Abstract: Flame spreading and flow field in solid propellant crack were studied by simulated test in order to provide analysis basis for crack propagation and branching The effects of pressurization rate, crack gap width and crack length on the combusting flow were investigated Flame front position was measured using a high speed motion analyzer This study indicates that the time required for the flame front to reach the crack tip decreases as the pressurization rate increases and the crack width decreases The maximum pressure in crack tip increases with an increase in pressurization rate and decreases with increase in crack width

Key words: Solid propellant rocket motor;Solid propellant;Crack;Flame spread;Combustion test

摘要： 通过设计实验装置形成了一条预制裂纹 ,用高速运动分析仪及数据采集系统测试了火焰在裂纹内的传播及裂纹内的压强变化 ,研究了不同几何特性和增压下 ,固体推进剂裂纹的燃烧流动情况。实验表明 :裂纹内的火焰传播速度受裂纹几何条件和增压的共同影响 ,增压越大 ,裂纹越窄 ,火焰传播速度越大。裂纹尖端压强与裂纹入口压强比的最大值也受增压和几何条件的影响 ,增压越大 ,裂纹越窄 ,该压强比越大。

关键词: 固体推进剂火箭发动机;固体推进剂;裂纹;火焰传播;燃烧试验