月地应急返回轨道优化设计  

Optimal design of the Moon-Earth emergency return trajectories

作　　者：陆林 李海阳[1] 刘将辉 杨路易 LU Lin;LI Haiyang;LIU Jianghui;YANG Luyi(College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)

机构地区：[1]国防科技大学空天科学学院

出　　处：《系统工程与电子技术》2020年第2期420-426,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金(11372345);载人航天预先研究项目(010201)资助课题

摘　　要：针对载人登月任务中的应急返回问题,对基于三脉冲变轨的方案进行优化设计。以圆型限制性三体问题(circular restricted three body problem,CR3BP)模型为基础,采用球坐标形式的月球返回运动模型。考虑环月轨道面、月球最小安全距离、终端近地距等约束,采用MultiStart算法对月地应急返回轨道进行全局优化。通过大量的计算仿真,验证了所提算法的有效性和可行性,并分析了不同轨道参数对性能指标的影响。研究结论对未来载人登月应急返回方案的设计具有重要的参考价值。The three-impulse trajectories are optimally designed for the emergency return problem in the manned lunar landing mission.The motion equations of lunar return trajectories are adopted in the spherical frame based on the model of the circulunar restricted three body problem.The Moon-Earth emergency return trajectories concerning the constraints of circular orbit plane,minimum safe distance with respect to the Moon and terminal perigee height are optimized globally by using the MultiStart algorithm.The effectiveness and reliability of the proposed approach are demonstrated by the simulation tests.Finally,according to a great deal of simulation results by the method,the effects of different orbit parameters on optimization objective are analyzed.The research conclusions can provide references for the design of emergency return trajectory scheme in the manned lunar landing mission in the future.

关 键 词：载人登月 应急返回 圆型限制性三体问题 全局优化 

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]