控制受限的挠性航天器姿态机动自适应变结构输出反馈控制

针对挠性航天器飞轮输出力矩受限情况下的姿态机动问题，提出了一种仅利用输出信息的自适应变结构输出反馈控制方法。在基于非线性和低阶模态的动力学模型基础上，给出了滑模存在条件以及自适应变结构输出反馈控制器设计的方法，并采用Lyapunov方法分析了滑动模态的存在性及稳定性。最后，将本文提出的控制方法应用于挠性航天器的姿态机动控制，并与传统的控制方法进行比较。数值仿真研究：在反作用飞轮的控制受限条件下，完成姿态机动的同时，有效地抑制挠性附件的振动；此方法具有设计简单、易于实现和鲁棒性好等特点。

Adaptive Variable Structure Output Feedback Maneuvering Control for Flexible Spacecraft with Input Constraints

This paper is concerned with attitude maneuvering control of a flexible spacecraft in the presence of uncertainty/external disturbances as well as control input saturation.To satisfy pointing requirements and simultaneously suppress vibrations,an adaptive output feedback sliding mode control(AOFSMC) was design,in which control input saturation is explicitly taken into consideration.The controller has the ability to reject the disturbance,deal with uncertainty and to ensure that the system trajectories globally converge to the sliding mode.To study the effectiveness of the corresponding control scheme,the traditional proportional-derivate(PD) and adaptive static output feedback control (ASOF) case is also developed for the control system.Both analytical and numerical results are presented to show the theoretical and practical merit of this approach.