Event-Triggered-Backstepping-Based Parallel Approaching Guidance Method for Maneuvering Target Interception

作     者：Yaohua Shen Mou Chen Zixuan Zheng Hongzhen Guo 

作者机构：College of Automation EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China School of AstronauticsNational Key Laboratory of Aerospace Flight DynamicsNorthwestern Polytechnical UniversityXian 710072P.R.China 

出 版 物：《Guidance, Navigation and Control》 (制导、导航与控制（英文）)

年 卷 期：2022年第2卷第1期

页      面：77-100页

学科分类：08[工学] 082601[工学-武器系统与运用工程] 082501[工学-飞行器设计] 0826[工学-兵器科学与技术] 082602[工学-兵器发射理论与技术] 0825[工学-航空宇航科学与技术] 

基　　金：supported in part by the National Natural Science Foundation of China under Grants No.62003269 Foundation of Science and Technology on Aerospace Flight Dynamics Laboratory(6142210200308) 

主　　题：Parallel approaching guidance maneuvering target nonlinear disturbance observer event-triggered mechanism backstepping method 

摘      要：In order to achieve a straight ballistic trajectory of missile and reduce the update frequency of the missile normal acceleration for the interception of maneuvering target,a backstepping-based parallel approaching guidance method is designed with nonlinear disturbance observer(NDO)technique and event-triggered(ET)mechanism in this *** order to suppress the adverse e®ect of target maneuver,the NDO is designed to estimate the target maneuvering ***,the NDO-based backstepping method is used to obtain the normal acceleration of missile and realize the parallel approaching *** order to reduce the update frequency of missile normal acceleration,the ET mechanism is employed in the parallel approaching guidance *** the missile trajectory is relatively straight,the normal acceleration of missile remains *** the contrary,if the missile trajectory is not straight,the normal acceleration of missile is updated to make the missile trajectory *** this way,the ET-based parallel approaching guidance can be ***,a determined method for the initial missile°ight-path angle is proposed to keep the normal acceleration of missile at zero in the initial stage of ***,Lyapunov stability analysis method is used to prove that all signals in the closed-loop guidance system are uniformly ultimately ***,simulation results show the e®ectiveness of the proposed guidance method.