Abstract
Delamination is the critical damage type for carbon fiber structures, which are increasingly being employed in primary aircraft structures. One common solution to prevent the delamination from propagating is to install fasteners, clamping the laminate together and partially arresting the delamination. Current research has indicated that multiple fasteners installed in series do not fully arrest delaminations, instead merely slowing the propagation of the crack, first by compressing the lamina together and second by transferring load via shear engagement of the fastener. It has also been found that fastener spacing can be significantly larger than the common spacing of 5 fastener diameters; experimental and computational studies have indicated that the failure mode is shifted away from delamination even with a fastener spacing of 2 inches, or 8 times the fastener diameter.
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