中文摘要：

为研究某多根药柱火箭发射药的非稳态温度场特性，设计了内装此种发射药火箭发动杌的传热实物模型，将模型置入温控箱内进行温升实验，以测得的发动机壳体外壁温度为已知条件，建立数理模型，在计算区域内生成非结构化网格，通过数值计算求出模型的非稳态温度场，在此基础上，分析和研究了温度场特性，研究结果对多根药柱火箭的实时药温测量系统的研制具有指导作用。

英文摘要：

In order to study the unstable temperature field characteristics of rocket propellant with seven columns, a heat transfer simulator for the rocket motor containing this kind of porpellant was devised. The simulator was placed in an attemperator, and then a temperature-lift experiment on the simulator was performed in the attemperator. A physical and mathematical model for heat transfer of the simulator was established on condition that the measured temperatures of outer wall of the motor（simulator） are used as known boundary. Unstructured grids were generated in calculation district, and unstable temperature field of the motor was worked out by numerical method. Based on the numerical calculation, temperature field characteristics of the motor were discussed. Studies of the paper offer instruction for development of real-time propellant temperature measuring system of the rocket.