A heated leading-edge structure (2) for an aircraft is proposed, comprising a leading edge panel (4) having an outer surface (6) configured to be contacted by an ambient flow, and an inner surface (8) opposite the outer surface (6), a rear panel (10) arranged at least partially arranged in a distance to the inner surface (8), a closed chamber (20) inside the leading-edge structure (2), a heating device (22) attached inside the chamber (20), and an air conveying device (24) in fluid communication with the heating device (22), wherein the air conveying device (24) is configured to convey air from inside the chamber (20) through the heating device (22) to be heated and returned to the chamber (20), such that a circulating flow of heated air is created inside the chamber (20).
HEATED LEADING-EDGE STRUCTURE FOR AN AIRCRAFT
BEHEIZTE VORDERKANTENSTRUKTUR FÜR EIN FLUGZEUG
STRUCTURE DE BORD D'ATTAQUE CHAUFFÉ POUR AÉRONEF
2024-05-22
Patent
Electronic Resource
English