Abstract
The main objective of this paper is to present prototype of wing spar joint using CATIA V5 software to study the behavior of wing spar joint as per actual working condition and to perform structural analysis of the wing spar joint based on condition of cyclic loading (fatigue loading). Determining the loading modes in the spar joint is subjected to static load and fatigue loads which should be taken into account in the evaluation of the strength and fatigue life. Initially, the components were modeled with CATIA V5 and imported to MSC PATRAN; MSC NASTRAN is used as a solver. From the obtained maximum tensile stresses, fatigue analysis was carried out to find fatigue life of the spar joint with different fatigue load spectra.
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