复合材料层合板结构振动声辐射优化

通过有限元法计算复合材料层合板结构的振动特性,然后采用瑞利积分进行结构的声辐射分析.在此基础上,给出考虑振动声辐射特性的复合材料层合板的优化设计模型,研究简谐激励力下的结构灵敏度计算,重点推导了声学灵敏度分析公式,并采用序列线性规划方法进行了优化求解.数值算例表明通过层合板铺层厚度和角度的优化可以有效降低结构的振动声辐射,同时验证了灵敏度算法的精度和优化方法的有效性.     

复合层合矩形板水下声辐射解析计算

基于一阶剪切形变理论(FSDT),建立四边简支矩形复合层合板水下声辐射解析模型,采用一种基于定积分的方法计算板表面流载声压,以提高辐射声阻抗的运算效率。为验证算法的正确性,将所得结果与数值计算方法进行了对比。1阶剪切形变理论计算结果也与经典层合板理论(CLPT)的计算结果进行了比较,指出其在计算复合层合板声辐射时的优势。最后分析了跨厚比,铺层角度等参数对声辐射的影响,为结构噪声控制提供参考。     

对声辐射模态法的改进

以简支矩形板为例，通过声辐射模态研究结果声辐射问题，从物理和数学意义上对声辐射模态进行了解释，并对声辐射的自由度进行讨论，由于声辐射模态形状是频率的函数，这限制了声辐射模态在噪声控制中的应用。本文提出对声辐射模态算法进行改进，使声辐射模态形状在中、低频时与频率无关。最后进行了数值计算研究，结果表明，这种方法是可行的。     

温度对高速列车层合板振动声辐射的影响

我国高速铁路线路分布十分广阔,季节更替明显,温度变化显著,而温度变化将对高速列车层合板的振动声辐射产生影响。针对这一问题,基于混合有限元-边界元方法,建立温度场下的高速列车层合板振动声辐射预测模型,分析温度变化对高速列车层合板振动声辐射的影响规律。结果表明:随着温度升高,层合板各阶固有频率逐渐降低。在不考虑温度对阻尼特性影响的情况下,温度对230 Hz~340 Hz范围内的振动和声功率级影响显著,随着温度升高,振动位移和声功率级逐渐增大。当温度从-50°C升高到50°C时,该频率范围内的声功率级峰值增大11 d B,即每增加10°C,该显著峰值声功率级增大约1.1 d B。该温度范围内的层合板声功率级总值随着温度的增大呈非线性增长,从-50°C升高到50°C时,声功率级总值增大约4 d B。相关结论可为在考虑温度影响条件下的车体低噪声设计提供参考。     

复合材料层合板故障诊断的一种新方法

本文计算了无损板在给定模态下各单元的能量,求得每个单元对该阶模态下全板能量的贡献,并通过模态实验得到损伤前后各阶固频的变化.分析发现两者之间存在着内在联系,从而得到一种分析小损伤位置和范围的新方法.     

有限元与声辐射模态的薄板声辐射灵敏度分析

采用有限元与声辐射模态方法研究了薄板声辐射的灵敏度。应用有限元方法求出结构的速度分布后,利用Rayleigh积分求出薄板的声压,然后将薄板的声辐射功率表示为薄板速度分布的正定厄米特二次型;将薄板的声辐射功率对设计变量求偏导,薄板声辐射的灵敏度转化为阻抗矩阵的灵敏度与速度分布的灵敏度,最后通过声辐射模态理论和有限元方法可以分别求出结构阻抗矩阵的灵敏度与速度分布的灵敏度。以四边简支的薄板作为数值算例,对所提出的方法进行了验证。     

温度变化下复合材料层合板的试验模态分析

通过动力测试试验研究了环境条件变化对复合材料层合板振动特性的影响 , 这对于复合材料结构基于动力响应健康监测和振动控制系统设计使用的安全性具有重要意义。在不同温度条件下利用锤击以及激振器实验方法测定复合材料层合板的动力响应 , 采用随机子空间法 (SSI) 识别了其固有频率、 阻尼以及模态振型。研究结果表明 , 复合材料层合板结构固有频率及阻尼比与温度变化存在逆相关关系 , 而所识别的模态振型变化并没有非常清晰的相关关系。分析结果进一步表明 , 复合材料结构振动控制和健康监测系统设计过程中需要考虑上述影响。      

含孔复合材料层合板逐渐损伤破坏分析

采用逐渐损伤模型有限元技术对含复合材料层板损伤破坏规律进行了研究，编制了面向对象的后处理软件，为损伤累积，损伤扩展与破坏以及损伤类型与模式的预测和研究提供了先进手段，并针对含孔T30／KH304复合材料层板进行了数值模拟和试验研究，研究表明，采用二维逐渐损伤模型及分析方法，以及所发展的后处理模拟分析软件能够较好地模拟含孔层合板的损伤破坏规律和位移－载荷的响应规律，以豚预测层合板的损伤类型，破坏模式和破坏强度，得到了一些有意义的结论。     

纤维增强复合材料层合板分层破坏的研究

本文对纤维增强复合材料层合板的分层破坏进行了大量的试验,同时用三维有限元进行应力分析。试验和分析结果表明此类层合板的分层总是发生在θ/90界面上,该界面上不仅层间剪应力大而且层间正应力也大。通过对不同θ/90界面的临界能量释放率的测定表明,对层合板不同的θ/90分层界面的G_ⅠC和G_ⅡC是随θ角的变化而变化。文中对一个Ⅰ型,Ⅱ型耦合型能量释放率分层判据的应用作了改进,试验结果表明此改进是有效的。     

圆锥头弹体冲击复合材料层合板数值模拟

采用ABAQUS软件建立了圆锥头弹体正冲击复合材料层合板的有限元模型,并与已有文献结果进行对比验证了模型的可靠性,进而研究圆锥头弹体以不同的入射角度冲击复合材料层合板时初始速度与剩余速度的关系、复合材料层合板的破坏形态及弹体发生跳弹的规律。结果表明：弹体以90°入射角冲击复合材料层合板,在距离临界速度较大时,弹体的剩余速度与初始速度呈线性关系;不同的初始速度对复合材料层合板的损伤面积和破坏机制也不相同;弹体的入射角度越小、复合材料层合板越厚,越容易产生跳弹现象,并给出了入射角度和铺陈层数对跳弹现象的影响规律。该研究可为各种防护装备的设计和优化提供参考。     

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.     

Theoretical modelling of laminated composite plates

Formulation of appropriate governing equations, simpler than the three-dimensional equations of elasticity yet capable of predicting, fairly accurately, all important response parameters such as stress and strain, is attempted in modelling a structural component. Several theoretical models are available in the literature for the analyses of plates. The emergence of fibre-reinforced plastics as an attractive form of structural construction, added a new complexity to the modelling considerations of laminates by requiring the estimation of the interlaminar stresses and strains. In this paper, modelling considerations of laminated composite plates are discussed. The classical laminated plate theory and higher-order shear deformation models are reviewed to bring out their interlaminar stress predictive capabilities, and some new modelling possibilities are indicated. This work has been supported by the Aeronautics Research and Development Board, Ministry of Defence, Government of India.     

Thermal buckling of cross-ply laminated composite and sandwich plates according to a global higher-order deformation theory

A two-dimensional global higher-order deformation theory is presented for thermal buckling of cross-ply laminated composite and sandwich plates. By using the method of power series expansion of continuous displacement components, a set of fundamental governing equations which can take into account the effects of both transverse shear and normal stresses is derived through the principle of virtual work. Several sets of truncated Mth-order approximate theories are applied to solve the eigenvalue problems of a simply supported multilayered plate. Modal transverse shear and normal stresses can be calculated by integrating the three-dimensional equations of equilibrium in the thickness direction, and satisfying the continuity conditions at the interface between layers and stress boundary conditions at the external surfaces. Numerical results are compared with those of the published three-dimensional layerwise theory in which both in-plane and normal displacements are assumed to be C⁰ continuous in the continuity conditions at the interface between layers. Effects of the difference of displacement continuity conditions between the three-dimensional layerwise theory and the global higher-order theory are clarified in thermal buckling problems of multilayered composite plates.     

层合板频率响应与声功率双目标优化设计

利用遗传算法对复合材料层合板结构的固有频率间隔和辐射声功率进行双目标优化设计。利用分层理论结合有限元模型求解层合板的固有频率和振速分布。通过声辐射模态理论,计算层合板结构辐射声功率。以铺设角度作为设计变量,第一阶与第二阶固有频率间隔和辐射声功率作为双目标优化目标函数,以某4层的层合板结构为例,采用目标加权法优化目标函数。研究了不同权重系数、不同频率时固有频率间隔最大化和声功率最小化对应的优化铺设角度。由数值分析结果可知:不同的权重系数比下获得的Pareto最优解不同;在同一权重系数下,两个优化目标所起的作用不尽相同;随着频率的增加,选择相对较大的权重系数可使Pareto最优解较好地兼顾两个优化目标。     

用变分渐近法进行复合材料层合板仿真及三维场重构

为有效模拟和准确重构复合材料层合板三维应力/应变/变形场,基于变分渐近方法构建单斜对称的复合材料层合板渐近修正理论和重构关系。主要内容包括:基于旋转张量分解概念用一维广义应变和翘曲表示板的三维应变场,以考虑包括板翘曲变形在内的所有变形;基于变分渐近法将原三维问题分析严格拆分为非线性二维板分析(等效单层板模型)和沿法线方向的一维线性分析;通过层合板厚跨比和二维应变量阶数2个较小参数将应变能渐近修正到第二阶,并转换为Reissner形式以便于实际应用;利用生成的二维板变形和翘曲函数精确重构三维场。通过一具有20层复合层合板的柱形弯曲算例表明:基于该理论和重构过程开发的渐近变分程序VAPAS重构生成的三维应力场精确性较一阶剪切变形理论和古典层合理论更好,与三维有限元精确解相一致。     

Computation of transient hygroscopic stresses in unidirectional laminated composite plates with cyclic and asymmetrical environmental conditions

External variations in temperature and moisture are of primary importance for the long term behaviour of structures made of polymer matrix composites, because they induce residual stresses within laminated composite plates. It was shown (Hahn et al., 1978; Benkeddad et al., 1995, 1996; Tounsi et al., 2000, 2002, 2004; Adda-Bedia et al., 2001; Tounsi and Adda-Bedia, 2003a, b) that the heterogeneity and the anisotropy of such plates, have an influence on the distribution of transient hygroscopic stresses through the thickness of composite plates. The aim of the present paper is to present a simplified approach for the calculation of transient hygroscopic stresses within unidirectional laminates in the case where these latter are exposed to the cyclic and unsymmetric environmental conditions. Several examples are presented to assess such stresses and to demonstrate the efficiency of the used method. These stresses have to be taken into consideration for the design of composite structures submitted to a moist environment.     

Finite volume analysis of laminated composite plates

A numerical procedure for analysis of general laminated plates under transverse load is developed utilizing the Mindlin plate theory, the finite volume discretization, and a segregated solution algorithm. The force and moment balance equations with the laminate constitutive relations are written in the form of a generic transport equation. In order to obtain discrete counterparts of the governing equations, the plate is subdivided into N control volumes by a Cartesian numerical mesh. As a result, five sets of N linear equations with N unknowns are obtained and solved using the conjugate gradient method with preconditioning. For the method validation, a number of test cases are designed to cover thick and thin laminated plates with aspect ratio (width to thickness) from 4 to 100. Simply supported orthotropic, symmetric cross‐ply, and angle‐ply laminated plates under uniform and sinusoidal pressure loads are solved, and results are compared with available analytical solutions. The shear correction factor of 5/6 is utilized throughout the procedure, which is consistent with test cases used in the reviewed literature. Comparisons of the finite volume method results for maximum deflections at the center of the plate and the Navier solutions obtained for aspect ratios 10, 20, and 100 shows a very good agreement. Copyright © 2016 John Wiley & Sons, Ltd.     

铺设角度与铺层顺序对层合板稳定性的影响

以层合板结构的临界屈曲载荷系数最大化为优化目标,基于改进型模拟退火算法对层合板结构铺设角度和铺层顺序进行优化。由于层合板结构的铺层角度是离散变量,模拟退火算法适合求解离散变量的优化问题。利用模拟退火算法优化层合板铺层,在算法内采用并行计算、引入记忆功能同时设置双阈值终止准则,有效地提高了优化过程的收敛速度,同时避免优化过程中出现局部最优解。以临界屈曲载荷系数作为目标函数,选取复合材料层合板的铺设角度顺序为设计变量,采用改进的模拟退火算法得出复合材料层合板的最优铺设角度以及铺层顺序。     

Buckling and free vibration of non-homogeneous composite cross-ply laminated plates with various plate theories

Various theories of homogeneous laminated plates are extended to study the buckling and free vibration behavior of non-homogeneous rectangular composite laminates. The equations governing the dynamic response of non-homogeneous composite laminates are deduced. Numerical results for the natural frequencies and critical buckling loads of symmetric cross-ply laminates are presented. The influences of the degree of non-homogeneity, aspect ratio, thickness ratio and in-plane orthotropy ratio on the natural frequencies and critical buckling loads are investigated. The results obtained for homogeneous cases are compared with their counterparts in the literature. The study concludes that the classical plate theory is inadequate for predicting the structural response of non-homogeneous laminates, and that the free vibration and the state of the stability are affected strongly by the degree of nonhomogeneity.