Skin-stringer design for composite wings

摘要

SKIN-STRINGER DESIGN FOR COMPOSITE WINGS Composite skin-stringer structures which reduce or eliminate the risk of delamination at the skin-stringer interface. This can be accomplished by arranging ply directions (i.e., the angles of the fibre paths of the ply) in a layup in a way such that for the dominant loading, the skin (4) and stringer (2) will each deform in a way that reduces relative opening (fracture Mode I) and/or sliding (fracture Mode II) and/or scissoring (fracture Mode III) at the skin-stringer interface. This is possible when coupling between specific deformations modes is purposefully activated instead of being suppressed. The ply directions in the stringer (2) are adjusted so that the stringer (2) deforms in a controlled fashion to suppress or "close" cracks that are about to form-before the undesirable modes of failure form-as load is applied. C>o ao