Trajectory design for the Moon departure libration point mission in full ephemeris model
Trajectory design for the Moon departure libration point mission in full ephemeris model
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DOI：
10.1007/s11431-011-4539-1
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发表时间：
2011-08
期刊：
影响因子：
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通讯作者：
Yang Chen;H. Baoyin;Junfeng Li
中科院分区：
文献类型：
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作者：
Yang Chen;H. Baoyin;Junfeng Li
月球探测器在完成预定的月球探测使命后，可能还有一些剩余的燃料，并能够在脱离月球轨道后执行一些额外的科学或技术任务。月球探测器的离月使命是本文研究的重点。分析了航天器绕月飞行摆脱月球引力的可能性。在考虑月球绕地球非匀速运动、太阳和行星引力以及星载发动机有限推力的全星历动力学模型下，研究了地月系统平动点使命的轨道设计问题。应用粒子群优化算法，研究了从月心轨道到L1晕轨道的转移轨道设计、地月晕轨道的位置保持策略以及同宿轨道和异宿轨道的构造。在考虑跟踪条件和工程约束的基础上，提出了月球探测器月球离地平动点使命的两种可行方案。
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.