星座寿命后碎片飞越轨道设计与优化  

Space Debris Flyby Trajectory Optimization of Satellite Constellation after Mission Life

作　　者：张思扬 王蜀泉[1,2] ZHANG Siyang;WANG Shuquan(Technology and Engineering Center for Space Utilization,Chinese Academy of Sciences,Beijing 100094,China;University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院空间应用工程与技术中心,北京100094 [2]中国科学院大学,北京100049

出　　处：《宇航学报》2024年第6期866-880,共15页Journal of Astronautics

基　　金：中国科学院地月空间探索先导专项(XDA30010500)。

摘　　要：针对星座卫星寿命结束后转变为大规模碎片的主动清理问题,提出一种多目标飞越方案,以SL(StarLink)星座为例设计从停泊轨道出发对多个轨道面、多枚碎片的飞越探测最优轨道。首先根据SL星座的轨道特征将目标按照轨道面进行聚类,然后根据球面几何关系和Gibbs公式对轨道机动参数进行降维,在开普勒运动假设下快速设计考虑航天器空飞、套圈飞行的单脉冲飞越多目标的轨道机动参数初值。最后基于分支定界广度优先方法,考虑J2引力摄动搜索单脉冲飞越双目标的飞行序列,得到燃耗最小的飞越轨道。数值仿真结果表明航天器通过24次轨道机动后,共飞越探测了48颗SL卫星,共需速度脉冲1.66 km/s,飞行时间9.64天,证明了所提出方法的有效性,为未来大规模空间碎片清理任务设计提供参考。Taking the SL constellation as an example to design the optimal orbits for flyby and detection of multiple orbital planes and multiple targets from the parking orbit,a multi-target flyby program to actively remove large debris converted by constellation satellites at the end of mission life is proposed.Firstly,the orbital planes of target satellites are classified according to the orbital characteristics of the constellation.Then,the dimension of the parameters of the orbital maneuver is reduced according to the spherical geometric and Gibbs'formula,and the method of single-impulse two-satellite flyby is proposed in consideration of the cases of cruise and multi-revolution in the suppose of the Kepler orbit.Based on the flyby orbits searched by the branch and bound breadth-first algorithm in the J2-perturbed model,the flyby sequence with the minimum cost-effectiveness ratio is obtained.The simulation results show that the spacecraft can flyby 48 SL satellites through 24 maneuvers in 9.64 days with the total impulse of 1.66 km/s,which proves the effectiveness of the proposed method and is helpful for the future large-scale space debris removal missions.

关 键 词：空间碎片 单脉冲多目标飞越 轨道优化 星座 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]