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。     

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.     

考虑层间和界面的玻璃纤维/环氧复合材料吸湿扩散实验和仿真

为研究复合材料层间和界面对吸湿扩散系数的影响,开展单向玻璃纤维/环氧复合材料和纯环氧树脂的吸湿实验,获取复合材料的三维扩散系数。采用光学显微镜和原子力显微镜分别获取复合材料层间和界面的参数。依据实验结果,建立包含层间和界面的复合材料瞬态扩散与稳态扩散有限元模型。结果表明:复合材料沿纤维方向的扩散系数大于纯树脂的扩散系数,垂直于纤维的两个方向的扩散系数不相等。包含层间的有限元模型能更真实地反映复合材料的结构及其吸湿过程,层间对垂直于纤维方向的扩散起促进作用。纬纱对沿其方向扩散的促进作用明显。为拟合复合材料的三维扩散系数,需要考虑界面扩散性能的正交各向异性。     

固体间不同厚度界面层的超声反射

将固体间界面层模拟为固体或流体薄层，本文讨论了界面层对斜入射纵波和横波的反射和透射，测量了垂直入射纵波的反射系统随声波频率的两铜块之间水界面层厚度的变化。理论和实验结果基本符合。     

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.     

Analysis of Interfacial Coating Effect on Thermal Stress in Composites

A preliminary model for the analysis of thermo-mechanical behaviour of interfacial coatings on thefibers in unidirectional composites have been developed on the solution of thermo-elastic mechan-ics. Thermal stress would be introduced into the composite during cooling because of the mismatchof thermo-mechanical properties among their components. The low modulus coating can effectivelyreduce the interracial stress caused by different thermal expansion coefficient between fibers and ma-trix, no matter how high or low the expansion coefficients of coatings are in CF/Al and SiC/Ticomposite systems, however, high modulus coating can decrease the interfacial compressive stress,only when the thermal expansion coefficient of coating is lower.     

纤维增强陶瓷复合材料的工艺热失配应力分析EI

在弹性力学圆筒理论和剪滞模型的基础上，依据考虑界面相和界面层效应的力学简化模型，分两种情况具体讨论复合材料制备过程中由于降温落差大小造成的工艺残余应力，并与Ｂｕｄｉａｎｓｋｙ等人的结果作了对比讨论。第一种情况考虑了界面层剪切效应，第二种略去了界面层剪切效应。为了更清楚地了解界面间正压力与剥离力之间的区别，分αｆ＞αｍ和αｆ＜αｍ两种情况来分析。     

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.     

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.     

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.