Three-dimensional time-varying sliding mode guidance law against maneuvering targets with terminal angle constraint

作     者：Xinxin WANG Hongqian LU Xianlin HUANG Yefeng YANG Zongyu ZUO Xinxin WANG;Hongqian LU;Xianlin HUANG;Yefeng YANG;Zongyu ZUO

作者机构：Center for Control Theory and Guidance TechnologyHarbin Institute of TechnologyHarbin 150001China The Seventh Research DivisionBeihang UniversityBeijing 100191China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2022年第35卷第4期

页      面：303-319页

核心收录：

学科分类：08[工学] 081105[工学-导航、制导与控制] 0804[工学-仪器科学与技术] 0811[工学-控制科学与工程] 

基　　金：co-supported by the National Natural Science Foundation of China(Nos.61673034 and 62073019) 

主　　题：Guidance law Maneuvering target Terminal angle constraint Three-dimensional Time-varying sliding mode 

摘      要：This paper deals with the problem of intercepting maneuvering targets with terminal angle constraints for missiles subjected to three-dimensional non-decoupling engagement *** achieve the finite-time interception and satisfactory overload characteristics, a time varying sliding mode control methodology is developed based on a time base generator function. The main feature of the proposed guidance law guarantees the Line-of-Sight(LOS) angles to converge to small neighborhoods of the desired values at the interception time. First, a fractional power extended state observer is used to estimate the unknown target acceleration, which can significantly reduce the adaptive switching gain. The fractional power extended state observer enjoys the advantage of better noise tolerance. Then, a newly designed sliding mode surface is constructed by introducing a time base generator function and the time-varying sliding mode guidance law is developed based on this time-varying sliding surface. The proposed guidance law significantly reduces the overload magnitudes. Numerical simulations are carried out to verify the performance of the proposed guidance law.