Abstract: To develop the rocket propellant temperature measuring unit, using computer numerical simulation and experimental method, researched a propellant’s transient temperature field under first boundary condition. The results of calculation and experiment complies well with each other and the changing rules of propellant transient temperature field as well as main thermal resistance affecting temperature distribution were gotten. Moreover, studied the difference between temperature at the half of propellant maximum thickness and mass weighted average temperature, and got the best position to measure temperature.

Key words: Rocket propellant;Temperature diatribution;Numerical simulation;Thermal conductivity

摘要： 为适应研制火箭推进剂初始温度测量装置的需要,利用计算机数值模拟和实验方法,研究了某种火箭推进剂在第一类边界条件下的非稳态温度场,程序计算结果与实验测量值吻合较好,得出了该推进剂的非稳态温度场的变化规律及影响温度分布的主要热阻,研究了常用的推进剂最大肉厚1/2处温度与质量加权平均温度的差别,给出了测量温度的最佳位置。

关键词: 火箭推进剂;温度分布;数值仿真;导热性