Airbus Operations Sl

Airbus Espana, S.l.

Vicente Martínez Valdegrama

José Orencio Granado Macarrilla

Jose Luis Lozano Garcia

Pedro Nogueroles Viñes

Manuel Recio Melero

Gonzalo Ramirez Blanco

Antonio De Julián Aguado

Luis Manuel Rodríguez Urbina

Jose Orencio Granado Macarrilla

Raúl Burgos Gallego

José Luis Lozano García

Teresa Latorre Plaza

Gonzalo Ramírez Blanco

Alberto Lozano Sevilla

Daniel Casares Rodríguez

Antonio Blázquez Ajenjo

Olaf Andreas Dietrich Carreño

Oscar De La Cruz Garcia

José Luis Lozano Garcia

Antonio Blazquez Ajenjo

Sevilla Alberto Lozano

Raul Burgos Gallego

Oscar De La Cruz GARCÍA

Daniel Casares Rodriguez

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 composite material part and method for manufacturing the part. The part has a large variation in thickness between a first zone having a thickness Eand a second zone having a thickness E, 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.

Composite material part with large variation in thickness

Its object is to allow measurement of the volume of fuel () using optic fiber cables (); it is characterized in that, adhered to one or more of the inner faces of the tank () there is at least one sheet () in which a plurality of optic fiber cables () with different lengths are included, located between the inner face of the tank and the sheet (). One set of the ends () of the optic fiber cables () are disposed so that they are in contact with the fuel () when it reaches their level, thereby allowing measurement of the fuel level at all times. The preferred embodiment distributes the optic fiber cables () on two opposing lateral faces of the tank () so that they cross over one another and in opposite directions to measure any fuel level. It is applied in aeronautics.

Liquid fuel tank for measuring fuel volume

A device provides electrical continuity between aeronautical components including a first fixed component and a second component displaceable with respect to the first component. The first and second components include electrically conducting surfaces. A first conductive piece is fixed to the first component and a second conductive piece is fixed to the second component. The first and second pieces are joined together with the possibility of sliding one on the other, in such a way that the first piece is connected to the conductive surface of the first component and the second piece is connected to the conductive surface of the second component, so that, when displacements take place of the second component with respect to the first component, the first piece slides on the second piece maintaining the electrical conductivity between the first and second components.

Device for providing electrical continuity between aeronautical components with relative movement

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

Provided herein are drainage valves for removing water accumulated in the lower part of fuel tanks of an aircraft. The valves can be affixed in correspondence with a lower skin forming part of the tanks. The lower skin includes recesses for the complementary housing of the heads of the valves that, in combination with some axial fastening nuts, immobilize the valves to that skin. The recesses can comprise a conical structure obtained by deformation of the lower skin, and with the deformation an inner elevated seat is further obtained, on which seat the axial fastening nuts press, maintaining the thickness of the skin in the area where the valves are located, thus preventing the area from weakening as it happens conventionally.

Fastening system for drainage valves

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.

Part of composite material having a wedge between two zones

The invention relates to a piece made of composite material with areas of different thickness manufactured from a stack of composite material fabrics comprising at least two adjacent areas () of different thickness and a transition area () between both configured with a single slope (), in which the stack is structured by: a first and a fourth section formed by at least two continuous fabrics () extending along the three mentioned areas (); a second section formed by one or more symmetrical and balanced fabric packets () ending in the transition area () placed among one or more continuous fabrics (); a third section formed by a symmetrical and balanced fabric packet () extending along the three mentioned areas () placed among one or more continuous fabrics ().

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Madrid, Spain

Vicente Martínez Valdegrama