大型卫星分舱段振动试验技术

摘要

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 coinci-dence between the tests and the theoretical computation. It is concluded that the response difference between the entire satel-lite 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.%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。