地月平动点小推力多目标交会任务设计与分析  

Design and Analysis of Low-thrust Multi-target Rendezvous Missions Near the Cislunar Libration Points

作　　者：宋亮俊 杜崇瑞 王亚敏 岳晓奎[1] 代洪华 SONG Liangjun;DU Chongrui;WANG Yamin;YUE Xiaokui;DAI Honghua(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;Innovation Academy for Microsatellites of Chinese Academy of Sciences,Shanghai 201203,China)

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国科学院微小卫星创新研究院,上海201203

出　　处：《宇航学报》2025年第3期568-579,共12页Journal of Astronautics

基　　金：国家重点研发计划(2021YFA0717100);国家重点研发计划(2021YFC2202600);陕西省科学技术协会青年人才托举计划项目(20240520)。

摘　　要：针对未来地月空间中平动点周期轨道上的多航天器在轨服务需求,首次探讨了平动点附近的小推力多目标交会问题。首先,建立了多目标交会的混合整数规划模型。其次,给出了周期轨道上小推力航天器交会轨迹的求解流程,并提出了一种基于截断策略的平动点交会轨迹数据库生成方法;在该方法的基础上,结合改进蚁群算法(ACO)和遗传算法(GA)分两阶段优化,获得最优的交会序列和交会时间。最后,将上述方法应用于对称南北Halo轨道上均匀分布的多颗卫星交会任务的算例仿真。研究结果不仅表明截断策略能够在保证求解结果最优性的前提下降低数据库体量和生成耗时,还揭示了交会优先级与目标相位差之间关系,为未来平动点航天器的在轨服务规划及在轨组装等任务提供技术支撑。The problem of low-thrust multitarget rendezvous near libration points is explored for the first time,in response to the on-orbit service demands of multi-spacecraft in the periodic orbit of libration points within the future cislunar space.Initially,a mixed integer programming model is established for multitarget rendezvous.Subsequently,the process for solving the rendezvous trajectory of low-thrust spacecraft in periodic orbit is outlined,and a method is proposed for generating a rendezvous trajectory database for libration points based on a truncation strategy.This method is then utilized to combine improved ant colony optimization(ACO)and genetic algorithm(GA)in two stages,in order to determine the optimal rendezvous sequence and rendezvous time.The approach is applied to simulate rendezvous missions involving multiple satellites uniformly distributed in symmetrical north and south Halo orbits.The results demonstrate that truncation strategies can reduce the size and generation time of the database while maintaining an optimal solution.Additionally,they reveal the relationship between rendezvous priority and target phase difference.This provides technical support for future tasks,including orbital servicing planning and on-orbit assembly of spacecraft at libration points.

关 键 词：多目标交会 圆型限制性三体模型(CRTBP) 地月空间 地月平动点轨道 小推力 

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]