论文部分内容阅读
本文根据实际固体火箭发动机的工作特点,以 Summerfield 的气相点火理论[1]为基础,建立了用炽热含氧流动气体点燃复合固体推进剂的气相点火模型;并着重从研究影响点火过程的主要因素方面考虑,通过简化,从该模型中导出了计算复合推进剂点火延迟时间的解析表达式;然后,就点火燃气的压力和氧化剂浓度这两种因素对点火延迟时间的影响,通过实验进行了验证。在理论与实验结果定性一致的基础上,本文认为,对于大多数以过氯酸铵为氧化剂的复合推进剂来说,是气相反应控制点火过程,因为利用炽热气体点火时,燃气的压力和氧化剂浓度是影响点火过程的主要因素。这一结论为如何调整设计参数,改进火箭发动机点火器的点火性能指出了方向。
Based on the working characteristics of the actual solid rocket motor and the gas-phase ignition theory of Summerfield [1], a gas-phase ignition model of composite solid propellant ignited by hot oxygen-containing flowing gas was established. The main factors affecting the ignition process were emphatically studied. In terms of simplification, an analytical expression for calculating the ignition delay time of composite propellant is deduced from the model. Then, the influence of ignition gas pressure and oxidant concentration on ignition delay time is verified by experiments . Based on the qualitative and experimental results, this paper argues that for the majority of composite propellants with ammonium perchlorate as oxidant, the gas phase reaction controls the ignition process, because when using hot gas to ignite, the gas pressure and oxidant Concentration is the main factor affecting the ignition process. This conclusion points out the direction of how to adjust the design parameters and improve the ignition performance of rocket engine igniter.