Coupling element for connecting two longitudinal stiffening...

Details Coupling element for connecting two longitudinal stiffening... Coupling element for connecting two longitudinal stiffening...

B - Operations, Transporting

64

C

B64C 1/06 (2006.01) B64C 1/12 (2006.01) F16B 5/06 (2006.01)

Patent

CA 2705426

The invention relates to a coupling element (1, 15, 47) for interconnecting stringers (38, 39) when joining two fuselage sections (32, 33) by means of at least one cross butt bracket (37), the fuselage sections comprising on their interior respective pluralities of stringers (38, 39) arranged on fuselage skins (35, 36) and frames (41), the coupling element having a root flange (2, 16, 46) and a frame flange (3, 17, 48). The coupling element establishes a connection between the opposite stringers (38, 39), the frame (41) and the fuselage skins (35, 36) or the cross butt bracket (37) so that the coupling element (1, 15, 47) allowing not only a connection of the stringer root but also a flank connection of the stringers.

Élément d'accouplement (1, 15, 47) pour relier des lisses (38, 39) au cours de l'assemblage de deux sections de fuselage (32, 33) au moyen d'au moins une éclisse de raccordement transversal (37), sachant : que les sections de fuselage présentent respectivement sur le côté intérieur une pluralité de membrures annulaires (41) et de lisses (38, 39) disposées sur des revêtements de cellules de fuselage (35, 36) ; que l'élément d'accouplement présente une bride de base (2, 16, 46) et une bride de membrure (3, 17, 48) ; et que l'élément d'accouplement réalise une liaison respective entre les lisses opposées (38, 39), la membrure annulaire (41) ainsi que les revêtements de cellules de fuselage (35, 36) ou respectivement l'éclisse de raccordement transversal (37), de sorte que l'élément d'accouplement (1, 15, 47) permet, en plus d'un rattachement de la base de la lisse, un rattachement au niveau du flanc des lisses.

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