为了研究固体火箭发动机意外遇到火焰环境时的热安全性问题，以高氯酸铵/端羟基聚丁二烯（AP/HTPB）复合固体推进剂为装填对象，针对某种小型固体火箭发动机建立了二维烤燃简化模型。分别对800 K、1 000 K、 1 200 K火焰环境下固体火箭发动机的烤燃特性进行了数值模拟。计算结果表明，3种火焰环境下，AP/HTPB最初着火位置均发生在靠近喷管的药柱外壁一环形区域内；随着火焰温度的提高，着火延迟期快速缩短，着火温度逐渐增大；绝热层的绝热作用随着火焰温度的增大而增强；复合固体推进剂中AP首先发生缓慢分解时的温度随火焰温度的提高而增大。
Abstract
In order to study the thermal safety problems of solid rocket motor in unexpected flame environment, a two-dimensional model for cook-off of a small solid rocket motor is established, in which the composite solid propellant AP/HTPB is taken as a loading object. The cook-off characteristics of the solid rocket motor are calculated in 800 K, 1 000 K and 1 200 K flame environments, respectively. The results show that the initial ignition position of AP/HTPB is occurred in an annular region on the outer wall of propellant close to the nozzle. With the improvement of the flame temperature, the ignition delay period is shortened quickly, and the ignition temperature is gradually increased. Heat insulating effect of the insulating layer increases as the flame temperature increases. The initial slow decomposition temperature of AP component in the composite solid propellant increases with the increase in flame temperature.
关键词
兵器科学与技术 /
热安全性 /
火焰环境 /
烤燃 /
固体火箭发动机 /
固体推进剂 /
高氯酸铵/端羟基聚丁二烯 /
数值计算
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Key words
ordnance science and technology /
thermal safety /
flame environment /
cook-off /
solid rocket motor /
solid propellant /
AP/HTPB /
numerical calculation
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基金
国家自然科学基金项目（51176076）； 江苏省研究生培养创新工程项目（SJLX15_0170）
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