Missile guidance law design based on free-time convergent error dynamics  

作　　者：LIU Yuanhe XIE Nianhao LI Kebo LIANG Yan’gang 

机构地区：[1]Aviation Combat and Service Institute,Aviation University of Air Force,Changchun 130022,China [2]College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410072,China [3]Naval Aeronautical University,Yantai 264000,China

出　　处：《Journal of Systems Engineering and Electronics》2024年第5期1315-1325,共11页系统工程与电子技术（英文版）

基　　金：supported by the National Natural Science Foundation of China(12002370).

摘　　要：To solve the finite-time error-tracking problem in mis-sile guidance,this paper presents a unified design approach through error dynamics and free-time convergence theory.The proposed approach is initiated by establishing a desired model for free-time convergent error dynamics,characterized by its independence from initial conditions and guidance parameters,and adjustable convergence time.This foundation facilitates the derivation of specific guidance laws that integrate constraints such as leading angle,impact angle,and impact time.The theoretical framework of this study elucidates the nuances and synergies between the proposed guidance laws and existing methodologies.Empirical evaluations through simulation comparisons underscore the enhanced accuracy and adaptability of the proposed laws.

关 键 词：guidance design free-time convergence error dynamics approach impact angle constraint impact time constraint 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置] TJ765[自动化与计算机技术—控制科学与工程]