关键词: 热学 , 火箭发射药 , 二维非稳态温度场 , 非结构化网格 , 数值模拟

Abstract: Simulating the temperature field of a rocket motor (including propellant) by numerical method is an effective way to get real-time temperatures of the rocket propellant. A physical model and a mathematical model for heat transfer of the researched rocket were established. Because the rocket propellant, which consists of seven columns, has a complex structure, it is impossible to calculate the calculated domain ’ s temperature field with structured grids. So triangular unstructured grids were generated m the domain and then all nodes discrete equations were deduced. The transient tempera?ture field of the domain, including propellant, was worked out by numerical method. The comparison between temperature curves, gotten by calculation and test, shows the calculation result is correct. So the transient temperature field of the complex structure propellant can be correctly simulated by the proposed method.

Key words: thermology , rocket propellant , two-dimensional transient temperature field , unstructured grid , numerical simulation