Publication Date: 2024/02/22
Abstract: Since most of the crucial components, including the front, rear, and wings, are attached to the central fuselage, it plays a significant influence in the design of aircraft fuselages, leading to increased payload and improved performance. So, the load applied to the part is transferred to the central fuselage part. The primary objective of our study is to optimize the fuselage skin to withstand varying loads, with a particular focus on the central fuselage part where the load is transferred. This central fuselage plays a pivotal role in the overall weight distribution of the aircraft. To achieve weight reduction, we employ material optimization techniques, specifically comparing aluminium alloy with hybrid composite materials. Material optimization involves a comprehensive comparison between aluminium alloy and hybrid composite materials, wherein composite laminates, comprising carbon fiber, glass fiber, and Hexply 8552, are applied over the fuselage skin. This approach allows us to analyze both the physical and structural properties of the fuselage. Various structural analyses, including Shear Test, Bending Test, Fatigue Test, Tensile Test, and Compression Test, have been meticulously conducted using ANSYS WORKBENCH Software. Boundary conditions are established according to specific requirements. The results unequivocally demonstrate that the hybrid composite material exhibits superior properties compared to conventional aluminium alloy. This includes enhanced performance and achieved material optimization, ultimately impacting the total weight of the aircraft.
Keywords: Material Optimization, Aluminium Alloy, Carbon Fibre, Glass Fibre, Hexply 8552, Hybrid Composite Materials.
DOI: https://doi.org/10.5281/zenodo.10691400
PDF: https://ijirst.demo4.arinfotech.co/assets/upload/files/IJISRT24JAN1593.pdf
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