通过对复合材料层合板刚度矩阵的转换,将中厚板等效为3D各向异性板,并将得到的等效弹性模量运用到有限元模型中,对轴压载荷作用下的中厚层合板进行稳定性分析。结果表明：有限元模拟得到的屈曲载荷与工程经验公式得到的屈曲载荷相差很小,简支情况下相差5.86%,固支情况下相差6.47%。证明这种等效方法是可行的,且可以提高复合材料中厚板的三维建模效率。
Based on stiffness matrix,the modulus of moderately thick composite laminates were translated to those of a 3D anisotropic solid.The stability of the laminates under axial compressive loading was analyzed by finite element model using effective elastic modulus.It shows that the buckling loading calculated by the FEM is close to that obtained from experiential formula,the difference is 5.86% under simple supported conditions and 6.47% under clamped supported conditions.It is proved that this method is feasible and can easily establish the model of moderately thick composite laminates in three-dimensional coordinates.
参考文献
| [1] | 邵小军,岳珠峰,李立州,张庆茂.复合材料中厚层合板在轴压位移和剪切作用下的稳定性研究[J].机械强度,2006(05):716-720. |
| [2] | 沈惠申 .复合材料层合厚板后屈曲[J].上海交通大学学报,1998,32(11):78-83. |
| [3] | Hasan Yildiz;Mehmet Sarikanat .Finite-element analysis of thick composite beams and plates[J].Composites science and technology,2001(12):1723-1727. |
| [4] | Bogdanovich A E;Deepak B P. .[J].Composites Part B:Engineering,1997,28(04):345-357. |
| [5] | 张振瀛.复合材料力学基础[M].北京:航空工业出版社,1989 |
| [6] | 中国航空研究所.复合材料结构稳定性分析指南[M].北京:航空工业出版社,2002 |
- 下载量()
- 访问量()
- 您的评分：
-
10%
-
20%
-
30%
-
40%
-
50%