(ISSN: 2349-2082)

International Journal For Ignited Minds
 Published Article
Simulation of Wing-Fuselage Attachment Bracket Lug for Fighter Aircraft
Shambhu Kumar , , Jyoshi Anil Kumar & Nagaraj Arali
The typical fighter aircraft undergoes complicated maneuvering during its flight. As a result, the aircraft will require immediate change in acceleration. The combination of high level of acceleration and complicated maneuvers will introduce high magnitude of loads on the wings. Wings attached to the fuselage structure through wing fuselage attachment brackets lug. The loads are transferred from the wing to the fuselage through the attachment brackets lug. For the continued airworthiness of an aircraft during its entire service life, static analysis together with fatigue and damage tolerance analysis plays a vital role. The objective is to validate the wing-fuselage attachment bracket from static, fatigue and damage tolerance point of view and estimate the inspection procedure/maintenance of the Wing-fuselage attachment bracket lug. For the validation of wing-fuselage attachment bracket, initially, the static load carrying capability of the wing-fuselage attachment bracket is calculated. Analysis for the strict safety experiments are carried out to check the structural integrity before usage. It is to ensure the static load carrying capability of the wing-fuselage attachment bracket. The fatigue analysis is carried out to determine the fatigue life of the part before initiation of a potential crack. The DT analysis is carried out to determine the crack propagation life for the part using the finite element method and Modified Virtual Crack Closure Integral (MVCCI) method.
Modified Virtual Closure Integral (MVCCI) Method, F&DT, Stress Intensity Factor (SIF), Crack Propagation and Fatigue Life.
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