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Volume 35 Issue 10
Oct.  2009
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Journal of Beijing University of Aeronautics and Astronautics  > 2009  >  35(10): 1174-1178.
Liu Hui, Xing Yuming, Eriqitaiet al. Computation of three-dimensional flow field in secondary gas injection for thrust vectoring nozzle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(10): 1174-1178. (in Chinese)
Citation: Liu Hui, Xing Yuming, Eriqitaiet al. Computation of three-dimensional flow field in secondary gas injection for thrust vectoring nozzle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(10): 1174-1178. (in Chinese)
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Computation of three-dimensional flow field in secondary gas injection for thrust vectoring nozzle

  • 1.

    School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 15 Oct 2008
  • Publish Date: 31 Oct 2009
    Abstract
  • The complex inner flow-field of the thrust vectoring nozzle based on secondary gas injection was numerically simulated using three-dimensional average Reynolds equations and the κ-ε turbulent models. The influences on the thrust vectoring efficiency and the thrust ratio of different injection parameters and the nozzle pressure ratio were analyzed and investigated. Results indicate that the effects of the position injection orifice, the injection angle and the injection mass flux on the vectoring angle couple each other.When the vectoring angle reaches its maximum value in design conditions, these injection parameters couldn-t reach their respective best value simultaneously.When the vectoring angle increases, The thrust ratio decreases and the thrust loss increases. The thrust vectoring of the rectangular injection orifice is better than that of the circular injection orifice. The vectoring angle increases with the decreasing of the nozzle pressure ratio.

     

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    • References(1)
  • [1] Kowal H J. Advances in thrust vectoring and the application of flow-control technology [J]. Canadian Aeronautics and Space Journal, 2002, 48(2):145-151 [2] Deere K A. Summary of fluidic thrust vectoring research conducted at NASA langley research center . AIAA-2003-3800, 2003 [3] 林飞,王根斌.固体火箭发动机推力向量控制[M]. 北京:国防工业出版社,1981:121-125 Lin Fei, Wang Genbin. Thrust vectoring control for solid rocket motor [M]. Beijing: National Defense and Industry Press, 1981:121-125 (in Chinese) [4] 吴雄,张为华,王中伟. 气体二次喷射矢量喷管混合流场数值模拟[J].弹箭与制导学报,2006,26(4):214-217 Wu Xiong, Zhang Weihua, Wang Zhongwei. Numerical simulation of the mixed flowfield in secondary gas injection vector nozzle [J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2006, 26(4):214-217 (in Chinese) [5] 王全,王强.激波诱导二元矢量喷管内流场特性数值研究[J].航空动力学报,2006, 21(4):681-685 Wang Quan, Wang Qiang. Computational analysis on static internal flowfield of shock vector controlled vectoring exhaust nozzles [J]. Journal of Aerospace Power, 2006, 21(4):681-685 (in Chinese)
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