Comparison of the effectiveness of boron/epoxy and graphite/epoxy patches for repaired cracks emanating from a semicircular notch edge

Finite element analysis of cracks in aging aircraft structures with bonded composite-patch repairs

“…However, a high shear modulus will cause the higher shear stress to develop in the adhesive or the substrate. This will inherently cause a failure of adhesion (delamination or breakage) because forces are pulling in opposing directions across the adhesive bond [15,19,25]. …”

Analysis of cracked aluminum plates with one-sided patch repair using p-convergent layered model

“…For the analysis of externally bonded systems, Ahn et al [12] demonstrated the performance of the model using p-refinement based on equivalent-single-layer theory modified by degenerated shell theory. Some recent papers [13,14] reported the behavior of cracked plates with externally bonded repairs, using FRANC 2D/L [15] which uses equivalent-single-layer theory. These 2-D models cannot appropriately model one-sided patch bonded systems which show significant out-of-plane behavior.…”

Analysis on the parameters of adhesively bonding patch repairing cracked sandwich face panel

“…Since the 70s of twenty century, Dr. Baker started the study on the adhesively bonding composite patch repairing the metal airframe of the aged aircraft [1]. Up to now, a lot of studies on the composite patch repairing the damaged metal airframe have been published [2][3][4][5][6]. The composite patch repair has become an effective way to restore the static strength and improve the fatigue character of the damaged metal airframe.…”

“…The effects of the patch thickness and the patch size have also been studied on the static strength of the laminate. The reference [6] studied the stress concentration factor and SIF of the aluminium plate with half circle notch on the edge repaired with the different composite in the 2D FEM. It can not check the stress partition in the thickness direction.…”