B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
B64C 1/00 (2006.01)
Patent
CA 2704764
A transverse splicing plate (1, 19, 37) for producing a fuselage of an aircraft by connecting several CFP fuselage sections (5, 26, 27, 43) that have in particular been produced in the winding method, in each case by forming a transverse seam (14, 28, 48), wherein the flexible transverse splicing plate (1, 19, 37) is of a multilayer construction, in other words it comprises a multitude of plate segments (7-9, 20-23, 38-40) arranged one above the other, wherein each of the plate segments (7-9, 20-23, 38-40) comprises a multitude of longitudinal slits (10, 11, 44, 45), each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections (5, 26, 27, 43) to be joined, in which tolerance compensation a sliding movement between the sub-plates (17, 18, 50, 51) of the plate segments (7-9, 20-23, 38-40) arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections (5, 26, 27, 43), and wherein on the inside the ends (6, 24, 25, 41) of the fuselage sections (5, 26, 27, 43) comprise chamfers (35, 36); as well as a method for producing a connection between two CFP fuselage sections (5, 26, 27, 43), which have preferably been produced in the winding method, by means of a transverse splicing plate (1, 19, 37) according to the invention.
L'invention concerne un couvre-joint transversal (1, 19, 37) pour réaliser une cellule de fuselage d'un aéronef par assemblage de plusieurs sections de fuselage (5, 26, 27, 43) en plastique renforcé de fibres de carbone, produites de préférence par un procédé d'enroulement, de manière à former un joint transversal (14, 28, 48) respectif. Ce couvre-joint transversal (1, 19, 37) flexible comprend plusieurs couches, à savoir une pluralité de segments de couvre-joint (7-9, 20-23, 38-40) superposés, chacun de ces segments de couvre-joint (7-9, 20-23, 38-40) présentant une pluralité de fentes longitudinales (10, 11, 44, 45) qui peuvent chacune exécuter indépendamment les unes des autres de légers mouvements de flexion radiaux pour compenser les tolérances dans le sens radial entre les sections de fuselage (5, 26, 27, 43) à assembler. Un mouvement de glissement se produit entre les parties (17,18, 50, 51) des segments de couvre-joint (7-9, 20-23, 38-40) superposés, dans le sens axial des sections de fuselage (5, 26, 27, 43) en forme de tonneau, les extrémités (6, 24, 25, 41) des sections de fuselage (5, 26, 27, 43) présentant sur leur côté intérieur un biseau (35, 36). L'invention concerne également un procédé d'assemblage de deux sections de fuselage (5, 26, 27, 43) en plastique renforcé de fibres de carbone, produites de préférence par un procédé d'enroulement, au moyen d'un couvre-joint transversal (1, 19, 37) selon l'invention.
Airbus Operations Gmbh
Mcfadden Fincham
LandOfFree
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