Production technologies for lightweight structures made from fibre–metal laminates in aircraft fuselages

Ucan, Hakan; Apmann, Hilmar; Graßl, Gregor; Krombholz, Christian; Fortkamp, Kai; Nieberl, Dorothea; Schmick, Fabian; Nguyen, Cong Tam; Akin, Deniz Nick

doi:10.1007/s13272-018-0330-3

Cited by 7 publications

(5 citation statements)

References 2 publications

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“…These advantages have made FMLs a potential lightweight and high-strength material for aerospace and transportation applications. However, the mechanical properties of fiber metal laminates (FMLs) are sensitive to the working environmental conditions, especially at higher temperatures where the resin matrix softens, affecting the interlaminar bond strength and transverse tensile strength [ 7 , 8 , 9 ]. Therefore, it is necessary to further investigate the tensile behavior and damage mechanism of glass-fiber-reinforced magnesium alloy laminates at different temperatures and numbers of holes to promote the application of FMLs in engineering.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigation of the Tensile and Failure Response of Multiple-Hole-Fiber-Reinforced Magnesium Alloy Laminates under Various Temperature Environments

et al. 2023

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In this paper, the tensile mechanical behavior and progressive damage morphology of glass-fiber-reinforced magnesium alloy laminate for different numbers of holes in a temperature range of 25–180 °C were investigated. In addition, based on extensive tensile tests, the tensile mechanical behavior and microscopic damage morphology of porous-glass-fiber-reinforced magnesium alloy laminates at different temperatures were observed by finite element simulation and scanning electron microscopy (SEM). Finally, the numerical simulation and experimental results were in good accordance with the prediction of mechanical properties and fracture damage patterns of the laminates, the average difference between the residual strength values of the specimens at ambient temperature was 5.57%, and the stress–strain curves were in good agreement. The experimental and finite element analysis results showed that the damaged area of the bonded layer tended to expand with the increase in the number of holes, which has a lesser effect on the ultimate tensile strength. As the temperature increased, the specimens changed from obvious fiber breakage (pull-out) and the resin matrix damage mode to matrix softening damage and interfacial delamination fracture damage. As the testing temperature of the specimens increased from 25 °C to 180 °C, the tensile strength of the specimens decreased by an average of 51.59%, while the tensile strength of the specimens showed a nonlinear decreasing trend. The damage mechanism of porous-glass-fiber-reinforced magnesium alloy laminates at different temperatures is discussed in this paper, which can provide a reference for engineering applications and design.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigation of the Tensile and Failure Response of Multiple-Hole-Fiber-Reinforced Magnesium Alloy Laminates under Various Temperature Environments

et al. 2023

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“…Glass Laminates Aluminum Reinforced Epoxy (GLARE) is lightweight hybrid material consisting of alternately bonded layers of thin aluminum and glass fiber-reinforced polymer composites [1,2]. As the most well-known fiber metal laminates, GLARE have been widely employed as skin material of aircraft fuselages, due to their high specific strength and stiffness, excellent fatigue resistance and damage tolerance [3][4][5][6][7]. However, most aircraft structures inevitably contain a large number of fastener holes [7,8], resulting in the degradation of mechanical properties.…”

Section: Introductionmentioning

confidence: 99%

“…As the most well-known fiber metal laminates, GLARE have been widely employed as skin material of aircraft fuselages, due to their high specific strength and stiffness, excellent fatigue resistance and damage tolerance [3][4][5][6][7]. However, most aircraft structures inevitably contain a large number of fastener holes [7,8], resulting in the degradation of mechanical properties. It is essential to illuminate the mechanical behavior and damage mechanism of GLARE with open-hole for expanding their applications.…”

Section: Introductionmentioning

confidence: 99%

Open-Hole Tensile Behavior and Progressive Damage of Hybrid Fiber Metal Laminates

et al. 2021

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Fiber metal laminates (FMLs) are typical multilayer composites including metallic foils and fiber reinforced polymers. These are considered as the attractive skin materials for lightweight vehicle, especially GLARE laminates for aircraft fuselages. The open-hole tensile behavior and progressive damage of GLARE laminate are studied experimentally and numerically. A combined progressive failure model with strain-based damage evolution laws are imposed on the composite layer based on the subroutine Abaqus-VUMAT. The cohesive zone model and equivalent plastic strain criterion with isotropic hardening is respectively employed to describe the interlaminar and metal layer damage. The effects on the geometry characteristics of open-hole are discussed, exploring the variation of residual strength, damage evolution process and damage affected zone. The two fracture modes and delamination failure are observed, all numerical results show good agreement with experiment obtained. The damage evolution of fiber both gradually vary from "butterfly" to "funnel" pattern for circluar and square open-hole. However, the different evolution emerges for matrix damage. Compared with circular one, the square open-hole can lead to more fiber damage than matrix one. The transition fillet can effectively disperse stress concentration, improving the residual strength of GLARE with square open-hole. The 45° off-axis is the optimal design of square open-hole to fully activate the reinforcement effect of fiber. All suggest the open-hole design is important to guarantee the application security for GLARE plate-like structure.

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“…In order to enhance the application of PAUT for Glare components, this paper presents an improved NDT routine for the detection and the evaluation of pre-preg gaps in Glare laminates. The presence of pre-preg gaps, resulting due to fibre placement movement, tow width variation, or complexity of manufactured part [27], has proven to negatively affect the mechanical properties both for fully composite materials [8,[28][29][30][31][32][33] and also for Glare laminates [15,34], and it will constitute a potential issue for the future automation of Glare manufacturing [7,35].…”

Section: Introductionmentioning

confidence: 99%

Non-destructive testing investigation of gaps in thin Glare laminates

Jakubczak

Nardi

Bieniaś

et al. 2019

Nondestructive Testing and Evaluation

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The manufacturing procedure of Fibre Metal Laminates (FMLs), such as Glare, consisting of alternating layers of pre-preg fibre and metal sheets is relatively complex, and defects can be introduced during manufacturing. The automation of the manufacturing steps is vital for future Glare production, and specific defects have to be considered. Among them, gaps between pre-preg plies represent a potential risk for the mechanical performances of the final laminate. In this paper/research, non-destructive testing (NDT) based on ultrasonic inspections are performed on Glare laminates with pre-preg gaps in order to extend and improve the current state of the art to different pre-preg gap widths, depths, and specimen lay-ups. Firstly, gaps were introduced in Glare specimens. Then, a conventional C-scan ultrasonic inspection is performed. In order to overcome the current limitations of a top or planar view of the laminates, the evaluation of the depth of the gaps in the laminates is performed by means of phased array pulse-echo ultrasonic testing (PAUT). Lastly, images of the laminate cross-section cut-outs have been collected in order to provide a meaningful evidence of the ultrasonic-based analysis. Results from different Glare lay-ups and gap widths and depths show the accuracy of the proposed investigation which is able to provide a detailed assessment of the gap occurrences also for very thin laminates, paving the way for portable and faster quality control strategies for future automated Glare manufacturing.

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Production technologies for lightweight structures made from fibre–metal laminates in aircraft fuselages

Cited by 7 publications

References 2 publications

Experimental and Numerical Investigation of the Tensile and Failure Response of Multiple-Hole-Fiber-Reinforced Magnesium Alloy Laminates under Various Temperature Environments

Experimental and Numerical Investigation of the Tensile and Failure Response of Multiple-Hole-Fiber-Reinforced Magnesium Alloy Laminates under Various Temperature Environments

Open-Hole Tensile Behavior and Progressive Damage of Hybrid Fiber Metal Laminates

Non-destructive testing investigation of gaps in thin Glare laminates

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