典型文献
Saturated super-twisting sliding mode missile guidance
文献摘要：
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 tar-gets is demonstrated.
文献关键词：
中图分类号：
作者姓名：
Mian GONG;Di ZHOU;Xinguang ZOU
作者机构：
School of Astronautics,Harbin Institute of Technology,Harbin 150001,China;School of Electronics and Information Engineering,Harbin Institute of Technology,Harbin 150001,China
文献出处：
引用格式：
[1]Mian GONG;Di ZHOU;Xinguang ZOU-.Saturated super-twisting sliding mode missile guidance)[J].中国航空学报（英文版）,2022(10):292-300
A类：
B类：
Saturated,twisting,sliding,mode,missile,guidance,This,paper,concentrates,developing,terminal,law,against,highly,maneuvering,target,whose,acceleration,very,close,that,even,exceeds,normal,finite,period,new,saturated,algorithm,proposed,applied,has,advantages,simple,structure,easy,parameter,tuning,rules,full,utilization,limit,control,input,designed,then,employed,system,Simulation,its,superior,performance,strong,gets,demonstrated
AB值：
0.541012
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