Terminal Angular Constraint Integrated Guidance and Control for Flexible Hypersonic Vehicle with Dead-Zone Input Nonlinearity  

作　　者：Hewei Zhao 

机构地区：[1]Detection Guidance and Control Teaching Research Section,Naval Aviation University,Yantai 264001,Shandong,China

出　　处：《Journal of Beijing Institute of Technology》2020年第4期489-503,共15页北京理工大学学报（英文版）

摘　　要：This paper presents an integrated guidance and control model for a flexible hypersonic vehicle with terminal angular constraints.The integrated guidance and control model is bounded and the dead-zone input nonlinearity is considered in the system dynamics.The line of sight angle,line of sight angle rate,attack angle and pitch rate are involved in the integrated guidance and control system.The controller is designed with a backstepping method,in which a first order filter is employed to avoid the differential explosion.The full tuned radial basis function(RBF)neural network(NN)is used to approximate the system dynamics with robust item coping with the reconstruction errors,the exactitude model requirement is reduced in the controller design.In the last step of backstepping method design,the adaptive control with Nussbaum function is used for the unknown dynamics with a time-varying control gain function.The uniform ultimate boundedness stability of the control system is proved.The simulation results validate the effectiveness of the controller design.

关 键 词：hypersonic vehicle terminal angular constraint dead-zone input nonlinearity full tuned radial basis function(RBF)neural network(NN) integrated guidance and control 

分 类 号：V448.12[航空宇航科学与技术—飞行器设计]