A torque and pitch managed four rotor aircraft, having intersecting blades connected by synchronizing gears. The power for the rotors is provided by individual motors, one for each rotor, preferably electric. Each rotor-motor assembly includes a torque managing means comprising two torque sensors, one measuring the load torque presented by the rotors and one measuring the drive torque supplied by the motors. A feedback or servo system for each rotor causes the motors to supply a drive torque that is equal to the load torque for each rotor. A second, overriding feedback system regulates the rotors rotational speed. Speed and direction of the aircraft is effected by adjusting the fixed pitch of the individual rotors. Power is supplied through a battery and motor/generator system located elsewhere in the aircraft.


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    Titel :

    TORQUE AND PITCH MANAGED QUAD-ROTOR AIRCRAFT


    Beteiligte:
    MULLINS JOE H (Autor:in)

    Erscheinungsdatum :

    07.09.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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