倾斜转弯高超声速飞行器滑模变结构解耦控制

针对在倾斜转弯时高超声速飞行器自动驾驶仪设计中系统参数不确定和干扰严重、各通道之间存在强烈耦合的问题,提出了一种全局积分滑模变结构解耦控制方法.该方法基于滑动模态对匹配的参数不确定和外界干扰的不变性原理,采用了一种全局积分型的滑模面,使系统在初始阶段就处于滑模态,同时通过滑模函数反馈削弱参数摄动及干扰产生的滑模误差,实现了各输出之间的全程解耦和鲁棒稳定.仿真结果证实了所提方法具有良好的跟踪性能和鲁棒性,能满足高超声速飞行器倾斜转弯协调控制的要求.

Decoupling controller design for bank-to-turn hypersonic vehicle based on sliding mode variable structure

An adaptive global integral sliding mode control approach is proposed to face the uncertainties and the serious cross coupling among the channels of hypersonic vehicle.This method is based on the invariant principle of sliding mode for uncertainties and disturbance,a global integral sliding is introduced,which makes the initial state of the system to locate at the sliding mode.The sliding mode error caused by disturbance and parameter perturbation is weakened with feedback,which decouples the output of the system and makes the system robust.Numerical simulation proves the efficiency and the robustness of the proposed algorithm,which satisfies the demand of the bank-to-turn hypersonic vehicle.