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The reduction of weight elements is considered as a major objective of several manufacturing companies. This objective will help in growing application sections of the used fiber composites for important structural elements. Modern fiber metal laminate (FML) having lightweight properties is established to be used instead of other substances in different applications including those related to the aerospace industrial sector. Fiber metal laminate is being deemed as an alternative significant substance that is being extensively explored due to its operation, unlike other current materials. There are different profitable FML such as GLARE (glass-reinforced aluminum laminate), established on elevated intensity ARALL glass fibers (aramid-reinforced aluminum laminate), built on fibers of aramid, in addition to CARALL (carbon-reinforced aluminum laminate), centered on fibers of carbon. This paper analyzes important information that contributes to the mechanical characteristics of FMLs under tensile, flexure, impact, etc. conditions.

In Fibersim the digital design of the composite preforms laying process begins with the creation of laminates, which define the required preforms and its plies. The digital design of ply-based laying process, zone-based laying process, multi-ply-based laying process, and the methods of multi-ply and zone-based laying process are elaborated.

Fibre metal laminates, hybrid composite materials built up from interlaced layers of thin metals and fibre reinforced adhesives, are future-proof materials used in the production of passenger aircraft, yachts, sailplanes, racing cars, and sports equipment. The most commercially available fibre–metal laminates are carbon reinforced aluminium laminates, aramid reinforced aluminium laminates, and glass reinforced aluminium laminates. This review emphasises the developing technologies for forming hybrid metal–polymer composites (HMPC). New advances and future possibilities in the forming technology for this group of materials is discussed. A brief classification of the currently available types of FMLs and details of their methods of fabrication are also presented. Particular emphasis was placed on the methods of shaping FMLs using plastic working techniques, i.e., incremental sheet forming, shot peening forming, press brake bending, electro-magnetic forming, hydroforming, and stamping. Current progress and the future directions of research on HMPCs are summarised and presented.

Fiber metal laminates (FMLs) are made by sandwiching a fiber-reinforced composite between thin layers of metals. FMLs are the most modern materials utilized in automotive and aerospace manufacture because of their superior mechanical behavior when compared to conventional metallic alloys. In the current work, the effect of hybridization between jute-reinforced composites and other fabrics on the mechanical properties of the designed FMLs was experimentally assessed under various tests, including tension, flexural, in-plane shear, interlaminar shear, and bearing tests. Aluminum alloy 1050 (AA 1050) was used as a metal component in the designed FMLs, while the composite components are jute (J), glass (G), aramid (A), carbon (C), and basalt (B) fabrics. To ensure good adhesion between Al-sheets and composite laminates, Al-sheets underwent both mechanical and chemical treatments. The intended FMLs were prepared via hand lay-up and compression casting techniques. The designed stacking sequences were 8 J, 2G/4J/2G, 2A/4J/2A, 2C/4J/2C, and 2B/4J/2B. According to the experimental results compared with the 8 J specimen, the 2G/4J/2G specimen presents maximum flexural strength, flexural modulus, and interlaminar shear strength with an improvement percent of 51.51, 212.33, and 15.72%, respectively. On top of that, the 2A/4J/2A specimen introduces maximum tensile failure strain and tensile toughness modulus with an enhancement percent of, respectively, 21.56 and 116.56%, while the 2C/4J/2C specimen introduces extreme tensile strength, tensile modulus, flexural strain, in-plane shear strength, and bearing strength with an upgrading percent of 181.91, 111.86, 21.24, 26.38, and 60.94%, respectively.

The combination of fibre metal laminates (FML) and sandwich structures can significantly increase the performance under impact of FMLs. The goal of this work was to create a material that will combine the superior properties of FMLs and foam sandwich structures in terms of the impact resistance and simultaneously have lower density and fewer disadvantages related to the manufacturing. An extensive impact testing campaign has been done using conventional fibre metal laminates (carbon- and glass-based) and in the proposed fibre foam metal laminates to assess and compare their behaviour. The main difference was observed in the energy absorption mechanisms. The dominant failure mechanism for fibre foam laminates is the formation of delaminations and matrix cracks while in the conventional fibre metal laminate the main failure mode is fibre cracking due to high local stress concentrations. The reduction in the fibre cracking leads to a better after-impact resistance of this type of structure improving the safety of the structures manufactured with these materials.

Technology has allowed the recent advancements like thick Monochromatic Teeth Veneers, Stacked or FeldspathicTeeth Veneers, Teeth Veneers with Reinforced Leucite, Lithium Disilicate Teeth Veneers, Lumineers and the fabrication of advanced qualities of porcelain veneer which are ultra thin and offer superior aesthetics, greater life span and maximum strength. When multiple thin layers of wafer thin shells are chemically bonded to the tooth structure it is called laminate veneer. \"lamination\" is the process which refers to joining the materials together [1]. Indications: * localised defects * generalised defects * intrinsic discolouration[5] * diastema * Chipped tooth * worn dentition * ->malaligned teeth * excessively discoloured teeth * ->hypocalcification * peg laterals * lingually positioned tooth[6] [7] Advantages: They are extensively used as they are biocompatible, strong, durable, stain resistant, show longetivety, little recovery time, good clinical performance and are minimally invasive compared to crowns[8]. [...]it is of great esthetic value[9].It is the highest quality cosmetic veneers.They are not as thick as monochromatic veneers.However the downside of these feldspar veneers is that they are not strong due to their low mechanical properties as the flexural strength is from 60-70 MPA[10].

Background Incremental hole-drilling (IHD) has shown its importance in the measurement of the residual stress distribution within the layers of composite laminates. However, validation of these results is still an open issue, especially near the interfaces between plies. Objectives In this context, this study is focused on experimentally verifying its applicability to fibre metal laminates. Methods Tensile loads are applied to cross-ply GFRP-steel [0/90/steel]s samples. Due to the difference in the mechanical properties of each ply, Classical Lamination Theory (CLT) predicts a distribution of the uniform stress within each layer, with pulse gradients between them. The interfaces act as discontinuous regions between the plies. The experimental determination of such stress variation is challenging and is the focus of this research. A horizontal tensile test device was designed and built for this purpose. A differential method is used to eliminate the effect of the existing residual stresses in the samples, providing a procedure to evaluate the ability of the IHD technique to determine the distribution of stress due to the applied tensile loads only. The experimentally measured strain-depth relaxation curves are compared with those determined numerically using the finite element method (FEM) to simulate the hole-drilling. Both are used as input for the IHD stress calculation method (unit pulse integral method). The distribution of stress through the composite laminate, determined by classical lamination theory (CLT), is used as a reference. Results Unit pulse integral method results, using the experimental and numerical strain-depth relaxation curves, compare reasonably well with those predicted by CLT, provided that there is no material damage due to high applied loads. Conclusions IHD seems to be an important measurement technique to determine the distribution of residual stresses in fibre metal laminates and should be further developed for a better assessment of the residual stresses at the interfaces between plies.

Fiber-metal-laminates (FML) provide a high variability in part properties and are often used to satisfy multiple component demands in aerospace applications. However, conventional use of hybrid laminates in the automotive sector is unrewarding due to high manufacturing costs and strongly restricted forming degrees. This paper presents an approach, which enables the manufacturing of laminate components with low bending radii for high volume applications. To separate the carbon fiber–reinforced polymers (CFRP) from the metal sheets, an elastomer layer was used, resulting in the omission of surface treatments for adhesion and corrosion prevention. The forming degrees presented in this work exceeded current approaches. Furthermore, the influence of the forming process on the mechanical properties was analyzed, thus ensuring the profitability of the presented approach for industrial applications.

In the presented research, 11 different laminates were compared, 8 of them were two-layered 3 of them were three-layered laminates. The laminates that were analyzed vary by the type of face-side textile material (knitted and nonwoven textiles), density and thickness of the foam, and specific properties (higher air permeability and low-emission foam). Depending on the different types of laminates, different laminating processes are used: hot-melt, flame, and powder laminations. The purpose of the presented research is to analyze the basic characteristics of the different laminate structures. Properties that are important for these types of laminates are the number of layers, areal density, thickness, resistance to rubbing, fire resistance, water vapor permeability, air permeability, breaking force and extension, thermal conductivity, and stratification. We found that the properties of laminates were not affected by the density and thickness of the foam. Nonwovens and other laminate components do not perform because they have lower abrasion resistance and lower tensile strength than knitted fabrics as the face layer. Knit laminates have good abrasion resistance, high air permeability, and water vapor permeability. Both are self-extinguishing to the first or second mark. Three-layered laminates have lower thermal conductivity and air permeability than two-layered laminates.

Composite materials such as Fiber Metal Laminates (FMLs) have attracted the interest of the aerospace and automotive industries due to their high strength to weight ratio, but to use them as structures it is necessary to master the manufacturing and wiring techniques of these materials. Therefore, this paper aims to address and summarize the drilling and milling processes in FMLs based on a literature review of papers published from 2000 to 2023. Parameters used in multi-material manufacturing and machining such as drilling and milling, tool geometry, tool coating, lubricants and coolants published by researchers were analyzed, compared and discussed. Machining process parameters related to sustainability were also analyzed. A SWOT analysis was carried out and discussed to identify opportunities for improvement in the machining process. There are opportunities to develop the surface treatment of aluminum alloys, such as testing other combinations than those already used, testing non-traditional surface treatments and manufacturing modes, and developing sustainable techniques during the FML manufacturing process. In the area of tooling, the opportunities are mainly related to coatings for tools and changing machining parameters to achieve an optimum finished part. Finally, to improve the sustainability of the process, it is necessary to test coated drills under cryogenic conditions to reduce the use of lubricants during the machining process.