Measurement of the static compressive strength of carbon-fibre/epoxy laminates

This paper describes an experimental study of the compressive failure of T800/924C carbon-fibre/efoxy composite laminates. Undirectional laminates loaded parallel to the fibres have compressive strengths that are 70% of the tensile strength and fail by fibre-microbuckling. During microbuckling the fibre debonds from the matrix, and the fibres break in bending. Multidirectional [(±45/0₂)₃]_sm laminates were also tested in compression, and the critical failure mechanism observed was microbuckling of the 0° plies. The failure strain was almost the same as for the undirectional laminate, The failure strain was almost the same as for the unidirectional laminate, which indicated that the ±45° plies have no significant influence on the failure strength of the 0° plies.     

Beam analysis of angle-ply laminate end-notched flexure specimens

Analysis and experiments on quasi-unidirectional and angle-ply laminate end-notched flexure specimens are presented. The analysis is based on laminated beam theory incorporating first-order shear deformation theory. Compliance and strain-energy release rate determined for relatively thin unidirectional and angle-ply laminate ENF specimens were in good agreement with a previous classical plate theory formulation. For thicker laminates, however, effects of shear deformation on the compliance of the ENF specimen become significant. An experimental study on glass/polyester quasi-unidirectional and angle-ply laminate ENF specimens was conducted. Specifically, [0]₆, [±30]₅ and [±45]₅ laminates with mid-plane delaminations were considered. Experimental compliance data agreed well with analytical predictions. The fracture toughness increased with increased angle θ at the ±θ interface. This is attributed to the fracture work associated with the debonding of transversely oriented fiber bundles in the quasi-unidirectional plies. The angle-ply laminates displayed more yarn debonding than the quasi-unidirectional laminate. For all laminates it was observed that the crack propagated in a non-uniform manner which is correlated with elastic coupling effects with cracked regions of the laminate beams.     

Mg(OH)2对苯并噁嗪环氧树脂复合材料阻燃性的影响

以Mg(OH)₂为无机阻燃剂,以苯并噁嗪(BZ)-环氧树脂(EP)为基体,通过热压成型制得Mg(OH)₂-玻纤布/BZ-EP层压板。通过垂直燃烧和极限氧指数测试层压板的阻燃性,分析了Mg(OH)₂粉体的用量、粒径及不同粒径粉体复合添加对复合材料阻燃性的影响,通过SEM对 Mg(OH)₂粉体在浸渍胶中的分散结构进行表征。研究发现: Mg(OH)₂粉体的粒径和用量对板材阻燃性有一定影响,不同粒径的粉体混合添加可以在复合材料中形成阻燃网络,达到最佳的阻燃效果,同时可以减小无机粒子对板材力学和电学性能的影响。当阻燃剂Mg(OH)₂用量为BZ-EP总质量的30wt%,粒径为2 μm的粉体(YX-105)和粒径为4 μm(YX-110)的粉体以质量比1:2复合添加时,所制层压板的极限氧指数为34%,垂直燃烧单个试样自熄时间最短为7.52 s,5个试样总自熄时间为49.81 s,达到UL-94V-0级标准。复合材料的弯曲强度为399.84 MPa,相对介电常数为3.848。     

中等应变率下单向玻璃纤维增强环氧树脂基复合材料的剪切本构关系

采用真空辅助成型工艺制备单向玻璃纤维增强环氧树脂基的[±45°]_8s复合材料试样,通过专用试验设备开展恒定应变率下的面内剪切性能研究,应变率范围为3×10^-4~128.4 s^-1。以Khan-Huang本构关系模型表达形式为基础,考虑应变率效应,建立了一种单向玻璃纤维增强环氧树脂基复合材料在中等应变率下的剪切本构模型,通过最小二乘法和遗传算法获得了最优本构参数。结果表明,单向玻璃纤维增强环氧树脂基复合材料的剪切性能具有应变率敏感性,剪切强度随着应变率的提高逐渐增大,在128.4s^-1时极限强度提高了35.5%。建立的本构关系模型能够准确反映剪切性能与应变率的关系,可用于中等应变率条件下的剪切性能预测。     

ZrW_(2)O_(8)-Cf/E51低/负热膨胀复合材料制备及超声时间对其热膨胀和力学性能的影响EI北大核心

为了制备低膨胀、高强、轻质复合材料,采用模压法制备了ZrW_(2)O_(8)-Cf/E51复合材料,并研究了超声时间对其微观组织、热膨胀行为和极限抗拉强度的影响。结果表明:在制备过程中颗粒团聚后容易受到纤维单丝阻挡并在纤维束表面聚集。在20 min之内,延长超声时间会减少ZrW_(2)O_(8)颗粒团聚。随着颗粒团聚的减少,复合材料断口会由平面状、无纤维拔出变为台阶状、有纤维拔出。在碳纤维和ZrW_(2)O_(8)颗粒的综合作用下,ZrW_(2)O_(8)-Cf/E51复合材料在热膨胀过程中膨胀量dL/L0会出现增大、减小和缓慢上升三个阶段,平均热膨胀系数也会出现相应的三个阶段。超声时间从5 min延长到20 min,ZrW_(2)O_(8)-Cf/E51复合材料的平均热膨胀系数降低了约130%,极限抗拉强度提高了约8%。     

基于纤维束/环氧树脂复合材料试验的单向层合板横向拉伸强度预测方法

实验研究表明,纤维束/环氧树脂复合材料试件的横向拉伸强度与工程上常用的单向层合板横向拉伸强度在趋势上具有很好的相关性,但是数值上存在一定差距。本文使用两种碳纤维和两种环氧树脂制备了三种纤维束/环氧树脂复合材料和单向层合板,并分别测量了纤维束/环氧树脂复合材料和单向层合板的横向拉伸强度,以及环氧基体的拉伸强度。在实验基础上,应用Griffith断裂强度理论建立了纤维束/环氧树脂复合材料和单向层合板的横向拉伸强度的关系模型,通过两种复合材料实验的结果拟合了该模型中的参数。利用第三种复合材料实验进行校验,发现该模型预测的单向层合板横向拉伸强度与实测强度之间达到很好的一致性,相对偏差为9%。采用本文提出的方法,可以用较为简单的纤维束/环氧树脂复合材料和环氧基体拉伸试验预测单向层合板的横向拉伸强度。     

A study on the low-velocity impact response of laminates for composite railway bodyshells

This paper presents a study on the low-velocity impact response of woven fabric laminates for the composite bodyshell of a tilting railway vehicle. In this study, low-velocity impact tests for the three laminates with size of 100 mm × 100 mm were conducted at three impact energy levels of 2.4 J, 2.7 J and 4.2 J. Based on these tests, the impact force, the absorbed energy and the damaged area were investigated according to different energy levels and stacking sequences. The damage area was evaluated by visual inspection and C-scan measurement. The test results showed that the absorbed energy of [fill]₈ laminate was highest whereas [fill₂/warp₂]_s laminate was lowest. The [fill]₈ laminate had the largest delamination area because of the highest impact energy absorption.     

基于断裂韧性预报复合材料层合板的开孔拉伸强度

开孔层合板的强度预报往往取决于孔边的临界长度,它不仅与材料性能,而且与铺层、孔径都有关。本文基于线弹性断裂力学,提出了一种预报对称铺层层合板开孔拉伸强度的新方法,只需提供正交层合板的断裂韧性和无缺口层合板的拉伸强度,显著降低对实验数据的依赖性。首先,将临界长度表作为层合板断裂韧性和无缺口拉伸强度的函数,再通过正交层合板[90/0]_8s的紧凑拉伸试验和虚拟裂纹闭合技术,确定出0°层断裂韧性,进而计算得到任意对称铺层层合板的断裂韧性。本文测试了T300/7901层合板[0/±45/90]_2s和[0/±30/±60/90]_s的开孔拉伸强度,孔径分别为3 mm、6 mm和9 mm。理论预报结果与试验值吻合较好,最大误差为15.2%,满足工程应用需求。      

Fatigue damage mechanics of composite materials Part III: Prediction of post-fatigue strength

A damage-based model for post-fatigue notch strength is presented. The model is an extension of a method developed previously to predict the notch strength of laminated composites. A simple finite element representation of the notch tip damage zone is used to obtain the localized damage-modified stress distribution. A uniaxial tensile stress failure criterion is applied to the 0° plies from which the laminate strength is evaluated. In conjunction with the fatigue damage growth law described in Part II, residual strength is calculated as a function of the applied loading conditions, specimen geometry and lay-up for (90/0)_s, (90/0)_2s and (90₂/0₂)_s T300/914C carbon-fibre/epoxy laminates subjected to tension-tension fatigue cycling.     

注塑成型纤维增强热塑性树脂复合材料刚度预测方法

基于Hsueh模型的应力场分布,采用代表性体积单元(RVE)平均近似方法,推导出可以退化成Halpin-Tsai模型的泊松比v12的显性表达式,与桥联模型基本重合.结合Fu模型和Giner模型,引入与纤维长径比(l/a)相关的指数衰减函数得到横向模量E22修正的Halpin-Tsai模型,与自洽模型重合.基于泊松比各向...     

Interfacial debonding in laminated titanium matrix composites

The results of an experimental program in which multiaxial loads were applied to [0₄] and [±45]_s silicon carbide/titanium (SiC/Ti) tubes are reviewed showing that stress coupling, matrix viscoplasticity (including room temperature creep) and fiber/matrix interfacial damage all contribute to nonlinear response and permanent strains in titanium matrix composites (TMC). A micromechanical model that explicitly considers the aforementioned phenomena is presented herein. The model assumes a periodic microstructure and uses finite elements to analyze a representative volume element. The composite is assumed to be in a state of generalized plane strain making it possible to discretize only a generic transverse plane while still being able to apply three-dimensional loading through appropriate boundary conditions. The response of laminated composites is predicted by incorporating the micromechanical results into nonlinear lamination theory. Predictions are presented to show the influence of the model parameters on the effective composite response of unidirectional [0₄] and angle-ply [±45]_s TMC laminates.     

纳米Mg(OH)2-ZnO/聚酰亚胺复合薄膜的介电和热性能

采用反向沉淀法制备了Mg（OH）₂-ZnO纳米粒子,通过原位聚合和热亚胺化的方法成功制备了不同纳米Mg（OH）₂-ZnO粒子质量分数的纳米Mg（OH）₂-ZnO/聚酰亚胺（PI）复合薄膜,通过SEM、热重分析、介电谱测试仪和击穿场强测试仪对薄膜的表面形貌、热稳定性、介电性能和击穿强度进行表征和测试。结果表明：Mg（OH）₂-ZnO纳米粒子均匀地分散在PI基体中,Mg（OH）₂-ZnO/PI热稳定性下降,介电常数、介电损耗和电导率增加,击穿场强随纳米粒子增加先增加后减小,在纳米粒子含量为2%时,达到最大值296 kV/mm。     

基于碳纤维的新型自支撑电极制备方法

借鉴自支撑电极的制备原理,利用电化学沉积结合(NH₄)₂S₂O₈和NaOH沉积液进行表面处理等手段制备了基于碳纤维表面Cu(OH)₂纳米结构的自支撑电极,分析测试了碳纤维表面的微观形貌、表面元素组成及其分布和表面物质的晶型以及利用水热反应在其表面附着电化学物质MnO₂后的电化学性能。结果发现,当(NH₄)₂S₂O₈的浓度为0.43 g/L、NaOH浓度为30.48 g/L、处理时间为12 min时,由SEM观察发现碳纤维表面的Cu(OH)₂纳米纤维的直径、长度、数量都较适宜;XPS、XRD和EDS的测试结果,沉积液处理后碳纤维表面部分单质铜转化为Cu(OH)₂,此结构非常有利于电化学物质的负载而由此构成开放、具有核壳结构的高性能电极材料;恒电流充放电(GCD)测试结果表明此电极材料具有极快的充放电速度。因此本文首次成功地在碳纤维表面的铜层表面原位生长出Cu(OH)₂纳米纤维,为未来以超级电容器为代表的能源设备的性能提升和商业化应用开拓了一种新的电极制备方法。      

纤维预热温度对连续Al2O3f/Al复合材料力学性能的影响

选用Nextel610型Al₂O₃纤维为增强体、ZL210A连续氧化铝合金为基体,采用真空压力浸渗法制备纤维增强铝基复合材料(Al₂O_3f/Al),纤维的体积分数为40%,预热温度分别为500、530、560和600℃,研究了纤维预热温度对Al₂O_3f/Al复合材料的微观组织、纤维损伤和力学性能的影响。结果表明：随着纤维预热温度的提高复合材料的致密度随之提高,最大达到99.2%,材料的组织缺陷最少,纤维的分布均匀;随着纤维预热温度的提高从复合材料中萃取出来的Al₂O₃纤维的拉伸强度不断降低,纤维预热温度为600℃的复合材料中Al₂O₃纤维的拉伸强度仅为1150 MPa,纤维表面粗糙,有大尺寸附着物。纤维的预热温度对Al₂O_3f/Al复合材料的拉伸强度有显著的影响。预热温度为500、530、560和600℃的复合材料其拉伸强度分别对应于298、465、498和452 MPa。组织缺陷、纤维损伤和界面结合强度,是影响连续Al₂O_3f/Al复合材料强度的主要因素。     

复合材料开孔层板压缩渐进损伤试验

为研究碳纤维增强树脂基复合材料开孔层板在压缩加载过程中的损伤起始、演化方式和损伤特点,采用微距拍摄、逐级加载超声C扫描、X光扫描和扫描电子显微镜观测4种观测手段对国产CCF300/5228A[45/0/-45/90]4s、[452/02/-452/902]2s、[454/04/-454/904]s3种铺层方式的开孔层板进行了压缩试验研究。对压缩载荷作用下开孔层板的损伤起始和损伤演化进行了观察和对比。对试验中观测到的纤维微屈曲、纤维挤出、孔边开裂和分层扩展等现象之间的关系进行了分析和说明。试验结果表明:压缩载荷下45°和90°铺层相邻位置为层板易分层位置,含45°和90°铺层相邻位置的开孔层板渐进损伤过程较为明显:开孔层板在压缩载荷下较早出现损伤,损伤的起始和演化缓解了孔边应力集中,促使压缩应变能在孔边逐步释放,推迟开孔层板压缩破坏的发生,提高层板压缩承载能力。研究结果可为材料结构损伤容限设计提供依据。     

The mechanical behavior of optical fiber sensor embedded within the composite laminate

Mechanical behavior, such as tensile and fatigue strength, of the optical fiber sensor embedded within the composite laminate was investigated. Tensile and fatigue tests were performed to evaluate the static and fatigue characteristics of optical fibers embedded within three types of laminated composite specimens, [0₆/OF/0₆]_T, [0₂/90₄/OF/90₄/0₂]_T and [0₃/90₃/OF/90₃/0₃]_T. The initiation of damage and fracture of the optical fiber were detected by observation of the intensity drop-off of laser signal transmitted through the optical fiber during test. Experimental results showed that the fatigue strength of optical fiber embedded within the cross-ply laminate is much lower than the fatigue strength of optical fiber within the unidirectional ply laminate. It was also found that the optical fiber embedded within unidirectional ply laminate fractured due to the fatigue damage accumulation of internal defects of optical fiber itself. However the optical fiber embedded within the cross-ply laminate fractured due to the growth of transverse matrix crack of host composite laminate.     

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.     

An investigation of non-linear elastic behavior of CFRP laminates and strain measurement using Lamb waves

This paper investigates the non-linear elastic behavior of unidirectional and cross-ply CFRP laminates and proposes a new method to measure tensile strain using Lamb waves. Young’s modulus was measured as a function of strain in situ using Lamb wave velocity during a tensile test. The stiffening effect of the carbon fibers on [0]₈ specimens and the softening effect of the epoxy matrix on [90]₈ specimens were accurately evaluated. Young’s modulus of the 0° ply was obtained as a quadratic function of strain. Using the function and the rule of mixture, the dependence of Young’s modulus on strain was accurately predicted for cross-ply laminates. Based on the results, the tensile strain was quantitatively correlated with the corresponding arrival time of the Lamb waves. The strains obtained from the proposed method agreed well with those from the strain gauge. Finally, the effect of transverse cracks on the in situ Young’s modulus of the cross-ply laminate under a tensile load was investigated. This method clearly detected even a small decrease in the Young’s modulus due to the transverse cracks in stiffening cross-ply laminate.     

A quasi-three-dimensional elastic wave propagation analysis for laminated composites

Localized impact problems for composite structures have recently become important. In this study, some elastic wave velocities in 7-ply GFRP laminate with [0₂/90₃/0₂] ply orientation after low speed impact was investigated by using both experimental methods and finite element methods. For the finite element simulation, the quasi-three-dimensional model was used. Comparing the results, the validity for the application of this model to the dynamic problem was estimated. Moreover the quasi-three-dimensional model is applied to the GFRP plates with interlaminar delamination. The relationship between the elastic wave velocities and delaminated states is discussed.     

基于纤维束增强树脂基复合材料测试的单向层合板层间剪切性能的预估方法

纤维束增强树脂基复合材料（FBC）及其单向层合板在标准Iosipescu剪切实验中表现出非常相似的破坏特征,然而测量得到的剪切强度却有明显差异。本文使用两种碳纤维和两种环氧树脂制备了3种FBC和单向层合板,对FBC剪切强度和单向层合板层间剪切强度进行了测量与分析。应用界面单元方法分析了纤维束与基体之间的界面应力场,发现FBC剪切试件中纤维束/基体界面附近的应力状态为拉剪耦合,而单向层合板中界面处于纯剪切应力状态,这一差异导致FBC剪切实验测量的强度低于单向层合板的剪切强度。本文基于Yamada-Sun强度理论建立了FBC剪切强度与单向层合板剪切强度之间的关系模型,应用该模型预测的单向层合板剪切强度与实测强度之间达到良好的一致性,相对偏差为10%左右。根据本文提出的方法,通过制样较简单的FBC试验能够预测和评估相应单向层合板的层间剪切性能。