复合材料层合板缺口强度的CDM三维数值模型

针对复合材料层合结构缺口强度问题,基于连续损伤力学（CDM）提出了一种三维损伤数值模型。模型区分了层内损伤（纤维失效、纤维间失效）和层间分层损伤的不同失效模式。采用三维Puck准则与Aymerich准则对上述2类损伤进行判定,材料失效后基于CDM中线性软化模型对材料损伤进行演化。模型考虑了复合材料层合板子层的就位效应和剪切非线性行为。对Carlsson的AS4/3501-6缺口拉伸强度试验进行数值模拟。结果表明:分析结果与试验结果吻合良好,证明了该模型能够准确地预测含缺口复合材料层合板面内拉伸强度。      

Failure assessment on central-sharp notched carbon/epoxy laminates

Fracture models to predict the strength of laminated composites having sharp notches demand the un-notched strength and the critical damage size ahead of the notch. The critical damage size, in general, depends on the material, geometry of the specimen and size of the sharp notch. The extraordinary success of a fracture model lies in its ability to combine a theoretical framework with experimentally measured quantities. Modifications are made in one of the stress-fracture criteria known as the point stress criterion for accurate prediction of notched tensile strength of composite laminates containing sharp notches. To examine the adequacy of these modifications, fracture data of central-sharp notched carbon/epoxy composite laminates with various lay-ups are considered. The notched strength estimates are found to be close to the test results. The modified point stress criterion is very simple and accurate in predicting the notched tensile strength of laminated composites.     

The prediction of R-curves and notched tensile strength for composite laminates

A new model is proposed to explain the cracking and fracture of notched composite laminates. It is based on the energy absorption associated with the micromechanisms of fracture. Crack-growth resistance curves (R-curves) are predicted for a wide range of laminate constructions and materials, and the corresponding notched strengths deduced. Both R-curve and notched strength predictions are in good agreement with published data. The effect of improved fibre-matrix bonding on laminate notched strength is investigated in a case-study, and is successfully predicted using the model.     

Effect of fibre/matrix adhesion on residual strength of notched composite laminates

Effects of fibre/matrix adhesion and residual strength of notched polymer matrix composite laminates (PMCLs) and fibre reinforced metal laminates (FRMLs) were investigated. Two different levels of adhesion between fibre and matrix were achieved by using the same carbon fibres with or without surface treatments. After conducting short-beam shear and transverse tension tests for fibre/matrix interface characterisation, residual strength tests were performed for PMCLs and FRMLs containing a circular hole/sharp notch for the two composite systems. It was found that laminates with poor interfacial adhesion between fibre and matrix exhibit higher residual strength than those with strong fibre/matrix adhesion. Major failure mechanisms and modes in two composite systems were studied using SEM fractography. The effective crack growth model (ECGM) was also applied to simulate the residual strength and damage growth of notched composite laminates with different fibre/matrix adhesion. Predictions from the ECGM were well correlated with experimental data.     

Tensile fracture behaviour of notched boron/aluminum composite laminates

This paper presents modifications in the stress fracture criteria (known as the point stress criterion and the average stress criterion), developed by Whitney and Nuismer to predict the tensile strength of composite laminates containing holes and cracks. A simple relation is used for the characteristic lengths to take care of the notch size dependence, which can improve the accuracy while evaluating the notched strength of composite laminates. The applicability of the simple relation is examined by considering a good amount of fracture data on boron/aluminium laminates. The present procedure correlates well with the test data on circular hole specimens as well as various cracked configurations and confirms that the approach can be applied for tensile strength estimations of notched composite laminates.     

Notch sensitivity of thermoset and thermoplastic laminates loaded in tension

Inplane tensile fracture of unnotched and notched thermoset graphite-epoxy and thermoplastic graphite-PEEK composite laminates is examined. Both fibre-dominated quasi-isotropic and matrix dominated ±45 angle-ply layups were investigated.Classical lamination theory predictions of elastic and strength properties of unnotched specimens are compared with experiments. Several notched geometries, i.e. centre-notched, double-edge notched and open-hole specimens subjected to tensile loading to fracture were examined. The notched strength of the quasi-isotropic laminates was analysed by a damage zone model, where damage around the notch is represented by an equivalent crack with cohesive force acting between the crack surfaces.Good agreement between experimental and calculated strength was observed for the graphite-epoxy laminates which failed in a collinear manner. For the graphite-PEEK laminates discrepancies between predicted and experimental strength are related to observed deviations from collinear crack growth. The angle-ply graphite-PEEK laminates showed larger notch sensitivity than the corresponding graphite-epoxy, probably due to less degree of stress relieving damage formation around the notch.     

An experimental study of the influence of fibre–matrix interface on fatigue tensile strength of notched composite laminates

The objective of this study was to investigate the effect of fibre–matrix interfacial adhesion on fatigue residual strength of polymer matrix composite laminates containing a circular hole. Composite laminates were manufactured using surface-treated and -untreated carbon fibres, and the interfacial adhesion was quantified by measuring the transverse flexural strength of the two material systems. Tensile–tensile cyclic fatigue experiments were conducted at three load levels. Residual strength of notched laminates, subjected to cyclic loading was then measured for the two composite systems. Damage mechanisms were analysed using C-scan and SEM fractography and correlated with notched residual strength.     

Fracture strength of composite laminates with an elliptical opening

The ultimate strength of composite laminates containing elliptical openings can be predicted reasonably well using two fracture models which utilize the first ply failure strength of the notched and corresponding unnotched laminates. These models have the capability to predict the fracture strength of anisotropic laminates with an opening of general construction and subjected to general in-plane loading. Although the characteristic lengths for the present models are determined empirically, it is found that the characteristic lengths for an elliptical opening of any aspect ratio can be expressed in a closed-form function. These parameters are determined using three (e.g., two circular holes and one crack) or more data points. The experimental result shows that the notched strength of the graphite/epoxy cross-ply laminate is quite sensitive to the opening aspect ratio.     

Tensile fracture strength of 2124Al–10 vol.% SiCp composite compact tension specimens

This paper examines the tensile fracture behavior of 2124Al–10 vol.% SiCp composites by generating the fracture data from the tensile as well as compact tension specimens. The composites were produced through squeeze casting process. For matrix strengthening and improving ductility, the specimens were heat-treated through solutionizing and ageing. The modified inherent flaw model is utilized for fracture strength evaluation. Fracture strength estimations are found to be in good agreement with test results. The modified relationship between the notched strength and the inherent flaw length will be useful for accurate prediction of the notched tensile strength of composite laminates.     

柔性非织造布和玻璃纤维布叠层热压制备玻璃纤维布/聚苯硫醚复合板材

为改善玻璃纤维增强聚苯硫醚（PPS）复合板材的力学性能,分别以柔性的玻璃纤维布和PPS非织造布作为增强体和基体,采用叠层热压成型法制备出刚性的复合板材,采用力学性能测试、XRD、PLM、SEM研究了热压温度、热压时间、玻璃纤维含量和处理玻璃纤维布的硅烷偶联剂种类对复合板材的力学性能、结晶度、结晶形态和微观形貌的影响。结果表明,在无硅烷偶联剂处理玻璃纤维布时,控制热压温度为320℃,热压时间为30 min,压力为30 MPa,玻璃纤维质量分数为50%,复合板材的拉伸强度和弯曲强度最佳,分别为286.0 MPa和175.0 MPa,缺口冲击强度达到61.6 MPa。使用硅烷偶联剂KH560处理玻璃纤维布,在最佳成型工艺条件下,复合板材力学性能改善最明显,其弯曲强度为394.9 MPa,弯曲模量为23.6 GPa,层间剪切强度为16.4 MPa,缺口冲击强度为81.0 MPa。通过优化实验条件和使用硅烷偶联剂处理玻璃纤维表面,复合板材的力学性能得到了明显提高。     

光滑与含孔复合材料压-压疲劳实验研究

本文新设计了光滑与含孔两种复合材料试样的抗失稳装置, 简述了这两种试样的压-压疲劳实验概况, 分析和讨论了其疲劳破坏机理, 提出复合材料疲劳损伤的“转捩点”概念。     

STRENGTH PREDICTION AND DAMAGE MECHANISMS OF GLASS/EPOXY WOVEN LAMINATES WITH CIRCULAR HOLES

Abstract— The notched strengths of four woven laminates (two orthotropic, one quasi-isotropic and one square symmetrical) under monotonic uniaxial loading, predicted with the point and average stress criteria, the two parameter criterion, the progressive degradation model, and the initial and improved point and minimal strength models, have been respectively compared with the experimental data. The damage mechanisms for the laminates were tentatively studied. The results show that, for minimal experimental information, the notched strengths predicted by the improved minimal strength models are the most precise and the progressive degradation model can numerically illustrate the damage mechanisms in detail. The damage mechanisms of the woven laminates were found to be very different from those of non-woven laminates.     

3D finite element analysis of tensile notched strength of 2/2 twill weave fabric composites with drilled circular hole

This paper presents the micromechanical three-dimensional finite element models of the 2/2 twill weave T300 carbon/epoxy woven fabric composite laminates with drilled circular holes of different sizes. A fiber breakage failure criterion for predicting the ultimate tensile notched strength of fiber dominated composites is also proposed. It is found that the location of failure initiation for laminates with large hole size is different from those for laminates with smaller holes while the stress concentration may not occur at the notch roots for the fiber dominated laminates. Based on the uniaxial, shear and von Mises stress distributions in the yarn and matrix, the influence of hole-size on the stress distributions and stress concentration is discussed. Standard tensile tests with modifications are performed for this particular type of woven fabric composites. The apparent strain concentration factors and notched strengths determined by experiments are presented and the finite element models are verified by satisfactory correlation between prediction and experiment.     

玻璃纤维-碳纤维混杂增强PCBT复合材料层合板的制备及低速冲击性能

采用环状对苯二甲酸丁二醇酯(CBT)预浸料,利用真空袋辅助热压工艺制备了玻璃纤维机织布-碳纤维机织布/聚环状对苯二甲酸丁二醇酯(GF-CF/PCBT)混杂复合材料层合板。利用双悬臂梁(DCB)和三点端部开口弯曲(3ENF)试验对连续纤维增强PCBT复合材料层合板的层间强度做出评估。同时,利用低速冲击试验结合Abaqus/Explicit有限元仿真重点考察了混杂纤维增强PCBT复合材料层合板的低速冲击性能。试验结果表明:尽管CF/PCBT复合材料层合板具有优异的层间性能,当冲击能量为114.3J时,由于CF自身的脆性,CF/PCBT复合材料层合板被完全穿透,而GF-CF/PCBT混杂复合材料层合板只在表面形成凹痕。与纯CF增强PCBT复合材料层合板相比,铺层形式为[CF/GF/CF]25的GF-CF/PCBT混杂复合材料层合板的抗冲击损伤能力提高2倍。仿真得到的云图显示,冲击引起的应力在CF中的分布区域要明显大于在GF中的分布区域。     

Off-axis notched strength of fiber–metal laminates and a formula for predicting anisotropic size effect

Experimental and theoretical studies of the effects of notch size and fiber orientation on the off-axis notched strength of the fiber–metal laminate GLARE-3 have been conducted. The notched strength decreased with increasing notch size, regardless of the fiber orientation. The notch sensitivity in GLARE-3 was highest in the fiber direction, and it decreased with increasing fiber orientation angle to the lowest in the 45° direction. A new multiaxial criterion for the tensile failure of notched orthotropic fiber composites was developed from a phenomenological point of view. From the proposed multiaxial failure criterion, an anisotropic size effect law for predicting the off-axis notched strength of orthotropic composite laminates was derived. By comparison with the experimental results on GLARE-3, it was demonstrated that the anisotropic size effect law can accurately and efficiently predict the off-axis notched strength of GLARE-3, regardless of the notch size and fiber orientation.     

基于应变能耗散的复合材料层合板面内缺口强度分析CDM模型

基于伴随能量释放的渐进损伤演化思想,建立了复合材料层合板面内失效分析的连续介质损伤力学（CDM）分析模型,该模型包含损伤表征、损伤起始判定和损伤演化法则3个方面。基于CDM模型,通过引入损伤状态变量表征损伤,建立了平面应力状态下的材料损伤本构模型。采用损伤参量 f_E改写Hashin准则,以判定损伤的起始。损伤演化由特征长度内的应变能释放密度控制,建立了损伤状态变量关于等效应变的渐进损伤演化法则。模型中还同时考虑了面内剪切非线性和网格敏感性,并进行了对比分析。对含缺口的[90/0/±45]_3s和[（±θ）₄]_s 2类典型复合材料层合板的面内拉伸失效进行了分析,结果表明,本文中的模型能有效预测复合材料层合板的面内拉伸强度。     

Notched strength of woven fabric composites with moulded-in holes

The feasibility of enhancing damage tolerance and durability of fibre composites through the design of microstructure has been examined using three woven fabric-reinforced composite systems (carbon, Kevlar and carbon-Kevlar in epoxy matrix). Enhancement in notched strength has been demonstrated by comparing the performance of composites with drilled and moulded-in circular holes. Specimens with moulded-in holes exhibited failure strengths which were 2.7–38.3% higher than those of drilled specimens. Furthermore, for certain lay-ups of Kevlar and carbon-Kevlar hybrid laminates, the presence of moulded-in holes did not reduce the unnotched laminate strength; indeed a strength enhancement of 0.4–22.1% was observed. Comparisons of experimental data with existing notched strength theories are made and directions for future research are indicated.     

Scaling effects in notched carbon fibre/epoxy composites loaded in compression

The aim of the work was to develop an understanding of the failure mechanisms controlling the strength of composites of different dimensions and hence to be able to predict size effects in composite structures without resorting to empirical laws. Adequate models do not currently exist, and extensive testing is necessary, which is very costly. The ability to predict the effect of size on strength would be a major step forward, which would reduce costs and encourage the more widespread usage of these materials in the aerospace and other industries. In this article the effects of scaling (specimen size) on the strength of notched laminates are presented. The most important variables have been identified as hole (notch) size, ply and laminate thickness. Manufacturing defects and specimen design can also lead to premature failures, especially in unnotched laminates, but in laminates with an open hole are of less significance, since the notch dominates the fracture. The compressive strength results are compared to data obtained for the same composite system and laminate stacking sequences loaded in uniaxial tension.     

An engineering formula for the stress concentration factor of orthotropic composite plates

An engineering formula for the theoretical stress concentration factor of orthotropic notched plates under tension is provided, as a function of the material elastic constants and the K_t of the corresponding isotropic case. The accuracy and limits of applicability of the new solution are discussed by comparison to data from the literature and results from FE analyses on notched geometries of practical interests. The proposed solution represents a very useful tool to estimate the stress concentration factor of notched orthotropic plates, composite orthotropic laminae, orthotropic unidirectional laminates and homogenised orthotropic composite laminates.