摘要
通过理论分析 ,建立了固体火箭发动机推进剂裂纹动态点火的理论模型 ,对裂纹内部燃烧流动情况进行了理论计算。在非结构网格下 ,用有限元方法计算了不同几何特性和增压梯度下 ,火焰在裂纹内的传播及裂纹内的压强变化情况。计算表明 :增压梯度越大 ,裂纹越窄 ,裂纹内的火焰传播速度越大 ,裂纹尖端压强也越大。
Crack combustion flow field in solid propellant was analyzed using two-dimension model of the gas flow along the crack coupled with a simplified ignition model Control equations were solved with finite element method (FEM) under unstructured grid Effects of pressurization rate and crack geometry on the flame propagation and pressure distribution in crack were studied Numerical simulation indicates that the velocity of flame propagation in crack and the pressure at the crack tip increase as the pressurization rate increases and the crack width decreases
出处
《推进技术》
EI
CAS
CSCD
北大核心
2000年第6期59-61,共3页
Journal of Propulsion Technology
关键词
固体推进剂火箭发动机
装药
裂纹
动态点火
Solid propellant rocket engine
Charge
Crack
Flow field simulation
Finite element method
