宇航学报 ›› 2022, Vol. 43 ›› Issue (6): 772-780.doi: 10.3873/j.issn.1000-1328.2022.06.008

• 制导、导航、控制与电子 • 上一篇    下一篇

近地星座异面遍历交会轨道全局优化

黄岸毅,罗亚中,李恒年   

  1. 1. 西安卫星测控中心宇航动力学国家重点实验室,西安 710043;2. 国防科技大学空天科学学院,长沙 410073;3. 空天任务智能规划与仿真湖南省重点实验室,长沙 410073
  • 收稿日期:2021-09-14 修回日期:2022-01-31 出版日期:2022-06-15 发布日期:2022-06-15
  • 基金资助:
    国家自然科学基金(11972044)

Global Trajectory Optimization of Non coplanar Ergodic Rendezvous in LEO Constellation

HUANG Anyi, LUO Yazhong, LI Hengnian   

  1. 1. Xi’an Satellite Control Center, Xi’an 710043, China;2. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;3. Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Mission, Changsha 410073, China
  • Received:2021-09-14 Revised:2022-01-31 Online:2022-06-15 Published:2022-06-15

摘要: 根据J 2摄动对轨道面的长期影响规律,提出了一种在近地低轨道星座卫星之间进行异面轨道交会的解析近似方法,并用于建立多星多约束遍历交会的混合整数规划模型,能够快速获得多星交会次序、交会时刻的最优解。仿真算例表明提出的方法适用于在轨服务、构型重建等类型任务的快速优化,计算速度和燃料消耗优于以往类似算法。

关键词: 低轨道卫星, 在轨服务, 多星异面交会, 最优交会, 混合整数规划

Abstract: According to the long term influence of  J 2  perturbation on the orbital plane, an analytical approximation method is proposed for the non coplanar orbital rendezvous between satellites in a low Earth orbit constellation. And then the method is used to establish a mixed integer planning model for multi satellite rendezvous with multiple constraints, which can quickly obtain the global optimal rendezvous sequence and transfer times. Simulation results show that the proposed method is suitable for the rapid optimization of tasks such as on orbit servicing and re configuration reconstruction, and the calculation efficiency and fuel consumption are better than those of the previous similar algorithms.

Key words: Low Earth orbit satellite, On orbit servicing, Multi satellite non coplanar rendezvous, Optimal rendezvous, Mixed integer planning

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