航天器非脆弱控制理论及应用研究进展

doi:10.12305/j.issn.1001-506X.2025.05.25

摘要/Abstract

摘要：

随着航天工程的逐步实施, 航天器正朝着高速、大尺度、多功能的大型化和复杂化方向发展, 强鲁棒非脆弱高精高稳控制技术是保证航天器在复杂太空环境下正常运行并成功实施空间任务的有效保障。本文梳理非脆弱控制理论的起源及发展, 进而总结基于线性矩阵不等式(linear matrix inequality, LMI)方法的鲁棒非脆弱控制器在航天器轨道及姿态控制中的应用, 在考虑加法式摄动和乘法式摄动的条件下, 进一步说明非脆弱状态反馈控制器、输出反馈控制器、干扰观测器及中间状态观测器的设计方法, 并对未来航天器非脆弱控制方法的发展与应用提出展望, 为航天器鲁棒非脆弱控制方法的研究探索提供思考, 以满足日益复杂的航天器高精高稳控制任务需求。

关键词: 非脆弱理论, 航天器控制, 线性矩阵不等式, 增益摄动, 鲁棒控制

Abstract:

With the gradual implementation of aerospace engineering, spacecraft are developing towards high-speed, large-scale, and multifunctional large-scale and complex directions. Strong and non-fragile high-precision and high-stability control technology is an effective guarantee to ensure the normal operation of spacecraft in complex space environments and the successful implementation of space missions.This article reviews the origin and development of non-fragile control theory, and summarizes the application of robust non-fragile controllers based on linear matrix inequality (LMI) methods in spacecraft orbit and attitude control.Further explain the design methods of non-fragile state feedback controller, output feedback controller, disturbance observer, and intermediate state observer are further explained under the conditions of considering additive and multiplicative perturbations. And prospects for the development and application of non-fragile control methods are provided for future spacecraft, providing thinking for the research and exploration of robust non-fragile control methods for spacecraft, in order to meet the increasingly complex requirements of high-precision and high stability control tasks for spacecraft.

Key words: non-fragile theory, spacecraft control, linear matrix inequality (LMI), gain perturbation, robust control

中图分类号:

V448

吕佰梁, 刘闯, 岳晓奎. 航天器非脆弱控制理论及应用研究进展[J]. 系统工程与电子技术, 2025, 47(5): 1638-1645.

Bailiang LYU, Chuang LIU, Xiaokui YUE. Advances in theory and application of spacecraft non-fragile control[J]. Systems Engineering and Electronics, 2025, 47(5): 1638-1645.

图/表 4

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