In accordance with an embodiment, a method of operating a rotorcraft (101) includes transitioning from a first mode to a second mode when a velocity of the rotorcraft (101) exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time. In the first mode, the translational speed of the rotorcraft (101) is determined based on a pilot stick signal, and in the second mode, an output of an attitude rate controller is proportional to an amplitude of the pilot stick signal


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    Titel :

    ROTORCRAFT CONTROL MODE TRANSITION SMOOTHING


    Weitere Titelangaben:

    DREHFLÜGLERSTEUERMODUSÜBERGANGSGLÄTTUNG
    LISSAGE DE LA TRANSITION DU MODE DE COMMANDE D'UN GIRAVION


    Beteiligte:
    KIM SUNG KYUN (Autor:in)

    Erscheinungsdatum :

    17.04.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge



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