Authors
1 Department of Mechanical Engineering, Marvdasht Branch, Islamic Azad University
2 Department of Mechanical Engineering, Marvdasht Branch, Islamic Azad University, Marvdasht, Iran
Abstract
The purpose of this paper is to estimate the fatigue life of an airplane wing with laminated composite skin, subjected to variable mechanical and thermal loads. To achieve this aim,at first, the three-dimensional model of airplane wing was drawn in CATIA software. Then, by transferring the model to the ABAQUS software, the finite element model of the wing wascreated. Here, the spars and ribs weremade ofaluminum T7075 and skin waslaminated composite with uni-directional and woven roving carbon epoxy layers. The convergence behavior of the structure wasexamined for selecting an appreciate element numbers. Finally, transient dynamic analysis followed by fatigue analysis of the wing structure was carried out. By performing fatigue simulation, the number of loading cycles resulted in failure of the structural components and wing skin panel was predicted. By comparing the simulation results with experimental research carried out by other researchers, the validity of the presented simulation method was demonstrated. The results of this research indicated that the replacement of traditional metallic wing skin with laminated composite skin causes a significant increase in fatigue life of the wing,besides a considerable weight reduction.
Keywords
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