挠性航天器非线性滑动模态控制和实验研究

THE NONLINEAR SLIDING MODE CONTROL AND EXPERIMENT RESEARCH FOR FLEXIBLE SPACECRAFT

挠性卫星在控制受限情况下 ,采用简单线性滑动模态设计的变结构控制器不能保证在整条开关线上存在滑动模态 ,因此在大角度机动控制中就不能保证过渡过程品质。本文针对这个问题 ,采用抛物线型滑动模态设计了一种过渡过程性能很好的变结构控制器 ,并且分析了这种非线性滑动模态的稳定性。

In traditional variable structure control scheme the sliding plane is linear and the sliding mode can not be realized on the whole sliding plane when control value is limited.The control system always overshoots in large angle maneuvers.This paper presents a nonlinear sliding mode variable structure control law which has particularly good transition process, and analyses the stability of the scheme.The validity of this scheme was validated by physical simulation at last.