FAILURE PREDICTION TECHNIQUE FOR COMPRESSION LOADED CARBON FIBER-EPOXY LAMINATE WITH OPEN HOLES
FAILURE PREDICTION TECHNIQUE FOR COMPRESSION LOADED CARBON FIBER-EPOXY LAMINATE WITH OPEN HOLES
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DOI：
10.1177/002199839102501106
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发表时间：
1991-11-01
影响因子：
2.9
通讯作者：
SMITH, PA
中科院分区：
文献类型：
--
作者：
SOUTIS, C;FLECK, NA;SMITH, PA
研究了含单孔的碳纤维-环氧复合材料的面内压缩断裂行为。失效是由于0度纤维微屈曲被分层包围。微屈曲区始于井眼边界。在2-3毫米的临界微扣长度变得不稳定之前，它在不断增加的载荷下稳定地延伸。采用内聚区模型对正交各向异性层合板的损伤扩展和破坏进行了分析，该模型将裸眼周围的损伤表示为加载在其表面上的线裂纹。所选材料和铺层的缺口强度实验结果与预测结果吻合良好。
The inplane compressive fracture behaviour of a carbon fibre-epoxy laminate containing a single hole is examined. Failure is due to 0-degrees fibre microbuckling surrounded by delamination. The microbuckled zone initiates at the hole boundary. It extends stably under increasing load before becoming unstable at a critical microbuckle length of 2-3 mm. The damage propagation and failure of the orthotropic laminate is analysed by a cohesive zone model, in which damage around the open hole is represented by a line crack loaded on its faces. Good agreement between experimental and predicted notched strength is observed for the chosen material and lay-up.