Accurate infrared radiance measurement of H<sub>2</sub>O<sub>2</sub>-kerosene rocket engine flume

Chen Hao; Li Shuaihui; Chen She; Li Sen; Li Teng; Wei Xiaolin; Yu Xilong; Fan Jing

doi:10.11729/syltlx20180171

Volume 33 Issue 5

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Chen Hao, Li Shuaihui, Chen She, et al. Accurate infrared radiance measurement of H2O2-kerosene rocket engine flume[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 76-80, 86. doi: 10.11729/syltlx20180171

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Chen Hao, Li Shuaihui, Chen She, et al. Accurate infrared radiance measurement of H₂O₂-kerosene rocket engine flume[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 76-80, 86. doi: 10.11729/syltlx20180171

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Accurate infrared radiance measurement of H₂O₂-kerosene rocket engine flume

doi: 10.11729/syltlx20180171

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

Received Date: 2018-11-07
Rev Recd Date: 2019-06-13
Publish Date: 2019-10-25

Abstract

Abstract

The quantitative measurement of infrared radiation (IR) of the attitude and orbit control rocket engine flume plays a key role in the aircraft penetration effectiveness research and in verification of the numerical simulation of the rocket engine flume flow field. In order to study the IR field of the rocket engine flume quantitatively, an experiment is conducted to measure the IR characteristics of the flume of one H₂O₂-kerosene small rocket engine. A cooled midwave infrared camera with a spectral band of 3.7~4.8 μm is developed. The detector, which has a mean NETD of 16 mK and an output resolution of 16 bits, is highly sensitive and has a wide dynamic range. With radiation calibration and calibration error analysis, the obtained grayscale images are converted, and the IR field distribution of the engine flume in the midwave infrared spectral band is acquired. The experiment result shows distinct Mach disks in the plume, and the peak radiation of the plume in the midwave infrared spectral band is 184 W/(m²·sr) with a measurement accuracy of 12 W/(m²·sr).
- engine flume,
- H₂O₂-kerosene,
- midwave infrared,
- radiance,
- Mach disk

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References(16)

References

[1]	李帅辉, 王育人, 樊菁.大气环境对空间红外探测影响的研究[C]//第十二届全国物理力学学术会议论文集. 2012. Li S H, Wang Y R, Fan J. Study of the effect of the atmosphere environment on the space limb infrared detection[C]//Proc of the 12th National Conference on Physical Mechanics. 2012.
[2]	Stair A T. MSX design parameters driven by targets and backgrounds[J]. Johns Hopkins Apl Technical Digest, 1996, 17(1):11.
[3]	Rochelle W C. Review of thermal radiation from liquid and solid propellant rocket exhausts[R]. NASA-TM-X-53579.
[4]	Nelson H F. Infrared radiation signature of tactical rocket exhausts[R]. AIAA-82-913, 1982.
[5]	Surzhikov S T. Monte Carlo simulation of plumes spectral emission[R]. AIAA-2003-3895, 2003.
[6]	陆伟宁.弹道导弹攻防对抗技术[M].北京:中国宇航出版社, 2007. Lu W N. Countermine technology of ballistic missile[M]. Beijing:China astronautic publishing house, 2007.
[7]	Harwell K E, Hyman W D, Jackson H T Jr, et al. Effects of external flow velocity on the spatial distribution of infrared radiation from a rocket exhaust plume[R]. AIAA-1976-443, 1976.
[8]	Devir A D, Lessin A B, Cohen Y, et al. Comparison of calculated and measured radiation from a rocket motor plume[R]. AIAA-2001-358, 2001.
[9]	Rankin B A, Gore J P, Hoke J L, et al. Radiation measurements and temperature estimates of unsteady exhaust plumes exiting from a turbine driven by pulsed detonation combustion[R]. AIAA-2013-0886, 2013.
[10]	贺博, 龚晓红, 林辉, 等.红外热像仪在固体火箭发动机羽焰测温中的应用[J].固体火箭技术, 2005, 28(2):153-156. doi: 10.3969/j.issn.1006-2793.2005.02.020 He B, Gong X H, Lin H, et al. Application of infrared thermal imaging device in temperature measurement of solid rocket motor plume[J]. Journal of Solid Rocket Technology, 2005, 28(2):153-156. doi: 10.3969/j.issn.1006-2793.2005.02.020
[11]	李建勋, 童中翔, 刘万俊, 等.航空发动机红外辐射实验与仿真[J].红外与激光工程, 2013, 42(3):549-555. doi: 10.3969/j.issn.1007-2276.2013.03.003 Li J X, Tong Z X, Liu W J, et al. Infrared radiation characteristic experiment and simulation of aeroengine[J]. Infrared and Laser Engineering, 2013, 42(3):549-555. doi: 10.3969/j.issn.1007-2276.2013.03.003
[12]	李帅辉, 陈涉, 余西龙, 等.地球大气中波红外辐射特性机载试验研究[C]//第七届全国高超声速科技学术会议论文集. 2014. Li S H, Chen S, Yu X L, et al. Study of airborne experiment of the earth-atmosphere medium-wave infrared radiation[C]//Proc of the 7th National Conference on Hypersonic Technology. 2014.
[13]	陆子凤.红外热像仪的辐射定标和测温误差分析[D].长春: 长春光学精密机械与物理研究所, 2010. Lu Z F. Calibration and the measurement error analysis of infrared imaging system for temperature measurement[D]. Changchun: Changchun Institute of Optics, Fine Mechanics and Physics, 2010.
[14]	陈钱, 隋修宝.红外图像处理理论与技术[M].北京:电子工业出版社, 2018. Chen Q, Sui X B. Infrared image processing theory and technology[M]. Beijing:Publishing House of Electronics Industry, 2018.
[15]	Li S, Ge Y, Wei X, et al. Mixing and combustion modeling of hydrogen peroxide/kerosene shear-coaxial jet flame in lab-scale rocket engine[J]. Aerospace Science and Technology, 2016, 56:148-154. doi: 10.1016/j.ast.2016.07.008
[16]	张小英, 向红军, 朱定强.固体火箭发动机地面和飞行过程中羽流红外辐射的计算研究[J].红外技术, 2016, 38(1):81-87. http://d.old.wanfangdata.com.cn/Periodical/hwjs201601014 Zhang X Y, Xiang H J, Zhu D Q. Study on plume infrared radiation of solid rocket in ground test and flight condition[J]. Infrared Technology, 2016, 38(1): 81-87. http://d.old.wanfangdata.com.cn/Periodical/hwjs201601014