The invention relates to a heat dissipation system and method for an aircraft wing fuel tank, belongs to the technical field of aircraft system design, and can realize a fuel heat dissipation function of the aircraft wing fuel tank, reduce the oil temperature in the fuel tank and improve the cooling capacity stored in the fuel. The heat dissipation system comprises a wing fuel tank, a fuel oil pipeline, a skin heat exchanger, an electric drive pump, a liquid level meter, a first switch valve, a second switch valve and a controller. The skin heat exchanger is arranged on a lower skin of the wing, and the skin heat exchanger is in fusion connection with the lower skin; the wing fuel tank is communicated with the skin heat exchanger through the fuel pipeline to form a loop; the wing fuel tank, the first switch valve, the skin heat exchanger, the electric drive pump and the second switch valve are sequentially arranged in the fuel flowing direction. The liquid level meter is arranged in the wing fuel tank; the first switch valve, the second switch valve, the electric drive pump and the liquid level meter are all electrically connected with the controller.

    本发明涉及一种飞机机翼油箱散热系统及方法,属于飞机系统设计技术领域,能够实现飞机机翼油箱燃油散热功能,降低燃油箱中油温,提升燃油中储存的冷量;该散热系统包括机翼油箱、燃油管路、蒙皮换热器、电驱动泵、液位计、第一开关阀、第二开关阀和控制器;所述蒙皮换热器设置在机翼的下蒙皮上,且所述蒙皮换热器与所述下蒙皮融合连接;所述机翼油箱通过所述燃油管路与所述蒙皮换热器连通形成回路;随燃油流动方向,依次设有所述机翼油箱、所述第一开关阀、所述蒙皮换热器、所述电驱动泵和所述第二开关阀;所述液位计设置在所述机翼油箱内;所述第一开关阀、所述第二开关阀、所述电驱动泵和所述液位计均与所述控制器电连接。


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    Titel :

    Aircraft wing fuel tank heat dissipation system and method


    Weitere Titelangaben:

    一种飞机机翼油箱散热系统及方法


    Beteiligte:
    XIE LIANG (Autor:in) / LI PENG (Autor:in) / HE XUNAN (Autor:in) / ZHOU QIAO (Autor:in) / FENG YUN (Autor:in)

    Erscheinungsdatum :

    2023-06-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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