A generic damage tolerance approach to bonded structures which permits prediction of adherent crack growth, adhesive delamination, and the interaction between adherent crack and interface delamination has been presented. This methodology was developed for predicting the coupled delamination and crack growth phenomenon in fibre metal laminates, but has shown promise for being applied to a wider range of bonded aircraft structures. The power of such an approach, particularly for cases where adherent cracking and adhesive delamination are expected simultaneously such as in bonded patch repairs, is evident. The methodology builds upon established methods for predicting crack growth and delamination growth under fatigue loading conditions and provides a sound description of their interaction. Using such an approach, numerous damage scenarios can be analyzed permitting a thorough damage tolerance analysis of bonded aircraft structures. The validity of this approach has only been demonstrated for a narrow range of applications. Although it is anticipated that the approach has a wide reaching generic applicability, the validity of the approach still needs to be verified for a wider range of materials and interfaces, including pure composite materials and cocured vs. secondary bonded interfaces.
Damage tolerance philosophy for bonded aircraft structures
2009
18 Seiten, 8 Bilder, 24 Quellen
Aufsatz (Konferenz)
Englisch
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