大型卫星分舱段振动试验技术  

Technology of Satellite Segment Vibration Test

作　　者：江浩 张利 程世祥 李太平 

机构地区：[1]上海卫星装备研究所第二研究室,上海200240

出　　处：《噪声与振动控制》2015年第2期96-100,共5页Noise and Vibration Control

基　　金：总装备部"十二五"星箭可靠性增长及产品化推进工程项目;卫星环境试验模拟技术规范研究(项目编号:46)

摘　　要：研究了大型卫星的分舱段振动试验技术,基于整星和分舱段振动试验时的测试点加速度响应的幅值相对误差累积最小,推导了一种舱段振动试验输入加速度谱的计算方法。以某型号结构星为研究对象,对分舱段输入条件进行了预示,开展了整星和舱段的振动试验研究。试验结果的分析表明,试验结果和理论吻合良好,分舱段和整星振动试验的响应差异主要取决于整星和舱段的频响函数特性。用提出的方法计算的分舱段输入能够保证测试点分舱段振动试验时的响应与整星振动试验时的误差最小。Vibration test technology of satellite segments was studied. Based on minimizing the accumulative relative errors of the amplitudes of the acceleration response at the testing points between entire satellite vibration test and segment vibration test, the algorithm for solving the input acceleration spectrum for the satellite segment vibration test was derived.Vibration tests were carried out for the entire satellite and its segments with this algorithm. The results show a good coincidence between the tests and the theoretical computation. It is concluded that the response difference between the entire satellite test and the segment test depends on their dynamical characteristics. The presented algorithm can ensure that the segment response is the best approximation of the entirety response of the satellite.

关 键 词：振动与波 卫星 分舱段 振动试验 响应误差 舱段输入 

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]