Abstract：The micro-vibration caused by the control moment gyros (CMG) would result in lowering the image quality of the optical sensing equipment on the satellite. Therefore, it’s necessary to design a device to resist micro-vibration. In this paper, the frequency character of CMG and the natural frequency of satellite were analyzed. Also, the FEA model was built to conduct parameterized design which involves modal control method. The vibration test of the whole isolation system was conducted under both unit-test and satellite-level test conditions to verify the pre-design. In the main vibration direction, the device could provide a maximized decrease in acceleration amplitude up to 97%, and there was only a deviation of 3Hz between the tested natural frequency and the simulated one. Therefore, the optimized isolation device may contribute to the other satellites in the future.
孙晓晨，郭彤，李晓莉，姚小松，杨若宸. 某型号卫星控制力矩陀螺隔振装置设计和试验技术研究[J]. 振动与冲击, 2023, 42(17): 135-143.
SUN Xiaochen, GUO Tong, LI Xiaoli, YAO Xiaosong, YANG Ruochen. Design and test technology of a certain satellite control moment gyro vibration isolation device. JOURNAL OF VIBRATION AND SHOCK, 2023, 42(17): 135-143.
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