A rotor hub system includes a rotor rotation axis, a flap hinge connected to the rotor rotation axis and enabling flapping motion of a rotor blade, a lead-lag hinge connected to the flap hinge and enabling lead-lag motion of the rotor blade, a first hub to which one end of the rotor blade is fixed, a rotating pitch control actuator connected to the first hub and rotating the first hub to enable pitching motion of the rotor blade, and a second hub equipped with the rotating pitch control actuator and hinged to the lead-lag hinge.
ROTOR HUB SYSTEM WITH ROTATING PITCH CONTROL ACTUATOR
2024-04-18
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
ACTUATOR FOR PITCH CONTROL FOR A ROTOR SYSTEM OF AN AIRCRAFT
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