A flight control computer (FCC) may implement automatic rotor tilt control by gathering or receiving, as inputs, airspeed or a commanded airspeed for the aircraft, acceleration or a commanded acceleration for the aircraft, pitch attitude of the aircraft and pilot pitch bias commands for the aircraft, a rotor tilt angle, and/or the like. The FCC calculates, from the airspeed, the commanded airspeed, the acceleration, the commanded acceleration, the pitch attitude, the pilot pitch bias commands, and/or the like, a commanded rotor tilt angle for the aircraft. From the aircraft rotor tilt angle and the commanded rotor tilt angle, the FCC calculates a rotor tilt angle error for the aircraft, and from the rotor tilt angle error, calculates a rotor tilt rate command for the aircraft. The FCC outputs the resulting rotor tilt rate command to (an) aircraft flight control element actuator(s) to tilt the aircraft rotor.


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    Titel :

    AUTOMATIC ROTOR TILT CONTROL


    Beteiligte:

    Erscheinungsdatum :

    29.06.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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