摘要
高分七号卫星是我国首颗亚米级高分辨率立体测绘卫星,为保证高分辨率光学遥感载荷定位精度要求,采用了隔振装置抑制控制力矩陀螺(CMG)在轨正常工作过程中产生的微振动干扰。文章建立了CMG隔振系统的动力学解析模型,提出了多频率约束下隔振装置的优化设计方法。基于高分七号CMG扰振频率和整星结构频率分布分析,对CMG隔振装置进行了优化设计,进而开展了系统模态仿真分析以及系统固有频率测试和整星隔振试验。仿真分析和试验结果表明:CMG隔振装置前三阶固有频率设计值与试验测试值误差不大于4 Hz,且CMG隔振装置在CMG主要扰动主方向具有94%以上的隔振效果。研究结果可为高分辨率遥感卫星隔振装置的优化设计和分析验证提供理论参考。
As China’s first sub-meter resolution stereo mapping satellite,GF-7 satellite adopts vibration isolation system to attenuate the micro-vibration disturbance generated by the control moment gyroscope(CMG)during its normal operation.The dynamic analytical model of the micro-vibration isolation system is established in this paper,and the corresponding optimal design method of micro-vibration isolation system with multi-frequency constraints is proposed.Based on the analysis of CMG disturbance frequencies and the satellite structure’s natural frequencies of GF-7 satellite,the natural frequency distribution of the micro-vibration isolation system is optimized.Finally,system modal simulation and natural frequency test,as well as the whole satellite micro-vibration isolation test,are conducted,which indicate that the errors of the first 3 natural frequencies of the micro-vibration isolation system is not bigger than 4Hz,and the attenuation effect of the isolation system is more than 94%in the CMG’s main disturbance directions.This study provides references for satellite micro-vibration isolation.
作者
吴琼
张新伟
罗敏
朱佳林
罗文波
WU Qiong;ZHANG Xinwei;LUO Min;ZHU Jialin;LUO Wenbo(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)
出处
《航天器工程》
CSCD
北大核心
2020年第3期123-130,共8页
Spacecraft Engineering
基金
国家重大科技专项工程。
关键词
高分七号卫星
控制力矩陀螺
隔振装置
GF-7 satellite
control moment gyroscope
micro-vibration isolation system
