基于拉伸载荷的碳纤维/环氧树脂层合板疲劳断裂机理

为研究拉伸载荷下碳纤维/环氧树脂层合板的疲劳性能，开展了4种应力水平下的T300/6511碳纤维平纹织物层合板的拉-拉疲劳实验，得到了不同应力水平下层合板的疲劳寿命。采用超声波C扫和扫描电子显微镜（SEM）观察断口形貌及内部损伤，讨论复合材料疲劳损伤发展积累过程和断裂机理。通过复合材料疲劳有限元分析模型，模拟了复合材料织物层合板疲劳损伤积累和失效过程，绘制了S-lg N曲线，分析发现模型预测的疲劳寿命及失效模式与实验结果吻合良好。疲劳加载时，层合板两侧自由边的表面首先出现基体开裂和分层损伤，随后诱发基体与纤维间界面破坏，损伤加剧，并迅速向内侧扩展；最后大量纤维和基体断裂，损伤贯穿整个截面，导致疲劳断裂。     

开孔T300/YH69层合板在不同应力水平下的疲劳强化行为

开孔的碳纤维增强层合板存在着疲劳后剩余强度提高的现象。通过对[-45,0,45,90]_2S和[0,90]_4S两种铺层的开孔碳纤维增强树脂基(T300/YH69)复合材料层合板进行实验，测定其静强度、疲劳极限和应力-寿命(S-N)曲线。结果表明，静强度分别为440.04 MPa和597.94 MPa,疲劳极限分别达到静强度的80%和86%。对试件施加不同应力水平的循环载荷，在循环次数达到10⁵后测量试件剩余强度，探究不同应力水平的疲劳载荷对剩余强度的影响，发现剩余强度在应力水平较低时无明显变化，在应力水平较高时明显提升，两种铺层结构的剩余强度最大分别为512.7 MPa和712 MPa。提升比例最高分别达到16.51%和19.07%。通过扫描电镜(SEM)发现疲劳试件断口相较于静拉伸试件断口更为整齐，纤维断裂方向更为一致。这是由于疲劳载荷作用下基体产生裂纹使得应力分布更均匀所致。     

玻璃纤维增强树脂基复合材料疲劳性能的试验研究

介绍了对玻璃纤维增强树脂基复合材料层合板疲劳问题的研究。试验采用MTS809液压电磁伺服疲劳试验机,对多种铺层平板试验件进行研究。试验得出不同铺层方向层合板的应力应变、疲劳寿命与加载比的关系曲线,并将试验数据与理论模型预测值进行了对比,分析了玻璃纤维增强树脂基复合材料层合板的疲劳机理。     

国产CCF300碳纤维4轴向无屈曲织物层合板力学性能对比研究

设计制备了两种4轴向碳纤维无屈曲织物(NCF):第一种织物全部采用东丽公司T700 12k碳纤维,第二种织物中66.7%碳纤维采用国产CCF300 3k碳纤维(与东丽T300 3k碳纤维相当)。对该两种织物层合板0°、90°和±45°4个方向的抗拉伸、抗弯曲和抗层间剪切性能进行了测试与对比研究。结果表明:在现有生产条件下,国产CCF300 3k碳纤维最多可以代替4轴向NCF中66.7%的进口T700 12k碳纤维;国产碳纤维NCF层合板各方向归一化后的抗拉伸强度比进口碳纤维NCF层合板低18.7%～26.1%,而其他性能没有显著差别;两种NCF层合板的抗拉伸和抗层间剪切破坏模式相似。     

含预置分层复合材料层合板低速冲击损伤分析

以T300/QY8911碳纤维复合材料层合板为研究对象，利用三维Hashin失效准则对层内损伤进行预测，引入Cohesive界面单元模拟层间分层破坏，使用Camanho刚度退化准则确定材料参数退化方案，并编写了用户材料子程序Vumat，利用ABAQUS软件对预置不同分层损伤复合材料层合板低速冲击过程进行了数值仿真模拟。在冲击载荷作用下研究层合板的动力学响应，得到不同预置分层对层合板总分层损伤面积的影响，同时分析了冲击过程中冲击点位移随时间变化的规律。结果表明：预置分层位置离层合板中间层越远，层合板抵抗冲击承载能力越弱。预置分层的分层数目越多，层合板的刚度越低，层合板抵抗冲击承载能力越弱。在预置分层的两侧，层间分层损伤面积呈塔状分布。含预置分层层合板受到冲击时，预置分层对分层损伤的扩展具有一定的抑制作用。     

国产CCF300碳纤维及CCF300/EH503R3复合材料湿热性能研究

采用SEM、AFM、XPS和FTIR对CCF300碳纤维表面形貌、表面化学特性及碳纤维上浆剂化学特性进行表征,并对CCF300/EH503R3复合材料湿热处理前后的力学性能进行研究。结果表明,碳纤维表面特性对碳纤维与环氧树脂界面结合性能具有显著影响。国产CCF300碳纤维表面粗糙,有明显沟槽,有利于表面机械啮合作用。132℃湿态环境下,复合材料的层间剪切强度、0°压缩强度和开孔压缩强度的保持率分别为51.6%、50.1%和55.5%。试验证明,CCF300碳纤维与EH503R3树脂具有良好的界面结合性,其复合材料具有优异的耐湿热性能。     

2.5维机织复合材料疲劳寿命预测

对2.5维机织复合材料进行了静力分析,在受拉伸载荷的情况下将其视为经纱层和纬纱层组合而成的层合板。以单向板疲劳寿命预测为基础,考虑到疲劳加载过程中刚度退化导致的应力重新分配,采用Miner理论对其拉-拉疲劳寿命进行预测,且对该方法进行了试验验证,为预测2.5维机织复合材料的疲劳寿命提供了一种途径。     

有拧紧力矩复合材料单钉接头疲劳寿命预测

通过对有拧紧力矩复合材料单钉接头疲劳加载过程应力分析及材料三维疲劳失效准则损伤判定,并结合建立的疲劳加载材料退化模型、材料性能退化方法及复合材料接头最终失效判据,建立了基于三维累积损伤分析的层合板接头疲劳载荷作用下寿命预测方法。最后,对拉-拉疲劳载荷作用下有拧紧力矩层合板接头的疲劳寿命及破坏模式进行了模拟分析,并与试验结果进行了对比,结果表明,建立的寿命预测方法能够很好地预测有拧紧力矩复合材料单钉接头的寿命以及破坏模式。     

先进战斗机用复合材料树脂基体

（续4）专家论坛QY8911-Ⅳ/S-2 玻璃纤维复合材料的热导率见表 53。QY8911-Ⅳ/T300 复合材料的常规力学性能见表 54。QY8911-Ⅳ/T300 复合材料同样具有良好的耐湿热性,基耐湿热性能见表 55。QY8911-Ⅳ/T300 复合材料韧性性能见表56。QY8911-Ⅳ为双组份体系,易于存放和取料。组份 A 为棕红色固体,软化点为 60℃～80℃;组份 B 为棕黄色液体。两组份经过熔融法即可配成单组份。该单组份软化点为 30℃～50℃,粘度—温度曲线见图16,它可溶于丙酮配制成真溶液。于 15℃～21℃ 环境下存放期为 3 个月。QY8911-Ⅳ 的固化规范见图 17 …     

T700/LT-03A层合板在不同环境下的拉伸性能研究

在室温、低温和湿热三种环境下,对碳纤维层合板分别开展了静力和拉-拉疲劳试验。得到了T700/LT-03A层合板的拉伸性能和破坏机理。在抗拉强度和抗疲劳性能方面,室温环境优于其它两种环境。试验和模拟结果表明:T700/LT-03A层合板在三种环境下的应力结果较为接近;与室温环境下的结果相比,低温和湿热环境下层合板的应力分别减少了3.37%和4.3%,而湿热环境下层合板的应力增大了5.69%。环境对该层合板的疲劳性能影响较大。研究成果对碳纤维复合材料的工程应用提供一定的参考。     

基于加速试验方法的复合材料长期寿命预测

将跨尺度失效理论(Micro-Mechanics of Failure,简称"MMF")、加速试验方法(Accelerated Testing Methodology,简称"ATM")和渐进损伤分析(Progressive Damage Analysis,简称"PDA")三种方法相结合,提出了一种可以预测复合材料长期寿命和失效过程的分析方法。对MMF失效准则进行改进,区分了基体拉伸和压缩细观失效模式。建立了MMF/ATM/PDA方法有限元计算流程,并在ABAQUS中使用用户自定义材料(UMAT)实现。通过对不同温度下复合材料纵向和横向单向板的拉伸、压缩试验测得静载和疲劳寿命,得到复合材料MMF/ATM细观临界值。采用MMF/ATM/PDA方法对准各向同性开孔板压缩长期寿命进行了预测,并对破坏过程进行了模拟,分析了纤维和基体的失效过程。试验结果和预测结果吻合良好,验证了方法的合理性。     

Fatigue life prediction of matrix dominated polymer composite materials

Fatigue life prediction is investigated analytically for matrix dominated polymer composite laminates having nonlinear stress/strain response, based on the fatigue modulus concept. Fatigue modulus degardation rate at any fatigue cycle was assumed as a power function of number of fatigue cycles. A new stress function describing the relation of initial fatigue modulus and elastic modulus was used to account for material non‐linearity at the first cycle. It was assumed that fatigue modulus at failure is proportional to the applied stress level. A new fatigue life prediction equation as a function of applied stress is proposed. The prediction was verified experimentally using cross‐ply carbon/epoxy laminate (CFRP) tube under torsional fatigue loading. It is shown that the proposed equation has wide applicability and agrees well with experimental data.     

氧化石墨烯改性碳纤维复合材料抗冲击行为研究

使用单层纳米氧化石墨烯（NGO）粒子对环氧树脂进行改性处理,采用真空辅助树脂传递模塑成型工艺制备了[±45/0/90]_2S铺层角度下的纯树脂及单层NGO改性碳纤维复合材料（CFRP）层合板。通过落锤冲击试验、超声C扫描检测、冲击后压缩试验等对纯树脂及单层NGO改性CFRP进行实验研究。结果表明,纯树脂及单层NGO改性CFRP在损伤阻抗及损伤容限实验中均存在拐点现象,且拐点出现在相同深度位置,其中纯树脂CFRP拐点位置为0.51 mm,单层NGO改性CFRP拐点位置为0.43 mm;相对于纯树脂CFRP,单层NGO改性CFRP可以显著提高复合材料的抗冲击性能及冲击后的压缩性能;通过对冲击后凹坑深度及凹坑面积进行数据模拟,可以用拟合公式实现对复合材料的损伤预测。     

On the longitudinal compressive strength prediction of unidirectional laminated composites based on an improved model

The compressive failure of unidirectional (UD) composite laminates is investigated using an improved model. Most of the existing models to predict the compressive strength of UD composites are either based on microbuckling or kinking of fibers. However, the failure mechanism analysis based on the SEM microscopy observations of failed specimens shows that the two mechanisms are responsible for the failure simultaneously when kinking occurs following the microbuckling of fibers. Therefore, the fiber microbuckling and fiber kinking models are combined to predict the compressive strength of UD T300/QY8911 composite laminate. Furthermore, this study proposes a new model for the stiffness of the foundation determination, making the predicted microbuckling strength closer to its real value. Also the effects of parameters presented in the prediction formula on the compressive strength are discussed, and it is found that the Young's modulus of matrix is the most important parameter. The predicted compressive strength using the improved model with combined modes shows a very good agreement with the experiment measurement. POLYM. COMPOS., 2011. © 2011 Society of Plastics Engineers     

Strength degradation and fractographic analysis of carbon fiber reinforced polymer composite laminates with square / circular hole using scanning electron microscope micrographs

In this article, experimental study has been carried out to obtain comparative information intended for designing and assembly of structural components made of carbon fiber reinforced polymer (CFRP) composite. Investigation on tensile strength has been done on unidirectional CFRP composite laminates with hole. Effect of stacking sequence, hole size, and hole shape on tensile strength has been examined independently by open hole tensile (OHT) test. Reduction in OHT strength is observed when stacking sequence is changed from [0]₈ to [0/90]_2s and when the hole size is increased. However, OHT strength is noticed to get increased when hole shape is changed from circular to square. Laminates containing square shaped hole demonstrate less sensitiveness towards tensile strength and show negligible effect of stacking sequences on the normalized strength than the circular hole. Fractographic analysis figures out the failure mechanism of tested specimens by correlating their mechanical properties. SEM micrographs and data analysis reveal that axial splits and local delamination effectively blunt the stress concentration around the hole resulting in higher OHT strength and less notch sensitiveness towards tensile strength.     

Numerical analysis of parametric effects on consolidation of angle‐bended composite laminates

In the previous study, the finite element formulation has been developed by our group based on two‐dimensional resin flow and fiber compaction model. Good agreement between simulations and experimental results was found under the one‐dimensional flow condition. In this article, the two‐dimensional model was used to simulate the consolidation of angle‐bended laminates with the convex tool in autoclave process. The effects of material properties on the consolidation were studied. It was found that the fiber bed shear modulus significantly affects the compaction behavior in the corner section of angle‐bended laminate, the fiber bed compaction property decide the laminate deformation, and the resin viscosity and fiber bed permeability affect the rate of laminate compaction and consolidation time. The angle‐bended T700/BMI QY8911‐Ilaminates were manufactured in autoclave process. The experimental data validate the numerical simulation method for the consolidation of the angle‐bended laminates. These results are greatly helpful for the optimization of processing parameters, improvement of composite parts quality, and reduction of the fabrication cost. POLYM. COMPOS., 2009. © 2008 Society of Plastics Engineers     

Delamination growth during fatigue of advanced polymer matrix composites

Abstract

Advanced polymer matrix composites such as carbon fibre reinforced polymers (CFRP), offer many advantages over more traditional materials such as metals. Usually, CFRP have greater strength/weight and stiffness/weight ratios than traditional engineering materials, which makes them ideal for use in many weight sensitive applications, especially in the aerospace sector. To maximise the use of these materials there is a need to gain a better understanding of how CFRP, and more generally FRPs, behave under fatigue load conditions. This work investigates the fatigue response and damage mechanisms found in a CFRP. Previous work has highlighted that fatigue with a compressive element is more damaging than pure tensile fatigue and that delamination is the dominant damage mechanism in both cases. However, in the tensile fatigue tests the primary delamination was on a different interface from the primary delamination found in the compression fatigue tests. The cause of this trend to delaminate along a particular interface has been investigated using mixed mode bend tests. These tests have been used to investigate the response of the interface to both static and fatigue loads. Initial tests have been carried out on the 0°/45° interface. Delamination growth was monitored at three levels of mode mixity, ratios of MI/MII of 1:1, 1:3 and 3:1. PRC/1848     

Research on the mechanical properties prediction of carbon/epoxy composite laminates with different void contents

The influence of the porosity on the static mechanical strength of the carbon fiber fabric reinforced epoxy composites laminates was investigated. The tensile, compressive, bending, and interlaminar strength test on the CFRP laminates with porosity of 0.33% and 1.50% were conducted and simulated by a finite element analysis model. The article proposes the failure criterion of the static mechanical strength of the fabric fiber reinforced composites based on the improved Hashin failure criterion that is suitable for the undirectional composite laminates. The basic composite strength parameters are used to evaluate the mechanical properties of CFRP laminates with different porosities. A finite element analysis model is established by using software ABAQUS™ combined with the sudden stiffness degradation model. The experiment results show that the tensile, compressive, bending, and interlaminar strength decrease with the increasing porosities. The tensile, compressive, bending, and interlaminar strength of the fabric carbon fiber reinforced epoxy composites laminates are simulated accurately by the finite element model. POLYM. COMPOS., 14–20, 2016. © 2014 Society of Plastics Engineers     

Fatigue behavior of quasi-isotropic carbon fiber/PEEK laminates under tension-tension loading

Fatigue behavior of carbon fiber reinforced poly(etheretherketone)(PEEK) laminates was investigated. The static tensile measurement, tension-tension fatigue loading tests, and residual tensile strength measurement of the [0/45/90/-45]_2s AS-4/PEEK laminates were performed at various levels of stress amplitudes. The influences of stress amplitude on the fatigue life and the residual tensile strength were investigated. The experimental results for fatigue life and residual tensile strength under different stress amplitudes are analyzed by the median rank method. The S-N curves at various survival probabilities are also presented by the pooled Weibull distribution function. Furthermore, a residual strength degradation model is used to predict the residual strength for the composites subjected to a number of fatigue cycles and to simulate the effects of the stress amplitude on the fatigue life. The agreement between experiment and theory is good.