蜂窝纸板面内平台应力表征

面内平台应力是评估蜂窝纸板面内承载性能的重要指标,且蜂窝纸板性能极易受环境湿度的影响.该文试验分析蜂窝纸板厚度、芯层和面层对其面内平台应力的影响;基于不同相对湿度条件下蜂窝原纸的纵向屈服强度,建立了相对湿度影响的蜂窝纸板面内平台应力模型,并与试验实测数据进行比较验证.结果表明:纸板厚度和面纸性能对蜂窝纸板面内平台应力有较大影响,芯层性能对其影响较小;所建立模型能较准确地反映环境相对湿度对纸蜂窝结构材料面内平台应力的影响.借助该模型,无需大量的试验,即可估算其考虑相对湿度的面内平台应力,为蜂窝纸板的配纸和合理选用提供理论依据.     

含面内波纹缺陷的复合材料层合板刚度性能

基于经典层合板理论（CLT）,并考虑面内波纹引起的拉伸-弯曲耦合作用,提出了含面内波纹缺陷的复合材料层合板刚度预测模型,定量研究了波纹比、纤维偏转角和波纹位置等面内波纹参数对其三维刚度性能的影响。结果表明：理论模型预测值与文献中的结果吻合较好;面内波纹对纵向弹性模量、横向弹性模量、面内剪切模量、主泊松比和面内弯曲刚度均产生了显著影响。该建模方法为研究波纹缺陷对复合材料力学性能影响提供了参考。     

2D-C/SiC复合材料面内剪切性能统计及强度B基准值

针对2D-C/SiC复合材料进行大子样面内剪切实验,研究材料面内剪切模量和强度的分布规律及强度B基准值。运用线性回归结合假设检验的方法,确定2D-C/SiC复合材料面内剪切力学性能的分布规律及参数,对比两种不同经验失效概率得到统计结果;通过观察试样最窄净截面微CT照片及断口电镜扫描照片,解释材料面内剪切强度分散性微观机制,基于分布规律,最终计算得到2D-C/SiC复合材料面内剪切强度威布尔B基准值。结果表明:强度和模量均同时服从威布尔、正态和对数正态分布,且理论模型与实验结果吻合良好,两种经验失效概率不影响力学性能分布规律;面内剪切强度分散性与最窄净截面致密度和界面脱粘长度有关;2D-C/SiC复合材料面内剪切强度威布尔B基准值为80.41MPa。     

面内异性材料的应力和应变状态分析

迄今有关材料应力和应变状态的分析多限于面内同性材料。然而,绝大多数板树为面内异性,因此对所有板材的塑性变形问题一味在面内同性之条件下研究未免就有不妥之处。本文在面内异性的前提下,对板料的应力和应变状态进行了分析,并且初步探讨了用液压胀形试验求得应力应变曲线的一些问题。     

不同针刺工艺的针刺复合材料面内拉伸强度分析

6种针刺工艺不同的碳纤维增强树脂基复合材料,其面内拉伸强度随着针刺密度和针刺深度的增大而降低,针刺处纤维的断裂使材料内的缺陷失稳扩展和面内纤维断裂,进而使材料整体拉伸失效。根据面内拉伸实验结果和纤维累计损伤理论并引入纤维体积折减系数,建立了分析针刺复合材料面内拉伸强度的理论模型。这个模型的预测结果与实验结果相符,并发现断裂纤维簇的个数与体积折减系数相关。用该模型可预报不同针刺工艺复合材料的面内拉伸强度,并指导设计针刺复合材料的预制体。     

三维编织玄武岩/环氧树脂复合材料在温度场下的高应变率压缩试验

研究了三维编织玄武岩长丝纤维束增强环氧树脂复合材料在23、60、90、120、150、210℃温度场下和不同应变率范围(1 300~1 600、1 600~2 000、2 000~2 300s-1)内的面外/面内冲击压缩响应特征。结果表明:试验温度高于或低于树脂玻璃化温度决定面外/面内冲击压缩的应力-应变曲线走势特征,即使试验条件(温度和气压)一致,面外冲击压缩与面内冲击压缩应力-应变曲线也存在较大差异。温度和应变率对压缩模量、峰值应力、破坏应变、比能量吸收均有不同程度影响。面外和面内压缩的破坏模式存在较大差异,受温度效应和应变率效应影响。     

缝合复合材料单向板的拉压性能

缝合复合材料改善了层合复合材料易分层的缺陷,其力学性能研究具有重要意义。建立缝合复合材料单向板的三维有限元分析模型,考虑了缝合针脚造成的纤维面内和面外弯曲,分析了纤维弯曲对拉伸和压缩性能的影响。结果表明,模型能很好预测缝合单向板拉伸和压缩性能,同时考虑纤维面内和面外弯曲对预测更为有利,纤维面内和面外弯曲是影响强度的主要因素,纤维面内弯曲对模量影响较大,而纤维面外弯曲对模量的影响可以忽略不计。     

基于单测点单方向多普勒激光测头面内振动测试方法

介绍了基于单测点单方向多普勒激光测头的面内未知方向正弦振动的测量方法。测点单一模态面内振动为稳定的正弦振动,将其振动速度用互相垂直的两个稳定振动速度分量来表示。只用一个单测点单方向激光测头通过分时测量各个测点的两个振动分量即可测出各个测点的面内振动速度矢量。以正弦激励信号为同步相位基准,通过点阵振动数据拟合得到超声电机定子在工作模态频率正弦激励下的面内振型。所开发的面内振动模态试验测试系统对超声电机的研究开发具有重要的应用价值。     

钢管混凝土肋拱面内受力全过程试验研究

本文进行了两根钢管混凝土单圆管肋拱面内全过程试验。试验结果表明,钢管混凝 土肋拱具有较好的弹塑性性能和较高的承载能力。本文介绍了试验的情况,分析了模型肋拱 面内受力全过程的性能,并初步探讨了其面内极限承载力的简化计算方法。     

单向面内约束混凝土双向板火灾试验及承载力分析

为研究混凝土板在面内约束作用下的火灾行为,对1块面内约束混凝土双向板进行了恒载-升温条件下的火灾试验,获得了试验板沿板厚的温度场分布、钢筋温度、板挠度和平面外变形以及板角约束力等规律。基于EC2和ASCE两本构模型,采用五种理论对四块不同面内约束作用下试验板的极限承载力进行对比分析。结果表明:单向面内约束作用时,试验板板顶出现沿约束力方向的平行裂缝;与挠度相比,板在垂直约束力方向的平面内膨胀变形较大且不可忽略;面内约束作用和破坏准则对火灾下混凝土双向板极限承载力有重要影响。     

复合材料圆柱壳非线性热弹耦合振动

根据复合材料圆柱壳的非线性动力方程,研究了复合材料圆柱壳的非线性热耦合振动,应用Galerlein原理及改进的L－P法对其非线性热耦合振动进行求解,并讨论分析了温度、长径比、厚径比对复合材料圆柱壳非线性热振动固有频率的影响。     

Buckling of FGM cylindrical shells subjected to pure bending load

In this paper, buckling behaviors of composite cylindrical shells made from functionally graded materials (FGMs) subjected to pure bending load were investigated. The material properties were assumed to be graded along the thickness. The non-uniform bending force on the shell section was considered in the buckling government equation of FGM cylindrical shells based on the Donnell shallow shell theory. The prebuckling deformation of the FGM cylindrical shells was neglected and the buckling mode was assumed to occur non-uniformly in local district along the shell circumferential direction. The eigenvalue method was used to obtain the buckling critical condition. The theoretical results were in excellent agreement with those of ABAQUS code. Results show that the inhomogenity of the materials is significant for buckling of FGM cylindrical shells.     

纤维增强复合材料迭层圆柱壳的几何非线性分析

本文从非线性弹性理论出发,在小应变、中等小转动的前提下,全面考虑了变形对于平衡方程的影响,导出了和传统理论不同的壳体非线性理论;并用摄动法和伽略金法分别求解了四边不可动固支正交各向异性复合材料迭层园桂壳块以及考虑横向剪切的四边可动简支园桂形扁壳的非线性弯曲问题。计算表明:变形较大时,变形对所有平衡方程的影响都是值得注意的。      

Vibration of composite-material cylindrical shells with ring and/or stringer stiffeners

Free vibration is analyzed for thin-walled circular cylindrical shells constructed of composite materials and provided with ring and/or stringer stiffeners. Numerical results are presented for graphite-epoxy shells: unstiffened and stiffened with rings only, stringers only, and both rings and stringers.     

Delamination buckling and postbuckling in composite cylindrical shells under combined axial compression and external pressure

A series of finite element analyses on the delaminated composite cylindrical shells subject to combined axial compression and pressure are carried out varying the delamination thickness and length, material properties and stacking sequence. Based on the FE results, the characteristics of the buckling and postbuckling behaviour of delaminated composite cylindrical shells are investigated. The combined double-layer and single-layer of shell elements are employed which in comparison with the three-dimensional finite elements requires less computing time and space for the same level of accuracy. The effect of contact in the buckling mode has been considered, by employing contact elements between the delaminated layers. The interactive buckling curves and postbuckling response of delaminated cylindrical shells have been obtained. In the analysis of post-buckled delaminations, a study using the virtual crack closure technique has been performed to find the distribution of the local strain energy release rate along the delamination front. The results are compared with the previous results obtained by the author on the buckling and postbuckling of delaminated composite cylindrical shells under the axial compression and external pressure, applied individually.     

复合材料圆柱壳的非线性稳定性分析

本文应用能量变分方法,对加筋多层的复合材料圆柱壳,进行了非线性稳定性分析,处理了均匀轴压和横向载荷两种载荷情况。文中用卡门-佟聂耳方程考虑了柱壳失稳时的几何非线性影响,同时通过剪切模量的非线性变化考虑了复合材料的物理并线性影响。本文也分析了初始缺陷对于屈曲特性的影响。文中具体计算了硼/环氧圆柱壳失稳的数值算例。分析和计算表明,材料的剪切非线性和初始缺陷的几何非线性对圆柱壳的屈曲特性有着显著的影响。     

Limit load carrying capacity for spherical laminated shells under external pressure

The aim of the present paper is to discuss possible failure modes encountered in the analysis of multilayered laminated spherical shells having different shallowness parameters and subjected to external pressure. Two various approaches are proposed: the first based on the global buckling analysis and local determination of FPF for each individual layer in a laminate and the second postulating global investigations of both buckling as well as failure (in the sense of LPF) phenomena in laminated structures. The intersection of two curves corresponding to bifurcation buckling and breaking of fibres forms the limit load carrying capacity curve for the analysed shells. The first part of the work is devoted to the analytical prediction of the LLCC curves. Next, the theoretical results are compared with the numerical ones obtained with the use of strict geometrically nonlinear formulation for composite shells. Various types of materials are analysed herein, i.e. both unidirectional as well as woven roving composite materials. The analysis includes also some remarks dealing with the possibility of composite topology optimization in order to obtain the maximal LLCC.     

Transient Dynamic Response of Clamped-Free Hybrid Composite Circular Cylindrical Shells

Dynamic response of multilayer circular cylindrical shells composed of hybrid composite materials subjected to lateral impulse load is studied in this paper. The boundary conditions (B.C.s) are considered to be clamped-free. Both isotropic (metal) and orthotropic (composite) layers are used simultaneously in the hybrid lamination. There is no limitation for fibre orientation. First order shear deformation theory (FSDT) and Love’s first approximation theory are utilized in the shell’s equilibrium equations. Equilibrium equations for free and forced vibration problems of the shell are solved using Galerkin method. Finally, time response of displacement components of Fibre-Metal Laminate (FML) cylindrical shells is derived using mode superposition method. The effect of lay up, material properties, fibre orientation and volume fraction of metal layers on the dynamic response of the shell are investigated. New interesting results are obtained and discussed providing a helpful insight for aircraft structure’s designers.     

Geometrically nonlinear analysis of laminate composite plates and shells using the eight-node hexahedral element with one-point integration

An eight-node hexahedral isoparametric element with one-point quadrature for the geometrically nonlinear static and dynamic analysis of plates and shells of laminate composite materials is formulated and implemented in this work. The element is free of volumetric and shear locking and spurious modes are not detected. Shear locking is avoided using a corotational system for strain and stress components, whereas volumetric locking is controlled using one-point quadrature for the dilatational (or spherical) part of the gradient matrix. The efficiency and potential of the three-dimensional element in the analysis of plates and shells of laminate composite materials undergoing large displacements and rotations are shown solving several numerical examples and comparing with results obtained by other authors using different plate and shells elements.     

Nonlinear Finite Element Analysis of Rubber Composite Shells

A finite-element solution for rubber composite shells is presented. Sandwich laminates with a rubber core have also been studied. Incompressibility of a rubber matrix and complexity of composite shells bring forth the need for a sound numerical model to describe the behavior of such engineering materials. The developed model was applied to a degenerate shell element within the limits of the first- and third-order shear deformation theories. The model allows to predict with a sufficient accuracy the nonlinear behavior of sandwich shells with composite skins and rubber cores and composite shells with a rubber matrix.