CAJ | 학술논문

分析了国内外载人火箭主动力的发展情况与发展趋势，介绍了我国1200 kN和180 kN两型液氧煤油发动机的研制历程、系统组成、工作原理、性能参数、关键技术和应用情况。两型发动机突破了补燃循环、自身起动、大范围工况调节、高效稳定燃烧、高压推力室冷却、反力式涡轮、大范围轴向力平衡、低温高DN值轴承、组合式涡轮泵密封、大直径低温阀、高精度调节器、推力矢量控制等关键技术。目前，两型发动机研制工作已基本完成，将成为我国新一代载人火箭的动力组合，实现我国航天主动力的更新换代。
분석료국내외재인화전주동력적발전정황여발전추세，개소료아국1200 kN화180 kN량형액양매유발동궤적연제역정、계통조성、공작원리、성능삼수、관건기술화응용정황。량형발동궤돌파료보연순배、자신기동、대범위공황조절、고효은정연소、고압추력실냉각、반력식와륜、대범위축향력평형、저온고DN치축승、조합식와륜빙밀봉、대직경저온벌、고정도조절기、추력시량공제등관건기술。목전，량형발동궤연제공작이기본완성，장성위아국신일대재인화전적동력조합，실현아국항천주동력적경신환대。
The development status and the trend of foreign and Chinese manned launch vehicles main power system were analyzed , and the research history , system composition , working principle , performance parameters , key technology and application prediction of the engines were introduced . The key technologies including staged combustion power cycle , self start-up, work condition adjus-ting in large range , high-efficiency stable burning , high pressure thrust chamber cooling , reaction turbine, axial thrust balance in large range , low temperature high DN bearing , combined face-riding seal, big diameter low temperature valve , high precision regulator and thrust vector control were re-solved .The engines have been successfully developed in China and will be used in the new -genera-tion manned launch vehicle .