Airbus Operations Sl

José Orencio Granado Macarrilla

Vicente Martínez Valdegrama

Raúl Burgos Gallego

Manuel Recio Melero

José Luis Lozano García

Alberto Lozano Sevilla

Teresa Latorre Plaza

Antonio Blázquez Ajenjo

Daniel Casares Rodríguez

Vincente Martínez Valdegrama

Daniel Casares Rodriguez

Antonio Blazquez Ajenjo

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

Manufacturing procedure of a composite part of a closed compartment with an integrated access assembly

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

Lightning and corrosion protection arrangement in an aircraft structural component

A method for laying-up the tapes of a prepeg composite material in the 0&#xb0; 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 Rof their curved segments is bigger than a predetermined value R; that the gap Gbetween two contiguous tapes is comprised between 0 and a predetermined value G; 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&#xb0; direction following trajectories complying with conditions described.

Laying-up method for non-planar composite components

Composite material part () with stringer () on ramp, manufactured from a stack of fabrics, which comprises at least one zone () with two sectors () having a greater thickness than that of the surrounding zones and with the stringer () situated on an edge () of said zone () in which: a) each group of fabrics (', . . . ) of said sectors () has the dimensions to form on said edge () a ramp with an acceptable gradient 1/p so that the stringer () remains situated on the ramp; b) the stacking of the zone () is carried out firstly by placing the fabrics (&#x2032;, . . . ) of the first sector () and on these the fabrics (&#x2032;, . . . ) of the second sector () in such a way that in the coinciding section () of said edge () the gradient of the resulting ramp is 1/(p/2).

Composite material part with stringer on ramp

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Madrid, Spain

José Orencio Granado Macarrilla