Efficient laminated composite beam element subjected to variable axial force for coupled stability analysis

A numerically efficient laminated composite beam element subjected to a variable axial force is presented for a coupled stability analysis. The analytical technique is used to present the thin-walled laminated composite beam theory considering the transverse shear and the restrained warping-induced shear deformation based on an orthogonal Cartesian coordinate system. The elastic strain energy and the potential energy due to the variable axial force are introduced. The equilibrium equations are derived from the energy principle, and explicit expressions for the displacement parameters are presented using the power series expansions of displacement components. Finally, the member stiffness matrix is determined using the force–displacement relations. In order to verify accuracy and efficiency of the beam element developed in this study, numerical results are presented and compared with results from other researchers and the finite beam element results, and the detailed finite shell element analysis results using ABAQUS; especially, the influence of variable axial forces, the fiber orientation, and boundary conditions on the buckling behavior of the laminated composite beams is parametrically investigated.     

Postbuckling and free vibrations of composite beams

An exact solution for the postbuckling configurations of composite beams is presented. The equations governing the axial and transverse deformations of a composite laminated beam accounting for the midplane stretching are derived. The inplane inertia and damping are neglected, and hence the two equations are reduced to a single nonlinear fourth-order partial–integral–differential equation governing the transverse deformations. We find out that the governing equation for the postbuckling of symmetric or asymmetric composite beams has the same form as that of beams made of an isotropic material. Composite beams with fixed–fixed, fixed–hinged, and hinged–hinged boundary conditions are considered. A closed-form solution for the postbuckling deformation is obtained as a function of the applied axial load, which is beyond the critical buckling load. To study the vibrations that take place in the vicinity of a buckled equilibrium position, we exactly solved the linear vibration problem around the first buckled configuration. Solving the resulting eigen-value problem results in the natural frequencies and their associated mode shapes. Both the static response represented by the postbuckling analysis and the dynamic response represented by the free vibration analysis in the postbuckling domain strongly depend on the lay-up of the laminate. Variations of the beam’s midspan rise and the fundamental natural frequency of the postbuckling domain vibrations with the applied axial load are presented for a variety of lay-up laminates. The ratio of the axial stiffness to the bending stiffness was found to be a crucial parameter in the analysis. This control parameter, through the selection of the appropriate lay-up, can be manipulated to help design and optimize the static and dynamic behavior of composite beams.     

On a moderate rotation theory of thin-walled composite beams

A small strain and moderate rotation theory of laminated composite thin-walled beams is formulated by generalizing the classical Vlasov theory of sectorial areas. The proposed beam model accounts for axial, bending, torsion and warping deformations and allows one to predict critical loads and initial post-buckling behaviour. A finite element approximation of the theory is also carried out and several numerical applications are developed with reference to lateral buckling of composite thin-walled members. The sensitivity of critical load to second-order effects in the pre-buckling range is pointed out.     

Super convergent shear deformable finite elements for stability analysis of composite beams

The super convergent finite beam elements are newly presented for the spatially coupled stability analysis of composite beams. For this, the theoretical model applicable to the thin-walled laminated composite I-beams subjected to the axial force is developed. The present element includes the transverse shear and the warping induced shear deformation by using the first-order shear deformation beam theory. The stability equations and force–displacement relationships are derived from the principle of minimum total potential energy. The explicit expressions for the seven displacement parameters are then presented by applying the power series expansions of displacement components to simultaneous ordinary differential equations. Finally, the element stiffness matrix is determined using the force–displacement relationships. In order to demonstrate the accuracy and the superiority of the beam element developed by this study, the numerical solutions are presented and compared with the results obtained from other researchers, the isoparametric beam elements based on the Lagrangian interpolation polynomial, and the detailed three-dimensional analysis results using the shell elements of ABAQUS. The effects of shear deformation, boundary condition, fiber angle change, and modulus ratios on buckling loads are investigated in the analysis.     

The influence of mechanical couplings on the compressive stability of anti-symmetric angle-ply laminates

The compressive stability of anti-symmetric angle-ply laminated plates with particular reference to the degrading influence of membrane–flexural coupling is reported in this paper. The degree of membrane–flexural coupling in the laminated composite plates is varied, essentially, by altering the ply-angle and the number of plies in the laminated stack for a given composite material system. The coupled compressive buckling solutions are determined in the paper using the finite strip method of analysis and the buckling displacement fields of the strip formulation are those which are able to provide zero in-plane normal movement at the edge boundaries of the laminated plates.

Results are given for anti-symmetric angle-ply laminated plates subjected to uniaxial compression and these have been obtained from fully converged finite strip structural models. Validation of the finite strip formulation is indicated in the paper through comparisons with exact solutions where appropriate. Increasing the number of plies in the laminated system is seen to reduce the degree of coupling and the critical stress levels are noted to tend towards the plate orthotropic solutions. The ply-angle corresponding to the optimised buckling stress for any particular laminate is noted in the paper to be influenced by the support boundary conditions at the plates unloaded edges. For any particular laminate the minimum critical buckling stress and corresponding natural half-wavelength of the buckling mode are shown to be highly sensitive to ply-angle variation.

Some post-buckling results are presented in the paper and these have been determined using the finite element method of analysis. The influence of membrane–flexural coupling is shown to be significant throughout the compressive post-buckling history of the laminated plates. The optimised ply-angle with regard to the critical compressive buckling stress of square simply supported anti-symmetric angle-ply laminates is shown to be less effective in the post-buckling range with regard to post-buckled compressional stiffness.     

Lateral buckling analysis of thin-walled laminated channel-section beams

The lateral buckling of a laminated composite beam with channel section is studied. A general analytical model applicable to the lateral buckling of a channel-section composite beam subjected to various types of loadings is derived. This model is based on the classical lamination theory, and accounts for the material coupling for arbitrary laminate stacking sequence configuration and various boundary conditions. The effects of the location of applied loading on the buckling capacity are also included in the analysis. A displacement-based one-dimensional finite element model is developed to predict critical loads and corresponding buckling modes for a thin-walled composite beam with arbitrary boundary conditions. Numerical results are obtained for thin-walled composites under central point load, uniformly distributed load, and pure bending with angle-ply and laminates. The effects of fiber orientation, location of applied load, and types of loads on the critical buckling loads are parametrically studied.     

Assessment of zigzag theory for static loading, buckling, free and forced response of composite and sandwich beams

An efficient zigzag one-dimensional (1D) theory of laminated beams is assessed by comparison of analytical solutions of simply supported beam with exact 2D elasticity solutions for static patch load, natural frequencies, harmonic transverse load with sinusoidal longitudinal variation and buckling under axial load. These results for a highly inhomogeneous test beam, symmetric composite beam, anti-symmetric composite beam and sandwich beam are also compared with first order (FSDT) and third order (TOT) shear deformation theories. The effect of the laminate lay-up and the thickness-to-span ratio on the accuracy is assessed. The zigzag theory yields much more accurate results than the TOT and FSDT.     

含脱层单向铺设层合梁非线性后屈曲分析

采用四分区模型,将含脱层单向铺设复合材料层合板梁分为4个子梁,根据复合材料层合理论,考虑后屈曲路径上位于脱层界面上、下子梁之间的局部受力与变形机制,建立了子梁之间接触力与变形之间的非线性定量关系。在此基础上,结合可伸长梁的几何非线性理论,推导出了计及接触效应的各子梁的非线性后屈曲控制方程。设定简支板梁的边界条件以及脱层前沿处各子梁之间力和位移的连续性条件,通过对控制方程和定解条件归一化,采用小参数摄动法求解,并根据梁的平衡微分方程的特点,解析其通解与特解的构造,获得了含脱层单向铺设层合梁受轴向压力作用的临界屈曲荷载及后屈曲平衡路径的理论解。通过对含脱层单向铺设的复合材料层合梁进行数值分析,综合讨论了脱层长度和深度等对层合板梁的临界屈曲载荷及接触性能的影响,并将所得的理论解与ABAQUS有限元分析得到的结果进行对比,结果表明二者高度吻合。研究发现梁的屈曲模态包含宏观的整体失效模态和界面的微观屈曲模态。梁的屈曲荷载和接触性能都是其固有属性,前者受梁的几何参数和材料参数的影响较显著,而后者则主要受脱层的位置和大小影响。     

轴向变速运动弯曲梁的固有频率分析

基于动力刚度矩阵法对轴向变速运动弯曲梁的固有频率进行分析,根据Hamilton原理,推导轴向变速运动弯曲梁的时域控制方程和边界条件,通过傅里叶变换得到频域控制方程和边界条件,求解频域控制方程,并结合位移边界条件和载荷边界条件,建立轴向变速运动弯曲梁的动力刚度矩阵模型;引入Hermite形式的形函数,建立了轴向变速运动弯曲梁的有限元模型。算例中,通过对比现有文献中的结果、有限元模型结果和动力刚度矩阵法模型结果,验证了该文所建立的力学模型,动力刚度矩阵法比有限元法具有更高的精度和效率,分析了轴向变速运动弯曲梁固有频率随着弯曲梁轴向运动速度、加速度、轴向受力、边界条件的变化规律。     

Analysis of shear-deformable composite beams in postbuckling

The nonlinear response of composite beams modeled according to higher-order shear deformation theories in postbuckling is investigated. The beam ends are restrained from axial movement, and as a result the contribution of the midplane stretching is considered. The equations of motion and the boundary conditions are derived using Hamilton’s principle. The shear deformation effect on the critical buckling load and static postbuckling response is introduced using classical, first-order, and higher-order shear deformation theories. This paper presents an exact solution for the static postbuckling response of a symmetrically laminated simply supported shear-deformable composite beam. The shear effect is shown to have a significant contribution to both the buckling and postbuckling behaviors. Results of this analysis show that classical and first-order theories underestimate the amplitude of buckling while all higher-order theories, considered in this study, yield very close results for the static postbuckling response.     

Analysis of shear-deformable composite beams in postbuckling

The nonlinear response of composite beams modeled according to higher-order shear deformation theories in postbuckling is investigated. The beam ends are restrained from axial movement, and as a result the contribution of the midplane stretching is considered. The equations of motion and the boundary conditions are derived using Hamilton’s principle. The shear deformation effect on the critical buckling load and static postbuckling response is introduced using classical, first-order, and higher-order shear deformation theories. This paper presents an exact solution for the static postbuckling response of a symmetrically laminated simply supported shear-deformable composite beam. The shear effect is shown to have a significant contribution to both the buckling and postbuckling behaviors. Results of this analysis show that classical and first-order theories underestimate the amplitude of buckling while all higher-order theories, considered in this study, yield very close results for the static postbuckling response.     

Complete solution of elastica for a clamped-hinged beam, and its applications to a carbon nanotube

Summary This paper treats an exact elastica solution for a clamped-hinged beam, and its applications to a carbon nanotube. Although the elastica has a long history, and the exact post-buckling solution for the Euler buckling problem has been known for at least 150 years, it seems that the elastica solution for a post-buckled clamped-hinged beam has never been obtained. Therefore, the exact solution obtained in this paper constitutes an addition to the existing family of elastica solutions. As an application of the results, a post-buckling analysis of a single wall carbon nanotube is studied. Also, a potential use of the post-buckling analysis of the carbon nanotube for the determination of its Young's modulus has been indicated.     

侧边边界条件对复合材料加筋板轴压载荷下屈曲和后屈曲性能的影响

为研究侧边边界条件对复合材料加筋板压缩稳定性能的影响,首先采用有限元软件对压缩载荷作用下的复合材料加筋板进行建模数值计算,得到加筋板在侧边简支和自由2种边界条件下的屈曲载荷和形式,然后采用工程计算方法对加筋板轴压承载能力进行了估算,参考计算结果,分别对侧边有支持和侧边自由2组加筋板进行轴向压缩试验,分析侧边边界条件对试验件的屈曲形式、屈曲载荷以及后屈曲破坏过程的影响。试验结果表明：侧边支持条件会影响加筋板的屈曲形式和破坏形式。对于侧边有支持的试验件,屈曲后整体变形较小,筋条的压缩断裂是主要的破坏形式;而侧边自由的试验件屈曲后会逐渐出现整体弯曲变形,变形引起的筋条脱粘和弯曲断裂则是主要的破坏形式,且筋条脱粘会显著降低结构的承载能力。有限元计算结果与试验结果较吻合,验证了有限元模型的合理性。采用工程计算方法对侧边有支持的加筋板承载能力进行估算具有较好的精度。     

Adaptive post-buckling response of carbon fibre composite plates employing SMA actuators

Restoration forces, associated with embedded activated pre-strained SMA wires, have successfully been employed to enhance the post-buckling behaviour of laminated plate structures while under the influence of a uniaxial load. The results of which will be presented. The manufacturing methodology of the hybrid SMA-carbon-epoxy plates is outlined. Optical micrographs illustrate the effect of embedding diametrical inclusions within a host composite. Thermal and structural finite-element analysis have been employed to predict the non-uniform temperature profile within the laminates and to provide insight to the SMA-hybrid structure adaptive response. It is shown that by utilizing the considerable control authority generated, even for a small actuator volume fraction, the out-of-plane displacement of the post-buckled laminates can be significantly reduced. Such displacement alleviation allows for the load redistribution away from the plate's unloaded edges i.e. there is a tendency for the plate to conform to the optimal flat configuration beyond its critical buckling load. However, the stability of the adaptive response is very much dependent upon the laminate stacking sequence. It is envisaged that the range of operational performance for such an adaptive hybrid structure may be extended over conventional materials and structures.     

The stability behavior of rotating composite shafts under axial compressive loads

This paper studies the stability behavior of a rotating composite shaft subjected to axial compressive loads using finite element method. The laminated composite shaft is modeled as a Timoshenko shaft by applying the equivalent modulus beam theory. Numerical results correlate well with the reported beam models. The critical speed of the thin-walled composite shaft is dependent on the stacking sequency, the length-radius ratio (L/R) and the boundary conditions. In addition, the effects of the rotational speeds and the disk location on the rotating shafts' stability are examined as well. The critical load of the rotating thin-walled composite shaft can be nearly assessed from the conventional buckling formulation.     

Post-buckling analysis of skew plates subjected to combined in-plane loadings

Post-buckling behavior of laminated composite, sandwich and functionally graded skew plates is analyzed in the present work. The problem formulation is based on higher-order shear deformation theory and von Kármán’s nonlinear kinematics. Linear mapping is used to transform the physical domain into the computational domain. Chebyshev polynomials are used for spatial discretization of governing differential equations and boundary conditions. The nonlinear terms are linearized using quadratic extrapolation technique. The effect of the skew angle on the buckling and post-buckling response of the composite, sandwich and FGM-clamped skew plates is investigated for different combinations of in-plane compressive loadings.     

BUCKLING AND INITIAL POST-BUCKLING OF THIN-WALLED COMPOSITE BEAMS

ABSTRACT

The buckling and initial post-buckling behaviour of thin-walled composite beams is analysed in this paper. The governing equations are based on the main assumption that the displacement components in the plane perpendicular to the axial direction are of the type of rigid-body motion. The shear strain in the middle surface of the beam wall is taken into account as the shear stiffness of the composite material is low. The governing equations are solved by a perturbation method. For the case of simply supported ends, double Fourier series are used to solve the equations for perturbation terms of different orders. Then, some formulas derived by Budiansky in the notation of functional analysis are cited to calculate the initial post-buckling parameters. The experimental results of five specimens of circular open cross-section are compared with the numerical results.     

航空复合材料加筋板剪切稳定性及后屈曲承载性能

开展了复合材料加筋板剪切稳定性试验,研究了加筋板在承剪状态下的屈曲载荷、屈曲模态、后屈曲承载性能及破坏模式。试验结果表明,加筋板在剪切屈曲载荷下形成的屈曲波长轴线与加强件轴线夹角约45°,当屈曲比达到1.2时,存在二次屈曲行为,最终破坏载荷约为屈曲载荷的1.28倍;加筋板在二次屈曲失稳前,加强件几乎保持直线,起"屈曲分隔"的作用。结合试验现象,进行了加筋板剪切屈曲及后屈曲性能理论分析,得出的理论屈曲载荷与试验屈曲载荷的相对误差为7.2%,后屈曲阶段的理论载荷-应变曲线与试验结果的相对误差在10%以内,并确定了后屈曲角随屈曲比的变化规律。     

Prebuckling and buckling analysis of variable angle tow plates with general boundary conditions

The concept of variable angle tow (VAT) placement is explored for enhancing the buckling resistance of composite plates subjected to axial compression loading. The problem is relatively difficult to solve because of varying stiffness properties and requires prior prebuckling analysis to determine the non-uniform stress variation followed by the buckling analysis of VAT plates. A stress function formulation for in-plane analysis and displacement formulation for buckling analysis was employed to derive the governing differential equations of VAT plates based on classical laminated plate theory. The Differential Quadrature Method (DQM) is applied to solve the differential equations. The novel aspect of the present work is the use of Airy’s stress function to model the prebuckling analysis of VAT plates which considerably reduces the problem size, computational effort and provides generality to model pure stress and mixed boundary conditions. DQM was applied first to solve the prebuckling problem of VAT plates subjected to cosine distributed compressive load/ uniform end shortening. Then, DQM was applied to solve the buckling problem of rectangular VAT plates subjected to axial compression under different plate boundary conditions. Results were validated with detailed finite element analysis and the relative accuracy and efficiency of the DQM approach is discussed.     

界面掀起和轴力对组合梁动力弯曲特性的影响

考虑组合梁界面的法向/切向部分相互作用以及各子梁轴力的二阶效应,利用Hamilton原理得到了位移描述的Euler-Bernoulli组合梁非线性动力弯曲及一阶近似的初边值问题,并应用微分求积法研究了考虑界面法向/切向部分相互作用组合梁的临界荷载和固有频率。在通过与已有解析解和有限元结果对比验证了本文微分求积法正确性和适用性的基础上,进行了参数分析,研究了组合梁界面刚度对组合梁动力特性和稳定性的影响以及轴力对组合梁固有频率的影响。数值结果表明：组合梁的固有频率与临界荷载随界面刚度的增加而增加,并逐步趋于完全作用组合梁的固有频率与临界荷载;当轴向压力逐渐增加并趋于临界载荷时,组合梁的一阶固有频率逐渐减小并趋于零,并且,临界载荷随法向和切向刚度的增加而增加。