摘要
翼柱形药柱模拟发动机的翼槽结构对点火瞬态过程的火焰传播规律存在着潜在的影响。通过试验分析不同质量流量的点火剂燃气以不同的角度喷射到翼柱形药柱模拟发动机的推进剂表面时的火焰传播规律,发现火焰峰传播到翼槽区域后,尾部翼槽底部区域被最后点燃。通过对试验进行数值仿真分析可知,压缩在翼槽底部温度较低的气体减弱了高温燃气与推进剂的换热,导致推进剂达到着火点温度的时间延迟,进而致使火焰峰传播速度降低,火焰峰最后到达尾部翼槽底部区域。
Fin-slot of SRM with finocyl grain is of the potential influence on the behavior flame spreading in the overall ignition transient.By test to analyze the flame propagation of SRM with finocyl grain in different ignition mass flow rate and injection angle,the results of test indicate the bottom of the tail fin-slot was ignited finally as the flame spread to the tail fin-slot.The results of simulation show that the low temperature gas in the tail-slot weaken the heat transfer effect of the high temperature gas,and further decrease the velocity of the flame propagation,the flame arrive to the bottom of the tail fin-slot finally.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第1期38-42,共5页
Journal of Solid Rocket Technology
作者简介
赵汝岩（1980-），男，博士，研究方向为航空航天发动机工作过程仿真。E-mail：Ruyanzhao@163.com
