复合材料圆锥壳体的外压稳定性*

本文采用Donnell型扁壳理论,在文献[1]的基础上,应用能量变分法分析了在均布外压作用下复合材料叠层圆锥壳体的稳定性问题,得到了临界载荷的近似表达式.数值结果表明,临界载荷的理论预示值与实验结果非常吻合.最后,讨论了材料弹性常数、铺层参数等因素对临界载荷的影响.本文所得结果对航空航天结构设计具有重要参考价值.     

双层网格开顶扁球壳的非线性稳定性分析

根据基于等效夹层壳思想的双层网格圆底扁球壳在极坐标下的平衡方程、相容方程,采用修正迭代法,对外边缘滑动固定、内边缘悬空和外边缘夹紧固定、内边缘悬空两种边界条件下,双层网格开顶圆底扁球壳的非线性稳定性进行了分析,得出了非线性载荷 位移关系及临界荷载的解析表达式,并讨论和分析了网壳几何参数对临界屈曲载荷的影响.     

复合材料加筋薄壁圆锥壳体有限变形的混合型理论

本文利用变分原理和平均筋条刚度法,建立了在任意载荷作用下纵向和环向密加筋复合材料圆锥壳体有限变形的Donnell型理论.考虑了面板最一般的弯曲拉伸耦合关系和加筋筋条的偏心效应的影响.导出了平衡条件、边界条件和变形协调方程.给出了以应力函数和挠度函数表示的耦合形式的非性性变系数偏微分方程组.对于一些特殊情况,给出了相应的简化方程.     

双层网格圆底扁球壳的非线性稳定问题

从基于等效夹层壳思想的双层网格扁壳,非线性弯曲理论的变分方程出发,利用坐标变换方法和驻值余能原理,导出双层网格圆底扁球壳,在均布压力作用下的轴对称大挠度方程和边界条件．采用修正迭代法,求得了两类边界条件下双层网格圆底扁球壳的非线性载荷-位移关系式和临界屈曲载荷的解析表达式,并讨论了几何参数对临界屈曲载荷的影响．     

复合材料旋转壳非线性稳定性分析计算

利用前屈曲一致理论和能量变分法分析计算了复合材料旋转壳非线性稳定性.前屈曲应变-位移关系采用非线性的卡门方程,能量积分采用数值积分,用势能最小原理求解前屈曲位移和内力,提出了求解临界载荷的实用计算方法,用FORTRAN语言编制了相应的计算机程序,并给出了算例.     

复合材料叠层圆柱壳的非线性动力稳定性理论

用Hamilton原理建立了复合材料叠层圆柱壳非线性动力稳定性理论的一般性基本方程,其中包含了非线性大挠度,横向剪切,纵向惯性力等因素。用变分法获得基本方程的解。分析表明:叠层圆柱壳在动载荷下会发生参数共振而进入动力不稳定区域而导致动力失稳。计算了几种典型复合材料圆柱壳:即T300/5208石墨环氧,E-玻璃环氧和ARALL圆柱壳。结果表明:这些因素对于各种复合材料圆柱壳的动力稳定性具有程度不同的重要影响,所以研究叠层圆柱壳动力稳定性时,考虑这些因素是重要的。     

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.     

扁球壳在热-机械荷载作用下的稳定性分析

基于扁壳几何非线性理论,应用虚功原理和变分法推导了均匀变温场中圆底扁薄球壳在均布外侧压力作用下的位移型几何非线性控制方程.考虑周边不可移简支边界条件,运用打靶法计算获得了不同几何参数的扁球壳轴对称弯曲变形的数值结果.定义了壳体临界几何参数.考察了壳体几何参数对平衡路径和临界荷载的影响.当壳体几何参数大于壳体临界几何参数时,上临界荷载随几何参数的增加单调增加,下临界荷载在很小范围内随几何参数的增加而增加,之后随几何参数的增加而减小.给定几何参数时,考察了不同均匀温度变化对壳体临界几何参数、临界荷载和平衡构型的影响.均匀升温使上临界荷载显著增加,使下临界荷载和临界几何参数显著减小.     

变厚度夹层截顶扁锥壳的非线性稳定性分析

对具有变厚度夹层截顶扁锥壳的非线性稳定问题进行了研究。利用变分原理导出表层为等厚度而夹心为变厚度的夹层截顶扁锥壳的非线性稳定问题的控制方程和边界条件,采用修正迭代法求得了具有双曲型变厚度夹层截顶扁锥壳的非线性稳定性问题的解析解,得到了内边缘与一刚性中心固结而外边缘为可移夹紧固支的变厚度夹层截顶扁锥壳临界屈曲载荷的解析表达式,讨论了几何参数和物理参数对壳体屈曲行为的影响。     

指数型体积分数功能梯度材料的薄壁圆柱壳振动

研究了指数型体积分数对功能梯度薄圆柱壳振动频率的影响.壳体厚度方向上的材料特性呈指数律变化.由Love薄壳理论,得到应变-位移及曲率-位移关系表达式.利用Rayleigh-Ritz方法,导出壳体的固有频率方程.假定轴向形态关系是典型的梁函数.壳体的固有频率取决于组合材料的体积分数.所得结果与已有文献的结果进行对比分析,说明本方法是正确的.     

The vibration and stability of non-homogeneous orthotropic conical shells with clamped edges subjected to uniform external pressures

In this paper an analytical procedure is given to study the free vibration and stability characteristics of homogeneous and non-homogeneous orthotropic truncated and complete conical shells with clamped edges under uniform external pressures. The non-homogeneous orthotropic material properties of conical shells vary continuously in the thickness direction. The governing equations according to the Donnell’s theory are solved by Galerkin’s method and critical hydrostatic and lateral pressures and fundamental natural frequencies have been found analytically. The appropriate formulas for homogeneous orthotropic and isotropic conical shells and for cylindrical shells made of homogeneous and non-homogeneous, orthotropic and isotropic materials are found as a special case. Several examples are presented to show the accuracy and efficiency of the formulation. The closed-form solutions are verified by accurate different solutions. Finally, the influences of the non-homogeneity, orthotropy and the variations of conical shells characteristics on the critical lateral and hydrostatic pressures and natural frequencies are investigated, when Young’s moduli and density vary together and separately. The results obtained for homogeneous cases are compared with their counterparts in the literature.     

Stability of Conical Shells of Metal Composites Beyond the Elastic Limit

The equations for integral instantaneous characteristics of composite materials consisting of elastoplastic fibers and matrix are derived based on the known hypotheses of uniform strain or stress fields. The constitutive relations for a layered shell are obtained. The numerical algorithm elaborated is used to solve the stability problem for conical boron-aluminum shells under external pressure and axial compression. It is shown that the shells of medium thickness lose their stability under loads whose magnitude depends on the plasticity of the binder. The plasticity has a decisive influence on the choice of the optimum directions of reinforcement. If the parameters of a shell are such that the buckling occurs beyond the elastic limit, the shell must be reinforced in the direction of precritical stresses. However, this is possible only upon separate action of loads.     

Stability of Composite Cylindrical Shells with Noncoincident Directions of Layer Reinforcement and Coordinate Lines

The stability problem is solved for cylindrical shells made of a laminated composite whose directions of layer reinforcement are not aligned with coordinate axes of the shell midsurface. Each layer of the composite is modeled by an anisotropic material with one plane of symmetry. The resolving functions of the mixed variant of shell theory are approximated by trigonometric series satisfying boundary conditions. The stability of the shells under axial compression, external pressure, and torsion is investigated. A comparison with calculation data obtained within the framework of an orthotropic body model is carried out. It is shown that this model leads to considerably erroneous critical loads for some structures of the composites. __________ Translated from Mekhanika Kompozitnykh Materialov, Vol. 41, No. 5, pp. 651–662, September–October, 2005.     

Stability of unfigured and stiffened shells made of fibrous composites

Conclusions Within the known generalizations of the theory of thin shells, formulas were obtained for calculating critical loads of unfigured and stiffened cylindrical shells made of fibrous composite materials under an external pressure and axial compression, taking into account not only the longitudinal (compressive) and flexural rigidity, but also the torsional and shear rigidities. From an analysis of the testing results of unfigured shells made of fiber-glass material, the divergence between the calculated and experimental data has been estimated by introducing into the formulas correction functions 0.181 In + 1.32 and a coefficient 0.697. The values of the safety factor were determined, which with a given reliability guarantee the selection of the geometrical parameters of the shells, amounting to (for a 0.95 reliability) 1.244 and 1.45.Paper presented at the Fourth All-Union Conference on the Mechanics of Polymer and Composite Materials (Riga, October, 1980).Translated from Mekhanika Kompozitnykh Materialov, No. 4, pp. 640–646, July–August, 1980.     

Postbuckling characteristics of angle-ply laminated truncated circular conical shells

The postbuckling characteristics of the angle-ply laminated composite conical shells subjected to the torsion, the external pressure, the axial compression, and the thermal loading considering uniform temperature change are studied using the semi-analytical finite element approach. The finite element formulation is based on the first-order shear deformation theory and the field consistency principle. The variations in the stiffness coefficients along the meridional direction due to the changes in the ply-angle and the ply-thickness of the filament wound conical shells are incorporated in the finite element formulation. The nonlinear governing equations are solved using the Newton–Raphson iteration procedure coupled with the displacement control method to trace the prebuckling followed by the postbuckling equilibrium path. The presence of asymmetric perturbation in the form of a small magnitude load spatially proportional to the linear buckling mode shape is considered to initiate the bifurcation of the shell deformation. The influence of semi-cone angle, ply-angle and number of circumferential waves on the prebuckling/postbuckling response of the anti-symmetric angle-ply laminated circular conical shells is investigated.     

Stability and free vibration analyses of double-bonded micro composite sandwich cylindrical shells conveying fluid flow

In this study, based on Reddy cylindrical double-shell theory, the free vibration and stability analyses of double-bonded micro composite sandwich cylindrical shells reinforced by carbon nanotubes conveying fluid flow under magneto-thermo-mechanical loadings using modified couple stress theory are investigated. It is assumed that the cylindrical shells with foam core rested in an orthotropic elastic medium and the face sheets are made of composites with temperature-dependent material properties. Also, the Lorentz functions are applied to simulation of magnetic field in the thickness direction of each face sheets. Then, the governing equations of motions are obtained using Hamilton's principle. Moreover, the generalized differential quadrature method is used to discretize the equations of motions and solve them. There are a good agreement between the obtained results from this method and the previous studies. Numerical results are presented to predict the effects of size-dependent length scale parameter, third order shear deformation theory, magnetic intensity, length-to-radius and thickness ratios, Knudsen number, orthotropic foundation, temperature changes and carbon nanotubes volume fraction on the natural frequencies and critical flow velocity of cylindrical shells. Also, it is demonstrated that the magnetic intensity, temperature changes and carbon nanotubes volume fraction have important effects on the behavior of micro composite sandwich cylindrical shells. So that, increasing the magnetic intensity, volume fraction and Winkler spring constant lead to increase the dimensionless natural frequency and stability of micro shells, while this parameter reduce by increasing the temperature changes. It is noted that sandwich structures conveying fluid flow are used as sensors and actuators in smart devices and aerospace industries. Moreover, carotid arteries play an important role to high blood rate control that they have a similar structure with flow conveying cylindrical shells. In fact, the present study can be provided a valuable background for more research and further experimental investigation.     

Formulation and evaluation of a finite element model for the linear analysis of stiffened composite cylindrical panels

A finite element model for linear static and free vibration analysis of composite cylindrical panels with composite stiffeners is presented. The proposed model is based on a cylindrical shell finite element, which uses a first-roder shear deformation theory. The stiffeners are curved beam elements based on Timoshenko and Saint-Venant assumptions for bending and torsion respectively. The two elements are developed in a cylindrical coordinate system and their stiffness matrices result from a hybrid-mixed formulation where the element assumed stress field is such that exact equilibrium equations are satisfied. The elements are free of membrane and shear locking with correct satisfaction of rigid body motions. Several examples dealing with stiffened isotropic and laminated plates and shells with eccentric as well as concentric stiffeners are analyzed showing the validity of the models.