The invention relates to a design of an airplane aileron execution mechanism. The problem that a combined servo steering engine is difficult to arrange on an airplane wing surface which is thin in appearance and of which the internal space of an airplane wing structure is limited can be solved. According to the airplane aileron execution mechanism, an electric hydraulic control distribution mechanism arranged on an airplane body can control left side acting cylinders arranged on a left aileron and right side acting cylinders arranged on a right aileron, so that a left control plane and a right control plane are driven to rotate, and the control plane of the airplane wing surface which is thin in appearance and of which the internal space of the airplane wing structure is limited can be driven through the combined servo steering engine.


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    Titel :

    Airplane aileron execution mechanism


    Beteiligte:
    SUN HUANYU (Autor:in) / XU WENLIANG (Autor:in) / SUN YONGHUAN (Autor:in) / ZHAO ZHONGRUI (Autor:in) / ZHAO DONGBAI (Autor:in)

    Erscheinungsdatum :

    2015-09-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge