卫星振动实验中台面加速度控制与过实验研究  

Satellite Vibration Environment Test:Acceleration Control and Over-test

作　　者：王亚波[1] 宋汉文[2] 陈昌亚[3] 齐晓军[3] 

机构地区：[1]复旦大学力学与工程科学系,上海200433 [2]同济大学航空航天与力学学院,上海200092 [3]上海卫星工程研究所,上海200240

出　　处：《力学季刊》2009年第3期427-431,共5页Chinese Quarterly of Mechanics

基　　金：国家自然科学基金资助(10772048)

摘　　要：针对航天飞行器振动台环境实验中的"过实验"问题与振动台控制方式展开研究。本文以被试结构和振动台为统一研究对象进行组合系统动力学建模,详细导出了"真实环境"、"台面加速度控制"和"界面力控制"等三种模式下的台面加速度、界面力、结构测点加速度响应等表达公式,并讨论了加速度控制和力控制下各自形成过实验的原因和频率位置,定义并解释了"双控"模式及其对过实验现象的补偿机理。借助离散算例仿真计算,解释了文中提出的各种概念及其数值效果。The research on the control mode of the shaking table and the over-testing problem of the aircraft in the vibration test were implemented. The dynamic system model by taking the test structure and the shaking table as the research object were built, then The formula of the acceleration of the table, the interface force and the acceleration response of the measuring points at the structure were deduced, in three modes which are the real environment mode, the acceleration control mode and the force control mode. The response amplify function in the acceleration control mode and the response amplify function in the force control mode were defined. The cause for the over-testing problem and the frequency location in the acceleration control and force control mode were discussed. The dual control mode and its compensa- tion mechanism for the over-testing problem were defined and explained. By a simulation example, compare the results in the acceleration control mode and the force control mode were compared, the concepts were explained and verified.

关 键 词：飞行器 振动台实验 过实验 力限振动 双控 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程] O325[理学—一般力学与力学基础]