Saturated super-twisting sliding mode missile guidance  

作　　者：Mian GONG Di ZHOU Xinguang ZOU 

机构地区：[1]School of Astronautics,Harbin Institute of Technology,Harbin 150001,China [2]School of Electronics and Information Engineering,Harbin Institute of Technology,Harbin 150001,China

出　　处：《Chinese Journal of Aeronautics》2022年第10期292-300,共9页中国航空学报（英文版）

基　　金：National Natural Science Foundation of China(No.61773142)。

摘　　要：This paper concentrates on developing a missile terminal guidance law against a highly maneuvering target whose maneuvering acceleration is very close to that of the missile or even exceeds the missile normal acceleration in a finite period of time.A new saturated super-twisting algorithm is proposed and applied to the design of missile guidance law.The proposed algorithm has the advantages of simple structure,easy parameter tuning rules and a full utilization of the limit control input.The designed saturated super-twisting sliding mode guidance law is then employed in a missile guidance system.Simulation and its superior performance against strong maneuvering targets is demonstrated.

关 键 词：Highly maneuvering target Input saturation Missile guidance control Robust control Sliding mode control Super-twisting algorithm 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]