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公开(公告)号：US10953624B2
公开(公告)日：2021-03-23
申请号：US15438896
申请日：2017-02-22
Applicant: Airbus Operations, S.L.
Inventor： Soledad Crespo Peña , Carlos García Nieto , Iker Vélez De Mendizabal Alonso , Enrique Guinaldo Fernández
IPC: B32B5/02 , B64C1/00 , B32B37/14 , B64C9/00 , B64C3/20 , B64D45/02 , B29C70/24 , B32B5/06 , B32B15/02 , B29L31/30 , B32B38/00
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.
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公开(公告)号：US20170197706A1
公开(公告)日：2017-07-13
申请号：US15402520
申请日：2017-01-10
Applicant: Airbus Operations, S.L.
Inventor： 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
CPC classification number: B64C21/06 , B64C3/182 , B64C3/26 , B64C2001/0072 , B64C2001/0081 , B64F5/00 , Y02T50/166
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.
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公开(公告)号：US11643222B2
公开(公告)日：2023-05-09
申请号：US16502436
申请日：2019-07-03
Applicant: Airbus Operations, S.L.
Inventor： Francisco Javier Honorato Ruiz , Jesús Javier Vázquez Castro , Enrique Guinaldo Fernández , Carlos García Nieto , Iker Vélez De Mendizábal Alonso
CPC classification number: B64F5/10 , B64C3/187 , B29L2031/3085 , B64C9/02
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.
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公开(公告)号：US11052996B2
公开(公告)日：2021-07-06
申请号：US15872460
申请日：2018-01-16
Applicant: Airbus Operations S.L.
Inventor： Carlos García Nieto , Iker Vélez De Mendizábal Alonso , Soledad Crespo Peña , Enrique Guinaldo Fernández , Jesús Javier Vázquez Castro , Álvaro Torres Salas
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.
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公开(公告)号：US10906631B2
公开(公告)日：2021-02-02
申请号：US15872619
申请日：2018-01-16
Applicant: Airbus Operations S.L.
Inventor： Carlos García Nieto , Iker Vélez De Mendizábal Alonso , Soledad Crespo Peña , Enrique Guinaldo Fernández , Jesús Javier Vázquez Castro , Álvaro Torres Salas
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.
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Patent Agency Ranking
公开(公告)号：US10532807B2
公开(公告)日：2020-01-14
申请号：US15402520
申请日：2017-01-10
Applicant: Airbus Operations, S.L.
Inventor： 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
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.
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公开(公告)号：US10745105B2
公开(公告)日：2020-08-18
申请号：US15645332
申请日：2017-07-10
Applicant: Airbus Operations, S.L.
Inventor： 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
IPC: B64C3/24 , B64C3/00 , B64D37/32 , B29C45/00 , B29D99/00 , B64C3/18 , B64C3/58 , B29K71/00 , B29K81/00 , B29K307/04 , B29K309/08 , B29L31/30
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.
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公开(公告)号：US10414497B2
公开(公告)日：2019-09-17
申请号：US15704114
申请日：2017-09-14
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Iker Vélez De Mendizábal Alonso , Esteban Martino González , Carlos García Nieto , Edouard Menard , Enrique Guinaldo Fernández , Soledad Crespo Peña , Jesús Javier Vázquez Castro
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.
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公开(公告)号：US20180022438A1
公开(公告)日：2018-01-25
申请号：US15645332
申请日：2017-07-10
Applicant: Airbus Operations, S.L.
Inventor： 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
CPC classification number: B64C3/24 , B29C45/0001 , B29C45/0005 , B29D99/0014 , B29K2071/00 , B29K2081/04 , B29K2307/04 , B29K2309/08 , B29L2031/3085 , B64C3/00 , B64C3/18 , B64C3/58 , B64D37/32 , Y02T50/44
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.
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公开(公告)号：US20170246833A1
公开(公告)日：2017-08-31
申请号：US15438896
申请日：2017-02-22
Applicant: Airbus Operations, S.L.
Inventor： Soledad Crespo Peña , Carlos García Nieto , Iker Vélez De Mendizabal Alonso , Enrique Guinaldo Fernández
CPC classification number: B32B5/028 , B29C70/24 , B29L2031/3085 , B32B5/02 , B32B5/06 , B32B15/02 , B32B37/14 , B32B2038/008 , B32B2260/021 , B32B2260/046 , B32B2262/106 , B32B2305/076 , B32B2305/72 , B32B2605/18 , B64C1/00 , B64C3/20 , B64C9/00 , B64C2001/0072 , B64D45/02 , D05D2209/12 , Y02T50/43
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.
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