Support for an aircraft structural component produced in a...

B - Operations – Transporting – 64 – C

Patent

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B64C 1/06 (2006.01)

Patent

CA 2732934

The invention relates to an elongated supporting pillar (20) for a high- strength structural component (2), wherein the supporting pillar (20) is designed to absorb bending forces that act transversely to a longitudinal direction of extension of the supporting pillar (20). The supporting pillar (20) comprises a wall (26) which at least partially encloses an elongated cavity (28) of the supporting pillar (20). A reinforcement structure (36; 38) is arranged within the cavity (28) and transversely to the direction of longitudinal extension in such a manner that the reinforcement structure (36; 38) can absorb at least some of the bending forces. The reinforcement structure (36; 38) is designed integrally with the wall (26), wherein both the wall (26) and the reinforcement structure (36; 38) comprise a meltable material.

Linvention concerne un support allongé (20) pour composant structural (2) à haute résistance. Selon linvention, le support (20) est conçu pour absorber les forces de flexion qui agissent transversalement à une direction de projection longitudinale du support (20). Le support (20) présente une paroi (26) qui entoure au moins partiellement un espace creux (28) allongé du support (20). À lintérieur de lespace creux (28) et transversalement par rapport à la direction longitudinale est disposée une structure de renforcement (36; 38) de sorte que la structure de renforcement (36; 38) peut absorber au moins une partie des forces de flexion. La structure de renforcement (36; 38) est réalisée dune seule pièce avec la paroi (26) et, selon linvention, la paroi (26) ainsi que la structure de renforcement (36; 38) sont toutes deux réalisées dans un matériau fusible.

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