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固液混合火箭发动机喷焰红外辐射特性分析

申文涛 董超 朱定强 蔡国飙

申文涛, 董超, 朱定强, 蔡国飙. 固液混合火箭发动机喷焰红外辐射特性分析[J]. 航空动力学报, 2012, 27(8): 1874-1880.
引用本文: 申文涛, 董超, 朱定强, 蔡国飙. 固液混合火箭发动机喷焰红外辐射特性分析[J]. 航空动力学报, 2012, 27(8): 1874-1880.
SHEN Wen-tao, DONG Chao, ZHU Ding-qiang, CAI Guo-biao. Analysis of infrared radiation of hybrid rocket motor exhaust plume[J]. Journal of Aerospace Power, 2012, 27(8): 1874-1880.
Citation: SHEN Wen-tao, DONG Chao, ZHU Ding-qiang, CAI Guo-biao. Analysis of infrared radiation of hybrid rocket motor exhaust plume[J]. Journal of Aerospace Power, 2012, 27(8): 1874-1880.

固液混合火箭发动机喷焰红外辐射特性分析

Analysis of infrared radiation of hybrid rocket motor exhaust plume

  • 摘要: 为了研究固液混合火箭发动机喷焰在不同飞行状态的红外辐射特性,建立了固液两相状态下喷焰的红外辐射计算模型,获得了喷焰在2~12μm波段的红外辐射.将喷焰的温度、压力、摩尔组分等作为输入条件,米氏散射(Mie)模型计算颗粒相的散射,采用有限体积法(FVM)离散辐射传递方程,利用中分辨率大气辐射传输(MODTRAN)模型计算不同观测距离的大气透过率,编程计算得到不同飞行高度,不同观测方向下喷焰的红外辐射.结果表明喷焰红外辐射亮度与温度分布类似,在2.7~3.0μm和4.2~4.5μm波段范围内的辐射较强,高温粒子在近红外比远红外对总辐射的贡献大,太空与地面观测不同飞行高度的发动机喷焰辐射率因大气衰减的不同而有所差异,可为目标跟踪与发动机设计提供参考.

     

  • [1] 宋志兵.固液混合发动机工作过程研究 .长沙:国防科学技术大学研究生院,2008. SONG Zhibing.Theoretical and experimental research on the internal operation process of hybrid rocket engine .Changsha:Graduate School of National University of Defense Technology,2008.(in Chinese)
    [2] Surzhikov S T.Direct simulation monte-carlo algorithms for the rocket exhaust plumes emissivity prediction .AIAA 2002-0795,2002.
    [3] Devir A,Lessin A,Lev M,et al.Comparison of calculated and measured radiation from a rocket motor plume //39th AIAA Aerospace Sciences Meeting & Exhibit.Reno,Nevada:AIAA,2001:1-11.
    [4] Devir A,Lessin A,Lev M,et al.Comparison of calcu-lated and measured radiation from a rocket motor plume .AIAA 2001-0358,2001.
    [5] Simmons F S.Rocket exhaust plume phenomenology[M].California:The Aerospace Press,2000.
    [6] Ludwing C B,Malkmus W,Reardon J E,et al.Handbook of infrared radiation from combustion .NASA SP-3080,1973.
    [7] 樊士伟,张小英,朱定强,等.用FVM法计算固体火箭羽流的红外特性[J].宇航学报,2005,26(6):793-797. FAN Shiwei,ZHANG 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):793-797.(in Chinese)
    [8] 王福恒.高速飞行体尾喷焰辐射特性研究进展[J].力学进展.1991,21(1):39-51. WANG Fuheng.The research development of the radiation characteristic for plume of a vehicle[J].Advances in Mechanics,1991,21(1):39-52.(in Chinese)
    [9] 张小英.火箭发动机羽流红外特性的数值计算 .北京:北京航空航天大学,2004. ZHAN Xiaoying.Numerical simulation of infrared characteristics of rocket plume .Beijing:Beijing University of Aeronautics and Astronautics,2004.(in Chinese)
    [10] 田辉,蔡国飙,王慧玉,等.固液混合火箭发动机燃烧室和喷管流动数值模拟[J].宇航学报,2006,27(2):281-285. TIAN Hui,CAI Guobiao,WANG Huiyu,et al.Numerical simulation of combustion chamber and nozzle flow in classical hybrid rocket motors[J].Journal of Astronautics,2006,27(2):281-285.(in Chinese)
    [11] Anfimov N A,Karabadjak G F,Khmelinin B A,et al.Analysis of mechanisms and nature of radiation from aluminum oxide in different phase states in solid rocket exhaust plumes .AIAA 93-2818,1993.
    [12] 谈和平,夏新林,刘林华,等.红外辐射特性与传输的数值计算[M].哈尔滨:哈尔滨工业大学出版社.2006.
    [13] 张小英,朱定强,蔡国飙.固体火箭羽流中Al2O3粒子的辐射特性[J].固体火箭技术,2006,29(4):247-250. ZHANG Xiaoying,ZHU Dingqiang,CAI Guobiao.Radiation character istics of Al2O3 particles in solid rocket plume[J].Journal of Solid Rocket Technology,2006,29(4):247-250.(in Chinese)
    [14] Plastinin Y A,Sipatchev H P,Karabadzhak G F,et al.Influence of alumina particles’ phase transition on its radiation in the middle infrared and ultraviolet regions of spectrum .AIAA 2000-0735,2000.
    [15] Plastinin Y,Karabadzhak G,Khmelinin B,et al.Ultraviolet,visible and infrared spectra modeling for solid and liquid-fuel rocket exhausts .AIAA 2001-0660,2001.
    [16] Malitson I H.Refraction and dispersion of synthetic sap-phire[J].Optical Soc.Am.,1962,52(12):1377-1379.
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出版历程
  • 收稿日期:  2011-09-08
  • 刊出日期:  2012-08-28

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