.png){kind=icon}
返回
Preliminary experimental study on solid-fuel rocket scramjet combustor
.png){kind=icon}
PRE
AI
DOI：10.1631/jzus.A1600489.png)
.png){kind=icon}
原文求助.png){kind=icon}
分享.png){kind=icon}
收藏
摘要
En 中文
Liquid or gaseous fuel scramjet technology has made great progress, and there has been some research attention to solid-fuel scramjet. A new scramjet configuration using solid fuel as propellant, namely solid-fuel rocket scramjet, is tested experimentally. It consists of two combustors. One is a rocket combustor used as gas generator, and the other is a supersonic combustor used for secondary combustion. The experiment simulates a flight Mach number of 4 at high altitude (stagnation temperature and pressure are 1170 K and 1.16 MPa, respectively), and metalized solid fuel is used as propellant. The results reveal that fuel-rich gas from the gas generator can burn with air in the supersonic combustor. Preliminary evaluation results show that the combustion efficiency of the propellant is about 90%, and the total pressure recovery coefficient in the supersonic combustor is about 0.6. These results indicate that the configuration of solid-fuel rocket scramjet is feasible.
Keyword:
Solid fuel
Rocket scramjet
Dual combustor
Direct-connect experiment
AI总结
对已上传原文的论文进行重点信息的提取，主要内容包括：简要概述、研究摘要、背景介绍、关键亮点、图文解析、展望与总结。
期刊
IF:
4.9
论文数:
2.1K
被引数:
4.6K
机构
引用论文
.png){kind=icon}
分享收藏A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations
OAAI
OAAI分享收藏
查看更多内容