An integrated auxiliary oil tank system for a wing body fairing of an airplane is characterized in that the auxiliary oil tank system is crosslinked with an oil supply chamber of the airplane, the oil supply chamber is positioned in a wing box of the airplane, the auxiliary oil tank system comprises an auxiliary oil tank and an auxiliary oil supply system associated with the auxiliary oil tank, the auxiliary oil tank is positioned at the rear part of the wing body fairing, and the auxiliary oil supply system is connected with the auxiliary oil tank. The surface curvature of the auxiliary fuel tank on the front side of an aircraft wing meets the wing body rectification requirement, the auxiliary fuel tank is fixed to an aircraft body through a supporting structure, and the auxiliary fuel supply system supplies fuel of the auxiliary fuel tank to a fuel supply chamber of an aircraft.

    一种飞机翼身整流罩一体化辅助油箱系统,该辅助油箱系统与飞机的供油室交联,供油室位于飞机的机翼翼盒内,所述的辅助油箱系统含有辅助油箱和与辅助油箱关联的辅助供油系统,所述的辅助油箱位于翼身整流罩的后部,飞机机翼的前侧,辅助油箱的表面曲率符合翼身整流要求,辅助油箱通过支撑结构固定在飞机机体上,辅助供油系统将辅助油箱的燃油提供给飞机的供油室。


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    Title :

    Aircraft wing body fairing integrated auxiliary fuel tank system


    Additional title:

    一种飞机翼身整流罩一体化辅助油箱系统


    Contributors:
    LI CHEN (author) / ZHANG ZHIGANG (author) / ZHAO ZHIWEI (author) / SHI SHAONAN (author)

    Publication date :

    2024-06-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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



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