多向玻碳纤维混杂复合材料的拉伸性能北大核心

为探讨±45°铺层比例对玻碳纤维混杂复合材料拉伸性能的影响,对层间混杂和夹芯混杂分别设计4种铺层方案,并进行拉伸性能实验。通过经典层合板理论对试样的拉伸模量进行估算,与实验结果对比并分析误差。基于混杂效应及±45°铺层比例的影响,对经典层合板理论结果进行修正。结果表明:在±45°铺层比例为40%时,±45°铺层可以对横向应力和剪应力起到很好的平衡作用,从而有效提高复合材料的拉伸性能;混杂效应及±45°铺层比例对经典层合板理论与实验结果的误差都有影响,提出的修正公式可在一定程度上反映其影响,并且可以得到更加准确的拉伸模量估算结果。     

混杂FRP得合材料单轴拉伸性能研究

为制备优异综合性能的混杂FRP(Fiber Reinforced Plastic/Polymer)复合材料,本文试验研究了芳纶、玄武岩、玻璃纤维与碳纤维混杂复合材料的单轴拉伸力学性能,分析了纤维种类、碳纤维相对体积含量、铺层方式等混杂参数对混杂效应的影响.结果表明,HFRP(Hybrid FRP)复合材料的单轴拉伸弹性模量基本符合混合定律,层间混杂FRP复合材料均表现出良好的混杂效应.当碳纤维铺层在中间时,碳/芳纶/玻璃层间混杂复合材料的混杂效应系数为0.647,混杂效应最优.     

混杂FRP复合材料单轴拉伸性能研究

为制备优异综合性能的混杂FRP(Fiber Reinforced Plastic/Polymer)复合材料,本文试验研究了芳纶、玄武岩、玻璃纤维与碳纤维混杂复合材料的单轴拉伸力学性能,分析了纤维种类、碳纤维相对体积含量、铺层方式等混杂参数对混杂效应的影响。结果表明,HFRP(Hybrid FRP)复合材料的单轴拉伸弹性模量基本符合混合定律,层间混杂FRP复合材料均表现出良好的混杂效应。当碳纤维铺层在中间时,碳/芳纶/玻璃层间混杂复合材料的混杂效应系数为0.647,混杂效应最优。     

多向玻碳纤维混杂复合材料的拉伸性能

为探讨±45°铺层比例对玻碳纤维混杂复合材料拉伸性能的影响,对层间混杂和夹芯混杂分别设计4种铺层方案,并进行拉伸性能实验。通过经典层合板理论对试样的拉伸模量进行估算,与实验结果对比并分析误差。基于混杂效应及±45°铺层比例的影响,对经典层合板理论结果进行修正。结果表明:在±45°铺层比例为40%时,±45°铺层可以对横向应力和剪应力起到很好的平衡作用,从而有效提高复合材料的拉伸性能;混杂效应及±45°铺层比例对经典层合板理论与实验结果的误差都有影响,提出的修正公式可在一定程度上反映其影响,并且可以得到更加准确的拉伸模量估算结果。     

VARTM工艺铺层取向对复合材料力学性能的影响

采用真空辅助树脂传递模塑(VARTM)工艺制作了玻璃纤维增强不饱和聚酯复合材料层合板,对其进行了拉伸、弯曲、冲击性能测试,并对铺层取向与玻璃纤维复合材料层合板力学性能的影响关系进行了实验研究。实验结果表明,0°取向玻纤增强复合材料在单一方向上的力学性能最佳,±θ取向比θ取向玻纤增强复合材料有更好的力学性能;θ单向铺层复合材料在外载荷作用下发生破坏,其断口破坏的角度与铺层角度一致,而在±θ多向铺层复合材料的断口形貌更复杂。通过合理的铺层设计可获得满足工程需要的复合材料制品。     

开孔CFRP复合材料层合板的损伤解析和实验探究

采用解析计算和拉伸试验相结合的方法,对开孔CFRP复合材料板的孔边应力和损伤进行了研究。基于复变函数方法并结合Tsai-Hill失效准则,计算得到了层合板各单层的主应力分布和首次损伤载荷系数。为了测定层合板面内拉伸性能并对解析结果进行验证,基于ASTM D5766-07试验标准对CFRP层合板进行了拉伸试验。研究结果表明:当开孔CFRP层合板承受沿长轴方向拉伸载荷时,0°和±45°铺层为主承力层,且主应力σ1最大值出现在与孔中心成65°～115°和245°～295°范围内;各层最小首次损伤载荷系数出现在65°～115°范围内,其中,45°层和-45°层的损伤载荷系数最小;当载荷达到初始损伤载荷时,层合板开始出现内部损伤和参数退化;拉伸试验后CFRP复合材料板试件损伤的形式主要为基体开裂和纤维断裂,损伤的区域在孔周边61°～90°和241°～270°范围内,试验结果与解析计算结果基本一致。     

混杂纤维复合材料性能研究

对碳纤维织物、玻璃纤维织物和芳纶织物的性能进行测试,采用热熔法分别制备了一种增韧中温固化环氧碳纤维织物预浸料、玻璃纤维织物预浸料和芳纶织物预浸料。预浸料以单种预浸料铺层和不同纤维织物预浸料混合铺层方式铺贴组合,通过模压法成型复合材料层合板,进行性能测试并对比。结果表明,增韧中温固化环氧树脂的不同纤维织物预浸料混合铺层成型的层压板力学性能可以根据铺层设计优化,并不损失不同纤维铺层之间的界面性能。     

±45°铺层比例对层合板弯曲性能影响的实验研究

为探讨±45°铺层比例对不饱和聚酯树脂/玻璃纤维复合材料板材弯曲性能的影响,针对不同±45°铺层比例的复合材料层合板进行了四点弯曲实验。研究了弯曲模量随±45°铺层比例的变化;对试件断口形式进行了宏观观察,分析不同±45°铺层比例层合板的断口破坏形式;最后通过经典层合板理论计算其理论模量,并对比分析与实验的不同。结果表明:在纯0°铺层中加入50%比例的±45°铺层,可以得到比纯0°铺层更大的弯曲模量,但比例不适宜过大或过小;±45°铺层在材料断裂时有优势,可以起到连接作用;弯曲模量理论值与实验值由于界面区的影响存在一定误差。     

芳纶纤维复合材料弯曲性能试验仿真

对叠层结构芳纶纤维织物增强复合材料的弯曲性能试验进行仿真,分析±45°纤维铺层对复合材料弯曲性能的影响.参照GB/T 3356-1999弯曲性能试验,生成了4种不同铺层结构小尺寸试样的几何模型,建立了三点弯曲试验的有限元模型,计算得到了试样的应力场结果,预测了试样的弯曲弹性模量及弯曲强度.结果表明:±45°芳纶纤维铺层将提高叠层结构的弯曲性能,为叠层结构的铺层优化设计提供了技术支持.     

T700／3234层合板力学性能的研究

研究了T700／3234层合板力学性能,T700／3234层合板铺层45°／-45°／0°／90°／0°／0°／90°／0°／-45°／45°.T700／3234中温固化环氧碳纤维单向预浸料适应于热压罐成型工艺方法.测试了23℃、60℃、80℃、100％下,T700／3234层合板拉伸性能、压缩性能、弯曲性能、层间剪切强度及层合板的拉伸剪切强度,得出不同温度下层合板各项力学性能的保持率,表明：T700／3234复合材料使用温度不大于80℃.     

Impact behavior of aramid fiber/glass fiber hybrid composites: The effect of stacking sequence

Aramid fiber/glass fiber hybrid composites were prepared to examine the effect of stacking sequence on the impact behavior of thin laminates. The effect of position of the aramid layer on the impact properties of hybrid composites was investigated using driven dart impact tester. The delamination area and fracture surface of hybrid composites were analyzed for correlation with impact energy. The addition of glass layer to aramid layer reduced the impact resistance of hybrid composite due to the restriction in the deformation of aramid layer. The position of aramid layer resulted in variations in the impact behavior of hybrid composites. When the aramid layer was at the impacted surface, the composite exhibited a higher impact energy. This was attributed to the fact that the flexible layer at the impacted surface in thin laminates can experience larger deformation. In three‐layer composites, the aramid fiber‐reinforced composite ( AAA ) exhibited the highest total impact energy due to high impact energy per delamination area (1EDA) in spite of low delamination area. Aramid fiber and glass fiber‐reinforced composites showed a different impact behavior according to the change of thickness. This was attributed to the difference in the energy absorption at interface between laminae.     

Impact behavior of hybrid composite plates

This experimental study deals with the impact response of hybrid composite laminates. Two different hybrid composite laminates, aramid/glass and aramid/carbon, and two different stacking sequences, such as [0/0/90/90]_A+ [90/90/0/0]_G for AG1 and [0/90/±45]_A+ [±45/90/0]_G for AG2 and so on (see Table I ), were chosen for impact testing. The impact energy was gradually increased until complete perforation took place, and an energy profiling method (EPM) was used to identify the perforation thresholds of composites. The damaged samples were visually inspected. The images of the several samples subjected to various impact energies were registered and used for comparison and identifying damage mechanisms. The perforation thresholds for [0/90/±45]_s aramid/glass and aramid/carbon laminates were found to be approximately 5% higher than those for their counterparts with the [0/0/90/90]_s stacking sequence. © 2010 Wiley Periodicals, Inc. J Appl Polym Sci, 2010     

复合材料面内剪切性能测试方法的研究

对常用的剪切实验方法进行了简单介绍,并采用典型的±45°偏轴拉伸法和V形开口轨道剪切法对双轴向玻璃纤维布制成的层合板的常温和低温剪切性能进行了研究。实验结果表明,V形开口轨道剪切法测得的剪切强度和模量高于±45°偏轴拉伸法,玻璃纤维增强环氧树脂基复合材料在低温状态下的剪切性能与常温相比有所提高。     

紫外老化对芳纶／环氧复合材料性能和结构的影响

通过紫外老化试验（温度（40±5）℃,湿度40％）,研究了芳纶、环氧及其复合材料的力学性能、玻璃化转变温度、失重随老化时间的变化,并用红外光谱分析了芳纶的结构变化。结果表明：经紫外老化后,芳纶／环氧的拉伸强度、失重率有明显的变化,芳纶结构和复合材料的玻璃化转变温度无明显的变化。     

Solid state bonding of graphite/thermoset composites via interchain transesterification reaction (ITR)

Thick section composite laminates are expensive and difficult to manufacture because of problems with porosity, large reaction exotherms from epoxies and residual strains. The copolyester thermosets described here can eliminate these problems. Through interchain transesterification reactions, individually cured prepreg plies of graphite reinforced copolyester can be bonded with each other in the solid state. ITR bonding is shown to produce well‐consolidated laminates with less than 2% void volume and mechanical properties comparable to those of current high‐end polymer matrix composites. DMA testing showed the glass transition to begin at 190°C for a 45% fiber volume fraction composite. Tensile testing of 55% fiber volume composites at room temperature showed modulus, strength and elongation to failure averages of 105.4 GPa, 1.02 GPa and 1.0% respectively.     

Comparison of mechanical properties of epoxy composites reinforced with stitched glass and carbon fabrics: Characterization of mechanical anisotropy in composites and investigation on the interaction between fiber and epoxy matrix

The primary purpose of the study is to evaluate and compare the mechanical properties of epoxy‐based composites having different fiber reinforcements. Glass and carbon fiber composite laminates were manufactured by vacuum infusion of epoxy resin into two commonly used noncrimp stitched fabric (NCF) types: unidirectional and biaxial fabrics. The effects of geometric variables on composite structural integrity and strength were illustrated. Hence, tensile and three‐point bending flexural tests were conducted up to failure on specimens strengthened with different layouts of fibrous plies in NCF. In this article, an important practical problem in fibrous composites, interlaminar shear strength as measured in short beam shear test, is discussed. The fabric composites were tested in three directions: at 0°, 45°, and 90°. In addition to the extensive efforts in elucidating the variation in the mechanical properties of noncrimp glass and carbon fabric reinforced laminates, the work presented here focuses, also, on the type of interactions that are established between fiber and epoxy matrix. The experiments, in conjunction with scanning electron photomicrographs of fractured surfaces of composites, were interpreted in an attempt to explain the failure mechanisms in the composite laminates broken in tension. POLYM. COMPOS., 2008. © 2008 Society of Plastics Engineers     

不同增强方式下泡沫夹芯复合材料三点弯曲性能研究

研究了缝合及加强筋增强方式下泡沫夹芯复合材料的三点弯曲性能.采用万能试验机分别进行了缝合与未缝合碳纤维、玻璃纤维、玻碳混杂纤维泡沫夹芯复合材料的三点弯曲实验,分别得出各自的载荷-挠度曲线,再引入加强筋的方式进一步研究缝合碳纤维泡沫夹芯复合材料的弯曲性能.结果表明,玻碳混杂纤维泡沫夹芯复合材料较玻璃纤维泡沫夹心复合材料性...     

(±45°/90°/0°)_s准各向同性层合板的拉伸强度

根据经典层合板理论,层合板(±45°/90°/0°)s是准各向同性层合板,其拉伸刚度在板面内各个方向上都相同,而拉伸强度是随偏轴角θ改变而变化,即强度方面不具有各向同性的特点。本文首先研究(±45°/90°/0°)s这种准各向同性层合板拉伸强度在偏轴角θ从0°至45°之间的变化情况,然后通过分别改变单层板强度参数和弹性常数来研究该层合板的拉伸强度的变化情况,并分析其破坏形式。最后与NCF材料的试验结果进行了比较。     

Flexural fatigue of marine laminates reinforced with woven roving of E-glass and of Kevlar® 49 aramid

A comparison of the flexural fatigue characteristics of E-glass and Kevlar® 49 aramid in polyester and vinyl ester resin hand lay-ups typical of boat hull laminates is presented. Data on unidirectional E-glass and aramid composites from epoxy preimpregnated tapes are reported for comparison. The data indicate that while the initial flexural strength of E-glass woven roving laminates is greater than that of aramid laminates, the runout stress of aramid laminates at 10⁶ fatigue cycles is similar or superior to glass. S-N curves for aramid laminates are flatter indicating better flexural fatigue resistance.     

Energo-Mechanical Evaluation of Damage Growth and Fracture Initiation in Aviation Composite Structures

The aim of the present paper is to (1) highlight the results of laboratory damage detection and monitoring in the aviation composite materials, during a mechanical testing constituted of multiple loadings, and (2) obtain a detailed understanding of damage evolution of composite specimens with regard to impact energy. Woven 12-ply glass fiber and 16-ply carbon fiber–reinforced epoxy composites (GFRP 92 125/L285/287 and CFRP 98 131/L285/287) were used as less studied subjects in research. This study explored the resistance to cracking and delamination of glass and carbon fiber laminates with the same resin system under low-load conditions.