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Testing and Analysis of Micro-Vibrations Generated by Control Moment Gyroscope in Different Installation Boundary

The micro-vibrations caused by CMG (Control Moment Gyroscope) can seriously degrade the pointing accuracy and imaging quality of spacecraft. To test the micro-vibrations generated by CMG and obtain the corresponding frequency spectrum characteristics is the key to design the vibration restraining and analyze the vibration transfer properties. In order to simulate the actual installation boundary of CMG on spacecraft, a flexible interface is designed to compare with the rigid interface in traditional testing methods. The results show that: due to the existence of coupling effect between the CMG structure and the flexible interface, the traditional rigid interface is unable to predict the disturbance emitted by CMG in the installation boundary of spacecraft accurately. To study the micro-vibrations produced by CMG in the installation boundary of flexible interface is of great significance.