测压孔径对下沉安装压力传感器测量的影响

doi:10.7527/S1000-6893.2018.22029

流体力学与飞行力学

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测压孔径对下沉安装压力传感器测量的影响

姚世勇, 闵昌万

中国运载火箭技术研究院空间物理重点实验室, 北京 100076

收稿日期:2018-01-19 修回日期:2018-03-07 出版日期:2018-12-15 发布日期:2018-07-13
通讯作者: 闵昌万 E-mail:minchangwan@126.com

Effects of opening diameter on measurement of recessed pressure transducers

YAO Shiyong, MIN Changwan

Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China

Received:2018-01-19 Revised:2018-03-07 Online:2018-12-15 Published:2018-07-13

摘要/Abstract

摘要： 对于高超声速飞行试验，飞行器在飞行过程中产生的气动加热会使其表面安装的传感器烧坏并导致试验测量失败。传感器下沉安装可以避免其与飞行器周围的高温气体直接接触，减轻传感器的热载荷。采用下沉安装传感器的方式对高超声速边界层的脉动压力进行了试验测量，研究了测压孔径对脉动压力特性的影响。结果表明，随着孔径增大，脉动压力强度减小，流场相关性增强。传感器下沉安装会引起空腔流动，随着孔径的增大，空腔流动对脉动压力测量的影响降低。在频带10~20 kHz范围内，测压孔径仅仅影响脉动压力强度，在频带1~10 kHz范围内，测压孔径对脉动压力波形周期的影响更为显著。非线性耦合将能量由高频小尺度向低频大尺度传递，导致发生自相互作用和非线性相位耦合的流动结构趋向低频，随着孔径增大，非线性相位耦合消失。此外，孔径越大，不同尺度结构的能量分布与齐平安装的相似性越高。

关键词: 测压孔径, 下沉安装, 高超声速, 脉动压力, 风洞试验

Abstract: Aerodynamic heating produced in the hypersonic flight test will destroy the pressure transducers mounted on the vehicle surface and lead to measurement failure. Recessed installation of transducers can avoid direct contact with the high temperature air surrounding the vehicles and abate the excessive heat loads. In this paper, experimental measurements of pressure fluctuations in a hypersonic boundary layer are carried out based on recessed installation of transducers and the effects of opening diameter on characteristics of fluctuating pressure are studied. The results show that the intensity of pressure fluctuation is reduced and the correlation of flow field is enhanced as the opening diameter increases. Recess mounting could cause cavity flow, and the influence of cavity flow on fluctuation pressure measurement is reduced as the opening diameter increases. Within the frequency band of 10-20 kHz, the opening diameter only mildly influences the fluctuating pressure intensity, but within the frequency band of 1-10 kHz, the opening diameter exerts more significant effects on the wave period of pressure fluctuations. Nonlinear phase lock resonance transfers the energy from high frequency structures to low frequency structures, leading to the flow structures occurring self-interaction and nonlinear phase coupling tending to the low frequency. As the opening diameter increases, the nonlinear phase coupling finally vanishes. In addition, the energy distributions of different scale structures share higher similarity with those under flush mounting with the increasing opening diameter.

Key words: opening diameter, recessed installation, hypersonic, pressure fluctuation, wind tunnel test

中图分类号:

V411

姚世勇, 闵昌万. 测压孔径对下沉安装压力传感器测量的影响[J]. 航空学报, 2018, 39(12): 122029-122029.

YAO Shiyong, MIN Changwan. Effects of opening diameter on measurement of recessed pressure transducers[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(12): 122029-122029.

参考文献

[1] 李周复. 风洞特种试验技术[M]. 北京:航空工业出版社, 2010. LI Z F. Special test techniques for wind tunnel[M]. Beijing:Aviation Industry Press, 2010(in Chinese).
[2] 原正庭. 亚音速飞机压力分布测量[J]. 航空学报, 1998, 19(4):486-488. YUAN Z T. In-flight measurement of static pressure on a subsonic transport aircraft[J]. Acta Aeronautica et Astronautica Sinica, 1998, 19(4):468-488(in Chinese).
[3] 陈怦, 余俊雅, 张德元, 等. 三角翼飞机气动压力测量试飞技术研究[J]. 飞行力学, 2001, 19(3):56-59. CHEN P, YU J Y, ZHANG D Y, et al. Flight test research of aerodynamics pressure measurement technique for a delta-wing aircraft[J]. Flight Dynamics, 2001, 19(3):56-59(in Chinese).
[4] 曹虎成, 周占廷, 李少鹏. 运输机襟翼压力分布飞行试验测量[J]. 实验流体力学, 2010, 24(3):96-98. CAO H C, ZHOU Z T, LI S P. In-flight test measurement of flap pressure distribution for aerotransport[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(3):96-98(in Chinese).
[5] 褚江, 王晓江, 陈胜杰. 超音速下压力分布测量飞行试验研究[J]. 科学技术与工程, 2012, 12(12):2893-2896. CHU J, WANG X J, CHEN S J. In-flight investigation of pressure distribution measurement in the supersonic flow[J]. Science Technology and Engineering, 2012, 12(12):2893-2896(in Chinese).
[6] RAMAN K R. Surface pressure fluctuations in hypersonic turbulent boundary layers:AIAA-1973-0997[R]. Reston, VA:AIAA, 1973.
[7] JULIANO T J. Nozzle modification for high-Reynolds-number quiet flow in the Boeing/AFOSR Mach-6 quiet tunnel[D]. West Lafayette, IN:Purdue University, 2006.
[8] CASPER K M, Hypersonic wind-tunnel measurements of boundary-layer pressure fluctuations[D]. West Lafayette, IN:Purdue University, 2009.
[9] GILBERT P L. Effect of tunnel noise on laminar stagnation-point heating at Mach 6[D]. West Lafayette, IN:Purdue University, 2010.
[10] WHEATON B M. Roughness-induced instabilities in a Mach-6 laminar boundary layer[D]. West Lafayette, IN:Purdue University, 2012.
[11] MARINEAU E C, MORARU C G, LEWIS D R, et al. Mach 10 boundary-layer transition experiments on sharp and blunted cones:AIAA-2014-3108[R]. Reston, VA:AIAA, 2014.
[12] JULIANO T J, BORG M P, SCHNEIDER S P. Quiet tunnel measurements of HIFiRE-5 boundary-layer transition[J]. AIAA Journal, 2015, 53(4):832-846.
[13] BORG M P, KIMMEL R L, STANFIELD S. Traveling crossflow instability for the HIFiRE-5 elliptic cone[J]. Journal of Spacecraft and Rockets, 2015, 52(3):664-673.
[14] HANLY R D. Effects of transducer flushness on fluctuating surface pressure measurements:AIAA-1975-0534[R]. Reston, VA:AIAA, 1975.
[15] HOWE J R, LANGANELLI A L. Surface pressure fluctuation measurements in attached transitional turbulent boundary layers at supersonic and hypersonic speeds:AIAA-1977-0113[R]. Reston, VA:AIAA, 1977.
[16] BERRY S A, CHEN F J, WILDER M C, et al. Boundary layer transition experiments in support of the hypersonics program:AIAA-2007-4266[R]. Reston, VA:AIAA, 2007.
[17] HANNEMANN K, SCHRAMM J M, WAGNER A, et al. A closely coupled experimental and numerical approach for hypersonic and high enthalpy flow investigations utilising the HEG shock tunnel and the DLR TAU code:NATO TR RTO-EN-AVT-186[R]. 2010.
[18] WELCH P D. The use of fast Fourier transform for the estimation of power spectra:A method based on time averaging over short, modified periodograms[J]. IEEE Transactions on Audio and Electroacoust, 1967, 15(2):70-73.
[19] 韩健. 高超声速尖锥边界层流动稳定性的子波分析与互双谱分析[D]. 天津:天津大学, 2010. HAN J. Wavelet analysis and cross bispectrum analysis of flow instability for hypersonic sharp cone boundary layer[D]. Tianjin:Tianjin University, 2010(in Chinese).
[20] FARGE M. Wavelet transforms and their applications to turbulence[J]. Annual Review of Fluid Mechanics, 1992, 24:395-458.

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测压孔径对下沉安装压力传感器测量的影响

Effects of opening diameter on measurement of recessed pressure transducers

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