NCJ型外层空间导弹的改进型PN导引律设计  

Modified PN guidance law design for NCJ exoatmospheric missiles

作　　者：叶青[1] 刘春生[1] YE Qing;LIU Chunsheng(School of Automation, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China)

机构地区：[1]南京航空航天大学自动化学院

出　　处：《系统工程与电子技术》2019年第10期2320-2327,共8页Systems Engineering and Electronics

基　　金：江苏省研究生创新项目(KYLX15_0267)资助课题

摘　　要：针对前部喷管控制型外层空间导弹拦截提出了改进型比例导引(proportional navigation,PN)导引律,在目标的加速度大小和方向都有不确定性的情况下能够以零脱靶量命中目标。与以往的PN导引律不同,改进型PN导引律增加了消除偏差的项,且比例系数是时变的。此外,针对拦截的初始条件不理想的情况,提出了一个过渡的导引律,在经过有限时间采用过渡的导引律之后能够使得运动变量满足改进型PN导引律的适用条件。最后,通过仿真验证了所提出的算法的可行性。A modified proportional navigation (PN) guidance law is designed for nose jet control exoatmospheric missiles, which guarantees zero miss distance even if there are uncertainties in the direction and magnitude of the target’s acceleration. Unlike traditional PN guidance laws, for the modified PN guidance law, a deviation elimination term is added and the PN gain is time-varying. Additionally, to deal with non-ideal interception scenarios, a transition guidance law is designed. After a finite time of implementing the transition guidance law, kinematic variables converge to be suitable for implementation of the modified PN guidance law. Simulation study are conducted to verify the feasibility of the proposed algorithm.

关 键 词：外层空间导弹 比例导引 前部喷管控制 

分 类 号：TP277[自动化与计算机技术—检测技术与自动化装置]