航天推进技术研究院主办
[1]路媛媛,张蒙正,严俊峰.火箭推力室喷管内激波对RBCC性能影响分析[J].火箭推进,2013,39(05):46-50.
LU Yuan-yuan,ZHANG Meng-zheng,YAN Jun-feng.Influences of shock wave in rocket nozzle on RBCC performance[J].Journal of Rocket Propulsion,2013,39(05):46-50.
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LU Yuan-yuan,ZHANG Meng-zheng,YAN Jun-feng.Influences of shock wave in rocket nozzle on RBCC performance[J].Journal of Rocket Propulsion,2013,39(05):46-50.
火箭推力室喷管内激波对RBCC性能影响分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年05期
页码:
46-50
栏目:
研究与设计
出版日期:
2013-10-31
- Title:
- Influences of shock wave in rocket nozzle on RBCC performance
- 文章编号:
- 1672-9374(2013)05-0046-05
- Keywords:
- RBCC; ejector mode; rocket nozzle; normal shock wave
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 针对火箭基组合循环（RBCC）动力系统引射火箭喷管的工作状况，采用准一维方法，假设引射模态火箭推力室喷管内在某些条件下产生的激波为正激波，分析了正激波的存在条件及其对RBCC动力系统性能的影响。结果表明：引射火箭推力室室压越低或飞行器飞行马赫数越高，引射火箭喷管内越易产生正激波；火箭喷管正激波的产生对RBCC动力系统引射性能及比冲特性有一定影响。
- Abstract:
- When the rocket works in some cases, shock wave may appear in rocket nozzle in RBCC engine. The shock wave is supposed to be a normal shock wave in the one-dimensional conceptual analysis model. The existence conditions and influences of the normal shock wave on performance of RBCC dynamical system were analyzed. The results indicate that the lower the total pressure is in rocket combustion chamber or the higher the flight Mach number is, the easier the normal shock wave appearances in the nozzle. The generation of the normal shock wave in rocket nozzle has a certain influence on the ejector performance of RBCC dynamical system.
参考文献/References:
[1]张蒙正, 李平, 陈祖奎. 组合循环动力系统面临的挑战及前景[J]. 火箭推进, 2009, 35(1): 1-8.
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备注/Memo
收稿日期：2012-12-24；修回日期：2013-05-15
基金项目：国家863项目（2010AA702308）
作者简介：路媛媛（1988—），女，硕士，研究领域为RBCC动力系统性能分析研究
更新日期/Last Update:
1900-01-01