复合材料平尾有限元建模方法研究

Investigation of finite element method for composite horizontal tail plane

为建立合理的复合材料有限元模型提供依据,本文采用MSC/PATRAN有限元程序对某大型飞机全复合材料水平尾翼分别建立总体有限元模型和详细有限元模型,对复合材料性质卡分别定义为膜元和壳元,通过MSC/NASTRAN线弹性静力分析求解器进行多工况的分析求解,比较了不同的有限元模型和复合材料性质卡在各载荷工况下的力学特性和应力分布。结果表明采用膜元和壳元没有明显的区别,在条件许可的情况下推荐使用详细有限元模型。

In order to provide the basis for building finite element model of composite,the global FEM and detail FEM model of composite horizontal stabilizer of a large aircraft was established based on MSC/PATRAN finite element program, and the composite property card of elements was individually defined as membrane and shell. By analyzing the multiple loading cases based on MSC / NASTRAN linear elastic static analysis solver, the mechanical properties and stress distribution of the different FEM model and composite property card was compared,the result indicated that there was no obvious difference between membrane and shell,and the detailed FEM model was recommended if condition was permitted.