Nonlinear Control Method for Hypersonic Vehicle Based on Double Power Reaching Law of Sliding Mode  

作　　者：Liu Rong Zhang Heng Liang Jin 

机构地区：[1]Key Laboratory of UAV’s Advanced Technology(Nanjing University of Aeronautics and Astronautics),Ministry of Industry and Information Technology [2]College of Automation Engineering,Nanjing University of Aeronautics and Astronautics [3]Key Laboratory of Aircraft Control Integration Technology,Aviation Industry Xi’an Flight Automatic Control Research Institute

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2018年第5期849-857,共9页南京航空航天大学学报（英文版）

基　　金：supported by the Advanced Research Foundation of Ministry of Army Equipment Development in 13th Five-Year(No.30102080101);the Aviation Science Funds(No.20165852052);the Fundamental Research Funds for the Central Universities(No.NS2018059)

摘　　要：The intelligence nonlinear control scheme via double power reaching law based sliding mode control method is proposed to solve the problems of model uncertainties and unknown outside disturbances.Firstly,the aerodynamic parameters of the morphing vehicle are replaced with curve-fitted approximation to build the accurate model for control design in the hypersonic flight.Then the nonlinear vehicle model is transformed into the strict feedback multi-input/multi-output nonlinear system by using the input-output feedback linearization approach.At the same time,the disturbance observer is used to approximate the unknown disturbance,and the sliding mode method is used to solve the problem of non-matching and uncertainty.Finally,according to the buffeting problem in sliding mode control,the double power is improved.Simulation results show that the proposed method can ensure the global stability of the closed-loop system,and has good tracking and robust performance.The intelligence nonlinear control scheme via double power reaching law based sliding mode control method is proposed to solve the problems of model uncertainties and unknown outside disturbances.Firstly,the aerodynamic parameters of the morphing vehicle are replaced with curve-fitted approximation to build the accurate model for control design in the hypersonic flight.Then the nonlinear vehicle model is transformed into the strict feedback multi-input/multi-output nonlinear system by using the input-output feedback linearization approach.At the same time,the disturbance observer is used to approximate the unknown disturbance,and the sliding mode method is used to solve the problem of non-matching and uncertainty.Finally,according to the buffeting problem in sliding mode control,the double power is improved.Simulation results show that the proposed method can ensure the global stability of the closed-loop system,and has good tracking and robust performance.

关 键 词：HYPERSONIC vehicle disturbance observer DOUBLE POWER SLIDING mode BUFFETING 

分 类 号：TN247[电子电信—物理电子学]