The invention provides an electric culvert vertical lifting co-rotor aircraft which comprises a fuselage, a main wing is arranged in the middle of the fuselage, and engines are connected to the positions, located on the front side and the rear side of the main wing, of the fuselage through engine flight attack angle electric adjusting mechanisms correspondingly; an aileron is arranged on the engine flight attack angle electric adjusting mechanism; the engines arranged front and back are mutually staggered up and down, and the front aileron, the main wing and the rear aileron are sequentially arranged from bottom to top. According to the electric culvert vertical lifting co-rotor aircraft, the front side aileron, the main wing and the rear side aileron are arranged at the lower height, the middle height and the upper height respectively, mutual influence of the engine and the wings when the engine and the wings play respective functions is avoided, and meanwhile the flight stability is improved.

    本发明提出了一种电涵垂升共转翼飞机,包括机身,机身中部设有主翼,机身上位于主翼的前、后两侧均各自通过发动机飞行攻角电动调节机构连接有发动机;发动机飞行攻角电动调节机构上设有副翼;前、后排列的发动机相互上下错开,前侧副翼、主翼和后侧副翼由下往上依次排列。本发明提供的电涵垂升共转翼飞机,前侧副翼、主翼、后侧副翼分设在下、中、上三个高度上,避免发动机和机翼在发挥各自功能时相互影响,同时增加了飞行的稳定性。


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    Titel :

    Electric culvert vertical lifting co-rotor aircraft


    Weitere Titelangaben:

    电涵垂升共转翼飞机


    Beteiligte:
    ZENG ZHAODA (Autor:in) / WANG HAO (Autor:in) / SHAN XIAOWEN (Autor:in) / JING XIAOHUI (Autor:in)

    Erscheinungsdatum :

    2023-08-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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