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Design Optimization and Static Analysis of a Lug Joint Located between Fuselage and Wing Structure of Transport Aircraft

Arivudainambi J, Vinothkumar T. S, Waseem B. A, Clastinmony G. P.

Abstract


Aircraft is a highly complex flying structure which undergoes various stress during operation. Generally transport aircraft undergoes nominal manoeuvring flights. During take-off and landing, wing produces maximum lift and it undergoes highest bending moment. The bending moment will be maximum at the root of the wing. The aircraft wings are attached to the fuselage structure through wing-fuselage attachment brackets. The bending moment and shear loads from the wing are transferred to the fuselage through the attachment joints. This paper deals with transfer of bending load through wing-fuselage attachment brackets of a transport aircraft. The stress analysis was carried out for wing-fuselage attachment bracket using Finite Element Method (FEM). Then I-section spar was optimized for bearing higher loads compared with the existing bracket for factor of safety. Prediction of the fatigue life of wing-fuselage attachment bracket in a transport aircraft was precisely made. The proposed aircraft structure uses materials such as Heat Treated AISI-4340 for Lug joint bracket and Aluminium Alloy – 2024-T351 for I-section wing spar and rivet joints. Fatigue life calculation was carried out for typical service loading condition using constant amplitude S-N data for various stress ratios and local stress at various stress concentration. The maximum tensile stress of proposed lug is observed as 519 N/mm2.


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