夹芯复合材料结构阻尼特性研究

从粘弹性材料的本构关系出发,应用复特征值理论推导了夹芯复合材料结构阻尼的计算方法;同时基于能量损耗原理和阻尼的产生机理,研究了夹芯复合材料结构阻尼计算的模态应变能方法;提出了两种承载/减振夹芯复合材料结构模型,应用动态力学热分析方法测量了芯材的阻尼参数;应用两种阻尼计算理论和有限元数值分析相结合的方法研究了两种夹芯结构模型的损耗因子,并与试验结果进行了比较;分析了夹芯厚度对结构损耗因子的影响.     

纤维增强复合材料动力学固有特性及阻尼特性分析

基于模态应变能原理,推导了复合材料层合梁阻尼计算式,进行复合材料模态应变能Abaqus有限元验证;采用手糊和真空工艺制作了3种不同复合材料层合梁试件,并开展了动力学试验,得到了复合材料层合梁固有频率和面内各向异性阻尼系数;分析了不同角度铺层对层合梁固有频率和结构阻尼比的影响规律.结果表明:复合材料面内损耗系数以剪切损耗最大;手糊制作的层合试件材料主方向损耗因子均较真空制作的要大;两种常用的正交布材料主方向损耗因子存在下列关系:高强正交布(手糊)＞无碱正交布(手糊)＞高强正交布(真空)＞无碱正交布(真空).     

嵌入双层阻尼薄膜共固化复合材料带筋结构的自由振动EI北大核心CSCD

为探究嵌入双层阻尼薄膜共固化复合材料带筋结构的振动特性,根据一阶剪切变形理论建立了该结构的动力学解析模型,将复模量理论和复合材料力学理论相结合,推导了其复数形式的控制方程,采用纳维法得到了满足位移边界条件的理论解,将理论解同有限元结果进行对比,验证了该模型的有效性。进一步利用已验证理论模型分析了结构的几何和材料参数对其动力学特性的影响。结果表明:结构固有频率随着筋条高度和宽度的增大而增大;随着筋条高度和宽度的增加,结构损耗因子随之减小;当两阻尼层剪切模量之比较大时,结构的固有频率和损耗因子对其剪切模量之比的变化不再敏感。     

岩棉夹芯金属屋面板的阻尼性能研究

岩棉夹芯金属板广泛应用于大跨度屋盖结构中,其弱刚度和阻尼性能会改变屋面脉动风荷载特性并影响屋盖结构的风振性能,但目前在设计中还鲜有考虑。对岩棉夹芯材料的拉压强度、弹性模量和泊松比等基本力学参数进行了测试。采用振动梁法进行了岩棉夹芯材料的阻尼性能试验,根据试验结果拟合得到了其损耗因子-频率曲线。进一步对一块0.4m×2m的典型跨度岩棉夹芯屋面板的阻尼特性进行数值分析,运用模态应变能法计算出该屋面板各阶模态下的损耗因子。结果表明,岩棉夹芯金属屋面板的模态损耗因子可高达0.5,其中垂直屋面板主振型的最小损耗因子都接近0.2,说明屋面板的阻尼效应在结构风振分析中不容忽视。     

基于材料参数随机性的粘弹性结构振动特性分析

基于粘弹性材料的随机性对粘弹性结构的振动特性进行了分析，研究了模量模型的随机性对结构固有频率和模态损耗因子的影响，在模型的随机性中分别考察了常复数模型，Kelvin-Voigt模型和三参数标准流变学模型，结果表明，粘弹性材料参数的随机性对粘弹性结构的模态损耗因子的影响还是比较大的，因此，对粘弹性结构采取随机分析是非常必要的。     

嵌入式共固化穿孔阻尼层复合材料结构动力学性能分析

建立嵌入式共固化穿孔阻尼层复合材料结构（ECPDLCS）的有限元模型（FEM）,提出用改进的应变能法分析该穿孔结构的阻尼损耗因子,模态分析实验验证了文中数值模拟模型和方法的有效性。用验证的模型和方法分别研究了阻尼层厚度、穿孔孔径和孔距对整体结构模态损耗因子和频率的影响,以及在阻尼层面积比相同的情况下,孔径和孔距的分布与复合材料整体结构动力学性能的关系。结果表明：增加阻尼层厚度、减小阻尼层穿孔孔径和孔距,均有利于增大模态损耗因子,但结构固有频率则会有不同程度地降低;在相同面积比的情况下,损耗因子随着孔距和孔径的增加而增加,而固有频率则随之降低。文中的模型和方法对ECPDLCS的动力学性能理论预估具有重要的指导意义。     

玻璃纤维夹芯材料力学性能与阻尼特性分析

对大跨度建筑用复合金属屋面板的玻璃纤维夹芯材料的力学性能进行了试验测定。测得了玻璃纤维棉层压方向和顺纹方向的拉压强度、弹性模量和泊松比等基本力学参数,结果表明层压方向和顺纹方向的力学性质不相同。采用振动梁法进行了阻尼特性试验,得到了材料损耗因子的值,并根据试验数据拟合出了玻璃纤维棉损耗因子-频率的曲线,在测试频率范围内材料的损耗因子值为0.5左右,表明该材料为高阻尼材料。进一步以一块玻璃纤维夹芯复合金属板为算例,采用模态应变能法对其阻尼特性进行了数值分析。玻璃纤维夹芯复合屋面板的各阶模态损耗因子在0.3～0.5左右,表明玻璃纤维夹芯复合金属板具有较高的结构阻尼,在大跨度结构风振计算中将玻璃纤维夹芯复合金属屋面板看作刚性板是不正确的。     

层间过渡约束阻尼结构动力响应的分布参数传递函数解

针对传统约束阻尼结构振动能耗散有限问题,引入“层间过渡层”设计的概念,提出一种层间过渡约束阻尼结构,采用分布参数传递函数法对该结构进行了动力响应分析。经推导,得到了阻尼结构的各阶损耗因子和频率的解析解,并进行了有限元仿真验证,二者计算结果吻合良好。以悬臂阻尼板为例,探讨了过渡层参数行为对其频响特性的影响,结果表明,在结构振动时,过渡层可将变形传递给阻尼层,起到放大阻尼层的剪切变形作用,从而耗散更多的振动能量;同时还讨论了过渡层的厚度、剪切模量、密度与泊松比对结构固有频率和损耗因子的影响,为进一步优化工作打下了良好基础。     

基于区间摄动法的不确定结构高频动响应预示

统计能量分析是目前航空航天、汽车、船舶和核能等领域解决高频段振动及噪声问题的有效方法之一。考虑稳态统计能量分析模型中损耗因子和外载荷的不确定性,将带有测量误差的内损耗因子和耦合损耗因子等参数以区间变量形式表示。提出基于区间摄动方法的不确定结构高频段动响应预示方法,给出每个统计能量分析子系统总能量区间的计算步骤及方法,揭示损耗因子和外载荷测量误差对稳态响应预示结果的影响规律,通过对两块复合板结构的实验验证了理论的合理性和有效性。     

结构动力学应用中若干基本概念的研究

结构动力特性被广泛应用于结构振动控制、结构可靠性设计和健康监测,由此涉及到一些动力学基本概念的理解问题尚待深入探讨。采用一简支梁横向振动算例以及分别通过模态位移法和模态加速度法对多自由度系统的响应振幅进行分析计算,探讨结构位移响应与第一阶固有频率的关系、结构各阶位移模态的贡献与模态应变能的关系。基于模态正交性,通过分析多自由度振动系统的位移响应,论述了系统共振的必要条件,即在保证系统振动频率(某阶固有频率)等于激励频率的同时,其位移响应还应呈现出相应模态的形态;实现多自由度系统纯模态共振,可用于精确识别结构的模态参数。     

Free vibration analysis of composite sandwich plates with different truss cores

The free vibration of composite truss core sandwich plates is investigated. The natural frequencies of the sandwich plate are calculated by using the classic laminated plate theory, the first-order shear deformation theory, Reddy's third-order shear deformation theory, and a Zig-Zag theory. The differences between the natural frequencies, obtained from the four theories, are compared. The influences of structural parameters on the natural frequencies and the ratios of natural frequency to equivalent density of the sandwich plates with pyramidal core, tetrahedral core, and 3D-Kagome core are studied with the aid of the Zig-Zag theory.     

玻璃纤维增强塑料夹层板振动能量流可视化研究

为探索复合材料结构在外部激励作用下的振动能量传递及分布特性,基于结构声强法对玻璃纤维增强塑料夹层板的振动能量可视化技术进行了研究。基于结构声强概念,结合复合材料结构层合理论推导了玻璃纤维增强塑料夹层板的结构声强解析表达式;给出了基于有限元数值方法的结构声强可视化计算实现流程,利用Python和Matlab语言编写了相应计算程序;接着从固有频率、振型及结构声强矢量三个方面验证了所提出可视化程序的有效性;以玻璃纤维增强塑料夹层板为例,利用结构声强技术提供的图形信息实现了激励源定位及振动能量传递特性的可视化分析;最后提取了剪切分量、扭转分量和弯曲分量对结构声强矢量的贡献情况,直观展示了剪切分量在振动能量传递过程中的决定性作用。     

The influence of correlating material parameters of gradient foam core on free vibration of sandwich panel

For the sandwich panel with mass density gradient (DG) foam core, the Young's modulus of the core varies with the mass density along the thickness direction. To characterize the correlative effect of Young's modulus and mass density of the DG closed-cell foam material, a simplified formula is presented. Subsequently, based on a high-order sandwich plate theory for sandwich panel with homogeneous core, a new gradient sandwich model is developed by introducing a gradient expression of material properties. Finite element (FE) simulation is carried out in order to verify this model. The results show that the proposed model can predict well the free vibration of composite sandwich panel with the gradient core. Finally, the correlating effects of material parameters of the DG foam core on the natural frequencies of sandwich panel are investigated. It is found that the natural frequencies of sandwich panels decrease as the gradient changes of the DG foam cores increase under the condition of that the core masses keep constant.     

基于剪切耗能假设的黏弹性夹芯梁的振动和阻尼特性

基于一阶剪切变形理论和哈密顿原理建立了三层粘弹性夹芯梁结构的有限元模型并对其振动和阻尼特性进行了研究。建模时认为粘弹材料层不可压缩,振动能量是依靠粘弹性层的剪切变形来耗散的。为验证本模型的正确性,将其与解析解作了对比。同时,为了证明本方法的优越性,将其与常用的“实特征模态”、“近似复特征模态”、“钻石法”和“近似法”四种数值方法做了比较。结果表明本方法的精度在这几种数值方法中是最好的。最后,讨论了粘弹性夹芯梁结构参数变化对系统固有频率和损耗因子的影响,得到了一些有工程实际意义的结论。     

复合材料夹层壳振动分析的高阶剪切变形理论

本文提出了计及复合材料面板横向剪切变形的夹层壳高阶位移模式,该模式满足夹层壳上、下表面剪应力为零的条件,并以此推导出夹层壳自由振动的有限元方程,讨论了夹层壳的夹芯及面板的阻尼特性,给出阻尼矩阵的形成方式,将数值计算与实验结果进行了对比,最后给出了阻尼比Ψ随夹芯厚度h_c、剪切模量G和阻尼损耗因子β的变化曲线.     

阻尼夹芯复合材料加筋板的振动分析与数值模拟

以阻尼夹芯复合材料加筋板为研究对象,依据一阶剪切变形理论(FSDT)和Hamilton原理,推导板和加强筋的应变能、动能表达式,采用变分原理建立控制微分方程,根据相关边界条件和傅里叶级数求解方程。建立了ANSYS阻尼夹芯复合材料加筋板的有限元模型,该模型考虑到阻尼夹芯复合材料加筋板中阻尼材料与纤维预浸料间的结合方式,用模态应变能有限元数值模拟方法研究了结构的动力学性能,并通过对数值模拟结果与理论解的比较,验证了模型的合理性和有效性。探讨了不同的筋条尺寸、不同的筋条数量、不同的筋条分布方式对阻尼夹芯复合材料加筋板动力学性能的影响,得出了阻尼夹芯复合材料加筋板的一阶模态频率和损耗因子随不同参数的变化曲线,其结论为阻尼夹芯复合材料加筋板的优化设计提供参考。     

长厚比对正六边形铝蜂窝夹层板等效板模型动力学计算精度的影响

为提高正六边形铝蜂窝夹层板的数值计算精度,研究了长厚比对其等效板模型动力学计算精度的影响。针对芯层均匀壁厚的正六边形铝蜂窝夹层板,首先研究了它的等效板模型,包括Reissner理论模型、蜂窝板理论模型和层合板低阶剪切理论模型;然后,将等效板模型与精细化模型相同模态振型的模态频率进行比较,分析了长厚比对等效板模型动力学计算精度的影响。结果表明:芯层均质化后模型模态频率的计算误差很小;层合板低阶剪切理论模型是计算精度较高的等效板模型;Reissner理论模型在长厚比为7.37时计算精度最低,蜂窝板理论模型对厚板的计算精度比薄板低,层合板低阶剪切理论模型对厚板的计算精度比薄板高。      

Modeling and Re-Examination of Nonlinear Vibration and Nonlinear Bending of Sandwich Plates with Porous FG-GPLRC Core

In this article, an inhomogeneous model is proposed to predict the material properties of porous GPL-reinforced composite (GPLRC) and to predict the mechanical responses of a sandwich plate which consists of top and bottom metal face sheets and a porous GPLRC core. The GPLRC core is assumed to be multilayers, and each layer may have different values of porosity coefficient to achieve a piece-wise functionally graded pattern. Young's moduli along with shear modulus of porous GPLRC core are predicted by a generic Halpin-Tsai model in which the porosity is included. Thermo-mechanical properties of both metal face sheets and porous GPLRC core are assumed to be temperature-dependent. The governing equations of motion for porous sandwich plates are solved by applying a two-step perturbation approach to obtain the analytical solutions for the two cases of nonlinear vibration and nonlinear bending of porous sandwich plates. Numerical studies are performed to compare the results obtained from the present model and the equivalent isotropic model (EIM). The results reveal that, for most cases, the difference of natural frequencies between two models is over 30%, and the vibration frequency–amplitude curves and the bending load–deflection curves are underestimated by using the EIM.     

Core material effect on wave number and vibrational damping characteristics in carbon fiber sandwich composites

A sandwich composite is typically designed to possess high bending stiffness and low density and consists of two thin and stiff skin sheets and a lightweight core. Due to the high stiffness-to-weight and strength-to-weight ratios, sandwich composite materials are widely used in various structural applications including aircraft, spacecraft, automotive, wind-turbine blades and so on. However, sandwich composite structures used in such applications often suffer from poor acoustic performance. Ironically, these superior mechanical properties make the sandwich composites “excellent” noise radiators. There is a growing interest in optimizing and developing a new sandwich composite which will meet the high stiffness-to-weight ratio and offer improved acoustic performance. The focus of this study is to investigate the structural–vibrational performance of carbon-fiber face sheet sandwich composite beams with varying core materials and properties. Core materials utilized in this study included Nomex and Kevlar Honeycomb cores, and Rohacell foam cores with different densities and shear moduli. The structural–vibrational performance including acoustic and vibrational damping properties was experimentally characterized by analyzing the wave number response, and structural damping loss factor (η) from the frequency response functions, respectively. It was observed that the relationship between the slopes of the wave number data for frequencies above 1000 Hz is inversely proportional to the core material’s specific modulus (G/ρ). The analysis also showed the importance of using a honeycomb core’s effective properties for equal comparison to foam-cored sandwich structures. Utilizing analytical modeling, the loss factors of the core materials (β) was determined based upon the measured structural loss factors (η) for a frequency range up to 4000 Hz. It was determined that low shear modulus cores have similar material damping values to structural damping values. However as the core’s shear modulus increases, the percent difference between these values is found to increase linearly. It was also observed that high structural damping values correlated to low wave number amplitudes, which correspond to reductions in the level of noise radiation from the structure.     

Vibration and damping analysis of a three-layered composite annular plate with a viscoelastic mid-layer

The natural frequencies and modal loss factors of the three-layered annular plate with a viscoelastic core layer and two polar orthotropic laminated face layers are considered. The discrete layer annular finite element is employed to derive the equations of motion for the three-layered annular plate. The viscoelastic material in the central layer is assumed to be incompressible, and the extensional and shear moduli are described by the complex quantities. Complex eigenvalued problems are then solved, and the frequencies and modal loss factors of the composite plate are extracted. The results of the symmetric and non-symmetric composite annular plates are both presented. The effects of material properties, radius to thickness ratio, stacking sequences and thickness of face layers, and thickness of the viscoelastic core layer are discussed.