Patents by Inventor Carlos GARCÍA NIETO

Carlos GARCÍA NIETO 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).

  • Patent number: 11643222
    Abstract: 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: Grant
    Filed: July 3, 2019
    Date of Patent: May 9, 2023
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Francisco Javier Honorato Ruiz, Jesús Javier Vázquez Castro, Enrique Guinaldo Fernández, Carlos García Nieto, Iker Vélez De Mendizábal Alonso
  • Patent number: 11541983
    Abstract: A method for manufacturing a composite assembly with a continuous skin for a rear end of an aircraft by obtaining an upper part of the rear end by composite tooling. The upper part comprises a multi-spar vertical tail plane. The spars of the vertical tail plane comprise widening roots that form an upper shell of the rear end and an upper skin. Furthermore, a lower part comprises a lower shell of the rear end including semi-complete frames and stringers and a lower skin. The upper and lower parts are assembled with a joining procedure. The upper and lower skins are joined to obtain the composite assembly with the continuous skin.
    Type: Grant
    Filed: June 17, 2019
    Date of Patent: January 3, 2023
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Esteban Martino-Gonzalez, Alberto Arana Hidalgo, Melania Sanchez Perez, Carlos Garcia Nieto, Jesus Javier Vazquez Castro, Edouard Menard, Fernando Iniesta Lozano, Maria Almudena Canas Rios
  • Patent number: 11377190
    Abstract: A method for manufacturing an aircraft rear section including a tail cone and a vertical tail plane, the method includes: providing pre-cured frames (1) each of which includes a section of the tail cone (2) and a section of the vertical tail plane (3); providing pre-cured stringers (4); placing the pre-cured stringers (4) each in respective positions within the pre-cured frames (1); placing a skin (5) around an external surface of the pre-cured frames (1); and curing the pre-cured frames (1), the pre-cured stringers (4), and the skin (5), forming the final aircraft rear section.
    Type: Grant
    Filed: June 13, 2019
    Date of Patent: July 5, 2022
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Esteban Martino-Gonzalez, Alberto Arana Hidalgo, Melania Sanchez Perez, Carlos Garcia Nieto, Jesus Javier Vazquez Castro, Edouard Menard, Fernando Iniesta Lozano, Maria Almudena Canas Rios
  • Patent number: 11267584
    Abstract: A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.
    Type: Grant
    Filed: June 14, 2019
    Date of Patent: March 8, 2022
    Assignee: Airbus Operations S.L.
    Inventors: Esteban Martino-Gonzalez, Alberto Arana Hidalgo, Melania Sanchez Perez, Carlos Garcia Nieto, Jesus Javier Vazquez Castro, Edouard Menard, Fernando Iniesta Lozano, Maria Almudena Canas Rios
  • Patent number: 11225015
    Abstract: 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: Grant
    Filed: January 14, 2019
    Date of Patent: January 18, 2022
    Assignee: 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
  • Patent number: 11220354
    Abstract: A method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane (800), obtaining a fuselage barrel tooling (420a), (420b), (420c) and (420d) the fuselage barrel tooling having a cut-out (503a), (503b), (503c) and longitudinal cavities (501a), (501b), (501c) and (501d), attaching the vertical tail plane tooling to the fuselage barrel tooling by the cut-out of the fuselage barrel tooling, performing a composite skin lay-up (801) over the fuselage barrel tooling and the vertical tail plane tooling to obtain a continuous skin, curing the composite skin lay-up, the vertical tail plane tooling and the fuselage barrel tooling and demolding the tools to obtain the composite assembly with a continuous skin (1300), (1600).
    Type: Grant
    Filed: July 18, 2019
    Date of Patent: January 11, 2022
    Assignee: Airbus Operations S.L.U.
    Inventors: Esteban Martino-Gonzalez, Alberto Arana Hidalgo, Melania Sanchez Perez, Carlos Garcia Nieto, Jesus Javier Vazquez Castro, Edouard Menard, Fernando Iniesta Lozano, Maria Almudena Canas Rios
  • Patent number: 11052996
    Abstract: A lifting device including: a movable discontinuity (1) located in a surface of the lifting device, the movable discontinuity (1) being movable between: an active position in which the movable discontinuity (1) acts as vortex generator, and a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface, a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface including openings (3) in its surface spanwise distant from each other in communication with the conduit (2), the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.
    Type: Grant
    Filed: January 16, 2018
    Date of Patent: July 6, 2021
    Assignee: Airbus Operations S.L.
    Inventors: Carlos García Nieto, Iker Vélez De Mendizábal Alonso, Soledad Crespo Peña, Enrique Guinaldo Fernández, Jesús Javier Vázquez Castro, Álvaro Torres Salas
  • Patent number: 10953624
    Abstract: A configuration and manufacturing method for a trailing edge of an aircraft airfoil, such as a control surface or a lifting surface is described. The trailing edge is formed and configured by upper and lower composite covers, which are stitched to each other with a metallic wire, such as the metallic wire is electrically in contact with upper and lower metallic meshes to provide electrical continuity between meshes. According to a method, upper and lower covers configuring the trailing edge, are stitched with the metallic wire before curing the covers, so that the metallic wire gets embedded within the composite material. A trailing edge for an aircraft airfoil, which is easy to manufacture and that at the same time fulfills aerodynamic, mechanical and electrical conductivity requirements is described.
    Type: Grant
    Filed: February 22, 2017
    Date of Patent: March 23, 2021
    Inventors: Soledad Crespo Peña, Carlos García Nieto, Iker Vélez De Mendizabal Alonso, Enrique Guinaldo Fernández
  • Patent number: 10906631
    Abstract: A lifting surface comprising a movable discontinuity located in the surface of the lifting surface. The movable discontinuity is movable between an active position in which the movable discontinuity acts as vortex generator, and a passive position in which the movable discontinuity is integrated into the surface of the lifting surface without acting as vortex generator. The lifting surface may be in an elevator, the elevator being rotatable around a hinge line with respect to the rest of the lifting surface. A bar is rigidly joined to the elevator. The bar, the elevator and the movable discontinuity are configured such that when the elevator rotates with respect to the rest of the lifting surface, the bar moves the movable discontinuity that departs from the surface of the lifting surface, acting as a vortex generator.
    Type: Grant
    Filed: January 16, 2018
    Date of Patent: February 2, 2021
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Carlos García Nieto, Iker Vélez De Mendizábal Alonso, Soledad Crespo Peña, Enrique Guinaldo Fernández, Jesús Javier Vázquez Castro, Álvaro Torres Salas
  • Patent number: 10843785
    Abstract: A pressure bulkhead for an aircraft comprising a pressurized zone, the pressure bulkhead made of a composite material and comprising a front panel intended to be faced towards the pressurized zone; and a rear panel, substantially parallel to the front panel and intended to be located farther from the pressurized zone than the front panel. The pressure bulkhead further comprises a plurality of longerons located between the front panel and the rear panel, each one of them being attached to the front panel and to the rear panel; and a plurality of stiffeners, some of them being attached to the front panel and a remainder of them being attached to the rear panel.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: November 24, 2020
    Assignee: Airbus Operations S.L.
    Inventors: Carlos García Nieto, Francisco José Cruz Domínguez, Juan Pablo Juste Mencía, Nuria Colmenarejo Matellano, Alejandro Martínez Cañizares
  • Patent number: 10830376
    Abstract: 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: Grant
    Filed: November 14, 2018
    Date of Patent: November 10, 2020
    Assignee: Airbus Operations S.L.
    Inventors: Francisco Javier Honorato Ruiz, Diego Sanchez Franco, Luis Rodriguez Urbina, Enrique Guinaldo Fernandez, Carlos Garcia Nieto
  • Patent number: 10745105
    Abstract: 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: Grant
    Filed: July 10, 2017
    Date of Patent: August 18, 2020
    Assignee: 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
  • Publication number: 20200023934
    Abstract: A method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane (800), obtaining a fuselage barrel tooling (420a), (420b), (420c) and (420d) the fuselage barrel tooling having a cut-out (503a), (503b), (503c) and longitudinal cavities (501a), (501b), (501c) and (501d), attaching the vertical tail plane tooling to the fuselage barrel tooling by the cut-out of the fuselage barrel tooling, performing a composite skin lay-up (801) over the fuselage barrel tooling and the vertical tail plane tooling to obtain a continuous skin, curing the composite skin lay-up, the vertical tail plane tooling and the fuselage barrel tooling and demolding the tools to obtain the composite assembly with a continuous skin (1300), (1600).
    Type: Application
    Filed: July 18, 2019
    Publication date: January 23, 2020
    Inventors: Esteban MARTINO-GONZALEZ, Alberto ARANA HIDALGO, Melania SANCHEZ PEREZ, Carlos GARCIA NIETO, Jesus Javier VAZQUEZ CASTRO, Edouard MENARD, Fernando INIESTA LOZANO, Maria Almudena CANAS RIOS
  • Patent number: 10538308
    Abstract: 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: Grant
    Filed: May 5, 2017
    Date of Patent: January 21, 2020
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Carlos Garcia Nieto, Fernando Pereira Mosqueira, Iker Velez De Mendizabal Alonso, Enrique Guinaldo Fernandez, Francisco Javier Honorato Ruiz
  • Patent number: 10532807
    Abstract: 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: Grant
    Filed: January 10, 2017
    Date of Patent: January 14, 2020
    Assignee: 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
  • Publication number: 20200010218
    Abstract: 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: Application
    Filed: July 3, 2019
    Publication date: January 9, 2020
    Inventors: Francisco Javier HONORATO RUIZ, Jesús Javier VÁZQUEZ CASTRO, Enrique GUINALDO FERNÁNDEZ, Carlos GARCÍA NIETO, Iker VÉLEZ DE MENDIZÁBAL ALONSO
  • Publication number: 20190382096
    Abstract: A method for manufacturing a composite assembly with a continuous skin for a rear end of an aircraft by obtaining an upper part of the rear end by composite tooling. The upper part comprises a multi-spar vertical tail plane. The spars of the vertical tail plane comprise widening roots that form an upper shell of the rear end and an upper skin. Furthermore, a lower part comprises a lower shell of the rear end including semi-complete frames and stringers and a lower skin. The upper and lower parts are assembled with a joining procedure. The upper and lower skins are joined to obtain the composite assembly with the continuous skin.
    Type: Application
    Filed: June 17, 2019
    Publication date: December 19, 2019
    Inventors: Esteban MARTINO-GONZALEZ, Alberto ARANA HIDALGO, Melania SANCHEZ PEREZ, Carlos GARCIA NIETO, Jesus Javier VAZQUEZ CASTRO, Edouard MENARD, Fernando INIESTA LOZANO, Maria Almudena CANAS RIOS
  • Publication number: 20190382136
    Abstract: A method for manufacturing an aircraft rear section including a tail cone and a vertical tail plane, the method includes: providing pre-cured frames (1) each of which includes a section of the tail cone (2) and a section of the vertical tail plane (3); providing pre-cured stringers (4); placing the pre-cured stringers (4) each in respective positions within the pre-cured frames (1); placing a skin (5) around an external surface of the pre-cured frames (1); and curing the pre-cured frames (1), the pre-cured stringers (4), and the skin (5), forming the final aircraft rear section.
    Type: Application
    Filed: June 13, 2019
    Publication date: December 19, 2019
    Inventors: Esteban MARTINO-GONZALEZ, Alberto ARANA HIDALGO, Melania SANCHEZ PEREZ, Carlos GARCIA NIETO, Jesus Javier VAZQUEZ CASTRO, Edouard MENARD, Fernando INIESTA LOZANO, Maria Almudena CANAS RIOS
  • Publication number: 20190382137
    Abstract: A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.
    Type: Application
    Filed: June 14, 2019
    Publication date: December 19, 2019
    Inventors: Esteban MARTINO-GONZALEZ, Alberto ARANA HIDALGO, Melania SANCHEZ PEREZ, Carlos GARCIA NIETO, Jesus Javier VAZQUEZ CASTRO, Edouard MENARD, Fernando INIESTA LOZANO, Maria Almudena CANAS RIOS
  • Patent number: 10414497
    Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.
    Type: Grant
    Filed: September 14, 2017
    Date of Patent: September 17, 2019
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Iker Vélez De Mendizábal Alonso, Esteban Martino González, Carlos García Nieto, Edouard Menard, Enrique Guinaldo Fernández, Soledad Crespo Peña, Jesús Javier Vázquez Castro