宇航学报 ›› 2021, Vol. 42 ›› Issue (12): 1483-1492.doi: 10.3873/j.issn.1000-1328.2021.12.001

• 飞行器设计与力学 • 上一篇    下一篇

地月Halo与DRO支持的往返月球任务轨道

曾豪,李朝玉,徐瑞,郝平,彭坤   

  1. 1.北京空间飞行器总体设计部,北京 100094;2.北京理工大学,北京 100081
  • 收稿日期:2021-02-22 修回日期:2021-05-10 出版日期:2021-12-15 发布日期:2021-12-15
  • 基金资助:
    国家自然科学基金(62006019)

Round trip Transfers to Earth Moon DRO and Halo for Supporting Lunar Exploration

ZENG Hao, LI Zhao yu, XU Rui, HAO Ping, PENG Kun   

  1. 1. Beijing Institute of Spacecraft System Engineering, China Academy of Space Technology, Beijing 100094, China;2.Beijing Institute of Technology, Beijing 100081, China
  • Received:2021-02-22 Revised:2021-05-10 Online:2021-12-15 Published:2021-12-15

摘要: 面向未来载人月球与深空探测任务需求,针对地月系统中低能往返环月轨道与平动点轨道的转移设计问题进行研究,在不同三体轨道下系统分析了环月轨道变化对任务飞行时间与燃料消耗等关键参数的影响,并提出月球往返轨道初值猜想搜索策略。为解决设计变量初值敏感性问题,结合空间不变流形与目标平动点轨道构型特性,采用微分修正算法快速构造初始转移轨迹。在同时考虑近月点与燃料最优转移多约束条件下,通过多重配点打靶法与序列二次规划算法对环月轨道与平动点轨道间往返轨迹进一步研究,并推导了约束方程的梯度公式提高计算效率。为分析往返轨道特性与验证设计策略的有效性,针对不同环月轨道倾角、三体轨道幅值等参数变化与转移时间、燃耗的关系进行分析,设计结果对探月飞行器近月空间部署往返轨道设计及参数选取具有重要的参考意义。


关键词: 平动点三体轨道, 往返轨迹, 初值问题, 混合优化

Abstract: For manned lunar and deep space exploration missions in the future, the transfer design of low energy round trip circumlunar orbit and libration point in the Earth Moon system is studied, the effect of circumlunar orbit changes on key parameters such as flight time and mission fuel consumption are systematically analyzed under different three body orbits, and a search strategy for the initial value of round trip orbit design is presented. In order to solve the problem of initial value sensitivity of design variables, a differential correction algorithm is used to rapidly construct the initial transfer orbit by combining the invariant manifold with the characteristics of the libration point orbit. Considering multiple constraints such as near lunar and optimal fuel simultaneously, the round trip trajectory between the circumlunar orbit and libration point orbit is further studied through the multiple shooting method and quadratic programming algorithm, and the gradient formula of the constraint equations is deduced to improve the design efficiency. In order to analyze the characteristics of round trip orbits and verify the effectiveness of the design strategy, the relationship between the variation of parameters, such as amplitude of three body orbits, the inclination of different circumlunar orbits, and the transfer time and fuel consumption is studied. The design results have important reference significance for the design of round trip orbits and selection of parameters for the deployment of lunar exploration vehicles.


Key words: Libration point three body orbit, Roundtrip orbit, Initial value problem, Hybrid optimization

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