关键词: 火箭发动机喷管;烧蚀;温度分布;固体火箭发动机

Abstract: This paper presents the numerical simulation for axisymmetric two-dimensional transient temperature distribution in composite nozzle of solid rocket motor which consists of graphite and silica-phenolics under the condition of moving boundaries caused by charring and ablating recession. Based on the method of coordinate system transformation and the concept of equivalent heat capacity, the unified partial differential equations are formed from the principle of energy balance for the element area in different material layers.In numerical simulation, the explicit scheme is used for the inner nodes of the mesh in the computational plane,and the implicit scheme is used for the boundary nodes.The calculating process is rather forthright.Numerical results of a sample are compared with the experimental data,which shows that this method can meet the precision requirement for engineering design.

Key words: Solid rocket engine;Ablation;Temperature distribution