非壅塞固体火箭冲压发动机及其贫氧推进剂  

Study of the Unchoked Ducted Rocket Engine and Fuel-Rich Propellant

作　　者：张炜[1] 夏智勋[1] 朱慧[1] 方丁酉[1] 徐东来 王虎干 曹军伟 朱葆华 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]空空导弹研究院,河南洛阳471000

出　　处：《国防科技大学学报》2002年第4期9-11,共3页Journal of National University of Defense Technology

摘　　要：研究了非壅塞固体火箭冲压发动机的工作特性。研制出了能量高、燃速高、燃速压强指数高、低压燃烧性能好的铝镁贫氧推进剂配方。采用连管式试验与数值分析相结合的方法 。The operating characteristics of the solid ducted rocket are numerically studied.The results show that the performance of the unchoked ducted rocket (UDR)is superior to that of choked one.The unchoked ducted rocket should work with the high burning rate exponent fuel rich propellant.The aluminum magnesium fuel rich propellants for the unchoked ducted rocket with high burning rate,exponent and good flammability limits are developed.Through the connected pipe tests and numerical analysis,the performance of the unchoked ducted rocket engine is investigated.

关 键 词：非壅塞 固体火箭冲压发动机 贫氧推进剂 

分 类 号：V435.21[航空宇航科学与技术—航空宇航推进理论与工程]