摘要
低温液体火箭发动机循环预冷受多因素影响,针对液氧煤油发动机自然循环系统回流管绝热条件对预冷效果的影响进行理论分析和试验研究,得到了有意义的数据和结论,对后续型号自然循环预冷系统设计提供了依据。
The circulation chill-down of a cryogenic rocket engine is affected by many factors.Theoretical analysis and experiments research were carried out for the study of the influence of the recirculation pipe adiabatic condition on the chill-down effect.The significant data and conclusions obatained can lead help for the design of the chill-down system.
出处
《低温与超导》
CAS
CSCD
北大核心
2011年第11期22-26,共5页
Cryogenics and Superconductivity
基金
上海市科技人才计划项目(上海市青年科技启明星计划)(09QB143600)
关键词
液氧煤油
循环预冷
火箭发动机
回流管绝热
LOX/RP1
Circulation chill-down
Rocket engine
Recirculation pipe adiabatic condition
