Research of scramjet thrust test in shock tunnel

ZHAO Rongjuan; LIU Shiran; ZHOU Zheng; WU Liyin; LYU Zhiguo

doi:10.11729/syltlx20210025

Volume 36 Issue 4

Sep. 2022

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2022 > 36(4): 103-108

ZHAO R J，LIU S R，ZHOU Z，et al. Research of scramjet thrust test in shock tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022，36（4）：103-108. doi: 10.11729/syltlx20210025

Citation:

ZHAO R J，LIU S R，ZHOU Z，et al. Research of scramjet thrust test in shock tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022，36（4）：103-108. doi: 10.11729/syltlx20210025

Citation:

ZHAO R J，LIU S R，ZHOU Z，et al. Research of scramjet thrust test in shock tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022，36（4）：103-108. doi: 10.11729/syltlx20210025

PDF( 5382 KB)

Research of scramjet thrust test in shock tunnel

doi: 10.11729/syltlx20210025

ZHAO Rongjuan^{1, 2
,},
LIU Shiran¹,
ZHOU Zheng²,
WU Liyin¹,
LYU Zhiguo^{1
,
,}

1.
Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China
2.
Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China

Received Date: 2021-03-26
Accepted Date: 2021-07-12
Rev Recd Date: 2021-07-03

Available Online: 2022-09-23

Publish Date: 2022-09-02

Abstract

Abstract

In order to meet the need of high-Mach number scramjet development, the scramjet thrust test technique in the shock tunnel is studied. A piezoelectric balance is used to test the scramjet thrust in the shock tunnel. The research includes the balance design, calibration and thrust test in the shock tunnel. The finite element analysis method is used in the balance design to optimize the balance structure. The simulation results show that the sensitivity of the balance can reach 17.447 mV/N, and the first-order frequency mode can reach 1022.40 Hz. The validation test is conducted in the shock tunnel with the fuel and without the fuel injection. The test results show that, the difference of the drag force is about 220 N between two different experimental conditions. Which means the thrust of the scramjet under different conditions can be distin-guished with the new developed balance.
- piezoelectric balance,
- scramjet,
- thrust test,
- shock tunnel

FullText(HTML)

References(21)

References

[1]	ITOH K. Aerothermodynamic and scramjet tests in high enthalpy shock tunnel[R]. AIAA 2007-1041, 2007. doi: 10.2514/6.2007-1041
[2]	TAKAHASHI M, UEDA S, KOMURO T, et al. Development of a new force measurement method for scramjet testing in a high enthalpy shock tunnel[R]. AIAA-99-4961, 1999. doi: 10.2514/6.1999-4961
[3]	ITOH K, UEDA S, KOMURO T, et al. Hypervelocity aerothermodynamic and propulsion research using a high enthalpy shock tunnel HIEST[R]. AIAA-99-4960, 1999. doi: 10.2514/6.1999-4960
[4]	ROBINSON M J,MEE D J,PAULL A. Scramjet lift, thrust and pitching-moment characteristics measured in a shock tunnel[J]. Journal of Propulsion and Power,2006,22(1):85-95. doi: 10.2514/1.15978
[5]	ROBINSON M J,MEE D J,TSAI C Y,et al. Three-component force measurements on a large scramjet in a shock tunnel[J]. Journal of Spacecraft and Rockets,2004,41(3):416-425. doi: 10.2514/1.10699
[6]	STALKER R J,PAULL A,MEE D J,et al. Scramjets and shock tunnels—The Queensland experience[J]. Progress in Aerospace Sciences,2005,41(6):471-513. doi: 10.1016/j.paerosci.2005.08.002
[7]	STALKER R J, SIMMONS J M, PAULL A, et al. Measurement of scramjet thrust in shock tunnels[R]. AIAA 94-2561, 1994. doi: 10.2514/6.1994-2516
[8]	ODAM J, PAULL A. Comparison of experimental thrust measurements with theoretical values for a scramjet engine[R]. AIAA 2003-6961, 2003. doi: 10.2514/6.2003-6961
[9]	HASS N, SHIH A, ROGERS R. Mach 12 & 15 scramjet test capabilities of the HYPULSE shock-expansion tunnel[R]. AIAA 2005-690, 2005. doi: 10.2514/6.2005-690
[10]	HANNEMANN K, SCHRAMM J M, KARL S, et al. Enhancement of free flight force measurement technique for scramjet engine shock tunnel testing[R]. AIAA 2017-2235, 2017. doi: 10.2514/6.2017-2235
[11]	HANNEMANN K, SCHRAMM J M, KARL S, et al. Free flight tesing of a scramjet engine in a large scale shock tunnel[R]. AIAA 2015-3608, 2015. doi: 10.2514/6.2015-3608
[12]	HOLDEN M S, WADHAMS T P, MACLEAN M, et al. A review of basic research and development programs conducted in the LENS facilities in hypervelocity folws[R]. AIAA 2012-0469, 2012. doi: 10.2514/6.2012-0469
[13]	DEIWERT G S, CAVOLOWSKY J A. Large scale scramjet tesing in the Ames 16 Inch Shock Tunnel[R]. AIAA 94-2519, 1994. doi: 10.2514/6.1994-2519
[14]	贺伟,童泽润,李宏斌. 单模块超燃发动机推力测量天平研制[J]. 航空动力学报,2010,25(10):2285-2289. HE W,TONG Z R,LI H B. Investigation of thrust balance for the single module scramjet[J]. Journal of Aerospace Power,2010,25(10):2285-2289.
[15]	汪运鹏,刘云峰,苑朝凯,等. 长试验时间激波风洞测力技术研究[J]. 力学学报,2016,48(3):545-556. doi: 10.6052/0459-1879-15-295 WANG Y P,LIU Y F,YUAN C K,et al. Study on force measurement in long-test duration shock tunnel[J]. Chinese Journal of Theoretical and Applied Mechanics,2016,48(3):545-556. doi: 10.6052/0459-1879-15-295
[16]	DURYEA G R,MARTIN J F. An improved piezoelectric balance for aerodynamic force[J]. IEEE Transactions on Aerospace and Electronic Systems,1968,AES-4(3):351-359. doi: 10.1109/TAES.1968.5408988
[17]	吕治国,刘洪山,齐学群,等. 飞船返回舱再入阶段高超声速六分量测力试验研究[J]. 空气动力学学报,2003,21(3):282-287. doi: 10.3969/j.issn.0258-1825.2003.03.004 LYU Z G,LIU H S,QI X Q,et al. Experiment study of hypersonic six-component force measurement for re-entry module in shock tunnel[J]. Acta Aerodynamica Sinica,2003,21(3):282-287. doi: 10.3969/j.issn.0258-1825.2003.03.004
[18]	黄军,邱华诚,刘施然,等. 应用于激波风洞的半导体应变天平技术研究[J]. 实验流体力学,2020,34(6):79-85. doi: 10.11729/syltlx20190122 HUANG J,QIU H C,LIU S R,et al. Research on semiconductor strain gage balance technology applied in shock tunnel[J]. Journal of Experiments in Fluid Mechianics,2020,34(6):79-85. doi: 10.11729/syltlx20190122
[19]	SCHEWE G,STEINHOFF C. Force measurements on a circular cylinder in a Cryogenic Ludwieg-Tube using piezoelectric transducers[J]. Experiments in Fluids,2007,42(3):489-494. doi: 10.1007/s00348-007-0250-1
[20]	SILVESTER T B,MORGAN R G. Skin-friction measurements and flow establishment within a long duct at superorbital speeds[J]. AIAA Journal,2008,46(2):527-536. doi: 10.2514/1.32668
[21]	赵荣娟,黄军,刘施然,等. ANSYS在压电天平设计中的应用[J]. 实验流体力学,2020,34(1):96-102. doi: 10.11729/syltlx20190005 ZHAO R J,HUANG J,LIU S R,et al. Application of ANSYS in piezoelectric balance design[J]. Journal of Experiments in Fluid Mechanics,2020,34(1):96-102. doi: 10.11729/syltlx20190005