An aircraft panel with a laminate structure is provided that comprises a stack of a plurality of metal sheet layers, at least one fibre reinforced adhesive layer, and at least one cover segment. At least one outer layer of the metal sheet layers comprises at least two separate metal sheets that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets. The at least one fibre reinforced adhesive layer comprises fibre elements embedded in a matrix structure. One of the at least one fibre reinforced adhesive layers is arranged between two adjacent metal sheet layers. Further, the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint. Still further, the at least one cover segment comprises at least one layer of reinforcement fibres.
JOINTS IN FIBRE METAL LAMINATES
2015-08-13
Patent
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2001
|Fibre metal laminates : an introduction
TIBKAT | 2001
|Fibre metal laminates : an introduction
SLUB | 2001
|