Integrated multispar torsion box of composite material

B - Operations – Transporting – 29 – C

Patent

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Details

B29C 70/34 (2006.01) B64C 3/00 (2006.01)

Patent

CA 2685478

The invention relates to a structure comprising a multispar torsion box made from composite material and intended for an aircraft, consisting of: a lower coating (12); an upper coating (11); multiple spars (9), each spar comprising a flange (13) and a web (14); multiple stringers (10) in the lower coating (12); and multiple stringers (10) in the upper coating (11). The invention is characterised in that the torsion box structure is produced by joining U-shaped unit structural elements provided with a flap (16) and C-shaped unit structural elements provided with a flap (17). The invention also relates to a method for producing a multispar torsion box structure made from composite material and intended for an aircraft.

L'invention concerne une structure intégrée de caisson de torsion multi-longerons en matériau composite pour aéronef, comprenant un revêtement inférieur (12), un revêtement supérieur (11), plusieurs longerons (9), dont chacun comprend une semelle (13) et une âme (14), plusieurs lisses (10) situées dans le revêtement inférieur (12) et plusieurs lisses (10) situées dans le revêtement supérieur (11). L'invention se caractérise en ce que la structure intégrée de caisson de torsion susmentionnée s'obtient par assemblage d'éléments structuraux unitaires en forme de U (15), d'éléments structuraux unitaires en forme de U avec jupe (16), et d'éléments structuraux unitaires en forme de C avec jupe (17). L'invention concerne également un procédé de fabrication d'une structure d'un caisson de torsion de type multi-longerons en matériau composite pour aéronef.

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