A lift-rotor hub for electric VTOL aircraft, intended to improve safety in the event of motor power loss, to enhance agility of the aircraft, to eliminate ailerons, and to reduce energy consumption of landing approach. The example embodiment shown in figure 2a provides these benefits by coupling blade-pitch to motor torque and the aerodynamic and inertial forces on the blade. It does not require any additional connection between aircraft and rotor. Like several prior designs, it requires only the torque supplied by the motor to rotor via a rotor shaft, but unlike those designs, the example embodiment shown in figure 2a sets a default negative or fine collective-pitch, which is increased to positive collective-pitch by torque from the motor. In the event of motor power loss the invention may provide a quick transition to negative-pitch to allow autorotation, as in an autogyro craft, so that by means of sufficiently large rotors the vehicle may then descend slowly without power. The embodiment shown in figure 2a can be configured to drive a lift-rotor at near constant rotation rate when hovering, even while the lift-rotor is driven with a wide range of torques to generate a wide range of lift thrusts. Fig. 2a -25 2 2.......*\4 `


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    Titel :

    TORQE ACTUATED VARIABLE PITCH ROTOR


    Beteiligte:
    PURNELL DONALD (Autor:in)

    Erscheinungsdatum :

    2023-04-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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