A control strategy based on feedback control in conjunction with input shaping technique to reduce flexible appendages vibration during a spacecraft’s rotational maneuver was proposed. This strategy could en-sure the achievement of attitude maneuver and the suppression of appendages vibration simultaneously. Con-sidering and the absence of knowledge of modal variables of flexible appendages and the presence of external disturbances, a feedback controller which only requires spacecraft attitude and angular velocity measurement was designed. Combined with the feedback controller, a multiple mode input shaper which used the frequency and damp 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 and suppresses the appendages’ vi-bration successfully during the attitude maneuver. In addition, it can provide strong robustness to system pa-rameter uncertainties.