压缩预应力对复合材料层板抗冲击损伤性能的影响

为确定压缩预应力对复合材料层板抗冲击损伤性能的影响,首先对不同压缩预应力下的碳纤维/双马树脂CCF300/5428层板进行了低速冲击和准静态压痕试验,然后通过热揭层和冲击后压缩试验分别得到了层板分层面积和剩余强度。结果表明:压缩预应力会大幅降低层板的接触刚度和弯曲刚度,从而导致相同冲击能量下层板凹坑深度和背部基体开裂长度增大;对于准静态压痕过程和相同冲击能量下的冲击过程,分层起始载荷和峰值载荷均随压缩预应力的增大而减小;在相同冲击能量下,随着压缩预应力的增大,层板内部分层总面积及冲击能量吸收比不断增大,剩余压缩强度不断降低。因此,压缩预应力会降低复合材料层板的冲击损伤阻抗,对损伤容限性能不利,在对承受压缩载荷结构的试验验证过程中应考虑压缩预应力对抗冲击损伤性能的影响。      

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。      

含低速冲击损伤复合材料层合板剩余压缩强度及疲劳性能试验研究

对T300/QY8911复合材料层板进行了低速冲击、 冲击后压缩以及冲击后疲劳试验研究。通过对冲击后的层板进行目视检测和超声C扫描获得了层板受低速冲击后的若干损伤特征; 在压-压疲劳试验中, 测量了损伤的扩展情况。讨论了冲击能量与损伤面积以及冲击后剩余压缩强度的关系, 分析了含冲击损伤层合板在压缩载荷及压-压疲劳载荷下的主要破坏机制。结果表明, 低速冲击损伤对该类层板的强度和疲劳性能影响很大, 在3.75 J/mm的冲击能量下, 层板剩余压缩强度下降了65%; 在压-压疲劳载荷作用下, 其损伤扩展大致可分为两个阶段, 占整个疲劳寿命约60%的前一阶段损伤扩展较为缓慢; 而疲劳寿命的后半阶段损伤则开始加速扩展, 并导致材料破坏。     

Tension fatigue analysis and life prediction for composite laminates

A tension fatigue life prediction methodology for composite laminates is presented. Tension fatigue tests were conducted on quasi-isotropic and orthotropic glass epoxy, graphite epoxy, and glass/graphite epoxy hybrid laminates. Edge delamination onset data were used to generate plots of strain energy release rate as a function of cycles to delamination onset. These plots were then used along with strain energy release rate analyses of delaminations initiating at matrix cracks to predict local delamination onset. Stiffness loss was measured experimentally to account for the accumulation of matrix cracks and for delimination growth. Fatigue failure was predicted by comparing the increase in global strain resulting from stiffness loss to the decrease in laminate failure strain resulting from delaminations forming at matrix cracks through the laminate thickness. Good agreement between measured and predicted lives indicated that the through-thickness damage accumulation model can accurately describe fatigue failure for laminates where the delamination onset behaviour in fatigue is well characterized, and stiffness loss can be monitored in real time to account for damage growth.     

含矩形边缘分层缺陷层合板的压缩性能

对含矩形边缘分层缺陷层合板的压缩性能进行试验研究和理论分析, 考察了层合板厚度(含铺层形式)、 分层位置、 形状、 面积以及环境等因素对压缩强度的影响, 并采用分层扩展以及软化夹杂两种模型对含分层层合板的压缩强度进行了计算和破坏机理分析。结果表明: 厚板对边缘分层缺陷不敏感, 中等厚度和薄层合板比较敏感; 缺陷的位置和形状对层合板压缩强度有一定的影响; 湿热环境改变了含缺陷板的压缩破坏机理, 并对中等厚度板和薄板的压缩强度有明显的影响。两种模型中软化夹杂模型效果较好, 可用于工程设计计算。      

碳纤维织物布层压复合材料湿热环境疲劳后剩余压缩强度

为了研究湿热环境对碳纤维织物布层压复合材料疲劳性能的影响,开展了碳纤维织物布含中心孔层压板疲劳试验和剩余压缩强度试验,并为湿热环境拉-压疲劳试验自行设计了湿热环境试验箱。参照ASTM标准设计加工了疲劳试验夹具和压缩试验夹具,分别在标准环境条件(温度(23±2)℃、相对湿度(50±5)%RH),湿热环境条件(温度(70±2)℃、相对湿度(85±5)% RH)下对试件进行拉-压疲劳试验,之后分别进行了剩余压缩强度试验。以标准环境疲劳试验件的剩余压缩强度为基准值,对比湿热环境疲劳试验件的破坏载荷对应的极限压缩强度,计算其与基准值的差值。通过试验结果对比,得到湿热环境下试验件疲劳后剩余压缩强度下降了14%,该湿热环境对载荷谱下的碳纤维织物布层压复合材料试验件疲劳后剩余压缩强度影响较小。      

复合材料层压板剩余刚度剩余强度关联模型

基于剩余强度和剩余刚度取决于同一损伤状态的假设,给出了基于剩余刚度的损伤定义和基于剩余强度的损伤定义之间的关系,建立了剩余刚度剩余强度关联模型。用3种不同铺层形式的层压板试验数据对本文中提出的剩余刚度模型及剩余强度模型进行了验证,结果表明:本文中提出的剩余刚度和剩余强度模型能很好地描述复合材料层压板疲劳过程中的剩余刚度和剩余强度退化规律;通过关联模型,可以在已知剩余刚度退化规律的前提下,用少量剩余强度试验确定剩余强度退化规律;与剩余刚度关联的剩余强度模型中的参数可以被认为是材料常数。      

复合材料加筋板低速冲击损伤及剩余压缩强度试验研究

采用落锤法对复合材料加筋板进行了低速冲击损伤（LVI）试验,根据复合材料加筋板构型,设计了冲击支持支架,研究了支持支架的间距对冲击结果的影响;用相同的冲击能量对复合材料加筋板结构中3处典型位置进行冲击,得到不同位置的损伤形貌;分别对完好件和损伤试验件进行压缩试验,将试验结果进行对比,分析不同位置的冲击损伤对结构压缩性能的影响。试验结果表明：在相同的冲击能量下,支持支架间距越小,所造成的冲击损伤越严重;在50 J冲击能量下,筋条区蒙皮处的冲击所造成的损伤不易观察,筋条间蒙皮处的冲击所造成的损伤最为明显,而筋条边缘蒙皮处的冲击可以导致筋条边缘的脱粘;冲击损伤会使加筋板屈曲载荷轻微下降,筋条间蒙皮和筋条区蒙皮冲击损伤对压缩结果影响相对较小,筋条边缘处的冲击会引起损伤处蒙皮的子层屈曲,并影响结构破坏形式,使结构压缩承载能力有较为明显的下降。     

Fatigue life prediction of woven composite laminates with initial delamination

An engineering approach for fatigue life prediction of fibre‐reinforced polymer composite materials is highly desirable for industries due to the complexity in damage mechanisms and their interactions. This paper presents a fatigue‐driven residual strength model considering the effect of initial delamination size and stress ratio. Static and constant amplitude fatigue tests of woven composite specimens with delamination diameters of 0, 4 and 6 mm were carried out to determine the model parameters. Good agreement with experimental results has been achieved when the modified residual strength model has been applied for fatigue life prediction of the woven composite laminate with an initial delamination diameter of 8 mm under constant amplitude load and block fatigue load. It has been demonstrated that the residual strength degradation‐based model can effectively reflect the load sequence effect on fatigue damage and hence provide more accurate fatigue life prediction than the traditional linear damage accumulation models.     

A prediction method for the compressive strength of impact damaged composite laminates

An analytic method for the prediction of the compressive strength of composite laminates containing impact damage has been developed. Using the characteristics of the impact damage detected by the ultrasonic time-of-flight C-scan technique, the state of the damage is modelled by an elliptical soft inclusion. The degradation of the elastic moduli of the material in the inclusion is determined by a sublaminate buckling analysis. The stress distribution in the laminate containing the inclusion with the reduced moduli is determined using a complex potential method and the stress results are used in conjunction with three failure criteria to predict the residual compressive strength. Compression-after-impact tests on flat laminates manufactured from the Toray T800H/ 3900-2 material have been conducted to produce experimental results for validating the analytical method. Good agreements between predicted residual compressive strengths and experimental results have been obtained.     

Z-pin增强复合材料层合板断裂韧性试验研究

针对Z-pin增强复合材料层合板, 开展了断裂韧性的试验研究。研究选取了3种Z-pin直径(0.28、 0.52、 0.80mm)且每种直径下分别以3种分布形式(5×5、 8×8、 10×10)排布Z---pin的增强方式, 为了确定比较基准, 试验中同时测试了不含Z-pin的复合材料层合板试样。通过Z-pin拔出试验测试了3种直径Z-pin从基体拔出过程中的载荷位移关系。利用双悬臂梁试验和端部开口弯曲试验分别测试了不含Z-pin和含Z-pin试样的Ⅰ型断裂应变能释放率G_ⅠC、 Ⅱ型断裂应变能释放率G_ⅡC。试验结果表明:? 与不含Z-pin的结构相比, Z-pin增强试样的Ⅰ型断裂应变能释放率G_ⅠC增大了83%~1110%, Ⅱ型断裂应变能释放率G_ⅡC增大了23%~438%; 在相同Z-pin体积含量下, 与增大Z-pin直径相比, 增大Z-pin分布密度能更有效地提高复合材料层合板的断裂韧性。      

Effect of fibre/matrix adhesion on residual strength of notched composite laminates

Effects of fibre/matrix adhesion and residual strength of notched polymer matrix composite laminates (PMCLs) and fibre reinforced metal laminates (FRMLs) were investigated. Two different levels of adhesion between fibre and matrix were achieved by using the same carbon fibres with or without surface treatments. After conducting short-beam shear and transverse tension tests for fibre/matrix interface characterisation, residual strength tests were performed for PMCLs and FRMLs containing a circular hole/sharp notch for the two composite systems. It was found that laminates with poor interfacial adhesion between fibre and matrix exhibit higher residual strength than those with strong fibre/matrix adhesion. Major failure mechanisms and modes in two composite systems were studied using SEM fractography. The effective crack growth model (ECGM) was also applied to simulate the residual strength and damage growth of notched composite laminates with different fibre/matrix adhesion. Predictions from the ECGM were well correlated with experimental data.     

复合材料层板冲击后压缩强度经验预测公式

复合材料被广泛应用于飞机结构中,其损伤容限性能是飞行器设计的重要指标。提出了一种基于冲击能量预测复合材料层板受冲击后剩余压缩强度的经验预测公式,并通过试验方法分析了剩余强度的影响因素,确定了经验公式形式与参数,对经验公式预测结果进行了验证。经过一定量的试验验证,本文所提出的经验预测方法的预测结果与试验结果吻合良好,研究结果表明,该方法是一种简便迅速的剩余强度工程预测方法。试验结果表明：剩余强度与冲击能量的关系适合采用分段幂函数进行拟合;冲击能量、层板厚度、铺层比例和韧性对复合材料层板冲击后压缩强度有较明显的影响,而冲头直径对剩余强度的影响不显著。     

对称角铺设矩形复合材料叠层板受低速冲击时的应力波传及解层破坏分析

采用碰撞力分段模型和一阶剪切理论分析了给定初始速度的铁球与四边简支的复合材料叠层板中心发生碰撞的动力学行为,包括碰撞力及接触时间的变化规律、叠层板的振动响应、应力波传、表面沉陷等。并根据忽略厚度的界面模型假设及简化的Tsai Wu张量理论对复合材料叠层板的解层破坏进行了计算和分析,并给出了破坏区大小与铁球初始速度的关系。研究表明:碰撞力与铁球的初始速度成正比;复合材料叠层板中应力波传沿固定方向的相速度在各层内相同,拉伸应力波传速度沿纤维总体占优的方向大于其垂直的方向,而剪切应力波传速度则相反。即使在较低的初始碰撞速度下, 复合材料叠层板的解层破坏也很明显,并且破坏区域随初始碰撞速度的增大而不断扩展,其形状也会发生改变。      

碳纤维复合材料层合板压缩性能的相关影响因素

碳纤维作为一种新型的增强材料,具有优良的理化性能,已在多个领域广泛应用.由于单向碳纤维复合材料层合板的压缩强度较低,其在结构复合材料方面的应用受到限制,提高其压缩性能成为关键.本文综述了影响碳纤维复合材料层合板压缩性能的相关因素,详细介绍了纤维弯曲、孔隙率、纤维体积分数、树脂性能等影响因素对碳纤维复合材料层合板的重要性,以及各影响因素之间的关系等,为提高碳纤维复合材料层合板压缩性能的研究提供了参考.     

面内损伤对埋藏分层影响的三维有限元分析

运用大型有限元软件ANSYS,基于复合材料层合板损伤理论,建立了含面内损伤和埋藏分层的复合材料层板三维有限元模型.分析了面内损伤对复合材料层板分层的影响.采用三维Hashin准则预测复合材料损伤,分层区损伤采用多种损伤模型,损伤发生后,认为材料仍连续,并修改损伤单元对应的材料参数.通过虚拟裂纹闭合技术（VCCT）计算分...     

Mixed-mode delamination growth of laminar composites by using three-dimensional finite element modeling

ABSTRACT Delamination is one of the most frequent failure modes in laminated composites. Its importance is crucial, because a delamination can occur in the interior of a panel without any noticeable damage on the surface, drastically reducing its strength and stiffness. A study has to be made on critical dimensions of delaminations and their shape, through the calculation of the strain energy release rate (SERR), G. This study was performed numerically, for a given geometry, with varying loads and shapes of delamination, in pure and mixed‐mode propagation. All numerical values were obtained with three‐dimensional finite element (FE) analyses from a commercial package. The use of three‐dimensional analyses in simple geometries helps establish the basis for the more complex ones, and the correspondence with the usual analytical or numerical bi‐dimensional plane‐strain analysis. The conclusions were (a) G is not constant along the crack tip, even for mode I propagation and straight crack tip; (b) the mean value of G obtained from a three‐dimensional analysis equals the value obtained in bi‐dimensional plane‐strain analysis; (c) in mixed‐mode propagation, the method exhibits a good correlation with experimental results and (d) the shape and mode partitioning of the SERR depend not only on the loading, but also on the shape of the crack front.     

Effects of temperature on impact damages in CFRP composite laminates

In this paper, the effect of temperature variations (low and high temperatures) was studied experimentally on impact damage to CFRP laminates. The composite laminates used in this experiment were CF/EPOXY orthotropic laminated plates with lay-up [0₆/90₆]_s and [0₄/90₄]_s, and CF/PEEK orthotropic laminated plates with a lay-up of [0₆/90₆]_s. A steel ball launched by the air gun was used to generate the CFRP laminate impact damage. For impact-damaged specimens, nondestructive evaluation (NDE), such as a scanning acoustic microscopy (SAM) was performed on the delamination-damaged samples to characterize damage growth at different temperatures.

Therefore, this study was undertaken to experimentally determine the interrelations between impact energy and impact damage (i.e. the delamination area and matrix) of CFRP laminates (CF/EPOXY and CF/PEEK) subjected to foreign object damages (FOD) at low and high temperatures.     

Effect of mode III fracture on composite laminates

The digital speckle correlation method (DSCM) is preformed to study the inplane displacements along the x and y direction of laminated composite panels containing preset elliptical damage. The different principle axis of the ellipse and the different sequence of laminates are considered in the experiments. It is shown that the method is very useful to get the displacements on the laminate surface and between the adjacent plies. According to the experiment results, the deformations of x and y direction can be obtained. The conclusion that the mode III fracture may exist and may have an effect on the crack growth is formed. The total strain energy release rate is calculated by the finite element method. Using Mindlin plate theory and the virtual crack closure technique, the energy release rate of mode III fracture can be calculated by FEM. The results show that mode III fracture has an influence on the total energy release rate and also on the delamination growth. The energy release rate of mode III fracture cannot be ignored. The delamination growth also is influenced by the stacking sequence.     

含冲击损伤复合材料层压板压缩破坏机制试验研究

为了研究含冲击损伤复合材料层压板的压缩破坏机制, 通过前后表面超声C扫描获得分层损伤在层压板内的分布情况, 使用应变片获取层压板两面的应变场, 采用声发射观察层压板压缩破坏过程。研究发现: 冲击分层损伤在厚度方向上的非对称分布引起层压板内部出现严重的应力集中, 致使纤维断裂并最终导致层压板整体破坏; 导致含冲击损伤层压板压缩破坏的主要原因为纤维断裂而非分层扩展。