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| Zig-zag theory for thick laiminated compoiste plates and finite element analysis |
| Received:September 23, 2014 Revised:March 14, 2015 |
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| DOI：10.7511/jslx201601007 |
| KeyWord:Zig-zag theory triangular element transverse normal strain laminated composite/sandwich plate transverse shear stress |
| Author | Institution |
| 隋晓东 |
沈阳飞机设计研究所, 沈阳 |
| 任晓辉 |
沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 |
| 秦政琪 |
沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 |
| 吴振 |
沈阳航空航天大学 辽宁省飞行器复合材料结构分析与仿真重点实验室, 沈阳 |
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| Abstract: |
| For bending problems of thick composite structures, the maximum percentage errors in the existed zig-zag theories are more than 35.In order to reasonably analyze the bending problems of such structures, this paper proposes an accurate and efficient zig-zag theory for thick composite plates.Number of unknown variables involved displacement fields is independent of layer number in laminates.Moreover, the first derivative of transverse displacement has been taken out from the in-plane displacement fields in the refined zig-zag theory, so that the C0 shape functions are only required during its finite element implementation.Based on the proposed zig-zag theory, a six-node triangular element in combination with finite element formulation is presented for bending analysis of thick laminated composite and sandwich plates, which is compared to the previous C1-type zig-zag theory.Numerical results showed that the proposed zig-zag theories is more accurate and efficient in comparison with the existed zig-zag theories. |
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