红外与激光工程, 2017, 46 (2): 0204003, 网络出版: 2017-03-31   

基于红外技术的液体火箭发动机尾焰流场测量研究

Study of liquid rocket engine plume flow field measurement based on the technology of infrared
作者单位
北京航天动力研究所, 北京 100076
摘要
利用傅里叶红外光谱仪(FTIR)和热像仪对常规液体火箭发动机尾焰流场红外光谱和图像进行了测量研究。红外光谱检测出了尾焰流场中的主要燃烧产物H2O、CO2以及微量燃烧产物NO、N2O。红外图像捕捉到了尾焰流场结构, 建立了图像特征与燃烧状态之间的关系。研究结果表明: 红外光谱仪和红外热像仪可对尾焰特征燃烧产物、流场结构进行精确测量, 红外技术的应用为发动机工作状态监测提供一种新的分析手段。
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.
参考文献

[1] Herget W F. Infrared spectroradiometer for rocket exhaust analysis[C]//NASA TeCH BRIEF, 1968: 10081-10085.

[2] 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.

[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] 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.

    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)

[5] 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.

    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)

[6] 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.

    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)

[7] 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.

    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)

[8] 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.

    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. 基于红外技术的液体火箭发动机尾焰流场测量研究[J]. 红外与激光工程, 2017, 46(2): 0204003. Wang Darui, Zhang Nan. Study of liquid rocket engine plume flow field measurement based on the technology of infrared[J]. Infrared and Laser Engineering, 2017, 46(2): 0204003.

本文已被 1 篇论文引用
被引统计数据来源于中国光学期刊网
引用该论文: TXT   |   EndNote

相关论文

加载中...

关于本站 Cookie 的使用提示

中国光学期刊网使用基于 cookie 的技术来更好地为您提供各项服务,点击此处了解我们的隐私策略。 如您需继续使用本网站,请您授权我们使用本地 cookie 来保存部分信息。
全站搜索
您最值得信赖的光电行业旗舰网络服务平台!