This paper is devoted to developing a closed-loop vibration suppression controller for a satellite with large flexible appendages based on component synthesis vibration suppression (CSVS) method. The dynamics model of a flexible satellite is firstly established by using the Newton–Euler methodology, and the dynamics model of the flywheel is also developed. A novel CSVS method is presented based on zero-vibration differentiator (ZVD), which can guarantee multi-order vibration suppression. Combined with the proposed CSVS method, traditional closed-loop controllers such as PD or sliding mode controllers can be applied to active vibration suppression. The stability of the proposed closed-loop CSVS controller is proved by the Lyapunov theory. Subsequently, the dynamic optimal control allocation algorithm is proposed for six flywheels, and a novel nonsingular fast terminal sliding mode controller is developed to obtain practical voltage control input for the flywheel drive control system. Finally, numerical simulations are carried out to validate the effectiveness of the proposed method.

本文致力于基于分量合成振动抑制（CSVS）方法，为具有较大柔性附件的卫星开发闭环振动抑制控制器。首先使用牛顿-欧拉方法建立了挠性卫星的动力学模型，并且还开发了飞轮的动力学模型。提出了一种基于零振动微分器（ZVD）的CSVS方法，该方法可以保证多阶振动抑制。结合提出的CSVS方法，可以将传统的闭环控制器（例如PD或滑模控制器）应用于主动振动抑制。李雅普诺夫理论证明了所提出的闭环CSVS控制器的稳定性。随后，提出了六个飞轮的动态最优控制分配算法，并开发了一种新颖的非奇异快速终端滑模控制器，以获得飞轮驱动控制系统的实用电压控制输入。最后，通过数值模拟验证了所提方法的有效性。