高超声速飞行器非线性干扰观测器动态面滑模控制  

A New Dynamic Surface Sliding Mode Control Scheme for Hypersonic Aircraft Based on Nonlinear Disturbance Observer

作　　者：梁帅[1] 孙秀霞[1] 刘树光[1] 刘日[1] 唐强[2] 

机构地区：[1]空军工程大学航空航天工程学院,西安710038 [2]西安飞行自动控制研究所,西安710065

出　　处：《空军工程大学学报（自然科学版）》2015年第3期7-11,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：航空科学基金资助项目(20135896025)

摘　　要：针对高超声速飞行器纵向模型具有高度非线性、多变量耦合以及参数不确定等特点,提出一种基于非线性干扰观测器的高超声速飞行器动态面滑模控制方案。利用非线性干扰观测器观测未知干扰,并通过动态面滑模设计控制器使观测误差指数收敛,针对高度和速度进行了稳定性分析,采用动态逆的方法设计速度控制器,控制律的设计保证了闭环系统的半全局一致稳定。仿真结果表明,该控制方案能够有效地的克服非线性干扰的影响,提高系统的鲁棒性。Aimed at that longitudinal hypersonic vehicle model has some features such as high nonlinearity, multivariable coupling and parameter uncertainty,etc.,a new dynamic surface sliding mode control scheme for hypersonic aircraft based on nonlinear disturbance observer is proposed.In the scheme nonlin-ear disturbance observer is used for observing the unknown nonlinear disturbance and the observer is in ex-ponential convergence by selecting the design parameters,then the dynamic surface sliding mode control is designed,and the proposed control scheme can be adopted to guarantee the semi-consistent and stable global system.Simulation results demonstrate that the use of the proposed control scheme can effectively overcome the nonlinear disturbance and enhance the robust performance of the system.

关 键 词：非线性干扰观测器 高超声速飞行器 动态面滑模控制 鲁棒性 

分 类 号：V249.122.1[航空宇航科学与技术—飞行器设计]