Impact Damage and Failure Mechanisms in Structure Relevant Composite Specimens

摘要

Impact damage and failure mechanisms, representative of stiffened composite wing211u001epanels, were studied as to using small but structure relevant (SR) specimens. It 211u001ewas investigated as to how laminate stacking sequence influences the location 211u001ewithin a laminate of the major delaminations that are generated by impact. Impact 211u001edamages for six different lay-ups showed major delaminations predominantly at the 211u001eply interfaces where they were expected. Subsequently, the residual strength of 211u001ethe SR specimens was determined in compression. The major impact induced 211u001edelaminations were also the delaminations that propagated under loading, driven 211u001eby bending or buckling of the 0-degree plies. However, with increased loading, 211u001etransverse shear of the delaminated sublaminates became the ultimate failure 211u001emechanism. Thus it was concluded that the residual strength of the SR specimens 211u001edepends primarily on the reduced global stability of the damaged laminate, and 211u001eless on the individual stability of the delaminated sublaminates.