固体火箭发动机长尾喷管传热数值模拟  

Numerical Simulation on Heat Transfer in Long-tail Nozzle of SRM

作　　者：吴川[1] 邢国强[1] 门们[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳479000

出　　处：《弹箭与制导学报》2016年第3期69-72,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为准确预示固体火箭发动机长尾喷管工作过程中的传热规律,文中采用流固耦合方法,对金属及多种非金属材料组成的长尾喷管建立了数值模型,基于Fluent计算软件对长尾喷管工作过程进行了非稳态传热数值计算。仿真结果表明,燃气对长尾喷管由内向外进行传热,但外壁面各区域温度场因内部材料不同差别较大。外壁面温度计算值与试验结果较吻合,可以为长尾喷管传热提供一种实用的计算方法。In order to accurately predict heat transfer characteristic of long-tail nozzle in solid rocket motor （SRM） , a numerical model was established for the long-tail nozzle composed of metal and several non-metallic materials using fluid-solid coupling method, unsteady heat transfer was calculated for the model based on CFD code FLUENT in this paper. Numerical results show that the heat of gas transfers from inside to outside in long-tail nozzle, but regional temperature field is different in external suzface because of inner materials. The analysis results show that the computation values are basically identical with testing results in external suzface. The method can provide a useful and convenient method for long-tail nozzle heat transfer analysis.

关 键 词：固体火箭发动机 长尾喷管 传热 流固耦合 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]