挠性航天器姿态机动直接自适应主动振动控制

刘敏; 徐世杰; 韩潮

挠性航天器姿态机动直接自适应主动振动控制

北京航空航天大学宇航学院, 北京100191

基金项目: 国家自然科学基金资助项目(10902003)

详细信息

作者简介:
刘敏(1984-),男,湖南衡阳人,博士生,liumin@sa.buaa.edu.cn.

中图分类号: V448.22⁺3
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出版历程
- 收稿日期: 2012-02-13
- 网络出版日期: 2013-03-31

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

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

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.
- 挠性航天器 /
- 姿态机动 /
- 直接自适应控制 /
- 振动抑制
Abstract: 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 vibration. Finally, the controller was applied to a flexible spacecraft in different initial conditions. Theoretical analysises 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 suppression can be accomplished effectively.
- flexible spacecraft /
- attitude maneuver /
- direct adaptive control /
- vibration control

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参考文献(1)

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