Airbus Operations Sl

Airbus Espania S.l

Desiderio Sánchez-Brunete Álvarez

Luis Manuel Descalzo Fernández

A metalization structure of aircraft panels and process for obtaining such structure including a panel made in composite material, the panel including a metal mesh or foil in its outer part, said panel further including a bore which in turn comprises a shank and an upper countersinking, such that the mentioned panel is fixed to another structural aircraft element by means of metal fixing elements. The structure includes a metallization layer arranged on the upper countersinking, extending in the adjacent area of the metal mesh or foil, such that it is ensured that electrical continuity exists between the upper countersinking and the metal mesh or foil during the time that the lightning bolt strikes the structure of the panel, further ensuring that most of the current discharged by the lightning bolt is conducted over the surface of the structure of the panel.

Protection against direct lightning strikes in riveted areas of CFRP panels

The present invention relates to a leading edge () for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement () firmly adhered to the mentioned inner face of the leading edge () arranged such that it confers the leading edge () with better capacity to adapt to deformability and greater absorption of energy due to impacts. The invention also relates to a method of manufacturing a leading edge () with a metallic reinforcement () for aircraft made of composite material.

Leading edge for aircraft made of reinforced composite material

The invention relates to a curing tool () for curing a composite material part formed by bundles of fibers embedded in a resin matrix in an installation, such as an autoclave, allowing the curing of the part by means of applying high pressures and/or temperatures, comprising at least one mechanical vibrating actuator () acting on the curing tool () itself to facilitate resin distribution in the part during the curing process.

Tool for aiding resin distribution during the curing of composite material parts

A method and device are provided for verification of the quality of placing of blind rivets. The verification method involves successively carrying out, during the application of traction force to a stem, initial measurements in an initial state of the application of the traction force to obtain an initial traction force and an initial displacement of the rivet stem relative to the rivet body, intermediate measurements in an intermediate stage of the application of the traction force to obtain an intermediate traction force and an intermediate displacement, and terminal measurements in a terminal stage of the application of the traction force to obtain a terminal traction force and a terminal displacement. The obtained values are compared to acceptable values in an assignment table.

Dynamic verification method for a riveting process with blind rivets carried out with an automatic riveting apparatus, and verifying device for carrying out the verification

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Madrid, Spain

Desiderio Sánchez-Brunete Álvarez