Aircraft including stiffener edge junctions and method for...

B - Operations – Transporting – 64 – C

Patent

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Details

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

Patent

CA 2702889

The invention relates to a system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners (4) interrupted by reinforcing frames (5). At said interruptions, the stresses experienced by the stiffeners (4) must be transmitted despite the presence of the reinforcing frames (5). Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the invention includes the creation of battens (15) that cover the ends (16) of consecutive sections (6) of a stiffener (4) and the skin (7) of the fuselage (1), extending under the reinforcing frame (5) in order to join said two consecutive sections (6).

L'invention se rapporte à un système de transmission des efforts lors d'une intersection de cadre de renfort et de raidisseur dans un fuselage et procédé de fabrication d'un tel système. Un fuselage d'avion comporte des raidisseurs (4) interrompus par des cadres (5) de renforts. Lors de ces interruptions, les efforts subits par les raidisseurs (4) doivent être transmis malgré la présence des cadres (5) de renforts. Les solutions connues sont difficiles à fabriquer et à installer et n'offrent pas un cheminement d'efforts simple quand elles sont composées uniquement de matériaux composites. L'invention prévoit, pour résoudre ce problème, de créer des éclisses (15) recouvrant les extrémités (16) des sections (6) consécutives d'un raidisseur (4) et la peau (7) du fuselage (1) en s'étendant sous le cadre (5) de renfort pour joindre ces deux sections (6) consécutives.

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