考虑姿态控制的控制力矩陀螺微振动抑制研究  

Research on the Micro-vibration Suppression for Control Moment Gyro Considering Satellite Attitude Control System

作　　者：廖宝鹏 臧旭 于开平[1] 柳超然 赵锐 胡蓉平 LIAO Bao-peng;ZANG Xu;YU Kai-ping;LIU Chao-ran;ZHAO Rui;HU Rong-ping(Department of Astronautic Science and Mechanics,Harbin Institute of Technology,Harbin 150001,China;Shanghai Institute of Aerospace Systems Engineering,Shanghai 201109,China)

机构地区：[1]哈尔滨工业大学航天科学与力学系,哈尔滨150001 [2]上海宇航系统工程研究所,上海201109

出　　处：《强度与环境》2020年第4期7-15,共9页Structure & Environment Engineering

基　　金：中央高校基本科研业务费专项资金资助(项目资助编号:HIT.NSRIF.2020014)。

摘　　要：高精度卫星上的光学载荷需要隔离振动来保证指向精度和成像质量,而卫星上用以姿态控制的控制力矩陀螺(CMG)在运行时会对卫星本体产生扰动力和扰动力矩,影响光学载荷的设计指标。本文以CMG这类典型的卫星姿态控制设备为研究对象,通过实验获得其振动特性,并在此基础上考虑姿态控制过程中调姿振动与六自由度隔振系统模态振型之间的耦合引起的共振现象,选择集群式CMG的安装方式实现两者间的稳定运行。而后根据理论分析对隔振系统的设计进行优化和有限元仿真,最后通过实验验证了隔振系统在微振动抑制上的有效性。The optical equipment on the high-precision satellite needs to isolate vibration to ensure the pointing accuracy and imaging quality,while the Control Moment Gyro(CMG)used for satellite attitude control system will generate disturbance forces and torques during operation,which will affect the design index of the optical equipment.In this paper,the CMG,as a typical active satellite attitude control equipment,is taken as the research object.Its vibration characteristics are obtained through experiments and,on this bases,the resonance phenomenon caused by the coupling between the attitude-adjusting vibration and the modal modes of the six-degree-of-freedom vibration isolation system is considered,and the clustered CMGs is selected to achieve stable operation.Then,according to the theoretical analysis,the design of the vibration isolation system is optimized and the finite element simulation is carried out.Finally,the effectiveness of the vibration isolation system in micro-vibration suppression is verified by experiments.

关 键 词：控制力矩陀螺 振动抑制 六自由度隔振 调姿振动 

分 类 号：V414.33[航空宇航科学与技术—航空宇航推进理论与工程]