固体火箭技术Issue(2)：179-184,197,7.DOI:10.7673/j.issn.1006-2793.2015.02.006
火箭引射模态下主火箭总压与RBCC发动机的匹配性
Operation match between primary rocket and RBCC engine during rocket ejector mode
吕翔 1郑思行 1何国强 1刘佩进1
作者信息
- 1. 西北工业大学 燃烧 热结构与内流场重点实验室，西安 710072
- 折叠
摘要
Abstract
Based on the traditional “pressure equal plane” hypothesis, ejection performance analysis model for RBCC primary rocket was established. Operation match between primary rocket and RBCC engine was investigated.The results show that:If the ar-ea ratio of isolator cross section is less than 0.65, flow choke will appear in isolator under lower total pressure of primary rocket, limiting further improvement of air mass flow.For ground static condition, the air mass flow increases with the increase total pressure of primary rocket. If fabric choke appears,further increasing total pressure of primary rocket will cause descending of air mass flow. During rocket ejector mode, the operation of RBCC engine can be divided into 3 different states, inlet sub-critical state dominated by ejecting effect, inlet critical state dominated by ejecting effect, inlet super-critical state dominated by ram effect, while the criti-cal Mach number for these states are 0.7 and 1.5 respectively.关键词
火箭基组合循环/高超声速飞行器/火箭引射模态/主火箭/隔离段Key words
rocket based combined cycle/hypersonic vehicle/rocket ejector mode/primary rocket/isolator分类
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吕翔,郑思行,何国强,刘佩进..火箭引射模态下主火箭总压与RBCC发动机的匹配性[J].固体火箭技术,2015,(2):179-184,197,7.
