基于自由装填固体火箭发动机的快烤试验结果,对发动机快烤第一响应阶段的径向传热进行了数值计算分析。结果表明,发动机温度分布受外部高温流场的影响,呈两侧受热多、底部受热少、上部受热最少的非均匀分布形态;直至发动机第一响应阶段结束,侧方外层推进剂的温度为397 K,底部外层推进剂的温度为359 K;推进剂在快烤30 s后开始进入温度稳定上升阶段,侧方外层推进剂的温度稳定上升率为1.55 K/s,底部外层推进剂的温度稳定上升率为1.09 K/s;推进剂内表面不具备自发点火的温度条件,这说明快烤过程中的径向传热并不是导致发动机自点火的主要因素。

Based on fast cook-off test results of free-loading solid rocket, numerical analysis of radial heat transfer in first stage of the motor's response to fast cook-off is carried out. The results show that motor's temperature distribution is affected by the external high temperature flow field, which has a non-uniform distribution pattern with more heat on both sides, less heat on the bottom, and least heat on the top. Until the end of first response stage, temperature of outer propellant on the side is 397 K, and temperature of outer propellant on the bottom is 359 K. After 30 s of fast cook-off, the temperature of propellant began to enter a stable rising stage. The temperature rise rate of outer propellant on the side is 1.55 K/s. The temperature rise rate of outer propellant on the bottom is 1.09 K/s. The temperature of inner propellant is not high enough to cause self-ignition. It shows that radial heat transfer is not the main factor that causes the motor to self-ignite in fast cook-off.