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

Wang Darui; Zhang Nan

doi:10.3788/irla201746.0204003

[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] 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] 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] 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] 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] 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)