基于NASTRAN的复合材料层合板层间应力分析

基于MSC.PATRAN/NASTRAN软件,采用一种准三维混合有限元模型,计算了复合材料层合板的层间应力,得到了层间应力对层合板面内应力分布的影响规律,为合理设计层合板,优化层间剪切强度,扩大层合板的应用范围,提供了分析手段和理论依据;这种准三维混合模型的有限元计算方法,提高了复合材料层合板的分析效率和分析精度,也为其他复合材料结构分析提供了新的分析思路和途径.     

复合材料层合圆柱壳的动力响应与层间应力

采用分层壳理论和厚度方向的二次插值函数推导出正交铺设层合圆柱壳的动力响应方程,并得出简支层合圆柱壳自由振动问题的解。对于给定算例,计算出的自振频率与三维分析的结果吻合良好,说明所推导的二维解具有足够精度。计算了前四阶模态对应的壳中应力。计算结果说明,对于高阶模态,层间应力相对于面内应力的比值远高于低阶模态的对应比值,高的层间正应力是高阶模态导致脱层破坏的主要原因。     

植物纤维复合材料层合板吸湿层间应力分析

为研究吸湿对植物纤维层合板层间应力的影响,采用超弹性吸湿本构模型来描述剑麻纤维增强苯甲基化木材(SFRBW)复合材料的吸湿力学行为,用Fortran语言编写了有限元用户材料子程序,建立了SFRBW层合板三维有限元模型,分析了不同湿度对不同铺设角的SFRBW斜交层合板受拉伸时的层间应力和自由边缘效应的影响.数值结果表明,...     

多层复合材料筒状结构在温度载荷作用下的层间应力建模与试验验证

多层复合材料筒状结构的残余应力可造成内部分层、结构失稳等,有必要结合理论和实验等研究其内部应力形成机制。基于各向异性线弹性本构和平面应力假设,建立了温度载荷作用下多层复合材料筒状结构内部应力的预测模型,并通过有限元仿真和热膨胀变形测试对模型有效性进行了校核和验证。结果表明：筒状结构环向的热膨胀变形从内层到外层逐渐增大,其中内层附近环向热膨胀系数低于面内热膨胀系数、外层附近环向热膨胀系数则高于面内热膨胀系数。在此基础上,结合模型理论分析揭示了层间应力对多层复合材料筒状结构的热膨胀变形行为的影响机制。在筒状结构形式下,温度加载引起的层间应力由一个涉及热膨胀系数和弹性参数的热力耦合项决定;由于多层复合材料面内与面外热膨胀系数存在差异,该应力耦合项不为0,从而在温度加载下形成了层间应力并影响了环向膨胀变形行为。基于上述认识,提出了调控多层复合材料筒状结构层间应力的有效措施。本文对揭示多层复合材料筒状结构的层间开裂物理机制、优化其热力匹配设计等具有重要意义。     

螺栓夹持填充孔复合材料层压板层间应力分析

为了研究含螺栓复合材料层压板连接接头的层间应力分布规律,提出了采用填充孔形式和虚拟界面层方法求解层间应力,并建立了三维有限元模型对受面内压缩载荷的螺栓夹持填充孔层压板进行分析。结果表明:层压板层间应力集中不仅发生在孔边,还会在螺栓头边缘附近出现,且夹持力越大螺栓头边缘附近的层间应力集中越严重;合理的螺栓夹持力能改善孔边应力状态,提高孔边抵抗分层的能力,但无法改善螺栓头边缘附近的层间剪切应力集中状态。因此,在进行含螺栓夹持的层压板机械连接结构孔边层间强度设计时,也要考虑螺栓头边缘的层间剪切应力集中问题,以提高复合材料结构的安全性。     

开孔碳纤维层合板层间应力分析

针对具有典型铺设角 的开孔碳纤维层合板, 采用三维有限元数值模拟方法, 分析了在单向拉伸载荷作用下孔边附近的层间应力, 讨论了界面层参数对层间应力的影响, 详细给出了典型铺设角之间层间应力的分布规律和最大层间应力产生的位置。结果表明: 对于相同铺设角的界面层, 沿厚度方向的位置影响层间应力的大小, 但不影响分布趋势; 而铺层顺序(如 或 )对层间应力的大小和分布趋势影响则较小。最大层间正应力产生于 的界面层, 位于与拉伸方向成90°的位置, 是外加拉伸应力的51%; 最大层间剪应力产生于 的界面层, 最大层间环向剪应力位于与拉伸方向成74°的位置, 是外加拉伸应力的64%; 而最大层间径向剪应力位于与拉伸方向成66°的位置, 是外加拉伸应力的25%。      

纤维复合材料界面层结构,性质及作用

系统地评述了纤维复合材料界面层结构，性质及其对宏观性能影响的研究工作，针对不同体系中形成的界面层，总结了用不同表征手段考察其结构的工作；通过简要回顾界面应力传递机理并比不同界面性质评价方法的意义，根据模型复合材料实验结果，讨论了界面性质对界面层的依赖性，提出了控制界面层形态和性质的原则和方法。     

金属基复合材料界面残余应力的研究进展

综述了金属基复合材料界面残余应力的各种影响因素、残余应力的实验测试方法和理论分析方法及残余应力对复合材料宏观力学性能的影响,分析讨论了目前研究中存在的问题和不足之处,并指出了今后工作的重点与方向.     

热塑性复合材料层合板的层间应力与损伤机理

使用有限元生成软件FEPG和表征热塑性复合材料AS4/PEEK非线性行为和应变率相关行为的三维粘塑性模型,计算了复合材料角铺设层合板在单向拉伸时的界面层间应力.层间应力的三维分布图表明,AS4/PEEK对称角铺设层合板的层间剪应力在自由边缘处存在很明显的自由边缘效应;层间正应力也存在自由边缘效应,对于轴向拉伸,其在自由边缘处的值为负.随着铺设角的增大,自由边缘处二者的值均减小.层间应力存在端头效应,甚至比边缘效应还明显.随着铺设角的增大,层间应力在两端头处的值降低,层间正应力由压应力变为拉应力.主要由纤维控制的角铺设AS4/PEEK层合板,在自由边缘处较大的层间剪应力是引起其层间分层的主要原因;主要由基体控制的角铺设AS4/PEEK层合板,其首先产生的是面内应力破坏,而不是层间分层.     

Application of Interlaminar Tests to Marine Composites. A Literature Review

This paper gives an overview of the characterization of the interlaminar properties of composites used for marine structures. Composites to be used in marine applications have particular requirements due to their environment, their large dimensions, mechanical loading and cost constraints. Under certain loading conditions (insert loading, impact) there is a risk of delamination as interlaminar strength of these materials is limited. This paper presents an overview of the tests available to measure delamination resistance. The parameters which influence this property, including the constituents (fibre, matrix, interface), specimen geometry, fabrication route and the resulting defects, and aging are reviewed here.     

Interlaminar Stress Determination in Carbon Fibre Epoxy Composites with the Embedded Strain Gauge Technique

Abstract: In order to determine interlaminar stresses, strain gauges have been embedded in carbon fibre/epoxy composites. Insulation problems occurring because of the electrical conductivity of the carbon fibres were successfully resolved with the help of special foils. Measurements on unidirectional and angle‐ply laminates were in good agreement with calculations based on the classical laminate theory. Moreover, the laminate strength was not significantly affected by the embedded strain gauges. The technique may also be applied to residual stress determination in composite components.     

Interlaminar shear stresses in laminated composite plates under thermal and mechanical loading

The combined effects of thermal and mechanical loadings on the distribution of interlaminar shear stresses in composite laminated thin and moderately thick composite plates are investigated numerically using the commercially available software package MSC NASTRAN/PATRAN. The validity of the present finite element analysis is demonstrated by comparing the interlaminar shear stresses evaluated using the experimental measurement. Various parametric studies are also performed to investigate the effect of stacking sequences, length to thickness ratio, and boundary conditions on the interlaminar shear stresses with identical mechanical and thermal loadings. It is observed that the effect of thermal environment on the interlaminar shear stresses in carbon-epoxy fiber-reinforced composite laminated plates are much higher in asymmetric cross-ply laminate and anti-symmetric laminate compared to symmetric cross-ply laminate and unidirectional laminate under identical loadings and boundary conditions.     

Application of Interlaminar Tests to Marine Composites. Relation between Glass Fibre/Polymer Interfaces and Interlaminar Properties of Marine Composites

The need for improved performance and the development of new composite manufacturing methods require a better understanding of the role of interface phenomena in the mechanical behaviour of these materials. The influence of the cure cycle on the bulk and surface properties of the matrix resin, and of composites based on polyester and epoxy resins reinforced with glass fibres has been studied. While the mechanical properties of the epoxy vary with cure temperature the surface tension is not affected. The increase in interfacial shear strength and interlaminar shear strength with increased cure temperature cannot be simply explained by the wetting of the fibres by the matrix. The importance of thermal stresses, generated at the interface by resin shrinkage and differences in thermal expansion, for the mechanical behaviour of the composite are demonstrated.     

Comparison of Interlaminar Fracture Toughness in Unidirectional and Woven Roving Marine Composites

This paper investigates the effect of fibre lay-up and matrix toughness on mode I and mode II interlaminar fracture toughness (G_Ic and G_IIc) of marine composites. Unidirectional and woven roving fibres were used as reinforcements. Two vinyl ester resins with different toughness were used as matrices. Results from both modes showed toughness variation that is consistent with matrix toughness. Values of G_Ic were not significantly influenced by fibre lay-up except at peak load points in the woven roving/brittle-matrix composite. Each peak load point, caused by interlocked bridging fibres, signified the onset of unstable crack growth. For unidirectional specimens, crack growth was stable and G_Ic statistically more reliable than woven roving specimens, which gave fewer G_Ic values due to frequent unstable crack growth. Mode II tests revealed that, except for crack initiation, G_IIc was higher in woven roving composites. This was due to fibre bridging, perpendicular to the crack growth direction, which encouraged stable crack growth and increased energy absorption. Mode II R-curves were obtained for the woven roving specimens. These R-curves provide additional information useful for characterising delamination resistance. The paper concludes that composites with woven roving fibres show similar mode I delamination characteristics to the unidirectional composites; but their mode II delamination characteristics, after crack initiation, are quite different.     

Bifurcation of Cracks in Laminated Ceramic Composites with Rigid Interlaminar Bonds

Bifurcation of cracks in symmetrical laminated two-component composites was analyzed. Geometric factors limiting this effect were established. The bifurcation area is shown to be determined by the following parameters: number of layers, cooling temperature range, elastic constants, and thermal expansion coefficients of the layers. Bifurcation conditions in the composite specimen with a given number of layers are compared with corresponding conditions for the specimen of the fixed total thickness.     

Interlaminar Fracture Toughness of CF/PEI and GF/PEI Composites at Elevated Temperatures

An experimental study has been conducted to assess temperature effects on mode-I and mode-II interlaminar fracture toughness of carbon fibre/polyetherimide (CF/PEI) and glass fibre/polyetherimide (GF/PEI) thermoplastic composites. Mode-I double cantilever beam (DCB) and mode-II end notched flexure (ENF) tests were carried out in a temperature range from 25 to 130°C. For both composite systems, the initiation toughness, G _IC,ini and G _IIC,ini, of mode-I and mode-II interlaminar fracture decreased with an increase in temperature, while the propagation toughness, G _IC,prop and G _IIC,prop, displayed a reverse trend. Three main mechanisms were identified to contribute to the interlaminar fracture toughness, namely matrix deformation, fibre/matrix interfacial failure and fibre bridging during the delamination process. At delamination initiation, the weakened fibre/matrix interface at elevated temperatures plays an overriding role with the delamination growth initiating at the fibre/matrix interface, rather than from a blunt crack tip introduced by the insert film, leading to low values of G _IC,ini and G _IIC,ini. On the other hand, during delamination propagation, enhanced matrix deformation at elevated temperatures and fibre bridging promoted by weakened fibre/matrix interface result in greater G _IC,prop values. Meanwhile enhanced matrix toughness and ductility at elevated temperatures also increase the stability of mode-II crack growth.     

非连续增强复合材料应力分析的简化模型

本文建立了非连续增强复合材料应力分析的简化模型,在此基础上引入复变函数理论导出复合材料内部应力大小及分布的解析表达式,并利用计算机进行了数值分析,结果表明,在增强体端部有很大的应力集中。     

热残余应力对C/SiC复合材料界面剪切强度影响的有限元分析

根据C/SiC复合材料的属性,建立单纤维顶出的二维轴对称模型,采用有限元法对C/SiC复合材料的界面剪切强度进行数值研究,分析中考虑材料制备过程中的残余应力对界面剪切强度的影响,在细观力学层面上系统分析纤维顶出过程的界面剪应力及其相关影响因素。分析得出,残余应力会对界面造成损伤,降低界面脱粘载荷。材料的界面承受能力与热膨胀系数呈正相关,与固化温度呈负相关。     

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。