One of the most important factors that affects the key performance of high performance spacecraft, such as the pointing precision is the micro-vibration generated due to the disturbed forces of rotary equipments like Momentum Wheel Assembly (MWA).Such disturbances are of low amplitude, less than 600Hz.In the low damped space environment, micro-vibrations have long decay time and degrade the performance of systems.One mini micro-vibration active control platform is addressed.This platform consist four piezoelectric folded beams as actuators and sensors to control the micro vibration.The model of MWA and the active control platform have been built based on finite element method and the modal responses have been carried out for the system.Linear quadratic Gauss(LQG) control method have been used to design the control system.Simulations of the system under two kinds of loading conditions have been studied.It’s shown that this active control platform is effective in controlling the vibration generated by MWA.