论文部分内容阅读
模拟固体火箭发动机内的点火瞬态,必须了解其推进剂固相表面的火焰传播过程及给定初始气/凝相上的火焰传播速度。通过在推进剂表面嵌入热电偶丝的类靶线法及光电探测法,对后向台阶型装药的高能推进剂开展了两次火焰传播实验。结果表明,上游推进剂表面是由火焰连续传播所点燃,下游表面是由上游推进剂燃烧产生的燃气所点燃,台阶底部区域则是最后点燃。同时发现单纯由电阻丝点火建立的火焰传播过程时间较长,其中气相扩散并点燃下游推进剂表面的平均速率为57.78 cm·s-1,上游火焰传播的平均速率仅为4.92 cm·s-1。
To simulate the ignition transient in a solid rocket engine, it is necessary to know the flame propagation process on the solid surface of the propellant and the flame propagation velocity on a given initial gas / condensate phase. The flame propagating experiment was carried out on the backward-stepped charge propellant by means of the target-like method with the thermocouple wire embedded in the surface of the propellant and the photodetection method. The results show that the surface of the upstream propellant is ignited by the continuous flame propagation, the downstream surface is ignited by the gas generated by the combustion of the upstream propellant, and the bottom of the step is finally ignited. At the same time, it was found that the propagation of flame propagated solely by the resistance wire ignited for a long time, in which the average rate of gas diffusion and ignition on the surface of the downstream propellant was 57.78 cm · s-1 and the average flame propagation velocity was only 4.92 cm · s-1 .