A novel guidance law using fast terminal sliding mode control with impact angle constraints. (September 2016)

• Record Type: Journal Article
• Authors: Sun, Lianghua; Wang, Weihong; Yi, Ran; Xiong, Shaofeng
• Is Part Of: ISA transactions. Volume 64(2016:Sep.)
• Page Start: 12
• Page End: 23
• Publication Date: 2016-09
• Subjects: Guidance law -- Impact angle constraints -- Extended state observer -- Sliding mode control; Engineering instruments -- Periodicals; Engineering instruments; Periodicals; Electronic journals; 629.805
• DOI: 10.1016/j.isatra.2016.05.004
• Languages: English
• ISSNs: 0019-0578

Abstract

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. Highlights: A novel FTSMC and ESO method is designed to satisfy more optimized trajectory. For the FTSMC design, a function σ ( r ) is introduced in the sliding mode surface. The control method satisfies the requirement of the impact angle constraints.