Simulation and Experiment of an Active-Passive Isolator for Micro-Vibration Control of Spacecraft

Because the optical payloads in the spacecraft is generally large, it is necessary to design a large-size Stewart platform for the attenuation of micro-vibration. However, it is difficult to carry out the ground experiment of integral control system without the influence of gravity. Therefore, the vibration control performance research of the single active-passive rod as the core component of Stewart platform, has become the primary and feasible tasks. Firstly, the active-passive rod structure is introduced, and its equivalent dynamic model, including piezoelectric exciter, damper, force sensor, active piezoelectric rod and concentrated load, is derived. Then the application methods of ideal force feedback control algorithm and PD control algorithm are given. Finally, the simulation and experimental study of the control system are completed respectively. The results show that the designed active-passive rod has good low-frequency micro-vibration isolation performance, which provides a basic reference for the subsequent active-passive vibration isolation platform research.