碳纤维增强环氧树脂复合材料与铝板胶螺混合连接接头失效仿真

基于商用有限元软件ABAQUS,建立了碳纤维增强环氧树脂复合材料（CFRP）层合板和铝板双搭接胶螺混合连接接头强度预测模型,并进行了仿真分析,同时与试验结果进行对比,探究了此类混合接头在拉伸载荷工况下的失效形式和承载能力。结果表明,拉伸加载过程中,螺栓通过分担部分载荷加强了胶接连接。混合接头的失效形式先表现为胶层的断裂失效,最终表现为层合板孔边挤压失效。利用模型预测的接头承载能力与试验结果的误差为9.7%,具有较好的吻合性。该分析方法能够为复合材料-金属胶螺混合连接的分析和设计提供一定的参考。      

碳纤维增强树脂基复合材料层合板胶螺混合连接失效机制

为研究碳纤维增强树脂基复合材料(CFRP)层合板单搭接双螺栓胶螺混合连接失效机制,采用基于断裂能断裂准则的连续渐进退化方式,仿真CFRP层合板刚度退化,采用基于能量的B-K准则仿真胶层的损伤演化,建立胶螺混合连接结构渐进损伤三维有限元模型,有限元模型预测的最大失效载荷与实验结果吻合较好。搭接长度L_a为影响胶螺混合接头刚度和强度的重要几何参数,螺栓的位置不会明显影响接头的刚度,粘结面积越大,强度越大。胶螺混合接头在拉伸载荷作用下,由于二次弯曲效应的影响,螺栓向左倾斜,搭接区域的胶层损伤起始于搭接区域胶层外侧,并由外侧向内部扩展到钉孔附近,当胶层损伤扩展到钉孔附近时,螺栓承载增加,胶层和螺栓共同承载,此时CFRP层合板开始出现损伤;最终,左侧钉孔处的上层合板和右侧钉孔处的下层合板产生分层损伤并发生断裂。      

缺陷对单搭胶接接头力学性能的影响

通过单向拉伸试验对比分析了两种接头的破坏模式及载荷-位移曲线, 研究了T700/TDE85复合材料单向层合板单搭接胶层内缺陷对接头破坏行为的影响。试验结果表明, 接头破坏的主导模式为界面破坏, 胶层中微小缺陷对接头强度的影响不大。为研究接头的失效机制, 采用有限元方法对两种接头失效进行数值分析, 模拟了接头搭接区界面剥离应力及剪切应力分布情况, 并分析了缺陷位置变化及面积变化对接头强度的影响。结果表明, 随着缺陷位置距接头搭接区自由端部越近, 接头强度越小, 且缺陷位置距接头搭接区自由端部2.5 mm以内, 缺陷对接头强度影响较大; 接头强度随缺陷面积的增大而减小, 并且缺陷面积占搭接区面积的比率在4.4%以内, 缺陷对接头强度的影响较小; 数值计算结果与实验结果吻合较好。     

搭接长度和铺层方式对CFRP复合材料层合板胶接结构连接性能和损伤行为的影响

针对不同搭接长度和铺层方式的碳纤维增强树脂（CFRP）复合材料层合板单搭胶接结构进行了拉伸试验,观察了试件的受力过程和失效形态,获得了载荷-位移曲线;同时基于连续损伤力学模型和三维Hashin失效准则模拟了CFRP复合材料层合板的层内损伤形成和演化,并利用内聚力模型来模拟层间及胶层的失效损伤,对CFRP复合材料层合板单搭胶接结构在拉伸作用下的失效强度和损伤机制进行了预测,通过对比验证了该数值方法的有效性;通过数值试验比较不同搭接长度和铺层方式的单搭胶接结构及双搭胶接结构的连接强度和损伤行为,并提出了一种优化的CFRP复合材料层合板胶接结构。结果表明:CFRP复合材料层合板胶接结构的极限失效载荷随着搭接长度的增大逐渐增加并趋于稳定值,且结构的失效形式逐渐从胶层自身剪切失效过渡到邻近胶层的层合板层间分层失效;CFRP复合材料层合板胶接结构的连接强度和损伤行为随着铺层方式的不同而改变,通过对3种铺层方式的对比和分析,得到性能最好的铺层方式是[0₃/90₃]_2S;在搭接长度为5~20 mm时,通过对搭接长度进行优化,得到单搭胶接结构的最优搭接长度是17 mm,双搭胶接结构的最优搭接长度是19.3 mm,与搭接长度为20 mm相比,单搭胶接结构和双搭胶接结构的连接强度分别提高了13.26%和0.43%。      

金属-复合材料胶接凹槽形貌增强及参数设计

金属-复合材料混合接头广泛存在于航空、船舶及汽车等领域,具有凹槽形貌的共固化金属-复合材料接头可保持复合材料结构的完整性和纤维的连续性。在被连接金属表面设计了±45°凹槽,评估了表面形貌对钢-玻璃纤维增强树脂复合材料(GFRP)接头胶接性能的影响,设计了单搭接拉伸剪切试验,验证胶接接头的剪切性能;在模拟中引入随机Weibull分布,定义内聚单元材料参数,结合矢量化用户材料(Vectorized user material,VUMAT)子程序模拟了接头的渐进失效过程,并建立±45°凹槽结构的代表性体积单元(Representative volume element,RVE)模型,分析了凹槽宽度和深度等参数对胶接接头的性能影响。研究表明,±45°凹槽结构可以显著提高钢-GFRP胶接接头的剪切强度,数值模拟强度和破坏模式与试验吻合;凹槽深度和宽度对结构胶接性能的影响显著,本文可为金属-复合材料接头的设计提供参考。      

搭接长度对CFRP单搭接胶接接头拉伸性能及破坏特征的影响

采用碳纤维增强复合材料(CFRP)基板制备不同搭接长度的单搭接胶接接头,并利用数字图像相关方法(DIC)、万能电子试验机等测试手段,对胶接接头失效载荷、断裂过程和应变场变化等进行表征,研究搭接长度对单搭接接头拉伸性能、断裂过程、应变分布以及破坏特征的影响.结果表明:随搭接长度增加,接头平均剪切强度先明显降低,后趋于稳定.拉伸过程中由偏心载荷所引起的接头次弯曲效应愈加显著,搭接区域端部变形程度逐渐增大,接头初始破坏位置由搭接区域端部中的一端向两端转变.接头正面和侧面端部的应变集中区域由非对称分布向对称分布过渡.接头受剥离力逐渐增大,层间主要失效形式由剪切向剥离破坏转变,接头破坏模式经历了由界面和轻微纤维撕裂到混合失效再到层间分层的过程.     

搭接区端部细观结构对受拉复合材料单搭接头力学响应的影响

在复合材料单搭接头的加工过程中,在搭接区端部会形成一些细观结构,从而在这些区域常存在比较严重的应力集中。应用实验和有限元方法研究了胶瘤和复合材料端部毛刺这2 种搭接区端部细观结构对受拉复合材料层合板单搭接头力学响应的影响。应用数字图像相关方法测量了搭接区端部的应变场分布情况,同时利用基于子模型技术的非线性有限元方法分析了搭接区端部细观结构的作用。实验结果与有限元分析结果吻合较好。实验和有限元结果都表明胶瘤分担了部分载荷,可以降低搭接区端部的应力集中。复合材料端部毛刺的作用与毛刺的具体结构关系密切,不同结构的毛刺对搭接区端部应力应变分布的影响是不同的。     

胶膜连接碳纤维增强树脂复合材料板-钢搭接接头室温条件的力学性能试验

针对碳纤维增强树脂（CFRP）复合材料板-钢搭接接头连接的糊状胶黏剂粘层厚一致性控制较难、铅垂向成形可能不易等问题,将糊状胶黏剂换成胶膜,制作了胶膜连接的五种粘结长度共15个CFRP板-钢双搭接接头试件,并对该胶膜连接的CFRP板-钢搭接接头进行了室温条件下的破环模式、有效粘结长度、传力规律、粘结-滑移本构、承载力等的试验研究。结果表明:所用胶膜的连接强度略高于CFRP板层间强度（即碳纤维与树脂基体的黏聚强度）;室温下,所用胶膜连接的CFRP板-钢搭接接头有效粘结长度约为80 mm;加载初期,剪应力最大值位于接头钢板端;继续加载,其位置向接头CFRP板端移动;加载末期,其位置位于距接头钢板端20 mm （粘结长度不超过80 mm时）或者50 mm （粘结长度不小于120 mm时）处;胶膜连接的CFRP板-钢搭接接头界面粘结-滑移模型为近似梯形,不同于胶黏剂连接的CFRP板-钢搭接接头的近似三角形,胶膜连接接头的延性大为提升;所用胶膜连接接头界面峰值剪应力、断裂能、界面刚度等代表值（可视为准平均值）分别为四种典型商品胶黏剂连接接头的1.2~3.0倍、1.6~5.7倍和5.4~7.5倍;在粘结长度不小于有效粘结长度条件下,所用胶膜连接接头的抗拉承载力代表值为四种典型商品胶黏剂连接接头的1.25~2.39倍;胶膜连接接头的抗拉承载力、最大位移的变异系数与糊状胶黏剂连接接头相差不大。      

复合材料RTM十字型接头疲劳性能对比实验研究

测试了复合材料RTM十字型接头疲劳性能,分析对比RTM、缝纫RTM和共胶接3种不同成型工艺十字接头的疲劳强度,结果表明:RTM成型十字接头具有良好的疲劳性能,缝纫RTM接头仅为前者的1/4,而先固化后胶接接头最低.研究还发现,复合材料疲劳寿命对成型工艺非常敏感,导致试验结果存在严重分散性.RTM和缝纫RTM的接头破坏都是从根部富树脂区的尖端率先产生裂纹,然后裂纹沿着富树脂区和玻璃布的界面向下扩展,直至接头的整体破坏;先固化后胶接接头则表现为中间层板和T接头的胶层拉伸破坏.     

碳纤维感应元件厚度对碳纤维增强热塑性复合材料感应焊接接头力学性能及断裂形式的影响

利用碳纤维织物与树脂薄膜制备了0.2 mm、0.3 mm与0.5 mm 3种不同厚度的碳纤维感应元件，并开展碳纤维增强热塑性复合材料(Carbon fiber reinforced thermoplastic composite,CFRTP)感应焊接建模仿真与工艺试验。观察CFRTP感应焊接接头成形形貌，开展接头拉伸剪切强度测试与断口形貌分析，着重探究感应元件厚度对接头力学性能与断裂形式的影响。研究结果表明：碳纤维感应元件能在不引入异质材料的前提下实现CFRTP的高质量感应焊接，但接头界面温度分布具有明显的不均匀性；随着感应元件厚度的增加，过量的树脂会降低接头的成形效果、连接质量与力学性能，同时界面的有效连接面积也随之减小；当感应元件厚度为0.2 mm时，焊接接头的拉伸剪切强度最高可达23.77 MPa；焊接接头的断裂形式包括感应元件内聚破坏、母材表层自破坏、界面破坏和混合破坏，造成接头失效的断裂机制根据感应元件厚度的改变而发生变化。     

Fatigue analysis and testing of adhesive joints

The fatigue resistance of a single-lap aluminium adhesive joint to cyclic loading in combined shear and bending mode is investigated by nonlinear finite element analysis and crack propagation experiments. The epoxy adhesive is modelled by an elasto-plastic overlay material model. The initial cycles build up a residual stress state, leading to nearly linear material behaviour in the following cycles. Fatigue crack propagation is modelled by removing adhesive elements. Two series of experiments with one-sided cyclic load were carried out. The crack length was monitored by measuring the bending compliance around the end of the overlap with clip-gauges. The crack length is determined as a simple linear function of the measured compliance. The experiments show nearly constant rate crack growth until failure, with no appreciable crack initiation period. The rate of crack growth is proportional to the stress level to the power m = 6.2. Fatigue life results are given in the form of S---N curves for adhesive thickness of 0.1 and 0.3 mm. There is no systematic influence of the thickness of the adhesive on the fatigue life. This supports the use of a crack propagation and fatigue life criterion formulated in terms of the energy release rate.     

The Effect of Composite Patches on the Failure of Adhesively-Bonded Joints Under Bending Moment

In this study, it was aimed to compare mechanical behavior of double-strap joints with aluminum (AA2024-T3) or 16-ply laminate of carbon/epoxy composite (T300/934) patches of different orientation angles at their overlap area subjected to bending moment. For this purpose, AA2024-T3 aluminum was used as adherend, while the adhesive was a two-part paste (DP 460). Six different types of joint samples were subjected to bending moment. The effect of patch material on failure load and stress distribution was examined experimentally and numerically. In the numerical analysis, the composite patches were assumed to behave linearly elastic, while adherend and adhesive layers were assumed to be nonlinear. It was found that the data obtained from 3-D finite element analysis were coherent with experimental results. Meanwhile, experiments showed that fiber orientation angles of the patches markedly affected the failure load of joints, failure mode and stress distributions appeared in adhesive and composite.     

A study on the strength of adhesively bonded joints with different adherends

In this study, mechanical properties of adhesively bonded single-lap joint (SLJ) geometry with different configurations of lower and upper adherends under tensile loading were investigated experimentally and numerically. The adherends were AA2024-T3 aluminum and carbon/epoxy composite with 16 laminates while, the adhesive was a two-part liquid, structural adhesive DP 460. In experimental studies, four different types of single-lap joints were produced and used namely; composite–composite (Type-I) with lower and upper adherends of the same thicknesses and four different stacking sequences, composite–aluminum (Type-II) with lower and upper adherends of the same thicknesses and four different stacking sequences, composite–aluminum (Type-III) with lower adherend (composite) of the same thickness but upper adherend of three different thicknesses, aluminum–aluminum (Type-IV) with lower adherend of the same thickness but upper adherend of three different thicknesses, composite–composite (Type-V) with [0]₁₆ stacking sequences and three different overlap length, aluminum–aluminum (Type-VI) with three different overlap length. In the numerical analysis, the composite adherends were assumed to behave as linearly elastic materials while the adhesive layer and aluminum adherend were assumed to be nonlinear. The results obtained from experimental and numerical analyses showed that composite adherends with different fiber orientation sequence, different adherend thicknesses and overlap length affected the failure load of the joint and stress distributions in the SLJ.     

Optimum thickness of joints made of GFPR pultruded adherends and polyurethane adhesive

This paper presents results of experimental and numerical investigations on double-lap joints composed of pultruded GFRP profiles and polyurethane adhesive subjected to quasi-static axial tensile loading. The objective was to investigate the effect of the joint geometry on the structural response of adhesively-bonded joints and, in particular, to seek for experimental evidence of an optimum adhesive layer thickness. The influence of the adhesive thickness (0.3–10.0 mm) and the overlap length (50–200 mm) on the joint behavior was investigated. It was found that there is an optimum adhesive thickness of approximately 1.0 mm and joint strength consistently increases with the overlap length.     

碳纤维复合材料假脚工艺参数对其冲击后疲劳性能的影响

基于三维逐渐损伤理论和有限元法,对碳纤维复合材料假脚的冲击及冲击后疲劳破坏过程进行分析,研究了不同的复合材料体系、几何尺寸、纤维铺设方式等工艺参数对碳纤维假脚的冲击损伤及疲劳性能的影响规律。结果表明,在冲击载荷作用下,碳纤维复合材料假脚的损伤模式主要为基体开裂、纤维压缩和分层;复合材料体系的横向和法向拉伸强度以及剪切强度等参数越小,假脚的冲击损伤面积越大,所能承受的疲劳循环次数越低;随着后龙骨厚度的增加,基体开裂损伤面积越来越大,分层损伤面积略有减小,而纤维压缩损伤几乎没有变化。尽管随着后龙骨厚度的增加,假脚的疲劳循环次数逐渐增大,但是相对于厚度的增加量,疲劳循环次数的增加量相对较小;不同铺层参数对碳纤维复合材料假脚的冲击损伤模式几乎没有影响。适度增加0°铺层的含量,可有效提高碳纤维复合材料假脚的疲劳性能。     

Damage mechanisms in composite bonded joints under fatigue loading

In the present paper, the fatigue damage mechanisms in composite bonded joints are analysed and discussed, with particular emphasis on the influence of layer orientation at the adhesive–adherend interface, corner geometry at the end of the overlap area and the stacking sequence. Results indicate that the corner geometry at the end of the bonded area as well as the length of the overlap have a significant influence on the fatigue strength of the joints, while the layer orientation at the adhesive/adherend interface was seen to have a lesser influence on the fatigue performance. The evolution of fatigue damage, consisting in its essential features of crack initiation followed by propagation up to a critical length, is investigated by means of optical and scanning electron microscopy and by monitoring the stiffness of the tested joints. As a result, it is seen that a 45° oriented layer at the adhesive-interface makes crack paths much more complicated with respect to 0° oriented interface joints, with an increase in the crack propagation resistance. Moreover, measurements of the evolution of axial stiffness are promising in order to develop a simplified technique to assess the crack propagation during fatigue life.     

Effect of adhesive thickness on fatigue and fracture of toughened epoxy joints – Part II: Analysis and finite element modeling

The effect of bondline thickness on the fatigue and fracture of aluminum adhesive joints bonded using a rubber-toughened epoxy adhesive was studied using finite element analysis. The fatigue data of Part I examined the dependence of the fatigue threshold and cyclic crack growth rate on the adhesive thickness under both mode-I and mixed-mode loading. The fracture data of Part I illustrated the relation between the adhesive thickness and the quasi-static crack initiation and steady-state critical strain energy release rates. These experimental trends are explained in terms of the effects of the adhesive thickness and the applied strain energy release rate on the stress distribution in the bondline, the stress triaxiality at the crack tip, and the plastic zone size in the adhesive layer.