CAJ | 학술논문

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。
연구료대형위성적분창단진동시험기술，기우정성화분창단진동시험시적측시점가속도향응적폭치상대오차루적최소，추도료일충창단진동시험수입가속도보적계산방법。이모형호결구성위연구대상，대분창단수입조건진행료예시，개전료정성화창단적진동시험연구。시험결과적분석표명，시험결과화이론문합량호，분창단화정성진동시험적향응차이주요취결우정성화창단적빈향함수특성。용제출적방법계산적분창단수입능구보증측시점분창단진동시험시적향응여정성진동시험시적오차최소。
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.