平面编织复合材料层合板低速冲击后的拉伸性能

对两种不同铺层形式的平面编织复合材料层合板低速冲击后拉伸性能进行了实验研究,在此基础上建立了有限元损伤扩展仿真模拟。在所建立的有限元模型中,将低速冲击损伤等效为形状规则的软化夹杂,并针对两种铺层形式采用不同的损伤判据和模量衰减准则。研究结果表明:该有限元模拟结果与实验结果符合,说明该模型能够准确地预测低速冲击后平面编织复合材料层合板的损伤扩展规律和剩余拉伸强度;不同铺层形式的平面编织复合材料层合板在低速冲击后拉伸的损伤扩展规律不同;它们的冲击后拉伸强度降均>50%,在复合材料结构设计中应该受到重视。      

复合材料层合板冲击损伤及剩余强度研究进展

综述了受低速冲击后复合材料层合板的损伤研究进展,重点介绍了倍受复合材料工程结构设计师所关注的含损复合材料层合板的剩余拉伸及压缩强度问题,最后对有待于进一步研究的问题进行了展望.     

缝合复合材料可用性--环境条件下层合板的冲击后压缩性能

为了解决缝合复合材料在航空航天结构中的应用问题,对国内生产的缝合/树脂膜渗透成型工艺复合材料层合板在三种不同环境条件下的低速冲击后压缩性能进行试验研究.结果表明,缝合改变了含冲击损伤层合板的压缩破坏机理,可以大幅度提高层合板在干态常温下的冲击后剩余压缩强度,但是对湿态高温下层合板的冲击后剩余压缩强度影响不大;缝合方向对冲击损伤面积和剩余压缩强度的影响较小,其中以0°缝合较为有利.     

复合材料层板低速冲击后剩余压缩强度

对两种材料体系和铺层的复合材料层合板进行低速冲击后压缩强度试验 , 以研究低速冲击后层合板的压缩破坏机理。讨论了表面凹坑深度、 背面基体裂纹长度、 损伤面积以及剩余压缩强度与冲击能量的关系。在试验研究的基础上 , 建立了复合材料低速冲击后剩余强度估算的一种椭圆形弹性核模型。该模型将冲击损伤等效为一刚度折减的椭圆形弹性核 , 采用含任意椭圆核各向异性板杂交应力有限元分析含损伤层合板的应力应变状态 ,并应用点应力判据预测层板的压缩(或压、 剪)剩余强度。理论分析与试验结果对比表明 , 该模型简单有效。      

CFRP层合板的二次低速冲击及剩余压缩强度试验研究

以碳纤维增强复合材料(Carbon fiber reinforced polymer,CFRP)层合板为研究对象,在结构的相同位置进行二次低速冲击,考察二次冲击时结构的动力响应和冲击后的剩余压缩强度,并与单次冲击的结果进行对比。在总冲击能量相同的前提下,采用落锤法对CFRP层合板进行冲击试验,得到结构单次和二次冲击的动力响应、能量吸收规律。采用超声波C扫描技术观测CFRP层合板内部的冲击损伤后,对CFRP层合板进行剩余压缩强度试验。系统研究和对比了单次和二次冲击对CFRP层合板在结构动力响应、能量吸收、损伤情况和剩余强度的影响。结果表明:总冲击能量分别为20 J、30 J、40 J时,二次冲击层合板试件吸收的总能量分别是单次冲击的52.50%、67.56%、81.41%,损伤总面积分别是单次冲击的60.58%、64.59%、80.60%;单次冲击后结构的剩余压缩强度分别是二次冲击的76.76%、78.65%、92.40%。此外,CAI-冲击能量、CAI-吸收能量和CAI-损伤面积曲线均在20 J的冲击能量下存在拐点。     

2.5D机织石英纤维增强树脂复合材料不同方向力学性能测试与模量预测2.5D机织石英纤维增强树脂复合材料不同方向力学性能测试与模量预测

石英纤维增强树脂复合材料常用于多物理场耦合环境下,为保证足够的层间性能,常采用2.5D机织的结构形式。本文对一种浅交弯联2.5D机织石英纤维增强双马树脂复合材料的三维力学性能进行全面测试,对比分析了材料在不同方向的拉伸性能和压缩性能,以及面内、面外剪切性能。测试结果表明,该复合材料的纬向拉伸、压缩模量略高于经向,而拉伸、压缩强度远高于经向,导致经向和纬向拉、压破坏模式差异显著,拉伸时弯曲的经向纤维被拉断,平直的纬向纤维劈裂,压缩时平直的纬向纤维压断,弯曲的经向纤维屈曲。同时,该种材料具有较高的面内、面外剪切变形能力。此外,本文基于混合定律,提出了一个2.5D机织复合材料经、纬向模量估算公式。基于材料微观结构特征,以包含经纱和纬纱的一个单胞作为代表性体积单元,建立有限元模型,预测该2.5D机织复合材料经向模量,预测结果与试验结果吻合很好。本文的研究对2.5D机织石英纤维/双马树脂复合材料的研发具有一定的指导意义。      

小尺寸试件层合板低速冲击后的剩余压缩强度

使用一种小尺寸试件试验方法来测量复合材料层合板低速冲击后的剩余压缩强度(CAI),以便减少试验费用,降低材料研制成本和周期。在试验研究的基础上,建立了复合材料低速冲击后剩余压缩强度估算的一种软化夹杂模型。该模型将冲击损伤等效成圆形低刚度的夹杂,用8节点等参元分析层合板的应力应变状态,以点应力准则为压缩破坏判据。理论分析结果与试验对比显示,该模型简单有效。     

阶梯型对接层合板复合材料力学性能的试验研究

为了确定采用2D机织物叠层方式制备复杂曲面结构复合材料制件过程中的增强织物对接缝间隔长度与其拉伸、弯曲性能的关系,基于对称铺层顺序[0°/0°/+45°/90°/-45°/90°]S,制备了连续铺层和对接间隔长度分别为4,8,12mm的四种环氧树脂基玻璃纤维2D机织物叠层结构RTM复合材料层合板试件,测定了2D玻璃纤维机织物层合板复合材料的拉伸和弯曲强度。试验结果表明,连续铺层的抗拉强度大约为357MPa,与对接铺层相比,其强度要高出35%左右,当对接间隔长度大于8mm时,拉伸应力不再随对接间隔长度的增加而变大,其拉伸强度基本保持在220MPa左右。另外,对接铺层的试验试件基本都在接口处断裂,这是由对接缝处应力集中造成的。由此实验结果可为复杂曲面结构复合材料提供一定的数据参考,使材料性能达到最优设计。     

三维整体夹芯机织复合材料的抗冲击与能量吸收性能

采用落锤冲击测试方法对几种类型3D整体夹芯机织复合材料板材的抗冲击性能进行测试,将测试结果与2D机织层合板、典型3D机织复合材料的抗冲击性能进行比较,分析影响复合材料抗冲击性能的因素.最后采用SEM分析试样的破坏过程与损伤机理.结果表明:当承受相同的冲击力时,具有合适夹芯结构的材料质量要比典型的三维机织复合材料板材轻的多,即可以满足工程上对结构体本身轻质、高强度性能及能量吸收能量的要求;接结方式的不同将影响复合材料板材的抗冲击性能,贯穿接结复合材料的抗冲击性能优于分层接结的复合材料;复合材料的抗冲击性能将随着增强纤维拉伸强度的增大而增大;在落锤冲击条件下,预制件经、纬纱的织造密度对三维整体夹芯机织复合材料板材的抗冲击性能影响很大.     

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。     

The impact properties and damage tolerance and of bi-directionally reinforced fiber metal laminates

Fiber metal laminates are an advanced hybrid materials system being evaluated as a damage tolerance and light weight solution for future aircraft primary structures. This paper investigates the impact properties and damage tolerance of glass fiber reinforced aluminum laminates with cross-ply glass prepreg layers. A systematic low velocity impact testing program based on instrumented drop weight was conducted, and the characteristic impact energies, the damage area, and the permanent deflection of laminates are used to evaluate the impact performance and damage resistance. The post-impact residual tensile strength under various damage states ranging from the plastic dent, barely visible impact damage (BVID), clearly visible impact damage (CVID) up to the complete perforation was also measured and compared. Additionally, the post-impact fatigue behavior with different damage states was also explored. The results showed that both GLARE 4 and GLARE 5 laminates have better impact properties than those of 2024-T3 monolithic aluminum alloy. GLARE laminates had a longer service life than aluminum under fatigue loading after impact, and they did not show a sudden and catastrophic failure after the fatigue crack was initiated. The damage initiation, damage progression and failure modes under impact and fatigue loading were characterized and identified with microscopy, X-ray radiography, and by deply technique.     

Mechanical behaviour of carbon and glass hybrid fibre reinforced polyester composites

Mechanical behaviour of carbon fibre/glass mat/polyester resin hybrid composites of sandwich construction is studied through tension, flexure, impact and post-impact tension tests. Tensile and flexural strength, modulus and failure strain values are compared to the calculated values. Total impact fracture energy and residual (after impact) tensile strength values of hybrid composites are analysed with regard to corresponding values of carbon/polyester composites. Failure of tested coupons was analysed by visual inspection and observation by scanning electron microscopy.     

Dynamic compression of cellular cores: temperature and strain rate effects

Cross-linked polyvinyl chloride closed-cell foams were examined under quasi-static and high strain rate compression loading using a servo-hydraulic testing machine and a modified split Hopkinson pressure bar apparatus consisting of polycarbonate bars for strain rates up to 1900 s⁻¹. Three foam densities were examined viz. 75, 130, and 300 kg/m³. Each core density has been subjected to compressive loading at room and elevated temperatures. A reverse trend in failure modes was observed when moving from room to elevated temperatures at high strain loading, which was not found in quasi-static testing at elevated temperatures. Accordingly, post-impact tests were conducted to evaluate the residual strength of the foam cores subject to elevated temperatures and HSR. Results of the post-impact test revealed that the foam cores are still capable of taking some loading. The residual strength of cores was fairly constant regardless of temperature therefore recovery of volume does not signify an increase in residual strength of cores.     

缝合复合材料层板低速冲击及冲击后压缩实验研究

通过对缝合复合材料层板进行低速冲击和冲击后压缩实验, 研究了不同类型的缝合复合材料层板的冲击损伤特性及冲击后压缩的剩余强度。实验研究表明: 基体损伤和分层是缝合层板与未缝合层板低速冲击的主要损伤模式, 缝合层板具有更好的抗冲击性能, 更高的冲击后压缩强度。缝合密度越大的层板其抗冲击性能越好, 冲击后压缩强度越高。缝合方向为0°的缝合层板较缝合方向为90°的缝合层板具有更好的抗冲击性能和更高的冲击后压缩强度。增加0°方向铺层, 减少45°、-45°方向铺层, 可以提高缝合层板的抗冲击性能和冲击后压缩强度。     

Impact and fatigue behaviour of hemp fibre composites

A series of experiments has been carried out to characterize the residual tensile and fatigue properties following impact of non-woven hemp fibre mat reinforced polyester. Additionally, the degradation of tensile modulus during fatigue cycling has been studied and related to the damage accumulation. For comparison purposes, ±45° glass fibre reinforced polyester samples have also been subjected to similar tests. It was found necessary to apply a relatively high pressure to the hemp composite during the curing stage in order to ensure a high enough fibre fraction to provide a significant reinforcing effect. With similar fibre weight fractions, the hemp and glass reinforced materials exhibited similar static tensile properties and fatigue lifetimes. Although the slightly steeper S–N curve of the hemp based material indicated a higher rate of reduction in fatigue strength with increasing cycles, it remained above the S–N curve for the glass based material showing that it was able to withstand slightly higher cyclic stress levels for equivalent numbers of cycles. The major difference in mechanical performance was the poorer resistance of the hemp based composite to impact. Also, the hemp based material failed in a much more brittle manner, without any visible signs of damage, such as the matrix cracking that was seen in the glass fibre based composite. It was found that, if the fatigue lifetime data of impact damaged samples were normalized against the post-impact residual tensile strength, then all data points lay close to a common S–N curve. This implies that residual fatigue lifetimes of damaged samples could be predicted from knowledge of their residual strength and the S–N curve for undamaged material.     

Z 向增强泡沫夹芯复合材料冲击损伤及冲击后压缩性能

基于热压罐成型工艺, 选择了树脂柱Z向增强泡沫芯材、碳纤维Z向增强泡沫芯材、Kevlar纤维缝纫增强泡沫芯材3种Z向增强复合材料结构, 对夹芯结构进行了低速冲击损伤和冲击后压缩(CAI)性能研究, 考察了不同Z向增强方式对冲击损伤面积和破坏模式的影响。结果表明, Z向增强对泡沫芯材产生了初始损伤, 其冲击后损伤面积大于未增强泡沫夹芯结构; 但Z向增强改变了夹芯结构的压缩破坏机制。通过选用合适的Z向增强材料和Z向增强参数, 能够提高夹芯结构的压缩强度和CAI强度。其中当增强材料为碳纤维, 增强参数为10 mm×10 mm时, 压缩强度提高了13%, CAI强度提高超过40%。     

High-temperature damage tolerance of carbon fibre-reinforced plastics:: 2. Post-impact compression characteristics

The post-impact compression strength of a poly(aryl sulfone) (PAS) thermoplastic, Radel 8320, and a toughened epoxy, Fibredux 924, matrix carbon fibre composites is examined at room temperature, 80°C and 150°C after non-penetrating impacts at combinations of these temperatures. Various fracture modes were identified but not found to have any correlation with variations in measured residual strength. In general terms, increasing the temperature of compression testing has a significant effect on the post-impact compression strength, whereas the temperature of the impact event has a marginal effect. There is evidence that the growth of impact generated delamination is restricted at the high temperatures during compression compared to growth at room temperature in the case of the epoxy matrix (thermoset), but this is not the case for the thermoplastic PAS.     

Review of low-velocity impact properties of composite materials

This paper is a review of low-velocity impact responses of composite materials. First the term ‘low-velocity impact’ is defined and major impact-induced damage modes are described from onset of damage through to final failure. Then, the effects of the composite's constituents on impact properties are discussed and post-impact performance is assessed in terms of residual strength.