A helicopter (1) having an anti-torque rotor (4') comprising: a supporting body (14'); a drive shaft (10') which rotates about a first axis (B) with respect to the supporting body (14'); a hub (11) connected operatively to drive shaft (10') for rotation about the first axis (B); at least one pair of blades (12) which are connected operatively to hub (11) for rotation about the first axis (B), and angularly movable with respect to second axes (D) to adjust the pitch angle of the blades (12); and an actuator (16') which can be operated to rotate the blades (12) about the second axes (D) to adjust the pitch angle of the blades (12); the actuator (16') has an electric motor (25') which generates torque along the first axis (B); and a mechanical stage (30') interposed between the electric motor (25') and the blades (12), and designed to convert the torque into rotation of the blades (12) about the respective second axes (D); the electric motor (25') fixed to the supporting body (14').
РУЛЕВОЙ ВИНТ ВЕРТОЛЕТА
2018-09-10
Patent
Electronic Resource
Russian
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2019