星历模型下地月自由返回全飞行过程轨道设计  

Design of Earth-Moon Free Return Transfer Trajectory under Ephemeris Model during the Entire Flight Process

作　　者：彭祺擘[1,2] 和星吉 陈天冀 武新峰 徐明 PENG Qibo;HE Xingji;CHEN Tianji;WU Xinfeng;XU Ming(China Astronauts Research and Training Center,Beijing 100094,China;School of Astronautics,Beihang University,Beijing 102206,China;Shenyuan Honors College,Beihang University,Beijing 100191,China)

机构地区：[1]中国航天员科研训练中心,北京100094 [2]北京航空航天大学宇航学院,北京102206 [3]北京航空航天大学未来空天技术学院/高等理工学院,北京100191

出　　处：《宇航学报》2023年第1期43-51,共9页Journal of Astronautics

基　　金：载人航天工程科技创新团队。

摘　　要：面向载人登月任务需要,针对星历模型下具备自由返回能力的地月转移轨道设计问题进行了研究。在三体模型下对地月三维自由返回轨道进行了求解,得到了地月空间内的自由返回轨道分布情况。在二体模型假设下对近月段的三脉冲变轨进行了求解,给出了变平面机动的计算方法。进一步提出了两轮逐次优化修正策略,分别以高度和再入走廊为主要约束,采用内点法和SQP算法在高精度星历模型下对自由返回轨道初值进行逐次优化修正。之后,采用SQP算法在星历模型下对近月三脉冲变轨进行优化修正,得到了星历模型下的自由返回+近月三脉冲变轨地月转移策略。仿真校验结果表明本文提出的方法能够在给定约束下有效求解星历模型下具备自由返回能力的地月转移轨道,为载人登月任务的转移轨道设计提供参考。Aiming at the need of manned lunar landing missions,the trajectory design problem of Earth-Moon transfer with free return capability under the ephemeris model is studied.The three-dimensional Earth-Moon free return trajectory is solved under the three-body model,by which the distribution of free return trajectories in the cislunar space is obtained.Under the assumption of two-body model,the three-pulse maneuvers strategy near the Moon is proposed.Furthermore,a two-step optimization correction method is proposed,during which the orbital altitude and reentry corridor are respectively considered as the main constraints.The interior-point method and SQP algorithm are used to optimize and correct the initial states of free return trajectory under the ephemeris model.Then,the lunar three-pulse maneuvers are optimized and corrected by SQP algorithm,and then the entire Earth-Moon transfer trajectory consisting of free return segment and lunar three-pulse maneuvers segment are obtained.The simulation results have verified the feasibility of the proposed method.

关 键 词：载人登月 星历模型 自由返回 地月转移 轨道设计 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]