Study of liquid rocket engine plume flow field measurement based on the technology of infrared

Wang Darui; Zhang Nan

doi:10.3788/IRLA201746.0204003

Fourier infrared spectrometer and thermal imager can be used to measure infrared spectra and image of conventional liquid rocket plume flow field. The infrared spectral of plume flow field was detected, the main products of combustion H2O, CO2, and traces of combustion products NO and N2O were measured. The plume flow field structure was captured by infrared image, the relationship between the image characteristics and combustion state was set up. The results show that the infrared spectrometer and infrared thermal imager can accurately measure characteristics of plume flow field combustion products, the flow field structure and the application of infrared technology for the engine work condition monitoring provides a new analysis method.

Study of liquid rocket engine plume flow field measurement based on the technology of infrared

1. Beijing Aerospace Propulsion Institute,Beijing 100076,China

Received Date: 2016-06-05

Rev Recd Date: 2016-07-10

Publish Date: 2017-02-25

Key words:

Fourier transform infrared spectrometer /
infrared thermal imager /
liquid rocket engine /
plume flow field /
condition monitoring

Abstract: Fourier infrared spectrometer and thermal imager can be used to measure infrared spectra and image of conventional liquid rocket plume flow field. The infrared spectral of plume flow field was detected, the main products of combustion H2O, CO2, and traces of combustion products NO and N2O were measured. The plume flow field structure was captured by infrared image, the relationship between the image characteristics and combustion state was set up. The results show that the infrared spectrometer and infrared thermal imager can accurately measure characteristics of plume flow field combustion products, the flow field structure and the application of infrared technology for the engine work condition monitoring provides a new analysis method.

HTML

Reference (8)

[1]	Harwell K E, Jackson Jr, Poslajko F. Comparison of theoretical and experimental spatial distribution of infrared radiation in a rocket exhaust[C]//AIAA, 1977:77-736.
[2]	Herget W F. Infrared spectroradiometer for rocket exhaust analysis[C]//NASA TeCH BRIEF, 1968:10081-10085.
[3]	Karabadzak G F, Teslenko V, Drakes J A, et al. Experimentation using the Mir Station as a space laboratory[C]//AIAA, 1998:1-8.
[4]	Yuan Zonghan, Sun Mei, Liu Guisheng. Application of IR thermal imaging system on the inspection of characteristic signal of solid propellant[J]. Laser and Infrared, 1996, 26(2):121-124. (in Chinese)袁宗汉, 孙美, 刘桂生. 固体推进剂特征信号的红外热像检测[J]. 激光与红外, 1996, 26(2):121-124.
[5]	Zhang Xiaoling, Li Chunying, Wang Hong. FTIR spectrum telemetry radiant energy of solid rocket propelant combustion[J]. Journal of Guangxi Normal University, 2003, 21(2):205-207. (in Chinese)张小玲, 李春迎, 王宏. FTIR光谱遥测固体火箭发动机推进剂燃烧辐射能[J]. 广西师范大学学报, 2003, 21(2):205-207.
[6]	Sun Xiaogang, Dai Jingmin, Cong Dacheng. Plume temperature measurement of a solid propellant rocket engine using multispectral thermometry[J]. Journal Tsinghua Univ(Sci Tech), 2003, 43(7):916-922. (in Chinese)孙晓刚, 戴景民, 丛大成. 基于多光谱法的固体火箭发动机羽焰温度测量[J]. 清华大学学报, 2003, 43(7):916-922.
[7]	Zhang Jinmin, Yuan Hua, Liu Junfeng. IR measuring technology for solid propellant plume[J]. Journal of Solid Rocket Technology, 2004, 27(2):161-164. (in Chinese)张劲民, 袁华, 刘俊峰. 固体推进剂红外辐射强度测试技术[J]. 固体火箭技术, 2004, 27(2):161-164.
[8]	Wang Darui, Zhang Nan, Ge Minghe. Infrared image study on gas external flow field of liquid rocket engine nozzle[J]. Missiles and Space Vehicles, 2016(2):26-30. (in Chinese)王大锐, 张楠, 葛明和. 液体火箭发动机喷管燃气外流场红外图像研究[J]. 导弹与航天运载技术, 2016(2):26-30.

Study of liquid rocket engine plume flow field measurement based on the technology of infrared

doi: 10.3788/IRLA201746.0204003

Abstract

References

Proportional views

通讯作者: 陈斌, bchen63@163.com

Article Metrics

Related

Proportional views