中国空间科学技术

中国空间科学技术 ›› 2024, Vol. 44 ›› Issue (5): 83-94.doi: 10.16708/j.cnki.1000-758X.2024.0076

• 论文 • 上一篇    下一篇

基于可达域分析的空间非合作围捕构型设计

李瑞峰，孙冲，王政，方群，张翔   

  1. 1 西北工业大学 航天学院，西安710072
    2 西北工业大学深圳研究院 空间操控先进概念研究联合实验室，深圳518060
  • 出版日期:2024-10-25 发布日期:2024-10-21

Capture configuration design for space non-cooperative target based on reachable domain

LI Ruifeng，SUN Chong，WANG Zheng，FANG Qun，ZHANG Xiang   

  1. 1 School of Astronautics，Northwestern Polytechnical University，Xi′an 710072，China
    2 Shenzhen Research Institute of Northwestern Polytechnical University，Shenzhen 518060，China
  • Published:2024-10-25 Online:2024-10-21

PDF (PC)

32

摘要： 多个低成本航天器协同围捕空间高价值非合作目标是轨道博弈的典型场景。在考虑目标自主机动情况下，如何快速设计围捕构型以可靠高效地实现在轨围捕是目前尚未解决的关键问题。提出一种基于可达域分析的航天器集群围捕构型设计方法。首先，建立围捕任务动力学模型，描述了集群围捕任务的条件，提出了基于连续推力机动可达域分析方法的多航天器协同围捕非合作目标的准则。进一步，采用最优控制理论求解航天器机动可达域，开展了可达域特性分析，提出了集群航天器协同可达域的半解析解。最后，提出一种4个航天器协同围捕构型设计方法。仿真结果验证了围捕构型设计方法的有效性，并与传统单航天器连续推力可达域求解方法对比，证明了可达域求解方法的可行性。

关键词: 可达域, 航天器集群, 围捕构型, 最优控制理论, 设计方法

Abstract: It is a typical scenario of orbit game that several low-cost spacecraft cooperate to capture highly valuable non-cooperative targets.In the consideration of autonomous maneuver of the target，the key problem unsolved is how to quickly design the capture configuration to achieve on-orbit capture reliably and efficiently.A design method of the spacecraft cluster capture configuration based on reachable domain（RD）is proposed.Firstly，the dynamic model of capture mission is established，and the conditions of the capture mission with cluster are described.Then，a criterion for multi spacecraft to capture non-cooperative targets is proposed based on the RD method for continuous thrust maneuver.Furthermore，the optimal control theory is used to solve the RD of spacecraft，the characteristics of the RD are analyzed，and then the semi-analytical solution of collaborative RD of the spacecraft cluster is proposed.Finally，a design method for collaborative capture configuration using four spacecraft is proposed.In this paper，the simulation results verify the full effectiveness of the cluster capture configuration design method；and compared with the traditional single spacecraft continuous thrust RD solution method，the feasibility of the method for solving the RD is proved.

Key words: reachable domain, spacecraft cluster, capture configuration, optimal control theory, design method