The effect of an elastomer interlayer thickness variation on the mechanical properties of Fiber-Metal-Laminates

2019 ◽  
Vol 219 ◽  
pp. 90-96 ◽  
Author(s):  
Matthias M. Stoll ◽  
Vincent Sessner ◽  
Manuel Kramar ◽  
Jakob Technau ◽  
Kay A. Weidenmann
Keyword(s):  
Mechanical Properties ◽  
Thickness Variation ◽  
Interlayer Thickness ◽  
Fiber Metal Laminates ◽  
Fiber Metal

Residual Stresses in Intrinsic UD-CFRP-Steel-Laminates - Experimental Determination, Identification of Sources, Effects and Modification Approaches

2015 ◽  
Vol 825-826 ◽  
pp. 369-376 ◽  
Author(s):  
Robert Prussak ◽  
Daniel Stefaniak ◽  
Christian Hühne ◽  
Michael Sinapius
Keyword(s):  
Mechanical Properties ◽  
Residual Stress ◽  
Tensile Strength ◽  
Epoxy Composite ◽  
Thermal Residual Stress ◽  
Fiber Metal Laminates ◽  
Fiber Metal ◽  
Impact Energies ◽  
The Impact ◽  
Specific Impact

This paper focuses on the reduction of process-related thermal residual stress in fiber metal laminates and its impact on the mechanical properties. Different modifications during fabrication of co-cure bonded steel/carbon epoxy composite hybrid structures were investigated. Specific examinations are conducted on UD-CFRP-Steel specimens, modifying temperature, pressure or using a thermal expansion clamp during manufacturing. The impact of these parameters is then measured on the deflection of asymmetrical specimens or due yield-strength measurements of symmetrical specimens. The tensile strength is recorded to investigate the effect of thermal residual stress on the mechanical properties. Impact tests are performed to determine the influence on resulting damage areas at specific impact energies. The experiments revealed that the investigated modifications during processing of UD-CFRP-Steel specimens can significantly lower the thermal residual stress and thereby improve the tensile strength.

A review of mechanical drilling on fiber metal laminates

2020 ◽  
pp. 002199832095774
Author(s):  
Eduardo Pires Bonhin ◽  
Sarah David-Müzel ◽  
Manoel Cléber de Sampaio Alves ◽  
Edson Cocchieri Botelho ◽  
Marcos Valério Ribeiro
Keyword(s):  
Mechanical Properties ◽  
Cutting Parameters ◽  
Burr Formation ◽  
Drilling Process ◽  
Machining Parameters ◽  
Specific Mass ◽  
Fiber Metal Laminates ◽  
Dimensional Error ◽  
Main Method ◽  
Fiber Metal

The use of fiber metal laminates (FML) in aeronautics components has been increased in the last years, mainly due to the gain in mechanical properties combined with low specific mass. However, in the assembly of these materials on the structures to which they will be attached, mechanical screwing is still the main method used, which requires the performance of drilling processes. Something it is very complicated for these materials and can cause damage that compromises the performance. Therefore, this work aims to approach and summarize the evolution of the mechanical drilling process on FML developed in the last years. By the work, the main problems that occur during the drilling of these materials are punctually approached, such as delamination, burr formation, dimensional error, poor roughness, and tool wear. In addition, it is presented how these problems are affected by the machining parameters (cutting parameters, geometry, material/coating tool, and cutting environment), as well as suggestions for minimizing process problems. Thus, the article intends to provide as much information as possible available in the literature, seeking to help researchers gain a comprehensive view of the mechanical drilling of fiber metal laminates.

scholarly journals The Mechanical Properties of Fiber Metal Laminates Based on 3D Printed Composites

Materials ◽  
2020 ◽  
Vol 13 (22) ◽  
pp. 5264
Author(s):  
Bharat Yelamanchi ◽  
Eric MacDonald ◽  
Nancy G. Gonzalez-Canche ◽  
Jose G. Carrillo ◽  
Pedro Cortes
Keyword(s):  
Mechanical Properties ◽  
3D Printing ◽  
High Velocity ◽  
Mechanical Performance ◽  
High Velocity Impact ◽  
Low Velocity ◽  
Fiber Metal Laminates ◽  
Velocity Impact ◽  
3D Printed ◽  
Fiber Metal

The production and mechanical properties of fiber metal laminates (FMLs) based on 3D printed composites have been investigated in this study. FMLs are structures constituting an alternating arrangement of metal and composite materials that are used in the aerospace sector due to their unique mechanical performance. 3D printing technology in FMLs could allow the production of structures with customized configuration and performance. A series of continuous carbon fiber reinforced composites were printed on a Markforged system and placed between layers of aluminum alloy to manufacture a novel breed of FMLs in this study. These laminates were subjected to tensile, low velocity and high velocity impact tests. The results show that the tensile strength of the FMLs falls between the strength of their constituent materials, while the low and high velocity impact performance of the FMLs is superior to those observed for the plain aluminum and the composite material. This mechanism is related to the energy absorption process displayed by the plastic deformation, and interfacial delamination within the laminates. The present work expects to provide an initial research platform for considering 3D printing in the manufacturing process of hybrid laminates.

The Influence of Loading Rate on the Interfacial Fracture Toughness of Carbon Fiber-Metal Laminates Based on Magnesium Alloy

2011 ◽  
Vol 328-330 ◽  
pp. 1373-1376 ◽  
Author(s):  
Gong Zhi Zhu ◽  
Chang Liang Zheng ◽  
Xiao Feng Lu
Keyword(s):  
Mechanical Properties ◽  
Fracture Toughness ◽  
Magnesium Alloy ◽  
Carbon Fiber ◽  
Loading Rate ◽  
Interfacial Fracture ◽  
Interfacial Fracture Toughness ◽  
Fiber Metal Laminates ◽  
Loading Rates ◽  
Fiber Metal

Glass fiber reinforced aluminum alloy laminates, such as ARALL, GLARE are used widely for aeronautics and astronautics industry with excellent mechanical properties such as high specific strength, specific Young’s Modulus, high damage tolerance, high resistance to fatigue crack growth and good impact resistance. In order to obtain better mechanical properties, aluminum alloy plates and glass fibers were replaced by magnesium alloy plates and carbon fibers to get carbon fiber-metal laminates based on magnesium alloy. Single cantilever beams were used to examine the influence of loading rate on the interfacial fracture toughness of carbon fiber-metal laminates based on magnesium alloy. The results show that crack propagation is stable at low loading rates whereas unstable at high rates. And loading rates have slight influence on interfacial fracture toughness at low rates range from 1mm/min to 1000mm/min. The fracture toughness at high rates in impact tests is greater than at low rate.

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 Improvement and Properties of Fiber Metal Laminates Used in Aircraft Wing by Using Graphite-Polyester

2019 ◽  
Vol 12 (4) ◽  
pp. 92-103
Author(s):  
Ahmed M. Kadhum ◽  
Saad T. Faris ◽  
Ali A. Al-katawy
Keyword(s):  
Mechanical Properties ◽  
Adhesion Force ◽  
Glass Fibers ◽  
Flexural Modulus ◽  
Aircraft Wing ◽  
Fiber Metal Laminates ◽  
Jute Fibers ◽  
Fiber Metal ◽  
Aluminum Alloy 2024 ◽  
Metal Layers

The main objective of this study is to reduce weight and to improve the mechanical properties of aircraft wing by using Hybrid materials known as fiber metal laminates (FMLs). They are new age of engineering materials, which consist of metal layers reinforced with fibers emerged by matrix phase.  In this study, seven layers were used to produce the FMLs, which are consist of aluminum alloy2024-T3 reinforced by carbon and glass fibers bonded with using blend of graphite-polyester as adhesion. The Carbon Glass Reinforced Aluminum Laminates (CAGRALLs) is used as FMLs. The results show that the CAGRALLs give better in mechanical properties because of increasing in tensile strength, yield strength, , elastic modulus, elongation at fracture, flexural modulus and impact toughness except flexural strength by comparing with FMLs by using commercial epoxy as adhesion for other researchers. The increasing in layers is led to weaken adhesion force between layers of FMLs that led to decrease almost mechanical properties. The FMLs has good mechanial properties by using carbon and glass fiber by comparing with carbon and jute fibers. The CAGRALLs have the higher numbers of cycles at failure under cyclic loadings than Aramid Reinforced Aluminum Laminates (ARALLs). The CAGRALLs have the lower density by comparing with aluminum alloy 2024-T3 and steel that used in manufacturing of aircraft wing.

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.

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