基于模糊PD控制的柔性航天器振动抑制研究  

Research on Vibration Suppression of Flexible Spacecraft Based on Fuzzy PD Control

作　　者：支敬德 戈新生[2] ZHI Jing-de;GE Xin-sheng(School of Automation,Bijing Information Science&Technology University,Beijing 100192,China;School of Mechanical and Electrical Engineering,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 [2]北京信息科技大学机电工程学院,北京100192

出　　处：《计算机仿真》2022年第3期52-56,209,共6页Computer Simulation

基　　金：国家自然科学基金重点资助项目(11732005)。

摘　　要：研究柔性结构振动与航天器姿态运动的刚柔耦合的控制问题,采用非约束模态法对柔性航天器构建适合控制器设计的状态空间模型。针对柔性航天器姿态机动控制问题,根据期望姿态角度与实际姿态角度给出的姿态信息得出姿态误差信号,以此信号设计了一种PD控制律。考虑到柔性航天器初始阶段姿态角速度过大的情况,在原有的PD控制基础上,加入了模糊控制,不仅减小了控制力矩输出,而且满足柔性航天器姿态机动要求的同时能有效抑制振动。数值仿真结果表明,所设计的模糊PD控制律是有效可行的,且有良好的控制性能。The problem of rigid and flexible coupling between the vibration of flexible structure and the attitude motion of spacecraft was studied in the paper.Aiming at the attitude maneuver control problem of flexible spacecraft,the attitude error signal was obtained according to the attitude information from the expected attitude angle and the actual attitude angle,and a PD control law was designed based on the signal.Considering that the attitude angular velocity of the flexible spacecraft is too large at the initial stage,fuzzy control was added on the basis of the original PD control,which not only reduces the control torque output,but also meets the attitude maneuver requirements of the flexible spacecraft and can effectively suppress the vibration.Numerical simulation results show that the proposed fuzzy PD control law is effective and feasible,and has good control performance.

关 键 词：柔性航天器 非约束模态 模糊控制 姿态机动 振动抑制 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]