挠性航天器退步自适应姿态机动及主动振动控制  

Backstepping Adaptive Attitude Maneuver and Active Vibration Control of Flexible Spacecraft

作　　者：刘敏[1] 杨军[1] 李学林[1] 徐世杰[2] 

机构地区：[1]中国空间技术研究院,北京100094 [2]北京航空航天大学宇航学院,北京100191

出　　处：《空间控制技术与应用》2015年第1期9-14,共6页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(11302244)

摘　　要：针对带有分布式压电陶瓷执行机构的挠性航天器姿态机动与主动振动控制问题,提出了一种退步直接自适应一体化控制方法.首先,建立了挠性航天器姿态机动与主动振动控制的模型,并分析了动力学子系统的近似严格正实性;然后,采用退步直接自适应控制方法,设计了挠性航天器的姿态机动主动振动控制器,并证明了控制闭环系统的稳定性;最后,进行了不同仿真条件下的数学仿真验证.理论分析与数学仿真结果表明,该控制方法不依赖航天器参数,对系统参数不确定性具有强鲁棒性,能有效抑制挠性附件的振动,对挠性航天器的控制是有效的.A backstepping direct adaptive attitude and vibration control method is proposed for flexible spacecraft with piezoelectric vibration suppression sensor and actuator pairs. Firstly,the attitude maneuver and vibration control model of a flexible spacecraft is derived,and the almost strict positive real property of the dynamics subsystem is discussed. Then,an attitude maneuver and vibration controller is designed based on backstepping directive control method,and the closed-loop stability is proved. Finally,the controller is applied to a flexible spacecraft in different initial conditions. Theoretical analysis and simulation results validate that the controller has strong robustness against the spacecraft inertial and flexible model uncertainties. Both the attitude maneuver and vibration suppression can be accomplished effectively.

关 键 词：挠性航天器 姿态机动 主动振动控制 直接自适应控制 

分 类 号：V448.223[航空宇航科学与技术—飞行器设计]