不同药型固液火箭发动机性能特点

朱浩; 蔡国飙

不同药型固液火箭发动机性能特点

朱浩^,,
蔡国飙

北京航空航天大学宇航学院,北京 100191

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- 被引次数: 0
出版历程
- 收稿日期: 2010-10-29
- 修回日期: 2010-12-13
- 刊出日期: 2011-10-28

Performance characteristics of hybrid rocket motors with different grain types

ZHU Hao^,,
CAI Guo-biao

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 根据平行层燃烧理论,推导了不同药型燃烧面积和燃烧边界长度随燃去肉厚变化的数学规律;在此基础上,建立了固液火箭发动机系统设计模型,将设计过程转化为数学模型;之后采用遗传算法对不同药型固液火箭发动机进行了优化设计.通过对优化结果的比较和分析,开展了不同药型应用于固液火箭发动机的性能特点及其机理的研究,指出了固液火箭发动机不同于固体火箭发动机的内弹道特性.
- 固液火箭发动机 /
- 系统设计 /
- 药型 /
- 优化设计 /
- 内弹道
Abstract: Based on the geometrical law of burning,the discipline how the burning area and burning perimeter length change with the increase of burned web thickness for different grain types was deduced.The hybrid rocket motor design model was established to convert the design process to mathematical model.Then a genetic arithmetic was used to optimize the design of hybrid rocket motor with different grain types.Through comparison and analysis of the optimal results,the study of hybrid rocket motor performance characteristics and the mechanism with different grain types were implemented,and the difference between the hybrid rocket motor and solid rocket motor in internal ballistic performance was pointed out.
- hybrid rocket motor /
- system design /
- grain type /
- optimal design /
- internal ballistic

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参考文献(14)

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