带有不确定参数的挠性航天器机动控制

Control of Flexible Spacecraft Attitude Maneuver with Uncertain Parameters

将输入成型技术与闭环反馈控制结合设计,实现航天器机动控制中挠性附件的振动抑制.针对挠性航天器姿态机动过程中,系统惯量、模态矩阵等参数的不确定性对输入成型器抑制挠性附件振动的影响,提出基于最大允许残余振动的输入成型器建模参数的计算方法,并量化分析不确定参数对挠性附件振动的影响,为选择合适的成型器提供定量的理论依据.该方法可降低传统输入成型器设计的保守性,有利于提高控制性能.仿真结果表明,将系统存在的不确定参量考虑在内,系统振动抑制效果要优于不考虑的情况.

Input shaping and closed-loop feedback control are combined to realize the vibration reduction of spacecraft with flexible appendages during the attitude maneuver control. To ensure the validity of input shaping for suppressing the vibration of flexible appendages, the effect of uncertain parameters, such as system inertia and modal matrix, are considered during the attitude maneuver. A method to calculate the model parameters of input shaper, which is based on maximum residual vibration, is proposed. And the impact of uncertain parameters to vibration reduction of flexible appendages is quantitatively analyzed, which can be as a theoretical basis for selecting proper input shaper. It reduces the conservation of traditional input shaper and contributes to enhance the control performance. Simulation analysis indicates that the vibration suppression with considering system uncertain parameters is better than without them.