固体火箭复合结构喷管传热的隐式计算方法

IMPLICIT SCHEME ON HEAT-CONDUCTION IN SOLID ROCKET COMPOUND-STRUCTURE NOZZLE

关键词:  固体火箭喷管  导热  隐式格式

Key words:  Solid rocket nozzle  Temperature distribution  Implicit scheme

摘要:

采用适用于多层复合结构的当量热容瞬态热传导方程,通过坐标变换解决多个移动边界问题,用ADI方法推导了二维隐式求解格式,在与烧蚀相耦合的情况下获得了复合结构喷管的温度分布。用隐式方法计算有效地减少了计算机时,对工程设计大有裨益。

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.