A rotor (8, 8', 106"', 106"", 106""', 106""") for an aircraft (1, 100) is described, comprising an input shaft (10, 108) rotatable around a first axis (C, I); an output member (15, 112) rotatable around a second axis (D, J); a coupling element (20, 20', 20", 20"') functionally interposed between the input shaft (10, 108) and the output member (15, 112) and adapted to transmit the motion from the input shaft (10, 108) to the output member (15, 112); the coupling element (20, 20', 20", 20"') is configured to allow, in use, a fixed or variable inclination between the respective first and second axes (C, I, D, J); the coupling element (20, 20', 20", 20"') comprises at least a first corrugated element (21, 22, 25, 120"', 121"', 120"", 121"", 122"") made of an elastically deformable material; the first corrugated element (21, 22, 25; 120"', 121"'; 120"", 121"", 122"") allows the inclination through elastic deformation.
ROTOR FOR AN AIRCRAFT CAPABLE OF HOVERING
ROTOR FÜR EIN FLUGZEUG, DAS SCHWEBEFÄHIG IST
ROTOR POUR UN AÉRONEF CAPABLE DE VOL STATIONAIRE
2022-08-03
Patent
Electronic Resource
English