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Static Analysis On Wing Spar Joint For An Aircraft Using Finite Element Method
Pavan G,  Manjunath M V
Aircraft is a highly complex flying structure which undergoes various stresses 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 bending moment and shear loads from the wing are transferred to the fuselage through the attachment joints. This paper deals with stress analysis of wing spar joint. The stress analysis was carried out for wing-spar joint using Finite Element Method (FEM). Prediction of the fatigue life of wing-spar joint in a transport aircraft was precisely made. The proposed aircraft structure uses materials such as Heat Treated AISI-4340 for T section joint and Aluminum 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. In this work estimation of fatigue life for crack initiation of spar joint structure were carried out at maximum stress location.
Keywords- Finite element approach, stress analysis, C clamp joint structure, static analysis, fatigue analysis.
Unique Identification Number - IJEDR1803026Page Number(s) - 144-152Pubished in - Volume 6 | Issue 3 | July 2018DOI (Digital Object Identifier) -    Publisher - IJEDR (ISSN - 2321-9939)
Cite this Article
Pavan G,  Manjunath M V,   "Static Analysis On Wing Spar Joint For An Aircraft Using Finite Element Method"
, International Journal of Engineering Development and Research (IJEDR), ISSN:2321-9939, Volume.6, Issue 3, pp.144-152, July 2018, Available at :http://www.ijedr.org/papers/IJEDR1803026.pdf