A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.


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    Title :

    PROCÉDÉ D'ASSEMBLAGE D'UNE PORTION DE FUSELAGE PAR SOUDAGE À FLEXIBILITÉ AMELIORÉE, PORTION DE FUSELAGE ET AERONEF AINSI OBTENUS


    Additional title:

    METHOD FOR ASSEMBLING A FUSELAGE PORTION BY WELDING WITH IMPROVED FLEXIBILITY, FUSELAGE PORTION AND AIRCRAFT OBTAINED THEREBY
    VERFAHREN ZUM VERBINDEN EINES RUMPFTEILS DURCH SCHWEISSEN MIT VERBESSERTER FLEXIBILITÄT, RUMPFTEIL UND SO ERHALTENES LUFTFAHRZEUG


    Contributors:

    Publication date :

    2025-04-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen