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.