Multi-Satellite Capture Configuration with Continuous Thrust

被引：0

作者：

Wang, Weike ^{[1
,2
]}

Wang, Hanjun ^{[1
]}

Liao, Tian ^{[1
]}

Li, Shunli ^{[1
]}

Zhu, Mengping ^{[2
]}

机构：

[1] School of Astronautics, Harbin Institute of Technology, 92 Xidazhi Street, Heilongjiang, Harbin

[2] Qian Xuesen Laboratory of Space Technology, China Academy of Space Technology, 104 Youyi Road, Beijing

来源：

Advances in Astronautics Science and Technology | 2024年 / 7卷 / 02期

基金：

中国国家自然科学基金;

关键词：

Capture configuration design; Continuous thrust; Interception strategy; Pursuit-evasion game;

D O I：

10.1007/s42423-024-00161-3

中图分类号：

学科分类号：

摘要：

The pursuit-evasion game of orbital satellite is an important research problem in the field of space security. In this pursuit-evasion game, intercepting the target usually requires superior maneuvering capabilities. To address this issue, a method is proposed in this paper to use multiple small satellites with weaker maneuvering capabilities to encircle and capture larger targets with stronger maneuvering abilities. Firstly, based on Tsiolkovsky’s formula, the planar interception problem is derived and a one-on-one planar interception strategy is designed. Next, the existence of solutions for planar mission is analyzed, and a multi-satellite encirclement configuration is designed based on elliptical passive flyby theory. Finally, simulation analysis is conducted on the impact of various design parameters of the planar interception configuration on the encirclement task. The results indicate that the initial distance between interceptor and target significantly affects interception time. Simulation results validate that the proposed interception strategy and encirclement configuration can achieve rapid interception of close-range targets effectively. © Chinese Society of Astronautics 2024.

引用

页码：133 / 143

页数：10

共 18 条

[1]

Liao T., Li S., Chen X., Zhu M., Numerical solution of spacecraft pursuit-evasion-capture game based on progressive shooting method, Proc Inst Mech Eng Part G J Aerosp Eng, (2023)

[2]

Luo Y., Zhu H., Li Z., Survey on spacecraft orbital pursuit-evasion differential games (in Chinese), Scientia Sinica Technologica, 50, 12, pp. 1533-1545, (2020)

[3]

Zy L., Zhu H., Yang Z., Luo Y.Z., A dimension-reduction solution of free-time differential games for spacecraft pursuit-evasion, Acta Astronautica, 163, pp. 201-210, (2019)

[4]

Liao T., Research on control and solving method of pursuit-evasion game for spacecraft (in Chinese) [Master’s Thesis], (2021)

[5]

Zeng X., Cai W., Yang L., Zhu Y., On the orbital pursuit-evasion games with low constant thrust-to-mass ratio, 2018 Chinese automation congress (CAC), pp. 1655-1660, (2018)

[6]

Ye D., Shi M., Sun Z., Satellite proximate interception vector guidance based on differential games, Chin J Aeron, 31, 6, pp. 1352-1361, (2018)

[7]

Zhu H., Optimal control of spacecraft orbital pursuit-evasion based on differential game (in Chinese) [Master’s Thesis], (2017)

[8]

Li Z., Zhu H., Luo Y., An escape strategy in orbital pursuit-evasion games with incomplete information, Sci China Technol Sci, 64, 3, pp. 559-570, (2021)

[9]

Zhu H., Luo Y.Z., Li Z.Y., Yang Z., Orbital pursuit-evasion games with incomplete information in the hill reference frame, In: Proceedings of 27Th International Symposium on Space Flight Dynamics (ISSFD)., pp. 1-6, (2019)

[10]

Zhou J., Research on Control Method for Spacecraft Pursuit-Evasion Based on Differential Game Theory (In Chinese), (2021)

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