The invention discloses an aircraft tail. According to the technical scheme, for a vertically taking-off and landing fixed-wing aircraft of Application No. 2015203521439, the aircraft tail aims at reducing resistance during rotary flight, accurately adjusting a aircraft landing point and adjusting the aircraft stability during rotary takeoff and landing. The aircraft tail consists of a full-automatic vertical tail, a full-automatic vertical tail strengthening beam or full-automatic vertical tail strengthening sheet, a full-automatic vertical tail rotation shaft, a full-automatic vertical tail server, an auxiliary horizontal tail, an auxiliary horizontal tail rotation shaft and an auxiliary horizontal tail server, wherein the full-automatic vertical tail can have a function of performing forward and reverse 180-degree rotation around the straight line parallel to the vertical axis of the aircraft under the control of the full-automatic vertical tail server, and the auxiliary horizontal tail can have a function of performing forward and reverse 90-degree rotation around the straight line parallel to the longitudinal axis of the aircraft under the control of the auxiliary horizontal tail server.


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    Titel :

    Aircraft tail


    Beteiligte:
    ZHANG BIN (Autor:in)

    Erscheinungsdatum :

    2015-12-09


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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