针对柔性航天器姿态机动时柔性附件的振动抑制问题，提出了一种基于输入成形和反馈控制联合的主动振动抑制策略，在保证航天器完成指定的姿态机动的同时抑制对系统影响较大的挠性附件的振动。考虑到柔性附件模态变量难以测得以及存在外界干扰力矩，设计了只利用姿态信息的反馈控制器，并根据整个闭环系统的振动频率和阻尼比信息设计前馈鲁棒多模态输入成形器，进一步提高闭环系统的性能。仿真结果表明，应用该策略成功地抑制柔性附件的振动及改善系统的机动时间，并使系统性能对参数的摄动具有很强鲁棒性。

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.