METHOD FOR ASSEMBLING A FUSELAGE PORTION BY WELDING WITH IMPROVED FLEXIBILITY, FUSELAGE PORTION AND AIRCRAFT OBTAINED THEREBY

• Main Authors: DE KERGOMMEAUX, Matthieu, DENTESANO, Johan, AGUERA, Damien
• Format: Patent
• Language: English; French; German
• Published: 03.04.2024
• Subjects: AEROPLANES; AIRCRAFT; AVIATION; COSMONAUTICS; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR; HELICOPTERS; PERFORMING OPERATIONS; TRANSPORTING

La présente invention vise à proposer un procédé d'assemblage de panneaux d'aéronef par soudage permettant d'en améliorer la flexibilité. Des panneaux (26, 28) sont aboutés selon des lignes de jonction longitudinales et fixés l'un à l'autre par leurs bords (30, 32) longitudinaux par soudage sans que les extrémités longitudinales (30A, 30B, 32A, 32B) de leurs bords (30, 32) soudés ne soient liées entre elles. Des viroles (38, 40) longitudinales sont fixées de manière à recouvrir partiellement la surface concave des panneaux (26, 28) au moins partiellement au niveau desdites extrémités (30A, 30B, 32A, 32B). L'absence de soudage aux extrémités apporte la flexibilité recherchée. La présente invention couvre également les portions de fuselage formées par l'assemblage de panneaux selon ce procédé ainsi que l'aéronef comprenant de telles portions. 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.