纤维增强聚合物基复合材料低速冲击研究进展

综述了连续纤维增强聚合物基复合材料的低速冲击响应研究进展。讨论了测试方法及相关影响参数,例如冲头的形状、冲击速率对复合材料冲击的影响;介绍了冲击损伤的类型,进一步描述了层压板结构参数(如层合板厚度,铺层和缝纫)、复合材料组分材料性能(如纤维,树脂和纤维/树脂界面)以及预应力、环境条件等的影响;提出了纤维增强聚合物基复合材料冲击响应研究今后的发展方向。     

基于超弹性特性的SMA复合材料层合板低速冲击损伤数值模拟方法

基于ABAQUS有限元软件结合VC++6.0程序设计,建立了含不同铺层角度、不同排列密度形状记忆合金(SMA)纤维的复合材料层合板有限元模型。将基于Brinson本构模型的SMA分段线性超弹性模型以及判断复合材料层内失效的三维HASHIN失效准则编译至ABAQUS/VUMAT子程序,使用界面单元模拟复合材料层间区域,建立了SMA复合材料层合板的低速冲击损伤及冲击后剩余强度数值模拟方法。对比了不含SMA纤维层合板、含SMA纤维层合板、含普通金属丝层合板在不同冲击能量下的损伤响应。进一步分析了SMA纤维体积分数和直径变化对冲击响应的影响。冲击后剩余压缩强度模拟结果表明:冲击能量为16J时,含体积分数25%、直径0.5mm的SMA纤维层合板的冲击后剩余压缩强度相比不含SMA纤维层合板提高5.78%、相比含普通金属丝层合板提高4.69%。随着SMA纤维体积分数提高,层合板的抗低速冲击能力增强,当体积分数一定时,较细的(0.3mm)SMA纤维比粗的(0.6mm)SMA纤维对层合板的抗低速冲击能力增强效果更好。     

对位芳纶/尼龙66的加工工艺对其力学性能的影响研究

由不同的加工工艺来研究对位芳纶/尼龙66(PPTA/PA66)复合材料的力学性能,结果表明:①随着PPTA纤维含量的增多,使用黏度较大的PA66基体进行复合时,PPTA/PA66复合材料的拉伸强度、弯曲强度都随之变大;对于冲击强度来说,PPTA纤维的加入,增加了其脆性,造成PPTA/PA66复合材料冲击强度不如原基体的冲击强度;②PPTA纤维含量在5%的情况下,当挤出机转速达到300r/min时材料的拉伸强度、冲击强度和弯曲强度出现极大值,此时的混合效果最理想;③较高的挤出温度有助于提高复合材料的拉伸强度和弯曲强度,对于冲击强度来说,PPTA/PA66复合材料冲击强度同样不如原基体的冲击强度;④PPTA纤维的长径比集中在65左右,芳纶纤维起到了增强效果。     

三维编织复合材料研究及应用现状

正三维编织复合材料是利用编织技术,把经向、纬向及法向的纤维束(或纱线)编织成一个整体,即为预成型结构件(简称"预制体"),然后以预制体作为增强材料进行树脂浸渍固化而形成的复合材料结构。由于增强纤维在三维空间多向分布,阻止或减缓了冲击载荷作用下复合材料层间裂纹的扩展,使得复合材料层间性能大大提升。因此,三维编织复合材料较普通层合复合材料具有更高的冲击损伤容限和断裂韧性。三维编织技术可按实际     

纤维增强水泥基复合材料的动力拉伸性能研究

采用分离式霍普金森杆对聚乙烯醇(PVA)纤维增强水泥基复合材料(PRCC)、基体材料、不同相对掺量的钢纤维和PVA纤维混合增强水泥基复合材料(HFRCC)进行了四种不同应变率下的动态劈拉试验,通过对材料的劈拉强度、能量吸收和破坏形态等方面的对比分析,探讨了三种材料的动力拉伸性能,结果表明材料表现出应变率敏感性,随着应变率的提高,动态劈拉强度和能量吸收能力相应增加。HFRCC对基体材料的劈拉强度提高可达到34%,而PRCC材料提高约20%。PVA纤维对材料的耗能能力的影响比钢纤维具有更强的应变率敏感性。钢纤维掺量占总纤维掺量25%的HFRCC材料耗能能力比PRCC略低5%,而钢纤维掺量达到总纤维掺量的62.5%时,HFRCC材料的耗能能力比PRCC的耗能能力显著提高。HFRCC在动态劈拉强度和能量吸收能力方面更加均衡,具有更好抵抗冲击的能力。     

剑麻纤维/酚醛树脂复合材料的动态力学性能、力学性能和热性能

采用碱处理方法对剑麻纤维(SF)进行处理、细化,通过模压成型制备剑麻纤维/酚醛树脂(SF/PF)复合材料.采用动态力学(DMA)、力学性能、热膨胀性能等测定研究了剑麻纤维的加入量对复合材料的动态力学性能、冲击强度、弯曲强度、弯曲模量、比强度、比模量、耐磨性能、热膨胀性能的影响,用扫描电镜(SEM)观察了材料冲击断面和磨损面的形态.结果表明,制得的SF/PF复合材料的α转变温度提高,贮存模量提高,材料的力学性能和耐磨性得到显著改善,加入SF的复合材料的冲击断裂面出现明显的纤维拔出形态,材料的磨损面呈现粘着磨损特征形态.     

聚酰亚胺纤维纬编织物增强橡胶基复合材料冲击性能

针对固体火箭发动机绝热层复合材料在冲击作用下因增强织物和橡胶基体变形不协调导致的破坏问题,基于罗纹纬编结构,设计制备了两种纤维细度、三种线圈长度和两种铺层结构的聚酰亚胺纤维纬编织物增强丁腈橡胶(NBR)复合材料,测试并分析了增强结构对复合材料低速冲击性能的影响。结果表明：选用大丝束纤维、长线圈及正交铺层的复合材料具有更高的冲击峰值载荷和吸能。采用轮廓仪和显微镜观测冲击损伤形貌,在20.1 J冲击能量下试样均未被穿透,基体沿纤维方向产生裂纹并沿厚度方向产生塑性变形是复合材料主要的损伤模式。     

超声振动对玻纤增强聚丙烯复合材料注射成型特性的影响

为了研究超声振动对纤维增强复合材料注射成型特性的影响,利用自行开发的超声辅助可视化注射成型实验装置对不同玻纤(GF)含量的GF增强聚丙烯(PP)复合材料进行了超声外场作用下的可视化实验,观测分析了超声功率对复合熔体充填流动行为的影响。此外,通过对试样不同部位的金相观察,分析了超声功率对复合材料纤维取向的影响。结果表明:超声功率会对复合材料注射成型的充填流动行为及制品的纤维取向产生影响,而复合材料纤维含量对超声振动的效果也有直接影响。在纤维含量较低时,超声振动对基体材料微观形态的作用为影响复合材料充填流动性及纤维取向的主因;在纤维含量较高时,超声振动对纤维的作用为影响复合材料充填流动性及纤维取向的主因。研究结果为复合材料超声辅助成型技术的发展提供了依据。     

低密度纤维增强纳米孔树脂基复合材料的断裂机制

纤维增强纳米孔树脂基复合材料(IPC)是一类轻质高效防隔热一体化耐烧蚀材料,具有典型的非均质结构特征。在外加载荷下,内部的纳米孔隙将会衍生出微裂纹。裂纹的萌生、聚合和扩展对复合材料的强度、刚度、变形性等力学性能有着重要的影响。本文分别以石英纤维针刺网胎(NQF)、石英纤维针刺网胎/纤维布(NQCF)为增强体,制备得到不同纤维结构增强的纳米孔酚醛树脂(NPR)基复合材料(NQF/NPR、NQCF/NPR),对比研究了材料拉伸强度、拉伸模量、断裂伸长率及拉伸疲劳性能,并采用CT原位拉伸装置表征了拉伸过程中复合材料的微观结构演变。结果表明：纤维布的引入极大提高了复合材料的力学性能,并且微裂纹首先在针刺区域边缘的树脂基体中出现。在裂纹扩展过程中,纤维结构对树脂基体的损伤起到了不同程度的阻碍作用。最后结合有限元法建立了NPR及纤维布的有限元模型,分析了不同尺度下材料的断裂机制。     

甘蔗渣纤维增强聚丙烯复合材料的制备和力学性能

利用注射成型制备了甘蔗渣纤维增强聚丙烯复合材料, 分析了纤维质量分数、 注射成型条件以及添加物对复合材料力学性能的影响。结果表明, 随着纤维质量分数的增加, 材料的弯曲模量呈递增趋势。由于甘蔗渣纤维热降解的发生, 材料的力学性能随筒体温度的增加呈下降趋势。在模具温度90℃、 注射间隔时间30s、 不同的筒体温度185℃和165℃的成型条件下, 材料的弯曲性能和冲击强度分别呈现最大值。添加了马来酸酐改性聚丙烯后, 材料的弯曲强度和冲击强度得到了提高。      

复合材料等厚层板热压成型中树脂流动过程数值模拟

树脂基复合材料热压成型过程中树脂流动在很大程度上决定着层板纤维含量、 孔隙含量以及层板尺寸 , 根据有效应力原理与达西渗流定律建立了描述复合材料等厚层板热压成型过程树脂流动与纤维密实的数学模型 , 采用有限单元方法实现了热压成型中纤维密实均匀状况的预报。分析了温度边界条件、 铺层方式对树脂流动过程的影响。结果表明: 温度边界条件对计算结果影响比较大 ; 铺层方式对层板厚度以及纤维体积分数分布规律影响非常大 ; 边界条件以及材料参数的准确性直接影响计算结果的可靠性。以 T700S/环氧 5228单向层板为例进行了实验验证 , 结果表明计算与实验结果的一致性非常好。      

Macroscale assessment of low-velocity impact on hybrid composite laminates

Composites are usually brittle materials and have low impact properties. Structural dimensions, stacking sequence, ply materials, ply thicknesses and ply angles are standard variables that influence composite‘s performance against impact loads. Stacking sequence in hybrid laminates affects the failure and impact resistance. Failure mechanisms at the low-velocity impact of a rigid object in hybrid laminates are complex, and the subsurface damage in a composite laminate cannot be detected directly. However, various simulation platforms make it easy to see the impact damage between the plies of laminate. This paper numerically investigated the effect of stack sequence and hybridization of two fiber types against low-velocity impact. The current study adopted four-layer composite laminates of carbon and glass fiber layers with a stacking plan [C/C/C/C], [C/G/C/G] and [G/C/G/C], having lay-up angles as [0°/45°/−45°/90°]. Keeping the impactor mass and the incident velocity constant, the laminates were subjected to low-velocity impact. The damage contours for a failure mode were recorded and compared at the ply level. The numerical study resulted in impact imitations showing comparisons of the damage contours using Hashin failure criteria. Hybrid laminates display better performance in absorbing impact energies; however, hybrid laminates experienced more subsurface damage due to more impact energy absorption.     

Compression properties of z-pinned composite laminates

The effect of z-pinning on the in-plane compression properties and failure mechanisms of polymer laminates is experimentally studied in this paper. The reduction to the compression modulus, strength and fatigue performance of carbon/epoxy laminates with increasing volume content and diameter of pins is determined. The elastic modulus decreases at a quasi-linear rate with increasing pin content and pin diameter. Softening is caused by fiber waviness around the pins and reduced fiber volume content due to volumetric swelling of the laminate from the pins. A simple model is presented for calculating the compression modulus of pinned laminates that considers the softening effects of fiber waviness and fiber dilution. The compression strength and fatigue life also decrease with increasing volume content and diameter of the pins. The strength and fatigue properties are reduced by fiber kinking caused by fiber waviness around the pins and the reduced fiber content caused by swelling. The deterioration to the compression properties is also dependent on the fiber lay-up pattern of the laminate, with the magnitude of the loss in properties increasing with the percentage of 0° (load bearing) fibers in the laminate. The paper gives suggestions for minimizing the loss to the compression properties to laminates due to pinning.     

Invariant Based Transversely-Isotropic Material and Failure Model for Fiber-Reinforced Polymers

In this article, a constitutive formulation of a transversely-isotropic material and failure model for fiber-reinforced polymers is presented comprising pre-failure material nonlinearities, a novel invariant based quadratic failure criterion (IQC) as well as post failure material softening. The failure surface of the IQ criterion is assumed to take the influence of triaxiality on fracture into account. Further, a distinction between fiber failure and inter-fiber failure is conducted. Material softening is governed by a fracture energy formulation and the introduction of an internal length. The constitutive model is implemented into a programming user interface of the commercial finite element program Abaqus. As results, different laminate lay-ups are modelled and exposed to different stress states in an FE analysis. The obtained failure surfaces and stress strain curves for each laminate lay-up are compared to experimental data. As further applications of the material model presented, a curved composite beam, showing delamination, and a 0 /90 /0 -rod, showing the characteristic damage state in the 90 layer, are simulated and compared to tests.     

Fracture mechanisms of wood/polyester laminates under quasi-static compression and shear loading

There is increasing use of natural fiber/polymer composites as alternatives to traditional structural materials like concrete and metals and to the inorganic fibers like carbon. While the fracture mechanisms during crushing of synthetic fiber/polymer composites have been thoroughly studied, limited information is available on post-fracture investigation and identification of the dominant fracture mechanisms of wood/polyester composites. In this study laminates of Douglas-fir veneer were fabricated using a catalyzed polyester resin and their potentials as energy absorbers have been investigated and discussed. Factors for this study were (i) laminates symmetry (face layers of 0° or 90°), (ii) lay-up balance (balanced and unbalanced) and (iii) number of lamina (8, 11, and 12). Samples were tested under quasi-static Combined Loading Compression (CLC) and their compressive performances were compared to control specimens using glass fiber as reinforcement. Results indicated that the effect of symmetry on compressive properties of wood veneer/polyester laminates was significant with laminates with face layers of 90° and core layers of 0° had the highest deflection to failure. Increasing the wood/polyester laminate thickness enhanced their energy absorbing ability by bringing more fracture mechanisms into play but it noticeably reduced the laminates compressive modulus. Despite the brittle failure of glass fiber composites wood laminates exhibited a progressive fracture mechanisms with shear buckling as the dominant mode of failure in symmetric samples. This progressive failure with high energy absorbing ability make wood/polyester laminates a good candidate to be used as an energy absorber structure where high deflection to failure and longer failure time are required.     

Effects of composite lay-up configuration and thickness on the damage self-sensing behavior of carbon fiber polymer-matrix composite

The lay-up configuration (unidirectional, crossply and quasi-isotropic) and thickness (8–24 laminae) affect the damage self-sensing characteristics of continuous carbon fiber epoxy-matrix composites. The damage is by drop impact directed at the top surface of the laminate. The oblique resistance (i.e., resistance at an angle between the longitudinal and through-thickness directions) is an effective damage indicator for all lay-up configurations and thicknesses. The surface resistance of the bottom surface is an effective damage indicator for thin (8-lamina) composites, though it is less sensitive to minor damage than the oblique resistance. The surface resistance of the top surface is less effective than that of the bottom surface for 8-lamina multidirectional composites. The through-thickness resistance is an effective damage indicator for 16- and 24-lamina quasi-isotropic composites, but is ineffective for 8-lamina composites of any lay-up configuration. In general, effectiveness means a monotonic and significant increase of the resistance with damage extent.     

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.     

Micromechanical Modeling of Impact Damage Mechanisms in Unidirectional Composite Laminates

Composite laminates are susceptible to the transverse impact loads resulting in significant damage such as matrix cracking, fiber breakage and delamination. In this paper, a micromechanical model is developed to predict the impact damage of composite laminates based on microstructure and various failure models of laminates. The fiber and matrix are represented by the isotropic and elastic-plastic solid, and their impact failure behaviors are modeled based on shear damage model. The delaminaton failure is modeling by the interface element controlled by cohesive damage model. Impact damage mechanisms of laminate are analyzed by using the micromechanical model proposed. In addition, the effects of impact energy and laminated type on impact damage behavior of laminates are investigated. Due to the damage of the surrounding matrix near the impact point caused by the fiber deformation, the surface damage area of laminate is larger than the area of ??impact projectile. The shape of the damage area is roughly rectangle or elliptical with the major axis extending parallel to the fiber direction in the surface layer of laminate. The alternating laminated type with two fiber directions is more propitious to improve the impact resistance of laminates.     

T300/QY8911十字叠层复合材料冲击损伤与破坏的实验研究

对T300碳纤维增强QY8911双马来酰亚胺树脂十字叠层复合材料的冲击损伤与破坏特性进行了实验研究。采用落锤(自由落体)冲击试验方法,测定了三类铺层结构板材的冲击破坏强度和冲击损伤能量门槛值;将冲击强度与破坏模式和静态三点弯曲情况做了对比。用宏、细观方法检测了冲击损伤特性。对低于门槛值的冲击动力学行为给出了分析模型。     

Postbuckling strengths of composite laminate with various shaped cutouts under in-plane shear

The aim of present investigation is to study the buckling and postbuckling response and strengths under positive and negative in-plane shear loads of simply-supported composite laminate with various shaped cutouts (i.e., circular, square, diamond, elliptical-vertical and elliptical-horizontal) of various sizes using finite-element method. The FEM formulation is based on the first order shear deformation theory which incorporates geometric nonlinearity using von Karman’s assumptions. The 3-D Tsai-Hill criterion is used to predict the failure of a lamina while the onset of delamination is predicted by the interlaminar failure criterion. The effect of cutout shape, size and direction of shear load on buckling and postbuckling responses, failure loads and failure characteristics of quasi-isotropic [i.e., (+45/−45/0/90)_2s] laminate has been discussed. In addition, the effect of composite lay-up [i.e., (+45/−45/0/90)_2s, (45/−45)_4s and (0/90)_4s] has also been reported. It is observed that the cutout shape has considerable effect on the buckling and postbucking behaviour of the quasi-isotropic laminate with large size cutout. It is also observed that the direction of shear load and composite lay-up have substantial influence on strength and failure characteristics of the laminate.