关键词: 固体火箭喷管;导热;隐式格式

Abstract: Solid rocket nozzle is usually made of compound materials and formed as a multi-layer compound-structure. Due to pyrolysis and ablation of nozzle lining ,the inner boundaries are moved. So, the heat-conductive in solid rocket nozzle is an axisymmetric, transient heat-conductive problem nuder the condition of moving boundaries in multi-layer compound-structure.The equivalent capacity transient heat-conductive equation is adopted in order to meet the condition of pyrolysis and multlayer comound-structure, and the coordinate transformtion is adopted in order to solve moving boundaries. Besides, meterial physical properties are considered as anisotropy and changing with temperature. By using ADI method, the axisymmetric implicit scheme is deduced. The temperature distribution in multi-layer compound -Structure nozzle is obtained under the condition of coupling with ablation.The computer time by using implicit scheme is reduced 3 times in comparison with explicit one.

Key words: Solid rocket nozzle;Temperature distribution;Implicit scheme