临近空间高超声速飞行器自适应反演滑模控制

Hypersonic Aircraft's Inverse Sliding Mode Adaptive Control Approach in Near Space

针对飞行器非线性动力学系统中存在的高度非线性、多变量耦合及参数不确定等特点,基于反演思想和滑模变结构控制方法,提出了一种飞行器自适应反演滑模控制器设计方法。该方法在反演设计的每一步都采用自适应滑模控制对各种不确定项及外界干扰进行补偿,避免了累积误差,实现对制导指令的鲁棒输出跟踪,并证明了跟踪误差收敛于原点附近任意小邻域。仿真结果验证了该方法满足跟踪性能要求。

In view of aircraft＇s nonlinear dynamics systems highly nonlinear, multivariable coupled and included uncertain parameters, a new inverse sliding mode controller was designed based on inverse design method and the variable structure control scheme. Sliding mode control was adopted in every inverse design to compensate for unmatched uncertainties and unknown disturbance. The approach prevents cumulative error and realizes robust output tracking to guide order. Tracking error is proved to converge to arbitrarily small area near origin. The simulation results show the effectiveness of this method.