高超声速1MHz高频脉动压力测试技术及其应用

纪锋; 解少飞; 沈清

doi:10.7638/kqdlxxb-2015.0117

高超声速1MHz高频脉动压力测试技术及其应用

中国航天空气动力技术研究院, 北京 100074

基金项目: 国家自然科学基金（11372296，11402256）

详细信息

作者简介:
纪锋(1981-),男,内蒙古,高级工程师,研究方向:高超声速风洞试验及试验技术.E-mail:jifeng815@sohu.com

通讯作者:
解少飞(1986-),研究方向:高超声速边界层转捩试验及试验技术.E-mail:flying_1125@126.com

中图分类号: V411.4
计量
- 文章访问数: 208
- HTML全文浏览量: 9
- PDF下载量: 607
出版历程
- 收稿日期: 2015-12-09
- 修回日期: 2016-01-31
- 网络出版日期: 2021-01-07
- 刊出日期: 2016-10-24

Hypersonic high frequency (1MHz) fluctuation pressure testing technology and application

China Academy of Aerospace Aerodynamics, Beijing 100074, China

摘要

摘要: 为了研究高超声速边界层内的高频脉动结构，特别是第二模态不稳定波，在FD-07风洞中搭建了一套1MHz量级高频脉动压力采集系统。风洞背景噪声和电磁噪声是影响高频脉动结构测量的主要原因。在风洞流场品质无法改变的前提下，对高频脉动压力采集系统的信号传输进行了改进，包括工频电源隔离、传输电缆屏蔽和采集设备接地等。通过改进措施，采集系统的抗电磁干扰和信号衰减的能力得到改善，其信噪比得以显著提升。结果表明，改进前后各频段噪声的能谱密度大幅降低(在频率400kHz以下，噪声能谱密度降低了一个量级以上)。最后，利用该测试技术成功地在FD-07高超声速风洞中进行了边界层稳定性实验，捕捉到了第二模态不稳定波，其主导频率范围与线性稳定性理论预测结果吻合。
- 高超声速 /
- 高频脉动结构 /
- 电磁噪声 /
- 信号衰减 /
- 第二模态不稳定波
Abstract: High frequency (1MHz) fluctuation pressure acquisition system was developed to study the high frequency fluctuation structures, especially the second mode instability waves, in hypersonic boundary layer in the FD-07 wind tunnel. Wind tunnel ground noises and electromagnetic noises affects measuring of high frequency fluctuation structures. Due to When the qualities of wind tunnel flow field can't change, a series of improvements were made for signal transmission of the system to enhance the ability of anti-electromagnetic interference and anti-attenuation. The improvements contained power supply isolation, shielding cable and ground connection, et al. The experimental results by comparison showed that signal to noise ratio (SNR) of the acquisition system increased remarkably, and the power spectrum densities of noises below 400kHz were reduced by one order of magnitude. Finally, hypersonic boundary stability experiment was performed successfully with the acquisition system in FD-07 tunnel. The second mode wave was detected, and the main frequency extent agreed with the results of linear stability theory (LST).
- hypersonic /
- high fluctuation structures /
- electromagnetic noise /
- signal attenuation /
- the second mode instability wave

HTML全文

参考文献(18)

[1]	Demetriades A. An experimental investigation of the stability of the laminar hypersonic boundary layer[D].[Ph.D. Dissertation]. California Institute of Technology, 1958.
[2]	Stetson K F, Thompson E R, Donaldson J C, et al. Laminar boundary layer stability experiments on a cone at Mach 8, Part 1:sharp cone. AIAA-83-1761[R]. Reston:AIAA, 1983.
[3]	Stetson K F, Thompson E R, Donaldson J C, et al. Laminar boundary layer stability experiments on a cone at Mach 8, Part 2:Blunt cone. AIAA-84-0006[R]. Reston:AIAA, 1984.
[4]	Stetson K F, Thompson E R, Donaldson J C, et al. Laminar boundary layer stability experiments on a cone at Mach 8, Part 3:Sharp Cone at Angle of Attack. AIAA-85-0492[R]. Reston:AIAA, 1985.
[5]	Stetson K F, Thompson E R, Donaldson J C, et al. Laminar boundary layer stability experiments on a cone at Mach 8, Part4:on Unit Reynolds number and environmental effects. AIAA-86-1087[R]. Reston:AIAA, 1986.
[6]	Fujii K. Experiment of two dimensional roughness effect on hypersonic boundary layer transition[J]. Journal of Spacecraft and Rockets, 2006, 43(4):731-738.
[7]	Fujii K. An experiment of two dimensional roughness effect on hypersonic boundary layer transition. AIAA 2005-0891[R]. Reston:AIAA, 2005.
[8]	Estorf M, Radespiel R. Surface-pressure measurements of second-mode instability in quiet hypersonic flow. AIAA 2008-1153[R]. Reston:AIAA, 2008.
[9]	Casper K M, Beresh S J, Henfing J F, et al. Hypersonic wind-tunnel measurements of boundary-layer pressure fluctuations. AIAA 2009-4054[R]. Reston:AIAA, 2009.
[10]	Berridge D C, Casper K M, Rufer S J, et al. Measurements and computations of second-mode instability waves in three hypersonic wind tunnels. AIAA 2010-5002[R]. Reston:AIAA, 2010.
[11]	Tanno H, Komuro T, Sato K, et al. Measurement of hypersonic boundary layer transition on cone models in the free-piston shock tunnel HIEST. AIAA 2009-0781[R]. Reston:AIAA, 2009.
[12]	Tanno H, Komuro T, Sato K, et al. Measurement of hypersonic high-enthalpy boundary layer transition on a 7 cone model. AIAA 2010-310[R]. Reston:AIAA, 2010.
[13]	Wagner A, Laurence S, Schrammz J M, et al. Experimental investigation of hypersonic boundary-layer transition on a cone model in the High Enthalpy Shock Tunnel (HEG) at Mach 7.5. AIAA 2011-2374[R]. Reston:AIAA, 2011.
[14]	Zhang C H, Tang Q, Lee C B. Hypersonic boundary-layer transition on a flared cone[J]. Acta Mechanica Sinica, 2013, 29(1):48-53.
[15]	Schneider S P. Developing mechanism-based methods for estimating hypersonic boundary-layer transition in flight:the role of quiet tunnels. AIAA 2013-2608[R]. Reston:AIAA, 2013.
[16]	Jiang Wei, Yang Yunjun, Chen Hewu. Investigation on aerodynamics of the spike-tipped hypersonic vehicle[J]. Journal of Experiments in Fluid Mechanics. 2011, 25(6):28-32.(in Chinese)姜维, 杨云军, 陈河梧. 带减阻杆高超声速飞行器外形气动特性研究[J]. 实验流体力学, 2011, 25(6):28-32.
[17]	Hu Guangshu. Digital signal processing[M]. Beijing:Tsinghua University Press, 2003:514-516. (in Chinese)胡广书. 数字信号处理[M]. 北京:清华大学出版社, 2003:514-516.
[18]	Mack L M. Linear stability theory and the problem of supersonic boundary layer transition[J]. AIAA Journal, 1975, 13(3):278-289.

施引文献(9)

期刊类型引用(7)

1.	李强，万兵兵，杨凯，朱涛. 高超声速尖锥边界层压力脉动和热流脉动特性试验. 航空学报. 2022(02): 240-248 . 百度学术
2.	沙心国，李睿劬，刘文伶，纪锋，袁湘江. 尖楔模型结构对脉动压力测量影响实验研究. 气体物理. 2021(03): 43-49 . 百度学术
3.	沙心国，郭跃，纪锋，袁湘江，沈清. 高超声速圆锥边界层失稳条纹结构实验研究. 空气动力学学报. 2020(01): 143-147 . 本站查看
4.	栗继伟，卢盼，汪球，赵伟. 激波风洞7°尖锥边界层转捩实验研究. 北京航空航天大学学报. 2020(11): 2087-2093 . 百度学术
5.	杨凯，朱涛，王雄，陶伯万，朱新新，王辉，杨庆涛. 原子层热电堆热流传感器研制及其性能测试. 实验流体力学. 2020(06): 86-91 . 百度学术
6.	任一鹏，杨小龙，林崧，于靖波，武玉玉，杨学军，朱莉，黄宇. 基于快速响应PSP技术的跨声速脉动压力实验研究. 宇航总体技术. 2019(01): 39-47 . 百度学术
7.	杨武兵，沈清，朱德华，禹旻，刘智勇. 高超声速边界层转捩研究现状与趋势. 空气动力学学报. 2018(02): 183-195 . 本站查看