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

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.