挠性航天器姿态机动直接自适应主动振动控制  

Active vibration control and attitude maneuver of flexible spacecraft via direct adaptive control method

作　　者：刘敏[1] 徐世杰[1] 韩潮[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《北京航空航天大学学报》2013年第3期285-289,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金资助项目(10902003)

摘　　要：针对具有压电陶瓷自敏执行机构的挠性航天器,基于直接自适应控制方法,设计了姿态机动主动振动控制器.首先,验证了在执行机构与敏感器同位安装时,挠性航天器系统的近似严格正实性;然后,设计了挠性航天器的直接自适应姿态机动主动振动控制器,使得航天器输出渐近跟踪具有理想控制性能的参考模型输出;最后,在多组仿真条件下进行了挠性航天器直接自适应姿态机动控制数值仿真.理论分析与仿真结果表明,该方法对航天器惯量和挠性附件模态的不确定性具有强鲁棒性,能够实现对多阶模态的同时控制,对挠性航天器的姿态机动主动振动控制是有效的.An attitude maneuver and active vibration control method was proposed for flexible spacecraft with piezoelectric material as flexible modes active suppression sensors and actuators. Firstly, the almost strict positive real （ASPR） property of flexible spacecraft with collocated sensors and actuators was discussed. Then, the direct adaptive controller was designed to both the attitude maneuver and flexible appendix vibra- tion. Finally, the controller was applied to a flexible spacecraft in different initial conditions. Theoretical anal- ysises and simulation results validate that the controller has strong robustness to spacecraft inertial and flexible model uncertainties, can suppress modes at the same time. Both the attitude maneuver and vibration suppres- sion can be accomplished effectively.

关 键 词：挠性航天器 姿态机动 直接自适应控制 振动抑制 

分 类 号：V448.223[航空宇航科学与技术—飞行器设计]