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首页> 外文期刊>The Aeronautical Journal >An experimental method to determine the intralaminar fracture toughness of high-strength carbon-fibre reinforced composite aerostructures
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An experimental method to determine the intralaminar fracture toughness of high-strength carbon-fibre reinforced composite aerostructures

机译：确定高强度碳纤维增强复合材料航空结构层内断裂韧性的实验方法

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摘要

Carbon fibres with high tensile strength are being increasingly utilised in the manufacture of advanced composite aerostructures. A Modified Compact Tension (MCT) specimen is often deployed to measure the longitudinal intralaminar fracture toughness but a high tensile strength often leads to premature damage away from the crack tip. We present an approach whereby the MCT specimen is supported by external fixtures to prevent premature damage. In addition, we have developed a novel measurement technique, based on the fibre failure strain and C-scanning, to determine the crack length in the presence of surface sublaminate delamination which masks the crack tip location. A set of cross-ply specimens, with a ((90/0)(s))(4) layup, were manufactured from an IMS60/epoxy composite system Two different data reduction schemes, compliance calibration and the area method, are used to determine the fibre-dominated initiation and propagation intralaminar fracture toughness values. Propagation values of fracture toughness were measured at 774.9 +/- 5.2% kJ/m(2) and 768.5 +/- 4.1% kJ/m(2), when using the compliance calibration method and the area method, respectively. Scanning Electron Microscopy (SEM) is carried out on the fracture surface to obtain insight into the damage mechanism of high-tensile-strength fibre-reinforced unidirectional composites. The measured tensile fracture toughness value is used in a fully validated computational model to simulate the physical test.
机译：具有高抗拉强度的碳纤维正越来越多地用于制造先进的复合航空结构。经常使用改良的紧凑拉伸（MCT）样品来测量纵向层内断裂韧度，但高拉伸强度通常会导致裂纹尖端过早损坏。我们提出了一种方法，其中MCT标本由外部固定装置支撑，以防止过早损坏。此外，基于纤维破坏应变和C扫描，我们已经开发了一种新颖的测量技术，可以在存在表面亚层脱层的情况下确定裂纹长度，该表面层脱层掩盖了裂纹尖端的位置。使用IMS60 /环氧复合材料系统制造了一组具有（（90/0）（s））（4）叠层的交叉层试样，使用了两种不同的数据缩减方案，即顺应性校准和面积法确定纤维为主的起始和扩展层内断裂韧性值。使用顺应性校准方法和面积方法分别测得的断裂韧度的传播值为774.9 +/- 5.2％kJ / m（2）和768.5 +/- 4.1％kJ / m（2）。在断裂表面上进行扫描电子显微镜（SEM），以深入了解高强度纤维增强单向复合材料的损伤机理。在完全验证的计算模型中使用测得的拉伸断裂韧性值来模拟物理测试。

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