This paper is concerned about the automatic finite element modeling of a wing structure. The row and column method is used to identify the structure parts(ribs, spars, skins and pillars). A customization module of...This paper is concerned about the automatic finite element modeling of a wing structure. The row and column method is used to identify the structure parts(ribs, spars, skins and pillars). A customization module of PCL(PATRAN Command Language under PATRAN 6.0) code from constructing airfoil curves to creating the entire wing FEM model is designed and developed. The geome tric, mesh density, material, load and boundary parameters can be easily and correctly input with the friendly interactive interface. A VFW614 wing is analyzed from creating airfoil curves to the show of stresses calculated by using NASTRAN 68 as an example. The results show that this customization module is very effective and efficient.展开更多
对于有限元分析来说,网格划分是其中最关键的一个步骤,网格划分的好坏直接影响到解算的精度和速度。对网格划分这个步骤所涉及到的一些问题,尤其是与复杂模型相关的一些有限元网格划分问题作简要阐述,并给出一个复杂模型的AN SY S有限...对于有限元分析来说,网格划分是其中最关键的一个步骤,网格划分的好坏直接影响到解算的精度和速度。对网格划分这个步骤所涉及到的一些问题,尤其是与复杂模型相关的一些有限元网格划分问题作简要阐述,并给出一个复杂模型的AN SY S有限元网格划分实例。为工程设计提供参考。展开更多
文摘This paper is concerned about the automatic finite element modeling of a wing structure. The row and column method is used to identify the structure parts(ribs, spars, skins and pillars). A customization module of PCL(PATRAN Command Language under PATRAN 6.0) code from constructing airfoil curves to creating the entire wing FEM model is designed and developed. The geome tric, mesh density, material, load and boundary parameters can be easily and correctly input with the friendly interactive interface. A VFW614 wing is analyzed from creating airfoil curves to the show of stresses calculated by using NASTRAN 68 as an example. The results show that this customization module is very effective and efficient.