某型发动机喷管-排气管系统建模方法

Modeling Method on Nozzle and Exhaust Pipe System of Rocket Engine

基于有限元分析法,研究某型发动机喷管-排气管系统建模方法。喷管的管束组件由多根螺旋管焊接而成,空间结构复杂,建立有限元模型难度大。将喷管沿轴线方向分为4段建模,采用多层各向异性壳单元模拟喷管管壁,通过偏转单元坐标x轴模拟螺旋角度。基于上述模型的模态分析与试验结果符合较好,模型可以用于振动分析。

The modeling method on nozzle and exhaust pipe system of rocket engine was studied based on finite element analysis. The nozzle subassembly was composed of spiral pipes and it is virtually impracticable to develop finite element model due to its structural characteristic. The nozzle was separated into 4 segments along its axes, nozzle wall was simulated by multi-layer orthotropic shell element, and the spiral angle was simulated by deflecting the X axis. Experiment results were in good agreement with modal analysis which showed that the model could be used in viberation analysis.