Structural element and method of manufacture

B - Operations – Transporting – 64 – C

Patent

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Details

B64C 3/18 (2006.01) B23K 20/12 (2006.01)

Patent

CA 2628929

The invention relates to a method for manufacturing a structural element intended for aeronautical construction, typically a wing spar comprising a web and one or more adjacent stringer elements, comprising the following steps (i) at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block, (ii) the first metal block comprises a first web portion and at least one stringer element the second metal block comprises a second web portion placing the first and second web portions end-to-end over their entire common length. The invention permits the manufacture of bifunctional or multifunctional structural elements comprising several assembled parts but whose stringers have a mechanical strength greater than that obtained by traditional methods .

L~invention concerne un procédé de fabrication d~un élément structurel destiné à la construction aéronautique, notamment un longeron d~aile comprenant une âme et un ou plusieurs éléments de lisse adjacents, le procédé comprenant les étapes suivantes : (i) au moins des premier et deuxième blocs métalliques sont mis à disposition, la limite d~élasticité en compression du premier bloc métallique étant supérieure à celle du deuxième bloc métallique, (ii) le premier bloc métallique comprend une première partie d~âme et au moins un élément de lisse, le deuxième bloc métallique comprend une deuxième partie d~âme, et les première et deuxième parties d~âme sont mises bout à bout sur toute leur longueur commune. L~invention permet de fabriquer des éléments structurels bifonctionnels ou multifonctionnels comprenant plusieurs pièces assemblées, dont les éléments de lisse offrant toutefois une plus grande robustesse mécanique que celle obtenue par les procédés classiques.

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