Feedback control in conjunction with input shaping for flexible spacecraft vibration suppression

A control strategy based on feedback control in conjunction with input shaping technique to reduce flexible appendages vibration during spacecraft's rotational maneuver was proposed. This strategy can ensure the achievement of attitude maneuver and appendages vibration suppression simultaneously. Considering the absence of modal variables knowledge of flexible appendages and the presence of external disturbances, a feedback controller which only requires the informations of spacecraft attitude and angular velocity was designed. Combined with the feedback controller, a multiple mode input shaper which utilizes the frequency and damping ratio of the whole closed loop system was designed to enhance the system performance. Simulation results show that the presented control strategy reduces the system response time duration and suppresses the appendages' vibration successfully during the attitude maneuver. In addition, it can provide strong robustness against system parameter uncertainties.