北京航空航天大学学报 ›› 2010, Vol. 36 ›› Issue (6): 650-653.

• 论文 • 上一篇    下一篇

弹道导弹在被动段轴向加速变轨弹道设计与优化

  

  1. (北京航空航天大学 宇航学院, 北京 100191)
  • 收稿日期:2009-04-20 出版日期:2010-06-30 发布日期:2010-07-02
  • 作者简介:张斌(1983-)男,湖南株洲人,博士生,zhangbin.1983@yahoo.com.cn.
  • 基金资助:

    国家863基金资助项目

Design and optimization on trajectory of increasing velocity along its original -velocity direction by impulse firing for ballistic missile to penetrate anti-missile system in passive ballistic curve

  • Received:2009-04-20 Online:2010-06-30 Published:2010-07-02

摘要:

针对在被动段脉冲发动机轴向加速变轨突防弹道计算建立了飞行动力模型,通过弹道仿真计算分析了脉冲发动机点火时间和脉冲发动机工作时间对弹道的影响.脉冲发动机总冲一定时,短时间-大推力模式下导弹的射程最大.在爬升段点火时,短时间-大推力导弹能量利用最高;在下降段点火时,长时间-小推力能量利用率最高.同时提出了脉冲轴向加速变轨突防弹道优化的约束条件,并对该问题进行了优化计算,优化后的发动机质量比优化前减少了24.87%.

Abstract:

A fly dynamics model of ballistic missile to penetrate the anti-missile system in the passive ballistic curve, which was based on the increasing velocity along its original velocity direction, was established. The influences of the impulse engine work time and the impulse engine ignition time on trajectory were analyzed based on the result of trajectory simulation. With a constant total impulse, the short time-large thrust model had maximum range. When impulse engine ignited at climbing stage, the model of short time-large thrust had maximum utilization ratio of energy, while the model of long time-small thrust had maximum utilization ratio of energy at descending stage. The constraint conditions of the optimization problem of increasing velocity along its original velocity direction by impulse firing were given. The results of optimization show that the mass of impulse engine decreases 24.87%. 

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发