Closed-form guidance law for velocity maximization with impact angle constraint

作     者：ZHANG Jiahui WEN Qiuqiu ZHANG Jiahui;WEN Qiuqiu

作者机构：School of AutomationBeijing Institute of TechnologyBeijing 100081China School of Aerospace EngineeringBeijing Institute of TechnologyBeijing 100081China 

出 版 物：《Journal of Systems Engineering and Electronics》 (系统工程与电子技术（英文版）)

年 卷 期：2024年第35卷第5期

页      面：1295-1303页

核心收录：

学科分类：08[工学] 081105[工学-导航、制导与控制] 0804[工学-仪器科学与技术] 0811[工学-控制科学与工程] 

主　　题：missile guidance law proportional-navigation guidance impact angle 

摘      要：Final velocity and impact angle are critical to missile *** efficient guidance law with compre-hensive consideration of the two performance merits is challeng-ing yet remains less ***,this paper seeks to solve a type of optimal control problem that maximizes final velocity subject to equality point constraint of impact angle *** is proved that the crude problem of maximizing final velocity is equivalent to minimizing a quadratic-form cost of *** closed-form guidance law is henceforth derived using optimal control *** derived analytical guidance law coincides with the widely-used optimal guidance law with impact angle constraint(OGL-IAC)with a set of navigation parameters of two and *** this basis,the optimal emission angle is determined to further increase the final *** derived optimal value depends solely on the initial line-of-sight angle and impact angle constraint,and thus practical for real-world *** proposed guidance law is validated by numerical *** results show that the OGL-IAC is superior to the benchmark guidance laws both in terms of final velocity and missing distance.