The invention discloses a tilt-rotor based on combination of four rotor wings and a fixed wing. The tilt-rotor is structurally characterized in that a first rotor wing, a second rotor wing, a third rotor wing and a fourth rotor wing are divided into two groups which are respectively symmetrically mounted on the two sides of a tilt-rotor body by two shafts; (1, 2) is a front motor group; (3, 4) is a rear motor group; a middle wing is horizontally mounted on the tilt-rotor body and is vertical to the tilt-rotor body; backswept wings on the two sides are respectively mounted on the two sides of the middle horizontal wing at a backswept angle of 50 degrees. According to the tilt-rotor disclosed by the invention, the four rotor wings and the fixed wing are enabled to share a set of power system to realize vertical takeoff and landing, hovering and cruise level flying; the front and rear tilting motor groups (1, 2) and (3, 4) share a set of tilting device to realize synchronous tilting by a tilting drive shaft, thereby simplifying a tilting structure and improving the operability and stability of the tilt-rotor.


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    Titel :

    Tilt-rotor based on combination of four rotor wings and fixed wing


    Beteiligte:
    WANG QING (Autor:in) / CAI ZHIHUA (Autor:in) / TAO ZEXU (Autor:in) / WANG CHUNQI (Autor:in) / DENG JUN (Autor:in) / ZHENG XINYUAN (Autor:in) / GAN YAPING (Autor:in) / HAN LIANG (Autor:in) / SHI YUMING (Autor:in) / BAI HE (Autor:in)

    Erscheinungsdatum :

    03.02.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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