Impact fatigue properties of epoxy resin filled with SiO2 particles

Impact fatigue tests were carried out on epoxy resin filled with SiO₂ particles. The effects of the percentage of SiO₂ particles and the impact cyclic loading frequency on the impact fatigue strength was investigated. The micromechanism of impact fatigue failure was examined and correlated with the morphology of the fracture surface. The impact stress amplitude, σ_t, can be estimated by the formula, σ₂(N_f · Te)^mt = D_t where (N_f· Te) is the cumulative duration time, and mt and D_t, are parameters describing impact fatigue characteristics. The impact fatigue strength and the static strength are governed by the percent of SiO₂ particles. Crack initiation under monotonie cyclic impact loading was attributed to decision of the epoxy-SiO₂ interface. Unstable crack propagation occurs when the crack passes through the SiO₂ particles.     

Failure of delaminated carbon/epoxy composite beams under cyclic compression

Experimental study of the response of laminated [(45/90/ — 45/0)₆]_s carbon/ epoxy virgin and pre-cracked composite beams to compressive cyclic loading is reported. The development of failure, in the form of delaminations, recorded continuously on video tape during the tests, revealed formation of delaminations close to the external faces of the beam. Some of the delaminations developed instantly and some propagated along the beam in jumps. Total failure occurred when the stress in the central ‘undamaged’ section of the beam reached a critical value. Calculation of the buckling load of unsymmetric laminated beams supports the experimental finding that a pre-crack close to the center of the specimen has no effect on the fatigue behavior of the beam. Prediction of time to first delamination crack, based on previous results, agree with the present experimental observation.     

Effect of the shear and coupling elements of the Aij and Dij matrices on the impact behavior of glass, aramid and hybrid fabric composites

The impact behavior of glass, aramid and glass–aramid hybrid fabric epoxy matrix composites was evaluated. Delamination was identified as the main macroscopic failure mode of the composites. A simple relationship based on the macromechanical behavior of laminated composites was established, relating coupling—A₂₆, D₂₆—and shear—A₁₆, D₁₆—elements of the extensional and bending stiffness matrices to the total energy absorbed at impact. The results obtained show that the A₆₆/D₆₆ ratio is a relevant parameter of concern, correlated with the behavior of the composites under impact. Additionally, the coupling matrix B_ij was shown to restrain the macroscopic delamination of the composites.     

Fracture behavior of cross-ply graphite/ epoxy laminates

Fracture behavior of cross-ply (0/90)_4s, (0/90)_10s, (0₂/90₂)_2s and (0₄/90₈/0₄)_T laminates of T300/934 graphite/epoxy material was studied using compact tension specimens of several widths and thicknesses, center notched tension and three point bend specimens. The process of damage initiation and propagation was studied and is discussed in detail. The critical stress intensity factor was evaluated and its variation with specimen size and type is shown. On the basis of these investigations, a suitable specimen for the evaluation of meaningful fracture toughness is suggested.     

A damping analysis of composite laminates using the closed form expression for the basic damping of Poisson's ratio

Various methods have been presented to obtain the effective damping of a symmetric laminated composite. In this paper, modified classical lamination theory based upon the elastic–viscoelastic correspondence principle was utilized by developing the basic damping of Poisson's ratio for accurately predicting the damping of laminated composite beams. The analysis involves an extension of the elastic–viscoelastic approach. Futhermore, Ni and Adams' theory was used for verifying the modified classical lamination theory. Six typical laminated composites with [±θ]_s,[0/θ]_s,[0/±θ/90]_s,[90/±θ/0]_s,[0/90/±θ]_s and [90/0/±θ]_s, stacking sequences were employed for this study. Numerical results have shown that damping values were in some difference among prediction methods over the particular range of fiber orientation.     

The relation between compressive strength of carbon/epoxy fabrics and micro-tow geometry with various bias angles

In this paper compressive tests of carbon/epoxy (plain weave, 3k) fabric composites were performed to investigate the relation between compressive strength and various bias angles and shear angles. Compressive properties such as chord modulus and maximum strength of the fabric composite materials are essential to analyze the drape behaviour and estimate the quality of the final products. Various specimens with different bias and shear angles which were fabricated by using autoclave de-gassing moulding process were prepared to estimate the strength and chord modulus with respect to the bias and shear angle variations. The stacking sequences of the compressive test specimens are [0]_10T, [15]_10T, [30]_10T and [45]_10T for bias specimens and [±37]_10T, [±32]_10T, [±28]_10T, [±22]_10T for sheared specimens. Micro-tow structures were observed to correlate the fabric compressive strength with crimp angle. Anti-buckling rig was involved to prevent specimens from buckling during the compressive tests. The compressive test was performed with 1.3 mm/min strain rates. Compressive test results were compared with calculation results. Facture modes which were classified in two different modes were analyzed using microscopic observation.     

Damage detection of surface cracks in composite laminates using modal analysis and strain energy method

This paper presents an approach to detect surface cracks in various composite laminates. Carbon/epoxy composite AS4/PEEK was used to fabricate laminated plates, [0]₁₆, [90]₁₆, [(0/90)₄]_S and [±45/0/90]_2S. Surface crack damage was created on one side of the plate using a laser cutting machine. Modal analysis was performed to obtain the mode shapes from both experimental and finite element analysis results. The mode shapes were then used to calculate strain energy using the differential quadrature method (DQM). Consequently, the strain energies of laminated plates before and after damaged were used to define a damage index which successfully identified the surface crack location.     

A study on interlaminar behavior of carbon/epoxy laminated curved beams by use of acoustic emission

Abstract

The interlaminar tensile strength of carbon/epoxy laminated curved beams with variable thickness and through-the-thickness tufted reinforcement is studied experimentally by means of a four-point-bending test in accordance with ASTM D6415. These tests are monitored by the acoustic emission (AE) technique in order to gain deeper knowledge of the delamination onset and post-failure behavior. The results show that AE technique has proven to perform well when identifying delamination onset and its evolution after failure. In addition to this, AE has demonstrated to be an appropriate tool to assess the manufacturing quality of the carbon/epoxy laminated curved-beam, once the right pattern has previously been established.     

Strength of carbon/epoxy laminates with countersunk hole

The aim of this study is to predict the static strength of carbon/epoxy laminates with countersunk hole. Also, three-point bend (TPB) specimens with the same lay-up were analysed. For this purpose, the notched strength of the laminates was analysed by a damage zone model (DZM), where damage around the notch is represented by an ‘equivalent crack’ with cohesive forces acting between the crack surfaces. The DZM requiring only basic properties of the laminate such as unnotched tensile strength, δ₀, fracture energy, G_c^*, and stiffnesses of the laminate. However, the complex geometry around the countersunk hole implies that both δ₀ and G_c^* will vary in this area, and in order to avoid this problem an approximate geometry of the countersunk hole is used in the DZM-calculations. With this approximation, good agreement between experimental and calculated strength was observed for the laminates with countersunk hole. This was also the case for the TPB specimens.     

Modelling of damage and failure of glass/epoxy composite plates subject to impact fatigue

An investigation has been carried out to study the impact fatigue damage of glass/epoxy laminated composites. Accumulation of damage, such as matrix cracking, delamination and fibre breakage, with repeated impact of the composite material may reduce the overall stiffness. These damage modes have been combined in a very complicated way to describe damage growth and fracture. A model is proposed for characterising the damage as a function of the normalised impact number. The scalar variable D, which characterises the material damage, is written as a function of the life duration β, using a modified form of the Mankowsky empirical law [Int J Solids Struct 32(11) (1995) 1607]. The macroscopic failure mode and the internal damage in laminated specimens of glass/epoxy as a consequence of impact fatigue are analysed at different levels of incident impact energy. The impact fatigue tests have been conducted on an apparatus built in our laboratory.     

单分散无溶剂纳米SiO2流体对环氧树脂的改性

以纳米粒子SiO₂为核、表面活性剂N,N-十二基-N-甲基-N-(3-三甲氧基甲硅烷基丙基)氯化铵(SID3392)为颈状层、聚(乙二醇)4-壬基苯基醚3-磺丙基钾盐(PEGS)为冠状层,制备出了无溶剂纳米SiO₂流体。无溶剂纳米SiO₂流体为牛顿流体,在室温下具有较低的黏度,在26.5 ℃时其黏度为4.3 Pa·s,无溶剂纳米SiO₂流体中SiO₂的含量为13.65wt%。将该无溶剂纳米SiO₂流体加入环氧树脂中,制备了无溶剂纳米SiO₂流体/环氧树脂复合材料。TEM结果表明: 无溶剂纳米SiO₂流体在环氧树脂基体中具有良好的分散性。DSC测试表明: 无溶剂纳米SiO₂流体的加入会略微降低环氧树脂的固化温度。当纳米SiO₂流体加入量为2.5wt%时,复合材料的冲击性能提高了164.7%,玻璃化温度提高了15.4 ℃。断面SEM结果显示无溶剂纳米SiO₂流体能够提高环氧树脂的韧性。     

单螺栓修复对含冲击损伤碳纤维/环氧树脂复合材料层合板压缩承载能力的影响

开展了单钉修复对含冲击损伤碳纤维/环氧树脂复合材料层合板压缩承载能力影响的试验研究。测试了三种不同能量冲击后碳纤维/环氧树脂复合材料层合板的压缩承载能力及失效模式,测定了单螺栓对碳纤维/环氧树脂复合材料层合板压缩承载能力的修复效率,并借助数字图像相关技术(DIC)表征手段揭示了单螺栓修复对含冲击损伤结构失效行为的影响。结果表明:冲击后碳纤维/环氧树脂复合材料层合板的压缩承载能力随着冲击能量的增加而降低,冲击损伤破坏了碳纤维/环氧树脂复合材料层合板结构的对称性,并导致结构在加载初期呈非对称的局部屈曲变形特征,局部屈曲诱发并加剧分层损伤扩展;单螺栓修复能有效恢复结构的整体对称性,在一定程度上抑制含冲击损伤碳纤维/环氧树脂复合材料层合板的局部屈曲,达到可观的修复效率。该研究为复合材料紧固件修理方案的制订及修理损伤容限的定义提供一定的指导意义。      

Pull-out steel fasteners from a laminated composite subjected to external pressure

Single steel fasteners of circular cross-section have been pulled out of predrilled laminated glass/epoxy composite cylinders located in a pressure cell in which external pressures of up to 56 MPa were applied. An analysis is presented which relates the external pressure, p_o, to the interfacial pressure, p_i, in terms of the elastic properties of the fastener and the composite and the radial clearance between them in the absence of an external pressure. The value of the coefficient of static friction, μ = 0·1, calculated from these experiments suggests that the observed axial pull-out forces of 2·5 kN for similar fasteners fired directly into the composite material, cannot be accounted for solely in terms of interfacial friction. Some evidence is presented which suggests that plastic deformation of the fastener surface into interstices within the surrounding material during impact penetration contributes to the initial resistance to pull-out.     

MWCNTs对环氧树脂及多尺度MWCNTs-碳纤维/环氧树脂复合材料力学性能的影响

通过对胺基化多壁碳纳米管（MWCNTs-NH₂）进行改性,得到改性MWCNTs悬浮液（MWCNTs-NH₂（M））。分别将羧基化MWCNTs （MWCNTs-COOH）和MWCNTs-NH₂（M）分散在环氧树脂（EP）中,采用热熔法制备了多尺度MWCNTs-碳纤维（CF）/EP复合材料。研究了MWCNTs对EP模量、韧性及EP与CF之间界面黏结强度的影响,并分析了MWCNTs与CF上浆剂的作用,评价了多尺度MWCNTs-CF/EP复合材料的力学性能。结果表明：官能团化的MWCNTs可对EP的模量和韧性起到更好的增强作用。MWCNTs接枝的-COOH或-NH₂可与CF上浆剂中的环氧基团发生化学反应,提高EP与CF之间的界面剪切强度。MWCNTs-NH₂（M）对多尺度MWCNTs-CF/EP复合材料力学性能的增强效果优于MWCNTs-COOH,当MWCNTs-NH₂（M）的含量为1wt%时,多尺度复合材料的0°压缩强度、90°压缩强度、弯曲强度、弯曲模量、冲击后压缩强度（CAI）分别提高了16.7%、16.3%、40.9%、30.3%、20.6%。     

Polyamide coating on carbon fibres and potential application in carbon/kevlar/epoxy hybrid composites

Hybrid unidirectional composite materials, consisting of alternately laminated layers of Kevlar-49 fibres and carbon fibres in an epoxy resin, have been studied. Before embedding, the carbon fibres were coated with a Nylon 6,6 film by an interfacial in-situ polymerization technique. Emphasis is given to the mechanical properties of the hybrid composites based on coated carbon, with those based on uncoated carbon, for various values of partial volume fraction of the carbon fibres, V_cf, polyamide content deposited on the carbon fibres, C_N, and total fibre (Kevlar + carbon) volume fraction, V_f.     

PEK-C膜层间增韧碳纤维/环氧树脂复合材料的力学性能

为探究热塑性酚酞基聚醚酮（Polyaryletherketone with Cardo,PEK-C）树脂薄膜及膜厚对层间增韧碳纤维/环氧树脂复合材料力学性能的影响,利用浸渍提拉法制备了三种不同厚度（分别约为1 μm、10 μm、30 μm）的PEK-C膜,通过热压成型制备了层间增韧碳纤维/环氧树脂复合材料层合板,对其进行了Ⅰ型层间断裂韧性、冲击后压缩强度、层间剪切及弯曲性能测试,并利用SEM观察微观形貌及AFM扫描微观相图。结果表明:不同PEK-C膜厚增韧碳纤维/环氧树脂复合材料的Ⅰ型层间断裂韧性、冲击后压缩强度及层间剪切强度有不同程度提高,Ⅰ型层间断裂韧性及层间剪切强度以膜厚为10 μm最佳,分别增大了157.17%和17.57%,冲击后压缩强度以膜厚为30 μm最佳,达到了186.67 MPa,这是由于PEK-C与环氧树脂在热压固化过程中形成了双相结构,改善了材料韧性;但弯曲性能持续下降,强度及模量由未增韧的1 551 MPa、106 GPa分别降至30 μm时的965 MPa、79 GPa,这是由于PEK-C树脂扩散进入环氧树脂中,降低了纤维体积分数及材料刚度。      

Enhancement of mechanical performance of epoxy/carbon fiber laminate composites using single-walled carbon nanotubes

Carbon nanotubes (CNT) in their various forms have great potential for use in the development of multifunctional multiscale laminated composites due to their unique geometry and properties. Recent advancements in the development of CNT hierarchical composites have mostly focused on multi-walled carbon nanotubes (MWCNT). In this work, single-walled carbon nanotubes (SWCNT) were used to develop nano-modified carbon fiber/epoxy laminates. A functionalization technique based on reduced SWCNT was employed to improve dispersion and epoxy resin-nanotube interaction. A commercial prepregging unit was then used to impregnate unidirectional carbon fiber tape with a modified epoxy system containing 0.1 wt% functionalized SWCNT. Impact and compression-after-impact (CAI) tests, Mode I interlaminar fracture toughness and Mode II interlaminar fracture toughness tests were performed on laminates with and without SWCNT. It was found that incorporation of 0.1 wt% of SWCNT resulted in a 5% reduction of the area of impact damage, a 3.5% increase in CAI strength, a 13% increase in Mode I fracture toughness, and 28% increase in Mode II interlaminar fracture toughness. A comparison between the results of this work and literature results on MWCNT-modified laminated composites suggests that SWCNT, at similar loadings, are more effective in enhancing the mechanical performance of traditional laminated composites.     

The effects of geometric parameters on the failure strength for pin-loaded multi-directional fiber-glass reinforced epoxy laminate

A numerical and experimental study was carried out to determine the failure of mechanically fastened fiber-reinforced laminated composite joints. E/glass–epoxy composites were manufactured to fabricate the specimens. Mechanical properties and strengths of the composite were obtained experimentally. Tests have been carried out on single pinned joints in [0/90/0]_s and [90/0/90]_s laminated composites. A parametric study considering geometries was performed to identify the failure characteristics of the pin-loaded laminated composite. Data obtained from pin-loaded laminate tests were compared with the ones calculated from a finite element model (PDNLPIN computer code). Damage accumulations in the laminates were evaluated by using Hashin's failure criteria combined with the proposed property degradation model. Based on the results, ply orientation and geometries of composites could be crucial for pinned laminated composite joints.     

Impact damage response of natural stitched single lap-joint in composite structures

In this paper the damage behaviour of natural stitched composite single lap-joints are investigated under low velocity impact loading conditions. For this study, the laminated hybrid composite beams were pinned using Flax yarns before curing process. The Charpy impact test was chosen to study the energy absorbing capability of single lap composite joints. Composite beams were fabricated from combination of glass/epoxy and carbon/epoxy composites. It was shown that composite beams which are stitched through the thickness are able to absorb more energy in comparison with adhesive bonded composite joints in the hybrid composite beams. The Charpy impact test of stitched composite single lap joint was also simulated by finite element analysis using software LS-DYNA and the results verified with relevant experimental data.     

一种多功能有机蒙脱土-纳米TiO2/环氧树脂复合材料

将有机蒙脱土（O-MMT）和纳米TiO₂共同复合到环氧树脂中,成功地制备出了一种高性能多功能O-MMT-纳米TiO₂/环氧树脂复合材料。由XRD检测结果和TEM观察结果证实,由于利用了O-MMT、纳米TiO₂与环氧树脂间的相互作用,蒙脱土（MMT）层被高度剥离,所得的二维MMT纳米单片与零维纳米TiO₂颗粒交错分布于树脂基体中。力学性能测试、热分析和耐沾污性试验表明,O-MMT-纳米TiO₂/环氧树脂复合材料的多项性能都比纯环氧树脂有大幅提高。