A method to determine the domain of a rocket exhaust plume

Liu Zunyang; Sun Xiaoquan; Shao Li; Wang Yafu

Volume 43 Issue 3

Apr. 2014

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Article Navigation > Infrared and Laser Engineering > 2014 > 43(3): 754-761

Liu Zunyang, Sun Xiaoquan, Shao Li, Wang Yafu. A method to determine the domain of a rocket exhaust plume[J]. Infrared and Laser Engineering, 2014, 43(3): 754-761.

Citation:

Liu Zunyang, Sun Xiaoquan, Shao Li, Wang Yafu. A method to determine the domain of a rocket exhaust plume[J]. Infrared and Laser Engineering, 2014, 43(3): 754-761.

A method to determine the domain of a rocket exhaust plume

1.
State Key Laboratory of Pulsed Power Laser Technology,Electronic Engineering Institute,Hefei 230037,China

Received Date: 2013-07-12
Rev Recd Date: 2013-08-10
Publish Date: 2014-03-25

Abstract

Aimed at calculating the infrared radiation of a rocket exhaust plume exactly and efficiently, a method for defining the domain of an exhaust plume was reported. As a basic work, the flow field was calculated by using the CFD software FLUENT, and the radiation was calculated by means of Finite Volume Method (FVM). Then, variables that might be able to be used to differentiate an exhaust plume from surrounding atmosphere such as temperature and species composition were studied and the mass fraction of CO was chosen. When calculating the infrared radiation of an exhaust plume, only the part where the CO mass fraction bigger than the threshold was taken into account, and the rest were neglected. The change law of size of calculation domain, calculation time and infrared radiation with thresholds were studied. The results show that, as the threshold decreases, the size of calculation domain and the calculation time increase monotonously and rapidly, while the infrared radiation changes a lot at first and becomes stable at last. Besides, it was indicated by simulation experiments that the CO mass fraction 0.000 5 as the threshold is acceptable to define the calculation domain of the exhaust plume.
- rocket exhaust plume,
- infrared radiation intensity calculation,
- domain definition,
- threshold

References

[1]	Nelson H F. Infrared radiation signature of tactical rocket exhausts [C]//St. Louis, Missouri: AIAA,AIAA/ASME 3rd Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference, 1985: AIAA-82-0913.
[2]
[3]
[4]	Rochelle W C. Review of thermal radiation from liquid and solid propellant rocket exhausts [R]. Huntsville: Marshall Space Flight Center, 1967: NASA TM X-53579.
[5]
[6]	Devir A, Lessin A, Lev M, et al. Comparison of calculated and measured radiation from a rocket motor plume [C]// Reno, Nevada: AIAA,39th AIAA Aerospace Sciences Meeting Exhibit, 2001: 2001-0358.
[7]
[8]	Duval R, Soufiani A, Taine J. Coupled radiation and turbulent multiphase flow in an aluminised solid propellant rocket engine [J]. Journal of Quantitative Spectroscopy Radiative Transfer, 2004, 84: 513-526.
[9]
[10]	Jiang Yi, Fu Debin. Numerical simulation for non equilibrium chemically reacting fluid field of the solid rocket motor exhaust plume [J]. Journal of Astronautics, 2008, 29 (2): 615-620.
[11]
[12]	Wang W, Wei Z, Zhang Q, et al. Study on infrared signature of solid rocket motor afterburning exhaust plume [C]// Nashville, TN: 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, 2010: AIAA 2010-6847.
[13]	Wang W, Wei Z, Zhang Q, et al. Infrared radiation signature of exhaust plume from solid propellants of different energy characteristics[C]//San Diego, California: 47th AIAA/ASME/ SAE/ASEE Joint Propulsion Conference Exhibit, 2011: AIAA 2011-6140.
[14]
[15]	Reardon J E, Lee Y C. A computer program for thermal radiation from gaseous rocket exhuast plumes(GASRAD)[R]. NASA-CR-161496, 1980:NASA-CR-161496.
[16]
[17]
[18]	Ludwig C B, Malkmus W, Walker J. The standardized infrared radiation mode[C], 1981: AIAA-81-1051.
[19]	Markarian P, Kosson R. Standardized Infrared Radiation Model (SIRRM-II) [R]. NY: Grumman Aerospace Corp, 1988: AFAL-87-098.
[20]
[21]	Surzhikov S T. Monte Carlo Simulation of Plumes Spectral Emission [R]. Institute for Problems in Mechanics Russian Academy of Sciences(IPMech RAS), 2006:
[22]
[23]	Shuai Y, Dong S K, Tan H P. Simulation of the infrared radiation characteristics of high-temperature exhaust plume including particles using the backward Monte Carlo method[J]. Journal of Quantitative Spectroscopy Radiative Transfer, 2005, 95: 231-240.
[24]
[25]
[26]	Shuai Yong, Dong Shikui, Liu Linhua. Simulation of infrared radiation characteristics of high temperature free-stream flow including particles by using backward Monte Carlo method[J]. Journal of Infrared and Millimeter Waves, 2005, 24(2): 100-104.
[27]
[28]	Shuai Yong, Dong Shikui, Tan Heping. Numerical simulation for infrared radiation characteristics of exhaust plume at 2.7 m [J]. Acta Aeronautica et Astronautica Sinica, 2005, 26(4): 402-405.
[29]
[30]	Cai G, Zhu D, Zhang X. Numerical simulation of the infrared radiative signatures of liquid and solid rocket plumes[J]. Aerospace Science and Technology, 2007(11): 473-480.
[31]	Fan Shiwei, Zang Xiaoying, Zhu Dingqiang, et al. Calculation of the infrared characteristics of the solid rocket plume with FVM method[J]. Journal of Astronautics, 2005, 26(6): 794-797.
[32]
[33]
[34]	Coelho P J. Fundamentals of a new method for the solution of the radiative transfer equation[J]. International Journal of Thermal Sciences, 2005, 44: 809-821.
[35]
[36]	Zhang Xiaoying, Zhu Dingqiang, Cai Guobiao. Study the infrared characteristics of the solid rocket plume with DOM method and the influence of altitude [J]. Journal of Astronautics, 2007, 28(3): 702-706.
[37]	Dong Shikui, Yu Jianguo, Li Donghui. Numerical modeling of infrared radiation properties of exhaust plume by the Discrete Ordinates Method in body-fitted coordinates [J]. Journal of University of Shanghai for Science and Technology, 2003, 25(2): 159-163.
[38]
[39]
[40]	Edwards D K, Babikian D S. Radiation from a nongray scattering, emitting, and absorbing solid rocket motor plume[J]. J Thermophysics, 1990, 4(4): 446-453.
[41]	Surzhikov S T. Three-dimensional model of the spectral emissivity of light-scattering exhaust plumes [J]. High Temperature, 2004, 42(5): 763-775.
[42]
[43]	Hao Jinbo, Dong Shikui, Tan Heping. Numerical simulation of infrared radiation properties of solid rocket engine exhaust plume[J]. Journal of Infrared and Millimeter Waves, 2003, 22(4): 246-250.
[44]
[45]	Nie Wansheng, Yang Junhui, He Haosheng, et al. The IR radiation characteristic of exhaust plume of the liquid rocket engine [J]. Journal of National University of Defense Technology, 2005, 27(5): 91-94.
[46]
[47]
[48]	Feng S, Nie W, Xie Q, et al. Numerical simulation of flow field and radiation of an aluminized solid-opellant rocket multiphase exhaust plume [C]//Miami, FL: 39th AIAA Thermophysics Conference, 2007: AIAA 2007-4415.
[49]
[50]	Dong Shikui, Tan Heping, Yu Qizheng, et al. Infrared radiative spectral band-model parameters for water vapor in the 300- 3000 K temperature range [J]. Journal of Engineering for Thermal Energy and Power, 2001, 16(1): 33-38.
[51]	Dong Shikui, Yu Qizheng, Tan Heping, et al. Narrow band model parameters of high temperature radiation for carbon dioxide of combustion products [J]. Journal of Aerospace Power, 2001, 16(4): 355-359.
[52]
[53]	Siegel R, Howell R J. Thermal Radiation Heat Transfer [M]. Washington D C: Hemisphere and McGraw-Hill, 1981.
[54]
[55]
[56]	Nelson H F. Influence of participates on infrared emission from tactical rocket exhausts [J]. J Spacecraft, 1984, 21(5): 425-432.
[57]
[58]	Simmons F S. Rocket Exhaust Plume Phenomenology [M]. EI Segundo: CA: The Aerospace Press and American Institute of Aeronautics and Astronautics, 2000.
[59]	Zhang Guangming, Sun Shengli, Zhang Wei, et al. Model and application of image plane illumination for the space- based infrared detecting of boost-phase missile [J]. Journal of Infrared and Millimeter Waves, 2007, 26(6): 425-428.

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通讯作者: 陈斌, bchen63@163.com

1.
沈阳化工大学材料科学与工程学院沈阳 110142

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A method to determine the domain of a rocket exhaust plume

1. State Key Laboratory of Pulsed Power Laser Technology,Electronic Engineering Institute,Hefei 230037,China

Received Date: 2013-07-12

Rev Recd Date: 2013-08-10

Publish Date: 2014-03-25

Key words:

rocket exhaust plume /
infrared radiation intensity calculation /
domain definition /
threshold

Abstract: Aimed at calculating the infrared radiation of a rocket exhaust plume exactly and efficiently, a method for defining the domain of an exhaust plume was reported. As a basic work, the flow field was calculated by using the CFD software FLUENT, and the radiation was calculated by means of Finite Volume Method (FVM). Then, variables that might be able to be used to differentiate an exhaust plume from surrounding atmosphere such as temperature and species composition were studied and the mass fraction of CO was chosen. When calculating the infrared radiation of an exhaust plume, only the part where the CO mass fraction bigger than the threshold was taken into account, and the rest were neglected. The change law of size of calculation domain, calculation time and infrared radiation with thresholds were studied. The results show that, as the threshold decreases, the size of calculation domain and the calculation time increase monotonously and rapidly, while the infrared radiation changes a lot at first and becomes stable at last. Besides, it was indicated by simulation experiments that the CO mass fraction 0.000 5 as the threshold is acceptable to define the calculation domain of the exhaust plume.

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Reference (59)

[1]	Nelson H F. Infrared radiation signature of tactical rocket exhausts [C]//St. Louis, Missouri: AIAA,AIAA/ASME 3rd Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference, 1985: AIAA-82-0913.
[2]
[3]
[4]	Rochelle W C. Review of thermal radiation from liquid and solid propellant rocket exhausts [R]. Huntsville: Marshall Space Flight Center, 1967: NASA TM X-53579.
[5]
[6]	Devir A, Lessin A, Lev M, et al. Comparison of calculated and measured radiation from a rocket motor plume [C]// Reno, Nevada: AIAA,39th AIAA Aerospace Sciences Meeting Exhibit, 2001: 2001-0358.
[7]
[8]	Duval R, Soufiani A, Taine J. Coupled radiation and turbulent multiphase flow in an aluminised solid propellant rocket engine [J]. Journal of Quantitative Spectroscopy Radiative Transfer, 2004, 84: 513-526.
[9]
[10]	Jiang Yi, Fu Debin. Numerical simulation for non equilibrium chemically reacting fluid field of the solid rocket motor exhaust plume [J]. Journal of Astronautics, 2008, 29 (2): 615-620.
[11]
[12]	Wang W, Wei Z, Zhang Q, et al. Study on infrared signature of solid rocket motor afterburning exhaust plume [C]// Nashville, TN: 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, 2010: AIAA 2010-6847.
[13]	Wang W, Wei Z, Zhang Q, et al. Infrared radiation signature of exhaust plume from solid propellants of different energy characteristics[C]//San Diego, California: 47th AIAA/ASME/ SAE/ASEE Joint Propulsion Conference Exhibit, 2011: AIAA 2011-6140.
[14]
[15]	Reardon J E, Lee Y C. A computer program for thermal radiation from gaseous rocket exhuast plumes(GASRAD)[R]. NASA-CR-161496, 1980:NASA-CR-161496.
[16]
[17]
[18]	Ludwig C B, Malkmus W, Walker J. The standardized infrared radiation mode[C], 1981: AIAA-81-1051.
[19]	Markarian P, Kosson R. Standardized Infrared Radiation Model (SIRRM-II) [R]. NY: Grumman Aerospace Corp, 1988: AFAL-87-098.
[20]
[21]	Surzhikov S T. Monte Carlo Simulation of Plumes Spectral Emission [R]. Institute for Problems in Mechanics Russian Academy of Sciences(IPMech RAS), 2006:
[22]
[23]	Shuai Y, Dong S K, Tan H P. Simulation of the infrared radiation characteristics of high-temperature exhaust plume including particles using the backward Monte Carlo method[J]. Journal of Quantitative Spectroscopy Radiative Transfer, 2005, 95: 231-240.
[24]
[25]
[26]	Shuai Yong, Dong Shikui, Liu Linhua. Simulation of infrared radiation characteristics of high temperature free-stream flow including particles by using backward Monte Carlo method[J]. Journal of Infrared and Millimeter Waves, 2005, 24(2): 100-104.
[27]
[28]	Shuai Yong, Dong Shikui, Tan Heping. Numerical simulation for infrared radiation characteristics of exhaust plume at 2.7 m [J]. Acta Aeronautica et Astronautica Sinica, 2005, 26(4): 402-405.
[29]
[30]	Cai G, Zhu D, Zhang X. Numerical simulation of the infrared radiative signatures of liquid and solid rocket plumes[J]. Aerospace Science and Technology, 2007(11): 473-480.
[31]	Fan Shiwei, Zang Xiaoying, Zhu Dingqiang, et al. Calculation of the infrared characteristics of the solid rocket plume with FVM method[J]. Journal of Astronautics, 2005, 26(6): 794-797.
[32]
[33]
[34]	Coelho P J. Fundamentals of a new method for the solution of the radiative transfer equation[J]. International Journal of Thermal Sciences, 2005, 44: 809-821.
[35]
[36]	Zhang Xiaoying, Zhu Dingqiang, Cai Guobiao. Study the infrared characteristics of the solid rocket plume with DOM method and the influence of altitude [J]. Journal of Astronautics, 2007, 28(3): 702-706.
[37]	Dong Shikui, Yu Jianguo, Li Donghui. Numerical modeling of infrared radiation properties of exhaust plume by the Discrete Ordinates Method in body-fitted coordinates [J]. Journal of University of Shanghai for Science and Technology, 2003, 25(2): 159-163.
[38]
[39]
[40]	Edwards D K, Babikian D S. Radiation from a nongray scattering, emitting, and absorbing solid rocket motor plume[J]. J Thermophysics, 1990, 4(4): 446-453.
[41]	Surzhikov S T. Three-dimensional model of the spectral emissivity of light-scattering exhaust plumes [J]. High Temperature, 2004, 42(5): 763-775.
[42]
[43]	Hao Jinbo, Dong Shikui, Tan Heping. Numerical simulation of infrared radiation properties of solid rocket engine exhaust plume[J]. Journal of Infrared and Millimeter Waves, 2003, 22(4): 246-250.
[44]
[45]	Nie Wansheng, Yang Junhui, He Haosheng, et al. The IR radiation characteristic of exhaust plume of the liquid rocket engine [J]. Journal of National University of Defense Technology, 2005, 27(5): 91-94.
[46]
[47]
[48]	Feng S, Nie W, Xie Q, et al. Numerical simulation of flow field and radiation of an aluminized solid-opellant rocket multiphase exhaust plume [C]//Miami, FL: 39th AIAA Thermophysics Conference, 2007: AIAA 2007-4415.
[49]
[50]	Dong Shikui, Tan Heping, Yu Qizheng, et al. Infrared radiative spectral band-model parameters for water vapor in the 300- 3000 K temperature range [J]. Journal of Engineering for Thermal Energy and Power, 2001, 16(1): 33-38.
[51]	Dong Shikui, Yu Qizheng, Tan Heping, et al. Narrow band model parameters of high temperature radiation for carbon dioxide of combustion products [J]. Journal of Aerospace Power, 2001, 16(4): 355-359.
[52]
[53]	Siegel R, Howell R J. Thermal Radiation Heat Transfer [M]. Washington D C: Hemisphere and McGraw-Hill, 1981.
[54]
[55]
[56]	Nelson H F. Influence of participates on infrared emission from tactical rocket exhausts [J]. J Spacecraft, 1984, 21(5): 425-432.
[57]
[58]	Simmons F S. Rocket Exhaust Plume Phenomenology [M]. EI Segundo: CA: The Aerospace Press and American Institute of Aeronautics and Astronautics, 2000.
[59]	Zhang Guangming, Sun Shengli, Zhang Wei, et al. Model and application of image plane illumination for the space- based infrared detecting of boost-phase missile [J]. Journal of Infrared and Millimeter Waves, 2007, 26(6): 425-428.

A method to determine the domain of a rocket exhaust plume

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