Design and optimization of defense hole system for biaxial-loaded composite laminates

Abstract

Design optimization of defense hole systems placed near the main circular cutout of composite laminated plates subject to biaxial loading is performed in this study. For that purpose, a numerical framework based on finite element models validated experimentally via RGB-photoelasticity and by reproducing selected cases available in literature is developed. Redesign optimization technique is utilized to reach the optimum geometric design parameters of the defense hole system, i.e., size and location. Parametric study for fiber orientation, biaxial loading ratio, stiffness ratio and stacking sequence is conducted as well. Stress concentration near circular cutouts can be reduced by 24.5%, 25.5%, 29.1%, 31.7% and 20.6% for values of the loading ratio equal to, respectively, 0, 0.25, 0.50, 0.75 and 1. Such significant reductions are obtained by introducing four elliptical defense holes along the principal stress direction lined up with fibers.

Buckling behavior of laminated composite stiffened cylindrical shell panels having cutout for different parametric variations

“…Other approaches to tackle the issue of stress and strain concentrations around cutouts include the use of fiber-steered laminates, 22–24 cutout reinforcement layout, 25 and defense hole system. 26 Some studies are available on the effects of cutout on the buckling load of cylindrical panel. However, the buckling of stiffened composite cylindrical panels with cutout has not been reported so far.…”