长试验时间爆轰驱动激波风洞技术研究

姜宗林; 李进平; 赵伟; 刘云峰; 俞鸿儒

doi:10.6052/0459-1879-12-160

长试验时间爆轰驱动激波风洞技术研究

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

基金项目: 国家重大科研装备项目和国家自然科学基金项目(90916028)资助.

详细信息

通讯作者:
姜宗林

中图分类号: V211.7
计量
- 文章访问数: 2209
- HTML全文浏览量: 161
- PDF下载量: 1296
出版历程
- 收稿日期: 2012-05-24
- 修回日期: 2012-06-20
- 刊出日期: 2012-09-17

INVESTIGATING INTO TECHNIQUES FOR EXTENDING THE TEST-DURATION OF DETONATION-DRIVEN SHOCK TUNNELS

State Key Laboratory of High-temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

Funds: The project was supported by the Development Project of the State Key Scientific Equipment and the National Natural Science Foundation of China (90916028).

摘要

摘要: 地面试验是先进高超声速飞行器研制的主要手段之一,获得满足高超声速气动实验研究的长时间高焓气流是发展激波风洞技术的关键难题之一.依据反向爆轰驱动方法,针对满足超燃试验有效时间的要求,讨论了爆轰驱动激波风洞运行缝合条件匹配、喷管起动激波干扰控制和激波管末端激波边界层相互作用等因素对激波风洞试验时间的制约及其相应的解决方法.应用这些延长试验时间的激波风洞创新技术,成功研制了基于反向爆轰驱动方法的超大型激波风洞,试验时间长达100ms,并有复现高超声速飞行条件的流动模拟能力.
- 高超声速飞行 /
- 反向爆轰驱动激波风洞 /
- 长试验时间 /
- 高温气体流动
Abstract: Ground test is the important and indispensable method for the research and development of hypersonic vehicle,and the acquisition of the high-enthalpy test flow with long enough test time in the test is one of the key challenges for the shock tunnel.Based on detonation-driven shock tunnel,several factors that are of significant influences on the test time are discussed and the corresponding solutions for extending test time are proposed in this paper,including the tailored condition,the shock starting process in the nozzle and the interaction of reflected shock and boundary layer,aiming to meet the requirement for the test time of supersonic combustion experiments.Through the application of the proposed methods,a large detonation-driven shock tunnel has been successfully developed,which can provide the test time of more than 100 microseconds and are capable of duplicating the hypersonic flight conditions.
- hypersonic flight /
- backward detonation shock tunnel /
- long test time /
- high temperature gas flow

HTML全文

参考文献(18)

Bertin JJ,Cummings RM.Critical hypersonic aerothermodynamic phenomena.Annual Review of Fluid Mechanics,2006,38:129-157

Holden MS.Design,development and calibration of the LENS facility.AFOSR-TR.1994,940161

Dunn MG,Moller JC,Steele RC.Development of a new high-enthalpy shock tunnel.AIAA-88-2782,1988

钱学森.我对今日力学的认识.力学与实践,1995,17(4):1 (Tsien Hsue-shen.My cognition on today's mechanics. Mechanics and Practice,1995,17(4):1 (in Chinese))

Holden MS,Parker R.LENS hypervelocity tunnels and application to vehicle testing at duplicated conditions.In:Advanced Hypersonic Test Facilities.Lu F,Marren D,eds.Progress in Astronautics and Aeronautics,Volume 198.AIAA,2002

Fickett W,Davis WC.Detonation Theory and Experiment.Mineola.New York:Dover Publications,INC.1979

Yu HR,Esser B,Lenartz M,et al.Gaseous detonation driver for a shock tunnel.Shock Waves,1992,2 (4):245-254

张欣玉,俞鸿儒,赵伟等.氢氧爆轰直接起始实验研究.流体力学测量与控制,1996,10(3):63-68 (Zhang Xinyu,Yu Hongru,Zhao Wei,et al.Turbulent jet initiation of oxy-hydrogen direct detonation.Aerodynamic Experiment and Measurement and Control,1996,10(2):63-68 (in Chinese))

赵伟,俞鸿儒.过临界喷管充气混合装置.空气动力学学报,1999,17(3):279-284 (Zhao Wei,Yu Hongru.The double over-critical nozzles device for filling and mixing mixture gases.Acta Aerodynamica Sinica,1999,17(3):279-284 (in Chinese))

Lu FK,Wilson DR,Bakos RJ,et al.Recent advances in detonation techniques for high-enthalpy facilities.AIAA Journal,2000,38 (9):1676-1684

Jiang ZL,Zhao W,Wang C,et al.Study on forward detonation driver for high enthalpy shock tunnels.AIAA Journal,2002,40(10):2009-2016

Flagg RF.Detailed analysis of shock tube tailored conditions.RAD-TM-63-64,1963

李进平,冯珩,姜宗林等.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 (3):291-296 (Li Jinping,Feng Heng,Jiang Zonglin,et al.Numerical computation on the tailored shock mach numbers for a hydrogen-oxygen detonation shock tube.Acta Aerodynamica Sinica,2008,26 (3):291-296 (in Chinese))

俞鸿儒,林建民,李仲发等.扩张激波管流动波图观察.空气动力学学报,1984,3:88-91 (Yu Hongru,Lin Jianmin,Li Zhongfa,et al.Observation of wave diagrams for shock tube with the divergent nozzle at diaphragm section.Acta Aerodynamica Sinica,1984,3:88-91 (in Chinese))

Laderman AL.Shock-tube performance with area divergence at the diaphragm section.AIAA Journal,1967,10:1904-1906

赵伟,姜宗林,俞鸿儒.高焓激波风洞爆轰驱动技术研究.空气动力学学报,2009,27:63-68 (Zhao Wei,Jiang Zonglin,Yu Hongru.Study on detonation drivers for high-enthalpy shock tunnels.Acta Aerodynamica Sinica,2009,27:63-68 (in Chinese))

李进平,冯珩,姜宗林.激波/边界层相互作用诱导的激波风洞气体污染问题.力学学报,2008,40(3):289-296 (Li Jinping,Feng Heng,Jiang Zonglin.Gas contamination induced by the interaction of shock/boundary layer in shock tunnel.Chinese Journal of Theoretical and Applied Mechanics,2008,40(3):289-296 (in Chinese))

Burtschell Y,Cardoso M.Numerical analysis of reducing driver gas contamination in impulse shock tunnels.AIAA Journal,2001,39:2357-2365