RBCC引射模态准一维性能分析模型  

Quasi-1D analysis model of rocket ejector mode

作　　者：吕翔[1] 何国强[1] 刘佩进[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《推进技术》2006年第6期529-531,541,共4页Journal of Propulsion Technology

摘　　要：基于准一维非稳态流动方程建立了RBCC引射模态性能分析模型，充分考虑壁面摩擦、有限速率化学反应和质量添加等因素。模型采用MacCormack格式求解，很好的解决了计算引射比、考虑环境压强等问题。与实验结果的对比表明，本模型计算结果的相对误差为5％～9％，发动机内的压强分布与实验结果基本一致，本模型可用于RBCC引射模态性能分析。Performance Analysis Model of Rocket Ejector Mode was established, based on quasi-1D transient flow equations. Factors such as skin friction, finite rate chemical reaction and mass injection were taken into account. A Mac- Cormack scheme was adopted for solving the equations, which obtains by-pass ratio correctly and well considers the ambient pressure. Compared with experimental results, the relative errors are about 5% - 9% and internal pressure distributions are basically consistent with experiment results, showing that the model is applicable for Rocket Ejector performance analysis.

关 键 词：火箭基组合循环发动机 引射模态 性能分析 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]