某型号卫星控制力矩陀螺隔振装置设计和试验技术研究  

Design and test technology of a certain satellite control moment gyro vibration isolation device

作　　者：孙晓晨 郭彤 李晓莉 姚小松 杨若宸 SUN Xiaochen;GUO Tong;LI Xiaoli;YAO Xiaosong;YANG Ruochen(Innovation Academy for Microsatellites,Chinese Academy of Sciences(CAS),Shanghai 201304,China)

机构地区：[1]中国科学院微小卫星创新研究院,上海201304

出　　处：《振动与冲击》2023年第17期135-143,共9页Journal of Vibration and Shock

摘　　要：针对某型号卫星控制力矩陀螺(control moment gyroscope,CMG)在轨工作产生的微振动对星载光学遥感载荷成像产生扰动的问题,文章对CMG扰振特性及卫星基频分析,建立了CMG隔振系统模型,基于CMG扰振特征频率完成了系统错频及隔振装置参数化优化设计,并通过地面单机级及整星级微振动试验对有限元建模结果进行验证。试验结果表明,在主要扰振方向上,主要扰振频点处最佳可实现97%隔振效果,系统的固有频率在仿真与敲击实验对比中误差低于3 Hz,对其他型号卫星的微振动隔振装置优化设计具有参考价值。Here,aiming at the problem of micro-vibration generated by a certain model of satellite control moment gyroscope(CMGs)during in orbit operation having disturbance to imaging of satellite-borne optical remote sensing loads,disturbance characteristics of CMG and satellite’s 1st natural frequency were analyzed,the CMG vibration isolation system model was established,and the system error frequency design and vibration isolation device parametric optimization design were completed based on CMG disturbance characteristic frequency.The finite element modeling results were verified through ground single level and whole star level micro-vibration tests.The test results showed that in main disturbance direction,the optimal vibration isolation effect of 97%can be achieved at main disturbance frequency point;for the system’s 1 st natural frequency,comparing the simulated value with the measured value in knocking tests only has an error of less than 3 Hz;the study results can provide a reference for optimization design of micro-vibration isolation devices of other satellites.

关 键 词：光学遥感卫星 微振动 错频设计 

分 类 号：TH113[机械工程—机械设计及理论]