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

作　　者：周梦琦 薛林[2] 闫晓勇[1] ZHOU Meng-qi XUE Lin YAN Xiao-yong(Beijing Institute of Electronic System Engineering, Beijing 100854, China The Second Research Academy of CASIC, Beijing 100854, China)

机构地区：[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

出　　处：《现代防御技术》2017年第5期42-47,共6页Modern Defence Technology

摘　　要：以近程防空导弹为背景,探讨了双脉冲推进技术对导弹性能的提升效果。建立了飞行弹道的数学模型,给出了制导方法及推力模型,借用遗传优化算法,以扩大导弹近界至远界各典型弹道的末速度为优化目标,对各种推力方案下推力参数进行了优化。研究表明,相比于传统单级推力形式,双脉冲推力对近程导弹末速度提升明显;优化得到了使导弹末端机动性能最优的双脉冲推力方案,为近程防空导弹双脉冲发动机的设计提供了理论依据。Based on short range antiaircraft missiles,the enhancement effect of dual pulse propulsion technology 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 

分 类 号：TJ761.13[兵器科学与技术—武器系统与运用工程] TJ765.1