卫星飞轮扰振控制技术研究  

Research on Vibration Disturbance Control of Momentum Wheel

作　　者：刘天雄[1] 范本尧[1] 杨慧[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2009年第1期53-60,共8页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：分析了卫星姿态控制部件飞轮所引起的红外地球敏感器的扰振响应问题和飞轮扰振机理。通过建立飞轮扰振响应动力学模型,提出了通过提高飞轮-红外地球敏感器系统的局部刚度,实现受扰红外地球敏感器系统响应频率解耦,同时调整飞轮-地球敏感器安装板的局部振型,从而实现控制红外地球敏感器响应幅值。根据仿真计算结果给出扰振控制措施的最优方案,飞轮扰振试验结果表明,通过提高局部刚度的减振措施能够有效地解决飞轮扰振问题。The problem of micro-vibration disturbance of momentum wheel for satellite Earth sensor is researched in this paper. The measures of micro-vibration disturbance control are presented through increasing the local stiffness of satellite instrument honeycomb plate. This method not only decouples the frequency response between the Earth sensor and the momentum wheel, but also regulates the vibration mode of the honeycomb plate. The results of numerical simulation and experiment indicate that the proposed method is effective.

关 键 词：卫星 飞轮 地球敏感器 扰振 振动控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]