航天器固定时间姿态饱和控制  

Saturated Fixed-time Attitude Control for Spacecraft

作　　者：肖超 郭永 邸富强 王力浩 李爱军[1] 王长青[1] XIAO Chao;GUO Yong;DI Fuqiang;WANG Lihao;LI Aijun;WANG Changqing(School of Automation,Northwestern Polytechnical University,Xi’an 710129,China;Xi’an Modern Control Technology Research Institute,Xi’an 710065,China)

机构地区：[1]西北工业大学自动化学院,西安710129 [2]西安现代控制技术研究所,西安710065

出　　处：《宇航学报》2025年第1期141-149,共9页Journal of Astronautics

基　　金：国家自然科学基金(62273277);陕西省国际科技合作计划(2023-GHZD-32)。

摘　　要：针对面临未知外部扰动与执行器饱和约束的航天器姿态控制系统,提出了一种鲁棒自适应抗饱和固定时间控制策略,解决了航天器在外部扰动与执行器饱和约束下的姿态跟踪控制问题。首先,基于齐次性理论,设计了一种可在固定时间内收敛到零的非奇异全阶终端滑模面。然后,结合所提出的滑模面与自适应控制,设计了一种鲁棒自适应抗饱和控制器,可确保航天器系统状态在固定时间内完成对期望指令的跟踪。最后,通过理论分析和数值仿真验证了所提出控制策略的有效性,其可为外部扰动与执行器饱和约束下航天器的姿态跟踪提供高精度控制方法。For the spacecraft attitude control system subject to unknown external disturbances and actuator saturation,a robust adaptive anti-saturation fixed-time control strategy is proposed to address the attitude tracking control problem.Initially,a non-singular full-order terminal sliding mode surface,which converges to zero within a fixed time,is designed utilizing homogeneity theory.Subsequently,by integrating this sliding mode surface with adaptive control,a robust adaptive anti-saturation controller is developed.This controller ensures that the spacecraft system's state tracks the desired command within a fixed time frame.The effectiveness of the proposed control strategy is substantiated through both theoretical analysis and numerical simulation,providing a high-precision control method for spacecraft attitude tracking under the aforementioned constraints.

关 键 词：航天器姿态控制 执行器饱和 固定时间控制 终端滑模控制 自适应控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]