The Method for Numerical Simulation of the Impact on the Infrared Radiation Seeker from the Warhead Shock Layer

Abstract:

It counts the impact on the infrared radiation seeker which in the head of the hypersonic missile. Firstly, it built the calculated model based on the shape of a missile, and compartmentalized the aerodynamics flow field grid , the infrared radiation seeker main mirror grid , the radiation field grid, and had the relation of the grids unambiguous, and got the communication of the aerodynamics flow field. Then it educed irradiance formula about the shock layer aerodynamic flow fled radiation affect to the infrared radiation seeker main mirror. The result is the infrared radiation wave band 3~5 to the main mirror, from the shock layer aerodynamic flow fled is about 120 W/m². The distributing law of the impact is annular circumfused the center of the main mirror, the infrared radiation is the highest in the center of the main mirror, decreased by the radius of the main mirror.

• Periodical: Applied Mechanics and Materials (Volume 390)
• Pages: 464-467
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.390.464
• Online since: August 2013
• Authors: Da Lei Luo, Jun Liu, Yuan Wang, Deng Feng Fan
• Keywords: Grid, Hypersonic Missile, Infrared Radiation, Numerical Simulation, Shock Layer

References

[1] Chinese PLA General Armament Department, Editorial Committee of military training book. Hypersonic aerodynamic heating and thermal protection[M]. Beijing: National Defense Industry Press, May 2003: 4-7, 37-42.

[2] Qu Zhanghua, Liu Wei, Zeng ming, et al. Hypersonic aerodynamics, Second Edition [M]. Changsha: National University of Defense Technology press, May 2001: 158-159.

[3] Yan Chao. Computational fluid dynamics method and application [M]. Beijing: Beihang University press, June 2006: 62-654.

[4] Luo Dalei. Hypersonic / supersonic aircraft head shock-wave layer infrared radiation characteristics numerical study[D]. [MS Thesis]. Changsha: National University of Defense Technology, Dec. 2012: 75-79.

[5] Jin Weiqi, Hu Weijie. Radiation, luminosity and chrominance measurement [M]. Beijing Institute of Technology press, June 2006: 3-446.

[6] Water H. Cheistiansen. Fundamentals of Nonequilibrium Gasdynamics-IV Nonequilibrium Radiation in Gases University of Washington. NASA TM 100673, September (1988).

[7] Ju Nianzeng. Radiometry and luminosity of science [M]. Beijing: Beijing Institute of Technology press, Feb 1990: 3-7.

[8] Yang Shiming, Tao Wenquan. Heat Transfer, Third Edition [M] Beijing: Higher Education Press, December 1998 : 249-256.

[9] Arnold J. O. , Line by Line Calculations of Spectra from Diatomic Molecules and Atoms Assuming A Voigt Line Profile. J. Quant. Spectrose. Radiat. Transfer, Vol. 9. 1969, 775_798.

DOI: 10.1016/0022-4073(69)90075-2

[10] LiuJun. Thermal chemical non-equilibrium flow and its radiation phenomenon of the experiment and numerical study [D]. [Ph.D. Thesis]. Changsha: National University of Defense Technology, April, 2004: 91-95.

[11] Luo Dalei, Liu Jun. The missile head flow field and radiation characteristics numerical study [C]. 15 th national computational fluid dynamics conference, Yantai, Shandong Province, August 2012, Beijing: Beihang University press, August 2012 . 1237-1241.

[12] Tan Heping, Xia Xinlin, Liu Linhua, et al. The infrared numerical calculation of radiation characteristics and transmission [M]. Harbin, Harbin industrial university press, October 2006: 1 -3.

[13] Park C. Problems of rate chemistry in the Flight Regimes of Aeroassisted Orbital Transfer Vehicles . V96 of program in Astronautics and Aeronantics: 511-537 , (1985).

DOI: 10.2514/5.9781600865718.0511.0537

[14] Anderson E. C, Lewis C H, Laminar or Turbulent Boundary-Layer Flows of Perfect Gases or Reacting Gas Mixture in Chemical Equilibrium，NASA，CR-1893，(1971).

[15] Murray A L, Lewis C H, Hypersonic Three Dimension Viscous Shock-LayerFlows Over Blunt Bodies，AIAA, Journal, 1978, 16 (12): 1279-1286.

DOI: 10.2514/3.61044