Airbus Espana, S.l.

Airbus Operations Sl

Construcciones Aeronauticas, S.a.

Airbus Operations Gmbh

Augusto Perez Pastor

Aquilino Garcia Garcia

Yolanda Miguez Charines

Carlos Cerezo Pancorbo

Manuel Huertas Garcia

Gabriel Cruzado Parla

Manuel De Castro Nodal

Rafael Dominguez Casado

Jorge Juan Galiana Blanco

José Manuel Menéndez Martin

Jose Cuenca Rincon

Alberto Martinez Cerezo

José Manuel Menéndez Martín

Antonio Durán Quiroga

Pedro Nogueroles Vines

Francisco Javier Jordán Carnicero

David Cano Cediel

Julio Nunez Delgado

Laura Álvarez Antoñón

Angel Pablo Gordo

José Manuel Menendez

Noelia Colas Garcia

Ángel Pablo Gordo Arias

Georgina Galera Cordoba

Antonio Duran Quiroga

Laura ÁLvarez Antonon

Method to make a T shaped stiffener form from a stiffener preform () having a foot () configured to be in contact with an aircraft panel, and a sole () with an edge (). The manufacturing method includes: obtaining laminates () formed of layers of composite material, folding the laminates () to be L shaped in cross section, joining the laminates to form a T shaped preform (), molding the edge of the sole () so that the edge is semicircular in cross section, applying to the edge () a strip of semi-cured carbon fabric (L) and a fresh strip of prepreg fiberglass (L), and curing the preform () to obtain the stiffener.

Manufacturing methods of net stiffeners

A manufacturing method of structures formed co-bonding second structural components to a first structural component. The method comprises the following steps: a) preparing for each second structural component an ensemble wherein a preform of the second structural component, surrounded by a band of a suitable material to form a vacuum bag, is disposed between curing tools which are thus in contact with the bag and not with the preform; b) positioning the ensembles on the first structural component and forming the vacuum bag for the complete structure joining the bands and complementary pieces; c) applying to the resulting assembly an autoclave cycle.

Manufacturing method of composite structures with curing tools arranged outside the vacuum bag

An apparatus for manufacturing composite stringers from a composite laminate comprising a male mold, a main caul plate, two fixed female mold halves, two secondary movable caul plates and a retention device. The main caul plate is located below the male mold, the female mold halves are located at both sides of the main caul plate and the secondary movable caul plates, each of them located respectively over each one of the two female mold halves. The male mold, the main caul plate, the two female mold halves and the two secondary caul plates are non-developable surfaces. The retention device keeps each secondary movable caul plate at a predetermined distance of its respective female mold half.

Device and method of manufacturing omega stringers

The present invention relates to a process for manufacturing panels () for aeronautical structures with U-shaped stiffening members () and I-shaped stiffening members () between their webs comprising the following steps: providing laminates for shaping the skin () on the curing tool (); providing planar laminates () for shaping the stiffening members (); shaping the U-shaped stiffening members () on individual shaping tools () and placing the I-shaped stiffening elements () in said tools; grouping said individual shaping tools () together on an assembly tool (); placing the group of stiffening members () on the skin (); placing a vacuum bag () on the assembly with the aid of profiles (); consolidating said assembly by means of a curing process under suitable pressure and temperature conditions using external tools () to assure verticality of the webs of the stiffening members ().

Process of manufacturing composite panels with U-shaped stiffening members

The invention relates to a process for making swaged lighting holes () in planar areas of parts () made of preimpregnated composite, by means of which the part () is arranged between a female tooling () with the final shape of the bottom side of the swaged part and a caul plate () with the final shape of the top side of the swaged part, except in an area () which must be swaged, pressure Pis applied on the caul plate () in the area of the part () that must be maintained substantially planar, and pressure Pis applied by means of a male tooling () on the area () of the part () which must be swaged at a forward speed allowing the flow of the resin during the slippage of the fibers of the material so that it may deform, adapting to the final shape of the female tooling ().

Process for making swaged lighting holes in planar areas of preimpregnated composite parts

Process for manufacturing monolithic composite structures comprising providing first and second subcomponents () of composite material, attaching an expansion compensating tooling to the second subcomponent, placing the second subcomponent along with said tooling on the first subcomponent and bonding it to the latter by means of an uncured structural adhesive, covering the assembly comprising the first and second subcomponents and the tooling with a vacuum bag, performing an autoclave cycle for curing the curable material contained in said assembly under high temperature and pressure conditions, withdrawing said assembly from the curing autoclave and removing the expansion compensating tooling to obtain the desired monolithic composite structure. The tooling for carrying out the process comprises metal L- or I-shaped beams having a rough surface adapted to be applied to the second subcomponent. The invention is useful for manufacturing aircraft parts.

Process and tooling for reducing thermally induced residual stresses and shape distortions in monolithic composite structures

A process for manufacturing primary structures of composite material with curing in a female tool, comprising the steps of laminating superimposed composite material layers in a pre-impregnated state; placing the obtained laminate over a forming tool, loading the assembly of the laminate and forming tool in a vacuum bell and applying a pre-established forming operation, loading the formed laminate, still in a green state, in a female tool suitable for its curing, placing lateral caul plates in the tool and inserting elastomeric pipes in channels of the caul plates, fitting a central caul plate, sealing the assembly and applying a vacuum bag with perforations to remove the air from its interior. The assembly is cured in an autoclave.

Process for manufacturing structures of composite material

A process for manufacturing pre-cured parts of composite material with green-applied stiffeners, comprising the lamination of superimposed pre-impregnated composite material sheets to obtain a base part ( ) and a second part ( ) intended to be bonded with it; curing the base part ( ); hot forming the laminate destined to form the second part ( ); removing the second part ( ) from the forming tool thereof and deposit it over the base part ( ), intercalating a structural adhesive sheet between both of them; closing the assembly of both parts inside a vacuum bag and loading said bag in an autoclave, carrying out a curing cycle of the second part ( ) under pressure and temperature, so that it is strongly adhered to the base part ( ). The invention is applicable to the field of aeronautics.

Process for manufacturing pre-cured parts of composite material with green-applied stiffeners

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Madrid, Spain

Augusto Perez Pastor