130火箭推进剂非稳态温度场特性数值研究

Numerical Research on Transient Temperature Field Characteristics of 130 Rocket Propellant

鉴于火箭弹发射前对推进剂温度精确测定的复杂性 ,利用目前应用广泛的计算机数值模拟技术 ,通过计算程序对 1 3 0火箭推进剂非稳态温度场进行了数值模拟 ,并利用设计的实验装置对推进剂的温度进行了试验测定 ,计算结果与测量点温度值吻合较好 ,得出了 1 3 0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。此外 ,本文确定了 1 3 0推进剂 (单药柱 )的温度特征点 。

According to the complexity of precisely measuring propellant temperature before firing rocket projectiles, with present widely used computer numerical simulation method, the article has simulated 130 rocket propellant transient temperature field by program and also measured propellant temperature by designed experimental unit. 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 distrabution have been gotten. Moreover the article has found temperature characteristic point for 130 propellant(single), the result has important meaning for developing propellant temperature real time measure unit.