The embodiment of the invention provides a fuel tank of an aircraft. The fuel tank comprises a first conical section, a middle column section and a second conical section, wherein the first conical section is connected with the middle column section in an inserted mode. The middle column section is connected with the second conical section in an inserted mode. The first conical section, the middlecolumn section and the second conical section are each of an orthogonally-arranged orthogonal network-shaped composite thin-wall structure. The fuel tank adopts a grid reinforced structure, and is high in overall rigidity and light in weight.

    本发明的实施例提供一种飞行器的燃料箱,包括:第一锥段、中间柱段和第二锥段;其中,所述第一锥段与所述中间柱段插接;所述中间柱段与所述第二锥段插接;所述第一锥段、所述中间柱段和所述第二锥段均为正置正交网络状的复合材料薄壁结构。本发明的燃料箱采用网格加筋结构,整体刚度高、重量轻。


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    Titel :

    Fuel tank of aircraft


    Weitere Titelangaben:

    一种飞行器的燃料箱


    Beteiligte:
    JI BAOFENG (Autor:in) / WANG ZHIYONG (Autor:in) / WANG FEI (Autor:in) / LIU FAJIE (Autor:in) / LIU HANYANG (Autor:in) / ZHANG PENG (Autor:in)

    Erscheinungsdatum :

    2020-10-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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