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《Opto-Electronic Engineering》 2010-10
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Numerical Simulation of the Infrared Radiation of Satellite Orbit-control Thruster Plume

JIN Wei~a, b,LING Yong-shun~b,Lü Xiang-yin~b ( a. State Key Lab of Pulsed Power Laser Technology; b. Key Lab of Infrared and Low Temperature Plasma of Anhui Province, Electronic Engineering Institute, Hefei 230037, China )  
To totally obtain infrared characteristic of satellites, it was necessary to know the infrared characteristic of satellite orbit-control thruster plume. A complete model for calculating the infrared radiation of satellite orbit-control thruster plume was founded. The model calculated the plume flow field, absorption coefficient and radiative luminance by using Finite Volume Method (FVM) in order. According to the spectral luminance obtained by using the model, the spectral and band radiative intensity at the range of 1 000~4 500 cm-1 were calculated further. Through analysis of the intensity, the spectral intensity values at 1 525 cm-1, 1 700 cm-1, 2 155 cm-1, 2 175 cm-1, 2 350 cm-1 and 3 750 cm-1 are larger than the values at other spectrums; and the largest band intensity may be corresponding to different azimuth angle at different vertical distance to the nozzle exiting plane. The figure of spectral intensity curve at 2 350 cm-1 and 3 750 cm-1 well agrees with the figures in similar papers. The result shows that the calculation model is reliable and accurate.
【Fund】: 国家863计划项目
【CateGory Index】: V435.6
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【Citations】
Chinese Journal Full-text Database 5 Hits
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【Co-citations】
Chinese Journal Full-text Database 10 Hits
1 ZHANG Xiao-ying1,ZHU Ding-qiang2,CAI Guo-biao2(1.School of Electric Power,South China University of Technology,Guangzhou 510640,China;2.Beijing University of Aeronautics and Astronautics,Beijing 100083,China);Calculation on infrared characteristics of rocket motor nozzle by using enclosed cavity-radiative heat flux method[J];Journal of Solid Rocket Technology;2007-02
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【Secondary Citations】
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