574 \u524d\u306e \u4e2d\u5fc3\u4f4d \u7f6e\u306f \u7a7a \u9593\u914d \u7f6e \u5236\u7d04 \u30bd\u30eb \u30d0 \u306b \u3088\u3063\u3066\u6700\u9069 \u5316 \u3055\u308c \u3066\u3044 \u308b\u305f \u3081,\u8abf \u6574\u5f8c \u306f \u305d\u306e\u8a55 \u4fa1 \u5024\u306f \u307b \u3068\u3093 \u3069\u306e\u5834 \u5408 \u6e1b\u5c11\u3059 \u308b\u3053 \u3068\u3068\u306a \u308b.\u305d \u3053\u3067,\u5f62 \u72b6 \u751f \u6210 \u306e \u4e2d\u5fc3 \u306e\u7a7a \u9593 \u7684\u914d\u7f6e \u3092\u7a7a \u9593\u914d \u7f6e\u5236 \u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066,\u5168 \u4f53 \u3068 \u3057 \u3066\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u306b\u5bfe \u3059 \u308b\u8a55\u4fa1 \u5024 \u3092\u4e00\u5b9a\u306e \u7bc4 \u56f2\u4ee5\u4e0b \u306b\u4e0b \u3052 \u306a\u3044 \u3088\nFig. 11 Flowchart of spatial design unit\n\u3046\u306b\u5f62\u72b6 \u306e \u4e2d\u5fc3 \u4f4d \u7f6e \u3092\u518d\u8abf \u6574 \u3059 \u308b(\u56f311(4),(5),\u56f313:\u53f3)\u3002\n\u5f62\u72b6 \u751f\u6210 \u306e \u4e2d\u5fc3 \u4f4d \u7f6e\u306e \u518d\u8abf \u6574 \u3068\u540c\u6642 \u306b,\u4e0a \u8ff0 \u3057\u305f \u3088 \u3046\u306b\u5e72\u6e09\n\u3057\u305f\u5f62 \u72b6\u306e \u30eb \u30fc \u30eb \u306b\u3064 \u3044 \u3066\u306e\u8abf \u6574 \u3082\u884c \u308f \u308c \u308b(\u56f311(6)).\u3053 \u306e \u30eb\u30fc \u30eb\u306e\u8abf \u6574 \u306b\u3064 \u3044\u3066 \u306f,\u524d \u7bc0 \u306e\u751f \u6210 \u30eb\u30fc\u30eb \u306b \u6ce8 \u76ee \u3057\u305f\u5f62\u72b6\n\u8868\u73fe \u306e \u62e1\u5f35 \u306b \u304a\u3044 \u3066\u8ff0 \u3079 \u305f\u901a \u308a\u3067 \u3042 \u308b.\n\u3053 \u3046 \u3057\u3066,\u6a5f \u80fd \u8981\u7d20 \u306e\u5f62 \u72b6 \u306e\u751f \u6210 \u3068\u8abf \u6574\u304c \u7d42 \u4e86 \u3057\u305f\u6642 \u306b,\u7a7a\n\u9593 \u30c7\u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8\u306b\u304a \u3044 \u3066,\u7a7a \u9593\u914d \u7f6e \u30683\u6b21 \u5143 \u5f62 \u72b6 \u306e\u77db \u76fe \u70b9 \u3092\u540c \u3058\u67a0\u7d44 \u3067\u89e3 \u6d88 \u3057\u306a\u304c \u3089,\u305d \u308c\u305e \u308c \u306e\u5236 \u7d04\u306b\u5bfe \u3059 \u308b\u8a55\u4fa1 \u5024 \u3092\u5168\u4f53 \u3068 \u3057\u3066\u4fdd \u3063\u305f\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u89e3 \u3092\u5f97,\u8a2d \u8a08\u8005 \u306b\u63d0\u793a \u3059 \u308b. \u8a2d\u8a08 \u8005 \u306f,\u3053 \u308c \u3092\u89b3\u5bdf \u3057,\u6c17 \u306b\u5165\u308c \u3070 \u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u306e \u30d7 \u30ed\u30bb \u30b9 \u304c \u7d42 \u308f \u308a,\u6c17 \u306b\u5165 \u3089\u306a \u3051\u308c\u3070 \u3082 \u3046\u4e00\u5ea6 \u5236 \u7d04 \u3092\u5909\u66f4 \u3057,\u5e7e \u4f55\u5b66 \u7684 \u5236\u7d04 \u30bd\u30eb\u30d0\u304b \u3082\u3057 \u304f\u306f\u7a7a \u9593\u914d \u7f6e\u5236 \u7d04 \u30bd\u30eb \u30d0 \u306b\u4e0e \u3048,\u5236 \u7d04 \u5145 \u8db3\u30d7\n\u30ed\u30bb \u30b9 \u3092\u518d\u5ea6 \u884c \u3046.\u3053 \u306e \u3088 \u3046\u306b \u3057\u3066,\u652f \u63f4 \u30b7 \u30b9\u30c6 \u30e0 \u3068\u5bfe \u8a71 \u7684 \u306b\n\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u3092\u884c \u3044,\u6700 \u7d42 \u7684 \u306b\u6c42 \u3081 \u308b\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3 \u3092\u5f97 \u308b.\n5.\u7a7a \u9593 \u30c7\u30b6 \u30a4 \u30f3\u652f\u63f4 \u30b7\u30b9 \u30c6 \u30e0\u306e \u8a66\u4f5c\n5.1\u30b7 \u30b9\u30c6\u30e0 \u306e\u69cb \u6210\n\u524d\u7ae0\u3067 \u793a \u3057\u305f\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u652f\u63f4 \u65b9 \u6cd5\u8ad6 \u306b\u57fa\u3065 \u3044\u3066,\u30b7 \u30b9 \u30c6 \u30e0\n\u3092\u8a66\u4f5c \u3057\u305f.\u30b7 \u30b9\u30c6 \u30e0\u306e\u5168 \u4f53 \u69cb \u6210 \u3092 \u56f314\u306b \u793a \u3059.\n\u672c \u30b7 \u30b9\u30c6 \u30e0\u306f,Sun Workstation\u4e0a \u3067C++\u3092 \u7528 \u3044 \u3066\u4f5c \u6210 \u3055\u308c \u3066\u304a \u308a,\u5927 \u304d \u304f\u5206\u3051 \u3066\u5236 \u7d04 \u8a2d\u5b9a \u30e6 \u30cb \u30c3 \u30c8,\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8,\u5236 \u7d04 \u30bd\u30eb\u30d0,\u30e6 \u30fc\u30b6 \u30a4\u30f3 \u30bf\u30d5 \u30a7\u30fc \u30b9,\u5e7e \u4f55 \u30a8 \u30f3\u30b8 \u30f3\u306e\n5\u3064 \u306e \u90e8\u5206 \u304b \u3089\u69cb \u6210 \u3055\u308c\u3066 \u3044 \u308b.\n\u7cbe \u5bc6 \u5de5 \u5b66 \u4f1a \u8a8cVo1.65,No.4,1999 529", + "5.2\u4eba \u5de5 \u885b \u661f\u8a2d \u8a08\u4e8b \u4f8b \u3078\u306e \u9069\u7528 5.2.1\u4eba \u5de5 \u885b \u661f\u8a2d \u8a08 \u306b\u304a \u3051 \u308b\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\n\u672c \u7814 \u7a76\u306e\u5bfe \u8c61 \u3068\u3057\u3066\u3044 \u308b\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u3067 \u306f,\u8a2d \u8a08 \u5bfe \u8c61 \u306b\u5bfe\u3059 \u308b\u30bf\u30b9 \u30af\u3084\u4ed5 \u69d8 \u306a\u3069 \u306f,\u3053 \u306e\u6bb5 \u968e\u4ee5 \u524d\u306b \u6c7a\u5b9a \u3055\u308c \u3066\u3044 \u308b\u5834 \u5408\u304c \u307b \u3068\u3093\u3069 \u3067\u3042 \u308b.\u5177 \u4f53 \u7684\u306b \u4eba\u5de5\u885b \u661f\u8a2d \u8a08 \u306b\u304a \u3044\u3066 \u306f,\u305d \u308c \u3089\u306f \u30df \u30c3\u30b7 \u30e7\u30f3 \u3068\u547c \u3070\u308c \u308b \u3082\u306e \u3067,\u305d \u306e \u4eba\u5de5\u885b \u661f\u306e \u76ee\u7684(\u4f8b \u3048\u3070 \u6c17\n\u8c61\u89b3 \u6e2c\u3084\u901a \u4fe1 \u306a \u3069)\u3067 \u3042 \u308a,\u307e \u305f\u30da \u30a4\u30ed \u30fc \u30c9(\u6253 \u3061\u4e0a\u3052 \u306b\u7528 \u3044 \u308b \u30ed \u30b1 \u30c3 \u30c8\u306b\u683c \u7d0d \u3067 \u304d\u308b\u5927 \u304d \u3055)\u3067 \u3042 \u308a,\u30b3 \u30b9 \u30c8\u306a\u3069 \u3067 \u3042 \u308b\u3002 \u305d \u3057\u3066,\u3053 \u3046\u3057\u305f\u4e8b\u9805 \u304c\u6c7a \u5b9a \u3055\u308c \u305f\u5f8c \u306e\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u306e \u4f5c\u696d \u306f, \u4ee5\u4e0b \u306e\u901a \u308a\u3067 \u3042 \u308b.\n1.\u30df \u30c3\u30b7 \u30e7\u30f3\u306b \u3088\u3063\u3066 \u6c7a\u3081 \u3089\u308c \u308b\u642d\u8f09 \u30df \u30c3\u30b7 \u30e7\u30f3\u6a5f \u5668 \u306b\u4f9d\n\u5b58 \u3057\u3066,\u885b \u661f \u306e\u5916 \u5f62 \u3092\u4eee\u5b9a \u3059 \u308b.\n2.\u30df \u30c3\u30b7 \u30e7\u30f3\u9042\u884c \u306b\u5fc5 \u8981 \u306a\u6a5f \u80fd \u3092\u914d\u5206 \u3057\u3066,\u5404 \u30b3 \u30f3\u30dd\u30fc \u30cd\n\u30f3 \u30c8\u306e \u4ed5\u69d8 \u3092\u6c7a\u5b9a \u3057,\u6a5f \u5668\u5bf8 \u6cd5 \u3092\u4eee \u5b9a\u3059 \u308b.\n3.\u5404 \u30b3 \u30f3\u30dd \u30fc\u30cd \u30f3 \u30c8\u306e \u3046\u3061,\u5168 \u4f53 \u306e\u914d\u7f6e \u306b\u5f71 \u97ff \u3092\u4e0e \u3048 \u308b \u3082\n\u306e \u3092\u7279 \u5b9a\u3059 \u308b.\n4.3\u3067 \u8ff0\u3079 \u3089\u308c\u305f\u6a5f \u5668\u4ee5 \u5916\u306e\u6a5f \u5668\u642d \u8f09\u4f4d\u7f6e \u3092\u6982 \u7565\u6c7a\u5b9a \u3059 \u308b.\n5.\u691c \u8a0e \u306e\u7d50 \u679c,\u6700 \u3082\u9069 \u3057\u3066\u3044 \u308b \u3068\u601d \u308f\u308c \u308b\u521d \u671f \u30ec \u30a4\u30a2 \u30a6 \u30c8\n\u6848 \u3092\u9078\u629e \u3059 \u308b.\n\u3053 \u3046\u3057\u3066,\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u89e3\u304c \u5f97 \u3089\u308c \u305f\u5f8c \u306b\u306f,\u5404 \u6a5f \u5668\u3078 \u306e\u914d \u7dda \u8a2d\u8a08 \u3092\u5b9f \u65bd \u3057,\u7d44 \u7acb \u3066\u9806 \u5e8f,\u63a8 \u9032 \u7cfb\u7d71 \u7ba1 \u3068\u306e\u5e72 \u6e09\u3084 \u5404 \u30b3 \u30f3\u30dd \u30fc \u30cd\u30f3 \u30c8\u3078\u306e \u4f5c\u696d \u8005 \u306e\u63a5 \u8fd1\u6027 \u3092\u78ba \u8a8d\u3059 \u308b \u306a\u3069\u306e \u8a73\u7d30 \u8a2d\u8a08 \u306b\u79fb \u3063\u3066 \u3044 \u304f.\n5.2.2\u5b9f \u65bd\u4f8b \u4fe1 \u983c\u6027\u304c \u6700 \u3082\u91cd \u8981 \u306a\u9805 \u76ee\u3067\u3042 \u308b\u4eba\u5de5 \u885b\u661f \u306b\u304a \u3051 \u308b\u7a7a \u9593\u30c7\u30b6 \u30a4 \u30f3\u306e \u7279\u5fb4 \u3068\u3057\u3066 \u306f,\u642d \u8f09 \u30df\u30c3\u30b7 \u30e7\u30f3\u6a5f \u5668\u4ee5\u5916 \u306e \u30b3\u30f3\u30dd \u30fc\u30cd \u30f3 \u30c8 \u306f,\u307b \u3068\u3093 \u3069\u65e2 \u306b\u4f7f \u7528 \u3055\u308c \u305f\u5b9f\u7e3e \u306e\u3042 \u308b\u6a5f \u5668 \u3092 \u30ab\u30bf \u30ed\u30b0 \u306e \u4e2d\u304b \u3089\u9078 \u629e\u3059 \u308b\u5834 \u5408\u304c \u591a\u3044 \u3053 \u3068\u304c \u6319\u3052 \u3089\u308c \u308b.\u3057 \u304b \u3057,\u3053 \u3046\u3057\u305f\u7279 \u5fb4 \u3092\u6301 \u3064\u4eba \u5de5\u885b \u661f\u306e\u8a2d \u8a08 \u3067\u3042 \u308b\u304c,\u305d \u306e \u30b3\u30f3\u30dd \u30fc \u30cd\u30f3 \u30c8\u306e \u3046\u3061 \u3067 \u3082\u6bd4 \u8f03\u7684 \u5f62\u72b6 \u306e \u81ea\u7531\u5ea6 \u306e\u9ad8 \u3044,\u3064 \u307e \u308a\u65b0\u898f \u306b \u5f62\u72b6 \u306e\u8a2d\u8a08 \u3092\u884c\n\u3046\u5834 \u5408\u304c \u591a \u3044 \u3082\u306e \u3068 \u3057\u3066\u71c3\u6599 \u30bf\u30f3 \u30af\u304c \u3042 \u308b.\u3053 \u308c \u306f,\u5404 \u4eba\u5de5 \u885b\n\u661f \u3092\u65b0 \u898f \u306b\u8a2d\u8a08 \u3059 \u308b\u5834\u5408 \u306b \u305d\u306e\u90fd \u5ea6\u8a2d \u8a08\u3059 \u308b\u3053 \u3068\u304c \u591a \u304f,\u3053 \u306e \u3053 \u3068\u306b\u3088\u308b\u4fe1\u983c \u6027\u3078 \u306e\u5f71 \u97ff\u304c \u6bd4\u8f03 \u7684\u5c11 \u306a\u3044 \u3082\u308a\u3067 \u3042 \u308b.\u3088 \u3063\u3066, \u3053 \u3053\u3067 \u306f\u5404 \u30b3\u30f3\u30dd\u30fc \u30cd \u30f3 \u30c8\u306e \u914d\u7f6e \u30b9\u30da \u30fc\u30b9 \u306e\u6982\u5f62 \u3068\u305d\u306e\u914d \u7f6e \u3092\n\u6c42 \u3081,\u3053 \u308c \u3089\u306e \u30b3\u30f3\u30dd \u30fc \u30cd \u30f3 \u30c8\u306e\u914d \u7f6e \u30b9\u30da \u30fc\u30b9 \u3068\u8981\u6c42 \u3055\u308c \u3066 \u3044 \u308b\u71c3 \u6599 \u306e\u5bb9\u91cf \u304b \u3089\u642d\u8f09 \u3059 \u308b\u71c3\u6599 \u30bf\u30f3 \u30af\u306e\u6982\u7565 \u5f62\u72b6 \u3092\u6c42\u3081 \u308b\u5834 \u5408 \u306e \u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u3092\u5b9f \u65bd\u4f8b \u3068\u3059 \u308b.\u307e \u305f,\u30df \u30c3\u30b7 \u30e7\u30f3\u304a \u3088\u3073 \u6253 \u3061 \u4e0a\u3052 \u30ed\u30b1 \u30c3 \u30c8\u306e\u30da \u30a4\u30ed\u30fc \u30c9\u306b \u3088 \u308a\u4eee \u5b9a \u3055\u308c \u305f\u885b \u661f \u306e\u5916\u5f62 \u306f\u56f315 \u306b\u793a \u3059 \u3068\u304a \u308a\u3067 \u3042 \u308b.\n\u5e7e\u4f55 \u5b66 \u7684\u5236 \u7d04\n\u3053\u306e\u5b9f \u65bd \u4f8b \u306b\u304a\u3051 \u308b\u5e7e \u4f55 \u5b66\u7684 \u5236\u7d04 \u306f ,\u5177 \u4f53 \u7684 \u306b\u306f11\u500b \u306e \u4e3b \u8981 \u30b3 \u30f3\u30dd\u30fc \u30cd \u30f3 \u30c8\u306b \u3064\u3044\u3066 \u306f \u5404\u5fc5\u8981 \u8a2d\u7f6e \u30b9\u30da \u30fc \u30b9\u3067\u3042 \u308a,\u71c3 \u6599 \u30bf\u30f3 \u30af\u306b\u3064 \u3044\u3066 \u306f\u4f53\u7a4d(\u71c3 \u6599\u306e \u5bb9\u91cf)\u3067 \u3042 \u308b.\u4ee5 \u4e0b \u306b,\u4f8b \u3068 \u3057 \u3066\u71c3 \u6599 \u30bf \u30f3 \u30af,\u96fb \u5727\u5b89 \u5b9a\u88c5 \u7f6e \u304a \u3088\u3073 \u30d0 \u30c3\u30c6 \u30ea\u306b\u3064 \u3044 \u3066\u306e\u5236 \u7d04 \u3092\n\u793a\u3059.\n\u71c3 \u6599 \u30bf\u30f3 \u30af(\u5bb9 \u91cf)1Ol \u96fb\u5727 \u5b89\u5b9a \u88c5\u7f6e40.0\u00d730.0\u00d730.Ocm \u30d0 \u30c3\u30c6 \u30ea .50.0\u00d730.0\u00d740.Ocm\n\u7a7a \u9593 \u914d\u7f6e \u5236\u7d04\n\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u306f,\u4ee5 \u4e0b \u306b\u793a \u3059 \u3088 \u3046\u306a\u4e3b \u8981 \u30b3 \u30f3\u30dd\u30fc \u30cd\u30f3 \u30c8\u9593\u306b\n\u6c42 \u3081 \u3089\u308c \u308b,\u914d \u7f6e \u306b\u95a2\u3059 \u308b\u5236\u7d04 \u3067 \u3042 \u308b.\n\u25cf\u901a \u4fe1 \u7cfb \u2190 \u2192 \u96fb \u6e90 \u7cfb \u306f \u8fd1 \u304f\u306b(\u30b3 \u30fc \u30c9\u306f \u306a \u308b\u3079 \u304f\u77ed \u304f\n\u3059 \u308b)\n\u25cf\u96fb\u6e90 \u7cfb \u2190 \u2192 \u71c3\u6599 \u30bf\u30f3 \u30af\u306f\u8fd1 \u304f\u306b(\u96fb \u6e90\u7cfb\u304c \u767a \u3059 \u308b\u71b1 \u306b\n\u3088\u308b\u71c3\u6599 \u306e \u51cd \u7d50\u9632 \u6b62\u306e \u305f \u3081)\n\u25cf\u540c \u3058\u7cfb\u7d71 \u306e \u3082\u306e\u306f\u8fd1 \u304f\u306b(\u63a5 \u7d9a \u30b1\u30fc\u30d6 \u30eb\u3092\u77ed \u304f\u3059 \u308b\u305f\u3081)\n\u25cf\u4eba\u5de5\u885b \u661f \u306e\u5730 \u7403\u9762 \u304a \u3088\u3073 \u30df\u30c3\u30b7 \u30e7\u30f3\u6a5f\u5668 \u3092\u642d\u8f09 \u3059 \u308b\u9762 \u306b\n\u306f,\u96fb \u6e90\u7cfb \u304a \u3088\u3073 \u59ff \u52e2\u5236 \u5fa1\u7cfb \u306a\u3069\u306e \u767a\u71b1 \u3059 \u308b\u6a5f \u5668 \u306f\u914d\u7f6e \u3067 \u304d\u306a \u3044(\u653e \u71b1 \u9762 \u3068\u3057\u3066\u9069 \u3057\u3066 \u3044 \u306a \u3044\u305f\u3081)\n\u4ee5\u4e0a \u306e\u6761 \u4ef6 \u3092\u4e0e \u3048 \u3089\u308c \u305f \u5f8c,\u4e0a \u8ff0 \u3057\u305f\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u306e\u4f5c \u696d\u5185\n\u5bb9 \u306b\u5f93 \u3063\u3066\u7a7a \u9593 \u30c7 \u30b6 \u30a4\u30f3 \u3092\u9032 \u3081 \u308b.\n\u521d \u671f \u30ec \u30a4\u30a2 \u30a6 \u30c8\u6848 \u3092\u9078\u629e \u3059 \u308b\n\u5e7e\u4f55 \u5b66\u7684 \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066,\u6a5f \u80fd\u8981 \u7d20\u306e\u6982 \u7565 \u5f62\u72b6 \u3092\u6c42 \u3081\u305f\n\u5f8c,\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088 \u3063\u3066,\u8981 \u6c42 \u3055\u308c \u305f \u30b3\u30f3\u30dd \u30fc\u30cd \u30f3 \u30c8 \u306e\u7a7a \u9593\u914d\u7f6e \u306e \u6982\u7565 \u3092\u751f\u6210 \u3059 \u308b.\u56f316\u306f \u305d\u306e \u7a7a \u9593\u914d\u7f6e \u30bd\u30eb\u30d0 \u306e \u51fa\u529b \u89e3\u306e \u5177\u4f53 \u4f8b \u3067\u3042 \u308b.\u76f4 \u7dda \u3067\u7d50\u3070 \u308c \u3066 \u3044 \u308b\u6a5f \u80fd\u8981 \u7d20 \u306f\u305d\u308c\u305e \u308c \u306b\u76f8 \u5bfe \u7684\u4f4d \u7f6e \u306e\u5236 \u7d04\u95a2 \u4fc2\u304c \u3042 \u308b \u3053 \u3068\u3092\u793a \u3057\u3066 \u3044 \u308b.\nsolver\n\u7d9a \u3044 \u3066,\u5e7e \u4f55\u5b66 \u7684\u5236 \u7d04 \u30bd\u30eb\u30d0 \u3068\u7a7a \u9593\u914d\u7f6e \u30bd\u30eb\u30d0 \u306b \u3088\u308b\u6982 \u7565\u306e \u8a2d\u8a08 \u89e3 \u306e\u77db\u76fe \u70b9 \u3092\u8abf \u6574\u3059 \u308b \u3053 \u3068\u306b \u3088\u3063\u3066\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3\u306e \u751f\u6210 \u3092\u8a66 \u307f \u308b.\u56f317\u306b \u305d \u306e\u904e \u7a0b \u3092\u793a \u3059.\u3053 \u306e \u9593 \u306b,\u5e72 \u6e09 \u3057\u305f \u30b3 \u30f3 \u30dd\u30fc \u30cd \u30f3 \u30c8\u306e\u914d \u7f6e \u30b9\u30da \u30fc \u30b9\u306e\u5f62 \u72b6 \u751f\u6210 \u30eb \u30fc\u30eb\u304c \u5909\u66f4 \u3055\u308c,\u305d \u308c \u3068\u540c\u6642 \u306b\u5f62 \u72b6 \u306e \u4e2d\u5fc3 \u4f4d \u7f6e \u306e\u79fb \u52d5 \u304c\u884c \u308f\u308c \u308b.\u5177 \u4f53 \u7684\u306b \u306f,3 .2 \u7bc0 \u306b \u304a\u3044 \u3066\u8ff0\u3079 \u305f \u751f\u6210 \u30eb \u30fc\u30eb\u306e\u7f6e \u304d\u63db \u3048\u306b \u3088\u308b\u5e72\u6e09\u89e3 \u6d88\u306e\u6226 \u7565 \u3092(1),(2),(3)\u306e \u9806 \u306b\u3059 \u3079 \u3066 \u8a66 \u307f,\u540c \u6642 \u306b\u5e72 \u6e09 \u3057\u305f\u90e8 \u5206 \u306e\u4f53 \u7a4d \u306b\u5f93 \u3063\u3066 \u4e2d\u5fc3\u4f4d \u7f6e\u304c \u79fb \u52d5 \u3055\u308c \u305f.\n\u3053\u306e \u3088 \u3046\u306b \u3057\u3066,\u7a7a \u9593 \u30c7 \u30b6 \u30a4\u30f3\u306e2\u3064 \u306e \u5074\u9762 \u306b \u3064\u3044 \u3066 \u540c\u6642\n\u306b\u8abf\u6574 \u3057\u306a\u304c \u3089\u5f62\u72b6 \u3092\u751f\u6210 \u3055\u305b,\u305d \u306e \u751f \u6210\u304c \u7d42\u4e86 \u3057\u305f\u6bb5 \u968e\u3067 \u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u3092\u5f97 \u308b.\u56f318\u306b,\u305d \u306e\u751f \u6210\u89e3 \u306e\u6c34 \u5e73 \u65b9\u5411 \u306e\u65ad \u9762 \u3068\u5782 \u76f4\u65b9 \u5411 \u306e\u65ad \u9762 \u3092\u793a \u3057,\u6c42 \u3081 \u308b\u71c3 \u6599 \u30bf \u30f3 \u30af\u306e\u6982 \u5f62 \u3092 \u56f319\u306b \u793a \u3059.\n530\u7cbe \u5bc6 \u5de5\u5b66 \u4f1a\u8a8cVol,65,No.4,1999", + "\u6b21 \u306b,\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8\u304c \u793a \u3057\u305f,\u4ed6 \u306e\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u306e \u30d0 \u30ea\u30a8 \u30fc \u30b7 \u30e7\u30f3\u306b\u3064 \u3044 \u3066,\u56f320\u306b \u65ad\u9762 \u56f3 \u3092\u793a \u3059.\u3053 \u3053\u3067 \u6bd4 \u8f03\u306e \u305f\u3081,\u5404 \u7a7a\u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u306b\u304a\u3051 \u308b\u305d \u308c\u305e \u308c\u306e \u5236\u7d04 \u306b\u5bfe \u3059 \u308b \u8a55\u4fa1 \u5024,\u304a \u3088\u3073\u71c3 \u6599 \u30bf\u30f3 \u30af\u306e\u7e26,\u6a2a,\u9ad8 \u3055\u306e\u6700 \u5927 \u5024 \u306b\u95a2 \u3059 \u308b\u6570 \u5024 \u3092\u88682\u306b \u793a\u3059.\n\u3053\u306e \u3088 \u3046\u306b \u3057\u3066\u5f97 \u3089\u308c \u305f\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u6848 \u306f,\u56f3 \u306b\u793a \u3057\u305f \u3088 \u3046\n\u306b,\u591a \u69d8 \u306a\u521d\u671f \u30ec \u30a4\u30a2\u30a6 \u30c8\u6848 \u3092\u751f \u6210 \u3057\u3066 \u3044 \u308b\u3053 \u3068\u304c \u89b3 \u5bdf \u3055\u308c \u308b. \u307e\u305f,\u71c3 \u6599 \u30bf\u30f3 \u30af\u306e\u5f62 \u72b6 \u306b \u304a\u3044 \u3066 \u3082,\u8981 \u6c42 \u3055\u308c \u305f\u5bb9\u91cf \u3092\u6301 \u3061, \u4ed6 \u306e \u30b3 \u30f3\u30dd\u30fc \u30cd \u30f3 \u30c8\u306e\u914d \u7f6e \u30b9\u30da \u30fc\u30b9 \u3068\u5e72\u6e09 \u3057\u306a\u3044\u5f62 \u72b6\u304c \u6c42 \u3081 \u3089 \u308c \u3066 \u3044 \u308b.\u305d \u3057\u3066,\u751f \u6210 \u3055\u308c \u305f\u71c3 \u6599 \u30bf\u30f3 \u30af\u306f\u5236 \u7d04 \u3068\u3057\u3066\u4e0e \u3048 \u3089 \u308c \u305f\u5bb9 \u91cf \u3092\u304a \u304a \u3080\u306d\u6e80 \u305f \u3057,\u304b \u3064 \u591a\u69d8 \u306a\u5f62 \u72b6 \u3092 \u3057\u3066\u3044 \u308b \u3053 \u3068\u304c \u78ba \u8a8d\u3067 \u304d\u308b.\u3057 \u304b \u3057,\u4e00 \u65b9\u3067\u71c3 \u6599 \u30bf\u30f3 \u30af\u306e\u5185 \u90e8\u5727 \u529b \u3092\u8003\u616e \u3057\u305f \u5834 \u5408 \u306b \u9069\u5f53 \u3067 \u306a\u3044 \u3088 \u3046\u306a\u5f62\u72b6 \u3082\u751f \u6210 \u3055\u308c \u3066 \u3044 \u308b.\n\u8a2d \u8a08 \u8005\u306f,\u3053 \u3046\u3057\u305f\u591a\u69d8 \u306a\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u3092\u691c \u8a0e \u3057\u305f\u5f8c,\u4ed6\n\u306e\u5236 \u7d04 \u306a\u3069 \u3092\u8003\u616e \u306b\u5165\u308c,\u9069 \u5f53\u306a \u3082\u306e \u3068\u8003 \u3048 \u3089\u308c \u308b\u89e3 \u3092\u9078\u629e \u3057,\n\u8a73 \u7d30\u8a2d \u8a08\u3078 \u3068\u79fb \u884c\u3059 \u308b.\n\u672c\u8ad6\u6587\u3067\u306f,\u7a7a \u9593\u30c7\u30b6\u30a4\u30f3\u306e2\u3064 \u306e\u5074\u9762\u3067\u3042\u308b,\u6a5f \u80fd\u8981\u7d20 \u306e3\u6b21 \u5143\u5f62\u72b6\u3068,\u305d \u306e\u7a7a\u9593\u7684\u914d\u7f6e\u3092\u540c\u3058\u67a0\u7d44\u306e\u4e2d\u3067\u6c7a\u5b9a\u3059\u308b \u305f\u3081\u306b,\u5f62 \u72b6\u8868\u73fe\u306b\u591a\u69d8\u6027\u3092\u6301\u305f\u305b\u305f\u9069\u5fdc\u6210\u9577\u578b\u5f62\u72b6\u8868\u73fe\u65b9\u6cd5 \u3092\u63d0\u6848\u3057\u305f.\u305d \u3057\u3066,\u672c \u5f62\u72b6\u8868\u73fe\u3092\u5fdc\u7528\u3057\u305f\u7a7a\u9593\u30c7\u30b6 \u30a4\u30f3\u306e\u652f \u63f4\u30b7\u30b9\u30c6\u30e0\u3092\u4f5c\u6210\u3057,\u4eba \u5de5\u885b\u661f\u8a2d\u8a08\u306b\u304a\u3051\u308b\u7a7a\u9593\u30c7\u30b6\u30a4\u30f3\u3092\u884c \u3044,\u6a5f \u80fd\u8981\u7d20\u306e3\u6b21 \u5143\u5f62\u72b6\u3068,\u305d \u306e\u7a7a\u9593\u7684\u914d\u7f6e\u3092\u540c\u3058\u67a0\u7d44\u306e\n\u4e2d\u3067\u6c7a\u5b9a\u3059\u308b\u65b9\u6cd5\u306e\u5b9f\u65bd\u4f8b\u3092\u793a\u3057\u305f.\u305d \u306e\u7d50\u679c,3\u6b21 \u5143\u5f62\u72b6 \u3068 \u7a7a\u9593\u7684\u914d\u7f6e\u304c\u540c\u3058\u67a0\u7d44\u306e\u4e2d\u3067\u53d6 \u308a\u6271\u3048,\u307e \u305f\u591a\u69d8\u306a\u7a7a\u9593\u30c7\u30b6\u30a4 \u30f3\u89e3\u304c\u5f97\u3089\u308c\u308b\u3053\u3068\u3092\u53ef\u80fd\u3068\u3057\u305f\u305f\u3081,\u672c \u65b9\u6cd5\u8ad6\u306e\u6709\u52b9\u6027\u304c\u793a \u3055\u308c\u305f.\n\u307e\u305f,\u4eca \u5f8c\u306e\u7814\u7a76\u306e\u8ab2\u984c\u3068\u3057\u3066\u306f\u4ee5\u4e0b\u306e\u3053\u3068\u304c\u8003\u3048\u3089\u308c\u308b.\n\u25cf\u751f\u7269\u306b\u6bd4\u8f03\u3057\u305f\u5834\u5408\u306e,\u3055 \u3089\u306a\u308b\u9069\u5fdc\u6210\u9577\u578b\u5f62\u72b6\u8868\u73fe\u306e\n\u9069\u5fdc\u6027\n\u25cf\u81ea\u5f8b\u7684\u306b\u5f62\u72b6\u306e\u4f4d\u7f6e\u3092\u79fb\u52d5\u3055\u305b\u308b\u3053\u3068\u306b\u3088\u308b,3\u3064 \u306e\u7a7a\n\u9593\u30c7\u30b6\u30a4\u30f3\u30bd\u30eb\u30d0\u306e\u7d71\u5408\n\u25cf\u672c\u65b9\u6cd5\u8ad6\u306e\u7406\u8ad6\u7684\u7acb\u5834\u304b\u3089\u306e\u8a73\u7d30\u306a\u691c\u8a0e\n\u53c2 \u8003 \u6587 \u732e\n1) R. Smith, S. Warrington and F. Mill: Shape Representation for Optimization, Proc. 1st IEE/IEEE Int. Conf. Genetic Algorithms in Engineering Systems: Innovations and Applications GALESIA '95, Sheffield, England,(1995)112. 2) S. Szykman and J. Cagan: Automated Generation of Optimally Directed Three Dimensional Component Layouts,\nDE-Vol.65-1, In Advances in Design Automation - vol. 1, ASME,(1993).\n3)\u9577 \u5742 \u4e00\u90ce,\u5c71 \u5cb8 \u6df3,\u7530 \u6d66 \u4fca\u6625:\u610f \u5320 \u30c7 \u30b6 \u30a4 \u30f3\u306e\u305f \u3081\u306e3D\u5f62 \u72b6\u30e2\n\u30c7 \u30eb(\u7b2c2\u5831)\u4e00 \u751f\u6210 \u30eb \u30fc\u30eb \u306b\u6ce8 \u76ee\u3057 \u305f\u5f62\u72b6 \u7279 \u5fb4 \u306e\u8868 \u73fe \u6cd5\u4e00,\u7cbe \u5bc6 \u5de5 \u5b66 \u4f1a\u8a8c,63,2,(1997)193.\n4) G. Pahl and W. Beitz: Engineering Design: A Systematic Approach, Springer-Verlag, London,(1988). 5) A. C. Thornton and A. L. Johnson: CADET: A Software Support Tool for Constraint Processes in Embodiment Design, Res. Eng. Design,8,(1996)1. 6) D. E. Goldberg: Genetic Algorithms in Search, Optimization & Machine Learning, Addison-Wesley, Readings,MA(1989). 7) C. Brown: Fast Display of Well-tessellated Surfaces, Computer and Graphics,4,4,(1979)77. 8) S. F. Smith: A Learning System Based on Genetic Algorithms, PhD Dissertation, University of Pittsburgh,(1980).\n9) V. Schnecke and O. Vornberger: A Genetic Algorithm for VLSI Physical Design Automation, Proc. 2nd Int. Conf. Adaptive Computing in Engineering Design and Control, ACEDC '96, University of Plymouth, I. C. Parmee (ed. ),(1996)53.\n\u7cbe \u5bc6 \u5de5 \u5b66 \u4f1a \u8a8cVol,65,No.4,1999 531" + ] + }, + { + "image_filename": "designv8_17_0000334_7_01_eucass9p127.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000334_7_01_eucass9p127.pdf-Figure1-1.png", + "caption": "Figure 1 Reference aircraft CSR-01: (a) wing planform; and (b) 3D model for Tornado [13]", + "texts": [ + " The idea is to \u00a6nd a geometry with minimum weight which achieves the stability constraints imposed by the reference aircraft. These schema could be applied to any unconventional con\u00a6guration; but this paper focuses on V-tail. The aircraft is going to be modeled as a wing and a tail. This decision is based on the fact that the reference wing always is the main wing; and also, some relevant parameters, as volume coe\u00a9cient, need the existence of the main wing in order to be possible to calculate them. Because of all these aspects, the tails are not analyzed in an isolated way. Figure 1 shows the geometry of the main wing of the reference aircraft and the model used. The work may consist of studying all the critical load cases in conventional tails, both HTP (Horizontal Tail Plane) and VTP (Vertical Tail Plane), which will be simulated through an aerodynamic software. These load cases can be summed up as follows [14]: for VTP, critical engine failure, Dutch roll, lateral gusts, yawing manoeuver and minimum control speed at ground; and for HTP, longitudinal gusts, maximum control de\u00a7ection, and pitching manoeuver" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure58-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure58-1.png", + "caption": "Figure 58 P-POD Mk. IV \u201cTuna Can\u201d Pusher Plate", + "texts": [ + " IV sheds much of its mass without losing any of its utility. The only sections of the Pusher Plate that actually saw a significant load were its legs. These were left untouched, but the rest of the entire part Page 72 was shaved down to be very slim, but because the part had a cylinder in the center of it, it still remained very stiff. Additionally, a chamfer was added to the outer edge of the slimmer tuna can wall which proved to completely eliminate the spring catching issue. The resulting re-design is shown below in Figure 58. This design saves 41 grams from the previous Pusher Plate design. The strength was verified by an FEA, subjecting the Pusher Plate to the Z-axis load acting downward on the legs. The margin of safety was slightly reduced from the previous design even though nothing on the load path of the Pusher Plate was changed. This was attributed to thinner structure at the point where the legs meet the rest of the part, causing a loss of stiffness in the corner. This margin of safety reduction from 11.5 to 11" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002707_8948470_09199824.pdf-Figure30-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002707_8948470_09199824.pdf-Figure30-1.png", + "caption": "FIGURE 30. Illustration of the UAV performance filter.", + "texts": [ + " The base of this performance filter is the same as the one of the backup policy (cf. [57]). The desired velocity is altered in a way that slows down convergence to the obstacles when getting close to it, and incentivizes divergence when past the soft margin. However, the closest point considered for the filtering of Vdes is not based on the distance between the current drone position and the obstacles, but the shortest distance between the drone position along the backup trajectory and the obstacles (cf. Fig. 30). Furthermore, the distance to this closest point is the shortest distance between the drone position along the backup trajectory and the obstacles. This way, the performance filter is able to better anticipate incoming obstacles which leads to less intrusions of the backup trajectory into the soft margin, which in turn leads to less interventions of the safety filter. In the end, these 3 components work together to provide a filter withminimal conservativeness andwith guaranteed collision avoidance (cf" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001882_O201336447764690.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001882_O201336447764690.pdf-Figure4-1.png", + "caption": "Figure 4. Schematic diagram of prototype crawler vehicle.", + "texts": [ + " Drawbar pull of the test rubber crawler vehicle was tested by a load cell (allowable load 4.9 kN, CAS Co., Ltd) at the vehicle weight of 5.49 kN. Data were acquired from the load cell by using the equipment DEWE 2010 (DEWETRON GmbH). Figure 3 is the schematic diagram of drawbar pull test of the test rubber crawler vehicle (HC-300C). Field testing of prototype rubber crawler-type vehicle Design of the prototype vehicle The prototype rubber crawler-type vehicle was designed in triangle shape crawler to travel in water contained paddy field with water depth of 0.6 m. Figure 4 shows the schematic diagram of prototype crawler vehicle. Distance between the crawlers of the prototype was determined into 720 mm with its traveling stability Table 3. Specification of the prototype crawler vehicle Parameters Unit Value Sizes of the prototype (LxWxH) mm 2800 x 1040 x 1460 Weight of the prototype(depending on weight) kN 5.59 ~ 9.21 Power of the prototype kW 5.1 Thickness of rubber crawler mm 20 Ground contact length of rubber crawler mm 900 Width of rubber crawler mm 180 Lug height of rubber crawler mm 15 Front height of rubber crawler mm 303 Rear height of rubber crawler mm 240 Front-end inclination of rubber crawler \u00b0 45 Rear-end inclination of rubber crawler \u00b0 45 Lug pitch of rubber crawler mm 65 Ground contact area of rubber crawlers m2 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003195_load.php_id_23121402-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003195_load.php_id_23121402-Figure2-1.png", + "caption": "FIGURE 2. Basic connection types. (a) Straight connection. (b) Crisscross connection.", + "texts": [ + " The width of the ground plane is symmetrically tapered by quarter circles of radius R between the parallel-coupled lines and the microstrip line to achieve the transition. Furthermore, the microstrip line ground functions as a reflector. A transition structure from a microstrip line to CPW line is introduced in the feed line section 56 www.jpier.org to facilitate testing or packaging of the antenna with GroundSignal-Ground (GSG) probes. Typically, there are two basic connection types for feeding the elements of a log-periodic dipole array, as shown in Fig. 2 [17]. Fig. 2(a) illustrates the straight feed with close spacing and phase alignment, which potentially reduces the difficulty of the antenna design and fabrication. However, this configuration can introduce detrimental interference effects due to phase progression, which can distort the radiation pattern. To address this issue, as shown in Fig. 2(b), a 180-degree phase inversion at the end of each element is employed, which is achieved by mechanically alternating the feed between adjacent elements. This strategy effectively reduces energy emission from short, adjacent elements, thereby improving the radiation pattern clarity and efficiency. However, it introduces design complexities that require complicated feedline transpositions, potentially increasing cost and maintenance. In addition, the specificity of phase relationships and element spacing can limit flexibility in array configuration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure3-1.png", + "caption": "Fig. 3, A generic, simplified problem for illustration purposes", + "texts": [ + " A modified version of this idea in Catia v5 is the so called \u201cRigid Spring\u201d virtual part where the stiffness of the ignored portion can be specified as a spring in series, with the truly rigid part. Such an element is graphically depicted in Fig.2. The configuration on the left refers to a \u201cRigid\u201d virtual part whereas the one on the right corresponds to a \u201cRigid Spring\u201d virtual part. The stiffness of the resulting spring needs to be estimated which can be done in relatively straightforward situations such as a one-dimensional geometry, under axial, bending, and torsional loading. To be more specific, the simple estimates based on elementary strength of material formulas are shown in Fig. 3. This figure is only for illustrative purposes. The variables \u201cG\u201d and \u201cE\u201d are the shear and Young\u2019s modulus respectively, whereas, \u201cJ\u201d and \u201cI\u201d are the polar and bending moments of area. Furthermore, \u201cA\u201d is the cross sectional area. If the length of the virtual part is represented by \u201cLVP\u201d, and the left end of the part is clamped, the important stiffnesses are given by the following expressions: 16th LACCEI International Multi-Conference for Engineering, Education, and Technology: \u201cInnovation in Education and Inclusion\u201d, 19-21 July 2018, Lima, Peru", + " The axial stiffness of this spring is calculated based on half the length of the virtual part, ie 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 = 25 \ud835\udc5a\ud835\udc5a . The rationale behind using 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 has to do with the fact that the mass of the virtual part is represented by a lumped value at the centroidal location. The exact location of the handler point should be taken into account when the stiffness of VP is calculated. In our analysis, because the lumped mass is placed at the centroid, the stiffness is calculated as shown below \ud835\udc58\ud835\udc49\ud835\udc43 = \ud835\udc34\ud835\udc38 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 = 8\ud835\udc38 + 8 \ud835\udc41/\ud835\udc5a . This value based on the direction shown in Fig. 3, should be inputted as depicted below. 16th LACCEI International Multi-Conference for Engineering, Education, and Technology: \u201cInnovation in Education and Inclusion\u201d, 19-21 July 2018, Lima, Peru. The calculated first three natural frequencies associated with the axial vibration using the \u201cRigid Spring\u201d virtual part are given in the Table II below. Note that the second column entries are the same theoretical values displayed in Table I, namely theoretical formula presented earlier (length of the bar being \ud835\udc3f = \ud835\udc3f\ud835\udc40\ud835\udc43 + \ud835\udc3f\ud835\udc49\ud835\udc43 = 150 \ud835\udc5a\ud835\udc5a) " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure59-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure59-1.png", + "caption": "Figure 59 P-POD Mk. IV Final Design Assembly", + "texts": [ + " An investigation and Page 74 redesign of the hinge could improve the strength of the Door and bring it up to the strength of the rest of the P-POD. Additionally, looking at an alternative access port design without the flange and gasket groove could provide even further mass savings. For some missions that mount high quantities of deployers (8-16), 100 grams per P-POD is a substantial mass difference, and if EMI is not needed it is a waste of mass to incorporate the EMI access port covers, as there is really no structural reason for having such strong access port covers. A CAD assembly of the final P-POD Mk. IV design is shown below in Figure 59. Page 75 CHAPTER V: ENVIRONMENTAL QUALIFICATION AND EMI TESTING P-PODs are subject to significant random vibration and thermal loads during launch. Everytime a new P-POD is going to fly on a launch vehicle, an engineering unit has to be put through a qualification program consisting of severe random vibration levels and extreme temperature cycling. Launch vehicle providers determine both the vibration and thermal maximum predicted environments (MPE) at the P-POD to LV interface. These environments are then used to derive qualification levels" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000174_f_version_1641029125-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000174_f_version_1641029125-Figure9-1.png", + "caption": "Figure 9. Excitation pattern and flux-path of the short-pitched winding 3 in Design B; (a) Phase A is excited; (b) Phase B is excited; and (c) Phase C is excited.", + "texts": [ + " Although the short-pitched winding 3 gives a better performance for 12/8 SRM, the number of flux reversals of this winding configuration is still high. This paper proposes an analysis method that can reduce the flux reversals on the stator yoke. The short-pitched winding 3 is divided into Design A and Design B as follows: \u2022 In Design A, as shown in Figure 8, the sequential magnetic poles in a clockwise direction are SNSN when excited phase A, NSNS when excited phase B, and NSNS when excited phase C. \u2022 In Design B, as shown in Figure 9, the sequential magnetic poles in a clockwise direction are SNSN when excited phase A, NSNS when excited phase B, and SNSN when excited phase C. The number of flux reversals in each segment of the stator yoke in the clockwise (A\u2013B\u2013 C\u2013A) and counter-clockwise (A\u2013C\u2013B\u2013A) direction of Design A is illustrated in Table 9. To calculate the total number of flux reversals in one revolution, Equation (10) is used. The total number of flux reversals on the yoke of the stator is 192 in both directions (clockwise and counter\u2013clockwise)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000193_f_2017_cy_c7cy01537b-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000193_f_2017_cy_c7cy01537b-Figure2-1.png", + "caption": "Fig. 2 Pictures of a WLE (a) and a coated WLE (b) and schematic view of the WLE and coating (c).", + "texts": [ + " in fixed-bed or fluidized-bed systems by simply extending the reactor using a transmitting inductor (cf. Fig. 1). For these reasons, we developed photocatalyst-coated WLEs with a diameter of 1 cm which serve as a completely integrated, wirelessly powered catalyst system for heterogeneous photocatalytic reactions. The easy usability of this system is subsequently demonstrated for a variety of photocatalytic reactions. Each WLE consists of a receiving circuit and a UVA-LED (365 nm emission), which are housed in a spherical shell (cf. Fig. 2). As the shell material, a polymer is preferable since it can be easily processed using injection molding which facilitates mass production at very competitive prices.32 Transparent photocatalytic active coatings on polymers such as polycarbonate are also well known for the removal of pollutants.33\u201335 Unfortunately, many polymers are not UV-transparent and thus unsuitable for this application. Therefore, a high-performance UV-transparent cyclic olefin polymer (COP) was chosen as a shell material" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004908_24_TSP_CMC_27124.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004908_24_TSP_CMC_27124.pdf-Figure1-1.png", + "caption": "Figure 1: Prone view of four ridge waveguide", + "texts": [ + " Based on the above analysis, this paper will combine with the advantages of slot antenna and aperture antenna, use multimode waveguide cavity structure to design an aperture antenna, which is fed to waveguide circular polarizer by slot coupling in order to realize circular polarization radiation. Meanwhile, it has the characteristics of broadband, broadband beam, wide axial ratio bandwidth and high radiation efficiency. Circularly polarized waves are synthesized by two orthogonal linearly polarized waves with equal amplitudes and 90\u00b0 phase difference. For the four-ridge waveguide circular polarizer, when the electromagnetic wave E1 (or E2) is excited by a 45\u00b0 angle waveguide with the ridge, as shown in Fig. 1, it can be decomposed into two equal amplitude and phase orthogonal polarization components Ex and Ey, where Ex is parallel to the vertical ridge and Ey is parallel to the horizontal ridge. When Ex and Ey pass through the ridge waveguide region of the circular polarizer, due to the different size of the vertical ridge and the horizontal ridge, two phase constants are generated for the two orthogonal polarization components TE1 and TE01 modes, respectively. When passing through a certain length L, a 90\u00b0 phase difference is generated, forming a circular polarization wave, that is, \u2205 = ( \u03b2x \u2212 \u03b2y ) \u00d7 L = 90\u25e6 (1) According to the microwave theory, in the waveguide system, the phase constant satisfies the following equation : \u03b2 = 2\u03c0 \u03bb [ 1 \u2212 ( \u03bb \u03bbcr )2 ]\u22121/2 (2) Among them, \u03bb is the wavelength in free space and \u03bbcr is the cutoff wavelength of waveguide" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002483_ees-2020-20-2-91.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002483_ees-2020-20-2-91.pdf-Figure8-1.png", + "caption": "Fig. 8. The fabricated dual-band dual-mode filter.", + "texts": [ + "1 dB while the measured minimum insertion losses are \u20131.86 dB and \u20132.32 dB. Three transmission zeros with frequency locations of 1.23 GHz, 1.53 GHz, and 2.01 GHz can be clearly observed, providing sharp band-toband rejection. The slight discrepancy in these results is attributed to fabrication tolerance as well as the SMA connectors which were not considered in the simulation. The existence of insertion loss is mainly due to conductor and dielectric circuit losses and could be improved by more careful fabrication and better measurement technology. Fig. 8 presents the fabricated dual-band dualmode filter. We have proposed a novel dual-band dual-mode BPF using a ring resonator with non-uniform linewidth. The operating principles of the proposed filter are presented above, and the nonuniform linewidth of the ring is created by off-setting the patch and hole centers. The proposed filter is characteristically dualmode; inductors and capacitors are applied to the gap, causing the filter to operate in two different bands. In addition, the frequency ratio of the proposed filter can be adjusted from 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003303_download_25868_15461-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003303_download_25868_15461-Figure4-1.png", + "caption": "Figure 4. Magnetic flux density contour plot", + "texts": [ + " The efficiency of CMG can be expressed as (7): \u03b7 = \ud835\udf0f\ud835\udc5c\ud835\udf14\ud835\udc5c \ud835\udf0f\ud835\udc56\ud835\udf14\ud835\udc56 (7) where \u03b7 is the CMG efficiency, \u03c4o and \u03c4i is the average torque at the inner rotor and outer rotor, \u03c9i and \u03c9o is the rotational speed of the inner rotor and outer rotor. Eddy current loss produced by the PM and iron loss produced by the magnetic material can be extracted directly from the simulation [16]. The evaluation steps can be simplified as in Figure 2. ISSN: 2088-8708 Int J Elec & Comp Eng, Vol. 12, No. 2, April 2022: 1161-1167 1164 The torque waveform shown in Figure 3 is measured for 0.06 seconds which is equivalent to the \u00bc of a full rotation of the inner rotor. The magnetic flux density contour plot is shown in Figure 4. The iron loss at the magnetic materials, eddy current loss at PM and distribution of all the losses in percentage were illustrated in Figures 5, 6 and 7 respectively. The average value at inner and outer torque were 64.19 N.m and 167.08 N.m respectively. From these values, gear efficiency yield 0.97 or 97%. Torque ripple at the inner rotor is slightly higher, 18% compares to the outer rotor, 0.15%. The bar graph in Figure 5 shows that the ferromagnetic pole piece produced the highest iron loss of 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001765_8948470_09166481.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001765_8948470_09166481.pdf-Figure2-1.png", + "caption": "FIGURE 2. Isometric view. (a) Solid cylindrical stacked DRs (b) Perforated stacked DRs.", + "texts": [ + " These three different permittivity cylindrical dielectric resonators were stacked in the order of their permittivity to achieve wide bandwidth antenna is proposed. The lowest permittivity, \u03b5r1 = 3.38 (DR1) dielectric pellet was loaded directly on top of resonating slot, followed by medium permittivity, \u03b5r2 = 4.55 (DR2) and high permittivity dielectric resonators, \u03b5r3 = 10.2 (DR3). However, the input impedance of the structure does not match enough and need to be improved further to enhance the bandwidth of the antenna. The cylindrical stacked DRs is drilled using CNC machine to introduce air inside the DRs as shown in Figure 2. The existence of air will reduce the effective permittivity of the DRs and improve the bandwidth of the antenna. C. DETERMINATION OF THE DIAMETER OF STACKED CYLINDRICAL DRS The diameter, d of stacked DRs can be determined using Equation (4). The stacked DRs are made from the standard dielectric material of available substrates in, RT/Duroid 4003 with the permittivity \u03b5r1 = 3.38 and thickness Hd1 = 0.813 mm, FR4 with permittivity \u03b5r2 = 4.55 and thickness Hd2 = 1.6 mm and RT/Duroid 6010 with the permittivity \u03b5r3 = 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure41-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure41-1.png", + "caption": "Figure 41 Side Panel FEA Results", + "texts": [ + " Page 57 Like the Bottom Panel, mounting flexibility is reduced, but in the long run, utilizing one mounting pattern can help reduce recurring engineering costs and provide a well known standardized mounting pattern. Aside from the mass reduction and access port mounting method, the side panel remains largely unchanged. An FEA was conducted to confirm the Side Panel\u2019s structural integrity, and it exhibited a high margin of safety of 6.4. A symmetric constraint was used to reduce solving time and all panel-topanel were assumed to be fixed. The X-axis load case described above was applied to the side panel rails. The resulting stress plot is shown below in Figure 41. The maximum stress was located near the fixed boundary constraint, and was well within acceptable levels. So far, all parts have exhibited extremely high margins. This is because of certain Page 58 containment requirements, along with mounting interfaces that make the part more robust than it needs to be for the loads themselves. P-POD Mk. IV Back Plate The next part analyzed was the Back Plate, that makes up the \u2013Z face of the P- POD. In the past, this part was strengthened due to concerns with the screw interfaces having high stress concentrations, making the exterior walls thicker and taller, and adding more screws" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003712__publico_Achiles.pdf-Figure4.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003712__publico_Achiles.pdf-Figure4.11-1.png", + "caption": "Figure 4.11 (a) and (b) show the normalized dissipated power density ( \ud835\udc37\ud835\udefc = \ud835\udc580 2 \ud835\udf152\ud835\udc43\ud835\udefc \ud835\udf15\ud835\udc58\ud835\udc65\ud835\udf15\ud835\udc58\ud835\udc66\u2044 ) for perpendicular and parallel polarizations, respectively, with p chosen", + "texts": [ + " 3D-FDTD simulations of the total power radiated to the far field by the perpendicular dipole for f=30% (circles), 49% (squares) and 70% (triangles). 4.3. OPTIMIZATION AND ANALYSIS 85 so that the dipole radiates 1 W in free space. According to (4.12), the perpendicular dipole emits only p-polarized waves whose amplitudes depend on k\u2225. It should be noted that without the grating this dependence would have produced circles in the Dz map. However, according to (4.24), (4.37) and (4.38), the grating changes the waves\u2019 momenta causing the dependence of k\u2225 to be changed to kx and ky and therefore deforming these circles, as shown in Figure 4.11 (a). As mentioned before, the bottom HMM layers are mainly responsible for wave reflection, therefore the Dz map deformations are small and the circles\u2019 pattern can still be seen in Figure 4.11 (a). In addition, the power is dissipated inside the circle k\u2225/k0 <10, which is the region where the medium behaves as a HMM (see Fig. 2 (b)). The parallel polarized dipole radiates TE and TM waves which are proportional to k\u2225, but modulated by sin(\u03c8) and cos(\u03c8), respectively (\ud835\udf13 = atan(\ud835\udc58\ud835\udc66 \ud835\udc58\ud835\udc65\u2044 )). Since only TM modes couple to the HMM, the Dx map also presents deformed circles modulated by cos(\u03c8), as can be seen in Figure 4.11 (b). Figure 4.10. Normalized Poynting vector of a perpendicularly (a) and parallel (d) polarized dipole placed at q=10nm. Normalized electric fields emitted by a perpendicularly (b,c) and parallel (e,f) polarized dipole decomposed in p- (b,e) and s-polarization (c,f). CHAPTER 4 - DESIGN AND ANALYSIS OF GRATING-ASSISTED RADIATION EMISSION OF QE IN HMM 86 Next, we calculate P\u03b1 and the normalized radiated power (\ud835\udef9\ud835\udefc 3\ud835\udc37=Q\u03b1/W0) as functions of \u0394x, \u0394y, and q. Figure 4.12 (a) and (c) show \ud835\udef9\ud835\udefc 3\ud835\udc37 for perpendicular and parallel polarizations, respectively, at q = 10 nm", + "10 (a,c), the dipole dissipates more power for perpendicular polarization due to the strong coupling to TM bulk modes. As a result, the Purcell factor at any position is higher for this orientation, as shown in Figure 4.12 (b,d). For instance, at q=10nm and \u0394y=\u0394x=0, Pz=145 and Px=62. Similarly to the 2D case, P\u03b1 and Q\u03b1 is higher for dipoles closer to the HMM surface, but it exponentially decays as the separation increases due to evanescent coupling to TM bulk modes. In summary, our approach allows both P\u03b1 and Figure 4.11. Normalized dissipated power of a perpendicularly (a) and parallel (b) polarized dipole placed at q = 10nm. Figure 4.12. Normalized radiated power (a,c) and Purcell factor (b,d) of a perpendicularly (a,b) and parallel (c,d) polarized dipole as function of its position variation x and y at q = 10nm. The solid black line in (a-d) represents the periodic array of nano-cylinders edges. 4.4. COMPARISON BETWEEN HMM WITH AND WITHOUT METALLIC GRATINGS 87 \u03a8\ud835\udefc 3\ud835\udc37to be mapped as function of the dipole\u2019s position", + " 3D-FDTD simulations of the total power radiated to the far field by the perpendicular dipole for f=30% (circles), 49% (squares) and 70% (triangles). ................................................................................................... 84 Figure 4.10. Normalized Poynting vector of a perpendicularly (a) and parallel (d) polarized dipole placed at q=10nm. Normalized electric fields emitted by a perpendicularly (b,c) and parallel (e,f) polarized dipole decomposed in p- (b,e) and s-polarization (c,f). ..................................... 85 Figure 4.11. Normalized dissipated power of a perpendicularly (a) and parallel (b) polarized dipole placed at q = 10nm. ....................................................... 86 Figure 4.12. Normalized radiated power (a,c) and Purcell factor (b,d) of a perpendicularly (a,b) and parallel (c,d) polarized dipole as function of its position variation x and y at q = 10nm. The solid black line in (a-d) represents the periodic array of nano-cylinders edges. ............... 86 LIST OF FIGURES 163 Figure 4.13. Effective Purcell factor (a,c,e) and quantum efficiency (b,d,f) for HMM_opt (squares) and HMM_ch3 (circles) considering scenarios I (a,b), II (c,d) and III (e,f)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003921_3272-021-00517-7.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003921_3272-021-00517-7.pdf-Figure5-1.png", + "caption": "Fig. 5 Inlet and outlet stations for measurement", + "texts": [ + " A standard inlet, in accordance with standard ISO 5801 [15], is used to determine the air mass flow through the engine. The ISO standard defines relevant design aspects, which have been considered during construction phase, as well as guidelines for taking measurements and postprocessing results. Measured quantities are not only used to check the engine\u2019s behavior, but are also taken as input parameters for numerical studies with ANSYS CFX, defining relevant boundary conditions. For this purpose, static pressure is measured across both, inlet and outlet stations of the engine. Figure\u00a05 indicates these inlet and outlet stations and provides some additional information about their axial position. In addition to the two aforementioned static pressures, the total pressure across the inlet is an important boundary condition for numerical investigations. To complete the set of boundary conditions, environmental pressure and temperature are measured. Since there is no 1 3 inflow velocity, these static conditions are afterwards taken as the reference stagnation conditions for CFD simulations", + " According to the related data sheet, each sensor is expected to provide a maximum offset of 1%. During preparation process, each pressure sensor is calibrated for its relevant effective range using a pressure calibrator. Again, these offset values are recorded and submitted to our measurement software. Our results of the calibration procedure confirm there indeed is a constant offset for each sensor, but always within the tolerated range according to the specifications. Measuring static pressures is relevant for the inlet and outlet stations according to Fig.\u00a05. At the corresponding axial stations, there is a number of circumferentially uniformly distributed pressure holes. Inlet pressure is taken by four holes, outlet pressure by six holes. For both stations, static pressure is physically averaged across all circumferential holes by a circular pneumatic tube. As we mentioned earlier, there is no need for an exact time-resolved pressure signal and thus we extend the pneumatic tubes between pressure hole and sensor to a few meters of length. By this means, the tubing physically damps pressure fluctuations from disturbances or similar and we receive a more smooth signal readout", + " Comparing full simulation and single blade passage results, for example, by considering static pressure values, reveals only small discrepancies. Therefore, possibly distorted results appear to be negligible and remaining operation points are investigated by simulating a single passage, as depicted in Fig.\u00a011. The details are discussed in the following section. As a start, Fig.\u00a011 intends to provide an overview of a blade passage domain, consisting of four axially aligned sub domains. The flow enters the domain through the interface marked as \u201cInlet\u201d, which is identical to the inlet station as defined in Fig.\u00a05. The same applies to the outlet station, where the fluid exits the entire domain. Boundary layers are geometrically resolved using prism layers. Turbulence is mathematically modeled by applying the sst-model. To simplify the numeric setup, turbulent inflow conditions are selected. Hence, possible laminar separation bubbles cannot be modeled. However, these are not within the primary focus of this study. For the inlet boundary, total pressure and total temperature are prescribed, based on environmental conditions during experiments" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002320_ejjia_9_2_9_201__pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002320_ejjia_9_2_9_201__pdf-Figure7-1.png", + "caption": "Fig. 7. Magnetic curcuit of developed model.", + "texts": [ + " 6, only 1/6 minute was modeled in the circumferential direction, and only 1/9 minute, which corresponds to one period, was modeled in the axial direction, and period conditions were set accordingly. Therefore, the characteristics occurring at the motor end have been ignored. The comparison model is an SPM structure with conventional magnet arrangement, and the NS poles periodically arranged in the axial and circumferential directions. The number of poles and the pitch of the magnetic poles as well as the armature and applied current are the same in the comparison model and in the developed model using the proposed magnet arrangement. Figure 7 shows the configuration of the magnetic pole of the developed model and the magnetization direction of each permanent magnet. The magnetic pole is composed mainly of a bulk iron core with isotropic magnetic properties, which is treated as the core and permanent magnets are placed on 5 surfaces, except on the surface facing the armature. Magnetization is set to take place in the axial direction of each named magnet so that the direction of magnetization of each permanent magnet is perpendicular to the surface of the center core with which it is in contact", + " Therefore, selecting a combination of the number of poles of permanent magnets and the number of armature slots armature slots in such a manner that their greatest common divisor becomes large as in the case of a conventional SPM motor (2) may be effective in suppressing fluctuation. Next, in order to ascertain the contribution of each permanent magnet to the thrust, we constructed three models, each having a magnetic pole that was composed of only one of the permanent magnets p, z, and r (see Fig. 13). Table 2 shows the average thrust obtained from the analysis, the maximum number of flux linkages assuming a magnetic circuit similar to that shown in Fig. 7 and the percentage contributed by the permanent magnet to the volume of the magnetic pole for each model, when the applied current is NI = 1200 [A Turn]. The average thrust is in all cases normalized by the average thrust of only the permanent magnet z, and the maximum number of flux linkages and the volume of the permanent magnet are also normalized by the corresponding values of the permanent magnet z. The contribution to the thrust was approximately the same as the number of flux linkages derived from each permanent magnet" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002506_.srce.hr_file_390601-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002506_.srce.hr_file_390601-Figure8-1.png", + "caption": "Figure 8 RobotStudio software - view of robot paths", + "texts": [ + " One of the tools that makes this possible is the ForceControl application, in which the robot's movements are adapted to feedback from force sensors. In the solution proposed by the authors, the FC Pressure option was used. On the basis of a series of test works, a solution was proposed in which a fixed tool was used, and the object reference system (WorkObject) associated with the robot's arm was mobile. The robot's IRC5 software along with the set trajectories of motion were created in the RobotStudio program (Fig. 8). The use of the force control approach allows the trajectory to adapt to the variable shape of the workpiece. An advantage of the proposed approach is the reduction of the level of interference generated by the electro-spindle motor. When the rotating tool is on the robot arm, the force sensor registers the force value with interferences resulting from dynamic phenomena related to the movement of the tool [29]. The hierarchical control structure shown in Fig. 9 was applied. The low-level controller uses a standard commercial solution based on the \"FC pressure\" strategy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001055_f_version_1698309724-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001055_f_version_1698309724-Figure10-1.png", + "caption": "Figure 10. Experimental device for measuring force and torque.", + "texts": [ + " This comparison enables the quantification of the accuracy improvement achieved by utilizing the proposed model, which incorporates the non-linear effects existing in the system. Through this verification process, the proposed model has been proven to have superior accuracy and fidelity compared to traditional harmonic models. This validation provides confidence in the proposed model\u2019s ability to accurately predict the behavior of the planar motor, enabling effective design and control strategies. To validate the accuracy of the proposed model, an experimental setup, depicted in Figure 10, is utilized for measurement and verification purposes. The setup consists of a four-degree-of-freedom motion platform capable of movement in the x, y and z directions, as well as rotation around the z-axis within the xy plane. Beneath the moving stage, a sixaxis force and torque sensor is fixed to measure the forces and torques exerted on the translator. The connection between the Halbach array and the sensor is established through a 3D-printed fixture, with the fixture height set at 100 mm, to ensure torque measurement 100 mm above the Halbach array" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002105_783_77_783_4144__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002105_783_77_783_4144__pdf-Figure1-1.png", + "caption": "Fig. 1 Electrode structure of the transducer Fig. 2 Mode shapes", + "texts": [], + "surrounding_texts": [ + "\u65e5\u672c\u6a5f\u68b0\u5b66\u4f1a\u8ad6\u6587\u96c6\uff08C\u7de8\uff09 \u539f\u8457\u8ad6\u6587 No.2011-JCR-0277\n\u00a92011 The Japan Society of Mechanical Engineers\n\u9ad8\u91ce \u660c\u5b8f*1\uff0c\u5ee3\u5d0e \u61b2\u4e00*2\uff0c\u6edd\u672c \u5e79\u592b*3\uff0c\u5e02\u6751 \u609f*4\uff0c\u4e2d\u6751 \u5065\u592a\u90ce*5\nHolding and Preloading Mechanism Using a Buckling Parallel Leaf Spring\nfor Ultrasonic Linear Motor\nMasahiro TAKANO *1 , Kenichi HIROSAKI, Mikio TAKIMOTO, Satoru ICHIMURA\nand Kentaro NAKAMURA\n*1 Industrial Research Institute of Ishikawa\n2-1 Kuratsuki, Kanazawa, Ishikawa, 920-8203 Japan\nTo increase the applicability of ultrasonic linear motors, we have developed a holding mechanism for the transducer using parallel leaf springs. The present mechanism is compact since the parallel leaf spring structure has functions for both holding and preloading at the same time. Also, a special design for the spring characteristics provides a non-linear load-displacement region with buckling phenomena. These results in a constant preload for some range of the displacement, then the motor performance does not alter even after abrasion of contact surfaces. In this report, the relationship between the dimension of the leaf spring and the force-displacement curves was investigated in order to obtain the design appropriate for constant preloading. Moreover, the effect of the vibration reduction by the holding mechanism was investigated theoretically and experimentally. The vibration reduction was as small as less than 10 % since the stiffness in terms of the vibration direction was relatively small. Finally, the dynamic responses of the motor with the holding mechanism were measured for a sinusoidal control signal. No prominent peak was observed in the motor\u2019s responses, however, the motor velocity change was distorted near the natural frequency of the holding mechanism.\nKey Words : Ultrasonic Motor, Linear Motor, Multilayered Transducer, Holding Mechanism, Leaf Spring, Buckling\n1. \u7dd2 \u8a00\n\u8d85\u97f3\u6ce2\u30e2\u30fc\u30bf\u306f\uff0c\u96fb\u78c1\u30e2\u30fc\u30bf\u3068\u306f\u7570\u306a\u308b\u99c6\u52d5\u539f\u7406\u3067\u3042\u308b\u3053\u3068\u304b\u3089\uff0c\u4f4e\u901f\u9ad8\u30c8\u30eb\u30af\uff0c\u4e0d\u8981\u306a\u767a\u751f\u97f3\u304c\u5c0f\u3055\u3044\uff0c\u505c \u6b62\u6642\u306b\u4fdd\u6301\u529b\u304c\u4f5c\u7528\u3059\u308b\u306a\u3069\u306e\u512a\u308c\u305f\u7279\u5fb4\u304c\u3042\u308b\uff0e\u7279\u306b\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306f\uff0c\u30dc\u30fc\u30eb\u306d\u3058\u306a\u3069\u306e\u4f1d\u9054\u6a5f\u69cb\u304c\u4e0d 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\u72b6\u3067\u3042\u308b\u3053\u3068\u304b\u3089\uff0c\u5c0f\u578b\u5316\u3084\u4f4e\u30b3\u30b9\u30c8\u5316\u306b\u6709\u5229\u306a\u69cb\u9020\u3068\u3044\u3048\u308b\uff0e\u7b46\u8005\u3089\u306f\uff0c\u3053\u308c\u307e\u3067\uff0c\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306e\u5236 \u5fa1\u6027\u3092\u6539\u5584\u3059\u308b\u3053\u3068\u3092\u76ee\u7684\u306b\u7e26\u30fb\u5c48\u66f2\u72ec\u7acb\u52b1\u632f\u96fb\u6975\u3092\u6709\u3059\u308b\u5e73\u677f\u578b\u7a4d\u5c64\u632f\u52d5\u5b50\u306e\u958b\u767a\u3092\u884c\u3063\u3066\u304d\u305f(7)(8)\uff0e\u3053\u306e\u632f\u52d5 \u5b50\u306f\u7e26 1\u6b21\u632f\u52d5\u3068\u5c48\u66f2 2\u6b21\u632f\u52d5\u3092\u72ec\u7acb\u306b\u52b1\u632f\u53ef\u80fd\u3067\u3042\u308a\uff0c\u5404\u632f\u52d5\u30e2\u30fc\u30c9\u306e\u632f\u52d5\u632f\u5e45\uff0c\u4f4d\u76f8\u5dee\u3092\u9069\u6b63\u306a\u72b6\u614b\u3067\u99c6\u52d5 \u3059\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u8d85\u97f3\u6ce2\u30e2\u30fc\u30bf\u306e\u5236\u5fa1\u6027\u3092\u6539\u5584\u3067\u304d\u308b\u3053\u3068\u3092\u5831\u544a\u3057\u305f(9)(10)\uff0e\n\u5ea7\u5c48\u5e73\u884c\u677f\u3070\u306d\u3092\u7528\u3044\u305f\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306e\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\uff0a\n* \u539f\u7a3f\u53d7\u4ed8 2011 \u5e74 3 \u6708 30 \u65e5 *1 \u6b63\u54e1\uff0c\u77f3\u5ddd\u770c\u5de5\u696d\u8a66\u9a13\u5834\uff08\u3012920-8203 \u77f3\u5ddd\u770c\u91d1\u6ca2\u5e02\u978d\u6708 2-1\uff09 *2 \u77f3\u5ddd\u770c\u5de5\u696d\u8a66\u9a13\u5834 *3 \u30cb\u30c3\u30b3\u30fc\uff08\u682a\uff09 *4 \u30b7\u30b0\u30de\u5149\u6a5f\uff08\u682a\uff09 *5 \u6b63\u54e1\uff0c\u6771\u4eac\u5de5\u696d\u5927\u5b66\u7cbe\u5bc6\u5de5\u5b66\u7814\u7a76\u6240 E-mail: takano@irii.jp\n77 \u5dfb 783 \u53f7 \uff082011-11\uff09\n4144\n\u2015 184 \u2015", + "\u5ea7\u5c48\u5e73\u884c\u677f\u3070\u306d\u3092\u7528\u3044\u305f\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306e\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\n\u00a92011 The Japan Society of Mechanical Engineers\n\u3053\u308c\u3089\u306e\u5e73\u677f\u72b6\u632f\u52d5\u5b50\u306f\uff0c\u632f\u52d5\u5b50\u81ea\u4f53\u306f\u5358\u7d14\u306a\u69cb\u9020\u3067\u3042\u308b\u304c\uff0c\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u3068\u3057\u3066\u7528\u3044\u308b\u5834\u5408\uff0c\u3053\u306e\u632f \u52d5\u5b50\u3092\u4fdd\u6301\u3057\uff0c\u304b\u3064\u632f\u52d5\u5b50\u3092\u30b9\u30e9\u30a4\u30c0\u306b\u52a0\u5727\u30fb\u63a5\u89e6\u3055\u305b\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e\u5f93\u6765\u306e\u4fdd\u6301\u65b9\u6cd5\u3068\u3057\u3066\u306f\uff0c\u632f\u52d5\u5b50\u306e\u632f\u52d5 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3\u306b\u672c\u30e2\u30fc\u30bf\u306e\u69cb\u6210\u3092\u793a\u3059\uff0eL1\u30e2\u30fc\u30c9\u306f\uff0c\u6469\u64e6\u30d8\u30c3\u30c9\u306e\u52a0\u5727\u65b9 \u5411\u306e\u632f\u52d5\u3092\u767a\u751f\u3059\u308b\u30e2\u30fc\u30c9\u3067\u3042\u308a\uff0c\u52a0\u5727\u529b\u3092\u5c48\u66f2\u632f\u52d5\uff08B2\u30e2\u30fc\u30c9\uff09\u3068\u540c\u671f\u3057\u3066\u5909\u5316\u3055\u305b\u308b\u3053\u3068\u3067\u6469\u64e6\u529b\u306e\u5236\u5fa1\u3092 \u884c\u3046\u632f\u52d5\u6210\u5206\u3067\u3042\u308b\uff0eB2\u30e2\u30fc\u30c9\u306f\u30b9\u30e9\u30a4\u30c0\u306e\u9001\u308a\u65b9\u5411\u306e\u632f\u52d5\u6210\u5206\u3092\u6301\u3064\u30e2\u30fc\u30c9\u3067\u3042\u308a\uff0c\u52d5\u529b\u6e90\u306b\u4f7f\u7528\u3055\u308c\u308b\uff0e\u672c \u632f\u52d5\u5b50\u306f\uff0c\u3053\u306e L1\u30e2\u30fc\u30c9\u3068 B2\u30e2\u30fc\u30c9\u3092\u5225\u3005\u306e\u96fb\u6975\u306b\u3088\u308a\u72ec\u7acb\u306b\u5236\u5fa1\u3067\u304d\u308b\u3053\u3068\u304c\u7279\u5fb4\u3067\u3042\u308b\uff0e\n4145\n\u2015 185 \u2015", + "\u5ea7\u5c48\u5e73\u884c\u677f\u3070\u306d\u3092\u7528\u3044\u305f\u8d85\u97f3\u6ce2\u30ea\u30cb\u30a2\u30e2\u30fc\u30bf\u306e\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\n\u00a92011 The Japan Society of Mechanical Engineers\nLeaf spring\nFriction head\nTransducer\nCase\nLeaf spring\nAdhesion\nAdhesion\nFig. 4 Holding and preloading mechanism\n\u8d85\u97f3\u6ce2\u30e2\u30fc\u30bf\u3067\u306f\uff0c\u632f\u52d5\u5b50\u3092\u5b89\u5b9a\u306b\uff0c\u304b\u3064\u4e00\u5b9a\u306e\u52a0\u5727\u529b\u3067\u30b9\u30e9\u30a4\u30c0\u306a\u3069\u306e\u79fb\u52d5\u4f53\u306b\u52a0\u5727\u63a5\u89e6\u3055\u305b\u305f\u72b6\u614b\u3067\u4fdd\u6301 \u3059\u308b\u6a5f\u69cb\u304c\u5fc5\u8981\u3068\u306a\u308b\uff0e\u56f3 4\u306b\u63d0\u6848\u3057\u305f\u672c\u632f\u52d5\u5b50\u306e\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\u3092\u793a\u3059\uff0e\u540c\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\u306f 2\u3064\u306e\u677f\u3070\u306d\u304c\u4e0a\u4e0b\u306b\u914d\u7f6e\u3055\u308c\u305f\u5e73\u884c\u677f\u3070\u306d\u69cb\u9020\u3068\u306a\u3063\u3066\u3044\u308b\uff0e\u677f\u3070\u306d\u306f\uff0c\u3070\u306d\u7528\u30b9\u30c6\u30f3\u30ec\u30b9\u92fc\uff08SUS301SEH\uff09 \u3092\u7528\u3044\u3066\u8a66\u4f5c\u3057\uff0c\u632f\u52d5\u5b50\u3068\u306e\u63a5\u7740\u306f\uff0c\u71b1\u786c\u5316\u578b\u30a8\u30dd\u30ad\u30b7\u7cfb\u63a5\u7740\u5264\u3092\u7528\u3044\u3066\u884c\u3063\u305f\uff0e\u632f\u52d5\u5b50\u3068\u677f\u3070\u306d\u306f\uff0c\u5c48\u66f2 2\u6b21 \u632f\u52d5\u30e2\u30fc\u30c9\u306e\u7bc0\u306e\u7b87\u6240\u3067\u63a5\u7740\u3055\u308c\u3066\u304a\u308a\uff0c\u677f\u3070\u306d\u306e\u4e21\u7aef\u90e8\u306f\u30b1\u30fc\u30b9\u306b\u56fa\u5b9a\u3055\u308c\u308b\uff0e\u677f\u3070\u306d\u306e\u5f62\u72b6\u306f\u5358\u7d14\u306a\u76f4\u7dda\u3067 \u306f\u7121\u304f\uff0c\u308f\u305a\u304b\u306b\u632f\u52d5\u5b50\u5148\u7aef\u65b9\u5411\u306b\u30aa\u30d5\u30bb\u30c3\u30c8\u3057\u305f\u66f2\u7dda\u5f62\u72b6\u3068\u306a\u3063\u3066\u3044\u308b\uff0e\u3053\u308c\u306b\u3088\u308a\u632f\u52d5\u5b50\u304c\u62bc\u8fbc\u307e\u308c\u305f\u3068\u304d\uff0c \u677f\u3070\u306d\u306b\u5ea7\u5c48\u73fe\u8c61\u304c\u751f\u3058\u308b\u305f\u3081\uff0c\u52a0\u5727\u65b9\u5411\u306e\u3070\u306d\u7279\u6027\u306f\u975e\u7dda\u5f62\u6027\u3092\u6709\u3059\u308b\u3053\u3068\u306b\u306a\u308b\uff0e\u3053\u306e\u73fe\u8c61\u3092\u5229\u7528\u3057\uff0c\u3070\u306d \u306e\u5f62\u72b6\u3092\u9069\u6b63\u306b\u8a2d\u8a08\u3059\u308c\u3070\uff0c\u3042\u308b\u9818\u57df\u3067\u5909\u4f4d\u306b\u5bfe\u3057\u3066\u52a0\u5727\u529b\u304c\u307b\u3068\u3093\u3069\u5909\u5316\u3057\u306a\u3044\u3070\u306d\u7279\u6027\u3092\u5f97\u308b\u3053\u3068\u304c\u3067\u304d\u308b\uff0e \u3086\u3048\u306b\u6469\u8017\u3084\u30bb\u30c3\u30c6\u30a3\u30f3\u30b0\u306a\u3069\u3067\u62bc\u8fbc\u307f\u91cf\u304c\u591a\u5c11\u5909\u5316\u3057\u3066\u3082\u5b89\u5b9a\u3057\u305f\u52a0\u5727\u529b\u3092\u7dad\u6301\u3059\u308b\u3053\u3068\u304c\u671f\u5f85\u3067\u304d\u308b\uff0e\u307e\u305f\uff0c \u5e73\u884c\u677f\u3070\u306d\u69cb\u9020\u306e\u305f\u3081\uff0c\u525b\u6027\u306e\u7570\u65b9\u6027\u304c\u3042\u308a\uff0c\u79fb\u52d5\u4f53\u304c\u79fb\u52d5\u3059\u308b\u65b9\u5411\uff08\u9001\u308a\u65b9\u5411\uff09\u306e\u525b\u6027\u3092\u6bd4\u8f03\u7684\u5927\u304d\u304f\u3059\u308b\u3053 \u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u3055\u3089\u306b\uff0c\u672c\u6a5f\u69cb\u306f\uff0c\u4fdd\u6301\u6a5f\u80fd\u3068\u52a0\u5727\u6a5f\u80fd\u3092\u4e00\u4f53\u5316\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u30ac\u30a4\u30c9\u306a\u3069\u306e\u90e8\u54c1\u304c\u7121\u304f\u30b3\u30f3 \u30d1\u30af\u30c8\u5316\u304c\u6bd4\u8f03\u7684\u5bb9\u6613\u3067\u3042\u308b\uff0e\n3. \u3070\u306d\u7279\u6027\n\u4fdd\u6301\u30fb\u52a0\u5727\u6a5f\u69cb\u306e\u3070\u306d\u7279\u6027\u3068\u3057\u3066\u306f\uff0c\u52a0\u5727\u529b\u306e\u5909\u5316\u304c\u751f\u3058\u306a\u3044\u3088\u3046\u306b\u3059\u308b\u305f\u3081\uff0c\u8377\u91cd\u304c\u4e00\u5b9a\u306b\u306a\u308b\u9818\u57df\u306f\uff0c\u3067 \u304d\u308b\u3060\u3051\u5927\u304d\u3044\u65b9\u304c\u671b\u307e\u3057\u3044\uff0e\u8377\u91cd\u304c\u4e00\u5b9a\u306b\u306a\u308b\u73fe\u8c61\u306f\uff0c\u5ea7\u5c48\u306e\u5f71\u97ff\u3068\u66f2\u3052\u525b\u6027\u306e\u5f71\u97ff\u306e\u30d0\u30e9\u30f3\u30b9\u306b\u3088\u3063\u3066\u751f\u3058\n4146\n\u2015 186 \u2015" + ] + }, + { + "image_filename": "designv8_17_0003501_f_version_1658412706-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003501_f_version_1658412706-Figure12-1.png", + "caption": "Figure 12. Working path.", + "texts": [ + " When agricultural machinery operates in the process of autonomous navigation, it needs to complete the actions of straight-line path tracking, headland turning, U-turn, etc., so as to complete the tracking of the entire working path. For this reason, in the process of autonomous navigation of agricultural machinery, the ground spraying work can be evenly completed to ensure a complete coverage area, and the specific working path needs to be planned in combination with the bow turning method. The working path is shown in Figure 12, in which the headland turning radius section R1 = R2 = 5 m, and the U-turn transition section L = 4 m. This working path can meet the needs of agricultural machinery autonomous navigation work. Machines 2022, 10, x FOR PEER REVIEW 12 of 21 3.4. Work Path Planning In this paper, the agricultural machinery is mainly designed and developed according to the working requirements of the plant protection machine, and its autonomous navigation working path is planned according to the walking path requirements of the plant protection machine when it is working", + " When agricultural machinery operates in the process of autonomous navigation, it needs to complete the actions of straight-line path tracking, headland turning, U-turn, etc., so as to complete the tracking of the entire working path. For this reason, in the process of autonomous navigation of agricultural machinery, the ground spraying work can be evenly completed to ensure a complete coverage area, and the specific working path needs to be planned in combination with the bow turning method. The working path is shown in Figure 12, in which the headland turning radius section R1 = R2 = 5 m, and the U-turn transition section L = 4 m. This working path can meet the needs of agricultural machinery autonomous navigation work. Figure 12. Working path. 3.5. Analysis of Simulation Results The initial position of the proposed vehicle is (0, 0), and the initial heading angle is set to 90\u00b0. Use different forward-looking distances to track the reference working path, and obtain the data of path tracking, lateral deviation change, and front-wheel turning angle change during vehicle driving. The simulation data based on the pure tracking algorithm based on fuzzy control and the traditional pure tracking algorithm are compared, and the error changes are analyzed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003997_e_download_7367_3540-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003997_e_download_7367_3540-Figure6-1.png", + "caption": "Figure 6. Effect of dynamic weight on tractor wheel pedestal area [13]", + "texts": [ + " Because the truck is not pulling the load then DBP = 0, so Fh - R = 0, or Fh=R (2) Thus the truck can move forward if: \u03a3 Fh \u2265R (3) The weight of the tractor used will directly affect the amount of rolling resistance which is estimated to be proportional to the dynamic weight on the cogs, so that: R = CR.W (4) Where CR = coefficient of rolling resistance, with the values as shown in Figure 5, W = dynamic weight on the wheel drive (kg). In an effort to increase traction on a tractor, the maximum shear force under the wheels (Fh max) (kg) equals maximum wheel traction (Hmax) (kg) Fh max = Hmax = 0.78.b.l.C + W tan \u03c6 (5) Where C is the soil cohesion (kg/cm2), b is the width of the track (cm), l is the length of the track in contact with the soil (cm) as in Figure 6, and \u03c6 is the internal friction angle. The designed tools had to increase the tractor wheels in wet soil condition, especially clay, were carried out by increasing the area of the tangents of the wheels to the ground. As the value of b and l increases, the value of traction automatically increases. The situation is done by using a steel wheel or a cage wheel [14], as shown in Figure 6. For CDD type trucks or 1.2 L (medium) trucks has load distribution on the front wheels (34%) and rear wheels (66%), as shown in Figure 7. Soil cohesion value (C) and soil internal friction angle (\u03c6) Oil palm transport trucks experience such skidding because they have to cross over the wet ground. The slippage occurs due to the soil undergoes such deformation or changes in shape due to the internal tensile forces between particles or soil cohesion that were not strong enough to withstand the shear loads when the movement of truck wheels", + " Dimension of U channel steel SNI 07- 0052-2006 in (mm) [21] Code h (cm) z (cm) U50 5 3.8 U65 6.5 4.2 U75 7.5 4 U80 8 4.5 U100 10 5 U120 12 5.5 U125 12.5 6.5 U140 14 6 U150 15 7.5 Refers to the Equation (5), the value of z is determined based on the dimensions of the two sides of the U channel steel in Table 3 and three sizes are selected at once namely U50, U65, and U80 with each side dimension or fin depth (z) 3.8, 4.2 and 4.5 cm. The truck wheel diameter (d) of 81.6 cm is used as a reference to scatter the projections of the fulcrum with the ground (l) (Figure 6). The numerical results by using Solidworks software from all fins (z) 3.8 cm on U50 steel obtained the length of the track in contact with the soil (l), which 36.03 cm based on the design sketch as in Figure 3 (a) is then shown in Figure 11. With the same step fin depth calculation, the length of the track in contact with the soil (l) is then obtained for the sketch design of the U65 and U80 dimensions. The results are shown in Table 4. Table 4. The results of the length of the track in contact with the soil U Channel Steel z (cm) l (cm) U50 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000838_NGU05_2021_Fomin.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000838_NGU05_2021_Fomin.pdf-Figure4-1.png", + "caption": "Fig. 4. The spatial model of a Y25 bogie", + "texts": [ + " The input parameters of the model were the technical characteristics of the carrying structure of a car with the design and actual dimensions, the spring suspension of the bogies, and the disturbing force (Table 2) [12]. The actual dimensions of the carrying structure of a boxcar were determined through the field tests. An 11217 boxcar manufactured by AO Altaivagon (Fig. 3) was used for the research as a predominant freight car type in Ukraine. The inertia coefficients of the Y25 bogie were determined by means of a spatial model in the Pro/e software complex (Fig. 4). The motion equation for the design model is as follows Table 1 The basic technical characteristics of the Y25 bogie Parameter Dimension Value Mass ton 4.9 (\u00b1 5 %) Track mm 1435 Bogie base mm 1800 Wheel diameter, (max/min) mm 920/840 Distance between the rail head and the center of the pivotal spherical center plate at a car weight of 20 tons mm 790 Cross gaps in the axlebox guides mm 2 \u00d7 10 Maximum axle load tons per axle 22.5 Speed of a freight car at an axle load of 22.5 tons per axle km per hour 100 Speed of a freight car at an axle load of 20" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004977__067_ecp09430117.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004977__067_ecp09430117.pdf-Figure5-1.png", + "caption": "Figure 5: thermal resistance in a radial conduction on a plane", + "texts": [ + " This produces a need to include the heat transfer from the surfaces in the simulation. In the DYMOLA thermal library, there is no mean to calculate the heat transfer on a 2D surface. We have introduced two plane models with the ability to calculate the heat transfer between the connectors\u2019 positions in relation to the position of the connectors. The first option to calculate the thermal properties on the plane and between different points which will be represented by the connectors, we will use the concept of the radial heat conduction on a disc [15] fig.5. Although this method is simple to calculate and use, it would be applicable only if the surface could be supposed unlimited due to the dimensions of the r1 and r2. The other option is to use the equivalent electrical network [16] fig.6, which represent the system with the system with the thermal resistances and capacitors which can be simulated as an electrical network. To simplify the models in the first stage of modeling procedure we suppose the problem as a steady state situation so that we can neglect the C" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000927_.5_0_2010.5_653__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000927_.5_0_2010.5_653__pdf-Figure8-1.png", + "caption": "Fig. 8 Motion without load", + "texts": [ + " The sudden acceleration is difficult because of the inertia of the mechanism. Therefore, preparation motion was inserted 30[msec] before the contact moment. PID control was used to follow the trajectory. The gain was determined by Ziegler-Nichols tuning method and 655 NII-Electronic Library Service Upper Links (l1) Lower Links (l1) Motor Rotary Encoder PulleysTiming Belt Gears for Symetric Shape l2 l3 Reduction Gear Fig. 7 A mechanical model of landing gear with parallel links manual fine tuning. The motion of the leg model and the angle is shown in Fig.8 and Fig.9 respectively. The graph shows the measured joint angle follows the target trajectory. 5\u00b73 SHOCK ABSORPTION IN LANDING The acceleration of soft landing of the one leg model was measured. The photo of exmerimental apparatus is shown in Fig.11. The leg model moves perpendicularly along the linear guide (curtain rail) constraining the rotation. There is a limit switch to detect the timing of the begining of falling. The signal of the switch can be used as a cue of the motion. The height of the model, that can be measured by sensors like GPS or LRF, is used for control before falling" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure11-1.png", + "caption": "Figure 11. Transducer calibration, (a) Fx, (b) Mx.", + "texts": [ + " Therefore, the newly-developed construction was subjected to a complete process of identification of the calibration matrix. The process was performed by single value loading of an object with force and torque of predetermined value in the chosen direction, so that other components were eliminated. To this end, a specially designed test stand in the form of a durable table with an extended frame comprising a number of longitudinal members and cross members supported on stable columns was used (Figure 11). The tabletop had numerous fixation holes enabling free and stable positioning of the calibrated transducer. For the performance of excitations, tension screws with integrated single axis force sensors were used. The calibration concept of the developed transducer construction was presented in Figure 12. The calibration procedure involves three stages, two of which pertain to the identification of force coefficients along the main default Y, Z axes and a single stage pertaining to the identification of coefficients related to the torque about the X axis" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000056_tation-pdf-url_54247-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000056_tation-pdf-url_54247-Figure9-1.png", + "caption": "Figure 9. Step-descending model of a five-wheeled wheelchair.", + "texts": [ + " Design conditions for descending a 100 mm step Physical Disabilities - Therapeutic Implications34 condition for the wheelchair is to maintain the center of gravity not to go beyond the step edge. The condition is represented by a coordinate of the wheelchair along X-axis, x g as, x g \u2007=\u2007R cos \u03b8 \u2212 L l cos \u03b8 l \u2007\u2264\u20070 (8) where, R is a radius of the large wheel, L l is the length between the drive wheel and the center of gravity, and \u03b8 l is the angle between the line L l and the X w axis as shown in Figure 9. To satisfy the conditions derived above, we determined the parameters of link mechanism for a prototype wheelchair as shown in Table 1. Five-Wheeled Wheelchair with an Add-On Mechanism and Its Semiautomatic... http://dx.doi.org/10.5772/67558 35 By using these parameters, we calculated the motion of the link mechanism. According to the change in the length of link AB, we plotted the trajectories of the points A, C, and D of the proposed mechanism by using Eqs. (4)\u2013(6). The result is shown in Figure 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004977__067_ecp09430117.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004977__067_ecp09430117.pdf-Figure7-1.png", + "caption": "Figure 7: plane thermal model represented by the thermal resistance network concept", + "texts": [ + " The other option is to use the equivalent electrical network [16] fig.6, which represent the system with the system with the thermal resistances and capacitors which can be simulated as an electrical network. To simplify the models in the first stage of modeling procedure we suppose the problem as a steady state situation so that we can neglect the C. This will simplify our plane thermal model to a model which has been divided by the smaller cubes which each will be represented by their thermal resistances. Fig. 7 These two thermal models can be used for modeling the plane model including its geometrical equations in DYMOLA. Once the mathematical equations and relations of the models have been extracted the models and the modeling procedure can be introduced. This new modeling method will need a new library which includes the electrical components presented with the new concept, and new components which will serve as the environment of the electronic circuit or the surfaces on which it will be installed. All of these new models ought to include the multi-domain models, properties and connectors inside them" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002718_3452-020-00107-0.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002718_3452-020-00107-0.pdf-Figure10-1.png", + "caption": "Fig. 10 Distribution of the critical strain (a) and recrystallized volume fraction (b) in the 3rd pass for bainitic steel", + "texts": [ + " Contrary, the microstructure evolution is noticeably different, due to high-temperature dynamic recrystallization dominated in the break down passes for both steels. Figures\u00a09 and 10 shows distributions of the critical strain and dynamically recrystallized volume fraction in the 3rd pass for pearlitic and bainitic steels, respectively. Results show that DRX was completed for the pearlitic steel (Fig.\u00a09b) while in bainitic steel only a small volume of metal recrystallized according to dynamic mechanism (Fig.\u00a010b). In the last pass, no 17, partial dynamic recrystallization for the pearlitic steel was observed, but the dominant mechanism of recrystallization was static. For bainitic steel, the value of the critical strain was greater than the value of the effective strain and dynamic recrystallization did not start. Static recrystallization only was observed (Fig.\u00a011). Modelling of the mechanisms of recrystallization (dynamic and static) showed that for pearlitic steel the recrystallization rate is larger than for bainitic steel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004264___lang_en_format_pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004264___lang_en_format_pdf-Figure13-1.png", + "caption": "Fig. 13 The current density magnitude at the first tuning, a. Solid BBS, b. Cylindrical BBS, c. Modified Cylindrical BBS", + "texts": [ + " 2012; accepted 15 June 2012 Brazilian Society of Electromagnetism-SBMag \u00a9 2012 SBMO/SBMag ISSN 2179-1074 170 The surface current density is an important factor to analyze the antenna parameters such as the electric field, the electric energy, the power flow, and the far field pattern. Assume that the current density is J then the relation between the electric field and the current density is [36] ( ) ( ) ( ) rrRdArJ R Rjk rV A \u2032\u2212= \u2212 = \u222b\u222b ; 4 exp \u03c0 (17) ( ) ( )( )rV j rVjE s \u22c5\u2207\u2207+\u2212= \u03c9 \u03c9\u00b5 1 (18) The value of ( )rV is calculated from section II. The current density at the first tuning frequency is given in Fig. 13 and for the third tuning frequency is given in Fig. 14 for the three antennas. The current level of the modified cylindrical BBS cannot be compared easily with the other ones because its admittance is a tandem like structure. Hence, the current peak cannot be determined easily only by using the simulation. But overall, it has lower value of Y than the solid BBS and higher that the cylindrical BBS. The same can be said for the delivered power curve given in Fig. 12 and the Y Journal of Microwaves, Optoelectronics and Electromagnetic Applications, Vol" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure23-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure23-1.png", + "caption": "Figure 23 Wired Interface Without Connector.", + "texts": [ + " A connector such as this placed into the P-POD inside of the pusher plate could mate to the other connector half, attached to the CubeSat. An example of this setup is shown below in Figure 22. Page 33 The configuration shown above is one of the direct contact wired options. Another option was to utilize a collection of items such as springs and pin contacts in order to achieve the same goal without using a commercial off-the-shelf connector. In-House Conical Spring System An example of this setup is shown below in Figure 23. The conical springs and the circular pads shown are conductors, and the pins serve as guides to ensure the conical spring does not slip off its designed location, ensuring contact. This setup could be put together for relatively low cost but there were some concerns. For instance, it would be difficult to provide industry approved shielding to each of the conical springs without interfering with their function. This system would also require a significant amount of assembly, which makes workmanship errors more likely and prolongs build times" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000652_0005208_10013678.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000652_0005208_10013678.pdf-Figure8-1.png", + "caption": "FIGURE 8. Unit-cell of the stepped septum polarizer.", + "texts": [ + " The goal function takes in account the scattering parameters of the device and the radiated fields: each septum\u2019s step is sized in order to maximimize the matching for all the three ports of the polarizer (the two rectangular waveguide input ports and the VOLUME 11, 2023 4607 square waveguide output port) and maximize the isolation while minimizing the axial ratio cost function (3), over the operative uplink Ka-band (27 \u2212 31 GHz). In Fig. 6a the performances of the designed septum polarized are shown: the reflection coefficient and the isolation between the input ports are both below \u221218 dB (Fig. 6). The axial ratio shows an excellent circularly polarization purity, below 0.4 dB over the operative band (Fig. 6b). Then the single element of the array, fed by two PPWs, has been simulated and optimized in a periodic environment as in Fig. 8, to study the scanning performances. The transition between the PPWs and the rectangular input waveguides of the septum polarizer is obtained by inserting in each input waveguide a capacitive iris of height hiris = 0.69 mm and thickness t = 0.5 mm, posed at ziris = 0.44 mm from the discontinuity. The circular polarization purity can be estimated through the computation of the far fields considering the cross-polar component rejection as defined in [44]. Or equivalently it can be expressed in terms of axial ratio, defined as the ratio of the lengths of the major and minor axes of the polarization ellipse of the radiated field defined as in [45]: AR = |Ez|2 + |Ey|2 + \u221a \u03b3 |Ez|2 + |Ey|2 \u2212 \u221a \u03b3 (8) where the parameter \u03b3 is given by: \u03b3 = |Ez|4 + |Ey|4 + 2|Ez|2|Ey|2 cos [ 2 (\u0338 Ez \u2212 \u0338 Ey )] (9) The optimized width and length of each step, xn and yn respectively, are shown in table 2, the final length of the blade is 19" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000065_m.C.2010.4.62-67.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000065_m.C.2010.4.62-67.pdf-Figure5-1.png", + "caption": "Fig. 5 Identification of the kinematics excitation functions", + "texts": [ + "25 cm), part of the leveling line longitudinal slope and rough unevenness elimination; the random part was extracted, it has a character of a random value of the centered stochastic function and it especially excites the vertical vibration of the vehicle and sig- 64 C O M M U N I C A T I O N S 4 / 2 0 1 0 nificantly affects the stochastic vibration of the vehicle\u2019s parts during the movement, application of the autoregression modeling theory for the suitable ARMA model specification and for generation of new statistically adequate realizations of the stochastic height unevenness behavior on the miscellaneous surface quality. The behavior of the chosen random kinematics excitation functions for road classification 5 and terrain are shown in Fig. 4. The points where these functions input into the computational model are presented in Fig. 5, where: v \u2013 vehicle speed, [km/h], L1 \u2013 wheel base No. 1, [m], (see Fig. 5), L2 \u2013 wheel base No. 2, [m], (see Fig. 5), uzL (1) \u2013 unevenness of the left rail in a vertical direction for the front axle, [m], uzP (1) \u2013 unevenness of the right rail in a vertical direction for the front axle, [m], uzL (2) \u2013 unevenness of the left rail in a vertical direction for the 1st back axle, i.e. , [m], uzP (2) \u2013 unevenness of the right rail in a vertical direction for the 1st back axle, i.e. , [m], uzL (3) \u2013 unevenness of the left rail in a vertical direction for the 2nd back axle, i.e. , [m], uzP (3) \u2013 unevenness of the right rail in a vertical direction for the 2nd back axle, i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure7-1.png", + "caption": "Fig. 7 Rigid-flexible coupling simulation model formulation of trailer TC02/07 based on optical fiber 650 test and analysis results based on three acceleration PSD contrast for hanging traction converter, as 651 seen in Fig. 5(f, g, h), including section \u2160 from stationary acceleration time history (a), section \u2161 from 652 critical acceleration time history (b)and section \u2162 from critical acceleration time history (c); And two 653 acceleration PSD contrast (d, e) for side beams in floor frame corresponding to (a) and (b). Between 654 aluminum alloy car body and the external equipments, two main interfaces are constituted with roof 655 interface (f) and floor frame interface (g), and rigid-flex coupling model of service car body (h) 656 formulated with weak coupling interface of floor frame so as to ensure 30-year service life. 657", + "texts": [ + "5 Hz for motor vehicle shaking, 637 which is approaching to the modal frequency of traction motors swung laterally with 638 hanging frame corresponding to rear motor bogie; ii) the main frequency is changed to ca. 639 1.5 Hz for trailer vehicle shaking, which is determined by the anti-roll nonlinear stiffness. 640 In order to avoid the strong electromagnetic interference, this tracking test adopts 658 the novel technique of optical fibber measuring, and the acceleration sensitivity can reach 659 1K Hz. For the floor frame, as shown in Fig. 7 (d, e), both side beams only generate the 660 high-frequency elastic vibration with the dominant frequency of ca. 290 Hz since the 661 unsteady aerodynamic load caused by the skirts with reinforcement design supports. 662 After the self-weight wedge tight failure on some rubber hanging joints, the traction 663 converter reciprocates and moves laterally, and the high-frequency elastic vibration with 664 the dominant frequency of ca. 350 Hz is significantly weakened. 665 Combined with the analysis results of this tracking test, as shown in Fig. 7 (f, g, h), 666 the rigid-flex coupling simulation model of trailer TC02/07 was formulated according to 667 the principle of weak coupling interface, and the formation mechanism of internal lateral 668 coupling resonance is fully confirmed by the dynamic simulation analyses [49 - 50]. 669 However, the new rubber hanging elements were mistakenly used to implement the DVA 670 damping technique. If the impact of repeated roll vibration is excluded, as shown in Fig. 671 8, the lateral acceleration of traction converter exceeds the limit specified in IEC61373 \u2013 672 2010, forcing the self-excited vibration of the middle diamond mode for service car body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001261_354-68291802051P.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001261_354-68291802051P.pdf-Figure1-1.png", + "caption": "Figure 1: Crane hook", + "texts": [ + " As for the MATLAB software package, to use the functions fmincon and use the expressions (5) and (6), respectively: [ ] ( ), , , , , , , 0, , , , , , ,X fval exitflag output lambda grad hessian fmincon fun X A b Aeq beq lb ub nonlcon= (5) [ ] ( ), , , , , , , , , , ,X fval exitflag output ga fun n A b Aeq beq lb ub nonlcon= (6) Analysis and Optimization of T-cross section of Crane Hook Considered as Curved Beam where the explanations of the MATLAB function are shown: fval - the value of solving target function, exitflag - shows the reason for the termination of solving execution, fun - objective function, output - shows the output informationduring optimization, nonlcon - calculating of non-linear inequality, lambda - Laqngrange multiplier, grad - the gradient of objective function in point X, hessian - the Hessian value of objective function in point X, 0X - the vector of initial values of optimization parameters, ,b beq - vectors, ,A Aeq - matrices, ( ), ( )C X Ceq X - vector functions. The PSO optimization algorithm is defined according to [18], and with that algorithm the optimal value are determined. Figure 1 shows a standard crane hook according to [19], as well as a critical cross section (I - I) on which the T-cross section is viewed (the right part of the section from the axis of loading force). The mathematical formulation of the objective function is shown as follows (Figure 2): 1 2 3 4( ) ( ) ( ) ( )T T T tf X A X A x x x x A b t h d= = = (7) The input parameters vector is: ( ), , dx Q a \u03c3= r (8) where are: Q - load capacity of crane hook, a - diameter of inner fiber of hook, [19] (Fig. 1), d\u03c3 - critical stress, [19]. Below text will showdetailed objectives and constraints. 4. OBJECTIVE FUNCTIONS AND CONSTRAINTS 4.1. Objective function The objective function is represented by the area of T-cross section of crane hook at the most critical place. (Figure 2). The cross-sectional area, or the objective function, is: T tA b t h d= \u22c5 + \u22c5 (9) 4.2. Constraint functions Optimization processes are based on permissible stresses, according to Winkler-Bach theory. The total deformation of fibers in the curved beam is proportional to the distance of the fiber from the neutral surface (axis)", + " - Markovi\u0107, G. - Stanojkovi\u0107 J. 1 1cR R e= + (17) 2 2 1 2 2 t T b t h d t h d e A \u22c5 + \u22c5 \u22c5 \u22c5 + \u22c5 = \u22c5 (18) o cy R r= \u2212 (19) T A Ar dA \u03c1 = \u222b (20) 2 2ln ln 2t A dA a t a Hb d a a t\u03c1 + \u22c5 + \u22c5 = \u22c5 + \u22c5 + \u22c5\u222b (21) QF Q g= \u22c5 (22) max Q cM F R= \u22c5 (23) x T oS A y= \u22c5 (24) where are: 1R - radius of inner fiber (Fig. 2), 2R - radius of outer fiber (Fig. 2), cR - polupre\u010dnik te\u017ei\u0161ne ose (Fig. 2), r - radius of neutral axis (Fig. 2), oy - distance between centroidal axis and neutral axis (Fig. 2), QF - axial force (Fig. 1), maxM - maximum bending moment, xS - static moment of area. 5. NUMERICAL REPRESENTATION OF OPTIMIZATION RESULTS Optimization is performed using the following optimization algorithms: GRG2 algorithm and EA algorithm, using the Solver Tool tool in the Analysis module in the Ms EXCEL software package; using the fmincon functions according to [16] and ga according to [17], in MATLAB software package; using the optimization algorithm for the PSO, according to [18], in MATLAB software package. The optimization parameters are the height h, the thickness d, the width bt and the thickness of the base t, of T-cross section (Figure 2). The geometric parameter a (Figure 1) is taken as the input size, according to standard [19] and is not the subject of optimization. Input optimization parameters are: FQ = 100 kN, a = 12.5 cm and \u03c3d = 8 kN/cm2. A standard crane hook with a load capacity of 10 t is observed. The cross sectional area of crane hook at the most critical place, in relation to which the optimal results are compared, is: As = 109.9 cm2, according to [19]. The values of minimum thicknesses t and d are not less than 1 cm. The following tables show the results of optimization (optimal geometric parameters of the crosssection, optimal cross-sectional area and savings) according to the above algorithms (Table 1 \u00f7 Table 5)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003238_f_version_1584177316-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003238_f_version_1584177316-Figure8-1.png", + "caption": "Figure 8. Motor frequency domain analy is chart: (a) layout of the a plied load, (b) Motor frequency impedance diagram.", + "texts": [ + " The impedance and frequency variation and the electrical resonance frequency of the piezoelectric stator can also be obtained. By using the solid mechanical analysis module in the COMSOL finite element analysis software, a voltage load is applied to the piezoelectric ceramics of the stator, and the form of the load is a plural form. The magnitude of the voltage on one side of the piezoelectric substrate is 0 V, and the magnitude of the voltage on the other side is 200 V. The layout of the applied load is shown in Figure 8a. The excitation voltage applied by phase A is 200 \u00d7 exp(\u03c0/2 \u00d7 i), and the excitation voltage applied by phase B is 200 \u00d7 exp(0 \u00d7 i). From the modal analysis results in Figure 5, the piezoelectric stator frequency is about at 40 kHz, so the frequency domain analysis is performed with 39.5\u201341.5 kHz. The frequency domain analysis result of the piezoelectric stator obtained by post-processing is shown in Figure 8. As shown in Figure 8b, the piezoelectric stator reaches the resonance frequency at 40.365 kHz, and the frequency corresponding to the maximum operating speed of the motor is obtained. Sensors\u00a02020,\u00a020,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 7\u00a0of\u00a018\u00a0 3.2.\u00a0Frequency\u00a0Domain\u00a0Analysis\u00a0 The\u00a0frequency\u00a0domain\u00a0analysis\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0determines\u00a0the\u00a0steady\u2010state\u00a0response\u00a0 when\u00a0it\u00a0is\u00a0excited\u00a0by\u00a0a\u00a0sinusoidal\u00a0voltage.\u00a0The\u00a0impedance\u00a0and\u00a0frequency\u00a0variation\u00a0and\u00a0the\u00a0electrical\u00a0 resonance\u00a0frequency\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0can\u00a0also\u00a0be\u00a0obtained.\u00a0 By\u00a0using\u00a0the\u00a0solid\u00a0mechanical\u00a0analysis\u00a0 odule\u00a0in\u00a0the\u00a0CO SOL\u00a0finite\u00a0ele ent\u00a0analysis\u00a0software,\u00a0 a\u00a0voltage\u00a0load\u00a0is\u00a0applied\u00a0to\u00a0the\u00a0piezoelectric\u00a0cera ics\u00a0of\u00a0the\u00a0stator,\u00a0and\u00a0the\u00a0for \u00a0of\u00a0the\u00a0load\u00a0is\u00a0a\u00a0plural\u00a0 form.\u00a0 The\u00a0 agnitude\u00a0 of\u00a0 the\u00a0 voltage\u00a0 on\u00a0 one\u00a0 side\u00a0 of\u00a0 the\u00a0 piezoelectric\u00a0 substrate\u00a0 is\u00a0 0\u00a0 V,\u00a0 and\u00a0 the\u00a0 magnitude\u00a0of\u00a0the\u00a0voltage\u00a0on\u00a0the\u00a0other\u00a0side\u00a0is\u00a0200\u00a0V.\u00a0The\u00a0layout\u00a0of\u00a0the\u00a0applied\u00a0load\u00a0is\u00a0shown\u00a0in\u00a0Figure\u00a0 8a.\u00a0The\u00a0excitation\u00a0voltage\u00a0applied\u00a0by\u00a0phase\u00a0A\u00a0is\u00a0200\u00a0\u00d7\u00a0exp(\u03c0/2\u00a0\u00d7\u00a0i),\u00a0and\u00a0the\u00a0excitation\u00a0voltage\u00a0applied\u00a0 by\u00a0phase\u00a0B\u00a0is\u00a0200\u00a0\u00d7\u00a0exp(0\u00a0\u00d7\u00a0i).\u00a0From\u00a0the\u00a0modal\u00a0analysis\u00a0results\u00a0in\u00a0Figure\u00a05,\u00a0the\u00a0piezoelectric\u00a0stator\u00a0 frequency\u00a0is\u00a0about\u00a0at\u00a040\u00a0kHz,\u00a0so\u00a0the\u00a0frequency\u00a0domain\u00a0analysis\u00a0is\u00a0performed\u00a0with\u00a039.5\u201341.5\u00a0kHz.\u00a0The\u00a0 frequency\u00a0domain\u00a0analysis\u00a0result\u00a0of\u00a0the\u00a0piezoelectric\u00a0stator\u00a0obtained\u00a0by\u00a0post\u2010processing\u00a0is\u00a0shown\u00a0in\u00a0 Figure\u00a08.\u00a0 As\u00a0shown\u00a0in\u00a0Figure\u00a08b,\u00a0the\u00a0piezoelectric\u00a0stator\u00a0reaches\u00a0the\u00a0resonance\u00a0frequency\u00a0at\u00a040.365\u00a0kHz,\u00a0 Figure\u00a08.\u00a0Motor\u00a0frequency\u00a0domain\u00a0analysis\u00a0chart:\u00a0(a)\u00a0layout\u00a0of\u00a0the\u00a0applied\u00a0load,\u00a0(b)\u00a0Motor\u00a0frequency\u00a0 impedance\u00a0diagram.\u00a0 3.3.\u00a0Transient\u00a0Analysis\u00a0 The\u00a0 transient\u00a0 analysis\u00a0 of\u00a0 the\u00a0 piezoelectric\u00a0 stator\u00a0 utilizes\u00a0 a\u00a0 state\u00a0 equation\u00a0 that\u00a0 describes\u00a0 the\u00a0 continuous\u00a0state\u00a0change\u00a0of\u00a0the\u00a0motor.\u00a0The\u00a0trajectory\u00a0and\u00a0vibration\u00a0displacement\u00a0of\u00a0the\u00a0piezoelectric\u00a0 stator\u00a0are\u00a0investigated\u00a0by\u00a0finite\u00a0element\u00a0analysis.\u00a0Based\u00a0on\u00a0the\u00a0frequency\u00a0domain\u00a0analysis,\u00a0the\u00a0phase\u00a0 A\u00a0voltage\u00a0excitation\u00a0is\u00a0defined\u00a0as\u00a0200\u00a0\u00d7\u00a0sin(2\u03c0\u00a0\u00d7\u00a0f),\u00a0the\u00a0phase\u00a0B\u00a0voltage\u00a0excitation\u00a0is\u00a0defined\u00a0as\u00a0200\u00a0\u00d7\u00a0 cos(2\u03c0\u00a0 \u00d7\u00a0 f),\u00a0 and\u00a0 f\u00a0 is\u00a0 40" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000500_f_version_1694334288-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000500_f_version_1694334288-Figure3-1.png", + "caption": "Figure 3. The system hardware of DJI Phantom 4.", + "texts": [ + " Since the integral equation presented earlier cannot be directly calculated numerically, Formulas (2) and (3) can be reformulated as Riemann integrals, expressed as follows: C\u0302(r) = N \u2211 i=1 Ti(1 \u2212 exp(\u2212\u03c3i\u03b4i))ci (4) Ti = exp(\u2212 i\u22121 \u2211 j=1 \u03c3j\u03b4j) (5) The Riemann integral is a fundamental concept in mathematical analysis that approximates the area under a curve by dividing it into smaller intervals and summing their contributions. In Formula (4), \u03b4i = ti + 1 \u2212 ti is the distance between adjacent samples. In Formula (5), Ti represents the accumulated transmittance between point i and point j. This function for calculating C\u0302(r) from the set of (ci, \u03c3i) values is trivially differentiable and reduces to traditional alpha compositing with alpha values \u03b1i = 1 \u2212 exp(\u2212\u03c3i\u03b4i). We perform data collection using the DJI Phantom 4 UAV. Figure 3 shows the UAV platform used in the experiments. The DJI UAV platform consists of two integral components: the aircraft itself and the integrated camera systems it carries. Detailed information is shown in Table 1. Appl. Sci. 2023, 13, x FOR PEER REVIEW 4 of 11 The color value C = (r,g,b) and the volume density \u03c3 obtained from the neural network\u2019s output are utilized in the process of volume rendering to derive the final pixel value. The loss between the volume rendering result and the original image is calculated and used as feedback to continuously optimize the reconstruction outcome", + " Since the integral equation presented earlier cannot b directly calculated numerically, Formulas (2) and (3) can be reformulated as Riemann integrals, expressed as follows: 1 \u02c6 ( ) (1 exp( )) N i i i i i C T c\u03c3 \u03b4 = = \u2212 \u2212r (4) 1 1 exp( ) i i j j j T \u03c3 \u03b4 \u2212 = = \u2212 (5) The Riemann integral is a fundamental concept in mathematical analysis that approximates the area under a curve by dividing it into smaller intervals and summing their contributions. In Formula (4), \u03b4i = ti + 1 \u2212 ti is the distance between adjacent samples. In Formula (5), Ti represents the accumulated transmittance between point i and point j. This function for calculating C\u0302(r) from the set of (ci, \u03c3i) values is trivially differentiable and reduces to traditional alpha compositing with alpha values \u03b1i = 1 \u2212 exp(\u2212\u03c3i\u03b4i). 3. Experiments and Results 3.1. Data and Implementation Details We perform data collection using the DJI Phantom 4 UAV. Figure 3 shows the UAV platform used in the experiments. The DJI UAV platform consists of two integral components: the aircraft itself and the int grated ca era systems it carries. Detailed information is shown in Table 1. Appl. Sci. 2023, 13, 10174 5 of 11 Table 1. Information on DJI Phantom 4 UAV. Equipment Specifications camera Image sensor: 1/2.3 inch CMOS; 12.4 million effective pixels Lens: FOV 94\u25e6 20 mm (35 mm format equivalent); f/2.8 focus to infinity Image size: 4000 \u00d7 3000 Image format: JPEG, DNG(RAW) aircraft Weight (including battery and paddles): 1380 g Maximum ascent speed: 6 m/s Maximum descent speed: 4 m/s Maximum horizontal flight speed: 72 km/h Maximum wind speed: 10 m/s Flight time: about 28 min Working temperature: 0 \u25e6C to 40 \u25e6C For the acquisition of UAV imagery, we employ the publicly available dataset provided by Pix4Dmapper", + " Table 2. Number of datasets and types of scenarios represented. Datasets Number Scene Dataset 1 34 Small Villa Dataset 2 55 Unconventional Landmark Architecture Dataset 3 100 Large Apartment Building The acquired UAV imagery dataset is highly representative, encompassing scenes crucial for reconstruction in production operations, such as significant landmarks, largescale apartment buildings, and small-scale villas. Figure 4 shows the types of scenarios. Appl. Sci. 2023, 13, x FOR PEER REVIEW 5 of 11 Figure 3. The system hardware of DJI Phantom 4. Table 1. Information on DJI Phantom 4 UAV. Equipment Specifications camera Image sensor:1/2.3 inch CMOS; 12.4 million effective pixels Lens: FOV 94\u00b0 20 mm (35 mm format equivalent); f/2.8 focus to infinity Image size:4000 \u00d7 3000 Image format: JPEG, DNG(RAW) aircraft Weight (including battery and paddles):1380 g Maximum ascent speed:6 m/s Maximum descent speed:4 m/s Maximum horizontal flight spe d:72 km/h Maximum wind speed:10 m/s Flight time: about 28 min Working temperature:0 \u00b0C to 40 \u00b0C For the acquisition of UAV imagery, we e ploy the publicly available dataset provided by Pix4Dmapper" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002809_nerator_20system.pdf-Figure1.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002809_nerator_20system.pdf-Figure1.5-1.png", + "caption": "Fig. 1.5: Negative voltage Applications: Class-C VCO [24] (a) VCO schematic (b) Class-C operation in PMOS only mode", + "texts": [ + " This allows the system to make dynamic trade-off between speed and power, as per the instantaneous requirements of its environment, thus resulting in a highly-efficient yet responsive system implementation. In RF circuit design domain, other than RF power-amplifier and static leakage reduction application, use of negative voltage supply has also been explored with high performance Class-C VCOs, as was recently reported in [24], [25]. In [24], negative voltage was used to bias and thus completely turn off NMOS cross-couple 5 pair, while the VCO was operating in the high-performance PMOS-only mode (Fig. 1.5). Eliminating the momentarily conducting path through NMOS pair, resulted in an at least 10% improvement in the LC tank quality factor, which directly translates into better phase-noise performance for the VCO. Thus for this application, the required negative voltage should have high regulation accuracy with moderate tuning range, while the negative voltage source should exhibit high power efficiency. Lastly, the GaN-HEMT based RF PA, as a subset of depletion mode biasing application, is of particular interest [20, 21, 27], as it places the most stringent requirements on the regulated negative voltage, used for gate biasing of the PA" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001479_f_version_1716187387-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001479_f_version_1716187387-Figure6-1.png", + "caption": "Figure 6. Schematic diagram of flexible solar array. Figure 6. Schematic diagram of flexible solar array.", + "texts": [ + " Although there is a significant difference in length between the two flexible solar arrays of the core module and lab module, the structure and principle are basically the same, the tension applied to the array surface especially is also basically the same. Therefore, one of the flexible solar arrays can be taken as an example to introduce the dynamic modeling process. The flexible solar array mainly consists of a lifting mechanism, a stretching mechanism, a deployable mechanism, a guiding mechanism, a driving mechanism, a storage box, a storage container, a battery array, a cable system, etc. Its state after fully deploying in-orbit is shown in Figure 6. The flexible solar array obtains the required stiffness through the tension applied by the tensioning mechanism and maintains a flat state. The single side array when fully deployed is shown in Figure 7. Aerospace 2024, 11, 411 12 of 30 Aerospace 2024, 11, x FOR PEER REVIEW 13 of 34 To facilitate the description of the vibration mode of the residual structure, ignoring the Y-direction manned spacecraft, the space station assembly can be viewed as a cross shaped configuration formed by the intersection of two lines", + " Although there is a significant difference in length between the two flexible solar arrays of the core module and lab module, the structure and principle are basically the same, the tension applied to the array surface especially is also basically the same. Therefore, one of the flexible solar arrays can be taken as an example to introduce the dynamic modeling process. The flexible solar array mainly consists of a lifting mechanism, a stretching mechanism, a deployable mechanism, a guiding mechanism, a driving mechanism, a storage box, a storage container, a battery array, a cable system, etc. Its state after fully deploying in-orbit is shown in Figure 6. The flexible solar array obtains the required stiffness through the tension applied by the tensioning mechanism and maintains a flat state. The single side array when fully deployed is shown in Figure 7. Figure 7. The single side array with fully deployed. Based on the design and working principle of the flexible solar array, the beam and shell elements are mainly used to model the structure, and to simulate the connections between the structures via linear and nonlinear spring elements. The initial tension of the tensioning mechanism acting on the flexible solar array is simulated by applying element temperature stress or the gap element to achieve the stiffness of the flexible solar array under the tensioning force" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000637_f_version_1649326514-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000637_f_version_1649326514-Figure1-1.png", + "caption": "Figure 1. One-pole cross-section of a 54s-6p SynRM.", + "texts": [ + " Nevertheless, the low power density and inferior efficiency are potential challenges of IMs [4]. The switched reluctance machine (SRM) is also a good candidate in terms of simple and robust rotor Energies 2022, 15, 2711. https://doi.org/10.3390/en15082711 https://www.mdpi.com/journal/energies structure and possible operation in high temperatures or high rotational speeds [8\u201310]. The major disadvantage is acoustic noise and vibration, which becomes significant at high speeds and high loads [11]. The synchronous reluctance motor (SynRM), as shown in Figure 1, has attracted more and more attention in recent years, even though it has not been widely used in the traction drive field. With 30 years of development, it has achieved the merits of having low cost, high efficiency, low maintenance, high reliability and high temperature resistance [12,13]. In addition, it is also characterized by no back electromagnetic force (EMF), leading to an inherent fault tolerance capability. All these features reveal that the SynRM is an attractive alternative for electrical mobility", + " As a result, central bridges in the second and third flux barriers are introduced to reduce the stress concentration on the outer ribs. The thicknesses of these central bridges are optimized to 0.3 mm and 1.0 mm, respectively. As shown in Figure 11b, the maximum stress is then reduced to 354 MPa, which allows a safety factor of 1.24. As a sacrifice, the machine torque is slightly reduced due to the leakage flux path created by the central bridges. The cross-section of the designed SynRM is shown in Figure 1. According to [29], the maximum torque of the Lexus LS 600h IPM motor within the temperature limit of 150 \u25e6C for a transient time of 18 s is around 233 Nm. The maximum torque of the optimized SynRM under the same peak current is 178 Nm, which accounts for only 76%. Therefore, the stack length of the designed SynRM is increased in order to meet the same torque and power requirements. As described in the literature [23,24], the PMaSynRM can be obtained directly from the optimized SynRM considering the maximized reluctance torque" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure12-1.png", + "caption": "Figure 12. Compression Load Tester", + "texts": [ + " For normal operation the appropriate arm, direction, acceleration, speed and degrees controls are set. These settings correspond with functions that dictate the motion of the stepper motor (arm) selected. Bench tests were performed to ensure the Pipe Traveler grippers were working correctly before placing the Pipe Traveler on vertical pipes. The first test performed was a gripper strength test. In this test a load cell was placed between a split cylinder which was then compressed by the gripper (Figure 12). The test showed that each gripper is able to apply over 1000 lbf to the pipes, which was more than adequate for the application. Page 9 of 15 Another bench test was performed to see how well the drive wheel was able to rotate a pipe when the grippers were applied. To conduct this test a pipe was placed in both grippers and gripped with varying forces. It was determined that when at least 250 lbf of gripper force was applied, the pipe was able to be easily rotated using 90 psi air on the drive wheel cylinder" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003560_robt.2020.590076_pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003560_robt.2020.590076_pdf-Figure8-1.png", + "caption": "FIGURE 8 | (Left) The grasping quality for object crest_minty_fresh with different hand design parameters. (Right) The hand object interaction for different final grasp qualities. The red circles stand for over-shot deformation and thus the quality is set to w = 0.", + "texts": [ + " We take the first object v8 as an example and the desired force is set to 2N. The grasp qualities for different hand parameters is shown as follows (see Figure 6). The best grasp quality is 0.3621 and the corresponding parameters are a = 0.5mm and h = 11mm. For another object pringles, the desired force is set to 3N and the best hand design parameters (a = 0.7mm and h = 10mm) are shown in Figure 7. For another object cre_minty_fresh, the desired force is set to 3N and the best hand design parameters (a = 1.0mm and h = 11mm) are shown in Figure 8. The 3D-printed fin-ray finger used for grasping two realworld objects is shown in Figure 9. The true deformations Frontiers in Robotics and AI | www.frontiersin.org 5 February 2021 | Volume 7 | Article 590076 for current examples are hard to measure. Therefore, we cannot directly compute the grasp quality in the realworld example. However, in the future work, we are planning to integrate tactile sensing with the soft finger, which allows us to estimate the grasp quality from previous experience (Li et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000987_ees-2022-4-r-112.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000987_ees-2022-4-r-112.pdf-Figure2-1.png", + "caption": "Fig. 2. Development steps for the triple-band UWB antenna: (a) Ant.0, (b) Ant.1, and (c) Ant.2.", + "texts": [ + " The substrate had a total size of 70 mm \u00d7 60 mm \u00d7 0.8 mm. The ultra-wide impedance bandwidth was achieved using CST software to simulate a compact structure. Fig. 1 shows the final design for a triple- MEKKI et al.: A UHF/UWB MONOPOLE ANTENNA DESIGN PROCESS INTEGRATED IN AN RFID READER BOARD band monopole antenna. The main aim of this study was to create a triple-band antenna reader for UHF/UWB operation. A circular patch disc monopole antenna with two-sided corner truncation and two circular and (+)-shaped slots make up this antenna [27]. Fig. 2 depicts the evolution of the introduced triple-band an- tenna from the basic UWB antenna step by step. There are three basic phases in the antenna design process. The circular patch-based CPW that feeds the antenna with a ground plane in Ant.0 is distinguished by its proportional coplanar design. The prior base antenna was changed to improve antenna performance and build a UWB antenna, although geometrical characteristics and the substrate remained the same as the basic antenna. In Ant.1, a two-sided corner truncation method was used to truncate the patch antenna corners. The specifications of the truncated corners utilized to increase bandwidth and provide better impedance matching throughout the operating bands are shown in Fig. 2 (Ant.1). To achieve the UWB response, the slots (+) and circular shapes were etched into the circular patch with a length (Ls), width (Ws), and circle radius (r) in Ant.2. Compared to the previous UWB antenna, impedance matching and operational bandwidth were significantly improved in the initial iteration. Fig. 3 shows the reflection coefficient S11 versus the frequency of the proposed antenna compared to the other antennas. The antenna (Ant.0) demonstrated broad capabilities with a -10 dB bandwidth spanning 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003971__2462_context_theses-Figure5-16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003971__2462_context_theses-Figure5-16-1.png", + "caption": "Figure 5-16: Extended approach of contact of cylindrical bodies (Reference [12, p. 130])", + "texts": [ + " However, for the contact of cylindrical bodies such as gears (Figure 5-15) or roller bearings, the Hertz theory is not solely sufficient to determine these parameters. In this case, the shape and size of the bodies themselves are important. In most practical analyses these calculations are difficult to perform and a lot of different approximations and assumptions have been developed over time. 59 For the simulation of the contact in MSC.Adams, the stiffness of the bodies is necessary to perform the calculations. The theory of K.L. Johnson, \u201ccontact of cylindrical bodies\u201d is extended by Vink System Design & Analysis48 will be considered as seen in Figure 5-16: To determine the stiffness of the body, the calculation is based on the stiffness H defined as, H = I = I (5-29) where the normal force is the tooth force and I is the displacement of the contact point. To perform the calculations with the theory of cylindrical bodies, the radius of the contact teeth has to be approximated as seen in Figure 5-17. Which leads to a tooth radius J for the pinion and J for the gear. 48 Applied in HertzWin 2.3.1 60 The displacement of the contact point I can be defined as, I = 2 \u2217 \u2217 1 \u2212 K \u2217 F \u2217 :ln( 4 \u2217 J ) + ln L4 \u2217 J M \u2212 1; (5-30)49 Where the compressive load per unit axial length P can be defined with the tooth force and the facewidth E of the gear as, = E (5-31) Where the semi-contact-width is given by, / = 4 \u2217 \u2217 J / K \u2217 F\u2217 (5-32)50 The composite modulus F\u2217 is given as F\u2217 = 2 \u2217 F \u2217 F 1 \u2212 \u2217 F + 1 \u2212 \u2217 F (5-33)51 where F and F are the young\u2019s modulus and and the passion\u2019s ratio of the contact materials" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004437_load.php_id_10052811-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004437_load.php_id_10052811-Figure3-1.png", + "caption": "Figure 3. (a) ESPRIT decomposition at 750 MHz. (b) ESPRIT fitting at 750 MHz.", + "texts": [ + " Given N > 2d + 1, ESPRIT can estimate d, ak and \u03b2k without error. Therefore, ESPRIT is an eigenspace parameter estimator that estimates a set of \u03b2n, \u03b1n in Eq. (1) based on the generalized singular value decomposition of the covariance matrix. Once they are estimated, cn can be found by the total least-squares criterion to arrive at the best fit of the total current J . In applying ESPRIT, we use the maximum model order N/2 to achieve a good fit to the data, where N (= 41) is the total number of data samples. Fig. 3(a) plots the extracted wave velocity of the four dominant modes. The vertical axis shows the phase velocity scale, which has been normalized to the speed of light in free space. The horizontal axis shows the distance along the helix winding (\u03be). The color in the plot indicates the strength of the each current mode versus distance, cne\u2212\u03b1n\u03be, displayed on a decibel scale. The change of the current mode strength along the helix winding is clearly seen. In Fig. 3(b), it is shown that the sum of the four dominant modes accurately reconstructs the original simulated current distribution. At this frequency, higher order modes are much weaker and can be neglected. In Fig. 3(a), T+ 0 and T+ 1 are the positive traveling current modes while T\u22120 and T\u22121 are the corresponding reflected current modes from the open end. It is seen that the magnitude of T+ 1 is almost constant along the helix and its phase velocity is smaller than that of the free space. This is the familiar slow wave on the helix and is typically considered the dominant radiation mode in the literature [8]. We also observe that at this frequency, T+ 0 exhibits a larger phase velocity but decays much faster than the T+ 1 mode" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure24-1.png", + "caption": "FIGURE 24. Side view of L-probe and T-probe models (a) L-probe (b) T-probe [28].", + "texts": [ + " The antenna operation from 600MHz to 1 GHz is significantly determined by mode 2. Modes 3 and 4 are dominant within the range of 1 to 1.15 GHz, based on the results of the characteristic angles presented in Fig. 23. The highest resonance is achieved by mode 5. A U-slot patch antenna is excited separately by using three different probe feeds: a vertical probe, an L-probe, and a T-probe. The resonant behavior produced by using different feeding probes can be analyzed using CMA. The modal analysis as shown in Fig. 24 concludes that a T-probe feed structure is more resonant and may produce the widest impedance bandwidth [28]. The modal excitation coefficient is analyzed between 2.5 GHz and 8.5 GHz. Modes with the highest modal excitation coefficient values are the main modes excited by the feed probe. Fig. 25(a) shows that mode 3 is the main mode excited by the conventional vertical probe from 2.5 to 5.7 GHz. On the other hand, mode 3 is also the main mode excited by the L-shaped probe between 2.5 and 6.1 GHz, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001904_017_ms-8-11-2017.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001904_017_ms-8-11-2017.pdf-Figure4-1.png", + "caption": "Figure 4. MBD full vehicle model, reference-handling model (left), BEAM Spring suspension vehicle prototype (right).", + "texts": [ + " The reference suspension has been defined to have \u00b170 mm wheel travel, and an understeering behavior has been chosen to ensure safety. Consequently, the front suspension has a \u22120.4\u25e6 of camber angle variation at maximum stroke and a toe-out of 0.7\u25e6 when the coil spring is fully compressed. Due to the rear suspension design for beam spring, no significant toe variation has been set. The camber variation for the reference rear suspension has been set to \u22122.1\u25e6. Beam suspension from geometric and kinematic point of view is identical for the two suspension models (reference and beam suspension models) as shown in Fig. 4. www.mech-sci.net/8/11/2017/ Mech. Sci., 8, 11\u201322, 2017 In this particular project, the beam has to be mounted transversely rather than longitudinally. The study shows in order to maximize the limit for elastic strain energy storage, the beam should be designed to have a tapered shape for vertical loading along the length (Yu and Kim, 1988). Still, a design with constant thickness along the length has been chosen to balance cost and performance, also because the space required for mounting the tapered beam is not available, and it is very difficult to prototype", + " 6, on the metal plate for mounting the upright, apart from the two coaxial hole (drilled to fix the upright), there is another small hole drilled on the vertical surface, for mounting the shock absorber, because drilling any more holes on the CFRP beam is not recommended for its reliability. The rear suspension is chosen to use a \u201cH arm\u201d topology3 to eliminate the need for another linkage for toe control. The side effect is that the toe variation during suspension stroke is limited. To recreate the performance of the beam suspension, the tool \u201cnon-linear beam\u201d in ADAMS/Car is used, which is shown in Fig. 4. The non-linear beam is defined as a flexible body made with several connected deformable segments, which is an ideal component to present the behavior of beam spring in multi-body dynamics model. Suspension geometry has been defined using the reference model to reach the performance target. To reach the same performance after substitution with the beam, several tuning and modification of the model may be necessary. As the beam is relatively deformable compared to the rigid control arm in conventional solution, kinematic performance for beam suspension has some variance using the same geometry from reference model" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001456_18_ms-9-327-2018.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001456_18_ms-9-327-2018.pdf-Figure1-1.png", + "caption": "Figure 1. Compliant wiper mechanism.", + "texts": [ + " A compliant mechanism can be modeled with rigid links, joints, and torsional springs by using the pseudo-rigid body model (PRBM) method. In this method, flexural segments are assumed to behave like revolute with torsional springs (Howell, 2001; Lobontiu, 2002). Using this technique, compliant mechanisms can be analyzed and synthesized similarly to rigid body mechanisms. Rigid mechanism synthesis is the preliminary step in the design of a compliant mechanism. Our patented design (Tan\u0131k and Karakus, 2013) (TR 2013- 10617), \u201can original partially compliant wiper mechanism\u201d, is presented in Fig. 1. The flexible links (rocker link and wiper blade pressing arm) and coupler of the four-bar mechanism are designed as a single piece. This design decreases the number of manufacturing steps of the wiper mechanism by forming coupler and rocker links together, from a single piece of steel sheet. The wiper pressing arm is a curved segment which is an extension of the rigid segment of the compliant link. The curvature of this arm provides the required pressing force on the windscreen, since there is no additional torsional spring in the structure. This design provides a significant reduction in the number of parts compared to the conventional rigid wiper mechanism. A detailed isometric view of the wiper mechanism is presented in Fig. 1. 1. Connection between wiper blade and wiper pressing arm 2. Wiper blade and curved wiper blade pressing arm 3. Connection between coupler and rocker (compliant link) 4. Relative position of coupler and rocker. At the undeflected position of the compliant link, the coupler and rocker links are overlapped and stay parallel to each other. Published by Copernicus Publications. 5. Connection of rocker to fixed link by revolute joint 6. Revolute joint between crank and coupler 7. Top view of the mechanism 8", + " The design procedure and the optimization routine are performed considering the L7e electric car (Fig. 4a). According to the dimensions given in Fig. 4b, the free parameters are selected as \u03b3min = 60\u25e6 and 2= 30\u25e6 and link 1 is heuristically optimized for the L7e car as a1 = 400 mm. We then calculated the dimensions of the rigid four-bar mechanism by using the following values in Eqs. (2)\u2013(4): a1 = 400mm, a2 = 91.70mm, a3 = 207.06mm, and a4 = 354.31mm. Wiper blade pressing arm length (Lv) (enlarged view 2 in Fig. 1: the length of the curved beam) is taken as Lv = 320mm. Lv should be approximately equal to half of the wiper arm length (Fig. 5a) so that the wiper blade applies a balanced force towards the windshield. As the wiper blade is attached to the coupler link that executes general plane motion in our design, calculation of the swept area is not as simple as in a conventional wiper mechanism, where the blade is attached to the rocker link and performs a fixed-axis rotation. In order to determine the wiper performance by means of the percentage of swept area over the visible area of the windscreen, an image processing code is used", + " Other components of the test setup are a windscreen model, a water circulation and spraying system, an actuator motor, a proximity sensor, and a cycle counter. www.mech-sci.net/9/327/2018/ Mech. Sci., 9, 327\u2013336, 2018 First the maximum deflection of the compliant segment was measured. It can be observed from Fig. 13 that the maximum deflection of the compliant segment is very close to the value that was calculated theoretically in Sect. 3. The fatigue tests, under continuous water spraying conditions, were then conducted. During the first experiment, the spot-welded connection between the compliant segment and the coupler link (Fig. 1) failed at a low cycle. Investigation of this failure indicated that the spot welding caused a deterioration in the structure of the material that caused a significant decrease in the fatigue strength of this part. The connection between the compliant segment and coupler link was redesigned by using the sandwiching method by bolts. This design also eliminated the stress concentrations at the edges. Following this modification, the prototype successfully completed over 1.1 million cycles, which means infinite life for a part manufactured from steel (Budynas and Nisbett, 2011)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001073_.srce.hr_file_280260-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001073_.srce.hr_file_280260-Figure5-1.png", + "caption": "Figure 5 Robots working on common target trajectories in different spatial positions and orientations with optimized position and avoidance parameters", + "texts": [ + ", ,1 , , ni nn cc ii \u2208== \u03c6 \u03c6 (9) where n is the number of configurations i.e. target points. Typically neurosurgical systems can use dual arm configurations with two different robots with different characteristics. The presented approach does not depend on the type of the robot used. The only requirement is to know the inverse and forward kinematic models of the used robots. For illustration of the optimization solutions, some of the simulated scenarios with the relations between the mutual working frame (phantom) and the robots are shown in Fig. 5. After running the optimization for several random phantom heights and orientations a very high execution rate for all phantom trajectories was noted. By setting the parameters as in section 3.1, no collisions for executed trajectories occurred between robots. Also, the linear movement from the trajectory entry to target points was executed without problems. High dexterity is here very important because linear movements can bring problems regarding singularity positions in the movement. Eventual positioning of the working frame outside of the robots workspace would also appear with the lack of IK solutions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000938_.2478_mspe-2020-0039-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000938_.2478_mspe-2020-0039-Figure9-1.png", + "caption": "Fig. 9 Diagram of pressing the pipe open from the front: 1 \u2013 pressed element, 2 \u2013 pneumatic hammer, 3 \u2013 control valve, 4 \u2013 supporting device, 5 \u2013 hose delivering compressed air, 6 \u2013 compressor", + "texts": [ + " In the method of pneumatic pressing it is possible to use the elements opened from the front as well [1, 10]. An installation of open elements causes that the extracted ground gets into the installation from the front, filling it in completely. A removal of the ground is carried out after reaching the final excavation by pushing it out with use of a so called air-lock. Due to lack of the soil compacting necessity, the dimensions of installed elements reach even 1400 mm. A diagram of the described method is presented in Fig. 9. Source: [8]. Another used method is the system of mechanical drilling which enables to make a passage in an trenchless technology, making a horizontal rebore with use of the head disintegrating the ground and with use of the right transport system [1, 8]. A rotary motion of the head ensures cutting of the ground and the platform auger, coupled with it, enables a transport to the initial excavation. Drilling can be made in one stage or in two stages. The drilling - pressing device consists of a pressure unit together with a hydraulic cylinder, a feeding screw with a drilling head and with pressed elements of the pipe" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure13-1.png", + "caption": "Fig. 13 The Equivalent stress on the e side of the spiroid worm drive.", + "texts": [ + "1299/jamdsm.2023jamdsm0073] A fixed constraint was set on the inner cylindrical wall of the worm gear and the cylindrical support is applied to the pinion cylinder, and the tangential direction was kept free. Finally, a torque of 100N\u00b7m was set on the pinion cylinder, as shown in the picture below: After the above Settings are completed, the equivalent stress and contact state of the wormwheel and pinion are calculated and results are shown in the following figures. 11 According to Fig. 12 and Fig. 13, when \u03b4=5\u00b0, the maximum equivalent stress on i surface and e surface of pinion is 614Mpa and 588Mpa respectively. The equivalent maximum stress on i surface of the wormwheel is 948Mpa and e surface is 595Mpa. According to the simulation results of sress, it is easy to observe that the equivalent stress on the iside is larger than that on the e-side, which is consistent with the analysis results of the induction method curvature in chapter 3. Figure 15 and Figure 16 illustrate the case when \u03b4=0, the maximum stress on i surfece and e surface of pinion is 426Mpa and 384Mpa respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000005_JETMR18-CINSP-09_511-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000005_JETMR18-CINSP-09_511-Figure1-1.png", + "caption": "Figure 1: Structure of proposed antenna", + "texts": [ + " DRA wideband is attainment for low values of dielectric constant [2] as the bandwidth of the DRA is conversely proportional to the dielectric constant. The DRA can be available in different shapes cylindrical rectangular, hemispherical [6]-[7]. During research work multiband featured such as pentagon, stair rectangular DRA are also obtained from different shapes [8]-[9]. Out of these elementary shapes, cylindrical DRA is highly used because of its extensive commercial obtain ability and diversified radiation pattern. 2. Antenna Design Figure 1 shows structure of annular shape microstrip feed with a ring DRA with reformed pentagon slot antenna. The proposed antenna is designed on an inexpensive FR4 substrate having dielectric constant of \u0190r 4.4, thickness hs =1.6, loss tangent 0.02. The length and width of the Http://www.ijetmr.com\u00a9International Journal of Engineering Technologies and Management Research [63] ground plane and substrate are 50mm x 50mm. The outer diameter DO of the DRA is 22mm and the internal diameter DI of the DRA. H is the height of the DRA is 11mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004768_9668973_09764722.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004768_9668973_09764722.pdf-Figure11-1.png", + "caption": "FIGURE 11. Comparison of the rotor figuration. (a) GO initial model. (b) Robust model.", + "texts": [ + "1 (3) where objt_ave, objt_ripple, objTHD, and objcogging are normalized average torque, torque ripple, B-EMFTHD, and cogging torque value. In order to focus on reducing the pulsation characteristics, weights on the torque ripple and B-EMFTHD are set as 0.4 and the target of the optimization is maximizing the objfinal . As a result of design optimization, a robust global solution was derived. The variables of the GO initial model and the robust model are tabulated on Table 4, and the rotor configuration is shown in Fig. 11. The performance comparison of the GO initial model and robust model is listed in Table 5. The average torque, torque ripple, B-EMF THD, and cogging torque, which are considered objectives, are 1.82%,\u221237.60%,\u221213.84%, and 29.36% improved, respectively. As the performances of the considered objectives of the robust model were improved compared with GO initial model, the applicability of the IMROA to the practical motor design optimization is verified. The effect of GO utilization and design optimization is tabulated in Table 2 and Table 5, respectively, and each method improves the performance of the IPMSM of the HEV application" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure10.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure10.2-1.png", + "caption": "Figure 10.2. A typical control blade geometry [26].", + "texts": [ + " The control blade is an S-R link that has its R joint axis in the vertical direction, with the S joint connecting to the vehicle-body forward of the wheel carrier. In practice, this type of S-R link may be realized with a thin metal \u201cblade\u201d, connecting with a rubber bushing to the vehicle body and attaching rigidly to the wheel carrier. The R joint mobility is thus provided by flexion of the control blade [26, pp. 260, 327\u2013328]. The control blade is typically completed with three lateral S-S links, as shown in 148 Figure 10.2. This suspension is commonly-used and was introduced by the 1999 Ford Focus [18, p. 404]. Its ubiquity and distinctiveness amongst other suspension types using the S-R link made it the example of choice for this chapter. To design control blades, the R joint axis is required to be vertical. In other words, u1 = k. What this means is that, at most, design position velocity and a Position 2 can be specified. This is because defining u1 completely removes three design variables. Unfortunately, experience has shown that synthesizing S-R links for design position velocity and a second position with u1 = k produces links that do not fit in a reasonable amount of space" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.10-1.png", + "caption": "Figure 2.10: SLADe under fully automated flight control (left) and arrangement of control surfaces (right) (15)", + "texts": [ + " It is two times bigger than the Black Widow, with total wingspan of 30cm (Figure 2.9). Control surface is also elevons configuration. However, due to the bigger size of the MAV, it can accommodate more components than the Black Widow. The complete control board is about 10cm long, consists of a tri-axis gyroscope, a tri-axis accelerometer, absolute and differential pressure sensors, on-board and environment temperature sensors, and a GPS module (14). A team at Stellenbosch University (South Africa) built an autonomous ducted-fan UAV shown in Figure 2.10. It was named as SLADe (Surface Launched Aerial Decoy). Feedback signals are obtained by MEMS inertial sensors, a GPS receiver, a magnetometer and an ultrasonic altimeter. It is a counter-rotating ducted-fan aircraft (i.e. each motor at the top and bottom of the duct rotates in opposite direction); therefore, the motor torque can be minimized. Control of the MAV is governed by varying speeds of the two motors and deflection of eight flaps near the duct\u2019s exit. The flaps\u2019 arrangement is shown in Figure 2.10, too. To design the control system, mathematical model of the aircraft was developed and linearised about hover trim condition. Five proportional-integral (PI) control systems were implemented, allows the aircraft to navigate in three-dimensional space while maintaining Chapter 2: Previous work on MAV development 11 an arbitrary heading angle, however, takeoff and landing still need to be manually performed (15). People at Drexel University (the USA) developed a very interesting fixed-wing MAV which can hover like a helicopter" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003058_010.5__63066-1___pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003058_010.5__63066-1___pdf-Figure2-1.png", + "caption": "Figure 2. COLLISION SCENARIO FOR THE EXPERIMENTAL TEST THAT IS BEING DESIGNED.", + "texts": [ + " The nonlinear force element is defined for elasto-plastic loading/unloading as ( ) ( ) ( ) 0 1 0 1 1 1 1 1 1 0 0 0 0 1 a m m m m a a a a T T if d R K T f K d if d d R K K d d if d d d R K d d \u2212 = + + \u23a7 \u239b \u239e\u23aa > \u2227 =\u239c \u239f\u23aa \u239d \u23a0\u23aa \u239b \u239e\u23aa= < < \u2227 =\u23a8 \u239c \u239f \u239d \u23a0\u23aa \u23aa \u2212 + < < \u2227 =\u23aa \u23aa+ \u2212\u23a9 \u2211 (7) and the nonlinear force element is defined for the plastic deformation lines loading/unloading as ( ) ( ) ( ) 0 1 1 0 1 1 1 R R R R R 0 R F T F K d d if d d R Kf F T T if d d R K \u23a7 \u239b \u239e\u2212 \u2212 \u2212 \u2212 > \u2227 =\u23aa \u239c \u239f \u23aa \u239d \u23a0= \u23a8 \u239b \u239e\u2212\u23aa \u2212 < \u2227 =\u239c \u239f\u23aa \u239d \u23a0\u23a9 (8) where Ki is the slope of the linear force segment i. The force is applied on the bodies along the line connecting the attachment points of the nonlinear force element. The contribution of other train related force elements that represent the friction forces between the system bodies or the vehicle suspension elements are described in reference (Milho, Ambr\u00f3sio & Pereira, 2002). The type of test collision scenario, that is used here to validate the design of the energy absorbing components of the train vehicle, is displayed in Figure 2. The corresponding multibody model includes three cars, for which the individual models are described in reference (Milho, Ambr\u00f3sio & Pereira, 2003) and summarized here. The topology of each train car represented in Figure 3 is used to model the three vehicles involved in the test to be designed. Five rigid bodies, B1 through B5 represent the passenger compartment, bogie chassis and deformable end NII-Electronic Library Service Copyright\u00a0 (c)\u00a0 2010\u00a0 by\u00a0 JSME\u00a0 extremities. The relative motion between the multibody components is restricted by revolute joints, R1 and R2, and by translation joints, T1 and T2", + " The inertia properties of the system components are shown in Table 1. For the bogies, the masses of bodies B2 and B3 are considered to be 1600 kg. The wheels and axles have a mass of 2800 kg and move only in x direction. The initial positions of the bodies along y are obtained considering that the static position of the global center of mass of group of bodies that define car-bodies A, B and C. The initial positions of the rigid bodies are obtained from the car-bodies geometries. M \u2013 mass; J \u2013 polar moment of inertia. In Figure 2 two energy absorption regions of the train car-bodies are identified. The high-energy zone (HE) corresponds to the structure designed to absorb by plastic deformation significant amounts of energy, located in the train extremities. The low energy zones (LE) refer to the regions of the car-bodies where potential impact can occur between consecutive cars of the same train set, which are generally required to absorb lower levels of energy. During a collision the energy absorption in the train occurs at the lowenergy zones, due to the couplers and buffers deformations, and at the high-energy ends, in virtue of the car-end structure deformation", + " Thus in this kind of analysis the initial conditions for the sensitivities are in general null. The optimization problem presented herein is used to design an experimental train crash test. The purpose of this experimental test is the validation of the low-energy end design developed within the framework of Brite/Euram III project SAFETRAIN (2001). The experimental test consists in having a vehicle moving with a velocity of 54 Km/h toward a composition with two vehicles stopped on the railroad, as depicted in Figure 2. The two stopped vehicles are equipped with the low-energy ends and connected by a coupler device. Vehicle C is equipped with a high-energy device in the colliding end. The optimum design problem consists in finding the masses of the train cars and the force level for the high-energy device, in order for the lowenergy devices to absorb energy of 1.4 MJ during the experimental test. A design constraint is imposed for the high-energy device that prevents it from having an energy absorption exceeding 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure2.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure2.3-1.png", + "caption": "Figure 2.3: TE polarized mode projected at an oblique angle on an interface between two lossless media (\u03b51 > \u03b52)", + "texts": [ + " Confined Propagation Mechanism Before stepping into the analysis of the propagation along the human body model, it is interesting to introduce the mechanism of the skin-confined onbody propagation. For two lossless media with the same permeability \u00b5, there is an oblique angle \u03b8c with respect to the normal of the interface between the two media, called the critical angle, which allows total reflection when a plane wave arrives on the interface with an incident angle equal to or greater than \u03b8c. This effect occurs only when the wave propagates from a denser media 1 to a less dense media 2, i.e., \u03b51 > \u03b52. As shown in figure 2.3, assuming a TE polarized wave (i.e., the electric field is only in the y-axis direction) propagates from the media 1 to the media 2 with an oblique incident angle \u03b8i. The angles \u03b8i, \u03b8r, and \u03b8t are respectively the incident, reflected, and transmitted wave angles relative to the normal of the interface. These three angles follow the Snell\u2019s law of refraction \u03b8r = \u03b8i (2-10) \u03b21 sin \u03b8i = \u03b22 sin \u03b8t (2-11) where \u03b21 and \u03b22 are the intrinsic wavenumbers of the two lossless media \u03b2i = \u03c9 \u221a \u00b5i\u03b5i (i = 1, 2) (2-12) The critical angle is given in [139] as \u03b8c = sin\u22121 (\u221a \u00b52\u03b52 \u00b51\u03b51 ) (2-13) We can see from (2-11) that when \u03b8i = \u03b8c, the transmission angle \u03b8t is \u03b8t = sin\u22121 ( \u03b21 \u03b22 sin \u03b8i ) = sin\u22121 (\u221a \u00b51\u03b51 \u00b52\u03b52 \u221a \u00b52\u03b52 \u00b51\u03b51 ) = sin\u22121(1) = 90\u25e6 (2-14) which means the transmitted wave propagates along the interface between the two media" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001782_f_version_1663924178-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001782_f_version_1663924178-Figure7-1.png", + "caption": "Figure 7. Boundary condition applied in FEA. 1\u2014femoral head, 2\u2014bone screw, 3\u2014implantable lengthening nail, 4\u2014medial condyle, 5\u2014lateral condyle.", + "texts": [ + " In this section, both mechanical stiffness and torques are analyzed and simulated while the driving torque is tested with the torque measurement system. Referring to the characteristics given in Table 1, the implantable lengthening nail is designed according to the parameters listed in Table 3. The implantable lengthening nail starts to distract along with the distal bone after clinicians perform an osteotomy. In our case, the maximal allowable distraction length showed an 80 mm gap between the proximal and distal bone at the end of the distraction period and before the consolidation phase (shown in Figure 7). Three principal forces acting on the femur throughout six gait phases (shown in Table 2) are applied at the lateral and medial condyle, while fixed support is applied at the femoral head. FEA is used to examine the implantable lengthening nail maximal stress and minimal natural frequency. According to the results of Table 4 and Figure 8, we noticed that the highest value of Von-Mises Stress occurs around the 80 mm gap, especially during the fifth phase of the walking gait cycle (around 952.15 MPa)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000403_citation-pdf-url_382-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000403_citation-pdf-url_382-Figure2-1.png", + "caption": "Figure 2. Definition of the Parameters in D-H Model", + "texts": [ + " On the subject of error analysis, Wang, J. & Masory, O. 1993, Gong, C. et al, 2000, Patel, A. J. & Ehmann, F. E. 2000 used forward kinematic solutions to obtain errors. Jacobian matrix was also used in obtaining errors. On the subject of the variation of parallel configurations, based on the work done by Dhingra, A. K. et al, 1999, 2000, Geng, Z. & Haynes, L. S. 1994, the influence of the configurations on the methods of finding closed form solutions can be found. In this paper, the D-H model (Figure 2) is used to define the TAU robot configuration, a complete set of parameters is included in the modeling process. Kinematic model and error model are established for including all types of errors using Jacobian matrix method for the TAU robot. Meanwhile, a very effective Jacobian Approximation Method is introduced to calculate the forward kinematic problem instead of the Newton-Raphson method. It denotes that a closed form solution can be obtained instead of a numerical solution. A full size Jacobian matrix is used in carrying out error analysis, error budget, and model parameter estimation and identification" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001044_a8fa772056d4fd55d520-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001044_a8fa772056d4fd55d520-Figure16-1.png", + "caption": "Fig. 16. RSI hygro-mechanical FEM. (Color online only)", + "texts": [ + " The vacuum induced dry out effect in composite structures is another possible issue that could impact optical images. Thus, the moisture desorption effect in M55J/954-3 material needs to be validated in order to analyse the defocusing effect between M1 and M2. To predict the moisture release deformation of composite materials, the coefficient of moisture expansion (CME) and maximum moisture content of M55J/954-3 need to be determined using moisture absorption/desorption tests (ASTM 2004). Once this information is obtained the numerical hygro-mechanical RSI finite element model (RSI FEM, shown in Fig. 16) can be created and the defocusing variation obtained. From Yang (2013, 2014), the CME values of M55J/954-3 material tube are calculated using the classical laminate theory. Point zero eighty-two per cent of the maximum moisture content can be measured on the M55J/954-3 UD flat sample and set as the environmental control value during RSI flight model assembly, alignment and calibration. According to the numerical prediction from RSI FEM, if the RSI structure humidity environment is well controlled to prevent additional moisture absorption after the RSI is baked out, 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001956_al-00674689_document-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001956_al-00674689_document-Figure4-1.png", + "caption": "Fig. 4: Overview of the multilayer winding (nl = 2)", + "texts": [ + " Furthermore, when a vacuum system is used, the behavior of brushes is poor even with DC current and heat transfer since the rotor is limited by conduction through the brushes. The field coil fed by a DC current creates a homopolar flux in the airgap and magnetizes the solid steel discs. The rotation creates a rotative axial field. The torque is created by interaction between this field and the rotating field produced by the three-phase armature winding. In Fig. 2, the main parameters used in this paper are given. 0-7803-7420-7/02/$17.00 \u00a9 2002 IEEE III. WINDING The principle of the multilayer winding is displayed in Fig. 4. Only one two-layer elementary element is shown. This winding is a double-face printed circuit in which each pole is connected to the same pole on the other face. A phase is constituted by associating nl electricallyconnected layers in series. For a three-phase motor with four pole pairs (p = 4), the phases are displaced by 120/p mechanical degrees. This technology is attractive because each phase is printed separately: the problem of crossing the ends of the windings has therefore been resolved" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002543_apers_D_N010104f.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002543_apers_D_N010104f.pdf-Figure5-1.png", + "caption": "Figure 5: The stresses at the waist section of a hyperboloid shell. (a) Stress components; (b) equivalent straight bars (aligned with the generators) placed at equal spacing to take up the stresses; (c) equilibrium of forces on a shell segment.", + "texts": [ + " This is because, for a hyperboloid shell, r1 is negative and r2 is positive. Now pr is negligible due to the cancellous bone within the VB cortical shell. Hence, by substituting pr = 0 (i.e. for an internally non-pressurized cortical VB hyperboloid shell) in eqn (9), we obtain N\u03c6 = ( r1 r2 ) N\u03b8. (10) Substituting r1 = (b2/a4)r3 2 from Fig. 2 into eqn (10), we obtain N\u03c6 = ( b2 a4 r2 2 ) N\u03b8. (11) 3.1 Stress analysis under axial compression We will now analyse the stresses in the hyperboloid shell (generators) due to a uniaxial compressive force, as shown in Fig. 5. Assume that there are two sets of n number of straight bars, placed at an equal spacing of (2\u03c0a/n) measured at the waist circle, which constitute the hyperboloid surface as shown in Fig. 5b. Due to the axisymmetric nature of the vertical load, no shear stresses are incurred in the shell, i.e. \u03c3\u03c6\u03b8 = 0 as in Fig. 5a. We then delineate a segment of the hyperboloid shell and consider its force equilibrium (as illustrated in Fig. 5c). At any horizontal section, by force equilibrium (2\u03c0r0) N\u03c6( sin \u03c6) = C. (12) Now, consider the segment at the waist circle, where \u03c6 = 90\u25e6 and r2 = r0 = a (throat radius), (2\u03c0a) N\u03c6 (\u03c6=90\u25e6) = C or N\u03c6 (\u03c6=90\u25e6) = C 2\u03c0a (compressive). (13) At the waist circle where r2 = a, eqn (11) yields N\u03b8(\u03c6=90\u25e6) = ( a4 b2 1 r2 2 ) N\u03c6 (\u03c6=90\u25e6) = ( a2 b2 ) N\u03c6 (\u03c6=90\u25e6), which on combining with eqn (13), leads to N\u03b8(\u03c6=90\u25e6) = ( a2 b2 ) C 2\u03c0a = C 2\u03c0a tan2 \u03b2, (14) which is compressive in nature. From Fig. 6, the equivalent resultant compressive force Fc in a fibre (generator of the hyperboloid surface) is given by F2 c = [ N\u03c6 ( \u03c0a n )]2 + [ N\u03b8 ( \u03c0b n )]2 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure52-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure52-1.png", + "caption": "Figure 52 P-POD Mk. IV Door Design", + "texts": [ + " The puzzling aspect of the Mk. III Rev. E Door, is that the stiff structure section is not directly on the load path between the CubeSat rail interface and the Door anchoring points. The more ideal case would be to have the CubeSat rails directly interface with the stiff structure of the door. A beam style design was used, using the geometry to maximize stiffness without a substantial increase in mass. From there, structure was routed towards the NEA anchoring point. The resulting Door design is shown below in Figure 52. The thicker ribs resulted in a mass Page 67 increase of 18 grams, but this was acceptable provided that the part was stiffer and stronger. In order to evaluate this part, an FEA was conducted. The hinge hole was constrained as a pin constraint to allow the door hinge to rotate around its axis. The release bolt hole and cone were fixed. The Z-axis load was applied to 4 square areas on the Door to simulate the manner the CubeSat loads the Door. Door deflection was evaluated to make sure no significant gaps were formed as a result of the loading that may lead to EMI leakage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001232_f_d2me2017_02004.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001232_f_d2me2017_02004.pdf-Figure7-1.png", + "caption": "Figure 7. The result of balance-arm", + "texts": [ + "1 Balance-arm MATEC Web of Conferences 136, 02004 (2017) DOI: 10.1051/matecconf/201713602004 D2ME 2017 MATEC Web of Conferences The loads on the balance-arm include the weight of counter, platform, luffing mechanism, balance-arm, the wind load and the tension of wire rope. The wind load of balance-arm can be got as: Fw=Cw pw\u03c9lh (1) Here Cw is wind coefficient 1.6, pw is rated wind pressure 250Pa, \u03c9 is structure full ratio 1.0, l is length of balance-arm, h is width of balance-arm. The result of finite element analysis is shown in Figure 7. The maximum equivalent stress of balance-arm is 50MPa, which is much less than the allowable stress [\u03c3]Q345B=259.40MPa. So the truss structure of balance-arm can meet the strength requirements. The tower head is mainly loaded with the tension force of lifting-arm and balance-arm. So there are 2 important work cases: 1) 3.125t load (overloading 25%) at 21m and the amplitude of balance-arm is the maximum 8m; 2) 5t load (overloading 25%) at 12.5m and the amplitude of balance-arm is 8m. The result is shown in Figure 8", + " References MATEC Web of Conferences 136, 02004 (2017) DOI: 10.1051/matecconf/201713602004 D2ME 2017 MATEC Web of Conferences The loads on the balance-arm include the weight of counter, platform, luffing mechanism, balance-arm, the wind load and the tension of wire rope. The wind load of balance-arm can be got as: Fw=Cw pw\u03c9lh (1) Here Cw is wind coefficient 1.6, pw is rated wind pressure 250Pa, \u03c9 is structure full ratio 1.0, l is length of balance-arm, h is width of balance-arm. The result of finite element analysis is shown in Figure 7. The maximum equivalent stress of balance-arm is 50MPa, which is much less than the allowable stress [\u03c3]Q345B=259.40MPa. So the truss structure of balance-arm can meet the strength requirements. The tower head is mainly loaded with the tension force of lifting-arm and balance-arm. So there are 2 important work cases: 1) 3.125t load (overloading 25%) at 21m and the amplitude of balance-arm is the maximum 8m; 2) 5t load (overloading 25%) at 12.5m and the amplitude of balance-arm is 8m. The result is shown in Figure 8. The maximum equivalent stress of head is 70.8MPa in case 1, 96.1MPa in case 2, much less than the allowable stress. So the lifting-arm and the whole structure can meet the strength requirements. Figure 7. The result of balance-arm (a) Case 1 (b) Case 2 Figure 8. The result of head In this paper the new moveable balance-weight system is proposed based on crane SXD50. Compared with the traditional type, the balance-weight can rotate around platform pulled by the luffing mechanism. The design can realize the moment equilibrium between the forward torque and the backward torque, which not only achieves the predetermined lifting ability, but also improves the force status of crane structure. All the parts of moveable balance-weight system meet the strength requirements with a big redundancy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001484__EEE-THESES_1563.pdf-Figure3.15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001484__EEE-THESES_1563.pdf-Figure3.15-1.png", + "caption": "Fig. 3.15 Near-field simulation: SPL patterns on the measuring plane by the use of (a) MCG method and (b) TD method. The target region is highlighted by the black circle in the center.", + "texts": [ + " This result means that the MCG method is more effective in focusing acoustical energy in the target region. 99 In general, in the far-field case, the MCG method is effective in acoustical hotspot generation, whereas the TD method is not applicable. 3.2.6.4 Near-field simulation In this section, the near-field simulation is presented. The same configuration as in the far-field simulation is used, except that the target region is set to 0.5 mD = away from the array. Since 0.61 mhD r< = , this simulation represents a near-field case. The resulting patterns are shown in Fig. 3.15 (a) and (b) correspondent to the MCG and TD methods, respectively. The SPL distributions along the measuring line by the two methods are demonstrated in Fig. 3.16. Numerical results are listed in Table 3.4. 100 is successfully synthesized in the circular region using both methods, and the overall patterns are nearly the same. According to Table 3.4, the average SPL in the target region is \u20130.30 dB using the MCG method, slightly higher than the SPL (\u20131.37 dB) using TD method. This similar performance is also demonstrated in the SPL distribution on the measuring line, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002938_f_version_1649840248-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002938_f_version_1649840248-Figure2-1.png", + "caption": "Figure 2. The equivalent circuit of the EESM (a) in the d-axis direction referred to the stator winding; (b) in the q-axis direction referred to the stator winding.", + "texts": [ + " The model of EESM is described in d-q reference frame with the following system of voltage Equations (1)\u2013(3) [18]: ud = Rsid + d\u03c8d dt \u2212 d\u03b8r dt \u03c8q (1) uq = Rsiq + d\u03c8q dt + d\u03b8r dt \u03c8d (2) u f = R f i f + d\u03c8 f dt (3) Energies 2022, 15, 2832 4 of 24 In the Equations (1)\u2013(3), the id, iq and ud, uq are the d-axis and q-axis components of the stator current and voltage; u f \u2014voltage of the field winding; i f \u2014the field winding DC current; \u03c8d and \u03c8q are the d-axis and q-axis components of the stator flux linkage; \u03c8 f \u2014rotor flux linkage; \u03b8r\u2014rotor angle; Rs and R f stator and field winding resistances, respectively. Based on the system of Equations (1)\u2013(3), the equivalent circuit of the EESM in rotor reference frame is presented in Figure 2. The advantage of the rotor reference frame is that the values of motor inductances remain constant during the change of the rotor position [18]. Energies 2022, 15, x FOR PEER REVIEW 4 of 25 \ud835\udc62 = \ud835\udc45 \ud835\udc56 + \ud835\udc51\ud835\udf13\ud835\udc51\ud835\udc61 + \ud835\udc51\ud835\udf03\ud835\udc51\ud835\udc61 \ud835\udf13 (2) \ud835\udc62 = \ud835\udc45 \ud835\udc56 + \ud835\udc51\ud835\udf13\ud835\udc51\ud835\udc61 (3) In the Equations (1)\u2013(3), the \ud835\udc56 , \ud835\udc56 and \ud835\udc62 , \ud835\udc62 are the d-axis and q-axis components of the stator current and voltage; \ud835\udc62 \u2014voltage of the field winding; \ud835\udc56 \u2014the field winding DC current; \ud835\udf13 and \ud835\udf13 are the d-axis and q-axis components of the stator flux linkage; \ud835\udf13 \u2014rotor flux linkage; \ud835\udf03 \u2014rotor angle; \ud835\udc45 and \ud835\udc45 stator and field winding resistances, respectively. Based o the system of Equations (1)\u2013(3), the equivalent circu t of the EESM in rotor reference frame is presented in Figure 2. The a vantage of the rotor reference frame is that the values of motor inductances remain constant during the change of the rotor position [18]. In Figure 2, \ud835\udc56 , \ud835\udc56 and \ud835\udc62 , \ud835\udc62 are the d-axis and q-axis components of the stator current and voltage; \ud835\udc62 voltage of field winding; \ud835\udc56 is the field winding DC current; \ud835\udc3f and \ud835\udc3f direct and quadrature magnetizing inductances; \ud835\udc3f leakage inductance of the stator; \ud835\udf13 and \ud835\udf13 are the d-axis and q-axis components of the stator flux linkage; \ud835\udc45 and \ud835\udc45 are stator and field winding resistances, respectively. In order to model the EESM in the d-q reference frame, it is necessary to define the following motor parameters: (1) \ud835\udc45 \u2014stator resistance; (2) \ud835\udc3f \u2014stator leakage inductance; (3) \ud835\udc3f \u2014direct axis magnetizing inductance; (4) \ud835\udc3f \u2014quadrature axis magnetizing inductance; (5) \ud835\udc45 \u2014rotor resistance referred to the stator side and (6) \ud835\udc3f \u2014rotor leakage inductance referred to the stator side. The inductances of synchronous motor model are calculated in the rotor reference frame as shown in Equations (4)\u2013(6). \ud835\udc3f = \ud835\udc3f + \ud835\udc3f (4)\ud835\udc3f = \ud835\udc3f + \ud835\udc3f (5)\ud835\udc3f = \ud835\udc3f + \ud835\udc3f (6) where the magnetizing inductances (\ud835\udc3f , \ud835\udc3f ) were taken as constant values (the magnetic nonlinearity of EESM ferromagnetic materials was neglected due to EESM operation In Figure 2, id, iq and ud, uq are the d-axis an q-axis components of the stator current and voltage; u f voltage of field winding; i f is the field winding DC current; Lmd and Lmq direct and quadrature magnetizing inductances; L\u03c3s leakage inductance of the stator; \u03c8d and \u03c8q are the d-axis and q-axis components of the stator flux linkage; Rs and R f are stator and field winding resistances, respectively. In order to model the EESM in the d-q reference frame, it is necessary to define the following motor parame ers: (1) Rs\u2014stator resistance; (2) L\u03c3s\u2014stator leakage inductance; (3) Lmd\u2014direct axis magnetizing inductance; (4) Lmq\u2014quadrature axis magnetizing inductance; (5) R\u2032f rotor resistance referred to the stator side and (6) L\u2032f \u2014rotor leakage inductance referred to the stator side" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000853_9668973_09718336.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000853_9668973_09718336.pdf-Figure11-1.png", + "caption": "FIGURE 11. Experimental setup of the angular resolution and repeatability test.", + "texts": [ + " 10 and Table 1 present the torque results as a function of the rotational angle. In the conventional mechanism, the maximum torque was measured to be 2.326 N\u00b7m when the rotational angle was the 24044 VOLUME 10, 2022 largest. Contrary to these natural phenomena, in the proposed revolute joint, the maximum torque was measured to be 0.015 N\u00b7m at 35\u25e6. B. ANGULAR RESOLUTION TEST To determine how much the angular resolution of the proposed mechanism has improved compared with the conventional mechanism, we conducted the angular resolution test, as shown in Fig. 11. The experimental setup consists of the proposed revolute joint, digital indicator, and articulating arm. We used a digital indicator (543-794B, MITUTOYO Corporation, Sakado, Japan) with a resolution of 1 \u00b5m and repeatability equal to 2 \u00b5m. The revolute link was designed to be contacted with the digital indicator 150 mm away from the rotational axis. When we rotated the motor by 90\u25e6, the vertical displacement at the tip was measured with the use of the digital indicator. Through the measured displacement, the angular displacement of the proposed mechanism1\u03b8p can be obtained as follows, 1\u03b8p = tan\u22121 dv lr (12) where dv and lr are the vertical displacement and the length of the revolute link, respectively", + " Based on the experiment, it was confirmed that the angular resolution of the proposed mechanism was increased approximately 77.5 times at 0\u25e6 and approximately 743.3 times at 70\u25e6 compared with the conventional mechanism. C. REPEATABILITY TEST In the medical robot, repeatability is important and had a significant impact on surgical outcomes. To confirm that the proposed revolute joint has a high repeatability, we repeatedly measured the tip position of the revolute link. The experimental setup was the same as the experimental setup for the angular resolution test, as shown in Fig. 11. The repeatability tests were conducted from 0\u25e6 to 15\u25e6, 30\u25e6, 45\u25e6, 60\u25e6, and 70\u25e6. The respective reverse direction tests were also conducted. Each set was repeated 30 times, and the results are listed in Table 3. We assessed the repeatability based on the standard deviation of the repeated positions. The repeatability was similar in all ranges and averaged approximately 1.43 \u00b5m. In addition, we evaluated the repeatability performance based on the coefficient of variation (CV) [18]. The CV of the proposed revolute joint varied from 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002893__icape2024_03014.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002893__icape2024_03014.pdf-Figure1-1.png", + "caption": "Fig. 1. Powered walking roof support type design: 1 \u2013 top beam; 2 \u2013 hydraulic rack; 3 \u2013 side guard; 4 \u2013 heading section; 5 \u2013 lagging section; 6 - bridge.", + "texts": [ + " The authors believe that one of the promising solutions to improve the efficiency and safety of tunneling operations is a powered walking roof support, which allows to create a temporary secure fastening of the mining face space above the tunneling combine and allows to anchor the mines without stopping the combine and outside its working area [2]. Thus, the powered walking roof support provides mechanized support for the roof of the mine and reduces the number of the tunneling combine forced stops for the roof fastening device. The powered walking roof support (Figure 1) in the mining creates an advanced temporary support of the roof rocks due to the alternating cyclic walking of the two-section support structure and the alternate perception of rock pressure from the roof rock mass by its sections, which provides protection of the workspace from roof rock collapses. The walking support moves after the combine, the excavation of the rock mass is carried out under the protection of the support, which ensures guaranteed safety of tunneling and increases the speed of excavation", + " The authors believe that one of the promising solutions to improve the efficiency and safety of tunneling operations is a powered walking roof support, which allows to create a temporary secure fastening of the mining face space above the tunneling combine and allows to anchor the mines without stopping the combine and outside its working area [2]. Thus, the powered walking roof support provides mechanized support for the roof of the mine and reduces the number of the tunneling combine forced stops for the roof fastening device. The powered walking roof support (Figure 1) in the mining creates an advanced temporary support of the roof rocks due to the alternating cyclic walking of the two-section support structure and the alternate perception of rock pressure from the roof rock mass by its sections, which provides protection of the workspace from roof rock collapses. The walking support moves after the combine, the excavation of the rock mass is carried out under the protection of the support, which ensures guaranteed safety of tunneling and increases the speed of excavation", + " The bottom-hole part of the workings is supported by protecting sections of the walking support 2, creating a temporary safety fastening and forming a safe working space, while the anchor installer 3 is also placed under the overlap of the walking support 2 in the side of the passed workings, which allows simultaneously with the excavation of the rock mass to permanently fix the roof and sides of the workings. Transportation of the recaptured rock mass is carried out by vehicle 4 in the mining area with a permanent anchorage. Fig. 1. Powered walking roof support type design: 1 \u2013 top beam; 2 \u2013 hydraulic rack; 3 \u2013 side guard; 4 \u2013 heading section; 5 \u2013 lagging section; 6 - bridge. One of the urgent scientific tasks in creating a walking temporary support is to determine its optimal technical parameters that support the roof in the tunneling face and are sufficient to perceive the emerging loads from the roof rocks. The experience of operating underground equipment requires to reduce the metal and energy consumption of the structure and support elements", + "2 mm) with RFID module allowing to control all processes in mining face from coal heading (Figure 4). GHH Group [12] and specialists from Nerospec SK develops technologies for full automation and remote control. With radio control panel T-RX100J designed by GHH Group operator can control mining devices from safe distance. The main advantage of this technology is universality of usage with other vendors technics. Powered walking roof support contains remote control system allowing operator to remove from mining face and control roof support from safe place (Figure 1). Universal remote control panel for mining devices is presented for working with underground mining and long-wall top coal caving modelling work bench. Remote control panel for moving mining devices has size 300 \u0445 100 \u0445 50 mm. Front panel contains two displays for technological parameters indication and buttons functions demonstration. It has no less than 20 programmable buttons. Back and side panels contains pins for connection to commutation devices. The panel provided with programmable hardware module for experimental mining devices control (Figure 6)", + " GHH Group [12] and specialists from Nerospec SK develops technologies for full automation and remote control. With radio control panel T-RX100J designed by GHH Group operator can control mining devices from safe distance. The main advantage of this technology is universality of usage with other vendors technics. Fig. 5. T-RX100J control panel (GHH Group). Powered walking roof support contains remote control system allowing operator to remove from mining face and control roof support from safe place (Figure 1). Universal remote control panel for mining devices is presented for working with underground mining and long-wall top coal caving modelling work bench. Remote control panel for moving mining devices has size 300 \u0445 100 \u0445 50 mm. Front panel contains two displays for technological parameters indication and buttons functions demonstration. It has no less than 20 programmable buttons. Back and side panels contains pins for connection to commutation devices. The panel provided with programmable hardware module for experimental mining devices control (Figure 6)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000087_5_secm-2014-0048_pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000087_5_secm-2014-0048_pdf-Figure10-1.png", + "caption": "Figure 10 Schematic diagram of the assumed pultrusion facility for cost calculation.", + "texts": [ + " This study focuses on the composite manufacturing processes and the costs for metallic load introductions and the assembly processes involved were not yet considered. The costs are determined by an overhead calculation considering the following direct costs: material cost, labor costs, machine costs, and tool costs [19]. The assumed values for determining the direct costs per driveshaft are specified in Table 2. The design of the new profiled lightweight shaft bodies is predestined for manufacturing by a combined braidingpultrusion process. The pultrusion facility (Figure 10) consists of a mandrel feeding station, braiding wheels for the profiled shell, a preforming station for the axial fibers, and continuous winding machines as well as a braiding wheel for the cylindrical shell. The impregnation and consolidation of the preforms is conducted in a pultrusion die. Following the die, which consists of an impregnation unit as well as a heating and a straightening zone, a caterpillar pull-off unit is pulling off the hollow profile still containing the mandrel. Afterward, a parallel moving saw cuts the consolidated shafts between the mandrels" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003529_8911222_10214345.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003529_8911222_10214345.pdf-Figure9-1.png", + "caption": "FIGURE 9. (a) Cross section of the stack-up. Details of the feeding network for (b) vertical launch connectors and (c) feeding probes (d) bend in the feeding lines. Fabricated prototypes of (e) the cluster array and (f) the reference array.", + "texts": [ + " Therefore, we can conclude that the cluster concept can still support sufficient bandwidth even when the objective is the improvement in spherical coverage. To intuitively demonstrate the beamforming capability, Fig. 8 presents the 2D total scan patterns at 29.5 GHz, which depict the maximum realized gains with optimized feed coefficients towards all angles in the upper hemisphere (+z). The scan patterns highlight the significant improvement of the cluster array over the reference array, as the realized gains of the proposed cluster array are mostly above 6 dBi, while the realized gains at all angles of the reference array remain below 4 dBi. Fig. 9 displays the feeding lines and the fabricated prototypes of the reference array and the cluster array. An additional layer is added underneath the ground plane to incorporate the feeding network as shown in Fig. 9 (a). The prepreg material is R-5680 with \u03b5r = 3.55 and tan\u03b4 = 0.004. The details of feeding lines are illustrated in Fig. 9 (b), (c), and (d). All the microstrip feeding lines on the bottom layer have a width of 0.19 mm and a length of 33 mm. In addition, the top layer is covered with metal to suppress surface waves, leaving a 12\u00d730 mm2 window for radiation. For practicality and ease of measurement, the dimensions Wsub and Lsub are enlarged This work is licensed under a Creative Commons Attribution 4.0 License. For more information, see https://creativecommons.org/licenses/by/4.0/ 2 3 2 4 2 5 2 6 2 7 2 8 2 9 3 0 0 Re fle cti on coe ffic ien t (d B) F r e q u e n c y ( G H z ) S 1 1 S 2 2 S 3 3 S 4 4 S 5 5 S 6 6 S 7 7 S 8 8 (a) 2 3 2 4 2 5 2 6 2 7 2 8 2 9 3 0 0 Re fle cti on coe ffic ien t (d B) F r e q u e n c y ( G H z ) S 1 1 S 2 2 S 3 3 S 4 4 (b) FIGURE 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002029_d.aspx_paperID_79349-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002029_d.aspx_paperID_79349-Figure21-1.png", + "caption": "Figure 21. Bend patch configuration.", + "texts": [ + " The fitted plot has been obtained after deriving the RLC parameters of the equivalent spice circuit. The poles and residues derived from a rational function using Matlab has been shown in Table 4. Figure 20 shows the obtained equivalent spice circuit using ADS tool and the RLC values have been shown in Table 5. DOI: 10.4236/ojapr.2017.53011 146 Open Journal of Antennas and Propagation Patch antenna with and without CSRR loading has been bent with a radius of 20 mm and 40 mm to show the effect of bending. The bend structures have been shown in Figure 21 and Figure 22, while the comparison of the return loss has been plotted in Figure 23. DOI: 10.4236/ojapr.2017.53011 147 Open Journal of Antennas and Propagation The patch configuration as defined in Section 3 has been used for the CSRR loading effect over its resonance frequency. Here the patch element has dimension of 13.9 mm \u00d7 18 mm \u00d7 0.017 mm with its inset feed of 13.05 mm \u00d7 2.8 mm \u00d7 0.017 mm and inset gap of 0.5 mm. This patch element has been laid over 30 mm \u00d7 30 mm \u00d7 1.57 mm Fr4 substrate with its relative permittivity 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001811_article-file_1690258-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001811_article-file_1690258-Figure6-1.png", + "caption": "Figure 6. Magnetic flux density distribution (a) Reference motor model (b) 3 slitted motor model (c) 5 slitted motor model.", + "texts": [ + "m] Relative Difference [%] Maximum 19.0308 23.4392 + 23.164 Average 11.5928 12.9987 + 12.127 When Figure 5 and Table 2 are examined, it is seen that the torque values obtained from the slitted motor model increase. It was determined that the average torque increased by 12.127 % and the maximum torque by 23.164 %. In addition, for making a healthy verify, a 5 slitted motor model has been solved in transient solver. The magnetic flux density distribution of the reference and different slitted motor models are given in Figure 6 (a), (b) and (c). When the figure is examined, it is seen that the flux density values are approximately the same. In Figure 7, the distribution of magnetic flux lines for reference and different slitted motor models are given. It is seen that flux lines can be directed by using slits. Figure 8 shows the current values obtained from the reference and slitted motor models. A slight increase has been observed in the current values obtained from the 3 slitted motor model. There has no difference between the 3 slitted and 5 slitted motor current waveforms" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004185__2022jamdsm0003__pdf-Figure28-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004185__2022jamdsm0003__pdf-Figure28-1.png", + "caption": "Fig. 28 The SC with 69 teeth and the SC with 55teeth", + "texts": [ + " When the CS is slotted the second cycle, the accumulative pitch errors of the one third of the CS tooth number which mentioned above are the red line in Fig.27(b). According to 15 the section 4, the accumulative pitch errors of the CS are shown in Fig.27(c). 2 \u00a9 2022 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2022jamdsm0003] When the tooth number of the SC exceeds half of the CS, the CS slotted by the SC with more teeth has higher transmission accuracy. For testing the correctness of this theoretical analysis, one SC with 55 teeth and another SC with 69 teeth were designed and slotted two circles as shown in Fig. 28. 16 2 \u00a9 2022 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2022jamdsm0003] The CS slotted by the SC with 55 teeth is called A-CS. The CS slotted by the SC with 69 teeth is called B-CS. In the experiment, the two CSs are slotted two cycles. The two CSs are manufactured as shown in Fig. 29. The two CSs are similar. Then, the gear detector was used to detect the accumulative pitch error. The TEC of the CS is calculated based on the accumulative pitch error. As is shown in Fig. 30, the coordinates of the measuring points in the same end face of the CS are measured by the FTA-L4D4000 surface roughness and profile integrated machine" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002655_e_download_1543_1085-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002655_e_download_1543_1085-Figure1-1.png", + "caption": "Figure 1. System Design Block Diagram", + "texts": [ + " In simple terms, the following is the working principle of the relay: when the coil gets electrical energy (energized), an electromagnetic force will arise which will attract the springing armature, and the contact will close. The working principle of this relay is: on C1 and C2 there is a coil as a driver, when C1 and C2 have not passed the current, the Com and No terminals will be connected, and when C1 and C2 are passed the current will move the Com plate so that the Com and No terminals will connected. In general, it consists of several parts which can be described in the following block diagram: The block image of the system block diagram can be seen in Figure 1. The design scheme for the designed tool can be seen in Figure 3.2. as follows If someone performs a voice command with the aim of turning on the load/light, the microphone will convert the sound into an electrical signal after which it will be processed by the sound sensor module with outputs such as, ground, vcc, signal, which will then go to the microcontroller, after processing, the microcontroller will provide a signal in the form of a 5 volt input, ground, and an instruction signal to turn on the lamp by means of a relay module with 1 channel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure10-1.png", + "caption": "Figure 10. (a) Stator end winding simplified model; and (b) inner end winding simplified model.", + "texts": [ + " Although the above equivalent method is a method to analyze the radial heat transfer effect, the extrusion 3-D model of the above equivalent model can also analyze the axial heat transfer effect. The 3-D models of the stator and inner rotor windings are shown in Figure 9. To build an accurate model of the end windings is more difficult than the winding model in the slot. This is mainly because the shape of each end winding isn\u2019t exactly the same and is also difficult to ascertain for the distributed-conductor machine. Therefore, this paper presents a simplified model of the end windings, as shown in Figure 10. Each end winding is equivalent to the two linear-structure windings. The axial length sum of the two linear-structure windings equals the length of one end winding. The linear-structure winding model and its equivalent parameters are the same as that in the slot. To simulate the heat transfer effect in the actual end winding, the end surfaces of two linear-structure windings are set to coupling surfaces to ensure the heat transfer between the two linear-structure windings. Therefore, the heat dissipation of linear-structure end windings depends on their surface (S1 and S2) heat convection coefficient and ambient temperature" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001044_a8fa772056d4fd55d520-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001044_a8fa772056d4fd55d520-Figure3-1.png", + "caption": "Fig. 3. M2 support ring configuration. (Color online only)", + "texts": [ + " Furthermore, the Main Plate is mounted onto the Top Panel by the Main Plate Support Frame, which is the main load path to the satellite bus. The Main Plate is a honeycomb panel composed of CFRP face sheet as well as an aluminium core. The fibre ply orientation and layup sequence for the CFRP face sheet is designed as [0\u00b02/\u00b145\u00b02/90\u00b02]S of M55J/954-3 material. The thickness of each ply is 0.125 mm. The aluminium core is made of 5056 alloy of 1/8-5056-0.002P hexagonal aluminum honeycomb with 50 mm thickness. Figure 3 shows the M2 Support Ring mounted onto the Top Panel by ring supporters and connected to the Main Plate by the M2 Struts Frame. Three (3) M2 Spiders are installed in the inner side of the M2 Support Ring to support the M2 bracket. The M2 bracket is the interface between the M2 Baffle and M2 Fitting. The secondary mirror is then mounted to the M2 Fitting. The M2 Support Ring is a ring shaped sandwich panel made of CFRP face sheet with an aluminium core. The M2 Support Ring face sheet material is [0\u00b02/\u00b145\u00b02/90\u00b02]S ply orientation with M55J/954-3 prepared material, and 5056 alloy of 1/8-5056-0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003431_jsaem_30_1_30_9__pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003431_jsaem_30_1_30_9__pdf-Figure11-1.png", + "caption": "Fig. 11(a)\u306b\u63d0\u6848\u3059\u308b\u8ca0\u8377\u8a66\u9a13\u6cd5\u306e\u63a5\u7d9a\u3092\u793a\u3059[8]\u3002\u8a66", + "texts": [ + "5 mm\uff09\u3092\u7528\u3044\u3066\u5b9f\u9a13\u3092\u884c\u3063\u305f\u3002\u30b3\u30a2\u306e\u5927\u304d\u3055\u304c \u6f0f\u308c\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\u306b\u4e0e\u3048\u308b\u5f71\u97ff\u3092\u4f4e\u6e1b\u3059\u308b\u305f\u3081\uff0c\u30b3 \u30a2\u306f\u307b\u307c\u540c\u3058\u30b5\u30a4\u30ba\u3068\u3057\u305f\u3002\u305d\u308c\u305e\u308c\u306e\u30c8\u30e9\u30f3\u30b9\u306b#1 \u3068#4 \u306e\u5dfb\u7dda\u30ac\u30a4\u30c9\u3092\u4f7f\u7528\u3057\u306a\u3044\u30e2\u30c7\u30eb\u3068\uff0c#1 \u3068#4 \u306e \u5dfb\u7dda\u30ac\u30a4\u30c9\u306e\u539a\u307f\u304c 1.0 mm\uff0c1.5 mm\uff0c2.0 mm\uff0c2.5 mm \u3068\u306a\u308b 4 \u3064\u30e2\u30c7\u30eb\u3092\u5408\u308f\u305b\u3066 5 \u3064\u30e2\u30c7\u30eb\u3092\u5b9f\u6a5f\u691c\u8a3c\u3057 \u305f\u3002#1 \u3068#4 \u306e\u5dfb\u7dda\u30ac\u30a4\u30c9\u3092\u7528\u3044\u306a\u3044\u30e2\u30c7\u30eb\u3067\u306f\uff0c\u4e00\u6b21 \u5dfb\u7dda\u3068\u4e8c\u6b21\u5dfb\u7dda\u306f\u7d76\u7e01\u30c6\u30fc\u30d7\u3067\u7d76\u7e01\u3057\u305f\u3002\u5dfb\u7dda\u30ac\u30a4\u30c9 \u306f 3D \u30d7\u30ea\u30f3\u30bf\u30fc(N2, Raise3D)\u3067\u88fd\u4f5c\u3057\u305f\u3002 Fig. 10 \u306b\u5dfb\u7dda\u30ac\u30a4\u30c9\u306e\u539a\u307f\u3068\u5404\u30c8\u30e9\u30f3\u30b9\u306e\u6f0f\u308c\u30a4\u30f3 \u30c0\u30af\u30bf\u30f3\u30b9\u306e\u95a2\u4fc2\u3092\u793a\u3059\u3002\u306a\u304a\uff0c#1 \u3068#4 \u306e\u5dfb\u7dda\u30ac\u30a4\u30c9 \u3092\u4f7f\u7528\u3057\u3066\u3044\u306a\u3044\u30e2\u30c7\u30eb\u306f\uff0c\u30ac\u30a4\u30c9\u539a\u307f\u3092 0 mm \u3068\u3057 \u3066\u8868\u8a18\u3057\u3066\u3044\u308b\u3002Mn-Zn \u3092\u7528\u3044\u305f\u30c8\u30e9\u30f3\u30b9\u3067\u306f\uff0c\u30ac\u30a4 \u30c9\u539a\u307f\u304c 1.0 mm \u306e\u6642\u306e\u4e8c\u6b21\u5074\u63db\u7b97\u6f0f\u308c\u30a4\u30f3\u30c0\u30af\u30bf\u30f3 \u30b9\u304c 2.75 \u03bcH \u3067\u3042\u3063\u305f\u306e\u306b\u5bfe\u3057\uff0c\u30ac\u30a4\u30c9\u539a\u307f\u304c 2.5 mm \u306e\u6642\u306f 41 %\u5897\u52a0\u3057\u3066 3.90 \u03bcH \u3068\u306a\u3063\u305f\u3002Ni-Zn \u3092\u7528\u3044 \u305f\u30c8\u30e9\u30f3\u30b9\u3067\u3082\u540c\u69d8\u306e\u50be\u5411\u3092\u793a\u3057\u305f\u3002\u4ee5\u4e0a\u306e\u3053\u3068\u304b\u3089\uff0c \u6f0f\u308c\u78c1\u675f\u304c\u975e\u78c1\u6027\u4f53\u3067\u3042\u308b#1 \u3068#4 \u306e\u5dfb\u7dda\u30ac\u30a4\u30c9\u306b\u96c6 \u4e2d\u3059\u308b\u305f\u3081\uff0c\u6f0f\u308c\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\u306f\u4f7f\u7528\u3059\u308b\u30b3\u30a2\u306e\u900f \u78c1\u7387\u306b\u4f9d\u5b58\u305b\u305a\u306b\u8abf\u6574\u53ef\u80fd\u3067\u3042\u308b\u3053\u3068\u304c\u5b9f\u8a3c\u3055\u308c\u305f\u3002 \uff15 \u4e8c\u53f0\u306e\u96fb\u6e90\u3092\u7528\u3044\u305f\u9ad8\u5468\u6ce2\u30c8\u30e9\u30f3\u30b9\u306e\u8ca0\u8377\u8a66\u9a13\u6cd5 5.1 \u52d5\u4f5c\u539f\u7406 Fig. 11(a)\u306b\u63d0\u6848\u3059\u308b\u8ca0\u8377\u8a66\u9a13\u6cd5\u306e\u63a5\u7d9a\u3092\u793a\u3059[8]\u3002\u8a66 Fig. 7 Structure of proposed transformer. Fig. 8 Vector plot of flux density in transformer. (a) Mn-Zn transformer (b) Ni-Zn transformer Fig. 9 Prototypes of proposed transformer with wire guide. Fig. 10 Relationships between leakage inductance and t#1 and t#4. Toroidal core Wire guide #4 Wire guide #3 Wire guide #2 Wire guide #1 Section S Center line Primary winding Secondary winding Magnetic flux density [mT] 0 2.5 2.0 1.5 1.0 0.5 Wire guide #1 Wire guide #2 Wire guide #3 Wire guide #4 Core 0 1 2 3 4 5 0 1 2 3L ea ka ge i nd uc ta nc e [\u03bc H ] Thickness of wire guide t#1 and t#4 [mm] Mn-Zn Ni-Zn I II III IV V \u9a13\u30c8\u30e9\u30f3\u30b9(\u5dfb\u6570\u6bd4 1:1)\u306e\u4e00\u6b21\u5074\u7aef\u5b50\u306b\u96fb\u6e90 a \u3092\uff0c\u4e00\u6b21 \u3068\u4e8c\u6b21\u306e\u540c\u6975\u6027\u7aef\u5b50\u9593\u306b\u96fb\u6e90 b \u3092\u63a5\u7d9a\u3057\u3066\u3044\u308b\u3002\u3055\u3089 \u306b\uff0c\u96fb\u6e90 b \u3092\u63a5\u7d9a\u3057\u305f\u306e\u3068\u306f\u9006\u6975\u6027\u306e\u4e00\u6b21\u3068\u4e8c\u6b21\u306e\u7aef \u5b50\u9593\u3092\u63a5\u7d9a\u3057\u3066\u3044\u308b\u3002\u672c\u8a66\u9a13\u6cd5\u306b\u304a\u3044\u3066\u306f\uff0c\u4e00\u6b21\u5074\u306b \u5165\u529b\u3055\u308c\u305f\u96fb\u529b\u306f\u4e8c\u6b21\u5074\u304b\u3089\u51fa\u529b\u3055\u308c\uff0c\u305d\u306e\u96fb\u529b\u306f\u518d \u4e8c\u6b21\u9396\u4ea4\u78c1\u675f\u306b\u7740\u76ee\u3057\u4e00\u6b21\u5074\u306b\u6f0f\u308c\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\u3092 \u96c6\u3081\u305f\u7b49\u4fa1\u56de\u8def\u3068\u3057\u3066\u8868\u3057\u3066\u3044\u308b\u3002\u3053\u3053\u3067\uff0cR1\uff0cR2\u306f \u4e00\u6b21\u3068\u4e8c\u6b21\u306e\u5dfb\u7dda\u62b5\u6297\uff0cLl \u306f\u30c8\u30fc\u30bf\u30eb\u306e\u6f0f\u308c\u30a4\u30f3\u30c0\u30af \u30bf\u30f3\u30b9\uff0cLm\uff0cRm\u306f\u52b1\u78c1\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\u3068\u9244\u640d\u62b5\u6297\u3092\u305d \u308c\u305e\u308c\u8868\u3057\uff0c" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000745_ture-tracking-v2.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000745_ture-tracking-v2.pdf-Figure1-1.png", + "caption": "Figure. 1 Coaxial two-wheeled vehicle model\uff0e", + "texts": [], + "surrounding_texts": [ + "simulation was performed to show the effectiveness of the designed controller, and after the validity of the controller was confirmed, an implementation experiment was conducted in an actual system to evaluate and examine the system.\nIn this study, a state space model that considers the road slope angle as a disturbance term similar to term used in a previous study (Chan et al., 2013) as a state variable was used for control design.\n{ \u0307( ) ( ) ( ) ( )\n( ) ( ) ( 1 )\nWhere A=[\n], B=[\n], C=, - [\n]\n[\n] [\n]\n[\n] [\n]\n[ ( ) ]\n( ) ( ) ( )\n( )", + "( )\nIn addition, in case of a model in which the vehicle body that is integrated, the posture angle of the vehicle body that is in an equilibrium state is uniquely determined. In the case of the model in which the vehicle body is divided vertically, it is in an equilibrium state. There are concerns about the occurrence of steady-state deviations because the body posture angle is infinite. Therefore, in this study, as in the previous study, the controller is designed using an expansion system that is servo-extended by adding an integrator to the attitude angle ( ) and wheel rotation angular velocity \u0307. The reference variables for ( ) and \u0307 are referred to as ( ) \u0307 respectively.\nThe dynamic characteristics of the controlled object cannot be expressed completely, and a modelling error is likely to occur. Therefore, there is no strict guarantee that the control system designed for a real system will work well, and in the worst case, the closed-loop system may become unstable. Therefore, it is necessary to design a controller that achieves the desired control performance for all models belonging to the set. Robustness in control is", + "to guarantee the control effect including the stability and response characteristics of the controlled object even when the control elements such as the controller and the plant are perturbed. Robust control refers to the fluctuation of the perturbed plant. In this research, a feedback system controller that satisfies performance is designed by linear matrix inequality (LMI) to realize control performance in compensating robustness against impulsive disturbance with state feedback(Liu & Dong, 2018). Linear matrix inequality (LMI) This study is a multi-purpose control with multiple control specifications to guarantee the stability of the system and to compensate the robustness against the road surface inclination and angle disturbance. At the same time, the paper seeks to present a general-purpose controller that can be added to the controller derivation when a new control requirement appears. Therefore, reduced form LMI that can satisfy multiple control requirements that satisfy performance and guarantee stability against tilt angle disturbance was used. A multipurpose and versatile controller is realized by reducing all the control specifications of this research to LMI conditions as shown below.\n[ * + ( )\n( ) ]\n[\n] ( )\n\uff0e\nIn order to derive a decision variable from LMI conditions and design a state feedback controller, a search algorithm is needed to derive , which is the objective function to be minimized. In this study, binary search was used as a search algorithm. First, the upper and lower limits are set so that the optimal solution for is included in the derivation flow. Then, the binary value is derived for the set upper and lower limits, and the LMI is solved for the binary value. If the LMI for the derived binary value has a solution, the search" + ] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure44-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure44-1.png", + "caption": "Figure 44 : Configuration du r\u00e9seau pr\u00e9sentant des WAIM 3D [41].", + "texts": [ + " Il permet d\u2019augmenter les capacit\u00e9s de d\u00e9pointage du r\u00e9seau infini de dip\u00f4le de 16\u00b0 dans le plan D, et de 10\u00b0 dans le plan H. Le plan E n\u2019\u00e9tant quasiment pas affect\u00e9 par l\u2019ajout de ce WAIM. Comme pr\u00e9c\u00e9demment, il est \u00e0 noter qu\u2019aucune am\u00e9lioration dans le plan E n\u2019est apport\u00e9e. Page 37 sur 182 La plupart des WAIM propos\u00e9s dans la litt\u00e9rature sont planaires, c\u2019est-\u00e0-dire que la surface des WAIM est parall\u00e8le \u00e0 celles des \u00e9l\u00e9ments du r\u00e9seau d\u2019antennes consid\u00e9r\u00e9. Tr\u00e8s peu d\u2019articles proposent des WAIM verticaux, ou 3D, dont la surface est perpendiculaire \u00e0 la surface du r\u00e9seau. [41] (Figure 44) propose par exemple l\u2019utilisation de WAIM 3D. Cependant, ces WAIM ne sont plac\u00e9s verticalement \u00e0 la surface du r\u00e9seau que pour des raisons de praticit\u00e9, en pr\u00e9sence de r\u00e9sonateurs ELC (\u00ab Electrique Inductif Capacitif). Aucune autre raison n\u2019est avanc\u00e9e pour l\u2019utilisation de WAIM verticaux. Comme dans les autres articles, les WAIM utilis\u00e9s ne permettent d\u2019am\u00e9liorer les capacit\u00e9s de d\u00e9pointage du r\u00e9seau d\u2019antennes seulement dans un seul plan, le plan E cette fois-ci, les effets \u00e9tant n\u00e9gligeables dans le plan H" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000640__1_download_id_75903-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000640__1_download_id_75903-Figure3-1.png", + "caption": "Figure 3: Applications and Objectives for NB-IOT: (a) Applications for NB-IoT and (b) Objectives for NB-IOT.", + "texts": [ + " NB-IoT typically allows uplink transmission at data rates of 160-200 kHz and down-link transmission at data rates of 160-250 kHz. It can serve regions of 1-8 km in urban environments and 25 km in suburban areas. When compared to the other three LPWA technologies, NB-IoT offers a lower cost of production, a longer working life, and wider coverage, as shown in Table 1. For next-generation use cases and applications, the NB-IoT provides LPWA coverage via massive devices [18]. NB-IoT is expected to be one of the technologies of 5G new radio (NR) networks, according to [19]. Figure 3(a) shows the applications of NB-IoT such as smart buildings [20], smart cities [21], intelligent or smart environmental monitoring systems [22], smart metering [23], and intelligent user services [24]. Also, Smart houses, smart wearable gadgets, smart people tracking, and other intelligent and smart user services. Pollution monitoring, intelligent agriculture, water quality monitoring, soil detection, and other aspects of the intelligent or smart environment monitoring system are described in [25, 26]. The main goals of NB-IoT are outlined in 3GPP specifications [3] and depicted in Figure 3(b). Abdulwahid Mohammed et al. TABLE 1. Comparisons between LoRa, SigFox, eMTC, and NB-IOT technologies [9]. Technologies Parameters LoRa SigFox eMTC NB-IoT Spectrum Unlicensed Unlicensed Licensed Licensed Modulation UL: DBPSK DL: GFSK UL: SC-FDMA DL: OFDMA UL: SC-FDMA DL: OFDMA Bandwidth 7.8 \u2013 500 kHz 200 kHz 1.08 MHz 180 kHz Range Urban : 2\u20135 km Suburban : ~ 15 km Urban : 3\u201310 km Suburban : 30\u201350 km Urban : ~ 5 km Suburban : ~ 17 km Urban : 1 \u2013 8 km Suburban : ~ 25 km Data rate < 50 bps < 100 bps (EU) < 600 bps (USA) < 1 Mbps 160 \u2013 250 kbps (DL) 160 \u2013 200 kbps (UL) Battery life > 10 years 8 \u2013 10 years 5 \u2013 10 years > 10 years Price < 5 $ < 10 $ < 10 $ < 5 $ Note :- UL: uplink , DL: downlink and CSS: chirp spread spectrum \u2022 Deep Coverage: The NB-IoT technology is designed to have both indoor and outdoor deep coverage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure8.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure8.4-1.png", + "caption": "Figure 8.4: Decomposed Oil Particles on Bearing Surfaces", + "texts": [ + " It is absolutely necessary that the rubbing surfaces of such a lubricant-free compressor be clean and free from any contaminants such as oil or dirt. Oil was used to prevent rusting of the prototype. For the lubricant-free RV prototype, the accidental presence of residual lubricant can cause the compressor to seize up as well. Residual oil was present during the initial test run of the compressor causing seizure at the journal bearings \u2013 due to the high friction heat at the rubbing surface with no lubricant network to circulate the oil, the trapped oil decomposed into hard carbon particles which then caused the compressor to seize up. Figure 8.4 shows the decomposed carbon particles on the rotor shaft, rotor shaft journal bearing surface, lower cylinder shaft, lower cylinder shaft and cylinder bearing sleeves of the RV prototype \u2013 the discolouration on the surfaces are the remnants of the burnt/decomposed oil residue. 159 After cleaning up and ensuring that the bearing surfaces were free from contaminants, the compressor was tested again in order to evaluate its performance. However, it was still 160 prone to seizure which can be attributed to the buildup of friction heat at the lower cylinder bearing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000558_al-01025785_document-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000558_al-01025785_document-Figure10-1.png", + "caption": "Figure 10: Second test scenario (arrows depict contact forces)", + "texts": [], + "surrounding_texts": [ + "In the figure 9 one can see the gap function and relative velocity plots. With respect to the previous sub-case rebounds off the ground are visible.\nInria", + "locity of one steering axis\nIn the second test setting rover is dropped onto a horizontal plane and stands idle on it during the first 50 seconds of the simulation. After 50 seconds from the beginning of the simulation a constant torque \u03c4 = 0.00002Nm is applied in one of the steering axes (steering axis FL) causing its rotational motion with linear velocity. Wheel makes two full rotations around its vertical steering axis (FL). Other external forces acting on the rover are the gravity and ground reaction. Initial position of the center of mass of the robot has been set to (x, y, z) = (5, 5, 2) [m]. Friction coefficient has been set to 0.4. Restitution coefficients (tangential and normal) have been set to zero.\nRT n\u00b0 448", + "In this case, following essential quantities have been plotted:\nIn the figure 11 one can see the variation of the steering axis displacement and velocity. After a constant torque is applied the axis is rotating with a linear velocity which corresponds to the quadratic shape of the displacement curve.\nInria" + ] + }, + { + "image_filename": "designv8_17_0001866_f_version_1571048987-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001866_f_version_1571048987-Figure5-1.png", + "caption": "Figure 5. Overall design setup of the open source waste plastic granulator with primary parts labeled with green arrows. Red arrows indicate the path of material flow.", + "texts": [ + " A circuit diagram for the electrical system is included in Figure 4a. Technologies 2019, 7, 74 7 of 21 Together, the four systems described in Sections 2.1\u20132.4 work together to achieve the overall objective of the design of the open source waste plastic granulator. Other than getting the material from place to place, all of the actual manipulation of the plastic to transform it from stock material into feedstock occurs due to the cutting and power transmission systems. An overall view of the machine\u2019s core systems is shown in Figure 5. Technologies 2019, 7, x FOR PEER REVIEW 7 of 21 Figure 4. (a) Circuit diagram for electrical control system of the open source waste plastic granulator and (b) circuit diagrams. i , t fo r syste s describe in Section . .4 t r j . l ce to place, all of the actual manipulation of the plas ic to transform it from stock m terial into feedsto k occ rs du to the cutting and power transmission systems. An overall view of the machine\u2019s core ystems is shown in Figure 5. Figure 5 shows the assembly of the three mechanical design systems, including all of the parts explained earlier as well some 3D printed parts and several parts not shown before. The total system dimensions are width of 0.72m, depth of 0.55m and height of 1.47m. The system has a mass of 125 kg. As can be seen in the above picture the server rack cart that was mentioned in the material guidance system is housing the main systems of the granulator. It holds the machine components so that the major axis of the large square tube is angled to allow plastic pieces to slide into the cutting mechanism. To accomplish this, several standard size \u00bd\u201d (12.7 mm)) steel pipes are attached to the server rack using u-bolts. The pipe in the rear (as shown in Figure 5) is attached directly to the bottom of the steel tube using pipe straps, while the pipe in the front is attached via nylon strapping to the eye-bolts shown on the top of the steel tube in the above figure. This is done to allow the builder of the machine to easily add a vibration-dampening spring at the front attachment point to mitigate any rotational imbalance that may be present in the machine. The hopper consists of the large tube sticking out of the top of the server rack as well as a plate that allows it to attach to the back of the square steel tube/main machine body", + " This allows users to safely place materials into the machine for cutting. The bend that materials will have to pass through in order to get from the machine\u2019s opening to the cutting mechanism ensures that a user cannot accidentally place their hands/arms inside the machine while it is cutting as well as stops granules from flying out of the machine during operation. To highlight the interaction between all three main mechanical systems a cutaway view showing the assembled granulation chamber in Figure 6. ll i t . i l fl . Figure 5 sho s the asse bly of the three echanical design syste s, including all of the parts explained earlier as ell so e 3 printed parts and several parts not sho n before. The total syste di ensions are idth of 0.72 , depth of 0.55 and height of 1.47 . The syste has a ass of 125 kg. s can be seen in the above picture the server rack cart that as entioned in the aterial guidance syste is housing the ain syste s of the granulator. It holds the achine co ponents so that the ajor axis of the large square tube is angled to allow plastic pieces to slide into the cutting mechanism. To accomplish this, several standard size 1 2 \u201d (12.7 mm)) steel pipes are attached to the server rack using u-bolts. The pipe in the rear (as shown in Figure 5) is attached directly to the bottom of the steel tube using pipe straps, while the pipe in the front is attached via nylon strapping to the eye-bolts shown on the top of the steel tube in the above figure. This is done to allow the builder of the machine to easily add a vibration-dampening spring at the front attachment point to mitigate any rotational imbalance that may be present in the machine. The hopper consists of the large tube sticking out of the top of the server rack as well as a plate that allows it to attach to the back of the square steel tube/main machine body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure1-1.png", + "caption": "Figure 1. Two-dimensional design of the prototype car frame", + "texts": [ + " In this article, the strength of seven types of support bars will be analyzed: the engine support bar, the control panel bar with the battery, two driver seat support bars, the leg support bar, the front body support bar, the roll bar body support bar, the rear body support bar, and the main bar. The profile size for the rear body support bar is 50x30x1.6 mm, while the other bars are 75x20x1.6 mm. The dimensions of the prototype vehicle frame align with the dimensions of the vehicle body design and the regulations. The overall dimensions of the prototype vehicle frame are 2500 mm in length, 410 mm in width, and 540 mm in height. The 2D and 3D design of the bar frame model is created using Autodesk Inventor. Figure 1 illustrates the dimensional sizes as a 2D sketch of the prototype vehicle frame. The chosen frame type is the ladder frame, which can accommodate various loads. mounting rod (1); control panel and battery (2); driver body (3); driver's legs (4); front body (5); rollbar body (6) rear body (7); main stem (8). The 3D model is created using Autodesk Inventor with the frame generator feature. The 3D modeling is utilized to provide a detailed overview of the designed structure of the frame. The frame structure is supported by two main bars and reinforced by several supporting bars" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001086_1934_context_journal-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001086_1934_context_journal-Figure3-1.png", + "caption": "Fig. 3. The schematic of running mechanism working in low speed.", + "texts": [ + " To change direction, the pressure oil, produced by the hydraulic system through application valve, drives steering cylinder piston rod to move telescopically [5]. They are located on both the front and rear frame. So, as shown in Fig. 1, either of the frames turns a certain angle, to achieve turning function. Running mechanism makes circular movement around the center of intersection point of front wheel\u2019s vertical line and rear wheel\u2019s. The distance between the intersectional point and the centerline of the frame is the steering radius as the geometric relationship shown in Fig. 3. 0 costan a b R \u03b8\u03b8 + = 0 cos tan a b R \u03b8 \u03b8 + = (1) When a vehicle is negotiating a turn, to balance the centrifugal force, the tires must develop an appropriate side force [11]. A side force acting on a tire produces a side slip angle. Particularly when the speed is higher, the angle is larger. Figure 4 shows that after the front wheels turn a certain angle, the side slip angle also need to be taken into account when analyzing the front wheel speed and the steering radius. According to the geometric relationships of triangle OAC and OBC as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004334_f_version_1614604730-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004334_f_version_1614604730-Figure1-1.png", + "caption": "Figure 1. The fire\u2019s point of origin and way through the power units.", + "texts": [ + " If we take into account the fact that in the vicinity of fluidized bed power units, there are large amounts of coal dust (among others on communication elements such as platforms, barriers), this will largely help to spread the fire wave within the boiler installations. Within a power unit\u2019s boiler island, a passing fire wave affected the unit\u2019s second pass (convection chamber), the cyclone, ash removal system, air-supply system, etc. The point of origin and the path of the fire wave are shown in Figure 1 [3]. References should be numbered in order of appearance and indicated by a numeral or numerals in square brackets, e.g., see the end of the document for further details on references [4,5]. The fire was initiated in the conveyor belt gallery situated in the coal and biomass supply line of power unit A. The fire wave later traveled through communication lines located between the power units and approached further generating units. The propagation of the fire wave necessitated evaluation of the degradation and damage caused to particular elements of the power units" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001775_f_version_1703313692-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001775_f_version_1703313692-Figure1-1.png", + "caption": "Figure 1. (a) Shear wave tensiometry was performed using a standard two-sensor device. The device was placed over the Achilles tendon. The transducer excited transverse waves and the propagation was measured with two accelerometers embedded in a silicone array. (b) Example of the first accelerometer measurements across a 10 s collection, with excitation wavelets introduced at 100 Hz. A single event consists of a modulated harmonic wavelet excitation and measured response.", + "texts": [ + " In this study, we present a novel approach to shear wave tensiometry that involves the utilization of shaped excitation pulses and a single-sensor technique for real-time tracking of in vivo tendon phase velocity. Our findings indicate that the application of shaped waveforms induces phase velocities with frequency dependence, in concordance with the inherent dispersion characteristics of the system. These outcomes have the potential to simplify and extend the application of shear wave tensiometry. Shear waves were excited in the Achilles tendon using a miniature surface transducer (Figure 1a). A shaped, discrete wavelet was chosen as the excitation signal such that the dominant harmonic component and amplitude modulation could be easily dissociated using a Hilbert transform. This input excitation \u03c8 was defined by the following piecewise representation: \u03c8 = { A\u00b7sin(2\u03c0 fAt)\u00b7sin(2\u03c0 fHt + \u03c6) f or 0 \u2264 t \u2264 t0 0 otherwise (1) where A was the peak of the amplitude modulation and fH was the dominant wavelet frequency. The amplitude modulation was defined as a half-sine with the frequency (Equation (2)) and duration (Equation (3)) defined to produce a wavelet with seven lobes (Figure 1b). fA = fH/7 (2) t0 = 3.5/ fH (3) Miniature skin-mounted accelerometers (PCB Piezotronics, Depew, NY, USA) were used to measure the transverse motion of the tendon at 20 mm and 28 mm from the transducer contact (Figure 1a). Wave speed was computed in two ways. The single-sensor method was applied only to the signal measured by the first accelerometer, and the timing of the wave arrival was quantified via both the group delay and relative phase shift. A two-step approach was implemented which distinguished the group and phase delays because in dispersive materials, these are known to be different [18]. To do this, the envelope of the measured acceleration was computed via a Hilbert transform [19] (Figure 2a). We then found the group delay T that maximized the normalized cross-correlation between the envelopes of the input excitation and the measured response (Figure 2b)", + " The a priori estimates of the system states were computed from the change in group and phase delay of consecutive events [20]. Phase velocity for the shear wave was computed from the known distance from the transducer to Micromachines 2024, 15, 32 3 of 9 the accelerometer (D = 20 mm) and the arrival times (Equation (4)). The transducer latency (\u03c4t) and the array latency (\u03c4a) were subtracted from the overall phase delay (Figure 3). vp = D/ ( T + \u03d5\u2032/2\u03c0 fH \u2212 \u03c4t \u2212 \u03c4a ) (4)Micromachines 2024, 15, x FOR PEER REVIEW 3 of 10 Figure 1. (a) Shear wave tensiometry was performed using a standard two-sensor device. The device was placed over the Achilles tendon. The transducer excited transverse waves and the propagation was measured with two accelerometers embedded in a silicone array. (b) Example of the first accelerometer measurements across a 10 s collection, with excitation wavelets introduced at 100 Hz. A single event consists of a modulated harmonic wavelet excitation and measured response. 2.2. Wave Speed Computation Wave speed was computed in two ways" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004397_jeee.2013.010305.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004397_jeee.2013.010305.pdf-Figure3-1.png", + "caption": "Figure 3. Simulated electric field on horizontal and vertical cut planes", + "texts": [ + " The slab mode launcher generates a cylindrical slab wave in the forward half space, which would result in a very wide beam width. A simple planar dielectric lens on top of the substrate is capable of focusing the beam effectively. Field simulations illustrate how the TM0 surface wave on the grounded slab is collimated by the planar lens. The guided wave is then gradually transformed into an ungrounded slab mode by the curved ground plane and is finally radiated from the substrate edge in end-fire direction. (Figure 3) The underlying focusing effect of the planar lens is discussed in the following subsection, along with a quantitative analysis of the propagation constant in the dielectric slab. The necessary curved ground body can be fabricated at low cost by plastic injection molding and subsequent electroplating. It may be part of the housing of a later wireless consumer product. Since the wave is loosely guided in the ungrounded part of the slab and the effective permittivity is low, reflections or scatterings from the substrate edge are negligible" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001782_f_version_1663924178-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001782_f_version_1663924178-Figure5-1.png", + "caption": "Figure 5. The schematic of the relationship between TL, TD, and F.", + "texts": [ + " Due to the presence of the planetary gearbox, even with some efficiency loss in the planetary gearbox, the driving torque generated from the electromagnetic driver is much smaller than the required lifting torque. Therefore, the driving torque TD is obtained in terms of Equation (3) [41\u201343]: TD = TL \u00b7 ( 1 e1i1 \u00b7 1 e2i2 \u00b7 \u00b7 \u00b7 1 enin ) , (3) where e is efficiency, i is reduction ratio, and n is the number of stages. The driving torque TD is rewritten as Equation (4) since the reduction ratio and efficiency of the planetary gearbox in each stage are equal. The relationship between lifting torque, driving torque and distraction force are illustrated in Figure 5 for better understanding. TD = TL \u00b7 1 (ei)n . (4) Although reduction ratio and the number of stages are effective ways of improving the distraction force, the total weight of the implantable lengthening nail became heavier. Hence, raising the driving torque of the electromagnetic driver is an alternative method. 3.2.2. Driving Torque for Actuation by Electromagnetic Driver The electromagnetic driver and internal permanent magnet combination are equivalent to PMBLDC motors since their rotors rotate synchronously when the stator provides a rotating magnetic field" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000496_f_version_1633693962-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000496_f_version_1633693962-Figure6-1.png", + "caption": "Figure 6. (a) Schematic of the ultra-broadband switchable absorber. (b) The unit cell of the metasurface composed of multiple layers. The dimensions are t1 = 13 \u00b5m, t2 = 25 \u00b5m, t3 = 39 \u00b5m, d1 = d3 = 0.3 \u00b5m, d2 = 1.1 \u00b5m, d4 = 0.5 \u00b5m, p1 = 90 \u00b5m, p2 = 45 \u00b5m, R1 = 42 \u00b5m, R2 = 34 \u00b5m, R3 = 25 \u00b5m, R4 = 19 \u00b5m, w1 = 2 \u00b5m, r1 = 15 \u00b5m, r2 = 11 \u00b5m, r3 = 8 \u00b5m, and w2 = 1 \u00b5m.", + "texts": [ + " The change in the real part of the refractive index mainly contributes to the frequency shift of the absorption peaks, while the variation of the imaginary part can result in a decay in absorptivity. In most cases both the real and imaginary parts are changed under external excitations, thus resulting in a decay of absorptivity. Via carefully designing the geometrical dimensions of multiple metal/VO2 rings and the thickness of the dielectric layer, an ultra-broadband switchable absorber without a reduction in absorptivity can be achieved. A schematic of the proposed design is shown in Figure 6. It is worth noting that, compared with the design in Figure 1, several modifications were made in order to achieve ultra-broadband absorption with high absorptivity, for both the upper and lower MPAs. First, we replaced the metal Au with high-loss Cr, for the relatively smaller Q factor of resonance. Second, the continuous VO2 film was placed below the Cr rings array, in order to further increase the loss and import a freely controllable parameter to optimize the broadband absorption property. Moreover, an extra layer of SiO2 was designed on top of the structure, which serves as an antireflection layer and helps to optimize the surface impedance" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure6-1.png", + "caption": "Figure 6. Permanent-magnet skew diagram for cogging torque reduction and elimination of undesired harmonic components.", + "texts": [ + " An advantage of 3D-FEA is that various components of flux density can be calculated highly accurately [32\u201335]. The design was simulated on commercial Vector Field Opera 14.0 3D software [36]. Usually, permanent-magnet skewing is beneficial for reducing the cogging torque in electric machinery. It also eliminates some undesired harmonics, reducing the back-EMF total harmonic distortion (THD). It should be noted that the back-EMF amplitude is also reduced slightly with skewing. Skewing angle should be less or equal to slot pitch. Fig. 6 portrays a diagram of the permanent magnet\u2019s geometric skewing with regards to stator teeth and slots. Skew angle (\u03c4p) is the angle at which the rotor\u2019s permanent magnets are skewed relative to the stator teeth. Through GA analysis, motor dimensions are obtained for each stator slot count. The FEA then provides the THD of back-EMF at various skew angles for the design candidates presented in Table 3. Fig. 7 shows THD variation against permanent-magnet skew angles. Minimum THD is clear to see for the motor with 15 stator slots and 9- degree permanent-magnet skew" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001984_el-00811520_document-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001984_el-00811520_document-Figure11-1.png", + "caption": "Figure 11: Overall view of the Huygens Probe attached to the parachute bridle (left, Lebreton and Matson, 2002); Accommodation of the HASI instrument on the Huygens Probe platform, top and side views (right, Fulchignoni et al., 2002).", + "texts": [ + " 20 Figure 5 - Sketch of the model used for calculating the Schumann resonance \u2026\u2026\u2026. 24 Figure 6 - Conductivity and permittivity profiles of the atmosphere of Venus \u2026\u2026\u2026. 28 Figure 7 - Electric field amplitude as a function of altitude in a lossless cavity \u2026\u2026... 31 Figure 8 - The Cassini Orbiter and the Huygens Probe \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026. 33 Figure 9 - Sketch of the descent sequence of the Huygens Probe upon Titan \u2026\u2026\u2026... 35 Figure 10 - Sketch of PWA sensors and Huygens Probe in deployed configuration \u2026 36 Figure 11 - General view of the Huygens Probe and parachute bridles \u2026\u2026\u2026\u2026\u2026\u2026 40 Figure 12 - The synopsis of PWA data \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026.. 42 Figure 13 - Relaxation carpets of the RP2 electrode \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026. 43 Figure 14 - Relaxation curves of RP2 due to negative charge carriers \u2026\u2026\u2026\u2026\u2026\u2026.. 43 Figure 15 - Atmospheric backscatter distance and Probe altitude measured by PWA .. 45 Figure 16 - Spectral representation of the surface roughness at particular altitude \u2026... 45 Figure 17 - Electric signal measured with the PWA receivers in the ELF range \u2026\u2026", + " The Huygens data are transmitted through two telemetry channels (A and B); the PWA spectra are split into odd and even lines, but only the even spectral lines are available because of the failure of the channel A receiver onboard Cassini. All spectra and RP data are split between the two telemetry channels. Only the MIP amplitude and phase are telemetered on both channels and are not affected by the loss of channel A. Operation Mode Sampling rate [kHz] Spectral range [Hz] Resolution [Hz] 40 The dipole antenna consists of two electrodes distant of 2.1 m, but the presence of the Huygens vessel reduces the effective length to 1.6 m; the dipole is aligned with the Yp axis of the Probe (Figure 11). 4.2.5. Acoustic Sensor The PWA analyzer includes a light and robust acoustic sensor mounted on a stub attached to the Huygens ring and exposed to the environment. The sensor detects the noise generated by the vessel and the parachutes, and the sounds of atmospheric events and turbulences. The acoustic transducer is a Kulite CT-190M low temperature pressure sensor and is specially suited for dynamic pressure measurements under extreme conditions. The transducer accuracy is about 5% and the pressure sensitivity is ~10 mPa, which is sufficient for detecting thunderclaps and strong winds", + " A 3D finite element model is therefore developed, and implemented with the Comsol Multyphysics software and a specific Matlab post-processing algorithm, to solve Poisson equation, r \u00f0 r\u00f0r\u00derF\u00f0r\u00de\u00de \u00bc r\u00f0r\u00de= 0, (14) where F is the potential, r the relative permittivity, r the charge volume density and r the space variable. Dirichlet boundary conditions are imposed on the body of the Huygens Probe and on the quadrupolar array, as well as continuity conditions at the planar interface between the two media, atmosphere and ground (Fig. 11). Eq. (14) is first solved under the assumption that sg \u00bc 0, in order to probe the influence of the body upon the determination of the ground dielectric constant. In fact, the algorithm computes, for a given charge distribution on the two transmitting electrodes and for a specific rest position of the Huygens Probe upon the surface, the ground dielectric constant that reduces the received voltage after landing to 70% of its level in vacuum. The system rest attitude is not known with accuracy. The symmetry axis of the vehicle body makes an angle probably less than 101 with the normal to the surface and the body does not penetrate the soil by more than 15 cm, as it can be inferred from the measurements performed with several other instruments: Descent Imager-Spectral Radiometer\u2014 DISR (Tomasko et al., 2005), Surface Science Package\u2014 SSP (Zarnecki et al., 2005) and Huygens Atmospheric Structure Instrument\u2014HASI (Fulchignoni et al., 2005). It is nevertheless important to test how sensitive is the determination of the dielectric constant to small penetration depths and tilt angles. The simulation outputs are summarized in Table 5 for several combinations of these two attitude parameters. We only consider tilts in the plane ARTICLE IN PRESS Fig. 11. Finite element mesh model representing the Huygens Probe and the quadrupolar array partially buried into the soil (left), and definitions of the penetration depth hp and the tilt angle at, in the plane defined by the symmetry axis of the system, and the booms which carry the sensors (right). Table 5 Ground dielectric constant derived from the finite element model, for various tilt angles and penetration depths Tilt (deg) Depth (cm) 0 5 10 0 2.53 2.62 3.13 5 1.95 2.41 3.19 10 1.91 2.15 \u2013 R. Grard et al", + " The far field numerical results are very similar to those obtained for a vertical Hertzian dipole at an altitude of 50 km, approximated by two spheres, 15 km in radius and distance of 35 km. Fig. 7 shows the frequency spectrum in the ELF range of the electric field generated by a source of arbitrary amplitude, for two conductivity profiles (CP1 and CP3), a PEC boundary on the surface and at a depth of 100 km, and an angular separation, that is the angle between the source centre and the receiver seen from Titan\u2019s centre, of 451. The receiver rests on the surface. The stimulus signal is stationary and its spectrum is flat in the frequency band of interest. ARTICLE IN PRESS Fig. 11. Electric signal measured with the PWA receivers in the ELF range before (upper two panels: 1 and 2), and after (lower two panels: 3 and 4), the operation mode change. Panels 1 and 3: Dynamic spectra with frequency resolutions 3 and 6Hz, respectively. Spectral levels are given by the color scales shown on the right-hand side. White stripes correspond to the data loss in channel A. Panels 2 and 4: Electric field of the spectral line around 36Hz against time. The peaks at 900 and 8870 s are due to the deployment of the third parachute and touchdown, respectively", + " Each spectrum is processed, split into odd and even lines, and sent on two telemetry channels (A and B). However, due to the loss of channel A, only even lines are available. PWA recorded 582 high- and 2588 low-resolution spectra. The spectral bands covered before and after the operation mode change are partly overlapping and partly complementary. However, due to the data loss, about one quarter of the ELF range is not covered at all during the whole descent. This domain consists of 3Hz stripes centred on the frequencies f ab \u00bc 3\u00f04nab 3\u00de, (11) where nab \u00bc 1, 2,y, 8. Fig. 11 shows the dynamic spectra of the ELF electric field and the strength of the lines at around 36Hz. The signal is enhanced in the interval 950\u20131800 s and displays other features, such as spikes at 900 and 8870 s, which correspond to the deployment of the stabilizer parachute and to the touchdown. There is also an increase of the signal over the whole frequency range at 5000 s (corresponding to an altitude of 21 km), which seems to coincide with the time at which the Huygens camera detects a thin haze layer (Tomasko et al", + " The simulation results provides an overview of the ELF wave distribution in the resonant cavity; the eigenfrequencies and Q-factors obtained with CP1 lie in the same range as those presented by Yang et al. (2006) with the FDTD approach. A significant aerosol concentration at high altitude increases the Q-factor (Eq. (4), Table 2), which can be higher than on Earth. The ELF electric field measurements performed during the descent of the Huygens Probe through the atmosphere of Titan reveals the existence of a narrow-band emission at around 36Hz (Fig. 11). The maximum and average amplitudes recorded during the descent are 17.5 and 2mVm 1Hz 1/2, respectively; the mean frequency increases steadily during the descent, from 35Hz at 140 km to 37Hz before touchdown (Fig. 13). The transition at an altitude of about 21 km (Fig. 11) seems to match the occurrence of a thin haze layer imaged by the camera onboard the Probe. If one discards the frequency points measured at altitudes less than 21 km, then the mean variation observed in Fig. 13 is close to 1Hz. For most cavity models, a spectral peak at 36Hz can match the second eigenfrequency (Fig. 3). Furthermore, the lowest eigenmode is either matching an absent line or the corresponding amplitude is small. The latter phenomenon can be understood if the angular separation between the source and the receiver is close to 901; the amplitude of the first eigenmode is negligible and only the second one is measurable (Fig", + " The horizontal component is roughly one order of magnitude smaller than the vertical one; it shows a trough that matches the conductivity peak, in accordance with Ampere law, and a peak close to 170 km. The PWA dipole is approximately horizontal and the variation of the \u2018\u201836Hz\u2019\u2019 level with altitude (see Figs. 11 and 12) should be compared, in first approximation, with that of the model horizontal component (Fig. 10). The measurements indicate that the peak electric field is seen at 90\u2013100km with a mean level of 7mVm 1 (Fig. 11). On Earth, the vertical component of the electric field related to the Schumann resonance is only 0.1mVm 1. We conjecture that the amplitude of the measured signal is strongly affected by atmospheric turbulence and the variation of the angle made by the antenna and the field orientation. Therefore, the data will be revisited when accurate Huygens Probe attitude and atmospheric parameters are available. Methane clouds have been observed at high latitudes (Brown et al., 2002; Griffith et al., 2005) but no related lightning activity has been reported", + " We tentatively assume a uniform vertical velocity field around the electrodes. The current injected between the Tx electrodes is nearly constant, and we neglect any small variation due to velocity. We consider only the coupling between the two electrodes Tx and Rx which are located on the same boom, and apply (19) to take into account the effect of velocity upon the contribution of Tx to the potential of Rx (the minor contribution of the opposite boom cannot be really estimated due to the presence of the Huygens body). We compute the relative ARTICLE IN PRESS Fig. 11. Measured normalized mutual impedances and theoretical values vs velocity and conductivity (same symbols as in Fig. 9). M. Hamelin et al. / Planetary and Space Science 55 (2007) 1964\u201319771974 variation of the Rx potential with respect to the steady case for arbitrary conductivity and velocity, and apply this corrective factor to the theoretical value of the complex mutual impedance (Eq. (7)). The components of the Tx\u2013Rx segment along, and perpendicularly to the velocity direction are 0.22 and 0.156m, respectively. The results are given in Fig. 11 which shows the curves of constant s/e0 and constant velocity. The velocity does not affect the theoretical prediction in a vacuum, but in a lossy medium an increase in velocity reduces the phase of the voltage induced by Tx at the location of Rx and moves the mutual impedance towards the real axis, closer to the experimental points of group A. The measurements that form the group A have been collected below an altitude of 100 km, through the ionized layer. They are consistent with a descent velocity of 50 (720)ms 1, in reasonable agreement with the measured velocity, of the order of 40ms 1", + " This discrepancy can be explained in a simple way by considering in our model that the velocity is uniform is an approximation. Close to the Huygens body the flow is deflected and accelerated by up to 20% with respect to the nominal descent velocity. We shall not attempt, at this stage, to improve further this first order model, and we tentatively conclude that the relative velocity effect is reasonably confirmed for the group A measurements. The conductivity is obtained with the abacus drawn in Fig. 11, and is read on the constant conductivity line passing through each experimental point. The two points in group B, close to the origin but outside the unity circle, do not yield any meaningful value for the permittivity. These measurements are made at t \u00bc 1050 and 1242 s, whereas those made 2 s before, at t \u00bc 1048 and 1240 s, respectively, lie inside the unit circle. This period follows the second parachute opening, and the attitude of Huygens may not be stabilized yet. One might also argue that, within 2 s, the system travels over a vertical distance of 100m and that the medium might change noticeably", + " The experimental points are dispersed mostly along the real axis, which could be caused by the rotation of the unlocked boom (25\u201330% of the nominal rotation angle). Under this assumption, a conductivity less than 0.2 nSm 1 can be estimated from the measurements. It is impossible to validate any of these two hypotheses, but both lead to conductivity less than 2 10 10 Sm 1 in the altitude range 100\u2013140 km. 4. Results and discussion 4.1. Conductivity and electron density profiles The conductivity profile deduced from the chart of Fig. 11 is shown in Fig. 13 at altitudes less than 100 km, where the mutual impedance phase and amplitude are compatible with the velocity effect. The relative error on the conductivity depends strongly on its level, and varies from 50% at 10 10 Sm 1 to 20% at its peak, 3 10 9 Sm 1. The uncertainty is mostly due to the insufficiently accurate modelling of the velocity effect. The measurements taken at very small time interval (2 s) are generally very similar, and their relative difference is small, of the order of 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure15-1.png", + "caption": "Figure 15 P-POD Mk. III Rev. E Nitrogen Purge Back Plate.", + "texts": [ + " Inert Gas Purge System The need for a nitrogen purge system for the P-POD came about when a specific CubeSat utilized a sensitive instrument as its primary payload. The instrument could not last for an appreciable duration exposed to oxygen. In order to accomplish this, the PPOD back plate was seen as the logical location for a nitrogen purge interface. The back plate was modified to accommodate an auxiliary access port to the \u2013Z face of the P-POD. Page 22 A one off Mk. III Rev. E Back Plate was manufactured for this specific case and is shown below in Figure 15. The primary design change being the addion of the central hole and cover mounting holes. Mounting holes were over designed, utilizing size 8 screws to fit the access port cover to the back plate. This strength was unnecessary, but a robust and easily workable interface was desired. Helicoils were also used to ensure there would be no damage due to repeated installation and removal. In order to prove that this method would work, a test with a modified P-POD was necessary in order to show that it was capable of holding positive gauge pressure with a realistic gas flow rate" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure9-1.png", + "caption": "Figure 9 Example of Torx-Drive Button Cap Screw", + "texts": [ + " However, late in the design process, the captive screw manufacturer strongly recommended using at least a whole diameter of the press-fit sleeve-in material surrounding the sleeve, to prevent the access port cover material from yielding when the sleeve is pressed into the tab. There is simply not enough space on the side panel for such large mounting tabs to be practically implemented. This necessitated the exploration of one final design option, in which the access port design itself was maintained, but the 4-40 Captive Screws were replaced by Torx-head 4-40 button cap screws. Gasket Interface with Button Cap Screws The Torx-drive screw used and access port cover design are shown below in Figure 9 and Figure 10. Page 11 The button cap screws have a lower profile than socket cap screws. Because of the head shape, button cap screws must utilize a smaller drive head then socket cap screws. The hex drive button cap screws are not capable of meeting the torque that is typically used on other size #4 screws on the P-POD, which drove the requirement to use the Torx-drive button cap screws, as the star shape allows for significantly higher installation torque values. This was tested on a scrap piece of aluminum and proved able to achieve 10 in-lb of installation torque, in line with the torque applied to the rest of the 4-40 screws on the P-POD" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002657_article_25867004.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002657_article_25867004.pdf-Figure1-1.png", + "caption": "Fig. 1 Finite-element model of ROPS with DLV (deflection-limiting volume) combination.", + "texts": [ + " The initial direction of loading shall be horizontal and perpendicular to a vertical plane through the machine's longitudinal centerline. The whole load acts upon ROPS, i.e. we neglect the influence of tractor frame, windscreen glasses, coupling bars and other elements. The protective frame is presented in the form of core design using rectangular pipes as structural elements. This allows one to analyze ROPS behavior under the action of functional load (lateral force) using the finite element method. 1. Creation a finite-element model with the applied lateral force F (Fig. 1). Copyright \u00a9 2016, the Authors. Published by Atlantis Press. This is an open access article under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/). 439 2. Solution of the elastic problem in the first approximation, i.e. the estimation of ROPS deflected mode is performed by the finite element method excluding plastic deformations. Therefore we calculate the stress intensity of the first approximation \u2013 I i\u03c3 . 3. Determination of variable elasticity parameters according to the method, widely used in theory of plasticity [6]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003781_f_version_1680255727-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003781_f_version_1680255727-Figure1-1.png", + "caption": "Figure 1. Sketch of seedling picking mechanism: 1. Planetary gear; 2. Intermediate gear; 3. Sun gear; 4. Seedling tray; 5. Seedling tray delivery mechanism; 6. Cam; 7. Linkage mechanism; and 8. Roller.", + "texts": [ + " In addition, the rod EG was fixed to the rod EH at a certain angle, a roller was hinged at the H point, and a torsion spring was added to ensure that the roller was always in contact with the cam. The cam and the housing were fixed on the input shaft, and the rotation of the input shaft drove the rotation of the cam and the housing, wherein the cam pushed the connecting rod EH to swing during the rotation and subsequently pushed the sun gear to swing through the connecting rod mechanism. The seedling picking arm was fixed to the output shaft, and the seedling clamping and pushing action was performed by the internal cam rocker mechanism. In Figure 1, point B is the output shaft axis, C\u2013D is the seedling picking arm, and point O is the input shaft axis. E, F, G, H are the end points of connecting rod FG and connecting rod EH respectively. Where point H is also the axis of the roller. Figures 3 and 4 show the sketch of the structure of the seedling picking arm and the 3D model, respectively. The fork is hinged on the arm housing through its center of rotation, one end of the fork is in contact with the fork cam, and the other end is connected to the seedling pushing rod, which is fixed in the cavity of the arm as a moving sub", + " Seedling pushing cam; 2. Fork; 3. Seedling pushing rod; spring; 4. Spring; 5. Seedling picking arm housing; 6. Seedling pushing plate; 7. Seedling picking needle; and 8. Seedling picking needle Figure 2. Cam-linkage planetary gear system seedling picking mechanism: 1. Left housing; 2. Planetary gear; 3. Intermediate gear; 4. Sun gear; 5. Cam; 6. Linkage mechanism; 7. Roller; 8. Seedling picking arm; 9. Right housing; 10. Rack mounting plate; and 11. Input shaft. Agriculture 2023, 13, 810 4 of 18 In Figure 1, point B is the output shaft axis, C\u2013D is the seedling picking arm, and point O is the input shaft axis. E, F, G, H are the end points of connecting rod FG and connecting rod EH respectively. Where point H is also the axis of the roller. Figures 3 and 4 show the sketch of the structure of the seedling picking arm and the 3D model, respectively. The fork is hinged on the arm housing through its center of rotation, one end of the fork is in contact with the fork cam, and the other end is connected to the seedling pushing rod, which is fixed in the cavity of the arm as a moving sub" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000174_f_version_1641029125-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000174_f_version_1641029125-Figure1-1.png", + "caption": "Figure 1. Winding arrangement for single-phase excitation; (a) Short-pitched winding 1; (b) Shortpitched winding 2; and (c) Short-pitched winding 3.", + "texts": [ + " The simple method, which is the flux reversal pattern, for evaluating the core loss of the stator in each winding arrangement is introduced. Furthermore, the winding selection procedure for a three-phase 12/8 SRM to achieve high torque density, low torque ripple, and cost-saving for manufacturing is described. The finite element program (JMAG) and PC\u2013SRD software are used mainly for the calculation of the torque density (static and dynamic), core loss, and structure of winding; winding weight, slot\u2013fill factor, etc. Figure 1 shows three diagrams of the short-pitched winding configuration and flux paths of the three-phase 12/8 SRM when a single phase (phase A) is excited with unipolar operation. For the short-pitched winding, each coil is wound around a single stator pole. The winding\u2019s polarities are arranged in the stator to give a magnetic pole when each phase is excited, resulting in the stator poles acting as a north (N) or south (S) magnetic pole, which is the main cause of magnetic\u2013flux path direction. The 12/8 SRM\u2019s winding polarities of shortpitched winding are modified to change the magnetic poles. In a particular phase, Figure 1a shows the magnetic\u2013flux paths when the sequential magnetic poles are the same, e.g., N\u2013 N\u2013N\u2013N and S\u2013S\u2013S\u2013S. The sequential magnetic poles are such that two poles have the same polarity, e.g., S\u2013N\u2013N\u2013S and N\u2013S\u2013S\u2013N in Figure 1b. The opposite of sequential magnetic poles, e.g., N\u2013S\u2013N\u2013S and S\u2013N\u2013S\u2013N, is shown in Figure 1c. The torque of SRM with short-pitched winding is produced due to the self-inductance variation. The mutual-inductance between the phase windings is ineffective and therefore neglected, resulting in T = 1 2 i2a dLa d\u03b8 + 1 2 i2b dLb d\u03b8 + 1 2 i2c dLc d\u03b8 (1) where the subscripts a, b, and c denote the phase; i, L, and \u03b8 are the phase current, selfinductance, and rotor position, respectively. Three diagrams of the winding configuration and flux paths in a three-phase 12/8 SRM when two phases (phase A and B) are excited with unipolar operation are shown in Figure 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000426_cle_download_972_673-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000426_cle_download_972_673-Figure1-1.png", + "caption": "Fig. 1: Junctionless Field Effect Transistor", + "texts": [], + "surrounding_texts": [ + "This research was designed to investigate the effects of scaling of parameters of junctionless transistors (JLT) with SiO2 gate oxide and Si3N4 gate oxide on the electrical characteristics of the two devices. It also compared the electrical performance of the two devices as a way of replacing the conventional SiO2 gate oxide with high-k dielectric such as Si3N4 gate oxide. Transistors of different gate lengths (LG) and nanowire diameter (dNW) will be designed, simulate, compared and analyzed to obtain the most optimal devices. SDE and sdevice tools of sentaurus TCAD will be use to simulate and extract the electrical properties of the devices. Lombardi mobility model and Philips unified mobility model will be applied electric field and doping dependent mobility degradation. A thin-film heavily doped silicon nanowire with a gate electrode that controls the flow of current between the source and drain will be use. The electrical characteristics will be appraised and compared with the inversion mode device for different gate length and nanowire diameter. Electrical characteristics such are drain induced barrier lowering (DIBL) and subthreshold slope (SS) will be extracted and may leads to low leakage current as well as a high On-state to Off-state current ratio. The performance of the transistors will be expected to improve by changing silicon dioxide (SiO2) with silicon nitrate (Si3N4). Philips unified mobility model and Lombardi mobility model were considered as field- and doping-dependent mobility degradation. For Dominant generation and recombination process in silicon and other indirect energy band gap materials, Shockley\u2013Read\u2013Hall was used. Also, the SRH dominate in direct band gap materials under conditions of very low carrier densities or very low level injection. Auger recombination model and Fermi\u2013Dirac statistics were also used as design model. Electrical parameters of nanowire junctionless transistor with HfO2 gate oxide was compared with that of Si3N4 gate oxide device to determine the best optimized device." + ] + }, + { + "image_filename": "designv8_17_0003712__publico_Achiles.pdf-FigureA.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003712__publico_Achiles.pdf-FigureA.5-1.png", + "caption": "Figure A.5. Real (solid symbols) and imaginary (hollow symbols) parts of the permeability (a) and permittivity (b) for a three cells thick metamaterial slab obtained with HFSS (squares), DL method (circles), and TL method (triangles).", + "texts": [ + " Scattering parameters for the three cells thick metamaterial slab shown in Figure A.2 (a). The solid symbols represent S11 and the hollow symbols S21. Scattering parameters for the three cells thick metamaterial slab shown in Fig. 3. The solid symbols represent S11 and the hollow symbols S21. Squares represent parameters extracted with HFSS (benchmark), circles with the (proposed) TL method, and triangles with the DL method. ................................................................ 132 Figure A.5. Real (solid symbols) and imaginary (hollow symbols) parts of the permeability (a) and permittivity (b) for a three cells thick 165 Figure B.1. Process to clean the MS. .......................................................................... 136 Figure B.2. The spin coater and the parameters utilized to deposit the PMMA layers on the top of the MS. .................................................................... 136 Figure B.3. Thickness (a) and roughness of 10 samples of the solution with PMMA and dichloromethane spin coated on the top of a MS" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000542_41230-021-0141-8.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000542_41230-021-0141-8.pdf-Figure1-1.png", + "caption": "Fig. 1: Schematic of water-cooled steel ingot mold system", + "texts": [ + " However, grain size, which is influenced by the cooling intensity, was rarely considered in the hot cracking potential (HCP) criterion. In this study, a 10 t water-cooled steel ingot with a large height-to-diameter ratio was studied by ultrasonic inspection, CT imaging, scanning electron microscopy (SEM), and high temperature confocal microscopy. Then, thermo-mechanical simulation and post-processing were carried out to analyze the internal shrinkage crack with a new hot cracking potential criterion, considering grain size distribution and mushy zone mechanical behavior within the brittle temperature range. Figure 1 shows the schematic of the water-cooled steel ingot mold system, including water pump, water tank, motor and control system, in which a water channel was set between the ingot inner mold and outer mold. The 10 t water-cooled ingot was made of P91 heat resistant steel with the composition shown in Table 1. The ingot shape was nearly a cone with the height of 3,180 mm, the upper diameter 820 mm, and the lower diameter 550 mm, i.e., the height-to-diameter ratio was 4.64, and the taper was 8.5%. Bottom pouring was used in the casting process with the pouring temperature of 1,550 \u00b0C and the filling speed in ingot body and riser of 16 kg\u00b7s-1 and 8 kg\u00b7s-1, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000542_41230-021-0141-8.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000542_41230-021-0141-8.pdf-Figure2-1.png", + "caption": "Fig. 2: Defects distribution in ingot with ultrasonic test (unit: mm)", + "texts": [ + " The exothermic compound and anti-piping compound were added with the heating capacity of 8,000 kJ\u00b7kg-1. The cooling water flow rate was 380 m3\u00b7h-1, and decreased to 230 m3\u00b7h-1 after one hour. The demolding time was 3.2 h. Ultrasonic inspection was carried out on the 10 t water-cooled steel ingot. Defects were found 480 mm below the riser and 180 mm above the ingot bottom with the average depth to surface of 150 mm. The defect area shape was an inverted cone with the upper part wide and lower part narrow, as in the red dashed area shown in Fig. 2. A short stock with diameter of 650 mm and thickness of 50 mm was cut from the cross section of the ingot by sawing machine, which was 2,260 mm above the ingot bottom as indicated by the purple rim shown in Fig. 2. A star shaped defect with diameter of about 80 mm in the stock center was found as seen in the marked red circle in Fig. 3. Then the stock was further meshed and cubic billets with the side size of 20 mm were prepared for X-ray high energy industrial CT as shown in Fig. 4. X-ray high energy industrial CT was used to carry out the transparent tomography image of the star shaped defects. Thousands of cross section images were stitched together by software and the porosities in the billets were counted quantitatively", + " (5) through (8), the larger BTR indicates the more vulnerable mushy zone. Figure 9(a) shows the shrinkage porosity in a water-cooled ingot based on solidification simulation, where a slender defects zone is predicted. Figure 9(b) shows the corresponding value of Niyama criterion. It can be seen that the center area in ingot with Niyama criterion below 30 K0.5\u00b7s0.5\u00b7cm-1 [Fig. 9(b)] is consistent with that with shrinkage porosity below 0.5% [Fig. 9(a)]. Compared with the ultrasonic inspection results in Fig. 2, the simulated defects in bottom positions are more accurate, while the top positions in Figs. 9(a) and (b) are overestimated. Besides, both simulated defects' widths are underestimated, because the defects zone contains both shrinkage porosity and hot crack. The shrinkage porosity criterion has limitation in prediction of such defects due to its derivation. Hot crack originates from porosities formed by insufficient mass feeding, and propagates under excessive tensile stress. Therefore, the hot cracking zone is usually larger than the shrinkage porosity zone", + " Figure 11(a) shows the simulated grain size distribution with large size in the core and the upper part, and small size in the side wall and the lower part of ingot. The result of HCP criterion is shown in Fig. 11(b), in which the positive value means tensile stress and the negative value means compressive stress. Compared with the CD and Katgerman criteria (Fig. 10), the HCP criterion also successfully predicts the hot cracking in the ingot center, and avoids overestimation of the hot cracking in the ingot chilled layer. As shown in Fig. 2, the ultrasonic inspection results reveal that the ultrasonic signal is shallow \u00b7 A Q \u00b7 \u00b7 BTR in the ingot upper part and deep in the ingot lower part. The simulation results of HCP criterion reflect the inverted cone shape of the defects zone, and more accurately predict the lower position of the defects. Since the numerical model does not cover the healing effect of molten steel feeding in the riser, the hot cracking potential is overestimated in the ingot upper part. Through the above observation and simulation, a scenario can be inferred for the internal shrinkage crack during solidification of the water-cooled steel ingot with a large height-to-diameter ratio" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000317_load.php_id_24031902-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000317_load.php_id_24031902-Figure1-1.png", + "caption": "FIGURE 1. Structure diagram of the motor. FIGURE 2. Structural diagram of the DMID.", + "texts": [ + " A Pareto, relative optimal solution set, is obtained, which can satisfy the requirements of low motor noise, ample average output torque, and small torque ripple, and the optimal design scheme was selected from it. Finally, the optimization results of the design variables are compared with the initial data to verify that the optimized structure can effectively reduce the electromagnetic vibration and noise of the motor while maintaining the original performance. Compared with the traditional low-speed high-torque permanent magnet motor, the tile-shaped permanent magnets in the motor structure, as shown in Figure 1, can increase the pole arc coefficient of the motor to improve the magnetic field distribution in the air gap. At the same time, a dovetail-shaped magnetic isolation device is added between the permanent magnets. On the one hand, this structure can fix tile-shaped permanent magnets well, and it is easy to install permanentmagnets. Using this device, while the structure of the stator and rotor remains unchanged, the contact area between the permanent magnet and the air gap is increased\u037e the air gap space is increased\u037e the magnetic flux leakage is reduced\u037e the magnetic field distribution of the air gap is improved\u037e and the device has better electrical performance" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001040_77_aoje_2_021025.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001040_77_aoje_2_021025.pdf-Figure4-1.png", + "caption": "Fig. 4 Hinged tile-based curling air surface architecture. (a) Top view shows the curling vacuum bladder formed with hinged T-shaped tiles. (b) Bottom view shows the layout of the straightening interconnected inflation bladders placed beneath each hinge.", + "texts": [ + " 2 / 021025-3 D ow nloaded from http://asm edigitalcollection.asm e.org/openengineering/article-pdf/doi/10.1115/1.4062220/7009677/aoje_2_021025.pdf by guest on 20 D ecem ber 2024 pout), eliminating the curling torques. When the inflated straightening bladder, aided by the external load, pulls the tile unit back to the fully straight position, the membrane is in tension again, and the operation cycle is complete. 2.2 Hinged Tile-Based Curling Air Surface. A hinged tilebased curling air surface, Fig. 4 is constructed with a series of connected curling tile units. Multiple T-shaped tiles are hinged together with a single curling vacuum bladder, surrounding the entire assembly. A series of straightening bladders is interconnected through small air channels spanning the hinge lines creating one contiguous straightening bladder system (Fig. 4(b)). A single vacuum port and a single inflation port simultaneously activate all the tile units with distributed actuation and displacement. The surface operates through the tile units. In the context of the windshield cowling, the surface covers the gap between the windshield and the hood and curls against the external wind load for the wipers to function. The cowling operates in a similar four-state cycle. In the gap closed state, the cowling is stowed, covering the wipers with one end fixed to the rear edge of the hood and the other resting on the windshield (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004912_ysRevLett.117.077401-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004912_ysRevLett.117.077401-Figure3-1.png", + "caption": "Fig. 3: A metasurface providing unidirectional transmission allows high transmission for obliquely incident plane waves propagating in the direction but absorbs radiation propagating in the \u2013 direction.", + "texts": [ + " Isolators provide high transmission in the direction and high absorption in the \u2013 direction, which protects devices in the region 0 from reflections originating from objects in the region 0 [29]. An ideal isolator is polarization independent, has , and 1 00 1 . From the stipulated S-parameters, it can be shown that the necessary 3D surface parameters are given by: / / , / / , (6) / / / , and all other terms are 0 [22]. In other words, the metasurface should provide identical, anisotropic electric and magnetic responses that are lossy. A metasurface providing unidirectional transmission that is designed to work for 45\u00b0 at 10 GHz is shown in Fig. 3. The electric response is generated using electric dipoles centrally loaded with an inductor (8.15 nH) and resistor (18.8 \u2126) in series, which forms a lossy resonator. The magnetic response is generated with loops that surround the dipoles. Each loop is symmetrically loaded with four capacitors (0.152 pF) and resistors (3.75 \u2126). The simulated transmittance in the direction | | and \u2013 direction | | is 94% and 0.9%, respectively, which gives an extinction ratio of 104 (20 dB). Therefore, the metasurface enables a directive source located below the metasurface 0 to illuminate an object above the metasurface 0 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004044_f_etic2017_01092.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004044_f_etic2017_01092.pdf-Figure1-1.png", + "caption": "Fig. 1. Perspective Top View of 3D Antenna.", + "texts": [ + " Here, microstrip meander line 3D antenna operating at 2.45GHz for IoT environment is described. Recent technology 3D antenna is believed to overcome some of the drawbacks identified in conventional antennas where it is required for certain application. The design and simulation processes are done by using CST Microwave Studio. The simulation result is optimized to achieve the best performance of the antenna. All manuscripts must be in English, also the table and Fig. texts, otherwise we cannot publish your paper. Antenna structure shown in Fig. 1 until Fig. 4 shows the proposed antenna designed. The antenna is mounted in the middle of a rectangular ground plane with the dimension of 21.6mm x 21.6mm. Originally, the size of antenna was determined by \u03bb/4. The width of the antenna was calculated by: c f (1) Where; =wave length, c=speed of light, f= frequency Calculation: = 3 10 2.45 = 0.1224 With the meander line technique implemented with 3D structure, each arm of the antenna L2 is 4.3mm. The antenna size is reduced to . Table 1 shows the antenna size and parameter" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000847_853_83_17-00194__pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000847_853_83_17-00194__pdf-Figure6-1.png", + "caption": "Fig. 6 Configuration of the twin gimbal system", + "texts": [], + "surrounding_texts": [ + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3G \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f \u03a3G \u306e z\u8ef8\u56de\u308a\u306b\u56de\u8ee2\u3059\u308b\uff0e\u305d\u306e\u89d2\u5ea6\u3092 \u03b3 \u3068\u3059\u308b\uff0e\u539f\u70b9\u3092\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3 \u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3G \u3092 z\u8ef8\u56de\u308a\u306b \u03b3 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30db\u30a4\u30fc\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3W \u3068\u3059\u308b\uff0e\n\u4ee5\u964d\u6570\u5f0f\u4e2d\u3067\u306f cos\u03b8 =C\u03b8 , sin\u03b8 = S\u03b8 \u3068\u7565\u8a18\u3059\u308b\uff0e\n3\u00b72 \u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\n\u307e\u305a\uff0c\u56de\u8ee2\u904b\u52d5\u3092\u8868\u3059\u305f\u3081\u306e\u5404\u525b\u4f53\u306e\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092\u660e\u3089\u304b\u306b\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u901f\u5ea6\u306f\u56de\u8ee2\u89d2\n\u03d5 ,\u03b1,\u03b2 ,\u03b3 \u306e\u6642\u9593\u5909\u5316\u306b\u3088\u3063\u3066\u8868\u3059\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u3053\u308c\u3092 \u03a3W \u3067\u8868\u3057\u305f\u3068\u304d W \u03c9W \u3068\u8a18\u3059\u3068\uff0c\nW \u03c9W = C\u03b3 S\u03b3 0 \u2212S\u03b3 C\u03b3 0\n0 0 1\n C\u03b1 \u03d5\u0307 + \u03b2\u0307\nS\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307\n (1)\n\u3068\u306a\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3G \u3067\u8868\u3057\u305f\u3082\u306e\u3092 G\u03c9G \u3068\u8a18\u3059\u3068\uff0c\u5f0f (1) \u306b\u304a\u3044\u3066 \u03b3 = 0, \u03b3\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u307e\u305f\u53f0\u8eca\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092 C\u03c9C \u3068\u8a18 \u3059\u3068\uff0c G\u03c9G \u306b\u5bfe\u3057\u3066 \u03b2 = 0, \u03b2\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u3086\u3048\u306b\uff0c\u305d\u308c\u305e\u308c\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u306a\u308b\uff0e\nG\u03c9G = C\u03b1 \u03d5\u0307 + \u03b2\u0307 S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 C\u03c9C = C\u03b1 \u03d5\u0307 \u03b1\u0307 S\u03b1 \u03d5\u0307 (2)\n3\u00b73 \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae \u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e\u6163\u6027\u30c6\u30f3\u30bd\u30eb\u3092\u305d\u308c\u305e\u308c \u03a3W ,\u03a3G,\u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092\nIW = IWX 0 0 0 IWY 0\n0 0 IWZ\n , IG = IGX 0 0 0 IGY 0\n0 0 IGZ\n , IC = ICX 0 0 0 ICY 0\n0 0 ICZ\n (3)\n\u3068\u3059\u308b\uff0e\u305f\u3060\u3057\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u5bfe\u79f0\u6027\u304b\u3089 IWX = IWY \u3067\u3042\u308a\uff0c\u3053\u306e\u5024\u3092 IWXY \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TWR,TGR,TCR \u306f\u305d\u308c\u305e\u308c\u5f0f (1)(2)\u3092\u7528\u3044\u3066\uff0c\nTWR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 } + IWZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307 )2 ]\n(4)\nTGR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03d5\u0307) = 1 2\n{ IGX ( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + IGY ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 + IGZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 )2 }\n(5)\nTCR(\u03b1, \u03b1\u0307, \u03d5\u0307) = 1 2 ( ICXC2 \u03b1 \u03d5\u0307 2 + ICY \u03b1\u03072 + ICZS2 \u03b1 \u03d5\u0307 2) (6)", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u3068\u306a\u308b\uff0e\n3\u00b74 \u30c4\u30a4\u30f3\u30b8\u30f3\u30d0\u30eb\u30e2\u30c7\u30eb\u306e\u5fc5\u8981\u6027\n\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae\u5f0f (4)\u306b\u306f\uff0c\u53f0\u8eca\u306e\u50be\u304d\u89d2\u901f\u5ea6 \u03b1\u0307 \u3068\u5730\u9762\u306e\u8d77\u4f0f\u306b\u3088\u308a\u751f\u3058\u308b\u89d2 \u901f\u5ea6 \u03d5\u0307 \u306e\u7a4d\uff0c\u304a\u3088\u3073\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u901f\u5ea6 \u03b2\u0307 \u3068 \u03d5\u0307 \u306e\u7a4d\u304c\u3042\u308b\uff0e\u3053\u308c\u3089\u306e\u305f\u3081\u306b\uff0c\u5bfe\u8c61\u306e\u904b\u52d5\u65b9\u7a0b\u5f0f\u306e\u4e2d\u306b\u5730\u9762\u306e \u8d77\u4f0f\u306b\u3088\u308a\u751f\u3058\u308b\u89d2\u901f\u5ea6 \u03d5\u0307 \u306b\u4f9d\u5b58\u3059\u308b\u30e2\u30fc\u30e1\u30f3\u30c8\u304c\u8907\u96d1\u306b\u4f5c\u7528\u3059\u308b\uff0e\u3055\u3089\u306b\u30db\u30a4\u30fc\u30eb\u306e\u89d2\u901f\u5ea6 \u03b3\u0307 \u3068 \u03d5\u0307 \u306e\u7a4d\u304c\u3042\u308b \u305f\u3081\uff0c\u904b\u52d5\u65b9\u7a0b\u5f0f\u306e\u4e2d\u306b \u03d5\u0307 \u3068 \u03b3\u0307 \u306e\u7a4d\u304b\u3089\u306a\u308b\u30e2\u30fc\u30e1\u30f3\u30c8\u304c\u73fe\u308c\u308b\uff0e\u3053\u308c\u306f\u5730\u9762\u306e\u50be\u304d\u306e\u5909\u5316\u306e\u305f\u3081\u53f0\u8eca\u306e\u59ff\u52e2\u304c \u30d4\u30c3\u30c1\u89d2\u65b9\u5411\u3078\u50be\u304f\u969b\u306b\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\u3078\u767a\u751f\u3059\u308b\u30b8\u30e3\u30a4\u30ed\u30e2\u30fc\u30e1\u30f3\u30c8\u306b\u76f8\u5f53\u3057\uff0c\u53f0\u8eca\u3092\u5012\u305d\u3046\u3068\u3059\u308b\u5916\u4e71\u3068\u306a\u308b\uff0e\n\u3053\u308c\u3089\u306e\u5916\u4e71\u9805\u3092\u6253\u3061\u6d88\u3059\u305f\u3081\u306b\uff0c\u540c\u4e00\u69cb\u9020\u306e\u30db\u30a4\u30fc\u30eb\u3068\u30b8\u30f3\u30d0\u30eb\u3092\u53f0\u8eca\u306e\u524d\u65b9\u3068\u5f8c\u65b9\u306b\u4e00\u7d44\u3065\u3064\u914d\u7f6e\u3059\u308b\u30c4\u30a4 \u30f3\u30b8\u30f3\u30d0\u30eb\u30e2\u30c7\u30eb\u3092\u69cb\u7bc9\u3059\u308b\uff0e\u56f3 6\u306b\u305d\u306e\u69d8\u5b50\u3092\u793a\u3059\uff0e\n\u524d\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u3092\u30b8\u30f3\u30d0\u30eb 1\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3G1 \u3092\u914d\u7f6e\uff0c\u524d\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u3092\u30db\u30a4\u30fc\u30eb 1\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3W1 \u3092\u914d\u7f6e\u3059\u308b\uff0e \u307e\u305f\uff0c\u5f8c\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u3092\u30b8\u30f3\u30d0\u30eb 2\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3G2 \u3092\uff0c\u5f8c\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u3092\u30db\u30a4\u30fc\u30eb 2\u3068\u3057\u5ea7\u6a19\u7cfb \u03a3W2 \u3092\u914d\u7f6e\u3059\u308b\uff0e \u524d\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03b21\uff0c\u524d\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u89d2\u5ea6\u3092 \u03b31\uff0c\u5f8c\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03b22\uff0c\u5f8c\u65b9\u306e\u30db \u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u89d2\u5ea6\u3092 \u03b32 \u3068\u3059\u308b\uff0e\n\u3053\u306e\u3068\u304d\uff0c\u524d\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TW1R \u306f\uff0c\nTW1R(\u03b1,\u03b21, \u03b1\u0307, \u03b2\u03071, \u03b3\u03071, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u03071 )2 + ( S\u03b21S\u03b1 \u03d5\u0307 +C\u03b21 \u03b1\u0307 )2 } + IWZ ( C\u03b21S\u03b1 \u03d5\u0307 \u2212S\u03b21 \u03b1\u0307 + \u03b3\u03071 )2 ]\n(7)\n\u5f8c\u65b9\u306e\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TW2R \u306f\uff0c\nTW2R(\u03b1,\u03b22, \u03b1\u0307, \u03b2\u03072, \u03b3\u03072, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u03072 )2 + ( S\u03b22S\u03b1 \u03d5\u0307 +C\u03b22 \u03b1\u0307 )2 } + IWZ ( C\u03b22S\u03b1 \u03d5\u0307 \u2212S\u03b22 \u03b1\u0307 + \u03b3\u03072 )2 ]\n(8)\n\u3068\u306a\u308b\uff0e\u3053\u3053\u3067\uff0c\u03b21 = \u03b2 , \u03b22 =\u2212\u03b2 , \u03b3\u03071 = \u03b3\u0307, \u03b3\u03072 =\u2212\u03b3\u0307 \u3068\u306a\u308b\u3088\u3046\u306b\uff0c\u30b8\u30f3\u30d0\u30eb\u306e\u50be\u304d\u89d2\u5ea6\u306b\u62d8\u675f\u3092\u304b\u3051\uff0c\u30db\u30a4\u30fc\u30eb \u306e\u56de\u8ee2\u5236\u5fa1\u3092\u884c\u3046\u3053\u3068\u306b\u3059\u308b\u3068\uff0c\u3053\u308c\u3089\u306e\u548c\u306f\nTWR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = TW1R(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307)+TW2R(\u03b1,\u2212\u03b2 , \u03b1\u0307,\u2212\u03b2\u0307 ,\u2212\u03b3\u0307, \u03d5\u0307)\n= IWXY\n( C2\n\u03b1 \u03d5\u0307 2 + \u03b2\u0307 2 +S2 \u03b2 S2 \u03b1 \u03d5\u0307 2 +C2 \u03b2 \u03b1\u03072 ) + IWZ { C2 \u03b2 S2 \u03b1 \u03d5\u0307 2 + ( S\u03b2 \u03b1\u0307 \u2212 \u03b3\u0307 )2 }\n(9)\n\u3068\u306a\u308a\uff0c\u03b1\u0307\u03d5\u0307 , \u03b2\u0307 \u03d5\u0307 , \u03b3\u0307 \u03d5\u0307 \u306e\u9805\u304c\u6253\u3061\u6d88\u3055\u308c\u308b\uff0e \u3057\u304b\u3057\u306a\u304c\u3089\uff0c\u3053\u3053\u3067\u306f\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u5236\u5fa1\u3092\u6b63\u78ba\u306b\u884c\u3046\u3053\u3068\u304c\u56f0\u96e3\u3067\u3042\u308b\u3053\u3068\u3092\u60f3\u5b9a\u3057 \u03b3\u03071 = (1+ \u03b4 )\u03b3\u0307, \u03b3\u03072 = \u2212(1\u2212\u03b4 )\u03b3\u0307 \u3068\u8a18\u8ff0\u3059\u308b\uff0e\u3053\u3053\u3067 \u03b3\u0307 \u306f \u03b3\u03071 \u3068 \u03b3\u03072 \u306e\u5927\u304d\u3055\u306e\u5e73\u5747\u5024\uff0c\u03b4 \u306f\u5e73\u5747\u5024\u304b\u3089\u306e\u3070\u3089\u3064\u304d\u3092\u8868\u3059\u30d1\u30e9\u30e1\u30fc\u30bf\u3067\u3042 \u308b\uff0e\u3053\u306e\u3068\u304d\uff0c\u5f0f (9)\u306f", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\nT \u2032 WR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = TW1R(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 ,(1+\u03b4 )\u03b3\u0307, \u03d5\u0307)+TW2R(\u03b1,\u2212\u03b2 , \u03b1\u0307,\u2212\u03b2\u0307 ,\u2212(1\u2212\u03b4 )\u03b3\u0307, \u03d5\u0307)\n= IWXY\n( C2\n\u03b1 \u03d5\u0307 2 + \u03b2\u0307 2 +S2 \u03b2 S2 \u03b1 \u03d5\u0307 2 +C2 \u03b2 \u03b1\u03072 ) + IWZ {( C\u03b2 S\u03b1 \u03d5\u0307 +\u03b4 \u03b3\u0307 )2 + ( S\u03b2 \u03b1\u0307 \u2212 \u03b3\u0307 )2 }\n(10)\n\u306e\u3088\u3046\u306b\u306a\u308b\uff0e\n\u540c\u69d8\u306b\uff0c\u524d\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TG1R \u306f\uff0c\nTG1R(\u03b1,\u03b21, \u03b1\u0307, \u03b2\u03071, \u03d5\u0307) = 1 2\n{ IGX ( C\u03b1 \u03d5\u0307 + \u03b2\u03071 )2 + IGY ( S\u03b21S\u03b1 \u03d5\u0307 +C\u03b21 \u03b1\u0307 )2 + IGZ ( C\u03b21S\u03b1 \u03d5\u0307 \u2212S\u03b21 \u03b1\u0307 )2 }\n(11)\n\u5f8c\u65b9\u306e\u30b8\u30f3\u30d0\u30eb\u306e\u56de\u8ee2\u904b\u52d5\u306b\u3088\u308a\u751f\u3058\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TG2R \u306f\uff0c\nTG2R(\u03b1,\u03b22, \u03b1\u0307, \u03b2\u03072, \u03d5\u0307) = 1 2\n{ IGX ( C\u03b1 \u03d5\u0307 + \u03b2\u03072 )2 + IGY ( S\u03b22S\u03b1 \u03d5\u0307 +C\u03b22 \u03b1\u0307 )2 + IGZ ( C\u03b22S\u03b1 \u03d5\u0307 \u2212S\u03b22 \u03b1\u0307 )2 }\n(12)\n\u3068\u306a\u308a\uff0c\u03b21 = \u03b2 , \u03b22 =\u2212\u03b2 \u306e\u5834\u5408\u306e\u3053\u308c\u3089\u306e\u548c\u306f\nTGR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03d5\u0307) = TG1R(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03d5\u0307)+TG2R(\u03b1,\u2212\u03b2 , \u03b1\u0307,\u2212\u03b2\u0307 , \u03d5\u0307)\n= IGX\n( C2 \u03b1 \u03d5\u0307 2 + \u03b2\u0307 2 ) + IGY ( S2 \u03b2 S2 \u03b1 \u03d5\u0307 2 +C2 \u03b2 \u03b1\u03072 ) + IGZ ( C2 \u03b2 S2 \u03b1 \u03d5\u0307 2 +S2 \u03b2 \u03b1\u03072 )\n(13)\n\u3068\u306a\u308b\uff0e\n3\u00b75 \u91cd\u5fc3\u306e\u4f4d\u7f6e\u3068\u901f\u5ea6\u30d9\u30af\u30c8\u30eb \u6b21\u306b\uff0c\u5404\u525b\u4f53\u306e\u91cd\u5fc3\u4f4d\u7f6e\u3068\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u306e\u8868\u73fe\u5f0f\u3092\u660e\u3089\u304b\u306b\u3059\u308b\uff0e\u03a3A \u306e\u539f\u70b9\u3092 PA0 \u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f\u8d77\u4f0f\u306e\u3042 \u308b\u5730\u9762\u4e0a\u3092\u52d5\u304f\uff0e\u3053\u3053\u3067\u306f\u5de6\u53f3\u65b9\u5411\uff08\u03a3B \u306e x\u8ef8\u65b9\u5411\uff09\u3078\u306f\u79fb\u52d5\u3057\u306a\u3044\u3068\u4eee\u5b9a\u3059\u308b\uff0e\u305d\u3053\u3067 PA0 \u3092 \u03a3B \u3067\u8868\u3059\u3068\u304d BpA0 = [0 yA0 zA0] T \u3068\u3059\u308b\uff0e\n\u30db\u30a4\u30fc\u30eb 1\u306e\u56de\u8ee2\u8ef8\u3068\u30b8\u30f3\u30d0\u30eb 1\u306e\u8ef8\u3068\u306e\u4ea4\u70b9\u3092 P01 \u3068\u8868\u3059\uff0eP01 \u306f PA0 \u304b\u3089\u898b\u3066 \u03a3C \u306e z\u8ef8\u6b63\u65b9\u5411\u306b b\uff0cy\u8ef8\u6b63 \u65b9\u5411\u306b d\u306e\u4f4d\u7f6e\u306b\u3042\u308b\uff0e\u30db\u30a4\u30fc\u30eb 1\u306e\u91cd\u5fc3\u306e\u70b9\u3092 PW1G\u3068\u3059\u308b\uff0ePW1G\u306f P01\u304b\u3089\u898b\u3066 \u03a3G1 \u306e z\u8ef8\u6b63\u65b9\u5411\u306b a\u306e\u4f4d\u7f6e \u306b\u3042\u308b\uff0e\u3053\u306e\u3068\u304d PW1G \u3092 \u03a3B \u3067\u8868\u3059\u3068\uff0cPA0 \u306e\u5ea7\u6a19\u306b PA0 \u304b\u3089 P01 \u3078\u306e\u30d9\u30af\u30c8\u30eb\u3092\u8db3\u3057\uff0c\u3055\u3089\u306b P01 \u304b\u3089 PW1G \u3078 \u306e\u30d9\u30af\u30c8\u30eb\u3092\u8db3\u3059\u3053\u3068\u3067\u6c42\u3081\u3089\u308c\u308b\uff0e\u3053\u308c\u3089\u3092\u3059\u3079\u3066 \u03a3B \u3067\u8868\u3059\u3068\uff0c\nBpW1G = 0 yA0\nzA0\n+ 1 0 0 0 C\u03d5 \u2212S\u03d5\n0 S\u03d5 C\u03d5\n C\u03b1 0 S\u03b1 0 1 0\n\u2212S\u03b1 0 C\u03b1\n 0\nd \u2212aS\u03b21 b+aC\u03b21\n (14)\n\u3067\u3042\u308b\uff0e\u307e\u305f\uff0c\u91cd\u5fc3\u4f4d\u7f6e\u306e\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u306f\u5f0f (14)\u3092\u4e01\u5be7\u306b\u6642\u9593\u5fae\u5206\u3059\u308c\u30701\nBp\u0307W1G = 1 0 0 0 C\u03d5 \u2212S\u03d5\n0 S\u03d5 C\u03d5\n C\u03b1(b+aC\u03b21)\u03b1\u0307 \u2212aS\u03b1 S\u03b21 \u03b2\u03071\nvA \u2212C\u03b1(b+aC\u03b21)\u03d5\u0307 \u2212aC\u03b21 \u03b2\u03071\n(d \u2212aS\u03b21)\u03d5\u0307 \u2212S\u03b1(b+aC\u03b21)\u03b1\u0307 \u2212aC\u03b1 S\u03b21 \u03b2\u03071\n (15)\n\u3068\u306a\u308b\uff0e\u3053\u3053\u3067 \u03a3A \u306e\u539f\u70b9 PA0 \u306e\u79fb\u52d5\u306f\u5730\u9762\u306e\u50be\u659c\u306b\u6cbf\u3063\u305f\u3082\u306e\u3067\u3042\u308b\u306e\u3067\uff0c\u305d\u306e\u79fb\u52d5\u901f\u5ea6\u306e\u65b9\u5411\u306f\u5730\u9762\u306e\u50be\u659c\uff0c \u3059\u306a\u308f\u3061\uff0c\u89d2\u5ea6 \u03d5 \u306b\u3088\u308a\u5b9a\u307e\u308b\uff0e\u3086\u3048\u306b\uff0c\u53f0\u8eca\u306e\u79fb\u52d5\u306e\u901f\u3055\u3092 vA \u3068\u3057\u3066 y\u0307A0 = vA cos\u03d5 , z\u0307A0 = vA sin\u03d5 \u3068\u8a18\u8ff0\u3067\u304d \u308b\u3068\u3057\u305f\uff0e\n\u540c\u69d8\u306b\uff0c\u30db\u30a4\u30fc\u30eb 2\u306e\u56de\u8ee2\u8ef8\u3068\u30b8\u30f3\u30d0\u30eb 2\u306e\u8ef8\u3068\u306e\u4ea4\u70b9\u3092 P02 \u3068\u8868\u3059\uff0eP02 \u306f PA0 \u304b\u3089\u898b\u3066 \u03a3C \u306e z\u8ef8\u6b63\u65b9\u5411\u306b b\uff0cy\u8ef8\u6b63\u65b9\u5411\u306b\u2212d\u306e\u4f4d\u7f6e\u306b\u3042\u308b\u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb 2\u306e\u91cd\u5fc3\u306e\u70b9\u3092 PW2G\u3068\u3059\u308b\uff0ePW2G\u306f P02\u304b\u3089\u898b\u3066 \u03a3G2 \u306e z\u8ef8\n1\u5f0f (14) \u306e\u4e21\u8fba\u306b\u56de\u8ee2\u884c\u5217\u3092\u304b\u3051\u305f1 0 0 0 C\u03d5 S\u03d5 0 \u2212S\u03d5 C\u03d5 BpW1G \u2212 0 yA0 zA0 = C\u03b1 0 S\u03b1 0 1 0 \u2212S\u03b1 0 C\u03b1 0 d \u2212aS\u03b21 b+aC\u03b21 \u306e\u4e21\u8fba\u3092\u6642\u9593\u5fae\u5206\u3057\u305f\u306e\u3061\u5f0f (14) \u3092\u4ee3\u5165\u3057\u306a\u304a\u3059\u3068\u8a08\u7b97\u304c\u7c21\u5358\u306b\u306a\u308b\uff0e" + ] + }, + { + "image_filename": "designv8_17_0003125_v.org_pdf_2405.06070-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003125_v.org_pdf_2405.06070-Figure2-1.png", + "caption": "Fig. 2. Illustrates the Husky full-fidelity model vs. the reduced order model with the model parameters used in the derivations in Section III.", + "texts": [ + " The amplifiers are isolated away from the actuators and are separated into 2 racks of 6 amplifiers each and then mounted onto either side of the robot. The host PC running MATLAB is connected to the Realtime machine using EtherCAT. The propulsion system is fitted with 4 Schubeler Electric Ducted fans (EDF) that provide approximately 8 kgf of thrust in total. It is built with a lightweight hexagonal aluminum composite structure sandwiched between carbon fiber plates, the design of which is extensively delineated in [22]. The equations of motion of the HROM can be derived using the energy based Euler-Lagrange dynamics formulation. As shown in Fig. 2, the positions of the leg ends are defined as functions of the spherical joint primitives, namely \u03d5 and \u03b3, along with the length of the leg l. The pose of the body can be defined using pB \u2208 R3, and Z-Y-X Euler angles \u03a6B . The rotation matrix can also then be defined from the Euler matrix as RB . The generalized coordinates of the robot body can then be defined as follows: q = [p\u22a4 B ,\u03a6 \u22a4 B ] \u22a4, (1) and the leg states of the robot can be defined as, qL = [. . . , \u03d5i, \u03b3i, li, . . . ] \u22a4, i \u2208 F , (2) where F = {FR,HR,FL,HL} represents the respective legs and thrusters" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004025_load.php_id_22120220-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004025_load.php_id_22120220-Figure4-1.png", + "caption": "Figure 4. (a) Schematic of decoupling structure, (b) its equivalent circuit model.", + "texts": [ + " The positioning and the dimensions of the decoupling structure, L-strip feed, and the interdigital filter shaped slits play a vital role in realizing the desired isolation and the radiation characteristics. Thus, these parameters are numerically finalized using the Finite-Element EM solver HFSS [35], and the optimal values are given in the caption of Fig. 3. Prior to discussing the evolution of the proposed antenna structure shown in Fig. 3, it is worth explicating how the decoupling network could generate the required phase shift of 270\u25e6 to the signal passing through it. To this end, an equivalent simplified circuit model of the design, shown in Fig. 4, is considered and analyzed. As observed, the interference signal originating from patch 1 couples to the decoupling network via the capacitive gap (g1), transmits through the network, and then couples to patch 2 via the other capacitive gap (g1). These two capacitive gaps could ideally be replaced by lumped capacitors (Cg), as shown in Fig. 4(b). These capacitors add nearly 90\u25e6 phase shift each, a total of 180\u25e6 phase shift. The microstrip line (L1) of the decoupling network is approximately \u03bbd/2 in length, where \u03bbd is the dielectric wavelength at the frequency of operation, thus generating a 180\u25e6 phase shift at the resonant frequency. On the other hand, each of the microstrip lines, labelled L2, is slightly longer than \u03bbd/4. From the transmission line analysis, an open-ended line with the length greater than \u03bbd/4 acts as an inductor, causing a phase delay of 90\u25e6. Thus, these two lines (L2) create a total phase lag of 180\u25e6. The capacitive gap (g2) between the lines (L2), modeled by a lumped capacitor Cl in Fig. 4(b), adds another 90\u25e6 phase shift to the signal at the resonant frequency. Hence, the total phase shift experienced by the signal transmitting from patch 1 to patch 2 via these decoupling transmission lines is approximately 270\u25e6. For further clarification, the evolution of the design and its S-parameters at each phase of the design are depicted in Fig. 5. As observed, when the tightly-spaced antenna elements are fed using the conventional SMA probe feeds (Antenna 1), the levels of the mutual coupling are as high as \u22124 dB at the resonating frequency of 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004544__39_article-p159.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004544__39_article-p159.pdf-Figure4-1.png", + "caption": "Fig. 4 3D model of the universal joint (1 \u2013 driving fork, 2 \u2013 bearing shell, 3 \u2013 needle bearing, 4 \u2013 sealing, 5 \u2013 lock ring, 6 \u2013 cross, 7 \u2013 joint bolt, 8 \u2013 driven fork)", + "texts": [ + " cos\ud835\udefc2 From the equation after adjustment is obtained tg\ud835\udf111 \u2032 = tg\ud835\udf112 . 1 cos\ud835\udefc2 [6] Inserting equation [6] into equation [4] tg\ud835\udf111 = tg\ud835\udf112 . 1 cos\ud835\udefc2 . cos\ud835\udefc1 [7] If \ud835\udefc1 = \ud835\udefc2 , then tg\ud835\udf111 = tg\ud835\udf112 (8) This means that the rotation of the driving shaft \ud835\udf111 equals the rotation of the driven shaft \ud835\udf112 . The construction of the universal joints allows transferring torque moment between two rotating abaxial shafts. In some cases, this allows axle shift (2). The most commonly used joint is the universal joint shown in Fig. 4. In the motor vehicles are used universal joints for maximal axes deviation 8\u00b0. Special design allows also greater deviation of the axes (5, 6). Kinematic simulation was made using the CAD/CAM/CAE system CATIA V5 on the model of the cardan shaft which contains two universal joints (Fig. 5). Between all connections with bearings, the revolute type of joint and one prismatic type of connection for central cardan shaft was used, which allows adjustment of the relative position between two parts of the cardan shaft through castellated shaft connection" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002913_fraeko2018_00070.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002913_fraeko2018_00070.pdf-Figure3-1.png", + "caption": "Fig. 3. Diagram of support and load with force F for normal testing of circumferential stiffness according to PN EN 1228: 1999.", + "texts": [ + " The \u2206dv deflections calculated in [7] for the determined circumferential stiffness variables So and for the assumed load were known, as shown in Fig. 2. The simulation was carried out accordingly to the variants of filling the pipe with hot sewage up to the height of 31.5 mm and 157.5 mm above the bottom of the manhole (10% and 50% of the height). Two load diagrams have been adopted. In the first one, the support scheme was applied, as in the case of laboratory testing of circumferential stiffness (Fig. 3), for the concentrated force load F = 600 N, which corresponded to the force used in [7] to determine the circumferential stiffness at 20\u00b0C (at a standard deflection of 3%). This made it possible to verify the correct operation of the pipe model adopted in the simulation. In the second diagram, the ground was laid up to the level of the pipe vault together with the surface load qv = 65 kPa, similar to the situation shown in Fig. 2. The calculations were based on the elastic-perfectly plastic model of PVC material preservation and the elastic-plastic constitutive model of soil with the Coulomb-Mohr strength criterion with the following parameters: volumetric density \u03c1 = 1", + " The first proposed justification indicates that the model adopted is inadequate for analysing this situation. At the same time, the authors did not find in the literature available to them the results of research The simulation was carried out accordingly to the variants of filling the pipe with hot sewage up to the height of 31.5 mm and 157.5 mm above the bottom of the manhole (10% and 50% of the height). Two load diagrams have been adopted. In the first one, the support scheme was applied, as in the case of laboratory testing of circumferential stiffness (Fig. 3), for the concentrated force load F = 600 N, which corresponded to the force used in [7] to determine the circumferential stiffness at 20\u00b0C (at a standard deflection of 3%). This made it possible to verify the correct operation of the pipe model adopted in the simulation. In the second diagram, the ground was laid up to the level of the pipe vault together with the surface load qv = 65 kPa, similar to the situation shown in Fig. 2. The calculations were based on the elastic-perfectly plastic model of PVC material preservation and the elastic-plastic constitutive model of soil with the Coulomb-Mohr strength criterion with the following parameters: volumetric density \u03c1 = 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004293_6_2050-5736-3-S1-P82-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004293_6_2050-5736-3-S1-P82-Figure4-1.png", + "caption": "Figure 4 Effect drawing 3", + "texts": [], + "surrounding_texts": [ + "Ultrasound and MRI imaging guiding system for Robotic assisted interventional procedures such as needle biopsy and FUS ablation have to be improved to allow a one stop shop multimodality image guidance. A specific holder which has the capability for connecting the application module of the interventional robotic system \u201cINNOMOTION\u201d (IBSmm, CZ) with SIEMENS wireless ultrasound probe (Acuson Freestyle) was designed and manufactured in order to achieve the desired function. The work is a subproject in FUTURA an EU FP7 funded project for the development of robotic assisted Ultrasound guided focused ultrasound." + ] + }, + { + "image_filename": "designv8_17_0002090_3-030-58147-3_44.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002090_3-030-58147-3_44.pdf-Figure3-1.png", + "caption": "Fig. 3. (a) Rendered 3D model of the device; (b) mechanism for pulling up/down the fabric belt. (c) A user testing the proposed system.", + "texts": [ + " Ten users (6 males, age 23\u201356, all right handed) took part in the experiment. One was a surgeon with many years of experience, three were medical students with 5 years of experience, while the remaining six were medical students with lower/no experience in performing open surgical procedures. The experiment aimed at simulating a cochlear implant surgery. Participants were asked to completely remove a blue colored rectangle (0.6 cm \u00d7 2.0 cm) from a piece of plywood using the instrumented drill (rotating at 15.000 rpm). Users wore the haptic ring on the left hand (see Fig. 3c), where a clear perception of the haptic feedback is allowed by the absence of vibrations. Participants were told that the task was considered successfully accomplished when the drilling force was maintained in a specific range, i.e. [0\u20137.5]N, without overreaching the limit time of 13 s. The time limit has been introduced to prevent subjects from being excessively slow in order to completely remove the blue color using low forces. Three feedback conditions were evaluated: i) no feedback (N); ii) vibratory (V) alert in case of exceeding the force threshold; iii) vibratory alert and cutaneous feedback proportional to the exerted force (C)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001671_O201325954480036.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001671_O201325954480036.pdf-Figure5-1.png", + "caption": "Fig. 5 Total deformations at structural analyses", + "texts": [ + " 1(b) \uac19\uace0 model 1\uc758 \uc808\uc810\uc218 \ubc0f \uc694\uc18c\uc218\ub294 \uac01\uac01 30416 \ubc0f 14716\uc774\uace0 model 2\uc758 \uc808\uc810\uc218 \ubc0f \uc694\uc218\ub294 \uac01\uac01 27577 \ubc0f 13161\uc774 \ub2e4. \uadf8\ub9ac\uace0 Table 2\ub294 Aluminum Alloy\uc758 \ubb3c\uc131\uce58\ub97c \ub098\ud0c0\ub0b8\ub2e4 [6] . 2.2 \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74 \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74\uc740 Fig. 2(a)\uc640 Fig. 3(a) \uac19\uc774 \ub098\uc0ac\uad6c\uba4d\uc744 \uc644\uc804 \ud788 \uace0\uc815\uc744 \uc2dc\ucf30\uc73c\uba70, Fig. 2(b)\uc640 Fig. 3(b)\uc5d0\uc11c\ub294 \ubc94\ud37c \uc55e\uc5d0 \ud798\uc744 Z+\ubc29\ud5a5\uc73c\ub85c \uc2e4\uc81c \ucda9\uaca9\uc5d0 \uc791\uc6a9\ub420 \uc218 \uc788\ub294 2500 N\uc758 \ud3c9\uade0\ud558\uc911\uc774 \uac00\ud558\uc600\ub2e4. \u2206\u2219 \u00d7 \u2219sec (1) \ub530\ub77c\uc11c \ucda9\uaca9\ub7c9\uc5d0 \uc758\ud558\uc5ec \uac00\ud574\uc9c0\ub294 \ucda9\uaca9\uc740 \u2219sec (2) 3. \ud574\uc11d\uacb0\uacfc 3.1 \uad6c\uc870\ud574\uc11d \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74\uc740 Fig. 2\uc640 Fig. 3 \uac19\uc73c\uba70, Fig. 4\uc640 Fig. 5\ub294 \ubc94 (a) Fixed support (b) Force condition \ud37c \uc55e\uc5d0 2500 N\uc758 \uc815\uc801 \ud798\uc744 \uac00\ud588\uc744 \ub54c \ub4f1\uac00\uc751\ub825\uacfc \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 4(a)\uc640 Fig. 4(b)\ub294 \ubc94\ud37c\uc758 \ub098\uc0ac\uad6c\uba4d\uc5d0\uc11c \ucd5c \ub300 \ub4f1\uac00\uc751\ub825\uc774 \uac01\uac01 187.09 MPa\uacfc 278.4 MPa\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 5(a)\uc640 Fig. 5(b)\ub294 \ubc94\ud37c \uc717\ubd80\ubd84\uc5d0\uc11c \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc73c\ub85c\uc11c \uac01\uac01 1.3772 mm\uc640 2.675 mm \ubcc0\ud615\ub41c \uac83\uc744 \uc54c \uc218\uac00 \uc788\ub2e4. \uc774 \uadf8\ub9bc\uc744 \ubcf4\uba74 Model 2\uc758 \ubcc0\ud615\ub7c9\uc774 Model 1\uc758 \ubcc0\ud615\ub7c9\ubcf4\ub2e4 \ub354 \ud06c\uae30 \ub54c\ubb38\uc5d0 Model 1\uc758 \uad6c\uc870\uac15\ub3c4\uac00 \ub354 \uc88b\ub2e4\uace0 \uc54c \uc218\uac00 \uc788\ub2e4 [7] . 3.2 \uc9c4\ub3d9 \ud574\uc11d \uc55e \ubc94\ud37c\uc758 \uace0\uc720\uc9c4\ub3d9\uc218\ub97c \uad6c\ud558\uae30 \uc704\ud574 \uc9c4\ub3d9 \ud574\uc11d\uc744 \uc218\ud589\ud558\uc600\uace0, Model 1\uacfc 2\uc5d0 \ub300\ud558\uc5ec \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Fig. 6\uacfc Fig. 7\uc5d0\uc11c \ubcfc \uc218 \uc788\ub2e4. \ub610\ud55c \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Table 3\uacfc Table 4\uc5d0\uc11c \ud655\uc778\ud560 \uc218 \uc788\uc73c\uba70, Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc5d0 \uc11c\uc758 \ucd5c\ub300 \uc804\ubcc0\ud615\ub7c9\uc740 62.671 mm\uc774\uace0 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc5d0\uc11c \uc758 \uc804\ubcc0\ud615\ub7c9\uc740 36.565 mm\ub85c\uc11c \ucd5c\ub300\uc758 \ubcc0\ud615\ub7c9\uc744 \ubcf4\uc774\uace0 \uc788\ub2e4. Model 1\uc758 4\ucc28\uc640 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc751\ub2f5\uc774 \uac00\uc7a5 \ud06c\ub2e4\uace0 \uc608\uce21\ud560 \uc218 \uc788\ub2e4. \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\ub97c Table 3\uacfc Table 4 \uc5d0\ub3c4 \ud655\uc778\ud560 \uc218 \uc788\uc73c\uba70, \ubcc0\ud615\uc774 \uc26c\uc6b0\uba70 \uacf5\uc9c4\uc774 \uc77c\uc5b4\ub0a0 \uac00\ub2a5\uc131\uc774 \ud070 \uac83\uc73c \ub85c \ubcf4\uc774\ub294 Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc758 \uc9c4\ub3d9\uc218\ub294 157" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004364_9312710_09358133.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004364_9312710_09358133.pdf-Figure14-1.png", + "caption": "FIGURE 14. The ship-based node used in experiments.", + "texts": [ + " The energy consumption of proposed node localization method is low, and the covertness of underwater mobile node is guaranteed. In the future, we will extend proposed TDoA-based node localization methods in an underwater positioning system with the dynamic topology of multiple surface beacons. Moreover, we will investigate the acoustic localization of underwater mobile nodes using single surface beacon.. APPENDIX A THE SHIP-BASED NODE USED IN THE EXPERIMENT The ship-based node used in the experiment is shown in Fig. 14. From Fig. 14, we observe that GPS antenna is deployed at the left side of ship, while the acoustic hydrophone tied with a CTD hangs at left of ship. From Fig. 14, we observe that recorded GPS positions are different from positions of acoustic hydrophone. To compensate position deviation between GPS module and acoustic hydrophone, we measured auxiliary range a and b, as shown in Fig. 15. The heading of ship, \u03b1, is recorded with GPS module. Let (xGPS , yGPS ) and (xhydro, yhydro) denote horizontal positions of GPS antenna and hydrophone, respectively. We have{ xhydro = xGPS \u2212 \u221a a2 + b2 cos(90\u2212 \u03b1 \u2212 \u03b2) yhydro = yGPS + \u221a a2 + b2 sin(90\u2212 \u03b1 \u2212 \u03b2) ,(A.1) where, \u03b2 = arctan b a " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.1-1.png", + "caption": "Figure 3.1: Revolving Vane Compressor with Bush Component", + "texts": [ + " The end design will have a cylinder with a short length so as to reduce the 25 chamber length but with a large diameter to accommodate the large working volume in the chambers. The preliminary design dimensions of the prototype are presented in Table 3.1 with a working volume of 50 cm3. number of rubbing components by two, design features in the prototype to implement low friction rubbing materials into the components and to select a suitable self-lubricating material for use in such components. In the design variant for the fixed vane RV compressor, a bush component is added to accommodate the movement of the vane within the rotor slot. Figure 3.1 shows a cross-section of the fixed vane RV compressor with the bush component. 26 The bush component is a simple and effective design that is able to accommodate the vane movement in the rotor slot while preventing leakage between the chambers. However, it is not without its disadvantages. The bush component presents an additional source of frictional loss and material wear while rotating in its slot and in addition, it imposes an additional constraint regarding the length of the vane; the length of vane in the slot must always extend past the centre of the bush at all times so as to hold the bush component in place \u2013 failure to do so would cause the bush to dislodge from its slot and jam the mechanism", + " With the new vane design, the RV mechanism now requires one less component and improved surface finishing is only needed for the rounded edges compared to the configuration with the bush component which required all the edges for all the components to be polished. In addition, the fillet also reduces the amount of dead volume in the compressor (as a ratio of total working volume) as shown in Figure 3.6. The fillet reduces the dead volume in the compressor by an average of approximately 20%. 29 Furthermore, the new vane and slot design has changed the geometric relationship between the cylinder and rotor. With the bush component, the centerline of the vane coincides at the edge of the rotor with the angle of swivel depicted by \u03b3 as shown in Figure 3.1 but for the new design, the tip of the vane now coincides with the slot centreline with the swivel angle represented by \u03b8v in Figure 3.5. The next section will go into the optimisation of these dimensions in order to minimise the amount of dead volume. First of all, the length of the vane has to be determined, which in turn dictates the depth of the slot. As the vane is required to be in contact at all times with the vane slot wall, the length of the vane has to be at least double the eccentricity of the cylinder and rotor and the slot length has to be even longer than the vane as it has to be able to accommodate the entire vane itself" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001876_41230-021-0125-8.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001876_41230-021-0125-8.pdf-Figure1-1.png", + "caption": "Fig. 1: Diagrams of single-phase one electrode monofilar (a) and bifilar (b), three-phase multielectrode monofilar (c) and three-phase bifilar (d) of ESR (1- consumable electrode, 2- molten slag, 3- molten pool, 4- solidified ingot, 5- water-cooled mould, 6- water-cooled base plate, 7- power source)", + "texts": [ + " 2 State of the art Today, the most common energy supply system is the three-phase system with sinusoidal EMFs of the same frequency shifted in phase by a certain angle, which ensures the efficiency of electric power transmission and the possibility of creating a rotating magnetic field, and at the same time, three-phase system makes possible the work of motors (synchronous, asynchronous and linear), and other electrical devices. Moreover, most metallurgical workshops are connected mainly to the three-phase grid worldwide. However, historically, the first commercial ESR furnace was built in the former USSR by process inventors Academicians Paton and Borys Medovar [1] with one consumable electrode and fed by single-phase alternating current supplied by a special transformer from a three-phase electric network. Starting from the ESR process invention, the single-phase monofilar diagram of power supply [Fig. 1(a)] was, and still is, the most widespread for the ESR furnaces. Single electrode configuration provides a high filling ratio, which could reach 0.6-0.7 (ratio of cross-section area). This feature has two consequences: positive - at greater filling ratio it is possible to melt with lower rate and the depth of the liquid metal pool is less; and negative - the production of high-quality electrodes of a large cross-section is difficult and expensive. Otherwise, the ESR ingot substantially inherits segregation from the consumable electrode. The monofilar connections of many smaller electrodes are also the way, but more welding work would increase the cost. The ESR under monofilar connection [Fig. 1(a)] alternating current mostly runs in the circuit: transformer - high current loop - consumable electrode - molten slag - growing ingot - bottom plate - high current loop - transformer. At the monofilar connection, there are two long parts (upper and lower lines) of high current loop carrying the same load. Each part of the high current loop of the monofilar furnace must ensure the passage of large current, which requires the use of large sections of copper busbars and water cooling of the cables to avoid their heating and connected losses", + " At the single-phase load, the cos\u03c6 is usually increased by introducing a capacitance or additional variable resistance to compensate for the inductance but the losses of electric energy are unavoidable. Modern, powerful ESR furnaces would produce a lot of harmonics and flickers in the supplying network. Therefore, the high power compensating devices are in use for the ESR furnace to reduce a disturbance to the network. From the very beginning, Chinese engineers have realized this problem and have started to use three-phase ESR furnaces, which reduce the side effects of single-phase load inherent to the monofilar ESR furnaces in the supplying three-phase network. Figure 1 schematically shows the diagram of single-phase monofilar [Fig. 1(a)] and bifilar [Fig. 1(b)] furnaces and threephase multi-electrode monofilar [Fig. 1(c)] and bifilar [Fig. 1(d)] furnaces, which were simulated and compared in this study. Bifilar configuration for ESR furnace power supply, as shown in Figs. 1(b) and (d), provides a shorter connection of high current loop via molten slag between electrodes: \u201ctransformer - one consumable electrode - liquid slag bath slag - second consumable electrode - transformer\u201d. In some cases, current can go through the liquid metal bath coming from and going back to the slag bath. The eventual current load in the circuit \u201celectrode - slag - mould - bottom plate - ingot - slag - second electrode\u201d appears at imbalance in bifilar pairs only (imbalance arises at the great difference in electrical resistivity between electrodes in the bifilar pair)", + " This phenomenon is one of the reasons inhibiting the widespread use of bifilar furnaces, but it is possible to overcome using a separate motor for each electrode. Another inhibition is the difficulties in designing the electrodes change and gas protection using the close chamber. The three-phase monofilar ESR furnace having three consumable electrodes connected to each phase is easier to be realized and controlled. In this case, the upper part of the high current loop is more complicated than at the single-phase monofilar and in the lower part - the same this variant has. The electric current here is also going through the whole ingot [as shown in Fig. 1(a) for analogous single-phase monofilar increasing a depth of the liquid metal (factor of ingots quality)] [2]. There are several recent articles discussing the results of simulation of magneto dynamic and heat processes for bifilar and multielectrode ESR. Researchers [3] have made a simulation of a three-phase ESR furnace using a proprietary ESR3D program to enmesh the solid model for a 80-120 t ingot and related equipment. The calculation results were of assistance in optimizing the ESR process to produce a large ingot that satisfied nuclear industry requirements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003337_f_version_1677642889-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003337_f_version_1677642889-Figure6-1.png", + "caption": "Figure 6. (a) FE model of space membrane deployable mechanism. (b) Zoomed-in view of the STEM. (c) Tensions and fixed support.", + "texts": [ + " According to these material and geometric parameters, the total mass of all the cables Mc is only related to the cable tension F and the membrane thickness t by substituting Equations (6), (7), (14) and (15) into Equation (18), as shown in the following equation. Mc = 0.0013F + 0.015t (19) Substituting the parameters mentioned above into Equation (17), Mm can be obtained as Mm = 0.373t (20) In summary, Equation (16) can be rewritten as M = 0.0013F + 0.388t + 32.54 (21) In simulation software ANSYS, the FE model of space membrane deployable mechanisms, including booms, cables and membrane, is established based on the aforementioned configuration design, as shown in Figure 6. The geometric parameters and material properties of the membrane mechanism are consistent with those mentioned in the previous section, and the latter is summarized and listed in Table 2. Thus, there are four unspecified parameters, respectively: mechanism height h, cable tension F, boom thickness \u03b4 and membrane thickness t, the parametric studies of which are carried out in the subsequent section. Here, only the case of h = 0.6 m, F = 30 N, \u03b4 = 0.50 mm and t = 25 \u00b5m is taken as an example to illustrate the FE modeling method", + " In the simulation, the membrane is modeled with Shell181 element, the booms are modeled with Beam 188 element and various cables are modeled with Link10 element. Considering the mesh convergence and simulation accuracy, a mesh of 9409 elements is adopted to model the whole mechanism. Bonded contact is adopted to model the attachment between the booms, cables and membrane. The root of the deployable booms is a fixed constraint, and the cable tension of 30 N is applied to the cables, as depicted in Figure 6c. Thus, the mode shape and frequency of the membrane mechanism can be analyzed, and the results are illustrated in Figure 7 with a fundamental frequency of 0.1302 Hz. To achieve noncontact measurement, the Polytec laser vibrometer is selected to measure the mode shape and frequency of the model membrane mechanism by scanning it with the laser camera, as shown in Figure 8. During the test, the Polytec controller controls the vibrator through the power amplifier to provide controllable excitation for the test frame, which drives the membrane mechanism vibration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.2-1.png", + "caption": "Figure 3.2: Bulbous Vane Design", + "texts": [ + " The bush component presents an additional source of frictional loss and material wear while rotating in its slot and in addition, it imposes an additional constraint regarding the length of the vane; the length of vane in the slot must always extend past the centre of the bush at all times so as to hold the bush component in place \u2013 failure to do so would cause the bush to dislodge from its slot and jam the mechanism. Hence, it would best to redesign the vane slot such that no bush component is required. Adahan [100] proposed a bulbous rounded end for the vane with a straight vane slot for a single-vane rotary pump patent. Application of this vane design to the RV mechanism is shown in Figure 3.2. The illustrated vane design allows proper operation of the compressor while eliminating the bush component. However, this introduces volumetric losses into the compressor due to the presence of dead volume highlighted in Figure 3.2. The amount of dead volume as a consequence of this design is shown in Figure 3.3 as a percentage of the total working volume. It is noted that at maximum, the amount of dead volume is approximately 2% of the total working volume. 27 Further improvements are made to the bulbous vane to mitigate the amount of dead volume in the design \u2013 a fillet is added to the sides of the vane to reduce the dead volume. In addition, as the angle of the vane swivel is fixed during compressor operation, the entire rounded edge of the bulbous end will not be fully utilised and can be removed as well" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureB.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureB.10-1.png", + "caption": "Figure B.10: ISR Hand, thin element embedded on a rubber joint [19].", + "texts": [ + " Furthermore, a comparison with an FEM package was done and differences in the reaction forces between testing and computational model were 8% for a deflection of 90 degrees. With a \u03c3y/E \u2248 17, it is expected that plastic deformation is present for that deflection. However, stresses were not presented in the publication. Deflections in other directions and the weight of the hand were not reported as they were not part of the presented requirements. B.3 Endoskeleton Structures B.3.1 University of Coimbra - ISR Hand The ISR Hand of the University of Coimbra used the urethane joints concept of the SDM Hand [19], see Fig. B.10. The importance of improving the compliance on the undesired directions was reported. For this reason a leafspring was integrated inside of the soft material. The hybrid approach led to increased stiffness in all directions compared to only the urethane joint. Calculations of the joint deflections of the rigid leafspring, in the actuation direction and in-plane bending, were made by traditional beam theory equations, which are only valid for small deflections. Reported weight: 530 g. B.3.2 University of Coimbra - UC Hand Later, the University of Coimbra presented a new prosthetic hand named the UC Hand [20]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000681_230-1-PB.pdf_id_6201-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000681_230-1-PB.pdf_id_6201-Figure2-1.png", + "caption": "Fig. 2. Flow rates and pressures at the servovalve", + "texts": [ + " 1b shows an option using high volumetric expansion (HVE) hoses between the servovalve and cylinder. The use of accumulators instead of hoses could also be possible for similar purposes. Two mathematical models are explained in this section: a nonlinear model, which is used for simulation in order to obtain force responses; and a linear model, used for the controller design and hose sizing. Both models are based on Fig. 1b. 2.1 Nonlinear Modelling of the Hydraulic System 2.1.1 Servovalve Modelling In the design of the hydraulic circuit, a symmetrical servovalve is used (Fig. 2) [22]. The dynamic relationship between the input control signal (UC) and the spool displacement, represented by an equivalent voltage (UCsp), can be approximated by a secondorder function: U U t U t UC nv Csp v nv Csp Csp d d d d = + + 1 2 2 2 2\u03c9 \u03be \u03c9 , (1) where \u03c9nv is the natural frequency of the valve and \u03bev represents the damping ratio of the valve. The flow rate through the valve, including the effects of internal leakage can be described by the 581Force Control of Hydraulic Actuators using Additional Hydraulic Compliance following equations [23], where a control signal range of \u201310 V to +10 V is assumed: \u2022 for UCsp \u2265 0: q K U U K p p K p pv v v vA p Csp Cn inp S A inp A T= + \u2212 \u2212 \u2212 , (2) q K U U K p p K p pv v v vB p Csp Cn inp B T inp S B= + \u2212 \u2212 \u2212 , (3) \u2022 for UCsp < 0: q K U U Kv p p K p p v v v v A p Csp Cn inp A T inp S A = \u2212 + \u2212 + \u2212 , (4) q K U U K p p K p p v v v v B p Csp Cn inp S B inp B T = \u2212 + \u2212 + \u2212 , (5) where qvA and qvB are the flow rates at ports A and B, respectively; pA and pB are the pressures in lines A and B, respectively; pS and pT represent the supply and the reservoir pressures, respectively; UCn is the nominal control signal" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001671_O201325954480036.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001671_O201325954480036.pdf-Figure4-1.png", + "caption": "Fig. 4 Equivalent stresses at structural analyses", + "texts": [ + " \ud574\uc11d \ub300\uc0c1\uc758 \uba54\uc2dc \ubaa8\uc591\uc740 Fig. 1(a)\uacfc Fig. 1(b) \uac19\uace0 model 1\uc758 \uc808\uc810\uc218 \ubc0f \uc694\uc18c\uc218\ub294 \uac01\uac01 30416 \ubc0f 14716\uc774\uace0 model 2\uc758 \uc808\uc810\uc218 \ubc0f \uc694\uc218\ub294 \uac01\uac01 27577 \ubc0f 13161\uc774 \ub2e4. \uadf8\ub9ac\uace0 Table 2\ub294 Aluminum Alloy\uc758 \ubb3c\uc131\uce58\ub97c \ub098\ud0c0\ub0b8\ub2e4 [6] . 2.2 \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74 \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74\uc740 Fig. 2(a)\uc640 Fig. 3(a) \uac19\uc774 \ub098\uc0ac\uad6c\uba4d\uc744 \uc644\uc804 \ud788 \uace0\uc815\uc744 \uc2dc\ucf30\uc73c\uba70, Fig. 2(b)\uc640 Fig. 3(b)\uc5d0\uc11c\ub294 \ubc94\ud37c \uc55e\uc5d0 \ud798\uc744 Z+\ubc29\ud5a5\uc73c\ub85c \uc2e4\uc81c \ucda9\uaca9\uc5d0 \uc791\uc6a9\ub420 \uc218 \uc788\ub294 2500 N\uc758 \ud3c9\uade0\ud558\uc911\uc774 \uac00\ud558\uc600\ub2e4. \u2206\u2219 \u00d7 \u2219sec (1) \ub530\ub77c\uc11c \ucda9\uaca9\ub7c9\uc5d0 \uc758\ud558\uc5ec \uac00\ud574\uc9c0\ub294 \ucda9\uaca9\uc740 \u2219sec (2) 3. \ud574\uc11d\uacb0\uacfc 3.1 \uad6c\uc870\ud574\uc11d \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74\uc740 Fig. 2\uc640 Fig. 3 \uac19\uc73c\uba70, Fig. 4\uc640 Fig. 5\ub294 \ubc94 (a) Fixed support (b) Force condition \ud37c \uc55e\uc5d0 2500 N\uc758 \uc815\uc801 \ud798\uc744 \uac00\ud588\uc744 \ub54c \ub4f1\uac00\uc751\ub825\uacfc \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 4(a)\uc640 Fig. 4(b)\ub294 \ubc94\ud37c\uc758 \ub098\uc0ac\uad6c\uba4d\uc5d0\uc11c \ucd5c \ub300 \ub4f1\uac00\uc751\ub825\uc774 \uac01\uac01 187.09 MPa\uacfc 278.4 MPa\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 5(a)\uc640 Fig. 5(b)\ub294 \ubc94\ud37c \uc717\ubd80\ubd84\uc5d0\uc11c \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc73c\ub85c\uc11c \uac01\uac01 1.3772 mm\uc640 2.675 mm \ubcc0\ud615\ub41c \uac83\uc744 \uc54c \uc218\uac00 \uc788\ub2e4. \uc774 \uadf8\ub9bc\uc744 \ubcf4\uba74 Model 2\uc758 \ubcc0\ud615\ub7c9\uc774 Model 1\uc758 \ubcc0\ud615\ub7c9\ubcf4\ub2e4 \ub354 \ud06c\uae30 \ub54c\ubb38\uc5d0 Model 1\uc758 \uad6c\uc870\uac15\ub3c4\uac00 \ub354 \uc88b\ub2e4\uace0 \uc54c \uc218\uac00 \uc788\ub2e4 [7] . 3.2 \uc9c4\ub3d9 \ud574\uc11d \uc55e \ubc94\ud37c\uc758 \uace0\uc720\uc9c4\ub3d9\uc218\ub97c \uad6c\ud558\uae30 \uc704\ud574 \uc9c4\ub3d9 \ud574\uc11d\uc744 \uc218\ud589\ud558\uc600\uace0, Model 1\uacfc 2\uc5d0 \ub300\ud558\uc5ec \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Fig. 6\uacfc Fig. 7\uc5d0\uc11c \ubcfc \uc218 \uc788\ub2e4. \ub610\ud55c \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Table 3\uacfc Table 4\uc5d0\uc11c \ud655\uc778\ud560 \uc218 \uc788\uc73c\uba70, Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc5d0 \uc11c\uc758 \ucd5c\ub300 \uc804\ubcc0\ud615\ub7c9\uc740 62.671 mm\uc774\uace0 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc5d0\uc11c \uc758 \uc804\ubcc0\ud615\ub7c9\uc740 36.565 mm\ub85c\uc11c \ucd5c\ub300\uc758 \ubcc0\ud615\ub7c9\uc744 \ubcf4\uc774\uace0 \uc788\ub2e4. Model 1\uc758 4\ucc28\uc640 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc751\ub2f5\uc774 \uac00\uc7a5 \ud06c\ub2e4\uace0 \uc608\uce21\ud560 \uc218 \uc788\ub2e4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004591_3239-020-00466-y.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004591_3239-020-00466-y.pdf-Figure2-1.png", + "caption": "FIGURE 2. Schematic presentation of the rotational angles of the grafts and the respective distances to the IJ.", + "texts": [ + " We were unable to implement a program controlled variation of the distance because we used a physiological anatomy, which is complex, skewed, and tortuous. Therefore, the location of the intersection of graft and CIV would vary, which led to the termination of the simulations either because of a faulty, or a failed connection of the CIV and the graft. In each of the four setups, the rotational angles were restricted either by the opposing CIV or graft and therefore, the limits had to be established individually. The different setups and the corresponding distances and ranges of the rotational angles are shown in Table 1. Figure 2 provides a schematic depiction of the rotational angles of the grafts and the respective distances to the IJ. The first part of the numerical study was designed to investigate the influence of the different parameters. Therefore, 20 design points were created for each of the chosen setups using Optimal-Space-Filling-Design (Ansys 19.0, ANSYS, Inc., Canonsburg, PA). This function facilitates the generation of sensibly distributed configurations for optimal parameter correlation. Subsequently, CFD simulations were performed for all created design points" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000266__titds2023_05005.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000266__titds2023_05005.pdf-Figure4-1.png", + "caption": "Fig. 4. Calculation scheme of forces acting on the undercarriage: Ms - sprung mass of the machine, g - free fall acceleration, Pi - elastic suspension force reduced to the i-th track roller, T1 - force acting in the front branch of the bypass, T2 - force acting in the rear branch of the bypass, Ss1 and Ss2 are the shoulders of the moments of the caterpillar tension forces relative to the center of the sprung mass, n is the number of road wheels on board, Js is the moment of inertia of the sprung mass.", + "texts": [ + " Most of the values depend on the strokes of the road wheels, which are defined as follows [21]: ( )\u03c6 ,i ok if z L (12) where \u0394z is the vertical displacement of the center of the sprung masses of the TTV, \u0394\u03c6 is the angle of rotation of the longitudinal axis of the hull passing through the center of the sprung mass. The calculation scheme for determining the position of the hull, taking into account the tension forces of the caterpillars (for the undercarriage with the rear drive wheel) is shown in Figure 4. The body of the machine is in equilibrium if the following condition is satisfied: 1 1 2 2 1 ( ) 1 1 2 2 1 sin \u03b3 sin \u03b3 0, 5 0 \u03c6 0 n i s s i n i ok i s s s i P \u0422 \u0422 M g M z P L \u0422 S \u0422 S J (13) Otherwise, the body tends to take an equilibrium position with accelerations \u03c6= , s s P Mz and M J (14) If the values of the sum of forces \u0394\u0420 and the sum of moments \u0394\u041c are not equal to zero, then we eliminate the resulting mismatch by moving the body along the height z and the angle of inclination \u03c6, as a result of which we find the increment of the suspension strokes of the i\u2013th rollers, new values of the strokes fi and new values of elastic forces Pi, etc" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004394_j_29_9_29_9_857__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004394_j_29_9_29_9_857__pdf-Figure4-1.png", + "caption": "Fig. 4 Virtual Line and relative errors", + "texts": [ + " 4\u306b\u793a\u3059\u3088\u3046\u306b\uff0c\u8eca\u4e21\u306e\u5f8c\u8f2a\u8ef8\u4e2d\u5fc3\u304b\u3089\u5730\u9762\u306b\u4e0b \u308d\u3057\u305f\u5782\u7dda\u3068\u5730\u9762\u3068\u306e\u4ea4\u70b9\u3092\u539f\u70b9\u3068\u3057\uff0c\u8eca\u4e21\u306e\u524d\u5411\u304d\u306b xv \u8ef8\uff0c \u5de6\u5411\u304d\u306b yv \u8ef8\u3092\u3068\u308b\u3088\u3046\u306a\u8eca\u4e21\u5ea7\u6a19\u7cfb O\u2013xvyv \u3092\u8003\u3048\u308b\uff0e\u305f \u3060\u3057\uff0c\u5730\u9762\u306f\u5e73\u9762\u3067\u3042\u308b\u3068\u3057\uff0cxwyw \u5e73\u9762\u3068 xvyv \u5e73\u9762\u306f\u540c\u4e00 \u5e73\u9762\u4e0a\u306b\u3042\u308b\uff0e\u5730\u9762\u4e0a\u306b\u56fa\u5b9a\u3055\u308c\u3066\u3044\u308b\u76ee\u6a19\u70b9\u3092 Pt \u3068\u3057\uff0c\u30ef\u30fc \u30eb\u30c9\u5ea7\u6a19\u7cfb Ow\u2013xwyw \u306b\u304a\u3051\u308b\u5ea7\u6a19\u3092 [xr, yr] T \u3068\u3059\u308b\uff0e\u4ee5\u4e0b \u3067\u306f\uff0c\u3059\u3079\u3066\u306e\u904b\u52d5\u306f\u3053\u306e\u5e73\u9762\u4e0a\u3067\u8d77\u3053\u3063\u3066\u3044\u308b\u3082\u306e\u3068\u3059\u308b\uff0e \u70b9 Pt \u3092\u901a\u308a\uff0c\u70b9 O \u3068\u70b9 Pt \u3092\u7d50\u3076\u7dda\u5206\u306b\u76f4\u4ea4\u3059\u308b\u4eee\u60f3\u7684 \u306a\u76f4\u7dda\u3092\u5c0e\u5165\u3059\u308b\uff0e\u3053\u306e\u3068\u304d\uff0c\u76ee\u6a19\u72b6\u614b\u3059\u306a\u308f\u3061\u76ee\u6a19\u70b9 Pt \u3092 \u4e2d\u5fc3\u3068\u3059\u308b\u4e00\u5b9a\u534a\u5f84\u306e\u5186\u8ecc\u9053\u4e0a\u3092\u8d70\u884c\u3059\u308b\u3053\u3068\u306f\uff0c\u8eca\u4e21\u5ea7\u6a19\u7cfb O\u2013xvyv \u306b\u304a\u3044\u3066\uff0c\u3053\u306e\u4eee\u60f3\u7684\u306a\u76f4\u7dda\u3092 xv \u8ef8\u306b\u5e73\u884c\u306b\uff0c\u304b\u3064 \u539f\u70b9\u3068\u306e\u8ddd\u96e2\u3092\u4e00\u5b9a\u306b\u4fdd\u3064\u3053\u3068\u3068\u306a\u308b\uff0e\u3053\u306e\u4eee\u60f3\u7684\u306a\u76f4\u7dda\u3092\u76f4 \u7dda A \u3068\u3059\u308b\uff0e\u76f4\u7dda A \u304c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306b\u3088\u308a\u753b\u50cf\u5e73\u9762\u4e0a\u306b\u6295\u5f71 \u3055\u308c\u305f\u66f2\u7dda\u3092 B\u2032 \u3068\u3059\u308b\uff0e\u3053\u3053\u3067\uff0c\u66f2\u7dda B\u2032 \u306f\u5f0f\uff0814\uff09\u3067\u8868\u3055\u308c \u308b\u4e8c\u6b21\u66f2\u7dda\u3067\u3042\u308b\u3068\u3059\u308b\uff0e\u3055\u3089\u306b\uff0c\u753b\u50cf\u5ea7\u6a19\u7cfb\u3067\u306e Pt \u306e\u5c04\u5f71 \u70b9 (Xt, Yt) \u306b\u304a\u3051\u308b\u66f2\u7dda B\u2032 \u306e\u63a5\u7dda\u3092\u76f4\u7dda A\u2032 \u3068\u3059\u308b\uff0e\u3053\u306e\u3068 \u304d\uff0c\u5168\u65b9\u4f4d\u30ab\u30e1\u30e9\u306e\u6027\u8cea\u3088\u308a\uff0c\u8eca\u4e21\u5ea7\u6a19\u7cfb\u306b\u304a\u3051\u308b\u76f4\u7dda A \u3068\u753b \u50cf\u5ea7\u6a19\u7cfb\u306b\u304a\u3051\u308b\u76f4\u7dda A\u2032 \u306e\u65b9\u5411\u306f\u4e00\u81f4\u3059\u308b\uff08Fig. 5\uff0c6\uff09\uff0e\u3053 \u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 29 \u5dfb 9 \u53f7 \u2014103\u2014 2011 \u5e74 11 \u6708 \u308c\u3089\u306e\u3053\u3068\u304b\u3089\uff0c\u753b\u50cf\u5ea7\u6a19\u7cfb\u3067\u306e\u76ee\u6a19\u72b6\u614b\u306f\u76f4\u7ddaA\u2032 \u3092\u753b\u50cf\u5ea7 \u6a19\u7cfb\u306e X \u8ef8\u306b\u5e73\u884c\u306b\uff0c\u304b\u3064\u539f\u70b9\u3068\u306e\u8ddd\u96e2\u3092\u4e00\u5b9a\u306b\u4fdd\u3064\u3053\u3068\u3068 \u306a\u308b\uff0e \u3053\u3053\u3067\uff0c\u73fe\u5728\u306e\u76f4\u7dda\u3068\u76ee\u6a19\u76f4\u7dda\u3068\u306e\u524d\u5f8c\u65b9\u5411\uff0c\u6a2a\u65b9\u5411\uff0c\u89d2\u5ea6 \u65b9\u5411\u306e\u76f8\u5bfe\u8aa4\u5dee\u3092\u305d\u308c\u305e\u308c \u0394x\uff0c\u0394y\uff0c\u0394\u03b8 \u3068\u3059\u308b\uff0e\u0394y\uff0c\u0394\u03b8 \u306f Fig. 4 \u306e\u3088\u3046\u306b\u3068\u308b\uff0e\u4eee\u60f3\u7684\u306a\u76f4\u7dda A \u3068\u30ef\u30fc\u30eb\u30c9\u5ea7\u6a19\u7cfb\u306e xw \u8ef8\u3068\u306e\u89d2\u5ea6\u3092 \u03b8r\uff0c\u76f4\u7dda\u306e\u56de\u8ee2\u901f\u5ea6\u3092 \u03c9r \u3068\u3059\u308b\u3068\uff0c\u5404\u76f8\u5bfe\u8aa4\u5dee \u306b\u3064\u3044\u3066\u4ee5\u4e0b\u304c\u6210\u308a\u7acb\u3064\uff0e \u0394x = (x \u2212 xr) cos \u03b8r + (y \u2212 yr) sin \u03b8r \u0394y = \u2212 (x \u2212 xr) sin \u03b8r + (y \u2212 yr) cos \u03b8r \u0394\u03b8 = \u03b8 \u2212 \u03b8r \uff0815\uff09 \u307e\u305f\uff0c\u3053\u306e\u6642\u9593\u5fae\u5206\u306f\u4ee5\u4e0b\u3068\u306a\u308b\uff0e d dt \u0394x = v cos \u0394\u03b8 \u2212 vr + \u0394y\u03c9r d dt \u0394y = \u2212\u0394x\u03c9r + v sin \u0394\u03b8 d dt \u0394\u03b8 = \u03c9 \u2212 \u03c9r \uff0816\uff09 \u3053\u3053\u3067\uff0c x\u0307 = v cos \u03b8 x\u0307r = vr cos \u03b8r y\u0307 = v sin \u03b8 y\u0307r = vr sin \u03b8r \uff0817\uff09 \u3068\u3044\u3046\u95a2\u4fc2\u3092\u7528\u3044\u3066\u304a\u308a\uff0cv \u306f\u8eca\u4e21\u306e\u901f\u5ea6\uff0cvr \u306f\u76ee\u6a19\u70b9\u306e\u901f\u5ea6 \u3067\u3042\u308b\uff0e \u3068\u3053\u308d\u3067\uff0c\u76ee\u6a19\u70b9\u306f\u30ef\u30fc\u30eb\u30c9\u5ea7\u6a19\u7cfb\u306b\u56fa\u5b9a\u3055\u308c\u3066\u3044\u308b\u305f\u3081 vr = 0 \u3067\u3042\u308b\uff0e\u307e\u305f\uff0c\u76ee\u6a19\u70b9\u304b\u3089\u898b\u3066\u5e38\u306b\u76f4\u7dda\u3068\u5782\u76f4\u306a\u65b9\u5411\u306b \u8eca\u4e21\u304c\u3042\u308b\uff0c\u3059\u306a\u308f\u3061\u524d\u5f8c\u65b9\u5411\u306e\u76f8\u5bfe\u8aa4\u5dee \u0394x = 0 \u304a\u3088\u3073\u6642\u9593 \u5fae\u5206 d/dt\u0394x = 0 \u3068\u306a\u308b\u305f\u3081\u306b\uff0c\u5f0f\uff0816\uff09\u3088\u308a wr \u306f\u6b21\u5f0f\u306e\u3088 \u3046\u306b\u5b9a\u307e\u308b\uff0e \u03c9r = \u2212v cos \u0394\u03b8 \u0394y \uff0818\uff09 \u4e00\u65b9\uff0c\u524d\u7ae0\u3067\u793a\u3057\u305f u\uff0cn\uff0cB3\uff0cB4 \u306f\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u8868\u3055\u308c \u308b [7]\uff0e u = 2 64 cos \u0394\u03b8 sin \u0394\u03b8 0 3 75 n = 2 64 h sin \u0394\u03b8 h cos \u0394\u03b8 \u2212\u0394y 3 75 B3 = \u2212h sin \u0394\u03b8 \u0394y B4 = \u2212h cos \u0394\u03b8 \u0394y \uff0819\uff09 \u3053\u3053\u3067\uff0ch \u306f\u30ab\u30e1\u30e9\u306e\u5730\u4e0a\u304b\u3089\u306e\u9ad8\u3055\u306b\u76f8\u5f53\u3059\u308b\u30d1\u30e9\u30e1\u30fc\u30bf\u3067 \u3042\u308b\uff0e\u5f0f\uff0819\uff09\u306e\u7b2c 3\u5f0f\uff0c\u7b2c 4\u5f0f\u3088\u308a\u6b21\u5f0f\u304c\u6210\u308a\u7acb\u3064\uff0e \u0394y = hp B2 3 + B2 4 \uff0820\uff09 \u0394\u03b8 = tan\u22121 B3 B4 \uff0821\uff09 \u307e\u305f\uff0c\u5f0f\uff0819\uff09\u306e B3\uff0cB4 \u3092\u6642\u9593\u306b\u95a2\u3057\u3066\u5fae\u5206\u3059\u308b\u3068\u5f0f\uff0816\uff09 \u3088\u308a\u6b21\u306e\u72b6\u614b\u65b9\u7a0b\u5f0f\u304c\u5c0e\u304b\u308c\u308b\uff0e d dt \" B3 B4 # = \" v h B2 3 \u2212 B4\u03c9r v h B3B4 + B3\u03c9r # + \" B4 \u2212B3 # \u03c9 \uff0822\uff09 \u3053\u3053\u3067\uff0c\u5f0f\uff0818\uff09\uff0c\uff0819\uff09\u3088\u308a\uff0c \u03c9r = v h B4 \uff0823\uff09 \u3068\u306a\u308a\uff0c\u72b6\u614b\u65b9\u7a0b\u5f0f\u306f\u6700\u7d42\u7684\u306b\u6b21\u5f0f\u3068\u306a\u308b\uff0e d dt \" B3 B4 # = v h \" B2 3 \u2212 B2 4 2B3B4 # + \" B4 \u2212B3 # \u03c9 \uff0824\uff09 \u3053\u3053\u3067\uff0c\u671b\u307e\u3057\u3044\u65cb\u56de\u534a\u5f84\u3092 \u0394y\u2217 \u3068\u3059\u308b\u3068\uff0c\u5148\u306e\u76ee\u6a19\u72b6\u614b\u306b \u95a2\u3059\u308b\u8b70\u8ad6\u3088\u308a\u5236\u5fa1\u76ee\u6a19\u306f\uff0c \u0394\u03b8 \u2192 0 \u0394y \u2192 \u0394y\u2217 \uff0825\uff09 \u3067\u3042\u308b\u304b\u3089\uff0c\u5f0f\uff0819\uff09\u3088\u308a\u753b\u50cf\u5e73\u9762\u4e0a\u306e\u76ee\u6a19\u306f\u6b21\u306e\u3088\u3046\u306b\u306a\u308b\uff0e B3 \u2192 0 B4 \u2192 B\u2217 4 = \u2212 h \u0394y\u2217 \uff0826\uff09 \u5b9a\u7406 1 \u30b7\u30b9\u30c6\u30e0\uff0822\uff09\u306b\u5bfe\u3057\u3066\u5236\u5fa1\u5165\u529b \u03c9 = \u2212 1 B\u2217 4 \u201c kB3 + v h ` B2 3 + B2 4 \u2212 2B4B \u2217 4 \u00b4\u201d \uff0827\uff09 \u3092\u9078\u3076\u3068\uff0cB3 \u2192 0, B4 \u2192 B\u2217 4 (t \u2192 \u221e) \u304c\u9054\u6210\u3055\u308c\u308b\uff0e \u8a3c\u660e \u30ea\u30a2\u30d7\u30ce\u30d5\u95a2\u6570\u306e\u5019\u88dc\u3068\u3057\u3066\u6b21\u5f0f\u3092\u8003\u3048\u308b\uff0e V = 1 2 B2 3 + 1 2 (B4 \u2212 B\u2217 4 ) 2 \uff0828\uff09 \u3053\u308c\u3092\u6642\u9593\u306b\u95a2\u3057\u3066\u5fae\u5206\u3059\u308b\u3068\uff0c V\u0307 = v h B3 ` B2 3 + B2 4 \u2212 2B4B \u2217 4 \u00b4 + B3B \u2217 4\u03c9 \uff0829\uff09 \u3068\u306a\u308b\uff0e\u3053\u3053\u3067\uff0c\u5236\u5fa1\u5165\u529b\u3068\u3057\u3066\u5f0f\uff0827\uff09\u3092\u9078\u3076\u3068\u5f0f\uff0829\uff09\u306f\uff0c V\u0307 = \u2212kB2 3 \u2264 0 \uff0830\uff09 \u3068\u306a\u308b\uff0e\u3053\u3053\u3067\uff0ck \u306f\u4efb\u610f\u306e\u6b63\u6570\u30b2\u30a4\u30f3\u3067\u3042\u308b\uff0eV\u0307 \u304c\u6709\u754c\u304b \u3064 V\u0308 \u304c\u4e00\u69d8\u9023\u7d9a\u3067\u3042\u308b\u3053\u3068\u304b\u3089\uff0cBarbalat\u2019s lemma [10]\u3088\u308a V\u0307 \u2192 0 (t \u2192 \u221e) \u3068\u306a\u308a\uff0c\u5f0f\uff0830\uff09\u3088\u308a\uff0cB3 \u2192 0 (t \u2192 \u221e) \u3068 \u306a\u308b\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u5f0f\uff0827\uff09\u3088\u308a\uff0c lim t\u2192\u221e \u03c9 = \u2212 v hB\u2217 4 ` B2 4 \u2212 2B4B \u2217 4 \u00b4 \uff0831\uff09 \u3068\u306a\u308b\uff0eB3 \u2192 0 (t \u2192 \u221e) , B\u03073 \u2192 0 (t \u2192 \u221e) \u3068\u306a\u308b\u3053\u3068\u3068\uff0c \u5f0f\uff0824\uff09\uff0c\uff0831\uff09\u304b\u3089\uff0c lim t\u2192\u221e B\u03073 = \u2212 v h B2 4 + B4 \u201e \u2212 v hB\u2217 4 ` B2 4 \u2212 2B4B \u2217 4 \u00b4\u00ab = v h B2 4 \u201e 1 \u2212 B4 B\u2217 4 \u00ab = 0 \uff0832\uff09 \u5b9a\u7fa9\u3088\u308aB4 = 0\u3067\u3042\u308b\u304b\u3089\uff0c\u5f0f\uff0832\uff09\u3088\u308a B4 \u2192 B\u2217 4 (t \u2192 \u221e) \u3068\u306a\u308a\uff0cB3\uff0cB4 \u304c\u305d\u308c\u305e\u308c\u76ee\u6a19\u5024\u306b\u53ce\u675f\u3059\u308b\uff0e\u306a\u304a\uff0cB3\uff0cB4 \u304c\u6709\u754c\u3067\u3042\u308b\u3053\u3068\u304b\u3089\uff0c\u5f0f\uff0820\uff09\u3088\u308a \u0394y = 0 \u3068\u306a\u3089\u306a\u3044\uff0e JRSJ Vol" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004038__1_1_article-p26.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004038__1_1_article-p26.pdf-Figure1-1.png", + "caption": "Fig. 1. Functional elements of a high-power low-speed engine at risk of explosion or fire", + "texts": [ + " A conceptual design of a prototype of a non-invasive, new generation leak detector for starting valves and its technical design have been presented. Exemplary implementations of the prototype detector have been shown and its selected functionalities have been discussed. This paper has ended with an assessment of the possibility of further development and the applications of this device. Keywords: explosion protection, leakage detector for starting valves, machine diagnostics, engine explosions, active monitoring system The operation of modern high-power combustion engines is inevitably associated with the risk of fire or explosion. In Figure 1, the example of a slow-running engine has shown that there is a hazard present in practically the entire engine environment, and it refers to, among other things, explosions in the crankcases (Chybowski et al, 2015), turbocharger explosions (Chybowski and Matuszak, 2007), fires in the flushing air reservoirs and piston spaces (Strojecki, 2011), fires in the exhaust manifolds (Chmura, 2012) and fires resulting from leaks of flammable substances (Bistrovi\u0107 and Ristov, 2017; Gawdzi\u0144ska et al., 2015; Kwieci\u0144ska, 2015)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003418_ice_Designed_for.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003418_ice_Designed_for.pdf-Figure2-1.png", + "caption": "Figure 2. Principle of determining the tensile force with a rope sensor", + "texts": [ + " [4], measuring the tensile force in the rope using the principle of bending deformation of the beam loaded with single force, see Figure 1. This device uses bodies with a measuring member and three contact points in a plane. The measured rope runs between these points. The two outside contact points on the device body, located at a known distance apart, serve as support of the measured rope. The third contact point is located at the midpoint distance of the pitch of the two outside contact points, which is distanced by the h value [m] from the axes intersection of the outside contact points, se Figure 2. Due to the acting tensile force T [N] in the rope, a compressive force F [N] is then exerted on the third contact point, see the relation (1), which is recorded by the measuring sensor. ( )F = 2. T. sin [N]\u03b1 (1) According to Figure 2, the following dependencies can be determined between the relevant parameters: = arctg(d/b) = arctg [(h + 2. R. cos)/(a - 2. R.sin)] d = h + 2. c = h + 2. R. cos [m] c = R. cos [m] b = a - 2. e = a - 2. R. sin [m] e = R. sin [m] (2) Obtaining the value of the tensile force in the carrier rope using a rope sensor, see Figure 1, is a commonly used method, however, it has certain limitations and drawbacks. Under certain circumstances, the basic limitation is the way of obtaining tensile force values in the individual ropes of rope suspensions that use a higher number of ropes", + " When the cage is moving within the elevator shaft, then the carrier ropes and thus also the rope sensors, which are mechanically attached to the cross- sections of the ropes, are in motion as well. The actual value of the tensile force acting on the rope axis is not directly measured by the rope sensor, it is determined proportionally from the normal force exerted, i.e. the force perpendicular to the rope axis. This normal force is a resultant of the components of the acting tensile forces in inclined sections of the measured rope, see Figure 2, and acts on the central contact member of the rope sensor. The actual value of the tensile force in the rope must therefore be determined by the comparative method. The accuracy of determining the actual tensile force in the rope is affected by the reshaping (deformation) of the rope sensor body and depends on the angle of inclination of the rope section and the distance of the gripping points of all contact points. The above mentioned limitations and drawbacks can be eliminated using the device for offsetting tensile forces in elevator ropes described below" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureB.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureB.8-1.png", + "caption": "Figure B.8: Leafspring design and PRB model [2].", + "texts": [], + "surrounding_texts": [ + "The flexure joints are optimized in the actuation direction with interest in an ellipsis compliance in the contact point. However, the publications did not show special attention for the compliance in the unwanted direction and the influence in the load-carrying capacity.\nReported weight: 400 g. [76].\nB.2.5 University of Wollongong [1]\nResearchers presented a flexure-based finger aimed for prosthetic applications. It consisted of three notch joints.\nThree conceptual notch designs were presented: a leafspring with round corners; a circular notch; and, an elliptical notch (Fig. B.7). The thickness (3 mm) and length of all elements was constant for all hinges.\nThe study is based on the compliance in the actuation direction. A Finite Element Analysis and validation were done with 5% relative error in the displacements of the end effector.\nPage 39", + "However, analysis on the stresses were not presented. The selected material was an elastomer, which makes sense for that thickness and the large range of motion.\nHysteresis was shown in flexion-extension of the finger, and it was attributed to material hysteresis and friction in the channels of the tendon.\nB.2.6 Ohio State University [2]\nFor soft joints, the compliance in the elongation direction becomes important. An adapted PRBM with an additional constant spring to model the elongation deformation was included.\nThe modified PRBM allows a better track of the tip of the finger than conventional PRBM or even the 3R PRBM [77], which is suited for large deformations.\nHowever, this model only takes into consideration flexion and extension of the finger. The PRBMs consider the joints to be constraint in the other directions, and these loads can be important when considering compliant grasping hands.\nB.2.7 Tennessee Technical University [3]\nTennessee Technical University presented three type of flexure-based fingers for robotic applications. A monolithic 3D printed finger design was studied, and comparisons between Fused Deposition Modelling (FDM) materials were done.\nPage 40", + "An empirical flexion extension testing was conducted. The joints were deflected up to 184 degrees, for which they encountered plastic deformation. The Cross-Leafspring was selected because it presented less plastic deformations.\nFurthermore, a comparison with an FEM package was done and differences in the reaction forces between testing and computational model were 8% for a deflection of 90 degrees. With a \u03c3y/E \u2248 17, it is expected that plastic deformation is present for that deflection. However, stresses were not presented in the publication.\nDeflections in other directions and the weight of the hand were not reported as they were not part of the presented requirements.\nB.3 Endoskeleton Structures\nB.3.1 University of Coimbra - ISR Hand\nThe ISR Hand of the University of Coimbra used the urethane joints concept of the SDM Hand [19], see Fig. B.10. The importance of improving the compliance on the undesired directions was reported. For this reason a leafspring was integrated inside of the soft material.\nThe hybrid approach led to increased stiffness in all directions compared to only the urethane joint. Calculations of the joint deflections of the rigid leafspring, in the actuation direction and in-plane bending, were made by traditional beam theory equations, which are only valid for small deflections. Reported weight: 530 g.\nB.3.2 University of Coimbra - UC Hand\nLater, the University of Coimbra presented a new prosthetic hand named the UC Hand [20]. Their design was an evolution of the previous ISR hand.\nFig. B.11 shows a 3D printed mold used to cast the silicon on a 3D printed endoskeleton. The objective was to offer a compliant finger with a soft contact able to deform into the shape of the graspable object.\nThe new wire flexure endoskeleton structure offers one degree of freedom more than the previous leafspring structure by releasing in-plane bending. This structure should be less beneficial for the support stiffness than the presented in the ISR Hand.\nRecent studies of the University of Coimbra have focused on the understanding of the flexure-based joints [21], several designs are presented in Fig. B.12.\nComparisons between the original curved leafspring design used in the ISR Hand, Fig. B.12a, and several topologies were made. A non-linear Finite Element Analysis\nPage 41" + ] + }, + { + "image_filename": "designv8_17_0000074_8948470_09035441.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000074_8948470_09035441.pdf-Figure10-1.png", + "caption": "FIGURE 10. Temperature field distribution.", + "texts": [ + " In order to obtain a uniform temperature distribution, two schemes are designed, analyzed and compared in the following. Figure 9 shows the geometry structure of micro-channel heat sinks. The cross section of the micro-channel heat sink is rectangle. The length, width and height of the inlet header and outlet header are 40 mm, 2.2 mm and 0.8 mm, respectively. The length, width and height of the small micro-channel are 36 mm, 1mm and 0.6 mm, respectively. The detailed VOLUME 8, 2020 52363 dimensions of the optimized parameters in Fig. 10 are as follows (unit: mm): l0 = 36, l1 = 8, l2 = 3, l3 = 40, b1 = 2.2, b2 = 1. Numerical simulations are conducted to obtain the temperature fields of two schemes for the microchannel heat sinks. Tables III and IV give the material properties and boundary conditions required by the simulation software ANSYS CFX. Figure 10 presents the temperature field distributions of structurally integrated active antenna. It can be observed from Fig. 10 that the temperature scope is from 48.04\u25e6C to 60.17\u25e6C. Table 5 gives the statistical results of the temperature distributions on the surface of the RF layer. It also provides the standard deviation of the temperature andmaximum temperature difference, which quantitatively evaluate the uniformity of the temperature distribution with and without heat sinks. The small deviation of the temperature and maximum temperature difference will cause smaller amplitude and phase variations of the radiating element excitations, which can provide a stable antenna electrical performance" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001212_f_version_1605160399-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001212_f_version_1605160399-Figure4-1.png", + "caption": "Figure 4. Stress distribution and sectional view ABCD at the strain of 3%: (a,b) the cell of specimen HT, (c,d) the cell of specimen HTSJ, and (e,f) the cell of specimen HTSW.", + "texts": [ + " In order to reveal the reason for the differences in compressive properties of the specimens, LS-DYNA was employed to describe the compressive behavior [27]. Finite element models of unit cells for specimens HT, HTSJ, and HTSW were established, and the elastic-plastic material model was applied to describe the behavior of matrix material. The parameters are as follows: density \u03c1 = 4.35 g/cm3, elastic modulus E = 110 GPa, yield strength \u03c3y = 1080 MPa, and Poisson\u2019s ratio \u00b5 = 0.3. The cells were loaded from the top surface to bottom surface at a fixed strain rate of 10\u22123 s\u22121. Figure 4 shows Materials 2020, 13, 5094 8 of 14 the stress distribution of cells and sectional views. It can be seen that the stress concentration of the cells for specimens HT and the HTSJ mainly occurs in the struts along the loading direction, while the stress concentration of the cell for specimen HTSW appears at the joint region. The sectional views clearly show the internal geometry of the different cells and the stress concentration regions are very close to structural weaknesses parallel to the loading direction, as shown in Figure 4b,d,f. It should be noted that the internal microstructures of specimen HTSW reinforce the structural weakness of hollow struts, while the internal microstructures of specimen HTSJ strengthen the non-weak regions of hollow struts. Stress-strain curves of the different cells were extracted from the numerical simulation as shown in Figure 5, and the results show that the compressive stresses were all increased with the addition of microstructures inside the cells. Thus, it can be concluded that adding different internal microstructures changes the structural weaknesses of the original cells and leads to the different bearing capacities of the cells" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001612_jassp.2016.73.79.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001612_jassp.2016.73.79.pdf-Figure2-1.png", + "caption": "Fig. 2. Diagrammatic representation of oblique view of transversely cut ovipositor (Ko et al., 2011)", + "texts": [ + " In planning low-dose brachytherapy delivery and positioning of radioactive seeds according to the preoperative dosimetric plan is one of the most important stages of the procedure. Therefore, the relationship between the needle design and the method of its motion in the tissue influences the significance of tissue damage, the ability to avoid obstacles along a curvilinear path and positioning accuracy of the seeds. Ko et al. (2011) developed a flexible probe potentially capable of threedimensional steering in soft tissue inspired by natureovipositor of a Giant Ichneumon wasp (Fig. 2). In experimental studies such needles were moved with different levels of bias (Fig. 3). Positioning accuracy of the needle tip was 0.68\u00b11.45 mm. Swaney et al. (2013) proposed to improve the controllability of a needle and to increase the curvature of the trajectory by giving a degree of freedom to asymmetrical tip of the needle placing nitinol wires along the needle (Fig. 4). A degree of freedom of the tip allows increasing the angle of deviation, therefore increasing maneuverability of the needle and its controllability resulting in potentially less tissue damage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002140_5-lajss-15-5-e71.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002140_5-lajss-15-5-e71.pdf-Figure2-1.png", + "caption": "Figure 2: Force analysis during impact condition.", + "texts": [ + " (2008): ( )2 03 1 / 4K e v = \u2212 (4) In above equation, e and 0v are the coefficient of restitution and initial impact velocity in the normal direction, re- spectively. Assuming the sliding motion along concave surface between two bodies, the friction force is considered as Latin American Journal of Solids and Structures, 2018, 15(5), e71 4/21 t nF F= , where is the friction coefficient. Note that during contact, two main forces, namely normal force ( )nF perpendicular to conical surface and tangential force ( )tF along the cone\u2019s wall will be simultaneously acted upon both satellites, as depicted in Figure 2. Based on Eq. (1), the function of intrusion should be evaluated to obtain impact force. To determine this, the dis- tance from point A to definite line BC is measured in each time step and negative values of intrusion during solving procedure present the relative penetration depth between two bodies. As illustrated in Figure 2, the aim of capture process is to adjust the parameters of buffer for passing the spherical tip mass through center of line BE. Keep in mind that improper set of buffer coefficients leads to rebounding motion between two vehicles and then, unsuccessful capture mission. To formulate a wide range of mechanical problem from very simple to very complex, multibody dynamics tool can be used where a collection of bodies may undergo relative motion with respect to each other. Accurate configuration of such systems is better described by arranging coordinate frames in the suitable position of each component", + " Now, consider a point specified by ( )1 2, , ,i i kq q q= r r in an arbitrary global coordinate frame, on which the im- pact force F may be exerted in multibody system during impact. With regard to the virtual work principle, the general- ized force related to coordinate jq can be obtained by: ( )/j i i jQ q= F r (10) The position vector for tip mass of probe in global frame is written as follows: cos cos sin sin S S C S S C u a h h v a h h + + = + + r (11) In which, h presents the distance between tip mass of probe and revolute pair in each time step of numerical solution. Based on Figure 2, the force vector F acted on the chaser at the point of contact (point A) is simply obtained as: ( ) ( ) ( ) ( ) sin cos . cos sin n T t T n T t T F F F F \u2212 + \u2212 + = + \u2212 + F (12) Similarly, the vector of impact position together with the vector of force exerted on the target can be easily written. Because our aim is to adjust the parameters of buffer for the purpose of successful capture process, the dynamic behavior of each satellite after impact should be essentially investigated" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004126_ists29_12_Pc_15__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004126_ists29_12_Pc_15__pdf-Figure8-1.png", + "caption": "Fig. 8. Analysis model of flat rib-stiffened shell antenna.", + "texts": [ + " At first, the simultaneous optimum design of the structure and the actuators is investigated for the flat rib-stiffened shell antenna by using the design optimization method examined in Section 3. Then, the experimental specimen is manufactured based on the results of the design optimization, and the feasibility of the optimum design is examined. 5.1. Optimum design for flat rib-stiffened shell antenna The optimum design of the flat rib-stiffened shell antenna is examined by using the design optimization method indicated in Section 3. Figure 8 shows the analysis model for the flat rib-stiffened shell antenna. The center of the antenna is clamped. On the other hand, the boundary condition 2, which is indicated in Section 3.1., is not considered to simplify the experimental setup. In addition, it is difficult to manufacture the shell which has the thickness distribution, and hence, the distribution of the shell thickness is not included in the design parameter of the optimization. The angle of the actuator is also difficult to setup. Based on the above description, the design variables, the constraints, and the nominal design for the optimization are indicated in Table 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002037_s-4400047_latest.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002037_s-4400047_latest.pdf-Figure4-1.png", + "caption": "Figure 4. (a) Schematic diagram of the DNN model. Comparison between the predicted curve and the target curve of wideband absorber (b) high-frequency (c) full-band.", + "texts": [ + " In previous work, the optimization of multiple structural parameters and target performances of THz metamaterial absorber was carried out using optimization algorithms and commercial 3D full-wave simulation software, which consumed considerable time and computational resources. Therefore, inspired by traditional neural networks, deep learning models, and genetic algorithms24-26, this paper introduces a DNN to optimize the proposed metamaterial absorber to achieve excellent absorption rates (Abr) under different operational states. The DNN model in this paper consists of three layers: Layers 1 to 3 have 64, 48, and 24 neurons, respectively, as shown in Fig. 4(a). This study obtained a total of 17,652 datasets from CST simulation results, which include combinations of structural parameters (SPs) and Abr. Of these, 12,356 are used for the training set, 3530 for the validation set, and 1766 for the test set. Python and the PyCharm framework were used to create the model, and the Adam optimizer was used for the optimization algorithm. The training process took a total of 783.43 s, with the Mean Absolute Error (MAE) and Root Mean Square Error (RMSE) being 0", + " By comparing the amplitude of the target curves with the predicted curves at these 90 frequency points, the more alignment points there are, the closer the parameters are to their optimal values. For a clearer comparison, we manually selected three datasets from several predicted output datasets. The structural parameters corresponding to the predicted curves are shown in Table 2. For all three predicted cases, high absorption rates were achieved within the wideband range, validating the effectiveness of our proposed DNN. Among these, Predicted_2 and Predicted_3 had higher errors than Predicted_1 (Fig. 4(b), (c)). Finally, considering bandwidth, intensity, and manufacturing factors, the Predicted_1 dataset was selected as the optimal structural parameters. Fig. 5 presents the absorption spectra of the absorber across different VO2 states. The absorption curves represented by wideband red and blue lines, correspond to VO2 in its metallic and insulating phases, respectively, when the Fermi level of graphene is set at 1 eV. Notably, in the insulating phase of VO2, a high-frequency wideband ranging from 9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001062_125_3_125_3_293__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001062_125_3_125_3_293__pdf-Figure2-1.png", + "caption": "Fig. 2. Magnetic structure and dimension of the usual model.", + "texts": [ + "2 3-D Finite Element Analysis The fundamental equation of the magnetic field using the 3-D finite element method can be written using the magnetic vector potential A as follows: rot (\u03bdrot A) = J0 + \u03bd0rot M \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (3) where \u03bd is the reluctivity, \u03bd0 is the reluctivity of the vacuum, M is the magnetization of the permanent magnet and J0 is the current density. 3. Analyzed Models and Results 3.1 Usual Electromagnetic Reset Switch Figure 1 shows a basic construction of a usual rocker switch with the electromagnetic reset function. It mainly consists of the electromagnetic structure, reset springs, electric contact part and handle. Figure 2 shows its detail magnetic structure. This model consists of the armature which contains two magnetic poles equipped with a permanent magnet, and the stator \u96fb\u5b66\u8ad6 D\uff0c125 \u5dfb 3 \u53f7\uff0c2005 \u5e74 293 which has a coil wound around its leg. This figure shows the situation when the switch is turned on, and the armature is pulled towards the stator and kept closed only by the attractive force of the permanent magnet. The residual magnetic flux density Br of this ferrite magnet is 0.42 T. The exciting coil has 2420 turns and its resistance is 160\u2126", + " Consequently, it becomes very important to design an efficient magnetic path for the magnetic flux excited by the current. The following attractive force ratio, R, is defined here as the ratio of the non-excitation attractive force to the 100 A excited attractive force in order to evaluate the efficiency of the magnetic structure. The ratio R of this model was observed 294 IEEJ Trans. IA, Vol.125, No.3, 2005 Novel Electromagnetic Structure for Reset Switch to be relatively low (R = 1.4). 3.2 Improved Model Figure 6 shows the enlarged view of the armature when the usual model in Figure 2 is observed from X-direction. This improved model is considered to be effective in increasing the magnetic flux excited by the current. The length of the two bypass cores L is extended to the inside of the armature so the magnetic flux excited by the current can return to the stator without flowing through the permanent magnet. Figure 7 shows the calculated results of the attractive force characteristics and the ratio R when the length L of the bypass cores is changed from 1.6 to 3.8 mm. It was observed that as the length of the bypass increases, the magnetic flux that flows through the bypass cores increases when the coil is not excited" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000095_cle_download_406_813-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000095_cle_download_406_813-Figure6-1.png", + "caption": "Fig. 6. Plant bed recommended settings for the proposed carrot seeder design", + "texts": [ + " The materials were also reconciled with its availability in the local market and the ease of fabrication especially in local settings where fabricators do not have access to precision fabrication laboratory. The criteria to measure the degree of success of the design is presented in Table 3. This includes the dropping efficiency, coefficient of variation, seeding capacity, and driving force. The plant bed has to be thoroughly prepared, free from clods and stones for optimum performance of the seeder [12]. There are some parts (Fig. 6.) of the plant beds that need to be prepared mainly in accordance to the dimension of the seeder. The dimensions are also critical to match the working size of the seeder. Plant bed height has to be 12.0 cm and top width is 50.0 cm. A clearance between the plant bed and the wheels is also necessary to avoid the wheels from scraping the side of the plant bed that can affect the stability of the seeder. This clearance should be at least 5 to 8 cm. Plant bed canal is also important and should be spacious enough to allow the wheels to freely pass through and the operator as well" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-Figure7-1.png", + "caption": "Fig. 7. Comparison of optimized hinge topologies over the range of motion while loaded with a sideways force Fz = \u22122 N.", + "texts": [ + " Page 20 The Angled Three-Flexure Cross Hinge presents a behavior that is close to linear without inflection points. Furthermore, it is of interest to analyze the behavior of the hinges under the weight of the grasped object. The sideways stiffness Ksw is the inverse ratio of a measured displacement dz at the contact point and an applied load Fz. See Fig. 2. Ksw is affected by the translational compliance in z and rotational compliances: Ksw = Fz dz (6) The behavior of Ksw over the range of motion is presented in Fig. 7. A tendon force was applied to deflect the flexure joint to an specific angle. At that deflection, a load Fz = \u22122 N was applied, and a Ksw was calculated as described in equation (6). In the optimization, while the grasping force was part of the cost function, the sideways stiffness was treated as a soft constraint. The Hole Cross Hinge outperformed over most of the range of motion, with a drop of support stiffness of only 28.7% (Fig. 7). This behavior matches with the high \u03c3max/\u03c3flex ratio from Fig. 6. It suggests a hinge with high stiffness in all directions. The Leafspring performed the second best for deflections beyond \u22125\u25e6 with a peak at \u221215\u25e6. This behavior is related to the off-centric load produced by the weight of the object being held. By analyzing the dashed lined from Fig. 8 it can be observed that, at \u221215\u25e6, that the torsional component is almost not present. The same behavior was Fig. 8. On the left, leafspring in undeflected state", + " Although, the infill of the parts is 25%, as reported by Pot, in the notch hinges 60% of the thickness have full infill. The experimental stiffness was used in equation C.1 for determining the stiffness of the finger. Effects such as creep and relaxation of the polymer are expected. However, the stiffness of the parallel guidance was measured with a difference of 3 months and a difference within 1% was found. C.1.3 Improvements The mechanisms designed by Pot to attach the finger, in both ends, are presented in Fig. 7, Section C.1.5. The base clamp and the interface between the finger and the parallel guidance were suggested as improvement points at the end of his report. Failure under high loads and lack of stiffness were found. The clamping in both ends of the finger relied in friction and clamping power to keep the finger in position. Furthermore, the alignment of the finger was not guaranteed and repetitive measurements were either. A redesign was done considering that additional interfaces could be print in the finger" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004537_d_1_download_id_3578-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004537_d_1_download_id_3578-Figure8-1.png", + "caption": "Figure 8: AM-AM and AM-PM performances of microwave power amplifiers. \u2206G is a compressed gain and \u2206\u03c6 is an insertion phase variation, that is, a phase distortion", + "texts": [ + " Before the distortion analysis, AM-AM and AM-PM performances have to be represented by behavioral modeling for high speed and high accurate calculation. Behavioral modeling is listed in Table 2 [11]. The traditional distortion analysis of microwave power amplifiers deals with polynomial regression such as power series or Volterra series [1] because harmonic contents are easily handled. Thus , polynomial regression is employed here as behavioral modeling for representing AM-AM (Pout vs Pin) and AM-PM (\u2206\u03c6 vs Pin) performances shown in Figure 8. Based on the AM-AM (Pout vs Pin) and AM-PM (\u2206\u03c6 vs Pin) performances of Figure 7, the 3rd polynomial equations are calculated, which are shown in (9) and (10). Pin and Pout are denoted as antilog value. \u2206\u03c6 is given as degree. (9) (10) The calculated AM-AM and AM-PM performances shown in Figure 7 are also demonstrated in Figure 9 in conjunction with behavioral modeling. A good agreement has been achieved between the calculated and modeled data. This load-line analysis software prepares two types of 2-tone analyses: 2-tone power series analysis for weak nonlinearity and 2-tone envelope analysis for strong nonlinearity [1]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000760_advpub_21006173__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000760_advpub_21006173__pdf-Figure3-1.png", + "caption": "Fig. 3. Interior Permanent Magnet Synchronous Motor", + "texts": [ + "1 Magnetic Equivalent Circuit To estimate the magnet operating point, the magnetic flux density of permanent magnet must be calculated. In this paper, the magnetic equivalent circuit, MEC, which allows the calculation of magnetic flux in real-time, is used thanks to the advantage of less computation than the finite elements analysis, FEA (17). The magnetic equivalent circuit consists of the magnetic resistances and the magneto-motive forces, MMF. IPMSM has been selected for verifying the proposed method as shown in Fig. 3 and the proposed magnetic equivalent circuit is shown in Fig. 4. Each value is calculated as following equations. l A = ........................................................................ (1) m e mF H l= ....................................................................... (2) wF N i= .................................................................... (3) where \u211c is the magnetic resistance, \ud835\udf07 is the magnetic permeability, \ud835\udc34 is the area and \ud835\udc59 is the length of the material, \ud835\udc39\ud835\udc5a is the MMF of the magnet, \ud835\udc3b\ud835\udc52 is the coercive force of the magnet, \ud835\udc59\ud835\udc5a is the length of the magnet, \ud835\udc39\ud835\udc64 is the MMF by the flowing current to the armature winding, \ud835\udc41 is the number of winding turns per the teeth, \ud835\udc56 is the instantaneous current" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001401__downloads_tb09j677c-Figure4.20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001401__downloads_tb09j677c-Figure4.20-1.png", + "caption": "Figure 4.20: Images of antenna structure with a) only port 1 dipole and ground plane and b) only single bow-tie and ground plane.", + "texts": [ + " Circle represents 1.3 GHz and square represents 2.4 GHz. . 42 Figure 4.17 Modal a) conductance and b) susceptance for FEKO single bow-tie structure. The legend is the same for both plots. . . . . . . . 43 Figure 4.18 Auxiliary modal admittance on Smith chart for single bow-tie. Circle represents 1.3 GHz and square represents 2.4 GHz. . . . . . . . 46 Figure 4.19 Auxiliary modal a) conductance and b) susceptance for single bow-tie. The legend is the same for both plots. . . . . . . . . . . . . . 47 Figure 4.20 Images of antenna structure with a) only port 1 dipole and ground plane and b) only single bow-tie and ground plane. . . . . . . 48 Figure 4.21 Auxiliary eigenvalues for the crossed bow-tie structure compared to auxiliary eigenvalues for the structure with only bow-tie and ground plane and for the structure with only dipole and ground plane. 49 ix TCM Theory of Characteristic Modes CMT Coupled Mode Theory CMA Characteristic Mode Analysis MIMO Multiple-input Multiple-output CM Characteristic Mode CA Characteristic Attribute EFIE Electric Field Integral Equation MoM Method of Moments PEC Perfect Electric Conductor CCE Capacitive Coupling Element ICE Inductive Coupling Element GNSS Global Navigation Satellite System AR Axial Ratio PCV Phase Center Variation x \u03c9 angular frequency, rad/s f frequency, Hz \u03bb wavelength, m H magnetic field intensity, A/m E electric field intensity, V/m J surface current density, A/m2 Jn eigencurrent or characteristic current, A/m2 \u03bbn eigenvalue \u03b4mn Kronecker delta We electric energy, J Wm magnetic energy, J MSn modal significance \u03b1n characteristic angle, \u00b0 an modal weighting coefficient V i n modal excitation coefficient Yin input admittance, S Yn modal admittance, S Gn modal conductance, S Bn modal susceptance, S K, G coupling coefficient \u0393 reflection coefficient xi Chapter 1 Antennas are present everywhere around us", + " The coupling due to eigenvalue crossing avoidances was discussed extensively throughout this chapter. The other type of coupling where coupling characteristic modes exhibit an in-phase and anti-phase characteristic in the charge distribution was discussed by Borchardt and LaPointe in [14], [15] and [30]. This in-phase and anti-phase relationship is a phenomenon that was shown in section 4.2.2 to be occurring in the eigencurrents on the dipole and bow-tie conductors. In an effort to understand this coupling, two structures, shown in Fig. 4.20, are analyzed using CMA in CST Studio. The structure in Fig. 4.20(a) consists of the port 1 dipole and the ground plane. The structure in Fig. 4.20(b) consists of the two triangular elements parallel to the port 1 dipole and the ground plane. In both structures, either the dipole or bow-tie is not present such that the analysis of each structure shows the decoupled response of the conductor that is present. The auxiliary eigenvalues relating to the two structures in Fig. 4.20 are compared to the auxiliary eigenvalues of the crossed bow-tie structure in Fig. 4.21. The eigenvalues with the subscript dipole are obtained from the structure in Fig. 4.20(a) and the eigenvalues with the subscript bowtie are obtained from the structure in Fig. 4.20(b). All other eigenvalues are from the crossed bow-tie structure and are the same as those in Fig. 4.11. The auxiliary eigenvalue, \u03bba, is identical between structures because it corresponds to the ground plane which is the same for every structure. In Fig. 4.13, this mode was shown to be the same as the first mode in a circular sheet. Since the eigenvalue for CMa a19,a111 does not change even if different conductors are placed above the circular ground plane, the mode can be stated as being decoupled" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004232_f_version_1608773898-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004232_f_version_1608773898-Figure6-1.png", + "caption": "Figure 6. Fingertip force diagram, for a tension, applied to the Lateral Artificial Tendon (LAT).", + "texts": [ + " For the EAT we have that: \ud835\udeff , EAT = \ud835\udc43 , \ud835\udc43 + \ud835\udc43 , \ud835\udc43 (1) \ud835\udeff , EAT = \ud835\udc43 , \ud835\udc43 + \ud835\udc43 , \ud835\udc43 + \u2113(\ud835\udf03 + \ud835\udf03 ) (2) \ud835\udeff , EAT = \u2113(\ud835\udf03 + \ud835\udf03 ) (3) For the palmar artificial tendon, we have: \ud835\udeff , PAT = \ud835\udc43 , \ud835\udc43 (4) PAT in an arbitrary position is given by the cosine law: \ud835\udeff , PAT = (\ud835\udc43 , \ud835\udc43\ud835\udea5 ) + (\ud835\udc43\ud835\udea5 , \ud835\udc43 ) \u2212 2(\ud835\udc43 , \ud835\udc43\ud835\udea5 )(\ud835\udc43\ud835\udea5 , \ud835\udc43 ) cos(\ud835\udf0b \u2212 \ud835\udf03 ) (5) \ud835\udeff , PAT = |\ud835\udeff , PAT \u2212 \ud835\udeff , PAT| (6) The same procedure is applied on LAT analysis: \ud835\udeff , LAT = \ud835\udc43 , \ud835\udc43 + \ud835\udc43 , \ud835\udc43 + \ud835\udc43 , \ud835\udc43 (7) \ud835\udeff , LAT = \ud835\udc43, \ud835\udc58 + \ud835\udc58, \ud835\udc43 \u2212 2 \ud835\udc43, \ud835\udc58 \ud835\udc58, \ud835\udc43 cos(\ud835\udf0b \u2212 \ud835\udf03 ) (8) For (i, j, k) \u2208 \u03b6; \u03b6 = {(3, 3, MCP), (4, 2, PIP), (5, 1, DIP)}. \ud835\udeff , LAT = |\ud835\udeff , LAT \u2212 \ud835\udeff , LAT| (9) Although the MCP angular movement which is given by PAT communicates this one to the other phalanges, this resultant force is negligible. The resultant force will be provided by LAT wire tension, being perpendicular at the phalanx surface. ?\u20d7? is shown in Figure 5 and it is a function of theta (\u03b81) angle. The fingertip force (?\u20d7?) is represented in Figure 6. To determine the fingertip force, \u03b2 must be written as a function of \u03b81. \ud835\udefd = sin \ud835\udc50\ud835\udc4e(\ud835\udf03 ) sin(\ud835\udf03 ) (10) ?\u20d7? = \ud835\udc47cos \ud835\udf0b 2 \u2212 \ud835\udefd (11) Equation (10) is provided by law of sines. As previously discussed, the parameters b and c (see Figure 6) are obtained through direct measurement and the wire length between P5 and P6 is a function of theta (a(\u03b81)). The result reveals that the ring position impacts on the force optimization resulting from the system. To optimize the fingertip force, we should pay attention to the kinematic coefficient alpha (\u03b1) given by ( ) in the Equation (10). The resulted force will be higher for lower a(\u03b81). Thus, to reduce a(\u03b81) is necessary to reduce b and increase c as much as possible. To represent this effect graphically (Figure 7) we plot Equations (10) and (11) merge them, with a(\u03b81) equal to the last term of Equation (8) replaced. These substitutions provide the plot equation of the Figure 7, Equation (12). ?\u20d7? = \ud835\udc47cos \u239d\u239b\ud835\udf0b 2 \u2212 sin \u23a3\u23a2\u23a2 \u23a1 \ud835\udc50(\ud835\udc43 , \ud835\udc37\ud835\udc3c\ud835\udc43) + (\ud835\udc37\ud835\udc3c\ud835\udc43, \ud835\udc43 ) \u2212 2(\ud835\udc43 , \ud835\udc37\ud835\udc3c\ud835\udc43)(\ud835\udc37\ud835\udc3c\ud835\udc43, \ud835\udc43 ) cos(\ud835\udf0b \u2212 \ud835\udf03 ) sin(\ud835\udf03 )\u23a6\u23a5\u23a5 \u23a4 \u23a0\u239e (12) The graph was built considering \ud835\udc47 = 80 \ud835\udc41 and \u03b8 \u2208 [0, \ud835\udf0b 2] which is the range of a healthy dip phalanx [18]. The blue curve represents \u03b11 given by b = 0.5 mm and c = 1.5 mm (b and c are shown in Figure 6) having P6 close to the DIP and P5 close to PIP joint. The orange curve has the parameters swapped, representing \u03b12 with b = 1.5 mm and c = 0.5 mm. In this paper, we presented a novel concept for hand orthosis, based on a soft exoskeleton approach for assistance in physiotherapy sessions and DLA for people with hand disabilities. The concept considered the biological constraints stimulating the natural tendons to comply with angular constraints. The proposed design allows for smooth coordination for the hands while giving power assistance to grasp objects and execute tasks" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002932_8821491_09069248.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002932_8821491_09069248.pdf-Figure6-1.png", + "caption": "FIGURE 6. (a): 3D model of the TLT in exploded view; (b): Photo of the implemented TLT.", + "texts": [ + "2 MHz. fL can thus be reasonably chosen to be around 1 MHz, which results in a minimum required L\u03bc of about 2 \u03bcH. The characteristic impedance is chosen to be the geometric mean of the high-side and low-side impedances: Z0 = \u221a ZHIZLO, which ensures proper termination of the lines and maximizes the TLT bandwidth [35]\u2013[37]. This design targets a 50 desired input impedance, resulting in ZHI = 50 , ZLO = 12.5 , and Z0 = 25 . The 2:1 Guanella TLT was implemented in a binocular structure as shown in Fig. 6(a) and 6(b). Each transmission line was implemented as a 25 RG141 coax cable enclosed in a series-stack of 14 toroid cores (Fair Rite 61 material, part #: 5961001901). This implementation results in a calculated L\u03bc of about 2.1 \u03bcH. The cores were selected to provide the required common-mode inductance while keeping core losses to a minimum. This loss arises due the common-mode voltage across L\u03bc of the top transmission line of Fig. 5(a) driving flux inside the cores. By inspecting Fig. 5(a), it can be seen that the common-mode voltage is half of the input voltage", + " At a worst-case input power of about 2.5 kW (with a 50 match), this voltage peaks at about 250 V, which results in about 6.5 W of core loss. (By contrast, the grounding scheme used in the proposed design imposes zero common-mode voltage on the bottom transmission line, and no core losses in the associated cores; we employ the second set of cores only to allow the use of other grounding schemes if so desired). 130 VOLUME 1, 2020 To manage the thermal dissipation at this worst-case power, a cooling structure was built as shown in Fig. 6(a) and 6(b). The Aluminum heat spreaders were machined to fit directly on the TLT structure to effectively absorb the heat generated from core loss. The two small PCBs shown were used to make the series and parallel connections of the transmission lines. The outer Aluminum bracket serves both as a mounting structure, as well as a ground connection for the TLT\u2019s input and output terminals. The implemented TLT was tested prior to its use in the full TMN system. With 50 connected to its primary side, the secondary impedance was measured as 12" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure13-1.png", + "caption": "Figure 13. Thermal field distribution under condition of water cooling used in the casing and axial forced air when both the SM and the DRM are running at the rated speed and rated load.", + "texts": [ + " Since the heat dissipation capacity of stator end windings are poorer than that of the windings in the core, the temperature of the stator end windings is higher than that of the windings in the core. However, the heat dissipation capacity of inner rotor windings in the core is poor for the inner rotor windings, so the temperature of inner rotor windings in the core is higher than that of end windings. When both the SM and the DRM are running at the rated speed and rated load, the 3-D thermal field distribution is calculated under condition of water cooling used in the casing and axial forced air, as shown in Figure 13. the windward side, middle cross-section, and the leeward side of the CS-PMSM are shown in Figure 14. In order to eliminate the effects of end face boundary conditions, the selected windward and leeward cross-sections are 2.5 mm away from the corresponding end face, respectively. The highest temperature of different parts in the above three cross-sections is shown in Table 7. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 7. From the temperature distribution of each cross-section in Table 7, it can be seen that the temperatures of the stator and inner rotor are very low, indicating that the axial force air have a good cooling effect on the CS-PMSM, especially for the inner rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000668__imane2017_06024.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000668__imane2017_06024.pdf-Figure1-1.png", + "caption": "Fig. 1. Parts made with (ordered) tree history.", + "texts": [ + " Stages to be completed when using this method are: defining the sketch plan, sketch achievement in the drawing plan chosen, making parameterized listing, imposing 2D restrictions, defining 3D characteristics and combining them. Regardless of the method chosen (classical or synchronous) the design continues with orthogonal and axonometric projections, projections sizing, adding shape and position deviations, and adding technical notes. For Solid Edge this tree- history method is called ordered. Basically, in the area of the modelling screen, superimposed on it there is an area where a number of information are written about the history of all operations performed, which is called PathFinder. For example Figure 1 illustrates the 3D models related to two pieces with different tree histories, but both contain at PathFinder level the same categories of information: file name, references of the base plans, the label \"Ordered\" and then a set of sketches followed by designation of a 3D feature. Mention must be made that in the files chosen it was considered that sketches should not be visible not to make difficult the understanding of the final geometry. Also it can be seen in each of the examples in Figure 1 that selecting a 3D feature from the tree PathFinder involves the allocation of a certain colour (shade of gray) to those portions of the three-dimensional model which relates to the feature selected. The tree structure of the PathFinder also observes the chronology of generating sketches or local 3D feature. Changing any element of the PathFinder structure means to keep in the modelling space those items inside the selected item for editing and not showing temporarily the subsequent ones [2]. As seen in Figure 2, the sketch editing involves its viewing in the modelling space and temporary not showing all the elements of the tree structure achieved subsequently" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure1.15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure1.15-1.png", + "caption": "Figure 1.15 : Section of a simplified electric motor geometry for modeling.", + "texts": [ + " Materials are investigated and chosen at WP1 and some characteristics are extracted from catalogs. The rotor consists of laminated core and surface mounted Samarium-Cobalt magnets. NdFeB magnets could be an option for the machine unless simulations show that the temperature field in the magnet could exceed the maximum allowed value. The stator is made up of a laminated core with teeth-and-slots configuration and distributed windings in slots. The shaft consists of a steel rod. The motor frame is made of aluminum. In a modeling approach, a simplified motor section is depicted in Figure 1.15. 1.4.3 Electric Motors, Suitable but? One of the challenges met in e-motors with high performance, for power traction applications, for instance, is the thermal concern. When high performance is targeted, loads should be increased and the heat produced due to losses increases correspondingly as well. Since the heat flux in a system influences its thermal behavior, the e-motor temperature evolution depends on these losses. To reach high specific power values, required to maximize motor power and minimize its weight for propulsion application, loads should be increased wisely such that acceptable motor operating conditions are respected" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004125_f_version_1625137414-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004125_f_version_1625137414-Figure16-1.png", + "caption": "Figure 16. Natural fibers composites as automotive components. Reproduced from ref. [240].", + "texts": [ + " [160] reviewed the mechanical properties of hybrid natural fiber composites for a bumper beam. Lower impact properties were discovered based on the mechanical evaluation of the various research studies using hybrid natural fiber as a major limitation in comparison with the conventional glass fiber composites applied as typical bumper beam material. Synthetic fibers aid in compensating for the limitation of natural fibers when used in a hybrid in order to improve the mechanical properties of the polymer composite [238,239]. Figure 16 illustrates examples of automotive components that implement natural fibers composites. In recent times, the sport sectors have grown to become the second most popular entertainment industry. Via technological enhancement, this sector has been reaching worldwide and influencing billions of people. In order to guarantee the safety, security, and sustainability of this sector, cost-effective, efficient, durable, recyclable, and reusable materials were needed by applying advancement in manufacturing and material processes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure8-1.png", + "caption": "Fig. 8 Formulations of strong coupling interface under floor frame of service car body after replacing 678 with new rubber hanging elements. (a) New V-type rubber hanging elements for traction converter. (b) 679 New Conic rubber hanging elements for traction transformer, toilet collection, etc. (c) Lateral 680 acceleration of traction converter exceeds limit specified in IEC61373 \u2013 2010 when running speed of 681 (420 - 480) km/h in tangent line at \u03bbe =0.10. (d) Lateral acceleration exceeds limit again when running 682 speed of (380 - 420) km/h in tangent line with slight central hollow tread wear. Considering strong 683 coupling interface formulated under floor frame, central rhombus modal frequency of service car body 684 is then increased slightly from inherent 8.66 Hz to 9.71 Hz due to corresponding master-slave node 685 constraints (e, f), by which lateral coupling relationship is established with acceleration response of 686 bogie frame lateral vibration, causing traction converter to occasionally generate internal coupling 687 resonance. Meanwhile, 1st lateral bending modal frequency of service car body is then decreased from 688 inherent 17.98 Hz to 14.85 Hz due to generalized mass increase (g, h). 689", + "texts": [ + " 940 As mentioned above, through the collaborative and innovative efforts of vehicle, rail 941 and passenger transport disciplines, the slight central hollow tread wear provides the 942 necessary conditions for the structural experts to better realize the structural dynamic 943 response design optimization of aluminium alloy car body. In order to ensure the weak 944 coupling interface, the independent design of equipment cabin under floor frame mainly 945 includes the following three points: 946 1) In order to avoid the negative impacts caused by the reciprocating lateral 947 movement of traction converter, e.g. skirt plate bracket cracks or bolt connection failure 948 (loosed or broken), it is necessary to use the novel rubber hanging elements, as shown in 949 Fig. 8 (a), the proportional damping is set as (0.3 - 0.5)% for elastomers. 950 IEC61373 \u2013 2010. (e \u2013 f) Safety assessment of lateral vibration for traction converter when running in a 958 tangent line with higher speeds of (420 \u2013 550) km/h and near to limit speed of 650 km/h under \u03bbe = 0.10. (g) 959 Safety assessment of lateral vibration for traction converter when running in a tangent line with service 960 speeds of (300 \u2013 380) km/h under \u03bbe = 0.35. (h) Safety assessment of lateral vibration for traction converter 961 when running in a tangent line with three speed grades of 480/650/780 km/h when considering negative 962 impacts of detrimental wear like central hollow tread wear" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002443_e_download_4406_3060-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002443_e_download_4406_3060-Figure1-1.png", + "caption": "Figure 1 Elements in draw wire sensor", + "texts": [ + " The wire that is attached to the sensor is used to measure the displacement and the sensor will provide the proportional output signal from the system. The basic components in a draw wire sensor are steel wire, mechanics element that consists of drum and spring motor and potentiometer to measure the generated signal. The design of the steel wire depends on the sensor design, where normally the wire is extremely thin and sheathed with polyamide. The thickness of the wire is around 0.8mm, however, it is depending on the types of the stress force involved. Figure 1 shows the illustration of the component in draw wire sensor [1]. The draw wire sensor is suitable for application that is large in measuring ranges, required a small sensory dimension and when a low cost solution is needed. The draw wire sensor is also convenient to use even in wet, dirty environment or even when the measuring range needs to travel over a harsh environment. The draw wire sensor is operated when a linear movement is transformed into a rotation by draw-wire principle and then an electrical signal is generated by the rotary encoder" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure3-1.png", + "caption": "Fig. 3 Transparent perspective views of the modified polycentric knee (a) Antero-lateral and (b) Postero-lateral", + "texts": [ + " The design criteria involve giving strength to weaker components in critical areas and reducing base materials at high strength robust areas to achieve the light weight of the product. The 3D CAD model is created in CATIA V5. The components of 4-bar knee is designed and assembled independently. The major design changes incorporated in the modified polycentric knee are based on simulation-based failure analysis reports and reported cases of damage from clinical observations as summarized in Table 3. Different transparent perspective views of the CAD model of the modified polycentric prosthetic knee have been shown in Fig. 3. The kinematic evaluation of a 4-bar polycentric knee is based on Grashof\u2019s law double rocker with length bar condition ( dcba ) as shown in Fig. 4(a), where a, b are the longest and shortest link respectively and c, d are the other links. The optimal dimensions of the polycentric knee mechanism is based on the data of the trajectory of the instantaneous center of rotation (ICOR) calculated from the kinematic analysis of the four-bar polycentric knee. This verifies the stability to set the ICOR behind the load line (x = 12 mm) as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004437_load.php_id_10052811-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004437_load.php_id_10052811-Figure4-1.png", + "caption": "Figure 4. (a) ESPRIT decomposition at 550 MHz. (b) ESPRIT fitting at 550 MHz.", + "texts": [ + " Kraus\u2019 empirical formula [2], which was derived based on the dominant T+ 1 mode, is added in the plot for comparison. The empirical curve implies the gain of the helix should increase as the frequency increases. However, the actual helix gain at 550 MHz is higher than that at 750 MHz. To better explain this result, we study the gain contribution from each current mode after the current decomposition (as illustrated earlier in Figs. 3(a)\u20135(a)). Figure 8(a) plots the gain contribution of the T+ 1 mode alone at 550MHz. It is shown as the red \u2018+\u2019 curve and is calculated based on the T+ 1 mode extracted in Fig. 4(a). The reference curve shown in the solid blue line is the gain due to the total current simulated using NEC. It is observed that the total gain is higher than that of the T+ 1 mode alone. In Fig. 8(b), we calculate the gain contribution from both T+ 1 and T\u22121 . As expected, the resulting curve does not change much from the T+ 1 mode case since the strength of T\u22121 is much weaker. However, as shown in Fig. 8(c), the gain increases to the same level as the total gain when the T+ 0 mode is added in" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000941_full_papers_FP51.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000941_full_papers_FP51.pdf-Figure18-1.png", + "caption": "Fig. 18, Model used for Case (f), \u201cRigid Spring\u201d virtual part, torsional", + "texts": [ + " column is the one calculated from the theoretical formula presented earlier (length of the bar being \ud835\udc3f\ud835\udc40\ud835\udc43 = 100 \ud835\udc5a\ud835\udc5a) The agreement is just about perfect as recorded in the table. Such perfect matches are strictly coincidental and in general do not take place in numerical simulation. Case (f) Rigid Spring Virtual Part, Torsional Vibration: As in the previous cases of axial and bending vibration, this is essentially the same problem considered in case (e) except that the \u201cRigid Spring\u201d virtual part is used. The first requirement here is to estimate the torsional stiffness of the \u201cVirtual Part\u201d as displayed in Fig. 18. The stiffness of this torsional spring is based on strength of materials formulas and given by \ud835\udc58\ud835\udc49\ud835\udc43 \ud835\udf03\ud835\udc67 = \ud835\udc3a\ud835\udc3d 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 . Note that the length, 0.5\ud835\udc3f\ud835\udc49\ud835\udc43 is used as the rest of the spring (the last 25 mm) which is not engaged and primarily goes for a ride. In this expression, J is the cross sectional polar moment of inertia given by = \ud835\udf0b 2 \ud835\udc454, where R is the shaft radius. As for the mass of the virtual part, due to the torsional motion, its rotary inertia is of significance. This inertia is estimated from \ud835\udc49\ud835\udc43 \ud835\udf03\ud835\udc67 = 1 2 \ud835\udc5a\ud835\udc49\ud835\udc43\ud835\udc45 2 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure2-1.png", + "caption": "Figure 2. Gripper in Open & Closed Configurations", + "texts": [ + " The drive wheel is pressed against a pipe by a pneumatic cylinder and is powered by a stepper motor. Four linear slides are used to allow the system to extend while maintaining rigidity. The slides are actuated by two pneumatic extension cylinders. The overall system design is shown in Figure 1. Pipe Traveler Assembly The gripper is used to allow the Pipe Traveler to clamp onto pipes, but still allow the unit to rotate around the pipe. This is achieved by using idler rollers located between fingers as the contact points on the pipe (See Figure 2). The idler rollers allow the grippers to support the weight of the Pipe Traveler while permitting rotation around a pipe. The gripping surface of the rollers is urethane rubber, which allows the grippers to accommodate imperfections in the pipes to be gripped. Page 3 of 15 A 24V DC motor with encoder is used to supply the gripping force. When the gripper is initially open, the motor will actuate and cause the drive screw to rotate. As the drive screw rotates it threads into the drive block. Since the drive screw cannot move, the drive block is pulled toward it" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001833_jeee.2013.010202.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001833_jeee.2013.010202.pdf-Figure3-1.png", + "caption": "Figure 3. The flux differential detector", + "texts": [ + " To avoid the harmful effects of faults it is necessary to detect them in their incipient phase [18]. The winding faults of the SRM can be sensed by several failure detectors [19]. One of the most simple fault detection devices is the over-current detector given in Figure 2 [20]. Its efficiency is limited due to insufficiently fast response time and the inability to detect all types of faults. Figure2. The current differential detector Another simple detector, the flux differential one, is shown in Figure 3. It requires additional search coils wrapped around the stator poles. The search coils of each phase are connected in series opposing, similarly to the connections of the main coils of the machine. During normal operation (without winding faults) the voltages induced in the two search coils are equal and opposite. Hence zero voltage will be at the input of the comparator. When a winding fault occur the imbalance in the pole fluxes induces different voltages in the two search coils. This voltage difference can be detected with the bidirectional comparator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000678_f_version_1704890043-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000678_f_version_1704890043-Figure4-1.png", + "caption": "Figure 4. Schematic illustration of a (a) three-point bending test setup and the main variables: support span (V), support radius (Rm), specimen length (L), specimen width (W), specimen thickness (t), and punch radius (Rp); (b) example of a punch force\u2013displacement (Fp \u2212 yp) curve of a sheet metal material.", + "texts": [ + " Unlike gradient-based methods, the Nelder\u2013Mead method does not require derivatives of the objective function and can handle functions with discontinuities. The identified hardening parameters of the studied materials are summarized in Table 3, and the corresponding hardening evolution curves are plotted in Figure 3b. The standard ASTM E290 [58] covers several bending tests used to evaluate the behavior of materials when subjected to bending loads under different boundary conditions. The most common is the guided-bend test, which uses a three-point bending setup (Figure 4a) without using a female die. The test is conducted by placing a rectangular specimen symmetrically on the support fixture mounted to the testing machine. Load is applied at the specimen\u2019s midpoint until either failure occurs or the predefined angle of bend or maximum angle for the fixture is achieved. The bending angle is determined during the test by projecting lines along the specimen\u2019s flat surfaces outside the bend region and measuring their intersecting angle. After completing the bending test, the curved surface of the bend is examined to evaluate the presence of cracks or surface irregularities. For sheet metal materials, the three-point bending test is widely used to evaluate the springback effect of the tested material. As represented in Figure 4b, the removal of the tools for a punch displacement, yp, of 20 mm leads to elastic recovery of the material, which results in different bending angles before, \u03b1i, and after, \u03b1 f , springback. The springback is entirely intercorrelated with the stress distribution on sheet metal after forming, and its magnitude is related to the ratio between the residual stress and the elastic modulus of the material [59]. It is also influenced by material properties such as strain hardening, elastic property evolution, the presence of Bauschinger effects, elastic and plastic anisotropy, and tribology between contacting surfaces [60]", + " Although the modulus of elasticity may not exert a substantial influence on the curves derived from the three-point test, a detailed understanding of the material\u2019s elastic properties is crucial to prevent errors when determining the material\u2019s plastic parameters. Hence, alongside determining the material\u2019s hardening parameters, the methodology should also conduct a preliminary check to confirm the material\u2019s classification as steel. Applying the Euler\u2013Bernoulli theory in a plane strain analysis and treating the initial flat sheet as a beam, the deflection of the sheet, \u03b4, in the elastic region in response to the punch force, can be determined as: \u03b4 = FpV3 48E\u2032 I (10) where I is the moment of inertia of the specimen, and V is the support span (see Figure 4). The modulus of elasticity, E\u2032, is slightly different from the uniaxial Young\u2019s modulus, E, and can be expressed as follows: E\u2032 = E 1 \u2212 \u03bd2 , (11) where \u03bd is the Poisson\u2019s ratio. Considering the sheet deflection equal to the punch displacement, \u03b4 = yp, the material Young\u2019s modulus can be calculated by: E = FpV3 (48yp I)(1 \u2212 \u03bd2) . (12) This equation enables the calculation of the three-point bending modulus using the punch force\u2013displacement curve. Using the three-point bending results presented in Figure 7a for the DP500 and DP780 materials and applying Equation (12), the elastic bending modulus is shown in Figure 7b for different punch displacement values lower than yp = 1 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003848__Issue3-05_paper.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003848__Issue3-05_paper.pdf-Figure3-1.png", + "caption": "Fig. 3. Asymmetric position of the seat bottom", + "texts": [ + " Due to the set general direction of sprocket drum revolutions resulting from the direction of rock transport, the wear of the seat bottoms and teeth flanks may be reduced by introducing the asymmetry of the profile of the sprocket drum seats. The proposed modification of sprocket dream seats\u2019 profile consists of inclining the seat bottom towards the expected direction of the basic drum revolutions in such a way that the perpendicular bisector of the seat bottom being a line perpendicular to the seat bottom led in the centre of the seat length, is not going through the revolution axis of the drum but is away from the axis of revolution by the distance r (Fig. 3) (Dolipski et al., 2011). In terms of design, the modification causes the displacement of the seat profile and reduction in distance between the seat bottom and the axis of revolution in relation to the standard dimension. The asymmetric position of the seat bottom also causes the asymmetry of the inclination angles of the tooth \u03b21 and \u03b22 flank on the both sides of the tooth segment. The shape of the seat may remain in accordance with the standard. By introducing an asymmetric profile, the revolution angle value ratio is changed of the front torus of the horizontal link running on the drum in relation to the seat bottom, to the vertical link revolution angle value in relation to the preceding horizontal link", + " The rotation of the vertical link in relation to the preceding horizontal link is lasting from the moment the horizontal link rear torus is contacting the tooth flank until the front torus of next horizontal link is contacting the bottom of the next seat. Profile asymmetry gives a possibility to change the \u03b11 value angle ratio of rotation of the horizontal link front running on the drum relative to the seat bottom, in relation to the \u03b12 angle value of the rotation of the vertical link in relation to the preceding horizontal link, as a result of which a friction path can be shortened of the horizontal link front torus against the seat bottom and the rotation angle of the vertical link can be extended relative to the preceding horizontal link (Fig. 3). The ratio value of angles of \u03b11/\u03b12 = 0.5 was used in the solution proposed for studies. The value is therefore decreased of the angle \u03b11 of rotation of the horizontal link front torus running on the drum relative to the seat bottom. The angle \u03b12 value of the rotation of the vertical link changes in relation to the preceding horizontal link, though. The purpose of the proposed modification of the sprocket drum seat profile is to reduce the wear of seat bottoms and tooth flanks with the general direction of sprocket drum revolutions consistent with the transport direction of output within the longwall" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003211_f_version_1426592263-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003211_f_version_1426592263-Figure3-1.png", + "caption": "Figure 3. Flux path in one pole of the BDRM.", + "texts": [ + " Based on the analysis results, a prototype was manufactured and the experimental results provided. Figure 2 shows the exploded view of the BDRM. It is a synchronous machine with a stator, claw-pole outer rotor and permanent-magnet inner rotor. The stator comprises laminated iron cores and ring-shaped windings, as shown in Figure 2a. The claw-pole rotor has three arrays of claws placed in non-magnetic bracket as shown in Figure 2b. Figure 2c shows the permanent-magnet rotor which is built in a flux-concentrated magnet topology. The flux path in one pole of the BDRM is shown in Figure 3. The flux from the magnet goes radially through the inner air gap into one claw, then across the outer air gap and into the stator, passing axially along the yoke, and once again radially passing the outer air gap into the next claw, and finally returns to the opposite polarity of the magnet, completing a flux loop. Brushless technology for a double-rotor machine is realized, which makes the BDRM a meaningful invention. When used in hybrid electric vehicle traction, the permanent-magnet rotor is connected to the crank shaft of the internal combustion engine (ICE), while the claw-pole rotor is connected to the final drive" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003647_f_version_1577096875-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003647_f_version_1577096875-Figure3-1.png", + "caption": "Figure 3. Section view of the little and middle finger with the model scaled to the 50th percentile female dimensions. The section view of the little finger shows the joints of the finger while the deeper cut into the middle finger shows the paths for both the flat flex cables (FFCs) and the tendon.", + "texts": [ + " In addition to the seven high-level parameters, the model contains 257 other parameters, which are either derived from the high-level parameters or are constant like fittings, so that a change in high-level parameter values results in a change of the dimensions of the entire finger. The parameters can, for example, be set to match the measured dimensions of the able hand of an amputee. We successfully tested the model using the 5th percentile female hand dimensions as well as the 95th percentile male hand dimensions. Figure 3 shows two specimens of the developed CAD-model scaled to the dimensions of the little and middle finger sized according to a median female hand. In addition to human sizing, special attention was given to the anthropomorphic shape of the fingers which is an important factor especially for the acceptance in prosthetic applications [45]. In Figure 4, the profile of a physical demonstrator is shown. We consciously made the decision to fuse the distal and intermediate phalanx into one part. Each finger hence has two joints, the MCP joint and the PIP joint", + " Both the distal/intermediate as well as the proximal phalanx are hollow for the most part to allow the springs to extend without friction and in order to save weight. We used spring steel with 0.1 mm thickness as the leaf spring material. Each joint is equipped with a stack of three leaf springs to reach a sufficiently high torque. As shown in Figures 1 and 3, a customizable number of sensors can be integrated into a finger, depending on the finger pad area available for the integration of tactile sensors. The middle, and thus largest, finger used in this work, shown in the bottom of Figure 3, contains a total number of ten sensors, which include two joint angle encoders, a distance sensor, three normal force sensors, three shear force sensors and one accelerometer. The sensor PCBs can be connected to a controller using FFCs via connectors on the joint angle encoder and distance sensor PCBs (see Figure 3), while the tactile sensor PCBs are connected through magnet wires. In order to find the optimal configuration and placement positions of the tactile sensors in each finger, we conducted tests to determine which surfaces of each finger are in contact when grasping different objects. These experiments were carried out prior to the definition of the tactile sensor layout and their results were used to define the area on the finger that should be covered with tactile sensors. We used the 50th percentile female version of the KIT Prosthetic Hand [41], as well as five objects (banana, baseball, bowl, drill, spam) from the YCB object set [48] and two objects (cola, green cup) from the KIT object set [49], in order to have a variation of shapes and sizes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001400_f_version_1634111124-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001400_f_version_1634111124-Figure1-1.png", + "caption": "Figure 1. PMSM model in wide temperature range.", + "texts": [ + " Then, under the condition that the output torque meets the requirements and the temperature of the motor does not exceed the maximum working temperature of materials, the response surface method is used to obtain the optimal solution of the magnetic pole structure parameters in order to reduce cogging torque. Finally, a prototype is developed for experimental verification. A surface-mounted inner rotor PMSM with six poles and eighteen slots is preliminarily designed, and the output torque is required to be no less than 10 Nm during operation, as shown in Figure 1. Some of its size parameters are shown in Table 1. When the PMSM works in a wide temperature range environment, it is necessary to consider the effect of temperature changes on the performance of each component material. According to different materials, the motor is divided into three parts: iron core, windings and permanent magnet. The motor core is composed of laminated silicon steel sheets, which can effectively reduce the eddy current and iron loss, improve motor efficiency and reduce heat and temperature rise during motor operation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003882_f_version_1645520937-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003882_f_version_1645520937-Figure6-1.png", + "caption": "Figure 6. Dynamic model of proposed mechanism for ejection process.", + "texts": [ + " By researched the transitions between different modes and the conditions for these transitions, including stance, taking-off under-actuated, flight, landing under-actuated, and recovery, they derived the potential and kinetic energies of the system and other terms of the Euler\u2013Lagrange equations. On this basis, we established the dynamic equation. Adopting the same coordinates as those in Figure 4 (O as the origin; the motor output shaft as the y axis), the mechanism is abstracted into a simpler model for dynamical analysis of the ejection process as shown in Figure 6. The mass of the whole mechanism excluding the pole is m2. The COM of this part is marked with the bigger black-and-white icon, and distance from it to point O is LM. The distances from point O to the two ends of the pole are L1 and L2, and that to the COM of the pole is LP. The mass of the pole is m1, with its COM on the smaller black-and-white icon. The angle between the horizontal plane and the pole is \u03b81, and that between the pole and line OM is \u03b82. Lagrange dynamical equations are set up to carry out dynamical analyses" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004178_.pdf_c_1606268078000-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004178_.pdf_c_1606268078000-Figure1-1.png", + "caption": "Figure 1. Continuously variable noncircular gear transmission", + "texts": [ + " Each branch loop is a three-element planetary row for differential coupling of two-order parallel noncircular gear pairs with non-uniform output speed, and then the constant speed ratio within a certain angle range is obtained through controllable overrunning clutch. Rotation shafts of this branch are free rotation without power transmission, ranging in other rotation angle. Accordingly, speed ratio can be continuously adjusted by changing the phase angle of two parallel noncircular gear pairs. The continuously variable noncircular gear transmission system model and skeleton of scheme mechanism are shown in Figure.1. Ya-Nan Hu et al. \u00b74\u00b7 As shown in Figure. 1, gear pairs 1-3 and 2-4 are noncircular gear pairs, while the rest are cylindrical gear pairs. This system with a constant transmission ratio involves the transmission unit superposition of two branch noncircular gear pairs with variable phase. During working process, a constant velocity input of component 1 will be transformed into the velocity output with linear function of component 3 and component 4, through the first level transmission of noncircular gear pair. And the constant output speed can be obtained in a limited range of angle, after the output speed of component 3 and 4 is differential coupling", + " His research interests include the development of the new type of gear transmission, fundamental study of curve-face gear, and surface topography of non-circular gear. E-mail: 20160702017@cqu.edu.cn Zhi-Qin Cai, born in 1988, is a lecturer at the School of Aeronautics and Astronautics, Xiamen University. He received his PhD in mechanical engineering from Chongqing University. His research interests include intelligent design of precision gear driven by shape coupling, micro-texture of tooth surface, and energy-saving transmission design. E-mail: caizhiqin@xmu.edu.cn Figures Figure 1 Continuously variable noncircular gear transmission Figure 2 The basic transmission characteristics of continuously variable noncircular gear transmission a) Gear velocity at all levels in continuously variable noncircular gear transmission (b) The transmission ratio of each level in continuously variable noncircular gear transmission Figure 3 The in uence of 1 b on transmission ratio of noncircular gear pair Figure 4 The in uences of 1 k on transmission ratio of noncircular gear pair Figure 5 Comparisons of transmission ratio and centrode of noncircular gear pairs with different transmission ratio parameters Figure 6 The in uence of zero modi cation on the contact ratio of noncircular gear Figure 7 The in uence of each parameter on the contact ratio (a) The in uence of the modi cation coe cient and tooth pro le angle of the rack cutter on the contact ratio (b) The in uence of module on the contact ratio Figure 8 The in uence of transmission ratio coe cient on contact ratio Figure 9 The analytical diagram of tooth pro le of driving gear Figure 10 The analytical diagram of meshing curve of noncircular gear pair Figure 11 The theoretical results of some meshing curves of noncircular gear pair by MATLAB Figure 12 The analytical diagram of contact pro le of driving gear and the addendum curve of driven gear Figure 13 The 2# theoretical contact tooth pro le of driving gear by MATLAB Figure 14 The tooth pro le curve of noncircular gear pair with MATLAB (a) Tooth pro le curve of driving gear (b) Tooth pro le curve of driven gear Figure 15 The experimental test platform of the noncircular gear transmission Figure 16 The length of contact pro le of driving gear Figure 17 The transmission ratio and contact pro le length of the driving gea" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure13-1.png", + "caption": "Figure 13. Actual force transducer model.", + "texts": [ + " For the performance of excitations, tension screws with integrated single axis force sensors were used. The calibration concept of the developed transducer construction was presented in Figure 12. The calibration procedure involves three stages, two of which pertain to the identification of force coefficients along the main default Y, Z axes and a single stage pertaining to the identification of coefficients related to the torque about the X axis. For the purpose of verification tests, an actual force transducer model was constructed, as shown in Figure 13. It was made as a screwed structure, onto which resistance force transducers were fixed in accordance with the distribution shown in Figure 10. Example results of the experiment performed for the Z axis on a physical model of a transducer were illustrated in the graphs below. Figure 14 presents the course of strains recorded for one of four strain gauge bridges adhered to the support structure of the transducer. For the purpose of the tests, single-axis strain gauges by Tenmex designated as TFs-5/120 were used" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001599_sue-17_Article16.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001599_sue-17_Article16.pdf-Figure5-1.png", + "caption": "Figure 5. Proposed antenna design in 3D view.", + "texts": [ + " The second dielectric substrate material FR4 extends upward with 1.6 mm. The chosen \u03b5r is 4.4. The Y Shaped radiating element aims to operate in 4.5 GHZ Frequency band. The performance results of the design is 65.3 %.The simulated antenna shows the better return loss values less than -10 DB13-15. The design is equal sided in dimensions. The structure of the radiating element is elaborated in Figure 4. The equal sided patch design is arranged on the top of Flame resistant substrate. The 3D prospect of antenna is available in Figure 5. Few things have to be shown attention when designing the radiating patch are as follows performing frequency, material on the top of which the radiating element is to be raised, materials permittivity. The scale values for the prompted equal sided structure are obtained using the relations. The side dimensions are 29.2 mm. Indian Journal of Science and Technology 3Vol 11 (17) | May 2018 | www.indjst.org The preferred substrate material is FR4 (Lossy) and the permittivity value is 4.4 and the thicknes chosen for the design is 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002338_8600701_08824219.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002338_8600701_08824219.pdf-Figure7-1.png", + "caption": "FIGURE 7. Current distribution when patch is excited at (a) 870MHz; (b) 890MHz; when dipole is excited at (c) 870MHz; (d) 890MHz.", + "texts": [ + " 6 gives the cross-band isolation comparison between filtering and non-filtering (traditional) HB elements operating at 880-960 MHz. It can be seen that the isolation in the lower operating band is only 5 dB when the traditional dipole is used. Using the proposed filtering element, the isolation is improved to 15 dB. Similarly, the isolation in the higher operating band will be worse if using the non-filtering patch at the lower band. To show themutual coupling clearly, the current distributions are given in Fig. 7 illustrates that patterns and current distributions when the patch antenna (operating at 790-862 MHz) is excited. As seen, the current at the dipole port is induced when the patch antenna is excited at 870 MHz. The current is very weak when the patch antenna is excited at 890 MHz (radiation VOLUME 7, 2019 127803 null). Similarly, when the dipole antenna (operating at 880- 960 MHz) is excited, the current on the patch edge is induced at 870 MHz, and it is very weak at 850 MHz (radiation null). C" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003376_ticles_srep06756.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003376_ticles_srep06756.pdf-Figure3-1.png", + "caption": "Figure 3 | FEM model of the PM spherical actuator with 3D magnet array. In the analysis, the connection links and housing parts are removed, because they have no significant influence on the magnetic flux distribution.", + "texts": [ + " Substituting the absolute positions of Hall-effect sensors into equation (1) and considering the periodicity of c and the range of a and b, the analytical expressions of the rotation angles could be obtained as a~arcsin ffiffiffiffiffiffi V6 KK1 4 q { ffiffiffiffiffiffi V5 KK1 4 q 2 sin a0 a[ { p 4 , p 4 , b~ 1 2 sgn V3j j{ V4j j\u00f0 \u00dearcsin ffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffi d{ ffiffiffiffiffiffiffiffiffiffiffiffiffi d2{e2 pp 2ab b[ { p 4 , p 4 , c~ 1 4 arcsin FV1{DV2 KK1 FE{DG\u00f0 \u00de sgn V1\u00f0 \u00de p 8 z 1 4 arcsin GV1{EV2 KK1 FE{DG\u00f0 \u00de 8>< >: cj jv p 8 p 8 v cj jv p 4 : \u00f04\u00de where a 5 sina1, b 5 cosa cosa1, c 5 sina cosa1, d~ V3zV4 KK1 z16c4, e~ V3{V4 KK1 A 5 cosb cosa0, B 5 cosa sina0, C 5 sinasin bsina0, D~ A{C\u00f0 \u00de2{B2 2 {4B2 A{C\u00f0 \u00de2, E 5 24B(A 2 C)[(A 2 C)2 2 B2], F~ AzC\u00f0 \u00de2{B2 2 {4B2 AzC\u00f0 \u00de2: \u00f05\u00de Numerical computation is employed to validate the derived analytical model of rotor orientation. The finite element method (FEM) model and the magnetization patterns of the PM poles are presented in Figure 3. Figure 4 shows the comparisons between analytical and actual rotation angles with 3D magnet array. The red line represents the actual tilting angle in FEM model, whereas the blue line is the tilting angle from analytical model. Relative large difference is SCIENTIFIC REPORTS | 4 : 6756 | DOI: 10.1038/srep06756 3 observed between the actual and analytical results in Figures 4(a) and (b), which is mainly caused by the simplification of analytical models. However, in Figure 4(c), the analytical model fits with the actual value more closely" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001370_advpub_23004537__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001370_advpub_23004537__pdf-Figure2-1.png", + "caption": "Fig. 2. Circuit model of IM in the stationary orthogonal-axis frame.", + "texts": [ + " This allows determining the percentage stray load loss for individual tested machines without performing an actual load test with torque and rotational speed measurements. The proposed torque estimation method is carried out on two test IMs fed by V/f control including flux weakening mode in a low frequency operation. The performance of torque estimation is verified by comparison with the measured value for three types of voltage waveforms: sine, square, and PWM drives. 2. Pre-determination of Parallel Equivalent Iron Loss Resistance and Percentage Stray Load Loss 2.1 Basic models Fig. 2 shows a circuit model in the stationary frame of an IM considering parallel equivalent iron loss resistance rc. The stator voltage and current vectors are denoted as v1=[v1 v1]T and i1=[i1 i1]T respectively, the load current vector im as [im im]T, an d the stator flux linkage vector 1 as [1 1]T. p is the number of pole pairs. v1 and i1 are calculated from the voltage and current in the three-phase ac coordinate system as follows. 1 1 2 / 6 1 / 6 0 1 / 2 v UV VW v v v v 1 (1) 1 1 3 / 2 0 1 / 2 2 i U W i i i i 1 (2) Fig", + " Thus, we consider that assuming the mechanical loss has little influence on torque estimation accuracy(15). 4 IEEJ Trans. \u25cf\u25cf, Vol.\u25cf\u25cf, No.\u25cf, \u25cf\u25cf\u25cf contribution proposed in this paper. In the 4th block, voltage and current data at rated load operation in a sine-wave drive at the rated voltage and rated frequency are created from the nameplate values. In the 5th block, using the voltage and current data created virtually in the 4th block, the torque 1ims for each perWSLN is estimated by stator flux linkage calculation based on the model in Fig. 2. Here, perWSLN changes from the expected minimum value perWSLNmin to the expected maximum value perWSLNmax with a step width perWSLN. The 6th block is the final step. When the final when 1ims is correctly obtained by taking into account the torque reduction due to mechanical loss and stray load loss, perWSLN is determined as the value that satisfies the condition at rated load; T1ims (average value of 1ims at steady state) corresponds to the rated torque TN. In the real world, finding the value of perWSLN when T1ims is closest to TN is done" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001163_O201110441050686.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001163_O201110441050686.pdf-Figure3-1.png", + "caption": "Fig. 3 Schematic of the crushing blade(unit: mm).", + "texts": [], + "surrounding_texts": [ + "9 The article was submitted for publication on 2010-11-16, reviewed on 2011-01-19, and approved for publication by editorial board of KSAM on 2011-01-31. The authors are Sung Il Kang, Graduate Student, Soo Nam Yoo, Professor, Chonnam National University, Gwangju, Korea, Yong Choi, Agricultural Researcher, National Academy of Agricultural Science, RDA, Suwon Korea, and Young Joo Kim, Senior Researcher, KSAM member, Environmental Materials & Components Center, Korea Institute of Industrial Technology, Jeonju, Korea. Corresponding author: S. N. Yoo, Professor, Department of Rural and Bio-systems Engineering and College of Agricultural and Life Sciences, Chonnam National University, Gwangju, 500-757, Korea; Tel: +82-62-530-2155; Fax: +82-62-530-2159; E-mail: .\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uac15\uc131\uc77c \uc720\uc218\ub0a8 \ucd5c \uc6a9 \uae40\uc601\uc8fc\nDevelopment of a Vine Crusher for Harvesting Sweet Potato\nS. I. Kang S. N. Yoo Y. Choi Y. J. Kim\nThis study was carried out to develop a vine crusher for harvesting sweet potato. The experimental two-row vine crusher attachable to agricultural tractor composed of vine crushing part with frail type vine crushing blades and vine lifting blades, power transmission part with chain and gear transmission mechanism, crushing height control part with two control wheels and manual levers, and implement frames, was designed and fabricated. And this vine crushing performance was also analyzed.\nFrom vine crushing tests, backward travel direction (i.e., rotational direction of the vine crushing blades) showed better vine crushing performance than forward travel direction. Crushing ratio of remained vine was increased, and length of remained vine and length of crushed vine were decreased as working speed was decreased and rotational speed of vine crushing blades was increased. At a working speed of 0.27 m/s and rotational speed of vine crushing blades of 800 rpm, crushing ratio of remained vine was 98%, length of remained vine was 104 mm, and length of crushed vine was 327 mm. But, when crushing vine on irregular ridges, vines and mulching vinyl were wound in the vine crushing part. Therefore, change of location of power transmission chain mechanism, and an automatic control device for controlling crushing height were needed.\nKeywords : Vine crusher, Sweet potato, Frail blade\n1. \uc11c \ub860\n\uc77c\ubc18\uc801\uc73c\ub85c \uad6d\ub0b4\uc758 \uace0\uad6c\ub9c8 \uc7ac\ubc30\ubc29\ubc95\uc740 \ubcd1\ud574\ucda9 \ubc29\uc9c0, \uc218\ud655 \ub7c9 \uc99d\uac00 \ub4f1\uc758 \uc7a5\uc810\uc73c\ub85c \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\uac00 \ub9ce\uc740 \ubc18\uba74, \uc678\uad6d\uc758\n\uacbd\uc6b0 \uc7ac\ubc30\uba74\uc801\uc774 \ub300\uaddc\ubaa8\ub85c \uac70\uc758 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30\ub97c \ud558\uc9c0 \uc54a\uc73c \uba70, \ubcc4\ub3c4\uc758 \ub369\uad74\ucc98\ub9ac\uc791\uc5c5 \uc5c6\uc774 \uc218\ud655\uc791\uc5c5 \ud6c4 \ub369\uad74 \ubc0f \ud611\uc7a1\ubb3c\ub85c \ubd80\ud130 \uace0\uad6c\ub9c8\ub97c \uc120\ubcc4\ud558\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \uad6d\uc678\uc758 \uacbd\uc6b0 \uace0\uad6c\ub9c8 \ub369 \uad74\ucc98\ub9ac\uae30\uc5d0 \uad00\ud55c \uc5f0\uad6c\ub294 \uac70\uc758 \uc5c6\ub294 \uc2e4\uc815\uc774\ub2e4. \uace0\uad6c\ub9c8 \uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \uc904\uae30\uc808\ub2e8\uae30\uc640 \ube44\ub2d0\uc81c\uac70 \uae30\uc758 \uc774\uc6a9\uc73c\ub85c ha\ub2f9 \uc791\uc5c5\uc2dc\uac04\uc740 \uc57d 8\uc2dc\uac04\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4 (Namerikawa, 1989). \ub610\ud55c \uc904\uae30\uac77\uc5b4\uc62c\ub9bc\ubd09\uacfc \ud504\ub808\uc77c type \ud68c\n\uc804\ub0a0 \uc808\ub2e8\ubc29\uc2dd\uc744 \uc774\uc6a9\ud55c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 1\uc870 \uace0\uad6c\ub9c8 \uacbd\uc5fd\ucc98\ub9ac \uc7a5\uce58\ub97c \uc774\uc6a9\ud558\uc5ec \uc8fc\ud589\uc18d\ub3c4 0.35\uff5e0.46 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 28.6 m/s\uc5d0\uc11c \uacbd\uc5fd\ucc98\ub9ac\uc728 91.7\uff5e92%, \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774 38\uff5e43 cm\ub85c \uacbd\uc5fd\ucc98\ub9ac \uc815\ub3c4\uac00 \uc591\ud638 \ud558\uc600\ub2e4\uace0 \ubcf4\uace0\ud558\uc600\uc73c\uba70 (Park and Choi, 1995), \uae30\uc874 \ub369\uad74\uc808\ub2e8\uc7a5\uce58 \ub4a4\uc5d0 \ub514\uc2a4\ud06c\ud615 \ub369 \uad74\uc808\ub2e8\uc7a5\uce58\ub97c \ucd94\uac00\ub85c \ubd80\ucc29, \uac1c\ub7c9\ud558\uc5ec \ud3c9\uade0 \uc904\uae30 \uc808\ub2e8\uae38\uc774\uac00 15.4 cm\ub85c \ub0ae\uc544\uc84c\uc74c\uc744 \ubcf4\uace0\ud558\uc600\ub2e4(Park and Choi, 1997). Ha(2006)\ub294 \ub3d9\ub825 \uacbd\uc6b4\uae30\ub97c \uc774\uc6a9, \uacbd\uc6b4\uae30 \ud6c4\ubc29\uc5d0 1\uc870\uc6a9 \ub369 \uad74\ucc98\ub9ac\uc7a5\uce58\ub97c \ubd80\ucc29\ud558\uc5ec 92%\uc758 \ub369\uad74\ucc98\ub9ac\uc728, 2.5 h/10a \uc791\uc5c5 \uc2dc\uac04\uc73c\ub85c \uad00\ud589 \uc778\ub825\uc758 \uc791\uc5c5\uc2dc\uac04\uc778 26 h/10a \ubcf4\ub2e4 \uc57d 1/10\ub85c \uc791\uc5c5\uc2dc\uac04\uc744 \uc808\uc57d\ud560 \uc218 \uc788\ub294 \uac83\uc73c\ub85c \ubcf4\uace0\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub9c8\ub298\n\ubc14\uc774\uc624\uc2dc\uc2a4\ud15c\uacf5\ud559 (J. of Biosystems Eng.) Vol. 36, No. 1, pp.9~14 (2011. 2) DOI:10.5307/JBE.2011.36.1.9\nOpen AccessResearch Article", + "\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uac1c\ubc1c\n\uc218\ud655\uc758 \uae30\uacc4\ud654\uc5d0 \uc788\uc5b4\uc11c \ud2b8\ub799\ud130 \ubd80\ucc29\ud615 \uc904\uae30\uc808\ub2e8 \ubc0f \ube44\ub2d0\ud53c \ubcf5 \uc81c\uac70\uae30\ub97c \uc774\uc6a9\ud558\uc5ec \uc808\ub2e8\ub192\uc774 100 mm, \uc8fc\ud589\uc18d\ub3c4 0.53 m/s, \uc808\ub2e8\ub0a0 \uc8fc\uc18d\ub3c4 67.86 m/s\uc5d0\uc11c \uc808\ub2e8\uc815\ub3c4 95.5%\ub85c \ubcf4\uace0\ud55c \ubc14 \uc788\ub2e4(Noh et al., 1999). \uc6b0\ub9ac\ub098\ub77c\uc758 \uace0\uad6c\ub9c8\uc758 \ucd1d \uc7ac\ubc30\uba74\uc801\uc740 2003\ub144\ub3c4 14,161 ha\uc5d0 \uc11c 2007\ub144 21,093 ha\ub85c \uafb8\uc900\ud55c \uc99d\uac00 \ucd94\uc138\uc5d0 \uc788\uc73c\ub098(MFAFF, 2009), \uc9c0\uae08\uae4c\uc9c0 \uae30\uc874\uc758 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc5d0 \ub300\ud55c \uc5f0\uad6c\ub294 1 \uc870\uc6a9\uc73c\ub85c \uc791\uc5c5\ub2a5\ub960\uc774 \ub5a8\uc5b4\uc9c0\uace0 \uc0ac\ub78c\uc774 \uc9c1\uc811 \ub530\ub77c\ub2e4\ub140\uc57c \ud558\ub294 \ub2e8\uc810\uc774 \uc788\uc73c\uba70 \ud604\uc7ac \ub18d\uac00\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8\uc218\ud655\uae30\uac00 \ubcf4\uae09 \ub418\uc5b4 \uc0ac\uc6a9\ub418\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 2\uc870\uc6a9 \uace0\uad6c\ub9c8 \uc218 \ud655\uae30\uc5d0 \uc801\ud569\ud558\uace0 \uae30\uc874 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ubcf4\ub2e4 \ud6a8\uc728\uc801\uc778 2\uc870 \uc6a9 \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\ub97c \uac1c\ubc1c\ud558\uace0\uc790 \ud558\uc600\ub2e4.\n2. \uc7ac\ub8cc \ubc0f \ubc29\ubc95\n\uac00. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc124\uacc4\uff65\uc81c\uc791\n1) \uc8fc\uc694 \uad6c\uc870 \ubc0f \uc81c\uc6d0\n\uadf8\ub9bc 1\uc5d0\uc11c\uc640 \uac19\uc774 \ud2b8\ub799\ud130 PTO\ub97c \uc774\uc6a9\ud558\uc5ec \ub3d9\ub825\uc774 \uc804\ub2ec\ub418 \ub294 \ud2b8\ub799\ud130 \ubd80\ucc29\ud615\uc73c\ub85c 2\uc870\uc758 \ub450\ub451 \ub369\uad74 \ud30c\uc1c4\uac00 \uac00\ub2a5\ud558\ub3c4\ub85d \uc81c\uc791\ud558\uc600\ub2e4. \uc8fc\uc694\uad6c\uc870\ub294 \ub369\uad74 \ud30c\uc1c4\ub0a0\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\ub85c \uad6c\uc131\ub418\uc5b4 \uc788\ub294 \ub369\uad74 \ud30c\uc1c4\ubd80, \ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc744 \ub369\uad74 \ud30c\uc1c4\ubd80 \uad6c\ub3d9\ucd95\uc73c\ub85c \uc804\ub2ec\ud574\uc8fc\ub294 \uae30\uc5b4\ubc15\uc2a4, \uc2a4\ud504\ub85c\ucf13, \uccb4 \uc778, \uae30\uc5b4 \ub4f1\uc73c\ub85c \uad6c\uc131\ub41c \ub3d9\ub825 \uc804\ub2ec\ubd80, \ub369\uad74 \ud30c\uc1c4\uc791\uc5c5 \uc2dc \ub450\ub451\n\uc758 \ub192\uc774\uc5d0 \ub530\ub77c \ubbf8\ub95c\uc758 \ub192\ub0ae\uc774\ub97c \uc870\uc808\ud568\uc73c\ub85c\uc11c \ub369\uad74 \ud30c\uc1c4\ubd80 \uc758 \ub192\uc774\ub97c \uc870\uc808\ud560 \uc218 \uc788\ub294 \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80, \ud2b8\ub799\ud130 \ubd80\ucc29\uc7a5\uce58 \ubc0f \ud504\ub808\uc784 \ub4f1\uc73c\ub85c \uc8fc\uc694\ubd80\ub97c \uad6c\uc131 \uc124\uacc4\uff65\uc81c\uc791\ud558\uc600\ub2e4.\n2) \ub369\uad74 \ud30c\uc1c4\ubd80\n\ub369\uad74 \ud30c\uc1c4\ubd80\ub294 \uadf8\ub9bc 2\uc5d0\uc11c\ucc98\ub7fc \ud68c\uc804\ub0a0 \ud30c\uc1c4\uc2dd\uc73c\ub85c \ub369\uad74 \ud30c \uc1c4\ub0a0, \ud30c\uc1c4\ub0a0 \ubd80\ucc29 \ube0c\ub77c\ucf13, \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5 \ucd95, \ub369\uad74 \uac77\uc5b4\uc62c \ub9bc\ub0a0, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ubd80\ucc29 \uc6d0\ud310, \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95, \uc9c0\uc9c0 \ubca0\uc5b4\ub9c1 \ub4f1 \uc73c\ub85c \uad6c\uc131 \uc81c\uc791\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0\uc740 \uadf8\ub9bc 3\uc5d0\uc11c\ucc98\ub7fc \uc81c\ucd08\n\uc6a9\uc73c\ub85c \ub9ce\uc774 \uc4f0\uc774\ub294 \uae38\uc774 120 mm, \ub450\uaed8 5 mm\uc758 \ud504\ub808\uc77c\ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \ud53c\uce58 70 mm \ub098\uc120\uc73c\ub85c \uc88c\uff65\uc6b0 \uac01\uac01 48\uac1c, \ucd1d 96\uac1c\ub97c \ubc30\uce58\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub0b4\uacbd 75 mm \uc911\uacf5\ucd95\uc778 \ud30c\uc1c4\ub0a0 \ucd95 \uc744 \ubca0\uc5b4\ub9c1\uc73c\ub85c \ub07c\uc6cc \ub9de\ucda4\ud558\uc5ec \uc88c, \uc6b0 \ud30c\uc1c4\ub0a0\ub4e4\uc744 \uac01\uac01 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ubd84\ub9ac \uad6c\ub3d9\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc740 \uadf8\ub9bc 4\uc5d0\uc11c\ucc98\ub7fc \ub05d\uc774 \ubfb0\uc871\ud55c \uae38\uc774 250 mm 6\uac1c \uc9c1\uc120\ub0a0\uc744 \uc6d0\uc8fc \ud53c\uce58\uac01 60\u00b0 \uac04\uaca9\uc73c\ub85c \ub192\uc774 \uc870\uc808\uc774 \uac00 \ub2a5\ud55c \ube0c\ub77c\ucf13\uc5d0 \ubd80\ucc29\ud558\uace0 \ube0c\ub77c\ucf13\uc744 \uc6d0\ud310\uc5d0 \uace0\uc815\ud558\uc600\ub2e4. \uc88c\uff65 \uc6b0\uff65\uc911\uc559 3\uacf3 6\uac1c\uc529 \ubaa8\ub450 18\uac1c\uc758 \ub0a0\uc744 \uc0ac\uc6a9\ud558\uc600\uc73c\uba70, \uccb4\uc778 \uc804 \ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9 \uc911\uacf5\ucd95 \uc548\uc758 \uc9c1\uacbd 35 mm \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\uc5ec \uac77\uc5b4\uc62c\ub9bc \uc791\uc6a9\uc744 \ud558\ub3c4\ub85d \ud558 \uc600\ub2e4.\n3) \ub3d9\ub825 \uc804\ub2ec\ubd80\n\ud2b8\ub799\ud130 PTO\uc5d0\uc11c \ucde8\ucd9c\ub41c \ub3d9\ub825\uc774 \uae30\uc5b4\ubc15\uc2a4\uc5d0\uc11c 2.5\ubc30\ub85c \uc99d \uc18d\ub418\uc5b4 \uad6c\ub3d9\ucd95 \uc88c\uff65\uc6b0\ub85c \ub098\ub258\uc5b4\uc838 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77 \uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uad6c\ub3d9\ud558\ub294 \uacfc\uc815\uc744 \uadf8\ub9bc 5\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \uad6c\ub3d9\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc6b0\uce21\uc758 \uad6c\ub3d9\ucd95\uc73c\ub85c", + "J. of Biosystems Eng. Vol. 36, No. 1.\n\ubd80\ud130 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\uc5d0 \uc758\ud558\uc5ec \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95 \uc548\uc5d0 \uc788\ub294 \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc744 \uc9c1\uc811 \uad6c\ub3d9\uc2dc\ud0a8\ub2e4. \uadf8\ub9bc 6\uc740 \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\ucd95\uc758 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \uc2dc\uc758 \ub3d9\ub825 \uc804\ub2ec \ubc29\ubc95\uc744 \ub098\ud0c0\ub0b8 \uac83\uc774\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \uc804\uc9c4\ubc29 \ud5a5 \ud68c\uc804(\uc815\ud68c\uc804)\uc740 \uae30\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c \ucf13\uacfc \uae30\uc5b4\uac00 \uc870\ud569\ub41c 2\uac1c\uc758 \ubc29\ud5a5\uc804\ud658 \ucd95\uacfc \ub369\uad74 \ud30c\uc1c4\ub0a0 \uad6c\ub3d9\n\ucd95\uc744 \uac70\uccd0 \uc911\uacf5\uc758 \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc \ud0a4\uace0, \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uc758 \ud2b8\ub799\ud130 \ud6c4\uc9c4\ubc29\ud5a5 \ud68c\uc804(\uc5ed\ud68c\uc804)\uc740 \uae30\n\uc5b4\ubc15\uc2a4 \uc88c\uce21\uc758 \uad6c\ub3d9\ucd95\uc5d0\uc11c \uccb4\uc778 \uc2a4\ud504\ub85c\ucf13\uacfc \ud150\uc158 \uc2a4\ud504\ub85c\ucf13\uc744\n\uac70\uccd0 \uc911\uacf5\uc758 \ud30c\uc1c4\ub0a0 \ucd95\uc744 \uccb4\uc778 \uc804\ub3d9\uc7a5\uce58\ub85c \uad6c\ub3d9\uc2dc\ud0a4\ub3c4\ub85d \ud558 \uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ucd95\uacfc \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \ucd95\uc758 \ud68c\uc804\uc18d\ub3c4\ube44\ub294 9 : 1\ub85c \uace0\ub791\uc5d0 \uc788\ub294 \ub3cc\uc5d0 \uc758\ud55c \ub369\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0 \uc190\uc0c1 \ubc0f \ub369\n\uad74 \uac77\uc5b4\uc62c\ub9bc\ub0a0\uc5d0 \uc758\ud55c \ube44\ub2d0\ud53c\ubcf5 \uc190\uc0c1 \ub4f1\uc758 \ubb38\uc81c\uc810\uc774 \ubc1c\uc0dd\ub420 \uc218\ub3c4 \uc788\uae30 \ub54c\ubb38\uc5d0 \ud68c\uc804\uc18d\ub3c4\uc758 \ucc28\uc774\uac00 \uc788\ub3c4\ub85d \ud558\uc600\ub2e4.\n4) \uc791\uc5c5\ub192\uc774 \uc870\uc808\ubd80\n\ub369\uad74\ucc98\ub9ac \uc791\uc5c5 \uc2dc \ub369\uad74 \ud30c\uc1c4\ubd80\uc758 \ud30c\uc1c4\ub192\uc774\ub97c \uc81c\uc5b4\ud558\uba70, \uace0 \ub791\uc744 \uc774\ud0c8\ud558\uc9c0 \uc54a\uace0 \uc791\uc5c5\uae30\uc758 \uc8fc\ud589 \uc548\uc815\uc131\uc744 \ub192\uc774\uae30 \uc704\ud558\uc5ec \uc124\uce58\ud55c \ubbf8\ub95c\uc758 \uad6c\uc870\ub97c \uadf8\ub9bc 7\uc5d0 \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \ubbf8\ub95c\uc740 \uc9c1\uacbd 400 mm, \ud3ed 100 mm\ub85c \ub450\ub451\uc758 \ud615\uc0c1\uc5d0 \ub530\ub77c \ub369\uad74\ud30c\uc1c4\ubd80\uc758\n\ub192\ub0ae\uc774\ub97c \uc704\ucabd\uc758 \ub808\ubc84\ub97c \ud68c\uc804\uc2dc\ucf1c \uc870\uc808\ud560 \uc218 \uc788\ub3c4\ub85d \ud558\uc600\uc73c \uba70, \ub192\uc774 \uc870\uc808\uc740 300 mm\uae4c\uc9c0 \uac00\ub2a5\ud558\ub3c4\ub85d \ud558\uc600\ub2e4. \ubbf8\ub95c\uc758 \uc124 \uce58 \uc704\uce58\ub294 \uc791\uc5c5\uae30 \ud6c4\ubc29 \uc791\uc5c5\uae30\ub97c \uc911\uc2ec\uc73c\ub85c \uc88c\uc6b0 2\uac1c, \ubbf8\ub95c \uc911 \uc2ec\uac04 \uac70\ub9ac\uac00 1400 mm\uac00 \ub418\ub3c4\ub85d \ubd80\ucc29\ud558\uc600\ub2e4.\n\ub098. \uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30 \uc131\ub2a5\uc2e4\ud5d8\n1) \uc2e4\ud5d8\ud3ec\uc7a5 \ubc0f \uc7ac\ub8cc\n\uace0\uad6c\ub9c8 \ub369\uad74\ucc98\ub9ac\uae30\uc758 \uc2e4\ud5d8 \uc911 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\uc5d0 \ub530\ub978 \ud30c\n\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c\ub9c8\ub294 \uc728\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758 \ud3c9 \uade0 \ud568\uc218\uc728\uc740 83.0%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \uc2e4\ud5d8\ud3ec\uc7a5\uc758 \ud1a0\uc131\uc740 \uc0ac\uc591 \ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 30 cm, \ub450\ub451\ub192 \uc774 25 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4. \uc8fc\ud589\uc18d\ub3c4 \ubc0f \ud30c\uc1c4\ub0a0 \ud68c\uc804\uc18d\ub3c4\ubcc4 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8 \ub300\uc0c1 \uace0\uad6c \ub9c8\ub294 \uc2e0\ud669\ubbf8 \ud488\uc885\uc73c\ub85c \uace0\uad6c\ub9c8 \ub369\uad74\uc758\ud3c9\uade0 \ud568\uc218\uc728\uc740 79.1%\ub85c \ub098\ud0c0\ub0ac\uc73c\uba70, \ud1a0\uc131\uc740 \uc0ac\uc9c8\ud1a0, \uc870\uac04\uac70\ub9ac 70 cm, \uc8fc\uac04\uac70\ub9ac 20 cm, \ub450\ub451\ud3ed 40 cm, \ub450\ub451\ub192\uc774 30 cm\ub85c \ub465\uadfc\ub450\ub451 \ube44\ub2d0\ud53c\ubcf5 \uc7ac\ubc30 \ud3ec\uc7a5\uc774\uc5c8\ub2e4.\n2) \uc2e4\ud5d8\ub0b4\uc6a9 \ubc0f \ubc29\ubc95\n\uac00) \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ub369\uad74 \ud30c\uc1c4\uc131\ub2a5 \uc2e4\ud5d8\n\ub369\uad74 \ud30c\uc1c4\ub0a0\uc758 \ud68c\uc804\ubc29\ud5a5\ubcc4 \ud30c\uc1c4\uc131\ub2a5\uc758 \ucc28\uc774\ub97c \uc870\uc0ac\ud558\uae30 \uc704\n\ud558\uc5ec \uc2e4\uc2dc\ud55c \uc2e4\ud5d8\uc73c\ub85c \ud2b8\ub799\ud130 \uc5d4\uc9c4 \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uc5d0 \ub530\ub77c \uc8fc \ud589\uc18d\ub3c4, PTO \ud68c\uc804\uc18d\ub3c4 \ubcc0\ud654\uac00 \uc5c6\ub3c4\ub85d \ud2b8\ub799\ud130 \uc5d4\uc9c4\uc18d\ub3c4\ub97c 2000 rpm\uc73c\ub85c \uace0\uc815\ud558\uace0, \uc8fc\ud589 \ubcc0\uc18d\ub2e8\uc218\ub97c Park and Choi (1995)\uac00 \ubcf4\uace0\ud55c \uc8fc\ud589\uc18d\ub3c4 0.35, 0.46 m/s\uc5d0\uc11c \uc8fc\ud589\uc18d\ub3c4\uac00 \ub0ae \uc744\uc218\ub85d \ub369\uad74 \ud30c\uc1c4\uc728\uc774 \ub192\uc558\uc73c\uba70, \ub18d\uac00\uc5d0\uc11c \uc8fc\ub85c \uc800\uc18d 1, 2\ub2e8 \uc744 \uc0ac\uc6a9\ud558\ub294 \uac83\uc744 \uace0\ub824\ud558\uc5ec \ubcf8 \uc2e4\ud5d8\ub3c4 \uc800\uc18d 1, 2\ub2e8\uc5d0 \ub9de\ucd94\uc5b4 \uc8fc\ud589\uc18d\ub3c4\ub97c \uac01\uac01 0.27, 0.37 m/s\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub369\uad74 \ud30c\uc1c4\ub0a0 \ud68c\uc804\ubc29\ud5a5 \uc815\ud68c\uc804, \uc5ed\ud68c\uc804 \ubcc0\uacbd\uc740 \uadf8\ub9bc 6\uc5d0\uc11c" + ] + }, + { + "image_filename": "designv8_17_0000183_f_version_1685352350-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000183_f_version_1685352350-Figure3-1.png", + "caption": "Figure 3. Schematic diagram of the structure of the eccentric PMs of the HCM. i re 3. ti i r f t e str ct re of the eccentric P s of the C .", + "texts": [ + " The equivalent current micro-elements \ud835\udc51\ud835\udc56 of the AB and CD sides and the AD side are then obtained: \ud835\udc51\ud835\udc56 = \ud835\udc3b cos \ud835\udf02 \ud835\udc51\ud835\udc4f\ud835\udc51\ud835\udc56 = \ud835\udc3b \ud835\udc45 sin \ud835\udefc \ud835\udc51\ud835\udefc\ud835\udc51\ud835\udc56 = \ud835\udc3b (\ud835\udc45 \u2212 \u210e ) sin \ud835\udefc \ud835\udc51\ud835\udefc, (4) where \ud835\udc3b is the coercivity, \ud835\udc51\ud835\udc4f is the radial length micro-element along the AB and CD sides, and \ud835\udc51\ud835\udefc is the angular micro-element along the circumferential direction. According to the above analysis, the motor structure parameters that affect the magnetic field distribution of the motor air gap are the PM thickness \u210e , the PM inner diameter \ud835\udc4f, the ORC inner diameter \ud835\udc45 , the IRC outer diameter \ud835\udc45 , and the motor pole pair number \ud835\udc43. Once the structural dimensions and the number of pole pairs of the HCM have been determined, its AMF can be practically changed by the eccentric structure of the PMs. Figure 3 shows a schematic diagram of the structure after the eccentric transformation of the inner diameter of the PMs. The centre O of the PM inner diameter is moved backwards along the PM centreline to the position of O\u2019. In order to avoid affecting the stator position, the new PM inner diameter has the same position of both end-points, and the new centre of the circle is O\u2019. Figure 3. Schematic diagram of the structure of the eccentric PMs of the HCM. Fig re 2. arallel ag etisi g tile s a t e e i ale t c rre t coil o el. The r maining coils can b calc lated in this way and then superimposed to obtain 2p pairs of the coil sets, pr duc g the following magnetic flux density expression: B(r, \u03b8) = \u00b50i \u03c0r \u221e \u2211 m=1 Rm o bm ( R2m i + b2m R2m o \u2212 R2m i )( rm Rm i + Rm i rm ) sin (m\u03b1)Z. (3) In the ESCM, the equivalent current along the radial side of the PM AB, CD is equal in magnitude and opposite in direction, and the equivalent currents along the AD and BC circumferences sides of the PMs are equal in magnitude and opposite in direction", + " The equivalent current micro-elements di of the AB and CD sides and the AD side are then obtained: diAB\u2212CD = Hcb cos \u03b7 db diBC = Hcb Ro sin \u03b1 d\u03b1 diAD = Hcb(R o \u2212 hm) sin \u03b1 d\u03b1 , (4) where Hcb is the coercivity, db is the radial length micro-element along the AB and CD sides, and d\u03b1 is the angular micro-element along the circumferential direction. According to the above analysis, the motor structure parameters that affect the magnetic field distribution of the motor air gap are the PM thickness hm, the PM inner diameter b, the ORC inner diameter Ro, the IRC outer diameter Ri, and the motor pole pair number P. Once the structural dimensions and the number of pole pairs of the HCM have been determined, its AMF can be practically changed by the eccentric structure of the PMs. Figure 3 shows a schematic diagram of the structure after the eccentric transformation of the inner diameter of the PMs. The centre O of the PM inner diameter is moved backwards along the PM centreline to the position of O\u2019. In order to avoid affecting the stator position, the new PM inner diameter has the same position of both end-points, and the new centre of the circle is O\u2019. Appl. Sci. 2023, 13, 6537 5 of 13 Figure 2. Parallel magnetising tile PMs and the equivalent current coil model. In the ESCM, the equivalent current along the radial side of the PM AB, CD is equal in magnitude and opposite in direction, and the equivalent currents along the AD and BC circumferences sides of the PMs are equal in magnitude and opposite in direction", + " The equivalent current micro-elements \ud835\udc51\ud835\udc56 of the AB and CD sides and the AD side are then obta ned: \ud835\udc51\ud835\udc56 = \ud835\udc3b cos \ud835\udf02 \ud835\udc51\ud835\udc4f\ud835\udc51\ud835\udc56 = \ud835\udc3b \ud835\udc45 sin \ud835\udefc \ud835\udc51\ud835\udefc\ud835\udc51\ud835\udc56 = \ud835\udc3b (\ud835\udc45 \u2212 \u210e ) sin \ud835\udefc \ud835\udc51\ud835\udefc, (4) where \ud835\udc3b is the coercivity, \ud835\udc51\ud835\udc4f is the radial length micro-element along the AB and CD sides, and \ud835\udc51\ud835\udefc is the angular micro-element along the circumferential direction. According to the above analysis, the motor structure parameters that affect the magnetic field distribution of the motor air gap are the PM thickness \u210e , the PM inner diameter \ud835\udc4f, the ORC inner diameter \ud835\udc45 , the IRC outer diameter \ud835\udc45 , and the motor pole pair number \ud835\udc43. Once the structural dimensions and the number of pole pairs of the HCM have been determined, its AMF can be practically changed by the eccentric structure of the PMs. Figure 3 shows a schematic diagram of the structure after the eccentric transformation of the inner diameter of the PMs. The centre O of the PM inner diameter is moved backwards along the PM centreline to the position of O\u2019. In order to avoid affecting the stator position, the new PM inner diameter has the same position of both end-points, and the new centre of the circle is O\u2019. After geometric operations, the coordinates of a point A (b(\u03b1), \u03b1\u2032) on the new inner diameter can be obtained asb(\u03b1) = \u221a (Ro \u2212 hm \u2212 \u03bb)2 + \u03bb2 \u2212 2\u03bb(Ro \u2212 hm \u2212 \u03bb)cos(\u03b1\u2032) \u03b1\u2032 = \u03b1\u2212 arcsin \u03bbsin(\u03b1) Ro\u2212hm\u2212\u03bb , (5) where \u03bb is the eccentricity of the inner diameter of the PMs, which is the length of the line OO\u2019 in Figure 3. Substituting Equations (4) and (5) into Equation (3), the micro-element of the AMF strength generated by the equivalent current on each side of the PMs at a point (r, \u03b8) in the air gap after the eccentric optimised design can be obtained as dBAB\u2212CD = \u00b50Hcbcos \u03b7db(\u03b1) \u03c0r \u221e \u2211 m=1 Rm o b(\u03b1)m ( R2m i + b ( \u03b1)2m R2m o \u2212 R2m i )( rm Rm i + Rm i rm ) sin(m\u03b7)Z dBBC = \u00b50HcbRo sin \u03b1\u2032d\u03b1 \u03c0r \u221e \u2211 m=1 ( R2m i + R2m o R2m o \u2212 R2m i )( rm Rm i + Rm i rm ) sin(m\u03b1\u2032)Zd\u03b1\u2032 dBAD = \u00b50HcbRo sin \u03b1\u2032d\u03b1 \u03c0r \u221e \u2211 m=1 Rm o b(\u03b1)m ( R2m i + b ( \u03b1)2m R2m o \u2212 R2m i )( rm Rm i + Rm i rm ) sin(m\u03b1\u2032)Zd\u03b1\u2032 ", + " Finite Element Simulation Verification In this paper, in order to evaluate the width of flat section of the AMF, the parameter \u03c4 is introduced, which is defined as the proportion of the top part to the half waveform width [25], as shown in Figure 4: \u03c4 = \u03b8p \u03b1p , (8) where \u03b8p is the part of the AMF that lies above 99% of the maximum value Bmax of the AMF in one cycle, and \u03b1p is the width of the half-cycle of the waveform. Appl. Sci. 2023, 13, 6537 6 of 13 After geometric operations, the coordinates of a point A (\ud835\udc4f(\ud835\udefc), \ud835\udefc\u2032) on the new inner diameter can be obtained as \ud835\udc4f(\ud835\udefc) = (\ud835\udc45 \u2212 \u210e \u2212 \ud835\udf06) + \ud835\udf06 \u2212 2\ud835\udf06(\ud835\udc45 \u2212 \u210e \u2212 \ud835\udf06) \ud835\udc50\ud835\udc5c\ud835\udc60(\ud835\udefc )\ud835\udefc\u2032 = \ud835\udefc \u2212 \ud835\udc4e\ud835\udc5f\ud835\udc50\ud835\udc60\ud835\udc56\ud835\udc5b \ud835\udf06 \ud835\udc60\ud835\udc56\ud835\udc5b( \ud835\udefc)\ud835\udc45 \u2212 \u210e \u2212 \ud835\udf06 , (5) where \ud835\udf06 is the eccentricity of the inner diameter of the PMs, which is the length of the line OO\u2019 in Figure 3. Substituting Equations (4) and (5) into Equation (3), the micro-element of the AMF strength generated by the equivalent current on each side of the PMs at a point (\ud835\udc5f, \ud835\udf03) in the air gap after the eccentric optimised design can be obtained as \u23a9\u23aa\u23aa\u23aa \u23a8\u23aa \u23aa\u23aa\u23a7\ud835\udc51\ud835\udc35 = \ud835\udf07 \ud835\udc3b \ud835\udc50\ud835\udc5c\ud835\udc60 \ud835\udf02 \ud835\udc51\ud835\udc4f(\ud835\udefc)\ud835\udf0b\ud835\udc5f \ud835\udc45\ud835\udc4f(\ud835\udefc) \ud835\udc45 + \ud835\udc4f(\ud835\udefc)\ud835\udc45 \u2212 \ud835\udc45 \ud835\udc5f\ud835\udc45 + \ud835\udc45\ud835\udc5f \ud835\udc60\ud835\udc56\ud835\udc5b( \ud835\udc5a\ud835\udf02)\ud835\udc4d \ud835\udc51\ud835\udc35 = \ud835\udf07 \ud835\udc3b \ud835\udc45 sin\ud835\udefc\u2032\ud835\udc51\ud835\udefc\ud835\udf0b\ud835\udc5f \ud835\udc45 + \ud835\udc45\ud835\udc45 \u2212 \ud835\udc45 \ud835\udc5f\ud835\udc45 + \ud835\udc45\ud835\udc5f \ud835\udc60\ud835\udc56\ud835\udc5b( \ud835\udc5a\ud835\udefc\u2032)\ud835\udc4d \ud835\udc51\ud835\udefc\u2032 \ud835\udc51\ud835\udc35 = \ud835\udf07 \ud835\udc3b \ud835\udc45 sin\ud835\udefc\u2032\ud835\udc51\ud835\udefc\ud835\udf0b\ud835\udc5f \ud835\udc45\ud835\udc4f(\ud835\udefc) \ud835\udc45 + \ud835\udc4f(\ud835\udefc)\ud835\udc45 \u2212 \ud835\udc45 \ud835\udc5f\ud835\udc45 + \ud835\udc45\ud835\udc5f \ud835\udc60\ud835\udc56\ud835\udc5b( \ud835\udc5a\ud835\udefc\u2032)\ud835\udc4d\ud835\udc51\ud835\udefc\u2032 . (6) The magnetic field strength at a point (\ud835\udc5f, \ud835\udf03) in the air gap can be obtained by summing the PM thickness integral along the AB\u2013CD edge and the PM tensor angle integral along the BC and AD edges: \ud835\udc35(\ud835\udc5f, \ud835\udf03) = \ud835\udc51\ud835\udc35 + \ud835\udc51\ud835\udc35 + \ud835\udc51\ud835\udc35 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003052_26_8_126_8_1086__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003052_26_8_126_8_1086__pdf-Figure4-1.png", + "caption": "Fig. 4. Kinematic model of two-wheeled vehicle.", + "texts": [], + "surrounding_texts": [ + "\u4e8b\u8c61\u99c6\u52d5\u578b\u5236\u5fa1\u5668\u306b\u3088\u308b\u5236\u5fa1\u7cfb\u8a2d\u8a08\n\u30082\u30fb3\u30fb1\u3009 \u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u540c\u5b9a \u3053\u3053\u3067\u306f\uff0cB\u884c\u5217 \u306e\u8981\u7d20\u304c\u672a\u77e5\u3067\u3042\u308b\u5834\u5408\uff0c\u305d\u308c\u3092\u4f4e\u5206\u89e3\u80fd\u5165\u51fa\u529b\u304b\u3089\u540c\u5b9a \u3059\u308b\u65b9\u6cd5\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\u3002\u3053\u306e\u624b\u6cd5\u306f\uff0c\u6587\u732e (7)\uff0c(9)\u3067\u793a\n\u3055\u308c\u3066\u3044\u308b\u9023\u7d9a\u6642\u9593\u7cfb\u3067\u306e\u7d50\u679c\u3092\u62e1\u5f35\u3057\u305f\u3082\u306e\u3067\u3042\u308b\u3002 \u6642\u523b j\u3067\u89b3\u6e2c\u5024 y( j)\u304c\u5f97\u3089\u308c\u305f\u3068\u3059\u308b\u3068\uff0c(1)\u5f0f\u3092\u89e3\u3044\u3066\uff0c\ny( j) = C j\u22121\u220f i=0 A (u( j)) x(0)\n+ C j\u22122\u2211 i=0\n\u239b\u239c\u239c\u239c\u239c\u239c\u239c\u239d j\u22121\u220f\nk=i+1\nA (u(k)) \u239e\u239f\u239f\u239f\u239f\u239f\u239f\u23a0 Bu(i)\n+ CBu( j \u2212 1) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (4)\n\u304c\u5f97\u3089\u308c\u308b\u3002\u3053\u3053\u3067\uff0cBu( j)\u306b\u6ce8\u76ee\u3059\u308b\u3068\uff0c\nBu( j) = \u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 b1u( j) ...\nbnu( j)\n\u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (5)\n= \u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 u( j)T 0 . . .\n0 u( j)T\n\u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 \u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 bT 1 ...\nbT n\n\u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (6)\n\u3068\u306a\u308b\u3002\u3053\u3053\u3067\uff0cbi\u306f B\u306e i\u756a\u76ee\u306e\u884c\u30d9\u30af\u30c8\u30eb\u3067\u3042\u308b\u3002(4)\uff0c (6)\u5f0f\u3088\u308a\uff0c\u89b3\u6e2c\u5024 y( j)\u306f\u521d\u671f\u72b6\u614b x(0)\u3068\u884c\u5217 B\u306e\u8981\u7d20\u306e\n\u7dda\u5f62\u548c\u3067\u8868\u305b\u308b\u3053\u3068\u304c\u308f\u304b\u308b\u3002 \u3057\u305f\u304c\u3063\u3066\uff0cM\u56de\u89b3\u6e2c\u5024\u304c\u5f97\u3089\u308c\u305f\u3068\u304d\uff0c\u305d\u308c\u305e\u308c\u306e\u89b3 \u6e2c\u5024\u3092 y( j1), \u00b7 \u00b7 \u00b7 , y( jM)\u3068\u3059\u308b\u3068\uff0c\u6b21\u5f0f\u304c\u6210\u308a\u7acb\u3064\u3002\n\u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 y( j1) ...\ny( jM)\n\u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 = Ob \u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 x(0) bT 1 ...\nbT n\n\u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (7)\n\u3053\u3053\u3067\uff0cOb\u306f (4)\uff0c(6)\u5f0f\u3088\u308a\u5b9a\u307e\u308b\u4fc2\u6570\u884c\u5217\u3067\u3042\u308b\u3002\u3053\u306e \u4fc2\u6570\u884c\u5217\u306e\u30e9\u30f3\u30af\u304c n+mn\u306e\u3068\u304d\uff0c\u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf x(0)\uff0cB \u3092\u540c\u5b9a\u3067\u304d\u308b\u3002\u540c\u5b9a\u3067\u304d\u308b\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u4e2d\u306b\u521d\u671f\u72b6\u614b x(0)\n\u304c\u542b\u307e\u308c\u3066\u3044\u308b\u306e\u3067\uff0crank(Ob) = n+mn\u304c\u6e80\u305f\u3055\u308c\u308b\u306a\u3089 \u3070\u53ef\u89b3\u6e2c\u3067\u3042\u308b\u3053\u3068\u3082\u8a00\u3048\u308b\u3002\n\u3053\u306e\u3068\u304d\uff0cB\u306e\u3044\u304f\u3064\u304b\u306e\u8981\u7d20\u304c\u65e2\u77e5\u3067\u3042\u3063\u305f\u308a\uff0c\u30d1\u30e9 \u30e1\u30fc\u30bf \u03b1\u304c\u3042\u308b\u6761\u4ef6\u3092\u6e80\u305f\u3057\u3066\u3044\u308b\u5834\u5408\uff0c\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u540c \u5b9a\u306b\u5fc5\u8981\u306a\u89b3\u6e2c\u306e\u56de\u6570\u306f\u3088\u308a\u5c11\u306a\u304f\u306a\u308b\u3002\u9023\u7d9a\u6642\u9593\u7cfb\u3067\u306e \u7d50\u679c\u306b\u3064\u3044\u3066\u306f\u6587\u732e (7)\u3092\u53c2\u7167\u3055\u308c\u305f\u3044\u3002 \u30082\u30fb4\u3009 \u5236\u5fa1\u8ad6\u7406 \u672c\u8ad6\u6587\u3067\u306f\uff0c\u30bb\u30f3\u30b5\u3084\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\n\u30bf\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u306f\u8a2d\u8a08\u5bfe\u8c61\u3067\u3042\u308b\u304c\uff0c\u5236\u5fa1\u8ad6\u7406\u306f\u3042\u3089\u304b\u3058 \u3081\u51fa\u6765\u4e0a\u304c\u3063\u3066\u3044\u308b\u3068\u3059\u308b\u3002\u672c\u8ad6\u6587\u3067\u8003\u3048\u3066\u3044\u308b\u5236\u5fa1\u7cfb\u3067 \u306f\uff0c\u5236\u5fa1\u8ad6\u7406\u306f\u73fe\u5728\u306e\u30bb\u30f3\u30b5\u306eON/OFF\uff0c\u3053\u308c\u307e\u3067\u306e\u5165\u529b\u306a \u3069\u304b\u3089\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e ON/OFF\u3092\u6c7a\u5b9a\u3059\u308b\u3082\u306e\u3067\u3042\u308a\uff0c\n\u3053\u308c\u306f\u8ad6\u7406\u6f14\u7b97\u3084\u6761\u4ef6\u5206\u5c90\u306a\u3069\u3092\u7528\u3044\u3066\u8a18\u8ff0\u3055\u308c\u308b\u3053\u3068\u306b \u306a\u308b\u3002 \u307e\u305f\uff0c\u5236\u5fa1\u5bfe\u8c61\u306b\u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf\u304c\u5b58\u5728\u3059\u308b\u5834\u5408\u306f\uff0c\u305d \u308c\u3092\u540c\u5b9a\u3059\u308b\u90e8\u5206\u3068\uff0c\u540c\u5b9a\u3057\u305f\u30d1\u30e9\u30e1\u30fc\u30bf\u3092\u7528\u3044\u3066\u5236\u5fa1\u3092\n\u884c\u3046\u90e8\u5206\u306b\u5206\u3051\u306a\u3051\u308c\u3070\u306a\u3089\u306a\u3044\u3002\u3057\u305f\u304c\u3063\u3066\uff0c\u5236\u5fa1\u7cfb\u306e \u8a2d\u8a08\u304a\u3088\u3073\u5b9f\u969b\u306e\u5236\u5fa1\u306e\u624b\u9806\u306f\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u306a\u308b\u3002\n\u8a2d\u8a08 \uff08 1\uff09 \u5236\u5fa1\u8ad6\u7406\u3092\u8a2d\u8a08\u3059\u308b\n\uff08 2\uff09 \u5236\u5fa1\u5bfe\u8c61\u306e\u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf \u03b1\u304c\u65e2\u77e5\u3068\u4eee\u5b9a\u3057\uff0c\u30bb \u30f3\u30b5\u30fb\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u3092\u8a2d\u8a08\u3059\u308b\u3002\u3053 \u308c\u3092\u3044\u304f\u3064\u304b\u306e \u03b1\u306b\u5bfe\u3057\u3066\u884c\u3046\u3002\n\u5236\u5fa1\n\uff08 3\uff09 \u5b9f\u969b\u306b\u5236\u5fa1\u7cfb\u3092\u52d5\u4f5c\u3055\u305b\u305f\u3089\uff0c\u307e\u305a\u672a\u77e5\u30d1\u30e9\u30e1\u30fc \u30bf\u3092\u540c\u5b9a\u3059\u308b\u3002\n\uff08 4\uff09 \u540c\u5b9a\u3057\u305f\u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf\u306b\u5bfe\u3057\u3066 (2)\u3067\u8a2d\u8a08\u3057\u3066 \u304a\u3044\u305f\u30bb\u30f3\u30b5\u30fb\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u3092\u9069\u7528\n\u3059\u308b\u3002\u3053\u306e\u3068\u304d\uff0c\u89b3\u6e2c\u5024\u304c\u5f97\u3089\u308c\u308b\u305f\u3073\u306b\u672a\u77e5\u30d1\u30e9 \u30e1\u30fc\u30bf\u3092\u540c\u5b9a\u3057\uff0c\u5024\u304c\u5909\u5316\u3057\u305f\u3089\u30d1\u30e9\u30e1\u30fc\u30bf\u3082\u5909\u5316 \u3055\u305b\u308b\u3002\n3. Mixed Logical Dynamical System\uff08MLDS\uff09\u306b \u3088\u308b\u8868\u73fe\u3068\u6700\u9069\u8a2d\u8a08\nMLD\uff08Mixed Logical Dynamical System\uff09\u3068\u306f\uff0c\u8ad6\u7406\u3084\n\u4e0d\u9023\u7d9a\u6027\u3092\u542b\u3093\u3060\u5236\u5fa1\u7cfb\u3092\uff0c\u88dc\u52a9\u8ad6\u7406\u5909\u6570\u3084\u88dc\u52a9\u5909\u6570\u3092\u5c0e \u5165\u3059\u308b\u3053\u3068\u3067\u7dda\u5f62\u5236\u7d04\u3092\u4f34\u3046\u7dda\u5f62\u96e2\u6563\u6642\u9593\u30b7\u30b9\u30c6\u30e0\u3068\u3057\u3066 \u8868\u73fe\u3057\u305f\u3082\u306e\u3067\u3042\u308b\u3002 \u6587\u732e (10)\u3067\u306f\uff0cMLD\u304c\uff0c\u7dda\u5f62\u30cf\u30a4\u30d6\u30ea\u30c3\u30c9\u30b7\u30b9\u30c6\u30e0\uff0c\u6709\n\u9650\u30aa\u30fc\u30c8\u30de\u30c8\u30f3\uff0c\u3042\u308b\u30af\u30e9\u30b9\u306e\u96e2\u6563\u4e8b\u8c61\u30b7\u30b9\u30c6\u30e0\uff0c\u5236\u7d04\u3092 \u6301\u3064\u7dda\u5f62\u30b7\u30b9\u30c6\u30e0\uff0c\u533a\u5206\u7dda\u5f62\uff08Piecewise Affine\uff0cPWA\uff09\u30b7 \u30b9\u30c6\u30e0\uff0cPWA \u30b7\u30b9\u30c6\u30e0\u306b\u3088\u3063\u3066\u8fd1\u4f3c\u3055\u308c\u308b\u975e\u7dda\u5f62\u30b7\u30b9\u30c6 \u30e0\u306a\u3069\u3092\u8868\u73fe\u3067\u304d\u308b\u5f62\u5f0f\u3067\u3042\u308b\u3053\u3068\u304c\u8ff0\u3079\u3089\u308c\u3066\u3044\u308b\u3002\u307e\n\u305f\uff0c\u76f8\u4e92\u4f9d\u5b58\u3059\u308b\u7269\u7406\u6cd5\u5247\uff0c\u8ad6\u7406\u7684\u6cd5\u5247\uff0c\u52d5\u4f5c\u5236\u7d04\u306b\u3088\u3063\u3066 \u8a18\u8ff0\u3055\u308c\u308b\u7cfb\u3092MLDS\u306b\u5909\u63db\u3059\u308b\u30a2\u30eb\u30b4\u30ea\u30ba\u30e0\u3084\uff0cMLD\n\u3092\u7528\u3044\u3066\u5236\u5fa1\u3092\u884c\u3046\u305f\u3081\u306e\u67a0\u7d44\u307f\u306b\u3064\u3044\u3066\u3082\u8ff0\u3079\u3089\u308c\u3066\u3044 \u308b\u3002\u3053\u306e\u67a0\u7d44\u307f\u306e\u4e2d\u3067\u306f\uff0c\u8ad6\u7406\u3084\u4e0d\u9023\u7d9a\u6027\u3092\u542b\u3093\u3060\u5236\u5fa1\u7cfb\u3092\nMLDS\u3078\u3068\u5909\u63db\u3059\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u30e2\u30c7\u30eb\u4e88\u6e2c\u5236\u5fa1\u3092\u7528\u3044\u305f \u5236\u5fa1\u554f\u984c\u3092\u6df7\u5408\u6574\u6570\u4e8c\u6b21\u8a08\u753b\u554f\u984c\uff08Mixed Integer Quadratic\nProgramming\uff0cMIQP\uff09\u3068\u3057\u3066\u5b9a\u5f0f\u5316\u3057\uff0c\u305d\u306e\u6700\u9069\u5316\u554f\u984c\u3092 \u89e3\u304f\u3053\u3068\u306b\u3088\u308a\u6700\u9069\u306a\u5236\u5fa1\u3092\u884c\u3046\u624b\u6cd5\u304c\u793a\u3055\u308c\u3066\u3044\u308b\u3002\n\u3053\u306e\u6587\u732e\u3067\u306f\uff0c\u3042\u3089\u304b\u3058\u3081\u5b9a\u3081\u305f\u7bc4\u56f2\u304b\u3089\u6700\u9069\u306a\u5165\u529b\u3092 \u6700\u9069\u5316\u306b\u3088\u308a\u9078\u3076\u624b\u6cd5\u306b\u3064\u3044\u3066\u8ff0\u3079\u3089\u308c\u3066\u3044\u308b\u3002\u305d\u308c\u306b\u5bfe \u3057\u672c\u8ad6\u6587\u3067\u306f\uff0c\u30bb\u30f3\u30b5\u3084\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u8a2d \u8a08\u304c\u3067\u304d\u308b\u3088\u3046MLD\u3092\u62e1\u5f35\u3057\u305f\u3002\u4ee5\u4e0b\u3067\u305d\u306e\u6982\u8981\u306b\u3064\u3044\n\u3066\u8ff0\u3079\u308b\u3002 \u6700\u521d\u306b\uff0c\u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf \u03b1\u304c\u540c\u5b9a\u3067\u304d\u3066\u3044\u308b\u3068\u3059\u308b\u3002(2) \u5f0f\u306b\u5bfe\u3057\uff0c[A(u) = Ai] \u2194 [\u03b4i = 1] \u3092\u6e80\u305f\u3059\u4e8c\u5024\u5909\u6570 \u03b4i \u2208 {0, 1} , i = 1, \u00b7 \u00b7 \u00b7 ,NA \u3092\u5c0e\u5165\u3059\u308b\u3068\uff0c\u3053\u306e\u5f0f\u306f\nx( j + 1) = NA\u2211 i=1 (Aix( j) + Bu) \u03b4i, [\u03b4i = 1]\u2192 u \u2208 Ui \u2229 U, NA\u2211 i=1 \u03b4i = 1,\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (8)\n\u3068\u306a\u308b\u3002\u3053\u306e\u5f0f\u306f PWA\u5f62\u5f0f\u306e\u72b6\u614b\u65b9\u7a0b\u5f0f\u3068\u306a\u3063\u3066\u3044\u308b\u3002 \u307e\u305f\uff0c\u51fa\u529b\u306e y\u3068 yl \u306e\u95a2\u4fc2\u306f fy \u3067\u8868\u3055\u308c\u308b\u304c\uff0c\u3053\u308c\u3092\n\u96fb\u5b66\u8ad6 D\uff0c126 \u5dfb 8 \u53f7\uff0c2006 \u5e74 1089", + "\u9023\u7acb\u4e0d\u7b49\u5f0f\u3067\u8868\u305b\u308b\u3068\u3059\u308b\u3068\uff0c[ fy(y) = yl,i ] \u21d4 [ Siy \u2264 Ri ]\n\u21d4 [ SiCx + Si D\u03b1y \u2264 Ri ] \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (9)\n\u3068\u306a\u308b\u3002\u3053\u3053\u3067\uff0cSi, Ri, i = 1, \u00b7 \u00b7 \u00b7 ,Nyl \u306f i\u756a\u76ee\u306e\u30bb\u30f3\u30b5\u304c ON\u3068\u306a\u308b\u6761\u4ef6\u3092\u8868\u3059\u884c\u5217\u3067\u3042\u308a\uff0c\u4e0d\u7b49\u5f0f\u306f\u8981\u7d20\u3054\u3068\u306b\u6210 \u7acb\u3057\u3066\u3044\u308b\u3082\u306e\u3068\u3059\u308b\u3002\u3053\u306e\u4e0d\u7b49\u5f0f\u306f\u56f3 3\u306e\u5404\u9818\u57df\u3092\u8868\u3057 \u3066\u3044\u308b\u3068\u8003\u3048\u308c\u3070\u3088\u3044\u3002\u307e\u305f\uff0c\u03b1y\u306f\u8a2d\u8a08\u5bfe\u8c61\u3068\u306a\u308b\u30bb\u30f3\u30b5 \u30d1\u30e9\u30e1\u30fc\u30bf\u3068\u306a\u308b\u3002\n\u3053\u308c\u3089\uff0c\u533a\u5206\u7dda\u5f62\u306e\u72b6\u614b\u65b9\u7a0b\u5f0f\u3084\u8ad6\u7406\u6f14\u7b97\u306a\u3069\u306f MLD\n\u3078\u5909\u63db\u3067\u304d\u308b\uff08\u5909\u63db\u65b9\u6cd5\u306b\u3064\u3044\u3066\u306f\u6587\u732e (10)\u3092\u53c2\u7167\u3055\u308c\u305f \u3044\uff09\u3002\u7d50\u679c\u3068\u3057\u3066\uff0c\u672c\u8ad6\u6587\u3067\u8003\u3048\u3066\u3044\u308b\u56f3 1\u306b\u793a\u3059\u5236\u5fa1\u7cfb\u306b \u5bfe\u3059\u308bMLD\u306f\u6b21\u5f0f\u3068\u306a\u308b\u3002\u23a7\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23a8\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23a9 x( j + 1) = Bz, j z( j) Ex, jx( j) + Ez, j z( j) + Eul , jul( j) + E\u03b4, j\u03b4( j)\n+Eul, j\u22121ul( j \u2212 1) + Eyl, jyl( j) + E\u03b1\u03b1y +Euu\u0303 \u2264 Econst\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (10)\n\u3053\u3053\u3067\uff0cz\u306fMLD\u3078\u306e\u5909\u63db\u306e\u969b\u306b\u5c0e\u5165\u3055\u308c\u308b\u88dc\u52a9\u7684\u306a\u9023 \u7d9a\u5909\u6570\u3067\u3042\u308a\uff0c\nz( j) = \u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 (Aix( j) + Bu) \u03b41 ...\n(Aix( j) + Bu) \u03b4NA\n\u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (11)\n\u3067\u3042\u308b\u3002\u03b4i \u2208 {0, 1}\u3092\u7528\u3044\u308b\u3068\uff0c\u53f3\u8fba\u306e\u7a4d\u3092\u4e0d\u7b49\u5f0f\u306b\u7f6e\u304d\u63db \u3048\u308b\u3053\u3068\u304c\u3067\u304d\uff0c\u305d\u308c\u3089\u306f (10)\u5f0f\u306e\u4e0d\u7b49\u5f0f\u306e\u4e2d\u306b\u73fe\u308c\u308b\u3002\n\u307e\u305f\uff0c\u03b4 = [ \u03b41, \u00b7 \u00b7 \u00b7 , \u03b4NA ]T\uff0cu\u0303 = [ uT 1 \u00b7 \u00b7 \u00b7uT Nu ]T \u3067\u3042\u308a\uff0c\u884c\u5217\nE \u306e\u6dfb\u5b57\u306f\uff0c\u639b\u304b\u3063\u3066\u3044\u308b\u5909\u6570\u3068\u305d\u306e\u6642\u523b\u3092\u8868\u3057\u3066\u3044\u308b\u3002 u\u0303\u306f\u53d6\u308a\u5f97\u308b\u5165\u529b\u5024\u306e\u96c6\u5408 U \u306e\u8981\u7d20\u3092\u30d9\u30af\u30c8\u30eb\u3067\u8868\u3057\u305f\u3082 \u306e\u3067\uff0c\u5236\u5fa1\u3092\u901a\u3057\u3066\u4e00\u5b9a\u306e\u5024\u3092\u53d6\u308b\u6642\u4e0d\u5909\u306e\u30d9\u30af\u30c8\u30eb\u3067\u3042\n\u308b\u3002ul \u306b\u5bfe\u3059\u308b\u9805\u304c\u4e8c\u3064\u3042\u308b\u306e\u306f\uff0c\u73fe\u5728\u306e\u5236\u5fa1\u5165\u529b\u304c\u904e\u53bb \u306e\u5236\u5fa1\u5165\u529b\u306b\u4f9d\u5b58\u3059\u308b\u52d5\u4f5c\u3092\u8868\u3059\u305f\u3081\u3067\u3042\u308a\uff0c\u3053\u306e\u90e8\u5206\u306f \u5236\u5fa1\u5247\u306e\u5236\u5fa1\u8ad6\u7406\u306b\u3088\u308a\u7570\u306a\u308b\u3002(10)\u5f0f\u306b\u304a\u3044\u3066\uff0c\u8ad6\u7406\u6761 \u4ef6\u306f\u7b49\u4fa1\u306a\u4e0d\u7b49\u5f0f\u306b\u5909\u63db\u3055\u308c\u3066\u3044\u308b\u305f\u3081\uff0c\u660e\u793a\u7684\u306b\u306f\u8868\u3055\n\u308c\u3066\u3044\u306a\u3044\u3053\u3068\u306b\u6ce8\u610f\u3055\u308c\u305f\u3044\u3002 MLD\u5f62\u5f0f\u306e\u30e2\u30c7\u30eb\u304c\u5f97\u3089\u308c\u305f\u3089\uff0c\u6700\u9069\u5316\u3057\u305f\u3044\u8a55\u4fa1\u95a2 \u6570 J \u3068\u8a55\u4fa1\u3059\u308b\u533a\u9593 j f \u3092\u6c7a\u5b9a\u3059\u308b\u3002\u8a55\u4fa1\u95a2\u6570\u306f\u5909\u6570\u306b\u5bfe \u3057\u3066\u4e8c\u6b21\u307e\u305f\u306f\u4e00\u6b21\u306e\u95a2\u6570\u3068\u3057\uff0c\u5236\u5fa1\u306e\u76ee\u7684\u3092\u53cd\u6620\u3055\u305b\u305f\n\u3082\u306e\u3068\u3059\u308b\u3002\u4e8c\u6b21\u306a\u3089\u3070\u6df7\u5408\u6574\u6570\u4e8c\u6b21\u8a08\u753b\u554f\u984c\uff0c\u4e00\u6b21\u306a\u3089 \u3070\u6df7\u5408\u6574\u6570\u7dda\u5f62\u8a08\u753b\u554f\u984c\u3068\u306a\u308b\u3002 \u3053\u308c\u3089\u306e\u8b70\u8ad6\u3092\u3075\u307e\u3048\u308b\u3068\uff0c\u30bb\u30f3\u30b5\u3084\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30d1\n\u30e9\u30e1\u30fc\u30bf\u306e\u8a2d\u8a08\u554f\u984c\u306f\uff0c\u4ee5\u4e0b\u306e\u6570\u7406\u8a08\u753b\u554f\u984c\u306b\u5e30\u7740\u3067\u304d\u308b\u3002\nGiven x(0), ul(0), j f ,\u03b1 find \u03b1y, u\u0303 which minimize J\nsubject to (10)\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (12)\n\u3053\u306e\u554f\u984c\u3092\u89e3\u3044\u3066\u5f97\u3089\u308c\u308b \u03b1y\uff0cu\u0303\u304c\uff0c\u6700\u9069\u306a\u30bb\u30f3\u30b5\u30fb\u30a2\u30af\n\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u3068\u306a\u308b\u3002 \u6df7\u5408\u6574\u6570\u8a08\u753b\u554f\u984c\u306e\u4ee3\u8868\u7684\u306a\u89e3\u6cd5\u3068\u3057\u3066\u5206\u679d\u9650\u5b9a\u6cd5\u304c\u3042\n\u3052\u3089\u308c\u308b\u3002\u8a73\u7d30\u306b\u3064\u3044\u3066\u306f\u6587\u732e (11)\u306a\u3069\u3092\u53c2\u7167\u3055\u308c\u305f\u3044\u3002\n4. \u4e8c\u8f2a\u8d70\u884c\u8eca\u4e21\u306e\u30e9\u30a4\u30f3\u8ffd\u5f93\u5236\u5fa1\u306b\u304a\u3051\u308b\u30d1\u30e9\u30e1\u30fc \u30bf\u306e\u6700\u9069\u8a2d\u8a08\n\u672c\u7ae0\u3067\u306f\uff0c\u3053\u308c\u307e\u3067\u306e\u7ae0\u3067\u8ff0\u3079\u3066\u304d\u305f\u624b\u6cd5\u3092\u4e8c\u8f2a\u8d70\u884c\u8eca \u4e21\u306e\u30e9\u30a4\u30f3\u8ffd\u5f93\u5236\u5fa1\u554f\u984c\u306b\u9069\u7528\u3057\u305f\u4f8b\u3092\u793a\u3059\u3002\n\u30084\u30fb1\u3009 \u5236\u5fa1\u7cfb\u306e\u30e2\u30c7\u30eb \u5236\u5fa1\u5bfe\u8c61\u3092\u56f3 4\u306b\u793a\u3059\u3002\u3053 \u306e\u5236\u5fa1\u7cfb\u3067\u306f\uff0c\u30bb\u30f3\u30b5\uff0c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306f\u3068\u3082\u306b\u4f4e\u5206\u89e3\u80fd \u3067\u3042\u308a\uff0c2\u3064\u3042\u308b\u30bb\u30f3\u30b5\u306f\u305d\u308c\u305e\u308c\u30e9\u30a4\u30f3\u4e0a/\u30e9\u30a4\u30f3\u5916\u306e\u307f \u3092\u89b3\u6e2c\u3067\u304d\uff0c\u30e9\u30a4\u30f3\u4e0a\u306e\u3069\u306e\u4f4d\u7f6e\u306b\u3044\u308b\u304b\u3068\u3044\u3046\u60c5\u5831\u306f\u89b3\n\u6e2c\u3067\u304d\u306a\u3044\u3068\u3059\u308b\u3002\u307e\u305f\uff0c\u30a2\u30c1\u30e5\u30a8\u30fc\u30bf\u306f\u3042\u308b\u4e00\u5b9a\u306e\u66f2\u7387 \u534a\u5f84\u3067\u306e\u53f3\u65cb\u56de/\u5de6\u65cb\u56de\u901f\u5ea6\u306e\u307f\u3092\u751f\u6210\u3067\u304d\u308b\u3082\u306e\u3068\u3059\u308b\u3002 \u3053\u306e\u8eca\u4e21\u306e\u904b\u52d5\u5b66\u30e2\u30c7\u30eb\u3092\u793a\u3059\u3002\u5ea7\u6a19\u7cfb\u306f\u30e9\u30a4\u30f3\u4e2d\u5fc3\u4e0a \u3092\u8eca\u4e21\u3068\u3068\u3082\u306b\u52d5\u304f\u5ea7\u6a19\u7cfb Ov \u2212 xvyv \u3092\u7528\u3044\u308b\u3002\u539f\u70b9 Ov\u306f \u30e9\u30a4\u30f3\u306e\u4e2d\u5fc3\u7dda\u4e0a\u306b\u3042\u308a\uff0cxv\uff0cyv \u8ef8\u306f\u305d\u308c\u305e\u308c\u30e9\u30a4\u30f3\u306b\u5bfe \u3057\u63a5\u7dda\u65b9\u5411\uff0c\u6cd5\u7dda\u65b9\u5411\u306b\u3068\u308b\u3002\u307e\u305f\uff0cyv \u8ef8\u306f\u8eca\u4e21\u306e\u91cd\u5fc3\u3092 \u901a\u308b\u3088\u3046\u306b\u3068\u308b\u3002\u8eca\u4e21\u306e\u72b6\u614b\u5909\u6570\u306f\uff0c\u91cd\u5fc3\u306e\u4f4d\u7f6e yv\u3068\u8eca\u4e21 \u306e\u5411\u304d \u03c6v \u3067\u3042\u308a\uff0c\u3053\u308c\u3092\u5de6\u53f3\u4e21\u8f2a\u306e\u89d2\u901f\u5ea6 \u03c9l\uff0c\u03c9r \u306b\u3088\u308a \u5236\u5fa1\u3059\u308b\u3002\u307e\u305f\uff0c\u5404\u5909\u6570\u306e\u6b63\u8ca0\u306f\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u3068\u308b\u3002yv \u8ef8 \u306f\u8eca\u4e21\u4e2d\u5fc3\u3092\u901a\u308a\uff0c\u30e9\u30a4\u30f3\u306e\u66f2\u7387\u4e2d\u5fc3\u65b9\u5411\u304c\u6b63\uff0c\u539f\u70b9\u3092\u30e9 \u30a4\u30f3\u4e2d\u592e\u3068\u306e\u4ea4\u70b9\u3068\u3059\u308b\u3002xv \u8ef8\u306f yv \u8ef8\u306e\u539f\u70b9\u3092\u901a\u308a\u304b\u3064 \u76f4\u4ea4\u3057\uff0c\u8eca\u4e21\u306e\u9032\u884c\u65b9\u5411\u3092\u6b63\u3068\u3059\u308b\u3002\u03c6v \u306f xv \u8ef8\u3068\u8eca\u4e21\u4e2d\n\u5fc3\u8ef8\u3068\u306e\u89d2\u5ea6\u3068\u3057\uff0c\u9032\u884c\u65b9\u5411\u306b\u5bfe\u3057\u3066\u5de6\u65b9\u5411\u3092\u6b63\u3068\u3059\u308b\u3002 \u3053\u3053\u3067\uff0c\u30e9\u30a4\u30f3\u306e\u5e45WL\uff0c\u8eca\u4f53\u4e2d\u5fc3\u3068\u8eca\u8f2a\u4e2d\u5fc3\u306e\u8ddd\u96e2W\uff0c \u8eca\u8f2a\u306e\u534a\u5f84 Rw\uff0c\u8eca\u4e21\u91cd\u5fc3\u304b\u3089\u30bb\u30f3\u30b5\u307e\u3067\u306e\u8ddd\u96e2 l \u306f\u65e2\u77e5 \u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u3068\u3059\u308b\u3002\u305d\u308c\u306b\u5bfe\u3057\uff0c\u30e9\u30a4\u30f3\u306e\u534a\u5f84 R \u304c\u672a\n\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf \u03b1 \u3067\u3042\u308a\uff0cR1\uff0cR2 \u306e\u3044\u305a\u308c\u304b\u306e\u5024\u3092\u3068\u308b \u3082\u306e\u3068\u3059\u308b\u3002\u307e\u305f\uff0c\u5de6\u53f3\u306e\u30bb\u30f3\u30b5\u306e\u914d\u7f6e \u03b1y,l\uff0c\u03b1y,r \u304c\u8a2d\u8a08 \u3059\u3079\u304d\u30bb\u30f3\u30b5\u30d1\u30e9\u30e1\u30fc\u30bf\u3067\u3042\u308b\u3002\u307e\u305f\uff0c\u53f3\u65cb\u56de\u6642\u306e\u5165\u529b \u3092 u1 = (\u03c9l,1 \u03c9r,1)T , \u03c9l,1 > \u03c9r,1\uff0c\u5de6\u65cb\u56de\u6642\u306e\u5165\u529b\u3092 u2 = (\u03c9l,2 \u03c9r,2)T , \u03c9l,2 < \u03c9r,2 \u3068\u3057\uff0c\u8eca\u4e21\u306e\u4e26\u9032\u901f\u5ea6\u3092 \u4e00\u5b9a\u306b\u4fdd\u3064\u305f\u3081\u306b \u03c9l,1 + \u03c9r,1 = \u03c9l,2 + \u03c9r,2 = const. \u306e\u5236 \u7d04\u3092\u52a0\u3048\u308b\u3002\u8a2d\u8a08\u3059\u3079\u304d\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u306f\uff0c\n1090 IEEJ Trans. IA, Vol.126, No.8, 2006", + "\u4e8b\u8c61\u99c6\u52d5\u578b\u5236\u5fa1\u5668\u306b\u3088\u308b\u5236\u5fa1\u7cfb\u8a2d\u8a08\nu\u0303 = [ uT\n1 uT 2\n]T \u3068\u306a\u308b\u3002\n\u4eca\uff0c||\u03c6v|| 1\u3092\u4eee\u5b9a\u3059\u308b\u3068\uff0c\u3053\u306e\u4e8c\u8f2a\u8d70\u884c\u8eca\u4e21\u306e\u72b6\u614b\u65b9 \u7a0b\u5f0f\u306f (13)\u5f0f\u3068\u306a\u308b\u3002\nx( j + 1) = A(u)x( j) + B(\u03b1)u( j)\ny( j) = Cx( j) + D\u03b1y x = (yv \u03c6v)T , u = (\u03c9l \u03c9r) T \u2208 {u1, u2}\nu1 = (\u03c9l,1 \u03c9r,1)T , \u03c9l,1 > \u03c9r,1\nu2 = (\u03c9l,2 \u03c9r,2)T , \u03c9l,2 < \u03c9r,2\n\u03c9l,1 + \u03c9r,1 = \u03c9l,2 + \u03c9r,2 = const. \u03b1y = ( \u03b1y,l \u03b1y,r )T\nA(u) = \u239b\u239c\u239c\u239c\u239c\u239c\u239d 1 a(u)Ts\n0 1 \u239e\u239f\u239f\u239f\u239f\u239f\u23a0 B(u) = \u239b\u239c\u239c\u239c\u239c\u239c\u239d 1 2 a(u)b1T 2 s 1 2 a(u)b2T 2 s\nb1Ts b2Ts\n\u239e\u239f\u239f\u239f\u239f\u239f\u23a0\nC = \u239b\u239c\u239c\u239c\u239c\u239c\u239d 1 l\n1 l\n\u239e\u239f\u239f\u239f\u239f\u239f\u23a0 , D = \u239b\u239c\u239c\u239c\u239c\u239c\u239d 1 0\n0 \u22121 \u239e\u239f\u239f\u239f\u239f\u239f\u23a0 a(u) =\n1 2 Rw(\u03c9l + \u03c9r),\nb1 = \u2212Rw 2 ( 1 R + 1 W ) , b2 = \u2212Rw 2 ( 1 R \u2212 1 W ) ,\nR \u2208 S \u03b1 = {R1,R2} \u3053\u3053\u3067\uff0c\u53f3\u65cb\u56de\uff0c\u5de6\u65cb\u56de\u305d\u308c\u305e\u308c\u306b\u5bfe\u3057\uff0cul = [ ul,1 ul,2 ]T = [1 0]T , [0 1]T \u3092\u5bfe\u5fdc\u3055\u305b\u308b\u3068 (13)\u5f0f\u306f\u6b21\u5f0f\u3068\u306a\u308b\u3002\u3053\u306e \u3088\u3046\u306b ul\u3092\u9078\u3076\u3053\u3068\u306b\u3088\u308a\uff0c\u65b0\u305f\u306a\u4e8c\u5024\u5909\u6570 \u03b4\u3092\u5c0e\u5165\u3059\u308b \u4ee3\u308f\u308a\u306b ul,i\u305d\u306e\u3082\u306e\u3092\u4f7f\u3063\u3066 PWA\u5f62\u5f0f\u306e\u72b6\u614b\u65b9\u7a0b\u5f0f\u3092\u5c0e \u304f\u3053\u3068\u304c\u3067\u304d\u308b\u3002\nx( j + 1) = 2\u2211\ni=1\n(Aix( j) + Biui) ul,i( j)\nAi = A(ui), Bi = B(ui) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (13) ul,1( j) + ul,2( j) = 1, ul,i \u2208 {0, 1}, (i = 1, 2) \u00b7 \u00b7 \u00b7 \u00b7 (14)\n\u307e\u305f\uff0c\u3053\u3053\u3067\u5b9a\u7fa9\u3057\u305f\u4e8c\u5024\u5909\u6570 ul\u306f\u5236\u5fa1\u5668\u304b\u3089\u9001\u3089\u308c\u308b\u4f4e \u5206\u89e3\u80fd\u306a\u5236\u5fa1\u5165\u529b\u3092\u8868\u3057\u3066\u304a\u308a\uff0c(13)\u5f0f\u306f\u5404\u5236\u5fa1\u5165\u529b\u306b\u5bfe \u3059\u308b\u5236\u5fa1\u5bfe\u8c61\u306e\u632f\u308b\u821e\u3044\u3092\uff0c(14)\u5f0f\u306f 2\u3064\u306e\u5236\u5fa1\u5165\u529b\u304c\u540c \u6642\u306b\u767a\u751f\u3057\u306a\u3044\u3053\u3068\u3092\u793a\u3057\u3066\u3044\u308b\u3002\u5236\u5fa1\u5668\u306b\u3088\u3063\u3066\u751f\u6210\u3055\n\u308c\u305f\u5236\u5fa1\u4fe1\u53f7\u306f\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306b\u9001\u3089\u308c\uff0c\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf \u306fON/OFF\u4fe1\u53f7\u3092\u5b9f\u969b\u306e\u5236\u5fa1\u5165\u529b\u306b\u5909\u63db\u3057\uff0c\u5236\u5fa1\u5bfe\u8c61\u306b\u5165 \u529b\u3059\u308b\u3002\u3053\u306e\u5909\u63db\u3092\u6b21\u5f0f\u3067\u8868\u3059\u3002\n[ u( j) = u1 ] \u2194 [ ul,1( j) = 1 ] [ u( j) = u2 ] \u2194 [ ul,2( j) = 1 ] \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (15)\n\u6b21\u306b\u30bb\u30f3\u30b5\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\u3002\u3053\u306e\u5236\u5fa1\u7cfb\u3067\u306f\uff0c\u30bb\u30f3\u30b5\u306f \u30e9\u30a4\u30f3\u4e0a\u306b\u3042\u308b\u304b\u5426\u304b\u306e\u307f\u3092\u89b3\u6e2c\u3067\u304d\u308b\u3088\u3046\u306a\u4f4e\u5206\u89e3\u80fd\u306e \u3082\u306e\u3092\u4eee\u5b9a\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u5b9f\u969b\u306b\u89b3\u6e2c\u3055\u308c\u308b\u51fa\u529b\u3082\u4f4e\u5206\u89e3\u80fd\n\u306a\u5024\u3068\u306a\u308b\u3002\u3053\u3053\u3067\u4ee5\u4e0b\u306e\u3088\u3046\u306a\u4e8c\u5024\u5909\u6570 yl = [ yl,1 yl,2 ]T \u3092\u5c0e\u5165\u3059\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u4f4e\u5206\u89e3\u80fd\u306a\u51fa\u529b yl\u3068\u89b3\u6e2c\u5024 y\u3068\u306e\n\u95a2\u4fc2\u3092\u6b21\u306e\u3088\u3046\u306b\u8868\u3059\u3002 [ y1( j) = cx( j) + \u03b1y,l \u2265 WL\n2\n] \u2194 [ yl,1( j) = 1 ] [ y2( j) = cx( j) \u2212 \u03b1y,r \u2264 \u2212WL\n2\n] \u2194 [ yl,2( j) = 1 ] c = (1 l), yl,i \u2208 {0, 1}, (i = 1, 2)\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (16)\nyl,i \u306f\u30bb\u30f3\u30b5\u304c\u30e9\u30a4\u30f3\u4e0a\u306b\u3042\u308b\u304b\u5426\u304b\u306b\u95a2\u3059\u308b\u4e8c\u5024\u5909\u6570\u3067 \u3042\u308a\uff0c\u30e9\u30a4\u30f3\u4e0a\u306b\u3042\u308b\u3068\u304d\u306f 0,\u30e9\u30a4\u30f3\u304b\u3089\u5916\u308c\u308b\u3068 1\u3092\u3068 \u308b\u3002\u5236\u5fa1\u5668\u306f\u3053\u306e\u4f4e\u5206\u89e3\u80fd\u306a\u51fa\u529b\u3092\u7528\u3044\u3066\u5236\u5fa1\u5165\u529b\u3092\u6c7a\u5b9a \u3059\u308b\u3002\n\u6b21\u306b\u5236\u5fa1\u5247\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\u3002\u3053\u306e\u5236\u5fa1\u7cfb\u306b\u304a\u3051\u308b\u5236\u5fa1\u5247 \u3068\u3057\u3066\uff0c\u201c\u4e00\u65b9\u306e\u30bb\u30f3\u30b5\u304c\u30e9\u30a4\u30f3\u304b\u3089\u5916\u3078\u51fa\u305f\u306a\u3089\u3070\u4eca\u3068\u9006 \u5411\u304d\u306b\u65cb\u56de\u3059\u308b\u201d\u3068\u3044\u3063\u305f\u5358\u7d14\u306a\u8ad6\u7406\u3067\u8868\u3055\u308c\u308b\u3082\u306e\u3092\u8003 \u3048\u308b\u3002\u3053\u308c\u3092\u4e8c\u5024\u5909\u6570 yl \u3068 ul \u306e\u8ad6\u7406\u5f0f\u3068\u3057\u3066\u8868\u3059\u3068\uff0c\u6b21 \u5f0f\u3068\u306a\u308b\u3002\nul( j) = \u23a7\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23a8\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23aa\u23a9 [1 0]T if [yl,1( j) = 1] ul( j \u2212 1) if [yl,1( j) = 0] \u2227[yl,2( j) = 0]\n[0 1]T if [yl,2( j) = 1]\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (17)\n(17)\u5f0f\u306e\u7b2c 1\u5f0f\u3068\u7b2c 3\u5f0f\u304c\u5165\u529b\u306e\u5207\u308a\u66ff\u3048\u3092\uff0c\u7b2c 2\u5f0f\u304c\u5165 \u529b\u306e\u4fdd\u6301\u3092\u8868\u3057\u3066\u3044\u308b\u3002\n\u30084\u30fb2\u3009 \u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u540c\u5b9a \u5b9f\u969b\u306e\u8d70\u884c\u30b3\u30fc\u30b9\u3067 \u306f\u30e9\u30a4\u30f3\u66f2\u7387\u304c\u5909\u5316\u3059\u308b\u3053\u3068\u304c\u60f3\u5b9a\u3055\u308c\u308b\u305f\u3081\uff0c\u30e9\u30a4\u30f3\u66f2 \u7387\u534a\u5f84 R\u304c\u672a\u77e5\u30d1\u30e9\u30e1\u30fc\u30bf\u3068\u306a\u308b\u3002\u3053\u306e\u3068\u304d\uff0c\u8eca\u4e21\u306f\u30bb\u30f3\n\u30b5\u306b\u3088\u3063\u3066\u6570\u56de\u30e9\u30a4\u30f3\u7aef\u3092\u89b3\u6e2c\u3059\u308b\u3053\u3068\u3067\u30e9\u30a4\u30f3\u66f2\u7387\u534a\u5f84 R\u3092\u63a8\u5b9a\u3059\u308b\u3053\u3068\u304c\u3067\u304d\u308b\u2020\u3002\u307e\u305f\uff0c\u8eca\u4e21\u306f\u63a8\u5b9a\u3057\u305f\u30e9\u30a4\u30f3 \u66f2\u7387\u534a\u5f84 R\u306b\u57fa\u3065\u3044\u3066\u5404\u30d1\u30e9\u30e1\u30fc\u30bf\uff08\u30bb\u30f3\u30b5\u4f4d\u7f6e\uff0c\u8eca\u8f2a\u306e \u89d2\u901f\u5ea6\uff09\u3092\u9069\u5fdc\u7684\u306b\u5909\u5316\u3055\u305b\u308b\u3053\u3068\u306b\u3088\u3063\u3066\u30e9\u30a4\u30f3\u8ffd\u5f93\u3092\n\u884c\u3046\u3002 \u3053\u306e\u305f\u3081\uff0c\u9069\u7528\u3059\u308b\u5404\u30d1\u30e9\u30e1\u30fc\u30bf\u306f\u305d\u308c\u305e\u308c\u306e\u30e9\u30a4\u30f3\u66f2 \u7387\u534a\u5f84 R1\uff0cR2 \u306b\u5bfe\u3057\u3066\u6700\u9069\u5316\u3055\u308c\u305f\u3082\u306e\u3092\u4f7f\u7528\u3059\u308b\uff08\u6b21 \u7bc0\u53c2\u7167\uff09\u3002\u3053\u308c\u306b\u3088\u3063\u3066\u30bb\u30f3\u30b5\u3084\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30d1\u30e9\u30e1\u30fc\n\u30bf\u306e\u6700\u9069\u5316\u554f\u984c\u306b\u304a\u3044\u3066 R\u3092\u5b9a\u6570\u3068\u3057\u3066\u6271\u3046\u3053\u3068\u304c\u3067\u304d\uff0c \u60f3\u5b9a\u3055\u308c\u308b\u3059\u3079\u3066\u306e R\u306b\u5bfe\u3057\u3066\u6700\u9069\u5316\u3059\u308b\u3053\u3068\u3067\u8d70\u884c\u30b3\u30fc \u30b9\u306b\u5bfe\u3059\u308b\u9069\u5fdc\u7684\u306a\u5236\u5fa1\u5247\u304c\u69cb\u7bc9\u3067\u304d\u308b\u3002\u3053\u306e\u3068\u304d\uff0c\u6700\u9069 \u5316\u306b\u304a\u3044\u3066\u3072\u3068\u3064\u306e R\u306b\u5bfe\u3059\u308b\u30bb\u30f3\u30b5\u30fb\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u30d1\n\u30e9\u30e1\u30fc\u30bf\u3092\u9069\u7528\u3057\u305f\u5834\u5408\u3067\u3082\u4ed6\u306e R\u306b\u5bfe\u3057\u3066\u5e38\u306b\u53ef\u5236\u5fa1\u6027 \u3067\u3042\u308b\u3053\u3068\u3092\u524d\u63d0\u3068\u3059\u308b\u3002\u672c\u7a3f\u3067\u6271\u3046\u4e8c\u8f2a\u8d70\u884c\u8eca\u4e21\u306b\u3064\u3044 \u3066 R W \u306e\u5834\u5408\u306e\u53ef\u5236\u5fa1\u6027\u306f\u4ee5\u4e0b\u3067\u4e0e\u3048\u3089\u308c\u308b (7)\u3002\nb1\u03c9l,1 + b2\u03c9r,1 > 0 b1\u03c9l,2 + b2\u03c9r,2 < 0 \u23ab\u23aa\u23aa\u23ac\u23aa\u23aa\u23ad \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (18)\n\u3053\u306e\u53ef\u5236\u5fa1\u6027\u306f\u8eca\u4e21\u304c\u30e9\u30a4\u30f3\u4e2d\u592e\u304b\u3089\u5de6\u53f3\u3069\u3061\u3089\u306b\u4f4d\u7f6e\u3059 \u308b\u5834\u5408\u3067\u3082 u1\uff0cu2\u3069\u3061\u3089\u304b\u306e\u5165\u529b\u306b\u3088\u3063\u3066\u30e9\u30a4\u30f3\u4e2d\u592e\u3078\u8eca \u4e21\u306e\u72b6\u614b\u3092\u9077\u79fb\u3055\u305b\u308b\u3053\u3068\u304c\u3067\u304d\u308b\u3053\u3068\u3092\u793a\u3057\u3066\u3044\u308b\u3002\n\u2020 \u534a\u5f84\u306f 1 R \u306e\u5f62\u3067 (13)\u5f0f\u4e2d\u306b\u73fe\u308c\u308b\u306e\u3067\uff0c\u3053\u306e\u5024\u3092\u540c\u5b9a\u3057\u305f\u5f8c R\u3092\n\u6c42\u3081\u308b\u3002\u5236\u5fa1\u306b\u306f 1 R \u306e\u5024\u306e\u307f\u304c\u5fc5\u8981\u3068\u306a\u308b\u3002\n\u96fb\u5b66\u8ad6 D\uff0c126 \u5dfb 8 \u53f7\uff0c2006 \u5e74 1091" + ] + }, + { + "image_filename": "designv8_17_0000814_13320-014-0196-x.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000814_13320-014-0196-x.pdf-Figure7-1.png", + "caption": "Fig. 7 Numerical analysis model of cable-steel wires.", + "texts": [ + " The sizes of the bridge-cable model and numerical analysis model are shown in Fig. 6. Sheng LI et al.: Broken Wires Diagnosis Method Numerical Simulation Based on Smart Cable Structure 369 It is necessary for establishing the cable-steel wires local model to analyze the relationship between the cable force and stress distributions of the monitoring steel wires. If using helix to simulate 2\u00b0 to 4\u00b0 twisting angle of outermost layer steel wires, it will consume large number of nodes to form a lay length. Figure 7(a) shows a one-sixth lay length cable model which divides a lay length into 6 segments. With an increase in the mesh precision, each steel wire will use a number of truss elements. To improve the numerical simulation efficiency, assuming the cable steel wires completely parallel, the simplified model is used as shown in Fig. 7(b) instead of the real helix model. The assumption is convenient for selecting the steel wire element, saving computing nodes, and does not change the steel wires stress distribution at each cable section compared with the real model in the cable length direction. The Chinese code [11] points out that a new cable must be replaced if the number of broken wires in the cable is more than 2%. According to the proportion requirement, the numerical simulation for broken wires degree mainly considers 1 to 2 steel wires breaking for the 55\u03c67 parallel steel wires stay cable" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure4-10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure4-10-1.png", + "caption": "Figure 4-10. Vue de l'antenne PIFA sur substrat de type FoamClad", + "texts": [ + " Dimensions des syst\u00e8mes d'antenne \u00e0 deux monopoles triangulaires...................... 108 Figure 4-7. Photographies des quatre syst\u00e8mes d'antennes \u00e0 deux monopoles r\u00e9alis\u00e9s ............. 109 Figure 4-8. Coefficients de r\u00e9flexion simul\u00e9s et mesur\u00e9s des syst\u00e8mes \u00e0 deux monopoles pour diff\u00e9rents \u00e9cartements ................................................................................................................. 110 Figure 4-9. Vues de l'antenne PIFA miniature ........................................................................... 112 Figure 4-10. Vue de l'antenne PIFA sur substrat de type FoamClad.......................................... 113 Figure 4-11. Bande passante obtenue pour l'antenne PIFA miniature en fonction du substrat .. 113 Figure 4-12. Dimensions d'un syst\u00e8me \u00e0 diversit\u00e9 spatiale utilisant deux antennes miniatures. 114 Figure 4-13 Sch\u00e9ma de l'antenne PIFA agile en polarisation et en fr\u00e9quence............................ 116 Figure 4-14. Tableau de correspondance entre les \u00e9tats de l'antenne agile et les \u00e9tats des diodes PIN ", + " Nous avons donc fait le choix d'utiliser un substrat pr\u00e9sentant une faible permittivit\u00e9 (proche de celle de l'air). Pour cette deuxi\u00e8me version, nous avons des contraintes suppl\u00e9mentaires au niveau de la conception car avec le substrat mousse (FoamClad de Arlon) la gravure chimique n'est pas possible. Le substrat pr\u00e9sente une permittivit\u00e9 de 1,1 et une \u00e9paisseur de 6,5 mm. Si nous d\u00e9sirons r\u00e9aliser cette antenne, elle devra \u00eatre grav\u00e9e m\u00e9caniquement \u00e0 l'aide d'une fraiseuse \u00e0 commande num\u00e9rique. Ceci explique les formes arrondies \u00e0 l'int\u00e9rieur du plateau sup\u00e9rieur 113 visible sur la Figure 4-10, elles d\u00e9pendent du plus petit diam\u00e8tre de fraise utilisable \u00e0 France T\u00e9l\u00e9com. L'antenne obtenue est l\u00e9g\u00e8rement plus grosse que la version avec le CLTE comme substrat mais elle a une bande passante \u00e0 -10 dB de 83 Mhz ce qui permet de couvrir presque toute la bande ISM, comme nous pouvons le constater sur la Figure 4-11. Le gain de bande passante s'explique par la permittivit\u00e9 plus faible mais essentiellement par l'\u00e9paisseur du FoamClad qui est de 6,5 mm. 114 Ces antennes de petites dimensions sont tr\u00e8s int\u00e9ressantes car il est facilement imaginable d'en disposer plusieurs dans un objet communicant afin de mettre en \u0153uvre de la diversit\u00e9 spatiale essentiellement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003512_e_download_9236_8414-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003512_e_download_9236_8414-Figure6-1.png", + "caption": "Figure 6(a): Generative designs of Articulated Rod of Radial Engine", + "texts": [ + " Once required mesh size has been finalised then generative designs can be obtained by varying different parameters, generative design of Articulated Rod of Radial Engine is created using Solid Edge CAD software. The designs are obtained in the various shapes, depending upon the constraints provided such as mass reduction percentage, elapse time and quality of the generated design. Mass reduction of the rod is observed within the range of 10-50% minimization of the original mass. The execution time varied from 20-30 minutes. Furthermore, factor of safety has been fixed as 1.4, considering the dynamic load of the rod. Figure 6 (a) and (b) shows the different designs obtained after the process along with the processing time and resultant weight of the rod. Next step is conventional or practically possible redesigning of our product inspired by generative design results. We redesigned three different types of models in a way that it can be produce by conventional methods or CAM (Computer Aided Manufacturing). Thereafter, FEA is performed once again to check the feasibility of the redesigned models, results along with model designs can is shown in Figure 7-9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000274___lang_en_format_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000274___lang_en_format_pdf-Figure2-1.png", + "caption": "Figure 2. CAD drawing of the B-pillar workpiece.", + "texts": [ + " These analyses were carried out to correlate the results of a reverse engineering approach with the most likely distribution of strain and cooling rates along the workpiece during the 3 Microstructural Evolution of a Hot-Stamped Boron Steel Automotive Part and Its Influence on Corrosion Properties and Tempering Behavior forming process. The sheet thickness used for simulations was of 1.1 mm. It was defined based on the thickness measurement in region 17, as this region presented almost zero deformation according to the simulation. The geometry of the B-pillar was collected from the final shape of the workpiece as part of the reverse engineering process to redesign tool details. The final computer-aided design (CAD) model is presented in Figure 2. As the hot stamping parameters were not provided for the analysis, boundary conditions were obtained from the works by Cui et al.30, Hu et al.31, Park et al.32, and Wang and Ma33, as will be specified ahead, in which the hot stamping of similar geometries made from the same material was studied, and from practical knowledge on industrial hot forming processes. The tools were designed with a constant 1.1 mm thick offset across the geometry. This is generally not recommended due to gaps resulting from thickness changes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure22-1.png", + "caption": "Figure 22. Thermal field distribution of three cross-sections: (a) the water inlet side; (b) the middle cross-section; and (c) the water outlet side.", + "texts": [ + " By comparison of Tables 10 and 9, it shows that the CS-PMSM can run safely when the water cooling used in the casing and axial forced air are simultaneously adopted in the CS-PMSM. When both the SM and the DRM are running at the low speed and rated load, the 3-D thermal field distribution is calculated under condition of water cooling used in the casing and the inner rotor, as shown in Figure 21. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the water inlet side, middle cross-section, and the water outlet side of the CS-PMSM are shown in Figure 22. The selected water inlet, middle and water outlet cross-sections are the same as those in Section 4.1. The highest temperature of each part in the above three cross-sections is shown in Table 11. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 11. From the temperature distribution of each cross-section in Table 11, it can be seen that the temperatures of the stator windings and inner rotor windings are higher than others. This is mainly because the windings are the major heat source under condition of the low speed and rated load" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001176_ai.28-6-2020.2298144-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001176_ai.28-6-2020.2298144-Figure10-1.png", + "caption": "Fig. 10. The effect of different VSWRs on the drain efficiency for at 43.2 dBm.", + "texts": [ + " The Microwave Office (MWO) was used to simulate the performance of the designed amplifier, where the designed amplifier is matched to the common impedance (50\u03a9); nevertheless, when beamforming technique and MIMO are applied, the antennas impedance varies. Figure 6 shows the selected Voltage Standing Wave Ratio (VSWRs), where the designed three-way amplifier performance is checked after forcing the amplifier to see these impedances due to the change of the VSWRs, Figure 7 and Figure 8 show the output power variation of the designed amplifier at the back-off region and the peak power region respectively. In addition, for the same tested regions, Figure 9 and Figure 10 showed the variations of the efficiency. Due to the impedance change, the amplifier performance is changed significantly. The maximum variation of the power was 3.5 dBm at the peak power and 3.2 dBm at the back-off region, whereas 21.3% was the efficiency variation at the peak power and 17.8% at the back-off power. This performance can be compared with [8], where more variation in the power was obtained and less variation in the efficiency, so that, the amplifier structure has a significant effect when different VSWRs are applied" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002725_load.php_id_11082407-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002725_load.php_id_11082407-Figure1-1.png", + "caption": "Figure 1. Configuration of a coplanar-strip dipole antenna for CP operation.", + "texts": [ + "8GHz, serves to demonstrate that the proposed antenna features wider RL and AR bandwidths than those in [11]. On the other hand, it is interesting to design an ultra-wideband (UWB) antenna for CP operation, since most of the reported UWB antennas radiate LP waves [1, 15\u201318]. Hence, the second example is to propose a UWB antenna for CP operation by resizing the same antenna structure as the first one. Moreover, the relevant researches on CP antenna have been reported in [19\u201333]. The configuration of a coplanar-strip dipole antenna for CP operation is shown in Fig. 1. The antenna consists of two coplanar strips of size L \u00d7 W with a gap g in the x-direction and an overlapped length 2h in the y-direction. The feeding point is at the center of the overlap region. A rigid mini-coaxial cable with a radius of 0.6 mm is adopted to feed the RF power to the antenna. The inner conductor of the cable is soldered to one strip, while the outer conductor of the cable is connected to the other strip. It is the strip width W that makes the proposed antenna capable of radiating CP waves due to there being two orthogonal currents on the strip", + " 3 and 4, the proposed antenna performs CP operation at 2.0GHz, which can also be understood by the current distributions, as shown in Fig. 9. The current vectors on the metal strip rotate clockwise with time, resulting in the fact that the forward radiation and backward radiation patterns are dominated by LHCP and RHCP, respectively. (see Fig. 6). Having shown the good performances of the proposed antenna on RL and AR bandwidths, it would be interesting to investigate the influence of the structure parameters W , g, and h (see Fig. 1) on the antenna characteristics such as RL and AR bandwidths. First, the structure parameters are taken the same as those in Section 3 except the parameter W . As shown in Fig. 10, the variation of the slab width W has a significant influence on RL, which implies that the impedance matching can be done by tuning W . In addition, Fig. 11 indicates that the increase of the slab width W results in the CP radiation. It should be noted that the conventional thin dipole antenna can be regarded as a special case of the proposed antenna when the slab width W approaches zero", + " Figures 14 and 15 show the RL and AR versus frequency, respectively, with all parameters in Section 3 kept unchanged except the gap g. The parameter g has a significant influence on RL but little effect on AR. From these parametric studies, the design procedure can be completed by three simple steps. The first step is to determine the parameter L by the required center frequency. The second step is to achieve good AR matching by tuning the parameters W and g. The final step is to do impedance matching using parameter g. In Sections 3 and 4, the proposed antenna (see Fig. 1) has been successfully applied in the lower frequency band around 1.8 GHz. In this Section, the same structure will be applied in the UWB with the parameters modified as L = 32mm, W = 12.5 mm, h = 7 mm, and g = 1.5mm. Fig. 16 shows the measured and simulated return losses. The measured \u221210 dB RL bandwidth is from 2.1 to 10.1 GHz, and the simulated one is also from 2.1 to 10.1 GHz. Both measured and simulated data match well and show that the proposed antenna can work well in UWB. Figure 17 shows AR of the proposed antenna by receiving signal in the z-direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002507_9-3-AComparative.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002507_9-3-AComparative.pdf-Figure2-1.png", + "caption": "Fig. 2: Base and movable platforms coordinate systems.", + "texts": [ + " It was used the acquisition, transmitting, and processing system dSPACE in combination with the speed controller drive RoboClaw 2 and an inertial sensor XsensMTi-G measurement of the Euler angles of the Stewart Platform [7]. II. INVERSE KINEMATIC Defined position and attitude of the Stewart platform, length of six actuators can be obtained using the inverse kinematic of the platform. Joints of actuators and platforms are known for a given platform, and it can be written in relation with the center of each platform in two www.ijaers.com Page | 26 coordinate systems, shown in Figure 2. The base platform coordinate system utilizes the center of the base platform F as origin, the xf-axis pointing between joints with actuators 1 and 6, zf-axis is perpendicular with the platform plane, and yf-axis completes the right-hand rule. The movable platform coordinate system center M and its axis xm, ym, and zm are defined in a similar way. The joints positions of the base and movable platforms, in its coordinate systems, are shown in Equation (1) and Equation (2), respectively. {\ud835\udc39\ud835\udc56} \ud835\udc39 = {\ud835\udc39\ud835\udc561 \ud835\udc39\ud835\udc562 0}\ud835\udc47 , \ud835\udc56 = 1,2, \u2026 ,6 (1) {\ud835\udc40\ud835\udc56} \ud835\udc40 = {\ud835\udc40\ud835\udc561 \ud835\udc40\ud835\udc562 0}\ud835\udc47 , \ud835\udc56 = 1,2, \u2026 ,6 (2) The transformation matrix [TMF] to obtaining coordinates of the movable coordinate system for the base coordinate system, can be obtained by using three rotations in sequence" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure98-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure98-1.png", + "caption": "Figure 98. Datum point selection screen (for specimen)", + "texts": [], + "surrounding_texts": [ + "Inputs E 1 Axial Modulus, msi E 2 Transverse Modulus, msi E 3 Modulus, msi G 12 = G 13 Shear Modulus, msi G 23 Shear Modulus, msi \u03c5 12 = \u03c5 13 Poisson\u2019s Ratio \u03c5 23 Poisson\u2019s Ratio MTM 49-LT Unidirectional 19.9 0.99 0.99 0.302 0.398 0.244 0.257 A.5.5. Isotropic Section Creation One section was created for the steel. To make a new section right click Section category and click create. Name it Isotropic, for the category chooses Solid, and for the type choose 150 Homogeneous. Click continue, and then choose Steel as the material. Apply the steel section to the steel pin part and the steel side plate. In this step, we also want to duplicate the SidePlate part. Right click on the SidePlate and click copy, name it SidePlate2. Expand the SidePlate options by pressing the (+) icon next to the part name, click Section Assignments, click the part and then it should highlight in red. Click done once selected. For the section choose the Isotropic section which was created then hit Ok. 151 Apply this same method to the SteelPin part and the Sideplate2 part. A.5.6. Composite Laminate Section Creation The specimen which was created was a carbon fiber laminate composed of 16 layers with an orientation of [0 0 +45 -45 +45 -45 90 90]s. Abaqus has a Composite layup tool which is found in each individual part. Keep the name default, set the initial ply count to eight and set the element type to solid. 152 A new window appears. In this window, all of the laminate stacking directions along with the rotation axis are specified. 153 Before a layup orientation can be created; a datum coordinate system needs to be defined. Click Create Datum CSYS. Create a rectangular coordinate system and keep the default name. Next, it will ask you to specify a point, click the point in the center of the hole shown below in the figure. Keep the Rotation axis to Axis 3 and keep the Stacking Direction to Element direction 3. Check the box that says, \u201cMake calculated sections symmetric\u201d. Since we are only going to specify eight of the plies, which are part of the orientation. Next, we need to specify where on the part we have this orientation. In the region section, double click it, click on the specimen, and then click the done button. Do that for each layer and then for the material section, choose Uni as the material. The element relative thickness should 154 equal the reciprocal of the amount of elements through the thickness of the part. For example, my mesh consists of two element, which span the thickness of the specimen. My element relative thickness was set to 0.5 (2-1). 155 Last of all, set each ply orientation angle starting with the outermost layer. Keep the integration point to one. The result should look like this. 156 A.5.7. Assembly Creation Under the Assembly submenu, create an Instance. Make each of the parts are set as Dependent also make sure to check the Auto-offset from other instances. 157 The next part requires getting used to Abaqus\u2019 assembly options. This can be tricky, but it takes practice. After moving each part around, the final assembly should look something like this below. Make sure the specimen is centered between both of the side steel plates. The specimen should sit 1 in. into the pin, which is how it was loaded in the experiment. The distance between the two side plates is 0.25 in. Make sure the top of the pin is touching the top of both of the side steel plates. 158 A set needed to be created for a specific node. Abaqus gives you an option to select a specific node of interest and name it whatever you please. Therefore, in my model I wanted to select a node, which is in the middle of the specimen and located at the bottom of the hole. This location is of critical importance to the model because that is the location I want to monitor the vertical 159 deflection. This is the location where we will want to compare the experimental extensometer displacement and the nodal displacement in the numerical model. While in the Assembly module, I created a new set, picked the corresponding node, and named it Monitor. Switch to the Step module and then you will see the main horizontal bar at the top of the screen change accordingly. Now the main horizontal bar should have an Output menu. Click into this menu and click DOF Monitor. There should be an option to toggle on, Monitor a degree of freedom throughout the analysis. Click Edit, and then click Points in the prompt area and choose the node set Monitor from the region selection dialog box. Now we set the Degree of Freedom we want to monitor. In our model, we are interested in the displacement in the Y direction because that is actually, what the extensometer measured in the experiment. As we can see in, we want to monitor the Y-axis displacement so we set the Degree of Freedom to 2. Now we click Ok. 160 Surfaces needed to be created for each specific part. A very important feature is located in the surface option, here the user is able to select and define a surface on any particular part in your model. So what I did was define a surface called InnerSpecimen, this was defined as the inner surface of the specimen\u2019s hole. The second surface I defined was the outer surface of the pin and named it Pin. A.5.8. Step Creation Two steps need to be created one for the contact step and another for the load step. Abaqus runs the steps in order so first we are going to tell Abaqus that there is contact between some of the parts and after that, contact is established the load step can be applied. Create the contact step 161 and make sure all of these match. Create the load step and make sure all of these match. 162 A.5.9. Interaction Creation Next, we need to create an interaction between the pin and the specimen along with the two side plates. Right click the Interactions submenu and click Create. Choose Surface-to-surface contact. Keep the name to default and make sure to make it for the Initial Step. Click the outer surface of the pin as the Master Surface. After this step, go into the assembly and hide the SteelPin part by right clicking on it, and selecting Hide. 163 Once the pin is hidden, selecting the slave surfaces is a lot easier. Select Slave at the bottom menu and then select the inner hole surface of the two steel plates along with the specimen (hold Shift to select more than one at a time). Then click done and that should be all. Keep it at Finite Sliding and keep the Discretization method to Surface-to-Surface. 164 Then click the create Contact interaction property button. Choose Contact and name it NoFric. Then under Mechanical Submenu add Normal and a Tangential Behavior. Pick penalty for Tangential Behavior and choose a friction coefficient of 0.46. For the normal Behavior, Pressure Over-closure \u201cHard\u201d Contact, Constraint enforcement method Default and make sure to allow separation after contact is checked. 165 A.5.10. Defining the Load Next, we need to define a load in the model. Right click the load submenu and click create. Name the load, then apply the load in the load step. Choose a Pressure load for type. Select bottom faces of the two steel plates (shown red in the figure). Select Total Force for the Distribution type, and enter a magnitude of -600 and keep amplitude as ramp. 166 167 A.5.11. Defining the Boundary Conditions Three boundary conditions were applied to the model. One boundary condition was applied to the top face of the specimen and this will simulate the clamps in the Instron machine. The second boundary condition was applied to the side steel plates. For this condition, we want to prevent the plates from moving out from the z-plane. The last boundary condition was initially applied to the contact step and then it became modified from the load step. The last boundary condition dictated how the pin was to move in the model. Right click on the boundary conditions (BCs) submenu and click create. Name it Fixed and apply it to the Contact step. For the category choose Mechanical and for type, choose Symmetry/Antisymmetry/Encastre. Then click Continue. Select all of the outer sections of the steel side plates. Choose Encastre as the type. 168 Right click on the boundary conditions (BCs) submenu and click create. Name it SideFaces and apply it to the Load step. For category choose mechanical and for type choose Displacement/Rotation. Then click continue. Select all of the outer sections of the steel side plates. Set the U3 equal to zero since no deflection is expected to occur in this direction. 169 Right click on the boundary conditions (BCs) submenu and click create. Name it PinBC and apply it to the Contact step. For category, choose mechanical and for type choose Displacement/Rotation. Then click continue. Select all the surfaces of the pin. 170 Right click on the load and press edit. Disable the U2 boundary condition by unchecking the box. A.5.12. Defining the Mesh The partitions that were created for the side plates and the specimen simplified the mesh defining process. The Seed Edges command was used for each part and each part was highlighted. 171 In the options, the number method was chosen and the bias was set to none. The sizing controls options defined how many elements would be assigned to each element of the partition. For my model, I kept the number of elements equal to two. After this, I clicked Ok. Apply the same method to all the parts. Apply these settings under the Mesh Controls options. 172 In the element type settings, make sure all of these are applied to both the pin and side plate parts. All of these settings should be default. For the specimen, only difference was to uncheck the Reduced integration box. 173 A.5.13. Creating the Job Lastly, we need to create a specific job for your model. Once a job is created, you need to right click on the job and submit it. Once submitted, the job will run and once it converges, it will say Completed assuming everything runs smoothly. To see the results, right click on the job and click the results. This should open up another tab where the user is able to see the different displacements and stresses in the different directions." + ] + }, + { + "image_filename": "designv8_17_0004549_f_version_1481292377-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004549_f_version_1481292377-Figure3-1.png", + "caption": "Figure 3. Illustration of the measurement method: (a) design of the measurement method; (b) diagram of the measurement reference coordinate frames.", + "texts": [ + " The direction vector cDi will be replaced by cDi = cDi \u2016cDi\u2016 , and point cPi will be replaced by cLi = [clix cliy 0]T , which is the intersection point of the laser beam and the image plane. Thus, the final result is:x y z = cDi\u2225\u2225cDi \u2225\u2225 ti + clix cliy 0 . (10) Once all of the extrinsic parameters of simple lasers are calibrated, our system can achieve a highly accurate measurement of the spherical target with three steps: (1) reconstruct the 3D positions of laser spots; (2) obtain the initial guess of the solution via sphere fitting; (3) refine the initial guess by nonlinear optimization. An illustration of the proposed measurement method is shown in Figure 3a. The measurement system has two different coordinate frames: {C} is the camera coordinate frame with its origin at the center of the camera aperture. {Im} is the image coordinate frame with its origin at the top left corner of the image plane. The relationship between the camera coordinate frame and the image coordinate frame can be described by a pinhole model. All of these coordinate frames are orthogonal. The principle of measuring an unknown spherical target is solving for the geometric parameters: cO = [cox, coy, coz]T , the 3D position of the sphere center with respect to frame {C}, and r, the radius of the sphere. A diagram of the coordinate frames is shown in Figure 3b. In order to calculate the parameters of an unknown sphere, at least four non-coplanar points on the surface of the sphere are needed. As shown in Figure 3a, the laser spot should satisfy the following two constraints: \u2022 The laser spot is on the optical line. \u2022 The laser spot is on the laser beam that has been calibrated in the prior section. Considering the first constraint, we firstly detect the laser spot i\u2019s pixel coordinate p\u0303i = [u v]T in the image. Then, the function of the optical line can be calculated by the approach described in the last section. We represent this line as: x y z = ki1Doi, (11) where Doi is determined by Equation (3). Considering the second constraint, the function of the laser beam i can be represented as:x y z = ki2 cDi + cLi, (12) where cDi and cLi can be determined by our proposed calibration method", + " Therefore, we should use the solution from four reconstruction points as the initial guess and refine it with nonlinear optimization by adding the projection point of the center of the sphere as a geometric constraints. To achieve a more accurate solution, we will utilize an optimized scheme for each frame by minimizing the combination of reprojection errors of laser spots and the center of the sphere as follows: minimize cO, r \u2211 i \u2016\u03c0(\u03a6i( cO, r, Di, Li))\u2212 p\u0303i\u20162 + \u03bb \u2016\u03c0(cO)\u2212 p\u0303o\u20162 , (16) where \u03bb is a tuning parameter and p\u0303i, p\u0303o are the image coordinates of the detected laser spot i and the center of the projected circle as shown in Figure 3a. The first term in the cost function Equation (16) is meant for penalizing the reprojection error of four laser spots, in which the function \u03c0() is the projection function and \u03a6i( cO, r, Di, Li) is the reconstruction function for each laser spot. As mentioned before, the reconstruction error of laser spots will lead to an inaccurate solution. To improve the robustness of the measurement system, we add a geometric prior term, which enforces the projection point of the optimized cO coinciding with the detected center of projected circle p\u0303o" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001861_4_isxn_9781522567356-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001861_4_isxn_9781522567356-Figure13-1.png", + "caption": "Figure 13. Divisions of shoe last design", + "texts": [ + " The two wireframes are then changed into the three types of surface shape: round surface side of the shoe last, upper side surface of the shoe last, and the bottom side surface of the shoe last as shown in Figure 14, Figure 15, and Figure 16. In this paper, the bottom surface of the shoe last is obtained by taking the surface results of the patient\u2019s foot from the scan that is then converted into a surface model of the bottom of the patient\u2019s foot. To obtain the rounded surface on the shoe last that corresponds to the standard shoe model as shown in Figure 3 (c) and according to the wishes of the two patients, it is necessary to change the shape of the rounded foot-side surface for the AFO for the patient as shown in Figure 13. This change is done by changing the original curved model based on the patient\u2019s foot into a new curve as shown in Figure 14, Figure 15, and Figure 16, as well as in accordance with the insole form as previously designed (Anggoro et al., 2017a; and Anggoro et al., 2018b) and well reported (Marco et al., 2015). The curve change process is performed by the engineer to form a rounded surface side for the patient\u2019s foot according to the face of the standard shoe shape. The results are presented in Figures 14, 15, and 16. The beginning of the formation of the rounded side surface of the shoe last begins with the curve of the wireframe on the curve of the leg (Figure 13) with the oblique involved in PowerSHAPE2016 as the original curve of the foot. This original curve was developed again into a new smooth wireframe and has been adjusted to the surface contours of the shoe desired by the patients. The round-side portion of the shoe last is required by the patient in accordance with Figure 3(c). To get a smooth curve, the engineer needs to edit the curve with a cutting process on the original curve so that it will become a really smooth tangency curve (Figure 13) until obtaining the necessary smooth curve for making the surface of the shoe last. In order to obtain a smooth, rounded side surface for the shoe based on the patient\u2019s request, the CAD shoe last engineer is required to perform a process to repoint the curves (Figure 14). This happens because the output of the curve creates a process with the oblique method and the edited curve often results in uneven positioning of each point curve, greatly affecting the smoothness quality on the surface being built. This process is done by editing a number of curve points between the wireframes. This should result in the same number of curve points (Figure 15) and should also match the rotational direction of the curve point on the wireframe so that each new wireframe can perform the operation on the surfaces with automatic surfacing in PowerSHAPE2016; a smooth surface finally converted to CAM and processed on the CNC machines. The wireframe for the 3D solid shoe last model in Figure 13, when presented in 2D drawing and juxtaposed with the insole shoe surface as produced by researchers (Anggoro et al., 2017a; Anggoro et al., 2018; Anggoro et al., 2018c; and Anggoro et al., 2017d), will show a clear comparison between the insole and real curve to create a new curve for the shoe last, the original curve of the foot from the scanning process, and the curve used to form the round side of the shoe last as presented in Figure 15. This figure shows the blue curve as the curve of the patient\u2019s foot from the scanning with Handyscann 700TM developed into a new model with curves forming the surface of the round side of the shoe last as shown in Figure 13. While the black curve (Figure 16) is a 2D wireframe insole which, when assembled with Figure 13, will be a 3D image including the shoe last with the orthotic shoe insole (Figure 17). From Figure 16, it can be seen that the output of the CAD assembly process between the shoe last and the shoe insole creates a complete fit; so precise and accurate that it is ready for the next step in the shoe last product fabrication process with a CNC machine. In this paper, the new method of manufacturing a shoe last is not done manually as before by Anggoro et al. (2018). Why? Because the initial shoe last in Figure 2 (b) by the best shoemaker in both Central Java and the Special Region of Yogyakarta, Indonesia, took almost 3 weeks with imprecise results in the shape and dimensions of both the 3D CAD models and physical models" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001896_9668973_09762722.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001896_9668973_09762722.pdf-Figure1-1.png", + "caption": "FIGURE 1. Double-pendulum model of an overhead crane.", + "texts": [ + " The FM input-shaping strategy is simulated using primary zero-vibration (ZV) and zero-vibration-derivative (ZVD) input-shapers. It is important to emphasize that the main goal of the proposed FM input-shaping strategy is to facilitate the use of singlemode input-shaping techniques for a time-varying doublependulum crane. The FM input-shaping strategy is nearly as fast and as robust as the primary input-shaping technique itself. II. MATHEMATICAL MODEL The overhead crane is modeled here as a double-pendulum with a variable length hoisting cable, as shown in Fig. 1. The payload of the crane is modeled as a rigid body of mass m attached to the end of a massless inextensible rigid cable of variable length `. The distance from the end of the cable to the center of gravity of the payload is r . The nonlinear equations of motion of the model are derived using the Lagrangian approach. The position of the center of gravity of the payload changes according to x = = u\u2212 ` sin\u03c61\u2212r sin\u03c62, (1) y = \u2212` cos\u03c61\u2212r cos\u03c62, (2) where u is the motion of the crane jib. The kinetic and potential energies of the system are T = 1 2 m ( u\u0307\u2212 \u02d9\u0300 sin\u03c61 \u2212 ` cos\u03c61\u03c6\u03071\u2212r cos\u03c62\u03c6\u03072 )2 + 1 2 m ( \u2212 \u02d9\u0300 cos\u03c61 + ` sin\u03c61\u03c6\u03071 + r sin\u03c62\u03c6\u03072 )2 + 1 2 J \u03c6\u030722 , (3) V = mg (\u2212` cos\u03c61\u2212r cos\u03c62) , (4) where J = mk2 is the mass moment of inertia of the payload, and k is its radius of gyration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.8-1.png", + "caption": "Figure 2.8 Geometry of seawater antenna on the ground plane [8]", + "texts": [ + " The liquid column height was estimated from the known volume of liquid in the PVC tube. The simulated results were in good agreement with the measured results. The resonant frequency for this simulated design was 1.51 GHz with a bandwidth of 8.27%, while the measured results on the prototype revealed a resonant frequency of 1.59 GHz and bandwidth of around 10.06%. Based on another design for ionic liquid antenna [8] done by the same author, a feeding probe loaded with nut and washer was introduced to improve the performance of the monopole water antenna as shown in Figure 2.8. Two saltwater antennas of diameter 2.5 cm and 5 cm was constructed. For each antenna, the salinity of the salt solution was 35 ppt and 70 ppt. Both saltwater antennas were mounted on a 30 X 30 cm aluminum ground plane. Simulation and experimental results shows that the radiation efficiency of the ionic liquid antenna is between 50 to 70% at microwave frequencies. It was also found that the resonant frequency of the antenna is inversely proportional to its radiator height, and a large bandwidth is observed at 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000853_9668973_09718336.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000853_9668973_09718336.pdf-Figure9-1.png", + "caption": "FIGURE 9. Experimental setup used for the torque measurements.", + "texts": [ + " TORQUE MEASUREMENTS Based on the static analysis, it was confirmed that the proposed revolute joint had high-torque efficiency. First, the proposed joint mechanically reduced the applied load torque as described in section III-B. Second, the increasing gear ratio (as a function of the rotational angle) helps the required motor torque to be reduced. To quantify the torque efficiency, we measured and compared the actual load torque applied to the motor in both the proposed and conventional mechanism cases. Fig. 9 shows the experimental setup for the torque measurement in the proposed joint. A torque sensor (TRD-50KC, CAS Corporation, Yangju, South Korea) was installed between the motor and the lead-screw-driven linear guide. While the revolute link was rotated by increasing the angle from 0\u25e6 to 70\u25e6 in 5\u25e6 increments, the torques applied to the motor were measured. Each set was repeated 5 times, and the measured torques were all the same as shown in Table 1. In the conventional mechanism, the measured torque at the rotational axis was the same as the torque applied to the motor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002325_16.99.108_linkid_pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002325_16.99.108_linkid_pdf-Figure5-1.png", + "caption": "Fig. 5(a-d): Magnetic flux density vector diagram (a) hM = 10.6 mm, (b) hM = 13.6 mm, (c) hM = 16.6 mm and (d) hM = 18.6 mm", + "texts": [ + " In the term of the performance, hM should make the motor straight axis reactance Xad more reasonable and in the point of technology, the permanent magnet should work at the best operating point. If the design of hM is too thin, it will lead to the increasing of the reject rate and it is easy to demagnetize, which will influence the service performance of motor. Let's take a 4-pole motor as example. When the length hM of magnetization direction for permanent magnet is different, the vector of internal magnetic flux density is shown in Fig. 5. Relationship between the different magnetization direction length of permanent magnet hM and the motor maximum output torque is shown in Fig. 6. As shown in Fig. 5 and 6, for the sake of ensuring the rotor core unsaturated, with the increase of hM, the value of torque increases is more fast. When hM reaches to a certain thickness, the value of the torque increases much slow. The reason is that the air gap flux density of the motor will increase with the increasing of hM and the magnetic potential, reluctance and magnetic flux leakage increase as well. When the thickness increases to a certain value, it will reduce the coefficient of the pole arc and result the waveform of air-gap flux density distorting" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004957_s-1380355_latest.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004957_s-1380355_latest.pdf-Figure1-1.png", + "caption": "Fig. 1. A thin-walled cylindrical shell", + "texts": [ + " The paper is organized as follows. In Section 2, the basic equations are proposed, and the nonlinear terms are divided into two parts according to their affiliations. In Section 3, a specified case is designed to explain the effects of the nonlinear terms mentioned in the paper followed by the results analysis and the comparison with FEM results in Section 4. Finally, the conclusion is drawn in Section 5. Consider a thin-walled cylindrical shell with radius 0.0485mR = and thickness 0.0015mh = as shown in Fig. 1. u , v and w are the displacements of the points on the middle surface, which divides the thickness of the shell equally, along the coordinates x , and z , respectively. The transient pressures are applied inward on the out wall of the shell along the radial direction in this paper. The following hypotheses are adopted in order to study the dynamic responses of cylindrical shells subjected to transient pressures. (H1) The shell is thin, namely, 1 10h R [15]. (H2) The Kirchhooff-Love hypotheses hold" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003690_load.php_id_08090904-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003690_load.php_id_08090904-Figure2-1.png", + "caption": "Figure 2. Geometry of the elliptic dielectric resonator antenna excited by a probe.", + "texts": [ + " In practice the difference will not be zero due to the expansion of the current distribution into finite number of basis functions with unknown coefficients, so we minimize the functional F ( E\u0304 ) = \u2329 L ( E\u0304 ) , W\u0304 \u232a \u2212 \u2329 f\u0304 , W\u0304 \u232a (3) The finite element method of the problem involves basically four steps [22]: \u2022 Discretizing the solution region into a finite number of sub-regions or elements. \u2022 Deriving governing equations for a typical element. \u2022 Assembling of all elements in the solution region. \u2022 Solving the system of equations obtained. In the finite element method, the radiation boundaries are used to simulate open problems that allow waves to radiate infinitely far into space. The waves are observed at the radiation boundary surface. More details about the finite element method can be found in [22]. Figure 2 shows the geometry of the cylindrical superquadric dielectric resonator antenna structure. The dielectric resonator antenna of height \u201ch\u201d and dielectric permittivity \u201c\u03b5r\u201d has a superquadric cross section area with aspect ratio \u201ca/b\u201d (major to minor axes ratio). The superquadric cross section curve is the locus of points satisfying the following equation [23], (x a )\u03bd + (y b )\u03bd = 1 x \u2264 a, and y \u2264 b (4) where \u201ca\u201d and \u201cb\u201d are the semi-axes in the x and y directions respectively, and \u03bd is a \u201csquareness parameter\u201d which controls the behavior of loop radius of curvature. The coordinates of any point on the curvature are given by, x = a\u03c8 (\u03b2) cos\u03b2 y = b\u03c8 (\u03b2) sin\u03b2 } (5) where \u03c8 (\u03b2) = (|sin\u03b2|\u03bd + |cos\u03b2|\u03bd)\u22121/\u03bd . The parameter \u03b2 is in the range (0 \u2264 \u03b2 \u2264 2\u03c0). An important feature of this particular representation is the fact that equal divisions in the parameter \u03b2 results in reasonably equal values of arc length for the sub-sectional segments. Figure 2(b) illustrates the superquadric geometry for \u03bd = 2, 3, and 10 and an aspect ratio of \u201ca/b\u201d = 1.5. Thus the superquadric loop allows modeling of different dielectric resonator configurations through the variation of parameters a, b, and \u03bd starting from circular (ellipse) to square (rectangular) cross sectional area. The feeding probe of length \u201c \u201d is embedded within the DRA at feed point (wx and wy). The DRA is mounted on an infinite size ground plane. As the squareness parameter \u201c\u03bd\u201d and aspect ratio \u201ca/b\u201d have the most effect on the dielectric resonator antenna characteristics, through out the paper these parameters are studied to obtain the best circular polarization" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure34-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure34-1.png", + "caption": "Figure 34: (a) Design 1 of Pantograph (b) Design 2 of Pantograph", + "texts": [], + "surrounding_texts": [ + "Table 1: Viscoelastic test data. ....................................................................................................... 4 Table 2: Experimental results of Prony shear relaxation series (Constant Poisson Ratio) [4]. ...... 6 Table 3: Experimental results of Prony bulk relaxation series (Constant Poisson Ratio) [4]. ....... 6 Table 4: Random vibration input PSD G acceleration. .................................................................. 9 Table 5: Solution details of inverter [8]. ...................................................................................... 10 Table 6: Solution details of iterative compliant landing mechanism. .......................................... 12 Table 7: Parameters of first conceptual design iteration. ............................................................. 15 Table 8: FEA versus Mathematical Results of Compliant LG Mechanism. ................................ 16 Table 9: PLA and ABS material properties [12] [13]. .................................................................. 22 Table 10: Segment lengths for compliant pantograph mechanism. ............................................. 24 Table 11: Material and compliant joint properties in the 3 pantograph designs. ......................... 26 Table 12: FEA results of the 3 pantograph designs. ..................................................................... 27 Table 13: Parametric design results of compliant joints for Design 1. ........................................ 27 1 1. Introduction A compliant mechanism achieves motion through elastic deformation of the body. Conventional mechanisms utilize joints and complex parts to achieve motion, they also undergo maintenance and require frequent lubrication. The strength of a compliant mechanism is it is lightweight, and not complex. Material with a lower elastic modulus is more likely to be used in compliant mechanisms due to their nature of large deformations under reasonable load. A stiff material would not be able to be used for a compliant mechanism because the structural deformation would be little and result in failure. Plastics are used mostly in compliant mechanisms. The current research of this report focuses on Acrylonitrile Butadiene Styrene (ABS). While ABS has a low elastic modulus, it also has a viscoelastic nature to it. Viscoelastic material behave as viscous, or elastic, or equal depending on the magnitude and scale of the applied shear stress [1]. Viscoelastic materials add a time dependency parameter, meaning that when a load is applied the structure takes time to go back to its original shape. This material property can be used for a variety of structures including: 1. Morphing Wings 2. Landing Gears 3. Car Windshield Wiper 4. Grippers As mentioned before, a compliant mechanism saves a lot of weight. This can be beneficial for a structure such as a morphing because even with a 1% reduction in drag achieved by morphing wings, a substantial yearly savings of USD 140 M can be achieved for the US fleet of wide-body transport aircraft [2]. Manufacturing costs for the listed structures also can be reduced since the amount of parts is reduced. This means that there will be little assembly labor costs. The research of this paper focuses on the design of a dynamic compliant landing gear mechanism of a rotorcraft. 2 2. Literature and Design Studies The literature and design studies are split into 7 sections. Future work will be listed at the end of the report to guide future research. Multiple design iterations were investigated in this research study and are presented in the paper. 2.1. Viscoelasticity Literature Study and Application in ANSYS ANSYS is the main FEA software that will be utilized in the thesis project. Material properties for viscoelastic materials exist in the material library of ANSYS. There are 5 options to choose from to model viscoelasticity [3]. 1. Prony Shear Relaxation 2. Prony Volumetric Relaxation 3. William-Landel-Ferry Shift Function 4. Tool-Narayanaswamy Shift Function 5. Tool-Narayanaswamy w/ Fictive Temperature Function To begin with the William-Landel-Ferry Shift function. The shift function has the form seen below [3]: log10(\ud835\udc34(\ud835\udc47)) = \ud835\udc361(\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) \ud835\udc362 + (\ud835\udc47 \u2212 \ud835\udc47\ud835\udc5f) (1) Where C1 and C2 are material parameters and Tr is a reference temperature. T is the temperature that is being studied. The point of this function is to shift the properties of a material from one temperature to another by approximating. The C values could include variables such as strain, etc. Since the current study does not include temperature and it is at constant temperature the William-Landel-Ferry Shift function does not need to be used. The Tool-Narayanaswamy Shift Function with Fictive Temperature Function is similar to the William-Landel-Ferry shift function where temperature is a parameter that is used in the integral part of the equations as seen below [3]. 3 ln(\ud835\udc34(\ud835\udc47)) = \ud835\udc3b \ud835\udc45 ( 1 \ud835\udc47\ud835\udc5f \u2212 1 \ud835\udc47 ) (2) Since the temperature in the current study is constant options 3-5 will be disregarded. The Prony series shear moduli is written in the following form [3]. \ud835\udc3a(\ud835\udc61) = \ud835\udc3a0 [\ud835\udefc\u221e \ud835\udc3a + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3a \ud835\udc5b\ud835\udc3a \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3a)] (3) Where \ud835\udc3a(\ud835\udc61) is the shear moduli, \ud835\udc3a\ud835\udc5cis the shear modulus of the material. \ud835\udefc is the relative moduli, n is the number of prony terms, and \ud835\udf0f is the relaxation time. Relaxation time is defined as the ratio of viscosity to stiffness of the material. Equation 3 can be rewritten in terms of the bulk moduli as well which is used in \u201cProny Volumetric Relaxation\u201d. This can be found in equation 4. Equations 4 and 3 are derived from the mechanistic rheological model seen in Figure 1. \ud835\udc3e(\ud835\udc61) = \ud835\udc3e0 [\ud835\udefc\u221e \ud835\udc3e + \u2211 \ud835\udefc\ud835\udc56 \ud835\udc3e \ud835\udc5b\ud835\udc3e \ud835\udc56=1 exp (\u2212 \ud835\udc61 \ud835\udf0f\ud835\udc56 \ud835\udc3e)] (4) The Prony Series is implemented in most FEA software. In Ansys, the inputs for the Prony Series are the relative moduli and relaxation time which are found in equations 4 and 3. To experimentally find these parameters material laboratory testing has to occur. The tests will have 4 to measure the shear and bulk modulus of the materials with respect to time. One of the tests includes a creep test where constant stress is applied to a specimen and the strain is recorded [5]. Table 1 shows test data that has been input into Ansys for a 4-bar linkage to study the effects of viscoelasticity. 5 As seen in Figure 3, the deflection induced on the mechanism takes time to converge to 0 even when there is no load applied. The ABS elastic modulus input into ANSYS is 2.62 GPa and has a Poisson Ratio of 0.37. 2.2. ABS Material Property Research and Application Finding accurate ABS material properties was pivotal for the design process of the project. This is to apply them to a 4-bar compliant mechanism in ANSYS. The 4-bar structure was designed based on a report with experimental results [6]. Load: - A 10 N force is applied on surface A in the negative x direction. - The load is ramped up to 10 N over 100 seconds and relaxed until 2000 seconds. Boundary Conditions: - Surface B is constrained in all degrees of freedom. 6 Geometry: - All linkages have the same geometry and are 7 in x 1 in x 3/16 in. The bottom linkage is 7 in. x 1.57 in. x 3/16 in. The ABS viscoelastic material properties were found in a research paper where material testing was done. The results can be seen in the tables below for shear and bulk modulus. The assumption that takes place in the experiment is that the Poisson ratio is constant which is accurate for a FEA analysis. find the relative moduli and relaxation time found in equations 3 and 4. 7 It can be seen in Figure 6 that the deformation of the compliant mechanism returns to 0 after 2000 seconds. This shows that the material is still in the elastic phase and there is no permanent deformation. It is also seen that the deformation is large for the compliant mechanism. There is a total shift of 3.3 cm. The equivalent von Misses stress is 30.2 MPa for this load case, leaving a safety factor of 1.45, the max yield stress is assumed to be 44 MPa. It is possible to increase the deformation of the compliant mechanism while maintaining structural integrity. 8 2.3. Modal Analysis of Viscoelastic Material A modal analysis of viscoelastic material was done to see if there were any effects on the natural frequency of the model. The modal analysis took place on the four bar linkage found in section 2.2. The only addition was that the 4 bar linkage was fixed along z to decrease complexity. A random vibration test was also done between a viscoelastic and non-viscoelastic model to see if there were any differences. The results of the model can be seen in the figure below. Figure 7 shows that viscoelasticity has no effect on the natural frequency of the structure. In reality, this is not the case because a viscoelastic material adds dampening as seen in Figure 1. The reason why the FEA results show no changes is because modal analysis is a linear analysis while viscoelasticity is non-linear. Figure 8 shows a random vibration analysis which shows the same results for the viscoelastic and non viscoelastic systems. A PSD G acceleration was applied over a range of frequencies. The same reasoning applies to the random vibration results as the modal analysis results. In reality, the effects of viscoelasticity reduce the natural frequency of a system [7]. 9 2.4. First Design Approach \u2013 Gripper Like Design After understanding the fundamentals of a compliant mechanism, alongside viscoelasticity section 2.4 focuses heavily on the design of the landing gear. The landing gear in section 2.4 is inspired by the design of a large-displacement-compliant mechanism. The mechanism is based on an inverter. The results of the force and displacement of the mechanism can be seen in Figure 9. 10 The main goal for a large displacement compliant mechanism is to apply deformation to an input and increase the deformation in the output by utilizing a mechanism that produces a mechanical advantage. The mechanical advantage in the inverter mechanism is an average of 2 and can be seen in Table 5. The first iteration of the compliant landing gear can be found below. The motion of the landing gear is to extend the legs parallel to the ground. Note that the thickness of the compliant mechanism is 3/16in. The first iteration of the mechanism had a 0.46 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio which was minimal. The force that was being applied to the structure was 400 N. The next 3 iterations are designed to increase the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio while pushing the structure to its maximum yield stress. 11 12 The final design, (iteration 4) achieves a 6:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio at its maximum yield stress (44 MPa). The main change between the first iteration and fourth iteration was the placement of the force and the thickness of the compliant joints. Thinner joints result in less stiffness resulting in higher deformation which is favorable in a compliant mechanism. Thin joints can pose some disadvantages, especially in crash tests. A standard 5 m/s crash test was done in ANSYS to compare to competitor drones [9]. The crash test consists of an impact analysis of the landing gear against concrete. The impact test results in buckling of the joint that extends the landing legs. This occurs due to how thin the section is. 13 2.5. Second Design Approach \u2013 4 Bar Linkage The design of the previous section wasn\u2019t reliant on mathematical parameters; rather, it was guided by intuition and underwent an iterative design process to reach the highest \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio. The design in section 2.5 was changed to similarly match the current design seen in Figure 15. The improvement that can be done to the reference mechanism is changing it to a compliant mechanism. This will reduce the weight of the rotorcraft and will reduce system complexity. Due 14 to the viscoelastic nature of ABS, the gas spring can be taken out. The parameter that will be optimized during the design is \ud835\udefe. The optimal \ud835\udefe is determined to be around 6 \u2013 15 degrees for rotorcraft [10]. \ud835\udc3f1 and \ud835\udc3f2 are 305 mm and 102 mm respectively. The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application. Manufacturing a joint with that little thickness is very hard, especially for current-day 3D printers. Applying a force that is less than 0.1 N is difficult, this also means that the structure will fail under any load applied to the mechanism. By looking at equation 7, increasing the thickness (b) of the mechanism will increase its moment of inertia making it capable of handling more load. This can result in reducing the thickness (t) of the joint which will increase the deflection of the mechanism. After some optimization, a final design is produced. The final design can be seen in Figure 22, and deflection and stress results in Figures 23 - 24. 17 18 19 The final design shows a structure that can be manufactured and tested to achieve a gamma of 5 degrees. While this does not meet the maximum 15-degree threshold it shows that it is possible to reach that degree with further optimization. 2.5.1. Second Design Approach - 4 Bar Linkage Optimization Equation 8 shows multiple parameters that can be changed to increase the angle. A parameter that was tested was the moment of inertia parameter \ud835\udc3c. This would be possible by adding more joints to the system. This ensures that the t value stays constant while the I value increases. When calculating Equation 8 for the design in Figure 22, \ud835\udc3c would be multiplied by a factor of 4. If more joints are added, theoretically the factor will increase which can double or triple \ud835\udefe. The conceptual design can be seen in Figure 25. Figure 26 shows the deformation in the y-axis. 20 Comparing the 10 joint design to the 4 joint design the \ud835\udefe values increase but not as predicted. This means that adding more joints will have some diminishing returns. The stress also increased in the 10 joint design since the load was more concentrated on the joints that were closer to the boundary condition and load application. Figure 27 shows that the middle joints do not have any stresses being imposed on them making a jointed section there futile. The next step was to minimize the number of joints that would be used and put them closer to the boundary condition and load application areas. This can be seen in Figure 28. The number of joints was reduced from 10 to 8 since diminishing returns were discovered in the last design. The same loading and boundary conditions were applied to keep the study 21 consistent with previous designs as a trade study. The Figures below show the stress and deflection of the bodies. The 8 joint mechanism improves on the 10 joint mechanism. \ud835\udefe was increased by 1.81 while the stress value was maintained. The main technique that was used to improve this value was by concentrating the complaint joints where the loads would be imposed. While the \ud835\udefe value is still less than the required which is 15 degrees, other factors were investigated to reach 15 degrees. ABS has been the main material of study. Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]. To size the pantograph in a way where a sufficient mechanical advantage would be achieved, the equations below are used [15]. \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = \ud835\udc42\ud835\udc35 \ud835\udc42\ud835\udc34 = \ud835\udc35\ud835\udc38 \ud835\udc34\ud835\udc37 (9) R here is a ratio that will output the pantograph\u2019s mechanical advantage. The letters in Equation 9 represent the segments seen in Figure 33. The compliant mechanism being tested in the reference material utilizes metals that do not require thick members to support the load. Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system. Table 12 represents the final results of the 3 designs. Table 11: Material and compliant joint properties in the 3 pantograph designs. Figure 36: Load and BC definition. Parameter Value Input Displacement (mm) 1 E (GPa) 2.62 b (mm) 17.5 t (mm) 2 R (mm) 5.25 27 It is important to note that the mesh in Figure 36 is finer around the joints as that is where the stress concentrations would occur. mechanical advantages of the pantograph designs do not vary as much. The FEA study justifies the choice of design 1 for further optimization. The joint geometry properties in Table 11 were based on intuition and no optimization was made for them. A parametric study on the radius of the joints will be conducted on ANSYS. The parametric design results can be seen below. 28 As seen in the data provided, increasing the radius which makes the thickness of the joint part smaller results in a better \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 value and reduces the overall stress imposed on the joints. It also shows a y deformation close to 7 mm which is what was predicted by equation 10. It might seem tempting to continue the increase in the radius of the body but due to manufacturing limits a thickness of 1.1 mm will suffice. The pantograph design \ud835\udefe heavily depends on the distance between both legs. This distance is determined by using the results from the previous analysis and pantograph designs, a final pantograph is produced in the figure below. The final results of the pantograph design can be seen in the table below. The deformation plots for all pantograph designs can be seen in the Appendix. Design Parameters Values \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b 6.85 \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 0.028 \ud835\udf0e\ud835\udc63\ud835\udc5c\ud835\udc5b\u2212\ud835\udc40\ud835\udc56\ud835\udc60\ud835\udc60\ud835\udc52\ud835\udc60 (MPa) 45.5 \ud835\udefe (deg) 15.03 While the pantograph design achieves the 15 degrees angle, it requires the legs to be close to each other which can cause instability during landing. This has to be taken into account when utilizing this design. 29 2.7. Fourth Design Approach \u2013 Slider Crank \u2013 Literature Study All previous designs contained a linear force to achieve the required \ud835\udefe value. An input rotational system has yet to be considered. As seen in Figure 15 the dynamic landing gear mechanism uses a rotational motor. The motor can be connected to both legs and because of the dynamics, one leg would rise while the other leg would go down. Since a linear output is required, utilizing a slider crank mechanism will be ideal. A paper showing a complaint mechanism of a slider crank can be seen in Figure 39 [16]. The hinges seen in Figure 39 are not the standard circular compliant joints seen in this thesis report. Similar to section 2.5, there are governing equations that can be used to optimize for the stroke produced by the slider crank while maintaining reasonable stress levels. These equations are derived as a result of the PRBM [16]. \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) (11) \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc3f\ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (12) Where \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 is the stroke of the slider, \ud835\udc3f is the length of \ud835\udc5f2, \ud835\udc5f5, \ud835\udc5f7 which can be seen in Figure 40, \ud835\udefe\ud835\udc5f is the characteristic radius factor, which can be determined from the Howell reference [17]. \u0394\ud835\udefd is the input rotational displacement, \ud835\udf03 is the angle with respect to the horizontal, \ud835\udc3e\ud835\udf03 is the 30 stiffness found from the PRBM model, lastly \ud835\udf19 can be determined from the Howell reference [17]. To maximize the total stroke while maintaining the stress, Equation 13 can be derived. \u0394\ud835\udc46\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2 \ud835\udc3e\ud835\udf03\ud835\udc38\ud835\udf03\ud835\udc61\ud835\udc39\ud835\udc3a\ud835\udefe\ud835\udc5f[1 \u2212 \ud835\udefe\ud835\udc5f(1 \u2212 cos(\ud835\udf03)] \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65\ud835\udc60\ud835\udc56\ud835\udc5b(\ud835\udf19 \u2212 \ud835\udf03) \ud835\udc60\ud835\udc56\ud835\udc5b ( \u0394\ud835\udefd 2 ) (13) A design example conducted by Tan\u0131k [16] shows that for an L of 100 mm, the resultant stroke is 68.4 mm while the stress is around 34 MPa. An image of the FEA model is shown below. 31 It is important to note that the stroke takes into account the forward and reverse lengths. In the case of the landing gear, half the stroke will be utilized. This means that 33.6 mm are produced against 100 mm of length. When calculating \ud835\udefe which symbolizes the angle seen in Figure 15 it would be a simple tangent equation. \ud835\udefe = tan\u22121 ( 33.6 100 ) = 18.57\u00b0 (14) As seen in equation 14 the slider crank mechanism has a very high capability of reaching large \ud835\udefe while maintaining reasonable stresses. A design change that would have to occur for the slider crank mechanism in Figure 39 is a landing leg would have to be designed to increase surface area when landing. 3. Future Work Future work will focus on implementing an optimization study for design (slider crank) since the work that was done for the thesis currently was a literature study. The fourth design seems promising because it solves the problem of the pantograph where instability would occur during landing. It also fixes the issue of the 4 bar linkage where reaching a \ud835\udefe of 15 degrees was challenging unless PLA was used which is a very elastic material. Other mechanisms will have to be investigated and tested to determine which type of mechanism works best with a landing compliant mechanism. The thesis focused heavily on achieving the required \ud835\udefe but did not focus on the impact loads that will occur on the landing gear. It is important to keep in mind that with compliant mechanisms there are always trade offs between too much deformation, too little deformation, and balancing stresses and loads. The materials studied in this thesis report were very limited and only one part was 3D printed. Future work can contain a trade off study between different types of 3D printed material and how they behave on the same compliant mechanism. Other materials can also be investigated as all the PRBM equations contain some type of material property. 32 4. Conclusion Current widespread mechanisms utilize joints, springs, screws, and other components that increase product weight, complexity, and maintenance time. Compliant mechanisms use flexure hinges that deform elastically under load. A compliant mechanism maximizes the deflection while maintaining the structural integrity of the product. Materials with a low elastic modulus are usually used for compliant mechanisms as they have a tendency to elastically deform better than materials with a larger elastic modulus. ABS is studied as the main material in this thesis research. ABS is a viscoelastic material that introduces a time-dependent nature of shear and bulk modulus to the mechanisms that are studied. It was found that in FEA the natural frequency of an object does not change if viscoelasticity is added to the system. This is not accurate to real conditions. A mechanism designed with a mechanical advantage and a compliant mechanism was created. A ratio of the input displacement and output displacement is an important parameter to gauge when designing a compliant mechanism. Since the area of research in this thesis project is landing gears, an impact analysis took place at 5 m/s to simulate a crash test. It was found that a compliant mechanism would buckle under that speed without the added weight of the UAV. This adds a design challenge. The dynamic rotorcraft landing gear design utilizes joints with a spring that is capable of having a gamma of 15\u00b0. 4 different designs were created to replace the traditional mechanism with compliant mechanisms. The first design is a gripper like landing design which did not focus on the \ud835\udefe value and more on the parallel movement of the landing legs with the ground. The second design was a four bar linkage design that was 3D printed with PLA to achieve a \ud835\udefe value of 15.6\u00b0. The third design was a pantograph mechanism was used and achieved a \ud835\udefe value of 15\u00b0. The final design was a slider crank mechanism and achieved a \ud835\udefe of 18.57 degrees\u00b0. During the design phase, numerous methodologies were utilized including 3D printing, FEA parametric analysis, and mathematical theory. 33" + ] + }, + { + "image_filename": "designv8_17_0004028_f_version_1585038971-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004028_f_version_1585038971-Figure1-1.png", + "caption": "Figure 1. Basic structure of the generator.", + "texts": [ + " The other type, concentrated winding, is evenly and symmetrically distributed on both sides of the generator middle plane, enabling the generator to operate in an electric state. The stator magnetic yoke composed of magnetic material comprises evenly divided stator pole boots with stator slots between them. The concentrated windings are placed on the stator pole boots. When the generator is used in the electric state, the concentrated windings conduct external power supply and deflect the rotor. Figure 1 shows the basic structural diagram of the generator. Energies 2020, 13, 1524 4 of 22 Energies 2020, 13, x FOR PEER REVIEW 4 of 22 The designed wind generator is suitable for small power applications, owing to its simple structure and installation. The proposed generator can also perform grid-connected operations. The generator uses a battery to store electricity; hence, it requires several batteries to obtain a high rated output voltage. The output voltage selected herein is not significantly high to reduce the cost of the complete machine" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002542_f_version_1490059570-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002542_f_version_1490059570-Figure1-1.png", + "caption": "Figure 1. Sample fractional-slot concentrated winding (FSCW)-interior permanent-magnet motor (IPM) with Qs =12 slots and p=8 poles.", + "texts": [ + "com/journal/energies Energies 2017, 10, 379 2 of 19 However, while the above loss models indeed are useful, they are most suitable for comparing the relative change in eddy-current losses for different combinations of Qs and p rather than accurately predicting the losses for given PM dimensions. Particularly, the effect of segmentation of the magnets and the impact of the skin effect is challenging. Additionally, these models target surface-mounted PMs rather than IPMs (a typical FSCW-IPM motor with Qs = 12 slots and p = 8 poles is depicted in Figure 1). Having a good approximation of the resulting PM losses is important for the machine designer since relatively small losses in the PMs can result in excessive temperatures due to the difficulty of transferring the resulting heat across the air gap. Essentially, predicting the losses in the PMs can be done accurately using three-dimensional (3D) finite-element (FEM)-based simulations (as demonstrated in [17]). However, the approach must still be considered relatively time consuming, although efforts have been made to reduce the computation times [18]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002923_v.org_pdf_2403.10934-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002923_v.org_pdf_2403.10934-Figure1-1.png", + "caption": "Fig. 1: Quadrotor model and coordinate frames.", + "texts": [ + " \u2022 Our controller features global stability and uses the inherent characteristics of quaternion dynamics in S3 to achieve such remarkable performance. \u2022 We compare our results with common controllers [19, 22, 23], and show consistent improvements in flight performance while minimizing actuator effort and saturation. II. QUADROTOR DYNAMICS This section presents the equations of flight for quadrotors to establish the notation for our control developments. Consider the inertial and body-fixed frames, Fe = {e1, e2, e3} and Fb = {b1,b2,b3}, as illustrated in Fig. 1. Define \u03be = [x, y, z] T to be the position of the vehicle, v \u2208 R3 the velocity, q = [ qw, q\u20d7 T ]T \u2208 S3 the unit quaternion representing the attitude, and \u03c9 \u2208 R3 the angular velocity. Then, the quadrotor flight dynamics is x\u0307 = \u03be\u0307 v\u0307 q\u0307 \u03c9\u0307 = v \u2212ge3 + 1 mq\u2217 \u2297 fe3 \u2297 q+ da 1 2q\u2297 [ 0 \u03c9 ] J\u22121 (\u2212\u03c9 \u00d7 J\u03c9 + \u03c4 ) + d\u03b1 , (5) where \u2297 is the quaternion product, q\u2217 is the conjugate of q, g is the gravity, m is the mass, J is the inertia matrix, f is the thrust, \u03c4 is the moments, and da and d\u03b1 are bounded external disturbances", + " We define the control input u \u2208 R4 to be the vector of thrusts generated by the rotors, given by u = ct\u2126 \u25e62, where \u2126 is the vector encompassing the angular rate of rotors, ct is the rotors\u2019 thrust coefficient, and \u25e6 is the Hadamard power. The control input maps to the force and moments applied on the quadrotor through [ f \u03c4 ] = Gu, (6) where G = 1 1 1 1 l sin(\u03b2) \u2212l sin(\u03b2) \u2212l sin(\u03b2) l sin(\u03b2) \u2212l cos(\u03b2) l cos(\u03b2) \u2212l cos(\u03b2) l sin(\u03b2) \u2212cq/ct \u2212cq/ct cq/ct cq/ct , (7) with cq being the rotors\u2019 torque coefficient and \u03b2 and l being geometric parameters defined in Fig. 1. III. CONTROLLER DESIGN This section presents the proposed 6-DOF quaternionbased sliding mode controller for quadrotors. Figure 2 illustrates the controller architecture. The reference trajectory consist of desired position \u03bed and heading b1r = [cos\u03c8d, sin\u03c8d, 0] T . To deal with the vehicle under-actuation, we employ a cascaded control structure including position and attitude control loops. We use SMC for both position and attitude control, enabling the robustness benefits of SMC for both control loops, as opposed to many position-only or attitude-only SMC designs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003966__130_1_130_1_84__pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003966__130_1_130_1_84__pdf-Figure7-1.png", + "caption": "Fig. 7. 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\u308c\u308b\u3002\u975e\u653e\u5c04\u578b\u306e\u96fb\u78c1\u8a98\u5c0e\u3068\u96fb\u78c1\u754c\u7d50\u5408\uff0c\u305d\u3057\u3066\u653e\u5c04\u578b\u306e \u30de\u30a4\u30af\u30ed\u6ce2\u96fb\u529b\u4f1d\u9001\u3068\u30ec\u30fc\u30b6\u30fc\u96fb\u529b\u4f1d\u9001\u3067\u3042\u308b\u3002\u53b3\u5bc6\u306b\u5206 \u304b\u308c\u3066\u3044\u308b\u8a33\u3067\u306f\u306a\u3044\u304c\uff0c\u5468\u6ce2\u6570\u8ef8\u3067\u307f\u308b\u3068 Fig. 1\u306e\u3088\u3046 \u306b\uff0c\u96fb\u78c1\u8a98\u5c0e\uff0c\u96fb\u78c1\u754c\u7d50\u5408\uff0c\u30de\u30a4\u30af\u30ed\u6ce2\u9001\u96fb\uff0c\u30ec\u30fc\u30b6\u30fc\u9001 \u96fb\u3068\u3044\u3046\u9806\u306b\u306a\u308b\u3002 \u672c\u7a3f\u3067\u8ff0\u3079\u308b\u96fb\u78c1\u754c\u7d50\u5408\u306f\u78c1\u754c\u7d50\u5408\u3068\u96fb\u754c\u7d50\u5408\u306e 2\u7a2e\u985e \u304c\u3042\u308b\u3002\u305d\u306e\u540d\u306e\u901a\u308a\uff0c\u78c1\u754c\u7d50\u5408\u306f\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\u3068\u53d7\u4fe1\u30a2 \u30f3\u30c6\u30ca\u304c\u78c1\u754c\u3067\u7d50\u5408\u3057\uff0c\u96fb\u754c\u7d50\u5408\u306f\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\u3068\u53d7\u4fe1\u30a2 \u30f3\u30c6\u30ca\u304c\u96fb\u754c\u3067\u7d50\u5408\u3059\u308b\u73fe\u8c61\u3067\u3042\u308b\u3002\u66f4\u306b\uff0c\u5171\u632f\u72b6\u614b\u3067\u96fb \u78c1\u754c\u306e\u7d50\u5408\u3092\u884c\u306a\u3046\u3053\u3068\u306b\u3088\u308a\u96fb\u529b\u4f1d\u9001\u3092\u5b9f\u73fe\u3055\u305b\u308b\u3002\n3. \u78c1\u754c\u7d50\u5408\u306b\u3088\u308b\u96fb\u529b\u4f1d\u9001\u2014\u30d8\u30ea\u30ab\u30eb\u30a2\u30f3\u30c6\u30ca\u2014\n\u78c1\u754c\u7d50\u5408\u3067\u4f7f\u7528\u3059\u308b\u30d8\u30ea\u30ab\u30eb\u30a2\u30f3\u30c6\u30ca\u306e\u30e2\u30c7\u30eb\u3092 Fig. 2 \u306b\u793a\u3059\u3002\u30a2\u30f3\u30c6\u30ca\u7d20\u5b50\u5358\u72ec\u306e\u7279\u6027\u3092\u8abf\u3079\u308b\u969b\u306f\uff0cFig. 2(a) \u306e 1\u7d20\u5b50\u306e\u7279\u6027\u3092\u8abf\u3079\u308b\u3002\u307e\u305f\uff0c\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\u3068\u53d7\u4fe1\u30a2\u30f3 \u30c6\u30ca\u9593\u306e\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u3092\u8abf\u3079\u308b\u969b\u306b\u306f\uff0cFig. 2(b)\u306e 2\u7d20\u5b50 \u306b\u304a\u3051\u308b\u7279\u6027\u3092\u8abf\u3079\u308b\u3002\u9001\u4fe1\u5074\u3068\u53d7\u4fe1\u5074\u306e\u30a2\u30f3\u30c6\u30ca\u306f\u540c\u3058 \u30a2\u30f3\u30c6\u30ca\u3092\u4f7f\u7528\u3059\u308b\u3002\u30a2\u30f3\u30c6\u30ca\u30d1\u30e9\u30e1\u30fc\u30bf\u306f Fig. 3\u306b\u793a\u3059\u3002 \u30d8\u30ea\u30ab\u30eb\u30a2\u30f3\u30c6\u30ca\u306e\u7279\u6027\u3092\u30e2\u30fc\u30e1\u30f3\u30c8\u6cd5\u306b\u3088\u308b\u96fb\u78c1\u754c\u89e3\u6790 \u3067\u793a\u3059\u3002\u53cd\u5c04\u4fc2\u6570 S 11\uff0c\u900f\u904e\u4fc2\u6570 S 21 \u306b\u5bfe\u3057\uff0c\u53cd\u5c04\u96fb\u529b\u306e \u52b9\u7387\u3092 \u03b711\uff0c\u900f\u904e\u96fb\u529b\u306e\u52b9\u7387\u3092 \u03b721 \u3068\u3059\u308b\u3068\uff0c(1)\uff0c(2)\u5f0f\u306e \u3088\u3046\u306b\u793a\u305b\u308b\u3002\n\u03b711 = |S 11|2 \u00d7 100 [%] \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (1)\n\u03b721 = |S 21|2 \u00d7 100 [%] \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (2)\n\u30a2\u30f3\u30c6\u30ca\u304c 1\u7d20\u5b50\u306e\u5834\u5408\u3068\u9001\u53d7\u4fe1\u30a2\u30f3\u30c6\u30ca\u306e\u8a08 2\u7d20\u5b50\u306e \u5834\u5408\u306b\u304a\u3051\u308b\uff0c\u5468\u6ce2\u6570\u306b\u5bfe\u3059\u308b \u03b711\uff0c\u03b721 \u3092 Fig. 4\u306b\u793a\u3059\u3002 1\u7d20\u5b50\u306e\u5834\u5408\u306f\u3069\u306e\u5468\u6ce2\u6570\u3067\u3082\u307b\u307c\u5168\u53cd\u5c04\u3092\u8d77\u3053\u3057\u3066\u304a\u308a\uff0c \u96fb\u6e90\u5074\u306b\u96fb\u529b\u304c\u623b\u3063\u3066\u3044\u308b\u3002\u5171\u632f\u5468\u6ce2\u6570\u306e\u6642\u306b\u95a2\u3057\u3066\u306f\u50c5 \u304b\u306b\u640d\u5931\u304c\u767a\u751f\u3057\u3066\u3044\u308b\u3002\u672c\u7a3f\u3067\u63d0\u6848\u3059\u308b\u30a2\u30f3\u30c6\u30ca\u5f62\u72b6\u306f \u6ce2\u9577\u306b\u5bfe\u3057\u975e\u5e38\u306b\u5c0f\u3055\u3044\u3002\u305d\u306e\u305f\u3081\uff0c\u5171\u632f\u72b6\u614b\u306b\u304a\u3044\u3066\u3082 \u5358\u72ec\u306e\u30a2\u30f3\u30c6\u30ca\u3068\u3057\u3066\u306f\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u30de\u30c3\u30c1\u30f3\u30b0\u304c\u96e3\u3057 \u304f\uff0c\u96fb\u78c1\u6ce2\u3092\u653e\u5c04\u51fa\u6765\u306a\u3044\u306e\u3067\u653e\u5c04\u640d\u306f\u307b\u307c0%\u3067\u3042\u308b\u3002\u305d \u306e\u305f\u3081\uff0c\u3053\u3053\u3067\u306e\u4e3b\u306a\u640d\u5931\u306f\u9285\u640d\u3067\u3042\u308b\u3002\u4e00\u65b9\uff0c2\u7d20\u5b50\u306e \u5834\u5408\u306f\uff0c\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\u304b\u3089\u53d7\u4fe1\u30a2\u30f3\u30c6\u30ca\u306b 2\u3064\u306e\u5171\u632f\u5468\u6ce2 \u6570\u306b\u304a\u3044\u3066\u9ad8\u52b9\u7387\u306e\u96fb\u529b\u4f1d\u9001\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002\u307e\u305f\uff0c\u3053\u306e\u3053 \u3068\u306b\u95a2\u3057\u3066\u306f\uff0c\u30083\u30fb3\u30fb1\u3009\u3067\u8a73\u7d30\u306b\u8ff0\u3079\u308b\u3002\n\u30083\u30fb1\u3009 \u30ae\u30e3\u30c3\u30d7 \u30ae\u30e3\u30c3\u30d7\u3092\u5909\u5316\u3055\u305b\u305f\u6642\u306e\u5468\u6ce2\u6570 \u306b\u5bfe\u3059\u308b \u03b711\uff0c\u03b721 \u3092 Fig. 5 \u306b\u793a\u3059\u3002k \u306f\u7d50\u5408\u4fc2\u6570\u3067\u3042\u308b\u3002 \u30ae\u30e3\u30c3\u30d7\u304c\u5c0f\u3055\u3044\u6642\u306f\u30d4\u30fc\u30af\u3068\u306a\u308b\u5171\u632f\u5468\u6ce2\u6570\u304c 2\u3064\u3068\u306a \u308b\u3002\u305d\u3057\u3066\uff0c\u30ae\u30e3\u30c3\u30d7\u304c\u5927\u304d\u304f\u306a\u308b\u3068 2\u3064\u306e\u30d4\u30fc\u30af\u304c 1\u3064 \u306b\u306a\u308b\u3002\u30d4\u30fc\u30af\u304c 2\u3064\u306e\u6642\uff0c\u30d4\u30fc\u30af\u3068\u306a\u308b\u5171\u632f\u5468\u6ce2\u6570\u306f\u5909 \u5316\u3059\u308b\u304c\uff0c\u6700\u5927\u52b9\u7387\u306f\u4e00\u5b9a\u3067\u3042\u308b\u3002\u3057\u304b\u3057\uff0c\u30d4\u30fc\u30af\u304c 1\u3064\u306b \u306a\u308b\u3068\u52b9\u7387\u304c\u60aa\u5316\u3059\u308b\u3002\u78c1\u754c\u7d50\u5408\u306b\u304a\u3044\u3066\uff0c2\u3064\u306e\u30d4\u30fc\u30af\u3068 \u306a\u308b\u5171\u632f\u5468\u6ce2\u6570\u3092 f \u2032m\uff0cf \u2032e ( f \u2032m < f \u2032e ) \u3068\u3059\u308b\u3002\u307e\u305f\uff0cFig. 5(a)\uff0c (b)\u306e 2\u3064\u306e\u30d4\u30fc\u30af\u3068\u306a\u308b\u5468\u6ce2\u6570\u306e\u9593\u306e\u8c37\u306b\u5f53\u308b\u5468\u6ce2\u6570\u3068 Fig. 5(d)\u306e 1\u3064\u306e\u30d4\u30fc\u30af\u3068\u306a\u3063\u305f\u6642\u306e\u5171\u632f\u5468\u6ce2\u6570\u306f\u30a2\u30f3\u30c6 \u30ca 1\u7d20\u5b50\u306e\u6642\u306e\u5171\u632f\u5468\u6ce2\u6570 f0 \u306b\u307b\u307c\u7b49\u3057\u3044\u3002\n\u30083\u30fb2\u3009 \u8fd1\u508d\u306b\u304a\u3051\u308b\u96fb\u78c1\u754c\u5206\u5e03 \u30a2\u30f3\u30c6\u30ca\u8fd1\u508d\u3067\u306e \u96fb\u78c1\u754c\u306e\u632f\u308b\u821e\u3044\u3092 Fig. 6\uff0cFig. 7\u306b\u793a\u3059\u3002\u5168\u3066\u78c1\u754c\u5206\u5e03\u3067 \u3042\u308b\u30022\u3064\u306e\u5171\u632f\u5468\u6ce2\u6570 f \u2032m\uff0c f \u2032e ( f \u2032m < f \u2032e )\u306b\u304a\u3044\u3066\u975e\u5e38\u306b \u7279\u5fb4\u7684\u306a\u5206\u5e03\u3092\u793a\u3059\u3002\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\u3068\u53d7\u4fe1\u30a2\u30f3\u30c6\u30ca\u306e\u5bfe\u79f0 \u9762\u306b\u304a\u3051\u308b\u78c1\u754c\u306e\u69d8\u5b50\u306b\u6ce8\u76ee\u3059\u308b\u3068\uff0cf \u2032m \u306b\u304a\u3044\u3066\u306f\u5bfe\u79f0\u9762 \u304c\u78c1\u6c17\u58c1\u3068\u306a\u308b\u3002\u78c1\u6c17\u58c1\u3068\u306f\uff0c\u5bfe\u79f0\u9762\u306b\u5782\u76f4\u306b\u78c1\u754c\u304c\u5206\u5e03 \u3059\u308b\u73fe\u8c61\u3067\u3042\u308b\u3002\u4e00\u65b9\uff0c f \u2032e \u306b\u304a\u3044\u3066\u306f\uff0c\u5bfe\u79f0\u9762\u304c\u96fb\u6c17\u58c1\u3068\n\u96fb\u5b66\u8ad6 D\uff0c130 \u5dfb 1 \u53f7\uff0c2010 \u5e74 85", + "\u306a\u308b\u3002\u96fb\u6c17\u58c1\u3068\u306f\uff0c\u5bfe\u79f0\u9762\u306b\u6c34\u5e73\u306b\u78c1\u754c\u304c\u5206\u5e03\u3059\u308b\u73fe\u8c61\u3067 \u3042\u308b\u3002\u3053\u308c\u306f\uff0c\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\u3068\u53d7\u4fe1\u30a2\u30f3\u30c6\u30ca\u306e\u96fb\u6d41\u306e\u632f\u5e45 \u306e\u7d76\u5bfe\u5024\u304c\u7b49\u3057\u304f\u306a\u308b\u306e\u3067\u5bfe\u79f0\u9762\u306b\u3053\u306e\u3088\u3046\u306b\u5206\u5e03\u3057\u3066\u3044 \u308b\u3088\u3046\u306b\u898b\u3048\u308b\u3002\u66f4\u306b\uff0cFig. 7\u306b\u793a\u3057\u305f\u3088\u3046\u306b\u96fb\u6d41\u306e\u5411\u304d \u304c\u78c1\u6c17\u58c1\u306e\u3068\u304d\u306f\u540c\u4f4d\u76f8\u306b\u8fd1\u304f\u306a\u308a\uff0c\u96fb\u6c17\u58c1\u306e\u3068\u304d\u306f\u9006\u4f4d \u76f8\u306b\u8fd1\u304f\u306a\u308b\u3002\u305d\u306e\u305f\u3081\uff0c\u78c1\u6c17\u58c1\uff0c\u96fb\u6c17\u58c1\u3068\u3057\u3066\u306e\u632f\u308b\u821e \u3044\u304c\u78ba\u8a8d\u3055\u308c\u308b\u3002\u5f8c\u306b\u7b49\u4fa1\u56de\u8def\u3067\u8ff0\u3079\u308b\u304c\uff0c\u96fb\u529b\u4f1d\u9001\u52b9\u7387 \u306f (9)\uff0c(10)\u5f0f\u3067\u5b9a\u7fa9\u3055\u308c\u308b\u306e\u3067\uff0c2\u3064\u306e\u5171\u632f\u5468\u6ce2\u6570\u306b\u304a\u3044 \u3066\u5171\u306b\u9ad8\u52b9\u7387\u306e\u96fb\u529b\u4f1d\u9001\u304c\u51fa\u6765\u308b\u3002Fig. 8\uff0cFig. 9\u3067\u306f\u8fd1\u508d \u3067\u306e\u78c1\u754c\u3068\u96fb\u754c\u306b\u3064\u3044\u3066\u793a\u3059\u3002Fig. 9\u306f\u6700\u5927\u5024\u3067\u898f\u683c\u5316\u3057 \u3066\u3042\u308b\u3002\u78c1\u6c17\u58c1\u306e\u6642\u306f\u30b3\u30a4\u30eb\u4e2d\u592e\u90e8\u306b\u304a\u3044\u3066\u306f\u78c1\u754c\u3092\u5f37\u3081 \u5408\u3044\uff0c\u96fb\u6c17\u58c1\u306e\u6642\u306f\u78c1\u754c\u3092\u5f31\u3081\u5408\u3063\u3066\u3044\u308b\u3002\u4e00\u65b9\uff0c\u30b3\u30a4\u30eb \u76f4\u4e0b\u306b\u304a\u3044\u3066\u306f\u78c1\u6c17\u58c1\u306e\u6642\u306f\u78c1\u754c\u3092\u5f31\u3081\u3042\u3044\uff0c\u96fb\u6c17\u58c1\u306e\u3068 \u304d\u306f\u78c1\u754c\u3092\u5f37\u3081\u3042\u3063\u3066\u3044\u308b\u3002\n\u78c1\u754c\u7d50\u5408\u578b\u306e\u30d8\u30ea\u30ab\u30eb\u30a2\u30f3\u30c6\u30ca\u3067\u3042\u308b\u304c\uff0c\u5b8c\u5168\u306b\u96fb\u754c\u7d50 \u5408\u304c\u6d88\u3048\u3066\u306f\u3044\u306a\u3044\u3002Fig. 9(a)\uff0c(b)\u306f\u5bfe\u79f0\u9762\u3067\u306e\u78c1\u754c\u3068\u96fb \u754c\u306e\u5206\u5e03\u3067\u3042\u308b\u304c\uff0c\u30b3\u30a4\u30eb\u306e\u5dfb\u304d\u7dda\u76f4\u4e0a\uff0c\u76f4\u4e0b\u3067\u306f\u96fb\u754c\u30a8 \u30cd\u30eb\u30ae\u30fc\u304c\u50c5\u304b\u306b\u5b58\u5728\u3057\uff0c2\u3064\u306e\u30b3\u30a4\u30eb\u306e\u5bfe\u79f0\u9762\u306b\u304a\u3051\u308b \u78c1\u754c\u3068\u96fb\u754c\u306e\u30a8\u30cd\u30eb\u30ae\u30fc\u5bc6\u5ea6\u306e\u6700\u5927\u5024\u3067\u6bd4\u3079\u305f\u5834\u5408\uff0c\u78c1\u754c \u30a8\u30cd\u30eb\u30ae\u30fc\u5bc6\u5ea6\u306b\u5bfe\u3057\u96fb\u754c\u30a8\u30cd\u30eb\u30ae\u30fc\u5bc6\u5ea6\u306e\u6bd4\u7387\u306f 4%\u7a0b \u3067\u3042\u308b\u3002\u96fb\u78c1\u754c\u7d50\u5408\u306e\u5834\u5408\uff0c\u78c1\u754c\u7d50\u5408\u3068\u96fb\u754c\u7d50\u5408\u3092\u5b8c\u5168\u306b \u5206\u96e2\u3059\u308b\u3053\u3068\u304c\u51fa\u6765\u305a\u306b\uff0ck = |km \u2212 ke|\u306e\u3088\u3046\u306b\u96fb\u754c\u3068\u78c1 \u754c\u306e\u4e21\u65b9\u306e\u5dee\u306e\u7d50\u5408\u3068\u306a\u308b\u5834\u5408\u304c\u591a\u3044\u2020\u3002\u4eca\u56de\u306f\u78c1\u754c\u304c\u652f\u914d \u7684\u3067\u3042\u308a\uff0ck = km \u3068\u307f\u306a\u305b\u308b (10)\uff5e(13)\u3002\n\u30083\u30fb3\u3009 \u78c1\u754c\u7d50\u5408\u306e\u7b49\u4fa1\u56de\u8def \u30a2\u30f3\u30c6\u30ca\u8a2d\u8a08\u3084\u3053\u306e\u30a2\n\u30f3\u30c6\u30ca\u306b\u63a5\u7d9a\u3059\u308b\u5468\u8fba\u56de\u8def\u3092\u8a2d\u8a08\u3059\u308b\u305f\u3081\u306b\u306f\uff0c\u96fb\u78c1\u754c\u7d50 \u5408\u306e\u73fe\u8c61\u3092\u96fb\u6c17\u56de\u8def\u3068\u3057\u3066\u89e3\u91c8\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\u3002\u3088\u3063\u3066\uff0c \u672c\u7bc0\u3067\u306f\u7b49\u4fa1\u56de\u8def\u3078\u306e\u7f6e\u304d\u63db\u3048\u3092\u3057\uff0c\u7b49\u4fa1\u56de\u8def\u3078\u7f6e\u304d\u63db\u3048 \u305f\u3053\u3068\u306b\u3088\u308a\u5c0e\u51fa\u3055\u308c\u308b\u5f0f\u3092\u793a\u3057\uff0c\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u793a\u3059\u610f\u5473 \u3092\u691c\u8a0e\u3059\u308b\u3002\u305d\u3057\u3066\uff0c\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u7b97\u51fa\u65b9\u6cd5\u3092\u793a\u3059\u3002\u6700\u5f8c \u306b\uff0c\u5b9f\u9a13\u7d50\u679c\u3068\u96fb\u78c1\u754c\u89e3\u6790\u3068\u7b49\u4fa1\u56de\u8def\u3092\u6bd4\u8f03\u3059\u308b\u3002\n\u30083\u30fb3\u30fb1\u3009 \u7b49\u4fa1\u56de\u8def\u306b\u3088\u308b\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u5f0f\u306e\u5c0e\u51fa \u30a2 \u30f3\u30c6\u30ca\u306f\u5171\u632f\u3057\u3066\u52d5\u4f5c\u3057\u3066\u3044\u308b\u306e\u3067\uff0cLC \u76f4\u5217\u5171\u632f\u3067\u8868\u305b \u308b\u3002\u653e\u5c04\u640d\u3068\u30aa\u30fc\u30e0\u640d\u3092\u5408\u308f\u305b\u305f\u640d\u5931\u3092R\u3067\u8868\u3059\u3002\u305f\u3060\u3057\uff0c\n\u2020 km \u306f\u78c1\u754c\u306b\u3088\u308b\u7d50\u5408\u4fc2\u6570\u3067\u3042\u308a\uff0cke \u306f\u96fb\u754c\u306b\u3088\u308b\u7d50\u5408\u4fc2\u6570\u3067\u3042\u308b\u3002\n86 IEEJ Trans. IA, Vol.130, No.1, 2010", + "\u78c1\u754c\u7d50\u5408\u3068\u96fb\u754c\u7d50\u5408\n\u640d\u5931\u306e\u5927\u90e8\u5206\u306f\u30aa\u30fc\u30e0\u640d\u3067\u3042\u308b\u3002 \u307e\u305a\uff0c1\u7d20\u5b50\u306b\u304a\u3051\u308b\u30a2\u30f3\u30c6\u30ca\u81ea\u4f53\u306e\u7b49\u4fa1\u56de\u8def\u3092 Fig. 10 \u306b\u793a\u3059\u3002Z0\u306f\u7dda\u8def\u306e\u7279\u6027\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u3067\u3042\u308b\u3002\u3053\u306e\u78c1\u754c \u578b\u30a2\u30f3\u30c6\u30ca\u3092 2\u3064\u4f7f\u7528\u3057\uff0c\u7247\u65b9\u3092\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\uff08L1\uff0cC1\uff0c R1\uff09\uff0c\u3082\u3046\u4e00\u65b9\u3092\u53d7\u4fe1\u30a2\u30f3\u30c6\u30ca\uff08L2\uff0cC2\uff0cR2\uff09\u3068\u3057\u305f\u6642\u306e\u7b49 \u4fa1\u56de\u8def\u3092 Fig. 11\u306b\u793a\u3059\u30022\u3064\u306e\u30a2\u30f3\u30c6\u30ca\u9593\u3067\u306e\u7d50\u5408\u306f\u78c1\u754c \u306b\u3088\u3063\u3066\u884c\u306a\u308f\u308c\u3066\u3044\u308b\u306e\u3067\uff0c\u76f8\u4e92\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9 Lm \u3067 \u7d50\u5408\u3092\u8868\u3059\u3002 \u6b21\u306b\uff0c2\u7d20\u5b50\u306b\u3088\u3063\u3066\u4f5c\u3089\u308c\u308b\u78c1\u754c\u7d50\u5408\u306e\u7b49\u4fa1\u56de\u8defFig. 11 \u3088\u308a\uff0cZ0 = 0\uff0cR = 0\u03a9\u3068\u3057\u305f\u6642\u306e\u5171\u632f\u5468\u6ce2\u6570 fm\uff0cfe\u3092\u6c42\u3081 \u308b\u3002\u5171\u632f\u6761\u4ef6\u3088\u308a\uff0c\u30ea\u30a2\u30af\u30bf\u30f3\u30b9 0\u304b\u3089 (3)\u5f0f\u3092\u5c0e\u304f\u3002\u9001 \u53d7\u540c\u3058\u30a2\u30f3\u30c6\u30ca\u3092\u4f7f\u3046\u306e\u3067\uff0cL = L1 = L2\uff0cC = C1 = C2\uff0c R = R1 = R2 = 0\u3068\u3057\u3066\uff0c\u305d\u3053\u304b\u3089 2\u3064\u306e\u89d2\u5171\u632f\u5468\u6ce2\u6570\uff0c (4)\uff0c(5)\u5f0f\u3092\u5c0e\u304f\u3002(4)\uff0c(5)\u5f0f\u304b\u3089\u7d50\u5408\u4fc2\u6570\u3068 2\u3064\u306e\u5171\u632f\u5468 \u6ce2\u6570\u3068\u306e\u95a2\u4fc2\u5f0f (6)\u3092\u5c0e\u304f\u3002Z0 0\uff0cR 0\u03a9\u306e\u5834\u5408\u306e\u53b3\u5bc6 \u306a\u5171\u632f\u5468\u6ce2\u6570 f \u2032m\uff0c f \u2032e \u306f\u5f0f\u304c\u7169\u96d1\u3068\u306a\u308b\u305f\u3081\u7701\u7565\u3059\u308b\u3002 \u4ee5\u4e0a\u3088\u308a\uff0c\u5171\u632f\u6642\u306e 2\u3064\u306e\u30a2\u30f3\u30c6\u30ca\u3092\u8fd1\u3065\u3051\uff0c\u78c1\u754c\u7d50\u5408 \u304c\u8d77\u3053\u3063\u305f\u6642\uff0c\u5171\u632f\u5468\u6ce2\u6570\u304c 2\u70b9\u73fe\u308c\u308b\u3053\u3068\u304c (4)\uff0c(5)\u5f0f \u304b\u3089\u308f\u304b\u308b\u3002Fig. 5\u3088\u308a\uff0c\u30ae\u30e3\u30c3\u30d7\u304c\u5c0f\u3055\u304f\u306a\u308a\uff0c\u7d50\u5408\u304c \u5f37\u304f\u306a\u308b\u3068\u5171\u632f\u5468\u6ce2\u6570\u304c\u96e2\u308c\u308b\u3053\u3068\u304c\u78ba\u8a8d\u3055\u308c\u308b\u304c\uff0c\u7d50\u5408 \u4fc2\u6570\u3068 2\u3064\u306e\u5171\u632f\u5468\u6ce2\u6570\u3068\u306e\u95a2\u4fc2 (6)\u5f0f\u304b\u3089\u3082\u5171\u632f\u5468\u6ce2\u6570 \u304c\u96e2\u308c\u308b\u3068\uff0c\u7d50\u5408\u4fc2\u6570\uff0c\u3064\u307e\u308a\u7d50\u5408\u306e\u5f37\u3055\u304c\u5927\u304d\u304f\u306a\u308b\u3053 \u3068\u304c\u308f\u304b\u308b\u3002\u305d\u3057\u3066\uff0c\u30ae\u30e3\u30c3\u30d7\u304c\u5927\u304d\u304f\u306a\u308a\u7d50\u5408\u304c\u5f31\u304f\u306a \u308b\u3068\u5171\u632f\u5468\u6ce2\u6570\u304c 1\u3064\u306b\u8fd1\u3065\u304f\u3002\u305d\u3057\u3066\uff0c\u640d\u5931\u304c\u306a\u3044\u5834\u5408 k = Z0/\u03c90L\u3068\u306a\u3063\u305f\u6642\u70b9\u3067\u30d4\u30fc\u30af\u3068\u306a\u308b\u5468\u6ce2\u6570\u304c\u4e00\u3064\u3068\u306a \u308a\uff0c\u52b9\u7387\u304c\u4f4e\u4e0b\u3057\u59cb\u3081\u308b\u3002\u66f4\u306b\uff0c\u30ae\u30e3\u30c3\u30d7\u304c\u5e83\u304c\u308a fm = fe \u3068\u306a\u3063\u305f\u6642\u306b\u306f\uff0ck = 0\u3068\u306a\u308a\u7d50\u5408\u304c\u306a\u304f\u306a\u308b\u3002\u3064\u307e\u308a\u96fb\u529b \u4f1d\u9001\u304c\u539f\u7406\u7684\u306b\u4e0d\u53ef\u80fd\u3068\u306a\u308b\u3002Z0 = 0\u03a9\u3067\u3042\u308c\u3070\uff0c\u7406\u8ad6\u4e0a k = 0\u3068\u306a\u308b\u307e\u3067\uff0c\u96fb\u529b\u4f1d\u9001\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002\u672c\u7a3f\u3067\u306f\uff0c\u7279\u306b \u660e\u8a18\u3059\u308b\u5834\u5408\u4ee5\u5916\u306b\u304a\u3044\u3066\u306f Z0 = 50\u03a9\u3068\u3059\u308b\u3002\n1 \u03c9Lm + 1\n\u03c9 (L1 \u2212 Lm) \u2212 1 \u03c9C1\n+ 1\n\u03c9 (L2 \u2212 Lm) \u2212 1 \u03c9C2\n= 0\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (3)\n\u03c9m = \u03c90\u221a\n1 + km\n= 1\u221a\n(L + Lm) C \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (4)\n\u03c9e = \u03c90\u221a\n1 \u2212 km\n= 1\u221a\n(L \u2212 Lm) C \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (5)\nkm = Lm L = \u03c92 e \u2212 \u03c92 m\n\u03c92 e + \u03c9 2 m \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (6)\n\u03c90 = 1\u221a LC \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (7) (\u03c90 = 2\u03c0 f0, \u03c9m = 2\u03c0 fm, \u03c9e = 2\u03c0 fe)\n\u6b21\u306b\uff0c\u7b49\u4fa1\u56de\u8def\u3088\u308a\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u3092\u8abf\u3079\u308b\u305f\u3081\u306b\uff0cS 21\u3092 \u6c42\u3081\u308b\u3068\uff0c(8)\u5f0f\u3068\u306a\u308b\u3002S 21\u3092 2\u4e57\u3059\u308b\u3068\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u306b\u306a \u308b\u306e\u306f (2)\u5f0f\u306b\u793a\u3057\u305f\u901a\u308a\u3067\u3042\u308b\u30022\u3064\u306e\u5171\u632f\u5468\u6ce2\u6570 fm\uff0cfe \u3068\u305d\u306e\u9593\u306e\u5468\u6ce2\u6570\u306b\u4f4d\u7f6e\u3059\u308b\u30a2\u30f3\u30c6\u30ca\u5358\u72ec\u3067\u306e\u5171\u632f\u5468\u6ce2\u6570 f0\u306b\u304a\u3044\u3066\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u3092\u5c0e\u304f\u3002\u305d\u308c\u305e\u308c\uff0c(9)\uff0c(10)\uff0c(11) \u5f0f\u3068\u306a\u308b\u3002\u7169\u96d1\u3055\u3092\u907f\u3051\u308b\u305f\u3081\u306b\uff0c(9)\uff0c(10)\uff0c(11)\u5f0f\u306b\u304a\u3044 \u3066\u640d\u5931\u9805 R\u306f\u7701\u7565\u3059\u308b\u3002\u640d\u5931\u3092\u542b\u3093\u3060\u7d50\u679c\u306f\u30083\u30fb3\u30fb3\u3009\u306b\u793a \u3059\u3002S 21 \u304c\u6700\u5927\u3068\u306a\u308b Z0\uff0cR\u3092\u8003\u616e\u3057\u305f\u5171\u632f\u5468\u6ce2\u6570\u3092 f \u2032m\uff0c f \u2032e \u3068\u3059\u308b\u3068\uff0c(12)\u5f0f\u304b\u3089 f \u2032m\uff0cf \u2032e \u3092\u6c42\u3081\uff0c\u7d50\u679c\u3092 (13)\uff0c(14) \u5f0f\u306b\u793a\u3059\u3002\u3053\u308c\u3092 (8)\u5f0f\u306b\u4ee3\u5165\u3059\u308b\u3068 S 21\u304c\u6c42\u307e\u308b\u304c\u5f0f\u304c\uff0c \u8907\u96d1\u306b\u306a\u308b\u306e\u3067\u3053\u3053\u3067\u306f\u7701\u7565\u3059\u308b\u3002 \u6b21\u306b\uff0c f0\uff0c fm\uff0c fe\uff0c f \u2032m\uff0c f \u2032e \u306e\u5927\u5c0f\u95a2\u4fc2\u3092\u793a\u3059\u305f\u3081\u306b\uff0cZ0 \u3092\u53ef\u5909\u3068\u3057 L\uff0cLm\uff0cC \u3092\u56fa\u5b9a\u3068\u3057\u3066\u8003\u3048\u308b\u3002\u640d\u5931\u306a\u3057\u3068\u3057 \u305f\u6642\u306e g = 150 mm\uff0cr = 150 mm\uff0cn = 5 turn\uff0cp = 5 mm\u306b \u304a\u3051\u308b\u7b49\u4fa1\u56de\u8def\u306b\u304a\u3044\u3066\u306f\uff0cFig. 12\u306e\u3088\u3046\u306b\u306a\u308b\u3002\nFig. 12(a) \u306e\u3088\u3046\u306b Z0 = 0 \u306e\u6642\u306b\u304a\u3044\u3066\u306f\uff0c(13)\uff0c(14) \u5f0f\u306b Z0 = 0 \u3092\u4ee3\u5165\u3059\u308b\u3068\uff0c(4)\uff0c(5) \u5f0f\u304c\u5c0e\u304b\u308c\u308b\u3053\u3068\u3088 \u308a\uff0c fm = f \u2032m\uff0c f \u2032e = fe \u3068\u306a\u308b\u3053\u3068\u304c\u308f\u304b\u308b\u3002\u4e00\u65b9\uff0cZ0 \u304c\u5927 \u304d\u304f\u306a\u308b\u3068\u305d\u306e\u5206 Z0 = R = 0\u3068\u3057\u305f\u6642\u306e\u5171\u632f\u5468\u6ce2\u6570 fm\uff0cfe \u3068\uff0cS 21 \u304c\u6700\u5927\u3068\u306a\u308b\u5171\u632f\u5468\u6ce2\u6570 f \u2032m\uff0cf \u2032e \u3068\u306e\u5dee\u304c\u5927\u304d\u304f\u306a \u308b\u3002Lm/ \u221a LC > Z0 \u306e\u6642\uff0c fm < f \u2032m < f0 < f \u2032e < fe \u3068\u306a\u308a\uff0c\nFig. 12(b) \u306e\u3088\u3046\u306b\u30d4\u30fc\u30af\u304c 2 \u3064\u306b\u306a\u308b\u3002Lm/ \u221a LC = Z0\n\u96fb\u5b66\u8ad6 D\uff0c130 \u5dfb 1 \u53f7\uff0c2010 \u5e74 87" + ] + }, + { + "image_filename": "designv8_17_0003548_om_article_19879.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003548_om_article_19879.pdf-Figure6-1.png", + "caption": "Figure 6. A 1KW four-phase six-pole permanent magnet fault-tolerant", + "texts": [], + "surrounding_texts": [ + "1) Permanent magnet material selection In this paper, we chose NdFeB N38H as the permanent magnet material, the remanence density Br20 is 1.23T, the temperature coefficient \u03b1Br is 0.12 %/\u2103, the irreversible demagnetization loss IL is 0.7%, the calculated coercive force of permanent magnet Hc20 is 899kA/m.\nWe can obtain following results according to the selection of NdFeB N38H:\n(1)Remanent flux density during the operating temperature:\n20 [1 ( 20) /100] [1 /100]\n1.18\nr Br r B t IL B\nT\n \n\n(2)Calculated coercive force during the operating temperature:\nmkA\nHILtH cBrc\n/7.833\n]100/1[]100/)20(1[ 20\n\n \n(3)Relative permeability of the permanent magnet:\n20\n0 20\n1.089 1000\nr\nr\nc\nB\nH \nwhere 0 is vacuum permeability, 0=410 -7\nH/m. 2) Determine the shape of permanent magnet Surface magnetic pole structure can improve the ability of isolation between the windings, in this article we use the surface-type tile-shaped magnetic poles in the permanent magnet fault tolerant motor, shown in Fig .3. The structure of permanent magnet contacting the air gap directly is easy processing and installation. And uses a concentric tile-shaped magnetic poles, i.e., the outer diameter and the inter diameter of the permanent magnets have a common center, it shown as in the Fig .4.\n3) Calculate the size of permanent magnet The main size parameters of permanent magnet part include the thickness and the width of permanent magnet, and can be determined by the following formula:\nThe thickness of permanent magnet hM is:\ni\nr\nr\nM\nB\nB h \n\n\n1\n (25)\nThe width of permanent magnet bM is:\n pM b (26)\nwhere \u03bcr is the relative permeability of ferromagnetic material; \u03b4i is the calculating air gap length of motor(cm); Br is the residual magnetic induction intensity of permanent magnet (T); B\u03b4 is the magnetic load (T); \u03b1p is the percentage of pole embrace. Generally Br/B\u03b4 equal to 1.1~1.35.\n4) Permanent magnet magnetization way of design In this paper, the arrangement of permanent magnet is\nin the way of Halbach array [11]\n, this kind of arrangement can not only enhance the air gap flux of motor, but also can weaken the magnetic flux of rotor yoke, which is particularly suitable for the rotor structure of using surface-mounted permanent magnet. Halbach array is a novel magnetic structure array that combines radial array with tangential array, as Fig .5(a) shows, so that we can make the magnetic field in one side of permanent magnet strengthening and the other side weakening. The rational design of Halbach array can make the air-gap flux density and the no-load back electromotive force having good sinusoidal.\nFig .5 (b) shows the distribution of magnetic equipotential line of the permanent magnet motor with Halbach array which is calculated by the ANOSOFT which is one of the finite element analysis software. As we can see, after using Halbach array, the magnetic flux of rotor yoke significantly reduced, while the magnetic flux that across air gap into the stator significantly increased, which increases the magnetic load of permanent magnet motor and the density of force and energy, so Halbach array is very suitable for the ideal for the permanent magnet fault-tolerant motor with the inter rotor structure of permanent magnet posted outside.", + "Rated voltage/V 36 Rated speed/r.min-1 1200\nMagnet Material NdFe\nN38H\nStator and rotor\nmaterial\nDW310-\n35\nOutside stator diameter/mm 131.2\nInside stator diameter/mm 65.6\nStator tooth\nwidth/mm 11.4 Stator yoke thick/mm 5.4\nInside rotor\ndiameter/mm 64 Rotor yoke thick/mm 11.5\nMagnet thickness/mm 8.7 Stator core length/mm 139.3\nNotch thickness/mm 4.6 Percentage of pole\nembrace 0.64\nGap length/mm 0.8 Winding turns of per\nphase 36\nThrough the simulation of ANSOFT software, we determined to use the Halbach array with two pieces of permanent magnet per pole, and the radian numbers of these two pieces of permanent magnet are 35\u00b0 and 25\u00b0. Because we can get the highest sinusoidal waveform of no-load back electromotive force with this radian. According to the design results of this motor, we got the parameters of this 1KW four-phase six-pole structure permanent magnet fault-tolerant motor that listed in Table 1.\nIII. EXPERIMENTAL TESTING OF THIS MOTOR\nBased on the permanents of motor size that designed before, We manufactured a 1KW experimental prototype of this four-phase six-pole permanent magnet fault-tolerant motor. The external appearance is shown in Fig .6.\nmotor\nFig .7 is an actual measured waveform of one phase no-load back electromotive force. From this figure, we can know that the sinusoidal of this waveform displayed very well, so the motor design is reasonably and accurate which laid a good foundation for the control research of fault-tolerant motor.\nIV. CONCLUSION\nIn this paper, for the requirement of power-driven applications with high-reliability, we have researched and designed one kind of permanent magnet motor of four-phase six-pole structure with Halbach array. Based on the characteristics of the motor structure and the analysis of fault-tolerant mechanism, and combined with the principles of electromagnetism and design method of Halbach array, we calculated the main dimensions and the electromagnetic parameters of the 1KW permanent magnet fault-tolerant motor. And through the experimental testing of this motor, we also verified the correctness and rationality of this motor design process.\nThe present paper has been financed by the National Natural Science Foundation of China (61004053, 61273151), Natural Science Foundation of Jiangsu Province (BK20141238), Qing Lan Project of Jiangsu Province, and Postgraduate Research Innovation Program of Jiangsu Province(CXLX13_681).\nREFERENCES\n[1] R. R. Errabelli , P. Mutschler. A fault tolerant digital controller for power electronic applications[C]. 13th Europe Conference on Power Electron Applications, 2009: 1-10.\n[2] Niu Xuemei, Gao Guoqin, Liu Xinjun,et al. Dynamics modeling and experiments of 3-DOF parallel mechanism with actuation redundancy[J]. Transactions of the Chinese Society of Agricultural Engineering, 2013,29(16):31-41.\n[3] A.M. El-Refaie. Fault-tolerant permanent magnet machines: a review[J]. IET Electronics Power Applications, 2011,5(1):59-74.\n[4] Ji Jinghua, Sun Yukun, Zhu Jihong, et al. Design, analysis and experimental validation of a modular permanent-magnet machine[J]. Transaction of China Electrotechnical Society, 2010,25(2): 22-29.\n[5] B. C. Mecrow, A. G. Jack. Design and testing of a four-phase fault-tolerant permanent-magnet machine for an engine fuel pump[J]. IEEE Transactions on Energy Conversion, 2004, 19(2): 132 - 137.\n[6] Hao Z Y, Hu Y W. Design and experimental analysis on the control system of high reliability fault tolerant permanent magnet motor", + "used in electric actuator [J]. Acta Aeronautica Et Astronautica Sinica, 2013, 34(1): 141-152.\n[7] M. T. Abolhassani, H. A. Toliyat. Fault tolerant permanent magnet motor drives for electric vehicles[C]. IEEE International Electric Machines and Drives Conference, 2009:1146-1152.\n[8] Hao Zhenyang, Hu Yuwen, Huang Wenxin, et al. Optimal current direct control strategy for fault tolerant permanent magnet motor[J]. Proceedings of the CSEE, 2011, 31(6): 46-51.\n[9] Si Binqiang, Ji Jinghua, Zhu Jihong, et al. Two fault tolerant strategies for four-phase permanent-magnet fault tolerant machine [J]. Control and Decision, 2013,28(7):1007-1012.\n[10] Tang Renyuan. Modern Permanent Magnet Machines-Theory and Design[M]. Beijing: Machinery Industry Press, 1997: 176.\n[11] Zhu Deming, Yan Yangguang. Features of Air-Gap Flux Density in Segmented Halbach Permanent Magnet Synchronous Motor and Its No-Load EMF Waveform Optimization[J]. Transactions of China Electrotechnical Society, 2008, 23(11):22-26." + ] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.18-1.png", + "caption": "Figure 1.18. Mercedes C111, circa 1969, using a five link IRS and a double wishbone IFS [62].", + "texts": [ + " One way to provide some measure of independent rear wheel motion economically is to allow the axle itself to deform, thus requiring the further classification of an axle as rigid or semi-rigid. The primary realization of the semi-rigid axle is the twist beam, introduced in 1974 by Volkswagen. An example of the type is shown in Figure 1.17. This design allows the axle to swing relative to the vehicle body, while independent wheel motion is a result of torsional deformation of the axle itself. On the other hand, more expensive cars did begin to use independent rear suspensions (IRS) shortly after the mid-century mark. Multilink designs, such as Mercedes-Benz\u2019s five link IRS, seen in Figure 1.18, provide the designer with considerable choice over how to guide the wheel\u2019s vertical motion. Recently, even cheaper, compact cars have adopted the IRS. This transition was initiated by the original Ford Focus, introduced to European 13 14 markets in 1999 with its multi-link control blade suspension [18, p. 391]. Later versions of the car continued with this successful design, Figure 1.19. The improved ride and handling due to the independent rear suspension led other automakers to redesign their compact cars \u2014 Volkswagen went as far as hiring ex-Ford engineers to replace the twist beam axle of the Golf with a Focus-style multi-link IRS [48]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004878_1_1_article-p394.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004878_1_1_article-p394.pdf-Figure3-1.png", + "caption": "Fig. 3. Velocity distribution (left side, in m/s) and pathlines (right side) for the part with spool controlled by solenoid", + "texts": [ + " CFD simulation was performed in ANSYS CFX code for fixed component position for steady state conditions and for the following assumptions: (a) fluid (hydraulic oil) is homogeneous and has a constant properties: density 880 [kg/m3], viscosity \u03c5 =40 [mm2/s]; (b) flow is turbulent: k-\u03d6 turbulence model was used; (c) model is in thermodynamics equilibrium, heat transfer is not included; (d) half of the geometrical model was used in simulations. An exemplary results of fluid flow inside flow control valve are shown in Fig.3 and Fig.4. Numerical simulations of flow inside the valve allowed also to obtain pressure drop at the first spool (controlled by solenoid) which is presented in Fig.5. Spool position is normalized value, where 0 is initial position (valve is closed) while 1 is fully open valve. Numerical simulations of flow inside valves bring new quality in modelling such components. Information which are obtained during CFD simulation allows to investigate phenomena which appears during fluid flow which might be used during design process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002037_s-4400047_latest.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002037_s-4400047_latest.pdf-Figure11-1.png", + "caption": "Figure 11. The absorption spectra for high-frequency wideband under TE and TM mode. (a,b) different polarization angles; (c,d) different incident angles.", + "texts": [ + " These results suggest that such high-frequency wideband absorbers hold promising potential for applications in optical switches. Notably, as the Fermi level of graphene shifts from 0.01 eV to 1 eV, the operational state of the absorber can transition from reflective (\"OFF\" state, with reflection above 52%) to absorptive (\"ON\" state, with absorption exceeding 90%) within a frequency range of 9.2 THz to 9.8 THz. To investigate the absorber's absorption properties under oblique incidence, we sim- ulated wideband absorption spectra for different polarizations and incidence angles in the 8.4~9.8 THz frequency range. Fig. 11(a)-(b) and 12(a)-(b) display the absorption spectra for high-frequency and full-band wideband absorbers under TE and TM polarized waves, respectively. The absorber\u2019s symmetrical structure results in negligible changes in absorption rates between the two polarizations, indicating its insensitivity to polarization angle. Additionally, the impact of varying oblique incidence angles on the absorption spectra of TE and TM waves was analyzed. For the high-frequency wideband absorber under TE polarization, an incidence angle below 30\u00b0 maintains absorption intensity above 80%, with a slight bandwidth broadening as the incidence angle increases. Conversely, for angles greater than 30\u00b0, the stable absorption characteristic of TM polarization is disrupted(Fig. 11(c)-(d)). This variation occurs because, in TE polarization, the electric field remains parallel to the x-axis, while in TM polarization, the tangential component of the electric field diminishes with increasing incidence angle. Consequently, the graphene's magnetic resonance and electric dipole resonances more efficiently excite TE polarization, resulting in a more stable wideband TE polarization absorber compared to TM polarization. Fig. 12(c) and 12(d) reveal that the full-band wideband absorber demonstrates superior absorption performance" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001339_ad.aspx_paperID_1114-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001339_ad.aspx_paperID_1114-Figure6-1.png", + "caption": "Figure 6. (a) Stator, rotor, and (b) their assembly of motor prototype", + "texts": [ + " Figure 5(b) lays out the EMF vectors of windings, where the slots of coils A1, -B1, and C1 are distributed in 120\u00b0E (electric degrees) of phase offset and the best shift \u03b3 of each phase current must lead them in 22.5\u00b0E, thereby remaining a balanced configuration. It was found that not only the torque increased 8.4%, but the ripple also decreased by changing the current shift from 0 to 22.5\u00b0E. The axial length of the motor was previously specified at 155 mm. To make the prototyping easier, it was downsized to 55 mm in view of precise machining and accurate assembling. Inevitably, such reduction of axial length must cause the rated torque to decrease by about 1/3 of the optimally designed motor. Figure 6(a) shows the stator core and concentrated windings, and the rotor assembly, glued on the outer surface of which are NeFeB 40SH magnets. A complete assembly of the torque motor is shown in Figure 6(b). The performance of the prototype motor was tested with the voltage supply of 220V. Figure 7 compares the back EMF waveforms from the FE analysis and experiment, where both curves are close to the pure sine function, but the error between the experimental back EMF and pure sine function is even less than 5%. It is also interesting to point out that the back EMF constant from the experiment is 4.48 V/rad/s, which is very close to 4.57 V/rad/s from the FE analysis. Figure 8 shows the relationship between the torque and current, where Tmag=31" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002607_wnload_140647_130388-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002607_wnload_140647_130388-Figure1-1.png", + "caption": "Figure 1: Conceptual Diagram of Grass Briquette Plant", + "texts": [ + " \u2044 Essentially, the screw power shaft operates both as conveyor and a power element. The screw is welded to the shaft with incremental screw height which provides the compressive force required for briquetting. Design considerations for screw press entails the power to overcome the inertia of the shaft and the screw, the power to convey the pulverized dried grass stock along the entire length of the press and the power to effectively compact the feedstock with little or no binder added. Biomass briquetting machine as shown in Figure 1 was designed for material size reduction (crushing), compaction and extrusion of produced briquette. From the theoretical formulations drawn from the design consideration, the machine parameters and specifications are given in Table 1. Table 1: Machine Parameters and Specifications S/No. Design Parameter Specification 1. Diameter of shaft at disc plate 20mm 2. Dynamic load on bearing 8.9kN 3. Power of the electric motor 1hp 4. Diameter of screw shaft 40.8mm 5. Dynamic load on bearing 11.42kN 6. Power of electric motor (Screw) 7hp Nigerian Journal of Technology Vol" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001073_.srce.hr_file_280260-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001073_.srce.hr_file_280260-Figure1-1.png", + "caption": "Figure 1 Robot cooperation at same target point with corrected roll angles", + "texts": [ + " Considering the use in static unchanging environments during the robots motion, a simpler approach for collision avoidance of cooperating robots intended to work in same spatial positions is presented in Tehni\u010dki vjesnik 24, 6(2017), 1705-1711 1707 this section and defined as a function. This approach takes the positions of the (n\u22121)th joints of cooperating manipulators and maximizes their spatial distance: ( ) .)( 1 2515 \u2212= r,r, J,Jde (5) This can be achieved in a controllable way by altering one of the unconstrained orientation parameters of the robot operation point \u2013 roll, pitch or yaw, depending on the robot tool configuration. For cooperative robots this means aligning both robot tools in the way they do not interfere with each other. In Fig. 1 an example situation is shown where both roll angles of the robots tools were corrected by the combined value of \u03b1 in order to avoid collision. For a practical application this can be implemented as the Euclidian distance calculated for each configuration of the robots. This function can be treated as a criterion which is suitable for the implementation into the final objective function. The goal of the function is to yield roll angles for both robots that maximize the distance between two joints and therefore minimize the parameter e" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001726_el-01651589_document-Figure1.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001726_el-01651589_document-Figure1.12-1.png", + "caption": "Figure 1.12: Reference vectors when the smartphone is static and in the absence of magnetic deviations.", + "texts": [ + " \u2022 magnetic field in SF provided by a magnetometer noted Smag and its projection in EF noted Emag. These 2 observation vectors can be modeled as following: Saccq = q\u22121 \u2297 Eaccq \u2297 q, (1.11) Smagq = q\u22121 \u2297 Emagq \u2297 q. (1.12) If the smartphone is in static phase (not translating), accext = [ 0 0 0 ]T and Eacc = [ 0 0 g ]T . (1.13) In absence of magnetic deviations, magext = [ 0 0 0 ]T and Emag = [ mx my mz ]T , (1.14) where mx, my and mz can be obtained using the WMM [(NGA) and the U.K.\u2019s Defence Geographic Centre (DGC), 2015]. Figure 1.12 shows these two vectors: Eacc in blue and Emag in green. In addition to accelerometer and magnetometer, the gyroscope is used to estimate variation of attitude. Unfortunately, the gyroscope bias leads after integration (Equation (1.7)) to an angular drift, increasing linearly over time. Since the use of only gyroscope is not enough for attitude estimation, accelerometer and magnetometer are used to get an absolute quaternion and compensate the drift. The crux in solving an attitude estimation problem then consists in combining inertial and magnetic sensor measurements in a relevant manner" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003898__Issue1-18_paper.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003898__Issue1-18_paper.pdf-Figure14-1.png", + "caption": "Fig. 14. Example of the pick system with numbered picks", + "texts": [ + " Each of the presented characteristics can be modified In such manner that the worst pick was or wasn\u2019t be eliminated. The presented definition of the parameter determining durability of picks, as well as requirements related to examinations of the wear rate result in necessity of assuming the following testing procedure (Krauze, 2012a): \u2022 preparation of cement-sand sample having assumed composition (cement, sand, aggregate, water) and uniaxial compression resistance, \u2022 measurement of the pick mass, \u2022 fixing of four tangential-rotary picks in special holders (Fig. 14), \u2022 cutting in laboratory conditions, \u2022 measurement of the pick mass after cutting process, \u2022 calculation of the volume of the winning obtained during tested picks operation, \u2022 determination of real properties of cut sample, \u2022 calculation of the parameter reflecting wear rate. It should be noted that the assessment on the basis of mass loss concerns quality assessment of whole pick. i.e. its cutting edge and pick body. However, indicators based on pick length loss can also be used for determining the cutting edge life-time", + " In case of testing the wear rate of tangential-rotary picks, mining artificial rock having high resistance to abrasion (cementsand sample), as well as uniform and isotropic properties, is recommended. The testing stand is equipped with measurement system being its integral part (torque meter, pressure transducers, distance transducers and measuring computer). It allows measurement of the cutting element load, including velocity and pressure in the advance system, thus resistances and power-consumption of the cutting process can be easily determined. Picks on the testing disc are located along the disc circumference every 90\u00b0 forming a system shown in Fig. 14. Each set of picks is mounted in numbered (from 1 to 4) holders on the disc. The holders allow fixing the picks independently on the manufacturer\u2019s fixing recommendations. The pick were weighted before and after testing with use of the weight AXIS (legalization scale 1g). Obtained mass loss and volume of cut sample are a basis of calculation of parameter determining pick wear rate. Finally, each pick is photographed in the planes located every 120\u00b0. Example photographs of a single series of tested picks is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure6.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure6.4-1.png", + "caption": "Fig. 6.4. Diagram of the front suspension system with marked objects of investigation", + "texts": [ + " Some of the results of damping characteristics of shock absorbers with different volume of fluid are shown in Fig. 6.2. The scheme of the research and process of shock absorber filling with working medium is presented in Fig. 6.3. The scope of the research contained the tests of the impact exerted by changes in the technical condition of a front suspension coil spring. A schematic representation of the suspension system of the vehicle tested with the subject of the research and the vibration recording points marked are presented in the Fig. 6.4. The identification of technical condition of suspension spring caused by defects (break) can be evaluated by the observation. The properties of coil springs are changing due to the operation period. It was assumed that the main factor of the vibration transfer related into spring is time and condition of operating in vehicle suspension. The experiments were conducted on passenger car with build in new and used (worn-out) suspension spring. The force vs. deflection characteristics of researching coil springs are presented in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000752_el-04725201_document-Figure3.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000752_el-04725201_document-Figure3.1-1.png", + "caption": "FIGURE 3.1 : Sch\u00e9ma de la ligne de transmission avec cavit\u00e9 d\u2019air (a) Vue isom\u00e9trique (b) Plan XY (c) Plan ZY.", + "texts": [ + " Dans notre cas, l\u2019imprimante 3D est capable d\u2019imprimer jusqu\u2019\u00e0 10 mm dans le vide. Au-del\u00e0 de cette valeur, un affaissement se produit, fragilisant la structure. Par cons\u00e9quent, toutes les \u00e9tudes sont men\u00e9es en tenant compte de la pr\u00e9cision de l\u2019imprimante 3D sur les axes X, Y et Z lors de la r\u00e9alisation des diff\u00e9rents \u00e9l\u00e9ments de l\u2019antenne. Cette \u00e9tude est r\u00e9alis\u00e9e par simulation et se concentre sur l\u2019optimisation de la transmission de puissance (param\u00e8tre |S21|dB) entre deux ports de 50 \u2126 \u00e0 la fr\u00e9quence de 2,45 GHz. La figure 3.1 illustre la ligne microruban de transmission avec la cavit\u00e9 d\u2019air dans le substrat, sous diff\u00e9rents angles de vue. Dans un premier temps, la largeur lcav est fix\u00e9e \u00e0 5 mm, l\u2019\u00e9paisseur de la cavit\u00e9 hcav est fix\u00e9e \u00e0 1 mm, et la longueur Lcav varie de 5 mm \u00e0 20 mm par pas de 1 mm. Les r\u00e9sultats sont pr\u00e9sent\u00e9s sur la figure 3.2 (a). Ensuite, la longueur de la cavit\u00e9 (Lcav) est fix\u00e9e \u00e0 20 mm, l\u2019\u00e9paisseur de la cavit\u00e9 (hcav) est fix\u00e9e \u00e0 1 mm, et la largeur (lcav) varie de 1 mm \u00e0 10 mm par pas de 1 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure4.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure4.3-1.png", + "caption": "Figure 4.3: Vane Volume Calculation", + "texts": [ + " \ud835\udc51\ud835\udc49\ud835\udc51\ud835\udc52\ud835\udc4e\ud835\udc51,\ud835\udc60\ud835\udc62\ud835\udc50 \ud835\udc51\ud703\ud835\udc50 = \u2212\ud835\udc59\ud835\udc50\ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 \ud835\udc51\ud835\udc5f\ud835\udc63\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 \u2212 \ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f 2 (\ud835\udc5f\ud835\udc5f \ud835\udc51\ud835\udf11\ud835\udc63 \ud835\udc51\ud703\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc63\ud835\udc5f cos\ud835\udf11\ud835\udc63 \ud835\udc51\ud835\udf11\ud835\udc63 \ud835\udc51\ud703\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc5f sin\ud835\udf11\ud835\udc63 \ud835\udc51\ud835\udc5f\ud835\udc63\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 ) (4.23) \ud835\udc51\ud835\udc49\ud835\udc51\ud835\udc52\ud835\udc4e\ud835\udc51,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc51\ud703\ud835\udc50 = \u2212\ud835\udc59\ud835\udc50\ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 \ud835\udc51\ud835\udc5f\ud835\udc63\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 + \ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f 2 (\ud835\udc5f\ud835\udc5f \ud835\udc51\ud835\udf11\ud835\udc63 \ud835\udc51\ud703\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc63\ud835\udc5f cos\ud835\udf11\ud835\udc63 \ud835\udc51\ud835\udf11\ud835\udc63 \ud835\udc51\ud703\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc5f sin\ud835\udf11\ud835\udc63 \ud835\udc51\ud835\udc5f\ud835\udc63\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 ) (4.24) \ud835\udc51\ud835\udc49\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 \ud835\udc51\ud703\ud835\udc50 = \ud835\udc59\ud835\udc50\ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 \ud835\udc51\ud835\udc5f\ud835\udc63\ud835\udc5f \ud835\udc51\ud703\ud835\udc50 (4.25) where 51 \ud835\udc51\ud835\udf11\ud835\udc63 \ud835\udc51\ud703\ud835\udc50 = \ud835\udc51\ud703\ud835\udc63 \ud835\udc51\ud703\ud835\udc50 \u2212 \ud835\udc51\ud835\udefe \ud835\udc51\ud703\ud835\udc50 (4.26) The volume of the vane can be computed by breaking down the vane into simpler geometric shapes and then adding up each of the components Av1, Av2, Av3 and Av4 which would give the volume for half of the vane by symmetry as shown in Figure 4.3. Equations (4.27)\u2013(4.30) show the area breakdown for each of the shape shown in Figure 4.3 and the volume of the vane can be calculated using Equation (4.31). \ud835\udc34\ud835\udc63,1 = 1 2 (\ud835\udc5f\ud835\udc50 2\ud835\udf11\ud835\udc63 \u2212 1 2 \ud835\udc5f\ud835\udc50\ud835\udc64\ud835\udc63 cos\ud835\udf11\ud835\udc63) + \ud835\udc64\ud835\udc63 2 (\ud835\udc59\ud835\udc63 \u2212 \ud835\udc5f\ud835\udc50 + \ud835\udc5f\ud835\udc50 cos\ud835\udf11\ud835\udc63 \u2212 \ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 2 sin\ud835\udf11\ud835\udc60\ud835\udc64\ud835\udc59) (4.27) \ud835\udc34\ud835\udc63,2 = 1 8 \ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 2 \ud835\udf11\ud835\udc60\ud835\udc64\ud835\udc59 (4.28) \ud835\udc34\ud835\udc63,3 = 1 8 \ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 2 sin\ud835\udf11\ud835\udc60\ud835\udc64\ud835\udc59 cos\ud835\udf11\ud835\udc60\ud835\udc64\ud835\udc59 (4.29) \ud835\udc34\ud835\udc63,4 = 1 2 ( \ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 2 cos\ud835\udf11\ud835\udc60\ud835\udc64\ud835\udc59 \u2212 \ud835\udc64\ud835\udc63 2 ) (\ud835\udc59\ud835\udc53\ud835\udc61 \u2212 \ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 2 sin\ud835\udf11\ud835\udc60\ud835\udc64\ud835\udc59) (4.30) \ud835\udc49\ud835\udc63,\ud835\udc61\ud835\udc5c\ud835\udc61\ud835\udc4e\ud835\udc59 = 2\ud835\udc59\ud835\udc50(\ud835\udc34\ud835\udc63,1 + 2\ud835\udc34\ud835\udc63,2 + 2\ud835\udc34\ud835\udc63,3 + \ud835\udc34\ud835\udc63,4) (4.31) where 52 \ud835\udf11\ud835\udc63 = sin\u22121 \ud835\udc64\ud835\udc63 2\ud835\udc5f\ud835\udc50 (4.32) Similar to the calculation of dead volume in the vane slot, the exact vane volume in each chamber is calculated by taking into account the angle of swivel for the vane" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004597_s-4255722_latest.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004597_s-4255722_latest.pdf-Figure2-1.png", + "caption": "Fig. 2: Geometry of the bellow-type linear bending actuator used in the study.", + "texts": [ + " [39] was used for the manufacturing of traditional actuators. The same geometry, which was devised considering a maximum actuation force of 4 bar for the 3D printed one, was devised in a series of preliminary tests which allowed the achievement of a design that did not leak under pressure, allowing proper connection with standard pneumatic connection hardware, keeping a costant pressure for the entire test duration. Specifically, the design focused on the identification of a valid value for the wall thickness parameter, identified by the letter S in Fig. 2b, which was finally set to 1.6 mm. Moreover, actuators were equipped with a resistive bending sensor - i.e. Flex Sensor by Spectra Symbol [40], as proposed in [41], hosted in the lower part of the device. This has introduced additional difficulties to the manufacturing process, as described in the following sections. The actuator was modeled using Dassault Syste\u0300mes Solidworks 2023 and exported in a STL format for further phases of the study. 3D printed actuators were fabricated using an FFF technique which, as previously discussed, completely removes the need of inner cor to model and generate the internal geometry of the device" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001734_e_download_2825_3901-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001734_e_download_2825_3901-Figure9-1.png", + "caption": "Figure 9. Critical strain areas", + "texts": [ + " Moreover, at the critical stress areas (Figure 7), it shows the twist moment load of the most dominant stress on the shaft between the turbine and compressor seat also some areas of the compressor seat. The most critical area shown by the red color that lies at the end of the compressor seat. Nevertheless, the displacement critical areas (Figure 8) that occur on the turbocharger shaft with the same load more indicates close to another one end of the compressor seat. It is due to the throwing force as the function of the length of the shaft. Same as the critical areas of stress, the strain (Figure 9) results also indicate the most potentially highest strain is located on the shaft between the turbine and compressor seat. Also, the areas could be potentially located on the right end of the compressor seat. While for the safety of factor (Figure 10), indicates that the entire area of the turbocharger shaft is a critical area. It can be said that this shaft has a good design for loads beyond its normal operations. If there is an excessive force this shaft can distribute the force to other parts of the shaft thus it becomes equal" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002346_5_40_8_40_8_859__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002346_5_40_8_40_8_859__pdf-Figure2-1.png", + "caption": "Fig. 2 Image of the jumping & rolling inspector to search the", + "texts": [ + "] q:\u30b7 \u30ea\u30f3\u30c0 \u306b\u6d41\u5165 \u3057\u305f \u30a8\u30cd\u30eb \u30ae\u30fc \u306e\u7dcf\u548c [J] R:\u7a7a \u6c17 \u306e \u6c17\u4f53\u5b9a \u6570 [J/(kgK)] r:\u30b7 \u30ea\u30f3\u30c0\u306e \u53d7\u5727 \u90e8\u5206 \u306e\u534a\u5f84 [m] S:\u5f01 \u304a \u3088\u3073\u7ba1\u8def \u306e\u6709\u52b9 \u65ad \u9762\u7a4d [m2] T:\u30b7 \u30ea\u30f3\u30c0 \u5185\u90e8 \u306e\u7a7a\u6c17 \u306e\u7d76\u5bfe \u6e29\u5ea6 [K] T0:\u30b7 \u30ea\u30f3\u30c0 \u304a \u3088\u3073 \u30b7 \u30ea\u30f3\u30c0\u5916\u90e8 \u306e\u7d76 \u5bfe\u6e29 \u5ea6 [K] T1:\u30b7 \u30ea\u30f3\u30c0 \u306b\u6d41\u5165 \u3057\u305f\u7a7a \u6c17\u306e\u7d76\u5bfe \u6e29 \u5ea6 [K] tmax:\u30ed \u30c3 \u30c9\u304c\u4f38 \u3073\u5207 \u308b\u6642 \u9593 [s] tv:\u5f01 \u306e\u4f5c \u52d5\u9045 \u308c\u6642 \u9593 [s] u:\u30b7 \u30ea\u30f3\u30c0\u5185 \u7a7a\u6c17 \u306e \u5185\u90e8 \u30a8 \u30cd\u30eb\u30ae \u30fc [J] V:\u30b7 \u30ea\u30f3\u30c0\u5185\u90e8 \u306e\u4f53\u7a4d(=Ax) [m3] Vmax: x\u304cL\u306b \u9054 \u3057\u305f \u3068 \u304d\u306e\u30b7 \u30ea\u30f3\u30c0 \u5185\u90e8 \u306e\u6700 \u5927\u4f53 \u7a4d(= AL) [m3] v:\u30ed \u30c3 \u30c9\u306b\u5bfe \u3059 \u308b \u30b7 \u30ea\u30f3\u30c0\u30c1 \u30e5\u30fc \u30d6\u306e\u901f\u5ea6 [m/s] vmax:\u30d4 \u30b9 \u30c8\u30f3\u306b\u885d \u7a81 \u3059 \u308b\u76f4 \u524d\u306e \u30b7 \u30ea\u30f3\u30c0 \u30c1 \u30e5\u30fc \u30d6\u306e\u901f \u5ea6 [m/s] v'max:\u30d4 \u30b9 \u30c8\u30f3 \u3068\u885d \u7a81 \u3057\u3066\u4e00\u4f53 \u5316 \u3057\u305f\u5f8c \u306e \u30b7 \u30ea\u30f3\u30c0\u30c1 \u30e5 \u30fc \u30d6\u306e\u901f \u5ea6 [m/s] W:\u8df3 \u8e8d \u6642 \u306e\u4ed5\u4e8b [J] x:\u30ed \u30c3 \u30c9\u306b\u5bfe \u3059 \u308b \u30b7 \u30ea\u30f3\u30c0 \u30c1 \u30e5\u30fc \u30d6\u306e\u5909\u4f4d \u91cf,\u6700 \u5927\u5024 \u306fL [m] \u03b1s:\u30b7 \u30ea\u30f3\u30c0\u58c1 \u9762 \u304b \u3089\u7a7a \u6c17 \u3078\u306e\u71b1\u4f1d \u9054\u7387 \u3068\u9762\u7a4d \u3068\u306e\u7a4d [W/K] \u03c1:\u6a19 \u6e96\u72b6 \u614b \u306b \u304a \u3051 \u308b\u7a7a \u6c17 \u306e\u5bc6\u5ea6 [kg/m3] \u03ba:\u6bd4 \u71b1\u6bd4(\u5b9a \u5727\u6bd4 \u71b1/\u5b9a \u7a4d\u6bd4 \u71b1) \u03b7:\u8df3 \u8e8d \u306e \u30a8\u30cd \u30eb\u30ae \u30fc\u52b9 \u7387 2. \u30ed\u30dc \u30c3 \u30c8\u306e \u5168 \u4f53 \u69cb \u9020 \u3068\u52d5 \u4f5c \u539f \u7406 \u672c\u7814 \u7a76 \u3067\u958b\u767a \u3057\u305f \u300c\u8df3\u8e8d \u30fb\u56de\u8ee2 \u79fb \u52d5 \u4f53\u300d \u306f,2\u3064 \u306e\u8eca\u8f2a \u3067 \u631f \u307e\u308c\u305f \u5186\u7b52\u7a7a \u9593 \u5185 \u306b1\u672c \u306e\u8e74 \u308a\u51fa \u3057\u811a \u3092\u6709 \u3059 \u308b\u69cb \u9020 \u3092\u57fa\u672c \u3068\u3057,\u5e73 \u5766 \u5730 \u306f\u52b9 \u7387 \u7684 \u306a\u56de\u8ee2 \u904b\u52d5 \u3067\u79fb\u52d5 \u3057,\u5927 \u304d\u306a\u969c\u5bb3 \u7269 \u306f \u8e74 \u308a\u51fa \u3057\u811a \u3067\u98db \u3073\u8d8a \u3048\u308b\u79fb \u52d5\u5f62 \u4f53 \u3067 \u3042 \u308b(Fig. 2).\u307e \u305f,\u7740 \u5730\u6642 \u306f\u8907\u96d1 \u306a\u59ff \u52e2\u5b89 \u5b9a\u5316 \u5236\u5fa1 \u3092\u884c \u306a \u3046\u5fc5 \u8981 \u306f\u306a \u304f,\u3069 \u306e \u3088\u3046 \u306a\u59ff \u52e2\u304b \u3089\u7740\u5730 \u3057\u3066 \u3082\u4fca\u654f \u306b\u59ff\u52e2 \u5fa9 \u5e30 \u3092\u5b9f\u73fe \u3055\u305b \u308b\u53d7\u52d5\u53ce \u7d0d \u811a\u304c \u88c5\u5099 \u3055\u308c \u3066\u3044 \u308b.\u305d \u3057\u3066\u6700\u7d42 \u7684 \u306b\u306f,\u5c0f \u578b \u30ab\u30e1 \u30e9\u3084 \u30de \u30a4 \u30af\u306b \u3088\u308b\u88ab \u707d\u8005\u63a2 \u7d22\u4f5c \u696d \u3092\u884c \u306a \u3046 \u3053\u3068\u3092 \u76ee\u7684 \u3068 \u3057\u3066\u3044 \u308b. \u3053\u308c \u307e\u3067 \u306e\u7814 \u7a76 \u3067 \u306f,2\u3064 \u306e\u7570 \u306a \u308b\u99c6 \u52d5\u65b9 \u5f0f \u3092\u7528 \u3044\u305f\u79fb \u52d5 \u4f53 \u3092\u958b\u767a \u3057,\u305d \u306e\u6709 \u52b9 \u6027 \u3092\u6bd4 \u8f03 \u691c \u8a0e \u3057 \u3066 \u304d\u305f2).\u305d \u306e \u3046 \u3061 Fig. 3\u306b \u793a \u3059 \u30ed \u30dc \u30c3 \u30c8:Leg-in-Rotor-II\u306f,\u8cea \u91cf2[kg] \u4ee5\u4e0b \u306730[cm]\u7acb \u65b9 \u306b\u53ce \u307e \u308b\u30b5 \u30a4 \u30ba \u3067\u69cb \u6210 \u3055\u308c \u3066 \u304a \u308a,\u8eca \u8f2a \u306fDC\u30e2 \u30fc\u30bf\u3067,\u307e \u305f\u8e74 \u308a\u51fa \u3057\u811a \u306f1\u672c \u306e\u7a7a \u5727 \u30b7 \u30ea\u30f3\u30c0\u3067 \u99c6\u52d5 \u3055\u308c,\u56de \u8ee2 \u3057\u306a\u304c \u3089\u8df3\u8e8d \u3059 \u308b \u3053\u3068\u304c\u3067 \u304d\u308b.\u305d \u306e \u3046\u3048, 2\u3064 \u306e\u53d7\u52d5 \u53ce\u7d0d\u811a \u306b \u3088 \u308a,\u30b7 \u30ea\u30f3\u30c0 \u306f\u79fb \u52d5\u9762 \u306b\u5bfe \u3057\u3066\u5e38 \u306b\u5782 \u76f4 \u65b9 \u5411 \u306b\u7dad\u6301 \u3055\u308c \u308b\u305f \u3081,\u9ad8 \u3044 \u8df3\u8e8d \u3092\u5b9f\u73fe \u3057\u3084 \u3059 \u3044\u69cb \u9020 \u3068 victims under debris Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001484__EEE-THESES_1563.pdf-Figure3.22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001484__EEE-THESES_1563.pdf-Figure3.22-1.png", + "caption": "Fig. 3.22 Acoustical-hotspot generation system configuration.", + "texts": [ + " In a real application, the calibration of the sources and varying radiation patterns of individual sources have to be considered. For an array of paper-cone loudspeakers widely used today, the radiation patterns of each speaker may be very different, and thus it is not easy to calibrate the array for wideband signals. This difficulty makes the MCG method too expensive to apply. However, the method will be useful in the future when very uniform and small-sized sources are available. 3.2.7.4 Far-field wideband simulation Consider a far-field hotspot generation scenario, as illustrated in Fig. 3.22. A 20- element linear array with element-spacing of 0.172 m is arranged along the x-axis and symmetry with respect to the origin of the coordinate. The target region is a line segment with x = [\u20130.1 m, 0.1 m] at y = 5 m. Consider the frequency band of [250, 2500] Hz. Since the distance from the target region to the array is 5 m, it can be regarded as a far-field case according to the criterion in Eq. (3.15). By using Eq. (3.7), a virtual target point is determined at (0, 5.70 m)O . Based on above settings, the time delays can be calculated using Eq", + "6507, \u20130.6658, \u20130.6658, \u20130.6507, \u20130.6206, \u20130.5755, \u20130.5156, \u20130.4409, \u2013 0.3518, \u20130.2485, \u20130.1311, 0] msec. Thus, the TD is obtained. The amplitude weights 112 for the MCG solution are calculated using Eq. (3.23), and obtained as [ ]11 22, ,..., NNA A A = [0.9754, 0.9829, 0.9896, 0.9957, 1.0010, 1.0055, 1.0091, 1.0118, 1.0137, 1.0146, 1.0146, 1.0137, 1.0118, 1.0091, 1.0055, 1.0010, 0.9957, 0.9896, 0.9829, 0.9754]. By using the TD and MCG solutions, the wideband array pattern on the measuring line (Fig. 3.22) can be simulated, as shown in Fig. 3.23 and Fig. 3.24 for 3D and 2D patterns, respectively. The difference of the average SPL in the target region by the two solutions with respect to the frequency is illustrated in Fig. 3.25. The following observations can be drawn from the simulated array patterns: (I) Both the TD and MCG solutions successfully generate acoustical hotspot at the target region. As shown by the 3D patterns in Fig. 3.23 and 2D patterns in Fig. 3.24, both solutions produce higher SPL around the target region of x = [\u20130" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure9-1.png", + "caption": "Fig. 9. The characteristic solution of foot-mounted single-stage gear reducer with the horizontal arrangement of the shafts (Hansen solution) [16].", + "texts": [ + " 6, 7, 8, 9, 10), with vertical (Fig. 11, 12) and with free shaft positions (Fig. 14, 15). Gear reducers with horizontal shaft position are usually manufactured with radial mounting and they present the old type of single-stage units. They passed through extremely intense shape development, from the usual and simple shapes, which insisted only on functionality and reduced material consumption (Fig. 6 and 7) to the very interesting contemporary forms, where great attention has been paid to the appearance of the gearbox (Fig. 9 and 10). If the gear reducer is intended for operation in an environment with high ambient temperature, as well as the higher engine power is used and higher losses can be expected, the housing should be manufactured with ribs (Fig. 7) to increase the outer surface of the housing and improve heat dissipation. Also, housing with ribs is used for large gear unit to increase their rigidity. To simplify the gearbox production as much as possible, many manufacturers produce one-piece housings to avoid machining of large contact areas between two parts of the housing. They have to provide an opening for large gears, usually at the top of housing (Fig. 8) or on one of the front side (Fig. 9 and 10) which afterwards should be closed with a cover. With this approach, they significantly simplify the machining of the housings, although the assembling of such gear units is somewhat more complex. Today, as stated above, basic attention is paid to aesthetic, i.e. product design. Modern solutions of single-stage universal gear reducer are recognized by simple and attractive form, slight shape transitions and somewhat higher material consumption. It is interesting to note that some manufacturers assemble single-stage gear reducers in the housings for two-stage gear units (cylindrical-bevel gear reducers) to increase the series of housing and thereby reduce production costs (Fig. 9 and 10). In order to increase the versatility of their gear reducers, some manufacturers produce the housings with feet on all four sidewise surfaces. In this way, the gearbox can be mounted with horizontal shaft arrangement, but also in vertical shaft arrangement. The additional opening is added through which the gears are mounted and it is closed by a cover. In order to increase the versatility of this gearbox, an additional flange is created on the front surfaces of the housing (Fig. 10). Single-stage universal gear reducers with vertical shaft arrangement are today more common in practice" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002838_f_version_1679473059-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002838_f_version_1679473059-Figure7-1.png", + "caption": "Figure 7. Meshing relationship of the conjugated straight-line internal gear pair.", + "texts": [ + " The coordinates of the meshing points in the movable coordinate S1 are converted to the fixed coordinate Sg, then the meshing line equation of the gear pair can be obtained, and the change relation is as follows: Rl g(\u03d51, x1) = Mg1(\u03d51)Re 1(x1) (45) where Rl g(\u03d51, x1) is the position vector of the meshing line in the coordinate Sg. Similar to the solution method of conjugate tooth profiles, the solution of Rl g(\u03d51, x1) must also satisfy the meshing Equation (17) of the gear pair. Taking the design parameters of the gear pair in Table 3 as an example, the meshing line solved by combining Equations (17) and (45) is shown in Figure 7. Its shape is similar to a parabolic curve, different from the linear meshing line of the involute gear pair, so their meshing characteristics are quite different. In order to ensure the continuity and smoothness of gear transmission, gear pairs must meet the restrictive conditions \u03b5 > 1 of the contact ratio \u03b5. In Figure 7, assuming that the gear pair rotates clockwise and the direction is positive, the curve I J is the actual meshing line of a pair of gear teeth during the meshing. The point I is the intersection between the meshing line and the addendum circle of the internal gear ring, and is the initial meshing point. The point J is the intersection between the meshing line and the addendum circle of the external gear, and is the final meshing point. When a pair of gear teeth enter and exit meshing, the corresponding angles of the external gear are \u03d501 and \u03d502, respectively, so the angle at which the external gear rotates is \u2206\u03d5 = \u03d502 \u2212 \u03d501 as the meshing point moves from the point I to point J, and then the contact ratio of the conjugated straight-line internal gear pair and the constraints it meets are as follows: \u03b5 = \u2206\u03d5 2\u03c0/z1 = \u03d502 \u2212 \u03d501 2\u03c0/z1 > 1 (46) In coordinate Sg, the following can be obtained from the geometric relationship in Figure 7: \u03c12 1 = h2 + r2 1 cos2(\u03b2\u2212 \u03d51) (47) \u03c12 2 = [h + e sin(\u03b2\u2212 \u03d51)] 2 + r2 2 cos2(\u03b2\u2212 \u03d51) (48) where \u03c11 and \u03c12 are the distances from the meshing point G to the center O1 and O2 of the external gear and internal gear ring, respectively. When the gear teeth enter meshing, there is a relation: \u03c12 = ra2; when the gear teeth exit meshing, there is a relation: \u03c11 = ra1. Substitute the above relations into Equations (47) and (48) to solve, and the expressions of \u03d51 and \u03d52 can be obtained: \u03d501 = \u03b2\u2212 arcsin eh + \u221a e2h2 \u2212 ( i212r2 1 \u2212 e2 )( r2 a2 \u2212 h2 \u2212 i212r2 1 ) i212r2 1 \u2212 e2 (49) \u03d502 = \u03b2\u2212 arccos \u221a r2 a1 \u2212 h2 r1 (50) Substituting Equations (49) and (50) into Equation (46), the calculation formula and constraint on the contact ratio of the conjugated straight-line internal gear pair can be obtained" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure9-1.png", + "caption": "Fig. 9 Mesh topology for the outlet pipe Fig. 10 Mesh topology for the inlet pipe", + "texts": [ + " It can be observed that the value \u03c8 becomes independent on the grid size, when the mesh element reaches N \u2265 1.2M for different flow rates. As a consequence, and to save the computational resources, the simulations used for the analysis are discretized over N=1.2 M grid elements distributed as follows: The meshes are distributed as following: \u2022 725,000 elements in the casing (static fluid domain) as shown in Figs. 7. \u2022 325,000 elements in the impeller (dynamic domain) as shown in Figs. 8. \u2022 70,000 elements in the inlet pipe (Fig. 9). \u2022 80,000 elements in the outlet pipes (Fig. 10). In these simulations, the impeller is rotated in three complete revolutions with a total duration time of 0.3 second (unsteady simulation). The setting of the interface surfaces model between impeller and the side flow channel is set to be transient \u201crotor-stator\u201d, due to the change of the relative position between the impeller and the side channel at each time step. For time integration, the second-order backward Euler is kept in the transient scheme" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002893__icape2024_03014.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002893__icape2024_03014.pdf-Figure3-1.png", + "caption": "Fig. 3. PRA_matic control panel (Elektro-Elektronik Pranjic).", + "texts": [ + " The industry produces a fairly large range of control panels, both stationary and remote, which are used to control various mining machines with a high degree of automation. Stationary control panels that allow remote control of mining equipment include consoles manufactured by various companies [9, 10, 12]. EEP Elektro-Elektronik Pranjic company is one of the leading in automation technologies in mining. The main intellectual and innovative product and application of EEP is PRA_matic\u00ae - complex underground mining control system. Spark proof PRA_matic\u00ae control blocks designed by EEP provide accurate electric hydraulic control and can execute up to 24 functions (Figure 3). Fig. 3. PRA_matic control panel (Elektro-Elektronik Pranjic). EEP Elektro-Elektronik Pranjic set on operation more than 60 sets of modern automatic control for underground mining. In this case, as a rule, underground personnel is necessary only for technological process control and maintenance. Automation allowed to upgrade safety and economic conditions. In some countries full automation of technological processes in mining face is provided with \"Robotic Mining\" complex control system designed by \"marco System Analysis and Development GmbH\" [10]", + " The industry produces a fairly large range of control panels, both stationary and remote, which are used to control various mining machines with a high degree of automation. Stationary control panels that allow remote control of mining equipment include consoles manufactured by various companies [9, 10, 12]. EEP Elektro-Elektronik Pranjic company is one of the leading in automation technologies in mining. The main intellectual and innovative product and application of EEP is PRA_matic\u00ae - complex underground mining control system. Spark proof PRA_matic\u00ae control blocks designed by EEP provide accurate electric hydraulic control and can execute up to 24 functions (Figure 3). EEP Elektro-Elektronik Pranjic set on operation more than 60 sets of modern automatic control for underground mining. In this case, as a rule, underground personnel is necessary only for technological process control and maintenance. Automation allowed to upgrade safety and economic conditions. In some countries full automation of technological processes in mining face is provided with \"Robotic Mining\" complex control system designed by \"marco System Analysis and Development GmbH\" [10]. This system provides with process and mechanisms computer control in mining face in full automated mode with one panel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.14-1.png", + "caption": "Figure 2.14 Geometry of the sea-water half-loop antenna [26]", + "texts": [ + "9 Geometry of monopole water antenna [10] ..................................................... 33 Figure 2.10 Simulation and Measurement S11 Result [10] .............................................. 34 Figure 2.11 S11 results for different salt concentration [10] ............................................ 35 Figure 2.12 Geometry of seawater monopole antenna [21] .............................................. 39 Figure 2.13 Reflection coefficients of seawater monopole antenna [21] ......................... 41 Figure 2.14 Geometry of the sea-water half-loop antenna [26] ........................................ 43 Figure 2.15 Measured and simulated reflection coefficients of the sea-water half-loop antenna [26] ...................................................................................................................... 44 Figure 2.16 Geometry of the hybrid water monopole-ring antenna [27] .......................... 45 Figure 2.17 Simulated reflection coefficient of hybrid water monopole antenna [27] ....", + " Thus, the radiation efficiency for the half-wavelength dipole in free space can be written as 1 i totalP P (2.15) If designed properly, this seawater monopole antenna may also be used for wide-band applications. Therefore, it may be interesting to look at its radiation characteristics over a wide frequency range. In 2015, a seawater half-loop antenna [26] was implemented, in contrast to the metalwire counterpart, it can be tunable and turned off in real time; therefore it is a more convenient small space antenna available to ships for maritime wireless communications. Figure 2.14 shows the geometry of the proposed sea-water half-loop antenna. As shown, the antenna mainly consists of a capacitive coupling feeding structure and a stream of sea water supplied by a water pump. The feeding structure is formed by a metallic tube with a tilt angle \u03b8, a feeding post and a dielectric-filled parallel-plate capacitor. When the antenna is activated, the seawater is first pumped into the metallic tube, and then the water stream shoots out from the tube to form a half-loop. The signal couples to the antenna from the feeding post through the parallel-plate capacitor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004932_.1186_1743-0003-9-51-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004932_.1186_1743-0003-9-51-Figure7-1.png", + "caption": "Figure 7 Free Body diagram of the load cell. The force F, whose components are Fx, Fy and Fz, applied at P, is equilibrated by GRF applied at COP along the same direction of F.", + "texts": [ + " The reference grid was a 2100x1050 mm sheet of aluminium, which was clamped to the sensorized surface. During the calibration, a subject was asked to load the walkway while moving for a ten-seconds-long trial. For each of the two plates, the data acquisition procedure accounted for records in k = 9 known positions that span all the surface. Since the distance between the spherical joint and the sensorized surface was h = 50 mm, the point of application of the force exerted by the sensorized surface to the load cell (see COP in Figure 7) does not coincide with the vertical projection of the spherical joint (see P in Figure 8 Recorded GRF after calibration. Representative 5-seconds-long record related of the set of forces developed by the operator while moving on the walkway during calibration procedures. The figure shows the components of GRF estimated by SENLY before (red) and after (green) calibrating, and compares them to those measured by the reference load cell (black). x, y and z axes are respectively the AP, ML and vertical directions. Figure 7) on the ground (see O in Figure 7). Therefore, the location of the GRF is given by: COPk x \u00bc xk \u00fe \u0394xk COPk y \u00bc yk \u00fe \u0394yk \u00f02\u00de where: \u2013 COPkx and COPky are the components of the point of GRF related to the kth reference position; \u2013 xk and yk are the coordinates of the vertical projection of the spherical joint on the surface (see O in Figure 7) related to the kth reference position; \u2013 \u0394xk and \u0394yk are the components of the distance between GRF (see COP in Figure 7) and vertical projection of the spherical joint on the sensorized surface (see O in Figure 7), related to the kth reference position. According to the force equilibrium shown in Figure 7, \u0394xk and \u0394yk can be estimated by the following Equations: \u0394xk \u00bc h Fx=Fz \u0394yk \u00bc h Fy=Fz \u00f03\u00de where Fx, Fy and Fz are the components of the applied force. The calibration algorithm was then based on the leastsquares approach, and aimed at estimating the 36 parameters constituting the calibration matrix resulting from the model described in (4): Fapp Mapp \u00bc C Fplat Mplat ; Fapp \u00bc Fxapp Fyapp Fzapp 2 4 3 5; Mapp \u00bc Mxapp Myapp Mzapp 2 4 3 5 Fplat \u00bc Fxplat Fyplat Fzplat 2 4 3 5; Mplat \u00bc Mxplat Myplat Mzplat 2 4 3 5 ; ; \u00f04\u00de where: \u2013 Fapp is the applied force measured by the reference sensor; \u2013 Mapp is the moment generated by Fapp and calculated with respect to the center of the reference frame related to the platform; \u2013 Fplat and Mplat are respectively estimated force and moment; \u2013 C is the 6x6 calibration matrix", + " alibration For each k position, a 10 s long record was acquired with 1000 Hz sample rate, involving 10x1000x6 non linear relations. The algorithm, therefore, estimated the 36 parameters minimizing the Root Mean Square (RMS) of the residual error. The movement of the subject on the walkway during calibration procedures generated variable forces which vertical and horizontal components ranged respectively between 500 N and 1000 N, and \u221250 N and 150 N (Figure 8). COP also deviated of about 15 mm from the centre of the load cell (see O in Figure 7). As expected, calibration improved both precision and accuracy of the measurement, decreasing RMS and maximum error and increasing correlation coefficients between applied and estimated variables, as reported in Table 2. Moreover, it allowed to achieve a better estimation of measurements than those adopted for other platforms of comparable size [15]. This section is firstly aimed at describing tests carried out to verify both the consistence of expected performance of the sensorized surface with actual ones, and the influence of both the instrumental noise and the noise due to moving belts" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001089_ff397de6de9d42fe.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001089_ff397de6de9d42fe.pdf-Figure1-1.png", + "caption": "Figure 1. (a) 2D and (b) 3D representation of geometrical sizing of tubular linear generator.", + "texts": [ + " Analysis of the correlation between the variable parameters of the generator and e ciency, power out, weight, cost, and cogging torque Regression is an approach to modeling the relationship between two or more variables functionally. The value of the variable y is estimated for the values of the independent variable x. Correlation is used to see whether there is relationship between two numerical variables, and if there is, to see the direction and size of this relationship. The mathematical model of the tubular linear generator (Figure 1) is written in MATLAB GUI. Analytical sizing data are given in Table 1. It is vital to identify the parameters that will have direct e ect on the performance of the generator in the optimization process, since incorrectly chosen design variable(s) has an undesirable in uence on the success of optimization. In addition, the determined input variables should not be associated with each other, since this will lead to calculating the correlation between output parameters and input parameters. It is important to nd out the correlation between input variables and output parameters and to nd out to what extent an input variable explains the output parameter" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure80-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure80-1.png", + "caption": "FIGURE 80. Theoretical model (a) and prototype (b) of the three-port UAV integrated antenna system. [46].", + "texts": [ + " The radiating currents are then synthesized to produce the desired radiation patterns using CMs on the ship platform. This is made more efficiently by the modal solutions in CM theory. Thirdly, non-protruding slits are then proposed to excite the synthesized currents. It is seen from Fig. 79 that 20 modes are significant (MS> 0.707) at around 5 MHz. These 20 modes are finally chosen to be synthesized in terms of radiation patterns. The next study in [46] involves the use of the CMAmethod for designing an electrically small unmanned aerial vehicle (UAV) antenna system, as shown in Fig. 80. Five steps are VOLUME 9, 2021 98857 involved in applying the CM theory to design this three-port antenna system, as follows: i. The existing platform which serves as the radiating aper- ture is integratedwith one ormore probes, which are used to excite currents on the platform. ii. The CMs of the platform are applied to synthesize radiation patterns efficiently. The efficiency of the design process is improved by replacing the full-wave simulations with simple linear combinations of CMs. iii. Small probes are designed to excite the currents for the synthesized radiation patterns" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004113_.aspx_paperID_130953-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004113_.aspx_paperID_130953-Figure6-1.png", + "caption": "Figure 6. Working arrangement of the parabolic reflector antenna (front-fed) [22].", + "texts": [ + " these signals become concentrated on a point and they all meet at this single point. On the other hand, if another source of energy (point source) is placed at the focal point (i.e. focus) of the parabolic reflector, parallel rays of signals are reflected. These reflected parallel rays are said to be \u201ccollimated\u201d [20] [21]. The point source of the parabolic reflector antenna i.e. the receiver, is placed at the focal point or the focus of the parabolic reflector which is in front of the parabola. This arrangement is referred to as \u201cfront fed\u201d as shown in Figure 6. The parabolic reflector antenna functions similarly to a searchlight or flashlight reflector which directs the signals in a narrow beam or receives signals from one particular direction only. Measurement Result Summary Results From the tables (Tables 1-7), it is observed that: 1) There\u2019s a slightly linear relationship between the signal quality and the surface area of the parabolic antenna, i.e. the signal strength increases with increase in aperture surface area. 2) Kang, J., Wang, W., Zhang, S" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure159-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure159-1.png", + "caption": "Figure 159 : Vue 3D d\u2019une maille \u00e9l\u00e9mentaire de la source bande X surmont\u00e9e des WAIM 1 et 2 optimis\u00e9s dans le cas 2.", + "texts": [ + " Comme pour le cas 1, l\u2019objectif \u00e9tant d\u2019obtenir des am\u00e9liorations mesurables en termes de gain, il est n\u00e9cessaire de connaitre les performances initiales de la source bande X en fonction de l\u2019angle de d\u00e9pointage. Les variations du coefficient de r\u00e9flexion actif en fonction de l\u2019angle de d\u00e9pointage pour les trois fr\u00e9quences choisies (9,9, 10 et 10,1GHz) sont report\u00e9s sur la Figure 158. Pour obtenir un coefficient de r\u00e9flexion actif sup\u00e9rieur \u00e0 -5dB pour au moins deux fr\u00e9quences, il faut obtenir des capacit\u00e9s de d\u00e9pointage allant au moins jusqu\u2019\u00e0 58\u00b0 dans le plan E, et jusqu\u2019\u00e0 74\u00b0 dans le plan H. La Figure 159 pr\u00e9sente une vue 3D d\u2019une maille \u00e9l\u00e9mentaire de la structure optimis\u00e9e. Page 160 sur 182 Contrairement au cas 1 pr\u00e9sent\u00e9 pr\u00e9c\u00e9demment, une am\u00e9lioration des performances est maintenant attendue dans le plan E, en plus du plan H. La structure WAIM est cette fois-ci compos\u00e9e du WAIM 1 permettant d\u2019optimiser le plan H et du WAIM 2 permettant d\u2019optimiser le plan E. Les WAIM 1 et WAIM 2 sont tous les deux compos\u00e9s de deux rubans rectangulaires identiques grav\u00e9s sur un substrat di\u00e9lectrique de Rogers RO 4003" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000164_e_download_1146_1073-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000164_e_download_1146_1073-Figure11-1.png", + "caption": "Fig. 11. Straight permanent magnet motor initial mesh", + "texts": [ + " The modeling of the flux lines for the suggest design which used ( Vizimag ) package can be represented by the Fig. 10-a represents the movement of free magnets on the straight slides with number of magnets steps when open source was a straight and Fig. 10-b represents the steps of free magnets on the free rotor with number of magnets steps when open source was a ring (cycle) shape. (b) when open source was a ring(circular) shape. At first, the initial mesh was designed in (DS Solidworks package) consistent with the straight parameters chosen previously as shown in Fig. 11. The mesh with 23705 nodes was then imported into (Infolytica Magnet) and a static 2D simulation was performed on both outer (stator) and inner(rotor) the distribution of flux lines is sketching with (femm), so that the magnetic field gradient can be computed. Fig. 12 shows the simulation of straight permanent magnet. The steps of inner (rotor) movement inside two outer(stator) are illustrated in Appendix (D). One of these results is the distribution of flux density as shown in Fig. 13. The magnet of (N35) is made with low cost therefore the energy is between 263 -287 that mean it easy to broken ,so the magnets must be fixed on core with glue to prevent its damaged" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004002_c_free.html_id_10138-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004002_c_free.html_id_10138-Figure1-1.png", + "caption": "Figure 1: Bogie frame (CAD model).", + "texts": [ + " In order to fill this gap, authors have proposed a first topological optimization approach based on the reference European standard for bogie structural requirements, including manufacturing constraints oriented to casting production process, that combines different modelling environments: CAD, FEM and Multibody. The benchmark aims to define an effective procedure to redesign a railway bogie frame, ensuring the mechanical performance of the system, including static, dynamic and fatigue evaluations. In addition, a multibody analysis was conducted to compare the optimized solution and the original one in terms of running dynamic. A fundamental condition for a complete assessment of the bogie innovation. The procedure was tested on a bogie frame designed for a light rail vehicle, illustrated in Figure 1. The methodology adopted by the authors for the innovation of the present bogie frame is briefly described and summed up in Figure 2. It aims to combine CAD environment, FE calculation, structural optimization process involving technological constraints oriented to casting process and multibody analysis to assess the running dynamic of the railway vehicle. One important objective of the activity was to create a suitable bogie frame design to produce it with a sand-casting process. It represents a real innovation in railway field, where this type of mechanical system, due to its complex features, it is always made up with structural steel and assembled through a welding process" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003827_f_version_1527132471-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003827_f_version_1527132471-Figure1-1.png", + "caption": "Figure 1. Actuator: (a) exploded view; (b) assembled view; and (c) final prototype.", + "texts": [ + " Creating 3D-printed actuators using plastic filaments and hobby-grade printers is significantly challenging because of the low resolution of hobby-grade printers, leading to: limited strength parts, rough (high friction) surfaces, thus reducing the efficiency, appreciable clearance, leading to leakages, and anisotropy of the parts, resulting in direction-dependent strength. In this research, the challenges are met by using metal in high stress parts, post-processing of the printed surfaces for a smooth finish, piston head design and O-ring placement for a leak-proof piston-cylinder interface. The CAD design and the final 3D-printed linear actuator are shown in Figure 1. The final actuator design had a weight of 0.34 kg, a bore diameter of 2.7 cm and a stroke length of 14.0 cm. The pneumatic cylinder consisted of four main components: (1) a 3D-printed cylinder body; (2) two 3D-printed sensor carriers, positioned around the cylinder to retain the position sensors; (3) a metal piston rod with a 3D-printed piston head; and (4) a 3D-printed end cap with bushings. 2.1.1. Cylinder The cylinder was 3D printed using the Ultimaker 3 Extended printer using a PolyLactic Acid (PLA) filament", + " The use of a steel rod shaft as opposed to a 3D-printed shaft was due to the ability of the former to handle the high stresses that are generated during the operation. The piston head was fitted with a high strength neodymium magnet. The neodymium magnet was available as an annulus. Thus, the piston head was 3D-printed with an internal threaded hole of a diameter equal to the inner circle of the magnet. A non-ferrous screw was used to secure the magnet to the piston head. In addition, the piston had a groove to mount the seal (O-ring) between the piston and cylinder and to mount four retainer blocks as shown in Figure 1. The magnetic field generated by the magnet was measured by the Hall effect sensors mounted along the length of the cylinder. The output voltages from the Hall effect sensors were calibrated to indicate the position of the piston head relative to the cylinder. The fluoroelastomer seal goes by the trade name Viton and has a Durometer 60A hardness. We found that the chosen seal used in our configuration was extremely effective at sealing the pneumatic piston at pressures up to 150 psig (1034 kN/m2)", + " Sensors The actuator had non-contact position sensors to measure the piston travel. The actuator also had 2 pressure sensors in the actuator chambers that were calibrated to measure the force. The position of the piston was obtained by using Hall effect sensors that measured the magnetic intensity of the neodymium magnet in the piston head. The magnetic intensity was measured using an array of Honeywell SS49E linear Hall effect sensors, arranged in sectional modules along the length of the pneumatic cylinder, as shown in Figure 1. The sensors were separated such that there was sufficient response overlap to allow absolute positioning of the piston-mounted neodymium magnet while minimizing the number of required individual Hall effect sensors. Each Hall effect sensor had a response length of 1.27 cm and required at least 0.635 cm of adjacent sensor overlap to calculate sufficient absolute sensor resolution. A total of 15 sensors was required to measure the piston position over the entire length of the piston. Figure 3 shows the raw voltage measured by the array of Hall effect sensors as the piston travels the full length" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000709_.1117_12.2307961.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000709_.1117_12.2307961.pdf-Figure17-1.png", + "caption": "Figure 17 : integrated FPA", + "texts": [], + "surrounding_texts": [ + "3.1 RSI overall configuration The Instrument features two main parts: The push-broom camera which includes the telescope and the Focal Plane Assembly (FPA) attached to the rear side of the telescope: Two Instrument Processing Units (IPU) mounted in cold redundancy inside the Bus and whose functions are to ensure the video data processing, the data compression and the telemetry/telecommand data processing (including thermal acquisition and control). 3.2 RSI Camera Telescope optical concept The camera is based on a compact Cassegrain-type telescope and a four-lenses field corrector Figure 5: Telescope optical concept Focal Length 2896 mm Pupil Diameter 600 mm F/N = 4.83 Field of View +/- 0.8\u00b0 Optical Quality WFE < 40 nm rms Figure 6: Optical Sub-assembly characteristics Silicon carbide for mirrors and structure The RSI design is based on an all-SiC opto-mechanical architecture (telescope structure, mirrors, and focal plane structural elements). This monolithic design approach, combined with the intrinsic SiC100 properties (high stiffness, low density, low thermal expansion, high thermal conductivity) allows to combine a high level of stability together with a low mass. Low mass: telescope mass ~ 60 kg, High Rigidity: first Eigen frequency >100Hz, High mechanical stability: inter mirror stability lower than 5\u03bcm, High thermo-elastic stability: quasi a-thermal configuration. Telescope structure The telescope structure is only featuring three main parts: the main plate (supporting the primary mirror), the secondary mirror support, and the rod connecting those two parts. ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-3 Telescope mirrors SiC mirrors can be light-weighted and polished with a high accuracy. Both mirrors were SiC CVD1 coated before polishing in order to minimize the roughness The Wave-front Error (WFE) was measured below 20 nm rms for each mirror, with a roughness lower than 1.0 nm rms. 1 CVD: Chemical Vapor Deposition Refocusing capability The secondary mirror is fixed on the structure by its interface flange. The primary mirror is fixed on to the structure through three iso-static invar mounts and thus thermally decoupled from the structure. Its temperature is controlled by a heater plate located between the mirror and the mounting plate. Setting different thermal control set points between the telescope structure and the primary mirror leads to a variation of the focal plane position, thanks to the low - but nonnull \u2013 thermal expansion coefficient of silicon carbide. The refocusing capability is +/- 200\u03bcm for a +/- 5\u00b0C thermal set point variation. Focal Plane Assembly (FPA) The focal plane assembly features only two CCD for the 5 required spectral bands. One CCD is dealing with the Panchromatic band and the other one is dealing with the multi-spectral bands. The separation of the entrance optical bean is ensured by an optical field separator. ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-4 A 4-line CCD for Multi-spectral bands ROCSAT2 took benefit of the pre-development performed by Atmel, under a CNES R&D contract. The TH31547 multi-spectral CCD consists of 4 photodetector lines, each line being made of 6000 photodiodes with 13\u03bcm step. The detector is operated at 5 Mpixel/s per video output. Each CCD line is coupled with a spectral band filter. The four slit filters are coated on the same glass substrate glued on the CCD. High speed video processing for the panchro- matic channel The panchromatic detection chain is based on the wellknown TH7834B detector (12000 useful 6.5 x 6.5 \u03bcm\u00b2 pixels). The challenge was to operate the four serial read-out registers at a 10 MHz pixel rate for satisfying the 308\u03bcs integration time required to achieve the 2- meter resolution. Front end electronics Each CCD is connected to a dedicated front-endelectronic board which ensures the clock driver distribution and the video signal pre-amplification. Integrated FPA ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-5 3.3 Integrated Video Processing Function The Instrument Processing Unit (IPU) is gathering the instrument electronics functions in a modular and highly integrated assembly. The IPU is coupled with the Focal Plane Assembly front-end electronics - Panchromatic Electronics Board (PEB) & Multi-spectral Electronics Boards (MEB) \u2013 and also with three Spacecraft main units: the On Board Management Unit (OBMU), the Solid State Recorder (SSR), and the Distribution & regulation Unit (DRU). Each IPU includes the necessary functions: to operate both CCD detectors - through the front end electronics located in the FPA to process the video analogue signal and to condition and to digitise all the pixel values, to compress the data flow with an improved adaptative rate regulated JPEG algorithm, to ensure the instrument thermal control. These functions are split on seven electronics boards racked in the same unit. 3.4 RSI Main Characteristics ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-6" + ] + }, + { + "image_filename": "designv8_17_0002797_f_version_1685957343-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002797_f_version_1685957343-Figure3-1.png", + "caption": "Figure 3. SRM 8/6 motor.", + "texts": [ + " This is based on the relationship between inductance L(\u03b8, i)|\u03b8=constant current i(t), and magnetic flux (\u03d5), which states that inductance is equal to the ratio of magnetic flux to current (L(\u03b8, i) |\u03b8=constant = \u03d5(\u03b8,i)|\u03b8=constant i(t) ). The SRM is composed of two materials: copper coils and a stator made of high- resistivity M19-29-gauge iron. Finite Element Method (FEM) and MATLAB tools are used to simulate the SRM\u2019s characteristics. The magnetic properties are calculated using FEM in ANSYS, based on a DXF file generated in AUTOCAD, as shown in Figure 3. Machines\u00a02023,\u00a011,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 10\u00a0 of\u00a0 21\u00a0 \u00a0 \u00a0 In\u00a0this\u00a0study,\u00a0it\u00a0is\u00a0demonstrated\u00a0that\u00a0the\u00a0Switched\u00a0Reluctance\u00a0Machine\u00a0(SRM)\u00a0can\u00a0be\u00a0 modeled\u00a0as\u00a0a\u00a0polynomial\u00a0GHM.\u00a0Consequently,\u00a0when\u00a0the\u00a0SRM\u00a0is\u00a0stimulated\u00a0by\u00a0a\u00a0sinusoi\u2010 dal\u00a0signal\u00a0with\u00a0a\u00a0frequency\u00a0of\u00a0 \ud835\udf14,\u00a0its\u00a0output\u00a0signal\u00a0may\u00a0comprise\u00a0harmonics\u00a0of\u00a0the\u00a0form\u00a0 \ud835\udc58\ud835\udf14.\u00a0 Table\u00a02.\u00a0Parameters\u00a0extracted\u00a0from\u00a0FEM\u00a0software.\u00a0 Current\u00a0(A)\u00a0 Flux\u00a0Linkage\u00a0 (Wb)\u00a00\u00b0\u00a0 Inductance\u00a0(H)\u00a0 0\u00b0\u00a0 Flux\u00a0Linkage\u00a0 (Wb)\u00a015\u00b0\u00a0 Inductance\u00a0(H)\u00a0 15\u00b0\u00a0 Flux\u00a0Linkage\u00a0 (Wb)\u00a030\u00b0\u00a0 Inductance\u00a0(H)\u00a0 30\u00b0\u00a0 0", + "\u00a0This\u00a0signal\u00a0has\u00a0a\u00a0frequency\u00a0band\u00a0with\u00a0sufficiently\u00a0high\u00a0harmonics,\u00a0enabling\u00a0the\u00a0 identification\u00a0of\u00a0SRM\u00a0parameters\u00a0through\u00a0a\u00a0single\u00a0experiment.\u00a0The\u00a0SRM\u2019s\u00a0electrical\u00a0model\u00a0 can\u00a0be\u00a0described\u00a0by\u00a0a\u00a0polynomial\u00a0GHM,\u00a0where\u00a0the\u00a0phase\u00a0current\u00a0 \ud835\udc56 \ud835\udc61 is\u00a0the\u00a0input\u00a0signal,\u00a0 and\u00a0the\u00a0phase\u00a0winding\u00a0voltage\u00a0 \ud835\udc49 \ud835\udc61 \u00a0 is\u00a0the\u00a0system\u00a0output\u00a0(Section\u00a02).\u00a0The\u00a0operating\u00a0fre\u2010 quency\u00a0starts\u00a0from\u00a0an\u00a0initial\u00a0frequency\u00a0 \ud835\udc53 10Hz\u00a0 and\u00a0increases\u00a0exponentially\u00a0to\u00a0a\u00a0final\u00a0 frequency\u00a0 \ud835\udc53 500Hz\u00a0 (Figure\u00a02).\u00a0The\u00a0frequency\u00a0band\u00a0is\u00a0selected\u00a0based\u00a0on\u00a0the\u00a0stator\u00a0and\u00a0 rotor\u00a0iron\u00a0saturati n\u00a0range.\u00a0 Figure\u00a03.\u00a0SRM\u00a08/6\u00a0motor.\u00a0 The\u00a0software\u00a0utilizing\u00a03D\u00a0finite\u00a0element\u00a0(FEM)\u00a0allows\u00a0for\u00a0the\u00a0model\u00a0simulation\u00a0of\u00a0the\u00a0 SRM\u00a0(Table\u00a03),\u00a0with\u00a0subsequent\u00a0export\u00a0of\u00a0all\u00a0input\u00a0(phase\u00a0current)\u00a0and\u00a0output\u00a0(voltage)\u00a0 data\u00a0to\u00a0MATLAB\u00a0tools.\u00a0The\u00a0proposed\u00a0methodology\u00a0is\u00a0designed\u00a0to\u00a0effectively\u00a0separate\u00a0the\u00a0 harmonics\u00a0of\u00a0the\u00a0SRM\u00a0output,\u00a0with\u00a0a\u00a0specific\u00a0focus\u00a0on\u00a0determining\u00a0the\u00a0filters\u00a0 \ud835\udc3a , \ud835\udc3a ,\u00a0 and\u00a0 \ud835\udc3a \u00a0 of\u00a0the\u00a0GHM\u00a0(refer\u00a0to\u00a0Figure\u00a01).\u00a0Notably,\u00a0the\u00a0only\u00a0parameters\u00a0unknown\u00a0in\u00a0the\u00a0obtained\u00a0 model\u00a0of\u00a0SRM\u00a0(the\u00a0GHM\u00a0of\u00a0Figure\u00a01)\u00a0are\u00a0the\u00a0filters\u00a0 \ud835\udc3a (s), \ud835\udc3a (s),\u00a0 and \ud835\udc3a (s)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003971__2462_context_theses-Figure5-5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003971__2462_context_theses-Figure5-5-1.png", + "caption": "Figure 5-5: Mode of a flexible body in MSC.Adams", + "texts": [ + " Figure 5-3 shows the Command window. 5.1.4 MBD \u2013 MSC.Adams Multi body dynamic (MBD) simulation is a system that consists of solid bodies that are connected to each other by joints. The bodies can interact with each other due to force/contact connections. It is a study of the influence of forces, like contact forces, gravity or other forces, that makes it possible to analyze the systems mechanism as motion and behavior. The MBD simulation was performed with MSC.Adams, Figure 5-4 shows the user interface. 45 Figure 5-5 shows a mode of the flexible body in MSC.Adams and Figure 5-6 shows the deformation of a crocked tooth during a contact. 46 To simulate the behavior of flexible bodies, all flexible parts need to have a finite element model structure. Due to this structure the DOF which are infinite becomes finite. However, due to more than ten thousands of nodes, the number of DOF is still very large. Each part has its own local reference frame (coordinate system) that is defined by a position vector to the global reference frame" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004425_icle_download_104_97-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004425_icle_download_104_97-Figure14-1.png", + "caption": "Figure 14: Representation of springs in three directions (Lacayo et al., 2019)", + "texts": [], + "surrounding_texts": [ + " The behavior and the response of both curves obtained are the same. The transition point from micro-slip to macro-slip in the positive and negative cycle is the same. The maximum and minimum forces within the loading cycle are also the same. The change in dissipation parameter will change the shape of the curve, the lower the parameter, the smoother the curve." + ] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure4.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure4.12-1.png", + "caption": "Figure 4.12 : Illustration of an electric motor 3-D section with cooling system channels.", + "texts": [ + " The cooling circuit, the heat exchanger, and the connections will be specifically described in the following subsections. 4.3.3 Cooling technology The thermal issue and cooling solutions are defined based on the analytical study in subsection 4.3.1. To maintain the motor temperatures below the limits, the cooling system focuses on frame liquid cooling with liquid jackets around the motor core, a possible rotor liquid cooling through the motor shaft, and end-windings potting. Cooling Channels in Motor The coolant circulation in motor channels is illustrated in Figure 4.12. A cooling circuit has been chosen consisting of a water-glycol jacket with the internal liquid flow around the motor and possibly a liquid flow inside the shaft (examples of such technology is found in [178], [179]). Through these liquid channels, the coolant will flow to absorb the thermal flux, and the outside environment acts as a heat evacuation medium to dissipate the absorbed heat. DOWTHERM SR-1 Fluid at 50% Ethylene Glycol has been chosen as a coolant in the circuit for multiple properties and in particular its low solidification temperature" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001811_article-file_1690258-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001811_article-file_1690258-Figure4-1.png", + "caption": "Figure 4. Detailed section of the slitted motor model.", + "texts": [ + "1 mm in order to avoid saturation in the rotor poles. Choosing wide slits reduces the rotor pole tooth thickness, which causes saturation in the rotor poles. Likewise, if the number of slits in the rotor poles is high, saturation occurs in the rotor poles. Three slits are made on each rotor pole. The main purpose of opening the slits is to increase the length of the air gap between the stator and rotor poles and accordingly to increase the reluctance value. The detailed section view of the proposed slitted motor model is given in Figure 4. RMxprt is an interactive software package used to design and analyze electrical machines. It is a template-based electrical machine design tool that provides fast and analytical calculations of machine performance. Various machines can be simulated and performance analysis can be performed using RMxprt. With the help of Maxwell, static electric fields, static magnetic fields, time varying magnetic fields and transient state analysis can be performed [14]. The analysis of reference and slitted motor models have been solved in Ansys Maxwell 2-D transient solver" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002307_df_en_2018_09_08.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002307_df_en_2018_09_08.pdf-Figure1-1.png", + "caption": "Fig. 1. Design scheme of laboratory and field experimental installation: \u0406 \u2014 wheeled arable and row-crop tractor; \u0406\u0406 \u2014 frontally mounted beet tops harvesting machine; 1 \u2014 frame; 2 \u2014 coupling device; 3 \u2014 support", + "texts": [ + " Experimental studies were conducted in the field conditions of the Fastovsky district of the Kyiv region. The object of experimental research was the working process of cutting the hitch developed by the unit. The conditions for conducting studies that were identified according to known methods [6-9] are given in the table 1. To implement the program of experimental research of the technological process of removing the wick with the use of a wiping machine, a laboratory-field experimental setup (Fig. 1) was developed that is frontal hinged on an ore-propagating wheeled tractor of the traction class 3.0, and the shearing cutting apparatus is made in the form of a horizontal rotor 4]. The machine allows to realize a continuous, complete cutting of the main mass of the tops with its subsequent loading into the vehicle. wheel; 4 \u2014 rotary cutting unit; 5 \u2014 transport device; 6 \u2014 loading device; 7 \u2014 drive The laboratory field experimentation plant (Figure 1) consists of a wheel ornon-propagating tractor I and a frontally coupled hook-picking machine II, which contains a frame 1, a coupling device 2, a copper wheel 3, a rotary shearing cutter 4, a transport device 5, a loading device 6 , as well as drive 7. The developed laboratory-field experimental setup [5] allows to fully carry out experimental researches of the experimental hoisting machine in accordance with the adopted program and methodology (Fig. 1), and consequently, with the possibility of changing the factors within the established limits: the rotor speed with the help of the drive mechanism and control tachometer; the speed of the hitch-picking machine by means of the tractor's gearbox and the control of its actual value by the track-measuring wheel; height of the rotor installation with a lever control mechanism with the ruler. On the basis of performed calculations, previous studies and analysis of a priori information, levels of variation of factors are established: - rotor speed of the machine: 500, 750, 1000 rpm; - the speed of the tops harvesting machine: 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000556_load.php_id_08123106-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000556_load.php_id_08123106-Figure1-1.png", + "caption": "Figure 1. Configuration of the preliminary TEM horn antenna.", + "texts": [ + " The measurement results show that the improved TEM horn antenna structure exhibits low VSWR as well as good radiation pattern over 2\u201314 GHz frequency band which is useful for automated pattern measurement ranges, eliminating the need for time consuming measurement interruptions normally required to change the source antenna to accommodate different frequency bands. Modified antenna also has significant applications in impulse radar systems, detection of low-observables, and test instrumentations in geological surveys. In the following section, the design method for the preliminary 2\u201314 GHz TEM horn is discussed in detail and in the Section 3 the proposed method for modification of the preliminary antenna is presented. Figure 1 shows the configuration of the preliminary TEM horn antenna. The construction of the TEM horn antenna is divided into two parts, a TEM double-ridged transition and a flare section of the horn with tapered parallel plates. The design of the horn section follows that of [16] which is explained briefly here. The TEM double-ridged transition is divided into two parts, a TEM double-ridged waveguide and a shorting plate (cavity back) located at the back of the waveguide. TEM horn antenna guides a spherical TEM-like mode between its two conductors" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure10.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure10.8-1.png", + "caption": "Fig. 10.8. Frequency distribution of the vibration for resonance passing of upper mounting of shock absorber", + "texts": [], + "surrounding_texts": [ + "100 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260" + ] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure6-1.png", + "caption": "Fig. 6. The characteristic solution of foot-mounted single-stage gear reducer with the horizontal arrangement of the shafts (Kissling solution) [14].", + "texts": [ + " Based on the analyzed gearbox housings, it can be noticed that all manufacturers produce the housings from cast iron. Only two of them (Bonfiglioli S, Leroy Somer) use aluminium alloys as material for housings of the low axis heights of reducer [13, 10]. In this way, they achieve a smaller weight of their gear units and thus better technical characteristics of their products. The housing design of single-stage gearbox depends most on the shaft arrangement and mounting method. According to this, there are gearboxes with horizontal (Fig. 6, 7, 8, 9, 10), with vertical (Fig. 11, 12) and with free shaft positions (Fig. 14, 15). Gear reducers with horizontal shaft position are usually manufactured with radial mounting and they present the old type of single-stage units. They passed through extremely intense shape development, from the usual and simple shapes, which insisted only on functionality and reduced material consumption (Fig. 6 and 7) to the very interesting contemporary forms, where great attention has been paid to the appearance of the gearbox (Fig. 9 and 10). If the gear reducer is intended for operation in an environment with high ambient temperature, as well as the higher engine power is used and higher losses can be expected, the housing should be manufactured with ribs (Fig. 7) to increase the outer surface of the housing and improve heat dissipation. Also, housing with ribs is used for large gear unit to increase their rigidity" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-FigureB.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-FigureB.5-1.png", + "caption": "Figure B.5: SDM hand [18].", + "texts": [ + " According to the researchers, the center of rotation of the EPM plays an important role in the dynamic influence compared to a typical PRB model. Guo and Lee\u2019s publication focused on the model, and the flexure-based hand is a case study. Trajectories of the center of rotation and tip of the fingers are presented. Functional requirements in terms of load-carrying capacity or weight of the device were not considered. B.2.4 Yale University Yale University introduced the use of leafsprings made of urethane for prosthetic hands [18], see Fig. B.5. The lower young modulus of the rubber joint offers high compliance in the actuation direction. However, it also offers undesired compliance in the other directions. The undesired compliance increase dramatically at large deflections, see Fig. B.6. As shown in Fig. B.6, the distance d1 increases as a large deflection of the joints occur. The increment of the arm (d1) considerably increases the torsion on the proximal joint (MCP). For this reason, the elastic joint at the MCP was later replaced by a pinjoint [11]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003857_1-4020-8159-6_11.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003857_1-4020-8159-6_11.pdf-Figure7-1.png", + "caption": "Figure 7b. Associative setting watch.", + "texts": [ + " This cognitive function allocation solution induces a competition process between the user and the artifact. The cognitive functions that are implemented in the watch are engineering-based. For example\u201a the multifunction knob is a very clever piece of engineering since with a single device one can set four time parameters. The main problem is that the end-user needs to be as clever as the engineer who designed the device in order to use it successfully\u201a or use an operation manual that will help supervise the userwatch interaction. and Artifact In the second design case (Figure 7a)\u201a there is a knob for each function (minutes\u201a hours\u201a week days and month days). This alternative design removes part of the selection confusion. The user needs to know that the upper-right knob is the hour-setting knob\u201a and so on as shown on Figure 7a. There is a pattern-matching problem. This design can be improved if the knobs are explicitly associated with the data to be set. Figure 7b presents a digital watch interface that removes the requirement for identifying which knob operates which hand or display from the user\u2014and with it the cognitive function of pattern matching. The knobdisplay relationship has become an explicit feature of the watch that exploits existing user attributes and affords selection of the correct knob. The user\u2019s task is now simply to select the knob that is next to the time data to be set\u201a and to turn this knob. This cognitive function allocation solution induces cooperation by sharing common data between the user and the artifact. Each time-setting device is associated to a single function that the end-user understands immediately such as in the design case shown in Figure 7b. The small physical distance between the time-setting knob and the corresponding data display makes this possible. The end-user does not need an operational manual. Artifact In the third example (Figure 8)\u201a new technology is used to design the watch\u201a which has the characteristic of setting time automatically in response to a voice command such as \u2018set the time to 23:53\u2019\u201a \u2018set the week day to Wednesday\u2019\u201a or \u2018set the month day to 24\u2019. We have transferred The select the hands or the right display\u201a turn the knob until the right time is set part of the cognitive function of setting the time to the required time is transferred to the watch" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004034_f_version_1579780510-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004034_f_version_1579780510-Figure1-1.png", + "caption": "Figure 1. Schematic diagram of typical SIPMSM and tile shape magnetic poles. (a) Schematic diagram of traditional SIPMSM; (b) Schematic diagram of tile shape magnetic poles.", + "texts": [ + " The reminders of this study are organized as follows. Section 2 describes the mathematical model of the proposed SIPMSM. Section 3 performs the parameter optimization for the SIPMSM. Experimental validation is carried out in Section 4 and conclusions are drawn in Section 5. Symmetry 2020, 12, 179 3 of 14 The shape of magnetic pole effects the output characteristics of PMSM directly. The permanent magnet of typical SIPMSM is a tile shape with inner and outer arc centers at the same point\u2014as shown in Figure 1. A PMSM with this kind of magnetic pole usually has the disadvantages of large cogging torque, large leakage and poor flux weakening capability [16]. Therefore, a novel SIPMSM is developed, as shown in Figure 2. The permanent magnet in the novel SIPMSM is an unequal thickness magnetic pole with different inner and outer radians, which results in the uneven distribution of the radial air-gap flux density and remarkable magnetic congregate effect. In order to reduce the leakage flux and the high harmonic content in the air-gap, an auxiliary slot is notched in the rotor, as shown in Figure 3. Symmetry 2020, 12, x FOR PEER REVIEW 3 of 14 2. The Proposed SIPMSM 2.1. Structure Design The shape of magnetic pole effects the output characteristics of PMSM directly. The permanent magnet of typical SIPMSM is a tile shape with inner and outer arc centers at the same point\u2014as shown in Figure 1. A P SM with this kind of magnetic pole usually has the disadvantages of large cogging torque, large leakage and poor flux weakening capability [16]. Therefore, a novel SIPMSM is developed, as shown in Figure 2. The permanent magnet in the novel SIPMSM is an unequal thickness magnetic pole with different inner and outer radians, which results in the uneven distribution of the radial air-gap flux density and remarkable magnetic congregate effect. In order to reduce the leakage flux and the high harmonic content in the air-gap, an auxiliary slot is notched in the rotor, as shown in Figure 3. Figure 1. Schematic diagram of typical SIPMSM and tile shape magnetic poles. (a) Schematic diagram of traditional SIPMSM; (b) Schematic diagram of tile shape magnetic poles. (a) (b) Figure 2. Schematic diagram of the novel SIPMSM and unequal thickness magnetic poles. (a) Schematic diagram of the novel SIPMSM; (b) Schematic diagram of unequal thickness magnetic poles. i re 1. Schematic diagram of typical SIPMSM and tile shape magnetic pol s. (a) Schematic diagr m of traditional SIPMSM; (b) Schematic diagr m of tile shape magnetic poles. Symmetry 2020, 12, x FOR PEER REVIEW 3 of 14 The shape of magnetic pole effects the output characteristics of PMSM directly. The permanent magnet of typical SIPMSM is a tile shape with inner nd outer arc centers at the same point\u2014as shown in Figure 1. A PMSM with t is kind of magnetic pole usually has the disadvantages of large cogging torque, large leakage and po r flux weakening capability [16]. Therefore, a n vel SIPMSM is developed, as shown in Figure 2. Th perm nent magnet in the novel SIPMSM is an unequal thickness magnetic pole with different inner and outer radians, which results in the uneven distribution of the radial air-gap flux density and remarkable magnetic congregate effect. In order to reduce the leakage flux and the high harmonic content in the air-gap, an auxiliary slot is notched in t rotor, s shown in Figure 3", + "16 nm and the flux weakening speed rate is 2.08. (2) The prototype test shows that\u2014compared with the traditional SIPMSM\u2014the new SIPMSM not only enhances the output torque and reduces the torque ripple, but also improves the performance of flux weakening speed expansion. At the same time, the high efficiency range of the constant power operation is widened, and more in line with the performance requirements of PMSM for electric vehicles. Therefore, the novel SIPMSM is more suitable for electric vehicles. Figure 1. Torque ri ple comparison betw en motor startup and rated load. From Figure 11, it can be seen that the output torque of the two SIPMSMs reaches a stable state at 77 s, owing to the same control mode and rated parameters. However, the output torque of the novel SIPMSM is clearly higher than the traditional SIPMS . This is because the reasonable design of the permanent magnets with unequal thickness makes the air-gap magnetic field have a significant magnetic congregate effect and enhances the output torque" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004509_i_10.3233_ATDE230467-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004509_i_10.3233_ATDE230467-Figure3-1.png", + "caption": "Figure 3. Structural parameters of the POM FS.", + "texts": [ + " According to the cloud maps in figure 2, the maximum strain of the POM FS is 0.0095, which occurs at the connection between the gear ring and the cup. The maximum displacement is 0.2052mm, which occurs at the bottom of the FS cup. The maximum stress is 26.19Mpa, which occurs at the connection between the gear ring and the cup. This indicates that the POM FS meets the strength and working conditions requirements for a FS in a precision harmonic drive. The cylinder length L, wall thickness d, and chamfer radius r, as presented in figure 3, are significant structural parameters that influence the stress distribution and magnitude of POM FS. Generally, longer FS can withstand greater loads, but may also result in higher bending stresses, while shorter FS generate higher torsional stresses. Thickerwalled FS can withstand higher loads, but lead to increased bending stresses, while thinner-walled FS has lower bending stresses but reduced stiffness. Appropriate chamfer radius can prevent stress concentration, reduce the maximum stress on the FS" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000539_cmtmte2018_05007.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000539_cmtmte2018_05007.pdf-Figure1-1.png", + "caption": "Fig. 1. Apparatus of tobacco leaf separation. 1 \u2013 chain contour; 2 \u2013 small drum; 3 \u2013 cutting edge of a small drum; 4 \u2013 ball bearing; 5 \u2013 pin; 6 \u2013sprocket; 7 \u2013 additional chain contour; 8 \u2013 roller; 9 \u2013 helical surface of roller; 10 \u2013 leaf-separating cell; 11 \u2013 air duct with nozzles.", + "texts": [ + " However the applied leaf-separating apparatuses have some disadvantages which do not supply with present agro-technological requirements demanding much of technological process of domestic tobacco variety harvesting. Use of leaf-separating apparatuses working with the use of rotating small drums with sharpened cutting edges fixed on chain contours as well as with equipped pneumatic system and holding rollers in harvesters allows increasing the completeness of leaf separation and decrease of leaf plate injury due to the rapid removal of leaves from the leaf separation area. The apparatus for separating tobacco leaves [8, 9] (Figure 1) includes two supporting chain contours 1 of infinite type, with small drums 2 having sharpened blades (cutting edges) and installed in the bearing supports 4 mounted on the bolts 5, as well as for rotating the small drums of sprocket 6 and additional chain contours 7. The apparatus is supplied with two rollers 8, mounted at angle relatively to the level and each other and having rotations towards each other. On every roller there was made the spiral surface 9. The drums form cells in the leaf-separation area 10", + " To orient the stalk, it is necessary to correlate the speed of movement, the frequency of rotation and the angle of inclination of the rollers, the lifting angle of the wound and other parameters [10]. At the same time, of course, the necessary condition is the movement of the harvester along the row, i.e. preservation of the course stability [11, 12, 13]. Such combination of factors will allow to observe the set technological efficiency and reliability of technological process, and as a consequence and economic efficiency [14, 15, 16, 17]. According to the design and technological scheme in Figure 1, the separation of the leaf from the stem of tobacco is produced by cutting small drums that move in a closed chain contour at a speed of V p.a., they have axial rotation \u03c9\u0431 due to the additional contour. At the same time, the movement of the machine along the row with \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u044c\u044eV\u043c that also brings components in the cutting force of the blade edge of a small drum. For a high-quality cut of the tobacco leaf, it is necessary to analyze the interaction between the cutting drum and the tobacco leaf, which will further determine the cutting force R\u0431, since it will determine the force of the anti-cutting part (the force of the airflow F\u0434\u0430\u0432 to hold the leaf)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002722_download_58477_60372-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002722_download_58477_60372-Figure2-1.png", + "caption": "Figure 2: Isometric Drawing of the Cylinder block", + "texts": [], + "surrounding_texts": [ + "The result obtained from the experimentation of the cylinder block on the engine test bed is shown on Table 4. Vol.12, No.1, 2022 The developed mathematical model from the application of the multiple linear regression technique is shown in eqaution (9) \ud835\udc4c = 1.993 \u2212 0.07583\ud835\udc34 + 0.03375\ud835\udc35 + 0.0225\ud835\udc36 (9) Where Y=Specific Fuel Consumption (SFC) in kg/kwh A=injection pressure in Mpa B=Load in N C= consumption ratio The optimal levels of the input parameters obtained from the Taguchi Design and Signal-tonoise are shown on Table 5 and Figure 4 respectively. The predicted value for the response parameter (Specific fuel consumption) is 0.680 kg/Kwh. The developed mathematical model was found to be statistically adequate with a p-value lesser than 0.05 using a significant level of 0.05. Also, the 3 input parameters were found to be significant as a result of them having a p-value that is less than 0.05 as shown on Table 6. Vol.12, No.1, 2022" + ] + }, + { + "image_filename": "designv8_17_0003809_el-03253472_document-Figure3.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003809_el-03253472_document-Figure3.8-1.png", + "caption": "Figure 3.8 : Vue 3D (a) et vue de devant zoom\u00e9e (b) de la ligne RH de la ligne 0-LH mod\u00e9lis\u00e9e sur HFSS", + "texts": [ + "32 Sachant que les lignes ont le m\u00eame substrat, il est logique qu\u2019elles aient la m\u00eame largeur. La longueur de chaque ligne \u00e9tant elle li\u00e9e aux \u00e9l\u00e9ments \u00e9lectriques, elle change selon la ligne \u00e9qui-LH consid\u00e9r\u00e9e. Nous pouvons observer que les lignes CRLH avec des bandes interdites plus larges ont des \u00e9l\u00e9ments distribu\u00e9s de longueur plus faible, ce qui entra\u00eene une meilleure compacit\u00e9 de ces structures. Une fois les param\u00e8tres physiques d\u00e9termin\u00e9s, les lignes peuvent \u00eatre simul\u00e9es sur HFSS (voir Figure 3.8). Deux lignes d\u2019acc\u00e8s de longueur lacces=40mm chacune sont rajout\u00e9es de part et d\u2019autre de la ligne RH simul\u00e9e afin que les performances de la ligne ne soient pas perturb\u00e9es par les effets de bords de la structure. Nous allons \u00e9tudier ici plus en d\u00e9tail le cas de la ligne 0-LH, sachant que le proc\u00e9d\u00e9 est identique pour les autres lignes \u00e9qui-LH. DECRIPTION DE LA METHODE DE DESIGN DE DEPHASEURS CRLH-TL 87 Les lignes sont mod\u00e9lis\u00e9es avec un ruban d\u2019\u00e9paisseur hline=37\u00b5m et un plan de masse d\u2019\u00e9paisseur hmasse=73\u00b5m" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004613_d_1_download_id_1840-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004613_d_1_download_id_1840-Figure3-1.png", + "caption": "Figure 3: Design of the realistic plasma director in CST Microwave Studio [8].", + "texts": [ + " The gaseous plasma is confined into a glass cylinder (pyrex material from CST library) of internal radius rint = rplasma = 3 mm and thickness of 0.6 mm: these values have been chosen according to real glass tubes that have been realized to confine the plasma in an experimental setup. Finally the glass cylinder is closed at the two extremities by two metallic electrodes of 1mm thickness that resemble those used to generate the plasma by RF surface wave technique. A detail of the director design in CST Microwave Studio is reported in Figure 3. In order to optimize the properties of the Yagi-Uda antenna when the two discharges are used as directors, we increased of 4 mm the distance between the two directors (this value was obtained performing optimization through a parameter sweep in CST). The last thing to point out about the model of our antenna concerns the off state of the plasma directors: in [1] when one or both the plasma bars were un-energized, they have been simply excluded from the simulations; in this work instead, we included the glass cylinders and metal electrodes in the simulations, replacing the plasma cylinder with vacuum when the plasma is off" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003069_df_ru_2024_02_07.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003069_df_ru_2024_02_07.pdf-Figure9-1.png", + "caption": "Figure 9 \u2014 Air flow current lines by velocity in the flow area without belting", + "texts": [], + "surrounding_texts": [ + "\u041f\u0430\u0434\u0435\u043d\u0438\u0435 \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0438 \u043f\u043e\u0442\u043e\u043a\u0430 \u043d\u0430\u0431\u043b\u044e\u0434\u0430\u0435\u0442\u0441\u044f \u043f\u043e \u0446\u0435\u043d\u0442\u0440\u0443 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\u043f\u0440\u0438\u043d\u044f\u0442\u044b\u043c \u0443\u0441\u043b\u043e\u0432\u0438\u044f\u043c \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435\u043d\u043d\u043e\u0439 \u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u0437\u0435\u0440\u043d\u0430.\n\u0421\u043f\u0438\u0441\u043e\u043a \u043b\u0438\u0442\u0435\u0440\u0430\u0442\u0443\u0440\u044b 1. \u0424\u0440\u043e\u043b\u043e\u0432, \u041a.\u0412. \u041c\u0430\u0448\u0438\u043d\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u0438\u0435. \u042d\u043d\u0446\u0438\u043a\u043b\u043e\u043f\u0435\u0434\u0438\u044f: \u0432 40 \u0442. /\n\u041a.\u0412. \u0424\u0440\u043e\u043b\u043e\u0432. \u2014 \u041c.: \u041c\u0430\u0448\u0438\u043d\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u0438\u0435, 2002. \u2014 \u0422. IV-16: \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0448\u0438\u043d\u044b \u0438 \u043e\u0431\u043e\u0440\u0443\u0434\u043e\u0432\u0430\u043d\u0438\u0435. \u2014 720 \u0441. 2. Experimental study on the influence of working parameters of centrifugal fan on airflow field in cleaning room / C. Zhang [et al.] // Agriculture. \u2014 2023. \u2014 Vol. 13, iss. 7. \u2014 DOI: https://doi.org/10.3390/agriculture13071368. 3. Operation technological process research in the cleaning system of the grain combine / I. Badretdinov [et al.] // Journal of Agricultural Engineering. \u2014 2021. \u2014 Vol. 52, no. 2. \u2014 DOI: https://doi.org/10.4081/jae.2021.1129. 4. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0418.\u0414. \u041d\u0430\u0443\u0447\u043d\u043e\u0435 \u043e\u0431\u043e\u0441\u043d\u043e\u0432\u0430\u043d\u0438\u0435 \u0438 \u0441\u043e\u0432\u0435\u0440\u0448\u0435\u043d\u0441\u0442\u0432\u043e\u0432\u0430\u043d\u0438\u0435 \u043f\u043d\u0435\u0432\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0438\u0445 \u0441\u0438\u0441\u0442\u0435\u043c \u0441\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0445 \u043c\u0430\u0448\u0438\u043d \u043d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u0442\u0435\u0445\u043d\u043e\u043b\u043e\u0433\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u0430 / \u0418.\u0414. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0421.\u0413. \u041c\u0443\u0434\u0430\u0440\u0438\u0441\u043e\u0432 // \u0412\u0435\u0441\u0442\u043d. \u041d\u0413\u0418\u042d\u0418. \u2014 2019. \u2014 \u2116 9(100). \u2014 \u0421. 5\u201316. 5. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u041d.\u0413. \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0442\u0435\u0440\u0438\u0430\u043b\u044b (\u0432\u0438\u0434\u044b, \u0441\u043e\u0441\u0442\u0430\u0432, \u0441\u0432\u043e\u0439\u0441\u0442\u0432\u0430) / \u041d.\u0413. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u0413.\u0410. \u0425\u0430\u0439\u043b\u0438\u0441, \u041c.\u041c. \u041a\u043e\u0432\u0430\u043b\u0435\u0432. \u2014 \u041c.: \u0418\u041a \u00ab\u0420\u043e\u0434\u043d\u0438\u043a\u00bb, \u0436\u0443\u0440\u043d\u0430\u043b \u00ab\u0410\u0433\u0440\u0430\u0440\u043d\u0430\u044f \u043d\u0430\u0443\u043a\u0430\u00bb, 1998. \u2014 208 \u0441.", + "KALINOUSKI \u0410liaksandr \u0410., M. Sc. in Eng. Leading Design Engineer E-mail: kiodpan@gomselmash.by\nScientific and Technical Centre of Combine Harvesters Manufacturing OJSC \u201cGomselmash\u201d, Gomel, Republic of Belarus\nReceived 18 January 2024.\nSYSTEM IN 2D FORMULATION\nThe paper presents the methodology of modelling air flows in the flow area of the air-screen cleaning system of a combine harvester in two-dimensional formulation. Recommendations are given on parameters adjustment of the computational fluid dynamics software package Ansys Fluent. An example is provided on aerodynamic calculation of cleaning system two-dimensional model. According to the estimation of the results of experimental studies and modelling, the error was not more than 10 %. Recommendations are formulated on the cleaning system design to obtain uniform airflow across its width. The application of this methodology makes it possible to carry out the model calculation on a personal computer without using clusters or high-performance servers. The obtained results will be subsequently used in further research of the combine harvester cleaning system.\nKeywords: cleaning system, flow area, 2D modelling, air flows, harvester\nDOI: https://doi.org/10.46864/1995-0470-2024-2-67-53-60\n1. Frolov K.V. Mashinostroenie. Entsiklopediya. T. IV-16. Sel-\nskokhozyaystvennye mashiny i oborudovanie [Mechanical engineering. Encyclopedia. Vol. IV-16. Agricultural machinery and equipment]. Moscow, Mashinostroenie Publ., 2002. 720 p. (in Russ.). 2. Zhang C., Geng D., Xu H., Li X., Li D., Wang Q. Experimental study on the influence of working parameters of centrifugal fan on airflow field in cleaning room. Agriculture, 2023, vol. 13, iss. 7. DOI: https://doi.org/10.3390/agriculture13071368. 3. Badretdinov I., Mudarisov S., Khasanov E., Nasurov R., Tuktarov M. Operation technological process research in the cleaning system of the grain combine. Journal of agricultural engineering, 2021, vol. 52, no. 2. DOI: https://doi.org/10.4081/ jae.2021.1129. 4. Badretdinov I.D., Mudarisov S.G. Nauchnoe obosnovanie i sovershenstvovanie pnevmaticheskikh sistem selskokhozyaystvennykh mashin na osnove modelirovaniya tekhnologicheskogo protsessa [Scientific justification and improvement of pneumatic systems for agricultural machines based on the simulation of technological process]. Vestnik NGIEI, 2019, no. 9(100), pp. 5\u201316 (in Russ.). 5. Kovalev N.G., Khaylis G.A., Kovalev M.M. Selskokhozyaystvennye materialy (vidy, sostav, svoystva) [Agricultural materials (types, composition, properties)]. Moscow, IK \u201cRodnik\u201d Publ., zhurnal \u201cAgrarnaya nauka\u201d Publ., 1998. 208 p. (in Russ.). 6. Fedorova N.N., Valger S.A., Danilov M.N., Zakharova Yu.V. Osnovy raboty v Ansys 17 [Basics of working in Ansys 17]. Moscow, DMK Press Publ., 2017. 210 p. (in Russ.).\n6. \u041e\u0441\u043d\u043e\u0432\u044b \u0440\u0430\u0431\u043e\u0442\u044b \u0432 Ansys 17 / \u041d.\u041d. \u0424\u0435\u0434\u043e\u0440\u043e\u0432\u0430 [\u0438 \u0434\u0440.]. \u2014 \u041c.: \u0414\u041c\u041a \u041f\u0440\u0435\u0441\u0441, 2017. \u2014 210 \u0441. 7. \u0418\u043d\u0436\u0435\u043d\u0435\u0440\u043d\u044b\u0439 \u0430\u043d\u0430\u043b\u0438\u0437 \u0432 ANSYS Workbench: \u0443\u0447\u0435\u0431. \u043f\u043e\u0441\u043e\u0431. / \u0412.\u0410. \u0411\u0440\u0443\u044f\u043a\u0430 [\u0438 \u0434\u0440.]. \u2014 \u0421\u0430\u043c\u0430\u0440\u0430: \u0421\u0430\u043c\u0430\u0440. \u0433\u043e\u0441. \u0442\u0435\u0445\u043d. \u0443\u043d-\u0442, 2010. \u2014 271 \u0441. 8. Argyropoulos, C.D. Recent advances on the numerical model ling of turbulent flows / C.D. Argyropoulos, N.C. Markatos // Applied Mathematical Modelling. \u2014 2015. \u2014 Vol. 39, iss. 2. \u2014 Pp. 693\u2013732. \u2014 DOI: https://doi.org/10.1016/j. apm.2014.07.001. 9. \u0414\u0435\u0440\u044f\u0433\u0438\u043d, \u0412.\u0424. \u041e\u0441\u043d\u043e\u0432\u044b \u0430\u044d\u0440\u043e\u0433\u0438\u0434\u0440\u043e\u0433\u0430\u0437\u043e\u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438: \u0443\u0447\u0435\u0431. \u043f\u043e\u0441\u043e\u0431\u0438\u0435 / \u0412.\u0424. \u0414\u0435\u0440\u044f\u0433\u0438\u043d. \u2014 \u041a\u0438\u0440\u043e\u0432\u043e\u0433\u0440\u0430\u0434: \u0413\u041b\u0410\u0423, 2006. \u2014 192 \u0441. 10. Ronald, P.L. Incompressible flow / P.L. Ronald. \u2014 Hoboken: John Wiley & Sons, Inc., 2013. \u2014 869 p. 11. \u0417\u0438\u0433\u0430\u043d\u0448\u0438\u043d, \u0410.\u041c. \u0412\u044b\u0447\u0438\u0441\u043b\u0438\u0442\u0435\u043b\u044c\u043d\u0430\u044f \u0433\u0438\u0434\u0440\u043e\u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0430. \u041f\u043e\u0441\u0442\u0430\u043d\u043e\u0432\u043a\u0430 \u0438 \u0440\u0435\u0448\u0435\u043d\u0438\u0435 \u0437\u0430\u0434\u0430\u0447 \u0432 \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u043e\u0440\u0435 Fluent: \u043c\u0435\u0442\u043e\u0434\u0438\u0447. \u043f\u043e\u0441\u043e\u0431\u0438\u0435 \u0434\u043b\u044f \u0443\u0447\u0435\u0431. \u0438 \u043d\u0430\u0443\u0447. \u0440\u0430\u0431\u043e\u0442\u044b \u0441\u0442\u0443\u0434\u0435\u043d\u0442\u043e\u0432 \u043d\u0430\u043f\u0440\u0430\u0432\u043b\u0435\u043d\u0438\u044f 270800 \u2014 \u00ab\u0421\u0442\u0440\u043e\u0438\u0442\u0435\u043b\u044c\u0441\u0442\u0432\u043e\u00bb (\u043a\u0432\u0430\u043b\u0438\u0444\u0438\u043a\u0430\u0446\u0438\u044f \u00ab\u0431\u0430\u043a\u0430\u043b\u0430\u0432\u0440\u00bb \u0438 \u00ab\u043c\u0430\u0433\u0438\u0441\u0442\u0440\u00bb) \u0438 \u0430\u0441\u043f\u0438\u0440\u0430\u043d\u0442\u043e\u0432 \u0441\u043f\u0435\u0446\u0438\u0430\u043b\u044c\u043d\u043e\u0441\u0442\u0438 05.23.03 / \u0410.\u041c. \u0417\u0438\u0433\u0430\u043d\u0448\u0438\u043d. \u2014 \u041a\u0430\u0437\u0430\u043d\u044c: \u0418\u0437\u0434-\u0432\u043e \u041a\u0430\u0437\u0430\u043d\u0441\u043a. \u0433\u043e\u0441. \u0430\u0440\u0445\u0438\u0442\u0435\u043a\u0442.-\u0441\u0442\u0440\u043e\u0438\u0442. \u0443\u043d-\u0442\u0430, 2013. \u2014 79 \u0441. 12. Moukalled, F. The finite volume method in computational fluid dynamics: an advanced introduction with OpenFOAM and Matlab / F. Moukalled, L. Mangani, M. Darwish. \u2014 Cham: Springer International Publishing Switzerland, 2016. \u2014 791 p. \u2014 DOI: https://doi.org/10.1007/978-3-319-16874-6. 13. \u0414\u044f\u0447\u0435\u043a, \u041f.\u0418. \u041d\u0430\u0441\u043e\u0441\u044b, \u0432\u0435\u043d\u0442\u0438\u043b\u044f\u0442\u043e\u0440\u044b, \u043a\u043e\u043c\u043f\u0440\u0435\u0441\u0441\u043e\u0440\u044b: \u0443\u0447\u0435\u0431. \u043f\u043e\u0441\u043e\u0431\u0438\u0435 \u0434\u043b\u044f \u0441\u0442\u0443\u0434\u0435\u043d\u0442\u043e\u0432, \u043e\u0431\u0443\u0447\u0430\u044e\u0449\u0438\u0445\u0441\u044f \u043f\u043e \u043d\u0430\u043f\u0440\u0430\u0432\u043b\u0435\u043d\u0438\u044e 270100 \u00ab\u0421\u0442\u0440\u043e\u0438\u0442\u0435\u043b\u044c\u0441\u0442\u0432\u043e\u00bb / \u041f.\u0418. \u0414\u044f\u0447\u0435\u043a. \u2014 \u041c.: \u0418\u0437\u0434-\u0432\u043e ACB, 2013. \u2014 432 \u0441. 14. Carolus, T. Fans: aerodynamic design \u2013 noise reduction \u2013 optimization / T. Carolus. \u2014 Wiesbaden: Springer Vieweg Wiesbaden, 2022. \u2014 253 p. \u2014 DOI: https://doi.org/10.1007/978-3-65837959-9. 15. \u0421\u043e\u043b\u043e\u043c\u0430\u0445\u043e\u0432\u0430, \u0422.\u0421. \u0420\u0430\u0434\u0438\u0430\u043b\u044c\u043d\u044b\u0435 \u0432\u0435\u043d\u0442\u0438\u043b\u044f\u0442\u043e\u0440\u044b: \u0430\u044d\u0440\u043e\u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0430 \u0438 \u0430\u043a\u0443\u0441\u0442\u0438\u043a\u0430 / \u0422.\u0421. \u0421\u043e\u043b\u043e\u043c\u0430\u0445\u043e\u0432\u0430. \u2014 \u041c.: \u041d\u0430\u0443\u043a\u0430, 2015. \u2014 460 \u0441. 16. Miu, P. Combine harvesters: theory, modeling, and design / P.I. Miu. \u2014 Boca Raton: Taylor & Francis Group, LLC, 2016. \u2014 436 p." + ] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure7-1.png", + "caption": "Fig. 7 Mesh topology for the static domain", + "texts": [], + "surrounding_texts": [ + "In order to investigate the suggested modifications, a commercial software ANSYS CFX-19.0 is used to perform 3D unsteady simulation for the flow analysis of the described RP. The Reynolds Averaged Naiver-Stokes equation (RANS) combined with the Sheer Stress Transport (SST) turbulence model are employed, as recommended by [7]. The Reynolds number, defined based on the diameter of impeller DT and the tip speed UT, is about 2\u00d7105. To keep the fine meshes near-wall capable of resolving the viscous sub-layer, y+ is kept in the range of 30~300 to comply with the log-law [25]. The computational domain is divided into three main parts as illustrated in Fig. 4a. The first one is the casing domain which contains the fluid flow around the impeller and surrounded by the external walls of casing body, the second and the third ones are the inlet pipe flow domain and the outlet pipe flow domain, respectively. In the casing flow part, the domain is divided into two parts as well, as shown in Fig. 4b; the dynamic layer domain, that represents the fluid layer rotating between walls of the impeller and fluid layer just above the impeller body; Fig. 5a and the static domain, which represents the remained part located between the casing body of the pump and the dynamic flow layer above the impeller, Fig. 5b. The lengths of the inlet and outlet pipes are about 11.1 and 13.5 times the casing diameter, respectively similar as in [7]. The centerline of the inlet pipe and outlet pipe are at angles of - 28.6o and +28.6o from the Y-axis, respectively, as shown in Fig. 6. The Boundary conditions in these current simulations are similar to that employed in [7]: \u2022 At inlet: the boundary set to be a constant static pressure and the flow is normally directed to the boundary condition with a medium turbulence intensity of 5%, which is a standard inflow boundary condition. \u2022 At outlet: the boundary condition is set to the opening with variable pre-defined mass flow rate (0.0218, 0.05, 0.109, 0.1635, 0.218, 0.2725 and 0.3815 kg/s). \u2022 The no-slip condition is employed near the solid walls. The multi-zone meshing topology is used, where triangular prisms are employed near the walls and tetrahedral mesh elsewhere as shown in Figs 7, 8, 9 and 10. In order to achieve convergence conditions, The study of the mesh independency is held on a various number of mesh elements N of 0.2 million (M), 0.5M, 0.7M, 1.2M, 1.9M, 3.2M and 4.5M. Two variables are tested to examine the mesh independency, the flow coefficient \u00d8 and the head coefficient . Where the flow coefficient \u00d8 is calculated from the flow rate Q passing through the pump and the cross-section area Ac = (2a1 + 2b1 + 2c1 + t) a2 - (2b1 + t) of the channel (See Figs. 2 and 3), \u00d8 = \ud835\udc44 \ud835\udc34\ud835\udc50 \ud835\udc48\ud835\udc47 , (1) Where UT = \u03c0 DT \u03c9 / 60 is the tip speed of impeller at rotational speed \u03c9 in revolutions per minute. The head (pressure) coefficient \u03c8 is calculated as a function of flow density \u03c1, UT, and the difference between the average values of pressures at discharge and suction sides (\ud835\udee5\ud835\udc43 = \ud835\udc43\ud835\udc51 \u2212 \ud835\udc43\ud835\udc60) at walls of the pipe as follow, = \ud835\udee5\ud835\udc43 0.5 \ud835\udf0c \ud835\udc48\ud835\udc47 2 , (2) The head coefficient \u201c\u03c8\u201d is calculated and plotted at different number of mesh elements as shown in Fig. 11. It can be observed that the value \u03c8 becomes independent on the grid size, when the mesh element reaches N \u2265 1.2M for different flow rates. As a consequence, and to save the computational resources, the simulations used for the analysis are discretized over N=1.2 M grid elements distributed as follows: The meshes are distributed as following: \u2022 725,000 elements in the casing (static fluid domain) as shown in Figs. 7. \u2022 325,000 elements in the impeller (dynamic domain) as shown in Figs. 8. \u2022 70,000 elements in the inlet pipe (Fig. 9). \u2022 80,000 elements in the outlet pipes (Fig. 10). In these simulations, the impeller is rotated in three complete revolutions with a total duration time of 0.3 second (unsteady simulation). The setting of the interface surfaces model between impeller and the side flow channel is set to be transient \u201crotor-stator\u201d, due to the change of the relative position between the impeller and the side channel at each time step. For time integration, the second-order backward Euler is kept in the transient scheme. Figure 12 shows comparisons between the current simulation and the experimental and numerical results introduced by Horiguchi et al. 2009 [7]. It can be concluded that, the current flow simulation shows an excellent agreement with the experimental and computed data of Horiguchi et al. 2009 [7]. Fig.12 Flow coefficient versus head coefficient of the RP: comparison between the present transient simulations of the current work with that of the experimental and numerical works done by Ref. [7]." + ] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure23-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure23-1.png", + "caption": "Figure 23. Contours of air velocity vectors (m/s) inside the air-gap. (a) Velocity magnitude. (b) Radial velocity.", + "texts": [ + " Therefore, temperature discrimination as the result of this phenomenon is very small. It is obvious that a temperature increase occurs proceeding from the inner radius towards the running clearance outlet. This is due to the air heating in the clearance. Maximum temperature occurred in stator areas adjunct with the winding coils especially in the areas nearer to inner radius due to higher winding per volume. In the other words, the maximum heat transfer coefficient is that in the rotor, where the radius is smallest. Figure 23 shows the velocity (m/s) of the air inside the air-gap, motor\u2019s inlet and outlet for both velocity magnitude and radial velocity. The velocity vectors on the x = 0 plane in Fig. 23(a) show the prevailing axial flow at the inlet. On this plane, as opposed to the case of the x = 0 plane, after the bend in the radial direction the cooling air passes through the groove between the magnets and the velocity magnitude is greater. The radial velocity in the back clearance is higher than in the front one because of its smaller size (Fig. 23(b)). A negative radial velocity region is visible at the front rotor inlet where the air intake occurs. Fig. 24 shows the colored path lines on rotor and permanent magnets showing a circulation. It\u2019s the result of low velocities in the relevant inlet recess around the inner radius and vice versa higher velocities in the relevant outlet recess around the outer radius. The velocity magnitude contours have been obtained on the radial surfaces shown in Fig. 25 (at angles 34\u25e6, 0\u25e6 and +34\u25e6). The region of the running clearance close to the rotor shows higher velocities than the one close to the stator (see Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000226__Thesis_Redacted.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000226__Thesis_Redacted.pdf-Figure3-1.png", + "caption": "Figure 3 - Exploded view of simulated exoskeleton model.", + "texts": [ + "........................ 20 Bibliography ............................................................................................... 21-23 Appendix .................................................................................................... 24-34 vi Figure 1 - The 4 key stages of the STG technique. ........................................ 5 Figure 2 \u2013 Finite state machine that governs the operation of the exoskeleton. The four stages mimic the stages seen in the STG technique. .. 7 Figure 3 - Exploded view of simulated exoskeleton model. ............................ 8 Figure 4 - Side by side comparison of simulation and experimental models. . 9 Figure 5 - The Emergency control state machine that takes effect once the sensors detect a fall event. The state machine attempts to correct the trajectory of the body and avoid the fall. ....................................................... 11 Figure 6 - The application of an external disturbance to the body that triggered the emergency control response", + " The purpose of the interface is to reliably test the controller during development and fine-tune it to represent the STG motion defined in the literature. The LabVIEW SoftMotion module, an interface module for LabVIEW and third-party software, supports this task by providing a method to interface SOLIDWORKS and LabVIEW, control the actuators, and read sensor data during the motion study. A 3D model that consists of four primary components is developed to simulate the motion. The components include: The torso and lower body as a single rigid structure, the arms, the crutches, and the ground. An exploded view of the model is shown in Figure 3. The simulated body seen in Figure 3 represents the anthropometry of the subject of the experimental model to ensure an accurate comparison. As such, the exoskeleton is modeled according to the data in Table II. 9 Actuators were placed on the shoulder and elbow joints to emulate the flexion and extension of the shoulder and triceps muscles. The joints were designed as pin joints as they provide the necessary motion required for the STG. These motors rotate the arm ahead of and behind the body and extend/retract the crutches. The SOLIDWORKS Motion Toolbox, a Multiphysics simulation tool, is used to simulate the designed model ambulating using the STG through the decision making of the state machine" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004293_6_2050-5736-3-S1-P82-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004293_6_2050-5736-3-S1-P82-Figure1-1.png", + "caption": "Figure 1 Sketch diagram", + "texts": [], + "surrounding_texts": [ + "Ultrasound and MRI imaging guiding system for Robotic assisted interventional procedures such as needle biopsy and FUS ablation have to be improved to allow a one stop shop multimodality image guidance. A specific holder which has the capability for connecting the application module of the interventional robotic system \u201cINNOMOTION\u201d (IBSmm, CZ) with SIEMENS wireless ultrasound probe (Acuson Freestyle) was designed and manufactured in order to achieve the desired function. The work is a subproject in FUTURA an EU FP7 funded project for the development of robotic assisted Ultrasound guided focused ultrasound." + ] + }, + { + "image_filename": "designv8_17_0003647_f_version_1577096875-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003647_f_version_1577096875-Figure2-1.png", + "caption": "Figure 2. Skeleton sketches used for the individual phalanges. The seven high-level parameters are used in these sketches to derive all dependent dimensions of the finger.", + "texts": [ + " Additionally, we incorporate distance, vibration and joint angle sensing into the system. Mechanical parts are realised using 3D-printing. In the remainder of this section we describe the interplay of mechanical scalability and electrical modularity and how these two central concepts are implemented in detail. For the mechanical structure of the fingers we created a single scalable CAD-model of the finger. It is based on a skeleton that contains all sketches for all important features of the finger, as can be seen in Figure 2. Based on this skeleton, the three individual parts for knuckle, proximal and distal phalanx are derived by referencing the sketches in the skeleton model. The skeleton can be parametrised using seven high-level parameters that can be set individually and independently of each other. These parameters define the width and height of the proximal interphalangeal (PIP) joint (PIPw and PIPh) as well as the lengths of the proximal, intermediate and distal phalanx (proximall , intermediatel and distall)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004255_cle_download_175_155-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004255_cle_download_175_155-Figure6-1.png", + "caption": "Figure 6 Assembly drawings of aircraft and pneumatic impeller", + "texts": [ + " After forming a single blade model, assemble the three blades to obtain the assembly model of the entire impeller of the pneumatic device (hereinafter referred to as the impeller), as shown in Figure 5. In order to avoid the collision between the lower fuselage of the aircraft and the impeller blades, and facilitate the release and retraction of the pneumatic device, the distance between the blade rotating wing tip and the lower fuselage is designed to be 300 mm. The assembly drawing is shown in Figure 6. According to the structural characteristics of the aircraft and the impeller, the triangular mesh of the unstructured mesh is used and locally refined. When dividing, the whole computing domain is divided into two parts: one part is the rotation domain, which is the rotating region of the impeller, and the mesh number is 470,000; the other part is the static region, which is excluding the pneumatic impeller all the area, the grid number is 2.8 million. The static domain and the rotating domain transfer the data between the grids through the interface, and the distribution after mesh division is shown in Figure 7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000754_40396_type_printable-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000754_40396_type_printable-Figure3-1.png", + "caption": "Fig 3. Schematic diagram of forces applied to valve.", + "texts": [ + "g002 where P1 is liquid surface pressure above the valve body; P2 is the liquid surface pressure below the valve body; \u03c1 represents the density of the liquid medium; g is the acceleration of gravity; V1 is the liquid velocity below the valve body; V2 is the liquid velocity above the valve body; z1 is the liquid surface height below the valve body; z2 is the liquid surface height above valve body; and Kr is the coefficient of resistance. The fluid resistance coefficient can be expressed as follows: Kr \u00bc DP rg \u00bc x V2 c 2g \u00f03\u00de where \u0394P is the difference in pressure; and \u03be is the local resistance factor. Considering the Westphalia phenomenon [1\u20134], the medium flow of valve clearance is expressed as follows: Qc \u00bc Apup Avuv \u00f04\u00de where Qc is the instantaneous flow of valve clearance. The value of \u03bcv is positive when the valve rises, and negative when the valve drops. Fig 3 depicts a schematic diagram of the forces acting on the valve, in consideration of the effects of inertia. The balance equation of the valve is expresses as follows: AvP1 \u00bc AvP2 \u00fe G\u00fe F0 \u00fe Ch\u00f0t\u00de \u00fema \u00f05\u00de doi:10.1371/journal.pone.0140396.g003 PLOSONE | DOI:10.1371/journal.pone.0140396 October 21, 2015 5 / 20 The mathematical model of valve movement can be deduced from Eqs (1)\u2013(5) as follows: m c h ::\u00f0t\u00deh\u00f0t\u00de2 \u00fe h\u00f0t\u00de3 \u00fe G\u00fe F0 c h\u00f0t\u00de2 \u00fe xrA2 vApup c\u00f0pdvsina\u00de2 _h\u00f0t\u00de xrA3 v 2c\u00f0pdvsina\u00de2 h\u00f0t\u00de_ 2 xrAvA 2 pu 2 p 2c\u00f0pdvsina\u00de2 \u00bc 0 \u00f06\u00de where m represents the valve quality; c is the spring stiffness; G represents gravity; F0 is the pre-load of the spring; \u03b1 is the angle between the axis and mating surface of the valve; dv is the diameter of the valve (see Fig 2)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003042_f_version_1666696010-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003042_f_version_1666696010-Figure2-1.png", + "caption": "Figure 2. Structure diagram of upright shallow rotary stubble clearing.", + "texts": [ + " The coverage of wheat stubble met the requirements of the performance test index of the no-tillage (less-tillage) planter in the Huang-Huai-Hai region in China. 2.2.1. Upright Shallow Rotary Stubble Cleaning In this test, the rotary tiller (IT225) was used. The limiting device on the cutter head enabled the two rotary tiller to be installed at 180\u25e6 and the cutter head diameter was Agriculture 2022, 12, 1728 4 of 14 200 mm. The rotary radius of the blade was 225 mm, the working width was 50 mm, and the blade thickness was 2 mm (Figure 2). The width of stubble clearing was 210 mm, and the stubble-clearing spacing between the two groups of tillers was 100 mm. The soil bin test was carried out by two arrangement modes of the blade, inward (Figure 2a) and outward (Figure 2b). During the test, the forward speed of the machine was 1.67 m/s, the depth of tillage was 50 mm, and the rotary speeds were 400, 500, 600, 700 and 800 rpm, respectively. The soil and straw throwing process was recorded by high-speed camera technology (the high-speed camera equipment was an industrial camera of OSG030-815UM) from the side and forward directions of the tiller and the best installation method was determined. Agriculture 2022, 12, 1728 4 of 14 In this test, the rotary tiller (IT225) was used. The limiting device on the cutter head enabled the two rotary tiller to be installed at 180\u00b0 and the cutter head diameter was 200 mm. The rotary radius of the blade was 225 mm, the working width was 50 mm, and the blade thickness was 2 mm (Figure 2). The width of stubble clearing was 210 mm, and the stubble-clearing spacing between the two groups of tillers was 100 mm. The soil bin test was carried out by two arrangement modes of the blade, inward (Figure 2a) and outward (Figure 2b). During the test, the forward speed of the machine was 1.67 m/s, the depth of tillage was 50 mm, and the rotary speeds were 400, 500, 600, 700 and 800 rpm, respectively. The soil and straw throwing process was recorded by high-speed camera technology (the high-speed ca era equip ent was an industrial ca era of OSG030-815U ) fro the side and for ard directions of the tiller and the best installation ethod as deter ined. Existing studies have shown that oblique rotary tillage can effectively reduce power consumption under specific conditions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001958_5_htmp-2016-0261_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001958_5_htmp-2016-0261_pdf-Figure1-1.png", + "caption": "Figure 1: Schematic diagram of T92/Super 304H dissimilar weld joints.", + "texts": [ + " *Corresponding author: Wang Shuo, Material Research Institute, State Key Laboratory of Efficient and Clean Coal-fired Utility Boilers (Harbin Boiler Company Limited), Harbin 150046, Heilongjiang Province, China, E-mail: 57626@163.com Wei Limin, Cheng Yi, Tan Shuping, Material Research Institute, State Key Laboratory of Efficient and Clean Coal-fired Utility Boilers (Harbin Boiler Company Limited), Harbin 150046, Heilongjiang Province, China T92 and Super 304H tubes were joined by gas tungsten arc welding using TP304H as filler metal. Figure 1 shows a schematic diagram of T92/Super 304H dissimilar weld joints. The chemical compositions of the two base metals and the filler metal are given in Table 1. All materials conform to the ASME standards. The welding parameters are shown in Table 2. The welded joints were subjected to post-weld heat treatment (PWHT) at 730\u2013760\u00b0C for 2 h to stabilize the austenitic phase and relieve residual stresses. After X-ray nondestructive testing, specimens were cut, machined and examined to test their mechanical and structural properties" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003898__Issue1-18_paper.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003898__Issue1-18_paper.pdf-Figure1-1.png", + "caption": "Fig. 1. Structure of tangential-rotary cutting pick", + "texts": [ + " It should be underlined that the new solutions of the underground exploitation machines and cutting heads assume using disc-type (Krauze, 2009c) and tangential-rotary picks (Bo\u0142oz, 2013). Cutting machines, particularly longwall and roadway shearers are exposed to more and more restrictive requirements due to their capacity, reliability, operational safety and personnel comfort. First of all, in order to assure proper machine operation, suitable cutting picks should be selected, including cutting pick holders. Standard tangential-rotary pick show in Fig. 1 is built of cone-shaped operational part, cylinder-shaped mandrel being holding part of the cutting pick and pick edge in form of sintered carbide insert. Shape and suitable mounting of the pick in the holder allows its free rotation what assures uniform pick wearing. The body and holding part are made of steel having high impact and abrasion resistance. Pick edge is made of various types of sintered car bides soldered to the pick body. Shape of the cutting pick described by linear and angular dimensions and properties of material used must satisfy definite requirements related with proper realization of the cutting process and its durability" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure9-1.png", + "caption": "Figure 9. An overview of the Elka1Q drone\u2014side view.", + "texts": [], + "surrounding_texts": [ + "The overall shape of the drone (as seen in Figures 8 and 9) is a compromise among the general assumptions (described in Section 1), size and weight of significant components (such as the battery pack), and smart usage of available materials. 2.3.1. Wings Typically, drone arms are made of carbon-fibre tubes because they are very stiff and lightweight at the same time. However, such a single tube could have a too big a diameter to fit into the drone\u2019s wing. Instead, we decided to use double 6 \u00d7 2 mm carbon-fibre flat bars as wing spars. Additionally, the space between them forms a convenient tunnel for electric wires. The wings are built of two matching full-balsa wood elements: a bottom and a top half, both CNC 3D milled and glued together. The leading and trailing edges of a wing are usually prone to accidental damage (especially a very thin trailing edge); therefore, both edges are reinforced with carbon-fibre 4\u00d7 1 mm flat bars. The carbon-fibre wing spars at the wingtips support the main motor holders (CNC milled from a 3mm-thick aluminium sheet). The two elements of the holders are screwed together to catch protruding wing spars tightly. Finally, the surface of the wing is covered by Oracover [32] film. The wing construction proves to be light and very durable. We could say it is a perfect balance between stiffness and elasticity. Initially, we chose a wing profile (an airfoil) optimized for high-speed flight: the P-51D tip (BL215) airfoil (see Figure 10). Generally speaking, high-speed airfoils have low drag, but, on the other hand, have a low lift coefficient, which results in a high stall speed, and that means the plane has to maintain high enough speed to stay airborne in a level flight. That should not be an issue if the pusher motor can accelerate the drone to that speed. Due to safety reasons, we decided to modify the original wings\u2014we made them much thicker (see Figure 11). Such a thick airfoil (thickness increased from 12% to 25% of the airfoil chord) gives us a much higher lift coefficient (resulting in a lower stall speed) at the cost of lowering the top speed. Nevertheless, lower stall speed means we could perform the in-flight experiments of switching between quadcopter and plane mode at lower (i.e., safer) speed, and we could do that in a less spacious airfield. The wing configuration used in the drone is called a \u201ctandem-wing\u201d or sometimes a \u201clifting-tail plane\u201d. Those names refer to the fact that the aft wing is not just a horizontal stabilizer, like in a classic \u201ctailplane\u201d configuration, but it contributes to the total lift force produced by the plane. It is a rare configuration due to possible stability and controllability issues [34,35]. Sometimes, quite the opposite statements can be found\u2014tandem-wing planes are easier to pilot because of safer stall behaviour [36]. However, there were at least a few successful tandem-wing planes, e.g., Quickie designed by Elbert Leander \u201cBurt\u201d Rutan (and later QAC Quickie Q2) [36,37] and the Proteus [38] built by Scaled Composites (Rutan\u2019s company). Another famous tandem-wing plane is the \u201cFlying Flea\u201d (French name: \u201cPou du Ciel\u201d), designed by Henri Mignet in 1933. A thorough study of many more historical and modern tandem-wing planes and UAVs, as well as their aerodynamic and stability studies, can be found in [34]. A wing that produces lift force also generates a downwash, i.e., the airflow direction behind the trailing edge of the wing is deflected down by the aerodynamic action of the wing. That phenomenon changes the effective Angle of Attack (AoA) of the rear wing in the tandem-wing configuration. Most tandem-wing planes have the front wing mounted lower than the rear wing to minimize the downwash effect of the front wing [34,35]. Additionally, it is recommended to set a higher AoA of the front wing than the aft wing\u2014such a wing setup affects the stall behaviour of the tandem-wing plane. The front wing with a higher AoA will stall first while the aft wing still produces lift force\u2014that situation will cause the plane to pitch down, increase the speed, and ultimately, end the front wing\u2019s stall (bring back its lift force) [36]. Following the suggestions, the front wing of the Elka1Q drone was mounted at ca. 4\u25e6 AoA and the aft wing at ca. 2\u25e6 AoA. Finally, there is at least one more critical aspect of every aircraft having wings: Centre of Gravity (CG, CoG). It is crucial to keep the longitudinal stability of an aircraft. We used a CG calculator from the eCalc toolset [30]. The results of the calculation are presented in Figure 12. 2.3.2. Fuselage The final fuselage design was based on a rigid PVC tube (100 mm diameter and 1 mm wall) and a lighter, but still solid plywood structure (Figures 15\u201317). The PVC tube acts similarly to a monocoque structure, eliminating the twisting about the longitudinal axis. The landing gear is non-retractable\u2014we made four fixed legs of 3 mm spring steel wire supported by pinewood blocks at the bottom of the fuselage. The overall structure of the wings and the fuselage proved to be very rigid and robust, surviving a few serious crash landings. The most significant disadvantage of such a compact construction is complicated maintenance of internal components, e.g., access to electronic boards, wires, and connectors." + ] + }, + { + "image_filename": "designv8_17_0000804_le_1878_context_etdr-Figure2.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000804_le_1878_context_etdr-Figure2.9-1.png", + "caption": "Figure 2.9 Location of tensile sample from tensile bar blanks (arrow indicates the surface analyzed).", + "texts": [ + " Then the molds were poured; from taping of the furnace to emptying the ladle took less than six and a half minutes. The castings were removed from the molds after they were cool to be handled. The tensile bar samples were taken from the middle of tensile rod castings. The rods were angle ground to separate them from the runner. The round blanks were then cut to 6-inch lengths by removing approximately two inches from the top of the bar and then turned on the CNC lathe. Metallography samples were taken from the outside bar near the runner (Figure 2.9). 14 The step bar was sectioned along each step using a horizontal, water-cooled bandsaw. A quarter inch slice was then taken approximately two inches from the ends of the twoinch-high step. The pieces were then further cut using a wet abrasive saw until the desired location was harvested in a mountable size (Figure 2.10) . 15 The bottom inch of each y-block was cut-off and used to turn one tensile bar. The metallography samples from the y-blocks were removed from the grip of the tensile bars after they were pulled" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000752_el-04725201_document-Figure2.18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000752_el-04725201_document-Figure2.18-1.png", + "caption": "FIGURE 2.18 : Photo de la r\u00e9alisation du gap (a) sans colle, (b) avec colle.", + "texts": [ + " Deux plaquettes de test comportant un gap sont r\u00e9alis\u00e9es (1 mm d\u2019\u00e9paisseur pour le filament Electrifi imprim\u00e9), l\u2019une avec un gap sans la colle conductrice et l\u2019autre avec un gap contenant la colle conductrice [109]. En effet, la diode est connect\u00e9e aux lignes \u00e0 l\u2019aide de la colle conductrice, il est donc int\u00e9ressant de voir si cette colle apporte des \u00e9l\u00e9ments parasites suppl\u00e9mentaires au gap. Cette mesure nous permet d\u2019observer l\u2019influence de la 60 2.4 - CONCEPTION DE LA RECTENNA pr\u00e9sence de la colle sur les param\u00e8tres S. La photo des r\u00e9alisations est montr\u00e9e sur la figure 2.18. Nous pouvons constater que le gap de la r\u00e9alisation en PLA et Electrifi poss\u00e8de une hauteur cons\u00e9quente (1 mm) par rapport aux hauteurs de gap sur des pistes de cuivre traditionnelles. L\u2019\u00e9paisseur de la colle conductrice appliqu\u00e9e sur le filament \u00e9lectrifi\u00e9 est difficile \u00e0 contr\u00f4ler. N\u00e9anmoins, pour toutes les r\u00e9alisations, nous avons essay\u00e9 de respecter une sur-\u00e9paisseur de 0,5 mm. Gap (sans colle) Gap (avec colle) La mesure est effectu\u00e9e \u00e0 l\u2019aide du PNA-X N5241A et les r\u00e9sultats des mesures des param\u00e8tres S (figure 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003783_article-file_2084844-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003783_article-file_2084844-Figure1-1.png", + "caption": "Figure 1. APC 15 inches x 4 inches propeller blade", + "texts": [ + " In this study, performance analysis is made by changing the number of propellers and the horizontal distance between these propellers. As stated in the previous section, there are 3 different methods for performance analysis and CFD method is applied in this analysis. The experimental method will also be added in future studies. The APC 15x4W propeller used in this study has 2 blades, fixed pitch angle, and 0.379 diameter. The operating range is between 1000-10000 rpm. The propeller is formed of thinthickness airfoil profile suitable for a low reynolds number as demonstrated in Figure 1. Also, the main parameters of the APC 15X4 propeller are indicated in Table 1. This study focuses on the performance analysis of the propellers using ANSYS FLUENT and their effects on each other depending on the horizontal distance and propellers number. The Multiple Reference Frame (MRF) model approach is selected to give the propeller rotation effect in flow analysis. The flow domain is divided into two domains: a stationary domain and a rotating domain. Rotating domain is created as a cylinder, completely enclosing the propeller and hub region" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003902_om_article_21697_pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003902_om_article_21697_pdf-Figure4-1.png", + "caption": "Fig. 4. Payload swing angle measuring device", + "texts": [ + " 1040 JOURNAL OF VIBROENGINEERING. JUNE 2021, VOLUME 23, ISSUE 4 In order to verify the established mathematical model can be applied to the Ship\u2019s Crane payload control research. For the measurement of the swaying angle, based on high precision potentiometer, building the payload swing angle measurement scheme. The swing angle measuring system is simple in structure, easy to install, and most importantly. The real-time measurement can be realized. The laboratory payload swing angle measuring device is shown in Fig. 4. Use WDD35-D1 precision conductive plastic potentiometer as potentiometer on an angle sensing device, the working principle is to add a stable voltage value across the sensor resistance. The movement of the brush on the elastic resistance of the guide rail will change the change of the measured resistance, such outputting the voltage value corresponding to the swing angle. The displacement of the brush is consistent with the measured displacement, and the output voltage value is linear with the displacement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003278_le_download_510_1021-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003278_le_download_510_1021-Figure3-1.png", + "caption": "Fig. 3. Sub-baric storage bin", + "texts": [ + " The AISI-316 SS is austenitic grade stainless steel and has good weldable and forming properties. It is resistant to both acid and alkali and has good corrosion-resistant properties. Non-contact parts like structure skid, fasteners etc. were fabricated from AISI304 SS. The storage bin was fabricated from FDA and 3A approved cold drawn AISI-316 SS. Sub-baric storage bin was designed and developed having cylindrical in geometry with conical shape at bottom side and flat circular plate on top side and has capacity of 500 kg to store food grains with hopper angle of 60\u00b0 as shown in Fig. 3. The physical properties of grains like grain pressures, packing behaviour and flow behaviour include the bulk density of the grain (W), the ratio of lateral to vertical pressure (k), the internal angle of friction (\u03d5) and the coefficient of friction of grain on the bin wall (\u03bc) were considered while designing the storage chamber. It has length, diameter and thickness of 1638, 750 and 4 mm, respectively. The four legs were fixed to the storage chamber with size of 1268 65 mm (L\u00d7D) to ensure smooth functioning and operation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure43-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure43-1.png", + "caption": "Figure 43 P-POD Mk. IV Back Plate", + "texts": [ + " In an effort to save mass, parts of the walls not near Page 59 mounting screws or other features were thinned but remained constant height with the rest of the part. Additionally, four standoffs were added to streamline the implementation of a gaseous purge system or the Power-On system. If either system is required, the part can simply be sent out and have mission specfic holes drilled into it. The amount of material removed was low, saving only 12 grams, but it did not increase the part\u2019s complexity an appreciable amount. The Back Plate following the changes is shown below in Figure 43. Additionally, an example of the purge interface is shown in Figure 44. The part was expected to lose little to no strengh with this Page 60 change, as no direct load path was altered and interfaces to other panels remained unchanged. In order to verify the prediction that the part retained its strength, an FEA was conducted under the Z-axis load case applied to the 4 spring plunger holes, which are the large holes shown in the corners of the figures above. All outer walls were considered fixed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002712__2_3_2_14-00528__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002712__2_3_2_14-00528__pdf-Figure1-1.png", + "caption": "Fig. 1 Schematic diagram of torque converter.", + "texts": [ + " Since the fundamental vibration frequency is half of the engine excitation frequency, these design methods are not applicable to the subharmonic vibration. Then, we performed modeling and numerical analysis to investigate the optimum design of the dynamic absorber to suppress the occurrence of the subharmonic vibration. The automatic transmission consists of a torque converter and a gear train. The torque converter is located between the engine and the gear train to transmit the torque induced by the engine to the gear train. The inside of the torque converter is filled with automatic transmission fluid (ATF). Figure 1 shows a schematic diagram of a torque converter. The torque converter consists of a pump impeller, a turbine runner and a stator. As the torque converter transmits torque through the fluid, the rotational speed of the turbine runner is slower than that of the pump impeller, which causes the inefficiency associated with torque converter. In order to overcome this disadvantage, a lock-up clutch, which connects the input and output sides through friction, is used. The piston is supported by springs called damper" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002593_9312710_09335981.pdf-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002593_9312710_09335981.pdf-Figure22-1.png", + "caption": "FIGURE 22. Ferrite permanent magnet flux density distribution.", + "texts": [ + " MPMA-SynRM PERMANENT MAGNET DEMAGNETIZATION ANALYSIS There are both IPM rotor and multilayer PMA-SynRM rotor structures in an MPMA-SynRM motor. When the maximum output current of the controller is 6 A and the internal power factor angle is 122 degrees when the rated operating temperature is 75\u25e6C, the working status of the permanent magnets of different rotors can be verified simultaneously under the excitation of the same stator current. Fig. 21 shows the magnetic density distribution of the Nd-Fe-B permanent magnet of the IPM rotor, and Fig. 22 shows the magnetic density distribution of the ferrite permanent magnet in the PMA-SynRM rotor. Fig. 21 shows that the Nd-Fe-B permanent magnet is still above the demagnetization point in the worst operating state of the motor. Fig. 22 shows that the proximity of the second layer of themultilayer ferrite to theNdFeB permanentmagnet in the axially adjacent IPM rotor is affected by it, so a small amount of demagnetization occurs at the axial edge of the permanent magnet at this position. However, its demagnetization range is extremely small, so it is not considered. IV. PERFORMANCE COMPARISON WITH IPM AND PMA-SynRM A. ANALYSIS AND COMPARISON To verify the improvement of motor performance, the performances of IPM, PMA-SynRM, and MPMA-SynRMare are compared under the condition of ensuring the basic size" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004897_f_version_1684752473-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004897_f_version_1684752473-Figure12-1.png", + "caption": "Figure 12. Stress contour map of composite tape spring laminate ply.", + "texts": [ + " This application ensur d that the model be t into a U-shape, which is consistent with the actual working state of the space unfolding mechanism. The parameters used in the analysis are given in Tables 1 and 2, the bo dary conditions are shown in Table 6. an the ply angles are shown in Figure 10. Figur 11 presents the FEM model in detail. Figure 10. Laminate ply angle. Figure 11. Finite element model. Table 6. Boundary conditions. Location Boundary Conditions Centroid of the cross-section A U1 = U2 = UR2 = UR3 = 0, UR1 = 1.57 Centroid f the cross-section B U1 = U2= U2 = UR2 = UR3 = 0, UR1 = \u22121.57 Figure 11. Finite element model. Figure 12 shows the stress contour plot of the composite tape spring after folding and bending. The figure shows that the stress distribution is similar to a rectangle, and the middle part of the cylindrical shell becomes flat, which is in line with the variation of cross-sectional curvature in the theoretical model. The maximum stress values for the four layers are 214.0 Mpa, 145.8 Mpa, 153.7 Mpa, and 238.8 Mpa, respectively. The maximum stress value occurs in the fourth layer, and the stress values \u03c31, \u03c32, and \u03c412 in the principal axis direction of the material at the node with the maximum stress value of \u2212255 Mpa, \u221230.9 Mpa, and \u221213.6 Mpa are extracted. The material strength parameters are shown in Table 7. Calculations are performed based on the Tsai\u2013Hill failure criteria. Appl. Sci. 2023, 13, 6315 12 of 14 \u03c32 1 X2 + \u03c32 2 Y2 + \u03c42 12 S2 \u2212 \u03c31\u03c32 X2 = ( 255 1272 )2 + ( 30.9 146 )2 + ( 13.6 57 )2 \u2212 255 \u00d7 30.9 12722 = 0.137 < 1 (25) Appl. Sci. 2023, 13, x FOR PEER REVIEW 14 of 16 Figure 12 shows the stress contour plot of the composite tape spring after folding and bending. The figure shows that the stress distribution is similar to a rectangle, and the middle part of the cylindrical shell becomes flat, which is in line with the variation of cross-sectional curvature in the theoretical model. The maximum stress values for the four layers are 214.0 MPa, 145.8 MPa, 153.7 MPa, and 238.8 MPa, respectively. The maximum stress value occurs in the fourth layer, and the stress values \u03c31, \u03c32, and \u03c412 in the principal axis direction of the material at the node with the maximum stress value of \u2212255 Mpa, \u221230.9 Mpa, and \u221213.6 Mpa are extracted. The material strength parameters are shown in Table 7. Calculations are performed based on the Tsai\u2013Hill failure criteria. 2 2 22 2 2 1 2 12 1 2 2 2 2 2 2 255 30.9 13.6 255 30.9 0.137 1 1272 146 57 1272 \u03c3 \u03c3 \u03c4 \u03c3 \u03c3 \u00d7 + + \u2212 = + + \u2212 = < X Y S X (25) The material is within the allowable range. Figure 12. Stress contour map of composite tape spring laminate ply. Table 7. Material strength parameters [23]. Property Value (MPa) Fiber tensile strength (Xt) 2390 Fiber compressive strength (Xc) 1272 Matrix tensile strength (Yt) 50 Matrix compressive strength (Yt) 146 Shear strength of the unidirectional ply (S) 57 4. Conclusions This paper analyzes the mechanical properties of composite laminated tape springs and analyzes and calculates the mechanical characteristics of the folding and bending process of composite laminated open-shell springs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure4-1.png", + "caption": "Fig. 4a Computational domain for RP Fig. 4b Casing of RP", + "texts": [ + "0 is used to perform 3D unsteady simulation for the flow analysis of the described RP. The Reynolds Averaged Naiver-Stokes equation (RANS) combined with the Sheer Stress Transport (SST) turbulence model are employed, as recommended by [7]. The Reynolds number, defined based on the diameter of impeller DT and the tip speed UT, is about 2\u00d7105. To keep the fine meshes near-wall capable of resolving the viscous sub-layer, y+ is kept in the range of 30~300 to comply with the log-law [25]. The computational domain is divided into three main parts as illustrated in Fig. 4a. The first one is the casing domain which contains the fluid flow around the impeller and surrounded by the external walls of casing body, the second and the third ones are the inlet pipe flow domain and the outlet pipe flow domain, respectively. In the casing flow part, the domain is divided into two parts as well, as shown in Fig. 4b; the dynamic layer domain, that represents the fluid layer rotating between walls of the impeller and fluid layer just above the impeller body; Fig. 5a and the static domain, which represents the remained part located between the casing body of the pump and the dynamic flow layer above the impeller, Fig. 5b. The lengths of the inlet and outlet pipes are about 11.1 and 13.5 times the casing diameter, respectively similar as in [7]. The centerline of the inlet pipe and outlet pipe are at angles of - 28" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002838_f_version_1679473059-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002838_f_version_1679473059-Figure4-1.png", + "caption": "Figure 4. Constraints of the addendum circle and dedendum circle of the external gear: (a) intersection; (b) meshing boundary point.", + "texts": [ + " In the transmission process of the gear pair, it is necessary to ensure that there is no interference collision between the addendum of the external gear and the dedendum of the internal gear ring or between the dedendum of the external gear and the addendum of the internal gear ring. The following relationships must be satisfied:{ ra1 + e \u2264 r f 2 r f 1 + e \u2264 ra2 (21) Substituting the relationships between the design parameters in Table 2 into Equation (21), the following can be obtained: { h\u2217a1 \u2264 h\u2217f 2 h\u2217f 1 \u2265 h\u2217a2 (22) As shown in Figure 4a, tooth profiles on both sides of a single external gear tooth must have an intersection E, and linear tooth profiles of two adjacent gear teeth must have an intersection F. If the tooth profiles exceed this limit position, the design will fail. According to the geometric relationship, the radius of the circle corresponding to the intersection can be written: rE = h sin \u03b2 (23) rF = h sin(\u03b2 + \u03c0/z1) (24) where h is the vertical distance between the center of the external gear O1 and the linear tooth profile on one side, which can be expressed as follows: h = r1 sin(\u03b8/2 + \u03b2) (25) As shown in Figure 4b, there is a meshing boundary point on the linear tooth profile of the external gear. According to the meshing principle, the intersection between the normal line of any meshing point G on the tooth profile and the pitch circle is the pitch point P. As the external gear rotates counterclockwise around center point O1, the meshing point G moves to the addendum of the tooth along the tooth profile, and the node P moves to the left along the pitch circle. When the normal line of the tooth profile and the pitch circle are tangent to the point P\u2032, the meshing point G\u2032 is the meshing boundary point" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001456_18_ms-9-327-2018.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001456_18_ms-9-327-2018.pdf-Figure6-1.png", + "caption": "Figure 6. Structure of the compliant wiper mechanism.", + "texts": [ + " In this section, we determine the dimensions of the compliant wiper mechanism by using a rigid-body-replacement synthesis technique (Howell, 2001). Numerous different compliant mechanisms can be designed from a single rigid body mechanism. However, in order to obtain a high oscillating output (wiper arm) with relatively low stresses, we preferred a \u201clong simple compliant segment\u201d (Figs. 1 and 6) for the compliant link, rather than a small length flexural compliant segment. The mechanism is displayed in a simplified form in Fig. 6. The mechanism is a partially compliant mechanism with two rigid links and one compliant link (link 3). There are three rigid segments and one simple compliant segment. Link 1 in Fig. 6 is the fixed link and link 2 is the crank, i.e., the input link of the mechanism, and performs a full rotation. Link 3 is the compliant link, formed from one rigid segment and one compliant segment, and it is the output link of the mechanism. The wiper blade is attached to the rigid segment of this link. There are three kinematic pairs (revolute joints) available in the mechanism. The compliant segment of the output link is connected to the ground by a revolute joint, where the moment is not available as a reaction force, and the other part of this segment is fixed to the rigid segment of link 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000609_e_download_7074_1095-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000609_e_download_7074_1095-Figure6-1.png", + "caption": "Fig. 6 Dynamic model for spur gear", + "texts": [ + " The product of dynamic load factor and location-based geometric factor determines the safe load-bearing ability of a gear, referring to Eq. (28). The product of dynamic load factor and specific sliding is the deciding factor for accumulated wear depths over n cycles, referring to Eq. (32). Hence the determination of dynamic load factors is critical in the analysis of any gearing system. To evaluate dynamic load factors for TSAAG, a gear pair in mesh is modeled as two rigid disks connected by a spring-damper set along the pressure line (refer to Fig. 6). The single Degree of Freedom (DOF) dynamic model considers the influence of mesh stiffness, damping forces \ud835\udc39\ud835\udc50, friction forces, static transmission error at the mesh interface, and are expressed as a time-varying function. The gear pairs are assumed to be of unit face width and free of tooth profile errors. The differential equations of motion (EOM) for a single DOF spring mass damper system can be expressed as eq r eq r eq rm x c x k x F (36) 1 2 1 2 e e eq e e m m m m m (37) Proceedings of Engineering and Technology Innovation, vol" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000403_citation-pdf-url_382-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000403_citation-pdf-url_382-Figure1-1.png", + "caption": "Figure 1. One of the TAU Robot Configurations", + "texts": [ + " The fully parallel-driven manipulators such as Stewart-platform have been investigated by many researchers. In general, the workspace of a robot arm consisting of only parallel kinematic chains is relatively small. Currently, there has been an increasing interest in the design of hybrid or serial-parallel robot manipulators which can provide salient features of both serial and parallel kinematic chains. An appropriately designed hybrid robotic manipulator will have a large loadcarrying capacity and workspace, and yet be comparatively small and lightweight. The TAU parallel configuration (Figure 1) is rooted in a series of inventions and was masterminded by Torgny Brogardh, 2000; 2001; 2002. The configura- tion of the robot simulates the shape of \u201c\u03c4\u201d like the name of the Delta robot named after the \u201c\u2207\u201d shape configuration of the parallel robot. As shown in Fig. 1.1, the basic TAU configuration consists of three driving axes, three arms, six linkages, 12 joints and a moving (tool) plate. There are six chains connecting the main column to the end-effector in the TAU configuration. The TAU robot is a typical 3/2/1 configuration, which configuration is shown in Figure 11 of Section 2. There are three parallel and identical links and another two parallel and identical links. Six chains will be used to derive all kinematic equations. Table 1 highlights the features of the TAU configuration", + " In order to further enlarge the size of the workspace, the addition of a revolute joint at the fixed base has been envisaged, introducing kinematic redundancy into the robotic manipulator. Its translational part can be thought as a reduced Stewart Error Modeling and Accuracy of Parallel Industrial Robots 579 platform with only three limbs. Like the Stewart platform, its kinematics has not been completely obtained: the inverse kinematics problem admits an analytical solution whereas the direct kinematics problem may require the use of iterative algorithms (Siciliano, 1999). Error Modeling and Accuracy of Parallel Industrial Robots 581 Octahedral Hexapod as shown in Fig. 1.6 is a demonstration machining center with six DOFs. It is a small, portable machine based on an octahedral framework. Machine motion is achieved by a Stewart Platform style actuation system. The framework and machining system can achieve high overall stiffness due to the fact that the structural members are generally in tension or compression with a minimum amount of bending stress. This structure allows the machine's capabilities to be independent of its foundation. Six identical struts with spherical pivots are mounted to the framework to drive the machining spindle, providing six-axis machining capability" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure29-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure29-1.png", + "caption": "Figure 29 Power-On Access Port FEM", + "texts": [ + " A conservative load case was used, assuming the entire load of the connector spring was placed on the access port half that it was mounted too. Additionally, the spring was assumed to be compressed twice as much as expected, a total of 0.5\u201d, which would produce a force of 14 lbf. Added to the plate was a 100 g gravity load in the Z-axis, which is higher then any qualification load the P-POD would see. The access port cover was fixed at its mounting holes, but the supporting spar from the second access port spar was ignored to get a worst case load scenario. The FEM analyzed showing constraints and loads is shown below in Figure 29, with Deflection and Stress plots shown in Figure 30. Maximum deflection for the specified load case was 0.004 inches, as shown. The maximum stress was seen on the ribs near the mounting holes, and was calculated to be 5616 psi. It is necessary that the Margin of Safety be calculated for Page 43 clarity. Margin of safety is calculated as shown in \ud835\udc74\ud835\udc7a = \ud835\udc7a\ud835\udc82 \ud835\udc7a \u2212 \ud835\udfcf Equation 2. \ud835\udc74\ud835\udc7a = \ud835\udc7a\ud835\udc82 \ud835\udc7a \u2212 \ud835\udfcf Equation 2 In this case, \ud835\udc46\ud835\udc4e is the material allowable stress, or yield stress when doing yield analysis, and \ud835\udc46 is the stress seen from the applied load" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-Figure2.15-1.png", + "caption": "Figure 2.15: Lightweight four-seater monoplane (19)", + "texts": [ + " To demonstrate the application of MATLAB/Simulink in aerospace industry, the MathWorks included some complete models in the MATLAB package. There were two models which served as the basic for the simulation model developed in this project: 1903 Wright Flyer and Pilot with Scopes for Data Visualization and Lightweight Airplane Design (19).The Chapter 2: Previous work on MAV development 14 model of the Wright brothers\u2019 airplane is shown in Figure 2.14. It was modeled as a 3-DOF object with the only control surface is the elevator. The lightweight four-seater monoplane in Figure 2.15 was also modeled as a 3-DOF object as shown in Figure 2.16. However, more details were added to this model compared to the previous one. Three control surfaces and the engine also presented in the model. Instruments\u2019 noise and environment\u2019s disturbance were simulated, too. Other lateraldirectional parameters were included to make it a 6-DOF model. This really helps model builders to get a basic understanding of all the required components in a complete aircraft model. Chapter 2: Previous work on MAV development 15 MATLAB/Simulink is widely used by MAV developers" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure12-1.png", + "caption": "Fig. 12 The Equivalent stress on the i side of the spiroid worm drive.", + "texts": [ + " 10 2 \u00a9 2023 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2023jamdsm0073] A fixed constraint was set on the inner cylindrical wall of the worm gear and the cylindrical support is applied to the pinion cylinder, and the tangential direction was kept free. Finally, a torque of 100N\u00b7m was set on the pinion cylinder, as shown in the picture below: After the above Settings are completed, the equivalent stress and contact state of the wormwheel and pinion are calculated and results are shown in the following figures. 11 According to Fig. 12 and Fig. 13, when \u03b4=5\u00b0, the maximum equivalent stress on i surface and e surface of pinion is 614Mpa and 588Mpa respectively. The equivalent maximum stress on i surface of the wormwheel is 948Mpa and e surface is 595Mpa. According to the simulation results of sress, it is easy to observe that the equivalent stress on the iside is larger than that on the e-side, which is consistent with the analysis results of the induction method curvature in chapter 3. Figure 15 and Figure 16 illustrate the case when \u03b4=0, the maximum stress on i surfece and e surface of pinion is 426Mpa and 384Mpa respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000086_cle_4164_context_etd-Figure5.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000086_cle_4164_context_etd-Figure5.2-1.png", + "caption": "Figure 5.2.1-2: Illustration of the Problem Associated with Finding the Slot Depth and Number of Turns", + "texts": [ + " Since the MATLAB optimization command is written to minimize the objective function, and part of the desire is to maximize the system conversion efficiency, the efficiency portion of the objective function must be defined as the reciprocal of efficiency as shown in equation 5.2.1-1. This part of the objective function directs the optimization routine to maximize the efficiency. efficiency FUNCTIONOBJECTIVE 1= (5.2.1-1) The system efficiency is determined by finding the ratio of the output power to the input power. In this situation, the input power is considered the power delivered to the alternator, so the efficiency of the engine is not considered. Therefore, the input power can be found by adding the core and copper losses to the electrical output power. Figure 5.2.1-1 illustrates the power flow diagram used in this calculation. The core losses are found from data supplied by the manufacturer. This data gives core loss values for a range of induction and is developed for excitation at 60 Hz. Therefore, a correction factor is needed to use this information at frequencies other than 60 Hz. In [6], the core loss is shown to be proportional to the frequency of 59 excitation. Consequently, the core loss at an arbitrary frequency, fa, can be found by determining the core loss at 60 Hz at the simulated level of induction from the supplied data and applying the correction as shown in equation 5", + " Therefore, the slot depth of the alternator is not used as an optimization variable. Instead, the slot depth is calculated such that the number of windings necessary to provide the desired voltage and power will fit in the slot area. A problem arises when finding the slot depth in that the number of windings is not known until the flux linkage is calculated. However, the flux linkage cannot accurately be determined until the slot depth is known due to the changes in reluctance as the slot depth varies. Figure 5.2.1-2 illustrates this problem. To solve this problem, an iterative technique similar to that used in the simulation routine is necessary. The optimization function begins by providing a guess for the number of turns, N, equal to the number of turns found in the previous optimization step. In the case of the first optimization step, the guess is provided by the user as part of the initial machine parameters. The slot depth is then calculated so the turns will fit into the slot area, taking into account the packing fraction of the particular wire size selected", + " ratedwindingemf desired oldnew IRV VNN \u2212 = (5.2.1-5) where Vemf is the internally generated voltage Rwinding is the winding resistance Once again, the differences between the new number of turns and the previous number of turns as well as the differences between the desired output voltage and power and the simulated output voltage and power are compared. If any of the 64 differences exceeds a predefined threshold, the process is repeated until the differences fall below the desired threshold. Figure 5.2.1-3 illustrates the flow chart of the optimization function. Once this iterative process is complete, the final system with the final number of turns is simulated. The output power and loss power are then calculated so the 65 efficiency can be evaluated and returned to the CONSTR function. For the optimization steps, the simplified finite element technique is used to determine the machine flux. Although this model does sacrifice some accuracy, the savings in computation time far outweighs the slightly reduced accuracy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001062_125_3_125_3_293__pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001062_125_3_125_3_293__pdf-Figure5-1.png", + "caption": "Fig. 5. Magnetic flux density distribution of the usual reset switch (magnetomotive force is 363 A).", + "texts": [ + " When the coil is excited so that the magnetic flux can flow in reverse and the attractive force decreases until it is less than the reset force of the spring, the armature is lifted upward and the switch is turned off. Figure 3 shows the finite element meshes used in this study. Figure 4 shows the attractive force characteristics by varying the magnetomotive force from 0 to 363 A. The computed results are entirely in good agreement with the measured ones, though they are pretty different at the magnetomotive force of 90 and 363 A because of errors in measurement. Figure 5 shows the magnetic flux density distributions when the magnetomotive force is 363 A. As shown in Figure 4, the attractive force of 5.2 N is quite large when the magnetomotive force is 0 A, but does not decrease to a value zero even if the large magnetomotive force of more than 350 A is supplied. This occurs because the magnetic flux excited by the current flows through the permanent magnet, where the magnetic resistance is quite large. Consequently, it becomes very important to design an efficient magnetic path for the magnetic flux excited by the current" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003855_le_1117_context_etdr-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003855_le_1117_context_etdr-Figure2-1.png", + "caption": "Figure 2 Series-Parallel Hybrid Drive System", + "texts": [ + " The secondary electric motor (MG1) is responsible to act as generator which transfer the power from the ICE to recharge battery and also acts as a power source to supply MG2 which assists in propulsion of vehicle [5]. 4 HEV\u2019s series-parallel combination of electric drive is powered by a battery and a mechanical drive using the legacy ICE engine powered by fuel. The wheels can be driven by ICE engine and electric traction motor. Both systems are connected to the drive shaft of the vehicle, as shown graphically in Figure 2. Both electrical machine and the engine are responsible for producing separate powers that are Ptm and Pice, respectively [6]. The required power produced by the ICE is through the combustion of fuel as the source of power. For the traction motor, the source of power is the battery. The main idea here is to use electrical drive as long as possible, before the ICE must be used for longer journey, as required, to minimize use of fuel as much as possible. This concept requires the vehicle to use as big a battery as possible" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000882_article-file_1157957-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000882_article-file_1157957-Figure5-1.png", + "caption": "Fig. 5. Force couple on the branch of the weld yoke", + "texts": [ + " While the critical cross section of the weld yoke is shown in Fig. 4, the critical dimensions on the cross section are given in table 1. In addition to keeping the max. stress on the critical section under control, the material selection for weld yoke is another key factor. The properties belonging to steel of C45 grade that is selected for the weld yoke, is shown in Table 2 below. Maximum force on the branch of the weld yoke, Considering the weld yoke on the driveshaft alone, force couple produced by the torque acting on it, is shown in Fig. 5 below. For the maximum torque value of 4,600 which acts on the weld yoke, the maximum force on the branch of the weld yoke, shown in Fig. 5, can be calculated by fallowing equation. \ud835\udc47 = \ud835\udc39\ud835\udc4f . \ud835\udc37 = \ud835\udc39\ud835\udc4f . 2\ud835\udc45 (1) \ud835\udc39\ud835\udc4f= 49.89 N where \u201cT\u201d is the maximum torque acting on the weld yoke, \u201cFb\u201c is the force on one branch of the weld yoke and D is the distance of the force action points on the each branch of the weld yoke, and \u201cR\u201d is the effective radius. The force on the branch, calculated above causes bending and shearing on the critical section. To calculate the bending stress on the critical section, respectively bending moment, and moment of inertia according to critical section, can be determined in following form" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure3.16-1.png", + "caption": "Figure 3.16: New Vane Design in Cylinder-Rotor Assembly", + "texts": [ + " 42 From the experiment, bearing grade PEEK exhibits better performance at high rotation speeds and load conditions with lower coefficient of friction compared to that of PTFE. In addition, the severe wear characteristic of PTFE as seen in Figure 3.14 shows that it is unsuitable for such application. In conclusion, PEEK shall be chosen as the material of choice for the fabrication of the components that undergo dry friction. With the proposal of the new vane design and selection of PEEK as the self-lubricating material for the compressor prototype, this section will now go into the design of the prototype. The exposed cylinder-rotor assembly can be found in Figure 3.16 to show the implementation of the proposed vane design. The thermodynamics of the chambers shall be discussed in detail in Chapter 5. Due to the unique characteristic of the eccentric rotor rotation in a rotating cylinder, the bearing layout for the revolving vane mechanism would be similar to that as proposed by Teh and Ooi [21] in which the cylinder is supported on both ends with the rotor supported on one end as shown by the cross-section layout in Figure 3.9. There is a cylinder cover that acts as the second bearing support for the cylinder" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002146_11044-013-9375-6.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002146_11044-013-9375-6.pdf-Figure2-1.png", + "caption": "Fig. 2 Different scenarios for the supporting foot contact with the ground and the assumed external reactions", + "texts": [ + " As it will be seen further, neither the constraint equations (p) = 0 nor constraint Jacobian C need to be introduced explicitly in the followed formulation. The modeling effort is therefore limited to the formulation of fr and fu. 2.2 Reactions from the ground The triple jump is composed of consecutive flying phases, when there is no contact with the ground, and single-support phases, when the jumper touches the runway with one of his feet (the final, not analyzed in this study landing in the sand pit is usually on two feet). The external reaction exerted on a supporting foot can be reduced to point P (Fig. 2), and modeled by means of lr = 3 components \u03bbr = [Rx Ry MP ]T irrespective of the possible contact scenarios, where Rx and Ry are the X and Y components of the reaction force, and MP is the reaction force moment about point P of the foot segment. During the flying phases \u03bbr is expected to vanish, which may be a criterion of validity of the developed dynamical model and accuracy of the recorded kinematic characteristics. The generalized force vector fr introduced in Eq. (1) can symbolically be represented as fr = Ar (p)\u03bbr (2) where the n \u00d7 lr (42 \u00d7 3) matrix Ar of distribution of \u03bbr in p directions has nonzero entries only in the rows corresponding to the supporting foot absolute coordinates", + "1 Anthropometric data and musculoskeletal geometry For the developed jumper model, the anthropometric data used in the inverse dynamics simulation of triple jump are: the lengths li of the segments, locations \u03beCi and \u03b7Ci of their mass centers in the local coordinate frames, and their masses mi and mass moments of inertia JCi with respect to Ci , i = 1, . . . , b. The locations of the shoulder and hip joints in the local reference frames of segments 2 and 4 (Fig. 1), and the distance from the ankle joint A to point P (Fig. 2), are also required. The lengths and the body mass can be measured directly from the subject. The segment masses and the mass center locations must then be estimated using the regression equations reported in, e.g., [32, 34\u201336], which is concerned with a series of additional measurements of characteristic circumferences and segment lengths of the subject body. In addition, the lower limb musculoskeletal model (Fig. 3) requires estimating the cross-sectional areas Aj of the specified muscles, and then the actual origin and insertion point locations in the local reference frames of appropriate segments" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000171_pdf_64FFEE170012.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000171_pdf_64FFEE170012.pdf-Figure4-1.png", + "caption": "Figure 4. Technical drawing for the vertical spikes shelling mechanism. Source: Author", + "texts": [ + "5, respectively (Hassan et al., 2009). The allowed bending stress (\u03b3d), and safety factor (SF) for the shaft with keyways were 40 Nm.m -2 and 1.5 respectively (Hassan et al., 2009). The shaft diameter was calculated to be 24 mm from Equation 16 (Olaoye and Adekanye, 2018). The standard available shaft size of 25 mm diameter was selected for this study based on the power calculations above. The spikes were then welded on the shelling shaft. The detailed drawing of the shelling shaft can be seen in Figure 4. dshaft= ( 16 \u03c0\u03c4d ((KbMmax)2+(KtMt) 2) 0.5 ) 1 3 ) \u00d7SF (16) Where dshaft=diameter of the shelling shaft (m); kb = combine shock and fatigue factor applied in bending moment; kt= combine shock and fatigue factor applied on torsional moment, Mmax= resultants bending moments (Nm), Mt = maximum torsional moment(Nm), \u03b3 d = allowable stress for steel shaft , and FS =safety factor. The shaft and the driven pulley were connected by a rectangular sunk key. The width and thickness of keys were calculated to be 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001089_ff397de6de9d42fe.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001089_ff397de6de9d42fe.pdf-Figure10-1.png", + "caption": "Figure 10. (a) Cranck slider mechanism. (b) Tubular linear permanent-magnet generator test rig.", + "texts": [ + " However, when the size of the magnet obtained from MOGA results was considered, it was di cult to produce magnets, speci cally. Thus, generator geometry was established based on the initial design geometry data. The distribution of the magnetic ux density on the length of the generator in ANSYS Maxwell 2D rz can be seen in Figure 8. The images of crank slider mechanism are given in Figure 9(a), (b), and (c). M43-24G geometry and magnetic rotor piece with iron sheet for the prototype are given in Figure 9(d) and (e). The prototype machine can be seen in Figure 10, which is fabricated based on the initial design. In Figure 10, the generator is driven by the crank slider mechanism (Figures 9(b) and 10(b)) proper to a 4-pole asynchronous motor. The results of the numerical analysis were compared with the testing prototype (unloaded) for 20 Hz driving frequency (Figure 11). Here, speed was calculated according to the crank sizes given. It was found that the results of the numerical analysis by ANSYS Maxwell and those of the application were in parallel to a great extent. In the experimental study, nominal working speed and frequency values were not reached due to mechanic vibration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003900_e_download_4701_4052-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003900_e_download_4701_4052-Figure13-1.png", + "caption": "Fig 13 Helicoidal antenna normal mode. a) front view, b) top view, c) profile view.", + "texts": [ + " 25614 Carlos Soria Ijecs Volume 11 Issue 11 November 2022 [Page -25612-25619] The parametric analysis for the number of turns is performed with the optimized parameters of diameter (12mm), separation between turns (4mm) and distance from the helix to the ground plane (2mm) and conductor diameter (0.55mm). Simulations are carried out from 2 to 20 turns. Figure 12 shows the results obtained. Fig 12 (a) Parameter S11 for different number of turns. Fig 12 (b) Radiation pattern in polar form for different number of turns. different parameters of the helix, trying to optimize its structure, with the aim of determining the best geometric configuration as well as the effects that occur in the radiation pattern, gain and coupling. The dimensions of the miniaturized proposed antenna (figure 13) are shown in table II. Table Ii. Dimensions Of The Miniaturized Helical Antenna Frequency F(MHz) 915 Wavelength (cm) 32.78 Spacing S(cm) 0.4 Diameter D(cm) 1.2 Length L(cm) 1 Ground plane diameter Dpt(cm) 1.5 In table III a comparison is made between the dimensions of the designed antenna and the miniaturized optimized antenna. It is observed that it was reduced from an antenna of 32.78cm high by 8cm wide to a miniaturized antenna of 1cm high by 1.5 wide. Losing less than 1dB of gain and obtaining the desired radiation pattern in the form of a dipole" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure4-1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure4-1-1.png", + "caption": "Figure 4-1: Infinite num ber of trajectories satisfying given constraints.", + "texts": [ + " Initial and final states consist of joint configuration and velocity which are denoted as 0i(to), &i(t0) and 0i(tf), 0i{tf). A ctuator torque is considered as a function of joint variables; i.e., displacements and velocities. The torques are denoted as T{(0,0) and Tjmjn(0 ,0) < T{ < Timax(0,0), where 0 and 0 are column vectors and Timt\u201e and Timax are lower and upper bounds of the zth joint torque. There are an infinite num ber of feasible trajectories w ith various t f between two states satisfying those actuator torque constraints (Fig. 4-1.a). Since it is required to m ap the various t f to a fixed value in order to include every feasible tra jectory in a certain boundary, tim e t is normalized into a param eter r so th a t every final tim e t f is m apped to 1 while the initial tim e t0 is m apped to 0 (Fig. 4-1.b). To solve this problem, Bang-Bang control theory is adopted such th a t the m ax im um control function is applied initially to each joint and the m inim um control function is applied after the switching time. After a brief review of the property of a param etric cubic spline curve, the m ethod of obtaining the optim al 0i(t), the 8 6 elapsed tim e (tf \u2014 t0 ) 5 and the switching tim e will be discussed. 4 .3 P aram etric C ubic S p line 4 .3 .1 F orm u lation o f a P aram etric C ubic Sp line Any joint trajectory, 9(t) w ith arb itrary tim e dependence can be approxim ated by a series of param etric cubic spline segments with a normalized tim e param eter Tg(cr) for each segment" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003809_el-03253472_document-Figure4.7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003809_el-03253472_document-Figure4.7-1.png", + "caption": "Figure 4.7 : Vue 3D de la maquette mod\u00e9lis\u00e9e : support seul (a) et prototype complet avec les connecteurs (b)", + "texts": [ + " La permittivit\u00e9 relative du prepreg que nous avons utilis\u00e9 pour la mod\u00e9lisation est \u00e9galement une valeur approch\u00e9e, de par la structure de nature h\u00e9t\u00e9rog\u00e8ne, elle a \u00e9t\u00e9 estim\u00e9e par le fabricant \u00e0 2.42. Plusieurs types de vias sont utilis\u00e9s : des vias traversants utilis\u00e9s au bout des stubs ou spirales (Microvia Laser Type II sur la Figure 4.6), et des vias servant de contact \u00e9lectrique entre la ligne et la capacit\u00e9 MIM (Microvia Laser Type I sur la Figure 4.6). Afin d\u2019\u00e9viter toute d\u00e9formation des prototypes \u00e0 cause des mesures, nous avons \u00e9galement fait fabriquer des supports illustr\u00e9s Figure 4.7, qui ont \u00e9galement permis de fixer les connecteurs SMA (Radiall) n\u00e9cessaires \u00e0 la caract\u00e9risation des prototypes. Les prototypes sont fix\u00e9s au support \u00e0 l\u2019aide de quatre vis en nylon. Les simulations des diff\u00e9rents prototypes ont \u00e9t\u00e9 effectu\u00e9es en prenant en compte les tol\u00e9rances donn\u00e9es par le fabricant et en mod\u00e9lisant des dispositifs les plus proches possibles des prototypes \u00e0 r\u00e9aliser, tels que les trous n\u00e9cessaires aux vis de fixage. APPLICATION DE LA METHODE A UN DEPHASEUR 180 EN BANDE C 115 Pour pouvoir obtenir les performances des diff\u00e9rents prototypes sans l\u2019influence de la connectique n\u00e9cessaire aux mesures, un kit de calibration est n\u00e9cessaire" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000591_f_version_1671613940-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000591_f_version_1671613940-Figure2-1.png", + "caption": "Figure 2. Stator slot shape of induction motor and its parameters.", + "texts": [ + " The breakdown torque, \u03c4bk can be calculated as [45]: \u03c4bk = 3pV2 ph 2\u03c9[R1 + \u221a R2 1 + (X1 + 1.15X2)2] (8) where p represents the number of poles and \u03c9 is the angular frequency. Finally, the power factor of the motor can be computed using the following expression: cos \u03c6 = Pout 3Vph I1\u03b7 (9) Stator slot geometries become the most relevant part of the IM performance enhancement because of the influence of stator resistance and leakage reactance on the three performance indicators [46]. The stator slot design in this work is based on stator shape, as illustrated in Figure 2. There are six parameters related to the stator slot, namely, stator slot opening width (Bs1), upper width (Bs2), lower width (Bs3), opening height (Hs1), wedge height (Hs2), and height (Hs3), as shown in the figure. Only Bs1, Bs2, and Hs3 are selected because they highly impact the magnetization characteristics and affect the stator resistance and reactance. The derivation of stator resistance and leakage reactance from the stator slot parameters is explained in [43]. The parameters are varied within certain limits to avoid the violation of mechanical motor dimensions and ensure the stator tooth flux density is within the allowed range" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004585_5_secm-2016-0335_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004585_5_secm-2016-0335_pdf-Figure1-1.png", + "caption": "Figure 1: Solid model of the composite leaf spring.", + "texts": [ + " The design parameters were determined by using geometric constraints and specified loading and boundary conditions. The requirements and parameters of the composite-based leaf spring used in this study were as follows: \u2013 gross axle load, W = 2.5 ton, \u2013 maximum desired vertical deflection, smax = 135\u00a0mm, \u2013 total length, L = 1300\u00a0mm, \u2013 spring rate, k = 18\u201320 kgf/mm, and \u2013 existing space for spring width, w = 70\u201380\u00a0mm. The composite-based leaf spring designed considering the aforementioned parameters is shown in Figure 1. Five different configurations as shown in Table 2 for composite plates were considered and manufactured using the RTM process. These configurations were selected so as to determine the effect of the fabric type and orientation on the mechanical behavior of the composite structures. These plates consisted mainly of unidirectional (UD) fabrics so that the leaf spring resists the stresses caused by the vertical load, which is the most dominating mechanical load applied on a leaf spring [23], as UD fibers have good strength properties along the fiber direction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure23-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure23-1.png", + "caption": "Figure 23. Volumetric shrinkage at ejection.", + "texts": [ + " From the analysis, along the shaft where the thickness variations are prominent, possible sinks are predicted (Figure 21). 4.3.2. Deflection and Warpage The deflection and warpage results (Figure 22) show how the part deflects from the originally designed shape. These mainly occur due to drastic differences in temperature at different part locations. This result helps design an appropriate cooling system and vary the design of the part to minimize defects during fabrication. Along the edge region, more even cooling is desired. 4.3.3. Volumetric Shrinkage at Ejection The volumetric shrinkage at ejection (Figure 23) decreases local volume from the end of the cooling stage to when the part has cooled to the ambient reference temperature, which shows the volumetric shrinkage for each area expressed as a percent of the original modeled volume. This result matches with the aforementioned quality prediction. In this study, we verified the final prototype AWM-750D using numerical simulations and wind tunnel tests and obtained the following main findings: 1. The blade surface roughness needs to be controlled in the manufacturing process for better efficiency and stable production, and we resolved these with the injection molding method based on numerical simulation for blade production" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002738_le_download_323_1480-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002738_le_download_323_1480-Figure4-1.png", + "caption": "Fig. 4: Buck converter design example", + "texts": [ + " 324 To obtain the average inductor current, we can use: R VI out avg,L = (10) Therefore, the maximum and the minimum current through the inductor are: t)1( L2 V R V 2 III outout L avg,Lmax,L \u03b1\u2212\u00d7+= \u2206 += (11) t)1( L2 V R V 2 III outout L avg,Lmin,L \u03b1\u2212\u00d7\u2212= \u2206 \u2212= (12) We can now with the same analysis obtain the maximum and minimum current trough the capacitor: T)1( L2 V 2 II outL min,c \u00d7\u03b1\u2212\u00d7= \u2206 = (13) T)1( L2 V 2 II outL min,c \u00d7\u03b1\u2212\u00d7\u2212= \u2206 \u2212= (14) The waveform for the current through the capacitor is shown below: From Figure 3, it\u2019s clearly that the average current through the capacitor is zero, but in one-half cycle the capacitor will charged and the increase in charge is: TI 8 1 2 T 2 I 2 1Q L L \u00d7\u2206\u00d7=\u00d7 \u2206 \u00d7=\u2206 (15) and because outc VV = , the increase in capacitor voltage is: Comprehensive and field study to design a buck converter for photovoltaic systems 325 C QVout \u2206 =\u2206 (16) Then from (8) and (15) we obtain: out 2out VfCL8 1V \u00d7\u00d7\u00d7 =\u2206 (17) In continuous conduction mode (CCM), 0I min,L = ; (the minimum current can be zero at the time of switching), so from (12) we have: T)1( L2 V R V outout \u00d7\u03b1\u2212\u00d7= (18) Then if the desired switching frequency f and load resistance R are established, the minimum inductor current required for CCM is: )1( f2 RLmin \u03b1\u2212\u00d7= (19) Likewise we can obtain: )1( L2 Rfmin \u03b1\u2212\u00d7= (20) )1( Lf2Rmin \u03b1\u2212 \u00d7 = (21) 3. BUCK CONVERTER DESIGN EXAMPLE Figure 4 shows the design of the Buck converter for which we will present an easy method to select component values: either a P-channel or an N-channel MOSFET may be used. In order to determine input capacitor, diode, MOSFET characteristics, one first needs to calculate the required inductor and output capacitor specifications. We will then, with the selected components, calculate the system\u2019s efficiency. S. Mouhadjer et al. 326 In our application we need to convert a 17 V power source to an output of 12 V to charge a lead-acid battery by using only one PV module (Photowatt PWX500) where we fixed the output current around 2 A for more efficiency. The switching frequency is selected at 100 kHz and the current ripple will be limited at 30 % of maximum load. We have now our input-output parameters values which are: V17Vin = , V12Vout = , A2IL = kHz100fsw = , 705.0VV inout ==\u03b1 , Lripple I3.0I \u00d7= From Figure 4 we can obtain directly the value of the inductor L : ripple sw outin I f)VV(L \u03b1 \u00d7\u2212= Calculate: \u00b5H75.58L = . An insufficient output capacitance and a high equivalent-series resistance, \u2018ESR\u2019 in the output capacitor caused a large overshoots and a large voltage ripple in the output. So we must include an output capacitor with ample capacitance and low ESR in order to resolve this problem. From (17) we have: out out 2 V VfL8 1C \u00d7 \u2206\u00d7\u00d7 = (22) Define ripple voltage: mV50Vout =\u2206 . Calculate: F128Cout \u00b5= (minimum)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-26-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-26-1.png", + "caption": "Figure 2-26. Exemple d'antenne PIFA repli\u00e9e", + "texts": [ + " La mise en \u0153uvre de cette technique peut r\u00e9duire la taille d'une antenne patch de 50% mais la largeur de bande est diminu\u00e9e ainsi que l'efficacit\u00e9 de rayonnement de l'antenne. La Figure 2-24 montre des exemples de mise en \u0153uvre de cette technique de miniaturisation. 58 Pour les antennes filaires comme les dip\u00f4les ou monopoles, imprim\u00e9s ou non, le repliement est \u00e9galement une modification de la forme originale de l'antenne qui permet de r\u00e9duire son encombrement. La Figure 2-25 pr\u00e9sente un exemple de monopole repli\u00e9. Le repliement peut \u00e9galement \u00eatre appliqu\u00e9 sur des structures planaires comme des PIFA (Figure 2-26) ou non seulement le repliement du plan rayonnement r\u00e9duit le volume de la structure mais cr\u00e9e en plus en effet capacitif qui contribue \u00e0 la diminution de la fr\u00e9quence de r\u00e9sonnance. 59 Un autre type de modification de design est l'utilisation de structures fractales, on parle alors d'antenne fractales. Il s'agit d'antenne classiques planaires ou filaires dont le design est issu d'algorithmes math\u00e9matiques bas\u00e9s sur des fonctions it\u00e9ratives. Parmi les formes fractales les plus utilis\u00e9es, il y a celles de Von Kock, de Hilbert et de Sierpinski" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001986_.1117_12.2308266.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001986_.1117_12.2308266.pdf-Figure1-1.png", + "caption": "Fig. 1: Pleiades Telescope", + "texts": [], + "surrounding_texts": [ + "The primary mirror has been grinded/lightened with undercutting technique; other mirrors have been lightened with an open-back-concept. With these lightening techniques, SESO is able to lighten mirrors with weight reducing level up to 70%-80%." + ] + }, + { + "image_filename": "designv8_17_0001762_e_download_1161_1020-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001762_e_download_1161_1020-Figure6-1.png", + "caption": "Figure 6 \u2013 Fuselage design profile", + "texts": [ + " The first compartment is cylindrical and will house the payload, electronic, and propulsion equipment. The compartment's length covers from the tip to the midpoint of the fuselage length, 0.95 m. The diameter of the case was estimated to be around 0.4 m maximum to maintain aerodynamic stability [14]. At the same time, the second compartment of the fuselage is smaller and made of an aluminium tube or carbon fibre for simplicity and reduced weight. The fuselage design was conducted using XFLR5 v6 software, as shown in Figure 6. Results for the centre of gravity and aircraft weight components. Table 6 presents the centre of gravity and aircraft weight components. The weights of the various aircraft components and their corresponding centre of gravity depict the aerodynamic stability and balance of the aircraft. Hence the multiple parts of the solar aircraft are designed and assembled using XFLR5 v6 software. The whole assembly in 3D views is shown in Figure 7. Section \u201cTechnics\u201d 4015 Airfoil analysis was conducted for four selected airfoils" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001449_2_2_12_22004614__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001449_2_2_12_22004614__pdf-Figure8-1.png", + "caption": "Fig. 8. Virtual plant in the common mode", + "texts": [ + " When the nominal values are set as (27) and (28) and compensation works, the governing equations are transformed as Motor \u03b8\u0308 ref = s2\u03b8m \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (30) Load Kfn (\u03b8m\u2212 \u03b8l) \u2212 s s+gml \u03c4dis l = J lns2\u03b8l \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (31) Spring \u03c4reac= Kfn (\u03b8m\u2212\u03b8l) \u2212 (Kfn\u2212 Kf) (\u03b8m \u2212 \u03b8l) \u00b7 \u00b7 \u00b7 \u00b7 (32) where the nominal error and other disturbance (that includes the external torque \u03c4ext) are expressed as \u03c4dis l = [\u03c4dis Cl , \u03c4 dis Dl ]. As with the theory of DOB, the disturbance is suppressed within the cutoff frequency. If the compensation using MLOB works perfectly, we can independently consider the design for each mode. The following sections explain the controller designs for the common and the differential modes based on the control goals shown in (12) and (13). 3.3.2 Common Mode Fig. 8 shows the virtual control plant in common mode. According to the control goal represented in (12), we design the common space controller and configure the acceleration reference \u03b8\u0308ref C so that the virtual control system is the force control system to control \u03c4C to keep zero. Thus, The external torque \u03c4C is fed back with torque command 0. (The operational torque \u03c4h and the environmental torque \u03c4e are obtained using observers or force sensors.) RRC, the control method considering loadside dynamics, suppresses vibration induced in resonant systems (21)\u2013(23)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002208_load.php_id_15010201-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002208_load.php_id_15010201-Figure3-1.png", + "caption": "Figure 3. Geometry and photograph of the proposed antenna with the sizes of r1 = 30 mm, r2 = 23.4 mm, r3 = 14.4 mm, r4 = 1.5 mm, a1 = 6.1 mm, b1 = 7.93 mm, h = 6mm, d1 = 3 mm, d2 = 0.4 mm, and \u03b4 = 120\u25e6. (a) Top and side view of the proposed antenna. (b) The details of the open elliptical-ring slot. (c) Photograph of the proposed antenna.", + "texts": [ + " Only in the gap area does the field distribution change, because the field must be perpendicular to the boundaries at the end of the lines. The electric field component EZ is nearly constant across the microstrip line and only changes slightly from the inner to the outer circumference. For TM 210 mode, an additional zero of the azimuthal component H\u03c6 is found, and the corresponding field distribution is shown in Figure 2(b). The mean value of the resonator length now is nearly equal to one wavelength. The resonance characteristics of the proposed antenna and the effects of key parameters are performed in the following section. Figure 3 presents the geometry of the proposed antenna. The circular patch with radius r2 is printed on a substrate of thickness h = 6mm, relative permittivity 2.65 and loss tangent 0.0025. And both the substrate and ground plane have radius r1. Six shorting vias of radius r4 are uniformly distributed along a circle with a displacement of r3 from the feeding point. Then, six open elliptical-ring slots are embedded to enclose each of the shorting vias. The details of the open elliptical-ring slots are shown in Figure 3(b). The open elliptical-ring slot has an inner semi-minor axis of a1 and an inner semi-major axis of b1 with width d1. However, the ratios between the major and minor axes of both the outer and inner ellipses are equal to b1/a1. The gap between the two open ends of each open elliptical-ring slot is d, and the angle between the gap center and major axis is \u03b4. For providing good radiation pattern performances across the three bands, the coaxial probe is placed at the center of the patch with the probe radius of 0.6 mm. The effects of vital parameters of the proposed antenna on the resonant frequency and impedance matching are discussed in this section. Figure 4 shows |S11| of the proposed antenna for different values of slot gap d. The other parameters of the antenna are shown in the caption of Figure 3. It is observed that when d increases, the second resonant frequency (TE 110 mode of the open elliptical-ring slot) increases for the decrease of the resonance path of the open elliptical-ring. Also, the increase of gap d causes a poor impedance matching at the third resonant frequency (TE 210 mode of the open elliptical-ring slot). From Figure 4, it can be seen that the first resonant frequency (monopolar patch mode) changes slightly since the position of the shorting vias does not change. |S11| of the proposed antenna with different values of angle \u03b4 is shown in Figure 5 with other parameters shown in the caption of Figure 3. It can be noticed from the figure that as the value of \u03b4 decreases, the first resonant frequency decreases, and there is only slight change in the second and third resonant frequencies. However, the decrease of \u03b4, which means that the feeding position of the open elliptical-ring slot is changed, causes a poor impedance matching at the second and third resonant frequencies. Figure 6 shows |S11| of the proposed antenna for different values of a1 (or slot width d1) with the other parameters shown in the caption of Figure 3. It is observed that when the value of a1 increases (or slot width of d1 decreases), the second and third resonant frequencies decrease due to the increase of the mean resonance path of the open elliptical-ring slot. Also, impedance matching of the second and third resonant frequencies turns better with the decrease of slot width. However, the first resonant frequency, dependent on the angle \u03b4 and the position of the shorting vias, changes little. Figure 7 shows |S11| of the proposed antenna for different distances between two adjacent slots with the other parameters shown in the caption of Figure 3. Noting that the slot width and the ratio between major and minor axes (b1/a1) are fixed when changing the distance between two adjacent slots. It is easily found that when the distance between two adjacent slots increases (the size of the slot decreases), the second and third resonant frequencies turn impedance mismatching for the weak coupling between the slots, but there is no change in the first resonant frequency. Therefore, the number of slots should be properly chosen in order to get a good impedance matching at both the TE 110 and TE 210 modes of the open elliptical-ring slot. In this paper, considering the radius of the circular patch, the number of slots is six. Figure 8 shows |S11| of the proposed antenna for different ratios between major and minor axes. The other parameters of the antenna are fixed as shown in the caption of Figure 3. The shorting via position of r3 is accordingly adjusted to maintain the adjacent slots not to overlap while the slot width is fixed. It is easily found that as the ratio between major and minor axes increases, the second and third resonant frequencies increase, and there is no change in the first resonant frequency. Also, the increased ratio makes the impedance matching of the whole resonant frequencies good and the two resonant frequencies of the TE 210 mode couple together to form the third resonant band. When the ratio is equal to 1, the open elliptical-ring slot becomes an open-ring slot, and a poor impedance matching is obtained. Therefore, an open elliptical-ring slot, not an open-ring slot, is necessary for the design of the proposed triple-band circular patch antenna. To verify the theory, a prototype, shown in Figure 3(c), is fabricated and measured. The measured and simulated |S11| of the prototype are presented in Figure 9, and a good agreement is achieved except for an acceptable frequency discrepancy which may be caused by the fabrication error. From the measured results in Figure 9, it is clearly observed that three resonant modes are excited, and their resonant frequencies (defined as the frequencies with minimum |S11|) are about 2.4 GHz, 3.5 GHz, 5.5 GHz and 6.0 GHz, which belong to the monopolar patch mode, TE 110 and TE 210 modes, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002748_e_download_7184_5916-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002748_e_download_7184_5916-Figure5-1.png", + "caption": "Fig. 5 \u2013 Composite joint in final form", + "texts": [ + " And therefore that diagonal line of the upper polygons of the hollow structure need to be mutually crossed and connected; As the octagonal protruding structure part on four sides is easy to be stressed and concentrated, the part protruding out of the outer edge of the quadrangular pyramid is cut off. The corner points of the hexagon and the trimmed octagon are respectively connected with the corresponding joints of the three-direction grid type single-layer --------------------------------------------------------------------------------------------------- DOI 10.14311/CEJ.2021.01.0014 194 grid structure to form partial web members of the three-direction grid type prestressed mega-grid structure. Finally, a composite joint is formed as shown in Figure 5. Geometric parameter setting of mega-structure According to the characteristics of the three-direction grid type prestress mega-grid structure, the geometric parameters of the mega-grid are set as shown in Figure 6, wherein Lx represents the length of the structural longitudinal mega-grid, Ly represents the length of the structural transversal mega-grid, and H represents the thickness of the structure; The number of long direction giant grids Nx, the number of span direction giant grids Ny, the number of long direction giant component interjoint grids N1, the numbers of span direction giant component interjoint grids N2, and the numbers of oblique direction giant component interjoint grids N3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure6-14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure6-14-1.png", + "caption": "Figure 6-14. Antenne miniature utilis\u00e9e dans le syst\u00e8me \u00e0 diversit\u00e9", + "texts": [ + "................................................................... 191 Figure 6-10. Repr\u00e9sentation de la g\u00e9om\u00e9trie du syst\u00e8me d'antennes LCIS................................ 194 Figure 6-11. Repr\u00e9sentation des trois orientations dans l'espace du syst\u00e8me LCIS ................... 194 Figure 6-12. Repr\u00e9sentation de la g\u00e9om\u00e9trie du syst\u00e8me d'antennes FTRD .............................. 195 Figure 6-13. Coefficients de r\u00e9flexion (S11) des deux syst\u00e8mes UWB ..................................... 196 Figure 6-14. Antenne miniature utilis\u00e9e dans le syst\u00e8me \u00e0 diversit\u00e9.......................................... 201 Figure 6-15. Syst\u00e8me d'antennes miniatures avant rotation ....................................................... 201 Figure 6-16. Repr\u00e9sentation du dip\u00f4le dans le rep\u00e8re initial ...................................................... 202 Figure 6-17. Vue des antennes patchs de r\u00e9f\u00e9rence avant rotation............................................. 203 Figure 6-18. Coefficients de r\u00e9flexion des antennes patchs polaris\u00e9es verticalement et horizontalement et de l'antenne miniature (\"chip antenna\") ", + " Les param\u00e8tres de la distribution en \u00e9l\u00e9vation pour l'environnement urbain choisi sont 1,6Vm = \u00b0 , 4,6V\u03c3 \u2212 = \u00b0et 4,4V\u03c3 + = \u00b0 pour la composante du champ selon \u03b8 et 1, 4Hm = \u00b0 , 4,9H\u03c3 \u2212 = \u00b0 et 7H\u03c3 + = \u00b0 pour la composante du champ selon\u03c6 . Le XPR est de 11,4 dB. Comme l'ensemble des environnements que nous avons consid\u00e9r\u00e9s dans nos travaux, la distribution en azimut est uniforme. 201 6.4.3 Syst\u00e8mes d'antennes Le syst\u00e8me est r\u00e9alis\u00e9 en utilisant deux antennes miniatures identiques d\u00e9crites dans le chapitre 4. Il s'agit d'une \"chip antenna\" r\u00e9alis\u00e9e sur un substrat de Arlon, le CLTE pr\u00e9sentant une permittivit\u00e9 de 2,98. Les d\u00e9tails de la g\u00e9om\u00e9trie de l'antenne sont rappel\u00e9s sur la Figure 6-14. Le syst\u00e8me est constitu\u00e9 d'un plan de masse rectangulaire de 100 x 50 mm, les antennes \u00e9tant dispos\u00e9es \u00e0 chacune des extr\u00e9mit\u00e9s de ce plan de masse. Ce syst\u00e8me pr\u00e9sente donc une diversit\u00e9 spatiale mais \u00e9galement une part de diversit\u00e9 de diagramme car la position de l'antenne par rapport au plan de masse conditionne fortement la directivit\u00e9 de ces antennes miniatures. Avant rotation, le syst\u00e8me est orient\u00e9 comme repr\u00e9sent\u00e9 sur la Figure 6-15. 202 Le syst\u00e8me pr\u00e9sentant une sym\u00e9trie, les deux antennes ont les m\u00eames propri\u00e9t\u00e9s" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000623__4_5_4_17-00007__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000623__4_5_4_17-00007__pdf-Figure8-1.png", + "caption": "Fig. 8 Developed 5-DOF controlled maglev motor.", + "texts": [ + " 5, and the result indicates that there is no magnetically saturated part. Fig. 6 and Fig. 7 show an estimated attractive force and rotating torque with the excitation current of 0-2 A. The calculated force and torque are sufficiently greater than the identified target performances. 3 2 \u00a9 2017 The Japan Society of Mechanical Engineers [DOI: 10.1299/mej.17-00007] A 5-DOF controlled maglev motor was developed referring to a finally determined motor geometries. The schematic of the developed motor is shown in Fig. 8. Specifications of the motor geometries and rotor permanent magnets are shown in Table 1. The developed motor has an outer diameter of 22 mm, a height of 33 mm and a magnetic air-gap length of 1.5 mm. The weight of the levitated rotor is 11 g. The thickness of the rotor permanent magnets is 1.0 mm. The motor stator and the rotor back iron are made of soft magnetic iron (SUY-1). The permanent magnets are made of Nd-Fe-B which has a coercivity of 907 kA/m and a residual flux density of 1.36 T. The number of turns in the concentrated windings wound on each stator tooth is 66" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002759_f_version_1705227457-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002759_f_version_1705227457-Figure8-1.png", + "caption": "Figure 8. The current distribution on the proposed surface on the top and bottom using different frequencies. (a) Distribution on 16.5 Hz. (b) Distribution on 19.5 GHz. (c) Distribution on 24 GHz.", + "texts": [ + " The \u2206\u03c6uv is +90 \u25e6 over 14 to 26 GHz in the frequency band, according to the phase fluctuation rate, illustrated in Figure 7c. Finally, Figure 7d illustrates the calculated AR based on the phase difference \u2206\u03c6uv obtained in Figure 7a using Equation (9). The anticipated AR is closely compatible with Figures 4a and 7d. The distribution of the surface currents for LTC PC on both the metasurface structure and the ground plane of the unit cell is analyzed to understand the underlying physical mechanism behind the conversion. In Figure 8a\u2013c, three plasmonic resonances (at 16.5 GHz, 19.5 GHz, and 24 GHz) are observed as a result of the interaction between the parallel and anti-parallel currents on the pattern layer (top layer) and the ground layer (bottom layer). The anti-parallel currents on the top and bottom layers lead to a strong magnetic resonance. In Figure 8a,c, the resonances at 19.5 GHz and 24 GHz are attributed to the intense currents along the outer edges (lengths) of the arrows, while the currents along the widths of the arrows cause the resonance at 16.5 GHz in Figure 8a. When the incident wave is y-polarized, the reflection of the RHCP waves occurs as the angle shifts from +90\u25e6 to \u221290\u25e6, and vice versa. The presence of coupling effects among both metallic patches contributes to the greater stability of RHCP conversion compared to LHCP conversion. The findings of the study suggest that these elements reveal the reasons behind the attainment of outstanding performance and the ultra-wideband LTC polarization conversion. The proposed design and the state of the art as already published are compared in Table 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003117_f_version_1437134814-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003117_f_version_1437134814-Figure11-1.png", + "caption": "Figure 11. Explanation of the reconstructed camera-pose-triangle and driving tracks. (a) Colored triangle represents the position of the recovered image and the camera projective center. The size of the triangle is followed by the size of the image data. (b) Red line represents the recovered vehicle driving tracks that carried recorder 1. The colored triangles are the reconstructed results that represent the position of the images taken by recorder 1.", + "texts": [ + " The abnormity in the image pairs (the RMSEs in our method were larger than the typical method) for which we offer the following analysis. We found that the abnormal pairs were usually shot at long-range distances (more than 200 m) with little overlap, leading ultimately to a decrease in the number of accurate matches. A large proportion of the outliers led to an orientation failure, which produced abnormal RMSE results. In general, however, it can be concluded from Figure 10 that the Mask effectively improved the matching accuracy. Figure 11 is an explanation of the reconstructed camera-pose-triangle in the following figures. The colored triangles represent the position of the recovered image/camera. Figures 12\u201314 shows the camera pose reconstruction results of three sets. The details and compositions of each set were described in Table 2. The difference between the typical method and our method is that the feature points on the Mask are removed before matching in our method. Since motor vehicles can only run in a smooth track, we were able to distinguish an unordered track as false reconstruction results easily" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004695_oradea2018_02004.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004695_oradea2018_02004.pdf-Figure11-1.png", + "caption": "Fig. 11. Finite elements model", + "texts": [ + " The numerical evaluation of the previously studied concepts, here the determining the deformation state as well as the contact distribution between the interest elements (guide and bolt). Determining the tensioning state is not taken into consideration because the applied forces are hot big and the physical models are rigid enough so that they can withstand higher loads. For the numerical evaluation of the studied models it was used the ANSYS Workbench software M. T. Late\u015f, R. Velicu and R. Papuc [8]. The assembly model with finite elements is shown in figure 11, a and in figure 11, b is shown a detail on the bolt meshing. On the elements found in contact there was made a finer meshing, meaning it had more layers of finite elements and nodes in order to have a better convergence of the results and contact from that area. After meshing there were obtained 16234 finite elements and 67696 modes. For this model there are shown two calculation cases, as follows: case 1: guide material PA46, F=5 N and \u03bc=0.28; case 2: guide material PA66, F=5 N and \u03bc=0.28; The method of applying the force is presented in figure 12 being identical for both analyzed cases" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure21-1.png", + "caption": "Figure 21: Image of the interior frame; Left: INEV axis of rotation, right: INEV built in within the DFPF axis [131].", + "texts": [ + " 36 Figure 19: The robotic force-plate with 2-DOF actuation (TOP: CAD drawing; BOTTOM: Experimental Prototype). The cubic support frame (1); internal and external layers of the footplate (2); the PF/DF motor and transmission system (3); the IN/EV motor and transmission system (4); the encoders (5); the foot strap (6); and mechanical stop (7). .................................................. 38 Figure 20: 3D CAD image of the robotic footplate support frame built of 1.5\u201d aluminum [131] .............. 39 ix Figure 21: Image of the interior frame; Left: INEV axis of rotation, right: INEV built in within the DFPF axis [131] .................................................................................................................................... 40 Figure 22: The robotic force-plate, load cells and sensing mechanism (TOP: experimental prototype; BOTTOM: CAD drawing). The load cells (1); acrylic plate (2); aluminum plate (3); metal crossbar (4); aluminum beams (5); the linear spring to create a preload (6)", + " It should be able to compensate the human weight and provide the possibility of effective rehabilitation experience for the patients with variety of lower extremity and control disorders. 36 Maximum user weight (Kg) 150 Footplate size (shoe size) Women 6 - Men 14 Based on the current systems in the market and research level [19-23, 76-87], and by integrating the interviews from the experts in physical therapy (n = 5), we have derived the electromechanical specification of the system as listed in Table 7. The building components of vi-RABT are shown in Figure 21. The system is composed of an electromechanical platform-based hardware in contact with the patient and a video screen to 37 present the interactive games. The system is equipped with force/angle sensors as well as actuators to apply 2-DOF rehabilitation exercises to each foot. Patients can use the system in a seated or standing posture. They face the large screen and are encouraged to engage in goaloriented VR games, to improve their ankle function. As shown in Figure 21, the ultimate system design is composed of 1) a stationary platform; 2) two robotic force-plates; 3) an adjustable seat; 4) the wide 3D projection screen and safety features. In the scope of this thesis, we are focused on a single robotic platform, used in the sitting position. This subsystem serves as the housing for the robotic force-plates and the safety rails. The stationary platform provides additional space around the robotic footplates for the patients to step on. This might be needed based on the specific training protocol, for example during standing pre-gait activities such as stepping practice or weight shifting in semi-tandem position" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001092_2_1_12_22004507__pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001092_2_1_12_22004507__pdf-Figure6-1.png", + "caption": "Fig. 6. Magnetic flux density of the jigsawpuzzle-shaped magnet", + "texts": [ + " Accordingly, the magnet is fixed by splicing, which is suitable for applications with arbitrary steering. the advantages of this approach are as follows: because the magnet structure is relatively complete, its overall mechanical strength is improved; because the bolt is fixed, the force is more uniform and service life is improved. An additional process for installing the plug is included, and the geometrical structure of the fixed magnets in the motor is shown in Fig. 5. Here A, B and C are the Magnet thickness, Magnet angle of spread and Frame thickness. Figure 6 is a color block representation of the magnetic flux density of the spliced magnets. The rated saturation magnetic flux density is 2.2 T. The areas where the maximum magnetic saturation occur after applying the new improvement strategy are clearly seen. Compared with the traditional design, the dovetail grooves are more evenly distributed. Figure 7 depicts the distribution of the magnetic field lines for the spliced configuration that relieves magnetic saturation. The simulation condition for the test includes a rotation speed of 3,400 rpm, and the material used for the pin is the same as that of the pole core of the prototype, which is S10C", + " Hybrid Excitation Optimization Design The hybrid-excitation-type DC machine has the advantage of high power density owing to the permanent magnets. Because of the influence of the structural characteristics, its magnetic field flux does not rely on a single source, and the electromagnetic flux is formed by the excitation winding and permanent magnets. The magnetic flux combination complement each other and have the following advantages: experiments show that the output power is improved without increasing the difficulty of processing. The trend of magnetic flux distribution with different thicknesses of the permanent magnet is shown in Fig. 6. Owing to the structural design of the hybrid-excitation-type DC machine, there is mutual interference between the magnetic field generated by the excitation winding and that of the permanent magnet in the stator, where the aluminum ring is isolated, and the interference between the two magnetic fields is bound to counter-rotate. However, since the purpose of the starter is to help the engine complete its startup work, the requirements for torque ripple in its application are relatively low; hence, there is no need to suppress this ripple" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002599_952ZMbRGOrcqD0ME.pdf-Figure5-1.png", + "caption": "Figure 5: Cloud Chart of Magnetic Induction Intensity", + "texts": [ + " Therefore, appropriate clearances and magnetic tooth thickness should be selected. This way, the transmission effect is the best, and the torque generated by magnetic field coupling is the most ideal, which can achieve the maximum output torque. According to the simulation experiment analysis, the model diagram of the magnetic planetary gear with the best parameters is obtained, and the distribution nephogram of magnetic field intensity and magnetic induction intensity is obtained, as shown in Figure 4 and Figure 5 respectively. Published by Francis Academic Press, UK -22- Magnetize the driving wheel and obtain the torque analysis diagram of the driven wheel. The torque varies in a function, with the minimum value being when the N pole is relative to the S pole. At this time, the N pole generates a downward magnetic field line, while the S pole generates an upward magnetic field line. At this time, the magnetic force is not circulating; When the maximum value is two N poles facing each other, the magnetic field lines of the two magnetic blocks are all downward, and when passing through the magnetic block, the magnetic force direction is upward" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure5.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure5.3-1.png", + "caption": "Figure 5.3: Vane Movement Relative to Vane Slot", + "texts": [ + " These expressions for the characteristic velocity vcv and hydraulic diameters Dcv of the fluid for the suction and compression chambers are then adapted accordingly. The new expressions for the characteristic velocity and the hydraulic diameter for the suction and compression chambers are shown in Equations (5.17) and (5.18), respectively. \ud835\udc63\ud835\udc50\ud835\udc63 = 1 \ud835\udc5f\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc5f\ud835\udc50 \u222b \ud703?\u0307?\ud835\udc5f \ud835\udc51\ud835\udc5f \ud835\udc5f\ud835\udc50 \ud835\udc5f\ud835\udc5f\ud835\udc50 = \ud703?\u0307? 2 (\ud835\udc5f\ud835\udc50 + \ud835\udc5f\ud835\udc5f\ud835\udc50) (5.17) \ud835\udc37\ud835\udc50\ud835\udc63 = 2\ud835\udc59\ud835\udc50(\ud835\udc5f\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc5f\ud835\udc50) \ud835\udc5f\ud835\udc50 \u2212 \ud835\udc5f\ud835\udc5f\ud835\udc50 + \ud835\udc59\ud835\udc50 (5.18) On the other hand for the vane slot chamber, since the vane movement in the vane slot chamber resembles that of a reciprocating compressor as shown in Figure 5.3, the characteristic velocity and hydraulic diameter are approximated to that of the reciprocating compressor given in various heat transfer correlations in the literature [31, 107\u2013109]; the characteristic velocity for the vane slot chamber would be the speed of the vane akin to piston speed and the hydraulic diameter would be the vane slot width. The respective expressions are shown in Equations (5.19) and (5.20). 61 \ud835\udc63\ud835\udc63\ud835\udc4e\ud835\udc5b\ud835\udc52,\ud835\udc50\ud835\udc63 = \ud835\udc51\ud835\udc5f\ud835\udc63\ud835\udc5f \ud835\udc51\ud835\udc61 (5.19) \ud835\udc37\ud835\udc63\ud835\udc4e\ud835\udc5b\ud835\udc52,\ud835\udc50\ud835\udc63 = 2\ud835\udc5f\ud835\udc63,\ud835\udc61\ud835\udc56\ud835\udc5d (5.20) With the heat transfer correlations presented in Section 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004515_id_0354-98362304229C-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004515_id_0354-98362304229C-Figure5-1.png", + "caption": "Figure 5. Expansion of electric vehicle chassis", + "texts": [ + " In compliance with the regulation, the Class M1 is designed as a hatchback 5-door car chassis with AB body type. To prevent major accident effects from the side of conventional vehicles, three different impact-dampening parts have been incorporated, as shown in fig. 4. The chassis design of the conventional vehicle has been completed, using simpler parts instead of structures with more complex surfaces to be manufactured. The conventional vehicle chassis, the design of which has been completed, underwent a transformation into the electric vehicle chassis shown in fig. 5 by incorporating the design considerations presented in figs. 6 and 7. The electric vehicle chassis has been designed by placing the batteries on the base of the vehicle and distributing the front load, which is typical of conventional vehicles, to the vehicle base. These design decisions improve the road holding and stability of electric vehicles when compared to conventional 4-wheel vehicles. Figure 6. Chassis designs of different electric vehicle brands [16] Figure 7. Electric vehicle's battery slot structure [17] In completed vehicle frames, attention should be given to the production, use, maintenance, and recycling stages of the materials used to minimize emissions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.30-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.30-1.png", + "caption": "Figure 1.30. Design evolution of the C5 rear lower control arm [45].", + "texts": [ + " These results allow structural design of these parts to proceed. An account of how the control arms for the C5 were developed is available in [45]. For the rear lower control arm, a basic design, Alpha I, was created that was functionally acceptable but not optimal. Finite element analysis led to Alpha II. Issues with mass, suitability for production, and the durability of the shock absorber mount led to a new Beta design. Further testing and refinement resulted in the Production design. Drawings of these four design stages are shown in Figure 1.30. When ready, compliance of the suspension components and vehicle body itself, from finite element analysis, can be added into the MBS model and the elastokinematics re-assessed. Eventually, the design is complete enough to consider the vehicle as a whole. In the last stage, the completed vehicle design is assessed to see if it meets the original ride and handling targets. Early on, whole-vehicle simulations are used. This allows changes to be made to the design before committing to hardware. Once the 31 design is ready, it is constructed and tested" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003536_830_81_15-00138__pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003536_830_81_15-00138__pdf-Figure13-1.png", + "caption": "Fig. 13 Overall view of the testing equipment. The power", + "texts": [], + "surrounding_texts": [ + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n6 '\n2hb Z \uff0824\uff09\n' M Z\nM \uff0825\uff09\n\u516c\u79f0\u66f2\u3052\u5fdc\u529b \u03c3M\u306f\uff0c26.5[N/mm 2 ]\u306b\u306a\u308b\u3053\u3068\u3092\u78ba\u8a8d\u3057\u305f\uff0e\u3053\u3053\u3067\uff0c\u5fdc\u529b\u96c6\u4e2d\u4fc2\u6570 \u03b1(Heywood, 1952)\u3092\u4ee5\u4e0b\u306e\u5f0f(26) \u3088\u308a\u8a08\u7b97\u3092\u3057\u305f\uff0e\u5f0f(26)\u4e2d\u306e B\uff0cb\uff0c\u03c1\u306f\u305d\u308c\u305e\u308c 2B=20.0[mm]\uff0c2b=8.0[mm]\uff0c\u03c1=6.0[mm]\u3067\uff0c\u305d\u306e\u5b9a\u7fa9\u3092\u56f3 11 \u306b \u793a\u3059\uff0e\n85.0\n8.437.5\n1\n1\n \n\n \n\n\n\n\n \n b\nb\nB b\nB\n\uff0826\uff09\nMS \uff0827\uff09\n3\na\na\n16 T d \uff0828\uff09\n\u5fdc\u529b\u96c6\u4e2d\u4fc2\u6570 \u03b1\u306f 1.16 \u3068\u306a\u308a\uff0c\u516c\u79f0\u66f2\u3052\u5fdc\u529b \u03b6M\u306f 26.5[N/mm 2 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da\u306f\u5f0f(28)\u3088\u308a\u6c42\u3081\u308b\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u5f0f(28)\u4e2d\u306e \u03b7a\u306f\u30ea \u30f3\u9752\u9285\u306e\u8a31\u5bb9\u305b\u3093\u65ad\u5fdc\u529b\u3067\u3042\u308b\uff0e\u4f5c\u7528\u3059\u308b\u30c8\u30eb\u30af T \u306f\u30c8\u30eb\u30af\u30e1\u30fc\u30bf\u306e\u8a31\u5bb9\u5024 Ta=20[N\u30fbm]\u3068\u3057\uff0c\u30ea\u30f3\u9752\u9285\u306e\u8a31\u5bb9 \u305b\u3093\u65ad\u5fdc\u529b \u03b7a\u306f \u03b7a=29.4[N/mm 2 ]\u3092\u7528\u3044\u305f(\u4e8c\u53cd\u7530\uff0c\u6885\u672c\uff0c1978)\uff0e\u5f0f(28)\u3088\u308a\uff0c\u8ef8\u306e\u6700\u5c0f\u5f84 da\u306f 15.1[mm]\u3068\u306a\u308a\uff0c\u4eca \u56de\u306e\u8a2d\u8a08\u5024 20[mm]\u306f\u5f37\u5ea6\u4e0a\u554f\u984c\u306e\u7121\u3044\u3053\u3068\u304c\u308f\u304b\u3063\u305f\uff0e\u56f3 12 \u306b\u6700\u7d42\u7684\u306a\u4fdd\u6301\u5668\u30fb\u51fa\u529b\u8ef8\u306e\u5916\u89b3\uff0c\u8868 3 \u306b\u51fa\u529b\u8ef8 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The material is phosphorus bronze. The torsion strength of the smallest diameter of the shaft was calculated and was confirmed to have no problems.\nMaterial Phosphor bronze\n(Cu 90.3%, Sn 9.3%, P 0.16%)\nNumber of retainer pocket - 8\nNominal bending stress [N/mm 2 ] \u03c3S 30.7\nShaft diameter [mm] d\u00b4 20\nTable 3 Final dimensions of the output shaft with retainer\nfrom the motor is measured by the torque meter and tachometer. Its power is transmitted to a gear pair with a gear reduction ratio of 1. The torque meter and tachometer are also set on the output side, making it possible to measure the power.", + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\n6\u30fb1 \u8a55\u4fa1\u6307\u6570\u306e\u5b9a\u7fa9 \u5165\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nin\uff0c\u51fa\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nout\uff0c\u5165\u529b\u5074\u30c8\u30eb\u30af\u306e\u8a08\u6e2c\u5024 Tin\uff0c\u51fa\u529b\u5074\u30c8\u30eb\u30af\u306e\u8a08\u6e2c\u5024 Tout \u3092\u7528\u3044\u3066\uff0c\u5f0f(29)\u304b\u3089\u52d5\u529b\u4f1d\u9054\u52b9\u7387 \u03b7eff\u306e\u7b97\u51fa\u3092\u884c\u3063\u305f\uff0e\u6b21\u306b\uff0c\u7406\u8ad6\u4e0a\u306e\u6e1b\u901f\u6bd4 ith\u3068\u5165\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nin\u3092 \u51fa\u529b\u56de\u8ee2\u901f\u5ea6\u306e\u5b9f\u6e2c\u5024 Nout\u3067\u5272\u3063\u305f\u5b9f\u6e2c\u6e1b\u901f\u6bd4 iac\u3092\u7528\u3044\u3066\uff0c\u6b21\u306e\u5f0f(30)\u304b\u3089\u3059\u3079\u308a\u7387 S \u306e\u7b97\u51fa\u3092\u884c\u3063\u305f\uff0e\u306a\u304a\uff0c \u5f93\u6765\u7814\u7a76\u3092\u57fa\u306b\uff0c\u672c\u7814\u7a76\u3067\u7528\u3044\u305f\u8ef8\u53d7\u54c1\u756a\u300cNU306E\u300d\u306e\u7406\u8ad6\u4e0a\u306e\u6e1b\u901f\u6bd4 ith\u3092\u8a08\u7b97\u3057\u305f\u7d50\u679c ith=2.543\u3067\u3042\u3063\u305f\uff0e\ninin\noutout eff\nTN\nTN\n\n \uff0829\uff09\n1001 th ac i i S \uff0830\uff09\n6\u30fb2 \u4f1d\u9054\u53ef\u80fd\u30c8\u30eb\u30af\u3068\u6e1b\u901f\u6bd4\u306e\u78ba\u8a8d \u5165\u529b\u56de\u8ee2\u901f\u5ea6\u3092\u305d\u308c\u305e\u308c\uff0c50\uff0c100\uff0c150\uff0c200[rpm]\u306b\u3057\u3066\uff0c\u4f1d\u9054\u53ef\u80fd\u30c8\u30eb\u30af\u3068\u6e1b\u901f\u6bd4\u306e\u78ba\u8a8d\u3092\u884c\u3063\u305f\uff0e\u5b9f\u9a13\u65b9 \u6cd5\u306f\uff0c\u51fa\u529b\u5074\u306e\u8a2d\u5b9a\u30c8\u30eb\u30af\u3092\u5f90\u3005\u306b\u5897\u52a0\u3055\u305b\u3066\uff0c4\u7ae0\u3067\u76ee\u6a19\u3068\u3057\u305f 20[N\u30fbm]\u304c\u904b\u8ee2\u53ef\u80fd\u304b\u3069\u3046\u304b\u306b\u95a2\u3057\u3066\u78ba\u8a8d\u3057 \u305f\uff0e\u56f3 15\uff0c\u56f3 16\uff0c\u306b\u5165\u529b\u56de\u8ee2\u901f\u5ea6\u304c 100\uff0c200[rpm]\u306e\u3068\u304d\u306e\u5b9f\u9a13\u7d50\u679c\u3092\u793a\u3059\uff0e\n\u3044\u305a\u308c\u306e\u56de\u8ee2\u901f\u5ea6\u3067\u3082\uff0c\u524d\u8ff0\u306e\u8a08\u7b97\u901a\u308a\u306e\u51fa\u529b\u30c8\u30eb\u30af 20[N\u30fbm]\u307e\u3067\u904b\u8ee2\u304c\u53ef\u80fd\u3067\u3042\u3063\u305f\uff0e\u3055\u3089\u306b\uff0c\u3059\u3079\u3066\u306e\u904b \u8ee2\u9818\u57df\u3067\u306e\u5b9f\u6e2c\u6e1b\u901f\u6bd4\u306e\u5e73\u5747\u306f\u5165\u529b\u56de\u8ee2\u901f\u5ea6 100[rpm]\u306e\u3068\u304d\u306b\u306f iac=2.539\uff0c200[rpm]\u306e\u3068\u304d\u306b\u306f iac=2.524 \u3068\u7406\u8ad6 \u4e0a\u306e\u6e1b\u901f\u6bd4 ith\u3067\u3042\u308b 2.543 \u306b\u8fd1\u3044\u5024\u3068\u306a\u3063\u305f\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u4e88\u5727\u30ea\u30f3\u30b0\u3092\u7528\u3044\u305f\u4e88\u5727\u65b9\u6cd5\u3067\u3082\u554f\u984c\u306a\u304f\u8a2d\u8a08\u5024\u901a \u308a\u306e\u30c8\u30eb\u30af\u3092\u4f1d\u9054\u3067\u304d\u308b\u3053\u3068\u304c\u78ba\u8a8d\u3067\u304d\u305f\uff0e\u307e\u305f\uff0c\u3044\u305a\u308c\u306e\u56de\u8ee2\u901f\u5ea6\u3067\u3082\u5b9f\u6e2c\u6e1b\u901f\u6bd4\u306f\u5b89\u5b9a\u3057\u305f\u6570\u5024\u3092\u5f97\u3066\u3044\u305f\uff0e" + ] + }, + { + "image_filename": "designv8_17_0001999_f_version_1692867577-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001999_f_version_1692867577-Figure5-1.png", + "caption": "Figure 5. 2D electro-hydraulic proportional directional valve with double solenoid drive [77].", + "texts": [ + " [77] used two proportional solenoids to drive the spool of a 2D electro-hydraulic proportional directional valve. A thrust\u2013twist coupling connected the proportional solenoids to the spool and converted the axial linear motion of the proportional solenoids into an axial linear and rotational motion of the spool. During control, the displacement of the spool was adjusted by varying the current of the two proportional solenoids. The 2D electro-hydraulic proportional directional valve with the double solenoid drive is shown in Figure 5. Processes 2023, 11, 2537 7 of 26 Processes 2023, 11, x FOR PEER REVIEW 7 of 28 flow directional valve, adding an LVDT (linear variable displacement transducer) to detect the displacement of the main spool to achieve closed-loop control. By optimizing the input signals of the two proportional solenoids, the control dead zone of the proportional directional valve was reduced. Meng B et al. [77] used two proportional solenoids to drive the spool of a 2D electro-hydraulic proportional directional valve. A thrust\u2013twist coupling connected the proportional solenoids to the spool and converted the axial linear motion of the proportional solenoids into an axial linear and rotational motion of the spool. During control, the displacement of the spool was adjusted by varying the current of the two proportional solenoids. The 2D electro-hydraulic proportional directional valve with the double solenoid drive is shown in Figure 5. The double solenoid drive is generally used in proportional directional valves, where the use of two solenoids allows the spool to move in both directions, thus enabling the direction of fluid flow in the directional valve to be changed. In addition to proportional directional valves, double solenoids can also be used for proportional flow valves. In the double solenoid drive method, a proportional solenoid is used to drive the spool, allowing for proportional adjustment of the spool. To accurately control the spool position, a displacement sensor is usually installed at one end of the spool to detect the spool displacement, which is then transmitted to the controller for closed-loop control" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003512_e_download_9236_8414-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003512_e_download_9236_8414-Figure7-1.png", + "caption": "Figure 7: First Re-designed model with FEA results", + "texts": [ + " Figure 6 (a) and (b) shows the different designs obtained after the process along with the processing time and resultant weight of the rod. Next step is conventional or practically possible redesigning of our product inspired by generative design results. We redesigned three different types of models in a way that it can be produce by conventional methods or CAM (Computer Aided Manufacturing). Thereafter, FEA is performed once again to check the feasibility of the redesigned models, results along with model designs can is shown in Figure 7-9. Once all completed, the design will be subjected to practical load testing to cross-check the real life feasibility of the models. After this investigation we can conclude that the generative design has a significant role in the industry in general and the machine design especially, in this investigation we have designed an articulated rod of a rotary engine based on a realistic dimensions and boudary conditions, the CAD model has been built using Solid Edge software, and the FEA has been done on the same software as well, in order to introduce it to the generative design part which is the main aim of this analysis" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002151_272X.2016.5.02_77271-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002151_272X.2016.5.02_77271-Figure1-1.png", + "caption": "Fig. 1. Calculation model of the turbo-generator with magnetic field distribution at the unbalanced load", + "texts": [ + " Numerical methods for the calculation of the magnetic fields are removed restrictions on the account of actual constructive shapes of electric machines as a whole and their elements, on account of the magnetic saturation. Here, powerful modern computers allow you to do this in the statics and dynamics. Examples of such studies are presented in papers by the author [7, 8] and other researchers, for example, in [9]. Object of investigations. Demonstration calculations are carried out on a three-phase two-pole TG, a cross section of the electromagnetic system of which is shown in Fig. 1. It has rated: power PN = 35 MW, phase voltages UsN = 6.3 kV and current IsN = 2315 A at the stator winding circuit \u2013 \u00abtriangle\u00bb; power factor cossN = 0.8; frequency fs = 50 Hz. Active stator length la = 2.7 m; nonmagnetic gap \u2013 27 mm; rotor radius \u2013 0.408 m; on the phase stator winding there are Ns = 18 consecutive turns, its relative shortening s = 22/27; phase winding resistances: active Rs = 0.00537 ; reactive from a frontal scattering Xv = 0.134 ; in the rotor winding the turns number Nr = 224", + " In this paper, at unbalanced loading phase currents are defined by their temporal functions: )cos( IamaA tIi ; )cos( IbmbB tIi ; (1) )cos( IcmcC tIi , where =2 fs is the angular frequency; Ima, Imb, Imc are the amplitudes of currents determined by their abovementioned RMS. The initial phase of currents Ia, Ib, Ic determined initially by summing the vectors in Fig. 2 and therefore rigidly connected with each other. They were then turned on all selected by numerical experiments a certain angle so that when = 0 resulting MMF of the stator winding Fs is directed along the longitudinal rotor axis d which is shown in Fig. 1. In such a way the necessary initial phase are received: Ia = 9.15\u00b0; Ib = \u2013117.56\u00b0; Ic = \u2013237.88\u00b0. In (1) additional rotation angle for all currents, respectively, rotates vector Fs of MMF at the same angle with the proviso that when at predetermined stator currents and excitation current to provide the required output 18 ISSN 2074-272X. Electrical Engineering & Electromechanics. 2016. no.5 electric power of TG as presented in [11]. Placed in such a position vector Fs is shown in Fig. 1. Together with the vector of MMF of field winding Ff they form a conditional resulting MMF at the load mode Fl. The system of phase relationships of electromagnetic quantities in TG is presented in detail in [11] for the mode of its symmetrical loading. This angle and field current If are determined by a special technique from the condition that they must provide the nominal output data of the TG: UsN voltage and power factor cossN which makes at a rated current of the stator IsN rated active power PN", + " On this basis by numerical experiments using already called \u00df value as the first approximation, it was found that the rated power at unbalanced loading is obtained at = \u2013167.2 and presented excitation current If = 632 A. The vector diagram of formed asymmetrical current system and obtained as results of computation other electromagnetic quantities calculation is presented below. For the analysis of electromagnetic processes in the active part of the TG magnetic field at given its winding currents is calculated in 2D formulation in its cross section (Fig. 1). This field is described by the known differential equation zz JkAk \u03bc rot 1 rot , (2) where Az, Jz are axial components of the magnetic vector potential (MVP) and current density; is the absolute magnetic permeability; k is the ort by axial axis z. Organization of calculation of temporal functions of electromagnetic quantities. The values stated with the purpose of the work of values of MFD, MFL and EMF are determined based on the calculation of the magnetic field of TG and their temporal functions by such multiposition calculations [7, 8] for time series with step t: tk=t(k\u20131); k=1, 2, ", + " Therefore, functions of actual quantities taking into account the TG magnetic field periodicity are formed at the rotor rotation from 0 to 180\u00b0 with angular step of 1\u00b0, i.e. \u041a equals to 180. The magnetic field based on (2) is calculated by the finite element method taking into account the saturation of the core by the FEMM software [12]. Operations during its work on the calculation of the field, the definition of electromagnetic parameters and the formation of temporary functions are carried out by the control program written on the algorithmic language Lua [13]. Magnetic field distribution at the unbalanced loading mode at initial time is shown in Fig. 1 by magnetic field lines. Note that the structure of the magnetic field corresponds approximately to what was the case in the symmetrical loading. Temporal functions of the magnetic flux density. The base quantity used in electromagnetic calcula- tions is the magnetic flux density in the form of its radial and angular components as well as its module: z r A r B 1 ; r A B z ; 22 BBB r . (6) Note that in areas of the laminated cores the FEMM software \u00aboutputs\u00bb MFD values \u00absmeared\u00bb for the whole of their axial length", + " A general interest is the nature of these functions the obtaining of which is, in principle, it has been possible on the basis of multiposition calculations of the magnetic fields. This is a non-trivial approach to electric machines in general. Magnetic flux leakage and EMF of stator phase windings. As it was already presented in [7] the base of the EMF is the temporal MFL function of the stator phase winding. MFL is obtained by the MVP distribution. For example, for each of the six phase zones (Fig. 1) MFL is determined by the formula S z as dSA S lN , (8) there S is the sectional area by conductive phase zone\u2019s elements. Determination of the MFL by the formula (8) is not difficult since to determine S and the integral in the integrated in the FEMM software Lua script there are appropriate procedures [14]. For all phase winding, for example for the phase A, MFL is obtained by the formula 'sAsAA , (9) there sA \u0438 'sA are the MFL in the phase zones A and 'A (Fig. 1) determined by formula (8). On this base in the process of already described calculation of the rotating magnetic field the discrete temporal MFL function is formed s(tk), k=1,2,...,\u041a, (10) where the index s is the generalized letter of any phase windings: A, B, C. The function s(tk) is decomposed as in [7, 8] according to known rules in the cosine harmonic series of odd harmonics taking into account the condition (5) gN ms t ...5,3,1 , )cos( , (11) where the summation over harmonics numbers is possible until Ng number which, in principle, is limited by accepted in (5, 10) value of K" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003588_O201305740751996.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003588_O201305740751996.pdf-Figure7-1.png", + "caption": "Fig. 7. Total Force and Moment", + "texts": [], + "surrounding_texts": [ + "QTW \ube44\ud589\uccb4\uc758 \ub3d9\uc5ed\ud559 \ubaa8\ub378\ub9c1\uc744 \uc704\ud574\uc11c\ub294 \ud56d \uacf5\uae30\uc758 \uc9c8\ub7c9\ubcc0\ud654\ub098 \uc9c8\ub7c9\ubd84\ud3ec\uc758 \ubcc0\ud654\uac00 \uc5c6\ub2e4\uace0 \uac00 \uc815\ud558\uace0 \ud56d\uacf5\uae30\uc5d0 \uc791\uc6a9\ud558\ub294 \uacf5\uae30\uc5ed\ud559\uc801 \ud798, \ucd94\ub825 \uc5d0 \uc758\ud55c \ud798, \uc911\ub825\uc5d0 \uc758\ud55c \ud798 \ub4f1\uc744 \uace0\ub824\ud55c\ub2e4. \ud56d\uacf5 \uae30\uc5d0 \uace0\uc815\ub418\uc5b4 \uc788\ub294 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\uac00 \uad00\uc131\uc88c\ud45c \uacc4\uc5d0 \ub300\ud574 \ud68c\uc804\ud558\uace0 \uc788\ub2e4\uace0 \uac00\uc815\ud558\uace0 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\uc5d0 \ub300\ud558\uc5ec \uac01\uc131\ubd84\ubcc4\ub85c \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc744 \uc815\ub9ac \ud558\uba74, Fig. 3\uacfc \uac19\uc774 \uc124\uacc4\ub41c \ube44\ud589\uccb4 \ud615\uc0c1\uc5d0 \ub300\ud574 6\uc790\uc720\ub3c4 \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc744 \uc5bb\uc744 \uc218 \uc788\ub2e4[6]. (1) (2) (3) (4) (5) (6) \uc704\uc758 \uc6b4\ub3d9\ubc29\uc815\uc2dd\uc5d0\uc11c \ubaa8\ub4e0 \ud798\uacfc \ubaa8\uba58\ud2b8\ub294 \ud56d\uacf5\uae30 \uc5d0 \uc791\uc6a9\ud558\ub294 \uac01 \ubd80\ubd84\uc758 \ud798\uacfc \ubaa8\uba58\ud2b8\uc758 \ud569\uc73c\ub85c \ud45c \ud604\ud560 \uc218 \uc788\ub2e4. \u2211 (7) \u2211 (8) \uc5ec\uae30\uc11c \uc544\ub798\ucca8\uc790 \ub294 \uac01\uac01 \ud504\ub85c \ud3a0\ub7ec \ud6c4\ub958 \ubd80\ubd84\uc5d0\uc11c\uc758 Slip stream \ud6a8\uacfc\uc5d0 \uc758\ud574 \ubc1c\uc0dd\ub418\ub294 \uacf5\uae30\uc5ed\ud559\uc801 \ud798, \ud6c4\ub958\uc5d0 \uc7a0\uae30\uc9c0 \uc54a\ub294 \uc8fc \uc775 \uba74\uc801\uc5d0 \ub300\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798, \uadf8\ub9ac\uace0 \ud504\ub85c\ud3a0\ub7ec \uc5d0 \uc758\ud574 \ubc1c\uc0dd\ub418\ub294 \ucd94\ub825 \ubc0f \uc911\ub825\uc5d0 \uc758\ud55c \ud798\uc744 \ub098 \ud0c0\ub0b8\ub2e4. Fig. 4\ub294 \ud504\ub85c\ud3a0\ub7ec \ud6c4\ub958\uc5d0 \uc7a0\uae30\ub294 \uc8fc\uc775 \uba74\uc801\uacfc \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84\uc744 \ubcf4\uc5ec\uc8fc\uace0 \uc788\ub2e4. \uc774\ub7ec\ud55c \ubcf5\uc7a1\ud55c \ub3d9\uc5ed\ud559\uc801 \ud2b9\uc131\uc744 \ubd84\uc11d\ud558\uae30 \uc704 \ud558\uc5ec \ubcf8 \ub17c\ubb38\uc5d0\uc11c\ub294 QTW\uc758 \uc885\ucd95 \ubc18\uc751\ub9cc\uc744 \uace0\ub824 \ud558\uc600\uc73c\uba70 \ub864 \uc6b4\ub3d9\uacfc \uc694 \uc6b4\ub3d9\uc740 \uace0\uc815\ub418\uc5b4 \uc788\ub2e4\uace0 \uac00\uc815\ud558\uc600\ub2e4. \ub610\ud55c \ud68c\uc804\uc775 \ubaa8\ub4dc\uc640 \ucc9c\uc774\ubaa8\ub4dc \uc601\uc5ed \uc5d0\uc11c\uc758 \ud574\uc11d\uc744 \uc218\ud589\ud558\uc600\ub2e4. \ud504\ub85c\ud3a0\ub7ec\uc5d0 \uc758\ud55c \ucd94\ub825 \uac01 \ud504\ub85c\ud3a0\ub7ec\uc5d0 \ubc1c\uc0dd\ub418\ub294 \ucd94\ub825\uc740 Momentum Theory\ub97c \uae30\ucd08\ub85c \ud55c\ub2e4. Fig. 5\uc5d0\uc11c \ud504\ub85c\ud3a0\ub7ec\ub97c \uc9c0\ub098\ub294 \uacf5\uae30\ud750\ub984\uc744 \ud45c\ud604\ud558\uace0 \uc788\ub2e4. Momentum Theory\uc640 Bernoulli's Equation\uc744 \uc774\uc6a9\ud558\uc5ec \uc720\ub3c4\uc18d\ub3c4\uc640 \ucd94\ub825\uc744 \uacc4\uc0b0\ud55c\ub2e4. \ud504\ub85c\ud3a0\ub7ec \uae30\uc900\uc73c\ub85c z\ucd95\uc758 \uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \uae43 \ud615\uc0c1 \ub4f1\uc744 \uace0\ub824\ud55c \uc18d\ub3c4\uc640 \ucd94\ub825\uc740 \ub2e4\uc74c\uacfc \uac19\uc774 \ud45c\ud604\ub41c\ub2e4[7]. (9) \u221e (10) \uc2dd(9)\uc5d0\uc11c \ub294 \uac01\uac01 \ud504\ub85c\ud3a0\ub7ec\uc758 \ud68c\uc804\ub514\uc2a4\ud06c\uc5d0 \uc218\uc9c1\uc778 \ubc29\ud5a5\uc758 \uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \uac01\uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \ud68c\uc804\ub514\uc2a4\ud06c \ubc18\uc9c0\ub984, \ud504\ub85c\ud3a0\ub7ec \ub4a4\ud2c0\ub9bc \uc815\ub3c4\ub97c \ub098\ud0c0\ub0b4\ub294 \uc0c1\uc218\uc774\uba70 \uc2dd(10)\uc5d0\uc11c\uc758 \u221e \uc740 \uac01\uac01, \ud504\ub85c\ud3a0\ub7ec\ub97c \uc9c0\ub09c \ud6c4\ub958\uc758 \uc18d\ub3c4, \ud504\ub85c\ud3a0\ub7ec\uc758 \uc591\ub825 \uae30\uc6b8\uae30, \ud504\ub85c\ud3a0\ub7ec\uc758 \ube14\ub808 \uc774\ub4dc \uc218, \ud504\ub85c\ud3a0\ub7ec \ucf54\ub4dc\uc758 \uae38\uc774\ub97c \ub098\ud0c0\ub0b8\ub2e4. \ud504\ub85c\ud3a0\ub7ec\ub97c \uc9c0\ub09c \uc720\ub3c4\uc18d\ub3c4 \ub294 \uc2dd(11)\uc640 \uac19\uc774 \ud45c\ud604\ub41c\ub2e4. \u221e \u2032 (11) \uc5ec\uae30\uc11c \u2032\ub294 \uc6d0\uac70\ub9ac \uc18d\ub3c4(Far-Field Velocity)\ub85c \uc2dd(12)\uc640 \uac19\uc774 \ub098\ud0c0\ub0bc \uc218 \uc788\ub2e4. \u2032 (12) \uc2dd(11)\ub97c \uc2dd(13)\uc758 Newton-Raphson method \ubc18 \ubcf5 \uae30\ubc95\uc744 \uc0ac\uc6a9\ud558\uc5ec \uc720\ub3c4\uc18d\ub3c4\ub97c \uad6c\ud560 \uc218 \uc788\ub2e4. (13) \uc5ec\uae30\uc11c \ub294 \uc2dd(14)\uc640 \uac19\ub2e4. \u221e \u221e (14) \uc218\ub834\uc2dc\uae4c\uc9c0 \ubc18\ubcf5 \uacc4\uc0b0\ud558\uc5ec \uad6c\ud55c \uc720\ub3c4\uc18d\ub3c4 \ub97c \uc2dd(15)\uc5d0 \uc801\uc6a9\ud558\uba74 \ub2e4\uc74c\uacfc \uac19\uc774 \ucd94\ub825\uc744 \uad6c\ud560 \uc218 \uc788\ub2e4. \u221e (15) Slip stream \ud6a8\uacfc Slip stream\uc774\ub780 \ud504\ub85c\ud3a0\ub7ec\uac00 \ucd94\ub825\uc744 \uc77c\uc73c\ud0a4\uba74 \uc11c \ud68c\uc804\ud560 \ub54c \uadf8 \ud68c\uc804\uba74\uc758 \ub4a4\ucabd\uc5d0 \ud504\ub85c\ud3a0\ub7ec\uc758 \uc804 \uc9c4 \uc18d\ub3c4\ubcf4\ub2e4 \ud070 \uc720\uc18d\uc758 \uae30\ub958\uac00 \uc0dd\uae30\ub294 \uac83\uc744 \ub9d0\ud55c \ub2e4. QTW\ub294 \ud504\ub85c\ud3a0\ub7ec\uac00 \uc8fc\uc775\uc5d0 \uace0\uc815\ub418\uc5b4 \ud2f8\ud2b8\uc2dc \uac19\uc774 \uc6c0\uc9c1\uc774\uae30 \ub54c\ubb38\uc5d0 Slip stream \ud6a8\uacfc\ub85c \uc778\ud574 \ud6c4\ub958\uc5d0 \uc7a0\uae30\ub294 \ubd80\ubd84\uc5d0 \ub300\ud574 \uc77c\uc815\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc774 \ubc1c\uc0dd\ud558\uac8c \ub41c\ub2e4. Fig. 6\uc740 \ub85c\ud130\uc5d0 \uc758\ud574 \ubc1c\uc0dd \ub418\ub294 \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud574 \ubc1c\uc0dd\ub418\ub294 \uc5d0\uc5b4\ud3ec\uc77c\uc758 \uc591\ub825\uacfc \ud56d\ub825\uc744 \uc124\uba85\ud55c \uadf8\ub9bc\uc774\ub2e4. Fig. 6\uc5d0\uc11c \uc8fc\uc775\uc758 \uc591\ub825\uacc4\uc218\ub294 \uc2dd(16)\uc73c\ub85c \ub098\ud0c0\ub0bc \uc218 \uc788\uc73c\uba70, \uc774 \ub54c \ubc1b\uc74c\uac01\uc5d0 \ub530\ub978 \uc591\ub825\uacc4\uc218 \ub294 \ud1b5\uc0c1\uc801\uc778 \uac12\uc778 0.1/deg\ub85c \uc124\uc815\ud558\uc600\ub2e4. (16) \ub294 \ud504\ub85c\ud3a0\ub7ec \ud6c4\ub958\uc5d0 \ub300\ud55c \uc8fc\uc775\uc758 \ubd99 \uc784\uac01\uacfc \uac19\uc740 \ud6a8\uacfc\uc640 \ucea0\ubc84\ub97c \uac00\uc9c4 \uc5d0\uc5b4\ud3ec\uc77c\uc774\ub77c\ub294 \uc810\uc744 \uace0\ub824\ud558\uc5ec 3\ub3c4\ub85c \uc124\uc815\ud558\uc600\ub2e4. \ub294 \uc870\uc885\uba85 \ub839\uc778 \ud50c\ub7a9\uac01\ub3c4\uc5d0 \ub530\ub978 \uc591\ub825\uacc4\uc218 \uc99d\uac00\ub97c \uace0\ub824\ud55c \ud56d\uc73c\ub85c 0.02\ub85c \uac00\uc815\ud588\uc73c\uba70 \ub294 \ud50c\ub7a9\uc758 \ubcc0\uc704\uc774 \ub2e4. (17) \uc2dd(17)\uacfc \uac19\uc774 \uc591\ub825\uacc4\uc218\ub97c \uc801\uc6a9\ud558\uc5ec \ud6c4\ub958\uc5d0 \uc7a0 \uae30\ub294 \ubd80\ubd84\uc5d0 \ub300\ud55c \uc591\ub825\uacfc \ud56d\ub825\uc744 \uad6c\ud560 \uc218 \uc788\uc73c \uba70, Fig. 4\uc640 \uac19\uc774 \ud6c4\ub958\uc5d0 \uc7a0\uae30\ub294 \ubd80\ubd84\uc758 \uba74\uc801\uc774 \uc77c\uc815\ud558\uc9c0 \uc54a\uc740 \uc810\uacfc \uc124\uacc4\ub41c QTW \ube44\ud589\uccb4\uc758 \uae30\ud558 \ud559\uc801 \ud615\uc0c1\uc744 \uace0\ub824\ud558\uc5ec \ud504\ub85c\ud3a0\ub7ec \uc9c0\ub984\uc758 70%\ub97c \ud3c9\uade0\uc801\uc73c\ub85c \uc7a0\uae30\ub294 \uc601\uc5ed\uc758 \uc2a4\ud32c\uc73c\ub85c \uac00\uc815\ud558\uace0 \uba74\uc801 \ub97c \uacc4\uc0b0\ud558\uc600\ub2e4. \ud56d\ub825\ubd80\ubd84\uc5d0\uc11c\ub294 QTW \ud615\uc0c1\uc758 \ud2b9\uc131\uc0c1 \ud504\ub85c\ud3a0\ub7ec\uc758 \ud6c4\ub958\uac00 \uc8fc\uc775 \ub05d\ub2e8\uae4c \uc9c0 \uc7a0\uae30\uae30 \ub54c\ubb38\uc5d0 \uc720\ud55c\ud55c \ub0a0\uac1c\uc758 \ud2b9\uc131\uc778 Vortex\uc5d0 \uc758\ud55c Downwash\uc640 Downwash\uc5d0 \uc758 \ud55c \uc720\ub3c4\ud56d\ub825\uc744 \ubb34\uc2dc\ud558\uace0 \ud615\uc0c1\ud56d\ub825\ub9cc\uc744 \uace0\ub824\ud558 \uc600\ub2e4. \uc2dd(17)\uc5d0\uc11c \ub3d9\uc555\uc740 \uc2dd(18)\uacfc \uac19\uc73c\uba70, \uc5ec\uae30 \uc11c \uc720\ub3c4\uc18d\ub3c4\ub294 \uc2dd(14)\uc5d0\uc11c \uacc4\uc0b0\ub41c \ud504\ub85c\ud3a0\ub7ec\uc758 \ud6c4\ub958\uc18d\ub3c4\uc5d0 \ud574\ub2f9\ub41c\ub2e4. (18) Slip stream\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\ub4e4\uc740 \ud2f8\ud2b8 \uac01\uc774\ub098 \ube44\ud589\uccb4 \uc790\uc138\uac01\uc5d0 \ubb34\uad00\ud558\uba70 \ud504\ub85c\ud3a0\ub7ec\uc5d0 \uc758 \ud574 \ubc1c\uc0dd\ub418\ub294 \ud6c4\ub958 \uc720\ub3c4\uc18d\ub3c4\uc640 \ud50c\ub7a9\ubcc0\uc704\uc5d0\ub9cc \uc601\ud5a5 \uc744 \ubc1b\uac8c \ub41c\ub2e4. Total force and Moment \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc740 Fig. 7\uacfc \uac19\uc774 \ud2f8\ud2b8 \uac01\ub3c4\uc5d0 \ub530\ub77c \uac01 \ud798\uc758 \ubc29\ud5a5\uc774 \ub2ec\ub77c\uc9c0\uae30 \ub54c\ubb38\uc5d0 \uac01 \ucd95 \ubc29\ud5a5\uc758 \ud798\uc758 \ud06c\uae30\ub97c \uacc4\uc0b0\ud560 \ub54c \ud2f8 \ud2b8 \uac01\ub3c4\ub97c \uace0\ub824\ud558\uc5ec\uc57c \ud55c\ub2e4. \uacc4\uc0b0\ub41c \ucd94\ub825\uacfc \ud6c4\ub958\uc5d0 \uc758\ud55c \uacf5\uae30\uc5ed\ud559\uc801\uc778 \ud798\uacfc \ubaa8\uba58\ud2b8\ub294 \ub2e4\uc74c\uacfc \uac19\uc774 \uae30\uccb4 \uace0\uc815 \uc88c\ud45c\uacc4\ub85c \ud45c\ud604 \ub420 \uc218 \uc788\ub2e4. sin (19) cos (20) cos sin cos (21) \uac01 \ub0a0\uac1c\uc5d0\uc11c \uc5bb\uc5b4\uc9c4 \ud798\ub4e4\uc744 \uc131\ubd84\ubcc4\ub85c \ub2e4\uc2dc \uc815\ub9ac \ud574 \ubcf4\uba74 \ub2e4\uc74c\uacfc \uac19\ub2e4. cossin (22) sin (23) sincos (24) cos (25) \ud2f8\ud2b8 \uac01\ub3c4\uc5d0 \ub530\ub77c \uac01 \ud798 \uc131\ubd84\ub4e4\uc744 \uae30\uccb4\uace0\uc815 \uc88c\ud45c\uacc4\ub85c \ubcc0\ud658\ud558\uc600\uc73c\uba70, \uac01 \ucd95\ubc29\ud5a5\uc758 \uacf5\uae30\uc5ed\ud559\uc801 \ud798\uc5d0 \ud6c4\ub958\uc5d0 \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84\uc5d0 \ub300\ud55c \ud798\uc744 \ucd94\uac00 \ud574 \uc8fc\uc5c8\ub2e4. \ud68c\uc804\uc775\ubaa8\ub4dc\uc5d0\uc11c\ub294 \uc7a0\uae30\uc9c0 \uc54a\ub294 \ubd80\ubd84 \uc774 \ud56d\ub825\uc73c\ub85c \uc791\uc6a9\ud558\uac8c \ub418\uace0 \ucc9c\uc774\ubaa8\ub4dc\ub97c \uac70\uccd0 \uace0 \uc815\uc775\ubaa8\ub4dc\ub85c \ud2f8\ud2b8\ub428\uc5d0 \ub530\ub77c \ud56d\ub825\uc740 \uc904\uace0 \uc591\ub825\uc740 \uc99d\uac00\ud558\uac8c \ub41c\ub2e4. \uc2dd(21)\uc758 \ud53c\uce6d\ubaa8\uba58\ud2b8\ub294 \uc804\ubc29\uc8fc\uc775 \uacfc \ud6c4\ubc29\uc8fc\uc775\uc758 \ucd94\ub825, \uc591\ub825 \ubc0f \ud56d\ub825\uc758 \ucc28\uc774\uc5d0 \uc758 \ud574 \ud06c\uae30\uac00 \uacb0\uc815\ub41c\ub2e4." + ] + }, + { + "image_filename": "designv8_17_0001671_O201325954480036.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001671_O201325954480036.pdf-Figure3-1.png", + "caption": "Fig. 3 Constraint condition of model 2", + "texts": [ + " 1 Meshes of models Table 2 Material property Young's Modulus (MPa) 71000 Poisson's Ratio 0.33 Density (g/cc) 2.77 Tensile Yield Strength (MPa) 280 Tensile Ultimate Strength (MPa) 310 \uadf8 \uad6c\uc870\uac15\ub3c4 \ubc0f \ub0b4\uad6c\uc131\uc744 \uac80\ud1a0, \uc608\uce21\ud558\ub294\ub370 \ud65c\uc6a9\uc774 \ud074 \uac83\uc73c\ub85c \uc0ac\ub8cc \ub41c\ub2e4 [3-5] . 2. \ubaa8\ub378\ub9c1 \ubc0f \uacbd\uacc4 \uc870\uac74 2.1 \uc5f0\uad6c \ubaa8\ub378 \ubcf8 \uc5f0\uad6c \uc55e \ubc94\ud37c \ubaa8\ub378\uc758 \ud06c\uae30\ub294 \uae38\uc774\uac00 1990.7 mm\uc774\uba70, \ub113\uc774\uc640 \uae4a\uc774\ub294 \uac01\uac01 537.75 mm\uc640 564.44 mm\uc774\ub2e4. \ubaa8\ub378\uc758 \ud615\uc0c1\uc740 \uc2e4\uc81c \ubc94\ud37c\uc758 \ubaa8\uc591\uc744 \ucc38\uc870\ud558\uc5ec CATIA\ub97c \uc774\uc6a9\ud558\uc5ec \ubaa8\ub378\ub9c1\ud55c \ud6c4 ANSYS \ub97c \uc774\uc6a9\ud558\uc5ec \ud574\uc11d\ud558\uc600\ub2e4. \ud574\uc11d \ub300\uc0c1\uc758 \uba54\uc2dc \ubaa8\uc591\uc740 Fig. 1(a)\uacfc Fig. 1(b) \uac19\uace0 model 1\uc758 \uc808\uc810\uc218 \ubc0f \uc694\uc18c\uc218\ub294 \uac01\uac01 30416 \ubc0f 14716\uc774\uace0 model 2\uc758 \uc808\uc810\uc218 \ubc0f \uc694\uc218\ub294 \uac01\uac01 27577 \ubc0f 13161\uc774 \ub2e4. \uadf8\ub9ac\uace0 Table 2\ub294 Aluminum Alloy\uc758 \ubb3c\uc131\uce58\ub97c \ub098\ud0c0\ub0b8\ub2e4 [6] . 2.2 \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74 \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74\uc740 Fig. 2(a)\uc640 Fig. 3(a) \uac19\uc774 \ub098\uc0ac\uad6c\uba4d\uc744 \uc644\uc804 \ud788 \uace0\uc815\uc744 \uc2dc\ucf30\uc73c\uba70, Fig. 2(b)\uc640 Fig. 3(b)\uc5d0\uc11c\ub294 \ubc94\ud37c \uc55e\uc5d0 \ud798\uc744 Z+\ubc29\ud5a5\uc73c\ub85c \uc2e4\uc81c \ucda9\uaca9\uc5d0 \uc791\uc6a9\ub420 \uc218 \uc788\ub294 2500 N\uc758 \ud3c9\uade0\ud558\uc911\uc774 \uac00\ud558\uc600\ub2e4. \u2206\u2219 \u00d7 \u2219sec (1) \ub530\ub77c\uc11c \ucda9\uaca9\ub7c9\uc5d0 \uc758\ud558\uc5ec \uac00\ud574\uc9c0\ub294 \ucda9\uaca9\uc740 \u2219sec (2) 3. \ud574\uc11d\uacb0\uacfc 3.1 \uad6c\uc870\ud574\uc11d \ubaa8\ub378\uc758 \uacbd\uacc4\uc870\uac74\uc740 Fig. 2\uc640 Fig. 3 \uac19\uc73c\uba70, Fig. 4\uc640 Fig. 5\ub294 \ubc94 (a) Fixed support (b) Force condition \ud37c \uc55e\uc5d0 2500 N\uc758 \uc815\uc801 \ud798\uc744 \uac00\ud588\uc744 \ub54c \ub4f1\uac00\uc751\ub825\uacfc \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 4(a)\uc640 Fig. 4(b)\ub294 \ubc94\ud37c\uc758 \ub098\uc0ac\uad6c\uba4d\uc5d0\uc11c \ucd5c \ub300 \ub4f1\uac00\uc751\ub825\uc774 \uac01\uac01 187.09 MPa\uacfc 278.4 MPa\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 5(a)\uc640 Fig. 5(b)\ub294 \ubc94\ud37c \uc717\ubd80\ubd84\uc5d0\uc11c \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc73c\ub85c\uc11c \uac01\uac01 1.3772 mm\uc640 2.675 mm \ubcc0\ud615\ub41c \uac83\uc744 \uc54c \uc218\uac00 \uc788\ub2e4. \uc774 \uadf8\ub9bc\uc744 \ubcf4\uba74 Model 2\uc758 \ubcc0\ud615\ub7c9\uc774 Model 1\uc758 \ubcc0\ud615\ub7c9\ubcf4\ub2e4 \ub354 \ud06c\uae30 \ub54c\ubb38\uc5d0 Model 1\uc758 \uad6c\uc870\uac15\ub3c4\uac00 \ub354 \uc88b\ub2e4\uace0 \uc54c \uc218\uac00 \uc788\ub2e4 [7] . 3.2 \uc9c4\ub3d9 \ud574\uc11d \uc55e \ubc94\ud37c\uc758 \uace0\uc720\uc9c4\ub3d9\uc218\ub97c \uad6c\ud558\uae30 \uc704\ud574 \uc9c4\ub3d9 \ud574\uc11d\uc744 \uc218\ud589\ud558\uc600\uace0, Model 1\uacfc 2\uc5d0 \ub300\ud558\uc5ec \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Fig. 6\uacfc Fig. 7\uc5d0\uc11c \ubcfc \uc218 \uc788\ub2e4. \ub610\ud55c \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Table 3\uacfc Table 4\uc5d0\uc11c \ud655\uc778\ud560 \uc218 \uc788\uc73c\uba70, Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc5d0 \uc11c\uc758 \ucd5c\ub300 \uc804\ubcc0\ud615\ub7c9\uc740 62" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure46-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure46-1.png", + "caption": "Figure 46 P-POD Mk. III Rev. E Bracket", + "texts": [ + " With the panel interfaces the same, the stress in the fastener holes was also the same, but because the part no longer has to go through the bake process, the margin of safety was even higher, going from 9.1 for the last version to 11.6 for the Mk. IV design. Page 61 P-POD Mk. IV Release Mechanism Bracket The next part modified was the NEA Bracket that attaches to the +Y Top Panel. The purpose of the part is to mount the NEA so that it can constrain the door. Unlike the other parts, this part is not required to contain anything, so skeleton or truss structures are acceptable. The original Mk. III Rev. E Bracket is shown below in Figure 46. The objective was to shave some mass off of the part without dramatically decreasing its stiffness, and while maintaining a positive margin of safety. Another odd aspect of the bracket, was that the through holes used to attach the Bracket to the Top Panel were not centered on the part, and were located extremely close to one edge. This was most likely Page 62 a feature left over from a previous version of the P-POD which utilized shear pins in the bracket. The shear pins were removed back when the Mk" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004553_ai.7-12-2021.2314491-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004553_ai.7-12-2021.2314491-Figure20-1.png", + "caption": "Fig. 20.Low carbon steel twist structure", + "texts": [], + "surrounding_texts": [ + "In this work, an attempt has been made to perform ergonomic redesign of passenger seat supporting frame. Different concepts were developed by considering various factors. Further RULA analysis was carried out to determine the effects of various postures on human comfort. Selected concept suitability was determined by FEA. It is observed that the Isection concept with rib shown in figure 25 is the optimum one for given functional and comfort requirments. Table 2 Result for Existing Design Table 3 Weighted Matrix" + ] + }, + { + "image_filename": "designv8_17_0003391_oad_jae.2007.1.47_85-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003391_oad_jae.2007.1.47_85-Figure1-1.png", + "caption": "Fig. 1 - Il nebulizzatore.", + "texts": [ + " a 56,5 rad/s (540 min-1), poich\u00e9 \u00e8 in questa fase di regime variabile che si possono verificare sovrasforzi rispetto ai valori richiesti dal ventilatore a rotazione nominale ed \u00e8 quella nella quale praticamente si sono verificate le rotture. Con i risultati dell\u2019analisi teorica si \u00e8 potuto realizzare una sperimentazione numerica, quindi quantificare l\u2019andamento della coppia effettivamente trasmessa durante il transitorio e, infine, indicare tra le possibili soluzioni, quella ottimale consistente nell\u2019adottare un limitatore di coppia [1, 2, 3, 4 e 5]. Il nebulizzatore in questione (fig. 1) era caratterizzato da un ventilatore centrifugo a pale rivolte all\u2019indietro in grado di elaborare una portata di 13.000 m3/h ed una pressione totale di 7.000 Pa ad un regime corrispondente di 424 rad/s (4.050 min-1). La potenza meccanica richiesta dal ventilatore Pv era di 31,5 kW, mentre il moltiplicatore, privo di limitatore di coppia e con una rapporto di 1:7,5, poteva trasmettere una potenza massima Pm di 33 kW corrispondente ad una coppia massima in uscita di 77,8 Nm a 424 rad/s. Il nebulizzatore, dotato anche di una pompa volumetrica che richiedeva una potenza Pp di 3,5 kW, era accoppiato ad una trattore da frutteto 4RM della potenza PM di 62,5 kW a 262 rad/s (2500 min-1) e una coppia massima CM di 169,5 Nm a 178 rad/s (1700 min-1)", + " La (4) \u00e8 un\u2019equazione differenziale del 1\u00b0 ordine non lineare la cui soluzione \u00e8: (5) dove: t \u00e8 il tempo (s); f \u00e8 la seguente radice: (6) La costante di integrazione Cost \u00e8 determinabile con la condizione iniziale \u03c9v=\u03c9vmin=150 rad/s per t=0: (7) Derivando la (5) e moltiplicando per il momento d\u2019inerzia I, si ottiene la coppia d\u2019inerzia in funzione del tempo t: (8) Combinando poi la coppia fluidodinamica richiesta dal ventilatore Cv, data dalla (1), con la (5), si ottiene una nuova equazione di Cv funzione del tempo t: (9) Sommando infine la (8) con la (9) si ricava l\u2019andamento rispetto al tempo della coppia totale richiesta dal ventilatore al moltiplicatore Cm durante il transitorio. Fig. 1 - The mistblower. Nella condizione di assenza di limitatore di coppia, l\u2019equazione (5) unitamente alla (7), che d\u00e0 la costante di integrazione a partire dalle condizioni iniziali e con i valori precedentemente trovati per le costanti c, d, e, kp, kv e \u03b7t, fornisce l\u2019andamento della velocit\u00e0 angolare della girante \u03c9v in funzione del tempo ed \u00e8 visibile in figura 2. L\u2019aumento graduale del regime del ventilatore si ferma al raggiungimento del valore nominale \u03c9vn previsto di 424 rad/s (4050 min-1), ad opera del regolatore del motore" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003024_3272-019-00421-1.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003024_3272-019-00421-1.pdf-Figure11-1.png", + "caption": "Fig. 11 Comparison of lift and circulation distribution from MICADO and FLOWer", + "texts": [ + " In the same manner the profile drag of the TuLam wing in case of full chord turbulent flow was assessed resulting in CD,Prof,turb = 72dc. For the evaluation of the TuLam wing design the aforementioned MICADO software was employed. For this purpose the aircraft geometry from the preliminary design stage with PrADO and from the detailed aerodynamic design (in particular the airfoil sections) were taken and a new aircraft sizing of the aircraft masses was performed for the design mission. A comparison of lift and circulation distribution between MICADO and FLOWer results show good agreement, Fig.\u00a011. In Fig.\u00a012 the potential block fuel reductions of the TuLam aircraft in comparison with the reference CSR-01 are presented. The CSR-01 is essentially a re-design of the A320-200 obtained with the MICADO software, [12]. It can be seen that for the design mission of 2500NM the TuLam configuration already shows a block fuel reduction of 4% compared to CSR-01, even if the wing is full chord 1 3 turbulent. The main reasons for this gain is a lighter wing resulting from comparatively thick airfoil sections (see Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004367_5_phys-2022-0223_pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004367_5_phys-2022-0223_pdf-Figure3-1.png", + "caption": "Figure 3: (a) 3D simulation model. (b) Disassembled prototype motor.", + "texts": [ + " Anisotropic bonded magnets are gradually being used in various micro-motors due to their high magnetic properties [30]. The magnetic rings used in this article are radially oriented anisotropic bonded magnetic rings. The two-dimensional topology and three-dimensional cross-section of the motor used in this article are shown in Figure 2. The specifications for the motor are listed in Table 1. The motor is modeled in finite element simulation software, and the 3D model specifications used in the simulation are consistent with the actual motor specifications. As shown in Figure 3, (a) is the 3D simulation model, (b) is the disassembled diagram of themodelmotor. In the simulation, the inclination angle range \u03b8sk of the trapezoidal magnetic pole structure is 0\u201350\u00b0, with a step size of 10\u00b0. When \u03b8sk varies from 0\u201350\u00b0, the cogging torque changes as shown in Figure 4 below. It can be seen from Figure 4 that as the skew angle of the magnet increases, the amplitude of the cogging torque gradually decreases, and the period of the cogging torque does not change significantly. The relationship between the peak-to-peak value of cogging torque and the skew angle of the magnet is shown in Figure 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001792_-3_2008_7-3_671__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001792_-3_2008_7-3_671__pdf-Figure1-1.png", + "caption": "Figure 1 Hydraulic Gough-Stewart platform", + "texts": [], + "surrounding_texts": [ + "Several approaches [7] have been proposed for dynamic analysis of Stewart platform. This optimization work is to expand the bandwidth for the control based on generalized natural frequency, and the Lagrangian method is a direct way to get the equivalent mass matrix. To be accurate, the whole leg inertia should be considered. In this paper the legs are decomposed into two parts: the fixed part (to the base) and the moving part (the piston part). The integration method is used to calculate the energy of each part, with this method the energy of particle system includes all the translational and rotational energy. The transformation matrix Ri from the leg coordinate to the base coordinate can be obtained as in [8]. Let the rotation matrix be defined by the roll, pitch, and yaw angles, namely, a rotation of co about the x-axis, followed by a rotation of u about the y-axis, and a rotation of 8 about the z-axis. Thus, it can be defined as (1) The length of the ith leg is given by (2) It yields d=D4 (3) where D is the Jacobian matrix, Piston part The ith leg velocity vector can be written as (4) where {xp yp zp} is the upper platform center coordinate in \u0192\u00b0O, and {xui yui zui} is the ith upper joint coordinate in 10p. In Figure 2, the coordinate of particle dli in ZO is (5) where li is the length between dli and the ith upper joint, {xai yai zai} is the ith down joint coordinate in \u0192\u00b0O, and {xi yi zi} is the ith upper joint coordinate in \u0192\u00b0O. Copyright (c) 2008 by JFPS, ISBN 4-931070-07-X 672 The kinematic energy of dli can be written as dT1i= 1 /2 \u03c1dliv2li (6) where \u0192\u00cf = mpis/lpis, mpis is the piston mass, and is is the piston length. Cylinder part The velocity of the ith upper joint can be written as vi= di\u30fbnli+ wi\u00d7di (7) No rotation is allowed about the leg axis, so the angular velocity of the cylinder part can be written as wi= nli\u00d7vi/di (8) It yields (9) Hence the total kinematic energy of the pistons is (10) where Ii = RiIibi RiT, lib i is the mass moment inertia of the ith leg about Bi expressed in the leg coordinate. The lagrangian dynamic formulation With the principle of virtual work and Lagrange equation, the hydraulic driven force can be written as (11) where K is the total kinetic energy, P is the total potential energy, Fext is the external generalized force. THE OPTIMUM METHOD Equivalent inertia matrix The equivalent inertia matrix is (12) where Ji= JTxi Jxi+ JTyi Jyi+ JTzi Jzi, Mp is the mass-inertia matrix of moving platform in \u0192\u00b0O. Generalized natural frequency It is assumed that the mechanical part is rigid, and the hydraulic oil can be compressed. The stiffness of the hydraulic spring is defined as (13) (14) where ,8 is the oil bulk modulus, A1 is the area of piston side, A2 is the area of rod side, Loin and Loi12 are the two equivalent chamber lengths of the cylinder. It can be obtained Kq= DTKhD (15) The generalized natural frequency on 6-DOF (x y z \u0192\u00d5 \u0192\u00b5 \u0192\u00c6) is given by (i= 1\uff5e6) (16) The optimization scheme In applications with requirements of high precise positioning and good dynamic performance, e.g. large flight simulators, the control of the platform is complicated and difficult, especially for the hydraulic platform. In general, the control of hydraulic actuators is more challenging than that of their electrical 673 Copyright (C) 2008 by JFPS, ISBN 4-931070-07-X counterparts when parallel manipulators are large. They exhibit a significant nonlinear behavior. The factors such as nonlinear flow/pressure characteristics, variations in the trapped fluid volume due to piston motion, fluid compressibility, flow forces and their effects on the spool position, and friction, all contributing to this nonlinear behavior. This will influence the actual control bandwidth, and it is less than half of the natural frequency in engineering. To expand the theoretical bandwidth for the control, the natural frequency characteristics must be considered in the optimal design. For large hydraulic Stewart platform with requirements, the lowest natural frequency in the total workspace and the generalized natural frequency when all the actuators are at their mid stroke are the key frequencies. The aim of the design is to obtain highest frequencies, and the natural frequencies when all actuators are at their mid stroke should be as close as possible. The optimization work is not based on the cost function. The steps in the optimization are as follows: Step 1 Choose an initial set of design parameters. It can be roughly determined from the workspace requirement, the desired linear and angular isotropic accelerations at some velocity state. Step 2 Determine the range of each design parameter, and give the graph results of the influence by the design parameters. Step 3 Choose a new set of design parameters from step 2, get the task frequencies. If it's not satisfied, change the deign parameters, especially the effective hydraulic driving area and oil bulk modulus (the system oil should be preprocessed if necessary), return to the step 2. Step 4 Compute the average hydraulic system power as a design reference by the system flow rate and pressure with design parameters. Step 5 Workspace verifying and other requirements examination. In the paper, the configuration is representative for a group of nearby or symmetric configurations. Based on the natural frequency, the bandwidth for the control will be determined more appropriate for the designer related to the control of the hydraulic parallel manipulator." + ] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure4.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure4.13-1.png", + "caption": "Figure 4.13 : Nacelle size with dimensions in mm from Airbus deliverable.", + "texts": [ + "10, and external radius equal to stator outer radius. Finally, the heat flux extracted through liquid cooling should be evacuated to the outside environment. This job is accomplished using an efficient heat exchanger designed for this purpose. 4.3.4 Heat Exchanger of Cooling System For the targeted hybrid aircraft, the nacelle is used to hold, cover, and protect the propulsion power units and components; it offers also an aerodynamical shape to these systems. Nacelle dimensions are defined by the project industrial partner Airbus as seen in Figure 4.13. It has a cylindrical revolved form of 532 mm central diameter and a total of 1382 mm length. It will enclose the propulsion components and could be used for other purposes in the design process of the hybrid propulsion chain for aeronautical application. In the current study, the nacelle of the propulsion system will be employed as a heat sink plate to help to design a heat exchanger at minimum weight. For this purpose, a pipe is wound to the internal surface of this nacelle. A sketch is depicted in Figure 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001984_el-00811520_document-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001984_el-00811520_document-Figure5-1.png", + "caption": "Figure 5: Electric field amplitude as a function of altitude in a lossless cavity with PEC boundaries, where Rint=Rv , Rext=Rv+h, and h=130 km. The permittivity is given by the profile of Fig. 2 (solid line) or is assumed to be that of vacuum (dashed line). The electric field maximum is reached at 31.5 km.", + "texts": [ + " 73 Table 16 - List of the SP2 instrument main characteristics \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026... 74 Table 17 \u2013 Permittivity and chemical composition of the JSC Mars-1 simulant \u2026\u2026.. 81 Table 18 - Accuracy of SP2 measurements \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026... 82 x xi List of Figures Figure 1 \u2013 Illustration of atmospheric electricity phenomena on Earth \u2026.\u2026\u2026\u2026...\u2026. 16 Figure 2 - Global lightning distribution obtained by satellite \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026 16 Figure 3 - Models of general characteristics of lightning strokes \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026.. 17 Figure 4 \u2013 Spherical cavity configurations used in the simulations \u2026\u2026\u2026\u2026\u2026\u2026\u2026.. 20 Figure 5 - Sketch of the model used for calculating the Schumann resonance \u2026\u2026\u2026. 24 Figure 6 - Conductivity and permittivity profiles of the atmosphere of Venus \u2026\u2026\u2026. 28 Figure 7 - Electric field amplitude as a function of altitude in a lossless cavity \u2026\u2026... 31 Figure 8 - The Cassini Orbiter and the Huygens Probe \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026. 33 Figure 9 - Sketch of the descent sequence of the Huygens Probe upon Titan \u2026\u2026\u2026... 35 Figure 10 - Sketch of PWA sensors and Huygens Probe in deployed configuration \u2026 36 Figure 11 - General view of the Huygens Probe and parachute bridles \u2026\u2026\u2026\u2026\u2026\u2026 40 Figure 12 - The synopsis of PWA data \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026", + " By definition, the radius of the gaseous planets is determined by the 1-bar reference surface that is of little interest for our modelling purposes. The cavity models of Venus, Earth, Mars, Jupiter, Io, Europa, Saturn, Titan, Uranus, and Neptune are described in the following. 24 3.2.1. Parameter Description The resonant cavity problem is solved in 2D axisymmetric and 3D configurations, either in the eigenfrequency or time-harmonic propagation mode. The model uses the finite element method to solve Equations (18-25) with boundary and continuity conditions (26-29) depending on geometry and mode selection. Figure 5 shows the most important cavity parameters: body surface radius; height of the ionosphere, cavity upper boundary; depth of the subsurface boundary, cavity lower boundary; conductivity profile of the atmosphere and lower ionosphere; permittivity profile of the atmosphere; conductivity profile of the interior; permittivity profile of the interior. Let us first expose how the electric properties of a cavity are estimated. The electron conductivity profile is derived from electron density and thermodynamics parameters such as temperature and pressure; the permittivity profile is derived from gas density and refractivity equations", + " The threshold density was 5 \u00a3 10212 kgm23. The uncertainty on the density determination25 is of the order of 10%, mainly due to the uncertainty on the aerodynamic drag coefficient and on the probe velocity. Density values relevant to the lower atmosphere, below 160 km, have been inferred from HASI direct measurements of pressure and temperature with the assumption of hydrostatic equilibrium and real gas law29. ARTICLES NATURE|Vol 438|8 December 2005 786 \u00a9 2005 Nature Publishing Group structure seen in Fig. 5 provides evidence for a regime of gravity waves similar to those observed in the Voyager radio occultation data31,32. Turbulence due to shear instability (Kelvin\u2013Helmholtz instability) is expected wherever the vertical shear of the wind speed is large. The wind shear measured by the Doppler Wind Experiment33 is sufficiently large that the features present between 50 and 150 km are likely to be related to turbulence. The vertical resolution of the temperature measurement was sufficient to resolve the instantaneous structure of the planetary boundary layer", + " This provided a unique opportunity to investigate in situ lightning and related phenomena (for example, corona discharges) on Titan21 that would produce electromagnetic waves38, excite global and local resonance phenomena in the surface\u2013 ionospheric cavity39,40 and could drive a global electric circuit22. Several impulsive events have been observed during the descent, for example at 2,800 s. The narrow-band wave emission seen near 36 Hz is reminiscent of a possible resonance generated by lightning activity in the spherical waveguide formed by the surface of Titan and the inner boundary of its ionosphere, but should be interpreted with caution. A comparison of the records presented in Fig. 8a and b shows that the first spectrogram (active mode) not only displays the Figure 5 | Temperature profile of the lower atmosphere as measured by the temperature sensors, TEM27 (expanded from Fig. 2). Temperature uncertainty is^0.25K in the range from 60 to 110K, and^1K above 110K. The temperature minimum of 70.43K is reached at the tropopause (about 44 km; 115 ^ 1 hPa). HASI temperatures are in very good agreement (within the error bars) with data obtained by Voyager radio occultation2 (ingress, circles; egress, crosses) assuming a pure nitrogen atmosphere. The error bars for Voyager data are reported: ^15K (egress) ^10K (ingress) near the 200-km level, ^0", + " Furthermore, as the presence of the large vessel induces potential distortion around the relaxation probes, the charge distributions produced by electrons and ions around the electrodes lose their spherical symmetry. This influence is not fully understood so far and is under investigation. Moreover, the relative position between the relaxation probes, the body of the Huygens Probe and the hypothetical vertical electric field varies during the descent trajectory, which demands for more sophisticated models (Figure 4 and Figure 5). Figure 3 - Slice in the plane z=0 that shows the electric potential distribution generated by the two relaxation probes (Model A). The potential of the electrodes is symmetric (+5V and \u20135V) and the perturbation induced by the body of the probe is visible. A multiphysics model including electrons, heavy ions and neutrals is being implemented. The system comprises the modelling of electrostatics, particle diffusion and incompressible flow equations for a more accurate analysis of the global dynamics and its influence in the electric measurements. Figure 4 - Slice in the plane z=0 that shows the electric potential distribution generated by the two relaxation probes and the vertical electric field (Model B). Figure 5 - Slice in the plane z=0 that shows the electric potential distribution generated by the two relaxation probes and a non perpendicular (20\u00b0) electric field (Model B). The MIP sensor has successfully obtained measurements from the surface of Titan during 30min. Although the results are strongly dependent of the attitude of the probe on the ground (Model C), and several parameters are not fully determined yet, the order of magnitude of the permittivity value of the ground can be established (Fulchignoni et al", + " (6) The measurement is independent of the sizes and shapes of the electrodes and of the array configuration. The PWA-MIP electrodes are mounted on a deployable boom system. The AC current source consists of a voltage generator with a pair of small capacitors, Ck, in series with TX1 and TX2. On the receiving side, the signals picked up by RX1 and RX2 are coupled to high impedance preamplifiers through coupling capacitors Ck. The differential signal is fed, via an ADC, into a processor that yields the amplitude and phase. The circuit diagram of MIP is illustrated in Fig. 5. It was anticipated (Grard et al., 1995) that the relatively low conductivity of the atmosphere would produce small phase shifts (Eq. (4)) and a low working frequency, 45Hz, was therefore selected for the descent. The mode of operation, the level of the stimulus (TX) and the gain of the receiver (RX), are changed automatically by the onboard software, according to predetermined sequences. The instrument with deployed booms was calibrated on the ground, in dry air, for each mode of operation. The precise knowledge of every discrete and stray circuit component is essential to the evaluation of systematic amplitude and phase errors which cannot be calibrated on the ground, because they are due to the effect of the environment on the load of the current source and on the input impedance of the preamplifiers", + " At the end of the descent, the phase is very close to that measured during calibration, j0, which indicates that, the electron conductivity is very small at low altitudes (Eq. (6)). Significant phase shifts are measured in the early phase of the descent, reflecting the existence of an electron layer with peak conductivity at an altitude of about 60 km. These results corroborate those obtained with the RP. The discrepancies are partly due to the facts that the Debye length is commensurate with the sensor radii in the electron layer, and that the two techniques do not measure the same ARTICLE IN PRESS TX1 TX2 RX1 RX1 ARX,\u03d5RX mediumuAC Ck Ck Ck Ck ~ Fig. 5. Simplified mutual impedance probe circuit diagram. R. Grard et al. / Planetary and Space Science 54 (2006) 1124\u20131136 1129 quantities: RP measures the electron and light ion conductivities, whereas MIP is sensitive to electrons only. The signal magnitude shows a profile that deviates from the expected trend. A constant level, close to that observed during pre-flight calibration, was anticipated. Instead, the level is up to 26% above the nominal value, about 0.1V, during most of the time (T43000 s)", + " 3\u20136 show the variations of the real and imaginary parts of the three lowest eigenfrequencies as functions of those parameters. The atmospheric conductivity, the presence of aerosols and the depth of the conductive boundary have a profound influence upon the Table 2 Comparison between the lowest eigenfrequency modes (Hz) on Titan for diffe boundaries are located at Rint \u00bc RT and Rext \u00bc RT+hT Profile mode CP1 CP2 CP3 First 7.27+4.77i 13.43+6.25i 16.0 Second 15.25+9.71i 28.13+10.57i 30.2 Third 25.31+14.80i 43.93+13.64i 44.9 Fig. 5. Same caption as in Fig. 4, but esoil \u00bc 3, and the eigenfrequencies are plotted against the imaginary part of the soil dielectric constant. Fig. 6. The three lowest eigenfrequencies of the cavity as functions of the PEC depth, for satm \u00bc CP1, esoil \u00bc 3, and ssoil \u00bc 10 9 Sm 1 (lines and symbols as in Fig. 4). eigenfrequencies. Therefore, the PWA data play an important role in constraining the cavity model and evaluating the Schumann resonance frequencies. Fig. 4 shows that an increase of permittivity reduces the eigenfrequencies of the cavity, because on / 1=2 for a homogeneous medium. The same general behaviour is observed for the imaginary part of the frequency. The variations of the resonance frequencies as functions of the losses in the soil (Fig. 5) resemble the dielectric relaxation described by Debye\u2019s dipole polarization model. Increasing the depth of the PEC boundary has contrasting effects on the eigenfrequency, because the real part rises while the imaginary part decreases (Fig. 6). For comparison, the components of the complex eigenfrequencies are represented by circles in Figs. 3\u20136, when the surface is a PEC boundary (Table 2). The knowledge of the real part of the eigenfrequency alone does not make it possible to distinguish between two cavity models. For example, this quantity equals 25Hz for n \u00bc 3 in Fig. 5, not only when d \u00bc 0, but also when d \u00bc 100 km and the imaginary part of the dielectric constant is about 3.5. There is no ambiguity for the imaginary part of the frequency, since the latter is always larger when d \u00bc 0 than when d \u00bc 100 km, whatever the imaginary part of the soil dielectric constant may be. Therefore, measuring the sole resonance frequencies is insufficient for a proper characterization of the cavity, and other parameters, such as the Q-factors, must be considered to constrain the results", + " The dynamic pressure of the air blow during the tests, leading to such Table 1 Summary of the first eigenmode of different models of PWA booms, as seen in four directions: X is along the boom axis, Z is along the MI-TR and relaxation sensors; horizontal and vertical are for the nominal Huygens attitude; torsional is around X Model Eigenmode (Hz) Flexural Z\u2013X Flexural Y\u2013X Flexural horizontal Flexural vertical Flexural average Torsional Mock-up (LPCE) ? ? ? ? \u223c30 ? Engineering (CISAS) 20.8 23 15\u201318 21\u201323 \u223c20 \u223c60 Flight spare (CISAS) ? ? ? \u223c25 25 \u223c68 Finite element modeling 24.2 25.2 NA NA 24.7 75.3 256 C. B\u00e9ghin et al. / Icarus 191 (2007) 251\u2013266 Fig. 5. Profile of the dynamic pressure during the first part of the descent. amplitude, is estimated to be of the order of 1000\u20131500 Pa at the boom tip. The dynamic pressure during the Huygens descent is plotted in Fig. 5, as deduced from the altitude profiles of gas density and descent velocity, assuming a laminar velocity flow and using the standard equation (3)Pd = \u03c1V 2 2 , where the mass density \u03c1 is derived from HASI\u2019s atmospheric data (Fulchignoni et al., 2005). We notice an increase of the dynamic pressure at t = 900 s, i.e. at the time of the main parachute jettison, associated with the sudden rise of the broadband ELF noise, due obviously to a transient shock response lasting about 10 s (Fig. 4). No remarkable simultaneous enhancement is visible at 36 Hz in the spectrogram of Fig", + " Contrary to the former approach that is based on volume elements, this method involves surface elements and requires less computer memory for the same resolution, but the practical limitation comes from the difficulty encountered in inverting a very large matrix. The method has been developed for satellites in space plasmas by Be\u0301ghin and Kolesnikova (1998). All conductive parts of the system are split into as many finite elements as necessary to give a representative mesh structure of the full system, including the discrete electric connections between elements. The geometry of the model has to comply with the constraints of a general-purpose code that is designed ARTICLE IN PRESS Fig. 5. SCD modelling in axial geometry (revolution axis parallel to Yp of Fig. 4). Fig. 6. Boom configuration and sensor lay-out, with the characteristic distances used in the SCD code. M. Hamelin et al. / Planetary and Space Science 55 (2007) 1964\u20131977 1971 for an axial symmetry (Fig. 5). Nevertheless, the actual distances between the antennas and the gondola structure are respected (Fig. 6). The parasitic electrostatic coupling between the sensors and the cabling inside the booms (shielded harness) is also included in the model. In this simulation, the transmitting and receiving rings are replaced either by spheres or by cylinders with the same free-space capacitance, and are loaded with the actual output and input impedances, respectively (Fig. 7). In a vacuum, the SCD model gives voltages between the Rx electrodes with amplitudes of 113", + " Deep in the molecular hydrogen envelope, the density increases beyond the gaseous phase threshold and a liquid environment is expected. The permittivity therefore increases with depth until it reaches the value of liquid hydrogen, which is \u223c1.25. The permittivity profiles shown in Fig. 4 are derived from the interior density models of the jovian planets (e.g. Lewis, 1995). The normalized radii of the solid\u2013liquid interfaces are \u223c0.76 and \u223c0.48 for Jupiter and Saturn, respectively. The conductivity profile of the interior (Fig. 5) is adopted from a theoretical model developed by Liu (2006). The conductivity of the atmosphere is derived from the electron density, pressure, temperature, and composition data collected by several spacecraft. The conductivity of the lower atmosphere is l for exploring the atmospheric environment and the subsurface of the planets ARTICLE IN PRESS YICAR:8477 JID:YICAR AID:8477 /FLA [m5+; v 1.79; Prn:15/11/2007; 13:19] P.6 (1-12) 6 F. Sim\u00f5es et al. / Icarus \u2022\u2022\u2022 (\u2022\u2022\u2022\u2022) \u2022\u2022\u2022\u2013\u2022\u2022\u2022 Fig. 5. Conductivity profiles of Jupiter (solid) and Saturn (dashed) atmospheres. Fig. 6. Conductivity profiles of Jupiter (solid) and Saturn (dashed) interiors. interpolated between that of the lower ionosphere and that of the upper interior (Figs. 5 and 6). Majeed et al. (2004) present an overview of the ionosphere\u2013thermosphere of the giant planets, which is a useful reference for comparison. Lightning activity is present on Jupiter and Saturn; it has been observed with Voyager 1, Galileo and Cassini (Gurnett et al", + "79i Nickolaenko and Hayakawa (2002) Mars Fig. 3 \u2013 \u2013 0 8.31 + 2.19i 15.64 + 4.27i 23.51 + 6.59i 13 Sukhorukov (1991) [5, 10] 10\u22127 5 8.28 + 2.10i 15.49 + 3.66i 22.82 + 5.53i 8.6 Pechony and Price (2004) 5 10\u221210 5 8.55 + 2.07i 15.93 + 3.62i 23.44 + 5.49i 11\u201312 Molina-Cuberos et al. (2006) 10 10\u221210 5 8.41 + 2.08i 15.72 + 3.63i 23.13 + 5.49i [5, 10] 10\u22127 10 7.93 + 2.06i 14.93 + 3.94i 22.41 + 6.04i 5 10\u221210 10 8.47 + 2.03i 15.85 + 3.89i 23.68 + 5.97i 10 10\u221210 10 8.20 + 2.03i 15.40 + 3.89i 23.05 + 5.96i Jupiter Fig. 5 Figs. 4 and 6 0.68 + 0.04i 1.21 + 0.07i 1.74 + 0.10i 0.76 Sentman (1990) 0.95 Guglielmi and Pokhotelov (1996) 1 Nickolaenko and Hayakawa (2002) Io Negligible \u2013 Evanescent wave \u2013 Nickolaenko and Rabinovich (1982) Europa Negligible \u2013 Evanescent wave \u2013 \u2013 Saturn Fig. 5 Figs. 4 and 6 0.93 + 0.06i 1.63 + 0.12i 2.34 + 0.18i \u2013 \u2013 Titan Fig. 7\u2014high 3 10\u22129 100 13.43 + 6.25i 28.13 + 10.57i 43.93 + 13.64i 11\u201315 Morente et al. (2003) Fig. 7\u2014low 3 10\u22129 100 19.15 + 2.27i 34.32 + 3.71i 49.48 + 5.22i 17\u201320 Nickolaenko et al. (2003) 8\u201310 Yang et al. (2006) Uranus Figs. 8\u201310 Ingress\u2014low water content 2.44 + 0.06i 4.24 + 0.11i 6.00 + 0.15i \u2013 \u2013 Figs. 8\u201310 Ingress\u2014high water content 1.02 + 0.25i 1.99 + 0.49i 3.03 + 0.67i Figs. 8\u201310 Egress\u2014low water content 2.47 + 0.06i 4.27 + 0", + " Therefore, if Schumann resonance is excited in the cavity, frequency splitting due to day-night asymmetry should be unambiguously detected on Venus. Although the ELF wave propagation and ray tracing models cannot be strictly compared, it is interesting to note that they predict similar altitudes for the maximum of the electric field (29.6 and 31.5 km for analytical and numerical approximations, respectively) and the ray that circles the planet at constant altitude (31.9 km). In fact, as shown in Fig. 5, the presence of a heterogeneous atmosphere refracts waves, which are preferentially focused at a particular altitude. Furthermore, introducing temperature lapse rate inversion, i.e. increasing density with altitude, allows the formation of local electric field maxima in a straightforward manner. The higher difference obtained with the analytical model is due to considering an exponential permittivity profile, which is only valid in a first approximation. Alike on Earth, the thickness of the cavity is little with respect to the radius and, therefore, the electric field horizontal polarization (EH) is almost two orders of magnitude smaller than the vertical polarization (EV) (Fig", + " For example, the number of Schumann resonances identified during stratospheric balloon campaigns is lower than in a quiet environment, which confirms that the vessel trajectory and dynamics impose significant constraints on the measurement. 6. Conclusions The distinctive properties of Venus atmosphere strongly influence the propagation of electromagnetic waves in the cavity. The atmospheric permittivity does not significantly modify the eigenfrequencies because the relative permittivity does not exceed ~1.034 close to the surface, but the density gradient produces a peak on the ELF electric field profile (Fig. 5). Wave attenuation is most likely less than on Earth (Table 4); the surface of Venus is not a PEC boundary, and subsurface losses contribute further to the intricacy of the cavity. The high refractivity of Venus atmosphere facilitates ducting phenomena and propagation beyond the geometric horizon. In certain conditions, electromagnetic waves can travel at a constant altitude (~31.9 km) because planetary curvature can be balanced by atmospheric refraction (see sketch in Fig. 3). This phenomenon preferentially focus electromagnetic waves at mid altitudes: i) according to our theoretical approximation considering an exponential atmospheric permittivity profile, the electric field maximum is at 29", + " The MI mole prototype was tested using materials such as polyethylene, quartz glass beads, and JSC-1 Mars soil simulant [5,6]. Measurement data was acquired at 16, 32, 64, 128, 256, 1024, 2048, and 4096 Hz. At each frequency, the results from a number of measurements were averaged in order to reduce the effect of noise and interference from external sources. Correction factors for signal amplitude and phases were calculated and applied, and the measurement results for conductivity and dielectric constant were calculated according to (2). Figure 4 and Figure 5 show the calibrated measurement results for a test where the instrument was embedded in a container filled with quartz glass beads. The squares show the prototype measurement results after calibration. The triangles show the results of a reference measurement using the plate capacitor technique [5]. The measurement error with respect to the reference measurement is ~ 20 % on average. The main error sources that have been identified so far are the current measurement circuitry, the phase measurement accuracy, the accuracy of the representative circuit models, and various parasitic capacitances affecting the receiver electrodes. Fig. 4. Conductivity measurement results for quartz glass beads (calibrated) Fig. 5. Permittivity measurement results for quartz glass beads (calibrated) 5. INSTRUMENT CAPABILITIES The accommodation of the quadrupolar electrode array on the mole surface allows performing measurements along the penetration path of the mole. The depth resolution is determined by the size of the electrode 0 5 10 15 20 25 4 6 8 10 12 14 x 10-9 C on du ct iv ity [S /m ] Iteration Nr. Convergence plot of MI measurement data calibration - molemodel3 0 5 10 15 20 25 1 1.5 2 2.5 3 3.5 4 D ie le ct ric C on st an t [ 1] iteration Nr", + " For the sake of comparison, the conductivity in a JSC Mars-1 saturated solution at 10Hz and at room temperature is ~ 5 \u00d7 10-4 Sm-1. Fig. 2. Conductivity (top) and relative dielectric constant (bottom) of the dry JSC Mars-1 simulant (\u03b8<0.005), at T=+20oC, for different porosities: \u03c6=0.58 (red), \u03c6=0.54 (green), and \u03c6=0.52 (blue). The temperature has been raised from -55\u00b0C to 20\u00b0C in steps of 15\u00b0C, with different gravimetric water contents. The results obtained at -55oC and -25oC are reported in Fig. 3 and 4. The results are seen from another perspective in Fig. 5, where the dielectric constant is plotted against frequency, with temperature as a parameter, for two selected values of the gravimetric water content. Quantitative results are illustrated in Tables 1 and 2. Water content and temperature both increase the conductivity and permittivity of the soil simulant. This effect is mostly conspicuous when the gravimetric water content is larger than 0.05; below this threshold, the electric properties of JSC Mars-1 are not very sensitive to moisture and temperature", + " JSC Mars-1 conductivity [Sm-1] at \u201355\u00b0C for a porosity of 0.54. Frequency Gravimetric water content 20Hz 300Hz 10kHz <0.005 2.7 2.4 2.2 0.1 6.7 4.7 3.3 Tab. 2. JSC Mars-1 relative permittivity at \u201355\u00b0C for a porosity of 0.54. Fig. 4. Relative dielectric constant of the JSC Mars-1 simulant with gravimetric water contents \u03b8<0.005 (top) and \u03b8=0.1 (bottom), as functions of frequency, for \u03c6=0.54 and temperatures: T=-55oC (red), -40oC (green), -25oC (blue), -10oC (black), +5oC (cyan), and +20oC (magenta). Fig. 5. Loss tangent of the JSC Mars-1 simulant, for \u03b8=0.1, \u03c6=0.54 and temperature: T=-55oC (red), -40oC (green), -25oC (blue), -10oC (black), +5oC (cyan), and +20oC (magenta). Plotting the loss tangent reveals new signatures whose complexities deserve further analysis. Two features, at least, are readily visible. The loss tangent increases with the water content and temperature. Note, however, that the general ordering of the curves is different for \u03b8=0.05 [1]. The study of these features may help to clarify which processes are at work in this frequency range" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002593_9312710_09335981.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002593_9312710_09335981.pdf-Figure1-1.png", + "caption": "FIGURE 1. Novel modular permanent magnet-assisted synchronous reluctance motor.", + "texts": [ + " In this paper, the combination of the finite element and the differential evolution algorithm is used to optimize both rotors simultaneously. A differential evolution algorithm has been used in multi-objective optimization. This is due to its robustness and effectiveness in solving problems and has nothing to do with the objective function and constraint properties [22], [23]. The structure is optimized with multiple parameters. II. ROTOR STRUCTURE OF MPMA-SynRM The MPMA-SynRM rotor structure is composed of the IPM rotor module and the PMA-SynRM rotor module. The rotor diagram of the axial modular combined motor is shown in Fig. 1. The figure shows that in this paper, an IPM permanent magnet motor is used for the front and rear modules of the motor and the PMA-SynRM rotor structure is used in the middle. The two modules are fixed on the same shaft and work under the same current. In this paper, the internal permanent magnet motor rotor structure of the MPMA-SynRM module is taken as 19948 VOLUME 9, 2021 an example. The permanent magnet material is Nd-Fe-B with a high magnetic energy product. This material provides the main back EMF, power factor, and main permanent magnet torque output for the MPMA-SynRM motor", + " When the internal power factor angle \u03b2PM = 122 degrees, the output torque of the IPMmotor reaches its maximum value. When the internal power factor angle \u03b2PMA\u2212SynRM = 145 degrees, the output torque of the PMA-SynRM motor reaches its maximum value. According to the MTPA control logic, when the stator is given a rated current, the IPM module and PMA-SynRM should simultaneously reach their own internal rate factor angles of peak torque. The PMA-SynRM rotor module needs to be rotated by \u03b1 degrees along the motor rotation direction, as shown in Fig. 1. The dpm axis of the IPM rotor is projected along the axial direction to the angle between the PMA-SynRM rotor plane and dPMA-SynRM, which is the mechanical Angle \u03b1, where \u03b1 is calculated in (5). \u03b1 = \u03b2PMA\u2212SynRM \u2212 \u03b2PM p (5) As shown in Fig. 6 and based on the above rotor coordination mode, the torque of the synthetic motor and IPM permanent magnet motor changes with the internal power factor angle torque. 19950 VOLUME 9, 2021 Since the MPMA-SynRM rotors are all synchronous rotors, the motor analysis uses space vector diagrams" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001904_017_ms-8-11-2017.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001904_017_ms-8-11-2017.pdf-Figure11-1.png", + "caption": "Figure 11. CAD model (left) and FEM model (right), the rear suspension has H arm layout and the mounting points are located near the beam geometry centre using bushings.", + "texts": [ + " Which means it is possible to substitute the conventional suspension (coil spring and metallic control arms) with CFRP beam spring suspension for standard passenger vehicles without changing the handling performance of the existing ones. 13Skid pad test with a radius of 40 m and simulate the vehicle from steady until reaching 1 g lateral acceleration. Mech. Sci., 8, 11\u201322, 2017 www.mech-sci.net/8/11/2017/ Using the approved vehicle-dynamics simulation results, the characteristics of the beam components were approximately defined and the first component CAD was created. FEM analysis has been done to obtain the optimum ply sequence (55 layers) and orientation (Fig. 11). The beam has been produced completely manually, by using a special vacuum bag technology and autoclave process (Uddin, 2013) to ensure the correct polymerization without any defects in the melt resin. The mold is floating with the carbon fiber to give the better surface finishing and ensure the uniform pressure on the whole piece (shown in Fig. 12). After cleaning the flanges and drilling for addition components (joint housing), the component is mounted on the chassis prototype. A simple test bench for evaluating the beam spring stiffness has been made (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000317_load.php_id_24031902-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000317_load.php_id_24031902-Figure12-1.png", + "caption": "FIGURE 12. Modal simulation mesh diagram.", + "texts": [ + " Therefore, the finite element method is used for motor modal analysis to avoid motor resonance. The literature shows that the end covers and the rotor have little impact on the vibration of the stator. Therefore, the end covers and the rotor are usually ignored [22, 23]. In modal analysis, finite element analysis is performed on the stator and casing. The lower surface of the motor casing was constrained to simulate the actual working state of the motor. The main motor mode simulation conditions are shown in Table 8. Figure 12 shows the mesh diagram of the modal simulation. Table 9 shows the vibrationmodes and frequencies under different modal orders. The corresponding harmonic amplitude increases significantly when the harmonic frequency is similar to the modal frequency. Therefore, when the variation pattern of the harmonic amplitude is analyzed, the motor modal frequency should be considered simultaneously. In Figure 13(a), the harmonic amplitudes of the 2f , 4f , 8f , and 10f orders after optimization are significantly lower than the preoptimization levels, and the suppression effect on the 4f order harmonic amplitude is the most obvious, with a reduction of 3190" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001133_f_version_1569401418-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001133_f_version_1569401418-Figure4-1.png", + "caption": "Figure 4. The definition of the transition curve coordinate system.", + "texts": [ + " The auxiliary coordinate systems o1 and oT0 respectively corresponding to T1 and T0 are established. The origin of o1 is located on the y-negative half axis of the T1, and the projection distance from the origin of T1 is equal to the curvature radius R1 at T1. The x-axis of o1 is parallel to the x-axis of T1, and the z-axis is parallel to the z-axis of o1. In addition, the angle between the y-axis of T1 and the y-axis is the transverse slope angle \u03b81. The definition of the coordinate system oT0 is similar to that of o1. The coordinate systems are shown in Figure 4. When the mileage s1 is known, the coordinates of the origin of T1 can be obtained from Equation (20): T1 = [x1, y1, z1] T = [s1, s3 1 6S0R0 , 0]T . (21) Considering that the orbit center line is a plane curve and parallel to the horizontal plane, the position vector of the coordinate origin of o1 in the reference system O can be obtained from Figure 5: O o1 P = p1x p1y p1z = x1 \u2212 Rc1 sin \u03d51 y1 \u2212 Rc1 cos \u03d51 cos \u03b81 \u2212Rc1 cos \u03d51 sin \u03b81 , (22) where Rc1 = R1/ cos \u03b81, R1 is the radius of the curve at the origin of T1 and \u03d51 is the direction angle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002140_5-lajss-15-5-e71.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002140_5-lajss-15-5-e71.pdf-Figure1-1.png", + "caption": "Figure 1: Probe-cone system used in capture process: (a) Chaser and proposed buffer; (b) Target.", + "texts": [ + " To only ascertain the effectiveness of proposed buffer in capture, a very simple experimental setup is established and also, the capture capability of buffer within an interval of 10 ,1\u00a0 0\u2212 for relative attitude angles between both vehicles is visualized. Numerical results indicate that the proposed mechanism is able to decrease the peak value of impact force, increase the contact duration and implement the successful capture process. At least two satellites, named chaser and target, with a physical contact are needed to investigate capture mission. Probe-cone system is mainly composed of a probe mounted on the main body of chaser and conical surface attached to target vehicle, as illustrated in Figure 1(a) and (b). This kind of system is used here due to its simple layout, computational easiness and effective alignment of both structures after impact. The chaser is considered to gradually approach to Latin American Journal of Solids and Structures, 2018, 15(5), e71 3/21 the conical zone installed on the target. According to Figure 1, the capture process will be successfully executed if the tip mass of probe is able to pass through the capture area. Figure 1(a) is given here in order to better understand how all involved components are assembled together. As can be seen in Figure 1(a), the motion of cylinder attached to chaser is restricted by a revolute pair and also, probe can freely slide along the cylinder (translational pair) during impact. From mechanical stability point of view, it is essential to apply a torsional spring acting around the rotation axis of revolute joint. The connection between probe and cylinder is also provided by an axial shock absorber. This proposed buffering mechanism allows the equivalent impacting mass to be slowly increased instead of its rapid change during impact process", + " To do this, the Lankarni-Nikravesh contact force model, which is commonly applicable model in a wide range of multibody systems, will be applied in the problem under consideration. In the normal direction to the impact surfaces, the nonlinear LankaraniNikravesh contact force model for parabolic distribution of contact stress is given by Lankarani and Nikravesh (1990): ( )1.5 nF K = + (1) In which, K and are the total contact stiffness and the hysteresis damping factor, respectively. and are respectively relative penetration depth and approaching velocity of two vehicles in the normal direction. Based on Figure 1, impact occurs between the spherical tip mass of probe with radius tR and a plane surface on concave cone. In this condition, the contact stiffness is defined by Flores et al. (2008): ( )4 / 3t t cK R = + (2) Where, t and c are, respectively, material properties of spherical tip mass and conical surface, given as (Goldsmith, 1960): ( ) ( )2 21 / , \u00a0 1 /t t t c c cE E = \u2212 = \u2212 (3) Where E and denote the Young\u2019s modulus and Poisson\u2019s ratio of two colliding bodies, respectively. Also, the hysteresis damping factor is given by Flores et al", + " The proposed buffer mechanism together with design flow strategy allows the designers to have a wide range of their easy-to-access parameters for obtaining the buffer coefficients. Case 1 Case 2 Case 3 This section is devoted into a simple and efficient ground-based experimental test to only show the performance of proposed buffer in the successful capture process. Keeping in mind that the theoretical model of capture mission has been verified by the software simulation, we have just paid our attention to establish a simple test due to limitations on Latin American Journal of Solids and Structures, 2018, 15(5), e71 16/21 data processing facilities. According to Figure 1(a) and (b), it is reasonable to simplify this process as plane motion because of rotational symmetry in the structure of probe, cone and buffer. Therefore, three freedoms are necessary for each vehicle in plane situation. The real configuration of experimental system is pictured in Figure 14(a). The test bench consists of a ball-wheeled chaser, a guiding motion rail, 2-DOF buffer attached to the chaser, a ball-wheeled target and string-pulley mechanism as a low-cost propelling system. Note that the guiding rail is used here to guarantee the initial relative motion of chaser in a straight line exactly similar to theoretical model" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003514__pdf_10.1145_3618396-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003514__pdf_10.1145_3618396-Figure4-1.png", + "caption": "Fig. 4. Homogenization process: given an applied macroscopic Biot strain Y in strain space (left), we solve (3) to compute the deformation of the periodic microstructure tiling. Averaging the resulting PK1 stress over the unit cell (2) obtains the homogenized Biot stress \ud835\udf0e = \ud835\udf13 \u2032 , a point in stress space (right).", + "texts": [ + " The few past efforts to extend microstructure design to finite strains have employed severe simplifications: controlling behavior in only a single loading scenario [Nakshatrala et al. 2013], at a few sampled loads [Behrou et al. 2021], or along one deformation path (e.g., uniaxial stretching) [Clausen et al. 2015; Schumacher et al. 2018a; Wang et al. 2014]. These limitations are acceptable in some situations, like for bistable auxetics [Chen et al. 2021a] known to admit a single low-energy deformation path. However, many applications call for tailoring properties over finite regions, E, of strain space (see Figure 4). The distinction is visualized in the inset sketch: control is needed over a full volume (translucent ball) instead of the sparse and low-dimensional samplings of past work, e.g. uniaxial strains with varying magnitude or direction (brown and blue dots, respectively). Characterizing and optimizing material properties over this finite region poses several computational challenges that our work seeks to address. Applications of finite-strain elastic metamaterial design abound. At themost basic level, microstructures can be designed to reproduce simple analytical models, like linear Hooke\u2019s laws or neo-Hookean materials", + " Tangent elasticity tensors\ud835\udc36 can be obtained by differentiating \ud835\udf0e(\ud835\udc39 ) once more with respect to \ud835\udc39 , and in this case derivatives of \ud835\udf4e\u2217 cannot be neglected: \ud835\udc36(\ud835\udc39 ) : \ud835\udc52\ud835\udc56 \ud835\udc57 = 1 |\ud835\udc4c | \u222b \u03a9 \ud835\udf13 \u2032\u2032(\u2207\ud835\udf4e\u2217(X; \ud835\udc39 ) + \ud835\udc39 ) : (\u2207\ud835\udf4e\ud835\udc56 \ud835\udc57 + \ud835\udc52\ud835\udc56 \ud835\udc57 ) dX, (4) where \ud835\udf4e\ud835\udc56 \ud835\udc57 := \ud835\udf15\ud835\udf4e\u2217 \ud835\udf15\ud835\udc39 : \ud835\udc52\ud835\udc56 \ud835\udc57 are equilibrium derivatives that we provide formulas for in Section 4.1, and \ud835\udc52\ud835\udc56 \ud835\udc57 := 1 2 (e\ud835\udc56 \u2297 e\ud835\udc57 + e\ud835\udc57 \u2297 e\ud835\udc56 ) is the canonical basis for symmetric matrices. Homogenization Process. To probe the material\u2019s behavior at a single applied Biot strain tensor Y, one first must solve the nonlinear, nonconvex optimization (3) with \ud835\udc39 = \ud835\udc3c + Y, after which the homogenized energy and stress can be calculated via (1) and (2). This process is visualized in Figure 4. However, we recall that our goal is to characterize the behavior over a finite strain region E, which for ACM Trans. Graph., Vol. 42, No. 6, Article 185. Publication date: December 2023. planarmicrostructures is a three dimensional space with coordinates (Y\ud835\udc65\ud835\udc65 , Y\ud835\udc66\ud835\udc66, Y\ud835\udc65\ud835\udc66 ). Therefore, separate instances of (3) must in theory be solved for each of infinitely many \ud835\udc39 \u2208 F , where F = {\ud835\udc3c + Y |Y \u2208 E}. In practice, an approximation to\ud835\udf13 or \ud835\udf4e\u2217 must be constructed with suitable accuracy over all of E, and this process must be computationally efficient to run in the inner loop of a design optimization" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure14.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure14.10-1.png", + "caption": "Fig. 14.10. The distribution of directional estimators: a) , b) & , c) & and d) total energy estimators , and for different gear position (vibration signals measured on the floor panel in location of driver feet)", + "texts": [ + " BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 173 174 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260 VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 175 176 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260 For the purpose of analysis of influence of gear position in transmission gearbox on vibration the estimators, defined in previous chapter, were compared. Fig. 14.10 present the distribution of these estimators with values for neutral gear. VOL. 1. R. BURDZIK. IDENTIFICATION OF VIBRATIONS IN AUTOMOTIVE VEHICLES. ISBN 978-609-95549-2-1 177 The purpose of the analysis was to identify vibration components caused due to the large pressure which occurs between the meshing teeth when gears transmit power. For these goal the time domain vibration was compared, which enables observation of vibration energy changes for the neutral idle gear and first-speed or fifth-speed gear position (Figs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003464_ees-2021-21-1-71.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003464_ees-2021-21-1-71.pdf-Figure1-1.png", + "caption": "Fig. 1. Layout of the dual-band meander microstrip antenna: (a) 3D view, (b) side view, and (c) top and overall unfolded antenna.", + "texts": [ + " The structure of a dual-band meander FPCB antenna is discussed in Section II, followed by the specifications of a dualband low-power-consumption active RFID tag in Section III. In Section IV, we describe the field tests using the designed tags, while some final conclusions are provided in Section V. An antenna working in the UHF (917\u2013923 MHz) and microwave bands (2.4\u20132.45 GHz) with the help of a meander line for size reduction was designed and fabricated for an RFIDbased subway car maintenance system. The structure and design of the dual-band antenna inspired by meander lines is illustrated in Fig. 1. Fig. 1(a) and (b) show the structure and Fig. 1(c) the overall unfolded schematic and dimensions of the radiator of the proposed design. The antenna consists of radiators and a ground plane, which comprises a battery (32 mm \u00d7 38 mm \u00d7 6 mm), PCB (32 mm \u00d7 38 mm \u00d7 1 mm; the component mounted on the PCB is metallic), and dielectric layer (composed of an air and ABS layer). The layer). The overall size of the antenna is 34 mm \u00d7 40 mm \u00d7 12 mm. The radiators are designed on the ABS (\u03b5r = 2.2, thickness = 1 mm) and FPCB (\u03b5r = 2.3, copper layer mass = 1 oz, thickness = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000436_0799-020-00359-8.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000436_0799-020-00359-8.pdf-Figure1-1.png", + "caption": "Fig. 1 Scheme of a double-acting pneumatic cylinder", + "texts": [ + " The equation of piston motion is given by [4]: ( ML + Mp ) x\u0308 = P1A1 \u2212P2A2 \u2212PaAr \u2212\u03b2x\u0307\u2212Ff \u2212FL (1) where x represents the rod position (m); P1 and P2 are the pressures in cylinder chambers 1 and 2, respectively (kPa); Pa defines the atmospheric pressure (kPa); Ar represents the rod transverse area (m2), A1 is the piston area in chamber 1 (m2); A2 is the area of the rod in chamber 2 obtained as A2 = A1 \u2212 Ar (m2); ML represents the load mass (kg); Mp represents the rod mass (kg); \u03b2 is the cylinder viscous friction (Kg/s); Ff denotes the Coulomb friction (N); and FL represents the external force (N). Figure 1 shows the main parts of the double-acting pneumatic cylinder (equation (1)) and Fig. 2 displays a free body diagram of the piston and the rod, where it shows the forces described in equation (1). In this free body diagram, FL and Fp represent the forces generated by the masses of the load and the rod, respectively; F\u03b2 is the force produced by the viscous friction. In the case of the force represented by the term PaAr\u2217, the symbol \u2217 is to describe that if the rod does not have a load, the rod transverse area is only considered, otherwise it is considered the area of the load", + " In the mean part of the stroke, the velocity of the moving element can be considered as a constant approximately. Pressure dynamics in cylinder chambers provides dipper insight into the kinetics of a piston or cylinder body. Pressures in the chambers of the pneumatic cylinder in horizontal and vertical position were measured all time along with the moving element forward and backward displacement, at three source pressures Ps = 200, 400, and 500 kPa. In these trials, the pressures P1 and P2 are measured dynamically in respective chambers 1 and 2, as shown in Fig. 1. Figure 8 shows the plots of chamber pressures when piston rod moves forward in horizontal position of cylinder at Ps = 200, 400 and 500 kPa. An analogous morphology is observed between the curves of pressure P1 in chamber 1 at different source pressures, the same is true for pressure P2 in chamber 2 for the three source pressures. A small latent time of about 0.013 s is observed after pushing the button of regulating valve. Then the pressure P2, starting from the source pressure, is gradually decreasing, except small fluctuations at the very beginning" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000623__4_5_4_17-00007__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000623__4_5_4_17-00007__pdf-Figure2-1.png", + "caption": "Fig. 2 Axial suspension force production with field strengthening Fig. 3 Independent control of restoring torque and radial control and field weakening suspension force with P\u00b12 pole algorithm.", + "texts": [ + " The levitated rotor is axially sandwiched between the top stator and the bottom stator. A double stator mechanism enhances a rotating torque production and achieves the 5-DOF active control of levitated rotor postures. The motor can generate axial suspension force and rotating torque with a single rotating magnetic field by utilizing vector control algorithm (Asama, et al, 2013; Nguyen, et al, 2011; Osa, et al, 2012b; Ueno, et al, 2000). An axial position (z) of the levitated rotor is actively controlled by field strengthening and field weakening as shown in Fig. 2. A rotating speed (\u03c9z) of the rotor is regulated by conventional q-axis current control. Inclination angles (\u03b8x and \u03b8y) and radial positions (x and y) of the levitated rotor can be controlled with P\u00b12 pole algorithm. In this theory, two rotating magnetic fields are assumed to be distributed in the air gap. One is a permanent magnet magnetic field which has pole number of P. The other is P plus or minus 2 pole magnetic field produced by the stator windings. The axial gap motor can simultaneously produces a restoring torque and a radial suspension force by generating the control magnetic field based on P\u00b12 pole algorithm (Osa, et al, 2012a)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.10-1.png", + "caption": "Figure 1.10. Gearbox steering system from a Willys CJ-3B [40].", + "texts": [ + " The steering linkage was revised so that the front wheels could be steered by hand, initially using a tiller. As internal combustion engines became increasingly powerful, the higher achievable speeds inspired further improvements in suspension and steering design. 7 For example, the steering wheel ultimately replaced the tiller. A typical steering system used a gearbox that converted rotation of the steering wheel into rotation of a Pitman arm, which was then connected to the wheels by a linkage, Figure 1.10. Further efforts in the early twentieth century included the application of shock absorbers, which damp oscillations of the passenger compartment independently of the leaf springs. Shock absorbers in this period were mostly the friction disk and blockand-belt snubber types, both relying on dry friction, while hydraulic shock absorbers became common after World War II [9]. The most ubiquitous car of the early twentieth century was the Ford Model T, with 16.5 million produced between 1908 and 1927" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000056_tation-pdf-url_54247-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000056_tation-pdf-url_54247-Figure2-1.png", + "caption": "Figure 2. Active-caster. (a) Active-caster (top view). (b) Active-caster drive mechanism.", + "texts": [ + " The descending abilities are realized together with the step-climbing function by constructing the add-on mechanism prototype. Also, we propose the semiautomatic control system for the proposed step-climbing and -descending strategies. By using the step detecting system, the front casters are hovered from the ground. Moreover, we propose the control method of the add-on mechanism in each process of the step-climbing and -descending motion. We have subsequently confirmed that the user could pass over a step automatically, using the proposed step-climbing and -descending strategies after the prototype assembly. Figure 2 shows a schematic top view of an active-caster and an overview of the drive unit whose wheel axis is located in an offset position of the steering axis as a passive caster. The distance between the axes is called \u201ccaster-offset\u201d as indicated by a parameter \u201cs\u201d in the figure. Five-Wheeled Wheelchair with an Add-On Mechanism and Its Semiautomatic... http://dx.doi.org/10.5772/67558 29 [ \u03c9 w \u03c9 s ] \u2007=\u2007 [ cos \u03b8 _____ r 0 0 sin \u03b8 ____ s ] v (1) where, \u03b8: angle between the velocity vector and wheel, r: wheel radius, s: caster offset, \u03c9 w : rotation of wheel axis, \u03c9 s : rotation of steering axis, and v: required velocity vector on the steering shaft. The active-caster was developed for holonomic and omnidirectional mobile robots by installing two or more numbers of active-caster units on a robotic platform [19]. However, one active-caster unit is used for the electric drive system for propelling the five-wheeled wheelchair whose top view is shown in Figure 3. The active-caster generates 2DOF velocity vector whose components are represented by v s and v w as shown in Figure 2(a). These components are generated independently by a coordinated control, 2DOF of the wheelchair frame, which can be controlled independently as well. The relationships of the wheelchair motion and the active-caster velocity components are represented in Eq. (2), where x p is a location of the active-caster steering shaft relative to the midpoint of large wheels of the manual wheelchair as shown in Figure 3. From Eqs. (1) and (2), we can derive a control law of the proposed five-wheeled wheelchair as in Eq" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001262_O201129362564253.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001262_O201129362564253.pdf-Figure2-1.png", + "caption": "Fig. 2 Structure of FBG accelerometer using cantilever & mass", + "texts": [], + "surrounding_texts": [ + "2.1.1 \uc5f4\ucc28 \uc6b4\ud589\uc5d0 \ub530\ub978 \ud130\ub110 \uad6c\uc870\ubb3c\uc758 \uc9c4\ub3d9 Table 1\uc740 Korea Railroad Research Institute [2]\uc5d0\uc11c \uc81c\uc2dc \ud55c \uacbd\ubd80\uace0\uc18d\ucca0\ub3c4 1\ub2e8\uacc4 \uad6c\uac04\uc758 \ucf58\ud06c\ub9ac\ud2b8\uada4\ub3c4\uc640 \uc790\uac08\ub3c4\uc0c1\uada4 \ub3c4\uac00 \ubd80\uc124\ub41c \ud130\ub110\uc5d0\uc11c KTX \uc8fc\ud589 \uc2dc \uad6c\uc870\ubb3c(\uce68\ubaa9, \uc2ac\ub798\ube0c, \ub77c\uc774\ub2dd)\uc5d0 \ubc1c\uc0dd\ud558\ub294 \uc9c4\ub3d9\uc744 \uce21\uc815\ud55c \uacb0\uacfc\uc774\ub2e4. \uc790\uac08\ub3c4\uc0c1\uada4\ub3c4 \uc758 \uacbd\uc6b0 \ucf58\ud06c\ub9ac\ud2b8\uada4\ub3c4\uc5d0 \ube44\ud574 \uc0c1\ub300\uc801\uc73c\ub85c \uce68\ubaa9\uc758 \uac70\ub3d9\uc774 \uc790 \uc720\ub86d\uae30 \ub54c\ubb38\uc5d0 \uad6d\ubd80\uc801\uc73c\ub85c \uc9c4\ub3d9\uc774 \ud3c9\uade0 25dB \ud06c\uac8c \ubc1c\uc0dd\ud558 \uc600\ub2e4. \ucf58\ud06c\ub9ac\ud2b8\uada4\ub3c4\uc758 \uacbd\uc6b0\ub294 \uce68\ubaa9\uacfc \uc2ac\ub798\ube0c\uac00 \uc77c\uccb4\ud654 \ub418\uc5b4 \uc788\uc5b4 \ub450 \uad6c\uc870\ubb3c\uc758 \uc9c4\ub3d9\ud615\uc0c1\uc774 \ub9e4\uc6b0 \uc720\uc0ac\ud55c \uac83\uc73c\ub85c \ub098\ud0c0\ub0ac\ub2e4. \ub77c\uc774\ub2dd\uc758 \uacbd\uc6b0\ub294 \ucf58\ud06c\ub9ac\ud2b8 \uada4\ub3c4\uac00 \ubd80\uc124\ub41c \ud130\ub110\uc774 \uc790\uac08\ub3c4\uc0c1 \uada4\ub3c4\uac00 \ubd80\uc124\ub41c \ud130\ub110\uc5d0 \ube44\ud574 5dB \uc815\ub3c4 \uc9c4\ub3d9\uc774 \uc791\uac8c \ubc1c\uc0dd\ud558 \ub294 \uac83\uc744 \uc54c \uc218 \uc788\uc73c\uba70, \ucf58\ud06c\ub9ac\ud2b8\uada4\ub3c4\uc758 \uacbd\uc6b0, 63~200Hz, \uc790 \uac08\ub3c4\uc0c1 \uada4\ub3c4\uc758 \uacbd\uc6b0, 50~315Hz\ub300\uc5ed\uc5d0\uc11c 50dB \uc774\uc0c1\uc758 \uc9c4\ub3d9 \uc774 \uce21\uc815\ub41c \uac83\uc73c\ub85c \ubcf4\uace0 \ub418\uc5c8\ub2e4. \ub530\ub77c\uc11c \uc774\ub7ec\ud55c \uc5f4\ucc28 \uc6b4\ud589\uc744 \uac00\uc9c4\uc6d0\uc73c\ub85c \ud558\uc5ec \ubc1c\uc0dd\ud558\ub294 \ub77c\uc774\ub2dd\uc758 \uc9c4\ub3d9 \ud2b9\uc131\uc744 \uc9c0\uc18d\uc801\uc73c \ub85c \uad00\uce21\ud55c\ub2e4\uba74, \uade0\uc5f4, \ubcc0\ud615, \ubc30\uba74\uacf5\uadf9 \ub4f1\uc73c\ub85c \uc778\ud55c \ud130\ub110\uc758 \uad6c \uc870\uc801 \ud2b9\uc131 \ubcc0\ud654\ub97c \uc608\uce21 \ud560 \uc218 \uc788\uc744 \uac83\uc73c\ub85c \ud310\ub2e8\ub41c\ub2e4. 2.1.2 \uac1c\ubc1c\uc131\ub2a5\uc758 \uacb0\uc815 \ucca0\ub3c4\ud130\ub110\uc758 \uacc4\uce21\uc2dc\uc2a4\ud15c\uc744 \uad6c\uc131\ud558\uba74\uc11c \uacc4\uce21\uc7a5\ube44\uc758 \uc120\uc815\uc744 \ub450\uace0 \uac00\uc7a5 \uc911\uc694\ud558\uac8c \uace0\ub824\ud574\uc57c \ud558\ub294 \uc810\uc740 22,000\ubcfc\ud2b8\uc758 \uace0\uc804 \uc555\uc5d0 \uc758\ud55c \uc804\uc790\uae30\uc7a5\uc758 \ud615\uc131\uc5d0\ub3c4 \ubd88\uad6c\ud558\uace0 \uacc4\uce21\uc758 \uc2e0\ub8b0\uc131\uc744 \ud655\ubcf4\ud574\uc57c \ud55c\ub2e4\ub294 \uac83\uc774\ub2e4. \uc77c\ubc18\uc801\uc73c\ub85c \uc9c0\ud558\uad6c\uc870\ubb3c\uc744 \ud3ec\ud568\ud55c \ud1a0\ubaa9\uad6c\uc870\ubb3c\uc5d0\ub294 \uc804\uae30\uc2dd \ub610\ub294 \uc9c4\ub3d9\ud604\uc2dd \uacc4\uce21\uae30\uae30\ub97c \uc774\uc6a9\ud55c \uacc4 \uce21\uc774 \ub110\ub9ac \uc801\uc6a9\ub418\uace0 \uc788\ub2e4. \uadf8\ub7ec\ub098 \uc804\uae30\uc2dd \ubc0f \uc9c4\ub3d9\ud604\uc2dd \uacc4\uce21 \uae30\uae30\ub294 \uad6c\uc870\ubb3c\uc758 \uc794\uc874\uae30\uac04 \ub3d9\uc548 \uc804\uc790\uc2dd \ubcc0\ud615\ub960\uacc4\uc640 \uc5f0\uacb0\uc120 \uc0ac\uc774\uc758 \ubd80\uc2dd\uc5d0 \uc758\ud55c \uacb0\ud568\uc774 \uc0dd\uae38 \uc218 \uc788\ub294 \ub2e8\uc810\uc774 \uc788\ub2e4. \uadf8 \ub9ac\uace0 \uac01 \uc13c\uc11c\uc5d0 \ud55c \uac1c\uc758 \uc5f0\uacb0\uc120\uc774 \ud544\uc694\ud558\uac8c \ub418\uc5b4, \uc790\ub3d9\ud654 \uacc4 \uce21 \uc2dc\uc2a4\ud15c\uacfc \uc13c\uc11c\uac04\uc758 \uc5f0\uacb0\uc120\uc774 \uae38\uc5b4\uc9c0\uac8c \ub418\uba74 \uc804\uc790\uae30\uc801 \ud2b9 \uc131\uc5d0 \ub530\ub77c \uc815\ud655\ud55c \uacc4\uce21 \ub370\uc774\ud130\ub97c \uc5bb\uc744 \uc218 \uc5c6\uac8c \ub41c\ub2e4. \uc774\uc5d0 \ube44\ud558\uc5ec, \uad11\uc12c\uc720\uaca9\uc790(FBG, Fiber Bragg Grating) \uc13c\uc11c\ub294 \uc7ac\uc9c8 \uc774 \uc11d\uc601(\uc720\ub9ac)\uc774\ubbc0\ub85c \uc7ac\ub8cc\uc758 \ud2b9\uc131\uc0c1 \ubd80\uc2dd\uc774 \ubc1c\uc0dd\ud558\uc9c0 \uc54a\ub294 \uc7a5\uc810\uc774 \uc788\ub2e4. \uadf8\ub9ac\uace0 \uad11(\ube5b)\uc744 \uc774\uc6a9\ud55c \uacc4\uce21 \ubc29\uc2dd\uc774\ubbc0\ub85c \uc804\uc790 \uae30\ud30c\uc5d0 \uc758\ud55c \uc601\ud5a5\uc744 \ubc1b\uc9c0 \uc54a\uc73c\uba70, \ub099\ub8b0 \ubc0f \uac04\uc811\ub8b0\uc5d0 \uc758\ud55c \uc13c \uc11c\uc758 \uc190\uc0c1\uc774 \ubc1c\uc0dd\ud558\uc9c0 \uc54a\ub294 \uc7a5\uc810\uc744 \uac00\uc9c0\uace0 \uc788\ub2e4. \uad11\uc12c\uc720\uaca9 \uc790\uc13c\uc11c\ub294 \ube5b\uc758 \ud30c\uc7a5\uc744 \uc774\uc6a9\ud55c \uc2e0\ud638\ucc98\ub9ac\ub85c \uc804\uc790\uae30\ud30c\ub098 \uae30\ud0c0 \uc774\uc0c1 \uc804\ub958 \ub4f1\uacfc \uac19\uc740 \uc678\ub825\uc5d0 \uc758\ud55c \uc601\ud5a5\uc744 \ubc1b\uc9c0 \uc54a\uc73c\ubbc0\ub85c \uc548 \uc815\uc801\uc778 \uc2e0\ud638\ub97c \ubc1b\uc744 \uc218 \uc788\ub2e4. \uad11\uc12c\uc720\uaca9\uc790\uc13c\uc11c\ub294 \uace0\uc720\ud30c\uc7a5 \ubcc0 \ud654\ub97c \uce21\uc815\ud558\uae30 \ub54c\ubb38\uc5d0 \uc2dc\uc2a4\ud15c\uc5d0 \uc804\uc6d0\uc774 \uc77c\uc2dc\uc801\uc73c\ub85c \uc911\ub2e8\uc774 \ub418\uac70\ub098, \uc2dc\uc2a4\ud15c \uace0\uc7a5\uc774 \ubc1c\uc0dd\ud560 \uacbd\uc6b0\uc5d0\ub3c4 \uc13c\uc11c\uc5d0 \ubcc4\ub3c4\uc758 \ubcf4 \uc815 \uc791\uc5c5\uc774 \ud544\uc694\ud558\uc9c0 \uc54a\uace0, \uc5f0\uacc4\ub41c \ub370\uc774\ud130\uc758 \ucd95\uc801\uc774 \uac00\ub2a5\ud55c \uc7a5\uc810\uc744 \uac00\uc9c0\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c \ucca0\ub3c4\ud130\ub110\uacfc \uac19\uc774 \uacc4\uce21 \ubaa9\uc801\uc0c1 \ubd88\uac00\ud53c\ud558\uac8c \uc804\uae30\uc120\ub85c\uc640 \uac00\uae5d\uac8c \uacc4\uce21\uae30\ub97c \uc124\uce58\ud574\uc57c \ud558\ub294 \uacbd \uc6b0 \uad11\uc12c\uc720 \uc13c\uc11c\ub97c \uc801\uc6a9\ud558\ub294 \uac83\uc774 \uc801\ud569\ud558\ub2e4. Table 2\ub294 \ud604\uc7ac \uc2dc\ud310\ub418\uace0 \uc788\ub294 FBG \uc13c\uc11c\ub97c \uc801\uc6a9\ud55c \uad11\uc12c \uc720\uac00\uc18d\ub3c4\uacc4\uc758 \uc885\ub958\uc774\ub2e4. \ubbf8\uad6d Micron optics\uc0ac\uc640 \uc720\ub7fd\uc758 gavea sensor\uc5d0\uc11c \uac1c\ubc1c\ud55c \uad11\uc12c\uc720\uac00\uc18d\ub3c4\uacc4\uc758 \uacbd\uc6b0\ub294 \uce21\uc815 \ubbfc \uac10\ub3c4\uac00 \uac01\uac01 16pm/g\uc640 22.32pm/g\ub85c \uc77c\ubc18 \uc804\uae30\uc2dd \uac00\uc18d\ub3c4\uacc4 \uc5d0 \ube44\ud558\uc5ec \uc815\ubc00\ub3c4\uac00 \ud604\uc800\ud788 \ub5a8\uc5b4\uc9c0\ub294 \ub2e8\uc810\uc774 \uc788\ub2e4. \uc77c\ubcf8 \u6771 \u4eac\u5074\u686d\uc5d0\uc11c \uac1c\ubc1c\ud55c \uad11\uc12c\uc720\uac00\uc18d\ub3c4\uacc4\uc758 \uce21\uc815 \ubbfc\uac10\ub3c4\ub294 597pm/ g\ub85c \ud130\ub110 \uc9c4\ub3d9 \uce21\uc815\uc5d0 \uc801\uc6a9\uc774 \uac00\ub2a5\ud560 \uac83\uc73c\ub85c \ud3c9\uac00\ub418\ub098, \uac00 \uaca9\uc774 \uc720\uc0ac\ud55c \uc0ac\uc591\uc758 \uae30\uc874 \uc804\uae30\uc2dd\uac00\uc18d\ub3c4\uacc4\uc758 5\ubc30 \uc774\uc0c1\uc73c\ub85c \ud130 \ub110\uc758 \uc548\uc804\uad00\ub9ac\ub97c \uc704\ud574\uc11c \uc801\uc6a9\ud558\uae30\uc5d0\ub294 \uacbd\uc81c\uc131\uc774 \ub5a8\uc5b4\uc9c0\ub294 \ub2e8 \uc810\uc774 \uc788\ub294 \uac83\uc73c\ub85c \uc870\uc0ac\ub418\uc5c8\ub2e4. \ub530\ub77c\uc11c \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 \ud130\ub110\uc758 \uc548\uc804\uad00\ub9ac \ubaa9\uc801\uc758 \uc9c4\ub3d9 \uc131\ub2a5 \ud3c9\uac00\uc5d0 \uc801\ud569\ud55c \uace0\uc0ac\uc591\uc758 \uad11\uc12c\uc720\uac00\uc18d\ub3c4\uacc4\ub97c \uacbd\uc81c\uc801\uc73c\ub85c \uac1c\ubc1c \ud558\uace0\uc790 \ud558\uc600\ub2e4. Fig. 1\uc740 \ucf58\ud06c\ub9ac\ud2b8\uada4\ub3c4\uac00 \uc124\uce58\ub41c \ud130\ub110\ub77c\uc774\ub2dd \uc5d0\uc11c \uc5f4\ucc28\uc6b4\ud589\uc5d0 \ub530\ub978 \uac00\uc18d\ub3c4\ub97c \uae30\uc874 \uc804\uae30\uc2dd\uac00\uc18d\ub3c4\uacc4\ub97c \uc774 \uc6a9\ud558\uc5ec \uce21\uc815\ud55c \uacb0\uacfc(Korea Railroad Research Institute [2]) \ub85c \uc774\ub97c \uace0\ub824\ud558\uc5ec \uac1c\ubc1c\uc0ac\uc591\uc744 \uacb0\uc815\ud558\uc600\ub2e4. \ub610\ud55c \uc77c\ubc18\uc801\uc778 \ud1a0 \ubaa9\uad6c\uc870\ubb3c\uc5d0 \uc801\uc6a9\ub418\ub294 \uac00\uc18d\ub3c4\uacc4\uc640 \ub3d9\ub4f1 \uc218\uc900\uc778 1,000pm/g\uc758 \ubaa9\ud45c \ubbfc\uac10\ub3c4\ub97c \uc124\uc815\ud558\uace0, \uce21\uc815\ud55c\uacc4\ub294 \uae30\uc874 \uad11\uc12c\uc720\uac00\uc18d\ub3c4\uacc4 \uc758 \uac1c\ubc1c\uc218\uc900\uc744 \uace0\ub824\ud558\uc5ec \u00b12g\ub85c \uc124\uc815\ud558\uc600\ub2e4. 2.1.3 \uad11\uc12c\uc720 \uac00\uc18d\ub3c4\uacc4\uc758 \uc6d0\ub9ac \ubc0f \uc131\ub2a5\uac1c\uc120 \uad11\uc12c\uc720\uc13c\uc11c\ub97c \uc801\uc6a9\ud55c \uac00\uc18d\ub3c4\uacc4\uc758 \uac00\uc7a5 \uc77c\ubc18\uc801\uc778 \uad6c\uc870\ub294 Fig. 2\uc5d0 \ub098\ud0c0\ub0b8 \ubc14\uc640 \uac19\uc774 FBG \uc13c\uc11c\uac00 \uc77c\uccb4\ub85c \ubd80\ucc29\ub41c \uce94 \ud2f8\ub808\ubc84\uc5d0 \ub9e4\uc2a4\ub97c \ubd80\ucc29\ud558\uc5ec, \ub9e4\uc2a4\uc758 \uc9c4\ub3d9\uc73c\ub85c \uc778\ud55c \uce94\ud2f8\ub808\ubc84 \uc758 \ubcc0\ud615\uc744 \ud1b5\ud574 \uac00\uc18d\ub3c4\ub97c \uc0b0\uc815\ud558\ub294 \ubc29\uc2dd\uc774\ub2e4. \uc774\ub7ec\ud55c \uae30\uc874\uc758 \uad11\uc12c\uc720 \uac00\uc18d\ub3c4\uacc4 \uad6c\uc870\ub294 \uce94\ud2f8\ub808\ubc84\uc758 \uac15\uc131 \uacfc \ub9e4\uc2a4\uc5d0 \ub530\ub77c\uc11c \ubbfc\uac10\ub3c4\uac00 \uacb0\uc815\ub41c\ub2e4. \ub530\ub77c\uc11c \uce21\uc815 \ubbfc\uac10\ub3c4 \ub97c \ub192\uc774\uae30 \uc704\ud574\uc11c\ub294 \ub9e4\uc2a4 \uc911\ub7c9\uc744 \ub192\uc774\uac70\ub098 \uce94\ud2f8\ub808\ubc84\uc758 \uac15\uc131 \uc744 \ub0ae\ucd94\ub294 \ub450 \uac00\uc9c0 \ubc29\uc548\uc774 \uc788\uc744 \uc218 \uc788\ub2e4. \uadf8\ub7ec\ub098, \ub9e4\uc2a4 \uc911 \ub7c9\uc744 \ub192\uc774\uae30 \uc704\ud574\uc11c\ub294 \uc13c\uc11c \ud06c\uae30\uac00 \ucee4\uc9c0\ub294 \ub2e8\uc810\uc774 \uc788\uc73c\uba70 \uce94 \ud2f8\ub808\ubc84 \uac15\uc131\uc744 \ub0ae\ucd94\uae30 \uc704\ud574\uc11c\ub294 \uc13c\uc11c\uc758 \uce21\uc815\ubc94\uc704, \uc7ac\ud604\uc131, \ucda9 \uaca9\uac15\ub3c4 \ub4f1 \ub9ce\uc740 \uc0ac\ud56d\ub4e4\uc744 \uace0\ub824\ud574\uc57c \ud55c\ub2e4\ub294 \ub2e8\uc810\uc774 \uc788\ub2e4. \ub530 \ub77c\uc11c \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 \ud1a0\ubaa9\uad6c\uc870\ubb3c\uc5d0 \uc124\uce58\uac00 \uc6a9\uc774\ud558\ub3c4\ub85d \ud06c\uae30 \uac00 \ud06c\uc9c0 \uc54a\uc73c\uba74\uc11c\ub3c4 \ubbfc\uac10\ub3c4\ub97c \ub192\uc77c \uc218 \uc788\ub294 \ubc29\uc548\uc73c\ub85c \uad11\uc12c \uc720 \uac00\uc18d\ub3c4\uacc4\uc758 \uad6c\uc870\ub97c \ubcc0\uacbd\ud558\uc600\ub2e4. \uc77c\ubc18\uc801\uc778 \ubcf4 \uad6c\uc870\ubb3c\uc5d0 \ubc1c\uc0dd\ud558\ub294 \uc751\ub825\uc740 \ub2e4\uc74c\uc758 \uc2dd\uc5d0 \uc758\ud558 \uc5ec \uacb0\uc815\ub41c\ub2e4. (1) \uc5ec\uae30\uc11c, f : \uc751\ub825 \uc5ec\uae30\uc11c, M : \uc791\uc6a9\ubaa8\uba58\ud2b8(pL) \uc5ec\uae30\uc11c, p : \ud558\uc911(\ub610\ub294 \uc9c8\ub7c9) \uc5ec\uae30\uc11c, L : \uace0\uc815\ub2e8\uc5d0\uc11c \ub9e4\uc2a4\uae4c\uc9c0\uc758 \uac70\ub9ac \uc5ec\uae30\uc11c, I : \ub2e8\uba742\ucc28\ubaa8\uba58\ud2b8, \uc5ec\uae30\uc11c, y : \uc911\ub9bd\ucd95\uc73c\ub85c\ubd80\ud130\uc758 \uac70\ub9ac \ub3d9\uc77c\ud55c \uce94\ud2f8\ub808\ubc84, \ub9e4\uc2a4 \uad6c\uc870\uc758 \uacbd\uc6b0, \uc2dd(1)\uc5d0 \uc758\ud558\uc5ec \ub3d9\uc77c \ud55c \uac00\uc18d\ub3c4 \ub610\ub294 \uacbd\uc0ac\uac01 \ubc1c\uc0dd \uc2dc \ub2e8\uba742\ucc28\ubaa8\uba58\ud2b8 I\uc640 \uc791\uc6a9\ubaa8 \uba58\ud2b8 M\uc774 \ub3d9\uc77c\ud558\uae30 \ub54c\ubb38\uc5d0, \uc911\ub9bd\ucd95\uc73c\ub85c\ubd80\ud130\uc758 \uac70\ub9ac y\uc5d0 \ub530 \ub77c\uc11c \uce21\uc815 \uc815\ubc00\ub3c4\uac00 \ubcc0\ud654\ud55c\ub2e4. \uc544\ub798\uc758 Fig. 3\uacfc \uac19\uc774 \uae30\uc874 \uac00 \uc18d\ub3c4\uacc4\uc758 \uacbd\uc6b0\uc5d0\ub294 \uce94\ud2f8\ub808\ubc84 \ubc14\ub85c \uc704\uc5d0 FBG \uad11\uc12c\uc720 \ubcc0\ud615 \ub960\uc13c\uc11c\ub97c \ubd80\ucc29\ud558\uc600\uc73c\ub098, \uac1c\ubc1c \uac00\uc18d\ub3c4\uacc4\uc5d0\ub294 \uc815\ubc00\ub3c4 \ud5a5\uc0c1\uc744 \uc704\ud574\uc11c\ub294 y\ub9cc\ud07c \ub5a8\uc5b4\uc9c4 \uc704\uce58\uc5d0 FBG \uad11\uc12c\uc720 \ubcc0\ud615\ub960\uc13c\uc11c \uc591 \ub2e8\uc744 \uace0\ucc29\uc81c\uc5d0 \uc758\ud558\uc5ec \ubd80\ucc29 \uace0\uc815\ud568\uc73c\ub85c\uc368 \ub3d9\uc77c\ud55c \ub9e4\uc2a4 \ubc0f \uce94 \ud2f8\ub808\ubc84 \uad6c\uc870\uc5d0 \ub300\ud558\uc5ec \uc815\ubc00\ub3c4\ub97c \ud06c\uac8c \ud5a5\uc0c1\uc2dc\ud0ac \uc218 \uc788\ub3c4\ub85d \uace0 \uc548\ud558\uc600\ub2e4. \uc608\ub97c \ub4e4\uba74 \uae30\uc874\uc758 \uce94\ud2f8\ub808\ubcf4\uc640 \ub9e4\uc2a4\ub85c \uc774\ub8e8\uc5b4\uc9c4 \uc2dc \uc791\ud488\uc758 \uad6c\uc870\ub85c \uc81c\uc791 \uc2dc \uce21\uc815\uac10\ub3c4(Sensitivity)\uac00 10pm/g\ub77c\uace0 \uac00\uc815\ud55c\ub2e4\uba74, Fig. 3\uacfc \uac19\uc774 y\ub97c 10\ubc30\ub85c \uc99d\uac00\uc2dc\ud0a4\uba74 \ub3d9\uc77c\ud55c \uad6c\uc870\uc5d0\uc11c \ud2b9\ubcc4\ud55c \ub178\ub825 \uc5c6\uc774 \uce21\uc815\uac10\ub3c4\uac00 10\ubc30\uc778 100pm/g\uac00 \ub41c\ub2e4. \ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 \uc774\ub7ec\ud55c \uc6d0\ub9ac\ub97c \uc774\uc6a9\ud558\uc5ec FBG \uad11\uc12c\uc720 \ubcc0\ud615\ub960 \uc13c\uc11c\uc758 \ubd80\ucc29\uc704\uce58 \ubcc0\uacbd\uc744 \ud1b5\ud558\uc5ec \uc815\ubc00\ub3c4\ub97c \ud5a5\uc0c1 \uc2dc\ud0a8 \uac00\uc18d\ub3c4\ub97c \uac1c\ubc1c\ud558\uc600\ub2e4. f My I -------= 2.1.4 \uac1c\ubc1c \uac00\uc18d\ub3c4\uacc4\uc758 \uac80\uc99d Fig. 1\uc758 \ucf58\ud06c\ub9ac\ud2b8\uada4\ub3c4\uac00 \uc124\uce58\ub41c \ud130\ub110\uc758 \ub77c\uc774\ub2dd\uc5d0\uc11c \uce21\uc815 \ud55c \uc5f4\ucc28\uc6b4\ud589\uc5d0 \uc758\ud55c \uc9c4\ub3d9 \uce21\uc815 \uacb0\uacfc\uc5d0 \uc758\ud558\uba74, \ud130\ub110 \ub77c\uc774\ub2dd \uc758 \uc9c4\ub3d9 \uce21\uc815\uc744 \uc704\ud574\uc11c\ub294 \uac00\uc18d\ub3c4\uc758 \ubd84\ud574\ub2a5\uc774 0.0005g \uc774\ud558 \ub85c \uac1c\ubc1c\ub418\uc5b4\uc57c \ud558\ub294 \uac83\uc73c\ub85c \ud310\ub2e8\ub418\uc5c8\ub2e4. \uc0c1\uae30 \ubaa9\uc801 \uc0ac\uc591\uc744 \ub9cc\uc871\ud558\uae30 \uc704\ud55c \ucd5c\uc801 \uc124\uacc4 \ud6c4 \uc2dc\uc791\ud488\uc744 \uc81c\uc791\ud558\uc5ec 1g\uc5d0 \ub300\ud55c \uce21\uc815 \ubbfc\uac10\ub3c4\uc640 \uac00\uc9c4\uc5d0 \uc758\ud55c \uce21\uc815\ubc94\uc704\ub97c \uc2e4\ud5d8\uc801\uc73c\ub85c \uac80\uc99d\ud558 \uc600\ub2e4. Fig. 4\ub294 \uac1c\ubc1c \uac00\uc18d\ub3c4\uacc4\uc5d0 \ub300\ud558\uc5ec 1g\uc758 \uac00\uc18d\ub3c4\ub97c \uac00 \ud55c \uacbd\uc6b0 \uce21\uc815\ub41c \ud30c\uc7a5\uc774\ub2e4. 3\ud68c\uc758 \ub3d9\uc77c\ud55c \uac80\uc99d\uc2dc\ud5d8 \uacb0\uacfc 1g \uc758 \uac00\uc18d\ub3c4\uc5d0 \ub300\ud558\uc5ec 1,400pm\uc758 \uc77c\uc815\ud55c \ud30c\uc7a5\uc774 \ub098\ud0c0\ub0ac\uc73c\uba70, 1,000pm/g\ub85c \uc124\uc815\ud55c \ubbfc\uac10\ub3c4 \uc694\uad6c \uc131\ub2a5\uc744 \ub9cc\uc871\ud558\uc600\ub2e4. \ub610\ud55c pre-strain \uc870\uc808\uc5d0 \uc758\ud558\uc5ec \uac00\uc18d\ub3c4 \uce21\uc815\ubc94\uc704\ub3c4 \u00b12g \uc774\ub0b4\ub85c \uc694 \uad6c \uc131\ub2a5\uc774 \ub9cc\uc871\ub418\uc5c8\ub2e4." + ] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.13-1.png", + "caption": "Figure 8.13: 3D ASO starting point: NACA 0012 surface of revolution enclosing human avatar", + "texts": [ + " Finally, I set up single and multipoint optimization cases where the geometry to be enveloped is that of a person in a seated position, with parameters identical to the previous case (Table 8.3). I exported a high-resolution model of an average U.S. adult in a seated driving position to a 190 stereolithography file (STL) using the University of Michigan Transportation Research Institute\u2019s (UMTRI) online tool6 [260]. I then resized and reduced the complexity of the triangulated mesh using Autodesk Meshmixer7 and imported it directly into the optimization environment; the final mesh (Figure 8.9b) had 626 triangles. Figure 8.13 shows the initial condition of the optimization. Figure 8.14 shows the optimized shape for the single point case. The drag decreased 61.3% compared to the grossly oversized baseline single point case. The optimizer generated a rounded leading edge and an elongated trailing cone with moderate closure angle. In this case, the rotational asymmetry is due to the asymmetric constraint geometry, not the flow condition. Figure 8.15 shows the optimized shape for the multipoint case. Drag decreased 78.5% compared to the grossly oversized baseline multipoint case" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002916_3272-021-00510-0.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002916_3272-021-00510-0.pdf-Figure13-1.png", + "caption": "Fig. 13 Final HLFC system architecture", + "texts": [ + " The comparison of the architectures in terms of total power requirements 1 3 PHLFC,tot indicates no significant difference between the collective and the individual ducting (see right side in Fig.\u00a012). With an increasing number of compressors, however, the power requirement decreases and almost converges from 3 compressors upwards. The power-saving with more than three compressors is disproportionate to the mass increase. That is why the final chosen configuration for the HLFC system is a decentralized architecture with three compressors and a collective ducting system. This architecture is depicted in Fig.\u00a013. The red dots mark the compressors, the green lines the ducting system with the outflow valve (green dot), and the blue line represents the electric wiring from the avionic bay to the compressors. The final parameters for the chosen HLFC system architecture can be found in Table\u00a05. With this architecture and the previously optimized suction distributions, the HLFC retrofit is derived next. For a suitable starting point for the evaluation of the HLFC technology, a turbulent reference (TR) of the ARB2028 is designed using MICADO [26, 34] as well as the database approach (see Sect" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.12-1.png", + "caption": "Figure 8.12: 3D multipoint minimum drag result for cylinder, \u03c1 = 1200", + "texts": [ + "3% 187 188 compared to the baseline single point case. The optimized shape is a long fairing with relatively tight leading edge curvature. The tightly curved leading edge is characteristic of single point aerodynamic shape optimization, since robustness to varying flow conditions is not required. Even though the problem is parameterized in a Cartesian frame, the finished shape is almost perfectly axisymmetric, as we would expect from a rotationally symmetric spatial constraint and flow condition. Figure 8.12 shows the optimized shape for the multipoint case. Drag decreased 52.2% compared to the baseline multipoint case. The optimized shape has a gently rounded nose and broader 189 aft body closure angle, which visually matches the crossflow condition. Compared to the single point case, the crossflow condition has added thickness in the x-y plane and reduced length overall. The rounder nose and extra thickness-to-chord ratio both help improve resistance to flow separation at the crossflow condition. Visually, the x-y thickness is not required simply for spatial integration reasons, but the x-z plane generally tightly conforms to the cylinder" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001789_cle_download_505_375-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure12-1.png", + "caption": "Figure 12. Improved models of IPMSM using Hiperco 50A material (a) 2 kW motor, (b) 5 kW motor and (c) 120 kW motor.", + "texts": [ + " Hiperco 50A, a higher-grade material, is used to form the stator core and teeth, whereas the rotor core material is kept unchanged. The Hiperco 50A material has magnetic saturation at 2.3 T and has properties that make it superior, as discussed in Table 3. Applying Hiperco 50A results in lower iron core losses and decreased magneto-motive force drop on the magnetic circuit. This would appear in the lower excitation requirement of IPMSM [26]. Finite element (FE) models of these ratings created based on the design details are shown in Figure 12. The design details of improved motors with Hiperco 50A material used as stator core for all three ratings are shown in Table 4. Dimensions of the improved motors listed are determined based on manual iterations assuming a higher value of flux density in the stator core as Hiperco 50A has high magnetic saturation (2.3 - 2.4 T). High flux density in the stator core is considered to reduce size and weight. During this exercise, the stator slot area is kept the same as the initial design. The width of the NdFeB permanent magnet bars used for designing the rotor poles, length of the air gap, and outer rotor diameter remain untouched and are similar to those of reference model for all three ratings" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001620_onf_ICEM14_08002.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001620_onf_ICEM14_08002.pdf-Figure1-1.png", + "caption": "Fig. 1 Loosening and disengaged of (a) motor-fastening-bolts of \u2018Shinkansen\u2019 (May 1992) and (b) axle bolt of \u2018Steel Dragon 2000\u2019 roller coaster, Nagashima (January 2005)", + "texts": [ + "ost of machines and products have various joint portions (e.g. fastening, welding and adhesive joints) for the effective productivity and maintainability. And bolt-nut joint, one of the joint structures is widely used as it\u2019s easiness to install and remove, produces big fastening power with small force and low price in production. However, several troubles on their strength and reliability occurred at these portions as illustrated in Fig. 1. So, serious attention must be paid to improve the strength and reliability of these portions. External load acting on the bolt-nut joint comes in two types. First, if the line of action of the forces on the joint is more or less parallel to the axes of the bolt, the joint is known to This is an Open Access article distributed under the terms of the Creative Commons Attribution-Noncommercial License 3.0, which permits unrestricted use, distribution, and reproduction in any noncommercial medium, provided the original work is properly cited" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001782_f_version_1663924178-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001782_f_version_1663924178-Figure4-1.png", + "caption": "Figure 4. Prototype of electromagnetic driver. 1\u2014nylon protective layer, 2\u2014stator core, 3\u2014copper wire, 4\u2014self-tapping screws.", + "texts": [ + " The thrust bearing is placed on the shafting tube so that the axial load acts directly on the protective shell without passing through the distraction mechanism. The distal bone begins to distract with the assistance of the distraction nail, meaning bone lengthening occurs as long as sufficient torque is provided. 2.2.2. Electromagnetic Driver The electromagnetic driver acts as a PMBLDC motor stator group, providing the external rotating magnetic field required to drive the internal permanent magnet, as shown in Figure 4. The electromagnetic driver mainly consists of a stator core, self-tapping screws, nylon protective layers, and copper wire coils. The electromagnetic driver is designed as a tuck-in design for the convenience of wearing. The stator core and middle nylon protective layer are attached firmly by screwing them together with the self-tapping screws. The function of the nylon protective layer is to prevent the sharp edges of silicon steel sheets from accidentally cutting the patient or current leakage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001833_jeee.2013.010202.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001833_jeee.2013.010202.pdf-Figure5-1.png", + "caption": "Figure 5. The cross section of the simulated SRM", + "texts": [ + " Taking into account the ratio of performance over cost the flux differential detector seems to be the best solution for advanced fault tolerant systems [21]. The effectiveness of this detector was studied by means of finite elements analysis (FEA). All the winding faults of a SRM cause unsymmetrical field distribution inside the machine [22]. The best way to emphasize these changes is to perform a precise numeric field analysis of the SRM. The nameplate data of the simulated 8/6 poles SRM are: 350 W, 300 V, 6 A, 600 r/min. The cross section of the motor together with its pole notations is given in Figure 5. The FEA was performed by means of Flux 2D [23]. The simulated conditions of the machine were: 1. healthy machine 2. coil A with 20% of turns shorted 3. coil A with 50% of turns shorted The most significant results for the machine conditions taken into study are given in Figure 6. The obtained flux lines are shown for the A stator pole being aligned, half-aligned and unaligned relatively to the rotor poles. As it can be clearly seen in these plots the symmetry of the magnetic flux distribution is more and more lost as the severity of the faults (the number of the shorted coils) is increasing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004992_O201217653783682.pdf-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004992_O201217653783682.pdf-Figure21-1.png", + "caption": "Fig. 21. Prototype motor of proposed BLSRM", + "texts": [ + " In the proposed structure, current i1 is conducted. The results are shown in Fig. 20. From the figure, we can find that radial force in the proposed structure remains almost constant with the variation of rotor position. However in the conventional structure, radial force varies noticeable with rotor position. In order to satisfy higher radial force, the current in the radial force winding of a conventional structure has to be increased. Experimental verification of the BLSRM with hybrid stator poles was performed to verify its validity. Fig. 21 shows stator and rotor designed for the prototype system. Detailed specifications of proposed BLSRM are shown in Table 3. Inner Diameter of Stator (mm) 62 Yoke Thickness of Stator (mm) 10 Length of Air Gap (mm) 0.3 Inner Diameter of Rotor (mm) 18 Yoke Thickness of Rotor (mm) 9.7 Fig. 22 shows the static experimental result. A 0.6kgf load is applied in radial directions. The top two curves are displacements in x and y directions, respectively. From the result, it can be seen that when the suspending controller is applied, the rotor can be kept in the balanced position" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004200_f_version_1602323787-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004200_f_version_1602323787-Figure14-1.png", + "caption": "Figure 14. Induction heating system installed under the stock-rail foot; 1: heating plate, 2: inductor, 3: fastening grip, and 4: power supply wire [21,22].", + "texts": [ + " An inductor producing a variable m gnetic field (5) and a ferrite pro ctive plat Energies 2020, 13, 5262 8 of 19 (6) are the basic parts of the heater. Placement of a power supply and control system (4) within the heater (2) is characteristic of this solution. Its simple design, high efficiency, fast snow melting, and applicability to all turnout models are among its advantages [20]. Energies 2020, 13, x FOR PEER REVIEW 8 of 19 Figure 13. Snow melting device mounted on the stock-rail web; 1: stock-rail web, 2: heater, 3: clamping system, 4: power supply system, 5: inductor, and 6: protective plate [20]. Figure 14 presents a modern solution of turnout induction heating [21,22]. This setup consists of an internal coil that generates a magnetic flux in the main core. The heating plate is made of a material that has poor magnetic properties, causing losses in the magnetic flux. The heat from the heating plate is distributed to the space between the stock-rail and switch-rail. The heating element reaches its operating temperature of about 120\u2013135 \u00b0C within five minutes, melting away snow and ice very effectively", + " s f s li ti s is i f t s l f t r l f ff ti t r t -s i t s t s f t f r il tr ffi . r s lts f r ff ts f t s s st s r il tr l s st s r t il l it r. ri i l t r t i ti ti s l ti is i t i i r [ , ]. I t r is i st ll i t rt f t sli l t l i t s it -r il tr ls. i t r i i is s li fr i -fr lt r t r . s l ti is si l i its si . t r l s i t r ss f i ti ti i r s s t sli l t t r t r , il t r t r s f t st -r il s it -r il, i r i ir t t t it t sli l t , ris s ll. ti s st rs r ffi i t, si i r s s l lt r i l i t s t t st -r il s it -r il t ir s. Figure 14. Induction heating system installed under the stock-rail foot; 1: heating plate, 2: inductor, 3: fastening grip, and 4: power supply wire [21,22]. c on heating equipment il ustrated in Figures 9\u201314 are notable for the variety of novel technol gical solutions. The authors are not aware of any labo ato y e of these solutions. Absence of such publications s evidence of th scale of the pr blem of effective turnout de-snowing and the consequent safety of rail traffic. Any results for effect of these systems on rail control systems are not available either" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002162_tation-pdf-url_53237-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002162_tation-pdf-url_53237-Figure19-1.png", + "caption": "Figure 19. Waveguide bends and junctions.", + "texts": [ + " Although corporate feed network has more loss than parallel feed network, it has much wider impedance bandwidth when tapered microstrip lines and tapered T-junctions are used. Each antenna input was defined as a 50 Microwave Systems and Applications260 The optimum value for the waveguide combiner was calculated to be an 8-to-1 combiner, with reduced height. Figure 18 shows a sketch drawing of the waveguide combiner. Most of the losses and the power division take place in the bends and T-junctions. Figure 19 shows a closer view of the waveguide junctions and bends. The parameters in Figure 19 are the main optimization parameters. Optimizer goals were to minimize losses and have better impedance match less than -15 dB throughout the desired bandwidth. The most crucial component in the design of such divider is the position of the shorting probe. Figure 20 shows the surface current of optimized combiner section. Optimized results are given in Figure 21. Figure 21 (bottom graphic) shows the transition characteristic at all ports; simulations estimate the worst case, a loss of 0.5 dB. The prototype antenna with all subarrays is built and the prototype is displayed in Figure 22" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure10.2-1.png", + "caption": "Figure 10.2: NACA\u2019s converted B-57 testbed, which used liquid hydrogen to power one engine [271]", + "texts": [ + " Hydrogen fuel in aviation has a surprisingly long history. Soon after liquid hydrogen was first produced for the space program, the NACA experimented with hydrogen combustion aircraft concepts. Silverstein and Hall [270] proposed using hydrogen fuel for a subsonic high-altitude bomber (Figure 10.1) in a declassified 1955 NACA research memo. Even then, it was apparent that integrating the enormous hydrogen tanks into the aircraft would be a significant challenge. From 1957 to 1959, NACA flew a B-57 Canberra bomber (Figure 10.2) converted to run one engine using liquid hydrogen fuel [271]. The airplane was able to transition from jet fuel to hydrogen and back again on numerous successful flights. The pilots noted that the hydrogen-powered engine tended to leave contrails even when the kerosene-powered engine did not. Simultaneously, Kelly Johnson\u2019s Skunk Works was seriously considering building a hydrogen-powered supersonic bomber [271]. The study airplane, known as the CL-400 Suntan, was canceled by 1958, but the government learned valuable insights on the safe handling of hydrogen fuels" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002118___format_pdf_lang_en-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002118___format_pdf_lang_en-Figure3-1.png", + "caption": "Fig. 3. A TNFD communication scenario: a) TAC verification scheme by estimating angle q and b) angle definition.", + "texts": [ + " Our approach is based on a condition called in this paper TAC as mentioned above. In other words, two UEs can participate simultaneously in TNFD communication when the separation angle between the locations of these UEs is sufficiently high than a threshold value at the PT side or the ST side depending on if the ongoing TNFD communication is source-based TNFD or destination-based TNFD. Before formulating TAC, we are interested to derive the angle (between the elements) that must be greater than a given threshold value. Fig. 3 a) shows an example of a TNFD communication scenario between the three following elements, BS, 1UE and 2UE , where 1UE and 2UE are assumed to be in the transmission range of each other. Moreover, in Fig. 3 a) are depicted the antennas beams 1BB (from BS toward 1UE ) , 2BB (from 2UE toward BS) and 21B (from 2UE toward 1UE ) , and their Brazilian Microwave and Optoelectronics Society-SBMO received 16 June 2020; for review 23 June 2020; accepted 15 Oct 2020 Brazilian Society of Electromagnetism-SBMag \u00a9 2021 SBMO/SBMag ISSN 2179-1074 symmetric lines that point exactly on the desired direction. Observe that q is the angle at the 2UE side between the symmetric lines of the beams 2BB and 21B . As illustrated in Fig. 3 a), we assume that the BS has a data packet for 1UE , and 2UE also has a data packet for the BS. Then, the BS can become PT or ST. If the BS initiates TNFD communication it becomes the PT and SR, 1UE and 2UE become the PR and the ST, respectively. If 2UE initiates a TNFD communication, it becomes the PT, then the BS become the PR and ST, while 1UE becomes the SR. In both scenarios, the angle q in Fig. 3 a) must be greater than a given threshold value in order to avoid inter-user interference from 2UE to 1UE . Before selecting the 2UE as the ST if 1UE is the PR or before selecting 1UE as the SR if 2UE is the PT, the BS must check whether, the angle q between the symmetric lines of the beams 2BB and 21B is greater than a given threshold value. The value of q depends not only on the width of the beam of the employed antennas [34] but also on the value of as shown in Fig. 3 a), and it is expressed as 2q b = + (1) where 2 b is the width of the beam as mentioned above, and is the angular separation of the beam 2BB and 21B as shown in Fig. 3 a). Fig. 3 b) indicates how we can derive the angle , where represents the angle between the two tangent lines at point P\u2019 of the two beams 2BB and 21B , respectively. The reference point P\u2019 corresponds to the half-power bandwidth (HPBW) of each beam. When is negative then the two beams may overlap and interference may occur if this ST or SR is selected to participate in the ongoing TNFD communication. The accurate choice of depends on the radiation pattern of the used antennas system. If the gain of the main lobe reduces sharply increasing angular separation from the main lobe direction, then the value of can be small" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure14-1.png", + "caption": "FIGURE 14. Rectangular conductive plane with four capacitive exciters; L = 150 mm, W = 75 mm, L1 = 33 mm, L2 = 35 mm, D = 5 mm. [25].", + "texts": [ + " It is apparent that in the frequency range of interest (from 2.4 to 2.5 GHz), most of the modes have an eigenvalue magnitude lower than 2, except for mode 7, 9 and 10, which are higher order modes. Specifically, mode 7 and 10 are identified as inductive modes (\u03bb > 0), whereas mode 9 is a capacitive mode (\u03bb < 0). Therefore, these higher order modes do not significantly contribute to the total radiated power in this frequency range. Four capacitive exciters have been used with the rectangular conductive plane as shown in Fig. 14. Next, the normalized modal weighing coefficient (MWC) amplitude analysis is performed when the CCEs are individually excited. This helps to understand which current modes are efficiently excited over the conductive plane within 2.4 to 2.5 GHz. Fig. 15 shows that the sources located along the y-axis (Port 1 and Port 2) can excite both modes 2 and 8 from the antenna. On the contrary, the CCEs located along the x-axis (Port 3 and Port 4) allows the efficient excitation of modes 2 and 5. The prototype of the proposed null-scanning antenna is illustrated in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000771_1081-023-09833-9.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000771_1081-023-09833-9.pdf-Figure4-1.png", + "caption": "Fig. 4 Subdivision of the wheel rim FE model into three main regions", + "texts": [ + " Theproposed simplified tiremodelling approachhas proved tobe effective in providing an accurate stress field estimation on thewheel both for static (Ballo et al. 2016a, 2018) and dynamic (Ballo et al. 2020b; Previati et al. 2019) loading conditions. The wheel rim numerical model is divided into three main regions, namely the outer rim, the central hub and the spokes. The outer rim is modelled by means of three-dimensional shell elements that reproduce the rim profile. Two partitions identify three regions of the wheel outer rim, namely the rim well (gray area in Fig. 4) and the rim bead seats (orange area in Fig. 4). Each region features a different rim thickness. Tire-rim reaction forces are introduced as a nodal force distribution applied at the bead seats. The rim central hub is built as a three-dimensional shell. As shown in Fig. 5 , the offset between the mounting surface and the wheel central plane is reproduced. A kinematic coupling realizes the connection between the flange inner edge and a central node fixed to the ground (Fig. 4). Linear quadrilateral elements are used for the modelisation of both the outer rim and the central hub. The adoption of shell elements is justified by the fact that both the outer rim and the central hub feature the thickness much smaller than the other dimensions. The spokes are modelled by linear beam elements (Fig. 4), connecting the outer nodes on the outer edge of the central hub and the portion of the rim surface connected to the spoke tip. Beam elements are exploited due to the significantly greater length dimension with respect to the other two dimensions. The connection between beams and shells is realized by sharing the nodes at the interface. The feasibility of modelling the wheel rim in such a way is demonstrated by performing comparative simulations on a numerical model where the outer rim is realized using solid elements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001969_86_s40638-017-0059-1-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001969_86_s40638-017-0059-1-Figure10-1.png", + "caption": "Fig. 10 Axonometric diagram of a double IP vehicle", + "texts": [ + " Significant amount of energy saving has been achieved specifically in the cart and tilt angle control efforts as appeared in Fig.\u00a09a, b. Furthermore, the HSDBC resulted in a great improvement in the control effort for the payload; this can be demonstrated by the significant improvement shown in Fig.\u00a09c in terms of less oscillations and the short time taken by the control signal to stabilize. Case study II: double IP with\u00a0an extended rod In this case study, an additional link is added and hence increasing the degrees of the freedom (DOF) and the complexity of the structure. The double IP with such configuration shown in Fig.\u00a010 is mimicking the scenario of a wheelchair on only two wheels which has been studied significantly by Ahmad and Tokhi [1]. The design of the two-wheeled robotic vehicle is based on double inverted pendulum system with a movable payload moving on an inclined surface with five DOF. The increased DOFs will enable the vehicle to maneuver freely in all directions and in different environments. Moreover, the second link provides an extended height to lift up the payload to a demanded height. The system equations of motion are presented with five highly coupled differential equations as follows: (12) 2C27\u03b4\u0308L + 2C1\u03b4\u0308R + C6\u03b8\u03081 cos(\u03b81 + \u03b1) \u2212 C6\u03b8\u0307 2 1 sin(\u03b81 + \u03b1) + 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure10-1.png", + "caption": "Figure 10. Exploded diagram of the designed motor.", + "texts": [ + " It is as a result of higher volume of the typical motor and consequently providing bigger area to dissipate the heat. The best motor design dimensions are selected based on the proposed candidates from all the methods (genetic algorithm, finite element analysis, and finite volume analysis simulation). However, the final optimized design is made possible with minor changes effectuated by the powerful FEA and FVA, with the strenuous task of changing permanent-magnet thickness, air-gap length, and length of stator yoke and rotor yoke several times. Fig. 10 shows the exploded view of the designed motor which is an inside-out double-rotor single-stator axialflux permanent-magnet motor. Table 7 lists the machine design\u2019s final dimensions and specifications. Figure 11 shows finite element field analysis of the designed 15- stator-slot per pole pair AFPM motor. Fig. 11(a) shows one eighth of the entire motor, the part which is used to model the FEA-designed AFPM motor\u2019s structure: 90\u25e6 of the half motor structure and 1 pole, fulfilling symmetry conditions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004975_load_0_0_49825_53866-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004975_load_0_0_49825_53866-Figure3-1.png", + "caption": "Figure 3: Dual-sided SyncRM: (a) assembly perspective view, (b) cut-out perspective view and (c) cut-out front view", + "texts": [ + " However, the modification of the motor did not affect its inner dimensions, that is the diameter of the shaft remains the same, and so does the (now termed) rotor inner ring (where before, it was just the rotor in Figure 2a), the size and locations of the windings is also the same, and so is the location and size of the stator poles. It is worth mentioning that the modified design is just a first attempt that is by no means optimized; there is plenty of room for improvement. It is assumed that the Dual-sided SyncRM will operate via the same power bus and PWM-controller scheme as the SRM2 [for further details, please see Stuikys and Sykulski (2020)]. A 3D model of the Dual-sided SyncRM is shown in Figure 3, and available (FCStd1, Step, Stl) to download here at this author\u2019s open profile page. This was built with the open-source software FreeCAD, and professionally photo-rendered using the open-source software CADrays. It\u2019s key characteristics are now briefly explained. The stator is composed of a rear structural disc-like feature that fixes onto the vehicle interface, and to which (on the other side) the poles are connected (Figure 3a). In turn, these stator poles slide inside the Dual-sided rotor, in itself composed of an inner and outer ring linked by structural connectors. The windings are virtually the same as the SRM2, with slight modifications being made at each extremity (necessary to hold the windings in place). As shown in the zoom at the lower left corner of Figure 3a, the individual wires are turned around the open slot/gap at the front end and at the closed slot/gap at the back. These prevent the wires from rising above the inner and outer surface of the stator pole (which would result in a clash with the rotor), allowing the rotor to turn freely. A back bearing (Figure 3a left) connects the (fixed) rear disc-like feature of the stator to the shaft (that is, the outer surface of the bearing is fixed from rotating, and the inner surface turns with the shaft) [this is more readily visible at the back of the half model in Figure 3b]. A front bearing provides the second support for the shaft (and thus also to the rotor). Similarly, the outer surface of the front bearing connects to a fixed structure of the vehicle. The rotor is geared to the shaft (via three angularly equidistant slots on the rotor that slide into three corresponding angular protrusions on the shaft \u2014 visible on Figure 3b). The rotor transmits its loads to the shaft, that in turn drives the wheel and/or axle (to which is connected via the inner teeth) [as the half model front view in Figure 3c illustrates]. From a manufacturing perspective, and while it may be complex to execute, it is entirely possible to machine the Dual-sided rotor as a single piece via a series of combined axial translation and rotational cuts. Alternatively, the single piece could be manufactured first via casting, which would be followed by precise machining of the critical surfaces (i.e., the cylindrical inner surface interface to the shaft and the poles\u2019 surfaces interfacing the inner and outer gaps) to the required precision. If extra stiffness (to the stator poles) is required, the tip of the stator poles can be connected via a ring (not shown in Figure 3), where care must be taken for this new ring not to interfere with the rotor. Making both the rotor and stator as single pieces makes it is easier to control the tolerances required to achieve the tight gaps, both radially inner and outer. Achieving the necessary gap width during assembly and operation is priority, and to that effect, the physical geometry of the support connectors in the rotor can (if necessary) be made of another shape (e.g., with angled corners) if it proves to be more convenient for manufacture" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001671_O201325954480036.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001671_O201325954480036.pdf-Figure6-1.png", + "caption": "Fig. 6 Total deformations at natural frequencies of model 1", + "texts": [], + "surrounding_texts": [ + "(a) Fixed support\n(b) Force condition\n\ud37c \uc55e\uc5d0 2500 N\uc758 \uc815\uc801 \ud798\uc744 \uac00\ud588\uc744 \ub54c \ub4f1\uac00\uc751\ub825\uacfc \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 4(a)\uc640 Fig. 4(b)\ub294 \ubc94\ud37c\uc758 \ub098\uc0ac\uad6c\uba4d\uc5d0\uc11c \ucd5c \ub300 \ub4f1\uac00\uc751\ub825\uc774 \uac01\uac01 187.09 MPa\uacfc 278.4 MPa\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc774\ub2e4. Fig. 5(a)\uc640 Fig. 5(b)\ub294 \ubc94\ud37c \uc717\ubd80\ubd84\uc5d0\uc11c \ucd5c\ub300 \ubcc0\ud615\ub7c9\uc744 \ub098\ud0c0\ub0b8 \uadf8\ub9bc\uc73c\ub85c\uc11c \uac01\uac01 1.3772 mm\uc640 2.675 mm \ubcc0\ud615\ub41c \uac83\uc744 \uc54c \uc218\uac00 \uc788\ub2e4. \uc774 \uadf8\ub9bc\uc744 \ubcf4\uba74 Model 2\uc758 \ubcc0\ud615\ub7c9\uc774 Model 1\uc758 \ubcc0\ud615\ub7c9\ubcf4\ub2e4 \ub354 \ud06c\uae30 \ub54c\ubb38\uc5d0 Model 1\uc758 \uad6c\uc870\uac15\ub3c4\uac00 \ub354 \uc88b\ub2e4\uace0 \uc54c \uc218\uac00 \uc788\ub2e4 [7] .\n3.2 \uc9c4\ub3d9 \ud574\uc11d\n\uc55e \ubc94\ud37c\uc758 \uace0\uc720\uc9c4\ub3d9\uc218\ub97c \uad6c\ud558\uae30 \uc704\ud574 \uc9c4\ub3d9 \ud574\uc11d\uc744 \uc218\ud589\ud558\uc600\uace0, Model 1\uacfc 2\uc5d0 \ub300\ud558\uc5ec \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Fig. 6\uacfc Fig. 7\uc5d0\uc11c \ubcfc \uc218 \uc788\ub2e4. \ub610\ud55c \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\uc640 \ubcc0\ud615\ub7c9\uc744 Table 3\uacfc Table 4\uc5d0\uc11c \ud655\uc778\ud560 \uc218 \uc788\uc73c\uba70, Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc5d0 \uc11c\uc758 \ucd5c\ub300 \uc804\ubcc0\ud615\ub7c9\uc740 62.671 mm\uc774\uace0 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc5d0\uc11c \uc758 \uc804\ubcc0\ud615\ub7c9\uc740 36.565 mm\ub85c\uc11c \ucd5c\ub300\uc758 \ubcc0\ud615\ub7c9\uc744 \ubcf4\uc774\uace0 \uc788\ub2e4. Model 1\uc758 4\ucc28\uc640 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc751\ub2f5\uc774 \uac00\uc7a5 \ud06c\ub2e4\uace0 \uc608\uce21\ud560 \uc218 \uc788\ub2e4. \uac01 \ubaa8\ub4dc\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc218\ub97c Table 3\uacfc Table 4 \uc5d0\ub3c4 \ud655\uc778\ud560 \uc218 \uc788\uc73c\uba70, \ubcc0\ud615\uc774 \uc26c\uc6b0\uba70 \uacf5\uc9c4\uc774 \uc77c\uc5b4\ub0a0 \uac00\ub2a5\uc131\uc774 \ud070 \uac83\uc73c \ub85c \ubcf4\uc774\ub294 Model 1\uc758 4\ucc28 \ubaa8\ub4dc\uc758 \uc9c4\ub3d9\uc218\ub294 157.88 Hz\uc774\uace0 Model 2\uc758 6\ucc28 \ubaa8\ub4dc\uc758 \uc9c4\ub3d9\uc218\ub294 222.41 Hz\uc774\ub2e4. \ub530\ub77c\uc11c \ucc28\uccb4\uc5d0", + "(b) Natural frequency at 2'nd\n(c) Natural frequency at 3'rd\n(d) Natural frequency at 4'th\n\uc11c\ub294 \uc2e4\uc81c\ub85c \uac00\ud639\ud55c \uc870\uac74\uc774\ub77c\ub3c4 \ud1b5\uc0c1 \uc774 \uc9c4\ub3d9\uc218 \uc774\uc0c1\uc73c\ub85c\ub294 \uacf5\uc9c4\uc774 \uc77c\uc5b4\ub098\uc9c0 \uc54a\ub294 \uac83\uc73c\ub85c \uc0ac\ub8cc\ub418\uc5b4 \uc774 \uc7a5\uce58 \uc124\uacc4\uc758 \ub0b4\uad6c\uc131 \uac80\uc99d\uc5d0 \uc720 \ud6a8\ud558\ub2e4\uace0 \ubcf4\uc778\ub2e4. \ubcf8 \uc5f0\uad6c \uacb0\uacfc\ub97c \uc790\ub3d9\ucc28\uc758 \ucc28\uccb4 \ubd80\ud488\uc5d0 \uc751\uc6a9\ud55c\ub2e4 \uba74, \ud53c\ub85c \ud30c\uc190 \ubc29\uc9c0 \ubc0f \uadf8 \ub0b4\uad6c\uc131\uc744 \uc608\uce21\ud560 \uc218 \uc788\ub2e4. \uc2e4\uc81c\uc801\uc73c\ub85c \ud558\uc911\uc774 \uc0c1\ub2f9\ud788 \uc791\uc544\uc9c4\ub2e4 \ud558\ub354\ub77c\ub3c4 \ub4f1\uac00\uc751\ub825\uc774\ub098 \ucd5c\ub300\uc751\ub825\uc774 \uadf8\ub2e4 \uc9c0 \uc791\uc544\uc9c0\uc9c0\ub294 \uc54a\uc558\uc73c\uba70, \uacf5\uc9c4\uc758 \uacbd\uc6b0\ub3c4 \uc704\uc5d0 \ub098\ud0c0\ub09c \uacf5\uc9c4\uc218 \uc774\uc0c1 \ub098\ud0c0\ub098\uc9c0 \uc54a\uc558\ub2e4. \ucc28\ub7c9\uc740 \uc8fc\ud589 \uc911 60\uff5e120 cycle/min (1\uff5e2 Hz) \uc758 \uc9c4\ub3d9\uc218\uc5d0\uc11c \uac00\uc7a5 \uc88b\uc740 \uc2b9\ucc28\uac10\uc744 \ubcf4\uc774\uba70 \ud604\uac00\uc7a5\uce58\ub294 \uc774 \ubc94\uc704 \ub0b4 \uc5d0\uc11c \uc124\uacc4\ub41c\ub2e4 [8] . \ub610\ud55c \uc774 \uacb0\uacfc\uc5d0\uc11c \ubcf4\uba74 \uc8fc\ud589 \uc911 157 Hz\uc640 222 Hz\uc5d0\uc11c \uacf5\uc9c4\uc774 \ubc1c\uc0dd\ud558\ub098 \uc2e4\uc81c\uc0c1\uc5d0\uc11c\ub294 \uc774\ubcf4\ub2e4 \ud6e8\uc52c \ub0ae\uc740 \uc9c4\ub3d9\uc218\ub85c \uc6b4\ud589\ub418\uae30 \ub54c\ubb38\uc5d0 \uc2b9\ucc28\uac10\uc774 \uc88b\ub3c4\ub85d \uc124\uacc4\ub97c \ud560 \uc218 \uc788\ub2e4\ub294 \uac80\uc99d \uacb0\uacfc \ub97c \ubcf4\uc600\ub2e4. \uadf8\ub9ac\uace0 \uc2e4\uc81c\uc801\uc73c\ub85c Fig. 2 \ubc0f Fig. 3\uc5d0\uc11c\uc640 \ub611\uac19\uc774 \uc55e \ubc94\ud37c\uc758 \uc55e\uba74\uc5d0 Force\ub97c 2500 N\uc758 \uad6c\uc18d\uc744 \uc8fc\uc5b4, \uc55e \ubc94\ud37c\uc5d0 \uc0dd\uae30\ub294 \ud558\ubaa8\ub2c9 \uc9c4\ub3d9\uc5d0 \ub300\ud558\uc5ec \ud574\uc11d\ud574 \ubcf4\uc558\ub2e4. \uc9c4\ub3d9\uc218\uc758 \ubc94\uc704\ub294 230 Hz\uae4c \uc9c0\ub85c \uc124\uc815\ud558\uc600\ub2e4. \uc55e\uc5d0 Modal \ud574\uc11d\uc758 \uacb0\uacfc\ub97c \ubcf4\uac8c \ub418\uba74 6\ucc28 \ubaa8\ub4dc \uc758 \uace0\uc720\uc9c4\ub3d9\uc218\uac00 230 Hz\ubc94\uc704 \ub0b4\uc5d0 \uc788\uae30 \ub54c\ubb38\uc5d0 \uac00\uc9c4 \uc8fc\ud30c\uc218 \uc601\uc5ed \uc744 \ub9de\ucdb0 \uacf5\uc9c4 \uc8fc\ud30c\uc218\ub97c \ud655\uc778\ud558\uc600\ub2e4. Model 1\uacfc 2\uc5d0 \ub300\ud558\uc5ec \uc9c4\ub3d9\uc218 \uc5d0 \ub300\ud55c \uc9c4\ud3ed \ubcc0\uc704 \uc751\ub2f5\uc744 \uc0b4\ud3b4 \ubcf8 Fig. 8(a), (b)\uc5d0\uc11c \ubcf4\uba74 \uc54c \uc218 \uc788\ub4ef\uc774 Model 1\uc740 159 Hz\uc5d0\uc11c\uc640 Model 2\ub294 110 Hz\uc758 \uc704\ud5d8 \uc9c4 \ub3d9\uc218\ub97c \uac01\uac01 \ub098\ud0c0 \ub0b4\uc5c8\ub2e4. \uc774\ub7ec\ud55c Model 1\uacfc 2\uc5d0 \ub300\ud55c \uc704\ud5d8 \uc9c4\ub3d9", + "(c) Natural frequency at 3'rd\n(d) Natural frequency at 4'th\nTable 3 Maximum total deformation and natural frequency per mode at model 1\nFrequency (Hz) Total deformation (mm)\n1\u2019st Mode 69.85 18.42 2\u2019nd Mode 77.302 19.189 3\u2019rd Mode 138.95 28.845 4\u2019th Mode 157.88 62.671 5\u2019th Mode 171.46 25.46 6\u2019th Mode 199.68 24.944\nTable 4 Maximum total deformation and natural frequency per mode at model 2\nFrequency (Hz) Total deformation (mm)\n1\u2019st Mode 43.001 16.019 2\u2019nd Mode 66.895 33.087 3\u2019rd Mode 108.97 14.083 4\u2019th Mode 111.25 31.77 5\u2019th Mode 134.35 20.562 6\u2019th Mode 222.41 36.565" + ] + }, + { + "image_filename": "designv8_17_0001871_f_version_1703208070-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001871_f_version_1703208070-Figure4-1.png", + "caption": "Figure 4. Configuration, inertia, and body-fixed frame of the quadrotor.", + "texts": [ + " When everything is considered, the ZQ-ARE model solves three distinct TQAREs quite well. It is noteworthy that the discussion given above confirms the ZNN technique\u2019s convergence qualities and Theorem 2\u2019s findings. Additionally, the ZQ-ARE model\u2019s computational complexity is O((2n2 \u2212 n)3), which is similar to that of other ZNN models that approach various quaternion matrix equations (see [25,28,30\u201332]). In this application, the ZNN design technique is used to stabilize the quadcopter device of Figure 4. Determining the position of a quadcopter requires the definition of coordinate systems since it is a vehicle with four separate drives and, at its center of gravity, an electric power system [49,50]. Three Euler angles and the vertical movement in the global coordinate system are the control parameters for a six-degree-of-freedom model device [51,52]. In order to ensure independent control over each drive and minimal aerodynamic effects, it is necessary to consider a fixed-frame body and a symmetrical model structure with the origin in the mass center [53,54]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003638_cmtmte2021_03006.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003638_cmtmte2021_03006.pdf-Figure1-1.png", + "caption": "Fig. 1. Diagram of the relative position of the projections of adjacent disks", + "texts": [ + " And if, for example, it is currently impossible to predict the soil crumbling with high accuracy, then the height of the ridge can be determined quite accurately, and its value has recently become an adjustment parameter. Thus, the analytical determination of the relationship between the height of the furrow bottom ridge and the design and technological parameters of the disk working bodies will allow us to set separate ranges of adjustment parameters at the design stage of the disk harrows. Disk harrows are most often performed with a row-by-row individual arrangement of working bodies. In this case, the mutual arrangement of adjacent disks is performed in three variants (Fig. 1): the orientation of the disks in one direction, the orientation in the \"dump\" and \"collapse\", which are characterized by the size of the radii of the disks, the angles of attack and the inclination of the disks to the vertical. Based on the design parameters, technological reliability and efficiency of disk units, the interaction of neighboring working bodies will be especially strongly reflected in the height of the ridge of the furrow bottom [17]. To study the influence of the design and technological parameters of disk working bodies on the ridges of the furrow bottom during their operation, it is necessary to obtain their relationship theoretically", + " In the case of placing adjacent disk working bodies on the unit\u2019s frame in the same direction, it is necessary to substitute R1 = R2, \u03b11 = \u03b12, \u03b21 = \u03b22 in the resulting equation (8). Then, the height of the ridge of the furrow bottom will be determined by the expression: 2 2 1,2 2( ) cos , 4sin o bz R R \u03b2 \u03b1 = \u00b1 \u2212 (9) where z\u043e1,2 \u2013. coordinates of intersection points of adjacent ellipses along the axis of OZ, if they are of the same orientation. When the adjacent disks are oriented on the unit according to the \"collapse\" option (Fig. 1), the following parameters must be used in the resulting equation (8) : R1 = R2, \u03b11 = \u03b12, |\u2013 \u03b21| = \u03b22. Then, the height of the ridge of the furrow bottom will be determined by the expression: 3 3 1,2 3 cos cos sin (2 cos sin ) ,p A R b B z C \u03b1 \u03b2 \u03b2 \u03b1 \u03b2+ + \u00b1 = (10) where z\u04401,2 \u2013 coordinates of intersection points of adjacent ellipses along the OZ axis when they are oriented in the \"collapse\". 2 3 2 sin cosA R \u03b1 \u03b2= 2 2 2 2 2 2 2 3 sin cos 4 cos (cos 2sin ) 4 (1 2cos )B R R b\u03b1 \u03b2 \u03b1 \u03b2 \u03b2 \u03b1= + + \u2212 \u2212 2 2 2 3 2cos sin 2sinC \u03b1 \u03b2 \u03b1= + To determine the height of the ridge of the furrow bottom when the adjacent disks are oriented on the unit\u2019s frame according to the scheme \"dump\" (Fig. 1), the following parameters must be used in equation (8): R1 = R2, \u03b11 = \u03b12, \u03b21 = |\u2013\u03b22|. After transformations, we obtain: 3 3 1,2 3 cos cos sin (2 cos sin ) ,c A R b B z C \u03b1 \u03b2 \u03b2 \u03b1 \u03b2+ \u2212 \u00b1 = (11) where z\u04411,2 \u2013 coordinates of intersection points of adjacent ellipses along the OZ axis when they are oriented in the \"dump\". Since the height of the ridge of the furrow bottom formed between the projections of two adjacent disk working bodies will be determined only by the lower point of intersection, then in the expressions (9, 10 and 11) it is necessary to use terms with the sign \"\u2013\"" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002883_9393742_09393751.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002883_9393742_09393751.pdf-Figure14-1.png", + "caption": "Fig. 14. Magnetic field distributions in (a) original design, (b) Scheme #1, and (c) Scheme #2.", + "texts": [ + " To have a fair comparison of the two PM-shield schemes (#1 and #2), their magnet volumes should be identical. Hence, hPMx of the arcuate magnet at the rotor side in Scheme #1 equals 9.75 mm. The total magnet volumes for both schemes are 29 cm3. The magnet volume at the stator side is in majority, which is 23.1 cm3. The magnetic field distributions in the original design, i.e. the magnet-free topology, and the two PM-shield schemes at unaligned rotor position at the phase excitation of 8A are presented in Fig. 14. The red and white arrows in Fig. 14 indicate the current flow and magnetic field directions, respectively. It is observed that the PMs can effectively modulate the magnetic field around the current exciting pole, and the leakage field is effectively reduced. Besides, it is noted that no-load magnetic field exists in the PM-shield configurations. Due to the magnetic saturation in the iron core, the flux-linkage loci with the increasing phase current levels are in nonlinearity. Unlike the original design, the total flux linkage of the PM-shield ADS-SRM consists of three components, i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004626_f_version_1458880549-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004626_f_version_1458880549-Figure1-1.png", + "caption": "Figure 1. Representation of the localization of two target vehicles using active light markers. The leading vehicle, endowed with a wide field of view camera, localizes two target vehicles that are equipped with a set of active light markers.", + "texts": [ + " To improve the chances of detecting point features and to identify individual vehicles, this paper proposes to endow the AUVs with light beacons, namely a set of active light markers blinking with distinctive patterns to facilitate their recognition. With this system, it is possible to track vehicles with full information about their relative pose with high accuracy and rapid update rates. In order to have a sensor with the widest possible field of view, an omnidirectional underwater camera was used to provide full vision of the lower hemisphere during the experiments (Figure 1). This paper presents all of the aspects related to the system: the components and methodologies used, as well as the experiments performed and the results obtained. Navigation and localization are two of the most important topics for underwater robotics. While navigation in land and air robotics is mainly based on the use of GPS and inertial sensors, the inability to receive GPS updates underwater makes the task of navigating precisely more challenging [3]. Most AUVs rely on the use of inertial sensors combined with a Doppler velocity log (DVL) [4], an acoustic-based instrument that measures relative velocities with respect to the water or ground" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004576__AME_2009_132087.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004576__AME_2009_132087.pdf-Figure1-1.png", + "caption": "Fig. 1. A-frame scheme", + "texts": [ + " The classical rigid finite element method (RFEM) has been used to discretise the frame. The algorithm of optimisation of the drive function for the drum of the hoisting winch is proposed. The goal of the optimisation is to ensure the stabilization of the load\u2019s position, i.e. to hold it at the required depth regardless of the ship\u2019s motion. In order to achieve appropriate numerical effectiveness, the optimisation problem has been solved using a simplified model of an A-frame. 2. A-frame model The scheme of an A-frame and the most important points of it are presented in Fig. 1. The following denotations are used: F \u2013 supporting structure, P \u2013 pulley, R \u2013 rope, H \u2013 drum of the hoisting winch, L \u2013 load, SR, SL \u2013 right and left servomotor forces, NR, NL \u2013 connection points of servomotors to the A-frame, AR, AL \u2013 connection points of the A-frame to the deck, xF,1,xF,2,xF,3 and xD,1,xD,2,xD,3 \u2013 coordinate systems assigned to the supporting structure (frame) and to the deck, respectively. In the formulation of equations of motion of the system (A-frame), homogeneous coordinates and transformations have been used (presented in details in Craig [2])" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002984__8_2_8_20-00446__pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002984__8_2_8_20-00446__pdf-Figure17-1.png", + "caption": "Fig. 17 The 3D-CAD model of the designed path-generating FCP", + "texts": [ + "16 shows the force-displacement characteristics when two links of the designed FCP displace in the us-direction from 1p(tm) = 1p(0.5). The red broken line denotes the characteristics when the posture angles were kept in the angles to maximize M(\u03b8r,m, \u03b8p,m, \u03b8y,m). The green dotted line denotes the characteristics when the posture angles were kept in the angles to minimize M(\u03b8r,m, \u03b8p,m, \u03b8y,m). This result shows that the force-displacement characteristics varies around the specified characteristics as expected in the design. The structure of the FCP designed in 3D-CAD is shown in Fig.17. Therefore, the FCP allowing a complex main-relative motion was able to be designed. In this section, a prototype of the FCP is fabricated and examined by experiments to confirm the validity of the design method. It was investigated that a prototyped FCP can generate the specified force-displacement characteristics translational directions of in sub-DOF in order to validate the proposed design method. In order to perform the experiment easily, the path-generating FCP which allows translation along a linear trajectory and 3-axial rotations was designed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003167_ostyka2018_01003.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003167_ostyka2018_01003.pdf-Figure2-1.png", + "caption": "Fig. 2. Geometric parameters of the brakes: a) basic version; b) with circular blade system; c) with inclined blades.", + "texts": [ + " The arguments in favor of the calculation using the QFD methodology are: \u2022 advanced analysis tools- for a large number of projects it is difficult and expensive to create an appropriate experimental model; in addition, CFD analysis allows to obtain data, which measurement in a physical experiment is impossible; \u2022 the possibility of multivariate analysis - allows you to test a large number of project variants in a short time; \u2022 increase productivity, design quality and reduce costs - CFD is a tool that ultimately contributes to the rapid appearance of the product on the market. Three types of open blade systems were selected for comparative analysis: \u2022 straight radial blades (basic version); \u2022 circular blades; \u2022 inclined blades (450). Figure 2 shows the basic geometric parameters of the three brake-retarder variants under study. The figure adopted the designation: \u03b4 - the thickness of the blade; D - the active diameter of the brake-retarder; d - the inner diameter of the flow of the brake-retarder; R0 - radius of curvature of the flow part of the retarder; Rl - the radius of curvature of the blades. a) b) Simulation of oil flow in the flow part of the brake-retarder is performed within the model of turbulent fluid flow [5]. The equations describing the change in velocity, pressure, turbulent energy, and dissipation have the form: - Navier-Stokes equation \ud835\udf15\ud835\udf15\ud835\udc7d\ud835\udc7d \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udc7d\ud835\udc7d\u2a02 \ud835\udc7d\ud835\udc7d) = \u2212 \u2207\ud835\udc5d\ud835\udc5d \ud835\udf0c\ud835\udf0c + 1 \ud835\udf0c\ud835\udf0c \u2219 \u2207(\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61) \u2219 (\u2207\ud835\udc7d\ud835\udc7d + (\u2207\ud835\udc7d\ud835\udc7d)\ud835\udc47\ud835\udc47) + \ud835\udc54\ud835\udc54, - continuity equation \u2207(\ud835\udc7d\ud835\udc7d) = 0, - equations for turbulent energy and dissipation rate \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 = \ud835\udc50\ud835\udc50\ud835\udf07\ud835\udf07 \u2219 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udc58\ud835\udc582 \ud835\udf00\ud835\udf00 , \ud835\udf15\ud835\udf15(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc58\ud835\udc58) \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc7d\ud835\udc7d \u2219 \ud835\udc58\ud835\udc58) = \u2207 ((\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \ud835\udf0e\ud835\udf0e\ud835\udc58\ud835\udc58 ) \u2219 \u2207\ud835\udc58\ud835\udc58) + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \u2219 \ud835\udc3a\ud835\udc3a \u2212 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf00, \ud835\udf15\ud835\udf15(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf00) \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc7d\ud835\udc7d \u2219 \ud835\udf00\ud835\udf00) = \u2207 ((\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \ud835\udf0e\ud835\udf0e\ud835\udf00\ud835\udf00 ) \u2219 \u2207\ud835\udf00\ud835\udf00) + \ud835\udc50\ud835\udc501 \u2219 \ud835\udf00\ud835\udf00 \ud835\udc58\ud835\udc58 \u2219 \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \u2219 \ud835\udc3a\ud835\udc3a \u2212 \ud835\udc50\ud835\udc502 \u2219 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf002 \ud835\udc58\ud835\udc58 , where V \u2013 the velocity vector; t \u2013 time; p \u2013 pressure; \u03c1 \u2013 the fluid density; \u03bc \u2013 the molecular dynamic viscosity; \u00b5t \u2013 the turbulent dynamic viscosity; g \u2013 the vector of gravitational acceleration; k \u2013 turbulent energy; \u03b5 \u2013 the rate of dissipation of turbulent energy", + " As the physical parameters of the working fluid in the simulation were taken: density \u03c1 = 840 \u043a\u0433/\u043c3; molecular viscosity \u03bc = 0.0071 \u043a\u0433/(\u043c\u0441); the flow of the working fluid \u2013 0.1 kg/s; working fluid temperature in the working area \u2013 no more than 120 \u0421; pressure at the inlet of the retarder \u2013 5.5 MPa. The algorithm of finite element analysis was used to solve the given equations [6]. The simulation used a uniform finite element design grid in the plane passing through the wheel rotation axis (figure 3a) and a uniform one in the perpendicular plane (figure 3b). c) Fig. 2. Geometric parameters of the brakes: a) basic version; b) with circular blade system; c) with inclined blades. Simulation of oil flow in the flow part of the brake-retarder is performed within the model of turbulent fluid flow [5]. The equations describing the change in velocity, pressure, turbulent energy, and dissipation have the form: - Navier-Stokes equation \ud835\udf15\ud835\udf15\ud835\udc7d\ud835\udc7d \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udc7d\ud835\udc7d\u2a02 \ud835\udc7d\ud835\udc7d) = \u2212 \u2207\ud835\udc5d\ud835\udc5d \ud835\udf0c\ud835\udf0c + 1 \ud835\udf0c\ud835\udf0c \u2219 \u2207(\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61) \u2219 (\u2207\ud835\udc7d\ud835\udc7d + (\u2207\ud835\udc7d\ud835\udc7d)\ud835\udc47\ud835\udc47) + \ud835\udc54\ud835\udc54, - continuity equation \u2207(\ud835\udc7d\ud835\udc7d) = 0, - equations for turbulent energy and dissipation rate \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 = \ud835\udc50\ud835\udc50\ud835\udf07\ud835\udf07 \u2219 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udc58\ud835\udc582 \ud835\udf00\ud835\udf00 , \ud835\udf15\ud835\udf15(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc58\ud835\udc58) \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc7d\ud835\udc7d \u2219 \ud835\udc58\ud835\udc58) = \u2207 ((\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \ud835\udf0e\ud835\udf0e\ud835\udc58\ud835\udc58 ) \u2219 \u2207\ud835\udc58\ud835\udc58) + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \u2219 \ud835\udc3a\ud835\udc3a \u2212 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf00, \ud835\udf15\ud835\udf15(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf00) \ud835\udf15\ud835\udf15\ud835\udf15\ud835\udf15 + \u2207(\ud835\udf0c\ud835\udf0c \u2219 \ud835\udc7d\ud835\udc7d \u2219 \ud835\udf00\ud835\udf00) = \u2207 ((\ud835\udf07\ud835\udf07 + \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \ud835\udf0e\ud835\udf0e\ud835\udf00\ud835\udf00 ) \u2219 \u2207\ud835\udf00\ud835\udf00) + \ud835\udc50\ud835\udc501 \u2219 \ud835\udf00\ud835\udf00 \ud835\udc58\ud835\udc58 \u2219 \ud835\udf07\ud835\udf07\ud835\udc61\ud835\udc61 \u2219 \ud835\udc3a\ud835\udc3a \u2212 \ud835\udc50\ud835\udc502 \u2219 \ud835\udf0c\ud835\udf0c \u2219 \ud835\udf00\ud835\udf002 \ud835\udc58\ud835\udc58 , where V \u2013 the velocity vector; t \u2013 time; p \u2013 pressure; \u03c1 \u2013 the fluid density; \u03bc \u2013 the molecular dynamic viscosity; \u00b5t \u2013 the turbulent dynamic viscosity; g \u2013 the vector of gravitational acceleration; k \u2013 turbulent energy; \u03b5 \u2013 the rate of dissipation of turbulent energy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000939_cmtmte2018_01106.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000939_cmtmte2018_01106.pdf-Figure1-1.png", + "caption": "Fig. 1. Contact geometry. a \u2013 surfaces without lubricant; b \u2013 surfaces with lubricant; 1 \u2013 an undeformed cylinder; 2 \u2013 a deformed cylinder.", + "texts": [ + " In this model equivalent moduli of elasticity of rough layers (\ud835\udc38\ud835\udc381\u2032) and smooth half-plane (\ud835\udc38\ud835\udc382\u2032 ) are determined by the following formulae \ud835\udc38\ud835\udc381\u2032 = 2\ud835\udc38\ud835\udc381\ud835\udc38\ud835\udc382\ufffd1\u2212\ud835\udc5a\ud835\udc5a\u2032\ufffd\ufffd1\u2212\ud835\udc5a\ud835\udc5a\u2032\u2032\ufffd \ud835\udc38\ud835\udc381(1\u2212\ud835\udc5a\ud835\udc5a\u2032)\ufffd1\u2212\ud835\udf07\ud835\udf072 2\ufffd+\ud835\udc38\ud835\udc382(1\u2212\ud835\udc5a\ud835\udc5a\u2032\u2032)\ufffd1\u2212\ud835\udf07\ud835\udf071 2\ufffd (3) \ud835\udc38\ud835\udc382\u2032 = 2\ud835\udc38\ud835\udc381\ud835\udc38\ud835\udc382 \ud835\udc38\ud835\udc381\ufffd1\u2212\ud835\udf07\ud835\udf072 2\ufffd+\ud835\udc38\ud835\udc382\ufffd1\u2212\ud835\udf07\ud835\udf071 2\ufffd (4) where \ud835\udc38\ud835\udc381,2 \u2013 moduli of elasticity of the contacting bodies, \ud835\udf07\ud835\udf071 and \ud835\udf07\ud835\udf072 \u2013 Poisson\u2019s ratio of the materials of the contacting bodies. The resultant equivalent modulus of elasticity \u0415\u044d, which determines the sum of elastic deformations of contacting surfaces, taking into account their rough layers, is: \ud835\udc38\ud835\udc38\u044d = 2\ud835\udc38\ud835\udc381 \u2032\ud835\udc38\ud835\udc382 \u2032 \ud835\udc38\ud835\udc381 \u2032+\ud835\udc38\ud835\udc382 \u2032 (5) One of the assumptions in this problem is the equal deformation of the cylinder both in case of a dry contact and in case of introduction of a lubricant in the contact zone (Fig. 1). According to Hertz theory half of the contact width of a deformed cylinder is determined by the dependence: \ud835\udc65\ud835\udc65\u00b11 = 2\ufffd2\ud835\udc4a\ud835\udc4a\ud835\udc4a\ud835\udc4a/\ud835\udf0b\ud835\udf0b\u0415\u044d (6) where R \u2013 the equivalent radius of curvature, determined by the correlation 1/R=1/R1+1/R2. Under the conditions of the slight temperature change and dependence of the viscosity of the lubricant \u03b7 on pressure \u0420 as in \ud835\udf02\ud835\udf02 = \ud835\udf02\ud835\udf020\ud835\udc52\ud835\udc52\ud835\udefc\ud835\udefc\ud835\udefc\ud835\udefc and taking into account Reynolds equation and the pressure at the border of Hertz joint (\ud835\udc65\ud835\udc65\u00b11), the dependence for calculating the thickness of lubricating film for contacting bodies with rough surfaces was deduced: \u210e0 = 0,888 \u2219 (1 + \ud835\udc5a\ud835\udc5a\u2032 + \ud835\udc5a\ud835\udc5a\u2032\u2032) \u2219 (\ud835\udefc\ud835\udefc \u2219 \ud835\udf02\ud835\udf02 \u2219 \ud835\udc63\ud835\udc63)0,727 \u2219 \ud835\udc4a\ud835\udc4a0,364 \u2219 \ufffd\u0415\u044d \ud835\udc4a\ud835\udc4a \ufffd 0,111 (7) where \ud835\udf02\ud835\udf020 \u2013 viscosity at atmospheric pressure; \ud835\udefc\ud835\udefc \u2013 pressure coefficient of viscosity; \u03c5 \u2013 hydromechanical velocity, which creates hydromechanical pressure between contacting surfaces, and is determined by the velocity with which the surfaces move" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000054_f_version_1676018743-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000054_f_version_1676018743-Figure2-1.png", + "caption": "Figure 2. Simplified model of the OBMs system with three base oscillations.", + "texts": [ + " The hardware experimental system of vehicle-mounted manipulator considering real chassis oscillation is developed for the first time. The rest of this paper is organized as follows. In Section 2, the problem statement as well as the dynamic model is described. In Section 3, the design process and stability analysis are presented. Section 4 provides the experimental implementation and results, and Section 5 gives concluding remarks of this paper. For simplicity, we consider a simple OBMs system in the study as the first step of our long term research. The system is presented in Figure 2. As shown in the figure, the manipulator is a one-DOF (degree of freedom) link, the payload uncertainty is mass blocks at the end of the link, and base oscillations are divided into three parts: (i) shake oscillation, (ii) pitch oscillation, and (iii) roll oscillation. Figure 2a\u2013c correspond to three oscillations, respectively. Moreover, OXYZ denotes the global frame; oxyz is base-fixed frame; ys, \u03b8p and \u03b8r denote shake, pitch and roll base oscillations, respectively; \u03b8l is link\u2019s angular position; L2 denote link length; Lx, Ly is the position of link joint point; a2 is the length between link\u2019s centroid and joint point. The dynamic model of above OBMs system is obtained using the Lagrangian formulation. Then, treating the base oscillations\u2019 terms as external perturbations of manipulator, we obtain the following uncertain model: Je q\u0308 + G(q) = U + S (1) where q = \u03b8l is system state variable; Je is the equivalent moment of inertia; G(q) denotes gravity force; U is link-side torque, namely, the control input needed to design; S is uncertain perturbation force caused by base oscillations", + " According to Equation (8) and Cauchy inequality, we obtain U2 = k2 d q\u03072 + k2 pq2 + 2kdkpqq\u0307 \u2264 4 3 (k2 d q\u03072 + k2 pq2 + kpkdqq\u0307) (34) Then, substituting Equations (10) and (11) into Equation (34), it has U2 \u2264 4 3 ( kp J2 e Jmax q\u03072 + k2 pq2 + kdkpqq\u0307) \u2264 4 3 (kp Je q\u03072 + k2 pq2 + kdkpqq\u0307) = 8 3 kpV = \u03b22 (35) It is clear that the control input is limited by the parameter \u03b2. By setting U0 = \u03b2, the property P1 will been obtained. To verify the performance of the proposed control, we developed an experimental platform, which is corresponding to the OBM model in Figure 2a. Moreover, before the hardware experiments, we firstly carried out simulations as a preliminary work of the hardware experiments. Before developing the hardware experiment platform, a virtual prototype system is firstly constructed. It is shown in Figure 3. The system consists of a one-link manipulator, a mounted frame (the oscillatory base), spring-tracks and a fixed base. The manipulator together with the mounted frame can oscillate along the tracks under external excitations. The spring is used to simulate the role of the vehicle shock absorber" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003966__130_1_130_1_84__pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003966__130_1_130_1_84__pdf-Figure15-1.png", + "caption": "Fig. 15. Parameters of meander-line antennas", + "texts": [], + "surrounding_texts": [ + "\uff08k = Z0/\u03c90L\uff09\u306e\u6642\uff0c fm < f \u2032m = f0 = f \u2032e < fe \u3068\u306a\u308a\uff0c Fig. 12(c)\u306e\u3088\u3046\u306b\u30d4\u30fc\u30af\u304c 1\u3064\u306b\u306a\u308b\u3002Lm/ \u221a LC < Z0 \u306e\n\u6642\uff0c fm < f0 < fe \u3068\u306a\u308a\uff0cFig. 12(d)\u306e\u3088\u3046\u306b 1\u3064\u306e\u30d4\u30fc\u30af \u304c\u5c0f\u3055\u304f\u306a\u3063\u3066\u3044\u304f\u3002\nS 21 (\u03c9)= 2 jLmZ0\u03c9\nL2 m\u03c9\n2\u2212 { R+ ( \u03c9L\u2212 1\n\u03c9C\n)}2\n+2 jZ0\n{ R+ ( \u03c9L\u2212 1\n\u03c9C\n)} +Z2\n0\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (8)\nS 21 (\u03c9m) =\n2 j Lm\u221a\n(L \u2212 Lm) C\n2 j Lm\u221a\n(L \u2212 Lm) C + Z0\n= 2\n2 \u2212 j Z0\n\u03c9mLm\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (9)\nS 21 (\u03c9e) = 2 j Lm\u221a (L+Lm)C\n2 j Lm\u221a (L+Lm)C + Z0\n= 2\n2 + j Z0 \u03c9eLm\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (10)\nS 21 (\u03c90) = 2 j Z0\nLm\u221a LC\nZ2 0 +\nL2 m LC\n= 2 j\n\u221a Z2\n0 \u00b7 L2 m LC\nZ2 0 +\nL2 m LC\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (11) \u2202S 21 (\u03c9) \u2202\u03c9 = 0 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (12)\n\u03c9\u2032m =\n\u221a\u221a 2L \u2212CZ2 0 \u2212 \u221a 4L2 m + Z4 0C2 \u2212 4LCZ2 0\n2 ( L2 \u2212 L2 m ) C\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (13)\n\u03c9\u2032e =\n\u221a\u221a 2L \u2212CZ2\n0 +\n\u221a 4L2\nm + Z4 0C2 \u2212 4LCZ2 0\n2 ( L2 \u2212 L2 m ) C\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (14)( \u03c9\u2032m = 2\u03c0 f \u2032m, \u03c9 \u2032 e = 2\u03c0 f \u2032e ) \u30083\u30fb3\u30fb2\u3009 \u7b49\u4fa1\u56de\u8def fm\uff0cfe\uff0cL\uff0cC\uff0cLm\u306e\u7b97\u51fa\u65b9\u6cd5 \u7b49 \u4fa1\u56de\u8def\u3092\u7528\u3044\u3066\u8b70\u8ad6\u3059\u308b\u305f\u3081\u306b\u306f\uff0c\u7b49\u4fa1\u56de\u8def\u3067\u4f7f\u308f\u308c\u3066\u3044 \u308b\u5404\u30d1\u30e9\u30e1\u30fc\u30bf\u3092\u7b97\u51fa\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\u3002\u78c1\u754c\u7d50\u5408\u3067\u306f\uff0c\u30a4 \u30f3\u30c0\u30af\u30bf\u30f3\u30b9\uff0c\u30ad\u30e3\u30d1\u30b7\u30bf\u30f3\u30b9\uff0c\u76f8\u4e92\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\uff0c\u640d \u5931\u306e\u8a08 4\u3064\u306e\u30d1\u30e9\u30e1\u30fc\u30bf\u304c\u6c42\u307e\u308c\u3070\u826f\u3044\u3002\u30b3\u30a4\u30eb\u72b6\u306e\u30a2\u30f3 \u30c6\u30ca\u306b\u304a\u3051\u308b\u30a4\u30f3\u30c0\u30af\u30bf\u30f3\u30b9\uff0c\u30ad\u30e3\u30d1\u30b7\u30bf\u30f3\u30b9\uff0c\u76f8\u4e92\u30a4\u30f3 \u30c0\u30af\u30bf\u30f3\u30b9\u3092\u7406\u8ad6\u5f0f\u304b\u3089\u6c42\u3081\u308b\u5834\u5408\u306f\u5358\u7d14\u306a\u5f62\u72b6\u4ee5\u5916\u3067\u306f \u6570\u5f0f\u304c\u8907\u96d1\u306b\u306a\u308b\u306e\u3067\uff0c\u672c\u7a3f\u3067\u306f\u96fb\u78c1\u754c\u89e3\u6790\u306b\u3088\u3063\u3066\u6c42\u3081 \u305f\u5024\u304b\u3089\u7b97\u51fa\u3059\u308b\u3002\n1\u7d20\u5b50\u306e\u7b49\u4fa1\u56de\u8def Fig. 10\u3088\u308a\u672a\u77e5\u6570 L\uff0cC \u3092\u6c42\u3081\u308b\u3002\u307e \u305a\uff0c1\u7d20\u5b50\u306e\u7b49\u4fa1\u56de\u8def Fig. 10\u3088\u308a Zin\u306f (15)\u5f0f\u3068\u306a\u308b\u3002\u307e \u305f\uff0c\u5171\u632f\u6761\u4ef6\u3088\u308a\uff0c\u30ea\u30a2\u30af\u30bf\u30f3\u30b9 0\u3068\u7f6e\u304f\u3053\u3068\u306b\u3088\u308a\u5171\u632f \u5468\u6ce2\u6570\uff0c(16)\u5f0f\u304c\u5c0e\u304b\u308c\u308b\u3002\u4e00\u65b9\uff0c(17)\u5f0f\u304b\u3089\u3082 Zin \u304c\u8a08 \u7b97\u51fa\u6765\u308b\u3002\u03c90\uff0cS 11 \u306f\u6e2c\u5b9a\u53ef\u80fd\u306a\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u305f\u3081\u65e2\u77e5\u3067 \u3042\u308b\u3002(15)\u5f0f\u3068 (17)\u5f0f\u306e\u865a\u90e8\u306e\u307f\u306b\u6ce8\u76ee\u3059\u308b\u3068\uff0c(18)\u5f0f\u3068 \u306a\u308b\u3002(18)\u5f0f\u306b f0\uff0c f0 + \u03b4\u3092\u4ee3\u5165\u3057\u9023\u7acb\u3057\u3066\u89e3\u304f\u3053\u3068\u306b\u3088 \u308a L\uff0cC \u304c\u6c42\u307e\u308b\u3002\u6b21\u306b\uff0c2\u7d20\u5b50\u306e\u7b49\u4fa1\u56de\u8def\u3088\u308a\uff0c\u672a\u77e5\u6570 Lm \u3092\u6c42\u3081\u308b\u3002(16)\uff0c(4)\uff0c(5)\u5f0f\u3088\u308a\u4ee5\u4e0b (19)\uff5e(22)\u306e\u5f0f\u304c \u5c0e\u304b\u308c\u308b\u30021\u7d20\u5b50\u3067\u306e\u5171\u632f\u5468\u6ce2\u6570\u3092 f0\uff0c2\u7d20\u5b50\u3067\u306e\u5171\u632f\u5468\n\u6ce2\u6570\u3092 fm\uff0c fe \u3068\u3057\uff0c\u305d\u306e\u6642\uff0c\u5404\u3005\u306e\u89d2\u5468\u6ce2\u6570\u3092 \u03c90\uff0c\u03c9m\uff0c \u03c9e\u3068\u3059\u308b\u3002 fm\uff0cfe\u304c\u6e2c\u5b9a\u53ef\u80fd\u306a\u91cf\u3067\u3042\u308a\uff0c\u65e2\u77e5\u3067\u3042\u308b\u3002\u307e \u305f\uff0cL\uff0cC\u306f\uff0c(18)\u5f0f\u3067\u6c42\u3081\u3089\u308c\u3066\u3044\u308b\u306e\u3067\uff0c(20)\uff5e(22)\u5f0f \u306e\u3044\u305a\u308c\u304b\u4e00\u3064\u5f0f\u3092\u4f7f\u3046\u3053\u3068\u306b\u3088\u308a Lm \u304c\u6c42\u307e\u308b\u3002\u4ee5\u4e0a\u3088 \u308a\uff0c fm\uff0c fe\uff0cL\uff0cC\uff0cLm \u304c\u6c42\u307e\u308b\u3002\nZin = R + j\n( \u03c9L \u2212 1\n\u03c9C\n) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (15)\n\u03c90 = 1\u221a LC \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (16)\nZin = 1 + S 11\n1 \u2212 S 11 Z0 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (17)\nIm [Zin] = Im\n[ 1 + S 11\n1 \u2212 S 11 Z0\n] = \u03c9L \u2212 1\n\u03c9C \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (18)\nC = 1\n\u03c92 0L \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (19)\nC = 1\n\u03c92 m (L + Lm)\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (20)\nC = 1\n\u03c92 e (L \u2212 Lm)\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (21)\nLm = f 2 e \u2212 f 2 m\nf 2 e + f 2 m L \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (22)\n\u6b21\u306b\u640d\u5931\u306b\u3064\u3044\u3066\u8003\u3048\u308b\u3002\u96fb\u529b\u4f1d\u9001\u306b\u304a\u3044\u3066\uff0c\u8003\u3048\u308b\u3079\n\u304d\u640d\u5931\u306f\u653e\u5c04\u640d\uff0c\u9285\u640d\uff0c\u9244\u640d\uff08\u6e26\u96fb\u6d41\u640d\uff0c\u30d2\u30b9\u30c6\u30ea\u30b7\u30b9\u640d\uff09 \u3067\u3042\u308b\u3002\u4f46\u3057\uff0c\u30d5\u30a7\u30e9\u30a4\u30c8\u7b49\u306e\u78c1\u6027\u4f53\u3092\u4f7f\u7528\u3057\u3066\u3044\u306a\u3044\u306e \u3067\u30d2\u30b9\u30c6\u30ea\u30b7\u30b9\u640d\u306f\u5b58\u5728\u3057\u306a\u3044\u3002\u9244\u5fc3\u3092\u5229\u7528\u3057\u3066\u3044\u306a\u3044\u306e \u3067\u6e26\u96fb\u6d41\u640d\u3082\u5b58\u5728\u3057\u306a\u3044\u3002\u653e\u5c04\u62b5\u6297 Rrad \u306f\u653e\u5c04\u640d\u304b\u3089\u9006\u7b97 \u3055\u308c\u308b\u5024\u3067\u3042\u308a\uff0c(23)\u5f0f\u3067\u8868\u3055\u308c\u308b\u3002\u3064\u307e\u308a\uff0c\u653e\u5c04\u96fb\u529b\u3092 \u6c42\u3081\u308b\u5fc5\u8981\u304c\u3042\u308a\uff0c\u3053\u308c\u306f\u9060\u65b9\u754c\u3078\u653e\u5c04\u3055\u308c\u308b\u30dd\u30a4\u30f3\u30c6\u30a3 \u30f3\u30b0\u30d9\u30af\u30c8\u30eb\u3092\u6c42\u3081\u308b\u3053\u3068\u306b\u306a\u308a\uff0c\u96fb\u78c1\u754c\u89e3\u6790\u306b\u3088\u3063\u3066\u6c42 \u3081\u3089\u308c\u308b\u5024\u3067\u3042\u308b\u3002\u307e\u305f\uff0c\u4eca\u56de\u306e\u8fd1\u508d\u754c\u30a2\u30f3\u30c6\u30ca\u306f\u975e\u5e38\u306b \u653e\u5c04\u640d\u304c\u5c0f\u3055\u304f\u307b\u307c 0%\u306e\u305f\u3081\uff0cRrad 0\u3068\u306a\u308b\u3002\u653e\u5c04\u640d \u304c\u591a\u3044\u5834\u5408\uff0c\u30a2\u30f3\u30c6\u30ca\u306e\u5b9f\u90e8\u306e\u30a4\u30f3\u30d4\u30fc\u30c0\u30f3\u30b9\u304c\u9ad8\u3044\u5834\u5408 \u306f\uff0c\u96fb\u78c1\u754c\u89e3\u6790\u3067\u6c42\u3081\u308b\u5fc5\u8981\u6027\u304c\u3042\u308b\u3002\u4e00\u65b9\uff0c\u9285\u640d Rohm\u3067 \u3042\u308c\u3070\uff0c(24)\uff0c(25)\u5f0f\u3088\u308a\u8a08\u7b97\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002\nRrad = P0\nI2 0\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (23)\nRohm = \u03c1l\n\u03c0\u03b4 (D \u2212 \u03b4) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (24)\n\u03b4 = \u221a 2 \u03c9\u03c3\u03bc \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (25)\n\uff08\u03c1\uff1a\u62b5\u6297\u7387\uff0cl\uff1a\u5168\u9577\uff0c\u03b4\uff1a\u8868\u76ae\u6df1\u3055\uff0cD\uff1a\u592a\u3055\uff0c\u03c3\uff1a\n\u5c0e\u96fb\u7387\uff0c\u03bc\uff1a\u900f\u78c1\u7387\uff09\n\u4ee5\u4e0b\uff0c\u5b9f\u969b\u306b L\uff0cC\uff0cLm\uff0cRohm \u3092\u6c42\u3081\u308b\u3002\u30a2\u30f3\u30c6\u30ca 1\u7d20 \u5b50\uff08r = 150 mm\uff0cn = 5 turn\uff0cp = 5 mm\uff09\u306b\u304a\u3051\u308b\u5185\u90e8\u30a4\u30f3 \u30d4\u30fc\u30c0\u30f3\u30b9 Zin \u3092 Fig. 13\u306b\u793a\u3059\u30021\u7d20\u5b50\u304b\u3089 f0\uff0c f0 + \u03b4\u3067\n88 IEEJ Trans. IA, Vol.130, No.1, 2010", + "\u78c1\u754c\u7d50\u5408\u3068\u96fb\u754c\u7d50\u5408\n\u306e Im[Zin]\u3092\u6c42\u3081\uff0c(18)\u5f0f\u306b\u4ee3\u5165\u3059\u308b\u3068\uff0cL = 8.5 \u03bcH\uff0cC = 9.7 pF\u304c\u6c42\u307e\u308b\u3002\u6b21\u306b\uff0c2\u7d20\u5b50\uff08g = 150 mm\uff09\u304b\u3089\uff0cZ0 = 0 \u3068\u3057\u3066 fm\uff0cfe\u3092\u96fb\u78c1\u754c\u89e3\u6790\u306b\u3066\u6c42\u3081\u308b\u3068\uff0cfm = 16.8 MHz\uff0c fe = 18.3 MHz\u3068\u306a\u308b\u3002(22)\u5f0f\u306b fm\uff0c fe\uff0cL\u3092\u4ee3\u5165\u3059\u308b\u3053 \u3068\u306b\u3088\u308a\uff0cLm = 0.71 \u03bcH\u304c\u6c42\u307e\u308b\u3002\u3053\u306e\u3068\u304d\uff0ckm = 0.08\u3067 \u3042\u308b\u3002\u6b21\u306b\uff0c\u9285\u306e\u5c0e\u96fb\u7387 \u03c1 = 5.8\u00d7 107\uff08S/m\uff09\uff0c\u6bd4\u900f\u78c1\u7387 \u03bcr = 1\uff0c\u5168\u9577 l = 4.7 m\uff0c\u7d20\u5b50\u306e\u592a\u3055 D = 2 mm\uff0c1\u7d20\u5b50\u3067\u306e\u5171 \u632f\u5468\u6ce2\u6570 f0 = 17.5 MHz\u3092 (24)\uff0c(25)\u5f0f\u306b\u4ee3\u5165\u3057\uff0cRohm = 0.82\u03a9\u3068\u6c42\u307e\u308b\u3002\u96fb\u78c1\u754c\u89e3\u6790\u306b\u3088\u308a 1\u7d20\u5b50\u306b\u304a\u3051\u308b\u5185\u90e8\u30a4 \u30f3\u30d4\u30fc\u30c0\u30f3\u30b9Zin\u306e\u5b9f\u90e8Re[Zin]\u304b\u3089\u76f4\u63a5\u6c42\u3081\u305f\u5024\u306f 1.46\u03a9 \u3067\u3042\u308a\uff0c\u307b\u307c\u540c\u3058\u3067\u3042\u308b\u3002\n\u30083\u30fb3\u30fb3\u3009 \u5b9f\u9a13\u7d50\u679c\uff0c\u96fb\u78c1\u754c\u89e3\u6790\uff0c\u7b49\u4fa1\u56de\u8def\u306e\u6bd4\u8f03 \u5b9f \u9a13\u7d50\u679c\uff0c\u96fb\u78c1\u754c\u89e3\u6790\uff0c\u7b49\u4fa1\u56de\u8def\u306e\u6bd4\u8f03\u3092\u884c\u306a\u3046\u3002\u7b49\u4fa1\u56de\u8def \u306b\u95a2\u3057\u3066\u306e\u5fc5\u8981\u306a\u30d1\u30e9\u30e1\u30fc\u30bf\u306f\u96fb\u78c1\u754c\u89e3\u6790\u3068\u9285\u640d\u304b\u3089\u6c42\u3081 \u305f L\uff0cC\uff0cLm\uff0cRohm\uff088.5 \u03bcH\uff0c9.7 pF\uff0c0.71 \u03bcH\uff0c0.82\u03a9\uff09\u3092 \u4f7f\u7528\u3059\u308b\u3002\u6c42\u3081\u65b9\u306f\uff0c\u30083\u30fb3\u30fb2\u3009\u306b\u793a\u3057\u305f\u901a\u308a\u3067\u3042\u308b\u3002\u307e\u305f \u96fb\u78c1\u754c\u89e3\u6790\u7d50\u679c\u306f\u30e2\u30fc\u30e1\u30f3\u30c8\u6cd5\u306b\u3088\u3063\u3066\u76f4\u63a5\u6c42\u3081\u305f\u5024\u3067\u3042 \u308b\u3002\u50c5\u304b\u306b\u8aa4\u5dee\u306f\u3042\u308b\u304c\uff0c\u5b9f\u9a13\u7d50\u679c\uff0c\u96fb\u78c1\u754c\u89e3\u6790\uff0c\u7b49\u4fa1\u56de \u8def\u306f\u307b\u307c\u4e00\u81f4\u3057\u3066\u3044\u308b\u3002\n4. \u96fb\u754c\u7d50\u5408\u306b\u3088\u308b\u96fb\u529b\u4f1d\u9001\u2014\u30e1\u30a2\u30f3\u30c0\u30e9\u30a4\u30f3\u30a2\u30f3 \u30c6\u30ca\u2014\n\u524d\u7ae0\u306f\u78c1\u754c\u7d50\u5408\u306b\u3064\u3044\u3066\u8ff0\u3079\u305f\u3002\u672c\u7ae0\u3067\u306f\uff0c\u96fb\u754c\u7d50\u5408\u306b \u3064\u3044\u3066\u8ff0\u3079\u308b\u3002\u96fb\u754c\u7d50\u5408\u3067\u4f7f\u7528\u3059\u308b\u30e1\u30a2\u30f3\u30c0\u30e9\u30a4\u30f3\u30a2\u30f3\u30c6 \u30ca\u306e\u30e2\u30c7\u30eb\u3092 Fig. 15\u306b\u793a\u3059\u3002x\u8ef8\u306b\u9577\u3044\u90e8\u5206\u3092\u4e00\u7b87\u6240\u306b\u3064 \u304d 1\u6bb5\u3068\u3057\uff0c\u5168\u3066\u306e\u6bb5\u6570\u3092 n\u6bb5\u3068\u3059\u308b\u3002\n\u30084\u30fb1\u3009 \u30ae\u30e3\u30c3\u30d7 \u30ae\u30e3\u30c3\u30d7\u3092\u5909\u5316\u3055\u305b\u305f\u6642\u306e\u5468\u6ce2\u6570 \u306b\u5bfe\u3059\u308b \u03b711\uff0c\u03b721\u3092 Fig. 16\u306b\u793a\u3059\u3002\u30d8\u30ea\u30ab\u30eb\u30a2\u30f3\u30c6\u30ca\u306e\u5834 \u5408\u3068\u540c\u69d8\u306b\u30ae\u30e3\u30c3\u30d7\u304c\u8fd1\u3044\u6642\u306f\u30d4\u30fc\u30af\u3068\u306a\u308b\u5171\u632f\u5468\u6ce2\u6570\u306f 2\u3064\u3068\u306a\u308a\uff0c\u30ae\u30e3\u30c3\u30d7\u304c\u5927\u304d\u304f\u306a\u3068 2\u3064\u306e\u30d4\u30fc\u30af\u304c 1\u3064\u306b \u306a\u308b\u3002\u30d4\u30fc\u30af\u304c 2\u3064\u306e\u6642\uff0c\u30d4\u30fc\u30af\u3068\u306a\u308b\u5171\u632f\u5468\u6ce2\u6570\u306f\u5909\u5316 \u3059\u308b\u304c\uff0c\u6700\u5927\u52b9\u7387\u306f\u4e00\u5b9a\u3067\u3042\u308a\uff0c\u30d4\u30fc\u30af\u304c 1\u3064\u306b\u306a\u308b\u3068\u52b9 \u7387\u304c\u60aa\u5316\u3059\u308b\u3053\u3068\u3082\u78c1\u754c\u7d50\u5408\u6642\u3068\u540c\u69d8\u3067\u3042\u308b\u3002\u305f\u3060\u3057\uff0c\u96fb \u754c\u7d50\u5408\u306b\u304a\u3044\u3066\u306f\uff0c2\u3064\u306e\u30d4\u30fc\u30af\u3068\u306a\u308b\u5171\u632f\u5468\u6ce2\u6570 f \u2032e\uff0c f \u2032m \u3092 f \u2032e < f \u2032m\u3068\u3059\u308b\u3002\u307e\u305f\uff0cFig. 16(a)\uff0c(b)\u306e 2\u3064\u306e\u30d4\u30fc\u30af\u3068 \u306a\u308b\u5468\u6ce2\u6570\u306e\u4e2d\u592e\u306e\u8c37\u306b\u5f53\u308b\u5468\u6ce2\u6570\uff0c\u3082\u3057\u304f\u306f\uff0cFig. 16(c)\uff0c (d)\u306e 1\u3064\u306e\u30d4\u30fc\u30af\u3068\u306a\u3063\u305f\u6642\u306e\u5171\u632f\u5468\u6ce2\u6570\u306f\u30a2\u30f3\u30c6\u30ca1\u7d20 \u5b50\u306e\u6642\u306e\u5171\u632f\u5468\u6ce2\u6570 f0 \u306b\u307b\u307c\u7b49\u3057\u3044\u3053\u3068\u3082\u540c\u69d8\u3067\u3042\u308b\u3002\n\u30084\u30fb2\u3009 \u8fd1\u508d\u306b\u304a\u3051\u308b\u96fb\u78c1\u754c\u5206\u5e03 \u30a2\u30f3\u30c6\u30ca\u8fd1\u508d\u3067\u306e \u96fb\u78c1\u754c\u306e\u632f\u308b\u821e\u3044\u3092\u793a\u3059\u3002\u96fb\u754c\u30d9\u30af\u30c8\u30eb\u3092 Fig. 17\uff0cFig. 18 \u306b\u793a\u3059\u3002Fig. 19\u306b\u306f\u96fb\u754c\u3068\u78c1\u754c\u5206\u5e03\u3092\u793a\u3059\u3002Fig. 20\u306b\u306f\u96fb \u6c17\u30a8\u30cd\u30eb\u30ae\u30fc\u5bc6\u5ea6\u3068\u78c1\u6c17\u30a8\u30cd\u30eb\u30ae\u30fc\u5bc6\u5ea6\u3092\u793a\u3059\u3002Fig. 20\u306f \u6700\u5927\u5024\u3067\u898f\u683c\u5316\u3057\u3066\u3042\u308b\u3002\u78c1\u754c\u7d50\u5408\u3068\u540c\u69d8\u306b\u96fb\u754c\u7d50\u5408\u306b\u304a\n\u96fb\u5b66\u8ad6 D\uff0c130 \u5dfb 1 \u53f7\uff0c2010 \u5e74 89", + "\u3044\u3066\u3082\uff0c2\u3064\u306e\u5171\u632f\u5468\u6ce2\u6570 f \u2032e\uff0cf \u2032m\u306b\u304a\u3044\u3066\u975e\u5e38\u306b\u7279\u5fb4\u7684\u306a \u5206\u5e03\u3092\u793a\u3059\u3002\u3053\u308c\u306f\u9001\u4fe1\u30a2\u30f3\u30c6\u30ca\u3068\u53d7\u4fe1\u30a2\u30f3\u30c6\u30ca\u306e\u5bfe\u79f0\u9762 \u306b\u304a\u3051\u308b\u96fb\u754c\u306e\u69d8\u5b50\u306b\u73fe\u308c\u308b\u3002 f \u2032e \u306b\u304a\u3044\u3066\u306f\u5bfe\u79f0\u9762\u306b\u5782\u76f4 \u306b\u96fb\u754c\u304c\u5206\u5e03\u3057\u96fb\u6c17\u58c1\u3068\u306a\u308a\uff0cf \u2032m\u306b\u304a\u3044\u3066\u306f\u5bfe\u79f0\u9762\u306b\u6c34\u5e73 \u306b\u96fb\u754c\u304c\u5206\u5e03\u3057\u78c1\u6c17\u58c1\u3068\u306a\u308b\u3002\u96fb\u6c17\u58c1\uff0c\u78c1\u6c17\u58c1\u306e\u5206\u5e03\u304c\u78ba \u8a8d\u3055\u308c\u308b\u306e\u306f\uff0c\u78c1\u754c\u7d50\u5408\u3068\u540c\u69d8\u3067\u3042\u308b\u304c\uff0c\u78c1\u6c17\u58c1\u3068\u96fb\u6c17\u58c1 \u304c\u767a\u751f\u3059\u308b\u5171\u632f\u5468\u6ce2\u6570\u3092\u8003\u3048\u308b\u3068\uff0c\u78c1\u754c\u7d50\u5408\u306b\u304a\u3044\u3066\u306f\uff0c f \u2032m < f \u2032e \u3067\u3042\u308a\uff0c\u96fb\u754c\u7d50\u5408\u306b\u304a\u3044\u3066\u306f\uff0c f \u2032e < f \u2032m \u3067\u3042\u308b\u3002\u307e \u305f\uff0cFig. 19\u3088\u308a\uff0c\u78c1\u754c\u304c\u7dba\u9e97\u306b\u6253\u3061\u6d88\u3055\u308c\u3066\u3044\u308b\u3053\u3068\u304c\u308f\u304b \u308b\u3002\u3053\u308c\u306f\uff0c\u30e1\u30a2\u30f3\u30c0\u30e9\u30a4\u30f3\u306e\u66f2\u304c\u308a\u304f\u306d\u3063\u305f\u5f62\u72b6\u306b\u3088\u308a \u96fb\u6d41\u304c\u9006\u5411\u304d\u306b\u6d41\u308c\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u78c1\u754c\u304c\u76f8\u6bba\u3055\u308c\u3066\u3044\u308b\u305f \u3081\u3067\u3042\u308b\u3002\u305d\u306e\u305f\u3081\uff0c\u5bfe\u79f0\u9762\u306b\u304a\u3044\u3066\u306f\u96fb\u6c17\u30a8\u30cd\u30eb\u30ae\u30fc\u5bc6\u5ea6 \u306b\u5bfe\u3057\uff0c\u78c1\u6c17\u30a8\u30cd\u30eb\u30ae\u30fc\u5bc6\u5ea6\u306e\u6bd4\u7387\u306f 0.001%\u672a\u6e80\u3067\u3042\u308b\u3002\n\u30084\u30fb3\u3009 \u96fb\u754c\u7d50\u5408\u306e\u7b49\u4fa1\u56de\u8def \u78c1\u754c\u7d50\u5408\u540c\u69d8\uff0c\u96fb\u754c\u7d50 \u5408\u306b\u304a\u3044\u3066\u3082\u7b49\u4fa1\u56de\u8def\u3092\u793a\u3059\u3002\u672c\u7bc0\u3067\u306f\uff0c\u96fb\u754c\u7d50\u5408\u306b\u304a\u3051\n\u308b\u7b49\u4fa1\u56de\u8def\u3078\u306e\u7f6e\u304d\u63db\u3048\u3092\u3057\uff0c\u30d1\u30e9\u30e1\u30fc\u30bf\u306e\u7b97\u51fa\u65b9\u6cd5\u3092\u793a \u3059\u3002\u6700\u5f8c\u306b\uff0c\u96fb\u78c1\u754c\u89e3\u6790\u3068\u7b49\u4fa1\u56de\u8def\u3092\u6bd4\u8f03\u3059\u308b\u3002 \u30084\u30fb3\u30fb1\u3009 \u7b49\u4fa1\u56de\u8def\u306b\u3088\u308b\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u5f0f\u306e\u5c0e\u51fa \u7b49 \u4fa1\u56de\u8def\u306b\u95a2\u3057\u3066\u306f\u78c1\u754c\u7d50\u5408\u3068\u540c\u69d8\u306b\u6c42\u3081\u308b\u3053\u3068\u304c\u51fa\u6765\u308b\u3002 \u305f\u3060\u3057\uff0c\u96fb\u754c\u7d50\u5408\u306e\u5834\u5408\uff0c\u78c1\u754c\u306e\u7d50\u5408\u3067\u306a\u3044\u306e\u3067\u76f8\u4e92\u30a4\u30f3\u30c0 \u30af\u30bf\u30f3\u30b9 Lm \u3067\u306f\u306a\u304f\uff0c\u76f8\u4e92\u30ad\u30e3\u30d1\u30b7\u30bf\u30f3\u30b9 Cm \u3092\u7528\u3044\u308b\u3002 \u307e\u305f\uff0c\u8a08\u7b97\u306e\u90fd\u5408\u4e0a T\u578b\u7d50\u5408\u3088\u308a \u03c0\u578b\u7d50\u5408\u3067\u8868\u3057\u305f\u307b\u3046\u304c \u7c21\u6613\u3068\u306a\u308b\u305f\u3081\uff0cFig. 21\u306e\u7b49\u4fa1\u56de\u8def\u3068\u3059\u308b\u3002Z0 = 0\uff0cR = 0\u03a9\u3068\u3057\u305f\u6642\u306e\u5171\u632f\u6761\u4ef6\u3088\u308a\uff0c\u30ea\u30a2\u30af\u30bf\u30f3\u30b9 0\u3068\u7f6e\u304f\u3053\u3068 \u306b\u3088\u308a (26)\u5f0f\u3092\u5c0e\u304f\u3002\u9001\u53d7\u540c\u3058\u30a2\u30f3\u30c6\u30ca\u3092\u4f7f\u3046\u306e\u3067\uff0cC = C1 = C2\uff0cL = L1 = L2\uff0cR = R1 = R2 = 0\u3068\u3057\u3066\uff0c\u305d\u3053\u304b\u3089 2 \u3064\u306e\u89d2\u5171\u632f\u5468\u6ce2\u6570\uff0c(27)\uff0c(28)\u5f0f\u3092\u5c0e\u304f\u3002(27)\uff0c(28)\u5f0f\u304b\u3089 \u66f4\u306b\u7d50\u5408\u4fc2\u6570\u3068 2\u3064\u306e\u5171\u632f\u5468\u6ce2\u6570\u3068\u306e\u95a2\u4fc2\u5f0f (29)\u3092\u5c0e\u304f\u3002 \u6b21\u306b\uff0c\u7b49\u4fa1\u56de\u8def\u3088\u308a\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u3092\u8abf\u3079\u308b\u305f\u3081\u306b\uff0cS 21\u3092 \u6c42\u3081\u308b\u3068\uff0c(30)\u5f0f\u3068\u306a\u308b\u3002\u3053\u3053\u3067\u306f\uff0c\u7169\u96d1\u3055\u3092\u907f\u3051\u308b\u305f\u3081 \u306b\uff0c\u640d\u5931\u9805 R\u306f\u7701\u7565\u3059\u308b\u3002S 21 \u3092 2\u4e57\u3059\u308b\u3068\u96fb\u529b\u4f1d\u9001\u52b9\u7387 \u306b\u306a\u308b\u306e\u306f (2)\u5f0f\u306b\u793a\u3057\u305f\u901a\u308a\u3067\u3042\u308b\u30022\u3064\u306e\u5171\u632f\u5468\u6ce2\u6570 fe\uff0c fm \u3068\u305d\u306e\u9593\u306e\u5468\u6ce2\u6570\u306b\u4f4d\u7f6e\u3059\u308b\u30a2\u30f3\u30c6\u30ca\u5358\u72ec\u3067\u306e\u5171\u632f \u5468\u6ce2\u6570 f0 \u306b\u304a\u3044\u3066\u96fb\u529b\u4f1d\u9001\u52b9\u7387\u3092\u5c0e\u304f\u3068\uff0c\u305d\u308c\u305e\u308c (31)\uff0c (32)\uff0c(33)\u5f0f\u304c\u6c42\u307e\u308b\u3002\n1 \u03c9Cm + 1\n\u03c9 (C1\u2212Cm)\u2212 1 \u03c9L1\n+ 1\n\u03c9 (C2\u2212Cm)\u2212 1 \u03c9L2\n=0\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (26)\n\u03c9e = \u03c90\u221a 1 + ke = 1\u221a (C + Cm) L \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (27) \u03c9m = \u03c90\u221a 1 \u2212 ke = 1\u221a (C \u2212 Cm) L \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (28) ke = Cm\nC = \u03c92 m \u2212 \u03c92 e\n\u03c92 m + \u03c9 2 e \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (29)\nS 21 (\u03c9) = 2 jZ0 Cm\n\u03c9 (C +Cm) (C \u2212Cm) / \u23a7\u23aa\u23aa\u23aa\u23aa\u23aa\u23a8\u23aa\u23aa\u23aa\u23aa\u23aa\u23a9 ( \u03c9L \u2212 1 \u03c9 (C +Cm) ) ( \u03c9L \u2212 1 \u03c9 (C \u2212Cm) )\n\u2212 2 jZ0 \u239b\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239c\u239d\u03c9L\u2212 1 \u03c9 (C+Cm) (C\u2212Cm)\nC\n\u239e\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u239f\u23a0\u2212Z2 0 \u23ab\u23aa\u23aa\u23aa\u23aa\u23aa\u23ac\u23aa\u23aa\u23aa\u23aa\u23aa\u23ad \u22121\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (30)\nS 21 (\u03c9e) = 2\n2 + jZ0\u03c9e C2 \u2212 C2 m\nC\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (31)\nS 21 (\u03c9m) = 2\n\u22122 + jZ0\u03c9e C2 \u2212 C2 m\nC\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (32)\nS 21 (\u03c90) =\n2 jZ0 Cm \u03c90 ( C2 \u2212C2 m )\nZ2 0 \u2212 2 j\nC2 m\nC2 \u2212 C2 m 1 \u03c90C + C2 m C2 \u2212 C2 m 1 \u03c92 0C2\n\u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (33)\n90 IEEJ Trans. IA, Vol.130, No.1, 2010" + ] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-Figure3.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-Figure3.3-1.png", + "caption": "Figure 3.3: Coordinate systems used in the theoretical approach", + "texts": [ + "15) Chapter 3: System modeling and simulation by MATLAB/Simulink 22 With \u03c1 is density of air, RA is the ducted-fan disk area, and e R A A \u03c3 = is ratio between the duct\u2019s exit area and disk area. The correction factor for velocity is: exitV n V\u221e = (3.16) For the aerodynamic data derived in the previous part, the only change is the velocity of the air stream; this change includes both magnitude and direction. Thus, the correction factor of magnitude for all the aerodynamic data of tails and stators is 2n , and correction factor of direction is angle of e\u03b1 . There are three coordinate systems used in this development which are shown in Figure 3.3: - The body axes system, which is fixed to the aircraft, the equations of motion set is derived in this coordinate system. - The stability axes system, of which x-axis is in line with the wind\u2019s velocity vector, it is used to derive the aerodynamic forces. - Horizontal vertical axes system, of which orientation does not change with time, it serves as an inertial reference system. Chapter 3: System modeling and simulation by MATLAB/Simulink 23 Chapter 1 of Reference (25) contains a detailed derivation of the equations of motion of a fixed-wing aircraft in a body-fixed axis system" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002970_cle_download_643_621-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002970_cle_download_643_621-Figure8-1.png", + "caption": "Figure 8. Tool permanent displacement at second punch evaluated", + "texts": [ + " Figure 7 shows that the maximum forming load increased with the size of fillet as the punch progressed for the full die-filling state. The values of the maximum load exhibited by 1.0 mm, 1.5 mm, 2.0 mm, and 2.5 mm fillets were 457 kN, 440 kN, 427 kN and 400 kN, respectively. This was attributed to the continuously increasing load in the final forming operation in order to fill the die corners. Accordingly, the largest size of fillet only required the lowest forming load rather than those of the smaller sizes. According to Figure 8, it certified that the permanent displacement was not proportional to the size of fillet, but increased as the size of fillet decreased. The highest and lowest values for the permanent displacement were attained as 0.0702 mm and 0.0662 mm when Rp were 0.1 mm and 2.5 mm, respectively. In addition, by referring to Figure 9, it shows that the highest value for maximum stress was 1600 MPa when Rp was at 0.1 mm and the lowest value for maximum stress was 1450 MPa as Rp approached 2.5 mm. significantly, the maximum stresses were observed at the corner of the punch, but not at the top surface" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000310_9668973_09745136.pdf-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000310_9668973_09745136.pdf-Figure18-1.png", + "caption": "FIGURE 18. Pitch angle tracking error.", + "texts": [ + " 19, when the aircraft model moves with two-DOF in the pitch and roll directions, three different controllers are used to make a comparison. As for pitch motion, computed-torque+DDPG controller manages to track the corresponding trajectory at around 3.2s, and 3.6s for computed-torque controller, 3.9s for DDPG controller; as for roll motion, computed-torque+DDPG controller spends 3.9s managing to track the trajectory, and 4.1s for computedtorque controller, 5.2s for DDPG controller. As can be seen from Fig. 18 and Fig. 20, as for pitch motion, the steady stable errors of the computed-torque+DDPG controller is within 0.08\u25e6, and the max tracking error is about 0.1\u25e6 for the DDPG controller, and 0.23\u25e6 for computed-torque controller; as for roll direction, the tracking error of computed-torque+DDPG controller is within 0.07\u25e6, and the max tracking error is about 0.1\u25e6 for DDPG controller, and 0.15\u25e6 for computed-torque controller. The yaw tracking history and error curves are shown in Fig. 21 and Fig. 22, the pre-trained agent maintains stable at around 0\u25e6 within 5s, and the computed-torque+DDPG control algorithm is the first to reach a stable state" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003142_0245-024-10117-6.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003142_0245-024-10117-6.pdf-Figure2-1.png", + "caption": "Fig. 2 Geometry, finite element mesh and vectors {v1, v2, v3} parametrising the growth tensor Cg. a Rectangular section beam, with {L, b, t} = {1, 1/10, 1/50}. b Circular section beam with {L, R, t} = {30, 1, 1/20}. In both cases, t is the thickness of the beam", + "texts": [ + " With respect to the upper and lower bounds used for {\u03b81, \u03b82, \u03b83} (see (5.6)), these are \u03b8 lb1 = 0; \u03b8 lb2 = 0; \u03b8 lb3 = 0; \u03b8ub1 = 2\u03c0; \u03b8ub2 = \u03c0; \u03b8ub3 = 2\u03c0. We have chosen these bounds since in the performed experiments, it is not expected that rotations of more than one loop take place, but of course the above bounds can be expanded if the geometry of the problem suggests so. The first examples consider applications where the geometry of the undeformed domain 0 resembles that of a beam. In particular, we consider the rectangular section beam in Fig. 2a and the beam with circular cross-section in Fig. 2b. For both cases, the eigenvectors {v1, v2, v3} featuring in the definition of Cg in (5.2) are defined as v1 = [ 1, 0, 0 ]T v2 = [ 0, 1, 0 ]T v3 = [ 0, 0, 1 ]T for the case in Fig. 2a and v1 = [ 1, 0, 0 ]T v2 = [ 0, \u2212 sin \u03b8, cos \u03b8 ]T v3 = [ 0, cos \u03b8, sin \u03b8 ]T for the case in Fig. 2b. In both cases, the boundary conditions are such that the displacements in X1 = 0 are 0 in the three directions {E1, E2, E3} of the configuration {X1, X2, X3}. Three target configurations, target = d ( 0), have been prescribed: (i) Shapemorphing configuration 1: rectangular cross-section beamwith target configuration given by d(X) = [ X1, X2, X3 + 0.15L sin ( 2\u03c0 X1 L )]T . (5.14) (ii) Shapemorphing configuration 2: rectangular cross-section beamwith target configuration given by d(X) = [ L 2\u03c0 sin ( 2\u03c0X1 L ) , X2, \u2212 L 2\u03c0 cos ( 2\u03c0X1 L )]T . (5.15) (iii) Shape morphing configuration 3: circular cross-section beam with target configuration given by d(X) = \u23a1 \u23a2\u23a2\u23a3 \u2212(R f + cos \u03b8)r cos ( 2\u03c0X1 L f + \u03c0L 4 ) (R f + cos \u03b8)r sin ( 2\u03c0X1 L f + \u03c0L 4 ) \u2212 6 r sin \u03b8 + X1L f L + 2 \u23a4 \u23a5\u23a5\u23a6 , (5.16) with R f = 6 and L f = 4, and with (r , \u03b8) given by r = \u221a X2 2 + X2 3, tan \u03b8 = X3 X2 . For the case of the rectangular cross-section beam in Fig. 2a, the final configurations attained at convergence are depicted in Fig. 3, correspondingwith the optimal solutions that yield the closest growth-driven configurations to the target configurations denoted as shape morphing configurations 1 and 2. In addition, Fig. 4 depicts the evolution of the cost function for the case of the shape morphing configuration 1. The interior-point algorithm has been used as the optimization method. With regard to the circular cross-section beam in Fig. 2b, with target configuration given in Eq. (5.16), the final growth-driven configuration is displayed in Fig. 5, along with the contour plot distribution of the three design variables {\u03bb\u03021, \u03bb\u03022, \u03bb\u03023}. The tight agreement with respect to the target configuration initially prescribed in Eq. (5.16) is shown in Fig. 5d. Next, we consider the two undeformed configurations given in Fig. 6a and the beam with circular cross-section in Fig. 6b. For both cases, the eigenvectors {v1, v2, v3} are defined as v1 = [ cos \u03b8, sin \u03b8, 0 ]T v2 = [\u2212 sin \u03b8, cos \u03b8, 0 ]T v3 = [ 0, 0, 1 ]T " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004626_f_version_1458880549-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004626_f_version_1458880549-Figure8-1.png", + "caption": "Figure 8. Representation of the target vehicle (S) and the camera vehicle (C) at instants k-1 and k.", + "texts": [ + " Temporal Filtering The use of an EKF filter proved very useful to reduce the noise of the estimated 3D poses of the target vehicle. At the same time, it allowed a better prediction of the 2D position of the markers in the images and significantly improves the performance of the system. State vector: The EKF state vector has two different parts, xk = [ p \u03bds ]T . The term p contains the six degrees of freedom defining the current position, p1, and orientation, p2, of the target vehicle S represented in the camera frame C at time k (see Figure 8): p = [ p1 T p2 T ]T = [ x y z \u03c6 \u03b8 \u03c8 ]T (11) The term \u03bds contains the six degrees of freedom defining the linear, \u03bd1,s, and angular, \u03bd2,s, velocities of the target vehicle with respect to the inertial frame E represented in the tracked vehicle frame Sk at time k: \u03bds = [ \u03bd1,s T \u03bd2,s T ]T (12) Prediction: Our model is governed by a non-linear function f : xk = f (xk\u22121, uk, nk) (13) which relates the state at a time k, xk, given the state at a time k \u2212 1, xk\u22121, a control input uk and a non-additive noise nk = [ nT 1 nT 2 ]T that follows a Gaussian distribution with zero mean and covariance Qk. According to the notation used in Figure 8, and assuming that the target vehicle follows a constant velocity model, f can be expressed as: xk = [ pk \u03bdk s ] = ( \u2206c) A \u2295 ( pk\u22121 B \u2295 \u2206s ) \u03bdk\u22121 s + n2\u2206t (14) where operators \u2295 and denote the commonly-used six degrees of freedom inversion and compounding operations [28], the term \u2206t denotes the time elapsed between time k\u2212 1 and k, the term \u2206c denotes the variation of the pose of the camera vehicle in the elapsed time \u2206t and is part of the control input uk, the term \u2206s corresponds to the variation of the pose of the target vehicle in the camera frame, Ck, and can be computed as: \u2206s = [ \u03bdk\u22121 1,s \u2206t + 1 2 n1\u2206t2 J\u03c9(pk\u22121 2 ) ( \u03bdk\u22121 2,s + n2\u2206t\u2212 RT(pk\u22121 2 )\u03bdk\u22121 2,g ) \u2206t ] (15) where \u03bd Gk\u22121 2,g is the angular velocity of the camera vehicle at the instant k\u2212 1 and is part of the control input uk, J\u03c9(pk\u22121 2 ) is the Jacobian that transforms the angular velocity of the target vehicle (S) with respect to camera vehicle (C) to p\u0307k 2 = [ \u03c6\u0307 \u03b8\u0307 \u03c8\u0307 ]T and is given by: J\u03c9(\u03c6, \u03b8, \u03c8) = 1 sin \u03c6 tan \u03b8 cos \u03c6 tan \u03b8 0 cos \u03c6 \u2212 sin \u03c6 0 sin \u03c6 cos \u03b8 cos \u03c6 cos \u03b8 (16) and RT(pk\u22121 2 ) is the rotation matrix that transforms a point expressed in the S coordinate system to the G coordinate system which depends on their relative attitude pk\u22121 2 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002418__32_5_32_32_456__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002418__32_5_32_32_456__pdf-Figure2-1.png", + "caption": "Fig. 2 Sectional view of the hand (top view)", + "texts": [ + " 1 \u6307\u306e\u958b\u9589\u6a5f\u69cb \u63d0\u6848\u7fa9\u624b\u306f\u5bfe\u5411\u306b\u914d\u7f6e\u3055\u308c\u305f\u540c\u4e00\u5f62\u72b6\u306e 3\u6307\u304c\u540c\u6642\u306b\u958b\u9589\u3059 \u308b\u3053\u3068\u306b\u3088\u308a\u5bfe\u8c61\u3092\u628a\u6301\u3059\u308b\uff0eFig. 2\u306b\u30cf\u30f3\u30c9\u306e\u5185\u90e8\u65ad\u9762\u3092\u793a \u3059\uff0e\u30cf\u30f3\u30c9\u306b\u306f\u52d5\u529b\u6e90\u306e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\uff08L12-R\uff0cFirgelli Technologies Inc\uff09\uff0c\u5236\u5fa1\u7528\u30de\u30a4\u30b3\u30f3\uff08Arduino Pro Mini\uff09\u304c \u5185\u8535\u3055\u308c\u3066\u3044\u308b\uff0eTable 1\u306b\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4ed5\u69d8\u3092\u793a \u3059\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306f\uff0c\u4f4d\u7f6e\u5236\u5fa1\u53ef\u80fd\u306a\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u3066\u3044\u308b\uff0e\u30cf\u30f3\u30c9\u5185\u90e8\u306b\u306f\u6307\u306e\u958b\u9589\u306e\u305f\u3081\u306b Fig. 3\u306b\u793a\u3059\u3088\u3046\u306a \u30ea\u30f3\u30af\u6a5f\u69cb\u3092\u63a1\u7528\u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4f38\u7e2e\u3059\u308b \u30b7\u30e3\u30d5\u30c8\u5148\u7aef\u90e8\u306f\u30ea\u30f3\u30af 1\u306b\u76f4\u7d50\u3057\u3066\u3044\u308b\uff0e\u30b7\u30e3\u30d5\u30c8\u304c\u521d\u671f\u4f4d \u7f6e\u304b\u3089\u4f38\u5c55\u3059\u308b\u3068\uff0c\u305d\u308c\u306b\u4f34\u3063\u3066\u30ea\u30f3\u30af 1\u304c\u30cf\u30f3\u30c9\u5185\u90e8\u3092\u79fb\u52d5 \u3057\uff0c\u5916\u88c5\u90e8\u3068\u306e\u63a5\u70b9\u3092\u30ac\u30a4\u30c9\u3068\u3057\u3066\u30ea\u30f3\u30af 2\u304c\u7e70\u308a\u51fa\u3055\u308c\uff0c\u30b7\u30e3 \u30d5\u30c8\u3068\u30ea\u30f3\u30af 2\u304c\u6210\u3059\u89d2\u5ea6\u304c\u5897\u52a0\u3059\u308b\uff0e\u3053\u308c\u306b\u3088\u3063\u3066\uff0c\u6307\u304c\u958b 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\u3080\u3088\u3046\u306b\u628a\u6301\u3059\u308b\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u6307\u5148\u306b\u88c5\u7740\u3059\u308b\u30b7\u30ea\u30b3\u30f3 \u88fd\u30ad\u30e3\u30c3\u30d7\uff08\u786c\u5ea6 30\u5ea6\uff0c\u539a\u3055 1.5 [mm]\uff09\u306f\uff0c\u628a\u6301\u3057\u305f\u7269\u4f53\u304c\u6ed1 \u308b\u306e\u3092\u9632\u304e\uff0c\u9069\u5ea6\u306b\u67d4\u3089\u304b\u3044\u6307\u5148\u3092\u5b9f\u73fe\u3057\u3066\u3044\u308b\uff0e\u307e\u305f\uff0c\u6307\u5148 \u5168\u4f53\u304c\u30b7\u30ea\u30b3\u30f3\u3067\u8986\u308f\u308c\u308b\u305f\u3081\uff0c\u66f8\u7c4d\u306e\u30da\u30fc\u30b8\u3092\u6372\u308b\u5834\u5408\u3084\u673a \u4e0a\u306e\u7269\u4f53\u3092\u305f\u3050\u308a\u5bc4\u305b\u308b\u5834\u5408\u306b\u3082\u6709\u52b9\u3067\u3042\u308b\uff0e3\u6307\u306f\u540c\u4e00\u5f62\u72b6 \u306e\u305f\u3081\uff0c\u6545\u969c\u6642\u306e\u4ea4\u63db\u3082\u5bb9\u6613\u3067\u3042\u308b\uff0e \u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201455\u2014 2014 \u5e74 6 \u6708 2. 2 \u5bfe\u5411\u914d\u7f6e\u306e 3\u6307 Fig. 4\u306b 3\u6307\u3092\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u914d\u7f6e\u3092\u793a\u3059\uff0e\u6b63\u9762\u304b\u3089\u898b \u3066\u6307\u5148\u4f4d\u7f6e\u304c\u5185\u5074\u3092\u9802\u89d2\u3068\u3059\u308b\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u3068\u306a\u308b\u3088\u3046\u306b\u914d\u7f6e \u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5\u30c8\u306e\u7e70\u308a\u51fa\u3057\u91cf\u304c\u540c\u3058 \u5834\u5408\uff0c\u6b63\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u3088\u308a\u3082\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u306e\u307b\u3046\u304c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\uff08\u4e21\u7aef\u77e2\u5370\u90e8\u5206\uff09\u3092\u3088\u308a\u5927\u304d\u304f\u78ba\u4fdd\u3067\u304d\u308b\uff0e500 [ml] \u306e\u30da\u30c3\u30c8\u30dc\u30c8\u30eb\u3092\u628a\u6301\u3067\u304d\u308b\u5341\u5206\u306a\u7a7a\u9593\u3092\u78ba\u4fdd\u3059\u308b\u305f\u3081\uff0c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\u306f 80 [mm]\u3068\u3057\u305f\uff0e Fig. 5\u306e\u5de6\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\uff0cOttobock\u793e\u306a\u3069\u306e 3\u6307\u306e\u7b4b\u96fb \u7fa9\u624b\u306f\uff0c\u30ea\u30f3\u30af\u306e\u904b\u52d5\u65b9\u5411\u304c\u56de\u8ee2\u8ef8\u306b\u5bfe\u3057\u3066\u76f4\u4ea4\u3057\u3066\u3044\u308b\u305f\u3081\uff0c \u5e73\u677f\u72b6\u306e\u5bfe\u8c61\u3092\u628a\u6301\u3059\u308b\u5834\u5408\uff0c\u56de\u5185\u5916\u3092\u884c\u308f\u305a\u306b\u628a\u6301\u53ef\u80fd\u306a\u65b9 \u5411\u306f 1 \u7a2e\u985e\u306e\u307f\u3067\u3042\u308b\uff08\u4e00\u822c\u7684\u306a 2 \u6307\u80fd\u52d5\u30d5\u30c3\u30af\u3082\u540c\u69d8\uff09\uff0e\u4e00 \u65b9\uff0cFig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003236_id_0354-51801805953L-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003236_id_0354-51801805953L-Figure2-1.png", + "caption": "Figure 2: Schematic diagram of tracked vehicle steering", + "texts": [ + " The structure of dual electric tracked vehicle is shown in Figure 1, which mainly includes seven parts: general controller, engine-generator set, rectifier, battery pack, DC/DC converters, driving motors and motor controllers. For the convenience of analysis, it\u2019s assumed that both the attachment coefficient and the resistance coefficient of ground are constant, the vertical load distribution of the inside and outside tracks is uniform, and the slip or skid of the tracks is ignored. The steering diagram is shown in Figure 2. With the inside driving force F1 and outside driving force F2, the vehicle overcomes inside resistance f1, outside resistance f2 and steering resistance torque M\u00b5 , then turns at angular speed \u03c9. L is the connection length of the track, B is the center distance of the tracks, V1 and V2 are the speed of the inside and outside tracks respectively, V0 is the longitudinal average speed of vehicle. In the absence of air resistance ,the equation formulas can be established as formula (1): F1 + F2 \u2212 f1 \u2212 f2 = mV\u03070 (F2 \u2212 F1)B/2 + ( f1 \u2212 f2)B/2 \u2212M\u00b5 = Iz\u03c9\u0307 f1 = f2 = 0", + " At the same time, considering the response delay of the motor drive system, the output torque is added with a first-order lag link, and the final output torque Tm is expressed as: Tm = Treq/(\u03c4s + 1) (Tb max(n) \u2264 Treq \u2264 Td max(n)) Td max(n)/(\u03c4s + 1) (Treq > Td max(n)) Tb max(n)/(\u03c4s + 1) (Treq < Tb max(n)) (13) Where Treq is the demand torque obtained by the control strategy, \u03c4 is the response time constant,Td max(n) and Tb max(n) respectively represent the maximum drive torque and maximum braking torque of the motor when the motor speed is n. 4.1.2 Vehicle trajectory model In order to describe the dynamic process of vehicle steering more accurately, a vehicle trajectory model is established [20]. As shown in Figure 2, a fixed coordinate system Oxy is established on the ground, when the vehicle begins to turn, the center of mass is represented by O, and the transverse and longitudinal direction of the vehicle are respectively represented by the x axis and y axis. A dynamic coordinate system O\u2032x\u2032y\u2032 is built on the vehicle body, when the vehicle is turning, the center of mass is represented by O\u2032 , and the transverse and longitudinal direction of the vehicle are respectively represented by the x\u2032 axis and y\u2032 axis" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000649_8600701_08779625.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000649_8600701_08779625.pdf-Figure1-1.png", + "caption": "FIGURE 1. Diagram of the structure of a fuel-controlled aircraft engine of a fuel-powered UAV (1) EFI unit, (2) UAV propeller, (3) rotating shaft, (4) Hall sensor, (5) steering-engine, (6) engine cylinder block, (7) CDI ignition, (8) starting motor, (9) multistage transmission gear, (10) throttle plate, (11) engine pedestal, and (12) ECU unit.", + "texts": [ + " Secondly, the experimental station is set up for the model verification. In addition, the provided fuel process is analyzed based on the simulation results, and then the effect of several key parameters on the power characteristics is studied. This research can be considered as the power characteristic optimization and cruising duration improvement of a fuel-powered UAV. A fuel-powered aircraft engine is electronic fuel injection (EFI)-modified to realize accurate fuel supply control during engine operation. From Fig. 1, the fuel-controlled aircraft engine is mainly composed of two capacitor discharge ignitions (CDIs) and one EFI unit, opposed engine cylinders, Hall sensor, throttle plate controlled by a steering-engine, starting motor, UAV propeller, and assorted engine control unit (ECU). The fuel injection control principle of the aircraft engine is as shown in Fig. 2. The main components in the fuel injection control system include the Hall sensor, fuel injector, and CDI ignition. A magnet is installed on the rotating shaft at 10\u201330\u25e6 before the pistons reach the top dead center" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure7-19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure7-19-1.png", + "caption": "Figure 7-19. Sch\u00e9ma du syst\u00e8me d'antennes utilis\u00e9", + "texts": [ + " 238 Suite \u00e0 la r\u00e9alisation de notre syst\u00e8me d'\u00e9valuation exp\u00e9rimentale du gain de diversit\u00e9 qui a demand\u00e9 un certain temps de prise en main, nous avons pu r\u00e9aliser une premi\u00e8re campagne de mesures que nous allons d\u00e9crire dans cette partie. L'objectif de cette campagne est de valider l'ensemble de notre syst\u00e8me d'\u00e9valuation exp\u00e9rimentale pour un nombre limit\u00e9 de situations. 7.3.1 Le syst\u00e8me d'antennes Pour r\u00e9aliser cette premi\u00e8re campagne de mesure nous avons utilis\u00e9 le syst\u00e8me compos\u00e9 de deux antennes patch \u00e0 double polarisation que nous avons pr\u00e9sent\u00e9 en d\u00e9tail dans le chapitre 4. Pour rappel, un sch\u00e9ma avec les dimensions du syst\u00e8me ainsi qu'une photo de celle-ci sont pr\u00e9sent\u00e9es la Figure 7-19 et la Figure 7-20 respectivement. Les antennes patch du syst\u00e8me sont carr\u00e9es et disposent de deux ports qui permettent de r\u00e9cup\u00e9rer en un m\u00eame point de l'espace \u00e0 la fois les composantes des ondes polaris\u00e9es verticalement et celles des ondes polaris\u00e9es horizontalement. Avec les quatre voies de ce syst\u00e8me nous allons donc chercher \u00e0 comparer trois configurations de diversit\u00e9 diff\u00e9rentes : la diversit\u00e9 spatiale avec les deux voies polaris\u00e9es verticalement, la diversit\u00e9 de polarisation en utilisant les deux voies du patch sup\u00e9rieur et enfin, la diversit\u00e9 spatiale et de polarisation en utilisant la voie polaris\u00e9e verticalement sur le patch sup\u00e9rieur et la voie polaris\u00e9e horizontalement sur le patch inf\u00e9rieur" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002045_nkhair2021_07004.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002045_nkhair2021_07004.pdf-Figure6-1.png", + "caption": "Fig. 6. Load distribution process", + "texts": [], + "surrounding_texts": [ + "Chassis design with specifications chassis length 6000mm, chassis width 2500mm, using AISI 1018 steel material, rectangular model with dimensions 120x80x3mm. The Von Mises stress value for AISI 1018 106 HR steel material is 29.06 MPa for the standard mesh, 28.6 MPa for the 10 mm control mesh and 28.15 MPa. The displacement value for AISI 1018 106 HR steel material is 0.3643 mm for the standard grid, 0.3704 mm for the 10 mm control grid and 0.3764 mm for the 5 mm control grid. The safety factor for AISI 1018 106 HR steel material is 9.32 for the standard fabric, 9.45 for the 10 mm control fabric and 9.58 for the control fabric." + ] + }, + { + "image_filename": "designv8_17_0000491_ajabssp.2010.1.6.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000491_ajabssp.2010.1.6.pdf-Figure1-1.png", + "caption": "Fig. 1: Offset double-disks opener (a) and modified double-disks opener (b)", + "texts": [ + " The objective of the present study was to assess the effects of adding two inclined mini disks to common doubledisk opener on the characteristics of seedbed furrow and banding fertilizer. Experimental equipments: In this study a commercially used no-tillage Double-Disk Opener (DDO) was compared with a novel opener named as modified DDO (MDO). Double-disk opener consisted of two flat disks with a diameter of 390 mm. One disk set 32 mm prior to work as a coulter and was aligned parallel to the traveling path vertically. Another disk was assembled with the angle of about 10\u00b0 as the distance of them at back was 60 mm (Fig. 1a.). This structure (offset double-disks) was also used in the modified opener, but two mini disks with diameters of 100 mm were mounted in the back (Fig 1b). The purpose of using this prototype was to lay fertilizer in the slot created by offset double-disks while mini disks create two horizontal grooves a little higher at both sides of the fertilizer slot. Such outline can ensure efficient vertical and horizontal separation between seed and fertilizer. Mini disks were assembled with the rake angle of 25\u00b0 in order to eliminate negative suction of disk implement for penetrating into the soil, because researchers found (Damora and Pandey, 1995) the furrow openers have lower draft at smaller width and wedge and a rake angle of 40\u00b0 or less" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003890_f_version_1688970560-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003890_f_version_1688970560-Figure13-1.png", + "caption": "Figure 13. Force analysis of the contact between the driving foot and the rotor.", + "texts": [ + " Therefore, the input displacement can be expressed by the following formula: ( ) ( ) ( ) ( )sin 2 sin 2O t U ft P t U ft\u03c0 \u03b4 \u03c0 \u03d5= \u2202 = + (21) Wherein, \u2202 and \u03b4 are electromechanical coupling coefficients, U is voltage amplitude and f is resonance frequency. Figure 11. Dynamics model of two degrees of freedom. As mentioned above, in order to better fit the rotor, the driving foot is specially planned, as shown in Figure 12. The elephant trunk is designed. The four fulcrum points 1 2 3 4PPPP do not exert force on the spherical rotor together. When the rotor has flexural vibration displacement, two fulcrum points will be separated from the rotor, and the remaining two fulcrum points will push forward the movement, as shown in Figure 13. When the rotor rotates around the Z axis, the two points of P1P4 release and do not contact the rotor, and the remaining two points will push it to rotate. In fact, in the process of rotor rotation, the force on the rotor is gradually transferred from the surface to the line at the last point, so the force on the rotor is enough for it to rotate. However, all the forces in this paper are summed up into one point for analysis. According to the above, the rotor is first subjected to pF , followed by the tangential force tF generated during bending The typical structure of a piezoelectric actuator is composed of a preload mechanism, a base, and a stator", + " Therefore, the input displacement can be expressed by the following formula: O(t) = \u2202U sin(2\u03c0 f t)P(t) = \u03b4U sin(2\u03c0 f t + \u03d5) (21) Wherein, \u2202 and \u03b4 are electromechanical coupling coefficients, U is voltage amplitude and f is resonance frequency. Sensors 2023, 23, 6264 12 of 19 As mentioned above, in order to better fit the rotor, the driving foot is specially planned, as shown in Figure 12. The elephant trunk is designed. The four fulcrum points P1P2P3P4 do not exert force on the spherical rotor together. When the rotor has flexural vibration displacement, two fulcrum points will be separated from the rotor, and the remaining two fulcrum points will push forward the movement, as shown in Figure 13. When the rotor rotates around the Z axis, the two points of P1P4 release and do not contact the rotor, and the remaining two points will push it to rotate. In fact, in the process of rotor rotation, the force on the rotor is gradually transferred from the surface to the line at the last point, so the force on the rotor is enough for it to rotate. However, all the forces in this paper are summed up into one point for analysis. According to the above, the rotor is first subjected to Fp, followed by the tangential force Ft generated during bending vibration", + " Modal Analysis T e m dal analysis and harmonic response analysis of the whole stator were carried out usin ANSYS Workbench software, and the stator parameters were constantly adjusted according to the modal analysis results to achieve frequency degeneracy. The polarization and parameter setting of piezoelectric ceramics were processed in Workbench software. The three working modes are shown in Figure 14, and the frequencies are 42.788 kHz, 42.795 kHz, and 43.027 kHz, respectively. The difference between these three characteristic frequencies is 0.007 kHz and 0.268 kHz respectively, and the difference is less than 0.6% of the stator resonant frequency, which indicates that the three vibration modes achieve good degeneracies. Figure 13. Force analysis of the contact between th driving foot and the rotor. 4. Driver odel of Electromagnetic-Piezoelectric Hybrid Drive otor 4.1. Modal Analysis The modal analysis and harmonic response analysis of the whole stator were carried out using ANSYS Workbench software, and the stator parameters were constantly adjusted according to the modal analysis results to achieve frequency degeneracy. The polarization and parameter setting of piezoelectric ceramics were processed in Workbench software" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003281_om_article_22266_pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003281_om_article_22266_pdf-Figure7-1.png", + "caption": "Fig. 7. Vibration collection point", + "texts": [], + "surrounding_texts": [ + "The electromagnetic vibration of PMSM can be analyzed by the modal superposition method. The radial electromagnetic force is applied to the finite element model of the motor structure as a load to calculate the electromagnetic vibration induced by the radial electromagnetic force generated by the field-circuit coupling method. Since low-frequency vibration is generally considered in engineering, electromagnetic vibration frequency of motors below 3500 Hz is mainly analyzed. The motor vibration collection point and collection point vibration acceleration spectrum are shown in Figs. 7 and 8. The main vibration frequencies of the housing and endcap are 320 Hz, 960 Hz and 1280 Hz. Because of the large amplitude of radial electromagnetic force at 320 Hz, it is easier to excite the mode of the stator system. At 960 Hz and 1280 Hz, the stator system resonance is excited due to 1194 JOURNAL OF VIBROENGINEERING. SEPTEMBER 2022, VOLUME 24, ISSUE 6 the dense stator system modes. Although the modes are denser at 2000 Hz-3500 Hz, the vibration amplitude of the stator system is relatively small and the energy is low. It is not easy to excite the modes of the motor." + ] + }, + { + "image_filename": "designv8_17_0001070_f_version_1687313919-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001070_f_version_1687313919-Figure2-1.png", + "caption": "Figure 2. 2-DOF robot manipulator.", + "texts": [ + " L2 f h(x) + LgL f h(x)u +KTH \u2265 0, (34) where K = [k0 k1] T, H = [h(x) L f h(x)]T and L f h(x), L2 f h(x), LgL f h(x) are defined by (30)\u2013(33), respectively. Remark 3. Safety is always required to be satisfied even though the states of the system break the limit. When the constraints hold, the tracking error cannot converge to the origin, which means the system is unstable from this perspective. Therefore, this is a compromise between safety and performance. In this section, numerical simulations exemplify the validity and performance of the proposed control strategy. Consider a two-link robotic manipulator system [15], as shown in Figure 2, whose dynamics equation is described as an Euler\u2013Lagrange system: M(q\u0308) + C(q, q\u0307)q\u0307 + G(q) = \u03c4 + \u03c4d. In this case, qi denotes the angular position of the ith arm, ri the length of the arm, mi the mass, and Ji the moment of inertial. Denote q = [q1 q2] T as the state of the system and the relative matrices are defined as M(q\u0308) = [ M11 M12 M21 M22 ] , C(q, q\u0307) = [ \u2212\u03b212(q2)q\u03072 1 \u2212 2\u03b212(q2)q\u03071q\u03072 \u03b212(q2)q\u03072 2 ] , G(q) = [ (m1 + m2)gr1 cos q2 + m2gr2 cos(q1 + q2) m2gr2 cos(q1 + q2) ] , where M11 = (m1 + m2)r2 1 + m2r2 2 + 2m2r1r2 cos q2 + J1, M12 = m2r2 2 + m2r1r2 cos q2, M21 = m2r2 2 + m2r1r2 cos q2, M22 = m2r2 2 + J2, \u03b212(q2) = m2r1r2 sin q2 with parameters given as r1 = 1 m, r2 = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003069_df_ru_2024_02_07.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003069_df_ru_2024_02_07.pdf-Figure1-1.png", + "caption": "Figure 1 \u2014 Section of the flow area of the combine cleaning system:", + "texts": [], + "surrounding_texts": [ + "\u0412\u0432\u0435\u0434\u0435\u043d\u0438\u0435. 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\u0441\u043b\u043e\u0432\u0430: \u0441\u0438\u0441\u0442\u0435\u043c\u0430 \u043e\u0447\u0438\u0441\u0442\u043a\u0438, \u043f\u0440\u043e\u0442\u043e\u0447\u043d\u0430\u044f \u043e\u0431\u043b\u0430\u0441\u0442\u044c, 2D-\u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u0435, \u0432\u043e\u0437\u0434\u0443\u0448\u043d\u044b\u0435 \u043f\u043e\u0442\u043e\u043a\u0438, \u043a\u043e\u043c\u0431\u0430\u0439\u043d\nDOI: https://doi.org/10.46864/1995-0470-2024-2-67-53-60\n\u043a\u0430\u0437\u0430\u0442\u0435\u043b\u044c \u0440\u0430\u0432\u043d\u043e\u043c\u0435\u0440\u043d\u043e\u0441\u0442\u0438 \u043f\u043e\u0442\u043e\u043a\u0430, \u043a \u043e\u0431\u0435\u0441\u043f\u0435\u0447\u0435\u043d\u0438\u044e \u043a\u043e\u0442\u043e\u0440\u043e\u0433\u043e \u043d\u0443\u0436\u043d\u043e \u0441\u0442\u0440\u0435\u043c\u0438\u0442\u044c\u0441\u044f.\n\u0415\u0441\u043b\u0438 \u0440\u0430\u0441\u0441\u043c\u043e\u0442\u0440\u0435\u0442\u044c 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\u0435\u0435 \u043b\u043e\u043a\u0430\u043b\u044c\u043d\u0430\u044f \u0430\u0434\u0430\u043f\u0442\u0430\u0446\u0438\u044f, \u0432 \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0435 \u043a\u043e\u0442\u043e\u0440\u043e\u0439 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u0435 \u0431\u0435\u0437\u0440\u0430\u0437\u043c\u0435\u0440\u043d\u043e\u0439 \u043f\u0435\u0440\u0435\u043c\u0435\u043d\u043d\u043e\u0439 y+, \u043e\u043f\u0438\u0441\u044b\u0432\u0430\u044e\u0449\u0435\u0439 \u043f\u0440\u043e\u0444\u0438\u043b\u044c \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0438 \u043f\u0440\u0438\u0441\u0442\u0435\u043d\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438, \u043d\u0435 \u043f\u0440\u0435\u0432\u044b\u0448\u0430\u0435\u0442 10, \u0447\u0442\u043e \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0443\u0435\u0442 \u0440\u0435\u043a\u043e\u043c\u0435\u043d\u0434\u043e\u0432\u0430\u043d\u043d\u043e\u0439 \u0432\u0435\u043b\u0438\u0447\u0438\u043d\u0435 [6]. \u041f\u0440\u0438\u0437\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0438\u0439 \u0441\u043b\u043e\u0439 \u043f\u0440\u0438\u0441\u0442\u0435\u043d\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u0441\u043e\u0434\u0435\u0440\u0436\u0438\u0442 10\u202615 \u044f\u0447\u0435\u0435\u043a \u0432 \u043d\u043e\u0440\u043c\u0430\u043b\u044c\u043d\u043e\u043c \u043d\u0430\u043f\u0440\u0430\u0432\u043b\u0435\u043d\u0438\u0438 \u043a \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044e \u043f\u043e\u0442\u043e\u043a\u0430. \u041a\u043e\u044d\u0444\u0444\u0438\u0446\u0438\u0435\u043d\u0442 \u0440\u043e\u0441\u0442\u0430 (Expansion Factor) \u0440\u0430\u0437\u043c\u0435\u0440\u043e\u0432 \u044f\u0447\u0435\u0435\u043a \u0441\u0435\u0442\u043a\u0438 \u0441\u043e\u0441\u0442\u0430\u0432\u0438\u043b 1,2. \u041f\u043e \u0438\u0442\u043e\u0433\u0443 \u043f\u043e\u0441\u0442\u0440\u043e\u0435\u043d\u043d\u0430\u044f \u0441\u0435\u0442\u043a\u0430 \u0438\u043c\u0435\u0435\u0442 \u0441\u043b\u0435\u0434\u0443\u044e\u0449\u0438\u0435 \u043f\u043e\u043a\u0430\u0437\u0430\u0442\u0435\u043b\u0438 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0430: \u043e\u0440\u0442\u043e\u0433\u043e\u043d\u0430\u043b\u044c\u043d\u043e\u0441\u0442\u044c (Mesh Orthogonality) \u2014 \u043d\u0435 \u043c\u0435\u043d\u0435\u0435 0,7; \u043a\u043e\u044d\u0444\u0444\u0438\u0446\u0438\u0435\u043d\u0442 \u043f\u0440\u043e\u043f\u043e\u0440\u0446\u0438\u043e\u043d\u0430\u043b\u044c\u043d\u043e\u0441\u0442\u0438 (Aspect Ratio) \u2014 \u043d\u0435 \u0431\u043e\u043b\u0435\u0435 50.\n\u0412 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u0440\u0430\u0431\u043e\u0447\u0435\u0433\u043e \u0442\u0435\u043b\u0430 \u043f\u0440\u0438\u043c\u0435\u043d\u0435\u043d\u0430 \u043c\u043e\u0434\u0435\u043b\u044c \u0432\u043e\u0437\u0434\u0443\u0445\u0430 (air) \u0441 \u043f\u043b\u043e\u0442\u043d\u043e\u0441\u0442\u044c\u044e 1,225 \u043a\u0433/\u043c3 \u0438 \u0432\u044f\u0437\u043a\u043e\u0441\u0442\u044c\u044e 1,7894\u00b710\u20135 \u043a\u0433/(\u043c\u00b7\u0441) \u043f\u0440\u0438 \u0442\u0435\u043c\u043f\u0435\u0440\u0430\u0442\u0443\u0440\u0435 20 \u00b0C.\n\u041d\u0430 \u0433\u0440\u0430\u043d\u0438\u0446\u0435 \u0432\u0445\u043e\u0434\u0430 \u0438 \u0432\u044b\u0445\u043e\u0434\u0430 \u0438\u0437 \u0440\u0430\u0441\u0447\u0435\u0442\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u043e\u043f\u0438\u0441\u0430\u043d\u044b \u0433\u0440\u0430\u043d\u0438\u0447\u043d\u044b\u0435 \u0443\u0441\u043b\u043e\u0432\u0438\u044f pressure-inlet \u0438 pressure-outlet \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0435\u043d\u043d\u043e \u0441 \u043e\u0442\u043d\u043e\u0441\u0438\u0442\u0435\u043b\u044c\u043d\u044b\u043c \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u0435\u043c p = 0 \u041f\u0430 (\u0430\u0442\u043c\u043e\u0441\u0444\u0435\u0440\u043d\u043e\u0435 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u0435 101 325 \u041f\u0430).\n\u0412 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u043c\u043e\u0434\u0435\u043b\u0438 \u0442\u0443\u0440\u0431\u0443\u043b\u0435\u043d\u0442\u043d\u043e\u0433\u043e \u0442\u0435\u0447\u0435\u043d\u0438\u044f \u0432\u044b\u0431\u0440\u0430\u043d\u0430 SST k-\u03c9-\u043c\u043e\u0434\u0435\u043b\u044c \u0441 \u0434\u0432\u0443\u043c\u044f \u0434\u0438\u0444\u0444\u0435\u0440\u0435\u043d\u0446\u0438\u0430\u043b\u044c\u043d\u044b\u043c\u0438 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044f\u043c\u0438, \u043f\u0440\u0435\u0434\u0441\u0442\u0430\u0432\u043b\u044f\u044e\u0449\u0430\u044f \u0441\u043e\u0431\u043e\u0439 \u043a\u043e\u043c\u0431\u0438\u043d\u0430\u0446\u0438\u044e k-\u03b5- \u0438 k-\u03c9-\u043c\u043e\u0434\u0435\u043b\u0435\u0439 \u0442\u0443\u0440\u0431\u0443\u043b\u0435\u043d\u0442\u043d\u043e\u0441\u0442\u0438: \u0434\u043b\u044f \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0442\u0435\u0447\u0435\u043d\u0438\u044f \u0432 \u0441\u0432\u043e\u0431\u043e\u0434\u043d\u043e\u043c \u043f\u043e\u0442\u043e\u043a\u0435 \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u0443\u044e\u0442\u0441\u044f \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044f k-\u03b5-\u043c\u043e\u0434\u0435\u043b\u0438, \u0430 \u0432 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u0432\u0431\u043b\u0438\u0437\u0438 \u0441\u0442\u0435\u043d\u043e\u043a \u2014 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044f k-\u03c9-\u043c\u043e\u0434\u0435\u043b\u0438. \u042d\u0442\u0430 \u043c\u043e\u0434\u0435\u043b\u044c \u0434\u043e\u0432\u043e\u043b\u044c\u043d\u043e \u0441\u0442\u0430\u0431\u0438\u043b\u044c\u043d\u0430, \u043f\u043e\u0434\u0445\u043e\u0434\u0438\u0442 \u0434\u043b\u044f \u0440\u0435\u0448\u0435\u043d\u0438\u044f \u0440\u0435\u0430\u043b\u044c\u043d\u044b\u0445 \u0438\u043d\u0436\u0435\u043d\u0435\u0440\u043d\u044b\u0445 \u0437\u0430\u0434\u0430\u0447 \u0438 \u0432\u043e \u043c\u043d\u043e\u0433\u0438\u0445 \u0441\u043b\u0443\u0447\u0430\u044f\u0445 \u043f\u0440\u0435\u0434\u043b\u0430\u0433\u0430\u0435\u0442 \u0445\u043e\u0440\u043e\u0448\u0438\u0439 \u043a\u043e\u043c\u043f\u0440\u043e\u043c\u0438\u0441\u0441 \u0441 \u0442\u043e\u0447\u043a\u0438 \u0437\u0440\u0435\u043d\u0438\u044f \u0442\u043e\u0447\u043d\u043e\u0441\u0442\u0438 [8].\n\u0422\u0430\u043a \u043a\u0430\u043a \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u043f\u043e\u0442\u043e\u043a\u0430 \u0432\u043e\u0437\u0434\u0443\u0445\u0430 \u0432 \u0441\u0438\u0441\u0442\u0435\u043c\u0435 \u0433\u043e\u0440\u0430\u0437\u0434\u043e \u043d\u0438\u0436\u0435 \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0438 \u0437\u0432\u0443\u043a\u0430, \u043f\u0440\u0438 \u0442\u0430\u043a\u0438\u0445 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u044f\u0445 \u0441\u0436\u0438\u043c\u0430\u0435\u043c\u043e\u0441\u0442\u044c \u0441\u0440\u0435\u0434\u044b \u043d\u0435\u0437\u043d\u0430\u0447\u0438\u0442\u0435\u043b\u044c\u043d\u0430 \u0438 \u0435\u0439 \u043c\u043e\u0436\u043d\u043e \u043f\u0440\u0435\u043d\u0435\u0431\u0440\u0435\u0447\u044c [9, 10]. \u0412 \u0441\u0432\u044f\u0437\u0438 \u0441 \u044d\u0442\u0438\u043c \u0434\u043b\u044f \u0440\u0435\u0448\u0435\u043d\u0438\u044f \u0441\u0438\u0441\u0442\u0435\u043c\u044b \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0439, \u043e\u043f\u0438\u0441\u044b\u0432\u0430\u044e\u0449\u0438\u0445 \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044f \u0441\u0440\u0435\u0434\u044b, \u0431\u044b\u043b \u043f\u0440\u0438\u043c\u0435\u043d\u0435\u043d \u0440\u0435\u0448\u0430\u0442\u0435\u043b\u044c \u043d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f Pressure-Based [11].\n\u0412 \u0432\u043e\u0437\u0434\u0443\u0448\u043d\u043e\u043c \u043f\u043e\u0442\u043e\u043a\u0435 \u0440\u0430\u0441\u0441\u043c\u0430\u0442\u0440\u0438\u0432\u0430\u0435\u043c\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u0438 \u0438\u0437\u043c\u0435\u0440\u0435\u043d\u0438\u0439 \u0438\u043c\u0435\u0435\u0442 \u043c\u0435\u0441\u0442\u043e \u043f\u0440\u043e\u0442\u0435\u043a\u0430\u043d\u0438\u0435 \u0432\u0438\u0445\u0440\u0435\u0432\u044b\u0445 \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u043e\u0432, \u0438 \u043f\u043e \u0440\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u0430\u043c \u044d\u043a\u0441\u043f\u0435\u0440\u0438\u043c\u0435\u043d\u0442\u0430\u043b\u044c\u043d\u044b\u0445 \u0437\u0430\u043c\u0435\u0440\u043e\u0432 \u0438\u0437\u043c\u0435\u043d\u0435\u043d\u0438\u0435 \u0432\u0435\u043b\u0438\u0447\u0438\u043d \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u0435\u0439 \u043f\u043e\u0442\u043e\u043a\u0430 \u0432 \u043a\u043e\u043d\u0442\u0440\u043e\u043b\u044c\u043d\u044b\u0445 \u0442\u043e\u0447\u043a\u0430\u0445 \u0434\u043e\u0441\u0442\u0438\u0433\u0430\u0435\u0442 30 %, \u043f\u043e\u044d\u0442\u043e\u043c\u0443 \u043f\u043e\u0441\u0442\u0430\u043d\u043e\u0432\u043a\u0430 \u0437\u0430\u0434\u0430\u0447\u0438 \u0442\u0440\u0435\u0431\u0443\u0435\u0442 \u043d\u0435\u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0433\u043e \u0440\u0435\u0448\u0435\u043d\u0438\u044f. \u0414\u043b\u044f \u0440\u0435\u0448\u0430\u0442\u0435\u043b\u044f \u0431\u044b\u043b\u0430 \u0432\u044b\u0431\u0440\u0430\u043d\u0430 \u0444\u043e\u0440\u043c\u0443\u043b\u0438\u0440\u043e\u0432\u043a\u0430 \u0441 \u0432\u0440\u0435\u043c\u0435\u043d\u043d\u043e\u0439 \u0430\u043f\u043f\u0440\u043e\u043a\u0441\u0438\u043c\u0430\u0446\u0438\u0435\u0439 Transient Formulation, \u0430 \u0434\u043b\u044f \u043e\u043f\u0438\u0441\u0430\u043d\u0438\u044f \u0432\u0437\u0430\u0438\u043c\u043e\u0434\u0435\u0439\u0441\u0442\u0432\u0438\u044f \u043c\u0435\u0436\u0434\u0443 \u043f\u043e\u0434\u0432\u0438\u0436\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u044c\u044e \u0432\u0435\u043d\u0442\u0438\u043b\u044f\u0442\u043e\u0440\u0430 \u0438 \u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u043e\u0439 \u043e\u0431\u043b\u0430\u0441\u0442\u044c\u044e \u0441\u0438\u0441\u0442\u0435\u043c\u044b \u043e\u0447\u0438\u0441\u0442\u043a\u0438 \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043d\u0430 \u043c\u043e\u0434\u0435\u043b\u044c \u0441\u043a\u043e\u043b\u044c\u0437\u044f\u0449\u0435\u0439 \u0441\u0435\u0442\u043a\u0438 Sliding Mesh Model.\n\u0420\u0430\u0437\u043c\u0435\u0440 \u0448\u0430\u0433\u0430 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u043f\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u0438 \u0394t \u043f\u0440\u0438 \u043d\u0430\u043b\u0438\u0447\u0438\u0438 \u0441\u043a\u043e\u043b\u044c\u0437\u044f\u0449\u0435\u0439 \u0441\u0435\u0442\u043a\u0438 \u0431\u044b\u043b \u0432\u044b\u0447\u0438\u0441\u043b\u0435\u043d \u0441\u043e\u0433\u043b\u0430\u0441\u043d\u043e \u0440\u0435\u043a\u043e\u043c\u0435\u043d\u0434\u0430\u0446\u0438\u044f\u043c [12]:\n\u0433\u0434\u0435 \u0394s \u2014 \u0440\u0430\u0437\u043c\u0435\u0440 \u044d\u043b\u0435\u043c\u0435\u043d\u0442\u0430 \u0441\u0435\u0442\u043a\u0438 \u0432 \u0441\u043a\u043e\u043b\u044c\u0437\u044f\u0449\u0435\u043c \u0438\u043d\u0442\u0435\u0440\u0444\u0435\u0439\u0441\u0435; \u03c5m \u2014 \u043e\u0442\u043d\u043e\u0441\u0438\u0442\u0435\u043b\u044c\u043d\u0430\u044f \u0441\u043a\u043e\u0440\u043e\u0441\u0442\u044c \u0434\u0432\u0438\u0436\u0443\u0449\u0435\u0439\u0441\u044f \u0437\u043e\u043d\u044b.\n1 \u2014 fan inlet; 2 \u2014 exit from the flow area; 3 \u2014 entrance from the threshing and separating device" + ] + }, + { + "image_filename": "designv8_17_0003971__2462_context_theses-Figure2-3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003971__2462_context_theses-Figure2-3-1.png", + "caption": "Figure 2-3: Typical megawatt wind turbine (Reference [1])", + "texts": [ + " However, today\u2019s system can now generate more than 5000kW13. The wind turbines run at a minimum wind speed of about 3 m/s and reach their rated power at around 14m/s. Wind turbines generally turn off at a wind speed of around 25 m/s for security 13 Reference [2, p. 273] Figure 2-1: Darrieus wind turbines (Reference [18]) Figure 2-2: Typical horizontal axis wind turbine (Reference [1]) 7 reasons. The wind power plant is controlled by limiting, which can be controlled, for example by adjusting the blade angles (pitch control)14. Figure 2-3 shows the main parts of these kind of wind turbines. The parts can be divided into four main groups; rotor, energy conversion, sensors & structure and electric gear as shown in Figure 2-4. Most of these systems are made of a rotor with three wing-shaped blades that are attached to a hub. The hub is attached to the nacelle, which houses the energy conversion and the sensors and structure parts. 14 Reference [22, p. L 29] 8 The shaft of the rotor which is called low speed shaft is attached to the gear box" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003011_e_download_5812_5060-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003011_e_download_5812_5060-Figure4-1.png", + "caption": "Fig. 4. The testing device for an experimental study on the progress of tangential forces at the set or variable slip s", + "texts": [ + " The corresponding dimensions of the contact spot according to Hertz are a = 14.32 mm; b = 5.77 mm. For the experimental study of the progresses of tangential forces at the set or variable slip s, another type of a laboratory device was developed, which is expected to verify or supplement the existing opinions based on the established coefficient of adhesion \u00b5, i.e. on the ratio between radial loading force and incurred tangential force. The principle of its activity is described by means of the diagram presented in Fig. 4. The tested samples of material 2, 3 are disc-shaped and have similar diameter. Both discs are driven directly by vector-controlled synchronous servomotors 4, 5. The upper system 3, 4 is located on rest 6 pivoted in relation to machine frame 1 around the indicated axis A. Servomotor 5 is located on horizontally-sliding rest 7. The shaft of the upper disc 3 is fitted with torsionally-flexible dynamograph 8. The radial loading of both discs can be adjusted by means of vertical drawbars 9 linked to girder dynamographs 10 in the bottom part" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure2.2-1.png", + "caption": "Figure 2.2: Original Revolving Vane Compressor Design [17]", + "texts": [ + "............ VIII A-5 Effect of Surface Roughness on Sliding Thermal Contact Resistance ... XIII A-6 Measurement Data, Theoretical Prediction and Uncertainty Analysis ...XVI A-7 Material Specifications for PEEK ...........................................................XIX A-8 Specifications for Measurement Instruments & Induction Motor ........ XXII viii List of Figures Figure 2.1: Rolling Piston Compressor .................................................................................... 5 Figure 2.2: Original Revolving Vane Compressor Design ...................................................... 7 Figure 2.3: Revolving Vane Working Principle ...................................................................... 8 Figure 2.4: Revolving Vane Inertial Torque Comparison ....................................................... 9 Figure 2.5: Improved Revolving Vane Journal Bearing Design............................................ 10 Figure 2.6: Predicted Fluid Flow in Revolving Vane Working Chamber ", + " However, it is also not without any flaws as well, evident from its vane design which causes high friction losses and material wear. With these undesirable characteristics in mind, the RV compressor design was conceived in a bid to remove these traits. The next Section 2.2 will detail the development of the RV compressor. The RV compressor design was first presented by Teh and Ooi [17\u201319] as a more mechanically efficient compressor alternative to the rolling piston compressor. A schematic of the very first RV compressor design is shown in Figure 2.2. 7 The RV compressor design appears to be similar to that of the rolling piston with the eccentric arrangement of the rotor and cylinder but the operating principles of both compressors are actually very much different. In the case of the RV mechanism, the roller and eccentric shaft of the rolling piston are merged into a single rotor and shaft component with a vane port and suction port cut into it. This reduces the friction loss between the roller and eccentric component. In addition, in order to circumvent the high contact force caused by the vane spring on the roller, the vane in the RV has been replaced with that of a swiveling one that is affixed to the cylinder and slides within the rotor slot during compressor operation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004311_9312710_09476016.pdf-Figure55-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004311_9312710_09476016.pdf-Figure55-1.png", + "caption": "FIGURE 55. (a) A BIE and (b) four BIEs placed on the top CubeSat face. [39].", + "texts": [ + " Next, the effects of a finite square ground plane and the introduction of a rectangular slot in Fig. 53 are examined. These modifications shifted the \u03b2n value of Mode 1 down in frequency, whereas the \u03b2n value of Mode 3 slightly rose upwards to 2.2 GHz, relative to the structure with finite ground plane. This is illustrated in Fig. 54. VOLUME 9, 2021 98851 Next, the study in [39] analyzed a new excitation mechanism called the BIE. It comprises two non-resonant half loops fed with opposite phases and equal magnitude, as seen in Fig. 55(a). Four BIEs are placed at the center of each face edge of the CubeSat, as illustrated in Fig. 55(b). The shape of the platform and the BIEs configuration enabled 11 modes to be excited significantly within the 2.4 to 2.45 GHz operating frequency range, as shown in Fig. 56. Current modes presented in Fig. 57 indicates maxima either located at the center of the edges (modes 1 to 6 and modes 10 to 12) or at the center of a face (modes 7 to 9). The locations of these exciters at the edges are suitable to avoid interfering with solar panels or other platform payloads or systems. F. METASURFACE In this section, several important literatures which uses CMA to predict modal behaviors of metasurfaces are presented" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003445_le_download_6534_pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003445_le_download_6534_pdf-Figure16-1.png", + "caption": "Figure 16 Test benches", + "texts": [ + "1 Materials The main maize variety Xianda 205 grown in the third accumulated temperate zone in the northeast region of China was chosen for the tests. The maize grains, maize stalks, maize cobs, and lightweight impurities were uniformly mixed according to the proportion of each component in the maize mixture obtained during the field tests with a maize grain combine harvester. The proportions are shown in Table 2. 5.1.2 Methods The laboratory tests were carried out by driving the cleaning device of the planar reciprocating vibrating screen as shown in Figure 16a and the cleaning device of the bionic screen as shown in Figure 16b through frequency converters (6ES6430-2UD27-1CA0, 6ES6430-2UD27-5CA0, Siemens, Germany). The bionic screen was divided into four areas of I, II, III, and IV with the same length along the longitudinal direction, and area I is the front of the bionic screen. The inlet airflow velocity of the bionic screen was 9.6 m/s, and its angle with the horizontal plane was 25\u00b0. The maximum concave depth was 50 mm, and the rotational speeds of the cams were 90 r/min. Compared with the planar reciprocating vibrating screen working under the optimal working parameters (the inlet airflow velocity was 9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure2.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure2.8-1.png", + "caption": "Figure 2.8. An independent suspension employing a ball joint and two rod links, reproduced from [26].", + "texts": [ + "7 has one wheel carrier K (k = 1); three links a, b, and c (l = 3); six joints labeled one through six (g = 6); two superfluous link rotations (r = 2); and (f1, . . . , f6) = (3, 3, 3, 3, 1, 2). Consequently, F = 1. Unfortunately, Matschinsky does not use his mobility formula as the basis of a systematic enumeration, instead presenting various architectures of interest and showing how they conform to the formula. He does however, consider rigid axle suspensions and the extremely rare compound suspensions, which guide multiple wheel 51 carriers, showing the generality of his approach. The generality also allows for independent suspensions like Figure 2.8 to be considered, with the wheel carrier both directly (with the ball joint) and indirectly (with the rod links) connected to the vehicle body. Raghavan\u2019s approach excludes mechanisms of this type. The downside of allowing other types is the potentially infinite number of possible architectures. Indeed, this is why Matschinsky chooses not to perform an enumeration, rather favoring a survey of historically important architectures. It is interesting then, that Raghavan considers a large number of joints and links and only one linkage type, while Matschinsky considers a small number of joints and links and a large number of linkage types" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000103_021_2021-4_8-988.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000103_021_2021-4_8-988.pdf-Figure9-1.png", + "caption": "Fig. 9. Pin-on-disc wear testing apparatus.", + "texts": [ + " With the help of Minitab software, by means of Face Centred Central Composite Design (FCCD), a type of RSM method, 20 experiments were generated for parameter load (10, 20,30N), aging temperature (151,153 and 155\u00b0 C) and aging time (3,4,5hrs). The sliding distance, sliding velocity and Track diameter were constant at 1000 m, 1m/s and 90mm. The wear testing factors used for the test are tabulated in Table 2. From the cast composite, the specimen size of 10 x 10 x 10 mm was machined and the sliding wear test was conducted as per ASTM G99 was carried out according to the experimental design obtained by adopting face centred composite design (FCCD). The wear testing was carried out in a pin \u2013on \u2013disc tribometer as shown in Fig. 9. The test was conducted in the air in the dry sliding state. During the wear test, the room temperature was noted to be 30\u00b0 C with a relative humidity of 45 \u00b1 15%. The specimen was kept firmly in contact with the EN 32 counter face disc of hardened steel with a Rockwell hardness of 65HRC in a specimen holder. By applying the applied load through a lever mechanism, the cast specimen was held in direct contact with the counterface disc. Before and after the procedure, the mass of the cast composite specimen was measured using an electronic weighing system with an accuracy of 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000771_1081-023-09833-9.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000771_1081-023-09833-9.pdf-Figure12-1.png", + "caption": "Fig. 12 Manufacturing constraint", + "texts": [], + "surrounding_texts": [ + "Design constraints are related to the structural stiffness, to the safety and to the manufacturing of the wheel. The first group of constraints is related to the structural stiffness of the wheel in radial, bending and torsional directions. Radial stiffness is evaluated by applying a cosine radial force distribution on the bead seats of the rim, over an angular span of 60 degrees (Stearns et al. 2004, 2006; Raju et al. 2007). In this case, displacements and rotations of the central hub are constrained. The radial stiffness is defined as Krad = Frad urad (2) where Frad is the resultant radial force and urad is the average radial displacement of the nodes located in the center of the loaded region. The radial stiffness is evaluated at three different angular locations of the wheel rim, namely the spoke centerline, the middle position between two adjacent spokes and an intermediate position not coincidingwith one of the previous two locations. The term Krad in Eq. 2 is the average value of the radial stiffnesses computed for the three considered loading positions. To calculate bending and torsional stiffness, the rim is fixed at the rim flanges and a concentrated bending or torsional moment is applied at the central hub. The second set of constraints refers to the safety of the wheel. Global buckling is evaluated by means of the eigenvalue problem of Eq. 3 (Cook et al. 2001) ([K] + \u03bbb[K ])\u2202D = 0 (3) where [K ] is the stress stiffnessmatrix evaluated for stresses associated to the applied arbitrary load. The eigenvector D associated to the eigenvalue \u03bbb defines the shape of the critical deformed configuration. In the analysis, external loads are applied in different locations of the rim to account for the rolling motion of the wheel. The eigenvalue problem is solved by means of the Abaqus standard solver. The constraint on global buckling therefore reads \u03bbb > \u03bbb,cr (4) In addition to Eq. 4, localized instabilities due to geometric features may occur as local buckling phenomenon. Such a condition is typical of thin-walled cross sections and is modeled through the simplified, but general, expression given by Ashby (2011) \u03c6 \u2264 \u03c6cr (5) where \u03c6 is the shape efficiency factor of the beam cross section subject to elastic bending (Ashby 2011; Gobbi et al. 2017), defined as \u03c6 = 12I A2 (6) where I and A are the second moment of inertia and the area of the cross section respectively. The critical value \u03c6cr of Eq. 5 depends on the cross section material and reads \u03c6cr \u223c= 2.3 \u221a E \u03c3adm (7) where E and \u03c3adm are the Young Modulus and the admissible stress of the material respectively. Finally, a third class of constraints takes into account the manufacturing phase of the wheel. In particular, milling and turning are considered as the main technological processes used for the construction of the wheel for a racing quadricycle. The manufacturing constraint aims at ensuring the feasibility of the part. A lower limit for the distance between the structural members of the spokes is set, as shown in Fig. 12for the X-spoke case. Table 5summarizes the limit values of the design constraints." + ] + }, + { + "image_filename": "designv8_17_0000371_f_version_1670506480-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000371_f_version_1670506480-Figure3-1.png", + "caption": "Figure 3. The mechanic model in overrunning condition of DASOC. Figure 3. The mechanic model in overrunning condition of DASOC.", + "texts": [ + " The self-locking angle is inversely proportional to the coefficient. The maximum self-locking angle is 11.4\u25e6 when the sliding friction coefficient is 0.1. For safety, the self-locking angle is between 7.5\u25e6 to 8.5\u25e6 in design. In the overrunning condition of the DASOC, the sliding friction of the outer ring and double arc sprag is the major resistance. Therefore, this chapter gives the limits of the size and shape of the sprag meeting the overrunning conditions of the overrunning clutch on the condition of sliding friction. As shown in Figure 3, the outer ring is in a clockwise rotation with the inner star wheel in overrunning condition. The static model of the double arc sprag is shown in Figure 3. If the outer ring and the double arc sprag are not in bonding condition, the upper arc of the double arc sprag can slide to the outer ring. Equation (4) can be derived. f AFn < AF t (4) Machines 2022, 10, x FOR PEER REVIEW 5 of 18 A tF and A nF are the tangential and normal force of the double arc sprag at Point A, respectively, and f is the sliding friction coefficient between the double arc sprag and outer ring. Because of the counterclockwise rotation between outer ring and the inner star wheel, the roller also has a counterclockwise trend movement at Point B under a self-locking state", + " The maximum self-locking angle is 11.4\u00b0 when the sliding friction coefficient is 0.1. For safety, the self-locking angle is between 7.5\u00b0 to 8.5\u00b0 in design. 2.2. The Overrunning Condition of DASOC In the ov rrunning condition of the DASOC, the sliding friction of the outer ring and double arc prag is the major re istan e. Therefore, this chapter gives the limits of the size and shape of the sprag meeting the overrunning conditions of the overrunning clutch on the condition of sliding friction. As sh wn in Figure 3, the outer ring is in a clockwise otation with the inner star wheel in ove running condition. The static m del of t e double arc sprag is shown in Figure 3. If the oute ring and the double arc sprag are not in bonding condition, the upper arc of the double arc sprag ca slide to the outer ring. Equation (4) can be derived. A A n tf F F (4) The roller has a clockwise rotation tendency at Point C with the friction of the double arc sprag and outer ring. At this time, the contact force at Point B can be omitted. By taking the double arc sprag as an isolation part, the moment is calculated at Point C and Equation (5) is derived. The roller has a clockwise rotation tendency at Point C with the friction of the double arc sprag and outer ring", + " As a new type of overrunning clutch, the calculation of its internal force and contact stress is the basis for further theoretical and applied research, so it is necessary to give the calculation of internal force and contact stress. In this section, the calculation method of the internal force and stress of this clutch will be given. In the bonding condition, the overrunning clutch forms a self-locking relationship through the geometry and positional relationship of the outer ring, double arc sprag, inner star wheel, spring, and other components, and its static model is shown in Figure 3. If we suppose the input torque at the outer ring is T. Equation (7) shows the tangential force with the static equilibrium equation. AF t = T zR (7) T is the torque acting on the clutch; z is the number of rollers of the roller type overrunning clutch; R is the radius of the outer ring, Ft is the shear formula of the outer ring acting on the double arc sprag. The normal force is also derived in Equation (8). AFn = T(1 + cos \u03d5) Rz sin \u03d5 (8) According to the hypothesis above, CF = 0 and DF = 0 in bonding condition" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004247_.1117_12.2304063.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004247_.1117_12.2304063.pdf-Figure1-1.png", + "caption": "Fig. 1: CAS Main Subassemblies & STM", + "texts": [ + " The Co-Alignment Sensor (CAS) is a part of ATLID Instrument, whose mission responds to the need to provide a picture of the 3-dimensional spatial and temporal structure of the radiative flux field at the top of the Earth atmosphere, within the atmosphere and at the Earth\u2019s surface. The CAS is located on the ATLID Optical Bench and is part of the control loop that allows identifying the pointing direction of the Laser signal return used to control the Laser co-Alignment with Optical Bench. CRISA is the final responsible of the whole CAS project design and development II. MODELS & PROJECT STATUS The following deliverable models are considered: \u2022 Structural and Thermal Model (STM see Fig. 1) with the following objectives: o Risk minimization o Manufacturing & Assembly Process Check o Qualification Testing \u2022 Protoflight Model (PFM) Actually, the STM became a Qualification Model from thermo-mechanical point of view. Currently, the STM qualification testing has been successfully completed. III. MAIN REQUIREMENTS Following main mechanical requirements are applicable: Mass, Structural & Thermal \u2022 Mass < 1.68kg \u2022 Stiffness>300Hz \u2022 Maximum Envelope: 198mm x 227mm x 130mm \u2022 I/F loads on each interface point /fixation: o Forces:14-55N o Torques: 0", + "06 W/K \u2022 MCCD temperature REPLACE THIS LINE WITH YOUR PAPER IDENTIFICATION NUMBER (DOUBLE-CLICK HERE TO EDIT) < 3 equation (equation (2)) utilizing Young\u2019s parabolic potential approximation [18] (equation (3)) and boundary conditions pertaining to the continuity of electrical flux [23]. \ud835\udf152\ud835\udf13 \ud835\udf15\ud835\udc5f2 + 1 \ud835\udc5f ( \ud835\udf15\ud835\udf13 \ud835\udf15\ud835\udc5f ) + 1 \ud835\udc5f2 \ud835\udf15 \ud835\udf15\ud835\udf03 ( \ud835\udf15\ud835\udf13 \ud835\udf15\ud835\udf03 ) + \ud835\udf152\ud835\udf13 \ud835\udf15\ud835\udc672 = \u2212\ud835\udc5e\ud835\udc41\ud835\udc37(\ud835\udc67) \ud835\udf16\ud835\udc46\ud835\udc56 \ud835\udc53\ud835\udc5c\ud835\udc5f \ud835\udc5f1 \u2264 \ud835\udc5f \u2264 \ud835\udc5f2 (1) where \ud835\udc5f, \ud835\udf03, and \ud835\udc67 are the cylindrical coordinate axes along the radial, angular, and axial (along the channel length) directions, \ud835\udf13 is the channel potential, \ud835\udc5e is the electron charge, \ud835\udf16\ud835\udc60\ud835\udc56 is the dielectric constant of silicon and \ud835\udc41\ud835\udc37(\ud835\udc67) is the donor concentration in the channel region of the Macaroni body cell. Furthermore, the structure shown in Fig. 1 is symmetrical along the axial direction, results in \ud835\udf13 independent of \ud835\udf03 i.e., \ud835\udf15\ud835\udf13(\ud835\udc5f,\ud835\udf03,\ud835\udc67) \ud835\udf15\ud835\udf03 = 0. Equation (1) will reduce to a 2D Poisson\u2019s equation given by [23] as: \ud835\udf152\ud835\udf13 \ud835\udf15\ud835\udc5f2 + 1 \ud835\udc5f ( \ud835\udf15\ud835\udf13 \ud835\udf15\ud835\udc5f ) + \ud835\udf152\ud835\udf13 \ud835\udf15\ud835\udc672 = \u2212\ud835\udc5e\ud835\udc41\ud835\udc37 \ud835\udf16\ud835\udc46\ud835\udc56 \ud835\udc52\ud835\udc65\ud835\udc5d ( \u2212\ud835\udc58\ud835\udc672 2\ud835\udf0e2 ) (2) Now, Young\u2019s parabolic potential approximation [18] can be utilized to simplify the 2D electrostatic potential distribution along the radial direction inside the channel region as: \ud835\udf13(\ud835\udc5f, \ud835\udc67) = \ud835\udc361(\ud835\udc67) + \ud835\udc5f. \ud835\udc362(\ud835\udc67) + \ud835\udc5f2. \ud835\udc363(\ud835\udc67) (3) Where \ud835\udc361(\ud835\udc67), \ud835\udc362(\ud835\udc67) and \ud835\udc363(\ud835\udc67) are arbitrary coefficients which can be obtained by using following boundary conditions [23]: a) Electric field lines inside the channel terminate at the silicon body-core filler dielectric interface i", + " Moreover, we define the potential at the channel-core filler interface (\ud835\udc5f = \ud835\udc5f1) as the inner potential, \ud835\udf13\ud835\udc5c = \ud835\udf13(\ud835\udc5f = \ud835\udc5f1, \ud835\udc67). Now, utilizing above boundary conditions and assumption, equation (2) can be expressed as: \ud835\udc512\ud835\udf130(\ud835\udc67) \ud835\udc51\ud835\udc672 \u2212 \ud835\udf130(\ud835\udc67) \ud835\udf062 = \u2212(\ud835\udc49\ud835\udc54\ud835\udc60\u2212\ud835\udc49\ud835\udc53\ud835\udc4f) \ud835\udf062 \u2212 \ud835\udc5e\ud835\udc41\ud835\udc37 \ud835\udf16\ud835\udc46\ud835\udc56 \ud835\udc52\ud835\udc65\ud835\udc5d ( \u2212\ud835\udc58\ud835\udc672 2\ud835\udf0e2 ) (4) Where \ud835\udc49\ud835\udc53\ud835\udc4f is the flat-band voltage and \ud835\udf06 is characteristic length of the Macaroni body 3D NAND flash cell expressed as \ud835\udf06 = \u221a 4\ud835\udf16\ud835\udc46\ud835\udc56\ud835\udc61\ud835\udc46\ud835\udc56+\ud835\udc36\ud835\udc5c\ud835\udc65\ud835\udc61\ud835\udc46\ud835\udc56 2 8\ud835\udc36\ud835\udc5c\ud835\udc65 [23]. The inner potential (\ud835\udf130 at the channel/core-filler interface in figure 1(c)) obtained by solving the differential equation utilizing the principle of superposition where the solution consists of a complementary function and a particular integral [23] as: \ud835\udf130(\ud835\udc67) = [ (\ud835\udc49\ud835\udc45 \u2212 \ud835\udc3e1) sinh ( \ud835\udc3f\ud835\udc54 \u2212 \ud835\udc67 \ud835\udf06 ) + (\ud835\udc49\ud835\udc45 + \ud835\udc49\ud835\udc51\ud835\udc60 \u2212 \ud835\udc3e2) sinh ( \ud835\udc67 \ud835\udf06 ) sinh ( \ud835\udc3f\ud835\udc54 \ud835\udf06 ) ] + {(\ud835\udc49\ud835\udc54\ud835\udc60 \u2212 \ud835\udc49\ud835\udc53\ud835\udc4f) + \ud835\udc5e\ud835\udc41\ud835\udc37\ud835\udf062 \ud835\udf16\ud835\udc46\ud835\udc56 \ud835\udc52\ud835\udc65\ud835\udc5d ( \u2212\ud835\udc58\ud835\udc672 2\ud835\udf0e2 )} (5) \ud835\udc3e1 and \ud835\udc3e2 are constants that can be expressed as [23]: This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License. For more information, see https://creativecommons.org/licenses/by-nc-nd/4.0/ > REPLACE THIS LINE WITH YOUR PAPER IDENTIFICATION NUMBER (DOUBLE-CLICK HERE TO EDIT) < 4 The surface potential (\ud835\udf13\ud835\udc46 at channel/gate oxide interface in fig. 1(c)) can be obtained as [23]: \ud835\udf13\ud835\udc60(\ud835\udc67) = \ud835\udf130 \u2032 (\ud835\udc67) + (\ud835\udc49\ud835\udc54\ud835\udc60 \u2212 \ud835\udc49\ud835\udc53\ud835\udc4f \u2212 \ud835\udf130 \u2032 (\ud835\udc67)) ( \ud835\udc61\ud835\udc46\ud835\udc56 2 8\ud835\udf062) (8) where \ud835\udf130 \u2032 (\ud835\udc67) is inner potential obtained by solving the differential equation utilizing the principle of superposition where the solution consists of a complementary function and a particular integral (PI). \ud835\udf130 \u2032 (\ud835\udc67) = \ud835\udc361 \u2032\ud835\udc52\ud835\udc65\ud835\udc5d ( \ud835\udc67 \ud835\udf06 ) + \ud835\udc362 \u2032\ud835\udc52\ud835\udc65\ud835\udc5d (\u2212 \ud835\udc67 \ud835\udf06 ) + \ud835\udc43\ud835\udc3c (9) Where \ud835\udc361 \u2032 and \ud835\udc362 \u2032 are constants with PI, can be expressed as [23]: \ud835\udc43\ud835\udc3c = (\ud835\udc49\ud835\udc54\ud835\udc60 \u2212 \ud835\udc49\ud835\udc53\ud835\udc4f) + \ud835\udf062 ( \ud835\udc5e\ud835\udc41\ud835\udc37 \ud835\udf16\ud835\udc46\ud835\udc56 ) \ud835\udc52\ud835\udc65\ud835\udc5d ( \u2212\ud835\udc58\ud835\udc672 2\ud835\udf0e2 ) (10) Furthermore, to estimate the \ud835\udc361 \u2032 and \ud835\udc362 \u2032 the following boundary conditions can be used [23]: a) The surface potential at the source terminal \ud835\udf13\ud835\udc60(\ud835\udc67 = 0) = \ud835\udc49\ud835\udc45 b) The surface potential at the drain end \ud835\udf13\ud835\udc60(\ud835\udc67 = \ud835\udc3f\ud835\udc54) = \ud835\udc49\ud835\udc45 + \ud835\udc49\ud835\udc51\ud835\udc60" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure85-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure85-1.png", + "caption": "Figure 85 : Vue de dessus de la structure simul\u00e9e double dip\u00f4le \u00ab r\u00e9aliste \u00bb", + "texts": [ + " Une structure avec juste les deux mailles bande X entourant l\u2019alimentation des dip\u00f4les est alors consid\u00e9r\u00e9e. Autour de ces deux mailles bande X, le grillage entourant les patchs sup\u00e9rieurs est prolong\u00e9 jusqu\u2019aux bords de l\u2019hexagone, constituant ainsi un plan de masse. De m\u00eame que pour la structure \u00ab compl\u00e8te \u00bb, un trou est r\u00e9alis\u00e9 dans le grillage, et la cavit\u00e9 s\u00e9parant les deux sources bande X est supprim\u00e9e afin de ne pas entraver l\u2019alimentation de la source bande L. Les simulations de cette structure, pr\u00e9sent\u00e9e sur la Figure 85, que nous allons appeler \u00ab r\u00e9aliste \u00bb ont des temps de calcul plus importants que ceux de la structure \u00ab simple \u00bb (environ le double), mais tout de m\u00eame bien inf\u00e9rieurs \u00e0 ceux pour la structure \u00ab compl\u00e8te \u00bb avec la plupart des \u00e9l\u00e9ments bande X. Les caract\u00e9ristiques des sources bande L simul\u00e9es sont toujours celles du tableau de la Figure 83. Les comparaisons avec et sans d\u00e9pointage des coefficients de r\u00e9flexion obtenus pour chacune des deux structures consid\u00e9r\u00e9es (\u00ab compl\u00e8te \u00bb avec la maille hexagonale compl\u00e9t\u00e9e au mieux avec les sources bande X, et \u00ab r\u00e9aliste \u00bb avec seulement les deux sources bande X entourant l\u2019alimentation des dip\u00f4les) sont pr\u00e9sent\u00e9es sur la Figure 86" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000548_3_NgTeckChew2009.pdf-Figure3.13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000548_3_NgTeckChew2009.pdf-Figure3.13-1.png", + "caption": "Figure 3.13: Leader-follower formation control of mobile robots. (a) Triangle formation control. In this case, lead vehicle 1 and followers 2 and 3 formed a triangular shape. Throughout the motion, this triangular shape is maintained. (b) Line formation. In this formation, the concept can be applied to vehicular vehicle following application. Notice that the follower may not follow exactly the trajectory of the lead vehicle and some path deviation may occurred. This configuration is similar to the direct-hooked kinematic configuration as described in section 3.3.1.", + "texts": [ + " Chapter 3. The Virtual Trailer Link For Vehicle Following 95 tion Control Strategy The concept of virtual trailer link model for vehicle following has some similarities with respect to the leader-follower formation control strategy [94], [95], [93]. The Leader-follower formation control strategy has been used in multiple robot systems. In this work, a desired formation shape is maintained during the robotic following operation. The formation can be of any shape. Two typical formations are as shown in figure 3.13. Chapter 3. The Virtual Trailer Link For Vehicle Following 96 When a line formation is formed, the multiple robotic control strategy can be implemented as a vehicle following system in ITS, which is the main application of this thesis. In the leader-follower line formation control strategy, it is desired to maintain a relative position (i.e a safe inter-vehicle separation ) between the lead vehicle and followers. Hence, a reactive controller is usually designed for the follower in response to the maneuvers of the lead vehicle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001928_9312710_09400416.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001928_9312710_09400416.pdf-Figure3-1.png", + "caption": "FIGURE 3. Relation between rotated angle and the loss function value for bounding box with different aspet radio of our ProjBB. In (a), the radio of weight and height (w/h) of the red/blue/green bounding box is 2/5/10. The quadrant label \u03b1 in our method is used to limit rotated angle range \u03b8 . If \u03b1 = 0, then \u03b8 \u2208 [0,90\u25e6); else if \u03b1 = 1 then \u03b8 \u2208 (\u221290\u25e6,0]. If green box (w = 20,h = 2,CD3 = \u221a 101) rotates from D3 to D\u20323, the rotation angle is equal to \u03b83 with \u03b1 = 0. Else if green box rotates from D3 to D\u2032\u20323 , the rotated angle \u03b83 \u2208 (\u221290\u25e6,0] with \u03b1 = 1. The same logistic stays for blue box (w = 10,h = 2,CD3 = \u221a 26) and red box (w = 4,h = 2,CD3 = \u221a 5). In (b), when the rotated angle \u03b8 > 0(\u03b8 < 0), the loss function becomes monotone increasing(decreasing). Moreover, larger aspect ratio leads to steeper loss.", + "texts": [ + " Different from previous approaches, our work explores a novel projection-based method, which uses six-parameter to describe rotated bounding box: two points position on the projected line (one center point (x, y) and one chosen vertex (|u|, |v|)), a projection ratio \u03c1 and a quadrant label \u03b1, named as ProjBB. Although our method is angle-free, the rotated bounding box is represented with theoretical uniqueness guarantee, which could prevent the boundary case problem as in Fig. 1(b). Besides, the uncertainty in regression could be inherently dismissed. As show in Fig. 3 For angular periodicity problem, relationships between angle distance and our loss is empirically studied in Fig. 3(b). The relation is a monotonic function without periodicity, which indicated that a larger rotating angle leads to larger corresponding loss. Moreover, our proposed method is aspect ratio sensitive. The aspect ratio in our representation for a bounding box is fixed, the problem in Fig. 2(a) is beyond our define. In order to address different measurement problem as Fig. 2(b) shows, relationships between different aspect ratio and our loss is also studied in Fig. 3(b). As orange dotted line (\u03b8 = \u03c0/4) in Fig. 3(b) shows, when the rotated angle is equal to \u03c0/4, the green bounding box will have the largest loss value. For the reason that the green bounding box has largest aspect ratio. Accordingly, our method also could alleviate regression inconsistent problem. Our main contributions are summarized in three folds: 1) We introduce a novel projection-based representation method, named as ProjBB, to describe rotated bounding boxes. ProjBB is angle-free and has three mainadvantages: i) More accurate angle distance without periodicity; ii) Projection ratio which is aspect ratio sensitive; iii) Theoretical uniqueness guarantee, which can eliminate the regression uncertainty effectively", + " The compared benchmark methods we choose include some one-stage method like: IENet [42], RetinaNet-H [9], RetinaNet-R [9]; some two-stage method like: FR-O [37], R2CNN [6], R-DFPN [30], RRPN [7], RADet [32], ICN [31], RoI-Transformer [8]. Results in Table. 3 shows that our ProjBB outperforms oriented object detection benchmarks. Especially in BR, LV, SH, SBF, HA, where the target objects have a relatively large aspect ratio, the AP results of both our methods (ProjBB and ProjBB-R) have a significant improvement, which confirms that our method is aspect ratio sensitive as Fig. 3 analyzed. The visualized detection results for those categories are obtained in Fig. 12 and Fig. 13. However, it remains challenging to accurately detect the objects with small size and small aspect ratio (such as SV and ST) based on our method. Besides, ProjBB-R almost shares similar detection accuracy with ProjBB on each categories, which is in accord with the detection results in Fig. 12. Our finding suggests that multiplied presenting anchors have little benefit on our method (but could VOLUME 9, 2021 58775 hurt the efficiency as described below)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003303_download_25868_15461-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003303_download_25868_15461-Figure1-1.png", + "caption": "Figure 1. Structure of CMG used in the analysis", + "texts": [ + " The understanding of the CMG loss is crucial before it can be applied as efficient torque converter. In this paper, torque multiplier CMG is designed with 8/3 gear ratio. The torque and losses are evaluated via finite element and analyzed. Iron loss and eddy current loss are compared and discussed. In this section, the working principle of CMG is briefly explained. Then, the proposed structure of the CMG is introduced. Finally, the simulation configuration is described. CMG utilized the flux modulation principle to transfer torque from the inner rotor to the outer rotor. In Figure 1, it is shown that the inner yoke is attached with pairs of surface-mount permanent magnet which we called as inner pole pair, pi. When it rotates, magnetic field density changes according to the rotor frequency around it. However, when ferromagnetic pieces are introduced outside of the inner rotor, it creates magnetic field density space harmonics. The governing equation of the highest magnitude of space harmonic flux density is (3): \u03a9h = \ud835\udc5d\ud835\udc56 \ud835\udc5d\ud835\udc56\u2212\ud835\udc5b\ud835\udc60 \u03a9r (3) where \u03a9h is the space harmonic frequency, p is the number of pair, ns is the ferromagnetic pole piece and \u03a9r is the rotor frequency", + " Int J Elec & Comp Eng ISSN: 2088-8708 Preliminary analysis of eddy current and iron loss in \u2026 (Mohd Firdaus Mohd Ab Halim) 1163 The range of single-step mechanical gear ratio commonly available in the market used in combustion engine, washing machine and agriculture sector are between 1 to 4 [13]\u2013[15]. In this paper, gear ratio 3.33 or 8/3 is chosen, which act as torque multiplier. Based on (4), the inner pole pair, outer pole pair and ferromagnetic pole piece are calculated and tabulated together with the dimension of CMG in Table 1. The structure of CMG with gear ratio 8/3 is illustrated in Figure 1. In order to evaluate the torque, losses and efficiency, finite element software, JMAG Designer 16.0 is used in 2D transient mode. The rotational speed for the inner rotor is set for 800 rpm in forwards direction while the outer rotor is set for 300 rpm backward direction. The duration of the simulation for data collection is \u00bc of a full rotation. The materials used in this simulation are shown in Table 2. As mentioned, torque values taken at inner and outer rotor is in transient mode. Hence, integral average will be used to calculate the efficiency" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004553_ai.7-12-2021.2314491-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004553_ai.7-12-2021.2314491-Figure8-1.png", + "caption": "Fig. 8. \u2018", + "texts": [ + " Frame is welded to the seat at one end and bolted at the bottom. In this concept, \u2018I\u2019 section structure is used to support the seat as shown in figure 6. Frame is welded to the seat at one end and bolted at the In this concept, \u2018I\u2019 section structure with ribs as shown in figure 7 is used to support the seat structure. Frame is welded to the seat at one end and bolted at the bottom. I\u2019- section model to support the seat bottom. I\u2019- Section model with cross ribs In this concept, \u2018I\u2019 section structure with cross ribs as shown in figure 8 is used to support the seat structure. Frame is welded to the seat at one end and bolted at the bottom. Rapid Upper Limb Assessment (RULA) analysis was carried out in CATIA package and score for the body at different regions include upper arm, lower arm, wrist, neck, trunk, and legs are obtained [7]. The score indicates the risk of Musculoskeletal Disorders (MSD). MSDs are injuries and disorders that affect the human body's movement or musculoskeletal system. The analysis was carried out under various sitting posture conditions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001817_451-41171703218M.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001817_451-41171703218M.pdf-Figure4-1.png", + "caption": "Figure 4a: The reduction the speed of movement of grain [10]", + "texts": [ + " These are the main causes of deformation and there are multiple solutions: adjustment of the pneumatic system with modern shapes of elbows, installation of the Venturi pipe directly below grain dinspenser in order to obtain sufficient speed at the beginning of movement, precise regulation of air and grain velocity through pipe, etc. Improving the flow of grain through the pneumatic system is conditioned by maintaining the desired and projected daily capacity required for uninterrupted production. The former principle of dosing (Figure 4a) has given good results in terms of design capacity, but with the consequence of significant damage to the piping system for a certain period of exploitation. Draft decision are primarily related to the installation of the Venturi injectors [10] at the entrance to the pneumatic system (Figure 4b) a directly under the collector. This solution would be accelerated at the beginning of grain getting into a tube system and slow moving design speed evenly over the whole cross-section. Flow is hereby improves by 50% and even up to 80% with the elimination of all phenomena that negatively affect it [02]. , 433 Journal of Applied Engineering Science 15(2017)3 b) Venturi injector Figure 4b: The reduction the speed of movement of grain [10] Grain flow is caused by the speed of air flow through the pipe system and the principle of movement is presented in Figure 5 [01, 02, and 03]. Tests by Foster [05, 06] indicate that the fracture of the grain is mostly influenced by the speed of air flow through the system and not the speed of moving the grain. Experimental tests for different materials show that the minimum velocity soybeans through a pneumatic system, which is 26.1 m / s, while below this speed material is very difficult to carried out through the system [06]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004050__DN10_DN10032FU1.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004050__DN10_DN10032FU1.pdf-Figure3-1.png", + "caption": "Figure 3: Dimensions of the Tensairity actuator.", + "texts": [ + " The first prototype was able to demonstrate the concept of the new actuator; however, the load path was very limited and the overall behaviour was not very satisfactory. Further studies have shown that a conical shape enhances the performance of the actuator enormously. The cables were replaced by an upper tension element, which is identical to the compression element. The Tensairity actuator consists of two flexible aluminium struts with 1.5 x 20 mm cross sectional area, which are tightly connected with pockets to the hull of a conical air chamber called the actuation chamber (black), as shown in fig. 3. Inside the actuation chamber is a smaller air chamber called the displacement chamber (grey). This chamber is dimensioned such that it fills the volume of the actuation chamber if the actuator is fully deflected. The role of the displacement chamber is to enhance the efficiency of the actuator and to support the deformation of the struts as described in Section 3.2. The pressure of both chambers can be changed independently. For a normal actuation cycle, only the pressure of the actuation chamber is changed, while the pressure in the displacement chamber is kept constant" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003110_9874358_09831045.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003110_9874358_09831045.pdf-Figure7-1.png", + "caption": "Fig. 7. Fabricated W-band prototype. (a) Assembled filter unit. (b) Close-up view of the internal cavity and one of the resonating iris slots.", + "texts": [ + " Each of the layers is aligned on top of one another using Vernier scale alignment marks before thermocompression bonding. To minimize the effect of underetching and promote a high accuracy between the simulated and measured results, the middle layer is fabricated using a fallout technique [25], and a compensative side wall underetching effect has been applied to the design. Once fabricated and assembled, both versions of the filters were tested using a Rohde & Schwarz ZVA67 with their respective up-converters. Fig. 7 shows the fabricated structure from EDM wire erosion, while Fig. 8 shows a comparison of the simulated and measured results over 75\u2013110 GHz. The measured return loss is better than 20 dB in the measured passband while the measured insertion loss at the measured center frequency is approximately 0.31 dB with an estimated Qu of \u2248 500. Fig. 9 presents the fabricated structure from DRIE micromachining, while Fig. 10 presents a comparison of the simulated and measured results over 220\u2013330 GHz. The measured return loss is better than 13" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001789_cle_download_505_375-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure1-1.png", + "caption": "Figure 1. Coss-sectional view of a typical radial-flux inner rotor spoke-type IPMSM.", + "texts": [ + " Various design variables like magnetic loading, slot-loading, space factor, winding factor, aspect ratio, split ratio, conductor current density, magnet fraction and core flux density are selected appropriately considering materials availability and performance requirements [21]. Usually, magnetic loading is assumed between 0.4 T to 0.9 T, and slot-loading is assumed between 100 to 400 A. The range of conductor current density is 4A/mm2 to 8A/mm2, and the magnet fraction is 0.67 to 0.9 [22]. The cross-sectional view of a typical spoke-type IPMSM is given in Figure 1 for a better understanding of the spoke-type permanent magnet rotor and slotted stator\u2019s physical arrangement along with the geometrical design parameters. The main dimensions of IPMSM have been calculated, with the assumption of L/D ratio [23], as follows: D2L = P 11\u03b7ocos\u03d5Bgackwn10\u22123 , (1) where P is the power rated, D the bore diameter, L the axial length of the motor, \u03b7o the assumed efficiency, cos\u03d5 the power factor, Bg the air-gap flux density, ac the electrical loading, and kw the winding factor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000179_iceesi2017_01019.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000179_iceesi2017_01019.pdf-Figure1-1.png", + "caption": "Fig. 1. Configuration of the PIFA antenna with L-shaped slot.", + "texts": [ + " \ud835\udc53\ud835\udc53(\ud835\udc3a\ud835\udc3a\ud835\udc3b\ud835\udc3b\ud835\udc67\ud835\udc67) \u2248 300 / [4(\ud835\udc3f\ud835\udc3f(\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a) + \ud835\udc4a\ud835\udc4a(\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a) + h(\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a)) \u221a\ud835\udf00\ud835\udf00\ud835\udc52\ud835\udc52\ud835\udc53\ud835\udc53\ud835\udc53\ud835\udc53] (3) The following equation is used to obtain the upper frequency band \ud835\udc53\ud835\udc53(\ud835\udc3a\ud835\udc3a\ud835\udc3b\ud835\udc3b\ud835\udc67\ud835\udc67) \u2248 300 / [4(\ud835\udc3f\ud835\udc3f2(\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a)+\ud835\udc3f\ud835\udc3f3(\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a)) \u221a\ud835\udf00\ud835\udf00\ud835\udc52\ud835\udc52\ud835\udc53\ud835\udc53\ud835\udc53\ud835\udc53 (4) \u00a9 The Authors, published by EDP Sciences. This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0/). In order to maintain the first resonant frequency (the lower) the dimension of the patch is adjusted. The configuration of the proposed antenna is presented in Figure 1, and it can be seen that there is an air separation between the ground plane and the substrate that hold the patch. For this case an effective dielectric constant is used in the above equations \ud835\udf00\ud835\udf00\ud835\udc52\ud835\udc52\ud835\udc53\ud835\udc53\ud835\udc53\ud835\udc53= \ud835\udf00\ud835\udf00\ud835\udc5f\ud835\udc5f.(h\ud835\udc60\ud835\udc60+ h\ud835\udc4e\ud835\udc4e\ud835\udc56\ud835\udc56\ud835\udc5f\ud835\udc5f)\ud835\udf00\ud835\udf00\ud835\udc5f\ud835\udc5f. h\ud835\udc4e\ud835\udc4e\ud835\udc56\ud835\udc56\ud835\udc5f\ud835\udc5f+ \ud835\udf00\ud835\udf00\ud835\udc4e\ud835\udc4e\ud835\udc56\ud835\udc56\ud835\udc5f\ud835\udc5f. h\ud835\udc60\ud835\udc60 (5) The feeding and the shorting wall are in line in Figure 1, separated by 4 mm from the edge where is located the shorting wall to the centre of the coaxial probe feed. 3.1 S11 measurement Vs simulation The simulation and measured result are Figure 2 where both result simulation and measurement are approximately the same. Measurement result drops at 0.9 GHz, whilst simulation result drops at 0.9 GHz. The antenna copper wire angle of the design hardware will affect the result. These may happen because of manual fabrication and designing hardware where the angle is very difficult to make it 90\u00b0 which is like a sharp angle as same in simulation design", + " Return loss value of the measured result shows that it is in good value for the radiation signal where the insertion loss value is less than -10. Shown in figure 3 is VSWR measurement versus simulation result. It is shows that, both of the results are approximately the same. VSWR is defined as the ratio of the maximum voltage to the minimum voltage in standing wave pattern along the length of a transmission line structure. It varies from 1 to (plus) infinity and is always positive. From the result, all the value is positive at the targeted frequency and it is approaching to 1. Fig. 1. Configuration of the PIFA antenna with L-shaped slot. In order to maintain the first resonant frequency (the lower) the dimension of the patch is adjusted. The configuration of the proposed antenna is presented in Figure 1, and it can be seen that there is an air separation between the ground plane and the substrate that hold the patch. For this case an effective dielectric constant is used in the above equations \ud835\udf00\ud835\udf00\ud835\udc52\ud835\udc52\ud835\udc53\ud835\udc53\ud835\udc53\ud835\udc53= \ud835\udf00\ud835\udf00\ud835\udc5f\ud835\udc5f.(h\ud835\udc60\ud835\udc60+ h\ud835\udc4e\ud835\udc4e\ud835\udc56\ud835\udc56\ud835\udc5f\ud835\udc5f)\ud835\udf00\ud835\udf00\ud835\udc5f\ud835\udc5f. h\ud835\udc4e\ud835\udc4e\ud835\udc56\ud835\udc56\ud835\udc5f\ud835\udc5f+ \ud835\udf00\ud835\udf00\ud835\udc4e\ud835\udc4e\ud835\udc56\ud835\udc56\ud835\udc5f\ud835\udc5f. h\ud835\udc60\ud835\udc60 (5) The feeding and the shorting wall are in line in Figure 1, separated by 4 mm from the edge where is located the shorting wall to the centre of the coaxial probe feed. Table 2. Parameter of PIFA antenna with L-shaped slot Parameters Value L2 16 mm L3 21 mm W 40 mm L 23 mm h ( height of the shorting wall ) 7.5 mm hs( height of the FR substrate-4 ) 1.58 mm hair ( height of the separation of air ) 5.92 mm hpt ( height of the copper ground plane ) 0.6 mm hc ( height of the copper microstrip antenna) 0.035 mm Total height (hpt + h + hc) 8.135 mm grosorv (width of the vertical slot of the L ) 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004992_O201217653783682.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004992_O201217653783682.pdf-Figure1-1.png", + "caption": "Fig. 1. Structure and control principle of proposed BLSRM", + "texts": [ + " Thus, suspending force and torque will be independently controlled by corresponding stator poles. This paper is organized as follows. Section II delineates the configuration of the motor and operating principle of radial force. Section 3 describes the analytical torque and radial force model of the BLSRM. Section 4 includes the mechanical and electromagnetic design such as critical speed, and parameters selection. Section 5 contains the basic sizing of the envelope and internal dimensions. Section 6 shows the validity verification by the experimental results. Fig. 1(a) shows the structures of the proposed BLSRM. In Fig. 1(a), differing from conventional structure, two types of stator poles are included on the stator. One is a torque pole such as A1, A2, B1 and B2, which mainly produce rotational torque. The other is a radial force pole such as Px1, Px2, Px3 and Px4, which mainly generate radial force to suspend rotor and shaft. At the same pole A2 are * School of Instrumentation Science and Opto-electronics Engineering, Beihang University, China. (huijun024@gmail.com) ** School of Instrumentation Science and Opto-electronics Engineering, Beihang University, China .(ljfbuaa@163.com) *** Dept. of Mechatronics Engineering, Kyungsung University, Busan, Korea . (jwahn@ks.ac.kr) Received 29 July 2012 ; Accepted 8 August 2012 connected in series to construct torque winding A, and windings on pole B1 and pole B2 are connected in series to construct torque winding B. windings on poles Px1, Px2, Px3 and Px4 are independently controlled to construct four radial force windings P1, P2, P3 and P4 in x and y directions. Fig. 1(b) shows the control principle of suspending force. From this figure, when the rotor has eccentric displacement in a positive y-direction, only current i2 will be turned on and the other radial force winding Px1, Px2 and Px3 are turned off. Accordingly radial force in negative y-direction is generated. Current i2 can be regulated until the rotor is in balanced position. Using same method, if the rotor has an eccentric displacement in the positive x-direction at the same time, only winding Px3 needs to be turned on and current i3 is regulated to make the rotor return to its zero eccentric position" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003094_f_version_1684942287-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003094_f_version_1684942287-Figure13-1.png", + "caption": "Figure 13. Analyzed distribution of forces on the knife blade considered along the yz plane.", + "texts": [ + " Here, Fc is the cutting force (N), Fc \u2032\u2032 is the horizontal force component by Figure 11 (N), and \u03b2 is the blade rake angle (\u25e6) It follows from the analysis of the parameters in Table 7 that the only significant influence (which is why Table 7 only includes the rake angle \u03b2, and the lines of the surface graph are parallel to the axis of variance of the blade angle \u03b1, which further confirms that the variance of this angle value is not significant) on the value of the Fc \u2032\u2032/Fc ratio is that of the blade rake angle \u03b2 (p < 0.001), where the statistical F-value for this variable is F = 7772.22. The lowest value of the Fc \u2032\u2032/Fc ratio was recorded for the entire range of values of the blade angle \u03b1 and the angle \u03b2 = 5\u25e6. In the next step, the distribution of forces on the knife blade along the yz plane was analyzed, as provided in Figure 13. This led to determining the force ratio Fw/Fc, which serves as an indicator of the efficiency of the cutting process, with the highest possible values thereof being desirable. The force component Fw is explained in greater detail below. In analyzing the array of forces projected on the axis y (see Figure 13), the following dependence (8) can be obtained, indicating that the force Fc is a sum of the working force Fw and the vertical component Ty of the frictional force T: Fc = Fw + Ty (8) where Fc\u2014force measured in the course of the cutting process of triticale straw (N); Fw\u2014working force (N); Ty\u2014vertical component of the frictional force T (N). Meanwhile, the value of the component of the working force can be expressed as follows: Fw = Fs + Fm (9) where Fw\u2014working force (N); Fs\u2014force necessary to only cut (separate) the straw material (N); Fm\u2014force necessary to overcome the resistances of the cut material; in other words, it is the force necessary to overcome the reaction force of the material compressed by the knife blade (N). The formula for the vertical component Ty of the frictional force T can be expressed as follows (see Figure 13): Ty = T \u00b7 cos \u03b1 = \u00b5\u00b7Fn\u00b7 cos \u03b1 = \u00b5\u00b7Fc\u00b7 cos \u00b7(90\u25e6 \u2212 \u03b1) \u00b7 cos \u03b1 (10) where (see Figure 13) T\u2014frictional force (N); Ty\u2014vertical component of the frictional force T (N); Fn\u2014normal force of the frictional force T (N); Fc\u2014force registered during the cutting process of triticale straw (N); \u03b1\u2014knife blade angle (\u25e6); \u00b5\u2014coefficient of friction; according to Richter (1954), \u00b5 = 0.3 [39]. Based on the above dependences, a formula was developed to determine the percentage share of the force Fw in the force Fc: Fc = Fw + Ty, (11) Fc = Fw + \u00b5\u00b7Fc\u00b7 cos \u00b7(90\u25e6 \u2212 \u03b1) \u00b7 cos \u03b1, (12) Fc \u2212 \u00b5\u00b7Fc\u00b7 cos \u00b7(90\u25e6 \u2212 \u03b1) \u00b7 cos \u03b1 = Fw, (13) Fc\u00b7(1\u2212 \u00b5\u00b7 cos \u00b7(90\u25e6 \u2212 \u03b1) \u00b7 cos \u03b1) = Fw, (14) Finally, Fw Fc = (1\u2212 \u00b5\u00b7 cos \u00b7(90\u25e6 \u2212 \u03b1) \u00b7 cos \u03b1)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000931_nf_efm2014_02064.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000931_nf_efm2014_02064.pdf-Figure8-1.png", + "caption": "Figure 8. The real models parts (above) and measured prototype parts (below).", + "texts": [ + " The larger version would not increasing their thermal output and therefore are suitable only for multicircuit systems. Were assembled and determined characteristics of the prototype parts individual in the physical form and in the form of the mathematical models. Subsequently, the manufacturer's engineering data was in the form of contingency tables and macros of VBA_MS_Excel. These created a computational database of all possible versions of the product. Every possible construction variant has therefore in advance clearly the composition of all components and can be easily used to create a CAD model (Figure 8). To calculate the total pressure loss, the user of the database only selects a desired matrix and the length of the exchanger. For each component is numerically or experimentally determined characteristics of the pressure field, depending on the flow rate. The computational database based on the specified input data, using the specific characteristics of each element can calculate the parameters of future devices. \u2022 Principle of the experiment The principle of the experiment (Figure 9,10) was based on the difference in fluid levels in the piezometric tubes to determine the pressure loss" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure3.18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure3.18-1.png", + "caption": "Figure 3.18: Metasurfaces (a) array of metal grids (b) array of metal patches", + "texts": [ + "1, the capacitive surface impedance needs to be added in parallel in the TRM calculation to convert the GDS waveguide to a higher permittivity structure. This can be achieved by a planar array type metasurface. Such metasurface is introduced and studied in [198], which gives a simple and accurate analytical grid impedance formulas based on the approximate Babinet principle for these metasurfaces. The actual topology of the architecture of the metasurface is a planar array of metal strips or patches as shown in figure 3.18. Let us first consider the strip array structure in figure 3.18(a), which is a square grid of metal strips located on a dielectric substrate in the yz-plane. The width of metal strips is defined as w, and the grid period is defined as D which is electrically small. Assuming that w D, then the strip could be seen as a conducting wire and the grid becomes a mesh of crossed metal wires. Considering that the plane of incidence is the xz-plane, when the incident wave has a non-zero y-axis or z-axis electric field component (i.e., parallel to the strips), the response of the grid surface is inductive", + " From this relation and the equations (3-22), (3-25), and (3-26), the grid impedance Zs of the TE-polarized and TM-polarized oblique excitation in the xz-plane can be derived as ZTE s = j \u03b7eff 2 \u03b1 (3-31) ZTM s = j \u03b7eff 2 \u03b1(1\u2212 k20 sin2 \u03b8 2k2eff ) (3-32) We can note that the grid impedance of the TE-polarized excitation is independent of the angle of incidence. However, for the TM-polarized excitation waves, the angle of incidence changes the grid impedance value of the metal strips array metasurface. The obtained impedance have an inductive form. For the complementary structure in figure 3.18(b), an array of square metal patches on a dielectric substrate, the grid impedance Zp can be deduced using the approximate Babinet principle [199]: ZTE s ZTM p = \u03b72eff 4 (3-33) ZTM s ZTE p = \u03b72eff 4 (3-34) where ZTM p and ZTE p are the grid impedance of the complementary structure (array of metal patches) for the TM-polarized and TE-polarized excitation, respectively. As shown in the Babinet principle, if the plane of incidence for the strips array in figure 3.18(a) is the xz-plane, the plane of incidence for the array of patches in figure 3.18(b) will be the xy-plane. However, our structure is assumed as square arrays of strips or patches, changing the plane of incidence will therefore not influence the grid impedance calculation. The grid impedance of the array of patches can then be deduced as ZTE p = \u2212j \u03b7eff 2\u03b1(1\u2212 k20 sin2 \u03b8 2k2eff ) (3-35) ZTM p = \u2212j \u03b7eff 2\u03b1 (3-36) It can be seen that, unlike the array of strips, the grid impedance of patches array is a capacitive one, and it is the TM-polarized mode now that is independent of the angle of incidence", + " This machine is specifically designed for structuring of laminated printed boards, such as our patch array metasurface antenna. In order to obtain clean edges and smooth grooves, all parameters of the laser process have been optimized and precisely adjusted. Figure 3.43 shows a manufacturing sample of the designed leaky-wave antenna. The fabrication accuracy of the sample was measured, which is within 10 \u00b5m. It could be noted that in order to reduce the accuracy error ratio of the production model, a larger patch and gap dimensions (D and w indicated in figure 3.18) of the metasurface may be considered in future works. Several attempts of prototype radiation pattern measurements have been done. Unfortunately, the beams of the leaky radiation were observed with only one prototype (see figure 3.44). Although the beams exhibit a 10\u25e6 shift toward the backward direction compared to the simulation result, the enhanced scanning range capability is very consistent with the simulation (i.e., \u2206\u03b8 = 37.5\u25e6 in the measurement in the operating frequency range of 57 GHz to 64 GHz, and \u2206\u03b8 = 35" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004353_v.org_pdf_2402.18897-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004353_v.org_pdf_2402.18897-Figure8-1.png", + "caption": "Fig. 8. Snapshots of the long-horizon (a) valve rotation task and (b) sphere rotation task carried out in the Drake simulator. Red arrows represent the contact forces. (a) The blue capsule represents the valve and rotates around the vertical axis. The fingers perform side-pushes and step over the valve in succession. (b) External disturbances are applied on the object and ring finger, as the white arrows indicate. The final state of the open-loop baseline is also shown. Object yaw angle and error curves are shown on the right.", + "texts": [ + " Thus, feed-forward controllers often result in larger deviations from planned motions and faster joint velocities once the contact is lost, as seen in the last column of Table I. In contrast, our controller balances tracking planned motions and making contacts, thus generating more stable motions. 2) Complex tasks: We further evaluate the contact controller and the proposed method in more complex cases. These experiments also show potential applications in the real world. The first case is rotating the valve, where nq = 17. In this case, the fingers should switch between pushing aside and stepping over the valve to accomplish the long-horizon manipulation, shown in Fig. 8(a). To our knowledge, such long-horizon manipulation is almost only studied in the machine-learning literature. We find it helpful to interpolate the nominal finger configuration qo,ref between two grasping poses of different fingertip heights. Otherwise, a longer horizon length is needed to avoid local optimums, which degrades control frequency. As shown in Fig. 8(a), the fingers sometimes need to exert forces below the valve, which is sensitive to contact loss. Our proposed contact controller effectively avoids such problems, as shown in the curves and the attached video. The second case is rotating the sphere in place, where nq = 19. The sphere should be aligned with the target orientation in SO(3). With our proposed controller, we exert spatial force disturbances on the object during 2.0 s \u223c 2.5 s and on the ring finger during 10.0 s \u223c 10.5 s. As shown in Fig. 8(b), the long-horizon manipulation fails without the contact controller due to contact loss and unintentional contact. Hence, the importance of our contact controller is proved. We also simulate the Free system in Fig. 4(b) and successfully rotate the sphere for more than 270\u25e6. However, the rolling contacts result in highly dynamic movements of the object, which violates the quasi-dynamic assumption and degrades the performance. We temporarily increase the damping of the object. As suggested by [2], designing special high-level objectives and enforcing the system to be quasi-dynamic at a low level could help to solve this problem" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003283_tation-pdf-url_13336-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003283_tation-pdf-url_13336-Figure7-1.png", + "caption": "Fig. 7. A T-pod with 3 d.o.f. (left) and a T-pod4 with 4 d.o.f.(right)", + "texts": [ + " As a result, a very compact and strong PKM is achieved, and it was possible to meet all of the requirements for the flexile underbody fixturing application. Parallel kinematic machines offer an inherent modularity. It is therefore natural that for any new PKM concept, a variety of derivatives exist. In the given case, we derive the T-pod based on the developed parallelogram module, by aligning two parallelogram planes such that the upper joints form (nearly) a single line, hereby blocking two rotations, and by placing the third parallelogram plane perpendicular, (see Fig. 7). The name was chosen because the joint locations on the movable platform resemble a T-shape. The advantage of this machine is the reduced footprint in one direction, so that it can be place in very narrow spaces, but in particular the possibility to remove the synchronization and add an extra motor to the perpendicular parallelogram, so that an optional tilt motion around the symmetry axis can be introduced leading to the T-pod4 configuration. This can be particular useful when fixturing buckled car body parts" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003276_981-97-1876-4_57.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003276_981-97-1876-4_57.pdf-Figure2-1.png", + "caption": "Fig. 2 LATM structure schematic", + "texts": [ + " The shape of the permanent magnets affects the distribution of the air-gap magnetic density, which affects the amplitude of the cogging torque, in the design of this article, the rotor is of conventional surfacemounted type, but the shape of the permanent magnets is in the shape of a bread-like, which reduces amplitude of cogging torque and thus improves the performance of the motor [17]. Based on the above analysis, the general structure of the motor was determined to be a new structure combining a concentrated winding and a bread-like shape of permanent magnets, as shown in Fig. 2. Subsequently, the motor was further designed based on the design parameters. The specific design parameters are listed in Table 1. The specific design process is as follows: First, based on Eq. (6) [16], select the materials for each component and estimate the size of the motor; Te = 2P\u03bc0\u03bcr Hchm I Ncle f ln(r2/r1) + \u03bcr ln(r3/r2) (6) In the above equation: P is the number of pole pairs, \u03bc0 is the permeability of air, \u03bcr is the permeability of permanent magnet, Hc is the coercivity of permanent magnet, hm is the thickness of permanent magnet, I is the current, Nc is the number of windings, le f is the effective length of the motor, r1 is the inner diameter of the permanent magnet, r2 is the outer diameter of the permanent magnet, r3 is the inner diameter of the stator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003064_citation-pdf-url_775-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003064_citation-pdf-url_775-Figure3-1.png", + "caption": "Fig. 3. The spatial distribution of the screws when the upper parallel to the base", + "texts": [ + " An imaginary link and an imaginary revolute pair, $0, with single-DOF, are added to each branch of the mechanism. Then each branch becomes an imaginary 6-DOF serial chain. In order to keep a kinematic equivalent effect, let the amplitude \u03c90 of the imaginary screw $0 of each branch always be zero; and let each screw system formed by imaginary $0 and the other five screws of the primary branch RPRRR be linearly independent. Considering the imaginary pair $0, the Pl\u00fccker coordinates of all six screws shown in Fig. 3b with respect to local o-X1Y1Z1 coordinate system are { } { } { } \u03b6 = = = 1 2 3 1 0 0 ; 0 0 0 0 0 0 ; 0 \u03c8 0 \u03c8 \u03b6 ; 0 0 0 $ $ $ { } { } { } \u03b6 = \u2212 = \u2212 \u2212 = 4 0 0 5 0 0 1 0 0 ; 0 \u03b6 \u03c8 0 \u03c8 ; 0 0 0 0 1 ; ' 0 0 L L L L $ $ $ (24) where \u03c8 and \u03b6 are directional cosines of the screw axes 2 $ and 3 $ . The screw matrix of each branch with respect to the local coordinate system is { }=\u23a1 \u23a4\u23a3 \u23a6 0 1 2 3 4 5, , , , ,Gg $ $ $ $ $ $ , and we have \u23a1 \u23a4 \u23a1 \u23a4= \u23a1 \u23a4\u23a3 \u23a6\u23a3 \u23a6 \u23a3 \u23a6 0 0 i iG A Gg . For each serial branch, the motion of the end-effector of the 3-RPS mechanism can be represented by the following expression ( )\u23a1 \u23a4= =\u23a3 \u23a6 0 1 ,2 , 3i H iG iV \u03c6 (25) where { }= T H P V \u03c9 v is a six dimension vector; \u03c9 is the angular velocity of the moving platform; vP is the linear velocity of the reference point P in the moving platform; and ( ) ( ) ( ) ( ) ( ) ( ) ( )( )= \u03c6 \u03c6 \u03c6 \u03c6 \u03c6 \u03c6i i i i i i i 0 1 2 3 4 5\u03c6 is a vector of joint rates", + " When the pitch of the principal screw is zero, = 0h \uff0c = 0 /0u \uff1b 00 /w = . Mathematically, u and w both can be any value except one. All other roots of Eq. (34) will not be considered, as they are algebraically redundant. Then, the corresponding three principal screws can be written as { } { } { } = = \u2212 = 1 2 3 0 0 0 ; 0 0 1 0 1 0 ; 0 0 1 0 0 ; 0 0 z z x z z P P $ $ $ (35) Any output motion may be considered as a linear combination of the three principal screws. The full-scale distribution result, Fig.3, of all screws obtained by linear combinations of three principal screws can also be verified by using another method presented in Huang et al., Principal Screws and Full-Scale Feasible Instantaneous Motions of Some 3-DOF Parallel Manipulators 361 (1996), and is identical with the actual mechanism model in our laboratory. The three principal screws belong to the fourth special three-system presented by Hunt (1978). When the upper platform is parallel to the fixed platform, all possible output twists of the upper platform except the translation along the Z direction are rotations corresponding screws with zero pitch. Their axes all lie in the moving platform and in all the directions. Fig. 3 shows the full-scale possible twist screws with zero-pitch. Therefore from this figure you don\u2019t attempt to make the moving platform rotate round any axis not on the plane shown in Fig. 3. That is impossible. 4.2 The upper platform rotates by an angle \u03b1 about line a2a3 When the upper platform continually rotates by an angle \u03b1 about line a2a3\uff0cnamely the mechanism is in the configuration that the lengths of the two input links are the same. Note that, for this kind of mechanisms the platform cannot continually rotate about axes lying in the plane shown in Fig.3 except some three axes including a2a3. In other words, it is very often impossible that the platform can continually rotated about an axis lying in the plane, as shown in Fig.3, (Zhao et al, 1999). The coordinates of point a1 on the upper platform and point A1 on the base have the following values ( ){ }\u03b1 \u03b1= \u2212 +1 03cos 1 /2 0 3 sin /2a r L r { }=1 0 0RA (36) In this configuration, the screw system including the imaginary pair of the first chain corresponding to [ ]0 1 G with respect to the fixed coordinate system is { } { } { } { } { } { } { } { } { } { } { } = = \u00d7 = = = = \u00d7 = = \u00d7 = = \u00d7 \u00d7 \u00d7 \u00d7 \u2032= \u2212 1 1 1 4 4 4 1 5 5 5 4 1 4 4 0 0 0 1 ; 0 0 1 01 1 1 2 2 02 1 1 3 3 03 1 1 1 0 1 1 0 1 1 1 ; ; ; ; / ; ; / ; ; ; ; / L $ S S S A S $ S S 0 L L $ S S L a L L $ S S S a S $ S S L S a L S L S $ (37) where { }= = \u22121 4 0 1 0S S \uff0c = \u22121 11L a A " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001834_g_vol8_928-IT028.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001834_g_vol8_928-IT028.pdf-Figure2-1.png", + "caption": "Fig. 2. Schematic equivalent of DC Motor.", + "texts": [], + "surrounding_texts": [ + "PID is a control method commonly used in terms of basic design and consists of ( pK ) proportional, integral ( iK ) and derivative ( dK ). It is demonstrated as (18) in the time domain. These parameters should be adjusted precisely and exactly to acquire desired performance characteristics of system. Nichols-Ziegler method can be used for adjusting these coefficients [9], [10]. The first values for Kp, Ki and Kd are determined by using Nichols-Ziegler. Then, PID coefficients are tuned the best. If it is not, controllers response is slow, settling time and overflow are increase. In this paper, as more competitive, durability of SMC method will compare to Tuned-PID control which its coefficients are adjusted via the best optimization values and also, analyses will be made in Section 6. dtteK dt tde KteKtu idp )( )( )()( (18) 222 Volume 8, Number 3, June 2016 If simplifications are made in (19) by using (17), (20) is obtained. If descriptions of state for SMC is made as in (21), (22) is obtained. Moreover, equation of sliding surface is acquired as in (23). a tb a a a t LJ KK A J B A L R A LJ K A 4321 ,,, (19) 143232 .. AeAAAAA a (20) )(),(),(),(),( 12121 teutXYtXtXXtX a (21) 1432322 ..)( AeAAAAAtX a (22) rrCeeCXXCs 21 (23) )sgn(0 sKCs rr (24) If (22) is substituted in (24) and parametric data of used motor, which are seen in Section 3, is also substituted in (25), )(tu control signal will produced as in (26). )sgn(. 1 )( 43232 1 sKAAACAA A tu (25) A change in signum function as shown in (27) is done to reduce processing load and relieve chattering. )sgn(88.412567.47 484.325 1 )( 12 sKXXCtu (26) 10,88.412567.47 484.325 1 )( 12 s s KXXCtu (27)" + ] + }, + { + "image_filename": "designv8_17_0002671_13320-015-0292-6.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002671_13320-015-0292-6.pdf-Figure1-1.png", + "caption": "Fig. 1 Structure of 3D CFBG accelerometer.", + "texts": [ + " Consequently, it is very essential to conduct the research on a three-dimensional chirped fiber Bragg grating (3D CFBG) vibration sensor. According to the application requirements, the overall design goals of the sensor are as follows: (1) Integration and seal design (2) Working frequency \u2265 500 Hz (3) Acceleration range \u2265 20 ms2 (4) Ambient temperature range: 20\u2012 \u2103 \u2012 80\u2103 (5) Single dimensional size \u2264100 mm According to this goal, we design a structure of the three-dimensional fiber grating vibration sensor as shown in Fig. 1. The sensor is composed of three unidirectional sensing units that are mutually vertical. Each sensing unit is composed of a base, an elastomer, a mass block, and two CFBGs, and its structure and principle are shown in Fig. 2. Two CFBGs written in the same optic fiber are formed into precise matching by accurate fabrication process, and they are symmetrically fixed between the base and the mass block. In order to avoid dead zone, we give them 2 nm/s pretension. When the sensor receives the vibration signal from the outside world, the mass supported by the elastic membrane will vibrate up and down to drive the CFBGs stretch along the axial direction, and the reflection peaks of CFBG1 and CFBG2 will change, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000892_f_version_1659594999-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000892_f_version_1659594999-Figure16-1.png", + "caption": "Figure 16. Fatigue life results of the optimized drive axle housing: (a) life cloud chart; (b) safety factor cloud chart.", + "texts": [ + "2283 mm. The maximum equivalent stress increased by 24.17 MPa to 229.54 MPa compared with that before optimization. Compared with the initial model, the stress and deformation are increased. This is because there are certain errors in the manual processing of the model, and the material cannot be deleted completely according to the topology optimization results, resulting in a slight increase in the deformation stress of the model. The distribution is the same as that before optimization. (a) (b) Figure 16. Fatigue life results of the optimized drive axle housing: (a) life cloud chart; (b) safety factor cloud chart. Figure 14. Comparison of optimized models: (a) before optimization; (b) after optimization. The s atics analysis of the ized drive axle housing is carried out again, nd the results are shown in Figure 15. Materials 2022, 15, 5268 19 of 28 (a) (b) Figure 14. Comparison of optimized models: (a) before optimization; (b) after optimization. The statics analysis of the optimized drive axle housing is carried out again, and the results are shown in Figure 15", + " it the initial model, the stress and deformation are increased. This is because there are certain errors in the manual processing of the model, and the material cannot be deleted completely according to the topology optimization results, resulting in a slight increase in the deformation stress of the model. The distribution is the same as that before optimization. The f tigue a alysis of he ptimized drive axle housing with maximum vertical fo ce is carried out again u ing the fatigue too in ANSYS, and the results are shown in Figure 16. Materials 2022, 15, 5268 19 of 28 Materials 2022, 15, 5268 19 of 28 (a) (b) Figure 14. Comparison of optimized models: (a) before optimization; (b) after optimization. The statics analysis of the optimized drive axle housing is carried out again, and the results are shown in Figure 15. (a) (b) Figure 15. Cloud chart of static analysis after optimization: (a) total deformation; (b) equivalent stress. After topology optimization, the maximum deformation increases slightly compared to before optimization; the value is 1", + " Compared with the initial model, the stress and deformation are increased. This is because there are certain errors in the manual processing of the model, and the material cannot be deleted completely according to the topology optimization results, resulting in a slight increase in the deformation stress of the model. The distribution is the same as that before optimization. The fatigue analysis of the optimized drive axle housing with maximum vertical force is carried out again using the fatigue tool in ANSYS, and the results are shown in Figure 16. Figure 16. Fatigue life results of the optimized drive axle housing: (a) life cloud chart; (b) safety factor cloud chart. After optimization, the minimum life and minimum safety factor decreased to varying degrees. The minimum life decreased from 10,723 to 7551.5, a reduction of 29.5%. The safety factor decreased from 0.33578 to 0.30043, a reduction of 10.5%. Then, the modal analysis of the optimized drive axle housing is carried out, and the results are shown in Table 4 and Figure 17. Table 4. The first-order to sixth-order natural frequency and description of vibration mode of the optimized drive axle housing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004044_f_etic2017_01092.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004044_f_etic2017_01092.pdf-Figure2-1.png", + "caption": "Fig. 2. The proposed 3D Antenna.", + "texts": [], + "surrounding_texts": [ + "Antenna structure shown in Fig. 1 until Fig. 4 shows the proposed antenna designed. The antenna is mounted in the middle of a rectangular ground plane with the dimension of 21.6mm x 21.6mm. Originally, the size of antenna was determined by \u03bb/4. The width of the antenna was calculated by: c f (1) Where; =wave length, c=speed of light, f= frequency Calculation: = 3 10 2.45 = 0.1224 With the meander line technique implemented with 3D structure, each arm of the antenna L2 is 4.3mm. The antenna size is reduced to . Table 1 shows the antenna size and parameter." + ] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-FigureB.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-FigureB.1-1.png", + "caption": "Figure B.1: A section view of an object s inside wing r and the minimum distance dmin between them", + "texts": [ + " This Appendix was originally a solo term project and report for Professor Quentin Stout\u2019s EECS 587 parallel computing class and has been lightly edited for inclusion in the dissertation. As originally described in Chapter 8, I identified a mathematical formulation for a geo- metric constraint that is deterministic, differentiable, and C0 continuous. I restate the basics here for clarity. We begin with triangulated representations of aircraft outer surface r and an inner object s to pack inside it, as pictured in Figure B.1. r and s are each represented as lists of vertices A, B, C of dimension 3 by m or n (the size of each mesh). When one object encloses another, the minimum distance dmin between them is greater than zero by some margin. Therefore, a first approach to a geometric constraint might involve computing dmin,rs \u2265 0 + tol. We can compute dmin between two triangulated surfaces by computing the minimum distance between each individual pair of triangles. The minimum distance between a pair of triangles can be found by a total of fifteen primitive tests between the vertices: six pointtriangle tests, and nine line-line tests [247]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001143_23_2_pag_55_vela_dg_-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001143_23_2_pag_55_vela_dg_-Figure2-1.png", + "caption": "Fig. 2. The constructive-functional scheme of the prehension device with the workpiece prehensed, after [13].", + "texts": [ + " It presents a series of advantages, as follows: - simple construction; - compact design with low weight; - small size; - reduced kinematic errors; - low electrical power consumption; - usable in the construction of devices for workpieces orientation and fixing. This paper shows the way to determine the actuating force of the SMA element required for prehension of a workpiece, knowing the weight of the workpiece and the dimensions of the prehension device elements. 2. The Constructive-Functional Scheme of the Prehension Device The device variant analyzed involves the replacement of the classic motor (electric, hydraulic, etc.) with an SMA actuator. The constructive-functional scheme of the device is shown in Fig. 1 and Fig. 2, in the variant without workpiece (Fig. 1) and in the variant with the prehensed workpiece (Fig. 2). The SMA actuator is solidarized with the fixed element (0). The shape-memory alloy element (1), a cylindrical helical spring, is axially deformed by expansion or compression through a well-defined operating program, developing the actuating force Fa and Kinetostatics of a Robotic Prehension Device Driven by Shape Memory Alloy Elements Robotica Management, 28-2 / 2023 56 the prehension force F2 of the fingers (6), and (7) respectively. The return to the initial position of the SMA spring and the action of the elastic forces (Fspr) of the springs (4) and (5) causes the return of the actuator's driving elements (2) and (3), of the fingers (6) and (7), releasing the working object (10)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004335_.srce.hr_file_403527-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004335_.srce.hr_file_403527-Figure3-1.png", + "caption": "Figure 3. Eddy current method", + "texts": [], + "surrounding_texts": [ + "Ultrasonic testing of solid materials is used to detect material imperfections and microcracks. It is based on the fact that solids are good conductors of sound waves. Sound waves are reflected within the material from its sides, and at the same time they are reflected from all imperfections in the material. The interaction of the material itself and the sound waves is better the smaller the wavelength of the sound. This also means that higher frequency waves are used. This material testing method is characterized by frequency waves from 0.5 MHz up to 25 MHz. The reason for this is that the interaction of waves is most pronounced if a wave of a certain wavelength comes into contact 186 Pomorski zbornik Posebno izdanje, 181-199 with an imperfection that is similar in magnitude to the wavelength of that sound. The observed laminates in composite vessels are usually a few millimeters thick, so it is necessary to adjust the sound wavelength so that it is in the range of a few millimeters. Equation 1 defines the sound wavelength for a given speed of sound and frequency. The speed of sound in air is approximately 343 m/s, but this value is not applicable in this case. As explained earlier, solid materials are good conductors of sound, which means that the speed of sound in solid materials is much higher than the speed of sound in air, so it is necessary to adjust the value of the speed of sound in the equation for the observed material. In case of carbon laminates that would be 3070 m/s. (1) c = Speed of sound [km/s] f = Frequency [MHz] \u03bb = Wave lenght [mm] The method of ultrasonic testing of materials is mainly based on two different procedures. The first procedure would be based on the measurement of reflected sound waves (pulse-echo) while the second procedure would be based on the measurement of waves that have completely passed to the other side of the material (throughtransmission). In practice, the method of measuring reflected waves is used much more for the reason that the measurement requires access to the material from only one side. The reflected wave method is also used to determine the speed of sound through the observed material. If the thickness of the material and the time required for the transmitted sound wave to return to the piezoelectric element are known, it is very easy to calculate the speed of sound through that material. (2) c = Speed of sound [m/s] d = Thickness of material [m] t = Time [s] Compared to other methods of non-invasive testing of solid materials, the ultrasonic method has its advantages and disadvantages. Advantages: - High sensitivity to imperfections inside the material - No preparation of the observed material is required - The depth to which the wave penetrates is much greater than with other methods - High precision in determining the size and position of imperfections - Minimum equipment required for testing (usually portable equipment) - The test procedure is not harmful to the material or the people conducting the test 187Pomorski zbornik Posebno izdanje, 181-199 Disadvantages: - High sensitivity to surface imperfection and surface curvature of the material - The surface of the material must be accessible for testing - A medium is required between the surface of the material and the piezoelectric probe - Materials that are not homogeneous are difficult to examine - Imperfections in the material that are oriented in the direction of sound are almost impossible to detect - Materials that are very thin (<1mm) are almost impossible to test with this method" + ] + }, + { + "image_filename": "designv8_17_0004003_1145_3197517.3201277-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004003_1145_3197517.3201277-Figure18-1.png", + "caption": "Fig. 18. Angular momentum of a spinning cube around its spinning axis. Unlike [Dinev et al. 2018], ourmethod preserves the global rotationalmotion.", + "texts": [ + " Publication date: August 2018. is always feasible, we plug in x := xn , v := vn , s := 1, t := 1 and see that all of the constraints are indeed satisfied. Instead of using the variable s, t , one could instead toggle the momentum constraints on and off depending on which of these quantities are conserved. However, this toggling strategy needs a complicated mechanism to control, including determining which quantities are conserved in a given simulation. For example, in a spinning cube example as shown in Figure 18, only the angular momentum around the spinning axis is conserved (one scalar). This control mechanism would be more difficult to design in cases with multiple attachment constraints or collisions. Another downside of the toggling strategy is its binary nature \u2013 the conserved quantities are either required to be conserved exactly, or not at all. The latter case, corresponding to turning off some of the momentum constraints, allows the projection to change these quantities arbitrarily which may be dangerous", + " Note that even though it may seem dangerous to be modifying positions especially with stiff materials, where small changes of positions can produce large changes of potential energy, this is not a problem with our method. In such cases, FEPR changes the positions only slightly in order to achieve the desired energy level because it tries to depart from the initial guess as little as possible. Dinev et al. [2018] proposed a method to correct the implicit midpoint result by blending it with a step of backward or forward Euler. This helps, but visible damping from backward Euler can creep in. We demonstrate this on a spinning cube example in Figure 18. In this example, we can see that when implicit midpoint overshoots the total energy, explosion is prevented by blending with backward Euler, which removes the excessive energy due to its numerical damping properties. Unfortunately, as a side effect, the blending ACM Transactions on Graphics, Vol. 37, No. 4, Article 79. Publication date: August 2018. of backward Euler also reduces the angular momentum and slows down the global motion. Our method is an add-on on top of any integrator and avoids this problem by exactly projecting energy while also carefully taking into account both linear and angular momentum" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002313_f_version_1692366120-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002313_f_version_1692366120-Figure2-1.png", + "caption": "Figure 2. Multirotor in six-arm configuration.", + "texts": [ + ", the systems used on the hexacopter, and the water-based part, installed on the landing deck of the ferry. The diagram highlights the relationships and connections between the subsystems, while detailed specifications are provided in the subsequent sections. The platform carrying the proposed system was an unmanned aerial vehicle of the multirotor helicopter type. After analyzing the aspects of reliability and lifting capacity in the design phase, it was decided to use a hexarotor configuration. This offered a good combination of drive redundancy and compact dimensions. The hexarotor is shown in Figure 2. In Figure 2, the frame of the multicopter (Figure 2A); one of the six arms (Figure 2B); the drive unit consisting of a propeller, a BLDC motor, and an electronic speed controller (Figure 2C); the converter power supply system (Figure 2D); the landing gear (Figure 2E); and the control system comprising an autopilot with a GNSS receiver (Figure 2F) are presented. This unmanned aerial vehicle was characterized by the fact that it was powered by wire from the ship\u2019s deck. Electricity was transmitted via a special cable from a ground source to dedicated electricity converters onboard the UAV. In addition, the hexarotor had a battery buffer in the event of damage to the tether, so that it was able to perform a quick but controlled landing. The weight of the helicopter, depending on the optoelectronic equipment and the length of the power cable, oscillated between 10" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure1-1.png", + "caption": "Figure 1. Development background, assembled model, and main components of AWM-750D.", + "texts": [ + " It contains blades of diameter 0.75 m and rated power of 100 W at 12.5 m/s of wind speed. The turbine blades are spiral-shaped, which is unique compared with those of conventional wind turbines and is registered as a patent, WO 2014/073741 A1 [23]. The power generating part of wind turbines is composed of three blades rotating around a shaft. We manufactured the blade via injection molding instead of rolling and stretching it in an axial direction due to the advantages of structural robustness, quality, and productivity. Figure 1 depicts the development background and major components of the system. We placed a generator upstream of the rotating part and a brake downstream to attain dynamic stability. Moreover, it can direct automatically toward the upcoming wind by drag, which is advantageous for drag-type wind turbines. The household small wind turbine system is aimed for installation and operation in urban environments, and it is crucial to enhance the operability for competitiveness in the market. The authors [24] analyzed that small wind turbines operating in the city possessed low operability due to uneven and low-speed wind and various buildings and obstacles" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure6-3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure6-3-1.png", + "caption": "Figure 6-3. Repr\u00e9sentation du dip\u00f4le dans le rep\u00e8re initial", + "texts": [ + " Diagramme du principe de base du calcul du gain de diversit\u00e9 r\u00e9f\u00e9renc\u00e9 ............. 163 Figure 5-16. Diagramme synth\u00e9tisant la m\u00e9thodologie d'\u00e9valuation de la diversit\u00e9 .................. 167 Figure 5-17. Diagramme synth\u00e9tisant le choix d'un syst\u00e8me multi-antennes............................. 168 xix Figure 6-1. Compteur d'eau sous les diff\u00e9rentes orientations consid\u00e9r\u00e9es ................................. 175 Figure 6-2. Distribution normalis\u00e9e du champ incident pour les composantes \u03b8 et \u03c6 ............. 177 Figure 6-3. Repr\u00e9sentation du dip\u00f4le dans le rep\u00e8re initial ........................................................ 178 Figure 6-4. Repr\u00e9sentation des syst\u00e8mes d'antennes \u00e9valu\u00e9s ..................................................... 179 Figure 6-5. Orientation du t\u00e9l\u00e9phone mobile Unik avant rotation.............................................. 182 Figure 6-6. Repr\u00e9sentation des diff\u00e9rentes orientations pouvant \u00eatre prises par le t\u00e9l\u00e9phone mobile Unik .....................................................", + " Ici nous n'allons donc consid\u00e9rer que le syst\u00e8me d'antennes en espace libre. 178 6.1.3 Syst\u00e8mes d'antennes Comme expliqu\u00e9 dans le chapitre pr\u00e9c\u00e9dent, notre m\u00e9thodologie th\u00e9orique n\u00e9cessite une antenne de r\u00e9f\u00e9rence. Dans ce cas, nous avons choisi d'utiliser une antenne dip\u00f4le comme antenne de r\u00e9f\u00e9rence. Chaque brin du dip\u00f4le mesure 25 mm avec un diam\u00e8tre de 2 mm. L'efficacit\u00e9 totale de cette antenne est de 0,98 \u00e0 la fr\u00e9quence de 2,45 GHz. Dans le rep\u00e8re initial, l'axe du dip\u00f4le est confondu avec l'axe Oy comme repr\u00e9sent\u00e9 sur la Figure 6-3. Dans notre cas nous allons comparer deux syst\u00e8mes que nous avons con\u00e7us pour \u00eatre utilis\u00e9s dans des objets communicants. Le premier syst\u00e8me \u00e9valu\u00e9 est le syst\u00e8me \u00e0 deux patchs \u00e0 double polarisation de dimension 100x43 mm pr\u00e9sent\u00e9 dans le chapitre 3. Ce syst\u00e8me pr\u00e9sentant quatre ports RF, il y a plusieurs combinaisons de ports possibles pour mettre en \u0153uvre diff\u00e9rentes diversit\u00e9s. Ici, nous ne consid\u00e9rerons que la diversit\u00e9 spatiale mise en \u0153uvre par les deux ports pr\u00e9sentant une polarisation lin\u00e9aire verticale", + " Pour l'environnement urbain, le XPR est de 7,3 dB et l'\u00e9talement angulaire est beaucoup plus important que pour le milieu indoor puisque nous avons comme param\u00e8tre de distribution en \u00e9l\u00e9vation 2, 2Vm = \u00b0 , 3,9V\u03c3 \u2212 = \u00b0et 17,8V\u03c3 + = \u00b0 pour la composante du champ incident selon \u03b8 et 2Hm = \u00b0 , 4,6H\u03c3 \u2212 = \u00b0 et 37, 4H\u03c3 + = \u00b0 pour la composante du champ incident selon\u03c6 . La Figure 6-7 repr\u00e9sente en 3D la distribution des deux composantes du champ incident de l'environnement urbain. 6.2.3 Syst\u00e8mes d'antennes Comme dans l'exemple pr\u00e9c\u00e9dent, nous avons choisi d'utiliser une antenne dip\u00f4le comme antenne de r\u00e9f\u00e9rence. Les brins ont un diam\u00e8tre de 2 mm et l'efficacit\u00e9 totale est proche de 0.98. Avant rotation, c'est-\u00e0-dire lorsque le t\u00e9l\u00e9phone est orient\u00e9 comme sur la Figure 6-5, l'axe du dip\u00f4le est confondu avec l'axe Oy comme repr\u00e9sent\u00e9 sur la Figure 6-3. 186 Nous allons utiliser les deux m\u00eames syst\u00e8mes d'antennes que dans le premier exemple, c'est-\u00e0-dire le syst\u00e8me \u00e0 deux patchs \u00e0 double polarisation et l'antenne PIFA agile en polarisation. Contrairement \u00e0 l'exemple pr\u00e9c\u00e9dent, nous allons traiter toutes les diversit\u00e9s qu'il est possible de mettre en \u0153uvre avec le syst\u00e8me \u00e0 deux patchs \u00e0 double polarisation. En effet comme ce syst\u00e8me a quatre voies, il est possible de mettre \u0153uvre de la diversit\u00e9 spatiale avec les voies polaris\u00e9es verticalement, de la diversit\u00e9 spatiale avec les voies polaris\u00e9es horizontalement, de la diversit\u00e9 spatiale avec les deux voies d'un m\u00eame patch et de la diversit\u00e9 de polarisation et d'espace en prenant une voie sur chaque antenne pr\u00e9sentant des polarisations diff\u00e9rentes", + "3 Syst\u00e8mes d'antennes Dans cet exemple, nous avons choisi d'utiliser une antenne dip\u00f4le comme antenne de r\u00e9f\u00e9rence. Un dip\u00f4le compos\u00e9 de deux brins cylindriques (dont le diam\u00e8tre est tr\u00e8s inf\u00e9rieur \u00e0 la longueur) n'est pas une antenne large bande. Nous avons donc d\u00e9fini dix dip\u00f4les dont la fr\u00e9quence de r\u00e9sonnance correspond \u00e0 chacune des 10 fr\u00e9quences \u00e9tudi\u00e9es. Les brins ont un diam\u00e8tre de 2 mm et l'efficacit\u00e9 totale est proche de 0.98 pour tous les dip\u00f4les simul\u00e9s (Tableau 6-8). Lorsque les dip\u00f4les sont dans l'orientation 1, leur axe est confondu avec l'axe Ox comme repr\u00e9sent\u00e9 sur la Figure 6-3. Num\u00e9ro de bande 1 2 3 4 5 6 7 8 9 10 Fr\u00e9quence centrale en GHz 3.495 3.994 4.493 6.490 6.989 7.488 7.987 8.486 8.986 9.484 Longueur des brins du dip\u00f4le en mm 17.25 14.75 12.75 8 7.25 6.5 6 5.5 5 4.5 Tableau 6-8. Longueur des brins des dip\u00f4les utilis\u00e9s pour chaque fr\u00e9quence \u00e9tudi\u00e9e Pour illustrer cet exemple montrant l'int\u00e9r\u00eat de notre m\u00e9thodologie dans le cas de syst\u00e8mes UWB \u00e0 diversit\u00e9 d'antennes, nous avons r\u00e9alis\u00e9 deux syst\u00e8mes UWB diff\u00e9rents \u00e0 deux antennes planaires. Le premier syst\u00e8me reprend un design d'une antenne UWB miniature du laboratoire LCIS [6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003046_icle_2682_context_td-Figure3.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003046_icle_2682_context_td-Figure3.9-1.png", + "caption": "Figure 3.9 Representative EIS 3-D Nyquist and Bode impedance plots as a function of time with fitted data obtained by modeling via the equivalent circuit for P675-HTT (a,b), P675-LTT (c,d), and P675-CN (e,f) highlighting the difference in impedance behavior for each of the steels and overall good quality of the fit.", + "texts": [ + " This zoomed in micrograph illustrates how carbides are affected in each of the steels and how corrosion affects the surrounding matrix. ................................................. 84 Figure 3.8 (a) Modified Randles circuit model used to fit the EIS data. Table of averaged values of fitting parameters obtained by fitting the equivalent xviii circuit to 25 individual EIS scans/cycles, obtained over a period of ~54 hours of testing. ......................................................................................... 85 Figure 3.9 Representative EIS 3-D Nyquist and Bode impedance plots as a function of time with fitted data obtained by modeling via the equivalent circuit for P675-HTT (a,b), P675-LTT (c,d), and P675-CN (e,f) highlighting the difference in impedance behavior for each of the steels and overall good quality of the fit. ........................................................................................ 86 Figure 3.10 Averaged fitting parameters for P675-HTT, P675-LTT, and P675-CN as a function of time cycles (scans) for Q1(a) and Q3 (b) using the modified Randles equivalent circuit", + " Modeling of the EIS scan data was performed by fitting the Nyquist impedance graphs to a predetermined equivalent circuit (Figure 3.8) using the fitting software provided by the potentiostat manufacturer. Fitting parameters were obtained to provide values for all elements in the equivalent circuit. Values for each of the circuit elements averaged over the entire test duration are shown in Figure 3.8; values displayed represent a minimum of 5 replicate tests, each containing 25 EIS scans/cycle. Figure 3.9 shows 3-dimensional Nyquist and Bode plots as a function of time coupled with the model fit to highlight the effectiveness of the model and showcase the differences amongst the behaviors of the steels. Figure 3.10a shows Q1 averaged values of each scan or cycle for each of the three steels. P675-HTT has a much larger Q1 value than the other two steels and increased as a function of time, while the other two steels show lower values that initially increase and 66 then stay constant for the remainder of the test" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000529_nload_file_fid_33183-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000529_nload_file_fid_33183-Figure1-1.png", + "caption": "Figure 1. Geometry of the model adopted in the paper", + "texts": [ + " An orthotropic material is characterized by the fact that its elastic mechanical properties have two symmetrical plans, thus only four independent elastic constants specifically E1, E2, G12, \u03bd12 are considered. The coefficient \u03bd12 can be determined using the equation: \ud835\udc38\ud835\udc381 \ud835\udc38\ud835\udc382 = \ud835\udf08\ud835\udf0812 \ud835\udf08\ud835\udf0821 ; (1) Using the hypotheses of Love-Kirchoff which neglect the effect of the shear forces and the rotational inertia, and introducing the parameters: \ud835\udc37\ud835\udc371 = \ud835\udc38\ud835\udc381\u210e3 12\ud835\udf07\ud835\udf07 ,\ud835\udc37\ud835\udc372 = \ud835\udc38\ud835\udc382\u210e3 12\ud835\udf07\ud835\udf07 ,\ud835\udc37\ud835\udc3712 = \ud835\udc3a\ud835\udc3a12\u210e3 12 \ud835\udf07\ud835\udf07 = 1 \u2212 \ud835\udf08\ud835\udf0812\ud835\udf08\ud835\udf0821, 2\ud835\udc3b\ud835\udc3b = \ud835\udf08\ud835\udf0821\ud835\udc37\ud835\udc371 + \ud835\udf08\ud835\udf0812\ud835\udc37\ud835\udc372 + 4\ud835\udc37\ud835\udc3712 (2) with reference to figure 1 [16], the equation of the motion follows: \ud835\udc37\ud835\udc371 \ud835\udf15\ud835\udf154\ud835\udc64\ud835\udc64 \ud835\udf15\ud835\udf15\ud835\udc65\ud835\udc654 (\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66, \ud835\udc61\ud835\udc61) + \ud835\udc37\ud835\udc371 \ud835\udf15\ud835\udf154\ud835\udc64\ud835\udc64 \ud835\udf15\ud835\udf15\ud835\udc66\ud835\udc664 (\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66, \ud835\udc61\ud835\udc61) + 2\ud835\udc3b\ud835\udc3b \ud835\udf15\ud835\udf154\ud835\udc64\ud835\udc64 \ud835\udf15\ud835\udf152\ud835\udf15\ud835\udf152 (\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66, \ud835\udc61\ud835\udc61) + \ud835\udf0c\ud835\udf0c\u210e \ud835\udf15\ud835\udf152\ud835\udc64\ud835\udc64 \ud835\udf15\ud835\udf15\ud835\udc61\ud835\udc612 (\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66, \ud835\udc61\ud835\udc61) = 0; (3) Considering a solution with general form: \ud835\udc64\ud835\udc64 = \ud835\udc4a\ud835\udc4a(\ud835\udc65\ud835\udc65, \ud835\udc66\ud835\udc66)(\ud835\udc34\ud835\udc34. cos(\ud835\udf14\ud835\udf14\ud835\udc61\ud835\udc61) + \ud835\udc35\ud835\udc35. sin(\ud835\udf14\ud835\udf14\ud835\udc61\ud835\udc61)); (4) And from former equations, it is possible to obtain an expression of two variables only: \ud835\udc37\ud835\udc371 \ud835\udf15\ud835\udf154\ud835\udc4a\ud835\udc4a \ud835\udf15\ud835\udf15\ud835\udc65\ud835\udc654 (\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66) + \ud835\udc37\ud835\udc371 \ud835\udf15\ud835\udf154\ud835\udc4a\ud835\udc4a \ud835\udf15\ud835\udf15\ud835\udc66\ud835\udc664 (\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66) + 2\ud835\udc3b\ud835\udc3b \ud835\udf15\ud835\udf154\ud835\udc4a\ud835\udc4a \ud835\udf15\ud835\udf15\ud835\udc65\ud835\udc652\ud835\udf15\ud835\udf15\ud835\udc66\ud835\udc662 (\ud835\udc65\ud835\udc65,\ud835\udc66\ud835\udc66) + \u039b4\ud835\udc4a\ud835\udc4a = 0; (5) with: \u039b2 = \ud835\udf14\ud835\udf14\ufffd\ud835\udf0c\ud835\udf0c\u210e ; (6) Equation (5) must be solved to satisfy the following limit conditions: M = 0, R = 0 for free side (F) M = 0; W = 0 for simply supported side (S) W = 0; \ud835\udf15\ud835\udf15\ud835\udc4a\ud835\udc4a \ud835\udf15\ud835\udf15\ud835\udc65\ud835\udc65\u2044 (\ud835\udc5c\ud835\udc5c\ud835\udc5c\ud835\udc5c \ud835\udf15\ud835\udf15\ud835\udc4a\ud835\udc4a \ud835\udf15\ud835\udf15\ud835\udc66\ud835\udc66\u2044 ) = 0 for clamped side (C) The response according to finite element analysis is based on some models of rectangular meshing with (20X20), (40X40), (80X80) and (120X120)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure12-1.png", + "caption": "Figure 12 : Anneaux concentriques fendus [11].", + "texts": [ + " Les deux premiers designs ne permettent qu\u2019une polarisation lin\u00e9aire, tandis que le dernier, utilisant la cellule Phoenix, peut r\u00e9aliser aussi bien une double polarisation lin\u00e9aire que circulaire. Le recours \u00e0 deux \u00e9l\u00e9ments fonctionnant chacun dans une bande de fr\u00e9quence distincte, mais partageant la m\u00eame maille, sur une unique couche rayonnante, n\u2019est pas fr\u00e9quent. En voici quelques exemples utilisant uniquement une excitation quasi-optique : 1) R\u00e9seaux r\u00e9flecteurs utilisant deux \u00e9l\u00e9ments monobandes [10, 11] (Figure 12 et Figure 11) Pour chacun de ces deux designs, le motif central fonctionne dans une bande de fr\u00e9quence, et le motif ext\u00e9rieur dans une autre. Ces deux antennes fonctionnent dans deux bandes de fr\u00e9quences proches entre les bandes K et Ka (ratio 1,5:1). Comme pour la plupart des r\u00e9seaux r\u00e9flecteurs, ces bandes de fr\u00e9quences sont tr\u00e8s faibles (< 1%). L\u2019antenne avec la croix de Malte modifi\u00e9e [10] permet de r\u00e9aliser une double polarisation circulaire tandis que l\u2019autre antenne [11], seulement une simple polarisation circulaire" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-29-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-29-1.png", + "caption": "Figure 2-29.Structure de Von Koch appliqu\u00e9e \u00e0 une antenne patch", + "texts": [ + " La Figure 2-27 pr\u00e9sente une structure de Von Kock appliqu\u00e9e \u00e0 un dip\u00f4le \u00e0 l'ordre un et \u00e0 l'ordre deux [2.13]. La structure pr\u00e9sente la propri\u00e9t\u00e9 suivante: \u00e0 mesure que l'on augmente le nombre d'it\u00e9rations (donc la longueur du dipole \u00e0 hauteur constante), la fr\u00e9quence de r\u00e9sonnance diminue. Ce qui revient \u00e0 diminuer la hauteur du dip\u00f4le pour travailler \u00e0 fr\u00e9quence constante. 60 Les structures fractales peuvent \u00e9galement \u00eatre appliqu\u00e9es \u00e0 des structures imprim\u00e9es ou planaires comme le montre l'antenne Figure 2-28 qui pr\u00e9sente un dip\u00f4le utilisant deux tapis de Sierpinski et la Figure 2-29 qui pr\u00e9sente un patch fractal. Les structures fractales permettent de r\u00e9duire la taille des antennes entre 20% et 40% mais elles sont aussi int\u00e9ressantes dans le cas d'applications multi-bandes. 2.5.2 Les mat\u00e9riaux \u00e0 forte permittivit\u00e9 La modification du design d'une antenne n'est pas la seule technique permettant une miniaturisation des antennes. L'utilisation de mat\u00e9riaux \u00e0 haute permittivit\u00e9 est \u00e9galement largement utilis\u00e9e. Ces substrats pr\u00e9sentant une permittivit\u00e9 largement sup\u00e9rieure \u00e0 10 permettent de r\u00e9duire les dimensions d'une antenne sans en modifier la g\u00e9om\u00e9trie" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001011_cle_download_656_630-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001011_cle_download_656_630-Figure1-1.png", + "caption": "Fig. 1: Schematic diagram of a lateromedial radiograph of the digit indicating sites of placement of the linear variable distance transducer (black arrow) and dorsal point of frog plate (open white arrow). P1 = first phalanx; P2 = second phalanx; P3 = third phalanx; DS = distal sesamoid bone.", + "texts": [ + " True lateromedial and dorsal 45\u00b0 proximal-palmarodistal oblique radiographs of the distal interphalangeal joint and P3 were taken40. The length of the solar and dorsal surfaces of P3 were measured and corrected for magnification. A point 4/5ths of the dorsal length of P3 distal to the distal interphalangeal joint was calculated and marked with a notch in the dorsal hoof wall, using thumb tacks as markers. The notch indicated the site for the insertion of the LVDT (200 AG linear variable distance transducer, D P Electronics, South Africa) probe (Fig. 1). Thirty-seven percent of the solar length of P3 palmar to the dorsalmost point of P3 was determined. This point identified the site of placement of the dorsalmost point of frog pressure as described by Platt quoted by Butler4 (Fig. 1). REFP shoes were nailed to both front hooves of all horses. The shoe is a mild (low carbon) steel horseshoe that is fitted in reverse to the hoof (Fig. 2). A mild steel (low carbon) \u2018carrying tab\u2019 (20 \u00d7 8 mm flat bar) welded to the inner curvature of the toe of the shoe had two 8 mm holes drilled into the tab approximately 2 cm apart which were tapped to accommodate Allen screws. A 1\u2013mm thick frog-shaped mild steel \u2018frog plate\u2019 was made, with 2 depressions partially drilled through the carrying tab surface corresponding to the holes in the carrying tab" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003925_f_version_1684286543-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003925_f_version_1684286543-Figure1-1.png", + "caption": "Figure 1. Structure diagram of pepper harvester. 1. Picking device, 2. driving console, 3. primary lift, 4. cleaning separation device, 5. engine, 6. secondary lift, 7. grain bin.", + "texts": [ + " The measurements were combined with the data from theoretical analysis to determine the effects of the engine and working parts speed and field pavement excitation on the vibration of the harvester, which can provide reference data and practical value for the vibration reduction optimization of pepper harvesters. Through vibration reduction optimization, the development of tracked pepper harvesters towards energy conservation and comfort can be further promoted. The 4JZ-1700 crawler pepper harvester is shown in Figure 1. When working in the field, the picking device drives the spring finger of the roller to pull the peppers down along with the stem, branches and leaves, and then sends them to the cleaning separation device through the primary lift. The driving shaft of the cleaning separation device drives the star-shaped wheel to work through the sprocket. The spacing of the star-shaped wheel is determined according to the stalk length of peppers. Therefore, the cleaning separation device can leak peppers into the secondary lift" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure6.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure6.1-1.png", + "caption": "Figure 6.1: Example of a battery thermal management arrangement (from Tesla patent [199])", + "texts": [ + " The purpose of this section is to describe new battery and electric machine heat sink models developed based on current best practices. 109 Arguably the state of the art in thermal management of large batteries is the Tesla Model 3. The Model 3 battery pack consists of hundreds of 21mm by 70mm lithium ion cells arranged in a rectangular array. The pack is manufactured by thermally and mechanically bonding two rows of cells to each ribbon (one row of cells on either side of the ribbon), forming a \u201cbandolier\u201d assembly [197]. The general arrangement is shown in Figure 6.1 The bandoliers are then stacked in rows to form the pack. Coolant is fed to each ribbon in parallel from an upstream manifold, an arrangement which has been estimated to double the heat rejection capability of the Model 3 compared to the earlier Model S [198]. I developed a battery-specific heat sink model based on Tesla\u2019s design. The goal of the model is to predict the time-varying cell temperature, T cell(t), given battery pack sizing parameters and coolant flow properties. First, the temperature drop from the cell volume to the cell surface must 110 be computed; then the convective heat transfer to the coolant must be obtained" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002810_ticle_download_30_26-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002810_ticle_download_30_26-Figure2-1.png", + "caption": "Fig. 2 Blades mounted on bike", + "texts": [], + "surrounding_texts": [ + "\u2022 No Gas Required, \u2022 Savings, \u2022 No Emissions, \u2022 Popularity, \u2022 Safe to Drive, \u2022 Cost Effective, \u2022 Low Maintenance, \u2022 Reduced Noise Pollution" + ] + }, + { + "image_filename": "designv8_17_0003838_4_9_54_M2013174__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003838_4_9_54_M2013174__pdf-Figure8-1.png", + "caption": "Fig. 8 Schematic explanation for a decrease in the latent heat of \u00a1/\u00a3 phase transformation under a magnetic field.", + "texts": [ + " The latent heat accompanying the \u00a1/\u00a3 phase transformation corresponds to the difference between the enthalpy in the \u00a1 phase and that in the \u00a3 phase at the phase transformation temperature. The temperature dependence of these enthalpies is larger for the \u00a1 phase than for the \u00a3 phase in pure iron.36) Because the \u00a1/\u00a3 phase transformation temperature increases under a magnetic field, the enthalpy difference between the \u00a1 and \u00a3 phases at the transformation temperature, that is, the latent heat for this transformation, under a magnetic field may decrease as schematically shown in Fig. 8, if the enthalpies themselves of those phases in iron are assumed to vary insignificantly with an applied magnetic field. This is a possible explanation for the decrease in the latent heat and entropy of the \u00a1/\u00a3 phase transformation under a magnetic field. The effect of a magnetic field on the latent heat and transformation entropy in pure Fe and FeCo binary alloys were studied using a specially designed DSC system, making it possible to measure DSC curves in a magnetic field. The main results obtained are as follows: (1) The \u00a1/\u00a3 transformation temperature in Fe and the Fe Co alloys increased with increasing magnetic field strength" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004590_O201319947248395.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004590_O201319947248395.pdf-Figure6-1.png", + "caption": "Fig. 6. Cloak problem with mesh schematics: (a) physical and (b) virtual domains. PEC=perfect electric conductor.", + "texts": [ + " Note that we must choose a non-uniform mesh in the virtual domain, so that we can simultaneously satisfy condition (iii), as well as the constraint on the number of cells in the radial direction in the two domains, namely that they be equal. Though we have some flexibility in terms of the variation of the cell size in the radial direction in the virtual domain, we choose this variation in \u0394r to be smooth, and monotonically increasing in terms of the cell size as we go from r=a to r=c\u2019, so that the summation of all the \u0394r\u2019s equal (c\u2019\u2212 a). An example of such a mesh is shown in Fig. 6. Having defined the meshes in the two domains, we finally turn to the task of determining the material parameters of the cloak in the physical domain. Since we wish to impose the criterion that the two sets of fields, namely (E1, H1) and (E2, H2) in the two domains, respec- tively, be identical. Eq. (2) tells us that the (\u03b51, \u03bc1) values in the physical domain, must be \u03b50/\u03b3n and \u03bc0/\u03b3n where \u03b3n is the ratio of the areas of the nth cell in the physical and virtual domains, respectively. It is evident that, under these conditions, the \u03b51 and \u03bc1 must start out at \u03b50/\u03b31 and \u03bc0/\u03b31, where \u03b31 the ratio of the dimensions of the first cell (at r=b) in the physical domain to that of the dimension of its counterpart (at r=a) in the virtual domain", + " Our objective here is to restore the field behaviour so that it is close to that of the original object that we had prior to the introduction of the perturbation. We now outline the procedure for the blanket design for the new object, shown on the left in Fig. 15, i.e., Fig. 15(1), which is in the physical domain, and is a modified version of the one shown in the right side of the same figure; i.e., Fig. 15(2), which corresponds to the virtual domain. Note that unlike the cylinder example we discussed earlier, the medium in the virtual domain, surrounding the object, is no longer free-space, as was the case shown in Fig. 6. Note also that the dimensions of the objects in the two domains are comparable, and are totally different from the legacy TO-design case, in which the scale factor between the dimensions of the object in the physical and virtual domains tends to infinity to render the target invisible. To find the parameters of the cloak for the modified geometry in Fig. 15, we revisit the integral forms of Maxwell\u2019s Equations, presented earlier in Eq. (2), to relate the material parameters associated with the two systems shown in the figure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure7-1.png", + "caption": "Fig. 7. Diagram of the structure mounting and loading", + "texts": [ + " The presented composite frame with sandwich-type walls was analysed using ANSYS Workbench 2020 R2. First-degree solid and shell elements were used in the analysis (Fig. 6). The data on the materials used in the analysis of the frame come from the ANSYS Workbench library. Test samples were made simultaneously with the frame, in order to determine the actual material parameters such as density or equivalent Young\u2019s modulus. The tests conducted, which will be described in the next article, will be used for validating the model. The following frame loads were assumed for analysis (Fig. 7): \u2022 point A \u2014 support, \u2022 point B \u2014 support, \u2022 point C \u2014 manipulator 200N (due to the lim- ited budget of the project and difficult to predict dynamic loads, a doubled force value was assumed), \u2022 point D \u2014 battery 75N, \u2022 point E \u2014 computer and electronics 5N, \u2022 point F \u2014 laboratory 29N. The analysis was performed for several variants of the grid in order to verify the convergence of the results. The similarity of the obtained results confirms the appropriate densification of the grid (Table 2). The analysis was carried out iteratively, starting from the base load value up to the dangerous load value (Table 3)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001771_s-3217716_latest.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001771_s-3217716_latest.pdf-Figure7-1.png", + "caption": "Figure 7 shows the performance distribution cloud map of the dual-elastic groove metal valve seat under the initial structural parameter. From Figure 7 (a), it can be seen that the inner corner of the valve seat Z -shaped groove is the most stressed, and the use stress of the valve seat material is 138MPa, which does not meet the strength requirements. Analysis of The main factor that affects the stress of the valve seat is the inner round of the Z -shaped groove. The corner size and the size of the contact area with the soft sealing ring, this size can be used as a design variable that optimizes the later multi-target optimization. From Figure 7 (b), it can be seen that the exterior part of the valve seat is deformed to the largest part of the valve body, and this size can also be used as a design variable optimized in the later period. From Figure 7 (C), it can be seen that the minimum fatigue life of valve seats is 36,214 cycles greater than the generally low -temperature valve seat design life. There is great room for optimization. The mass can be measured by ANSYS Workbench software for 12.36kg.", + "texts": [], + "surrounding_texts": [ + "Seat" + ] + }, + { + "image_filename": "designv8_17_0000056_tation-pdf-url_54247-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000056_tation-pdf-url_54247-Figure6-1.png", + "caption": "Figure 6. A step-descending strategy for a five-wheeled wheelchair.", + "texts": [ + " After the completion of the static wheelie, large wheels are locked by the braking mechanism of the wheelchair. By coordinated motions of the drive wheel and the linear actuator (Figure 5(g)), the drive wheel climbs up the wall of a step and reaches to the top. Thus, a series of stepclimbing sequence is completed (Figure 5(h)). We then explain the step-descending strategy in which a user approaches a step from the front side of the wheelchair. To avoid a risk of falling from the top of a step to the ground, we apply the static wheelie motion in the step-descending process as well. Figure 6 shows the Physical Disabilities - Therapeutic Implications32 moves to the edge of the step (Figure 6(b)). After applying gentle brake to the large wheels of a wheelchair for reducing an impact of landing on the ground, the wheelchair starts to descend a step by maintaining the static wheelie situation (Figure 6(c)). The breaks are unlocked after the large wheel lands on the ground, the front casters can then be landed on the ground using the linear actuator motion (Figure 6(d)). The drive wheel lands on the ground after the forward movement of the wheelchair (Figure 6(e)). Thus, the step-descending motion of the wheelchair is completed. In this section, we derive a geometry model of the proposed link mechanism. Figure 7 shows a schematic side view of the reconfigurable link mechanism with a manual wheelchair. We define a coordinate system of the wheelchair \u03a3-X w Z w , where the origin of the coordinate is at the point of contact between the large wheel and the ground as shown in Figure 7. The linear actuator on the link mechanism is attached at the back of the wheelchair frame at an angle \u03b1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004245_SIJINT-2015-088__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004245_SIJINT-2015-088__pdf-Figure3-1.png", + "caption": "Fig. 3. Curvature of the bar at the multiple stands.", + "texts": [ + " From the definition of tangential angle dy/ dx, Eq. (15) is natural because dx2 increases to \u03bbdx1 while dy2 is remains the same. To summarize, the previous model of curvature after rolling is based on two important assumptions. However, one of these assumptions is not true (Eq. (1)) because 1/\u03c11 is not related to \u03c9. Also, the basis of the effect 1/\u03c11 on 1/\u03c12 (Eq. (15)) is valid only when no elongation difference occurs at the delivery-side. The inconsistency of Eq. (1) can be represented when a series of rolling stands are assumed (Fig. 3); 1/\u03c12 is the delivery-side curvature at the first rolling stand (Fig. 3(a)), and also the entry-side curvature at the second rolling stand (Fig. 3(b)). 1/\u03c12 can be represented using both 1/\u03c11 and \u0394v2 because it is delivery-side curvature at the first rolling stand (Fig. 3(b)), whereas it is also the entry-side curvature at the second rolling pass, and represented as only \u0394v2 at the third rolling stand (Fig. 3(a)). Although these two curvatures should be identical, different definition were used in the existing model. To produce a reasonable explanation, curvature of the centerline should depend only on the velocity difference, and the effect of the entry-side curvature should be included in the delivery-side velocity difference. It is known that if the width of the bar is more than 10 times of thickness of it, strain in the width direction is under 3% which is not taken to be significant.6) If the width of the strip b is assumed to not change during rolling, the thickness and velocity difference between DS and WS can be represented as \u2206 \u2206 \u2206 \u2206 H H H v v v h h h v v v DS WS DS WS DS WS DS WS = \u2212 = \u2212 = \u2212 = \u2212 ( ) ( ) ( ) ( ) , 1 1 1 2 2 2 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure2.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure2.4-1.png", + "caption": "Figure 2.4. Joint types, reproduced from [26].", + "texts": [ + " Raghavan found 76 two-link spatial architectures, 224 threelink spatial architectures, 160 four-link spatial architectures, and 56 five-link spatial architectures. The desired overall mobility could not be achieved with more than five links. Matschinsky [26] presents a smaller set of joints and links suitable for independent suspensions than Raghavan, perhaps guided by practical experience during his time at BMW. He also focuses only on the spatial case. Regarding joints, Matschinsky presents those of Figure 2.4, where f is the degree-of-freedom of the joint. The ball joint, Figure 2.4a, called the spherical joint by Raghavan, has f = 3, and can often be replaced by the rubber joint, Figure 2.4b, which, according to Matschinsky, has 48 \u201c. . . good resistance against transient overload, freedom from maintenance, better noise isolation and lower cost.\u201d This substitution is possible when only one axis of rotation is primarily used by a ball joint, allowing the two orthogonal rotations to occur via bushing compliance. The turning joint, Figure 2.4c, also known as the revolute joint, is another possibility, as is the turning-and-sliding joint, Figure 2.4d, also known as the cylindric joint. Matschinsky notes that the turning joint is often implemented practically with two rubber joints, while the turning-and-sliding joint takes the form of a telescopic damper; see Figure 2.5. Finally, he mentions the ball-and-surface joint, Figure 2.4e, but says it is very rarely found in independent suspensions, discussing it further only in the context of rigid axle suspension linkages. Matschinsky does not construct links combinatorially like Raghavan, instead directly stating the most important types, Figure 2.6. The rod link, Figure 2.6a, has a ball joint (or equivalent rubber joint) at each end. It comes with a superfluous rotation r, which does not affect the wheel carrier motion. The triangular link, also known as the A-arm or wishbone, Figure 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure3-1.png", + "caption": "Figure 3. Gripper Cross Sections", + "texts": [ + " The gripping surface of the rollers is urethane rubber, which allows the grippers to accommodate imperfections in the pipes to be gripped. Page 3 of 15 A 24V DC motor with encoder is used to supply the gripping force. When the gripper is initially open, the motor will actuate and cause the drive screw to rotate. As the drive screw rotates it threads into the drive block. Since the drive screw cannot move, the drive block is pulled toward it. As the block moves back, pins connected to the fingers are pulled back which closes the grippers (See Figure 3). When the gripper closes onto a pipe completely the torque supplied by the motor is turned into a linear force which is transferred through the thrust bearing to the load washer. The load washer is then able to provide force feedback to the motor to shut it off when the desired load on the pipe is obtained. An exploded view of the assembly can be seen in Figure 4. Page 4 of 15 An extension system is incorporated into the Pipe Traveler design to allow the second set of grippers to extend to the next pipe" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004730_3f31d5da70be485b.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004730_3f31d5da70be485b.pdf-Figure5-1.png", + "caption": "Fig. 5a Cross-section in the casing fluid domains Fig. 5b Cross-section in the radial pump impeller", + "texts": [ + " The computational domain is divided into three main parts as illustrated in Fig. 4a. The first one is the casing domain which contains the fluid flow around the impeller and surrounded by the external walls of casing body, the second and the third ones are the inlet pipe flow domain and the outlet pipe flow domain, respectively. In the casing flow part, the domain is divided into two parts as well, as shown in Fig. 4b; the dynamic layer domain, that represents the fluid layer rotating between walls of the impeller and fluid layer just above the impeller body; Fig. 5a and the static domain, which represents the remained part located between the casing body of the pump and the dynamic flow layer above the impeller, Fig. 5b. The lengths of the inlet and outlet pipes are about 11.1 and 13.5 times the casing diameter, respectively similar as in [7]. The centerline of the inlet pipe and outlet pipe are at angles of - 28.6o and +28.6o from the Y-axis, respectively, as shown in Fig. 6. The Boundary conditions in these current simulations are similar to that employed in [7]: \u2022 At inlet: the boundary set to be a constant static pressure and the flow is normally directed to the boundary condition with a medium turbulence intensity of 5%, which is a standard inflow boundary condition" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004293_6_2050-5736-3-S1-P82-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004293_6_2050-5736-3-S1-P82-Figure3-1.png", + "caption": "Figure 3 Effect drawing 2", + "texts": [], + "surrounding_texts": [ + "Ultrasound and MRI imaging guiding system for Robotic assisted interventional procedures such as needle biopsy and FUS ablation have to be improved to allow a one stop shop multimodality image guidance. A specific holder which has the capability for connecting the application module of the interventional robotic system \u201cINNOMOTION\u201d (IBSmm, CZ) with SIEMENS wireless ultrasound probe (Acuson Freestyle) was designed and manufactured in order to achieve the desired function. The work is a subproject in FUTURA an EU FP7 funded project for the development of robotic assisted Ultrasound guided focused ultrasound." + ] + }, + { + "image_filename": "designv8_17_0000764_f_version_1633592417-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000764_f_version_1633592417-Figure2-1.png", + "caption": "Figure 2. Top view of the device in section through flexible elements (the description of the components is the same as Figure 1).", + "texts": [ + " This is connected to part 4 by means of a pair of parallel elastic elements 1, on which the strain gauges 2 are placed. Part 4 serves to keep the elastic elements 1 at the same height and to bend each pair only along one of the axes. x or y. Therefore, it is a sort of boundary. Part 5 is connected directly to the rope of the crane 7 by means of pulleys 6. The device designed in this way ultimately represents the attachment of part 5 at one point. Part 5 thus performs a spherical movement in connection with the end of the rope. The operation of the device is clear from Figure 2. If the load moved only in the direction of the x-axis, only the elastic elements lying on the y-axis would bend. The output from the strain gauges would correspond to the swing angle of the load in the plane formed by the x-axis and the rope. Let us denote this angle by \u03d5x. The load would therefore swing similarly to a simple planar pendulum. Similarly, for the movement of the load in the plane formed by the y-axis and the rope, only the elastic elements lying on the x-axis would be bent. This angle is called \u03d5y", + " In Figure 4, a ruler is visible and a point is attached to the weight on the rope. In the equilibrium position of the system, the tip of the weight points to the zero of the ruler. The ruler has a symmetrical distribution, i.e., from zero in the middle to 10 cm on each side. Thus, it is possible to measure the displacement from the equilibrium position to each side. In this experiment, the pendulum moved only in the plane; the spherical motion would say nothing about the accuracy of the device. Thus, with respect to Figure 2, the ruler placed on the ground is parallel to the x-axis of the measuring device and the load moves in the plane formed by the rope and the x-axis as a planar pendulum. A total of 10 measurements were performed on the device, always proceeding in one direction from \u221210 cm to 10 cm on a ruler in 1 cm increments. At the end of each cycle, i.e., the measurement of 21 values belonging to the 21 values on the ruler, the device was allowed to swing freely and then the next measurement was started in the same way" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001579_.1117_12.2304271.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001579_.1117_12.2304271.pdf-Figure4-1.png", + "caption": "Fig. 4 Detector test mount with ULIS 03041 device mounted on (left) , test mount (right)", + "texts": [], + "surrounding_texts": [ + "A. Operating Conditions\nDuring the mission the detector will be used in TDI (Time Delay Integration) mode. The detector will be read out in 5 blocks of 20 rows each, with TDI applied to each odd numbered block such that blocks 1, 3 and 5\nrepresent the optical scene bands from the dichroic filters; band 7 (centre = 8.8m, BW = 0.9m), band 8(centre= 10.8m, BW = 0.9m) and band 9 (centre = 12m, BW = 0.9m) of the MSI TIR. The TDI processing is performed in the front end electronics (FEE) by adding the first line of a block for the first ground line interval to the second line of the block during the second ground line interval etc. to the 20 th line (i.e. In TDI mode signals from N rows in each image area are co-added from N successive frames). During each ground line interval the detector is readout multiple times (nominally 5) and the pixel data added to get the data for a ground line interval ready for TDI addition.\nIII. QUALIFICATION TESTING\nFrom the original batch received at SSTL, 11 micro-bolometers underwent the tests shown in the flow diagram depicted in Fig 2. For all tests adequate ESD protection (e.g. wearing a wrist strap) where applicable was used.\n Die shear\ntest\nProc. of SPIE Vol. 10563 105632D-3", + "A. Functional tests\nFor all environmental tests apart from those of a destructive nature all devices were functionally tested before and after the specific environmental test sequence. The devices subjected to particularly long tests were functionally tested at intermediate steps to ensure the integrity of the devices or determine premature failure.\nB. SSTL\u2019s electro-optical test facility.\nThe general schematic diagram for the tests setup is shown in Fig 3. The detector was mounted in a dedicated \u2018flex\u2019 board (with sprung loaded sockets to avoid soldering of the detectors and allow easy mounting) connected to the FEE board. The flex board was mounted on a specifically designed jig with pipe connections for temperature control. Heat was removed from the hot side of the detector by a re-circulated liquid coolant.\nThe detector clocks and biases were supplied by the FEE board powered by the Electrical Ground Support Equipment (EGSE) board programmed from the host PC via a 1G Ethernet interface. The optical stimulation was provided by a wide area black body mounted inside the temperature enclosure (see Fig. 3) to allow for an f/1 signal to the system. The accuracy of the measurement system depends on the resolution of the black body control unit, water bath and front end electronics hence minor changes on the test conditions were expected during the measurements.\nIV. MECHANICAL QUALIFICATION\nA. Vibration Testing\nA dedicated test cube with tapped holes on the sides and top was used for these tests. The cube was bolted onto an intermediate plate which bolts directly onto the shaker. The cube allowed for testing all axes without the need for a slip table. The detector was bolted directly onto the cube where a facet had been modified to accommodate the detector ensuring that the device plus pins sat flat on the surface of the cube keeping all pins connected to ground by means of a nylon clamp fixed onto the cube.\nProc. of SPIE Vol. 10563 105632D-4", + "The test article was required to be tested in all three axes. The order of testing in each axis was as follows:\nLow Level Sine\nA low level instrumentation check was carried out for each axis to ensure that the test setup is functioning correctly,\nQualification Random\nRandom vibration levels were derived from the tests results of the MSI structural model vibration campaign. An accelerometer was placed at the location of the chip and the levels during the test measured. The output spectrum was then enveloped to produce a test profile used during vibration\nQualification Sine\nThe qualification levels for combined sine and quasi-static are shown in Table 1\nTable 2 shows a summary of the change in electro-optical parameters after vibration\nSame test cube used during the vibration campaign was used for these tests. The cube allowed for measuring on all axes simultaneously. The detector was bolted onto the side of the cube ensuring that the device plus pins sat flat on the surface and all pins were connected to ground. The pins were held in position by means of a nylon clamp fixed onto the plate. The Test Levels for the detector shock qualification testing were derived from the shock measurements performed on the Engineering Confidence Model [ECM] of the MSI.Table 3 shows a summary of the change in electro-optical parameters after shock testing" + ] + }, + { + "image_filename": "designv8_17_0004544__39_article-p159.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004544__39_article-p159.pdf-Figure9-1.png", + "caption": "Fig. 9 Cardan shaft sloped under angle 25\u00b0 with parallel centerlines of the input and output shaft", + "texts": [ + " This result obtained through kinematic simulation using the CAD/CAM/CAE system CATIA V5 proves, that using two universal joints in cardan shaft construction with parallel input and output shafts leads to neutralization of cardan error and input and output angular speeds and accelerations for both shafts are constant and equal zero. This theory was confirmed through equations [8]. The second case completed on the same cardan shaft construction but with the central cardan shaft was sloped under a higher angle with the value 25\u00b0. The graph in Fig. 9 shows the obtained values of angular acceleration of the central cardan shaft where it can be seen that the amplitude of angular acceleration has a higher value than in Fig. 7. When the angle \u03b1 between the input driving shaft and central cardan shaft (central cardan shaft and output driven shaft) grows, then the amplitude of angular acceleration grows too. The third case simulates the variable cardan shaft where the angle \u03b1 changes value from -40\u00b0 to 40\u00b0 while the input driving shaft did four turns (1440\u00b0)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003069_df_ru_2024_02_07.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003069_df_ru_2024_02_07.pdf-Figure8-1.png", + "caption": "Figure 8 \u2014 Air flow velocity fields in the flow area without belting", + "texts": [], + "surrounding_texts": [ + "\u0414\u043b\u044f \u0443\u043b\u0443\u0447\u0448\u0435\u043d\u0438\u044f \u0441\u0445\u043e\u0434\u0438\u043c\u043e\u0441\u0442\u0438 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0432 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0435 \u0441\u0445\u0435\u043c\u044b \u0438\u043d\u0442\u0435\u0440\u043f\u043e\u043b\u044f\u0446\u0438\u0438 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u043f\u0440\u0438\u043d\u044f\u0442\u0430 \u043e\u043f\u0446\u0438\u044f PRESTO! 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\u0443\u0441\u0440\u0435\u0434-\n\u043d\u0435\u043d\u043d\u0430\u044f \u043f\u043e \u0440\u044f\u0434\u0430\u043c1 2 3 4 5 6 \u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0441 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u043e\u043c\n\u0442. 1 3,2 2,8 2,7 2,8 2,9 3,1 2,9 3,2 \u0442. 2 2,8 2,6 2,4 2,3 2,8 2,9 2,6 2,8 \u0442. 3 2,9 2,7 2,4 2,4 2,7 2,8 2,7 2,9 \u0442. 4 2,8 2,8 2,4 2,4 2,6 2,9 2,7 2,9 \u0442. 5 4,0 3,4 3,2 3,3 3,5 3,9 3,6 3,8 \u0442. 6 3,8 3,3 3,2 3,3 3,5 3,7 3,5 3,4 \u0442. 7 3,3 3,0 2,9 2,8 2,8 3,0 3,0 3,2 \u0442. 8 3,1 3,0 2,5 2,4 3,1 3,0 2,9 3,1 \u0442. 9 3,7 3,6 3,2 3,3 3,7 3,8 3,6 3,8 \u0442. 10 3,1 3,2 3,1 3,0 3,4 3,3 3,2 3,3 \u0442. 11 3,2 2,8 3,0 3,1 3,1 3,3 3,1 3,3 \u0442. 12 6,1 6,1 6,0 6,1 6,0 6,2 6,1 6,6 \u0442. 13 8,2 8,2 8,0 7,9 8,0 8,1 8,1 8,5\n\u0412\u0430\u0440\u0438\u0430\u043d\u0442 \u0431\u0435\u0437 \u0431\u0435\u043b\u044c\u0442\u0438\u043d\u0433\u0430 \u0442. 1 3,9 3,8 3,7 3,5 3,6 4,0 3,8 4,1 \u0442. 2 2,8 2,6 2,6 2,7 2,9 3,1 2,8 3,0 \u0442. 3 3,0 3,0 2,9 3,0 3,2 3,4 3,1 3,2 \u0442. 4 3,1 3,0 2,8 2,9 3,0 3,2 3,0 3,2 \u0442. 5 3,2 3,1 2,7 2,8 3,0 3,1 3,0 3,2 \u0442. 6 3,0 3,0 2,9 2,7 2,7 2,9 2,9 3,1 \u0442. 7 3,2 3,1 2,6 2,5 3,1 3,0 2,9 3,2 \u0442. 8 3,1 3,2 2,8 2,8 3,0 2,9 3,0 3,1 \u0442. 9 3,2 3,2 2,7 3,0 3,2 3,3 3,1 3,3 \u0442. 10 2,8 2,9 2,6 2,6 2,9 3,0 2,8 3,1 \u0442. 11 3,1 2,9 2,8 2,9 3,2 3,0 3,0 3,3 \u0442. 12 3,7 3,5 3,3 3,6 3,4 3,5 3,5 3,8 \u0442. 13 6,6 6,1 5,9 6,3 6,5 6,2 6,3 6,8\n\u041f\u0440\u0438\u043c\u0435\u0447\u0430\u043d\u0438\u0435: *\u043e\u0442\u0441\u0447\u0435\u0442 \u0432\u0435\u0434\u0435\u0442\u0441\u044f \u043e\u0442 \u043f\u0440\u0430\u0432\u043e\u0439 \u0431\u043e\u043a\u043e\u0432\u0438\u043d\u044b \u043f\u043e \u0445\u043e\u0434\u0443 \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u044f \u043a\u043e\u043c\u0431\u0430\u0439\u043d\u0430.\n\u0422\u0430\u0431\u043b\u0438\u0446\u0430 \u2014 \u0420\u0435\u0437\u0443\u043b\u044c\u0442\u0430\u0442\u044b 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IV-16: \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0448\u0438\u043d\u044b \u0438 \u043e\u0431\u043e\u0440\u0443\u0434\u043e\u0432\u0430\u043d\u0438\u0435. \u2014 720 \u0441. 2. Experimental study on the influence of working parameters of centrifugal fan on airflow field in cleaning room / C. Zhang [et al.] // Agriculture. \u2014 2023. \u2014 Vol. 13, iss. 7. \u2014 DOI: https://doi.org/10.3390/agriculture13071368. 3. Operation technological process research in the cleaning system of the grain combine / I. Badretdinov [et al.] // Journal of Agricultural Engineering. \u2014 2021. \u2014 Vol. 52, no. 2. \u2014 DOI: https://doi.org/10.4081/jae.2021.1129. 4. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0418.\u0414. \u041d\u0430\u0443\u0447\u043d\u043e\u0435 \u043e\u0431\u043e\u0441\u043d\u043e\u0432\u0430\u043d\u0438\u0435 \u0438 \u0441\u043e\u0432\u0435\u0440\u0448\u0435\u043d\u0441\u0442\u0432\u043e\u0432\u0430\u043d\u0438\u0435 \u043f\u043d\u0435\u0432\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0438\u0445 \u0441\u0438\u0441\u0442\u0435\u043c \u0441\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0445 \u043c\u0430\u0448\u0438\u043d \u043d\u0430 \u043e\u0441\u043d\u043e\u0432\u0435 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f \u0442\u0435\u0445\u043d\u043e\u043b\u043e\u0433\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043f\u0440\u043e\u0446\u0435\u0441\u0441\u0430 / \u0418.\u0414. \u0411\u0430\u0434\u0440\u0435\u0442\u0434\u0438\u043d\u043e\u0432, \u0421.\u0413. \u041c\u0443\u0434\u0430\u0440\u0438\u0441\u043e\u0432 // \u0412\u0435\u0441\u0442\u043d. \u041d\u0413\u0418\u042d\u0418. \u2014 2019. \u2014 \u2116 9(100). \u2014 \u0421. 5\u201316. 5. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u041d.\u0413. \u0421\u0435\u043b\u044c\u0441\u043a\u043e\u0445\u043e\u0437\u044f\u0439\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435 \u043c\u0430\u0442\u0435\u0440\u0438\u0430\u043b\u044b (\u0432\u0438\u0434\u044b, \u0441\u043e\u0441\u0442\u0430\u0432, \u0441\u0432\u043e\u0439\u0441\u0442\u0432\u0430) / \u041d.\u0413. \u041a\u043e\u0432\u0430\u043b\u0435\u0432, \u0413.\u0410. \u0425\u0430\u0439\u043b\u0438\u0441, \u041c.\u041c. \u041a\u043e\u0432\u0430\u043b\u0435\u0432. \u2014 \u041c.: \u0418\u041a \u00ab\u0420\u043e\u0434\u043d\u0438\u043a\u00bb, \u0436\u0443\u0440\u043d\u0430\u043b \u00ab\u0410\u0433\u0440\u0430\u0440\u043d\u0430\u044f \u043d\u0430\u0443\u043a\u0430\u00bb, 1998. \u2014 208 \u0441." + ] + }, + { + "image_filename": "designv8_17_0004028_f_version_1585038971-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004028_f_version_1585038971-Figure10-1.png", + "caption": "Figure 10. Three-dimensional model of the wind turbine.", + "texts": [ + " Table 3 lists the values of deflection torques at different angles. Based on these tables, when the deflection angle increases, the distance between the rotor and the stator increases, which causes a decrease in the deflection torque. Table 3. Value of deflection torques. Angle X-Axis Deflection Torque Value (N*m) Y-Axis Deflection Torque Value (N*m) 0 \u25e6 0.019923 0.011817 5 \u25e6 1.1979 1.2316 10 \u25e6 1.0811 1.0864 15 \u25e6 0.94953 0.97457 20 \u25e6 0.85378 0.85074 25 \u25e6 0.7826 0.78247 30 \u25e6 0.74123 0.71937 4. Wind Turbine Modeling Figure 10 shows the 3D model of the multi-DOF deflecting-type permanent-magnet synchronous wind turbine. The turbine usually comprises of a wind wheel, vertical shaft, bearing, bearing seat, tower, Energies 2020, 13, 1524 10 of 22 footing, coupling, multi-DOF deflecting-type PMSG, controller, and an inverter [24\u201326]. According to Figure 10, the wind turbine has a double-layer wheel structure, and each layer has three shafts. Figure 11a shows a two-dimensional structural model of the double-layer wind wheel, whereas Figure 11b shows a 3D structural model of the one-layer wind wheel. Table 4 lists the specific parameters of the wind turbine obtained from the measured data of the wind turbine prototype from the wind power laboratory at Hebei University of Science and Technology. Energies 2020, 13, x FOR PEER REVIEW 10 of 22 25\u00b0 0.7826 0.78247 30\u00b0 0.74123 0.71937 4. Wind Turbine Modeling Figure 10 shows the 3D model of the multi-DOF deflecting-type permanent-magnet synchronous wind turbine. The turbine usually comprises of a wind wheel, vertical shaft, bearing, bearing seat, tower, footing, coupling, multi-DOF deflecting-type PMSG, controller, and an inverter [24\u201326]. According to Figure 10, the wind turbine has a double-layer wheel structure, and each layer has three shafts. Figure 11a shows a two-dimensional structural model of the double-layer wind wheel, whereas Figure 11b shows a 3D structural model of the one-layer wind wheel. Table 4 lists the specific parameters of the wind turbine obtained from the measured data of the wind turbine prototype from the wind power laboratory at Hebei University of Science and Technology. Figure 10. Three-dimensional model of the wind turbine. (a) (b) Figure 11. Wind wheel model: (a) two-dimensional structural model of the double-layer wind wheel; (b) 3D structural model of the one-layer wind wheel. Table 4. Specific parameters of the wind turbine. Parameter Value Parameter Value Height of the blade 0.3 m Rated power 10 kW Radius of the blade 0.65 m Radius of shaft 0.2 m Height of shaft 5 m Starting wind speed 2\u20133 m/s r i Energies 2020, 13, x FOR PEER REVIEW 10 of 22 25\u00b0 0.7826 0.78247 30\u00b0 0.74123 0.71937 4. Wind Turbine Modeling Figure 10 shows the 3D model of the multi-DOF deflecting-type permanent-magnet synchronous wind turbine. The turbine usually comprises of a wind wheel, vertical shaft, bearing, bearing seat, tower, footing, coupling, multi-DOF defle ti g-type PMSG, cont oller, and an inverter [24\u201326]. According to Fig re 10, t e wind turbine has a double-layer wheel structure, and each layer has three shafts. Figure 11a shows a two-dimensional structural model of the double-layer wind wheel, whereas Figure 11b shows a 3D structural m d l of the one-layer wind wh el" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002084_010.5__63975-1___pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002084_010.5__63975-1___pdf-Figure6-1.png", + "caption": "FIGURE 6. (a) KINEMATIC CONFIGURATION OF THE CAM FOLLOWER MECHANISM; (b) FOLLOWER DISPLACEMENT.", + "texts": [ + " This clash is undesirable for two main reasons; firstly, because it accelerates the cam and follower wear, and secondly, because it decreases the kinetic energy available for the cutting operation, since part of the energy is be absorbed by that impact. Hence, the file quality is significantly penalized (Flores, 2009). The multibody system of the cutting file machine is made of three rigid bodies (cam \u2013 the driver, follower \u2013 the driven element, and the ground or frame), one revolute joint, and one translational joint. Figure 6a depicts the kinematic configuration of the cam follower mechanism. It is known that for nb rigid body system with nc independent constraint equations, the mobility or degrees of freedom (DOF) is given by ncnbDOF \u2212\u00d7= 6 (36) This mathematical expression, usually called as Gr\u00fcebler equation, can be used to determine the mobility of multibody system. Thus, from Eq. (36), the DOF of the cam-follower mechanism is equal to 1, implying one, and only one, motion generator. Since the follower can not rotate about its own axis, and the follower curvature radius is very large when compared to its own dimensions, the follower can be considered of the type flat faced. Thus, to keep the analysis NII-Electronic Library Service Copyright (c) 2010 by JSME simple, the present study was performed for a disk cam flat follower type mechanism. The flat faced follower has the advantage of a zero degree pressure angle throughout its motion, which is an important feature, since most of camfollower mechanisms are designed with pressure angles as small as possible (Flores, 2009). Figure 6b schematically illustrates the experimental data relative to the follower displacement diagram corresponding to a sixth part of the cam angle rotation, since the cam has six rebounds and the cam-follower motion repeats itself six times in each complete cam rotation. In Fig. 6b, point A represents the maximum follower displacement, point B defines the instant of impact between the follower and file body, point C corresponds to the minimum follower displacement, that is, the maximum penetration/deformation of the body file, and finally, point D represents the re-contact between the cam and follower after the rebound effect. Observing Fig. 6b, it is evident that the follower motion can be divided into two main phases, namely, the fall and the rise movements. In turn, these two phases can be analyzed into two different parts. Starting from maximum follower elevation, point A, the follower motion can be described and summarized by the following steps: (i) Fall #1 - from point A to point B: during the fall phase, the follower motion is influenced by three main factors, namely, the gravity effect, the spring action and friction phenomenon that exists between the follower and guide" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000852__jte_67_5_67_77__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000852__jte_67_5_67_77__pdf-Figure1-1.png", + "caption": "Fig. 1 Gear (1) rotates clockwise with gear rotation speed \u03c9. The conjugate cams (7 and 13) are fixed on the dobby box body. The cam swing arms (4 and 9) are hinged on the gear (1), and can rotate around its hinged joints, thus transmitting the uniform circular motion of the loom to the slider frame. The uniform circular motion of the loom, which is transmitted to the slider frame through the gear (1), the slider of the modulator is hinged at point C, forms the dobby rotational motion of the main shaft O.", + "texts": [], + "surrounding_texts": [ + "Key Words : Cam profile, Modulator, Dynamic model, Vibration response, Machining errors\n* Corresponding author: E-mail : yuhongbin@tiangong.edu.cn, Tel : 0086-13323321892\nIn textile machinery, the rotary dobby is currently one of the most advanced high-speed opening devices used in modern highspeed weaving machines [1-3]. The dobby mechanism divides the warp yarn into two layers, and forms a channel for the weft yarn to pass through. This process is achieved by converting the rotational main shaft motion of the loom into vertical motion of the heddle frame. Dobby must have good mechanical properties to adapt to the high-speed loom production. In recent years, a rotary dobby can be found in shuttleless looms such as rapier and air-jet looms. It is widely employed due to their compact structure, high motion accuracy, relatively simple control, and stable operation.\nThe modulator is the core part of the rotary dobby. During the weaving process, the heddle frame is lifted [4]. Hence, force and vibrational characteristics of the modulator have an important influence on the weaving process of the heddle frame, which drives the warp yarn. Therefore, it is necessary to analyze the dynamic characteristics of the modulator, particularly the high-precision and high-speed characteristics of the conjugate cam-roller assembly [5]. Motion accuracy and dynamic characteristics influencing factors are relatively complicated. Therefore, dynamics and reliability of the modulator have to be investigated in detail.\nCam followers represent an important impact system type, which is widely used in various applications. Generally, a cam rotating with a constant speed provides the follower drive force. One of the most common examples is the valve mechanism of an internal combustion engine. In this mechanism, the cam rotation moves the engine valve through the follower, and the spring ensures the restoring force required to maintain contact between the components [6]. In high-speed cams, the inevitable camshaft fluctuations affect the accuracy of the follower [7, 8]. Rothbart [9] employed a shift cam and explicitly embedded its shifting speed as a design parameter. The vibrational response graph can be used to evaluate the influence of various parameters on the cam follower dynamics. These parameters include the cam speed, stiffness characteristics, and various cam profiles [10].\nComplex behavior of impact mechanical equipment has become an important subject of the ongoing research [11]. As previously mentioned, one of the most common examples is an internal combustion engine valve mechanism, where contact loss between the cam and the follower occurs during high-speed rotation [12, 13]. This causes a reduction in the engine efficiency, fuel consumption, and emission performance [14]. Gatti [15] proposed a preliminary study on the follower vibration control when it is directly acted upon by the cam.", + "According to the above presented research, a certain foundation has already been laid for further analysis of the rotary dobby dynamics. In order to improve the production efficiency of modern looms, their speed is also continuously increased. Consequently, the machine vibration and stability are decreased when subjected to higher speeds, which shortens the service life of the loom. Therefore, in this paper, the principle of lumped parameter method and fourth-order Runge-Kutta method (among other methods), combined with the system dynamics theory, are employed to construct the modulator dynamic model. Furthermore, the numerical solution method is established, and dynamics calculation procedures are complied. Modulator dynamic response analysis for the cam profile processing errors are conducted. Moreover, main influencing factors affecting the reliability and stability of the modulator are compared and analyzed. Lastly, theoretical basis and guidance for improving the efficiency and product quality of the rotary dobby are provided [16].\nSchematic drawing of the cam-slider modulator is presented in\nDobby modulator movement is transmitted to the heddle frame through the link. Dynamic performance of the modulator directly affects the shedding performance of the loom. Currently, for kinematics and dynamics analysis of the rotary dobby, elastic deformation effect of the mechanism components on the heddle frame motion performance is not considered. With the development of dobby for lightweight and high-speed applications, the inertial forces and system flexibility have sharply increased. Therefore, the elastic deformation of components has an increased impact on the overall system performance. The flexible body in the system has an important effect on the motion of the entire system. During modulator operation, its vibration response has a significant impact on the overall dynamics of the loom system. Therefore, the elastic characteristics of the modulator must be considered", + "when investigating overall dynamic characteristics of the dobby. By studying the influence of the modulator components, flexible deformation effect on the opening performance is investigated. Moreover, theoretical basis for solving the problems of low operational stability and poor reliability is established. In mechanical systems, flexible components have a significant impact on the movement of the entire system. To accurately simulate motion of the entire mechanical system, the influence of the flexible body on the system motion characteristics has to be considered and its vibrational characteristics analyzed.\nDynamic model of the cam slider modulator is shown in Fig. 2 (a). The lumped parameter method is used to simplify the mechanism into two masses, three dampers, and three springs. In the dynamic model of the cam slider modulator, m1 represents the combined concentrated mass of cam roller 1, swing arm 1, link 1, and half of the main shaft link. Parameter m2 represents the combined concentrated mass of cam roller 2 and swing arm 2. Additional springs and damping elements are simplified as spring coefficients k1, k2 and k3. The viscous damping coefficients b1, b2, and b3 are used to tie masses m1 and m2 to the contact point. The aforementioned is depicted in Fig. 2 (b).\nSeparated bodies of the cam slider modulator followers 1 and 2 are considered for the force analysis. Followers 1 and 2 are simultaneously subjected to the elastic restoring force and the damping force in the vertical direction. The force analysis is shown in Fig. 2 (c).\nAccording to Newton's second law and under assumption of negligible friction resistance between the cam and the roller, modulator differential motion equation can be derived:\n(1)\nS (t) = S1 (t) + \u2206S (t) (2)\nH (t) = H1 (t) + \u2206H (t) (3)\n(4)\nwhere: S (t) - Actual displacement of the contact point A between the main cam and the roller. S1 (t) - Ideal displacement of the contact point A between the main cam and the roller. \u2206S (t) - Displacement variation of the contact point A between the main cam and the roller. H (t) - Actual displacement of the contact point B between the auxiliary cam and the roller. H1 (t) - Ideal displacement of the contact point B between the auxiliary cam and the roller. \u2206H (t) - Displacement variation of the contact point B between the auxiliary cam and the roller. y1 - Actual movement displacement of the mass m1 of the follower. y2 - Actual movement displacement of the mass m2 of the follower. k1, k2 and k3 - Spring stiffness.\n\u03b8 - Gear rotation angle, \u03b8 \u2208[0\u00b0, 360\u00b0). \u03c9 - Gear rotation speed. t - Gear running time.\nIn an ideal situation, for a relatively low rotational speed of the gear, the contact point between the cam surface and the roller never separates. We accurately study the static dynamic behavior of the modulator through theory, and the displacement characteristic curve S1 (t) calculated by the contact between the cam and the roller under the ideal fit condition. The S1 (t) displacement curve is shown in Fig. 3. Follower mass m1 meets the expected displacement characteristic curve S1 (t), while follower mass m2 meets the expected displacement characteristic curve H1 (t). Assuming there is no assembly errors and the two rollers are in close contact with the conjugate cam profile: S1 (t) = H1 (t), \u2206S (t) = \u2206H (t) = 0.\nMass m1 is considered as an example. The mass is placed in an ideal state. Displacement motion equation of m1 in the modulator is then:\ny = F (U, q1, \u00b7\u00b7\u00b7, qn) (5)\nwhere: y - Roller follower displacement of ideal cam. U - Displacement of ideal cam drive. q1, \u00b7\u00b7\u00b7, qn - Theoretical parameters of each component in the rotating speed change mechanism.\nIn the actual state, due to various modulator errors and parameter changes, the movement displacement U of the driving part cam should be increased by a certain amount U + \u2206U. The actual parameter qi of each component can be represented by qi + \u2206qi. In the actual state, the modulator displacement motion equation of m1 is as follows:\ny1 = F (U + \u2206U, q1 + \u2206q1, q2 + \u2206q2, \u00b7\u00b7\u00b7, qn + \u2206qn) (6)\nThis formula can be expanded according to the Taylor series expansion. Because the change items \u0394U and \u0394qi are both relatively" + ] + }, + { + "image_filename": "designv8_17_0000637_f_version_1649326514-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000637_f_version_1649326514-Figure11-1.png", + "caption": "Figure 11. Mechanical stress distribution of the designed SynRM rotors at the speed of 10,230 rpmL: (a) The optimized SynRM rotor; (b) The optimized SynRM rotor with central bridges.", + "texts": [ + " It is interesting that the variation in the torque ripple for the solutions on the Pareto front is more significant than the variations of average torque and efficiency. The optimal point is then selected to achieve the minimum torque ripple, with slight penalization on average torque and efficiency. The projections of this optimal point on each plane are drawn by the black points in Figure 10. The rotor parameter values of the optimal SynRM are shown in Table 3. Since the Lexus LS 600h IPM motor is operated as high as 10,230 rpm [29], the rotor structure analysis of the designed SynRM is conducted. Figure 11a shows the rotor mechanical stress distribution towards centrifugal stress. The maximum stress is noticed to be 1461 MPa, while the Yield stress of the iron lamination is only around 440 MPa. As a result, central bridges in the second and third flux barriers are introduced to reduce the stress concentration on the outer ribs. The thicknesses of these central bridges are optimized to 0.3 mm and 1.0 mm, respectively. As shown in Figure 11b, the maximum stress is then reduced to 354 MPa, which allows a safety factor of 1.24. As a sacrifice, the machine torque is slightly reduced due to the leakage flux path created by the central bridges. The cross-section of the designed SynRM is shown in Figure 1. According to [29], the maximum torque of the Lexus LS 600h IPM motor within the temperature limit of 150 \u25e6C for a transient time of 18 s is around 233 Nm. The maximum torque of the optimized SynRM under the same peak current is 178 Nm, which accounts for only 76%" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure8-1.png", + "caption": "Figure 8. H-M-H strain map for the force value of 150 N acting along the X axis.", + "texts": [], + "surrounding_texts": [ + "In order to perform simulation tests, a properly parametrised virtual models were prepared, as presented in Figure 6. Specialist CAD-3D software was used to prepare them. With the use of pre- and postprocessors of graphic engineering interpretation, the calculation model was described with solid elements enabling approximation of operating characteristics of an object in real conditions [47,48]. Based on the adopted transducer construction and the occurring loads, tetrahedral parabolic second-order elements were used in the prepared model. This ensured a more accurate mathematical representation than in the case of linear elements [49]. The degrees of freedom were defined based on the actual operation of the transducer by depriving the nodes around the installation holes of the capability to move along the longitudinal and transverse axes of the transducer. As a result, its contact with the area of tool installation to the test stand was reflected [9]. The capability of the nodes in the installation holes to move along all axes was removed. During the tests, forces and torques were applied to the nodes constituting the face surface of the connector. As a result of the performed simulation tests (FEM), strain distribution for three cases was obtained, corresponding to the permissible forces and torques. Strain values reduced for the analysed structure were obtained using the von Mises yield criterion. In each simulation experiment, the loads were applied to the surface constituting the agricultural tool installation area. The first of the considered load states concerned the maximum permissible strain of the construction along the Z axis, i.e., perpendicular to the surface. For the adopted force Fz = 450 N, the maximum strain values of 29 MPa were obtained and were concentrated around the internal through holes. The second considered load component was the excitation along the Y axis, i.e., in the direction parallel to the installation surface. The applied load with the value of Fy = 200 N caused a concentration of strain around the outermost holes. The read values did not exceed 39 MPa. The last of the tested states concerned the effects related to the torque moment about the X axis. For the adopted load of Mx = 150 Nm, strains with a maximum value of 0.24 MPa were obtained. The strains were concentrated in the terminal points of the crosswise edge of the connection with the brackets. The results of the analyses of the body structure, presenting the strain distribution caused by the effect of loads in the form of force acting along the Y axis and the torque about the X axis, were provided in figures from Figures 7\u20139. The strength tests performed with the use of the finite element method provided essential information about the strain distribution in the considered body structure. They showed an adequate degree of transducer stress relief, and no cross-sensitivity occurred between various channels. The obtained results form the basis for the proper selection of appropriate points for the positioning of the strain gauge sensors. Moreover, the test results made it possible to evaluate the concurrent effect of a higher number of loads on the body structure. The tests also took into account an extreme example, when all the maximum value loads act on the system. It was found that the structure had adequate strength and that the permissible strain values were not exceeded." + ] + }, + { + "image_filename": "designv8_17_0000931_nf_efm2014_02064.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000931_nf_efm2014_02064.pdf-Figure5-1.png", + "caption": "Figure 5. FEM model of the basic construction part of exchanger with meandr and unilateral inlet/outlet.", + "texts": [], + "surrounding_texts": [ + "The numerical model for calculating the pressure loss of the heat convector was carried out in the finite element (FEM) Fluid Dynamics module of COMSOL Multiphysics. COMSOL Multiphysics is suitable for modeling various physical phenomena by electrostatics and electrokinetics through dynamic processes up to the fluid flow and compression of isotropic or anisotropic materials [9]. This software includes a number of tools designed to solve a wide range of problems that are described by partial differential equations as specifically in this case used Navier-Stokes equation (2). COMSOL was used to compute the implicit algorithm where at each time instants velocity gradually updated in time t with a time increment t + dt according to equation (3) as opposed to explicit algorithm that is suitable for other types of dynamic analyzes as said Petr#, Nov\u00e1k, Her\u00e1k and Simanjuntak [10-11]. tt i tt ii uuu \u0394+\u0394+ ++ \u2212= 11\u03b4 , (3) where tt iu \u0394+ is the vector of nodal displacement for the i-iteration in the time tt \u0394+ . The numerical model allows the modeling of the vector momentum distribution of the fluid flowing in the coil. The results affect the corresponding initial and boundary conditions that are particularly difficult due to the complicated geometry of the heat exchanger, through which flows the driving medium. The boundary conditions were defined the same way as with the real devices, for the selected observed temperature (12, 23, 40 and 60 \u00b0 C) and for the selected flow velocity. The input parameters of the numerical model for analysis of the pressure loss are shown in Table 1. The model itself was based on the modified 3D CAD data model of the heat exchanger with a real dimensional geometry. The suitable variant of the calculation depending on the size of the Reynolds number was chosen in the simulation. This is a laminar flow, turbulent flow with a low Re number called \"transitional region\" and turbulent flow. \u2022 The Reynolds number (4) where \u03b7 is the dynamic viscosity (1), N\u00b7s\u00b7m-\u00b2; \u03c1 is the density of the fluid, kg\u00b7m-3; D is the inner diameter of the round pipe and v is the mean velocity of the fluid, m\u00b7s-1. During the model simulation of process like this, problems arrise in the convergence of solutions. Sometimes the finite solution can despite very sophisticated procedures Gauss elimination iterate with unacceptable error. Therefore, it is necessary already when drawing up the model that there will be close to the real behavior. This suggests a suitable design adaptive finite element mesh that meets the criteria of flow, boundary and initial conditions, etc. These are a primary target in order to appropriate numbers of iterations already in the beginning of the calculation (Figure 2) to a sufficient degree for minimize the resulting residue defined by equation (5). The calculation is shown in Figure 2. and in Table 2. The resulting dependence of the convergence calculation, which is given by the expression, sizes residues and the number of iterations (linear or nonlinear). [ ] zkz n k c zfsdzzfia == \u2212 == 1 1 )(Re)( 2 1 \u03c0 , (5) where a-1 is rezidium of the function f (z) at the nodal point z0 and f(z) represents a function meromorphic Laurent series around the isolated singular point (node), and must pay (z0 & z). Res [f (z)] z = zk is called the rezidium of function f (z) in the k-th nodal point zk. 02064-p.3 When using the adaptive techniques, it may happen that even though the critical threshold will significantly soften, the stiffness matrix becomes badly definite. Therefore the use of the multi-network methods (multigrid method), which essentially combines a finite iterative method [12]. The error of the solution can be divided into singular (local) and global. Singular is the high frequency error that is not locally extensive, but can be reduced with the iterative process. Global lowfrequency error, has the nature of a smooth function and affects virtually all of the solutions in the areas. The finite element mesh was therefore created from 3D Solid tetrahedron (10-node elements) with the total numbers of degrees of freedom specified in the Table 2. For a sufficiently and accurate solution in geometrically complex areas (radius, knees), adaptive technique were developed in elements of 0.002 mm size. Detail of the proposed finite element mesh is shown in Figure 3. 02064-p.4" + ] + }, + { + "image_filename": "designv8_17_0003644_article_25839670.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003644_article_25839670.pdf-Figure2-1.png", + "caption": "Fig. 2 Sectional view of 4-pole 36-slot permanent magnet machine", + "texts": [ + " (1) as 2 2 2 1 n 10 2 ( ) ( ) sin 4 a cog n nz pr p zLT R R nG B nzp\u03b1 \u03b1 \u00b5 \u221e = = \u2212 \u2211 (7) Both 2 ( )rB \u03b8 and 2[ ] ( , ) m m h h \u03b4 \u03b8 \u03b1+ are supposed to have effects on cogging torque, but not every Fourier component of them does work. There are only the nz/2p Fourier components of Br 2 (\u03b8) and the n Fourier components of 2[ ] ( , ) m m h h \u03b4 \u03b8 \u03b1+ that affect cogging torque, which means that the reduction of Br(nz/2p) and Gn leads to a less cogging torque. This paper chooses a 4-pole 36-slot surface mounted permanent magnet machine as the prototype, with its parameters shown in Table. 1.The sectional view of the prototype is shown as Fig. 2. All the attempts are simulated with the finite-element methods. Optimization of pole-arc coefficient. It can be seen from Eqn. (7) that only the nz/2p Fourier components of Br 2(\u03b8) has influence on the cogging torque, which means that once the numbers of pole-pairs and slots are determined, the Fourier component of Br 2(\u03b8) will be derived. From analysis we know that the Fourier components of Br 2(\u03b8) are related to pole-arc coefficient. When the number of stator slots is 36, cogging torque is only associated with the 9k (k is an integral number) Fourier components of Br 2(\u03b8)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003454_6_61_4_61_4_501__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003454_6_61_4_61_4_501__pdf-Figure2-1.png", + "caption": "Fig. 2 Teeth cross section of helical gear given", + "texts": [], + "surrounding_texts": [ + "\u8ad6\u6587\n\u4eee\u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6 \u306b\u57fa\u3065 \u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\n\u5275\u6210\u6b6f\u5207 \u308a*\n\u8429 \u539f \u89aa \u4f5c* *\nPractical Face Gear Hobbing based on a Theory of Virtual Shifted Gear\nShinsaku HAGIWARA\nFace gears are made by a continuous generating-shaping process on a Fellows Gear Shaper or\nsimilar type machine using a special fixture. Their gears, which have some advantages of easy setting, smooth mating for the mating pinion of spur or helical, low cost, and other things, are often substituted for bevel gears. In order to hob by use of a conventional hob machine and commercial hob, a theory of virtual shifted gear for determining the maximum practical outside diameter, the minimum practical inside diameter, and the face width of face gears, is proposed in face gear design. As a result, hobbed face gear could be obtained to become the point which the teeth become pointed at the outside and the point where tooth trimming occurs at the inside. In addition, contact test will be permitted to touch smoothly if being burnished enough.\nKey words : practical face gear, virtual shifted gear, maximum practical outside diameter,\nminimum practical inside diameter, contact test\n1. \u306f \u3058 \u3081 \u306b\n\u73fe \u5728 \u4f7f \u7528 \u3055\u308c \u3066 \u3044 \u308b \u5404 \u7a2e \u6b6f \u8eca \u306f,\u8a2d \u8a08 \u304c \u8907 \u96d1 \u306b\u306a \u308b \u3068 \u305d \u308c \u306b\u4f34 \u3044\u305d \u306e\u88fd \u4f5c \u306b \u306f \u5c02 \u7528 \u306e \u6b6f \u5207 \u308a\u76e4 \u304c \u5fc5 \u8981 \u3068\u306a \u308b \u5834 \u5408 \u304c\n\u591a\u3044.\u305d \u306e \u4ee3\u8868 \u7684 \u306a \u3082\u306e \u306e \u4e00 \u3064 \u306b \u304b \u3055\u6b6f \u8eca \u304c \u6319 \u3052 \u3089\u308c \u308b. \u3057\u304b \u3082\u304b \u3055\u6b6f \u8eca \u306f \u5404 \u6b6f \u5207 \u308a\u76e4 \u30e1\u30fc \u30ab \u72ec \u81ea\u306e \u898f \u683c \u3092 \u3082 \u3061\u4ed6 \u793e\n\u3068\u306e \u4e92 \u63db \u6027 \u304c \u60aa \u3044 \u306a \u3069\u306e \u6b20 \u70b9 \u304c \u3042 \u308a,\u3055 \u3089 \u306b\u4fa1 \u683c \u306e \u9762 \u3067 \u3082 \u4e00\u822c \u306e \u30ae \u30e4 \u306b \u6bd4 \u3079 \u9ad8 \u4fa1 \u3067 \u3042 \u308b .\u305d \u306e \u305f \u3081 \u3057\u3070 \u3057\u3070 \u901a \u5e38 \u306e \u6b6f\n\u5207 \u308a\u76e4 \u306b \u3088 \u308b \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u304c \u304b \u3055\u6b6f \u8eca \u306e \u4ee3 \u7528 \u3068 \u3057\u3066\u6ce8 \u76ee \u3055 \u308c\u305f1).\u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306f \u901a \u5e38,\u5e73 \u6b6f \u8eca \u307e \u305f \u306f \u306f \u3059 \u3070\u6b6f \u8eca \u306e \u30d4\u30cb \u30aa \u30f3 \u3068 \u76f4 \u89d2 \u306b \u304b \u307f \u5408 \u3046\u4e00 \u7a2e \u306e \u30af \u30e9 \u30f3 \u30af\u30ae \u30e4 \u3067 \u3042 \u308b. \u304b\n\u3055\u6b6f \u8eca \u3068\u6bd4 \u8f03 \u3057\u3066 \u76f8 \u624b \u6b6f \u8eca \u306b \u305f \u3044 \u3057\u3066 \u30aa \u30f3\u30bb \u30f3 \u30bf \u3067 \u3082\u30aa \u30d5 \u30bb \u30c3 \u30c8\u3067 \u3082 \u7528 \u3044 \u308b \u3053 \u3068\u304c \u3067 \u304d,\u7d44 \u7acb \u8abf \u6574 \u304c \u7c21 \u5358,\u3057 \u304b \u3082\u5b89\n\u4fa1 \u306a \u3069\u306e \u5229 \u70b9\u304c \u3042 \u308b.\n\u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e \u88fd \u4f5c \u306f \u4e00 \u822c \u7684 \u306b,\u30d5 \u30a7\u30ed \u30fc \u30b9 \u578b \u6b6f \u8eca \u5f62 \u524a\n\u308a\u76e4 \u306b \u4ed8\u5c5e \u88c5 \u7f6e \u3092 \u53d6 \u308a\u4ed8 \u3051 \u3066 \u5275 \u6210 \u6b6f \u5207 \u308a\u306b \u3088 \u308a \u884c \u3046.\u3057 \u304b\n\u3057\u3053 \u3053 \u3067 \u3082 \u5c02 \u7528\u6a5f \u306e \u666e \u53ca \u7387 \u306f\u4f4e \u304f,\u3057 \u304b \u3082\u9ad8 \u4fa1 \u3067 \u3042 \u308b \u3068\u8a00 \u3063\u305f\u554f \u984c \u304c \u3042 \u308b 2).\n\u3053 \u308c \u307e \u3067 \u306b \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306b \u95a2\u3059 \u308b\u5831 \u544a1)\uff5e6)\u306f \u6975 \u3081 \u3066 \u5c11\n\u306a \u3044 \u304c,\u306a \u304b \u3067 \u3082\u5742 \u672c1)2)\u3089 \u306f \u666e \u901a \u30dc \u30d6 \u306b \u3088 \u308b \u6b6f \u5207 \u308a\u53ef \u80fd\n\u306a \u30dc \u30d6 \u306e \u958b \u767a \u306a \u3069 \u3092\u691c \u8a0e \u3057,\u5b9f \u7528 \u306e \u53ef \u80fd \u6027 \u3092 \u793a \u5506 \u3057\u3066 \u3044 \u308b.\n\u672c \u7814\u7a76 \u3067 \u306f,\u5b9f \u7528 \u7684 \u306a \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u3092 \u901a \u5e38 \u306e \u30db \u30d6 \u76e4 \u3068\u5e02\n\u8ca9 \u30db \u30d6 \u3092 \u82e5 \u5e72 \u5de5 \u592b \u3059 \u308b \u3053 \u3068 \u3067,\u5f93 \u6765 \u3088 \u308a\u7c21 \u5358 \u306b\u88fd \u4f5c \u3059 \u308b \u3053 \u3068\u306b \u4e3b \u76ee\u7684 \u3092\u304a \u304f.\u305d \u306e \u305f \u3081 \u306b \u4eee \u60f3 \u306e \u8ee2 \u4f4d \u6b6f \u8eca \u7406 \u8ad6 \u3092 \u7528 \u3044 \u305f\u8fd1 \u4f3c \u7684 \u306a \u8a2d \u8a08 \u30fb\u8a08 \u7b97 \u6cd5 \u3092\u63d0 \u6848 \u3059 \u308b.\u305d \u3057\u3066 \u8fd1 \u4f3c \u5f0f \u306b \u5f93 \u3044\n\u6b6f\u5207 \u308a\u3055\u308c\u305f\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4 \u306b\u5bfe \u3057,\u304b \u307f\u5408\u3044\u8a66\u9a13\u3088 \u308a\u672c\u624b \u6cd5\u306e\u59a5\u5f53\u6027 \u3068\u5b9f\u7528\u6027\u3092\u691c\u8a0e \u3057\u305f.\n2. \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u8a2d \u8a08 \u30fb\u8a08 \u7b97 \u6cd5\n\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u88fd\u4f5c\u306b\u5fc5\u8981\u306a\u57fa\u790e\u8cc7\u6599\u3068\u3057\u3066,\u6b6f \u6570, \u30e2 \u30b8\u30e5\u30fc\u30eb,\u5727 \u529b\u89d2,\u53ca \u3073\u5927\u7aef\u76f4\u5f84\u3068\u5c0f\u7aef\u76f4\u5f84\u304c\u3042\u308b.\u3053 \u3053\n\u3067\u672c\u6765\u306e\u6b6f\u5f62 \u3068\u4e21\u76f4\u5f84\u306e\u53b3\u5bc6\u306a\u7406\u8ad6\u5f0f\u306f\u975e\u5e38\u306b\u8907\u96d1\u306b\u306a\u308b \u305f\u3081,\u901a \u5e38\u306e\u30dc\u30d6\u76e4\u3068\u5e02\u8ca9\u30db\u30d6\u306b\u3088\u308b\u6b6f\u5207\u308a\u3067\u306f\u7406\u60f3\u306e\u6b6f\n\u5f62\u5275\u6210\u306f\u4e0d\u53ef\u80fd\u3067\u3042\u308b.\u3057 \u304b \u3057\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u3068\u76f8\u624b\u30d4\u30cb\u30aa \u30f3\u3068\u306e\u9593\u3067,\u5b9f \u969b\u4e0a\u3055\u307b\u3069\u554f\u984c \u3068\u306a\u3089\u306a\u3044\u304b\u307f\u5408\u3044\u304c\u88fd\u4f5c \u3067\u304d\u308b\u306a\u3089\u5b9f\u7528\u7684\u4fa1\u5024\u306f\u3042\u308b\u3068\u8a00\u3048\u308b.\u305d \u306e\u305f\u3081\u306b\u4eee\u60f3\u306e\n\u8ee2\u4f4d\u6b6f\u8eca\u306b\u3088\u308b\u8fd1\u4f3c\u7684\u306a\u8a2d\u8a08 \u30fb\u8a08\u7b97\u6cd5\u3092\u8a66\u307f\u305f.\u305d \u306e\u57fa\u672c\n\u7684\u306a\u8003\u3048\u306f,\u5927 \u80c6\u306a\u4eee\u5b9a\u3067\u3042\u308b\u304c,\u56f31\u306e \u3088\u3046\u306b1\u679a \u306e\u5c0f \u6b6f\u8eca\u304c\u540c\u3058\u6b6f\u6570\u306e\u8907\u6570(\u56f3 \u3067\u306f3\u679a)\u306e \u76f8\u5f53\u5e73\u6b6f\u8eca\u3068\u30aa\u30d5 \u30bb \u30c3\u30c8\u306e\u4f4d\u7f6e\u3067\u304b\u307f\u5408\u3063\u3066\u3044\u308b\u3068\u8003\u3048\u308b.\u3053 \u3053\u3067G2\u306f \u30d5\u30a7 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G1 \u306f\u8ca0,G3\u306f \u6b63\u306e\u8ee2\u4f4d\u3068\u306a\u308b.\u3053 \u306e\u3088\u3046\u306b\u3059\u308c\u3070\u30d5\u30a7\u30fc\u30b9\n\u30ae\u30e4\u306e\u5927\u7aef\u76f4\u5f84\u3068\u5c0f\u7aef\u76f4\u5f84\u3092\u6c7a\u5b9a\u3059\u308b\u554f\u984c\u306f,\u5358 \u306a\u308b\u8ee2\u4f4d \u6b6f\u8eca\u306e\u554f\u984c \u3068\u306a\u308b.\u307e \u305f,\u6b63 \u306e\u8ee2\u4f4d\u65b9\u5411\u3067\u306f\u6b6f\u5148\u304c\u3068\u304c\u308a,\n\u8ca0\u306e\u8ee2\u4f4d\u65b9\u5411\u3067\u306f\u5207\u308a\u4e0b\u3052\u3092\u8d77\u3053\u3059.\u305d \u3053\u3067\u5927\u7aef\u306f\u6700\u5927\u3067 \u6b6f\u5148\u306e\u3068\u304c \u308a\u3092\u751f\u305a\u308b\u70b9\u304c\u9650\u754c\u3068\u306a \u308a,\u5c0f \u7aef\u306f\u6b6f\u306e\u5207\u308a\u4e0b\n\u3052\u3092\u3069\u306e\u3088\u3046\u306b\u6271 \u3046\u304b\u306b\u3088 \u3063\u3066\u9650\u754c\u304c\u6c7a\u5b9a\u3055\u308c\u308b.\u5143 \u6765, \u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306f\u6b6f\u5e45\u3092\u5927\u304d\u304f\u3068\u308c\u306a\u3044\u3068\u3044\u3046\u6b20\u70b9\u304c\u3042\u308b\u304c, \u3053\u3053\u3067\u306f\u3067\u304d\u308b\u3060\u3051\u5927\u304d\u304f\u3068\u308b\u3088\u3046\u306b\u8a2d\u8a08\u3059\u308b.\n\u56f32\u306f,\u57fa \u6e96\u30e9\u30c3\u30af\u3067\u6b63\u306e\u8ee2\u4f4d\u91cf\u3092X\u30fbm\u4e0e \u3048\u3066\u6b6f\u5207 \u308a\n\u3057\u305f\u306f\u3059\u3070\u6b6f\u8eca\u306e\u6b6f\u76f4\u89d2\u65ad\u9762\u3067\u3042\u308b.\u56f3 \u4e2d\u306e\u8af8\u8a18\u53f7\u306f * \u539f\u7a3f\u53d7\u4ed8 \u5e73\u62106\u5e74 6 \u6708 22 \u65e5\n* * \u6b63 \u4f1a \u54e1 \u5c71\u68a8 \u5927 \u5b66 \u5de5 \u5b66 \u90e8(\u7532 \u5e9c \u5e02\u6b66 \u75304- 3- 11 )\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 501", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\nRg: \u57fa \u790e \u5186 \u7b52 \u534a \u5f84 R0: \u57fa \u790e \u30d4 \u30c3\u30c1 \u5186 \u7b52 \u534a \u5f84\nRx: \u6b6f \u5f62 \u4e0a \u306e \u4efb \u610f \u306e \u534a \u5f84 Tg: \u57fa\u790e\u5186\u7b52\u4e0a\u306e\u5186\u5f27\u6b6f\u539a T0: \u57fa \u6e96 \u30d4 \u30c3\u30c1 \u5186\u7b52 \u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a\nTx: Rx\u4e0a \u306e \u5186 \u5f27 \u6b6f \u539a 2\u03c8g: \u5f27Tg\u306b \u5bfe \u3059 \u308b\u4e2d \u5fc3 \u89d2\n2\u03c80: \u5f27T0\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2\n2\u03c8x: \u5f27Tx\u306b \u5bfe \u3059 \u308b \u4e2d\u5fc3 \u89d2 \u03b1x: Rx\u4e0a \u306b \u304a \u3051 \u308b\u304b \u307f \u5408 \u3044 \u5727 \u529b \u89d2 \u03b10: \u5de5 \u5177 \u5727 \u529b \u89d2\n\u3092\u8868 \u3059.\n(a) \u5927 \u7aef \u76f4 \u5f84\n\u56f32\u3067 \u4efb \u610f \u306e \u534a \u5f84Rx\u306b \u304a \u3051 \u308b \u5186\u5f27 \u6b6f \u539aTx\u306f,X\u3092 \u8ee2 \u4f4d\n\u4fc2 \u6570 \u3068 \u3057\u3066\n( 1 )\n\u3067\u8868\u305b\u308b.\u307e \u305f\u57fa\u6e96\u30d4\u30c3\u30c1\u5186\u4e0a\u306e\u5186\u5f27\u6b6f\u539aT0 \u306f\n( 2 )\n\u3068\u306a \u308b.\u5f0f(1)\u306b \u5f0f(2)\u3092 \u4ee3 \u5165\u3059 \u308b \u3068\n( 3 )\n\u3068\u306a \u308b.\u5f93 \u3063\u3066,\u5927 \u7aef \u76f4 \u5f84 \u306f \u6b6f \u5148 \u306e \u3068\u304c \u308a\u3092\u9650 \u754c \u306b\u3059 \u308b \u306b \u306fTx=0\u3068 \u3059 \u308c \u3070 \u3088 \u3044.\u5f0f(3)\u3092inv\u03b1x\u306b \u3064 \u3044 \u3066 \u89e3\n\u304f\u3068\n( 4 )\n\u3068 \u306a \u308b.\u3053 \u3053\u3067\n( 5 )\n( 6 )\n\u3068\u3059 \u308b \u3068,\u76f8 \u5f53 \u5e73 \u6b6f \u8eca \u306e\u6b6f \u6570Zv\u306f,\u03b3 \u3092\u57fa \u790e \u5186 \u7b52 \u306d \u3058\u308c\n\u89d2 \u3068 \u3057\n( 7 )\n\u3068\u306a\u308b.\u307e \u305f\u4efb\u610f\u306e\u534a\u5f84Rx\u4e0a \u306e\u8ee2\u4f4d\u4fc2\u6570X \u306f\n( 8 )\n\u3067 \u8868 \u3055\u308c \u308b.\u3088 \u3063\u3066 \u5927 \u7aef \u534a \u5f84D0 \u306f\n( 9 )\n\u3088 \u308a\u6c7a \u5b9a \u3055 \u308c \u308b.\n(b) \u5c0f \u7aef \u76f4\u5f84\n\u5c0f \u7aef \u76f4 \u5f84 \u306e \u6c7a \u5b9a \u306b \u3064 \u3044 \u3066 \u306f,\u56f33\u306b \u793a \u3059 \u3088 \u3046 \u306b,\u6b6f \u306e\u5207 \u308a\u4e0b \u3052 \u3092 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5e73 \u9762 \u307e \u3067 \u751f \u3058\u3066 \u3082 \u826f\u3044 \u3068\u4eee\n\u5b9a5)\u3059 \u308b.\u8ca0 \u306e \u8ee2 \u4f4d \u304b \u3089,\u57fa \u6e96 \u5727 \u529b \u89d220\u309c \u306e \u5834 \u5408,\u5e73 \u6b6f \u8eca \u306e \u9650 \u754c \u6b6f \u6570 \u306fZmin=17\u3067 \u3042 \u308a,\u8ee2 \u4f4d \u4fc2 \u6570X \u306f\n( 10 )\n\u5f93 \u3063\u3066 \u5c0f \u7aef \u76f4\u5f84Di\u306f \u6b21 \u5f0f \u3088 \u308a\u6c42 \u307e \u308b.\npositive shift\n502 \u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u5893\u3064\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n( 11 )\n\u305f \u3060 \u3057,Z'\u306f \u5207 \u308a\u4e0b \u3052 \u3092 \u3069 \u3053 \u307e \u3067 \u8a31 \u3059 \u304b \u306b \u3088 \u3063\u3066 \u6c7a \u307e \u308b\n\u6b6f \u6570 \u3067,\u56f33\u306e \u5834 \u5408 \u3067 \u306fZ'=6\uff5e8\u306b \u3059 \u308c \u3070 \u3088 \u3044.\n(c) \u30aa \u30d5 \u30bb \u30c3 \u30c8\u4e0b \u3067 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84\n\u56f34\u306b \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3057\u3066 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84 \u306e \u5909 \u5316 \u306e\n\u69d8 \u5b50 \u3092 \u793a \u3059.\u56f3 \u4e2d \u306e \u5404 \u8a18 \u53f7 \u306f \u305d \u308c \u305e \u308c\na: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf Z: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e\u6b6f \u6570 \u03c9: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u89d2 \u901f \u5ea6\n\u03b2: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u89d2 R0: \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84 Ra: \u30aa \u30d5\u30bb \u30c3 \u30c8\u3067 \u5909 \u5316 \u3057\u305f \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84\nV0: \u534a \u5f84R0\u4e0a \u306e \u901f \u5ea6 Va: \u534a\u5f84Ra\u4e0a \u306e \u901f \u5ea6\n\u3092\u8868 \u3059.\u3053 \u308c \u3088 \u308a,\u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306b\u5bfe \u3057\u3066 \u5c0f \u6b6f \u8eca \u304c \u30aa \u30f3\u30bb \u30f3 \u30bf(P\u306e \u4f4d \u7f6e)\u306b \u304a \u3044 \u3066 \u306f,\u5c0f \u6b6f \u8eca \u306e \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84 \u306e \u6bd4 \u306f\u6b6f \u6570 \u306e \u6bd4(\u89d2 \u901f \u5ea6 \u306e \u6bd4)\u306b \u7b49 \u3057 \u304f\u306a \u308b \u304c,\u30aa \u30d5 \u30bb \u30c3 \u30c8 (\nP'\u306e \u4f4d \u7f6e)\u4e0b \u3067 \u306f \u4e21 \u534a \u5f84 \u306e \u6bd4 \u306f,\u306f \u3059 \u3070 \u89d2 \u306e \u5f71 \u97ff \u3092 \u53d7\n\u3051\u3066 \u5fc5 \u305a \u3057\u3082\u6b6f \u6570 \u306e \u9006 \u6bd4 \u306b\u7b49 \u3057 \u304f\u306f \u306a \u3089 \u306a \u3044.\u3059 \u306a \u308f \u3061 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3059 \u308b \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84Ra \u306f\n( 12 )\n\u3068\u306a \u308b.\u307e \u305f,\u5f0f(12)\u3067 \u03b2\u306e \u4ee3 \u308f \u308a\u306b \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf a\n\u3092\u7528 \u3044\u3066 \u8868 \u3059 \u3068\n( 13 )\n\u3068\u306a \u308b.\u305f \u3060 \u3057,\u30aa \u30f3\u30bb \u30f3 \u30bf\u3067 \u306fa=0\u3067 \u3042 \u308b.\u3088 \u3063\u3066 \u30d4 \u30c3\u30c1 \u5186\u76f4 \u5f84Dp \u306f\n( 14 )\n\u3067\u8868 \u305b \u308b.\u4ee5 \u4e0a \u304c \u8a2d \u8a08 \u6cd5 \u3067 \u3042 \u308b.\u6b21 \u306b \u5177 \u4f53 \u7684 \u8a08 \u7b97 \u6cd5 \u306f, \u307e\n\u305a \u5404 \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u306b\u5bfe \u3057\u3066 \u5f0f(13)\u3088 \u308aDp\u3092 \u6c42 \u3081 \u308b. \u305d \u306eDp\u306b \u5bfe \u3057\u5f0f(9),(10)\u3088 \u308aDo,Di\u3092 \u7b97 \u51fa \u3059 \u308b\n\u56f35\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e\u6b6f \u6570 \u3068 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u3067 \u5927 \u7aef,\u5c0f \u7aef \u76f4 \u5f84 \u304c \u3069\u306e \u3088 \u3046 \u306b\u5909 \u5316 \u3059 \u308b \u304b \u306e \u8a08 \u7b97\u7d50 \u679c \u3092\u793a \u3059.\u3053 \u308c \u3088 \u308a\n\u6b6f \u6570 \u304c \u5897 \u3059 \u3068,\u4e21 \u76f4\u5f84 \u304c \u5927 \u304d \u304f \u306a \u308b \u3068\u540c \u6642 \u306b\u4e21 \u76f4 \u5f84 \u306e \u5dee, \u3064 \u307e \u308a\u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b.\u307e \u305f,\u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u304c \u5927 \u304d \u3044 \u307b\n\u3069\u5927 \u7aef,\u5c0f \u7aef \u76f4\u5f84 \u53ca \u3073 \u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b \u3053 \u3068\u304c \u308f \u304b \u308b.\u3053 \u308c \u306f \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u306e \u5897 \u52a0 \u306b\u4f34 \u3044 \u30d4 \u30c3\u30c1 \u5186 \u76f4\u5f84 \u304c \u5927 \u304d \u304f\u306a \u308b \u304b \u3089\u3067 \u3042 \u308b.\u3057 \u304b \u3057\u306a \u304c \u3089\u6b6f \u6570 \u304c40\u679a,\u30aa \u30d5 \u30bb \u30c3 \u30c8 10\n\u30fbm\u306b \u5bfe \u3057\u6b6f \u5e45 \u306f5mm\u7a0b \u5ea6 \u3067 \u3042 \u308a,\u540c \u3058 \u304f\u6b6f \u6570140 \u679a\n\u3067 \u308210mm\u7a0b \u5ea6 \u3068\u6b6f \u5e45 \u304c \u72ed \u3044.\u3053 \u306e \u3053 \u3068\u306f \u5148 \u306b\u8ff0 \u3079 \u305f \u3088\n\u3046\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e1\u3064 \u306e \u6b20 \u70b9 \u3067 \u3082\u3042 \u308b \u308f \u3051 \u3067 \u3042 \u308b.\u3055 \u3089\npitch plane\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 503" + ] + }, + { + "image_filename": "designv8_17_0004400_e_download_7768_6705-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004400_e_download_7768_6705-Figure2-1.png", + "caption": "Fig 2. Finite element model of the helicopter rotor blade", + "texts": [ + " An investigated helicopter rotor blade (Fig 1) is equipped with NACA23012 airfoil and has a rectangular shape with active part radius 1.56 m and chord length 0.121 m. This rotor blade consists of D-spar made of unidirectional GFRP (Glas Fiber Reinforced Polymer), skin made of +450/\u2013450 GFRP, foam core, MFC actuators and balance weight. MFC actuators consist of piezoceramic fibres embedded in an epoxy matrix and sandwiched between polyamide films that have attached interdigitated electrode patterns as shown in Fig 2. The direction of piezoceramic micro-fibres in MFC coincides with the direction of outside GFRP skin layers. The thickness of skin GFRP layer is 0.125 mm and thickness of MFC layer is 0.3 mm. The material properties of the rotor blade components are as follows: \u2022 GFRP: Ex = 11.981 GPa, Ey = 11.981 GPa, Ez = 45.166 GPa, Gxz = 4.583 GPa, Gyz = 4.583 GPa, Gxy = 1.289 GPa, \u03c5yz = 0.238, \u03c5xz = 0.238, \u03c5xy = 0.325, \u03c1 = 2008 kg/m3. \u2022 Foam (Rohacell 51 FX): E = 0.035 GPa, G = 0.014 GPa, \u03c5 = 0.25, \u03c1 = 52 kg/m3. \u2022 Lead: E = 13.790 GPa, G = 2.000 GPa, \u03c5 = 0.44, \u03c1 = 11300 kg/m3. \u2022 MFC: Ex = 30.0 GPa, Ey = 15.5 GPa, Ez = 15.5 GPa, Gxz = 10.7 GPa, Gyz = 10.7 GPa, Gxy = 5.7 GPa, \u03c5yz = 0.4, \u03c5xz = 0.4, \u03c5xy = 0.35, d33 = 4.18\u00d710\u201310 m/V, d32 = d31 = \u20131.98\u00d710\u201310 m/V, \u03c1 = 4700 kg/m3. 3D finite element model of the rotor blade is produced by ANSYS (Fig 2), where rotor blade skin and spar \u201cmoustaches\u201d are modelled by the linear layered structural shell elements SHELL99, and spar and foam \u2013 by 3D 20 node structural solid elements SOLID186. The clamped boundary conditions are applied from one end-side of the rotor blade. Thermal strain analogy between piezoelectric strains and thermally induced strains is used to model piezoelectric effects, when piezoelectric coefficients characterizing an actuator are introduced as thermal expansion coefficients determined by the following relationship: , ES ij ij d \u0394 =\u03b1 where dij is the effective piezoelectric constant and \u2206ES is the electrode spacing (Fig 3) taken as \u2206ES = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000028__article-file_879665-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000028__article-file_879665-Figure4-1.png", + "caption": "Fig. 4. Top view of the rectangular MPA", + "texts": [ + " In this study, as a first step, a rectangular MPA for fr=1.575 GHz, \u03bb=0.19m with substrate material duroid (\u0190r=2.2) is designed. For maximum bandwidth substrate thickness (h) is chosen as 95 mm which is approximately 5% of wavelength (hmax=0.05 \u03bb=9.52mm). Patch width (W) and physical length (L) are calculated as 75.23 mm (Eq. 6) and 54.41 mm (Eq. 4), respectively, while extension length (\u0394L) is 4.86 mm (Eq. 2), which are given in Table 1. From the simulation results of the rectangular patch antenna (Fig. 4), it is observed that return loss S11=-24.06, the resonant frequency fr=1.498 GHz and the 10dB bandwidth is BW=135 MHz (Fig. 5) and VSWR=1.337 (Fig. 6). Then the proposed antenna with two quartercircular slots (centers on the top right and left corners of the rectangular patch), is designed (0.05L\u2264r\u22640.5L) (Fig 7). 10 different radius values are used for quarter-circular slots. And each model is simulated for 7 different h values. That is 70 simulations are performed for the designed antenna and fr and BW values are obtained to observe the impacts of circular slots (Table 2)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000967_rc14_07.10041904.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000967_rc14_07.10041904.pdf-Figure1-1.png", + "caption": "Figure 1. A reflectarray unit cell surface currents.", + "texts": [ + " Commercially available computer model of CST Microwave Studio has been used to design a unit cell patch element with proper boundary conditions in order to analyze the scattering parameters of an infinite reflectarray. Initially a reflectarray with rectangular patch element is designed to resonate at 10 GHz using Rogers RT/Duroid 5880 (\u03b5r = 2.2 and tan \u03b4 = 0.0010) as a substrate with thickness of 0.508 mm. Then different types of slot configurations are introduced in the patch element and the effect on the performance of the reflectarray was observed. The direction of port excitation and surface currents on a patch without slot is shown in Figure 1. It can be observed from Figure 1 that the maximum current on the surface of the patch occurs in the centre of the length of patch when the electric field is excited in the Y -direction. The phenomenon of the occurrence of maximum current in the centre of the patch element is shown in Figure 2(a) by simulating the reflectarray in commercially available computer model of CST Microwave Studio. In Figure 2(b), it has been clearly shown that the current on the surface of the patch element is significantly modified by the introduction of rectangular slot in the patch element" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001734_e_download_2825_3901-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001734_e_download_2825_3901-Figure8-1.png", + "caption": "Figure. 8. Critical displacement areas", + "texts": [ + "02663x 10-8 at 60% of the engine load, 5.93051 x 10-8 at 70% of the engine load, 5.8344 x 10-8 at 80% of the engine load, 5.78634 x 10-8 at 90% of the engine load and 5.54604 x 10-8 at full load. Moreover, at the critical stress areas (Figure 7), it shows the twist moment load of the most dominant stress on the shaft between the turbine and compressor seat also some areas of the compressor seat. The most critical area shown by the red color that lies at the end of the compressor seat. Nevertheless, the displacement critical areas (Figure 8) that occur on the turbocharger shaft with the same load more indicates close to another one end of the compressor seat. It is due to the throwing force as the function of the length of the shaft. Same as the critical areas of stress, the strain (Figure 9) results also indicate the most potentially highest strain is located on the shaft between the turbine and compressor seat. Also, the areas could be potentially located on the right end of the compressor seat. While for the safety of factor (Figure 10), indicates that the entire area of the turbocharger shaft is a critical area" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003103_26_tylek_203-215.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003103_26_tylek_203-215.pdf-Figure11-1.png", + "caption": "Fig. 11 Innovative design of an openable dibble on rockers \u2013 motion kinematics", + "texts": [], + "surrounding_texts": [ + "At the current stage of the project, a complete machine planting module has been designed (Adamczyk et al. 2019). It is composed of three main components (Fig. 8). The first one is a tool for planting spot prepa- ration. The second component is a movable dibble for placing seedlings in the soil. According to the assumed efficiency, the work of the machine should take place while travelling (without stopping), with the best possible vertical positioning of the seedling. The last element is a system of two pressing wheels with continuously adjustable geometry. The planting spot preparation tool is mounted in an oscillatory manner on the frame of the working unit via the first rocker arm and an actuator that allows adjusting the position and force of the tool pressing against the soil, while the pressing element is mounted on the frame by the second rocker, the position and pressure of which are regulated by a separate actuator. The main element of the planting unit is in the form of a cylindrical dibble connected to the carriage, which is mounted slidably in relation to the frame and is moved in relation to it along the horizontal axis by means of an independent drive. Ultimately, the planting module is to be mounted on a specialised, autonomous carrier, while in the case of aggregating the module with agricultural or forestry tractors, the frame of the working unit should be equipped with an appropriate levelling system. The developed conceptual model of such a solution is presented in Fig. 9. Attached to the frame in its rear part, there is an adjustable swing axle with support wheels and, in its front part, a swing hitch to the tractor. Levelling is performed by analysing the indications from the acceleration sensor (gravity sensor) mounted to the frame of the working unit. Fig. 10 and 11 below show an openable dibble in which the jaws and the cylinder are opened by one drive. The appropriate kinematics is ensured by rockers with pivots placed at an angle, thanks to which the opening occurs as a result of lifting the movable parts of the dibble. The recessed part is characterised by Croat. j. for. eng. 44(2023)1 209 relatively high slenderness which minimises the resistance during penetration into the soil. The fixed part of the dibble remains in contact with the ground until the dibble is fully open, which ensures proper following of the ground during continuous operation of the machine. In the first working phase, a seedling is fed to the dibble, placed in the upper position with its jaws closed, stationary relative to the frame. The seedling is fed by a guide constituting part of the carriage. It moves along the cylinder (by gravity or thanks to the forced flow of compressed air) until it rests on the inner walls of the jaws. Then the dibble is driven into the soil, with the simultaneous commencement of the movement following the ground: the dibble moves downwards in relation to the carriage and towards the back of the frame. After placing the dibble in the soil, the jaws are opened and the dibble is lifted until the entire plant comes out of the cylinder. At this point, the carriage is moved back to its starting position relative to the robot\u2019s frame, the jaws are clamped again, and a new cycle begins. Elements of the module control system are presented in Fig. 12. The valve coils of the hydraulic actuators, the sensors and additional buttons for operating the module are connected to the controller. The device can be controlled directly from the display by re-setting selected sections or by running the programme in the automatic mode. The operation of the device in the automatic mode is divided into several stages. In the first stage, the condition of compliance of the current position of the device with the initial, transport position is checked: the dibble is raised, the crane is moved to the left, the gripper jaws are clenched. Depending on the indications of inductive sensors mounted on the crane, the gripper and the piston position sensor, the controller generates a voltage signal to the electric valves responsible for the operation of the crane section, the dibble and the gripper until the device is in its initial, transport position. In the next stage, the controller starts counting the time needed to place the seedling in the dibble gripper. After 2 seconds, the controller goes on to the third step. The third step also consists in checking the pressure in the hydraulic system and the output state of the inductive sensor mounted at the opposite end of the crane, which provides information about reaching its extreme position. If the pressure exceeds 200 bar or if the inductive sensor changes its state to high, the dibble stops penetrating into the soil, rises and returns to the transport position. Then, after reaching the starting position, it proceeds without waiting for the second step. In the fourth step, the 210 Croat. j. for. eng. 44(2023)1 controller sends a signal to the electric valve responsible for opening the dibble jaws. This step is performed until one of the inductive sensors mounted on the gripper changes its state, i.e. one of the gripper jaws opens. At this point, the controller moves to step five, in which the controller sends a signal to the electric valve responsible for lifting the dibble. This step is performed until the piston rod of the dibble actuator reaches the position of less than 50% of the maximum extension. In the sixth step, the controller continues sending a signal to the electric valve responsible for inserting the dibble actuator piston rod, lifting the dibble in this way, and a signal is sent to the electric valve which controls the hydraulic valve of the engine crane. Signals to the electric valves are sent until the crane is in the transport position \u2013 moved to the extreme left, while the dibble is raised. In step seven, the controller sends a signal to the electric valve responsible for closing the gripper. After this step, the process starts all over again: the controller returns to the first step and the cycle of planting the next seedling is initiated (Tylek et al. 2021a). A pilot study of the planting module (Fig. 12) shows that operation in the automatic mode in partially prepared terrain (the soil loosened, with a low coefficient of compactness, and a fairly level surface) satisfies the functional requirements. In the case of planting seedlings of coniferous species (pine, spruce), the work efficiency of the planting module was equal to 14.3\u00b12.7 seedlings/min. For deciduous species (oak, beech) it was lower and amounted to 9.1\u00b13.2 seedlings/min. In this case, the performance was characterised by significantly higher variability. This corresponds to planting in a previously prepared reclaimed area. During the machine\u2019s operation under real conditions in the forest, the dibble will work in the terrain with an irregular profile; therefore, it will be necessary to provide information about the exact penetration of the dibble into the ground. An ultrasonic sensor or a limit switch can be used for this purpose. The aim of further research will be to find out which of the sensors is better suited for this purpose." + ] + }, + { + "image_filename": "designv8_17_0000615_.1117_12.2308193.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000615_.1117_12.2308193.pdf-Figure12-1.png", + "caption": "Fig. 12 Section of wheel showing buttons", + "texts": [ + " Component details are as under. 3 mm thick Aluminum 6061-T651 plate as base simulating filter wheel material Aluminum 6061-T651 clamps on the two ends of the germanium filter, fixed with the base RTV sandwiched between the filter and the clamps Rectangular germanium piece 80mm long x 25 mm wide x 5 mm thick. Wheel was realized from Aluminium 6061-T651, for circular germanium filters. All 18 Filters were integrated. Wheel has 0.5 mm raised buttons coplanar within 0.05mm as interface with the mounts, as shown in Fig. 12. They ensure specified alignment of filters with reference to optical axis. In order to validate the finalized design of Soft mount, two stage qualification was carried out, first at mount level and subsequently at wheel level. Lastly, wheel underwent qualification tests as part of integrated EOM also. Assembly was put into the chamber and subjected to thermal excursions between 180K and 303K. Dwelling at both the extreme temperatures was done for 60 minutes. Temperature was monitored at base and filter" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002715_200-1-PB.pdf_id_3300-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002715_200-1-PB.pdf_id_3300-Figure5-1.png", + "caption": "Fig. 5. Carrying structure (portal) of type \u2033\u0397\u2033", + "texts": [ + " 2: M m g L L m L L L dyn,s r r r b r = 2 2 2 2 +( ) + \u2212( ) \u03c8 \u03c8 \u03c8 \u03c8 \u03c8 \u03b1 \u03c8 cos sin sin sin cos . (15) 3 FINITE ELEMENT MODEL OF THE STRUCTURE 3.1 Model Description The whole portal-rotating crane is divided into two subsystems: the moving structure, and the boom. The relationship between the structure and the boom is simplified in such a way that the influence of load and the dead weight of the boom is reduced to the points of the upper and lower supports of the boom. The type \u0397 carrying structure of the considered portal crane is shown in Fig. 5. 596 Vasiljevi\u0107, R. \u2013 Ga\u0161i\u0107, M. \u2013 Savkovi\u0107, M. The carrying structure is a rigid spatial frame. Its base has dimensions L\u00d7B. The main structural parts of the carrying structure are the legs, the slanted columns, and the lower and the upper beams. The legs are identical (height H) and stand at the same level. The slanted columns are identical (length C) and they are connected to the legs as well as to the upper and lower beams. The distance between the upper and the lower beams is equal to H0. The upper beam has the function of the upper support of the boom, and it is made of a circular ring with the diameter D" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002684_f_version_1565510199-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002684_f_version_1565510199-Figure12-1.png", + "caption": "Figure 12. Prototype processing. Figure 12. Prototype processing.", + "texts": [ + " When the copper layer thickness is greater than 0, the power factor is considerably improved because eddy current effects are generated in the copper layer, and the power factor increases when the copper-clad rotor is used. In addition, the amplitude of the stator current at full load is only slightly increased compared with the amplitude of stator current at no load, indicating that the motor can work for a long time under large slip conditions. The calculation result of ECM has good consistency with the calculation results of FEM, and the maximum error does not exceed 15%. 5. Experimental Verification A non-copper plating prototype is built (as shown in Figure 12) to verify the accuracy of the results presented above, and experimental tests are conducted. The motor experimental platform is shown in Figure 13. The speed and torque of the prototype were measured with a torque-speed sensor. The load torque is provided by the eddy current brake and the eddy current brake and measuring instrument are connected by the coupling. The power supply of the prototype is provided by Frequency converter. Another copper plating prototype is being processed and will be presented in future research", + " When the copper layer thickness is greater than 0, the power factor is considerably improved because eddy current effects are generated in the copper layer, and the power factor increases when the copper-clad rotor is used. In addition, the amplitude of the stator current at full load is only slightly increased compared with the amplitude of stator current at no load, indicating that the motor can work for a long time under large slip conditions. The calculation result of ECM has good consistency with the calculation results of FEM, and the maximum error does not exceed 15%. 5. Experimental Verification A non-copper plating prototype is built (as shown in Figure 12) to verify the accuracy of the results presented above, and experimental tests are conducted. The motor experimental platform is shown in Figure 13. The speed and torque of the prototype were measured with a torque-speed sensor. The load torque is provided by the eddy current brake and the eddy current brake and measuring instrument are connected by the coupling. The power supply of the prototype is provided by Frequency converter. Another copper plating prototype is being processed and will be presented in future research" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure12-1.png", + "caption": "Fig. 12. The characteristic solution of single-stage gear reducer with vertical shafts arrangement foot and flange-mounted way (STM TEAM solution) [18].", + "texts": [ + " In this way, the gearbox can be mounted with horizontal shaft arrangement, but also in vertical shaft arrangement. The additional opening is added through which the gears are mounted and it is closed by a cover. In order to increase the versatility of this gearbox, an additional flange is created on the front surfaces of the housing (Fig. 10). Single-stage universal gear reducers with vertical shaft arrangement are today more common in practice. They are produced with a different way of connecting: foot-mounted gearbox (Fig. 11a), flange-mounted gearbox (Fig. 11b) and foot and flange-mounted gearbox (Fig. 12). Gear reducers with vertical shaft arrangement have a simpler machining processing, but assembling is a bit complicated. Some manufacturers that produce gear reducers in small series, practice using an universal housing with feet or flange connected by screws. The housings of single-stage gear reducers with free shaft arrangement (but also all other arrangements) are manufactured as rounded (Fig. 13), but also as squared (Fig. 14). When they are assembled with a hollow shaft, they are called shaft-mounted gear units", + " 10 and 15) presents the most universal gear reducer. This type of reducer is adapted for all positions and ways of mounting, but at the same time, it is the most expensive due to extensive machine processing and the largest consumption of materials. Therefore, their intensive development could not be expected further, but they will be produced by an only small number of manufacturers to satisfy operating requirements. Gear reducers with vertical shaft arrangement footmounted (Fig. 21), flange-mounted (Fig. 22) and foot and flange-mounted (Fig. 12) are probably the most basic positions of mounting that will be required in future due to relatively low production costs, suitable form and low cost of materials. Other forms are less required and they are produced by smaller manufacturers who want to cover the market segment which is not covered by large manufacturers. Further intensive development of shaft-mounted single-stage gear reducers can be also expected. Their installation doesn\u2019t require flanges at the output shaft which provide cheaper construction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000161_om_article_21583_pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000161_om_article_21583_pdf-Figure2-1.png", + "caption": "Fig. 2. Scheme of the intermittent motion planetary mechanism", + "texts": [ + " This provides the intermittent motion of the output shaft. The aim of the paper is theoretical and experimental kinematic study of the proposed planetary mechanism with elliptical gears. 124 JOURNAL OF MEASUREMENTS IN ENGINEERING. SEPTEMBER 2020, VOLUME 8, ISSUE 3 The proposed mechanism is characterized by the following main parameters: radius \ud835\udc45 = \ud835\udc51 2\u2044 of the sun spur gear, radius \ud835\udc45 = \ud835\udc51 2\u2044 of the satellite spur gear, semi-major axis \ud835\udc4e, minor axis \ud835\udc4f, eccentricity \ud835\udc52 and focal distance \ud835\udc50 of elliptical gears (Fig. 2). As can be seen from Fig. 2, to ensure intermittent motion of the output link, the dimensions of the cylindrical and elliptical gears are related by the following equations: \ud835\udc45 = \ud835\udc4e + \ud835\udc50, (1)\ud835\udc45 = \ud835\udc4e \u2212 \ud835\udc50. (2) To conduct a kinematic analysis of the proposed mechanism, there is constructed positions and linear velocities plans of mechanism links (Fig. 3) [26, 28]. Intermittent motion of the output link in this case is achieved by the fact that point D on the velocity plan will not intersect the zero line. The vector CC' from the point C lying at the same level as the point C in the mechanism scheme shows the velocity of the carrier point C" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002983_f_version_1677124185-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002983_f_version_1677124185-Figure3-1.png", + "caption": "Figure 3. Overall configuration of the illustrative aircraft.", + "texts": [ + " The turbojet mode is assumed to operate up to Ma = 3; above Ma = 3, the ramjet mode starts to work and operates up to Ma = 6; above Ma = 6, the scramjet mode operates. The fuel of the propulsion system is liquid hydrogen. Figure 2. Diagram of propulsion system. To balance the aerodynamic performance between low speeds and high speeds, and to accommodate the fuel and the payload, a blended wing body configuration with a low aspect ratio wing is selected for the illustrative aircraft. As shown in Figure 3, the engine is mounted under the blended wing body and the surface of fuselage in front of the engine Figure 1. Mission profile of the illustrative aircraft. According to the above performance requirements and mission profile, the illustrative aircraft should have the ability to accelerate from subsonic to hypersonic and fly from low altitude to high altitude. Conventional engines like the turbojet are obviously unable to complete this mission. Extensive research on airbreathing propulsion systems for hypersonic aircraft have been conducted since the 1960s [23]", + " The propulsion system can work in three different modes: turbojet, r mjet, and scramjet. The turbojet mode is assumed to operate up to Ma = 3; above Ma = 3, the ramjet mode starts to work and operates up to Ma = 6; above Ma = 6, th scramjet mode operate . The fuel of the propulsion syste is liquid hydrogen. Figure 2. Diagram of propulsion system. To balance the ic performance between low speeds and high speeds, and to accommodate t the payload, a blen ed wing body configuration with a low aspect ratio wing is for the illustrative ai craft. As shown in Figure 3, the engine is mounted under t e le e ing body and the surface of fuselage in front of the engine Figure 2. Diagram of propulsion system. To balance the aerodynamic performance between low speeds and high speeds, and to accommodate the fuel and the payload, a blended wing body configuration with a low aspect ratio wing is selected for the illustrative aircraft. As shown in Figure 3, the engine is mounted under the blended wing body and the surface of fuselage in front of the engine is al ost flat, which makes the air intake more uniform and stable. A vertical tail is located on the rear of the fuselage to ensure lateral-directional stability and control. Aerospace 2023, 10, 199 5 of 20 Aerospace 2023, 10, 199 5 of 20 is almost flat, which makes the air intake more uniform and stable. A vertical tail is located on the rear of the fuselage to ensure lateral-directional stability and control. . Figure 3. Overall configuration of the illustrative aircraft. 3. Method of Initial Sizing The task of the initial sizing is to estimate the aircraft takeoff gross weight, empty weight, fuel weight, planform area, volume, and required thrust of the TBCC engine (three modes). The initial sizing method consists of weight and volume estimations, the constraint analysis for the thrust-to-weight ratio, and the wing loading. Additionally, the engine characteristics and aerodynamic characteristics should be reasonably estimated by approximate models", + " Aerospace 2023, 10, 199 12 of 20 3.4.2. Model of Aerodynamics Characteristics Usually, the assumption for aerodynamic characteristics in initial sizing is based on the aerodynamic data of existing aircraft. However, for the airbreathing hypersonic aircraft, the aerodynamic data published are very limited. In this study, the aerodynamic characteristics of the illustrative aircraft are obtained from a rapid prediction method for the given configuration. For the configuration of the illustrative aircraft as seen in Figure 3, a rapid aerodynamic prediction program [33], which is based on Euler equations, is applied to get non-viscous lift and drag. The viscous drag is estimated using the Eckert\u2019s reference temperature methods and the Van Driest II formula [34]. For the illustrative aircraft, the lift coefficient (CL) and drag coefficient (CD) at the different Ma are estimated and shown in Figure 7. The data of those coefficients are fitted by the following equations: CL = CL\u03b1 \u00b7 \u03b1 + CL0 (20) CD = CDmin + K\u2032C2 L + K\u2032\u2032(CL \u2212 CLmin) 2 = K1C2 L + K2CL + CD0 (21) where CL\u03b1 is lift-curve slope; CL0 is lift coefficient when \u03b1 is zero; CDmin is the minimum drag coefficient; K\u2032 is the inviscid drag due to lift; K\u201d is the viscous drag due to lift; CLmin is lift coefficient at CDmin; K1 = K\u2032+ K\u2032\u2032; K2 = \u22122K\u2032\u2032CLmin; and CD0 is the drag coefficient at zero lift, CD0 = CDmin + K\u2032\u2032C2 Lmin" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001667_article_25876638.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001667_article_25876638.pdf-Figure2-1.png", + "caption": "Fig. 2 Sketch map of Air-Launch", + "texts": [ + " Named after system unlocking and before the rocket centroid move out of cabin for the first stage-- cabin traction phase (Case1), from rocket centroid out of cabin to rocket completely depart from cabin for the second stage-- rotating out of cabin phase (Case2), the phase after the separation of carrier and rocket for the third stage\u2014separation phase (Case3). And make the stage that carrier leveling before the system unlock for the airdrop preparation phase (Case0). The airdrop process is shown in figure.2. The function of the internal air launch vehicle is to achieve the successful launch of the rocket under certain conditions. And achieving the ignition condition of predetermined index is the premise of the successful launch, therefore launching performance can be defined as: in the case of characteristic parameters determination, the ability that achieve the successful launch. In order to determine the emission performance, we should determine the characteristic parameters of the system and the ignition condition, the structure and function of comprehensive system must be considered" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004230_f_version_1525350108-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004230_f_version_1525350108-Figure2-1.png", + "caption": "Figure 2. Geometry of the HDI-based 5G filtering patch radiator: (a) 3D and (b) top views.", + "texts": [ + ", y-oriented) field must be radiated within the angular region \u03c6 \u2208 [\u221260, 60] (deg) \u222a \u03b8 \u2208 [75, 105] (deg), the axial ratio and the ellipticity angle being AR (\u03b8, \u03c6) \u2265 20 dB and |\u03c7| \u2264 10 deg, respectively (the axial ratio being defined as AR (\u03b8, \u03c6) = \u03b31(\u03b8, \u03c6) \u03b32(\u03b8, \u03c6) , while the (broadside) ellipticity angle is equal to \u03c7 = arctan [ \u03b32(\u03b80, \u03c60) \u03b31(\u03b80, \u03c60) ] , \u03b31 (\u03b8, \u03c6) and \u03b32 (\u03b8, \u03c6) being the major and the minor axes of the polarization ellipse in the (\u03b8, \u03c6) direction, respectively\u2014Table 1). In order to fit all these radiation requirements subject to the assigned geometrical constraints (Table 1), the geometry of the elementary radiator shown in Figure 2 has been properly synthesized by considering a two-layer structure and the HDI fabrication [15] as dictated by the customer. Accordingly, off-the-shelf HDI dielectric boards have been adopted. In more detail, the bottom feeding substrate is a ground-backed Laminate R-5785(N) with relative permittivity \u03b5 f = 3.34, dielectric loss tangent tan \u03b4 f = 3.0\u00d7 10\u22123, and thickness d f = 0.5 mm, while the top layer is Prepreg R-5680 with \u03b51 = 3.6, tan \u03b41 = 4.0\u00d7 10\u22123, and d1 = 0.132 mm (Figure 2a). A microstrip line of length b and width a has been etched on top of the feed substrate and it is used to excite the overlying (solid) radiating patch. Concerning the latter, its shape has been modeled with a spline-based technique [16] to increase the set of possible patch shapes without recurring to complex or huge-number of DoF descriptors and allow an effective fitting of all performance requirements (Figure 2b). To force a geometrical/electric symmetry, only one half of the patch contour has been optimized by setting a set of K = 8 control points for the spline curve, pk = (yk, zk), k = 1, ..., K (Figure 2b), points p2, ..., p7 being automatically mirrored with respect to the (x, y) symmetry plane (Figure 2b). The geometrical descriptors of the single radiator, \u0398 = {a, b} \u222a {(yk, zk) , k = 1, ..., K} (Figure 2), have been determined by means of a customized PSO devoted to minimize a cost function quantifying the mismatch between requirements and performance of the synthesized arrangement of trial radiating elements. It is worth pointing out that the PSO has been chosen because of its well-known effectiveness and computational efficiency in dealing with nonlinear/non-differentiable cost functions and real-valued search-spaces [17\u201324], making it more suitable for the design problem at hand with respect to, for instance, genetic algorithms (GAs), which are more effective to deal with discrete/binary search spaces [17]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002883_9393742_09393751.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002883_9393742_09393751.pdf-Figure1-1.png", + "caption": "Fig. 1. 3D view of ADS-SRM.", + "texts": [ + " Finally, the magnet demagnetization analysis on the Study on Magnetic Shielding for Performance Improvement of Axial-Field Dual-Rotor Segmented Switched Reluctance Machine Wei Sun, Student Member, IEEE, Qiang Li, Le Sun, Member, IEEE, and Xuefeng Jiang, Member, IEEE S SUN et al: STUDY ON MAGNETIC SHIELDING FOR PERFORMANCE IMPROVEMENT OF AXIAL-FIELD DUAL-ROTOR 51 SEGMENTED SWITCHED RELUCTANCE MACHINE rare-earth and ferrite PM-shield ADS-SRMs is implemented through 3D FEM and the lumped-parameter thermal network (LPTN) models. II. INTRODUCTION OF PM-SHIELD ADS-SRM A. Introduction to ADS-SRM The 3D view of ADS-SRM is shown in Fig. 1 [21]. As shown in Fig. 1(a), the machine consists of a single internal stator and two external rotors. As shown in Fig. 1(b), epoxy potting under the vacuum condition is applied to the phase windings, and therefore, all the stator parts are assembled robustly. Besides, all eight rotor segments at each side are inserted in a nonmagnetic rotor bracket. Fig. 1(c) shows the prototype of ADS-SRM. The specifications and main geometric parameters are given in Table I. The flux density distributions at the phase excitation of 8A near typical rotor positions, i.e. unaligned and aligned rotor positions, are shown in Figs. 2(a) and 2(b), respectively. It is found that the leakage field is significant near unaligned rotor position, especially between the excitation pole and the flux-conductive rings. For better reflection of the flux leakage, 2D FEM is carried out on the 2D analysis model plot in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004335_.srce.hr_file_403527-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004335_.srce.hr_file_403527-Figure1-1.png", + "caption": "Figure 1. Fiber orientation", + "texts": [ + " Plastomers: - Polyethylene (PE) - Polypropylene (PP) - Polyamide (PA) - Acrylonitrile butadiene styrene plastic (ABS) Duromers: - Epoxy resin - Vinyl-ester resin - Polyester resin 183Pomorski zbornik Posebno izdanje, 181-199 Epoxy resin is most commonly used as a matrix in carbon fiber reinforced composites. The properties of such a composite largely depend on the length and diameter of the carbon fibers, the fiber orientation, the fiber to matrix ratio in the composite, and the mechanical properties of the fibers and matrix themselves. Figure 1 shows some of the possible orientations of the carbon fibers in the matrix. Carbon fiber composite laminates often contain imperfections that can cause damage due to external loads. In order to eliminate the possibility of damage, it is necessary to examine the laminate. Test methods are divided into invasive and noninvasive. Invasive methods are also destructive methods because a sample is taken for testing the laminate, and the sampling itself creates damage in the laminate. For composite materials, non-invasive laminate testing methods are far more acceptable" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002182_om_article_19326_pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002182_om_article_19326_pdf-Figure5-1.png", + "caption": "Fig. 5. Surgical retractor tip model", + "texts": [ + " Details regarding this rapid concept to prototype are outlined in a prior publication [4]. However, a fully functional handle and wire actuating mechanism was successfully 3D printed. The tip mechanism was then prototyped at Nagasaki University by machine specialists and the fully functional retractors were evaluated by medical staff and the functionality and operating dynamics were confirmed during an operation on a porcine lung which closely resembles human lungs. 1196 \u00a9 JVE INTERNATIONAL LTD. JOURNAL OF VIBROENGINEERING. MAR 2018, VOL. 20, ISSUE 2. ISSN 1392-8716 Fig. 5 shows the multi-joint articulated mechanism modelled in 3D-CAD and Table 1 indicates the component sizes, each finger consists of an articulated set of plates that are wire actuated from both sides to permit the bending and straightening of the fingers. The design is such that when the fingers are aligned and straightened they can pass through a 12-mm trocar. Each of the three joints provides 30 degrees of articulation providing a total curvature of 90 degrees. Fig. 6(b) shows a cross section of the articulating tip mechanism" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000403_citation-pdf-url_382-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000403_citation-pdf-url_382-Figure8-1.png", + "caption": "Figure 8. Components for the Design of Structures with the Same Features as the Delta Robot. (Courtesy of Brogardh, T, 2000).", + "texts": [ + " The joints can be implemented as ball and socket bearings, which makes it possible to obtain high precision in addition to high stiffness and low mass for the joint arrangement. 4. The actuated platform is positioned with 3 translational DOFs in a parallel fashion without angular displacement. Systematic clustering of the links connected to the actuated robot platform has been studied. Based on this design approach new parallel arm structures have been identified and some new robot concepts have been found (Brogardh, T, 2000). Figure 8 shows schematically the basic components needed to achieve the Each of the links of type B (Figure 8) can be connected to one or more of the links of type A. One could say that each link of type B can be connected to a cluster of links of type A and it is possible to introduce a simple clustering scheme, where for example 2/2/2 means that the links of type A are clustered with 2 links to each of the 3 links of type B. To achieve parallel movements of the actuated platform (to preserve the tilt angles), type A links belonging to the same cluster must be parallel and have the same length. Moreover, to avoid a A new class of parallel robot, namely, TAU robot, has been created based on the 3/2/1 configuration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003554__AME_2021_138393.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003554__AME_2021_138393.pdf-Figure4-1.png", + "caption": "Fig. 4. Input parameters for stress and displacement testing on the webs", + "texts": [ + " The stress and displacement of two gear pairs are investigated when the hole diameters on the webs of gears 4 and 6 change between 40\u201355 mm and 10\u201320 mm, respectively, and the hole number changes from 4 to 8. The input parameters and calculation results for the case of the maximum hole number and the maximum hole diameters that still satisfy the required conditions are shown in Figs. 4\u20136. The required conditions are stress and displacement conditions and the dimensional relationship conditions between the holes and the gear web to satisfy the working principle of the winch. In Fig. 4, the force acting on the tooth is placed in an area calculated according to the gear design theory. The pressure caused by the interference joint is also applied. Using Ansys software, the computational model meshed with the size of 0.15 mm \u00d7 0.15 mm, 0.5 mm \u00d7 0.5 mm, and 2 mm \u00d7 2 mm on where the force is applied on the tooth surface, the neighborhood of the first place, and others, respectively. The maximum stresses and displacements on the webs and gear roots in Figs. 5 and 6 show that they are within allowable limits" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004319_echaterobot_download-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004319_echaterobot_download-Figure4-1.png", + "caption": "Figure 4. Detail of the robotic wrist variant no. 3", + "texts": [], + "surrounding_texts": [ + "This variant is a combination of the preceding variants and it features all of their advantages such as simple structure and a relatively low height." + ] + }, + { + "image_filename": "designv8_17_0000920_f_version_1693378799-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000920_f_version_1693378799-Figure3-1.png", + "caption": "Figure 3. Schematic representation of waveguide feeding structures: (a) top- or bottom-mounted coaxial probe (transition A); (b) edge-mounted coaxial probe (transition B); (c) microstrip line to waveguide (transition C).", + "texts": [ + " In the final step, the two designed structures are joined together, and the antenna dimensions are fine-tuned. One could also design the feeding structure and the antenna part together. However, in such a case, there is a non-negligible possibility of designing the antenna as a resonator loaded with radiating slots (note that the considered waveguide section is short-circuited at both sides; see Figure 2), leading to narrow operating bandwidth design. In this section, we discuss three different types of feeding transitions, as shown in Figure 3: \u2022 Transition A: Top- or bottom-mounted coax-to-waveguide transition; \u2022 Transition B: Edge-mounted coax-to-waveguide transition; \u2022 Transition C: Microstrip line-to-waveguide transition. The width and height of the waveguide are denoted as a and b, respectively, while the permittivity of the waveguide filling is denoted as \u03b5r. Two types of molds were considered: a rigid mold with a height of b = 15.8 mm (made from Styrodur) and a bendable mold with a height of b = 6.35 mm (made from foam PF-4). Final waveguide dimensions are provided in Table 1", + " Figure 5 shows the calculated S11 parameters of transitions B for both types of molds. As shown in Figure 5, both wire-fed and strip-fed transitions B provide matching in the 5.8 GHz ISM band. In general, a strip-fed shorting elbow tends to provide better impedance matching compared to a wire-fed shorting elbow. This is because the strip provides a larger surface area for the EM wave to couple into the waveguide, resulting in improved power transfer and reduced reflection. The final considered transition is a microstrip line-to-rectangular waveguide transition, as shown in Figure 3c. The transition includes an SMA connector, a 50 \u2126 microstrip transmission line, and a linear microstrip taper. Since in this case, radiation losses are present, a symmetrical two-port cascade network of the waveguide and transitions (as shown in Figure 3c) was analyzed in order to design the transition. The taper width (w) was obtained using the CST optimizer tool with the goal of maximizing the S21 parameter at the central frequency of 5.8 GHz. The taper length should be a multiple of a quarter of a guided wavelength [24,25], and the best performance is obtained with tapers that are 3\u03bb/4 long. The taper dimensions of transition C obtained by optimization are listed in Table 4. Figure 6 shows the simulated S11 and S21 parameters of a double-cascaded transition network" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003081_le_download_1199_891-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003081_le_download_1199_891-Figure6-1.png", + "caption": "Fig. 6. Results of Meshing Models With Mesh Quality Indicators", + "texts": [ + " Figure 5 shows the final result of making the connection model. After that, the model will be converted from an STL file into a Solid Part before the model analysis process is carried out. The meshing process was generated manually with an input element size of 2 mm, where the size produced a good-quality mesh. It can be seen that the majority of the mesh results are on a scale interval of 0.13 - 0.38 for quad4 and tri3-shaped elements. According to the Skewness scale, the closer to 0, the mesh quality is classified as good (Emzain et al., 2021). Figure 6 shows the results of the meshing model with mesh quality indicators. Boundary conditions for fixed support applied were on the top area of the model except for the ventilation holes starting from the back of the palm to the back of the arm. On the opposite side, especially in the area around the wrist to the tip of the palm, a force was applied with loading ranging from 0 to 30 N. This interval force is assumed to occur when the model is applied to the patient's hand for fixation. Figure 7 shows the boundary conditions of the wrist-hand orthosis model" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003220_20JIYE_G1103158C.pdf-Figure2.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003220_20JIYE_G1103158C.pdf-Figure2.6-1.png", + "caption": "Figure 2.6 Simplified Raman spectrometer layout", + "texts": [ + "1 Internal forces in a solid body under a self-equilibrating system of forces.. 8 Figure 2.2 Positive normal and shearing stresses .......................................................... 9 Figure 2.3 LOCOS birds beak ..................................................................................... 14 Figure 2.4 Schematic of a fully filled TSV structure near the wafer surface .............. 16 Figure 2.5 Inelastic scattering in Raman Spectroscopy ............................................... 19 Figure 2.6 Simplified Raman spectrometer layout ...................................................... 20 Figure 2.7 Line profile of a spectral line shows the line wings and line kernel .......... 21 Figure 2.8 (a) Damped oscillation (b) Fourier transformation of ( )x t indicates the intensity 2 0( ) ( )I A ....................................................................................... 23 Figure 3.1 Process flow (a) 100 \u00c5 thermal oxide deposition;(b) Boron implantation; (c) 8 k\u00c5 CVD oxide; (d) via formation by DRIE Si etch and using oxide as the hard mask; (e) liner deposition; (f ) Ta barrier/Cu seed deposition, Cu-ECP, Cu-CMP and nitride passivation layer deposition; (g) contact opening; and (h) Al metallization and patterning" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000302_f_version_1554344750-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000302_f_version_1554344750-Figure5-1.png", + "caption": "Figure 5. Cavity shortwave radiometer solid model cross section.", + "texts": [ + " Figure 4 shows a cross section of the VACNT shortwave radiometer along with a photograph of the detector prior to integration. The heatsink mounts provide thermal isolation from the spacecraft; they are made of Ultem R\u00a9\u2014a very strong plastic with low thermal conductivity. The sapphire dome is soldered to the heatsink and maintains a stable longwave infrared background. Sapphire was chosen over quartz for its high thermal conductivity, which minimizes temperature gradients. The analogous cavity SW radiometer is shown in Figure 5. Details of the temperature sensing and electronics used in RAVAN\u2019s radiometers are found in Appendix B. Figure 2, below, shows a cross section of a VACNT shortwave radiometer along with a photograph of the detector prior to integration. Both the baffle and the heatsink are screwed to the spacecraft, which is not shown. The heatsink mounts provide thermal isolation from the spacecraft; they are made of Ultem\u00ae\u2014a very strong plastic with low thermal conductivity. The sapphire dome is soldered to the heatsink and maintains a stable long wave infrared background" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002313_f_version_1692366120-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002313_f_version_1692366120-Figure4-1.png", + "caption": "Figure 4. Structure of the power cord unwinder: 1\u2014frame, 2\u2014winding roll, 3\u2014guiding trolley with tension sensor (potentiometer), 4\u2014AC asynchronous triple-phase motor, 5\u2014belt transmissions, 6\u2014damper, 7\u201450 m of power cord. On the right-hand side, there is a picture that presents the concept of tension measurement by the potentiometer.", + "texts": [ + " On the other hand, the six motors of the hexacopter consumed about 3 kW of power. Hence, the weight of the power cord to be lifted by the hexacopter as payload was about 2.2 kg. It should be noted that the power cord was specially selected for this application. To provide a constant unwinding and winding speed, and to ensure power cord tension regardless of the current length of its unwound part, the cord had to be wound evenly on the main roll. Thus, the structure of the power cord unwinder had to meet these specifications. It is shown in Figure 4. A guiding trolley 3\u00a9 mounted on a screw moved proportionally to the length of the unwound/wound power cord 7\u00a9, in a way that guaranteed that the cord would be wound coil by coil on a single layer. This was crucial because the 1 mm2 AWG wires of the power cord could be temporarily overloaded and would have to be cooled by the air (the supply voltage was 230 VAC). The openwork structure of the roll with the power cord helped with this. On the other hand, a power cord with 1.5 mm2 wires would be too heavy" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003401_load.php_id_10011908-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003401_load.php_id_10011908-Figure1-1.png", + "caption": "Figure 1. Geometrical dimensions of the antennas under consideration: (a) Dipole, (b) loop, (c) microstrip patch, and (d) PIFA.", + "texts": [ + " Wet specimen had a watery surface, saturated specimen had moisture only inside, and air dried specimen was exposed to ambient room temperature and humidity. From [18], we obtained the loss tangent data using tan(\u03b4) = \u03c3/(\u03b5r\u03b50\u03c9), where \u03c9 is angular frequency. To investigate the return loss, transmission loss, gain and pattern of antennas buried inside a concrete pier a dipole, a loop, a microstrip patch, and a planar inverted-F antenna (PIFA) were designed for operation at 2.45 GHz in free space. The geometry and dimensions of these antennas are given in Fig. 1. Two cases of embedding scenarios were considered: Case 1 \u2014 A concrete cylinder without steel rebars and Case 2 \u2014 A concrete cylinder with steel rebars. Fig. 2(a) represents Case 1 while Fig. 2(b) represents Case 2. For simplicity and ease of simulation a cylindrical concrete pier of 100 mm height and 228 mm radius was considered. We consider that two antennas each of the same kind are placed inside air boxes with dimensions a, b and c. Each antenna is oriented along the z-axis which is also the axis of the cylindrical concrete pier", + " For the patchs the transmission data is\u221243 dB at resonance and between\u221246 and\u221243 dB within the operating frequency band of 2.42 to 2.51 GHz. The worst case transmissions one may expect between two antennas in saturated concrete are \u221260 dB, \u221250 dB, and \u221255 dB and \u221246 dB for dipoles, loops, and PIFAs and patches, respectively. These are 20 dB, 30 dB, 15 dB, and 33.5 dB in saturated concrete than that in air dried concrete. A simplified model of a bridge pier consisting of two steel reinforcements is shown in Fig. 1(b). The dipoles, loops, PIFAs, and patches were placed next to the steel reinforcement and simulated using HFSS. Computed return loss and transmission data for all four types of the antennas are shown in Fig. 6, where the distance of each antenna from the nearby steel rebar is shown in Table 2. The presence of the steel rebar in close proximity deteriorates the dipole return loss significantly. This is because dipole antennas require larger separation from nearby metallic structures. The PIFA and the loop both have well defined resonances with good return loss characteristics" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004512_servlets_purl_771234-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004512_servlets_purl_771234-Figure22-1.png", + "caption": "Figure 22 and Figure 23 show crosssections of the guard heater with a PX converter mounted inside. With the PX converters being cylindrical in shape, this was the obvious choice for the shape of the guard heater. Thus, to surround the 3.8 cm diameter x 10.16 cm long converter, the guard heater canister is 7.6 cm in diameter x 15.2 cm long. It is made of 1.6 mm thick stainless steel, and has several cuts to thermally segregate different portions of it in the axial direction. Heating elements are attached to the three zones of the curved wall to control the heat transfer at the converter wall. Another heating element is attached to the flat top plate to guard the hot end heater. Finally, it is easier to control a heater than a fan, so the cold end of the converter is kept at a constant temperature by the combination of an over-cooling fan and the cold end heater. The converter is mounted in such a way that the part of the", + "texts": [ + " As noted above, this simulates the circumstances the converter would see as an element in a many-converter system in which it is surrounded by identical converters Guard Heater Test Setur, To test the power output of AMTEC converters experimentally, and be able to vary the thermal environment an AMTEC converter is exposed to, a guard heater enclosure was created. Here we describe the test setup, including the design and functionality of the guard heater, the instrumentation used to control and measure temperatures, and possible future modifications that could be made to the guard heater system to increase its flexibility. converter wall surrounding the BASE tubes is guarded by the largest guard heater section (the topmost section in Figure 22), while the two smaller guard heater sections guard the remainder of the converter wall. Void spaces between the guard heater canister and the converter are filled with Fiberfrax insulation, a refractory wool type material made by Unifrax\u2019. The entire guard heater canister is also surrounded by 2\u201d of Fiberfrax, then covered with a fiberglass blanket. \u2019. Unifrax Corporation, 2351 Whirlpool Street, Niagara Falls, N.Y. 14305-2413 22 * c\u2018 \u2019 > The hot end converter heater is a coiled Kanthal wire cast in ceramic" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure3.39-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure3.39-1.png", + "caption": "Figure 3.39: Designed leaky-wave antenna with launcher and connector", + "texts": [ + " As can be seen, most of the energy is directed by the launcher to the forward direction to excite the antenna. and connector In order to achieve experimental measurements, the designed antenna requires a connector to power the coplanar line of the launcher. A 1.85 mm jack end (female) launch connector (model reference number 1892-04A-5 [205]) manufactured by Southwest Microwave is added to the previous simulation to verify if it is suitable for experimental use. The dimensions of the connector are shown in figure 3.38, and the simulated model is shown in figure 3.39. The connector is commonly used for the transition between coaxial cable and printed circuit boards (PCBs) operating at frequencies up to 67 GHz. A threaded clamping plate is implemented to fix the connected PCB as shown in figures 3.38 and 3.39. Figure 3.40 shows the simulated S11 parameters, which has greatly changed compared to the simulation without connector. The -10 dB bandwidth has been reduced from 7.7 GHz to only 1.9 GHz (59.6 GHz to 61.5 GHz). This is due to the discontinuity between the coaxial access and the coplanr line as well as the launcher being designed with an ungrounded 3.11. LAUNCHER coplanar line. The grounding and clamping plates of the connector changed the geometry of the initial launcher design, which added a ground to the starting coplanar line of the launcher, as shown in figure 3.39. Therefore, the input impedance of the launcher is no longer matched to 50 \u2126. For example, for the coplanar line configuration in figure 3.29, the ungrounded coplanar line calculator in [206] gives an input impedance of 50.67 \u2126, while the grounded coplanar line calculator in [207] gives an input impedance of 41.55 \u2126. Consequently, the transitions \u201ccoaxial cable to grounded coplanar line\u201d and \u201cgrounded coplanar line to ungrounded coplanar line\u201d at the launcher section degrades the performance of the energy transfer to the leaky-wave antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000420_.1117_12.2296104.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000420_.1117_12.2296104.pdf-Figure6-1.png", + "caption": "Fig. 6. Source pack", + "texts": [ + " The off axis design suppresses the problem of stray light generated by the internal obstruction. The goal of the truss is to support the primary mirror (OAP), the fold mirror and the Focal Plane assembly (FPA) (Fig. 5). The truss is in stainless steel and is black painted with MAP PU1. Main Chamber Black Tent Black sheets Auxiliary chamber Collimator Proc. of SPIE Vol. 10562 105624V-3 The light source is either a Laser-Driven white Light Source (LDLS) or a 20W laser diode (\u03bbc = 805 nm) equipped with an optical fiber. The source baffling has 2 main objectives (Fig.6): An additional reflective fiber to fiber coupler allows to insert optical density for decreasing light flux or filters for selecting the wavelength. The monitoring is placed into the collimated beam. It consists into a fold mirror, a collecting lens and a photodiode. The purpose of the MGSE is to locate the instrument in correct orientation with respect to the collimated beam. The MGSE orients the instrument in the range \u00b1 180\u00b0 in azimuth and -5\u00b0/+85\u00b0 in elevation. The WISPR DM is mounted onto a stack of stages (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002703_1334-022-00450-w.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002703_1334-022-00450-w.pdf-Figure4-1.png", + "caption": "Fig. 4 GTS for r1. The labels of the states denote the output of the TS in the respective state", + "texts": [], + "surrounding_texts": [ + "Both variants of certifying synthesis introduced in the previous sections consider the certificates of all other system processes in the local objective of a process pi . This is not always necessary since \u03d5i might be satisfiable even if another process deviates from its guaranteed behavior. In this section, we present an optimization of certifying synthesis that reduces the number of considered certificates. For every pi , we compute a set of relevant processes Ri \u2286 P\u2212\\{pi }. Certifying synthesis then only considers the certificates of the relevant processes: Let R i = {\u03c8 j \u2208 | p j \u2208 Ri }, GR i = {g j \u2208 G | p j \u2208 Ri }. For LTL certificates, we require si | \u03c8i \u2227 ( R i \u2192 \u03d5i ). For GTS, si gi and si | GR i \u03d5i need to hold.Wedenote such solutions of certifying synthesis with (S, )R and (S,G)R. The construction of the set of relevant processesRi has to ensure that certifying synthesis is still sound and complete. In the following, we introduce a syntactic definition of relevant processes that does so. It excludes processes from pi \u2019s set of relevant processes Ri whose output variables do not occur in the subspecification \u03d5i : Definition 6.1 (Relevant processes)Let \u03d5 be an LTL formula with decomposition \u3008\u03d51, . . . , \u03d5n\u3009. The relevant processes Ri \u2286 P\u2212\\{pi } of process pi \u2208 P\u2212 are given by Ri = {p j \u2208 P\u2212\\{pi } | Oj \u2229 prop(\u03d5i ) = \u2205}. Intuitively, since Oj \u2229 prop(\u03d5i ) = \u2205 holds for a process p j \u2208 P\u2212\\Ri with i = j , \u03d5i does not restrict the satisfying valuations of the output variables of p j . Thus, if a sequence satisfies \u03d5i , then it does so for any valuations of the variables in Oj . Hence, the guaranteed behavior of p j does not influence the satisfiability of \u03d5i and thus pi does not need to consider it: Theorem 6.1 Let \u03d5 be an LTL formula. Moreover, let S = \u3008s1, . . . , sn\u3009 be a vector of strategies. 1. If (S, )R realizes \u03d5 for some vector of LTL certificates, then s1 || \u00b7 \u00b7 \u00b7 || sn | \u03d5. If s1 || \u00b7 \u00b7 \u00b7 || sn | \u03d5 holds, then there exist vectors S \u2032 and \u2032 of strategies and LTL certificates such that (S \u2032, \u2032)R realizes \u03d5. 2. If (S,G)R realizes \u03d5 for some vector G of GTS, then s1 || \u00b7 \u00b7 \u00b7 || sn | \u03d5. If s1 || \u00b7 \u00b7 \u00b7 || sn | \u03d5 holds, then there exist vectors S \u2032 and G\u2032 of strategies and GTS such that (S \u2032,G\u2032)R realizes \u03d5. Proof For both LTL certificates and GTS, soundness follows immediately from the fact thatRi \u2286 P\u2212\\{pi } holds and thus we have both R i \u2286 i and GR i \u2286 Gi . Next, we show the completeness of certifying synthesis with LTL certificates. Suppose that s1 || \u00b7 \u00b7 \u00b7 || sn | \u03d5 holds. Then, by Theorem 4.1, there exists a vector of LTL certificates such that (S, ) realizes \u03d5. In particular, this holds for the certificates : = \u3008\u03c81, . . . , \u03c8n\u3009 with L(\u03c8i ) = {comp(si , \u03b3 ) \u222a \u03b3 \u2032 | \u03b3 \u2208 (2Ii )\u03c9, \u03b3 \u2032 \u2208 (2V \\Vi )\u03c9}. Let i = {\u03c8 j | p j \u2208 P\u2212\\{pi }}. We construct strategies s\u2032 i as follows: For all \u03b3 \u2208 (2Oenv)\u03c9, \u03b3 \u2032 \u2208 (2V \\Oenv)\u03c9, let \u03c3\u03b3,\u03b3 \u2032 = (comp(s1 || \u00b7 \u00b7 \u00b7 || sn, \u03b3 ) \u2229 Oi ) \u222a ((\u03b3 \u222a \u03b3 \u2032) \u2229 Ii ). Then, we define comp(s\u2032 i , (\u03b3 \u222a \u03b3 \u2032) \u2229 Ii ) : = \u03c3\u03b3,\u03b3 \u2032 . Let S \u2032 : = \u3008s\u2032 1, . . . , s \u2032 n\u3009. Let \u03c8 \u2032 i be an LTL formula with L(\u03c8 \u2032 i ) = {comp(s\u2032 i , \u03b3 ) \u222a \u03b3 \u2032 | \u03b3 \u2208 (2Ii )\u03c9, \u03b3 \u2032 \u2208 (2V \\Vi )\u03c9}. Let \u2032 : = \u3008\u03c8 \u2032 1, . . . , \u03c8 \u2032 n\u3009 and \u2032 i,R : = {\u03c8 \u2032 j | p j \u2208 Ri }. Then, (S \u2032, \u2032)R realizes \u03d5. The proof is given in [15]. Next, we consider certificates represented by GTS. Suppose that s1 || \u00b7 \u00b7 \u00b7 || sn | \u03d5 holds. Let S \u2032 and be the vectors of strategies and LTL certificates constructed as in the first part of this proof such that (S \u2032, )R realizes \u03d5. Let i = {\u03c8 j | p j \u2208 P\u2212\\{pi }}, R i : = {\u03c8 j | p j \u2208 Ri }. We construct a GTS gi as follows: gi is a copy of s\u2032 i , yet, the labels of gi ignore output variables v \u2208 Oi that are not contained in OG i , i.e., ogi (t, i) = oi (t, i) \u2229 OG i for all states t and all inputs i \u2208 2Ii , where ogi is the labeling function of gi and oi is the labeling function of s\u2032 i . Let G : = \u3008g1, . . . , gn\u3009, Gi : = {g j | p j \u2208 P\u2212\\{pi }}, GR i : = {g j | p j \u2208 Ri }. Then, (S \u2032,G)R realizes \u03d5. For the proof, we refer to [15]. For certifying synthesis with relevant processes, we can only guarantee that for every vector of strategies s1, . . . , sn with s1 || \u00b7 \u00b7 \u00b7 || sn | \u03d5, there are some strategies that are part of a solution of certifying synthesis. These strategies are not necessarily s1, . . . , sn : A strategy si may make use of the certificate of a process p j outside of Ri . That is, it may violate \u03d5i on an input sequence \u03b3 that does not stick to g j although \u03d5i is satisfiable for \u03b3 . Strategy si is not required to satisfy \u03d5i on \u03b3 , a strategy that may only consider the certificates of the relevant processes, however, is. As long as the definition of relevant processes allows for finding some solution of certifying synthesis, like the one introduced in Definition 6.1 does as a result of Theorem 6.1, certifying synthesis is nevertheless sound and complete." + ] + }, + { + "image_filename": "designv8_17_0004509_i_10.3233_ATDE230467-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004509_i_10.3233_ATDE230467-Figure2-1.png", + "caption": "Figure 2. FEM modeling process of the POM FS.", + "texts": [ + " The establishment of the POM FS model is based on the following simplification: 1) The deformation of the FB is neglected and FB and WG are regarded as a single entity; 2) The neutral layer shell of the POM FS is subject to zero stress; 3) In the event of deformation of the POM FS, the axial displacement of the shell is not considered; 4) The bottom of the POM FS cylinder remains impervious to deformation; 5) The tooth end of the POM FS is simplified as an equivalent gear, and the thickness of the tooth end wall is 3 1.67 times that of the smooth cylinder. Figure 2 illustrates the FEM modeling and analysis of the POM FS, and the specific steps can be described as follows. Step 1: Model creation and geometric parameters settings. A simplified threedimensional model of the harmonic drive, consisting of CS, FS, and WG (FB) was established. The FS material was set as POM, while the WG (FB) material was set as steel No.45. Their material properties are presented in table 1. Step 2: Definition of contact surfaces and conditions. The inner surface of the FS served as the contact surface, while the outer ring of the WG acted as the target surface. The type of contact condition was set as \"Frictional\", with the friction coefficient specified as 0.15. Step 3: Mesh generation. The mesh size was set to 0.1mm. Step 4: Application of load and constraints. The WG inner ring and FS output flange were set as fixed supports. The torque was applied at the tooth end of the FS, with a rated torque of 52 Nm. Step 5: Results generation. The stress, displacement and strain cloud maps were extracted. According to the cloud maps in figure 2, the maximum strain of the POM FS is 0.0095, which occurs at the connection between the gear ring and the cup. The maximum displacement is 0.2052mm, which occurs at the bottom of the FS cup. The maximum stress is 26.19Mpa, which occurs at the connection between the gear ring and the cup. This indicates that the POM FS meets the strength and working conditions requirements for a FS in a precision harmonic drive. The cylinder length L, wall thickness d, and chamfer radius r, as presented in figure 3, are significant structural parameters that influence the stress distribution and magnitude of POM FS", + " Based on the above analysis, the order of the influence of cylinder length, wall thickness, and chamfer radius on the stress of POM FS is as follows: cylinder length > wall thickness > chamfer radius. Taking the parameters of cylinder length, wall thickness, and chamfer radius as optimization targets, the minimum stress values for each parameter were determined to be L = 60mm, d = 0.3125mm, and r = 1.4mm. A POM FS model was established based on these parameters, and the FEM simulation was performed following the procedure in section 2. The stress, displacement, and strain cloud maps of the optimized POM FS are exhibited in figure 5. By comparing figure 2 and figure 5, it can be observed that the maximum stress of POM FS decreases from 26.19MPa to 23.81MPa, the maximum displacement decreases from 0.2052mm to 0.1746mm, and the maximum strain decreases from 0.0095 to 0.0083. The stress, displacement, and strain decrease by 9.09%, 14.91%, and 12.63%, respectively. These results indicate that the structural parameter optimization method proposed in this paper achieves significant improvements in the mechanical performance and stability of the POM FS" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002629__12_129_12_1155__pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002629__12_129_12_1155__pdf-Figure8-1.png", + "caption": "Fig. 8. Robot arm PA-10", + "texts": [], + "surrounding_texts": [ + "\u80fd\u52d5\u8996\u899a\u3092\u7528\u3044\u305f\u63a2\u7d22\u30ed\u30dc\u30c3\u30c8\u306e\u958b\u767a\nX = \u03b1 2 \u00b7 h \u00b7 tan\u03d5 \u00b7 ( \u2212 d\u2032 + \u221a d\u20322 + (h + d)2 \u2212 (h\u2032 + d)2 )\n+ 512 tan\u03d5 \u00b7 d \u00b7 ( 1 h\u2032 \u2212 1 h ) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (25)\nh\u2032 = h \u2212 ( (h + d) \u00b7 tan \u03b8\n2 \u2212 h \u00b7 tan\u03c6\n) \u00b7 sin \u03b8 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (26)\nd\u2032 = h \u00b7 tan \u03c6 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (27)\n\u2217d\u2032 > (h + d) \u00b7 tan \u03b8\u306e\u969b\u306f\nh\u2032 = h + ( (h + d) \u00b7 tan \u03b8\n2 \u2212 h \u00b7 tan\u03c6\n) \u00b7 sin \u03b8\n6. \u30b7\u30b9\u30c6\u30e0\u306e\u80fd\u52d5\u5316\n\u30ab\u30e1\u30e9\u306e\u52d5\u304d\u3092\u30aa\u30af\u30eb\u30fc\u30b8\u30e7\u30f3\u30fb\u8996\u91ce\u89d2\u554f\u984c\u3092\u56de\u907f\u3059\u308b \u3088\u3046\u306b\u5236\u5fa1\u3059\u308b\u305f\u3081\u306b\uff0c\u300c\u30ab\u30e1\u30e9\u306e\u52d5\u304d\u306b\u5bfe\u5fdc\u3057\u305f\u753b\u9762\u5185\u306e\n\u5bfe\u8c61\u306e\u898b\u3048\u65b9\u5909\u5316\u30e2\u30c7\u30eb\u300d\u306e\u4e88\u6e2c\u60c5\u5831\u304b\u3089\uff0c\u3082\u3063\u3068\u3082\u30aa\u30af \u30eb\u30fc\u30b8\u30e7\u30f3\u304c\u767a\u751f\u3059\u308b\u53ef\u80fd\u6027\u304c\u4f4e\u3044\u3068\u4e88\u6e2c\u3055\u308c\u308b\u30ab\u30e1\u30e9\u306e \u72b6\u614b\u3092\u63a8\u5b9a\u3059\u308b\u3002 \u30ab\u30e1\u30e9\u306e\u5404\u72b6\u614b\u306e\u8a55\u4fa1\u65b9\u6cd5\u306b\u306f (12)\uff0c(25)\uff0c(26)\uff0c(27)\u5f0f\n\u3092\u7528\u3044\u308b\u3002\u30ab\u30e1\u30e9\u306e\u72b6\u614b\u304c\u5909\u5316\u3057\u305f\u969b\u306e\u753b\u9762\u5185\u306b\u304a\u3051\u308b\u5404 \u5bfe\u8c61\u306e\u79fb\u52d5\u30e2\u30c7\u30eb\u3092\u69cb\u6210\u3057\uff0c\u5404\u5bfe\u8c61\u306e\u79fb\u52d5\u30e2\u30c7\u30eb\u304b\u3089\u5404\u5bfe \u8c61\u304c\u8996\u91ce\u5185\u306b\u53ce\u307e\u308a\uff0c\u30aa\u30af\u30eb\u30fc\u30b8\u30e7\u30f3\u304c\u767a\u751f\u3057\u306a\u3044\u3088\u3046\u306a \u30ab\u30e1\u30e9\u306e\u72b6\u614b\u3092\u53ef\u8996\u9818\u57df S \u3068\u3057\uff0c\u305d\u306e\u9650\u754c\u72b6\u614b\u3092\u53ef\u8996\u9650\u754c\n(xk, yk)\u3068\u3057\u3066 Fig. 5\u306b\u304a\u3044\u3066\u793a\u3059\u3002 Fig. 5\u306b\u304a\u3044\u3066\u7e26\u8ef8\u304c 0\u3068\u306a\u3063\u3066\u3044\u308b\u90e8\u5206\u306f\uff0c\u30aa\u30af\u30eb\u30fc \u30b8\u30e7\u30f3\u30fb\u8996\u91ce\u89d2\u554f\u984c\u304c\u751f\u3058\u3066\u3057\u307e\u3046\u53ef\u80fd\u6027\u304c\u3042\u308b\u30ab\u30e1\u30e9\u306e \u72b6\u614b\u3092\u8868\u3057\u3066\u3044\u308b\u3002\u53ef\u8996\u9818\u57df\u5185\u306e\u5404\u72b6\u614b (i, j)\u304b\u3089\u53ef\u8996\u9650\u754c\n\u307e\u3067\u306e\u6700\u77ed\u306e\u8ddd\u96e2\u3092 D\u3068\u3057 (28)\u5f0f\u306e\u3088\u3046\u306b\u8a2d\u5b9a\u3057\uff0c\u3053\u306e D\u3092\u8a55\u4fa1\u95a2\u6570\u3068\u3057\u3066\u7528\u3044\u308b\u3002\u8a55\u4fa1\u95a2\u6570\u304c\u6700\u5927\u3068\u306a\u308b\u72b6\u614b\u3092 \u30aa\u30af\u30eb\u30fc\u30b8\u30e7\u30f3\u304c\u767a\u751f\u3059\u308b\u53ef\u80fd\u6027\u304c\u4f4e\u3044\u3068\u30ab\u30e1\u30e9\u306e\u72b6\u614b\u3068 \u4e88\u6e2c\u3057\uff0c\u6b21\u306e\u30ab\u30e1\u30e9\u306e\u72b6\u614b\u3068\u3057\u3066\u30ab\u30e1\u30e9\u306e\u52d5\u304d\u3092\u5236\u5fa1\u3059\u308b\u3002\nD(i, j) = min k\u2208edge(S )\n\u221a (xk \u2212 i)2 + (yk \u2212 j)2 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (28)\n7. \u30b9\u30c6\u30ec\u30aa\u7406\u8ad6\n\u64ae\u5f71\u3057\u305f\u8907\u6570\u306e\u753b\u50cf\u304b\u3089\uff0c\u5404\u5bfe\u8c61\u306e\u753b\u9762\u5185\u306b\u304a\u3051\u308b\u5ea7\u6a19\n\u3092\u62bd\u51fa\u3057\uff0c\u30b9\u30c6\u30ec\u30aa\u7406\u8ad6\u3092\u69cb\u6210\u3059\u308b\u3053\u3068\u3067\u5404\u5bfe\u8c61\u306e 3\u6b21\u5143 \u5ea7\u6a19\u3092\u63a8\u5b9a\u3059\u308b\u3002\n\u5f93\u6765\u306e\u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u306b\u304a\u3044\u3066\u306f\u5e73\u884c\u79fb\u52d5\u306e\u307f\u306e 1\u81ea\u7531\u5ea6 \u7cfb\u3067\u3042\u3063\u305f\u304c\uff0c\u672c\u7814\u7a76\u306b\u304a\u3051\u308b\u30b9\u30c6\u30ec\u30aa\u8996\uff08\u4ee5\u4e0b\uff0c\u56de\u8ee2\u30b9\n\u30c6\u30ec\u30aa\uff09\u3067\u306f\uff0c\u5e73\u884c\u30fb\u56de\u8ee2\u3068 2\u3064\u306e\u81ea\u7531\u5ea6\u7cfb\u3092\u6709\u3057\u3066\u3044\u308b \u70ba\uff0c\u3088\u308a\u5e45\u5e83\u3044\u72b6\u6cc1\u3067\u306e\u30bb\u30f3\u30b7\u30f3\u30b0\u304c\u53ef\u80fd\u3067\u3042\u308b\u3002 \u56de\u8ee2\u904b\u52d5\u3092\u8003\u616e\u3057\u305f\u30b9\u30c6\u30ec\u30aa\u8996\u3068\u3057\u3066\uff0c\u30ab\u30e1\u30e9\u5185\u90e8\u30d1\u30e9 \u30e1\u30fc\u30bf\u3092\u7528\u3044\u3066\u5965\u884c\u304d\u65b9\u5411\u3092\u63a8\u5b9a\u3059\u308b\u624b\u6cd5\u3068\u3057\u3066 (7) (8) \u306a\u3069\n\u304c\u6319\u3052\u3089\u308c\u308b\u3002 \u672c\u7814\u7a76\u306b\u304a\u3044\u3066\u306f\u5148\u306b\u5b9a\u7fa9\u3057\u305f (12)\uff0c(25)\uff0c(26)\uff0c(27)\u5f0f \u3092\u7528\u3044\u3066\u30ab\u30e1\u30e9\u306e\u79fb\u52d5\u524d\u5f8c\u306b\u64ae\u5f71\u3057\u305f\u753b\u50cf\u306e\u8996\u5dee\u304b\u3089\u5965\u884c \u304d\u65b9\u5411\u306e\u63a8\u5b9a\u3092\u884c\u3046\u3002\u5e73\u884c\u79fb\u52d5\u91cf I\uff0c\u30ab\u30e1\u30e9\u306e\u56de\u8ee2\u91cf \u03b8\uff0c\u30ab\n\u30e1\u30e9\u304b\u3089\u898b\u305f\u3068\u304d\u306e\u5bfe\u8c61\u3068\u306e\u306a\u3059\u89d2\u03c6\uff0c\u30ab\u30e1\u30e9\u5ea7\u6a19\u7cfb\u304b\u3089\u30ab \u30e1\u30e9\u306e\u4e2d\u5fc3\u307e\u3067\u306e\u8ddd\u96e2 d\u53ca\u3073\u8996\u5dee X \u304c\u65e2\u77e5\u3067\u3042\u3063\u305f\u5834\u5408\uff0c \u5bfe\u8c61\u307e\u3067\u306e\u8ddd\u96e2 h\u306f\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u7d50\u3073\u3064\u304f\u3002\nX = \u03b1 2 \u00b7 h \u00b7 tan\u03d5 \u00b7 ( \u2212 I + d\u2032\n+ \u221a \u2212d\u20322 + (h + d)2 \u2212 (h\u2032 + d)2 )\n+ 512 tan\u03d5 \u00b7 d \u00b7 ( 1 h\u2032 \u2212 1 h ) \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (29)\nh\u2032 = h \u2212 ( (h + d) \u00b7 tan \u03b8\n2 \u2212 h \u00b7 tan\u03c6\n) \u00b7 sin \u03b8 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (30)\nd\u2032 = h \u00b7 tan\u03c6 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (31)\n\u2217d\u2032 > (h + d) \u00b7 tan \u03b8\u306e\u969b\u306f\nh\u2032 = h + ( (h + d) \u00b7 tan \u03b8\n2 \u2212 h \u00b7 tan\u03c6\n) \u00b7 sin \u03b8\n\u30bb\u30f3\u30b7\u30f3\u30b0\u306b\u3088\u308a\u6c42\u3081\u305f\u8996\u5dee X\u3088\u308a\u5bfe\u8c61\u307e\u3067\u306e\u5965\u884c\u304d\u65b9\u5411 \u306e\u5927\u304d\u3055\u3067\u3042\u308b h\u3092\u8a08\u7b97\u3059\u308b\u3002 \u307e\u305f\u30ab\u30e1\u30e9\u306e\u72b6\u614b\u3092\u8003\u616e\u3059\u308b\u305f\u3081\u306b\u30ef\u30fc\u30eb\u30c9\u5ea7\u6a19\u7cfb\u3068\u30ab \u30e1\u30e9\u5ea7\u6a19\u7cfb\u306e\u76f8\u5bfe\u95a2\u4fc2\u53ca\u3073\u30ab\u30e1\u30e9\u306e\u5149\u5b66\u30d1\u30e9\u30e1\u30fc\u30bf\u304b\u3089\u5bfe\n\u8c61\u306e\u6a2a\u30fb\u7e26\u65b9\u5411\u306e\u5ea7\u6a19\u3092\u5c0e\u51fa\u3059\u308b\u3002\u8003\u3048\u65b9\u3068\u3057\u3066\u306f\u30ab\u30e1\u30e9 \u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3 (12)\u306e\u969b\u3068\u540c\u3058\u3067\u3042\u308b\u3002\u30ab\u30e1\u30e9\u56de\u8ee2\u884c\u5217 \u3092 R\u5e73\u884c\u79fb\u52d5\u30d9\u30af\u30c8\u30eb\u3092 t\u3068\u3059\u308b\u3068\u7a7a\u9593\u306e\u30ef\u30fc\u30eb\u30c9\u5ea7\u6a19\uff08\u672c \u5b9f\u9a13\u306b\u304a\u3044\u3066\u306f\u30ed\u30dc\u30c3\u30c8\u30a2\u30fc\u30e0\u306e\u30d9\u30fc\u30b9\u5ea7\u6a19\u7cfb\uff09[X, Y, Z]T \u3068\u753b\u9762\u4e0a\u306e\u5ea7\u6a19 [u, v]T \u3068\u306f\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u7d50\u3073\u3064\u304f\u3002\n\u03c9 \u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 u v\n1 \u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 = A [ R | t ] \u23a1\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a2\u23a3 X Y Z\n1\n\u23a4\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a5\u23a6 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 \u00b7 (32)\n\u3053\u306e\u3053\u3068\u3092\u5229\u7528\u3057\uff0c\u3042\u3089\u304b\u3058\u3081\u6c42\u3081\u3066\u304a\u3044\u305f\u5965\u884c\u304d\u65b9\u5411\u306e \u5927\u304d\u3055 h\u3092\u4ee3\u5165\u3059\u308b\u3068 \u03c9\u304c\u6c42\u307e\u308a\uff0c\u30ab\u30e1\u30e9\u5ea7\u6a19 (u, v)\u3092\u4ee3\n\u5165\u3059\u308b\u3068\u5404\u5bfe\u8c61\u306e 3\u6b21\u5143\u5ea7\u6a19\u304c\u6c42\u307e\u308b\u3002\n8. \u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\n\u672c\u7814\u7a76\u3067\u306f\u5e73\u884c\u30fb\u56de\u8ee2\u3092\u4f75\u7528\u3057\u305f\u56de\u8ee2\u30b9\u30c6\u30ec\u30aa\u8996\u3092\u63d0\u6848 \u3057\u3066\u3044\u308b\u3002\u305d\u3053\u3067\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u3066\u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u3068\u56de \u8ee2\u30b9\u30c6\u30ec\u30aa\u3092\u6bd4\u8f03\u3057\uff0c\u7406\u8ad6\u7684\u306b\u7cbe\u5ea6\u3092\u691c\u8a3c\u3059\u308b\u3002\n(12)\uff0c(29)\uff0c(30)\uff0c(31)\u5f0f\u30e2\u30c7\u30eb\u3092\u7528\u3044\u3066\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\n\u30f3\u3092\u884c\u3046\u3002\u91cf\u5b50\u5316\u8aa4\u5dee\u3092\u60f3\u5b9a\u3057\u305f\u5206\u6563 1 [pix]\u306e\u89b3\u6e2c\u30ce\u30a4\u30ba \u53ca\u3073\u30ab\u30e1\u30e9\u306e\u52d5\u304d\u306e\u8aa4\u5dee\u3092\u60f3\u5b9a\u3057\u305f\u5206\u6563 0.2 mm\u306e\u30b7\u30b9\u30c6\n\u96fb\u5b66\u8ad6 D\uff0c129 \u5dfb 12 \u53f7\uff0c2009 \u5e74 1159", + "\u30e0\u30ce\u30a4\u30ba\u3092\u30e2\u30c7\u30eb\u306b\u5370\u52a0\u3057\uff0c\u305d\u306e\u969b\u306e\u4e88\u6e2c\u5024\u3068\u771f\u5024\u3068\u306e\u8aa4 \u5dee\u3092\u6bd4\u8f03\u3057\u305f\u3002 \u901a\u5e38\u306e\u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u306b\u304a\u3051\u308b\u771f\u5024\u3068\u306e\u8aa4\u5dee\uff0c\u56de\u8ee2\u30b9\u30c6\u30ec\n\u30aa\u306b\u304a\u3051\u308b\u771f\u5024\u3068\u306e\u8aa4\u5dee\u3092\u305d\u308c\u305e\u308c\u8a08\u7b97\u3057\uff0c\u771f\u5024\u3068\u306e\u5206\u6563 \u3092 Fig. 6\uff0cFig. 7\u306b\u304a\u3044\u3066\u793a\u3059\u3002\u5206\u6563\u5024\u3092\u898b\u308b\u3068\u5206\u304b\u308b\u3088\u3046 \u306b\uff0c\u5e73\u884c\u30fb\u56de\u8ee2\u3068 2\u3064\u306e\u81ea\u7531\u5ea6\u3092\u6709\u3059\u308b\u56de\u8ee2\u30b9\u30c6\u30ec\u30aa\u306f\u5e73 \u884c\u30b9\u30c6\u30ec\u30aa\u3068\u6bd4\u3079\u3066\u3082\u7cbe\u5ea6\u3092\u843d\u3068\u3055\u305a\u306b\u89b3\u6e2c\u51fa\u6765\u3066\u3044\u308b\u4e8b\n\u304c\u78ba\u8a8d\u3067\u304d\u308b\u3002\u3064\u307e\u308a\uff0c\u5e73\u884c\u79fb\u52d5\u8ddd\u96e2\u304c\u5341\u5206\u53d6\u308c\u306a\u3044\u3088\u3046 \u306a\u72b6\u6cc1\u4e0b\u306b\u304a\u3044\u3066\u306f\uff0c\u56de\u8ee2\u30b9\u30c6\u30ec\u30aa\u3092\u5c0e\u5165\u3059\u308b\u3053\u3068\u3067\u8ddd\u96e2 \u306e\u77ed\u3044\u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u3088\u308a\u7cbe\u5ea6\u306e\u9ad8\u3044\u30bb\u30f3\u30b7\u30f3\u30b0\u304c\u53ef\u80fd\u3067\u3042 \u308b\u3068\u3044\u3048\u308b\u3002\u305f\u3060\u3057\uff0c\u8a08\u7b97\u304c\u8907\u96d1\u3067\u3042\u308b\u70ba\u540c\u7b49\u306e\u8ddd\u96e2\u3092\u5e73\n\u884c\u79fb\u52d5\u3055\u305b\u305f\u969b\u306e\u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u3088\u308a\u306f\u591a\u5c11\u30ce\u30a4\u30ba\u306e\u5f71\u97ff\u3092 \u53d7\u3051\u3066\u3044\u308b\u3002\u3057\u304b\u3057\uff0c\u56de\u8ee2\u30b9\u30c6\u30ec\u30aa\u306e\u5e73\u884c\u79fb\u52d5\u8ddd\u96e2\u3092\u5341\u5206 \u3068\u308c\u3070\u8aa4\u5dee\u306e\u5206\u6563\u304c 0.5 mm\u4ee5\u4e0b\u306b\u6291\u3048\u3089\u308c\u308b\u3053\u3068\u304b\u3089\uff0c\u7cbe\n\u5ea6\u7684\u306b\u306f\u554f\u984c\u306a\u3044\u3068\u601d\u308f\u308c\u308b\u3002\n9. \u5b9f \u9a13\n\u30089\u30fb1\u3009 \u5b9f\u9a13\u74b0\u5883 \u5b9f\u9a13\u306b\u306f Fig. 8\u306b\u793a\u3059\u4e09\u83f1\u91cd\u5de5\u88fd \u306e 7\u81ea\u7531\u5ea6\u30ed\u30dc\u30c3\u30c8\u30a2\u30fc\u30e0 PA-10\u3092\u7528\u3044\u308b\u3002 \u30a2\u30fc\u30e0\u306e\u5148\u7aef\u306b\u8996\u91ce\u89d2 36\u25e6 \u306e CCD\u30ab\u30e1\u30e9\uff08SONY\uff09\u3092\n1\u53f0\u53d6\u308a\u4ed8\u3051\u3066 Fig. 9\u306e\u3088\u3046\u306b\u914d\u7f6e\u3057\u305f\u5404\u5bfe\u8c61\u306e\u5ea7\u6a19\u3092\u80fd\n\u52d5\u8996\u899a\u3092\u7528\u3044\u3066\u6c42\u3081\u3066\u3044\u304f\u3002\u901a\u5e38\u306e\u6b63\u898f\u5316\u76f8\u95a2\u3092\u7528\u3044\u305f\u5e73 \u884c\u30b9\u30c6\u30ec\u30aa\u3067\u306f\u30aa\u30af\u30eb\u30fc\u30b8\u30e7\u30f3\u554f\u984c\u30fb\u8996\u91ce\u89d2\u554f\u984c\u306e\u5f71\u97ff\u306b\n\u3088\u308a\uff0c\u5e73\u884c\u79fb\u52d5\u8ddd\u96e2\u306f 40 mm\u4ee5\u4e0a\u306b\u8a2d\u5b9a\u3067\u304d\u306a\u3044\u72b6\u6cc1\u3067\u3042 \u308b\u3002\u5bfe\u8c61\u7269\u4f53\u306f\u534a\u5f84 20 mm\u30fb\u9ad8\u3055 85 mm\u306e\u5186\u67f1\uff0c\u540c\u4e00\u5f62\u72b6 \u3067\u753b\u50cf\u51e6\u7406\u306b\u3088\u308b\u5bfe\u8c61\u540c\u58eb\u306e\u5224\u5225\u306f\u3067\u304d\u306a\u3044\u3002Fig. 9\u306b\u304a\n\u3044\u3066\u660e\u8a18\u3055\u308c\u3066\u3044\u308b\u5404\u5bfe\u8c61\u306e\u5ea7\u6a19\u306f\u5bfe\u8c61\u7269\u4f53\u306e\u91cd\u5fc3\u5ea7\u6a19\u3092 \u8868\u3057\u3066\u3044\u308b\u3002\u4fe1\u53f7\u306e\u6d41\u308c\u3092 Fig. 10\u306b\u3088\u3063\u3066\u793a\u3059\u3002 \u30a2\u30fc\u30e0\u304b\u3089\u306e\u60c5\u5831\u306f\u30b5\u30fc\u30dc\u30c9\u30e9\u30a4\u30d0\u3092\u4ecb\u3057\u3066\u904b\u52d5\u5236\u5fa1\u30dc\u30fc \u30c9\u306b\u9001\u3089\u308c\uff0c\u4f4d\u7f6e\uff0c\u59ff\u52e2\uff0c\u901f\u5ea6\u60c5\u5831\u3068\u3057\u3066 PC\u306b\u9001\u3089\u308c\u308b\u3002\u307e\n\u305f\u30ab\u30e1\u30e9\u304b\u3089\u5f97\u3089\u308c\u305f\u5bfe\u8c61\u7269\u4f53\u306e\u753b\u50cf\u60c5\u5831\u306f\u753b\u50cf\u51e6\u7406\u30dc\u30fc \u30c9 IP7000\uff08HITACHI\uff09\u3092\u4ecb\u3057\u3066\u5f62\u72b6\uff0c\u8ddd\u96e2\u60c5\u5831\u3068\u3057\u3066 PC\n\u306b\u9001\u3089\u308c\u308b\u3002\u306a\u304a\u672c\u7814\u7a76\u306b\u304a\u3044\u3066\u306f\u30ab\u30e1\u30e9\u306e\u5185\u90e8\u30d1\u30e9\u30e1\u30fc \u30bf\u306f\u3042\u3089\u304b\u3058\u3081\u6c42\u3081\u3066\u304a\u304d\uff0c\u30ab\u30e1\u30e9\u306e\u5236\u5fa1\u60c5\u5831\u304b\u3089\u5f97\u3089\u308c\n\u308b\u904b\u52d5\u30d1\u30e9\u30e1\u30fc\u30bf\u306f\u5229\u7528\u3067\u304d\u308b\u3082\u306e\u3068\u3059\u308b\u3002\u753b\u50cf\u51e6\u7406\u30dc\u30fc \u30c9\u306e\u753b\u7d20\u6570 512 [pix] \u00d7 512 [pix]\u306b\u8a2d\u5b9a\u3057\u305f\u3002\n1160 IEEJ Trans. IA, Vol.129, No.12, 2009", + "\u80fd\u52d5\u8996\u899a\u3092\u7528\u3044\u305f\u63a2\u7d22\u30ed\u30dc\u30c3\u30c8\u306e\u958b\u767a\n\u30089\u30fb2\u3009 \u5b9f\u9a13\u7d50\u679c \u5b9f\u9a13\u74b0\u5883\u306b\u304a\u3044\u3066\u80fd\u52d5\u8996\u899a\u3092\u5b9f\u884c \u3057\u305f\u969b\uff0c\u8a55\u4fa1\u95a2\u6570 D\u304c\u6700\u5927\u3068\u306a\u308b\u30ab\u30e1\u30e9\u306e\u72b6\u614b\u306f\u5e73\u884c\u79fb\u52d5 \u91cf I \u306f 510 mm\uff0c\u56de\u8ee2\u91cf \u03b8\u304c 26\u25e6 \u3068\u306a\u3063\u305f\u3002\u79fb\u52d5\u524d\u5f8c\u306e\u30ab \u30e1\u30e9\u306b\u3088\u308b\u64ae\u5f71\u753b\u50cf\u3092 Fig. 11, Fig. 12\u306b\u304a\u3044\u3066\u793a\u3059\u3002\nFig. 11, Fig. 12\u306b\u304a\u3044\u3066\u78ba\u8a8d\u3067\u304d\u308b\u3088\u3046\u306b\uff0c\u30aa\u30af\u30eb\u30fc\u30b8\u30e7 \u30f3\u554f\u984c\u3084\u8996\u91ce\u89d2\u554f\u984c\u304c\u751f\u3058\u308b\u3053\u3068\u306a\u304f\u30bb\u30f3\u30b7\u30f3\u30b0\u3067\u304d\u3066\u3044 \u308b\u3053\u3068\u304c\u78ba\u8a8d\u3067\u304d\u308b\u3002 \u307e\u305f\u63d0\u6848\u624b\u6cd5\u3067\u3042\u308b\u56de\u8ee2\u30b9\u30c6\u30ec\u30aa\u306b\u3088\u308a\u5404\u5bfe\u8c61\u306e\u5965\u884c\u304d\n\u65b9\u5411\u63a8\u5b9a\u3092\u884c\u306a\u3063\u305f\u7d50\u679c\uff0c\u53ca\u3073\u6bd4\u8f03\u5bfe\u8c61\u3068\u3057\u3066\u4eca\u56de\u306e\u5b9f\u9a13\u74b0 \u5883\u306b\u304a\u3044\u3066\u30aa\u30af\u30eb\u30fc\u30b8\u30e7\u30f3\u554f\u984c\u3092\u8003\u616e\u3057\u305f\u969b\u306e\uff0c\u5e73\u884c\u30b9\u30c6\u30ec \u30aa\u306b\u304a\u3051\u308b\u6700\u5927\u79fb\u52d5\u8ddd\u96e2\u306f40 mm\u3067\u3042\u3063\u305f\u305f\u3081\uff0c40 mm\u306e \u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u306b\u3088\u308a\u5404\u5bfe\u8c61\u306e\u5965\u884c\u304d\u65b9\u5411\u63a8\u5b9a\u3092\u884c\u306a\u3063\u305f\u7d50\n\u679c\u3092 Table 1\u306b\uff0c\u63d0\u6848\u624b\u6cd5\u306b\u3088\u308a\u6c42\u3081\u305f\u5965\u884c\u304d\u63a8\u5b9a\u60c5\u5831\u304b\u3089 \u30b9\u30c6\u30ec\u30aa\u7406\u8ad6\u3092\u69cb\u7bc9\u3057\u6c42\u3081\u305f 3\u6b21\u5143\u5ea7\u6a19\u63a8\u5b9a\u7d50\u679c\u3092Table 2\n\u306b\u304a\u3044\u3066\u793a\u3059\u3002 Table 1\u304b\u3089\uff0c\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u3068\u540c\u69d8\u306b\u79fb\u52d5\u8ddd\u96e2\u306e\u77ed\u3044\n\u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u3088\u308a\u63d0\u6848\u624b\u6cd5\u306e\u65b9\u304c\u6b63\u78ba\u306a\u5965\u884c\u304d\u65b9\u5411\u306e\u63a8\u5b9a \u7d50\u679c\u3092\u5f97\u3089\u308c\u3066\u3044\u308b\u3053\u3068\u304c\u78ba\u8a8d\u3067\u304d\u308b\u3002\u63d0\u6848\u624b\u6cd5\u306b\u304a\u3051\u308b\n\u4e0a\u624b\u304f\u30de\u30c3\u30c1\u30f3\u30b0\u3067\u304d\u305a\u306b\uff0c\u30ce\u30a4\u30ba\u3068\u3057\u3066\u5f71\u97ff\u3092\u4e0e\u3048\u3066\u3057 \u307e\u3063\u305f\u3053\u3068\u304c\u539f\u56e0\u3068\u3057\u3066\u8003\u3048\u3089\u308c\u308b\u3002 \u307e\u305f Table 2\u304b\u3089\uff0c3\u6b21\u5143\u5ea7\u6a19\u306e\u63a8\u5b9a\u7d50\u679c\u306b\u304a\u3044\u3066\u3082\u307b\u307c \u6b63\u78ba\u306b\u63a8\u5b9a\u3067\u304d\u3066\u3044\u308b\u3053\u3068\u304c\u78ba\u8a8d\u3067\u304d\u308b\u3002\u30ab\u30e1\u30e9 CCD\u7d20\n\u5b50\u9762\u65b9\u5411\u306b\u95a2\u3057\u3066\u306f\uff0c\u4e00\u90e8\u5965\u884c\u304d\u63a8\u5b9a\u7d50\u679c\u3068\u77db\u76fe\u304c\u751f\u3058\u3066 \u3044\u308b\u90e8\u5206\u304c\u898b\u53d7\u3051\u3089\u308c\u308b\u3002\u3053\u308c\u306f\u30ab\u30e1\u30e9\u5185\u90e8\u30d1\u30e9\u30e1\u30fc\u30bf\u7528 \u3044\u3066\u3082\uff0c\u8003\u616e\u3057\u304d\u308c\u306a\u304b\u3063\u305f\u30ab\u30e1\u30e9\u306e\u72b6\u614b\u8aa4\u5dee\u306e\u5f71\u97ff\u3067\u3042 \u308b\u3068\u8003\u3048\u3089\u308c\u308b\u3002\n\u4eca\u56de\u306e\u5b9f\u9a13\u3067\u306f\u5e45 40 mm\u30fb\u9ad8\u3055 85 mm\u306e\u5bfe\u8c61\u7269\u4f53\u3092\u7528\u3044 \u305f\u3002\u901a\u5e38\uff0c\u30ed\u30dc\u30c3\u30c8\u30cf\u30f3\u30c9\u306b\u3066\u5bfe\u8c61\u3092\u53d6\u5f97\u3059\u308b\u5834\u5408\uff0c\u30de\u30fc\u30b8 \u30f3\u3092\u542b\u3081\u305f\u30cf\u30f3\u30c9\u306e\u5927\u304d\u3055\u306f\u7d04 2\u500d\u3092\u60f3\u5b9a\u3059\u308b\u3053\u3068\u304b\u3089\uff0c\u672c\n\u5b9f\u9a13\u3067\u4f7f\u7528\u306e\u5bfe\u8c61\u7269\u4f53\u3092\u53d6\u5f97\u3059\u308b\u306b\u306f\u554f\u984c\u306a\u3044\u7cbe\u5ea6\u3067\u3042\u308b \u3068\u3044\u3048\u308b\u3002\u5ea7\u6a19\u63a8\u5b9a\u307e\u3067\u306b\u8981\u3057\u305f\u64ae\u5f71\u56de\u6570\u306f 3\u56de\u3068\u306a\u3063\u3066 \u304a\u308a\uff0c\u52b9\u7387\u7684\u304b\u3064\u6b63\u78ba\u306a\u30bb\u30f3\u30b7\u30f3\u30b0\u304c\u5b9f\u73fe\u3067\u304d\u305f\u3068\u8a00\u3048\u308b\u3002\n10. \u304a\u308f\u308a\u306b\n\u672c\u8ad6\u6587\u3067\u306f\u8907\u6570\u306e\u7269\u4f53\u540c\u58eb\u304c\uff0c\u5bc6\u306b\u914d\u7f6e\u3055\u308c\u3066\u3044\u308b\u3088\u3046 \u306a\u72b6\u6cc1\u306b\u304a\u3044\u3066\uff0c\u5404\u5bfe\u8c61\u306e\u6b63\u78ba\u306a 3\u6b21\u5143\u5ea7\u6a19\u3092\u6c42\u3081\u308b\u624b\u6cd5 \u3092\u63d0\u6848\u3057\u305f\u3002\u63d0\u6848\u624b\u6cd5\u306f\u5404\u5bfe\u8c61\u304c\u72ec\u7acb\u3057\u3066\u30bb\u30f3\u30b7\u30f3\u30b0\u3067\u304d\n\u308b\u5730\u70b9\u3092\uff0c\u30ab\u30e1\u30e9\u306e\u52d5\u304d\u306b\u5bfe\u5fdc\u3057\u305f\u753b\u9762\u5185\u306e\u5bfe\u8c61\u306e\u898b\u3048\u65b9 \u5909\u5316\u3092\u30e2\u30c7\u30eb\u5316\u30fb\u4e88\u6e2c\u3057\uff0c\u80fd\u52d5\u5316\u3059\u308b\u3053\u3068\u3067\u3088\u308a\u52b9\u7387\u7684\u306a \u30bb\u30f3\u30b7\u30f3\u30b0\u304c\u53ef\u80fd\u3068\u306a\u3063\u305f\u3002 \u80fd\u52d5\u8996\u899a\u306b\u3088\u308a\u52b9\u7387\u7684\u306a\u30bb\u30f3\u30b7\u30f3\u30b0\u3092\u3057\u3064\u3064\uff0c\u56de\u8ee2\u578b\u30b9\n\u30c6\u30ec\u30aa\u7acb\u4f53\u8996\u3092\u7528\u3044\u308b\u3053\u3068\u3067\u5e73\u884c\u79fb\u52d5\u8ddd\u96e2\u3092\u5341\u5206\u306b\u3068\u308b\u3053 \u3068\u304c\u3067\u304d\u308b\u3088\u3046\u306b\u306a\u308a\uff0c\u8ddd\u96e2\u306e\u77ed\u3044\u5e73\u884c\u30b9\u30c6\u30ec\u30aa\u306b\u6bd4\u3079\u3066 \u7cbe\u5ea6\u306e\u826f\u3044\u7d50\u679c\u3092\u5f97\u308b\u3053\u3068\u3092\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u53ca\u3073\u5b9f\u9a13\u306b \u3066\u78ba\u8a8d\u3059\u308b\u3053\u3068\u304c\u3067\u304d\u305f\u3002\n\u4eca\u56de\u306f\u753b\u50cf\u51e6\u7406\u624b\u6cd5\u3068\u3057\u3066\u9ad8\u901f\u3067\u3042\u308b\u6b63\u898f\u5316\u76f8\u95a2\u306e\u307f\u3092 \u7528\u3044\u305f\u3053\u3068\u304b\u3089\uff0c\u524d\u63d0\u6761\u4ef6\u3068\u3057\u3066\u521d\u671f\u4f4d\u7f6e\u306b\u304a\u3044\u3066\u5bfe\u8c61\u540c \u58eb\u306f\u72ec\u7acb\u3057\u3066\u8a8d\u8b58\u3067\u304d\u308b\u5fc5\u8981\u6027\u304c\u3042\u3063\u305f\u304c\uff0c\u5b9f\u74b0\u5883\u306b\u9069\u5fdc \u3055\u305b\u308b\u305f\u3081\u306b\u306f\u521d\u671f\u4f4d\u7f6e\u306b\u304a\u3044\u3066\u5bfe\u8c61\u540c\u58eb\u304c\u91cd\u306a\u3063\u3066\u898b\u3048\n\u3066\u3044\u3066\u3082\u30bb\u30f3\u30b7\u30f3\u30b0\u3067\u304d\u308b\u5fc5\u8981\u6027\u304c\u3042\u308b\u3002\u305d\u3053\u3067\u521d\u671f\u72b6\u614b \u306b\u304a\u3044\u3066\u306e\u307f\uff0cedge\u60c5\u5831\u53ca\u3073 LmedS\u30cf\u30d5\u5909\u63db (13) (14)\u3092\u7528\u3044 \u305f\u753b\u50cf\u51e6\u7406\u30b7\u30b9\u30c6\u30e0\u3092\u5c0e\u5165\u3059\u308b\u3053\u3068\u3067\uff0c\u3053\u306e\u554f\u984c\u306b\u5bfe\u3057\u3066\n\u5bfe\u51e6\u3057\u3066\u3044\u304d\u305f\u3044\u3002 \uff08\u5e73\u621020\u5e7412\u670824\u65e5\u53d7\u4ed8\uff0c\u5e73\u621021\u5e746\u670823\u65e5\u518d\u53d7\u4ed8\uff09\n\u6587 \u732e\n\uff08 1\uff09 D. Lowe: Distinctive image features from scale-invariant keypoints, International, Journal of Computer Vsion (IJCV), Vol.60, No.2, pp.91\u2013110 (2004) \uff08 2\uff09 \u4e95\u539f\u6709\u4ec1\u30fb\u85e4\u5409\u5f18\u4e98\u30fb\u9ad8\u6728\u96c5\u6210\u30fb\u516c\u6587\u5b8f\u660e\u30fb\u7389\u6d25\u5e78\u653f\uff1a\u300c\u7570\u306a\u308b\u90e8\u5206 \u7a7a\u9593\u306b\u304a\u3051\u308b PCA-SIFT \u3092\u7528\u3044\u305f\u4ea4\u901a\u9053\u8def\u6a19\u8b58\u8a8d\u8b58\u300d \uff08 3\uff09 K. Kinoshita and K. Deguchi: \u201cAn Optimal Camera Movement for Active\n\u96fb\u5b66\u8ad6 D\uff0c129 \u5dfb 12 \u53f7\uff0c2009 \u5e74 1161" + ] + }, + { + "image_filename": "designv8_17_0004142_tation-pdf-url_20709-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004142_tation-pdf-url_20709-Figure18-1.png", + "caption": "Fig. 18. The phasor diagram of the voltage sag compensation in the R-L load", + "texts": [ + " To compensate the voltage sag using SMES, it is necessary that the proper values of am and inv\u03d5 be calculated and applied to the inverter. If the phasor voltage of the R-L load 2 www.intechopen.com Power Quality \u2013 Monitoring, Analysis and Enhancement 274 (resulting only from the generator) before and after the voltage sag is shown by pv and nv , respectively, and the phasor voltage of this R-L load (resulting only from connecting the SMES to the power network) after the voltage sag is shown by , smesv then the phasor diagram of the R-L load voltage can be shown as given in Fig. 18, using which, the following equations can be obtained: 1 sin sin tan cos cos \u2212 \u2212 = \u2212 p p n n smes p p n n g \u03bd \u03d5 \u03bd \u03d5 \u03d5 \u03bd \u03d5 \u03bd \u03d5 (14) ( )cos cos cos= \u2212smes p p n n smes\u03bd \u03bd \u03d5 \u03bd \u03d5 \u03d5 (15) By calculating smes\u03d5 and smesv from (14) and (15), and by using the power flow that considers only the effect of the SMES system, the values of the am and inv\u03d5 for applying to the threelevel NPC inverter can be calculated. The power network shown in Fig. 17 was simulated using MATLAB software; the parameters used in this figure are the same as those defined in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002141_ngRunqiG1000407F.pdf-Figure4-5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002141_ngRunqiG1000407F.pdf-Figure4-5-1.png", + "caption": "Figure 4-5. (a) Even-mode network of the prototype I. (b) Odd-mode network of the prototype I.", + "texts": [ + " The TZs of the proposed dual-band BPFs are only determined by the characteristic impedances of the parallel connected MMRs and have an explicit form, as shown in Table 4.1. These expressions of TZs can be confined under the targeted TZs, thus deriving one set of equations. Another set of 68 equations is obtained by equating the coefficients of the numerator, to get the same distribution of the reflection zeroes. All the circuit design parameters are obtained by solving two sets of equations. 4.2.5 Synthesis Procedure Before the discussion of any circuit schematic, a complete synthesis procedure is summarized in Figure 4-5. First the design specifications are given including the information as the center and the band edge frequencies and the ripple factor. The TZs are considered with their locations in the real and imaginary frequency plane. The filter order for each passband is fixed as three. Next, the filter schematic is chosen based on Table 4.1. The circuit selecting criteria is mainly based on the controllability of the ripple factor and the locations of the TZs. Once the circuit schematic is determined, the even-/odd-mode analysis method is used to derive its 69 transfer function", + " Another explanation is simply put that the MMR (Z1, Z2 and Z3) is responsible for defining inner edge frequency as well as to generate the TZs. Zs is for defining the outer edge frequency as well as to provide an appropriate loading to the MMR (Z1, Z2 and Z3). Thus, Zs alone is ill-adequate to achieve a controllable ripple factor. An iterative/optimization method by the commercial toolbox [86] has been used to solve the non-linear equation. The choice of the initial value would be multiple. One example would be the two parallel connected UWB BPFs (seen in Figure 4-1) of the same bandwidth as (\u03b82-\u03b84)/90. Figure 4-5 shows the frequency responses of one pair of controllable TZs. As tz2 varies from a negative to positive value, the second pair of TZs is moved from imaginary to real frequencies. The calculated response is indistinguishable from the desired theoretical one, which has verified the synthesis procedure. 73 4.3.2 Prototype II with Two Pair of Controllable TZs For the prototype II, coupled lines are used to control the pair of TZs in the imaginary frequencies (also it has the influence toward the other pair of TZs as tabulated in Table 4", + "3, the rejection for the lower/upper side of the 1st/2nd passband improves slightly, while the rejection between the two passbands drops. Figure 4-11 shows the variation of the TZs in the imaginary frequency plane (as the variation of tz1) with fixing the other design specifications. As tz1 changes from -1 to -5, there is little change of the filtering responses as seen in Figure 4-11(a), while there is an obvious change for the group delay as seen in Figure 4-11(b). In a summary of the three circuit prototypes as tabulated in Table 4.1, according to Figure 4-5, Figure 4-7 and Figure 4-9, these circuit schematics share the similar circuit structure and the design principle, while prototype II has an additional degree of freedom in controlling the group delay and prototype III having the capability in further adjusting the in-band ripple factor. Therefore, it can be concluded that the proposed structure and the synthesis procedure has the capability in effectively controlling the in-band ripple factor (\u025b) and the dual-band isolation. 77 Table 4.4 Design Parameters of Prototype III under Different \u025b Characteristic Impedance (\u03a9) \u025b Z1e Z1o Z2 Z3 Zs1 Zs2 160" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003775_f_version_1632811037-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003775_f_version_1632811037-Figure1-1.png", + "caption": "Figure 1. The generalized approach of a single-layer FSS structure (the ground plane is omitted).", + "texts": [ + " Section 3 presents and discusses the optimization results obtained by the utilization of the proposed framework to design and optimize two representative examples of FSSs structures that exhibit dual-band frequency operation. In detail, Section 3.1 describes the parameters that are considered to set up the optimization process for designing both the unit cell and the FSS structure, whereas Sections 3.2 and 3.3 include the main results based on several system metrics obtained by the optimization process. Finally, Section 4 concludes the findings and outlines the future steps of this work. Figure 1 pictures the generalized approach of a single-layer FSS structure. Without losing the generalization of the problem definition, a single-layer FSS design (a similar problem definition can be expressed for dual- or even triple-layer FSS structures) consists of a unit cell (usually of metal) which is periodically repeated along a two-dimensional lattice. Beneath the lattice of the unit cells, a grounded substrate layer (usually of dielectric) is placed. Based on the electromagnetic theory, when an incident field triggers the FSS structure, the latter one performs as an absorber [13], a reflector [14], or a transmitter [12], based on the frequency of the incident field" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000332_u.167226813.34621561-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000332_u.167226813.34621561-Figure2-1.png", + "caption": "Fig. 2: Mechanical Structure of Lower Limb", + "texts": [ + " The internet of things technology has also been introduced in this field to provide medical facilities at remote places. In the proposed work [31] pressure sensor is used to collect data which is transmitted by STM32 controller. 3.1 Mechanical Structure of LLRR Dynamic Equations It is often convenient to express the dynamic equation of the manipulator in terms of a single equation that abstracts some details and show some structure of the manipulator. The structure of 2-degree of freedom is taken into consideration for the rehabilitation robot[32]. This structure as shown in figure 2 consist of two links and two joints that is hip joint and knee joint to form a lower limb. Mathematically, the Newton-Euler motion equation of the 2-link manipulator is given as follows: I(q)q\u0308 + T (q, q\u0307)q\u0307 + G(q) + F (q\u0307) + \u03c4d = \u03c4 (1) Where q, q\u0307 and q\u0308 represents joint angles, velocities and accelerations. The I(q) \u2208 R2x2 denotes mass/inertia matrix, T(q,q\u0307) \u2208 R2x2 denotes the Coriolis/centrifugal matrix, G(q) \u2208 R2x1 is the force due to gravity, F(q\u0307) represents the frictional force, \u03c4d is the unknown disturbances and \u03c4 = [\u03c41, \u03c42] is the control torque where \u03c41, \u03c42 is the hip and knee joint torque respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002482_f_version_1640925346-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002482_f_version_1640925346-Figure9-1.png", + "caption": "Figure 9. H-M-H strain map for the force value of 200 N acting along the Y axis.", + "texts": [], + "surrounding_texts": [ + "The dependence of the deformation of material used for the construction of the transducer, which showed linear characteristics in relation to the excitation forces, was adopted as the basis for transducer operation. Therefore, the use of resistance strain gauges as sensors was possible. In order to increase the measurement sensitivity and avoid the need to employ a compensation system, it was decided that the four-leg Wheatstone bridge structure would be used in the developed system. To measure the three components, a redundant system in the form of four strain gauge n > 3 bridges was used. The force vector for the considered identification system of three components takes a general form of F = ( Fy, Fz, Mx ) ; therefore, to measure it, at least three strain signals must be recorded \u03c3tens = (\u03c31, \u03c32,\u03c33), which were additionally extended by a redundant signal in the adopted solution \u03c34. For conditions defined as described above, the equation system can be expressed in the matrix form (1): \u03c3tens(t) = F(t)\u00b7M (1) where: \u03c3tens(t)\u2014vector of recorded strains, F(t)\u2014vector of sought for excitations. The mathematical model of the transducer, which ties the sought-for calculations with the recorded strains, can be presented in the form of the following equation system (2): \u03c31(t) = a1\u00b7Fy(t) + b1\u00b7Fz(t) + c1\u00b7Mx(t) \u03c32(t) = a2\u00b7Fy(t) + b2\u00b7Fz(t) + c2\u00b7Mx(t) \u03c33(t) = a3\u00b7Fy(t) + b3\u00b7Fz(t) + c3\u00b7Mx(t) \u03c34(t) = a4\u00b7Fy(t) + b4\u00b7Fz(t) + c4\u00b7Mx(t) (2) where: \u03c31(t), . . . , \u03c33(t)\u2014recorded strains, Fy(t), . . . , Mx(t)\u2014excitations acting on the transducer, a1, . . . , c4\u2013sensitivity coefficients tying strains with loads. The considered equation system does not have an unambiguous solution because it is an overdetermined system. However, a pseudo-solution can be found for the system, which in accordance with the principles of the adjustment calculus is determined based on the minimum mean square error (MMSE) estimator [24]. Then, equation (3): F\u2032(t) = (( MT \u00b7M )\u22121 ) \u00b7 ( MT \u00b7\u03c3tens(t) ) , (3) is a solution indicating property (4): (M\u00b7F(t)\u2212 \u03c3tens(t)) T \u2212 (M\u00b7F(t)\u2212 \u03c3tens(t)) = min. (4) But the solution has a physical sense if the matrix ( Md T \u00b7Md ) is non-singular (5), i.e., det ( MT \u00b7M ) 6= 0 (5) Equation (5) can be interpreted as follows: the forces operating in the system cause various effects in the form of loads with different values. Otherwise, it would be impossible to determine which load caused the recorded strain increase. Strain gauge distribution on the transducer construction was shown in Figure 10. In order to measure the Fz component, a group of strain gauges numbered S5, S6, S9, S10 was used, whereas, to identify force Fy, the S1, S2, S3, S4, as well as S13, S14, S15, S16 dcomponent. Strain gauges connected into properly configured Wheatstone bridges made it possible to determine the calibration matrix: M1j M2j M3j M4j = 1 4 (\u03b56 \u2212 \u03b55 \u2212 \u03b59 + \u03b510)j 1 4 (\u03b52 \u2212 \u03b51 \u2212 \u03b53 + \u03b54)j 1 4 (\u03b514 \u2212 \u03b513 \u2212 \u03b515 + \u03b516)j 1 4 (\u03b57 \u2212 \u03b58 \u2212 \u03b511 + \u03b512)j j = 1, . . . , 4 (6) where using \u03b5n, the value of deformation of a single strain gauge was determined." + ] + }, + { + "image_filename": "designv8_17_0003103_26_tylek_203-215.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003103_26_tylek_203-215.pdf-Figure10-1.png", + "caption": "Fig. 10 Innovative design of an openable dibble on rockers", + "texts": [ + " Ultimately, the planting module is to be mounted on a specialised, autonomous carrier, while in the case of aggregating the module with agricultural or forestry tractors, the frame of the working unit should be equipped with an appropriate levelling system. The developed conceptual model of such a solution is presented in Fig. 9. Attached to the frame in its rear part, there is an adjustable swing axle with support wheels and, in its front part, a swing hitch to the tractor. Levelling is performed by analysing the indications from the acceleration sensor (gravity sensor) mounted to the frame of the working unit. Fig. 10 and 11 below show an openable dibble in which the jaws and the cylinder are opened by one drive. The appropriate kinematics is ensured by rockers with pivots placed at an angle, thanks to which the opening occurs as a result of lifting the movable parts of the dibble. The recessed part is characterised by Croat. j. for. eng. 44(2023)1 209 relatively high slenderness which minimises the resistance during penetration into the soil. The fixed part of the dibble remains in contact with the ground until the dibble is fully open, which ensures proper following of the ground during continuous operation of the machine" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001892_e_download_4116_2763-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001892_e_download_4116_2763-Figure3-1.png", + "caption": "Fig. 3. Diagram showing the flow paths", + "texts": [ + "12) of non-linear differential equations of the first order and differential equation (2.10) of the second order constitute the base for the determination of characteristic (2.1) of the mono-tube hydraulic shock absorber with and without the bypass. One can denote Qj\u2212i (j = 1, i = 2 or j = 2, i = 1) \u2013 the mass flow rate from chamber Kj (e.g. rebound for j = 1) to chamber Ki (e.g. compression i = 2). In the case of the flow in the reverse direction: Qj\u2212i = 0 (then Qi\u2212j 6= 0). Since the oil flow between these chambers occurs through orifices in the piston (Fig. 3) and through the bypass, the flow rate can be written as Qj\u2212i = Q piston j\u2212i +Q bypass j\u2212i (2.13) where the flow rate Qpistonj\u2212i is the sum of three flow rates (Fig. 3) Qpistonj\u2212i = Q leakage j\u2212i +Qorificej\u2212i +Q valve j\u2212i (2.14) representing the flow rates resulting from leakage past piston, flow through bleed orifices and flow through valves in the piston. The oil flow in the reversed direction, from chamber Ki to Kj, determined by the mass flow rate Qi\u2212j , causes a mass decrease in chamber Ki. Thus, the oil mass change in chamber Ki can be written in the following form Qi = Qj\u2212i \u2212Qi\u2212j (2.15) Since, from the law of mass conservation between mass flow rates the following relation occurs: Q1 +Q2 +Q3 = 0", + " After referring the orifice area to the area of the compression side of the piston, this area depends on the dimensionless parameter \u03b1j\u2212i in the following way Aorificej\u2212i = \u03b1j\u2212iA2 (2.21) Values of the remaining areas depend on the oil pressure in the neighbouring chambers of the shock absorber and on the relative piston displacement. The flow through the compression intake or through the rebound intake is controlled by pressures p1 and p2. Bleed orifices are the most often covered by a stack of circular plates (Fig. 3) deflecting under the influence of the resultant pressure force, and gradually uncovering the orifices. The effective cross-sectional area depends mainly on the pressure difference p1 \u2212 p2 in the shock absorber chambers as well as on geometrical and physical parameters of the plates. The accurate determination of the area change law requires the accurate modelling of the specific technical solution. Disregarding inertia of the plates, the valve can be modelled by means of a stiff plate preliminarily pressed down by a spring of a progressive characteristic" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002748_e_download_7184_5916-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002748_e_download_7184_5916-Figure8-1.png", + "caption": "Fig. 8 \u2013 Diagram of the relationship between the hexagons", + "texts": [ + " The projections of the midspan composite joint and the edge composite joint on the lower chord plane are hexagons and octagons respectively, and the hexagons and octagons are not necessarily regular polygons. The specific geometric parameters are shown in Figure 7 (a). DOI 10.14311/CEJ.2021.01.0014 195 The single member of the three-direction grid single-layer reticulated structure is replaced by the inverted pyramid truss. In order to make the huge grid arrangement even, the overall structure stress reasonable, the member type reduces as far as possible, so the inverted quadrangular pyramid truss must be arranged reasonably. In the structure shown in Figure 8, the lines connecting the central point of the hexagon to the four corner points are equal, that is, the lengths of the four line segments are equal and are all e; The connecting lines of the central point of the hexagon and the remaining two corner points are equal, and the lengths of the two line segments are B; In order to ensure that the members are evenly distributed and properly stressed, l in the illustration must be perpendicular and bisect C. To sum up, in order to reduce the structural mega grid to the form as shown in Figure 7 (b), and ensure uniform bar specification and uniform stress, the triangle divided by the hexagon must be a regular triangle, that is, b = e, so the hexagon of the projection of the mid-span composite joint in the lower chord plane must be a regular hexagon" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure2-1.png", + "caption": "Figure 2. Loading the truss using the generator frame on the electric motor", + "texts": [ + " mounting rod (1); control panel and battery (2); driver body (3); driver's legs (4); front body (5); rollbar body (6) rear body (7); main stem (8). The 3D model is created using Autodesk Inventor with the frame generator feature. The 3D modeling is utilized to provide a detailed overview of the designed structure of the frame. The frame structure is supported by two main bars and reinforced by several supporting bars. The main bars receive reaction forces from seven types of supporting bars whose strength is calculated. Figure 2 illustrates the 3D modeling and the distribution of loads on the bar frame. The weight force is assumed to be located at the center of the bar. Assumptions for mass include the driver's mass of 56 kg, the driver's body mass being 85% of the driver's mass, i.e., 47.6 kg, the driver's leg mass being 15% of the driver's mass, i.e., 8.4 kg, electric motor mass of 3.5 kg, and control panel and battery mass of 3.2 kg. The assumed mass of the prototype car body is 28 kg, with 60% of the mass on the roll bar, i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure51-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure51-1.png", + "caption": "Figure 51 P-POD Mk. III Rev. E Door", + "texts": [ + " The results involved a slight increase in stress from the previous design, yielding a Margin of Safety of 0.4, down from 0.5 for the previous design. This decrease was not seen as an issue. The FEA results are shown below in Figure 50. Page 65 P-POD Mk. IV Door The next part evaluated was the Door. This part was seen as a part that was due for a redesign. It is consistently the weak point of the P-POD, and often deflects enough to exhibit a noticeable increase in door-collar gap. A stiffer door that could better compress the EMI gasket was desired. The P-POD Mk. III Rev. E Door is shown below in Figure 51. The first item addressed was the material coating employed on the P-POD Door. A PTFE impregnated hard anodization was used on the part, which requires a high temperature bake that lowers the yield stress to 80% of its original value. Because this part is the limiting factor of the P-POD, the need of this coating was seriously questioned. The next best alternative is simply using a standard hard anodization process, increasing the hardness of the running surface, while only taking a slight reduction in sliding friction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004399_.srce.hr_file_276795-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004399_.srce.hr_file_276795-Figure3-1.png", + "caption": "Fig. 3 Basic digging strategies", + "texts": [ + " Steps 3 and 4 are key operations requiring the identification of the bucket-soil interaction and the generation of adaptive bucket paths. Based on the soil characteristics as well as the conditions of any encounters between the bucket and buried obstacles, the excavator can be operated according to the following digging strategies: Penetration and curl: This strategy is used to excavate soft soils, which produce low reaction forces. The bucket is moved into the ground vertically. Once the desired penetration depth is reached, the bucket is curled to collect soil (Fig. 3a). Penetration, drag, and curl: This strategy is used to dig hard soils, which are difficult to penetrate and they produce high reaction forces. Boom joints are used to control the bucket when it penetrates the soil. The bucket tooth is then dragged in a straight line to collect the soil (Fig. 3b). TRANSACTIONS OF FAMENA XLI-3 (2017) 67 (a) Penetration and rotation (soft soil) (b) Penetration, drag and curl (hard soil) Cartesian plane XOY. A large, hard rock was located on the bucket path as an obstacle. A dynamic simulation was performed to investigate the digging behaviour and to identify reaction forces according to the soil type. The initial bucket angle of 101\u00b0 and the simulation time of 10s were used in order to increase the accuracy of the simulation results. The forces obtained were used as a knowledge base to develop an intelligent controller of the excavator" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003809_el-03253472_document-Figure3.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003809_el-03253472_document-Figure3.9-1.png", + "caption": "Figure 3.9 : Vue d\u2019un port d\u2019onde excit\u00e9 (a) et de la boite d\u2019air entourant la structure (b)", + "texts": [ + " Deux lignes d\u2019acc\u00e8s de longueur lacces=40mm chacune sont rajout\u00e9es de part et d\u2019autre de la ligne RH simul\u00e9e afin que les performances de la ligne ne soient pas perturb\u00e9es par les effets de bords de la structure. Nous allons \u00e9tudier ici plus en d\u00e9tail le cas de la ligne 0-LH, sachant que le proc\u00e9d\u00e9 est identique pour les autres lignes \u00e9qui-LH. DECRIPTION DE LA METHODE DE DESIGN DE DEPHASEURS CRLH-TL 87 Les lignes sont mod\u00e9lis\u00e9es avec un ruban d\u2019\u00e9paisseur hline=37\u00b5m et un plan de masse d\u2019\u00e9paisseur hmasse=73\u00b5m. Pour simuler la propagation d\u2019une onde dans la ligne, deux ports d\u2019onde de part et d\u2019autre de la ligne sont cr\u00e9\u00e9s et excit\u00e9s (voir Figure 3.9.a). Afin de borner le domaine de calcul en consid\u00e9rant le prototype analys\u00e9 dans l\u2019air, une boite d\u2019air entoure la structure avec une condition aux limites de radiation (voir Figure 3.9.b). Nous pouvons alors observer dans un premier temps les r\u00e9sultats concernant les imp\u00e9dances d\u2019entr\u00e9e et de sortie de la ligne afin de valider l\u2019hypoth\u00e8se d\u2019une ligne adapt\u00e9e \u00e0 50\u2126. L\u2019imp\u00e9dance d\u2019entr\u00e9e \u00e9tant l\u00e9g\u00e8rement d\u00e9cal\u00e9e de la valeur 50\u2126 (<3%), une rapide \u00e9tude param\u00e9trique (<3min) de la largeur de la ligne Wline permet d\u2019obtenir une valeur plus adapt\u00e9e de 1.61mm. Pour \u00e9valuer si cette ligne a le m\u00eame comportement que la ligne th\u00e9orique calcul\u00e9e, nous allons nous int\u00e9resser \u00e0 sa phase enroul\u00e9e" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004966_f_version_1447207939-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004966_f_version_1447207939-Figure2-1.png", + "caption": "Figure 2. Illustration of the proposed microfluidic metamaterial absorber with the rectangular waveguides: a = 64 mm, b = 16 mm, c = 53 mm, x = 41.5 mm, y = 41.5 mm, L = 22.92 mm, w = 10.22 mm.", + "texts": [ + " As a result, the resonant frequency varies depending on the properties of the fluid on the surface. The proposed tuning mechanism is material dependent, while the operation of PIN diodes or MEMS switches are voltage dependent which needs continuous power supply. Although external energy consumption is required to inject liquids into the channels, the microfluidic technology does not require a complex bias network design. The absorbing performance of the proposed absorber is tested in the waveguide as illustrated in Figure 2. The proposed absorber is inserted into two open-ended rectangular waveguides in full-wave simulation setup. The incident electric and magnetic fields are indicated in Figure 2. The 1 \u00d7 4 unit cell array is designed after considering the size of the waveguide. In order to inject liquid metal through inlets and outlets, we designed the length (a) of the sample to be larger than the length of the waveguide. The absorption phenomenon of the metamaterial absorber can be understood by simultaneous electric and magnetic resonances [33,34]. Figure 3a,d shows the simulated magnitudes of electric fields of the designed microfluidic metamaterial absorber at 10.96 GHz, and 10.61 GHz, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000469_uyenHongQuan2010.pdf-Figure3.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000469_uyenHongQuan2010.pdf-Figure3.1-1.png", + "caption": "Figure 3.1: Effective angle of attack for horizontal tail", + "texts": [ + "7) - Stators: The stators are always configured in asymmetric setting; hence, in the longitudinal plane, only the total drag is affected by the stators. 2 0.2557 0.0371 SD SC \u03b4= + (3.8) Chapter 3: System modeling and simulation by MATLAB/Simulink 20 - Wing and duct: 1.5236yC \u03b2= \u2212 (3.9) 0.0083lC \u03b2= \u2212 (3.10) 0.0218nC \u03b2= or 3 0.2508 0.0153nC \u03b2 \u03b2= + (3.11) - Stators: Only rolling moment is affected by stators\u2019 deflection. 0.0425l SC \u03b4= \u2212 (3.12) Due to the geometry of the vehicle, the horizontal tail only exposes to the free air stream if the angle of attack is larger than the effective value which is shown in Figure 3.1 below: This idea was first given by Suhartono (23), and the effective angle of attack will be calculated as: The duct\u2019s diameter is about 20cm , and the distance from duct\u2019s exit to the horizontal tail\u2019s trailing edge is about18cm . Hence, the angle of attack at which the horizontal tail becomes exposed to the free air stream is: ( )1 010 tan 0.6 34 18 effective rad\u03b1 \u2212 = = \u2248 (3.13) Chapter 3: System modeling and simulation by MATLAB/Simulink 21 As this value is relatively high for cruising flight, it can be concluded that the horizontal tail is fully under the air stream exiting from the duct" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004522_nf_trs2017_01002.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004522_nf_trs2017_01002.pdf-Figure1-1.png", + "caption": "Fig. 1. Exterior design of continuous silo foundation.", + "texts": [ + " Extended foundation and the outlined in the plan foundations deform during stabilization of soils and under work, which determines the overall deformation diagram of the foundation and its stress-strain behavior (SSB) in the future. The problem of determining SSB comes down to solving complex configuration plate with stiffness characteristics, which differ significantly from one another, on quasi-elastic basis. Stiffness parameters of a large continuous foundation depend on geometrical dimensions (Fig. 1). The value of soil resistance under the bottom of foundation depends on stiffness of the foundation itself and the applied loads, which are different as a result of distribution across the footprint of the structure. There are numerous loads across the foundation: the pressure, transferred from the upper body of the silo (snow load); the dead weight of the upper body of the silo; the load of loose materials on the walls of the silo resulting from friction; the load of the weight of the product applies to the other parts of the silo" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001789_cle_download_505_375-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure7-1.png", + "caption": "Figure 7. Flux density plot of 5 kW, 24 000 rpm reference motor.", + "texts": [ + " Figure 4 represent the torque profile of 2 kW, 200 000 rpm IPMSM obtained from FEA. Figure 5 shows the flux density plot of 2 kW, 200 000 rpm IPMSM. This reference 2 kW, 200 000 rpm IPMSM has average torque of 0.0956 N.m. The actual flux density is close to the assumed flux density in various magnetic sections of the motor. The closeness between actual flux density and assumed flux density validates the sizing of the motor. The torque profile and flux density plot of 5 kW, 24 000 rpm IPMSM using M19 material is in Figure 6 and Figure 7, respectively. This 5 kW, 24 000 rpm IPMSM has average torque of 1.99 N.m. It can be observed that the actual flux density is close to the assumed flux density in various magnetic sections of the 5 kW motor. The torque profile and flux density map of the reference 120 kW, 10 000 rpm IPMSM acquired from FEA are shown in Figures 8 and 9, respectively. The average torque of this 120 kW, 10 000 rpm IPMSM is 114 N.m. Similar to the previous two designed motors, the actual flux density is close to the assumed flux density in various magnetic sections of the motor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004581_f_daic2020_03006.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004581_f_daic2020_03006.pdf-Figure1-1.png", + "caption": "Fig. 1. Projections of an ellipsoid working body Fig. 2. Experimental unit", + "texts": [], + "surrounding_texts": [ + "In accordance with the requirements of state and industry standards (GOST 24057-80, OST 70.2.15-73, OST 70.2.2-2002), experimental studies of the working body of the rotary tool, as well as its economic and energy assessment, were carried out in the laboratory. Dynamometry is a reliable experimental method that can be used to determine the traction resistance of surface tillage tools [4]. The direct measurement method allows to get the value of the required parameter through the force measuring link, and the indirect measurement method - based on the results of any other characteristics measuring. An electronic dynamometer is used as a link for force measuring, and various sensors [15] connected to a working body or tool are used to implement indirect measurement methods. The experimental device developed by us was installed in a separate deformable beam, which was attached to the frame of the cart. Strain gauge resistors of the brand KF5P1-15200 (hereinafter referred to as the load sensor) were installed on the beam in such a way that it was possible to measure the tensile strain, and therefore the traction resistance of the disk working body. According to the prepared planning matrix, the experiment is repeated three times for different values of the tillage depth and the speed of ellipsoid disk movement. At the initial stage, in accordance with the operating instructions of the measuring information system IP 264, strain gauge bridges were calibrated. As it is known, when the experimental tool moves forward along the soil channel, the strain gauge beam is stretched, as a result of which the electrical resistance of the load sensor attached to it changes. The measuring information system IP 264 processes the signals received from the strain gauge bridges and transmits them to a personal computer. With the help of computer software the measurement results are displayed graphically. Then, taking the maximum values from the graphs using calibration data, they are converted to the unit of measurement - N (Newton). When determining the traction resistance of an ellipsoid working body, the method of planning a complete factor experiment is used. Table 1 shows that the variable parameters of the experiments are as follows: working body speed (casrt) - 8, 10, 12 km/h, tillage depth (the depth of immersion of the working body in the soil) - 0.04; 0.06; 0.08 m. As a result of data processing, a quantitative assessment of the influence of various factors on the traction resistance of the disk was obtained. multiple regression equation: Y = + + + + + , (1) where Y - response function; , \u2013 the first, the second factors of the process under study, \u2212 characterizing the values of the response function Y in the centre of the plan; , - coefficients characterizing the degree of influence of the first and second factors on response function Y; , , \u2212 - coefficients characterizing the significance of the influence of relevant factors on the response function Y." + ] + }, + { + "image_filename": "designv8_17_0000095_cle_download_406_813-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000095_cle_download_406_813-Figure7-1.png", + "caption": "Fig. 7. Power transmission and clutch assembly of the carrot seeder", + "texts": [ + " 4, comprises of hopper, metering disc, and additional parts such as the seed discharge guide or stopper and furrow opener. The metering disc was designed to contact the hopper at a quarter of its circumference, which increases the chance of the seed cells to successfully load seeds during rotation. The metering discs are arranged in series on an axle (Fig. 5). The metering disc axle is in turn connected to the axle of the ground wheel by means of a chain and sprocket. Provision to engaged and disengaged the metering discs is provided by means of a clutch assembly as shown in Fig. 7. This way the seeder can still be moved through its wheel during transport and maneuvering without rotating the metering disc. Additional features to minimize the use of another pair of wheels at the rear portion of the seeder, a skid (Fig. 8) is designed that would serve as depth controller for the furrow opener. The skid is purposely designed to scrape flatten the surface of the plant bed which makes the furrow opening more efficient. It is also served as depth controller so that the furrow opener will create furrow of uniform depth" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002308_f_version_1637226395-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002308_f_version_1637226395-Figure2-1.png", + "caption": "Figure 2. Cut through the developed VEGA antenna showcasing its three sections. Together the antenna flare, throat section and planar orthomode transducer (OMT) are able to produce two distinct orthogonal linear polarizations.", + "texts": [ + " As one of the key influences on the transponder design, the antenna coupling of the newly developed L-band antennas was investigated and the results will be presented in this paper. The antenna developed for the compact transponder design in L-band is referred to as a VEGA antenna, which is an abbreviation of the German equivalent to the choked Gaussian horn antenna. The antenna is dual-polarized, which means it is able to receive or transmit two polarizations\u2014horizontal and vertical [3]. Structurally, the VEGA antenna can be separated into three parts. The antenna flare, its throat section, as well as its planar orthomode transducer (OMT) as shown in Figure 2. The antenna has an overall height of 0.75 m and a maximum diameter of approximately 0.7 m. The OMT is responsible for generating a TE11 mode, which is transformed into a hybrid mode by the throat section. Through the antenna flare, the hybrid mode will be coupled into free space as a Gaussian beam mode with linear polarization [4]. In order to generate the TE11 mode within the OMT, two metal probes opposite of each other have to be fed simultaneously with the same signal but with an induced 180\u00b0 phase difference between the probes\u2019 inputs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000999_f_version_1484806357-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000999_f_version_1484806357-Figure1-1.png", + "caption": "Figure 1. Presented antenna Geometry (a) 3-D view; (b) Top view. Figure 1. Presented antenna Geometry (a) 3-D view; (b) Top view.", + "texts": [ + " Lower frequency band of the proposed design may be termed as wideband as it covers three LTE bands 2, 3, and 9 simultaneously. The simulation of the presented MIMO antenna is performed with the help of Ansoft HFSS v 16.0 and a good agreement is found between the simulated and measured results. The remainder of this paper covers antenna geometry description in Section 2. Antenna design analysis including effect of electric field on mutual coupling will be presented in Section 3. Section 4 is dedicated to discuss results in detail and Section 5 concludes the paper. The geometry of the proposed design is shown in Figure 1. It consists of an L-shaped rectangular dielectric resonator (DR) excited by two symmetrical slots of equal dimensions coupled through microstrip feed lines. DR is made up of ceramic material (\u03b5r = 10) and has a loss tan\u03b4 = 0.002, and is placed on a ground plane of size 100\u00d7 100 mm2. FR4 substrate (\u03b5r = 4.6) of the size of the ground plane with height 1.6 mm is the base layer of the design. Figure 1a shows a cylindrical air-gap of 22 mm in height with a hole of 6 mm radius drilled in the DR along with two metallic strips (6 \u00d7 20 mm2) at the optimized position to improve isolation. A top view of the design is shown in Figure 1b, in which pl and pw is the length and width of both the coupling slots, whereas s1 + s2 + s3 is the stub length to improve impedance matching and m_w is the width of the microstrip feed lines (placed at the bottom surface of the substrate). Both the coupling slots have the dimensions pw \u00d7 pl etched on the ground plane and are fed by two 50 \u2126 microstrip feed lines. Table 1 lists the optimized dimensions of the proposed design after a thorough parametric analysis. Sensors 2017, 17, 148 2 of 15 Ishimiya et al", + " r f r f t i l e cy band of the proposed design may be termed as wideband as it covers three LTE bands 2 3, and 9 simultaneously. The simulation of the pr sented MIMO antenna is performed with the help of Ansoft HFSS v 16.0 and good agreeme t is found b tween he simulated an measured results. t t si i c i t f electric field on mutual coupling will be presented in Section 3. Section 4 is edicated to discuss results in detail and Section 5 concludes the aper. he geo etry of the proposed design is shown in Figure 1. It consists of an L-shaped rectangular dielectric resonator (DR) excited by two symmetrical slots of equal dimensions coupled through microstrip feed lines. DR is made up of ceramic material (\u03b5r = 10) and has a loss tan\u03b4 = 0.002, and is placed on a ground plane of size 100 \u00d7 100 mm2. FR4 substrate (\u03b5r = 4.6) of the size of the ground plane with height 1.6 mm is the base layer of the design. Figure 1a shows a cylindrical air-gap of 22 mm in height with a hole of 6 mm radius drilled in the DR along with two metallic strips (6 \u00d7 20 mm2) at the optimized position to improve isolation. A top view of the design is shown in Figure 1b, in which pl and pw is the length and width of both the coupling slots, whereas s1 + s2 + s3 is the stub length to improve impedance matching and \ud835\udc5a_\ud835\udc64 is the width of the microstrip feed lines (placed at the bottom surface of the substrate). Both the coupling slots have the dimensions pw \u00d7 pl etched on the ground plane and are fed by two 50 \u2126 microstrip feed lines. Table 1 lists the optimized dimensions of the proposed design after a thorough parametric analysis. Sensors 2017, 17, 148 3 of 15 This section presents the details about the dimension calculation of the DR and the parametric study of the design along with the effects of the cylindrical air-gap and metal strips on the mutual coupling between the ports", + " At the field intersection point, a cylindrical air-gap is introduced which changes the corresponding phases of the E-field at the boundaries of the air-gap. When the field enters from a higher to lower primitively material cylindrical air-gap, it deviates away from the normal direction [11], thus reducing the interaction between the E-field from the two ports. This effect can be seen at the boundaries where field through each port is tangentially oriented resulting in a considerable decrease in mutual coupling. In order to further reduce the coupling effects, two metallic strips are introduced at the corner of the DR shown in Figure 1a. It is well known that the tangential components of electric field vanish when it strikes on a metallic surface, only the transverse component can exist. This results in further deviation of the E-filed originating from each port from each other resulting in a further reduction in mutual coupling. Air-gaps [12] and metallic strips are being used to increase bandwidth and impedance matching, respectively. However, in this design this combination has been used as a coupling reduction technique. The magnitude E-field plot is shown in Figure 7", + " At the field intersection point, a cylindrical air-gap is introduced which changes the corresponding phases of the E-field at the boundaries of the air-gap. When the field enters from a higher to lower primitively material cylindrical air-gap, it deviates away from the normal direction [11], thus reducing the interaction between the E-field from the two ports. This effect can be seen at the boundaries where field through each port is tangentially oriented resulting in a considerable decrease in mutual coupling. In order to further reduce the coupling effects, two metallic strips are introduced at the corner of the DR shown in Figure 1a. It is well known that the tangential components of electric field vanish when it strikes on a metallic surface, only the transverse component can exist. This results in further deviation of the E-filed originating from each port from each other resulting in a further reduction in mutual coupling. Air-gaps [12] and metallic strips are being used to increase bandwidth and impedance matching, respectively . However, in this design this combination has been used as a coupling reduction technique. The magnitude E-field plot is shown in Figure 7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004695_oradea2018_02004.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004695_oradea2018_02004.pdf-Figure6-1.png", + "caption": "Fig. 6. Device used to determine the static friction coefficients", + "texts": [ + " The reciprocating module, shown in figures 3 and 4, is suitable for performing tests on small samples of different pieces, and the motion is alternative rectilinear. The work frequency of the module is between 0.1 \u2013 60 Hz, and the maximum load is F = 1000 N. Also, the rotary module, presented in the same figure, is suitable for experimental determination in rotational motions. The torque value range 0.001 \u2013 5000 rpm, and the maximum load force is F = 1000 N. To evaluate the static friction coefficient between the tooth chain links and guide segments there were designed and built four testing devices C. C. Gavril\u0103 [6]. In figure 6, there are presented the models used for tdetermining the friction coefficient, in the laboratory conditions from Transilvania University Research Institute. All models were designed with CATIA V5. In the prismatic tribometer there were performed two study cases: case I - determining the static friction coefficient at contact between the tooth chain links and PA46 polyamide guide segments, in lubricated environment; case II - determining the static friction coefficient at contact between the tooth chain links and PA66 polyamide guide segments, in lubricated environment, presented in figure 7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001345_f_version_1621584150-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001345_f_version_1621584150-Figure13-1.png", + "caption": "Figure 13. Solid model of the propeller.", + "texts": [ + "018 \u22125 \u2264 \u03b1 \u2264 \u22122 \u22122 \u2264 \u03b1 \u2264 1 1 \u2264 \u03b1 < 15 (30) According to the performance calculation process, chord length b and pitch angle \u03b8 are the initial input condition. In the different sections, b is fixed once the diameter of the propeller is determined. To meet the rated thrust, \u03b8char is adjusted, and the iterative calculation needs to be performed with the data of airfoil performance. The shape parameters are shown in Figure 12. The pitch angle decreased with the increase of r. The chord length first increased, reached a maximum value near 0.5R, and then decreased. The 3D solid model of the propeller is shown in Figure 13 and was constructed according to the design parameters. Figure 14 shows the angle of attack and interference angle of the propeller, which were designed according to the vortex theory and standard strip analysis. The interference angle \u03b2 affects the angle of attack \u03b1 and, consequently, the aerodynamic performance of the blade. The AOA was negative near the root, and most of the blade section showed a small AOA. The deviation of four different mesh qualities is shown in Figure 15. The cell number of the coarse mesh was 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000753_ownload_120693_75664-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000753_ownload_120693_75664-Figure5-1.png", + "caption": "Figure 5. The robustness optimization uses sequential and hierarchical FEA of global and local models. The global structure and the local weld models are linked together using the bending and membrane stresses in the vicinity of the weld.", + "texts": [ + " The red circles represent the fatigue life with 2 mm misalignment and varying weld angle and size (see Figure 4 for definitions). In both groups (of red circles), the fatigue life increases with increasing weld size. For the lower group, with an increase in fatigue life up to 29%, the weld angle is 15 degrees. For the upper group, with a decrease in the fatigue life up to 30%, the weld angle is 30 degrees. Demonstration of the robustness optimization workflow The FE-modeling techniques are presented in Figure 5: A parametric FE-model was prepared using Ansys Parametric Design Language (APDL) macros. The coarse linear shell element mesh was used in the FE-model of the structure, and the dense plane strain element mesh for the welded details in separate models. The global structure and local weld models were linked together using the bending and membrane stresses in the vicinity of the weld. The main steps of the robustness optimization are presented in Figure 6. In Figure 6, first the input distributions are defined based on the measurements or the estimated values, then the surrogate model is formed by using the parametric FEA" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004597_s-4255722_latest.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004597_s-4255722_latest.pdf-Figure8-1.png", + "caption": "Fig. 8: 3D printed actuator pressurized and corresponding bending angle measured.", + "texts": [ + " As previously mentioned, the experimented also allowed to register data on the bending of the actuators during the test. The results shown in Table 3 present values measured by the bending of the sensor over each cycle; the values are acquired by the 5V sensor and digitally converted by the Arduino Uno in the [0-1023] range. Preliminary experiments were performed to characterize the behavior of the sensor and map the values read by the sensor corresponding to specific bending angles of soft actuators; a linear relationship between sensor reading and global bending angle of the actuator, computed as showed in Fig. 8 was verified, at least for the range of [0\u00b0 - 120\u00b0], which allowed to compute angle data presented in Table 3. Data was collected at the maximum bending position, corresponding to the pressure peak. Table 3 shows the average bending value of each test, computed across all registered values until failure. The table highlights the regularity of the performances showed by different specimens of the same group. Fig. 8 shows acquired measures for both groups across the entire tests. For 3D printed actuators, acquired measures showed a practically constant bending behavior of the actuators throughout the test that is share by all the specimens. In other words, no significant drift in the relationship between actuation pressure and bending angle exerted by the actuator is observed. A slight drift is observed, on average, for casted specimen fabricated in silicone; Table 4 reports the mean value of the flexion sensor computed for the first and last fifth of the fatigue test for all the silicone specimens, along with the overall mean value" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000174_f_version_1641029125-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000174_f_version_1641029125-Figure2-1.png", + "caption": "Figure 2. Winding arrangement for double-phase excitation; (a) fully-pitched winding 1 and (b) fullypitched winding 2.", + "texts": [ + " The torque of SRM with short-pitched winding is produced due to the self-inductance variation. The mutual-inductance between the phase windings is ineffective and therefore neglected, resulting in T = 1 2 i2a dLa d\u03b8 + 1 2 i2b dLb d\u03b8 + 1 2 i2c dLc d\u03b8 (1) where the subscripts a, b, and c denote the phase; i, L, and \u03b8 are the phase current, selfinductance, and rotor position, respectively. Three diagrams of the winding configuration and flux paths in a three-phase 12/8 SRM when two phases (phase A and B) are excited with unipolar operation are shown in Figure 2. In the fully-pitched winding arrangement of the three-phase 12/8 SRM, each coil spans the surrounding three adjacent stator poles. Figure 2a shows the fully-pitched winding diagram when the number of turns per pole is the same as the number of turns per pole of the short-pitched winding, while Figure 2b shows the fully-pitched winding when it is wound with double the number of turns per pole of the short-pitched winding. The fully-pitched winding can operate with either unipolar (double-phase on at a time) or bipolar operation (double-phase on at a time and all three phases on at a time) [5\u20137]. The torque of the fully-pitched winding is only produced due to the rate of change of the mutual-inductance (M) among phases, and torque production can be achieved by exciting two phases simultaneously instead of only one phase in the short-pitched winding" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002430_9312710_09385133.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002430_9312710_09385133.pdf-Figure12-1.png", + "caption": "FIGURE 12. CMOS BPD-PA mounted on Roger\u2019s RO4000/FR4 PCB.", + "texts": [ + " 48836 VOLUME 9, 2021 The PSD simulation also validates the BPD\u2019s capability in reducing the spectral regrowth when tested with modulated signals. III. MEASUREMENT RESULTS The proposed BPD-PA is fabricated in a 180 nm CMOS process and integrated on Roger\u2019s RO4000 dielectric materials with FR4 cores, two-layer circuit board. The photomicrograph of the BPD-PA which consumes an area of 1.69 mm2 was captured using the eVue digital imaging system. The BPD-PA together with the PCB implementation is illustrated in Fig. 12. Fig. 13 depicts the simulated and measured S-parameters and stability factor of the designed BPD-PA. In measurement, the maximum small signal gain, S21 achieved is 16.5 dB. The BPD-PA has an operating bandwidth of 2.4 GHz, from 0.4 to 2.8 GHz. The input return loss, S11 and output return loss, S22 are less than \u221210 dB across the aforementioned frequency bandwidth. The BPD-PA also exhibits unconditionally stable characteristics across the operating bandwidth as depicted in Fig. 13. The continuous wave (CW)measured performance at different frequencies for the designed BPD-PA is illustrated in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000427_el-00634931_document-Figure2-16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000427_el-00634931_document-Figure2-16-1.png", + "caption": "Figure 2-16. Structure d'une antenne IFA", + "texts": [ + " Il n'y a donc pas de direction de rayonnement privil\u00e9gi\u00e9e ce qui est int\u00e9ressant car dans le cas d'objet communiquant l'orientation de l'objet peut \u00eatre quelconque. La polarisation de ce type d'antenne est tr\u00e8s li\u00e9e \u00e0 la forme du plateau et sera \u00e9galement diff\u00e9rente en fonction de la direction consid\u00e9r\u00e9e. 51 L'antenne PIFA poss\u00e8de une variante planaire appel\u00e9e IFA pour Inverted F Antenna r\u00e9alisable sur circuit imprim\u00e9. Le principe reste le m\u00eame que pour la PIFA mais en deux dimensions. Il y a un brin rayonnant aliment\u00e9 auquel on applique une condition de court circuit \u00e0 l'une de ces extr\u00e9mit\u00e9s comme le montre la Figure 2-16. Il y a moins de degr\u00e9 de libert\u00e9 dans le design qu'avec une PIFA mais cette structure est int\u00e9ressante car elle peut facilement \u00eatre r\u00e9alis\u00e9e sur des circuits imprim\u00e9s et aliment\u00e9e par une ligne microruban. La contrainte de la r\u00e9alisation m\u00e9canique en trois dimensions est alors supprim\u00e9e. 52 Dans nos travaux nous nous sommes largement int\u00e9ress\u00e9s \u00e0 ces structures car elles r\u00e9pondent \u00e0 de tr\u00e8s nombreuses contraintes propres aux objets communicants. Comme nous les verrons, nos travaux nous ont conduits \u00e0 d\u00e9poser un brevet proposant de rendre agile en fr\u00e9quence et en polarisation une antenne PIFA" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.1-1.png", + "caption": "Figure 2.1 Antenna as a transition device [4]", + "texts": [ + " Chapter 2 This chapter presents some basic concepts of antennas for HF applications and reviews the recent works on water antennas. An antenna is a device designed to transmit or receive electromagnetic wave, matching these sources of energy and the free-space. It is also known as radiant systems. The IEEE antenna standards define an antenna as ''that part of a transmitting or receiving system that is designed to radiate or to receive electromagnetic wave [3].'' In other words, antenna is the transitional structure between free-space and a guiding device [4], as shown in Figure 2.1. Antennas are widely used in the field of wireless communications. Mobile communications involving aircraft, spacecraft, ships, or land vehicles requires antennas. Antennas can be designed to transmit or receive electromagnetic waves that belong to different frequency bands. For example, an antenna that is designed to operate in the HF range is termed a HF antenna. Table 2.1 lists the frequency bands and their corresponding wavelengths in the electromagnetic spectrum. Referring to Table 2.1, HF consists of radio frequency electromagnetic waves between 3 to 30 MHz" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003420_-3-031-53397-6_6.pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003420_-3-031-53397-6_6.pdf-Figure14-1.png", + "caption": "Fig. 14 Innovative gripping tool made in AM using lattice structures, topological optimization and generative design algorithms", + "texts": [ + " The methodological approaches developed over the last decade were employed in the frame of industrial projects as 2019\u20132022 PON project ISAF\u2014Integrated Smart Assembly Factory with Leonardo S.p.A. [ 25]; 2014\u20132016 PON STEP FAR\u2014 Development of eco-compatible materials and technologies of drilling and trimming processes and of robotized assembly with Leonardo S.p.A and scientific collaborations, e.g. with Stellantis Research Center, where members of the DII unit played key roles leading to novel devices, innovative/integrated technological solutions, which were also covered by an international patent [ 26] (Fig. 14). In addition, two members of the DII unit working in the field were nominated among the World\u2019s Top 2% Scientists in 2022. Nuclear fusion is the energy source that powers our Sun and stars. Should we succeed in replicating this reaction on Earth, we would get a virtually unlimited and \u201cclean\u201d energy source. The most advanced nations in the world are working together to face physics and engineering challenges of future fusion reactors. In this context, the research group at DII is playing a significant role" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002849_tation-pdf-url_69105-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002849_tation-pdf-url_69105-Figure5-1.png", + "caption": "Figure 5. Magnetic flux distribution and flux density in the switched reluctance machine for the aligned rotor position.", + "texts": [], + "surrounding_texts": [ + "DOI: http://dx.doi.org/10.5772/intechopen.89097 Using the same reasoning as above; Eq. (2) will apply for the unaligned rotor position as well as for the aligned case as shown in Figures 4 and 5. In fact Eq. (2) is used to compute the flux-linkage for any rotor angular position with respect to the stationary stator. One further outcome we are able to accomplish\u2014in addition to varying the rotor angular position to compute the flux-linkage for that rotor position\u2014is to vary the phase current that is being circulated in the concentrated winding of the stator pole. Therefore, if we increase the current from zero to its full rated peak value (see Table 1), for each of the rotor positions from the fully aligned to the fully unaligned, in steps of 1 mechanical degree, the complete flux-linkage map of the 18/12 SR machine will result, as plotted in Figure 6. Some highly notable observations of Figure 6a are that for the aligned rotor position, the flux-linkage builds up very quickly for the range of currents, after which it levels off considerably; this occurs in the region of 80 (amps) called the magnetic saturation point. The unaligned rotor position flux-linkage is fairly linear Modeling and Control of Switched Reluctance Machines aligned position. The intermediate rotor position flux-linkage curves, generally speaking, become highly nonlinear as the rotor tends toward the fully aligned position. If the flux-linkage curves with respect to the rotor position are examined taking the phase current as a parameter, as in Figure 6b, it may be seen that linearity is not present at all, and for a given current value, the flux-linkage value will vary with respect to all rotor positions from the fully unaligned to the fully aligned. This is true irrespective of the rotor rotation in clockwise or counterclockwise direction, as in Figure 6b. The torque production of the SR machine can be described in terms of the fluxlinkage map shown in Figure 6a. If we were to consider only the fully aligned and unaligned rotor position flux-linkage curves, as in Figure 7, then it would follow that as the rotor tends toward the fully aligned position, the current build-up in the phase winding would increase the stored magnetic field energy Wf. The phase current would then follow the same profile as in Figure 3, yet this time it is shown with respect to the flux-linkage curves in Figure 7 (red dashed). As can be seen from the graphical representation, the magnetic co-energy W0 is represented by the area bound by the aligned and the unaligned flux-linkage curves and therefore is given by Eq. (3) in terms of the aligned flux-linkage: W 0 \u00bc \u00f0i 0 \u03a8di\u00a0\u00f0Joules\u00de (3) Thus, generally, if the magnetic field co-energy is created as a result of the rotor moving from the unaligned to the aligned position, while the phase current is kept constant, the torque generated,T, can be computed as in Eq. (4): T \u00bc \u2202W 0 \u2202\u03b8 i\u00bcconstant N m\u00f0 \u00de (4)" + ] + }, + { + "image_filename": "designv8_17_0004567_id_0354-98362300167Z-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004567_id_0354-98362300167Z-Figure3-1.png", + "caption": "Figure 3. Magnetic flux density distribution of the PMSM", + "texts": [ + " In this paper, the PMSM for EV with the spiral water cooled system is the object of study and the specific parameters of the motor are given in tab. 1. To accurately calculate the steady-state temperature distribution of the PMSM at each speed range, the 3-D finite element model shown in fig. 2 was established and solved in this investigation. Taking the maximum speed of 50 kW, 11500 rpm as an example, the magnetic flux density distribution and iron loss of the motor were calculated using the combination of Ansoft Maxwell 2D and Ansoft Simplorer. The distribution of the magnetic flux density of the motor is shown in fig. 3. The highest magnetic density is located at the rotor isolation bridge, with a maximum density of 1.61 T. The stator and rotor iron loss are 2.89 kW and 279 W, respectively. Figures 4(a) and 4(b) show the high quality grid discretization scheme and the grid independence verification, respectively. The details of the hexahedral co-nodal grid of the PMSM are shown in the enlarged view in fig. 4(a). The overall distortion of the co-nodal grid is 0.63, thus ensuring accuracy in the calculation of the thermal behaviour of the motor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002523_download_23462_11570-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002523_download_23462_11570-Figure2-1.png", + "caption": "Figure 2. The doping profile of 14 nm double gate NMOS", + "texts": [ + " In Figure 1, Silvaco ATHENA is used to display the completed device for a 14 nm \ud835\udc5b-type horizontal double gate MOSFET with a bilayer graphene/high-k/metal gate. The device is shown in its completed form since it has been constructed. Due to the obvious change in the design of the gate, the amount of doping introduced into the device has changed because of the change in design. Figure 1 shows the silicon, graphene, high-k/metal gate, and aluminium configurations of the 14 nm NMOS horizontal double gate MOSFET design in 14 nm HfO2/WSix technology. Figure 2 shows material measurements of the device, and Figure 3 shows the doping profile of the 14 nm NMOS horizontal double gate MOSFET design. Using the Taguchi L9 orthogonal array approach researchers were able to achieve the lower leakage current predicted by ITRS 2013. In this experiment, the smaller the grade attributes of the IOFF, the better the grade attributes. The following stage was to discover the control parameters that have the greatest impact on the device features in order to have a better knowledge of the device characteristics" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002936_f_version_1617941308-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002936_f_version_1617941308-Figure6-1.png", + "caption": "Figure 6. Important rotor positions of an ORDSPMG (a) \u201copposite\u201d position, (b) \u201cconjunction\u201d position.", + "texts": [ + " It has 3 phases, each phase is wound around of 4 toothed poles and each pole has four small teeth. Its power supply is obtained by rectangular phase currents. The phase supply is dependent on the aligned position and the unaligned position. The aligned position of a phase is defined to be the situation where the stator poles teeth and the rotor poles teeth of the considered phase are perfectly aligned; this position is called \u201cconjunction\u201d position. At this position, PMs-flux in the considered phase is maximum (Figure 6b). The PMs\u2019 flux decreases gradually as the rotor poles\u2019 teeth move away from the aligned position. When the rotor poles teeth are misaligned with the stator poles teeth, the position is called \u201copposite\u201d position, where at this position, the PMs\u2019 flux in the considered phase is minimum (Figure 6a). As the direction of PMs\u2019 flux does not change for these two positions, it means that the PMs\u2019 flux is unidirectional (see Figure 7) and therefore the cogging torque can be neglected. A positive current is injected into armature coil when the rotor moves from the opposite (or unaligned) position to the conjunction (aligned) position over one electric period. This current produces flux of the same polarity with that of PM. This leads to the generation of positive torque. A smooth output torque is finally produced as a combined result of three phase operation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004813_f_version_1706019242-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004813_f_version_1706019242-Figure4-1.png", + "caption": "Figure 4. The layers\u2019 details of the proposed design, M and D, refer to the metal and dielectric layer, respectively. There are three dielectric layers and four metallic layers.", + "texts": [ + " The final design can scan the beam from \u221260 to + 60 , which is an extraordinary performance compared to the existing literature [4,35,39,40]. The detailed results are presented in Section 3. (a) (b) (c) Figure 3. Antenna utilizing substrate-guided grounded concept. (a) Configuration of the antenna metallic patterns excited from waveguide port, (b) electric field distributions, and (c) simulated 3D highly directive radiation patterns obtained at 20 GHz. 2.2. Final Design In order to develop the antenna based on the SGG method, a circular disc with a radius of 150 mm and a pillbox feeding (quasi-optical) system are developed. Figure 4 shows the details of each layer in the proposed design before assembling the antenna structure. The proposed antenna consists of four conducting layers (M1:M4) interleaved by three dielectric substrates (D1:D3). Table 1 shows the parameter of the antenna where all the dimensions are in (mm). Figure 3. Antenna utilizing substrate-guided grounded concept. (a) Configuration of the antenna metallic patterns excited from waveguide port, (b) electric field distributions, and (c) simulated 3D highly directive radiation patterns obtained at 20 GHz. 2.2. Final Design In order to develop the antenna based on the SGG method, a circular disc with a radius of 150 mm and a pillbox feeding (quasi-optical) system are developed. Figure 4 shows the details of each layer in the proposed design before assembling the antenna structure. The proposed antenna consists of four conducting layers (M1:M4) interleaved by three dielectric substrates (D1:D3). Table 1 shows the parameter of the antenna where all the dimensions are in (mm). L1 W1 R1 R2 R3 R4 Lh Wh Sv dv Sw Wst Sst 340 115 111.4 157.2 155 150 16 12 1.5 1 5 4 4 2.2.1. Radiating Disc Linear periodic metallic patterns in a circular manner are printed on a disc to form a top layer, as depicted in Figure 4 (M4). The disc is separated from the other structure to produce beam steering by its rotation (D3 with M4). The configuration of metallic patterns can be chosen based on the required beam direction; it works as an antenna array. Thus, the critical factors are the number of strips, distance between them, and width of each strip. The space between the elements is chosen to avoid any grating lobes and achieve high gain. By changing the shape and size of the metallic patterns, the beam can be varied", + " To demonstrate this idea, metallic patterns are printed on the top side of the disc. After careful optimization of the patterns, a period of 8 mm and a total length of 15 \ud835\udf06 along the i l si , and , refer to the metal and dielectric layer, r . re three dielectric layers and four metallic layers. Table 1. Dime sions of the proposed antenna; all values in mm. L1 W1 R1 R2 R3 R4 Lh Wh Sv dv Sw Wst Sst 340 115 111.4 157.2 155 150 16 12 1.5 1 5 4 4 2.2.1. Radiating Disc Linear periodic metallic patterns in a circular manner are printed on a disc to form a top layer, as depicted in Figure 4 (M4). The disc is separated from the other structure to Sensors 2024, 24, 732 6 of 14 produce beam steering by its rotation (D3 with M4). The configuration of metallic patterns can be chosen based on the required beam direction; it works as an antenna array. Thus, the critical factors are the number of strips, distance between them, and width of each strip. The space between the elements is chosen to avoid any grating lobes and achieve high gain. By changing the shape and size of the metallic patterns, the beam can be varied", + " After careful optimization of the patterns, a period of 8 mm and a total length of 15 \u03bb along the x-direction at 20 GHz are chosen. A width of 4 mm and a spacing of 4 mm, which provide beam pointing at the phi = 0\u25e6 and theta = 8\u25e6 direction, are considered. 2.2.2. Feeding Structure To make the antenna compact, pillbox-based feeding is implemented underneath the disc, as shown in Figure 2. A detailed view of the feeding mechanism along with the used substrates is described in Figure 5. The feeding structure consists of an SIW horn feeding, parabolic reflector, and coupling slot, as shown in Figure 4. The geometric properties of the parabolic reflectors offer the transformation of a cylindrical wave originating from the paraboloid\u2019s focus into a plane wave directed along the parabola axis. Therefore, the feeding structure and the coupling slot are arranged and placed in different layers to avoid aperture blocking. The feeding is positioned in the focal plane of the parabolic reflector located on the lower substrate (D1), which is integrated with the horn and SIW structure to feed and guide the waver, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004264___lang_en_format_pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004264___lang_en_format_pdf-Figure9-1.png", + "caption": "Fig. 9 Antenna dimensions and settings in mm", + "texts": [ + " For every BBS\u2019s the resulting antenna is shown in Fig. 8. Journal of Microwaves, Optoelectronics and Electromagnetic Applications, Vol. 11, No. 1, June 2012 Brazilian Microwave and Optoelectronics Society-SBMO received 6 Jan. 2012; for review 2 Feb. 2012; accepted 15 June 2012 Brazilian Society of Electromagnetism-SBMag \u00a9 2012 SBMO/SBMag ISSN 2179-1074 169 that is used to interface the waveguide power source to the antenna (interfacing material) which has \u00b5 r=1 and \u03b5r=3. The settings for every antenna are shown in Fig. 9. A Visual Basic (VB) subroutine was built to carry out the circuit analysis inside CST studio suite. The antennas are tested for the range between 10MHz to 50GHz. The Input Return Loss (IRL) curve and its phase for the antennas are shown in Fig. 10. The delivered power is shown in Fig.12 Journal of Microwaves, Optoelectronics and Electromagnetic Applications, Vol. 11, No. 1, June 2012 Brazilian Microwave and Optoelectronics Society-SBMO received 6 Jan. 2012; for review 2 Feb. 2012; accepted 15 June 2012 Brazilian Society of Electromagnetism-SBMag \u00a9 2012 SBMO/SBMag ISSN 2179-1074 170 The surface current density is an important factor to analyze the antenna parameters such as the electric field, the electric energy, the power flow, and the far field pattern" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000095_cle_download_406_813-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000095_cle_download_406_813-Figure8-1.png", + "caption": "Fig. 8. Skid of the seeder", + "texts": [ + " The metering discs are arranged in series on an axle (Fig. 5). The metering disc axle is in turn connected to the axle of the ground wheel by means of a chain and sprocket. Provision to engaged and disengaged the metering discs is provided by means of a clutch assembly as shown in Fig. 7. This way the seeder can still be moved through its wheel during transport and maneuvering without rotating the metering disc. Additional features to minimize the use of another pair of wheels at the rear portion of the seeder, a skid (Fig. 8) is designed that would serve as depth controller for the furrow opener. The skid is purposely designed to scrape flatten the surface of the plant bed which makes the furrow opening more efficient. It is also served as depth controller so that the furrow opener will create furrow of uniform depth. The components of the seeder were designed to deliver the requirements for planting carrots. Table 1 presents the specifications of the seeder. The seeder was designed to plant seeds spaced at 12.5 cm between row and 10 cm between hills" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001798_n_Compress_20464.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001798_n_Compress_20464.pdf-Figure2-1.png", + "caption": "Fig. 2. (a) The experimental system; (b) the vibration device", + "texts": [ + " The material specific heat capacity under three moisture contents were measured by JTKD-II thermal conductivity tester (JANTYTECH Ltd., Beijing, China). The results are shown in Table 1. Because the volume of material used in the compression test was small, the difference of the material Wang et al. (2023). \u201cAlfalfa vibration & compression,\u201d BioResources 18(1), 417-428. 419 specific heat capacity had no significant influence on temperature change. In the subsequent text, the material specific heat capacity would be considered as the same. An experimental system designed in this study is shown in Fig. 2a. A cylindrical die with a channel diameter of 45 mm and a length of 120 mm was used to make briquettes from the materials. The compression piston was driven by a hydraulic drive and control system that could provide the compression speed of 2.16 mm/s. The assisted vibration was generated by a crank-slider mechanism, in which the slider pushed the connecting bars and a ring flange that was connected to the ejector rod. Thus, the experimental material in the die was subjected to an axial vibration applied by the ejector rod from below, see Fig. 2b. The vibration device could provide vibration with amplitude of 1.5 mm and frequency range of 0 to 25 Hz. To compare the effects of assisted vibration on compression of alfalfa, six Pt100 thermocouple temperature sensors (Shanghai Songdao heating sensor Co., Ltd, China, Nominal temperature 0 to 200 \u2103, LIN\u00b10.1%) were employed for measuring the compression temperature. The signals were amplified by a temperature transmitter and detected simultaneously by a data acquisition board NI USB-6210 (National Instruments Company Ltd" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004054___lang_en_format_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004054___lang_en_format_pdf-Figure1-1.png", + "caption": "Fig. 1. Conventional MPAs (i) Microstrip line fed MPA (ii) Proximity-coupled fed MPA (iii) Aperture-coupled fed MPA", + "texts": [ + " The results of simulated MPAs, the results of the fabricated MPAs, and a comparative study of proposed MPA with the MPAs available in the literature are described in section IV. Section V provides concluding remarks. II. DESIGN OF CONVENTIONAL MPAS AND MODIFIED FRACTAL DGS A. Conventional MPAs For ease of analysis, three conventional patch antennas denoted as Design_1 (with microstrip line feeding), Design_2 (with proximity-coupled feeding), and Design_3 (with aperture-coupled feeding) are considered and they are shown in Fig. 1. In Design_1, the substrate material used is FR4_epoxy with a relative permittivity ( ), relative permeability (\u00b5r), and a dielectric loss tangent (tan ) of 4.4, 1, and 0.018, respectively. The Design_2 and Design_3, utilize this FR4 epoxy as the lower substrate and Rogers RT/Duroid 5880 as the upper substrate with a of 2.2, \u00b5r of 1, and a tan of 0.0009, respectively. The three conventional MPAs are resonating at 2.4 GHz. The dimensions of the antennas are calculated using the empirical formulae of the transmission line model of an MPA [16]", + " These unremoved areas facilitate the electric field to build up across the ground structure and as a result of this effective capacitance of the model increases substantially [17]. Since the return current in the square areas surrounding the etched boundary of the ground plane remains the same, the effective inductance almost remains the same. The DGS model as shown in Fig. 3 (i)-c provides significant miniaturization than the conventional DGS model as shown in Fig. 3 (i)-b [17]. Also, the MPA provides improved performance by controlling the gap between the boundary lines of wired DGS in both x and y directions. The Design_1, Design_2, and Design_3 as shown in Fig. 1, embedded with these ten different DGS patterns are simulated using HFSS software. The performances of these three designs with all the ten cases are mentioned in Table II. It is observed from the table that in Design_1, 2, and 3, with the ten DGS models, there is a decrease in resonant frequency with respect to their plain ground plane without DGS. Between Type1 (MFDGS) and Type2 (M-MFDGS), Type2 provides an improved size reduction than Type1 in all the two iterations. Additionally, the wire DGS has a better reduction in the frequency of resonance as compared to their corresponding simple DGS structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002798_e_download_5515_3621-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002798_e_download_5515_3621-Figure10-1.png", + "caption": "Figure 10. Simulated result for the 3-dimensional of radiation pattern, (a) front view and (b) side view", + "texts": [ + "33 dB compared to other width sizes. Therefore, in the final design, 90 mm width was selected for the reflector size and the length of 220 mm was found to be the best between return loss and size. Take note that, a larger size of reflector is not recommended for any portable device. Microstrip antenna with reflector and air gap for short range communication in \u2026 (Noor Azwan Shairi) The simulated three-dimensional radiation pattern of the optimized microstrip antenna for the front view is shown in Figure 10(a) and the side view is shown in Figure 10(b). As can be seen to the red color of the radiation pattern, the antenna radiation was directed to the z-axis which is toward the front view of the microstrip antenna. Beside that, it is proven that the reflector changes the microstrip antenna to be a directive gain. However, there is a small side lobe and back lobe that would be an unwanted radiation pattern for the directive antenna. Figure 11 shows the two-dimensional view of the radiation pattern for the microstrip antenna. This is another way of plotting and analyzing the radiation pattern of the antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003785__downloads_6q182k630-Figure2.4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003785__downloads_6q182k630-Figure2.4-1.png", + "caption": "Figure 2.4: Hard Disk Servo Plant", + "texts": [ + " The data on the disks are organized into concentric 23 circles which are referred to as tracks. The disks are rotated at a high speed. The data on the disk is written or read using a read/write head. This read/write head is attached to an arm which is actuated by a voice coil motor (VCM), and it moves in the radial direction from one track to the other. The plant of a hard disk drive consists of the VCM and the attached arm with the read/write head. A high-level diagram of the plant re-drawn from [36] is shown in Figure 2.4. The differential equations that govern the electromechanical dynamics of the VCM are given by (2.8) [35]. J d2\u03b8 dt2 + C d\u03b8 dt = Kii L di dt +Ri = V \u2212Ki d\u03b8 dt (2.8) J is the inertia of the arm and read/write head, C is the viscous damping coefficient of the bearings, Ki is the electromotive force constant of the VCM, \u03b8 is the angular position of the arm, L is the electrical inductance, R is the electrical resistance, i is the current to the VCM, and V is the voltage to the VCM. Applying the Laplace transform to (2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003220_20JIYE_G1103158C.pdf-Figure4.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003220_20JIYE_G1103158C.pdf-Figure4.3-1.png", + "caption": "Figure 4.3 (a) The Model for Cu-filled TSV with oxide liner, we have used Eq. (1) & (2) to calculate resistance (R) and capacitance (Cox). (b) Represents the crosssectional view of the real image of Cu-TSV.", + "texts": [ + "11 Crystal direction of (100) wafer ............................................................... 37 Figure 3.12 Distributions of biaxial stress near surface (Depth=0.2\u03bcm) ..................... 37 Figure 3.13 Silicon anisotropic properties ................................................................... 38 Figure 4.1 The sample real image and its die map ...................................................... 39 Figure 4.2 The area Raman line scan were performed ................................................ 40 Figure 4.3 (a) The Model for Cu-filled TSV with oxide liner, we have used Eq. (1) & (2) to calculate resistance (R) and capacitance (Cox). (b) Represents the crosssectional view of the real image of Cu-TSV. ............................................................... 41 Figure 4.4 (a) Represent the thermo-mechanical stress distribution for 4 to 10\u00b5m TSVs (b) The corresponding simulation curves. ......................................................... 42 Figure 4.5 C-V plots for constant ratio and constant liner thickness mode for 50, 25 & 10\u00b5m TSV length", + " Based on the ITRS road map 2011, the greater accessibility of higher number of TSVs in a specified area depends on the smarter miniaturization of the interconnect dimension in 3D IC packaging. Of course, scaling of TSV dimension has an inevitable effect on resistance, capacitance, signal transport as well as the thermomechanical stress issue. We find that the lowering of TSV diameter is permissible 41 under thermo-mechanical stress issue, however, the signal transmission delay could be tunable via controlling the oxide layer capacitance to the lower end. The single Cu filled TSV with liner separation has been demonstrated as shown in Figure 4.3. The use of liner material in TSV interconnection technology has some implications. Firstly its role is to minimize the leakage current and secondly to consider as an annular material to absorb the stress under thermal treatment [15]. However it has an adverse effect to create the capacitance to make delaying the signal transmission. At the annealing process of Cu-TSV, we have observed that the Sisurface is under strong compressive stress at the closer vicinity of the TSV holes and that exponentially decreasing up to a certain distance of 1\u00b5m from the TSV periphery and finally becomes almost constant until next of TSV" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000745_ture-tracking-v2.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000745_ture-tracking-v2.pdf-Figure10-1.png", + "caption": "Figure 10 Prototype machine (front/side view)", + "texts": [], + "surrounding_texts": [ + "Figure 11 shows the appearance and main dimensions of the stable coaxial two-wheeled vehicle used in this study. The center of gravity of the entire stable coaxial motorcycle is 64.7 mm below the center of rotation of the wheels. The drive mechanism at the top of the car body has a self-locking function by adopting a DC motor unit using a worm gear. The movable limit angle of the upper part of the car body is \u00b1 45 degrees in the front and back, and the total weight is 23 kg. The upper part of the car body is a poster frame, which is a robot with an advertising function that can present information to the people around. This is because it is assumed to be used as a moving mechanism for service robots. This paper describes how to build an environment for model-based development with Arduino, which is the CPU used to build the implementation environment required for rapid prototyping (RCP) required for this experiment. In recent years, an open source model-based development (MBD) environment using Arduino microcomputers, which has been widely used as a microcomputer for electronic work, has been provided free of charge. The MBD development environment with Arduino is diverse, such as HILS (Hardware in the Loop System) environment by automatic code generation that generates Simulink model code from Matlab / Simulink and directly implements on Arduino, and RCP (Rapid Control Prototyping) by implementation model. The development environment can be constructed at a very low cost. In this study, an RCP environment that uses Arduino Mega as an input / output device from a host PC via a USB cable using Arduino Mega was implemented and compared the designed control systems. The system representation is as shown in Figure 12." + ] + }, + { + "image_filename": "designv8_17_0003094_f_version_1684942287-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003094_f_version_1684942287-Figure11-1.png", + "caption": "Figure 11. Analyzed force distribution on the xy plane.", + "texts": [ + " An analysis of the parameter values provided in Table 5 indicates that the value of the cutting force Fc was significantly affected by the blade rake angle \u03b2 (p < 0.001). The statistical F-value for this variable was F = 28.09, in comparison to the F-value of the blade angle \u03b1, which was F = 2.40. A further conclusion is that the lowest value of the cutting force Fc necessary to separate the triticale straw was recorded for the parameter values \u03b1 = 45\u25e6 and \u03b2 = 30\u25e6. The distribution of forces on the knife blade was analyzed considering two planes of the assumed Cartesian coordinate system x, y, z. Figure 11 presents the force distribution on the blade considering the analysis of the influence of the variance of the rake angle \u03b2 along the xy plane. Based on the analyzed force distribution along the xy plane, as in Figure 11, it was assumed that the force value Fc recorded in the course of the experiment was the vertical component of the force Fc \u2032. The force Fc \u2032 may then be considered the main cutting force enacted perpendicular to the cutting edge of the knife. The second component of the cutting force Fc \u2032 was the horizontal component enacted along the direction of the axis x. The vectors of all the above-mentioned forces were applied at the point of contact of the cutting edge of the blade and the straw (see Figure 11). The dependence for calculating the Fc \u2032 can be expressed as below (4): F\u2032c = Fc cos \u03b2 (4) where Fc \u2032\u2014force perpendicular to the edge of the knife blade (N); Fc\u2014measured cutting force (N); \u03b2\u2014blade rake angle (\u25e6). The dependence on the horizontal component Fc \u2032\u2032 is expressed as below (5): F\u2032\u2032c = Fc \u00b7 tan \u03b2 (5) where Fc \u2032\u2032\u2014force horizontal to the measured Fc (N); Fc\u2014measured vertical component of the cutting force (N); \u03b2\u2014blade rake angle (\u25e6). Therefore, the ratio of the horizontal component Fc \u2032\u2032 to the measured cutting force Fc can be expressed as below (6): F\u2032\u2032c Fc = tan \u03b2 (6) The value of the ratio expressed as (5) can be considered a coefficient [33\u201338] that determines the percentage share of the horizontal force component Fc \u2032\u2032 relative to the force value Fc measured in the experiment. This can be interpreted in the following manner: a too-high ratio of the horizontal force component Fc \u2032\u2032 may contribute to the undesired phenomenon of the straw stem moving in the direction of the axis x (see Figure 11), consequently leading to the straw moving from under the blade, and thus preventing separation, as this partial displacement leads to a longer path to be traveled by the knife blade. This has a negative effect on the energy efficiency of the process, as it directly increases its duration. It would be, therefore, necessary to mount an additional component in the cutting station to eliminate the possibility of the movement of the straw stems, thus increasing the cost of the cutting station. Similar conclusions may be drawn for machinery that cuts a large amount of straw stems simultaneously", + " The difference between the predicted R2 = 0.9983 and the adjusted R2 = 0.9986 coefficients of determination, which was lower than 0.2, along with the Adeq Precision value of 151.6901, indicates the usefulness of the model to estimate the value of the force. The obtained model is presented in Formula (7), and its graphical representation is shown in Figure 12. Fc \u2032\u2032/Fc = \u22120.0170033 + 0.019676 \u00d7 \u03b2, (7) a degrees of freedom. Here, Fc is the cutting force (N), Fc \u2032\u2032 is the horizontal force component by Figure 11 (N), and \u03b2 is the blade rake angle (\u25e6) It follows from the analysis of the parameters in Table 7 that the only significant influence (which is why Table 7 only includes the rake angle \u03b2, and the lines of the surface graph are parallel to the axis of variance of the blade angle \u03b1, which further confirms that the variance of this angle value is not significant) on the value of the Fc \u2032\u2032/Fc ratio is that of the blade rake angle \u03b2 (p < 0.001), where the statistical F-value for this variable is F = 7772" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001252_O201620240595779.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001252_O201620240595779.pdf-Figure16-1.png", + "caption": "Fig. 16. Cogging torque measurement setup", + "texts": [ + " The core losses in both stator and rotor laminations for motor with normal rotor and motor with shifted magnet rotor are calculated and depicted in Fig. 14. Comparison between the two LSPMS motors show that by shifting magnets the core loss is slightly increased. In order to validate the numerical results two prototype LSPMS motors are selected based on parameters shown in Table 1. The main difference between the two motors is the distribution of PMs on their rotors. One motor has a uniformly distributed PMs and the other one has shifted PMS as shown in Fig. 15. LSPMS motor and the cogging torque measurement setup are shown in Fig. 16. In order to measure cogging torque, a rotating index plate is assembled onto the wormgear unit. The rotating index plate can turn and hold the stator securely with accurate angular position. The rotor position is being kept stationary during the measurements. One end of a balanced beam is attached to the rotor shaft and the other end is being placed on the tray of a digital weight gauge (as shown in Fig. 16). With the beam in a level position, the weight gauge is set to zero. In order to allow measurement of both positive and negative values of cogging torque, a pre load is added to the measurement end to ensure that the bar is always in contact with the tray. As the stator is turned in the lathe, the relative position between the rotor and the stator is changed. By reading the measured force the resulted cogging torque can be calculated as follows [24]. .( )cog read pre loadT L F F \u2212= \u2212 (30) In which L is the arm length of the balanced beam from the center of rotor shaft to the acting point on the digital gauge" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.9-1.png", + "caption": "Figure 1.9. Ackermann\u2019s steering mechanism [1].", + "texts": [ + " These concerns lessened with the introduction of a new type of steering arrangement. The innovation, patented in 1817 by Rudolf Ackermann, was to eliminate the center pivot, and instead have a pivot on each end of the front axle. This was accomplished by having a pin mounted at the end of axle, called a kingpin, about which a wheel carrier could turn. The wheel was then mounted, appropriately, to the wheel carrier. The carriers on the axle were connected by a link, which in turn was connected to a link that animals could be hitched to, Figure 1.9. The geometry of the mechanism was selected such that the packaging and slip issues described previously were mitigated. Automobiles, as known today, began appearing towards the end of the nineteenth century, and were little more than carriages with their own power source. The steering linkage was revised so that the front wheels could be steered by hand, initially using a tiller. As internal combustion engines became increasingly powerful, the higher achievable speeds inspired further improvements in suspension and steering design" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000853_9668973_09718336.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000853_9668973_09718336.pdf-Figure5-1.png", + "caption": "FIGURE 5. Prototype of the proposed revolute joint.", + "texts": [ + " In addition, an electromagnetic brake (BXR-020-10LE, MIKIPULLEY Co., Kawasaki, Japan) was applied between the motor and lead-screw-driven linear guide as a double safety device. The brake was actuated by a spring force when there was no electrical current. Therefore, the angle of the revolute joint was maintained even if the power was off. With the exception of commercial products, such as bearings, linear guides, and pulleys, the remaining parts were machined from aluminum alloy or stainless steel. Fig. 5 shows the prototype of the proposed revolute joint. III. STATIC ANALYSIS A. ANGULAR RESOLUTION Given that the revolute link is directly connected to the motor in the conventional mechanism, the resolution of the conventional joint is the same as the resolution of the motor. Unlike the conventional joint, the proposed revolute joint has a higher angular resolution than that of the motor. When the motor rotates the lead-screw of the linear guide by one circle, the block of the linear guide translates by a single screw lead" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001052_f_version_1704097252-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001052_f_version_1704097252-Figure4-1.png", + "caption": "Figure 4. View of the r logy.", + "texts": [ + " The process begins with using an accelerometer to measure the vibrations generated by the running machinery. The accelerometer generates a voltage signal that corresponds to the amount and frequency of vibrations produced by the machine. The vibration analysis is performed by measuring the vibration level and performing additional Fourier transform spectrum analysis. The focus of this research is to determine the vibration level of machines and their holding places to compare the damping property of the investigated object. To achieve a successful analysis, there are several steps to follow (see Figure 4). Machines\u00a02024,\u00a012,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 7\u00a0 of\u00a0 15\u00a0 \u00a0 \u00a0 Figure\u00a04.\u00a0View\u00a0of\u00a0the\u00a0research\u00a0methodology.\u00a0 The\u00a0local\u00a0Fourier\u00a0spectrum\u00a0of\u00a0each\u00a0segment\u00a0can\u00a0be\u00a0generated\u00a0around\u00a0the\u00a0window\u2019s\u00a0 position,\u00a0 and\u00a0 the\u00a0 temporal\u00a0variation\u00a0of\u00a0 the\u00a0 frequency\u00a0 can\u00a0be\u00a0observed\u00a0 locally.\u00a0This\u00a0 is\u00a0 achieved\u00a0by\u00a0equation\u00a0in\u00a0the\u00a0following\u00a0way\u00a0[22]:\u00a0 \ud835\udc12\ud835\udc13\ud835\udc05\ud835\udc13 \ud835\udc65 \ud835\udc61 \ud835\udf0f, \ud835\udf14 \u2263 \ud835\udc4b \ud835\udf0f, \ud835\udf14 \ud835\udc65 \ud835\udc61 \ud835\udf14 \ud835\udc61 \ud835\udf0f \ud835\udc52 \ud835\udc51\ud835\udc61,\u00a0 (12) where\u00a0x(t)\u2014vibration\u00a0signal\u00a0to\u00a0be\u00a0transformed;\u00a0X(\u03c4,\u00a0\u03c9)\u2014essentially\u00a0the\u00a0Fourier\u00a0transform\u00a0 of\u00a0x(t)\u03c9(t\u2212\u03c4);\u00a0e\u2014complex\u00a0function\u00a0representing\u00a0magnitude\u00a0and\u00a0phase\u00a0of\u00a0the\u00a0signal\u00a0over\u00a0 time\u00a0and\u00a0frequency;\u00a0\u03c9(t\u2212\u03c4)\u2014window\u00a0function\u00a0(Hann\u00a0window)\u00a0centered\u00a0around\u00a0zero", + "\u00a0Machines\u00a0under\u00a0Investigation\u00a0and\u00a0Measurement\u00a0Setups\u00a0 In\u00a0the\u00a0current\u00a0research,\u00a0two\u00a0machines\u00a0of\u00a0the\u00a0same\u00a0type\u00a0were\u00a0installed\u00a0in\u00a0parallel\u00a0and\u00a0 operated\u00a0in\u00a0one\u00a0recycle\u00a0line\u00a0(Figure\u00a05a).\u00a0The\u00a0test\u00a0measurement\u00a0processes\u00a0and\u00a0equipment\u00a0 are\u00a0shown\u00a0in\u00a0Figure\u00a05b,\u00a0including\u00a0a\u00a0National\u00a0Instrument\u00a0USB-443x\u00a0data\u00a0collector\u00a0with\u00a0an\u00a0 AS-065\u00a0B&K\u00a0accelerometer\u00a0and\u00a0PC\u00a0for\u00a0data\u00a0proceeding.\u00a0 \u00a0 (a)\u00a0 (b)\u00a0 The local Fo ri f each segment can be generated around the window\u2019s position, and t t l ariation of the frequency can be observed locally. This is achieved by equati i g ay [ 2]: STFT{x(t)}(\u03c4, \u03c9) Machines\u00a02024,\u00a012,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 7\u00a0 of\u00a0 15\u00a0 \u00a0 \u00a0 Figure\u00a04.\u00a0View\u00a0of\u00a0the\u00a0research\u00a0methodology.\u00a0 The\u00a0local\u00a0Fourier\u00a0spectrum\u00a0of\u00a0each\u00a0segment\u00a0can\u00a0be\u00a0generated\u00a0around\u00a0the\u00a0window\u2019s\u00a0 position,\u00a0 and\u00a0 the\u00a0 temporal\u00a0variation\u00a0of\u00a0 the\u00a0 frequency\u00a0 can\u00a0be\u00a0observed\u00a0 locally.\u00a0This\u00a0 is\u00a0 achieved\u00a0by\u00a0equation\u00a0in\u00a0the\u00a0following\u00a0way\u00a0[22]:\u00a0 \ud835\udc12\ud835\udc13\ud835\udc05\ud835\udc13 \ud835\udc65 \ud835\udc61 \ud835\udf0f, \ud835\udf14 \u2263 \ud835\udc4b \ud835\udf0f, \ud835\udf14 \ud835\udc65 \ud835\udc61 \ud835\udf14 \ud835\udc61 \ud835\udf0f \ud835\udc52 \ud835\udc51\ud835\udc61,\u00a0 (12) where\u00a0x(t)\u2014vibration\u00a0signal\u00a0to\u00a0be\u00a0transformed;\u00a0X(\u03c4,\u00a0\u03c9)\u2014essentially\u00a0the\u00a0Fourier\u00a0transform\u00a0 of\u00a0x(t)\u03c9(t\u2212\u03c4);\u00a0e\u2014complex\u00a0function\u00a0representing\u00a0magnitude\u00a0and\u00a0phase\u00a0of\u00a0the\u00a0signal\u00a0over\u00a0 time\u00a0and\u00a0frequency;\u00a0\u03c9(t\u2212\u03c4)\u2014window\u00a0function\u00a0(Hann\u00a0window)\u00a0centered\u00a0around\u00a0zero", + " All data collected from the accelerometer are recorded through a data collector (software NI Max ver. 21) as amplitude vs. time, known as a time waveform. These data are analyzed using Machines 2024, 12, 29 7 of 14 computer program algorithms and are then reviewed by engineers to determine the health of the machine and identify any possible impending problems such as an unbalance, high vibration, etc. Prior to the main measurements, the accelerometers were calibrated using a B&K portable accelerometer calibrator type 4294. Machines\u00a02024,\u00a012,\u00a0x\u00a0FOR\u00a0PEER\u00a0REVIEW\u00a0 7\u00a0 of\u00a0 15\u00a0 \u00a0 \u00a0 \u00a0 Figure\u00a04.\u00a0View\u00a0of\u00a0the\u00a0research\u00a0methodology.\u00a0 The\u00a0local\u00a0Fourier\u00a0spectrum\u00a0of\u00a0each\u00a0segment\u00a0can\u00a0be\u00a0generated\u00a0around\u00a0the\u00a0window\u2019s\u00a0 position,\u00a0 and\u00a0 the\u00a0 temporal\u00a0variation\u00a0of\u00a0 the\u00a0 frequency\u00a0 can\u00a0be\u00a0observed\u00a0 locally.\u00a0This\u00a0 is\u00a0 achieved\u00a0by\u00a0equation\u00a0in\u00a0the\u00a0following\u00a0way\u00a0[22]:\u00a0 \ud835\udc12\ud835\udc13\ud835\udc05\ud835\udc13 \ud835\udc65 \ud835\udc61 \ud835\udf0f, \ud835\udf14 \u2263 \ud835\udc4b \ud835\udf0f, \ud835\udf14 \ud835\udc65 \ud835\udc61 \ud835\udf14 \ud835\udc61 \ud835\udf0f \ud835\udc52 \ud835\udc51\ud835\udc61,\u00a0 (12) where\u00a0x(t)\u2014vibration\u00a0signal\u00a0to\u00a0be\u00a0transformed;\u00a0X(\u03c4,\u00a0\u03c9)\u2014essentially\u00a0the\u00a0Fourier\u00a0transform\u00a0 of\u00a0x(t)\u03c9(t\u2212\u03c4);\u00a0e\u2014complex\u00a0function\u00a0representing\u00a0magnitude\u00a0and\u00a0phase\u00a0of\u00a0the\u00a0signal\u00a0over\u00a0 time\u00a0and\u00a0frequency;\u00a0\u03c9(t\u2212\u03c4)\u2014window\u00a0function\u00a0(Hann\u00a0window)\u00a0centered\u00a0around\u00a0zero" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000623__4_5_4_17-00007__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000623__4_5_4_17-00007__pdf-Figure1-1.png", + "caption": "Fig. 1 Structure of proposed 5-DOF controlled maglev motor.", + "texts": [ + " Since 2015, further miniaturization of the 5-DOF controlled maglev motor has been carried out to develop an implantable maglev VAD applicable to pediatric patients under ten years of age (Osa, et al, 2016). In this paper, magnetic levitation performance of the further miniaturized maglev motor with 5-DOF active control concept was investigated. The proposed 5-DOF controlled magnetically levitated motor is an axial gap type permanent magnet synchronous motor. The motor has a top stator, a bottom stator and a levitated rotor as shown in Fig. 1. The top stator and bottom stator have a completely identical geometry. The levitated rotor is axially sandwiched between the top stator and the bottom stator. A double stator mechanism enhances a rotating torque production and achieves the 5-DOF active control of levitated rotor postures. The motor can generate axial suspension force and rotating torque with a single rotating magnetic field by utilizing vector control algorithm (Asama, et al, 2013; Nguyen, et al, 2011; Osa, et al, 2012b; Ueno, et al, 2000)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.5-1.png", + "caption": "Figure 8.5: Triangle distance tests", + "texts": [ + " While there are numerous approaches to computational geometry, I chose simple triangulated surfaces for generality and efficiency. Many unstructured CFD grids are natively triangular due to tetrahedral volumes, and structured grids using hexahedral volumes can be easily triangulated. Spline or other parametric surfaces are also easily triangulated. Furthermore, many efficient distance and intersection algorithms have already been developed for triangular geometry primitives. The minimum distance between two triangles can be found through six point-triangle distance tests and nine edge-edge tests (Figure 8.5). I implemented the point-triangle and edge\u2013edge distance tests of Ericson [247]. While lower-cost distance tests exist in the literature, Ericson\u2019s approach is vectorizable, allowing the use of analytic differentiation to obtain derivatives. During optimization, the pair of triangles determining dmin changes for every iteration, and the 179 gradients of dmin are discontinuous. Tracking dmin alone also ignores useful information from the (possibly many) pairs of triangles that are almost the closest" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004862_0005208_10196331.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004862_0005208_10196331.pdf-Figure13-1.png", + "caption": "FIGURE 13. Configuration of the final antenna (Antenna E): (a) Side view, (b) End view.", + "texts": [ + " To ensure the precision of the machining and stability of the structure, protrusions are made on the upper sides of the baluns to fit into the rabbets on the dipole substrate and ground reflector. In Addition, the protrusions make it simple to solder between the ground reflector, baluns, and the dipole substrate. To firmly guarantee the orthogonal placement, Slot 1 and Slot 2 are discretely embedded in Baluns 1 and 2. Figs. 12(a) and 12(b) show the design parameters of Balun 1 and Balun 2, respectively. Furthermore, to achieve a high gain unidirectional pattern, a ground reflector is placed underneath the balun and parallel to the dipole substrate as shown in Fig. 13. 78760 VOLUME 11, 2023 An important parameter that affects the impedance matching of the Antenna E is the height of the balun H (see Fig. 13(a)). This parameter is investigated by varying H with respect to \u03bb0. Where \u03bb0 is the free space wavelength at the lowest frequency band. Figs. 14(a) and 14(b) show the simulated reflection coefficients and impedance from Balun 1 and 2 respectively. The parametric results indicate a good matching for H = 0.215\u03bb0. Finally, the design parameters of the proposed antenna (Antenna E) are provided in Table 1, and its configuration is depicted in Fig. 13(b). In the following chapter, the numerical and measurement results such as S-parameters, radiation pattern, and realized gain outcomes are provided and the comparison between them is given. V. NUMERICAL AND MEASUREMENT RESULTS In this part, numerical and experimental outcomes are provided and compared. Besides, the performance of the proposed antenna is compared with the literature in detail. The antenna and balun structures are fabricated by using LPKF milling technology. Rogers 4003C having a thickness of 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003719_cle_download_546_224-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003719_cle_download_546_224-Figure1-1.png", + "caption": "Fig. 1. Numerical dynamic model of the \u201cMBC \u2013 foundation\u201d system. Lifting crane numerical model: 1 \u2014 a telescopic boom, 2 \u2014 a rotary platform, 3 \u2014 a crane platform, 4 \u2014 a bogie, 5 \u2014 a hoist rope. Railway track section model: 6 \u2014 a ballast section, 7 \u2014 a subgrade, 8 \u2014 assembled rails and sleepers. Other elements: 9 \u2014 a framework of sleepers, 10 \u2014 a load", + "texts": [ + " The analytical dynamic model of the MBC system shall adequately reflect the basic physical and mechanical characteristics of the actual boom crane elements. Simulation is carried out in SolidWorks Simulation (module for structural analysis using the finite element method) and SolidWorks Motion (module for comprehensive dynamic and kinematic structural analysis) (Alyamovsky, 2015; Kurowski, 2017). The virtual 3D model of a lifting crane of the \u201cMBC \u2013 foundation\u201d system is based on the structure of the Sokol 80.01M railway boom crane (Fig. 1). Bogies as well as elements not presented in the model in terms of design (power unit engine, rotation mechanism, hook assembly, automatic coupler, winch hydraulic motor, winch, counterbalance, operator\u2019s cab, etc.) are accounted for by concentrated and distributed masses and forces. The developed numerical dynamic model of the \u201cMBC \u2013 foundation\u201d system in SolidWorks Motion conventionally consists of three levels (Table 1) and can be adjusted according to the following: \u2013 the geometric and mass inertia characteristics of lifting crane elements; \u2013 the correspondence between the reactions of the lifting crane model outriggers with the reactions obtained using methods described by Gokhberg (1988) and Vainson (1989); \u2013 stiffness and strength characteristics of elements, parts, and assemblies of the lifting machine and framework of sleepers; \u2013 the theory of soil mechanics; \u2013 the system of differential equations for free and forced oscillations of the telescopic boom section, load, and frame, with account for foundation pliability" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000156_ownload_109198_pdf_6-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000156_ownload_109198_pdf_6-Figure2-1.png", + "caption": "Fig. 2. Folding defect in cold forging process: die scheme (a), formed part (b), 1 \u2013 upper section, 2 \u2013 lower section, 3 \u2013 folding defect", + "texts": [ + " In the cold forging process, billet and tooling temperatures are room temperature. Material flows and dies cavity filling are very important in this process. The material flow behavior and the influence of various factors involved in the process were explored. During the cold forging process with an axisymmetric billet, a movable punch applies force on billet material and the material flows to form the formed part in dies cavity. A finite element simulation is developed to study the defect formation mechanism. Fig. 2 shows the material behavior in cold forging process. It is observed that in the forming process appears a defect as a folding defect on the material flow (Fig. 2). In this study, the material flow behavior has been included with combined behaviors as forward, backward and radial flows. There are two major stages for filling dies cavity. First stage, when the punch presses the billet, the material under the punch moves down and up. Die cavity in lower section faster than upper section fills. After that the material flow under punch completely moves up, second stage begins. In second stage a critical inner curved surface in upper section appears. The punch movement continues down and the flow pattern further develops a defect as folding defect that shown in Fig. 2. In this process study to predict and avoid defect as a folding defect is very important and necessary to create precision parts. Based on the revealed folding defect, it is therefore necessary to design a kinematical mechanism by using finite element simulation to avoid defect as a folding defect. In this investigation in order to avoid folding defect and to make new material flow and to create a precision part without folding defect has been used a movable lower die in dies component. Fig. 3 and Fig 4 present the simulation results of material flow behavior" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure1.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure1.11-1.png", + "caption": "Figure 1.11 : Typical electric machines for traction applications, (a) PMSM (with interior magnets configuration), (b) IM, (c) SRM [25].", + "texts": [ + " Indeed, with the wide variety of options, it has been proved \u2013 based on the diversity of the adopted types in existing electrified vehicles - that a suitable type depends on the technological targets aimed to be reached and some economic constraints (mainly motor construction cost). Once an electric motor category and type seem to fit the specifications and requirements, researchers launch a process of design and optimization. This same procedure is conducted for air vehicles or planes as well. However, constraints and targets are quite different since external conditions and issues at altitudes are not similar, and objective loads are by far greater. The typical types of electric machines used in traction applications are presented in Figure 1.11 in assembled and exploded views. One can find that mainly the three presented types (Permanent-Magnet, Induction, and Switched-Reluctance machines) are the most suitable types for electrified powertrains allowing the engine to operate closer to its peak efficiency areas, lowering fuel consumption in hybrid vehicles [25]. Statistics on electric motors technology for EV and HEV propulsion during the last twenty years are depicted in Figure 1.12. Data from [22] show that over the last twenty years, the PMSM type is widely used for electric propulsion vehicles (73% of vehicles with electrified propulsion)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002053_e_download_2200_1306-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002053_e_download_2200_1306-Figure6-1.png", + "caption": "Figure 6: Semi-rigid chain diagram", + "texts": [ + " The bottom half (uncut side) of each segment mimics the routing route pattern and is uncut so that the exoskeleton has a basic foundational shape. The holes used to connect the adjacent segments together are placed on the edges of the segment as this ensures maximum flexibility and rotational ability. The exoskeleton will also be able to adjust according to people with different heights and sizes, as the semi-rigid structure allows for compatibility for different users. ISSN: 2167-1907 www.JSR.org 5 As seen from figure 6, these 5 segments can be defined as modular-designed semi-rigid chains which consist of chain elements, pins, routing grooves, and contact surfaces. The routing groove from each semi-rigid chain shown above is what will be used to implement the aforementioned routing system suited to the human anatomy, and it will be the base of each chain. To ensure that the metallic string is able to follow the routing system, a hole is placed along the routing groove so that the string is able to not only follow the predetermined guiding route but will also be secure throughout the entire exoskeleton. As seen in figure 6, the pin is designed optimally for flexibility and allows for each semi-rigid chain to rotate individually modularly as a human\u2019s leg\u2019s motion is not completely uniform until it is along the routing groove. The design of the pin and chains also allows for secure stability, as the dimensions of each chain are adjusted such that they just perfectly can fit into each other, and can be easily secured by the pin. As aforementioned, the contact surface of each chain is also smoothened out so that there aren\u2019t any sharp corners or anything that could cause potential harm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001134__iceas2022_04002.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001134__iceas2022_04002.pdf-Figure1-1.png", + "caption": "Fig. 1. Example of a CubeSat architecture.", + "texts": [ + " To conduct a satellite mission, two segments are needed: the space segment, which is the satellite that will be in orbit for data acquisition; and the ground segment or the facilities accompanying the satellite during the mission. The satellite architecture is a combination of two main parts: the structure, which contains the technologies that ensure the satellite\u2019s functions; and the payload, which regroups the tools needed for the experimentation. The satellite structure is a combination of several subsystems, as shown in Fig.1. * Corresponding author: chanouialae@gmail.com \u00a9 The Authors, published by EDP Sciences. This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0/). The choice of the payload hardware and software depends on the conducted mission. For instance, in earth observation and onboard image processing, the payload hardware can be a single or multiple cameras combined with a processing unit. The processing unit can either be the satellite OBC or a payload dedicated controller that is in charge of image capture and processing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002000_f_version_1666604679-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002000_f_version_1666604679-Figure1-1.png", + "caption": "Figure 1. The structure, layout, and body frame definition of Q-SAT. Solar cells marked in red are used for joint estimation of the sun vector.", + "texts": [ + " Redundancy analyses are also presented in Section 3. Simulation and experiments that evaluate the overall design and the on-orbit performance of IPSS will be discussed in Section 4. Finally, we summarize in Section 5. In this section, an overview of the layout and working principle of Q-SAT will be introduced briefly. The mechatronic design as well as the sun vector inversion methods of the proposed IPSS will be presented in-depth. The structure, layout, and body frame definition of Q-SAT are shown in Figure 1. Q-SAT is a small spherical satellite with a diameter of 510 mm and weighs about 23 kg. The satellite consists of two hemispherical shells, an equatorial ring, and a cuboid central frame to install various onboard devices. The hemispherical shells are sculpted from single blocks of aluminum alloy to guarantee machining accuracy and overall strength. 20 pentagonal and hexagonal plates are installed on each hemispherical frame to seal the structure. Both hemispheres are attached to the equatorial ring, which also connects the cuboid central frame and the separation system", + " To guarantee the spherical structure, solar arrays are mounted on the surface of the two hemispheres. Q-SAT works in a 500 km sun-synchronous orbit. The specifications and orbit parameters of Q-SAT are summarized in Table 1. The spherical Q-SAT was launched as a secondary payload, which is a challenging task. We have designed a customized electromagnetic separation system for Q-SAT to address the problem [4,5]. To provide interfaces with the separation system, 4 protrusions are designed around the equatorial ring of Q-SAT as shown in Figure 1. The separation system has two main functions: locking and release. The locking state is achieved by applying preloaded spring forces to the 4 protrusions which were also restricted by limit blocks of the separation system. In the locking state, Q-SAT is fixed to the separation system. Once the release signal is received, the separation system removes the limit blocks concurrently by a series of delicate transmissions using electromagnetic forces. When the limit blocks are drawn out, Q-SAT will be pushed into space by the preloaded spring forces", + " The bias momentum wheel works in a constant speed mode to provide extra stability in inertial space to avoid attitude divergence under weak magnetic control. The sun vector and geomagnetic vector are used as references to determine the three-axis attitude of Q-SAT (only the geomagnetic vector is used when Q-SAT enters the shadow zone). The reference vectors can be obtained from the sun ephemeris [11] and the International Geomagnetic Reference Frame (IGRF) [12] with precise orbit data. The proposed IPSS and a COTS magnetometer are used for the sun and geomagnetic vector measurement in the body frame. As shown in Figure 1, solar cells marked in red are utilized for joint estimation of the sun vector. As shown in Figure 2, the IPSS consists of 16 solar cells evenly distributed on the spherical surface, 16 thermal resistors for temperature compensation, and corresponding sampling circuits. The 16 solar cells are identical monocrystalline-silicon cells that are widely applied in solar power stations. The sun vector can be determined uniquely from at least 3 non-coplanar solar cells with valid measurements. IPSS is designed to have full spherical coverage of 4\u03c0 and thus can provide immediate sunray vector estimation under any attitude" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004567_id_0354-98362300167Z-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004567_id_0354-98362300167Z-Figure1-1.png", + "caption": "Figure 1. Calculation process for BEM, FEM", + "texts": [ + " (14) is: 0 0 ( ) ( ) 0 ( )d td d d t t t t e e \u2212 \u2212= + A A u u p (15) By using a level-by-level calculation to precisely identify the boundary nodes in the PMSM calculation area, the exponential function of the final matrix can be subdivided into: 2 2 0 0 0 0 1 1 1 ( - ) ( - ) ( - ) ( - ) 2! ! ! A t n n n n n e I A t t A t t A t t A t t n n = + + ++ += (16) The Taylor series expansion on the left-hand side of the equal sign of eq. (16) has been omitted in this paper due to the space limitation of the article. Furthermore, in order to more clearly illustrate our process of applying BEM and FEM for comparative heat transfer investigation of the PMSM, the calculation process of the two numerical methods is shown in fig. 1. In this paper, FEM is applied to numerically calculate the temperature distribution of the PMSM for EV. The temperature distribution of the motor at different speeds was investigated with the 3-D finite element PMSM model developed , and the heat transfer performance was tested using the made prototype. In the analysis, the 3-D finite element model was dimensioned identically to the prototype. In order to simulate the real operation of the PMSM, it is assumed that the motor is well insulated. Other assumptions are: \u2013 The fluid flow velocity inside a water-cooled system is much less than the speed of sound, so the fluid is considered incompressible" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001938_f_tera2018_05010.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001938_f_tera2018_05010.pdf-Figure1-1.png", + "caption": "Fig. 1. Photo of opened cryostat with three samples on three sapphire lenses (left), and schematics of sensitivity measurements (right): 1 fast radiation source, 2 bandpass and lowpass filters, 3 hemisphere lens, 4 extension substrate, 5\u2013 bolometer array", + "texts": [ + " Another layout modification is in eliminating of additional layer of so-called thin gold that suppressed superconductivity and connecting Al electrodes directly to thick TiAuPd antennas that also improve cooling of superconducting electrodes. Our previous arrangement of experiment was based on a back-to-back horn that reduces a role of antenna dimensions on overall spectral characteristics and beampattern. In present research we have developed results of previous results [1, 2] and used immersion sapphire lens instead of horn. Such substrate lens provides direct illumination of array, avoid substrate modes, and increase the gain of planar antenna. Top view of dilution cryostat [3] with 3 such lenses is presented in Fig. 1. Each sample was connected to room-temperature electronics through cold resistors that provide suppression of interferences and noise. The sapphire hemisphere lens diameter is 8 mm. Total extension for hyperhemisphere should be 1.5 mm, in this case antenna on the chip 0.28 mm thick is placed in the second focus of elliptical lens. Such elliptical lens convert a spherical wave into a planar wave. Cryogenic fast radiation source comprising NiCr film on sapphire substrate was equipped with a thermometer and placed on 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003866_55_S1110865703212130-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003866_55_S1110865703212130-Figure5-1.png", + "caption": "Figure 5: (a) An example instance of graph coloring problem, and (b) the mapped graph for the proof of Theorem 1.", + "texts": [ + " For a given local buffer size, determining the minimum global buffer size is difficult if a local buffer may have multiple lifetime intervals, which is stated in the following theorem. Theorem 1. If the lifetime of a local buffer may have multiple lifetime intervals and all data types have the same size, the decision problem whether there exists a mapping from a given number of local buffers to a given number of global buffers is NP-hard. Proof. We will prove this theorem by showing that the graph coloring problem can be reduced to this mapping problem. Consider a graph G(V,E) where V is a vertex set and E is an edge set. A simple example graph is shown in Figure 5a. We associate a new graph G\u2032 (Figure 5b) where a pair of nodes are created for each vertex of graph G and connected to the dummy source node S and the dummy sink node K of the graph G\u2032. In other words, a vertex in graph G is mapped to a local buffer in graph G\u2032. The next step is to map an arc of graph G to a schedule sequence in graph G\u2032. For instance, an arc AB in graph G is mapped to a schedule segment (A\u2032B\u2032A\u2032\u2032B\u2032\u2032) to enforce that two local buffers on arcs A\u2032A\u2032\u2032 and B\u2032B\u2032\u2032 may not be shared. As we traverse all arcs of graph G, we generate a valid schedule of graph G\u2032" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000652_0005208_10013678.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000652_0005208_10013678.pdf-Figure2-1.png", + "caption": "FIGURE 2. Parallel plate lens-like structure: (a) 2D sketch of the QOBF, (b) 3D view of one of the two identical continuous PPW lens-like beamformers.", + "texts": [ + " The choice of the thickness is the minimum achievable by milling machining without potentially bending the blade. The PPW\u2019s height is hppw = 2 mm, which guarantee the propagation of the fundamental q-TEM of the PPW structure over the whole operative band. The lens diameter is D = 20\u03bb0 at the operative frequency f0 = 30 GHz, and the focal distance is F = 0.7D. Each QOBF is fed by one of the 7 horns disposed along a circular focal curve centered in O and traced between the two focal points F1 and F2 as shown in Fig. 2b, so that one QOBF covers the angular range between \u221216.5\u25e6 and 19.5\u25e6 and the other from \u221219.5\u25e6 and 16.5\u25e6. Both focal points are 4604 VOLUME 11, 2023 symmetrical with respect to the x-axis, and they are defined by their angular positions \u03b1 = \u00b131.5\u25e6. The horns launch a cylindrical wave inside the PPW which is converted in a nearly plane wave feeding in turn one of the two ports of the septum polarizers linear array. They have an aperture size afeed = 14mm, about 1.5\u03bb0 at f0, and height of hppw = 2mm. Such aperture size is chosen to achieve an edge taper of about \u221210 dB considering a focal-to-length ratio F/D = 0.7. Fig.3 shows the normalized field amplitude launched inside the PPW by an horn at the center G of the focal curve C as sketched in Fig. 2. The cylindrical-to-planar wave front conversion achieved by the QOBF is shown in Fig. 4: the phase distribution along a line lp = 0.7D long (corresponding to \u221210 dB field tapering) at the output of the QOBF is depicted for a feeding horn at the center G of the focal curve C and when feed #5 (Fig. 2) is active. The maximum phase distortion with respect to an ideal TEM-mode phase front is about \u00b125\u25e6, corrisponding to a phase rotation of less than 0.07 wavelengths at the center frequency f0 = 30.0 GHz. The horns are fed by standard WR28 waveguides and thus a transition to coaxial line is used in measurements. B. SEPTUM LINEAR ARRAY POLARIZER The septum array polarizer has been first designed as a standalone device. The circular polarization generation can be easily explained considering two cases for the excitation of the two input rectangular waveguides" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001062_125_3_125_3_293__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001062_125_3_125_3_293__pdf-Figure3-1.png", + "caption": "Fig. 3. Finite element meshes (406,224 elements).", + "texts": [ + " This figure shows the situation when the switch is turned on, and the armature is pulled towards the stator and kept closed only by the attractive force of the permanent magnet. The residual magnetic flux density Br of this ferrite magnet is 0.42 T. The exciting coil has 2420 turns and its resistance is 160\u2126. When the coil is excited so that the magnetic flux can flow in reverse and the attractive force decreases until it is less than the reset force of the spring, the armature is lifted upward and the switch is turned off. Figure 3 shows the finite element meshes used in this study. Figure 4 shows the attractive force characteristics by varying the magnetomotive force from 0 to 363 A. The computed results are entirely in good agreement with the measured ones, though they are pretty different at the magnetomotive force of 90 and 363 A because of errors in measurement. Figure 5 shows the magnetic flux density distributions when the magnetomotive force is 363 A. As shown in Figure 4, the attractive force of 5.2 N is quite large when the magnetomotive force is 0 A, but does not decrease to a value zero even if the large magnetomotive force of more than 350 A is supplied" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure55-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure55-1.png", + "caption": "Figure 55. Drawing of the two steel side plates", + "texts": [], + "surrounding_texts": [ + "1 = variable 1 2 = variable 2 3 = variable 3 br = bearing comp = compressive extes = extensometer i = at ith data point long = longitudinal direction max = maximum xxii min = minimum pin = pin location s = symmetric spec = specimen ten = tensile trans = transverse direction ult = ultimate x = x-direction xx = in the axial direction for the +/-45\u00b0 shear tensile test y = y-direction xy = xy-direction (plane) 1 CHAPTER 1: INTRODUCTION In this chapter, previous and current thesis work is introduced. Section 1.1 introduces the different two different types of aircraft structures. In Section 1.2, the differences between an adhesively bonded joint and a mechanically fastened joint are explained. In Section 1.3, previous work is mentioned, considerations are made in order to avoid testing parameters, which have already been tested, and the three different failure mechanisms are explained. Section 1.4 explains the thesis goal and the thesis scope. 1.1 Introduction to Conventional & Advanced Composite Structures When you think of an aircraft\u2019s wing, it is composed of multiple panels and not usually made as a single piece. The use of joints becomes essential in an aircraft\u2019s wing (since joints serve to attach multiple structural components together to form one part). Ideally, the designer wants to avoid using them, since they can contribute a significant amount of weight to the overall aircraft\u2019s structure. Current aircraft manufactures are transitioning from a conventional aircraft structure to an advanced composite structure since the advantage of switching to an advanced composite structure is the significant reduction in parts and joints. Composite materials have desirable characteristics such as being: very stiff, extremely strong, and extremely light. For example, the Airbus\u2019 A350 aircraft structure is made up of 53% composite materials [1]. Even though the total amount of joints can be significantly reduced, that does not mean they can be avoided altogether. 2 As composites become more widely used in the Aerospace Industry, there still lies limited research in their ability to perform as joints. Their main flaw is their poor behavior in redistributing stress concentrations. Even though there has been a lot of research in composite joints, not enough advancement has been made compared to its metal counterpart. Metal joints (in particular, Aluminum joints) have been used for years in the Aerospace Industry. Currently, composite joints are overdesigned (made a lot thicker than they need to be) which leads to weight penalties. Design that is more detailed needs to done on composite joints in order to improve its ultimate bearing strength. 1.2 Introduction to Adhesively Bonded Joints & Mechanically Fastened Joints Two types of joints exist: one is the mechanically fastened joint, and the other is the adhesively bonded joint. In Figure 1, one can see an adhesively bonded single shear joint, a mechanically fastened single shear joint and a mechanically fastened double shear joint. The region between the two plates, in the adhesively bonded double shear joint, is the thin layer of structural adhesive used to bond both structural components together. Adhesively bonded joints are typically lighter but are often more difficult to design. No holes need to be made in an adhesively bonded joint. Reduction of holes reduces the amount of stress concentrations. Adhesively bonded joints can be problematic since the surface finish needs to be accounted for to achieve a strong bond between two surfaces. Another issue with adhesively bonded joints is that they cannot be removed as easily as a mechanical joint. 3 Mechanically fastened joints are widely used in the Aerospace Industry since they are more practical in the sense that they can be easily removed if a part needs to be replaced, repaired, or checked. Two types of mechanically fastened joints exist: single shear and double shear. In addition, a mechanically fastened joint can contain many fasteners. Mechanically fastened joints require a hole through both structural components, which creates stress concentrations. Both of the structural assemblies are held together by a bolt, and nut. 4 1.3 Previous Literature on Mechanically Fastened Composite Joints Numerous papers have been made on mechanically fastened composite joints, and in this section, the most important finds will be mentioned. According to Alan Baker[3], for a mechanically fastened double shear joint, load is transferred mainly through compression on the internal face of the fastener holes and as well as on a component of shear on the outer faces of the plate due to friction. Mechanically fastened composite joints can be made very durably but the designer needs to spend a longer time in the design process. According to Okutan [4], problems arise when the designer wants to analyze them since they have an anisotropic and heterogeneous nature. According to Chen [5], the behavior of a composite joint could be influenced by four parameters. The first is the material parameter. The material parameter includes fiber types, form, resin type, fiber orientation, laminate stacking sequence, material cure cycle, etc. The second is the geometric parameter. This includes the specimen width (W) and the hole edge distance (e). These are usually reported as W/D and e/D ratios where D is the diameter of the hole. A huge contributor to the strength of the specimen is the specimen thickness (t). The pitch is the distance between two or more holes in a multiple hole composite joint. The third (also very important) is the fastener parameter. This includes fastener type, fastener size, washer size, hole size, and tolerance. The last is the design parameter. The design parameter includes loading type (tension, compression, fatigue), loading direction, loading speed, hydraulic clamping pressure, joint type (single lap, double lap), environment, etc. 5 The lay-up sequence also played a significant role in the overall strength of the double shear joint, as well. Quinn & Matthews [6] studied in detail the effect of stacking sequences on the pin bearing strength in glass-reinforced plastics. They concluded that placing a 90\u00b0 layer ply on the outer surface of the laminate increased the overall bearing strength. Liu [7] tested different laminate thicknesses by varying the bolt diameter. He concluded that thick laminates with smaller diameter holes and thin laminates with larger diameter holes were a lot weaker than laminates with similar hole and laminate thicknesses. Stockdale & Matthews [8] studied the effects of bolt clamping pressure and found that boltclamping pressure played a huge role in the overall strength of the composite joint. Kim [9] tested to see the effects of temperature and moisture on the strength of graphite-epoxy laminates. From this experiment, the actual stress distribution of the joint is very difficult to find since the region is so small. The use of strain gages is impractical because that region is under a very high stress so any kind of strain gage applied would crush because of the force. That is why numerous researchers have been working on methods of modeling composite joints with the help of various finite element programs. The load capacity of a laminate is severely degraded due to the effects of hole clearance and friction. Hyer & Klang [10] investigated this phenomenon with a pin-loaded orthotropic plate. Pierron [11] used Abaqus to calculate the stress distribution around the hole of a woven composite joint. Most finite element modeling was done using 2D shell elements and recently there has been an increased amount of 3D modeling of composite joints. Previous researchers mention that the joint strength depends mainly on the failure criterion. 6 Only a small section of the bearing stress vs. bearing strain curve is linear, and then after, it becomes nonlinear. Stress concentrations cause crushing in a small section of the geometry, making it a very difficult nonlinear problem. Chang [12] created a 2D finite element model and assumed a frictionless contact with a rigid pin and a cosine normal load distribution in the pin-hole boundary. Another difficulty in modeling the composite joint requires the user to combine the failure criteria with a property degradation model. As the composite takes more load, the actual material properties are degrading over time, which would mean the modulus is decreased after each new load is applied. Lessard [2] used a 2D linear model along with a non-linear model to predict the strength of the composite joint. There are five different kinds of failure, which can occur in a laminate: matrix tensile, compressive failure, fiber/matrix shearing, fiber tensile, and fiber compressive failure. The Hashin failure criterion is an important criterion used to characterize failure within a laminate. 1.3.1 Previous Literature on Loading Rate Effects on Mechanically Fastened Composite Joints In flight, the aircraft might experience various dynamic loading conditions, so not only do composites need to be tested in quasi-static loading case, but also in a dynamic load case. Metals are not as load rate dependent as composite materials. Ger [13] tested a number of carbon and carbon fiber glass hybrid composites at dynamic loading rates of 6 to 7 m/s. The double shear joint configuration carried more load at high loading rates. It was also noted that for all joint configurations the stiffness of the joint increased significantly with 7 loading rate. In addition, what was noted was that the total energy absorption of the joint decreased significantly in the dynamic tests. Contradictory to Ger [13], Li [14] tested different types of joint configurations subject to a bearing load and found that energy absorption increased. Li [14] tested at higher rates of 4-8 m/s and found this interesting trend. The dynamic behavior of composite joints is much more complicated than its behavior for the quasi-static condition due to the involvement of strain rate and inertial effects. Li [14] concluded that crashworthiness design of tested composite joints could be based on their tensile strength design. Ger [13] mentioned there must be a significant safety factor applied to take into account bearing strength variations with loading rate. The failure modes might also be affected due to an increased loading rate. 1.3.2 Types of Failure in Mechanically Fastened Composite Joints According to Larry Lessard [2], it has been observed experimentally that mechanically fastened composite joints fail under three basic mechanisms: net-tension, shear-out, and bearing (in addition, combinations of these mechanisms are often given separate names). Typical damage mechanism is shown below in Figure 2. Looking at previous work, a net-tension and a shear-out failure are more catastrophic than a bearing failure. The best way to see if a bearing failure has occurred is to look at the bearing stress vs. bearing strain plot. Once the stress gets to its peak value and suddenly drops off to zero, then one can conclude it was a shear-out or a net-tension failure. If after the ultimate bearing stress, the specimen continues to carry load but deforms as a result, this means that the joint was designed very safely. According to Okutan [4], the optimum orientation for a bearing type of failure is a quasi-isotropic laminate orientation. A quasi-isotropic laminate 8 orientation means the laminate has the isotropic properties in plane. According to USNA [15], a quasi-isotropic part has either randomly oriented fiber in all directions, or has fibers oriented such that equal strength is developed all around the plane of the part. The geometry of a mechanically fastened composite joint is quite complex since it can affect the failure mode of the double shear joint specimen. Kretsis [16] & Matthews [16] tested fiber glass and carbon fiber reinforced plastics and found that the width(W), end distance(e), diameter of hole(D), and laminate thickness(h) all contribute to the overall mechanically fastened double shear joint strength. The most interesting aspect is that as the width of the specimen decreases to a specific amount, the mode of failure changes from bearing to net-tension. The W/D (width to hole diameter ratio of the composite double shear joint specimen) must be at least 5 order to avoid the net tensile type failure. Another interesting thing to note is when the end distance of the hole is a certain distance from the edge of the plate, the failure turned from bearing to shear-out (where shear-out is considered a special case of bearing failure). 9 1.4 Thesis Goals & Scope In the preceding sections of this thesis paper, the word double shear specimen will be used to represent one test specimen with a mechanically fastened double shear joint configuration. The goal of the thesis is to determine how the strength of a composite double shear joint is affected by two different cure cycles and five different loading rates. The composite joint will be tested in the double shear case and the laminate orientation was decided to be a quasi-isotropic laminate (based upon based on Yeole\u2019s double shear experimental results [17]). Yeole [17] tested three different laminate orientations in his thesis, and concluded that a quasi-isotopic laminate took the highest stress. Yeole [17] also mentioned that the testing of composite materials at fast loading rates could be an interesting topic to explore. ASTM 5961[18], which is the ASTM for bearing response of composite materials, required an extensometer to measure the relative pin displacement since using crosshead displacement is not an accurate method. A fixture was designed and manufactured in order to accommodate an extensometer. Finally, the numerical model was made to validate only the linear elastic portion of the experimental results. There are seven chapters in this thesis. Chapter 1, the introduction, includes a brief introduction to: composite materials, the difference between adhesively bonded joints and mechanically fastened composite joints, and the loading rate effects on mechanically fastened composite double shear joint bearing strengths. It also includes a brief literature review, the statement of the problem and the objective and organization of thesis. Chapter 2 focuses on manufacturing of the double shear specimens and the tensile specimens. Chapter 3 focuses on the experimental material testing 10 procedure conducted on the MTM49 Unidirectional Carbon Fiber pre-preg. It also explains the double shear fixture used for the testing. Chapter 4 focuses on the equations used in the experimental and theoretical calculations. Chapter 5 introduces the experimental result validation and then discusses the experimental results. Chapter 6 introduces: the numerical model, which was created using Abaqus 6.14 software, the convergence plot, and lastly, what, influences the numerical results. Chapter 7 is where the experimental results are compared to the numerical finite element results. Lastly, Chapter 8 is where the conclusions are drawn and different recommendations are made for the future work. In the reference section, one can find most of the related topics in the form of theses, books, reports and even papers published in numerous journals. In the appendix section, one find: drawings of the fixture, a tutorial on setting up the Bluehill2 double shear test method, a tutorial on finding the unknown engineering constants with the Autodesk software, a tutorial on outputting the force vs. hole deformation in Abaqus, and a tutorial on the composite double shear specimen Abaqus model. 11 CHAPTER 2: MANUFACTURING & PREPARING OF THE SPECIMENS This chapter will introduce the type of specimens that were manufactured and tested in the Instron machine along with their dimensions. All the dimensions were based on published ASTM test standards. ASTM is an international standards organization, which develops and publishes voluntary consensus technical standards for a wide range of materials, products, systems and services. 2.1 Tensile Specimen & Double Shear Specimen Dimensions The dimensions for the 0\u00b0 tensile specimens and the 90\u00b0 tensile specimens were found in ASTM D3039 [19] Standard test method for tensile properties of fiber-resin composites. The dimensions used for the shear modulus +/- 45\u00b0 were found in ASTM D3518 [20]. Below in Figure 3, one can see all of the tensile specimen dimensions for each specific fiber orientation angle. Figure 4 shows a drawing of all four different fiber orientation tensile specimens. The +/- 45\u00b0 shear specimens and the quasi-isotropic laminate specimens had the same dimensions. Figure 5 shows the dimensions, based on ASTM D5961 [18], of the composite double shear specimens. The quasiisotropic tensile specimens were tested to see how the theoretical material properties matched. 12 13 2.2 Manufacturing Process In the Cal Poly\u2019s Aerospace Engineering Composites Lab, there are two ways to manufacture a composite. One can use pre-preg material or apply a wet layup process. Pre-preg material is a lot easier to use since it already has the resin infused inside the material. In order to preserve the resin in the pre-preg material, it needed to be stored in a freezer at low temperatures. Once the pre-preg material is thawed, then the user is able to apply it to a mold or create a plate out of it. The second way, the wet-layup process, consisted of having the fibers in their pure form, which usually come in a roll, and having a two-part epoxy. Once the fibers were cut out from the roll, the two-part epoxy is mixed with the correct ratio and then applied to the dry fibers. The part is then sealed, with a vacuum bag (where all the air is removed from the part). Then the cure cycle of the 14 resin is applied to the vacuum-bagged part. All of the tensile and double shear specimens were made on the heat press. When making a composite plate in the heat press, the user needed to sandwich the laminate between two nonporous sheets and two 0.25 in. thick Steel plates. Figure 6 shows how the heat press cure process was set-up. The non-porous sheets served to prevent the resin from sticking to the steel plates. The composite plate, the steel plates and the non-porous sheets were placed inside the heat press and then the cure cycle was programmed. Once cured, the composite plate was cut into various size specimens. 2.2.1 Double Shear Specimens All the composite double shear specimens were made with the quasi-isotropic laminate orientation. The quasi-isotropic laminate orientation, [0 0 +45 -45 +45 -45 90 90]s, is short hand for [0 0 +45 -45 +45 -45 90 90//90 90 -45 +45 -45 +45 0 0]. The subscript s means that the laminate 15 is symmetrical about the last ply (which in this case is a 90\u02da ply). The alternate cure cycle was the Cytec\u2019s MTM 49 cure cycle and the datasheet cure cycle was the Umeco\u2019s MTM 49 cure cycle.. The material was first thawed since according to the Umeco\u2019s [22] MTM 49 datasheet, if the roll is open to the environment, condensation will occur on the pre-preg material, which will degrade the quality and the aesthetic look of the material. Sixteen 12 in. by 12 in. plies were cut out and orientated in the quasi-isotropic laminate orientation of [0 0 +45 -45 +45 -45 90 90]s. All the respective angles within each ply of the laminate were carefully kept within \u00b1 1\u00b0. Shown in Figure 7, a protractor was used to make sure each ply in the laminate was within \u00b1 1\u00b0. Once all the plies were stacked very carefully (in order to prevent air pockets from occurring within the laminate), the cure cycle was programmed into the heat press. Air pockets create areas where delamination can occur, which leads to the formation of cracks. Cracks can severely weaken composite structures. The second step consisted of programming the cure cycle into the heat press. Shown in Figure 16 8, is Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22]. Two different cure cycles were tested to see its effects on the material\u2019s double shear bearing stress. Increasing the dwell temperature from 248\u00b0F to 275\u00b0F and increasing the dwell time from 60 minutes to 90 minutes both affect the mechanical characteristics of the resin. The dwell temperature is the temperature which is held constant in the cure process (for this material, it occurs after the temperature ramp up stage). The dwell time is the duration of the dwell temperature stage. Each different carbon fiber matrix system will have its own recommended cure cycle printed in its specific datasheet. In the experimental section, one can see the difference in mechanical properties of the material based on the two different cure cycles. The first cure cycle was Cytec\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [22] (also known as the alternate cure cycle). The heat press was adjusted to the specific cure cycle. First, the cure cycle temperature ramped up from room temperature of 77\u00b0F to 275\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 275\u00b0F for 90 minutes. After the 90 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. A uniform pressure of 2 psi was applied on top and bottom of the plate. 17 The second cure cycle was Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg cure cycle [21], shown in Figure 9 (also known as the datasheet cure cycle). The heat press was adjusted to the specific cure cycle. First, the press ramped the temperature up from the room temperature to 248\u00b0F, at a rate of 5\u00b0F/min. The second cooking step dwelled (kept temperature constant) the 248\u00b0F for 60 minutes. After the 60 minutes, the material cooled down to 120\u00b0F at a rate of 5\u00b0F/min. for 15 minutes. The pressure was held constant between both cure cycles. 18 The third step consisted of preparation of the test specimens. Once the composite laminate finished curing, the material was removed from the press and was cut with a tile saw, which had a diamond-coated blade. The tile saw had an adjustable clamp that helped keep the cuts within 0.1 of an inch. Figure 10 shows the tile saw used to cut the specimens. A straight cut was made on the composite laminate, in order to clean up the edge of the plate. Next, the top side of the plate was aligned to the straight section of the small tile saw. The cuts were made carefully in order to keep a 90\u00b0 angle on the side of the cured laminate. Once all the cuts were made, and the zero direction of the laminate was located accordingly, specimens were cut to the correct width. Based on ASTM D5961 [18], a W/D (specimen width to hole diameter ratio of the composite double shear joint specimen) of 6 and e/D (hole edge distance to diameter of hole ratio) of 3 were used. These geometric conditions guaranteed the double shear composite specimens failed in bearing and not in net-tension or shear-out. Based on these geometric conditions, the specimens needed to be 1.5 in. wide by 5.5 in. in length. The tile saw 19 was used to trim the long 1.5 in. wide specimens to their final length of 5.5 in. A small aluminum block was clamped to the tile saw, which helped minimize variations in the length of all the specimens and allowed multiple specimens to be cut at the same time. After the specimens were cut to their specified length and width, they were grouped into sets of five. A mini microfiber-board fixture was created in order for five holes to be drilled at the same time. The fixture was clamped into the drill press. Five composite double shear specimens were stacked onto the drill fixture and the top left corner of each composite double shear specimen was aligned to the top left corner of the fixture. An Aluminum template was placed on top of the composite double shear specimens and was used to align the 0.25 in. diamond coated end mill bit. Once the composite double shear specimens were aligned accordingly, a small c-clamp was used to constrain the specimens along with the Aluminum template from moving/rotating during the drilling process. In Figure 11, one can see the fixture, the Aluminum template and the end mill bit used for the hole drilling process. 20 Once the holes were created for all the composite double shear specimens, there needed to be a 0.5 in. wide horizontal slit on each face of the composite double shear specimens. A thin Aluminum template was created to assist in locating a specific distance from the hole. This slit needed to be placed accurately within a tolerance of 0.01 in. The template is shown below in Figure 12, and the flat edge of the Aluminum template was used to locate the slit location. The slit needed to be as horizontal as possible and deep enough to catch the moveable knife-edge of the extensometer. 21 Emery cloth helped distribute the high clamping pressure (which is applied by the hydraulic clamps) which occurred at the bottom of the double shear specimen and the emery cloth prevented the composite double shear specimen from slipping during the test. Aluminum tabs were not needed for the double shear test because the specimens failed before reaching 7,000 lbs. The emery cloth works up to a maximum load of 7,000 lbs. The emery cloth was 1.5 in. wide and had a grit level of 120, which is shown in Figure 13. Each specimen only needed emery cloth on one end. Only a 3 in. long piece was needed to cover all of the specimen\u2019s width. A small portion of painters tape served to hold the emery cloth in position. The emery cloth was also reusable; so one piece of emery cloth could be used on two or more specimens. In Figure 13, on the right, shows the ready-to-test composite double shear specimen. 22 2.2.2 Tensile Specimens The same method was applied for the composite tensile specimens, except that these specimens did not have a hole. Stacking the layers needed to be done in a very careful manner in order to prevent misalignment. Once the composite shear modulus specimens and the 90\u00b0 composite tensile specimens were cut to 10 in. by 1 in., then all that was needed was to apply the emery cloth to the ends. Painters tape was used to secure the emery cloth in position. Then, the composite shear modulus specimens and the 90\u00b0 specimens were ready for testing. The 0\u00b0 unidirectional carbon fiber composite tensile specimens required 2 in. long aluminum tabs (as specified by ASTM 3039 [19]). Sandpaper was used on the surface, near the ends of the 0\u00b0 unidirectional carbon fiber composite tensile specimens. A small section of the surface was 23 abraded, and then, acetone was used to clean the surface. Structural adhesive was used to bond the Aluminum tabs to the 0\u00b0 unidirectional carbon fiber composite tensile specimens. After a full day of curing, the 0\u00b0 unidirectional carbon fiber composite tensile specimens were ready to be tested in the Instron 8801 machine. In Figure 14, one can see the ready-to-test 0\u02da unidirectional carbon fiber composite tensile specimens and the +/-45\u02da composite shear modulus specimens. 24 CHAPTER 3: TESTING PREPARATION & PROCEDURE In this chapter, the test preparation and procedure are explained thoroughly. Section 3.1 introduces the type of testing machine used for the experiment. Various test recommendations are made and included inside the preceding subsection. The Auto-Loop tuning feature is explained in detail and an example is made to assist the user in using this feature. The Specimen Protect feature in Bluehill2 is explained with full detail, which helped produce very consistent experimental results. Finally, in Section 3.3, the tensile double shear test and tensile test procedures are explained. The design and set-up of the double shear fixture is shown in detail as well. In the Appendix, the Bluehill2 test method creation was explained for a double shear tensile test. 3.1 Intro to Uniaxial Testing Using the Instron 8801 Servo-hydraulic Test Machine All the material tests were conducted on an Instron 8801. This machine is a dual column servohydraulic testing system. It meets the challenging demands of various dynamic and static testing requirements. The machine allows the user to hook up external force or strain transducers. A dynamic knife-edge extensometer was used for both, the tensile and double shear tests. The machine works in conjunction with a controller, which can be used to control the machine without the use of a computer. A servo-hydraulic system is composed of an actuator, which can apply a tremendous amount of load onto a test specimen. The load cell has a +/- 100 kN limit which means it can measure accurately up to +/- 22,000 lbs. axial force (in compression/tension). For the tensile double shear test, the maximum load that was seen during the test was around 1,700 lbs. and for 25 the tensile test, a maximum load of 7,000 lbs. was seen. The thicker the laminate, the higher the load the specimen could take before failure. Shown in Figure 15, one can see the Instron 8801 testing setup. The machine\u2019s crossheads contain metal jaws, which (powered by a hydraulic system) are able to clamp the specimen. The hydraulic clamping pressure is adjustable so for standard tensile testing, the pressure is set to 160 bar and for testing fragile composite resins, one would want to drop the pressure to 80 bar. Lowing the hydraulic pressure helped reduce premature specimen cracking. The crosshead mechanism loaded with a specimen is shown below in Figure 16. The specimen is placed carefully between two the hydraulically powered metal clamps which secure 26 the specimen in place. 3.1.1 Instron Servo-hydraulic Test Machine Recommendations For determining the modulus of elasticity along with the modulus of rigidity, the most accurate measuring tools were the extensometer and the strain gage. The crosshead displacement was not very accurate since the system displaces due to the compliance in the grips, and the actuator assembly. This displacement of the crosshead can cause unreliable results in the modulus of elasticity where accuracy is very important. The Instron crosshead and the extensometer both yielded slightly different stress/strain curves. This difference in stress/strain curves is due to the Instron crossheads displacing a little more than the extensometer. The extensometer measured only the deflection of the specimen relative to both of the extensometer knife-edges. The extensometer 27 had a gage length of 0.5 in. and a knife-edge width of 0.5 in. The dynamic extensometer, catalog no. 2620-826, can be seen in Figure 17. The top knife-edge is fixed and the bottom knife-edge records precise deflections. The extensometer was attached using two rubber bands. The rubber bands were wrapped multiple times around the specimen to prevent the knife-edges from slipping. Whenever the extensometer was handled, the safety pin was in place at all times. If the user wants to run a three-point or 4-point bend test, the crosshead displacement is accurate enough to capture the vertical displacement accurately. If the user wants even more accuracy, they are able to hook up an extensometer to the three-point bend fixture and record vertical displacement with that device rather than the crosshead displacement. The Instron 8801 machine has a few features, which need to be utilized in order to minimize testing errors. The load and position calibration should never be changed or conducted. Before any 28 test is conducted, the user should Auto-loop tune the load cell only once. Each time a new material is being tested; for example, carbon fiber compared to Aluminum, the load cell should be Autoloop tuned. A list of load cell control gains should be recorded in a separate table for each material, to avoid having inexperienced individuals auto-loop tune the machine. Some precautions in the auto-loop tuning process include to never auto-loop tune a material that will fails under 120 lbs. and to never set the force amplitude above 500 lbs. This may cause the machine to cycle through very rapidly. 3.1.2 Tutorial on Auto-Loop Tuning of the Load Cell for an 1 in. wide By 1/16 in. Thick Aluminum Specimen Each time a new type of material is tested in the machine the load cell needs to be auto-loop tuned whether it be Aluminum, Steel, carbon fiber, hemp composite, fiberglass or any other composite material. Auto-loop tuning the force insured that the load cell is set up to perform accurately for each specific material. The auto-loop tuning tool adjusted various gains on the load cell controller. This was done through the Bluehill2 console (under the load cell menu). Measure the cross-sectional area of the tensile specimen and note its yield stress (if a metal) or ultimate stress (if a brittle material). For example, for Aluminum, the yield stress is around 35 ksi and the tensile specimen had a cross-sectional area of 0.062 in.2. Make sure to apply a force which keeps the material well under its yield or ultimate stress (so 25 ksi was applied to the Aluminum specimen). 29 Insert the Aluminum tensile specimen into the hydraulic clamps and load the specimen to 1,500 lbs. Also, set the amplitude force to 500 lbs. In the auto-loop tuning wizard, the Proportional gain (P) needs to be set to one before any auto-loop tuning is conducted. The specimen will be exposed to a cyclic load of 1,500 lbs. \u00b1 500 lbs. After the auto-loop tuning completes, it will say Auto-loop tuning completed successfully and then, in the next window record the P, I, D and L values. The P value should be 12.564, the I value should be 0.56, the D value should be 0.49 and the L value should be 0.8. These gain values are essential to the auto-loop tuning process. Each time a new material is tested, it is advised to specify the correct P, I, D and L values in the console and only if those values are unknown then the material needs to be auto-loop tuned. After running the auto-loop tuning tool on the MTM 49 unidirectional carbon fiber material, the P (proportional gain) equaled 13.481 and I (integral gain) equaled 0.578. Both D and L equaled zero. Typically, the material needs to be auto-loop tuned in a load range where accuracy is needed. This range is typically, where the modulus of elasticity is measured in between 25% to 50% of ultimate stress as stated by ASTM D3039 Tensile Properties of Polymer Matrix Composite Materials [19]. If the material fails during the auto-loop tuning process, the actuator will shake violently and will not stop itself. Hit the red emergency stop button on the control panel or hit the red button on the Instron servo-hydraulic machine to power off the actuator. Start back up the machine and run the auto-loop tuning tool again at a lower force. 30 3.1.3 Tutorial on Specimen Protect The specimen is prone to premature failure due to high clamping forces exerted by the hydraulic clamps. Instron's Specimen Protect feature protects a specimen against this phenomenon. This feature is found inside the console, it is labeled Specimen Protect, and the symbol looks like small shield. Before using the Specimen Protect feature, go into the console, enter the Specimen Protect option menu and make sure the load threshold is set to 44 lbs. Clamp the bottom of the test specimen. Once the bottom of the specimen is clamped, move the actuator up until the top of the specimen sits in between the top crosshead's clamps. Turn on the Specimen Protect feature in the console and this will automatically move the bottom crosshead slightly up or down in order to prevent the specimen from experiencing more than 44 lbs. After both the top and bottom of the specimen are clamped, turn off the Specimen Protect feature and continue with the test. Every time a new specimen is inserted into the hydraulic clamps, this feature needs to be utilized in order to prevent premature failure. 3.2 Bluehill2 Test Preparation The machine was connected to a Windows desktop and from there Bluehill2 and the console were used to monitor machine inputs and outputs. According to Instron, the console software provides full system control from a PC: including waveform generation, calibration limit set up, and status monitoring. In real-time, Bluehill2 outputted various experimental results: strain values, load values, displacement values, and exc. All the raw data was outputted into an Excel file, which 31 could be used for post-processing calculations. 3.2.1 Bluehill2 Test Parameter Setup The main software of interest was the Bluehill2 software. In Bluehill2, the user has options of changing various testing parameters. Each test can be created and saved to a separate testing file, which can later be accessed when the user needs to conduct that type of test. Three different tests were created in the Bluehill2 software. The tensile test and tensile double shear test were created with the Bluehill2 software. Before a test file is created, it is required of the user to know what values are of interest for a specific structural test. The ASTM should exactly specify which the testing parameters should be used for the specific test. ASTM D5961 [18] suggested to test at a load rate of 0.05 in./min., to sample at a rate of at least 2 samples per second, and to output the extensometer displacement instead of the crosshead displacement. It also specified to run the test until a maximum force is reached and until the maximum force decreased by 30%. If the force didn\u2019t drop to 30% of the maximum; run the test until the pin displacement is equal to half of the hole diameter. For the pin displacement, the test ended once the extensometer read a displacement of 0.1 in. since that was the maximum range of the extensometer. The test specimen slipped in the grips when the force in the force vs. time plot flattens out, with respect to time, the specimen was slipping. The hydraulic pressure was manually set to 160 bar on the side of the machine. The fastener, which secured the Steel collars to the sides of the specimen, was hand tightened. Five different loading rates were 32 applied and adjusted accordingly inside the Bluehill2 software. 3.3 Instron Experimental Test Procedure The Instron start-up checklist was followed in the lab in order to start the machine safely. The first step of the checklist was to turn on the main power switch in the back of the lab. After turning on the main power switch, the next step was to turn on the Instron controller by pressing the power switch in the back of the Instron controller. Once the controller warmed up fully, a small blinking light appeared on the load calibration section of the controller. The calibrate button was pressed on the load menu of the controller. Next, the Cal button was pressed. Once the Restore button was pressed, the machine was fully calibrated even though it read \u201cCalibration not restorable.\u201d The desktop was turned on, and once the system booted up, the Bluehill2 software was started. As the software started up, it automatically started the console. The console is how the computer communicates with the Instron machine. The extensometer was plugged into the back of the Instron machine and it showed up under Strain 1 (in the Bluehill2 software). Once the extensometer was plugged in, it flashed in the console screen reminding the user that it needed to be calibrated. The extensometer\u2019s calibration was restored to a previous calibration. From this point on, the tensile test, or the double shear bearing test could be started. 3.3.1 Tensile Testing Procedure Before starting any ordinary tensile test, the user needed to have at least six tensile specimens 33 prepared for the test. For each tensile specimen, the thickness, width and gage length (distance between the tabs) were recorded. The Specimen Protect feature was also used when initially clamping the specimens. The first composite tensile specimen was tested to failure (without the extensometer), in order to find its ultimate failure load. A limit load was created for the extensometer and was decided based on the ASTM D3039 [19]. As stated in ASTM D3039 [19], the material's modulus of elasticity can be measured anywhere between 25% and 50% of its ultimate load or yield load (if it is a metal). The limit load was calculated by multiplying the 1st specimen\u2019s ultimate load by 0.25 and this value was specified in Bluehill2\u2019s end of test criteria. In Bluehill2 software, there is an option of recording the strain using an extensometer and once the limit load is reached, the test will pause allowing the user to remove the extensometer. Next, the remaining five composite tensile specimens were tested. The next composite tensile specimens were loaded in the machine and the extensometer was attached for each specimen. Figure 18 shows a composite tensile specimen (with an extensometer mounted on its surface). Once at the limit load, the extensometer was removed, and the test continued up to the ultimate load. Note that the initial modulus recorded by the extensometer was very accurate, and after removal of the extensometer, the crosshead took over and the accuracy declined. 34 3.3.2 Double Shear Testing Procedure Once the standard Instron startup procedure was completed, the tensile double shear Bluehill2 test method was started. In the Appendix, one can find a detailed tutorial on the tensile double shear Bluehill2 test method. Procedure A double shear tension, in ASTM 5961 [18], was followed closely. The user needed to make sure that all the dimensions were recorded such as specimen width, specimen length, and specimen thickness and distance between the edge of the specimen to the hole edge. The fixture used for the double shear test consisted of an assembly made up of three cold drawn Steel plates with two bolts and nuts connecting all three plates. The double shear fixture is shown in between the clamps on the left in Figure 19. The double shear fixture is shown, in the center, in Figure 19. The close-up of the collar-specimen assembly is shown, on the right side, in 35 Figure 19 as well. Each double shear joint specimen was sandwiched between two Steel plates, two Steel collars, four washers and a nut, which can be seen on the left and the center in Figure 20. The extensometer, as required by the ASTM 5961 [18], is fixed on the fixture with a small steel plate and two bolts, shown on the right in Figure 20. The extensometer's knife edge was carefully placed inside the slit of the specimen and secured with a rubber band. The nut which held the screw assembly together with the specimen was only hand tightened. In the Bluehill2 software, as stated earlier, the end of test occured if the maximum force droped by 30% or if the maximum extensometer displacement was 0.1 in. This end of test criteria worked perfectly for the 0.05 in./min., 0.1 in./min. and 1 in./min. loading rates. But for the 2 in./min. and 6in./min. loading rates, the maximum extensometer displacement was lowered to 0.05 in. At faster loading rates (above 2 in./min.), the actuator had problems stopping immediately at very small deflections (0.1 in.) so applying this adujstment prevented the extensometer from accidently breaking due to over-deflection of the crossheads. 36 37 CHAPTER 4: THEORETICAL SOLUTION METHOD In this chapter, information is given on the equations that were used to find all of the mechanical properties of the material used. The theoretical equations used to come up with the macromechanical behavior of a lamina and laminate are included as well. 4.1 Experimental Equations 4.1.1 Equations Used for Unidirectional Carbon Fiber and Aluminum Double Shear Specimens The width to diameter ratio of the specimens needed to be measured and recorded. Below, W, is the specimen width, and D is the diameter of the hole. \ud835\udc4a \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc4a/\ud835\udc37 The edge to diameter ratio of the specimens needed to be measured and recorded. \ud835\udc38 \ud835\udc37 \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = (\ud835\udc54 + \ud835\udc37/2)/\ud835\udc37 The diameter to thickness ratio of the specimens was measured and recorded. Below h is specified as the thickness of the specimen. \ud835\udc37 \u210e \ud835\udc5f\ud835\udc4e\ud835\udc61\ud835\udc56\ud835\udc5c = \ud835\udc37/\u210e The bearing stress was calculated by dividing the force, P, by the force per hole factor, k (equal (1) (2) (3) 38 to 1 for double shear test), with the diameter of the whole, D and by the thickness of the specimen, h. \ud835\udf0e\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strength was calculated by dividing the maximum force, Pmax, by the force per hole factor, k, with the diameter of the hole, D and by the thickness of the specimen, h. \ud835\udc39\ud835\udc4f\ud835\udc5f = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/(\ud835\udc58 \u2217 \ud835\udc37 \u2217 \u210e) The bearing strain was determined from the extensometer displacement, \ud835\udeff\ud835\udc56 divided by the k, force per hole factor, and the diameter of the hole, D. \ud835\udf16\ud835\udc56 \ud835\udc4f\ud835\udc5f = \ud835\udeff\ud835\udc56/(\ud835\udc58 \u2217 \ud835\udc37) The bearing chord stiffness was only reported if there existed an offset bearing strength. The linear portion, where the bearing stress ranges from 25 \u2013 40 ksi, is the bearing chord stiffness region. \ud835\udc38\ud835\udc4f\ud835\udc5f = \u2206\ud835\udf0e\ud835\udc4f\ud835\udc5f/\u2206\ud835\udf16\ud835\udc4f\ud835\udc5f 4.1.2 Equations Used for Tensile Testing of Unidirectional Carbon Fiber and Aluminum Specimens The maximum tensile strength F, was calculated by dividing the maximum force by the cross- (7) (6) (5) (4) 39 sectional area A. \ud835\udc39 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65/\ud835\udc34 The tensile stress, \ud835\udf0e, was calculated by dividing the force by the cross-sectional area, A. \ud835\udf0e\ud835\udc56 = \ud835\udc43\ud835\udc56/\ud835\udc34 The chord modulus of elasticity, E, was calculated by the difference two tensile stress points and their equivalent tensile strain points. \ud835\udc38 = \u0394\ud835\udf0e/\u0394\u03b5 The extensometer strain, \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 , was calculated by dividing the extensometer displacement, \ud835\udeff\ud835\udc56, by the extensometer\u2019s gage length, \ud835\udc3f\ud835\udc54. The gage length of the extensometer was always 0.5 in. \ud835\udf16\ud835\udc52\ud835\udc65\ud835\udc61\ud835\udc52\ud835\udc60,\ud835\udc56 = \ud835\udeff\ud835\udc56/\ud835\udc3f\ud835\udc54 The axial and transverse strains were plotted with respect to axial force. The slope of the transverse strain vs. axial load, \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 , was divided by the slope of the axial strain vs. axial load, \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 , and this equaled the Poisson\u2019s ratio of the material. \ud835\udf10 = \u2212\ud835\udc51\ud835\udf16\ud835\udc61 \ud835\udc51\ud835\udc43 / \ud835\udc51\ud835\udf16\ud835\udc59 \ud835\udc51\ud835\udc43 (8) (9) (10) (11) (12) 40 4.1.3 Equations Used with the Rosette Strain Gage Using the Equations (13) \u2013 (15), one can find the principle strains in the x-direction, \ud835\udf16\ud835\udc65, y- direction, \ud835\udf16\ud835\udc66 and finally the shear strain in the xy-direction, \ud835\udefe\ud835\udc65\ud835\udc66 . The three different theta values, \u03b81, \u03b82, \u03b83 were all angles relative to the axial strain gage. The strain rosette was placed on the composite quasi-isotropic specimen's surface so that each strain gage was in 0\u00b0, +45\u00b0 and 90\u00b0. So \u03b81 equaled 0\u00b0, \u03b82 equaled +45\u00b0, and lastly \u03b83 equaled 90\u00b0. The principle plane stresses were also transformed with a transformation matrix to the desired angle, \u03b8. In the transformation matrix c = cos \u03b8 and s = sin \u03b8. Where A is considered the transformation matrix below. The transformed plane stresses, \ud835\udf0e\u2032, equaled the transformation matrix, A times the plane stresses, \ud835\udf0e. (13) (14) (15) (16) (17) 41 Once the three principle strains were calculated then a transformation matrix was used to transform each of the three strains to the desired angle, \u03b8. The transformed plane strains, \ud835\udf16\u2032, equals Reuter's Matrix, R, times the transformation matrix, A, by the inverse of the R matrix, and lastly times the plane strains. The modulus of rigidity, G, was found by dividing the modulus of elasticity, \ud835\udc38, by 2 times Poisson\u2019s ratio, \ud835\udf10, plus 1. \ud835\udc3a = \ud835\udc38 2(1+\ud835\udf10) 4.1.4 Equations Used for In-Plane Shear Modulus Testing of Unidirectional Carbon Fiber Specimens The maximum shear stress, \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 (18) (19) (20) (21) 42 divided by the cross-sectional area times two. \ud835\udf0f12,\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65 2\ud835\udc34 The shear stress, \ud835\udf0f12, is calculated by dividing the maximum force, \ud835\udc43\ud835\udc5a\ud835\udc4e\ud835\udc65divided by the cross- sectional area times two. \ud835\udf0f12,\ud835\udc56 = \ud835\udc43\ud835\udc56 2\ud835\udc34 The modulus of elasticity in the +/- 45\u00b0 shear modulus test, \ud835\udc38\ud835\udc65\ud835\udc65, was calculated by the difference two stress points and their equivalent strain points. \ud835\udc38\ud835\udc65\ud835\udc65 = \u2212\u0394\ud835\udf0e \u0394\u03b5 The shear chord modulus of elasticity, \ud835\udc3a12, was calculated by the Equation (25). \ud835\udc3a12 = 1/( 4/\ud835\udc38\ud835\udc65\ud835\udc65 \u2212 1/\ud835\udc381 \u2212 1/\ud835\udc382 + 2\ud835\udf1012/\ud835\udc381 ) Converting normal strain to shear strain is done by dividing the shear strain by 2. \ud835\udf16 = 1/2 \u2217 \ud835\udefe 4.1.5 Equations Used for Volume Fraction Testing of Cured Reinforced Resins The ignition loss of the specimen in weight percent is calculated by subtracting the weight of the specimen, W1, and the weight of the residue, W2. (22) (23) (24) (25) (26) 43 Ignition lost, weight % = [(\ud835\udc4a1 \u2212 \ud835\udc4a2)/\ud835\udc4a1 ] \u2217 100 4.2 Theoretical Equations 4.2.1 Equations Used to Find Laminate In-Plane Engineering Constants The NASA Composite Laminate Report [24] was used to find all the laminate in-plane engineering constants (or also known as in-plane laminate material properties). Before finding the laminate in-plane engineering constants, the assumptions must be stated. The quasi-isotropic laminate, with a layup sequence of [0 0 +45 -45 +45 -45 90 90]s, meant that it\u2019s symmetrical and balanced. A symmetrical laminate simplifies the calculations since all that is needed to determine the in-plane engineering constants is the A matrix since the B matrix is composed of all zeros. But for asymmetrical laminates, one would need A, B, and D matrices. The subscripted numbers after the matrix, for example, the 1 and 2 in A12, which is in the number in the first row and second column of the matrix. The theoretical method of finding the laminate in-plane engineering constants required knowledge of Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material properties [21]. The experimental datasheet material properties were used inside the theoretical method. In Equation (28), to find the modulus in the x-direction, the stress in the x-direction is divided by the strain in the x-direction. Which can be also written as force per length in the x-direction, Nx , divided by the laminate thickness, h all over the strain. (27) 44 The A matrix simplifies to the one below since the Bij matrix is all zeros. For each layer in the laminate one needs to solve for a unique Q matrix. If a laminate has 16 different layers then there will be 16 Q matrices and after they are all solved they need to be summed together to form the A matrix. Equations (29) \u2013 (40) will be needed in order to solve for each value in the Q matrix. For any angled ply, one uses Equations (33) \u2013 (40). (32) (31) (30) (29) (33) (34) (28) 45 There is no force (or stress in the other two directions) so those are set to zero. This further simplifies the equations. (35) (36) (37) (41) (40) (39) (38) 46 After further simplification of the Equations (42) \u2013 (44), Equation (46) was equal to our modulus in the x-direction, Ex , only after this number was divided by the laminate thickness, h. \ud835\udc38\ud835\udc65 = \ud835\udc41\ud835\udc65/(\ud835\udf16\ud835\udc65 0 ) \u2217 1/\u210e Next, the same exact method is applied to the y-direction. The modulus in the y-direction, Ey equaled Equation (48). \ud835\udc38\ud835\udc66 = \ud835\udc41\ud835\udc66/(\ud835\udf16\ud835\udc66 0 ) \u2217 1/\u210e Next, the same exact method is applied to the xy-direction. The shear modulus in the xy- direction was found, in Equation (50), Gxy , only after divided by the laminate thickness, h. (42) (43) (44) (45) (46) (48) (47) 47 \ud835\udc3a\ud835\udc65\ud835\udc66 = \ud835\udc41\ud835\udc65\ud835\udc66/(\ud835\udefe\ud835\udc65\ud835\udc66 0 ) \u2217 1/\u210e Poisson\u2019s ratio, \u03c5xy , of the laminate was calculated using Equation (51). Poisson\u2019s ratio, \u03c5yx , of the laminate can was calculated using Equation (52). (51) (52) (50) (49) 48 CHAPTER 5: EXPERIMENTAL RESULTS In this chapter, the experimental results are explained in detail. Section 5.1 explained the validation process, which was conducted, on all the strain measurement devices. The axial modulus of elasticity and Poisson\u2019s ratio of Aluminum were validated. Section 5.2 summarized the material testing which was conducted on the unidirectional carbon fiber material. Section 5.3 explained the unidirectional carbon fiber material property testing. Section 5.4 explained the quasiisotropic carbon fiber laminate material property testing. Section 5.5 explained the experimental results found for the Aluminum double shear specimens. Section 5.6 explained the quasi-isotropic carbon fiber double shear specimens\u2019 experimental results. 5.1 Experimental Measurement Device Validation Before any strain measurement device was used on a composite material, its accuracy needed to be validated with commonly known material. In this case, an Aluminum specimen was tensile tested with a strain gage orientated in the axial direction, and another strain gage orientated in the transverse direction. Since the axial strain gage, the extensometer and the crosshead were measuring axial strain, their readings were compared. In the past theses, students were using the crosshead displacement to measure the modulus of elasticity. Using the crosshead displacement was very unreliable and it is explained in more detail in the next sub section. 49 5.1.1 Extensometer vs. Axial Strain Gage vs. Crosshead Displacement The test set-up of the Aluminum specimen is shown in Figure 21. The three principle directions and the clamped sections of a standard uniaxial tensile specimen are shown in Figure 21. Below in Table 1, an Aluminum sample was loaded and unloaded three times up to a tensile stress of 25 ksi. The tensile stress was calculated using Equation (9). A tensile stress of 25 ksi lies in the material\u2019s linear elastic region and it is far away from materials yield stress of 35 ksi. Table 1 shows the comparison of experimental results between the extensometer, strain gage and crosshead. Table 1 also shows the dimensions of the Aluminum specimen. The strain gage and extensometer experimental results were validated with the Aluminum 2024-T4 datasheet mechanical properties [25]. The moduli of elasticity, in Table 1, are in msi (10E6 lbs./in.2) and were calculated using Equation (10). There was less than 1% error between the extensometer and the strain gage when compared to the Aluminum 2024\u2019s modulus of elasticity. When comparing to the crosshead, there was an error of 64%. The crosshead displacement is not as accurate as an extensometer or a strain gage, because the crossheads have compliance (inside the actuator assembly) which elongates as load is applied. The actuator assembly starts to elongate, which significantly affects the experimental strain results. The small standard deviation showed how consistent the results were when using the three different measurement tools and the testing machine. 50 showing the clamped sections and the 3 principle directions (right) 51 Below in Figure 22, one can see the three runs that were done using the extensometer and the axial strain gage. The crosshead displacement was excluded from Figure 22, since the experimental strain varied so drastically from the extensometer and the axial strain gage. The strain gage and the extensometer read very similar moduli of elasticity. The extensometer and strain gage proved to be reliable, so both measurement tools were used on the composite specimens. 52 5.1.2 Poisson\u2019s Ratio Validation Using Axial and Transverse Strain Gages The Poisson's ratio of the Aluminum 2024-T4 needed to be validated. In Figure 23, one can see the axial and transverse strains plotted with respect to the axial force. The axial strain gage output is shown in blue and the transverse strain gage is shown in red. A linear curve fit was applied to both sets of strain gage data and their respective linear equations are shown, as well. Poisson's Ratio equaled to a value of 0.26, for the Aluminum specimen, using Equation (13). 53 5.2 Summary of Carbon Fiber Material Properties Below in Table 2, the results accumulated from Umeco\u2019s MTM 49 Unidirectional Carbon Fiber pre-preg material datasheet [21] are summarized. The values which have a (-) dash meant that they were not given in the material's datasheet. The strengths were specified in ksi, which is 10E^3 lbs./in. Table 3 shows the experimental material properties of the Umeco's MTM 49 Unidirectional Carbon Fiber pre-preg material, which were experimentally tested in the Cal Poly\u2019s Aerospace Composites Lab. Table 4 shows the experimentally tested and calculated quasi-isotropic laminate properties. Poisson's ratio, for Umeco\u2019s MTM49 Unidirectional pre-preg material was used from a previous report\u2019s value [26] of 0.25. All these material properties are further explained in the next few sections. Looking at Table 2 and Table 3, the 0\u00b0 compressive modulus is 22.3 msi and the 0\u00b0 tensile modulus is 26.6 msi. All of the tensile axial moduli of elasticity were similar but they were slightly higher than the compressive modulus specified in the datasheet. The tensile and compressive modulus should be very similar since the fibers are assumed to behave like an isotropic material. This material was not tested in compression since compression specimens need to be a lot shorter, in length (ideally have less than 0.5in. in gage length). An extensometer could not be mounted on the surface of the compression specimen since there is not enough room between the grips. The best way to measure, the compressive modulus of elasticity would be to use an optical high-speed camera, which records the relative motion through optics. 55 5.3 Unidirectional Carbon Fiber Material Property Testing 5.3.1 Test for 0\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens A laminate of 8 plies, [0]8T, was laid up and tested along the fiber direction. The 0\u00b0 direction is always the direction of the applied load in a uni-axial test. The ASTM 3039 [19] required a minimum of five specimens per test, and having more than five specimens helped improve the 56 consistency of the results. Each specimen was 10 in. long by 0.5 in. wide and with a thickness of 0.046 in. The ASTM 3039 [19] required curing 2 in. long by 0.5 in. wide Aluminum tabs on the specimens to prevent premature failures from occurring. The grip pressure was set to 160 bar. The tensile test began with testing one 0\u00b0 unidirectional carbon fiber composite tensile specimen (without an extensometer) to failure, to find its ultimate load. The limit load of 2,000 lbs. was chosen since the ultimate load was 4,600 lbs. The last six 0\u00b0 unidirectional carbon fiber composite tensile specimens were loaded to 2,000 lbs., and at 2,000 lbs., the test was paused so that the extensometer could be removed safely. Once the extensometer was removed, the Instron machine's crossheads took over in measuring the tensile strain. The load cell accurately measured the ultimate load up to an accuracy of +/- 45 lbs. In Figure 24, the 0\u00b0 unidirectional carbon fiber composite tensile specimens are shown to the left and one of the clamped post-test 0\u00b0 unidirectional carbon fiber composite tensile specimen is shown on the right. Figure 25 shows all seven of the tested 0\u00b0 unidirectional carbon fiber composite tensile specimens (each color represents a different specimen). Figure 26 shows the extensometer mounted on the 0\u02da unidirectional carbon fiber composite tensile specimen with two rubber bands. The compressive modulus was specified in the datasheet and the tensile modulus was not specified in the datasheet. The experimental tensile modulus was compared to the compressive modulus and the difference between the two values was 19%. A 17% difference between the tensile strength when compared to the datasheet values. 57 58 60 5.3.2 Test for 90\u00b0 Unidirectional Carbon Fiber Composite Tensile Specimens Next, a laminate of 14 plies, [90]14T, was laid up and tested along the matrix direction. A couple extra test specimens were tested to find the optimum hydraulic clamping pressure. The clamping pressure was initially set to 160 bar and once the specimen was clamped, it cracked. The hydraulic clamp pressure was reduced to 60 bar in order to prevent this premature failure from occurring. Eight specimens were tested since the material is very brittle and unpredictable. When examining the stress-strain plot of the 90\u00b0 unidirectional carbon fiber composite tensile specimens, the ultimate tensile stress determined the location of where the specimen would fail. As one can see in Figure 27, the four 90\u02da unidirectional carbon fiber composite specimens, which failed at an ultimate tensile stress of around 5 ksi, ended up breaking in the center. Whereas, the specimens which failed at a lower ultimate tensile stress failed near the emery cloth. The experimental results (between all the specimens) showed a very consistent modulus of elasticity. The ultimate tensile strength of the material varied, due to the matrix is very brittle. The failure of a brittle material is very unpredictable which one can see in the Figure 28. There was 17% difference between the datasheet 90\u00b0 modulus of elasticity and a 29% difference between the 90\u00b0 tensile strength when compared to the datasheet values. The ultimate tensile strength variations might have been due to the low accuracy of the load cell, which typically occurs at low loads (around 100 lbs.) since the accuracy of the load cell is +/- 45 lbs. Table 6 shows the experimental results of all the 90\u00b0 unidirectional carbon fiber composite tensile specimens. 61 63 5.3.3 Test for +/-45\u00b0 Shear Modulus Specimens After following ASTM D3518 [20], a laminate was created with an orientation of [+/- 45]4S which is a symmetric laminate with alternating positive and negative 45\u00b0 plies. Another way to write this is [+45 -45 +45 -45 +45 -45 +45 \u2013 45]s. The extensometer was placed at 0\u00b0 relative to the specimen. The axial modulus of elasticity, Exx, was recorded and Equation (25) was used to find G12. Equation (25) requires knowledge of E1, E2, and \u03c512. Eight shear modulus specimens, for consistency, were tested since ASTM D3518 [20] required a minimum of five shear modulus specimens. The shear modulus specimens are shown in Figure 29. The post-tested shear modulus specimens looked the same as the pre-tested shear modulus specimens (since the failure occurred in the matrix and not in the fiber). Figure 30 shows the highly consistent shear specimen results. Table 7 showed the detailed experimental results. There was 35% difference between the in-plane shear modulus and a 43% difference between the in-plane shear strength when compared to the datasheet values. Testing for the shear strength is not an easy task since the shear modulus specimen has to be in full shear state at failure. The tabs on the ends of the specimen create stress concentrations on the ends, which cause the specimen to fail prematurely. 64 66 5.4 Quasi-Isotropic Laminate Material Testing 5.4.1 Test for Quasi-isotropic Tensile Specimens The same test method used for the 0\u00b0 and 90\u00b0 specimens was used to test the carbon fiber quasi-isotropic tensile specimens. Once one quasi-isotropic tensile specimen was tested to failure, the ultimate load was recorded to be 6,500 lbs. The next six quasi-isotropic tensile specimens were tested with the extensometer up to a force of 2,000 lbs. The test paused once the force reached 2,000 lbs. and then the extensometer was removed. Figure 31 shows the quasi-isotropic tensile specimens before (on left) and after (on right) they were tested. The region circled in red showed the area where there was a fiber failure. Figure 32 showed a close-up of the tensile failure. In Figure 32, looking at the picture on the right, one can see the 0\u00b0 fibers on the outer layer held together, while in the center of the laminate, a crack began to form. The crack, in Figure 32, is circled in red. 67 68 From Figure 33, one can see a close-up of the strain rosette, which was on Specimen #1. Shown in Figure 34, a rectangular strain rosette (CEA- 06-120CZ-120 made by VishayPG) produced very accurate results. The rosette was placed on the quasi-isotropic tensile specimen at a 0\u00b0-45\u00b0-90\u00b0 orientation and the wires were soldered very accurately. Each strain gage resistance was checked (with a voltmeter) and read 120 Ohms. The strain gage worked correctly if the resistance across the strain gage read the correct resistance specified in the user manual. The quasi-isotropic tensile specimen #1 was tested one time by recording the strains in the 0\u00b0 direction, 45\u00b0 direction and 90\u00b0 direction. In addition, when the strain gage was being applied to the surface, an 80-grit sandpaper was applied to the surface of the quasi-isotropic tensile specimen. The sanding of the outer 0\u00b0 layer might have affected the material\u2019s mechanical properties. Table 8 shows this 8% difference in modulus of elasticity between the extensometer and the strain gage. From Figure 35, one can see the slight drop in stress (at 20 ksi) due to the pause in the test. The different line colors show the seven different quasi-isotropic tensile specimens that were tested. The main thing to note is the percentage difference between the modulus of elasticity found with the strain rosette and the extensometer. The ultimate tensile strengths were very consistent which showed from a very low standard deviation of 3.87 ksi. 69 70 72 5.4.2 Quasi-Isotropic Tensile Specimen #1 In-Plane Experimental Material Properties Figure 36 shows experimental strain values of the extensometer, the axial strain gage, the +45\u00b0 strain gage and the transverse strain gage. A slight variation exists between the axial strain gage and the extensometer because the extensometer was not placed in the same location as the strain gage. The sanding error, like stated in the previous section, might have also contributed to the error of 8%. The test was stopped at a force of 2,000 lbs. A linear curve fit was applied to all of the three separate strain gage readings and are shown in Figure 36. Next, the Poisson\u2019s ratio of the quasiisotropic tensile specimen was found using Equation (12) and in-plane shear modulus of the quasiisotropic laminate was found using Equation (23). The axial modulus of elasticity was found using Equation (10). 73 5.4.3 Quasi-Isotropic Laminate In-Plane Theoretical Material Properties The theoretical material properties were found using the NASA report on Basic Mechanics of Laminated Composite Plates [24]. In Section 4.2.1, one can find the equations used to calculate the theoretical material properties. Before these equations could be used, a few assumptions were made: (1) The material to be examined is made of up of one or more plies (layers), each ply consisting of fibers that are all uniformly parallel and continuous across the material. The plies do not have to be of the same thickness or the same material. [23] (2) The material to be examined is in a state of plane stress, i.e., the stresses and strains in the through-the-thickness direction are ignored. [23] (3) The thickness dimension is much smaller than the length and width dimensions. [23] The values in Table 9 were needed in order to come up with the theoretical material properties. Table 9 shows the values that were applied into the laminate theory since the laminate theory required knowledge of the material properties of one layer of the unidirectional carbon fiber material. With the help of a strain rosette and the use of Equations (13) - (15), all the in-plane principle strains could be found. 74 Below in Table 10, one can see the calculated experimental material properties using the strain gage rosette. Three different in-plane laminate material properties were calculated based on three different force values (1500 lbs., 1750 lbs. and 1900 lbs.). The theoretical material properties were in agreement with the experimental material properties since the error between the modulus of elasticity was only around 10% and only 2% for the Poisson\u2019s ratio. The low standard deviation showed the reliability of the testing equipment and the strain measurement devices. 75 5.5 Fiber Volume Fraction Test ASTM D2584 [27], Standard Test Method for Ignition Loss of Cured Reinforced Resins, was followed closely. Three volume fraction specimens were tested inside the furnace shown on the right in Figure 37. On the left of Figure 37, one can see a fiber volume fraction test specimen. The fiber volume fraction specimen was placed on top of an Aluminum plate. While the furnace was preheated to a temperature of 1000\u00b0F, the Aluminum plate was weighed and each fiber volume fraction specimen was weighed in grams and then converted to lbs. in order to keep the units consistent. The measuring scale had a least scale reading of 0.1 g. The dimensions of each fiber 76 volume fraction specimens were carefully measured and recorded. Each specimen was placed on the Aluminum plate and left inside the furnace for one hour. Once all the epoxy burned off, the fiber volume fraction specimen was weighed and this was weight of the fibers. The initial weight of the fiber volume fraction specimen minus the final weight of the fiber volume fraction specimen was the weight of the resin (matrix). After doing some simple calculations, along with using the cured resin matrix density of 1.24 g/cm3(from the material\u2019s datasheet); the fiber weight fraction along with the fiber volume fraction was calculated and compared to the datasheet. In Table 11, one can see the three different fiber volume fractions along with the fiber weight fractions. The fiber volume fraction specimen dimensions are crucial to the determination of the fiber volume fraction. The measured thickness of the fiber volume fraction specimen varied from 0.1 in. to 0.103 in., which meant that the heat press cooked unevenly. The slight variation of the specimen\u2019s thickness affected the volume fraction by 4%. The 8.3% difference between the experimental fiber volume fraction and the datasheet fiber volume fraction varied because not enough pressure was applied to the laminate during the curing process. The lower fiber volume fraction of 0.55 compared to 0.6 meant that there was more resin in the laminate. Not enough resin was squeezed out in the cure process. The pressure applied by the heat press was limited, so achieving the optimum fiber volume fraction (of 0.6) was difficult. The fiber volume fraction significantly affected all of the material property testing which was conducted on the Umeco MTM 49 unidirectional material. A low standard deviation showed that the data was very consistent. 78 Section 5.6 was conducted in order to validate the numerical model with the experimental data. Modeling a metal before modeling a composite is very important because metals behave in a more predictable fashion. Metals are a lot simpler to model since they exhibit isotropic behavior whereas composites exhibit orthotropic behavior. The material property inputs for an isotropic material are much less than for a composite material. For a composite, the user has to input three different moduli of elasticity, three moduli of rigidity, and three Poisson\u2019s ratios. For metals, the user only inputs the modulus of elasticity and the Poisson\u2019s ratio. In this validation, Aluminum 2024-T4 was used as the material of choice. Once the linear elastic model was validated with a metal, then any other material should be validated as well, but only for the linear elastic region of the material. This also validates the boundary conditions and any interactions, which were used in the numerical model. 5.6 Aluminum 2024-T4 Double Shear Test The Aluminum 2024-T4 double shear specimens were tested on the same double shear fixture as the composite double shear specimens. From Figure 38, one can see the bearing stress vs. bearing strain response of the five tested Aluminum double shear specimens. The first section of the bearing stress vs. bearing strain plot (the flat initial region) is the strain correction region. Compliance between the Instron parts, along with the clamps, occurred upon initial loading of the specimen. The deformation of all the internal parts of the Instron machine in the strain correction region. The linear elastic region, (shown inside the red square in Figure 38) for the Aluminum, was between 5 ksi and 40 ksi and after this region; the material experienced a non-linear behavior 79 up to its ultimate bearing strength. The strain correction region and the non-linear region were removed, which can be seen in Figure 39. The non-linear region and the strain correction region were not part of the numerical model. Figure 38 showed that specimen #5 failed at an ultimate bearing stress of 130 ksi and the other four specimens failed around 114 ksi. The extensometer\u2019s knife-edge slipped on the face of specimen #1 through #4, but for specimen #5, the extensometer did not slip. The linear elastic region can be seen in Figure 39. The specimen alignment might have caused the variations in the linear elastic strain values. The ultimate bearing strength matched up the Aluminum 2024-T4 material\u2019s datasheet [25]. Table 12 shows the experimental results of the Aluminum double shear specimens. Both the yield and ultimate strengths were calculated in the Table 12. Figure 40 shows a bearing type of failure, which occurred in all the Aluminum double shear specimens. Figure 41 shows the Aluminum double shear specimens before and after they were tested. The region circled in red shows the area where the failure occurred. Each specimens\u2019 hole diameter increased in size and also each specimens\u2019 hole diameter did not go back to its original shape once the load was removed, which showed that the material reached a plastic deformation. 80 82 5.7 Composite Double Shear Test As one can see in Figure 42 (from a paper by Yi Xiao [28]), the composite double shear specimens behaved differently than Aluminum double shear specimens. Recall, all the composite double shear specimens were manufactured with a quasi-isotropic laminate orientation of [0 0 +45 83 -45 +45 -45 90 90]s. The 4%D is considered the bearing strength of the material. The composite double shear specimens held load (without failing) up to the knee point. At the knee point, the first ply failed (after this point, the material properties started to degrade) and the slope of the curve was reduced. The load increased up to the final point, also known as the ultimate bearing strength of the material, where it maxed out. One positive thing about designing a structure to fail in bearing, as opposed to net-tension or shear-out, is that the force dropped 30% of the maximum load. Whereas, in net-tension or shear-out failure, the load dropped down to zero. Figure 43 shows a close-up of the bearing failure, which occurred on the composite double 84 shear specimens. As one can see, there is an excessive amount of damage near the pin location. All of the specimens exhibited a similar type of failure, so there was no need to take a picture of each of the failed specimens. Figure 44 shows ASTM 5961\u2019s [18] failure codes used to characterize any of the failure modes seen in a composite double shear test. The failure code, B1I, is used throughout the rest of the experimental section, which signifies a bearing type of failure. 85 86 5.7.1 Curing Cycle 1 (Cytec\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test Figure 45 shows the composite double shear specimens before and after the double shear test. In Figure 45, on the right, highlights the crushing regions, in red. All the failures are consistent. Eight specimens were tested for each of the five loading rates. For load rate 0.1 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. When looking at the alternate cure cycle experimental data, in Tables 13 & 14, an interesting 87 trend appeared. At slower loading rates, the composite double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min. the composite double shear specimens failed at an average stress of 64.4 ksi and 63.5 ksi whereas at 1 in./min., 2 in./min. and 6 in./min. the composite double shear specimens failed around 52.3 ksi. Looking at all the different loading rates, it seemed as if all the composite double shear specimens had a similar knee point. 2 in./min. and 6in./min. showed a greater drop in load after the composite double shear specimens reached their ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. did not show a huge drop in load after the specimens reached the ultimate load. 89 The maximum values of all the plots, in Figure 46, were the ultimate bearing strengths. When looking at Figure 46, one can see that as the loading rate increased the non-linear region decreased in size. The red-circled sections, in Figure 46, show how the non-linear region decreased in size. The linear region does not change as drastically as the non-linear region. As the load rate increased, the rate of damage also increased which explained the reduction, in size, of the non-linear region. 90 Looking at all of the load rates, the moduli in the non-linear regions are lower than the linear elastic regions. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. 91 5.7.2 Curing Cycle 2 (Umeco\u2019s MTM 49 Unidirectional Carbon Fiber Cure Cycle) for Double Shear Test When looking at the datasheet cure cycle experimental data, in Tables 15 & 16, a similar trend appeared. At slower loading rates, the double shear specimens performed slightly better than at higher loading rates. At 0.05 in./min. and 0.1 in./min., the specimens failed at an average stress of 62.7 ksi and 67.7 ksi, whereas at 1.0 in./min., 2 in./min. and 6 in./min., the specimens failed around or under 52.0 ksi. It also looks like at 2 in./min. and 6in/min. show a greater drop in bearing strength after the specimen reaches its ultimate load. Loading rates 0.05 in./min. and 0.1 in./min. do not show a huge drop in strength after the specimens reach the ultimate load. In general, fast loading causes more damage to the specimen which overall reduces the specimen's ability to carry load. There was no standard equation or method of finding the actual knee point of the material, so only the ultimate bearing strength was analyzed. Eight specimens were tested for each of the five loading rates. For load rates 2 & 6 in./min, the extensometer significantly slipped on specimen #8, which is why the data was removed. 93 When looking at Figure 47, one can see that as the loading rate increased the non-linear region decreased in size. In Figure 47, the red-circled section also showed the non-linear region decreased, in size, with increased loading rate. 94 5.7.3 Comparison between Cure 1 & Cure 2 In Figure 48, it is very clear that as loading rate increased, the ultimate bearing strength of the 95 material decreased regardless of the cure cycle. Further research can be done on how different cure cycles can affect the bearing response of a composite double shear specimen. Making the matrix less brittle and more ductile might improve the ultimate bearing strength of the material. Cure cycle 2 (Umeco\u2019s cure cycle) was 2% stronger in bearing when compared to the cure cycle 1 (Cytec\u2019s cure cycle). The MTM 49 Unidirectional carbon fiber pre-preg material was very sturdy by not being affected by an alternate cure cycle. 5.7.4 Comparison Between The Aluminum Double Shear Specimens & Quasi-Statically Loaded (0.05 in./min.) Composite Double Shear Specimens Aluminum is standardly tested at quasi-static load rate of 0.05 in./min, since it\u2019s strain rate independent [30] (not affected by different loading rates). The Aluminum double shear specimens 96 performed a lot better in bearing than the composite double shear specimens. Since the carbon fiber is more brittle by nature, its ultimate bearing strength is significantly lower than Aluminum. of the Aluminum double shear specimens was around 118 ksi and the ultimate bearing strength of the composite double shear specimens was around 63 ksi. That means that carbon fiber is 53% weaker than Aluminum 2024-T4 in a double shear joint configuration. The Aluminum double shear specimens yielded at around 40 ksi compared to the composite double shear specimens, which yielded at 30 ksi. As one can see from the bearing stress vs. bearing strain graphs, there is a huge difference in ultimate bearing strength between of both materials. It is interesting to note that both materials showed a strain correction region. The Aluminum double shear specimens and the composite double shear specimens did not catastrophically fail (they deformed without significantly dropping the applied load). 97 CHAPTER 6: NUMERICAL ANALYSIS Chapter 6 explains the overall finite element approach. Section 1 introduces the finite element model and different considerations, which were applied to the model. Section 2 explains the idea behind a convergence plot and its importance. Section 2 explains what factors influenced the numerical results. 6.1 Finite Element Analysis Introduction Once a Finite Element Analysis model is validated with experimental results, it can then be used in the design process. Abaqus 6.14-1 was used to model the double shear bearing test experiment conducted. All the different Finite Element software work very similarly and the only difference between them is their program interface. However, they all essentially break up the model into small elements and calculate the stress state on each element. The material properties are assigned to the elements and then, the boundary conditions and loads are applied to the model. In some cases when there are two or more parts, one might have to define different types of interactions or constraints for the model (for example, how those parts move relative to each other). The numerical software also predicts non-linear behavior, which requires a lot more material properties. Plasticity required the user to model the damage done on the material as load increased, which meant, implementing a degradation model. First, a numerical model was created and validated for the Aluminum 2024-T4 double shear 98 specimen. The Aluminum numerical model was only validated through the linear elastic region of the experimental data, which was shown in Figure 39. The Aluminum numerical model was adjusted for the composite specimen and the experimental results were compared to the numerical results. Abaqus keeps the units consistent, so when working with US Customary units make sure to stay consistent with the units, if using inches, stick to using inches. The displacement plots should be in the same units as one started with, and the stresses should be in pounds per square inch (psi). 6.1.1 Geometric Definitions The numerical model contained four parts. The two side plates, double shear specimen, and pin were modeled as deformable 3D solids. Both steel plates along with the double shear specimen were partitioned. The steel collars and center middle plate were neglected for simplicity. All the bolts, nuts and washers were also neglected in the model for simplicity reasons. 6.1.2 Material Creation, Section Assignments, & Meshing All the dimensions were defined in English units and the dimensions for each of the parts came from the fixture design. The fixture used in the numerical model was simplified. All the composite material properties were inputted in the elastic engineering constants. Table 17 showed the material properties, which were, applied to the Aluminum numerical model. A Steel solid homogeneous section and an Aluminum solid homogeneous section were created. 99 A composite layup section was applied to the composite double shear specimen and the element type was set to solid. Table 18 shows the material properties that were applied to the composite double shear specimen. In the composite layup section, the user is able to set the element stacking direction, the coordinate system, and the rotation axis. The user can also specify the laminate orientation and select the region for each ply within the model. In the Appendix, there is a tutorial of how the Abaqus composite double shear specimen was modeled. A single layer of unidirectional carbon fiber material is considered a transversely orthotropic material, where E2 is equal to E3 and G12 is equal to G13. E2 and E3 are both considered the matrix and E1 is considered the fiber. One thing to note was that the compressive modulus in the 1- direction (axial) was slightly lower than the tensile modulus, which was found in the Experimental section of the report. The Poisson\u2019s ratio in the 23-direction and the shear modulus in the 23- direction are usually very difficult to find experimentally. Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager was used to find some of the material properties that could not 100 be found experimentally. In the Appendix, one can find the tutorial on how to use Autodesk\u2019s Simulation Composite Analysis 2015 Material Manager. One can also find a step-by-step Abaqus tutorial on the composite double shear specimen. Parts of the step-by-step tutorial were found from D.S. Mane [29] . The parts were individually partitioned which made meshing them very simple. Once the partition was created, the user needed to use the Seed Edge command, then select whole part, and for method select \u201cby number\u201d. As indicated below in sizing control, the user is able to assign the number of elements from one to however many. The convergence plot was constructed using four different nodes per element. The element\u2019s relative thickness was set to 0.5 since there were only two elements that made up the thickness of the part. 101 6.1.3 Assembly, Interactions & Steps The whole assembly was modeled very similarly to the experiment. Each part was given a dependent instance and no tie constraints were used in the model. A contact step and a load step were added to the analysis. The contact step initiated the contact between the pin and the steel plates and also the pin and the specimen. The load step served to apply load to the analysis once full contact was established. The pin was not constrained to the specimen with a tie constraint because that implied a condition similar to being welded. So in contrast, a surface-to-surface interaction was established between the pin, the steel plates and the specimen. The sliding formulation selected was finite sliding. The pin was set as the master surface and the slave surface consisted of two surfaces. One was the surface in contact with the pin and the inner side of the specimen and the other was the surface in contact with the pin and the inner side of both steel plates. The slave adjustment was set to a value of 0.007 in. A contact property with a tangential behavior (the friction formulation was set to penalty and the friction coefficient was set to 0.46). In addition, a normal behavior contact property with the pressure-overclosure was set to \u201cHard\u201d Contact; constraint enforcement method was set to default, and allowed separation after contact. 6.1.4 Boundary Conditions & Loads The boundary conditions applied to the model needed to be assigned carefully. The top face of the specimen (opposite face with the hole) was fully fixed in the x, y and z directions. This was 102 similar to the clamped condition, which is applied by Instron\u2019s crossheads. The second boundary condition that was applied was on the outer pin surface and the inner hole surfaces of the steel plates and the bearing specimen. In the contact step, the pin, steel plates and specimen were not allowed to move in the x, y and z directions. The load step was modified to allow the side plates, pin and specimen to move in only the y-direction. The combined load of 600 lbs. was applied to both of the bottom faces of the steel plates. This was done by applying the load, in the load step, as a total force distribution pressure load. The loading condition used in the model was similar to the experimental loading condition, where a fraction of the force is applied at each time interval. Some elements in the model experienced plastic deformation only when the applied load was over 800 lbs. This meant that certain elements were in stress state beyond their linear elastic limit. The ultimate force was not predicted, by the numerical analysis, since that occurred in the non-linear region. 6.2 Numerical Results This section provides the explanation of the convergence plot and talks about the factors, which influenced the numerical results. In Chapter 7, the numerical results are explained in detail. 6.2.1 Convergence Plot For the numerical model, a partition was created on the face of the specimen. Taking time to draw a symmetrical and neat partition prevented the mesh from becoming unsymmetrical and 103 prevented unusual results. The partitioned double shear specimen is shown in Figure 49. In Figure 50, one can see a close up of the partitioned region around the hole. After a partition was created, the user was able to assign a specific amount of elements using the Seed Edge command. Here the user is able to set the total amount of nodes per element to any value. For the convergence plot, 2, 6, 8, and 10 nodes per element were chosen, and the final vertical deflection at the pin was compared. A convergence plot was created to see if adding more elements to the model actually improved accuracy. Knowing the optimum amount of elements for the least amount of time for the model to complete is very important in the design process. As one can see from Figure 51, as the total amount of nodes per element increased, the deflection did not change significantly. Using more than six elements per node did not significantly improve accuracy, but it did take longer to run. 6.2.2 Factors That Influenced the Numerical Results Increasing the total amount of elements through the thickness of the part, did not significantly affect the pin deflection results. Changing the axial modulus (from tensile to compressive) significantly affected the pin deflection results. The compressive axial modulus was imported into Abaqus rather than the tensile modulus, because the double shear test is mainly a compression type of loading. The fibers are in compression around the hole. When initially assuming a frictionless contact (when the frictional coefficient equaled zero) the specimen ended up colliding with one of the side plates. Changing the frictionless coefficient 104 from zero to 0.46 helped prevent the specimen from colliding with one of the side plates. 105 106 CHAPTER 7: COMPARISON BETWEEN EXPERIMENTAL & NUMERICAL DOUBLE SHEAR RESULTS The slope of the reaction force vs. pin displacement was compared between both the experiment data and the numerical model. First, the numerical Aluminum model was validated. Then the numerical composite model was validated. 7.1 Numerical Aluminum Model Comparison to Experimental Results Looking at Figure 59, the region highlighted in red was due to the compliance in the testing assembly. The bearing stress vs. bearing strain plot was then converted to a load (reaction force in the y-direction) vs. pin displacement plot. All of the specimens were plotted up until the linear region. Looking at Figure 60, of the five tested Aluminum double shear specimens, the numerical results only matched up with one. The four other Aluminum double shear specimens might have slipped with respect to the extensometer\u2019s knife-edge. One way to tell is by the lower load (reaction force in the y-direction) vs. pin displacement slopes. In Table 19, the total error when comparing the experimental slope to the numerical slope was 16%. Misalignment of the specimen might have caused this significant error to occur. 107 108 7.2 Composite Numerical Model Comparison to Experimental Results Figure 54 showed the load (reaction force in y-direction) vs. pin displacement response of the 0.05 in./min. composite double shear specimens that were cured to the recommended datasheet cure cycle. Three of the eight tested composite double shear specimens at 0.05 in./min. did not slip. The strain was corrected using the same method that was applied to the Aluminum double shear specimens. Of the eight carbon fiber specimens that were tested, only three of them closely matched up to the numerical results. The numerical model was loaded to 600 lbs., which was still within linear elastic limit of the material. The load (reaction force in y-direction) vs. pin displacement slopes between all the experimental specimens shown were compared to the numerical model. In Table 20, the average error between the numerical slope and the experimental slopes was about 7.1%. Alignment is a huge factor, which can affect experimental results quite significantly. There will always be error between the experimental and numerical results. The numerical 109 results are the idealized results and the experimental results have so many factors, which can influence their results. Errors from 7% to 16%, for both the aluminum double specimens and the composite double shear specimens, are actually quite reasonable because there is always error in the manufacturing process, displacement measuring equipment, load cell, specimen alignment exc. 111 CHAPTER 8: CONCLUSION The first important contribution of this study was to see how different loading rates affected the ultimate bearing strength of a composite material. One can see that at 0.05 in./min. and 0.1 in./min. (for both cure cycles) the composite double shear specimens carried more load compared to higher load rates of 1 in./min., 2 in./min. and 6 in./min.. All of the specimens failed in bearing and not in net-tension or shear-out. The second important contribution of this study was to see how the recommended datasheet cure cycle and the alternate cure cycle affected the ultimate bearing strength. The two different cure cycles behaved very similarly under the five different loading rates. The average ultimate bearing strength of the Aluminum double shear specimens was 118 ksi and for the composite double shear specimens it was 65 ksi. The experiment showed that carbon fiber material is significantly weaker, in a double shear tensile loading configuration, compared to Aluminum. Ductile materials, like Aluminum for example, handle the double shear tensile loading configuration a lot better than the carbon fiber material, which is brittle. Each carbon fiber sheet is relatively thin which is also very poor for carrying bearing stress. Usually what designers do is use inserts inside and around the hole if they need to improve the bearing strength of a composite joint. The inserts help redistribute the stress concentrations (which are caused by mechanical fasteners) and prevent the brittle material from cracking. The inserts are usually made from ductile materials, like fiberglass or Aluminum. 112 8.1 Recommendations The experiments were carried out using carbon fiber unidirectional pre-preg tape. Similar research can be done using various other materials like: kevlar, fiberglass, or even hemp. Similar testing can be done using a single shear joint configuration. Various carbon fiber types can be tested as well. MTM-28 material is a thicker type of unidirectional fiber, which would be very interesting to test. A high-speed video camera would be a more efficient way to monitor deflection since the extensometer's range was the limiting factor in the data capture. A more in depth case study can be conducted on different cure cycles of composite resins. The pre-load function in the Bluehill2 software can be utilized in order to try to eliminate some of the strain correction region. In addition, a more in-depth experimental analysis can be conducted on the knee point region of the composite (carbon fiber) double shear specimen. 113 REFERENCES 1. Airbus Versus Boeing-Composite Materials: The sky's the limit. http://www.lemauricien.com/article/airbus-versus-boeing-composite-materials-sky-slimit. 2. Lessard, L.B. (1995). Computer aided design for polymer-matrix composite structures. In S.V. Hoa (Eds.), Design of joints in composite structures. New York: Marcel Dekker. 3. Baker, A. (1997). Composites engineering handbook. In P.K. Mallick (Eds.), Joining and repair of aircraft composite structures. New York: Marcel Dekker. 4. Okutan, B. (2001). Stress and Failure Analysis of Laminated Composite Pinned Joints. Journal of Composite Materials, 19. 5. Chen, J.C., Lu, C.K., Chiu, C.H., & Chin, H. (1994). On the influence of weave structure on pin-loaded strength of orthogonal 3D composites. Composites, 25, No: 4, 251-262. 6. Quinn, W.J., & Matthews F.L. (1977, April). The effect of stacking sequence on the pin- bearing strength in glass fiber reinforced plastic. Journal of Composite Materials, 11, 139- 145. 7. Liu, D., Raju, B.B., & You, J. (1999). Thickness effects on pinned joints for composites. Journal of Composite Materials, 33, 2-21. 8. Stockdale, J.H., & Matthews, F.L. (1976, January). The effect of clamping pressure on bolt bearing loads in glass fiber-reinforced plastics. Composites, 34-39. 114 9. Kim, S.J., & Kim, J.H. (1995). Effects of geometries, clearances, and friction on the composite multi-pin joints. AIAA Journal, 34, No: 4, 862-864. 10. Hyer, M.W., & Klang, E.C. (1985). Contact stresses in pin-loaded orthotropic plates. Journal of Solids and Structures, 21, No: 9, 957-975. 11. Pierron, F., Cerisier, F., & Lermes, M.G. (2000). A numerical and experimental study of woven composite pin-joints. Journal of Composite Materials, 34, No: 12, 1028-1053. 12. Chang, Fu-Kuo, Scott, R.A., & Springer, G.S. (1982, November). Strength of mechanically fastened composite joints. Journal of Composite Materials, 16, 470-494. 13. Ger, G.S., Kawata, K., Itabashi, M.: Dynamic tensile strength of composite laminate joints fastened mechanically. Theor. Appl. Fract. Mech. 24(2), 147\u2013155 (1996). 14. Li, Q.M., Mines R.A.W., Birch R.S. (2000, September). Static and dynamic behavior of composite riveted joints in tension. 15. United States Naval Academy (USNA). (2003). Composite Orientation Code. http://www.usna.edu/Users/mecheng/pjoyce/composites/Short_Course_2003/7_PAX_Sh ort_Course_Laminate-Orientation-Code.pdf 16. Kretsis, G., & Matthews, F.L. (1985, April). The strength of bolted joints in glass fiber/epoxy laminates. Journal of Composite Materials, 16, 92-102. 17. Yeole, Amit. (2006, December). Experimental Investigation and Analysis for Bearing Strength Behavior of Composite Laminates. 115 18. Anonymous, \u201cStandard Test Method for Bearing Response of Polymer Matrix composite Laminates,\u201d ASTM Standards, Designation: 5961/5961M-05. 19. Anonymous, \u201cStandard test method for tensile properties of fiber-resin composites,\u201d ASTM Standards, Designation: 3039-76. 20. Anonymous, \u201cStandards. In-plane shear stress-strain response of unidirectional reinforced plastics,\u201d ASTM Standards, Designation: 3518-76. 21. Umeco, \u201cMTM 49 Series Pre-preg System \u2013 Unidirectional Material Properties.\u201d 22. Cytec, \u201cMTM 49-3 \u2013Unidirectional Material Properties.\u201d 23. Instron, \u201cInstron 8801 Servo-hydraulic Machine Photo.\u201d http://www.instron.us/en-us/ 24. Nettles, A.T., (1994, October) \u201cBasic Mechanics of Laminated Composite Plates.\u201d 25. ASM Aerospace Specification Metals Inc., \u201cDatasheet Mechanical Properties of Aluminum 2024-T4.\u201d 26. Anonymous, \u201cProject 1 Report\u201d ME-412. 27. Anonymous, \u201cStandard test method for ignition loss of cured reinforced resins,\u201d ASTM Standards, Designation: 2584-02. 28. Xiao, Yi. \u201cBearing strength and failure behavior of bolted composite joints (part II: modeling and simulation). 29. De, S. MANE 4240/CIVL 4240: Introduction to Finite Element. Abaqus Handout. 30. Semb, Evind. \u201cBehavior of Aluminum at Elevated Strain Rates and Temperatures.\u201d 116 APPENDICES A.1. Drawings for the Fixture Assembly 117 118 A.2. Tutorial on Bluehill2 Test File Setup Various settings were changed inside the BlueHill2 software. Below, I will show a couple of the parameters that were changed. Navigating through the menus is self-explanatory. In the Control submenu, the load rate was changed for each test. The quasi-static case was tested first at a load rate of 0.05 in./min. The second load rate, which was tested, was 0.1 in./min., the third was 1 in./min., the fourth was 2 in./min. and the fifth speed, which was tested, was 6 in./min. 119 The end of test criteria was changed to the ASTM specification. End of test 1 specifies the drop in the load of 30% the peak value and end of test 2 is specified as an extensometer displacement of 0.1 in. The extensometer shows up at Displacement (Strain 1) as a separate channel. 120 In the Control submenu, the sampling rate was changed from the default rate of 10 samples/sec to 3 samples/sec as required by ASTM D5961. This change showed a significant reduction of noise within the extensometer displacement readings. A value of 500 ms was adjusted for the time channel and the load sampling rate was left to default interval of 56 lbf. 121 Below in the Control submenu, the source of tensile strain was changed from the BlueHill2 default channel of \u201cTensile Strain\u201d to the \u201cStrain 1\u201d. The extensometer shows up as \u201cStrain 1\u201d. 122 Bluehill2 also has the option of calculating numerous parameters. In my experimental testing, I needed to calculate the ultimate bearing strength so I picked User Calculation. Then Bluehill2 gives you an option to define various variables like: D (diameter of hole), k (calculation factor for double shear k = 1), Pmax (maximum force carried by the specimen prior to failure), and t (defined as the thickness of the laminate). After all of your variables are defined, the equation designer tool 123 is used to create your equation of interest. In the Results submenu, the user is able to pick exactly which values he/she wants to output while in the test screen. The results are outputted as a column of values for each of the different test specimens. I wanted to output all of these parameters below while I was conducting my tests. 124 In the Graph submenu, the user is able to output two real-time changing graphs. For graph 1, I chose to output Instron crosshead displacement vs. load and for graph 2 I chose to output extensometer displacement vs. load. The X-Data was set to either Extension (for Instron crosshead displacement) or Displacement (Strain 1) (for extensometer displacement. The Y-Data was set to Load for both graph 1 and graph 2. 125 In the Raw Data submenu, Bluehill2 has a great function, which allows the user to export any given output of experimental data into a .csv file. This file can later be opened up with Excel and used to calculate various experimental stresses, strains and other parameters of interest. For my experimental testing, I was interested in outputting: time, crosshead displacement, extensometer 126 displacement, load and corrected position. The last bit of raw data, which needed to be outputted, is shown below. This set of data is saved onto the same .CSV file as the one specified in the previous screen. This set of data is located in its own set of two columns in the .CSV file. 127 A.3. Tutorial on Finding the Unknown Engineering Constants Autodesk created a very powerful tool, which can help the user figure out unknown engineering constants of a ply. For example from the experimental results, the user is able to experimentally determine E1, E2, G12 and \u03c512. Shown below are all the values, which the user inputs into the Autodesk Simulation Composite Analysis 2015 Material Manager. Make sure to label the 128 material a unique name and choose the correct units. The fiber type should be carbon intermediate for the MTM 49 since it is not the ultra-high fiber modulus. The volume fraction should be the one, which was found experimentally in the Results chapter, of 0.55. In Figure 67, in the first row of the Ultimate Lamina Strengths the user inputs the tensile strength in the 0\u00b0 and the 90\u00b0 directions. In the second row, the user inputs the compressive strength in the 0\u00b0 and 90\u00b0 directions and finally, in the last row, the user the user inputs the in-plane shear strengths. 129 In Figure 68, the user will input the known modulus of elasticity into the Lamina Elastic Constants section. The in-plane Poisson's ratio, which was assumed to be around 0.244, was used from a previous paper, which found the material property experimentally on the same MTM 49 Unidirectional material. The in-plane shear modulus was inputted from the experimental testing. 130 The key is to assume a value if you do not know what it is. After all the values have been inserted into the program go into the File, menu and then click optimize. It will ask you if you want to save the material properties somewhere and all you do is specify where you want to save the data. It will take a couple seconds to optimize the values accordingly. A.4. Tutorial on Outputting Force vs. Pin Deflection from Abaqus The pin deflection needed to be monitored for one node on the specimen. The area of interest is shaded in dark blue and the red dot signifies which node was monitored for its vertical deflection. In Figure 70, one can see the deflection in the y-direction, which occurs around the hole. This hole 131 is a localized compression zone. 132 Next what was needed was to have a force vs. time graph. The top most nodes on the specimen were fixed using the encastre boundary condition. The reaction force in the y-direction was captured for all the nodes that make up the top of the specimen. Once all the reactions at each nodes were captured, the whole region was summed up. Under create XY plot click ODB field output and then click continue. Under the Variables tab, find the Output variable box, and in the position menu, click Unique Nodal and then go into RF: Reaction Force and check the RF2 button. Since we are interested in the reaction force in the y-direction (2 direction). Next, click the Elements/Nodes tab and then pick the from viewport button and then click Edit Selection. Once all the fixed nodes are selected, as shown in Figure 72 below, click the Done button in the viewport. Lastly, go into Active Steps/Frames; make sure All steps are selected and set it to Frame. In the bottom of the window, make sure a green checkmark is applied to both the Contact and the Load steps. 133 Using the Create XY Data option in Abaqus, the user is able to go into Operate on XY data. In the Operators window, pick sum((A,A,...)), then under XY data, select all the Reaction Force nodes, which show up as _RF:RF2 and then click Add to Expression. Once all the nodes are inside the Sum operator, hit the Plot Expression button. This will output a force vs. time graph. 134 Once both the force vs. time graph and deflection vs. time graph are created, one needs to combine both graphs. In the Create XY Data, click Operate on XY Data and then press Continue. Under the operator tab, find combine(X,X) and then click it once. The combine operator requires two variables for the plot. For the first variable, click the deflection XY data, and for the second variable, click the Reaction Force 2 XY data. Make sure a comma separates both variables. Once done click the plot expression button and this should bring up a Force vs. Pin Deflection plot as shown in Figure 74. 135 A.5. Tutorial on Modeling the Double Shear Bearing Specimen Assembly Open up Abaqus 6.14. The numerical model should look like something like this. The complete assembly, the pin and one of the side plates modeled with Abaqus 6.14. 136 A.5.1. Model Creation Create a new model by right clicking the Models category. Name it DoubleShear. Then press Ok. 137 A.5.2. Part Creation Next, we have to create the parts for the model, after that, we partition each of the parts. Click on the + button to expand the options inside the DoubleShear model. Right click on Parts and press Create. A menu will appear like the one shown below. Name the part SteelPin. Keep the modeling space: 3D, the type: deformable, the base feature shape: Solid and for the base feature type: Extrusion. Click continue. 138 Click the Create Circle button. Using the dimension tool below set the radius to 0.125 in. Always be consistent with your units (I am using inches). 140 Next, we need to create the double shear specimen. Copy the step above and only change the name of the part to Specimen. Use the rectangle tool (to the right of the circle tool) and make a basic rectangle. 141 Using the dimension tool set the width of the part to 1.5 in. and the length of the part to 5.5 in. Create a Line down the middle of the part. Locate the center of hole 0.75 in. from the bottom edge of the specimen and make sure the hole is centered along the specimen\u2019s width. 142 Now, delete the centerline with the eraser tool, which is highlighted and then click on the centerline (which should highlight in red) and click done. Click the eraser tool to disable it. 143 In the bottom of the drawing window, it should read, \u201cSketch the section for the solid extrusion\u201d. Click the Done button. Set the depth to 0.1 in. Since the carbon fiber specimen\u2019s thickness was 0.1 in. Next, we need to create the side steel plate. Copy the step above and only change the name of the part to SidePlate. Use the rectangle tool (to the right of the circle tool), make a basic rectangle, and use the circle tool to create a hole in the plate. The side steel plate should be 2 in. by 4 in. and it should have a 0.141 in. radius hole. Which is located 1.0 in. from the top of the side plate. Lastly, remove the centerline and then set the depth to 0.25 in. Since the side steel plates had a thickness of 0.25 in. The three parts should look like this once they are completed. 144 A.5.3. Partition Creation A partition was created on the side plates and on the specimen. This made sure that when the mesh was generated all the elements stayed symmetrical. One major source of error in finite element analysis is due to elements not being symmetrical and the same size. One way to avoid this problem is to create your own mesh, which requires the user to partition the part based on what is of interest to him/her. Pick Tools, in the top drop down menu, and choose Partition. Click Face for the partition type and then click on the side plate face highlighted in orange. 145 Click Done and then it will ask to click a line vertical and to the right. Shown below, the highlighted edge is shown in pink, and the non-highlighted edges are shown in red. The part will switch from 3D to 2D and then here the user is able to create the partition desired. Create the partition below with these dimensions using the circle and line tools. It is important to keep the mesh coarse on parts which are not of main interest. 146 Apply the same method to the double shear specimen. The partition on this specimen was a lot more detailed than on the steel side plate. There are six circles, which are all equally spaced apart. The three outer radii were 0.5 in., 0.375 in., and 0.625 in. The three inner radii were 0.1875 in., 0.25 in., and 0.3125 in. A finer partition was created on the three inner radii where the circle was segmented into 64 equally spaced smaller sections. 147 The final partitioned parts should look like this. 148 A.5.4. Material Creation The material properties need to be created. Two materials were used in the analysis: steel and a unidirectional carbon fiber material. Under the Parts category, right click and click create. Name the material Steel. Go into the Mechanical option, then press elasticity, then elastic. Keep the type set to a default isotropic setting. Set the Young\u2019s Modulus to 34e6 and set the Poisson\u2019s ratio to 0.3. Follow the step right above, and create a new material and name it Uni. For the type, select 149 Engineering Constants. Include the material properties in the Table below (remember that msi is 106 psi)." + ] + }, + { + "image_filename": "designv8_17_0002268_el-02950845_document-Figure3.5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002268_el-02950845_document-Figure3.5-1.png", + "caption": "Figure 3.5: One classical periodic leaky-wave antenna based on a grounded dielectric slab covered with periodic metal strips", + "texts": [ + " One of the earliest periodic leaky-wave antenna models was introduced in [170], where an image dielectric line was used for the waveguide and an array of slots was cut into the ground plane on each side of the narrow dielectric central line. The most commonly used slow-wave guiding strucutre in this class is the rectangular dielectric slab with or without ground plane. Since the waves propagating in the guide are slow-wave, even if the guide is open, they are bounded within the guide. However, surface perturbations, such as grating of grooves [171, 172] or grating of metal strips [173], can be added to the guiding structure to make it leaky, thereby achieving radiation. Figure 3.5 shows a classical periodic leaky-wave antenna model in which metal strips are periodically placed along the longitudinal direction of a grounded dielectric slab. In general, it is necessary to well select the dimensions (e.g., thickness) of the dielectric slab such that only the dominant mode propagates in the guide to ensure high radiation efficiency. For slow-wave modes, leakage occurs only when discontinuities are presented on the waveguide. The added periodic arrays on the slow-wave guides can be effectively considered as discontinuities" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004004_f_version_1605861537-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004004_f_version_1605861537-Figure1-1.png", + "caption": "Figure 1. Multiplier Counterweight in (a) fully extended configuration (FE); (b) fully closed configuration (FC). (c) The test configuration R, where a standard 1000 kg ballast was mounted on the rear three-point hitch. Schematics for the calculation of tractor mass distribution are reported in Appendix A.", + "texts": [ + " To this end, a comparative analysis is conducted of the regression curves and the prediction bounds of tractive efficiency and net traction ratio, obtained from field tests involving a tractor with three different front/rear axle weight distributions. In addition, the economic impact that the adoption of a ballast position adjustment devices could have on agricultural activities is estimated by theoretically predicting productivity and fuel consumption during ploughing. 2. Materials and Methods A tractor ballasted with the MC was tested to compare its tractive performance in different device configurations (Figure 1). Ballast displacement was performed through a mechanical linkage actuated by the tractor hydraulic remotes. The mass of the bare device (i.e., with no ballast connected) was 500 kg and the ballast chosen to perform the tests had a mass of 500 kg; hence, the total mass of the system comprising the MC and the ballast was 1000 kg; that is, the mass of a standard front ballast designed for the tractor used in the tests. Agronomy 2020, 10, 1820 3 of 18Agrono y 2020, 10, x FOR PEER REVIEW 3 of 18 Tests were carried out with a New Holland T7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003371__IJATEE_2022_1_7.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003371__IJATEE_2022_1_7.pdf-Figure5-1.png", + "caption": "Figure 5 Drive shaft model", + "texts": [ + "4Drive shaft actuator model The rotating part in the hub consists of the blades, the axis that connects the blades to the overdrive system and the pitch angle servos, which rotate the blades around their longitudinal axes. The transmission system consists of low and high-speed shafts, gearboxes, and brakes. The drive shaft model that drives the gearbox and generator is not entirely rigid. The driveshaft is modelled as a spring with damping and a mass at each end. The dynamics of the drive shaft and the structural part of the simplified wind turbine have here been put together into a single system, depicted in Figure 5. It is noted that only the drive shaft on the rotor side is considered elastic and that the gear is lossless. As depicted in Figure 6, the dynamic of the shafttorque can be described by the following Equation 36 and 37. \u0307 (36) \u0307 \u0307 \u0307 (37) The drive train dynamics, which describes the system using \u0307 \u0308 can now be seen below (Equation 38). \u0307 \u222b (38) The same procedure was also used to find the \u0307 . The constants are defined as the drive train damping factor = 1/s) as well as the drive train spring factor = 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002091_rynica2018_10007.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002091_rynica2018_10007.pdf-Figure12-1.png", + "caption": "Fig. 12. Third mode shape \u2013 flexural horizontal, f3 = 0.92 Hz, \u03b5 = 0.00121m/m.", + "texts": [], + "surrounding_texts": [ + "Theoretical analyzes consisted in verification of the calculated vibration frequencies of the footbridge with values obtained on the basis of in situ tests. A variable in theoretical analyzes was the value of tension in main cables. Due to the lack of information about the values of pre-stress forces during the construction of the object, the authors made an attempt to estimate these values on the basis of dynamic tests. For this purpose, a threedimensional model of the footbridge was made in the Autodesk Simulation Multiphysics program. The model was built with use of beam, truss and shell elements. The created 3D model in accordance with [4] was classified as (e1+e2, p3). Figure 9 presents the FE model of the bridge. Below, in Table 2, the most important information on the structural elements of the footbridge is presented. The towers were set as fixed at the support without the possibility of translation nor rotation. On the basis of the inventory, the cables were defined as braided steel ropes, for which the elastic modulus E is 165 GPa. The value of the Young\u2019s modulus for girders and crossbars was 200 GPa. Two types of analyzes were carried out: static (Static Stress with Nonlinear Material Models) and modal (Natural Frequency with Nonlinear Material Models). In the created model, it was necessary to perform the division of main cables because of the presence of hangers used to suspend the deck to the main cables. Truss elements cannot be divided in analyzes in the linear range because the system becomes geometrically unstable. Such division and introduction of pre-stretch forces to cables is only possible in the case of non-linear analyzes. On the basis of the static analysis, the value of the deflection in the middle of the span was verified. The modal analysis was used to verify the received theoretical mode shapes and natural frequencies of the system. With such assumptions, eleven computational situations were analyzed and, on this basis, the evaluation of the pre-tension forces was made. Various strain values were applied to the cables according to the formula: \u03b5 = \u03c3 / E (1) where : \u03c3 \u2013 stress [MPa], E \u2013Young\u2019s modulus [GPa], \u03b5 \u2013 strain [m/m]. The values of stresses in the cables were selected in such a way that the span deflection in the middle caused by the tension forces and the dead weight resulted in positive values (upwards). Twenty mode shapes and natural frequencies of vibrations were obtained in the modal analysis. From the analyzes, it was found out that vertical flexible forms were obtained in the case of modes no. 1, 2, 6, 7, 12, 15 and 20, horizontal (including torsional) \u2013 no. 3, 10, 11, 13 and 14. Other modes show forms of cables and hangers vibration. Exemplary natural mode shapes of vibrations of the footbridge are shown in Figs 10-12, and the obtained results for vertical flexural and torsional mode shapes are summarized in Table 3. Fig.11. Second mode shape \u2013 flexural vertical, f2 = 0.71 Hz, \u03b5 = 0.00121m/m. The deflections in the middle of the span for each analytical case can be found in the last column in Table 3. In order to visualize the selection of the deflection value for which the most accurate natural frequency results were obtained, in Fig. 13 a collective graph of the strains-frequencies function is shown. Red circles represent the values obtained on the basis of the FFT analyzes of in situ accelerations. Analyzing the results obtained from in situ tests (measurements of accelerations and FFT analysis) and theoretical analyzes (Natural Frequency with Nonlinear Material Models) listed in Table 4 and Fig. 13, it was found that the highest accuracy of results was obtained for the initial strains in cables introduced with the values equal to 0.00121 m/m. Below, in Table 4, the values of relative errors for the compared values were calculated with use of the following formula: \u03b4i = (fit \u2013 fir) / fit (2) where: fit and fir \u2013 the values of the i-th natural frequency obtained on the basis of in situ tests and theoretical analysis. The values for FFT for each mode shapes were selected based on all analyzes carried out from all measured acceleration courses. Analyzing the values presented in Table 4, one can conclude that the obtained results are satisfactory. The average relative error is in the 10% range for the analyzed natural frequencies of the structure. It should be remembered that the authors did not have any technical documentation of the analyzed object, which was the reason for some assumptions, for example regarding the parameters of some elements of the footbridge, which were difficult to access and impossible to measure using the basic measuring instruments." + ] + }, + { + "image_filename": "designv8_17_0000319_gs_2024dubai_338.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000319_gs_2024dubai_338.pdf-Figure5-1.png", + "caption": "Figure 5. Ball and plate model (Cham Ham and Taufiq, 2015)", + "texts": [ + "13) is the transfer function for rotational displacement (\u03b8) as an output but if we want to take angular speed (\u2375) as an output for transfer function there will be some changes and the transfer function will become [Ogata, K. (1970)]. \ud835\udf14\ud835\udf14 \ud835\udc63\ud835\udc63 = \ud835\udc3e\ud835\udc3e\ud835\udc61\ud835\udc61 \ud835\udc60\ud835\udc602\ud835\udc3d\ud835\udc3d\ud835\udc3d\ud835\udc3d+\ud835\udc60\ud835\udc60\ud835\udc3d\ud835\udc3d\ud835\udc60\ud835\udc60+\ud835\udc3e\ud835\udc3e\ud835\udc4f\ud835\udc4f\ud835\udc3e\ud835\udc3e\ud835\udc61\ud835\udc61 Eq. 4.14 The main goal of the project is to keep the ball stable on a flat plate with predefined bounds. The platform's sensor will work to identify the position of the ball on the plate surface, and if the position changes, the sensor will send a signal to the controller to bring it back to the intended spot. The servo motor will operate in tandem with the controller to regulate the ball's position and maintain it inside the bounds. From the Figure 5, we can determine the transfer function for the moving ball on x direction considering the following: x is the distance covered in x direction. \u03b8 is the angle of the plate. \u03b1 is the angle of the motor. m is the mass . L is the length of the plate. \ud835\udc39\ud835\udc39\ud835\udc3e\ud835\udc3e = \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc60\ud835\udc60\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a(\ud835\udf03\ud835\udf03) Eq. 4.15 \ud835\udc39\ud835\udc39\ud835\udc41\ud835\udc41 = \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udf03\ud835\udf032 Eq. 4.16 \u00a9 IEOM Society International \ud835\udc39\ud835\udc39\ud835\udc4f\ud835\udc4f\ud835\udc3e\ud835\udc3e\ud835\udc4f\ud835\udc4f\ud835\udc4f\ud835\udc4f = \ud835\udc3d\ud835\udc3d \ud835\udc45\ud835\udc452 + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a Eq. 4.17 \ud835\udc39\ud835\udc39\ud835\udc41\ud835\udc41 = \ud835\udc39\ud835\udc39\ud835\udc4f\ud835\udc4f\ud835\udc3e\ud835\udc3e\ud835\udc4f\ud835\udc4f\ud835\udc4f\ud835\udc4f + \ud835\udc39\ud835\udc39\ud835\udc3e\ud835\udc3e Eq. 4.18 \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udf03\ud835\udf032 = \ud835\udc3d\ud835\udc3d \ud835\udc45\ud835\udc452 + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc60\ud835\udc60\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a(\ud835\udf03\ud835\udf03) Eq. 4.19 \ud835\udc3d\ud835\udc3d \ud835\udc45\ud835\udc452 + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a + \ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc60\ud835\udc60\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a(\ud835\udf03\ud835\udf03) \u2212\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udc5a\ud835\udf03\ud835\udf032 = 0 Eq. 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure18-1.png", + "caption": "Figure 18. Thermal field distribution of three cross-sections: (a) the water inlet side; (b) the middle cross-section; and (c) the water outlet side.", + "texts": [ + " In contrast, the water cooling mode used in the inner rotor can only take away the heat of the inner rotor by the axial cooling slots. When both the SM and the DRM are running at the low speed and rated load, the 3-D thermal field distribution is calculated under condition of only water cooling used in the casing, as shown in Figure 17. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the water inlet side, middle cross-section, and the water outlet side of the CS-PMSM are shown in Figure 18. The selected water inlet, middle and water outlet cross-sections are the same as those in Section 4.1. The highest temperature of different parts in the above three cross-sections is shown in Table 9. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 9. From the temperature distribution of each cross-section in Table 9, it can be seen that the stator temperature is much lower than the temperature of the inner rotor, indicating that the water cooling used in the casing has a good cooling effect on the stator, but it has a poor cooling effect on the inner rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001904_017_ms-8-11-2017.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001904_017_ms-8-11-2017.pdf-Figure6-1.png", + "caption": "Figure 6. Drilled hole for mounting the shock absorber on rear beam (1).", + "texts": [ + " On the rear axle, the geometry of the beam is different from the front and its shape is similar to a simple rectangular plate with curvature. The curved shape is to ensure the necessary preload when the vehicle is assembled and to permit the right vertical wheel travel same as front. Comparing with the front McPherson suspension (shock absorber mounted between the upright and the top mount on the chassis), the rear SLA suspension shock absorber is usually mounted on the lower suspension control arm. In Fig. 6, on the metal plate for mounting the upright, apart from the two coaxial hole (drilled to fix the upright), there is another small hole drilled on the vertical surface, for mounting the shock absorber, because drilling any more holes on the CFRP beam is not recommended for its reliability. The rear suspension is chosen to use a \u201cH arm\u201d topology3 to eliminate the need for another linkage for toe control. The side effect is that the toe variation during suspension stroke is limited. To recreate the performance of the beam suspension, the tool \u201cnon-linear beam\u201d in ADAMS/Car is used, which is shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003079_062_mft.2021.097.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003079_062_mft.2021.097.pdf-Figure3-1.png", + "caption": "Fig. 3 Barrier fittings", + "texts": [], + "surrounding_texts": [ + "indexed on: http://www.scopus.com 765\nstandard \u010cSN 69 0012 - Stable pressure vessels - operating requirements, as well as the needs of beer production technology in our own brewery are governed.\nWhen drawing up the operating instructions, it is also necessary to take into account the fact that the vessel is designed as a pressure vessel for a working pressure of 3 bar and this pressure must not be exceeded during operation. The container is not designed for the possibility of a sudden vacuum, for example, when changing the sanitation technology. The operating instructions must also be supplemented with a condition for entering the container: \"The container may only be entered after it has been completely ventilated and in suitable footwear which will not damage the inner polished surface.\" [20]\nBefore filling the container, the hose with the young beer supply must first be connected to the filling neck of the DN 65 container. Furthermore, the flap on the shut-off valve for air extraction during filling must be open. The young beer supply pipe must be secured against a sudden increase in pressure above 3 bar (max. Working overpressure of the lager tank). The pressure could increase after a longer filling time if the operator forgot to open the DN 20 flap at the barrier device. This situation is very unlikely from the point of view of traffic needs, but it is necessary to consider it.\nDuring the final fermentation of the beer, the increasing pressure is permanently released by a barrier device set by the operator. The usual barrier pressure does not exceed 0.9 bar.\nWhen emptying the container, the filter supply line hose must first be connected to the DN 65 container discharge port. Connect the compressed air supply hose (max. Overpressure 2.5 bar) to the damper flap. Open both flaps and empty the container by pushing it with air. [20]\nMaintenance consists of a visual inspection of the condition of the equipment, inspection of the seals and the function of the safety and measuring devices located on the pipeline according to the conditions specified for the vehicle.\nRegular maintenance of a clean surface in accordance with the principles arising from the hygienic requirements for equipment in the food industry.\nPart of the maintenance is also the implementation of inspections and tests according to \u010cSN 690012 Stable pressure vessels - operational requirements. [21]\nThe assembly of the lager tank armature is based on many years of experience in the technology of the production process, where the goal is the slow fermentation of residual carbohydrates at low temperatures of 0 \u00f7 2 \u00b0C and the saturation and fixation of CO2 in beer. Another of the more important processes in the lager tank is the clarification of beer and the acquisition of maturity and stabilization.\nThe fittings are designed for filling and draining,\nfor payment (adjustment) of the amount of overpressure in the tank needed for the correct course of fermentation and maturation of young beer in the lager cellar. It is also equipped with a sampling tap for sampling during the process and a shut-off valve. To control the temperature, a thermometer well is welded in the front bottom, for the possibility of fitting a thermometer.\nDuring the final fermentation of the beer, the increasing pressure is permanently released by a shutoff device set by the operator. The choice of compensating overpressure is governed by the conditions during final fermentation and is determined in the technology for beer production. Usually, the barrier pressure does not exceed 0.9 bar.\nThe barrier device is designed for a maximum barrier overpressure of 2.4 bar. During discharge, the contents of the tank are emptied by means of compressed air (by pushing), which is fed into the tank via the piping of the barrier valve. The supply air must not have a higher pressure than the permitted operating pressure in the tank - 2.5 bar. The compressed air supply line must have a separate fuse.\nThe fitting is a system of pipes equipped with a filling and at the same time draining neck DN 65 closed by a flap. Venting nozzle DN 20 with a shut-off pipe, on which a shut-off device with a manometer and a shut-off flap is located. At the front of the tank is a sampling tap DN 8.\nThe valve is mounted on an established lager tank according to the supplier's installation documentation. It is attached to the tanks via a screw connection and is held by means of pipe sleeves anchored to the front bottom of the tank. Upon agreement with the customer, it is possible to complete the entire fitting at the manufacturer of the lager tank [21].\nThe choice of a suitable material was based on many years of experience of a company that manufactures appliances and other machinery for breweries and the food industry.\nThe material must meet at least the following basic", + "766 indexed on: http://www.scopus.com\nconditions: sufficient strength, corrosion resistance, have sufficient notched toughness and ductility, guaranteed weldability and comply with the Decree of the Ministry of Health No. 38/2001 Coll. Annex No.8.\nFrom the above basic criteria, the austenitic stainless steel X5CrNi 18-10 (food steel) was recommended, which is alloyed (Cr 17 - 19.5%, Ni 8 - 10.5, C <0.07%). The steel is marked according to \u010cSN EN 10088-1 1.4301. The Czech equivalent of this steel, according to the old material designation, corresponds to steel 17 240.4 with a chemical composition and with basic physical properties according to the original standard \u010cSN 417240. A similar foreign steel is known under the designation AISI 304.\nAccording to Government Decree No. 93/2015, Annex No. 1, item 7.5, steels for pressure equipment must meet the condition of a minimum value of ductility, which must be greater than 14%, and its impact work during the bending impact test, measured on a bar with the notch must be greater than 27J at room temperature. This steel meets X5CrNi 18-10.\nThe determination of the conformity assessment procedure (determination of the module) is carried out in accordance with \u00a74 NV No. 93. \u00a74, paragraph 1 letter c) applies to the specified category III.\nAccording to \u00a74 NV No. 93 for category III, the manufacturer can choose one of the five possible conformity assessment procedures (module). If none of the above modules complies with the manufacturer, it is possible to carry out an overall verification of the unit with module G. Module G applies to the strictest category IV. As this is a piece of production of the container, I choose the conformity assessment procedure \"G\" - verification of the whole according to point\n11 of Annex No. 3 to this Regulation. The basic principle in the assessment according to module G is that the manufacturer ensures and declares that the pressure equipment for which it has been issued by an authorized person complies with the provisions of this Regulation that apply to it. Before issuing a certificate, the manufacturer must submit to the authorized person the technical documentation to the following minimum extent:\n\u00b7 a general description of the pressure equip-\nment\n\u00b7 assembly drawing, including detailed dra-\nwings of individual parts\n\u00b7 strength calculation\n\u00b7 scope of performed NDT tests on welded\njoints of the vessel\n\u00b7 welding procedures\n\u00b7 where appropriate, descriptions and explana-\ntions necessary for the understanding of the\nfunction of the pressure equipment.\nSimultaneously with these documents, the manufacturer prepares the accompanying technical documentation (operating instructions, etc.) and prepares the risk analysis.\nBased on the assessment of the submitted documentation, the authorized person issues an EC certificate and the manufacturer is obliged to place the CE mark on the product on the basis of the issued certificate. Only then can the manufacturer place the device on the market.\nThe basic requirements for the construction of pressure vessels are given in Annex No. 1 to NV 93. The main requirements include the correct design of the entire equipment with emphasis on the overall safety of the vessel for the entire considered service life. These requirements include:\n\u00b7 sufficient strength and stability of the vessel,\nwhich must be demonstrated by a correctly\nchosen calculation method\n\u00b7 taking into account the internal overpressure,\nor determining the reaction forces and mo-\nments caused by the supports and fixing of\nthe pipe parts on the vessel\n\u00b7 taking into account corrosion or erosion, etc.\nIn order to demonstrate sufficient strength of the container, the base material must be suitably selected with regard to its mechanical properties - sufficient yield strength at design temperature, tensile strength and, if required, sufficient notched toughness of the material, good weldability [21].", + "indexed on: http://www.scopus.com 767\nMeasurement results and calculation\nFor the strength calculation of the lager tank, it is first necessary to determine the basic geometric dimensions of the vessel (length of the cylindrical part) with these input dimensions, which are entered by the\ncompany Sekos \u00dast\u00ed nad Labem s.r.o. (Fig. 4) For geometric design of the container the basic entered parameters such as the total volume and the outer diameter of the tank, it is necessary to calculate the volumes of individual components and the length of the cylindrical vessel.\nTo the bottom volume calculation selected deep arched bottom according to DIN 28011 type A.\nTo calculate the basic dimensions, authors choose a bottom thickness of 6 mm, height of the cylindrical\nedge of the bottom h1 3.5\u2219s.\n= 0.1 \u22c5 ( \u2212 2 ) (1)\n! = 0.1 \u22c5 (2 \u2212 2 \u22c5 0.006) ! = 0.786 \" = 786 \"\nwhere da \u2013 outer diameter of the bottom, s - thickness of the bottom\nCalculation of the volume of a cylindrical vessel\n!#\u00e1$%& = !%&$' \u2212 2 \u22c5 ! (2)\n!#\u00e1$%& = 16.65 \u2212 2 \u22c5 0.786 !#\u00e1$%& = 15.07 \" = 15070 \"\nCalculation of the length of the cylindrical vessel\n*#\u00e1$%& = +\u22c5,-\u00e1/34 9\u22c5:;< (3) *#\u00e1$%& = +\u22c5 >.?@ 9\u22c5B< *#\u00e1$%& = 4.8 \"" + ] + }, + { + "image_filename": "designv8_17_0001834_g_vol8_928-IT028.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001834_g_vol8_928-IT028.pdf-Figure1-1.png", + "caption": "Fig. 1. (a)Phase portrait of sliding mode control, (b) Sliding surface, reaching mode and high frequency switching.", + "texts": [ + " Although SMC which is founded on the VSC was unknown until 1977, when Utkin made a study, then, it has been started to use for linear and nonlinear applications in the international communities [11]. SMC, which has low sensitivity against to parametric changes of the system and disturbing effects, is an effective method to control complex and dynamic systems. Moreover it can operate under uncertain conditions which commonly occur in the modern technology [12]. SMC consists of two parts called as reaching mode and sliding mode and its phase portrait is shown like Fig. 1(a). The first of all, a surface is designed for system to be controlled. As shown Fig. 1(b), control signal switched high frequency slide state trajectories of the system to this surface and this surface is called sliding surface. The movement along this surface represents output action of the system. SMC method tries to pull states of system from sliding surface to origin. Movement in sliding surface signify sliding mode and is stage from starting point to sliding mode called as reaching mode. States of system are insensitive to parametric changes and disturbing effects. The aim of the SMC is that output of system is to tracking to desired reference and to produce signal \u2018u\u2019 which makes minimum to tracking error" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003944_6514899_10305151.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003944_6514899_10305151.pdf-Figure10-1.png", + "caption": "FIGURE 10. Back view of the 1\u00d72 ME-dipole antenna With metasurface.", + "texts": [ + " 9. Also, Fig. 9 is simulated with the metasurface, consisting of 2\u00d75 resonator unit cells to reduce the coupling within 52- 62 GHz, as explained in section II. The metasurface is 1 mm (0.2\u03bb) above the surface of the antenna. MS spacer is used as an airgap between the antenna and the metasurface for mechanical support as shown in Fig. 9. Rogers RT 5880, with a thickness of 1 mm, is used as a spacer and mechanical support to create an air gap between the antenna and the metasurface, as shown in Fig. 10. Fig. 11 shows the simulated S-parameters of the proposed antenna with and without the metasurface (MS). It should be noted that the 2\u00d75 unit cells are added on the top and bottom of the superstrate. It can be seen that the resonance frequency band (52-64 GHz) of the antenna is not affected by adding the metasurface. However, the mutual coupling between the antenna elements has been significantly reduced by a maximum of 53 dB within the bandwidth of interest. This coupling reduction is obviously attributed to the unique resonator unit cell, carefully designed to exhibit negative permittivity in the bandwidth of interest" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004360_rticle_125987571.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004360_rticle_125987571.pdf-Figure3-1.png", + "caption": "Fig. 3. Vertical movement of innovated equipment.", + "texts": [ + " 2) was based on the assumption of using a Hybrid III test dummy and an H2015 H-point test dummy to load the car seat (Fig. 7). Therefore, we had to increase the total height of the device to 2400 mm. We added a second frame and placed a vertical motor with a platform between two frames. Therefore, a variable platform was created, in which it is possible to change the required working height according to the need the type of loading. For vertical drive, it was elected new linear actuator type GSX60. The technical characteristics are given in the technical description (Fig. 3). Now the vertical movement can be realized in the interval up to 180 mm with a total load up to 150 kg, i.e. the whole car seat with accessories and plus the load of about 100 kg. The concept of horizontal movement is based on the movement of two horizontal plates, which are connected via linear guides. A new linear moving was chosen for the drive actuator type GSX40. The lower horizontal plate is connected to the vertical actuator, the upper plate is used to fix the tested seat. The design allows the entire horizontal module to rotate, i" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002748_e_download_7184_5916-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002748_e_download_7184_5916-Figure4-1.png", + "caption": "Fig. 4 \u2013 Hexagonal and Octagonal Connections", + "texts": [ + " 3 \u2013 Schematic diagram of three-direction grid type prestressed mega-grid structures The geometric model of three-direction grid prestressed reticulated mega-structure is essentially a flat plate-type space structure, so the establishment of the geometric model of the hexagonal mid-joint and the octagonal side joint is the key to generate the structural model. The above-mentioned \"hexagon\" refers to that projection of the inverted quadrangular pyramid truss in the interior of the structure on the intersect connecting plane, and the \"octagon\" refers to the projection of the inverted quadrangular pyramid truss on four out edges on the intersecting connecting plane. The specific connection mode is shown in Figure 4, wherein (A) is the connection mode of the internal inverted quadrangular pyramid;(B) is an inverted quadrangular pyramid connection with four outer edges. As shown in the figure above, both the internal and external connection modes of the cross connection part are hollowed out, which will cause uneven force on the bar and adversely affect the overall stiffness. And therefore that diagonal line of the upper polygons of the hollow structure need to be mutually crossed and connected; As the octagonal protruding structure part on four sides is easy to be stressed and concentrated, the part protruding out of the outer edge of the quadrangular pyramid is cut off" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001295_0005208_10124947.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001295_0005208_10124947.pdf-Figure6-1.png", + "caption": "FIGURE 6. IPM performance results in ansys maxwell 2d according to Table 7.", + "texts": [ + " The images of the motor geometry generated in the tests performed using the data in Table 6 and the design parameters of these motor are given in Fig. 5 and Table 7. For the motor design parameters taken from Table 7, the obtained results for the 3 motor models created in Ansys RMXprt are given in Table 8. Similarly, the percentage error results obtained for the test data applied to the input of the neural networks in Table 6 are given in Table 8. The results of the 2D finite element model (2D Ansys Maxwell) for the IPM models created using the Ansys RMXprt model are given in Fig. 6. Input and Output powers and RMS values for these analyzes are given for each IPM model in Fig. 6. The efficiency of the IPM models is calculated by RMS values. In addition, the results regarding the flux densities on the rotor, stator and slot geometries are given in Fig. 6. As it can be understood from Fig. 6, the obtained results with the empirical equations in Ansys RMXprt and the obtained results from the 2D Ansys Maxwell models are converge each other in terms of both efficiency and flux densities and confirmation of the model. As a result of experiment and testing processes, the proposed model shows the satisfied results to generate the initial geometry image and extract the design parameters from image geometry of IPM motor. Furthermore, the generated geometry and extracted motor design parameters are met the desired performance requirements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002658_2452-020-03846-0.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002658_2452-020-03846-0.pdf-Figure3-1.png", + "caption": "Fig. 3 Geometric parameters defining the shape", + "texts": [ + " To create over-constrained mechanisms, we use tubular rigidly foldable origami symmetrically generated from a polygonal cross section with parallel extrusion [3, 9]. The geometry of the system is based on part of a large torus which, by its assembly, can be used to create various forms/arrangements e.g. a covered corridor (Fig.\u00a02). Five steps are needed to construct a rigid-foldable and flatfoldable origami torus. In particular, the second and third steps guarantee that these characteristics can be achieved (Fig.\u00a03). 1. We construct the torus defined by radiuses of smaller and bigger circles, defined as r and R , respectively. We set XYZ axes such that the bigger circle lies on XY plane, the smaller circle lies on XZ plane, and the origin lies on the center of torus. 2. Construct a section polyline P on the small circle. A parallelogram strip is formed by extruding P along Vol:.(1234567890) direction on XYplane. The angle between and \u2212X axis is denoted by . The choice of is important for the stiffness of the structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001753_No.67-5_03.02.20.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001753_No.67-5_03.02.20.pdf-Figure1-1.png", + "caption": "Fig. 1. The overhead two dimensional crane control system", + "texts": [ + " The cart is subject to a friction force cdd \u0307, the tension of the rope Tx, and an external force F\u0303 that is controlled. There is a winch (of radius b and moment of inertia J ) on the cart, that changes the length of the rope r. It is influenced by a friction crr \u0307 , tension b2T, and external torque C\u0303 . We neglect the dynamics of the winch itself, but we take into account the torque that the movement of the winch produces, that serves as a second control in the system. The position of the pendulum is expressed with respect to the global frame (X, Z) via coordinates (x, z). See Fig. 1. 1. Introduction Several authors considered crane systems, both two- and threedimensional, and investigated their structural properties [2], flatness [5], motion planning and tracking [1, 16]. Independently of the dimension, these systems share common properties that can be further generalized. In this article, we propose a class of m-crane control systems constituting a multidimensional generalization of the above-mentioned systems. We describe this class, investigate its properties and prove that m-crane systems are feedback equivalent to a normal form, more precisely, to the second order chained form with drift", + " \u03c6id ( j) (t0),\u2007for\u20070 \u2219 j \u2219 4, (30) and the remaining ai5, \u2026, ai9 are given by the system of linear equation \u03c6id (k)(tf) = 1 (tf \u00a1 t0)k l = k 9 \u2211 l! (l \u00a1 k)! ail,\u2007for\u20070 \u2219 k \u2219 4. (31) Notice that we solve equations (28\u201231) independently for each i = 1, \u2026, m. To summarize, there are 10m coefficients aik in total, 5m to be calculated from (30) and the remaining 5m can be calculated by solving m linear systems given by (31). 6. Simulation results The simulation model corresponds to the small laboratory crane (schematic drawing is presented in Fig. 1), that is characterized by parameters given in Table 1. Bull. Pol. Ac.: Tech. 67(5) 2019 A control problem considered in the simulations concerns trajectory tracking of the load for the 2-crane case described by (1) or, equivalently, by (11), where the position of the load is given by (x, z) = (x1, x2). By Proposition 4, (\u03c61, \u03c6 2) = (x, z) are the flat outputs of the 2-crane system (11). In order to achieve the trajectory tracking problem, we combine cascade controller (24, 26) and trajectory generator (28\u201231)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003454_6_61_4_61_4_501__pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003454_6_61_4_61_4_501__pdf-Figure6-1.png", + "caption": "Fig. 6 Face gear hobbing", + "texts": [], + "surrounding_texts": [ + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u5893\u3064\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n( 11 )\n\u305f \u3060 \u3057,Z'\u306f \u5207 \u308a\u4e0b \u3052 \u3092 \u3069 \u3053 \u307e \u3067 \u8a31 \u3059 \u304b \u306b \u3088 \u3063\u3066 \u6c7a \u307e \u308b\n\u6b6f \u6570 \u3067,\u56f33\u306e \u5834 \u5408 \u3067 \u306fZ'=6\uff5e8\u306b \u3059 \u308c \u3070 \u3088 \u3044.\n(c) \u30aa \u30d5 \u30bb \u30c3 \u30c8\u4e0b \u3067 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84\n\u56f34\u306b \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3057\u3066 \u306e \u30d4 \u30c3\u30c1 \u5186 \u76f4 \u5f84 \u306e \u5909 \u5316 \u306e\n\u69d8 \u5b50 \u3092 \u793a \u3059.\u56f3 \u4e2d \u306e \u5404 \u8a18 \u53f7 \u306f \u305d \u308c \u305e \u308c\na: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf Z: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e\u6b6f \u6570 \u03c9: \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u89d2 \u901f \u5ea6\n\u03b2: \u30aa \u30d5 \u30bb \u30c3 \u30c8\u89d2 R0: \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84 Ra: \u30aa \u30d5\u30bb \u30c3 \u30c8\u3067 \u5909 \u5316 \u3057\u305f \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84\nV0: \u534a \u5f84R0\u4e0a \u306e \u901f \u5ea6 Va: \u534a\u5f84Ra\u4e0a \u306e \u901f \u5ea6\n\u3092\u8868 \u3059.\u3053 \u308c \u3088 \u308a,\u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306b\u5bfe \u3057\u3066 \u5c0f \u6b6f \u8eca \u304c \u30aa \u30f3\u30bb \u30f3 \u30bf(P\u306e \u4f4d \u7f6e)\u306b \u304a \u3044 \u3066 \u306f,\u5c0f \u6b6f \u8eca \u306e \u30d4 \u30c3\u30c1 \u5186\u534a \u5f84 \u306e \u6bd4 \u306f\u6b6f \u6570 \u306e \u6bd4(\u89d2 \u901f \u5ea6 \u306e \u6bd4)\u306b \u7b49 \u3057 \u304f\u306a \u308b \u304c,\u30aa \u30d5 \u30bb \u30c3 \u30c8 (\nP'\u306e \u4f4d \u7f6e)\u4e0b \u3067 \u306f \u4e21 \u534a \u5f84 \u306e \u6bd4 \u306f,\u306f \u3059 \u3070 \u89d2 \u306e \u5f71 \u97ff \u3092 \u53d7\n\u3051\u3066 \u5fc5 \u305a \u3057\u3082\u6b6f \u6570 \u306e \u9006 \u6bd4 \u306b\u7b49 \u3057 \u304f\u306f \u306a \u3089 \u306a \u3044.\u3059 \u306a \u308f \u3061 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cfa\u306b \u5bfe \u3059 \u308b \u30d4 \u30c3\u30c1 \u5186 \u534a \u5f84Ra \u306f\n( 12 )\n\u3068\u306a \u308b.\u307e \u305f,\u5f0f(12)\u3067 \u03b2\u306e \u4ee3 \u308f \u308a\u306b \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf a\n\u3092\u7528 \u3044\u3066 \u8868 \u3059 \u3068\n( 13 )\n\u3068\u306a \u308b.\u305f \u3060 \u3057,\u30aa \u30f3\u30bb \u30f3 \u30bf\u3067 \u306fa=0\u3067 \u3042 \u308b.\u3088 \u3063\u3066 \u30d4 \u30c3\u30c1 \u5186\u76f4 \u5f84Dp \u306f\n( 14 )\n\u3067\u8868 \u305b \u308b.\u4ee5 \u4e0a \u304c \u8a2d \u8a08 \u6cd5 \u3067 \u3042 \u308b.\u6b21 \u306b \u5177 \u4f53 \u7684 \u8a08 \u7b97 \u6cd5 \u306f, \u307e\n\u305a \u5404 \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u306b\u5bfe \u3057\u3066 \u5f0f(13)\u3088 \u308aDp\u3092 \u6c42 \u3081 \u308b. \u305d \u306eDp\u306b \u5bfe \u3057\u5f0f(9),(10)\u3088 \u308aDo,Di\u3092 \u7b97 \u51fa \u3059 \u308b\n\u56f35\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e\u6b6f \u6570 \u3068 \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u3067 \u5927 \u7aef,\u5c0f \u7aef \u76f4 \u5f84 \u304c \u3069\u306e \u3088 \u3046 \u306b\u5909 \u5316 \u3059 \u308b \u304b \u306e \u8a08 \u7b97\u7d50 \u679c \u3092\u793a \u3059.\u3053 \u308c \u3088 \u308a\n\u6b6f \u6570 \u304c \u5897 \u3059 \u3068,\u4e21 \u76f4\u5f84 \u304c \u5927 \u304d \u304f \u306a \u308b \u3068\u540c \u6642 \u306b\u4e21 \u76f4 \u5f84 \u306e \u5dee, \u3064 \u307e \u308a\u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b.\u307e \u305f,\u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u304c \u5927 \u304d \u3044 \u307b\n\u3069\u5927 \u7aef,\u5c0f \u7aef \u76f4\u5f84 \u53ca \u3073 \u6b6f \u5e45 \u304c \u5927 \u304d \u304f\u306a \u308b \u3053 \u3068\u304c \u308f \u304b \u308b.\u3053 \u308c \u306f \u30aa \u30d5\u30bb \u30c3 \u30c8\u91cf \u306e \u5897 \u52a0 \u306b\u4f34 \u3044 \u30d4 \u30c3\u30c1 \u5186 \u76f4\u5f84 \u304c \u5927 \u304d \u304f\u306a \u308b \u304b \u3089\u3067 \u3042 \u308b.\u3057 \u304b \u3057\u306a \u304c \u3089\u6b6f \u6570 \u304c40\u679a,\u30aa \u30d5 \u30bb \u30c3 \u30c8 10\n\u30fbm\u306b \u5bfe \u3057\u6b6f \u5e45 \u306f5mm\u7a0b \u5ea6 \u3067 \u3042 \u308a,\u540c \u3058 \u304f\u6b6f \u6570140 \u679a\n\u3067 \u308210mm\u7a0b \u5ea6 \u3068\u6b6f \u5e45 \u304c \u72ed \u3044.\u3053 \u306e \u3053 \u3068\u306f \u5148 \u306b\u8ff0 \u3079 \u305f \u3088\n\u3046\u306b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e1\u3064 \u306e \u6b20 \u70b9 \u3067 \u3082\u3042 \u308b \u308f \u3051 \u3067 \u3042 \u308b.\u3055 \u3089\npitch plane\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 503", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a8\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n\u306b\u304b \u307f \u5408 \u3044 \u5727 \u529b \u89d2 \u306f \u5c0f \u7aef \u304b \u3089 \u5927\u7aef \u306b \u5411 \u304b \u3063\u3066 \u5927 \u304d \u304f\u306a \u308b5) \u305f\u3081,\u6709 \u52b9 \u306a\u52d5 \u529b \u4f1d \u9054 \u4e0a,\u4eee \u306b \u6b6f \u5e45 \u3092\u6e1b \u5c11 \u3055\u305b \u308b \u306b \u306f, \u5927\n\u7aef \u304b \u3089\u6e1b \u3089\u3059 \u3079 \u304d \u3067 \u3042 \u308b.\n3. \u901a \u5e38 \u306e \u30dc \u30d6 \u76e4 \u306b \u3088 \u308b \u6b6f \u5207 \u308a \u3068\u304b \u307f \u5408 \u3044 \u8a66 \u9a13\n\u4e0a\u8a18 \u306e \u8a08 \u7b97\u7d50 \u679c \u306b \u57fa \u3065 \u3044 \u3066 \u901a \u5e38 \u306e \u30dc \u30d6 \u76e4(HAMAI,H- 102 )\n\u3068\u5e02 \u8ca9 \u30db \u30d6(\u30e2 \u30b8 \u30e5 \u30fc \u30eb1,\u5de5 \u5177 \u5727 \u529b \u89d220\u309c,\u306d \u3058\u308c \u89d21\u309c 57',\n\u5207\u308c \u6b6f \u5217 \u65706)\u3092 \u7528 \u3044 \u3066 \u6b6f \u5207 \u308a\u3092 \u884c \u3063\u305f.\u5f53 \u521d,\u30dc \u30d6 \u3067 \u6b6f \u5207 \u308a \u3057\u305f \u5834 \u5408,\u5185 \u6b6f \u6b6f \u8eca \u306e \u30c8\u30ed \u30b3 \u30a4 \u30c9\u5e72 \u6e09 \u306b\u4f3c \u305f \u3053 \u3068\u304c \u30dc \u30d6 \u3068\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u3068 \u306e \u9593 \u306b\u8d77 \u3053 \u308a,\u6b6f \u5f62 \u306e \u5927 \u304d \u306a \u304f\u305a \u308c \u304c \u4e88\n\u60f3 \u3055 \u308c \u305f \u306e \u3067,\u30dc \u30d6 \u306e \u5207 \u308c \u6b6f \u304c3\u5217(\u5e458mm)\u306b \u306a \u308b \u3088 \u3046 \u306b \u5207 \u65ad \u3057\u305f \u3082\u306e \u3092\u7528 \u3044 \u3066 \u8a66 \u9a13 \u7684 \u306b \u6b6f \u5207 \u308a\u3092 \u884c \u3063\u305f(\u30db \u30d6 \u5e45 \u306b\u3088\n\u308b\u6b6f \u5e45 \u7b49 \u3078 \u306e \u5f71 \u97ff \u306f \u5225 \u5831 \u3067 \u8a73 \u7d30 \u306b \u8ff0 \u3079 \u308b).\n\u56f36\u306b \u5177 \u4f53 \u7684 \u6b6f \u5207 \u308a\u6cd5 \u3068\u6b6f \u5207 \u308a\u5f8c \u306e \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u3092 \u793a \u3059.\n\u6b6f \u5207 \u308a\u306f \u3044 \u308f \u3086 \u308b \u30b3 \u30f3\u30d9 \u30f3 \u30b7 \u30e7\u30ca \u30eb \u6cd5 \u3067 \u3042 \u308a,\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u7d20 \u6750 \u306b \u5bfe \u3057 \u3066,(1)\u30db \u30d6 \u306e \u4e2d \u5fc3 \u3092 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u4e2d\u5fc3 \u304b \u3089\u6a2a \u306b\u79fb \u52d5 \u3055\u305b \u6240 \u5b9a \u306e \u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u3092 \u4e0e \u3048 \u308b.(2)\u30dc \u30d6 \u3092 \u3042 \u3089\u304b\n\u3058\u3081 \u5168\u6b6f \u305f \u3051 \u5206 \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u8ef8 \u65b9\u5411 \u306b\u9001 \u308a,\u305d \u3057\u3066(3) \u4e0a \u65b9 \u5411 \u306b\u9001 \u3063\u3066 \u7d42 \u4e86\u3059 \u308b.\u88fd \u4f5c \u3055\u308c \u305f \u30d5 \u30a7\u30fc \u30b9\u30ae \u30a2\u306e \u6b6f \u5f62 \u4f8b\n\u3092 \u56f37\u306b \u793a\u3059.\u5168 \u4f53 \u7684 \u306b\u6b6f \u306e \u4e21 \u7aef \u306f \u5927 \u7aef \u76f4 \u5f84 \u3068\u5c0f \u7aef \u76f4\u5f84 \u554f\n\u306b \u3046 \u307e \u304f\u914d \u7f6e \u3055\u308c \u3066\u304a \u308a,\u8fd1 \u4f3c \u5f0f \u306e \u59a5 \u5f53\u4ef6 \u304c \u8a00\u3048 \u308b.\n\u6b21 \u306b\u88fd \u4f5c \u3057\u305f \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u6b6f \u9762 \u306b \u30b9 \u30b9 \u3092\u4ed8 \u3051,\u5e73 \u6b6f \u8eca\n(Z=20)\u3068 \u304b \u307f \u5408 \u3044\u8a66 \u9a13 \u3092 \u884c \u3044 \u30b9 \u30b9\u306e \u5265 \u304c \u308c\u5177 \u5408\u304b \u3089\n\u6b6f \u5f53 \u305f \u308a\u72b6 \u614b \u3092\u89b3 \u5bdf \u3057\u305f.\u56f38\u306b,\u56f37\u3067 \u793a \u3057 \u305f \u30d5\u30a7\u30fc \u30b9\n504 \u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61. No. 4. 1995", + "\u8429\u539f:\u4eee \u60f3\u8ee2\u4f4d\u6b6f\u8eca\u7406\u8ad6\u306b\u57fa\u3065\u304f\u5b9f\u7528\u30d5\u30a7\u30fc\u30b9\u30ae\u30e4\u306e\u5275\u6210\u6b6f\u5207\u308a\n\u30ae \u30e4 \u306b \u3064 \u3044 \u3066 \u306e \u307f \u7d50 \u679c \u3092\u793a \u3059.\u304b \u307f \u5408 \u3044 \u90e8 \u5206 \u306f,\u5168 \u4f53 \u306b \u5927\n\u7aef,\u5c0f \u7aef,\u30d4 \u30c3\u30c1 \u5186 \u4ed8\u8fd1 \u306b \u9650 \u3089\u308c \u3066 \u304a \u308a,\u6b6f \u5f53 \u305f \u308a\u91cf \u3082\u5c11 \u306a \u304b \u3063\u305f.\u3053 \u308c \u306f \u8fd1 \u4f3c \u5f0f \u306b \u57fa \u3065 \u3044 \u3066 \u5275 \u6210 \u6b6f \u5207 \u308a \u3057\u305f \u7d50 \u679c \u3067 \u306f \u6700 \u3082 \u81ea\u7136 \u306a \u72b6 \u614b \u3067 \u3042 \u308a,\u3059 \u308a\u3042 \u308f \u305b \u3092 \u5341 \u5206 \u306b \u884c \u3048 \u3070 \u826f\u597d\n\u306a \u304b \u307f \u5408 \u3044 \u304c \u5f97 \u3089\u308c \u308b \u3053 \u3068\u3092 \u793a \u5506 \u3057\u3066 \u3044 \u308b.\n4. \u7d50 \u8ad6\n\u672c \u7814 \u7a76 \u3067 \u306f,\u5b9f \u7528 \u7684 \u306a \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u3092 \u5f93 \u6765 \u3088 \u308a\u7c21 \u5358 \u306b \u88fd\n\u4f5c \u3059 \u308b \u305f \u3081 \u306b \u30d5 \u30a7 \u30fc \u30b9 \u30ae \u30e4 \u306e \u8a2d \u8a08 \u30fb\u8a08 \u7b97 \u6cd5 \u306b\u3064 \u3044 \u3066 \u691c \u8a0e \u3057, \u3055 \u3089\u306b \u901a \u5e38 \u306e \u30dc \u30d6 \u76e4 \u306b \u3088 \u308b \u5275 \u6210 \u6b6f \u5207 \u308a\u3092 \u8a66 \u307f \u305f.\u305d \u306e \u7d50 \u679c, \u4ee5 \u4e0b \u306e \u7d50 \u8ad6 \u3092\u5f97 \u305f.\n(1) \u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4 \u306e \u5927\u7aef,\u5c0f \u7aef \u76f4\u5f84 \u3092 \u6c7a \u5b9a \u3059 \u308b \u305f \u3081 \u306b \u4eee\n\u60f3 \u306e \u8ee2 \u4f4d \u6b6f \u8eca \u7406 \u8ad6 \u306b \u57fa\u3065 \u304d,\u305d \u308c \u305e \u308c \u5927 \u7aef \u306b \u304a \u3051 \u308b \u3068 \u304c \u308a\u306e \u9650 \u754c \u3068\u5c0f \u7aef \u3067 \u306e \u5207 \u308a\u4e0b \u3052 \u3092 \u8003 \u616e \u3057\u305f\u8fd1 \u4f3c \u5f0f \u306e \u63d0\n\u6848 \u3092 \u3057\u305f.\n(2) (1)\u306b \u57fa \u3065 \u304d\u901a \u5e38 \u306e \u30db \u30d6 \u76e4 \u3068\u8584 \u304f\u5207 \u65ad \u3057\u305f \u5e02 \u8ca9 \u30db \u30d6 \u3092\n\u7528 \u3044 \u3066 \u8a66 \u9a13 \u7684 \u306b\u6b6f \u5207 \u308a \u3057\u305f \u3068 \u3053 \u308d \u8fd1 \u4f3c \u5f0f\u306e \u59a5 \u5f53 \u6027 \u304c \u78ba\n\u8a8d \u3067 \u304d\u305f.\u3055 \u3089 \u306b\u304b \u307f \u5408 \u3044 \u8a66 \u9a13 \u3088 \u308a,\u5b9f \u7528 \u6027 \u3082\u898b \u3044 \u3060 \u305b \u305f.\n(3) \u30d5 \u30a7\u30fc \u30b9 \u30ae \u30e4 \u306e \u8a2d \u8a08 \u3067 \u7279 \u306b\u91cd \u8981 \u3068 \u306a \u308b\u6b6f \u5e45 \u306b\u304a \u3044 \u3066,\n\u6b6f \u6570 \u3068\u30aa \u30d5 \u30bb \u30c3 \u30c8\u91cf \u306e \u5897 \u52a0 \u306f \u30d4 \u30c3\u30c1 \u5186 \u76f4\u5f84 \u3092 \u5927 \u304d \u304f\u3059 \u308b \u305f \u3081 \u7d50 \u679c \u3068 \u3057\u3066\u6b6f \u5e45 \u306f \u5927 \u304d \u304f\u306a \u308b.\n\u7d42\u308f\u308a\u306b,\u672c \u7814\u7a76\u306b\u5bfe \u3057\u3054\u5354\u529b\u3092\u8cdc \u308a\u307e\u3057\u305f\u5143\u5c71\u68a8\u5927\u5b66\n\u5de5\u5b66\u90e8\u7cbe\u5bc6\u5de5\u5b66\u79d1\u6559\u6388,\u6545 \u9234\u6728\u79c0\u592b\u5148\u751f \u306b\u611f\u8b1d\u306e\u610f\u3092\u8868 \u3057\n\u307e\u3059.\n\u53c2 \u8003 \u6587 \u732e\n1) \u65b0\u8358 \u8b39 \u4e00,\u5742 \u672c \u6b63 \u53f2,Md.Rezaur Rahman:\u56de \u8ee2 \u5f62 \u30d4 \u30cb \u30aa \u30f3\n\u30ab \u30c3\u30bf\u306e \u958b \u767a \u3068 \u3053\u308c \u306b \u3088 \u308b \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u306e \u30db \u30d6 \u5207 \u308a,\u65e5 \u672c \u6a5f \u68b0 \u5b66 \u4f1a \u8ad6 \u6587 \u96c6(\u7b2c3\u90e8),43,373(1977) 3526\u3001 2) \u5742 \u672c \u6b63 \u53f2,\u7af9 \u5185 \u82b3 \u7f8e,\u4e2d \u6751 \u5e73,\u6d45 \u5c3e \u6643 \u901a,\u65b0 \u8358 \u8b39 \u4e00: \u666e\n\u901a \u30db \u30d6 \u3067 \u6b6f \u5207 \u308a \u3057\u305f \u30d5 \u30a7\u30fc \u30b9 \u30ae\u30e4 \u3068 \u3053\u308c \u3092\u7528 \u3044 \u305f \u81ea\u52d5\u5272 \u51fa \u88c5 \u7f6e,\u7cbe \u5bc6\u5de5 \u5b66 \u4f1a\u8a8c,52,11(1986) 1954. 3) \u6210 \u702c \u653f \u7537,\u6a2a \u7530 \u6643:\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4(1),\u6a5f \u68b0 \u306e \u7814\u7a76,6, 4\n(1954) 49.\n4) \u6210 \u702c \u653f \u7537,\u6a2a \u7530 \u6643:\u30d5 \u30a7\u30fc \u30b9\u30ae \u30e4(2),\u6a5f \u68b0 \u306e \u7814\u7a76,6, 5\n(1954) 55.\n5) V.Francis and J. Silvag : Face Gear Design Factors,\nGear Gesign and Application, McGraw-Hill,New York, N.Y. , (1967) 87.\n6) \u9234 \u6728 \u79c0 \u592b,\u8429 \u539f \u89aa \u4f5c,\u7db2 \u5009\u653f \u57fa,\u4e2d \u6751 \u82b3 \u5f66:\u30c6 \u30fc\u30d1 \u30ae \u30e4 \u306b\n\u95a2 \u3059 \u308b \u7814 \u7a76(\u7b2c2\u5831),\u7cbe \u6a5f \u5b66 \u4f1a \u5c71 \u68a8 \u5730 \u65b9 \u8b1b \u6f14 \u4f1a\u8b1b \u6f14\u8ad6 \u6587 \u96c6,(1986) 105.\n\u66f8 \u8a55\n\u7523 \u696d \u7528 \u30ed\u30dc \u30c3 \u30c8\u8a00 \u8a9e \" SLIM \"\n\u7de8\u8457\u8005 \u65b0\u4e95\u6c11\u592b \u767a \u884c (\u8ca1) \u65e5\u672c\u898f\u683c\u5354\u4f1a\nJIS B 8439-1992\u3068 \u3057\u3066\u6a19 \u6e96 \u5316 \u3055\u308c \u305f \u30ed \u30dc\u30c3 \u30c8\u8a00\u8a9e\"SLIM\" \u306b \u95a2 \u3059 \u308b\u89e3 \u8aac \u66f8 \u3067 \u3042 \u308b.(\u793e)\u65e5 \u672c \u30ed\u30dc \u30c3 \u30c8\u5de5\u696d \u4f1a \u306b \u304a \u3044 \u306610\u5e74 \u306e\u5e74 \u6708 \u3092\u639b \u3051 \u3066\u898f \u683c \u4f5c \u6210 \u306b \u3053 \u304e\u3064 \u3051 \u305f \u3082\u306e \u3092,\u4e00 \u822c \u306e \u8aad \u8005 \u306b \u308f \u304b \u308a\u3084\u3059 \u3044 \u3088 \u3046\u306b \u30ed\u30dc \u30c3 \u30c8\u8a00\u8a9e \u306e\u57fa \u790e \u304b \u3089\u5e73 \u6613 \u306b\u89e3 \u8aac \u3057\u3066 \u3044 \u308b.\u3053 \u306e \u5206 \u91ce \u306f \u30e1 \u30fc\u30ab \u304c,\u5404 \u793e \u5404\u69d8 \u306e \u8a00\u8a9e \u51e6 \u7406 \u7cfb \u3092\u6301 \u3063 \u3066 \u304a \u308a,\u7a81 \u51fa \u3057\u305f \u65b9 \u5411\u6027 \u304c \u793a \u3055\u308c \u3066 \u3044 \u306a \u3044 \u305f \u3081,\"SLIM\"\u306b \u306f \u305d \u306e\u5171 \u901a \u90e8 \u5206 \u306e \u307f \u304c \u5b9a \u7fa9 \u3055\u308c \u3066 \u3044 \u308b.\u672c \u66f8 \u306e \u524d \u534a \u306f,\u30ed \u30dc \u30c3 \u30c8\u306e\u904b \u52d5 \u5b66 \u306a \u3069,\u30ed \u30dc \u30c3 \u30c8\u8a00 \u8a9e \u3092, \u3042 \u308b \u3044 \u306f \u30ed\u30dc \u30c3 \u30c8\u306e \u904b \u52d5 \u3092 \u7406 \u89e3 \u3059 \u308b \u305f \u3081 \u306e \u57fa \u790e \u3067 \u3042 \u308a,\u5f8c \u534a \u306f \"SLIM\"\u306e \u6587 \u6cd5 \u89e3 \u8aac \u66f8 \u3068 \u305d \u306e \u5fdc \u5ddd \u4f8b \u3067 \u3042 \u308b\n.\u591a \u304f\u306e \u4f8b \u306f,\u8a00 \u8a9e \u7406\n\u89e3 \u306e\u5927 \u304d \u306a\u52a9 \u3051 \u3068\u306a \u308b.\n\u672c\u66f8 \u306e \u5185\u5bb9 \u306f,\n1. \u30ed\u30dc \u30c3 \u30c8\u8a00\u8a9e \u6982 \u8ad6\n\u30ed\u30dc \u30c3 \u30c8\u8a00 \u8a9e \u3068\u306f,\u30ed \u30dc \u30c3 \u30c8\u8a00\u8a9e \u306e\u7a2e \u985e,\u7528 \u8a9e \u306e \u5b9a \u7fa9 \u30ed\u30dc \u30c3 \u30c8\u8a00 \u8a9e \u306e \u6a19 \u6e96\u5316\n2. \u30ed\u30dc \u30c3 \u30c8\u8a00\u8a9e \u306e\u57fa \u790e\n\u6c34 \u5e732\u95a2 \u7bc0 \u30ed\u30dc \u30c3 \u30c8\u306e\u7406 \u8ad6,\u591a \u95a2\u7bc0 \u578b \u30ed\u30dc \u30c3 \u30c8,\u52d5 \u4f5c \u3084\u4f5c \u696d \u306e \u6307 \u793a \u65b9 \u6cd5,\u30ed \u30dc \u30c3 \u30c8\u8a00\u8a9e \u306b \u304a \u3051 \u308b \u30c7 \u30fc \u30bf\u578b \u3068\u30c7 \u30fc \u30bf\u69cb \u9020, \u30ed\n\u30dd \u30c3 \u30c8\u5236 \u5fa1\u547d \u4ee4 \u306e\u5b9f \u969b,\u30bb \u30f3\u30b5 \u60c5 \u5831\u51e6 \u7406 \u306e\u5b9f \u969b,\u305d \u306e \u4ed6 \u306e \u547d \u4ee4 \u306e\u5b9f \u969b,\u30ed \u30dc \u30c3 \u30c8\u8a00 \u8a9e \u30b7 \u30b9 \u30c6 \u30e0\u306e \u69cb \u6210\n3. \u30ed \u30dc\u30c3 \u30c8\u8a00 \u8a9eSLIM\u306e \u6587 \u6cd5\nSLIM\u306e \u57fa \u672c \u69cb \u9020,\u30c7 \u30fc \u30bf,\u5ba3 \u8a00,\u52d5 \u4f5c \u3092\u4f34 \u308f \u306a \u3044 \u6587,\u30ed \u30dc \u30c3\n\u30c8\u5236 \u5fa1 \u6587\n4. \u6a19 \u6e96 \u30ed\u30dc \u30c3 \u30c8\u8a00 \u8a9eSLIM\u3092 \u7528 \u3044 \u305f \u30ed\u30dc \u30c3 \u30c8\u30d7 \u30ed \u30b0 \u30e9 \u30df\u30f3\u30b0\n\u30ed\u30dc \u30c3 \u30c8\u79fb \u52d5 \u547d \u4ee4 \u3068\u30d7 \u30ed\u30b0 \u30e9 \u30e0\u69cb \u9020,\u4e26 \u884c \u79fb \u52d5 \u3068\u56de \u8ee2 \u30bb \u30f3\u30b5\n\u5229 \u7528,\u5468 \u8fba \u6a5f \u5668 \u306e\u5236 \u5fa1,\u30c6 \u30a3 \u30fc\u30c1 \u30f3\u30b0\u6a5f \u69cb\n5. \u304a \u308f \u308a\u306b\nSLIM\u6a19 \u6e96 \u5316 \u306e \u554f \u984c \u70b9,SLIM\u3068STROLIC,\u30ed \u30dc \u30c3 \u30c8\u8a00 \u8a9e \u306e \u5c06 \u6765\n\u3068 \u306a \u3063\u3066 \u3044 \u308b.\n\u305d \u308c \u305e \u308c \u306b \u591a \u304f\u306e \u56f3,\u8868,\u53c2 \u8003 \u6587 \u732e \u3092 \u6319 \u3052 \u305f \u5177 \u4f53 \u7684 \u306a\u8aac \u660e \u3067 \u3042 \u308a,\u7279 \u306b \u30d7 \u30ed \u30b0 \u30e9 \u30e0 \u4f8b \u3068JIS\u898f \u683c \u304c \u8f09 \u3063 \u3066 \u3044 \u308b \u3053 \u3068 \u306f,\u3053 \u306e1 \u518a\n\u3067\"SLIM\"\u3092 \u7406 \u89e3 \u3059 \u308b\u306e \u306b \u597d\u90fd \u5408 \u3067 \u3042 \u308b. (\u7b39 \u5cf6 \u548c\u5e78)\n(A5\u5224,262\u30da \u30fc \u30b8,3700 \u5186)\n\u7cbe\u5bc6\u5de5\u5b66\u4f1a\u8a8c Vol. 61, No. 4, 1995 505" + ] + }, + { + "image_filename": "designv8_17_0001922_1044-023-09952-2.pdf-Figure23-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001922_1044-023-09952-2.pdf-Figure23-1.png", + "caption": "Fig. 23 Undesired contact interaction that can be observed in the C4 model if the pocket clearance is smaller than the radial clearance of the bearing", + "texts": [ + " 22, is based on the internal circle\u2013circle interaction introduced above. In this model, the radius of the cage pocket was defined with sufficient clearance to allow free movement of the balls while ensuring that the interactions between the balls and races are not compromised. However, it is important to note that if the radial clearance of the bearing is excessively large, the rolling elements may make contact with a non-existent part of the cage pocket instead of the rings, as schematically represented in Fig. 23. Nevertheless, this solution proved to be more computationally attractive since the definition of 2 (C1), 6 (C2) or 10 (C3) plane\u2013circle contacts was replaced for just one circle\u2013circle interaction. Moreover, when using several planes, the contact scenario can change from one plane to the following one, which involves an abrupt variation of the contact location and contact direction. By contrast, the circle\u2013circle interaction ensures a smooth contact evolution in the ball\u2013cage contact. Regarding the consistency of the model, the results presented in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003232_Aw_20Kuan_20Thai.pdf-Figure6.10-1.png", + "caption": "Figure 6.10: Gas Pressure Forces in Working Chambers", + "texts": [ + "44) To this end, the friction force on the vane acting on the cylinder is equal and opposite to that of the vane slot. The friction torque at the vane slot acting on the cylinder can then be expressed as shown in Equation (6.45). \ud835\udc47\ud835\udc53,\ud835\udc63 \ud835\udc50 = \u2212\ud835\udc39\ud835\udc53,\ud835\udc63 \ud835\udc5f (\ud700 sin \ud703\ud835\udc63 \u2212 \ud835\udc64\ud835\udc60\ud835\udc59\ud835\udc5c\ud835\udc61 2 ) (6.45) The normal forces on the bearings for the cylinder and rotor are affected by both the pressure forces in the chambers and the vane sliding forces. These forces will be evaluated in the plane of rotation and resolved in Cartesian coordinates for ease of calculation. Beginning with the gas pressure forces in the chambers, Figure 6.10 shows the gas pressure forces acting on the cylinder and rotor. The resolved forces due to the suction and compression pressures are then tabulated in Equations (6.46)\u2013(6.53). 110 Suction: Cylinder: \ud835\udc39\ud835\udc65,\ud835\udc60 \ud835\udc50 = \u2212\ud835\udc5d\ud835\udc60\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50(1 \u2212 cos \ud703\ud835\udc50) (6.46) \ud835\udc39\ud835\udc66,\ud835\udc60 \ud835\udc50 = \u2212\ud835\udc5d\ud835\udc60\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50 sin \ud703\ud835\udc50 (6.47) Rotor: \ud835\udc39\ud835\udc65,\ud835\udc60 \ud835\udc5f = \ud835\udc5d\ud835\udc60\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f(1 \u2212 cos \ud703\ud835\udc5f) (6.48) \ud835\udc39\ud835\udc66,\ud835\udc60 \ud835\udc5f = \ud835\udc5d\ud835\udc60\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f sin \ud703\ud835\udc5f (6.49) Compression: Cylinder: \ud835\udc39\ud835\udc65,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc50 = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50(1 \u2212 cos \ud703\ud835\udc50) (6.50) \ud835\udc39\ud835\udc66,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc50 = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc50 sin \ud703\ud835\udc50 (6.51) Rotor: \ud835\udc39\ud835\udc65,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc5f = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f(1 \u2212 cos \ud703\ud835\udc5f) (6.52) \ud835\udc39\ud835\udc66,\ud835\udc50\ud835\udc5c\ud835\udc5a \ud835\udc5f = \ud835\udc5d\ud835\udc50\ud835\udc5c\ud835\udc5a\ud835\udc59\ud835\udc50\ud835\udc5f\ud835\udc5f sin \ud703\ud835\udc5f (6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000658_nf_eko2017_00082.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000658_nf_eko2017_00082.pdf-Figure2-1.png", + "caption": "Fig. 2. Airflow through the single heat exchanger chamber in one cycle of work of the device and the three dimensional view of the device (fig. authors).", + "texts": [], + "surrounding_texts": [ + "Currently in Poland described heat exchanger is not very well known and widely used, even though its construction was known and developed long before the rotary heat exchanger. This heat exchanger is an attractive alternative to other heat exchangers, both recuperators and regenerators. The purpose of this article is a closer representation of the storage matrix heat exchanger, its construction, high efficiency, but occasionally reported in the literature. The storage matrix heat exchangers are often also called accumulative heat exchangers or reversible heat exchangers and operate on the principle of alternating washing out of accumulative storage matrixes within a specified period of time by an exhaust air stream and external air stream [1]. Air distribution through the chambers of storage blocks is arranged by using dampers, mechanically coupled with each other. The following is a flowchart of storage matrix heat exchanger. The exchanger consists of two independent storage blocks and a dampers system with actuators for changing the direction of air flow. Storage matrix is similar to the matrix used in rotary heat exchangers. The main difference lies in the layered arrangement of plates and the undulating arrangement between the layers of sheets of metal. Storage matrix chambers are separated from each other by a vertical partition. After a predetermined time, the air flow is reversed by dampers. As a result of matrix temperature difference and air stream temperature, outlet air stream temperatures changes. Time of one cycle of air flow through the storage matrix chambers are variable and depend on the manufacturer of approx. * Corresponding author: maciej.skrzycki@pwr.edu.pl \u00a9 The Authors, published by EDP Sciences. This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0/). 20 seconds [2] to even 100 seconds [3]. The graph in Fig. 1 shows an operation of storage matrix heat exchanger [4]. Storage blocks chambers have a responsive mechanism to change the direction of air flow during even less than 1 second [2] - it is shown in Fig. 1 and 2. The average heat flux transferred in a storage matrix heat exchanger can be assumed as follows [5]: CHGRZ ok aksr ttVc Q Q _ (1) Qak \u2013 heat accumulated in the matrix of a regenerator, kW \u03c4ok \u2013 regenerator cycle, s okCHGRZ g sr GRZg sr tt o 1,_ (2) t GRZ, t CH \u2013 air stream temperatures in the charging and discharging phase, \u00b0C \u03c5g \u015br \u2013 average matrix temperatures at the end and beginning of charging phase, \u00b0C c, \u03c1, V \u2013 specific heat, density, air stream, \u03ba \u2013 heat flux reduced in the regenerator , kW In analogy to the rotary heat exchangers, also in the storage matrix heat exchangers the cycle is split into two equal phases: heat transfer from the air to the matrix and from the matrix to the air. This process (shown in Fig. 3) can be described as \u03c40=\u03c41+ \u03c42 [5]. The work of storage matrix regenerators is symmetrical \u2013 time of flow of warm air stream through a first chamber of heat exchanger is equal to the time of flow of cool air stream through the second chamber of heat exchanger. The sum of these times is the time of cycle of air flow through the heat exchanger [2]. The time needed to change the direction of the flow of air streams is assumed as negligible. At the time of switching of dampers at the inlet and outlet of heat exchanger the air streams contacts with each other. Accordingly, the use of storage matrix heat exchangers is similar to the rotary heat exchangers and is not recommended if there is an emission of harmful substances, aromatic substances, etc. because of the risk of flow of these substances in the heat exchanger to the external air stream [2]. Storage matrix heat exchangers respective to the flow of the air streams can be compared to the counterflow heat exchangers. In the heat exchanger cross-section the temperature fluctuations are recurrent in each cycle of work of exchanger \u2013 in charging and discharging phase [6]. These temperatures decrease along with decreasing of cycle time or the length of the air flow in the heat exchanger, as well as with the change of the heat capacity of the storage matrix." + ] + }, + { + "image_filename": "designv8_17_0000652_0005208_10013678.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000652_0005208_10013678.pdf-Figure10-1.png", + "caption": "FIGURE 10. Exploded view of the antenna: four metal blocks are screwed together and the septum array polarizer is fixed between the two QOBFs.", + "texts": [ + " It is also worth noticing that the asymmetry in the performance is due to the asymmetric design of the septum polarizer. C. FINAL ANTENNA STRUCTURE The twomirrored QOBFs are connected to an array of septum polarizers made of 32 elements, through a PPW bent section. The connection of all antenna parts is not trivial. In particular the input ports of the arrays of septum are separated by a metallic wall of 0.5 mm. Such a thickness cannot be used for the bottom parts of the QOBFs for mechanical constraints. Therefore a PPW 90\u25e6 bend has been added at the end of QOBFs as sketched in Fig. 10. The bend has been designed following the procedure outlined in [31] and optimized to reduce reflections. A smooth transition of about \u03bb0 has been added to connect the PPW of the lens (hppw = 2 mm) to the input rectangular waveguide of the septum with an height ht = 2.925 mm. The array of septum polarizers is then connected between the two stacked QOBFs with the metallic wall of the septums housed in a specific slot in the lower plates of the QOBFs, as shown in the exploded wiew in Fig. 10. To guarantee the electrical contact between the components an RF choke is introduced on the lower plate of both the QOBFs. III. MANUFACTURING AND EXPERIMENTAL RESULTS The antenna has been manufactured in a modular way, with 5 different parts: each QOBF has been realized by milling of VOLUME 11, 2023 4609 aluminium blocks, while the array of septum polarizers by EDM at IETR. The various parts are then connected by using dowel pins and screws as shown in Fig. 11. The overall size of the assembled antenna is 281" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000174_f_version_1641029125-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000174_f_version_1641029125-Figure8-1.png", + "caption": "Figure 8. Excitation pattern and flux-path of the short-pitched winding 3 in Design A; (a) Phase A is excited; (b) Phase B is excited; and (c) Phase C is excited.", + "texts": [ + " From the dynamic simulation results, it can be concluded that the short-pitched winding 3 is suitable for 12/8 SRM in terms of cost-saving, simple manufacturing process, torque ripple, and motor performance. Although the short-pitched winding 3 gives a better performance for 12/8 SRM, the number of flux reversals of this winding configuration is still high. This paper proposes an analysis method that can reduce the flux reversals on the stator yoke. The short-pitched winding 3 is divided into Design A and Design B as follows: \u2022 In Design A, as shown in Figure 8, the sequential magnetic poles in a clockwise direction are SNSN when excited phase A, NSNS when excited phase B, and NSNS when excited phase C. \u2022 In Design B, as shown in Figure 9, the sequential magnetic poles in a clockwise direction are SNSN when excited phase A, NSNS when excited phase B, and SNSN when excited phase C. The number of flux reversals in each segment of the stator yoke in the clockwise (A\u2013B\u2013 C\u2013A) and counter-clockwise (A\u2013C\u2013B\u2013A) direction of Design A is illustrated in Table 9. To calculate the total number of flux reversals in one revolution, Equation (10) is used" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004515_id_0354-98362304229C-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004515_id_0354-98362304229C-Figure11-1.png", + "caption": "Figure 11. Evaluation of mesh quality by skewness criterion", + "texts": [ + " Mesh process of electric vehicle chassics Figure 8. Finite element interface When creating finite element models, the Tetrahedron method was preferred as the mesh method due to its desired accuracy and analysis time required for obtaining results. In addition, to achieve a high quality mesh, the first meshing process involved applying point, line, and local mesh processes, tailored to the structure of the part. By using the Skewness criterion, the mesh quality close to perfection was achieved, as shown in fig. 11, validating the accuracy and quality of the process. After the meshing process, loads and boundary conditions, including force, momentum, contact zones, and gravitational acceleration, are determined to match the actual working conditions of the structure. The vehicle chassis must be strong enough to withstand these stresses. These conditions are determined based on the loading conditions outlined in the Euro NCAP standard. Additionally, the vehicle chassis must be capable of cushioning the impacts that occur during an accident without compromising the occupants safety" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002674_f_version_1683615605-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002674_f_version_1683615605-Figure1-1.png", + "caption": "Figure 1. The Southampton tube sensor. The sensor is mounted on a platform on the digit tip which also acts upon the Force-Sensitive Resistor. The tube directly connects to the slipping object and so the frictional signal is coupled to the air in the tube and so the microphone. The airborne noises are poorly linked and so are much smaller and can be removed from the slip signal. (Design thanks to the late Mervyn Evans).", + "texts": [ + " Moore [25] attempted to decouple the microphone from the hand through mounting a microphone on a mass placed upon a rubber pad on the the distal end of the thumb, (the tip of the thumb that opposed the index finger was also roughening up). While successful in reducing the signal from the hand it was less effective at reducing airborne noise. Barkhordar created a more effective means to separating signal from noise [57]. A hearing aid microphone (EA series microphones, Knowles Electronics Co. 73 Victoria Road, Burgess Hill, West Sussex, RH15 9LP, UK) was arranged with its stub-pipe through the wall of a rubber tube, which was then in contact with the grip surface, as shown in Figure 1. Slip signals vibrate the wall of the tube. The signals are readily transmitted to the air within the tube and onto a microphone. Airborne vibrations have to excite the rubber of the tube before they can create a signal in the tube. Hence, the impedance of the path is matched more closely to surface signals than airborne noises. This means the interference signals are much smaller, (micro-volt for interference compared to milli-volt for slip signal), and so interference can be thresholded out [57]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004586_f_version_1672399768-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004586_f_version_1672399768-Figure1-1.png", + "caption": "Figure 1. Vehicle longitudinal dynamics.", + "texts": [ + " The current study is arranged as follows: The vehicle modeling is displayed in Section 2. The proposed control strategy, with the necessary derivations and stability proof, is specified in Section 3. Section 4 exemplifies the performance of the suggested method through a simulation study. A conclusion is then reached in Section 5. As a vehicle is in motion, it is exposed to the following extraneous longitudinal forces: longitudinal tire grip forces, aerodynamic drag forces, climbing resistance forces, and rolling resistance forces (see Figure 1). Appl. Sci. 2023, 13, 501 4 of 15 Appl. Sci. 2023, 13, x FOR PEER REVIEW 4 of 17 is specified in Section 3. Section 4 exemplifies the performance of the suggested method through a simulation study. A conclusion is then reached in Section 5. forces: longitudinal tire grip forces, aerodynamic drag forces, climbing resistance forces, and rolling resistance forces (see Figure 1). Figure 1. Vehicle longitudinal dynamics. The aggregate effect of the forces along the vehicle\u2019s longitudinal axis is expressed as follows: ( )xf xr aero xf xrmx mgsin = + \u2212 \u2212 \u2212 \u2212f f f (1) where xff and xrf are the longitudinal forces arising from the encounter between the tire and the road, aerof is the longitudinal aerodynamic drag force, and xf and xr are the forces resulting from the rolling resistance of the front and rear tires, respectively. m is the vehicle mass, g is the acceleration caused by gravity, and is the road\u2019s an- gle of inclination" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.8-1.png", + "caption": "Figure 1.8. Wheelbase and track illustrated [63].", + "texts": [ + " It is positive when the top of the wheel leans away from the vehicle; negative when it leans into the vehicle. See Figure 1.6. \u2022 The toe angle of a wheel is the angle between a longitudinal axis of the vehicle and the line of intersection of the wheel plane and the road surface. It is positive when the front of the wheel aims toward the vehicle (toe-in) and negative when the front of the wheel aims away from the vehicle (toe-out). See Figure 1.7. \u2022 Track is the lateral distance between the tire contact points of an axle, measured along the ground. See Figure 1.8. \u2022 Wheelbase is the longitudinal distance between the front and rear tire contact points of one side of the vehicle, measured along the ground. See Figure 1.8. 4 5 6 Early, animal-drawn, four-wheeled vehicles consisted of a platform mounted on two axles, with a wheel at each end of the axles. At the center of the front axle was a flat plate with a pin, which fit into a hole in a plate on the platform. This allowed the front axle to turn relative to the platform. The animals\u2019 harness was attached to the front axle, so when the animals pulled the vehicle it could steer accordingly. If the vehicle was intended to carry passengers, it was common to suspend the platform from the axles with chains or leather straps, making journeys more comfortable" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002204_00161-018-0660-8.pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002204_00161-018-0660-8.pdf-Figure15-1.png", + "caption": "Fig. 15 Single lenticular girder, natural frequency extraction, numerical results (postprocessing in SOFiSTiK)", + "texts": [ + " 14, where comparison is given to the original in situ measurements taken in 1969. The curves show a good qualitative agreement. The quantitative assessment revealed the 9% discrepancy between in situ and numerical results which is also fine. Table 3 presents some representative values to support this observation. In the next step, the natural frequency extraction was performed. Here different numerical integration rules to obtain element mass matrix (55)1 were tested. The obtained values are depicted in Fig. 15. 7.2 Year 2008 load test, in situ results, FEM simulations In August 2008, dynamic and static load tests of the whole roof structure were performed. The positions of measuring points are shown in Fig. 16. In load test, the static load was created by pairs of hanging bags filled with stones, and the weight of each bag was 9 kN. Their placement is shown in Fig. 17 along with the actual photograph in Fig. 18. The following load protocol was applied \u2022 2 readings of displacements at every 15 min prior to load, \u2022 1 reading directly after the placement of the next row of the hanging bags, \u2022 1 reading directly after the placement of the whole load, \u2022 series of successive readings at each 15min under the whole load, the loadwas kept as long as the increment of displacement in two consecutive readings did not differ more than 2% from the total load, \u2022 1 reading after removal of the row of load, \u2022 1 reading directly once the last portion of load was removed, \u2022 series of successive readings at each 15 min until the stabilization of the structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000411_wnload_169156_170710-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000411_wnload_169156_170710-Figure1-1.png", + "caption": "Fig. 1. Estimation scheme for designing a regression model of the surface of a working body", + "texts": [ + " The study objectives: \u2013 to establish the elements of functional similarity; \u2013 to construct the geometric, numeric, and regression model of the surface of a biological analog; \u2013 to derive a mathematical model of the interaction between soil and the working surface of a tillage tool; \u2013 to design an effective prototype and to test it practically. A comparative analysis of the design of deep-rippers and the structure of a body of marine animals has revealed that the biological analog that could be used is the body of a hammerhead fish [14]. Based on results of the visual analysis of a series of photographic images of the body of a biological analog, in accordance with the basic criteria of similarity, we have designed a structural scheme of the chisel (Fig. 1). A mathematical model can be only regressive in character. Why so? The fact is that the equation should be modified in accordance with calculations based on the analytical model of interaction between a blade and soil. Modification is based on a numerical method, and a regression equation is derived exactly in this way. The input parameter is coordinate \u0425\u0456, or the length of a body from the frontal part to the i-th cross-section, the output parameter is Yi, or the working width of the i-th cross-section (Fig. 1). The dimensions of the body of a biological analog in Fig. 1 are scaled to the adopted working width of 170 mm based on the results from a dimensional analysis into the series of photographic images of an actual animal, they are therefore conditional. The resulting numerical array (Table 1) is processed by the method of least squares to derive a regression equation of the surface profile. Table 1 Numerical model of the surface profile of a biological analog \u0425, mm Measured value 1.0 50 100 150 200 250 300 Y, mm Measured value 1.0 40 55 65 75 105 170 Estimated value 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002059_cle_download_346_147-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002059_cle_download_346_147-Figure10-1.png", + "caption": "Fig. 10. System response curve and Ziegler and Nichols approach.", + "texts": [ + " The functional diagram of the water flow controller for drip irrigation in this study is shown in Fig. 9. The system uses PID control methods. The controller input is an error signal which is the difference between the setpoint and the flow sensor. The PID parameters were obtained using the ZieglerNichols method. This method is based on the system's response to an open loop indicated by the unit step function. The concept of determining the PID parameters is based on the system response curve, as shown in Fig.10. The system response will form an S-shaped curve. In this curve, a line is made that is tangent to the curve line. The tangent line will intersect with the abscissa axis and the maximum line. The tangent line intersection with the abscissa axis is a measure of dead time (L), and the intersection with the maximum line represents the delay time (T) measured from the time point L. The results of the measurement are then entered into Table 2. The control strategy for this system is PID control. The results of testing the system in the open loop condition obtained a curve like Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure10.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure10.1-1.png", + "caption": "Figure 10.1. Illustration of the S-R link.", + "texts": [ + " For roll center height results, see Figure 9.11. Despite specifying only design position velocity and one jounce position (z = 25 mm), the wheel-travel curves closely match the specification. Not only that, but a kingpin axis and an Ackermann criterion have been achieved. Due to its excellent kinematics and relative simplicity versus the five link suspension, the SLA has long been associated with performance and racing cars. 142 143 144 145 Chapter 10 The S-R Link The S-R link indirectly connects the wheel carrier to the vehicle body, Figure 10.1. The body-side S joint is given by coordinate vector x0, while the wheel-side R joint is given by column vector u1 and coordinate vector x1. These line coordinates must satisfy u1 \u00b7 u1 = 1 (x1 \u2212 x0) \u00b7 u1 = 0. When the wheel is moved from Position 1, the design position, to Position i by an isometry having Ai \u2208 SO(3) and bi \u2208 R3, the new location of the point on the R joint axis is xi := Aix1 + bi, while the new direction of the R joint axis is ui := Aiu1. 146 The equations that must be satisfied in this Position i are very similar to the R-S link: (xi \u2212 x0) \u00b7 (xi \u2212 x0) = (x1 \u2212 x0) \u00b7 (x1 \u2212 x0) (xi \u2212 x0) \u00b7 ui = 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002626_IJEEE-V10I11P106.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002626_IJEEE-V10I11P106.pdf-Figure2-1.png", + "caption": "Fig. 2 presents the slot diagram for the 10-slot and 19-pole design, showcasing (a) the vectors of back electromotive force windings, and (b) the arrangement of phase windings.", + "texts": [ + " The choice of a 10-stator slot and 19-rotor pole configuration for the proposed Fault-Tolerant Flux-Switching Stator-PM (FTFSSPM) motor is based on its ability to minimize cogging torque compared to the 10-slot and 18-pole design, which exhibits a very low LCM despite having the highest winding factor. This selection is supported by prior testing and verification [37], which confirmed that the 10-slot and 19-pole combinations produce symmetrical back electromotive force, reducing cogging torque. In contrast, the 10-slot and 18-pole design leads to significant harmonic distortion. For reference, the slot diagram of the proposed FTFSSPM motor is depicted in Figure 2. However, Table 1 provides the specifications of the design parameters for easy comparison and analysis. In this section of the research paper, the primary focus lies in analysing key attributes under the no-load operating condition. Specifically, it delves into electromotive force (Back-EMF), flux-linkage, and cogging torque. A comprehensive presentation of these characteristics is methodically conveyed in figures ranging from Figure 3 to Figure 6. Figure 3(a) illustrates that the motor design employing a Ferrite magnet (Y30BH) demonstrates a marginal increase in back-EMF" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure23-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure23-1.png", + "caption": "Figure 23: Deflection results of final design \ud835\udefe = 5.2\u00b0.", + "texts": [ + " While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage. Investigating a mechanism that can produce a mechanical advantage might be beneficial. A pantograph seen in Figure 33 shows the idea behind the concept. 24 As seen in Figure 33, a small input displacement causes a large output displacement. One study of a compliant mechanism of a pantograph achieved a 7:1 \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b ratio [15]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003421_agritech-x_06001.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003421_agritech-x_06001.pdf-Figure4-1.png", + "caption": "Fig. 4. Sketch of external gear.", + "texts": [], + "surrounding_texts": [ + "2( ) sin( )2 2 Da yDa (17)\nWe will find the area of the sector limited by the engagement profile, the integration limits - the angles of coverage of the working camera at the maximum volume [8]:\n 4,32\n1 1 1 3,534\nd S x y d\nd \n(18)\n 4,32\n1 2 2 3,534\nd S x y d\nd \n(19)\n 24,321\n11 13,5342 S R d (20)\n 24,321\n22 23,5342 S R d (21)\n 24,321\n22 23,5342 S R d (22)\nFind the geometric volume of the hydraulic machine: 2310 2 2 1 z Vg b e Da z (23) Based on the calculations, we build a sketch of the impeller.\n cos( ) cos( 2 ) 1 ( ) 21 2 cos( 1 ) 11 2 cos( ) 11 cos( 2 ) 11 z x e z R z R z r (24)", + "4 Conclusion\nThe design of heroic programs requires the use of various methods and tools. They include evolute construction methods, reverse engineering, finite element method, and computer modeling.\nThese methods make it possible to optimize the design of gerotor transmissions in order to achieve high efficiency and reliability. They help determine optimal transmission parameters, such as tooth shape, radii and profiles, and analyze its strength and deformations.\nComputer simulations and simulations allow virtual transmission tests, reducing the risks and costs of physical prototyping. This allows designers to develop transmissions faster and more efficiently.\nThe optimal design of heroic transmission depends on the requirements and conditions of a particular application. Designers must consider factors such as required torque, rotational speed, loads and operating conditions to create a gear that will perform its functions optimally.\nReferences\n1. I.V. Karnaukhov, E.A. Sorokin, A.A. Nikitin, V.V. Abramov, M.D. Pankiv, IOP Conference Series: Earth and Environmental Science 981, 042054 (2022)\n2. V.I. Posmetev, V.O. Nikonov, V.V. Posmetev, IOP Conference Series: Earth and Environmental Science 392, 012038 (2019)\n3. V.O. Nikonov, V.I. Posmetev, V.V. Posmetev, IOP Conference Series: Earth and Environmental Science 392, 012039 (2019)\n4. I.I. Gabitov, A.V. Negovora, M.M. Razyapov, A.A. Kozeev, R.J. Magafurov, IOP Conference Series: Materials Science and Engineering 632, 012048 (2019)\n5. Wen Jing Hu, Zheng Meng, Journal of Physics: Conference Series 1574, 012028 (2022) 6. Yuanzhi Huang, Journal of Physics: Conference Series 2143, 012048 (2021) 7. C. Khamnounsak, S. Likit, Journal of Physics: Conference Series 1380, 012018 (2019) 8. R.T. Emelyanov, A.S. Klimov, K.S. Kravtsov, I.B. Olenev, E.S. Turysheva, Journal of\nPhysics: Conference Series 1515, 042078 (2020)" + ] + }, + { + "image_filename": "designv8_17_0003838_4_9_54_M2013174__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003838_4_9_54_M2013174__pdf-Figure4-1.png", + "caption": "Fig. 4 Changes in the \u00a1/\u00a3 transformation starting temperature in Fe and FeCo alloys as a function of Co concentration with a 6-T magnetic field. The solid circles represent \u00a1\u00bc \u00a3 transformations and the open circles represent \u00a3 \u00bc \u00a1 ones.", + "texts": [ + "1 \u00a1/\u00a3 transformation temperature in a magnetic field Figures 3(a) and 3(b) show examples of DSC curves for the \u00a1\u00bc \u00a3 and \u00a3\u00bc \u00a1 transformations for the Fe19Co alloy, respectively, both with and without a magnetic field. The latent heat of this transformation was evaluated from the area of the DSC peak, and the transformation entropy was determined by the latent heat divided by the \u00a1/\u00a3 transformation starting temperature. The transformation starting temperature, the latent heat and the transformation entropy obtained are summarized in Table 2. Figure 4 shows changes in the \u00a1/\u00a3 transformation starting temperature in pure Fe and FeCo alloys as a function of Co concentration in a 6-T magnetic field. These transformation temperatures increased with the application of a 6-T magnetic field, in good agreement with previous reports.2527,32) We measured the increase in the \u00a1\u00bc \u00a3 transformation starting temperatures in a 6-T magnetic field (TS6T \u00b9 TS0) to be 1, 7 and 10K for pure Fe, the Fe9.5Co alloy, and the Fe19Co alloy, respectively. The increases for the \u00a3 \u00bc \u00a1 transformation were 3, 6 and 12K for pure Fe, the Fe9", + " Figure 5 shows changes in the \u00a1/\u00a3 transformation temperature in the Fe19Co alloy as a function of magnetic field strength; for comparison, data from Fukuda et al.27) with an Fe20 at% Co alloy are also plotted. The transformation temperature linearly increases with magnetic field strength. However, the slope of the line is found to be higher for Fukuda\u2019s result than for ours. This may be because of two reasons. One would be attributed to the difference in the cobalt concentrations in those alloys. As shown in Fig. 4, an increase in the transformation temperature is more enhanced with increasing Co concentration in FeCo alloys. This likely result in a higher slope in Fig. 5 as the Co concentration increases. The other would be the demagnetizing filed depending on specimen\u2019s shape. The dimensions of the sample used in Fukuda\u2019s study was 20mm \u00a9 2mm \u00a9 0.5mm, and a magnetic field was applied along the long side direction of the specimen. On the other hand, the sample used in this study was cuboidal. Therefore, an effective strength of a magnetic field applied would be lower for our sample than for Fukuda\u2019s one though the same external magnetic field was applied", + " These experimental results are corroborated by previous reports. Fukuda et al.27) used the Clausius Clapeyron equation to predict the change of the \u00a1/\u00a3 phase transformation temperature under a magnetic field for pure Fe and FeCo alloys. The ClausiusClapeyron equation in a magnetic field is given by, dT0 dH \u00bc M S ; \u00f01\u00de where M and S are the differences in magnetization and entropy between the two phases, respectively, T0 is the average of the \u00a1 \u00bc \u00a3 and \u00a3\u00bc \u00a1 phase transformation temperatures and H is a magnetic field. As shown in Fig. 4 in their report,27) the calculated transformation temperature changes from applying a magnetic field were lower than those obtained by resistivity measurements, except for pure Fe. In addition, the difference between the experimental and calculated values increased with Co concentration. In their calculations, the entropy change S of the \u00a1/\u00a3 phase transformation was assumed to vary insignificantly with an applied magnetic field. These results suggest that the entropies of the FeCo alloy \u00a1/\u00a3 phase transformations would decrease in an applied magnetic field; they also suggest that the entropy reduction would become more pronounced with increasing Co concentration" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003539_O200921140047629.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003539_O200921140047629.pdf-Figure2-1.png", + "caption": "Fig. 2. Structure of omni-directional linear piezoelectric actuator and electrodes on PZT.", + "texts": [], + "surrounding_texts": [ + "\uc13c\uc11c\ud559\ud68c\uc9c0 \uc81c18\uad8c \uc81c3\ud638, 2009 \u2212 186 \u2212\n\uc815\uc6b0\uc11d\u00b7\uac15\uc885\uc724\u00b7\uae40\uc815\ub3c4\u00b7\ubc31\ub3d9\uc218\u00b7\uc870\ubd09\ud76c\u00b7\uae40\uc601\ud638\u00b7\uc724\uc11d\uc9c4\n\ub41c\ub2e4. \ub610\ud55c, \ub780\uc96c\ubc18 \uc9c4\ub3d9\uc790\uc640 \ub3d9\uc77c\ud55c \u03bb /4 \uae38\uc774\uc758 \ud63c\uc744 \uc5f0\uacb0\ud558\uba74 \ud63c\uc758 \uc704, \uc544\ub798 \ub2e8\uba74\uc801\uc758 \ube44\uc728\ub9cc\ud07c \uc9c4\ub3d9\uc774 \uc99d \ud3ed\ub418\uba70 \ub3d9\uc791 \uc8fc\ud30c\uc218\uac00 1/2\ub85c \uac10\uc18c\ud558\uace0 \ubc1c\uc0dd\ub825\uc774 \uc99d\uac00 \ud558\uba70 \uc9c4\ub3d9\uc18d\ub3c4\ub294 \uac10\uc18c\ub418\ub294 \ud2b9\uc9d5\uc744 \uac16\ub294\ub2e4.\n\ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\uc758 \ubcc0\uc704\ub97c \uc54c\uae30 \uc704\ud574\uc11c\ub294 \uc5ed\uacc4\uc218 A, \uae30\uacc4 \uc784\ud53c\ub358\uc2a4 Z, \ub4f1\uac00 \uae30\uacc4\uc800\ud56d r \ub4f1\uc744 \uc774\uc6a9\ud558\uc5ec \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\uc758 \uae30\uacc4\uc801 \uc9c4\ub3d9\uc744 \ud655\uc778\ud574\uc57c \ud55c\ub2e4. \uc5ed\uacc4\uc218\uc758 \uacc4 \uc0b0\uc740 \ub2e4\uc74c \uc2dd(1)\uacfc \uac19\ub2e4.[7-10]\n(1)\n\uc5ec\uae30\uc11c, d, e33, Sc, \u03c52, \u03c50\ub294 \uac01\uac01 \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\uc758 \ub450 \uaed8, \uc555\uc804 \uc751\ub825\uc815\uc218, 1\uac1c\uc758 \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4 \ud310\uc758 \ub2e8\uba74\uc801, D\uba74\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc18d\ub3c4, A\uba74\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc18d\ub3c4\ub97c \ub098\ud0c0\ub0b8\ub2e4. \ub610\ud55c Fig. 1\uc5d0\uc11c \ub098\ud0c0\ub09c \uac83\ucc98\ub7fc A-F\uae4c\uc9c0\uc758 \uac01 \ubd80\ubd84\uc5d0 \uc11c\uc758 \uc9c4\ub3d9 \uc18d\ub3c4\ub97c \uc54c\uc544\uc57c \ud558\uace0 A-B \uad6c\uac04\uc5d0\uc11c\uc758 \uc9c4\ub3d9 \uc18d\ub3c4\ub294 \ub2e4\uc74c \uc2dd(2)\uacfc \uac19\ub2e4.\n(2)\n\uc5ec\uae30\uc11c, k1\uc740 A-B \uad6c\uac04\uc758 \ud30c\uc7a5 \uc815\uc218\uc774\uace0, l\uc740 A-B \uad6c\uac04\uc758 \uae38\uc774, \u03c51\uc740 B\uba74\uc5d0\uc11c \ubc1c\uc0dd\ub418\ub294 \uc9c4\ub3d9\uc18d\ub3c4\ub97c \ub098\ud0c0 \ub0b8\ub2e4. \ub530\ub77c\uc11c \ub450 \ubc88\uc9f8 C-D \uad6c\uac04\uc758 \uc9c4\ub3d9 \uc18d\ub3c4 \ubd84\ud3ec \u03c52 \ub294 \ub2e4\uc74c \uc2dd(3)\uacfc \uac19\uc774 \ub098\ud0c0\ub0b8\ub2e4.\n(3)\n\uc5ec\uae30\uc11c, Z1=S1\u03c11c1 \uc640 Z2=S2\u03c12c2\ub294 \uac01\uac01 A-B \uad6c\uac04 \uadf8 \ub9ac\uace0 C-D \uad6c\uac04\uc758 \ud30c\ub3d9 \uc784\ud53c\ub358\uc2a4\ub97c \ub098\ud0c0\ub0b4\uace0 S, \u03c1, c\ub294 \uac01\uac01 \ub2e8\uba74\uc801, \uc7ac\ub8cc\uc758 \ubc00\ub3c4, \ud30c\uc7a5\uc758 \uc18d\ub3c4\ub97c \ub098\ud0c0\ub0b4\uba70 k2=\u03c9/c2=2 \u03c0f/c2\ub294 C-D \uad6c\uac04\uc758 \uc885\ud30c\uc758 \ud30c\uc7a5 \uc815\uc218\ub97c \ub098 \ud0c0\ub0b8\ub2e4.\n\uc138 \ubc88\uc9f8 E-F \uad6c\uac04\uc758 \uc9c4\ub3d9\uc18d\ub3c4\ubd84\ud3ec \u03c53\ub294 \ub2e4\uc74c \uc2dd(4)\n\uc73c\ub85c \ud45c\ud604\ub41c\ub2e4.\n(4)\n\uc9c4\ub3d9\uc790\uc758 \uae30\uacc4\uacf5\uc9c4 \uc8fc\ud30c\uc218 f0=60 kHZ \ub77c\uace0 \ud558\uba74 \uac01 \uad6c\uac04\uc5d0\uc11c\uc758 \uc7ac\ub8cc\uc758 \ubc00\ub3c4 \u03c1, \uc885\ud30c\uc758 \uc18d\ub3c4 c, \ub2e8\uba74\uc801 S, \ud30c\ub3d9\uc784\ud53c\ub358\uc2a4 Z, \ud30c\uc7a5\uc815\uc218 k\uc740 Table 1\uacfc \uac19\uc774 \uc815\ub9ac\ub418 \uc5b4 \uc9c8 \uc218 \uc788\ub2e4.\n\uc9c0\uae08\uae4c\uc9c0 \uacc4\uc0b0\ub41c \uc218\uce58\ub97c \uc2dd(1)\uc5d0 \uc801\uc6a9\ud558\uba74 \uc9c4\ub3d9\uc790\uc758 \uc5ed\uacc4\uc218 A1\uc740 0.904 N/V\uac00 \ub41c\ub2e4. \ud6a1\ud6a8\uacfc\ub97c \uac16\ub294 \uc885\uc9c4\ub3d9 \uc790\uc758 \uc9c4\ub3d9\ub825 \ud3c9\ud615\uc2dd\uc5d0\uc11c \uacf5\uc9c4 \uc8fc\ud30c\uc218\uc5d0\uc11c\uc758 \uc9c4\ub3d9\uc18d\ub3c4 \u03c50\ub294 \ub2e4\uc74c \uc2dd(5)\uc640 \uac19\ub2e4[7,9-10].\n\u03c50=A1V/r0 (5)\n\ub530\ub77c\uc11c A1=0.904 N/V \uc640 \ud604\uc7ac \uc2e4\uc6a9\ud654 \ub41c \uc9c4\ub3d9\uc790\uc758 r0=50 N/m/s\ub97c \ub300\uc785\ud558\uace0 \uc561\ucd94\uc5d0\uc774\ud130\uc5d0 \uc778\uac00\ub418\ub294 \uc2e4\ud6a8 \uc804\uc555\uc774V=1 \ub77c\uace0 \ud558\uba74 \uc9c4\ub3d9\uc18d\ub3c4\ub294 0.18 m/s\uc774 \ub418\uace0 \uacf5 \uc9c4 \uc8fc\ud30c\uc218 f0=60 kHz \uc774\ubbc0\ub85c \uc2e4\uc81c \uc9c4\ub3d9\uc790\uc758 \ubcc0\uc704 \u03be0\ub294 \ub2e4\uc74c \uc2dd(6)\uc744 \uc774\uc6a9\ud558\uc5ec \uacc4\uc0b0\ub418\uc5b4 \uc9c4\ub2e4.\n(6)\n\ub530\ub77c\uc11c \uacf5\uc9c4 \uc601\uc5ed\uc5d0\uc11c \uc815\ud604\ud30c \uc785\ub825\uc2dc 90o\uc640 270o \ucd5c \ub300 \uc9c4\ud3ed\uc744 \uac00\uc9c8 \ub54c \uc9c4\ub3d9\uc790\uc758 \ucd5c\ub300 \ubcc0\uc704\ub294 \uc57d 33 nm\ub97c \uac16\ub294 \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\uc774\ub2e4.\n2.2. \uad6c \uc870 Fig. 2\uc640 \uac19\uc774 \ud63c\uc744 \uc6d0\ubfd4 \ud615\ud0dc\uc758 \uad6c\uc870\ub85c \uc124\uacc4\ud558\uc600\uc73c \uba70 \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\uc758 \ub2e8\uc77c\ud654 \ubc0f \uad6c\uc870\uc758 \ud1b5\ud569\uc73c\ub85c \uc77c\uc815 \ud55c \uc9c4\ub3d9\uc758 \uc0dd\uc131\uc774 \uac00\ub2a5\ud558\ub3c4\ub85d \ud558\ub098\uc758 \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\uc5d0 \ub124 \uac1c\uc758 \uc804\uadf9\uc744 \ubd84\ub9ac\ud558\uc600\ub2e4. \uadf8\ub9ac\uace0 \ub780\uc96c\ubc18 \uc9c4\ub3d9\uc790\uc640 \ud0c4\uc131\uccb4\ub97c \ubcfc\ud2b8\ub85c \uacb0\ud569\ud55c \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\uc640 \uc6d0\ubfd4 \ud615\ud0dc\uc758 \ud63c \uc704\uc5d0 \uc774\ub3d9\uc790\uc640\uc758 \uc811\ucd09\ubd80\uc778 \uc54c\ub8e8\ubbf8\ub098 \ud301\uc774 \uc788\ub2e4. \uc54c \ub8e8\ubbf8\ub098 \ud301\uc740 \ub9c8\ucc30\uc5d0 \ub530\ub978 \ub9c8\ubaa8\ud604\uc0c1\uc744 \uc904\uc774\uae30 \uc704\ud558\uc5ec \uc0ac\uc6a9\ub418\uc5c8\uace0 \uc774 \ud301\uc5d0\uc11c\uc758 \ud0c0\uc6d0\uc6b4\ub3d9\uc744 \ud1b5\ud558\uc5ec \uc774\ub3d9\uc790\uc758 \uc120\ud615\uc6b4\ub3d9\uc744 \uac00\ub2a5\ud558\uac8c \ud55c\ub2e4. \uc124\uacc4\ub41c \uc804\ubc29\ud5a5\uc131 \uc120\ud615 \uc555\uc804 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \ub192\uc774\ub294 \uc57d 50 mm, \uc9c1\uacbd\uc740 20 mm \uc774\uace0 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \uac00\uc6b4\ub370\uc5d0\ub294 \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4 \ub450 \uac1c\uac00 \uc0bd\uc785 \ub418\uc5b4 \uc788\ub2e4.\nA1 1 d e33 S c \u03c52 \u03c50\u2044\u22c5 \u22c5 \u22c5\u2044=\n\u03c51 \u03c50 k1cos l1=\n\u03c52 \u03c50 k2cos x2 k1cos x1 Z1 Z2\u2044( ) k1l1sin k2x2tan\u22c5\u2013{ }=\n\u03c53 \u03c52 k3cos x3 1 Z2 Z3\u2044( ) [ \u22c5\u2013=\nk1l2 Z1 Z2\u2044( )k1l1+{ } k3x3]tan\u22c5tan\n\u03be0 \u03c50 \u03c90 2\u2044\u2044 0.033 10 6\u2013 \u00d7= =\n2", + "\u2212 187 \u2212 J. Kor. Sensors Soc., Vol. 18, No. 3, 2009\n\uc804\ubc29\ud5a5\uc131 \uc120\ud615 \uc555\uc804 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \uc124\uacc4\uc640 \ubd84\uc11d\n\uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\ub97c \ub3d9\uc77c\ud55c \ud06c\uae30\ub85c \ubd84\ud560\ud55c 4\uac1c\uc758 \uc804\uadf9 \uacfc \uc561\ucd94\uc5d0\uc774\ud130 \uad6c\ub3d9\uc744 \uc704\ud55c \uc785\ub825\uc2e0\ud638\ub97c \ubcf4\uc5ec\uc900\ub2e4. \uc774 \uc804\ubc29\ud5a5\uc131 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \uad6c\ub3d9\uc740 \ub450\uac1c\uc758 \uc804\uadf9\uc5d0 \uc815\ud604\ud30c \ub97c \uc778\uac00\ud558\uace0 \ub098\uba38\uc9c0 \ub450 \uac1c\uc758 \uc804\uadf9\uc5d0\ub294 \uc5ec\ud604\ud30c\ub97c \uc778\uac00 \ud558\uc5ec \uad6c\ub3d9\ub418\uba70 \ub450 \uac1c\uc758 \uc815\ud604\ud30c\uc640 \ub450 \uac1c\uc758 \uc5ec\ud604\ud30c\uc758 \uc870 \ud569\uc744 \ud1b5\ud558\uc5ec x, -x, y, \uadf8\ub9ac\uace0 -y \ubc29\ud5a5\uc73c\ub85c \uad6c\ub3d9\ud560 \uc218 \uc788\ub2e4.\n3. \uc2e4\ud5d8 \ubc0f \uace0\ucc30\n\ubcf8 \uc5f0\uad6c\uc5d0\uc11c\ub294 \uc720\ud55c\uc694\uc18c\ubc95(finite element method : FEM)\uc744 \uc774\uc6a9\ud55c \uc2dc\ubbac\ub808\uc774\uc158 \ud504\ub85c\uadf8\ub7a8 ATILA(Adaptronics Inc., US)\ub97c \uc774\uc6a9\ud558\uc600\uace0 \uc870\ud654 \ubd84\uc11d(harmonic analysis)\uc744 \ud1b5\ud574 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \uacf5\uc9c4\uc8fc\ud30c\uc218\uc640 \uc5b4\ub4dc\ubbf8\ud134 \uc2a4 \ud2b9\uc131, \uacf5\uc9c4 \ubaa8\ub4dc\uc5d0 \ub530\ub978 \ubcc0\uc704\ub7c9\uc744 \ubd84\uc11d\ud558\uc600\ub2e4.[11-12] Fig. 3\uc740 40~100 kHz \uae4c\uc9c0\uc758 \uc870\ud654 \ubd84\uc11d\uc744 \ud1b5\ud55c \uc5b4\ub4dc\ubbf8 \ud134\uc2a4 \ud2b9\uc131\uacfc \uacf5\uc9c4 \uc601\uc5ed\uc5d0\uc11c\uc758 \uc6c0\uc9c1\uc784\uc744 \ubcf4\uc5ec\uc900\ub2e4.\nFig. 2\uc5d0\uc11c\uc640 \uac19\uc774 4\uac1c\uc758 \uc804\uadf9 \uc911 \ub450 \uac1c\uc758 \uc804\uadf9\uc5d0\ub294\n1\ubcfc\ud2b8\uc758 \uc0ac\uc778\ud30c\ub97c \ub098\uba38\uc9c0 2\uac1c\uc758 \uc804\uadf9\uc740 1\ubcfc\ud2b8\uc758 \ucf54\uc0ac \uc778\ud30c\ub97c \uc785\ub825\uc73c\ub85c \ud558\uc600\uc73c\uba70 \uac01 \uacf5\uc9c4 \uc601\uc5ed\uc5d0\uc11c \uc54c\ub8e8\ubbf8\ub098 \ud301\uc758 \uc6c0\uc9c1\uc784\uc744 \ud655\uc778\ud558\uc600\ub2e4. \uc774\ub860\uc801\uc778 \uacb0\uacfc\uc640 \ube44\uc2b7\ud558\uac8c 62.2 kHz \uc5d0\uc11c\uc758 \ubcc0\uc704\ub294 \uc57d 32.5 nm\uc758 \uacb0\uacfc\ub97c \uc5bb\uc5c8\ub2e4. \uadf8\ub7ec\ub098 \uac01 \uacf5\uc9c4\uc601\uc5ed\uc5d0\uc11c\ub294 \ud6a1\uc9c4\ub3d9\uc774\ub098 \uc885\uc9c4\ub3d9 \uc6b4\ub3d9\ub9cc \uc744 \ubcf4\uc600\uc73c\uba70 \uc120\ud615\uc6b4\ub3d9\uc744 \uc704\ud574\uc11c\ub294 \ud0c0\uc6d0 \uc6b4\ub3d9\uc774 \ud544\uc694\ud558 \ub2e4. \ub530\ub77c\uc11c \uc885\uc9c4\ub3d9\uacfc \ud6a1\uc9c4\ub3d9 \uc0ac\uc774\uc5d0\uc11c\uc758 \uc8fc\ud30c\uc218\ub4e4\uc778 59.5, 60.5, 61. 25, \uadf8\ub9ac\uace0 63.25 kHz\uc5d0\uc11c \uc2dc\ubbac\ub808\uc774\uc158 \ud558\uc600\uace0 \uadf8 \uacb0\uacfc\ub294 Fig. 4\uc640 \uac19\ub2e4.\n\uc774\ub860\uc801 \uacb0\uacfc\uc640 \uac19\uc774 \uc885\uc9c4\ub3d9\uacfc \ud6a1\uc9c4\ub3d9 \uc0ac\uc774 \uc8fc\ud30c\uc218\ub4e4 \uc740 \ucd5c\ub300 5 nm \uc815\ub3c4\uc758 \ud0c0\uc6d0 \uc6b4\ub3d9\uc744 \uc5bb\uc5c8\ub2e4. \ub9c8\uc9c0\ub9c9\uc73c\ub85c \uc561\ucd94\uc5d0\uc774\ud130\uc758 \uc804\ubc29\ud5a5\uc131\uc744 \ud655\uc778\ud558\uae30 \uc704\ud558\uc5ec Fig. 5\uc640 \uac19 \uc740 \uc785\ub825 \uc2e0\ud638\uc758 \uc870\ud569\uc5d0 \ub530\ub978 \uc561\ucd94\uc5d0\uc774\ud130\uc758 \ubc29\ud5a5 \uc804\ud658 \uc744 \ud655\uc778\ud558\uc600\ub2e4. Fig. 5(a)\ub294 Fig. 3\uc758 \uc555\uc804 \uc138\ub77c\ubbf9\uc2a4\uc5d0 \ubcf4\uc5ec\uc900 \uac83\uacfc \uac19\uc774 \uc785\ub825\uc2e0\ud638\uac00 \uc778\uac00\ub418\uc5c8\uc744 \ub54c\uc758 \uacb0\uacfc\ub85c x\uc640 z \ubc29\ud5a5\uc758 \ubcc0\uc704\ub9cc\uc744 \uac00\uc9c0\uba70 Fig. 5(b)\ub294 \uc0ac\uc778\uc2e0\ud638\ub97c \uc704\ucabd\uc73c\ub85c \ucf54\uc0ac\uc778 \uc2e0\ud638\ub97c \uc544\ub798\uc758 \uc804\uadf9\uc5d0 \uc785\ub825\ud558\uc600\uc744 \ub54c \uc758 \uacb0\uacfc\ub85c y\uc640 z \ubc29\ud5a5\uc758 \ubcc0\uc704\ub9cc\uc744 \uac16\ub294\ub2e4.\n\ub530\ub77c\uc11c, \ubcf8 \ub17c\ubb38\uc5d0\uc11c \uc81c\uc548\ub41c \uc804\ubc29\ud5a5\uc131 \uc561\ucd94\uc5d0\uc774\ud130\ub294\n3", + "\uc13c\uc11c\ud559\ud68c\uc9c0 \uc81c18\uad8c \uc81c3\ud638, 2009 \u2212 188 \u2212\n\uc815\uc6b0\uc11d\u00b7\uac15\uc885\uc724\u00b7\uae40\uc815\ub3c4\u00b7\ubc31\ub3d9\uc218\u00b7\uc870\ubd09\ud76c\u00b7\uae40\uc601\ud638\u00b7\uc724\uc11d\uc9c4\n\uacf5\uc9c4 \uc8fc\ud30c\uc218\uc5d0\uc11c \ubc1c\uc0dd\ub418\ub294 \ud6a1\uc9c4\ub3d9 \ubaa8\ub4dc\uc640 \uc885\uc9c4\ub3d9 \ubaa8\ub4dc \uc0ac\uc774\uc758 \uc8fc\ud30c\uc218\ub97c \ud1b5\ud574 \uc120\ud615\uc6b4\ub3d9\uc774 \uac00\ub2a5\ud55c \ud0c0\uc6d0 \uada4\uc801\uc744 \uc0dd\uc131\ud558\uc600\uace0 \uc0ac\uc778\ud30c\uc640 \ucf54\uc0ac\uc778\ud30c\uc758 \uc870\ud569\uc744 \ud1b5\ud574 \ubc29\ud5a5 \uc804 \ud658\uc774 \uac00\ub2a5\ud55c \uc804\ubc29\ud5a5\uc131 \uc555\uc804 \uc561\ucd94\uc5d0\uc774\ud130\uc784\uc744 \ubcf4\uc5ec\uc8fc\uace0 \uc788\ub2e4.\n4. \uacb0 \ub860\n\ubcf8 \ub17c\ubb38\uc5d0\uc11c\ub294 \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\ub97c \uc774\uc6a9\ud55c \uc804\ubc29\ud5a5\uc131 \uc120 \ud615 \uc555\uc804 \uc561\ucd94\uc5d0\uc774\ud130\uc5d0 \uad00\ud558\uc5ec \ub098\ud0c0\ub0b4\uc5c8\ub2e4. \uc555\uc804\uccb4\uc758 \ud30c \ub3d9 \ubc29\uc815\uc2dd\uacfc \uc124\uacc4\ub41c \ubc18\ud30c\uc7a5 \uc9c4\ub3d9\uc790\uc758 \uad6c\uac04\ubcc4 \uc9c4\ub3d9 \uc18d \ub3c4 \ub4f1\uc744 \uacc4\uc0b0\ud558\uc5ec \uc774\ub3d9\uc790\uc640 \uc811\ucd09\ubd80\uc778 \ud301\uc5d0\uc11c \uc57d 33 nm \uc758 \ubcc0\uc704\ub97c \ud655\uc778\ud558\uc600\ub2e4.\n\uc124\uacc4\ub41c \uc561\ucd94\uc5d0\uc774\ud130\ub97c \uc555\uc804 \uc804\uc6a9 \uc2dc\ubbac\ub808\uc774\uc158 \ud234\uc778 ATILA\ub97c \uc774\uc6a9\ud558\uc5ec \uc8fc\ud30c\uc218\uc5d0 \ub530\ub978 \uc5b4\ub4dc\ubbf8\ud134\uc2a4 \ud2b9\uc131\uc744 \ud655\uc778\ud558\uc600\uace0 \uacf5\uc9c4\uc601\uc5ed\uc5d0\uc11c \uc885\uc9c4\ub3d9 \ub610\ub294 \ud6a1\uc9c4\ub3d9\uc744 \ud558\uc600 \uc73c\uba70 \uc774\ub54c\uc758 \ubcc0\uc704\ub294 32.5 nm\ub85c \uc774\ub860\uc801 \uacc4\uc0b0 \uacb0\uacfc\uc640 \uac70 \uc758 \uc77c\uce58\ud558\uc600\ub2e4. \uadf8\ub7ec\ub098 \uc81c\uc548\ub41c \uc561\ucd94\uc5d0\uc774\ud130\uc758 \uc120\ud615\uc6b4\ub3d9 \uc744 \uc704\ud574\uc11c\ub294 \uc811\ucd09\ubd80\uc5d0\uc11c\uc758 \ud0c0\uc6d0 \uc6b4\ub3d9\uc774 \uc694\uad6c\ub418\uae30 \ub54c\ubb38 \uc5d0 \uc885\uc9c4\ub3d9\uacfc \ud6a1\uc9c4\ub3d9 \uc0ac\uc774\uc758 \uc8fc\ud30c\uc218\uc5d0\uc11c \uc2dc\ubbac\ub808\uc774\uc158 \ud558 \uc600\uc73c\uba70 \ucd5c\ub300 \ubcc0\uc704 5 nm\uc758 \ud0c0\uc6d0 \uc6b4\ub3d9\uc744 \ud655\uc778\ud558\uc600\ub2e4. \ub610 \ud55c, \uc555\uc804\uccb4\uc758 \uc804\uadf9\ub4e4\uc5d0 \uc0ac\uc778\ud30c\uc640 \ucf54\uc0ac\uc778\ud30c\ub97c \uc870\ud569\ud558\uc5ec \uc778\uac00\ud568\uc73c\ub85c\uc368 \uc6d0\ud558\ub294 \ubc29\ud5a5\uc73c\ub85c \uc81c\uc5b4\uac00 \uac00\ub2a5\ud558\uc600\ub2e4.\n\ucc38\uace0 \ubb38\ud5cc\n[1] D. Mazeika, P. Vasiljev, G. Kulvietis, and J. Tiskev-\nicius, \u201cDevelopment of new type linear piezoelectric actuator using traveling wave\u201d, 5th International Workshop on Piezoelectric Materials and Application in Actuators, 2008.\n[2] E. Purwanto and S. Toyama, \u201cControl method of a\nspherical ultrasonic motor\u201d, AIM, IEEE/ASME International Conference, vol. 2, pp. 1321-1326, 2003. [3] J, Wang, K, Mitchell, W. Jewell, and D. Howe,\n\u201cMulti-degree-of-freedom spherical permanent magnet motors\u201d, Robotics and Automation, ICRA 01, vol. 2, pp. 1798-1805, 2001. [4] K. Takemura, D. Harada, and T. Maeno, \u201cControl of\nmulti-DOF ultrasonic motor using neural network based inverse model\u201d, Intelligent robots and system, vol. 2, pp. 2187-2192, 2002. [5] \uae40\uc815\uc21c, \uae40\ubb34\uc900, \ud558\uac15\ub82c, \u201c\uc555\uc804 \ud6a1\ud6a8\uacfc\ub97c \uc774\uc6a9\ud55c \ubb34\uc9c0\n\ud5a5\uc131 \uc8fc\ud30c\uc218\uac00\ubcc0 \ucd08\uc74c\ud30c\ud2b8\ub79c\uc2a4\ub4c0\uc11c\u201d, \uc13c\uc11c\ud559\ud68c\uc9c0, \uc81c 13\uad8c, \uc81c6\ud638, pp. 417-423, 2004. [6] S. Ueha and Y. Tomikawa, Ulrasonic Motors - The-\nory and Applications, 1993.\n[7] T. Sashida and T. kenjo, An Introduction to ultrasonic\nmotors, Oxford, U.K. : Clarendon, pp. 6-8, 1993.\n[8] Kenji Uchino, Piezoelectric Actuators and Ultra-\nsonic Motors, pp. 154-196, 1997.\n[9] Kenji Uchino, \uc555\uc804\u00b7\uc804\uc65c\uc138\ub77c\ubbf9\uc2a4 -\uc6d0\ub9ac\uc640 \uc751\uc6a9 \uc2e4\n\ub840-, 1985.\n[10] E, Zauderr, Partial Differential Equations of\nApplied Mathmatics, New York wiley, 1989.\n[11] E. heinonen, J. Juuti, and S. Leppavuori, \u201cCharac-\nterization and modelling of 3D piezoelectric ceramic structures with ATILA software\u201d, J. European Ceramic Society, vol. 25, no. 12, pp. 2467- 2470, 2005. [12] \uace0\ud604\ud544, \uac15\uc885\uc724, \uc724\uc11d\uc9c4, \u201cATILA\ub97c \uc774\uc6a9\ud55c \uc18c\ud615 \uc120\n\ud615 \uc555\uc804 \ubaa8\ud130\uc758 \uc124\uacc4\u201d, \uc804\uae30\uc804\uc790\uc7ac\ub8cc\ud559\ud68c\uc9c0, \uc81c18\uad8c, \uc81c12\ud638, pp. 18-26, 2005.\n4\n\uc815 \uc6b0 \uc11d\n\u2022 2009\ub144 \ud638\uc11c\ub300\ud559\uad50 \uc804\uc790\uacf5\ud559\uacfc \uc878\uc5c5(\uacf5\n\ud559\ubc15\uc0ac)\n\u2022 2007\ub144~2009\ub144 \ud55c\uad6d\uacfc\ud559\uae30\uc220\uc5f0\uad6c\uc6d0 \ud559\n\uc0dd \uc5f0\uad6c\uc6d0\n\u2022 2009\ub144~\ud604\uc7ac \ud55c\uad6d\uacfc\ud559\uae30\uc220\uc5f0\uad6c\uc6d0 \uc778\ud134\n\uc5f0\uad6c\uc6d0\n\u2022\uc8fc\uad00\uc2ec\ubd84\uc57c: \ucd08\uc74c\ud30c \uc561\ucd94\uc5d0\uc774\ud130 \ubc0f \uad6c\ub3d9\n\ub4dc\ub77c\uc774\ubc84 \uac1c\ubc1c, \uc13c\uc11c \ub124\ud2b8\uc6cd, \uc5d0\ub108\uc9c0 \ud558 \ubca0\uc2a4\ud305\n\uac15 \uc885 \uc724\n\u2022 2000\ub144 \uc5f0\uc138\ub300\ud559\uad50 \uc804\uae30\ucef4\ud4e8\ud130\uacf5\ud559\uacfc \uc878\n\uc5c5(\uacf5\ud559\ubc15\uc0ac)\n\u2022 2002\ub144~2004\ub144 The University of\nBirmingham, Post-doc.\n\u2022 2000\ub144~\ud604\uc7ac \ud55c\uad6d\uacfc\ud559\uae30\uc220\uc5f0\uad6c\uc6d0 \ubc15\ub9c9\n\uc7ac\ub8cc\uc5f0\uad6c\uc13c\ud130 \ucc45\uc784\uc5f0\uad6c\uc6d0\n\u2022\uc8fc\uad00\uc2ec\ubd84\uc57c: \uc555\uc804 \uc5d1\uce04\uc5d0\uc774\ud130, \ub9c8\uc774\ud06c\ub85c\n\ud30c \uc18c\uc790, \ub9c8\uc774\ud06c\ub85c\ud30c \uac15\uc720\uc804\uccb4" + ] + }, + { + "image_filename": "designv8_17_0002324_e_download_2470_2477-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002324_e_download_2470_2477-Figure3-1.png", + "caption": "Figure 3 Design of Rim for RDP in 3D (left) and real (right)", + "texts": [], + "surrounding_texts": [ + "To solve the problem in this research researcher will make prototype to be simulated with open water test method. The step researcher take is: 1. Problem Identification 2. Study of literature 3. Collecting Data 4. Design Prototype of Propeller 5. Simulation 6. Data analysis and Discussion 7. Conclusion and Recommendation" + ] + }, + { + "image_filename": "designv8_17_0000796_wnload_185038_184674-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000796_wnload_185038_184674-Figure1-1.png", + "caption": "Fig. 1. The scheme of the surface of the plow body and the slope function of the projection of", + "texts": [ + " The coordinate system Oxyz is chosen such that the axis Ox is directed opposite to the movement of the plow body, the axis Oy is located in the horizontal plane and the axis is vertical. With this arrangement of the surface, the angle of projection of the genera on the horizontal plane of projections Oxy is denoted by \u03b3 the angle of projection of the genera to the axis Ox on the vertically longitudinal plane through \u03b2 . Surface diagram and function graphs ( ) ( )a x tg x\u03b3= \u0442\u0430 ( ) ( )b x tg x\u03b2= are presented in Fig. 1. Logarithmic spirals were adopted as the guide curves 1 1 1 01 wr r e \u03d5= end 2 2 2 02 wr r e \u03d5= , where 1r , 2r \u2014 the current radius vectors of the guide curves; 01r , 02r \u2014 the initial radius vectors of the guide curves (1), (2); 1w , 2w \u2014 tangents of angles between the current radius vector and the tangent; \u03d5 parameter, namely the polar angle of rotation of the radius of the vector. The coordinate is programmed in the radians of the polar angle 1\u03d5 . Agro-technical assessment of the quality of work of plows with standard cultural and semiscrew shelves of buildings was carried out on the percentage of plowing of crop residues" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001133_f_version_1569401418-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001133_f_version_1569401418-Figure6-1.png", + "caption": "Figure 6. The attitude relation of the coordinate system on the left/right track.", + "texts": [ + " (29) The relative posture relations of T1 and T0 cannot directly reflect the posture relations of both sides of the track. For this reason, the coordinate system TL1 is established on the left track of the transition curve corresponding to the center line coordinate system T1, and the coordinate system TR1 is established on the right track. The characteristics of the transition curve determine that the origins of TR1 and TL1 are located on the y-axis of the T1 coordinate system, and the distance from the origin of T1 is, respectively, \u00b1 1 2 D (D is gauge). The coordinate system is shown in Figure 6. As for attitude, the x-axis of TR1 is along the tangent direction of the right side rail and the x-axis of TL1 is along the tangent direction of the left side rail. There is an angle between them and the x-axis of T1. The spatial relationship is shown in Figure 5. The angle \u03b3 can be approximated to the ratio between the track super high h and the mileage s: \u03b3 = h sT1 = D 2 sin \u03b81 sT1 \u2248 D 2 \u03b81 sT1 = D 2 \u03b80sT1 S0 sT1 = D\u03b80 2S0 . (30) When the parameters of the transition curve are determined, h is a constant" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000735_XXIX-B1-479-2012.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000735_XXIX-B1-479-2012.pdf-Figure9-1.png", + "caption": "Figure 9 The relationship between INS and camera", + "texts": [ + " In the aspect of the lever arm calibration, the perspective position of each image ( ) is exactly known after the bundle adjustment, and the calculation about the INS/GNSS position vector ( ) is conducted by the interpolation at the same time. Then the lever arms ( ) can be solved by the following equation (Li, 2010): (1) In the aspect of the boresight calibration, the rotation matrix between the camera frame and the mapping frame of each image ( ) is also obtained from the bundle adjustment results, and the rotation matrix between the body frame and mapping frame of each image can be measured by INS. The relationship is shown in Figure 9. Eventually, the rotation matrix ( ) can be calculated by the matrix multiplication (Li, 2010): (2) From those equations, the accuracy of the calibration is dominated by the quality of the INS/GNSS POS data and the bundle adjustment results. This relationship also affects DG of the MMS indirectly. In this case, the distribution of the control points in the image and the quality of the INS/GNSS data are very important in the calibration. The calibration result of the proposed MMS Van is shown in Table 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000788_tation-pdf-url_48757-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000788_tation-pdf-url_48757-Figure1-1.png", + "caption": "Figure 1. Schematic diagram showing ribbon preparation by single roller melt spinning technique and ribbon-wheel sticking distance at adhesion times t1, t2 and t3 [1].", + "texts": [ + " In this chapter, the processing of different soft magnetic alloys through rapid solidification has been discussed, and the alloys are categorized according to their properties and applications. Amongst different rapid solidification processing routes, melt spinning is the most common technique for yielding soft magnetic metallic ribbons in large quantity. Sometimes this technique is also described as chill block melt spinning (CBMS). Basically, the ribbons are synthesized as the stream of molten alloy from a quartz crucible is purged through argon gas pressure on a rapidly rotating wheel made from the metals like pure Cu, Cu-Be alloy and stainless steel (Fig. 1). As shown in Fig. 1, the ribbon is typically maintaining a contact of sticking distance (dt1 rF (27) Furthermore, the limit range of the addendum coefficient and dedendum coefficient of the gear pair can be given according to Equation (27): 0 < h\u2217a1 \u2264 h\u2217f 2 h\u2217a1 < min(rE ,rG\u2032)\u2212r1 m 0 < h\u2217a2 \u2264 h\u2217f 1 < r1\u2212rF m (28) 3.1.2. Tooth Profile Angle Tooth profile angle \u03b2 refers to the included angle between the linear tooth profile and the symmetrical center line of the external gear, which directly determines the shape of the linear tooth profile and is an important parameter affecting the meshing characteristics of the gear pair. As shown in Figure 5a, the intersection H of the linear tooth profile and the reference circle of the external gear is fixed. With the increase of tooth profile angle \u03b2, the corresponding tooth profiles of the addendum circle and dedendum circle of the external gear decrease. When the tooth profile angle reaches \u03b21, the dedendum circle will disappear. According to the geometric relationship, the following can be obtained:{ h = r1 sin(\u03b21 + \u03b8/2) h = r f 1 sin(\u03b21 + \u03c0/z1) (29) The following can be calculated from Equation (29): \u03b21 = arctan r f 1 sin(\u03c0/z1)\u2212 r1 sin(\u03b8/2) r1 cos(\u03b8/2)\u2212 r f 1 cos(\u03c0/z1) (30) When the tooth angle reaches \u03b22, the addendum circle will disappear", + " According to the geometric relationship, the following can be calculated ra1 sin(\u03c0 \u2212 \u03b8/2\u2212 \u03b22) = r1 sin \u03b22 (31) The following can be calculated from Equation (31): \u03b22 = arctan r1 sin(\u03b8/2) ra1 \u2212 r1 cos(\u03b8/2) (32) The size of \u03b21 and \u03b22 is determined by specific design parameters. The disappearance of the addendum circle or dedendum circle will lead to the design failure of the external gear. Therefore, the maximum tooth profile angle \u03b2max should be selected as the smaller value of \u03b21 and \u03b22, namely: \u03b2max = min(\u03b21, \u03b22) (33) As shown in Figure 5b, it is assumed that the meshing point of the gear pair is at the vertex B of the linear tooth profile. As the tooth profile angle \u03b2 decreases, the point B moves to the right along the addendum circle, and the normal line through point B intersects the pitch circle at the pitch point P. According to the meshing principle, when segment PB\u2032 is tangent to the pitch circle, the tooth profile angle reaches the minimum value \u03b2min. With the further reduction of the tooth profile angle, the tooth profile at the addendum of the tooth will exceed the meshing boundary point without the conjugate tooth profile" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003708_19_ms-10-47-2019.pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003708_19_ms-10-47-2019.pdf-Figure6-1.png", + "caption": "Figure 6. Experimental setups of MBCDM: (a) prototype of the MBCDM; (b) driving capability test; (c) transmission backlash test.", + "texts": [ + " By increasing the preload force, the system could achieve lower transmission Mech. Sci., 10, 47\u201356, 2019 www.mech-sci.net/10/47/2019/ backlash, but the rate of decrease is reduced. It is necessary to find the threshold value of preload force to keep the backlash in a stable state. The results of the parameter sensitivities provide some suggestions about optimizing the transmission characteristics. In order to validate the proposed design and performance analysis methods, a prototype of the designed MBCDM has been constructed, as shown in Fig. 6a. All components are assembled together carefully and the MBCDM possesses a compact structure and light weight with 342g. The experimental system mainly consists of the MBCDM, torque sensor (Kistler 9349A, with measuring range of \u00b130 Nm), optical encoder A (AEDA-3300TBN, with resolution of 191.74 \u00b5rad), optical encoder B (HEIDENHAIN RON285, with resolution of 1.364 \u00b5rad), inertial plate, torque motor, magnetic powder brake, and dSPACE1103 semi-physical simulation system. The optical encoder A and the optical encoder B are used to obtain the rotational displacement of input and output shaft, respectively. The torque sensor is uti- lized to measure the real-time torque on the shaft. The inertial plate is mounted on the test apparatus to simulate the mass unbalances. The torque motor is installed at one end to test the driving capability of the MBCDM, as shown in Fig. 6b. The transmission backlash would be tested when the torque motor is replaced by the magnetic powder brake, as shown in Fig. 6c. A dSPACE system (DS-1103) is utilized to decode the feedback signals and generate real-time codes for such a system. To test the driving capability of the MBCDM, the torque motor is installed at one end, as shown in Fig. 6b. The MBCDM system works in the position closed-loop mode. Meanwhile, the torque motor gives a low slope ramp signal on the condition of open loop. Figure 7 shows the time history of realtime output torque measured by the torque sensor. The maximum output torque is about 3.3 N\u00d7m, which is slightly less than the theoretical value of 3.9 N\u00d7m. The reasons include the preload is hard to reach the designed value and the synchronous control problems of the dual motors. It would be www.mech-sci.net/10/47/2019/ Mech", + " The reasons for ripple torque of precise cable drive are plentiful, such as repetitive contact, load variation and DC current offset from the motor. Figure 8b shows the spatial frequency spectrum of the angular response error. The highest peak is measured at 694.3 cycle rad\u22121 with the amplitude of 24.67 \u00b5rad. It shows that the ripple torque in MBCDM is a function of the rotational displacement. The effect could be modeled and suppressed to improve the position control accuracy. The magnetic powder brake is installed to test the transmission backlash of the MBCDM, as shown in Fig. 6c. In order to keep the pulleys in quasi-static condition to avoid the cable vibration due to resonance, the MBCDM is excited by a sinusoidal signal of frequency of 0.1 Hz and amplitude of 50 mrad in position closed-loop control mode. Transmission error could be calculated by Eq. (2), with the real-time rotational displacement of input and output shaft from optical encoder A and B. Figure 9a shows that the external torque and transmission error undergo a sudden change simultaneously. Transmission backlash is defined as the amount of the abrupt variation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002098__icssf2024_02007.pdf-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002098__icssf2024_02007.pdf-Figure7-1.png", + "caption": "Fig. 7. Peeler machine, breaking and separator dry soybean husk based on electric blower technology.", + "texts": [ + " When soybeans are placed in the machine, an automatic mechanism (peeling, splitting, and separating) begins to remove the dry soybean skin. As they enter the machine, the soybeans rotate, rubbing against the curved edges of the roller, which causes the soybeans to peel and split. Through the pipe of the separator, the broken soybeans enter and exit. With the use of a blower, the soybean epidermis is blown, and the soybeans with a heavier mass will fall into the reservoir. The design results of the machine can be seen in Figure 7. The same kind of soybean was used in three separate tests on the soybean machine [11]. The following data were calculated for this test's results: 1) Testing of engine capacity calculation. Therefore, the average yield from a peeler, splitter, and separator for dry soybean husk employing electric blower technology is 213,048 kg/hour. 2) Using a machine to determine the success rate of stripping. blower technology to get results 74.03%. 3) Calculation of the efficiency of testing the epidermis blown by the blower percentage was 83" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002045_nkhair2021_07004.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002045_nkhair2021_07004.pdf-Figure4-1.png", + "caption": "Fig. 4. Side View of Rice Transport Vehicle Chassis", + "texts": [], + "surrounding_texts": [ + "Chassis design with specifications chassis length 6000mm, chassis width 2500mm, using AISI 1018 steel material, rectangular model with dimensions 120x80x3mm. The Von Mises stress value for AISI 1018 106 HR steel material is 29.06 MPa for the standard mesh, 28.6 MPa for the 10 mm control mesh and 28.15 MPa. The displacement value for AISI 1018 106 HR steel material is 0.3643 mm for the standard grid, 0.3704 mm for the 10 mm control grid and 0.3764 mm for the 5 mm control grid. The safety factor for AISI 1018 106 HR steel material is 9.32 for the standard fabric, 9.45 for the 10 mm control fabric and 9.58 for the control fabric." + ] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure1.15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure1.15-1.png", + "caption": "Figure 1.15. MacPherson strut IFS [55].", + "texts": [ + " This amounted to allowing each \u201chalf\u201d of the axle to swing independently, Figure 1.12. Some designs of this type were even employed as rear suspensions, and used the drive axle as one of the arms. The design favored by GM was the double wishbone, also known as the short-long-arm (SLA), seen in Figure 1.13. In addition to leaf springs and coil springs, torsion springs were also in use. An example can be seen in Figure 1.14. In this figure, there is also a hydraulic shock absorber. As the century went along, the MacPherson strut suspension, Figure 1.15, introduced in the late 1940s, became an increasingly popular IFS. This was due to its relatively few number of components, especially when the spring is placed over the strut, and its ability to provide a steer DOF. The rack and pinion steering system, seen in Figure 1.2, in use in Europe by the 1930s, found its way to American cars in the 1970s. While the shimmy problem and styling demands led to the almost total extinction of the traditional front axle in favor of the double wishbone and MacPherson suspensions, there was no similarly urgent reason to discard the rear axle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002418__32_5_32_32_456__pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002418__32_5_32_32_456__pdf-Figure9-1.png", + "caption": "Fig. 9 Grip force measured by force sensors", + "texts": [], + "surrounding_texts": [ + "\u660e\u3059\u308b\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306f\uff0c\u7b4b\u53ce\u7e2e\u306b\u3088\u308a\u6307\u304c\u958b\u304d\uff0c\u7b4b\u53ce\u7e2e\u3057\u306a\u3044 \u5834\u5408\u306f\u9589\u3058\u308b\u65b9\u5f0f\u306b\u306a\u3063\u3066\u3044\u308b\uff0e\u3059\u306a\u308f\u3061\uff0c\u80fd\u52d5\u30d5\u30c3\u30af\u306b\u304a\u3044\u3066 \u30cf\u30fc\u30cd\u30b9\u3092\u4ecb\u3057\u3066\u30b1\u30fc\u30d6\u30eb\u3092\u727d\u5f15\u3059\u308b\u3068\u6307\u304c\u958b\u304f\u30dc\u30e9\u30f3\u30bf\u30ea\u30fc \u30aa\u30fc\u30d7\u30f3\u3068\u540c\u69d8\u306e\u65b9\u5f0f\u3067\u3042\u308b\uff0e\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306f\u30cf\u30f3\u30c9\u306b\u5185\u8535\u3057 \u305f\u30de\u30a4\u30b3\u30f3\uff08Arduino Pro Mini\uff09\u306b\u5b9f\u88c5\u3057\u3066\u3044\u308b\uff0e\u8ddd\u96e2\u30bb\u30f3 \u30b5\u306f\u30de\u30a4\u30b3\u30f3\u306b\u63a5\u7d9a\u3055\u308c\uff0c\u30de\u30a4\u30b3\u30f3\u5185\u8535\u306e AD\u5909\u63db\u6a5f\u80fd\u306b\u3088\u3063 \u3066\uff0c\u30b5\u30f3\u30d7\u30ea\u30f3\u30b0\u5468\u6ce2\u6570 100 [Hz] \u3067\u30b5\u30f3\u30d7\u30ea\u30f3\u30b0\u3059\u308b\uff0e\u30b5\u30f3 \u30d7\u30ea\u30f3\u30b0\u3057\u305f\u5024\u306f\u73fe\u5728\u5024 x(n) \u3068\u904e\u53bb 9 \u70b9\uff0c\u5168 10 \u70b9\u306e\u5358\u7d14\u79fb \u52d5\u5e73\u5747\u306b\u3088\u308a\u5e73\u6ed1\u5316\u3055\u308c\u308b\uff0e\u3053\u3053\u3067\uff0cn \u70b9\u3081\u306e\u5e73\u6ed1\u5316\u5f8c\u306e\u5024\u3092 xs(n)(n = 0, \u00b7 \u00b7 \u00b7 , N) \u3068\u3059\u308b\uff0e \u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306e\u51e6\u7406\u306e\u6d41\u308c\u3092 Fig. 7\u306b\u793a\u3059\uff0e\u307e\u305a\uff0c\u64cd\u4f5c\u3092\u884c \u3046\u524d\u306b\u30e6\u30fc\u30b6\u306b\u5408\u308f\u305b\u3066\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u3092\u884c\u3046\uff0e\u30cf\u30f3\u30c9\u672c \u4f53\u306e\u30b9\u30a4\u30c3\u30c1\u3092\u9577\u62bc\u3057\u3059\u308b\u3068\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u958b\u59cb\u3055\u308c\u308b\uff0e \u306f\u3058\u3081\u306b\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u524d\u8155\u306b\u88c5\u7740\u3057\u305f\u72b6\u614b\u3067\u30b9\u30a4\u30c3\u30c1\u3092\u62bc\u3057\uff0c \u7b4b\u53ce\u7e2e\u3057\u3066\u3044\u306a\u3044\u5e73\u5e38\u6642\u306e\u30bb\u30f3\u30b5\u5024\u3092 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3057\uff0c \u305d\u306e\u5e73\u5747\u5024 Xrest \u3092\u8a08\u7b97\u3059\u308b\uff0e\u6b21\u306b\uff0c\u6700\u5927\u306b\u7b4b\u53ce\u7e2e\u3057\u305f\u72b6\u614b\u3067 \u30b9\u30a4\u30c3\u30c1\u3092\u518d\u5ea6\u62bc\u3059\u3068\uff0c\u30bb\u30f3\u30b5\u5024\u304c 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3055\u308c\uff0c \u305d\u306e\u5e73\u5747\u5024 Xmax \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e\u6b21\u306b\uff0cXmax \u3068 Xrest \u306e\u5dee\u5206 Xdif \u3092\u6b21\u5f0f\u3067\u8a08\u7b97\u3059\u308b\uff0e\nXdif = Xmax \u2212Xrest \uff081\uff09\n\u3053\u306e Xdif \u3068\u6307\u304c\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5 \u30c8\u306e\u6700\u5927\u7e70\u308a\u51fa\u3057\u91cf Lmax \u3092\u7528\u3044\u3066\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u99c6\u52d5\u30d1\u30e9\u30e1\u30fc \u30bf R \u3092\u6c7a\u5b9a\u3059\u308b\uff0e\nR = Lmax\nXdif \uff082\uff09\n\u4ee5\u4e0a\u3067\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u7d42\u4e86\u3059\u308b\uff0e\u3053\u306e\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7 \u30f3\u30d7\u30ed\u30bb\u30b9\u306f\uff0c3\u56de\u306e\u30b9\u30a4\u30c3\u30c1\u64cd\u4f5c\u3067\u884c\u3048\u308b\u305f\u3081\u30e6\u30fc\u30b6\u81ea\u8eab\u3067 \u884c\u3046\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u307e\u305f\uff0c3 \u79d2\u4ee5\u5185\u306b\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3 \u304c\u5b8c\u4e86\u3059\u308b\u306e\u3067\uff0c\u518d\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u6642\u9593\u3092\u5fc5\u8981\u3068\u3057\u306a\u3044\uff0e \u6b21\u306b\u64cd\u4f5c\u6642\u306b\u3064\u3044\u3066\u8aac\u660e\u3059\u308b\uff0e\u64cd\u4f5c\u6642\u306e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5e73\u6ed1\u5316 \u5f8c\u306e\u5024\u3092 xs(k)(k = 0, \u00b7 \u00b7 \u00b7 ,K) \u3068\u3059\u308b\u3068\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u30b7\u30e3\u30d5\u30c8 \u306e\u7e70\u308a\u51fa\u3057\u91cf l(k) \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e\nl(k) = R(xs(k)\u2212Xrest) \uff083\uff09\n\u3053\u306e\u3068\u304d\uff0c\u4f55\u3089\u304b\u306e\u539f\u56e0\u306b\u3088\u308a l(k) > Lmax \u3068\u306a\u3063\u305f\u5834\u5408\u306f\uff0c l(k) = Lmax \u3068\u3057\uff0cl(k) \u306e\u5024\u3092\u6307\u4ee4\u5024\u3068\u3057\u3066\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u305f\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306b\u9001\u308b\uff0e 2. 5 \u30bd\u30b1\u30c3\u30c8\u5f62\u72b6\u3068\u30cf\u30f3\u30c9\u30db\u30eb\u30c0 Fig. 8 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2\u3092\u63a5\u7d9a\u3059\u308b\u8ef8\u306e\u307f\u91d1\u5c5e\u3067\u3042\u308b\uff0e\u6700\u7d42\u7684\u306a\u7fa9\u624b \u306e\u30b9\u30da\u30c3\u30af\u306fTable 2\u3068\u306a\u3063\u305f\uff0e\u30bd\u30b1\u30c3\u30c8\u3092\u542b\u3080\u5168\u4f53\u306e\u91cd\u3055\u306f 300 [g] \u3068\u306a\u308a\uff0cOttobock \u793e\u306e Myobock \u306e\u30bd\u30b1\u30c3\u30c8\u8fbc\u307f\u306e\u91cd \u91cf\u7d04 900 [g] \u306b\u6bd4\u3079\u308b\u3068 3 \u5206\u306e 1 \u3068\u306a\u3063\u305f\uff0e\u89d2\u578b\u30ea\u30c1\u30a6\u30e0\u30a4\u30aa \u30f3\u96fb\u6c60\uff089 [V]\uff0c\u5bb9\u91cf 500 [mAh]\uff09\u3092\u7528\u3044\u3066\uff0c30\u79d2\u3054\u3068\u306b\u958b\u9589\u3092 \u7e70\u308a\u8fd4\u3057\u305f\u5834\u5408\u306e\u30d0\u30c3\u30c6\u30ea\u30fc\u99c6\u52d5\u6642\u9593\u306f\uff0c\u7d04 6\u6642\u9593\u3067\u3042\u308b\uff0e\u307e \u305f\uff0cFig. 9\u306e\u3088\u3046\u306b\u529b\u30bb\u30f3\u30b5\u3067\u8a08\u6e2c\u3057\u305f\u5834\u5408\uff0c\u5404\u30bb\u30f3\u30b5\u306b\u304b\u304b \u308b\u529b\u306e\u5e73\u5747\u5024\u306f\uff0c5.8 [N]\u3067\u3042\u3063\u305f\uff0e500 [ml]\u306e\u30da\u30c3\u30c8\u30dc\u30c8\u30eb\u3092 \u628a\u6301\u3057\u3066\uff0c\u6301\u3061\u4e0a\u3052\u308b\u3053\u3068\u304c\u3067\u304d\u308b\u3053\u3068\u3092\u78ba\u8a8d\u3057\u305f\uff0e\u6307\u5148\u30ad\u30e3\u30c3 \u30d7\u306f\u30b7\u30ea\u30b3\u30f3\u88fd\u306e\u305f\u3081\uff0c\u578b\u306b\u3088\u308b\u6210\u5f62\u304c\u5fc5\u8981\u304c\u3042\u308b\u304c\uff0c\u6307\u5148\u306b\n\u30b7\u30ea\u30b3\u30f3\u30b7\u30fc\u30c8\u3092\u8cbc\u308a\u4ed8\u3051\u308b\u3053\u3068\u3067\u4ee3\u66ff\u53ef\u80fd\u3067\u3042\u308a\uff0c\u30b5\u30dd\u30fc\u30bf \u3082\u751f\u5730\u304c\u3042\u308c\u3070\u578b\u7d19\u304b\u3089\u88fd\u4f5c\u3059\u308b\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u307e\u305f\uff0c\u30de \u30a4\u30b3\u30f3\uff0c\u30bb\u30f3\u30b5\uff0c\u30e2\u30fc\u30bf\u306f\u524d\u8ff0\u306e\u3088\u3046\u306b\u4e00\u822c\u306b\u5e02\u8ca9\u3055\u308c\u3066\u3044\u308b \u305f\u3081\uff0c3D \u30d7\u30ea\u30f3\u30bf\u3055\u3048\u3042\u308c\u3070\u8907\u88fd\u306f\u5bb9\u6613\u3067\u3042\u308b\uff0e\u4ed6\u306e\u7b4b\u96fb\u7fa9 \u624b\u3068\u306e\u5358\u7d14\u306a\u4fa1\u683c\u6bd4\u8f03\u306f\u96e3\u3057\u3044\u304c\uff0c\u30c8\u30fc\u30bf\u30eb\u306e\u6750\u6599\u8cbb\u306f 5\u4e07\u5186 \u4ee5\u4e0b\u3068\u306a\u308a\uff0c\u4f4e\u30b3\u30b9\u30c8\u3067\u306e\u88fd\u4f5c\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\n3. SHAP\u306b\u3088\u308b\u8a55\u4fa1\n\u8a66\u4f5c\u7fa9\u624b\u306e\u6709\u52b9\u6027\u3092\u691c\u8a3c\u3059\u308b\u305f\u3081\uff0c\u524d\u8155\u5207\u65ad\u8005\u306b\u3088\u308b\u8a55\u4fa1\u3092 \u884c\u3063\u305f\uff0e\u5b9f\u9a13\u53c2\u52a0\u8005\u306f 1\u540d\u306e\u5de6\u524d\u8155\u5207\u65ad\u8005\uff08\u7537\u6027\uff0c60\u4ee3\uff09\u3067\u3042\u308b\uff0e \u65ad\u7aef\u9577\u306f 12 [cm]\u3067\uff0c\u65e5\u5e38\u7684\u306b\u88c5\u98fe\u7fa9\u624b\u3092\u7528\u3044\u3066\u304a\u308a\uff0c\u4f5c\u696d\u7528\u7fa9 \u624b\u306e\u4f7f\u7528\u7d4c\u9a13\u306f\u306a\u3044\uff0e\u8a55\u4fa1\u306b\u306f\u30a4\u30ae\u30ea\u30b9\u3067\u958b\u767a\u3055\u308c\u305f\u4e0a\u80a2\u6a5f\u80fd \u306e\u8a55\u4fa1\u30c6\u30b9\u30c8\u3067\u3042\u308b SHAP\uff08Southampton Hand Assessment Procedure\uff09[13] [14]\u3092\u7528\u3044\u305f\uff0eSHAP\u306f\u65e5\u5e38\u751f\u6d3b\u306b\u304a\u3051\u308b\u628a\u6301 \u30bf\u30a4\u30d7\u306e\u4f7f\u7528\u983b\u5ea6\u306e\u5206\u6790\u306a\u3069\u306b\u57fa\u3065\u304d\uff0cFig. 10\u306b\u793a\u3059\u3088\u3046\u306a\uff0c \u624b\u304c\u65e5\u5e38\u7684\u306b\u884c\u3046 6\u7a2e\u306e\u628a\u6301\u306e\u80fd\u529b\u3092\u8a55\u4fa1\u3059\u308b\uff0e6\u7a2e\u306e\u628a\u6301\u306b \u5bfe\u5fdc\u3057\u305f\u62bd\u8c61\u7269\u4f53\u305d\u308c\u305e\u308c\u306b\u3064\u3044\u3066\uff0c\u6728\u6750\u307e\u305f\u306f\u91d1\u5c5e\u304b\u3089\u6210\u308b 12\u7a2e\u306e\u7269\u4f53\u3092\u64cd\u4f5c\u3059\u308b\u8ab2\u984c\u3068\uff0c6\u7a2e\u306e\u628a\u6301\u3092\u4f7f\u7528\u3059\u308b 14\u7a2e\u306e \u65e5\u5e38\u751f\u6d3b\u52d5\u4f5c\u306e\u8ab2\u984c\u3067\u69cb\u6210\u3055\u308c\u3066\u3044\u308b\uff0e\u5404\u8ab2\u984c\u3092\u5b8c\u4e86\u3059\u308b\u307e\u3067 \u306e\u6642\u9593\u3092\u8a08\u6e2c\u3057\uff0c\u9054\u6210\u306b 100\u79d2\u4ee5\u4e0a\u304b\u304b\u308b\u5834\u5408\u306b\u306f\u8ab2\u984c\u3092\u5931\u6557 \u3068\u3059\u308b\uff0eSHAP\u306f\u4e0a\u80a2\u6a5f\u80fd\u306b\u3064\u3044\u3066\u30b9\u30b3\u30a2\u306e\u8a08\u7b97\u304c\u53ef\u80fd\u3067\u3042\u308b \u304c\uff0c\u5b9f\u9a13\u53c2\u52a0\u8005\u306f\u4ed6\u306e\u7fa9\u624b\u306e\u4f7f\u7528\u7d4c\u9a13\u306f\u306a\u3044\u305f\u3081\u4eca\u56de\u306f\u4ed6\u306e\u7fa9 \u624b\u3068\u306e\u30b9\u30b3\u30a2\u306e\u6bd4\u8f03\u306f\u884c\u308f\u305a\uff0c\u500b\u3005\u306e\u8ab2\u984c\u304c\u9042\u884c\u53ef\u80fd\u3067\u3042\u308b\u304b \u3069\u3046\u304b\u306b\u7740\u76ee\u3057\u3066\u8a55\u4fa1\u3057\u305f\uff0e \u524d\u8155\u5207\u65ad\u8005\u306b\u3088\u308b\u8a55\u4fa1\u3092\u884c\u3046\u524d\u306b\uff0c\u8a66\u4f5c\u7fa9\u624b\u3067 6\u7a2e\u306e\u62bd\u8c61\u7269 \u4f53\u3092\u628a\u6301\u53ef\u80fd\u304b\u78ba\u8a8d\u3057\u305f\uff0eFig. 11\u306b\u793a\u3059\u3088\u3046\u306b\uff0cFig. 10\u3068\u540c \u69d8\u306e 6\u7a2e\u306e\u628a\u6301\u304c\u53ef\u80fd\u3067\u3042\u308a\uff0c\u8a66\u4f5c\u7fa9\u624b\u306e\u8a55\u4fa1\u306b SHAP\u304c\u9069\u7528 \u53ef\u80fd\u3067\u3042\u308b\uff0e \u5b9f\u9a13\u53c2\u52a0\u8005\u304c\u88c5\u7740\u3057\u305f\u7fa9\u624b\u306f\u6700\u7d42\u4ed5\u69d8\u3068\u540c\u69d8\u3067\u3042\u308b\u304c\uff0c\u578b\u6210 \u5f62\u304c\u5fc5\u8981\u306a\u30b7\u30ea\u30b3\u30f3\u88fd\u306e\u6307\u5148\u30ad\u30e3\u30c3\u30d7\u3067\u306f\u306a\u304f\uff0c\u30b7\u30ea\u30b3\u30f3\u30b7\u30fc \u30c8\uff08\u786c\u5ea6 30\u25e6\uff0c\u539a\u3055 1.5 [mm]\uff09\u3092\u6307\u5148\u5f62\u72b6\u306b\u5408\u308f\u305b\u3066\u63a5\u7740\u3057\u305f\nJRSJ Vol. 32 No. 5 \u201458\u2014 June, 2014", + "\u3082\u306e\u3092\u4f7f\u7528\u3057\uff0c\u6700\u3082\u4f4e\u30b3\u30b9\u30c8\u306b\u5b9f\u73fe\u3067\u304d\u308b\u4ed5\u69d8\u3067\u691c\u8a3c\u3057\u305f\uff0e\u30cf \u30f3\u30c9\u306f\u638c\u5c48 45\u25e6 \u3067\u56fa\u5b9a\u3057\u305f\uff0e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306f\u5c3a\u5074\u624b\u6839\u5c48\u7b4b\u306e\u76f4\u4e0a \u306b\u914d\u7f6e\u3057\uff0c\u4e0a\u304b\u3089\u4f38\u7e2e\u6027\u306e\u30a2\u30f3\u30c0\u30fc\u30e9\u30c3\u30d7\u3092\u5dfb\u3044\u3066\u56fa\u5b9a\u3057\uff0c\u305d \u306e\u4e0a\u304b\u3089\u30bd\u30b1\u30c3\u30c8\u3092\u88c5\u7740\u3057\u305f\uff0e\u30bd\u30b1\u30c3\u30c8\u306e\u88c5\u7740\u306f\u30b5\u30dd\u30fc\u30bf\u306e\u30d0 \u30f3\u30c9\u3067\u56fa\u5b9a\u3059\u308b\u3053\u3068\u3067\uff0c\u5b9f\u9a13\u53c2\u52a0\u8005\u81ea\u8eab\u3067\u3082\u7247\u624b\u3067\u88c5\u7740\u53ef\u80fd\u3067 \u3042\u3063\u305f\uff0e SHAP\u30c6\u30b9\u30c8\u3092\u884c\u3046\u524d\u306b\u7b4b\u53ce\u7e2e\u306b\u5fdc\u3058\u3066\u6307\u306e\u958b\u9589\u304c\u53ef\u80fd\u304b\u3069 \u3046\u304b\u78ba\u8a8d\u3057\u305f\uff0e\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u5f8c\uff0c\u80a9\u95a2\u7bc0\u5185\u65cb 0\u25e6 \u8098\u95a2\u7bc0\u5c48 \u66f2 80\u25e6 \u306e\u59ff\u52e2\u3067\u6307\u3092\u63e1\u308b\u3088\u3046\u306a\u30a4\u30e1\u30fc\u30b8\u3067\u7b4b\u53ce\u7e2e\u3057\u305f\u6642\u306e\u8ddd\u96e2 \u30bb\u30f3\u30b5\u306e\u5024\u3092 Fig. 12\u306b\u793a\u3059\uff0e\u7b4b\u53ce\u7e2e\u306b\u3088\u3063\u3066\u30bb\u30f3\u30b5\u2013\u76ae\u819a\u9593\u306e \u8ddd\u96e2\u304c\u7e2e\u307e\u308b\u3053\u3068\u3067\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5024\u304c\u4e0a\u6607\u3059\u308b\u5305\u7d61\u6ce2\u5f62\u304c\u5f97 \u3089\u308c\uff0c\u3053\u306e\u3068\u304d\u7fa9\u624b\u306e\u6307\u304c\u610f\u56f3\u901a\u308a\u306b\u958b\u9589\u3059\u308b\u3053\u3068\u3092\u78ba\u8a8d\u3057\u305f\uff0e \u307e\u305f\uff0c\u80a9\u95a2\u7bc0\u5185\u65cb 0\u25e6 \u8098\u95a2\u7bc0\u5c48\u66f2 0\u25e6 \u306e\u59ff\u52e2\uff0c\u80a9\u95a2\u7bc0\u5185\u65cb 90\u25e6 \u8098 \u95a2\u7bc0\u5c48\u66f2 80\u25e6 \u306e\u59ff\u52e2\u3067\u3082\u540c\u69d8\u306b\u6307\u304c\u610f\u56f3\u901a\u308a\u306b\u958b\u9589\u3067\u304d\u308b\u3053\u3068 \u3092\u78ba\u8a8d\u3057\u305f\uff0e \u7523\u696d\u6280\u8853\u7dcf\u5408\u7814\u7a76\u6240\u304a\u3088\u3073\u56fd\u7acb\u969c\u5bb3\u8005\u30ea\u30cf\u30d3\u30ea\u30c6\u30fc\u30b7\u30e7\u30f3\u30bb \u30f3\u30bf\u30fc\u306e\u502b\u7406\u5be9\u67fb\u59d4\u54e1\u4f1a\u306e\u627f\u8a8d\u3092\u5f97\u3066\uff0c\u5b9f\u9a13\u53c2\u52a0\u8005\u306b\u306f\u4e8b\u524d\u306b \u7814\u7a76\u306e\u5185\u5bb9\u3068\u30ea\u30b9\u30af\u306b\u95a2\u3059\u308b\u8aac\u660e\u3092\u6587\u66f8\u3068\u53e3\u982d\u3067\u884c\u3044\uff0c\u540c\u610f\u3092 \u5f97\u305f\u4e0a\u3067\u8a55\u4fa1\u3092\u884c\u3063\u305f\uff0e 3. 1 \u62bd\u8c61\u7269\u4f53\u306e\u64cd\u4f5c\u8ab2\u984c\u306e\u7d50\u679c \u62bd\u8c61\u7269\u4f53\u306e\u64cd\u4f5c\u8ab2\u984c\u306f\uff0cFig. 13\u306b\u793a\u3059\u3088\u3046\u306b\uff0c\u8efd\u91cf\u7269\uff08\u6728\u6750\uff09\n\u307e\u305f\u306f\u91cd\u91cf\u7269\uff08\u91d1\u5c5e\uff09\u304b\u3089\u6210\u308b 12\u7a2e\u306e\u62bd\u8c61\u7269\u4f53\u3092\uff0c\u673a\u4e0a\u306e\u898f\u5b9a \u306e\u4f4d\u7f6e\u306b\u79fb\u52d5\u3059\u308b\u8ab2\u984c\u3067\u3042\u308b\uff0e5\u5206\u307b\u3069\u64cd\u4f5c\u7df4\u7fd2\u3092\u3057\u3066\u3082\u3089\u3044\uff0c \u7fa9\u624b\u306e\u64cd\u4f5c\u306b\u3042\u308b\u7a0b\u5ea6\u6163\u308c\u305f\u6bb5\u968e\u3067\u30c6\u30b9\u30c8\u3092\u884c\u3063\u305f\uff0eTable 3 \u306b\u7d50\u679c\u3092\u793a\u3059\uff0e\u8efd\u91cf\u7269\u306b\u95a2\u3057\u3066\u306f\uff0c\u3059\u3079\u3066\u306e\u628a\u6301\u30bf\u30a4\u30d7\u3067 7\u79d2 \u4ee5\u5185\u3067\u9054\u6210\u3067\u304d\u305f\uff0e\u91cd\u91cf\u7269\u306b\u3064\u3044\u3066\u306f\uff0c\u5074\u9762\u3064\u307e\u307f\uff08Lateral\uff09 \u3092\u9664\u3044\u3066 10 \u79d2\u4ee5\u5185\u3067\u9054\u6210\u3067\u304d\u305f\uff0e\u5074\u9762\u3064\u307e\u307f\u306f\u76f4\u65b9\u4f53\u306e\u5074\u9762 \u306b\u53d6\u308a\u4ed8\u3051\u3089\u308c\u305f\u628a\u624b\u3092\u3064\u307e\u3093\u3067\u79fb\u52d5\u3059\u308b\u8ab2\u984c\u3067\u3042\u308b\u304c\uff0c\u91cd\u91cf \u7269\u306e\u91cd\u5fc3\u304b\u3089\u96e2\u308c\u305f\u4f4d\u7f6e\u3092\u628a\u6301\u3057\u306a\u3051\u308c\u3070\u306a\u3089\u306a\u3044\u3053\u3068\u306b\u52a0\u3048\uff0c \u91d1\u5c5e\u88fd\u306e\u628a\u624b\u304c\u6ed1\u308a\u3084\u3059\u304b\u3063\u305f\u3053\u3068\u304c\u9054\u6210\u3067\u304d\u306a\u304b\u3063\u305f\u539f\u56e0\u3067 \u3042\u308b\u3068\u8003\u3048\u3089\u308c\u308b\uff0e\u91cd\u91cf\u7269\u306e\u5074\u9762\u3064\u307e\u307f\u4ee5\u5916\u306e 11\u8ab2\u984c\u306f\u56f0\u96e3\u306a \u304f\u9054\u6210\u3067\u304d\u305f\u3053\u3068\u304b\u3089\uff0c\u524d\u8155\u5207\u65ad\u8005\u304c\u8a66\u4f5c\u3057\u305f\u7fa9\u624b\u3092\u7528\u3044\u3066 6 \u7a2e\u306e\u628a\u6301\u3092\u53cd\u6620\u3057\u305f\u62bd\u8c61\u7269\u4f53\u306e\u64cd\u4f5c\u304c\u53ef\u80fd\u3067\u3042\u308b\u3053\u3068\u3092\u78ba\u8a8d\u3067 \u304d\u305f\uff0e\u65e5\u5e38\u7684\u306b\u4f5c\u696d\u7528\u7fa9\u624b\u3092\u4f7f\u7528\u3057\u306a\u3044\u5207\u65ad\u8005\u304c 10 \u5206\u7a0b\u5ea6\u306e \u7df4\u7fd2\u3067\u64cd\u4f5c\u3067\u304d\u308b\u3088\u3046\u306b\u306a\u3063\u305f\u3053\u3068\u304b\u3089\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u7528\u3044\u305f \u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u304c\u6709\u52b9\u3067\u3042\u308b\u3053\u3068\u304c\u793a\u3055\u308c\u305f\uff0e\u307e\u305f\uff0c\u5b9f\u9a13\u53c2\u52a0\u8005 \u306f\u77ed\u65ad\u7aef\u3067\u3042\u3063\u305f\u304c\uff0c\u7269\u4f53\u3092\u628a\u6301\u3057\u305f\u72b6\u614b\u3067\u3082\u30bd\u30b1\u30c3\u30c8\u304b\u3089\u5207 \u65ad\u7aef\u304c\u629c\u3051\u843d\u3061\u305a\uff0c\u5341\u5206\u306a\u61f8\u5782\u529b\u304c\u767a\u63ee\u3067\u304d\u308b\u3053\u3068\u304c\u793a\u3055\u308c\u305f\uff0e 3. 2 \u65e5\u5e38\u751f\u6d3b\u52d5\u4f5c\u8ab2\u984c\u306e\u7d50\u679c \u65e5\u5e38\u751f\u6d3b\u52d5\u4f5c\u306b\u95a2\u3059\u308b\u8ab2\u984c\u306e\u7d50\u679c\u3092 Table 4\u306b\u793a\u3059\uff0e\u5168 14 \u8ab2\u984c\u4e2d 6\u8ab2\u984c\u304c 100\u79d2\u4ee5\u5185\u3067\u9054\u6210\u3067\u304d\u305f\uff0e\u9054\u6210\u53ef\u80fd\u3067\u3042\u3063\u305f\u30bf \u30b9\u30af\u306f\uff0c\u7d19\u3092\u3081\u304f\u3063\u3066\u88cf\u8fd4\u3059\uff08Page Turning\uff09\uff0c\u7d19\u30d1\u30c3\u30af\u306e\u6c34\u3092\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201459\u2014 2014 \u5e74 6 \u6708" + ] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure20-1.png", + "caption": "Figure 20. Axes of rotation and control forces produced by the drone\u2019s motors and elevons (at the rear wing).", + "texts": [ + " We planned to install a down-facing rangefinder for a smooth auto-landing feature. Initially, an ultrasonic sensor was tested, but we decided to replace it with a tiny, affordable, and very reliable Time-of-Flight (ToF) laser rangefinder (Pololu VL53L1X [40]). With its range up to 400cm, the auto-landing mode works perfectly smoothly. We used good-quality 18 AWG power wires with XT60 and XT30 connectors. For the signal connectors, we used Ninigi NXG-02 [41] (2mm raster connectors), 2\u20136 pins, depending on a particular component to connect. Figure 20 explains the forces acting on the drone\u2019s body and primary axes of rotation. The drone dynamics can be analysed from a quadcopter and a plane point of view. The forces and moments equations can be derived from Euler\u2019s equations for rigid body dynamics\u2014this is thoroughly explained in [12,17,18]. We also explained in our previous paper [42] how the quadcopter control forces Fq (see Figure 20) are mixed to obtain desired moments for the roll, pitch, and yaw axes. Although the quadcopter-like control always actuates all four motors, the control task can be decomposed into isolated controllers for each rotation axis separately [42]. The Fp force in Figure 20 is the forward-directed force produced by the pusher propeller (when the pusher motor is active). The trailing edge of the rear wing was converted into full-length elevons, i.e., control surfaces that act as an elevator when deflected in the same direction and as ailerons when deflected differentially [12]. The drone has no rudder, which means that while flying in the plane mode (a level flight using pusher motor and wings\u2019 lift force, quadcopter motors shut down), only rotation around the roll and pitch axes is possible" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003315__Issue1-15_paper.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003315__Issue1-15_paper.pdf-Figure12-1.png", + "caption": "Fig. 12. Scheme (a) and physical model (b) of the frictional joint with resistance wedge", + "texts": [ + " Changes of mean values of axial forces in the bolts of stirrups for the frictional joint with and without the resistance wedge 0 20 40 60 80 100 120 140 160 180 0 0,05 0,1 0,15time, s Q , k N Bolts of frictional joint without resistance wedge Bolts of frictional joint with resistance wedge -30 -20 -10 0 10 20 30 40 50 0 0,1 0,2 0,3 0,4 0,5 0,6 0,7 0,8 0,9 1 1,1 h,m % Frictional joint with resistance wedge Frictional joint without resistance wedge In order to describe analytically an operation of the frictional joint with the resistance wedge physical and mathematical models were developed. In a Figure 12 physical model and scheme of the frictional joint with the resistance wedge are presented. At development of the physical model a discontinuous motion with a dry friction (Brodny 2011b; Leine et al., 1998; Nakano & Maegawa, 2009) and results of modelling of mechanized supports presented in work (Szweda, 2001) was taken into consideration. In this system frictional joint was modeled as two focused masses of cooperating sections (m1 and m2) each enlarged by the mass of one stirrup. Sections are pressed against with a force N, whose value is equal to the total value of axial forces in the bolts of stirrups" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003944_6514899_10305151.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003944_6514899_10305151.pdf-Figure8-1.png", + "caption": "FIGURE 8. MGW extension (a) Top View, and (b) S-parameters.", + "texts": [ + " Therefore, we have designed a microstrip line to MGW extension by This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License. For more information, see https://creativecommons.org/licenses/by-nc-nd/4.0/ Oludayo Sokunbi and Ahmed Kishk: Millimeter-wave ME-Dipole Array Antenna Decoupling Using a Novel Metasurface Structure FIGURE 7. Extended view of the 1\u00d72 ME-dipole antenna without metasurface. extending the feedline and using the MGW technology on the extended line. We have also used the same dimensions of unit cells on the extension, as shown in Fig. 8(a). The extracted sparameter of the line is shown in Fig. 8(b), showing good reflection and very low insertion loss within 50-70 GHz bandwidth. The MGW extension in Fig. 8 is then connected with the MIMO 1\u00d72 antenna in Fig. 7 and is shown in Fig. 9. Also, Fig. 9 is simulated with the metasurface, consisting of 2\u00d75 resonator unit cells to reduce the coupling within 52- 62 GHz, as explained in section II. The metasurface is 1 mm (0.2\u03bb) above the surface of the antenna. MS spacer is used as an airgap between the antenna and the metasurface for mechanical support as shown in Fig. 9. Rogers RT 5880, with a thickness of 1 mm, is used as a spacer and mechanical support to create an air gap between the antenna and the metasurface, as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001765_8948470_09166481.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001765_8948470_09166481.pdf-Figure1-1.png", + "caption": "FIGURE 1. Geometry of the hybrid DRA (a) Front view (b) Back view (c) Side view (d) Isometric view.", + "texts": [ + " For comparison, the proposed antenna was compared with the currently published state of the art designs. A summary of wideband hybrid DRAs is listed in Table 1, in which the antennas are compared in terms of electrical size, impedance bandwidth and radiation efficiency. Following this, the antenna design and its details are described in Section 2 while the experimental results and analysis are provided in Sections 3 and 4, respectively. II. ANTENNA DESIGN The structure of the proposedwideband hybrid DRA is shown in Figure 1. This antenna consists of three stackedDRs loaded on top of a resonating slot etched on the ground plane of RT/Duroid RO4003C substrate (\u03b5r = 3.38) with a thickness of 0.813 mm. The width W, length, L and thickness of the dielectric substrate are 20 mm, 30 mm and 0.813 mm, respectively. In this design, three different dielectric substrates which are RO4003C (\u03b5r = 3.38) with a thickness of 0.813 mm, FR-4 (\u03b5r = 4.55) with a thickness of 1.6 mm and RT/Duriod 6010 (\u03b5r = 10.2) with a thickness of 1.27 mm were used as the resonating elements" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure19-1.png", + "caption": "Figure 19. The robotic force-plate with 2-DOF actuation (TOP: CAD drawing; BOTTOM: Experimental Prototype). The cubic support frame (1); internal and external layers of the footplate (2); the PF/DF motor and transmission system (3); the IN/EV motor and transmission system (4); the encoders (5); the foot strap (6); and mechanical stop (7).", + "texts": [ + " 31 Figure 18: Overall design of the virtually interfaced robotic ankle and balance trainer (vi-RABT): The support frame (1) provides room for stepping forward/backward; Subjects feet will be strapped on the robotic force-plates (2); The surrounding rails (3) provides safety features to the patients during practice; The system can be used in standing or sitting posture using the adjustable chair (4); and patients will be instructed to play the VR game on the screen (5) (modified from [131]) ................................................................................................................................. 36 Figure 19: The robotic force-plate with 2-DOF actuation (TOP: CAD drawing; BOTTOM: Experimental Prototype). The cubic support frame (1); internal and external layers of the footplate (2); the PF/DF motor and transmission system (3); the IN/EV motor and transmission system (4); the encoders (5); the foot strap (6); and mechanical stop (7). .................................................. 38 Figure 20: 3D CAD image of the robotic footplate support frame built of 1.5\u201d aluminum [131] .............. 39 ix Figure 21: Image of the interior frame; Left: INEV axis of rotation, right: INEV built in within the DFPF axis [131] " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004291_advpub_22-00301__pdf-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004291_advpub_22-00301__pdf-Figure6-1.png", + "caption": "Fig. 6 Changes in the toe angles for different configurations of the suspension in which point B is located slightly forward of point D when the lateral force acts on the wheel. As shown in figure (a), for the case where the side B-D and the axis C-H are parallel and have the same length, change in toe angle does not occur. As shown in figure (b), for the case where distance DH is larger than that of BC, change in toe angle in the direction of toe-out occurs. As shown in figure (c), for the case where distance DH is smaller than that of BC, change in toe angle in the direction of toe-in occurs.", + "texts": [], + "surrounding_texts": [ + "\u00a9 The Japan Society of Mechanical Engineers\n\u6700\u5f8c\u306b\u3053\u308c\u3089\u306e\u529b\u306b\u3088\u308b\u5909\u4f4d\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306b\u4e26\u9032\u3068\u56de\u8ee2 \u306e\u5909\u4f4d\u3092\u751f\u3058\u3055\u305b\u308b\uff0e\u8868 1 \u306b\u793a\u3057\u305f\u3088\u3046\u306b kDY\u306f kGY\u306b\u6bd4\u3079\u5927\u304d\u3044\u305f\u3081\uff0c\u3053\u3053\u3067\u306f\u3053\u308c\u3089\u306e\u5909\u4f4d\u3092\u70b9 D \u306e\u8eca\u4e21\u5185 \u5411\u304d\u306e\u4e26\u9032\u5909\u4f4d\u3068\u70b9 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D\u307e\u308f\u308a\u306e\u56de\u8ee2\u306b\u8d77\u56e0\u3057\u3066\u751f\u3058\u308b\uff0e\u305f\u3060\u3057\uff0c\u70b9 D, H\u306e\u8eca\u4e21\u5de6\u53f3 \u65b9\u5411\u3078\u306e\u5909\u4f4d\u5dee\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\u3059\u3067\u306b\u30e2\u30fc\u30c9\u2160\u3067\u8003\u616e\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u8b70\u8ad6\u3059\u308b\u5834", + "\u00a9 The Japan Society of Mechanical Engineers\n\u5408\u306f\u70b9 D, H \u306f\u8eca\u4e21\u5de6\u53f3\u65b9\u5411\u3078\u306f\u5909\u4f4d\u3057\u306a\u3044\u3082\u306e\u3068\u3057\u305f\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u8fba B-D\uff0c\u30bf\u30a4\u30ed\u30c3\u30c9\u8ef8 C-H \u304a\u3088\u3073\u30db\u30a4\u30fc \u30eb\u90e8\u306e\u8fba B-C \u306f 4 \u7bc0\u30ea\u30f3\u30af\u6a5f\u69cb\u3092\u69cb\u6210\u3057\u3066\u3044\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u8fba B-D \u304c\u70b9 D \u307e\u308f\u308a\u306b\u56de\u8ee2\u3059\u308b\u3053\u3068\u306b\u3088\u308a\u8ef8 C-H \u3068\u306e\u30ea\u30f3\u30af\u4f5c\u7528\u306b\u3088\u308a\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u304c\u8d77\u3053\u308b\u53ef\u80fd\u6027\u304c\u3042\u308b\uff0e\u3053\u308c\u3092\u3044\u304f\u3064\u304b\u306e\u5834\u5408\u306b\u5206\u3051\u3066\u8003\u3048\u308b\uff0e\n\u306f\u3058\u3081\u306b\uff0c\u70b9 B\u304c\u70b9 D\u3088\u308a\u3082\u8eca\u4e21\u524d\u65b9\u306b\u4f4d\u7f6e\u3059\u308b\u5834\u5408\u306b\u3064\u3044\u3066\u691c\u8a0e\u3057\u305f\uff0e\u691c\u8a0e\u306b\u969b\u3057\uff0c\u56f3 6(a), (b), (c)\u306b\u793a\u3059\u3088 \u3046\u306b\uff0c\u8ef8 C-H\u304c\u8fba B-D\u3068\u5e73\u884c\u306a\u5834\u5408\uff08\u56f3 6(a)\uff09\uff0c\u8ef8 C-H\u3068\u8fba B-D\u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u5e83\u304c\u3063\u3066\u3044\u308b\u5834\u5408 \uff08\u56f3 6(b)\uff09\uff0c\u8ef8 C-H \u3068\u8fba B-D \u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u72ed\u304f\u306a\u3063\u3066\u3044\u308b\u5834\u5408\uff08\u56f3 6(c)\uff09\u306e 3 \u3064\u3092\u8003\u3048\u305f\uff0e\u305f\u3060 \u3057\uff0c\u3044\u305a\u308c\u3082\u8fba B-D\u306b\u5bfe\u3057\u3066\u8ef8 C-H\u304c\u306a\u3059\u89d2\u5ea6\u306f\u5927\u304d\u304f\u306a\u3044\u3082\u306e\u3068\u3059\u308b\uff0e\u307e\u305f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306f\u53cd\u6642\u8a08\u307e\u308f\u308a\u306b\u56de \u8ee2\u3057\uff0c\u305d\u308c\u306b\u4f34\u3063\u3066\u8ef8 C-H \u3082\u540c\u3058\u65b9\u5411\u306b\u56de\u8ee2\u3059\u308b\u3068\u3059\u308b\uff0e\u306a\u304a\uff0c\u56f3 6 \u3067\u306f\u70b9 A\u304a\u3088\u3073\u70b9 A\u3068 B \u3092\u3064\u306a\u3050\u7dda\u306f\u7701 \u7565\u3057\u3066\u3042\u308b\uff0e\u307e\u305a\uff0c\u56f3 6(a)\u306e\u8ef8 C-H \u304c\u8fba B-D \u3068\u5e73\u884c\u306a\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306f\uff0c\u8fba B-D \u3068\u8ef8 C-H \u306f\u7b49\u9577\u3067\u3042 \u308b\u3068\u3059\u308b\u3068\uff0c\u70b9 B, C, H, D\u3092\u3064\u306a\u3044\u3067\u5f97\u3089\u308c\u308b\u30ea\u30f3\u30af\u6a5f\u69cb\u306f\u30d1\u30e9\u30ec\u30eb\u30ea\u30f3\u30af\u3068\u306a\u308b\u305f\u3081\uff0c\u70b9 B, C\u306e\u5909\u4f4d\u306f\u56f3 6(a) \u306b\u9ed2\u77e2\u5370\u3067\u793a\u3059\u3088\u3046\u306b\u540c\u3058\u3068\u306a\u308a\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u751f\u3058\u306a\u3044\uff0e\u3064\u304e\u306b\uff0c\u56f3 6(b)\u306e\u3088\u3046\u306b\u8fba B-D\u3068\u8ef8 C-H \u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u5e83\u304c\u3063\u3066\u3044\u308b\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306f\uff0c\u56f3 6(b)\u306b\u9ed2\u77e2\u5370\u3067\u793a\u3059\u3088\u3046\u306b\uff0c\u70b9 C\u306e\u8eca \u4e21\u5185\u5074\u3078\u306e\u5909\u4f4d\u91cf\u304c\u70b9 B\u306e\u5909\u4f4d\u91cf\u3088\u308a\u3082\u5927\u304d\u304f\u306a\u308b\uff0e\u305d\u306e\u305f\u3081\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\uff0e\u6700\u5f8c \u306b\uff0c\u56f3 6(c)\u306e\u3088\u3046\u306b\u8fba B-D\u3068\u8ef8 C-H\u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u72ed\u304f\u306a\u3063\u3066\u3044\u308b\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306f\uff0c\u56f3 6(c)\u306b\u9ed2\u77e2\u5370\u3067\u793a\u3059\u3088\u3046\u306b\uff0c\u70b9 C\u306e\u8eca\u4e21\u5185\u5074\u3078\u306e\u5909\u4f4d\u91cf\u304c\u70b9 B \u306e\u5909\u4f4d\u91cf\u3088\u308a\u3082\u5c0f\u3055\u304f\u306a\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u30db\u30a4\u30fc\u30eb \u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a4\u30f3\u306b\u306a\u308b\uff0e\n\u3064\u304e\u306b\uff0c\u70b9 B\u304c\u70b9 D\u3088\u308a\u3082\u8eca\u4e21\u5f8c\u65b9\u306b\u4f4d\u7f6e\u3059\u308b\u5834\u5408\u306b\u3064\u3044\u3066\u691c\u8a0e\u3057\u305f\uff0e\u691c\u8a0e\u306b\u969b\u3057\u56f3 7(a)\uff0c(b)\uff0c(c)\u306b\u793a\u3059\u3088\u3046 \u306b\u8ef8 C-H\u304c\u8fba B-D\u304c\u5e73\u884c\u306a\u5834\u5408\uff08\u56f3 7(a)\uff09\uff0c\u8ef8 C-H\u3068\u8fba B-D\u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u5e83\u304c\u3063\u3066\u3044\u308b\u5834\u5408\uff08\u56f3 7(b)\uff09\uff0c\u8ef8 C-H\u3068\u8fba B-D\u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u72ed\u304f\u306a\u3063\u3066\u3044\u308b\u5834\u5408\uff08\u56f3 7(c)\uff09\u306e 3\u3064\u3092\u8003\u3048\u305f\uff0e\u3053\u3053\u3067\u3082\u8fba B-D\u306b\u5bfe\u3057\u3066\u8ef8 C-H\u304c\u306a\u3059\u89d2\u5ea6\u306f\u5927\u304d\u304f\u306a\u3044\u3082\u306e\u3068\u3059\u308b\uff0e\u307e\u305f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u56de\u8ee2\u306f\u56f3 6\u3068\u306f\u9006\u306e\u6642\u8a08\u307e\u308f\u308a\u306b \u306a\u308a\uff0c\u305d\u308c\u306b\u4f34\u3063\u3066\u8ef8 C-H \u3082\u540c\u3058\u65b9\u5411\u306b\u56de\u8ee2\u3059\u308b\u3068\u3059\u308b\uff0e\u307e\u305a\uff0c\u56f3 7(a)\u306e\u8ef8 C-H \u304c\u8fba B-D \u3068\u5e73\u884c\u306a\u5834\u5408\u3092\u8003\u3048 \u308b\uff0e\u3053\u306e\u5834\u5408\u306f\u8fba B-D\u3068\u8ef8 C-H\u306f\u7b49\u9577\u3067\u3042\u308b\u3068\u3059\u308b\u3068\uff0c\u56f3 6(a)\u3068\u540c\u69d8\u306b\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u751f\u3058\u306a\u3044\uff0e\u3064\u304e \u306b\uff0c\u56f3 7(b)\u306e\u3088\u3046\u306b\u8ef8 C-H\u3068\u8fba B-D\u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u5e83\u304c\u3063\u3066\u3044\u308b\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306f\uff0c\u70b9 C \u306e\u8eca\u4e21\u5185\u5074\u3078\u306e\u5909\u4f4d\u91cf\u304c\u70b9 B\u306e\u5909\u4f4d\u91cf\u3088\u308a\u3082\u5c0f\u3055\u304f\u306a\u308b\uff0e\u305d\u306e\u305f\u3081\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a4\u30f3\u306b\u306a\u308b\uff0e\u6700 \u5f8c\u306b\u56f3 7(c)\u306e\u3088\u3046\u306b\u8ef8 C-H\u3068\u8fba B-D\u306e\u9593\u9694\u304c\u8eca\u4e21\u5185\u5074\u306b\u5411\u304b\u3063\u3066\u72ed\u304f\u306a\u3063\u3066\u3044\u308b\u5834\u5408\u3092\u8003\u3048\u308b\uff0e\u3053\u306e\u5834\u5408\u306f\uff0c\u70b9", + "\u00a9 The Japan Society of Mechanical Engineers\nC\u306e\u8eca\u4e21\u5185\u5074\u3078\u306e\u5909\u4f4d\u91cf\u304c\u70b9 B\u306e\u5909\u4f4d\u91cf\u3088\u308a\u3082\u5927\u304d\u304f\u306a\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a \u308b\uff0e\u4ee5\u4e0a\u304b\u3089\uff0c\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u70b9 D \u307e\u308f\u308a\u306e\u30ed\u30a2\u30a2\u30fc\u30e0\u56de\u8ee2\u65b9\u5411\u306f\u70b9 B \u3068\u70b9 D \u306e\u524d\u5f8c\u4f4d\u7f6e\u95a2\u4fc2\u306b\u3088\u3063\u3066\u6c7a\u5b9a\u3055 \u308c\uff0c\u305d\u306e\u56de\u8ee2\u6319\u52d5\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306e\u65b9\u5411\u306f\uff0c\u8fba B-C \u304a\u3088\u3073\u8ef8 C-H \u306e\u30ea\u30f3\u30af\u4f5c\u7528\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\u3053\u3068\u304c\u5206\u304b \u308b\uff0e\u307e\u305f\u30c8\u30fc\u89d2\u5909\u5316\u91cf\u306f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u56de\u8ee2\u89d2\u306e\u5927\u304d\u3055\u3068\u30ea\u30f3\u30af\u4f5c\u7528\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\u3053\u3068\u304c\u5206\u304b\u308b\uff0e\n3\u30fb4 \u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316 \u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u70b9 A\u304c\u8eca\u4e21\u5916\u5074\u3078\u5909\u4f4d\u3057\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u304c\u8ef8 B-C\u307e\u308f\u308a\u306b\u8eca\u4e21\u5f8c\u65b9\u304b\u3089\u898b\u3066\u6642\u8a08 \u307e\u308f\u308a\u306b\u56de\u8ee2\u3059\u308b\u3053\u3068\u306b\u8d77\u56e0\u3057\u3066\u751f\u3058\u308b\u3082\u306e\u3067\u3042\u308b\uff0e\u305f\u3060\u3057\uff0c\u70b9 B, C\u306e\uff39\u8ef8\u65b9\u5411\u5909\u4f4d\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\u3059\u3067\u306b \u30e2\u30fc\u30c9\u2160\u304a\u3088\u3073\u30e2\u30fc\u30c9\u2161\u3067\u8003\u616e\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u8b70\u8ad6\u3059\u308b\u5834\u5408\u306b\u306f\u70b9 B, C\u306f\u5909\u4f4d\u3057\u306a\u3044 \u3082\u306e\u3068\u3059\u308b\uff0e\u56f3 4(a)\u306b\u793a\u3059\u3088\u3046\u306b\uff0c\u70b9 B\u304c\u70b9 C\u3088\u308a\u4f4e\u3044\u5834\u5408\u306f\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u56de\u8ee2\u306f\u5e73\u9762\u8996\u4e0a\u3067\u6642\u8a08\u307e\u308f\u308a\u306e\u6210\u5206 \u3092\u3082\u3064\u3053\u3068\u306b\u306a\u308a\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u3068\u306a\u308b\uff0e\u305d\u3057\u3066\u540c\u6642\u306b\u30dd\u30b8\u30c6\u30a3\u30d6\u65b9\u5411\u3078\u306e\u30ad\u30e3\u30f3\u30d0\u89d2\u5909 \u5316\u3092\u751f\u3058\u308b\uff0e\u9006\u306b\u70b9 B\u304c\u70b9 C\u3088\u308a\u9ad8\u3044\u5834\u5408\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a4\u30f3\u3068\u306a\u308a\uff0c\u540c\u6642\u306b\u30dd\u30b8\u30c6\u30a3\u30d6\u65b9\u5411\u3078\u306e\u30ad\u30e3\u30f3\u30d0 \u89d2\u5909\u5316\u3092\u751f\u3058\u308b\uff0e\u70b9 B\u3068 C\u304c\u540c\u3058\u9ad8\u3055\u306e\u5834\u5408\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u306f\u751f\u3058\u305a\uff0c\u30dd\u30b8\u30c6\u30a3\u30d6\u65b9\u5411\u3078\u306e\u30ad\u30e3\u30f3\u30d0\u89d2\u5909\u5316\u306e\u307f\u304c \u751f\u3058\u308b\uff0e\u4ee5\u4e0a\u304b\u3089\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306e\u65b9\u5411\u306f\uff0c\u70b9 B\u3068\u70b9 C\u306e\u4e0a\u4e0b\u65b9\u5411\u306e\u4f4d\u7f6e\u95a2\u4fc2\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\uff0c\u30c8\u30fc \u89d2\u5909\u5316\u306e\u5927\u304d\u3055\u306f\u8ef8 B-C \u306e\u524d\u5f8c\u65b9\u5411\u3078\u306e\u50be\u304d\u89d2\uff0c\u304a\u3088\u3073\u8ef8 B-C \u307e\u308f\u308a\u306e\u70b9 A \u306e\u56de\u8ee2\u89d2\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\u3053\u3068\u304c \u5206\u304b\u308b\uff0e\n3\u30fb5 LF-C/S\u3068\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u8af8\u5143\u306e\u307e\u3068\u3081 \u3053\u3053\u3067\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u306b\u304a\u3051\u308b LF-C/S \u3068\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u8af8\u5143\u306e\u95a2\u4fc2\u306b\u3064\u3044\u3066\u307e\u3068\u3081\uff0c \u8a2d\u8a08\u3078\u5fdc\u7528\u3059\u308b\u969b\u306e\u6307\u91dd\u306b\u3064\u3044\u3066\u8ff0\u3079\u3066\u304a\u304f\uff0eLF-C/S\u306f\u30e2\u30fc\u30c9\u2160, \u2161, \u2162\u304b\u3089\u306a\u308b\uff0e\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u56f3 4(a)\u306b\u793a\u3059\u5bf8\u6cd5 b, c \u306e\u6bd4\u304a\u3088\u3073\u3070\u306d\u5b9a\u6570 kDY\u3068 kHY\u3067\u6c7a\u307e\u308a\uff0c\u4e00\u822c\u7684\u306a FF \u7528\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7 \u30f3\u3067\u306f\u30c8\u30fc\u30a4\u30f3\u306b\u306a\u308b\u3053\u3068\u304c\u591a\u3044\uff0e\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u70b9 B, C, H, D\u3092\u3064\u306a\u3044\u3067\u5f97\u3089\u308c\u308b\u30ea\u30f3\u30af\u6a5f\u69cb\u306e \u914d\u7f6e\u306b\u3088\u308a\u30c8\u30fc\u89d2\u5909\u5316\u65b9\u5411\u304c\u6c7a\u5b9a\u3055\u308c\uff0c\u30c8\u30fc\u30a4\u30f3\u30c8\u30fc\u30a2\u30a6\u30c8\u306e\u3069\u3061\u3089\u306e\u65b9\u5411\u306b\u3082\u306a\u308a\u5f97\u308b\uff0e\u307e\u305f\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u91cf \u306f\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u5e73\u9762\u8996\u56de\u8ee2\u89d2\u306e\u5927\u304d\u3055\u3068\u30ea\u30f3\u30af\u4f5c\u7528\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\uff0e\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306e\u65b9\u5411\u306f\uff0c\u70b9 B \u3068\u70b9 C \u306e\u4e0a\u4e0b\u65b9\u5411\u306e\u4f4d\u7f6e\u95a2\u4fc2\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u306e\u5927\u304d\u3055\u306f\u8ef8 B-C \u306e\u524d\u5f8c\u65b9\u5411\u3078\u306e\u50be\u304d\u89d2\u304a\u3088\u3073\u8ef8 B-C \u307e\u308f\u308a\u306e\u70b9 A \u306e\u56de\u8ee2\u89d2\u306b\u3088\u308a\u6c7a\u5b9a\u3055\u308c\u308b\uff0e\u4e00\u822c\u7684\u306a FF \u7528\u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u3067\u306f\uff0c\u70b9 B \u306f\u70b9 C\u3088\u308a\u3082\u4f4e\u3044\u4f4d\u7f6e\u306b\u8a2d\u5b9a\u3055\u308c\u308b\u305f\u3081\uff0c\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u306a\u308b\uff0e\u30e2\u30fc\u30c9\u2160\uff0c\u30e2\u30fc\u30c9\u2161\uff0c\u30e2\u30fc\u30c9\u2162\u306e 3\u3064" + ] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure11-1.png", + "caption": "Figure 11. Thermal field distribution under condition of only water cooling used in the casing when both the SM and the DRM are running at the rated speed and load.", + "texts": [ + "0242 W/m\u00b7K, so the thermal resistance of the inner and outer air gap is quite big, making the heat-dissipating capability of the inner rotor poor. Therefore, when the SM and the DRM are still running at full load of 32 Nm under the low speed condition, there is still an overheating problem for the CS-PMSM. When both the SM and the DRM are running at the rated speed and rated load, the 3-D thermal field distribution is calculated under condition of only water cooling used in the casing, as shown in Figure 11. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the water inlet side, middle cross-section, and the water outlet side of the CS-PMSM are shown in Figure 12. In order to eliminate the effects of end face boundary conditions, the selected water inlet and water outlet cross-sections are 2.5 mm away from the corresponding end face, respectively. The highest temperature of different parts in the above three cross-sections is shown in Table 6. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004768_9668973_09764722.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004768_9668973_09764722.pdf-Figure4-1.png", + "caption": "FIGURE 4. Configuration of the conventional NO model and the GO model. (a) NO model. (b) GO model.", + "texts": [ + " However, the flux path on the teeth part is constant in the radial direction regardless of the rotor position. Therefore, when the GO is applied to the teeth part, magnetic flux flows in the rolling direction of the core, and the effect of improving the performance of the motor can be high, which can be confirmed from Fig. 1. C. PERFORMANCE COMPARISON OF THE NO MODEL AND THE GO MODEL Based on the magnetic flux path analysis results of the NO model, the GO is applied to the stator teeth part to enhance the performance of the IPMSM. The configurations of the NO and GO models are shown in Fig. 4. The GO model has a connection part at the boundary of the NO and GO, so that the teeth can be fixed to the attraction between the rotor and the stator. The load and no-load condition analysis using FEA is conducted, and the detailed analysis results and comparison are tabulated in Table 2. In detail, for the no-load condition, the iron loss of the GOmodel was 25.40% reduced compared with the NO model. The line to line back-electromotive force (B-EMF) was 0.53% increased, the B-EMF total harmonic distortion (THD) was 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001833_jeee.2013.010202.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001833_jeee.2013.010202.pdf-Figure1-1.png", + "caption": "Figure 1. The switched reluctance machine", + "texts": [ + "eywords Switched Reluctance Motor, Winding Faults, Fault Detection, Fault Tolerance. The switched reluctance motor (SRM) is a double salient electrical machine with a passive rotor (see Figure 1). Its stator is manufactured of punched laminations bonded into a stack. The rotor, made also of conventional laminations, is passive, having no windings, excitation, squirrel-cage or permanent magnets [1, 2]. A phase winding comprises two coils placed on opposite poles connected in series. The excitation must be a sequence of current pulses applied to each phase in turn. Its operation is based on the variable reluctance principle [3]. The torque is produced by the tendency of the rotor to reach a position where the inductance and the flux produced by the energized winding are maximized" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001261_354-68291802051P.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001261_354-68291802051P.pdf-Figure2-1.png", + "caption": "Figure 2: T-cross section", + "texts": [ + " As for the MATLAB software package, to use the functions fmincon and use the expressions (5) and (6), respectively: [ ] ( ), , , , , , , 0, , , , , , ,X fval exitflag output lambda grad hessian fmincon fun X A b Aeq beq lb ub nonlcon= (5) [ ] ( ), , , , , , , , , , ,X fval exitflag output ga fun n A b Aeq beq lb ub nonlcon= (6) Analysis and Optimization of T-cross section of Crane Hook Considered as Curved Beam where the explanations of the MATLAB function are shown: fval - the value of solving target function, exitflag - shows the reason for the termination of solving execution, fun - objective function, output - shows the output informationduring optimization, nonlcon - calculating of non-linear inequality, lambda - Laqngrange multiplier, grad - the gradient of objective function in point X, hessian - the Hessian value of objective function in point X, 0X - the vector of initial values of optimization parameters, ,b beq - vectors, ,A Aeq - matrices, ( ), ( )C X Ceq X - vector functions. The PSO optimization algorithm is defined according to [18], and with that algorithm the optimal value are determined. Figure 1 shows a standard crane hook according to [19], as well as a critical cross section (I - I) on which the T-cross section is viewed (the right part of the section from the axis of loading force). The mathematical formulation of the objective function is shown as follows (Figure 2): 1 2 3 4( ) ( ) ( ) ( )T T T tf X A X A x x x x A b t h d= = = (7) The input parameters vector is: ( ), , dx Q a \u03c3= r (8) where are: Q - load capacity of crane hook, a - diameter of inner fiber of hook, [19] (Fig. 1), d\u03c3 - critical stress, [19]. Below text will showdetailed objectives and constraints. 4. OBJECTIVE FUNCTIONS AND CONSTRAINTS 4.1. Objective function The objective function is represented by the area of T-cross section of crane hook at the most critical place. (Figure 2). The cross-sectional area, or the objective function, is: T tA b t h d= \u22c5 + \u22c5 (9) 4.2. Constraint functions Optimization processes are based on permissible stresses, according to Winkler-Bach theory. The total deformation of fibers in the curved beam is proportional to the distance of the fiber from the neutral surface (axis). The strains of the fibers are not proportional to these distances, since the fibers are not equal in length, unlike the straight beam. In the case of bending stress that does not exceed the permitted flow stress limit, the stress of any fiber of the beam is proportional to the stress of the fibers, so that the elastic stresses in the fibers of the curved beam are not proportional to the distance from the neutral surface. For the same reason, the neutral axis in the curved beam does not pass through the center of gravity of the cross-section. The mathematical formulation of the constrain functions, according to the allowed stresses, [20] in characteristic points (Figure 2) is:: max 1 1 1 1 Q d T x F M hg A S R \u03c3 \u03c3= = + \u22c5 \u2264 (10) and max 2 2 2 2 Q d T x F M hg A S R \u03c3 \u03c3= = \u2212 \u22c5 \u2264 (11) where are: 1 1h r R= \u2212 (12) 2 2h R r= \u2212 (13) 1 2H h t h h= + = + (14) 1 2 aR = (15) 2 2 aR H= + (16) Pavlovi\u0107, G, - Savkovi\u0107, M. - Zdravkovi\u0107, N. - Markovi\u0107, G. - Stanojkovi\u0107 J. 1 1cR R e= + (17) 2 2 1 2 2 t T b t h d t h d e A \u22c5 + \u22c5 \u22c5 \u22c5 + \u22c5 = \u22c5 (18) o cy R r= \u2212 (19) T A Ar dA \u03c1 = \u222b (20) 2 2ln ln 2t A dA a t a Hb d a a t\u03c1 + \u22c5 + \u22c5 = \u22c5 + \u22c5 + \u22c5\u222b (21) QF Q g= \u22c5 (22) max Q cM F R= \u22c5 (23) x T oS A y= \u22c5 (24) where are: 1R - radius of inner fiber (Fig. 2), 2R - radius of outer fiber (Fig. 2), cR - polupre\u010dnik te\u017ei\u0161ne ose (Fig. 2), r - radius of neutral axis (Fig. 2), oy - distance between centroidal axis and neutral axis (Fig. 2), QF - axial force (Fig. 1), maxM - maximum bending moment, xS - static moment of area. 5. NUMERICAL REPRESENTATION OF OPTIMIZATION RESULTS Optimization is performed using the following optimization algorithms: GRG2 algorithm and EA algorithm, using the Solver Tool tool in the Analysis module in the Ms EXCEL software package; using the fmincon functions according to [16] and ga according to [17], in MATLAB software package; using the optimization algorithm for the PSO, according to [18], in MATLAB software package. The optimization parameters are the height h, the thickness d, the width bt and the thickness of the base t, of T-cross section (Figure 2). The geometric parameter a (Figure 1) is taken as the input size, according to standard [19] and is not the subject of optimization. Input optimization parameters are: FQ = 100 kN, a = 12.5 cm and \u03c3d = 8 kN/cm2. A standard crane hook with a load capacity of 10 t is observed. The cross sectional area of crane hook at the most critical place, in relation to which the optimal results are compared, is: As = 109.9 cm2, according to [19]. The values of minimum thicknesses t and d are not less than 1 cm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004937_f_version_1639053480-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004937_f_version_1639053480-Figure5-1.png", + "caption": "Figure 5. Computer aided design of SolidWorks simulation using multi-degrees of freedom.", + "texts": [ + " Machines 2021, 9, 349 6 of 40 Machines 2021, 9, x FOR PEER REVIEW 7 of 42 4. Numerical Simulation 4.1. Detachment Detection through Follower Displacement (a) SolidWorks program was used in the modeling of computer aided design (CAD), [21]. In the numerical simulation, the follower moved with three degrees of freedom (up-down, right-left, and rotation about z-axes). The two rollers in both sides between the wall and the mass of the spring\u2013damper system helped the multi-degrees of freedom moved up and down as indicated in Figure 5. In SolidWorks program, there were three types of integrator, (GSTIFF), (SI2-GSTIFF) and (WSTIFF), in which the integrator of the type (GSTIFF) was selected. The (GSTIFF) solves the complex nonlinear dynamics system, and it can be operated over a range of speeds of the cam. The integrator (GSTIFF) works with maximum iteration (50), initial integrator step size (0.0001), minimum integrator step size (0.0000001), and maximum integrator step size (0.001). The dimensions of cam, flat-faced follower, and the two guides are taken from Ref", + "5 mm), outside diameter (OD = 10 mm), and the spring stiffness (K = 400 N/m). 4. u erical Si ulation 4.1. Detachment Detection through Follower Displacement (a) SolidWorks program was used in the modeling of computer aided design (CAD), [21]. In the numerical simulation, the follower moved with three degrees of freedom (updown, right-left, and rotation about z-axes). The two rollers in both sides between the wall and the mass of the spring\u2013damper system helped the multi-degrees of freedom moved up and down as indicated in Figure 5. In SolidWorks program, there were three types of integrator, (GSTIFF), (SI2-GSTIFF) and (WSTIFF), in which the integrator of the type (GSTIFF) was selected. The (GSTIFF) solves the complex nonlinear dynamics system, and it can be operated over a range of speeds of the cam. The integrator (GSTIFF) works with maximum iteration (50), initial integrator step size (0.0001), minimum integrator step size (0.0000001), and maximum integrator step size (0.001). The dimensions of cam, flat-faced follower, and the two guides are taken from Ref", + " X(t) X(t) + R2 b The analytic solution of the follower displacement is as in below because the follower displacement is varied in x and y directions: X = \u221a X2 1 + X2 2 (A13) Appendix B The numerical simulation of SolidWorks program were illustrated in the following steps as in below: (a) Ten parts such as (polydynecam.SLDPRT, flat-facedfollower.SLDPRT,guideno1.SLDPRT, guideno2.SLDPRT, outsideframe.SLDPRT, massboxno1.SLDPRT, massboxno2.SLDPRT, massboxno3.SLDPRT, massboxno4.SLDPRT, and cylindricalrollers.SLDPRT) has been created using the modeling computer aided design (CAD) of SolidWorks program. It Machines 2021, 9, 349 39 of 40 can be assembled the above nine parts using camfollowerassembly.SLDASM to obtain Figure 5. (b) Select Motion Analysis from Motion Study Tab and select number frames per second equal to 1000 to make the solution of the dynamic motion more accurate. (c) Select the Option of Units from Document Properties Tab and select MMGS. (d) Select Gravity from Motion Study Tab and select the y-direction. (e) Select Contact from Motion Study Tab and check mark the box of Use Contact Groups in which there will be two boxes. Select the cam geometry in the first box and select the follower geometry in the second box to make the contact between the cam and the follower" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000639_mtime_20170330153413-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000639_mtime_20170330153413-Figure10-1.png", + "caption": "Figure 10: Equilibrium after moving the external force Nd to the position of the steel reinforcement.", + "texts": [], + "surrounding_texts": [ + "lation case, assuming \u03b5c>\u03b5c3. The goal of the design is again to calculate the needed cross sectional area of steel reinforcement As. In order to calculate As, we need first to calculate the unknown quantities x, z1 and z2. We move again the external force Nd to the position of the steel reinforcement and we have the figure below. We need to determine if at the ULS the concrete zone or the steel is at the critical strain. Again, first we put both materials at the ultimate strain, so we have: 3c cu (34) s ud (35) 3 33 3 3 3 3 31 1 3 cu ud cucu ud cu cu c cu c ud cu x d x d x x d (36) 1 1c cdF x f b (37) Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 1 1 2 x z d (38) 2 1 1 2c cdF x x f b (39) 1 1 2 1 2 3 3 x x x x z d x d (40) 1 2c c cF F F (41) We will calculate the sum of moments at the steel reinforcement position. The sign of the sum of moments will show us whether the concrete zone or the steel is at the ultimate strain at the ULS. The sum of moments is (clockwise positive): 1 1 2 2steel c c sdM F z F z M (42) We have then two cases: Case 1. \u03a3\u039c\u22650 The concrete force has to be decreased for the equilibrium of the cross section. The steel stays at the ultimate strain (\u03b5s=\u03b5ud), while for concrete \u03b5c\u2264\u03b5cu3, as shown in the figure below. Case 2. \u03a3\u039c<0 The concrete force has to be increased for the equilibrium of the cross section. Concrete stays at the ultimate strain (\u03b5c=\u03b5cu3), while for steel \u03b5s<\u03b5ud, as shown in the figure below. For both cases, we need to determine the value of x that satisfies the equilibrium of the cross section. After having determined x, we can then proceed with the other calculations and Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis finally end up with the needed reinforcement area As. The value of x can be determined by using trial and error iterations, or by using some kind of optimization in order to achieve section equilibrium. Good tools for this are MS Excel (Goal Seek or Solver functions) and also Matlab with its built-in root-finding and optimization tools. In the present study, we have used three equivalent approaches, (a) Solver function of MS Excel, (b) Matlab and (c) a homemade code which finds x by performing iterations, dividing the allowable height of the section by two at each iteration until convergence (equilibrium). All three approaches provide the same results at the end, as expected. In the next sections, we will assume a value for x and we will end up with the equilibrium equation, i.e. the sum of moments at the steel reinforcement position which has to be zero at the equilibrium. Case 1. \u03a3\u039c\u22650, Steel at the ultimate strain We assume an initial value for x and we use the following equations: s ud (43) c ud c ud x x d x d x (44) Case 1a: If \u03b5c>\u03b5c3 In this case we have the triangular diagram plus a rectangular diagram for the concrete zone and the upmost fiber of the concrete section works at the ultimate stress fcd. From the similar triangles we have: 31 1 3 c c c c c s c s x d x d (45) 1 1c cdF x f b (46) 1 1 2 x z d (47) 2 1 1 2c cdF x x f b (48) 1 1 2 1 2 3 3 x x x x z d x d (49) 1 2c c cF F F (50) 1 1 2 2steel c c sdM F z F z M (51) After we reach the equilibrium (\u03a3\u039csteel=0), and given that the steel reinforcement works in full stress, above the yield strain, the steel area can be easily calculated by Eq. (31). Case 1b: If \u03b5c\u2264\u03b5c3 In this case we have only the triangular diagram for the concrete zone, there is no rectangular part for the stresses and the upmost fiber of concrete works at stress \u03c3c\u2264fcd, as follows: 3 c c cd cd c f f (52) Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 2 1 2c cF x b (53) 2 3 x z d (54) 2c cF F (55) 2 2steel c sdM F z M (56) Again, after we reach the equilibrium (\u03a3\u039csteel=0), and given that the steel reinforcement works in full stress, above the yield strain, the steel area can be calculated by Eq. (31). Case 2. \u03a3\u039c<0, concrete zone at the ultimate strain We assume an initial value for x and we use the following equations: 3c cu (57) 3 3 3 3 3 31 1 3 s cu cu s cu c cu c cu s d x x x d x x x d (58) 1 1c cdF x f b (59) 1 1 2 x z d (60) 2 1 1 2c cdF x x f b (61) 1 1 2 1 2 3 3 x x x x z d x d (62) 1 2c c cF F F (63) 1 1 2 2steel c c sdM F z F z M (64) Case 2a: \u03b5s\u2265\u03b5ys The steel reinforcement works in full stress, above the yield strain and as a result the steel area can be calculated by Eq. (31). Case 2b: \u03b5s<\u03b5ys The steel reinforcement does not work in full stress, as it works below the yield strain. The steel stress \u03c3s can be calculated by Eq. (28) and the steel area can be calculated by Eq. (25)." + ] + }, + { + "image_filename": "designv8_17_0004698_e_download_3551_3389-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004698_e_download_3551_3389-Figure5-1.png", + "caption": "Fig. 5. Re-structuring of networks for efficient utilization of LUTs", + "texts": [ + " This requires transferring some subnetworks from their original networks to sub-networks that belong to different networks. For example sub-network X0 that originally belonged to 4(a) is now transferred to 4(b) and included with sub-networks X2 and Z1. This re-structuring of sub-networks ensures a proper utilization of the LUT fabric. Note that the 6-input LUTs in Xilinx FPGAs can implement a single 6-input function or two 5-input functions with shared inputs. The re-structured sub-networks are shown in figure 5. The re-structured sub-networks are then efficiently mapped onto 6-input LUTs by directly mapping their functionalities onto these target elements. Re-construction and Re-timing: The parent network is then constructed by connecting the mapped networks from step III. The overall structure is a simple feed-forward structure having a unidirectional dataflow. This feed-forward nature lends itself for efficient pipelining by simply placing the registers along the feed-forward cut-sets. The final mapped and re-timed structure is shown in figure 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure19-1.png", + "caption": "Figure 19: FEA results of the first iteration of conceptual design.", + "texts": [ + "5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0.5 mm. When the thickness of the joint is 0.5 mm the force that can be applied is very small. This poses two problems, manufacturability and application" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004544__39_article-p159.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004544__39_article-p159.pdf-Figure13-1.png", + "caption": "Fig. 13 Cardan shaft assembled from two universal joints (a- incorrect, b- correct)", + "texts": [ + " When the angle \u03b1 between the input driving shaft and central cardan shaft (central cardan shaft and output driven shaft) grows, then the amplitude of angular acceleration grows too. The third case simulates the variable cardan shaft where the angle \u03b1 changes value from -40\u00b0 to 40\u00b0 while the input driving shaft did four turns (1440\u00b0). Fig. 12 shows angular acceleration during the whole kinematic analysis. This type of analysis also proves that if angle \u03b1 is decreasing then angular acceleration is decreasing too and viceversa. If we want to use a cardan shaft for higher axis deviation then we should use a design with two universal joints as you can see in Fig. 13b. With this solution, there are two deviation axis \ud835\udefc1 and \ud835\udefc2 which generate two cardan errors of the same size but opposite direction. The results from kinematic simulation obtained through the CAD/CAM/CAE system CATIA V5 proves theory analytically obtained equations. The use of one universal joint will lead to an angular velocity and acceleration with sinusoidal shape on the driven shaft as can be seen in Figs. 7, 10 and 12. This state is also valid for a central cardan shaft, when the cardan shaft is assembled from two universal joints. By using two universal joints, a stabilized rotational speed is achieved at the output driven shaft (Fig. 13b). If the cardan shaft is assembled incorrectly as you can see in Fig. 13a, then the angular speed and acceleration of the output driven shaft will be affected by two cardan errors. This state is very bad for the whole machine because vibrations caused by incorrectly assembled cardan shaft can lead to permanent failure of the machine. This paper has been supported by the Scientific Grant Agency of the Slovak Republic VEGA under the grants No. 1/0477/14 and MTF2016/006. This publication was realized through the project: \"UNIVERSITY SCIENTIFIC PARK: CAMPUS MTF STU - CAMBO\" (ITMS: 26220220179) supported by the Research & Development Operational Program funded by the EFRR" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004329_f_version_1614262193-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004329_f_version_1614262193-Figure1-1.png", + "caption": "Figure 1. Sections of a polymer liner/mandrel with boss connection.", + "texts": [ + " [16] observed higher matrix cracking at the dome-cylinder interface through the SEM analysis, in comparison to the cylindrical section. This region was seen to be prone to high stress concentration during the hydrostatic test. This article analyses the effect of different dome geometries on the stress distribution at the domecylinder interface. A cylindrical pressure vessel can be divided into three sections; a cylindrical section and two domes. The valves or boss is attached to one end of the dome as shown in the Figure 1 and these are usually symmetric, meaning both domes are similar, but they can also vary depending on the application. In filament winding, one can differentiate between geodesic and non-geodesic paths for the fibre. While the designing and the winding of the cylindrical section can be done with relative ease, doing this for the dome section can be quite challenging. Since orthotropic materials are used to make CPV\u2019s, one begs the question as to whether there is an optimal dome contour that can be achieved" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.25-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.25-1.png", + "caption": "Figure 2.25 : Motor oil cooling, (left) circuit illustration, (right) with rotor and shaft with holes [133].", + "texts": [ + " Most of the concerned authors suggested using oil as a coolant in internal liquid channels for electric safety reasons. To improve the performance at low speed and high torque of a 43 kW induction motor (TEFC machine with turbine fitted on the external part of the shaft and housing fins), Assaad et al. [133] proposed to integrate an oil cooling circuit in a hollow shaft having three holes inside the motor. These holes are used for oil injection directly on motor active parts and are illustrated in Figure 2.25. Nategh et al. [36] proposed oil jackets used for both stator and end-windings cooling. They simulated and tested experimentally two machines made respectively with two different impregnation materials (varnish and epoxy) and under different cooling conditions and losses levels. In their system, after flowing in the stator channels, the oil drops off on the outer surface of the end winding body and is then collected at the bottom side of the housing. The collected oil is emptied using two outlets mounted in both end shields" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004097_s-2682592_latest.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004097_s-2682592_latest.pdf-Figure11-1.png", + "caption": "Fig. 11 Semi-active damping solutions between inter-vehicles and associated technical implementation. (a) 773 Motor-trailer-motor trainset with relevant parameters. (b) Cracks occur on lower part of outer windshield at 774 both sides. (c) Semi-active damping implementation with stiffness and damping in lateral and vertical 775 directions per constraint point. (d) Principles of pneumatic technique when activated or inactivated. 776", + "texts": [ + " the self-excited 752 vibration of car body up-swung or roll mode occurs within the range of vehicle speed 753 (140 - 200) km/h at \u03bbe < 0.10. When the anti-roll torsion bar device is not activated, the 754 above self-excited vibration will be converted into the modal vibration of car body yaw. 755 Therefore, the self-adaptive improved design needs a low-cost solution to remove or 756 eliminate the car body instability. 757 4.2 Solution to car body instability at minimum cast 758 Combined with the specific application of outer windshield [54], as shown in Fig. 11, the 759 implementation of semi-active damping technique between inter-vehicles is proposed 760 with the conservation principle of momentum, i.e. the inertia moment of car body yaw is 761 much greater than that of car body roll, Izz>>Ixx, At the same time, this technical 762 implementation also avoids cracks in the lower part of outer windshield on both sides due 763 to slot disturbance effects. 764 Like the self-adaptive improved design of high-speed bogies with four ZF Sachs 765 T60 per bogie [55], the dynamic simulation of three-vehicle trainset shown in Fig. 11a 766 can also prove that this low-cost solution will improve the influence of car body 767 instability on ride comfort, and the lateral evaluation index Wz<2.5 within the range of 768 vehicle speed (140 - 200) km/h at 0.03< \u03bbe \u2264 0.10. Compared with the integrated 769 suspension control solution of car body lateral and roll [40], the semi-active damping 770 technique is technically reliable and easy to maintain between inter-vehicles. 771 4.3 Comprehensive assessment of safety and stability 777 By using three different wheel profile designs and the lateral span variations of nominal 778 rolling circles, as shown in Table 2, the eight different conditions are constructed for 779 wheel-rail matching" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001707_O201511639883976.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001707_O201511639883976.pdf-Figure12-1.png", + "caption": "Fig. 12. Antenna return loss and radiation pattern for Model_2.", + "texts": [], + "surrounding_texts": [ + "\uc804\ubc29\ud5a5 \ud328\ud134\uc744 \uac16\uace0 \uc788\ub2e4. \ub530\ub77c\uc11c, \ubcf8 \ub17c\ubb38\uc5d0\uc11c \ucc28\ub3d9\ubaa8\ub4dc\uc640 \uacf5\ud1b5\ubaa8\ub4dc\ub97c \ud615\uc131\ud55c\n\ub9e4\uce6d\uc2a4\ud130\ube0c\ub97c \uc0ac\uc6a9\ud558\uc5ec \ubaa8\ub178\ud3f4 \uc548\ud14c\ub098\uc758 \uc774\uc911\uacf5\uc9c4 \ud2b9\uc131 \uc758 \ub300\uc5ed\ud3ed, \ubc29\uc0ac\ud2b9\uc131\uc744 \uac1c\uc120\ud560 \uc218 \uc788\uc74c\uc744 \ud655\uc778\ud558\uc600\ub2e4. \uc774 \uacb0\uacfc\ub97c \uc0ac\uc6a9\ud558\uc5ec RFID/USN \ub300\uc5ed\uacfc WiFi \ub300\uc5ed\uc758 \uc8fc\ud30c\uc218\n\ub97c \uc0ac\uc6a9\ud558\ub294 \ucd08\uc18c\ud615 \ubb34\uc804\uae30\uc5d0 \uc801\ud569\ud55c \uc548\ud14c\ub098 \uc124\uacc4\uc5d0 \uc801 \uc6a9\ud560 \uc218 \uc788\uc74c\uc744 \ud655\uc778\ud558\uc600\ub2e4.\n\u2163. \uacb0 \ub860\n\ubcf8 \ub17c\ubb38\uc5d0\uc11c\ub294 \ub9e4\uce6d\uc2a4\ud130\ube0c\ub97c \uc0ac\uc6a9\ud558\uc5ec RFID/USN 920", + "MHz \ub300\uc5ed(917\uff5e923.5 MHz)\uacfc WiFi 2.4 GHz \ub300\uc5ed(2.4\uff5e 2.4835 GHz)\uc5d0\uc11c \ub3d9\uc791\ud558\ub294 \ubb34\uc804\uae30\uc6a9 \uc774\uc911\ub300\uc5ed \ubaa8\ub178\ud3f4 \uc548 \ud14c\ub098\ub97c \uc81c\uc548\ud558\uc600\ub2e4. \ubb34\uc804\uae30 \ud06c\uae30\ub294 52\u00d792 mm2\uc774\uace0, \uc548\ud14c \ub098 \ubd80\ubd84\uc758 \ud06c\uae30\ub294 52\u00d715 mm2 \ud06c\uae30\ub85c \uc81c\ud55c\ud558\uc600\uc73c\uba70, \uae30\ud310 \uc740 \ub450\uaed8\uac00 0.8 mm\uc774\uace0, \uae30\ud310\uc740 \uc0c1\ub300\uc720\uc804\uc728\uc740 4.4\uc778 FR4\n\uae30\ud310\uc744 \uc0ac\uc6a9\ud558\uc600\ub2e4. \ubaa8\ub178\ud3f4 \uc548\ud14c\ub098\uc758 \ud2b9\uc131 \uac1c\uc120\uc744 \uc704\ud574 \uc774\uc911 \uc2a4\ud130\ube0c\ub97c \uc0ac\uc6a9\ud558\uc5ec \ucc28\ub3d9\ubaa8\ub4dc\uc640 \uacf5\ud1b5\ubaa8\ub4dc\ub97c \ud615\uc131\ud558\n\ub3c4\ub85d \ud0ed\uc758 \uc704\uce58\ub97c \uc870\uc815\ud568\uc73c\ub85c\uc368 \ub9ac\uc561\ud134\uc2a4 \uac12\uc744 \uc870\uc815\ud558\uc5ec \uc548\ud14c\ub098\ub97c \uc124\uacc4\ud558\uace0, \uc81c\uc791\ud558\uc5ec \uc2e4\ud5d8\uc744 \ud1b5\ud574 \ubcf8 \ub17c\ubb38\uc758 \ud0c0 \ub2f9\uc131\uc744 \uc785\uc99d\ud558\uc600\ub2e4. \uc2e4\ud5d8\uacb0\uacfc, \uc774\uc911\ub300\uc5ed\uc11c \ubc18\uc0ac\uc190\uc2e4 10", + "dB\ub97c \ub9cc\uc871\ud558\uc600\uc73c\uba70, \ucd5c\ub300 \ub300\uc5ed\ud3ed\uacfc \uc548\ud14c\ub098 \uc774\ub4dd\uc740 RFID \ub300\uc5ed\uc5d0\uc11c 82 MHz(8.9 %)\uc640 3.17 dB, WiFi \ub300\uc5ed\uc5d0\uc11c 360 MHz(15.1 %)\uc640 1.95 dB\uc774\uba70, \ubc29\uc0ac\ud2b9\uc131\uc740 \uc804 \ubc29\ud5a5 \ud2b9\uc131\uc744 \uac16\uace0 \uc788\ub2e4. \ubcf8 \ub17c\ubb38\uc5d0\uc11c \ucc28\ub3d9\ubaa8\ub4dc\uc640 \uacf5\ud1b5\ubaa8\ub4dc\ub97c \ud615\uc131\ud55c \ub9e4\uce6d\uc2a4\ud130 \ube0c\ub97c \uc0ac\uc6a9\ud558\uc5ec \ubaa8\ub178\ud3f4 \uc548\ud14c\ub098\uc758 \uc774\uc911\uacf5\uc9c4 \ud2b9\uc131\uacfc \ub300\uc5ed\ud3ed, \ubc29\uc0ac\ud2b9\uc131\uc744 \uac1c\uc120\ud560 \uc218 \uc788\uc74c\uc744 \ud655\uc778\ud558\uc600\ub2e4. \uc774 \uacb0\uacfc\ub97c \uc0ac \uc6a9\ud558\uc5ec RFID/USN \ub300\uc5ed\uacfc WiFi \ub300\uc5ed\uc758 \uc8fc\ud30c\uc218\ub97c \uc0ac\uc6a9\ud558 \ub294 \ucd08\uc18c\ud615 \ubb34\uc804\uae30\uc5d0 \uc801\ud569\ud55c \uc548\ud14c\ub098 \uc124\uacc4\uc5d0 \uc801\uc6a9\ud560 \uc218 \uc788 \uc73c\uba70, \uc2dc\uc2a4\ud15c\uc5d0 \uc548\ud14c\ub098\ub97c \uc124\uacc4\ud568\uc73c\ub85c\uc368 \ubb34\uc804\uae30\uc758 \uc81c\uc870\uc6d0 \uac00 \uc808\uac10\uacfc \uc0dd\uc0b0\uc131\ud5a5\uc0c1\uc744 \uac00\uc838\uc62c \uc218 \uc788\uc73c\uba70, \uc544\uc6b8\ub7ec \ubb34\uc804 \uae30 \uc0dd\uc0b0\ub2e8\uac00\ub97c \uc808\uac10\ud558\uc5ec \uac00\uaca9\uacbd\uc7c1\ub825\uc744 \ud5a5\uc0c1\uc2dc\ud0ac \uc218 \uc788\ub2e4.\n[1] \ubc29\uc1a1\ud1b5\uc2e0\uc704\uc6d0\ud68c, \"\ub300\ud55c\ubbfc\uad6d \uc8fc\ud30c\uc218 \ubd84\ubc30\ud45c\", \ubc29\uc1a1\ud1b5\uc2e0 \uc704\uc6d0\ud68c \uace0\uc2dc \uc81c 2012-100\ud638, 2012\ub144 6\uc6d4. [2] \uc774\uc0c1\ud754, \uae40\uae30\uc900, \uc815\uc885\ud638, \uc724\uc601\uc911, \uae40\ubcd1\ub0a8, \"\uae30\uc0dd \ub8e8\ud504 \uad6c\uc870\ub97c \uc774\uc6a9\ud55c \ud734\ub300 \ub2e8\ub9d0\uae30\uc6a9 \ub2e4\uc911 \ub300\uc5ed \ucd08\uc18c\ud615 \ub8e8\ud504\n\uc548\ud14c\ub098\uc5d0 \uad00\ud55c \uc5f0\uad6c\", \ud55c\uad6d\uc804\uc790\ud30c\ud559\ud68c\ub17c\ubb38\uc9c0, 21(6), pp. 706-713, 2010\ub144 6\uc6d4. [3] \uc774\uc120\ud604, \uae40\ud638\uc9c4, \uc774\uc0c1\uc11d, \uc774\uc601\ud6c8 \uc678 3\uba85, \"Flexible pla-\nnar loop antenna \ud2b9\uc131\", \ud55c\uad6d\uc804\uc790\ud30c\ud559\ud68c \uc804\uc790\ud30c\uae30\uc220\ud558 \uacc4\ud559\uc220\ub300\ud68c, 12(1), p. 18, 2011\ub144 7\uc6d4. [4] \uc720\ud0dc\ud6c8, \uae40\ud0dc\ud615, \"UHF \ub300\uc5ed\uc6a9 CPW \uae09\uc804 \ucd08\uad11\ub300\uc5ed \ud3c9 \uba74\ud615 \ubaa8\ub178\ud3f4 \uc548\ud14c\ub098\", \ud55c\uad6d\uc804\uc790\ud30c\ud559\ud68c\ub17c\ubb38\uc9c0, 23(7), pp. 761-767, 2012\ub144 7\uc6d4. [5] \uae40\uae30\ubc31, \ub958\ud64d\uade0, \uc6b0\uc885\uba85, \"Bluetooth, WiMAX, UWB \uc2dc \uc2a4\ud15c\uc6a9 \uc5ed L\ud615 \ubb34\uae09\uc804 \uc18c\uc790 \uacb0\ud569 \ud504\ub9b0\ud2b8\ud615 \uad11\ub300\uc5ed \ud3f4 \ub514\ub4dc \ubaa8\ub178\ud3f4 \uc548\ud14c\ub098\", \ud55c\uad6d\uc804\uc790\ud30c\ud559\ud68c\ub17c\ubb38\uc9c0, 22(11), pp. 1101-1110, 2011\ub144 11\uc6d4. [6] \uc774\uc0c1\uc11d, \uc774\uc601\ud6c8, \"2.4 GHz \ub300\uc5ed\uc758 On-Board Broadband \uc548\ud14c\ub098 \ud2b9\uc131\", \ud55c\uad6d\uc804\uc790\ud30c\ud559\ud68c\ub17c\ubb38\uc9c0, 25(1), pp. 39-46, 2014\ub144 1\uc6d4. [7] \uc774\uc601\ud6c8, \ubc15\uc601\ubc30, \"\ubb34\uc804\uae30\uc758 On-board WiFi \uc548\ud14c\ub098 \ud2b9\uc131 \ubd84\uc11d\", \ud55c\uad6d\uc804\uc790\ud30c\ud559\ud68c \uc885\ud569\ud559\uc220\ub300\ud68c\ub17c\ubb38\uc9d1, 24(1), pp. 95, 2014\ub144 11\uc6d4 [8] Kin-lu Wong, Planar Antenna for Wireless Communications, Wiley, 2003. [9] C. A. Balanis, Antenna Theory Analysis and Design, 3rd Ed, Wiley Interscience, 2005. [10] H. Geroge, Practical Antenna Handbook, McGraw-Hill, 2011.\n\ubc15 \uc601 \ubc30\n2010\ub144 2\uc6d4: \uc2e0\ub77c\ub300\ud559\uad50 \uc804\uc790\uacf5\ud559\uacfc (\uacf5\ud559\uc0ac) 2012\ub144 2\uc6d4: \uc2e0\ub77c\ub300\ud559\uad50 \uc804\uc790\uacf5\ud559\uacfc (\uacf5\ud559\uc11d\uc0ac) 2011\ub144 2\uc6d4\uff5e\ud604\uc7ac: \uc138\uc601\uc815\ubcf4\ud1b5\uc2e0 \uc911\uc559\uc5f0\uad6c\uc18c \uc120\uc784\uc5f0\uad6c\uc6d0\n[\uc8fc \uad00\uc2ec\ubd84\uc57c] RF \uc218\ub3d9\ubd80\ud488, \ud3c9\uba74\ud615 \uc548\ud14c\ub098 \ub4f1\n\uc774 \uc0c1 \uc11d\n1982\ub144 2\uc6d4: \ucda9\ubd81\ub300\ud559\uad50 \uc804\uae30\uacf5\ud559\uacfc (\uacf5\ud559\uc0ac) 1984\ub144 2\uc6d4: \ucda9\ubd81\ub300\ud559\uad50 \uc804\uae30\uacf5\ud559\uacfc (\uacf5\ud559\uc11d\uc0ac) 1989\ub144 2\uc6d4: \uad11\uc6b4\ub300\ud559\uad50 \uc804\uae30\uacf5\ud559\uacfc (\uacf5\ud559\ubc15\uc0ac) 1989\ub144 8\uc6d4\uff5e\ud604\uc7ac: \ud55c\uad6d\uc804\uc790\ud1b5\uc2e0\uc5f0\uad6c\uc6d0\n\ucc45\uc784\uc5f0\uad6c\uc6d0 [\uc8fc \uad00\uc2ec\ubd84\uc57c] RF \uc218\ub3d9\ubd80\ud488, \ud3c9\uba74\ud615 \uc548\ud14c\ub098 \ub4f1" + ] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure2-1.png", + "caption": "Figure 2. Three failure mechanisms for a mechanically fastened composite joint [4]", + "texts": [ + " Ger [13] mentioned there must be a significant safety factor applied to take into account bearing strength variations with loading rate. The failure modes might also be affected due to an increased loading rate. 1.3.2 Types of Failure in Mechanically Fastened Composite Joints According to Larry Lessard [2], it has been observed experimentally that mechanically fastened composite joints fail under three basic mechanisms: net-tension, shear-out, and bearing (in addition, combinations of these mechanisms are often given separate names). Typical damage mechanism is shown below in Figure 2. Looking at previous work, a net-tension and a shear-out failure are more catastrophic than a bearing failure. The best way to see if a bearing failure has occurred is to look at the bearing stress vs. bearing strain plot. Once the stress gets to its peak value and suddenly drops off to zero, then one can conclude it was a shear-out or a net-tension failure. If after the ultimate bearing stress, the specimen continues to carry load but deforms as a result, this means that the joint was designed very safely" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002607_wnload_140647_130388-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002607_wnload_140647_130388-Figure2-1.png", + "caption": "Figure 2: An Auger", + "texts": [ + " The mass of shaft is the product of density and volume, The volume of flight, Where D, is the screw/conveyor diameter; d, is the shaft diameter and t, thickness Okafor [6] computed the power to overcome the mass as: In (4), the mean peripheral velocity, Vm is given by where Tm, is the lead of screw and N is revolution per minute of screw. Similarly, throughput capacity can be computed as; Where D is the outer screw diameter, d is the inner screw diameter, is the screw lead, n is the rotational speed, C is the correction factor based on the angle of inclination which is taken as 1, is the filling coefficient of the screw cross section and is the bulk density of the pulverized grass. Figure 2 shows a typical auger used to convey biomass to the grinding plate. Nigerian Journal of Technology Vol. 35, No. 3, July 2016 529 Hence the power required to convey the grass can be derived thus; Q, is the conveyor capacity; L is the projected length of the screw conveyor; Fm is the material factor and W is the bulk density. Khumi [2] shows that the force required for actual grinding of the grass is the product of pressure and the surface area of contact. The surface area of the circular disc plate is given by; Again, power can be represented as the product of force and the velocity, where velocity; where, is the angular velocity which is equal to that of the shaft, The power required to overcome frictional losses can be computed assuming 10% losses due to frictional forces" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003554__AME_2021_138393.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003554__AME_2021_138393.pdf-Figure2-1.png", + "caption": "Fig. 2. The dimensions of gear pairs 3-4 and 5-6", + "texts": [ + " They consist of the modules, the tooth numbers, and the face widths. The other is four variables manually optimized with the help of structural analysis software such as Ansys. These include the hole diameters and hole numbers on the gears. Besides, the material replacement for the gear and pinion webs is also made to optimize the weight. Gear pair 3-4 and 5-6 in Fig. 1 are spur gear train (helix angle \u03b2 = 0, pressure angle \u03b1 = 20\u25e6). The gear structure in the transmission is selected as shown in Fig. 2, its parameters and design data are set up for Table 1. The gear ratio of the system must be ensured so that the handwheel drive 5b is suitable for the driving force of one average person. i = Mx4 Mq \u03b734 \u03b756 = i34 i56 , (1) where Mx4 is the torque in the shaft for which gear 4 is fitted, Mq is the torque rotated by the operator and \u03b734, \u03b756 are efficiency of gear driver 3-4 and 5-6. For spur gear pairs 3-4 and 5-6, the relationship between their parameters is shown in Table 2 [5]. The torques in the shafts for which gear 4, pinion 5 and gear 6 mounted with them are determined as follows: Mx4 = SmaxDtb 2 , (2) Mx5 = Mq , (3) Mx6 = Mx3 = Mx4 Z3 Z4 \u03b734 , (4) where Smax is the largest tension force when the rope is tangled into the drum, Dtb is the average diameter of the drum and the other parameters are identified as shown in Table 1", + " (m3)im3 ]T , im3 = 1 \u2212 nm3 , (5) m5 = [ (m5)1 (m5)2 . . . (m5)im3 ]T , im5 = 1 \u2212 nm5 , (6) b3 = [ (b3)1 (b3)2 . . . (b3)ib3 ]T , ib3 = 1 \u2212 nb3 , (7) b5 = [ (b5)1 (b5)2 . . . (b5)ib5 ]T , ib5 = 1 \u2212 nb5 , (8) Z3 = [ (Z3)1 (Z3)2 . . . (Z3)iZ3 ]T , iZ3 = 1 \u2212 nZ3 , (9) Z4 = [ (Z4)1 (Z4)2 . . . (Z4)iZ4 ]T , iZ4 = 1 \u2212 nZ4 , (10) Z5 = [ (Z5)1 (Z5)2 . . . (Z5)iZ5 ]T , iZ5 = 1 \u2212 nZ5 , (11) where nm3, nm5, nb3, nb5, nZ3, nZ4, nZ5 are the number of corresponding values of m3, m5, b3, b5, Z3, Z4, Z5. The structure of two gear pairs selected is shown in Fig. 2. From Table 1, Table 2, and equation (1), their weight can be determined by W1 = \u03c0\u03c1 4 \u00b7 106 [ b3m2 3 Z2 3 ( 1 + i234 ) \u2212 ( D2 i4 \u2212 d2 o4 ) (b3 \u2212 bw4) \u2212n4d2 p4bw4 \u2212 ( d2 3 + d2 4 ) b3 ] , (12) W2 = \u03c0\u03c1 4 \u00b7 106 [ b5m2 5 Z2 5 ( 1 + i2/i234 ) \u2212 ( D2 i6 \u2212 d2 o6 ) (b5 \u2212 bw6) \u2212n6d2 p6bw6 \u2212 ( d2 5 + d2 6 ) b5 ] , (13) where \u03c1 is the density of the material used to manufacture the gear (pinion); W1 is the weight of gear pair 3-4; W2 is the weight of gear pair 5-6. Hence, the objective function is W = W1 +W2 (14) and the goal of the work is to minimize the total weight W " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002238_e_download_8004_8699-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002238_e_download_8004_8699-Figure1-1.png", + "caption": "Figures 1. Design stages of proposed antenna", + "texts": [ + " The first solver is based on the finite element method (FEM) for solving electromagnetic structures and the second on the finite integration technique (FIT), to compare the results of the proposed antenna. When compared with other microstrip dual band antenna our antenna possesses the advantage of not only having a broad bandwidth, high gain but also a smaller size [5]-[9]. The elliptical patch antenna proposed is applied on the dielectric material FR4 substrate with a thickness h=1.58 mm, relative permittivity and Tangent loss . Initially an elliptical patch antenna is considered with inset-feed and the different design stage is shown in Figure 1. The final geometry of the proposed antenna is shown in Figure 2, consists of two rectangular slots in the radiation patch that plays a significant role in determining the resonating frequency because they can control the electromagnetic coupling effects between the patch and the ground plane. The parameters calculated and optimized of the proposed antenna for 14 GHz operating frequency are shown in Table 1. ISSN: 2088-8708 Int J Elec & Comp Eng, Vol. 8, No. 3, June 2018 : 1596 \u2013 1601 1598 The proposed antenna is designed and simulated using an electromagnetic solver based on the finite element method (FEM) and another solver based on the finite integration technique (FIT), to compare the results of the proposed antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002098__icssf2024_02007.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002098__icssf2024_02007.pdf-Figure5-1.png", + "caption": "Fig. 5. The components of the peeler, splitter and separator of dry soybean husk are based on electric blower technology.", + "texts": [ + " According to Ali Hasbi Ramadhani's research, designing and constructing a machine with a 250 kg/hour production capacity for peeling, fracturing, and separating soybean epidermis utilizing an AC motor and a hebus blower [8]. With the aid of electric motors with side-turn outlet directions to facilitate the process of stripping and separating soybean skin, Mr Yunus was able to increase the quantity and quality of productivity for small industrial groups at the 2017 national seminar using the results of designing a machine to break and peel soybean skin [9]. The results of the discussion and literature study resulted in the identified design results as shown in Figure 5. The machine's design process begins with a concept design that is refined through comprehensive drawings before being assembled on the machine in accordance with the necessary parameters [10], such as: a) This tool uses an electric motor drive with a power of 1 PK; b) The tool uses stainless steel 304 with dimensions of 60 x 90 x110 cm; c) This tool is used to separate the seeds and the epidermis using a 2-inch Electric blower; d) The main regulator on the blower uses a dimmer, while as a backup it uses a ball valve; e) This tool has dimensions of 600 mm x 400 mm x 930 mm; And f) This tool has a 30 Kg reservoir" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000028__article-file_879665-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000028__article-file_879665-Figure3-1.png", + "caption": "Fig. 3. Microstrip patch antenna structure [14]", + "texts": [], + "surrounding_texts": [ + "MPA antenna, consists of a metallic plate as ground, a radiating patch and a dielectric substrate between them [14]. h is the dimension of the substrate between ground and patch (0.003 \u03bb0< h < 0.05 \u03bb0), where \ud835\udf060 is the wavelength in free space. The dielectric constant of substrates that can be used for MPA is in the range of 2.2 \u2264\u0190\ud835\udc5f\u226412, [14]. The length of MPA, L, is the most effective parameter to define resonance frequency and it is usually varied between \ud835\udf060/3 \u8b1b\u6f14\u8ad6\u6587\u96c6, Vol.2004, No.17(2004), pp.374-377.\nFig. 21 Temperature rise values of the pinion gear tooth\nsurface when the input rotating speed is 100 rpm and 200 rpm. The 100 rpm result is indicated by the circle, and the 200 rpm result is indicated by the triangle. The temperature rises in proportion to the output torque, confirming that the temperature is higher at 200 rpm.", + "\u00a9 2015 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.15-00138]\nHeywood, R. B., Designing by Photoelasticity,Chapman & Hall(1952), pp.178-182. Johnson, K. L., Contact Mechanics, ninth printing(2003), Cambridge University Press, pp.99-101. \u6728\u6751\u6d69\u884c, \u7530\u6751\u5b5d, \u7247\u91ce\u572d\u4e8c, \u6e05\u6c34\u53cb\u6cbb, \u5ca9\u6df5\u660e, \u4e0d\u601d\u8b70\u6b6f\u8eca\u6a5f\u69cb\u3092\u7528\u3044\u305f\u52d5\u529b\u5207\u66ff\u88c5\u7f6e\u306e\u958b\u767a, \u65e5\u672c\u6a5f\u68b0\u5b66\u4f1a\n2009\u5e74\u5ea6\u5e74\u6b21\u5927\u4f1a\u8b1b\u6f14\u8ad6\u6587\u96c6, Vol.2009, No.4(2009), pp.27-28.\n\u6e05\u6ca2\u82b3\u79c0, \u5f35\u65b0\u6708, \u6d45\u8f2a\u79c0\u592b, \u52a0\u85e4\u6b63\u540d, \u4e95\u4e0a\u514b\u5df1, \u6ce2\u52d5\u6b6f\u8eca\u6e1b\u901f\u6a5f\u306e\u632f\u52d5\u4f4e\u6e1b\u306b\u95a2\u3059\u308b\u7814\u7a76\uff08\u7b2c 1\u5831, \u6ce2\u52d5\u6b6f\u8eca\u6e1b\n\u901f\u6a5f\u306e\u9ad8\u7cbe\u5ea6\u89d2\u5ea6\u4f1d\u9054\u8aa4\u5dee\u306e\u6e2c\u5b9a\uff09, \u65e5\u672c\u6a5f\u68b0\u5b66\u4f1a\u8ad6\u6587\u96c6 C\u7de8, Vol.64, No.625(1998), pp.3596-3602.\n\u5c0f\u51fa\u9686\u592b, \u5b87\u4f50\u7f8e\u521d\u5f66, \u5bae\u8fd1\u5e78\u9038, \u576a\u5009\u516c\u6cbb, \u6b6f\u8eca\u306e\u66f2\u3052\u75b2\u52b4\u5f37\u5ea6\u306b\u53ca\u307c\u3059\u5fae\u7c92\u5b50\u30b7\u30e7\u30c3\u30c8\u30d4\u30fc\u30cb\u30f3\u30b0\u306e\u5f71\u97ff, \u65e5\n\u672c\u6a5f\u68b0\u5b66\u4f1a 2010\u5e74\u5ea6\u5e74\u6b21\u5927\u4f1a\u8b1b\u6f14\u8ad6\u6587\u96c6, Vol.2010, No.4(2010), pp.107-108.\n\u68ee\u5ddd\u6d69\u6b21, \u4e2d\u6c5f\u9053\u5f66, \u4e2d\u539f\u597d\u53cb, \u5b89\u90e8\u5bff\u58eb, \u30b7\u30e7\u30c3\u30c8\u30d4\u30fc\u30cb\u30f3\u30b0\u3092\u65bd\u3057\u305f\u9ad8\u6fc3\u5ea6\u6d78\u70ad\u713c\u5165\u308c\u6b6f\u8eca\u306e\u6b6f\u9762\u5f37\u3055, \u65e5\u672c\n\u6a5f\u68b0\u5b66\u4f1a 2007\u5e74\u5ea6\u5e74\u6b21\u5927\u4f1a\u8b1b\u6f14\u8ad6\u6587\u96c6, \u65e5\u672c\u6a5f\u68b0\u5b66\u6a5f\u7d20\u6f64\u6ed1\u8a2d\u8a08\u90e8\u9580MPT2004\u30b7\u30f3\u30dd\u30b8\u30a6\u30e0<\u4f1d\u52d5\u88c5\u7f6e>\u8b1b \u6f14\u8ad6\u6587\u96c6, Vol.2007, No.7(2007), pp.33-34.\n\u4e8c\u53cd\u7530\u5b5d, \u6885\u672c\u535a, \u6a19\u6e96\u6a5f\u68b0\u88fd\u56f3\u304a\u3088\u3073\u8a2d\u8a08, \u7b2c 3\u7248, \u5171\u7acb\u51fa\u7248\u682a\u5f0f\u4f1a\u793e(1978), p.127. \u65e5\u672c\u7cbe\u5de5\u682a\u5f0f\u4f1a\u793e, NSK\u30c6\u30af\u30cb\u30ab\u30eb\u30ec\u30dd\u30fc\u30c8, No.728\uff082013\uff09, G-4, pp.62-95. Palmgren, A., Ball and Roller Bearing Engineering second edition, S. H. Burbank & Co.(1945), p.43. \u5869\u6d25\u52c7, \u677e\u672c\u5c07, \u6771\ufa11\u5eb7\u5609, \u5409\u898b\u58ee\u53f8, \u6885\u7530\u5f70\u5f66, \u5712\u90e8\u6d69\u4e4b, \u8ee2\u304c\u308a\u8ef8\u53d7\u8ee2\u7528\u578b\u9ad8\u901f\u30de\u30a4\u30af\u30ed\u30c8\u30e9\u30af\u30b7\u30e7\u30f3\u30c9\u30e9\u30a4\n\u30d6\uff08\u7b2c 1\u5831, \u30de\u30a4\u30af\u30ed\u30c8\u30e9\u30af\u30b7\u30e7\u30f3\u30c9\u30e9\u30a4\u30d6\u306e\u8a66\u4f5c\u3068\u8a55\u4fa1\uff09, \u65e5\u672c\u6a5f\u68b0\u5b66\u4f1a\u8ad6\u6587\u96c6 C\u7de8, Vol.72, No.716(2006), pp.1337-1344.\n\u65e5\u672c\u91d1\u5c5e\u5b66\u4f1a\u7de8, \u91d1\u5c5e\u30c7\u30fc\u30bf\u30d6\u30c3\u30af, \u6539\u8a02 4\u7248, \u4e38\u5584\u682a\u5f0f\u4f1a\u793e(2004), p.132. \u6771\ufa11\u5eb7\u5609, \u9f4b\u85e4\u6f84\u77e5, \u7a32\u5897\u4e00\u525b, \u30cf\u30a4\u30d6\u30ea\u30c3\u30c9\u5897\u6e1b\u901f\u6a5f\u306b\u95a2\u3059\u308b\u57fa\u790e\u7684\u7814\u7a76\uff08\u8ef8\u65b9\u5411\u4e88\u5727\u3092\u7528\u3044\u305f\u5834\u5408\u306e\u89e3\u6790\u3068\u5b9f\n\u9a13\uff09, \u65e5\u672c\u6a5f\u68b0\u5b66\u4f1a\u8ad6\u6587\u96c6 C\u7de8, Vol.79, No.804(2013), pp.2899-2916.\n\u5409\u5d0e\u6b63\u654f, \u5f93\u6765\u306e\u30b7\u30e7\u30c3\u30c8\u30d4\u30fc\u30cb\u30f3\u30b0\u3068\u5fae\u7c92\u5b50\u30d4\u30fc\u30cb\u30f3\u30b0\u3092\u7d44\u5408\u305b\u305f\u4e8c\u6bb5\u30d4\u30fc\u30cb\u30f3\u30b0\u3067\u4ed8\u4e0e\u3055\u308c\u308b\u6b8b\u7559\u5fdc\u529b\u306e\u5206\n\u5e03\u5f62\u614b\u3068\u305d\u308c\u304c\u6d78\u70ad\u713c\u5165\u308c\u6b6f\u8eca\u306e\u6298\u640d\u5f37\u5ea6\u306b\u53ca\u307c\u3059\u5f71\u97ff, \u65e5\u672c\u6a5f\u68b0\u5b66\u4f1a\u8ad6\u6587\u96c6 C \u7de8, Vol75, No756(2009), pp.2191-2199.\nReferences\nHarris, T. A. and Kotzalas, M. N., Essential concepts of bearing technology fifth edition, Tylor & Francis(2007), pp.109-112.\nHashitani, M., Usude, J. and Yanase, Y., Trend of gear manufacturing technology, Proceedings of the JSME machine design\n& tribology division MPT2004 symposium Vol.2007, No.7(2007), pp.33-34 (in\nJapanese).\nHeywood, R. B., Designing by Photoelasticity,Chapman & Hall(1952), pp.178-182. Johnson, K. L., Contact Mechanics, ninth printing, Cambridge University Press(2003), pp.99-101.\nKimura, H., Tamura, T., Katano, K., Shimizu, T. and Iwabuchi, A., Development of power transmission change system with\nparadox gear reduction, Proceedings of the JSME 2009 annual conference, Vol.2009, No.4(2009), pp.27-28 (in Japanese).\nKiyosawa, Y., Zhang, X., Asawa, H., Kato, M. and Inoue, K., On the reduction of torsional vibration of strain wave gearing\n(1st report, high precision measurement of rotational transmission error), Transactions of the Japan Society of Mechanical Engineers, Series C, Vol.64, No.625(1998), pp.3596-3602 (in Japanese).\nKoide, T., Usami, H., Miyachika, K. and Tsubokura, K., Effect of fine particle bombarding on bending fatigue strength of\ngears, Proceedings of the JSME 2010 annual conference, Vol.2010,No.4(2010),pp.107-108 (in Japanese).\nMorikawa, H., Nakae, M., Nakahara, Y. and Abe, H., Tooth surface durability of vacuum case-hardened gears treated with\nshot-peening, Proceedings of the JSME 2007 annual conference, Vol.2007,No.7(2007),pp.33-34 (in Japanese).\nNitanda, T. and Umemoto, H., Standard drafting machines and design, the third edition, Kyoritsu shuppan Co., Ltd. (1978),\np.127 (in Japanese).\nNSK Ltd., NSK technical report, No.728\uff082013\uff09, G-4, pp.62-95 (in Japanese).\nPalmgren, A., Ball and Roller Bearing Engineering second edition, S. H. Burbank & Co.(1945), p.43." + ] + }, + { + "image_filename": "designv8_17_0003111_0061518_09960948.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003111_0061518_09960948.pdf-Figure9-1.png", + "caption": "Fig. 9. TM filter after the application of the classical spurious suppression method. (a) 3-D view of the filter. (b) Wideband filter response.", + "texts": [ + " For that reason, only the three resonances due to irises 2, 3, and 4 are visible in Fig. 8(c). The classical approach for eliminating parasitic bands consists of the minimization of all possible couplings to higher order modes generating the parasitic band. As an example, this technique has been applied in [12]. In case of TM filters, according to Fig. 8(a), the best way for decreasing as much as possible all the coupling between higher order modes on adjacent cavities is to alternate the iris orientation from horizontal to vertical. This is shown in Fig. 9(a). Indeed, according to Fig. 7, because of the field distribution of the fundamental resonant TM110 mode, its coupling does not depend on the iris orientation [33]. This means that the filter passband is not influenced by the orientation. Something different happens instead to the higher order modes: the first horizontal iris excites the TM120 spurious mode, but the second (vertical) iris does not excite the TM120 mode [33]. Actually, the coupling to TM120 modes obtained by a vertical iris is very small, but it is not zero. This small residual coupling is responsible for the spurious frequencies around 15/16 GHz shown in the response of Fig. 9(b). Of course, this response is much better than that in Fig. 8(c), where no strategies for removing spurious frequencies were taken into account. However, some spurious frequencies are still present. Actually, vertical irises may also excite the TM210 mode thus creating additional spurious resonances around 16 GHz. However, in the response of Fig. 9(b), these resonances have been removed by placing vertical irises in a specific position from the cavity center where TM210 mode has the minimum magnetic field. This corresponds to a distance from the center equal to a quarter of the cavity size (w/4) [33]. In order to reach this new position, the distance of the vertical irises from the center has been increased. This results in an undesired increase of the coupling M12 that ruins the filter response. In order to recover the original M12 value, iris size w2 has been reduced", + " This increases all couplings in the higher mode parasitic band except the central one. This results in the improvement of the suppression of the higher order mode parasitic band. Note that, according to Fig. 10(a), the distance px of the iris from the cavity center is here used to remove parasitic bands. In [28], the same parameters are used for controlling the TZs. This means that in spurious self-suppression method, the control of TZs is a little bit more limited. However, in contrast to the classical approach of Fig. 9 where TZs completely disappear, in filter designs using spurious self-suppression method, a certain control capability of the TZs still remains, as shown later on. The three steps described above are here applied to the fourth-order TM cavity filter of Fig. 8, starting from the central iris rotation. 1) Central Iris Orthogonally Positioned: The four-pole filter of Fig. 8, after its central iris has been vertically positioned, is shown in Fig. 10(a) and (b). Its response is shown in Fig. 10(c). In theory, according to the modal field distribution of Fig", + " 3) If in a cavity, irises are both above (or both below) the cavity center, the TZ generated by the cavity is in the lower stopband. 4) If in a cavity, irises are one above and the other below the cavity center, the TZ generated by the cavity is in the upper stopband. Rule numbers 3 and 4 are a consequence of the change of sign of the coupling to the TM110 mode when the position of one of the two irises passes from above to below the cavity center [28]. According to classical TM filter configuration of Fig. 8(a), all irises are aligned. This results in a number of TZs equal to the number of cavities. According to Fig. 9(a), when the classical spurious suppression method is applied, each cavity has irises orthogonally positioned. According to rule number 1, this results in no TZs. This can be clearly seen in Fig. 9(b) where no TZs are present close to the filter band. According to Fig. 16(a), when the proposed spurious selfsuppression is applied, the two central cavities have irises orthogonally positioned, losing the capability of generating the bypass coupling in the two central cavities. In terms of routing scheme, this means that the coupling between NRN A and B (as well as B and C) is equal to zero when the spurious self-suppression method is applied. In all other cavities, irises are instead aligned and the bypass coupling is maintained" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure31-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure31-1.png", + "caption": "Figure 31: 3D printed 8 joint PLA design.", + "texts": [ + " Changing the material to a more flexible material can assist with this. Table 9 compares ABS to PLA which are both 3D printable materials. 22 same plastics with different material properties based on manufacturing techniques. With that being said, TPU generally has a lower stiffness and higher flexibility when compared to ABS. While this is good for achieving the \ud835\udefe factor required it is important to make sure that the landing gear is stiff enough to handle the loads. The 8 joint design was scaled down and 3D printed using ABS to test the mechanism. Figure 31 shows half of the 3D printed landing gear mechanism to save printing time and filament. The maximum \ud835\udefe that was produced from the 3D printed mechanism was around 15.6 degrees. It is important to note that the structure could deform further than 15.6 degrees but the linkages would not be parallel to each other. The visual for the deformation can be seen in Figure 23 32. Attaching the cable to the lug on the leg with a motor can simulate what is being seen in Figure 15. 2.6. Third Design Approach - Pantograph The second design approach was using a parallelogram 4 bar linkage which did not produce a mechanical advantage" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001052_f_version_1704097252-Figure6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001052_f_version_1704097252-Figure6-1.png", + "caption": "Figure 6. ie of the easurement points of machines.", + "texts": [ + "\u00a0Machines\u00a0under\u00a0Investigation\u00a0and\u00a0Measurement\u00a0Setups\u00a0 In\u00a0the\u00a0current\u00a0research,\u00a0two\u00a0machines\u00a0of\u00a0the\u00a0same\u00a0type\u00a0were\u00a0installed\u00a0in\u00a0parallel\u00a0and\u00a0 operated\u00a0in\u00a0one\u00a0recycle\u00a0line\u00a0(Figure\u00a05a).\u00a0The\u00a0test\u00a0measurement\u00a0processes\u00a0and\u00a0equipment\u00a0 are\u00a0shown\u00a0in\u00a0Figure\u00a05b,\u00a0including\u00a0a\u00a0National\u00a0Instrument\u00a0USB-443x\u00a0data\u00a0collector\u00a0with\u00a0an\u00a0 AS-065\u00a0B&K\u00a0accelerometer\u00a0and\u00a0PC\u00a0for\u00a0data\u00a0proceeding.\u00a0 The machine\u2019s vibration was measured in the main body, the four mounting elements (divided into two elements T and M), and the bases elements (B) to which the machine is attached on the ground (Figure 6). \u00a0 the\u00a0machine\u00a0and\u00a0identify\u00a0any\u00a0possible\u00a0impending\u00a0problems\u00a0such\u00a0as\u00a0an\u00a0unbalance,\u00a0high\u00a0 vibratio ,\u00a0etc.\u00a0Prior\u00a0to\u00a0the\u00a0main\u00a0measurements,\u00a0the\u00a0accelerometers\u00a0were\u00a0calibrated\u00a0using\u00a0 a\u00a0B&K\u00a0portable\u00a0accelerometer\u00a0calibrator\u00a0type\u00a04294.\u00a0 The\u00a0machine\u2019s\u00a0vibration\u00a0was\u00a0measured\u00a0in\u00a0the\u00a0main\u00a0body,\u00a0the\u00a0four\u00a0mounting\u00a0elements\u00a0 (divided\u00a0into\u00a0two\u00a0elements\u00a0T\u00a0and\u00a0M),\u00a0and\u00a0the\u00a0bases\u00a0elements\u00a0(B)\u00a0to\u00a0which\u00a0the\u00a0machine\u00a0is\u00a0 attached\u00a0on\u00a0the\u00a0ground\u00a0(Figure\u00a06).\u00a0 Figure\u00a06.\u00a0View\u00a0of\u00a0the\u00a0measurement\u00a0points\u00a0of\u00a0machines.\u00a0 To\u00a0explain\u00a0the\u00a0obtained\u00a0results,\u00a0the\u00a0machine\u00a0is\u00a0placed\u00a0in\u00a0an\u00a0x,\u00a0y,\u00a0z\u00a0coordinate\u00a0system\u00a0 according\u00a0to\u00a0Figures\u00a05\u00a0and\u00a06.\u00a0The\u00a0measurement\u00a0points\u00a0are\u00a0defined,\u00a0and\u00a0the\u00a0obtained\u00a0re- sults\u00a0are\u00a0presented\u00a0in\u00a0graphs\u00a0and\u00a0tables,\u00a0with\u00a0conclusions\u00a0provided\u00a0at\u00a0the\u00a0end\u00a0of\u00a0the\u00a0ma- chine\u2019s\u00a0vibrational\u00a0analysis.\u00a0 3.\u00a0Results\u00a0and\u00a0Discussion\u00a0 3.1.\u00a0Results\u00a0for\u00a0Machine\u00a0\u2116\u00a01\u00a0 The\u00a0results\u00a0are\u00a0presented\u00a0in\u00a0graphical\u00a0form\u00a0for\u00a0the\u00a0examples,\u00a0and\u00a0a\u00a0comparison\u00a0with\u00a0 the\u00a0body\u00a0vibration\u00a0with\u00a0the\u00a0most\u00a0vibrated\u00a0mounting\u00a0element\u00a0of\u00a0the\u00a0machine\u00a0is\u00a0presented\u00a0 also" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001341___lang_en_format_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001341___lang_en_format_pdf-Figure1-1.png", + "caption": "Figure 1. Structure diagram of the crawler soybean combine harvester 1. Driver\u2019s cab; 2. Grain box; 3. Seed lifter; 4. Re-threshing lifter; 5. Threshing roller; 6. Threshing wheel; 7. header feeding auger; 8. header; 9. Chassis; 10. Horizontal seed spiral conveyor; 11. Horizontal", + "texts": [ + " This paper studied the soybean harvesting process, determined the main crushing forms of soybeans, and analyzed the influence of different operation links on soybean crushing during the harvesting process, such as header feeding auger, horizontal seed spiral conveyor, horizontal miscellaneous residue spiral conveyor, and threshing roller, and determined the proportion of different crushing forms in each operation link.The influence of the operating parameters such as the forward speed of the harvester, threshing roller speed, and deflector angle on the soybean crushing form was studied experimentally, and the results can provided a reference for the optimization of the soybean harvester. The experimental device was a crawler soybean combine harvester, which is widely used in the main soybean producing areas in China. The machine, as shown in Figure\u00a01, included a cab, grain box, seed lifter, re-threshing lifter, threshing roller, threshing wheel, cutter feed stirrer, header, undercarriage, horizontal seed spiral conveyor, horizontal trash spiral conveyor, and cleaning sieve. The unit had a working width of 1500 mm, engine power of 68 kW, machine size (length \u00d7 width \u00d7 height) of 4850 mm \u00d7 2000 mm \u00d7 2450 mm, feeding capacity of 1.2\u20133 kg/s, and operating efficiency of 0.4\u20130.7 hm2/h. The operation process was as follows. Soybeans were cut, and then were plucked into the inside of the cutting platform through the paddle wheel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000087_5_secm-2014-0048_pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000087_5_secm-2014-0048_pdf-Figure15-1.png", + "caption": "Figure 15 Torque specimen geometry (left) and testing setup (right).", + "texts": [ + " preforms were infused in a Resin-Transfer-Molding-(RTM-) Process using the Resin Araldite\u00ae LY556 with Aradur\u00ae 917 hardener. Both chemicals were supplied by Huntsman Advanced Materials GmbH, Bad S\u00e4ckingen, Germany. The manufactured specimens are subjected to torque loading using a tension-torsion testing machine \u201cZ250/SN5A\u201d with an ultimate torque capacity of 2000 Nm. This machine was manufactured by Zwick GmbH & Co, Ulm, Germany. The test is performed under compensation of axial loads with an application of torque at a twist speed of 5\u00b0/min (quasi-static). Figure 15 provides an overview of the specimen geometry and the fixture used to introduce the torque loads. Further experiments are in preparation to assess the influence of specimen geometry. For those tests, the manufacturing of specimen with an outer diameter of 100\u00a0mm and a wall thickness of 18\u00a0 mm is planned. For testing those tubular samples, a servohydraulic test stand with an ultimate load capacity of 40 kNm is available at the ILK. Figures 16 and 17 show the achieved failure load levels and stiffness values of the tubular specimens depending on the textile structure (compare Figure 13)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-Figure3-1.png", + "caption": "Fig. 3. Angled Three-Flexure Cross Hinge with design parameters (Lflex, Bphal, Win and t). a) Undeflected position with pre-curved flexures; b) deflected position with straightened flexures.", + "texts": [ + " Width and thickness represent an average of the proximaljoint dimensions of all fingers for both males and females, except the thumb. The length of the hinge is designed so that half of it is inside of the palm. See Fig. 2. Thus, the center of rotation of the flexure hinge is at the end of the palm and the beginning of the finger, which is equivalent to the location in a human hand. The proximal phalange acts as a housing for the other half of the joint. C. Hinge Topologies A series of hinge topologies are defined in advance. See Fig. 3. Their performance during power grasp is compared. \u2022 Leafspring (LS) \u2022 Solid-Flexure Cross Hinge (SFCH) \u2022 Three-Flexure Cross Hinge (TFCH) \u2022 Hole Cross Hinge (HCH) \u2022 Angled Three-Flexure Cross Hinge (ATFCH) The initial topologies are designed such that, in the un-deflected position, there is one rotational degree of freedom for flexion and extension of the fingers, and the stiffnesses in support directions are high. For comparison, a flexure hinge consisting of only a single leafspring is also evaluated, which provides support stiffnesses only in three degrees of freedom. This topology is used as a reference, as it is often used for prosthetic and robotic hands [2]\u2013[4]. An initially curved design is added to generate high support stiffness at large deflections while sacrificing stiffness at smaller deflections. See Fig. 3e. Several of these hinges were defined previously by [7], including their design parameters p. The Hole Cross Hinge combines the constant bending moment of a Three-Flexure Cross Hinge with the full width of a Solid-Flexure Cross Hinge except at the crossing where reinforced parts are used. The concept of the Angled Three-Flexure Cross Hinge is introduced in this paper, with a topology similar to that of the Three-Flexure Cross Hinge. The hinge is defined so as to obtain straight elements when a specific angle is achieved", + " In both cases, the applied force will be of vertical direction, since it is due to the gravitational force of a grasped mass. Two separate situations ask for two different designs of test rigs, these are explained in the next section. 3.1 Global design Global design rules that apply on both test rigs are explained before zooming in to the separate testing principles. Besides these two principles the following parts are explained in separate sections: clamps, measurement tools and limitations in construction. In figure 3 the full test rig is seen, which gives an overview of all components. As mentioned before, mostly all parts of the test rig will be 3D printed. The printed material is be polylactic acid (PLA). This material has been chosen since this plastic is the easiest and most precise to print 407 Page 55 with nowadays. The assumed properties of the PLA are found in the List of Demands (see Appendix 1) . However, since 3D printing might cause weaker properties than the base material, a safety factor of three is used in calculations for designing plastic parts", + " Furthermore, the force will be applied in the center between the two notch flexure to keep the test rig balanced, a holder similar to the torsion case is placed on top of the flexure. Other options next to a flexure mechanism, like a slot with a guider or linear guidance were not chosen, respectively due to problems with friction and availability. To compensate for the dead weight of the notch flexure and the clamp, a spring is attached between the weight holder of the flexure and the support frame. At this location the forces of the weights and the spring are working on the same axis (see figure 3 number eight and ten. The spring is chosen by calculating the spring constant using Hooke\u2019s Law (Beuche, p. 95 [11]) since the mass, and therefore gravitational force of the dead weight is known. Equal to the torsion test rig, the height of the tip clamp is adjustable in vertical and horizontal direction by several slots as seen in figure 5. One of the two notch flexure is seen in figure 5, used to enable the vertical displacement. According to the specifications the maximum needed deflection (\u2206) is 5 mm", + " An initially curved design is added to generate high support stiffness at large deflections while sacrificing stiffness at smaller deflections. Several of these hinges were defined previously by [7] including their design parameters p. Page 67 \u03b8max Lflex Bphal y x Win t za) b) The HCH combines the constant bending moment of a TFCH, with the full width of SFCH, except at the crossing where reinforced parts are used. The concept of the ATFCH is introduced in this paper, with a similar topology to the TFCH. The hinge is defined such to obtain straight elements when a specific angle is achieved, Fig. 3b. The length of the leafsprings are equal, as the diagonals of an isosceles trapezoid, to have an even stress distribution during deflection around the z-axis. This hinge is parametrized by the parameter vector p. p = { Lflex Bphal Win t } (1) Where Lflex is the length of elements, Bphal is the distance of the base (short side of the isosceles trapezoid), Win is the width of the inner element and t is the thickness of the elements, see Fig. 3. D. Optimization Flexible multibody software SPACAR is used to evaluate the performance of the intrinsic geometric nonlinearities of the hinges [14]. By using nonlinear 3D beam elements, it is possible to efficiently compute the performance of a series of design parameters in large displacement motions and small elastic deformations. As a result a relatively small number of elements produce accurate results at low computational cost. A shape optimization based on the Nelder Mead method is used. The objective is to find the set of design parameters p that maximize the performance within the specified constraints C(p) [15]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003940_article_25898767.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003940_article_25898767.pdf-Figure1-1.png", + "caption": "Fig 1. map of intelligent vehicle path tracking cos", + "texts": [ + " Based on fuzzy logic, it can complete driver's experience control, and the mapping rules can be generated by training and learning to realize the intelligent control of vehicles. In this paper, an intelligent vehicle navigation path recognition model based on neural network is designed to ensure that intelligent vehicle can track the expected path in the upper cycle with high speed and precision. This paper provides an analytical basis for the design of the intelligent vehicle navigation path model by tracking the moving path of the intelligent vehicle. Figure 1 is the schematic diagram of the intelligent vehicle path tracking. The position coordinates of the intelligent vehicle are represented by ( , , )TR x y , ( , y)x is the coordinate of the intelligent vehicle in the world coordinate system, and represents the angle between the intelligent vehicle and the X-axis. Point P denotes the tangent point of the position R of the intelligent vehicle to the vehicle's moving path, the distance from R point to P Copyright \u00a9 2018, the Authors. Published by Atlantis Press" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000755_cle_download_242_206-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000755_cle_download_242_206-Figure13-1.png", + "caption": "Figure 13. The simulation results of the maximum stress on the electric motor mount are 0.35 MPa.", + "texts": [ + " The main rod receives force from the reaction force on the support rod. The simulation results per stem are as follows: 1. Electric motor mount The electric motor mount receives a weight force of 34.335 N, which acts in the y-axis direction. This part only consists of one rod to support the electric motor. Using the frame analysis feature, the simulation results on the electric motor mount are bending moment, maximum stress, and displacement, each with values of 1674.76 N.mm, 0.35 MPa, and 0.0007 mm. Figure 13 shows the simulation results of the maximum stress value on the electric motor mount. 2. Control panel and battery mount The control panel and battery holder receive a weight force of 31.392 N acting in the y-axis direction. This section only has one rod to support the control panel and battery. The simulation results obtained are bending moment, maximum stress, and displacement, values are 1538.65 N.mm, 0.32 MPa, and 0.0007 mm, respectively. Figure 14 shows the simulation results of the maximum stress values at the control panel and battery mounts" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003835_f_version_1676453559-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003835_f_version_1676453559-Figure5-1.png", + "caption": "Figure 5. STRATOFLY MR3 LH2 tank architecture [20].", + "texts": [ + " An overview of the complete trajectory in terms of altitude and Mach profiles of the vehicle are reported in Figure 3. The propellant mass variation over time is shown in Figure 4a. The thrust and mass flow profiles are reported in Figure 4b for the ATR (continuous line) and DMR (dotted line). The propellant subsystem is in fact one of the most impactful plants on-board the STRATOFLY MR3 vehicle, since the use of LH2 requires a large amount of volume that is dedicated to tanks and delivery lines. The overall tank architecture (Figure 5) is made up of seven main assemblies (front additional tank\u2014FAT including sub-compartments front intake\u2014FI, front part\u2014FP, middle front part\u2014MFP, middle part\u2014MP, middle rear part\u2014MRP and rear part\u2014RP, then front pillow tank\u2014FPT, rear pillow tank\u2014RPT, front wing tank\u2014FWT, center wing tank\u2014CWT, rear wing tank\u2014RWT and wing tip tank\u2014 WTT). These vessels are sized in terms of volume and thicknesses (both structural and insulation) [20] in order to propose a feasible bubble layout, distributing structural loads and offering a good compromise between center of gravity (CoG) control during flight and thermal management needs" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000465_om_article_19503_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000465_om_article_19503_pdf-Figure1-1.png", + "caption": "Fig. 1. Torsional vibration damper based on parallel viscoelastic coupling of seismic mass. a) torsional vibration damper Geislinger for large engines; b) rubber damper for commercial vehicle engines", + "texts": [ + "6 \u00a9 JVE INTERNATIONAL LTD. VIBROENGINEERING PROCEDIA. DEC 2017, VOL. 16. ISSN 2345-0533 For dynamic torsional vibration dampers in large engines (see Fig. 1 on the left), the optimal parameters of the elastic and damping coupling of the seismic ring can be ensured by suitable design, since the flexible parts are made of metallic elements and the lubricating oil is used as the damping medium. The optimum parameters of such a torsional damper remain stable even during a long-term engine operation. In smaller engines for commercial vehicles or tractors, the viscoelastic coupling of the damper ring is usually realized with a rubber spring, usually made of natural rubber (see Fig. 1 on the right). The disadvantages of rubber dampers are, in particular, insufficient damping properties of the rubber spring compared with the optimal values resulting from the respective computational models [1-4]. For internal combustion engines with higher power output, the design of rubber torsional dampers is difficult because the dissipated power in the rubber elements can reach up to hundreds of watts, and insufficient heat removal would cause their destruction. Classical viscous torsional dampers [2, 3] have a relatively low damping effect" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004334_f_version_1614604730-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004334_f_version_1614604730-Figure15-1.png", + "caption": "Figure 15. Reduced stress contour lines in the upper part of the container, according to Huber and Mises hypothesis [MPa]: (a) Calculation results of the upper cover of the bed material tank from the outside, (b) Calculation results of the upper cover of the bed material tank from the inside.", + "texts": [ + " Impact strength of approximately 200 MPa was assumed for the observed low quality of weld lines on the fuel hoppers. The strength analysis showed that at air pressure inside the container equal to 50 kPa and at uneven thermal impact that occurred simultaneously, reduced stress in the area of hopper weld lines reached approximately 270 MPa (Figure 14). This contributed to the breaking of the discussed area of the container 8z. At the same time, reduced stress in the container\u2019s upper part was observed at approximately 870 MPa (Figure 15). The latter observation, along with the fact that the tests performed prove the ultimate strength of steel S235 to be at the level of 315 MPa, means that this area experienced a sudden discontinuity of the investigated object\u2019s casing [20]. The strength analysis also showed clearly that as the air pressure inside the container rose to approximately 50 kPa and the casing heated unevenly, the casing broke in its both upper and lower parts. Measurement results allowed to estimate the effects of the fire wave that passed through a power station" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure11-1.png", + "caption": "Figure 11. Bar chart of calculated total power losses in windings for Motor #1 and Motor #2; rotational torque is treated as input quantity and is identical for both motors.", + "texts": [ + " The supply currents of two motors are not identical, and their disparity increases as rotational speed goes up and we enter the second control zone. As in the case of calculation results shown in Figure 8, we may state that equalization of the rotational torque in the first control zone has led to an increase in the supply current of Motor #2. In the second control zone, and as the field becomes more weakened, Motor #1 must be supplied with a higher current in order to maintain rotational torque at the required level. Total winding losses are shown in Figure 11, while AC winding losses are shown in Figure 12. Characteristics shown in Figure 11 confirm the fact that Motor #1 is characterized by higher winding losses over the entire operational range. This is due to greater winding resistance and higher winding operational temperatures. Power losses associated with current displacement effects, i.e., AC winding losses, are shown separately in Figure 12. In this case, higher losses are clearly generated in Motor #2 windings; this is supplied at a much higher frequency since the number of pole pairs is increased from p = 16 to p = 28, and speed range remains unchanged. Even though AC winding losses are higher, their contribution to total losses (Figure 11) is insignificant. Calculated total losses in the stator core are shown in Figure 13. Losses in Motor #2 core are greater than those of Motor #1 on account of higher values of flux density (produced by permanent magnets) in the electromagnetic circuit (see Figure 5) and higher supply currents (Figure 11). We may observe in these curves that core losses increase as rotational speed increases and then they stabilize at more or less constant levels; this is due to field weakening and operation in the second control zone. The field weakening zone for Motor #1 is commenced somewhat earlier. Characteristics of calculated stator total losses are presented in Figure 14; this is the sum of losses shown in Figures 11 and 13. It must be noted that these losses determine temperature distribution in the stator core", + " The stator core is heated by its own losses and winding losses, which are transferred through the core to the coolant. In the case of lowest loads (rotational torque Tm = 50 Nm) losses of Motor #2 are higher over the entire range of rotational speed. These are mostly losses generated in the stator\u2019s magnetic core; throughout the entire operational range, these losses are higher in Motor #2 (Figure 14). As the load increases, winding losses increase in both motors, but winding losses in Motor #1 increase at a much higher rate (see Figure 11), while stator core losses do not vary much with changes in the current. When charts for different losses are compared, we observe that while load increases, the area where Motor #2 losses are lower than Motor #1 losses moves away from lower speeds towards maximum speed. In the case of rotational torque equal to Tm = 450 Nm, total losses generated in the motor stator are higher in Motor #1 over the entire rotational speed range. When load is increased, difference in stator\u2019s total losses also grows" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004159_f_version_1645110353-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004159_f_version_1645110353-Figure9-1.png", + "caption": "Figure 9. Filter and Line compensation terms.", + "texts": [ + " v1_re f = vs_re f + L f d dt i1 + Rl i2 \u2212 Rl Cl 2 d dt v2 + Ll d dt i2 \u2212 Ll Cl 2 d2 dt2 v2 (47) These equations can be elaborated as the previous ones, obtaining Equation (48) v1dq_re f = vsdq_re f + L f \u03c9rS i1dq + Rl i2dq \u2212 Rl Cl 2 \u03c9rS v2dq + Ll \u03c9rS i2dq + \u03c92 r Ll Cl 2 v2dq (48) Equation (48) can be written in its components, as shown in Equations (49) and (50). v1d_re f = vsd_re f \u2212\u03c9rL f i1q + Rl i2d + Rl Cl 2 \u03c9rv2q \u2212 Ll \u03c9r i2q + \u03c92 r Ll Cl 2 v2d (49) v1q_re f = vsq_re f + \u03c9rL f i1d + Rl i2q \u2212 Rl Cl 2 \u03c9rv2d + Ll \u03c9r i2d + \u03c92 r Ll Cl 2 v2q (50) It is necessary to add the calculated voltage drops, as shown in Figure 9, to adequately compensate for the line and the filter. This compensation works properly when the line parameters are the rated ones, but, as already mentioned, the line undergoes temperature variations, which means parameters variations; so, it is important to investigate through the simulations if the parameter variations affect significantly the drive behavior. Energies 2022, 15, x FOR PEER REVIEW 14 of 22 2 1 _ _ 1 2 2 2 22 2 l l q ref sq ref r f d l q l r d l r d r l q C C v v L i R i R v L i L vw w w w= + + - + + (50) It is necessary to add the calculated voltage drops, as shown in Figure 9, to adequately compensate for the line and the filter. This compensation works properly when the line arameters are the rate ones, but, as already mentio ed, the line undergoes temperature variations, which means parameters variations; so, it is important to investigate through the simulations if the parameter variations affect significantly the drive behavior. Figure 9. Filter and Line compensation terms. 7. Simulation Results The entire system is implemented in MATLAB/Simulink environment. The simulator is divided into two parts: the control, which is a discrete-time region (the entire control has been designed to have a frequency of 3.3 kHz), and the model of the physical elements. Table 2 contains the filter and line parameters, respectively. The line is modeled using a three-phase distributed parameters block provided by Simscape, which is based on the Bergeron\u2019s travelling wave method, described in [14]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000639_mtime_20170330153413-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000639_mtime_20170330153413-Figure15-1.png", + "caption": "Figure 15: Strain and forces distribution.", + "texts": [], + "surrounding_texts": [ + "For the parabolic-rectangle stress-strain relation case, we use the same methodology as in the case of the bilinear stress-strain relation. The only difference is the shape of the concrete stress distribution where the triangular section becomes now parabolic, and also the ultimate Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis strain and the strain corresponding to the start of the rectangular section which become \u03b5cu2 (instead of \u03b5cu3) and \u03b5c2 (instead of \u03b5c3), respectively, as shown in the figure below. In the above figure, x2 is the distance from the neutral axis to the centroid of the parabolic section. The parabolic section is \u201cfull\u201d in the figure, as \u03b5c>\u03b5c2. In the bi-linear case, the calculation of the area and centroid of the non-rectangular part was obvious, because of the triangular shape, but for the parabolic case, integration has to be used, as will be described in detail later. Again, we need to determine if at the ULS the concrete zone or the steel is at the critical strain. First, we put both materials at the ultimate strain, so we have: 2c cu (65) s ud (66) 2 22 2 2 2 2 21 1 2 cu ud cucu ud cu cu c cu c ud cu x d x d x x d (67) 1 1c cdF x f b (68) 1 1 2 x z d (69) The above equations are almost the same as the ones used in the bi-linear case, but of course in the parabolic-rectangle case we use \u03b5c2 and \u03b5cu2 instead of \u03b5c3 and \u03b5cu3. Yet, this time in order to calculate Fc2 we need to integrate Eq. (2) to calculate the area of the parabolic part. For the parabolic part of the stress, i.e. for strains \u03b5c in the region [0, \u03b5c2], we have the indefinite integral: 1 2 2 2 1 1 1 1 n c n c cd cc c c cd c c cd c f d f d f n (70) Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis Thus the area E1 of the full parabolic part [0, \u03b5c2] is given by the definite integral: 2 1 2 0 1 c c c c cd n E d f n (71) The area E1 of the full parabolic part is shown in the figure below in black color. If the integration is done on the cross section height, for the strain \u03b5c2 the corresponding height of the section is (x-x1) and as a result the corresponding area of the full parabolic part A1 is given by: 1 11 cd n A x x f n (72) The area A1 of the full parabolic part is shown in the figure below in black color. The area A1 of the full parabolic part is shown in black color. The concrete force Fc2 is given by: 2 1 11c cd n F A b x x f b n (73) In order to calculate z2 we need to calculate the distance x2 defining the centroid of the A1 area. In terms of strains, the centroid \u03b5centroid of the E1 area is given by the definite integral: Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 2 1 1 0 1 c centroid c c cd E (74) The indefinite integral in this case is given by: 12 2 2 2 2 1 d 1 1 d 2 2 1 nn cd c c c cc c cd c c c c cd c n c c f nf f n n (75) Thus the centroid of the full parabolic part is given by: 2 1 2 1 0 1 3d 2 2 c centroid c c c c n E n (76) If the integration is done on the section height, for the strain \u03b5c2 the corresponding height of the cross section is (x-x1) and as a result the corresponding centroid of the full parabolic part x2 is given by: 1 2 1 1 2 3 2 2 centroid c n x x x x x n (77) Then we have 2 2z d x x (78) 1 2c c cF F F (79) Again, we will calculate the sum of moments at the steel reinforcement position. The sign of the sum of moments will show us whether the concrete zone or the steel is at the ultimate strain at the ULS. The sum of moments is (clockwise positive): 1 1 2 2steel c c sdM F z F z M (80) We then have again two cases: Case 1. \u03a3\u039c\u22650 The concrete force has to be decreased for the equilibrium of the cross section. The steel stays at the ultimate strain (\u03b5s=\u03b5ud), while \u03b5c\u2264\u03b5cu2. Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis Case 2. \u03a3\u039c<0 The concrete force has to be increased for the equilibrium of the cross section. The concrete stays at the ultimate strain (\u03b5c=\u03b5cu2), while \u03b5s<\u03b5ud. The methodology is exactly the same as the one of the bi-linear case. To start, we assume a value for x and we should change it until we reach the final equilibrium. The equations below end up with the calculation of the sum of moments which has to be zero at the equilibrium. Case 1. \u03a3\u039c\u22650, Steel at the ultimate strain We assume an initial value for x and we use the following equations: s ud (81) c ud c ud x x d x d x (82) Case 1a: If \u03b5c>\u03b5c2 In this case we have the parabolic diagram plus a rectangular diagram and the upmost fiber of concrete works at the ultimate stress fcd. From the similar triangles we have: 31 1 3 c c c c c s c s x d x d (83) 1 1c cdF x f b (84) 1 1 2 x z d (85) In a similar way as previously (integrations), and since we have again a full parabolic part, we have: 2 11c cd n F x x f b n (86) 2 1 3 2 2 n x x x n (87) 2 2z d x x (88) 1 2c c cF F F (89) Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 1 1 2 2c c sdM F z F z M (90) After we reach the equilibrium (\u03a3\u039c=0), and given that the steel reinforcement works in full stress, above the yield strain, the steel area can be easily calculated by Eq. (31). Case 1b: If \u03b5c\u2264\u03b5c2 In this case we have only part of the parabolic diagram, there is no rectangular diagram and the upmost fiber of concrete works at stress \u03c3c\u2264fcd. 2 c c cd cd c f f (91) \u03a4his time in order to calculate Fc2 we need to integrate Eq. (2) to calculate the area of the parabolic part, not for the full parabola (up to \u03b5c2), but for the region [0, \u03b5c] where \u03b5c\u2264\u03b5c2. Using the indefinite integral of Eq. (70) we can calculate the corresponding area E2 of the parabolic part for the region [0, \u03b5c] where \u03b5c\u2264\u03b5c2 as a definite integral as follows: 1 1 2 2 2 2 2 0 1 1 1 1 1 1 c n n c c c cd c c c c c cd c cd c f E d f f n n (92) The area E2 of the parabolic part for the region [0, \u03b5c] is shown in the figure below in black color. If the integration is done on the section height, for a strain \u03b5c<\u03b5c2 the corresponding height of the cross section is x while for the theoretical strain \u03b5c2 the corresponding height of the cross section would be x\u2219\u03b5c2/\u03b5c and as a result the corresponding area of the parabolic part A2 is given by: Vagelis Plevris, George Papazafeiropoulos and Manolis Papadrakakis 1 1 2 2 2 2 2 1 1 1 1 1 1 1 n n c c c c c c c c cd cd x A f x f x n n (93) The area A2 of the parabolic part in this case is shown in the figure below in black color. \u03b5C<\u03b5c2 \u03b5s=\u03b5ud x Fs Strains Forces z2 Fc2 \u03c3c\u03b2,\u03b3>0.5\u3068 \u306a \u308a,\u4e21 \u811a\u304c\u7740\u5730 \u3057\u305f\u72b6\u614b\u3067\u306e\u64cd\u4f5c \u304c\u4e3b\u6d41 \u3068\u306a \u308b.R\u304c \u5c0f \u3055\u304fDp=1.0\u79d2 \u3067V\u304c \u901f\u3044\u56f3\n\u6ce2\u6570\u6210\u5206\u306f\u811a\u306e\u904b\u3073\u306b\u540c\u671f\u3057\u3066,1\u6b69 \u884c\u5468\u671f\u4e2d\u306b2\u30b5 \u30a4\u30af\u30eb\u306e\u5909\u52d5\u3092\u3059\u308b.\u307e \u305f,L\u3068F\u306e \u6642\u9593\u7684\u306a\u95a2\u9023\u6027 \u306f,\u56f3(a)\u3067\u306fL\u304c \u6975\u5c0f\u3068\u306a\u308b\u4e21\u811a\u652f\u6301\u76f8\u306e\u521d\u671f\u306bF\u306f \u6975\u5927\u5024\u3068\u306a\u308b.\u56f3(b)\u3067\u306f,L\u306f \u4e21\u811a\u652f\u6301\u76f8\u306b\u81f3\u308b\u76f4\u524d \u306b\u6975\u5927\u5024\u3092,\u76f4\u5f8c\u306b\u6975\u5c0f\u76f4\u3092\u3068\u308b\u8fd1\u508d\u3067F\u306f \u6975\u5927\u5024\u3068 \u306a\u308b.\u3053\u308c\u3089\u306e\u6319\u52d5\u3092,\u56f32\u3068 \u540c\u3058\u6642\u9593\u5206\u5272\u6cd5\u3067\u793a\u3059 \u56f33(a),(b)\u306e\u59ff\u52e2\u5909\u5316\u3068\u4f75\u305b\u3066\u5206\u6790\u3059\u308b.\nF\u304c \u5927\u304d\u3044\u91cd\u8ca0\u8377(\u4f4e\u6b69\u884c\u901f\u5ea6)\u306e\u56f33(a)\u3067\u306f,\u8098\u90e8\n\u3092\u5c48\u66f2\u3055\u305b\u3066\u5f37\u304f\u628a\u6301\u3057\u305f\u63e1\u308a\u90e8\u306b\u8eab\u4f53\u3092\u8fd1\u63a5\u3055\u305b, \u6b69\u5e45\u3092\u56f33(b)\u306b\u6bd4\u3079\u3066\u76f8\u5bfe\u7684\u306b\u5c0f\u3055\u304f\u523b\u307f\u9593\u6b20\u7684\u306a\u6b69 \u884c\u52d5\u4f5c\u3092\u3059\u308b.\u305d\u306e\u969b\u306b,\u5f8c\u811a\u3092\u4e3b\u652f\u6301\u811a\u3068\u3057\u3066,\u4ed6 \u811a\u306e\u8e0f\u51fa\u3057\u52d5\u4f5c\u306b\u540c\u671f\u3055\u305b\u305f\u4f53\u91cd\u5fc3\u306e\u79fb\u52d5\u3092\u7528\u3044,\u4e21 \u811a\u652f\u6301\u76f8\u306b\u81f3\u308b\u9593\u306b\u5927\u304d\u306aF\u3092\u767a\u63ee\u3059\u308b.\u305d \u306e\u5f8c\u306f, \u30d9\u30eb \u30c8(\u8eca\u3044\u3059)\u306e\u79fb\u52d5\u306b\u3088\u308bL\u306e \u5897\u5927\u306b\u4f34\u3063\u3066\u50be\u659c\u3057\n\u305f\u59ff\u52e2\u3092\u6574\u3048\u308b\u305f\u3081,\u5f8c \u811a\u304c\u8e0f\u51fa\u3057\u52d5\u4f5c\u306b\u79fb\u308b\u3068F\u306f\n\u6e1b\u3058,\u652f\u6301\u811a\u306e\u524d\u65b9\u306b\u5230\u9054\u5f8c\u304b\u3089F\u306f\u5897\u5927\u3059\u308b.\nF\u304c\u5c0f\u3055\u3044\u8efd\u8ca0\u8377(\u9ad8\u6b69\u884c\u901f\u5ea6)\u306e\u56f33(b)\u3067\u306f,\u6b69 \u5e45 \u3092\u5927\u306b\u3057\u305f\u52d5\u4f5c\u3092\u8981\u3059\u308b\u305f\u3081\u306b,\u63e1 \u308a\u90e8\u304b\u3089\u8eab\u4f53\u3092\u96e2 \u3057\u3066\u8098\u90e8\u3092\u4f38\u9577\u3055\u305b\u305f\u59ff\u52e2\u3092\u3068\u308a,\u8e0f\u51fa\u3057\u811a\u306e\u7740\u5730\u4f4d \u7f6e\u3092\u91cd\u8ca0\u8377\u6642\u306b\u6bd4\u3079\u3066\u524d\u65b9\u306b\u3059\u308b.\u5927 \u304d\u306a\u6b69\u5e45\u3067\u811a\u3092 \u9032\u3081\u308b\u969b\u306b,\u5168\u8eab\u304c\u6025\u6fc0\u306b\u524d\u65b9\u3078\u79fb\u884c\u3059\u308b\u305f\u3081L\u306f\u77ed\n\u7e2e\u3055\u308c\u308b.\u4e21\u811a\u652f\u6301\u306e\u72b6\u614b\u306b\u79fb\u884c\u3057\u305f\u76f4\u5f8c\u306b\u306f,\u524d\u811a \u3092\u4e3b\u652f\u6301\u811a\u3068\u3059\u308b\u62bc\u4ed8\u3051\u52d5\u4f5c\u3068\u4f75\u305b,\u5f8c \u811a\u306e\u8e74\u308a\u529b\u306b\n\u3088\u308b\u4f53\u91cd\u5fc3\u306e\u79fb\u52d5\u3068\u305d\u306e\u6163\u6027\u529b\u306e\u52b9\u679c\u306b\u3088\u308aF\u3092\u767a\u63ee\n\u3059\u308b.\u3057\u304b\u3057,V\u304c \u5927\u304d\u304fL\u304c\u901f\u304f\u5897\u3059\u3053\u3068\u306b\u3088\u308b\u59ff \u52e2\u306e\u4e0d\u5b89\u5b9a\u3092\u9632\u6b62\u3059\u308b\u305f\u3081,\u76f4 \u3061\u306b\u4ed6\u811a\u3092\u9032\u3081\u3066\u3044\u308b.\n3\u30fb2 \u8ca0\u8377\u306b\u5bfe\u3059\u308b\u81ea\u5f8b\u7684\u306a\u62bc\u4ed8\u3051\u6b69\u884c\u52d5\u4f5c\u3068\u4e3b \u89b3\u7684\u904b\u52d5\u5f37\u5ea6\u306e\u8a55\u4fa1 \u8ca0\u8377\u306b\u5bfe\u3059\u308b\u5e73\u5747\u6b69\u884c\u901f\u5ea6 V\u3068 \u5e73\u5747\u62bc\u4ed8\u3051\u529bF\u306e \u95a2\u4fc2\u3092\u56f34\u306b \u793a\u3059.\u3053 \u306e\u7279\u6027\u306f,\n\u88ab\u9a13\u8005\u304c\u610f\u8b58\u7684\u306b\u529b\u3080\u3053\u3068\u306a\u304f\u901a\u5e38\u306e\u62bc\u4ed8\u3051\u64cd\u4f5c\u306b\u3088\n(0) (1) (2) (3) (4)\n(a) R=160N/(km/h) (V = 0.5km/h)\n(0) (1) (2) (3) (4)\n(b) R=5N/(km/h) (V = 4.5km/h)\nFig. 3 Stick pictures of pushing with walking" + ] + }, + { + "image_filename": "designv8_17_0002184_load.php_id_22112102-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002184_load.php_id_22112102-Figure3-1.png", + "caption": "Figure 3. No-load magnetic field distributions with no excitation current. (a) Initial position, (b) twenty-degree movement.", + "texts": [ + " The motion equation of the proposed machine is given as Te=Jm d\u03c9 dt + TL + \u03bb\u03c9 (6) where Jm is the inertia of motion, \u03c9 the mechanical angular speed, TL the load torque, and \u03bb the damping coefficient. The finite element model of the proposed motor can be obtained by combining Maxwell equations of Eq. (4) to Eq. (6). The main specifications of the proposed VFMFMM are shown in Table 1. When no current passes through the machine excitation winding, that is, when it is under no excitation, no-load magnetic field distributions of the proposed VFMFMM under different rotor positions are shown in Fig. 3. It can be seen from Fig. 3 that although the field modulated motor is a branch of PMSM, its spatial magnetic field distribution is quite different from the traditional PMSM. The pole pairs of the stator windings of the traditional PMSM spatial magnetic field are equal to the pole pairs of the permanent magnet, while the pole pairs of the stator windings of the PMVM are no longer equal to the pole pairs of the permanent magnet. For the proposed VFPMVM, the permanent magnet pole pair is 14, and the stator winding space pole pair is 4" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001937_f_version_1584794417-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001937_f_version_1584794417-Figure1-1.png", + "caption": "Figure 1. A schematic of the fused deposition modeling (FDM) method.", + "texts": [ + " By removing the constraints, an inelastic strain, so-called prestrain, remains in the material and forms an irregular shape. The material is in a free-stress state at this stage. In the shape recovery process, the SMP is heated to recover its original shape, which is known as free strain recovery, and finally is cooled back to the low temperature. FDM technology, as a filament-based material-extrusion 3D printing method, applies a similar thermomechanical process on the material during the fabrication. Therefore, it may have the potential to fabricate 4D SMP architectures along with the shape programming. Figure 1 depicts a schematic of FDM technology. At first, the material is heated inside the liquefier up to Tln, which is higher than the transition temperature (Tg), and then forced out of the nozzle and deposited onto the platform by the 4D printer head moving at speed Sp. In this step, the material is stretched similar to the heating\u2013loading process of the SMP programming step that induces the prestrain. Therefore, the printing speed may affect the prestrain value. It would be sensible that greater speed produces more significant mechanical loading, hence inducing greater prestrain" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004635_506_1_delkline_1.pdf-Figure6.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004635_506_1_delkline_1.pdf-Figure6.3-1.png", + "caption": "Figure 6.3. Kingpin geometry definition.", + "texts": [ + " It amounts to another design position velocity specification. But either the linearity of the design equations or a wheel position are lost.) 101 Equation (6.1) may now be translated into suspension geometry terminology. If `1 is the line through a link solution x0 and x1, then a choice for a1, its direction vector, is x1\u2212x0. The vector b1 is the moment vector of the line `1, found by crossing any point on the line with the chosen direction vector. Hence, let b1 = x1\u00d7(x1\u2212x0) = x0\u00d7x1. For the kingpin, which will be line `2, consider the geometry of Figure 6.3. The kingpin is given by four parameters: kingpin inclination angle \u03c3, positive when the kingpin leans toward the vehicle body; scrub radius rs, positive when the kingpin/ground intersection is inboard of the wheel center; caster angle \u03c4 , positive when the kingpin leans rearward; and caster offset n, positive when the kingpin/ground intersection is ahead of the tire contact point. Consequently, a choice of direction vector for `2 is a2 = \u2212 tan \u03c4 tan\u03c3 1 . A point on the kingpin is (n, rs,\u2212r)T ; the corresponding moment vector of `2 is b2 = r tan\u03c3 + rs r tan \u03c4 \u2212 n rs tan \u03c4 + n tan\u03c3 " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004801_cle_2630_context_etd-Figure7.1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004801_cle_2630_context_etd-Figure7.1-1.png", + "caption": "FIGURE 7.1: DIPOLE POSITIONING FOR MUTUAL COUPLING [13]", + "texts": [ + "2) It is readily seen that the input impedance or the driving point impedance of a particular element is not only a function of its own self impedance but also a function of: -The the relative current flowing in the other elements and -The mutual impedance between elements. Several authors have treated the subject of estimating the value of the mutual impedance between elements [4], [6], [13] In particular, C. Balanis (13] gives simple mathematical relations for estimating the mutual impedance of wires positioned for mutual coupling. Refering to figure 7.1, showing two wires suspended in space and parallel to each other, the induced voltage at antenna 2, referred to its current at the input terminal, due to radiation from antenna 1, is given by: r /2V yJ El 2 1(z)I 2 (z)dz (7.3) 2i -//2 where Ezatis the E-field component radiated by antenna 1 which is parallel to antenna 2. It would be calculated as if antenna 2 were absent. I2 (z) represents the current distribution along antenna 2. This basic relation is used to develop a formula for the mutual impedance between antennas 1 and 2, using known relations for the E-field and assuming a sinusoidal current distribution in the dipoles. [13] (7.3) can rewritten as: 2 . 1 ,,,j2mf +12/2 sin 2 V 4rI2i -12/2 2 (7.4) x ekRi + &ikR, -2cos( ejkrjdz R1 R2 2 r 126 And the mutual impedance of (7.2) , referred to the input current I of antenna 1, can be written as [13]: Z2_ V21 - j'q 1,,m12mf12/2 s1in k(1 #- I z I~ 47I~ 2 i 22 k2 |z (7.5) X -jkR -jkR 2 ( 11 _-jkr x + -2cos k dz where Ri , R2 and r are the distances of figure 7.1 127 and k2 = WPE, 7 = intrinsic impedance of the medium = Vp /E I m , I m = maximum currents of antennas 1 and 2 I i , I i = Input currents of antennas 1 and 2 The mutual impedance ,as given by (7.5) is referred to the current at the input terminals and can be translated to the current maxima by [13]: 4,i2i Z 2 1 =Zi I 2 Im 2 m (7.6) Lr O r Z2 m 2 /2 . / 2m. sin k -- z o2/2 2 (7.7) e-.jk R --jkiR -jkr X + -2cos k - dz R R 2 2 r For two identical antennas (each of length 1 = nX/2, n= 1,2,3..) (7" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004872_9658_1_bbrelje_1.pdf-Figure8.2-1.png", + "caption": "Figure 8.2: Schematic view of a wing OML and interior component", + "texts": [ + " The constraint metric calculation must not depend on the convexity of each object (since aircraft wings are often locally concave). Differentiable: The constraint metric(s) must be differentiable and at least C0 continuous (prefer- 174 ably C1). Efficient: The constraint metric(s) must have computation time and memory requirements with acceptable scaling properties (with hundreds to tens of thousands of geometric design variables, objects, and surface polygons). for MDO To derive a mathematical definition of containment, let us consider some component (with outer surface A) to be fit inside OML surface B (Figure 8.2). Definition. Let A be a connected surface defined in three-dimensional real space. Definition. Let B be a closed, connected, orientable surface defined in three-dimensional real space. Closed orientable 3D surfaces have a defined interior volume and can be thought of as 3D solids or closed 3D shells. A watertight CFD mesh always meets this definition. Formally, the volume enclosed by B and the surface B are not identical, but I call them both B for simplicity. Definition. Let dmin be the minimum distance between A and B" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001789_cle_download_505_375-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure14-1.png", + "caption": "Figure 14. Flux density plot of improved 2 kW, 200 000 rpm motor.", + "texts": [ + " The performance results obtained for FEA of the improved models designed using Hiperco 50A material for core are enlisted in Table 5. Improved Hiperco 50A models offer 88.2%, 92.5%, and 93.3% efficiency for 2 kW, 200 000 rpm, 5 kW, 24 000 rpm and 120 kW, 10 000 rpm rating motors, respectively. Improved torque profiles and flux density plots are generated as per the FEA results obtained with the application of Hiperco 50A material as stator core and teeth material. The torque profile and flux density plot of 2 kW, 200 000 rpm IPMSM obtained from FEA for the improved motor is presented in Figure 13 and Figure 14, respectively. The torque profile and flux density plot for the improved motor with rating 5 kW, 24 000 rpm IPMSM using Hiperco 50A material are shown in Figure 15 and Figure 16, respectively. This 5 kW, 24 000 rpm improved IPMSM has average torque of 1.99 N.m., similar to the initial design. Still, the torque profile is considerably better than that of the initially designed motor with M19 material. It can be observed that the actual flux density is close to the assumed flux density in various magnetic sections of both 2 kW and 5 kW motors" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004807_f_version_1708441601-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004807_f_version_1708441601-Figure1-1.png", + "caption": "Figure 1. Various stud es on ROPS safety: (a) sequence of d formation of an energy absorption disc as simulated by using the finite el ment m thod (R printed with permission from Ref. [23]. 2019, Latorre-Biel, J.I.); (b) ROPS deformation and motio state of the dummy when a collision occurs (Reprinted with permission from Ref. [25]. 2012. Chen, C.)", + "texts": [ + " In this study, previous studies on the analysis of lateral overturning and backward rollover of tractors were summarized to enhance safety and identify factors causing tractor accidents. The characteristics of each study were examined and summarized to determine the latest trends in tractor safety evaluation, thereby providing insights into reducing agricultural tractor accidents. To reduce the number of tractor accidents, the installation of a ROPS, a mechanical structure designed to mitigate impact on the driver during accidents, has been proposed (Figure 1). Myers and Hendricks [21] analyzed the mortality rate resulting from tractor accidents in the United States and advocated for the installation of a ROPS in agricultural tractors to decrease mortality rates. The ROPS originated in Sweden and New Zealand in the 1950s. During 1959\u20131978, numerous countries, including Norway, Finland, New Zealand, and the United States, introduced regulations mandating the installation of a ROPS, leading to a significant reduction in tractor rollover risks. Moreover, the number of deaths decreased depending on the type and utilization method of the ROPS [22]", + " Hunter and Owen [27] mentioned that although the installation of a ROPS cannot perfectly prevent driver injury caused by tractor rollover, it is a crucial safety measure. Therefore, research is required to evaluate the safety of tractors and decrease the accident rate. Studies on safety are mainly conducted by performing authorized tractor tests and theoretical analysis. Recently, however, safety has been analyzed by employing various methods, such as simulations and scale models (Figure 2). Agriculture 2024, 14, 334 3 of 14Agriculture 2024, 14, x FOR PEER REVIEW 3 of 16 Figure 1. Various studies on ROPS safety: (a) sequence of deformation of an energy absorption disc as simulated by using the finite element method (Reprinted with permission from Ref. [23]. 2019, Latorre-Biel, J.I.); (b) ROPS deformation and motion state of the dummy when a collision occurs (Reprinted with permission from Ref. [25]. 2012. Chen, C.) Therefore, research is required to evaluate the safety of tractors and decrease the ac- cident rate. Studies on safety are mainly conducted by performing authorized tractor tests and theoretical analysis" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002418__32_5_32_32_456__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002418__32_5_32_32_456__pdf-Figure1-1.png", + "caption": "Fig. 1 Appearance of the developed prosthesis (left hand)", + "texts": [], + "surrounding_texts": [ + "\u5b66\u8853\u30fb\u6280\u8853\u8ad6\u6587\n\u6a5f\u80fd\u6027\u3068\u30c7\u30b6\u30a4\u30f3\u6027\u3092\u8003\u616e\u3057\u305f \u8efd\u91cf\u30fb\u4f4e\u30b3\u30b9\u30c8\u306e\u5bfe\u54113\u6307\u7fa9\u624b\n\u5409 \u5ddd \u96c5 \u535a\u22171\u22172 \u7530 \u53e3 \u88d5 \u4e5f\u22171\u22172 \u962a \u672c \u771f\u22173 \u5c71 \u4e2d \u4fca \u6cbb\u22173\u22174\n\u677e \u672c \u5409 \u592e\u22172 \u5c0f\u7b20\u539f \u53f8\u22171 \u6cb3 \u5cf6 \u5247 \u5929\u22175\nLow-Cost and Lightweight Trans-Radial Prosthesis with Three Opposed Fingers\nConsidering Functionality and Design\nMasahiro Yoshikawa\u22171\u22172, Yuya Taguchi\u22171\u22172, Shin Sakamoto\u22173, Shunji Yamanaka\u22173\u22174,\nYoshio Matsumoto\u22172, Tsukasa Ogasawara\u22171 and Noritaka Kawashima\u22175\nAt present, there are body-powered hooks and myoelectric prosthetic hands that trans-radial amputees can use for work. Though the body-powered hook has good workability in detailed works, the design of the hook spoils its appearance and the harness impairs the feelings of wearing. The myoelectric prosthetic hand has a natural appearance similar to the human hand and intuitive operability with a myoelectric control system. However, it is high cost and heavyweight. Because of these problems, many amputees use cosmetic prostheses especially in Japan. In this paper, we report a low-cost and lightweight electric prosthesis with three opposed fingers considering functionality and design. A simple mechanism to control fingers by a linear actuator contributes to satisfactory workability, lightweight, and low cost. A control system using an inexpensive distance sensor allows intuitive operability as the myoelectric sensor at low cost. A socket is easily removable so that users can wear properly as the situation demands. It has a sophisticated appearance as a tool and can be produced by a 3D printer. The total weight of the hand and socket is 300 [g]. Evaluation tests utilizing Southampton Hand Assessment Procedure (SHAP) demonstrated that developed prosthesis was effective to operate light objects for daily use.\nKey Words: Prosthesis, Distance Sensor, 3D Printer, Socket\n1. \u306f \u3058 \u3081 \u306b\n\u73fe\u72b6\uff0c\u524d\u8155\u5207\u65ad\u8005\u304c\u9078\u629e\u53ef\u80fd\u306a\u4f5c\u696d\u7528\u306e\u7fa9\u624b\u306b\u306f\uff0c\u5927\u304d\u304f\u5206 \u3051\u3066\u80fd\u52d5\u30d5\u30c3\u30af\u3068\u7b4b\u96fb\u7fa9\u624b\u304c\u3042\u308b\uff0e\u80fd\u52d5\u30d5\u30c3\u30af\u306f\u5207\u65ad\u80a2\u3068\u53cd\u5bfe \u5074\u306e\u80a9\u306e\u52d5\u304d\u3092\u5229\u7528\u3057\u3066\u30b1\u30fc\u30d6\u30eb\u3092\u727d\u5f15\u3057\u30d5\u30c3\u30af\u72b6\u306e\u624b\u5148\u306e\u958b \u9589\u3092\u64cd\u4f5c\u3059\u308b\u7fa9\u624b\u3067\u3042\u308a\uff0c\u4f5c\u696d\u6027\u306b\u512a\u308c\uff0c\u7cbe\u7dfb\u306a\u4f5c\u696d\u306b\u9069\u3057\u3066 \u3044\u308b [1]\uff0e\u53cd\u9762\uff0c\u30b1\u30fc\u30d6\u30eb\u3092\u727d\u5f15\u3059\u308b\u30cf\u30fc\u30cd\u30b9\u3092\u4f53\u306b\u88c5\u7740\u3059\u308b\u305f\n\u539f\u7a3f\u53d7\u4ed8 2013 \u5e74 7 \u6708 24 \u65e5 \u22171\u5948\u826f\u5148\u7aef\u79d1\u5b66\u6280\u8853\u5927\u5b66\u9662\u5927\u5b66 \u60c5\u5831\u79d1\u5b66\u7814\u7a76\u79d1 \u22172\u7523\u696d\u6280\u8853\u7dcf\u5408\u7814\u7a76\u6240 \u77e5\u80fd\u30b7\u30b9\u30c6\u30e0\u7814\u7a76\u90e8\u9580 \u22173\u6176\u61c9\u7fa9\u587e\u5927\u5b66\u5927\u5b66\u9662 \u653f\u7b56\u30fb\u30e1\u30c7\u30a3\u30a2\u7814\u7a76\u79d1 \u22174\u6771\u4eac\u5927\u5b66 \u751f\u7523\u6280\u8853\u7814\u7a76\u6240 \u22175\u56fd\u7acb\u969c\u5bb3\u8005\u30ea\u30cf\u30d3\u30ea\u30c6\u30fc\u30b7\u30e7\u30f3\u30bb\u30f3\u30bf\u30fc\u7814\u7a76\u6240 \u904b\u52d5\u6a5f\u80fd\u7cfb\u969c\u5bb3\u7814\u7a76\u90e8 \u22171Graduate School of Information Science, Nara Institute of Sci-\nence and Technology, NAIST \u22172Intelligent Systems Research Institute, National Institute of Ad-\nvanced Industrial Science and Technology, AIST \u22173Graduate School of Media and Governance, Keio University \u22174Institute of Industrial Science, The University of Tokyo \u22175Dept. Rehabilitation for the Movement Functions, Research In-\nstitute, National Rehabilitation Center for the Persons with Disabilities, NRCD\n\u25a0 \u672c\u8ad6\u6587\u306f\u63d0\u6848\u6027\u3067\u8a55\u4fa1\u3055\u308c\u307e\u3057\u305f\uff0e\n\u3081\u88c5\u7740\u6027\u304c\u60aa\u304f\uff0c\u30d5\u30c3\u30af\u306e\u30c7\u30b6\u30a4\u30f3\u304c\u5916\u89b3\u3092\u640d\u306d\u3066\u304a\u308a\uff0c\u4f7f\u7528 \u306b\u969b\u3057\u3066\u306e\u5fc3\u7406\u7684\u8ca0\u62c5\u304c\u5927\u304d\u3044\uff0e\u80fd\u52d5\u30d5\u30c3\u30af\u306f\u88fd\u54c1\u5316\u304b\u3089 50\u5e74 \u4ee5\u4e0a\u7d4c\u3063\u3066\u3044\u308b\u304c\uff0c\u6a5f\u69cb\u3084\u5916\u89b3\u306f\u5909\u5316\u3057\u3066\u304a\u3089\u305a\uff0c\u7814\u7a76\u958b\u767a\u306f \u3042\u307e\u308a\u9032\u3093\u3067\u3044\u306a\u3044\uff0e \u4e00\u65b9\uff0c\u7b4b\u96fb\u7fa9\u624b\u306f\u4eba\u9593\u306e\u624b\u306b\u8fd1\u3044\u5916\u89b3\u3092\u6709\u3057\uff0c\u5207\u65ad\u7aef\u304b\u3089\u8a08\u6e2c \u53ef\u80fd\u306a\u7b4b\u96fb\u4f4d\u3092\u4fe1\u53f7\u6e90\u3068\u3059\u308b\u76f4\u611f\u7684\u306a\u64cd\u4f5c\u6027\u304c\u7279\u9577\u3067\u3042\u308b\uff0e\u80fd\u52d5 \u7fa9\u624b\u306e\u3088\u3046\u306b\u30cf\u30fc\u30cd\u30b9\u3092\u5fc5\u8981\u3068\u3057\u306a\u3044\u305f\u3081\uff0c\u88c5\u7740\u6027\u3082\u826f\u3044\uff0eOtto bock\u793e\u306f 1960\u5e74\u4ee3\u306b\u958b\u9589\u53ef\u80fd\u306a 3\u6307\u3092\u6301\u3063\u305fMyobock\u3092\u5546\u54c1 \u5316\u3057\uff0c\u6700\u8fd1\u3067\u306f 5\u6307\u306e\u52d5\u4f5c\u304c\u53ef\u80fd\u306aMichelangelo Hand [2]\u3092 \u5546\u54c1\u5316\u3057\u3066\u3044\u308b\uff0eTouch Bionics\u793e\u306e iLimb [3]\uff0cRSL Steeper \u793e\u306e bebionic [4]\u3082\u540c\u69d8\u306e 5\u6307\u306e\u7fa9\u624b\u3067\u3042\u308b\uff0e\u73fe\u5728\u306e\u7fa9\u624b\u306e\u7814 \u7a76\u958b\u767a\u306f\u3053\u306e\u3088\u3046\u306a 5\u6307\u306e\u7b4b\u96fb\u7fa9\u624b\u3092\u3044\u304b\u306b\u5b9f\u73fe\u3059\u308b\u304b\u306b\u6ce8\u529b \u3055\u308c\u3066\u3044\u308b [5]\uff5e[12]\uff0e\u3057\u304b\u3057\uff0c\u4eba\u9593\u306e\u624b\u3068\u540c\u69d8\u306e\u5916\u89b3\u3068\u6a5f\u80fd\u3092 \u5b9f\u73fe\u3059\u308b\u305f\u3081\u306b\u306f\uff0c\u8907\u6570\u306e\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\uff0c\u8907\u96d1\u306a\u6a5f\u69cb\uff0c\u9ad8\u6027 \u80fd\u306a\u30d7\u30ed\u30bb\u30c3\u30b5\u304c\u5fc5\u8981\u3068\u306a\u308a\uff0c\u5fc5\u7136\u7684\u306b\u9ad8\u4fa1\u3068\u306a\u308b\uff0e\u5b89\u4fa1\u3068\u3055 \u308c\u308bOtto bock\u793e\u306eMyobock\u3067\u3082 150\u4e07\u5186\uff0c\u9ad8\u4fa1\u306a\u7fa9\u624b\u3067\u306f 500\u4e07\u5186\u4ee5\u4e0a\u3068\u306a\u308b\u305f\u3081\uff0c\u65e5\u672c\u306e\u88dc\u88c5\u5177\u306e\u652f\u7d66\u5236\u5ea6\u3067\u306f\u652f\u7d66\u304c \u56f0\u96e3\u3067\u3042\u308a\uff0c\u3053\u308c\u3089\u306e\u7b4b\u96fb\u7fa9\u624b\u3092\u5165\u624b\u3059\u308b\u3053\u3068\u306f\u5bb9\u6613\u3067\u306f\u306a\u3044\uff0e \u307e\u305f\uff0c\u7b4b\u96fb\u7fa9\u624b\u306f\u5207\u65ad\u80a2\u3092\u633f\u5165\u3059\u308b\u30bd\u30b1\u30c3\u30c8\u90e8\u3092\u542b\u3081\u3066 900 [g]\nJRSJ Vol. 32 No. 5 \u201454\u2014 June, 2014", + "\u4ee5\u4e0a\u306e\u91cd\u91cf\u304c\u3042\u308b\u304c\uff0c\u7fa9\u624b\u3092\u5207\u65ad\u7aef\u3067\u652f\u6301\u3059\u308b\u5207\u65ad\u8005\u306b\u3068\u3063\u3066 \u306f\u91cd\u304f\uff0c\u3088\u3046\u3084\u304f\u5165\u624b\u3057\u3066\u3082\u305d\u306e\u91cd\u3055\u306b\u6163\u308c\u305a\u306b\u4f7f\u7528\u3092\u4e2d\u6b62\u3059 \u308b\u30e6\u30fc\u30b6\u3082\u591a\u3044\uff0e \u3053\u306e\u3088\u3046\u306a\u4f5c\u696d\u7528\u7fa9\u624b\u306e\u8ab2\u984c\u306b\u3088\u308a\uff0c\u524d\u8155\u5207\u65ad\u8005\u306e\u591a\u304f\u306f\u4f5c \u696d\u7528\u7fa9\u624b\u3092\u4f7f\u7528\u305b\u305a\uff0c\u6d88\u6975\u7684\u9078\u629e\u3068\u3057\u3066\u624b\u306b\u8fd1\u3044\u5916\u89b3\u306e\u88c5\u98fe\u7fa9 \u624b\u3092\u4f7f\u7528\u3057\u3066\u3044\u308b\uff0e\u3057\u304b\u3057\uff0c\u88c5\u98fe\u7fa9\u624b\u306f\u7269\u3092\u62bc\u3055\u3048\u308b\u7a0b\u5ea6\u306e\u6a5f \u80fd\u3057\u304b\u306a\u304f\uff0c\u65e5\u5e38\u751f\u6d3b\u3067\u306f\u4e0d\u4fbf\u3067\u3042\u308b\uff0e \u4eba\u9593\u306e\u624b\u3068\u540c\u69d8\u306e\u5916\u89b3\u3068\u6a5f\u80fd\u3092\u6301\u3063\u305f\u7fa9\u624b\u3092\u5b9f\u73fe\u3059\u308b\u3053\u3068\u306f \u4eca\u5f8c\u3082\u91cd\u8981\u306a\u8ab2\u984c\u3067\u306f\u3042\u308b\u304c\uff0c\u73fe\u5728\u4f5c\u696d\u7528\u306e\u7fa9\u624b\u3092\u5fc5\u8981\u3068\u3057\u3066 \u3044\u308b\u5207\u65ad\u8005\u3078\u306e\u73fe\u5b9f\u7684\u306a\u30a2\u30d7\u30ed\u30fc\u30c1\u3082\u5fc5\u8981\u3067\u3042\u308b\uff0e\u305d\u3053\u3067\uff0c\u672c \u7814\u7a76\u3067\u306f\u4f5c\u696d\u6027\uff0c\u64cd\u4f5c\u6027\uff0c\u88c5\u7740\u6027\u306a\u3069\u306e\u6a5f\u80fd\u6027\u3068\u30c7\u30b6\u30a4\u30f3\u6027\u306b \u512a\u308c\u305f\u8efd\u91cf\u30fb\u4f4e\u30b3\u30b9\u30c8\u306e\u96fb\u52d5\u7fa9\u624b\u3092\u958b\u767a\u3057\uff0c\u5207\u65ad\u8005\u306b\u65b0\u305f\u306a\u4f5c \u696d\u7528\u7fa9\u624b\u306e\u9078\u629e\u80a2\u3092\u63d0\u6848\u3059\u308b\uff0e\u958b\u767a\u3059\u308b\u7fa9\u624b\u306f\u4eba\u9593\u540c\u69d8\u306e 5\u6307 \u304c\u5fc5\u8981\u3068\u3044\u3046\u767a\u60f3\u3092\u8ee2\u63db\u3057\uff0c\u5bfe\u5411\u914d\u7f6e\u306e 3\u6307\u3092\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5 \u30a8\u30fc\u30bf\u3067\u5236\u5fa1\u3059\u308b\u6a5f\u69cb\u3068\u3059\u308b\u3053\u3068\u3067\uff0c\u4f4e\u30b3\u30b9\u30c8\u30fb\u8efd\u91cf\u5316\u3092\u56f3\u308b\u3068 \u3068\u3082\u306b\uff0c\u4f5c\u696d\u6027\u3092\u62c5\u4fdd\u3059\u308b\uff0e\u307e\u305f\uff0c\u5b89\u4fa1\u306a\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u7528\u3044\u308b \u3053\u3068\u3067\uff0c\u7b4b\u96fb\u30bb\u30f3\u30b5\u540c\u69d8\u306e\u76f4\u611f\u7684\u306a\u64cd\u4f5c\u6027\u3092\u4f4e\u30b3\u30b9\u30c8\u3067\u5b9f\u73fe\u3059 \u308b\uff0e\u5207\u65ad\u7aef\u3068\u306e\u30a4\u30f3\u30bf\u30d5\u30a7\u30fc\u30b9\u3068\u306a\u308b\u30bd\u30b1\u30c3\u30c8\u306f\uff0c\u666e\u6bb5\u306f\u88c5\u98fe \u7fa9\u624b\u3092\u4f7f\u7528\u3057\u3066\u3044\u308b\u5834\u5408\u3067\u3082\uff0c\u81ea\u5b85\u3084\u8077\u5834\u306b\u304a\u3051\u308b\u4f5c\u696d\u7528\u3068\u3057 \u3066\u4f7f\u3044\u5206\u3051\u3089\u308c\u308b\u3088\u3046\u306b\uff0c\u5bb9\u6613\u306b\u7740\u8131\u53ef\u80fd\u3068\u3057\u305f\uff0e\u305d\u3057\u3066\uff0c\u611b \u7740\u3092\u6301\u3063\u3066\u4f7f\u3048\u308b\u3088\u3046\u306b\uff0c\u9053\u5177\u3068\u3057\u3066\u6d17\u7df4\u3055\u308c\u305f\u5916\u89b3\u3092\u5099\u3048\u308b\uff0e \u63d0\u6848\u3059\u308b\u7fa9\u624b\u306e\u7279\u9577\u3092\u307e\u3068\u3081\u308b\u3068\u4ee5\u4e0b\u306e 5\u70b9\u3067\u3042\u308b\uff0e\n\u2022\u4f5c\u696d\u6027\u3092\u8003\u616e\u3057\u305f\u5bfe\u5411\u914d\u7f6e\u306e 3\u6307 \u2022\u7b4b\u96fb\u7fa9\u624b\u3068\u540c\u69d8\u306e\u76f4\u611f\u7684\u306a\u64cd\u4f5c\u6027\u3092\u6301\u3064\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0 \u2022\u5bb9\u6613\u306b\u7740\u8131\u53ef\u80fd\u306a\u30bd\u30b1\u30c3\u30c8 \u2022\u9053\u5177\u3068\u3057\u3066\u6d17\u7df4\u3055\u308c\u305f\u5916\u89b3 \u2022\u8efd\u91cf\u30fb\u4f4e\u30b3\u30b9\u30c8\n\u5177\u4f53\u7684\u306a\u6570\u5024\u76ee\u6a19\u3068\u3057\u3066\u306f\uff0c500 [g] \u7a0b\u5ea6\u306e\u7269\u4f53\u3092\u628a\u6301\u3067\u304d\uff0c \u30bd\u30b1\u30c3\u30c8\u3092\u542b\u3081\u305f\u7dcf\u91cd\u91cf\u306f 300 [g]\uff0c6\u6642\u9593\u7a0b\u5ea6\u306e\u9023\u7d9a\u4f7f\u7528\u304c\u3067 \u304d\u308b\u3053\u3068\u3068\u3057\uff0c\u7247\u624b\u5207\u65ad\u8005\u306e\u5065\u5e38\u80a2\u306b\u5bfe\u3059\u308b\u88dc\u52a9\u80a2\u3068\u3057\u3066\u306e\u7528 \u9014\u3092\u4e3b\u306b\u60f3\u5b9a\u3057\u3066\u3044\u308b\uff0e \u672c\u7a3f\u3067\u306f\uff0c\u4e0a\u8a18\u958b\u767a\u65b9\u91dd\u306b\u57fa\u3065\u3044\u3066\u8a66\u4f5c\u3057\u305f\u96fb\u52d5\u7fa9\u624b\u3068\uff0c\u4e0a \u80a2\u6a5f\u80fd\u306e\u8a55\u4fa1\u30c6\u30b9\u30c8 SHAP\uff08Southampton Hand Assessment Procedure\uff09\u306b\u57fa\u3065\u3044\u305f\u5207\u65ad\u8005\u306b\u3088\u308b\u8a66\u4f5c\u7fa9\u624b\u306e\u8a55\u4fa1\u7d50\u679c\u306b\u3064 \u3044\u3066\u5831\u544a\u3059\u308b\uff0e\n2. \u6a5f\u80fd\u6027\u3068\u30c7\u30b6\u30a4\u30f3\u6027\u3092\u8003\u616e\u3057\u305f\u5bfe\u5411 3\u6307\u96fb\u52d5\u7fa9\u624b\nFig. 1\u306b\u8a66\u4f5c\u3057\u305f\u96fb\u52d5\u7fa9\u624b\uff08\u5de6\u624b\u7528\uff09\u306e\u5916\u89b3\u3092\u793a\u3059\uff0e\u7fa9\u624b\u306e \u69cb\u6210\u8981\u7d20\u306f\uff0c\u5927\u304d\u304f\u5206\u3051\u3066\u30cf\u30f3\u30c9\uff0c\u30cf\u30f3\u30c9\u30db\u30eb\u30c0\uff0c\u30bd\u30b1\u30c3\u30c8\uff0c\u8ddd \u96e2\u30bb\u30f3\u30b5\uff0c\u30b5\u30dd\u30fc\u30bf\u306b\u5206\u3051\u3089\u308c\u308b\uff0e\u30cf\u30f3\u30c9\u306f\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc \u30bf\u3067\u958b\u9589\u3059\u308b\u5bfe\u5411\u914d\u7f6e\u306e 3\u6307\u3092\u5099\u3048\u308b\uff0e\u524d\u8155\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u88c5 \u7740\u3057\uff0c\u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u30bb\u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u5fdc\u3058 \u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\uff0e\u5207\u65ad\u7aef\u3092\u633f\u5165\u3059\u308b\u30bd\u30b1\u30c3\u30c8\u306f\uff0c\u30b5\u30dd\u30fc\u30bf\u306e \u7559\u3081\u5177\u3067\u7de0\u3081\u4ed8\u3051\u308b\u3053\u3068\u3067\u5bb9\u6613\u306b\u88c5\u7740\u53ef\u80fd\u3067\u3042\u308b\uff0e\u4ee5\u4e0b\uff0c\u7fa9\u624b \u306e\u5404\u8981\u7d20\u306b\u3064\u3044\u3066\u8a73\u7d30\u306b\u8ff0\u3079\u308b\uff0e\n2. 1 \u6307\u306e\u958b\u9589\u6a5f\u69cb \u63d0\u6848\u7fa9\u624b\u306f\u5bfe\u5411\u306b\u914d\u7f6e\u3055\u308c\u305f\u540c\u4e00\u5f62\u72b6\u306e 3\u6307\u304c\u540c\u6642\u306b\u958b\u9589\u3059 \u308b\u3053\u3068\u306b\u3088\u308a\u5bfe\u8c61\u3092\u628a\u6301\u3059\u308b\uff0eFig. 2\u306b\u30cf\u30f3\u30c9\u306e\u5185\u90e8\u65ad\u9762\u3092\u793a \u3059\uff0e\u30cf\u30f3\u30c9\u306b\u306f\u52d5\u529b\u6e90\u306e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\uff08L12-R\uff0cFirgelli Technologies Inc\uff09\uff0c\u5236\u5fa1\u7528\u30de\u30a4\u30b3\u30f3\uff08Arduino Pro Mini\uff09\u304c\n\u5185\u8535\u3055\u308c\u3066\u3044\u308b\uff0eTable 1\u306b\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4ed5\u69d8\u3092\u793a \u3059\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306f\uff0c\u4f4d\u7f6e\u5236\u5fa1\u53ef\u80fd\u306a\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u3066\u3044\u308b\uff0e\u30cf\u30f3\u30c9\u5185\u90e8\u306b\u306f\u6307\u306e\u958b\u9589\u306e\u305f\u3081\u306b Fig. 3\u306b\u793a\u3059\u3088\u3046\u306a \u30ea\u30f3\u30af\u6a5f\u69cb\u3092\u63a1\u7528\u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4f38\u7e2e\u3059\u308b \u30b7\u30e3\u30d5\u30c8\u5148\u7aef\u90e8\u306f\u30ea\u30f3\u30af 1\u306b\u76f4\u7d50\u3057\u3066\u3044\u308b\uff0e\u30b7\u30e3\u30d5\u30c8\u304c\u521d\u671f\u4f4d \u7f6e\u304b\u3089\u4f38\u5c55\u3059\u308b\u3068\uff0c\u305d\u308c\u306b\u4f34\u3063\u3066\u30ea\u30f3\u30af 1\u304c\u30cf\u30f3\u30c9\u5185\u90e8\u3092\u79fb\u52d5 \u3057\uff0c\u5916\u88c5\u90e8\u3068\u306e\u63a5\u70b9\u3092\u30ac\u30a4\u30c9\u3068\u3057\u3066\u30ea\u30f3\u30af 2\u304c\u7e70\u308a\u51fa\u3055\u308c\uff0c\u30b7\u30e3 \u30d5\u30c8\u3068\u30ea\u30f3\u30af 2\u304c\u6210\u3059\u89d2\u5ea6\u304c\u5897\u52a0\u3059\u308b\uff0e\u3053\u308c\u306b\u3088\u3063\u3066\uff0c\u6307\u304c\u958b \u304f\uff0e\u30b7\u30e3\u30d5\u30c8\u304c\u77ed\u7e2e\u3059\u308b\u3068\uff0c\u30b7\u30e3\u30d5\u30c8\u3068\u30ea\u30f3\u30af 2\u306e\u6210\u3059\u89d2\u5ea6\u304c \u6e1b\u5c11\u3057\uff0c\u30ea\u30f3\u30af 2\u304c\u30cf\u30f3\u30c9\u5185\u90e8\u306b\u5f15\u304d\u8fbc\u307e\u308c\u6307\u304c\u9589\u3058\u308b\uff0e3\u6307 \u304c\u540c\u69d8\u306b\u4f5c\u52d5\u3059\u308b\u3053\u3068\u3067\uff0c\u6307\u306e\u958b\u9589\u304c\u884c\u308f\u308c\u308b\uff0e\u3053\u306e\u3088\u3046\u306a\u30b7 \u30f3\u30d7\u30eb\u306a\u6307\u306e\u958b\u9589\u6a5f\u69cb\u306f\uff0c\u30cf\u30f3\u30c9\u306e\u8efd\u91cf\u5316\u3068\u5c0f\u578b\u5316\u306b\u5bc4\u4e0e\u3059\u308b\uff0e Fig. 2 \u306e\u6307\u306e\u65ad\u9762\u56f3\u3067\u793a\u3057\u305f\u3088\u3046\u306b\uff0c\u6307\u306e\u95a2\u7bc0\u306b\u306f\u30c8\u30fc\u30b7\u30e7 \u30f3\u30d0\u30cd\uff08\u3070\u306d\u5b9a\u6570 11.5 [N\u00b7mm/deg]\uff09\u3092\u7d44\u307f\u8fbc\u307f\uff0c\u7269\u4f53\u306b\u99b4\u67d3 \u3080\u3088\u3046\u306b\u628a\u6301\u3059\u308b\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u6307\u5148\u306b\u88c5\u7740\u3059\u308b\u30b7\u30ea\u30b3\u30f3 \u88fd\u30ad\u30e3\u30c3\u30d7\uff08\u786c\u5ea6 30\u5ea6\uff0c\u539a\u3055 1.5 [mm]\uff09\u306f\uff0c\u628a\u6301\u3057\u305f\u7269\u4f53\u304c\u6ed1 \u308b\u306e\u3092\u9632\u304e\uff0c\u9069\u5ea6\u306b\u67d4\u3089\u304b\u3044\u6307\u5148\u3092\u5b9f\u73fe\u3057\u3066\u3044\u308b\uff0e\u307e\u305f\uff0c\u6307\u5148 \u5168\u4f53\u304c\u30b7\u30ea\u30b3\u30f3\u3067\u8986\u308f\u308c\u308b\u305f\u3081\uff0c\u66f8\u7c4d\u306e\u30da\u30fc\u30b8\u3092\u6372\u308b\u5834\u5408\u3084\u673a \u4e0a\u306e\u7269\u4f53\u3092\u305f\u3050\u308a\u5bc4\u305b\u308b\u5834\u5408\u306b\u3082\u6709\u52b9\u3067\u3042\u308b\uff0e3\u6307\u306f\u540c\u4e00\u5f62\u72b6 \u306e\u305f\u3081\uff0c\u6545\u969c\u6642\u306e\u4ea4\u63db\u3082\u5bb9\u6613\u3067\u3042\u308b\uff0e\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201455\u2014 2014 \u5e74 6 \u6708", + "2. 2 \u5bfe\u5411\u914d\u7f6e\u306e 3\u6307 Fig. 4\u306b 3\u6307\u3092\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u914d\u7f6e\u3092\u793a\u3059\uff0e\u6b63\u9762\u304b\u3089\u898b \u3066\u6307\u5148\u4f4d\u7f6e\u304c\u5185\u5074\u3092\u9802\u89d2\u3068\u3059\u308b\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u3068\u306a\u308b\u3088\u3046\u306b\u914d\u7f6e \u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5\u30c8\u306e\u7e70\u308a\u51fa\u3057\u91cf\u304c\u540c\u3058 \u5834\u5408\uff0c\u6b63\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u3088\u308a\u3082\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u306e\u307b\u3046\u304c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\uff08\u4e21\u7aef\u77e2\u5370\u90e8\u5206\uff09\u3092\u3088\u308a\u5927\u304d\u304f\u78ba\u4fdd\u3067\u304d\u308b\uff0e500 [ml] \u306e\u30da\u30c3\u30c8\u30dc\u30c8\u30eb\u3092\u628a\u6301\u3067\u304d\u308b\u5341\u5206\u306a\u7a7a\u9593\u3092\u78ba\u4fdd\u3059\u308b\u305f\u3081\uff0c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\u306f 80 [mm]\u3068\u3057\u305f\uff0e Fig. 5\u306e\u5de6\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\uff0cOttobock\u793e\u306a\u3069\u306e 3\u6307\u306e\u7b4b\u96fb \u7fa9\u624b\u306f\uff0c\u30ea\u30f3\u30af\u306e\u904b\u52d5\u65b9\u5411\u304c\u56de\u8ee2\u8ef8\u306b\u5bfe\u3057\u3066\u76f4\u4ea4\u3057\u3066\u3044\u308b\u305f\u3081\uff0c \u5e73\u677f\u72b6\u306e\u5bfe\u8c61\u3092\u628a\u6301\u3059\u308b\u5834\u5408\uff0c\u56de\u5185\u5916\u3092\u884c\u308f\u305a\u306b\u628a\u6301\u53ef\u80fd\u306a\u65b9 \u5411\u306f 1 \u7a2e\u985e\u306e\u307f\u3067\u3042\u308b\uff08\u4e00\u822c\u7684\u306a 2 \u6307\u80fd\u52d5\u30d5\u30c3\u30af\u3082\u540c\u69d8\uff09\uff0e\u4e00 \u65b9\uff0cFig. 5 \u306e\u53f3\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\uff0c3 \u6307\u3092\u5bfe\u5411\u306b\u914d\u7f6e\u3059\u308b\u3068\uff0c\u56de\n\u5185\u5916\u3092\u884c\u308f\u305a\u306b 3\u7a2e\u985e\u306e\u628a\u6301\u65b9\u5411\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u80a9 \u3084\u4f53\u5e79\u306e\u52d5\u304d\u3067\u56de\u5185\u5916\u306e\u52d5\u304d\u3092\u88dc\u511f\u3059\u308b\u4ee3\u511f\u52d5\u4f5c\u3092\u6291\u5236\u3057\uff0c\u7121 \u7406\u306e\u306a\u3044\u59ff\u52e2\u3067\u306e\u64cd\u4f5c\u304c\u53ef\u80fd\u3068\u306a\u308b\uff0e3\u6307\u306b\u3088\u3063\u3066\u5177\u4f53\u7684\u306b\u3069 \u306e\u3088\u3046\u306a\u628a\u6301\u304c\u53ef\u80fd\u304b\u306f 3\u7ae0\u3067\u8ff0\u3079\u308b\uff0e 2. 3 \u30e6\u30fc\u30b6\u306e\u6307\u958b\u9589\u610f\u56f3\u3092\u691c\u51fa\u3059\u308b\u8ddd\u96e2\u30bb\u30f3\u30b5 \u63d0\u6848\u7fa9\u624b\u306f\u524d\u8155\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u88c5\u7740\u3057\uff0c\u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u30bb \u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u5fdc\u3058\u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\u65b9\u5f0f\u3092\u7528 \u3044\u3066\u3044\u308b\uff0eFig. 6\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5916\u89b3\u3092\u793a\u3059\uff0e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306b\u306f\uff0c \u975e\u63a5\u89e6\u3067\u8ddd\u96e2\u304c\u8a08\u6e2c\u53ef\u80fd\u306a\u30d5\u30a9\u30c8\u30ea\u30d5\u30ec\u30af\u30bf\uff08SG-105\uff0cKODENSHI\uff09\u3092\u7528\u3044\u305f\uff0e\u7b4b\u53ce\u7e2e\u3092\u884c\u3063\u3066\u3044\u306a\u3044\u72b6\u614b\u3067\uff0c\u8ddd\u96e2\u30bb\u30f3 \u30b5\u3068\u76ae\u819a\u9593\u306e\u8ddd\u96e2\u3092\u4e00\u5b9a\u306b\u4fdd\u3064\u305f\u3081\uff0c\u57fa\u677f\u4e0a\u306b\u914d\u7f6e\u3057\u305f\u30d5\u30a9\u30c8 \u30ea\u30d5\u30ec\u30af\u30bf\u306e\u4e0a\u4e0b\u306b\u9ad8\u3055 5 [mm] \u306e\u30dd\u30ea\u30de\u30fc\u30b7\u30fc\u30c8\uff08PORON L-24, \u30a4\u30ce\u30a2\u30c3\u30af\uff09\u306e\u30b9\u30da\u30fc\u30b5\u3092\u8a2d\u3051\u305f\uff0e\u3053\u306e\u30bb\u30f3\u30b5\u3092\u524d\u8155\u5207 \u65ad\u7aef\u306e\u7b4b\u53ce\u7e2e\u306b\u5fdc\u3058\u3066\u76ae\u819a\u8868\u9762\u306b\u9686\u8d77\u304c\u898b\u3089\u308c\u308b\u5834\u6240\uff0c\u4f8b\u3048\u3070\uff0c \u5c3a\u5074\u624b\u6839\u5c48\u7b4b\u306e\u76f4\u4e0a\u306a\u3069\u306b\u88c5\u7740\u3059\u308b\uff0e\u30bb\u30f3\u30b5\u306f\u4f38\u7e2e\u6027\u306e\u30d0\u30f3\u30c9 \u306a\u3069\u3067\u56fa\u5b9a\u3059\u308b\u304b\uff0c\u5f8c\u8ff0\u3059\u308b\u30bd\u30b1\u30c3\u30c8\u306e\u5185\u5074\u306b\u56fa\u5b9a\u3059\u308b\uff0e\u975e\u63a5 \u89e6\u306e\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u4f7f\u7528\u3059\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u7b4b\u96fb\u30bb\u30f3\u30b5\u306e\u6b20\u70b9\u3067\u3042 \u308b\u6c57\u306b\u3088\u308b\u8aa4\u52d5\u4f5c\u306e\u554f\u984c\u304c\u306a\u304f\uff0c\u91d1\u5c5e\u96fb\u6975\u304c\u76f4\u63a5\u76ae\u819a\u306b\u89e6\u308c\u306a \u3044\u30e1\u30ea\u30c3\u30c8\u304c\u3042\u308b\uff0e\u307e\u305f\uff0c\u30d5\u30a9\u30c8\u30ea\u30d5\u30ec\u30af\u30bf\u306f\u5b89\u4fa1\u306b\u8cfc\u5165\u53ef\u80fd \u306a\u6c4e\u7528\u96fb\u5b50\u90e8\u54c1\u306e\u305f\u3081\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u5168\u4f53\u3067\u3082 300\u5186\u7a0b\u5ea6\u3067\u88fd\u4f5c \u53ef\u80fd\u3067\u3042\u308a\uff0c\u7b4b\u96fb\u30bb\u30f3\u30b5\u306b\u6bd4\u3079\u3066\u5927\u5e45\u306a\u4f4e\u30b3\u30b9\u30c8\u5316\u3092\u56f3\u308c\u308b\uff0e 2. 4 \u8ddd\u96e2\u30bb\u30f3\u30b5\u306b\u57fa\u3065\u304f\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0 \u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u57fa\u3065 \u3044\u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e\u672c\u8ad6\u6587\u3067\u8aac\nJRSJ Vol. 32 No. 5 \u201456\u2014 June, 2014" + ] + }, + { + "image_filename": "designv8_17_0004625_16_01_smdo160007.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004625_16_01_smdo160007.pdf-Figure1-1.png", + "caption": "Figure 1. Schematic presentation of tightening load in a bolted joint.", + "texts": [], + "surrounding_texts": [ + "Key words: Bolted joints, Multiple bolts, Tightening preload, Optimum tightening process.\nA bolt is composed of a screw or a stud with its nut(s). We can have a screw directly screwed in a structure or a screw going through with a nut at opposite end of the head or a stud screwed in structure with one nut at the other end or a stud going through with one nut at each end.\nVarious types of loadings can be applied to the bolted joints: direct compression or traction loads, bending moment, internal pressure, shear loading, torsion, cyclic loading, vibrations, etc.\nWe find bolted joints in almost all industries such as: air and spacecraft, automobile, railway, nuclear, wind-turbine, petro-chemistry, civil engineering, shipping industry, defense, machine tool and so. . .\nThe range of size of bolts is extremely large, from less than 2 mm to more than 500 mm.\nThe tightening load generated after the tightening operation is a tension load in the bolt and a compression load on the joint members to prevent any movement between them (Figures 1 and 2).\nIf a movement occurs between the joint members, it means that the bolted joint is failing. This is the most common cause of structural joint failure.\nThis is often due to the tightening operation not having been carried out properly.\nWhen an external traction load is applied to the assembly we have the following graph (Figures 3 and 4).\nOnly a part of the external load is applied to the bolt when the tightening load is sufficient.\nFigure 5 illustrates an external compression load being applied to the assembly.*e-mail: jeanmichelmonville@gmail.com\nThis is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.", + "However, as traction load is more common than compression load and generates higher stress levels, it is we will analyse in this document.\nThe loads on parts depend on the stiffness of each part, bolt Kb and structure Ks.\nFor the traction load on bolt we come to:\nF b \u00bc F o \u00fe F e Kb\nKb \u00fe Ks : \u00f01\u00de\nFor the residual compression load on the structure we have:\nF s \u00bc F o F e Ks\nKb \u00fe Ks : \u00f02\u00de\nMore accurately, the load on bolt and the residual compression on the structure depend on the way the external load is applied (Figure 6).", + "Two factors are defined to take this into account (see Ref. [1]). They are related to the distance x shown on the following picture.\nLoad application coefficient: c \u00bc x l . Load factor assembly:\nk \u00bc c Kb\nKb \u00fe Ks .\nLoads become:\nF b \u00bc F o \u00fe c Kb\nKb \u00fe Ks\nF e for bolt; \u00f03\u00de\nand:\nF s \u00bc F o 1 c Kb\nKb \u00fe Kp\nF e for structure: \u00f04\u00de\nIf we let x = l in the equations above we come back to the previous ones.\nGenerally, a high tightening load is good for fatigue life. As we can see, the magnitude of the alternative load on the bolt is reduced (Figure 7).\nThe stresses in the screw or stud depend on: the tightening method used, the external loads applied to the assembly and, as seen, the way these external loads are applied.\nGenerally the traction stress is the most important. The stress level is also higher right at the thread root\ndiameter.\nWithout torsional stress on the bolt, there is only traction stress (Figures 8 and 9).\nOn the average it is:\nrB \u00bc F o\nAe : \u00f05\u00de" + ] + }, + { + "image_filename": "designv8_17_0002315_cle_download_253_179-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002315_cle_download_253_179-Figure2-1.png", + "caption": "Figure 2. Bogie Structure Applied in Current Passenger Coaches [8]", + "texts": [ + " This type of train is now being developed to be able to travel distances at a better speed than before while maintaining stability, riding quality index, and ride comfort index during operation. This new train would be called a stainless-steel new generation (SS-NG) passenger coach. One of the ways for achieving this target is by designing a bogie structure for the train. Bogie is a wheel unit system in the train that is placed on the rolling stock and the passenger coaches [4]. Generally, there are three bogies which are structured under the rolling stock and two bogies under passenger coaches. The current bogie\u2019s structure applied to the stainless-steel passenger train is shown in Figure 2. This type of bogie is applied in the passenger train of SS-2018. As can be seen from the figure, the bogie is a unit where the wheelset and steel frame are connected by a suspension system. The bogie plays an important role in supporting the structure of the carriage, directing the movement of the train along the rail lines, and keeping the train from derailment, which affects the safety and comfort factors during the travel [5]. Kalivoda & Neduzha (2019) studied the safety level of the train against derailment which is one of the requirements for railroad permits in the EN 14363 standard" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001786_3-540-69389-5_68.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001786_3-540-69389-5_68.pdf-Figure5-1.png", + "caption": "Fig. 5. The h refinement of a triangular element: breaking of the element interior followed by breaking of the element edges", + "texts": [ + " Once the structure of triangular finite elements is generated, we can proceed with mesh refinements in the areas with strong singularities, where the numerical error is large. The decision about required refinements is made by knowledge driven artificial intelligence algorithm [6], [7], [8], [9], [10]. The selected finite elements can be either h, p or hp refined. The h refinement is expressed by breaking element edges and interiors. To break an element interior means to generate four new element interiors, and three new edges, as it is illustrated on middle panel in Fig. 5. To break an element edge means to generate two new edge nodes and one new vertex, as it is illustrated on right panel in Fig. 6 for all three edges of the original triangular element. These procedures are expressed by (PI12-15) productions presented in Figs. 3-4. The newly created finite elements are never stored in the data structure. They are dynamically localized at the bottom level of generated refinement trees. The following mesh regularity rules are enforced during the process of mesh transformation, see [6]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004695_oradea2018_02004.pdf-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004695_oradea2018_02004.pdf-Figure16-1.png", + "caption": "Fig. 16. The distribution of the contact pressure", + "texts": [], + "surrounding_texts": [ + "Based on the obtained results after the experimental tests and the comparative analysis of the two materials, it was found that PA66 polyamide has better characteristics in terms of friction reduction. These results show that from tribological point of view, the pair of materials analyzed have a specific behaviour different that the general know one characterized by the Stribeck curve. On the basis of the results obtained after the study, using finite elements analysis it is highlighted that for the contact between the chain links and two guide segments there were obtained small values for the contact pressure due to high mechanical characteristics of the studied polyamide. It must be mentioned that these results are in accordance with the specific literature Van, J. Ruiten, R. Proost, and M. Meuwissen [9]. Because the transmitted force from the application point to the fastening point is done only throught the contacts between components, there were no significat equivalent tensions." + ] + }, + { + "image_filename": "designv8_17_0004511_cle_download_981_416-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004511_cle_download_981_416-Figure2-1.png", + "caption": "Figure 2: Revolute clearance joint model", + "texts": [ + " The velocity and acceleration of slider and contact force in revolute clearance joint and two spherical joints were obtained by rigid-transient in ANSYS. The dimension of the model as depicted in Table 1 In revolute ideal joint center of journal and bearing is coincident, but in revolute clearance joint the center of their different. The clearance always absent in revolute joint is due to tolerance manufacture, assembly, wear which it allows motion between two body. The base and crank are connected by revolute clearance joint as depicted in Figure 2. Dynamic of this joint is due to journal impact into bearing causes collision between the journal and bearing in dry contact condition. B jc r r= \u2212 (1) where jB rr , are the radii of the bearing and the journal, and lB and dB, are the length of bearing and diameter of the bearing, respectively. \u00a9 2021 Tr\u01b0\u1eddng \u0110\u1ea1i h\u1ecdc C\u00f4ng nghi\u1ec7p th\u00e0nh ph\u1ed1 H\u1ed3 Ch\u00ed Minh Similarly, clearance is also existed in a practical spherical joint which is difference between a radius of ball and radius of socket. The model of a spherical clearance joint as outlined in Figure 3 is used to connect between crank and connecting rod, between the connecting rod and the slider. The connecting rod was set flexible, the ball is flexible, the socket is rigid. The material property of base, crank, connecting rod and slider is structural steel with Modulus of elasticity is 200 GPa, Poisson\u2019s ratio is 0.3, density is 7850 kg/m3. The model was meshed by automotive with 22749 triangle elements and 41481 nodes. The boundary condition was set up as illustrated in Figure 2 consist of fix joint, revolute clearance joint, two spherical joints with clearance, translation joint and joint load with iput velocity 300 rpm. \u00a9 2021 Tr\u01b0\u1eddng \u0110\u1ea1i h\u1ecdc C\u00f4ng nghi\u1ec7p th\u00e0nh ph\u1ed1 H\u1ed3 Ch\u00ed Minh The initial the crank lies a straight line y-axis direction with time step is 0.001s, input driven speed is 300 rpm put on in revolute clearance joint link between crank and base. In this investigation assumed that the ball rolls in socket of spherical clearance joint with 0.01 coefficient friction and journal rolls in bearing of revolute clearance joint with 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000771_1081-023-09833-9.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000771_1081-023-09833-9.pdf-Figure2-1.png", + "caption": "Fig. 2 Two-dimensional axisymmetric finite element model of the tire", + "texts": [ + " Finite Element modeling of the tire is conducted according to two main steps, as described in Korunovic et al. (2007), Ghoreishy (2006) and Yan (2003). In the first step, a two-dimensional axisymmetric finite element model of the tire is created. The geometry of the tire is digitally reconstructed from measurements on the actual tire with a FARO R\u00a9 measuring arm. Points located along the internal and external profile of the tire are sampled and used to reconstruct the actual geometry of the tire. The obtained shape is discretized by finite elements (Fig. 2). In the model, the main structural components that make up the tire (i.e. the tread, the sidewalls, the belts, the carcass ply and the beads) are included. Steel belt plies and nylon carcass ply are modelled by equally spaced rebar layers (2014). The rubber components, namely tread, undertread and sidewalls are modelled as solid sections with isotropic hyperelastic materials described by a Neo-Hooke constitutive law (Ballo et al. 2016a). Due to the lack of information on the actual compound of the tire, the Neo-Hooke coefficients are identified from experimental static stiffness tests both in radial and lateral directions", + " A comprehensive description of the experimental tests performed for the identification of the tire parameters can be found in Stabile et al. (2021a). Stiffness values obtained from both experimental tests and numerical simulations are listed in Table 1. The section of the tire is constrained at the bead seats region, where the tire is in contact with the rim. As the tire cross section was scanned with the tire off the rim, in the simulation the bead seats are laterally displaced to be exactly in the contact position. A uniform inflation pressure is applied at the inner surface as depicted in Fig. 2. In the second step, a three-dimensional (3D)model is built by a complete revolution of the deformed section of the axisymmetric model. In this second step, the ground surface is modelled as a rigid plane as shown in Fig. 3. The contact between the tire and the plane is defined by a Coulomb friction model. Vertical and lateral loads are applied by imposing a displacement of the rigid plane. The reaction forces at constrained nodes are extracted by means of a handwritten Python script. Nodes for forces extraction are highlighted in red in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003283_tation-pdf-url_13336-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003283_tation-pdf-url_13336-Figure5-1.png", + "caption": "Fig. 5. FlexPLP based on pivotable extensible parallelogram actuator module (left) and its application on a twisted Deltapod mechanism (right)", + "texts": [ + " Unfortunately, such parallelograms did not exist so far, and it was not obvious how to design them. A parallelogram that can be extended and retracted by a single motor can be made out of two cylinders with ball screws and a mechanical coupling, like gears or belts. If such a parallelogram is required to pivot around two axes, the distance between the cylinders changes and things become more complicated. Nevertheless, several solutions were developed by the authors, and the most compact one was chosen (see Fig. 5). The coupling www.intechopen.com New Trends and Developments in Automotive Industry 214 uses a sequence of bevel gears and a synchronization belt to accommodate for the parallelogram\u2019s pivoting motion (patent pending). Four universal joints provide the required degrees of freedom. www.intechopen.com FlexLean - Flexible Automation for Automotive Body Assembly 215 The result of this operation is that the machine is compacted, while the condition number remains almost identical \u2013 hence stiffness and velocity relations are not affected" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000866_f_version_1679564325-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000866_f_version_1679564325-Figure5-1.png", + "caption": "Figure 5. Compression, bending and torsion deformation of a pole with double arm in the console. Schematic representation (a) and state of deformations (b). Figure 5. Compression, bending and torsion deformation of a pole with double arm in the console. Schematic representation (a) and state of deformations (b).", + "texts": [ + "882 mm, the values amin, amed, and amax deviate by +2.51%, +8.71%, and +19.78% respectively. If only reasonable values, greater than the highest determined value, are taken from Table 7, i.e., ar-s-t \u03b5 [0.95 mm; 1.0 mm], then the corrected average value is amed-1 = 0.9633 mm, being 9.24% higher than the theoretical elastic deformation \u03b4 = 0.882 mm. 3.2.3. Deformation Study of a Pole with Double Arm in the Console Another case of loading\u2013compression, bending and torsion\u2013is exemplified by a pole with double arm in the console as in Figure 5. Geometric characteristics (square section with side s3 = 280 mm, lengths l1 = 940 mm, l2 = 500 mm, and l3 = 400 mm, areas A1 = A2 = A3 = 280 \u00d7 280 = 78,400 mm2) ensure that the body volume is 0.144 m3. Axial moments of inertia are I1 = I2 = I3 = (s3)4/12 = 512.2 \u00d7 106 mm4 and the moment of polar inertia is (Ip)2 = (s3)4/6 = 1024.43\u00d7 106 mm4. The body is loaded (compression, bending and torsion) with a force F = 250 kN evenly distributed at the end of the arm. Materials 2023, 16, x FOR PEER REVIEW 10 of 17 Using Relation (3), the values for the constant a were calculated for all \ud835\udc36 = \ud835\udc36 = 35 combinatio s of three levels of discretization, as show in Tabl 7", + "882 mm, the values amin, amed, and amax deviat by +2.51%, +8.71%, and +19.78% respectively. If only re sonable v lues, greater than the highest determi ed value, are taken from Table 7, i.e., ar-s-t \u2208 [0.95 mm; 1.0 mm], then the correct d average value is amed-1 = 0.9633 mm, eing 9.24% higher than the theoretical elastic deformation \u03b4 = 0.882 m. 3.2.3. Deformation Study of a Pole with Double Arm in the Console Another case of loading\u2013compression, bending and torsion\u2013is exemplified by a pole with double arm in the console as in Figure 5. Geometric characteristics (square section with side s3 = 280 mm, lengths l1 = 940 mm, l2 = 500 mm, and l3 = 400 mm, areas A1 = A2 = A3 = 280 \u00d7 280 = 78,400 mm2) ensure that the body volume is 0.144 m3. Axial moments of inertia are I1 = I2 = I3 = (s3)4/12 = 512.2 \u00d7 106 mm4 and the moment of polar inertia is (Ip)2 = (s3)4/6 = 1024.43 \u00d7 106 mm4. The body is loaded (compression, bending and torsion) with a force F = 250 kN evenly distributed at the end of the arm. Materials 2023, 16, 2555 11 of 16 The elastic deformation of the body was determined analytically using the Castigliano theorem [25] (p" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004033__DN06_DN06014FU1.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004033__DN06_DN06014FU1.pdf-Figure2-1.png", + "caption": "Figure 2: (a) A thin-walled cylindrical shell with a honeycomb core. (b) An equivalent thin-walled hollow cylindrical shell.", + "texts": [ + " The analysis assumes the radius and length of the cylinder, the required load capacity, and the materials of the shell and the core are given. The values of the shell thickness, the core thickness, and the core density that minimize the weight of the structure are determined. A thin-walled shell with a compliant core has an overall radius a, length L, outer shell thickness t, inner core thickness tc, and weight w. It is compared with an equivalent hollow cylinder of radius a, length L, wall thickness teq, and identical weight w in (Fig. 2). The outer shell of the cylinder with the compliant core and the hollow cylinder are made of the same isotropic material, with density \u03c1, Young\u2019s modulus E, material failure strength \u03c3f, and Poisson\u2019s ratio \u03bd. Similarly, the core has density \u03c1c, Young\u2019s modulus Ec, and Poisson\u2019s ratio \u03bdc. We limit our analysis to thin-walled shells with large radius to thickness ratios, a/t. The materials under consideration are considered to behave linearly elastically up to the material failure, which we take to be deviation from linear elasticity" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003066_9_1_08_Kodnyanko.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003066_9_1_08_Kodnyanko.pdf-Figure1-1.png", + "caption": "Fig. 1. The design scheme of the thrust bearing", + "texts": [], + "surrounding_texts": [ + "\u2013 331 \u2013\nJournal of Siberian Federal University. Engineering & Technologies, 2019, 12(3), 331-338 ~ ~ ~\n\u0423\u0414\u041a 621.9:621.89\nQuality of Dynamics of a Circular Gas-Static Thrust Bearing with an Elastic Suspended Support Center\nVladimir A. Kodnyanko and Andrei S. Kurzakov* Siberian Federal University\n79 Svobodny, Krasnoyarsk, 660041, Russia\nReceived 16.06.2017, received in revised form 25.12.2018, accepted 27.02.2019\nA design, a mathematical model are presented and a calculation technique of quality indicators of the gas-static thrust bearing dynamics with the elastic suspended support center is described. It is shown that the application of such improvement allows to eliminate completely essential shortcomings of the quality of dynamics characteristic for a bearing with annular diaphragms and transforms the construction into a dynamic system with optimal dynamic characteristics \u2013 high indicators of degree of stability, aperiodic nature of the transient process, values of the oscillation index that are peculiar to ideally damped dynamic systems.\nKeywords: gas-static bearing, thrust gas-static bearing, quality of dynamics, degree of stability, oscillation index, transient process, stability of dynamic system.\nCitation: Kodnyanko V.A., Kurzakov A.S. Quality of dynamics of a circular gas-static thrust bearing with an elastic suspended support center, J. Sib. Fed. Univ. Eng. technol., 2019, 12(3), 331-338. DOI: 10.17516/1999-494X-0140.\n\u041a\u0430\u0447\u0435\u0441\u0442\u0432\u043e \u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438 \u043a\u0440\u0443\u0433\u043e\u0432\u043e\u0433\u043e \u0433\u0430\u0437\u043e\u0441\u0442\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430 \u0441 \u043e\u043f\u043e\u0440\u043d\u044b\u043c \u0446\u0435\u043d\u0442\u0440\u043e\u043c \u043d\u0430 \u0443\u043f\u0440\u0443\u0433\u043e\u043c \u043f\u043e\u0434\u0432\u0435\u0441\u0435\n\u0412.\u0410. \u041a\u043e\u0434\u043d\u044f\u043d\u043a\u043e, \u0410.\u0421. \u041a\u0443\u0440\u0437\u0430\u043a\u043e\u0432 \u0421\u0438\u0431\u0438\u0440\u0441\u043a\u0438\u0439 \u0444\u0435\u0434\u0435\u0440\u0430\u043b\u044c\u043d\u044b\u0439 \u0443\u043d\u0438\u0432\u0435\u0440\u0441\u0438\u0442\u0435\u0442\n\u0420\u043e\u0441\u0441\u0438\u044f, 660041, \u041a\u0440\u0430\u0441\u043d\u043e\u044f\u0440\u0441\u043a, \u043f\u0440. \u0421\u0432\u043e\u0431\u043e\u0434\u043d\u044b\u0439, 79\n\u041f\u0440\u0435\u0434\u0441\u0442\u0430\u0432\u043b\u0435\u043d\u0430 \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0446\u0438\u044f, \u043f\u0440\u0438\u0432\u0435\u0434\u0435\u043d\u0430 \u043c\u0430\u0442\u0435\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0430\u044f \u043c\u043e\u0434\u0435\u043b\u044c \u0438 \u043e\u043f\u0438\u0441\u0430\u043d\u0430 \u043c\u0435\u0442\u043e\u0434\u0438\u043a\u0430 \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u043f\u043e\u043a\u0430\u0437\u0430\u0442\u0435\u043b\u0435\u0439 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0430 \u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438 \u0433\u0430\u0437\u043e\u0441\u0442\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u043e\u0433\u043e \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430 \u0441 \u043e\u043f\u043e\u0440\u043d\u044b\u043c \u0446\u0435\u043d\u0442\u0440\u043e\u043c \u043d\u0430 \u0443\u043f\u0440\u0443\u0433\u043e\u043c \u043f\u043e\u0434\u0432\u0435\u0441\u0435. \u041f\u043e\u043a\u0430\u0437\u0430\u043d\u043e, \u0447\u0442\u043e \u043f\u0440\u0438\u043c\u0435\u043d\u0435\u043d\u0438\u0435 \u044d\u0442\u043e\u0433\u043e \u0443\u0441\u043e\u0432\u0435\u0440\u0448\u0435\u043d\u0441\u0442\u0432\u043e\u0432\u0430\u043d\u0438\u044f \u043f\u043e\u0437\u0432\u043e\u043b\u044f\u0435\u0442 \u043f\u043e\u043b\u043d\u043e\u0441\u0442\u044c\u044e \u0443\u0441\u0442\u0440\u0430\u043d\u0438\u0442\u044c \u0445\u0430\u0440\u0430\u043a\u0442\u0435\u0440\u043d\u044b\u0435 \u0434\u043b\u044f \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430 \u0441 \u043a\u043e\u043b\u044c\u0446\u0435\u0432\u044b\u043c\u0438 \u0434\u0438\u0430\u0444\u0440\u0430\u0433\u043c\u0430\u043c\u0438 \u0441\u0443\u0449\u0435\u0441\u0442\u0432\u0435\u043d\u043d\u044b\u0435\n\u00a9 Siberian Federal University. All rights reserved This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License (CC BY-NC 4.0).\n* Corresponding author E-mail address: kowlad@rambler.ru", + "\u2013 332 \u2013\nVladimir A. Kodnyanko and Andrei S. Kurzakov. Quality of Dynamics of a Circular Gas-Static Thrust Bearing\u2026\n\u043d\u0435\u0434\u043e\u0441\u0442\u0430\u0442\u043a\u0438 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0430 \u0435\u0433\u043e \u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438 \u0438 \u043f\u0440\u0435\u0432\u0440\u0430\u0442\u0438\u0442\u044c \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0446\u0438\u044e \u0432 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u0443\u044e \u0441\u0438\u0441\u0442\u0435\u043c\u0443 \u0441 \u043e\u043f\u0442\u0438\u043c\u0430\u043b\u044c\u043d\u044b\u043c\u0438 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u0438\u043c\u0438 \u0445\u0430\u0440\u0430\u043a\u0442\u0435\u0440\u0438\u0441\u0442\u0438\u043a\u0430\u043c\u0438 \u2013 \u0432\u044b\u0441\u043e\u043a\u0438\u043c\u0438 \u043f\u043e\u043a\u0430\u0437\u0430\u0442\u0435\u043b\u044f\u043c\u0438 \u0441\u0442\u0435\u043f\u0435\u043d\u0438 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Kodnyanko and Andrei S. Kurzakov. 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\u0420\u0435\u0439\u043d\u043e\u043b\u044c\u0434\u0441\u0430 [2]\n( )3\n1\n\u03c3 , \u03c4\n0, ( , \u03c4) (\u03c4), ( ,0) 1,\nc cc c c\nc c d c P HPRH P R R R P P R P P R R \u2202\u23a7 \u2202\u2202 \u239b \u239e =\u23aa \u239c \u239f\u23aa\u2202 \u2202 \u2202\u239d \u23a0\u23a8 \u2202\u23aa = = =\u23aa \u2202\u23a9\n(1)\n( )3\n1\n\u03c3 , \u03c4\n( , \u03c4) (\u03c4), (1, \u03c4) 1, ( ,0) 1,\nrr r\nr d r r\nP HPRH P R R R\nP R P P P R \u23a7 \u2202\u2202\u2202 \u239b \u239e =\u23aa \u239c \u239f\u2202 \u2202 \u2202\u23a8 \u239d \u23a0 \u23aa = = =\u23a9\n(2)\n\u0433\u0434\u0435 Pc(R, \u03c4) \u0438 Pr(R, \u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u0432 \u0441\u043c\u0430\u0437\u043e\u0447\u043d\u044b\u0445 \u0437\u0430\u0437\u043e\u0440\u0430\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u0435\u0439; Hc(\u03c4) \u0438 H(\u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0442\u043e\u043b\u0449\u0438\u043d\u044b \u0437\u0430\u0437\u043e\u0440\u043e\u0432 \u0432 \u044d\u0442\u0438\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u044f\u0445; Pd(\u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u044f \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u043d\u0430 \u0432\u044b\u0445\u043e\u0434\u0435 \u043a\u043e\u043b\u044c\u0446\u0435\u0432\u044b\u0445 \u0434\u0438\u0430\u0444\u0440\u0430\u0433\u043c; R, \u03c4 \u2013 \u0440\u0430\u0434\u0438\u0443\u0441 \u0438 \u0442\u0435\u043a\u0443\u0449\u0435\u0435 \u0432\u0440\u0435\u043c\u044f.\n\u0417\u0434\u0435\u0441\u044c 2 2\n0 0 0\u03c3 12 / \u0430r p h t\u03bc= (3) \u2013 \u00ab\u0447\u0438\u0441\u043b\u043e \u0441\u0434\u0430\u0432\u043b\u0438\u0432\u0430\u043d\u0438\u044f\u00bb \u0433\u0430\u0437\u043e\u0432\u043e\u0433\u043e \u0441\u043b\u043e\u044f [3], \u0433\u0434\u0435 \u03bc \u2013 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u0430\u044f \u0432\u044f\u0437\u043a\u043e\u0441\u0442\u044c \u0433\u0430\u0437\u043e\u0432\u043e\u0439 \u0441\u043c\u0430\u0437\u043a\u0438, t0 \u2013 \u043c\u0430\u0441\u0448\u0442\u0430\u0431 \u0442\u0435\u043a\u0443\u0449\u0435\u0433\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u0438.\n(1)\n\u0430\n(2)\n\u0433\u0434\u0435 Pc(R, \u03c4) \u0438 Pr(R, \u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u0432 \u0441\u043c\u0430\u0437\u043e\u0447\u043d\u044b\u0445 \u0437\u0430\u0437\u043e\u0440\u0430\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u0435\u0439; Hc(\u03c4) \u0438 H(\u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0442\u043e\u043b\u0449\u0438\u043d\u044b \u0437\u0430\u0437\u043e\u0440\u043e\u0432 \u0432 \u044d\u0442\u0438\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u044f\u0445; Pd(\u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446 \u044f \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u043d\u0430 \u0432\u044b\u0445\u043e\u0434\u0435 \u043a\u043e\u043b\u044c\u0446\u0435\u0432\u044b\u0445 \u0434\u0438\u0430\u0444\u0440\u0430\u0433\u043c; R, \u03c4 \u2013 \u0440\u0430\u0434\u0438\u0443\u0441 \u0438 \u0442\u0435\u043a\u0443\u0449\u0435\u0435 \u0432\u0440\u0435\u043c\u044f.\n\u0417\u0434\u0435\u0441\u044c\n3\n\u043f\u043e\u0432\u0435\u0440\u0445\u043d\u043e\u0441\u0442\u0438 \u043e\u043f\u043e\u0440\u043d\u043e\u0433\u043e \u0446\u0435\u043d\u0442\u0440\u0430 5 \u043f\u0440\u043e\u0438\u0441\u0445\u043e\u0434\u0438\u0442 \u0434\u0435\u0444\u043e\u0440\u043c\u0430\u0446\u0438\u044f \u043a\u043e\u043b\u044c\u0446\u0430 4, \u0432\u0441\u043b\u0435\u0434\u0441\u0442\u0432\u0438\u0435 \u0447\u0435\u0433\u043e \u044d\u0442\u043e\u0442 \u0446\u0435\u043d\u0442\u0440 \u0441\u043c\u0435\u0449\u0430\u0435\u0442\u0441\u044f \u043d\u0430 \u0432\u0435\u043b\u0438\u0447\u0438\u043d\u0443 e \u0432 \u043d\u0430\u043f\u0440\u0430\u0432\u043b\u0435\u043d\u0438\u0438 \u0432\u0430\u043b\u0430 1. \u041f\u043e \u0441\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044e \u0441 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\u0447\u0442\u043e \u043c \u0436\u0435\u0442 \u0441\u043f\u043e\u0441\u043e\u0431 \u0442\u0432\u043e\u0432\u0430\u0442\u044c \u043f\u043e\u0432\u044b\u0448\u0435\u043d\u0438\u044e \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0430 \u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438 \u043a\u043e\u043d\u0441\u0442\u0440\u0443\u043a\u0446\u0438\u0438.\n\u0430\u0442\u0435\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u043e\u0435 \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u0435\n\u0418\u0441\u0441\u043b\u0435\u0434\u043e\u0432\u0430\u043d\u0438\u0435 \u043a\u0430\u0447\u0435\u0441\u0442\u0432\u0430 \u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438 \u0413\u041f \u043f\u0440\u043e\u0432\u0435\u0434\u0435\u043d\u043e \u0432 \u0431\u0435\u0437\u0440\u0430\u0437\u043c\u0435\u0440\u043d\u043e\u0439 \u0444\u043e\u0440\u043c\u0435. \u0420\u0430\u0437\u043c\u0435\u0440\u043d\u044b\u0435\n\u0432\u0435\u043b\u0438\u0447\u0438\u043d\u044b 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\u0441\u0438\u043b.\n\u0430\u0442\u0435\u043c\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0430\u044f \u043c\u043e\u0434\u0435\u043b\u044c \u043e\u043f\u0438\u0441\u044b\u0432\u0430\u0435\u0442 \u0434\u0432\u0438\u0436\u0435\u043d\u0438\u0435 \u0441\u0436\u0430\u0442\u043e\u0433\u043e \u0433\u0430\u0437\u0430 \u0432 \u043e\u0431\u043b\u0430\u0441\u0442\u044f\u0445 \u0441\u043c\u0430\u0437\u043e\u0447\u043d\u043e\u0433\u043e\n\u0441\u043b\u043e\u044f, \u043e\u0431\u0440\u0430\u0437\u043e\u0432\u0430\u043d\u043d\u043e\u0433\u043e \u043f\u043e\u0432\u0435\u0440\u0445\u043d\u043e\u0441\u0442\u044f\u043c\u0438 \u0432\u0430\u043b\u0430 1 \u0438 \u0446\u0435\u043d\u0442\u0440\u0430 5 (\u0446\u0435\u043d\u0442\u0440\u0430\u043b\u044c\u043d\u0430\u044f \u043e\u0431\u043b\u0430\u0441\u0442\u044c 0 \u2264 r \u2264 r1), \u043d\u0430\u0440\u0443\u0436\u043d\u043e\u0433\u043e \u043a\u043e\u043b\u044c\u0446\u0430 \u0434\u0438\u0441\u043a\u0430 3 (\u043a\u043e\u043b\u044c\u0446\u0435\u0432\u0430\u044f \u043e\u0431\u043b\u0430\u0441\u0442\u044c r1 \u2264 r \u2264 1). \u041e\u0431\u043b\u0430\u0441\u0442\u0438 \u0441\u043e\u043f\u0440\u0438\u043a\u0430\u0441\u0430\u044e\u0442\u0441\u044f \u043f\u043e \u043e\u043a\u0440\u0443\u0436\u043d\u043e\u0441\u0442\u0438 \u0440\u0430\u0434\u0438\u0443\u0441\u0430 r1, \u043d\u0430 \u043a\u043e\u0442\u043e\u0440\u043e\u0439 \u0440\u0430\u0441\u043f\u043e\u043b\u043e\u0436\u0435\u043d\u044b \u043a\u043e\u043b\u044c\u0446\u0435\u0432\u044b\u0435 \u0434\u0438\u0430\u0444\u0440\u0430\u0433\u043c\u044b.\n\u0424\u0443\u043d\u043a\u0446\u0438\u044f \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u0432 \u0441\u043c\u0430\u0437\u043e\u0447\u043d\u043e\u043c \u0441\u043b\u043e\u0435 \u044d\u0442\u0438\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u0435\u0439 \u043f\u043e\u0434\u0447\u0438\u043d\u044f\u0435\u0442\u0441\u044f \u0441\u0438\u0441\u0442\u0435\u043c\u0435 (1) \u2013 (2)\n\u043a\u0440\u0430\u0435\u0432\u044b\u0445 \u0437\u0430\u0434\u0430\u0447 \u0434\u043b\u044f \u0434\u0438\u0444\u0444\u0435\u0440\u0435\u043d\u0446\u0438\u0430\u043b\u044c\u043d\u043e\u0433\u043e \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u044f \u0420\u0435\u0439\u043d\u043e\u043b\u044c\u0434\u0441\u0430 [2]\n( )3\n1\n\u03c3 , \u03c4\n0, ( , \u03c4) (\u03c4), ( ,0) 1,\nc cc c c\nc c d c P HPRH P R R R P P R P P R R \u2202\u23a7 \u2202\u2202 \u239b \u239e =\u23aa \u239c \u239f\u23aa\u2202 \u2202 \u2202\u239d \u23a0\u23a8 \u2202\u23aa = = =\u23aa \u2202\u23a9\n(1)\n( )3\n1\n\u03c3 , \u03c4\n( , \u03c4) (\u03c4), (1, \u03c4) 1, ( ,0) 1,\nrr r\nr d r r\nP HPRH P R R R\nP R P P P R \u23a7 \u2202\u2202\u2202 \u239b \u239e =\u23aa \u239c \u239f\u2202 \u2202 \u2202\u23a8 \u239d \u23a0 \u23aa = = =\u23a9\n(2)\n\u0433\u0434\u0435 Pc(R, \u03c4) \u0438 Pr(R, \u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u0432 \u0441\u043c\u0430\u0437\u043e\u0447\u043d\u044b\u0445 \u0437\u0430\u0437\u043e\u0440\u0430\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u0435\u0439; Hc(\u03c4) \u0438 H(\u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0442\u043e\u043b\u0449\u0438\u043d\u044b \u0437\u0430\u0437\u043e\u0440\u043e\u0432 \u0432 \u044d\u0442\u0438\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u044f\u0445; Pd(\u03c4) \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u044f \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f \u043d\u0430 \u0432\u044b\u0445\u043e\u0434\u0435 \u043a\u043e\u043b\u044c\u0446\u0435\u0432\u044b\u0445 \u0434\u0438\u0430\u0444\u0440\u0430\u0433\u043c; R, \u03c4 \u2013 \u0440\u0430\u0434\u0438\u0443\u0441 \u0438 \u0442\u0435\u043a\u0443\u0449\u0435\u0435 \u0432\u0440\u0435\u043c\u044f.\n\u0417\u0434\u0435\u0441\u044c 2 2\n0 0 0\u03c3 12 / \u0430r p h t\u03bc= (3) \u2013 \u00ab\u0447\u0438\u0441\u043b\u043e \u0441\u0434\u0430\u0432\u043b\u0438\u0432\u0430\u043d\u0438\u044f\u00bb \u0433\u0430\u0437\u043e\u0432\u043e\u0433\u043e \u0441\u043b\u043e\u044f [3], \u0433\u0434\u0435 \u03bc \u2013 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u0430\u044f \u0432\u044f\u0437\u043a\u043e\u0441\u0442\u044c \u0433\u0430\u0437\u043e\u0432\u043e\u0439 \u0441\u043c\u0430\u0437\u043a\u0438, t0 \u2013 \u043c\u0430\u0441\u0448\u0442\u0430\u0431 \u0442\u0435\u043a\u0443\u0449\u0435\u0433\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u0438. (3) \u2013 \u00ab\u0447\u0438\u0441\u043b\u043e \u0441\u0434\u0430\u0432\u043b\u0438\u0432\u0430\u043d\u0438\u044f\u00bb \u0433\u0430\u0437\u043e\u0432\u043e\u0433\u043e \u0441\u043b\u043e\u044f [3], \u0433\u0434\u0435 \u03bc \u2013 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u0430\u044f \u0432\u044f\u0437\u043a\u043e\u0441\u0442\u044c \u0433\u0430\u0437\u043e\u0432\u043e\u0439 \u0441\u043c\u0430\u0437\u043a\u0438, t0 \u2013 \u043c\u0430\u0441\u0448\u0442\u0430\u0431 \u0442\u0435\u043a\u0443\u0449\u0435\u0433\u043e \u0432\u0440\u0435\u043c\u0435\u043d\u0438.\n\u0414\u043b\u044f \u043e\u043f\u0440\u0435\u0434\u0435\u043b\u0435\u043d\u0438\u044f \u043d\u0435\u0438\u0437\u0432\u0435\u0441\u0442\u043d\u043e\u0433\u043e \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f Pd(\u03c4) \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0438 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0435 \u043d\u0435\u0440\u0430\u0437\u0440\u044b\u0432\u043d\u043e\u0441\u0442\u0438 \u0441\u043c\u0430\u0437\u043e\u0447\u043d\u043e\u0433\u043e \u043f\u043e\u0442\u043e\u043a\u0430\n4\n\u0414\u043b\u044f \u043e\u043f\u0440\u0435\u0434\u0435\u043b\u0435\u043d\u0438\u044f \u043d\u0435\u0438\u0437\u0432\u0435\u0441\u0442\u043d\u043e\u0433\u043e \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f Pd(\u03c4) \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0438 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0435 \u043d\u0435\u0440\u0430\u0437\u0440\u044b\u0432\u043d\u043e\u0441\u0442\u0438\n\u0441\u043c\u0430\u0437\u043e\u0447\u043d\u043e\u0433\u043e \u043f\u043e\u0442\u043e\u043a\u0430\nQ (\u03c4) Q (\u03c4) Q (\u03c4),r c d\u2212 = (4) \u0433\u0434\u0435\n( ) 1 1\n22 3 3Q ,Q ,Q ,cr\nr c c d d H d R R R R\nPPRH RH A H P P R R\n= =\n\u2202\u2202 = \u2212 = \u2212 = \u03a8\n\u2202 \u2202 (5)\n\u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u043c\u0430\u0441\u0441\u043e\u0432\u043e\u0433\u043e \u0440\u0430\u0441\u0445\u043e\u0434\u0430 \u0433\u0430\u0437\u0430 \u043d\u0430 \u0432\u0445\u043e\u0434\u0435 \u0432 \u0437\u0430\u0437\u043e\u0440\u044b \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0443\u044e\u0449\u0438\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u0435\u0439 \u0438 \u043d\u0430 \u0432\u044b\u0445\u043e\u0434\u0435\n\u0438\u0437 \u043a\u043e\u043b\u044c\u0446\u0435\u0432\u044b\u0445 \u0434\u0438\u0430\u0444\u0440\u0430\u0433\u043c, \u0433\u0434\u0435 Ad \u2013 \u043a\u0440\u0438\u0442\u0435\u0440\u0438\u0439 \u043f\u043e\u0434\u043e\u0431\u0438\u044f \u043f\u0438\u0442\u0430\u044e\u0449\u0438\u0445 \u043e\u0442\u0432\u0435\u0440\u0441\u0442\u0438\u0439, \u03a8 \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u044f \u0438\u0441\u0442\u0435\u0447\u0435\u043d\u0438\u044f \u041f\u0440\u0430\u043d\u0434\u0442\u043b\u044f [2].\n\u0423\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0435 \u0441\u0438\u043b\u043e\u0432\u043e\u0433\u043e \u0440\u0430\u0432\u043d\u043e\u0432\u0435\u0441\u0438\u044f \u0432\u0430\u043b\u0430 1 \u043f\u0440\u0435\u0434\u0441\u0442\u0430\u0432\u043b\u044f\u043b\u0438 \u0432 \u0432\u0438\u0434\u0435\nW(\u03c4) (\u03c4) (\u03c4),inF F\u2212 = (6) \u0433\u0434\u0435 F \u2013 \u0432\u043d\u0435\u0448\u043d\u044f\u044f \u0441\u0438\u043b\u0430, W = Wr + Wc \u2013 \u043d\u0435\u0441\u0443\u0449\u0430\u044f \u0441\u043f\u043e\u0441\u043e\u0431\u043d\u043e\u0441\u0442\u044c \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430,\n( ) ( ) 1\n1\n1 2\n2 0\n(\u03c4)(\u03c4) 2 1 , (\u03c4) 2 1 , (\u03c4) \u03c4\nR\nr r c c in R\nd HW R P dR W R P dR F M d = \u2212 = \u2212 =\u222b \u222b (7)\n\u2013 \u0441\u043e\u0441\u0442\u0430\u0432\u043b\u044f\u044e\u0449\u0438\u0435 \u043d\u0435\u0441\u0443\u0449\u0435\u0439 \u0441\u043f\u043e\u0441\u043e\u0431\u043d\u043e\u0441\u0442\u0438 \u043f\u043e \u043e\u0431\u043b\u0430\u0441\u0442\u044f\u043c \u0437\u0430\u0437\u043e\u0440\u0430 \u0438 \u0441\u0438\u043b\u0430 \u0438\u043d\u0435\u0440\u0446\u0438\u0438 \u0432\u0430\u043b\u0430 1, M \u2013 \u0435\u0433\u043e \u043c\u0430\u0441\u0441\u0430.\n\u0421\u043c\u0435\u0449\u0435\u043d\u0438\u0435 \u03b5(\u03c4) \u0446\u0435\u043d\u0442\u0440\u0430 5 \u0438 \u0444\u0443\u043d\u043a\u0446\u0438\u044e \u0437\u0430\u0437\u043e\u0440\u0430 Hc(\u03c4) \u043d\u0430\u0445\u043e\u0434\u0438\u043b\u0438 \u043f\u043e \u0444\u043e\u0440\u043c\u0443\u043b\u0430\u043c\n( ) ( )2 1 1 , \u03b5 , \u03b5,H H m H c cW R P K W W H H= \u2212 = \u2212 = \u2212 (8)\n\u0433\u0434\u0435 Km \u2013 \u043f\u043e\u0434\u0430\u0442\u043b\u0438\u0432\u043e\u0441\u0442\u044c \u0443\u043f\u0440\u0443\u0433\u043e\u0433\u043e \u043a\u043e\u043b\u044c\u0446\u0430 4.\n\u0418\u0441\u0441\u043b\u0435\u0434\u043e\u0432\u0430\u043d\u0438\u0435 \u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438 \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430 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\u043e\u043f\u043e\u0440 (\u0441\u0440\u0435\u0434\u044b \u0421\u0418\u0413\u041e) [4] \u043c\u0435\u0442\u043e\u0434\u0430\u043c\u0438 \u0442\u0435\u043e\u0440\u0438\u0438 \u043b\u0438\u043d\u0435\u0439\u043d\u044b\u0445 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u0438\u0445 \u0441\u0438\u0441\u0442\u0435\u043c [6, 7]. \u0420\u0435\u0448\u0435\u043d\u0438\u0435 \u043a\u0440\u0430\u0435\u0432\u044b\u0445 \u0437\u0430\u0434\u0430\u0447 (1), (2) \u0434\u043b\u044f \u043b\u0438\u043d\u0435\u0430\u0440\u0438\u0437\u043e\u0432\u0430\u043d\u043d\u044b\u0445 \u0438 \u043f\u0440\u0435\u043e\u0431\u0440\u0430\u0437\u043e\u0432\u0430\u043d\u043d\u044b\u0445 \u043f\u043e \u041b\u0430\u043f\u043b\u0430\u0441\u0443 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0439 \u0420\u0435\u0439\u043d\u043e\u043b\u044c\u0434\u0441\u0430 \u043f\u043e\u043b\u0443\u0447\u0435\u043d\u043e \u0447\u0438\u0441\u043b\u0435\u043d\u043d\u044b\u043c \u043c\u0435\u0442\u043e\u0434\u043e\u043c [5], 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\u0443\u0441\u0442\u043e\u0439\u0447\u0438\u0432\u043e\u0441\u0442\u0438 \u0438 \u0431\u044b\u0441\u0442\u0440\u043e\u0434\u0435\u0439\u0441\u0442\u0432\u0438\u044f \u0413\u041f \u043a\u0430\u043a \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u043e\u0439\n\u0441\u0438\u0441\u0442\u0435\u043c\u044b \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0438 \u0441\u0442\u0435\u043f\u0435\u043d\u044c \u0443\u0441\u0442\u043e\u0439\u0447\u0438\u0432\u043e\u0441\u0442\u0438 \u03b7 [6]. \u0417\u0430\u043f\u0430\u0441 \u0443\u0441\u0442\u043e\u0439\u0447\u0438\u0432\u043e\u0441\u0442\u0438 \u0413\u041f \u043e\u0446\u0435\u043d\u0438\u0432\u0430\u043b\u0438 \u043f\u0440\u0438 \u043f\u043e\u043c\u043e\u0449\u0438 \u043f\u043e\u043a\u0430\u0437\u0430\u0442\u0435\u043b\u044f \u043a\u043e\u043b\u0435\u0431\u0430\u0442\u0435\u043b\u044c\u043d\u043e\u0441\u0442\u0438 \u041f [7] \u0430\u043c\u043f\u043b\u0438\u0442\u0443\u0434\u043d\u043e-\u0447\u0430\u0441\u0442\u043e\u0442\u043d\u043e\u0439 \u0445\u0430\u0440\u0430\u043a\u0442\u0435\u0440\u0438\u0441\u0442\u0438\u043a\u0438\n\u043f\u0435\u0440\u0435\u0434\u0430\u0442\u043e\u0447\u043d\u043e\u0439 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u043e\u0439 \u043f\u043e\u0434\u0430\u0442\u043b\u0438\u0432\u043e\u0441\u0442\u0438 \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430 ( ) ( ) / ( )K s H s F s= \u0394 \u0394 , \u0433\u0434\u0435\n,H F\u0394 \u0394 \u2013 \u043b\u0430\u043f\u043b\u0430\u0441\u043e\u0432\u044b \u0442\u0440\u0430\u043d\u0441\u0444\u043e\u0440\u043c\u0430\u043d\u0442\u044b \u043c\u0430\u043b\u044b\u0445 \u043e\u0442\u043a\u043b\u043e\u043d\u0435\u043d\u0438\u0439 \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0443\u044e\u0449\u0438\u0445 \u0444\u0443\u043d\u043a\u0446\u0438\u0439 \u043e\u0442 \u0438\u0445\n\u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u044b\u0445 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u0439, s \u2013 \u043f\u0435\u0440\u0435\u043c\u0435\u043d\u043d\u0430\u044f \u043f\u0440\u0435\u043e\u0431\u0440\u0430\u0437\u043e\u0432\u0430\u043d\u0438\u044f \u041b\u0430\u043f\u043b\u0430\u0441\u0430 [6, 7].\n(4)\n\u0433\u0434\u0435\n4\n\u0414\u043b\u044f \u043e\u043f\u0440\u0435\u0434\u0435\u043b\u0435\u043d\u0438\u044f \u043d\u0435\u0438\u0437\u0432\u0435\u0441\u0442\u043d\u043e\u0433\u043e \u0434\u0430\u0432\u043b\u0435\u043d\u0438\u044f Pd(\u03c4) \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0438 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0435 \u043d\u0435\u0440\u0430\u0437\u0440\u044b\u0432\u043d\u043e\u0441\u0442\u0438\n\u0441\u043c\u0430\u0437\u043e\u0447\u043d\u043e\u0433\u043e \u043f\u043e\u0442\u043e\u043a\u0430\nQ (\u03c4) Q (\u03c4) Q (\u03c4),r c d\u2212 = (4) \u0433\u0434\u0435\n( ) 1 1\n22 3 3Q ,Q ,Q ,cr\nr c c d d H d R R R R\nPPRH RH A H P P R R\n= =\n\u2202\u2202 = \u2212 = \u2212 = \u03a8\n\u2202 \u2202 (5)\n\u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u043c\u0430\u0441\u0441\u043e\u0432\u043e\u0433\u043e \u0440\u0430\u0441\u0445\u043e\u0434\u0430 \u0433\u0430\u0437\u0430 \u043d\u0430 \u0432\u0445\u043e\u0434\u0435 \u0432 \u0437\u0430\u0437\u043e\u0440\u044b \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0443\u044e\u0449\u0438\u0445 \u043e\u0431\u043b\u0430\u0441\u0442\u0435\u0439 \u0438 \u043d\u0430 \u0432\u044b\u0445\u043e\u0434\u0435\n\u0438\u0437 \u043a\u043e\u043b\u044c\u0446\u0435\u0432\u044b\u0445 \u0434\u0438\u0430\u0444\u0440\u0430\u0433\u043c, \u0433\u0434\u0435 Ad \u2013 \u043a\u0440\u0438\u0442\u0435\u0440\u0438\u0439 \u043f\u043e\u0434\u043e\u0431\u0438\u044f \u043f\u0438\u0442\u0430\u044e\u0449\u0438\u0445 \u043e\u0442\u0432\u0435\u0440\u0441\u0442\u0438\u0439, \u03a8 \u2013 \u0444\u0443\u043d\u043a\u0446\u0438\u044f \u0438\u0441\u0442\u0435\u0447\u0435\u043d\u0438\u044f \u041f\u0440\u0430\u043d\u0434\u0442\u043b\u044f [2].\n\u0423\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0435 \u0441\u0438\u043b\u043e\u0432\u043e\u0433\u043e \u0440\u0430\u0432\u043d\u043e\u0432\u0435\u0441\u0438\u044f \u0432\u0430\u043b\u0430 1 \u043f\u0440\u0435\u0434\u0441\u0442\u0430\u0432\u043b\u044f\u043b\u0438 \u0432 \u0432\u0438\u0434\u0435\nW(\u03c4) (\u03c4) (\u03c4),inF F\u2212 = (6) \u0433\u0434\u0435 F \u2013 \u0432\u043d\u0435\u0448\u043d\u044f\u044f \u0441\u0438\u043b\u0430, W = Wr + Wc \u2013 \u043d\u0435\u0441\u0443\u0449\u0430\u044f \u0441\u043f\u043e\u0441\u043e\u0431\u043d\u043e\u0441\u0442\u044c \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430,\n( ) ( ) 1\n1\n1 2\n2 0\n(\u03c4)(\u03c4) 2 1 , (\u03c4) 2 1 , (\u03c4) \u03c4\nR\nr r c c in R\nd HW R P dR W R P dR F M d = \u2212 = \u2212 =\u222b \u222b (7)\n\u2013 \u0441\u043e\u0441\u0442\u0430\u0432\u043b\u044f\u044e\u0449\u0438\u0435 \u043d\u0435\u0441\u0443\u0449\u0435\u0439 \u0441\u043f\u043e\u0441\u043e\u0431\u043d\u043e\u0441\u0442\u0438 \u043f\u043e \u043e\u0431\u043b\u0430\u0441\u0442\u044f\u043c \u0437\u0430\u0437\u043e\u0440\u0430 \u0438 \u0441\u0438\u043b\u0430 \u0438\u043d\u0435\u0440\u0446\u0438\u0438 \u0432\u0430\u043b\u0430 1, M \u2013 \u0435\u0433\u043e \u043c\u0430\u0441\u0441\u0430.\n\u0421\u043c\u0435\u0449\u0435\u043d\u0438\u0435 \u03b5(\u03c4) \u0446\u0435\u043d\u0442\u0440\u0430 5 \u0438 \u0444\u0443\u043d\u043a\u0446\u0438\u044e \u0437\u0430\u0437\u043e\u0440\u0430 Hc(\u03c4) \u043d\u0430\u0445\u043e\u0434\u0438\u043b\u0438 \u043f\u043e \u0444\u043e\u0440\u043c\u0443\u043b\u0430\u043c\n( ) ( )2 1 1 , \u03b5 , \u03b5,H H m H c cW R P K W W H H= \u2212 = \u2212 = \u2212 (8)\n\u0433\u0434\u0435 Km \u2013 \u043f\u043e\u0434\u0430\u0442\u043b\u0438\u0432\u043e\u0441\u0442\u044c \u0443\u043f\u0440\u0443\u0433\u043e\u0433\u043e \u043a\u043e\u043b\u044c\u0446\u0430 4.\n\u0418\u0441\u0441\u043b\u0435\u0434\u043e\u0432\u0430\u043d\u0438\u0435 \u0434\u0438\u043d\u0430\u043c\u0438\u043a\u0438 \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430 \u043f\u0440\u043e\u0432\u043e\u0434\u0438\u043b\u043e\u0441\u044c \u0434\u043b\u044f \u043c\u0430\u043b\u044b\u0445 \u043a\u043e\u043b\u0435\u0431\u0430\u043d\u0438\u0439 \u0432\u0430\u043b\u0430 1 \u0432\n\u043e\u043a\u0440\u0435\u0441\u0442\u043d\u043e\u0441\u0442\u0438 \u0443\u043f\u043e\u043c\u044f\u043d\u0443\u0442\u043e\u0439 \u00ab\u0440\u0430\u0441\u0447\u0435\u0442\u043d\u043e\u0439 \u0442\u043e\u0447\u043a\u0438\u00bb \u043f\u0440\u0438 \u043f\u043e\u043c\u043e\u0449\u0438 \u0441\u043f\u0435\u0446\u0438\u0430\u043b\u0438\u0437\u0438\u0440\u043e\u0432\u0430\u043d\u043d\u043e\u0439 \u043a\u043e\u043c\u043f\u044c\u044e\u0442\u0435\u0440\u043d\u043e\u0439 \u0441\u0440\u0435\u0434\u044b \u043c\u043e\u0434\u0435\u043b\u0438\u0440\u043e\u0432\u0430\u043d\u0438\u044f, \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u0438 \u0438\u0441\u0441\u043b\u0435\u0434\u043e\u0432\u0430\u043d\u0438\u044f \u0433\u0430\u0437\u043e\u0441\u0442\u0430\u0442\u0438\u0447\u0435\u0441\u043a\u0438\u0445 \u043e\u043f\u043e\u0440 (\u0441\u0440\u0435\u0434\u044b \u0421\u0418\u0413\u041e) [4] \u043c\u0435\u0442\u043e\u0434\u0430\u043c\u0438 \u0442\u0435\u043e\u0440\u0438\u0438 \u043b\u0438\u043d\u0435\u0439\u043d\u044b\u0445 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u0438\u0445 \u0441\u0438\u0441\u0442\u0435\u043c [6, 7]. \u0420\u0435\u0448\u0435\u043d\u0438\u0435 \u043a\u0440\u0430\u0435\u0432\u044b\u0445 \u0437\u0430\u0434\u0430\u0447 (1), (2) \u0434\u043b\u044f \u043b\u0438\u043d\u0435\u0430\u0440\u0438\u0437\u043e\u0432\u0430\u043d\u043d\u044b\u0445 \u0438 \u043f\u0440\u0435\u043e\u0431\u0440\u0430\u0437\u043e\u0432\u0430\u043d\u043d\u044b\u0445 \u043f\u043e \u041b\u0430\u043f\u043b\u0430\u0441\u0443 \u0443\u0440\u0430\u0432\u043d\u0435\u043d\u0438\u0439 \u0420\u0435\u0439\u043d\u043e\u043b\u044c\u0434\u0441\u0430 \u043f\u043e\u043b\u0443\u0447\u0435\u043d\u043e \u0447\u0438\u0441\u043b\u0435\u043d\u043d\u044b\u043c \u043c\u0435\u0442\u043e\u0434\u043e\u043c [5], \u0433\u0430\u0440\u0430\u043d\u0442\u0438\u0440\u0443\u044e\u0449\u0438\u043c \u0437\u0430\u0434\u0430\u043d\u043d\u0443\u044e \u0442\u043e\u0447\u043d\u043e\u0441\u0442\u044c \u0440\u0430\u0441\u0447\u0435\u0442\u0430 \u043a\u043e\u043c\u043f\u043b\u0435\u043a\u0441\u043d\u044b\u0445 \u043a\u043e\u044d\u0444\u0444\u0438\u0446\u0438\u0435\u043d\u0442\u043e\u0432 \u043f\u0440\u0438 \u0438\u043d\u0442\u0435\u0433\u0440\u043e \u0434\u0438\u0444\u0444\u0435\u0440\u0435\u043d\u0446\u0438\u0430\u043b\u044c\u043d\u044b\u0445 \u0438\u0437\u043e\u0431\u0440\u0430\u0436\u0435\u043d\u0438\u044f\u0445 \u043e\u0431\u043e\u0431\u0449\u0435\u043d\u043d\u044b\u0445 \u043a\u043e\u043e\u0440\u0434\u0438\u043d\u0430\u0442 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u043e\u0439 \u043c\u043e\u0434\u0435\u043b\u0438 (1) \u2013 (8).\n\u0414\u043b\u044f \u043a\u043e\u043b\u0438\u0447\u0435\u0441\u0442\u0432\u0435\u043d\u043d\u043e\u0439 \u043e\u0446\u0435\u043d\u043a\u0438 \u0443\u0441\u0442\u043e\u0439\u0447\u0438\u0432\u043e\u0441\u0442\u0438 \u0438 \u0431\u044b\u0441\u0442\u0440\u043e\u0434\u0435\u0439\u0441\u0442\u0432\u0438\u044f \u0413\u041f \u043a\u0430\u043a \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u043e\u0439\n\u0441\u0438\u0441\u0442\u0435\u043c\u044b \u0438\u0441\u043f\u043e\u043b\u044c\u0437\u043e\u0432\u0430\u043b\u0438 \u0441\u0442\u0435\u043f\u0435\u043d\u044c \u0443\u0441\u0442\u043e\u0439\u0447\u0438\u0432\u043e\u0441\u0442\u0438 \u03b7 [6]. \u0417\u0430\u043f\u0430\u0441 \u0443\u0441\u0442\u043e\u0439\u0447\u0438\u0432\u043e\u0441\u0442\u0438 \u0413\u041f \u043e\u0446\u0435\u043d\u0438\u0432\u0430\u043b\u0438 \u043f\u0440\u0438 \u043f\u043e\u043c\u043e\u0449\u0438 \u043f\u043e\u043a\u0430\u0437\u0430\u0442\u0435\u043b\u044f \u043a\u043e\u043b\u0435\u0431\u0430\u0442\u0435\u043b\u044c\u043d\u043e\u0441\u0442\u0438 \u041f [7] \u0430\u043c\u043f\u043b\u0438\u0442\u0443\u0434\u043d\u043e-\u0447\u0430\u0441\u0442\u043e\u0442\u043d\u043e\u0439 \u0445\u0430\u0440\u0430\u043a\u0442\u0435\u0440\u0438\u0441\u0442\u0438\u043a\u0438\n\u043f\u0435\u0440\u0435\u0434\u0430\u0442\u043e\u0447\u043d\u043e\u0439 \u0444\u0443\u043d\u043a\u0446\u0438\u0438 \u0434\u0438\u043d\u0430\u043c\u0438\u0447\u0435\u0441\u043a\u043e\u0439 \u043f\u043e\u0434\u0430\u0442\u043b\u0438\u0432\u043e\u0441\u0442\u0438 \u043f\u043e\u0434\u043f\u044f\u0442\u043d\u0438\u043a\u0430 ( ) ( ) / ( )K s H s F s= \u0394 \u0394 , \u0433\u0434\u0435\n,H F\u0394 \u0394 \u2013 \u043b\u0430\u043f\u043b\u0430\u0441\u043e\u0432\u044b \u0442\u0440\u0430\u043d\u0441\u0444\u043e\u0440\u043c\u0430\u043d\u0442\u044b \u043c\u0430\u043b\u044b\u0445 \u043e\u0442\u043a\u043b\u043e\u043d\u0435\u043d\u0438\u0439 \u0441\u043e\u043e\u0442\u0432\u0435\u0442\u0441\u0442\u0432\u0443\u044e\u0449\u0438\u0445 \u0444\u0443\u043d\u043a\u0446\u0438\u0439 \u043e\u0442 \u0438\u0445\n\u0441\u0442\u0430\u0446\u0438\u043e\u043d\u0430\u0440\u043d\u044b\u0445 \u0437\u043d\u0430\u0447\u0435\u043d\u0438\u0439, s \u2013 \u043f\u0435\u0440\u0435\u043c\u0435\u043d\u043d\u0430\u044f \u043f\u0440\u0435\u043e\u0431\u0440\u0430\u0437\u043e\u0432\u0430\u043d\u0438\u044f \u041b\u0430\u043f\u043b\u0430\u0441\u0430 [6, 7].\n(5)" + ] + }, + { + "image_filename": "designv8_17_0003971__2462_context_theses-Figure5-6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003971__2462_context_theses-Figure5-6-1.png", + "caption": "Figure 5-6: Deformed tooth during simulation", + "texts": [ + "Adams Multi body dynamic (MBD) simulation is a system that consists of solid bodies that are connected to each other by joints. The bodies can interact with each other due to force/contact connections. It is a study of the influence of forces, like contact forces, gravity or other forces, that makes it possible to analyze the systems mechanism as motion and behavior. The MBD simulation was performed with MSC.Adams, Figure 5-4 shows the user interface. 45 Figure 5-5 shows a mode of the flexible body in MSC.Adams and Figure 5-6 shows the deformation of a crocked tooth during a contact. 46 To simulate the behavior of flexible bodies, all flexible parts need to have a finite element model structure. Due to this structure the DOF which are infinite becomes finite. However, due to more than ten thousands of nodes, the number of DOF is still very large. Each part has its own local reference frame (coordinate system) that is defined by a position vector to the global reference frame. ADMAS FLEX_BODY\u2019s considers only small, linear body deformations at the local reference frame of the flexible body" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000319_gs_2024dubai_338.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000319_gs_2024dubai_338.pdf-Figure2-1.png", + "caption": "Figure 2: The mechanical construction of a previous ball and plate system", + "texts": [ + " The system used a resistive touch screen in order to get the position feedback of the ball and a dedicated touch screen controller to convert the analog values that resulted from the touch screen to digital values which can be used by the PC. The touch screen controller conveys the ball coordinates to the PC through RS-232 cable instead of USB due to its simple protocol. Then the coordinates of the ball are sent to LabVIEW development environment in order to control the servo motors (the actuators). A controller is implemented in the LabVIEW by generating a PWM (Pulse Width Modulation) signal with the help of PID controller. Figure 2 shows the construction of the system (Appleton, B, Rijal, R. et al. 2017). (S. Awtar et.al., 2002) System 2 This system was done by the engineering Faculty of Kocaeli University. The system used the fuzzy logic to control and stabilize the system. In this system a digital camera is used as a sensor. A picture of the platform is captured by the camera and then processed using image processing in MATLAB/Simulink environment in order to obtain the ball\u2019s x and y coordinates. When the coordinates are determined, fuzzy logic is implemented also by MATLAB/Simulink to generate the control output" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000853_9668973_09718336.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000853_9668973_09718336.pdf-Figure1-1.png", + "caption": "FIGURE 1. Configuration of the robotic system used for brain stimulation.", + "texts": [ + " Finally, the discussion and conclusion are presented in section V and VI, respectively. II. LEAD-SCREW-DRIVEN REVOLUTE JOINT A. DESIGN CONSIDERATION Our target application of the proposed revolute joint is a robotic system intended to be used for noninvasive brain stimulation (NIBS). Given that the robotic system for NIBS has many advantages, several systems have been developed [16], [17]. Our robotic system consists of a 2-DOFs RCM mechanism, a 6-DOFs Stewart platform, and a low-intensity focused ultrasound (FUS) transducer as shown in Fig. 1. Using the Stewart platform, high precision and speed can be ensured. In addition, the small workspace of the Stewart 24040 VOLUME 10, 2022 platform was supplemented by applying the RCM mechanism. Through the proposed robot configuration, the required precision and workspace for NIBS can be achieved. However, in the RCM-mechanism-based robotic system (see Fig. 1), the load on the revolute joint is very high. Given that the revolute joint rotates the heavy and long arc mechanism with the Stewart platform and FUS transducer, it should have a high resolution and high-torque efficiency. In addition, without imposed restrictions on the rotation range, it is possible that the patient and the arc link may collide. To overcome these challenges and apply the mechanism to the brain stimulation robot, we designed a new type of the revolute joint. B. MECHANICAL DESIGN The concept design of the proposed revolute joint is described in Fig", + " The repeatability was similar in all ranges and averaged approximately 1.43 \u00b5m. In addition, we evaluated the repeatability performance based on the coefficient of variation (CV) [18]. The CV of the proposed revolute joint varied from 0.022 % to 0.002 % and was obtained by dividing the standard deviation and the mean distance. D. FEASIBILITY TEST To verify the feasibility of the proposed revolute joint, we applied the mechanism to the robotic system for brain stimulation. The configuration of the robotic system was the same as that described in Fig. 1. The arc guide had a radius of 300 mm and a weight of approximately 10 kg, including the end effector. Using the proposed mechanism, a rotation test was performed from \u221260\u25e6 to 60\u25e6 as shown in Fig. 12. According to the test, it was confirmed that the proposed revolute joint can rotate the long arc part with a low-performance motor in a stable manner. The motor generates a continuous torque of 3 Nm, which is smaller than the required motor VOLUME 10, 2022 24045 torque for the arc rotation. It was also confirmed that the angle of the arc part could be maintained at any angle through the electromagnetic brake with the use of a stop torque of only 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004154_radschool_disstheses-Figure4-30-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004154_radschool_disstheses-Figure4-30-1.png", + "caption": "Figure 4-30: Trajectory in joint configuration space from [0.0, -1 .0 , \u20141.0] to [0.0,1.0,1.0] w ith constant torque bounds.", + "texts": [], + "surrounding_texts": [ + "155\no.cn\nO.IOO'\n\u2014,\u2014 -1 4 0 0 \u2014\u201c1---------1 1 \u2019 ,_ \u2022 j .200 -o .w o -o .io o o ^ x n 0.100\na. S traight line tra jectory\nM -\n-0 .100--o .iao -0.100-\n\u20220.100 0 1.200\n\u20220 .100- \u20220.100 0\n\u2022 o .n o -\n-0\u00bbJ\nb. M inimum time trajectory\nFigure 4-29: Trajectory in Cartesian space from [0.0, \u20141.0, \u20141.0] to [0.0,1.0,1.0] w ith constant torque bounds.", + "156\nM inimum tim e tra jectory $2 .vs. 0! (\u2014 ) 03 .VS. 0! (...) Straight line tra jectory ( - -)", + "157\nLEGEND Straight line trajectory (\u2014 ) Minimum time trajectory (\u2014 )" + ] + }, + { + "image_filename": "designv8_17_0001895_f_version_1680326135-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001895_f_version_1680326135-Figure22-1.png", + "caption": "Figure 22. Torque waveform of the final DRAFPM motor and magnetic flux density distribution at load.", + "texts": [ + " Therefore, considering that the design objective of the no-load BEMF is maximization, the 24 pole 18 slot 12 turns model was selected as the final model. The design variable optimization results of the final selected 24 pole 18 slot 12 turn model are shown in Table 6. Figure 21 shows the final design shape of the DRAFPM motor compared to the target RFPM motor. Compared to the target RFPM motor, the no-load BEMF increased by 20.19%, and the THD decreased by 69.69%. At load, torque was increased by 21.92%. Figure 22 shows the torque waveform of the final DRPMSM motor and the magnetic flux density at load. Table 6. Final Model Design Variable of Optimization Results. DV1 DV2 DV3 DV4 DV5 DV6 DV7 DV8 N_turns T_Rotor_BY T_mag T_shoe T_teeth T_winding G_mag G_shoe 12 [mm] 1.93 [mm] 1.49 [mm] 1.28 [mm] 17.40 [mm] 3.29 [mm] 1.00 [mm] 1.55 [mm] Figure 21. Shape of final DRAFPM motor and target RFPM motor model. Amid the rapid progress of the robot market, interest in cooperative robots that can collaborate with humans is increasing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure12-1.png", + "caption": "Fig. 12 Distribution of stress (a) Antero-lateral (b) Postero-lateral; (c) Maximum stress at critical areas under cyclic load condition II", + "texts": [], + "surrounding_texts": [ + "The distribution of von-Mises stress, maximum deflection, number of cycles before failure, and safety factor of the modified polycentric prosthetic knee are investigated in this fatigue analysis. The results of von-Mises stress distribution during cyclic strength simulation are shown in Figs. 11 and 12. For both loading conditions, the von-Mises stress developed at the front and back joint bars is 18 to 23 MPa as shown in Figs. 11a, 11b, 12a, and 12b. The maximum stresses of 91 and 71 MPa are developed in the knee joint unit lower for load conditions I and II respectively as depicted in Figs. 11c and 12c. Therefore, it can be predicted that the modified polycentric prosthetic knee prosthesis employed in this research can withstand cyclic stress considering the high fatigue strength of AA7075-T6. The cyclic strength test results for the modified knee prosthesis are shown in terms of total deformation in Fig. 13. A maximum deformation has been observed at the point of load application which is 0.38 mm as shown in Fig. 13a. The alignment coupling unit of the knee prosthesis experiences the maximum deformation of 0.18 mm as depicted in Figs. 13b and 13c, suggesting the least amount of displacement. A deformation less than 2.5 mm during fatigue testing suggests that this modified prosthetic knee has sufficient strain-bearing ability to meet the structural norms, as recommended by the ISO 10328:2016 standard. The results of cyclic strength simulations for commonly failing components are summarized in Table 4. It is observed that the maximum developed stress is sufficiently below the fatigue strength of AA7075 T6 and the deformation produced is extremely minimal. There is a significant increase in fatigue life (no. of cycles) of most of the knee components. These values indicate that the modified polycentric knee prosthesis qualifies the requirements of ISO 10328:2016 standard." + ] + }, + { + "image_filename": "designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000950_06_1_JiangShan08.pdf-Figure4.11-1.png", + "caption": "Figure 4.11: Transfer curve of 1.5-bit stage with gain error.", + "texts": [ + " Based on the charge conservation, Q1 == -Q2' the transfer function of the op amp gain can be expressed as: 1 Gs + GF Gs Vout == 1 (Yin\u00b7 C - Di . ~ef . -C ) 1 + Ao.(3 F F where {3 == GF / ( GF +CS +Gin) is the feedback factor in the holding mode. If A o. {3 >> 1, the transfer function can be written as: 1 Gs + GF Gs Vout == (1 - A o . (3)(Yin . C F - Di . ~ef . CF) (4.10) Therefore, the finite op amp DC gain introduces an error equal to 1/(Ao . (3) which lowers the residue amplifier gain. The transfer function of the 1.S-bit stage with gain error is shown by the dash-line in Figure 4.11. This gain error depends on the input and reaches its maximum when the output voltage reaches its maximum value. To prevent the gain error flowing to the following stage, the error 1/(Ao . (3) must be less than half the LSB of following stages, thus the stages in the front must have higher op amp DC gain requirements. In a pipelined ADC, the op amp of first stage requires the highest DC gain. For an N-bit pipelined ADC, if the first stage is 1.S-bit stage, its following stages have a resolution of N - 1, therefore gain error requirement is 1 1 --<-- Ao " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003835_f_version_1676453559-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003835_f_version_1676453559-Figure2-1.png", + "caption": "Figure 2. STRATOFLY MR3 propulsive flow path.", + "texts": [ + " The integration of the propulsive system at the top of the vehicle allows for maximizing the available planform area for lift generation without additional drag penalties, thus increasing the aerodynamic efficiency (up to a maximum value in a cruise of about 7), and it allows for optimizing the internal volume. Specifically, STRATOFLY MR3 integrates six air turbo rocket engines, ATR, that operate up to Mach 4\u20134.5 (available thrust at sea level 233 kN for each engine), and one dual-mode ramjet, DMR, that is used for hypersonic flight from Mach 4.5 up to Mach 8 (available thrust 664 kN in cruise). The powerplant flow path is shown in Figure 2 for what concerns the complete ATR-DMR arrangements. As can be seen, the high-speed flow path feeding the DMR (red) is the main duct of the powerplant, allowing the flow to pass through the overall vehicle from the intake (gray) to the final common nozzle (blue). ATR ducts are instead grouped in two assemblies (green) on both sides of the main DMR duct (three engines per side). These are fed by opening a portion of the intake up to Mach 4\u20134.5, whose gap can be modulated depending on the flow field" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004385_aper_ETC2017-356.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004385_aper_ETC2017-356.pdf-Figure3-1.png", + "caption": "Figure 3: The Reference nozzle configuration (top) and the NEWAC configuration (bottom)", + "texts": [ + " CONFIGURATIONS The need for developing an efficient heat recuperation configuration, with particular interest in the IRA-engine, has been in the focal point of European research in the last two decades in the framework of major European research projects such as: Component Validator for Environmentallyfriendly Aero-Engine/CLEAN, Advanced exhaust gas recuperator technology for aero-engine applications/AEROHEX, NEW Aero engine Core concepts/NEWAC and Low Emissions CoreEngine Technologies/LEMCOTEC. These research activities were performed through a combination of detailed experimental measurements and CFD computations. In these investigations the HEX porosity model concept was developed and implemented for the incorporation of the HEX major pressure loss and heat transfer characteristics in the CFD computations. These research studies started with detailed investigations of an initial (Reference) recuperative nozzle configuration, presented in Fig.3 (left), being always based on the MTU tubular HEX. At this initial design the HEXs were placed in a 0o (HEX 1)/20o (HEX 2)/20o (HEX 3)/0o (HEX 4) orientation in relation to the incoming flow of the exhaust gas. The referenced angles correspond to the angles between the hot-gas (red arrow) and each HEX. Further investigations of the Reference configuration with the use of 3D CFD computations supported also by experimental validation, revealed significantly increased pressure losses, originating mainly from a noticeable flow maldistribution inside the hot-gas exhaust nozzle installation. Optimization actions were initiated which resulted in the NEWAC nozzle installation, presented in Fig.3 (right), including modifications in the orientation of the HEXs installation from the reference nozzle geometry orientation to 17o (HEX 1)/20o (HEX 2)/13o (HEX 3)/17o (HEX 4), redesign of the aerodynamic cone and the nozzle walls and optimization of the supporting covers of the bow region of the HEXs to smooth the flow velocity and avoid the creation of local maxima inside the heat exchangers. The referenced angles correspond to the angles between the hot-gas (red arrow) and each HEX. These modifications, which were performed through CFD computations and experimental measurements, resulted in a more than 10% reduction of the outer pressure losses (the inner losses remained unaffected since the same basic HEX was used) which led to a relative reduction of specific fuel consumption of 1%" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000637_f_version_1649326514-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000637_f_version_1649326514-Figure3-1.png", + "caption": "Figure 3. Parameters definition of a SynRM rotor with three barriers per pole.", + "texts": [ + " The automatic drawing procedure proposed in [15], however, requires only two main parameters for SynRM rotor modeling, i.e., insulation ratio kair and barrier end angle \u03b8b. The streamlined flux barrier shape is adopted, which is set to be parallel to the d-axis flux lines and perpendicular to the q-axis flux lines when saturation is neglected. This allows one to theoretically maximize the d-axis inductance and minimize the q-axis inductance, thus achieving a high saliency ratio and high torque. Points on the q-axis, as shown in Figure 3, are selected as starting points of the flux barrier boundaries, and their coordinates are computed through the width of each flux barrier tbi and the width of each iron path w f ei. By introducing the insulation ratio and the barrier end angles, w f ei is calculated according to the d-axis flux density distribution, and tbi is obtained based on the q-axis magnetic voltage drop across the corresponding flux barrier. Related equations and some tuning tricks to overcome geometric issues can be referred to [15]", + " Therefore, the SynRM rotor optimization can be achieved by combining the automatic modeling and simulation procedure with DE algorithm. The evaluation of individuals is completed by calling the FEA tool and finding the Pareto front, which are described in Figure 2. As previously mentioned, the optimization parameters are the insulation ratio kair and the barrier end angles \u03b8b. In fact, the number of barrier end angles depends on the number of flux barriers per pole. For example, the parameters definition of a three-barrier SynRM rotor is shown in Figure 3. The optimization objectives are focused on average torque and torque ripple, aiming at a low-torque-ripple and high-torque design. The torque ripple is defined as the ratio of peak-to-peak value to the average torque. According to the previous investigation [15], three and four flux barriers per pole are studies in order to balance the output torque and manufacture difficulties. The optimization result for SynRM with three barriers per pole is plotted in Figure 4a, and the corresponding result of the four barriers per pole motor is shown in Figure 4b" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure9-1.png", + "caption": "Fig. 9. The fixed surfaces of rims in the model of the twin rear wheels of the rear axis of the tipper: (a) the case when both twin wheels contacted the ground; (b) the case when only one tire of twin wheel contacted the ground", + "texts": [ + " Also, from conversations with MercedesBenz truck dealers, information was obtained that the wheel rims are made of hot-rolled steel. The Yield stress for such steel was equal to 300 MPa, and the Tensile Strength was equal to 440 MPa [64]. The rims are connected by the plane interface covering the rim end faces (Fig. 8c). The corresponding pin holes / bolts in both hubs are coaxial with each other (Fig. 8b). The contact elements were plane ones with the augmented option. The surfaces of the rims contacting with the wheel tires were fixed on one bottom half of their circumference (Fig. 9). The common practice is that the rim is fixed in its holes and possibly on the inner surface of the hole [65\u201368]. The fixing of the rim surfaces, as in the present case, facilitates the introduction of changes in the rim load without the need to model a very complex and difficult element, which is the tire. However, it may introduce some rigidity of the analyzed rims concerning reality. Particularly large deviations would be achieved with rims made of aluminum alloys. Fortunately, in the analyzed case, the rims were made of steel, which is a much stiffer material", + " The actual pressure in the twin wheel analyzed has not been known and it could even exceed its limit values. During the current analysis, the following principle was followed: if the calculated von Mises stresses in the rim caused by the load from the car weight and the driving torque exceed the plasticity limit of the rim material, they will exceed it even more if the influence of the presence of compressed air in the tire is considered. Two cases were considered: the first one when both twin wheels contacted the ground (Fig. 9a) and the second one when only one tire of the twin wheel contacted the ground (Fig. 9b). The maximal drive torque T was symmetrical, half its value, applied to the annular part of the plane of each hub containing the holes for pins/bolts connecting the twin wheels (Fig. 10). Half of the maximum vertical load G on the rear axle of the tipper by one twin wheel of this axle was applied to the same annular fragments of the plane (Fig. 10). The maximum vertical load G reached the value equal to a weight resulting from the permissible rear axle mass m mra\u2212perm, namely 16 0000 N. The grid of the curvilinear 10-node tetrahedral finite elements was shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001484__EEE-THESES_1563.pdf-Figure3.24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001484__EEE-THESES_1563.pdf-Figure3.24-1.png", + "caption": "Fig. 3.24 Simulated 2D array patterns using (a) MCG solution, and (b) TD solution.", + "texts": [ + "5156, \u20130.4409, \u2013 0.3518, \u20130.2485, \u20130.1311, 0] msec. Thus, the TD is obtained. The amplitude weights 112 for the MCG solution are calculated using Eq. (3.23), and obtained as [ ]11 22, ,..., NNA A A = [0.9754, 0.9829, 0.9896, 0.9957, 1.0010, 1.0055, 1.0091, 1.0118, 1.0137, 1.0146, 1.0146, 1.0137, 1.0118, 1.0091, 1.0055, 1.0010, 0.9957, 0.9896, 0.9829, 0.9754]. By using the TD and MCG solutions, the wideband array pattern on the measuring line (Fig. 3.22) can be simulated, as shown in Fig. 3.23 and Fig. 3.24 for 3D and 2D patterns, respectively. The difference of the average SPL in the target region by the two solutions with respect to the frequency is illustrated in Fig. 3.25. The following observations can be drawn from the simulated array patterns: (I) Both the TD and MCG solutions successfully generate acoustical hotspot at the target region. As shown by the 3D patterns in Fig. 3.23 and 2D patterns in Fig. 3.24, both solutions produce higher SPL around the target region of x = [\u20130.1 m, 0.1 m], compared to the SPL in the neighboring region. (II) As shown in Fig. 3.23 and Fig. 3.24, the two solutions arrive at the same array patterns. The resulting average SPLs in the target region obtained by the two solutions are very close. Throughout the frequency band, the SPL difference is smaller than 0.04 dB, as demonstrated in Fig. 3.25. In general, the simulation results have shown that both the MCG and TD solutions can be used in far-field wideband acoustical-hotspot generation, and they have similar performance. Therefore, for the far-field case in the free field, the TD method is recommended due to its simpler implementation" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004975_load_0_0_49825_53866-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004975_load_0_0_49825_53866-Figure4-1.png", + "caption": "Figure 4: FEMM mesh for the (a) SRM2 and (b) Dual-sided SyncRM", + "texts": [ + " One reason is that by using vector theory, the area of the quadrilateral between the aligned and unaligned flux-linkage responses (to changing operating current) determines directly the conversion energy W \u2032, which in turn translates into reluctance torque and electromagnetic power (this is further explained later in the Results section). Another reason is that this method is validated against experimental data provided by Takeno et al (2012), which yielded a good correlation. Moreover, it is well documented and clearly traceable (making it transparent), allowing identification of how it works and of its limitations. To this effect, the present research charted numerically the flux-linkage performance, both for the original SRM2 (Figure 4a) and novel Dual-sided SyncRM (Figure 4b). The planar electromagnetic simulation of the motor was conducted using the open-source software FEMM, with the motor cross section drawn using the opensource software NanoCAD (Arslan, 2021). Each mesh comprise of \u223c 35500 cells for the SRM2 and \u223c 48400 cells for the Dual-sided SyncRM. Simulations were conducted for various rotor angular positions, namely 0, 2, 4, 6, 8, 10, 12 and 15 degrees (between stator and rotor pole axis). The results are available as DWG and FEMM files for download at this author\u2019s profile page on the open-source platform Figshare, for both the SRM2 and the Dual-sided SyncRM" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure4-1.png", + "caption": "Figure 4. An overview of popular UAV types.", + "texts": [ + " Many aspects of the drone are discussed, including, but not limited to test flight results (Figures 2 and 3). We define the size and weight constraints as follows: a ready-to-fly drone should fit into a square of 1 \u00d7 1 m and weigh less than 3 kg (without payload). It should be able to carry at least 300 g of payload and stay airborne for at least 15 min. This research aims to design, build, and test a UAV with maximized range and hovering time. There are many different types of UAVs, each having unique features. Figure 4 presents the most common configurations: (a) A flying wing [9,10]\u2014typically used for long-endurance missions, e.g., photogrammetry or aerial photography. It is not a VTOL drone. (b) A fixed-wing plane [11,12]\u2014similar applications as for a flying wing. Fixed-plane UAVs are usually bigger and can carry more payload. If the plane has landing gear, it can operate from a runway. Again, it is not a VTOL drone. (c) A helicopter [13,14]\u2014can fulfil VTOL missions when a heavy payload is required. Complex mechanical design, many moving parts, and inefficient due to the energy required for the tail rotor, which does not contribute to the lifting force" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001456_18_ms-9-327-2018.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001456_18_ms-9-327-2018.pdf-Figure8-1.png", + "caption": "Figure 8. Rigid-body-replacement procedure.", + "texts": [ + " There are three kinematic pairs (revolute joints) available in the mechanism. The compliant segment of the output link is connected to the ground by a revolute joint, where the moment is not available as a reaction force, and the other part of this segment is fixed to the rigid segment of link 3. Therefore, this segment can be modeled as a cantilever beam, with a force at the free end, as shown in Fig. 7. By using the rigid mechanism dimensioned in Sect. 2, we start the replacement synthesis. First, we need to draw the PRBM to scale (Fig. 8). As discussed in Sect. 2, an angle between a3 and a4 of 90\u25e6 is used for the PRBM. The compliant segment of the compliant mechanism is overlapped with link 4 of the PRBM so that the initially straight beam lays on the revolute joints of a4. The length of compliant segment l is determined by using the characteristic radius factor \u03b3 \u2217 (Howell, 2001), as in Eq. (5): l = a4/\u03b3 \u2217. (5) The characteristic radius factor \u03b3 \u2217 is determined as follows: the compliant segment of the mechanism can be modeled as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004695_oradea2018_02004.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004695_oradea2018_02004.pdf-Figure5-1.png", + "caption": "Fig. 5. Rotary module", + "texts": [], + "surrounding_texts": [ + "It is known the fact that, if two bodies are put in contact, so that one exerts pressure on the other, results a tangent force on each of the bodies contact surface, called sliding friction force. It is also known, that this tangent force represents the action of a body onto the other body being equal and with opposite direction on each of the two contact surfaces G. W. Stachowiak, A. W. Batchelor [1]. Knowing the parameters of friction is an essential issue in tribological research, because friction always appears when there is a relative rotation between surfaces found in contact. Friction is produced in the absence of lubricant (dry friction) or in the partial or total presence of the lubricant (limit friction, mixed, elastohydrodynamic, hydrodynamic, hydrostatic etc.) W. Shizhu, H. Ping [2]. The friction phenomenon is characterized by a multitude of parameters. Amongst them, one of the most important (if not the most important) is the friction coefficient F. C. Chiu, G. F. Kao [3]. The friction coefficients are of two types: static friction coefficient \u03bcs and kinetics friction coefficients (dynamic) \u03bcc B. Mouhmid, A. Imad, N. Benseddiq [4] The static friction coefficients are the coefficients that appear at the limit between stop and movement, so at the start. Knowing the static friction coefficients represent a specific importance, especially in the friction joints where the starts and stops are frequent . Because of the multiple factors that can interfere in the friction process, the calculation equations for determining the friction coefficients are complex and difficult to resolve. For this reason, it is very important that the friction coefficients are determined through experimental methods, but with a high precision J. Williams [5]." + ] + }, + { + "image_filename": "designv8_17_0004049_f_version_1657704624-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004049_f_version_1657704624-Figure8-1.png", + "caption": "Figure 8. An overview of the Elka1Q drone dimensions\u2014top view.", + "texts": [], + "surrounding_texts": [ + "The overall shape of the drone (as seen in Figures 8 and 9) is a compromise among the general assumptions (described in Section 1), size and weight of significant components (such as the battery pack), and smart usage of available materials. 2.3.1. Wings Typically, drone arms are made of carbon-fibre tubes because they are very stiff and lightweight at the same time. However, such a single tube could have a too big a diameter to fit into the drone\u2019s wing. Instead, we decided to use double 6 \u00d7 2 mm carbon-fibre flat bars as wing spars. Additionally, the space between them forms a convenient tunnel for electric wires. The wings are built of two matching full-balsa wood elements: a bottom and a top half, both CNC 3D milled and glued together. The leading and trailing edges of a wing are usually prone to accidental damage (especially a very thin trailing edge); therefore, both edges are reinforced with carbon-fibre 4\u00d7 1 mm flat bars. The carbon-fibre wing spars at the wingtips support the main motor holders (CNC milled from a 3mm-thick aluminium sheet). The two elements of the holders are screwed together to catch protruding wing spars tightly. Finally, the surface of the wing is covered by Oracover [32] film. The wing construction proves to be light and very durable. We could say it is a perfect balance between stiffness and elasticity. Initially, we chose a wing profile (an airfoil) optimized for high-speed flight: the P-51D tip (BL215) airfoil (see Figure 10). Generally speaking, high-speed airfoils have low drag, but, on the other hand, have a low lift coefficient, which results in a high stall speed, and that means the plane has to maintain high enough speed to stay airborne in a level flight. That should not be an issue if the pusher motor can accelerate the drone to that speed. Due to safety reasons, we decided to modify the original wings\u2014we made them much thicker (see Figure 11). Such a thick airfoil (thickness increased from 12% to 25% of the airfoil chord) gives us a much higher lift coefficient (resulting in a lower stall speed) at the cost of lowering the top speed. Nevertheless, lower stall speed means we could perform the in-flight experiments of switching between quadcopter and plane mode at lower (i.e., safer) speed, and we could do that in a less spacious airfield. The wing configuration used in the drone is called a \u201ctandem-wing\u201d or sometimes a \u201clifting-tail plane\u201d. Those names refer to the fact that the aft wing is not just a horizontal stabilizer, like in a classic \u201ctailplane\u201d configuration, but it contributes to the total lift force produced by the plane. It is a rare configuration due to possible stability and controllability issues [34,35]. Sometimes, quite the opposite statements can be found\u2014tandem-wing planes are easier to pilot because of safer stall behaviour [36]. However, there were at least a few successful tandem-wing planes, e.g., Quickie designed by Elbert Leander \u201cBurt\u201d Rutan (and later QAC Quickie Q2) [36,37] and the Proteus [38] built by Scaled Composites (Rutan\u2019s company). Another famous tandem-wing plane is the \u201cFlying Flea\u201d (French name: \u201cPou du Ciel\u201d), designed by Henri Mignet in 1933. A thorough study of many more historical and modern tandem-wing planes and UAVs, as well as their aerodynamic and stability studies, can be found in [34]. A wing that produces lift force also generates a downwash, i.e., the airflow direction behind the trailing edge of the wing is deflected down by the aerodynamic action of the wing. That phenomenon changes the effective Angle of Attack (AoA) of the rear wing in the tandem-wing configuration. Most tandem-wing planes have the front wing mounted lower than the rear wing to minimize the downwash effect of the front wing [34,35]. Additionally, it is recommended to set a higher AoA of the front wing than the aft wing\u2014such a wing setup affects the stall behaviour of the tandem-wing plane. The front wing with a higher AoA will stall first while the aft wing still produces lift force\u2014that situation will cause the plane to pitch down, increase the speed, and ultimately, end the front wing\u2019s stall (bring back its lift force) [36]. Following the suggestions, the front wing of the Elka1Q drone was mounted at ca. 4\u25e6 AoA and the aft wing at ca. 2\u25e6 AoA. Finally, there is at least one more critical aspect of every aircraft having wings: Centre of Gravity (CG, CoG). It is crucial to keep the longitudinal stability of an aircraft. We used a CG calculator from the eCalc toolset [30]. The results of the calculation are presented in Figure 12. 2.3.2. Fuselage The final fuselage design was based on a rigid PVC tube (100 mm diameter and 1 mm wall) and a lighter, but still solid plywood structure (Figures 15\u201317). The PVC tube acts similarly to a monocoque structure, eliminating the twisting about the longitudinal axis. The landing gear is non-retractable\u2014we made four fixed legs of 3 mm spring steel wire supported by pinewood blocks at the bottom of the fuselage. The overall structure of the wings and the fuselage proved to be very rigid and robust, surviving a few serious crash landings. The most significant disadvantage of such a compact construction is complicated maintenance of internal components, e.g., access to electronic boards, wires, and connectors." + ] + }, + { + "image_filename": "designv8_17_0000550_9551808_09551816.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000550_9551808_09551816.pdf-Figure12-1.png", + "caption": "Fig. 12. Configuration of vibration and noise test equipment.", + "texts": [ + " The data acquisition system included a power analyzer (Yokogawa, WT1800), a 5 Nm-rated torque sensor (Kistler, 4503B), and other components as shown in Fig. 10 [9]. During this experiments, 55 V DC current was supplied to the test motor and the current was limited to 1.8 times the motor power rating to obtain the motor operating range. The full load performance maps of the proposed motor are plotted in Fig. 11 (a)-(d). Table VIII shows a comparison between the 2D FEA and experimental results for efficiency according to speed. We assumed that the mechanical loss is 6% of the output power. Fig. 12 presents the configuration of vibration and noise test equipment. The setup included an FFT analyzer (Bruel & Kjaer), tachometer, microphone and accelerometer. Fig. 13 and Fig. 14 show the results of the FFT and order tracking analysis for vibration acceleration during run-up (0\u20133500 rpm). It was found that the vibration acceleration was mainly generated at the pole pass frequency, as expected. There was a rotational frequency in the experiment but it could be eliminated through rotor balancing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure138-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure138-1.png", + "caption": "Figure 138 : Abaque pour l\u2019optimisation \u00e0 65\u00b0 dans le plan E, pour dx=5mm, avec un ruban rectangulaire, \u00e0 10GHz.", + "texts": [ + " Comme pr\u00e9c\u00e9demment, nous nous rendons compte que nous obtenons des r\u00e9sultats relativement diff\u00e9rents entre la th\u00e9orie et HFSS. Pour tenter d\u2019optimiser la source bande X dans le plan E, nous partons alors d\u2019un couple (Lx, wx) donn\u00e9 pour un dx choisi \u00e9gal \u00e0 5mm. Ensuite, nous optimisons avec HFSS en faisant varier Lx et wx. Finalement, nous atteignons un d\u00e9pointage jusque 67\u00b0 avec un Lx=15,53mm et wx=5,01mm. Ces dimensions donnent pourtant en th\u00e9orie, une source bande X tr\u00e8s d\u00e9sadapt\u00e9e \u00e0 65\u00b0 dans le plan E, comme pr\u00e9sent\u00e9 sur la Figure 138, qui pr\u00e9sente l\u2019abaque permettant d\u2019optimiser la source bande X \u00e0 65\u00b0 dans le plan E. L\u2019\u00e9toile en magenta correspond au couple (Lx, wx) choisi. Page 139 sur 182 Le couple choisi correspond en th\u00e9orie \u00e0 une source bande X d\u00e9sadapt\u00e9e \u00e0 65\u00b0 dans le plan E, mais permet finalement d\u2019atteindre 67\u00b0 dans le plan E. La Figure 139 pr\u00e9sente la structure optimis\u00e9e finale avec les WAIM 1 et WAIM 2 optimis\u00e9s. Les performances finales de la source bande X surmont\u00e9e des WAIM 1 et WAIM 2 sont pr\u00e9sent\u00e9es sur la Figure 139" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001389_f_version_1613447863-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001389_f_version_1613447863-Figure3-1.png", + "caption": "Figure 3. Cross-section of SMzs200S32 manufactured by \u0141-KOMEL; siting of PT-100 temperature sensors in different elements of motor is shown, they are partly indicated as drive end (D) and non-drive end (N) sensors: 1\u2014winding in slot N, 2\u2014winding in slot D, 3\u2014neutral point of winding, 4\u2014winding ends N, 5\u2014winding ends D, 6\u2014laminations D, 7\u2014laminations N, 8\u2014radiator disk D, 9\u2014radiator disk N, 10\u2014casing of cooling system D, 11\u2014casing of cooling system N, 12\u2014water at inlet point, 13\u2014water at outlet point, 14\u2014permanent magnets. D\u2014drive side; N\u2014non-drive side.", + "texts": [ + " For research purposes, this motor was equipped with a number of PT100 temperature sensors, placed in various elements of the stator and rotor (permanent magnets). Additionally, a small wireless temperature recorder was developed. It is installed on the rotor surface and the sensor mounted on the magnet is connected to the recorder. Temperature can be registered continuously and data are sent wirelessly [34]. The cross-section of the motor with the positions of the temperature sensors is shown in Figure 3. Motor at the test stand was supplied from Sevcon Gen4 Size8 inverter dedicated to EV supply. During tests, the inverter was supplied with nominal voltage V = 350 VDC (about 235 V at motor terminals). Since the rotor position angle sensor had to be used, a magnetic absolute encoder with analog Sin\u2013Cos output was applied. Control of the motor drive was conducted with the help of a computer-aided measurement and control device with dedicated control. The motor operates in two zones: constant torque zone and field weakening zone" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000847_853_83_17-00194__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000847_853_83_17-00194__pdf-Figure3-1.png", + "caption": "Fig. 3 Simulation model : pitch angle \u03b2", + "texts": [], + "surrounding_texts": [ + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 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2\u3064\u306e\u30b8\u30f3\u30d0\u30eb\u304c\u53d6\u308a\u4ed8\u3051\u3089\u308c\u3066\u304a\u308a\uff0c\u56de\u8ee2 \u8ef8\u307e\u308f\u308a\u306b\u81ea\u7531\u306b\u56de\u8ee2\u3059\u308b\uff0e\u56f3 3\u306b\u793a\u3059\u30b8\u30f3\u30d0\u30eb\u306e\u30d4\u30c3\u30c1\u89d2\u65b9\u5411\u306e\u56de\u8ee2\u89d2\u3092 \u03b2 \u3067\u8868\u3059\uff0e2\u3064\u306e\u30b8\u30f3\u30d0\u30eb\u306f\u5bfe\u79f0\u306b\u914d\n\u7f6e\u3055\u308c\uff0c\u305d\u308c\u3089\u306e\u89d2\u5ea6\u304c\u540c\u3058\u5927\u304d\u3055\u306b\u306a\u308b\u3088\u3046\u306b\u30ae\u30a2\u3067\u62d8\u675f\u3057\u3066\u3044\u308b\uff0e\u5404\u30b8\u30f3\u30d0\u30eb\u306b\u306f\u56de\u8ee2\u3059\u308b\u30db\u30a4\u30fc\u30eb\u3068\uff0c\u305d \u306e\u56de\u8ee2\u306e\u305f\u3081\u306e DC\u30e2\u30fc\u30bf\u3092\u914d\u7f6e\u3057\u3066\u3044\u308b\uff0e\n\u53f0\u8eca\u306f\u4e0d\u5b89\u5b9a\u7cfb\u3067\u3042\u308b\u305f\u3081\u3044\u305a\u308c\u8ee2\u5012\u3059\u308b\uff0e\u305d\u3053\u3067\u53f0\u8eca\u3084\u30b8\u30f3\u30d0\u30eb\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u8a2d\u8a08\u6761\u4ef6\u3092\u5909\u5316\u3055\u305b\u305f\u3068\u304d\u306b\uff0c\n\u8ee2\u5012\u307e\u3067\u306e\u6642\u9593\u3092\u3067\u304d\u308b\u3060\u3051\u9577\u304f\u3059\u308b\u3088\u3046\u306a\u6700\u9069\u8a2d\u8a08\u304c\u3067\u304d\u308b\u3053\u3068\u304c\u671b\u307e\u3057\u3044\uff0e\u8a2d\u8a08\u6761\u4ef6\u3068\u3057\u3066\u56f3 4\u306b\u793a\u3059\u3088\u3046 \u306b\u30b8\u30f3\u30d0\u30eb\u56de\u8ee2\u8ef8\u304b\u3089\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3\u307e\u3067\u306e\u8ddd\u96e2 a\u3068\u5730\u9762\u304b\u3089\u30b8\u30f3\u30d0\u30eb\u56de\u8ee2\u8ef8\u307e\u3067\u306e\u9ad8\u3055\uff08\u53f0\u8eca\u306e\u811a\u306e\u9577\u3055\uff09b\u306b \u7740\u76ee\u3057\uff0c\u305d\u308c\u305e\u308c a = 0.11,6.11,12.11[mm], b = 92.10,102.05,112.0[mm]\u3068\u5909\u5316\u3067\u304d\u308b\u3088\u3046\u306a\u69cb\u9020\u3068\u3057\u305f\uff0e\n\u30db\u30a4\u30fc\u30eb\u3092\u9664\u304f\u53f0\u8eca\u3068\u30b8\u30f3\u30d0\u30eb\u306f\u30a2\u30eb\u30df\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u307f\u9244\u88fd\u3068\u3057\u3066\u3044\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f\u534a\u5f84 40[mm]\uff0c\u539a\u3055 15[mm] \u3067\uff0c\u8cea\u91cf\u306f\u7d04 0.61[kg]\uff0c\u56de\u8ee2\u8ef8\u307e\u308f\u308a\u306e\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306f\u7d04 0.472\u00d710\u22123[kg m2]\u3067\u3042\u308b\uff0e\u3053\u306e\u30db\u30a4\u30fc\u30eb\u3092DC\u30e2\u30fc", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30bf\u3067\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3055\u305b\u308b\uff0e\u305f\u3060\u3057\uff0c2\u3064\u306e\u30db\u30a4\u30fc\u30eb\u89d2\u901f\u5ea6\u306e\u5927\u304d\u3055\u306f\u540c\u3058\u3067\u65b9\u5411\u3092\u9006\u306b\u3059\u308b\uff0e\u4e8b\u524d\u306b\u884c\u3063\u305f\u4e88 \u5099\u5b9f\u9a13\u3067\u306f\uff0c\u56de\u8ee2\u6570\u3092 7000[rpm]\u7a0b\u5ea6\u306b\u3059\u308b\u3068\uff0c\u30b8\u30f3\u30d0\u30eb\u3068\u53f0\u8eca\u304c\u3068\u3082\u306b\u63fa\u308c\u306a\u304c\u3089\u6b73\u5dee\u904b\u52d5\u3092\u884c\u3044\u9577\u6642\u9593\u306b\u308f \u305f\u308a\u5012\u308c\u305a\u306b\u7acb\u3061\u7d9a\u3051\u308b\u3053\u3068\u304c\u3067\u304d\u305f\uff0e10000[rpm]\u7a0b\u5ea6\u306b\u3059\u308b\u3068\u53f0\u8eca\u306e\u5074\u9762\u304b\u3089\u30d7\u30e9\u30b9\u30c1\u30c3\u30af\u30cf\u30f3\u30de\u3067\u885d\u6483\u3092\u4e0e\n\u3048\u3066\u3082\u8ee2\u5012\u3057\u306a\u3044\u307b\u3069\u5916\u4e71\u306e\u5f71\u97ff\u3092\u53d7\u3051\u306b\u304f\u3044\u3053\u3068\u3082\u78ba\u8a8d\u3067\u304d\u305f\uff0e\u3053\u306e\u3088\u3046\u306b\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u6570\u3092\u4e0a\u3052\u308c\u3070\u5b89\u5b9a \u6027\u304c\u5411\u4e0a\u3059\u308b\u3053\u3068\u306f\u5bb9\u6613\u306b\u78ba\u8a8d\u3067\u304d\u308b\uff0e\u3057\u304b\u3057\u306a\u304c\u3089\uff0c\u56de\u8ee2\u6570\u3092 7000[rpm]\u4ee5\u4e0a\u306b\u3059\u308b\u3068\u56de\u8ee2\u8ef8\u306e\u89e6\u308c\u56de\u308a\u632f\u52d5\n\u304c\u5927\u304d\u304f\u306a\u308a\uff0c\u9a12\u97f3\u3082\u6fc0\u3057\u304f\u306a\u3063\u305f\uff0e\n\u305d\u3053\u3067\uff0c\u672c\u7814\u7a76\u3067\u306f\u30db\u30a4\u30fc\u30eb\u306e\u56de\u8ee2\u6570\u3092\u3042\u307e\u308a\u5927\u304d\u304f\u3057\u306a\u304f\u3068\u3082\u5b89\u5b9a\u6027\u3092\u826f\u597d\u306b\u4fdd\u3064\u3053\u3068\u304c\u3067\u304d\u308b\u3088\u3046\u306a\u8a2d\u8a08 \u6307\u91dd\u3092\u691c\u8a0e\u3059\u308b\uff0e\u306a\u304a\u56f3 1\u306b\u793a\u3059\u5b9f\u9a13\u88c5\u7f6e\u3092\u3082\u3068\u306b\u56f3 2,3\u3067\u793a\u3057\u305f\u30e2\u30c7\u30eb\u3092 SolidWorks\u4e0a\u3067\u4f5c\u6210\u3057\uff0c\u5404\u525b\u4f53\u306e\u8cea\n\u91cf\u3084\u6163\u6027\u30e2\u30fc\u30e1\u30f3\u30c8\u306a\u3069\u306e\u7279\u6027\u3092\u6c42\u3081\u3066\u304a\u308a\uff0c\u6b21\u7ae0\u4ee5\u964d\u306e\u7406\u8ad6\u89e3\u6790\u3084\u30b7\u30df\u30e5\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u4f7f\u7528\u3057\u3066\u3044\u308b\uff0e\n3. \u904b \u52d5 \u30e2 \u30c7 \u30eb\n3\u00b71 \u5ea7\u6a19\u7cfb\n\u56f3 5\u306b\u5bfe\u8c61\u3068\u3059\u308b 2\u8f2a\u53f0\u8eca\u3092\u793a\u3059\uff0e\u56f3 5\u306f\u5ea7\u6a19\u7cfb\u306e\u8aac\u660e\u3092\u660e\u78ba\u306b\u3059\u308b\u305f\u3081\u306b\uff0c\u30b8\u30f3\u30d0\u30eb\u6a5f\u69cb\u3092 1\u3064\u306e\u307f\u63cf\u3044\u3066\n\u3044\u308b\uff0e\u53f0\u8eca\u306b\u306f\u30b8\u30f3\u30d0\u30eb\u304c\u53d6\u308a\u4ed8\u3051\u3089\u308c\uff0c\u53d6\u308a\u4ed8\u3051\u8ef8\u5468\u308a\u306b\u81ea\u7531\u306b\u56de\u8ee2\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306b\u306f\u30db\u30a4\u30fc\u30eb\u3092\u56de\u8ee2\u3055\u305b\n\u308b\u30e2\u30fc\u30bf\u304c\u56fa\u5b9a\u3055\u308c\uff0c\u30e2\u30fc\u30bf\u306b\u3088\u308a\u30db\u30a4\u30fc\u30eb\u304c\u4e00\u5b9a\u56de\u8ee2\u6570\u3067\u56de\u8ee2\u3057\u3066\u3044\u308b\uff0e\n\u03a3B \u3092\u5730\u9762\u4e0a\u306b\u56fa\u5b9a\u3057\u305f\u57fa\u6e96\u5ea7\u6a19\u7cfb\u3068\u3059\u308b\uff0ez\u8ef8\u306f\u925b\u76f4\u4e0a\u5411\u304d\uff0cx\u8ef8\u306f\u53f0\u8eca\u9032\u884c\u65b9\u5411\u3092\u6b63\u9762\u3068\u3059\u308b\u3068\u304d\u53f3\u624b\u3068\u306a\u308b \u5411\u304d\uff0cy\u8ef8\u306f\u6c34\u5e73\u65b9\u5411\u3067\u53f0\u8eca\u306e\u9032\u884c\u3059\u308b\u5411\u304d\u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f\u8d77\u4f0f\u306e\u3042\u308b\u9762\u3092\u4e0a\u308a\u4e0b\u308a\u3059\u308b\u3053\u3068\u3092\u60f3\u5b9a\u3059\u308b\uff0e\u53f0\u8eca\u306e \u5e95\u9762\u306b\u539f\u70b9\u3092\u3068\u308a\uff0c\u03a3B \u3092 x\u8ef8\u56de\u308a\u306b\u5730\u9762\u306e\u50be\u304d\u89d2\u5ea6 \u03d5 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u5ea7\u6a19\u7cfb\u3092 \u03a3A \u3068\u3059\u308b\uff0e\u53f0\u8eca\u306f 2\u8f2a\u3067\u8d70\u884c\u3059 \u308b\u305f\u3081\uff0c\u9032\u884c\u65b9\u5411\u306b\u5bfe\u3057\u3066\u5de6\u53f3\u65b9\u5411\uff08\u30ed\u30fc\u30eb\u89d2\u65b9\u5411\uff09\u306b\u5012\u308c\u3088\u3046\u3068\u3059\u308b\uff0e\u3053\u306e\u50be\u304d\u89d2\u5ea6\u3092 \u03a3A\u306e y\u8ef8\u56de\u308a\u306b \u03b1 \u3068\u8868 \u3059\uff0e\u539f\u70b9\u3092\u53f0\u8eca\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3A\u3092 y\u8ef8\u56de\u308a\u306b \u03b1 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u53f0\u8eca\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3C \u3068\u3059\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u56de \u8ee2\u89d2\u5ea6\u3092 \u03a3C \u306e x\u8ef8\u56de\u308a\u306b \u03b2 \u3068\u8868\u3059\uff0e\u539f\u70b9\u3092\u30b8\u30f3\u30d0\u30eb\u306e\u91cd\u5fc3\u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3C \u3092 x\u8ef8\u56de\u308a\u306b \u03b2 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30b8\u30f3\u30d0", + "\u00a9 2017 The Japan Society of Mechanical Engineers[DOI: 10.1299/transjsme.17-00194]\n\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3G \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306f \u03a3G \u306e z\u8ef8\u56de\u308a\u306b\u56de\u8ee2\u3059\u308b\uff0e\u305d\u306e\u89d2\u5ea6\u3092 \u03b3 \u3068\u3059\u308b\uff0e\u539f\u70b9\u3092\u30db\u30a4\u30fc\u30eb\u306e\u91cd\u5fc3 \u4f4d\u7f6e\u306b\u7f6e\u304d \u03a3G \u3092 z\u8ef8\u56de\u308a\u306b \u03b3 \u3060\u3051\u56de\u8ee2\u3055\u305b\u305f\u30db\u30a4\u30fc\u30eb\u4e0a\u306e\u5ea7\u6a19\u7cfb\u3092 \u03a3W \u3068\u3059\u308b\uff0e\n\u4ee5\u964d\u6570\u5f0f\u4e2d\u3067\u306f cos\u03b8 =C\u03b8 , sin\u03b8 = S\u03b8 \u3068\u7565\u8a18\u3059\u308b\uff0e\n3\u00b72 \u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\n\u307e\u305a\uff0c\u56de\u8ee2\u904b\u52d5\u3092\u8868\u3059\u305f\u3081\u306e\u5404\u525b\u4f53\u306e\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092\u660e\u3089\u304b\u306b\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u901f\u5ea6\u306f\u56de\u8ee2\u89d2\n\u03d5 ,\u03b1,\u03b2 ,\u03b3 \u306e\u6642\u9593\u5909\u5316\u306b\u3088\u3063\u3066\u8868\u3059\u3053\u3068\u304c\u3067\u304d\u308b\uff0e\u3053\u308c\u3092 \u03a3W \u3067\u8868\u3057\u305f\u3068\u304d W \u03c9W \u3068\u8a18\u3059\u3068\uff0c\nW \u03c9W = C\u03b3 S\u03b3 0 \u2212S\u03b3 C\u03b3 0\n0 0 1\n C\u03b1 \u03d5\u0307 + \u03b2\u0307\nS\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307\n (1)\n\u3068\u306a\u308b\uff0e\u30b8\u30f3\u30d0\u30eb\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3G \u3067\u8868\u3057\u305f\u3082\u306e\u3092 G\u03c9G \u3068\u8a18\u3059\u3068\uff0c\u5f0f (1) \u306b\u304a\u3044\u3066 \u03b3 = 0, \u03b3\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u307e\u305f\u53f0\u8eca\u306e\u59ff\u52e2\u306e\u5909\u5316\u3092\u8868\u3059\u89d2\u901f\u5ea6\u30d9\u30af\u30c8\u30eb\u3092 \u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092 C\u03c9C \u3068\u8a18 \u3059\u3068\uff0c G\u03c9G \u306b\u5bfe\u3057\u3066 \u03b2 = 0, \u03b2\u0307 = 0\u3068\u3057\u305f\u3082\u306e\u3068\u4e00\u81f4\u3059\u308b\uff0e\u3086\u3048\u306b\uff0c\u305d\u308c\u305e\u308c\u4ee5\u4e0b\u306e\u3088\u3046\u306b\u306a\u308b\uff0e\nG\u03c9G = C\u03b1 \u03d5\u0307 + \u03b2\u0307 S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 C\u03c9C = C\u03b1 \u03d5\u0307 \u03b1\u0307 S\u03b1 \u03d5\u0307 (2)\n3\u00b73 \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae \u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e\u6163\u6027\u30c6\u30f3\u30bd\u30eb\u3092\u305d\u308c\u305e\u308c \u03a3W ,\u03a3G,\u03a3C \u3067\u8868\u3057\u305f\u3082\u306e\u3092\nIW = IWX 0 0 0 IWY 0\n0 0 IWZ\n , IG = IGX 0 0 0 IGY 0\n0 0 IGZ\n , IC = ICX 0 0 0 ICY 0\n0 0 ICZ\n (3)\n\u3068\u3059\u308b\uff0e\u305f\u3060\u3057\uff0c\u30db\u30a4\u30fc\u30eb\u306e\u5bfe\u79f0\u6027\u304b\u3089 IWX = IWY \u3067\u3042\u308a\uff0c\u3053\u306e\u5024\u3092 IWXY \u3068\u3059\u308b\uff0e\u30db\u30a4\u30fc\u30eb\uff0c\u30b8\u30f3\u30d0\u30eb\uff0c\u53f0\u8eca\u306e \u56de\u8ee2\u904b\u52d5\u306b\u5bfe\u3059\u308b\u904b\u52d5\u30a8\u30cd\u30eb\u30ae TWR,TGR,TCR \u306f\u305d\u308c\u305e\u308c\u5f0f (1)(2)\u3092\u7528\u3044\u3066\uff0c\nTWR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03b3\u0307, \u03d5\u0307) = 1 2\n[ IWXY {( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 } + IWZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 + \u03b3\u0307 )2 ]\n(4)\nTGR(\u03b1,\u03b2 , \u03b1\u0307, \u03b2\u0307 , \u03d5\u0307) = 1 2\n{ IGX ( C\u03b1 \u03d5\u0307 + \u03b2\u0307 )2 + IGY ( S\u03b2 S\u03b1 \u03d5\u0307 +C\u03b2 \u03b1\u0307 )2 + IGZ ( C\u03b2 S\u03b1 \u03d5\u0307 \u2212S\u03b2 \u03b1\u0307 )2 }\n(5)\nTCR(\u03b1, \u03b1\u0307, \u03d5\u0307) = 1 2 ( ICXC2 \u03b1 \u03d5\u0307 2 + ICY \u03b1\u03072 + ICZS2 \u03b1 \u03d5\u0307 2) (6)" + ] + }, + { + "image_filename": "designv8_17_0004292_s-1961964_latest.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004292_s-1961964_latest.pdf-Figure11-1.png", + "caption": "Fig. 11 Distribution of stress (a) Antero-lateral (b) Postero-lateral; (c) Maximum stress at critical areas under cyclic load condition I", + "texts": [], + "surrounding_texts": [ + "The distribution of von-Mises stress, maximum deflection, number of cycles before failure, and safety factor of the modified polycentric prosthetic knee are investigated in this fatigue analysis. The results of von-Mises stress distribution during cyclic strength simulation are shown in Figs. 11 and 12. For both loading conditions, the von-Mises stress developed at the front and back joint bars is 18 to 23 MPa as shown in Figs. 11a, 11b, 12a, and 12b. The maximum stresses of 91 and 71 MPa are developed in the knee joint unit lower for load conditions I and II respectively as depicted in Figs. 11c and 12c. Therefore, it can be predicted that the modified polycentric prosthetic knee prosthesis employed in this research can withstand cyclic stress considering the high fatigue strength of AA7075-T6. The cyclic strength test results for the modified knee prosthesis are shown in terms of total deformation in Fig. 13. A maximum deformation has been observed at the point of load application which is 0.38 mm as shown in Fig. 13a. The alignment coupling unit of the knee prosthesis experiences the maximum deformation of 0.18 mm as depicted in Figs. 13b and 13c, suggesting the least amount of displacement. A deformation less than 2.5 mm during fatigue testing suggests that this modified prosthetic knee has sufficient strain-bearing ability to meet the structural norms, as recommended by the ISO 10328:2016 standard. The results of cyclic strength simulations for commonly failing components are summarized in Table 4. It is observed that the maximum developed stress is sufficiently below the fatigue strength of AA7075 T6 and the deformation produced is extremely minimal. There is a significant increase in fatigue life (no. of cycles) of most of the knee components. These values indicate that the modified polycentric knee prosthesis qualifies the requirements of ISO 10328:2016 standard." + ] + }, + { + "image_filename": "designv8_17_0002938_f_version_1649840248-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002938_f_version_1649840248-Figure4-1.png", + "caption": "Figure 4. The modeled single-phase rotary transformer topologies: (a) axial and (b) radial. (The air gap width in the figures between the secondary and primary parts of the rotary transformers is intentionally enlarged for demonstrational purposes).", + "texts": [ + " To enhance the transferred power, efficiency and to decrease the size, high supply frequency is used, as recently reported in [19\u201321]. However, the complexity of inverters and their high price are the major inconveniencies imposed by supply of high frequencies. It should be also noted that the operation of the rotary transformers within the higher frequency range requires the usage of the ferrite materials having poor mechanical strength under high speeds and temperatures [17]. Therefore, in this study, we specifically focused on analysis of the radial and axial rotary transformer topologies (Figure 4) for lower range of supply frequencies. The geometry of the single-phase axial and radial rotary transformers is shown in Figure 4a,b, respectively. Energies 2022, 15, x FOR PEER REVIEW 7 of 25 2.3. The Wireless Power Transfer System Applied for the EESM Excitation 2.3.1. The Geometries of Wireless Power Transfer Systems Applied for EESM Excitation The WPT technologies for the EESM excitation are, in general, performed via different couplings approaches such as: resonant inductive, inductive and capacitive. The solutions with the resonant coupling (i.e., via capacitor) contribute to the compensation of the reactive power and to the zero voltage switching in the inverter on the transformer\u2019s primary side", + " To enhance the transferred power, efficiency and to decrease the size, high supply frequency is used, as recently reported in [19\u201321]. However, the complexity of inverters and their high price are the major inconveniencies imposed by supply of high frequencies. It should be also noted that the operation of the r tary transf rmers within th higher frequency r nge requi es the usage of the ferrite materials having poor mechanical trength under high speeds and temperatures [17]. Therefore, in this study, we specifically focused on analysis of the radial and axial rotary transformer topologies (Figure 4) for lower range of supply frequencies. The geometry of the single-phase axial and radial rotary transformers is shown in Figure 4a,b, respectively. 2.3.2. Analytical Approach for Modeling of Rotary Transformers The voltage \ud835\udc49 across the transformer windings can be calculated assuming the sinusoidal waveforms of the voltages based on the Equation (22), derived from Faraday\u2019s law [22]: Figure 4. The single-phase rotary transformer top logies: (a) axial and (b) radial. (The ir gap width in the figures bet the secondary and primary parts of the rotary transformers is intenti ll larged for demonstra ional pur oses). 2.3.2. Analytical Approach for Modeling of Rotary Transformers The voltage Vrms across the transformer windings can be calculated assuming the sinusoidal waveforms of the voltages based on the Equation (22), derived from Faraday\u2019s law [22]: Vrms = \u221a 2\u03c0 f NBmax Ac1 (22) where Bmax is the maximum value of the magnetic flux density in T, f is the supply frequency in Hz; N is the number of turns of the windings and the Ac1 is the first effective cross-section area of the transformer core in m2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003809_el-03253472_document-Figure3.26-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003809_el-03253472_document-Figure3.26-1.png", + "caption": "Figure 3.26 : Vue 3D zoom\u00e9e du stub (a), de la spirale (b) et de la spirale-m\u00e9andre (c)", + "texts": [ + "2mm, ce qui est sup\u00e9rieur \u00e0 la longueur de cellule actuelle. Le circuit en \u03a0 pour la ligne 2-LH est toujours r\u00e9alisable en utilisant des vias plus fins, ce qui peut entra\u00eener une d\u00e9gradation des performances de la ligne \u00e0 cause du diam\u00e8tre des vias \u00e0 la limite de la tol\u00e9rance de fabrication. Les circuits en T seront plus faciles \u00e0 r\u00e9aliser au niveau de la capacit\u00e9, m\u00eame si l\u2019inductance est plus encombrante. DECRIPTION DE LA METHODE DE DESIGN DE DEPHASEURS CRLH-TL 100 La m\u00eame \u00e9tude est effectu\u00e9e sur les structures 3D d\u2019inductance illustr\u00e9es Figure 3.26. Nous allons en particulier d\u00e9tailler les r\u00e9sultats du stub, en effectuant l\u2019\u00e9tude param\u00e9trique de la longueur de stub autour de la valeur estim\u00e9e de 2.6mm (Figure 3.27). La valeur optimale de lstub est alors de 2.3mm : Les structures de spirale et de spirale-m\u00e9andre ne seront pas mod\u00e9lis\u00e9es car les valeurs d\u2019inductances recherch\u00e9es sont trop faibles pour obtenir des mod\u00e8les r\u00e9alisables. Dans les circuits en \u03a0, chaque cellule contient deux inductances de valeur 2.LL : DECRIPTION DE LA METHODE DE DESIGN DE DEPHASEURS CRLH-TL 101 Ces structures pr\u00e9sentent alors un fort encombrement vis-\u00e0-vis de la largeur globale de la ligne CRLH" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001283_download_25029_20643-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001283_download_25029_20643-Figure2-1.png", + "caption": "Figure 2 Architectures considered for ePumps: (a) FMVP and (b) VMFP.", + "texts": [ + " The study demonstrated how a decentralized hydraulic actuation could bring energy efficiency gains up to 40% with respect to the conventional centralized system. It also showed that among the main actuators, the arm of the machine experiences the highest dynamics, making its design challenging for electrification applications. Therefore, the authors selected the arm actuator for their study on electrification, considering a highly efficient actuation system with all functions as individual systems. For the current study, two different architectures for ePumps are considered (Figure 2) based on flow control strategy: one where the EM has a variable speed that can be achieved by the use of an inverter and the pump has a fixed displacement (VMFP) and one where the motor speed is fixed, and the pump displacement is varied (FMVP), by means of hydraulic or electrohydraulic control architectures. The third type of ePump architecture, based on VMVP operation, where both EM speed and HM displacement are varied and chosen to maximize efficiency, is outside the scope of the current paper" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000900_011_MIC-2011-3-3.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000900_011_MIC-2011-3-3.pdf-Figure1-1.png", + "caption": "Figure 1: Illustration of the AUVSAT where the inertial {i} and body {b} coordinate frames are shown as well as the reaction wheel rates \u2126.", + "texts": [ + " According to (Egeland and Gravdahl, 2002), the rotation matrix corresponding to the quaternion (2) is given by R(\u03b7, \u03b5) = I + 2\u03b7S(\u03b5) + 2S(\u03b5)2, (3) where I \u2208 R3\u00d73 is the identity matrix and S( \u00b7 ) \u2208 R3\u00d73 is the skew-symmetric vector cross product operator defined such that x1 \u00d7 x2 = S(x1)x2, \u2200 x1,x2 \u2208 R3. Note that the quaternion representation has an inherent redundancy and the quaternions q and \u2212q represent the same physical orientation, but q is rotated 2\u03c0 relative to \u2212q about an arbitrary axis (Kristiansen et al., 2009). Let {b} be a coordinate frame attached to a rigid spacecraft and {i} an inertial reference frame. (An illustration of the coordinate frames can be seen in Figure 1.) Then it can be seen that the kinematic differential equations can be expressed (Egeland and Gravdahl, 2002), as R\u0307i b = Ri bS(\u03c9bib), (4) where \u03c9bib is the angular velocity of the body frame {b} relative the inertial frame {i} decomposed in the body frame, and Ri b is the rotation matrix between the frames. For simplicity, Ri b is denoted R throughout the paper. Using (2)\u2013(4) the kinematic differential equations can then be expressed as q\u0307 = 1 2 E(q)\u03c9bib, (5) where E(q) = [ \u2212\u03b5> T(q) ] and T(q) = \u03b7I + S(\u03b5)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000706_O201332479507885.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000706_O201332479507885.pdf-Figure11-1.png", + "caption": "Fig. 11\uc740 \ud0c8\uace1\uae30 \ud558\ubd80\uad6c\uc870\ubb3c\uacfc \uc5d4\uc9c4\uc2e4, \ubc30\ucd9c\uad6c, \ub36e\uac1c, \ud480\ub9ac \ub36e\uac1c\uc758 \uc870\ub9bd \ubc29\ubc95\uc744 \ubcf4\uc5ec\uc900\ub2e4.", + "texts": [], + "surrounding_texts": [ + "Fig. 16\uc740 \ucf69 \ud0c8\uace1\uae30\uc758 \uc791\uc5c5 \uc6d0\ub9ac\ub97c \uc124\uba85\ud558\uae30 \uc704\ud558\uc5ec \ubc88\ud638\ub97c \uae30\uc785\ud558\uc600\ub2e4. \uc218\ud655\ud55c \ud6c4 \ub9c8\ub978 \ucf69\uc744 \uc88c\uce21\uc55e\ucabd\uc758 \ud22c \uc785\uad6c\u24ea\uc744 \ud1b5\ud574 \ud22c\uc785\ud558\uba74 \ubc14\uc774\ud2b8\u2460\uc774 \ud68c\uc804\uc744 \ud558\uba74\uc11c \ucf69\uae4d \uc9c0\ub97c \ubb3c\uace0 \ud0c8\uace1\uc2e4\ub85c \ubcf4\ub0b8\ub2e4. [Fig. 16] Sequence of threshing work principle \ud0c8\uace1\uc2e4\uc548\uc5d0 \uc788\ub294 \ud0c8\uace1\ud1b5\u2461\uc740 \ub0a0\uc744 \ub098\uc120\ud615\uc73c\ub85c \ubc30\uce58\ud558 \uc5ec \uc55e\ucabd\uc5d0\uc11c \ub4a4\ucabd\uc73c\ub85c \ucf69\uae4d\uc9c0\ub97c \ubb3c\uba74\uc11c \ud0c8\uace1\uc744 \ud55c \ud6c4 \ucf69 \uae4d\uc9c0\ub294 \ub4a4\ucabd\uc758 \uad6c\uba4d\uc744 \ud1b5\ud574 \ubc30\ucd9c\ub418\uace0 \ucf69\uc740 \uc120\ubcc4\ub9dd\u2462\uc744 \ud1b5\ud574 \uc544\ub798\ub85c \ub5a8\uc5b4\uc9c4\ub2e4. \uc774\ub54c \ucf69\uae4d\uc9c0 \uc720\ub3c4\ud310(2-1)\uc774 \uc55e\uc5d0 \uc11c \ub4a4\ub85c \ube44\uc2a4\ub4ec\ud788 \ub193\uc5ec \ubc29\ud5a5\uc744 \uc7a1\uc544\uc8fc\uc5b4 \ucf69\uae4d\uc9c0\uc758 \ud750\ub984 \uc744 \ub3d5\uace0 \ucf69\uae4d\uc9c0\uac00 \uc801\ucc44\ub418\uc9c0 \uc54a\uac8c \ud55c\ub2e4. \uc120\ubcc4\ub9dd\u2462\uc744 \ud1b5\ud574 \ub5a8\uc5b4\uc9c4 \ucf69\uc740 \ud754\ub4e4\ucc44\u2464\uc5d0 \ub5a8\uc5b4\uc9c0\uace0 \ud754\ub4e4\ucc44\u2464 \uc704\uc5d0 \ub5a8\uc5b4\uc9c0 \uc9c0 \ubabb\ud558\uace0 \uc55e\uc73c\ub85c \ud280\uc5b4\ub098\uac00\ub294 \ucf69\uc740 \ucf69\uc720\ub3c4\ud310\u2463\uc5d0 \ub9de\uace0 \ud754\ub4e4\ucc44\u2464\uc704\uc5d0 \ub2e4\uc2dc \ub5a8\uc5b4\uc9c4\ub2e4. \ud754\ub4e4\ucc44\u2464 \uc704\uc5d0 \ub5a8\uc5b4\uc9c4 \ucf69\uc740 \ucea0\uc0e4\ud504\ud2b8(5-1)\uac00 \ud754\ub4e4\ucc44\u2464 \ub97c \ud754\ub4e4\uba74\uc11c \ud754\ub4e4\ucc44\u2464\uc758 \uacbd\uc0ac\ub97c \ub530\ub77c \ubca8\ud2b8\u2466 \uc704\uc5d0 \ub5a8\uc5b4 \uc9c0\uace0 \uc1a1\ud48d\ud32c\u2465\uc774 \ud68c\uc804\ud558\uba74\uc11c \ud754\ub4e4\ucc44\uc640 \ubca8\ud2b8 \uc0ac\uc774\uc5d0 \uc1a1\ud48d \uc744 \ud558\uac8c\ub41c\ub2e4. \ubd80\ud53c\uac00 \uc791\uace0 \ubb34\uac70\uc6b0\uba70 \uacf5\ucc98\ub7fc \ub465\uadfc\ud615\uc0c1\uc758 \ucf69\uc740 \ubc14\ub78c\uc5d0 \ub0a0\ub9ac\uc9c0 \uc54a\uace0 \ubca8\ud2b8 \uc544\ub798\ub85c \uad74\ub7ec \ub5a8\uc5b4\uc9c0\uace0 \ubd80 \uc11c\uc9c4 \ucf69\uae4d\uc9c0\ub294 \uac00\ubccd\uace0 \ubd80\ud53c\uac00 \ucee4\uc11c \ubca8\ud2b8\uc640 \ubc14\ub78c\uc5d0 \uc2e4\ub824 \ubc16\uc73c\ub85c \ubc30\ucd9c\ub41c\ub2e4. \uc774\ub54c \ubc14\ub78c\uc758 \uac15\ub3c4\ub97c \uc870\uc808\ud558\uae30 \uc704\ud558\uc5ec \uacf5\uae30\uc758 \uc591\uc744 \uc870\uc808\ud560 \uc218 \uc788\uac8c \uc124\uacc4\ub418\uc5c8\ub2e4. \ubca8\ud2b8 \uc544\ub798\ub85c \ub5a8 \uc5b4\uc9c4 \ucf69\uc740 \uc720\uc790\ud615\uad00\u2467\uc73c\ub85c \ub5a8\uc5b4\uc9c0\uace0 \uc720\uc790\ud615\uad00\u2467 \uc548\uc5d0 \uc788 \ub294 \uc774\uc1a1 \uc2a4\ud06c\ub958\u2468\ub97c \ud0c0\uace0 \ubc30\ucd9c\uad6c\ub85c \ubcf4\ub0b4\uc9c4\ub2e4. \ubc30\ucd9c\uad6c\ub85c \ub5a8\uc5b4\uc9c4 \ucf69\uc740 \ubc30\ucd9c\ud32c\u2469\uc774 \uc1a1\ud48d\ud558\ub294 \ubc14\ub78c\uc744 \ud0c0\uace0 \ubc30\ucd9c\uad6c\u246a \ubc16\uc73c\ub85c \ubcf4\ub0b4\uc9c4\ub2e4. \ubc30\ucd9c\ud32c\uc758 \uc1a1\ud48d\ub7c9\uc740 \uc2dc\ud5d8\uac00\ub3d9\uc744 \ud1b5\ud574 \uc801 \uc815\ud55c \uacf5\uae30\uc758 \uc591\uc73c\ub85c \uc870\uc808\ub418\uc5c8\ub2e4. \ubc30\ucd9c\uad6c\uc5d0 \uc774\ubb3c\uc9c8\uc774 \ub07c\uc77c \uc218 \uc788\uc73c\ubbc0\ub85c \uc190\uc774\ub098 \uccad\uc18c\ub3c4\uad6c\uac00 \ub4e4\uc5b4\uac08 \uc218 \uc788\ub3c4\ub85d \ucabd\ubb38 \uc744 \ub450\uc5b4 \uc5b8\uc81c\ub4e0 \uccad\uc18c\ub97c \ud560 \uc218 \uc788\uac8c \ub418\uc5b4 \uc788\ub2e4. \ubc30\ucd9c\uad6c\u246a \uc744 \ud1b5\ud574 \ub098\uc628 \ucf69\uc740 \uc790\ub8e8\ubc1b\uce68\ub300\u246b \uc704\uc5d0 \uc62c\ub824\uc9c4 \uc790\ub8e8\uc5d0 \ubc14 \ub85c \ub2f4\uae30\uac8c \ub41c\ub2e4. \ucd5c\uc885\uc801\uc73c\ub85c \ubc30\ucd9c\ub418\uc5b4 \uc790\ub8e8\uc5d0 \ub2f4\uae34 \ucf69\uc5d0 \ub294 \uc774\ubb3c\uc9c8\uc774 \uac70\uc758 \uc11e\uc774\uc9c0 \uc54a\uace0 \uae54\ub054\ud558\uac8c \ud0c8\uace1\uc744 \ud560 \uc218 \uc788 \ub2e4." + ] + }, + { + "image_filename": "designv8_17_0002543_apers_D_N010104f.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002543_apers_D_N010104f.pdf-Figure8-1.png", + "caption": "Figure 8: (a) Stress resultants at the waist section of the hyperboloid shell under bending. (b) Equilibrium of forces on a shell segment. (c) Equivalent diagonal forces in the intersecting bars to take up the stresses around a shell element on the compression side of the hyperboloid shell.", + "texts": [ + " Combining eqns (17) and (18), we have M = 4 \u222b a 0 y2 a \u03c3a t cos \u03b1 dy M = 4t\u03c3a \u222b a 0 y2 a cos \u03b1 dy. (19) Substituting for y = a sin \u03b1 and dy = a cos \u03b1 d\u03b1, eqn (19) can be rewritten as M = 4t\u03c3a \u222b \u03c0/2 0 a2 sin2 \u03b1 a cos \u03b1 a cos \u03b1 d\u03b1. (20) Integrating eqn (20) gives M = \u03c0a2t\u03c3a. (21) The normal stress at the waist circle in terms of the bending moment can be written as \u03c3a = M \u03c0a2t . (22) Then, N\u03c6, on the waist-circle element at distance a from the neutral axis, is given by (N\u03c6)a = \u03c3at. Thus from eqn (22), (N\u03c6)a = M \u03c0a2 . (23) According to Fig. 8c the force (Fm) in the generator is given by F2 m = [( \u03c0a n (N\u03c6)a )2 + ( \u03c0b n (N\u03b8)a )2 ] . (24) Substituting the value of N\u03b8 from eqn (11), we get F2 m = [( \u03c0a n ( N\u03c6 ) a )2 + ( \u03c0b n ( a2 b2 (N\u03c6)a ))2 ] . (25) Since tan \u03b2 = a/b, eqn (25) reduces to F2 m = ( M \u03c0a2 )2 ( \u03c0a n )2 [ 1 + tan2 \u03b2 ] or Fm = M na cos \u03b2 , (26) where Fm can be either compressive or tensile force based on the location of the generators relative to the plane about which the bending moment is applied. 3.3 Stress analysis under torsional loading Next, we analyse the compressive and tensile forces in the hyperboloid shell generators when the VB is subjected to pure torsion (T )" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003562_5_agriceng-2019-0036-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003562_5_agriceng-2019-0036-Figure9-1.png", + "caption": "Figure 9. Distribution of pressure along the car body line concept 4", + "texts": [], + "surrounding_texts": [ + "Analysis of the simplified simulation of air flow around the test car body concept concerns the impact of the change of the shape of the front part of the vehicle on the distribution of pressure and on functional and aesthetic properties. In concept 1, a zone of the increased pressure, which is present in the front part, results from the geometric shape of the car body (Fig. 6). Visible reduction of pressure in the driver\u2019s space referred to the surrounding proves a more effective protection of a driver against air blows during driving. A built-up space for driver\u2019s legs considerably protects driver\u2019s body parts against outside impact. A visible zone of the increased pressure around the front part in concept 2 proves an increased head aerodynamic resistance (Fig. 7); however, reduced turbulences in the driver\u2019s space show the most effective protection against air blows that influence a driver. Ensuring aerodynamic shapes of the part of the vehicle that is the most exposed to air resistance results in the reduced space for a driver which negatively influences the operator\u2019s position during driving. In concept 3 (Fig. 8) the front part has an aesthetic function and improves driver\u2019s comfort by enabling him to maintain an unhindered position of legs during driving. In the symmetry plane of the vehicle, reduction of the head pressure value is observed. However, this structure is the weakest regarding protection of the driver\u2019s body against damage from the surrounding. Due to its geometry, the driver\u2019s body is more exposed to air blows. Concept 4 has protective functions of inside mechanisms and the driver\u2019s body parts maintaining at the same time aesthetic values. However, manoeuvring without obstacles is impeded in this concept. In all concepts, the use of a windshield protecting a driver, favourably influences the comfort of use of the vehicle since it limits air turbulence in the passenger space. Analysis of flow in the symmetry plane of the vehicle presents a local formation of aerodynamic resistance; however, the structure of the front part in concept 3 and 4 allows efficient reduction of the pressure increase." + ] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure17-1.png", + "caption": "Figure 17. Thermal field distribution under condition of only water cooling used in the casing when both the SM and the DRM are running at the low speed and rated load.", + "texts": [ + " Comparison of Table 8 with Table 7 shows that the temperature of each part when the axial force air is used in the machine is lower than the temperature of each part when the water cooling is used in the inner rotor. This is mainly because the axial forced air can cool not only the inner rotor core by the axial cooling slots and the air gap but also the end range. In contrast, the water cooling mode used in the inner rotor can only take away the heat of the inner rotor by the axial cooling slots. When both the SM and the DRM are running at the low speed and rated load, the 3-D thermal field distribution is calculated under condition of only water cooling used in the casing, as shown in Figure 17. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the water inlet side, middle cross-section, and the water outlet side of the CS-PMSM are shown in Figure 18. The selected water inlet, middle and water outlet cross-sections are the same as those in Section 4.1. The highest temperature of different parts in the above three cross-sections is shown in Table 9. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 9" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004557_9312710_09416651.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004557_9312710_09416651.pdf-Figure17-1.png", + "caption": "FIGURE 17. Proposed notched shape magnet.", + "texts": [ + " In the next phase, sampling is done to design the experiments by using the Latin hyper cube (LHC) sampling technique. Then to approximate the objective function, the kriging method is applied. The optimal value for the selected design variable is obtained through the genetic algorithm (GA). In the last phase, 3D FEM is performed to verify the output of the proposed machine. VOLUME 9, 2021 64185 A simple notched shape magnet as shown in Fig. 7(b), was chosen as the beginning point for optimization of the rotor pole. Length and width of notch illustrated as X1 [0.5-3.5 mm] and X2 [0.5-5 mm], respectively in Fig. 17, were chosen as the design variables. Each notch is just like a small rectangle, so we select any two sides X1 and X2 as design variables. The length and width of both variables must be greater than 0 mm to create a notch as well as for a significant notch it must be at least 0.5 mm. The maximum length is equal to half of the magnet width which is 7/2 = 3.5 mm, greater than half of the magnet will change its overall basic rectangular shape. For a given number of notches, the width should not greater than 5 mm" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002063_f_version_1669287462-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002063_f_version_1669287462-Figure8-1.png", + "caption": "Figure 8. Schematic diagram of the forces acting on a particle in the vicinity of the solid\u2013liquid interface.", + "texts": [ + " Optical microscope images of samples (a) without PMF and (b) with PMF. The control of inclusion, that is, whether the inclusion is engulfed or pushed by the solidification front, is determined by the competition of forces acting on the inclusion. The balance of forces can produce a steady-state pushing speed [24\u201329], namely critical velocity; otherwise, the disruption of balance can cause inclusions to be engulfed or pushed. The different forces experienced by inclusions near the solidification front are shown in Figure 8. Metals 2022, 12, x FOR PEER REVIEW 8 of 12 The control of inclusion, that is, whether the inclusion is engulfed or pushed by the solidification front, is det r in d by the competition of forces acting on the inclusion. The balance of forces can produce a steady-state pushing speed [24\u201329], namely critical velocity; otherwise, the disruption of balance can cause inclusions to be engulfed or pushed. The different forces experienced by inclusions near the solidification front are shown in Figure 8. The forces acting on the inclusion during the solidification process vary in time. At the initial stage, the distance between the inclusion and solidification front is large, and the repulsive and attractive forces are very small. When the solidification front approaches inclusion to the nanometer level, the repulsive forces become larger. In time, the forces rise steeply, and the balance between the repulsive forces and the opposing forces becomes very delicate. Based on the balance of forces acting on the inclusions, the expression of the critical velocity is generated" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003278_le_download_510_1021-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003278_le_download_510_1021-Figure1-1.png", + "caption": "Fig. 1. 3-D model of bin", + "texts": [ + " Sub-baric storage bin is cylindrical in geometry with conical shape at bottom side and flat circular plate on top side. The material of construction was decided as AISI-316 SS and both units were designed to work in full vacuum of 5 kPa with outside operating pressure of 101.1 kPa (NTP). Computer Aided Design/Engineering (CAD/CAE) and FEA analysis were used to determine the Von Mises stress, deformation and factor of safety. [19- 20]. The 3-D model of the unit was developed using Pro/ENGINEER software as shown in Fig. 1. This graphical model was then saved in IGES-(Initial Graphics Exchange Specification) neutral format and imported to ANSYS-14 workbench for stress analysis. The operating parameters, material properties and boundary conditions were fed to ANSYS-14 work bench for stress analysis. In order to optimize the wall thickness, the stress analysis was conducted using different design software (Pro/E, ANSYS) by following the procedures as detailed by Kraan et al., [19] [21] as shown in Fig. 2. After completion of therotical design of sub-baric storage bin in design software and completer stress analysis, the fabrication work was carried out as per FDA c-GMP and 3A hygiene standards [17]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000027_6_65_4_65_4_525__pdf-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000027_6_65_4_65_4_525__pdf-Figure15-1.png", + "caption": "Fig. 15 Externals of satellite", + "texts": [], + "surrounding_texts": [ + "\u6a5f \u80fd\u8981 \u7d20 \u9593\u306b\u6210 \u308a\u7acb \u3064\u4f4d\u7f6e \u95a2\u4fc2 \u306b\u3064 \u3044\u3066 \u306e\u5236 \u7d04 \u3092\u5145\u8db3 \u3055\u305b \u308b \u3082 \u306e \u3067\u3042 \u308b.\u3053 \u306e \u30bd\u30eb\u30d0 \u306b \u304a\u3044 \u3066\u306f,\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u30e6\u30cb \u30c3 \u30c8\u304c \u8a2d\n\u8a08\u89e3 \u3092\u751f\u6210 \u3059 \u308b\u524d \u306b,\u6a5f \u80fd \u8981\u7d20\u306e \u4f4d\u7f6e \u306e\u6982 \u7565 \u3092\u6c42 \u3081 \u308b \u3053 \u3068\u3092 \u76ee \u7684 \u3068\u3057\u3066\u3044 \u308b.\u305d \u306e\u305f \u3081,\u3053 \u3053\u3067 \u306f\u6a5f \u80fd\u8981 \u7d20\u306e \u4e2d\u5fc3 \u5ea7 \u6a19 \u306e\u307f \u3092 \u53d6 \u308a\u6271 \u3046.\u3053 \u306e\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb \u30d0 \u306b \u3088\u3063\u3066\u6c42 \u3081 \u3089\u308c \u305f \u4e2d\u5fc3\u5ea7 \u6a19 \u304b \u3089,\u4e0a \u8ff0 \u3057\u305f \u5e7e\u4f55 \u5b66\u7684 \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066\u6c42\u3081 \u3089\u308c \u305f\u5f62\u72b6 \u304c\u751f \u6210\u3059 \u308b\u3053 \u3068\u306b \u306a\u308b.\u5177 \u4f53 \u7684 \u306b\u306f,\u3053 \u306e \u30bd\u30eb \u30d0 \u306f\u5b9f \u6570\u8868 \u73fe \u306e \u67d3 \u8272\u4f53 \u3092 \u3082\u3064GA\u3092 \u5fdc \u7528 \u3057\u3066 \u304a \u308a,VLSI(Very Large Scale Integrated)\u30c1 \u30c3\u30d7 \u306e \u30ec \u30a4\u30a2 \u30a6 \u30c8\u8a2d\u8a08(\u4f8b \u3048\u30709))\u306b \u304a \u3044 \u3066\u7528 \u3044 \u3089\u308c \u3066 \u3044 \u308b \u3082\u306e \u3068\u57fa \u672c \u7684 \u306b\u540c\u69d8 \u306e \u624b \u6cd5 \u30923\u6b21 \u5143 \u306b\u62e1 \u5f35 \u3057\u305f\n\u624b \u6cd5 \u3092\u63a1\u7528 \u3057\u3066\u3044 \u308b.\n\u4e0a\u8ff0 \u3057\u305f2\u3064 \u306e \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066,\u305d \u308c\u305e \u308c\u6a5f \u80fd \u8981\u7d20 \u306e\u6982 \u7565 \u5f62 \u72b6 \u3068\u6982\u7565 \u306e\u4f4d \u7f6e \u3092\u5f97 \u305f\u5f8c \u306b,\u3053 \u306e\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8\u306b \u3088\u3063 \u3066\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u3092\u751f \u6210\u3059 \u308b.\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u30e6 \u30cb \u30c3 \u30c8\u306b\u304a \u3051 \u308b \u30a2\u30eb \u30b4 \u30ea\u30ba \u30e0\u306f,\u5236 \u7d04 \u3092\u5145 \u8db3\u3059 \u308b\u30d7 \u30ed\u30bb \u30b9\u3067 \u306f \u306a \u304f,\u5e7e \u4f55 \u5b66 \u7684 \u5236\u7d04 \u30bd\u30eb\u30d0 \u3068\u7a7a \u9593\u914d \u7f6e \u30bd\u30eb\u30d0\u304c \u751f \u6210 \u3057\u305f\u5236 \u7d04\u5145 \u8db3 \u89e3 \u3092\u7d71 \u5408 \u3057, \u6a5f \u80fd\u8981 \u7d20 \u306e3\u6b21 \u5143 \u5f62 \u72b6 \u3068\u305d\u306e\u7a7a \u9593 \u7684 \u914d\u7f6e \u3092\u540c \u3058\u67a0 \u7d44 \u306e \u4e2d \u3067\u6c42 \u3081 \u308b \u3053 \u3068\u304c \u76ee\u7684\u3067 \u3042 \u308b.\u3053 \u3053\u3067,\u300c\u540c\u3058\u67a0 \u7d44\u306e \u4e2d\u3067 \u300d\u6c42 \u3081 \u308b \u3053 \u3068 \u3068\u306f,\u5e7e \u4f55\u5b66 \u7684\u5236\u7d04 \u30bd\u30eb\u30d0 \u3068\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0\u304c \u751f\u6210 \u3057\u305f\u8a2d \u8a08\u89e3 \u306e\u77db \u76fe\u3059 \u308b\u90e8 \u5206 \u306b\u3064 \u3044\u3066,\u305d \u308c\u305e \u308c \u306b\u5bfe \u3057\u3066 \u300c\u540c \u3058\u67a0 \u7d44 \u306e \u4e2d\u3067 \u300d\u4fee \u6b63 \u3092\u52a0 \u3048,\u5e7e \u4f55 \u5b66\u7684 \u5236\u7d04 \u3068\u7a7a \u9593\u914d \u7f6e\u5236 \u7d04 \u306b \u3088\u3063\u3066 \u751f\u6210 \u3055\u308c \u305f2\u3064 \u306e \u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3 \u306b\u95a2\u3059 \u308b\u8a2d \u8a08 \u89e3\u306e \u59a5\u5354 \u70b9 \u3092\u63a2 \u7d22 \u3057, \u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3 \u89e3 \u3092\u751f\u6210 \u3059 \u308b \u3053 \u3068\u3092\u610f \u5473 \u3057\u3066\u3044 \u308b.\u4ee5 \u4e0b \u306b,\u56f3 \u4e2d \u306e \u756a\u53f7 \u306b\u6cbf \u3044 \u306a\u304c \u3089,\u5404 \u6bb5 \u968e \u306b\u3064 \u3044\u3066 \u8aac \u660e\u3059 \u308b.\n\u56f311(1)\u306b \u304a\u3044\u3066,\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066\u751f \u6210 \u3055\u308c \u305f, \u6a5f \u80fd\u8981\u7d20 \u306e\u5ea7 \u6a19 \u3092\u5f97 \u308b(\u56f312\u306e1).\u6b21 \u306b,\u56f312\u306e2\u306b \u793a\u3059 \u3088 \u3046\u306b,(1)\u306b \u304a \u3044\u3066 \u5f97 \u3089\u308c \u305f\u5ea7 \u6a19 \u3092 \u4e2d\u5fc3 \u306b,\u5f62 \u72b6 \u3092\u751f\u6210 \u3059 \u308b. \u3053\u306e\u6bb5 \u968e\u3067 \u306f,\u6a5f \u80fd\u8981 \u7d20 \u9593\u306b\u5e72\u6e09 \u306f \u306a\u3044 \u305f\u3081,\u66f4 \u306b\u5f62\u72b6 \u306f\u6bb5 \u968e\n\u7684 \u306b\u751f \u6210 \u3055\u308c \u308b(\u56f311(2),(3)) .\u56f312\u306e3\u306b \u793a\u3059 \u3088 \u3046\u306b,\u5f62 \u72b6\u304c \u751f \u6210 \u3055\u308c\u3066 \u3044 \u304f\u306b\u5f93 \u3063\u3066,\u96a3 \u63a5\u3059 \u308b\u6a5f \u80fd \u8981\u7d20\u304c \u5e72 \u6e09 \u3057,\u5171 \u6709 \u90e8\u5206 \u304c\u767a \u751f \u3059 \u308b.\u3053 \u306e\u5834 \u5408,\u56f311(4),(5),(6)\u306b \u793a \u3059 \u3088 \u3046\u306b, \u5f62\u72b6 \u751f\u6210 \u306e \u4e2d\u5fc3\u4f4d \u7f6e \u3068\u5e72 \u6e09 \u3057\u305f\u5f62\u72b6 \u306e\u30eb \u30fc\u30eb \u306b\u3064 \u3044\u3066 \u306e\u8abf \u6574\u304c \u540c \u3058\u67a0 \u7d44 \u306e \u4e2d\u3067\u884c \u308f \u308c \u308b.\n\u5f62\u72b6 \u306e \u4e2d\u5fc3 \u4f4d\u7f6e \u306e\u8abf \u6574 \u306f,\u56f313\u306b \u793a\u3059 \u3088 \u3046\u306b,\u5e72 \u6e09 \u3057\u305f\u6a5f\n\u80fd \u8981\u7d20A,B\u306f,\u305d \u308c\u305e \u308c \u306e\u5f62 \u72b6 \u306e\u751f \u6210 \u306e \u4e2d\u5fc3 \u3092NA,NB\u65b9 \u5411 \u306b\u79fb \u52d5\u3059 \u308b\u3002 \u305d\u306e\u79fb \u52d5 \u8ddd\u96e2 \u306f,\u305d \u306e \u5171\u6709 \u90e8 \u5206 \u306e\u4f53\u7a4d \u3092V;\u3068 \u3059 \u308b \u3068,\u4ee5 \u4e0b \u306e \u3088 \u3046\u306b\u5b9a \u7fa9\u3059 \u308b(\u56f313:\u5de6).\n\u3013(1)\n\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066\u751f\u6210 \u3055\u308c \u305f\u5f62\u72b6 \u751f \u6210\u306e \u4e2d\u5fc3 \u4f4d\u7f6e \u3092NA,NB\u65b9 \u5411\u306b\u79fb \u52d5 \u3055\u305b \u305f\u5834 \u5408,\u8abf \u6574 \u524d\u306e \u4e2d\u5fc3\u4f4d \u7f6e\u306f \u7a7a \u9593\u914d \u7f6e \u5236\u7d04 \u30bd\u30eb \u30d0 \u306b \u3088\u3063\u3066\u6700\u9069 \u5316 \u3055\u308c \u3066\u3044 \u308b\u305f \u3081,\u8abf \u6574\u5f8c \u306f \u305d\u306e\u8a55 \u4fa1 \u5024\u306f \u307b \u3068\u3093 \u3069\u306e\u5834 \u5408 \u6e1b\u5c11\u3059 \u308b\u3053 \u3068\u3068\u306a \u308b.\u305d \u3053\u3067,\u5f62 \u72b6 \u751f \u6210 \u306e \u4e2d\u5fc3 \u306e\u7a7a \u9593 \u7684\u914d\u7f6e \u3092\u7a7a \u9593\u914d \u7f6e\u5236 \u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066,\u5168 \u4f53 \u3068 \u3057 \u3066\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u306b\u5bfe \u3059 \u308b\u8a55\u4fa1 \u5024 \u3092\u4e00\u5b9a\u306e \u7bc4 \u56f2\u4ee5\u4e0b \u306b\u4e0b \u3052 \u306a\u3044 \u3088\nFig. 11 Flowchart of spatial design unit\n\u3046\u306b\u5f62\u72b6 \u306e \u4e2d\u5fc3 \u4f4d \u7f6e \u3092\u518d\u8abf \u6574 \u3059 \u308b(\u56f311(4),(5),\u56f313:\u53f3)\u3002\n\u5f62\u72b6 \u751f\u6210 \u306e \u4e2d\u5fc3 \u4f4d \u7f6e\u306e \u518d\u8abf \u6574 \u3068\u540c\u6642 \u306b,\u4e0a \u8ff0 \u3057\u305f \u3088 \u3046\u306b\u5e72\u6e09\n\u3057\u305f\u5f62 \u72b6\u306e \u30eb \u30fc \u30eb \u306b\u3064 \u3044 \u3066\u306e\u8abf \u6574 \u3082\u884c \u308f \u308c \u308b(\u56f311(6)).\u3053 \u306e \u30eb\u30fc \u30eb\u306e\u8abf \u6574 \u306b\u3064 \u3044\u3066 \u306f,\u524d \u7bc0 \u306e\u751f \u6210 \u30eb\u30fc\u30eb \u306b \u6ce8 \u76ee \u3057\u305f\u5f62\u72b6\n\u8868\u73fe \u306e \u62e1\u5f35 \u306b \u304a\u3044 \u3066\u8ff0 \u3079 \u305f\u901a \u308a\u3067 \u3042 \u308b.\n\u3053 \u3046 \u3057\u3066,\u6a5f \u80fd \u8981\u7d20 \u306e\u5f62 \u72b6 \u306e\u751f \u6210 \u3068\u8abf \u6574\u304c \u7d42 \u4e86 \u3057\u305f\u6642 \u306b,\u7a7a\n\u9593 \u30c7\u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8\u306b\u304a \u3044 \u3066,\u7a7a \u9593\u914d \u7f6e \u30683\u6b21 \u5143 \u5f62 \u72b6 \u306e\u77db \u76fe \u70b9 \u3092\u540c \u3058\u67a0\u7d44 \u3067\u89e3 \u6d88 \u3057\u306a\u304c \u3089,\u305d \u308c\u305e \u308c \u306e\u5236 \u7d04\u306b\u5bfe \u3059 \u308b\u8a55\u4fa1 \u5024 \u3092\u5168\u4f53 \u3068 \u3057\u3066\u4fdd \u3063\u305f\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u89e3 \u3092\u5f97,\u8a2d \u8a08\u8005 \u306b\u63d0\u793a \u3059 \u308b. \u8a2d\u8a08 \u8005 \u306f,\u3053 \u308c \u3092\u89b3\u5bdf \u3057,\u6c17 \u306b\u5165\u308c \u3070 \u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u306e \u30d7 \u30ed\u30bb \u30b9 \u304c \u7d42 \u308f \u308a,\u6c17 \u306b\u5165 \u3089\u306a \u3051\u308c\u3070 \u3082 \u3046\u4e00\u5ea6 \u5236 \u7d04 \u3092\u5909\u66f4 \u3057,\u5e7e \u4f55\u5b66 \u7684 \u5236\u7d04 \u30bd\u30eb\u30d0\u304b \u3082\u3057 \u304f\u306f\u7a7a \u9593\u914d \u7f6e\u5236 \u7d04 \u30bd\u30eb \u30d0 \u306b\u4e0e \u3048,\u5236 \u7d04 \u5145 \u8db3\u30d7\n\u30ed\u30bb \u30b9 \u3092\u518d\u5ea6 \u884c \u3046.\u3053 \u306e \u3088 \u3046\u306b \u3057\u3066,\u652f \u63f4 \u30b7 \u30b9\u30c6 \u30e0 \u3068\u5bfe \u8a71 \u7684 \u306b\n\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u3092\u884c \u3044,\u6700 \u7d42 \u7684 \u306b\u6c42 \u3081 \u308b\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3 \u3092\u5f97 \u308b.\n5.\u7a7a \u9593 \u30c7\u30b6 \u30a4 \u30f3\u652f\u63f4 \u30b7\u30b9 \u30c6 \u30e0\u306e \u8a66\u4f5c\n5.1\u30b7 \u30b9\u30c6\u30e0 \u306e\u69cb \u6210\n\u524d\u7ae0\u3067 \u793a \u3057\u305f\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\u652f\u63f4 \u65b9 \u6cd5\u8ad6 \u306b\u57fa\u3065 \u3044\u3066,\u30b7 \u30b9 \u30c6 \u30e0\n\u3092\u8a66\u4f5c \u3057\u305f.\u30b7 \u30b9\u30c6 \u30e0\u306e\u5168 \u4f53 \u69cb \u6210 \u3092 \u56f314\u306b \u793a \u3059.\n\u672c \u30b7 \u30b9\u30c6 \u30e0\u306f,Sun Workstation\u4e0a \u3067C++\u3092 \u7528 \u3044 \u3066\u4f5c \u6210 \u3055\u308c \u3066\u304a \u308a,\u5927 \u304d \u304f\u5206\u3051 \u3066\u5236 \u7d04 \u8a2d\u5b9a \u30e6 \u30cb \u30c3 \u30c8,\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8,\u5236 \u7d04 \u30bd\u30eb\u30d0,\u30e6 \u30fc\u30b6 \u30a4\u30f3 \u30bf\u30d5 \u30a7\u30fc \u30b9,\u5e7e \u4f55 \u30a8 \u30f3\u30b8 \u30f3\u306e\n5\u3064 \u306e \u90e8\u5206 \u304b \u3089\u69cb \u6210 \u3055\u308c\u3066 \u3044 \u308b.\n\u7cbe \u5bc6 \u5de5 \u5b66 \u4f1a \u8a8cVo1.65,No.4,1999 529", + "5.2\u4eba \u5de5 \u885b \u661f\u8a2d \u8a08\u4e8b \u4f8b \u3078\u306e \u9069\u7528 5.2.1\u4eba \u5de5 \u885b \u661f\u8a2d \u8a08 \u306b\u304a \u3051 \u308b\u7a7a \u9593\u30c7 \u30b6 \u30a4 \u30f3\n\u672c \u7814 \u7a76\u306e\u5bfe \u8c61 \u3068\u3057\u3066\u3044 \u308b\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u3067 \u306f,\u8a2d \u8a08 \u5bfe \u8c61 \u306b\u5bfe\u3059 \u308b\u30bf\u30b9 \u30af\u3084\u4ed5 \u69d8 \u306a\u3069 \u306f,\u3053 \u306e\u6bb5 \u968e\u4ee5 \u524d\u306b \u6c7a\u5b9a \u3055\u308c \u3066\u3044 \u308b\u5834 \u5408\u304c \u307b \u3068\u3093\u3069 \u3067\u3042 \u308b.\u5177 \u4f53 \u7684\u306b \u4eba\u5de5\u885b \u661f\u8a2d \u8a08 \u306b\u304a \u3044\u3066 \u306f,\u305d \u308c \u3089\u306f \u30df \u30c3\u30b7 \u30e7\u30f3 \u3068\u547c \u3070\u308c \u308b \u3082\u306e \u3067,\u305d \u306e \u4eba\u5de5\u885b \u661f\u306e \u76ee\u7684(\u4f8b \u3048\u3070 \u6c17\n\u8c61\u89b3 \u6e2c\u3084\u901a \u4fe1 \u306a \u3069)\u3067 \u3042 \u308a,\u307e \u305f\u30da \u30a4\u30ed \u30fc \u30c9(\u6253 \u3061\u4e0a\u3052 \u306b\u7528 \u3044 \u308b \u30ed \u30b1 \u30c3 \u30c8\u306b\u683c \u7d0d \u3067 \u304d\u308b\u5927 \u304d \u3055)\u3067 \u3042 \u308a,\u30b3 \u30b9 \u30c8\u306a\u3069 \u3067 \u3042 \u308b\u3002 \u305d \u3057\u3066,\u3053 \u3046\u3057\u305f\u4e8b\u9805 \u304c\u6c7a \u5b9a \u3055\u308c \u305f\u5f8c \u306e\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u306e \u4f5c\u696d \u306f, \u4ee5\u4e0b \u306e\u901a \u308a\u3067 \u3042 \u308b.\n1.\u30df \u30c3\u30b7 \u30e7\u30f3\u306b \u3088\u3063\u3066 \u6c7a\u3081 \u3089\u308c \u308b\u642d\u8f09 \u30df \u30c3\u30b7 \u30e7\u30f3\u6a5f \u5668 \u306b\u4f9d\n\u5b58 \u3057\u3066,\u885b \u661f \u306e\u5916 \u5f62 \u3092\u4eee\u5b9a \u3059 \u308b.\n2.\u30df \u30c3\u30b7 \u30e7\u30f3\u9042\u884c \u306b\u5fc5 \u8981 \u306a\u6a5f \u80fd \u3092\u914d\u5206 \u3057\u3066,\u5404 \u30b3 \u30f3\u30dd\u30fc \u30cd\n\u30f3 \u30c8\u306e \u4ed5\u69d8 \u3092\u6c7a\u5b9a \u3057,\u6a5f \u5668\u5bf8 \u6cd5 \u3092\u4eee \u5b9a\u3059 \u308b.\n3.\u5404 \u30b3 \u30f3\u30dd \u30fc\u30cd \u30f3 \u30c8\u306e \u3046\u3061,\u5168 \u4f53 \u306e\u914d\u7f6e \u306b\u5f71 \u97ff \u3092\u4e0e \u3048 \u308b \u3082\n\u306e \u3092\u7279 \u5b9a\u3059 \u308b.\n4.3\u3067 \u8ff0\u3079 \u3089\u308c\u305f\u6a5f \u5668\u4ee5 \u5916\u306e\u6a5f \u5668\u642d \u8f09\u4f4d\u7f6e \u3092\u6982 \u7565\u6c7a\u5b9a \u3059 \u308b.\n5.\u691c \u8a0e \u306e\u7d50 \u679c,\u6700 \u3082\u9069 \u3057\u3066\u3044 \u308b \u3068\u601d \u308f\u308c \u308b\u521d \u671f \u30ec \u30a4\u30a2 \u30a6 \u30c8\n\u6848 \u3092\u9078\u629e \u3059 \u308b.\n\u3053 \u3046\u3057\u3066,\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u89e3\u304c \u5f97 \u3089\u308c \u305f\u5f8c \u306b\u306f,\u5404 \u6a5f \u5668\u3078 \u306e\u914d \u7dda \u8a2d\u8a08 \u3092\u5b9f \u65bd \u3057,\u7d44 \u7acb \u3066\u9806 \u5e8f,\u63a8 \u9032 \u7cfb\u7d71 \u7ba1 \u3068\u306e\u5e72 \u6e09\u3084 \u5404 \u30b3 \u30f3\u30dd \u30fc \u30cd\u30f3 \u30c8\u3078\u306e \u4f5c\u696d \u8005 \u306e\u63a5 \u8fd1\u6027 \u3092\u78ba \u8a8d\u3059 \u308b \u306a\u3069\u306e \u8a73\u7d30 \u8a2d\u8a08 \u306b\u79fb \u3063\u3066 \u3044 \u304f.\n5.2.2\u5b9f \u65bd\u4f8b \u4fe1 \u983c\u6027\u304c \u6700 \u3082\u91cd \u8981 \u306a\u9805 \u76ee\u3067\u3042 \u308b\u4eba\u5de5 \u885b\u661f \u306b\u304a \u3051 \u308b\u7a7a \u9593\u30c7\u30b6 \u30a4 \u30f3\u306e \u7279\u5fb4 \u3068\u3057\u3066 \u306f,\u642d \u8f09 \u30df\u30c3\u30b7 \u30e7\u30f3\u6a5f \u5668\u4ee5\u5916 \u306e \u30b3\u30f3\u30dd \u30fc\u30cd \u30f3 \u30c8 \u306f,\u307b \u3068\u3093 \u3069\u65e2 \u306b\u4f7f \u7528 \u3055\u308c \u305f\u5b9f\u7e3e \u306e\u3042 \u308b\u6a5f \u5668 \u3092 \u30ab\u30bf \u30ed\u30b0 \u306e \u4e2d\u304b \u3089\u9078 \u629e\u3059 \u308b\u5834 \u5408\u304c \u591a\u3044 \u3053 \u3068\u304c \u6319\u3052 \u3089\u308c \u308b.\u3057 \u304b \u3057,\u3053 \u3046\u3057\u305f\u7279 \u5fb4 \u3092\u6301 \u3064\u4eba \u5de5\u885b \u661f\u306e\u8a2d \u8a08 \u3067\u3042 \u308b\u304c,\u305d \u306e \u30b3\u30f3\u30dd \u30fc \u30cd\u30f3 \u30c8\u306e \u3046\u3061 \u3067 \u3082\u6bd4 \u8f03\u7684 \u5f62\u72b6 \u306e \u81ea\u7531\u5ea6 \u306e\u9ad8 \u3044,\u3064 \u307e \u308a\u65b0\u898f \u306b \u5f62\u72b6 \u306e\u8a2d\u8a08 \u3092\u884c\n\u3046\u5834 \u5408\u304c \u591a \u3044 \u3082\u306e \u3068 \u3057\u3066\u71c3\u6599 \u30bf\u30f3 \u30af\u304c \u3042 \u308b.\u3053 \u308c \u306f,\u5404 \u4eba\u5de5 \u885b\n\u661f \u3092\u65b0 \u898f \u306b\u8a2d\u8a08 \u3059 \u308b\u5834\u5408 \u306b \u305d\u306e\u90fd \u5ea6\u8a2d \u8a08\u3059 \u308b\u3053 \u3068\u304c \u591a \u304f,\u3053 \u306e \u3053 \u3068\u306b\u3088\u308b\u4fe1\u983c \u6027\u3078 \u306e\u5f71 \u97ff\u304c \u6bd4\u8f03 \u7684\u5c11 \u306a\u3044 \u3082\u308a\u3067 \u3042 \u308b.\u3088 \u3063\u3066, \u3053 \u3053\u3067 \u306f\u5404 \u30b3\u30f3\u30dd\u30fc \u30cd \u30f3 \u30c8\u306e \u914d\u7f6e \u30b9\u30da \u30fc\u30b9 \u306e\u6982\u5f62 \u3068\u305d\u306e\u914d \u7f6e \u3092\n\u6c42 \u3081,\u3053 \u308c \u3089\u306e \u30b3\u30f3\u30dd \u30fc \u30cd \u30f3 \u30c8\u306e\u914d \u7f6e \u30b9\u30da \u30fc\u30b9 \u3068\u8981\u6c42 \u3055\u308c \u3066 \u3044 \u308b\u71c3 \u6599 \u306e\u5bb9\u91cf \u304b \u3089\u642d\u8f09 \u3059 \u308b\u71c3\u6599 \u30bf\u30f3 \u30af\u306e\u6982\u7565 \u5f62\u72b6 \u3092\u6c42\u3081 \u308b\u5834 \u5408 \u306e \u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u3092\u5b9f \u65bd\u4f8b \u3068\u3059 \u308b.\u307e \u305f,\u30df \u30c3\u30b7 \u30e7\u30f3\u304a \u3088\u3073 \u6253 \u3061 \u4e0a\u3052 \u30ed\u30b1 \u30c3 \u30c8\u306e\u30da \u30a4\u30ed\u30fc \u30c9\u306b \u3088 \u308a\u4eee \u5b9a \u3055\u308c \u305f\u885b \u661f \u306e\u5916\u5f62 \u306f\u56f315 \u306b\u793a \u3059 \u3068\u304a \u308a\u3067 \u3042 \u308b.\n\u5e7e\u4f55 \u5b66 \u7684\u5236 \u7d04\n\u3053\u306e\u5b9f \u65bd \u4f8b \u306b\u304a\u3051 \u308b\u5e7e \u4f55 \u5b66\u7684 \u5236\u7d04 \u306f ,\u5177 \u4f53 \u7684 \u306b\u306f11\u500b \u306e \u4e3b \u8981 \u30b3 \u30f3\u30dd\u30fc \u30cd \u30f3 \u30c8\u306b \u3064\u3044\u3066 \u306f \u5404\u5fc5\u8981 \u8a2d\u7f6e \u30b9\u30da \u30fc \u30b9\u3067\u3042 \u308a,\u71c3 \u6599 \u30bf\u30f3 \u30af\u306b\u3064 \u3044\u3066 \u306f\u4f53\u7a4d(\u71c3 \u6599\u306e \u5bb9\u91cf)\u3067 \u3042 \u308b.\u4ee5 \u4e0b \u306b,\u4f8b \u3068 \u3057 \u3066\u71c3 \u6599 \u30bf \u30f3 \u30af,\u96fb \u5727\u5b89 \u5b9a\u88c5 \u7f6e \u304a \u3088\u3073 \u30d0 \u30c3\u30c6 \u30ea\u306b\u3064 \u3044 \u3066\u306e\u5236 \u7d04 \u3092\n\u793a\u3059.\n\u71c3 \u6599 \u30bf\u30f3 \u30af(\u5bb9 \u91cf)1Ol \u96fb\u5727 \u5b89\u5b9a \u88c5\u7f6e40.0\u00d730.0\u00d730.Ocm \u30d0 \u30c3\u30c6 \u30ea .50.0\u00d730.0\u00d740.Ocm\n\u7a7a \u9593 \u914d\u7f6e \u5236\u7d04\n\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u306f,\u4ee5 \u4e0b \u306b\u793a \u3059 \u3088 \u3046\u306a\u4e3b \u8981 \u30b3 \u30f3\u30dd\u30fc \u30cd\u30f3 \u30c8\u9593\u306b\n\u6c42 \u3081 \u3089\u308c \u308b,\u914d \u7f6e \u306b\u95a2\u3059 \u308b\u5236\u7d04 \u3067 \u3042 \u308b.\n\u25cf\u901a \u4fe1 \u7cfb \u2190 \u2192 \u96fb \u6e90 \u7cfb \u306f \u8fd1 \u304f\u306b(\u30b3 \u30fc \u30c9\u306f \u306a \u308b\u3079 \u304f\u77ed \u304f\n\u3059 \u308b)\n\u25cf\u96fb\u6e90 \u7cfb \u2190 \u2192 \u71c3\u6599 \u30bf\u30f3 \u30af\u306f\u8fd1 \u304f\u306b(\u96fb \u6e90\u7cfb\u304c \u767a \u3059 \u308b\u71b1 \u306b\n\u3088\u308b\u71c3\u6599 \u306e \u51cd \u7d50\u9632 \u6b62\u306e \u305f \u3081)\n\u25cf\u540c \u3058\u7cfb\u7d71 \u306e \u3082\u306e\u306f\u8fd1 \u304f\u306b(\u63a5 \u7d9a \u30b1\u30fc\u30d6 \u30eb\u3092\u77ed \u304f\u3059 \u308b\u305f\u3081)\n\u25cf\u4eba\u5de5\u885b \u661f \u306e\u5730 \u7403\u9762 \u304a \u3088\u3073 \u30df\u30c3\u30b7 \u30e7\u30f3\u6a5f\u5668 \u3092\u642d\u8f09 \u3059 \u308b\u9762 \u306b\n\u306f,\u96fb \u6e90\u7cfb \u304a \u3088\u3073 \u59ff \u52e2\u5236 \u5fa1\u7cfb \u306a\u3069\u306e \u767a\u71b1 \u3059 \u308b\u6a5f \u5668 \u306f\u914d\u7f6e \u3067 \u304d\u306a \u3044(\u653e \u71b1 \u9762 \u3068\u3057\u3066\u9069 \u3057\u3066 \u3044 \u306a \u3044\u305f\u3081)\n\u4ee5\u4e0a \u306e\u6761 \u4ef6 \u3092\u4e0e \u3048 \u3089\u308c \u305f \u5f8c,\u4e0a \u8ff0 \u3057\u305f\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u306e\u4f5c \u696d\u5185\n\u5bb9 \u306b\u5f93 \u3063\u3066\u7a7a \u9593 \u30c7 \u30b6 \u30a4\u30f3 \u3092\u9032 \u3081 \u308b.\n\u521d \u671f \u30ec \u30a4\u30a2 \u30a6 \u30c8\u6848 \u3092\u9078\u629e \u3059 \u308b\n\u5e7e\u4f55 \u5b66\u7684 \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088\u3063\u3066,\u6a5f \u80fd\u8981 \u7d20\u306e\u6982 \u7565 \u5f62\u72b6 \u3092\u6c42 \u3081\u305f\n\u5f8c,\u7a7a \u9593\u914d\u7f6e \u5236\u7d04 \u30bd\u30eb\u30d0 \u306b \u3088 \u3063\u3066,\u8981 \u6c42 \u3055\u308c \u305f \u30b3\u30f3\u30dd \u30fc\u30cd \u30f3 \u30c8 \u306e\u7a7a \u9593\u914d\u7f6e \u306e \u6982\u7565 \u3092\u751f\u6210 \u3059 \u308b.\u56f316\u306f \u305d\u306e \u7a7a \u9593\u914d\u7f6e \u30bd\u30eb\u30d0 \u306e \u51fa\u529b \u89e3\u306e \u5177\u4f53 \u4f8b \u3067\u3042 \u308b.\u76f4 \u7dda \u3067\u7d50\u3070 \u308c \u3066 \u3044 \u308b\u6a5f \u80fd\u8981 \u7d20 \u306f\u305d\u308c\u305e \u308c \u306b\u76f8 \u5bfe \u7684\u4f4d \u7f6e \u306e\u5236 \u7d04\u95a2 \u4fc2\u304c \u3042 \u308b \u3053 \u3068\u3092\u793a \u3057\u3066 \u3044 \u308b.\nsolver\n\u7d9a \u3044 \u3066,\u5e7e \u4f55\u5b66 \u7684\u5236 \u7d04 \u30bd\u30eb\u30d0 \u3068\u7a7a \u9593\u914d\u7f6e \u30bd\u30eb\u30d0 \u306b \u3088\u308b\u6982 \u7565\u306e \u8a2d\u8a08 \u89e3 \u306e\u77db\u76fe \u70b9 \u3092\u8abf \u6574\u3059 \u308b \u3053 \u3068\u306b \u3088\u3063\u3066\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3\u306e \u751f\u6210 \u3092\u8a66 \u307f \u308b.\u56f317\u306b \u305d \u306e\u904e \u7a0b \u3092\u793a \u3059.\u3053 \u306e \u9593 \u306b,\u5e72 \u6e09 \u3057\u305f \u30b3 \u30f3 \u30dd\u30fc \u30cd \u30f3 \u30c8\u306e\u914d \u7f6e \u30b9\u30da \u30fc \u30b9\u306e\u5f62 \u72b6 \u751f\u6210 \u30eb \u30fc\u30eb\u304c \u5909\u66f4 \u3055\u308c,\u305d \u308c \u3068\u540c\u6642 \u306b\u5f62 \u72b6 \u306e \u4e2d\u5fc3 \u4f4d \u7f6e \u306e\u79fb \u52d5 \u304c\u884c \u308f\u308c \u308b.\u5177 \u4f53 \u7684\u306b \u306f,3 .2 \u7bc0 \u306b \u304a\u3044 \u3066\u8ff0\u3079 \u305f \u751f\u6210 \u30eb \u30fc\u30eb\u306e\u7f6e \u304d\u63db \u3048\u306b \u3088\u308b\u5e72\u6e09\u89e3 \u6d88\u306e\u6226 \u7565 \u3092(1),(2),(3)\u306e \u9806 \u306b\u3059 \u3079 \u3066 \u8a66 \u307f,\u540c \u6642 \u306b\u5e72 \u6e09 \u3057\u305f\u90e8 \u5206 \u306e\u4f53 \u7a4d \u306b\u5f93 \u3063\u3066 \u4e2d\u5fc3\u4f4d \u7f6e\u304c \u79fb \u52d5 \u3055\u308c \u305f.\n\u3053\u306e \u3088 \u3046\u306b \u3057\u3066,\u7a7a \u9593 \u30c7 \u30b6 \u30a4\u30f3\u306e2\u3064 \u306e \u5074\u9762 \u306b \u3064\u3044 \u3066 \u540c\u6642\n\u306b\u8abf\u6574 \u3057\u306a\u304c \u3089\u5f62\u72b6 \u3092\u751f\u6210 \u3055\u305b,\u305d \u306e \u751f \u6210\u304c \u7d42\u4e86 \u3057\u305f\u6bb5 \u968e\u3067 \u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u3092\u5f97 \u308b.\u56f318\u306b,\u305d \u306e\u751f \u6210\u89e3 \u306e\u6c34 \u5e73 \u65b9\u5411 \u306e\u65ad \u9762 \u3068\u5782 \u76f4\u65b9 \u5411 \u306e\u65ad \u9762 \u3092\u793a \u3057,\u6c42 \u3081 \u308b\u71c3 \u6599 \u30bf \u30f3 \u30af\u306e\u6982 \u5f62 \u3092 \u56f319\u306b \u793a \u3059.\n530\u7cbe \u5bc6 \u5de5\u5b66 \u4f1a\u8a8cVol,65,No.4,1999", + "\u6b21 \u306b,\u7a7a \u9593\u30c7\u30b6 \u30a4\u30f3\u30e6 \u30cb \u30c3 \u30c8\u304c \u793a \u3057\u305f,\u4ed6 \u306e\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u306e \u30d0 \u30ea\u30a8 \u30fc \u30b7 \u30e7\u30f3\u306b\u3064 \u3044 \u3066,\u56f320\u306b \u65ad\u9762 \u56f3 \u3092\u793a \u3059.\u3053 \u3053\u3067 \u6bd4 \u8f03\u306e \u305f\u3081,\u5404 \u7a7a\u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u306b\u304a\u3051 \u308b\u305d \u308c\u305e \u308c\u306e \u5236\u7d04 \u306b\u5bfe \u3059 \u308b \u8a55\u4fa1 \u5024,\u304a \u3088\u3073\u71c3 \u6599 \u30bf\u30f3 \u30af\u306e\u7e26,\u6a2a,\u9ad8 \u3055\u306e\u6700 \u5927 \u5024 \u306b\u95a2 \u3059 \u308b\u6570 \u5024 \u3092\u88682\u306b \u793a\u3059.\n\u3053\u306e \u3088 \u3046\u306b \u3057\u3066\u5f97 \u3089\u308c \u305f\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u6848 \u306f,\u56f3 \u306b\u793a \u3057\u305f \u3088 \u3046\n\u306b,\u591a \u69d8 \u306a\u521d\u671f \u30ec \u30a4\u30a2\u30a6 \u30c8\u6848 \u3092\u751f \u6210 \u3057\u3066 \u3044 \u308b\u3053 \u3068\u304c \u89b3 \u5bdf \u3055\u308c \u308b. \u307e\u305f,\u71c3 \u6599 \u30bf\u30f3 \u30af\u306e\u5f62 \u72b6 \u306b \u304a\u3044 \u3066 \u3082,\u8981 \u6c42 \u3055\u308c \u305f\u5bb9\u91cf \u3092\u6301 \u3061, \u4ed6 \u306e \u30b3 \u30f3\u30dd\u30fc \u30cd \u30f3 \u30c8\u306e\u914d \u7f6e \u30b9\u30da \u30fc\u30b9 \u3068\u5e72\u6e09 \u3057\u306a\u3044\u5f62 \u72b6\u304c \u6c42 \u3081 \u3089 \u308c \u3066 \u3044 \u308b.\u305d \u3057\u3066,\u751f \u6210 \u3055\u308c \u305f\u71c3 \u6599 \u30bf\u30f3 \u30af\u306f\u5236 \u7d04 \u3068\u3057\u3066\u4e0e \u3048 \u3089 \u308c \u305f\u5bb9 \u91cf \u3092\u304a \u304a \u3080\u306d\u6e80 \u305f \u3057,\u304b \u3064 \u591a\u69d8 \u306a\u5f62 \u72b6 \u3092 \u3057\u3066\u3044 \u308b \u3053 \u3068\u304c \u78ba \u8a8d\u3067 \u304d\u308b.\u3057 \u304b \u3057,\u4e00 \u65b9\u3067\u71c3 \u6599 \u30bf\u30f3 \u30af\u306e\u5185 \u90e8\u5727 \u529b \u3092\u8003\u616e \u3057\u305f \u5834 \u5408 \u306b \u9069\u5f53 \u3067 \u306a\u3044 \u3088 \u3046\u306a\u5f62\u72b6 \u3082\u751f \u6210 \u3055\u308c \u3066 \u3044 \u308b.\n\u8a2d \u8a08 \u8005\u306f,\u3053 \u3046\u3057\u305f\u591a\u69d8 \u306a\u7a7a \u9593\u30c7 \u30b6 \u30a4\u30f3\u89e3 \u3092\u691c \u8a0e \u3057\u305f\u5f8c,\u4ed6\n\u306e\u5236 \u7d04 \u306a\u3069 \u3092\u8003\u616e \u306b\u5165\u308c,\u9069 \u5f53\u306a \u3082\u306e \u3068\u8003 \u3048 \u3089\u308c \u308b\u89e3 \u3092\u9078\u629e \u3057,\n\u8a73 \u7d30\u8a2d \u8a08\u3078 \u3068\u79fb \u884c\u3059 \u308b.\n\u672c\u8ad6\u6587\u3067\u306f,\u7a7a \u9593\u30c7\u30b6\u30a4\u30f3\u306e2\u3064 \u306e\u5074\u9762\u3067\u3042\u308b,\u6a5f \u80fd\u8981\u7d20 \u306e3\u6b21 \u5143\u5f62\u72b6\u3068,\u305d \u306e\u7a7a\u9593\u7684\u914d\u7f6e\u3092\u540c\u3058\u67a0\u7d44\u306e\u4e2d\u3067\u6c7a\u5b9a\u3059\u308b \u305f\u3081\u306b,\u5f62 \u72b6\u8868\u73fe\u306b\u591a\u69d8\u6027\u3092\u6301\u305f\u305b\u305f\u9069\u5fdc\u6210\u9577\u578b\u5f62\u72b6\u8868\u73fe\u65b9\u6cd5 \u3092\u63d0\u6848\u3057\u305f.\u305d \u3057\u3066,\u672c \u5f62\u72b6\u8868\u73fe\u3092\u5fdc\u7528\u3057\u305f\u7a7a\u9593\u30c7\u30b6 \u30a4\u30f3\u306e\u652f \u63f4\u30b7\u30b9\u30c6\u30e0\u3092\u4f5c\u6210\u3057,\u4eba \u5de5\u885b\u661f\u8a2d\u8a08\u306b\u304a\u3051\u308b\u7a7a\u9593\u30c7\u30b6\u30a4\u30f3\u3092\u884c \u3044,\u6a5f \u80fd\u8981\u7d20\u306e3\u6b21 \u5143\u5f62\u72b6\u3068,\u305d \u306e\u7a7a\u9593\u7684\u914d\u7f6e\u3092\u540c\u3058\u67a0\u7d44\u306e\n\u4e2d\u3067\u6c7a\u5b9a\u3059\u308b\u65b9\u6cd5\u306e\u5b9f\u65bd\u4f8b\u3092\u793a\u3057\u305f.\u305d \u306e\u7d50\u679c,3\u6b21 \u5143\u5f62\u72b6 \u3068 \u7a7a\u9593\u7684\u914d\u7f6e\u304c\u540c\u3058\u67a0\u7d44\u306e\u4e2d\u3067\u53d6 \u308a\u6271\u3048,\u307e \u305f\u591a\u69d8\u306a\u7a7a\u9593\u30c7\u30b6\u30a4 \u30f3\u89e3\u304c\u5f97\u3089\u308c\u308b\u3053\u3068\u3092\u53ef\u80fd\u3068\u3057\u305f\u305f\u3081,\u672c \u65b9\u6cd5\u8ad6\u306e\u6709\u52b9\u6027\u304c\u793a \u3055\u308c\u305f.\n\u307e\u305f,\u4eca \u5f8c\u306e\u7814\u7a76\u306e\u8ab2\u984c\u3068\u3057\u3066\u306f\u4ee5\u4e0b\u306e\u3053\u3068\u304c\u8003\u3048\u3089\u308c\u308b.\n\u25cf\u751f\u7269\u306b\u6bd4\u8f03\u3057\u305f\u5834\u5408\u306e,\u3055 \u3089\u306a\u308b\u9069\u5fdc\u6210\u9577\u578b\u5f62\u72b6\u8868\u73fe\u306e\n\u9069\u5fdc\u6027\n\u25cf\u81ea\u5f8b\u7684\u306b\u5f62\u72b6\u306e\u4f4d\u7f6e\u3092\u79fb\u52d5\u3055\u305b\u308b\u3053\u3068\u306b\u3088\u308b,3\u3064 \u306e\u7a7a\n\u9593\u30c7\u30b6\u30a4\u30f3\u30bd\u30eb\u30d0\u306e\u7d71\u5408\n\u25cf\u672c\u65b9\u6cd5\u8ad6\u306e\u7406\u8ad6\u7684\u7acb\u5834\u304b\u3089\u306e\u8a73\u7d30\u306a\u691c\u8a0e\n\u53c2 \u8003 \u6587 \u732e\n1) R. Smith, S. Warrington and F. Mill: Shape Representation for Optimization, Proc. 1st IEE/IEEE Int. Conf. Genetic Algorithms in Engineering Systems: Innovations and Applications GALESIA '95, Sheffield, England,(1995)112. 2) S. Szykman and J. Cagan: Automated Generation of Optimally Directed Three Dimensional Component Layouts,\nDE-Vol.65-1, In Advances in Design Automation - vol. 1, ASME,(1993).\n3)\u9577 \u5742 \u4e00\u90ce,\u5c71 \u5cb8 \u6df3,\u7530 \u6d66 \u4fca\u6625:\u610f \u5320 \u30c7 \u30b6 \u30a4 \u30f3\u306e\u305f \u3081\u306e3D\u5f62 \u72b6\u30e2\n\u30c7 \u30eb(\u7b2c2\u5831)\u4e00 \u751f\u6210 \u30eb \u30fc\u30eb \u306b\u6ce8 \u76ee\u3057 \u305f\u5f62\u72b6 \u7279 \u5fb4 \u306e\u8868 \u73fe \u6cd5\u4e00,\u7cbe \u5bc6 \u5de5 \u5b66 \u4f1a\u8a8c,63,2,(1997)193.\n4) G. Pahl and W. Beitz: Engineering Design: A Systematic Approach, Springer-Verlag, London,(1988). 5) A. C. Thornton and A. L. Johnson: CADET: A Software Support Tool for Constraint Processes in Embodiment Design, Res. Eng. Design,8,(1996)1. 6) D. E. Goldberg: Genetic Algorithms in Search, Optimization & Machine Learning, Addison-Wesley, Readings,MA(1989). 7) C. Brown: Fast Display of Well-tessellated Surfaces, Computer and Graphics,4,4,(1979)77. 8) S. F. Smith: A Learning System Based on Genetic Algorithms, PhD Dissertation, University of Pittsburgh,(1980).\n9) V. Schnecke and O. Vornberger: A Genetic Algorithm for VLSI Physical Design Automation, Proc. 2nd Int. Conf. Adaptive Computing in Engineering Design and Control, ACEDC '96, University of Plymouth, I. C. Parmee (ed. ),(1996)53.\n\u7cbe \u5bc6 \u5de5 \u5b66 \u4f1a \u8a8cVol,65,No.4,1999 531" + ] + }, + { + "image_filename": "designv8_17_0002886_nal_Thesis_Suren.pdf-Figure4.2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002886_nal_Thesis_Suren.pdf-Figure4.2-1.png", + "caption": "Figure 4.2: Miniature crack propagation test specimen design (all dimensions are in mm) a) CT specimen design (thickness = 1 mm) b) Fatigue crack propagation fixtures with front and back microscopes to measure crack length.", + "texts": [ + " Understanding the extent of damage in SGI microstructure, the sample was re-tested for additional load cycles of 50,000, or 30,000, or 20,000. The sample was again studied under OM to observe cracks initiation and microcracks propagation before it was reloaded. The re-testing and OM observation were repeated until sufficient cracks were initiated with clear microcrack growth. The sample was finally studied thoroughly in the SEM to have a clear view of the crack initiation sites and mechanisms. The miniature Compact Tension (CT) specimen, as illustrated in Figure 4.2 a) was designed considering ASTM standard E647 [160] for the FCP tests. ASTM standard E647 provides a comprehensive guideline for the FCP test. The CT specimens were metallographically polished before the test for clear visualization of cracks. Load ratios of R = 0.1 and 0.4 were selected, and an initial stress intensity factor range (\u2206Kstart) of 13 MPa \u221a m was used based on FCP test results reported in previous work [161]. Displacement is measured with the in-built displacement sensor. For the FCP studies, two intermediate crack sizes were considered; short Nanyang Technological University Singapore Ch. 4. Tensile and Fatigue Damage Mechanisms in SGI 4.1. Test Specimens and Methods Page : 105 crack size with the crack tip still in the stable crack region was considered short intermediate crack, and the crack with the crack tip approaching the unstable region was considered long intermediate crack. During the test, the crack was observed and measured by OM placed on two faces of the specimen (Figure 4.2 b)). The lengths of cracks on both faces were measured during the test. The average crack length and the applied load were used in Eq. 4.1 to evaluate stress intensity factor (\u2206K). \u2206K = \u2206P B \u221a W (2 + \u03b1) (1\u2212 \u03b1)3/2 (0.886 + 4.64\u03b1\u2212 13.32\u03b12 + 14.72\u03b13 \u2212 5.6\u03b14) (4.1) where, \u03b1 = a/W, a is the average crack length \u2206P is the applied load range B is the thickness of the CT specimen W is the characteristic length of the CT specimen The calculated stress intensity factors were plotted against fatigue crack growth rate (da/dN)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002970_cle_download_643_621-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002970_cle_download_643_621-Figure9-1.png", + "caption": "Figure 9. Tool stress contour at second punch evaluated by finite element method for different sizes of corner fillet.", + "texts": [ + " This was attributed to the continuously increasing load in the final forming operation in order to fill the die corners. Accordingly, the largest size of fillet only required the lowest forming load rather than those of the smaller sizes. According to Figure 8, it certified that the permanent displacement was not proportional to the size of fillet, but increased as the size of fillet decreased. The highest and lowest values for the permanent displacement were attained as 0.0702 mm and 0.0662 mm when Rp were 0.1 mm and 2.5 mm, respectively. In addition, by referring to Figure 9, it shows that the highest value for maximum stress was 1600 MPa when Rp was at 0.1 mm and the lowest value for maximum stress was 1450 MPa as Rp approached 2.5 mm. significantly, the maximum stresses were observed at the corner of the punch, but not at the top surface. It was observed that the metal flow was mainly influenced by the tool geometry, in which provided the effects to the force constraints of the process, stress concentration and permanent displacement on the tool. Furthermore, it was observed that the geometry of the tool influenced the deformation of the workpieces, given that the fillet corner increased, die wear would decrease and hence the fatigue life increased, since a small corner would introduce high stress concentration and permanent displacement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure43-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure43-1.png", + "caption": "Figure 43: Y axis deformation of pantograph design 2.", + "texts": [], + "surrounding_texts": [ + "The figures below show the deformation plots for the pantograph designs. Figure 44: Y axis deformation of design 3. Figure 45: Y axis deformation of final design. 36" + ] + }, + { + "image_filename": "designv8_17_0002044_8948470_09078103.pdf-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002044_8948470_09078103.pdf-Figure20-1.png", + "caption": "FIGURE 20. Thermal field distribution of the conductor rotors (a) the temperature of the axial conductor rotor (b) the temperature of the radial conductor rotor.", + "texts": [ + " The eddy current effect is generated in the conductor rotor. The resistance and eddy current increase together with the thickness of the conductor rotor, which increases the torque and temperature. Therefore, the maximum temperature of the device must exist in the conductor rotor. If the thickness of the copper rotor continues to increase after reaching the skin depth, the resistance will increase and the temperature will continue to rise, but the torque will not increase, or even decrease due to the thermal effect of eddy current loss. Fig. 20 and Fig. 21 (a) show the temperature distribution of the axial and radial conductor rotors under the rated load. It is shown that the variation of temperature with the thickness of VOLUME 8, 2020 78375 the axial and radial conductor rotors is consistent with the above conclusions. The thickness of the conductor rotor will also effect the temperature rise of the permanent magnet. If the temperature is high excessively, the permanent magnet will be demagnetized permanently. The temperature distribution of the permanent magnet and the influence of the conductor rotor thickness on permanent magnets (PMS) temperature are shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure54-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure54-1.png", + "caption": "Figure 54 P-POD Mk. IV Door Hinge Stress", + "texts": [ + " IV Door were roughly one half those of the previous design, which was considered to be a success. The stress of the part exhibited a slight decrease in stress at the high stress point of the door, on the inner edge of the inner hinge. Coupled with the allowable stress inscrease due to the removal of the PTFE baking process for the coating, this part exhibits a significantly higher margin of safety than the previous design. The resulting analysis stress plots are shown below in Figure 53. Additionally, a hinge closeup is shown in Figure 54. The Page 68 hinge exhibits significant stress, but shows up light blue instead of red because of some severe stress elements near boundary conditions. The Margin of Safety at the maximum stress point depicted was 0.06. This is significantly lower than other components of the P-POD, but the previous design exhibited a negative margin, so this was considered a Page 69 significant improvement. The changes to the door resulted in a 18 gram mass increase, which was worth the improvement. P-POD Mk. IV Access Port Covers The access port covers were also redesigned to accommodate the EMI Gasket, as well as the changes to the mounting method described in Chapter 2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002255_40544-019-0269-3.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002255_40544-019-0269-3.pdf-Figure3-1.png", + "caption": "Fig. 3 Photograph of the tribo-meter and schematic of wear test.", + "texts": [ + " Generally, there was no cavitation or agglomeration on the surface, which indicated the even \u2223www.Springer.com/journal/40544 | Friction http://friction.tsinghuajournals.com distribution of fillers into the PI matrix. Before tribotests, the PI composites were polished by metallographic sandpaper to a roughness below 0.1 \u03bcm. The friction and wear tests involving sliding against a Si3N4 ball were evaluated on a ball-on-disk tribometer (HSR-2M, China) referred to the ASTM G99-04 Pin-on-Disk pattern at room temperature. The schematic diagram of the friction couple is shown in Fig. 3. The Sample Tensile strength (MPa) Elongation percentage (%) Elastic modulus (GPa) Electrical resistance PI-1 273.4 5.3 13.47 300 \u2126\u2013400 \u2126 | https://mc03.manuscriptcentral.com/friction Si3N4 ball is 4 mm in diameter. Before each test, the Si3N4 ball and the block samples were cleaned with cotton dipped in acetone. The wear volume was computed from the cross-sectional worn area multiplied by the circumference of the wear track and calculated using Eq. (1). The specific wear rate K (mm3/N\u00b7m) was calculated from the volume loss using Eq" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000482_119_3_119_3_282__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000482_119_3_119_3_282__pdf-Figure1-1.png", + "caption": "Fig. 1. Axial gap type self-bearing motor", + "texts": [], + "surrounding_texts": [ + "\u8ad6\u6587 \u6c38\u4e45\u78c1\u77f3 \u30a2\u30ad \u30b7\u30e3\u30eb\u578b \u30bb\u30eb \u30d5\u30d9\u30a2 \u30ea\u30f3\u30b0 \u30e2 \u30fc\u30bf\u306e \u30a2\u30ad\u30b7 \u30e3\u30eb \u65b9\u5411\n\u529b \u3068 \u30c8\u30eb \u30af\u7279\u6027 \u304a\u3088\u3073 \u305d\u306e\u5236\u5fa1\n\u4e3b \u54e1 \u4e0a \u91ce \u54f2(\u8328 \u57ce\u5927\u5b66\u5927\u5b66\u9662)\n\u6b63 \u54e1 \u5ca1 \u7530 \u990a \u4e8c(\u8328 \u57ce\u5927\u5b66\u30a8\u5b66\u90e8)\nCharacteristics of Axial Force and Rotating Torque and their Control of PM type Axial Gap\nSelf-bearing Motor\nSatoshi Ueno, Member, Yohji Okada, Member (Ibaraki University)\nThis paper introduces an axial gap type self-bearing motor . It is intended for a disc type flat motor to\nhave both functions of rotation and axial position control . This motor is simple in construction and requires a simple control system. A permanent magnet type motor is analyzed theoretically and tested experimen tally. The torque characteristics of the tested motor is measured with the various axial force and air gap . Independent control of the axial force and torque is introduced for the servo motor control and synchronous motor control. The results are showing high possibility of the proposed motor and control system .\n\u30ad\u30fc \u30ef \u30fc \u30c9:\u78c1 \u6c17 \u6d6e \u4e0a,\u6c38 \u4e45\u78c1 \u77f3 \u30e2 \u30fc \u30bf,\u78c1 \u6c17\u8ef8 \u53d7,\u30bb \u30eb \u30d5\u30d9 \u30a2 \u30ea\u30f3\u30b0 \u30e2 \u30fc \u30bf,\u6d6e \u4e0a \u5236 \u5fa1\n1.\u306f \u3058 \u3081 \u306b\n\u8fd1\u5e74,\u5de5 \u4f5c \u6a5f\u68b0,\u30bf \u30fc\u30dc \u5206 \u5b50\u30dd \u30f3\u30d7,\u30d5 \u30e9 \u30a4\u30db \u30a4\u30fc\u30eb \u306a \u3069\u306e \u9ad8\u901f \u56de\u8ee2 \u3059 \u308b\u8ef8 \u306e \u652f\u6301 \u306b,\u78c1 \u6c17 \u8ef8\u53d7 \u304c\u6b21 \u7b2c \u306b\u4f7f \u7528 \u3055\u308c \u308b \u3088 \u3046\u306b\u306a \u3063\u3066\u3044 \u308b(\u03b7\u3002\u78c1\u6c17 \u8ef8\u53d7 \u306f ,\u78c1 \u6c17 \u7684 \u306a\u529b \u306b \u3088\u3063\u3066 \u56de\u8ee2\u4f53 \u3092\u975e\u63a5 \u89e6\u3067 \u4fdd \u6301\u3059 \u308b\u306e \u3067,\u6469 \u64e6 \u30fb\u6469\u8017 \u304c \u306a \u304f,\u6f64 \u6ed1\n\u6cb9\u304c \u4e0d \u5fc5 \u8981 \u3068\u306a \u308a,\u771f \u7a7a \u4e2d\u306a \u3069\u306e\u7279 \u6b8a\u74b0 \u5883 \u4e0b\u3067 \u306e\u4f7f \u7528 \u306b\u9069\n\u3057\u3066 \u3044\u308b \u3002 \u3053\u308c \u3089\u306e\u5fdc \u7528\u306e \u4e2d \u306b\u306f,\u56de \u8ee2 \u529b \u3092\u4e0e \u3048 \u308b\u30e2 \u30fc \u30bf \u304c\u5fc5 \u8981 \u306a \u3082\u306e\u304c \u3042 \u308a,\u30e2 \u30fc \u30bf\u306e \u4e21\u7aef \u3092\u78c1 \u6c17\u8ef8 \u53d7 \u306b \u3088 \u308a\u652f \u6301\n\u3059 \u308b\u69cb \u9020 \u304c\u591a \u3044 \u3002 \u3053\u306e \u305f\u3081,\u88c5 \u7f6e\u304c \u5927\u578b \u5316\u3059 \u308b,\u8ef8 \u9577\u306e\u5897 \u52a0 \u306b \u3088\u3063\u3066\u5f3e \u6027 \u30e2\u30fc \u30c9\u306b\u60aa\u5f71 \u97ff \u3092\u4e0e \u3048 \u308b \u3068\u3044 \u3063\u305f\u554f \u984c\u304c \u3042 \u308b\u3002 \u305d \u3053\u3067,\u78c1 \u6c17 \u8ef8\u53d7 \u3068\u4ea4\u6d41 \u30e2 \u30fc \u30bf\u306e \u69cb\u9020 \u304c \u985e\u4f3c \u3057\u3066\u3044 \u308b \u3053 \u3068\u306b\u6ce8 \u76ee \u3057,\u3053 \u308c \u3089 \u3092\u4e00\u4f53 \u5316 \u3057\u305f \u30e9\u30b8 \u30a2\u30eb\u578b \u30e2 \u30fc \u30bf\u304c \u63d0\n\u6848 \u3055\u308c \u305f(2)\uff5e(4)\u3002\u3053\u306e\u30e2 \u30fc \u30bf\u306f \u7269\u30ed\u30fc \u30bf\u306e \u30e9\u30b8 \u30a2\u30eb\u65b9 \u5411\u306e\u4f4d \u7f6e\u5236 \u5fa1 \u3068 \u56de\u8ee2 \u30c8\u30eb \u30af\u306e\u767a \u751f \u3092\u5358 \u4e00\u306e \u30b9 \u30c6\u30fc \u30bf\u3067 \u884c \u3048 \u308b \u3088 \u3046 \u306b \u3057\u305f \u3082\u306e \u3067\u3042 \u308b\u3002 \u3053\u306e \u3088 \u3046\u306a \u30e2 \u30fc \u30bf\u306f,\u5f93 \u6765,\u6d6e \u4e0a\u30e2 \u30fc \u30bf\u3042 \u308b\u3044 \u306f\u30d9 \u30a2 \u30ea\u30f3\u30b0 \u30ec\u30b9\u30e2 \u30fc \u30bf\u3068\u547c\u3070 \u308c \u3066\u3044 \u308b\u304c ,\u30e2 \u30fc \u30bf\u81ea\u8eab\u304c \u78c1 \u6c17\u8ef8 \u53d7 \u306e\u6a5f \u80fd \u3092\u6301 \u3063 \u3066\u3044 \u308b \u3068\u3044 \u3046\u610f\u5473 \u3092\u660e\u78ba \u306b\n\u3059 \u308b\u305f\u3081,\u672c \u8ad6 \u6587\u3067 \u306f,\u30bb \u30eb \u30d5\u30d9 \u30a2 \u30ea\u30f3\u30b0\u30e2 \u30fc \u30bf \u3068\u547c \u3076 \u3002\n\u30e9\u30b8 \u30a2\u30eb\u578b \u30bb \u30eb \u30d5\u30d9 \u30a2 \u30ea\u30f3\u30b0 \u30e2 \u30fc \u30bf\u3067\u306f ,\u30e9 \u30b8 \u30a2\u30eb \u65b9 \u5411\n\u529b \u3092\u767a \u751f \u3055\u305b \u308b \u305f\u3081 \u306b,\u30e2 \u30fc \u30bf \u30ea\u30f3\u30b0\u78c1 \u754c \u306b\u52a0 \u3048\u3066 \u00b12\u6975 \u306e \u56de\u8ee2 \u78c1\u754c \u3092\u30b9 \u30c6\u30fc \u30bf\u3067\u767a \u751f \u3055\u305b \u306a\u3051 \u308c\u3070 \u306a \u3089\u305a,\u30b9 \u30c6\u30fc \u30bf\u306e\u69cb \u9020 \u3084 \u5236\u5fa1 \u304c\u8907 \u96d1 \u306b \u306a \u308b\u554f\u984c \u304c \u3042 \u308b\u3002 \u307e\u305f ,\u56de \u8ee2\u578b \u4eba \u5de5 \u5fc3\u81d3 \u7528 \u8840 \u6db2\u30dd \u30f3\u30d7 \u306b\u78c1 \u6c17 \u8ef8\u53d7 \u3084 \u30bb\u30eb \u30d5\u30d9 \u30a2 \u30ea\u30f3\u30b0 \u30e2 \u30fc \u30bf \u3092\u5fdc\u7528 \u3059 \u308b\u8a66 \u307f\u304c \u884c \u308f \u308c \u3066 \u3044 \u308b\u304c(4)\uff5e(6),\u5c0f \u578b \u5316 \u3084\u4fe1 \u983c\u6027\n\u306e \u305f \u3081\u306b \u306f,\u3067 \u304d \u308b\u3060\u3051 \u7c21\u5358 \u306a\u69cb \u9020 \u3067\u975e \u63a5\u89e6 \u652f \u6301 \u3068\u99c6\u52d5\u304c\n\u884c \u3048 \u308b \u3053 \u3068\u304c \u671b \u307e \u3057\u3044\u3002\n\u7269 \u4f53 \u3092\u78c1 \u6c17 \u306b \u3088 \u308a\u652f\u6301 \u3059 \u308b\u5834 \u5408,\u30a2 \u30fc \u30f3\u30b7 \u30e7\u30a6\u306e\u5b9a\u7406 \u3088 \u308a\u78c1 \u77f3 \u3092\u3069 \u306e \u3088 \u3046\u306b\u914d\u7f6e \u3057\u3066 \u3082,\u5168 \u8ef8 \u5b89 \u5b9a \u306a\u6d6e\u4e0a \u306f\u5b9f\u73fe\u3067 \u304d\u306a\u3044\u3002 \u3057\u304b \u3057,\u4e00 \u8ef8 \u3055\u3048 \u5236\u5fa1 \u3092\u884c \u3048 \u3070\u5b89 \u5b9a \u306a \u6d6e\u4e0a \u3092\u5b9f\u73fe \u3067 \u304d \u308b(7)(8)\u3002\u305d \u3053\u3067\u4ee5 \u524d \u306b,\u7c21 \u5358 \u306a\u69cb\u9020 \u3068\u5236 \u5fa1 \u3067 ,\u56de \u8ee2 \u30c8 \u30eb \u30af\u306e\u767a \u751f \u3068\u4e00\u8ef8 \u306e \u5236\u5fa1\u304c \u53ef \u80fd \u306a \u30a2\u30ad \u30b7 \u30e3\u30eb \u30bb\u30eb \u30d5\u30d9\u30a2 \u30ea \u30f3\u30b0 \u30e2\u30fc \u30bf \u3092\u63d0 \u6848 \u3057,\u57fa \u672c \u539f\u7406 \u306b\u3064 \u3044 \u3066\u78ba \u8a8d \u3057\u305f(9)\u3002 \u3053\u306e \u30e2 \u30fc \u30bf\u306f,\u30c7 \u30a3\u30b9 \u30af\u578b \u30ed\u30fc \u30bf\u3092\u7528\u3044 \u3066 ,\u30ed \u30fc \u30bf\u306b\u56de\u8ee2 \u30c8\u30eb \u30af \u3092\u767a \u751f \u3055\u305b \u308b\u3068 \u3068 \u3082\u306b,\u30a2 \u30ad \u30b7 \u30e3\u30eb \u65b9\u5411 \u306e\u4f4d \u7f6e \u5236\u5fa1 \u3092\u540c\u6642 \u306b\u884c \u3046\u3053 \u3068 \u3092\u53ef \u80fd \u306b \u3057\u3066 \u3044 \u308b\u3002\u30e2 \u30fc \u30bf\u306e \u5f62\u5f0f \u3068 \u3057\u3066 \u306f ,\u6c38 \u4e45\u78c1 \u77f3 \u578b,\u30ea \u30e9 \u30af \u30bf\u30f3\u30b9\u578b,\u8a98 \u5c0e \u578b\u304c \u8003 \u3048 \u3089\u308c ,\u305d \u308c\u305e \u308c \u306b\u3064 \u3044 \u3066,\u5438 \u5f15 \u529b\u5236 \u5fa1 \u3068\u56de\u8ee2 \u30c8\u30eb \u30af\u306e \u767a \u751f \u3092\u540c \u6642\u306b\u884c \u3048\u308b \u3053\u3068 \u3092\u78ba \u8a8d \u3057\u3066 \u3044 \u308b\u3002\n\u540c \u69d8\u306e\u69cb \u9020 \u306e \u30e2\u30fc \u30bf\u3068 \u3057\u3066\u306f,\u6771 \u4eac \u5de5\u696d \u5927 \u5b66\u306e \u30b0\u30eb \u30fc\u30d7 \u306b \u3088 \u308a,\u30b7 \u30e3 \u30d5 \u30c8\u30ec \u30b9\u30a2 \u30ad \u30b7 \u30e3\u30eb\u30ae \u30e3\u30c3\u30d7\u30d9 \u30a2 \u30ea\u30f3\u30b0 \u30ec\u30b9 \u30e2 \u30fc \u30bf\u304c\u63d0 \u6848 \u3055\u308c \u3066 \u3044 \u308b(10)(11}\u3002\u3053\u306e \u30e2 \u30fc \u30bf\u3067 \u306f ,\u30c7 \u30a3\u30b9 \u30af\u578b \u30ed\u30fc \u30bf\u306e \u7247\u5074 \u306b \u6c38\u4e45\u78c1 \u77f3 \u578b \u30e2 \u30fc \u30bf\u3092 ,\u53cd \u5bfe \u5074 \u306b \u30ea\u30e9\u30af \u30bf\u30f3 \u30b9\u578b\u30e2 \u30fc \u30bf\u3092\u914d\u7f6e \u3057,\u30ea \u30e9 \u30af\u30bf \u30f3\u30b9\u578b \u30e2 \u30fc \u30bf\u306e \u78c1\u675f \u306b \u3088\u3063\u3066 \u30ed\u30fc \u30bf\u306e \u30a2\u30ad \u30b7 \u30e3\u30eb\u65b9 \u5411 \u5909\u4f4d \u3060 \u3051\u3067 \u306a \u304f,\u50be \u304d\u3082\u5236 \u5fa1 \u3059 \u308b \u3053\u3068 \u3092 \u7f85\u7684 \u3068\u3057\u3066 \u3044 \u308b\u3002 \u3053\u306e \u305f\u3081,\u30b9 \u30c6 \u30fc \u30bf\u306e\u69cb\u9020 \u3084\u5236 \u5fa1\u304c \u8907 \u96d1 \u306b \u306a\u308b\u554f \u984c \u306f\u89e3 \u6c7a\u3067 \u304d\u306a \u3044\u3002\n\u672c\u7814 \u7a76 \u3067\u63d0 \u6848 \u3059 \u308b\u30e2 \u30fc \u30bf\u306f,\u69cb \u9020\u3084 \u5236\u5fa1 \u7cfb \u3092\u306a \u308b\u3079 \u304f\u7c21 \u5358 \u306b\u3059 \u308b\u305f \u3081,\u5236 \u5fa1 \u8ef8 \u3092 \u30a2\u30ad \u30b7 \u30e3\u30eb\u65b9 \u5411 \u306e \u307f \u3068\u3057,\u30b9 \u30c6\u30fc\n\u30bf\u3092\u30ed\u30fc \u30bf\u306e\u7247\u5074 \u3042 \u308b\u3044\u306f\u4e21 \u5074 \u306b\u914d\u7f6e \u3059 \u308b\u69cb \u9020 \u3068\u3057\u3066\u3044 \u308b \u3002\n282 T.IEE Japan, Vol. 119-D, No. 3,'99", + "\u30a2 \u30ad \u30b7 \u30e3\u30eb \u578b \u30bb \u30eb \u30d5\u30d9 \u30a2 \u30ea \u30f3\u30b0 \u30e2 \u30fc \u30bf\n\u56f32\u6c38 \u4e45 \u78c1\u77f3 \u578b \u30ed\u30fc \u30bf\nFig. 2. Permanent magnet type rotor\n\u30b9\u30c6\u30fc \u30bf \u3092\u4e21\u5074 \u306b \u914d\u7f6e \u3059 \u308b\u69cb\u9020 \u3067 \u306f,\u4e8c \u3064\u306e \u30b9\u30c6 \u30fc \u30bf\u306e\u5438\n\u5f15\u529b \u306e\u5dee \u3067 \u30a2\u30ad \u30b7 \u30e3\u30eb \u65b9 \u5411\u529b \u3092\u767a \u751f \u3055\u305b \u308b\u3002 \u3053\u306e \u3068\u304d,\u7247 \u5074\u306e \u5438 \u5f15\u529b \u3092\u5f37 \u3081,\u53cd \u5bfe \u5074 \u3092\u5f31 \u3081 \u308b\u5236\u5fa1 \u3092\u884c \u3046\u305f\u3081,\u3053 \u306e \u30bf\u30a4\u30d7\u306e \u30a2 \u30ad \u30b7 \u30e3\u30eb\u578b \u30bb \u30eb \u30d5\u30d9 \u30a2 \u30ea\u30f3\u30b0 \u30e2 \u30fc \u30bf\u3092\u30d7 \u30c3\u30b7\u30e5 \u30d7\u30eb \u578b \u3068\u547c\u3076 \u3053\u3068\u306b \u3059 \u308b\u3002\u4e00 \u65b9,\u30b9 \u30c6 \u30fc \u30bf\u3092\u7247\u5074 \u306b\u914d\u7f6e \u3059 \u308b\u69cb\u9020 \u306e \u30a2\u30ad \u30b7\u30e3\u30eb \u578b\u30bb \u30eb \u30d5\u30d9 \u30a2 \u30ea\u30f3\u30e2 \u30fc \u30bf \u3092\u30b7 \u30f3\u30b0\u30eb \u578b \u3068\u547c\u3076 \u3002\u30d7 \u30c3\u30b7\u30e5 \u30d7 \u30eb\u578b \u3067\u306f,\u4e09 \u76f8 \u30a4\u30f3\u30d0 \u30fc \u30bf\u304c \u4e8c \u3064\u5fc5 \u8981\n\u3068\u306a \u308b\u304c,\u30a2 \u30ad\u30b7 \u30e3\u30eb \u65b9 \u5411\u306e\u4f4d \u7f6e \u5236\u5fa1 \u6027 \u80fd\u3084 \u56de\u8ee2 \u7279\u6027 \u3092\u6539\n\u5584\u3059 \u308b \u3053 \u3068\u304c\u3067 \u304d\u308b \u03c32)\u3002\u30b7 \u30f3\u30b0 \u30eb\u578b\u3067 \u306f,\u4e00 \u3064\u306e \u4e09\u76f8 \u30a4\u30f3 \u30d0 \u30fc \u30bf\u3067\u99c6 \u52d5\u3059 \u308b\u3053 \u3068\u304c \u3067 \u304d\u308b\u305f\u3081 ,\u5236 \u5fa1\u7cfb \u3092\u7c21\u5358\u5316 \u3067 \u304d, \u30ed\u30fc \u30bf\u306e \u7247\u5074 \u306e \u5f62\u72b6 \u3092\u81ea\u7531 \u306b\u6c7a \u3081 \u308b \u3053 \u3068\u304c \u3067 \u304d\u308b\u306e\u3067 ,\u5fdc \u7528\u4e0a\u6709\u5229 \u306b\u306a \u308b \u3068\u8003 \u3048 \u3089\u308c \u308b\u3002\u4eba\u5de5 \u5fc3\u81d3 \u306b\u5fdc \u7528\u3059 \u308b\u5834 \u5408\u306f,\n\u6c38 \u4e45\u78c1 \u77f3\u578b \u30e2 \u30fc \u30bf\u304c,\u30ed \u4e00 \u30bf\u306e \u767a\u71b1 \u304c\u5c0f \u3055\u304f,\u52b9 \u7387\u304c \u9ad8 \u3044 \u305f\u3081,\u6700 \u3082\u9069 \u3057\u3066 \u3044 \u308b \u3068\u8003\u3048 \u3089\u308c \u308b\u3002\n\u672c \u8ad6\u6587 \u3067 \u306f,\u30b7 \u30f3\u30b0 \u30eb\u578b \u6c38\u4e45 \u78c1 \u77f3 \u30e2\u30fc \u30bf\u306e \u30a2 \u30ad \u30b7\u30e3\u30eb \u65b9 \u5411\u529b \u3068\u56de\u8ee2 \u30c8\u30eb \u30af\u3092,\u89e3 \u6790 \u3068\u5b9f \u9a13 \u306b \u3088 \u308a\u660e \u3089\u304b \u306b \u3057,\u305d \u306e\n\u5236\u5fa1 \u65b9\u6cd5 \u306b \u3064\u3044 \u3066\u691c \u8a0e \u3092\u884c \u3046\u3002\n2.\u30a2 \u30ad \u30b7 \u30e3\u30eb \u578b \u30bb \u30eb \u30d5 \u30d9 \u30a2 \u30ea\u30f3 \u30b0 \u30e2 \u30fc \u30bf\n\u30b7 \u30f3\u30b0\u30eb \u52d5\u4f5c \u306e \u30a2 \u30ad \u30b7 \u30e3\u30eb\u578b \u30bb\u30eb \u30d5\u30d9 \u30a2 \u30ea\u30f3\u30b0\u30e2 \u30fc 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\u5411\u306e\n\u4f4d \u7f6e \u5236\u5fa1 \u306b \u306f,\u3053 \u306e \u56de\u8ee2 \u78c1\u754c \u306b \u3088 \u308a\u767a \u751f \u3059 \u308b\u78c1 \u6c17\u5438 \u5f15 \u529b \u3092 \u7528 \u3044 \u308b\u3002\u305d \u306e \u305f\u3081 \u30ed\u30fc \u30bf\u306b \u306f,\u30b9 \u30c6\u30fc \u30bf\u65b9 \u5411\u3078 \u306e\u529b \u3092\u52a0 \u3048 \u308b \u3053 \u3068\u306f \u3067 \u304d\u308b\u304c,\u305d \u308c \u3068\u306f\u53cd\u5bfe \u65b9 \u5411\u306e \u529b \u3092\u4e0e \u3048 \u308b\u3053 \u3068\u304c \u3067 \u304d\u306a \u3044\u3002 \u305d \u3053\u3067,\u30d0 \u30a4\u30a2 \u30b9\u30ab \u3068 \u3057\u3066\u5916 \u90e8\u304b \u3089z\u65b9 \u5411\u306e \u529b \u3092\u52a0 \u3048 \u308b\u5fc5\u8981 \u304c \u3042 \u308b\u3002 \u30ed\u30fc \u30bf\u306f,\u30b9 \u30c6 \u30fc \u30bf\u304b \u3089\u306e \u30a2\u30ad \u30b7\u30e3 \u30eb\u65b9\u5411 \u529bfm\u3068 \u30d0 \u30a4\u30a2\u30b9\u30abfb\u304c \u91e3 \u308a\u5408 \u3063\u305f\u72b6\u614b \u3067 \u56de\u8ee2 \u3059 \u308b\u3002 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\u3088\u3073\u03b8x,\u03b8y,\u03b8z\u306e\u5ea7 \u6a19 \u3092\u5b9a \u3081 \u308b\u3002 \u305f\u3060 \u3057,x,y,\u03b8x,\u03b8y\u306f \u30e9\u30b8 \u30a2\u30eb\u8ef8\u53d7 \u306b \u3088 \u308a\u62d8 \u675f \u3055\u308c,\u30ed \u30fc \u30bf \u306f,g,\u03b8z\u306e \u65b9 \u5411 \u306b \u81ea\u7531\u5ea6 \u3092\u6301 \u3064 \u3082\u306e \u3068\u3059 \u308b\u3002 \u305d \u3057\u3066,\u30ed \u30fc \u30bf \u3068\u30b9\u30c6\u30fc \u30bf\u306e\u5e73\u8861 \u70b9\u3067 \u306e\u30a8 \u30a2\u30ae \u30e3\u30c3\u30d7 \u3092g\u3068 \u3059 \u308b\u3002\u30ed\u30fc \u30bf \u306b\u306f,\u30a2 \u30ad \u30b7\u30e3\u30eb\u30e2 \u30fc \u30bf\u306b \u3088 \u308b\u5438 \u5f15\u529bfm\u3068 \u56de\u8ee2 \u30c8\u30eb \u30afTm , \u304a \u3088\u3073\u30d0 \u30a4\u30a2 \u30b9\u30ab \u3093\u304c \u4f5c \u7528 \u3059 \u308b\u3002 \u307e\u305f,\u56f33\u306e \u3088 \u3046\u306b\u78c1 \u675f \u306e\u5ea7 \u6a19\u8ef8 \u3092\u7f6e \u304f\u3002 \u3053\u306e\u56f3 \u306f,\u30a2 \u30ad\u30b7 \u30e3\u30eb \u578b\u30e2 \u30fc \u30bf\u3092 \u5186\u5468 \u65b9\n\u5411 \u306b\u6cbf \u3063\u3066\u5c55 \u958b\u3057\u305f \u5f62\u3067 \u793a \u3057,\u56f3 \u306e\u89d2 \u5ea6 \u306f\u96fb \u6c17\u89d2 \u3067 \u8868 \u3055\u308c \u3066 \u3044 \u308b\u3002\u30b9 \u30c6\u30fc \u30bf\u306b \u306f,120\u00b0 \u305a \u3064\u96e2 \u308c \u305f \u03b1,b,c\u306e \u4e09\u76f8 \u306e\u5dfb \u7dda\u304c \u5dfb\u304b \u308c \u3066\u3044 \u308b \u3068 \u3057,\u30ed \u30fc \u30bf\u306b\u306f,\u6c38 \u4e45\u78c1 \u77f3\u306e\u4ee3 \u308f \u308a\u306b\nf\u306e \u5dfb\u7dda \u304c \u5dfb\u304b \u308c \u3066 \u3044 \u308b \u3068\u3059 \u308b\u3002\u5b9f \u969b \u306e \u30ed \u30fc \u30bf\u306b\u306f,\u5dfb \u7dda \u3067\u306f \u306a \u304f\u6c38\u4e45 \u78c1\u77f3\u304c \u53d6 \u308a\u4ed8 \u3051 \u3089\u308c \u3066\u3044 \u308b\u304c,\u30ed \u30fc \u30bf\u306e\u5dfb \u7dda \u306b\u4e00 \u5b9a\u306e \u96fb \u6d41 \u3092\u6d41 \u305b \u3070,\u6c38 \u4e45\u78c1 \u77f3 \u3068\u540c \u3058\u306b \u3088 \u3046\u306b\u6271 \u3048 \u308b\u3002\n\u56f33\u306e \u03b1,b,c\u8ef8 \u306f,\u305d \u308c\u305e \u308c\u306e \u5dfb\u7dda \u306b \u3088\u3063 \u3066\u4f5c \u3089\u308c \u308b\u78c1 \u675f \u306e \u901a \u308b\u5411 \u304d\u3092\u8868 \u3057\u3066 \u3044 \u308b\u3002 \u305d \u3057\u3066,d\u8ef8 \u306f,\u30ed \u30fc \u30bf\u5dfb \u7dda \u306b \u3088 \u308a\u4f5c \u3089\u308c \u308b\u78c1\u675f \u306e\u5411 \u304d\u306b \u3068 \u308a,q\u8ef8 \u306f,d\u8ef8 \u3068\u76f4\u4ea4 \u3059 \u308b\u65b9\n\u5411 \u306b \u3068\u308b\u3002d\u8ef8 \u3068 \u03b1\u8ef8 \u3068\u306e\u5dee \u3092\u96fb\u6c17 \u89d2\u3067\u03c6\u3068\u3059 \u308b\u3002\n\u30b9\u30c6\u30fc \u30bf\u5dfb\u7dda \u306e \u81ea\u5df1 \u30a4\u30f3\u30c0 \u30af\u30bf\u30f3\u30b9L\u03b1,Lb,Lc\u306f ,\u30ed \u30fc \u30bf \u304c \u975e \u7a81\u6975 \u306a\u306e\u3067,\u30ed \u30fc \u30bf\u306e \u56de\u8ee2\u4f4d \u7f6e\u03c6\u306b\u95a2\u4fc2 \u306a \u304f\u30a8 \u30a2\u30ae \u30e3\u30c3 \u30d7\u306e \u95a2\u6570 \u3068\u306a \u308b\u3002\u9244 \u5fc3\u5185 \u90e8\u306e\u78c1 \u6c17 \u62b5\u6297 \u3092\u7121 \u8996\u3059 \u308b \u3068,\u78c1 \u6c17 \u62b5 \u6297 \u306f\u30a8 \u30a2\u30ae \u30e3\u30c3\u30d7 \u306b\u6bd4\u4f8b \u3059 \u308b\u306e \u3067,\u6b21 \u306e \u3088 \u3046\u306b\u8868\u305b \u308b\u3002\n(1)\n\u3053\u3053\u3067,L\u03b10\u306f \u30b9 \u30c6\u30fc \u30bf\u5dfb\u7dda \u306e\u6709\u52b9 \u30a4 \u30f3\u30c0 \u30af\u30bf \u30f3\u30b9,L\u03b1 \u300d\u306f \u6f0f \u308c \u30a4\u30f3\u30c0 \u30af\u30bf \u30f3\u30b9,Lao\u306f \u5358\u4f4d \u9577 \u3055\u5f53 \u305f \u308a\u306e\u6709 \u52b9 \u30a4\u30f3 \u30c0 \u30af\u30bf \u30f3\u30b9,2\u306f \u30ed\u30fc \u30bf\u306e\u5909 \u4f4d \u3092\u8868\u3059\u3002 \u30b9\u30c6 \u30fc \u30bf\u5dfb\u7dda \u9593\u306e \u76f8 \u4e92\n\u96fb \u5b66\u8ad6D,119\u5dfb3\u53f7,\u5e73 \u621011\u5e74 283", + "\u30a4\u30f3\u30c0 \u30af\u30bf \u30f3\u30b9L\u03b1b,Lbc,Lc\u03b1 \u306f,\u6709 \u52b9 \u30a4\u30f3\u30c0 \u30af\u30bf \u30f3\u30b9\u306e\u307f\n\u304c \u95a2\u4fc2 \u3059 \u308b \u3068\u4eee\u5b9a \u3059 \u308b \u3068\n(2)\n\u3068\u306a \u308b\u3002\u30ed\u30fc \u30bf\u5dfb \u7dda \u306e \u81ea\u5df1 \u30a4\u30f3\u30c0 \u30af \u30bf\u30f3\u30b9Lf\u306f,\u30b9 \u30c6\u30fc \u30bf \u30b9 \u30ed \u30c3 \u30c8\u306e \u5f71 \u97ff \u3092\u7121\u8996 \u3059 \u308b \u3068,\n(3)\n\u3068 \u306a\u308b\u3002 \u3053 \u3053\u3067,LfO\u306f \u30ed\u30fc \u30bf\u5dfb\u7dda \u306e\u6709 \u52b9 \u30a4 \u30f3\u30c0 \u30af \u30bf\u30f3\u30b9,\nLf\u3054\u306f \u30ed\u30fc \u30bf\u5dfb \u7dda \u306e\u6f0f \u308c \u30a4 \u30f3\u30c0 \u30af\u30bf\u30f3 \u30b9,L\u77e5 \u306f \u5358\u4f4d\u9577 \u3055\u5f53 \u305f \u308a\u306e \u6709\u52b9 \u30a4\u30f3 \u30c0 \u30af \u30bf\u30f3\u30b9 \u3092\u8868 \u3059\u3002 \u30ed\u30fc \u30bf\u5dfb\u7dda \u3068\u30b9\u30c6 \u30fc \u30bf\n\u5dfb \u7dda\u306e\u76f8 \u4e92 \u30a4\u30f3\u30c0 \u30af \u30bf\u30f3\u30b9L\u03b1 \u30ce,L\u03b4\u222b,Lc\u222b\u306f,\u30ed \u30fc \u30bf\u306e \u56de\u8ee2 \u4f4d \u7f6e \u306b \u3088\u3063\u3066 \u5909\u5316 \u3057,\u6b21 \u5f0f \u306e \u3088 \u3046\u306b\u4eee \u5b9a \u3059 \u308b\u3002\n(4)\n\u3053 \u3053\u3067,M\u03b1f\u306f \u30ed\u30fc \u30bf\u5dfb\u7dda \u3068\u30b9\u30c6 \u30fc \u30bf\u5dfb \u7dda\u306e \u76f8\u4e92 \u30a4\u30f3\u30c0 \u30af\n\u30bf\u30f3\u30b9\u306e\u6700 \u5927 \u5024,M'af\u306f \u5358\u4f4d \u9577 \u3055\u5f53\u305f \u308a\u306e \u30b9\u30c6 \u30fc \u30bf\u5dfb \u7dda \u3068 \u30ed\u30fc \u30bf\u5dfb \u7dda\u306e\u76f8 \u4e92 \u30a4\u30f3\u30c0 \u30af\u30bf\u30f3\u30b9\u306e\u6700 \u5927\u5024 \u3092\u8868 \u3059\u3002Lbf,Lcf\n\u306f,\u03c6 \u3092 \u305d\u308c\u305e \u308c\u03c6\u4e002/3\u03c0,\u03c6+2/3\u03c0\u306b\u7f6e \u304d\u63db \u3048\u305f \u3082\u306e \u3068\u306a \u308b\u3002 \u307e\u305f,\u89e3 \u6790 \u3092\u7c21\u5358\u306b\u3059 \u308b\u305f\u3081,\u30ed \u30fc \u30bf\u5dfb\u7dda\u306e \u81ea\u5df1 \u30a4\u30f3\u30c0 \u30af\u30bf \u30f3\u30b9\u306f,\u69cb \u9020 \u3068\u78c1 \u77f3\u306e \u7b49\u4fa1 \u56de\u8def\u3067 \u6c7a \u307e\u308b\u306e\u3067,LfO=3/2L\u03b10\n\u3068\u4eee\u5b9a \u3059 \u308b \u3068,\u6b21 \u306e \u95a2\u4fc2\u304c \u6210 \u308a\u7acb \u3064\u3002\n(5)\nf,\u03b1,b,c\u8ef8 \u306e \u96fb \u6d41 \u6bce,\u3314,%,\u4e5e,\u3068 \u78c1 \u675f \u9396 \u4ea4 \u6570 \u03bbf,\u03bb \u03b1,\u03bb\u3089,\u03bb\u3002\n\u306e \u95a2 \u4fc2 \u306f,\n(6)\n\u3068\u306a \u308b\u3002\u5909 \u63db\u884c \u5217\n\u3092\u5a7f \u3044 \u3066,\u5f0f(6)\u306e \u95a2\u4fc2 \u3092dq\u8ef8 \u306b\u5ea7 \u6a19\u5909 \u63db \u3057,\u5f0f(5)\u306e \u95a2\n\u4fc2 \u3092\u7528 \u3044 \u308b \u3068,\u4ee5 \u4e0b \u306ef,d,q\u8ef8 \u306e \u96fb\u6d41if,id, iq\u3068 \u78c1 \u675f \u9396\u4ea4 \u6570 \u03bbf,\u03bbd,\u03bb9\u306e\u95a2\u4fc2\u304c \u5f97 \u3089\u308c \u308b\u3002\n(7)\n\u30b3\u30a4\u30eb\u306b\u84c4\u3048\u3089\u308c\u308b\u78c1\u6c17\u30a8\u30cd\u30eb\u30aeW\u306f,\n\u3068\u306a \u308b\u306e \u3067,\u30a2 \u30ad \u30b7 \u30e3\u30eb \u65b9 \u5411 \u306e\u5438 \u5f15 \u529bfm\u306f,\u6975 \u5bfe\u6570 \u3092P \u3068\u3059 \u308b\u3068,\u6b21 \u5f0f \u306e \u3088 \u3046\u306b \u6c42 \u307e\u308b\u3002\n(8)\n\u56de\u8ee2 \u30c8\u30eb \u30afTm\u306f,\u78c1 \u675f\u9396 \u4ea4\u6570 \u03bb\u3068\u96fb\u6d41 \u6b6a\u306e\u7a4d \u3068\u306a \u308b\u306e\u3067,\u5f0f\n(7)\u306e \u95a2\u4fc2 \u304b \u3089,\n(9)\n\u3068\u306a\u308b\u3002 \u3053\u308c \u3088\u308a,\u30a2 \u30ad \u30b7 \u30e3\u30eb \u65b9\u5411\u529b \u306f,d\u8ef8 \u96fb \u6d41 \u3068\u30ed\u30fc\u30bf \u96fb\u6d41 \u306b \u3088 \u308b\u529b \u3068q\u8ef8 \u96fb\u6d41 \u306b \u3088\u308b\u767a \u751f \u3059 \u308b\u529b \u306e\u548c \u3068\u306a \u308a,\u56de \u8ee2 \u30c8\u30eb \u30af\u306fq\u8ef8 \u96fb\u6d41 \u306b\u6bd4 \u4f8b \u3059 \u308b \u3053\u3068\u304c \u308f\u304b \u308b\u3002\n\u6b21 \u306b\u4e00\u5b9a \u6b04\u6ce2\u6570 \u306e\u5bfe\u79f0 \u4e09\u76f8 \u96fb\u6d41 \u3067\u99c6 \u52d5\u3059 \u308b\u5834 \u5408\u3092\u8003 \u3048\u308b\u3002\n\u3053\u306e \u5834\u5408 \u306e \u30b9\u30c6 \u30fc \u30bf\u306e\u5404 \u76f8\u306e \u96fb \u6d41 \u3092\u4ee5 \u4e0b\u306e \u5f0f \u3067\u8868 \u3059\u3002\n(10)\n\u3053 \u3053\u3067,Im\u306f \u5404\u76f8 \u306e\u96fb \u6d41\u306e\u6ce2 \u9ad8\u5024 \u3092\u8868 \u3057,Im\u22670\u3068 \u3059 \u308b\u3002\n\u307e\u305f,\u03c9 \u306f \u30b9\u30c6 \u30fc \u30bf\u96fb \u6d41 \u306e\u89d2 \u901f\u5ea6,t\u306f \u6642 \u9593,\u03b4 \u306f4\u8ef8 \u3068\u30b9 \u30c6 \u30fc \u30bf\u96fb \u6d41 \u306b \u3088\u308b\u78c1 \u675f\u306e \u4f4d\u76f8 \u5dee \u3092\u8868 \u3059\u3002 \u5909\u63db\u884c \u52170\u3092 \u7528 \u3044 \u3066,d,q\u8ef8 \u306b\u5ea7 \u6a19 \u5909\u63db \u3092\u884c \u3046 \u3068\n(11)\n\u3068\u306a \u308a,\u30a2 \u30ad\u30b7 \u30e3\u30eb\u65b9 \u5411\u529b \u3068\u56de\u8ee2 \u30c8\u30eb \u30af\u306f,\u5f0f(11)\u3092 \u5f0f(8) \u3068\u5f0f(9)\u306b \u4ee3 \u5165 \u3059 \u308b \u3053\u3068 \u306b \u3088 \u308a,\n(12)\n(13)\n\u3068\u306a\u308b\u3002\u3053\u308c \u3088 \u308a,\u56de \u8ee2 \u30c8\u30eb \u30af\u306f,\u03b4 \u3068Im\u306e \u5927 \u304d \u3055\u3068\u306b \u3088\u3063 \u3066 \u6c7a \u307e \u308a,1m\u306e \u5927 \u304d \u3055\u304c \u4e00\u5b9a \u306a \u3089\u3070,\u56de \u8ee2 \u30c8\u30eb \u30af\u306f,\u6b63 \u5f26\n\u6ce2 \u72b6 \u306b\u5909 \u5316 \u3059 \u308b\u3002 \u30a2 \u30ad \u30b7 \u30e3\u30eb\u65b9 \u5411 \u529b \u306f,Im\u304c \u4e00\u5b9a \u306a \u3089\u3070, \u03b4\u306b \u3088 \u3063\u3066\u4f59\u5f26 \u6ce2\u72b6 \u306b\u5909\u5316 \u3059 \u308b \u3053 \u3068\u304c \u793a \u3055\u308c \u308b\u3002\n4.\u30a2 \u30ad \u30b7 \u30e3\u30eb \u65b9 \u5411 \u529b \u3068 \u56de \u8ee2 \u30c8\u30eb \u30af \u306e \u5236 \u5fa1\n\u524d \u7bc0 \u3067\u5f97 \u3089\u308c \u305f\u7d50\u679c \u306b\u57fa\u3065 \u3044 \u3066,\u30a2 \u30ad \u30b7 \u30e3\u30eb\u65b9 \u5411\u529b \u3068\u56de\n\u8ee2 \u30c8\u30eb \u30af\u306e\u5236\u5fa1 \u65b9 \u6cd5 \u306b\u3064 \u3044\u3066 \u691c\u8a0e \u3059 \u308b\u3002 \u3053 \u3053\u3067 \u306f,\u5b9a \u5e38\u72b6 \u614b \u3067\u306e \u5236\u5fa1 \u306b \u3064\u3044 \u3066\u8003 \u3048\u308b\u3002\n\u30084\u30fb1>\u3001\u30b5 \u30fc\u30dc \u30e2 \u30fc\u30bf(\u9589 \u30eb \u30fc\u30d7 \u30c8\u30eb \u30af)\u5236 \u5fa1 \u307e\u305a, \u30ed\u30fc \u30bf\u306e \u89d2\u4f4d \u7f6e \u3092\u691c \u51fa \u3057,\u56de \u8ee2\u89d2 \u5ea6 \u60c5\u5831 \u306b\u57fa\u3065 \u3044 \u3066 \u56de\u8ee2 \u30c8\n\u30eb \u30af\u3068\u30a2 \u30ad \u30b7 \u30e3\u30eb\u65b9 \u5411\u529b \u3092\u5236\u5fa1 \u3059 \u308b\u65b9\u6cd5 \u3092\u8003 \u3048 \u308b\u3002 \u3053\u306e \u3088\n\u3046 \u306a\u5236 \u5fa1 \u65b9\u6cd5 \u306f,AC\u30b5 \u30fc\u30dc \u30e2 \u30fc \u30bf,\u30d6 \u30e9 \u30b7 \u30ec\u30b9DC\u30e2 \u30fc\n284 T. IEE Japan, Vol. 119-D, No.3, '99" + ] + }, + { + "image_filename": "designv8_17_0001771_s-3217716_latest.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001771_s-3217716_latest.pdf-Figure17-1.png", + "caption": "Figure 17: Optimized double resilient groove metal valve seat performance distribution diagram", + "texts": [ + " The entire solution concentration can find the optimal solution of the Pareto at the same time to meet the three optimization goals, as shown in the red dot in the figure. The three-dimensional model of the front and rear valve seats is shown in Figure 16. 3 4 5 6 7 10 12 1 4 1 6 1 8 2 0 11.0 11.5 12.0 12.5 13.0 H1(m m) M (k g ) H 3 (mm) 11.18 11.32 11.46 11.60 11.74 11.88 12.02 12.16 12.30 12.44 12.58 2 3 4 5 6 3 4 5 6 7 10.2 10.5 10.8 11.1 11.4 11.7 H3(m m) M (k g ) R 2 (mm) 10.19 10.35 10.50 10.66 10.82 10.97 11.13 11.29 11.44 11.60 11.76 Figure 17 shows the performance distribution of the performance of the valve seat structure after the optimization. From Figure 17, the maximum equivalent value of the dual-elastic groove metal valve seat after the optimization is 98.11MPa, which is reduced by 43.45% compared with the maximum equivalent force value before the optimization, and the structure meets the structure. The intensity requirements; the maximum deformation value of the valve seat after optimization is 0.41mm, which is reduced by 45.33%from the maximum deformation value before optimization, and meets the structural stiffness requirements; The fatigue life value increased by 114" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001530_cle_download_859_820-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001530_cle_download_859_820-Figure1-1.png", + "caption": "Fig. 1 Combined conveyor", + "texts": [ + " To do this, pressure pipelines of different cross-sectional length are installed in the side walls of the gutter and connected to nozzles symmetrically mounted on the inside of the side walls of the gutter, reinforced at the bottom with low-fraction material. Pressure pipes can be made of box section, as a low-fraction material can be used tempered glass. This design of the conveyor allows to obtain a jet of liquid, to have a low coefficient of friction of the chips against the bottom of the chute, ie in general to increase the efficiency of transportation. The compact arrangement of pressure pipes and nozzles allows to reduce considerably the overall dimensions of the device. The combined conveyor (Fig. 1) has a gutter of semicircular cross-section, at the side walls of which are installed pressure pipelines 1 also shaped corresponding to the cross section of the auger, but moved along the length of the cross section. Nozzles 2 with oval outlets 3 are welded to the pipelines. Under pressure, the coolant is fed through pipes into pressure pipelines, from where it is injected into the chute through nozzles in the form of jets parallel to the bottom. To prevent chips from entering the nozzles, protective screens are mounted above them", + " Jets of liquid flying out of the holes pick up the chips 4 and move it from one jet to another, thereby ensuring the movement and mixing of the transported particles that did not fall into the area of action of the screw spiral. The installed auger 5 can be made of both tape and blade construction. Under even more limited conditions, it is advisable to use several modified nozzle designs in the form of slits formed by wall elements to transport chips from the cutting area of the machine. In this case, the energy of the resulting jets is fully used and larger chips can be moved. In this case, the chips in some areas float \"on the stream\" and slide along the bottom of the gutter. Denote by Li (Fig. 1) \u2013 the distance between the nozzles along the length of the chute, which is also a value equal to the pitch of the auger spiral, h \u2013 height from the middle of the nozzles to the bottom, \u03b1 \u2013 angle of the chute, B \u2013 width of the chute, 1.05-1.1 external diameter of the auger, a and b \u2013 half the length and width of the nozzle hole, \u03c6 \u2013 the angle of the axis of the jets with the longitudinal axis of the chute, Qr \u2013 fluid flow from one nozzle, d \u2013 average particle size. Let the X axis coincide with the gutter axis, the \u0425\u0423 plane coincide with the bottom plane, and the Z axis coincide with it" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure14-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure14-1.png", + "caption": "Fig. 14 Contact status of the spiroid worm drive.", + "texts": [ + " The maximum stress on i surface of the worm gear is 370Mpa and e surface is 420Mpa. From the simulation results, it can be observed that the stress on the i-side of the helicon gear is larger than that on the e-side, which is consistent with the previous analysis results. When combining the tooth surface stresses of the face worm gear drive and the spiroid worm drive, the results demonstrate the regularity of a decrease in curvature induced by a reduction in pinion cone angle. A conclusion can be drawn from Fig. 14 and Fig. 17 that the spiroid gear has a relatively uniform contact area and a larger number of contact teeth under this parameter, indicating a good contact state. (a) Contact status of the on i surface (b) Contact status of the e surface (a) Equivalent stress of the pinion (b) Equivalent stress of the wormwheel 2 \u00a9 2023 The Japan Society of Mechanical Engineers[DOI: 10.1299/jamdsm.2023jamdsm0073] This research investigates the impact of the pinion cone angle reduction on the meshing performance of the face worm gear drive and reveal the asymmetric meshing characteristics of the tooth surface on both sides of the transmission pair" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure13.38-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure13.38-1.png", + "caption": "Fig. 13.38. Distribution of frequency energy front floor panel vibration estimators & ( ) and for different engine rotational speed", + "texts": [], + "surrounding_texts": [ + "166 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260 Analysing of engine rotational speed influence on structure of vibration presented as TFR the method of TFR energy estimator were developed. This method enables determining the energy of" + ] + }, + { + "image_filename": "designv8_17_0004361_rs-740948_latest.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004361_rs-740948_latest.pdf-Figure8-1.png", + "caption": "Fig 8 compliant slider crank mechanism by FEA", + "texts": [], + "surrounding_texts": [ + "Solid modeling was done using the solid works software: The FEM analysis was used as a strong tool for calculating stress, relative rotation between the crank and the connecting rod, slider displacement and fatigue life. . This FEM analysis has been conducted in standard FEA package Ansys 16. The Material Aluminium alloy is used for the compliant hinge which is been directly selected from the engineering data. Connections: Three new connections are been created in the form of joints. The three joints are as follows: 1. Revolute joint between connecting rod and crank (Joint 1) 2. Revolute joint between the ground and the crank (Joint 2) 3. Translational joint between the ground and base of the slider (Joint 3) Fig11 Connection of joints in Admas Boundary conditions: In the analysis setting :Number of steps = 4,Auto time stepping= ON, Initial time step= 0.2 sec,Minimum time step = 0.1 sec,Maximum time step = 0.3 sec,Time integration = ON. Joint rotation is been provided to the crank. For each second, a rotation of 90 degree is been provided. So, rotation of 360 degree or full one rotation takes a total time of 4 seconds witch can be seen in figure. Rotation is been given to crank in tabular form. 1. Solutions The graph and tabular data of relative displacement of the slider .The maximum displacement was 60.052mm Total equivalent stress in hinge is maximum in outside surface of hinge but minimum at center. Also, Fatigue life was found out and results clearly shows the hinge is only part with minimum life. Fig14 fatigue Life V. EXPERIMENTATION The experimental setup consists of Motor, Shaft, Disc with holes, Connecting rod, Slider, Base frame" + ] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure22-1.png", + "caption": "Figure 22: The robotic force-plate, load cells and sensing mechanism (TOP: experimental prototype; BOTTOM: CAD drawing). The load cells (1); acrylic plate (2); aluminum plate (3); metal crossbar (4); aluminum beams (5); the linear spring to create a preload (6).", + "texts": [ + " The cubic support frame (1); internal and external layers of the footplate (2); the PF/DF motor and transmission system (3); the IN/EV motor and transmission system (4); the encoders (5); the foot strap (6); and mechanical stop (7). .................................................. 38 Figure 20: 3D CAD image of the robotic footplate support frame built of 1.5\u201d aluminum [131] .............. 39 ix Figure 21: Image of the interior frame; Left: INEV axis of rotation, right: INEV built in within the DFPF axis [131] .................................................................................................................................... 40 Figure 22: The robotic force-plate, load cells and sensing mechanism (TOP: experimental prototype; BOTTOM: CAD drawing). The load cells (1); acrylic plate (2); aluminum plate (3); metal crossbar (4); aluminum beams (5); the linear spring to create a preload (6)..................................... 41 Figure 23: Torque calculation of the subject\u2019s foot on the footplate along the DFPF axis [131]. .............. 42 Figure 24: Torque calculation of the patient foot on the footplate along the INEV axis [131] ", + " The footplate is the most important subsystem of the vi-RABT as it must provide controlled rotation, speed and torque with accuracy and precision. It will be controlled by a motor/gearbox combination for each degree of freedom, inversion/eversion and plantarflexion/dorsiflexion. The gearbox is necessary to provide a torque amplification and speed reduction. In order to decide on the motors necessary for each rotational direction, calculations were performed for speed and torque. The 2-DOF actuation was provided by a two layer design for the footplate. As shown in Figure 22, the robotic footplate is composed of an internal force-plate surrounded by an external housing. The internal layer (i.e. the force-plate) was considered for the IN/EV movement and the 39 external layer for DF/PF, hence the robotic force-plate. As shown in Fig 22, the patients\u2019 feet will be strapped onto the acrylic footplate and subjects can interact with the system in standing or seated posture. The force-plate is supported on the cubic support frame via plates, load cells, bars and ball bearings. The support frame is 73cm (L) \u00d7 33cm (W) \u00d7 33cm (H) with a 36.5cm (L) \u00d7 16.5cm (W) footplate. It is made of 3.8 cm (1.5 inch) aluminum bars, which was shown to have minimal deflection and stress under our maximum weight application (150 Kg). The mechanical design and early system fabrications were achieved in collaboration with undergraduate mechanical engineering students as a capstone project [131]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002701_cle_6001_context_etd-Figure7.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002701_cle_6001_context_etd-Figure7.6-1.png", + "caption": "Figure 7.6: Beamforming architecture of a 1024 ULA receiver using the proposed architecture. The rewiring block performs multiplexing as shown in Fig. 7.3.", + "texts": [ + " For example, simultaneous receiver beams are imperative for high-capacity MIMO wireless communication systems. Multiple independent RF beams can be generated by applying an N -point spatial FFT at each time sample across a uniform linear array (ULA) of antennas [157,158]. For an N -element ULA with Nyquist (i.e., \u03bb/2) spacing, the N beams are uniformly spaced in the spatial frequency domain with an interval of 2\u03c0/N . The proposed architecture can be used to replace the FFT for this purpose, thus generating N = 1024 beams from a 1024-element ULA as shown in Fig. 7.6. In the proposed system, each ADFT bin corresponds to a unique direction in space. Ideally these bins should be identical to the spatial DFT bins, but their magnitude could deviate because of the approximation. The four worst bins for each of the three algorithms are shown 116 in Fig. 7.7. The resulting errors are small enough to be acceptable in low-SNR scenarios. Realization of 1024-element ULAs for generating narrow beams in currentlylicensed frequency bands (upto the V band) may be challenging due to the large sizes of the resulting apertures" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001670_ev_9_1_9_1_1465__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001670_ev_9_1_9_1_1465__pdf-Figure2-1.png", + "caption": "Fig. 2 Studied electrical machine", + "texts": [ + " The HEV traction drives require an ability to operate at constant power over a wide speed range, good overload performance and high efficiency [Soong et al., 2002]. Due to the permanent magnet excitation, PM brushless machines are inherently efficient and hence have been extensively used for HEV applications [Zhu et al., 2008]. Then, surface mounted permanent magnet synchronous machines are popularly used in this application [Isfahani et al., 2008]. Also in this paper, we have proposed a SMPMSM with distributed windings (Figure 2). For electrical machines, the iron losses computation is usually a very complex problem. Many authors [Zhu et al., 2002; Mi et al., 2003; Yamazaki et al., 2006; Seo et al., 2009; Tariq et al., 2009; Doffe et al., 2010; Chen et al., 2010; Barcaro et al., 2008; Ding et al., 2010] have proposed iron losses models to compute the iron losses in the electric machines that the authors [Krings and Soulard, 2010] has made an overview and comparison of iron losses models for electric machines. However, all proposed iron losses models are to compute the iron losses at a desired speed/torque or some speed/torque values", + " Analyzing the driving cycle and basing on the base point, we have some important parameters such as the maximum torque, the maximum speed, the maximum power and the average power during the cycle, the number of points where the speed is higher than the base speed. Figure 1 and Table 1 have shown that there are some points that can attain a power around 40 kW but the values of the average power during the cycle are of 4.8 kW and 10.5 kW for Artemis-Urban and Artemis-Road, respectively. As explained in the introduction, we have chosen a SMPMSM for this application. It is presented in Figure 2 is characterized by the distributed windings with 48 slots and 8 surface mounted permanent magnets (Br = 0.6T) on the rotor. In this part, we have supposed that the magnetic circuit is unsaturated and that there aren\u2019t harmonics of current and of flux at no-load. Then, such as this machine is a surface mounted permanent magnet machine, it does not show the saliency. Also with the above hypothesis, we have the well-known torque equation as the following [Nguyen et al., 2010]: qem .Ip.T . 2 3 (1) Where p is the pole pair numbers, \u0424 is the maximum flux created by magnets, Iq is the maximum stator qaxis current" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001135_cle_download_672_566-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001135_cle_download_672_566-Figure5-1.png", + "caption": "Fig. 5. Design options of the Tesla disk pump for blood pumping [9]: a \u2013 the thickness of the disk rotor to the periphery is reduced; \u0431 \u2013 the thickness of the disk rotor to the periphery increases; \u0432 \u2013 the rotor disks of uniform thickness; \u0433 \u2013 rotor with an axial disc locking", + "texts": [], + "surrounding_texts": [ + "SUPPORT IN CARDIAC SURGERY (REVIEW)" + ] + }, + { + "image_filename": "designv8_17_0001142_f_version_1426588746-Figure19-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001142_f_version_1426588746-Figure19-1.png", + "caption": "Figure 19. Thermal field distribution under condition of water cooling used in the casing and axial forced air when both the SM and the DRM run at the low speed and rated load.", + "texts": [ + " However, the heat dissipation capacity of inner rotor windings in the core is poor for the inner rotor windings, so the temperature of inner rotor windings in the core is higher than that of end windings. Comparing Table 9 with Table 6, it shows that the temperature of each part under condition of the low speed and rated load is much lower than that under condition of the rated speed and rated load. When both the SM and the DRM are running at the low speed and rated load, the 3-D thermal-field distribution is calculated under condition of water cooling used in the casing and axial forced air, as shown in Figure 19. To illustrate the axial thermal field distribution of the CS-PMSM, the thermal field distributions of the windward side, middle cross-section, and the leeward side of the CS-PMSM are shown in Figure 20. The selected windward and leeward cross-sections are the same as those in Section 4.2. Meanwhile, the temperatures of the end windings of the stator and inner rotor are also listed in Table 10. From the temperature distribution of each cross-section in Table 10, it can be seen that the temperatures of the stator and inner rotor are very low, indicating that the axial force air has a good cooling effect on the CS-PMSM, especially for the inner rotor" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001089_ff397de6de9d42fe.pdf-Figure9-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001089_ff397de6de9d42fe.pdf-Figure9-1.png", + "caption": "Figure 9. (a) Slider-crank mechanism dimensions: r: radius of crank, l: length of connecting rod, and : rank angle. (b) Crank slider mechanism view in application. (c) Measurement of length of connecting rod. (d) Parts of the generator. (e) Generator view of the prototype.", + "texts": [ + " In line with the design data given in Table 1, calculations of linear generator were made in the interface [19]. However, when the size of the magnet obtained from MOGA results was considered, it was di cult to produce magnets, speci cally. Thus, generator geometry was established based on the initial design geometry data. The distribution of the magnetic ux density on the length of the generator in ANSYS Maxwell 2D rz can be seen in Figure 8. The images of crank slider mechanism are given in Figure 9(a), (b), and (c). M43-24G geometry and magnetic rotor piece with iron sheet for the prototype are given in Figure 9(d) and (e). The prototype machine can be seen in Figure 10, which is fabricated based on the initial design. In Figure 10, the generator is driven by the crank slider mechanism (Figures 9(b) and 10(b)) proper to a 4-pole asynchronous motor. The results of the numerical analysis were compared with the testing prototype (unloaded) for 20 Hz driving frequency (Figure 11). Here, speed was calculated according to the crank sizes given. It was found that the results of the numerical analysis by ANSYS Maxwell and those of the application were in parallel to a great extent", + " \\Multiobjective approach developed for optimizing the dynamic behavior of incremental linear actuators\", COMPEL: The International Journal for Computation and Mathematics in Electrical and Electronic Engineering, 33(3), pp. 953{964 (2014). 23. Alpar, R. \\Uygulamal _Istatistik ve Ge cerlilikG uvenirlik\", Detay yay nc l k, pp. 1{668, Ankara, Turkey (2014). 24. http://www.webcitation.org/query?url=https%3A% 2F%2Ftr.scribd.com%2Fdocument%2F370055766%2 FAnsys-Maxwell-18-Online-Help&date=2018-07-09 The application of the cosine theorem according to the triangle in the moving system in Figure 9(a) is: l2 = x2 + r2 2xr cos ; (A.1) x2 2xr cos = l2 r2; (A.2) x2 2xr cos +r2 cos2 = l2 r2+r2 cos2 ; (A.3) (x r cos )2 = l2 r2(1 cos2 ); (A.4) where: sin2 = 1 cos2 : (A.5) By taking the square root of two sides of the equality: x r cos = p l2 r2 sin2 ; (A.6) x = r cos + p l2 r2 sin2 : (A.7) l is length and r a crank radius, which is constant. The crank angle ( ) varies between (0 {360 ) and x is the only variable that a ects the piston position. At = 0 , the piston is in the top point and position size is l+ r" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002718_3452-020-00107-0.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002718_3452-020-00107-0.pdf-Figure11-1.png", + "caption": "Fig. 11 Distribution of the recrystallized volume fraction (a) for pearlitic steel and critical strain (b) and effective strain (c) for bainitic steel in the last pass", + "texts": [ + " Results show that DRX was completed for the pearlitic steel (Fig.\u00a09b) while in bainitic steel only a small volume of metal recrystallized according to dynamic mechanism (Fig.\u00a010b). In the last pass, no 17, partial dynamic recrystallization for the pearlitic steel was observed, but the dominant mechanism of recrystallization was static. For bainitic steel, the value of the critical strain was greater than the value of the effective strain and dynamic recrystallization did not start. Static recrystallization only was observed (Fig.\u00a011). Modelling of the mechanisms of recrystallization (dynamic and static) showed that for pearlitic steel the recrystallization rate is larger than for bainitic steel. However, during 1.5\u00a0s after the last pass, the recrystallization of both steels was completed. 1 3 Finally, distributions of temperature and grain size at the rail cross-section after the rolling process were determined (Fig.\u00a012). The results show that pearlitic steel has larger grains than bainitic steel. The distribution of grain diameter is more uniform for bainitic steel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003657__2023jamdsm0073__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003657__2023jamdsm0073__pdf-Figure2-1.png", + "caption": "Fig. 2 The shaft section of the pinion surface.", + "texts": [ + " Additionally, the pinion has an installation offset of ZA, and the distance from the center of the pinion to the center of the gear is equal to A. The unit vectors of coordinate systems \u03a3, \u03a3m1, \u03a3P, and \u03a3m2 are (is, js, ks), (im1, jm1, km1), (ip, jp, kp), and (i m2, jm2, km2), correspondingly, with a transmission ratio of i12=\u03c91/\u03c92=\u03c61/\u03c62. The coefficient matrix that transforms the rotating frame \u03a3m1 to the rotating frame \u03a3m2 is presented below: 1 2 2 1 2 2 2 1 2 1 2 2 2 2 21 1 1 cos sin cos sin sin cos sin cos sin sin sin cos sin cos sin cos 0 0 0 0 0 1 A A A Z A Z M \u2212 \u2212 \u2212 \u2212 \u2212 \u2212 \u2212 = (1) As shown in Fig. 2, the parameter u represents the radial distance of the worm. Additionally, the pressure angle of the pinion on both the i and e sides are referred to as \u03b1i and \u03b1e, respectively, and the tooth profile angles are represented by vi and ve. Finally, \u03b4 corresponds to the cone angle of the pinion. Due to the presence of a cone angle in the pinion, there is a difference in displacement along the axial and radial directions when it rotates by a certain angle. Fig. 3 illustrates the displacement in each direction within worm and cutter system" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002591_cle_download_492_437-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002591_cle_download_492_437-Figure1-1.png", + "caption": "Figure 1: Four Pole (A) and Six Pole (B) Generators", + "texts": [ + " These have advantages of high The Comparative Analysis of the Performances of Four and Six Pole Pairs Permanent Magnet Synchronous Generator 2 Tanzania Journal of Engineering and Technology (Tanz. J. Engrg. Technol.), Vol. 38 (No. 1), June 2019 efficiency and reliability since there is no need of external excitation and conductor losses are removed from the rotor (Ocak at el., 2012). In this work the two permanent magnet generators with inner rotor were analysed based on number of pole pairs where the generator with 4 pole pairs and 6 pole pairs were designed and their performance was compared (Figure 1). Generator with inner rotor suits very well for small wind turbines. This kind of design makes the construction of a turbine more convenient due to simple installation of the wind rotor directly to the generator surface. On the other hand, the construction with inner stator blocks the heat transfer from the stator winding. In the first step of study, the main dimensions of the generator were determined. The stack length, air-gap length, slots and number of poles were optimised for design of an inner rotor permanent magnet generator", + " Figure 7 shows the slot design of PM generator and the proposed size, which normally depends on the size of the generator and the proposed power output. The newly designed PM AC Synchronous machines were tested in different rotational speed, starting from 50 rpm to 1300 rpm, which is equivalent to wind speed of 0.3 m/s to 7.8 m/s as converted through Equation 11 (Kolar et al., 2012): ))(( )(60000 )( 1 RotormmDiameter msSpeed RpmSpeed \u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026\u2026. (11) Complete machine design structures of the generators (Figure 1) were run with the Maxwell software with reference speed 350 rpm. The rotational speed was varied at the interval of 50 rpm (i.e. 50, 100, 150, 200\u20261300 rpm) where at each different rotational speed, the values of all parameters were recorded and the behaviour and performance of the machines were examined. The computation of all other parameters will be based on the reference speed, which was selected to be 350 rpm, and maximum speed 1000 rpm, which is equivalent to 2.1 m/s of wind speed to 6.0 m/s" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001952__2706_context_theses-Figure18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001952__2706_context_theses-Figure18-1.png", + "caption": "Figure 18. Composite tensile specimen between the clamps (left) composite tensile specimen with extensometer (right)", + "texts": [ + " The limit load was calculated by multiplying the 1st specimen\u2019s ultimate load by 0.25 and this value was specified in Bluehill2\u2019s end of test criteria. In Bluehill2 software, there is an option of recording the strain using an extensometer and once the limit load is reached, the test will pause allowing the user to remove the extensometer. Next, the remaining five composite tensile specimens were tested. The next composite tensile specimens were loaded in the machine and the extensometer was attached for each specimen. Figure 18 shows a composite tensile specimen (with an extensometer mounted on its surface). Once at the limit load, the extensometer was removed, and the test continued up to the ultimate load. Note that the initial modulus recorded by the extensometer was very accurate, and after removal of the extensometer, the crosshead took over and the accuracy declined. 34 3.3.2 Double Shear Testing Procedure Once the standard Instron startup procedure was completed, the tensile double shear Bluehill2 test method was started" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000357_2015_60_2015_29__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000357_2015_60_2015_29__pdf-Figure1-1.png", + "caption": "Fig. 1 Suspension layout and terms.", + "texts": [], + "surrounding_texts": [ + "\u3070\u306d\u8ad6\u6587\u96c6 \u7b2c60\u53f7\uff082015\uff09 29\n1. \u306f\u3058\u3081\u306b \u30de\u30af\u30d5\u30a1\u30fc\u30bd\u30f3\u30b9\u30c8\u30e9\u30c3\u30c8\u30bf\u30a4\u30d7\u306e\u81ea\u52d5\u8eca\u7528\u30b5\u30b9\u30da\u30f3 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\u30e2\u30fc\u30e1\u30f3\u30c8\u3092\u767a\u751f\u3055\u305b\uff0c\u5de6\u53f3\u306e\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u3067\u3053\u306e\u30e2\u30fc\n\u4efb\u610f\u8377\u91cd\u8ef8\u767a\u751f\u88c5\u7f6e\u306b\u3088\u308b\u30b3\u30a4\u30eb\u3070\u306d\u53cd\u529b\u7dda\u304c\u8eca\u4e21\u7279\u6027\u306b\u53ca\u307c\u3059\u5f71\u97ff\u8abf\u67fb *\n\u897f\u6ca2 \u771f\u4e00 **\uff0c\u4ef2\u6751 \u5d07\u5e83 ***\uff0c\u53e4\u5ddd \u548c\u592b ***\uff0c\u68ee\u5c71 \u5343\u91cc ***\uff0c\u4f50\u85e4 \u9686\u4e00 ***\nExperimental Study on the Effect of Coil Spring Reaction Force Vector on Suspension System Characteristics\nShinichi NISHIZAWA, Takahiro NAKAMURA, Kazuo FURUKAWA, Senri MORIYAMA and Ryuichi SATO\nIn MacPherson strut applications for automotive suspension systems, the desired coil spring reaction force vector that minimizes damper friction and king pin moment is typically determined by Statics/ Kinematics calculations. There is not a single device available on the open market today which can simulate the coil spring reaction force vector within the suspension system. Such a programmable coil spring reaction force generator was developed in 2003, and was then improved in 2013 from the standpoint of accuracy, durability and reliability. Using this modified device, the relationship between the spring reaction force vector and damper friction, as well as spring reaction force vector and king pin moment, can be experimentally studied to confirm vehicle characteristics without actually making any prototype coil springs. The validity of this device was proven by comparing to actual coil spring based testing data. Depending upon the desired characteristics of a particular vehicle, the requirement for the coil spring reaction force vector can be experimentally determined with this device. To aid in this effort the device was designed in a universal manner for any strut application by mere replacement of strut-dependent seat adapters. This paper describes how beneficial this device is to determine the ideal requirement for coil spring reaction force vector via actual measured data.\nKey Words: Force Line, Reaction Force Vector, Stewart Platform, Damper Friction, Self Steer Torque, Bearing Friction\n\u539f\u7a3f\u53d7\u4ed8\u65e5 2014\u5e7412\u67089\u65e5 \uff0a \u65e5\u672c\u3070\u306d\u5b66\u4f1a2013\u5e74\u5ea6\u79cb\u5b63\u8b1b\u6f14\u4f1a \uff0a\uff0a NHK International Corporation \uff0a\uff0a\uff0a \u65e5\u672c\u767a\u6761\u682a\u5f0f\u4f1a\u793e \uff08NHK spring Co, ltd\uff09", + "30\n\u30e1\u30f3\u30c8\u306e\u5408\u6210\u304c\u5927\u304d\u304f\u306a\u308b\u3068\uff0c\u8eca\u4e21\u306e\u76f4\u9032\u6027\u304c\u60aa\u5316\u3059\u308b\u3053 \u3068\u306b\u306a\u308b\uff0e 2.2 \u69cb\u9020\u7684\u306a\u6539\u5584\nUSPG2003\u3068USPG2013\u306f\uff0c\u3069\u3061\u3089\u3082\u6cb9\u5727\u30b7\u30ea\u30f3\u30c0\u30926\u672c \u4f7f\u3063\u3066\u30b9\u30c1\u30e5\u30ef\u30fc\u30c8\u30d7\u30e9\u30c3\u30c8\u30d5\u30a9\u30fc\u30e0\u3092\u69cb\u6210\u3057\uff0c6\u81ea\u7531\u5ea6 \u306e\u4efb\u610f\u306a\u529b\u53ca\u3073\u30e2\u30fc\u30e1\u30f3\u30c8\u306e\u5834\u3092\u767a\u751f\u3055\u305b\u308b\u3053\u3068\u3067\u30b3\u30a4 \u30eb\u3070\u306d\u306e\u53cd\u529b\u5834\u3092\u6a21\u64ec\u3059\u308b\uff0e\u4e21\u8005\u306e\u4ed5\u69d8\u306e\u9055\u3044\u3092Table 2 \u306b\u793a\u3059\uff0eUSPG2003\u3067\u306f\u6cb9\u5727\u30b7\u30ea\u30f3\u30c0\u3092\u30a2\u30c3\u30d1\u30fc\u30de\u30a6\u30f3\u30c8 \u3068\u30ed\u30a2\u30b7\u30fc\u30c8\u9593\u306b\u53d6\u308a\u4ed8\u3051\u3066\u3044\u305f\u304c\uff0cUSPG2013\u3067\u306f\u4e0a\u4e0b \u30b7\u30fc\u30c8\u306b\u5e3d\u5b50\u578b\u306e\u30b8\u30b0\u3092\u53d6\u308a\u4ed8\u3051\uff0c\u305d\u306e\u5e3d\u5b50\u306e\u30c4\u30d0\u306e\u90e8\u5206 \u306b\u30b7\u30ea\u30f3\u30c0\u3092\u53d6\u308a\u4ed8\u3051\u305f\uff0e\u3053\u308c\u306b\u3088\u308a\u30b7\u30ea\u30f3\u30c0\u306e\u9577\u3044\u8907\u52d5 \u30b7\u30ea\u30f3\u30c0\u306e\u4f7f\u7528\u304c\u53ef\u80fd\u306b\u306a\u308a\u30b9\u30c8\u30ed\u30fc\u30af\u3082\u62e1\u5927\u3057\u305f\uff0e\u3055\u3089 \u306b\uff0c\u53d6\u4ed8\u3051\u4f4d\u7f6e\u7bc4\u56f2\u304c\u5927\u304d\u304f\u306a\u3063\u305f\u3053\u3068\u3067\uff0c\u5b9f\u73fe\u3067\u304d\u308b FLP\u306e\u7bc4\u56f2\u304c\u9762\u7a4d\u6bd4\u3067\u7d045.8\u500d\u306b\u5e83\u304c\u3063\u305f\uff08\u30b9\u30c8\u30e9\u30c3\u30c8\u8ef8\u5468 \u308a\u3067\u03c650mm\u2192\u03c6120mm\uff09\uff0e\u30b7\u30ea\u30f3\u30c0\u304c\u8907\u52d5\u3068\u306a\u3063\u305f\u3053\u3068 \u3067\uff0c\u30b7\u30ea\u30f3\u30c0\u306e\u53d6\u4ed8\u3051\u7bc4\u56f2\u5916\u306eFLP\u3082\u5b9f\u73fe\u53ef\u80fd\u3068\u306a\u3063\u3066\u3044 \u308b\u304c\uff0c\u30b3\u30a4\u30eb\u3070\u306d\u3067\u306f\u305d\u306e\u3088\u3046\u306aFLP\u3092\u5b9f\u73fe\u3067\u304d\u306a\u3044\u305f\u3081\uff0c \u4eca\u56de\u306e\u8a66\u9a13\u3067\u306f\u30b7\u30ea\u30f3\u30c0\u3092\u77ed\u7e2e\u3055\u305b\u308b\u8ca0\u306e\u8907\u529b\u306f\u4f7f\u7528\u3057\u3066\n\u3044\u306a\u3044\uff0e\u307e\u305f\uff0c6\u672c\u306e\u8ef8\u529b\u304c\u5165\u529b\u3055\u308c\u308b\u306e\u306f\u4e0a\u4e0b\u5e3d\u5b50\u306e\u30c4 \u30d0\u90e8\u5206\u3067\u3042\u308a\uff0c\u3053\u306e\u5236\u5fa1\u9762\u306fFLP\u3092\u8abf\u6574\u3057\u305f\u30b3\u30a4\u30eb\u3070\u306d\u306e \u4e0a\u4e0b\u3070\u306d\u5ea7\u9762\u3088\u308a\u4e0a\u4e0b\u306b\u5927\u304d\u304f\u96e2\u308c\u3066\u3044\u308b\uff0e\u8981\u3059\u308b\u306b\u30b7\u30ea \u30f3\u30c0\u8ef8\u529b\u306e\u5927\u304d\u306a\u5909\u5316\u306b\u3088\u3063\u3066\uff0c\u4e0a\u4e0b\u3070\u306d\u5ea7\u9762\u4e0a\u306eFLP\u3092 \u5fae\u8abf\u6574\u3059\u308b\u3053\u3068\u306b\u306a\u308a\uff0c\u3053\u306e\u5236\u5fa1\u9762\u3068\u3070\u306d\u5ea7\u9762\u3068\u306e\u9ad8\u3055\u5dee \u304c\u7cbe\u5ea6\u30a2\u30c3\u30d7\u306b\u8ca2\u732e\u3057\u3066\u3044\u308b\uff0e \u307e\u305f\uff0cUSPG2003\u306f\uff0c\u6cb9\u5727\u30b7\u30ea\u30f3\u30c0\u3092\u76f4\u63a5\u30ed\u30a2\u30b7\u30fc\u30c8\n\u3068\u30a2\u30c3\u30d1\u30fc\u30de\u30a6\u30f3\u30c8\u306b\u53d6\u308a\u4ed8\u3051\u3066\u3044\u305f\u305f\u3081\uff0c\u5225\u306e\u30b9\u30c8 \u30e9\u30c3\u30c8\u306b\u53d6\u308a\u4ed8\u3051\u308b\u3068\u304d\u306b\u306f\uff0c\u53d6\u4ed8\u3051\u5b54\u306e\u88fd\u4f5c\u3068CMM \uff08Coordinate Measuring Machine\uff09\u306b\u3088\u308b\u53d6\u4ed8\u3051\u5b54\u4f4d\u7f6e\u306e\u518d \u8a08\u6e2c\u3092\u4f59\u5100\u306a\u304f\u3055\u308c\u3066\u3044\u305f\uff0eUSPG2013\u3067\u306f\u5e3d\u5b50\u307e\u3067\u3092\u542b \u3081\u305f\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u90e8\u3092\uff0c\u4e0a\u4e0b\u3068\u3082\u306b\u30b7\u30fc\u30c8\u30a2\u30c0\u30d7\u30bf\u3092\u4ecb \u3057\u3066\u30b7\u30fc\u30c8\u4e0a\u306b\u30b3\u30a4\u30eb\u3070\u306d\u306e\u4ee3\u308f\u308a\u306b\u4e57\u305b\u308b\u3060\u3051\u3067\u3042\u308a\uff0c \u30b7\u30ea\u30f3\u30c0\u306e\u53d6\u4ed8\u3051\u4f4d\u7f6e\u306f\u30b9\u30c8\u30e9\u30c3\u30c8\u306b\u3088\u3063\u3066\u5909\u308f\u308b\u3053\u3068\u306f \u306a\u3044\uff0e\u5225\u30b9\u30c8\u30e9\u30c3\u30c8\u3078\u306e\u9069\u7528\u306f\uff0c\u30b7\u30fc\u30c8\u30a2\u30c0\u30d7\u30bf\u3092\u88fd\u4f5c\u3059 \u308b\u3060\u3051\u3067\u3088\u304f\uff0c\u5b89\u5b9a\u3057\u305f\u7cbe\u5ea6\u3068\u696d\u52d9\u30eb\u30fc\u30c1\u30f3\u5316\u306e\u5bb9\u6613\u3055 \u3082USPG2013\u306e\u5229\u70b9\u3068\u306a\u308b\uff0e\u3055\u3089\u306b\uff0c\u5404\u6cb9\u5727\u30b7\u30ea\u30f3\u30c0\u306b\u306f LVDT\uff08Linear Variable Differential Transformer\uff09\u3092\u88c5\u5099\u3057\uff0c \u4e0a\u4e0b\u5ea7\u9762\u306e\u56de\u8ee2\u3084\u3070\u306d\u9ad8\u3055\u3092\u30ea\u30a2\u30eb\u30bf\u30a4\u30e0\u8a08\u6e2c\u3067\u304d\u308b\u3088\u3046 \u306b\u3057\u305f\u305f\u3081\uff0c\u9ad8\u3055\u306b\u5fdc\u3058\u3066\u5782\u76f4\u53cd\u529b\u3092\u5236\u5fa1\u3059\u308b\u3053\u3068\u306b\u3088\u308a \u3070\u306d\u5b9a\u6570\u3092\u6301\u305f\u305b\u308b\u3053\u3068\u3082\u53ef\u80fd\u3067\u3042\u308b\uff0e 2.3 \u5236\u5fa1\u65b9\u5f0f\u306e\u6539\u5584\nUSPG2003\u306b\u304a\u3044\u3066\u306f\uff0c\u5404\u6cb9\u5727\u30b7\u30ea\u30f3\u30c0\u3067\u767a\u751f\u3059\u308b\u8ef8\u529b \u3092\uff0c\u5404\u8db3\u306b\u53d6\u308a\u4ed8\u3051\u305f\u5358\u8ef8\u30ed\u30fc\u30c9\u30bb\u30eb\u306b\u3088\u3063\u3066\u30d5\u30a3\u30fc\u30c9 \u30d0\u30c3\u30af\u5236\u5fa1\u3057\u3066\u304a\u308a\uff0c\u5404\u30b7\u30ea\u30f3\u30c0\u53d6\u4ed8\u3051\u4f4d\u7f6e\u306b\u8aa4\u5dee\u304c\u306a\u3044 \u3082\u306e\u3068\u4eee\u5b9a\u3057\u3066\uff0c\u76ee\u6a19FLP\u3092\u5b9f\u73fe\u3059\u308b\u5404\u8db3\u306e\u76ee\u6a19\u8ef8\u529b\u3092\u8a08 \u7b97\u3057\uff0c\u305d\u306e\u5024\u3092\u5404\u5236\u5fa1\u30eb\u30fc\u30d7\u306e\u76ee\u6a19\u5024\u3068\u3057\u3066\u4e0e\u3048\u3066\u3044\u305f\uff0e \u3057\u304b\u3057\uff0c\u5404\u8ef8\u529b\u304c\u76ee\u6a19\u5024\u901a\u308a\u306b\u767a\u751f\u3057\u3066\u3082\uff0c\u5404\u8db3\u306e\u4e21\u7aef\u306b \u4f4d\u7f6e\u3059\u308b\u30dc\u30fc\u30eb\u30b8\u30e7\u30a4\u30f3\u30c8\u3067\u6469\u64e6\u304c\u767a\u751f\u3057\uff0c\u5b9f\u969b\u306b\u751f\u6210\u3055 \u308c\u305fFLP\u304c\u3069\u3053\u306b\u6765\u3066\u3044\u308b\u304b\u306f\u77e5\u308b\u7531\u304c\u306a\u304b\u3063\u305f\uff0e\u307e\u305f\uff0c\nTable 2 Comparison of USPG2003/2013 specifications.Table 1 Definition of variables and terms.\nUSPG2003 USPG2013\nStroke 24 mm 40 mm\nMax Load 12,000 N 12,000 N\nFLP \u03d5 50 \u03d5 120\nSensor around strut axis around strut axis\nFeedback 6 axial load cells 1) FLP 2) Vertical reaction force 3) Mz\nA pp\nea ra\nnc e", + "\u3070\u306d\u8ad6\u6587\u96c6 \u7b2c60\u53f7\uff082015\uff09 31\n\u529b\u306e\u767a\u751f\u306b\u3088\u308a\u30ed\u30a2\u30b7\u30fc\u30c8\u304c\u5c11\u3057\u3067\u3082\u5909\u5f62\u3059\u308b\u3068\uff0c\u5404\u8db3\u306e \u53d6\u4ed8\u3051\u4f4d\u7f6e\u5ea7\u6a19\u304c\u5909\u308f\u308a\uff0c\u8a08\u7b97\u3055\u308c\u305f\u8ef8\u529b\u306e\u76ee\u6a19\u5024\u81ea\u4f53\u304c \u6b63\u3057\u3044\u3082\u306e\u3067\u306f\u306a\u304f\u306a\u3063\u3066\u3057\u307e\u3046\u3068\u3044\u3046\u554f\u984c\u304c\u3042\u3063\u305f\uff0e \u4e00\u65b9\uff0cUSPG2013\u3067\u306f\u5404\u8db3\u306b\u30ed\u30fc\u30c9\u30bb\u30eb\u306f\u5b58\u5728\u3057\u306a\u3044\uff0e \u30b7\u30fc\u30c8\u30a2\u30c0\u30d7\u30bf\u3068USPG\u306e\u5e3d\u5b50\u3068\u306e\u9593\u306b6\u5206\u529b\u8a08\u3092\u8a2d\u7f6e\u3057\uff0c \u30e6\u30cb\u30d0\u30fc\u30b5\u30eb\u30b8\u30e7\u30a4\u30f3\u30c8\u3084\u30b7\u30ea\u30f3\u30c0\u306e\u6469\u64e6\u306a\u3069\uff0c\u3059\u3079\u3066 \u3092\u542b\u3081\u305f\u4e0a\u3067\u7d50\u679c\u7684\u306b\u767a\u751f\u3059\u308bFLP\u3092\u76f4\u63a5\u8a08\u6e2c\u3059\u308b\u3088\u3046\u306b \u3057\u305f\uff0e\u305d\u3057\u3066\uff0c\u5236\u5fa1\u91cf\u306f\u5404\u8db3\u306e\u8ef8\u529b\u3067\u306f\u306a\u304f\uff0cFLP\u3092\u76f4\u63a5 \u30d5\u30a3\u30fc\u30c9\u30d0\u30c3\u30af\u5236\u5fa1\u3059\u308b\u3088\u3046\u306b\u3057\u305f\uff0e\u3053\u308c\u306b\u3088\u308a\uff0c\u8db3\u306e\u53d6 \u4ed8\u3051\u4f4d\u7f6e\u304c\u305a\u308c\u3066\u3082\uff0cFLP\u304c\u76ee\u6a19\u5024\u306b\u5408\u3046\u3088\u3046\u306b\u8ef8\u8db3\u306f\u81ea \u52d5\u8abf\u6574\u3055\u308c\uff0cFLP\u306e\u5b9f\u73fe\u7cbe\u5ea6\u304c\u98db\u8e8d\u7684\u306b\u6539\u5584\u3057\u305f\uff0e 2.4 \u5236\u5fa1\u7cfb\u306e\u8a2d\u8a08\nFig. 2\u306bUSPG2013\u306eSIMULINK\u30e2\u30c7\u30eb\u3092\u793a\u3059\uff0e\u8d64\u3044\u70b9 \u7dda\u3067\u56f2\u3093\u3060\u90e8\u5206\u306f\u6cb9\u5727\u30b7\u30ea\u30f3\u30c0\u3068\u305d\u306e\u8ef8\u529b\u3092\u691c\u51fa\u3059\u308b6\u5206 \u529b\u8a08\u306e\u30e2\u30c7\u30eb\u3067\u3042\u308a\uff0c\u5236\u5fa1\u7cfb\u8a2d\u8a08\u6642\u306b\u306f\u7d44\u307f\u8fbc\u3093\u3067\u3044\u308b \u304c\uff0c\u5b9f\u969b\u306e\u5236\u5fa1\u30d7\u30ed\u30b0\u30e9\u30e0\u306b\u306f\u7d44\u307f\u8fbc\u307e\u306a\u3044\u90e8\u5206\u3067\u3042\u308b\uff0e FLP\uff0c Pz\uff0cMz\u306e3\u3064\u306b\u5bfe\u3057\u3066\uff0c\u30e6\u30fc\u30b6\u304c\u76ee\u6a19\u5024\u3092\u8a2d\u5b9a\u3057\uff0c \u305d\u308c\u305e\u308c\u3092\u76ee\u6a19\u5024\u3078\u5236\u5fa1\u3059\u308b\u305f\u3081\u306e3\u3064\u306e\u72ec\u7acb\u3057\u305f\u30d5\u30a3\u30fc \u30c9\u30d0\u30c3\u30af\u30eb\u30fc\u30d7\u3092\u5f62\u6210\u3057\u305f\uff0e\u305d\u308c\u305e\u308c\u306e\u30eb\u30fc\u30d7\u306f\uff0c\u4f4d\u7f6e\u5b9a \u5e38\u504f\u5dee\u3092\u30bc\u30ed\u3068\u3059\u308b\u305f\u3081\u306b1\u578b\u5236\u5fa1\u3068\u3057\uff0cPI\uff08Proportional Integral\uff09\u30b3\u30f3\u30c8\u30ed\u30fc\u30e9\u3092\u633f\u5165\u3057\u305f\uff0e\u5177\u4f53\u7684\u306a\u8a08\u7b97\u5f0f\u306f\u3053\u3053 \u3067\u306f\u5272\u611b\u3059\u308b\uff0e 2.5 \u30bd\u30d5\u30c8\u30a6\u30a7\u30a2\u3078\u306e\u7d44\u307f\u8fbc\u307f\nSIMULINK\u30e2\u30c7\u30eb\u3067\u306e\u52d5\u4f5c\u78ba\u8a8d\u5f8c\uff0c\u5236\u5fa1\u90e8\u3092C++\u3067\u30b3\u30fc \u30c7\u30a3\u30f3\u30b0\u3057\uff0c\u30de\u30a4\u30af\u30ed\u30cd\u30c3\u30c8\u793e\u306eINtime\u30b7\u30b9\u30c6\u30e0\u306b\u7d44\u307f\u8fbc \u3093\u3060\uff0eINtime\u306f\uff0cWindows\u3088\u308a\u4f4e\u3044\u30ec\u30d9\u30eb\u306b\u5165\u308a\u8fbc\u3080\u30ea \u30a2\u30eb\u30bf\u30a4\u30e0OS\u3067\u3042\u308a\uff0cWindows\u306f\uff0c\u5272\u8fbc\u307f\u30d9\u30af\u30bf\u306e254\u756a 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5\u306b\u793a\u3059\u3088\u3046\u306b\uff0cUSPG2013\u3092\u901a\u5e38\u306e\u30b3\u30a4\u30eb\u3070\u306d\u53cd \u529b\u7dda\u6e2c\u5b9a\u6a5f\u306b\u8a2d\u7f6e\u3057\u305f\uff0e\u56f3\u4e2d\u306e\u9ec4\u8272\u70b9\u306f\uff0c\u53cd\u529b\u7dda\u6e2c\u5b9a\u6a5f\u306e \u30ed\u30fc\u30c9\u30bb\u30eb\u3067\u8a08\u6e2c\u3057\u305fFLP\uff0c\u9752\u70b9\u306fUSPG2013\u306e\u5185\u90e8\u30ed\u30fc \u30c9\u30bb\u30eb\u3067\u8a08\u6e2c\u3057\u305fFLP\u3092\u8868\u3059\uff0e\u3053\u308c\u3089\u3092\u30b3\u30a4\u30eb\u3070\u306d\u306e\u4e0a\u4e0b \u5ea7\u9762\u3067\u306eFLP\u3078\u305d\u308c\u305e\u308c\u5909\u63db\u3057\uff0c\u4e21\u8005\u3092\u6bd4\u8f03\u3059\u308b\uff0e\u9752\u70b9\u306f\uff0c USPG2013\u3078\u4e0e\u3048\u305f\u76ee\u6a19FLP\u306b\u5bfe\u3057\uff0c\u4f4d\u7f6e\u5b9a\u5e38\u504f\u5dee\u30bc\u30ed\u3067 \u5236\u5fa1\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u8aa4\u5dee\u304c\u00b10.1mm\u4ee5\u5185\u3067\u3042\u308b\u3053\u3068\u304c\u78ba\u8a8d \u3067\u304d\u3066\u3044\u308b\uff0e\u3064\u307e\u308a\uff0c\u4e0a\u4e0b\u5ea7\u9762\u4e0a\u3078\u5909\u63db\u3057\u305f\u4e21FLP\u304c\u4e00\u81f4" + ] + }, + { + "image_filename": "designv8_17_0002506_.srce.hr_file_390601-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002506_.srce.hr_file_390601-Figure1-1.png", + "caption": "Figure 1 Measurement of blade geometry by contact method - simultaneous measurement of several points, including the position of the gripper", + "texts": [ + " There are a number of technologies for their production, from the most advanced, such as the process of casting blades by the monocrystalline method, to manufacturing them on CNC machines or additive manufacturing [4], up to the electrochemical method, which has been used for decades. Shaping blades as a result of electrochemical machining is economically justified; however, this technology is sensitive to a number of factors affecting the change of process parameters such as temperature, value of flowing current, gap width, etc. The uniqueness of blade design requires a manual individualized grinding process for each piece, and then finishing polishing. In the field of blade geometry measurements, contact and contactless methods are used. Contact methods (Fig.1) involve the use of various types of automatic devices with measuring probes used to determine the dimensions of the blade at selected points. Examples of such devices are described in [5, 6]. Sometimes robots with measuring probes [7] are also used, but this solution can only be used in the case of low requirements regarding accuracy, because the accuracy of robots is relatively small. Coordinate measuring machines (CMM) [8] are also used. In non-contact methods laser devices [9] and various types of scanners [10] stationary mounted [11] or on robot arms [12] are used" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002722_download_58477_60372-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002722_download_58477_60372-Figure7-1.png", + "caption": "Figure 7: Meshed Cylinder block", + "texts": [ + "0005 Load(N) 1 1.0005 0.0005 Compression ratio 8 8.0006 0.0006 Specific fuel consumption(kg/Kwh) 0.6801 0.6904 0.0103 The developed cylinder block was subjected to Finite element analysis to ascertain the optimal values of the thermal condition of the component. The AutoCAD designed internal combustion engine component was imported into the Steady state thermal analysis environment of the Finite element ANSYS software. The component was meshed into 10190 and 19616 elements and nodes respectively as shown in Figure 7. The already meshed component had its cylindrical compartment inputted with a temperature of 100oC as shown in Figure 8. Also, a stagnant-air horizontal at 22oC was used as the convection value for the entire cylinder block as shown in Figure 9. The cylinder block was further subjected to temperature and total heat flux output analysis in order to ascertain the effect of the inputted parameters on the component as shown on Figures 10 and 11 respectively. The temperature output result showed that the highest temperature of 100oC occurred around the cylinderical bore axis while the lowest temperature of 51" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001810_2478_bipcm-2023-0030-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001810_2478_bipcm-2023-0030-Figure2-1.png", + "caption": "Fig. 2 \u2013 FEA model, global view.", + "texts": [ + " (1) is recommended by classical literature, (Boiangiu et al., 1967; Demian, 1980), in order to design a bimetal with optimum, maximum, deformation. A CAD model of the bimetal was defined parametric with FreeCAD. All the study cases, Table 1, were generated automatically using corresponding geometrical dimensions. The CAD models were meshed automatically, imposing conditions for finer mesh in the vicinity of the interface surface, Figs. 3-5. The models were considered encastred at the left end, Fig. 2. A variation of temperature of 100\u00b0C was applied to all studied cases. The physical proprieties for Invar and Copper were included from the library of materials available in FreeCAD. The investigation of the FEA results focussed on the following directions: a) Deformations Uz represents the deformation along Oz axis of the points situated on line AB, Fig. 1. For the D case, the Uz maximum value, at the right end, from FEA simulation is: UzMAX(FEA results) = 5.74 mm. In the D case, the value for UzMAX, at the right end was also calculated by use of analytical formulas recommended by (Young et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004559_tation-pdf-url_51513-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004559_tation-pdf-url_51513-Figure7-1.png", + "caption": "Figure 7. The ultrasound indentation device and a schematic representation of the procedure followed to create the tissue\u2019s force/deformation curve [52].", + "texts": [ + " The mechanical part should be mounted in such a way that the probe can be compressed/indented to different feet sizes. The motor can generate uniform movement of the probe. A number of studies which conducted experiments with ultrasound indentation device [52, 53] used a custom loading Viscoelasticity in Foot-Ground Interaction http://dx.doi.org/10.5772/64170 227 device that consists of a linear array ultrasound probe which was in series with a dynamometer (load cell) and mounted on a rigid frame (Figure 7). In addition to the use of indentation device in experimental analyses of the plantar soft tissue, this device has been commonly used to quantify the mathematical and finite element (FE) models that govern the behaviour of soft tissue during loading. This is discussed in the next section under mechanical behaviour model. Ultrasound strain elastography has been used for assessment of plantar soft tissue stiffness in patients with diabetic neuropathy and was recognised to have potentials for diagnosing tissue mechanical malfunction in clinical setting [54]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003138_y-asift__article.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003138_y-asift__article.pdf-Figure3-1.png", + "caption": "Figure 3: Geometric interpretation of affine decomposition.", + "texts": [ + " The perspective deformation of a plane object induced by a camera motion is a planar homographic transform, which is smooth, and therefore locally tangent to affine transforms u(x, y) 7\u2192 u(ax+ by+ e, cx+ dy+ f) in each image region. era Motion Any affine map A with strictly positive determinant which is not a similarity has a unique decomposition A = [ a b c d ] = H\u03bbR1(\u03c8)TtR2(\u03c6) = \u03bb [ cos\u03c8 \u2212 sin\u03c8 sin\u03c8 cos\u03c8 ] [ t 0 0 1 ] [ cos\u03c6 \u2212 sin\u03c6 sin\u03c6 cos\u03c6 ] , where \u03bb > 0, \u03bbt is the determinant of A, Ri are rotations, \u03c6 \u2208 [0,\u03a0), and Tt is a tilt, namely a diagonal matrix with first eigenvalue t > 1 and the second one equal to 1. Figure 3 shows a camera motion interpretation of the affine decomposition: \u03c6 and \u03b8 = arccos 1/t are the viewpoint angles, \u03c8 parameterizes the camera spin and \u03bb corresponds to the zoom. The camera (the small parallelogram on the top-right) is assumed to stay far away from the image u and starts from a frontal view u, i.e., \u03bb = 1, t = 1, \u03c6 = \u03c8 = 0. The camera can first move parallel to the object\u2019s plane: this motion induces a translation T that is eliminated by assuming without loss of generality that the camera axis meets the image plane at a fixed point" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002418__32_5_32_32_456__pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002418__32_5_32_32_456__pdf-Figure3-1.png", + "caption": "Fig. 3 Mechanism of the hand opening and closing (top view)", + "texts": [], + "surrounding_texts": [ + "\u4ee5\u4e0a\u306e\u91cd\u91cf\u304c\u3042\u308b\u304c\uff0c\u7fa9\u624b\u3092\u5207\u65ad\u7aef\u3067\u652f\u6301\u3059\u308b\u5207\u65ad\u8005\u306b\u3068\u3063\u3066 \u306f\u91cd\u304f\uff0c\u3088\u3046\u3084\u304f\u5165\u624b\u3057\u3066\u3082\u305d\u306e\u91cd\u3055\u306b\u6163\u308c\u305a\u306b\u4f7f\u7528\u3092\u4e2d\u6b62\u3059 \u308b\u30e6\u30fc\u30b6\u3082\u591a\u3044\uff0e 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\u2022\u8efd\u91cf\u30fb\u4f4e\u30b3\u30b9\u30c8\n\u5177\u4f53\u7684\u306a\u6570\u5024\u76ee\u6a19\u3068\u3057\u3066\u306f\uff0c500 [g] \u7a0b\u5ea6\u306e\u7269\u4f53\u3092\u628a\u6301\u3067\u304d\uff0c \u30bd\u30b1\u30c3\u30c8\u3092\u542b\u3081\u305f\u7dcf\u91cd\u91cf\u306f 300 [g]\uff0c6\u6642\u9593\u7a0b\u5ea6\u306e\u9023\u7d9a\u4f7f\u7528\u304c\u3067 \u304d\u308b\u3053\u3068\u3068\u3057\uff0c\u7247\u624b\u5207\u65ad\u8005\u306e\u5065\u5e38\u80a2\u306b\u5bfe\u3059\u308b\u88dc\u52a9\u80a2\u3068\u3057\u3066\u306e\u7528 \u9014\u3092\u4e3b\u306b\u60f3\u5b9a\u3057\u3066\u3044\u308b\uff0e \u672c\u7a3f\u3067\u306f\uff0c\u4e0a\u8a18\u958b\u767a\u65b9\u91dd\u306b\u57fa\u3065\u3044\u3066\u8a66\u4f5c\u3057\u305f\u96fb\u52d5\u7fa9\u624b\u3068\uff0c\u4e0a \u80a2\u6a5f\u80fd\u306e\u8a55\u4fa1\u30c6\u30b9\u30c8 SHAP\uff08Southampton Hand Assessment Procedure\uff09\u306b\u57fa\u3065\u3044\u305f\u5207\u65ad\u8005\u306b\u3088\u308b\u8a66\u4f5c\u7fa9\u624b\u306e\u8a55\u4fa1\u7d50\u679c\u306b\u3064 \u3044\u3066\u5831\u544a\u3059\u308b\uff0e\n2. \u6a5f\u80fd\u6027\u3068\u30c7\u30b6\u30a4\u30f3\u6027\u3092\u8003\u616e\u3057\u305f\u5bfe\u5411 3\u6307\u96fb\u52d5\u7fa9\u624b\nFig. 1\u306b\u8a66\u4f5c\u3057\u305f\u96fb\u52d5\u7fa9\u624b\uff08\u5de6\u624b\u7528\uff09\u306e\u5916\u89b3\u3092\u793a\u3059\uff0e\u7fa9\u624b\u306e \u69cb\u6210\u8981\u7d20\u306f\uff0c\u5927\u304d\u304f\u5206\u3051\u3066\u30cf\u30f3\u30c9\uff0c\u30cf\u30f3\u30c9\u30db\u30eb\u30c0\uff0c\u30bd\u30b1\u30c3\u30c8\uff0c\u8ddd \u96e2\u30bb\u30f3\u30b5\uff0c\u30b5\u30dd\u30fc\u30bf\u306b\u5206\u3051\u3089\u308c\u308b\uff0e\u30cf\u30f3\u30c9\u306f\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc \u30bf\u3067\u958b\u9589\u3059\u308b\u5bfe\u5411\u914d\u7f6e\u306e 3\u6307\u3092\u5099\u3048\u308b\uff0e\u524d\u8155\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u88c5 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\u3059\uff0e\u30cf\u30f3\u30c9\u306b\u306f\u52d5\u529b\u6e90\u306e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\uff08L12-R\uff0cFirgelli Technologies Inc\uff09\uff0c\u5236\u5fa1\u7528\u30de\u30a4\u30b3\u30f3\uff08Arduino Pro Mini\uff09\u304c\n\u5185\u8535\u3055\u308c\u3066\u3044\u308b\uff0eTable 1\u306b\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4ed5\u69d8\u3092\u793a \u3059\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306f\uff0c\u4f4d\u7f6e\u5236\u5fa1\u53ef\u80fd\u306a\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u3066\u3044\u308b\uff0e\u30cf\u30f3\u30c9\u5185\u90e8\u306b\u306f\u6307\u306e\u958b\u9589\u306e\u305f\u3081\u306b Fig. 3\u306b\u793a\u3059\u3088\u3046\u306a \u30ea\u30f3\u30af\u6a5f\u69cb\u3092\u63a1\u7528\u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u4f38\u7e2e\u3059\u308b \u30b7\u30e3\u30d5\u30c8\u5148\u7aef\u90e8\u306f\u30ea\u30f3\u30af 1\u306b\u76f4\u7d50\u3057\u3066\u3044\u308b\uff0e\u30b7\u30e3\u30d5\u30c8\u304c\u521d\u671f\u4f4d \u7f6e\u304b\u3089\u4f38\u5c55\u3059\u308b\u3068\uff0c\u305d\u308c\u306b\u4f34\u3063\u3066\u30ea\u30f3\u30af 1\u304c\u30cf\u30f3\u30c9\u5185\u90e8\u3092\u79fb\u52d5 \u3057\uff0c\u5916\u88c5\u90e8\u3068\u306e\u63a5\u70b9\u3092\u30ac\u30a4\u30c9\u3068\u3057\u3066\u30ea\u30f3\u30af 2\u304c\u7e70\u308a\u51fa\u3055\u308c\uff0c\u30b7\u30e3 \u30d5\u30c8\u3068\u30ea\u30f3\u30af 2\u304c\u6210\u3059\u89d2\u5ea6\u304c\u5897\u52a0\u3059\u308b\uff0e\u3053\u308c\u306b\u3088\u3063\u3066\uff0c\u6307\u304c\u958b \u304f\uff0e\u30b7\u30e3\u30d5\u30c8\u304c\u77ed\u7e2e\u3059\u308b\u3068\uff0c\u30b7\u30e3\u30d5\u30c8\u3068\u30ea\u30f3\u30af 2\u306e\u6210\u3059\u89d2\u5ea6\u304c \u6e1b\u5c11\u3057\uff0c\u30ea\u30f3\u30af 2\u304c\u30cf\u30f3\u30c9\u5185\u90e8\u306b\u5f15\u304d\u8fbc\u307e\u308c\u6307\u304c\u9589\u3058\u308b\uff0e3\u6307 \u304c\u540c\u69d8\u306b\u4f5c\u52d5\u3059\u308b\u3053\u3068\u3067\uff0c\u6307\u306e\u958b\u9589\u304c\u884c\u308f\u308c\u308b\uff0e\u3053\u306e\u3088\u3046\u306a\u30b7 \u30f3\u30d7\u30eb\u306a\u6307\u306e\u958b\u9589\u6a5f\u69cb\u306f\uff0c\u30cf\u30f3\u30c9\u306e\u8efd\u91cf\u5316\u3068\u5c0f\u578b\u5316\u306b\u5bc4\u4e0e\u3059\u308b\uff0e Fig. 2 \u306e\u6307\u306e\u65ad\u9762\u56f3\u3067\u793a\u3057\u305f\u3088\u3046\u306b\uff0c\u6307\u306e\u95a2\u7bc0\u306b\u306f\u30c8\u30fc\u30b7\u30e7 \u30f3\u30d0\u30cd\uff08\u3070\u306d\u5b9a\u6570 11.5 [N\u00b7mm/deg]\uff09\u3092\u7d44\u307f\u8fbc\u307f\uff0c\u7269\u4f53\u306b\u99b4\u67d3 \u3080\u3088\u3046\u306b\u628a\u6301\u3059\u308b\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u6307\u5148\u306b\u88c5\u7740\u3059\u308b\u30b7\u30ea\u30b3\u30f3 \u88fd\u30ad\u30e3\u30c3\u30d7\uff08\u786c\u5ea6 30\u5ea6\uff0c\u539a\u3055 1.5 [mm]\uff09\u306f\uff0c\u628a\u6301\u3057\u305f\u7269\u4f53\u304c\u6ed1 \u308b\u306e\u3092\u9632\u304e\uff0c\u9069\u5ea6\u306b\u67d4\u3089\u304b\u3044\u6307\u5148\u3092\u5b9f\u73fe\u3057\u3066\u3044\u308b\uff0e\u307e\u305f\uff0c\u6307\u5148 \u5168\u4f53\u304c\u30b7\u30ea\u30b3\u30f3\u3067\u8986\u308f\u308c\u308b\u305f\u3081\uff0c\u66f8\u7c4d\u306e\u30da\u30fc\u30b8\u3092\u6372\u308b\u5834\u5408\u3084\u673a \u4e0a\u306e\u7269\u4f53\u3092\u305f\u3050\u308a\u5bc4\u305b\u308b\u5834\u5408\u306b\u3082\u6709\u52b9\u3067\u3042\u308b\uff0e3\u6307\u306f\u540c\u4e00\u5f62\u72b6 \u306e\u305f\u3081\uff0c\u6545\u969c\u6642\u306e\u4ea4\u63db\u3082\u5bb9\u6613\u3067\u3042\u308b\uff0e\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201455\u2014 2014 \u5e74 6 \u6708", + "2. 2 \u5bfe\u5411\u914d\u7f6e\u306e 3\u6307 Fig. 4\u306b 3\u6307\u3092\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u914d\u7f6e\u3092\u793a\u3059\uff0e\u6b63\u9762\u304b\u3089\u898b \u3066\u6307\u5148\u4f4d\u7f6e\u304c\u5185\u5074\u3092\u9802\u89d2\u3068\u3059\u308b\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u3068\u306a\u308b\u3088\u3046\u306b\u914d\u7f6e \u3057\u3066\u3044\u308b\uff0e\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5\u30c8\u306e\u7e70\u308a\u51fa\u3057\u91cf\u304c\u540c\u3058 \u5834\u5408\uff0c\u6b63\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u3088\u308a\u3082\u4e8c\u7b49\u8fba\u4e09\u89d2\u5f62\u306e\u914d\u7f6e\u306e\u307b\u3046\u304c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\uff08\u4e21\u7aef\u77e2\u5370\u90e8\u5206\uff09\u3092\u3088\u308a\u5927\u304d\u304f\u78ba\u4fdd\u3067\u304d\u308b\uff0e500 [ml] \u306e\u30da\u30c3\u30c8\u30dc\u30c8\u30eb\u3092\u628a\u6301\u3067\u304d\u308b\u5341\u5206\u306a\u7a7a\u9593\u3092\u78ba\u4fdd\u3059\u308b\u305f\u3081\uff0c\u6307\u306e \u30b9\u30c8\u30ed\u30fc\u30af\u306f 80 [mm]\u3068\u3057\u305f\uff0e Fig. 5\u306e\u5de6\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\uff0cOttobock\u793e\u306a\u3069\u306e 3\u6307\u306e\u7b4b\u96fb \u7fa9\u624b\u306f\uff0c\u30ea\u30f3\u30af\u306e\u904b\u52d5\u65b9\u5411\u304c\u56de\u8ee2\u8ef8\u306b\u5bfe\u3057\u3066\u76f4\u4ea4\u3057\u3066\u3044\u308b\u305f\u3081\uff0c \u5e73\u677f\u72b6\u306e\u5bfe\u8c61\u3092\u628a\u6301\u3059\u308b\u5834\u5408\uff0c\u56de\u5185\u5916\u3092\u884c\u308f\u305a\u306b\u628a\u6301\u53ef\u80fd\u306a\u65b9 \u5411\u306f 1 \u7a2e\u985e\u306e\u307f\u3067\u3042\u308b\uff08\u4e00\u822c\u7684\u306a 2 \u6307\u80fd\u52d5\u30d5\u30c3\u30af\u3082\u540c\u69d8\uff09\uff0e\u4e00 \u65b9\uff0cFig. 5 \u306e\u53f3\u56f3\u306b\u793a\u3059\u3088\u3046\u306b\uff0c3 \u6307\u3092\u5bfe\u5411\u306b\u914d\u7f6e\u3059\u308b\u3068\uff0c\u56de\n\u5185\u5916\u3092\u884c\u308f\u305a\u306b 3\u7a2e\u985e\u306e\u628a\u6301\u65b9\u5411\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u80a9 \u3084\u4f53\u5e79\u306e\u52d5\u304d\u3067\u56de\u5185\u5916\u306e\u52d5\u304d\u3092\u88dc\u511f\u3059\u308b\u4ee3\u511f\u52d5\u4f5c\u3092\u6291\u5236\u3057\uff0c\u7121 \u7406\u306e\u306a\u3044\u59ff\u52e2\u3067\u306e\u64cd\u4f5c\u304c\u53ef\u80fd\u3068\u306a\u308b\uff0e3\u6307\u306b\u3088\u3063\u3066\u5177\u4f53\u7684\u306b\u3069 \u306e\u3088\u3046\u306a\u628a\u6301\u304c\u53ef\u80fd\u304b\u306f 3\u7ae0\u3067\u8ff0\u3079\u308b\uff0e 2. 3 \u30e6\u30fc\u30b6\u306e\u6307\u958b\u9589\u610f\u56f3\u3092\u691c\u51fa\u3059\u308b\u8ddd\u96e2\u30bb\u30f3\u30b5 \u63d0\u6848\u7fa9\u624b\u306f\u524d\u8155\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u88c5\u7740\u3057\uff0c\u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u30bb \u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u5fdc\u3058\u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\u65b9\u5f0f\u3092\u7528 \u3044\u3066\u3044\u308b\uff0eFig. 6\u306b\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5916\u89b3\u3092\u793a\u3059\uff0e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306b\u306f\uff0c \u975e\u63a5\u89e6\u3067\u8ddd\u96e2\u304c\u8a08\u6e2c\u53ef\u80fd\u306a\u30d5\u30a9\u30c8\u30ea\u30d5\u30ec\u30af\u30bf\uff08SG-105\uff0cKODENSHI\uff09\u3092\u7528\u3044\u305f\uff0e\u7b4b\u53ce\u7e2e\u3092\u884c\u3063\u3066\u3044\u306a\u3044\u72b6\u614b\u3067\uff0c\u8ddd\u96e2\u30bb\u30f3 \u30b5\u3068\u76ae\u819a\u9593\u306e\u8ddd\u96e2\u3092\u4e00\u5b9a\u306b\u4fdd\u3064\u305f\u3081\uff0c\u57fa\u677f\u4e0a\u306b\u914d\u7f6e\u3057\u305f\u30d5\u30a9\u30c8 \u30ea\u30d5\u30ec\u30af\u30bf\u306e\u4e0a\u4e0b\u306b\u9ad8\u3055 5 [mm] \u306e\u30dd\u30ea\u30de\u30fc\u30b7\u30fc\u30c8\uff08PORON L-24, \u30a4\u30ce\u30a2\u30c3\u30af\uff09\u306e\u30b9\u30da\u30fc\u30b5\u3092\u8a2d\u3051\u305f\uff0e\u3053\u306e\u30bb\u30f3\u30b5\u3092\u524d\u8155\u5207 \u65ad\u7aef\u306e\u7b4b\u53ce\u7e2e\u306b\u5fdc\u3058\u3066\u76ae\u819a\u8868\u9762\u306b\u9686\u8d77\u304c\u898b\u3089\u308c\u308b\u5834\u6240\uff0c\u4f8b\u3048\u3070\uff0c \u5c3a\u5074\u624b\u6839\u5c48\u7b4b\u306e\u76f4\u4e0a\u306a\u3069\u306b\u88c5\u7740\u3059\u308b\uff0e\u30bb\u30f3\u30b5\u306f\u4f38\u7e2e\u6027\u306e\u30d0\u30f3\u30c9 \u306a\u3069\u3067\u56fa\u5b9a\u3059\u308b\u304b\uff0c\u5f8c\u8ff0\u3059\u308b\u30bd\u30b1\u30c3\u30c8\u306e\u5185\u5074\u306b\u56fa\u5b9a\u3059\u308b\uff0e\u975e\u63a5 \u89e6\u306e\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u4f7f\u7528\u3059\u308b\u3053\u3068\u306b\u3088\u308a\uff0c\u7b4b\u96fb\u30bb\u30f3\u30b5\u306e\u6b20\u70b9\u3067\u3042 \u308b\u6c57\u306b\u3088\u308b\u8aa4\u52d5\u4f5c\u306e\u554f\u984c\u304c\u306a\u304f\uff0c\u91d1\u5c5e\u96fb\u6975\u304c\u76f4\u63a5\u76ae\u819a\u306b\u89e6\u308c\u306a \u3044\u30e1\u30ea\u30c3\u30c8\u304c\u3042\u308b\uff0e\u307e\u305f\uff0c\u30d5\u30a9\u30c8\u30ea\u30d5\u30ec\u30af\u30bf\u306f\u5b89\u4fa1\u306b\u8cfc\u5165\u53ef\u80fd \u306a\u6c4e\u7528\u96fb\u5b50\u90e8\u54c1\u306e\u305f\u3081\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u5168\u4f53\u3067\u3082 300\u5186\u7a0b\u5ea6\u3067\u88fd\u4f5c \u53ef\u80fd\u3067\u3042\u308a\uff0c\u7b4b\u96fb\u30bb\u30f3\u30b5\u306b\u6bd4\u3079\u3066\u5927\u5e45\u306a\u4f4e\u30b3\u30b9\u30c8\u5316\u3092\u56f3\u308c\u308b\uff0e 2. 4 \u8ddd\u96e2\u30bb\u30f3\u30b5\u306b\u57fa\u3065\u304f\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0 \u7b4b\u53ce\u7e2e\u6642\u306b\u304a\u3051\u308b\u8ddd\u96e2\u30bb\u30f3\u30b5\u3068\u76ae\u819a\u8868\u9762\u9593\u306e\u8ddd\u96e2\u5909\u5316\u306b\u57fa\u3065 \u3044\u3066\u6307\u306e\u958b\u9589\u3092\u884c\u3046\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e\u672c\u8ad6\u6587\u3067\u8aac\nJRSJ Vol. 32 No. 5 \u201456\u2014 June, 2014", + "\u660e\u3059\u308b\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306f\uff0c\u7b4b\u53ce\u7e2e\u306b\u3088\u308a\u6307\u304c\u958b\u304d\uff0c\u7b4b\u53ce\u7e2e\u3057\u306a\u3044 \u5834\u5408\u306f\u9589\u3058\u308b\u65b9\u5f0f\u306b\u306a\u3063\u3066\u3044\u308b\uff0e\u3059\u306a\u308f\u3061\uff0c\u80fd\u52d5\u30d5\u30c3\u30af\u306b\u304a\u3044\u3066 \u30cf\u30fc\u30cd\u30b9\u3092\u4ecb\u3057\u3066\u30b1\u30fc\u30d6\u30eb\u3092\u727d\u5f15\u3059\u308b\u3068\u6307\u304c\u958b\u304f\u30dc\u30e9\u30f3\u30bf\u30ea\u30fc \u30aa\u30fc\u30d7\u30f3\u3068\u540c\u69d8\u306e\u65b9\u5f0f\u3067\u3042\u308b\uff0e\u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306f\u30cf\u30f3\u30c9\u306b\u5185\u8535\u3057 \u305f\u30de\u30a4\u30b3\u30f3\uff08Arduino Pro Mini\uff09\u306b\u5b9f\u88c5\u3057\u3066\u3044\u308b\uff0e\u8ddd\u96e2\u30bb\u30f3 \u30b5\u306f\u30de\u30a4\u30b3\u30f3\u306b\u63a5\u7d9a\u3055\u308c\uff0c\u30de\u30a4\u30b3\u30f3\u5185\u8535\u306e AD\u5909\u63db\u6a5f\u80fd\u306b\u3088\u3063 \u3066\uff0c\u30b5\u30f3\u30d7\u30ea\u30f3\u30b0\u5468\u6ce2\u6570 100 [Hz] \u3067\u30b5\u30f3\u30d7\u30ea\u30f3\u30b0\u3059\u308b\uff0e\u30b5\u30f3 \u30d7\u30ea\u30f3\u30b0\u3057\u305f\u5024\u306f\u73fe\u5728\u5024 x(n) \u3068\u904e\u53bb 9 \u70b9\uff0c\u5168 10 \u70b9\u306e\u5358\u7d14\u79fb \u52d5\u5e73\u5747\u306b\u3088\u308a\u5e73\u6ed1\u5316\u3055\u308c\u308b\uff0e\u3053\u3053\u3067\uff0cn \u70b9\u3081\u306e\u5e73\u6ed1\u5316\u5f8c\u306e\u5024\u3092 xs(n)(n = 0, \u00b7 \u00b7 \u00b7 , N) \u3068\u3059\u308b\uff0e \u64cd\u4f5c\u30b7\u30b9\u30c6\u30e0\u306e\u51e6\u7406\u306e\u6d41\u308c\u3092 Fig. 7\u306b\u793a\u3059\uff0e\u307e\u305a\uff0c\u64cd\u4f5c\u3092\u884c \u3046\u524d\u306b\u30e6\u30fc\u30b6\u306b\u5408\u308f\u305b\u3066\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u3092\u884c\u3046\uff0e\u30cf\u30f3\u30c9\u672c \u4f53\u306e\u30b9\u30a4\u30c3\u30c1\u3092\u9577\u62bc\u3057\u3059\u308b\u3068\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u958b\u59cb\u3055\u308c\u308b\uff0e \u306f\u3058\u3081\u306b\uff0c\u8ddd\u96e2\u30bb\u30f3\u30b5\u3092\u524d\u8155\u306b\u88c5\u7740\u3057\u305f\u72b6\u614b\u3067\u30b9\u30a4\u30c3\u30c1\u3092\u62bc\u3057\uff0c \u7b4b\u53ce\u7e2e\u3057\u3066\u3044\u306a\u3044\u5e73\u5e38\u6642\u306e\u30bb\u30f3\u30b5\u5024\u3092 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3057\uff0c \u305d\u306e\u5e73\u5747\u5024 Xrest \u3092\u8a08\u7b97\u3059\u308b\uff0e\u6b21\u306b\uff0c\u6700\u5927\u306b\u7b4b\u53ce\u7e2e\u3057\u305f\u72b6\u614b\u3067 \u30b9\u30a4\u30c3\u30c1\u3092\u518d\u5ea6\u62bc\u3059\u3068\uff0c\u30bb\u30f3\u30b5\u5024\u304c 1\u79d2\u9593\uff08100\u70b9\uff09\u53d6\u5f97\u3055\u308c\uff0c \u305d\u306e\u5e73\u5747\u5024 Xmax \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e\u6b21\u306b\uff0cXmax \u3068 Xrest \u306e\u5dee\u5206 Xdif \u3092\u6b21\u5f0f\u3067\u8a08\u7b97\u3059\u308b\uff0e\nXdif = Xmax \u2212Xrest \uff081\uff09\n\u3053\u306e Xdif \u3068\u6307\u304c\u6700\u5927\u306b\u958b\u3044\u305f\u3068\u304d\u306e\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306e\u30b7\u30e3\u30d5 \u30c8\u306e\u6700\u5927\u7e70\u308a\u51fa\u3057\u91cf Lmax \u3092\u7528\u3044\u3066\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u99c6\u52d5\u30d1\u30e9\u30e1\u30fc \u30bf R \u3092\u6c7a\u5b9a\u3059\u308b\uff0e\nR = Lmax\nXdif \uff082\uff09\n\u4ee5\u4e0a\u3067\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u304c\u7d42\u4e86\u3059\u308b\uff0e\u3053\u306e\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7 \u30f3\u30d7\u30ed\u30bb\u30b9\u306f\uff0c3\u56de\u306e\u30b9\u30a4\u30c3\u30c1\u64cd\u4f5c\u3067\u884c\u3048\u308b\u305f\u3081\u30e6\u30fc\u30b6\u81ea\u8eab\u3067 \u884c\u3046\u3053\u3068\u304c\u53ef\u80fd\u3067\u3042\u308b\uff0e\u307e\u305f\uff0c3 \u79d2\u4ee5\u5185\u306b\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3 \u304c\u5b8c\u4e86\u3059\u308b\u306e\u3067\uff0c\u518d\u30ad\u30e3\u30ea\u30d6\u30ec\u30fc\u30b7\u30e7\u30f3\u306b\u6642\u9593\u3092\u5fc5\u8981\u3068\u3057\u306a\u3044\uff0e \u6b21\u306b\u64cd\u4f5c\u6642\u306b\u3064\u3044\u3066\u8aac\u660e\u3059\u308b\uff0e\u64cd\u4f5c\u6642\u306e\u8ddd\u96e2\u30bb\u30f3\u30b5\u306e\u5e73\u6ed1\u5316 \u5f8c\u306e\u5024\u3092 xs(k)(k = 0, \u00b7 \u00b7 \u00b7 ,K) \u3068\u3059\u308b\u3068\uff0c\u6b21\u5f0f\u306b\u3088\u308a\u30b7\u30e3\u30d5\u30c8 \u306e\u7e70\u308a\u51fa\u3057\u91cf l(k) \u304c\u8a08\u7b97\u3055\u308c\u308b\uff0e\nl(k) = R(xs(k)\u2212Xrest) \uff083\uff09\n\u3053\u306e\u3068\u304d\uff0c\u4f55\u3089\u304b\u306e\u539f\u56e0\u306b\u3088\u308a l(k) > Lmax \u3068\u306a\u3063\u305f\u5834\u5408\u306f\uff0c l(k) = Lmax \u3068\u3057\uff0cl(k) \u306e\u5024\u3092\u6307\u4ee4\u5024\u3068\u3057\u3066\u30b5\u30fc\u30dc\u6a5f\u69cb\u3092\u6301\u3063 \u305f\u30ea\u30cb\u30a2\u30a2\u30af\u30c1\u30e5\u30a8\u30fc\u30bf\u306b\u9001\u308b\uff0e 2. 5 \u30bd\u30b1\u30c3\u30c8\u5f62\u72b6\u3068\u30cf\u30f3\u30c9\u30db\u30eb\u30c0 Fig. 8 \u306b\u65ad\u7aef\u3092\u633f\u5165\u3059\u308b\u5de6\u624b\u7528\u306e\u30bd\u30b1\u30c3\u30c8\u3068\u30cf\u30f3\u30c9\u30db\u30eb\u30c0 \u3092\u793a\u3059\uff0e\u30bd\u30b1\u30c3\u30c8\u306e\u9060\u4f4d\u7aef\u306f\u30cf\u30f3\u30c9\u30db\u30eb\u30c0\u3068\u63a5\u7d9a\u3057\uff0c\u30cf\u30f3\u30c9\u3092\n\u65e5\u672c\u30ed\u30dc\u30c3\u30c8\u5b66\u4f1a\u8a8c 32 \u5dfb 5 \u53f7 \u201457\u2014 2014 \u5e74 6 \u6708" + ] + }, + { + "image_filename": "designv8_17_0002387__cdbme-2023-1152_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002387__cdbme-2023-1152_pdf-Figure1-1.png", + "caption": "Fig. 1: Illustration of a microstent for minimally invasive treatment of Fallopian tube occlusions. Section A-A of Fallopian tube and microstent with radial loading F and simplified in vitro as well as in silico setup for the analysis of microstent loading behavior, in numerical and experimental investigations, respectively.", + "texts": [ + " These methods gain pregnancy rates of approximately 50% but are referred to high costs (IVF), physical stress (surgery) or significant reocclusion rates (catheterisation). Compared, every method gains a high level of psychological stress [2,3]. Based on tubal catheterisation, we previously presented the concept of a selfexpanding polymeric microstent for a minimally invasive treatment option of Fallopian tube occlusions [4,5]. Within the current work, the performance of the microstent during diameter reduction due to implantation was investigated in vitro and in silico. Figure 1 illustrates the radial loading situation for the microstent by the Fallopian tube tissue. ______ *Corresponding author: Ariane Dierke: Institute for ImplantTechnology and Biomaterials e.V., FriedrichBarnewitz-Str. 4, 18119 Rostock-Warnem\u00fcnde, Germany, e-mail: ariane.dierke@iib-ev.de Laura Supp, Hagen Paetow, Thomas Stahnke, Michael Stiehm, Andrea Bock, Klaus-Peter Schmitz, Stefan Siewert: Institute for ImplantTechnology and Biomaterials e.V., RostockWarnem\u00fcnde, Germany Paula Rosam: Department of Obstetrics and Gynecology, University Hospitals Schleswig-Holstein, Kiel, Germany Luise Knorre, Klaus-Peter Schmitz: Institute for Biomedical Engineering, Rostock University Medical Center, RostockWarnem\u00fcnde, Germany Marek Zygmunt: Department of Obstetrics and Gynecology, University Medicine Greifswald, Greifswald, Germany Therefore, microstent prototypes with an outer diameter do = (2" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000268_7_10_27_10_1169__pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000268_7_10_27_10_1169__pdf-Figure1-1.png", + "caption": "Fig. 1 Lateral motion and natural frequency design strategy", + "texts": [ + " 1 \u5186\u5f27\u534a\u5f84\u3068\u7b49\u4fa1\u306a\u30d0\u30cd\u5b9a\u6570\u306e\u9078\u5b9a\uff08\u30b5\u30b8\u30bf\u30eb\u5e73\u9762\u5185\uff09 \u307e\u305a\uff0c\u30b5\u30b8\u30bf\u30eb\u5e73\u9762\u5185\u306e\u904b\u52d5\u3092\u62d8\u675f\u3059\u308b\u8db3\u9996\u30d0\u30cd\u306e\u8a2d\u8a08\u65b9\u6cd5 \u306b\u3064\u3044\u3066\u8ff0\u3079\u308b\uff0e\u30b5\u30b8\u30bf\u30eb\u5e73\u9762\u5185\u306b\u304a\u3044\u3066\u8db3\u9996\u30d0\u30cd\u3068\u6241\u5e73\u8db3\u3092 \u7528\u3044\u308b\u3053\u3068\u306e\u6709\u52b9\u6027\u306f Hobbelen\u3089 [11]\u3084Wisse\u3089 [7] \u306b\u3088\u3063 \u3066\u793a\u3055\u308c\u3066\u3044\u308b\uff0eWisse\u3089 [7]\u306b\u3088\u308c\u3070\uff0c\u5186\u5f27\u8db3\u306b\u3088\u308b\u652f\u6301\u70b9\u306e \u79fb\u52d5\u306f\uff0c\u8db3\u9996\u30d0\u30cd\u306b\u3088\u308b ZMP\u306e\u79fb\u52d5\u306b\u7b49\u4fa1\u3068\u898b\u306a\u3059\u3053\u3068\u304c\u3067 \u304d\u308b\uff0e\u7cfb\u5168\u4f53\u306e\u8cea\u91cf\u3092 M\uff0c\u91cd\u529b\u52a0\u901f\u5ea6\u3092 g\uff0c\u5186\u5f27\u8db3\u534a\u5f84\u3092 RS\uff0c \u306d\u3058\u308a\u30d0\u30cd\u5b9a\u6570\u3092 k\u03b8 \u3068\u3059\u308b\u3068\u6b21\u5f0f\u304c\u6210\u308a\u7acb\u3064 [7]\uff0e k\u03b8 = MgRS \uff081\uff09 2. 2 \u30ed\u30fc\u30eb\u8ef8\u56de\u308a\u306e\u30d0\u30cd\u5b9a\u6570 \u6b21\u306b\uff0c\u30e9\u30c6\u30e9\u30eb\u5e73\u9762\u5185\u306e\u904b\u52d5\u3092\u8003\u3048\u308b\uff0eFig. 1\u5de6\u56f3\u306b\u793a\u3059\u3088 \u3046\u306b\uff0c\u30e9\u30c6\u30e9\u30eb\u65b9\u5411\u306e\u63fa\u52d5\u3092\u7a4d\u6975\u7684\u306b\u767a\u751f\u3055\u305b\u308b\u305f\u3081\uff0c\u811a\u304c\u925b \u76f4\u59ff\u52e2\u304b\u3089\u5916\u5074\u306b\u50be\u3044\u305f\u3068\u3053\u308d\u3067\u5e73\u8861\u70b9\u3092\u6301\u3064\u3088\u3046\u306b\u8db3\u3092\u50be\u659c \u3055\u305b\u3066\u53d6\u308a\u4ed8\u3051\u308b\uff0eKuo [4]\u306f\uff0c\u3053\u306e\u50be\u659c\u306b\u3088\u3063\u3066\u7cfb\u5168\u4f53\u306e\u91cd\u5fc3 \u4f4d\u7f6e\u304c\u652f\u6301\u8db3\u4e0a\u65b9\u306b\u79fb\u52d5\u3057\u9759\u7684\u5b89\u5b9a\u6027\u304c\u78ba\u4fdd\u3055\u308c\u308b\u3053\u3068\u3067\uff0c\u6b69 \u884c\u306e\u52d5\u7684\u5b89\u5b9a\u5316\u3078\u306e\u52b9\u679c\u3092\u671f\u5f85\u3057\u3066\u3044\u308b\uff0e\u3057\u304b\u3057\uff0cKuo [4]\u306f\u8db3 \u9996\u306b\u95a2\u7bc0\u3092\u3082\u3046\u3051\u3066\u3044\u306a\u304b\u3063\u305f\u305f\u3081\uff0c\u8db3\u5916\u7e01\u3092\u4e2d\u5fc3\u3068\u3057\u305f\u30ed\u30fc \u30eb\u56de\u8ee2\u304c\u767a\u751f\u3057\uff0c\u63a5\u5730\u9762\u3092\u7dad\u6301\u3067\u304d\u306a\u3044\u3060\u3051\u3067\u306a\u304f\uff0c\u8ee2\u5012\u3059\u308b \u3068\u3044\u3046\u554f\u984c\u304c\u3042\u308a\uff08Fig. 1\u5de6\u7aef\uff09\uff0c\u63a5\u5730\u9762\u5185\u306b\u5727\u529b\u4e2d\u5fc3\u3092\u914d\u7f6e\u3059 \u308b\u305f\u3081\u306e\u52d5\u7684\u88dc\u511f\u5668\u3092\u7528\u3044\u3066\u3044\u308b\uff0e\u3053\u308c\u306b\u5bfe\u3057\u7b46\u8005\u3089\u306f\uff0c\u30d0\u30cd \u306b\u3088\u3063\u3066\u63a5\u5730\u9762\u3092\u78ba\u4fdd\u3057\u3064\u3064\u30ed\u30fc\u30eb\u904b\u52d5\u3055\u305b\u308b\u3053\u3068\u3092\u8003\u3048\u308b\uff0e \u30e9\u30c6\u30e9\u30eb\u5e73\u9762\u5185\u3067\u8db3\u9996\u306b\u30d0\u30cd\u3092\u3082\u3046\u3051\u305f\u5834\u5408\uff08Fig. 1 \u5de6\u304b\u3089 2 \u756a\u76ee\uff09\uff0c\u5916\u5074\u306b\u56de\u8ee2\u3057\u305f\u3068\u3053\u308d\u3067\u30d0\u30cd\u304c\u52b9\u304d\u59cb\u3081 ZMP \u304c\u5916\u306b \u79fb\u52d5\u3059\u308b\uff0e\u3053\u308c\u306b\u3088\u3063\u3066\uff0c\u5916\u5074\u306b\u8ee2\u5012\u3057\u3088\u3046\u3068\u3057\u3066\u3044\u305f\u91cd\u5fc3\u3092 \u8db3\u5e95\u306b ZMP\u304c\u3068\u3069\u3081\u3089\u308c\u308b\u7bc4\u56f2\u3067\u5185\u5074\uff08\u904a\u811a\u5074\uff09\u306b\u5f15\u304d\u623b\u3055 \u308c\uff0c\u8db3\u5e95\u306e\u63a5\u5730\u72b6\u614b\u304c\u7dad\u6301\u3067\u304d\u308b\uff0e\u3053\u3053\u3067\uff0c\u91cd\u5fc3\u306e\u56de\u8ee2\u89d2\u5ea6\u3092 \u03c6\uff0cZMP\u307e\u3067\u306e\u8ddd\u96e2\u3092 dZMP\uff0c\u30ed\u30fc\u30eb\u8ef8\u56de\u308a\u306e\u306d\u3058\u308a\u30d0\u30cd\u4fc2\u6570 \u3092 k\u03c6 \u3068\u3057\uff0c\u52a0\u901f\u5ea6\u304c\u5341\u5206\u5c0f\u3055\u3044\u3068\u4eee\u5b9a\u3059\u308b\u3068\uff0c\u30e2\u30fc\u30e1\u30f3\u30c8\u306e \u91e3\u308a\u5408\u3044\u304b\u3089 MgdZMP = k\u03c6\u03c6 \uff082\uff09 \u304c\u6210\u308a\u7acb\u3064\uff0e\u3053\u3053\u3067\uff0cZMP\u3068\u56de\u8ee2\u89d2\u5ea6\u306e\u4e0a\u9650\u3092\u305d\u308c\u305e\u308c d\u0304ZMP\uff0c \u03c6\u0304 \u3068\u3059\u308b\u3068\uff0c\u30d0\u30cd\u5b9a\u6570\u306f\u6b21\u5f0f\u3092\u6e80\u305f\u3059\u5fc5\u8981\u304c\u3042\u308b\uff0e k\u03c6 < Mgd\u0304ZMP /\u03c6\u0304 \uff083\uff09 \u3055\u3089\u306b\uff0c\u30e9\u30c6\u30e9\u30eb\u5e73\u9762\u5185\u306e\u7b49\u4fa1\u5186\u5f27\u534a\u5f84 RL \u3068 \u03c6\u0304 \u306b\u3088\u308b\u652f\u6301\u70b9 \u306e\u79fb\u52d5\u91cf\u304c ZMP\u306e\u6700\u5927\u79fb\u52d5\u91cf\u306b\u7b49\u3057\u3044\uff0c\u3064\u307e\u308a\uff0cd\u0304ZMP \u2248 RL\u03c6\u0304 \u3068\u3057\u3066\u5f0f\uff083\uff09\u306b\u4ee3\u5165\u3059\u308c\u3070 k\u03c6 < MgRL \uff084\uff09 \u3068\u306a\u308b\uff0e\u91cd\u5fc3\u4f4d\u7f6e\u304c\u4e21\u811a\u9593\u306e\u4e2d\u5fc3\u306b\u3042\u308b\u305f\u3081\uff08Fig. 1\u53f3\uff09\uff0c\u5e73\u8861 \u70b9\u304b\u3089\u305a\u308c\u305f\u4f4d\u7f6e\u3067\u6b69\u884c\u6a5f\u306f\u30ed\u30fc\u30eb\u904b\u52d5\u3059\u308b\uff0e\u305d\u306e\u305f\u3081\uff0c\u5358\u7d14 \u306b\u632f\u5b50\u3068\u3057\u3066\u306e\u5b89\u5b9a\u6027\u306f\u6210\u308a\u7acb\u305f\u306a\u3044\u304c\uff0cRL \u304c\u8db3\u9996\u2013\u91cd\u5fc3\u9593\u8ddd \u96e2 lG \u3088\u308a\u5927\u304d\u3051\u308c\u3070\u91cd\u529b\u632f\u5b50\u306e\u610f\u5473\u3067\u5b89\u5b9a\u3067\u3042\u308b\uff0eZMP\u306e\u79fb \u52d5\u91cf\u3092\u56de\u8ee2\u89d2\u5ea6 \u03c6 \u306b\u5bfe\u3057\u3066\u5c0f\u3055\u304f\u3057\u305f\u3044\u5834\u5408\uff0cRL \u3092\u5c0f\u3055\u3081\u306b \u53d6\u308c\u3070\u3088\u3044\u304c\u4e0d\u5b89\u5b9a\u5316\u3059\u308b\u53ef\u80fd\u6027\u304c\u3042\u308b\uff0e\u03c6 \u3092\u62bc\u3055\u3048\u308b\u5834\u5408\u306f\uff0c RL \u3092\u5927\u304d\u304f\u3057 k\u03c6 \u3092\u4e0a\u9650\u306b\u8fd1\u304f\u53d6\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e 2", + " 6\u306b\u793a\u3059\uff0e\u3053\u306e\u56f3 \u304b\u3089\uff0c\u521d\u3081\u306e 10\u6b69\uff080.7 [s]\uff5e5 [s]\uff09\u306f\u6b69\u884c\u89d2\u632f\u52d5\u6570 7.2 [rad/s]\uff0c \u5e73\u5747\u6b69\u5e45 45 [mm]\u3067\u6b69\u884c\u3057\uff0c\u305d\u306e\u5f8c 6.0 [rad/s]\uff0c54 [mm] \u3068\u5909 \u5316\u3057\u3066\u3044\u308b\u3053\u3068\u304c\u5206\u304b\u308b\uff08\u3053\u306e\u3088\u3046\u306a\u50be\u5411\u306f\uff0c10 \u56de\u4e2d 8 \u56de\u898b \u3089\u308c\u305f\uff09\uff0e\u3053\u308c\u306f\uff0c\u524d\u534a\uff0c\u8db3\u5e95\u304c\u5b8c\u5168\u306b\u8def\u9762\u3068\u63a5\u89e6\u3057\u306a\u304c\u3089\u6b69\u884c \u3059\u308b\u304c\uff0c5 [s] \u4ed8\u8fd1\u3067\u5de6\u53f3\u306e\u632f\u5e45\u304c\u5927\u304d\u304f\u306a\u308a\u652f\u6301\u8db3\u306e\u5185\u5074\u304c\u6301 \u3061\u4e0a\u304c\u308b\u5f62\u3067\u6b69\u884c\u3057\u305f\u305f\u3081\uff0c\u632f\u52d5\u304c\u9045\u304f\u306a\u308a\uff0c\u305d\u308c\u306b\u4f34\u3063\u3066\u6b69 \u5e45\u304c\u62e1\u5927\u3057\u305f\u3053\u3068\u306b\u3088\u308b\uff08\u3053\u306e\u305f\u3081\u8db3\u5e95\u5916\u7e01\u306b\u5e45 10 [mm]\u7a0b\u5ea6 \u306e\u6ed1\u308a\u6b62\u3081\u3092\u8a2d\u3051\u308b\u5fc5\u8981\u304c\u3042\u3063\u305f\uff09\uff0e\u3055\u3089\u306b\uff0c\u659c\u9762\u50be\u659c\u3092\u5927\u304d\u304f \uff087.1 [deg]\uff09\u3059\u308b\u3068\u6b69\u5e45\u3068\u5de6\u53f3\u632f\u5e45\u304c\u62e1\u5927\u3059\u308b\u305f\u3081 3\u5272\u306f\u6a2a\u306b\u8ee2 \u5012\u3057\uff0c\u50be\u659c\u3092\u5c0f\u3055\u304f\uff086.2 [deg]\uff09\u3059\u308b\u3068\u6b69\u5e45\uff0c\u5de6\u53f3\u632f\u5e45\u3068\u3082\u306b \u6f38\u6e1b\u3057\uff0c\u3059\u3079\u3066\u306e\u5b9f\u9a13\u3067\u9014\u4e2d\u505c\u6b62\u3057\u305f\uff0e\u3053\u306e\u3053\u3068\u304b\u3089\uff0c\u03b2 = 0 \u3067\u306f\u30e9\u30c6\u30e9\u30eb\u632f\u52d5\u304c\u901f\u3059\u304e\u308b\u305f\u3081\uff0c\u3088\u308a\u632f\u52d5\u6570\u306e\u9045\u3044\u6b69\u884c\u30e2\u30fc \u30c9\u306b\u5207\u308a\u66ff\u308f\u308b\u3053\u3068\u3067\uff0c\u8db3\u5e95\u306e\u63a5\u5730\u72b6\u614b\u306f\u78ba\u4fdd\u3067\u304d\u306a\u3044\u304c\u5b89\u5b9a \u3057\u305f\u6b69\u884c\u3068\u306a\u3063\u305f\u3082\u306e\u3068\u8003\u3048\u3089\u308c\u308b\uff0e\u307e\u305f\uff0c\u524d\u8ff0\u3057\u305f\u7d50\u679c\u3068\u6bd4 \u8f03\u3059\u308b\u3068\u8db3\u5916\u7e01\u3092\u4e0a\u306b\u3042\u3052\u308b\u3088\u3046\u306b\u8db3\u3092\u53d6\u308a\u4ed8\u3051\u308b\uff08Fig. 1\uff09\u3068 \u632f\u52d5\u304c\u9045\u304f\u306a\u308b\u3053\u3068\u3082\u5206\u304b\u308b\uff0e\u904a\u811a\u306e\u56fa\u6709\u632f\u52d5\u6570\u306f\u4e00\u5b9a\u3067\u3042\u308b \u306e\u3067\uff0c\u3053\u306e\u3053\u3068\u304b\u3089\u6b69\u884c\u306e\u632f\u52d5\u6570\u306f\u30e9\u30c6\u30e9\u30eb\u904b\u52d5\u306e\u632f\u52d5\u6570\u306b\u4f9d \u5b58\u3057\u3066\u5909\u5316\u3059\u308b\u3053\u3068\u3082\u78ba\u8a8d\u3067\u304d\u308b\uff0e\u03b2 = 0 \u3067\u3082\u6b69\u884c\u3067\u304d\u308b\u304c\uff0c \u03b2 = 5 \u306e\u307b\u3046\u304c\u3088\u308a\u904a\u811a\u306e\u56fa\u6709\u632f\u52d5\u6570\u306b\u8fd1\u304f\uff0c\u8db3\u5e95\u304c\u5b8c\u5168\u306b\u63a5 \u5730\u3059\u308b\u3068\u3044\u3046\u610f\u5473\u3067\u5b89\u5b9a\u306a\u6b69\u884c\u304c\u5f97\u3089\u308c\u3066\u3044\u308b\uff0e\u3053\u306e\u3053\u3068\u304b\u3089\uff0c \u8db3\u53d6\u308a\u4ed8\u3051\u89d2\u306f\uff0cKuo [4] \u3084Wisse \u3089 [5] \u304c\u671f\u5f85\u3057\u305f\u9759\u7684\u5b89\u5b9a \u6027\u3092\u78ba\u4fdd\u3059\u308b\u3060\u3051\u3067\u306a\u304f\uff0c\u30e9\u30c6\u30e9\u30eb\u904b\u52d5\u306e\u56fa\u6709\u632f\u52d5\u6570\u3092\u5909\u5316\u3055 \u305b\u308b\u52b9\u679c\u3092\u6301\u3064\u3068\u3044\u3048\u308b\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u6b69\u884c\u3092\u52d5\u7684\u306b\u5b89\u5b9a\u5316\u3059 \u308b\u305f\u3081\u306b\u306f\u4e21\u52b9\u679c\u3092\u8003\u616e\u3057\u3053\u308c\u3092\u8a2d\u8a08\u3059\u308b\u5fc5\u8981\u304c\u3042\u308b\uff0e 4. \u304a \u308f \u308a \u306b \u672c\u5831\u544a\u3067\u306f\uff0c\u30d0\u30cd\u8db3\u9996\u3068\u6241\u5e73\u8db3\u3092\u6301\u3064\u4e09\u6b21\u5143\u53d7\u52d5\u6b69\u884c\u6a5f\u306b\u3064 \u3044\u3066\u8003\u5bdf\u3057\uff0cWisse\u3089 [10]\u306e\u8db3\u9996\u30d0\u30cd\u8a2d\u8a08\u6cd5\u3092\u30e9\u30c6\u30e9\u30eb\u5e73\u9762\u5185 \u3067 ZMP\u79fb\u52d5\u91cf\u3092\u5236\u9650\u3059\u308b\u5f62\u3067\u62e1\u5f35\u3057\uff0c\u811a\u4e0a\u7aef\u306b\u914d\u7f6e\u3055\u308c\u305f\u304a \u3082\u308a\u3092\u7528\u3044\u3066\u811a\u3068\u30ed\u30fc\u30eb\u8ef8\u56de\u308a\u306e\u56fa\u6709\u632f\u52d5\u6570\u3092\u540c\u671f\u3055\u305b\u308b\u3053\u3068 \u3067\u3053\u308c\u3092\u5b9f\u73fe\u3057\u305f\uff0e\u5f97\u3089\u308c\u305f\u7d50\u679c\u3092\u4ee5\u4e0b\u306b\u307e\u3068\u3081\u308b\uff0e \u2022\u4e09\u6b21\u5143\u53d7\u52d5\u6b69\u884c\u6a5f\u306f\u305d\u306e\u5831\u544a\u4f8b\u81ea\u4f53\u304c\u5c11\u306a\u3044\u306a\u304b\u3067\uff0c\u6241\u5e73 \u8db3\u3068\u30d0\u30cd\u8db3\u9996\u3092\u6301\u3064\u8a66\u4f5c\u6a5f\u306b\u3088\u308a\u5f15\u8fbc\u9818\u57df\u304c\u6975\u3081\u3066\u5e83\u3044\u4e09 \u6b21\u5143\u53d7\u52d5\u6b69\u884c\u3092\u5b9f\u73fe\u3057\u305f\uff0e \u2022\u6241\u5e73\u8db3\u3068\u30d0\u30cd\u8db3\u9996\u306b\u3088\u3063\u3066\u30e8\u30fc\u8ef8\u56de\u308a\u30e2\u30fc\u30e1\u30f3\u30c8\u306b\u3088\u308b\u4e0d \u5b89\u5b9a\u6027\u304c\u4f4e\u6e1b\u3055\u308c\uff0cWisse \u3089 [5] \u306e\u7528\u3044\u305f\u7279\u6b8a\u306a\u88dc\u511f\u5668\u3092 \u7528\u308b\u3053\u3068\u306a\u304f\u5b89\u5b9a\u306a\u6b69\u884c\u3092\u5b9f\u73fe\u3057\u305f\uff0e \u2022\u811a\u4e0a\u90e8\u306b\u53d6\u308a\u4ed8\u3051\u308b\u304a\u3082\u308a\uff0c\u30d0\u30cd\u5b9a\u6570\uff0c\u8db3\u53d6\u308a\u4ed8\u3051\u89d2\u5ea6\u306a \u3069\u306b\u3088\u3063\u3066\u30e9\u30c6\u30e9\u30eb\u904b\u52d5\u306e\u632f\u52d5\u6570\u304c\u5909\u5316\u3057\uff0c\u811a\u306e\u56fa\u6709\u632f\u52d5 \u6570\u306b\u8fd1\u3044\u3068\u3053\u308d\u3067\u6700\u3082\u6b69\u884c\u304c\u5b89\u5b9a\u3068\u306a\u308b\u3053\u3068\u3092\u793a\u3057\u305f\uff0e \u4eca\u5f8c\u306e\u8ab2\u984c\u3068\u3057\u3066\uff0c\u904a\u811a\u3068\u30e9\u30c6\u30e9\u30eb\u904b\u52d5\u3092\u540c\u671f\u3055\u305b\u308b\u305f\u3081\u306e \u4f4d\u76f8\u7279\u6027\u89e3\u6790\uff0c\u3088\u308a\u6b69\u5e45\u306e\u5927\u304d\u3044\u6b69\u884c\u306e\u5b9f\u73fe\uff0c\u30dd\u30a2\u30f3\u30ab\u30ec\u5199\u50cf \u306b\u3088\u308b\u4e09\u6b21\u5143\u6b69\u884c\u306e\u5b89\u5b9a\u89e3\u6790\u306a\u3069\u304c\u6319\u3052\u3089\u308c\u308b\uff0e \u53c2 \u8003 \u6587 \u732e [ 1 ] G" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002883_9393742_09393751.pdf-Figure11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002883_9393742_09393751.pdf-Figure11-1.png", + "caption": "Fig. 11. PM-shield ADS-SRM in Schemes (a) #1 and (b) #2.", + "texts": [ + " Hence, the solutions for the leakage field reduction in the 3D model are revealed, which will be introduced in detail next. As shown in Figs. 8 and 9, the two existence ways for the flux leakage are at the stator and rotor sides, respectively. When the PMs are installed at both the stator and rotor sides for the flux leakage shielding, there are two possible configurations (Schemes #1 and #2) can meet the requirement, which are shown in Fig. 10. And the corresponding motor geometries are shown in Fig. 11. In Fig. 10, FPM1 and FPM2 represent the MMFs provided by the PMs installed at the front and back sides of the excitation pole, respectively. FPM3 and FPM4 in Fig. 10(a) represent the MMFs provided by the PMs installed at the front and back sides of the excitation-pole end surfaces, respectively. FPM3 in Fig. 10(b) refers to the PMs installed facing the excitation-pole end surfaces. SUN et al: STUDY ON MAGNETIC SHIELDING FOR PERFORMANCE IMPROVEMENT OF AXIAL-FIELD DUAL-ROTOR 53 SEGMENTED SWITCHED RELUCTANCE MACHINE For the flux leakage shielding in ADS-SRM, the installed PMs should overlap the cross sections of the leakage flux paths" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003036_cmtmte2018_04028.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003036_cmtmte2018_04028.pdf-Figure1-1.png", + "caption": "Fig. 1. Vibrator prototype 3D model.", + "texts": [ + " The force of driving (removal) of the driven element, amplitude of vibrations and other technical specifications of similar systems were selected as such. In the following, such input parameters of the model as the shaft rotation frequency and eccentric weights are selected based on the initial data. Creation and operation of a vibration system model is based on main dynamics laws and system vibration theory. First, when mechanism shaft loads are known, plain bearings that meet operation requirements and conditions are selected. Then a 3D device model is built using NX 11 CAD graphic editor (Fig. 1). A 3D model is used to determine the vibrator prototype mass-center data. After that a dynamic model is developed in Euler 10.11 Pro software based on the available data (Fig. 2). When the required input parameters and mass-center characteristics have been introduced in the dynamic model, it is possible, by changing free parameters, to obtain set speeds, accelerations and other parameters of the device parts. An example in Fig. 3 shows the relationship between the driving shaft angular speed and operation time of different eccentric weights" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure10.12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure10.12-1.png", + "caption": "Fig. 10.12. Frequency distribution of the vibration for resonance passing of floor under rear right passenger\u2019s feet", + "texts": [], + "surrounding_texts": [ + "102 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260" + ] + }, + { + "image_filename": "designv8_17_0001549_tation-pdf-url_35276-Figure15-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001549_tation-pdf-url_35276-Figure15-1.png", + "caption": "Fig. 15. Generated gear and generating positions of the rack-cutter with a rounded-tip", + "texts": [], + "surrounding_texts": [ + "Computer graphs of generating and generated surfaces can be obtained by using a programming language and graphic processor. In this study codes are developed by using GW-BASIC language to obtain the coordinates of the surfaces. GRAPHER 2-D Graphing System is used for displaying computer graphs of the cutters and gears. Also the ANSYS Preprocessor module is used for displaying gear generating process. Illustrative examples are given for both rack- and pinion-type cutters for different types of tool tip geometries. For rack-type generation, types of tip fillet geometry are selected from the study proposed by Alipiev (Alipiev, 2009, 2011) and the related geometries displayed in the table are adopted to the present mathematical model. Table 1 displays the variation of tip geometry of the rack cutters. www.intechopen.com As illustrated in Table 1, the rack cutter of type-1a has different clearances at its different sides. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. The tooth semi-thicknesses at pitch line of the cutter are different from each other. Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 2.01 and right side radius of rounding m 3.02 . Figure 8 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. As illustrated in Fig. 2. and classifed type-1b in Table 1, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The tooth semi-thicknesses at pitch line of the cutter are same. This type of cutter is adopted from the standard generating rack to asymmetric gearing. The relation ship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 38.01 and right side radius of rounding m 33.02 . Generating and generated surfaces and trochoidal paths are illustrated in Fig 9. Rack cutters with asymmetric teeth can also be designed with full rounded tips. The rack cutter of type-2a has a single rounded edge. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. As depicted in Table 1 the centers of the rounded tip are at the center line of the cutter tooth. The tooth semi-thicknesses at pitch line of the cutter are same. Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 5.221 , right side pressure angle 152 , left side radius of rounding m 4.01 and right side radius of rounding m 587.02 . Figure 10 displays the generating cutter of type-1a, generated surface and trochoidal paths of the tip. For visual clearity, only the corresponding halves (of secondary trochoids) that contribute to final formation of the generated tooth shape are shown. www.intechopen.com Mechanical Engineering 518 www.intechopen.com www.intechopen.com Mechanical Engineering 520 As classifed type-2b in Table 1, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The tooth semi-thicknesses at pitch line of the cutter are different. The relation ship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 5.2 , number of teeth 24z , left side pressure angle 5.221 , right side pressure angle 152 , left side radius of rounding m 514.01 and right side radius of rounding As illustrated in Table 2, the shaper cutter of type-1a has different clearances at its different sides. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 35.02 . Figure 12 displays the generating cutter of type-1a , generated surface and trochoidal paths of the tip. www.intechopen.com As illustrated in Fig. 3. and classifed type-1b in Table 2, the cutter has a constant clearance for its all sides. The side with a higher pressure angle has a higher radius of rounding. The relationship between left and right side roundings is )sin1()sin1( 2211 . Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 25.01 and right side radius of rounding m 222.02 . Generating and generated surfaces and trochoidal paths are illustrated in Fig 13. The shaper cutter of type-2a has a single rounded edge. The side with a higher pressure angle has a lower radius of rounding and a lower clearance. As depicted in Table 2 the centers of the rounded tip are at the center line of the cutter tooth. Design parameters are selected as module mmm 3 , number of teeth 20z , left side pressure angle 201 , right side pressure angle 152 , left side radius of rounding m 373.01 and right side radius of rounding m 449.02 . Figure 14 displays the generating cutter of type-2a , generated surface and trochoidal paths of the tip. For visual clearity, only the corresponding halves (of secondary trochoids) that contribute to final formation of the generated tooth shape are shown. The shaper cutter with asymmetric involute teeth and with a single rounded edge can not be designed for constant clearance in case of standard tooth height. As illustrated in Fig. 3., the center of the rounding should be on the pressure line of the cutter. As a result, the geometric varieties of pinion-type tool tip is limited for indirect generation. www.intechopen.com Mechanical Engineering 522 www.intechopen.com Figure 17 displays relative positions of the pinion cutter with symmetric involute teeth and a fully-rounded tip. The trochoidal curves exhibits symmetry according to center line of gear tooth space. Generating with a sharp-edge pinion cutter is depicted in Fig.18. In this case, primary trochoids determine the shape of the generated tooth fillet. The secondary trochoids do not exist. Video files displaying generating positions of the cutter can be obtained with a proper software. In this study, ANSYS Parametric Design Language (APDL) is also used for obtaining graphic outputs and animation files displaying the simulated motion path of the generating cutters (ANSYS, 2009). Video files can be seen in the author\u2019s web page: http://www.istanbul.edu.tr/eng2/makina/cfetvaci/gearpage.htm www.intechopen.com Mechanical Engineering 524 www.intechopen.com Computer Simulation of Involute Tooth Generation 525" + ] + }, + { + "image_filename": "designv8_17_0001471_load.php_id_12120204-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001471_load.php_id_12120204-Figure16-1.png", + "caption": "Figure 16. Magnetic potential for rotor and permanent magnets of designed slotted-TORUS AFPM motor.", + "texts": [], + "surrounding_texts": [ + "One of the objectives of this work is to design the AFPM motor with sinusoidal back-EMF waveform; in other words, the back-EMFs should be as sinusoidal as possible. Fig. 17 shows the 3-phase back- EMFs at rated speed (1500 rpm) for 15-stator-slot AFPM synchronous machine for both with, and without permanent-magnet skewing; also FEA-calculated maximum and RMS value of back-EMF are displayed. The adoption of the fractional winding (q = 5/4) implies a beneficial filtering effect on the back-EMF waveform and avoid high distortion. This fact is confirmed in Fig. 18 (Fourier transform analysis of the backEMF waveforms) by the amplitudes of 5th and 7th harmonics which are rather low, the most important harmonics well-known as the teeth harmonics of a q = 1 winding. It is also found that the THD drastically decreases from 8.1% to 2.5% with 9-degree optimized permanentmagnet skewing for 15-stator-slot AFPM synchronous machine." + ] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure21-1.png", + "caption": "Fig. 21. Characteristic forms of foot-mounted single-stage gear reducer (PGR solution) [9].", + "texts": [ + " Gear reducer with horizontal shaft arrangement, with the housings with feet on all four sidewise surfaces and with connected flanges (Fig. 10 and 15) presents the most universal gear reducer. This type of reducer is adapted for all positions and ways of mounting, but at the same time, it is the most expensive due to extensive machine processing and the largest consumption of materials. Therefore, their intensive development could not be expected further, but they will be produced by an only small number of manufacturers to satisfy operating requirements. Gear reducers with vertical shaft arrangement footmounted (Fig. 21), flange-mounted (Fig. 22) and foot and flange-mounted (Fig. 12) are probably the most basic positions of mounting that will be required in future due to relatively low production costs, suitable form and low cost of materials. Other forms are less required and they are produced by smaller manufacturers who want to cover the market segment which is not covered by large manufacturers. Further intensive development of shaft-mounted single-stage gear reducers can be also expected. Their installation doesn\u2019t require flanges at the output shaft which provide cheaper construction" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002883_9393742_09393751.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002883_9393742_09393751.pdf-Figure2-1.png", + "caption": "Fig. 2. Flux density distributions at (a) unaligned and (b) aligned rotor positions.", + "texts": [], + "surrounding_texts": [ + "50 CES TRANSACTIONS ON ELECTRICAL MACHINES AND SYSTEMS, VOL. 5, NO. 1, MARCH 2021\n Abstract\u2014A category of permanent-magnet-shield (PM-shield) axial-field dual-rotor segmented switched reluctance machines (ADS-SRMs) are presented in this paper. These topologies are featured by using the magnetic material to shield the flux leakage in the stator and rotor parts. Besides, the deployed magnets weaken the magnetic saturation in the iron core, thus increasing the main flux. Hence, the torque-production capability can be increased effectively. All the PM-shield topologies are proposed and designed based on the magnetic equivalent circuit (MEC) model of ADS-SRM, which is the original design deploying no magnet. The features of all the PM-shield topologies are compared with the original design in terms of the magnetic field distributions, flux linkages, phase inductances, torque components, and followed by their motion-coupled analyses on the torque-production capabilities, copper losses, and efficiencies. Considering the cost reduction and the stable ferrite-magnet supply, an alternative proposal using the ferrite magnets is applied to the magnetic shielding. The magnet demagnetization analysis incorporated with the thermal behavior is performed for further verification of the motor performance.\nIndex Terms\u2014Switched reluctance machine (SRM), magnetic shielding, magnetic equivalent circuit (MEC), demagnetization, thermal behavior.\nI. INTRODUCTION\nWITCHED reluctance machine (SRM) is becoming research focus in recent years due to its unique advantages such as simple and rugged construction, low cost, fault-tolerant operation capability, and high-speed and high-temperature operation adaptabilities [1]-[3]. These features enable SRM a good candidate for electric vehicles, electric bicycle, aircraft, railway transport, and other transportation appliances [4]-[9].\nIn spite of the above described advantages, some issues still exist for SRM, which are the challenges for the further applications of SRM. The first is the lower torque density compared with the permanent-magnet synchronous motor\nManuscript received July 17, 2020; revised November 29, 2020; accepted January 05, 2021. date of publication March 25, 2021; date of current version March 18, 2021.\nThis work was supported in part by the National Natural Science Foundation of China under Grant 51807094. (Corresponding author: Wei Sun)\nThe authors are with the School of Automation, Nanjing University of Science and Technology, Nanjing 210094, China (e-mails: sunwei_njust@foxmail.com; chnliqiang@njust.edu.cn; sunle@njust.edu.cn; jxf@njust.edu.cn).\nDigital Object Identifier 10.30941/CESTEMS.2021.00007\n(PMSM), which means that higher current density is necessary for the same energy conversion [10]. This is caused by the absence of the high-energy-density permanent magnet (PM) in the magnetic structure. To improve the torque density, many investigations have been implemented on the modified motor topologies such as the axial-field topologies, the dual-stator/rotor configurations, the optimal stator/rotor pole combinations, etc. [11]-[13]. Besides, a group of SRM featured with the segmental stator or rotor is introduced for the torque-density improvement [2], [14].\nAlthough the torque density can be effectively improved through the above methods, the issue concerned with the fringing and leakage field is remarkable in SRM due to double saliency, which is inherent in SRM. It has been recognized that some of the fringing field can generate the braking torque [15]. The leakage field does not contribute to any torque production and can reduce the utilization of the magnetomotive force (MMF) [16]. Besides, the leakage inductance increases the time constant of the phase winding, which will decrease the phase current and narrow the speed range [16]. Several methods have been proposed to reduce the fringing and leakage field in SRM, including the modification of the winding layouts, the utilization of the grain-oriented steel sheet, the optimization of the stator/rotor pole profile, and the PM shield [15], [17]-[20]. However, the possibilities for the ferrite magnets in the PM-shield configuration have never been considered, and the demagnetization of the magnetic material has never been analyzed.\nThis paper presents a category of PM-shield axial-field dual-rotor segmented switched reluctance machine (ADS-SRM) by deploying the magnets to shield the flux leakage and improve the torque output. First, the flux leakage in ADS-SRM is revealed, and the possible PM-shield configurations for the leakage field shielding are introduced based on the magnetic equivalent circuit (MEC) models. Besides, the derivation of the adopted rare-earth magnet dimensions is delivered based on the MEC models. Second, the features of the rare-earth PM-Shield topologies are compared with the original design, which is the topology deploying no magnet, by three-dimensional (3D) finite-element method (FEM). As an extension, the possibilities for the ferrite magnets are analyzed, and the comparative study between the rare-earth and ferrite PM-shield configurations is performed. Finally, the magnet demagnetization analysis on the\nStudy on Magnetic Shielding for Performance Improvement of Axial-Field Dual-Rotor\nSegmented Switched Reluctance Machine\nWei Sun, Student Member, IEEE, Qiang Li, Le Sun, Member, IEEE, and Xuefeng Jiang, Member, IEEE\nS", + "SUN et al: STUDY ON MAGNETIC SHIELDING FOR PERFORMANCE IMPROVEMENT OF AXIAL-FIELD DUAL-ROTOR 51 SEGMENTED SWITCHED RELUCTANCE MACHINE\nrare-earth and ferrite PM-shield ADS-SRMs is implemented through 3D FEM and the lumped-parameter thermal network (LPTN) models.\nII. INTRODUCTION OF PM-SHIELD ADS-SRM\nA. Introduction to ADS-SRM\nThe 3D view of ADS-SRM is shown in Fig. 1 [21]. As shown in Fig. 1(a), the machine consists of a single internal stator and two external rotors. As shown in Fig. 1(b), epoxy potting under the vacuum condition is applied to the phase windings, and therefore, all the stator parts are assembled robustly. Besides, all eight rotor segments at each side are inserted in a nonmagnetic rotor bracket. Fig. 1(c) shows the prototype of ADS-SRM. The specifications and main geometric parameters are given in Table I. The flux density distributions at the phase excitation of 8A near typical rotor positions, i.e. unaligned and aligned rotor positions, are shown in Figs. 2(a) and 2(b), respectively. It is found that the leakage field is significant near unaligned rotor position, especially between the excitation pole and the flux-conductive rings.\nFor better reflection of the flux leakage, 2D FEM is carried out on the 2D analysis model plot in Fig. 3. The 2D analysis model can reflect the performance of ADS-SRM very well as the comparison of the static-torque characteristics shown in Fig. 4. The flux line distributions in the 2D analysis model at unaligned and aligned rotor positions along with the corresponding MEC models are shown in Fig. 5. The red flux paths in Fig. 5(c) represent the leakage flux paths between the excitation pole and the flux-conductive ring. The leakage flux linked by the coil itself and the leakage flux at aligned rotor position, as shown in Fig. 5(b), are negligible due to the sparse leakage flux lines. In addition, it is observed from Figs. 5(a) and 5(c) that the leakage flux paths are normal to the rotor moving direction. The leakage flux paths bypass a portion of magnetic flux in the air gap, thus reducing the electrical utilization and narrowing the speed range [16].", + "B. Inspiration for Leakage Field Reduction\nIn the previous section, the leakage field in ADS-SRM is reflected by the 2D analysis model. However, the leakage field in ADS-SRM should be much more complex due to the multiple air gaps, but it has no impact on the discussion on the solutions.\nTo shield the flux leakage in Fig. 5(a), the additional MMF in reverse series in the gap between the excitation pole and the flux-conductive ring is necessary, as shown in Fig. 6(a). It is observed that the PMs are installed with the magnetic polarity conflicting with that of the excitation pole. The corresponding flux line distributions are shown in Fig. 6(b). It is indicated in Fig. 6(b) that the leakage flux is almost eliminated. By contrast, much more flux lines go through the rotor segments. The comparison of the static-torque characteristics between the 2D analysis model without and with the PM shield at the phase excitation of 8A is shown in Fig. 7. It can be observed that, with the PM shield, the torque-production capability increases significantly. Hence, 2D finite-element analysis (FEA) proves the effectiveness of the PM shield for the leakage field shielding and the torque out improvement.\nFor further discussion on the PM-shield application in the 3D model, it is necessary to sketch the flux patterns of ADS-SRM. As stated in the foregoing section, the flux leakage is much more significant near unaligned rotor position. In this paper, the emphasis is laid on the leakage field suppression at this position. The flux patterns at unaligned rotor position is shown in Fig. 8. The corresponding MEC model is shown in Fig. 9. In Fig. 9, F1 represents the MMF provided by the coils, Rx is the reluctance in each branch. The red flux paths in Fig. 9 denote the leakage flux paths. It is indicated that the MEC model of the 3D model is much more complex than that in Fig. 5. The leakage field exists in two ways. One is between the side surfaces of the excitation pole and the flux-conductive rings, and the other between their end surfaces. Hence, the solutions for the leakage field\nreduction in the 3D model are revealed, which will be introduced in detail next.\nAs shown in Figs. 8 and 9, the two existence ways for the flux leakage are at the stator and rotor sides, respectively. When the PMs are installed at both the stator and rotor sides for the flux leakage shielding, there are two possible configurations (Schemes #1 and #2) can meet the requirement, which are shown in Fig. 10. And the corresponding motor geometries are shown in Fig. 11. In Fig. 10, FPM1 and FPM2 represent the MMFs provided by the PMs installed at the front and back sides of the excitation pole, respectively. FPM3 and FPM4 in Fig. 10(a) represent the MMFs provided by the PMs installed at the front and back sides of the excitation-pole end surfaces, respectively. FPM3 in Fig. 10(b) refers to the PMs installed facing the excitation-pole end surfaces." + ] + }, + { + "image_filename": "designv8_17_0004426_iceesi2017_01022.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004426_iceesi2017_01022.pdf-Figure1-1.png", + "caption": "Fig. 1. Basic Structure of Substrate Integrated Waveguide (SIW) [14]", + "texts": [ + " This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0/). mm, with a tangent loss of 0.044 and a dielectric constant of 2.35. In this paper, the photographic paper substrate is used in the coupler design because the substrate loss in SIW is dependent on the substrate thickness; the thicker the substrate, the better the insertion loss. The design is accomplished using Computer Simulation Tools (CST) software. The configuration of SIW transmission lines is illustrated in Fig. 1. The waveguide substrate are covered with two metal (high conductivity) surfaces on top and bottom to let the propagation of all TEn0 modes [15]. The two silver epoxy holes are placed on the side line of the rectangular waveguide that functions to prevent and reduce signal leakage. Both metal posts are set symmetrically in order to control the signal flow. Two extra silver epoxy posts that set in every port act as reflection cancelling elements by varying the sections of Substrate Integrated Waveguide (SIW) [14]", + " The transition between SIWs and microstrip line is realized using microstrip taper to match both electrical and magnetic field distributions between the two medias [14]. In this paper, the proposed coupler is designed on photographic paper substrate materials where the metal (conductive) used is copper as a ground plane and metallic via holes. The relative dielectric constant (\u025br) of the photographic paper is 2.35, thickness (h) is 0.69 mm and loss tangent (tan \u03b4) is 0.044. The effective width (Weff ) and effective length (Leff) of the Substrate Integrated Waveguide (SIW) cavity shown in Fig. 1 can be determined using expression (1) and (2). s dWWeff 95.0 2 (1) s dLLeff 95.0 2 (2) Where, W and L are the width and length of Substrate Integrated Waveguide (SIW) cavity. Fig. 3 illustrates the two of SIW cavity design main parameters, diameter of metallic via holes (d) and the gap distance between via holes (s). For SIW cavity designs, conditions expressed in (3) and (4) must be followed. 5 gd (3) ds 4 (4) Where, 2 2 2 )()2( 2 wc fr g (5) f is the frequency c is the speed of light The ratio of d/p is important in order to inhibits leakage loss in SIW, which applicable range is 0" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002628_t_of_a_Composite.pdf-Figure12-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002628_t_of_a_Composite.pdf-Figure12-1.png", + "caption": "Fig. 12. Total displacements for the load with a hazardous multiplier", + "texts": [], + "surrounding_texts": [ + "The presented composite frame with sandwich-type walls was analysed using ANSYS Workbench 2020 R2. First-degree solid and shell elements were used in the analysis (Fig. 6). The data on the materials used in the analysis of the frame come from the ANSYS Workbench library. Test samples were made simultaneously with the frame, in order to determine the actual material parameters such as density or equivalent Young\u2019s modulus. The tests conducted, which will be described in the next article, will be used for validating the model. The following frame loads were assumed for analysis (Fig. 7): \u2022 point A \u2014 support, \u2022 point B \u2014 support, \u2022 point C \u2014 manipulator 200N (due to the lim- ited budget of the project and difficult to predict dynamic loads, a doubled force value was assumed), \u2022 point D \u2014 battery 75N, \u2022 point E \u2014 computer and electronics 5N, \u2022 point F \u2014 laboratory 29N. The analysis was performed for several variants of the grid in order to verify the convergence of the results. The similarity of the obtained results confirms the appropriate densification of the grid (Table 2). The analysis was carried out iteratively, starting from the base load value up to the dangerous load value (Table 3). The following drawings presented (Fig. 8, Fig. 9, Fig. 10) show the results for the analysis without force multipliers. Figures 11, 12, and 13 shows the results for the analysis with the critical load included. Figure 14 show where the frame joins the rocker-bogie suspension beam. It is possible to identify the point where the reduced stresses reach a value close to the hazardous value for the material used in the structure. Due to the complex state of stresses occurring in this point, potentially dangerous for the structure, additional local laminate layers should be applied to increase the durability of the structure. Figure 15 show the progress of changes in the value of reduced stresses as a function of the force multiplier and the safety factor as a function of the force multiplier. Despite the linear increase in load, a non-linear decrease of the safety factor can be observed, which may result from the change in the relationship between the values of shear stresses and the values of normal stresses." + ] + }, + { + "image_filename": "designv8_17_0002562_f_version_1605520280-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002562_f_version_1605520280-Figure4-1.png", + "caption": "Figure 4. Free body diagram of the exoskeleton and human.", + "texts": [ + " The configurations of coupling between human and exoskeleton model are shown in Figure 2. To ensure the simulation accurately mimicked to the gait training task, parallel bars were added to avoid the human model from falling down by providing stability. Both hands of the human model are constrained to the parallel bars using a slide joint to allow forward and backward motion. Figure 3 demonstrates the gait training simulation of the human exoskeleton model walking with both hands holding the parallel bars. Figure 4 illustrates a free body diagram of the exoskeleton and human model. O1, O2, and O3 are the center position of hip, knee, and ankle joint, respectively; \u03b81, \u03b82, and \u03b83 represent angles of hip, knee, and ankle, respectively; l1, l2, and l3 are length of the femur, tibia, and foot, respectively; and lGi is the center of gravity (CoG) of links 1, 2, and 3. In this paper, each link of the exoskeleton and human is modeled as one DoF pendulum model, which replicates one joint of the exoskeleton and human, as shown in Figure 5" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002688__download_8923_15183-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002688__download_8923_15183-Figure1-1.png", + "caption": "Figure 1: Double disk coulter: 1 \u2013 plate with a pointed tip, 2 \u2013 hollow rack, 3 \u2013 seed guide, 4 \u2013 holder, 5 \u2013 cut with a convergence angle \u03b3, 6 \u2013 mounting rack, 7 \u2013 cut made outside the straight profile of the lower edge, \u03b1 \u2013 approach angle, \u03b2 \u2013 roll angle, L \u2013 cut length", + "texts": [ + " \ud835\udc462 \ud835\udc56\ud835\udc5b\ud835\udc4e\ud835\udc51 = \ud835\udc46\ud835\udc46\ud835\udc56\ud835\udc5b\ud835\udc4e\ud835\udc51 \ud835\udc532 , (17) \ud835\udc46\ud835\udc46\ud835\udc56\ud835\udc5b\ud835\udc4e\ud835\udc51 = \ud835\udc5b \ud835\udc41 \u2211 \ud835\udc62=1 (\ud835\udc66\ud835\udc62\ud835\udc50\ud835\udc4e\ud835\udc59\ud835\udc50 \u2212 \u0304\ud835\udc66\ud835\udc62exp) 2 , (18) where yu calc \u0438 yu exp are the response values in the u-th experiment calculated by the regression equation and determined experimentally. The hypothesis about the equation adequacy can be accepted when the value of the Fisher\u2019s test obtained as a result of calculations does not exceed the tab value for the selected level of significance, that is, when Ftab \u2265 Fcalc Based on the results of the study, a double disk coulter was developed (Figure 1) [15]. The process of uniform seed distribution along the furrow length is affected by many factors: design parameters of the coulter, technological parameters of the sowing unit, agrotechnical requirements. Since the available coulters are installed on the seeding machine with a standard row spacing of 150 mm, it is necessary to ensure uniform seed distribution along the furrow length in order to prevent seed thickening in the row. In the experimental studies, the following parameters of the proposed coulter were changed: the cut length of the outer side of the rectilinear profile of the lower edge of the rack varied within 20\u201380 mm (L), the approach angle in the horizontal plane (\u03b1) and the roll angle in the vertical plane (\u03b2) varied within 3\u201328 deg" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure4-1.png", + "caption": "Fig. 4. The characteristic solution of shaft-mounted singlestage gear reducer with the output gear between bearings (Winsmith solution) [11].", + "texts": [], + "surrounding_texts": [ + "Single-stage reducers are exclusively manufactured in single-stage housings, although there are manufacturers who do not produce single-stage units at all. Different axis heights present a special problem, since the mounting ways are not the same in that case, the approaches of defining load capacity and gear ratio are different and appropriate materials used for manufacturing of gear reducers are not same, especially for smaller heights. By applying different measures, manufacturers of gear reducers bring out their own conceptual solution in order to differentiate their design from the competition solution or to achieve better characteristics. Manufacturers make the efforts to provide greater rigidity and stability of the entire gear unit by appropriate shape and weight distribution of gearbox housing. Axis height of the gear unit is one of the most important characteristics of gear reducers since it affects the value of gear ratio and load capacity, and sometimes it results in different conceptual designs. Axis heights of universal gear reducers are prescribed according to the standard row R20. Since this row is very dense, most manufacturers produce reducers with axis height in a standard row R10 (these numbers belong to the standard row R20). But soon they increased axis heights in order to increase gear ratio, and now reducers are produced with axis height in a standard row R20/2. In the area of the most used gearbox sizes, some manufacturers produce so-called intermediate sizes with the axis heights in row R20 [6,7]. In recent time, manufacturers of gear reducers try to achieve the same axis heights in order to ensure greater exchangeability of their gear units. This is especially important for smaller manufacturers, so they can offer their products instead of those of large manufacturers. This additionally means that they must have the same mounting dimensions, e.g. dimensions of the holes for base screws on the feet or flange and their position, etc. Axis heights of single-stage gear reducers are presented in Table 1 [2]. Based on the axis heights presented in this table, it can be concluded that all manufacturers of single-stage gear reducers cover the interval of axis height from 63 mm till 112 mm. Some manufacturers also offer smaller or larger heights. As it can be seen no manufacturer fully respect the row R10 or R20/2, but they introduce additional heights, so-called intermediate sizes. For example, axis heights of 90, 100 and 112 mm are often requested, so the large manufacturers produce gear units with this axis height in the row R20. Single-stage reducers with the minimum axis height of 50 mm are only manufactured by Lenze and Bonfiglioli. SEW produces single-stage gearboxes up to the height of 140 mm and Siemens-Flender and Leroy Somer up to 160 mm. Gear reducer solution design should be realized in that way that only one bearing on output shaft receives the axial force. In that way, the cost of both bearings on the output shaft will be smaller, mounting and dismounting will be much simpler and the shaft is allowed to be expanded properly when heated. [7,8,9] The helical gear should be positioned between the bearings, which ensure greater shaft rigidity. It is preferable the gear is positioned in the middle between the bearings to provide as even as possible the contact between two gear flanks. If it is not possible, the position of the gear should be realized in that way to ensure even contact of two flanks. Analyzing the characteristic conceptual solutions of single-stage universal gear units, only two conceptual solutions are possible: when output gear is overhang (Fig. 1-a) and when output gear is positioned between the bearings (Fig. 1-b). At foot-mounted single-stage reducers, the pinion is positioned above the output gear, so that the large electric motor can be installed. In this way, the input shaft is at sufficient height relative to the base. The solution with the overhung output gear has larger dimensions and thus the weight of gear reducer (Fig. 2). Also, the deflection of this gear is slightly larger, but it is negligible because of the large diameter of the output shaft. However, this type of conceptual solution is much more often used than the solution with the gear between bearings (Fig. 3, 4). During adopting the conceptual solution of gear reducer, mounting method and way of mounting elements should be considered. Also, this consideration must be given to the way of connecting gear reducer housing with housings of other units, or with the cover, electric motor, or adapter for IEC motors. Of course, this must take into account the minimum consumption of material, the lower the volume of machining and the sufficient strength and rigidity of the housing. Universal single-stage gear reducers are produced as one-housing or two-housing units. However, the most usual way is monoblock housing produced as one-piece element. A large rear opening of single-stage reducer housing usually allows the installation of large gears. When it is not possible, a special cover is assembled as a connection between housing and electric motor (Lenze solution [12], Fig. 5). In this case, there is no need to open housing from the top. According to the mounting method, single-stage gear reducers can be produced in two ways: with or without special cover \u2013 intermediate connector (Table. 2). It is clear that only axial mounting of the parts is carried out in one-piece housing of single-stage gear reducer. It can be noticed from Table 2. that only two manufacturers produce gear units without an intermediate connector. All other manufacturers use this connector and in that way, they achieve higher gear ratio. Based on the analyzed gearbox housings, it can be noticed that all manufacturers produce the housings from cast iron. Only two of them (Bonfiglioli S, Leroy Somer) use aluminium alloys as material for housings of the low axis heights of reducer [13, 10]. In this way, they achieve a smaller weight of their gear units and thus better technical characteristics of their products." + ] + }, + { + "image_filename": "designv8_17_0003053_article_25893772.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003053_article_25893772.pdf-Figure4-1.png", + "caption": "Fig. 4 Modelling and flexible of crane ship", + "texts": [ + "5 ( ) f c c c cx s current c c c cy s c c c OA cn X U A C Y U A C N U A L C , (13) Where, \u03c1 is the density of sea-water, UC is relative current rate, Acf and Acs are the front projection area and side projection area of ship hull underwater, Ccx(\u03b2), Ccy(\u03b2) and Ccn(\u03b2) are current moment coefficients obtained in towing tank experiments, \u03b2 is the ocean current angle in ship coordinate system, which is 0 if the current is along the X direction and clockwise is positive, the range is [0\u03bf,360\u03bf). The ship geometry should be simplified in advance to improve the simulation efficiency without considerable errors introduced. The hull, crane turntable and boom have been simplified and keep the overall dimensions unchanged, as well as the original mass, effective moment of inertia and other effective parameters. The prototype geometric model is created in Solidworks, as shown in Fig. 4(a). The hoisting system is composed of the flexible boom and sling. The boom is meshed in Ansys APDL and import the MNF file into Adams. The mesh of the boom is shown in Fig. 4(b). The stiffness of the wire rope is nonlinear when the boom vibrates. It will not only increase the computational load, but also make the simulation does not converge well. It is necessary to linearize the sling stiffness in the current work. The nonlinear stiffness of the wire rope is shown in Fig. 5 and the wire rope can be treated as approximately quasi-linearized according to the nonlinear vibration theory. Suppose the displacement is: 1 cosx a . (14) Elastic restoring coefficient, Fs, is: 0 0( 0) ( cos ) cos 0 (0 )s l a x F a K a x a " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003681_577_PDEng_Report.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003681_577_PDEng_Report.pdf-Figure5-1.png", + "caption": "Fig. 5: CAD model of the lateral bending case", + "texts": [ + "7 G GPa 1.5 \u03c3max MPa 50.0 \u03c3max / E 29.4 several optimizations, the probability of finding a solution within 5% of the global optimum is greatly increased. For example, the probability to find a result within 5% of the global optimum for the Three-Flexure Cross Hinge is 62%. When conducting sixteen optimizations, the probability of finding a solution close to the global optimum is approximately 99% [17]. E. Experimental Setup To validate the numerical model, a setup for measuring stiffness was used. See Fig. 5. A parallel guidance, 1-DOF in the gravity direction, is actuated when weights are added to the end effector. The vertical displacement is measured through a linear-variable differential-transformer (LVDT) sensor. The actuation stiffness of the parallel guidance has been taken into account. To attach the finger to the parallel guidance, a wire flexure is used in the DOF of the parallel guidance. Since the wire flexure constrains only 1-DOF, torsion and in-plane bending can be measured from the tip of the finger", + " Influence of sideways force for optimized Hole Cross Hinge (Fz = [0;\u22121;\u22122] N) and Angled Three-Flexure Cross Hinge (Fz = [0;\u22121;\u22122;\u22125] N). A. Experimental test Before measuring the finger, the parallel guidance was characterized, and the stiffness was measured when loaded up to displacements of 4.3 mm. The stiffness of the parallel guidance was linear in the whole range of motion. This was used later to subtract from the stiffness of the measurement, as these are in parallel. With the experimental setup shown in Fig. 5,[ 0\u25e6 \u221215\u25e6 \u221230\u25e6 ] deflections angles were tested for a Hole Cross Hinge. These measurements are compared for validation with the flexible multibody and FEM models in Fig. 10. Differences of 32.6%, at 0\u25e6, were found between the flexible multibody analysis and the experimental results. This model considers the attachment of the finger and the phalange to be rigid. Differences can be attributed to the manufacturing of the finger. Design parameters, like the thickness of the flexures, are not linear with the performance of the hinges", + " There is a holder on both sides of the disc to be able to balance the test rig with contra weights. 3.1.b Lateral bending case For the lateral bending case, the focus is to purely move one end of the specimen in vertical direction and to fix the other end. Also for this testing principle there are many machines on the market [9], but these machines also do not fulfil the demands due to the same arguments as for the torsion case. The notch flexure that is used is the optimal way to get this single direction movement with the least friction (see figure 5. Hereby should be noted that the deflection in vertical direction is small enough to neglect the shortening effect in horizontal direction (for further explanation about the shortning effect and why this can be neglected, see Herman Soemers (2011, para. 3.3.1) Design principles of precision mechanisms [10]. The force that is needed to make this displacement is calculated to be within the region of maximum applied force used during testing. This amount has to be validated afterwards to obtain a factor for the force that goes into shifting the flexure itself in vertical direction", + " To compensate for the dead weight of the notch flexure and the clamp, a spring is attached between the weight holder of the flexure and the support frame. At this location the forces of the weights and the spring are working on the same axis (see figure 3 number eight and ten. The spring is chosen by calculating the spring constant using Hooke\u2019s Law (Beuche, p. 95 [11]) since the mass, and therefore gravitational force of the dead weight is known. Equal to the torsion test rig, the height of the tip clamp is adjustable in vertical and horizontal direction by several slots as seen in figure 5. One of the two notch flexure is seen in figure 5, used to enable the vertical displacement. According to the specifications the maximum needed deflection (\u2206) is 5 mm. As mentioned in section 3.1 Global design, a thickness (t) of 12.2 mm is needed for the tread inserts. For D to h, a ratio of 0.1 is ideal [10]. Then, the applied force for a certain deflection is the least when dimension p is taken the longest. Due to limitations with the 3D printing bed it is taken as 140 mm. With these input values, the method for calculating notch flexures in Herman Soemers (2011, section 3", + " The objective is to find the set of design parameters p that maximize the performance within the specified constraints C(p) [15]. popt = argmin p F(p), subject to: C(p) \u2264 0 (2) The method minimizes a cost function F(p) which is defined to achieve the lowest ratio between stress and grasping force at \u221230\u25e6 of flexion. F(p) = \u03bb \u03c3p Fgrasp (3) Page 68 TABLE I OPTIMIZATION PARAMETERS [17] Parameter Unit \u03b8min/\u03b8max \u221215\u25e6/30\u25e6 tmin/tmax mm 0.5/2.5 E GPa 1.7 G GPa 1.5 \u03c3limit MPa 35.0 \u03c3max MPa 50.0 \u03c3max / E 34.0 LVDT WeightPhalange Flexure Parallel Guidance sensor Clamp Wire Flexure Fig. 5. Experimental setup for stiffness measurement. (LVDT) sensor. The strain energy storage of the parallel guidance has been take into account. To attach the finger to the parallel guidance, a wire flexure is used in the DOF of the parallel guidance. Since the wire flexure only constrains 1-DOF, torsion and in-plane bending is expected to be measured from the tip of the finger. A finger with only the MCP joint was printed using an SLS process. In the finger the section corresponding to the median phalange is hollow with a shell of 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.16-1.png", + "caption": "Figure 2.16 Geometry of the hybrid water monopole-ring antenna [27]", + "texts": [ + "12 Geometry of seawater monopole antenna [21] .............................................. 39 Figure 2.13 Reflection coefficients of seawater monopole antenna [21] ......................... 41 Figure 2.14 Geometry of the sea-water half-loop antenna [26] ........................................ 43 Figure 2.15 Measured and simulated reflection coefficients of the sea-water half-loop antenna [26] ...................................................................................................................... 44 Figure 2.16 Geometry of the hybrid water monopole-ring antenna [27] .......................... 45 Figure 2.17 Simulated reflection coefficient of hybrid water monopole antenna [27] ..... 46 Figure 2.18 Geometry of the hybrid water monopole-conical antenna [27] ..................... 46 Figure 3.1 Geometry of monopole antenna with different feeding mechanism ............... 50 Figure 3.2 Infinite boundary condition ............................................................................. 51 Figure 3.3 Frequency range settings ", + " The measurements are conducted in a seaside environment. Figure 2.15 shows the simulated and measured reflection coefficient of the antenna. It can be observed that the impedance bandwidth of this antenna is around 27%. The measured gain is -0.2 dB at 110 MHz, corresponding to a radiation efficiency of about 35%. In [27], two novel broadband hybrid water antennas are presented. The hybrid antenna is composed of a seawater monopole and a distilled-water ring antenna. The structure of the proposed hybrid water antenna is shown in Figure 2.16. The seawater monopole is placed on a dielectric base of Teflon with relative permittivity 2.1 and on the ground. A clear acrylic tube is chosen to hold the seawater. It is vertically fitted with the Teflon base and sealed with silicone gasket. The length and radius of the seawater monopole are 1 m and 50 mm respectively. The relative permittivity of seawater is 81 and conductivity 4 S/m. The feeding probe loaded with an aluminium disk is inserted in the seawater tube. A ring tube with distilled-water is placed on the Teflon base surrounding the seawater monopole which plays as a ring dielectric resonator antenna" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000369_f_version_1619616056-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000369_f_version_1619616056-Figure5-1.png", + "caption": "Figure 5. Design for injection molding.", + "texts": [ + " Figure 4 shows the experimental wind turbine model placed in a wind tunnel. We installed the assembled wind turbine in the facility and proximity sensors (PR08-2DN) to measure the rotational speeds around the rotating shaft. In addition, we connected the DC electronic load measuring device (M9716B) to measure the electricity generated from AWM-750D. The device is used to check signals from sensors and devices according to the wind speed change. The design of the part used in the molding analysis is given in Figure 5a, while Figure 5b shows the cooling channels used in the simulation. Table 1 shows the dimension of the part along x-, y-, and z-axes. Polypropylene (PP), also known as polypropene, is a thermoplastic polymer used in various applications. It is produced via chain-growth polymerization from the monomer propylene. In this work, Supran PP1340 supplied by SAMBARK LFT Co., Ltd. (Chungcheongnamdo, Yesan-gun, Korea) was used as the polypropylene. Using the Autodesk Moldflow advisor, the rheological behavior data of the feedstock, the other properties of the material, and molding process parameters used in the simulation are organized in Tables 2 and 3" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000920_f_version_1693378799-Figure22-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000920_f_version_1693378799-Figure22-1.png", + "caption": "Figure 22. Measurement of the S21 parameter between wearable antennas placed on a body phantom (a) and on a human body (b).", + "texts": [ + ", there are small differences in the measured parameters of the two realized antennas. To verify the feasibility of the on-body antenna design, the fabricated antennas were tested and measured in the presence of the human body. Two on-body antennas were placed vertically on a cylindrical phantom (with dimensions of a = 12.5 cm, height h = 30 cm) filled with liquid representing the electromagnetic properties of the human body at 5.8 GHz, and their positions were varied along the rim of the phantom. In other words, according to the measurement setup illustrated in Figure 22a, the axes of the waveguide antennas and the axis of the cylindrical phantom were parallel to each other, and the antennas were attached to the phantom with the wide waveguide wall and spaced in the circumferential direction (the angular distance (\u03d5) between the antennas refers to the distance between the axes of the waveguide antennas). The liquid used was a 20% ABV ethanol solution (\u03b5r = 50.89, \u03c3 = 8.64 S/m [28]). Note that the S21 parameter of the two-antenna system represents the power transfer between antennas. In addition, the antennas were placed on the human body, and the S21 parameter was measured, as shown in Figure 22b (the measurement setup is identical to that with a cylindrical phantom) . The human body was modeled in CST using the IEEE body model in the 5.8 GHz ISM band (\u03b5 = 48.2, \u03c3 = 6 S/m [29]), and the human shape was approximated as a cylinder with an elliptical cross section with the length of the major and minor axes equal 35 cm and 25 cm, respectively. The S21 parameters of the on-body wearable antennas placed on the cylindrical phantom filled with 20% ABV ethanol, as well as for the real human body, are shown in Figures 23 and 24" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000976_ticle_1705029901.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000976_ticle_1705029901.pdf-Figure2-1.png", + "caption": "Figure 2: Sketch of mechanism movement", + "texts": [ + " In this design, high-strength aluminum alloy is used, and the whole structure is based on a bionic design, similar to the human legs structure. In the principle scheme design, the following issues need to be considered: (1) the size of the mechanical device to match the human body; (2) the fixed mechanical device combined with the human body; (3) the degree of freedom of the mechanical device to match the joints of the human body; (4) placement of the fitness damping device. Combining the above considerations, a skeleton of the mechanism of the lower limb fitness mechanical exoskeleton is derived as shown in Figure 2. 3.1 Structure scheme design (1) waist structure The waist structure should be selected to achieve the purpose of wearing comfortable, breathable, with a certain degree of toughness, and could provide effective fixation. When considering people's actual fitness, they tend to sweat, and the use of outer cloth and inner cotton design will absorb the human sweat, so that the body remains dry and comfortable, while the leather belt will not have such a function. In terms of the fixing method, both buckle and sticking buttons can be used when the belt is thin, whereas it is preferable to choose the sticking button when the belt is wide because the excessive volume of the buckle will lead to sliding displacement" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003855_le_1117_context_etdr-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003855_le_1117_context_etdr-Figure7-1.png", + "caption": "Figure 7 PMSM Motor Cross Section", + "texts": [ + " Thus the inverter is a major part of the motor drive circuit allowing for controlling the currents in the motor, and motor to produce smooth torque output. A typical inverter drive circuit is shown in Figure 6. In this paper, inverter is modeled as an ideal 3 phase current source from the controller. 11 2.1.2.2 Electric Machine Main function of an electric drive is the ability to convert electrical energy into mechanical energy. This is accomplished by the use of an electric machine or a motor. In this study, a PMSM was used as part of the system modeling. A cross section view of a typical 3 phase, 4 pole PMSM is shown in Figure 7. Surface mounted (permanent) magnets establish the flux in the rotor. The stator windings are in the slots such that a sinusoidal flux density is produced in the air gap. A typical motor torque and power curve as a function of motor rotational speed is shown in Figure 8. Motor torque as a function of speed is given by = \u2212 , (2.1) where is the stall torque, is the no load rotational speed (RPM), and K is a constant. 12 Motor power as a function of rotational speed, shown in Figure 8, is given by = " + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002819__jmr_14_3_031005.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002819__jmr_14_3_031005.pdf-Figure4-1.png", + "caption": "Fig. 4 Stephenson-3", + "texts": [ + " These are the permutation cognates found by Roberts [1]. 3.4 Stephenson-1 Valid Permutations. The only valid nontrivial permutation of rotations for the Stephenson-1 is the transposition \u03b81\u2194 \u03b82. Hence, the group action corresponds with Z2. This action gives a permutation cognate. 3.5 Stephenson-2A Valid Permutations. The group of signature-preserving permutations for Stephenson-2A is Z2 \u00d7 Z2 generated by the two transpositions \u03b82 \u2194 \u03b83 and \u03b84 \u2194 \u03b85 yielding permutation cognates (Fig. 3). 3.6 Stephenson-3 Valid Permutations. Considering Fig. 4, Roth [7] determined that the cognates of the Stephenson-3 mechanism are generated by applying Roberts cognates to the four-bar formed by links 0-1-2-3 and a skew pantograph transformation to links 10-4-5 as discussed in Ref. [8]. The results of the computation from Sec. 2.2 match those previously known results as follows. First, the group of valid permutations of the Stephenson-3 mechanism corresponds with S3 \u00d7 Z2 where the S3 arises from a three-way symmetry of the rotations \u03b81, \u03b82, and \u03b83 while the Z2 arises from the transposition \u03b84\u2194 \u03b85" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000808_J_IPMRJ-05-00253.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000808_J_IPMRJ-05-00253.pdf-Figure1-1.png", + "caption": "Figure 1 Axis of human movement in three-dimensional plane. 1a: frontal plane", + "texts": [ + " In order to make this successful, one has to recognize three-dimension concepts in the joints and muscles of the trunk, rather than in 1-2 dimensions.9 Then, any movement becomes smooth without extra tension or waste of power. Consequently, this process and direction can give athletes higher level of performance. All athletes want to move the trunk naturally and smoothly without unnecessary tension. In order to make it easier, to consider movement in the light of three dimensions would be recommended.10 There are three planes to recognize in the sports and rehabilitation (Figure 1). Authors and collaborators have often explained the phenomena in the following. They are i. Frontal plane: axis of special movement that causes reptiles to make torsion and move forward (Figure 1a), ii. Sagittal plane: axis of movement that is observed when rabbits jump forward in mammals (Figure 1b), iii. Horizontal plane: axis of movement in which the monkey twists the pelvis and pushes half of the body forward (Figure 1c). These examples are useful to understand. As to the red and green arrows in Fig.1a, these indicate the changes in body axis during moving forward. The sprawling posture shows the fundamental design principles and the constraints on 3-dimension kinematics of the body and limbs axis as its locomotion.11 Generally, locomotion of tetrapods involves coordinated efforts for appendicular and axial musculoskeletal systems. The interaction of limbs and the ground may generate horizontal, vertical and mediolateral groundreaction forces.12 Int Phys Med Rehab J. 2020;5(4):175\u2012177. 175 \u00a92020 Moriyasu et al" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002984__8_2_8_20-00446__pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002984__8_2_8_20-00446__pdf-Figure2-1.png", + "caption": "Fig. 2 Structure of the flexibly constrained pair (FCP), where a link with several cam surfaces and a link with several spherical surfaces are constrained with several linear springs.", + "texts": [ + " However, possible structures of the mechanism with the MFCRP are limited because the relative motion of the MFCRP is only in one pattern, which is rotational motion with multi-directional flexibility. However, if flexible kinematic pairs with various relative motion can be achieved, this limitation can be removed. In this paper, the concept of the MFCRP is extended as \u201dflexibly constrained pair (FCP)\u201d and a design method of the FCP to achieve various relative motion including a relative translation between the links is proposed and examined. Fig.2 shows schematic diagram of the FCP. The FCP has a link with several spherical surfaces and a link with several cam surfaces. The two links are kept in contact by several linear springs so that each spherical surface and cam surface are in contact at a point. When the two links move relatively with slippage in the translation directions, they have stiffness generated by normal reaction forces between the links and elastic forces of the linear springs as shown in Fig.3 (a). In the same way, when the two links move relatively in the rotational directions, they have rotational stiffness as shown in Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002172_el-03369796_document-Figure36-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002172_el-03369796_document-Figure36-1.png", + "caption": "Figure 36 : (a) Configuration du r\u00e9seau, (b) D\u00e9tail de la structure [33].", + "texts": [ + " Tous les \u00e9l\u00e9ments sont aliment\u00e9s de la m\u00eame mani\u00e8re, par couplage avec des lignes microstrip, \u00e0 travers des fentes orthogonales r\u00e9alis\u00e9es dans le plan de masse. Ce design donne un ratio de fr\u00e9quences de 4:1, et des largeurs de bandes faibles, non explicit\u00e9es. La capacit\u00e9 de bipolarisation est cependant exerc\u00e9e. Contrairement aux designs ayant recours \u00e0 des patchs perfor\u00e9s, au sein des structures chevauch\u00e9es, les patchs fonctionnant \u00e0 la bande de fr\u00e9quences basse se situent sous les patchs fonctionnant \u00e0 la bande de fr\u00e9quences haute, leur servant de plan de masse. 1) Structures chevauch\u00e9es [33] (Figure 36) Ces structures, permettant d\u2019\u00e9viter les perforations dans un ou plusieurs patchs, ont \u00e9galement l\u2019avantage par rapport aux patchs perfor\u00e9s d\u2019offrir des largeurs de bandes plus importantes pour les bandes de fr\u00e9quences les plus basses. Cependant, les designs utilisant des patchs perfor\u00e9s sont plus compacts. Page 31 sur 182 Ce r\u00e9seau propose des largeurs de bandes de fr\u00e9quences tr\u00e8s bonnes, notamment pour la bande de fr\u00e9quence la plus basse : 17,6 % en bande L et 15 % en bande C (ratio 4:1). De plus, la bipolarisation est offerte par ce design, permettant \u00e9galement de r\u00e9aliser un d\u00e9pointage de +/- 25\u00b0, par le choix de l\u2019espacement entre les patchs fonctionnant \u00e0 une m\u00eame fr\u00e9quence" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure8-1.png", + "caption": "Fig. 8. The characteristic solution of foot-mounted single-stage gear reducer with the horizontal arrangement of the shafts (Hansen solution) [16].", + "texts": [ + " If the gear reducer is intended for operation in an environment with high ambient temperature, as well as the higher engine power is used and higher losses can be expected, the housing should be manufactured with ribs (Fig. 7) to increase the outer surface of the housing and improve heat dissipation. Also, housing with ribs is used for large gear unit to increase their rigidity. To simplify the gearbox production as much as possible, many manufacturers produce one-piece housings to avoid machining of large contact areas between two parts of the housing. They have to provide an opening for large gears, usually at the top of housing (Fig. 8) or on one of the front side (Fig. 9 and 10) which afterwards should be closed with a cover. With this approach, they significantly simplify the machining of the housings, although the assembling of such gear units is somewhat more complex. Today, as stated above, basic attention is paid to aesthetic, i.e. product design. Modern solutions of single-stage universal gear reducer are recognized by simple and attractive form, slight shape transitions and somewhat higher material consumption. It is interesting to note that some manufacturers assemble single-stage gear reducers in the housings for two-stage gear units (cylindrical-bevel gear reducers) to increase the series of housing and thereby reduce production costs (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure3-1.png", + "caption": "Fig. 3. The characteristic solution of foot-mounted single-stage gear reducer with the output gear between bearings (Nord solution) [8].", + "texts": [ + " At foot-mounted single-stage reducers, the pinion is positioned above the output gear, so that the large electric motor can be installed. In this way, the input shaft is at sufficient height relative to the base. The solution with the overhung output gear has larger dimensions and thus the weight of gear reducer (Fig. 2). Also, the deflection of this gear is slightly larger, but it is negligible because of the large diameter of the output shaft. However, this type of conceptual solution is much more often used than the solution with the gear between bearings (Fig. 3, 4). During adopting the conceptual solution of gear reducer, mounting method and way of mounting elements should be considered. Also, this consideration must be given to the way of connecting gear reducer housing with housings of other units, or with the cover, electric motor, or adapter for IEC motors. Of course, this must take into account the minimum consumption of material, the lower the volume of machining and the sufficient strength and rigidity of the housing. Universal single-stage gear reducers are produced as one-housing or two-housing units" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004563_blicFiles_00187b.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004563_blicFiles_00187b.pdf-Figure2-1.png", + "caption": "Figure 2. Arrangement of tractors and the measured machine", + "texts": [ + " Measuring of the overall pulling resistance of the machine When measuring the pulling forces of mechanisation devices two basic variants of arrangement can be used. If the measured machine is mounted by means of a three-point suspension (and this was our case), two tractors must be used for the measuring: the first one is the source of pulling force (pulling tractor Fendt 926 vario) while the other (Fendt 822 favorit) functions as a carrier (of the measured machinery). The tensometric sensor itself then links up both tractors and transfers the pulling force from the first tractor to the second one. The arrangement of both tractors is presented in Figure 2. In case that the sensor of the pulling force can be mounted directly on the tractor it is not necessary to use the connecting device. In our field experiments the pulling resistance of the disc harrow DISKER DN 4.5 (Farmet-\u010cesk\u00e1 Skalice) with the working width of 4.5 m was measured. On the ground of load-capacity of the sensor, the working mesh of the machine was reduced by unmounting both side disks. The resulting width was 2.65 m. Characteristics of cultivated soil (moisture content and specific density) were determined by means of a laboratory analysis of obtained soil samples" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004590_O201319947248395.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004590_O201319947248395.pdf-Figure2-1.png", + "caption": "Fig. 2. Transformation optics-based cloak schematics and corresponding materials in the (a) physical geometry and (b) virtual geometry. PEC=perfect electric conductor, EM=electromagnetic.", + "texts": [ + " The caveat, though, is that the procedure provides us no guarantees that the materials parameters dictated by the transformation are physically realizable, and/or that they can be fabricated in practice to achieve cloak designs which satisfy the desired specifications, such as small thickness, wide bandwidth, polarization insensitivity, etc. The realizability issue, alluded to above, becomes even more critical when we attempt to design an \u201cinvisible\u201d cloak, the so-called \u2018holy grail\u2019 of cloak designers. We will now explain why this is the case with a simple example shown in Fig. 2. Let us assume, for the sake of convenience, that the target we wish to cloak is a sphere and that we are going to follow the TO paradigm for this task. This problem has been extensively studied by a number of authors [1-22] and they have derived the material parameters for the cloak by invoking the TO, and using the Jacobian of the transformation (Eq. (1)), which makes the cloaked object totally disappear (become invisible). In Fig. 3 we plot the material parameters, presented in [18], which makes the cylinder (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002555_354-68291504125V.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002555_354-68291504125V.pdf-Figure2-1.png", + "caption": "Figure 2: Dynamic model of the boom", + "texts": [ + " The second phase 1-2 is the phase of balanced movement of portal during the time tr, which is characterized by constant velocity vr. In the phase 2-3 (time tk) portal slows down constantly with deceleration ak until it stops. The distance covered is determined according the velocity profile, figure 1. Vasiljevi\u0107, R. - Ga\u0161i\u0107, M. \u2013 Savkovi\u0107, M. 3.1. Description of model Boom is an integral part of portal crane. In the system of portal crane, the arrow is idealized as an individual subsystem. Regarding this, Figure 2 shows the equivalent dynamic model of the boom portal crane. The model is designed for the determination of dynamic loads. Boom is seen as an individual subsystem that performs oscillation. Boom subsystem consists of a supporting structure of the boom and the cable system. Equivalent dynamic model is formed so that, on the one hand, keeping the main dynamic characteristics of arm and on the other hand, defined the problem is mathematically solvable. Discretization of supporting structure of the boom is done on a light rod with a reduced weight on top. From Figure 2 shows that the subsystem of the boom with load represented by two mass element, two light rod and a circular drive. The supporting structure of the boom was presented with a light cane which length is Ls and mass m1, which is reduced to the arrowhead. Rope system stream is introduced by non flexible light cane which length is Lu and mass m2, enabling the oscillation of load. Mass m2 represents the mass of the load. So arrowhead or m1 and m2 are connected non flexible light cane length Lu. Rotary column is represented by a circular disc of the axial moment of inertia J and torque of rotation T", + " Distance joint radius of the column axis is equal to r. Reduced mass m1 is based on the recommendations in the paper [4] can be determined according to the following relation: sm=m 3 1... 4 1 1 (1) where ms weight of of the boom. 3.2. Mathematical formulation To set the mathematical formulation of a dynamic model of the boom i formed will be used Langran\u017eeve equations of the second kind. The equations of motion of elements of the boom are set on the basis of eqvivalent dynamic model shown in Figure 2. The dynamic equations of motion of the system are as follows: \u03d5cos1sin 2 2 2 dt Yd L \u03b8(t)=-\u03c9(t)\u03b8 p u + (2a) \u03d5sin1sin 2 2 2 dt Yd L \u03c8(t)=-\u03c9(t)\u03c8 p u + (2b) TtJ =)(\u03d5 (2c) where \u03b8 angle of oscillation of the cargo in the longitudinal direction, \u03c8 angle of oscillation of cargo in the lateral direction, rotation angle, \u03c6 rotation angle column boom, Yp linear displacement portal and \u03c9 angular frequency of oscillation of the load. 3.2.1. Oscillation of cargo The first two equations (2a) and (2b) shall be determined by the laws of undamped oscillation of the pendulum as a function of time by generalized coordinates \u03b8 i \u03c8 due to the acceleration of the portal given diagram according to Figure 1", + "2. Dynamic load In accordance with the adopted generalized coordinates of oscillation of the dynamic model of boom, dynamic bending moment occurs due to oscillation loads in two directions: Vasiljevi\u0107, R. - Ga\u0161i\u0107, M. \u2013 Savkovi\u0107, M. \u2022 dynamic bending moment due to the oscillation of cargo in the longitudinal direction, and \u2022 dynamic bending moment due to oscillation of cargo in the lateral direction. Dynamic bending moment due to the oscillation of the cargo in the longitudinal direction reads, figure 2: ( ) ( )( ) ( )\u03b8\u03b1\u03b8\u03b8 \u03b1\u03b8\u03b8\u03b8 \u03b1 cossinsin cossincos cos= 2 2 2 2 1 usu suu sdin,p LLLm rLLLgm rLgmM \u2212 ++++ ++ (14) Dynamic bending moment due to oscillation loads in the lateral direction can be twofold, slika 2: ( ) ( )\u03c8\u03b1\u03c8\u03c8 \u03c8\u03c8\u03c8 cossinsin sincos= 2 2 2 21 usu uudin,b LLLm LLgmM \u2212 ++ (15) ( )rLLmM sudin,b +\u03b1\u03c8\u03c8 coscos= 2 22 (16) In this subchapter shall in the case of portal cranes applied theoretical dynamic analysis laid out in subheadings 2 and 3 to verify its correctness and the formation of conclusions" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001143_23_2_pag_55_vela_dg_-Figure3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001143_23_2_pag_55_vela_dg_-Figure3-1.png", + "caption": "Fig. 3. Scheme for kinetostatical analysis of the lower finger.", + "texts": [ + " The return to the initial position of the SMA spring and the action of the elastic forces (Fspr) of the springs (4) and (5) causes the return of the actuator's driving elements (2) and (3), of the fingers (6) and (7), releasing the working object (10). For a better prehension, the fingers (6) and (7) are provided with the jaws (8) and (9) respectively. The component links are connected by means of translational kinematical joints A and B, rototranslational kinematical joints C and D and rotational kinematic joints E, F, H and J. 3. Kinetostatical Analysis In order to determine the computational relations of forces and reactions in kinematic joints, Fig. 3 shows the scheme for the kinetostatic analysis of the lower finger, which is made on the basis of kinematic and constructive data \u03b1, \u03b2, l1, and l2. For the design of the prehension device, it is necessary to determine the prehension force F2, necessary for keeping the workpiece oriented and fixed during handling. Knowing this force enables the computing of the force Fa developed by the shape memory element, considering the following: - calculation of the forces acting on the components, the reactions in the kinematical joints and the angle of rotation of the actuator driving elements, as a function of the dimensions of the workpiece; - the value of the force F2 required to keep the workpiece oriented and fixed during the handling process; - the value of the rotation angle \u03b1 set by the designer, depending on the stroke of the finger jaws (8), (9) and the design theme; - the elastic force (Fspr) of the helical springs for returning to the initial position of the finger jaws (8) and (9), determined at the design stage as a function of: the dimensions of the components, the frictional forces in the kinematical joints, the weight of the components and the working position of the device (horizontal, vertical or inclined). On the basis of the kinetostatical scheme in fig. 3, knowing the force F2, taking into account the other forces acting on the component elements and the reactions in the kinematical joints, as well as the angles of rotation depending on the dimensions of the workpiece, it is possible to calculate the required force Fa developed by the SMA element. For the return of the fingers to the initial position, the force Fa produced by the SMA element acts in reverse, together with the elastic force Fspr generated by the return of the springs (4) and (5) to the initial state" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004125_f_version_1625137414-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004125_f_version_1625137414-Figure8-1.png", + "caption": "Figure 8. Schematic diagram of the hybridization layer of sugar palm yarn fibers with glass fiber mat-reinforced unsaturated polyester composite. Reproduced from ref. [136].", + "texts": [ + " According to Caseri [132], the interaction could be either weak because of van der Waals forces, hydrogen bonding, and weak electrostatic interactions, or it might be strong due to the chemical interactions between the different components. A number of studies on hybrid natural fiber composites have been conducted, and they provide a range of properties that are not possible to achieve with a single type of reinforcement [133,134]. As a result, a balance of mechanical perfor- mance and cost reduction for engineering applications could be realized. However, hybrid natural fiber composites are generally limited up to 50% of fiber loading [135]. Figure 8 shows an example of the hybridization layer between sugar palm yarn fiber with glass fiber mat-reinforced unsaturated polyester composites conducted by Nurazzi et al. [136]. A combination of several types of natural fibers in different forms (e.g., woven, non-woven, long fiber, short fiber, and powder) in a polymer matrix is possible for the development of hybrid composites for a variety of applications such as automotive, aerospace, furniture, etc. [133,137\u2013139]. Asim et al. [140] studied the influence of hybridization of PALF and kenaf fiber at different fiber loading on the mechanical properties of phenol formaldehyde composites" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003235_8948470_09084153.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003235_8948470_09084153.pdf-Figure2-1.png", + "caption": "FIGURE 2. Relative position between screw and nut.", + "texts": [ + " The sign of transmission ratio is dependent on the direction of PM helix, either left-handed or right-handed. Left-handed PM helix results in a negative transmission ratio, and right-handed PM helix results in a positive transmission ratio. The MLS investigated in this paper is right-handed. Similar to magnetic gears or couplings, the values of thrust force and torque of MLS are determined by the relative position between the nut and screw. However, the position of helical PM could be measured from both axial and angular directions, as indicated in Fig. 2. The load angle \u03b4 is defined as \u03b4 = 1\u03b8 + G \u00b71z (2) where 1\u03b8 and 1z denote the angular and axial position difference, respectively. And the thrust force and torque on screw can be approximated as T \u2248 Tm sin \u03b4 (3) F = G \u00b7 T \u2248 G \u00b7 Tm sin \u03b4 (4) where Tm is the pull-out torque. B. DETENT EFFECT One of the challenges to popularize the MLS lies in the realization of radially magnetized helical PMs. To achieve high force density, sintered NdFeB PMs are usually adopted in the MLS. However, it\u2019s hard to manufacture continuous sintered NdFeB PMs with standard radial magnetization" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004291_advpub_22-00301__pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004291_advpub_22-00301__pdf-Figure4-1.png", + "caption": "Fig. 4 Inner side view and rear view of the front wheel assy when LF acts on the wheel. In the rear view, the black arrows represent Y-direction components of the forces acting on points A, B, C and J. The white arrow represents the displacement of point A. LF acts on point J in the negative Y-direction. On points B and C, forces with positive Y-direction components act. On point A, a force with negative Y-direction component acts, and displacement in positive Y-direction occurs.", + "texts": [], + "surrounding_texts": [ + "\u00a9 The Japan Society of Mechanical Engineers\n\u3053\u308c\u306f\uff0c\u7b49\u9577\u5e73\u884c\u306b\u8fd1\u304f\u306a\u308b\u3088\u3046\u8a2d\u5b9a\u3059\u308b\u3053\u3068\u3067\u8fba B-D\u3068\u8ef8 C-H\u3092\u30d1\u30e9\u30ec\u30eb\u30ea\u30f3\u30af\u5316\u3057\uff0c\u3053\u308c\u306b\u3088\u308a\u30b5\u30b9\u30da\u30f3\u30b7 \u30e7\u30f3\u3078\u306e\u524d\u5f8c\u5165\u529b\u6319\u52d5\u306b\u5bfe\u3057\u30db\u30a4\u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u3092\u5c0f\u3055\u304f\u6291\u3048\u308b\u305f\u3081\u3067\u3042\u308b\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u70b9 G \u306e\u3070\u306d\u5b9a\u6570 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\u4e21\u5185\u5411\u304d\u3068\u306a\u308b\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\u307e\u305f\uff0c\u70b9 A, J\u3092\u901a\u308b\u8ef8\u307e\u308f\u308a\u306e\u30e2\u30fc\u30e1\u30f3\u30c8\u304a\u3088\u3073\u30db\u30a4\u30fc\u30eb\u90e8\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u91e3\u5408 \u3044\u306b\u3088\u308a\uff0c\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u3068\u3082\u306b\u8eca\u4e21\u5916\u5411\u304d\u3068\u306a\u308b\u3053\u3068\u304c\u308f\u304b\u308b\uff0e\u6b21\u306b\u70b9A, B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u5927\u304d\u3055 \u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u4ee5\u4e0b\u3067\u306f\u3053\u308c\u3089\u306e\u529b\u306e\u5927\u304d\u3055\u3092\u305d\u308c\u305e\u308c FAY\uff0cFBY\uff0cFCY\u3068\u8868\u3057\uff0cLF\u306e\u5927\u304d\u3055\u3092 FY\u3068\u8868\u3057\u305f\uff0e\u8ef8 A-J\u3068\u8ef8 B-C\u306e\u4ea4\u70b9\u3092 L\u3068\u3057\uff0c\u70b9 L\u304b\u3089\u70b9 A, B, C, J\u307e\u3067\u306e\u8ddd\u96e2\u3092\u305d\u308c\u305e\u308c a\uff0cb\uff0cc\uff0cd\u3068\u3057\u3066\u5404\u70b9\u306b\u4f5c\u7528\u3059\u308b\u529b \u306e\u5927\u304d\u3055\u306e\u6bd4\u3092\u8868\u3059\u3068 FAY : FY =d : a, FBY : FCY = c : b\u3068\u306a\u308b\uff0e\u3053\u308c\u3089\u3092\u30db\u30a4\u30fc\u30eb\u90e8\u80cc\u9762\u8996\u3067\u3042\u308b\u56f3 4(b)\u306b\u9ed2\u77e2\u5370\u3067 \u793a\u3059\uff0e\u3064\u304e\u306b\uff0c\u70b9 A \u306e\u5909\u4f4d\u306e\u5411\u304d\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u70b9 A \u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u70b9 A \u306b\u8a2d\u7f6e\u3055\u308c\u305f\u3070\u306d\u306b\u3088\u308a\u751f\u3058\u308b\uff0e \u305d\u306e\u305f\u3081\u70b9 A\u306f\u8eca\u4e21\u5916\u5411\u304d\u306b\u5909\u4f4d\u3059\u308b\uff0e\u3053\u308c\u3092\u56f3 4(b)\u306b\u767d\u629c\u304d\u77e2\u5370\u3067\u793a\u3057\u305f\uff0e\n\u3064\u304e\u306b\u56f3 5\u306e\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u5e73\u9762\u8996\u3092\u4f7f\u3063\u3066\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u304a\u3088\u3073\u5909\u4f4d\u306b\u3064\u3044\u3066\u8003\u3048\u305f\uff0e\u307e\u305a\u30db\u30a4\u30fc\u30eb\u90e8 \u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u3053\u3053\u3067\u306f X\u8ef8\u65b9\u5411\u6210\u5206\u3082\u542b\u3081\u3066\u8003\u3048\u308b\uff0e\u70b9 C\u304a\u3088\u3073\u70b9 H\u306f\u30dc\u30fc\u30eb\u30b8\u30e7 \u30a4\u30f3\u30c8\u3067\u3042\u308b\u305f\u3081\uff0c\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u30bf\u30a4\u30ed\u30c3\u30c9\u8ef8 C-H\u306b\u6cbf\u3046\u3082\u306e\u306b\u306a\u308b\uff0e\u524d\u8ff0\u306e\u3088\u3046\u306b\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 C\u306b \u4f5c\u7528\u3059\u308b\u529b\u306e Y\u8ef8\u65b9\u5411\u6210\u5206\u306f\u8eca\u4e21\u5916\u5411\u304d\u306e\u305f\u3081\uff0c\u56f3 5\u306e\u5e73\u9762\u8996\u306b\u304a\u3051\u308b\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u8eca\u4e21\u5916 \u5411\u304d\uff0c\u304b\u3064\u3084\u3084\u524d\u65b9\u3092\u5411\u304f\uff0e\u70b9 A\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f Y\u8ef8\u306b\u6cbf\u3063\u305f\u65b9\u5411\u3068\u3059\u308b\u3068\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u529b\u306e\u91e3\u5408\u3044\u304b\u3089\uff0c\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u8eca\u4e21\u5916\u5411\u304d\uff0c\u304b\u3064\u3084\u3084\u5f8c\u65b9\u3092\u5411\u304f\uff0e\u56f3 5\u3067\u306f\u3053\u308c\u3089\u306e\u529b\u3092\u9ed2\u77e2\u5370\u3067\u8868\u3057\u305f\uff0e\u307e\u305f\u70b9 B, C\u306b\u4f5c\u7528 \u3059\u308b\u529b\u306e\u5927\u304d\u3055\u3092\u305d\u308c\u305e\u308c FB, FC\u3068\u8868\u793a\u3057\u305f\uff0e\u3072\u304d\u3064\u3065\u304d\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u304a\u3088\u3073\u30bf\u30a4\u30ed\u30c3\u30c9\u4e0a\u306e\u70b9 C\u306b\u4f5c\u7528 \u3059\u308b\u529b\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u3053\u308c\u3089\u306e\u70b9\u306b\u306f\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e\u53cd\u4f5c\u7528\u304c\u50cd\u304f\u305f\u3081\uff0c\u30db\u30a4\u30fc\u30eb\u90e8\u306e\u70b9 B, C\u306b\u4f5c\u7528\u3059\u308b\u529b\u3068\u306f\u5411\u304d\u304c\u9006\u3067\u5927\u304d\u3055\u304c\u540c\u3058\u529b\u304c\u4f5c\u7528\u3059\u308b\uff0e", + "\u00a9 The Japan Society of Mechanical Engineers\n\u6700\u5f8c\u306b\u3053\u308c\u3089\u306e\u529b\u306b\u3088\u308b\u5909\u4f4d\u306b\u3064\u3044\u3066\u8003\u3048\u308b\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306b\u4e26\u9032\u3068\u56de\u8ee2 \u306e\u5909\u4f4d\u3092\u751f\u3058\u3055\u305b\u308b\uff0e\u8868 1 \u306b\u793a\u3057\u305f\u3088\u3046\u306b kDY\u306f kGY\u306b\u6bd4\u3079\u5927\u304d\u3044\u305f\u3081\uff0c\u3053\u3053\u3067\u306f\u3053\u308c\u3089\u306e\u5909\u4f4d\u3092\u70b9 D \u306e\u8eca\u4e21\u5185 \u5411\u304d\u306e\u4e26\u9032\u5909\u4f4d\u3068\u70b9 D\u306b\u95a2\u3059\u308b\u53cd\u6642\u8a08\u307e\u308f\u308a\u306e\u56de\u8ee2\u5909\u4f4d\u3067\u8003\u3048\u308b\uff0e\u307e\u305f\uff0c\u30bf\u30a4\u30ed\u30c3\u30c9\u4e0a\u306e\u70b9 C\u306b\u4f5c\u7528\u3059\u308b\u529b\u306f\u70b9 H\u3092\u8eca\u4e21\u5185\u5074\u306b\u5909\u4f4d\u3055\u305b\u308b\uff0e\u3053\u308c\u3089\u306e\u5909\u4f4d\u3092\u56f3 5\u3067\u306f\u767d\u629c\u304d\u77e2\u5370\u3067\u793a\u3057\u3066\u3042\u308b\uff0e\u306a\u304a\u70b9 D, H\u306e\u5909\u4f4d\u306f\u53b3\u5bc6\u306b\u306f Y \u8ef8\u65b9\u5411\u4ee5\u5916\u306e\u6210\u5206\u3082\u6301\u3064\u304c\uff0c\u3053\u308c\u3089\u304c\u30c8\u30fc\u89d2\u5909\u5316\u306b\u4e0e\u3048\u308b\u5f71\u97ff\u306f\u975e\u5e38\u306b\u5c0f\u3055\u3044\u306e\u3067\u7121\u8996\u3057\u305f\uff0e\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u56de\u8ee2 \u3092\u8003\u616e\u3057\u306a\u3044\u5834\u5408\uff0c\u70b9 D, H\u306e Y\u8ef8\u65b9\u5411\u306e\u5909\u4f4d\u306e\u5411\u304d\u306f\u305d\u306e\u307e\u307e\u70b9 B, C\u306e Y\u8ef8\u65b9\u5411\u306e\u5909\u4f4d\u306e\u5411\u304d\u3068\u306a\u308b\u306e\u3067\u70b9 B, C\u306f\u8eca\u4e21\u5185\u5411\u304d\u306b\u5909\u4f4d\u3059\u308b\uff0e\u305f\u3060\u3057\uff0c\u70b9 B, C\u306e\u5909\u4f4d\u91cf\u306f\u4e00\u822c\u306b\u306f\u540c\u3058\u3067\u306f\u306a\u3044\uff0e\u305d\u306e\u305f\u3081\u3053\u306e\u5dee\u306b\u8d77\u56e0\u3057\u5e73\u9762\u8996 \u3067\u898b\u305f\u30db\u30a4\u30fc\u30eb\u306b\u30c8\u30fc\u89d2\u5909\u5316\u304c\u751f\u3058\u308b\uff0e\u3053\u308c\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u672c\u8ad6\u6587\u3067\u306f\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3068\u547c\u3076\u3053\u3068 \u306b\u3059\u308b\uff0e\u307e\u305f\uff0c\u4e0a\u8ff0\u306e\u3088\u3046\u306b\u30ed\u30a2\u30a2\u30fc\u30e0\u306f\u70b9 D\u3092\u4e2d\u5fc3\u3068\u3057\u3066\u56de\u8ee2\u3059\u308b\uff0e\u3053\u306e\u56de\u8ee2\u306b\u8d77\u56e0\u3057\u3066\u5e73\u9762\u8996\u3067\u898b\u305f\u30db\u30a4\u30fc \u30eb\u306b\u524d\u5f8c\u6319\u52d5\u304c\u751f\u3058\u308b\uff0e\u3053\u306e\u969b\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u524d\u8fba B-D\u3068\u30bf\u30a4\u30ed\u30c3\u30c9\u8ef8 C-H\u306e\u30ea\u30f3\u30af\u4f5c\u7528\u306b\u3088\u308a\u30db\u30a4\u30fc\u30eb\u306b\u30c8\u30fc\u89d2 \u5909\u5316\u304c\u751f\u3058\u308b\uff0e\u3053\u308c\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u672c\u8ad6\u6587\u3067\u306f\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3068\u547c\u3076\u3053\u3068\u306b\u3059\u308b\uff0e\u3055\u3089\u306b\uff0c\u56f3 4(b) \u306b\u793a\u3057\u305f\u3088\u3046\u306b\uff0c\u70b9 A\u306f\u8eca\u4e21\u5916\u5411\u304d\u306b\u5909\u4f4d\u3059\u308b\uff0e\u3053\u308c\u306b\u8d77\u56e0\u3057\u3066\u30db\u30a4\u30fc\u30eb\u90e8\u304c\u8ef8 B-C\u307e\u308f\u308a\u306b\u56de\u8ee2\u3059\u308b\u3053\u3068\u3067\u30c8 \u30fc\u89d2\u5909\u5316\u304c\u751f\u3058\u308b\uff0e\u3053\u308c\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u672c\u8ad6\u6587\u3067\u306f\u30e2\u30fc\u30c9\u2162\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3068\u547c\u3076\u3053\u3068\u306b\u3059\u308b\uff0e\u4ee5\u4e0b\u306b\u3053 \u308c\u3089\u306e 3\u3064\u306e\u30e2\u30fc\u30c9\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u9806\u306b\u691c\u8a0e\u3059\u308b\uff0e\n3\u30fb2 \u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316 \u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u70b9 D\u3068 H\u306e\u5de6\u53f3\u65b9\u5411\u3078\u306e\u5909\u4f4d\u5dee\u306b\u8d77\u56e0\u3057\u3066\u751f\u3058\u308b\u3082\u306e\u3067\u3042\u308b\uff0e\u4e00\u822c\u7684\u306a FF\u8eca\u7528 \u30b9\u30c8\u30e9\u30c3\u30c8\u5f0f\u30d5\u30ed\u30f3\u30c8\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u3067\u306f\uff0c\u56f3 4(a)\u306b\u793a\u3057\u305f\u70b9 C, L \u9593\u306e\u8ddd\u96e2 c \u306f\u70b9 B, L \u9593\u306e\u8ddd\u96e2 b \u3088\u308a\u3082\u5927\u304d \u3044\uff0e\u305d\u306e\u305f\u3081\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u4e0a\u306e\u70b9 B\u306b\u4f5c\u7528\u3059\u308b\u529b\u306e Y\u8ef8\u65b9\u5411\u6210\u5206\u306e\u5927\u304d\u3055 FBY\u3068\uff0c\u30bf\u30a4\u30ed\u30c3\u30c9\u4e0a\u306e\u70b9 C\u306b\u4f5c\u7528\u3059 \u308b\u529b\u306e Y\u8ef8\u65b9\u5411\u6210\u5206\u306e\u5927\u304d\u3055 FCY\u306e\u95a2\u4fc2\u306f FBY : FCY = c : b\u3068\u793a\u3055\u308c\uff0cFBY > FCY\u306b\u306a\u308b\uff0e\u4e00\u65b9\uff0c\u8868 1\u306b\u793a\u3059\u3088\u3046\u306b \u70b9 D, H \u306e\u3070\u306d\u5b9a\u6570 kDY, kHY\u306f\u540c\u7a0b\u5ea6\u306e\u5927\u304d\u3055\u3092\u6301\u3064\u305f\u3081\uff0c\u70b9 D, H \u306e\u5909\u4f4d\u91cf\u306f\uff0c\u70b9 D \u306e\u8eca\u4e21\u5185\u5074\u3078\u306e\u5909\u4f4d\u91cf\u304c\u70b9 H\u306e\u5909\u4f4d\u91cf\u3088\u308a\u3082\u5927\u304d\u304f\u306a\u308b\uff0e\u3057\u305f\u304c\u3063\u3066\uff0c\u70b9 B\u306e\u8eca\u4e21\u5185\u5074\u3078\u306e\u5909\u4f4d\u91cf\u304c\u70b9 C\u306e\u5909\u4f4d\u91cf\u3088\u308a\u3082\u5927\u304d\u304f\u306a\u308a\uff0c\u30db\u30a4 \u30fc\u30eb\u306e\u30c8\u30fc\u89d2\u5909\u5316\u306f\u30c8\u30fc\u30a4\u30f3\u65b9\u5411\u306b\u306a\u308b\uff0e\u3053\u306e\u3088\u3046\u306b\uff0c\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u4e00\u822c\u306b\u306f\u30c8\u30fc\u30a4\u30f3\u3068\u306a\u308b\u3053 \u3068\u304c\u591a\u3044\uff0e\u4ee5\u4e0a\u304b\u3089\uff0c\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u4e3b\u306b\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u8af8\u5143\u306e\u5bf8\u6cd5 b, c \u304a\u3088\u3073\u3070\u306d\u5b9a\u6570 kDY, kHY \u306e 4 \u5024\u306b\u3088\u3063\u3066\u6c7a\u5b9a\u3055\u308c\u308b\u3053\u3068\u304c\u5206\u304b\u308b\uff0e\u3053\u306e\u30e2\u30fc\u30c9\u2160\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u30c8\u30fc\u30a4\u30f3\u304b\u3089\u30c8\u30fc\u30a2\u30a6\u30c8\u306b\u3059\u308b\u3053\u3068 \u306f\uff0c\u5bf8\u6cd5 b\u3092 c\u3088\u308a\u3082\u5927\u304d\u304f\u3059\u308b\uff0c\u3082\u3057\u304f\u306f kHY\u3092 kDY\u306b\u6bd4\u3079\u3066\u5341\u5206\u4f4e\u3044\u3082\u3068\u306e\u3068\u3059\u308b\u3053\u3068\u3067\u53ef\u80fd\u306b\u306a\u308b\u304c\uff0c\u3053\u308c \u306f\u4e00\u822c\u7684\u306b\u306f\u4ed6\u306e\u30b5\u30b9\u30da\u30f3\u30b7\u30e7\u30f3\u7279\u6027\u306e\u5236\u7d04\u306b\u3088\u308a\u56f0\u96e3\u3067\u3042\u308b\u3053\u3068\u304c\u591a\u3044\uff0e\n3\u30fb3 \u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316 \u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\uff0c\u30ed\u30a2\u30a2\u30fc\u30e0\u306e\u70b9 D\u307e\u308f\u308a\u306e\u56de\u8ee2\u306b\u8d77\u56e0\u3057\u3066\u751f\u3058\u308b\uff0e\u305f\u3060\u3057\uff0c\u70b9 D, H\u306e\u8eca\u4e21\u5de6\u53f3 \u65b9\u5411\u3078\u306e\u5909\u4f4d\u5dee\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u306f\u3059\u3067\u306b\u30e2\u30fc\u30c9\u2160\u3067\u8003\u616e\u3057\u3066\u3044\u308b\u305f\u3081\uff0c\u30e2\u30fc\u30c9\u2161\u306b\u3088\u308b\u30c8\u30fc\u89d2\u5909\u5316\u3092\u8b70\u8ad6\u3059\u308b\u5834" + ] + }, + { + "image_filename": "designv8_17_0000229_om_article_22311_pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000229_om_article_22311_pdf-Figure1-1.png", + "caption": "Fig. 1. A six DOF dynamic model", + "texts": [], + "surrounding_texts": [ + "Finite element model and lumped mass model are used for simulating gear systems with cracks. The lumped mass model is usually considered in case the shafts and the bearings supporting the gears are assumed to be rigid. For flexible shafts, finite element model is used. Different mathematical models have been developed for different purposes in the past decades. In the previous studies, main objective in the primary analysis of the gear system was to predict tooth dynamic loads for designing gears at high speeds. Different degree of freedom models like 4 DOF, 6 DOF, 8 DOF and 12 DOF models have been used for the lumped mass model systems. The stress intensity factors are the major parameters to estimate the characteristics of crack. Weight function techniques which are analytical methods and several other numerical methods have been used by researchers to calculate tooth stress intensity factors. Following the work done by earlier researchers [1-12], six degree of freedom dynamic model has been developed. In the present study simulation was performed for both healthy and cracked cases and then gear mesh stiffness corresponding to crack sizes can be input into dynamic model. ODE45 function is used to build the model and solve the equations of motion. Experimental studies say that dynamic analysis should include time varying gear mesh stiffness and gear backlash. Dynamic models of gear pair transmission are classified in four categories as Linear Time Invariant model, Linear Time varying models which include time varying gear mesh stiffness, non-linear time invariant which include gear backlash and non-linear time varying models which include time varying gear mesh stiffness and gear backlash respectively. A complex model has been used following earlier researchers [15, 16] of finite elements that excludes many of the constructs that simplify them. At the shaft frequency, they discovered the system\u2019s forced vibration response, excited by mass unbalances and performed gear errors using modal summation. But the high frequency, internal, static propagation, error excitation, which has the key function in producing noise, was not considered. In a recent paper by Gregory (1963) made a comprehensive study of linear mathematical models used in gear dynamics analysis is considered as the number of nonlinear contact forces in vertical direction at each contact point. Using ANSYS software, the driving shaft and driven shaft are designed by the Beam188 element and the driving and driven gears are modeled by the Solid185 element. The nodes are coupled at holes of each gear and at the central axis, master node is coupled. Depending on the neutral file obtained from the ANSYS software, MSC ADAMS is used to develop the flexible model. The vibration signals of spur gears with multiple cracks are measured. ISSN PRINT 2345-0533, ISSN ONLINE 2538-8479, KAUNAS, LITHUANIA 45" + ] + }, + { + "image_filename": "designv8_17_0003156_1_files_28155276.pdf-Figure3.3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003156_1_files_28155276.pdf-Figure3.3-1.png", + "caption": "Figure 3.3: Pulling side of wire movement system", + "texts": [ + " More details of the system can be seen in Figure 3.2. The system is made up of two parts, the pulling and the payoff sides. The pulling side consists of a large frame made of square steel tube that is home to two spools, each driven by Pacesetter 48R-5H 0.75 hp motors and controlled by TECO JNEV-201-H3 AC drives. There are also three guiding and tensioning pulleys, as well as an AMACOIL AKI3-15-6 traversing unit and a Shimpo DT-105A tachometer to monitor the wire speed. The pulling system is featured in Figure 3.3. The payoff side has a single spool with a friction brake on it to give appropriate wire tension and ensure it does not freewheel from inertia when the system stops. There is also a Cometo AS574 single plane wire straightener and two guide pulleys to control the entry into the wire straightener. The wire payoff system is featured in Figure 3.4. The parameters of interest in this study are the wire temperature at the bed inlet and outlet, the bed temperature, the wire speed and the fluidizing velocity" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003971__2462_context_theses-Figure4-3-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003971__2462_context_theses-Figure4-3-1.png", + "caption": "Figure 4-3: Ring gear notation", + "texts": [ + " Furthermore the number of teeth of planetary gears do not have an influence to the gear ratio of the system. Hence, the number of teeth of the plenary gears 26 are dependent of the teeth of the ring gear and the teeth of the sun gear as well as the module and the diameter of the ring and sun gear: In cases of wind turbines, the maximum outer diameter for the ring gear is limited by the housing of the system. Hence, for the ring gear pitch diameter is dependent of the outer diameter and the thickness of the rim as well as dedendum (Figure 4-3). Therefor the pitch diameter is: 2 \u2217 (4-2) determined by gearbox housing (4-3) (4-4) 26 defined from table27 (4-5) 0.1\u2026 0.4 (4-6) 28 3.5\u2026 4.2 \u2217 (4-7) 29 29 Reference [9, p. 705] 27 For a given pitch diameter , a defined helix angle (in this thesis =0) and a defined module , the number of teeth\u2019s of the ring gear can be determined. = \u2217 cos( ) (4-8)30 Because of obvious reasons, the number of teeth of the ring gear has to be a whole number. That means that the calculated value has to be rounded. The corrected number of teeth of the ring gear \u2217 leads to a corrected pitch diameter \u2217" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004515_id_0354-98362304229C-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004515_id_0354-98362304229C-Figure4-1.png", + "caption": "Figure 4. Expansion of conventional vehicle chassis", + "texts": [ + " The design of conventional and electric vehicle chassis has been carried out in accordance with TSE standards, considering the MARTOY Regulation (The Regulation on Approval and Market Surveillance of Motor Vehicles and their Trailers) [15]. In compliance with the regulation, the Class M1 is designed as a hatchback 5-door car chassis with AB body type. To prevent major accident effects from the side of conventional vehicles, three different impact-dampening parts have been incorporated, as shown in fig. 4. The chassis design of the conventional vehicle has been completed, using simpler parts instead of structures with more complex surfaces to be manufactured. The conventional vehicle chassis, the design of which has been completed, underwent a transformation into the electric vehicle chassis shown in fig. 5 by incorporating the design considerations presented in figs. 6 and 7. The electric vehicle chassis has been designed by placing the batteries on the base of the vehicle and distributing the front load, which is typical of conventional vehicles, to the vehicle base" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure17-1.png", + "caption": "Fig. 17. Characteristic design solutions of single-stage gear reducer with different flange diameters connected with housing by screws (NRW solution) [5].", + "texts": [ + " NRW is one of the few manufacturers who produce foot-mounted single-stage gearboxes with an output shaft positioned both up and down (Fig. 16). The output shaft is very rarely positioned above the pinion since it often prevents installation of motor gear reducer on a flat surface. This manufacturer also produces foot and flange-mounted single-stage gear units for three different flange diameters, which is rarely required. It also produces flange-mounted gear reducers with different flange diameters that are connected with housing by screws (Fig. 17). NRW produces gear units with the classic input shaft and with the adapter for IEC motors with flanges B5 and B14. The design of the housing is quite complex, taking into account the cost savings of the material as well as the reinforcement of the housing. The form is simple and attractive (Fig. 18). [5] * Corresponding author: racmil@uns.ac.rs Single-stage gear reducer with free shaft arrangement, ie. shaft-mounted gear units are mounted directly to the driving shaft and the shaft position itself adapts to the specific mounting conditions (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003315__Issue1-15_paper.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003315__Issue1-15_paper.pdf-Figure13-1.png", + "caption": "Fig. 13. Characteristics of friction force (a) and external force (b) acting on the frictional joint", + "texts": [ + " Value of friction force T is dependent on the pressure force N and on the value of static (\u03bcst) and kinetic (\u03bck) friction coefficients between the surfaces of contacting sections. However, application of the resistance wedge causes that resistances to motion in the joint are much higher than resulting from the action of static and kinetic friction forces. Therefore, resistances connected with the action of resistance wedge were taken into consideration in equations describing the friction force. Distribution of friction force increased by the resistances connected with the action of resistance wedge is presented in a Figure 13a. General equation describing the changes in value of friction force with considered resistances connected with an operation of the resistance wedge has following form: max max max max 3 2 3 2 3 2 3 2 3 2 3 2 3 2 sgn( ) 0 0 sgn( ) 0 0 sgn ( ), 0 0 st st st k st T W for y y and y y W T T W W y y y y W T T y y y y y y W T . for for . . . . . . . and and and and and (2) where: 1 1 3 1 1 3( ) ( )W k y y c y y max 3 2; ( , )st st kT N T f a y y . ; a \u2014 coefficient of increase of resistances to motion in the frictional joint", + " Coefficient of increase of resistances to motion in the frictional joint is contingent on the geometrical parameters of the resistance wedge and on the magnitude of a yield in the frictional joint. In analyzed model it was assumed, that its value will change from 0 to 0.3, what means that value of the friction force during a yield will not decrease below the maximum value of static friction force (Tst max). External active force P(t) acting on the frictional joint with the resistance wedge is a result of composition of two exponential functions (Fig. 13b) and is describe by following equation: ( ) ( ) (1 )d t t T T y st stP t P P e P e ; for dT T (3) where: Py \u2014 maximum value of dynamic impulse, kN, Pst \u2014 value of fixed static loading, kN, Td \u2014 time constant of dynamic impulse decay, s, T \u2014 time constant of component impulse decay, s. Value of force transmitted through the frictional joint, which characterizes reaction of the base was determined from following relationship: 2 2 2 2( )R t c y k y . (4) Developed mathematical model was subjected to numerical analysis, whose results allowed to determine the dynamic characteristics of the frictional joint with the resistance wedge determining the changes in value of force transmitted through the frictional joint (R(t))" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000917_1467-022-32892-y.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000917_1467-022-32892-y.pdf-Figure2-1.png", + "caption": "Fig. 2 | Rough force analysis of magnetic (Fmagnetic) and capillary (Fcapillary) interactions underlying the self-sorting of A-B and A-A. Photographs of a A-B and c A-A building blocks at air/water interfaces and schematic illustration of the magnetic/capillary interactions; stepwise snapshots as the building blocks of b A-B and d A-A approach. Scale bars: 8mm.", + "texts": [ + " Hence, we inserted two glass slides deposited with rough platinum aggregates (Supplementary Fig. 1a, b) at the bottom surface of EPS; upon placed onto H2O2 solutions, the platinum catalyzed the decomposition of H2O2 for vigorous release of oxygen bubbles, which exerted asymmetrical forces on opposite sides and resulted in selfpropulsion of EPS with a random motion trajectory (Supplementary Movie 1, Fig. 1b). The second design of capillary self-alignment was achieved by the wettability conflicts (Supplementary Fig. 2): two opposite side surfaces of EPS weremodified with a fluorinated coating to exhibit hydrophobicity38; the other two side surfaces were adhered with hydrophilic magnetic plates that were pre-modified with polyelectrolyte multilayers18. The capillary-driven assembly of two hydrophilic surfaces were observed in Fig. 1c: as the building blocks approach into proximity, the menisci gradually contact and merge to eliminate excessive surface areas, which is energy-favorable to minimize the interfacial free energy", + " The underlying challenge is to identify the surface chemistry of positive (A) or negative (B) polyelectrolytes on the hydrophilic surfaces. However, the selectivity of the electrostatic attraction between A-B and the electrostatic repulsion between A-A, can not distinguish these assemblies of AB or AA atmacroscopic scales because the molecular-leveled electrostatic interactions are much weaker than the long-ranged capillary forces. One possible solution is to build a selective mechanism at the \u03bcm-to-mm scale by coupling the capillary interactions with another long-ranged force, e.g., magnetic force (Fig. 1f). As shown in Fig. 2a: the lateral forces between A-B include the N-Smagnetic attraction and the capillary attraction, which generate additive effects to draw A-B together. Indeed, we observed the attraction during the approaching processes of A-B (Fig. 2b, Supplementary Movie 2); meanwhile, the original displacement between A-B was gradually adjusted by a slight rotation to achieve a precise matching. On the contrary, the magnetic N-N repulsion and the capillary attraction compete between A-A (Fig. 2c). By the subtle adjustments of the relative strength of both interactions, the resultant force displayed a repulsive effect to hinder the formation of AA clusters as shown in Fig. 2d andSupplementaryMovie 3. Thesephenomena suggested that the MSA results were determined by the strength difference between magnetic and capillary forces dependent on the dynamically changing distance between the building blocks. Namely, the understandings of the quantified force-distance correlations are requisite to reveal the assembly mechanism. Calculation and measurement of capillary/magnetic forces Therefore,we have studied the contributions of capillary andmagnetic forces by calculations, simulations, and force measurements", + " The measurement was conducted by a cycled contact-separation process between A-B, during which the force changes exerted on A and the distance that B had been moved were in situ recorded. We have summarized the measured magnetic force, the calculated capillary forces and the resultant lateral forces between A-B andA-A in Fig. 3b, c. From the localmagnificationof A-A in the inset of Fig. 3c, we could observe that the capillary forces were larger than magnetic forceswhen the interactive distancewas larger than 10.6mm but became lower as the distance reduced, which supported the observed repulsion between A-A when the building blocks approach into proximity (Fig. 2d). Namely, the self-sortingmechanismofA-B and A-A or B-B is established by the additivity of magnetic/capillary forces Nature Communications | (2022) 13:5201 3 b t d N B N S Fmagnetic + Fcapillary Fmagnetic - Fcapillary a c Fcapillary Fcapillary N N Attraction t Repulsion A AA Fig. 3 | Calculations and simulations of capillary and magnetic forces. a Capillary forces induced by single (F\u0302 capi) and merged (Fcapi) menisci at the threephase-contacting lines dependent on the angles (\u03b8\u0302 and \u03b8) between the according menisci and the horizontal direction as the interactive distance (xd) changes; the resultant lateral force for assembly is FMSA", + " 3d by the simulation when the interactive distance was varied (xd = 15, 10, 5, 0mm). As A-B approached and contacted, the total free energy decreased to the minimized level, which was an assumed energy condition of \u2018zero\u2019 potential in the simulation. Anydisplacements between thehydrophilic surfaces ofA-B will lead to the conflicts of the adjacent hydrophilic-hydrophobic surfaces and increase the free energy. Finally, A-B underwent a selfalignment process to form an ordered dimer as confirmed by the experimental results in Fig. 2b. The distribution of the magnetic potential in cases of A-B and A-A were simulated with the methods of finite element analysis (Fig. 3e, f), which fitted the global effects of the magnetic attraction (A-B) and repulsion (A-A) well. Applicationof the self-sortingmechanism for selective assembly To apply the above self-sorting mechanism in selective assembly, we used a model system consisting of two As and one B. Unlike the molecular self-assembly with numerous building blocks to provide averaged results, the MSA research relies on a number of parallel assembly events to provide statistical results" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001094__2412_context_theses-Figure57-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001094__2412_context_theses-Figure57-1.png", + "caption": "Figure 57 P-POD Mk. III Rev. E \u201cTuna Can\u201d Pusher Plate", + "texts": [ + " Unfortunately, in order to accommodate EMI gaskets, the access port cover set adds 134 grams compared to the previous access port cover set. P-POD Mk. IV Pusher Plate The next component of interest was the pusher plate. The original design initiative of the new pusher plate was to provide additional volume for CubeSats. The Page 71 volume within the P-POD mainspring was previously unused. Thus, the original \u201cTuna Can\u201d Pusher Plate was designed for the P-POD Mk. III Rev. E. This design is shown below in Figure 57. This design added roughly 50 grams to the total mass of the P-POD, but provided additionaly volume for the CubeSat to use, and included a cylindrical wall that protects the CubeSat from any main spring movements. This pusher plate had the opportunity to prove its function on an Atlas V Launch, where a CubeSat had a large protrusion off of its \u2013Z face that fit inside the pusher plate. So the P-POD Mk. III Rev. E Pusher Plate\u2019s design intent was met, but it was unnecessarily bulky given the load cases it was seeing" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002731_el-03158868_document-Figure2.24-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002731_el-03158868_document-Figure2.24-1.png", + "caption": "Figure 2.24 : Schematic representation of an open electric motor jet impingements on stator windings.", + "texts": [ + " [125] suggested the following correlation for averaged Nusselt number of rotating disk under confined jet impingement cooling: \ud835\udc41\ud835\udc62\ud835\udc5f\ud835\udc51 \u0305\u0305 \u0305\u0305 \u0305\u0305 \u0305 = 1.97619 ( \ud835\udc61\ud835\udc5b\ud835\udc5c\ud835\udc67 \ud835\udc37\ud835\udc57 ) 0.0909 ( 4\ud835\udc44\ud835\udc57 \ud835\udf0b\ud835\udf08\ud835\udc57\ud835\udc37\ud835\udc57 ) 0.75 ( \ud835\udf08\ud835\udc57 4\ud835\udf14\ud835\udc5f\ud835\udc51 2) \u22120.1111 ( \ud835\udf06\ud835\udc60 \ud835\udf06\ud835\udc53 ) \u22120.9 (2.48) Where \ud835\udc61\ud835\udc5b\ud835\udc5c\ud835\udc67 is the distance from the rotor disk to the nozzle, \ud835\udf06\ud835\udc60 and \ud835\udf06\ud835\udc53 are the thermal conductivities of the solid and the fluid respectively. Air Jet Impingement on Windings A possible air jet cooling technique applied at the surface of the end-windings is depicted in Figure 2.24. This technique aims mainly to improve the convection coefficient in this area and to create a circulation of fresh air arriving at the surface of these hot spot zones. These two factors will significantly help to extract heat from the motor windings efficiently (see. subsection 2.2.2.3 for end-windings end-space convection). 2.3.2.5 Liquid Cooling Many authors investigated liquid cooling in electrical machines as water jackets around the stator [80], [126] or refrigerant cooling of the stator [127], [128]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001404_22_Vol._51_59-73.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001404_22_Vol._51_59-73.pdf-Figure1-1.png", + "caption": "Figure 1. Scheme of dynamic loading of a loading device when lifting a load \u201cfrom weight\u201d", + "texts": [ + " When determining the starting modes of the lifting mechanisms of overhead cranes, the results of the following indicators were considered: excessive driving force, rope speed and rigidity of the supporting structure, mass of the engine rotor and load, kinetic and potential excessive force, system stiffness and time, load dynamics, oscillation frequency, conditions and mode of movement, etc. When assessing the dynamic load on load-gripping devices, the following should be considered: under conditions of proper operation, mainly only the vertical dynamic load during the operation of the load-lifting mechanism is significant, since, during the operation of the crane movement mechanisms and the rotation of its slewing part, it does not exceed 5-6% of the static load (Fig. 1) [1; 2]. Note: a) on an overhead crane; b) design scheme Source: [1; 2] There are two options for lifting the load: \u201cfrom weight\u201d and \u201cwith pickup\u201d/\u201dfrom the base\u201d [4-6]. In both cases, the dynamic coefficient (\u041ad) is determined by the dependence: \u041a\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51 = 1 + \u0420\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51\ud835\udc51/\ud835\udc44\ud835\udc44\ud835\udc44\ud835\udc44\ud835\udc59\ud835\udc59\ud835\udc59\ud835\udc59 , (1) where: \u0420dyn \u2013 in the first case is a function of the excess driving force and the stiffness of the supporting structure and in the second case is a function of the rope speed and the stiffness of the supporting structure" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002765_11633-014-0800-y.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002765_11633-014-0800-y.pdf-Figure2-1.png", + "caption": "Fig. 2 The 2-link manipulator on the ground", + "texts": [ + " And no external forces or torques apply on the system. 3) The system consists of a base and several links. The pose of the base is not controlled actively, and every joint between the links can rotate freely within a range under active control. The space manipulator system is shown in Fig. 1, where MC is the mass center of the system. When the space manipulator system is in the ground alignment stage the base can be fixed, for there exists gravity. To facilitate discussion, in this paper a planar 2-link manipulator is chosen, as shown in Fig. 2. In Fig. 2, Bi is the i-th link; Ci is the centroid of the link; mi is the link mass; i is the link length. ai is a scalar from the i-th joint to the centroid of the next link; bi is a scalar from the i-th centroid of the link to the joint of the next link; qi is the joint position. By geometric analysis and using the homogeneous coordinate transformation, we get the position of the endeffector[17]. pe = \u23a1 \u23a2\u23a3 \u2212l1s1 \u2212 l2s12 l1c1 + l2c12 0 \u23a4 \u23a5\u23a6 (1) where s1 = sin q1, s12 = sin(q1 + q2), c1 = cos q1, c12 = cos(q1 + q2)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002355_f_usme2019_01032.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002355_f_usme2019_01032.pdf-Figure2-1.png", + "caption": "Fig. 2. The axle test-bench with load application on cantilevers.", + "texts": [ + " The imbalance weight through the cardan shaft is set in rotation by electric motor. Testing the axle on such a test-bench develops a strong vibration impact on the test-bench foundation and on the premises where it is in operation. Vibration impact reduction on the foundation is reached by means of installation of elastic elements under the test-bench frame. In order to reduce the vibration caused by the test process the test-bench structural design was suggested for simultaneous testing of several axles [13] installed symmetrically on the platform (Fig. 2). The vectors of forces created by imbalances on axles are contradirectional and are compensated. The group drive ensures a preset synchronization of unbalanced weights with required phase shift. Simultaneous loading of several axles allows reducing the time of testing. With another test pattern [2] the axle of a part thereof is loaded as a free-ended beam (Fig. 3). There are no any particular advantages of such loading patterns as compared to each other. However, the installation of the axle on two supports is somewhat more suitable as compared to vertical cantilever-like installation with a wheel" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure20-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002222_BPASTS_2022_70_3.pdf-Figure20-1.png", + "caption": "Fig. 20. The von Mises stress distribution in the assembly of the modelled rims for the case of transport of pallets with paving stones during driving on the dirt road when case only one tire of the one twin wheel of the rear axle were in contact with the road", + "texts": [ + " In this case, both tires of each twin wheel of the rear axle were in contact with the road. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during driving on the dirt road were shown in Fig. 19. They did not exceed values of 160 MPa. In this case, both tires of each twin wheel of the rear axle were in contact with the road as well. The obtained values of the von Mises stress distribution for the case of transport of pallets with paving stones during driving on the dirt road were shown in Fig. 20. They did not exceed values of 400 MPa. In this case, only one tire of the one twin wheel of the rear axle was in contact with the road. Although in most cases analyzed, the obtained values of the von Mises stresses did not exceed the value of the Yield Stress of assumed steel, in the last case they were higher than the Yield Stress by about 25%. Additionally, such stress values were 1.65- fold higher than the highest estimated value of the surface fatigue strength and the core fatigue strength presented in Table 1" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000548_3_NgTeckChew2009.pdf-Figure3.11-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000548_3_NgTeckChew2009.pdf-Figure3.11-1.png", + "caption": "Figure 3.11: Off-hooked kinematic configuration with n links", + "texts": [ + " As there are no physical links in the virtual trailer model, the dynamics of the virtual trailer can be ignored, thus simplifying the modelling process. The design of the virtual trailer kinematic configuration for vehicle following involves selection of the optimal configuration. This is determined by two parameters - the number of virtual trailer links and the length of each link. As discussed in Section 3.3.2, the off-hooked kinematic configuration with 2-link configuration has a zero steady state error if D = L, as shown in Figure 3.8. The results from Section 3.3.2 can be generalized to a case of an n-links trailer system. Figure 3.11 shows the setup of the off-hooked kinematic configuration with n links. Through analogy, it is important for the virtual trailer number 2 to be able to follow the trajectory of virtual trailer number 1 if the length of the link D1 = L2. In general, the i-th virtual trailer will be able to follow the trajectory of the (i\u22121)-th virtual trailer if the length of the linkages is set as Di\u22121 = Li. Hence, under ideal conditions, the n-th virtual trailer should follow the trajectory of the lead vehicle" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000046_cle_download_743_255-Figure7-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000046_cle_download_743_255-Figure7-1.png", + "caption": "Figure 7: Equivalent stress at 30 s", + "texts": [ + " Therefore, the strain rate at the initial state is very small and gradually increases with the rise of temperature. At the edges around the interface, the heat flux comes from the directions that are not blocked by the thermal insulate layer, as a result, the thermal shock appears. The instant thermal stress and strain distribution in the symmetry plane of chip Q1 at 30 s are shown in Fig. 6, it can be seen obvious stress and strain concentration at the interfacial edge between wafer and Pb5Sn (denoted by E12 in follows), and SnAg3Cu0.5 and Cu (denoted by E45 in follows). Fig. 7 shows the equivalent stress distribution in materials 1, 2 and 3 near the interfacial edges. The stress concentration is found at the interfacial edge between materials 1 and 2. Fig. 8 depicts the equivalent strain distribution in materials 3, 4 and 5, and we can also see a severe strain concentration appearing at the interfacial edge between materials 4 and 5. Here the failures of solder joints are mainly concerned, it can be understood from the stress and strain distributions that the failures may occur at the interfacial edges of either E12 or E45" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.18-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000797_ING_20SZE_20LING.pdf-Figure2.18-1.png", + "caption": "Figure 2.18 Geometry of the hybrid water monopole-conical antenna [27]", + "texts": [ + " The outer radius and height of the ring antenna are 160 mm and 600 mm, respectively. The relative permittivity of distilled water is 81 and conductivity 0.0002 S/m. By changing the space between the monopole and ring antennas, the hybrid antenna can have a good impedance performance, the final simulated S11 result is shown in Figure 2.17(a). A wide impedance bandwidth from 52.5 to 162.5 MHz (102%) is achieved. If the ring antenna is replaced by conical antenna, the impedance bandwidth can be improved. The cross-section view of the antenna is shown in Figure 2.18. The final dimension of this antenna are as follows: h1 = 1000 mm, h2 = 650 mm, h3 = 15 mm, h4 = 20 mm, a = 50 mm, a2 = 131 mm, a3 = 190 mm, t = 81 mm. The simulated impedance characteristic is shown in Figure 2.17(b). It can be seen that the conical geometry adds an additional resonance. The impedance bandwidth is from 54.5 to 251.4 MHz (129%). Water antennas have been reviewed in this chapter with published papers and theoretical analysis. The literature review aimed to provide some background information on the topic of antennas, as well as to give an overview of the kind of research that has been done to date on water antennas" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001434_L1300-2011-00065.pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001434_L1300-2011-00065.pdf-Figure5-1.png", + "caption": "Figure 5. Pipe Traveler Extended & Contracted", + "texts": [ + " The load washer is then able to provide force feedback to the motor to shut it off when the desired load on the pipe is obtained. An exploded view of the assembly can be seen in Figure 4. Page 4 of 15 An extension system is incorporated into the Pipe Traveler design to allow the second set of grippers to extend to the next pipe. Also, after a pipe is released, it is necessary for the pipe traveler to retract from a pipe before it rotates to another pipe. To provide the motive force for extension and retraction, two pneumatic cylinders are used (Figure 5). Four commercial linear slides are used to provide linear stability and support the large moment during extension. The rotation mechanism operates by using a pneumatic cylinder to push a drive wheel against the pipe. The large bore cylinder is used to apply a contact force on the pipe for rotation. The drive wheel is powered with a stepper motor. When the motor is actuated, friction between the wheel and the pipe causes the wheel to drive itself around the pipe. This motion rotates the entire Pipe Traveler around the pipe until the unit is aligned with the next pipe" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002781_1_files_45689001.pdf-Figure17-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002781_1_files_45689001.pdf-Figure17-1.png", + "caption": "Figure 17: Flexure Hinge [11].", + "texts": [ + " The angle of the linkages with respect to the ground before deformation is 80 degrees [9]. The conceptual design of the compliant mechanism will be based on these parameters. To optimize the design of the compliant mechanism, optimization equations have to be applied. The main parameters that have to be kept in mind are force, stress, geometry, and deflection. The 3 equations below are used [11]. \ud835\udc58 = \ud835\udc40 \ud835\udf03 (5) \ud835\udc58 = 2\ud835\udc38\ud835\udc4f\ud835\udc612.5 9\ud835\udf0b\ud835\udc450.5 (6) \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc65 = \ud835\udc40\ud835\udc50 \ud835\udc3c (7) Where \ud835\udc58 is the stiffness in Nm/rad, b, t, and R are geometric dimensions in mm which can be seen in figure 17. M is the moment applied on the linkage, and I is the second area moment of inertia on the thin section in \ud835\udc5a\ud835\udc5a4. To maximize \ud835\udf03 equations 5-7 are used to create equation 8. \ud835\udf03 = \ud835\udf0e\ud835\udc5a\ud835\udc4e\ud835\udc659\ud835\udf0b\ud835\udc450.5\ud835\udc3c 2\ud835\udc38\ud835\udc4f\ud835\udc612.5\ud835\udc50 (8) Similarly to section 2.4, an iterative process is utilized. The geometric properties in Figure 17 will match the ones seen in Figure 4. These parameters are displayed in Table 7. 15 equations 5-8. The setup of the FEA model is found below. 16 The results of Figure 18 can be seen in Figure 19. Table 8 shows the difference between the FEA \ud835\udefe results and the mathematical \ud835\udefe results. reliable. Optimization of the geometric factor t is produced graphically. Figure 20 shows gamma with respect to t, and Figure 21 shows the force applied with respect to t. It can be seen in Figure 20 that if 15 degrees were to be achieved, the thickness of the joint has to be less than 0", + " Another difference is that the input and output load are pointing upwards in Figure 33, for the purposes of landing gear design the ideal direction would be to the right. 3 different designs were utilized where \ud835\udc45 = \ud835\udc42\ud835\udc38 \ud835\udc42\ud835\udc37 = 350 50 = 7 (10) The segment lengths for the mechanism can be found in the table below. These lengths were scaled so that the compliant mechanism could fit in the structure and not interfere with each other. main difference in these designs is changing the type of compliant mechanism that was used. So 25 far a double sided circular cutout has been used as seen in Figure 17. Single sides cutouts will be used at corner locations. 26 Figure 36 shows the boundary conditions and load that will be placed on the designs, Table 11 will summarize and display the material and compliant joint properties applied on all 3 designs. A parameter that will be tested is the \ud835\udc62\ud835\udc65 \ud835\udc62\ud835\udc66 ratio which shows how much the landing leg moves in x with respect to y. Ideally, this value would be 0 but this is not achievable. Another parameter is the \ud835\udc62\ud835\udc5c\ud835\udc62\ud835\udc61 \ud835\udc62\ud835\udc56\ud835\udc5b which shows the mechanical advantage achieved by the system" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002803_cle_download_681_563-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002803_cle_download_681_563-Figure5-1.png", + "caption": "Figure 5 \u2013 hydrostatic seals:", + "texts": [ + " Continuous design improvement for thermohydrodynamic seals allowed using combined seal assemblies in some coolant pumps, in which the last and next to the last stages are thermohydrodynamic [5]. 50 ISSN 2073-6321. \u042f\u0434\u0435\u0440\u043d\u0430 \u0442\u0430 \u0440\u0430\u0434\u0456\u0430\u0446\u0456\u0439\u043d\u0430 \u0431\u0435\u0437\u043f\u0435\u043a\u0430 4(88).2020 Under high pressure differential and rotational speed, when it is required to provide a long service life and insignificant leaks are allowed, seals with a continuous liquid film are increasingly used. They include hydrostatic seals consisting of the same components as conventional mechanical seals. To form a guaranteed gap between sealing surfaces (Figure 5, a), closed chambers 2 are made on one of them, which are connected through throttles 3 to cavity 1. Axial gap size depends on the size of throttles, chambers as well as force of springs. The throttles are a correcting member and provide selfregulation of the axial gap. When the gap decreases, pressure profile in the opening increases, and when the gap increases, the pressure decreases. To limit leaks through seals and to ensure self-regulation of the axial gap between the sealing surfaces, the throttles should have a high hydraulic resistance and therefore, are made with a very small crosssection (capillary). A significant disadvantage of capillaries is their tendency to clogging and erosion wear. In such cases, normal operation of seals is disrupted. Figure 5, b shows the design of a hydrostatic seal with a self-regulating axial gap [6], in which hydrostatic pressure from external source 1 is used to separate the operating surfaces. Water under high pressure is supplied through capillaries 3 to the cavities of chambers 4 made on fixed ring 2. a \u2013 with fixed gap; b \u2013 with regulated gap; c \u2013 with controlled leaks Axial gap size depends on water flow rate through the capillaries. The seal allows separation of the operating surfaces before shaft rotation, and also, if necessary, regulation of water supply to seal cavity changing thereby the axial gap between the operating surfaces. Disadvantages of such seal include possible damages of the external pressure support system, sensitivity to liquid contamination degree, to thermal transients and to changes in the throttle characteristics due to clogging or erosion. A hydrostatic seal with intermediate pressure extraction (Figure 5, c) [7] manufactured by Hayward Tyler (UK) is of interest. The main seal components are: ring 2, which rotates together with shaft 1; and axial component (piston) 3 installed in casing 5. An annular groove connected by channels to the intermediate chamber is made on the operating end surface of the piston. Spring 4 ensures the primary contact between ring 2 and piston 3. Seal operation principle is based on the fact that the controlled axial gap between the sealing surfaces is automatically maintained by external throttle 6" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001789_cle_download_505_375-Figure16-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001789_cle_download_505_375-Figure16-1.png", + "caption": "Figure 16. Flux density plot of improved 5 kW, 24 000 rpm motor.", + "texts": [ + "3% efficiency for 2 kW, 200 000 rpm, 5 kW, 24 000 rpm and 120 kW, 10 000 rpm rating motors, respectively. Improved torque profiles and flux density plots are generated as per the FEA results obtained with the application of Hiperco 50A material as stator core and teeth material. The torque profile and flux density plot of 2 kW, 200 000 rpm IPMSM obtained from FEA for the improved motor is presented in Figure 13 and Figure 14, respectively. The torque profile and flux density plot for the improved motor with rating 5 kW, 24 000 rpm IPMSM using Hiperco 50A material are shown in Figure 15 and Figure 16, respectively. This 5 kW, 24 000 rpm improved IPMSM has average torque of 1.99 N.m., similar to the initial design. Still, the torque profile is considerably better than that of the initially designed motor with M19 material. It can be observed that the actual flux density is close to the assumed flux density in various magnetic sections of both 2 kW and 5 kW motors. Figure 17 and Figure 18 represent the improved torque profile and flux density plot of 120 kW, 10 000 rpm IPMSM with Hiperco 50A material obtained from FEA, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001904_017_ms-8-11-2017.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001904_017_ms-8-11-2017.pdf-Figure2-1.png", + "caption": "Figure 2. Unloaded front CFRP beam.", + "texts": [ + " This can also provide better handling with a small scrub radius at relative high speed (Milliken and Milliken, 1995). The rear suspension cannot have the same level of space reduction, but the weight is reduced by component and function integration. The most common application of CFRP is weight reduction of the chassis frame and body panels while keeping the same durability. In this application, CFRP is used to create a deformable beam spring to substitute the suspension lower control arm, which is virtually divided into three sections by the bushing mounting point on the left and right (Fig. 2). During the parallel wheel travel (wheels of the same axis on both side moves in the same direction vertically), the beam deforms like a bow, functioning like a normal coil spring. When one wheel is moving vertically in the opposite direction of the other wheel (known as the opposite wheel travel) the beam deforms into an \u201cS\u201d shape, working like an anti-roll bar. To achieve the desired vehicle dynamics performance, the stiffness of the beam under parallel wheel travel and opposite wheel travel are achieved by the correct number of the ply and the stacking sequence that is used during manufacturing of CFRP beam spring", + " 5The properties used in MBD model include: elastic modulus, shear modulus, Poisson ratio and density. Stacking sequence of CFRP beam spring is designed in FEM model. ables using simple formulas, which can be modified to create DoE iterations. In order to perform the calculation for moment of inertia automatically during DoE iterations, additional scripts are necessary. Front suspension has a large slot in the center of the beam component (giving space for electric motor and other components), which is modeled as two separate beam attached with each other at the beam ending (as shown in Fig. 2). The rear beam is also divided into two separate part to achieve H-arm structure on rear suspension. In such configuration, the beam components in the model are named as: \u2013 Front suspension front beam (beam_front_nrl/nrr/nrs6_lca_front) \u2013 Front suspension rear beam (beam_front_nrl/nrr/nrs_lca_rear) \u2013 Rear suspension front beam (beam_rear_nrl/nrr/nrs7_lca_front) \u2013 Rear suspension rear beam (beam_rear_nrl/nrr/nrs_lca_rear) There are 3 different DoE scripts for this model: \u2013 Generate parameter variables \u2013 Modify beam component force calculation formula \u2013 Create target measurement reading function Nonlinear beam elements in a single beam are sharing the same geometry properties8 (thickness and width)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001401__downloads_tb09j677c-Figure3.8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001401__downloads_tb09j677c-Figure3.8-1.png", + "caption": "Figure 3.8: Modal eigencurrent distribution on bow-tie structure with 60 mm stubs for a) J1 at 1 GHz and b) J3 at 2.4 GHz. Eigencurrents are normalized to their respective maximums and have units of dBA/m.", + "texts": [ + "5 Modal significance and reflection coefficient for bow-tie antenna with no stubs and at stubs lengths of 40 mm and 60 mm. . . . . . . . 16 Figure 3.6 Characteristic attributes for the characteristic modes excited by the port and the driven reflection coefficient of the bow-tie antenna with 60 mm stubs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 Figure 3.7 Reflection coefficient displayed on smith chart for bow-tie antenna with 60 mm stubs and without stubs. Circle represents 0.5 GHz and square represents 5 GHz. . . . . . . . . . . . . . . . . . . . . . . 18 vii Figure 3.8 Modal eigencurrent distribution on bow-tie structure with 60 mm stubs for a) J1 at 1 GHz and b) J3 at 2.4 GHz. Eigencurrents are normalized to their respective maximums and have units of dBA/m. . 19 Figure 3.9 Far-field radiation pattern of CM1 and CM3 for the bow-tie and the bow-tie with stubs in a) E-plane (z-x plane) and b) H-plane (z-y plane). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 Figure 3.10 Images of a) fabricated bow-tie and b) fabricated bow-tie with stubs", + " By optimizing the dimensions of the bow-tie with stubs, the loop can be to be moved 17 closer to the center of the chart such that the reflection coefficient is less than 0.33 between the resonances. The focus of the analysis performed in this chapter was to demonstrate how characteristic modes can be manipulated rather than optimization, therefore, the optimization was not performed. The excited eigencurrents, J1 and J3, on the bow-tie structure with stubs are shown near their respective modal resonances in Fig. 3.8. Similar to the case without stubs, the half wavelength current distribution is present on J1 and the three half wavelength current distribution is present on J3. Both modes have current that flows on the stubs. For J1, the currents on each stub are self contained since they oppose each other directly on the stub. Thus cancelling out and minimizing the impact the stubs have on the first mode. For J3, current minimums still occur in the middle of the bow-tie offset from the center by 14.5 mm. However, the currents that flow in the y-direction from the two opposite phases add together as they travel along the stub" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000709_.1117_12.2307961.pdf-Figure4-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000709_.1117_12.2307961.pdf-Figure4-1.png", + "caption": "Figure 4: Camera configuration", + "texts": [], + "surrounding_texts": [ + "3.1 RSI overall configuration The Instrument features two main parts: The push-broom camera which includes the telescope and the Focal Plane Assembly (FPA) attached to the rear side of the telescope: Two Instrument Processing Units (IPU) mounted in cold redundancy inside the Bus and whose functions are to ensure the video data processing, the data compression and the telemetry/telecommand data processing (including thermal acquisition and control). 3.2 RSI Camera Telescope optical concept The camera is based on a compact Cassegrain-type telescope and a four-lenses field corrector Figure 5: Telescope optical concept Focal Length 2896 mm Pupil Diameter 600 mm F/N = 4.83 Field of View +/- 0.8\u00b0 Optical Quality WFE < 40 nm rms Figure 6: Optical Sub-assembly characteristics Silicon carbide for mirrors and structure The RSI design is based on an all-SiC opto-mechanical architecture (telescope structure, mirrors, and focal plane structural elements). This monolithic design approach, combined with the intrinsic SiC100 properties (high stiffness, low density, low thermal expansion, high thermal conductivity) allows to combine a high level of stability together with a low mass. Low mass: telescope mass ~ 60 kg, High Rigidity: first Eigen frequency >100Hz, High mechanical stability: inter mirror stability lower than 5\u03bcm, High thermo-elastic stability: quasi a-thermal configuration. Telescope structure The telescope structure is only featuring three main parts: the main plate (supporting the primary mirror), the secondary mirror support, and the rod connecting those two parts. ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-3 Telescope mirrors SiC mirrors can be light-weighted and polished with a high accuracy. Both mirrors were SiC CVD1 coated before polishing in order to minimize the roughness The Wave-front Error (WFE) was measured below 20 nm rms for each mirror, with a roughness lower than 1.0 nm rms. 1 CVD: Chemical Vapor Deposition Refocusing capability The secondary mirror is fixed on the structure by its interface flange. The primary mirror is fixed on to the structure through three iso-static invar mounts and thus thermally decoupled from the structure. Its temperature is controlled by a heater plate located between the mirror and the mounting plate. Setting different thermal control set points between the telescope structure and the primary mirror leads to a variation of the focal plane position, thanks to the low - but nonnull \u2013 thermal expansion coefficient of silicon carbide. The refocusing capability is +/- 200\u03bcm for a +/- 5\u00b0C thermal set point variation. Focal Plane Assembly (FPA) The focal plane assembly features only two CCD for the 5 required spectral bands. One CCD is dealing with the Panchromatic band and the other one is dealing with the multi-spectral bands. The separation of the entrance optical bean is ensured by an optical field separator. ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-4 A 4-line CCD for Multi-spectral bands ROCSAT2 took benefit of the pre-development performed by Atmel, under a CNES R&D contract. The TH31547 multi-spectral CCD consists of 4 photodetector lines, each line being made of 6000 photodiodes with 13\u03bcm step. The detector is operated at 5 Mpixel/s per video output. Each CCD line is coupled with a spectral band filter. The four slit filters are coated on the same glass substrate glued on the CCD. High speed video processing for the panchro- matic channel The panchromatic detection chain is based on the wellknown TH7834B detector (12000 useful 6.5 x 6.5 \u03bcm\u00b2 pixels). The challenge was to operate the four serial read-out registers at a 10 MHz pixel rate for satisfying the 308\u03bcs integration time required to achieve the 2- meter resolution. Front end electronics Each CCD is connected to a dedicated front-endelectronic board which ensures the clock driver distribution and the video signal pre-amplification. Integrated FPA ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-5 3.3 Integrated Video Processing Function The Instrument Processing Unit (IPU) is gathering the instrument electronics functions in a modular and highly integrated assembly. The IPU is coupled with the Focal Plane Assembly front-end electronics - Panchromatic Electronics Board (PEB) & Multi-spectral Electronics Boards (MEB) \u2013 and also with three Spacecraft main units: the On Board Management Unit (OBMU), the Solid State Recorder (SSR), and the Distribution & regulation Unit (DRU). Each IPU includes the necessary functions: to operate both CCD detectors - through the front end electronics located in the FPA to process the video analogue signal and to condition and to digitise all the pixel values, to compress the data flow with an improved adaptative rate regulated JPEG algorithm, to ensure the instrument thermal control. These functions are split on seven electronics boards racked in the same unit. 3.4 RSI Main Characteristics ICSO 2004 International Conference on Space Optics Toulouse, France 30 March - 2 April 2004 Proc. of SPIE Vol. 10568 105680M-6" + ] + }, + { + "image_filename": "designv8_17_0002838_f_version_1679473059-Figure21-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002838_f_version_1679473059-Figure21-1.png", + "caption": "Figure 21. Geometric models: (a) external gear and internal gear ring; (b) rack cutter and external gear.", + "texts": [ + " The method is also adopted for the tooth profiles of the rack cutter and the small segment of the tooth profile below the singular point of the conjugate tooth profile is abandoned. The modified tooth profiles of the internal gear ring and rack cutter are shown in Figure 20. The coordinates of the tooth profile solved by MATLAB\u00ae are imported into the design software SoildWorks\u00ae, the complete tooth curves are generated after mirroring and arraying, and then the 3D geometric models of the gear pair are obtained by stretching; the models assembled according to the meshing relationship are shown in Figure 21. The model of the rack cutter is built in the same way. The accuracy of the models is related to the step size of parameter x1 in the equations of the external gear\u2019s tooth profile. The smaller the step size, the more coordinates on the tooth curves, and the higher the accuracy of the models. This article has carried out a detailed investigation into the design constraints of the conjugated straight-line internal gear pair for the first time, based on the mathematical model of the gear pair. The constraints of the gear pair in the designing and machining process, such as design parameters, contact ratio, and interference, were deduced, and the influence of design parameters on the design constraints were analyzed, such as number of teeth, module, tooth profile angle, tooth thickness coefficient, addendum coefficient, etc" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002849_tation-pdf-url_69105-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002849_tation-pdf-url_69105-Figure1-1.png", + "caption": "Figure 1. Cross-sectional view of the electromechanical structure of a three-phase 18/12 switched reluctance machine.", + "texts": [ + " Since the principle of operation of SR machines does not require any permanent magnets for the production of torque, such machines offer an excellent alternative electric motor technology at this moment in time in the context of the cost and environmental impact uncertainties of permanent magnet materials [2]. Usually, the SR motor will be designed to operate from a fixed DC voltage supply, such as a battery, and the stator windings of the machine will be of the concentrated type. A typical structure of an SR electric motor or generator is shown in Figure 1. In Figure 1 the depicted machine contains 18 stator poles and 12 rotor poles; therefore this particular SR machine configuration is abbreviated as an 18/12 SR motor. Therefore, with the knowledge of these variables, we are able to compute the number of \u201csteps\u201d the rotor will make in a single revolution as it gets aligned to each of the energized stator poles, as in Eq. (1): number of rotor steps \u00bc m Nr (1) wherem is the number of phases andNr is the number of rotor poles. For the 18/ 12 configuration, Eq. (1) gives 36 steps", + " By application of the open license finite element method [5] to the magnetic analysis of the chosen SRM2 design, the aligned and the unaligned rotor positions are analyzed in terms of the magnetic flux distributions in the magnetic circuit of the device, as shown in Figures 4 and 5. Figures 4 and 5 are used to describe the fundamental theory of SR machines in terms of the phase flux-linkage. Therefore, if we consider the amount of magnetic flux \u03a6, measured in units of weber, being established in the stator pole around which the number of conductors N is wound in the concentrated manner as in Figure 1, then the flux-linkage thus created is given in Eq. (2): \u03a8 \u00bc N \u03a6 V s\u00f0 \u00de (2) where instead of the intuitive units of weber-turns, we choose to use the voltseconds (as a derived SI unit) since this unit of measurement will be very handy when we explain the significance of the flux-linkage in the SR machine analysis section. Furthermore, the phase flux-linkage computed in Eq. (2) is multiplied by the number of the coils connected in series, Ns, to obtain the total flux-linkage for that particular phase" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001352_pdf_tmm-18-e2473.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001352_pdf_tmm-18-e2473.pdf-Figure2-1.png", + "caption": "Figure 2. Bench test on kingpin.", + "texts": [ + " *Corresponding author: jtbuzzatti@hotmail.com 2/12Tecnol Metal Mater Min. 2021;18:e2473 tests in kingpins. Statistical tools were applied, adapted to the data acquisition of forces for fatigue testing. Thus, similarly to [3,13,15-18], the criteria used were: selectivity, linearity, precision, accuracy, stability, and robustness and all the forces were acquired in laboratory tests. The analysed results were obtained in kingpin fatigue tests done at LAMEF. The tests were performed on a bench test (250 kN capacity (Figure 2). The horizontal forces aimed to simulate the loads experienced by the kingpins. The force values were acquired through a force transducer (load cell), which was duly calibrated. A controller such as identification, impurities and quantitative tests of the active fraction in samples of medicaments or related components. The guide to validation and analytical quality control [14], developed by Brazilian government agencies, divides physical-chemical tests into distinct groups and categories and indicates minimum parameters that should be assessed" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000189_f_version_1689302083-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000189_f_version_1689302083-Figure2-1.png", + "caption": "Figure 2. Forces acting in a magnetic microrobot navigating within a blood vessel.", + "texts": [ + " Section 2 describes the mathematical model of a three-dimensional (3D) microrobot navigating within a cylindrical blood vessel, and path planning using a joystick device is developed. The proposed 3D observerbased state feedback control strategy is presented in Section 3. Simulation results and a comparative study that show the effectiveness of the proposed control strategy are reported in Section 4. Section 5 concludes the paper. Consider the three-dimensional (3D) motion, of a spherical microrobot of radius r and density \u03c1r, that moves within a blood vessel (Figure 2). The vector p = (x, y, z) denotes the position vector of the microrobot with x, y, and z are the coordinates of the directions of the microrobot along the~i,~j and~k axes, respectively. v = (vx, vy, vz) denotes the velocity vector with vx, vy, and vz are the microrobot velocities along the~i, ~j and~k . During the navigation in a 3D-fluid environment, the microrobot is subject to the forces depicted in Figure 2, namely the following [19]: the gravitational force Fg, the electrostatic force Fel , the contact force Fc, the Van der Waals force Fvdw, the hydrodynamic force Fd and the actuation magnetic force Fm. Most studies on the control of a microrobot have been conducted under the assumption that the microrobot navigates in the middle of the blood vessel [20,21]. In this case, it is assumed that the forces Fel , Fc and Fvdw are negligible compared to Fd and Fg forces, and, consequently, their effects are insignificant and can be neglected" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0002084_010.5__63975-1___pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0002084_010.5__63975-1___pdf-Figure5-1.png", + "caption": "FIGURE 5. (a) OVERALL VIEW OF THE CUTTING FILE MACHINE; (b) SCHEMATIC REPRESENTATION OF THE CORRESPONDING MECHANICAL SYSTEM.", + "texts": [ + " Thus, the normal and tangential impact laws can be stated as two inclusions ( )d UprPNi Ni\u03be\u2212 \u2208 (34) ( )d d SgnP PTi i Ni Ti\u03bc \u03be\u2212 \u2208 (35) Finally, the complete description of the dynamics of nonsmooth system, which accounts for both impact and impact-free phases, is given by Eqs. (27)-(35). This problem can be solved by using the Moreau time-stepping method (Flores et al., 20101). In this section, a cam-follower mechanism applied in an industrial machine is used as a demonstrative application example of the nonsmooth dynamics approach. Figure 5 shows the overall view and the schematic representation of this machine-tool. The file teeth are produced by impact of the cutting beater (system composed by follower, cylinder and chisel), with a reciprocate movement. To generate this movement, the cutting bench has a wheel with six rebounds (cam) whose rotation forces the pin to move up. This will lift up the cylinder, to which the chisel is attached, which immediately falls down, when reaching the up-dead-point, impelled by the spring and its own weight (Flores, 2009)" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004599_(5)_2017_549-562.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004599_(5)_2017_549-562.pdf-Figure13-1.png", + "caption": "Figure 13. Degenerationofgeometrydue tounsuitedparameter constellations.", + "texts": [ + " As soon as an error occurs, all dependent geometric features are inactivated automatically. By this, the user receives a direct graphical and logical response of the current parameter constellation in the model. The following example should demonstrate the behavior: In conceptual development proportional models are used to analyze spatial requirements. These models are controlled by parameters. As such models can get quire complex the update behavior cannot be predicted for every parameter constellation, especiallywhenusing geometric features like trims. Therefore, Fig. 13 shows an exterior proportional model with continuously decreasing chassis width (W116). If the value for the chassis width is getting too small, the required trims would cause an update error when using the regular update function of the used CAD system. Experienced users wouldmaybe able to activate/inactivate the propermodel areas on their own, whereas unexperienced users or such which do not use the dataset every day might not. In this case the parameterization framework is inactivating automatically all dependent geometric areas and also checks linked datasets if the geometric stability could be ensured" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000608_f_version_1542789923-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000608_f_version_1542789923-Figure2-1.png", + "caption": "Figure 2. (a) simple positioning system that utilizes a GT-type belt to drive the table and (b) its representative dynamic model.", + "texts": [ + " It has been shown that the effective stiffness of the length-changing belts can be directly calculated as a function of the nominal stiffness value, the belt width, and the real-time length of the belt [10] such that: ki(t) = Csp b Li(t) (1) where ki is the effective stiffness as a function of time, Csp is the nominal stiffness, b is the belt width, and Li(t) is the length of the belt section at time t. For any case where the length remains constant, the effective and nominal stiffnesses are equal since the value of Li(t) is a constant. Note that the value of Csp may be a constant or function of material properties for different belt materials; it cannot be considered a function of time the way that the length of the belt is. The most commonly-used GT-style belt is the GT-2; Figure 1 shows the fundamental geometry and specifications for this type of belt. Figure 2 shows a common application, where a GT-style belt is used to transfer motion from a stepper motor to drive a linear positioning system. Also shown is a 2D dynamic model representation of such a system (Figure 2b), where the differences in effective stiffness, based on belt length, in the belt sections are clearly evident. The sections L1 and L2 change in effective stiffness as a function of time, while section L3 stays constant during use [11,12] so the effective and nominal stiffnesses are equal. The work described in this note explored the nominal stiffness Csp and the best way to model it in dynamic systems where belt length is not constant. Several previous studies have assumed that rubber-based timing belts have a linear nominal stiffness [5,11\u201318]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001672_nu_140_01_011010.pdf-Figure13-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001672_nu_140_01_011010.pdf-Figure13-1.png", + "caption": "Fig. 13 A modified fiber stamping unit concept to improve the FTEs of the printer outlined in Refs. [1] and [2]", + "texts": [ + "org/m anufacturingscience/article-pdf/140/1/011010/6405745/m anu_140_01_011010.pdf by guest on 20 D ecem ber 2024 the yield stress, which correlates with a drop in the FTE in Fig. 12. It should be noted here that the model predictions in Fig. 10(b) assume that the cohesive zone parameters are independent of the tangential velocity. However, even under this assumption, the use of the model-predicted peak stress in the fibers as a measure of the fiber transfer efficiency appears to be valid (Fig. 12). 4.4 Possible Implementation Strategy on 3D Printing Platform. Figure 13 shows one possible translation of the findings from Secs. 4.2 and 4.3 into a fiber stamping unit design concept for the FrSC 3D printer [1,2]. The realization of this concept would involve assembling the carrier substrates onto a feed reel. The carrier substrates would then travel over a stamping roller (0.25 in radius) as the 3D-printed part translates at a speed equal to the tangential velocity of the roller. A take-up reel would then collect the empty carrier substrates. Such an implementation is expected to improve the fiber transfer efficiency encountered during the stamping step for the FrSC 3D printer [1,2]" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003281_om_article_22266_pdf-Figure5-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003281_om_article_22266_pdf-Figure5-1.png", + "caption": "Fig. 5. The first five constrained modes of the stator system", + "texts": [ + " The electromagnetic vibration noise of PMSM is determined by the radial electromagnetic force wave acting on the stator structure and the radial modes of the stator structure. In this paper, the vibration and noise of the motor are carried out on the bench, so the six degrees of freedom of the cross-section bolt holes are constrained according to the actual constraints to simulate the motor installation state, as shown in Fig. 4. Add boundary conditions to simulate the constrained modes of the motor. This article lists the first five radial modes and frequencies of the stator system, which are shown in Fig. 5. The left is the vibration mode of the stator system, and the right is the vibration mode of the stator core. 1192 JOURNAL OF VIBROENGINEERING. SEPTEMBER 2022, VOLUME 24, ISSUE 6 The main radial electromagnetic force frequency of the motor is an even multiple of the current frequency. As can be seen from Fig. 6, when the excitation frequency is close to the modal frequency of the stator system, it will cause the stator system to resonate, especially in 960 Hz and 1280 Hz, the stator modal frequencies are dense, which are easy to cause the resonance of stator system" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0004713_2_7_2_ajme-2-7-2.pdf-Figure8-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0004713_2_7_2_ajme-2-7-2.pdf-Figure8-1.png", + "caption": "Figure 8. Von Misses stress distribution", + "texts": [ + " The loading corresponding to the double scroll weight of the sheet coil, was applied by the form of pressure having effect on the upper panel. The whole arm is made of the St430C material (steel class EN 10025 S275JO). Maximum of calculated von Misses stress can by 275MPa 239MPa, 1,15 eh yd M R f (19) whereas ehR is the yield stress, M is the coefficient of material reliability [4]. When calculating, the material was considered as isotropic and linear elastic, with elastic constants: Young module 210000MPaE , Poisson ratio 0,3 . Values of the Von Misses stress are displayed in Figure 7 and in Figure 8. The maximal stress value is 95MPa . The behaviour of Von Misses stress on the back part of the operating machine\u2019s arm is presented in Figure 8. From the functional point of view, it is necessary not to have large deformations of the operation machines arm, because it would cause the downslide of the sheet metal coil from the arm [2]. In Figure 9, there is portrayed the distribution of the arm resultant displacements. The largest displacement is 1,62mm at the place of free end of the arm. In this paper, an example of stress analysis using finite element method of a in an industrial operating machine has been described. The method principle as well as the solution results have been provided" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000558_al-01025785_document-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000558_al-01025785_document-Figure1-1.png", + "caption": "Figure 1: Assumed model of the robot", + "texts": [], + "surrounding_texts": [ + "\u2022 vwheels - wheels angular velocity \u2022 R - reaction forces (impulsions) in lagrangian (global) coordinates \u2022 \u03bbN (\u03bbn\u0304) - normal component of the contact force (impulsion) in local coordinates \u2022 \u03bbTx (\u03bbt\u0304) - tangential component of the contact force (impulsion) in local coordinates in the x direc- tion \u2022 \u03bbTz (\u03bbs\u0304) - tangential component of the contact force (impulsion) in local coordinates in the z direction \u2022 yN (yn\u0304) - gap function (distance between contact point and the constraint function) \u2022 y\u0307N (y\u0307n\u0304) - normal component of the local contact velocity \u2022 y\u0307Tx (y\u0307t\u0304) - tangential component x of the local contact velocity \u2022 y\u0307Tz (y\u0307s\u0304) - tangential component z of the local contact velocity For each scenario a subset of the above quantities has been plotted. RT n\u00b0 448" + ] + }, + { + "image_filename": "designv8_17_0001070_f_version_1687313919-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001070_f_version_1687313919-Figure1-1.png", + "caption": "Figure 1. The phase trajectory of the system.", + "texts": [ + " By Lemma 1, it can be confirmed that the states of the system will converge to the sliding surface s = 0 within finite time. Then, we consider the case that x2i = 0. Substituting (17) into (3), we have x\u03072 =\u2212 (C0q\u0307 + G0)\u2212M0 ( M2s + (\u03c1 + M1) s \u2016s\u2016 \u2212M\u22121 0 (C0x2 + G0)+ \u039b\u22121 2 \u0393\u22121 2 (In + \u039b1\u03931 diag(|x1|\u03931\u2212In)) sign2In\u2212\u03932(x2) ) + d(t, x) =\u2212M2s\u2212M1 s \u2016s\u2016 + \u03c1 s \u2016s\u2016 + d(t, x) \u2264\u2212M2s\u2212M1 s \u2016s\u2016 which suggests that x\u03072i < \u2212M1 and x\u03072i > M1 for the cases si > 0 and si < 0, respectively. This indicates that the states of the system will not remain at the points x2i = 0. It is shown in Figure 1 that the controller will drive the states to the sliding surface s = 0 when x2 = 0. Remark 1. Both NFTSM and conventional TSM share a nonlinear term of tracking error to achieve fast convergence when the states are far from the origin. However, the convergence rate changes slowly when the system approaches the sliding surface. Unlike TSM, a linear term of x1 is introduced into the sliding surface to ensure a fast rate while approaching the nearby origin. See [15,16] for more details on how the states converge to zero when the sliding surface is reached" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001211_3-540-40899-4_97.pdf-Figure2-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001211_3-540-40899-4_97.pdf-Figure2-1.png", + "caption": "Fig. 2. Current Prototype", + "texts": [ + " If the rods can endure both expansion and contraction, 2 rods are necessary for 2 rotational motion and sufficient unless the lever and rods are in same plane. If the rods can endure only expansion, 3 rods are necessary and sufficient unless any 3 of the rods and the lever are in same plane. The latter case is more practical because a long rod cannot endure high pressure. If wires are used for the rods, the pivots are not necessary. Actually, our prototype has 4 wires in order to avoid confliction. (See Fig. 2(b).) In Fig. 1, the rods are outside of the lever. In this case, the rotation range around z-axis is limited by the conflict between rods and gimbal. Therefore, our prototype has rods inside the lever as shown in Fig. 2(b). Remote Actuation Any electromagnetic actuator and a magnetic metal must not enter the neighborhood MR gantry. As for a fluid motor, actuation is free from magnet and electricity but its control system consists of magnetic valves. Even An ultrasonic motor, which doesn\u2019t include any magnetic body, makes noise to MR image, while working if it\u2019s close to MR imaging area. So the remote actuation is currently the best solution for MR manipulator, and LPM is one of the remote actuation mechanisms. Mechanical Safety A serial link manipulator, which is widely used in factories, has potential danger of conflict between elbow joint and surgeon", + " The inclination of the output is limited by the limit angle of pivot, universal joints, and by conflict between the lever and rods. The translational displacement along the lever is restricted by the sliding range of sliding and rotating pair. The translational workspace changes according to the ratio of the output lever length to input lever length. So, allowable input must be analyzed at the time of design. We made a prototype of LPM manipulator for so-called double doughnut type of open MRI (See Fig. 2(a)). The purpose of this prototype is to make clear mechanical problems. So this prototype is not MR compatible but all components are designed to be exchangeable with MR compatible components. The reasons are that MR compatibility of mechatronics is studied in another paper (second topic), and that MR compatible components are very expensive. For example, titanium has good MR compatibility and biocompatibility but costs very much. For the same reason, the back drivability of manipulator is not implemented to the current prototype. The manipulator, which drives the input of LPM, is decided to fixed-linear parallel mechanism (FLP) [8]. The FLP is one of parallel mechanisms, has 6 linear actuators fixed on the base, and has 6 middle-links, which connect between the endplate and actuators in parallel (See Fig. 2(a)). FLP has good property of remote actuation because its actuators always stay in the same positions distant from MR gantry. FLP has demerit that it has narrow workspace especially in orientation but parallelepiped mechanism also has narrow workspace in orientation. So this demerit is not bottleneck of workspace. Those are why FLP is used. Kinematic parameters are decided by conventional Monte-Carlo method to meet the workspace of \u00b1100[mm] in x-, y-, z-axes, and \u00b130[deg.] around x-, y-, z-axes" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000378_29_9786099603629.pdf-Figure11.6-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000378_29_9786099603629.pdf-Figure11.6-1.png", + "caption": "Fig. 11.6. Example of the unstable frequency (STFT of enfine block vibration, axis \u2013 time window 0.25 s, resolution 0.4884 Hz)", + "texts": [ + " The received signal is strongly interfered by various vibration sources and that is why there is a necessity to use advanced methods of signal selection and observation in time-frequency domains. The TFR of the signals propagated in three orthogonal axes is presented in Fig. 11.5. It shows the complex structure of vibration of motor engine. The transformations of the vibration signal into time-frequency representation enables analyzing of energy of vibration carrying by the defined frequency. Thus the periodic unstable of frequencies can be observed (Fig. 11.6). 114 JVE INTERNATIONAL LTD. JVE BOOK SERIES ON VIBROENGINEERING. ISSN 2351-5260 To consider motor engine as vibration generator in vehicle investigation on influence of operating parameters and conditions of combustion engine were conducted. As most important condition of working engine the rotational speed expressed as revolutions per minute (rpm) was assumed. The results of the investigation are presented in Fig. 11.7-11.9 as collection of charts presenting time and frequency functions of vibration generated for increasing rpm of engine" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0001917_f_version_1484053212-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0001917_f_version_1484053212-Figure1-1.png", + "caption": "Figure 1. Prototype of the five-degrees-of-freedom (5-DOF) AC hybrid magnetic bearings (HMB)-supported motorized spindle.", + "texts": [ + " In addition, the regulation times and real-time performances are comparable to the disturbance response experiment\u2019s results based on the \u201cswitching model\u201d. Moreover, the results of the stiffness tests show that the proposed full prediction model can provide a control system for the most suitable mathematical models of the suspension force, which is the closest to the actual condition model. Therefore, the effectiveness of the \u201cfull prediction model\u201d applied to the control system can be verified by referring to the results of the performance test experiments under different operating stages. Figure 1 shows the prototype and its exploded view of machinery parts of the 5-DOF AC HMB-supported motorized spindle. The AC 2-DOF HMB and AC\u2013DC 3-DOF HMB models are responsible for supporting the shaft, as shown in Figures 2 and 3. Energies 2017, 10, 75 2 of 17 and mature classical control technologies [17]. Although these two magnetic bearing models are highly reliable, not all model generations have been applied to the 5-DOF motorized spindle. Therefore, several new model generations are greatly anticipated in order to determine the most suit ble an accurate motorized spindle model for a given working condition" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000560_onf_pt2020_01005.pdf-Figure10-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000560_onf_pt2020_01005.pdf-Figure10-1.png", + "caption": "Fig. 10. The characteristic solution of single-stage gear reducer with both horizontal and vertical arrangement of the shafts (Rossi solution) [17].", + "texts": [ + " It is interesting to note that some manufacturers assemble single-stage gear reducers in the housings for two-stage gear units (cylindrical-bevel gear reducers) to increase the series of housing and thereby reduce production costs (Fig. 9 and 10). In order to increase the versatility of their gear reducers, some manufacturers produce the housings with feet on all four sidewise surfaces. In this way, the gearbox can be mounted with horizontal shaft arrangement, but also in vertical shaft arrangement. The additional opening is added through which the gears are mounted and it is closed by a cover. In order to increase the versatility of this gearbox, an additional flange is created on the front surfaces of the housing (Fig. 10). Single-stage universal gear reducers with vertical shaft arrangement are today more common in practice. They are produced with a different way of connecting: foot-mounted gearbox (Fig. 11a), flange-mounted gearbox (Fig. 11b) and foot and flange-mounted gearbox (Fig. 12). Gear reducers with vertical shaft arrangement have a simpler machining processing, but assembling is a bit complicated. Some manufacturers that produce gear reducers in small series, practice using an universal housing with feet or flange connected by screws", + " Using special mounts this position can be adapted to different positions and ways of mounting (Fig. 20), but these solutions are somewhat expensive than usual footmounted or flange-mounted solutions. * Corresponding author: racmil@uns.ac.rs Based on the performed design solutions of single-stage gear reducers produced by leading manufacturers of gear units, it can be concluded that further intensive development of all types of these reducers can be expected. Gear reducer with horizontal shaft arrangement, with the housings with feet on all four sidewise surfaces and with connected flanges (Fig. 10 and 15) presents the most universal gear reducer. This type of reducer is adapted for all positions and ways of mounting, but at the same time, it is the most expensive due to extensive machine processing and the largest consumption of materials. Therefore, their intensive development could not be expected further, but they will be produced by an only small number of manufacturers to satisfy operating requirements. Gear reducers with vertical shaft arrangement footmounted (Fig. 21), flange-mounted (Fig" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003376_ticles_srep06756.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003376_ticles_srep06756.pdf-Figure1-1.png", + "caption": "Figure 1 | Concept design and coordinate systems. Twenty four coils are mounted on the stator and symmetrically distributed along the equator. The PM poles are arranged on two rotor surfaces. The inner and outer rotors are fixed together through the L-shaped links. In other words, the magnets are", + "texts": [ + " The concept design and poles arrangement of the spherical actuators with 3D magnet array is presented. The magnetic field distribution is then analyzed numerically. A novel distribution of Hall-effect sensors is presented to measure flux density around the rotor. The result is compared with the analytical flux model, and thus to obtain the rotor orientation. Experiments are conducted on research prototype to validate the proposed measurement method. The proposed method could be implemented into other spherical actuators with different pole patterns. Figure 1 shows the schematic structure of permanent magnet spherical actuator with 3D magnet array. Two Cartesian coordinate systems, XYZ and xyz, are attached on stator and rotor, respectively. They are coincident with each other at the initial position. The motion of rotor can be separated into two steps: 1) the rotor shaft is moved to coincide with desired vector; 2) the rotor rotates about the vector. In this paper, the rotation sequence of the rotor is presented as follows. . Firstly, frame {xyz} rotates about x-axis by an angle of a, and is transformed into frame {x1y1z1}", + " SCIENTIFIC REPORTS | 4 : 6756 | DOI: 10.1038/srep06756 4 Sensor7 : r 1 0 0\u00bd T , Sensor8 : r 0 1 0\u00bd T : \u00f08\u00de The analytical expression of the rotor orientation thus becomes y~21sgn Vij j{ Vj ffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffi ln 0:159K Vl r y[ { p 4 , p 4 , c~ 1 4 arccos V7 0:159K c[ 0, p 4 : \u00f09\u00de where y 5 a when i 5 5,j 5 6,l 5 8, and y 5 b when i 5 3,j 5 4,l 5 7.Experiments are also conducted on the orientation measurement for spherical actuators with 2D magnet array. The outer rotor in Figure 1 is removed from the system, i.e., the magnet poles are arranged in 2D surface. By using the same approach, the analytical solution of rotor orientation is expressed as y~24sgn Vij j{ Vj ffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffi ln 0:05K Vl r y[ { p 4 , p 4 , c~ 1 4 arccos V7 0:05K c[ 0, p 4 : \u00f010\u00de The actual rotation angles are compared with those computed from analytical equations with the experimental sensor datum. Figure 5 shows the comparison of a about x-axis, b about y-axis, and c about z-axis in 3D and 2D magnet array, respectively" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0003938_O201525961722111.pdf-Figure1-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0003938_O201525961722111.pdf-Figure1-1.png", + "caption": "Fig. 1. The reflector ring-slot patch antenna with reflector and design parameters: (a) top; (b) side.", + "texts": [ + "kr) Received: December 31, 2014; Accepted: March 13, 2015 http://www.jeet.or.kr \u2502 1781 2 4r t t rP PG G R \u03bb \u03c0 \u239b \u239e= \u239c \u239f \u239d \u23a0 (1) where, Pr is received power, Pt is transmitted power, G1 is transmitted antenna gain, Gr is received antenna gain, R is distance between transmitted and received antenna. Therefore, the received antenna with a high gain is a key factor to high received power. One of the ways to enhance the gain of the planar radiating element is to let the field interfere with each other. To do this, we suggest the geometry as in Fig. 1. It is composed of the ring-slot antenna backed by a reflector such as Fig. 1 (b). The ring-slot patch antenna is operated in TM11 mode. Thus the circumference of the ring is the half wavelength of the operating frequency. Complying with the need to reduce the size of antenna, we insert slits as shown in Fig. 1 (a) to make the effective length of the current path along the ring increase. As an additional design element, the patch corners are cut to create a circular polarization for better reception of energy in an arbitrary angle position [12]. This circular polarized field is radiated forward and backward together. The backward wave hits the reflector and is reflected into the forward direction. With the distance between the radiating element and the reflector, the characteristics of the interference between the forward and reflected field change and can lower the gain" + ], + "surrounding_texts": [] + }, + { + "image_filename": "designv8_17_0000859_914r47t_fulltext.pdf-Figure25-1.png", + "original_path": "designv8-17/openalex_figure/designv8_17_0000859_914r47t_fulltext.pdf-Figure25-1.png", + "caption": "Figure 25: The transmission systems about both axes; pulley and timing belts [131].", + "texts": [ + " 40 Figure 22: The robotic force-plate, load cells and sensing mechanism (TOP: experimental prototype; BOTTOM: CAD drawing). The load cells (1); acrylic plate (2); aluminum plate (3); metal crossbar (4); aluminum beams (5); the linear spring to create a preload (6)..................................... 41 Figure 23: Torque calculation of the subject\u2019s foot on the footplate along the DFPF axis [131]. .............. 42 Figure 24: Torque calculation of the patient foot on the footplate along the INEV axis [131] .................. 43 Figure 25: The transmission systems along both axes; the pulley and timing belts are shown [131]. ........................................................................................................................................................... 46 Figure 26: The linear motor controllers by Copley Controls ...................................................................... 48 Figure 27: The block diagram of the Xenus servo amplifier in torque control mode. ................................ 49 Figure 28: The real-time machine is in continuous communication with the robotic footplate to read the sensors and drive motors", + " The process of machining/fabricating these parts was done with high accuracy, within one-thousandth of an inch (0.001\u201d) to ensure proper alignment. The internal footplate must have been perfectly square to prevent contact with the support frame during rotation. In order to increase the system stability and also measure the applied force on the footplate, the internal layer is built of five different components: an acrylic plate, an aluminum plate, load cells, metal crossbars and aluminum beams as shown in Figure 25. The patient\u2019s foot is strapped on the 41 acrylic plate. Acrylic was chosen because it is significantly lighter than aluminum and provides a relatively high rigidity. The aluminum plate was attached to the acrylic plate to support and strengthen the footplate and ensure minimal deflection. Four load cells (53CR from Honeywell Inc., Morristown, NJ) were inserted symmetrically in the four corners of the footplate, in between the aluminum plate and the two metal crossbars. The metal crossbars are connected to the surrounding aluminum beams" + ], + "surrounding_texts": [] + } +] \ No newline at end of file