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地-月L2点中继星月球近旁转移轨道设计
孙超1,2, 唐玉华1, 李翔宇1,2, 乔栋1,2
1.北京理工大学 宇航学院, 北京 100081;2.深空探测自主导航与控制工业与信息化部重点实验室, 北京 100081
摘要:
位于地月L2点周期轨道的中继星将首次为“嫦娥4号”月球背面着陆探测任务提供通信中继服务。中继星转移轨道设计是中继任务实施的关键环节。针对中继星转移轨道存在转移时间、近月点高度和halo轨道振幅等约束条件,系统研究了基于月球近旁的地月L2点转移轨道设计方法。首先基于限制性三体模型,分析了halo轨道族与着陆点可见性关系;然后将月球近旁转移轨道分为地月直接转移段和地月动平衡点附近周期轨道拟流形入轨转移段,采用带有状态约束的微分修正算法对这两段轨道进行拼接,得到了从地球附近至目标轨道族的月球近旁转移轨道;最后,针对南族halo轨道分析了halo轨道振幅和月球飞越高度对转移轨道设计的影响,以及转移轨道的入轨相位分布。仿真结果表明:月球近旁转移轨道设计方案具备工程上的可行性与优越性。该方案可以为实际工程任务和应用提供参考。
关键词:  地月L2点;中继星;月球近旁;转移轨道
DOI:10.15982/j.issn.2095-7777.2017.03.010
分类号:V412.4+1
基金项目:新世纪优秀人才支持计划支持项目;国家自然科学基金项支持项目(11572038);“飞行器动力学与控制”111引智创新基地支持项目
Design of Earth-Moon L2 Halo Orbit Transfer Trajectory for Relay Satellite Using Lunar Flybys
SUN Chao1,2, TANG Yuhua1, LI Xiangyu1,2, QIAO Dong1,2
1.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2.Key Laboratory of Autonomous Navigation and Control for Deep Space Exploration, Ministry of Industry and Information Technology, Beijing 100081, China
Abstract:
The satellite on Earth-Moon L2 periodic orbit will provide communication relay for CE-4,China’s first Lunar landing exploration mission on the moon’s far side. The transfer orbit design plays an important role in the implementation of the relay mission. Considering the constrains on transfer time,flyby altitude and amplitude of the halo orbits,this paper systematically studies the Earth-Moon L2 transfer trajectory using Lunar flybys. First,based on the restricted three-body problem(RTBP),the visibility of the landing point with different families of halo orbits is analyzed. Then,the transfer orbit is divided into Earth-Moon direct transfer segment and quasi manifolds associated with halo orbits. The differential correction algorithm with state constraints is employed to match the two segments. Finally,aiming at southern family of halo orbits,the influence of orbit amplitude and Lunar flyby altitude on the cost of transfer as well as orbit insertion phase are discussed respectively. The simulation shows the feasibility and engineering advantages of lunar flyby transfer.
Key words:  Earth-Moon L2 point;relay satellite;Lunar flyby;transfer orbit