In order to save computational time during optimization process, we want to know if optimization of simplified model can give us a trend to follow to improve much more complicated model. By running optimization process from the most general case, an infinite plate containing a hole under a traction loading to more complicated case, finite plate containing a hole with traction and pressure loading, we obtained results for a simplified model. Then we used these results into a more complicated problem. By using this approach, we optimize an aircraft composite fuselage panel. For these optimizations, we focused on mechanical part of this system, objective is to reduce the stress concentration factor. Results obtained with optimization procedure and results from the real model have similar trends. Therefor this procedure can be used to save a lot of optimization computational time.

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