燃气弹射发射筒内燃气-空气二次燃烧现象研究  

Study on Secondary Combustion of Jet-flow and Air Inner Tube of Gas Ejection Launcher

作　　者：胡晓磊[1] 乐贵高[1] 李仁凤[1] 马大为[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《弹道学报》2014年第4期76-81,共6页Journal of Ballistics

基　　金：国防基础科研项目

摘　　要：燃气发生器喷出的燃气射流与发射筒内空气发生二次燃烧现象对导弹发射装置产生强烈的热冲击和烧蚀。为了研究含运动边界的发射筒内二次燃烧现象,采用三阶精度MUSCL格式求解9组分10步H2/CO基元化学反应动力学模型,使用域动分层网格更新方法模拟导弹运动。在与燃气自由射流冲击平台效应实验数据对比验证的基础上,分析了发射筒内二次燃烧现象对发射筒内流场和内弹道的影响以及筒内燃气-空气二次燃烧产生的原因。数值结果表明:二次燃烧不仅影响温度场分布,而且影响导弹的内弹道特性;发射筒内二次燃烧现象是由于燃气发生器喷出的可燃成分与发射筒内O2发生了强烈的化学反应导致的。研究结果对燃气弹射导弹内弹道设计提供了一定的理论基础。The missile launcher is subjected to thermo-impact and ablation while secondary combustion of jet-flow and air in inner tube of gas ejection launcher occurring.To study the secondary combustion with moving boundary inner tube,a three-order accurate MUSCL scheme was employed to solve 10-step and 9 species chemical reactions of H2/CO.The zone moving and dynamic laying method was adopted to simulate missile motion.The method was reliable by comparing with experimental results of free-jet flow impacting on plat.The effects of secondary combustion on jet field characteristic,motion law of internal trajectory and cause for secondary combustion were studied.The results show that the secondary combustion not only affects the temperature distribution,but also the motion law of internal trajectory.Intense chemical reaction of combustible jet-flow components with O2 in the tube results in the secondary combustion.The research provides theoretical foundations for the optimization design of gas ejection launcher.

关 键 词：内弹道 燃气弹射 二次燃烧 域动分层 数值模拟 

分 类 号：TJ762[兵器科学与技术—武器系统与运用工程]