空间动能拦截末段导引法研究及其仿真  

Terminal Guidance Method Study and Simulation in Space Kinetic Interception

作　　者：张彦[1] 冯书兴[2] 

机构地区：[1]装备指挥技术学院研究生部 [2]装备指挥技术学院试验指挥系,北京101416

出　　处：《系统仿真学报》2007年第9期2124-2126,共3页Journal of System Simulation

基　　金：863计划资助项目(863-2003AA713012)

摘　　要：针对空间动能拦截的特点,利用了比例导引法控制视线转率的优点,兼顾考虑了控制脱靶量以提高动能拦截精度,设计了空间动能拦截末段导引法。该导引方法基于目前发动机一般工作于脉冲条件下的实际情况,能有效地控制视线转率和脱靶量,并能够保持拦截器飞行弹道的稳定性。仿真结果验证了该方法的有效性。Based on the characteristics of space kinetic energy interception and advantages of proportional guidance, taking controlling the undershooting rate into account to increase precision, a terminal guidance method was designed to space kinetic energy interception problem. To the fact that the engines are almost impulse engines at present, this method can restrain the turn rate and undershooting rate effectively. Besides, it can also keep the stability of the trajectory. Simulation results indicate the validity of this method.

关 键 词：空间动能拦截 末段导引 脱靶量 比例导引法 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]