The invention discloses a pitching and yawing conditional decoupling empennage regulating mechanism for an aircraft. The regulating mechanism comprises an empennage fixed part and an empennage movable part arranged at the tail part of the aircraft, as well as a yawing steering engine and a pitching steering engine arranged on the aircraft body, wherein the empennage fixed part is provided with an oscillating bearing; a rotating shaft is connected in the oscillating bearing in a sleeved manner; the rotating shaft is fixedly connected with the empennage movable part; the yawing steering engine and the rotating shaft are in rigid transmission connection through a yawing connecting rod; the pitching steering engine and the empennage movable part are in rigid transmission connection through a pitching connecting rod; the pitching steering engine and the yawing steering engine are arranged in the fuselage of the aircraft body; the structural form that a driving steering engine is arranged at the tail part of the aircraft traditionally is abandoned, so that the tail part weight of the aircraft is effectively reduced. Compared with the traditional movement decoupling empennage regulating mechanism, the pitching and yawing conditional decoupling empennage regulating mechanism, disclosed by the invention, can realize mechanical decoupling of an empennage mechanism under certain path instead of decoupling through software resolving and greatly improves the reliability, stability and regulation precision of a system.


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    Titel :

    Pitching and yawing conditional decoupling empennage regulating mechanism for aircraft


    Beteiligte:
    XU WENFU (Autor:in) / LI GUANGMING (Autor:in) / PAN ERZHEN (Autor:in) / LUO CAN (Autor:in)

    Erscheinungsdatum :

    16.12.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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    Baranoff, A V / Hopf, L | NTRS | 1931


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