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

作　　者：ZHANG Jiahui WEN Qiuqiu 

机构地区：[1]School of Automation,Beijing Institute of Technology,Beijing 100081,China [2]School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China

出　　处：《Journal of Systems Engineering and Electronics》2024年第5期1295-1303,共9页系统工程与电子技术（英文版）

摘　　要：Final velocity and impact angle are critical to missile guidance.Computationally efficient guidance law with compre-hensive consideration of the two performance merits is challeng-ing yet remains less addressed.Therefore,this paper seeks to solve a type of optimal control problem that maximizes final velocity subject to equality point constraint of impact angle con-straint.It is proved that the crude problem of maximizing final velocity is equivalent to minimizing a quadratic-form cost of cur-vature.The closed-form guidance law is henceforth derived using optimal control theory.The 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 six.On this basis,the optimal emission angle is determined to further increase the final velocity.The derived optimal value depends solely on the initial line-of-sight angle and impact angle constraint,and thus practical for real-world appli-cations.The proposed guidance law is validated by numerical simulation.The results show that the OGL-IAC is superior to the benchmark guidance laws both in terms of final velocity and missing distance.

关 键 词：MISSILE guidance law proportional-navigation guidance impact angle 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]