An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.


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    Titel :

    MAIN ROTOR ROTATIONAL SPEED CONTROL FOR ROTORCRAFT


    Weitere Titelangaben:

    HAUPTROTORDREHZAHLSTEUERUNG FÜR DREHFLÜGELFLUGZEUG
    COMMANDE DE VITESSE DE ROTATION DE ROTOR PRINCIPAL POUR GIRAVION


    Beteiligte:
    WEINER STEVEN D (Autor:in) / EADIE WILLIAM J (Autor:in)

    Erscheinungsdatum :

    2020-05-06


    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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