Abstract
Fiber metal laminate (FML) belongs to metallic materials class consisting of layers of metal and fiber composite laminates which bonded together. This permits the structure to behave as very simple metal structure with affordable properties such as good resistance to corrosion, high strength to weight ratio, good resistance to fire, better fatigue properties. For the last few decades, the Fiber Metal laminates (FML) which yields high performance as a light weight material and accordingly its increasing demand in aircraft industry have a strong basement towards the development of refined fiber laminated structures. As a hybrid composites these FML’s is a composition of fibers reinforced material bonded with thin metal layers. The most common types of FMLs are CARALL (carbon reinforced aluminum laminate), GLARE (glass reinforced aluminum laminate), ARALL (aramid reinforced aluminum laminate), CentrAl, that bounded by a GLARE core and layers of aluminum. These hybrid composites which have two key constituents namely aluminum metals and fiber-reinforced laminate, offer numerous advantages such as resist fatigue failure and overcome the crack growth mostly in aircraft applications.Glare composed of thin aluminium sheets that are bonded together using an epoxy adhesive film in which glass fibers are embedded. The presence of the epoxy layers causes the attention has to be given to moisture ingress, which can occur during the aircraft service life.An important parameter that might influence the material properties is the service temperature. During the day time the ambient temperature changes from - 40o to 55o C. The in-service temperature of the airplane changes from -55o C to 70oC. Especially the increased or elevated temperatures could affect the material properties of the epoxy and thus the glare properties. Hence this study mainly focused on temperature influences on glare material when the laminate thickness is considered as variable and total heat flux is calculated for the temperature differences.
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