Aircrafts are susceptible to various types of static and dynamic loading. Calculation of these loads are of prime importance in order to ensure the safety of an aircraft. Fatigue load is one such type of load which has to be evaluated. This project work comprises of design and fatigue analysis of a wing structure when different materials are used. The wing is of rectangular planform and is designed using CATIA V5. In order to illustrate the importance of materials and spar cross section in determining the structural strength of a wing, two materials (Carbon Epoxy and S-2 Glass) and two spar cross sections (I-Section and Rectangular Section) are chosen for detailed analysis. Following this structural analysis is carried out on ANSYS R18.1 using the static structural module to obtain the Equivalent Von-Misses stress distribution, life, damage, factor of safety and fatigue sensitivity of the wing structure due to the application of load. From the results obtained it can be observed that composites have high strength to weight ratio comparatively and hence the stresses developed in such materials are lower. On changing the spar cross section the variation in the results are clearly visible. Thereby indicating the important role of selection of materials and structural cross section in determining the strength of an aircraft structure.
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