Mechanical properties of a novel fiber–metal laminate based on a polypropylene composite

2009 ◽  
Vol 41 (7) ◽  
pp. 828-838 ◽  
Author(s):  
J.G. Carrillo ◽  
W.J. Cantwell
Keyword(s):  
Mechanical Properties ◽  
Polypropylene Composite ◽  
Fiber Metal Laminate ◽  
Fiber Metal

scholarly journals Research Progress on Interlaminar Failure Behavior of Fiber Metal Laminates

2020 ◽  
Vol 2020 ◽  
pp. 1-20
Author(s):  
Yizhe Chen ◽  
Yichun Wang ◽  
Hui Wang
Keyword(s):  
Mechanical Properties ◽  
Failure Modes ◽  
Control Method ◽  
Research Progress ◽  
Failure Behavior ◽  
Control Methods ◽  
Fiber Metal Laminate ◽  
Fiber Metal ◽  
Structural Parts ◽  
New Research

Fiber metal laminate (FML) is a kind of lightweight material with excellent mechanical properties combining advantages of metal laminates and fiber reinforced composites. It has been widely used in the aerospace and transportation fields and is especially used as structural material such as aircraft skins, wings, and tails. However, under complex service conditions, interlaminar failure in FMLs greatly reduced mechanical properties of the material, even leading to serious economic and safety disasters. The failure and destruction of important structural parts of aircraft and other manned transportation vehicles are extremely unsafe for people. Therefore, it is of great significance to summarize the interlaminar failure behavior of FMLs and find ways to avoid these defects. This review paper is a collection of various researches done by many groups, which systematically discuss the interlaminar failure behaviors and their control methods of FMLs. The application status of several common FMLs in aircraft structures was given. The common interlaminar failure modes of FMLs and the testing and evaluation methods of interlaminar properties were stated. The failure mechanisms and the corresponding control methods were analyzed. Finally, the future developments of FMLs were also discussed by the authors. Through this review article, readers can obtain new research progress about the control method, the mechanism and future development on the failure behavior of FMLs in a more efficient way.

A new constitutive bulk material model to predict the uniaxial tensile nonlinear behavior of fiber metal laminates

2017 ◽  
Vol 53 (1) ◽  
pp. 26-35 ◽  
Author(s):  
Gholam Hossein Majzoobi ◽  
Mohammad Kashfi ◽  
Nicola Bonora ◽  
Gianluca Iannitti ◽  
Andrew Ruggiero ◽  
...  
Keyword(s):  
Mechanical Properties ◽  
Material Model ◽  
Tensile Tests ◽  
Uniaxial Tensile ◽  
Plastic Behavior ◽  
Processing Unit ◽  
Fiber Metal Laminates ◽  
Constitutive Material Model ◽  
Fiber Metal Laminate ◽  
Fiber Metal

In this investigation, a constitutive material model to predict elastic–plastic behavior of fiber metal laminates is introduced. The constants of the model can be obtained from the geometry and mechanical properties of the sublayers. This model can significantly reduce the computational efforts and central processing unit time by ignoring the contact between the fiber metal laminate layers. The ability of the model to predict plastic behavior of material makes it applicable to different metallic layers. Mechanical properties of each sublayer are obtained from tensile tests. The results of finite element analysis of the fiber metal laminate specimens using layered and bulk models revealed that the influence of glue was ignorable. The proposed model was validated by performing tensile tests on fiber metal laminate grades I and II and also on low and high metal volume fraction.

scholarly journals Improving the Mechanical Properties of Fiber Metal Laminate Composite Used in Aircraft Wing

2019 ◽  
Vol 22 (1) ◽  
pp. 9-13
Author(s):  
Ahmed Mohammad Kadum ◽  
Ali A. Al-katawy ◽  
Saad T. Faris ◽  
Ehklas E. Kader
Keyword(s):  
Mechanical Properties ◽  
Laminate Composite ◽  
Adhesion Force ◽  
Glass Fibers ◽  
Aircraft Wing ◽  
Fiber Metal Laminates ◽  
Jute Fibers ◽  
Fiber Metal Laminate ◽  
Fiber Metal ◽  
Aluminum Alloy 2024

The purpose of this study is to reduce weight and improve the mechanical properties of aircraft wing using Hybrid materials known as fiber metal laminates (FMLs). In this study, seven layers were used to produce the FMLs that consist of aluminum alloy2024-T3 reinforced by carbon and glass fibers bonded with blend of epoxy-resole. The Carbon Glass Reinforced Aluminum Laminates (CAGRALLs) was used as FMLs. The results showed that The CAGRALLs gave good mechanical properties because of increasing in tensile strength, elongation at fracture and impact toughness except flexural strength by comparing with other FMLs using commercial epoxy. The increasing in layers led to weaken adhesion force between layers of FMLs caused decreasing almost mechanical properties. The FMLs has good mechanical properties by using carbon and glass fibers by comparing with carbon and jute fibers. The CAGRALLs have higher numbers of cycles at failure under cyclic loadings than Aramid Reinforced Aluminum Laminates (ARALLs). The CAGRALLs have lower density by comparing with aluminum alloy 2024-T3 that used in manufacturing of aircraft wing.

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.

scholarly journals Experimental Test on Glare Composite of an Aircraft Structure Under Tensile Strength Failure

2019 ◽  
Vol 9 (2) ◽  
pp. 674-677
Keyword(s):  
Mechanical Properties ◽  
Experimental Test ◽  
Glass Fibers ◽  
Testing Machine ◽  
Strain Curve ◽  
Aircraft Structure ◽  
Loading Test ◽  
Strength Failure ◽  
Fiber Metal Laminate ◽  
Fiber Metal

A Glass Aluminum fiber metal laminate GLARE is a set of materials manufactured by strong bonding glass/epoxy layers within the metal layers. The combined set of materials will be providing the better mechanical properties and weight reduction for an aircraft structure. The fiber metal laminate model was fabricated as per ASTM standards 200×30×5mm and then the experimental test under tensile loading test was conducted by using universal testing machine UTM as observed the stress-strain curve as the failure strength of GLARE reaching point and finally obtained results. Also to determine the mechanical properties and material characteristics of the unidirectional loading on E-glass fibers used to assemble GLARE for an aircraft structure

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