利用规避机动的月球返回拓展任务转移轨道设计方法  

Trajectory design of Lunar return extended mission using avoidance maneuver

作　　者：董跃 尚海滨[1] 国志磊 DONG Yue;SHANG HaiBin;GUO ZhiLei(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Deep Space Exploration Laboratory,Beijing 100195,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]深空探测实验室,北京100195

出　　处：《中国科学:物理学、力学、天文学》2025年第2期209-226,共18页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家自然科学基金(编号:12472354)资助项目。

摘　　要：为提升月球返回拓展任务转移轨道设计的灵活性,构建了月球返回规避机动无约束设计模型,并据此发展了利用规避机动的月球返回拓展任务转移轨道设计方法.首先,分析讨论了规避机动后轨道安全约束的三种情况,发展了一种规避拉起高度自适应控制技术,在不引入设计约束的情况下实现了满足安全高度需求的同平面规避机动解析计算;然后,推导了规避机动与转移轨道参数之间的映射关系,提出了一种基于旋转平面的规避机动设计方法,实现了规避机动与后续转移轨道的匹配,并据此建立了月球返回规避机动无约束设计模型;最后,分析了规避机动的轨道几何与燃料消耗特性,分别以大幅值逆行轨道(DRO)与小行星为目标构建了月球返回拓展任务转移轨道设计模型,对所提方法进行了数值验证.数值仿真结果表明,提出的月球返回拓展任务转移轨道设计方法具有较强的寻优能力,能够支持不同探测目标的月球返回拓展任务转移轨道设计.In order to improve the flexibility of transfer trajectory design for extended lunar return missions, a constraint-free designmodel for Lunar return avoidance maneuver is constructed, and a transfer trajectory design method for extended Lunarreturn missions using avoidance maneuver is developed accordingly. First, three cases of safety constraints after theavoidance maneuver are discussed, and an adaptive control technique for the avoidance altitude is developed, whichrealizes the analytical calculation of the in-plane avoidance maneuver that satisfies the safety requirements withoutintroducing any constraint. Then, the mapping between the avoidance maneuver and the parameters of the transfertrajectory is derived. A rotating plane-based avoidance maneuver design method is proposed to realize the mappingbetween the avoidance maneuver and the subsequent transfer trajectory, and the constraint-free design model of the Lunarreturn avoidance maneuver is established accordingly. Finally, the orbital geometry and fuel consumption characteristicsof the avoidance maneuver are analyzed. The transfer trajectory design models of the Lunar return expansion mission areconstructed with the DRO and the asteroid as the targets. Numerical simulation results show that the proposed transfertrajectory design method has a powerful optimization capability and can support the transfer trajectory design fordifferent exploration targets.

关 键 词：月球探测 转移轨道 轨道机动 拓展任务 优化设计 

分 类 号：G63[文化科学—教育学]