| { | |
| "id": "AIDAA11", | |
| "url": "https://www.bmtdynamics.org/cgi-bin/display.pl?name=AIDAA11", | |
| "title": "High Order Optimal Feedback Control of Lunar Landing and Rendezvous Trajectories", | |
| "pdfs": [ | |
| { | |
| "url": "https://www.bmtdynamics.org/pub/papers/AIDAA11/AIDAA11.pdf", | |
| "filename": "AIDAA11.pdf", | |
| "size_bytes": null | |
| } | |
| ], | |
| "page_text": "Publications\nReprint Server\nHigh Order Optimal Feedback Control of Lunar Landing and Rendezvous Trajectories\nAbstract\nOptimal feedback control is classically based on\r\nlinear approximations, whose accuracy drops off\r\nrapidly in highly nonlinear dynamics. A high\r\norder optimal control strategy is proposed in this\r\nwork, based on the use of differential algebraic\r\ntechniques. In the frame of orbital mechanics,\r\ndifferential algebra allows the dependency of the\r\nspacecraft state on initial conditions and\r\nenvironmental parameters to be represented by high\r\norder Taylor polynomials. The resulting polynomials\r\ncan be manipulated to obtain the high order\r\nexpansion of the solution of two-point boundary\r\nvalue problems. Based on the reduction of\r\nthe optimal control problem to an equivalent two-point\r\nboundary value problem, differential algebra\r\nis used in this work to compute the high order\r\nexpansion of the solution of the optimal control\r\nproblem about a reference trajectory. New optimal\r\ncontrol laws for displaced initial states are\r\nthen obtained by the mere evaluation of polynomials.\nP. Di Lizia, R. Armellin, F. Bernelli-Zazzera, M. Berz,\nin:\nCEAS 2011 The International Conference of the European Aerospace Societies\n, (2011)\nDownload\nClick on the icon to download the corresponding file.\nDownload Adobe PDF version (500055 Bytes).\nGo Back\nto the reprint server.\nGo Back\nto the home page.\nThis page is maintained by\nKyoko Makino\n. Please contact her if there are any problems with it." | |
| } |