An Adhesive Interleaf to Reduce Stress Concentrations Between Plys of Structural Composites

摘要: The advent of composite laminates on the airframe scene has not always led to success commensurate with high promise material properties. In many secondary structures, designs have saved weight and money. primary structure, glass Kevlar have, in some measure, given way superior properties carbon fibre composites. simpler generally met their structural goals. more complex designs, premature failures been unexpected disconcerting. reasons for these are be found fundamental laminate, i.e., tension, compression, flexure, inter-laminar shear. author suggests that a cause is Achilles heel transfer shear due bending between skins stringers “box”beams wings empenages. same problem waits fuselage structure using skin stringers. These shears wholly overlooked by stress analysts. Plies adhesive film often introduced at strategic locations where flows predicted. Neverthless, there three questionable facets contemporary approach, namely,