Hybrid composite-metal aircraft landing gear and engine...

B - Operations – Transporting – 32 – B

Patent

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Details

B32B 15/08 (2006.01) B64C 1/06 (2006.01)

Patent

CA 2666595

A hybrid composite-metal component is provided. The component includes an elongate inner metal piece, an outer metal piece disposed about at least a portion of the inner metal piece, and composite material disposed between the inner metal piece and the outer metal piece. The component may further include at least one of a seal and at least one fastener joining the inner metal piece and outer metal piece. Both the inner metal piece and the outer metal piece may include at least one tapered end. The tapered ends of both the inner metal piece and the outer metal piece each may include a double taper.

L'invention concerne un composant composite-métal hybride. Le composant comprend une pièce de métal interne allongée, une pièce de métal externe disposée autour d'au moins une portion de la pièce de métal interne, et un matériau composite disposé entre la pièce de métal interne et la pièce de métal externe. De plus, le composant peut comporter soit un joint soit une attache joignant la pièce de métal interne et la pièce de métal externe. La pièce de métal interne et la pièce de métal externe peuvent présenter au moins une extrémité effilée dont chacune peut inclure une biconicité.

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