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针对具有压电陶瓷自敏执行机构的挠性航天器,基于直接自适应控制方法,设计了姿态机动主动振动控制器.首先,验证了在执行机构与敏感器同位安装时,挠性航天器系统的近似严格正实性;然后,设计了挠性航天器的直接自适应姿态机动主动振动控制器,使得航天器输出渐近跟踪具有理想控制性能的参考模型输出;最后,在多组仿真条件下进行了挠性航天器直接自适应姿态机动控制数值仿真.理论分析与仿真结果表明,该方法对航天器惯量和挠性附件模态的不确定性具有强鲁棒性,能够实现对多阶模态的同时控制,对挠性航天器的姿态机动主动振动控制是有效的.
Aiming at the flexible spacecraft with piezoelectric ceramic self-sensing actuator, the attitude maneuver active vibration controller is designed based on the direct adaptive control method.Firstly, it is verified that when the actuator and the sensor are installed in the same position, the flexible spacecraft system Then, the direct adaptive attitude maneuver active vibration controller of flexible spacecraft is designed, which makes the spacecraft output asymptotically track the reference model output with ideal control performance. Finally, under the condition of multi-group simulation The numerical simulation of the attitude adaptive maneuvering of the flexible spacecraft is carried out.Theoretical analysis and simulation results show that this method is robust to the uncertainties of spacecraft inertia and flexible attachment modalities, At the same time, it is effective to control the attitude maneuver active vibration of flexible spacecraft.