Abstract: Aiming at the special index requirement of microvibration spectrum integration of advanced payloads developed by quantum science experiments, time-frequency transfer experiments and other projects, a separate active vibration isolation approach was investigated. The separated vibration isolation approach divides a satellite into a payload module (PM) and a support module (SM). Considering the connection of flexible cables and limit springs between the two modules, the dynamic model was first established. Subsequently, a six-degree-of-freedom vibration isolation controller based on acceleration feedback was designed. Considering the electrical noise of the control and drive circuit, the vibration isolation performance of the payload module with respect to the support module was analyzed in the time domain and frequency domain. The simulation results show that the cumulative power spectral density (PSD) of the PM's acceleration within 0.5~200Hz is less than 2μgn after active vibration isolation. Finally, the influence of the controller parameters on the cumulative PSD of the payload module′s acceleration was analyzed. The separated active vibration isolation method provides a technical way for the vibration isolation of ultra-quiet scientific satellite.

Key words: separated scientific satellite, active vibration isolation, dynamic modeling, micro vibration, spectrum analysis