含分层损伤复合材料加筋层合板的分层扩展研究

建立了复合材料加筋结构的后屈曲和分层损伤扩展行为的数值模拟方法．基于Mindlin一阶剪切理论和von-Karman大挠度理论的层合板和层合梁单元，提出了含分层损伤复合材料加筋层合板分层扩展行为的有限元分析方法；利用虚裂纹闭合技术计算分层前缘的总能量释放率，并采用总能量释放率准则分层扩展判据，结合自适应网格移动技术，对在压缩载荷作用下的具有不同加筋形式，不同初始分层面积和形状的加筋板结构分层扩展行为进行了数值模拟研究，在分析中还考虑了加筋刚度、位置和分布，分层形状和大小、边界支撑强弱和分层前缘的接触效应对结构分层扩展行为的影响．本所提出的研究方法对工程界关于复合材料结构的设计具有重要意义．     

基于广义函数空间的不连续梁振动分析

首先运用广义函数建立了轴向力作用下含任意不连续点的弹性基础Euler(欧拉)梁的自由振动的统一微分方程.不连续点的影响由广义函数(Dirac delta函数)引入梁的振动方程.微分方程运用Laplace变换方法求解;与传统方法不同的是,该文方法求得的模态函数为整个不连续梁的一般解.由于模态函数的统一化以及连续条件的退化,特征值的求解得到了极大地简化.最后,以梁-质量块模型和轴向力作用下弹性基础裂纹梁模型为例验证了该文方法的正确性与有效性.     

变刚度复杂梁结构损伤检测方法研究

提出了适用于复杂梁结构损伤检测的子段模态应变能法SSEM(subsectionstrainenergymethod),并分析了该方法的适用性条件．通过对变截面梁的有限元计算,以及对纤维增强复合材料风机叶片缩比模型的试验分析,验证了SSEM方法确定的结构损伤指标对损伤准确定位的可靠性．该基于振动的变刚度复杂梁结构的损伤检测方法,可应用于工程实际中梁和类梁整体结构的损伤检测．     

任意弹性边界的多段梁自由振动研究

研究了连续多段梁的自由振动特性.为区别于诸简支等传统约束边界,提出了弹性约束边界下多段梁结构的自由振动特性分析方法.首先根据谱几何法,在传统Fourier级数的基础上添加四个辅助函数,构造了多段Euler梁中每段的横向位移函数.其次,将位移函数的假设谱几何形式代入多段梁结构的Lagrange函数得到新的表达式,由Hamilton原理将自由振动问题化成矩阵特征值形式,从而求解出任意弹性边界条件下多段梁的自振频率和模态.针对四个具体算例,通过改变边界处弹簧刚度值可求得不同边界条件下连续多段梁的自振频率和模态.与已有文献的结果比较,充分验证了该文方法的正确性、规范性和高效性.     

应用多刚体离散化方法对梁的动力屈曲和后屈曲分析

基于梁的多刚体离散化模型（有限段模型）,建立了梁的链式多刚体-铰链-弹簧系统模型,利用坐标变换方法建立了相应的非线性多自由度系统的参数振动方程,并利用约束参数法对所得到的多度系统的Mathieu-Hill方程进行了梁的动力屈曲分析,得到系统的参数共振域．因为所用的离散化模型与动力方程对梁的变形并无限制,所以可以用所得到的数学模型在其失稳域对梁的动力后屈曲进行数值仿真分析．通过实例的数值仿真,证明了这种梁的参数振动模型与分析方法的正确性．     

金属材料疲劳裂纹扩展速率估计的分层模型

裂纹扩展速率与应力强度因子幅值的关系曲线,是金属构件损伤容限设计及寿命预测的重要疲劳性能数据．为了充分、合理地运用在不同测试条件下获得的试验数据,分层随机样本模型,将总体样本分为若干层,每一层样本都是在相同的测试条件下获得的试验数据,结合压力容器的实际工作状况,对每一层样本赋予适当的权重,从而对疲劳裂纹扩展速率方程做出更符合实际要求的估计．实际计算表明,对不同炉号试样提供的Q235A级钢材的裂纹扩展速率数据,运用分层随机样本模型得到的结果,明显地优于运用简单随机样本模型分别处理每个炉号试样提供的数据所得的结果．     

纤维体积分数可变的复合材料梁计及转动惯量和剪切变形时的固有频率

研究纤维体积分数沿着厚度可变的对称复合材料梁的振动.分析中考虑了一阶剪切变形和转动惯量.该解法可适应任意边界条件.纤维体积分数沿着梁的厚度方向以坐标的m幂次多项式形式连续渐变.可变的纤维体积分数,在对称复合材料梁中形成功能梯度材料(FGM),会引起梁的某些振动特性的改变.结果显示,剪切变形、纤维体积分数和边界条件,对复合材料梁的固有频率和振型的影响.     

用截面变形耦合有限元法分析复合材料梁

复合材料板和梁具有优良的特性, 从而获得了广泛的应用．然而由于材料的各向异性, 使得对这类材料构件作变形和应力分析时,即使应用如有限元法的数值分析手段仍是非常复杂费时的．为此提出了一个可应用常规有限单元法,分析等截面复合材料梁承受均匀拉弯扭载荷的一个简单精确分析的实施方法．由于巧妙地利用了变形的对称特性,使得分析只需建立在梁的一个切片构造的几何模型上,用常规三维实体有限单元进行结构离散．推导了精确的变形场模式,并借助结构平移自由度的耦合关系使得数值分析易于实施．并通过数值算例来阐明方法的实施过程．     

中厚度复合材料夹芯层板变分渐近精细模型

为准确预测对中厚度复合材料夹芯层板分层开裂至关重要的沿厚向应力/应变分布,利用板固有小参数将原三维板分析严格拆分为沿厚向的一维分析和二维板非线性分析,并将原三维能量渐近扩展为系列二维近似能量泛函;通过对近似能量泛函中主导变分项(含翘曲项)的渐近修正,得到与原三维模型尽可能接近的近似能量,从而构建无需任何场变量假设的精细模型,并转换为工程常用的Reissner模型形式．通过4层复合材料夹芯板柱形弯曲算例表明:基于所构建模型重构的三维场精度较一阶剪切变形理论和经典层合理论更好,与精确解基本一致;由于所构建的变分渐近模型为等效单层板模型,在保证足够精度的前提下,相比三维有限元计算可减少2~3阶计算量,在精确性和有效性间取得较好的折衷．     

基于非约束模态的中心刚体-Timoshenko梁动力学建模与分析北大核心CSCD

梁的横向变形会导致梁纵向缩短,建模过程中考虑梁横纵变形二次耦合项则存在动力刚化现象,这说明梁的纵向变形会对模型的广义刚度造成影响.对于做旋转运动的梁结构,旋转运动时还会受到离心力的作用而产生轴向拉力,轴向拉力同样也会引起梁的轴向变形,这种影响对粗短梁更加明显.以大范围运动中心刚体-Timoshenko梁模型为研究对象:首先,运用Timoshenko梁理论以及Hamilton原理建立含离心力的动力学模型;其次,引入非约束模态概念,采用Frobenius方法求解非约束模态振型函数以及固有频率;最后,通过数值仿真探究不同恒定转速时非约束模态与约束模态广义刚度的差异和非约束模态条件下离心力对模型的影响.     

Localization of a delamination and estimation of its length in a composite laminate beam by the VSHM and pattern recognition methods

The purpose of this study was to investigate the delamination damage in laminate composite beams in order to adapt the vibration-based structural health monitoring (VSHM) method for laminated structures. The analysis was concentrated on the vibration characteristics of laminated specimens, in particular, on the first several natural frequencies of a composite laminate beam with a delamination damage. The core of this work is an experimental investigation into the vibration response of a composite laminate beam and its changes caused by delaminations of different sizes and different location in the beam. The aim was to determine how the first six harmonic frequencies are changed by a delamination, and the results show that they can be successfully used to clarify the presence, location, and dimensions of delaminations in a composite beam. A pattern recognition analysis was used to locate the damage, while its detection and evaluation were performed by using changes in the harmonic frequencies. A finite-element analysis was carried out, and the variations in the natural frequencies due to delamination are found to be in good agreement with experimental results.     

Stress and fracture analysis in delaminated orthotropic composite plates using third-order shear deformation theory

The third-order shear deformable plate theory is applied in this work to calculate the stresses and energy release rates in delaminated orthotropic composite plates with straight crack front. The delaminated parts are modeled by the general third-order plate theory, while a double-plate model with interface constraint is developed for the uncracked portion of the plate. The governing equations of the uncracked part are formulated by considering the equilibrium and the displacement continuity along the interface. As an example, a simply-supported delaminated orthotropic plate subjected to a point force is solved adopting Lévy plate formulation and the state-space approach. The mode-II and mode-III energy release rate distributions along the crack front were calculated by the J-integral. To verify the analytical results the 3D finite element model of the plate was constructed and the energy release rates were calculated by the virtual crack-closure technique. A previous second-order plate theory solution was also utilized in the course of the comparison. The results indicate a good agreement between analysis and numerical computation and that third-order theory is better in some cases than the second-order approximation.     

Compressive stability of multilayered delaminations in composites

The behavior of defects of the near-surface crack type was investigated in laminated composites. Multilayered delaminations in compressed elements were examined on the assumption that cylindrical bending of the delamination is accompanied by shear within the framework of a model similar to the Timoshenko model. The effect of the mechanical properties and thickness and number of layers in the delaminated section on the critical buckling strain and strain corresponding to the beginning of growth of the delamination was investigated. It was shown that when the delaminated section contains several bearing layers and the rigidity of the composite with respect to interlaminar shear is small, consideration of the shear in the delaminated section can lead to a significant change in the critical compressive strains and/or critical size of the delamination.Translated from Mekhanika Kompozitnykh Materialov. Vol. 33, No. 3, pp. 312–320, May–June, 1997.     

Post-critical behaviour of delaminated composite struts

Postbuckling responses of delaminated composite struts are semi-analytically modelled. The model used allows to describe the postbuckling behaviour beyond the state where delamination growth is initiated. In the current work, a multi-layered composite strut of differently stacked transversally isotropic unidirectional layers is investigated. A pre-existing delamination is assigned in between two layers. By using only four generalized coordinates postbuckling responses incorporating delamination growth are determined. © 2016 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim)     

Delamination growth of laminated circular plates under in-plane loads and movable boundary conditions

An investigation is made on interlaminar delamination growth of composite laminated circular plates under in-plane loads and movable delamination boundary conditions. A four-dissociated-region model is developed on the basis of von-Karman plate theory. The model is geometrically nonlinear and the laminated circular plate considered is subjected to axisymmetrical delamination. The effects of transverse shear deformation and contact effect of the delamination on the laminated plates are taking into account in the development of the governing equations of the laminated circular pates with random axisymmetrical delamination. The formulas for describing the total energy release rate and its individual mode components along the delamination front are also derived with considerations of Griffith criterion for fracture. Based on the model established, the delamination growth is numerically studied; and the influences of the parameters such as delamination radii and depths, together with material properties of the plates on the energy release rate are analyzed in detail.     

外部压力作用下复合材料层合圆柱壳的脱层扩展分析

含脱层的层合圆柱壳在承受外部压力作用时,容易发生脱层扩展,进而引起结构失效．基于可动边界变分原理并考虑脱层间的接触效应对圆柱壳在外部压力作用下的脱层扩展进行了分析,同时应用Griffith准则,导出了脱层前缘各点处的能量释放率表达式,且以轴对称脱层层合圆柱壳为例进行了数值计算,讨论了脱层大小、脱层深度、几何尺寸、材料性质及纤维铺层方式等因素对脱层扩展的影响．     

Dynamic loading of layered composite beams with damage of delamination type

Failure of composite beams containing initial delamination is investigated under low-speed impact by a dropping weight. Bolotin's theory of dynamic failure (1992) is used. The start and stop time of growth of a nonsymmetric delamination crack is studied. It is found that the initial extension starts and subsequently continues at the crack tip, which is located closer to the impact point. Then extension is observed on the second crack tip, and finally a synchronous growth of delamination occurs at both crack tips. With constant impact energy, the final size of delamination does not depend on its initial size. The start and stop time of delamination growth increases as the initial defect approaches the beam surface.Presented at the 10th International Conference on the Mechanics of Composite Materials (Riga, April 20–23, 1998).Moscow Power Engineering Institute, Technical University, Russia. Translated from Mekhanika Kompozitnykh Materialov, Vol. 34, No. 6, pp. 787–794, November–December, 1998.     

层合板壳脱层屈曲的有限元分析

通过建立一类新的参考面有限单元,得到适用于分析层合板壳脱层屈曲问题的有限元方法。指出了利用Mindlin假设意义下的变形协调条件,可以将大多数胜任层合板壳分析的一般板壳单元改造为相应的参考面单元。这一方法确保了位移场的合理性和协调条件的满足。为验证参考面单元的有效性,还对壳体脱层屈曲的几个算例作了数值分析。     

Caracterización de la delaminación en materiales compuestos mediante la teoría de mezclas serie/paralelo

This paper presents a new procedure to deal with the delamination problem found in laminated composites, based in a continuum mechanics formulation. The procedure proposed obtains the composite constitutive performance with the Serial/Parallel mixing theory, developed by F. Rastellini. This theory characterizes composite materials by coupling the constitutive behaviour of the composite components, imposing an iso–strain relation among the components in the fibre (or parallel) direction and an iso-stress relation in the remaining directions (serial directions). The proposed procedure uses a damage formulation to characterize the constitutive behaviour of matrix component in order to obtain the stress-strain performance of this material.With these two formulations, the delamination phenomenon is characterized naturally by the numerical simulation, being unnecessary the definition of special elements or computationally expensive techniques like the definition of contact elements or mesh separation. Matrix failure, as a result of the stress state found in it, leads to a reduction of the stiffness and strength capacity of the composite in its serial directions, among them, the shear component. This stiffness reduction provides a composite performance equivalent to what is found in a delaminated material.To prove the ability of the formulation proposed to solve delamination problems, the End Notch Failure test is numerically simulated and the results obtained are compared with experimental ones. The agreement found in the results with both simulations, numerical and experimental, validate the proposed methodology to solve the delamination problem.     

Analytical solution for the fully coupled static response of variable stiffness composite beams

An analytical solution is presented for the 3D static response of variable stiffness non-uniform composite beams. Based on Euler-Bernoulli theory, a set of governing differential equations are obtained, in which four degrees of freedom are fully coupled. For the variable stiffness beam, the governing field equations have variable coefficients reflecting the stiffness variation along the beam. Using the direct integration technique, the general analytical solution is derived in the integral form and the closed-form expressions of the obtained solutions are presented employing a series expansion approximation. The series expansion representation enables the proposed approach to be applicable for variable stiffness composite beams with arbitrary span-wise variation of properties. As an alternative solution, the Chebyshev collocation method is applied to the proposed formulation to verify the results obtained from the analytical solution. A number of variable stiffness composite beams made by fibre steering with various boundary conditions and stacking sequences are considered as the test cases. The static response are presented based on the analytical solution and Chebyshev collocation method and excellent agreement is observed for all test cases. The proposed model presents a reliable and efficient approach for capturing the complicated behaviour of variable stiffness non-uniform composite beams.