空间非合作航天器抓捕后姿态抗干扰控制

刘闯; 岳晓奎

doi:10.7527/S1000-6893.2020.24849

航空学报 >

2021 , Vol. 42 >Issue 11: 524849 - 524849

DOI: https://doi.org/10.7527/S1000-6893.2020.24849

论文

空间非合作航天器抓捕后姿态抗干扰控制

刘闯 ,
岳晓奎

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1. 西北工业大学航天学院, 西安 710072;
2. 西北工业大学航天飞行动力学技术重点实验室, 西安 710072

收稿日期: 2020-10-09

修回日期: 2020-12-20

网络出版日期: 2021-01-14

基金资助

国家自然科学基金（62103336，11972026，U2013206）；陕西省自然科学基金（2020JQ-132）；中国博士后科学基金（2020M683571）；陕西省科协青年人才托举计划（2021-1-2）；国防科技重点实验室基金（6142210200310）；中央高校基本科研业务费专项资金（3102019HTQD007）

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Anti-disturbance attitude control for post-capture non-cooperative spacecraft

LIU Chuang ,
YUE Xiaokui

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1. School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. National Key Laboratory of Aerospace Flight Dynamics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2020-10-09

Revised date: 2020-12-20

Online published: 2021-01-14

Supported by

National Natural Science Foundation of China (62103336, 11972026, U2013206); Natural Science Foundation of Shaanxi Province (2020JQ-132); China Postdoctoral Science Foundation (2020M683571); Young Talent Fund of Shaanxi Association for Science and Technology (2021-1-2); the Science and Technology Foundation of National Key Laboratory of Aerospace Flight Dynamics (6142210200310); the Fundamental Research Funds for the Central Universities (3102019HTQD007)

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摘要

针对空间非合作航天器抓捕后存在未知不确定惯性参数的柔性组合体姿态稳定控制问题，基于中间状态观测器设计方法提出了一种新的姿态稳定抗干扰控制方法，同时考虑了诸多扰动及控制输入受限问题。研究结果表明，传统的姿态稳定控制方法需要已知柔性航天器惯性参数信息及状态信息，上述信息未知情况下会使姿态难以高精度稳定控制，且容易导致控制输入不满足受限要求。针对该问题，考虑控制输入幅值及变化率受限前提，提出了一种基于中间状态观测器的抗干扰控制方法，通过引入辅助变量构造新型中间状态观测器，同时估计组合体状态信息及综合干扰，设计出了一种新的组合体姿态稳定抗干扰控制器。通过Lyapunov稳定性分析方法证明了所设计的控制器能够保证闭环系统的全局渐近稳定性。相比于已有的混合H₂/H_∞控制器，所提出的抗干扰控制器在应用时不需要柔性组合体的姿态及模态信息，并且也不需要惯性参数的辨识过程。最后，通过给定参数进行仿真对比，进一步验证了所设计控制器的有效性和优越性。

关键词： 非合作航天器; 空间抓捕后; 姿态控制; 抗干扰控制; 振动抑制

本文引用格式

刘闯 , 岳晓奎 . 空间非合作航天器抓捕后姿态抗干扰控制[J]. 航空学报, 2021 , 42(11) : 524849 -524849 . DOI: 10.7527/S1000-6893.2020.24849

Abstract

For the attitude stabilization control problem of post-capture non-cooperative spacecraft with unknown and uncertain inertial parameters, a novel anti-disturbance attitude control method is proposed based on an intermediate state observer, while considering multiple disturbances and control input magnitude and rate constraints. The traditional attitude stabilization control methods often need known information on the inertial parameter and state of the flexible spacecraft. If the above information is unknown, it will be difficult to achieve attitude stabilization with high precision, and it will be easy to cause the control input to be not able to meet the restricted requirements. To solve this problem, considering the control input magnitude and rate constraints, an anti-disturbance control method is proposed based on an intermediate state observer. The observer is constructed by introducing an auxiliary variable using the state information and lump disturbance, and a novel anti-disturbance controller is then designed. The Lyapunov stability analysis method is used to prove that the designed controller can ensure the global asymptotic stability of the closed-loop system. Compared with the existing mixed H₂/H_∞ controller, the developed controller does not require the attitude and modal information of the flexible body, and the identification process of inertial parameters either. Finally, simulation comparisons further verify the effectiveness and superiority of the designed controller.

Key words： non-cooperative spacecraft; space post-capture; attitude control; anti-disturbance control; vibration suppression

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