Thrust/Drag measurement techniques of a free flight scramjet in a shock tunnel

CHEN Yongfu; LU Hongbo; WEN Shuai; CHEN Xing; SUN Riming

doi:10.7638/kqdlxxb-2021.0300

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Thrust/Drag measurement techniques of a free flight scramjet in a shock tunnel

更新时间：2026-05-28

- Thrust/Drag measurement techniques of a free flight scramjet in a shock tunnel
- Vol. 40, Issue 1, Pages: 141-148(2022)
- 作者机构：
  
  中国航天空气动力技术研究院,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0300
  CLC： V211.751
- Published：2022
- 稿件说明：
移动端阅览
陈勇富, 卢洪波, 文帅, 等. 激波风洞超燃冲压发动机推阻测量技术[J]. 空气动力学学报, 2022, 40(1): 141−148.

CHEN Yongfu, LU Hongbo, WEN Shuai, et al. Thrust/Drag measurement techniques of a free flight scramjet in a shock tunnel[J]. 2022, 40(1): 141-148.
陈勇富, 卢洪波, 文帅, 等. 激波风洞超燃冲压发动机推阻测量技术[J]. 空气动力学学报, 2022, 40(1): 141−148. DOI： 10.7638/kqdlxxb-2021.0300

CHEN Yongfu, LU Hongbo, WEN Shuai, et al. Thrust/Drag measurement techniques of a free flight scramjet in a shock tunnel[J]. 2022, 40(1): 141-148. DOI： 10.7638/kqdlxxb-2021.0300.

摘要

面向高马赫数超燃冲压发动机推阻性能测量需求，基于FD-21高焓激波风洞，建立了基于自由飞原理的发动机模型推阻测量技术，创新引用了电永磁铁悬挂释放技术与高精度时序控制技术。设计了梯形多孔圆形阵列标记板，使用基于圆形特征阵列标记与图像识别技术的模型典型特征追踪方法，并对位移原始数据进行最近邻离群点剔除，用二阶中心差分求取模型加速度并进行傅里叶频谱分析，通过巴特沃斯低通滤波方法去除微分运算引入的高频噪声。进行了发动机模型自由落体运动试验和通流试验，探讨了自由飞测力技术的数据处理方法，获得了发动机模型的受力数据，给出了测量技术的精准度。在自由落体运动试验中，获得的加速度与当地标准重力加速度值偏差约为±2%。在FD-21风洞名义马赫数10模拟条件下进行了两次冲压发动机通流试验，获得的水平方向加速度相对偏差为2.32%，竖直方向加速度的相对偏差为7.44%。

Abstract

To investigate the performance of a Mach 8 scramjet

a free flight force measurement technique was developed in a high-enthalpy free piston driven shock tunnel FD-21. A nonlinear motion track method integrating the circular feature markers and image recognition was proposed. The scramjet model was suspended and released by a novel electric permanent magnet which controls the model accurately. A high-precision sequence control system was adopted to implement the time synchronization. To facilitate the tracking of the scramjet model

a trapezoidal porous circular array marker plate was designed and mounted on the outward surface of the model. The lamp-house illumination method was employed in the backlight system

in which the maximum power of the photosource is up to 300 W and the average brightness can reach 45000 Lux at one meter working distance. Based on the characteristics of circular array

a typical model tracking method using the image recognition technique was studied. An outlier elimination of the original displacement data was implemented using the nearest neighborhood algorithm. The noise-free acceleration was subsequently obtained by the second derivative of the filtered displacement. Data processing methods including the motion displacement extraction were discussed by two types of experiments involving a free-falling scramjet in the quiescent air and a free-flight scramjet without fuel injection at Mach 10. The force data of the engine model was obtained

and the precision of measurement technology was discussed. For the former

the measured gravity acceleration is consistent with the local true value with a deviation of only ±2%. For the latter

there exhibits a good repeatability with a deviation of 2.32% for the horizontal acceleration and 7.44% for the vertical acceleration. In the future research plan

the protection device of the electric permanent magnet will be further optimized. In addition

more measurement methods

such as triaxial accelerometers and stress wave balances

will be used to realize cross validation by comparing with the method based on multiple-circles tracking and backlight imaging

so as to verify the universality and applicability in the thrust resistance measurement of scramjets in high-enthalpy flows.

关键词

Keywords

references

URZAY J. Supersonic combustion in air-breathing propulsion systems for hypersonic flight[J]. Annual Review of Fluid Mechanics, 2018, 50(1): 593-627. DOI:10.1146/annurev-fluid-122316-045217

YU G , FAN X J . Supersonic combustion and hypersonic propulsion[J]. Advances in Mechanics, 2013, 43(5): 449-472. (in Chinese)

CURRAN E T. Scramjet engines: the first forty years[J]. Journal of Propulsion and Power, 2001, 17(6): 1138-1148. DOI:10.2514/2.5875

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

VANYAI T. Experimental investigation of a 3D thermal compression scramjet using advanced optical techniques[D]. University of Queensland Library, 2018. doi: 10.14264/uql.2018.247

DENMAN Z J, WHEATLEY V, SMART M K, et al. Supersonic combustion of hydrocarbons in a shape-transitioning hypersonic engine[J]. Proceedings of the Combustion Institute, 2017, 36(2): 2883-2891. DOI:10.1016/j.proci.2016.08.081

VANYAI T, GRIEVE S, STREET O, et al. Fundamental scramjet combustion experiments using hydrocarbon fuel[J]. Journal of Propulsion and Power, 2019, 35(5): 953-963. DOI:10.2514/1.b37472

HIRAIWA T, ITO K, SATO S, et al. Recent progress in scramjet/combined cycle engines at JAXA, Kakuda space center[J]. Acta Astronautica, 2008, 63(5-6): 565-574. DOI:10.1016/j.actaastro.2008.04.011

TAKAHASHI M, KOMURO T, SATO K, et al. Performance characteristics of scramjet engine with different combustor shapes at hypervelocity condition over Mach 10 flight[C]//43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, Cincinnati, OH. Reston, Virginia: AIAA, 2007. AIAA2007-5395. doi: 10.2514/6.2007-5395

SCHRAMM J M, SUNAMI T, ITO K, et al. Experimental investigation of supersonic combustion in the HIEST and HEG free piston shock tunnels[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, Nashville, TN. Reston, Virginia: AIAA, 2010. doi: 10.2514/6.2010-7122

LAURENCE S J, KARL S, MARTINEZ SCHRAMM J, et al. Transient fluid-combustion phenomena in a model scramjet[J]. Journal of Fluid Mechanics, 2013, 722: 85-120. DOI:10.1017/jfm.2013.56

LAURENCE S J, LIEBER D, MARTINEZ SCHRAMM J, et al. Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor. Part I: Shock-tunnel experiments[J]. Combustion and Flame, 2015, 162(4): 921-931. DOI:10.1016/j.combustflame.2014.09.016

YAO X Y, WANG C, YU J, et al. High-Mach-number scramjet engine tests in JF12 shock tunnel[J]. Physics of Gases, 2019, 4(5): 25-31. (in Chinese)

CHEN J M, CHEN X, BI Z X, et al. Review on experimental technology of high enthalpy shock tunnel[J]. Acta Aerodynamica Sinica, 2018, 36(4): 543-554. (in Chinese)

GU S D, OLIVIER H. Capabilities and limitations of existing hypersonic facilities[J]. Progress in Aerospace Sciences, 2020, 113: 100607. DOI:10.1016/j.paerosci.2020.100607

PAULL A, STALKER R J, MEE D J. Experiments on supersonic combustion ramjet propulsion in a shock tunnel[J]. Journal of Fluid Mechanics, 1995, 296: 159-183. DOI:10.1017/s0022112095002096

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

DOHERTY L. An experimental investigation of an airframe integrated three-dimensional scramjet engine at a Mach 10 flight condition[D]. University of Queensland Library, PhD Thesis, 2014. doi: 10.14264/uql.2014.382

MARIE T, HIDEYUKI T, TOMOYUKI K. Free-flight force measurement technique for scramjet powered vehicle in shock tunnel[C]//32nd International Symposium on Shock Waves (ISSW32 2019), Singapore: Research Publishing Services, 2019. doi: 10.3850/978-981-11-2730-4_0276-cd

TANNO M, TANNO H. Aerodynamic characteristics of a free-flight scramjet vehicle in shock tunnel[J]. Experiments in Fluids, 2021, 62(7): 1-12. DOI:10.1007/s00348-021-03229-0

HANNEMANN K, SCHRAMM J M, KARL S, et al. Free flight testing of a scramjet engine in a large scale shock tunnel[C]//Proc of the 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Glasgow, Scotland. Reston, Virginia: AIAA, 2015. AIAA 2015-3608. doi: 10.2514/6.2015-3608

HANNEMANN K, SCHRAMM J M, KARL S, et al. Enhancement of free flight force measurement technique for scramjet engine shock tunnel testing[C]//21st AIAA International Space Planes and Hypersonics Technologies Conference, Xiamen, China. Reston, Virginia: AIAA, 2017. AIAA 2017-2235. doi: 10.2514/6.2017-2235

JOARDER R, JAGADEESH G. A new free floating accelerometer balance system for force measurements in shock tunnels[J]. Shock Waves, 2003, 13(5): 409-412. DOI:10.1007/s00193-003-0225-y

LAURENCE S J, DEITERDING R, HORNUNG G. Proximal bodies in hypersonic flow[J]. Journal of Fluid Mechanics, 2007, 590: 209-237. DOI:10.1017/s0022112007007987

LAURENCE S J, HORNUNG H G. Image-based force and moment measurement in hypersonic facilities[J]. Experiments in Fluids, 2009, 46(2): 343-353. DOI:10.1007/s00348-008-0565-6

LAURENCE S J, KARL S. An improved visualization-based force-measurement technique for short-duration hypersonic facilities[J]. Experiments in Fluids, 2010, 48(6): 949-965. DOI:10.1007/s00348-009-0780-9

LAURENCE S J. On tracking the motion of rigid bodies through edge detection and least-squares fitting[J]. Experiments in Fluids, 2012, 52(2): 387-401. DOI:10.1007/s00348-011-1228-6

LAURENCE S J, BUTLER C S, MARTINEZ SCHRAMM J, et al. Force and moment measurements on a free-flying capsule in a shock tunnel[J]. Journal of Spacecraft and Rockets, 2017, 55(2): 403-414. DOI:10.2514/1.A33820

LU H B, CHEN X, SHEN J M, et al. Flight condition achievement of Mach number 8 in a new shock tunnel of CAAA and its scramjet experimental investigation[J]. Physics of Gases, 2019, 4(5): 13-24. (in Chinese)

INGLE V K, PROAKIS J G, 著. 数字信号处理(MATLAB版)[M]. 刘树棠, 陈志刚, 译. 西安: 西安交通大学出版社, 2013: 177-254.

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