The invention relates to leading edge device (10) for an aerodynamic component (100), comprising a skin element (12) defining an aerodynamic profile and being formed of a single-piece structure, wherein the skin element (12) has an inner surface (14) and an outer surface (16). The leading edge device (10) further comprises a support structure (20) having at least one support element (22), wherein the at least one support element (22) is bonded to the inner surface (14) of the skin element (12) via a connecting zone (15) that at least partially extends across the inner surface (14) of the skin element (12). The outer surface (16) of the skin element (12) defines a surface region (17) opposite to the connecting zone (15) where the outer surface (16) is closed. The invention also relates to a method for manufacturing a leading edge (10) device for an aerodynamic component (100).
LEADING EDGE DEVICE FOR AN AERODYNAMIC COMPONENT AND METHOD FOR MANUFACTURING A LEADING EDGE DEVICE FOR AN AERODYNAMIC COMPONENT
VORDERKANTENVORRICHTUNG FÜR EIN AERODYNAMISCHES BAUTEIL UND VERFAHREN ZUR HERSTELLUNG EINER VORDERKANTENVORRICHTUNG FÜR EIN AERODYNAMISCHES BAUTEIL
DISPOSITIF DE BORD D'ATTAQUE POUR UN COMPOSANT AÉRODYNAMIQUE ET PROCÉDÉ DE FABRICATION D'UN DISPOSITIF DE BORD D'ATTAQUE POUR UN COMPOSANT AÉRODYNAMIQUE
2024-05-22
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2025
|European Patent Office | 2025
|Leading edge buckling due to aerodynamic heating
SLUB | 1960
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