Abstract: 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

Key words: Solid propellant rocket engine;Charge;Crack;Flow field simulation;Finite element method

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。

关键词: 固体推进剂火箭发动机;装药;裂纹;流场仿真;有限元法