Structural composite material structures with a metal...

C - Chemistry – Metallurgy – 23 – C

Patent

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Details

C23C 4/02 (2006.01) C23C 4/06 (2006.01)

Patent

CA 2694559

Structural component of non-conductive composite material, particularly for aircraft (panel (1), frame (3), stringer (2), etc), that comprises in the surface a metal-type layer (4), such that the mentioned structural component together with the remaining metallized structural components can provide the aircraft with the sufficient conductive metal mass. According to a second aspect of the invention, a metallization method is proposed in the manufacture of a structural component, particularly for aircraft, made of composite material, which method allows the geometric configuration of the add-on by applying it in an extensive or limited manner to predetermined contours by means of using templates. This constructive feature allows creating integrated electric circuits in the airplane structure by means of creating independent tracks with different widths and thicknesses.

La présente invention concerne un élément structurel en matériau composite non conducteur, notamment pour un aéronef (panneau (1), châssis (3), lisse (2) et autres) qui comporte dans sa surface, une couche de type métallique (4) de sorte que l'élément structurel selon l'invention et les autres éléments structurels métallisés constituent pour l'aéronef, une masse métallique conductrice suffisante. Selon un aspect de l'invention, un procédé de métallisation est proposé dans la fabrication d'un élément structurel, notamment pour un aéronef, réalisé en matériau composite, ledit procédé assurant la configuration géométrique de la partie ajoutée du fait de son application effectuée de manière extensive ou limitée sur des contours prédéterminés au moyen de gabarits. Cette caractéristique de construction permet de créer des circuits électriques intégrés dans la structure d'aéronef par la création de tracés indépendants de différentes largeurs et épaisseurs.

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