摘要
针对同心筒热发射燃气射流二次燃烧冲击效应问题,采用3阶精度的MUSCL格式求解11组分12步基元化学反应动力学模型,弹体运动运用域动分层网格更新方法,数值模拟了同心筒发射H2/CO混合燃气流场。在燃气自由射流二次燃烧数值模拟结果与文献实验数据对比验证的基础上,分析了同心筒发射燃气流含化学反应的流动特点,以及在导弹出筒时筒口导流板结构对弹体的影响。数值结果表明:在筒外燃气与空气混合区域出现明显的二次燃烧,而在筒内二次燃烧几乎可以忽略;当弹底出筒后,从内外筒间隙排除的燃气、导弹尾部燃气射流和弹底之间相互干扰,形成反溅激波;反应流流场轴线温度高于冻结流和单一组分流流场轴线温度;导流板结构能明显降低弹体表面温度,其高度最优值在1.5倍内外筒间隙附近。研究结果对同心筒发射装置结构优化设计具有一定理论参考意义。
To study the thermo-impact of jet flow secondary combustion, a three-order accurate MUSCL scheme is employed to solve 12-step reaction and 11 species chemical reactions of HJCO mixed combus- tion gas field in concentric canister launcher（ CCL）, and the zone moving and dynamically layering meth- ods are adopted to simulate missile motion. Compared with free-jet flow experimental results, it is shown that the method is feasible. The jet field characteristic with chemical reactions and the temperature chan- ges of missile body are analyzed. The results show that chemical reaction occures in mixing layer of gas and air out of cylinder and there is no reaction in CCL tube. Reflective shock is due to the mutual inter- ference of gas out of cylinder, exhaust plume and missile tail. The axial temperature of reaction flow field is higher than those of frozen flow and single component flow. Guider can reduce missile body tempera- ture and its height optimal value is near 1.5 times the clearances inside and outside cylinder. The re- search can provide theoretical significance for the optimization design of CCL structures.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2014年第1期62-69,共8页
Acta Armamentarii
基金
国防预先研究项目(403050102)
关键词
液体力学
同心筒热发射
二次燃烧
域动分层网格
导流板
fluid mechanics
concentric canister launcher
secondary combustion
dynamic mesh up- date method
guider
