Abstract: Procedure for the manufacture of a composite part (13) of a closed compartment, said part (13) having an access assembly to said compartment through an opening (11) in said part (13), said access assembly comprising a cover (27) for said opening (11) and a housing panel (25) for said cover (27), comprising steps of: a) providing common laminates (31, 31?, 31?) of a composite material for said cover (27) and said housing panel (25) in an uncured state; b) cutting said common laminates (31, 31?, 31?) by the perimeter foreseen for said cover (27) and separating the cover laminates (33, 33?, 33?) and the housing panel laminates (35, 35?, 35?); c) manufacturing separately, on the one side, the cover (27) using said cover laminates (31, 31?, 31?) and, on the other side, the part (13) together with said housing panel (25) using said housing panel laminates (35, 35?, 35?).

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 composite material part and method for manufacturing the part. The part has a large variation in thickness between a first zone having a thickness E1 and a second zone having a thickness E2, which is made as a single part with a transition zone, external surfaces of which have gradients of magnitude, in which the structure of the stack includes; b1) a plurality of continuous plies that extend in the three zones; b2) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone; b3) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone.

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: Composite material part (11) with stringer (31) on ramp, manufactured from a stack of fabrics, which comprises at least one zone (13) with two sectors (17, 19) having a greater thickness than that of the surrounding zones and with the stringer (31) situated on an edge (21) of said zone (13) in which: a) each group of fabrics (27, 27? . . . ; 29, 29?, . . . ) of said sectors (17, 19) has the dimensions to form on said edge (21) a ramp with an acceptable gradient 1/p so that the stringer (31) remains situated on the ramp; b) the stacking of the zone (13) is carried out firstly by placing the fabrics (27, 27?, . . . ) of the first sector (17) and on these the fabrics (29, 29?, . . . ) of the second sector (19) in such a way that in the coinciding section (35) of said edge (21) the gradient of the resulting ramp is 1/(p/2).

Abstract: Procedure for the manufacture of a composite part (13) of a closed compartment, said part (13) having an access assembly to said compartment through an opening (11) in said part (13), said access assembly comprising a cover (27) for said opening (11) and a housing panel (25) for said cover (27), comprising steps of: a) providing common laminates (31, 31?, 31?) of a composite material for said cover (27) and said housing panel (25) in an uncured state; b) cutting said common laminates (31, 31?, 31?) by the perimeter foreseen for said cover (27) and separating the cover laminates (33, 33?, 33?) and the housing panel laminates (35, 35?, 35?); c) manufacturing separately, on the one side, the cover (27) using said cover laminates (31, 31?, 31?) and, on the other side, the part (13) together with said housing panel (25) using said housing panel laminates (35, 35?, 35?).

Abstract: An aircraft lifting surface structured as a torsion box comprising upper and lower skins (19, 21) stiffened by span wise stringers (25, 25?, 25?), said aircraft lifting surface comprising one or more fuel tanks (31, 33, 35, 37) arranged inside of said torsion box and separated by bulkheads (41), the stringers (25, 25?, 25?) having extended feet in the intersection areas with said bulkheads (41), also comprising filler panels (45) of said skins (19, 21) covering the holes that remain between said skins (19, 21) and said bulkheads (41) outside said intersection areas, whose configuration is adapted for covering the space between the extended feet (26, 26?) of stringers (25, 25?), leaving a gap with them of a predetermined width (W1), thereby providing a self-fastening capability over each skin plane that facilitates the attachment of said filler panels (45) to said skins (19, 21).

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 composite material part and method for manufacturing the part. The part has a large variation in thickness between a first zone having a thickness E1 and a second zone having a thickness E2, which is made as a single part with a transition zone, external surfaces of which have gradients of magnitude, in which the structure of the stack includes; b1) a plurality of continuous plies that extend in the three zones; b2) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone; b3) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone.

Abstract: A part of composite material having a wedge between two zones, the second zone being shorter than the first zone, whose structure includes from its outer surface to its inner surface: a first section formed from at least two continuous sheets extending parallel to its outer surface, the gradient of the wedge being between 20% and 50%; a wedge in the shape of a triangular prism with its larger surface dimensioned in such a way that it forms a wedge having a gradient of less than 20%; a second section formed by a plurality of continuous sheets extending parallel to the surface bounded by the first section with the wedge placed upon it. The invention also relates to a process for manufacture of the part.

Abstract: Procedure for the manufacture of a composite material part (11) having, at least, one reinforced area (13) of greater thickness than the surrounding areas, in which the dimensions and laying up sequence of the plies (21, 21?, 21?, 21??) that are used in the laying up step of said reinforced area (13), are determined so that, at least one of the plies (21?, 21?, 21??) crosses over the ply situated beneath it for reducing the volume of said reinforced area (13). The invention also refers to a composite material part (11) manufactured with said procedure, particularly a CFRP skin of an aircraft lifting surface.

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.

Abstract: Composite material part (11) with stringer (31) on ramp, manufactured from a stack of fabrics, which comprises at least one zone (13) with two sectors (17, 19) having a greater thickness than that of the surrounding zones and with the stringer (31) situated on an edge (21) of said zone (13) in which: a) each group of fabrics (27, 27? . . . ; 29, 29?, . . . ) of said sectors (17, 19) has the dimensions to form on said edge (21) a ramp with an acceptable gradient 1/p so that the stringer (31) remains situated on the ramp; b) the stacking of the zone (13) is carried out firstly by placing the fabrics (27, 27?, . . . ) of the first sector (17) and on these the fabrics (29, 29?, . . . ) of the second sector (19) in such a way that in the coinciding section (35) of said edge (21) the gradient of the resulting ramp is 1/(p/2).

Abstract: A part (5) of composite material having a wedge (13) between two zones (11, 15), the second zone (15) being shorter than the first zone (11), whose structure comprises from its outer surface (21) to its inner surface (23): a first section (31) formed from at least two continuous sheets (41) extending parallel to its outer surface (21), the gradient of the wedge (13) being between 20% and 50%; a wedge (33) in the shape of a triangular prism with its larger surface (27) dimensioned in such a way that it forms a wedge having a gradient of less than 20%; a second section (35) formed by a plurality of continuous sheets (45) extending parallel to the surface bounded by the said first section (31) with the said wedge (33) placed upon it. The invention also relates to a process for manufacture of the part (5).