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In aviation industries, most of the stiffened structural components are manufactured by forming and laminating process. Combination of several conventional manufacturing processes is required in modern industries in hybrid laminate production. Fiber metal laminates undergo various joining process during assembly of aero-structures. Among them, forming and drilling are often required during assembly. Understanding the significance of various process parameters enables quality production and assembly of fiber metal laminates structures. Many researchers explored the cause and effect of few parameters and mechanisms which significantly alter the quality of form and drill. This review describes the progress in forming and drilling of fiber metal laminates for aerospace applications. Especially towards the process parameters, defects and their causes along with the preferred solutions recommended by the researcher society in forming and drilling processes. Numerous factors have controlled the quality of forming and drilling processes. Due to the machining parameters, different failure modes will occur in different layup of the laminates. To overcome the failures in machining/forming of fiber metal laminates, choosing the optimum parameter for the selection based procedure is needed to improve quality of fiber metal laminates.

Recently, composite materials have been used in various domains. The reasons for this are low weight and can withstand high strength. New developments of the conventional composites replacing the metal and metal matrix materials in addition to environmental effects are also very minimal. In this, work is undertaken to prepare the fibre reinforced composites and study their mechanical behaviour of combinations. To prepare the fibre reinforced composite (FRP), glass wool (GW) is incorporated into epoxy resin with the varying weight percentage of 0, 30, 40 and 50 by the way of compression moulding method. The composites were assessed on its properties such as tensile strength, flexural strength, impact strength, hardness and density of the composites and have been performed with ASTM standards at room temperature. The fracture regions were studied using scanning electron microscopy (SEM). From the experimental results, high strength was attained at 40 weight % addition of glass wool into epoxy matrix. It is found that the composites have a better strength, which makes this method more convenient and less costly.

Fiber metal laminates (FMLs) are structural materials that play a vital role in the aviation sector, in which they are exposed to cyclic long-term loading. This article investigates creep response and rupture mechanisms of glass laminate aluminum reinforced epoxy (GLARE) FMLs based on microindentation creep testing. Specimens were manufactured by compression molding, and experiments were conducted under different test parameters, namely, aluminum surface treatment (in terms of surface roughness), creep chamber temperature, indentation load, and run time. In addition, rupture mechanisms were analyzed using scanning electron microscopy. The individual interaction of control parameters on creep strain and mass loss response was studied using Taguchi method. Among the studied factors, specimen condition and creep chamber temperature predominantly control creep rupture, whereas load and time were less important, as confirmed by statistical predictions using linear regression.

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