Deterministic and probabilistic buckling response of fiber–metal laminate panels under uniaxial compression

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Costas D. Kalfountzos ◽  
George S.E. Bikakis ◽  
Efstathios E. Theotokoglou
Keyword(s):  
Glass Fiber ◽  
Buckling Load ◽  
Sensitivity Analyses ◽  
Logarithmic Scale ◽  
Content Type ◽  
Buckling Behavior ◽  
Fiber Metal Laminate ◽  
Curvature Parameter ◽  
Buckling Coefficient ◽  
Fiber Metal

Purpose The purpose of this paper is to study the deterministic elastic buckling behavior of cylindrical fiber–metal laminate panels subjected to uniaxial compressive loading and the investigation of GLAss fiber-REinforced aluminum laminate (GLARE) panels using probabilistic finite element method (FEM) analysis. Design/methodology/approach The FEM in combination with the eigenvalue buckling analysis is used for the construction of buckling coefficient–curvature parameter diagrams of seven fiber–metal laminate grades, three glass-fiber composites and monolithic 2024-T3 aluminum. The influences of uncertainties concerning material properties and laminate dimensions on the buckling load are studied with sensitivity analyses. Findings It is found that aluminum has a stronger impact on the buckling behavior of the fiber–metal laminate panels than their constituent uni-directional or woven composites. For the classical simply supported boundary conditions, it is found that there is an approximately linear relation between the buckling coefficient and the curvature parameter when the diagrams are plotted in double logarithmic scale. The probabilistic calculations demonstrate that there is a considerable probability to overestimate the buckling load of GLARE panels with deterministic calculations. Originality/value In this study, the deterministic and probabilistic buckling response of fiber metal laminate panels is investigated. It is shown that realistic structural uncertainties could substantially affect the buckling strength of aerospace components.

Buckling of fiber metal laminated plates – numerical and experimental studies

2020 ◽  
Vol 92 (3) ◽  
pp. 472-481
Author(s):  
Elluri Venkata Prasad ◽  
Shishir Kumar Sahu
Keyword(s):  
Aspect Ratio ◽  
Boundary Conditions ◽  
Thickness Ratio ◽  
Buckling Load ◽  
Element Formulation ◽  
Buckling Loads ◽  
Content Type ◽  
Buckling Behavior ◽  
Fiber Metal ◽  
Ply Orientation

Purpose The purpose of this study is to study the buckling behavior of new aircraft material, i.e. glass fiber metal laminated (GFML) plates. Design/methodology/approach The first-order Reissner–Mindlin theory is used in the present finite element formulation to determine the buckling loads of GFML plates. A program is developed in MATLAB for analyzing the effect of different parameters on buckling loads GFML plates. A set of experiments was performed to determine critical buckling loads of GFML plates using universal testing machine INSTRON 8862 and compared with predictions using the numerical model. Findings The effects of various parameters such as aspect ratio, side to thickness ratio, ply orientation and boundary conditions on buckling loads of GFMLs are examined. With the increase of aspect ratio, the reduction in buckling load is observed, while the increase inside to thickness ratio decreases the buckling load of GFML plates. There is a slight variation in buckling load with the increase of ply orientation. The buckling load is significantly influenced by boundary conditions because of restraint at the edges. Practical implications These types of materials are used in lightweight structures such as aircraft, aerospace and military vehicles. The results reported in the present study can be used as design guidelines while designing fiber metal laminated (FML) plated structures. Originality/value For the first time, the authors have studied the buckling behavior of bidirectional woven FML plates using both numerical and experimental techniques.

scholarly journals Influence of drilling parameters on thrust force and burr on fiber metal laminate (Al 2024-T3/glass fiber reinforced epoxy)

Procedia CIRP ◽  
2021 ◽  
Vol 101 ◽  
pp. 338-341
Author(s):  
Eduardo Pires Bonhin ◽  
Sarah David-Müzel ◽  
Erick Siqueira Guidi ◽  
Edson Cocchieri Botelho ◽  
Marcos Valério Ribeiro
Keyword(s):  
Glass Fiber ◽  
Thrust Force ◽  
Fiber Reinforced ◽  
Glass Fiber Reinforced ◽  
Drilling Parameters ◽  
Fiber Metal Laminate ◽  
Fiber Metal ◽  
Al 2024

Property Evaluation of FML (Glare)

2021 ◽  
Vol 1020 ◽  
pp. 212-216
Author(s):  
Sunil Bhat ◽  
H. Adarsha ◽  
V. Ravinarayan ◽  
V.P. Kaushik
Keyword(s):  
Mechanical Properties ◽  
Residual Stress ◽  
Aluminum Alloy ◽  
Chemical Composition ◽  
Glass Fiber ◽  
Adhesively Bonded ◽  
Property Evaluation ◽  
Fiber Metal Laminate ◽  
Fabrication Procedure ◽  
Fiber Metal

Fiber metal laminate (Glare) made of 2014-T6 aerospace aluminum alloy sheets adhesively bonded with E-glass fiber based composite prepregs is investigated in the paper. The fabrication procedure of the laminate is explained. Chemical composition, macrostructure and residual stress of aluminum alloy are obtained. Mechanical properties of the laminate viz. tensile, flexural and shear strengths are measured.

Drawing potential of fiber metal laminates in hydromechanical forming: A numerical and experimental study

2018 ◽  
Vol 22 (5) ◽  
pp. 1386-1403 ◽  
Author(s):  
Alireza Saadatfard ◽  
Mahdi Gerdooei ◽  
Abdolhossein Jalali Aghchai
Keyword(s):  
Glass Fiber ◽  
Numerical Study ◽  
Fluid Pressure ◽  
Chamber Pressure ◽  
Drawing Ratio ◽  
Fiber Reinforced ◽  
Fiber Metal Laminates ◽  
Glass Fiber Reinforced ◽  
Fiber Metal Laminate ◽  
Fiber Metal

It is known that fiber metal laminates as one of hybrid materials with thin metal sheets and fiber/resin layers have limited formability in conventional forming methods. This paper presents an experimental and numerical study for drawability of glass fiber-reinforced aluminum laminates under hydromechanical drawing technique. Fiber metal laminates comprised of a layer of woven glass fiber-reinforced prepreg, sandwiched between two layers of aluminum alloy. In order to produce fiber metal laminates, the laminates were subjected to a sufficient squeezing pressure under a controlled heating time and temperature by using a hydraulic hot press. A hydromechanical tooling equipped with blank-holder force and fluid pressure control system was used to form the initial circular fiber metal laminate blank. Finally, the effect of parameters such as pre-bulging pressure, final chamber pressure, and drawing ratio on process variables was evaluated. Also, the characteristic curve of hydromechanical drawing of fiber metal laminate i.e. chamber pressure in terms of drawing ratio was achieved by means of experimental tests and numerical simulations. The results showed that the maximum drawing ratio of defect-free fiber metal laminates, namely without any tearing, wrinkling, and delamination was obtained at pre-bulging and chamber pressure of 35 and 80 bar, respectively.

scholarly journals Buckling of simply supported GLARE cylindrical panels subjected to uniform compression

2021 ◽  
Vol 349 ◽  
pp. 01004
Author(s):  
Costas Kalfountzos ◽  
George Bikakis ◽  
Efstathios Theotokoglou
Keyword(s):  
Logarithmic Scale ◽  
The Finite Element Method ◽  
Uniform Compression ◽  
Simply Supported ◽  
Glass Fiber Composites ◽  
Composite Layers ◽  
Cylindrical Panels ◽  
Curvature Parameter ◽  
Analytical Formulas ◽  
Buckling Coefficient

In this article, the elastic buckling behaviour of cylindrical GLARE (GLAss REinforced) panels with classically simply supported boundary conditions under uniaxial compression is investigated using the finite element method (FEM) and eigenvalue buckling analysis. The buckling coefficient-curvature parameter diagrams of five GLARE grades are obtained and studied along with the diagrams of two glass-fiber composites and monolithic 2024-T3 aluminum, using validated FEM models. It is found that aluminium has a stronger impact on the buckling behaviour of the GLARE panels than the composite layers. From the constructed buckling coefficient - curvature parameter diagrams in double logarithmic scale it is found that there is an approximately linear relation between the buckling coefficient and the curvature parameter of the panels. Based on this finding, appropriate regressions are implemented in order to derive approximate analytical formulas of the buckling coefficient as a function of the curvature parameter for the considered materials.

Elastic Instability of Rectangular Sandwich Panel of Orthotropic Core With Different Face Thicknesses and Materials

1960 ◽  
Vol 27 (3) ◽  
pp. 474-480 ◽  
Author(s):  
C. C. Chang ◽  
I. K. Ebcioglu
Keyword(s):  
Sandwich Panel ◽  
Buckling Load ◽  
Shear Instability ◽  
Elastic Instability ◽  
Single Family ◽  
Buckling Behavior ◽  
Family Of Curves ◽  
Buckling Coefficient ◽  
Temperature Levels ◽  
Moduli Of Elasticity

This paper treats the instability of rectangular sandwich panels with nonisotropic cores and faces of different materials or thicknesses. The simply supported panel is loaded with a uniform edge compression. The solution is expressed in terms of a major buckling coefficient, given as the ratio of the critical lateral buckling load to the critical cylindrical buckling load, which is a function of several nondimensional parameters. A single family of curves shows the buckling behavior for all parameters. The effect of a moderate temperature differential between the two faces can be approximately considered by modifying their moduli of elasticity in accordance with their temperature levels. Besides the regular panel instability, a zone of core shear instability is determined and discussed in detail. Numerical examples are presented to illustrate the application of the analysis.

scholarly journals Experimental Testing and Analytical Modeling of Asymmetric End-Notched Flexure Tests on Glass-Fiber Metal Laminates

Metals ◽  
2019 ◽  
Vol 10 (1) ◽  
pp. 56 ◽  
Author(s):  
Konrad Dadej ◽  
Jarosław Bieniaś ◽  
Paolo Sebastiano Valvo
Keyword(s):  
Glass Fiber ◽  
Experimental Testing ◽  
Metal Composite ◽  
Interface Model ◽  
Experimental Campaign ◽  
Composite Interface ◽  
Theoretical Predictions ◽  
Elastic Interface ◽  
Fiber Metal ◽  
Rigid Interface

An experimental campaign on glass-fiber/aluminum laminated specimens was conducted to assess the interlaminar fracture toughness of the metal/composite interface. Asymmetric end-notched flexure tests were conducted on specimens with different fiber orientation angles. The tests were also modeled by using two different analytical solutions: a rigid interface model and an elastic interface model. Experimental results and theoretical predictions for the specimen compliance and energy release rate are compared and discussed.

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