A rotor (3, 5) is described that comprises: a hub (6, 8); a plurality of blades (7, 14); each blade (7, 14) extends along an axis (B) and comprises: a leading edge (20) and a trailing edge (21); a top surface (22) and a bottom surface (23), a chord (15) joining points of the leading edge (20) and the trailing edge (21); and a closed shell (30) made of composite material and adapted to withstand the torque directed along a first axis (B) of the blade (7, 14); the shell (30) comprises a first and a second element (31, 32) separate from each other, delimiting the respective shell (30) on mutually opposite sides; a first connection element (34) arranged on the side of the associated leading edge (20) and interposed between the first ends (37, 38) of the respective first and second elements (31, 32); and a third element (80) connected to the associated first and second elements (31, 32) and arranged on the side of the leading edge (20); the first connection element (34) is connected to respective first faces (100), and the third element (80) is connected to respective second faces (101) of the first and second elements (31, 32); the blade (7, 14) comprises a fourth element (70) interposed between the fourth element (80) and the first connection element (34).
ROTOR FOR A HOVER-CAPABLE AIRCRAFT
ROTOR FÜR EIN HOVER-FÄHIGES FLUGZEUG
ROTOR POUR UN AERONEF CAPABLE DE VOL STATIONNAIRE
2020-12-30
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |