Abstract: A lightning and corrosion protection arrangement for a joint between an outer metallic part (11) and an aircraft structural component (13) completely or partially made of CFRP by means of a row of metallic rivets (15), that comprise inner and outer metallic layers (21, 25) and an intermediate dielectric layer (23), the inner metallic layer (21) in contact with said structural component (13) being thinner and bigger than the outer metallic layer (21) in contact with the metallic part (11), the intermediate dielectric layer (23) extending in an area bigger than the area of the foot (12) of the metallic part (11) by a predetermined minimum linear distance D1 between its edges, the outer metallic layer (25) extending in an area bigger than the area of the intermediate dielectric layer (23) by a predetermined minimum linear distance D2 between its edges.

Abstract: A method for laying-up the tapes of a prepeg composite material in the 0° direction of a non-planar composite component on a suitable mold using an ATL machine includes the steps of: a) determining the trajectories of the tapes as modified trajectories of geodesic trajectories complying with the following conditions in their projections in an horizontal plane: that the curvature radius R2 of their curved segments is bigger than a predetermined value Rmin; that the gap G2p between two contiguous tapes is comprised between 0 and a predetermined value Gmax; and b) providing modified trajectories to the ATL machine. The invention also refers to a non-planar composite component such as an skin of an aircraft wing having the tapes in the 0° direction following trajectories complying with conditions described.

Abstract: A method for laying-up the tapes of a prepeg composite material in the 0° direction of a non-planar composite component on a suitable mould using an ATL machine comprising steps of: a) determining the trajectories of said tapes as modified trajectories of geodesic trajectories complying with the following conditions in their projections in an horizontal plane: that the curvature radius R2 of their curved segments is bigger than a predetermined value Rmin; that the gap G2p between two contiguous tapes is comprised between 0 and a predetermined value Gmax; b) providing said modified trajectories to said ATL machine. The invention also refers to a non-planar composite component such as an skin of an aircraft wing having the tapes in the 0° direction following trajectories complying with said conditions.

Abstract: A lightning and corrosion protection arrangement for a joint between an outer metallic part (11) and an aircraft structural component (13) completely or partially made of CFRP by means of a row of metallic rivets (15), that comprise inner and outer metallic layers (21, 25) and an intermediate dielectric layer (23), the inner metallic layer (21) in contact with said structural component (13) being thinner and bigger than the outer metallic layer (21) in contact with the metallic part (11), the intermediate dielectric layer (23) extending in an area bigger than the area of the foot (12) of the metallic part (11) by a predetermined minimum linear distance D1 between its edges, the outer metallic layer (25) extending in an area bigger than the area of the intermediate dielectric layer (23) by a predetermined minimum linear distance D2 between its edges.

Abstract: Aircraft component which comprises at least one panel (11) of composite material, formed by a skin (13) and a plurality of stiffening stringers (15) which are configured with a core (17) and a base (19) of width (A), said stiffening stringers (15) comprising first local flarings (21) of their bases (19) intended to provide areas for joining with other parts located in flat zones of the skin (13) and second local flarings (23) of their bases (19) which are intended to provide areas for joining with other parts located in zones of the skin (13) which include change-in-thickness ramps (33), being configured in the form of two end sections (41, 45) located above flat zones of the skin (13) and a central section (43) located above one of said ramps (33) of the skin (13), one of said end sections (41, 45) acting as an area for joining with other parts.