RBCC引射模态准一维性能分析模型

Quasi-1D analysis model of rocket ejector mode

关键词:  火箭基组合循环发动机  引射模态  性能分析

Key words:  Rocket-based-combined-cycle(RBCC)  Rocket ejector mode  Performance analysis

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M acCorm ack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。

Abstract:

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 MacCormack 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.