Preliminary orbit design for a Mars sample return mission

Abstract

Mars sample return missions are the focus of international deep space exploration planning in recent years. In this paper, the orbit design of the different flight phases of a Mars sample return mission is studied with consideration of practical engineering constraints, using 2028 launch opportunity as an example; based on comparative analysis of different schemes, feasible orbit designs are recommended for future Mars sample return missions. Preliminary analysis and design of the mission orbit are carried out and the analysis results of the main flight phases are provided in the paper, and the discussion focuses on launch opportunity, Earth to Mars transfer, Mars orbit insertion, rendezvous and docking in Mars orbit, and Mars to Earth transfer. It is shown in the paper that the launch opportunities for Mars sample return missions emerge every two years, and the launch windows in 2028 opportunity concentrate in the November; considering the high risk of the research and development of heavy lift rockets, the scheme that the descent and ascent module, the orbiter and reentry module are launched separately using two available rockets is recommended; the Mars to Earth return opportunities emerge about every two years, and the return windows open about two years after the Earth departure.