基于弱稳定边界理论的低能地月转移轨道设计  

Design of Low-energy Transfer Orbits Based on Weak Stability Boundary

作　　者：李宸硕 田百义 王义宇 张泽旭[1] 徐田来 LI Chenshuo;TIAN Baiyi;WANG Yiyu;ZHANG Zexu;XU Tianlai(School of Astronautics,Harbin Institute of Technology,Harbin 150001,China;Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]北京空间飞行器总体设计部,北京100094

出　　处：《宇航学报》2024年第7期1135-1145,共11页Journal of Astronautics

基　　金：国家自然科学基金重点项目资助(52238002);中央高校基本科研业务费专项资金资助(2022FRFK01001)。

摘　　要：针对弱稳定边界轨道求解困难、模型复杂、对初值的敏感程度较高等问题,提出了一种基于弱稳定边界的地月低能转移轨道设计方法,通过一种双层优化算法求解流形拼接问题,实现航天器低能地月转移。首先计算地月L2点Halo轨道及不变流形;随后将其与日地系统Halo轨道的不变流形进行拼接,计算离散流形拼接点,根据离散流形拼接点的速度和位置选择优化初值;最后建立流形拼接的优化模型,优化求解得到双圆限制性四体模型下的转移轨道。仿真结果表明,该轨道设计方法转移所需的能量较低,并满足多种约束条件,可为未来地月探测低能轨道设计提供参考。In response to the challenges of solving weakly stable boundary orbits,dealing with complex models,and high sensitivity to initial values,a method for designing low-energy transfer orbits between the Earth and the Moon is proposed based on weakly stable boundaries.A two-layer optimization algorithm is used to solve manifold connection problem and realize low energy Earth-Moon transfer of spacecraft.Firstly,the method involves calculating the Halo orbit and invariant manifold at the Earth-Moon L2 point.Then,the discrete manifold connection points are calculated,and the optimized initial values are selected according to the velocity and position of the discrete manifold connection points.Finally,the optimization model of manifold connection is established,and the transfer orbit under the bicircular restricted four-body problem model is obtained.The simulation results show that the proposed orbit design method has low transfer energy and complies with many constraints,which can provide reference for low-energy orbit design of future cislunar exploration.

关 键 词：弱稳定边界理论 地月低能转移轨道 不变流形拼接 双层优化 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]