星上控制力矩陀螺的高频抖动减振研究  

High Frequency Vibration Isolation of CMG for Satellite

作　　者：张尧[1] 徐世杰[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《宇航学报》2011年第8期1722-1727,共6页Journal of Astronautics

基　　金：国家自然科学基金(10902003)

摘　　要：研究卫星姿态控制执行机构的隔振问题。首先介绍了隔振器原理及其参数选择依据,重点建立了含有隔振平台的整星动力学模型,并使用金字塔构型的CMGs作为执行机构。通过使用Adams工程软件验证了所建立的隔振平台动力学模型的正确性,最后通过整体仿真,验证了隔振装置对星体姿态稳定度的改善作用,为CMGs的隔振系统工程化设计提供理论支持。The high frequency vibration isolation of Control Moment Gyro（CMG） for satellites is discussed in this paper.Firstly,the present study expatiates the theory of the vibration isolator and the reason of choosing certain parameters.Then,a whole-satellite dynamics model with a vibration isolation platform and pyramid configuration CMGs is proposed.The validity of the dynamics model of the vibration isolation platform is then verified by using the commercial software Adams.Finally,numerical examples based on a satellite are provided,the simulation results illustrate the ameliorative effect of vibration isolation device on the satellite attitude stabilization.It is hoped that the present study can contribute to analysis of the influence of vibration isolation system on the whole satellite and can provide the theoretical support for the engineering implementation of the vibration isolation platform for CMGs.

关 键 词：控制力矩陀螺 抖动控制 隔振平台 姿态控制 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]