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.
METHOD FOR ASSEMBLING A FUSELAGE PORTION USING WELDING, WITH IMPROVED FLEXIBILITY, AND FUSELAGE PORTION AND AIRCRAFT THUS OBTAINED
04.04.2024
Patent
Elektronische Ressource
Englisch
Europäisches Patentamt | 2025
|Europäisches Patentamt | 2021
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