Modelling and simulation of a mini micro-vibration active control platform for spacecrafts

One of the most important factors affecting the key performance of high performance spacecrafts, such as, the pointing precision is the micro-vibration generated due to disturbance forces of rotary equipments like momentum wheel assembly (MWA). Such disturbances have low amplitudes, their frequencies are less than 600Hz. In a low damped space environment, micro-vibrations have a long decay time and degrade the performance of space craft systems. One mini micro-vibration active control platform was presented here. This platform contained four piezoelectric folded beams as actuators and sensors to control the micro vibration. The dynamic model of a MWA and the active control platform was built based on the finite element method and their modal responses were computed. Linear quadratic Gauss(LQG) control method was used to design the control system. Simulations for the control system's behavior under two kinds of loading conditions were performed. It was shown that this active control platform is effective to control the micro-vibration generated by MWA.