复合材料层合浅拱的动态“跳跃”

本文考虑几何非线笥但不计横向剪切效应，给出了复合材料事浅拱的动力方程，并利用伽了辽金法求出了均布阶跃载荷作用下、两端铰支、对称铺层的层合浅的拱的动力响应是分析了动力稳定性。计算结果表明：不同的铺层顺序和结构几何参数对介载荷的影响很大。     

考虑初始几何缺陷时复合材料层合浅拱的动态“跳跃”

考虑几何非线性但不计横向剪切效应，给出了复合材料合浅拱的动力方程，利用伽辽金法求出了均布阶跃载荷作用下，两端铰支、正交铺层的对称层合浅拱在计及初始几何缺陷情况下的动力响应，并由Ｂ－Ｒ准则分析了动力稳定性计算结果表明：初始缺陷对于结构参数γ较大的拱的临界动力载荷有很大的影响。     

两端铰支层合浅拱的非线性‘跳跃''稳定性

利用叶开源和刘人怀提出的修正迭代法 ,导出了两端铰支、对称正交铺层的浅拱在均布载荷作用下的三次近似特征关系式 ,进而分析了结构几何参数、铺层数等对于‘跳跃失稳’临界载荷的影响 ,并通过与‘动力失稳’临界载荷的比较 ,讨论了两个‘失稳’概念的区别。     

面内阶跃载荷下矩形薄板的塑性动力屈曲

对于面内阶跃载荷作用下矩形薄板的塑性动力屈曲问题,将临界应力和屈曲惯性项指数参数作为双特征参数求解。由相邻平衡准则导出失稳控制方程,由动力屈曲发生瞬间的能量转换和守恒准则,导出波阵面上的屈曲变形补充约束条件。失稳控制方程、边界条件、塑性波阵面上的连续条件和补充约束条件构成了定量求解两个特征参数和动力屈曲模态的完备条件。研究了矩形薄板塑性动力屈曲过程中板的厚宽比、冲击载荷大小、屈曲模态和临界屈曲长度之间的关系。     

受轴向冲击有限长弹性直杆中应力波引起的分叉问题

研究了有限长理想直杆受阶跃载荷作用的弹性动力屈曲问题。将直杆的屈问题归结为由轴向应力波传播而导致的杆的分叉问题，并考虑了应力波反射的影响。给出了分叉发生的临界条件并对具体实例进行了计算。最后对阶跃载荷及脉冲载荷对杆的动力屈曲的影响进行了讨论。     

复合材料结构的动力屈曲研究进展

本文系统地回顾了复合材料结构的动力屈曲研究进展，对周期性动载荷和瞬态动载荷作用下，复合材料结构的动力屈曲作了阐述；讨论了耦合效应，横向剪切变形、初始几何缺陷以及铺层方式等因素对动力屈曲的影响；就复合材料结构动力屈曲研究的发展前景提出了一些有益的建议     

匀速轴向压力作用下两边简支直杆的动力屈曲

根据在不同的变形状态下匀速轴向受压的、两边简支的弹性直杆的动力屈曲控制方程,对直杆一阶、二阶形式的动力屈曲利用差分方法和有限元数值模拟方法进行计算和比较,并通过改变加载速度得到相应的数值解。计算结果表明:在保证精度的情况下,加载速度的增加使得两边简支直杆屈曲模态由一阶向二阶发生渐变;在屈曲刚发生阶段,屈曲载荷保持不变,之后屈曲载荷随着加载速度的增加而逐渐增大,且存在临界加载速度使屈曲载荷在该位置发生突变。     

径向余弦冲击的长圆柱壳弹性脉冲屈曲

根据已有的实验现象假定变形模态，采用Ｌａｇｒａｎｇｅ方法分析了单位长度薄圆环在余弦冲击载荷作用下的弹性脉冲动屈曲。导出了动力屈曲方程组，借助数值方法求解方程，并与已有的计算进行了比较，得出结论     

脱层梁屈曲的高阶剪切理论

脱层的存在将会大大降低层合结构的屈曲载荷。该文将含任意位置脱层的两端固支梁分成多段子层,用厚度的三次多项式模拟脱层梁屈曲时子层的轴向位移,利用变分原理和欧拉方程导出了脱层梁的屈曲方程和定解条件,并用状态空间方法进行求解。通过与一阶剪切理论和经典理论的比较,指出了它们各自的适用范围;考虑了脱层梁三种不同的屈曲模态。分析了脱层长度、深度、位置和材料的铺层方向对脱层梁屈曲载荷的影响;最后给出了多处简单脱层的屈曲分析。     

弹性圆柱壳冲击扭转屈曲的突变模型

本文将突变理论用于处理冲击载荷下弹性结构的屈曲问题,文中建立了结构冲击屈曲的突变准则,认为临界阶跃载荷位于所提出突变系统的分叉集之中,并由此对两端固支的弹性圆柱壳扭转屈曲进行了分析,给出了不同初缺陷时的临界阶跃扭矩计算公式,通过对临界静态扭矩的计算,表明临界阶跃扭矩小于临界静态扭矩.     

A nondestructive dynamic method for the determination of the critical load of elastic columns

A dynamic method for predicting the buckling load of an elastic column is formulated. The method is based on the integral-equation representation of a column with varying cross section and elastic springs at the boundaries. The experimental inputs are the dynamic properties of the unloaded column (trequencies, mode shapes and masses). The buckling loads predicted for three tested configurations agreed well with loads defined by other static and dynamic methods.     

非均匀径向冲击下圆柱壳塑性动屈曲

本文采用王仁等提出的塑性动力屈曲的能量准则讨论了圆柱壳在不均匀的外部径向冲击下的塑性动屈曲问题，获得了屈曲的占优波数公式及临界冲击速度公式，初步的实验证明本文的结论是合理的。同时进一步证明该能量准则的有效性。     

柱壳在轴向冲击载荷作用下动态塑性屈曲的实验研究

圆柱壳的动态塑性屈曲问题的研究主要是集中在屈曲模态方面，至于屈曲的临介载荷与临介时时间则研究的较少，ＳＨＰＢ用于研究材料在高应变率下动态力学性能已为大家所熟悉，但用于研究结构的动态屈曲则未见报道，本文利用一装置对柱壳的动态塑性屈曲进行了实验研究，测出了壳体屈曲过程的载荷，轴向缩短量与时间的关系曲线，得到屈曲时的临介载荷与临介时间，同时发现壳体屈曲变形的一些规律并与静态实验的结果进行了比较，为理论分     

弹性圆柱壳在轴向应力波传播过程中的非对称屈曲

讨论弹性圆柱壳端部受冲击载荷作用，在应力波传播过程中的非对称屈曲问题。通过求解扰动方程得到了动态屈曲的分叉条件、临界载荷和屈曲模态。数值结果表明，当壳壁厚不很薄时，轴对称屈曲临界载荷比非对称临界载荷高；反之，轴对称临界载荷会比非对称临界载荷低。不同的冲击载荷，屈曲模态也将不同。     

在轴向应力波传播和反射过程中弹性有限长圆柱壳非对称动态屈曲

本文讨论弹性有限长圆柱壳端部受冲击载荷作用，在轴向应力波传播和反射过程中的非对称动态屈曲问题。通过建立和求解扰动方程得到了动态屈曲的分叉条件，临界载荷和屈曲模态。数值结果表明：当壳壁厚不很薄时，轴对称屈曲临界载荷比非轴对称临界载荷高；反之，轴对称临界载荷会比非对称临界载荷低；由于应力波的反射，临界载荷降低，因而更容易发生屈曲，屈曲模态也有其不同特点。     

弹塑性梁在轴向应力波下的动态屈曲

本文考虑轴向应力波效应，利用分叉理论研究各种支承半无限长弹塑性梁的动态屈曲问题。在轴向阶梯载荷和脉冲载荷冲击下得到了梁的临界屈曲载荷及初始屈曲模态。其结果与实验现象相一致。同时也为研究结构动态屈曲问题提供了有效途径。     

投影云纹法在研究加劲板后屈曲平衡路径及后屈曲模态转化过程的应用

本文应用投影云纹法研究受压加劲板的大挠度非线性问题。用投影云纹法测量加劲板后屈曲平衡路径,记录了随着载荷的增加,加劲板后屈曲模态变化的全过程。将云纹图输入微型计算机处理,获得了加劲板的全场位移和全场应力的分布情况。用投影云纹法所测得的结果同理论计算值基本吻合。     

Exact solution and stability of postbuckling configurations of beams

We present an exact solution for the postbuckling configurations of beams with fixed–fixed, fixed–hinged, and hinged–hinged boundary conditions. We take into account the geometric nonlinearity arising from midplane stretching, and as a result, the governing equation exhibits a cubic nonlinearity. We solve the nonlinear buckling problem and obtain a closed-form solution for the postbuckling configurations in terms of the applied axial load. The critical buckling loads and their associated mode shapes, which are the only outcome of solving the linear buckling problem, are obtained as a byproduct. We investigate the dynamic stability of the obtained postbuckling configurations and find out that the first buckled shape is a stable equilibrium position for all boundary conditions. However, we find out that buckled configurations beyond the first buckling mode are unstable equilibrium positions. We present the natural frequencies of the lowest vibration modes around each of the first three buckled configurations. The results show that many internal resonances might be activated among the vibration modes around the same as well as different buckled configurations. We present preliminary results of the dynamic response of a fixed–fixed beam in the case of a one-to-one internal resonance between the first vibration mode around the first buckled configuration and the first vibration mode around the second buckled configuration.     

Free vibration analyses of axially loaded laminated composite beams based on higher-order shear deformation theory

The dynamic stiffness matrix method is introduced to solve exactly the free vibration and buckling problems of axially loaded laminated composite beams with arbitrary lay-ups. The Poisson effect, axial force, extensional deformation, shear deformation and rotary inertia are included in the mathematical formulation. The exact dynamic stiffness matrix is derived from the analytical solutions of the governing differential equations of the composite beams based on third-order shear deformation beam theory. The application of the present method is illustrated by two numerical examples, in which the effects of axial force and boundary condition on the natural frequencies, mode shapes and buckling loads are examined. Comparison of the current results to the existing solutions in the literature demonstrates the accuracy and effectiveness of the present method.     

A dynamic method for measuring the critical loads of elastic flat plates

A dynamic method is described for determining the linear buckling loads of elastic, perfectly flat, rectangular plates. The proposed method does not require the application of in-plane loads; it requires only vibrational excitation of the plate. The buckling load is determined from the measured normal modes of vibration. The method is applicable to isotropic as well as anisotropic plates with any type of edge support. The accuracy of the dynamic method was evaluated by tests in which buckling loads of aluminum and graphite fiber-reinforced-epoxy composite plates were determined both by the dynamic method and by imposing static in-plane loads on the plates. The results of the dynamic and static tests agree closely. A. Segall (on leave from RAFAEL, Israel)