The present invention relates to laminate structures. In order to provide a laminate construction with increased size and improved stability, an aircraft panel (10) with a laminate structure (12) is provided that comprises a stack of a plurality of metal sheet layers (14), at least one fibre reinforced adhesive layer (16), and at least one cover segment (18). At least one outer layer of the metal sheet layers comprises at least two separate metal sheets (20, 22) that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint (24) of the two separate metal sheets. The at least one fibre reinforced adhesive layer comprises fibre elements (26) embedded in a matrix structure (28). 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 (30) of the laminate structure, the cover segment covering a region (32) of the overlapping joint. Still further, the at least one cover segment comprises at least one layer of reinforcement fibres (34).
Joints in fibre metal laminates
Verbindungen in Fasermetalllaminaten
Joints dans des stratifiés métalliques fibreux
26.06.2024
Patent
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2001
|Fibre metal laminates : an introduction
TIBKAT | 2001
|Fibre metal laminates : an introduction
SLUB | 2001
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