登月舱用深度变推下降级发动机系统方案研究  

System study of deep throttling descent rocket engine for lunar lander

作　　者：刘登丰[1] 黄仕启[1] 周伟[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2014年第4期22-28,76,共8页Journal of Rocket Propulsion

基　　金：中国航天科技集团公司支撑项目(2010JY27)

摘　　要：在我国的载人登月技术方案中,为实现软着陆,登月舱需要一种大推力、高性能、多次起动,能够大范围变推力的泵压式发动机。通过研究国外登月用下降级发动机技术发展现状和趋势,基于我国氢氧发动机和低温推进剂空间贮存水平,进行了深度变推发动机的系统方案研究;通过分析比对燃气发生器循环和膨胀循环系统优缺点,确定发动机系统方案为涡轮串联闭式膨胀循环;采用空间可长时间贮存的液氧/甲烷推进剂组合,可满足任务周期要求;根据推力深度调节时对各组合件性能要求,确定喷注器燃烧稳定技术和燃烧室身部传热技术是深度变推发动机研制的核心关键技术。A lunar lander descent engine with throttle-ability, high thrust, high performance and restart capability is needed for manned lunar landing mission in the scheme demonstration. According to the present state and trend of descent engines in other countries, based on the technology of Chinese LH2/LOX rocket engine and the space storage level of cryogenic propellant in orbit, the system study of deep throttling rocket engine was carried out. The characteristics of expander and generator cycle engines were analyzed. The turbo-series close expander cycle engine was demonstrated as the engine system scheme. It is pointed out that the CH4/LOX propellant which can be stored in space for a long period can satisfy the requirements in mission period. According to the performance requirements of each assembling unit while the thrust is adjusted deeply, the combustion stability technology of injector and the heat transfer technology of combustor body are identified as the key ones for deep throttling engine development.

关 键 词：登月舱 深度变推 膨胀循环 液氧甲烷发动机 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]