地月L2点空间站转移轨道设计与特性分析  

Trans-halo Trajectory Design and Characteristic Analysis of Earth-Moon L2 Point Space Station

作　　者：曹鹏飞 贺波勇 刘景勇[1] 彭祺擘[3] CAO Pengfei;HE Boyong;LIU Jingyong;PENG Qibo(Beijing Aerospace Control Center,Beijing 100094,China;State Key Laboratory Of Astronautics Dynamics,Xi’An Satellite Control Center,Shaanxi Xi’an 710043,China;Scientific Research Training Center for Chinese Astronauts,Beijing 100094,China)

机构地区：[1]北京航天飞行控制中心,北京100094 [2]西安卫星测控中心宇航动力学国家重点实验室,西安710043 [3]中国航天员科研训练中心,北京100094

出　　处：《载人航天》2019年第6期755-760,770,共7页Manned Spaceflight

基　　金：国家自然科学基金(11773004;11303001;61573049;61571032)

摘　　要：针对低运输成本的未来地月L2点Halo轨道空间站补给任务轨道转移问题,研究了基于不变流形和月球借力的间接转移轨道设计方法及轨道参数特性。首先建立了三脉冲从近地停泊轨道出发到Halo轨道的间接转移轨道设计模型;然后提出了二体解析初值搜索和局部梯度优化相结合的串行优化方法,并采用圆型限制性三体问题模型验证了方法的正确性与快速性;最后,通过大量仿真算例分析了间接转移轨道参数特性。结果表明不变流形插入点相位和Halo轨道幅值对间接转移轨道燃料消耗影响较大,而月球借力高度影响则比较小。To solve the orbital transfer problem of the resupply mission with low transportation cost to the future L2-point Halo orbital space station,the design method and the orbital characteristics of the indirect transfer trajectory based on the invariant manifold and lunar fly-by were studied.First,the design model of a three-pulse indirect transfer trajectory from the low Earth orbit to the L2 point Halo orbit was established.Then,a serial optimization method combining the two-body analytic initial value searching and local gradient optimization was proposed.The correctness and rapidity of the method were verified by the circular restricted three body problem.In the end,a large number of simulation examples were used to analyze the indirect transfer orbit characteristics.It was found that the invariant manifold insertion phase and Halo orbit amplitude had a greater impact on the fuel consumption of the indirect transfer trajectories.While,the effect of the lunar fly-by altitude was relatively small.

关 键 词：地月L2点 HALO轨道 空间站 转移轨道 不变流形 月球借力 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]