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Volume 31 Issue 06
Jun.  2005
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Journal of Beijing University of Aeronautics and Astronautics  > 2005  >  31(06): 637-641.
HUANG Jun, HUAI Jin-peng, WU Zheet al. Optimization Selection in Conceptual Design of Advanced Trainer Aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2002, 28(6): 656-659. (in Chinese)
Citation: Tian Hui, Cai Guobiao, Wang Huiyu, et al. Computation of fuel regression rate in classical hybrid rocket motors[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(06): 637-641. (in Chinese)
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Computation of fuel regression rate in classical hybrid rocket motors

  • School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 13 Jan 2004
  • Publish Date: 30 Jun 2005
    Abstract
  • The combustion characteristic in classical hybrid rocket motors has been studied. The heat transfer process in the gas and the solid fuel has been considered. Coupling computation is presented by the regression rate equations based on the heat transfer theory and the Arrhenius law. The regression rate at various oxidizer mass flow rates, axis distances, ambient operating temperatures and times is obtained. Fuel regression rate mainly infects with oxidizer mass flow rate and axial distance. Regression rate increases as oxidizer mass flow rate increases and decreases as axial distance increases. The temperature sensitivity of solid fuel in a hybrid rocket motor is low and we need not assign a weight margin for variations in ambient operating temperatures. Adiabatic combustion temperature at various oxidizer mass flow rates and grain length is obtained by thermodynamic calculation and has a maximum as oxidizer mass flow rate increases. The results are in agreement with the some references and useful for further study.

     

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  • [1] Е Б 伏尔科夫, Г Ю 马金格, Ю Н 希什金. 任汉芬, 杨培松译. 组合型火箭发动机[M]. 北京:国防工业出版社, 1976 [2] Ronald W H, Gary N H, Wiley J L. Space propulsion analysis and design[M]. USA:The McGraw-Hill Companies, Inc Primis Custom Publishing, 1995 [3] Kim Hoo-Joong, Kim Yong-Mo. Numerical modeling for combustion processed of hybrid rocket engine . AIAA2001-4504, Utah:AIAA, 2001 [4] 胡建新, 夏智勋, 张为华, 等. 固液混合火箭发动机简单反应流模拟[J]. 弹道学报, 2002, 14(4):19~30 Hu Jianxin, Xia Zhixun, Zhang Weihua, et al. Simple reacting flow simulation of hybrid rocket motor[J].Journal of Ballistics, 2002, 14(4):19~30(in Chinese) [5] Martin J C, Kenneth K K, Arie P, et al. Heat flux and internal ballistic characterization of a hybrid rocket motor analog . AIAA97-3080, WA:AIAA, 1997
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