纤维增强复合材料层板高速冲击损伤数值模拟

推导了复合材料应变率相关三维本构关系, 并将其用于复合材料层板高速冲击损伤的数值模拟。该模型在复合材料层间引入界面单元模拟层间分层, 结合三维Hashin失效准则进行单层板面内损伤识别, 引入材料刚度退化, 采用非线性有限元方法, 研究了复合材料层板高速冲击的破坏过程及层板的损伤特性。数值分析结果表明, 剩余速度预报结果与实验结果吻合较好, 层板的主要损伤形式是层间分层、 基体微裂纹和纤维断裂, 减小弹体直径、 增大铺层角度和层板厚度能够有效降低层板损伤面积。      

碳纤维增强树脂复合材料-热成型钢超混杂层合板层间力学性能

通过双悬臂梁试验(DCB)研究了金属表面处理和界面插层协同作用对碳纤维增强树脂复合材料(CFRP)-热成型钢超混杂层合板层间力学性能的影响。试验结果表明,采用金属表面处理与界面插层协同增韧方案,可以极大地提升层合板的I型层间断裂韧性。其中,喷砂/界面胶膜插层试件(GB36#/AF)的I型层间断裂韧性相比于脱脂试件提高了343%;喷砂/界面纯树脂插层试件(GB36#/EP)相比于脱脂试件,其Ⅰ型层间断裂韧性提高了129%。并基于内聚区模型对CFRP-热成型钢超混杂层合板分层失效进行了有限元模拟。最后借助激光共聚焦扫描显微镜(LSM)、接触角测量仪(CAG)、扫描电子显微镜(SEM)等对热成型钢表面形貌和试件的断裂面进行了表征并揭示了层间增韧的机制。      

The damage tolerance of carbon fiber reinforced composites—A workshop summary

The principal objective of this workshop was to identify the critical problem areas associated with the damage tolerance of carbon-fiber reinforced composite materials. The discussion was divided into six areas: (1) damage tolerant materials; (2) testing methods; (3) structural life prediction; (4) damage tolerant design concepts; (5) repair methods; and (6) nondestructive testing. Approximately 1 h was devoted to the discussion of each of these topics. Discussion was stimulated by having one, two, or three introductory presentations by the discussion leaders of each topic followed by open discussion. In this report, my impressions of the discussion on each topic are combined with those of the discussion leaders and presented in the following format: Summary of Presentations; Summary of Discussion; and Critical Issues. It is possible to obtain the final conclusions of the workshop by examining the critical issues listed at the end of each section.

The discussion was lively, controversial, and open. The main conclusions to be drawn from the workshop are: (1) damage from impact is the worst type of damage for these materials—significant reductions in the compressive strength will occur following impact; (2) fatigue damage at the present time does not limit the use of these materials but as new materials are developed fatigue failure may become an issue; (3) very little is understood about the micromechanics of damage, hence it is impossible to predict the effect of changing the properties of the individual components (fibers, matrix, and fiber-matrix interface) on the bulk material properties; (4) better analytical models to describe the formation and growth of impact-damage are badly needed; and (5) rapid NDT methods to inspect large components are required.     

纤维增强地质聚合物混凝土早期冲击力学性能的对比研究

为对比研究玄武岩纤维和碳纤维对地质聚合物混凝土（geopolymeric concrete ,GC）早期冲击力学性能的改善效果,首先以矿渣与粉煤灰作为原材料,并采用液体硅酸钠与NaOH作为碱激发剂,配制了纤维体积掺量分别为0、0.1%、0.2%、0.3%的玄武岩纤维增强地质聚合物混凝土（basalt fiber reinforced geopolymeric concrete ,BFRGC）和碳纤维增强地质聚合物混凝土（carbon fiber reinforced geopolymeric concrete ,CFRGC）,再采用Φ100 mm 霍普金森压杆 (split Hopkinson pressure bar ,SHPB) 试验装置测试了两种材料3d、7d的冲击力学性能,并对试验进行对比分析。结果表明：纤维增强地质聚合物混凝土 (fiber reinforced geopolymeric concretes ,FRGCs) 早期冲击力学性能具有显著的应变率相关性;BFRGC的早期动态强度特性优于CFRGC;BFRGC在10–102 s-1范围内的能量吸收能力与CFRGC的相当,但BFRGC相对于CFRGC在吸收冲击能上的优势,将会随着应变率的增加而越发明显。对比可知：BFRGC较CFRGC而言,具有更加优越的早期冲击力学性能,主要体现在动态强度和能量吸收能力上。     

Energy absorption efficiency of carbon fiber reinforced polymer laminates under high velocity impact

In this paper, response of carbon fiber reinforced polymer (CFRP) laminates subjected to high velocity impact has been investigated by experimental and numerical methods. Experiments using a two-stage light gas gun were conducted to investigate the impact process and to validate the finite element model. The energy absorption efficiency (EAE) of CFRP laminates with different thickness was investigated. According to the results of experiments and numerical calculations, thin CFRP laminates have a good EAE under relative higher velocity impact; by contraries, a superior EAE is displayed in thick laminates under relative lower velocity impact. Subsequently, EAE of CFRP laminates was compared with that of 304 stainless-steel plates. In a specific impact velocity range, EAE of CFRP laminates is higher than that of 304 stainless-steel. Thus, CFRP laminates have a potential advantage to substitute the metal plates to be used in high velocity impact resistance structures under a specific impact velocity range.     

纤维金属层板低速冲击试验和数值仿真

为开展纤维金属层板（FML）低速冲击有限元数值仿真研究,改进了传统的连续损伤力学（CDM）模型,然后对FML落锤低速冲击试验进行数值仿真,并与实验结果进行对比验证。分别采用5.11 J 和10.33 J冲击能量对FML进行落锤低速冲击试验,得到冲击载荷、位移和能量时程曲线,分析FML的动态响应和失效模式。建立了考虑塑性应变、压缩刚度衰减特征和纤维拉伸断裂损伤的新CDM模型,描述S2-玻璃纤维/环氧树脂（S2-galss/epoxy）复合材料的损伤本构,并编写VUMAT子程序,通过ABAQUS/Explicit求解器对FML落锤冲击试验进行数值仿真。研究结果表明：低能量冲击条件下,FML背面主要为鼓包和裂纹等失效模式,位移峰值随冲击能量的提高而增加,冲击载荷峰值在穿透前也随冲击能量的提高而增加;采用改进的CDM模型描述FML中S2-galss/epoxy复合材料铺层后,有限元数值计算可以较好地预测FML低速冲击载荷下的动态响应;有限元数值仿真结果表明,FML中第2层复合材料铺层发生的纤维断裂损伤比第1层的更严重。     

The damage tolerance of GRP laminates under biaxial prestress

The damage tolerance of E-Glass reinforced/polyester laminated plates subjected to a low velocity impact while under an in-plane prestress is investigated. Prior to test, the plates are subjected to either uniaxial or biaxial loading by means of a specially designed test rig which enables independent tension/tension, tension/compression or compression/ compression testing in all stress/strain quadrants. Impact tests are carried out for a single strike energy for a comprehensive range of pre-strains. Absorbed energy, damage area, peak impact loads and the maximum permanent indentation depth are assessed in characterising the resulting damage.

It is shown that the shape, orientation and size of the damage zone is strongly influenced by the nature and magnitude of the pre-strain. Impact specimens subject to shear loading give rise to the largest increase in damage area when compared to unstressed plates.     

吸湿后碳纤维复合材料正交层板拉伸疲劳性能

湿环境下复合材料疲劳性能会严重退化,影响结构的使用安全,在确定复合材料结构寿命时须考虑湿环境的影响.对常温下湿态和干态下碳纤维复合材料正交层合板的拉伸疲劳性能进行实验,研究饱和吸湿对正交层合板拉伸疲劳性能的影响,获得了两种环境下层合板的S-N曲线.在此基础上,建立有限元模型,并对吸湿后正交层合板的疲劳寿命和损伤演化情况进行预测,计算结果与实验结构吻合较好,证明了模型的有效性.结果表明,饱和吸湿对正交层合板的拉伸疲劳性能影响很大.吸湿后正交层合板的拉伸疲劳寿命明显低于干态情况,而且S-N曲线的斜率稍低,层合板的纤维损伤起始与扩展情况与干态情况也有较大差别.     

The impact resistance of polypropylene-based fibre–metal laminates

The high velocity impact response of a range of polypropylene-based fibre–metal laminate (FML) structures has been investigated. Initial tests were conducted on simple FML sandwich structures based on 2024-O and 2024-T3 aluminium alloy skins and a polypropylene fibre reinforced polypropylene (PP/PP) composite core. Here, it was shown that laminates based on the stronger 2024-T3 alloy offered a superior perforation resistance to those based on the 2024-O system. Tests were also conducted on multi-layered materials in which the composite plies were dispersed between more than two aluminium sheets. For a given target thickness, the multi-layered laminates offered a superior perforation resistance to the sandwich laminates. The perforation resistances of the various laminates investigated here were compared by determining the specific perforation energy (s.p.e.) of each system. Here, the sandwich FMLs based on the low density PP/PP core out-performed the multi-layer systems, offering s.p.e.’s roughly double that exhibited by a similar Kevlar-based laminate.A closer examination of the panels highlighted a number of failure mechanisms such as ductile tearing, delamination and fibre failure in the composite plies as well as permanent plastic deformation, thinning and shear fracture in the metal layers. Finally, the perforation threshold of all of the FML structures was predicted using the Reid–Wen perforation model. Here, it was found that the predictions offered by this simple model were in good agreement with the experimental data.     

阳极氧化工艺对纤维-铝合金层板力学性能的影响

通过改变铝合金表面阳极氧化工艺参数, 研究了阳极氧化电压和时间对玻璃纤维-铝合金(GLARE)层板抗拉强度和层间剪切强度的影响。通过SEM观察了铝合金表面Al₂O₃多孔膜和层板断面形貌, 分析了铝合金/树脂胶接界面对层板力学性能的影响。结果表明, 阳极氧化电压为20 V时, GLARE层板抗拉强度和层间剪切强度随着阳极氧化时间延长而增大, 在20 min时出现最大值, 继续延长阳极氧化时间, 层板强度随之下降; 阳极氧化时间为20 min时, GLARE层板抗拉强度和层间剪切强度随着阳极氧化电压增大而增大, 在20 V时出现最大值, 继续增大电压, 强度随之下降。     

阳极氧化工艺对纤维-铝合金层板力学性能的影响

通过改变铝合金表面阳极氧化工艺参数,研究了阳极氧化电压和时间对玻璃纤维-铝合金(GLARE)层板抗拉强度和层间剪切强度的影响.通过SEM观察了铝合金表面Al2O3多孔膜和层板断面形貌,分析了铝合金/树脂胶接界面对层板力学性能的影响.结果表明,阳极氧化电压为20 V时,GLARE层板抗拉强度和层间剪切强度随着阳极氧化时间延长而增大,在20 min时出现最大值,继续延长阳极氧化时间,层板强度随之下降;阳极氧化时间为20 min时,GLARE层板抗拉强度和层间剪切强度随着阳极氧化电压增大而增大,在20V时出现最大值,继续增大电压,强度随之下降.     

模压工艺对玻璃纤维增强聚丙烯复合材料层合板力学性能的影响

利用热模压工艺制备玻璃纤维增强聚丙烯（GF/PP）复合材料层合板,通过差示扫描量热（DSC）法试验分析,确定相变参数,运用ANSYS有限元分析,将复合材料热力学参数与温度的非线性关系定义到材料特性中,研究模压成型过程中温度场变化情况,为模压成型工艺制度的确立提供理论指导和依据。以压缩强度、层间剪切强度和冲击韧性作为力学性能评价指标,采用响应曲面法探讨和分析制备工艺对GF/PP复合材料层合板力学性能的影响,得到最优模压工艺制备参数,获得最高复合材料层合板力学性能,为GF/PP复合材料自动铺放奠定铺放工艺基础。试验结果表明:模压加热工艺参数对复合材料层合板力学性能的影响度（从大到小）依次为:热压温度、热压时间、热压压力。较优的模压加热工艺参数为:热压温度228℃、热压时间6 min、热压压力1.1 MPa,在此工艺条件下制备的GF/PP复合材料层合板,层间剪切强度为31.12 MPa,压缩强度为100.96 MPa,冲击韧性为2.27 kJ/cm2。      

纤维增强复合材料层板高速倾斜冲击损伤数值模拟

根据复合材料三维黏弹性本构关系,建立了纤维增强复合材料层板高速倾斜冲击损伤的数值分析模型.该模型在复合材料层间引入界面单元模拟层间分层,结合三维Hashin失效准则进行单层板面内损伤识别,引入材料刚度折减方案,采用菲线性有限元方法,研究高速倾斜冲击下复合材料层板的破坏过程和损伤特性.研究结果表明:层板的主要损伤形式是层间分层、基体微裂纹和纤维断裂;冲击速度不变而入射角度增大时,剩余速度减小,层板损伤面积在一定入射角度范围内有明显变化;入射角度不变而冲击速度增大时,剩余速度增大,层板损伤面积在一定速度范围内也有明显变化.     

纤维增强复合材料层板高速倾斜冲击损伤数值模拟

根据复合材料三维黏弹性本构关系, 建立了纤维增强复合材料层板高速倾斜冲击损伤的数值分析模型。该模型在复合材料层间引入界面单元模拟层间分层, 结合三维Hashin失效准则进行单层板面内损伤识别, 引入材料刚度折减方案, 采用非线性有限元方法, 研究高速倾斜冲击下复合材料层板的破坏过程和损伤特性。研究结果表明: 层板的主要损伤形式是层间分层、 基体微裂纹和纤维断裂; 冲击速度不变而入射角度增大时, 剩余速度减小, 层板损伤面积在一定入射角度范围内有明显变化; 入射角度不变而冲击速度增大时, 剩余速度增大, 层板损伤面积在一定速度范围内也有明显变化。     

Damage resistance and damage tolerance of hybrid carbon-glass laminates

The influence of impact energy and stacking sequence on the damage resistance and Compression After Impact (CAI) strength of Carbon and Glass Fibre Reinforced Plastic (CFRP and GFRP respectively) hybrid laminates is investigated. CAI tests demonstrate that, in comparison to fully CFRP laminates, hybrid laminates show increases in structural efficiency of up to 51% for laminates subject to a 12J impact and 41% for those subject to an 18J impact. Laminates displaying the highest stresses at failure are those that exploit stacking sequences and GFRP content to prevent delaminations from forming close to the outer surface of the laminate during impact. This favourable damage morphology inhibits both sublaminate-buckling-driven delamination propagation and anti-symmetric laminate buckling failures.     

Detection of impact damage in CFRP laminates

The initiation and propagation of damage in carbon fibre composites subjected to impact loading has been investigated. High velocity impact tests were conducted on a variety of stacking configurations using a nitrogen operated gas gun. The damage processes were characterised using X-radiography, ultrasonic C-scanning, optical microscopy and the deply technique. The merits and weaknesses of applying such damage detection techniques to the monitoring of impact damage in composites are discussed. The consequence of the various fracture mechanisms on residual tensile strength is also considered.     

Vibroacoustic performance of fiber metal laminates with delamination

In the present work, the numerical assessment of vibroacoustic (VA) performance of fiber metal laminates (FML) with mid-plane center delamination is presented. A fluid structure interaction study has been done using finite element method (FEM). Experimental validation is performed on an aluminium (AL) panel for verifying the correctness of finite element (FE) idealization procedure to simulate the fluid-structure interaction. Delamination is introduced in the FE model of FML panel and VA analysis is subsequently carried out. Sound transmission loss (STL) is computed on the panel with center delamination and without delamination. The overall sound pressure level (OASPL) shows that the presence of delamination (40% in total area) in FML has not changed the total energy of the transmitted sound when compared to aluminium and composites. However, in the narrow frequency bands (150–200 Hz, 200–250 Hz), the sound transmission nature has been significantly affected due to local delamination modes participating in the fluid-structure interaction process.