分层有限元模型下层合板声功率优化设计

基于遗传算法对层合板结构辐射声功率最小化进行铺设角优化;利用分层有限元模型求解层合板固有频率及振速分布;通过声辐射模态理论计算结构辐射声功率。以铺设角作为设计变量、辐射声功率作为优化变量,分别以某4层、8层层合板结构为例,研究不同频率时声功率最小化对应的优化铺设角。数值分析结果表明,在同一优化铺设角下,优化后第一阶声功率与辐射总声功率差别不大;对相同层合板结构而言,随频率增加声功率优化量增大;相同厚度下层合板铺设层越多声辐射功率优化量越小。     

复合材料层合板的声辐射模态幅值分析

低频时, 控制振动结构第一阶声辐射模态伴随系数可有效控制总声功率。通过分层有限元模型可以求解层合板的位移模式。对层合板的固有频率和动态响应进行了理论推导。结合声辐射模态理论, 研究了层合板铺设角度、 弹性模量比、 跨厚比以及阻尼比等结构参数对层合板结构第一阶声辐射模态伴随系数的影响。计算结果表明, 分层理论结合有限元方法可以较准确地计算层合板固有频率, 而且铺设角度和跨厚比对层合板结构声辐射模态影响较大。     

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。     

复合材料层合板声功率及灵敏度研究

采用分层理论结合有限元模型分析复合材料层合板结构的振动特性,并用声辐射模态理论进行结构声辐射分析。在此基础上,分析声功率关于设计参数的灵敏度,推导声功率灵敏度的表达公式。以四层复合材料层合板为例,着重对声功率关于层合板结构铺层角度和铺层厚度的灵敏度进行了分析研究。数值计算结果显示在层合板基频处,辐射声功率达到最大值,同时在该处灵敏度有明显的升降过程。另外,对于低噪声层合板应以±45°对称的铺设将是最为恰当的设计方案。     

采用分层理论计算层合板的固有频率和振型

采用有限元方法并结合分层理论对复合材料层合板的固有频率和振型进行理论计算,再用实验验证。通过分层有限元模型求解层合板的位移模式,对层合板固有频率进行计算。分析有限元网格数,铺设角度、铺设层数等对固有频率的影响,获得层合板自由振动的前九阶振型,采用实验进行了验证。结果表明,提出的方法可较精确计算层合板的固有频率和振型。     

基于直接搜索方法的层合板多目标优化设计

直接多目标搜索方法(DMS)是一种不需要计算梯度信息并且能实现全局收敛的多目标优化方法。基于直接多目标搜索方法,以简支层合板铺设角度为设计变量,基频和声功率为目标函数进行层合板结构振动与声多目标优化。分别以4层、8层复合材料层合板为例,用DMS方法对其优化设计,并与传统的遗传算法(GA)对比。结果表明,对于4层复合材料层合板,DMS方法比GA方法优化速度快,且能得到全局最优解;对于8层复合材料层合板,用DMS方法比4层板优化所需时间多,但相比GA方法,DMS方法优化更快。     

约束阻尼板结构振动声辐射优化

根据经典薄板理论,建立约束阻尼板有限元模型,将其视作镶嵌于无限大刚性障板,利用Rayleigh积分法推导结构的辐射声功率及灵敏度表达式。以一阶峰值频率或频带激励下的声功率最小化为目标,约束阻尼材料体积分数为约束条件,建立拓扑优化模型,采用渐进优化算法,编制了优化计算程序,获得了约束阻尼材料的最优拓扑构型,并与全覆盖板及基板的辐射声功率进行了对比。研究表明：以声功率最小化为目标,对约束阻尼材料布局进行拓扑优化,能有效抑制结构的振动声辐射,为结构低噪声设计提供了重要的理论参考和技术手段。     

基于动态加权系数和多目标进化的模型修正方法

建立准确的结构动力学模型是结构响应分析的基础,由于模型简化的不确切等因素,必然会带来一定的误差,为了获得高精度的动力学分析模型,需要结合试验数据对模型进行修正。模态试验结果中包含了试件不同状态不同阶次的频率和振型信息,模型修正时需要建立多个目标函数,提出了一种基于动态加权系数的多目标模型修正方法。通过对解的群体实施进化,在每一代非劣解中,挑选各个子目标函数的局部最优解,计算各个局部最优解与子目标期望值的差距,并根据差距对加权系数动态调整,从而在进化过程中对加权系数进行优化,避免维数灾难问题,实现各个子目标函数的快速收敛。采用该方法对导弹全弹动力学模型进行了修正,子目标函数个数达到16个,与基于Pareto最优的模型修正方法相比,用较少的代数实现了各个子目标函数的收敛,提高了群体搜索的效率,取得了较好的修正效果。     

层合板结构声辐射模态传感器分析与测量

利用压电高分子材料聚偏氟乙烯(Polyvinylidene fluoride,PVDF)设计一种阵列式传感器来测量复合材料层合板结构的声辐射模态幅值。以声辐射模态传感器设计理论作为基础,进一步分析了声辐射模态传感器的测量精度影响因素,即粘贴位置和粘贴方向等。利用了声辐射模态传感器对层合板结构的固有频率、声辐射模态幅值以及声功率的进行测试分析。并对实验数据与理论仿真结果进行了分析。     

基于非对称复合材料层合板的准零刚度隔振系统

提出了基于正交铺设复合材料层合板的准零刚度隔振系统。采用理论分析与有限元方法研究了有残余热应力的正交铺设复合材料层合板的双稳定特性及负刚度特性。发现层合板具有负刚度特性的变形区间随层板厚度增加而逐渐变窄。正交铺设复合材料层合板在其厚度略厚于失去双稳定特性临界厚度时具有准零刚度特性。利用准零刚度正交铺设复合材料层合板构造了简单的隔振系统,研究其在中心加速度激励下的加速度传递幅值,并与线性隔振系统的隔振效果进行比较。结果显示该准零刚度隔振系统固有频率低于线性隔振系统固有频率,加速度传递峰值小于线性隔振系统,有效隔振频率范围宽于线性隔振系统。     

Optimal lay-up design of variable stiffness laminated composite plates by a layer-wise optimization technique

The optimal lay-up design for the maximum fundamental frequency of variable stiffness laminated composite plates is investigated using a layer-wise optimization technique. The design variables are two fibre orientation angles per ply. Thin plate theory is used in conjunction with a p-element to calculate the fundamental frequencies of symmetrically and antisymmetrically laminated composite plates. Comparisons with existing optimal solutions for constant stiffness symmetrically laminated composite plates show excellent agreement. It is observed that the maximum fundamental frequency can be increased considerably using variable stiffness design as compared to constant stiffness design. In addition, optimal lay-ups for the maximum fundamental frequency of variable stiffness symmetrically and antisymmetrically laminated composite plates with different aspect ratios and various combinations of free, simply supported and clamped edge conditions are presented. These should prove a useful benchmark for optimal lay-ups of variable stiffness laminated composite plates.     

传递矩阵法分析复合材料层合板的传声损失

为了得到不同频率下正交各向异性复合材料层合板的传声损失,基于传递矩阵的方法,推导出层合板的传声损失计算公式。通过建立复合材料层合板的传声计算模型,研究了层合板铺设角度、板厚度和板密度等结构参数对层合板的传声损失影响。计算结果表明：复合材料的密度与传声损失之间没有明显的线性关系,而是随着频率的增加而上升;层合板的总厚度越大,传声损失也越大,而且各层之间厚度不同,也会引起传声损失的较大改变;层合板铺层角度越大,传声损失也越大。采用传递矩阵法能充分考虑复合材料层合板的铺设方式和铺层角度等因素的影响,利用层合板层间的速度和应力连续边界条件,准确的反应复合材料层合板隔声性能。     

The Artificial Bee Colony algorithm in layer optimization for the maximum fundamental frequency of symmetrical laminated composite plates

In this study the layer optimization was carried out for maximizing the lowest (first) fundamental frequency of symmetrical laminated composite plates subjected to any combination of the three classical boundary conditions, and the applicability of the Artificial Bee Colony (ABC) algorithm to the layer optimization was investigated. The finite element method was used for calculating the first natural frequencies of the laminated composite plates with various stacking sequences. The ABC algorithm maximizes the first natural frequency of the laminated composite plate defined as an objective function. The optimal stacking sequences were determined for two layer numbers, twenty boundary conditions and two plate length/width ratios. The outer layers of the composite plate had a stiffness increasing effect, and as the number of clamped plate edges was increased both he stiffness and natural frequency of the plate increased. The optimal stacking sequences were in good agreement with those determined by the Ritz-based layerwise optimization method (Narita 2003: J. Sound Vibration 263 (5), 1005–1016) as well as by the genetic algorithm method combined with the finite element method.     

A PROCEDURE TO SELECT THE BEST MATERIAL COMBINATIONS AND OPTIMALLY DESIGN HYBRID COMPOSITE PLATES FOR MINIMUM WEIGHT AND COST

The optimal layup with least weight or cost for a symmetrically laminated plate subject to a buckling load is determined using a hybrid composite construction. A hybrid construction provides further tailoring capabilities and can meet the weight, cost and strength constraints while a non-hybrid construction may fail to satisfy the design requirements. The objective of the optimization is to minimize either the weight or cost of the plate using the ply angles, layer thicknesses and material combinations as design variables. As the optimization problem contains a large number of continuous (ply angles and thicknesses) and discrete (material combinations) design variables, a -sequential solution procedure is devised in which the optimal variables are computed in different stages. The proposed design method is illustrated using graphite, kevlar and glass epoxy combinations and the efficiencies of the hybrid designs over the non-hybrid ones are computed.     

Structural optimization of rotating tapered laminated thick composite plates with ply drop-offs

In this study, structural optimization of rotating tapered thick laminated composite plates with ply drop-offs has been investigated numerically. The governing differential equations of motion of the tapered composite plate have been presented including the energy associated with the inertia force, coriolis force, displacement dependent centrifugal force and initial stress resultants due to steady state rotation. Four noded quadrilateral finite element has been formulated based on the first order shear deformation theory. Finite element analysis results are validated with experimental results for natural frequencies of the tapered plate with various configurations. Various cases of optimization problems are formulated with different objective functions in terms of maximization of natural frequencies and damping factors (individually and combined) and solved using genetic algorithm in order to obtain optimal ply sequence and ply orientation. It is shown that the optimization problem with maximization of fundamental modal damping factor without rotating condition yields the optimal layout as 90° for all the layers in the plate. It is also observed that maximization of the fundamental modal damping factor yields identical optimal orientation for uniform and all the configurations of a tapered composite plate.     

A new kind of energy transfer from high frequency mode to low frequency mode in a composite laminated plate

This paper brings to light a new type of nonlinear resonant motion in a fiber-reinforced composite laminated rectangular thin plate, which is not reported in other literature. The investigated system is a simply supported symmetric cross-ply composite laminated rectangular thin plate subjected to parametric excitation whose frequency is near to the first-order natural frequency of the plate. This new phenomenon demonstrates that the responses of a low-order frequency mode can be excited by those of a high-order frequency mode. The high-order frequency is the first-order natural frequency of the test plate, and the low-order frequency here is lower than the first-order nature frequency. Experimental research works on the nonlinear vibrations of the composite laminated rectangular thin plate have been carried out for the first time. It is found from the experimental results that the nonlinear dynamic responses consist of four modes, whose frequencies include a lower frequency than the first-order natural frequency, 1/3 sub-harmonic, 2/3 sub-harmonic and the first-order natural frequencies. In this case, the amplitude of the mode for lower frequency is larger than those of modes for the aforementioned frequencies. Moreover, the theoretical job goes to analyze this new phenomenon. An analytical mode is given to explain the interactions between the first-order mode and the lower-frequency mode observed in the experiment. Based on Reddy’s third-order shear deformation plate theory, the nonlinear governing equations of motion are formulated for the test plate under parametric excitation. Galerkin’s method is utilized to discretize the partial differential governing equations of motion for the composite laminated rectangular thin plate to a two-degree-of-freedom nonlinear system. The results of numerical simulations qualitatively agree very well with the experimental results. In addition, the multi-pulse chaotic motions are also found in numerical simulations.     

Dynamic characterization of the thickness-tapered laminated plant fiber-reinforced polymer composite plates

Evolution of the laminated woven natural fiber fabric-reinforced polymer composite structures makes a way to the development of the non-uniform laminated composite structures in order to achieve the stiffness variation throughout the structure. An attempt is made in this work to carry out the experimental and numerical investigations on the dynamic characteristics of the thickness-tapered laminated woven jute/epoxy and woven aloe/epoxy composite plates. The governing differential equations of motion for the thickness-tapered laminated composite plate are developed using the h-p version FEM based on higher order shear deformation theory. The validation of the present finite element formulation is carried out by comparing the natural frequencies obtained using the finite element formulation with those natural frequencies determined experimentally. The developed model is further validated with the available literature works on tapered composite plate to confirm the efficiency of h-p version FEM. This work also explores the study of the vibrational characteristics of composite plates under the influence of plant fiber’s transverse isotropic material characteristics and porosity associated with plant fiber composites through the elastic constants evaluated in the author’s previous work. Also the influences of aspect ratios, ply orientations, and taper angles under various end conditions on the natural frequencies of the woven jute/epoxy composite plate are studied using the present finite element formulation. The forced vibration response of the thickness-tapered laminated woven jute/epoxy composite plate under the harmonic force excitation is carried out considering CFCF and CFFF end conditions.     

Optimum stacking sequence design of laminated composite circular plates with curvilinear fibres by a layer-wise optimization method

The optimum stacking sequence design for the maximum fundamental frequency of symmetrically laminated composite circular plates with curvilinear fibres is investigated for the first time using a layer-wise optimization method. The design variables are two fibre orientation angles per layer. The fibre paths are constructed using the method of shifted paths. The first-order shear deformation plate theory and a curved square p-element are used to calculate the objective function. The blending function method is used to model accurately the geometry of the circular plate. The equations of motion are derived using Lagrange’s method. The numerical results are validated by means of a convergence test and comparison with published values for symmetrically laminated composite circular plates with rectilinear fibres. The material parameters, boundary conditions, number of layers and thickness are shown to influence the optimum solutions to different extents. The results should serve as a benchmark for optimum stacking sequences of symmetrically laminated composite circular plates with curvilinear fibres.