AP/HTPE星形装药固体火箭发动机三维烤燃特性研究

3D Cook-off Characteristics Study of Solid Rocket Motor with AP/HTPE Star-Charged

关键词:  固体火箭发动机  热安全性  烤燃  数值计算  AP/HTPE

Key words:  Solid rocket motor  Thermal safety  Cook-off  Numerical simulation  AP/HTPE

摘要:

为了有效提高火箭、导弹武器在高温环境下的热安全性，增强其战场生存能力，基于AP基推进剂的烤燃反应机理，建立了装填星形孔高氯酸铵/端羟基聚醚（AP/HTPE）复合固体推进剂的三维非稳态固体火箭发动机烤燃模型。针对慢速和快速两种不同的热载荷条件，分别采用3.6~10.8K/h的慢烤升温速率和1.45~1.95K/s的快速烤燃升温速率对固体火箭发动机进行多工况的烤燃数值模拟。结果表明：发动机着火延迟时间和升温速率呈负相关趋势。升温速率的变化对发动机着火温度无显著影响。在快速烤燃条件下，升温速率的不同使得发动机着火位置出现跳跃性变化。

Abstract:

In order to effectively improve the thermal safety of rocket and missile weapons in high temperature environments and enhance their battlefield survivability， a 3D unsteady solid rocket motor cook-off model loaded with a star-shaped hole ammonium perchlorate/terminal hydroxyl polyether （AP/HTPE） composite solid propellant was developed based on cook-off reaction mechanism of AP-based propellants. Numerical simulations of solid rocket motors were carried out for slow and rapid heat load conditions， using slow cook-off heating rates of 3.6K/h to 10.8K/h and rapid cook-off heating rates of 1.45K/s to 1.95K/s for multiple operating conditions respectively. The results show that there is a negative correlation between the motor ignition delay time and the heating rate. Changes in the heating rates had no significant effect on the ignition temperature. Under the condition of fast cook-off， the difference of heating rate causes the motor ignition position to change jumpingly.