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Patent Agency Ranking
公开(公告)号：US20170129191A1
公开(公告)日：2017-05-11
申请号：US15343788
申请日：2016-11-04
Applicant: Airbus Operations, S.L.
CPC classification number: B29C70/342 , B29C33/42 , B29C45/26 , B29C70/222 , B29C70/446 , B29C70/462 , B29C70/48 , B29K2105/08 , B29K2307/04 , B29L2031/005 , B29L2031/3082 , B29L2031/7096 , B64C1/1461 , B64C1/1492 , Y02T50/43
Abstract: The present disclosure refers to the manufacturing process of an aperture surrounding frame for an aircraft fuselage. The method includes providing a tubular braiding material (2) with a perimeter equal to the perimeter of the frame to be manufactured, cutting the tubular braiding material (2) to obtain annular-shaped braiding slices (3), providing an annular-shaped inner mold (4) where the annular-shaped inner mold has a surface with a desired shape for the aperture surrounding frame, layering up at least one braiding slice (3) around the inner mold (4), forming the at least one braiding slice (3) around the inner mold (4), and curing the aperture surrounding frame pre-form. The present disclosure also refers to an aperture surrounding frame (1) for an aircraft fuselage formed as a continuous body by at least one annular-shaped braiding slice (3) with a perimeter equal to the perimeter of the desired aperture surrounding frame.
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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：US09033695B2
公开(公告)日：2015-05-19
申请号：US14337678
申请日：2014-07-22
Applicant: Airbus Operations S.L.
IPC: B29C45/17
CPC classification number: B29C45/1777 , B29C33/0061 , B29C70/443 , B29C70/48 , B29C70/546 , F16B2/14
Abstract: An injection interface device comprising a wedge having a first surface mountable over the joint between the mold and the terminal element and a second surface being inclined with respect to the first surface. A fixation element is mountable against the second surface and an attachment element. The device is configured so that it avoids or prevents the movement of the wedge in a direction parallel to the mold and the movement of the fixation element in a direction perpendicular to the mold so that a displacement of the fixation element parallel to the mold makes a displacement of the wedge in a direction perpendicular to the mold so that the wedge presses against the terminal element to seal it.
Abstract translation: 一种注射界面装置，包括楔形件，其具有可安装在模具和端子元件之间的接头上的第一表面和相对于第一表面倾斜的第二表面。 固定元件可抵靠第二表面和附接元件安装。 该装置被构造成使得它避免或阻止楔块沿着与模具平行的方向的移动以及固定元件在垂直于模具的方向上的移动，使得固定元件与模具平行的位移使得 楔形件在垂直于模具的方向上移位，使得楔形件压靠端子元件以将其密封。
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公开(公告)号：US10293557B2
公开(公告)日：2019-05-21
申请号：US15343788
申请日：2016-11-04
Applicant: Airbus Operations, S.L.
IPC: B29C70/34 , B29C33/42 , B29C45/26 , B29C70/48 , B29C70/44 , B29C70/46 , B29C70/22 , B64C1/14 , B29K105/08 , B29K307/04 , B29L31/30 , B29L31/00
Abstract: The present disclosure refers to the manufacturing process of an aperture surrounding frame for an aircraft fuselage. The method includes providing a tubular braiding material (2) with a perimeter equal to the perimeter of the frame to be manufactured, cutting the tubular braiding material (2) to obtain annular-shaped braiding slices (3), providing an annular-shaped inner mold (4) where the annular-shaped inner mold has a surface with a desired shape for the aperture surrounding frame, layering up at least one braiding slice (3) around the inner mold (4), forming the at least one braiding slice (3) around the inner mold (4), and curing the aperture surrounding frame pre-form. The present disclosure also refers to an aperture surrounding frame (1) for an aircraft fuselage formed as a continuous body by at least one annular-shaped braiding slice (3) with a perimeter equal to the perimeter of the desired aperture surrounding frame.
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公开(公告)号：US20150030715A1
公开(公告)日：2015-01-29
申请号：US14337678
申请日：2014-07-22
Applicant: Airbus Operations S.L.
IPC: B29C45/17
CPC classification number: B29C45/1777 , B29C33/0061 , B29C70/443 , B29C70/48 , B29C70/546 , F16B2/14
Abstract: An injection interface device comprising a wedge having a first surface mountable over the joint between the mold and the terminal element and a second surface being inclined with respect to the first surface. A fixation element is mountable against the second surface and an attachment element. The device is configured so that it avoids or prevents the movement of the wedge in a direction parallel to the mold and the movement of the fixation element in a direction perpendicular to the mold so that a displacement of the fixation element parallel to the mold makes a displacement of the wedge in a direction perpendicular to the mold so that the wedge presses against the terminal element to seal it.
Abstract translation: 一种注射界面装置，包括楔形件，其具有可安装在模具和端子元件之间的接头上的第一表面和相对于第一表面倾斜的第二表面。 固定元件可抵靠第二表面和附接元件安装。 该装置被构造成使得它避免或阻止楔块沿着与模具平行的方向的移动以及固定元件在垂直于模具的方向上的移动，使得固定元件与模具平行的位移使得 楔形件在垂直于模具的方向上移位，使得楔形件压靠端子元件以将其密封。
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