低温推进剂火箭发动机预冷方案研究  

Research on Precooling of Cryogenic Propellant Rocket Engines

作　　者：孙礼杰 樊宏湍[2] 刘增光[2] 张亮 

机构地区：[1]上海宇航系统工程研究所,上海201108 [2]上海航天技术研究院,上海201109

出　　处：《上海航天》2012年第4期41-48,共8页Aerospace Shanghai

摘　　要：对国内外低温推进剂火箭发动机采用的排放预冷、自然循环预冷和强制循环预冷等预冷方案进行了综述。介绍了国内新一代运载火箭使用的新型低温液体发动机的预冷研究。对液氧煤油发动机预冷方案中推进剂类型、发动机所在子级、自然循环多因素综合等影响方案的主要因素,以及发动机预冷方案中的维护、沸腾传热与两相流数值模拟等关键技术进行了分析。The bleed, natural recirculation and forced recirculation preeooling methods used in cryogenic propellant rocket engine in domestic and aboard were summarized in this paper. The research on the precooling of new cryogenic propellant rocket engine for the new generation launch vehicle in China was introduced. The key factors of propellant type, the sub-stage of the engine and multifactor integrated of natural recirculation which affected the precooling scheme, and the key technologies such as the maintaining and boiling heat transfer and two- phase flow numerical simulation were discussed.

关 键 词：运载火箭 低温推进剂 发动机预冷 排放预冷 自然循环预冷 强制循环预冷 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]