摘要
针对航天器在进行姿态机动时挠性附件的主动振动控制问题,提出一种基于自适应鲁棒方法和H∞理论相结合的控制方案。为有效地进行振动抑制,主动振动控制器采用H∞状态反馈理论,并且设计时充分考虑由于忽略挠性附件模型高阶模态所带来的结构不确定性,保证振动的快速衰减和方法的鲁棒性。同时,采用自适应鲁棒方法设计姿态控制器,有效地降低干扰和转动惯量不确定性对系统性能的影响,并采用Lyapunov方法分析系统的稳定性。最后,数字仿真结果说明,所提的方法是合理和有效的。
A new approach combining adaptive robust control and theory was proposed for active vibration control of a flexible spacecraft with attitude maneuver control. For effective vibration suppression in flexible appendages, the controller based on state feedback theory was used and the structural uncertainties caused by neglecting higher order modes were fully considered in the design procedure, they ensured rapid decay of vibration and the robustness of the approach. Then, the adaptive robust method was applied to develop the attitude controller of the spacecraft to reduce the influences of disturbances and uncertainties of moment of inertia. Lyapunov theory was adopted to analyze the system stability. Finally, the reasonability and effectiveness of the proposed method was testified via simulations.
出处
《振动与冲击》
EI
CSCD
北大核心
2013年第12期110-115,共6页
Journal of Vibration and Shock
基金
哈尔滨市优秀学科带头人基金项目(2012RFXXG029)
关键词
挠性航天器
姿态机动
自适应鲁棒
振动控制
flexible spacecraft
attitude maneuvering
adaptive robust control
vibration suppression
