Active Vibration Suppression and Attitude Control of Coupled Spacecraft

A lumped strategy based on PPF, angular velocity observer and terminal sliding mode control algorithm is proposed for attitude control of coupled spacecraft without angular velocity measurement. Firstly, a PPF combined with fast robust input shaper is designed to suppress the flexible vibration of coupled spacecraft. Then, a finite time terminal sliding mode control algorithm based on the angular velocity estimation error is designed to achieve fast and high-precision attitude control of coupled spacecraft. In simulation, the effectiveness of the proposed control algorithm is verified.