Surface modification of carbon fiber/epoxy composites with randomly oriented aramid fiber felt for adhesion strength enhancement

To increase the strength of an adhesive joint whose adherend is composed of a carbon fiber/epoxy composite, the surface of the adherend is reinforced with randomly oriented aramid fiber felt before the full cure of the adherend. With this smart cure cycle, the aramid fibers are exposed from the adherend, promoting a bridging effect between the fibers and the adhesive. The cured carbon fiber/epoxy composite material, on which the aramid fiber felt is placed, is co-cure bonded with a smart cure cycle developed in this work. The improvement of the adhesive bonding strength due to the aramid fiber felt is measured with the single-lap shear test of adhesively bonded joints. Additionally, the flexural strength of the carbon fiber/epoxy composite adherend with the co-cure bonded aramid fiber felt is measured.     

服役低温老化对铝合金-玄武岩纤维增强树脂复合材料粘接接头力学性能的影响及失效预测

为了给铝合金-玄武岩纤维增强树脂(BFRP)复合材料粘接结构在汽车工业中的应用提供参考和指导,加工了铝合金-BFRP复合材料粘接接头。结合汽车服役中的温度区间,选取?10℃和?40℃的低温老化环境,对接头进行0、10、20、30天的老化。对老化后的粘接接头进行准静态拉伸试验和剪切试验,得到不同老化时间下铝合金-BFRP粘接接头的准静态失效强度。结合DSC和FTIR分析低温老化对BFRP复合材料的影响,并对粘接接头的失效断面进行宏观分析和SEM分析。结果表明:在低温老化环境中,胶粘剂与BFRP复合材料的化学性质受低温老化作用影响不大,BFRP中的官能团与玻璃化转变温度(T_g)没有发生明显的变化,接头的失效强度和失效模式主要受胶粘剂与粘接基材的热应力影响。对于拉伸接头,随着低温老化时间的增加,BFRP复合材料纤维与树脂基体间的结合力降低,铝合金-BFRP复合材料接头的失效断面中纤维撕裂的比例逐渐减少,拉伸接头失效强度逐渐下降。老化后剪切接头仍为内聚失效,BFRP复合材料的低温老化对铝合金-BFRP复合材料剪切接头的失效强度几乎没有影响,剪切接头失效强度的下降主要是胶粘剂与粘接基材热膨胀系数不一致引起的热应力的影响。采用二次应力准则公式对?10℃和?40℃低温环境下,拉应力、剪应力值随老化时间的变化规律进行了拟合,在此失效准则的基础上,根据响应面原理,建立接头失效强度随老化时间变化的三维曲面,为粘接技术在车身结构中的工程应用提供参考。      

粘接剂对1420铝锂合金压印接头疲劳性能的影响

压印连接以高效率、低能耗的优点在薄板材料连接中被广泛应用,但其连接强度相对较低,鉴于此,压印-粘接复合连接应运而生。本文以1420铝锂合金为原材料,制备了1420同种材料组合的压印接头及压印-粘接复合接头并进行对比。通过拉-剪静态力学试验测定两种接头的静力学强度及承载能力,通过拉-拉动态疲劳试验测定两种接头的动态疲劳性能,采用三参数法拟合疲劳寿命曲线,并对疲劳失效断口进行分析。结果表明:压-粘接头的静强度比压印接头提高了108.17%,接头承载能力提高169.63%。在短寿命区,两种接头均为颈部断裂失效;在中长疲劳寿命区,压-粘接头的疲劳寿命优于压印接头,压-粘接头疲劳断裂位置为压印点,压印接头疲劳断裂位置为下板。对疲劳断口进行SEM分析,发现两组疲劳断口均呈现韧性断裂与脆性断裂同时出现的特征。     

A comparison of engineered cementitious composites versus normal concrete in beam-column joints under reversed cyclic loading

Engineered cementitious composites (ECC) are a class of high-performance fiber reinforced cementitious composite with strain hardening and multiple cracking properties. For a reinforced concrete member, substitution of conventional concrete with ECC can significantly improve the deformation characteristics in terms of reinforced composite tensile or shear strength and energy dissipation ability. In this paper, a number of RC/ECC composite beam-column joints have been tested under reversed cyclic loading to study the effect of substitution of concrete with ECC in the joint zone on the seismic behaviors of composite members. The experimental parameters include shear reinforcement ratio in the joint zone, axial load level on the column and substitution of concrete with ECC or not. According to the test results, for the specimens without shear reinforcement in the joint zone, substitution of concrete with ECC in the joint zone cannot change the brittle shear failure in the joint zone, but can significantly increase the load capacity and ductility of the beam-column joint specimens, as well as the energy dissipation ability due to high ductility and shear strength of ECC material. For the specimens with insufficient or proper shear reinforcement ratio, substitution of concrete with ECC in the joint zone can lead to failure mode change from brittle shear failure in the joint zone to a more ductile failure mode, i.e. flexural failure at the base of the beam, with increased load capacity, ductility and energy dissipation ability. Increase of axial load on column and shear reinforcement in the joint zone have little effect on seismic behaviors of the members when they failed by flexural failure at the base of beam. In a word, the substitution of concrete with ECC in the joint zone was experimentally proved to be an effective method to increase the seismic resistance of beam-column joint specimens.     

Co-cured in-line joints for natural fibre composites

Little attention has been paid to joining unidirectionally-reinforced high strength natural fibre composites in the manufacture of engineered structures. Therefore the main objective of the paper is to investigate the effect of joint geometry on the strength of natural fibre composite joints. Epoxy-bonded single lap shear joints (SLJs) between henequen and sisal fibre composite elements were manufactured and tested in tension to assess the shear strength of the structural bonds. The performance of co-cured joints, termed “intermingled fibre joints” (IFJs) and “laminated fibre joints” (LFJs) was also evaluated. These IFJ and LFJ configurations possess much higher lap shear strengths than the single lap shear joints and the failure modes of the three joint configurations are compared. SLJ and LFJ joints have been modelled using finite element analysis, allowing interpretation of the experimental observations.     

复合材料中厚板沉头连接结构强度与损伤失效

针对复合材料沉头螺栓连接结构的强度与损伤问题,开展了两种厚度复合材料层合板凸头与沉头螺栓连接结构挤压强度对比试验研究。试验结果表明,增加层合板厚度会引起连接结构挤压强度下降,但沉头连接结构下降比例小于凸头连接结构。通过数值模拟方法对复合材料中厚板沉头连接结构的强度及损伤失效进行分析。提出一种非线性面内连续损伤与三维混合失效模型,模型考虑了复合材料基体剪切非线性特征并改进了纤维损伤失效判据,有效解决了数值模拟中沉头复合材料连接结构难于收敛的问题。对比分析表明:沉头连接结构的数值计算结果与试验结果吻合良好,极限强度最大计算误差8.62%。     

Development of a strength model for the cocured stepped lap joints under tensile loading

The cocured stepped lap joints for composite structures were manufactured and tested under static and fatigue tensile loads. From the tests, it was found that the joints were shear-failed at the joining interfaces. As the length of the stepped lap of the joint increased, the average static tensile strength of the joint increased, while the average static shear strength decreased in proportion to the length of the stepped lap of the joint. The fatigue endurance limit was found to be 30–40% of the static strength.

Also, the cocured stepped lap joints were manufactured by curing plies laid-up on the composite plates which had machined stepped laps. The static strength of the joints manufactured by the latter method was found to be 70–80% of the static strength of the joints manufactured without machining and the fatigue endurance limit was found to be about 25% of the static strength.     

高强箍筋高强混凝土梁柱节点抗震性能试验研究

为研究高混凝土梁柱节点的抗震性能,进行了4个高强箍筋混凝土节点和1个普通箍筋混凝土节点的低周往复荷载加载试验,研究了高强混凝土节点的破坏形态、滞回特性、耗能能力、受剪性能及箍筋的应力水平,分析了箍筋强度、体积配箍率和箍筋形式对节点承载力、延性、耗能和剪切变形的影响。结果表明：高强箍筋节点的破坏过程与普通箍筋节点类似;提高箍筋屈服强度对节点的承载力提高效果有限,但可有效提高位移延性和耗能能力,同时限制了节点核心区的剪切变形;试件达到极限位移时,普通箍筋试件箍筋已屈服,复合高强箍筋试件箍筋强度发挥比较充分,表现出较好的抗震性能。     

局部采用纤维增强混凝土梁柱节点抗震性能试验研究

为了提高梁柱节点受剪承载力、变形能力及耗能能力,同时避免节点钢筋拥挤而导致的施工困难,采用纤维增强混凝土(FRC)代替普通混凝土作为节点核心区基体材料,考虑轴压比和节点核心区配箍率的影响,进行了7个FRC梁柱节点和1个钢筋混凝土(RC)梁柱节点对比试件的拟静力试验,分析其破坏形态、承载力、变形能力、耗能能力、节点核心区剪应力-剪应变曲线和梁端塑性铰区弯矩-转角曲线。结果表明,在节点核心区主斜裂缝出现前,试件已具有很高的受剪承载力和变形能力;当轴压比试验值为0.07~0.28时,随着轴压比增大,FRC试件的受剪承载力、侧向变形能力、耗能能力及节点核心区的剪切强度和剪切变形能力增加;增加节点核心区配箍率,承载力退化有所减缓;FRC试件梁端塑性铰转动能力有较大提高。     

PEC柱-异形钢梁框架中节点抗震性能试验研究

为研究PEC柱（partially encased concrete composite column）-型钢梁框架中节点破坏特征及抗震性能,完成了3个PEC柱-型钢梁中节点及1个钢框架梁柱中节点对比试件的低周往复加载试验。分析了试件中节点的破坏形态、滞回耗能、承载能力、延性性能、强度退化、刚度退化、节点域力学机理,研究了轴压比及梁截面变化对该类中节点抗震性能的影响。研究结果表明：PEC柱-型钢梁中节点滞回曲线呈纺锤形,具有钢框架节点的力学特性;型钢柱内部填充混凝土后试件初始刚度、承载力分别提升约40%、31.1%,且试件仍具有较好的延性性能及耗能能力;当轴压比试验值为0.25~0.35时,随着轴压比增加,试件承载力显著增加,延性性能有所下降,耗能能力则有所提升;试件均为梁弯曲破坏,损伤程度无明显变化。改变柱一侧梁的截面尺寸后,试件的承载能力、延性性能有一定提升,耗能能力、强度及刚度退化规律无明显影响,但PEC柱-变截面型钢梁中节点发生节点核心区剪切破坏,主要原因为改变柱一侧梁截面高度后,造成节点域输入剪力增大所致。按常规节点设计的变截面梁中节点不能满足\     

复合材料单搭接头的剪切强度对比实验研究

在常温和湿热高温的环境下,分别进行了三种不同的成碰工艺(RTM、引入缝纫的RTM和胶接)制备的单搭接头的剪切强度实验,研究了成型工艺对单搭接头的剪切强度的影响,并根据实验现象分析了单搭接头的剪切破坏机理.实验结果表明:引入缝纫的RTM成型试样的剪切强度性能最高,而胶接成型试样的剪切强度最低;环境温度对RTM和引入缝纫RTM成型试样的剪切强度影响不大,而对胶接成型试样的剪切强度有较大影响.     

Integral Manufacturing of Composite Skin-Stringer Assembly and Their Stability Analyses

Stiffened composite constructions are increasingly being used in the primary structures of aircraft. One key component in these structures is the assembly between the skin and the stringer. The purpose of the stringers sandwiched between two separate layers of skin is to provide structural integrity to a relatively weak skin-structure. Current practice is to fabricate the skin and the stringer separately, assemble them with adhesively bonded joints, and then co-cure the entire assembly in an autoclave. However, the reliability of the joint manufactured in this fashion is not dependable and hence requires riveting of the skin with the stringer by hundreds of mechanical fasteners. Although the mechanical fastener improves the joint reliability, it certainly increases the weight and reduces the strength of the structure by introducing stress concentration points around the rivet holes. In order to eliminate these disadvantages, an innovative low cost manufacturing technique has been developed. The technique utilizes the vacuum assisted resin transfer molding (VARTM) process to co-inject both the skin and the stringer in one integral step. Furthermore, the skin and the stringer are now part of one continuous fabric preform which by default eliminates any adhesive bonding. Several skin-stringer assemblies with plain weave carbon fabric and SC-15 epoxy resin have been manufactured following this procedure. Stability of the manufactured skin-stringer assembly has been investigated experimentally. The extensive analysis focused on the determination of the critical load corresponding to the instability of the structure, failure load and study of the failure mechanisms. Details of manufacturing procedures and experimental investigations are presented in the paper.     

Static and high-rate loading of single and multi-bolt carbon–epoxy aircraft fuselage joints

Single-lap shear behaviour of carbon–epoxy composite bolted aircraft fuselage joints at quasi-static and dynamic (5 m/s and 10 m/s) loading speeds is studied experimentally. Single and multi-bolt joints with countersunk fasteners were tested. The initial joint failure mode was bearing, while final failure was either due to fastener pull-through or fastener fracture at a thread. Much less hole bearing damage, and hence energy absorption, occurred when the fastener(s) fractured at a thread, which occurred most frequently in thick joints and in quasi-static tests. Fastener failure thus requires special consideration in designing crashworthy fastened composite structures; if it can be delayed, energy absorption is greater. A correlation between energy absorption in multi-bolt and single-bolt joint tests indicates potential to downsize future test programmes. Tapering a thin fuselage panel layup to a thicker layup at the countersunk hole proved highly effective in achieving satisfactory joint strength and energy absorption.     

服役温度对铝合金-碳纤维增强树脂复合材料粘接接头准静态失效的影响

为了研究服役温度对铝合金-碳纤维增强树脂(CFRP)复合材料粘接接头准静态失效的影响，本文加工了铝合金-CFRP复合材料粘接接头。考虑车辆实际运行工况下的服役温度，选取低温(?40℃)、常温(20℃)和高温(80℃)三种环境温度，结合设计的Arcan夹具对铝合金-CFRP复合材料粘接接头分别进行1 mm/min和100 mm/min的准静态试验，得到不同温度下铝合金-CFRP复合材料对接接头(BJs)、45°嵌接接头(45°SJs)和剪切接头(TSJs)的准静态失效强度，并结合失效断面对接头失效形式进行分析，建立了失效准则方程和三维响应曲面。结果表明:不同加载速率下的铝合金-CFRP复合材料粘接接头失效强度在高温环境下均呈明显的下降趋势，在低温环境下均呈一定程度的上升趋势。高温下的失效模式为胶层的内聚失效，低温下的失效模式中纤维撕裂的比例上升。相对于1 mm/min加载速率下的准静态失效强度，各温度和应力状态下的铝合金-CFRP复合材料粘接接头在100 mm/min加载速率下的准静态失效强度明显提高。      

交变载荷对CFRP复合材料-铝合金粘接接头剩余强度的影响

为了给碳纤维增强聚合物（CFRP）复合材料粘接结构的安全设计及应用提供参考,针对CFRP复合材料-铝合金对接接头,研究了拉-拉交变载荷作用下的疲劳寿命特性及剩余强度变化规律。设计专用夹具,完成接头的制作及固化,并测试其拉伸、剪切准静态失效强度,在此基础上进行不同载荷水平下的疲劳寿命测试。选取特定载荷水平,测试不同循环次数后的接头剩余强度,并对失效形式进行观察分析。结果表明:CFRP复合材料-铝合金对接接头强度-寿命（S-N）曲线在单对数坐标上符合线性函数规律;随着交变载荷循环周期的增加,接头剩余强度呈先慢后快的下降趋势,而且在较大的载荷水平下,下降幅度更为明显;经历交变载荷循环前、后接头失效形式发生改变,由局部CFRP复合材料表层撕裂转变为局部界面破坏。结合试验测试所获得的初始失效准则,并引入疲劳退化因子,建立内聚力模型对交变载荷作用下的粘接接头强度衰减进行数值模拟,结果表明所建立模型能够有效预测交变载荷作用下的接头剩余强度。      

Experimental and numerical investigation of the influence of imperfect bonding on the strength of NCF double-lap shear joints

The influence of imperfect bonding, owing to partial lack of adhesive, on the strength of composite non-crimp fabric (NCF) double-lap shear (DLS) joints was experimentally and numerically investigated. Fabrics were layered and compacted using a thermoplastic veil while infiltration of the preforms was done using the vacuum assisted process. Paste adhesive bonding was carried out by implementing the novel insertion squeeze flow process. Quality of adhesive bonding was tested using X-ray imaging and ultrasonic C-scan inspection. The tensile lap shear strength of the DLS joints was determined experimentally. Digital macrographs revealed that the specimens failed due to shear failure of the adhesive (debonding) and fracture of the composite boundary layer. As a second approach, a mesomechanical model based on the FE method and the (homogenized) progressive failure analysis method was developed. In the model, the areas without adhesion, as detected by the C-scans, were included. Numerical simulations of failure initiation and progression at the NCF joint and the adhesive indicated that it is possible to predict the strength and failure mechanisms of the imperfect bonded DLS joints.     

A novel predictive model for mechanical behavior of single-lap GFRP composite bolted joint under static and dynamic loading

Mechanical connection of composite is critical due to its complicated meso-structure and failure mode, which has become a bottleneck on reliability of composite material and structure. Although many researches on composite bolted joints have been carried out, the theory and experiment on mechanical behavior of such a joint structure under dynamic loading were rarely reported. Here, we propose a novel predictive model for quasi-static and dynamic stiffness of composite bolted joint by introducing the strain rate dependent elastic modulus into the mass spring model. Combined with the composite laminate theory and Tsai-Hill theory, the present model was capable of predicting the strain rate dependent stiffness and strength of the composite bolted joint. Quasi-static and impact loading experiments were carried out by Zwick universal hydraulic testing machine and split Hopkinson tension bar, respectively. The stiffness and strength predicted by our model showed good accordance with the experiment data with errors below 12% under quasi-static loading and below 30% under impact loading. The results indicated that under impact loading, stiffness and strength of the composite bolted joint were significantly higher than their quasi-static counterparts, while the failure mode of the joint structure trended towards localization which was mainly bearing failure. Among various lay-up ratios studied, the optimal lay-up ratio for quasi-static and dynamic stiffness was 0:±45:90 = 3:1:1.     

Strength and damage tolerance of composite–composite joints with steel and titanium through the thickness reinforcements

Today’s aeronautic, automotive and marine industry is in demand of structurally efficient, low weight alternatives for composite–composite joints which combine the advantages of low weight input of adhesively bonded joints and high damage tolerance of through the thickness bolted joints. In the present work, composite–composite joints are reinforced through the thickness by thin metal inserts carrying cold metal transfer welded pins (CMT pins). The influence of pin alignment and type of pin on the damage tolerance of single lap shear (SLS) composite–composite joints is investigated. The use of titanium reinforcements is evaluated and compared to stainless steel reinforced, adhesively bonded and co-cured specimens. A detailed analysis of the stress–strain behavior is given and the stiffness and energy absorption of the SLS joints during tensile loading is assessed. The results show that joints reinforced with CMT pins absorb significantly higher amounts of energy, when compared to adhesively bonded and co-cured joints.     

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。      

制造公差对复合材料螺栓连接结构强度分散性的影响

为解决由于螺栓和复合材料板制孔制造过程中不可避免的制造公差引起的配合间隙的不同,而使复合材料螺栓连接钉载分配不同,从而导致螺栓连接强度分散性的问题,以英制高锁螺栓和孔板制孔的制造公差为例,研究不同配合间隙下双剪四钉螺栓连接钉载分配情况,并进一步采用改进的特征曲线法、改进的强度包线法和渐进损伤模型对螺栓连接结构的强度进行预测,得到四钉连接失效强度的分散区间分别为[-3.87%,2.16%]、[-4.01%,3.95%]和[-3.16%,5.14%]。结果说明如果紧固件及螺栓孔均符合制造标准,则其对强度的影响范围不超过6%。