航天器姿态机动的自适应鲁棒控制及主动振动抑制

针对航天器在进行姿态机动时挠性附件的主动振动控制问题，提出一种基于自适应鲁棒方法和 理论相结合的控制方案。为有效地进行振动抑制，主动振动控制器采用 状态反馈理论，并且设计时充分考虑由于忽略挠性附件模型高阶模态所带来的结构不确定性，保证振动的快速衰减和方法的鲁棒性。同时，采用自适应鲁棒方法设计姿态控制器，有效地降低干扰和转动惯量不确定性对系统性能的影响，并采用Lyapunov方法分析系统的稳定性。最后，数字仿真结果说明，本文提出的方法是合理和有效的。

Adaptive Robust Attitude Maneuver Control of Flexible Spacecraft with Active Vibration Suppression

A new approach combined adaptive robust method and theory is proposed for active vibration control of a flexible spacecraft during attitude maneuver control．For effective vibration suppression in flexible appendages, the controller based on state feedback theory is used and the structural uncertainties caused by neglecting higher order modes are fully considered in the design procedure, which ensures the rapid decay of the vibration and the robustness. Then, adaptive robust method which can reduce the influences of disturbances and uncertainties of moment of inertia is applied to develop the attitude controller of the spacecraft and the Lyapunov theory is introduced to prove the system stability. Finally, the reasonability and effectiveness of the proposed method is testified via the simulation.