The invention relates to the field of airplane body structures, and provides an empennage and fuselage connecting structure and an airplane, the connecting structure comprises a first empennage connecting rib, a second empennage connecting rib, a fuselage connecting rib, a fuselage connecting corner box and a reinforcing band plate; each group of first empennage connecting ribs and each group of second empennage connecting ribs enclose a closed curve for accommodating an empennage box section; the fuselage connecting rib is used for fixedly connecting the first and second empennage connecting ribs respectively; one end of the fuselage connecting rib is fixed on the fuselage connecting corner box; the reinforcing band plates are arranged on the upper portions and the lower portions of the first empennage connecting ribs and the second empennage connecting ribs and fixed to the fuselage connecting ribs. And the fuselage connecting corner box is fixedly connected to the fuselage tail frame. The connecting structure is a box-shaped structure and has large course torsional rigidity; stress concentration at the joint is reduced based on an empennage skin dispersed load transfer mode; the fuselage connecting rib edge strips, the fuselage connecting corner boxes and the connecting band plates form a shear-resistant structure, and the lateral shear rigidity is large; the structure is simple and installation is convenient.

    本发明涉及飞机机体结构领域,提供了一种尾翼与机身的连接结构及飞机,所述连接结构包括第一尾翼连接肋、第二尾翼连接肋、机身连接肋、机身连接角盒和加强带板;每组第一和第二尾翼连接肋围合为一封闭曲线,用于容纳尾翼盒段;机身连接肋用于分别固定连接第一和第二尾翼连接肋,机身连接肋一端固定在机身连接角盒上;加强带板设置在多组第一和第二尾翼连接肋的上部和下部,并与机身连接肋固定;机身连接角盒固定连接在机身尾框上。本发明连接结构为盒型结构,具有较大航向扭转刚度;基于尾翼蒙皮分散传递载荷方式,减小连接处应力集中;机身连接肋缘条、机身连接角盒和连接带板形成抗剪结构,具有较大侧向剪切刚度;结构简单,安装方便。


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    Titel :

    Connecting structure of empennage and fuselage and airplane


    Weitere Titelangaben:

    尾翼与机身的连接结构及飞机


    Beteiligte:
    SHI JINGWEI (Autor:in) / WANG JIANLI (Autor:in) / GAO YUNFEI (Autor:in) / LIU SHENZHE (Autor:in) / SHI LIFENG (Autor:in) / WANG LIJIAN (Autor:in)

    Erscheinungsdatum :

    23.05.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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