弹道导弹极限能量弹道的求解与仿真  

Solution and Simulation of Limited Energy Trajectory for Ballistic Missile

作　　者：肖滨[1] 郭鹏程[1] 衡军[1] 张丛智[1] 

机构地区：[1]海军潜艇学院作战指挥系,山东青岛266071

出　　处：《系统仿真技术》2009年第1期12-17,共6页System Simulation Technology

基　　金：国家"八六三"高技术计划资助项目(2002AA115130);国家"九七三"重大基础研究资助项目(51306)

摘　　要：弹道导弹的弹道运动可以看作是导弹绕地心质点的二体运动,在经过发射点到落点的多个椭圆弹道中,发射速度最小的弹道称为最小能量弹道。一般来讲,随着发射速度的增大弹道落点速度和俯角都会增大,因此较高的发射速度可以提高导弹的末端突防概率。在椭圆轨道扁心率与轨道参数关系的研究基础上,研究提出了极限能量弹道轨道根数的求解方法,并进行了仿真开发和实现。理论和仿真结果证明了依靠提高发射速度来增大落点速度和俯角推断的正确性。The ballistic movement of ballistic missile can be considered as two body movement in which the missile moves around the centroid of the earth. There are multiple elliptical orbits from launching point to landing point, and the trajectory needing the minimal launching velocity is called the Minimal Energy Trajectory. In general, with the increase of launching velocity from the minimum, the landing velocity and pitch become growing, hence to enhance the breaching probability in the terminal. Based on the research of the relationship between the prolate ratio and other parameters of elliptical orbit, the solution of orbit parameters for Limited Energy Trajectory is put forwards, and simulation is developed and implemented. The academic and simulated results testified the validity of the conclusion that landing velocity and pitch are increased by increasing launching velocity.

关 键 词：弹道 最小能量弹道 极限能量弹道 仿真 

分 类 号：TP301[自动化与计算机技术—计算机系统结构] E9[自动化与计算机技术—计算机科学与技术]