一种预测层合板层间剪应力的新后处理方法

层合板是航空航天领域典型的承力构件,过大的层间应力是导致其分层失效的主要原因.准确的层间应力预测往往依赖于三维平衡方程后处理方法(TPM).然而,该方法需要计算面内应力的一阶导,使得基于C0型板理论构造的线性单元无法使用TPM计算横向剪应力.本文在三维平衡方程后处理方法的基础上,提出了一种新后处理方法(NPM).新后处理方法通过虚功等效法消除了三维平衡方程后处理方法中产生的位移参数的高阶导.基于提出的新后处理方法和C0型板理论,仅需使用线性单元就可以预测层合板的横向剪应力.为了验证所提方法的有效性,本文基于修正锯齿理论(RZT)和所提方法构造了一种C0连续的三节点三角形线性板单元.数值算例表明,所提方法和三维平衡方程后处理方法具有相同的计算精度,提出的板单元能够准确高效地预测层合板的横向剪应力.此外,所提方法便于结合现有的有限元商用软件使用,基于商用软件中板壳单元获得的节点位移,使用新后处理方法极易获得准确的层间剪应力.     

Analysis of nonlinear vibration for symmetric angle-ply laminated viscoelastic plates with damage

The behavior of nonlinear vibration for symmetric angle-ply laminated plates including the material viscoelasticity and damage evolution is investigated. By employing the von Karman's nonlinear theory, strain energy equivalence principle and Boltzmann superposition principle, a set of governing equations of nonlinear integro-differential type are derived. By applying the finite difference method, Newmark method and iterative procedure, the governing equations are solved. The effects of loading amplitudes, exciting frequencies and different ply orientations on the critical time to failure initiation and nonlinear vibration amplitudes of the structures are discussed. Numerical results are presented for the different parameters and compared with the available data. The project supported by the National Natural Science Foundation of China (10272042) and the Special Science Fund of the Doctoral Discipline of the Ministry of Education, China (20020532018) The English text was polished by Ron Marshall.     

粘弹层合板的自由振动和横向应力

Based on Reddy＇s layerwise theory, the governing equations for dynamic response of viscoelastic laminated plate are derived by using the quadratic interpolation function for displacement in the direction of plate thickness. Vibration frequencies and loss factors are calculated for free vibration of simply supported viscoelastic sandwich plate, showing good agreement with the results in the literature. Harmonious transverse stresses can be obtained. The results show that the transverse shear stresses are the main factor to the delamination of viscoelastic laminated plate in lower-frequency free vibration, and the transverse normal stress is the main one in higher-frequency free vibration. Relationship between the modulus of viscoelastic materials and transverse stress is analyzed. Ratio between the transverse stress＇s maximum value and the in-plane stress＇s maximum-value is obtained. The results show that the proposed method, and the adopted equations and programs are reliable.     

Buckling and postbuckling behavior of antisymmetrically angle-ply laminated composite plates

The buckling and postbuckling behaviors of perfect and imperfect antisymmetricallyangle-ply laminated composite plates under uniaxial compression have been studied byperturbation technique which takes deflection as its perturbation parameter.In this paper,the effects of in-plane boundary conditions,angles,total number oflayers and initial geometric imperfection on the postbuckling behavior of laminated plateshave been discussed.     

A wavelet approach for active-passive vibration control of laminated plates

As an extension of the wavelet approach to vibration control of piezoelectric beam-type plates developed earlier by the authors,this paper proposes a hybrid activepassive control strategy for suppressing vibrations of laminated rectangular plates bonded with distributed piezoelectric sensors and actuators via thin viscoelastic bonding layers.Owing to the low-pass filtering property of scaling function transform in orthogonal wavelet theory,this waveletbased control method has the ability to automatically filter out noise-like signal in the feedback control loop,hence reducing the risk of residual coupling effects which are usually the source of spillover instability.Moreover,the existence of thin viscoelastic bonding layers can further improve robustness and reliability of the system through dissipating the energy of any other possible noise induced partially by numerical errors during the control process.A simulation procedure based on an advanced wavelet-Galerkin technique is suggested to realize the hybrid active-passive control process.Numerical results demonstrate the efficiency of the proposed approach.     

Effect of interlaminar imperfections on a behaviour of laminated plates

Summary The effect of interlaminar bonding imperfections on behaviour of shells, investigated in [1], is elaborated here for a special case of laminated plates. The problem is stated for linear elastic materials, within the small displacement gradient theory. The obtained results are ilustrated by an example.

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Einfluß der Zwischenschichtdefekte auf das Verhalten geschichteter Platten

Übersicht Der in [1] beschriebene Einfluß der Zwischenschichtdefekte auf das Verhalten geschichteter Schalen wird hier speziell für den Sonderfall geschichteter Platten studiert. Das Problem wird unter Berücksichtigung der linearen Elastizitätstheorie und der Theorie der kleinen Verschiebungsgradienten betrachtet. Die erhaltenen Ergebnisse werden anhand eines Beispiels illustriert.

     

Bending of multiferroic laminated rectangular plates with imperfect interlaminar bonding

The bending problem of a multiferroic rectangular plate with magnetoelectric coupling and imperfect interfaces is investigated via three-dimensional exact theory. A generalized spring layer model is proposed to characterize the imperfection of the bonding behavior at interfaces. In particular, the linear relation between the electric displacement and the jump of electric potential, the corresponding one for the magnetic field as well as linear relations among different physical fields are adopted. State space formulations are established, which, compared to the analysis for perfect laminates, only introduces a so-called interfacial transfer matrix. The present analysis can be readily used for the piezoelectric, piezomagnetic and elastic laminates by setting the proper material constants as zero. Numerical results are presented and discussed.     

An exact symplectic solution for the dynamic analysis of shear deformable antisymmetric angle-ply laminated plates

From the mixed variational principle, by the selection of the state variables and its dual variables, the Hamiltonian canonical equation for the dynamic analysis of shear deformable antisymmetric angle-ply laminated plates is derived, leading to the mathematical frame of symplectic geometry and algorithms, and the exact solution for the arbitrary boundary conditions is also derived by the adjoint orthonormalized symplectic expansion method. Numerical results are presented with the emphasis on the effects of length/thickness ratio, arbitrary boundary conditions, degrees of anisotropy, number of layers, ply-angles and the corrected coefficients of transverse shear.     

Non-linear response of laminated plates and shells to thermomechanical loading: Implications of violation of interlaminar shear traction continuity requirement

A number of results focusing on the implications brought by the violation of the inter-laminar shear traction continuity requirement on the non-linear response of shear deformable laminated flat and curved panels subjected to thermomechanical loading are presented. The results cover a large number of situations, and in this context, the effects of transverse shear, tangential edge constraints, shell curvature, initial geometric imperfections, lateral pressure and compressive edge loads, membrane and thicknesswise temperature gradient, presence of a Winkler linear/non-linear foundation, coupled with that of the fulfilment/violation of the shear traction interlaminar continuity requirement upon the static and dynamic non-linear response of laminated plates and shells are highlighted. In order to address this problem, as a necessary pre-requisite, a higher-order geometrically non-linear laminated shell model fulfilling both the kinematical and shear traction interlaminar continuity requirements and incorporating the previously mentioned effects is presented. The results obtained in the framework of this laminated shell model are compared with the ones obtained within a higher-order shell model in which the kinematic interlaminar continuity conditions are solely satisfied, and the implications resulting from the violation of the shear traction interlaminar continuity requirement are highlighted.     

Free vibration analysis of stiffened laminated plates

Based on the semi-analytical solution of the state-vector equation theory, a novel mathematical model for free vibration analysis of stiffened laminated plates is developed by separate consideration of plate and stiffeners. The method accounts for the compatibility of displacements and stresses on the interface between the plate and stiffeners, the transverse shear deformation, and naturally the rotary inertia of the plate and stiffeners. Meanwhile, there is no restriction on the thickness of plate and the height of stiffeners. To demonstrate the excellent predictive capability of the model, several examples are analyzed numerically. The model presented in this paper can also be easily modified to solve the problems of stiffened piezolaminated plates and shells, or plates and shells with piezoelectric material patches.     

Bending and vibration of composite laminated plates

Hybrid-stress finite element method is applied for analysis of bending and vibration of composite laminated plates in this paper. Firstly, based on the modified complementary principle, a rectangular hybrid-stress plate bending element is presented which applies to analysis of laminates. Inside the element, different stress parameters are assumed according to different layers. The boundary displacements are determined by means of the assumption of YNS theory on the boundary of elements. The element formed in this way not only can take effects of transverse shear deformation and local warping into account, but also has less degrees of freedom. Then, problems of bending and vibration of laminates are solved by using this element, and the numerical results are compared with the exact solutions. This shows that the results obtained in the paper are very close to the exact results.     

Nonlinear vibration of viscoelastic laminated composite plates

The dynamic behavior of laminated composite plates undergoing moderately large deflection is investigated by considering the viscoelastic properties of the material. Based on von Karman's nonlinear deformation theory and Boltzmann's superposition principle, nonlinear and hereditary type governing equations are derived through Hamilton's principle. Finite element analysis and the method of multiple scales are applied to examine the effect of large amplitude on the dissipative nature as well as on the natural frequency of viscoelastic laminated plates. Numerical experiments are performed for the nonlinear elastic case and linear viscoelastic case to check the validity of the procedure presented in this paper. Limitations of the method are discussed also. It is shown that the geometric nonlinearity does not affect the dissipative characteristics in the cases that have nonlinearity of perturbed order.     

Nonlinear vibration of generally laminated anisotropic thick plates

Summary Nonlinear equations of motion of generally laminated anisotropic plates are derived by use of Hamilton's principle. The effects of transverse shear and rotatory inertia are included in the analysis. The equations of motion so obtained readily reduce to those obtained in a recent nonlinear theory of anisotropic plates including transverse shear and rotatory inertia and to the dynamic von Kármán equations of plates. Based on the Galarkin procedure and principle of harmonic balance approximate solutions to the governing equations of generally laminated rectangular plates are formulated for various boundary conditions. Including the effects of transverse shear and rotatory inertia numerical results for the ratio of nonlinear frequency to linear frequency of symmetric angle-ply and cross-ply laminates, unsymmetric angle-ply and cross-ply laminates and an arbitrarily laminated plate are presented graphically for various values of elastic properties, fiber orientation angle, number of layers, thickness-to-span ratio and aspect ratio. Present results are also compared with the existing data.

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Nichtlineare Schwingungen von anisotropen, dicken Verbundplatten

übersicht Die nichtlinearen Bewegungsgleichungen anisotroper, dicker Verbundplatten werden mit Hilfe des Prinzips von Hamilton hergeleitet. Dabei werden die Einflüsse der Schubspannungen und der Drehträgheit berücksichtigt. Mit dem Verfahren von Galerkin und der Methode der harmonischen Balance werden Näherungslösungen für Rechteckplatten bei verschiedenen Randbedingungen gewonnen. Numerische Ergebnisse für verschiedene Materialparameter sind graphisch dargestellt und werden mit bereits bekannten Ergebnissen verglichen.

     

Analysis of interlaminar stress and nonlinear dynamic response for composite laminated plates with interfacial damage

By considering the effect of interfacial damage and using the variation principle, three-dimensional nonlinear dynamic governing equations of the laminated plates with interfacial damage are derived based on the general sixdegrees-of-freedom plate theory towards the accurate stress analysis. The solutions of interlaminar stress and nonlinear dynamic response for a simply supported laminated plate with interfacial damage are obtained by using the finite difference method, and the results are validated by comparison with the solution of nonlinear finite element method. In numerical calculations, the effects of interfacial damage on the stress in the interface and the nonlinear dynamic response of laminated plates are discussed.     

A general analytical solution for elastic vibration of rectangular thin plates

A general solution of differential equation for lateral displacement lunction of rectangular elastic thin plates in free vibration is established in this paper. It can be used to solve the vibration problem of rectangular plate with arbitrary boundaries. As an example, the frequency and its vibration mode of a rectangular plate with four edges free have been solved.     

Free axisymmetric vibration of transversely isotropic laminated circular plates

Based on the three dimensional elastic theory, the state equation of the axisymmetric free vibration of transversely isotropic circular plates is established. Taking the advantage of finite Hankel transform, two exact solutions are derived for two boundary conditions, i. e. the rigid-slipping boundary and elastic simply supported boundary. Finally, numerical results are presented and compared with those of FEM. The project is supported by the National Natural Science Foundation of China and the Zhejiang Provincial Natural Science Foundation.     

Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

The influence of fiber orientation,flow yaw angle and length-to-thickness ratio on flutter characteristics of angle-ply laminated plates in supersonic flow is studied by finite element approach.The structural model is established using the Reissner-Mindlin theory in which the transverse shear deformation is considered.The aerodynamic pressure is evaluated by the quasi-steady first-order piston theory.The equations of motion are formulated based on the principle of virtual work.With the harmonic motion assumption,the flutter boundary is determined by solving a series of complex eigenvalue problems.Numerical study shows that (1) The flutter dynamic pressure and the coalescence of flutter modes depend on fiber orientation,flow yaw angle and length-to-thickness ratio;(2) The laminated plate with all fibers aligned with the flow direction gives the highest flutter dynamic pressure,but a slight yawing of the flow from the fiber orientation results in a sharp decrease of the flutter dynamic pressure;(3) The angle-ply laminated plate with fiber orientation angle equal to flow yaw angle gives high flutter dynamic pressure,but not the maximum flutter dynamic pressure;(4) With the decrease of length-to-thickness ratio,an adverse effect due to mode transition on the flutter dynamic pressure is found.     

Multi-mode nonlinear vibration and postbuckling of antisymmetrically laminated imperfect angle-ply cylindrical panel with free straight edges

Summary A multi-mode solution to nonlinear vibration and postbuckling of the titled problem is presented for two straight edges free from forces and bending moments and the other edges subjected to identical variation of rotational stiffness and normal boundary forces. The dynamic Marguerre-type nonlinear equations are adopted. The transverse deflection and stress function are expanded into two series with timedependent coefficients. The Galerkin procedure furnishes an infinite system of ordinary differential equations for these time functions. The method of harmonic balance is used for a solution of a finite number of these equations. The postbuckling behavior is treated as a special case. Numerical results in nonlinear vibration and postbuckling of antisymmetrically laminated angle-ply panel are presented graphically for different panel parameters and also compared with available data.

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Nichtlineare Schwingung und Nachbeulen einer antisymmetrisch geschichteten, imperfekten zylindrischen Schale mit freien geraden Rändern

Übersicht Für das im Titel genannte Problem wird bei Normalkraftbelastung und Verdrehsteifigkeit der kreisbogenförmigen Ränder eine Lösung der dynamischen, nichtlinearen Marguerre-Gleichungen in Form verallgemeinerter Fourier-Reihen für die Durchbiegung und Spannungsfunktion mit zeitabhängigen Koeffizienten vorgestellt. Das Galerkin-Verfahren liefert ein System unendlich vieler gewöhnlicher Differentialgleichungen für diese Zeitfunktionen. Zur Lösung einer endlichen Zahl der Gleichungen wird die Methode der harmonischen Balance benutzt. Für verschiedene Schalenparameter werden numerische Resultate zur Schwingung und zum Nachbeulen in graphischer Form dargestellt und mit fremden Ergebnissen verglichen.