Abstract:

Flight scheme utilizing the remaining propellant of the reentry test of China lunar exploration is investigated in this article. First, according to the trajectory and satellite status at the end of the reentry mission, the feasible flight goals are analyzed. Consequently, the flight scheme is designed with the flight goal of collinear libration points in the sun-earth/moon and the earth-moon systems. Second, for the requirements of trajectory design and control in the scheme, the methods of direct orbit transfer and orbit entry to libration point and orbit transfer between different libration points are investigated. Compared with the present method of trajectory design based on the invariant manifold, these methods need no or less calculation of manifolds and have a simpler calculation procedure. Therefore, the methods can greatly decrease the calculation burden, and are suitable to the actual flight mission. Finally, the trajectory and control plan are designed for the flight scheme based on the above methods. Furthermore, the corresponding TT&C condition is analyzed for all maneuvers. This research shows that some innovative and valuable flight tests can be performed and testified in the sun-earth/moon space by use of the remaining propellant of the reentry test mission, which are significant to accumulate valuable TT&C technique and experience for the future ‘Kuafu’ mission, lunar missions, and some other deep space exploration of China. Additionally, this research is especially beneficial and applicable to a future multi-mission instance in the deep space exploration.

Key words: Reentry test, Lunar exploration, Flight scheme, Trajectory design, Libration point