箱形复合材料层板结构的内噪声优化控制

基于结构声强法研究了箱形复合材料层板结构在动荷载作用下的结构噪声控制.将叠层顺序为[45°/-45°/45°/-45°]的碳纤维/环氧层合板与铝板分别组成的箱形结构的被动和主动噪声控制进行了比较.应用MSC/NASTRAN商业软件计算了箱形复合材料层板结构表面在动荷载作用下各单元的力和速度,再应用MATLAB自编程序计算得出箱形复合材料层板结构表面的结构声强.根据结构声强向量图和流线图,可得出安置阻尼器和施加主动控制力的可能的有效位置.再利用声场计算得到安置阻尼器和施加主动控制力的最优有效位置.基于结构声强的噪声控制法为实际车辆和航空机舱提供了一种简洁而直观的内噪声控制的参考方法.     

?????????????????????

探讨了载荷重构技术在智能化复合材料结构健康监测中的应用，着重针对一个自感 知复合材料层合板的载荷重构进行了研究. 首先，基于弹性波动理论和层合板理论，建立了 低速冲击载荷作用下正交铺层层合板的前向波动模型的状态空间表达式；通过构造误差指标 $J$, 应用优化求逆重构了载荷时程和载荷的作用点，并应用算例对以上方法进行了验证.     

压电复合材料梁和板的变形控制问题

由于具有良好的结构、力学性能,复合材料层合板在现代飞行器上大量应用;而压电复合材料,作为一种新兴的智能材料,由于其独特的力电耦合性能得到了人们更多的关注。本文研究含有压电片的复合材料梁和板在电场作用下的变形控制问题。基于经典的梁理论和层合板理论,分别研究了下列问题:(1)双压电片布置的悬臂梁的变形;(2)含有压电层的层合板变形控制问题;(3)含有一对压电片的层合板的变形控制问题。针对上述问题,分别给出了理论解和数值解,并进行了相关讨论分析。结果表明压电材料可对结构进行精确控制,因此本文的结果可对复合材料梁和板在电场作用下的变形控制问题提供工程参考。     

复合材料层合板的颤振特性及振动抑制研究

研究了超声速流中压电复合材料层合板的颤振特性及振动抑制方法。采用一阶活塞理论计算了超声速流场中的气动压力,基于经典层合板理论和Hamilton原理推导了压电复合材料层合板的动力学模型,设计了滑模观测器以减少观测溢出,通过Lyapunov方法证明观测器的稳定性,应用观测状态设计了LQR控制器,讨论了几何参数、铺设角度对压电复合材料层合板颤振特性的影响,利用SIMULINK仿真求解了层合板的脉冲响应,验证了控制器的有效性。结果表明,合理规划层合板的几何参数和铺设角度可提高系统颤振稳定性,滑模观测器能够较为准确地追踪原始系统且具有良好的鲁棒性,LQR控制可以在一定范围内消除层合板的颤振点,并且能够有效地控制压电复合材料层合板在颤振边界处的振动,Q矩阵越大,振动控制效果越好,压电层厚度越大,LQR控制效果越好。     

含椭圆孔非对称层合板的Green函数

运用作者建立的复合材料层合板问题的求解方法，得到了含椭圆孔和裂纹的无限大非对称层合板在广义集中载荷作用下的Ｇｒｅｅｎ函数．利用这些结果可研究含孔或裂纹的非对称层合板在集中载荷作用下的力学行为，还可结合边界元方法对复杂层合板结构建立有效的数值分析方法     

复合材料板的几何非线性行为综述

本文概述了利用分析方法了解弹性层合板静态大挠度,后屈曲和非线性动态响应方面的进展.在对称层合板情况下不存在弯曲-拉伸耦合.应用了正交异性板或各向异性板的经典非线性理论,还提供了有关这些板的参考文献.简要评述了许多类型边界条件下一般层合板的非线性剪切变形理论和一般解法.在本综述中讨论的使复合材料板几何非线性行为复杂化的一些影响因素是:横向剪应力和正应力,转动惯量和面内惯量,面内初始边界力,几何缺陷,切口,以及非经典边界条件.     

大开口复合材料层合板强度破坏研究

复合材料层合板的各向异性及非均质,使得复合材料层合板内部的破坏形式非常复杂.在复合材料结构的设计中,为满足制造及使用功能上的需求,在复合材料层合板承力结构件上不可避免地需要设计各种开口.然而,含大开口复合材料层合板的强度破坏问题变得更为复杂,使得现有的强度理论面临新的挑战.针对碳纤维增强复合材料大开口层合板受单向拉伸载荷作用下的强度破坏问题进行了数值分析和实验研究.首先,根据Hashin准则和刚度退化模型,对含不同圆形开口尺寸的[0]_(10)单向铺层、[0/90]_5和[±45]_5正交铺层的层合板,进行了单向拉伸载荷作用下渐进失效的数值模拟分析,获得了对应结构的极限载荷和破坏模式.在此基础上,采用数字图像相关方法,进行复合材料大开口层合板强度破坏的实验研究.研究结果表明,大开口复合材料层合板在单向拉伸加载下主要呈现脆性破坏形式,破坏起始位置处于应力集中区.此外,破坏强度和失效模式与复合材料铺层方式和开口尺寸大小密切相关.其中[±45]_5铺层的开口层合板承载能力最弱,分层破坏最严重.开口尺寸越大,结构的极限载荷值越低.同实验测试结果相比,数值模拟对复合材料层合板的损伤失效分析略显不足,往往很难全面分析复合材料层合板破坏失效过程中的各种因素的影响.     

复合材料板的几何非线性行为综述

本文概述了利用分析方法了解弹性层合板静态大挠度,后屈曲和非线性动态响应方面的进展.在对称层合板情况下不存在弯曲-拉伸耦合.应用了正交异性板或各向异性板的经典非线性理论,还提供了有关这些板的参考文献.简要评述了许多类型边界条件下一般层合板的非线性剪切变形理论和一般解法.在本综述中讨论的使复合材料板几何非线性行为复杂化的一些影响因素是:横向剪应力和正应力,转动惯量和面内惯量,面内初始边界力,几何缺陷,切口,以及非经典边界条件.     

六层非对称正交双稳态复合材料层合板的动态跳跃研究

本文研究了中心固支，四边自由的六层非对称正交双稳态复合材料层合板(0/0/0/90/90/90)的动态跳跃现象，并展示了双稳态复合材料层合板在动态跳跃前后和过程中的非线性振动。考虑冯卡门大变形，利用Reddy三阶剪切变形理论和哈密顿原理，建立了动力学与控制方程。利用动力学与控制方程，得到了李雅普诺夫指数图、庞加莱截面图和时间历程图，分析了双稳态复合材料层合板的周期振动、概周期振动、混沌振动和动态跳跃现象。     

复合材料层合板的二次屈曲和二次分枝点分析

为了研究复合材料层合板的二次分叉特性 ,利用能量变分原理和非线性几何方程建立了具有弹性约束的复合材料层合板在面内载荷作用下的非线性稳定性控制方程组。控制方程组用广义傅立叶级数法进行求解 ,并得到载荷 -挠度曲线。基于分叉理论中的 Lerray-Schaulder定理 ,采用小挠动法 ,直接导出了复合材料层合板的二次失稳方程。研究结果表明 ,非对称层板也可能存在分叉 ,弹性转动支持系数和铺层等因素对二次分叉有很重要的影响。随着弹性系数的增大 ,二次失稳载荷值与初次失稳载荷值之比下降     

Green’s functions for multi-phase isotropic laminated plates

This work develops a series of Green’s functions for multi-phase Kirchhoff isotropic laminated plates. First, we derive the Green’s functions for a composite laminated plate composed of two bonded dissimilar isotropic laminated semi-infinite plates. Second, the obtained results for bimaterials are judiciously applied to obtain the Green’s function solution for a circular elastic inclusion embedded in an infinite isotropic laminated plate. Third, Green’s functions for a composite space composed of an arbitrary number of wedges of different isotropic laminated plates are derived. Finally, we derive Green’s functions for a laminated plate with an elliptical and a parabolic boundary, respectively.     

用高阶位移模式分析复合材料层合板的自由振动

建立一种新的高阶位移模式：分层假设复合材料层合板的位移场，利用各层间应力及位移的连续性条件，导出了作为整体的层合板控制微分方程。最后，采用这一高阶剪切理论来分析复合材料矩形层合板的自由振动。数值计算采用有限差分法，并编制了计算程序，计算得出了六种不同边界条件、不同铺层、不同宽厚比工况下的矩形层合板的自振频率。同经典理论解进行比较，可以看出本文方法简便易行，且精度较高，可以在微机上实用。     

Delamination of laminated composite plates by p-convergent partial discrete-layer elements with VCCT

The simulation of the delamination process in laminated composite plates is quite complex and requires advanced finite element modeling techniques. Failure analysis tools must be able to predict initiation, size and propagation of delamination process. This paper presents the p-convergent partial discrete-layer elements with the virtual crack closure technique (VCCT) for the delamination analysis of laminated composite plates. The proposed element can be formulated by the suitable dimensional reduction from three-dimensional solid to two-dimensional plate. It is assumed that the piecewise linear variation of in-plane displacements and the constant value of out-of-plane displacements across the thickness. The higher-order approximation based on integrals of Legendre polynomials is used to define displacement fields. The three-dimensional VCCT is also slightly modified to incorporate with the proposed elements to estimate the energy release rate. The initiation of delamination occurs when the energy release rate for a displacement increment is same as the critical energy release rate corresponding to fracture toughness. The approach is to use a fracture mechanics criterion, but to avoid the complex moving mesh technique. At first, the validation and characteristic of the proposed elements are investigated on isotropic plates and orthotropic laminated plates, compared with referenced values. Then for fracture analysis, the efficiency of proposed approach is demonstrated with the help of additionally two problems such as the double-cantilever-beam test and the orthotropic laminated square plate with interior delamination.     

Buckling and postbuckling behavior of antisymmetrically angle-ply laminated composite plates

The buckling and postbuckling behaviors of perfect and imperfect antisymmetricallyangle-ply laminated composite plates under uniaxial compression have been studied byperturbation technique which takes deflection as its perturbation parameter.In this paper,the effects of in-plane boundary conditions,angles,total number oflayers and initial geometric imperfection on the postbuckling behavior of laminated plateshave been discussed.     

An exact analytical approach for in-plane and out-of-plane free vibration analysis of thick laminated transversely isotropic plates

In this article, the governing equations of motion of thick laminated transversely isotropic plates are derived based on Reddy’s third-order shear deformation theory. These equations are exactly converted to four uncoupled equations to study the in-plane and out-of-plane free vibrations of thick laminated plates without any usage of approximate methods. Based on the present analytical approach, exact Levy-type solutions are obtained for thick laminated transversely isotropic plates and, for some boundary conditions, the exact characteristic equations hitherto not reported in the literature are given. Also, the in-plane and out-of-plane deformed mode shapes are plotted for different boundary conditions. The present solutions can accurately predict both the in-plane and out-of-plane natural frequencies and mode shapes of thick laminated transversely isotropic plates.     

A dropped-weight apparatus for low-speed impact testing of composite structures

A dropped-weight test apparatus has been developed that can be used to perform low-speed impact tests on composite aircraft structures. This vertical drop-weight test apparatus is simple, compact, inexpensive and has precision impact and self-arresting design features similar to the more sophisticated, expensive test machines. The test apparatus has been used to perform low-speed impact response studies on laminated composite plates to understand the influence of impactor and target parameters on structural response and to develop a validated analysis method. Some of the experimental results generated by using this test apparatus for composite laminated plates are presented in the present paper and compared with the corresponding analytical results.     

Stability of parametric vibrations of hybrid composite plates

In this paper, the dynamic stability of laminated hybrid composite plates subjected to periodic uniaxial stress and bending stress is studied. The governing equations of motion of Mathieu-type are established by using the Galerkin method with reduced eigenfunctions transforms. Based on Bolotin's method the regions of dynamic instability of laminated hybrid composite plates are determined by solving the eigenvalue problems. The effects of layer thickness ratio, layer number, core material and load parameter on the dynamic instability of laminated hybrid composite plates are investigated and discussed.     

复合材料正交加筋板在横向载荷下挠度计算的半解析法

本文采用一种新的半解析法,即独特利用Heaviside函数建立与加筋板等效的变刚度模型来开展复合材料双向正交加筋板在横向载荷下的弯曲挠度分析．此模型可以准确地描述筋条在板面上的分布,以及由于筋条的存在而导致的板面刚度不均匀分布．使用Galerkin加权残值法求解该模型的控制方程,得到不同边界条件和载荷情况下的级数解．对于双向正交加筋板,将此半解析法的结果与传统均匀化方法和使用商业有限元软件ABAQUS建立的有限元模型所得到的弯曲挠度结果比较,验证了此方法的准确性和优越性．不同于传统均匀化方法,本双向正交加筋板的弯曲挠度半解析法可精确、有效地获取加筋间的局部弯曲挠度,可以促进复合材料结构的设计分析与优化的研究进展．     

Geometrically nonlinear isogeometric analysis of laminated composite plates based on higher-order shear deformation theory

In this paper, we present an effectively numerical approach based on isogeometric analysis (IGA) and higher-order shear deformation theory (HSDT) for geometrically nonlinear analysis of laminated composite plates. The HSDT allows us to approximate displacement field that ensures by itself the realistic shear strain energy part without shear correction factors (SCFs). IGA utilizing basis functions namely B-splines or non-uniform rational B-splines (NURBS) enables to satisfy easily the stringent continuity requirement of the HSDT model without any additional variables. The nonlinearity of the plates is formed in the total Lagrange approach based on the small strain assumptions. Numerous numerical validations for the isotropic, orthotropic, cross-ply and angle-ply laminated plates are provided to demonstrate the effectiveness of the proposed method.