Micro-Measurements: building better wings

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:

http://www.vishaypg.com/docs/25526/25526.pdf