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.

See the full case study at this link:



jjohnson's picture

Jim Johnson

Technical Sales Manager