航天推进技术研究院主办
[1]侯早,王福民,旷武岳.冲压发动机超声速进气道研究进展[J].火箭推进,2008,34(05):31-34.
Hou Zao,Wang Fumin,Kuang Wuyue.Development of supersonic scramjet inlet[J].Journal of Rocket Propulsion,2008,34(05):31-34.
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Hou Zao,Wang Fumin,Kuang Wuyue.Development of supersonic scramjet inlet[J].Journal of Rocket Propulsion,2008,34(05):31-34.
冲压发动机超声速进气道研究进展
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年05期
页码:
31-34
栏目:
专论与综述
出版日期:
2008-10-30
- Title:
- Development of supersonic scramjet inlet
- Keywords:
- scramjet; supersonic inlet; concept innovation
- 分类号:
- V430
- 文献标志码:
- A
- 摘要:
- 超声速进气道是冲压发动机的关键部件之一。简要介绍了冲压发动机常用的典 型进气道。重点叙述了进气道的最新研究成果，主要包括等溢流角弯曲前缘侧壁压缩进气道 设计概念、支板引射压缩进气道、双模态超燃冲压发动机变几何进气道、全外压缩式超声速 “参数进气道”、固定型面方转椭圆形超声速进气道(REST)等的设计概念与方案。最后概括 了先进进气道的发展趋势。
- Abstract:
- Supersonic inlet is the key part of a supersonic air-breath engine．In this paper，typ— ical inlets used for supersonic engine ate simply introduced，and recent achievements of inlets are described，including hypersonic sidewall compression inlet with constant spillage a．sle design at non—uniform incoming flow，strutjet compression scramjet inlets，a variable geometry inlet for dual mode ramjet．entirely outside compress supersonic“parameters inlet”，a fixed—geometry hypersonic inlet with rectangular-to-elliptical shape transition(REST)．Before all inlet design，it is sug— gested that the design conception of inlet should be innovated，near and far scheming also should be designed．Muhieipital point of view together design is especially important．
参考文献/References:
[l]Holland Scott D．An Experimental Parametric Study of
Geometric，Reynolds Number，and Ratio of Specific Heats
Effects in‰e--dimensional Sidewall Compression
Scramjet Inlets al Mach 6[R]．AIAA93-0740．
[2]Siebenhaar A，Bulman M J．The Role of the Strutjet
Engine in New Gbbal and Space Markets[R]．IAF-98一S．
5．04．
[3]3 Falempin F，Goldfeld M，Nestoulia R，et a1．Evaluation of
a Variable Geometry Inlet for Dual Mode Ramjet[R]．
AIAA一2002—5232．
[4]Michael K Smart，Carl A Trexler．Mach 4 Performance of
a Fixed-geometry Hypersonic Inlet with Rectangular-toelliptical
Shape Transition[R]．AIAA一2003—12．
[5]丛敏．阿连特技术系统公司试验高超声速发动机[J]．飞
航导弹．2007，(10)：42
[6]蔡元虎，张建东，壬占学．TBCC发动机用进气道设
计及沿飞行轨迹斜板角度优化分析[J]．西北工业大学
学报．2007，25(5)：615--619．
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备注/Memo
收稿日期：2008—03—06；修回日期：2008--06-24。 作者简介：侯早(1978一)，男，工程师，研究领域为液体火箭发动机技术。
更新日期/Last Update:
1900-01-01