Anisotropic Constraint Effects on Interactive Damage Progression of General Lay-up Composites

1998 ◽  
Vol 65 (4) ◽  
pp. 970-979 ◽  
Author(s):  
J. Fan ◽  
J. Zhang
Keyword(s):  
Plate Theory ◽  
Matrix Cracking ◽  
Layer Model ◽  
First Order ◽  
Stiffness Reduction ◽  
Damage Progression ◽  
Unique Approach ◽  
Constraint Effects ◽  
Intractable Problem ◽  
Progressive Matrix

In this paper, a five-layer model is proposed to analyze the anisotropic constraint effects on interactive damage progression. Incorporating this model with the general theory of overall moduli of a cracked body, the effective damage factors proposed by Fan and Zhang in 1993 have been extended as quantitative measures for characterizing the anisotropic constraint effects on damage-induced stiffness reduction of general lay-up composites. By applying the first-order shear deformation plate theory to each sublayer these factors are determined and applied for investigating progressive matrix cracking-delamination interaction. Results show that by this rather unique approach, the intractable problem of anisotropic constraint effects of general lay-up composites on interactive damage progression can be handled in a systematic manner.

First Order Analysis of Stiffness Reduction Due to Matrix Cracking

1992 ◽  
Vol 26 (7) ◽  
pp. 1009-1030 ◽  
Author(s):  
Peter Gudmundson ◽  
Sören Östlund
Keyword(s):  
Matrix Cracking ◽  
Order Analysis ◽  
First Order ◽  
Stiffness Reduction

A progressive analysis of matrix cracking-induced delamination in composite laminates using an advanced phantom node method

2016 ◽  
Vol 51 (20) ◽  
pp. 2933-2947 ◽  
Author(s):  
Johannes Reiner ◽  
Martin Veidt ◽  
Matthew Dargusch ◽  
Lutz Gross
Keyword(s):  
Composite Laminates ◽  
Crack Density ◽  
Matrix Crack ◽  
Matrix Cracking ◽  
Geometrically Nonlinear Analysis ◽  
Stiffness Reduction ◽  
Crack Tips ◽  
New Formulation ◽  
Phantom Node Method ◽  
Progressive Matrix

Matrix cracking-induced delamination in composite laminates is qualitatively and quantitatively investigated in a finite element framework. The phantom node method is extended to incorporate breakable interfaces at transverse matrix crack tips. New user-defined element types in Abaqus improve the numerical stability in a geometrically nonlinear analysis. The new formulation allows for accurate prediction of matrix crack density and stiffness reduction in a number of composite laminates. Furthermore, the advanced phantom node method is able to simulate progressive matrix cracking-induced delamination with good accuracy.

Delamination of Laminate Plates

2014 ◽  
Vol 969 ◽  
pp. 97-100 ◽  
Author(s):  
Eva Kormaníková
Keyword(s):  
Finite Element Analysis ◽  
Mixed Mode ◽  
Plate Theory ◽  
Laminate Plate ◽  
Element Analysis ◽  
Interface Elements ◽  
First Order ◽  
Plate Elements ◽  
Interface Modeling ◽  
Shear Deformable

The paper deals with numerical modeling of delamination of laminate plate consists of unidirectional fiber reinforced layers. The methodology adopts the first-order shear laminate plate theory and fracture and contact mechanics. There are described sublaminate modeling and delamination modeling by the help of finite element analysis. With the interface modeling there is calculated the energy release rate along the lamination front. Numerical results are given for mixed mode delamination problems by implementing the method in a 2D finite analysis, which utilizes shear deformable plate elements and interface elements. Numerical example is done by the commercial ANSYS code.

FLUTTER SUPPRESSION OF AN ELASTICALLY SUPPORTED PLATE WITH ELECTRO-RHEOLOGICAL FLUID CORE UNDER YAWED SUPERSONIC FLOWS

2013 ◽  
Vol 13 (01) ◽  
pp. 1250073 ◽  
Author(s):  
SEYYED M. HASHEMINEJAD ◽  
M. NEZAMI ◽  
M. E. ARYAEE PANAH
Keyword(s):  
Elastic Foundation ◽  
Sandwich Plate ◽  
Sliding Mode ◽  
Plate Theory ◽  
System Response ◽  
First Order ◽  
Fluid Core ◽  
Pasternak Elastic Foundation ◽  
Elastically Supported ◽  
Er Fluid

This paper investigates the active control of the supersonic flutter motion of an elastically supported rectangular sandwich plate, which has a tunable electrorheological (ER) fluid core and rests on a Winkler–Pasternak elastic foundation, subjected to an arbitrary flow of various yaw angles. The classical thin plate theory is adopted. The ER fluid core is modeled as a first order Kelvin–Voigt material, and the quasi-steady first order supersonic piston theory is employed for the aerodynamic loading. The generalized Fourier expansions in conjunction with Galerkin method are employed to formulate the governing equations in the state-space domain. The critical dynamic pressures at which unstable panel oscillations occur are obtained for a square sandwich plate, with or without an interacting soft/stiff elastic foundation, for selected applied electric field strengths and flow yaw angles. The Runge–Kutta method is then used to calculate the open-loop aeroelastic response of the system in various basic loading configurations. Subsequently, a sliding mode control (SMC) synthesis is set up to actively suppress the closed loop system response in yawed supersonic flight conditions with imposed excitations. The results demonstrate the performance, effectiveness, and insensitivity with respect to the spillover of the proposed SMC-based control system.

Size-Dependent Geometrically Nonlinear Forced Vibration Analysis of Functionally Graded First-Order Shear Deformable Microplates

2016 ◽  
Vol 32 (5) ◽  
pp. 539-554 ◽  
Author(s):  
R. Ansari ◽  
R. Gholami ◽  
A. Shahabodini
Keyword(s):  
Size Effect ◽  
Nonlinear Equations ◽  
Forced Vibration ◽  
Plate Theory ◽  
Couple Stress Theory ◽  
Continuation Method ◽  
Functionally Graded ◽  
Geometrical Parameters ◽  
Governing Equations ◽  
First Order

AbstractIn this paper, a non-classical plate model capturing the size effect is developed to study the forced vibration of functionally graded (FG) microplates subjected to a harmonic excitation transverse force. To this, the modified couple stress theory (MCST) is incorporated into the first-order shear deformation plate theory (FSDPT) to account for the size effect through one length scale parameter, only. Strong form of nonlinear governing equations and associated boundary conditions are obtained using Hamilton's principle. The solution process is implemented on two domains. The generalized differential quadrature (GDQ) method is first employed to discretize the governing equations on the space domain. A Galerkin-based scheme is then applied to extract a reduced set of the nonlinear equations of Duffing-type. On the second domain, through a time differentiation matrix operator, the set of ordinary differential equations are transformed into the discrete form on time domain. Eventually, a system of the parameterized nonlinear equations is acquired and solved via the pseudo-arc length continuation method. The frequency response curve of the microplate is sketched and the effects of various material and geometrical parameters on it are evaluated.

Comparison of First-Order Shear and Plane Strain Assumptions in Warpage Prediction of Simply Supported Printed Wiring Boards

2000 ◽  
Vol 123 (1) ◽  
pp. 1-5 ◽  
Author(s):  
Yarom Polsky ◽  
I. Charles Ume
Keyword(s):  
Plane Strain ◽  
Plate Theory ◽  
Shear Deformation Theory ◽  
Transverse Load ◽  
Transverse Shear Strain ◽  
Printed Wiring Board ◽  
Simply Supported ◽  
First Order ◽  
Support Conditions ◽  
Wiring Board

The influence of transverse shear strain in the lamination theory modeling of Printed Wiring Board (PWB) deflection due to support conditions was examined. The in-plane mechanical properties of the core materials of a commercial PWB were measured as a function of temperature. Classical laminated plate theory and first-order shear deformation theory solutions for the out-of-plane deflection of a bare board configuration with two opposite edges simply supported and the remaining edges free were obtained. The weight of the board was approximated as a distributed transverse load. The effect of material property decrease with temperature and FR-4 layer thickness were examined to compare first-order shear and plane strain assumptions for the predicted warpage.

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