Trajectory design for the Moon departure libration point mission in full ephemeris model  

作　　者：CHEN Yang BAOYIN HeXi LI JunFeng 

机构地区：[1]School of Aerospace, Tsinghua University, Beijing 100084, China

出　　处：《Science China(Technological Sciences)》2011年第11期2924-2934,共11页中国科学（技术科学英文版）

基　　金：supported by the National Natural Science Foundation of China (Grant Nos. 10832004 and 11072122)

摘　　要：The lunar probe may still have some remaining fuel after completing its predefined Moon exploration mission and is able to carry out some additional scientific or technological tasks after escaping from the Moon orbit.The Moon departure mission for the lunar probe is the focus of this paper.The possibility of the spacecraft orbiting the Moon to escape the Moon's gravitational pull is analyzed.The trajectory design for the Earth-Moon system libration point mission is studied in a full ephemeris dynamical model,which considers the non-uniform motion of the Moon around the Earth,the gravity of the Sun and planets and the finite thrust of the onboard engine.By applying the Particle Swarm Optimization algorithm,the trajectory design for the transfer from the Moon-centered orbit to the L1 halo orbit,the station-keeping strategies for the Earth-Moon halo orbit and the construction of homoclinic and heteroclinic orbits are investigated.Taking the tracking conditions and engineering constraints into account,two feasible schemes for the Moon departure libration point mission for the lunar probe are presented.

关 键 词：Moon exploration trajectory design full ephemeris model libration point halo orbit 

分 类 号：V11[航空宇航科学与技术—人机与环境工程] TP242[自动化与计算机技术—检测技术与自动化装置]