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基于user-defined function(UDF)技术将固体火箭发动机喷管热结构计算程序嵌入到FLUENT软件中,通过UDF宏命令实现FLUENT耦合传热结果数据的提取,编写了接触边界的自动识别程序,采用直接约束法模拟喷管界面间的接触非线性问题,实现了固体火箭发动机喷管热结构的一体化计算.
Based on user-defined function (UDF) technology, the calculation program of thermal structure of solid rocket motor nozzle was embedded in FLUENT software. The UDF macro command was used to extract the data of FLUENT coupling heat transfer and the automatic identification program of contact boundary was prepared. Constraint method to simulate the contact nonlinearity between the nozzle interface to achieve a solid rocket engine nozzle thermal structure of the integrated calculation.