Authors :
R S Harish; K Veda Abhishek; Harish U V; Tharundeep K; G. Sakthivel; N Raghukiran
Volume/Issue :
Volume 7 - 2022, Issue 3 - March
Google Scholar :
http://bitly.ws/gu88
Scribd :
https://bit.ly/3iC0ET0
DOI :
https://doi.org/10.5281/zenodo.6383529
Abstract :
Topology optimization has become an effective
tool for light-weight and performance design, especially
in the aeronautics and aerospace industry. It has proved
to meet the requirement to produce intricate parts that
are more robust and lightweight. This technology has
proved costeffectiveness, improved payload capacity, and
increased fuel economy in the aerospace sector, and
enabled structural components to deliver the same or
enhanced performance while using less material. Among
the aircraft, the fuselage and the wings are important
structural components. Wing fuselage lug attachment
bracket is the connecting element that connects the wings
and the fuselage. Catastrophic failure of the bracket may
sometimes lead to the separation of the aircraft structure.
This work is focused on modelling, shape optimization,
and analysis of an aircraft wing-fuselage lug attachment
bracket. The methodology involves modelling and shape
optimization of the bracket using different sets of
materials. Finite elemental modelling and structural
analysis were done to study the stresses and deformation
on the bracket. Fatigue damage estimation is carried out
to study the behavior of bracket for repeated cyclic
loading.
Keywords :
Topology optimization, wing-fuselage attachment bracket, fatigue damage, static structural, load factor, mass reduction.
Topology optimization has become an effective
tool for light-weight and performance design, especially
in the aeronautics and aerospace industry. It has proved
to meet the requirement to produce intricate parts that
are more robust and lightweight. This technology has
proved costeffectiveness, improved payload capacity, and
increased fuel economy in the aerospace sector, and
enabled structural components to deliver the same or
enhanced performance while using less material. Among
the aircraft, the fuselage and the wings are important
structural components. Wing fuselage lug attachment
bracket is the connecting element that connects the wings
and the fuselage. Catastrophic failure of the bracket may
sometimes lead to the separation of the aircraft structure.
This work is focused on modelling, shape optimization,
and analysis of an aircraft wing-fuselage lug attachment
bracket. The methodology involves modelling and shape
optimization of the bracket using different sets of
materials. Finite elemental modelling and structural
analysis were done to study the stresses and deformation
on the bracket. Fatigue damage estimation is carried out
to study the behavior of bracket for repeated cyclic
loading.
Keywords :
Topology optimization, wing-fuselage attachment bracket, fatigue damage, static structural, load factor, mass reduction.
