大幅度延长激波风洞试验时间
A big increase in shock tunnel test times
查看参考文献20篇
|
文摘
|
发展高超吸气推进技术为何如此艰难?探求阻碍发展的根源需要可信赖的地面试验装置.提出大幅度延长激波风洞试验时间,用来突破干净空气吸气推进试验装置马赫数未超过5的局限.采用小直径驱动段降低爆轰驱动激波管缝合激波马赫数,使爆轰驱动激波风洞试验时间能够大幅度延长.建成的长试验时间激波风洞JF-12的试验时间超过100 ms. |
|
其他语种文摘
|
Why is it such difficult to develop hypersonic airbreathing propulsion? It is in need of a reliable ground test facility for ex-ploring the source of development obstruction. A big increase in shock tunnel test times for breaking the upper bound of Mach number 5 associated with airbreathing propulsion was proposed. Smaller diameter of detonation driver was adopted for decreasing Tailored incident shock Mach number, enabling the test times of detonation driven shock tunnel to be extended by a big margin. Test times of constructed detonation driven shock tunnel JF-12 were over 100 ms. |
|
来源
|
中国科学. 物理学
, 力学, 天文学,2015,45(9):094701-1-094701-6 【核心库】
|
|
DOI
|
10.1360/sspma2015-00260
|
|
关键词
|
激波管
;
激波风洞
;
试验时间
;
爆轰驱动
;
高超吸气推进
|
|
地址
|
中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
|
|
语种
|
中文 |
|
文献类型
|
研究性论文 |
|
ISSN
|
1674-7275 |
|
学科
|
力学 |
|
基金
|
财政部重大科研装备自主创新专项(试点)基金资助项目
|
|
文献收藏号
|
CSCD:5526904
|
参考文献 共
20
共1页
|
|
1.
中国科学院学部联合办公室.
中国科学院院士自述,1996:157-158
|
被引
1
次
|
|
|
|
|
2.
郑耀(译).
通向马赫数10之路,2012:6
|
被引
1
次
|
|
|
|
|
3.
钱学森. 致王寿云等六同志信.
钱学森现代军事科学思想,2010:176-177
|
被引
1
次
|
|
|
|
|
4.
Marren D. The AEDC hypervelocity wind tunnel 9.
Prog Astronaut Aeronaut,2002,198:468
|
被引
1
次
|
|
|
|
|
5.
陈立子(译).
可压缩流的动力学与热力学(上册),1966:55
|
被引
1
次
|
|
|
|
|
6.
Reubush D E.
Modification to the Lang-ley 8-foot high temperatur tunnel for hypersonic propulsion testing. AIAA Paper, AIAA 87-1887,1987
|
被引
1
次
|
|
|
|
|
7.
Hertzberg A. A shock tube method of generating hypersonic flows.
J Aero Sci,1951,18:803-804
|
被引
3
次
|
|
|
|
|
8.
Wittlife C E. The tailored inter face hypersonic shock tunnel.
J Aero Sci,1959,26:219-228
|
被引
4
次
|
|
|
|
|
9.
Courant R.
Supersonic Flow and Shock Waves,1948
|
被引
66
次
|
|
|
|
|
10.
Glass I I.
Handbook of Supersonic Aerodynamics Sec 18, Shock Tube. NAVORD Report. Rep.1488,1959
|
被引
1
次
|
|
|
|
|
11.
Flagg R F.
Detailed Analysis of Shock Tube Tailored Condition. RAD-TM-63-64,1963
|
被引
2
次
|
|
|
|
|
12.
李进平. 爆轰驱动激波管缝合激波马赫数计算.
空气动力学学报,2008,26:291-296
|
被引
12
次
|
|
|
|
|
13.
Morrison W R B. New generation of free-piston shock tunnel.
Current Topics in Shock Waves. 208,1989:582-587
|
被引
1
次
|
|
|
|
|
14.
Holden M S. Large Energy National Shock Tunnel (LENS).
Description and Capabilities,1991
|
被引
1
次
|
|
|
|
|
15.
Holden M S. LENS hypervelocity tunnels and application to vehicle at duplicated flight conditions.
Prog Astronaut Aeronaut,2002,198:17-27
|
被引
1
次
|
|
|
|
|
16.
Yu H. Recent developments in shock tube application.
Proceeding of 1989 Japan National Symposium on Shock Wave Phanomena,1989:1-79
|
被引
1
次
|
|
|
|
|
17.
俞鸿儒. 探索发展激波风洞爆轰驱动技术.
力学学报,2011,43:978-983
|
被引
4
次
|
|
|
|
|
18.
Dunn M G.
Development of a new high-enthalpy shock tunnel. AIAA Paper, AIAA-88-2782,1988
|
被引
1
次
|
|
|
|
|
19.
Pennelegion L.
The Change in Shock Tunnel Tailoring Mach Number Due to Driver Gas Mixtures of Helium and Nitrogen. Aeronautical Research Council Reports and Memoranda,1965
|
被引
1
次
|
|
|
|
|
20.
. 8个重大科研装备自主创新项目后动.
人民日报(海外版),2008
|
被引
17
次
|
|
|
|
|
了解气象卫星更多信息，请访问