现代防御技术2017，Vol.45Issue(5)：42-47,6.DOI:10.3969/j.issn.1009-086x.2017.05.008
近程防空导弹发动机推力方案优化研究
Optimizing Motor Propulsion Scheme in Short Range Antiaircraft Missiles
周梦琦 1薛林 2闫晓勇1
作者信息
- 1. 北京电子工程总体研究所,北京100854
- 2. 中国航天科工集团第二研究院,北京100854
- 折叠
摘要
Abstract
Based on short range antiaircraft missiles,the enhancement effect of dual pulse propulsiontechnology for missile performance is studied.The mathematical model of flight trajectory,guidance and thrust are built.Aiming at promoting the terminal velocity,the performance parameters of the engine with different propulsion schemes are optimized by genetic algorithm for each typical trajectory from near edge to far edge.According to the optimization,the terminal velocity of short range missiles is promoted more markedly by dual pulse propulsion than by traditional single stage propulsion;the optimal dual pulse thrust scheme of terminal maneuvering performance has been acquired.These results offer theoretical evidence for the design of dual pulse motor in short range antiaircraft missiles.关键词
近程导弹/防空导弹/推力方案/双脉冲推力/末端速度/遗传算法Key words
short range missiles/antiaircraft missiles/thrust scheme/dual pulse thrust/terminal velocity/genetic algorithm分类
军事科技引用本文复制引用
周梦琦,薛林,闫晓勇..近程防空导弹发动机推力方案优化研究[J].现代防御技术,2017,45(5):42-47,6.
