scholarly journals Bending Response of Cross-Ply Laminated Composite Plates with Diagonally Perturbed Localized Interfacial Degeneration

2013 ◽  
Vol 2013 ◽  
pp. 1-13 ◽  
Author(s):  
Chee Zhou Kam ◽  
Ahmad Beng Hong Kueh
Keyword(s):  
Composite Plate ◽  
Laminated Composite ◽  
Composite Plates ◽  
Interface Element ◽  
Laminated Composite Plates ◽  
Laminated Composite Plate ◽  
Bending Performance ◽  
Element Approach ◽  
Bending Behavior ◽  
Bending Response

A laminated composite plate element with an interface description is developed using the finite element approach to investigate the bending performance of two-layer cross-ply laminated composite plates in presence of a diagonally perturbed localized interfacial degeneration between laminae. The stiffness of the laminate is expressed through the assembly of the stiffnesses of lamina sub-elements and interface element, the latter of which is formulated adopting the well-defined virtually zero-thickness concept. To account for the extent of both shear and axial weak bonding, a degeneration ratio is introduced in the interface formulation. The model has the advantage of simulating a localized weak bonding at arbitrary locations, with various degeneration areas and intensities, under the influence of numerous boundary conditions since the interfacial description is expressed discretely. Numerical results show that the bending behavior of laminate is significantly affected by the aforementioned parameters, the greatest effect of which is experienced by those with a localized total interface degeneration, representing the case of local delamination.

Vibroacoustic analysis of a thin laminated composite plate with surface-boned piezoelectric patches and subjected to general boundary conditions

2021 ◽  
Vol 263 (4) ◽  
pp. 2501-2509
Author(s):  
Zhengmin Hu ◽  
Kai Zhou ◽  
Yong Chen
Keyword(s):  
Fourier Series ◽  
Boundary Conditions ◽  
Composite Plate ◽  
Laminated Composite ◽  
Composite Plates ◽  
General Boundary ◽  
General Boundary Conditions ◽  
Acoustic Response ◽  
Laminated Composite Plates ◽  
Laminated Composite Plate

In this paper, a semi-analytical model is proposed to deal with the vibroacoustic problems of laminated composite plates with surfaced-boned piezoelectric patches and subjected to general boundary condition using the modified Fourier series method. Based on Kirchhoff plate theory, the dynamic equation of the laminated composite plate is derived using Hamilton's principle. In order to satisfy general boundary conditions, the displacement solution of the plate is expressed in the form of two-dimensional Fourier series and serval auxiliary functions. The acoustic response of the laminated composite plate due to a harmonic concentrated force is obtained with the Rayleigh integral. Besides, the mass and stiffness contribution of the piezoelectric patch are taken into consideration in the present study. Through enough convergent studies and comparative studies, the convergence, accuracy and universality of the proposed method are validated. The developed semi-analytical model can be used for efficient and accurate analysis and design of laminated composite plates equipped with shunted piezoelectric patches. Finally, the effects of the resistor and inductor shunt damping circuits on the vibration and acoustic response is discussed.

Dynamic Analysis of Orthotropic Laminated Composite Plate Under Axial Load on Elastic Foundation

2006 ◽  
Author(s):  
M. T. Ahmadian ◽  
T. Pirbodaghi
Keyword(s):  
Natural Frequency ◽  
Elastic Foundation ◽  
Composite Plate ◽  
Shear Deformation Theory ◽  
Compressive Force ◽  
Laminated Composite ◽  
Free Vibration Analysis ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Laminated Composite Plate

In this paper, free vibration analysis of laminated composite plates is carried out using first shear deformation theory and finite element method. Effect of axial tension and compression forces on the natural frequencies of the structure is investigated. Applying elastic foundation under the laminated composite plates has enabled us to achieve desired frequencies. The displacements are based C° – nine plate bending element and each node has three degree of freedom. The equations of motion are derived using Hamilton's principle. Results indicate the tension forces will increase the natural frequency while the compression force reduces the natural frequency. The buckling force of plate is computed by increasing the absolute value of compressive force until the natural frequency tends to zero. Dynamic of moving mass in a circular path on the laminated composite plate is also investigated. Displacement of plate center reveals a sinusoidal pattern in time.

Non-linear response and buckling of imperfect laminated composite plates under in-plane pulse forces

2021 ◽  
pp. 095440622199639
Author(s):  
Rajesh Kumar ◽  
Vishal Singh ◽  
SN Patel ◽  
Tanish Dey
Keyword(s):  
Dynamic Response ◽  
Composite Plate ◽  
Failure Load ◽  
Laminated Composite ◽  
Composite Plates ◽  
Dynamic Buckling ◽  
Laminated Composite Plates ◽  
Laminated Composite Plate ◽  
Non Linear ◽  
Static Failure

This study presents a semi-analytical solution of the non-linear dynamic response, shock spectrum, and dynamic buckling of an imperfect angle-ply laminated composite plate under various types of in-plane pulse forces. The laminated composite plate is modeled using a higher-order shear deformation theory and von-Kármán geometric nonlinearity. The non-linear governing partial differential equations (PDEs) of imperfect laminated composite plates are derived via Hamilton’s principle. Using Galerkin’s method, the non-linear PDEs are transformed into non-linear algebraic equations for the static stability problems and non-linear ordinary differential equations for the dynamic problem such as dynamic response, shock spectrum, and dynamic buckling. The buckling load of the plate is obtained through the associated eigenvalue problem. The static failure load of the composite plate is evaluated using the post-buckling analysis based on the Tsai-Wu failure criterion. The dynamic response and shock spectrum of the composite plate are determined via Newmark’s method. The dynamic failure load of the plate is evaluated using Newmark’s method based on the Tsai-Wu failure criterion. Dynamic buckling is to be characterized by dynamic load factor (DLF), which is represented as the ratio of the dynamic failure load to the static failure load. Based on the pulse/shock duration time, the pulse forces are divided into three loading regimes known as impulsive, dynamic, and quasi-static. The study revealed that the DLF values are > 1, < 1, and [Formula: see text]1 respectively for the case of impulsive, dynamic, and quasi-static loading regimes of pulse force. The influences of various types of in-plane pulse forces, amplitude and time duration of pulse forces, and amplitude of initial geometric imperfections on the non-linear dynamic response, shock spectrum, and dynamic buckling behavior of the laminated composite plate are addressed in detail. The results will help in the appropriate design of the laminated composite plate against dynamic buckling.

Analytical and Experimental Investigation of Ballistic Impact on Thin Laminated Composite Plate

2018 ◽  
Vol 10 (02) ◽  
pp. 1850020 ◽  
Author(s):  
Reza Mohamadipoor ◽  
Ehsan Zamani ◽  
Mohammad Hossein Pol
Keyword(s):  
Composite Plate ◽  
Laminated Composite ◽  
Composite Plates ◽  
Ballistic Limit ◽  
Laminated Composite Plates ◽  
Laminated Composite Plate ◽  
Residual Velocity ◽  
Limit Velocity ◽  
Ballistic Experiment ◽  
Ballistic Limit Velocity

Penetration of flat-ended cylindrical projectiles into thin laminated composite plates was investigated analytically and experimentally. An analytical modeling was carried out for thin laminated composite plates by developing a new function for deflection by computing Von Karman nonlinear strains and by using the principle of energy balance. During the perforation process, different regions were considered for the plate, such as fracture region, elastic deformation region, delamination region, and undeformed region. The energy absorbed by each region was measured in small time intervals. To validate this model, the ballistic experiment is performed on the thin laminated composite plate near and beyond ballistic limit velocity. The samples were made from plain woven glass/epoxy using a hand lay-up method. In addition to the initial velocity, the residual velocity of the projectile was also measured using two parallel laser curtains. A comparison drawn between analytical and experimental results demonstrated a good consistency in the residual velocity of the projectile. Finally, the distribution of strains along the plate thickness direction over time, the different amounts of absorbed energy of the failure modes, delamination radius, and energy are assessed at near and beyond ballistic limit velocity.

scholarly journals Experimental and Numerical Buckling Analyses of Laminated Composite Plates under Temperature Effects

2010 ◽  
Vol 19 (4) ◽  
pp. 096369351001900 ◽  
Author(s):  
Emin Ergun
Keyword(s):  
Composite Plate ◽  
Numerical Solutions ◽  
Laminated Composite ◽  
Composite Plates ◽  
Buckling Load ◽  
Fibre Reinforcement ◽  
Stacking Sequence ◽  
Laminated Composite Plates ◽  
Different Temperatures ◽  
Good Agreement

The aim of this study is to investigate, experimentally and numerically, the change of critical buckling load in composite plates with different ply numbers, orientation angles, stacking sequences and boundary conditions as a function of temperature. Buckling specimens have been removed from the composite plate with glass-fibre reinforcement at [0°]i and [45°]i (i= number of ply). First, the mechanical properties of the composite material were determined at different temperatures, and after that, buckling experiments were done for those temperatures. Then, numerical solutions were obtained by modelling the specimens used in the experiment in the Ansys10 finite elements package software. The experimental and numerical results are in very good agreement with each other. It was found that the values of the buckling load at [0°] on the composite plates are higher than those of other angles. Besides, symmetrical and anti-symmetrical conditions were examined to see the effect of the stacking sequence on buckling and only numerical solutions were obtained. It is seen that the buckling load reaches the highest value when it is symmetrical in the cross-ply stacking sequence and it is anti-symmetrical in the angle-ply stacking sequence.

Analytical modeling of laminated composite plates integrated with piezoelectric layer using Trigonometric Zigzag theory

2020 ◽  
Vol 54 (29) ◽  
pp. 4691-4708
Author(s):  
Aniket Chanda ◽  
Rosalin Sahoo
Keyword(s):  
Transverse Shear ◽  
Piezoelectric Layer ◽  
Composite Plate ◽  
Laminated Composite ◽  
Composite Plates ◽  
Solution Technique ◽  
Shear Stresses ◽  
Smart Composite ◽  
Laminated Composite Plate ◽  
Zigzag Theory

The analytical solution for static analysis of laminated composite plate integrated with piezoelectric fiber reinforced composite actuator is obtained using a recently developed Trigonometric Zigzag theory. The kinematic field consists of five independent field variables accommodating non-linear variation of transverse shear strains through the thickness of the laminated composite plate. The principle of minimum potential energy is adopted to derive the governing equations of equilibrium. Navier’s solution technique is employed to convert the system of coupled partial differential equations into a system of algebraic equations. The electric potential is assumed to vary linearly through the thickness of the piezoelectric layer. The analytical formulation also does not include voltage as an additional primary variable. The response in the form of deflection and stresses are obtained for smart composite plates subjected to electro-mechanical loads and compared with the elasticity solutions and available results reported by other researchers in the existing literature. The transverse shear stresses are accurately determined by an efficient post-processing technique of integrating the equilibrium equations of elasticity. Parametric studies on actuation in the response of the smart composite plate are also presented graphically in order to have a clear understanding of the static behavior.

The Research of Structural Parameters on Natural Frequency of Laminated Composite Plates

2013 ◽  
Vol 740 ◽  
pp. 461-464
Author(s):  
Fei Zhao ◽  
Jin Wu Wu
Keyword(s):  
Natural Frequencies ◽  
Structural Parameters ◽  
Orientation Angle ◽  
Laminated Composite ◽  
Composite Plates ◽  
Element Model ◽  
Laminated Composite Plates ◽  
Laminated Composite Plate ◽  
Modulus Ratio ◽  
Depth Ratio

In this paper, natural frequencies of laminated composite plates were studied. The layerwise finite element model is imposed to determine the natural frequencies of laminated composite plates. The effects of panel orientation angle, elastic modulus ratio and width-depth ratio on the natural frequencies of the laminated composite are then discussed. With an example of a sixteen-laying laminated plate, the numerical simulations show that the factor of key structural parameters to the natural frequencies of the laminated composite plate is panel orientation angle and width-depth ratio.

Large Deflection of a Laminated Composite Plate With Different Extensional and Flexural Material Properties

2010 ◽  
Author(s):  
Rifat Arıko¨k ◽  
Zahit Mecitog˘lu
Keyword(s):  
Material Properties ◽  
Composite Plate ◽  
Large Deflection ◽  
Virtual Work ◽  
Flexural Modulus ◽  
Laminated Composite ◽  
Composite Plates ◽  
Equation System ◽  
Laminated Composite Plate ◽  
Element Analysis

This paper presents the large deflection elastic analysis of the hand lay-up composite plates with different extensional and flexural modulus including geometric nonlinearity effects that are taken into account with the von Ka´rma´n large deflection theory of thin plates. Governing equations of the motion are derived by means of the virtual work principle. Then the Galerkin method is applied to reduce the nonlinear coupled differential equations into a nonlinear algebraic equation system. The MATLAB and MATHEMATICA software are used to solve the equation system. Because of the common nonuniformities in hand lay-up fabric laminates such as resin surface layers and unequal layer thickness, the flexural and extensional modulus of such laminated composites are different. By the way, since the bending and in-plane effects are together affect to the nonlinear behavior of a composite laminate, it should give more reliable results when using different flexural and extensional modulus in the analysis. In this study, the results of approximate analysis, ANSYS finite element analysis and experimental study are obtained and compared for a fully-clamped laminated composite plate subjected to a uniform pressure load. The material properties used in the analysis are determined tension and three-point bending tests.

scholarly journals SOUND TRANSMISSION LOSS ACROSS A FINITE CLAMPED DOUBLE-LAMINATED COMPOSITE PLATE WITH POROELASTIC MATERIAL

2020 ◽  
Vol 57 (6A) ◽  
pp. 150
Author(s):  
Thanh Ngoc Pham
Keyword(s):  
Composite Plate ◽  
Transmission Loss ◽  
Sound Transmission ◽  
Laminated Composite ◽  
Double Series ◽  
Composite Plates ◽  
Thin Plates ◽  
Sound Transmission Loss ◽  
Laminated Composite Plate ◽  
Poroelastic Material

A theoretical study of sound transmission loss across a clamped double-laminated composite plate filled with poroelastic material is formulated. Biot’s theory is employed to describe wave propagation in elastic porous media. The two face composite plates are modeled as classical thin plates. By using the modal superposition theory, a double series solution for the sound transmission loss of the structure is obtained with the help of the Galerkin method. The analytical model is validated against previous experimental results of a single sound wave under normal incidence. The numerical results suggest that the density of poroelastic material, the type of composite materials and the composite plies arrangement have significant effects on the sound transmission loss of considered structure.

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