Patents by Inventor Francisco Javier Honorato Ruiz
Francisco Javier Honorato Ruiz 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: 11987343Abstract: An aircraft empennage includes a vertical tail plane, a rear fuselage section attached to the vertical tail plane and including a skin and internal reinforcing members, a horizontal tail plane comprising two lateral torsion boxes and a framework located between the two lateral torsion boxes comprising a front spar, a rear spar and two ribs extending between the front and the rear spar and each adjacent to a lateral torsion box. The framework encloses a portion of the vertical tail plane along its spanwise direction. The aircraft empennage includes an attachment assembly attaching the framework to the rear fuselage section, the attachment assembly crossing the skin and extends between the internal reinforcing members of the rear fuselage section and the framework.Type: GrantFiled: November 15, 2021Date of Patent: May 21, 2024Assignee: Airbus Operations S.L.U.Inventors: Francisco Javier Honorato Ruiz, María Muruzabal Sopelana
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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: 11643222Abstract: A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.Type: GrantFiled: July 3, 2019Date of Patent: May 9, 2023Assignee: AIRBUS OPERATIONS S.L.Inventors: Francisco Javier Honorato Ruiz, Jesús Javier Vázquez Castro, Enrique Guinaldo Fernández, Carlos García Nieto, Iker Vélez De Mendizábal Alonso
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Publication number: 20220250735Abstract: An aircraft empennage includes a vertical tail plane, a rear fuselage section attached to the vertical tail plane and including a skin and internal reinforcing members, a horizontal tail plane comprising two lateral torsion boxes and a framework located between the two lateral torsion boxes comprising a front spar, a rear spar and two ribs extending between the front and the rear spar and each adjacent to a lateral torsion box. The framework encloses a portion of the vertical tail plane along its spanwise direction. The aircraft empennage includes an attachment assembly attaching the framework to the rear fuselage section, the attachment assembly crossing the skin and extends between the internal reinforcing members of the rear fuselage section and the framework.Type: ApplicationFiled: November 15, 2021Publication date: August 11, 2022Inventors: Francisco Javier HONORATO RUIZ, María MURUZABAL SOPELANA
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Patent number: 11225015Abstract: A method for manufacturing, layer-upon-layer, an integral composite aeronautical structure, wherein the method comprises: (a) providing an additive manufacturing tool comprising a depositing mold shaping an aerodynamic surface and at least one head configured to be moved over the depositing mold and to deposit fibrous material reinforcement and/or meltable material; (b) depositing fibrous material reinforcement embedded within meltable material onto the depositing mold, at least one layer of a lower aerodynamic face-sheet being built thereby; (c) depositing meltable material onto at least a portion of the outer layer of the lower aerodynamic face-sheet, at least one layer of core structure being built thereby; and (d) depositing fibrous material reinforcement embedded within meltable material onto at least the outer layer of the core structure, at least one layer of an upper aerodynamic face-sheet being built thereby; wherein steps (b), (c) and (d) are performed using Additive Manufacturing technology.Type: GrantFiled: January 14, 2019Date of Patent: January 18, 2022Assignee: Airbus Operations S.L.U.Inventors: Francisco Javier Honorato Ruiz, Enrique Guinaldo Fernández, Carlos García Nieto, Guillermo Hernáiz López, Jesús Javier Vázquez Castro, Diego Lastra Gil, Iker Vélez De Mendizábal Alonso, Alberto Arana Hidalgo
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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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Patent number: 10830376Abstract: A composite structure (1) for an aircraft, having at least one insert (2) for receiving attachment devices, each insert (2) includes a core (3) having a major dimension and containing at least one through-hole (4), and a composite strip arrangement formed by a first section (5) surrounding the core (3) and attached to said core (3) by an adhesive polymeric layer, and a second section (6) including at least one free end (6a). The first (5) and the second portion (6) of the composite strip arrangement are disposed over a first surface (1a) of the composite structure (1), such that the major dimension of the core (3) is positioned transversal to said first surface (1 a). The at least one insert (2) is co-cured with the composite structure (1).Type: GrantFiled: November 14, 2018Date of Patent: November 10, 2020Assignee: Airbus Operations S.L.Inventors: Francisco Javier Honorato Ruiz, Diego Sanchez Franco, Luis Rodriguez Urbina, Enrique Guinaldo Fernandez, Carlos Garcia Nieto
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Patent number: 10745105Abstract: A tip structure for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, HTP's, VTP's) is a unitary body and includes a tip shell and a metallic material on the outer surface of the tip shell suitable to withstand a lighting strike. The tip shell has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and the metallic material has been integrally formed with the tip shell.Type: GrantFiled: July 10, 2017Date of Patent: August 18, 2020Assignee: Airbus Operations, S.L.Inventors: Soledad Crespo Peña, Francisco Javier Honorato Ruiz, Iker Vélez De Mendizabal Alonso, Carlos García Nieto, Enrique Guinaldo Fernández, Álvaro Torres Salas, Pablo Cebolla Garrofe, Álvaro Calero Casanova
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Patent number: 10538308Abstract: An aircraft aerodynamic surface (1) including a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) including a front spar (31) and a trailing edge (32) and a second control surface (4) having a front spar (41), a trailing edge (42), and a pivot device (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) including two lateral ribs (9, 9?), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which includes two lateral ribs (20, 20?), three internal ribs (17, 18, 19), two internal spars (24, 24?) and one internal spar (23).Type: GrantFiled: May 5, 2017Date of Patent: January 21, 2020Assignee: AIRBUS OPERATIONS S.L.Inventors: Carlos Garcia Nieto, Fernando Pereira Mosqueira, Iker Velez De Mendizabal Alonso, Enrique Guinaldo Fernandez, Francisco Javier Honorato Ruiz
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Patent number: 10532807Abstract: A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.Type: GrantFiled: January 10, 2017Date of Patent: January 14, 2020Assignee: Airbus Operations, S.L.Inventors: Carlos García Nieto, Enrique Guinaldo Fernández, Pablo Cebolla Garrofe, Iker Vélez De Mendizabal Alonso, Soledad Crespo Peña, Francisco Javier Honorato Ruiz, Álvaro Torres Salas, Álvaro Calero Casanova
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Publication number: 20200010218Abstract: A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.Type: ApplicationFiled: July 3, 2019Publication date: January 9, 2020Inventors: Francisco Javier HONORATO RUIZ, Jesús Javier VÁZQUEZ CASTRO, Enrique GUINALDO FERNÁNDEZ, Carlos GARCÍA NIETO, Iker VÉLEZ DE MENDIZÁBAL ALONSO
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Patent number: 10377464Abstract: This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection molding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection molding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demolded.Type: GrantFiled: March 13, 2017Date of Patent: August 13, 2019Assignee: AIRBUS OPERATIONS, S.L.Inventors: Pablo Cebolla Garrofe, Álvaro Calero Casanova, Soledad Crespo Peña, Carlos Garcïa Nieto, Iker Vélez De Mendizábal Alonso, Enrique Guinaldo Fernandez, Francisco Javier Honorato Ruiz, Alvaro Torres Salas
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Publication number: 20190217536Abstract: A method for manufacturing, layer-upon-layer, an integral composite aeronautical structure, wherein the method comprises: (a) providing an additive manufacturing tool comprising a depositing mold shaping an aerodynamic surface and at least one head configured to be moved over the depositing mold and to deposit fibrous material reinforcement and/or meltable material; (b) depositing fibrous material reinforcement embedded within meltable material onto the depositing mold, at least one layer of a lower aerodynamic face-sheet being built thereby; (c) depositing meltable material onto at least a portion of the outer layer of the lower aerodynamic face-sheet, at least one layer of core structure being built thereby; and (d) depositing fibrous material reinforcement embedded within meltable material onto at least the outer layer of the core structure, at least one layer of an upper aerodynamic face-sheet being built thereby; wherein steps (b), (c) and (d) are performed using Additive Manufacturing technology.Type: ApplicationFiled: January 14, 2019Publication date: July 18, 2019Inventors: Francisco Javier HONORATO RUIZ, Enrique GUINALDO FERNÁNDEZ, Carlos GARCÍA NIETO, Guillermo HERNÁIZ LÓPEZ, Jesús Javier VÁZQUEZ CASTRO, Diego LASTRA GIL, Iker VÉLEZ DE MENDIZÁBAL ALONSO, Alberto ARANA HIDALGO
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Publication number: 20190145550Abstract: A composite structure (1) for an aircraft, having at least one insert (2) for receiving attachment devices, each insert (2) includes a core (3) having a major dimension and containing at least one through-hole (4), and a composite strip arrangement formed by a first section (5) surrounding the core (3) and attached to said core (3) by an adhesive polymeric layer, and a second section (6) including at least one free end (6a). The first (5) and the second portion (6) of the composite strip arrangement are disposed over a first surface (1a) of the composite structure (1), such that the major dimension of the core (3) is positioned transversal to said first surface (1 a). The at least one insert (2) is co-cured with the composite structure (1).Type: ApplicationFiled: November 14, 2018Publication date: May 16, 2019Inventors: Francisco Javier HONORATO RUIZ, Diego SANCHEZ FRANCO, Luis RODRIGUEZ URBINA, Enrique GUINALDO FERNANDEZ, Carlos GARCIA NIETO
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Publication number: 20180022438Abstract: A tip structure for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, HTP's, VTP's) is a unitary body and includes a tip shell and a metallic material on the outer surface of the tip shell suitable to withstand a lighting strike. The tip shell has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and the metallic material has been integrally formed with the tip shell.Type: ApplicationFiled: July 10, 2017Publication date: January 25, 2018Applicant: Airbus Operations, S.L.Inventors: Soledad Crespo Peña, Francisco Javier Honorato Ruiz, Iker Vélez De Mendizabal Alonso, Carlos García Nieto, Enrique Guinaldo Fernández, Álvaro Torres Salas, Pablo Cebolla Garrofe, Álvaro Calero Casanova
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Patent number: 9868510Abstract: A structure of a control surface for aircrafts, such as elevators, rudders, landing flaps, ailerons, and other similar lifting surfaces. The control surface includes a front spar, a rear spar, a plurality of ribs, at least one hinge fitting, and at least one actuator fitting, the hinge and actuator fittings joined with the front spar. A first rib is joined with a hinge fitting to form a first oblique angle with the front spar; a second rib is joined with an actuator fitting to form a second oblique angle with the front spar. The rear spar, located between the front spar and trailing edge of the control surface, extends only between the second rib and an outboard end of the control surface. The ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff.Type: GrantFiled: December 23, 2014Date of Patent: January 16, 2018Assignee: AIRBUS OPERATIONS S.L.Inventors: Fernando Pereira Mosqueira, Enrique Guinaldo Fernandez, Carlos Garcia Nieto, Francisco Javier Honorato Ruiz, Andrea Ivan Marasco, Francisco José Cruz Dominguez
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Publication number: 20170320561Abstract: An aircraft aerodynamic surface (1) including a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) including a front spar (31) and a trailing edge (32) and a second control surface (4) having a front spar (41), a trailing edge (42), and a pivot device (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) including two lateral ribs (9, 9?), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which includes two lateral ribs (20, 20?), three internal ribs (17, 18, 19), two internal spars (24, 24?) and one internal spar (23).Type: ApplicationFiled: May 5, 2017Publication date: November 9, 2017Inventors: Carlos GARCIA NIETO, Fernando PEREIRA MOSQUEIRA, Iker VELEZ DE MENDIZABAL ALONSO, Enrique GUINALDO FERNANDEZ, Francisco Javier HONORATO RUIZ
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Publication number: 20170259902Abstract: An aircraft aerodynamic surface includes a torsion box having an upper skin, a lower skin, and a front spar, and a leading edge having an external shell and an impact resisting structure. The external shell may be shaped with an aerodynamic leading edge profile, being configured to provide Laminar Flow Control (LFC) to the leading edge. The impact resisting structure is spanwise arranged between the external shell and the front spar, and is configured for absorbing a bird strike to prevent damage in the front spar. Also, at least one of the external shell and the impact resisting structure is fitted with the upper and lower skins of the torsion box to thereby facilitate leading edge exchange.Type: ApplicationFiled: March 8, 2017Publication date: September 14, 2017Applicant: Airbus Operations, S.L.Inventors: Pablo Cebolla Garrofe, Iker Vélez De Mendizabal Alonso, Soledad Crespo Peña, Álvaro Calero Casanova, Carlos García Nieto, Enrique Guinaldo, Francisco Javier Honorato Ruiz, Álvaro Torres Salas
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Publication number: 20170259903Abstract: This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection moulding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection moulding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demoulded.Type: ApplicationFiled: March 13, 2017Publication date: September 14, 2017Inventors: Pablo CEBOLLA GARROFE, Álvaro CALERO CASANOVA, Soledad CRESPO PEÑA, Carlos GARCÍA NIETO, Iker VÉLEZ DE MENDIZÁBAL ALONSO, Enrique GUINALDO FERNANDEZ, Francisco Javier HONORATO RUIZ, Alvaro TORRES SALAS
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Publication number: 20170197706Abstract: A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.Type: ApplicationFiled: January 10, 2017Publication date: July 13, 2017Applicant: Airbus Operations, S.L.Inventors: Carlos García Nieto, Enrique Guinaldo Fernández, Pablo Cebolla Garrofe, Iker Vélez De Mendizabal Alonso, Soledad Crespo Peña, Francisco Javier Honorato Ruiz, Álvaro Torres Salas, Álvaro Calero Casanova