Patents by Inventor Soledad CRESPO PEÑA
Soledad CRESPO PEÑA 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: 11052996Abstract: 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: GrantFiled: January 16, 2018Date of Patent: July 6, 2021Assignee: 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
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Patent number: 10953624Abstract: 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: GrantFiled: February 22, 2017Date of Patent: March 23, 2021Inventors: Soledad Crespo Peña, Carlos García Nieto, Iker Vélez De Mendizabal Alonso, Enrique Guinaldo Fernández
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Patent number: 10906631Abstract: 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: GrantFiled: January 16, 2018Date of Patent: February 2, 2021Assignee: 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
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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: 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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Patent number: 10414497Abstract: 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: GrantFiled: September 14, 2017Date of Patent: September 17, 2019Assignee: 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
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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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Patent number: 10239602Abstract: Disclosed is a multi-spar torsion box structure comprising a plurality of spars of composite material arranged to form a multi-cell structure with two or more cells extending longitudinally along the torsion box, and upper and lower skin covers formed of composite material and joined to upper and lower surfaces of the multi-cell structure, respectively. The structure further comprises at least one belt-like reinforcing element extending around the outer perimeter of the torsion box, and fixed to the upper and lower surfaces of the multi-cell structure, and transversely arranged with respect to the longitudinal direction of the torsion box. The belt-like reinforcing element is made of a metallic or a composite material. The disclosed torsion box can advantageously be used in the manufacture of aircraft lifting surfaces, such as horizontal tailplanes (HTP) or wings.Type: GrantFiled: May 20, 2016Date of Patent: March 26, 2019Assignee: AIRBUS DEFENCE AND SPACE, S.A.Inventors: Carlos Garcia Nieto, Soledad Crespo Pena, Jesus Javier Vazquez Castro
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Publication number: 20180201361Abstract: 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: ApplicationFiled: January 16, 2018Publication date: July 19, 2018Inventors: Carlos GARCÍA NIETO, Iker VÉLEZ DE MENDIZÁBAL ALONSO, Soledad CRESPO PEÑA, Enrique GUINALDO FERNÁNDEZ, Jesús Javier VÁZQUEZ CASTRO, Álvaro TORRES SALAS
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Publication number: 20180201360Abstract: 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: ApplicationFiled: January 16, 2018Publication date: July 19, 2018Inventors: Carlos GARCÍA NIETO, Iker VÉLEZ DE MENDIZÁBAL ALONSO, Soledad CRESPO PEÑA, Enrique GUINALDO FERNÁNDEZ, Jesús Javier VÁZQUEZ CASTRO, Álvaro TORRES SALAS
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Publication number: 20180072423Abstract: 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: ApplicationFiled: September 14, 2017Publication date: March 15, 2018Inventors: Iker VÉLEZ DE MENDIZÁBAL ALONSO, Esteban MARTINO GONZÁLEZ, Carlos GARCÍA NIETO, Edouard MENARD, Enrique GUINALDO FERNÁNDEZ, Soledad CRESPO PEÑA, Jesús Javier VÁZQUEZ CASTRO
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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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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: 20170246833Abstract: 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: ApplicationFiled: February 22, 2017Publication date: August 31, 2017Applicant: Airbus Operations, S.L.Inventors: Soledad Crespo Peña, Carlos García Nieto, Iker Vélez De Mendizabal Alonso, Enrique Guinaldo Fernández
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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
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Publication number: 20170088249Abstract: The present disclosure refers to the configuration and manufacturing process of a rib for the construction of an aircraft torsion box. In the method, a flat stack of plies of composite material is layered up, which is then cut to form a flat pre-form having an outer contour having flanges, and an internal contour having two or more diagonal trusses with flanges at opposite sides. The flat pre-form is press-formed to fold the flanges of the outer and internal contour to form a rib pre-form, which is finally cured. The present disclosure also refers to a composite rib having a unitary body by forming a single pre-form of stacked plies. The present disclosure allows the manufacture of the rib in one-shot process, integrating all the ribs components such that the assembly time and cost of the rib are minimized.Type: ApplicationFiled: September 29, 2016Publication date: March 30, 2017Inventors: Carlos GARCÍA NIETO, Iker VELEZ DE MENDIZABAL ALONSO, Enrique GUINALDO FERNANDEZ, Soledad CRESPO PEÑA
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Publication number: 20160340022Abstract: The present disclosure refers to a multi-spar torsion box structure comprising a plurality of spars of composite material arranged to form a multi-cell structure with two or more cells extending span-wise at the torsion box, and upper and lower skin covers of composite material respectively joined to upper and lower surfaces of the multi-cell structure. The structure further comprises at least one belt-like reinforcing element extending on the outer perimeter of the torsion box, and fixed to the upper and lower surfaces of the multi-cell structure, and transversely arranged with respect to the span-wise direction of the torsion box. The belt-like reinforcing element is made of a metallic or a composite material. The present disclosure can advantageously be used in the manufacture of aircrafts lifting surfaces, such as horizontal tail planes (HTP) or wings.Type: ApplicationFiled: May 20, 2016Publication date: November 24, 2016Inventors: Carlos Garcia Nieto, Soledad Crespo Pena, Jesus Javier Vazquez Castro