A rotor system for electrically powered rotorcraft is described, providing the benefits of autorotation for safety, and fast thrust response, regardless of rotor inertia. The rotor system includes a rotor hub and two or more rotor blades, and an electric motor driving the rotor hub. The rotor hub includes a mechanism which adapts the collective incidence of the rotor blades in response to the torque applied by the electric motor. When there is little or no motor torque, the rotor hub holds the blades at a shallow incidence, which supports autorotative descent. During autorotative descent, the motor controller coupled to the electric motor utilizes electrical braking to moderate the rotor RPM and thrust. When the electric motor provides power to the rotor for normal flight, the collective blade incidence adjusts in response to the motor torque, providing a fast response in rotor thrust, thus avoiding the lag in rotor thrust that would occur through RPM control.


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    Title :

    Rotor system for electrically powered rotorcraft


    Contributors:

    Publication date :

    2024-07-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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