The International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences
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Articles | Volume XLII-3/W1
Int. Arch. Photogramm. Remote Sens. Spatial Inf. Sci., XLII-3/W1, 35–39, 2017
https://doi.org/10.5194/isprs-archives-XLII-3-W1-35-2017
Int. Arch. Photogramm. Remote Sens. Spatial Inf. Sci., XLII-3/W1, 35–39, 2017
https://doi.org/10.5194/isprs-archives-XLII-3-W1-35-2017

  25 Jul 2017

25 Jul 2017

MISSION PROFILE AND DESIGN CHALLENGES FOR MARS LANDING EXPLORATION

J. Dong, Z. Sun, W. Rao, Y. Jia, L. Meng, C. Wang, and B. Chen J. Dong et al.
  • Beijing Institute of Spacecraft System Engineering, Beijing, China

Keywords: Mars, Exploration, Landing, Parachute, Validation

Abstract. An orbiter and a descent module will be delivered to Mars in the Chinese first Mars exploration mission. The descent module is composed of a landing platform and a rover. The module will be released into the atmosphere by the orbiter and make a controlled landing on Martian surface. After landing, the rover will egress from the platform to start its science mission. The rover payloads mainly include the subsurface radar, terrain camera, multispectral camera, magnetometer, anemometer to achieve the scientific investigation of the terrain, soil characteristics, material composition, magnetic field, atmosphere, etc. The landing process is divided into three phases (entry phase, parachute descent phase and powered descent phase), which are full of risks. There exit lots of indefinite parameters and design constrain to affect the selection of the landing sites and phase switch (mortaring the parachute, separating the heat shield and cutting off the parachute). A number of new technologies (disk-gap-band parachute, guidance and navigation, etc.) need to be developed. Mars and Earth have gravity and atmosphere conditions that are significantly different from one another. Meaningful environmental conditions cannot be recreated terrestrially on earth. A full-scale flight validation on earth is difficult. Therefore the end-to-end simulation and some critical subsystem test must be considered instead. The challenges above and the corresponding design solutions are introduced in this paper, which can provide reference for the Mars exploration mission.