A novel guidance law using fast terminal sliding mode control with impact angle constraints

被引：35

作者：

Sun, Lianghua ^{[1
]}

Wang, Weihong ^{[1
]}

Yi, Ran ^{[2
]}

Xiong, Shaofeng ^{[3
]}

机构：

[1] Beihang Univ BUAA, Sch Automat Sci & Elect Engn, Beijing, Peoples R China

[2] Beijing Aerosp Measurement & Control Technol Co L, Beijing, Peoples R China

[3] Beijing Inst Space Launch Technol, Beijing, Peoples R China

来源：

ISA TRANSACTIONS | 2016年 / 64卷

关键词：

Guidance law; Impact angle constraints; Extended state observer; Sliding mode control; EXTENDED STATE OBSERVER; LINEAR-SYSTEMS; TIME; TARGETS; MISSILE; DESIGN;

D O I：

10.1016/j.isatra.2016.05.004

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

This paper is concerned with the question of, for a missile interception with impact angle how to design a guidance law. Firstly, missile interception with impact angle constraints is secondly, a novel guidance law using fast terminal sliding mode control based on extended state is proposed to optimize the trajectory and time of interception; finally, for stationary targets, velocity targets and maneuvering targets, the guidance law and the stability of the closed loop system analyzed and the stability of the closed loop system is analyzed, respectively. Simulation results that when missile and target are on a collision course, the novel guidance law using fast terminal mode control with extended state observer has more optimized trajectory and effectively reduces time of interception which has a great significance in modern warfare. (C) 2016 ISA. Published by Elsevier Ltd. All rights reserved.

引用

页码：12 / 23

页数：12

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