摘要
鉴于火箭弹发射前对推进剂温度精确测定的复杂性,利用计算机数值模拟技术,对某种火箭推进剂在第三类边界条件下的非稳态温度场进行了数值模拟,并利用实验装置对推进剂的温度进行了实验测定,计算结果与测量点温度值吻合较好,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。
Whereas the complexity of precisely measuring propellant temperature before firing rocket projectiles with computer numerical simulation method,numerically under third kind boundary condition a rocket propellant transient temperature field was simulated and propellant temperature was measured by experimental unit.The results of calculation and measurement comply well with each other.Varia- tion rules of propellant transient temperature field was obtained as well as main thermal resistance af- fecting temperature distribution.Moreover,the difference between temperature at the point of half of propellant maximum thickness and mass weighted average temperature was studied.
出处
《火炮发射与控制学报》
北大核心
2003年第3期5-9,共5页
Journal of Gun Launch & Control
