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ROCKETS TECHNOLOGY

The Study on Plume Characteristic of Two-phase Chemical Reaction of Modified Double-base Propellant

  • LI Meng ,
  • ZHANG Xiaohong ,
  • SUN Mei ,
  • WANG Changjian
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  • Xi'an Modern Chemistry Research Institute, Xi'an 710065, China

Received date: 2011-04-01

  Online published: 2025-05-29

Abstract

The plume characteristic of modified double-base propellant was investigated. The NASA-CEA program was used for calculating theoretical performance of the propellant. A control equation set was established, which includes the transport equation, chemical reaction dynamic process and gas-solid two-phase flow process. Structures and species of plume were obtained with the Fluent software. The results show that finite rate chemistry reaction model and the discrete phase model are all influential in the plume calculation, and provide reference for plume characteristic effect study.

Cite this article

LI Meng , ZHANG Xiaohong , SUN Mei , WANG Changjian . The Study on Plume Characteristic of Two-phase Chemical Reaction of Modified Double-base Propellant[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2012 , 32(1) : 123 -126 . DOI: 10.15892/j.cnki.djzdxb.2012.01.006

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References

[1]
Sanford Gordon, Bonnie J McBride. Computer programfor calculation chemical eguilibrium compositions and ap-plications: I Analysis NASA RP-1311[R]. 1994.
[2]
Bonnie J MeBride, Sanford Gordon. Computer program for cal-culation chemical eguilibrium compositions and applications: IIUsers Mawual and profram description NASA-RP-1311[R]. 1996.
[3]
J Troyes, I Dubois, V Borie, et al. Multi-phase reactivenumerical simulations of a model solid rocket motor ex-haust jet, AIAA2006-4414[J]. 2006.
[4]
Xiao-Yen J Wang, James R Yuko. Thermal analysis onplume heating of the main engine on the crew explorationvehicle service module, NASA/TM2007-215049[R]. 2007.
[5]
NATO Research and Technology Organisation. Terminology and assessment methods of solid propellant rocketexhaust signature,AGARD-AR-287[R]. 1993.
[6]
徐义华, 胡春波, 张胜敏, 等. 固体火箭发动机羽流红外辐射特性研究[J]. 固体火箭技术, 2010, 33(2): 176- 181.
[7]
李猛, 王宏. 火箭发动机排气羽流特征信号预示技术研究综述[J]. 飞航导弹, 2010(3): 54- 57.
[8]
李猛, 王宏, 陈雪莉. 复杂化学平衡应用计算程序[J]. 四川兵工学报, 2010, 31(9): 132- 134.
[9]
王伟臣, 魏志军, 等. 后燃对火箭发动机羽流红外特性的影响[J]. 航空动力学报, 2010, 25(11): 2612- 2618.
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