弹性介质中受轴向冲击载荷作用的圆柱壳的屈曲临界载荷计算分析

建立并求解了弹性介质中圆柱壳的径向位移控制方程,考虑边界条件及相容条件,得到了应力波传播及反射过程中圆柱壳的动力屈曲分叉条件.通过计算得到了不同时间段屈曲临界载荷与应力波波阵面到达圆柱壳的位置、弹性介质的刚度、壳体未嵌入弹性介质部分的长度与总长之比的关系.数值计算结果表明,弹性介质中的圆柱壳发生轴对称屈曲和非轴对称屈曲趋势一致;嵌入弹性介质部分越深、弹性介质刚度越大圆柱壳越难屈曲;屈曲临界载荷随着弹性介质刚度的增大经历了增长缓慢、增长迅速以及增长较慢3个阶段;应力波反射前波阵面通过分界面后,屈曲仅发生在应力波传播区域,反射波波阵面通过分界面前,临界载荷较小时屈曲先发生在反射端部,随着轴向阶数增大,屈曲覆盖整个圆柱壳区域,反射波波阵面通过分界面后,壳体发生的屈曲始终覆盖整个圆柱壳区域.     

弹性介质中正交各向异性微管的屈曲分析

已有实验表明,处于细胞质中的微管可以比自由微管承受更大的压力而不发生屈曲．基于嵌入式碳纳米管屈曲的Winkler模型,利用正交各向异性情形的Winkler模型研究了细胞质中充当细胞骨架的微管的屈曲行为．计算表明,本模型可以较好地预测嵌入弹性介质中的微管较自由微管承受更大屈曲压力这一现象,而且所得到的临界屈曲压力与微管受压屈曲的实验值吻合\．同时,所得的结果也表明周围介质与微管的相互作用可以极大地提高微管抵抗屈曲的能力,该结果很好地阐释了介质与微管相互作用从而提高微管抗屈曲压力的相互作用机制\．模拟结果表明,所给出的模型可以对嵌入弹性介质中的微管的屈曲行为进行很好地模拟．     

受沿任意方向单向拉伸的织物的屈曲分析

对编织物受沿与其经线方向成任意角度θ(0<θ<90°)的单向拉伸时的屈曲进行了分析,得到了确定其屈曲方向角β的方程,给出了当θ=45°和θ=30°时确定屈曲方向角β的方程的解曲线.证明了当编织物受到沿非经向/非纬向的单向拉伸时,屈曲是可能的,得到了两种可能的屈曲模态(弯曲模态和拉伸模态)以及相应的屈曲条件.Zhang和Fu(2001)的结果为其结论的特例.     

加肋圆柱壳在轴压作用下的屈曲和后屈曲

本文讨论完善和非完善的,纵向加肋和正交加肋圆柱壳在轴压作用下的屈曲和后屈曲性态.依据文[1]提供的圆柱薄壳屈曲的边界层理论及其分析方法,给出了加肋圆柱壳在轴压作用下的屈曲和后屈曲理论分析.本文同时讨论肋骨与壳板材料不同时对加肋圆柱壳屈曲和后屈曲性态的影响.     

薄球壳在均布外压与温度耦合作用下的热屈曲研究

从张量方法推导出的轴对称薄球壳屈曲方程出发,推导出在均布外压与温度耦合作用下用位移表示的薄球壳热屈曲方程;应用虚功原理建立薄球壳屈曲最小势能泛函;进一步用Ritz(里兹)法分析了周边简支的半球壳的3种热屈曲问题.得到了: 1) 温度不超过屈曲临界温度值时,均布外压的临界载荷;2) 均布外压载荷为0时,屈曲临界温度值;3) 均布外压载荷不超过临界载荷时,屈曲临界温度值.     

Synchronous/Asynchronous Buckling of Double-Layered Microplate Systems北大核心CSCD

采用修正的偶应力理论和双变量高阶剪切变形理论,发展了层间填充弹性介质的双层微板系统在面内压缩荷载作用下的屈曲模型.基于Euler-Lagrange方程推导了系统屈曲的控制微分方程,运用Navier法获得了上下层均为四边简支时系统同步/异步屈曲的解析解.通过数值算例讨论了系统各参数对其屈曲特性的影响.结果表明：系统的异步屈曲特性依赖于材料尺度参数、长宽比和弹性介质模量,而同步屈曲特性仅依赖于前两项,并且异步屈曲荷载高于同步屈曲荷载;弹性介质的Pasternak模量较之于Winkler模量对系统的屈曲特性影响更显著.     

轴向冲击下理想塑性直杆动态屈曲的过应力简化分析模型*

本文在理想塑性直杆的动态屈曲分析中引入应变率效应,得到相应的动力学微分方程,求出了屈曲半波长,临界载荷和屈曲时间的表达式.讨论了应变率效应对杆的塑性动态屈曲的影响.并与文[4]的理论和试验结果作了比较.     

弹性杆的动态屈曲模态

本文提出了屈曲相关初缺陷的概念,采用最优模态分析方法,由Bernolli-Euler梁方程出发给出了弹性杆在齐次边条件下的动态屈曲模态、由此对两端固支弹性杆的动态屈曲模态进行了讨论.     

球壳的环向剪切屈曲

通过球壳微元初始屈曲的微分几何分析,推导出一组新的精确的屈曲分支方程,并且应用Galerkin变分法研究铰支球壳承受环向剪切力时的整体稳定性,构造了接近分支点变形状态的屈曲模式,首次求得了从扁球壳到半球壳大范围内的扭转屈曲临界特征值,临界荷载强度和临界应力.     

非轴对称面内边界力作用下环形板的屈曲和过屈曲

本文基于[1,2]中提出的开孔薄板大挠度的一般理论和[4]中建立的分析开孔薄板屈曲和过屈曲性态的有限单元法,讨论了在边界上受面内非轴对称法向压力作用下环形板的屈曲和过屈曲.     

The effects of various parameters on an aeroelastic optimization problem

The optimal design of a panel flutter problem is investigated in this paper. A semi-infinite flat panel with either a homogeneous or sandwich cross section is considered. The thickness distribution of the panel is allowed to vary while the total weight is held fixed, and the distribution which maximizes the critical flutter parameter for stability is chosen as the optimal design. This design is calculated here by means of a generalized Ritz procedure, with the panel thickness assumed to have a certain form. Variations in the following parameters are then considered: a minimum allowable thickness, aerodynamic damping, in-plane loading, and nonstructural stiffness and mass for the case of a sandwich panel. It is shown that the optimal design may be significantly affected by changes in these parameters.     

基于动态因子结构的贝叶斯分位面板协整研究

针对传统面板协整检验在建模过程中易受异常值影响以及其原假设设置的主观选择问题,本文利用动态公共因子刻画面板数据潜在的截面相关结构,提出基于动态因子的截面相关结构的贝叶斯分位面板协整检验,结合各个主要分位数水平下参数的条件后验分布,设计结合卡尔曼滤波的Gibbs抽样算法,进行贝叶斯分位面板协整检验;并进行Monte Carlo仿真实验验证贝叶斯分位面板协整检验的可行性与有效性。同时,采用中国各省金融发展和经济增长的面板数据进行实证研究,结果发现在各主要分位数水平下中国金融发展和经济增长之间具有协整关系。研究结果表明:贝叶斯分位面板协整检验方法避免了传统面板数据协整方法由于原假设设置不同而发生误判的问题,克服了异常值的影响,能够提供全面准确的模型参数估计和协整检验结果。     

Free edge stress prediction in thick laminated cylindrical shell panel subjected to bending moment

A thick composite cylindrical shell panel with general layer stacking is studied to investigate the free edge and 3D stresses in the panel which is subjected to pure bending moment. To this aim, a Galerkin based layerwise formulation is presented to discretize the governing equation of the panel to ordinary differential equations. Employing a reduced displacement field for the cylindrical panel, the governing equations for thick panel are developed in terms of displacements and a set of coupled ordinary differential equations is obtained. The governing equations are solved analytically for free edge boundary conditions and applied pure bending moment. The accuracy of numerical results is examined and the distribution of interlaminar and in-plane stresses is studied. The free edge stresses are studied and the effect of radius to thickness ratio, width to thickness ratio and layer stacking on the distribution of stresses is investigated. The focus of numerical results is on the prediction of boundary layer and free edge stress distribution.     

Nonstationary transversal vibrations of thermoelastic web with a constant velocity motion

We consider axial movements of elastic web performing small transversal vibrations. We take into account thermal loadings on the moving web (panel) and determine the critical temperature providing the divergence (instability) of thermoelastic panel. We perform an analysis of non-stationary vibrations of the panel. Solving dynamical problem is based on application of Galerkin’s method. As an example, we present the analytical solution to the problem of nonstationary thermoelastic panel vibrations for the case of two shape functions.     

Nonlinear buckling and postbuckling of a shear-deformable anisotropic laminated cylindrical panel under axial compression

The nonlinear buckling and postbuckling of a shear-deformable anisotropic laminated cylindrical panel of finite length is investigated based on a boundary-layer theory for buckling. The layers of the panel are assumed to be linearly elastic. The governing equations are based on Reddy’s higher-order shear deformation theory of shells and include the von Karman-type kinematic nonlinearity and extension/twist, extension/flexure, and flexure/twist couplings. The nonlinear prebuckling deformations and the initial geometric imperfections of the panel are both taken into account. The postbuckling behavior of the panel under axial compression is analyzed. A singular perturbation technique is employed to determine its buckling loads and postbuckling equilibrium paths. The numerical illustrations concern the postbuckling behavior of perfect and imperfect moderately thick anisotropic laminated cylindrical panels with different geometric parameters and stacking sequences. The new finding reveals that there arises a compressive stress along with an associate shear stress and twisting when a moderately thick anisotropic laminated cylindrical panel is subjected to axial compression.     

面板数据的单位根检验和协整检验——实证分析西部省市固定投资与工业增加值之间的关系

本文介绍了面板数据的单位根检验和协整检验,实证分析西部九省市固定投资和工业增加值的关系,Engle-G ranger检验拒绝部分省市具有均衡增长关系,面板协整检验接受西部地区具有均衡增长关系。     

The dynamic analysis of the functionally graded piezoelectric (FGP) shell panel based on three-dimensional elasticity theory

In this paper, three-dimensional elasticity solution is extended to investigate a FGPM finite length, simply supported shell panel under dynamic pressure excitation. The host panel is assumed to be of some functionally graded piezoelectric material (FGPM). The ordinary differential equations (o.d.e.) are derived from the highly coupled partial differential equations (p.d.e.) using series expansions of mechanical and electrical displacements. The resulting system of ordinary differential equations is solved by means of Galerkin finite element method. At last, numerical examples are presented for a FGPM shell panel. To verify the validity of code and formulation, the results of a FGM panel and a FGM plate are compared with the published results.     

Influence of the temperature of dissipative heating on the damping of forced resonance vibrations of a simply supported viscoelastic cylindrical panel with the help of piezoelectric actuators

We consider the problem of active damping of the forced resonance vibrations of a viscoelastic cylindrical panel with the help of piezoelectric actuators. The end faces of the panel are assumed to be simply supported and heat-insulated. An analytical solution of the problem of electromechanics is obtained. On this basis, the dissipative function is calculated, and the energy equation is solved. We also analyze the influence of the temperature of dissipative heating on the efficiency of active damping of the forced vibrations of a cylindrical panel.     

Is reliability a new science? A paper from the panel session held at the 10th International Conference on Mathematical Methods in Reliability

The 10th International Conference on Mathematical Methods in Reliability, MMR 2017, held in Grenoble, France during July 3‐7, entailed a panel discussion entitled “Is reliability a new science?” with Mark Brown, Regina Liu, William Meeker, Sheldon Ross, and Nozer Singpurwalla as panelists. Bill Meeker also doubled as a chair and as a moderator of the panel. The panel discussion was spawned by the recent appearance of a book by Professor Paolo Rocchi, Docent Emeritus of IBM, titled “Reliability is a new science: Gnedenko was right” published by Springer in 2017. The panel discussion was well attended and enthusiastically received and could serve as a forerunner to other such panel discussions at future MMR conferences. This paper presents some elements from the lively debate generated by this discussion.     

Exact Controllability and Boundary Stabilization of Torsional Vibrations of an Internally Damped Flexible Space Structure

In this paper, we study the exact controllability and boundary stabilization of the torsional vibrations of a flexible space structure (such as a solar cell array) modeled by a rectangular panel, incorporating the material damping of the structure. The panel is hoisted at one end by a rigid hub and the other end is totally free. For the attachment of this hub on one side of the panel, the hub dynamics leads to a nonstandard boundary condition. To incorporate internal damping of the material, we assume Voigt-type viscoelasticity of the structure. Exact controllability theory is established using the Hilbert uniqueness method by means of a control torque applied only on the rigid hub of the panel. At the same time, uniform exponential energy decay rate is obtained directly for the solution of this problem.