Infrared radiation characteristics and detectability analysis of point source based on high-speed sliding

Niu Qinglin; Yang Xiao; Chen Biao; He Zhihong; Liu Lianwei; Dong Shikui

doi:10.3788/IRLA201847.1104001

Volume 47 Issue 11

Jan. 2019

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Niu Qinglin, Yang Xiao, Chen Biao, He Zhihong, Liu Lianwei, Dong Shikui. Infrared radiation characteristics and detectability analysis of point source based on high-speed sliding[J]. Infrared and Laser Engineering, 2018, 47(11): 1104001-1104001(8). doi: 10.3788/IRLA201847.1104001

Citation:

Niu Qinglin, Yang Xiao, Chen Biao, He Zhihong, Liu Lianwei, Dong Shikui. Infrared radiation characteristics and detectability analysis of point source based on high-speed sliding[J]. Infrared and Laser Engineering, 2018, 47(11): 1104001-1104001(8). doi: 10.3788/IRLA201847.1104001

Infrared radiation characteristics and detectability analysis of point source based on high-speed sliding

doi: 10.3788/IRLA201847.1104001

1.
Key Laboratory of Aerospace Thermophysics,Ministry of Industry and Information Technology,Harbin Institute of Technology,Harbin 150001,China;
2.
China Luoyang Electronic Equipment Testing Center,Luoyang 471003,China

Received Date: 2018-06-13
Rev Recd Date: 2018-07-17
Publish Date: 2018-11-25

Abstract

Detection distances of the hypersonic aircraft based on a point source infrared detectability were predicted under the ground-based and space-based observation platforms. Two-temperature N-S equations were solved and the fluid-solid conjugation heat transfer technique were used for calculations of the surface temperature. Absorption coefficients of species were evaluated by the line-by-line method, and the radiative transfer equation was solved with the line-of-sight method to obtain intrinsic radiation characteristics of the HTV-2 type vehicle. The detectability of the two platforms was calculated considering the atmospheric transmittance, background and path radiation parameters. Results show that the radiation intensity of the target is determined by surface emissions comparing with the gas radiation. The intensity integrated within the 3-5 m band is high nearly an order of magnitude than that within the 8-12 m band. Under the condition of a constant sensitivity, the maximum detection range is strongly dependent on the spectral regions and observation angles. The maximum detection distances under ground-based and space-based stations are 450 km and 1 450 km for the 3-5 m band, and 300 km and 550 km for the 8-12 m band, respectively.
- HTV-2,
- detection distance,
- infrared radiation,
- hypersonic flows,
- thermal nonequilibrium

References

[1]	Walker S H, Sherk J, Shell D, et al. The DARPA/AF falcon program:the hypersonic technology vehicle# 2(HTV-2) flight demonstration phase[C]//15th AIAA International Space Planes and Hypersonic System and Technologies Conference, 2008.
[2]	Blanchard R, Anderson B, Welch S, et al. Shuttle orbiter fuselage global yemperature measurements from infrared images at hypersonic speeds[C]//Atmospheric Flight Mechanics Confernce and Exhibit, 2013, 19(55):153-170.
[3]	Mahulkar S P, Songawane H R, Rao G A. Infrared signature studies of aerospace vehicles[J]. Progress in Aerospace Sciences, 2007, 43(7):218-245.
[4]	Ross M, Werner M, Mazuk S, et al. Infrared imagery of the space shuttle at hypersonic entry conditions[C]//46th AIAA Aerospace Sciences Meeting and Exhibit, 2008(1):7-10.
[5]	Horvath, Thomas J. Remote observations of reentering spacecraft including the space shuttle orbiter[C]//IEEE Aerospace Conference, 2013:6497380.
[6]	Schwartz R, Verstynen H, Gruber J, et al. Remote infrared imaging of the space shuttle during hypersonic flight:HYTHIRM mission operations and coordination[C]//42nd AIAA Thermophysics Conference, 2011:27-30.
[7]	Brandis A M, Johnston C O, Cruden B A, et al. Uncertainty analysis and validation of radiation measurements for earth reentry[J]. Journal of Thermophysics and Heat Transfer, 2015, 29(2):209-221.
[8]	Ozawa T, Garrison M B, Levin D A. Accurate molecular and soot infrared radiation model for high-temperature flows[J]. Journal of Thermophysics and Heat Transfer, 2007, 21(1):19-27.
[9]	Andrienko D A, Boyd I D. Kinetic models of oxygen thermochemistry based on quasi-classical trajectory analysis[J]. Journal of Thermophysics and Heat Transfer, 2016, 30(1):T4968.
[10]	Park C. Assessment of two-temperature kinetic model for ionizing air[J]. Journal of Thermophysics and Heat Transfer, 1989, 3(3):233-244.
[11]	Perrin M Y, Colonna G, D'Ammando G, et al. Radiation models and radiation transfer in hypersonics[J]. The Open Plasma Physics Journal, 2014, 7(1):114-126.
[12]	Gnoffo P A. Upwind-biased, point-implicit relaxation strategies for viscous, hypersonic flows[C]//9th Computational Fluid Dynamics Conference, 1989(6):13-15.
[13]	Shao C, Nie L, Chen W. Analysis of weakly ionized ablation plasma flows for a hypersonic vehicle[J]. Aerospace Science and Technology, 2016, 51:151-161.
[14]	Menter F R, Kunta M, Langtry R. Ten years of industrial experience with the SST turbulence model[J]. Heat and Mass Transfer, 2003, 4(1):625-632.
[15]	Surahikov S. Radiative gas dynamics of MSL at angle of attack[C]//54th AIAA Aerospace Sciences Meeting, 2016(1):4-8.
[16]	Willams F A. Combustion Theory[M]. 2nd ed. US:Benjamin/Cummings, Inc., 1985.
[17]	Liu Y, Vinpkur M. Upwind algorithms for nonequilibrium flows[C]//27th AIAA Aerospace Sciences Meeting, 1989(1):9-12.
[18]	Nam H J, Kwon O J. Infrared radiation modeling of NO, OH, CO, H2O, and CO2 for emissivity/radiance prediction at high temperature[J]. Infrared Physics Technology, 2014, (8):001-003.
[19]	Mu L, Ma Y, He Z, et al. Radiation characteristics simulation of non-equilibrium flow field around the hypersonic blunted cone[J]. Journal of Engineering Thermophysics, 2012, 33(11):1958-1962.
[20]	Rothman L, Gordon I, Barber R, et al. HITEMP, the high-temperature molecular spectroscopic database[J]. Journal of Quantitative Spectroscopy and Radiative Transfer, 2010, 111(15):2139-2150.
[21]	Niu Q, He Z, Dong S. Prediction of shock-layer ultraviolet radiation for hypersonic vehicles in near space[J]. Chinese Journal of Aeronautics, 2016, 29(5):1367-1377.
[22]	Ren K, Tian J, Gu G, et al. Operating distance calculation of ground-based and air-based infrared system based on Lowtran7[J]. Infrared Physics Technology, 2016, 77(7):414-420.
[23]	Ferrero P, D'Ambrosio D. A numerical method for conjugate heat transfer problems in hypersonic flows[C]//40th Thermophysics Conference, 2008(6):4247.
[24]	Packan D, Laux C O, Gessman R J, et al. Measurement and modeling of OH, NO, and CO infrared radiation at 3400 K[J]. Journal of Thermophysics and Heat Transfer, 2003, 17(4):450-456.
[25]	Zhen Huaping, Jiang Chongwen. Review on hypersonic technology verification HTV-2 vehicle[J]. Winged Missile Journal, 2013, 6(6):7-13. (in Chinese)甄华萍, 蒋崇文. 高超声速技术验证飞行器HTV-2综述[J]. 飞航导弹, 2013, 6(6):7-13.
[26]	Cheng H K. Perspectives on hypersonic viscous and nonequilibrium flow research[R]. NASA-CR-190817, 1992:140151.
[27]	Acton J M. Hypersonic boost-glide weapons[J]. Science Global Security, 2015, 23(3):191-192.

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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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Infrared radiation characteristics and detectability analysis of point source based on high-speed sliding

1. Key Laboratory of Aerospace Thermophysics,Ministry of Industry and Information Technology,Harbin Institute of Technology,Harbin 150001,China;

2. China Luoyang Electronic Equipment Testing Center,Luoyang 471003,China

Received Date: 2018-06-13

Rev Recd Date: 2018-07-17

Publish Date: 2018-11-25

Key words:

Abstract: Detection distances of the hypersonic aircraft based on a point source infrared detectability were predicted under the ground-based and space-based observation platforms. Two-temperature N-S equations were solved and the fluid-solid conjugation heat transfer technique were used for calculations of the surface temperature. Absorption coefficients of species were evaluated by the line-by-line method, and the radiative transfer equation was solved with the line-of-sight method to obtain intrinsic radiation characteristics of the HTV-2 type vehicle. The detectability of the two platforms was calculated considering the atmospheric transmittance, background and path radiation parameters. Results show that the radiation intensity of the target is determined by surface emissions comparing with the gas radiation. The intensity integrated within the 3-5 m band is high nearly an order of magnitude than that within the 8-12 m band. Under the condition of a constant sensitivity, the maximum detection range is strongly dependent on the spectral regions and observation angles. The maximum detection distances under ground-based and space-based stations are 450 km and 1 450 km for the 3-5 m band, and 300 km and 550 km for the 8-12 m band, respectively.

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Reference (27)

[1]	Walker S H, Sherk J, Shell D, et al. The DARPA/AF falcon program:the hypersonic technology vehicle# 2(HTV-2) flight demonstration phase[C]//15th AIAA International Space Planes and Hypersonic System and Technologies Conference, 2008.
[2]	Blanchard R, Anderson B, Welch S, et al. Shuttle orbiter fuselage global yemperature measurements from infrared images at hypersonic speeds[C]//Atmospheric Flight Mechanics Confernce and Exhibit, 2013, 19(55):153-170.
[3]	Mahulkar S P, Songawane H R, Rao G A. Infrared signature studies of aerospace vehicles[J]. Progress in Aerospace Sciences, 2007, 43(7):218-245.
[4]	Ross M, Werner M, Mazuk S, et al. Infrared imagery of the space shuttle at hypersonic entry conditions[C]//46th AIAA Aerospace Sciences Meeting and Exhibit, 2008(1):7-10.
[5]	Horvath, Thomas J. Remote observations of reentering spacecraft including the space shuttle orbiter[C]//IEEE Aerospace Conference, 2013:6497380.
[6]	Schwartz R, Verstynen H, Gruber J, et al. Remote infrared imaging of the space shuttle during hypersonic flight:HYTHIRM mission operations and coordination[C]//42nd AIAA Thermophysics Conference, 2011:27-30.
[7]	Brandis A M, Johnston C O, Cruden B A, et al. Uncertainty analysis and validation of radiation measurements for earth reentry[J]. Journal of Thermophysics and Heat Transfer, 2015, 29(2):209-221.
[8]	Ozawa T, Garrison M B, Levin D A. Accurate molecular and soot infrared radiation model for high-temperature flows[J]. Journal of Thermophysics and Heat Transfer, 2007, 21(1):19-27.
[9]	Andrienko D A, Boyd I D. Kinetic models of oxygen thermochemistry based on quasi-classical trajectory analysis[J]. Journal of Thermophysics and Heat Transfer, 2016, 30(1):T4968.
[10]	Park C. Assessment of two-temperature kinetic model for ionizing air[J]. Journal of Thermophysics and Heat Transfer, 1989, 3(3):233-244.
[11]	Perrin M Y, Colonna G, D'Ammando G, et al. Radiation models and radiation transfer in hypersonics[J]. The Open Plasma Physics Journal, 2014, 7(1):114-126.
[12]	Gnoffo P A. Upwind-biased, point-implicit relaxation strategies for viscous, hypersonic flows[C]//9th Computational Fluid Dynamics Conference, 1989(6):13-15.
[13]	Shao C, Nie L, Chen W. Analysis of weakly ionized ablation plasma flows for a hypersonic vehicle[J]. Aerospace Science and Technology, 2016, 51:151-161.
[14]	Menter F R, Kunta M, Langtry R. Ten years of industrial experience with the SST turbulence model[J]. Heat and Mass Transfer, 2003, 4(1):625-632.
[15]	Surahikov S. Radiative gas dynamics of MSL at angle of attack[C]//54th AIAA Aerospace Sciences Meeting, 2016(1):4-8.
[16]	Willams F A. Combustion Theory[M]. 2nd ed. US:Benjamin/Cummings, Inc., 1985.
[17]	Liu Y, Vinpkur M. Upwind algorithms for nonequilibrium flows[C]//27th AIAA Aerospace Sciences Meeting, 1989(1):9-12.
[18]	Nam H J, Kwon O J. Infrared radiation modeling of NO, OH, CO, H2O, and CO2 for emissivity/radiance prediction at high temperature[J]. Infrared Physics Technology, 2014, (8):001-003.
[19]	Mu L, Ma Y, He Z, et al. Radiation characteristics simulation of non-equilibrium flow field around the hypersonic blunted cone[J]. Journal of Engineering Thermophysics, 2012, 33(11):1958-1962.
[20]	Rothman L, Gordon I, Barber R, et al. HITEMP, the high-temperature molecular spectroscopic database[J]. Journal of Quantitative Spectroscopy and Radiative Transfer, 2010, 111(15):2139-2150.
[21]	Niu Q, He Z, Dong S. Prediction of shock-layer ultraviolet radiation for hypersonic vehicles in near space[J]. Chinese Journal of Aeronautics, 2016, 29(5):1367-1377.
[22]	Ren K, Tian J, Gu G, et al. Operating distance calculation of ground-based and air-based infrared system based on Lowtran7[J]. Infrared Physics Technology, 2016, 77(7):414-420.
[23]	Ferrero P, D'Ambrosio D. A numerical method for conjugate heat transfer problems in hypersonic flows[C]//40th Thermophysics Conference, 2008(6):4247.
[24]	Packan D, Laux C O, Gessman R J, et al. Measurement and modeling of OH, NO, and CO infrared radiation at 3400 K[J]. Journal of Thermophysics and Heat Transfer, 2003, 17(4):450-456.
[25]	Zhen Huaping, Jiang Chongwen. Review on hypersonic technology verification HTV-2 vehicle[J]. Winged Missile Journal, 2013, 6(6):7-13. (in Chinese)甄华萍, 蒋崇文. 高超声速技术验证飞行器HTV-2综述[J]. 飞航导弹, 2013, 6(6):7-13.
[26]	Cheng H K. Perspectives on hypersonic viscous and nonequilibrium flow research[R]. NASA-CR-190817, 1992:140151.
[27]	Acton J M. Hypersonic boost-glide weapons[J]. Science Global Security, 2015, 23(3):191-192.

Infrared radiation characteristics and detectability analysis of point source based on high-speed sliding

doi: 10.3788/IRLA201847.1104001

Abstract

References

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通讯作者: 陈斌, bchen63@163.com

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