Aerospace Engineering Commons^™

The Effect Of The Fastener Of Different Configuration Composite Panels On Failure Analysis, Robert Austin

Master's Theses

This study presents the effect of the stacking sequence and fiber orientation on a composite sandwich panel subjected to static in-plane bolt loading. Six plates were constructed with laminates of unidirectional carbon fiber and cross ply weaves of fiberglass. The orientations that were examined included 0, +/- 45, and 90 degrees. Half of the plates had fiberglass lamina on the outside of the laminate while the other three plates had the carbon fiber on the outside. Experimental and analytical tests were performed to determine the best orientations and stacking sequence.

For the numerical analysis, plates with fibers oriented at +/- …