B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
B64C 1/06 (2006.01) B64F 5/00 (2006.01)
Patent
CA 2699651
Method for producing a fuselage airframe of an aircraft, wherein a plurality of fuselage sections positioned in tandem is joined together, said method comprising the steps of: a) production of an outer skin segment (1, 4, 9, 14, 20) having on the underside a continuous longitudinal opening (3, 11, 22), b) widening the outer skin segment (1, 4, 9, 14, 20) in order to introduce additional components, c) joining the outer skin segments (1, 4, 9, 14, 20) to a rigid fuselage section (23) which is already present, with the formation of a partial transverse seam (33), d) positioning a prefabricated lower shell (5, 17, 21) in the longitudinal opening (3, 11, 22), in order to close the outer skin segment (1, 4, 9, 14, 20), e) completing the partial transverse seam (33) to form a transverse seam and joining the lower shell (5, 17, 21) together with the outer skin segment (1, 4, 9, 14, 20) with the formation of at least two longitudinal seams (46, 47), and f) joining the floor frame (34) together with the outer skin segment (1, 4, 9, 14, 20). The outer skin segments (1, 4, 9, 14, 20) each have a continuous longitudinal opening (3, 11, 22), and as a result of widening or compressing sides of the outer skin segments (1, 4, 9, 14, 20), a tolerance compensation is possible when joined to a further rigid fuselage section (23). Furthermore, the longitudinal opening (3, 11, 22) provides an excellent inner accessibility through the outer skin segments (1, 4, 9, 14, 20). As a result of the fitting and joining of a lower shell (5, 17, 21), the outer skin segments (1, 4, 9, 14, 20) are joined to the further fuselage section (23) with the completion of the partial transverse seam (33) to form the encircling transverse seam (48) and with the formation of at least two continuous longitudinal seams (46, 47).
La présente invention concerne un procédé de réalisation d'une cellule de fuselage d'un aéronef, plusieurs sections de fuselage successives étant assemblées au moyen des opérations suivantes : a) fabrication d'un segment d'enveloppe extérieure (1, 4, 9, 14, 20) présentant une ouverture longitudinale (3, 11, 22) qui s'étend en continu sur le dessous; b) écartement du segment d'enveloppe extérieure (1, 4, 9, 14, 20) pour introduire des éléments supplémentaires; c) raccord du segment d'enveloppe extérieure (1, 4, 9, 14, 20) à une section de fuselage rigide (23) préexistante en formant une jointure transversale partielle (33); d) positionnement d'une coque inférieure (5, 17, 21) préfabriquée dans l'ouverture longitudinale (3, 11, 22) pour refermer le segment d'enveloppe extérieure (1, 4, 9, 14, 20); e) complètement de la jointure transversale partielle (33) pour donner une jointure transversale et assemblage de la coque inférieure (5, 17, 21 ) et du segment d'enveloppe extérieure (1, 4, 9, 14, 20) en formant au moins deux jointures longitudinales (46, 47); et f) assemblage de la structure de plancher (34) et du segment d'enveloppe extérieure (1, 4, 9, 14, 20).
Airbus Operations Gmbh
Oyen Wiggs Green & Mutala Llp
LandOfFree
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