针对挠性航天器姿态机动过程中的振动抑制问题,提出了一种新的姿态控制方法.通过对闭环系统的柔性模态设计输入成形器,抑制挠性附件的振动;在此基础上,设计一种包含机动时间、稳定时间及模态振动能量的优化性能指标,选取闭环系统的刚体模态阻尼比,并优化反馈控制参数,保证刚体运动的平稳性.仿真结果表明所提方法可提高挠性航天器姿态机动的性能. Aiming at the problem of vibration suppression in attitude maneuvering of flexible spacecraft, a new attitude control method is proposed. The vibration of the flexible attachment is restrained by designing the input shaper for the flexible mode of the closed-loop system. On this basis, A kind of optimized performance index which includes the maneuvering time, the stabilization time and the modal vibrational energy, the rigid-body mode damping ratio of the closed-loop system is selected, and the feedback control parameters are optimized to ensure the stability of the rigid body motion. Simulation results show that the proposed method can improve the flexibility Sexual spacecraft attitude maneuvering performance.