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Wu Longbao, Xie Xiaofang, Wang Chengcheng, Yu Jiahui. Modeling and simulation of supersonic missile temperature distribution[J]. Infrared and Laser Engineering, 2013, 42(1): 1-6.
Citation: Wu Longbao, Xie Xiaofang, Wang Chengcheng, Yu Jiahui. Modeling and simulation of supersonic missile temperature distribution[J]. Infrared and Laser Engineering, 2013, 42(1): 1-6.

Modeling and simulation of supersonic missile temperature distribution

  • Received Date: 2012-05-05
  • Rev Recd Date: 2012-06-03
  • Publish Date: 2013-01-25
  • The calculation of supersonic missile temperature distribution plays an important role in the study of its infrared characteristic. Two primary radiation points of supersonic missile-fuselage and plume, were analyzed deeply. A temperature distribution model of supersonic missile was built, and the feasibility was proved by simulation. Firstly, a theoretical model and semi-empirical formula were adopted to calulate the temperature distribution of supersonic missile. Secondly, in the model, the plume was disposed as supersonic circular symmetrical adiabatic isentropic airflow approximately. The distribution of air airflow parameters were calculated by the characteristic method line. Thirdly, a theoretic model and calculation method of the plume shape were established. Finally, taking one missile as an example, the computing model was used to compute the temperature distribution of supersonic missile. The results indicate that this is an effective method to calulate the temperature distribution of supersonic missile according to the comparison between the result values and the measured values.
  • [1]
    [2] Xu Yongqin. Research on the conception of hypesonic vehicle system[D]. Xi'an: Northwestern Polytechnical University, 2005: 23-27. (in Chinese)
    [3] 徐勇勤. 高超音速飞行器总体概念研究[D]. 西安: 西北工业大学, 2005: 23-27.
    [4] Li Hanshan, Yuan Chaohui, Lei Zhiyong. Infrared radiation characteristics analysis of high velocity projectile in detection screen[J]. Infrared and Laser Engineering, 2009, 38(5): 777-781. (in Chinese)
    [5] Liu Juan, Gong Guanghong, Han Liang, et al. Modeling and simulation of airplane infrared characteristic[J]. Infrared and Laser Engineering, 2011, 40(7): 952-956. (in Chinese)
    [6]
    [7]
    [8] Zhang Fuxiang. The Dynamics of the Rocket Jetflow[M]. Harbin: Harbin Institusion of Engineering Press, 2004: 121-126. (in Chinese)
    [9] Philip E O, Buelow, Schwer Douglas A, et al. A preconditioned dual-time, diagonalized ADI scheme for unsteady computations[D]. Pennsylvania: Pennsylvania State Univ, 1997.
    [10] 李翰山, 袁朝辉, 雷志勇. 探测光幕中的高速弹丸红外辐射特性分析[J]. 红外与激光工程, 2009, 38(5): 777-781.
    [11] Yan Bo. Real-time simulation research of the fluid field based on particle system[D]. Wuhan: Huazhong University of Science and Technology, 2009, 26(5): 21-25. (in Chinese)
    [12]
    [13]
    [14] Gao Sili, Tang Xinyi. Building model of the plume released from the flying machine and simulation[J]. Opto-Electronic Engineering, 2007, 34(8): 25-27. (in Chinese)
    [15] 刘娟, 龚光红, 韩亮, 等. 飞机红外辐射特性建模与仿真[J]. 红外与激光工程, 2011, 40(7): 1209-1213.
    [16] 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. (in Chinese)
    [17]
    [18]
    [19] 张福祥. 火箭燃气射流动力学[M]. 哈尔滨: 哈尔滨工程大学出版社, 2004: 121-126.
    [20]
    [21]
    [22]
    [23] 鄢博. 基于粒子系统的喷焰流场实时仿真研究[D]. 武汉: 华中科技大学, 2009, 26(5): 21-25.
    [24]
    [25]
    [26] 高思莉, 汤心溢. 空中飞行目标尾焰红外辐射信号的建模与仿真[J]. 光电工程, 2007, 34(8): 25-27.
    [27]
    [28]
    [29] 姜毅, 傅德彬. 固体火箭发动机尾喷焰复燃流场计算[J]. 宇航学报, 2008, 29(2): 615-620.
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Modeling and simulation of supersonic missile temperature distribution

  • 1. Graduate Management Team,Naval Aeronautical Engineering Institute,Yantai 264001,China;
  • 2. Armament Science and Technology,Naval Aeronautical Engineering Institute,Yantai 264001,China

Abstract: The calculation of supersonic missile temperature distribution plays an important role in the study of its infrared characteristic. Two primary radiation points of supersonic missile-fuselage and plume, were analyzed deeply. A temperature distribution model of supersonic missile was built, and the feasibility was proved by simulation. Firstly, a theoretical model and semi-empirical formula were adopted to calulate the temperature distribution of supersonic missile. Secondly, in the model, the plume was disposed as supersonic circular symmetrical adiabatic isentropic airflow approximately. The distribution of air airflow parameters were calculated by the characteristic method line. Thirdly, a theoretic model and calculation method of the plume shape were established. Finally, taking one missile as an example, the computing model was used to compute the temperature distribution of supersonic missile. The results indicate that this is an effective method to calulate the temperature distribution of supersonic missile according to the comparison between the result values and the measured values.

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