An adaptive flight control system for controlling the pitch of blades of a propulsive propeller of a hybrid helicopter as a function of the return value of the pitch. The adaptive flight control system comprises control means supplying the pitch control order, a piloting member controlling variation of the pitch, and piloting means applying a control gain in order to transform the control order into a setpoint, and transmitting the setpoint to the piloting member. The piloting means include information return means applying a return gain that is variable to the return value of the variation of the pitch to the piloting means, also modifying the control gain as a function of the return value.


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    Titel :

    ADAPTIVE FLIGHT CONTROL SYSTEM FOR THE YAW AND THRUST FLIGHT CONTROLS OF A HYBRID HELICOPTER


    Beteiligte:
    BIHEL JEAN-ROMAIN (Autor:in) / GROLL ARNAUD (Autor:in) / BIEST ROMUALD (Autor:in) / SASSI ZOUHAIR (Autor:in)

    Erscheinungsdatum :

    2017-05-25


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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