CFRP复合材料构件胶接特性及失效规律研究

对不同铺层方式和不同胶层厚度的复合材料胶接单搭结构(SLJs)的连接性能进行了研究。使用内聚力模型模拟了SLJs的胶层退化及失效过程，通过与实验对比验证了数值模型的有效性；基于改进后的三维Hashin失效准则，模拟了复合材料层合板的损伤演化。结果表明：胶层的退化形态及失效规律与胶层粘连的复合材料铺层角度密切相关，当胶层两侧粘连的复合材料铺层角度为0°时，胶层会退化形成椭圆环状；当胶层两侧粘连的复合材料铺层角度为45°或-45°时，胶层会退化形成上下中心对称的水滴状；当胶层两侧粘连的复合材料铺层角度为90°时，胶层会退化成沙漏状。0°铺层与胶层相邻时，结构的极限失效载荷最大，此时复合材料未出现损伤；当90°铺层与胶层相邻，结构的极限失效载荷最小且复合材料出现基体损伤、纤维损伤和分层损伤。胶层厚度在0.05～0.5mm时，复合材料胶接单搭结构的连接性能最好，当胶层厚度大于0.5mm,结构的连接性能会大幅下降。     

复合材料层合板开口补强选型分析

论文开展了受拉伸复合材料层合板圆形开口四种补强型式的研究.首先,基于Hoffman准则,分析补强型式对首层失效强度的影响,再通过比较开口周围最大应力和应变的降低程度,分析圆缺、环形、椭圆缺和矩形缺四种补强型式的补强效率.通过有限元参数化建模,分析了几何尺寸对补强效率的影响,给出了不同补强型式适合的补强范围.研究表明通过合理地设计补强型式可以有效地降低应力集中,提高拉伸破坏强度.分析结果可以为复合材料飞机结构在相似形状和载荷条件下的补强设计提供参考.     

含分层损伤复合材料层合板的压缩强度研究

给出了基于一阶剪切变形理论的含分层损伤层合板有限元分析模型,将含分层损伤层合板在压缩载荷作用下的强度破坏分析和屈曲破坏分析统一起来。先区分其破坏形式,然后再进行具体破坏分析,在屈曲特性分析中考虑了铺层强度破坏引起的刚度折减的影响,数值结果表明,该文给出的方法和结论对含分层损伤复合材料层合板的设计更具参考价值。     

含切口损伤复合材料层合板拉伸失效行为研究

对含有不同切口损伤的复合材料层合板试件进行了拉伸试验,采用电阻应变计同步测量切口损伤前缘区域随载荷的变化,测定含切口损伤层合板的剩余强度,并讨论了损伤长度和损伤角度对剩余强度的影响规律。建立含切口损伤复合材料层合板有限元模型,分析了含切口损伤复合材料层合板的拉伸失效行为,计算了含切口损伤复合材料层合板的剩余强度,确定了剩余强度与切口损伤状态的关系。计算结果与试验结果具有较好的一致性。     

复合材料层板损伤后刚度衰退的实验研究

对复合材料单向板进行了0°、90°、45°拉伸实验,对铺层为[0°/90°]、[±45°]的层合板进行了拉伸实验,对玻璃纤维、碳纤维、芳纶纤维缠绕的NOL环试样分别进行了短梁剪切实验。实验结果表明:碳纤维/环氧树脂基体复合材料单向板没有明显的非线性行为,而层合板在树脂开裂、面内及层间剪切破坏导致的刚度降低却很明显。层间剪切破坏不仅导致剪切刚度的降低,还会引起弯曲刚度的降低。玻璃纤维、芳纶纤维增强树脂基复合材料在三点弯曲实验过程中体现了较强的抗损伤能力,韧性较好;而碳纤维增强树脂基复合材料抗层间损伤能力较差。本文用标准实验方法,跟踪载荷-变形曲线,得到了用于应力分析的刚度衰减系数。用最大应力准则及实验得到的刚度衰减系数,对直径为1400mm的纤维缠绕壳体进行了变形分析,计算结果与实验值一致性较好。     

复合材料失效判据有效性验证方法研究

为系统地验证复合材料失效判据计算精度和有效性范围,给出了4种材料体系、6种铺层形式的层合板在单轴、双轴载荷下的失效试验数据,用以评估复合材料失效判据在单向层合板失效包线、多向层合板初始失效包线、多向层合板最终失效包线、层合板变形及层合板的破坏特性等五个方面的预测能力。并根据验证方法和有效性评估策略对失效判据计算精度进行量化考核,给出了失效判据在五个层面上的计算精度。     

开孔复合材料层合板强度不确定性分析

以拉伸载荷作用下AS4/3501-6开孔复合材料层合板为研究对象,采用考虑复合材料层合板就地强度效应的有限断裂力学模型和基于方差的敏感性测度分析模型相结合的方法,研究单层板宏观力学性能不确定性对具有不同孔径和铺层顺序的开孔复合材料层合板破坏强度的影响．研究结果表明：单层板力学性能对开孔板强度影响程度的大小与孔径相关,但敏感性排序与孔径无关．同时,单层板力学性能敏感性测度与层合板铺层顺序有关,层合板各向异性比越大,开孔板拉伸破坏受单层板纤维方向拉伸强度的影响越大,而且开孔板拉伸强度与单层板纤维方向拉伸强度呈正相关,与横向弹性模量呈负相关,与面内剪切模量和纵向弹性模量不具有单调关系．     

不同铺层角含孔复合材料板的损伤研究

针对0o、45o、90o铺层角复合材料层合板的含孔结构损伤问题,提出了一种基于层合板各铺层孔边应力解析解的首次损伤载荷系数分析计算模型。根据非均匀各向异性层合板的弹性特性,采用复变函数曲线映射方法获取了层合板孔边界积分方程,计算获得了0o、45o、90o角度铺层层合板各铺层的孔边纤维主方向和垂直于纤维主方向的应力分量;采用Tsai-Hill强度理论,对层合板各铺层进行孔边首次损伤载荷系数计算。分析结果表明:试件左右两端面在受到均布拉伸载荷p的作用下,各铺层中具有90o铺层角的铺层首次损伤载荷系数最小,具有0o铺层角的铺层首次损伤载荷系数最大,说明具有90o铺层角的铺层最先出现损伤,对应铺层首次损伤出现在孔边90o方向区域。将计算值与现有文献结果进行比较,误差小于10%,二者具有较好的一致性。     

含缺口复合材料层合板的三维有限元失效分析

本文研究了复合材料层合板最终强度计算的有限元理论,讨论了修正的Newton-Raphson迭代方法在层合板失效过程中应力场计算的迭代过程.同时本文建立了带缺口的复合材料层合板三维有限元模型,充分考虑层合板的纤维断裂、基体开裂和分层三种失效模式,采用修正的三维Hashin准则作为失效判断的依据,计算了三种不同铺层的层合板最终失效载荷值,与试验值吻合得很好.鉴于层压板材料常数ν23的数值难于测定的特点,讨论其对最终失效载荷的影响.在三维有限元模型的基础上,实现了失效扩展仿真分析.     

含孔复合材料层合板静拉伸三维逐渐损伤分析

针对面内静拉伸纤维增强复合材料含中孔层合板，发展了参数化三维逐渐损伤模型. 该模型 可以模拟含中孔层合板损伤起始、发展及最终结构破坏整个过程，并能较好地预测含中孔层 合板的破坏模式和破坏强度. 采用所发展的模型和有限元三维逐渐损伤分析技术即应力分 析、失效判定准则及损伤过程中材料性能退化等，对其他文献所提供的9种不同类型含中孔层合板进行了损伤扩展分析及强度预测，同时对层合板的损伤基本机理、类型及其相互关联作用进行了探讨，计算结果与文献实验结果非常吻合.     

基体开裂的正交复合材料对称层合板的粘弹性力学行为

本文讨论了含有均匀基体裂纹的正交复合材料对称层合板的线性粘弹性力学行为.采用二维剪切滞后模型并对其层间剪应力在厚度方向进行线性假设分布,求得层合板的平均应力应变的线弹性解,利用等效约束模型和经典层合理论可得到层合板因为含有基体裂纹而所引起的刚度退化现象.在弹性-粘弹性对应原理的基础上对其层合板的线粘弹性进行了讨论和研究.结果表明:层合板的松弛模量和蠕变泊松比随着时间的增加而减少,到达稳态后其值基本上是恒值.并跟Zocher的解析解和有限元数值解作了比较,发现结果非常吻合.     

Fracture of composite laminates by three-point bend

An experimental investigation has been carried out on the fracture behavior of T300/5208 graphite/epoxy laminates using three-point bend and tension tests. One laminate, a [0/±45/90] _ns orientation, was used withn=1 for tension specimens andn=4 and 8 for bend specimens. The crack-growth-resistance curve was constructed by compliance matching from crack-opening displacement and load data obtained from three-point bend tests. The value of effective crack length and corresponding crack resistance at onset of instability was nearly constant and independent of the initial crack length and laminate thickness. Experimental data from both bend and tension tests correlated reasonably well to the average-stress-failure criterion. Data were also compared with results found in the literature.     

复合材料刚度性能表征的协同损伤力学模型

针对复合材料层合板的弥散型损伤,提出一个刚度性能表征的协同损伤力学模型. 该模型兼顾了微观物理损伤响应和宏观材料刚度性能表征. 从微观角度,建立细观RVE 模型求解裂纹表面张开位移和滑开位移,以此定义损伤张量,并在宏观上通过对材料应变和损伤表面位移进行均匀化处理,建立单向板或层合板的损伤刚度矩阵和损伤张量之间的联系. 以基体裂纹为例,详细分析并建立了横向裂纹和纵向裂纹的损伤本构. 计算了[±θ/90₄]_S 铺层层合板中基体横向裂纹对刚度性能的影响,结果表明该方法能够准确地预测复合材料层合板由损伤导致的刚度性能衰减.      

考虑内部损伤影响的层合板最终强度预测

层合板强度分析若只考虑面内失效而忽略自由边界处的分层失效,往往会高估强度值,得不到合理的预测结果.该文提出了一种层合板强度的数值分析方法,综合考虑了层合板的面内失效(基体失效和纤维断裂)以及层间分层失效.采用有限元方法对层合板进行结构分析得到板的应力响应,结合面内失效判据和分层失效判据对层合板各个单层进行失效判断,采用刚度退化和逐步失效方法求得层合板的最终失效强度.与以往方法相比,该文模型和方法考虑的因素更全面.数值算例表明该方法预测得到的最终失效载荷和分层起始载荷和已有文献实验结果一致.     

Three-dimensional microscopic interlaminar analysis of cross-ply laminates based on a homogenization theory

In this study, a method for three-dimensional microscopic interlaminar analysis of cross-ply laminates is developed based on a homogenization theory to analyze microscopic interactions between unidirectional long fiber-reinforced laminae. For this, a unit cell of a cross-ply laminate, which includes interlaminar areas, is defined under the assumption that each lamina in the laminate has a transversely square fiber array. Then, showing that the laminate has a point-symmetric internal structure, the symmetry is utilized to introduce half of the unit cell as the domain of analysis. Moreover, the domain of analysis is divided into substructures using a substructure method combined with the homogenization theory, significantly reducing the computational costs. The present method is then applied to the analysis of interlaminar stress distributions in a carbon fiber/epoxy cross-ply laminate subjected to in-plane uniaxial tension. It is shown that microscopic shear stress noticeably occurs at the interface between the 0°- and 90°-plies. It is also shown that the microscopic interaction between the two plies is observed only in the vicinity of the interface.     

Buckling behavior of compression-loaded composite cylindrical shells with reinforced cutouts

Results from a numerical study of the response of thin-walled compression-loaded quasi-isotropic laminated composite cylindrical shells with unreinforced and reinforced square cutouts are presented. The effects of cutout reinforcement orthotropy, size, and thickness on the non-linear response of the shells are described. A high-fidelity non-linear analysis procedure has been used to predict the non-linear response of the shells. The analysis procedure includes a non-linear static analysis that predicts stable response characteristics of the shells and a non-linear transient analysis that predicts unstable dynamic buckling response characteristics. The results illustrate the complex non-linear response of a compression-loaded shell with an unreinforced cutout. In particular, a local buckling response occurs in the shell near the cutout and is caused by a complex non-linear coupling between local shell-wall deformations and in-plane destabilizing compression stresses near the cutout. In general, reinforcement around a cutout in a compression-loaded shell can retard or eliminate the local buckling response near the cutout and increase the buckling load of the shell. However, results are presented that show how certain reinforcement configurations can cause an unexpected increase in the magnitude of local deformations and stresses in the shell and cause a reduction in the buckling load. Specific cases are presented that suggest that the orthotropy, thickness, and size of a cutout reinforcement in a shell can be tailored to achieve improved buckling response characteristics.     

Deformation of Cross-Ply Composite Laminates with Cracked Ceramic Matrix

The deformation of cross-ply ceramic-matrix composite laminates under biaxial loading is studied theoretically. Experimentally, microscopic damage evolution in cross-ply ceramic-matrix composite laminates has not been well characterized yet, mainly due to the difficulties involved in testing of anisotropic plates under biaxial loading. It is assumed that the initial damage mechanism observed in ceramic-matrix composite laminates is the formation of tunneling macrocracks both in the 90°- and 0°-plies. The paper addresses the stiffness-deterioration behavior of cross-ply ceramic-matrix laminates with transverse and longitudinal macrocracks. The analysis is based on the equivalent-constraint model of a damaged laminate. Numerical results for SiC/CAS cross-ply laminates of various lay-ups are presented and discussed__________Translated from Prikladnaya Mekhanika, Vol. 41, No. 1, pp. 37–46, January 2005.     

Dynamic crushing characteristics of high strength steel cylinders with elliptical geometric discontinuities

Thin-walled members are commonly used as energy absorbers in engineering structures and often contain cutouts. This study performed numerical simulations of high strength steel cylindrical shells with elliptical cutouts subjected to dynamic axial impact. The LS-DYNA code was the primary analytical tool used to analyze the influence of cutout locations, cutout shapes and symmetry of cutout on the energy absorption capabilities and the crush characteristics of tubes with a cutout. For high strength steel tubes made from a rate sensitive material, the stress-strain curves of different strain rates were used to elucidate the effect of dynamic impact on the strain rate. Our results show that collapse crushing behavior is strongly influenced by the location and symmetry of cutouts and the variation of major axis influences the peak crush load.     

Steady-state aeroelasticity of fluid flow over a laminated composite plate

A stress-function-based variational approach is used to determine the interlaminar stresses in a multilayered strip of laminate subject to arbitrary combinations of axial extension, bending, and the steady-state aerodynamic loading of fluid flow over the upper surface of laminated composite plate. Symmetric four-layer, cross-ply and angle-ply laminates are considered in details. Some numerical solutions by using a personal computer are obtained. The present results for four-layer laminates show that the aerodynamic loading has significant effects on the interlaminar stresses near the free-edge regions.     

Effects of material and stacking sequence on behavior of composite plates with holes

Strain distributions to failure, tensile and compressive strain-concentration factors, and strength-reduction factors were determined for glass-, boron-, and graphite-epoxy plates with holes loaded in tension. Strain gages, photoelastic coatings and moiré techniques were used. Ten variations of layup and stacking sequence were studied. The boron-epoxy composite was found to be the stiffest and strongest of the three. The graphite laminate with the highest stress concentration and the most linear strain response exhibited the highest strength-reduction factor. In all cases, the maximum strain at failure on the hole boundary was higher than the ultimate tensile-coupon strain. In general, it was found that, the higher the stress-concentration factor, the higher the strength-reduction factor. Thus, the [0/90/0/90]_s layup with a stress-concentration factor of 4.82 had a strength-reduction factor of 3.18. At the other extreme, the most flexible layup [±45/±45]_s with the lowest stress-concentration factor of 2.06 had the lowest strength-reduction factor of 1.10. Stacking sequences associated with the tensile interlaminar normal stress or high interlaminar shear stress near the boundary, resulted in laminates 10 to 20 percent weaker than corresponding alternate stacking sequences. Furthermore, it was found that stacking-sequence variations can alter the mode of failure from catastrophic to noncatastrophic.