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针对进行大角度快速机动的刚柔耦合卫星,提出了有限时间控制方法。首先在考虑卫星本体运动与柔性附件变形耦合效应的情况下,建立一次近似刚柔耦合动力学模型。其次假设柔性附件振动信息可测,考虑外部干扰和转动惯量不确定性,基于非奇异快速终端滑模(NFTSM)原理,设计了有限时间全状态反馈控制器,根据Lyapunov原理证明其有限时间稳定性;进一步考虑柔性附件振动信息不可测的实际情况,设计了非奇异快速终端滑模动态输出反馈控制器,该控制器仅利用角度和角速度信息就可以实现有限时间快速姿态稳定。最后对提出的控制算法进行了数值仿真,并通过与现有文献中控制算法进行对比,验证了本文设计的输出反馈控制算法的有限时间快速稳定特性。
Aiming at the rigid-flexible coupled satellite with large-angle and fast maneuver, a finite-time control method is proposed. Firstly, considering the coupling effect between satellite body motion and flexible attachment, an approximate rigid-flexible coupling dynamic model is established. Secondly, based on the non-singular fast terminal sliding mode (NFTSM) theory, a finite state all-state feedback controller is designed based on the assumption that the vibration information of the flexible attachment is measurable. Considering the uncertainties of external disturbance and moment of inertia, the finite state time- Considering the fact that the vibration information of the flexible attachment is unmeasurable, a non-singular and fast terminal sliding mode dynamic output feedback controller is designed. The controller can achieve the fast attitude stabilization for a limited time by using only the angular and angular velocity information. Finally, the proposed control algorithm is numerically simulated and compared with the existing control algorithms to verify the finite-time fast stability of the proposed output feedback control algorithm.