Authors :
Atharva Salunkhe; Chetan Patil; Harshvardhan Deshmukh; Yash Shinde; Krishna.B. Jadhav
Volume/Issue :
Volume 9 - 2024, Issue 1 - January
Google Scholar :
http://tinyurl.com/ym4jj4rn
Scribd :
http://tinyurl.com/yvet9u3m
DOI :
https://doi.org/10.5281/zenodo.10691400
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.
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.
