复合材料冲击损伤高分辨率超声成像检测与损伤行为分析

冲击损伤是复合材料结构易产生的一种危害性缺陷,针对碳纤维复合材料层压结构特点,分析脉冲超声波在复合材料中的反射特性,当能减小入射声波脉冲的时域占宽,提高其品质,可显著改善超声检测表面盲区和纵向分辨率。利用入射声波在冲击损伤区形成的反射信号及其渡越时间可确定冲击损伤的深度和大小。研究采用高分辨率脉冲超声B扫描和层深C扫描(T扫描)成像方法,可揭示复合材料内部冲击损伤及其大小与沿厚度方向的分布特征,进行复合材料冲击损伤量化评估与损伤行为可视化分析。试验结果表明,在入射脉冲单周脉冲特性条件下,当来自复合材料缺陷的回波信号的渡越时间达到入射声波脉冲时域占宽的一半左右时,即可清晰地提取到时域可分辨的缺陷回波信号,使超声检测表面盲区和纵向分辨率达到单个复合材料预浸料铺层的厚度,约0.13 mm。利用超声断面B扫描成像,可以形象地再现复合材料中冲击损伤的断面分布与扩展情况以及损伤的深度等确切信息。采用超声T扫描成像,则可以直观地再现冲击损伤在复合材料铺层方向的分布及其损伤区域(面积)等定量信息。二者的结合则为揭示复合材料冲击损伤的3D分布及其特征提供一种超声成像检测量化评估和损伤行为可视化分析方法。     

泡沫夹层复合材料与复合材料层合板低速冲击性能的比较

采用[0°]8,[0°,90°]2s方式铺成的碳纤维增强环氧树脂预浸料作为泡沫夹层复合材料的面板,PMI(聚甲基丙烯酰亚胺)泡沫作为芯材,制得泡沫夹层复合材料(12mm厚);采用相同预浸料和[0°]16,[0°,90°]4s的铺层方式制备了复合材料层合板(2mm厚),对比研究了两种复合材料的低速冲击性能。结果表明:无论是泡沫夹层复合材料还是复合材料层合板,正交铺层结构比单向铺层结构的冲击载荷峰值高,冲击损伤程度小,抗冲击能力好;在两种铺层方式下,泡沫夹层复合材料的抗冲击能力明显优于复合材料层合板的。     

基于超声复解析信号的碳纤维层压复合材料检测方法研究

采用超声波检测碳纤维层压复合材料时,换能器将接收到层间产生的反射信号。为了有效利用层间反射信号表征碳纤维层压复合材料内部树脂及纤维铺层的几何状态,开展基于超声复解析信号的检测方法研究。介绍超声复解析信号的基本理论,阐述其相对原始A型信号的优势;定义用于成像的复解析信号表征参量,设计基于表征参量的检测成像算法,采用简化声学模型分析碳纤维层压复合材料微观结构超声响应对表征参量的影响;针对包含冲击损伤的碳纤维增强复合材料层压板开展阵列超声检测试验,试验结果表明基于超声复解析信号的检测成像方法可清晰观测出碳纤维层压复合材料微观结构内部的纤维铺层几何形态,基于原始A型信号的检测成像方法无法有效观测,超声复解析信号具有用于表征评价复合材料脱层、褶皱等缺陷的巨大潜力。     

预浸料放置时间对芳纶复合材料层间剪切强度影响作用研究

芳纶Ⅲ复合材料制品的性能受成型工艺参数影响，通过对预浸料成型工艺流程分析，发现预浸料的放置时间为影响芳纶Ⅲ复合材料层间剪切强度(Interlaminar Shear Strength, ILSS)的主要参数。为了研究预浸料放置时间对芳纶Ⅲ复合材料层间剪切强度的影响规律和敏感度，采用短梁法层间剪切实验方法，获得预浸料不同放置时间情况下所对应的强度数值。根据实验数据建立该工艺参数对层间剪切强度的回归模型，通过对残差、预测值与实际值对比等检验分析，验证回归模型的可靠性及有效性。使用该回归模型能够准确地给出预浸料不同放置时间下芳纶Ⅲ复合材料的层间剪切强度，并且获得单参数灵敏度曲线。通过对灵敏度曲线的分析，可以确定参数的稳定性和不稳定性范围。实验结果表明，随着放置时间的增长，芳纶Ⅲ复合材料层间剪切强度呈现先增大后减小的趋势，0°/0°、0°/90°、±45°铺层情况对应的预浸料最佳放置时间在10～22 h内，在这一工艺参数范围内可以保证芳纶Ⅲ复合材料具有最大层间剪切强度。     

孔口缝合补强对层间应力影响的数值模拟

使用空间杆单元模拟缝合线,对含孔复合材料层合板开口缝合补强结构进行有限元模拟计算。研究含孔复合材料层合板在轴向拉伸载荷作用下,圆孔附近各个铺层交界面处层间正应力和剪应力的分布情况,将缝合后的层间应力值与缝合前的相关数值进行比较,并研究不同缝合参数(针距、行距、边距、单缝合和双缝合)对孔边层间应力的影响。结果表明,缝合补强后孔边的层间应力明显减小。孔边附近层间应力的分布与相邻铺层的铺层角有很大关系,不同铺层之间的层间应力有显著差别。不同铺层之间的层间应力沿孔边区域存在应力转换点(即层间应力由正值变为负值)。     

复合材料层合板冲击后疲劳寿命试验研究与数值模拟

通过对复合材料典型层合板进行落锤冲击试验引入冲击损伤,并对冲击后的复合材料层合板进行不同载荷水平的压-压疲劳试验,得到了不同疲劳载荷作用下层合板损伤扩展规律及疲劳寿命。建立了冲击后层合板疲劳寿命有限元数值计算模型,对层合板进行冲击仿真,并利用有限元软件用户子程序编程,将冲击后计算所得损伤分布结果设置为层合板压—压疲劳寿命计算的起始状态,从而获得层合板在不同疲劳载荷水平下的损伤扩展结果及压—压疲劳寿命数值仿真结果。将试验与有限元数值计算疲劳寿命结果绘制了S-N曲线,通过对比验证了计算结果的准确性,形成一套复合材料层合板冲击后疲劳寿命预测数值计算模型。     

树脂固化温度与纤维铺设方式对C/E复合材料制孔质量的影响

在碳纤维树脂复合材料制备及加工过程中均较容易产生各种缺陷,并影响构件最终的加工质量及使用性能.为研究碳纤维树脂复合材料制备过程中产生的缺陷对制孔出口质量的影响,提出一种通过改变预浸料固化温度模拟材料制造缺陷的方法,并对不同温度固化和不同方式铺设的样件进行了模拟制孔试验,分析剩余刚度对材料内部缺陷扩展及制孔出口质量的影响...     

变截面舵类零件复合材料成型工艺研究

以某产品舵复合材料成型工艺方案和模具方案为研究对象,对方案进行实际应用和成品检测,结果证明该模具结构合理、操作方便,且铺层设计合理,成型加工零件满足图纸、技术文件要求,可广泛适用于树脂基复合材料舵类零件的工艺设计与模具设计加工中,为树脂基复合材料舵类预浸料层压零件的铺层工艺设计、模具结构设计和加工奠定基础。     

复合材料夹芯结构低速冲击性能研究

复合材料夹芯结构为电子设备与外层蒙皮提供了一体化设计的思路,可以大幅降低飞行器的结构重量。通过低速冲击试验和ABAQUS仿真研究了5 J和10 J冲击能量下某飞行器复合材料机翼蒙皮典型夹芯区域在低速冲击下的性能。随着冲击能量的增加,复合材料泡沫夹芯结构的能量吸收率由5 J的72.0%提升至10 J的76.0%。由仿真结果可知,当冲击能量达到10 J时,出现了纤维损伤,且损伤沿表层铺层角度扩展,基体压缩损伤主要出现在冲击正面,基体拉伸损伤主要出现在冲击背面,损伤随冲击能量的增加而变大。当冲击能量达到10 J时,上面板与泡沫芯体粘接处也产生了较大的损伤。     

基于非线性Lamb波二阶谐波的复合材料冲击损伤检测

为避免复合材料受冲击产生微裂纹而导致结构破坏,需评估受低速冲击的复合材料损伤程度。采用Lamb波二阶谐波法,挑选合适模态,对受不同能量冲击损伤的复合材料试样进行检测,并与无损伤试样进行对比。结果表明,非线性Lamb波二级谐波可检出复合材料低速冲击,且非线性参数与冲击能量成正相关。     

基于应变损伤模型的复合材料层合板低速冲击数值模拟

提出了一种基于应变的复合材料损伤模型,考虑了复合材料冲击过程中出现的面内纤维断裂与压缩,基体开裂与挤裂。在使用Abaqus软件进行数值模拟计算时,自编的用户子程序VUMAT和Cohe-sive模型分别实现了复合材料面板的损伤和层间分层。通过对层合板在不同能量下的低速冲击的有限元模拟发现,模拟得到的分层损伤形状和面积、冲头最大挠度、接触力和凹坑深度都与试验结果吻合较好。     

Ultimate strength of composite laminates with free-edge delamination

The present paper deals with the free edge effect of composite laminates by using a generalized quasi-three dimensional analysis and experimental verification of an analysis performed for laminates with Teflon inserted on interfaces to simulate initial free-edge delamination. We performed tensile tests for laminates [30₂/?30₂/90]_s carbon-epoxy laminates with free-edge delamination under uniaxial tension. The experiment reveals that extensional stiffness of the laminate decreases by the initiation of the delamination, and that strength of the laminate without delamination is smaller than that of the laminates with delamination. Generalized quasi-three dimensional finite element technique, which employs energy release rate and maximum stress criteria, is developed to estimate behavior of the laminate after initial delamination. The numerical result by use of this technique predicts the ultimate strength of the laminates with sufficient accuracy according as the comparison with an experimental stress-strain curve. In the experiment conducted both for the laminate with initial delamination and the laminate without initial delamination, an unexpected results were obtained that is the ultimate load of the laminate without initial delamination was lower than that of the laminate with initial delamination. We presented clear explanation on the phenomenon occurred and developed the method to predict the nonlinear behavior of the laminate with or without initial delamination.     

Damage detection in multilayered fiber–metal laminates using guided-wave phased array

This study employs the Lamb wave method to detect damage in Fiber–metal laminates (FMLs). The method is based on quasi-isotropic behavior approximation and beamforming techniques. Delay and sum and minimum variance distorsionless response beamformers are applied to a uniform linear phased array. The simulation in finite element software is conducted to evaluate the performance of the presented procedure. The two types of damage studied are the following: (1) Delamination between fiber–epoxy and metal layers and (2) crack on the metal layer. The present study has the following important contributions: (1) Health monitoring of multi-damaged FMLs using Lamb waves and beamforming technique, (2) detection of damage type, (3) detection of damage size by 1D phased array, and (4) identification of damages that occurred very close to the laminate edges or close to each other.     

Modélisation,identification et simulations éléments finis des phénomènes de délaminage dans les structures composites stratifiées

Modelling, identification and finite element predictions of delamination in laminated composite structures. In order to forecast the delamination initiation and propagation in a finite element context, a previously defined damage meso-modelling of composite laminates is used. At the meso-level, the laminate is described as an assembly of damageable layers and interlaminar interfaces. The present work concerns the modelling, the identification and the finite element predictions of delamination phenomena in composite structures. Finite element predictions are conducted with non-linear geometric and material hypothesis. The interface modelling is implemented in the finite element code Castem 2000 developped by CEA. Classic edge delamination tension and propagation tests are conducted in order to improve the interface damage model approach in the finite elements context.     

基于HyperWorks 的不同铺层方式复合材料剪切强度有限元分析

剪切强度和剪切韧性是反映复合材料构件在复合受力状态下承载能力及耗能能力的重要指标,不同铺层方式的单向玻璃纤维与短切玻璃纤维混杂增强复合材料层合板的层间剪切性能有明显差异。文中基于HyperWorks 商用有限元软件建立了精确的复合材料层合板模型,通过数值模拟分析不同铺层方式复合材料层合板的层间剪切性能。研究结果表明,铺层材料对复合材料层合板的层间剪切性能影响较大,而铺层顺序对复合材料层合板的层间剪切性能影响较小。     

不同铺层转角T700/E44 复合材料拉伸强度有限元分析

碳纤维复合材料的失效行为与复合材料内部的应力状态有关,不同铺层转角的单向碳纤维复合材料层合板的性能具有明显差异。文中利用HyperWorks 商用有限元软件建立了T700/E44 复合材料层合板拉伸模型,基于Chang-Chang 复合材料失效模型对不同铺层转角复合材料层合板的 X 向及 Y 向拉伸性能进行了数值模拟分析。研究结果表明,复合材料层合板以45° 铺层转角对称结构层合时,复合材料有着最佳的综合拉伸性能。这对高性能雷达中复合材料部件的铺层结构设计具有重要的指导意义。     

复合材料层合板准静态压痕损伤实验研究与数值模拟

对复合材料层合板准静态横向压缩特性损伤进行了研究。在损伤模拟过程中采用机体开裂和分层扩展判据,分类考虑了不同的损伤形式,通过修正损伤层材料的常数来模拟层板损伤所造成的局部刚度下降对横向压痕过程的影响。损伤模拟结果与超声C扫描的结果吻合较好。     

Interlaminar stress analysis of general composite laminates

In this study, based on the reduced from of elasticity displacement field for a long laminate, an analytical method is established to exactly obtain the interlaminar stresses near the free edges of generally laminated composite plates under the extension and bending. The constant parameters, which describe the global deformation of a laminate, are properly computed by means of the improved first-order shear deformation theory. Reddy's layerwise theory is subsequently utilized for analytical and numerical examinations of the boundary layer stresses within arbitrary laminated composite plates. A variety of numerical results are obtained for the interlaminar normal and shear stresses along the interfaces and through the thickness of laminates near the free edges. Finally the effects of end conditions of laminates on the boundary-layer stress are examined.     

Damage localization using experimental modal parameters and topology optimization

This work focuses on the development of a damage detection and localization tool using the topology optimization feature of MSC.Nastran. This approach is based on the correlation of a local stiffness loss and the change in modal parameters due to damages in structures. The loss in stiffness is accounted by the topology optimization approach for updating undamaged numerical models towards similar models with embedded damages. Hereby, only a mass penalization and the changes in experimentally obtained modal parameters are used as objectives. The theoretical background for the implementation of this method is derived and programmed in a Nastran input file and the general feasibility of the approach is validated numerically, as well as experimentally by updating a model of an experimentally tested composite laminate specimen. The damages have been introduced to the specimen by controlled low energy impacts and high quality vibration tests have been conducted on the specimen for different levels of damage. These supervised experiments allow to test the numerical diagnosis tool by comparing the result with both NDT technics and results of previous works (concerning shifts in modal parameters due to damage). Good results have finally been achieved for the localization of the damages by the topology optimization.