复合材料圆柱壳轴压屈曲性能分析

对完整复合材料圆柱壳轴向压缩性能进行了试验研究,得到了圆柱壳结构的破坏载荷和各测量点的载荷-应变曲线,通过分析得出结构的破坏形式为屈曲破坏。利用ANSYS有限元软件建立了模型,对复合材料圆柱壳进行屈曲分析,将有限元计算的结构变形和屈曲载荷与试验结果进行对比,计算结果与试验结果一致,验证了模型的有效性。利用建立的有限元模型,分析了开口尺寸和铺层角度对含矩形开口的复合材料圆柱壳屈曲载荷的影响。在开口处加装复合材料口盖对结构进行补强,补强后的柱壳结构满足强度设计要求。     

复合材料气瓶的有限元建模与屈曲分析

复合材料气瓶在空间系统中逐渐取代全金属气瓶而得到越来越广泛的应用.利用ANSYS大型有限元程序建立复合材料气瓶及其内衬的有限元模型,建模中将纤维缠绕层作为复合材料层合板处理,考虑了封头处缠绕层厚度及缠绕角沿子午线不断变化的情况.建立了气瓶整体结构的特征值屈曲分析与非线性屈曲分析有限元方程,并分别进行了气瓶整体结构和内衬的外压失稳(屈曲)分析计算,得出了气瓶整体结构及内衬的屈曲模态形状和临界外压.     

2.5维编织复合材料力学性能的有限元分析

在已有研究的基础上,提出了一个新的2.5维编织复合材料有限元模型,该模型较为真实地模拟了织物内纤维束的轮廓结构和走向,可用于2.5维编织复合材料力学性能的有限元数值分析.利用该模型采用有限元法对2.5维编织复合材料进行了有效弹性性能的数值预报,并合理确定了复合材料内部应力场分布;同时提出经向纤维束横截面宽厚比是影响2.5维编织复合材料有效弹性性能的主要因素,分析了其影响情况.采用VARTM工艺制备了试验件,并对其进行力学性能测试.通过实验值和理论值的对比,结果表明:有限元计算得到的结果与实验值吻合较好,从而验证了该模型的有效性.     

二维二轴1×1编织复合材料细观结构模型及力学性能有限元分析

考虑纤维束相互挤压及横截面形状变化, 采用纤维束截面六边形假设, 建立了二维二轴1×1编织复合材料的参数化单胞结构模型。通过引入周期性位移边界条件, 基于细观有限元方法, 对编织材料的弹性性能进行预测, 讨论了编织角及纤维体积含量对面内弹性常数的影响, 并分析了典型载荷下单胞细观应力场分布。研究表明: 单胞结构模型有效反映了纤维束的空间构型和交织特征, 实现了不同编织工艺参数下模型的快速建立; 基于单胞有限元模型的弹性性能预测结果与试验结果较为吻合; 模型给出了单胞合理的应力场分布, 为二维编织复合材料的结构优化和损伤预测奠定基础。      

三维编织复合材料拉伸性能试验研究

制定了一套适用于测定三维编织复合材料拉伸性能的试验方法，并结合试验数据，总结了编织参数与三维编织复合材料拉伸性能的关系。     

三维多向编织复合材料宏细观力学性能有限元分析研究进展

三维多向编织复合材料综合力学性能优异,有望在航空航天领域作为主承力结构而得到广泛应用。有限元分析(FEA)方法是三维多向编织复合材料宏细观力学性能研究最为经济和有效的分析手段。从细观结构模型、刚度强度性能预测及界面性能分析等方面评述了细观有限元法的研究进展;从接头结构承载性能分析和冲击性能模拟等方面介绍了宏观有限元法的研究概况;分析了目前研究中存在的主要问题并对后续的研究工作进行了展望,为研究者了解该领域的研究现状和发展趋势提供了有价值的参考。     

复合材料加筋板后屈曲特性研究

通过对复合材料加筋板进行轴向压缩实验和非线性有限元模拟,研究了其后屈曲阶段的损伤和破坏行为.加筋板在实验中被压缩至完全破坏,压溃的加筋板表现出复杂的后屈曲损伤,包括筋条脱粘、纤维断裂、分层、基体开裂等损伤模式.有限元模型中引入了Hashin准则和基于二次应力的胶层失效准则,失稳及破坏载荷的预测结果和实验值吻合较好.分析...     

复合材料压力容器含凹陷内胆屈曲的有限元分析

提出了一种复合材料压力容器含凹陷金属内胆屈曲的三维有限元分析方法.基于平面应变假设,建立了含凹陷半圆环收缩屈曲分析模型,通过修改有限元模型中内胆的节点坐标,将内胆初始凹陷引入模型中,采用非线性迭代法逐步增大面内载荷,实现了含凹陷半圆环的收缩屈曲分析.在此基础上,建立复合材料压力容器含凹陷内胆的三维有限元分析模型,同时考...     

复合材料圆柱壳的轴压屈曲失效试验

为了研究高径比大于1的复合材料圆柱壳的轴压屈曲性能及其失效模式,对2组单向纤维圆柱壳和3组外侧环裹环向纤维圆柱壳进行了轴压试验,观察了试件的受力过程和破坏形态,获得了荷载-位移曲线和荷载-应变曲线,利用有限元模型分析了单向纤维圆柱壳两种屈曲形式的破坏机制,对比分析了两种铺层试件的轴压性能。结果表明:单向纤维复合材料圆柱壳出现先纵向劈裂后板壳屈曲和先柱壳屈曲后纵向劈裂的两种破坏模式;外侧环向纤维可改善圆柱壳的轴压性能,屈曲发展有一定的阶段性并表现出延性特征,破坏形式和承载力均较为稳定。     

带碟形封头压力容器内压屈曲有限元分析

本文针对对轴对称压力容器在内压作用下的变形特点，将结构划分为若干完全相同的子结构，通过求解单个子结构的增量平衡方程，得到了整个结构的应力，应变状态，由于各子结构及其受力状态完全相同，因此结构发生屈曲时各子结构具有完全相同的初应力和初应变刚度矩阵，根据这一特点，本文采用复约束方程，通过求解单个子结构的屈曲方程得到了整个结构的屈曲载荷和模态。大大减小了所求解问题的规模，并且在此简化过程中没有引入任何附     

A 3D cylindrical finite element model for thick curved beam stress analysis

A finite element model is proposed to perform stress analysis for thick curved beams and panels subjected to various types of loadings. The model has 18 nodes in a three‐dimensional cylindrical co‐ordinates system. Three stress components on radial surface (σ_rr, τ_rθ, and τ_rz) and three displacement components (u_r, u_θ, and u_z) are used as nodal degrees of freedom. Therefore, the continuity condition for both stresses and displacements is achieved in the radial direction. Formulation of nodal shape functions and equilibrium equations are based on three‐dimensional elasticity theory and a minimum potential energy method. The accuracy of the method is verified with the standard test problems and exact solutions from the theory of elasticity. The model shows no locking phenomena. Convergence is investigated and the application to layered composite panel is illustrated. Copyright © 2003 John Wiley & Sons, Ltd.     

Finite element buckling analysis of rotationally periodic laminated composite shells

A finite element (FE) buckling analysis of rotationally periodic laminated composite shells is performed in this paper. Because the buckling mode of such structures is characterized as rotationally periodic, a corresponding FE buckling analysis scheme is proposed to reduce the computational expenses. Moreover, a new kind of relative degrees‐of‐freedom element is developed, which can be connected to other solid elements with ease and can yield satisfactory results with a relatively coarse FE mesh. Numerical results of two laminated cylindrical shells subjected to lateral pressure are compared with theoretical ones. The good agreement of them shows the validity of this new computational strategy. Finally, a practical structure is analysed to demonstrate the advantage of this method. Copyright © 2001 John Wiley & Sons, Ltd.     

磁悬挂天平偏航电磁场的二维有限元分析

在磁悬挂天平偏航控制中，偏航线圈中的电流变化对模型姿态变化影响十分显著．为了提高天平的偏航控制精度，有必要对天平偏航电磁场进行更为精确的分析．该文采用有限单元法对磁悬挂天平偏航电磁场进行了分析，得到了比传统计算方法更为准确的结果，并在实验中进行了验证，从而为磁悬挂天平的偏航控制提供了参考．     

纤维缠绕复合材料气瓶内衬的屈曲分析

为深入了解纤维缠绕复合材料气瓶的内衬屈曲情况,基于ANSYS有限元软件,运用数值模拟方法对纤维缠绕复合材料气瓶的金属内衬结构进行屈曲分析,建立了复合气瓶内衬结构的有限元模型,采用特征值法分析得出内衬1~10阶的屈曲模态,并利用非线性稳定法绘出内衬位移量随外压变化曲线.结果表明,计算得到的内衬临界失稳外压为0.199 MPa,与复合气瓶内衬外压试验结果相符合,证实了本文对于复合气瓶内衬屈曲分析的可靠性.     

复合材料柱面壳压缩性能分析

对三分之一复合材料柱面壳进行压缩性能试验研究与理论分析, 试验得到柱面壳的破坏方式为屈曲破坏。利用有限元法对其建模分析和静强度分析, 得到的静强度远大于屈曲强度, 因此柱壳应该首先发生屈曲破坏, 这与试验结果相符; 且理论计算所得的屈曲强度与试验结果相符, 说明该模型可以用来分析整个复合材料柱壳的压缩破坏行为, 研究结果可为柱壳的结构设计提供参考。对比某一载荷下理论模型与实际模型上对应点的应变, 发现二者结果相符, 证明有限元建模有效。然后分别对理论模型进行屈曲分析。      

Post-buckling finite element analysis of composite cylindrical panels in axial compression

The post-buckling behaviour of composite cylindrical panels in axial compression is investigated using the nonlinear finite element theory. A branch switching algorithm with an ‘eigenmode injection’ is discussed. The effect of the reinforcement angle on the buckling load, as well as the post-buckling behaviour of the panels, are analysed. Examples are considered for separated and closely spaced bifurcation points.

By varying the reinforcement angle of the panels from 0 to 90°, two kinds of buckling modes are discovered for asymmetric and unstable symmetric lowest points of bifurcation. Local minima for the secondary branches of geometrically perfect panels are no less than 15% of their buckling loads, while values of the buckling loads alter more than twice in this region.

A 16-node degenerated shell element with full integration scheme is used.     

Nonlinear hygro-thermo-elastic vibration analysis of doubly curved composite shell panel using finite element micromechanical model

Nonlinear free vibration behavior of laminated composite curved panel under hygrothermal environment is investigated in this article. The mathematical model of the laminated panel is developed using Green–Lagrange-type geometrical nonlinearity in the framework of higher-order mid-plane kinematics. The corrugated composite properties are evaluated through the micromechanical model and all the nonlinear higher-order terms are included in the present model for the sake of generality. The equation of vibrated panel is obtained using Hamilton's principle and discretized with the help of the finite element steps. The solutions are computed numerically using the direct iterative method. The effect of parameters on the nonlinear vibration responses is examined thoroughly by solving the wide variety of numerical examples.     

Nonlinear buckling analysis of hygrothermoelastic composite shell panels using finite element method

Hygrothermal stresses due to the change in environmental condition may induce buckling and dynamic instability in the composite shell structures. In the present investigation, the hygrothermoelastic buckling behavior of laminated composite shells are numerically simulated using geometrically nonlinear finite element method. The orthogonal curvilinear coordinate is used for modeling a general doubly curved deep or shallow shell surface. The geometrically nonlinear finite element formulation is based on general nonlinear strain–displacement relations in the orthogonal curvilinear coordinate system. The present theory can be applicable to thin and moderately thick shells. The mechanical linear and nonlinear stiffnesses, and the nonmechanical nonlinear geometric stiffness matrices and the hygrothermal load vector are presented. It is also observed that during the present numerical solution of nonlinear equilibrium equation, in order to construct the nonlinear stiffness matrices for the first load step, the initial deformation can be assumed as zero or any computer generated small random number or the properly scaled fundamental buckling mode shape. To verify the present formulations and finite element code, the present results are compared well with those available in the open literature. Parametric studies such as thickness ratio and shallowness ratio on buckling are performed for spherical, truncated conical and cylindrical composite shell panels. The buckling behavior and deflection shapes are characterized by multiple wrinkles along unreinforced direction at higher moisture concentrations or temperature rise.     

Delamination buckling and propagation analysis of honeycomb panels using a cohesive element approach

The cohesive element approach is proposed as a tool for simulating delamination propagation between a facesheet and a core in a honeycomb core composite panel. To determine the critical energy release rate (G _c) of the cohesive model, Double Cantilever Beam (DCB) fracture tests were performed. The peak strength (_c) of the cohesive model was determined from Flatwise Tension (FWT) tests. The DCB coupon test was simulated using the measured fracture parameters, and sensitivity studies on the parameters for the cohesive model of the interface element were performed. The cohesive model determined from DCB tests was then applied to a full-scale, 914×914 mm (36×36 in.) debond panel under edge compression loading, and results were compared with an experiment. It is concluded that the cohesive element approach can predict delamination propagation of a honeycomb panel with reasonable accuracy.