带挠性伸杆机构小卫星的复合振动控制  

COMPOSITE VIBRATION CONTROL METHOD FOR SMALL SATELLITE WITH FLEXIBLE BOOMS

作　　者：任善永[1] 楚中毅[1] 

机构地区：[1]北京航空航天大学惯性技术重点实验室 新型惯性仪表与导航系统技术国防重点学科实验室,北京100191

出　　处：《动力学与控制学报》2013年第1期77-81,共5页Journal of Dynamics and Control

基　　金：国家自然科学基金(50905006);教育部博士学科点专项基金(20091102120027)资助项目~~

摘　　要：为了满足空间探测任务的要求,需采用轻质的伸杆机构支撑各类探测载荷远离卫星本体以避免平台剩磁对空间测量信息的干扰,而挠性伸杆的弹性振动会耦合影响到卫星本体,从而降低卫星本体的姿态控制精度.考虑到挠性附件振动的复杂性及其对航天器本体的耦合影响,采用最优指令整形抑制挠性伸杆的低阶模态振动,并在本体控制中设计自适应扰动抑制滤波器进一步抵消挠性伸杆的残余振动对本体的干扰作用.仿真结果表明,此复合振动控制方法可显著的提高此小卫星的姿态控制精度.In order to avoid the magnetic influence of satellite to the measurement information in the space detection missions, lightweight flexible booms are required to support various types of payload on their tip away from the satellite platform. While the elastic vibration of flexible booms will affect the attitude control accuracy of the satellite. Considering the complexity of appendages vibration and its effect on the satellite, an optimal input shaping（OIS） is applied to the flexible booms to suppress its low order mode vibration, and then an adaptive disturbance rejection filter（ADRF） is designed to reject the disturbance caused by the residual vibration of booms further. Simulation results show that the proposed composite vibration control method can improve the satellite attitude control accuracy greatly.

关 键 词：挠性伸杆 最优指令整形 自适应扰动抑制滤波器 复合振动控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]