本文的主要工作面向液体火箭发动机设计CAD技术，并选择再生冷却式液体火箭发动机推力室设计CAD技术研究作为方向。
This paper mainly focuses on CAD of LRE design, and present studies on CAD technique of recycled cooling LRE combustion chamber.
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。
This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
液体火箭发动机发汗冷却推力室的结构层板可能出现受热皱损。
Heat transfer possibly results in the thermal wrinkling of transpiration cooling platelet of the liquid rocket engine (LRE) 's thrust chamber.
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