基于动态输出反馈的挠性航天器主动振动抑制

针对航天器三轴同时姿态机动时挠性附件的振动抑制问题，提出了基于动态输出反馈控制的主动振动抑制方法。采用拉格朗日方法和四元数参数化建立了挠性航天器的非线性模型。利用航天器姿态控制问题固有的无源性，设计了1种仅利用姿态四元数而无需以角速度测量、挠性变形位移及速率测量作为反馈的动态控制规律，并采用压电作动器来抑制挠性结构的振动。基于Lyapunov方法证明了所设计的动态控制器保证了姿态的渐近稳定和模态的振动的衰减。仿真结果表明了所提出的控制方法的可行性和有效性。

Active Vibration Suppression of Flexible Spacecraft Based on Dynamic Output Feedback

A dynamic controller is presented for rest-to-rest flexible spacecraft attitude maneuver with the active vibration suppression. On the basis of the Lagrangian approach and quaternion pammeterization, the nonlinear model of the flexible spacecraft is obtained. This controller does not need the knowledge of modal variables and spacecraft angular velocity. The unavailable measurements of these variables are compensated by appropriate dynamics of the controller, which supplies their estimates. The Lyapunov technique is applied to design this dynamic controller, that ensures the stability of the system. Possible source of instability of the controlled system in real cases are the influence of the flexibility on the rigid motion and the presence of disturbances acting on the structure. In order to attenuate their effects and to damp out the undesirable vibrations affecting the spacecraft attitude, distributed piezoelectric actuators are employed. The simulation results reveal the interest and the practical feasibility of such a control scheme.