This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。
A calculation of the wall temperature distribution in liquid propellant rocket engine chamber with milled grooves was completed by the aid of three-dimensional finite element method.
采用三维有限元模型对液体火箭发动机铣槽推力室进行了壁温分布计算。边界条件按一维经验公式处理。计算中比较了不同冷却剂流量。
A calculation of the wall temperature distribution in liquid propellant rocket engine chamber with milled grooves was completed by the aid of three-dimensional finite element method.
采用三维有限元模型对液体火箭发动机铣槽推力室进行了壁温分布计算。边界条件按一维经验公式处理。计算中比较了不同冷却剂流量。
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