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公开(公告)号：US10576723B2
公开(公告)日：2020-03-03
申请号：US14288931
申请日：2014-05-28
Applicant: Airbus Operations, S.L.
Inventor： Alejandro Fernandez Alonso , Aquilino Garcia Garcia , Jorge Juan Galiana Blanco , Pablo Cebolla Garrofe , Carlos Romon Banogon
Abstract: 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.
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公开(公告)号：US11518067B2
公开(公告)日：2022-12-06
申请号：US17129057
申请日：2020-12-21
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Pablo Cebolla Garrofe
IPC: B29B11/00 , B29B11/06 , B29K307/04
Abstract: A method for forming fiber composite preforms, the preform (1) include a web (2), a flange (3) and a bent part (2.1), and the method includes: laying-up a laminate (4) onto a tooling (5), the laminate (4) comprising lateral and transverse edges (4.1, 4.2) and the tooling (5) comprising a male part (7) comprising a surface (7.1) and a lateral wall (7.2), the web (2) being configured to be located over the surface (7.1) of the male part (7) and the flange (3) being configured to be located over the lateral wall (7.2) of the male part (7); forming the preform (1) over the male part (7); clamping the lateral edges (4.2) of the laminate (4) to the tooling (5) such that the web (2) and the flange (3) of the laid-up laminate (4) are kept under tensional loads, and bending a longitudinal portion of the male part (7).
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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：US20170259902A1
公开(公告)日：2017-09-14
申请号：US15452899
申请日：2017-03-08
Applicant: Airbus Operations, S.L.
Inventor： 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
CPC classification number: B64C3/26 , B64C3/185 , B64C3/28 , B64C5/02 , B64C21/06 , B64D2045/0095 , Y02T50/166
Abstract: 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.
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公开(公告)号：US10377464B2
公开(公告)日：2019-08-13
申请号：US15457499
申请日：2017-03-13
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： 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
IPC: B64C3/26 , B29C45/00 , B29C45/14 , B29C45/40 , B29C69/00 , B29C33/48 , B29K105/06 , B29L31/30 , B29C33/30 , B64C3/28 , B64C21/06 , B29K105/12
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20140352877A1
公开(公告)日：2014-12-04
申请号：US14288931
申请日：2014-05-28
Applicant: Airbus Operations, S.L.
Inventor： Alejandro Fernandez Alonso , Aquilino Garcia Garcia , Jorge Juan Galiana Blanco , Pablo Cebolla Garrofe , Carlos Romon Banogon
IPC: B32B38/00
CPC classification number: B32B38/00 , B29C33/38 , B29C33/405 , B29C70/44 , B29K2995/0046 , B29K2995/007 , B29L2031/001 , B29L2031/003 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B32B2038/0076 , B32B2305/77 , Y10T156/1002
Abstract: 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.
Abstract translation: 一种用于固化飞机的复合结构的混合工具，例如桁条，扭转箱，皮肤板，翼面，水平尾部或垂直稳定器等。混合工具包括金属部分和布置在金属部分的表面上的弹性部分 。 弹性部分和金属部分彼此永久地接合，使得金属部分和弹性部分一起限定具有复制待固化的复合材料片的表面的至少一部分的形状的表面。 该工具能够令人满意地固化具有最小厚度和/或非常积极的厚度变化的复合材料片。
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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：US09669919B2
公开(公告)日：2017-06-06
申请号：US14587647
申请日：2014-12-31
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Diego García Martín , Lara Barroso Fernández , Pablo Cebolla Garrofe , David Alfonso Cerezo Arce , Ignacio José Márquez López
IPC: B64C1/00 , B64C3/00 , B64C5/00 , B64C3/18 , B64C3/20 , B64C3/26 , B32B37/02 , B32B37/06 , B32B37/10 , B32B37/16 , B32B41/00 , B64C5/02 , B64D27/26 , B29C70/44 , B29D99/00 , B64F5/10 , B32B38/00
CPC classification number: B64C3/18 , B29C70/443 , B29D99/0014 , B32B37/02 , B32B37/06 , B32B37/1018 , B32B37/16 , B32B41/00 , B32B2038/0076 , B32B2038/0096 , B32B2309/68 , B32B2309/70 , B32B2605/18 , B64C3/20 , B64C3/26 , B64C5/02 , B64D27/26 , B64D2027/264 , B64F5/10 , Y02T50/43
Abstract: Highly integrated infused box made of composite material with two skins (3), several ribs (4), several stringers (5), a front spar and a rear spar, comprising a first semibox (1) and a second semibox (2) joined by connecting means, in which the first semibox (1) comprises one skin (3) and the ribs (4), and the second semibox (2) comprises one skin (3), the front spar, the rear spar and the stringers (5). A manufacturing method is also provided, which comprises forming processes for the first semibox (1), the second semibox (2) and an assembly process of the first semibox (1) with the second semibox (2).
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公开(公告)号：US09669581B2
公开(公告)日：2017-06-06
申请号：US14494012
申请日：2014-09-23
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Diego García Martín , Carlos Romón Banogon , Pablo Cebolla Garrofe , Francisco Javier Honorato Ruiz , Aquilino García García , Francisco Javier Chamorro Alonso , Julio Núñez Delgado
IPC: B64F5/00 , B29C65/48 , B29C33/48 , B64C3/00 , B64C3/18 , B64C3/24 , B64C5/00 , B29C33/30 , B29D99/00 , B64F5/10 , B29L31/30
CPC classification number: B29C65/4805 , B29C33/30 , B29C33/485 , B29D99/0014 , B29L2031/3076 , B64C3/00 , B64C3/18 , B64C3/24 , B64C5/00 , B64F5/10
Abstract: Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.—positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.—subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).
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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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