Progressive damage and residual strength of a carbon fibre reinforced metal laminate
Progressive damage and residual strength of a carbon fibre reinforced metal laminate
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DOI：
10.1177/002199839703100802
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发表时间：
1997-01-01
影响因子：
2.9
通讯作者：
Mai, YW
中科院分区：
文献类型：
--
作者：
Lawcock, G;Ye, L;Mai, YW
对碳纤维增强金属层合板(FRML)的残余强度行为进行了实验研究。进行了力学试验，测定了缺口贴片层合板的拉伸性能曲线和残余强度。对缺口尺寸为10~40 mm的中心裂纹和中心圆孔，研究了缺口几何形状的影响。锯切试件的残余强度下降幅度大于圆孔试件。C扫描和光学显微镜结合化学腐蚀技术被用来研究这些层合板的渐进损伤和失效机制。观察到了分层、裂纹扩展和纤维断裂等损伤模式。锯切试件的铝层和复合层都有稳定的裂纹扩展，而圆孔试件的铝层没有明显的裂纹扩展，但复合层出现了裂纹。结果表明，缺口尖端前方的分层是复合材料层开裂的主要原因。应用建立的纤维增强复合材料平均应力准则对残余强度数据进行了关联，得到了较好的一致性。
An experimental study on the residual strength behaviour of a Carbon Fibre Reinforced Metal Laminate (FRML) was conducted. Mechanical tests were carried out to determine the laminate tensile property profiles and residual strength of notched coupon laminates. The effect of notch geometry was studied for both centre cracks and centre circular holes with notch sizes ranging from 10 to 40 mm. The reduction in residual strength for the saw-cut specimens was greater than that for the circular hole specimens. C-scan and optical microscopy associated with a chemical etching technique were used to investigate progressive damage and failure mechanisms in these laminates. Damage modes such as delamination, crack growth and fibre breakage were observed. Stable crack growth was seen in both the aluminium and composite layers for the saw-cut specimens, but no visible crack growth in the aluminium layers in the circular hole specimens was found although cracking in the composite layer occurred. It is concluded that delamination ahead of the notch tip is attributed to cracking of the composite layer. The average stress criterion developed for fibre reinforced composites was applied to correlate residual strength data and good agreement was obtained.