Patents by Inventor Jorge Juan Galiana Blanco
Jorge Juan Galiana Blanco has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11858229Abstract: Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.Type: GrantFiled: January 27, 2021Date of Patent: January 2, 2024Assignees: Airbus Operations, S.L.U., Airbus Operations GmbHInventors: Francisco Javier Honorato Ruiz, Eugenio Piñeyroa De La Fuente, Alfonso González Gozalbo, Ángel Pascual Fuertes, Jorge Juan Galiana Blanco, Diego García Martín, Alfonso Parra Rubio, Jorge Martin Beato, Carlos Delgado Alcojor, Eduardo González Hernando, Alberto Gallegos Elvira, José Francisco Alonso Rodríguez, René Schröder
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Patent number: 11738525Abstract: A composite forming station for forming a T-profile composite part from a planar laminate. The composite forming station includes in-line rollers arranged along a forming direction, wherein a thickness and/or edge angle each roller is greater than the preceding roller, wherein the rollers gradually splay apart feet sections of the planar laminate to convert the laminate to the T-profile composite part.Type: GrantFiled: May 29, 2020Date of Patent: August 29, 2023Assignee: AIRBUS OPERATIONS, S.L.U.Inventors: Francisco Javier Chamorro Alonso, Pedro Nogueroles Viñes, Aquilino García García, Jorge Juan Galiana Blanco, Augusto Pérez Pastor, Julián Martin Isabel
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Publication number: 20220339852Abstract: A manufacturing system (1) for manufacturing shaped laminates including: forming tools (2.1, 2.2) extending along a longitudinal direction X, located parallel to one another and configured to receive a laminate (4) between the forming tools; a shaping tool (3) extending along the longitudinal direction X and along a transversal direction Z, and configured to receive the laminate (4) on an external surface of the shaping tool, wherein the forming tools (2.1, 2.2) or the shaping tool (3) are movable in the longitudinal direction X and in the transversal direction Z, relative to the at least one of the shaping tool (3) and the two forming tools (2.1, 2.2).Type: ApplicationFiled: April 22, 2022Publication date: October 27, 2022Inventors: Diego GARCÍA MARTÍN, Raúl BURGOS GALLEGO, Jorge Juan GALIANA BLANCO, Nuria RODRIGO CABALLERO, Aquilino GARCÍA GARCÍA, Augusto PÉREZ PASTOR, Julián MARTIN ISABEL, Fernando MUÑOZ AJENJO
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Publication number: 20210229387Abstract: Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.Type: ApplicationFiled: January 27, 2021Publication date: July 29, 2021Inventors: Francisco Javier HONORATO RUIZ, Eugenio PIÑEYROA DE LA FUENTE, Alfonso GONZÁLEZ GOZALBO, Ángel PASCUAL FUERTES, Jorge Juan GALIANA BLANCO, Diego GARCÍA MARTÍN, Alfonso PARRA RUBIO, Jorge MARTIN BEATO, Carlos DELGADO ALCOJOR, Eduardo GONZÁLEZ HERNANDO, Alberto GALLEGOS ELVIRA, José Francisco ALONSO RODRÍGUEZ, René SCHRÖDER
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Publication number: 20210069997Abstract: A method for manufacturing a structure by curing together a base laminate and structural components placed thereon. Particularly, the uncured structural component has a peripheral tapered foot edge so that the vacuum bag placed thereon follows all the uncured plies without an abrupt leap from the structural component foot to the base laminate.Type: ApplicationFiled: September 3, 2020Publication date: March 11, 2021Inventors: Augusto PÉREZ PASTOR, Francisco Javier CHAMORRO ALONSO, Aquilino GARCÍA GARCÍA, Jorge Juan GALIANA BLANCO, Pedro NOGUEROLES VIÑES
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Publication number: 20200376790Abstract: A composite forming station for forming a T-profile composite part from a planar laminate. The composite forming station includes in-line rollers arranged along a forming direction, wherein a thickness and/or edge angle each roller is greater than the preceding roller, wherein the rollers gradually splay apart feet sections of the planar laminate to convert the laminate to the T-profile composite part.Type: ApplicationFiled: May 29, 2020Publication date: December 3, 2020Inventors: Francisco Javier CHAMORRO ALONSO, Pedro NOGUEROLES VIÑES, Aquilino GARCÍA GARCÍA, Jorge Juan GALIANA BLANCO, Augusto PÉREZ PASTOR, Julián MARTIN ISABEL
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Patent number: 10576723Abstract: A hybrid tool for curing composite structures for aircrafts, such as stringers, torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers, etc. The hybrid tool comprises a metallic portion and an elastic portion arranged on a surface of the metallic portion. The elastic portion and the metallic portion are permanently joined to each other so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool is capable of satisfactorily curing pieces of composite material which have a minimum thickness and/or a very aggressive change of thickness.Type: GrantFiled: May 28, 2014Date of Patent: March 3, 2020Assignee: AIRBUS OPERATIONS S.L.Inventors: Alejandro Fernandez Alonso, Aquilino Garcia Garcia, Jorge Juan Galiana Blanco, Pablo Cebolla Garrofe, Carlos Romon Banogon
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Publication number: 20140352877Abstract: A hybrid tool for curing composite structures for aircrafts, such as stringers, torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers, etc. The hybrid tool comprises a metallic portion and an elastic portion arranged on a surface of the metallic portion. The elastic portion and the metallic portion are permanently joined to each other so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool is capable of satisfactorily curing pieces of composite material which have a minimum thickness and/or a very aggressive change of thickness.Type: ApplicationFiled: May 28, 2014Publication date: December 4, 2014Applicant: Airbus Operations, S.L.Inventors: Alejandro Fernandez Alonso, Aquilino Garcia Garcia, Jorge Juan Galiana Blanco, Pablo Cebolla Garrofe, Carlos Romon Banogon
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Publication number: 20130168009Abstract: A method for manufacturing pieces of composite material having varied thicknesses is disclosed. The method includes a first stacking stage and a second forming and drying stage. In the second stage, a forming tool, which is adapted to the configuration of the piece, except in the zone affected by the change in thickness, is used. In the first stage, one or more pre-forms of the piece are stacked successively with some cloths having the dimensions needed for producing the change of thickness, some laminates of a peelable material, and some supplementary cloths in such a way that the resulting layers have the thickness needed to be adapted to the forming tool. At the end of the second stage, laminates resulting from the supplementary cloths and laminates of a peelable material are removed.Type: ApplicationFiled: March 6, 2012Publication date: July 4, 2013Applicant: Airbus Operations, S.L.Inventors: Pablo Cebolla Garrofe, Carlos Romon Banogon, Francisco Javier Honorato Ruiz, Alejandro Fernandez Alonso, Aquilino Garcia Garcia, Jorge Juan Galiana Blanco, Pedro Nogueroles Vines
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Publication number: 20130101801Abstract: Aircraft component, such as an aircraft wing, that comprises at least one panel (11) of a composite material formed by a skin (13) and at least a stiffening stringer (15) configured by a web (17) and a foot (19) bonded to said skin (13); the stringer (15) having a run-out zone inside said panel (11) subjected to a high load level; the stringer (15) having a web (17) of decreasing height in said run-out zone and a foot (19) having a first section (31) of variable width from an initial value W1 to a final value W2 and a second section (33) with a width W2 in said run-out zone; the foot (19) and the web (17) of said stringer (15) having a decreasing thickness in said run-out zone for improving the load transfer from the stringer (15) to the skin (13).Type: ApplicationFiled: September 10, 2012Publication date: April 25, 2013Applicant: AIRBUS Operations S.L.Inventors: Francisco Javier Honorato Ruiz, Jose Maria Pina Lopez, Pedro Nogueroles Vines, Augusto Perez Pastor, Cesar Bautista De La Llave, Pablo Cebolla Garrofe, Alberto Arana Hidalgo, Aquilino Garcia Garcia, Jorge Juan Galiana Blanco, Ewa Aneta Glowacz, Alejandro Fernandez Alonso, Angel Garcia Sacristan, Carolina Elena Frias Fuentes
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Patent number: 7597772Abstract: The present invention relates to a tubular-shaped component (19) for an aeronautical fuselage made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer skin (1) and a plurality of anchoring elements (3) for anchoring other elements to subsequently be incorporated transversally arranged between said stiffeners or stringers (2). The invention also comprises a jig (18) comprising a support body (12) and a plurality of panels (9) that can shift between an extended position (10) and a retracted position (10?) in both directions and a process for manufacturing said component (19) in the last step of which once the tubular component (19) is formed and cured, it is separated from the jig (18) by means of a longitudinal movement after the shifting of those elements of the jig (18) preventing it, and particularly the panels (9) that can be shifted.Type: GrantFiled: October 30, 2006Date of Patent: October 6, 2009Assignee: Airbus Espana, S.L.Inventors: Alberto Ramon Martinez Cerezo, Elena Arevalo Rodriguez, Jorge Juan Galiana Blanco, Francisco Javier Jordan Carnicero
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Publication number: 20090217529Abstract: The present invention relates to a tubular-shaped component (19) for an aeronautical fuselage made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer skin (1) and a plurality of anchoring elements (3) for anchoring other elements to subsequently be incorporated transversally arranged between said stiffeners or stringers (2). The invention also comprises a jig (18) comprising a support body (12) and a plurality of panels (9) that can shift between an extended position (10) and a retracted position (10?) in both directions and a process for manufacturing said component (19) in the last step of which once the tubular component (19) is formed and cured, it is separated from the jig (18) by means of a longitudinal movement after the shifting of those elements of the jig (18) preventing it, and particularly the panels (9) that can be shifted.Type: ApplicationFiled: October 30, 2006Publication date: September 3, 2009Inventors: Alberto Ramon Martinez Cerezo, Elena Arevalo Rodriguez, Jorge Juan Galiana Blanco, Francisco Javier Jordan Carnicero