RBCC引射模态准一维性能分析模型

推进技术 ›› 2006, Vol. 27 ›› Issue (6): 529-531.

RBCC引射模态准一维性能分析模型

吕翔,何国强,刘佩进

西北工业大学航天学院陕西西安710072;西北工业大学航天学院陕西西安710072;西北工业大学航天学院陕西西安710072

发布日期:2021-08-15

Quasi-1D analysis model of rocket ejector mode

Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

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。

关键词: 火箭基组合循环发动机;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.

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

吕翔,何国强,刘佩进. RBCC引射模态准一维性能分析模型[J]. 推进技术, 2006, 27(6): 529-531.