柔性航天器姿态快速机动的自适应控制方法

Adaptive Control Method for Fast Attitude Maneuver of Flexible Spacecraft

研究带柔性附件航天器的姿态快速机动控制问题。根据带柔性附件的航天器的动力学模型推导并建立其特征模型。基于所建立的特征模型设计一种自适应控制方法,该方法设计简单,控制器参数物理意义明确,便于调试,可同时实现航天器的姿态快速机动控制和弹性附件的振动快速抑制。理论分析和数学仿真表明,该方法对控制器参数及被控对象的不确定性有很强的鲁棒稳定性和鲁棒性能,能取得比工程中常用的比例-微分(PD)控制更快的机动速度和更好的控制性能。

In this paper, the issue on fast attitude maneuver control of a spacecraft with flexible appendix is studied. The characteristic model is derived based on the dynamics model of the spacecraft with flexible appendix. A characteristic model based adaptive control method is proposed which can achieve the fast attitude maneuver and vibration attenuation simultaneously. The controller is simple to design with explicit physical meanings on its design parameters and ease of the controller tuning. Both theoretical analysis and computer simulation show that the method proposed in this paper has good robust stability and robust performance to both varying controller parameters and plant uncertainties. Comparison with the traditional proportional-derivative （PD） control method shows that the adaptive control method proposed is superior to PD control in achieving faster attitude maneuver and vibration attenuation of the flexible spacecraft.