中文摘要：

针对挠性航天器姿态机动控制中存在的参数不确定性、外部干扰、挠性附件振动及挠性模态不易直接测量的问题，提出一种具有干扰抑制的自适应输出反馈机动控制器设计方法。设计中无需忽略挠性附件和中心刚体的耦合，利用挠性附件固有物理特性构造一种结构简单的开环模态观测器，然后用以此获得的模态估计信息及可测量的姿态四元数和角速度信息，基于自适应反步设计方法进行反馈控制器设计，实现了无需增加压电作动器即可增强挠性模态阻尼性，保证了闭环系统在参数不确定存在和外部干扰作用下的姿态稳定鲁棒性和挠性模态振动抑制性，同时对外部干扰力矩具有L：增益抑制性能。理论证明和仿真研究结果均表明了所设计控制器的有效性和可行性。

英文摘要：

According to the attitude maneuver control problem of a flexible spacecraft with parametric un- certainties, external disturbances, elastic vibration and the unmeasured vibration variables, a design scheme is proposed for an adaptive output feedback maneuver controller with disturbance attenuation. In the design of this controller, the coupling between flexible appendage and rigid body was not neglected. An open-loop modal observer with simple structure was constructed by utilizing the inherent physical properties of flexible appendages, and then a feedback controller on the obtained modal estimates, meas- urable quaternion and angular velocity was designed based on the adaptive backstepping technique. The proposed controller enhances the damping without adding piezoelectric actuator and guarantees the robust stability of the closed-loop system and also the L2-gain performance for the external torque disturbance un- der the case with parametric uncertainties and external disturbances. Both theoretic demonstration and simulation results illustrate the effectiveness and feasibility of the proposed control scheme.