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OPTIMAL DESIGN OF COMPOSITE WING SPAR SUBJECTED TO FATIGUE LOADINGS
Students at the Cal Poly Department of Mechanical and Aerospace Engineering were tasked with the challenge of ensuring that a wing structure is within design limits. To accomplish this task, a Finite Element Analysis (FEA) of the wing and loading conditions was created and a structural test performed. The FEA model was then validated using Micro-Measurements System 8000 data system, strain gages, and strain gage installation materials.
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