摘要
研究了挠性航天器姿态机动过程中挠性附件的主动振动控制问题。针对刚性主体上带有挠性梁的航天器,在建立挠性系统动力学模型的基础上,采用滑模变结构控制策略进行挠性航天器的大角度机动控制,为了快速抑制由于刚体运动而激发的弹性振动,在挠性梁上配置压电致动器,并通过速度反馈设计压电致动器的控制律。仿真结果表明,此方法在实现了旋转机动的同时,有效抑制了弹性振动。
The active suppression of vibrations of flexible appendages during large-angle maneuvers of flexible spacecraft. The flexible model to be investigated is a rigid central body with a flexible beam appendage which can unergo a single axis rotation. On the basis of model obtained using the Lagrangian approach, attitude controller acting on the rigid hub, is designed by the sliding mode variable structure control （VSC） method to drive large-angle slew maneuvering. To effectively suppress the simultaneous elastic vibrationin movement,piezoelectric actuators bonded on the surface of flexible beam are designed by using velocity feedback method. Numerical simulation results are presented to show and improved performance for vibration control in the attitude maneuvering of flexible spacecraft can result by combining the advantages of both controller.
出处
《火力与指挥控制》
CSCD
北大核心
2006年第6期31-33,37,共4页
Fire Control & Command Control
关键词
挠性航天器
变结构控制
压电致动器
振动抑制
flexible spacecraft ,variable structure control ,piezoelectric actuators ,vibration suppression
