The invention relates to a leading-edge device (1) for an aerodynamic component (120). The leading-edge device (1) comprises a first skin element (10) having an inner surface (11) and an aerodynamic outer surface (12), and further comprises a second skin element (20) having an inner surface (21) and an aerodynamic outer surface (22). The leading-edge device (1) further comprises a first coupling element (13) protruding from the inner surface (11) of the first skin element (10) and a second coupling element (23) protruding from the inner surface (21) of the second skin element (20). The first and second coupling elements (13, 23) are coupled to each other in a coupling region (30). The first skin element (10) and the first coupling element (13) are formed as a single-piece structure. The invention also relates to a method for manufacturing a leading-edge device (1) 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
26.03.2025
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Europäisches Patentamt | 2025
|Europäisches Patentamt | 2024
|Europäisches Patentamt | 2021
|Leading edge buckling due to aerodynamic heating
SLUB | 1960
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