An anti-torque rotor (4, 4') of a helicopter (1), having : a supporting body (14, 14'); a drive shaft (10, 10') which rotates about a first axis (B) with respect to the supporting body (14, 14'); a hub (11) connected operatively to drive shaft (10, 10') and angularly fixed with respect to first axis (B); at least one blade (12) which is connected operatively to hub (11), is angularly fixed with respect to first axis (B), and is angularly movable with respect to a second axis (D) to adjust the pitch angle of blade (12); and an actuator (16, 16') which can be operated to rotate blade (12) about second axis (D) to adjust the pitch angle of blade (12); actuator (16, 16') has an electric motor (25, 25') which generates torque along the first axis (B); and a mechanical stage (30, 30') interposed between the electric motor (25, 25') and blade (12), and designed to convert the torque into rotation of blade (12) about the respective second axes (D); electric motor (25, 25') is fixed to supporting body (14, 14').
Helicopter anti-torque rotor
Drehmomentausgleichsrotor eines Hubschraubers
Rotor anticouple d'hélicoptère
2016-02-10
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |