An aircraft wing (fig.3,3) has a spanwise direction extending between a root (fig.3,16) and a tip end (fig.3,15), and a chordwise direction extending between a leading edge (fig.3,13) and a trailing edge (fig.3,14). A tubular fuel tank 12a-c is located between upper and lower wing covers 10,11, with a longitudinal axis extending in the spanwise direction. The fuel tank and each cover are integrally formed using composite material, such as carbon fibre reinforced or laminate materials. Preferably, pairs of fuel tanks are integrally formed, adjacent in the chordwise direction. Each tank may have a vertical wall extending between the covers forming a spar-like structure for the wing. Preferably, the tank cross-section is a rounded square or squircle, with a noodle or filler 78 used between rounded exterior corners of adjacent tanks. Each tank may have a port (fig.4a,81) for coupling to a fuel line, and be load bearing and safe-life for the aircraft wing. A method of manufacturing an aircraft wing by laying up composites and co-bonding the fuel tank to the covers is also claimed.


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    Title :

    Aircraft wing with tubular fuel tanks


    Contributors:

    Publication date :

    2022-08-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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    European Patent Office | 2021

    Free access

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