fiber metal laminate
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Materials ◽  
2022 ◽  
Vol 15 (2) ◽  
pp. 439
Author(s):  
Mingshi Wang ◽  
Jianxun Zhang ◽  
Hui Yuan ◽  
Haoyuan Guo ◽  
Wenbo Zhuang

The plastic behavior in the large deflection response of slender sandwich beams with fiber metal laminate (FML) face sheets and a metal foam core under transverse loading is studied. According to a modified rigid–perfectly plastic material approximation, an analytical model is developed, and simple formulae are obtained for the large deflection response of fully clamped FML sandwich beams, considering the interaction of bending and stretching. Finite element (FE) calculations are conducted, and analytical predictions capture numerical results reasonably in the plastic stage of large deflection. The influences of metal volume fraction, strength ratio of metal to composite layer, core strength, and punch size on the plastic behavior in the large deflection response of FML sandwich beams are discussed. It is suggested that, if the structural behavior of fiber-metal laminate sandwich beams is plasticity dominated, it is similar to that of metal sandwich beams. Moreover, both metal volume fraction and the strength ratio of metal to composite layer are found to be important for the plastic behavior in the large deflection response of fiber metal laminate sandwich beams, while core strength and punch size might have little influence on it.


2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Costas D. Kalfountzos ◽  
George S.E. Bikakis ◽  
Efstathios E. Theotokoglou

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.


2021 ◽  
Vol 14 (4) ◽  
pp. 79-89
Author(s):  
Saad Theeyab Faris ◽  
Ali Adwan Al-katawy ◽  
Ahmed Mohammad Kadhum

The Fiber Metal Laminates (FMLs) was studied and improved the mechanical properties were used for aircraft wing. The FMLs are consisting of metal sheets reinforced with fiber bonded by matrix phase. The FMLs consist of seven layers to produce the Hybrid composite materials that made from 2024-T3 Aluminuim sheets with carbon and glass fibers as reinforcement and bonded using adhesion materials that are locally manufactured from resole resin with adding using epoxy resin. By using the FMLs, the mechanical characteristics have been improved and the weight of the aircraft wing has been reduced. The mechanical characteristics have been improved comparing to other FMLs using commercial epoxy. The FMLs with carbon and glass fibers have high tensile strength and elastic modulus but low yield and elongation comparing with the FMLs of carbon fibers as a reinforcement. The flexural modulus and impact toughness is high for the FMLs with glass fiber comparing with jute fibers with adding using carbon fiber as areinforcement.The Aramid Reinforced Aluminum Laminates (ARALLs) have low fatigue strength than FMLs using carbon fiber as reinforcement. The FMLs are lower ratio of ultimate to yield strength and density than 2024-T3 Aluminum alloy that commonly used in aircraft wing.


2021 ◽  
Vol 2 (Oktober) ◽  
pp. 50-56
Author(s):  
Muhammad Juliansyah Winarto ◽  
Lalu Saefullah ◽  
Willem Loe Mau

The combat vehicles that Indonesia Army belong to most of the materials are steel, for example the armored vehicle anoa 6x6. Steel material is used as a fire protection on the vehicle, it will greatly affect the performance of the vehicle. It is caused the steel material has a high density, which is around 7750 kg/m3to 8050 kg/m3. So, with a large enough volume of the vehicle body, it will increase the burden of the vehicle. As well as the engine load will increase, and more power is needed to be able to move the vehicle. Seeing these problems, it is necessary to have a research or study on alternative materials to replace the body of a combat vehicle that can withstand fire from opposing weapons that cause personnel to be injured. In this study, experimental and simulation methods were used using the ansys application to analyze the strength of the composite material in the form of an aluminum layer that had been treated to increase the hardness value. Furthermore, it is coated with a composite material using a carbon fiber matrix of epoxy, HGM and polyurethane. The coating material is called Fiber Metal Laminate (FML), so the material used has a lighter density, the load received by the vehicle engine is lighter, and the performance of the vehicle will be more effective and efficient.


Materials ◽  
2021 ◽  
Vol 14 (19) ◽  
pp. 5771
Author(s):  
Jipeng Zhang ◽  
Yue Wang ◽  
Wen Yang ◽  
Yuan Zhao

Mechanical joints are commonly required in structures made of fiber metal laminate (FML), which pose a threat due to multi-site stress concentrations at rivet or bolt holes. Thus, for a reasonably designed FML joint, it is essential to characterize the failure mechanism of multiple-hole FML; however, little information about this has been found in open literature. In the present work, influences of hole arrangement and loading strategy (on-axis or off-axis) on the failure mechanism of multiple-hole FML were investigated, by performing finite element analyses and energy dissipation analyses with elastoplastic progressive damage models that took curing stress into account. Six types of specimens with holes arranged in parallel and staggered forms were designed, whose geometrical parameters were in strict accordance with those specified for composites joints. It indicated that the stress distribution, gross/net notched strength, critical fracture path, and damage evaluation process were only slightly influenced by the hole number and hole arrangement. On the other hand, they were strongly influenced by the loading strategy, due to the transition of failure domination. Results presented here can provide evidence for introducing design regulations of composite joints into the more hybrid FML, and for reasonably determining its multiple-hole strength merely based on the sing-hole specimen.


2021 ◽  
Vol 167 ◽  
pp. 108026
Author(s):  
Wentao He ◽  
Linfeng Wang ◽  
Huancai Liu ◽  
Changzi Wang ◽  
Lu Yao ◽  
...  

2021 ◽  
Vol 1190 (1) ◽  
pp. 012028
Author(s):  
Dietrich Voswinkel ◽  
Hüseyin Sapli ◽  
Dennis Kloidt ◽  
Thomas Heggemann ◽  
Werner Homberg ◽  
...  

Materials ◽  
2021 ◽  
Vol 14 (19) ◽  
pp. 5547
Author(s):  
Eu-Tteum Park ◽  
Jeong Kim ◽  
Beom-Soo Kang ◽  
Woojin Song

The microwave composite forming (MCF) process can reduce manufacturing cost because the process time is reduced by the dielectric heating of the mold and the composite material. In a previous study, the MCF process using a commercial microwave oven with a polytetrafluoroethylene mold was applied. Disadvantages of the previous MCF process have been investigated. These included the difference in tensile properties according to the cutting location, absence of a method to measure temperature during the MCF process, and the fact that the input power cannot be controlled according to the temperature. To solve these problems, a microwave oven with a silicon carbide mold was proposed in this study. Uniaxial tensile tests were conducted to obtain the tensile properties of the fiber metal laminate (FML) specimen. In addition, a microscopic image was captured to investigate the non-adhesive area. The tensile properties and thickness distribution of the FML specimens manufactured by the proposed and previous MCF processes were compared according to the cutting location of the FML sheets. Furthermore, the non-adhesive area was quantified to compare the processes. The results revealed that the proposed MCF process improved the tensile properties of the FML specimen and reduced the non-adhesive area.


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