title: A novel guidance law using fast terminal sliding mode control with impact angle constraints.
abstract: This paper is concerned with the question of, for a missile interception with impact angle constraints, how to design a guidance law. Firstly, missile interception with impact angle constraints is modeled; secondly, a novel guidance law using fast terminal sliding mode control based on extended state observer is proposed to optimize the trajectory and time of interception; finally, for stationary targets, constant velocity targets and maneuvering targets, the guidance law and the stability of the closed loop system is analyzed and the stability of the closed loop system is analyzed, respectively. Simulation results show that when missile and target are on a collision course, the novel guidance law using fast terminal sliding mode control with extended state observer has more optimized trajectory and effectively reduces the time of interception which has a great significance in modern warfare.
authors.affiliation: School of Automation Science and Electrical Engineering, Beihang University (BUAA), Beijing, China. Electronic address: sun649198230@163.com.
authors.forename: Lianghua
authors.initials: L
authors.lastname: Sun
authors.affiliation: School of Automation Science and Electrical Engineering, Beihang University (BUAA), Beijing, China.
authors.forename: Weihong
authors.initials: W
authors.lastname: Wang
authors.affiliation: Beijing Aerospace Measurement & Control Technology Co., Ltd., China.
authors.forename: Ran
authors.initials: R
authors.lastname: Yi
authors.affiliation: Beijing Institute of Space Launch Technology, China.
authors.forename: Shaofeng
authors.initials: S
authors.lastname: Xiong
keywords: Extended state observer; Guidance law; Impact angle constraints; Sliding mode control