Wing-Fuselage Lug Stress Prediction Using Finite Element Method

Abstract:

This paper describes the methodology to predict the stress level that occurs at the wing-fuselage lugs (joints). The finite element models of the wing, the wing lugs and the fuselage lugs were developed. Finite Element Analyses were performed using NASTRAN finite element software. CQUAD4 and BAR2 elements were used to represent the individual structures of the wing such as the ribs and stringers. The applied load was based on the symmetrical level flight condition. Once the load distribution acting at the wing had been calculated and applied, reaction forces at the nodes representing the wing lugs were obtained and these values applied to the lug models where the maximum stress value acting at the lugs was obtained.

• Periodical: Applied Mechanics and Materials (Volume 393)
• Pages: 317-322
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.393.317
• Online since: September 2013
• Authors: Abdul Malik Hussein Abdul Jalil, Wahyu Kuntjoro
• Keywords: Finite Element Analysis (FEA), Wing-Fuselage Lugs

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