沿垂等温平板的自然对流问题的近似解析解

本文用加权残值得到了沿垂等温平板的自然对流问题的近似解析解。和已有准确解的比较表明，在平板表面附近，近似解有很好的精度，而且速度场的精度比温度场更好一些。文末还对配域法的准收敛问题作了说明。     

含初缺陷复合材料圆柱曲板的动力屈曲分析

基于修正的一阶剪切变形理论，利用Ｈａｍｉｌｔｏｎ原理导出包含横向剪切变形和转动惯量的复合材料长圆柱曲板的非线性动力方程，通过将位移和载荷展开为Ｆｏｕｒｉｅｒ级数，把非线性偏微分方程组转化为二阶常微分方程组，并可由四阶Ｒｕｎｇｅ－Ｋｕｔｔａ方法数值求解，通过算例，讨论了有关因素对迭层复合材料圆柱曲板动力屈曲的影响。     

叠层靶板弹击实验及弹道侵彻机理的数值模拟研究

为了提高军盔等防护装备的防弹性能,采用非线性动态显式有限元分析软件ANSYS/LS DYNA5.6.1模拟了几种复合材料防弹靶板的抗弹道侵彻过程,弹头采用标准1.1g模拟弹片。结合v50弹击实验分析了靶板在此类弹击下的破坏机理和吸能方式,对靶板的选材、铺层顺序、层数和制造工艺等提出合理化建议,主要是沿靶板厚向应采用非均匀的三段式结构和工艺。     

弱粘结的斜交铺设层合圆柱壳的柱形弯曲

导出了两端简文的具有弱粘结界面的任意斜交铺设层合圆柱壳柱形弯曲问题的一个精确弹性理论解。分析中采用线性弹簧模型来表征界面的弱粘结特性。引进新的物理量改写了基本方程,导出了对应的状态空间列式,并利用变量替换技术将该状态方程转换成常系数状态方程,从而方便求解。最后给出了数值算例,并讨论了弱界面的影响。     

Chaotic Analysis of Nonlinear Viscoelastic Panel Flutter in Supersonic Flow

In this paper chaotic behavior of nonlinear viscoelastic panels in asupersonic flow is investigated. The governing equations, based on vonKàarmàn's large deflection theory of isotropic flat plates, areconsidered with viscoelastic structural damping of Kelvin's modelincluded. Quasi-steady aerodynamic panel loadings are determined usingpiston theory. The effect of constant axial loading in the panel middlesurface and static pressure differential have also been included in thegoverning equation. The panel nonlinear partial differential equation istransformed into a set of nonlinear ordinary differential equationsthrough a Galerkin approach. The resulting system of equations is solvedthrough the fourth and fifth-order Runge–Kutta–Fehlberg (RKF-45)integration method. Static (divergence) and Hopf (flutter) bifurcationboundaries are presented for various levels of viscoelastic structuraldamping. Despite the deterministic nature of the system of equations,the dynamic panel response can become random-like. Chaotic analysis isperformed using several conventional criteria. Results are indicative ofthe important influence of structural damping on the domain of chaoticregion.     

Deteriorated Geometrical Stiffness for Higher Order Finite Elements with Application to Panel Flutter

Higher order elements were first design for linear problems where, in certain situations, they present advantages over the lower order elements. A method to efficiently extend their use to geometrical nonlinear problems as panel flutter and postbuckling behavior is presented. The chaotic and limit-cycle oscillations of an isotropic plate are obtained based on direct integration of the discretized equation of motion. The plate is modeled using the von Karman theory and the geometrical nonlinearities are separated in a nonlinear term of the first kind which manifests especially in the prebuckling and buckling regimes, and a nonlinear term of the second kind which is responsible for the postbuckling behavior. A fifth order, fully compatible element has been used to model thin plates while the inplane loads where introduced through a membrane element. The aerodynamics was modeled using the first order 'piston theory. The method introduces the concept of a deteriorated form of the second geometric matrix which is equivalent to neglecting higher order terms in the strain energy of the plate. This allows for a drastic reduction in the computational effort with no observable loss of accuracy. Well established results in the literature are used to validate the method.     

Two-dimensional thermoelastic analysis of a functionally graded cylindrical panel due to nonuniform heat supply

This paper is concerned with the theoretical treatment of the steady-state thermoelastic problem of a functionally graded cylindrical panel due to nonuniform heat supply in the circumferential direction. The thermal and thermoelastic constants of the cylindrical panel are expressed as power functions of the radial coordinate. We obtain the exact solution for the two-dimensional temperature change in a steady state, and thermal stresses of a simple supported cylindrical panel under the state of plane strain. Some numerical results are shown in figures and tables. Furthermore, the influence of the nonhomogeneity of the material, the radius ratio and the span angle upon the temperature change, displacements and stresses is investigated.     

超音速气流中受热壁板的稳定性分析

采用Galerkin方法建立二维壁板的非线性气动弹性运动方程，用一阶活塞理论模拟壁板 受到的气动力. 基于李雅普诺夫间接法分析了平壁板的稳定性，得到了壁板失稳的边界 曲线；采用牛顿迭代法分析了壁板的屈曲变形，进而分析了后屈曲状态下壁板的稳定性； 在时域中分析了后屈曲状态下壁板的颤振边界. 分析结果表明，为了保证计算精度， 在二维壁板的静态失稳及过屈曲变形分析中，至少要取二阶谐波模态；在平壁板的超音速颤 振(动态失稳)边界分析中至少应取四阶模态. 还对壁板的温升，壁板长厚比、壁板密 度和气流马赫数作了无量纲变参分析，研究了这些参数的变化对壁板稳定性的影响规律. 研 究中发现，当气流速压较低时壁板一般会稳定在低阶谐波模态的屈曲变形位置，但是如果系 统出现多个渐近稳定的不动点，即使作用在壁板上的气流速压很低，壁板也有可能在较低速 压下发生二次失稳型颤振.     

爆炸荷载作用下方形夹芯板动力学响应与优化设计数值分析

为研究方形蜂窝铝板在爆炸荷载作用下的动力学响应,基于LS-DYNA非线性有限元软件,建立了TNT炸药-前后面板-蜂窝夹芯-空气的三维有限元模型。采用ALE(任意的拉格朗日欧拉)多物质流固耦合算法分析了蜂窝铝板在冲击荷载作用下的变形机理、塑性变形、能量吸收以及结构的优化。数值模拟结果表明:随着面板厚度、核心高度的增加,蜂窝铝板在冲击荷载作用下的塑性变形明显减小,抵抗变形的能力增强;随着爆轰入射角度的增加,结构的破坏程度有所减小,入射角越大这种效果越发明显。对结构给定边长和受冲击面积以及面板厚度配合比、夹芯量纲为一的高度进行了局部的优化分析,为设计优质铝蜂窝板提供参考。