rover_name,mass_total_kg,wheel_radius_m,wheel_width_m,n_wheels,chassis_mass_kg,solar_area_m2,battery_capacity_wh,avionics_power_w,grouser_height_m,grouser_count,payload_mass_kg,in_class,citation,imputation_notes
Rashid,10.0,0.10,0.08,4,2.0,0.4,50.0,10.0,0.015,14,1.5,true,"Hurrell et al. 2025 Space Science Reviews 221:37; Els et al. LPSC 2021 #1905; MBRSC Emirates Lunar Mission materials","wheel_width, grouser_height_m, and grouser_count updated to Hurrell et al. 2025 flight-wheel values; chassis is structural-only (35%-of-m_total ROT bucket minus the science payload); battery + avionics scaled from mass class. payload_mass_kg ~ 1.5 kg = 4 cameras + microscopic imager + Langmuir probe per Emirates Lunar Mission (Rashid) instrument list (schema v9: payload is a separate mission requirement, no longer folded into chassis)"
Sojourner,10.6,0.065,0.08,6,2.0,0.22,40.0,10.0,0.010,12,1.5,true,"Wilcox & Nguyen 1998; NASA Mars Pathfinder / Sojourner rover mission materials","chassis structural-only ~ 33%-of-m_total per Wilcox & Nguyen 1998 minus payload; grouser_count estimated at 12; Mars rover used as lunar-micro proxy (gravity correction pending real-rover validation). payload_mass_kg ~ 1.5 kg = APXS (~0.55 kg) + 3 cameras + electronics"
CADRE-unit,2.0,0.08,0.04,4,0.5,0.1,10.0,5.0,0.0,0,0.3,false,"Rothenbuchner et al. 2023 IEEE Aerospace #2300; NASA/JPL CADRE project materials","In the design-space class after the 2026-05-27 schema floor widening (chassis 0.5 kg / torque 0.05 Nm / battery 5 Wh), but OUT of the bottom-up mass model's calibration regime — MassModelParams specific-mass constants are calibrated to 5-50 kg micro-rovers, and at 2 kg the fixed-cost terms (4 x motor_base 0.15 kg + avionics_base 0.3 kg + ...) over-predict total mass by ~100%. Specs per Rothenbuchner 2023 IEEE Aerospace + NASA/JPL CADRE press. chassis structural-only ~ 40%-of-m_total ROT minus payload; no grousers (smooth wire-spoke rims). payload_mass_kg ~ 0.3 kg = stereo-camera + small comms-ranging payload"
Resilience-Tenacious,5.0,0.06,0.04,4,1.7,0.15,25.0,8.0,0.005,12,0.3,true,"ispace HAKUTO-R Mission 2 mission overview and press materials; ispace Mission 2 updates","In-class after the 2026-05-27 ultra-micro floor widening. Specs per iSpace HAKUTO-R M2 mission overview; chassis structural-only ~ 40%-of-m_total ROT minus payload; small grousers visible in iSpace press imagery. payload_mass_kg ~ 0.3 kg = HD camera payload"
ExoMy,8.0,0.055,0.06,6,3.0,0.10,30.0,10.0,0.008,12,0.0,true,"ESA ExoMy open-hardware documentation","Earth educational rover; chassis = 37.5% of m_total; specs approximate per ESA ExoMy docs. payload_mass_kg = 0 (educational platform, no dedicated science instrument)"
Pragyan,26.0,0.085,0.07,6,6.5,0.5,60.0,20.0,0.008,12,3.5,true,"ISRO Chandrayaan-3 press materials; Chandrayaan-3 Pragyan instrument-suite materials","wheel_width, solar_area, battery, avionics all scaled from class and mission duration (6 lunar hours); chassis structural-only ~ 38%-of-m_total ROT minus payload. payload_mass_kg ~ 3.5 kg = APXS + LIBS spectrometers per Chandrayaan-3 Pragyan instrument suite"
Yutu-2,135.0,0.15,0.15,6,45.0,1.3,130.0,40.0,0.0,0,25.0,false,"Di et al. 2020 Icarus; Ding et al. 2022 Acta Astronautica; Chang'e-4 / Yutu-2 payload manifest","out-of-class (medium, >50 kg ceiling); chassis structural-only = published-derived bucket minus the ~25 kg science payload. payload_mass_kg ~ 25 kg = Lunar Penetrating Radar + VNIS + APXS + panoramic/navigation cameras per Chang'e-4 Yutu-2 payload manifest; solar deployable 2-wing"
MARSOKHOD-proto,70.0,0.17,0.13,6,24.0,0.5,100.0,30.0,0.015,12,8.0,false,"Kemurjian et al. 1993","out-of-class (medium); chassis structural-only ~ 46%-of-m_total ROT minus payload; specs per Kemurjian et al. 1993. payload_mass_kg ~ 8 kg = instrument mast + manipulator/sampling proto payload"