载人月球极地探测定点返回轨道设计  

Design of point return orbit for human lunar polar exploration mission

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,长沙410073

出　　处：《中国空间科学技术》2020年第5期61-71,共11页Chinese Space Science and Technology

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

摘　　要：针对载人月球极地探测任务,对定点返回轨道优化设计问题进行了研究。根据月球极地轨道的特性,介绍了三种返回轨道机动方案。结合三脉冲变轨方案,采用了从初步计算到精确计算的串行求解策略,对定点返回轨道进行优化设计。初步计算阶段,建立了基于近月点伪参数的三段二体拼接模型,将三脉冲机动段与月球逃逸段解耦,求解轨道初值;精确计算阶段,提出了两段拼接方法,分别进行逆向和正向高精度数值积分。经过仿真测试,验证了该策略求解的有效性和准确性。最后,通过大量的仿真计算,分析了定点返回轨道的特性。研究结论对未来载人月球极地探测定点返回轨道方案的设计具有重要的参考价值。The optimal design of point return orbit was studied for human lunar polar exploration mission.According to the characteristics of lunar polar orbit(LPO),three return orbit maneuver schemes were proposed.Considering three-impulse maneuver scheme,a serial orbit solution strategy from initial calculation to accurate calculation was adopted to design point return orbit.The initial orbit was obtained by establishing a novel model with three-segment two-body patched orbits based on pseudo-perilune parameters to decouple the three-impulse maneuver with the lunar escape.Two-segment orbits were matched to get precise point return orbit by using numerical continuation theory and the suggested backward and forward orbital integral model with high precision perturbation.The effectiveness and reliability of the approach proposed were demonstrated by simulation test.According to the simulation results by the method,the orbit characteristics of point return orbit were analyzed.The research conclusions can provide reference for the design of point return orbit scheme in human lunar polar exploration missions in the future.

关 键 词：月球极地 载人登月 定点返回 轨道设计 轨道特性 

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]