基于扰动观测器的大挠性航天器姿态预见控制  

Attitude preview control for large flexible spacecraft based on disturbance observer

作　　者：包燕伟 管萍[1] 戈新生[1] 曹彧腾 BAO Yanwei;GUAN Ping;GE Xinsheng;CAO Yuteng(School of Automation,Beijing Information Science&Technology University,Beijing 100192,China)

机构地区：[1]北京信息科技大学自动化学院,北京100192

出　　处：《北京信息科技大学学报（自然科学版）》2024年第3期8-15,共8页Journal of Beijing Information Science and Technology University

基　　金：国家自然科学基金重点项目(11732005);国家自然科学基金青年项目(12002058)。

摘　　要：针对航天器的大型挠性附件振动会严重影响其姿态控制的问题,设计了基于扰动观测器的信息融合姿态预见控制器。将挠性附件振动引起的不确定项视作对姿态的复合扰动,设计扰动观测器对该复合扰动进行实时估计。在此基础上,通过融合期望轨迹和系统动态方程等信息,依据信息融合理论,推导了大挠性航天器的姿态预见控制律,用以改善航天器姿态系统的控制性能。所设计的姿态控制算法具有设计过程简单及容易实现等优点。仿真结果表明,所设计的控制策略对挠性附件振动具有较好的抑制作用,航天器姿态角能快速达到期望指令,具有良好的控制特性。Considering that the vibration of large flexible appendages for spacecraft seriously affects its attitude control,an information fusion attitude preview controller based on disturbance observer was designed.The uncertainty caused by the vibration of the flexible appendages was considered as compound disturbance to the attitude.A disturbance observer was designed to estimate the compound disturbance in real time.On this basis,the attitude preview control law of large flexible spacecraft was derived according to the information fusion theory,by fusing information such as desired trajectory and system dynamic equations,resulting in improved control performance of the spacecraft attitude system.The designed attitude control algorithm has the advantages of simple design process and easy implementation.The simulation results indicate that the designed control strategy with good control characteristics can effectively suppress the vibration of the flexible appendages,and the spacecraft attitude angle can reach the desired command quickly.

关 键 词：大挠性航天器 扰动观测器 信息融合 预见控制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]