A flapping wing aerial vehicle comprises at least a first and second wing, a support structure, to which the wings are connected, at least one flapping mechanism, comprising at least a first spar and a flapping actuator, the at least first spar being attached to the wing membrane of the first wing and/or the second wing, the flapping actuator being configured to pivot said at least one spar with respect to a flapping pivot axis substantially parallel to a Z-axis for inducing a flapping motion of said first wing and/or second wing; a first attitude control mechanism, configured to induce a pitch moment; a second attitude control mechanism, configured to induce a yaw moment; a third attitude control mechanism, configured to induce a roll moment; and an attitude controller, wherein the first attitude control mechanism, the second attitude control mechanism, and the third attitude control mechanism are separate mechanisms.


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    Titel :

    FLAPPING WING AERIAL VEHICLE


    Beteiligte:
    KARASEK MATEJ (Autor:in)

    Erscheinungsdatum :

    04.06.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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