火箭基组合循环发动机引射模态流动分析  

Flow analysis and validation of rocket ejector mode for rocket based combined cycle

作　　者：王国辉[1] 蔡体敏[1] 何国强[1] 刘佩进[1] 黄生洪[1] 秦飞[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《推进技术》2002年第4期298-302,共5页Journal of Propulsion Technology

摘　　要：应用迎风格式有限体积方法求解N S方程的基础上 ,数值模拟了火箭基组合循环 (RBCC)发动机引射模态进气道 /混合段 /燃烧室 /尾喷管 /引射火箭内的流动过程 ,分析了引射模态流道中的复杂流动结构 ,从理论上探讨了火箭引射模态工作过程机理 ,讨论了RBCC实验模型的混合性能 ,最后与实验结果进行了比较 ,二者吻合较好。Upwind scheme limited volume methodology was employed to solve Navier Stockes equation,the flow field in the inlet/mixer/combustor/nozzle/ejector rocket of a RBCC test model was simulated,the sophisticated flow structure in the duct was analysized,the principle of rocket ejector pumping and mixing ability of the model was discussed,and finally,the calculation was validated by the experimentation with good agreement each other All this results provide some theoretical basis for the deep research about RBCC ejector mode operation and parameter optimization

关 键 词：流动分析 火箭发动机 引射式冲压发动机 复合式发动机 引射模态 数值仿真 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]