Abstract: Control moment gyros (CMGs) based on attitude control systems have made of very attractive for space application. However, CMG itself can cause high frequency disturbances that influence the image performance of high resolution remote sensing satellites. For improving the attitude accuracy and stability of these satellites, a multi-degree-of-freedom vibration isolation platform is adopted to reduce the disturbances caused by CMGs, and the application of this platform installed between CMGs and satellite bus is studied. The first step constructs an integrated satellite dynamic model including the vibration isolation platform and flexible solar arrays with Newton-Euler method and Kane equations. The transformation matrix of the vibration isolation platform is then obtained based on the reasonable assumptions. Then the influence of the vibration isolation platform of CMGs on the attitude control system is analyzed, while the influences of the flexible solar arrays on the performance of vibration isolation platform and that on the attitude control stabilization are discussed. The constraint conditions of the parameters of this platform are obtained based on the above analyses. The third part selects the reasonable parameters of the vibration isolation platform and these of the flexible solar arrays. Finally, using these parameters, the performance of the vibration isolation platform on the satellite is testified and the attitude accuracy and stability are predicted by numerical simulations.

Key words: Attitude control, Control moment gyro, Jitter control, Vibration isolation platform