Z向增强平纹编织C/SiC复合材料层间剪切强度(英文)

碳纤维平纹编织物和穿透厚度的碳纤维Z-pins制作的预成型体,通过化学气相渗透工艺制备了Z-pins增强平纹编织C/SiC复合材料。采用双缺口剪切压缩试验测定了Z-pins增强平纹编织C/SiC复合材料的层间剪切强度,通过断口的电镜照片分析了层间剪切的破坏机理。研究了Z-pins个数对层间剪切强度的影响。结果表明:与未增强陶瓷基复合材料相比较,当Z-pins个数达到一定数量时,Z-pins插入能够提高层间剪切强度,层间剪切强度随Z-pins个数的增多而增加。Z-pins插入改变了陶瓷基复合材料的层间破坏机理,使层间织物与基体的脱离变为Z-pins的剪切破坏和层间织物与基体脱离的双重破坏机制。     

Z-pin增强CMC层间Ⅰ+Ⅱ混合型断裂韧性

提出手工预缝纫方法将3K丝束的T300碳纤维引入预成型体,采用CVI工艺在预成型体和缝线处同时渗透SiC基体,制备了Z-pin增强平纹编织C/SiC陶瓷基复合材料。通过三点弯曲试验测定了Ⅰ+Ⅱ混合型应变能释放率,分析了材料的裂纹扩展行为和Z-pin增强机理。结果表明:随着裂纹扩展长度的增大,Ⅰ+Ⅱ型裂纹扩展阻力不断增大,相同裂纹扩展长度,增加Z-pin植入密度可以提高粘结强度,增大止裂作用。Z-pin增强平纹编织C/SiC陶瓷基复合材料裂纹扩展的耗能途径主要是层间界面剥离、Z-pin弹性剪切和拉伸变形。     

Z-pin增强陶瓷基复合材料I型应变能释放率

碳纤维平纹编织物和碳纤维Z-pin制备的预成型体,通过化学气相渗透(CVI)工艺制成Z-pin增强平纹编织陶瓷基复合材料层压板。通过双悬臂梁试验研究Z-pin增强平纹编织陶瓷基复合材料层压板的层间I型应变能释放率和增强机理。研究Z-pin面积密度对层间I型应变能释放率的影响。结果表明:Z-pin增强平纹编织陶瓷基复合材料层压板主要增强机理表现为层间裂纹扩展受阻,Z-pin与层压板界面解离,Z-pin桥联裂纹和Z-pin拔出;增大Z-pin面积密度,层间I型应变能释放率增大。     

采用Z-Pin增强体的3D炭/炭复合材料层间断裂行为

采用炭纤维平纹织物和精细Z-pin制备了新型3D炭纤维预制件。炭基体采用等温化学气相沉积和高温煤沥青高压浸渍炭化制备。短梁剪切试验和开口拉剪试验用来表征Z-pin增强体对剪切破坏模式的影响。短梁剪切失效模式为似塑性，而拉剪失效模式为非似塑性破坏。分析了产生此现象的机制，短梁剪切假塑性失效由炭／炭复合材料叠层中纤维束内、纤维束间和叠层间微裂纹扩展形成，而产生拉剪失效的单一层间裂纹扩展不引起宏观假塑性现象。采用Z-pin作为提高层间剪切强度的增强体间隔1．5mm比间隔2，5mm可提高剪切强度40％～50％，陔技术将成为3D炭／炭复合材料预制体制备更为先进的技术．     

Z-pin增强酚醛复合材料层合板的层间拉伸性能

本文探索研究了Z-pin的植入对酚醛复合材料层合板层间拉伸性能的影响。通过向酚醛复合材料层合板中植入体积分数为0.78%(植入间距5mm×5mm)的石英/酚醛Z-pin,对其进行层间拉伸性能测试,结果表明,随着Z-pin的植入,层合板的层间拉伸性能显著提高,并伴随破坏模式的变化、材料韧性的增加。最后,根据复合材料力学,建立Z-pin增强层合板的简单力学模型,通过桥率试验与层间拉伸试验,对其进行验证和修正,得出Z-pin植入对层合板的层间性能的影响规律。     

织物结构对复合材料力学性能影响的试验研究

为探讨不同结构形式织物对复合材料力学性能的影响及其损伤破坏机制之间的差异,通过宏观拉压试验,研究了经编及平纹碳纤维织物增强树脂基复合材料的拉伸及压缩力学性能,并利用声发射对试验过程进行实时监测,对破坏后的断口进行显微镜观察分析,分别给出了两种材料的拉伸和压缩破坏机制.研究结果表明:织物结构形式对复合材料的力学性能有较大影响,与经编织物复合材料相比,平纹织物复合材料的拉伸、压缩强度均较低,且其拉伸、压缩破坏试样的断口相对齐平,分层现象不明显;根据声发射监测结果可以判定两种复合材料损伤过程中的损伤类型,与经编织物相比,平纹织物复合材料拉/压过程中的声发射电压信号相对稳定且整体强度较低.     

纤维束波动效应对平纹编织复合材料损伤行为的影响

平纹编织复合材料中纤维束波动效应会引起随动材料主方向变化及面外剪切应力集中,为了研究其对平纹编织复合材料力学性能及损伤行为的影响,提出改进的像素法细观有限元单胞模型。模型根据纤维束波动曲线定义了材料主方向的变化,采用Hashin准则模拟纤维束的损伤起始,并引入剪切修正因子考虑面外剪切应力对面内拉伸损伤的影响。模型可以预测平纹编织复合材料的面内拉伸强度和损伤演化过程,结果表明:纤维束材料主方向波动会引起平纹编织复合材料面内拉伸强度下降;面外剪切应力集中是导致复合材料最终失效的主要原因,且随着剪切修正因子增大,复合材料面内拉伸强度显著降低;纤维束材料主方向波动和面外剪切应力集中均对平纹编织复合材料的损伤行为和破坏机理产生了影响,需要在数值分析中对其进行准确描述。      

玄武岩纤维-碳纤维混杂平纹织物增强环氧树脂基复合材料的制备与力学性能

对以平纹织物为增强体的混杂纤维复合材料（HFRP）的刚度和强度进行研究。设计热压工艺并制备7组具有不同混杂比的玄武岩纤维-碳纤维（玄-碳）混杂增强环氧树脂基复合材料试样进行拉伸试验。基于平纹织物的结构特征,对传统混合定律加以修正,提出以平纹织物为增强体的HFRP刚度估算模型。基于HFRP层合板的破坏机制,提出材料仅发生一次破坏的临界混杂比,并分成三个混杂比范围给出强度估算模型。最终以体现分散度的混杂效应系数对估算结果加以修正。结果表明：计算值与试验值近似,预估模型计算所得临界混杂比与试样拉伸试验时的应力-应变曲线分析结果相符,模型可为今后的实际应用提供理论依据。本文提出的预估方法可以反应混杂比和分散度对平纹织物为增强体的HFRP强度和刚度的影响,扩展了混合定律的应用范围。     

苯酚电聚合膜修饰炭纤维表面对环氧基复合材料性能的影响

将连续炭纤维束用自制的空气梳分散成单丝状长带后, 通过采用循环伏安法的电化学方法将单体苯酚在炭纤维表面聚合成膜, 对炭纤维进行表面修饰, 以提高复合材料中炭纤维与树脂基体的界面粘结性能。红外光谱分析表明, 苯酚电聚合膜能够增加炭纤维表面的羟基、 醚键等活性官能团, 从而提高炭纤维与环氧树脂基体的界面粘结强度。与未进行表面修饰的炭纤维增强环氧树脂复合材料相比, 以聚苯酚膜修饰的炭纤维单丝带增强的环氧树脂基复合材料横向拉伸强度最大提高了90%, 纵向拉伸强度最大提高了45%, 层间剪切强度最大提高了110%。实验也表明, 将炭纤维束分散成炭纤维单丝带后能够更有效地增强复合材料的各项力学性能。      

双马来酰亚胺复合材料Z-pin制备及性能研究

采用拉挤成型工艺制备了一种基于双马来酰亚胺树脂的微径炭纤维复合材料细杆(Z-pin),通过差示扫描量热方法(DSC)研究了双马来酰亚胺树脂的固化反应特性,并由此确定其拉挤工艺参数.通过动态热机械分析仪测定了双马来酰亚胺树脂的玻璃化转变温度,结合复合材料Z-pin纤维体积含量及层间剪切强度对比分析发现,双马来酰亚胺树脂基...     

单向纤维增强陶瓷基复合材料单轴拉伸行为

采用细观力学方法对单向纤维增强陶瓷基复合材料的单轴拉伸应力-应变行为进行了研究。采用Budiansky-Hutchinson-Evans（BHE）剪滞模型分析了复合材料出现损伤时的细观应力场,结合临界基体应变能准则、应变能释放率准则以及Curtin统计模型三种单一失效模型分别描述陶瓷基复合材料基体开裂、界面脱粘以及纤维失效三种损伤机制,确定了基体裂纹间隔、界面脱粘长度和纤维失效体积分数。将剪滞模型与3种单一失效模型相结合,对各个损伤阶段的应力-应变曲线进行模拟,建立了准确的复合材料强韧性预测模型,并讨论了界面参数和纤维韦布尔模量对复合材料损伤以及应力-应变曲线的影响。与室温下陶瓷基复合材料单轴拉伸试验数据进行了对比,各个损伤阶段的应力-应变、失效强度及应变与试验数据吻合较好。     

Plasma surface modification of advanced organic fibres

The interlaminar shear strength, interlaminar fracture energy, flexural strength and modulus of extended-chain polyethylene/epoxy composites are improved substantially when the fibres are pretreated in an ammonia plasma to introduce amine groups on to the fibre surface. These property changes are examined in terms of the microscopic properties of the fibre/matrix interface. Fracture surface micrographs show clean interfacial tensile and shear fracture in composites made from untreated fibres, indicative of a weak interfacial bond. In contrast, fracture surfaces of composites made from ammonia plasma-treated fibres exhibit fibre fibrillation and internal shear failure as well as matrix cracking, suggesting stronger fibre/matrix bonding, in accord with the observed increase in interlaminar fracture energy and shear strength. Failure of flexural test specimens occurs exclusively in compression, and the enhanced flexural strength and modulus of composites containing plasma-treated fibres result mainly from reduced compressive fibre buckling and debonding due to stronger interfacial bonding. Fibre treatment by ammonia plasma also causes an appreciable loss in the transverse ballistic impact properties of the composite, in accord with a higher fibre/matrix interfacial bond strength.     

复合材料微细杆增强复合材料研究进展

纤维增强树脂基复合材料具有轻质高强的特点,但复合材料层合板层间韧性和抗冲击性能差,复合材料微细杆(Z-pin)增强技术极大地改善了这一不足,被广泛应用于各工业制造领域.近年来,Z-pin增强复合材料的制备工艺不断发展,目前主要有热压罐法和超声植入法(UAZ).Z-pin增强复合材料的层间增韧和抗冲击性能提高效果显著,但...     

Effects of vacuum thermal cycling on mechanical and physical properties of high performance carbon/bismaleimide composite

The aim of this article was to investigate the effects of vacuum thermal cycling on mechanical and physical properties of high performance carbon/bismaleimide (BMI) composites used in aerospace. The changes in dynamic mechanical properties and thermal stability were characterized by dynamic mechanical analysis (DMA) and thermogravimetric analysis (TGA), respectively. The changes in linear coefficient of thermal expansion (CTE) were measured in directions perpendicular and parallel to the fiber direction, respectively. The outgassing behavior of the composites were examined. The evolution of surface morphology and surface roughness were observed by atomic force microscopy (AFM). Changes in mechanical properties including transverse tensile strength, flexural strength and interlaminar shear strength (ILSS) were measured. The results indicated that the vacuum thermal cycling could improve the crosslinking degree and the thermal stability of resin matrix to a certain extent, and induce matrix outgassing and thermal stress, thereby leading to the mass loss and the interfacial debonding of the composite. The degradation in transverse tensile strength was caused by joint effects of the matrix outgassing and the interfacial debonding, while the changes in flexural strength and ILSS were affected by a competing effect between the crosslinking degree of resin matrix and the fiber-matrix debonding.     

Effects of fiber surface treatments on mechanical properties of epoxy composites reinforced with glass fabric

In this study, effects of fiber surface treatments on mechanical behavior and fracture mechanism of glass fiber/epoxy composites were investigated experimentally. To change the composition of the glass and regenerate to the hydroxyl groups, activation pretreatment of heat cleaned woven glass fabric was performed using (v/v) HCl aqueous solution at different concentrations before silane treatment. The treatment of silanization of heat cleaned and acid activated glass fibers with γ-glycidoxypropyltrimethoxysilane were performed. In this work, short beam shear test has been conducted to determine the performance of the acid treatment and the silane treatment in terms of the interlaminar shear strength. The silane coating on the heat cleaned glass fibers increased the interlaminar shear strength of the composite. However, the silane coating on the acid activated glass fibers did not improve the interlaminar shear strength of the composite. In addition, the strengths of the glass fabric specimens in tension and flexure were investigated. When the glass fibers are first treated with HCl solution and then with silane coupling agent, the tensile strengths of the composites decreased significantly. Scanning electron photomicrographs of fractured surfaces of composites were performed to explain the failure mechanisms in the composite laminates broken in tension.     

Mode I and mode II fracture toughness of E-glass non-crimp fabric/carbon nanotube (CNT) modified polymer based composites

In this study, mode I and mode II interlaminar fracture toughness, and interlaminar shear strength of E-glass non-crimp fabric/carbon nanotube modified polymer matrix composites were investigated. The matrix resin containing 0.1 wt.% of amino functionalized multi walled carbon nanotubes were prepared, utilizing the 3-roll milling technique. Composite laminates were manufactured via vacuum assisted resin transfer molding process. Carbon nanotube modified laminates were found to exhibit 8% and 11% higher mode II interlaminar fracture toughness and interlaminar shear strength values, respectively, as compared to the base laminates. However, no significant improvement was observed for mode I interlaminar fracture toughness values. Furthermore, Optical microscopy and scanning electron microscopy were utilized to monitor the distribution of carbon nanotubes within the composite microstructure and to examine the fracture surfaces of the failed specimens, respectively.