控制力矩陀螺微振动时的固有频率波动机理研究  

Study on mechanism of natural frequency fluctuation of CMG during micro-vibration

作　　者：朱泽昊 周徐斌[1] 刘兴天[1,2] 杜冬 冯彦军[1] ZHU Zehao;ZHOU Xubin;LIU Xingtian;DU Dong;FENG Yanjun(Shanghai Institute of Satellite Engineering;Shanghai Aerospace Equipment Micro-Vibration Environment Simulation Engineering Technology Research Center:Shanghai 201109,China)

机构地区：[1]上海卫星工程研究所 [2]上海航天装备微振动环境模拟工程技术研究中心,上海201109

出　　处：《航天器环境工程》2023年第3期233-240,共8页Spacecraft Environment Engineering

基　　金：国家自然科学基金面上项目(编号:51875363);173基础加强重点项目(编号:2020-JCJQ-ZD-125-00)。

摘　　要：为了解控制力矩陀螺(CMG)与蜂窝板的共振机理从而指导微振动地面试验,建立了一个蜂窝板上CMG的等效动力学模型。通过等效板理论和薄板理论推导蜂窝板刚度矩阵的半解析解;结合随框架角变化的CMG惯量矩阵和陀螺矩阵获得CMG固有频率及其波动的变化规律。并提出控制力矩陀螺的设计建议,以期为CMG的地面试验设计提供理论支撑和指导意见,解决CMG与蜂窝板的共振问题。In order to understand the resonance mechanism between the control moment gyroscope(CMG)and the honeycomb panel to guide the micro-vibration ground tests,an equivalent dynamic model of CMG on honeycomb panel was established.A semi-analytical solution of the stiffness matrix of honeycomb panel was derived by the equivalent plate theory and thin plate theory.By combining the CMG inertia matrix and gyroscopic matrix,which vary with the frame angle,the variation pattern of the CMG natural frequency and its fluctuation were obtained.The design suggestion for the CMG was proposed in order to provide theoretical support and guidance for the ground test design of CMG,as well as solve the resonance problem between CMG and honeycomb panel.

关 键 词：控制力矩陀螺 陀螺效应 薄板理论 固有频率 动力学模型 刚度矩阵 

分 类 号：V414.1[航空宇航科学与技术—航空宇航推进理论与工程]