固液混合火箭发动机燃烧的边界层计算

推进技术 ›› 2002, Vol. 23 ›› Issue (5): 379-382.

固液混合火箭发动机燃烧的边界层计算

田辉,蔡国飙,王慧玉,张振鹏

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083

发布日期:2021-08-15
基金资助:
航天科技创新基金项目。

Computation of combustion in hybrid rocket motor using a boundary layer theory

School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083, China

Published:2021-08-15

摘要/Abstract

摘要： 针对固液混合火箭发动机典型的边界层燃烧理论,用边界层的方法对固液混合火箭发动机燃烧进行了计算,计算采用二维轴对称的层流边界层方程,化学模型采用有限速率模型。计算考虑了不同氧化剂流率,不同吹入参数的多种情况,得到了固体混合发动机边界层的温度场分布,并利用计算结果,拟合了固体燃料的燃速公式,与相关文献的比较说明计算正确,结果符合燃烧机理和流动规律,为进一步研究固液混合火箭发动机的燃烧问题打下了基础。

关键词: 固液推进剂;混合推进剂火箭发动机;边界层燃烧;推进剂燃速

Abstract: A boundary layer numerical solution was used for the computation of combustion in hybrid rocket motor according to the boundary burning theory. Various value of mass transfer number and the oxidizer mass flux were considered in the calculation. The regression rate of the solid fuel was formulized based on the calculation. The results show good agreement with the related references and useful for further study.

Key words: Solid liquid propellant;Hybrid propellant rocket motor;Boundary layer combustion;Propellant burning rate

田辉,蔡国飙,王慧玉,张振鹏. 固液混合火箭发动机燃烧的边界层计算[J]. 推进技术, 2002, 23(5): 379-382.