摘要
以控制力矩陀螺(Control Moment Gyroscope,CMG)-柔性基础结构耦合系统为研究对象,提出了使用CMG解析动态加速性和柔性基础结构解析加速性对固定界面扰动力进行修正,以获取柔性界面扰动力的分析方法,并将分析结果与Simulink动力学建模与仿真的结果进行了对比与分析。分析与仿真结果吻合较好,可以为扰源-航天器耦合微振动特性分析提供参考。
This paper takes the coupled system of CMG and the flexible mounting structure as the research object,proposes an analysis method to predict the coupled disturbance by correcting the grounded disturbance by using the analytical dynamic accelerance of the CMG and the analytical accelerance of the flexible mounting structure,and then compares the analysis result with that of Simulink dynamic modelling and simulation.Analysis result agrees well with that of simulation,which can provide reference for analysis of the coupled micro-vibration between disturbance source and spacecraft.
出处
《航天器工程》
北大核心
2015年第5期58-65,共8页
Spacecraft Engineering
基金
国家重大科技专项工程
