复合材料的耐油性试验

本文对Ｔ３００／５４０５和Ｔ３００／８９１１复合材料单向板与迭层板做了耐油性试验，结果表明：Ｔ３００／５４０５耐油性优于Ｔ３００／８９１１，且迭层板耐油性优于单层板。     

复合材料夹层板壳一种等效分析方法

本文研究了复合材料夹层板壳的一种等效分析方法,首先由壳体理论导出了夹层板壳的内力和位移表达式,通过与各向异性单层板壳理论的比较,提出了二者等效的条件,从而把夹层板壳问题简化为一个等效各向异性单层板壳问题,这用有限元法很容易求解,并对一个工程实例进行了计算,证实了该方法的有效性。      

液面上复合材料板的非线性动力响应

导出置于液面上的复合材料迭层板变形时流体作用力的近似表达式：由ａｍｉｌｔｏｎ原理建立考虑横向剪切变形以及流固耦合效应时迭层板的非线性动力方程;采用Ｐａｒｋ差分公式求解了板的非线性流固耦合动力响应;讨论了不同截荷类型下流场深度及几何非线性对动力响应的影响     

复合材料夹层板壳一种等效分析方法

本文研究了复合材料夹层板壳的一种等效分析方法,首先由壳体理论导出了夹层板壳的内力和位移表达式,通过与各向异性单层板壳理论的比较,提出了二者等效的条件,从而把夹层板壳问题简化为一个等效各向异性单层板壳问题,这用有限元法很容易求解,并对一个工程实例进行了计算,证实了该方法的有效性。     

各向异性损伤理论与复合材料层板损伤的实验研究(一)-各向异性损伤理论

本文讨论了各向异性损伤力学的基本概念并介绍了以应变等效性假设为基础的Lemaitre模型和以能量等效性假设为基础的Cordebois模型.在此基础上作者导出了两种损伤模型的损伤能释放率的表达式.文中作者定义了一维损伤时弹性材料板单元的一些损伤定义,并导出了两种模型在一维损伤时损伤能释放率Y₂的简单表达式,从而为复合材料层板损伤测量的实验研究提供了理论基础,     

板片空间结构体系的结构分析：板片空间结构体系研究论文之二

本文对板片空间结构体系结构分析中的主要问题：复合迭层板的强度分析及总体结构的稳定性分析作了具体论述，并用结构模型试验对理论分析结果的可靠性作了验证。     

复合材料迭层板柱状弯曲的非线性流固耦合动力响应分析

导出置于液面上的复合材料迭层板变形时流体作用力的近似表达式; 由Ham ilton 原理建立了考虑横向剪切变形以及流固耦合效应时迭层板的非线性动力方程; 采用差分方法求解了迭层板的非线性流固耦合动力响应; 讨论了不同载荷类型下流场深度及几何非线性对动力响应的影响。      

实体退化板单元及其在板的振动分析中的应用

经典板壳单元是由板壳理论构造出来的,而经典的板壳理论是在空间弹性理论的基础上考虑板壳的基本假定得来的。在空间等参数单元的基础上,直接引入板壳的基本假定,修改空间等参数单元的弹性矩阵,从而构造出适合于厚薄板壳分析的20结点实体退化板单元,并将其应用于开口圆柱薄壳的静力分析和厚薄板的固有振动分析。数值算例表明,该单元收敛快,稳定性好,具有较高的精度。此外,该单元还可以用于曲边变厚度板、壳体及层合板的振动分析。     

板锥网壳结构的静力有限元分析

板锥网壳结构是一种受力性能合理,技术经济效益良好的新型空间结构形式。本文采用组合结构有限元法对板锥网壳结构进行了线弹性静力分析,分别考虑了三种计算力学模型,着重研究了具有内节点的三角形板单元及复合材料层合板单元,编制了板锥网壳结构的专用计算程序。     

复合材料层板层间缺陷分析——剪切滑移

根据三维弹性平衡方程和层间剪切滑移条件,导出了一个复合材料层板层间剪切滑移模型。本文模型具有一般形式的二维板壳理论的位移场及其平衡方程,但因引入了能反映层板界面粘贴情况及板面条件的剪切变形函数,模型因而简单又精确。层板的弯曲问题和屈曲问题被考虑,层间弱粘贴的影响被讨论。数值结果与精确解比较,表明了本文模型的高精度。      

复合材料层板的拟协调罚单元*

本文在文献提出的多变量拟协调元和罚函数相结合的方法基础上构造了考慮耦合和剪切效应的十五自由度三角形层合板单元。此单元适用于薄和中厚层合板的强度分析,具有收敛和应用范围广的优点。文中以各向同性和复合材料层合板多组数例证明了该单元的有效性,同时还讨论了跨厚比L/h和弹性模量比E₁/E₂与剪切效应的关系,得出了一些有意义的结论。     

Static and Dynamic Analysis of Laminated Thick and Thin Plates and Shells by a Very Simple Displacement-based 3-D Hexahedral Element with Over-Integration

A very simple displacement-based hexahedral 32-node element (denoted as DPH32), with over-integration in the thickness direction, is developed in this paper for static and dynamic analyses of laminated composite plates and shells. In contrast to higher-order or layer-wise higher-order plate and shell theories which are widely popularized in the current literature, the proposed method does not develop specific theories of plates and shells with postulated kinematic assumptions, but simply uses the theory of 3-D solid mechanics and the widely-available solid elements. Over-integration is used to evaluate the element stiffness matrices of laminated structures with an arbitrary number of laminae, while only one element is used in the thickness direction without increasing the number of degrees of freedom. A stress-recovery approach is used to compute the distribution of transverse stresses by considering the equations of 3D elasticity. Comprehensive numerical results are presented for static, free vibration, and transient analyses of different laminated plates and shells, which agree well with existing solutions in the published literature, or solutions of very-expensive 3D models by commercial FEM codes. It is clearly shown that the proposed methodology can accurately and efficiently predict the structural and dynamical behavior of laminated composite plates and shells in a very simple and cost-effective manner.     

Impact analysis of laminated composite plates and shells by super finite elements

A super finite element method that exhibits coarse-mesh accuracy is used to predict the transient response of laminated composite plates and cylindrical shells subjected to non-penetrating impact by projectiles. The governing equations are based on the classical theories of thin laminated plates and shells taking into account the von Karman kinematics assumptions for moderately large deflections. A non-linear Hertzian-type contact law accounting for curvatures of the colliding bodies is adopted to calculate the impact force . The theoretical basis of the present finite element model is verified by analysing impact-loaded laminated composite plate and shell structures that have previously been studied through analytical or other numerical procedures. The predictive capability of the present numerical approach is successfully demonstrated through comparisons between experimentally-measured and computed force-time histories for impact of carbon fibre-reinforced plastic (CFRP) plates. The current computational model offers a relatively simple and efficient means of predicting the structural impact response of laminated composite plates and shells.     

Free and forced vibration analysis of laminated composite plates and shells using a 9-node assumed strain shell element

The natural frequencies of isotropic and composite laminates are presented. The forced vibration analysis of laminated composite plates and shells subjected to arbitrary loading is investigated. In order to overcome membrane and shear locking phenomena, the assumed natural strain method is used. To develop a laminated shell element for free and forced vibration analysis, the equivalent constitutive equation that makes the computation of composite structures efficient was applied. The Mindlin-Reissner theory which allows the shear deformation and rotary inertia effect to be considered is adopted for development of nine-node assumed strain shell element. The present shell element offers significant advantages since it consistently uses the natural co-ordinate system. Results of the present theory show good agreement with the 3-D elasticity and analytical solutions. In addition the effect of damping is investigated on the forced vibration analysis of laminated composite plates and shells.     

Transient analysis of FGM and laminated composite structures using a refined 8-node ANS shell element

In this paper, we investigate the vibration analysis of functionally graded material (FGM) and laminated composite structures, using a refined 8-node shell element that allows for the effects of transverse shear deformation and rotary inertia. The properties of FGM vary continuously through the thickness direction according to the volume fraction of constituents defined by sigmoid function, but in this method, their Poisson’s ratios of the FGM plates and shells are assumed to be constant. The finite element, based on a first-order shear deformation theory, is further improved by the combined use of assumed natural strains and different sets of collocation points for interpolation the different strain components. We analyze the influence of the shell element with the various location and number of enhanced membrane and shear interpolation. Using the assumed natural strain method with proper interpolation functions the present shell element generates neither membrane nor shear locking behavior even when full integration is used in the formulation. The natural frequencies of plates and shells are presented, and the forced vibration analysis of FGM and laminated composite plates and shells subjected to arbitrary loading is carried out. In order to overcome membrane and shear locking phenomena, the assumed natural strain method is used. To validate and compare the finite element numerical solutions, the reference solutions of plates based on the Navier’s method, the series solutions of sigmoid FGM (S-FGM) plates are obtained. Results of the present theory show good agreement with the reference solutions. In addition the effect of damping is investigated on the forced vibration analysis of FGM plates and shells.     

Effects of transverse shear and rotatory inertia on large amplitude vibration of composite plates and shells

A review of research in the area of large amplitude vibration of composite plates and shells is presented in this paper. The main focus of this paper is on the effects of geometric nonlinearity, transverse shear deformation and rotatory inertia on the vibration behaviour of single-layered plates and shells. Recent advances made in these areas are reviewed. Some literature on laminated plates and shells made of filamentary composite material is also included. Particular attention is given to the recent developments in the analytical methods of solution. Recent research leading to advances in numerical techniques is also included in the present overview.     

板壳分析与应用

板壳分析是现代固体力学的一个重要分支。这门学科几乎与一切工程设计都有关联,对航天、航空、航海、机械、石化、建筑、水利、动力、仪表、交通等工程设计,尤其具有指导意义。现今,经典的薄板壳线性 理论已较成熟,并在各种工程设计中起着指导作用。然而,在薄板壳非线性领域和厚板壳线性领域,还有许多问题未被解决。章在介绍这门学科发展历史的基础上,概述了作近四十年结合工程实际对波纹板壳、单层板壳、双层金属旋转扁壳、网格扁壳、夹层板壳和复合材料层合板壳等六类薄板壳的非线性弯曲、稳定和振动问题以及厚、薄板壳弯曲问题进行理论探索的情况。     

复合材料任意壳体稳定性研究(Ⅱ)─—本构关系及稳定方程

文中分析了复合材料单层板的弹性主方向及非弹性主方向的弹性特性,进而分析了一般层合板的弹性特性及多层壳的弹性特性,以及导得具有普遍性的多层壳的稳定方程.      

Modal validation of a set of C0-compatible composite shell finite elements

This paper presents efficient C⁰-compatible finite elements for modelling laminated composite shells under free vibrations. Derived from the first-order shear deformation theory (equivalent single-layer laminate model), the elements are well adapted for evaluating the global dynamic response (natural frequencies and mode shapes) of moderately thick multilayered shells. The components of their structural matrices are based on an exact integration per layer, which results in a higher solution accuracy than with standard explicit through-the-thickness schemes. The described finite element formulation, which can be easily implemented in commercial finite element codes, is next validated by means of several experimental modal test cases on thin to relatively thick plates or shells.