同心筒发射燃气流二次燃烧数值研究及导流板结构改进

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。

Numerical Simulation of Secondary Combustion Gas Field in Concentric Canister Launcher and Improvement Measures of Guider

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 H₂/CO mixed combustion gas field in concentric canister launcher(CCL), and the zone moving and dynamically layering methods 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 changes 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 interference 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 temperature and its height optimal value is near 1.5 times the clearances inside and outside cylinder. The research can provide theoretical significance for the optimization design of CCL structures.