Composite patch repair of cracked metallic aircraft structures has recently
been accepted as one of the means of improving fatigue life and attaining
better structural integrity. The effectiveness of such patches for cracked
sheets can be measured as an achievable reduction in the crack lip stress i
ntensity factor (SIF). In this paper, a study has been conducted to get an
optimum design of symmetric (balanced) composite patch to a centre cracked
metallic sheet. It has been achieved considering the SIF at the crack tip o
f the sheet as constraint and the plan-form shape of patch and the thicknes
s of patch as design variables. The results of square, circular, elliptical
and rectangular patches are presented. The effectiveness of smaller patch
length perpendicular to the crack compared to the full-length patch in the
same direction has been brought out. A new configuration called skewed patc
h is studied. Reduction in weight of the patch due to skewed configuration
has been brought out. The effectiveness of patch thickness over the patch p
lan-form shape in reducing SIF has been brought out. (C) 2000 Elsevier Scie
nce Ltd. All rights reserved.