scholarly journals Buckling Analysis of Laminated Composite Panel with Elliptical Cutout Subject to Axial Compression

2012 ◽  
Vol 2012 ◽  
pp. 1-10 ◽  
Author(s):  
Hamidreza Allahbakhsh ◽  
Ali Dadrasi
Keyword(s):  
Load Capacity ◽  
Laminated Composite ◽  
Cylindrical Panel ◽  
Reduction Factor ◽  
Buckling Analysis ◽  
Buckling Load ◽  
Least Square ◽  
Composite Panel ◽  
Finite Element Software ◽  
Composite Cylindrical Panel

A buckling analysis has been carried out to investigate the response of laminated composite cylindrical panel with an elliptical cutout subject to axial loading. The numerical analysis was performed using the Abaqus finite-element software. The effect of the location and size of the cutout and also the composite ply angle on the buckling load of laminated composite cylindrical panel is investigated. Finally, simple equations, in the form of a buckling load reduction factor, were presented by using the least square regression method. The results give useful information into designing a laminated composite cylindrical panel, which can be used to improve the load capacity of cylindrical panels.

scholarly journals Post-Buckling Behaviour of laminated Cylindrical Panels with/without Cut-Outs

2019 ◽  
Vol 8 (3) ◽  
pp. 8026-8030
Keyword(s):  
Compressive Load ◽  
Laminated Composite ◽  
Cylindrical Panel ◽  
Buckling Load ◽  
Equilibrium Path ◽  
Cylindrical Panels ◽  
Post Buckling ◽  
The Impact ◽  
Generalized Finite Element ◽  
Composite Cylindrical Panel

Buckling and post-buckling analysis of isotropic and laminated composite cylindrical plates/panels under compressive load has been done by equilibrium path approach (arc-length technique). The impact of cut outs on buckling and post-buckling load of an isotropic and laminated composite cylindrical plates/panels has been assessed by utilizing summed up generalized finite element programming ANSYS. In post-buckling Eigen mode imperfection shape is picked for creating geometric undulations on cylindrical panels with/without circular cut-outs. The impact of the area and size of the cut out and furthermore the composite utilize point on the buckling load of laminated composite cylindrical panel is explored with simply supported boundary conditions. The post-buckling consequences of laminated cylindrical panels have been validated with existing appropriate writing (18) and are additionally stretched out for analysis of sheets/plates with cutouts. It has been seen that the as the curvature of the panel increases load bearing capacity is increasing irrespective of the material and with/without cut out.

Structural Optimization of Laminated Composite Plates for Maximum Buckling Load Capacity Using Genetic Algorithm

2007 ◽  
Vol 348-349 ◽  
pp. 725-728 ◽  
Author(s):  
Omer Soykasap ◽  
Şükrü Karakaya
Keyword(s):  
Genetic Algorithm ◽  
Structural Optimization ◽  
Load Capacity ◽  
Laminated Composite ◽  
Global Solutions ◽  
Composite Plates ◽  
Buckling Load ◽  
Laminated Composite Plates ◽  
Static Loads ◽  
Aspect Ratios

In this study, the structural optimization of laminated composite plates for maximum buckling load capacity is performed by using genetic algorithm. The composite plate under consideration is a 64-ply laminate made of graphite/epoxy, is simply supported on four sides, and subject to in-plane compressive static loads. The critical buckling loads are determined for several load cases and different plate aspect ratios using 2-ply stacks of 02, ±45, 902. The problem has multiple global solutions, the results of which are compared with previously published results.

Numerical and Experimental Buckling and Post - Buckling Analysis of Composite Cylindrical Panel with Delamination

2013 ◽  
Vol 477-478 ◽  
pp. 39-42
Author(s):  
Marek Barski ◽  
Aleksander Muc ◽  
Przemysław Pastuszak ◽  
Agnieszka Bondyra
Keyword(s):  
Numerical Analysis ◽  
Experimental Verification ◽  
Experimental Analysis ◽  
Cylindrical Panel ◽  
Composite Panel ◽  
Fem Method ◽  
Buckling Behavior ◽  
Post Buckling ◽  
The Stability ◽  
Composite Cylindrical Panel

The present work is devoted to the analysis of a buckling behavior of a cylindrical composite panel. The considered structure is subjected to the uniform axial compression. The wall of the panel consists of the 8 layers. In addition, in the geometrical center of the structure there is a square delamination located between the fourth and the fifth layer. The main goal is to determine the buckling and post - buckling behavior as well as the influence of the delamination on the stability of the structure. The nonlinear numerical analysis is carried out with aid of the FEM method. The experimental verification is also performed. The results obtained from numerical and experimental analysis show very similar behavior of the structure.

Buckling Analysis of Ring-Stiffened Laminated Composite Cylindrical Shells by Fourier-Expansion Based Differential Quadrature Method

2012 ◽  
Vol 225 ◽  
pp. 207-212 ◽  
Author(s):  
Saeed Barani ◽  
Davood Poorveis ◽  
Shapoor Moradi
Keyword(s):  
Fourier Expansion ◽  
Differential Quadrature Method ◽  
Cylindrical Shells ◽  
Laminated Composite ◽  
Longitudinal Direction ◽  
Buckling Analysis ◽  
Differential Quadrature ◽  
Quadrature Method ◽  
First Order ◽  
Finite Element Software

This article focuses on the application of the Fourier-expansion based differential quadrature method (FDQM) for the buckling analysis of ring-stiffened composite laminated cylindrical shells. Displacements and rotations are expressed in terms of Fourier series expansions in longitudinal direction and their first order derivatives are approximated with FDQM in circumferential direction. The 'smeared stiffener' approach is adopted for the stiffeners modeling. Two FORTRAN programs prepared for linear and nonlinear analysis and results were compared by ABAQUS finite element software. Buckling loads of stiffened and unstiffened shells considering the effects of changes in shell and stiffener geometric and material properties and also shell lay-ups are investigated.

scholarly journals Experimental and Numerical Buckling Analysis of Delaminated Hybrid Composite Beam Structures

2010 ◽  
Vol 24-25 ◽  
pp. 393-400 ◽  
Author(s):  
M.M. Nasr Esfahani ◽  
H. Ghasemnejad ◽  
P.E. Barrington
Keyword(s):  
Hybrid Composite ◽  
Laminated Composite ◽  
Composite Beams ◽  
Buckling Load ◽  
Buckling Mode ◽  
Buckling Modes ◽  
Critical Buckling Load ◽  
Finite Element Software ◽  
Numerical Studies ◽  
Laminated Composite Beams

In this paper the effect of delamination position on the critical buckling load and buckling mode of hybrid composite beams is investigated. Experimental and numerical studies are carried out to determine the buckling load of delaminated composite beams. The laminated composite beams with various laminate designs of [G90]6, [C90]8, [C0/G0]4 and [C90/G90]4 were manufactured and tested to find the critical buckling load. Three different defect positions were placed through the thickness to find three main buckling modes. It was found that delamination position and lay-up can affect the buckling mode and also the critical buckling load. By approaching the delamination position to the outer surface of the specimen the buckling load decreases. The buckling process of hybrid and non-hybrid composite beams was also simulated by finite element software ANSYS and the critical buckling loads were verified with the relevant experimental results.

Stability and Failure Study of Suddenly Loaded Laminated Composite Cylindrical Panel

2019 ◽  
Vol 11 (10) ◽  
pp. 1950093 ◽  
Author(s):  
Vasanth Keshav ◽  
Shuvendu Narayan Patel ◽  
Rajesh Kumar
Keyword(s):  
Nonlinear Dynamic ◽  
Compressive Load ◽  
Laminated Composite ◽  
Cylindrical Panel ◽  
Dynamic Buckling ◽  
Radius Of Curvature ◽  
Curved Panel ◽  
Convergence Study ◽  
Curved Panels ◽  
Composite Cylindrical Panel

In this paper, nonlinear dynamic buckling of laminated composite cylindrical panels subjected to in-plane impulsive compressive load is studied along with the failure analysis. Balanced and symmetric angle-ply laminated composite curved panels are considered. Convergence study is performed, and results are validated with the results from the existing literature, and then the dynamic buckling loads are calculated. The failure index of laminated composite curved panel is also calculated to check the precedence of first ply failure load over nonlinear dynamic buckling load. The effect of aspect ratio, loading function, and radius of curvature is studied. The analysis is carried out using finite element method. It is observed that the first ply failure for balanced and symmetric angle-ply laminated composite curved panels occurs after the panel has buckled due to dynamic impulse loads.

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