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Volume 33 Issue 07
Jul.  2007
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Journal of Beijing University of Aeronautics and Astronautics  > 2007  >  33(07): 789-792.
Zhang Zhimin, Li Jinqiu, Guo Yanyanget al. Computational Model of Progressive Failure in Composite Sandwich Structures[J]. Journal of Beijing University of Aeronautics and Astronautics, 1999, 25(5): 565-568. (in Chinese)
Citation: Li Qiang, Fan Wei, Yan Chuanjunet al. Numerical simulation of converging-diverging nozzle flow in pulse detonation rocket engine[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(07): 789-792. (in Chinese)
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Numerical simulation of converging-diverging nozzle flow in pulse detonation rocket engine

  • School of Power and Energy, Northwestern Polytechnical University, Xi-an 710072, China

  • Received Date: 30 Mar 2006
  • Publish Date: 31 Jul 2007
    Abstract
  • Exhaust nozzle is one of the key components of pulse detonation rocket engine (PDRE). Exhaust nozzle can be used to improve the propulsion performance of PDRE. Method of characteristic (MOC) was used to calculate one-dimensional CJ(Chapman-Jouguet)detonation wave propagating in the ideal detonation tube. The unsteady blowdown process after the CJ detonation wave reach the exit of detonation tube was two-dimensional axisymmetric numerical simulated. The results of numerical simulation demonstrated the development of the unsteady flow field, and the unsteady waves and vortexes were discussed. Contrary to PDRE without nozzle, the CD nozzle can augment propulsive performance by 18.24%.

     

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  • [1] Bratkovich T E, Aarnio M J, Williams J T, et al. An introduction to pulse detonation rocket engines (PDREs) . AIAA 97-2742, 1997 [2] Kailasanath K. Review of propulsion applications of detonation waves [J]. AIAA Journal ,2000, 38(9):1698-1708 [3] McBride B J, Gordon S. Computer program for calculation of complex chemical equilibrium compositions and applications . NASA Reference Publication 1311, 1996 [4] Matsutomi Y, Meyer S E, Heister S D , et al. Impulse measurements and analytical studies on a cyclic pulse detonation engine . AIAA2003-4824, 2003
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