我国大推力补燃氢氧发动机研究进展  

Advances of Large-Thrust Staged Combustion Cycle Hydrogen/Oxygen Rocket Engine in China

作　　者：孙纪国 岳文龙[1] SUN Jiguo;YUE Wenlong(Beijing Aerospace Propulsion Institute,Beijing 100076,China)

机构地区：[1]北京航天动力研究所

出　　处：《上海航天》2019年第6期19-23,68,共6页Aerospace Shanghai

摘　　要：氢氧火箭发动机因具有很高的性能,在国内外运载火箭中得到了广泛应用。为了更好地开展深空探测,必须研制大推力氢氧火箭发动机。本文综合分析了国内外氢氧发动机的发展历史和现状,简要介绍了我国220 t补燃循环氢氧发动机方案和关键技术研制进展,该技术方案先进。通过开展试验件冷态试验和缩尺组件热试验等,研究了核心部组件的关键技术和方案选型。开展全尺寸预燃室热试验等分系统热试验,研究组件级技术,初步突破了部分关键技术。建议加快开展大推力氢氧发动机工程研制,促进我国航天推进技术发展。Because of its high performance,hydrogen/oxygen rocket engine has been widely used in launch vehicles at home and abroad.In order to better carry out deep space exploration,it is necessary to develop large thrust hydrogen/oxygen rocket engine.In this paper,the development history and status of hydrogen/oxygen engines at home and abroad are comprehensively analyzed.An advanced technical scheme in China,i.e.,the 220 t staged com-bustion cycle hydrogen/oxygen engine scheme,is introduced,and the research and development of the related key technologies are simply introduced.Cold tests for test articles,hot tests for scale components,etc.are conducted to study the key technologies of the core components and scheme selection.Subsystem hot tests such as full-size preburner hot tests are carried out to study the component-level technology,and some key technologies have been preliminarily broken through.It is suggested that the development of large-thrust should be accelerated so as to promote the development of space propulsion technology in China.

关 键 词：氢氧 发动机 补燃循环 重型火箭 大推力 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]