An experimental and numerical investigation into damage mechanisms in tapered laminates under tensile loading
An experimental and numerical investigation into damage mechanisms in tapered laminates under tensile loading
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拉伸载荷下锥形层压板损伤机制的实验和数值研究
DOI：
10.1016/j.compositesa.2020.105862
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发表时间：
2020
期刊：
影响因子：
--
通讯作者：
S. Hallett
中科院分区：
文献类型：
--
作者：
Bing Zhang;L. Kawashita;Mike I. Jones;J. K. Lander;S. Hallett
层合复合材料的穿透厚度减薄对于重量和气动效率是必不可少的，但它们也可能是损伤的起始点。通过实验和高保真有限元模拟，研究了中等锥度层合板和严重锥度层合板在粗细两端夹持载荷下的拉伸破坏机理。主要的失效模式是从锥形区域中的终止层开始的分层，这对在铺层下降位置处的小分层缺陷非常敏感。对于位置和载荷，实验测量和有限元预测在所有情况下都具有很好的相关性。在严重锥度的情况下，接触应力影响分层，因此还需要考虑纤维破坏准则，包括纤维方向拉应力及其与接触施加的贯穿厚度的直接应力和剪应力的相互作用。
Through-thickness thickness reductions in laminated composites are essential for weight and aerodynamic efficiency, but they can also be the site of damage initiation. Tensile failure mechanisms of modestly tapered laminates, loaded via gripping their thick and thin ends, and a severely tapered laminate, loaded by contact at its tapered section, were investigated via experiments and high-fidelity finite element modelling. The primary failure mode is by delamination, initiated from a terminated ply in the tapered region, which is quite sensitive to a small delamination defect at a ply drop location. Experimental measurements and FE predictions correlate very well in all cases for both location and load. In the severely tapered case, the contact stress influences the delamination and so a fibre failure criterion also needs to be considered, including both the fibre direction tensile stress and its interaction with through-thickness direct and shear stresses imposed by the contact.
DOI：
10.1016/j.compositesa.2012.12.007
发表时间：
2013-05-01
影响因子：
8.7
作者：
Lemanski, S. L.;Wang, J.;Wisnom, M. R.
通讯作者：
Wisnom, M. R.