宇航学报 ›› 2016, Vol. 37 ›› Issue (2): 159-168.doi: 10.3873/j.issn.1000-1328.2016.02.004

• 飞行器设计与力学 • 上一篇    下一篇

不同月球借力约束下的地月Halo轨道转移轨道设计

张景瑞,曾豪,李明涛   

  1. 1. 北京理工大学宇航学院,北京100081;2.中国科学院空间科学与应用研究中心,北京100190
  • 收稿日期:2015-03-30 修回日期:2015-09-14 出版日期:2016-02-15 发布日期:2016-02-25
  • 基金资助:

    北京理工大学研究生科技创新活动专项计划(2015CX10001)

A Design Method for Earth Moon Halo Orbit Transfer Trajectory Under Different Constraints to Moon Gravity Assisted Maneuvers

ZHANG Jing rui, ZENG Hao, LI Ming tao   

  1. 1.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
    2. Center for Space Science and Applied Research, Chinese Academy of Sciences, Beijing 100190, China
  • Received:2015-03-30 Revised:2015-09-14 Online:2016-02-15 Published:2016-02-25

摘要:

针对地月系L2点不同任务需求下的低耗能转移轨道设计问题,基于不变流形理论与混合优化技术,深入研究了不同月球借力约束与不同幅值Halo轨道的入轨点(简称HOI点)对转移轨道飞行时间与燃料消耗的影响,给出了HOI点选择策略。首先结合任务要求并考虑月球引力影响,在月球借力点施加不同约束条件,通过微分修正算法调整Halo轨道的稳定流形,设计月球到Halo轨道的转移轨道。采用遗传算法与微分修正算法相结合的混合优化策略,在同时考虑地球停泊轨道高度、倾角、升交点赤经与航迹角等多约束条件下,对燃料最优的地月转移轨道进行研究。最后,分析月球借力高度、借力方位角和不同HOI点对平动点转移轨道飞行时间与燃耗变化量的影响,对于考虑月球借力的地月平动点转移轨道设计与应用具有重要的参考价值。

关键词: Halo轨道, 不变流形, 借力飞行, 混合优化

Abstract:

To design low-energy Earth-Moon L2 Halo orbit transfer trajectory for different mission requirements, a deep research on the influence of different constraints to the moon gravity-assisted maneuvers and Halo orbit insertion (HOI) points with different amplitudes on time of flight and fuel consumption is made, and a selection strategy for HOI points is proposed in this paper. Firstly, combined with mission requirements and effects of the moon gravity, different constraints are applied to the moon gravity-assisted maneuvers. Stable manifold of Halo orbit is adjusted through differential correction algorithm and the transfer trajectory from moon to Halo orbit is designed. Then, in consideration of orbit altitude , orbit inclination, right ascension of ascending node and track angle at the same time, the hybrid optimization strategy combined genetic algorithm with differential correction algorithm is adopted to study Earth-Moon Halo orbit transfer trajectories with optimal fuel consumption. At last, the influence of moon gravity-assisted altitude and azimuth as well as different HOI points on flight time and fuel consumption of transfer trajectories is respectively analyzed, which has reference value for design and application of Earth-Moon Halo orbit transfer trajectories.

Key words: Halo orbit, Invariant manifold, Moon gravity-assisted maneuver, Hybrid optimization

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