This investigation focused on the prediction of damage formation in the region of a composite wing where an intercostal blade stiffener is stitched and cocured to the wing skin. Of particular interest was the tendency for delaminations to propagate between the stiffener flanges and the skin as well as the capability of stitch rows to arrest delamination growth. Finite element analysis was performed on an intercostal stiffener configuration. Additionally, mechanical testing was performed on specimens of the same configuration under tensile and compressive loading. A delamination was placed in the finite element models at locations identified as most susceptible to delamination formation. For a given load, strain energy release rates were calculated for increasing delamination length. Of particular interest was the tendency for delaminations to grow as well as the capability of stitch rows to arrest delamination growth. Stitches were modeled using linear springs with both extensional and shear stiffnesses. Finite element analyses were able to identify the locations of delamination formation under both tensile and compressive loading. Additionally, finite element predictions of delamination growth for stitched and unstitched stiffeners were in agreement with experimental results.
Analysis of damage development in stitched composite stiffeners
1999
11 Seiten, 5 Quellen
Conference paper
English
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