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Patent Agency Ranking
公开(公告)号：US10807732B2
公开(公告)日：2020-10-20
申请号：US15807857
申请日：2017-11-09
Applicant: Airbus Operations GmbH , Airbus Operations S.L.
Inventor： Daniel Reckzeh , Raul Carlos Llamas Sandin
Abstract: An aircraft comprising a fuselage extending along a longitudinal axis between a fore section and an aft section, wings mounted to the fuselage, a tail unit mounted to the aft section of the fuselage, and a first propulsion unit and a second propulsion unit both mounted to the aft section of the fuselage in such a way that a first axis of rotation of the first propulsion unit and a second axis of rotation of the second propulsion unit both extend in a vertical center plane spanned by the longitudinal axis and a yaw axis. The provided centerline mounted double-engine aircraft allows for a simple manufacture, maintenance and retrofit of the engines, in that the first propulsion unit and/or the second propulsion unit are arranged outside the fuselage.
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公开(公告)号：US09481443B2
公开(公告)日：2016-11-01
申请号：US14445537
申请日：2014-07-29
Applicant: Airbus Operations S.L.
Inventor： Alfonso Gonzalez Gozalbo , Raul Carlos Llamas Sandin
CPC classification number: B64C1/068 , B64C1/10 , B64C1/26 , B64C5/02 , B64C5/16 , B64C7/00 , B64C9/00 , B64C25/00 , B64C2025/005
Abstract: A rear fuselage section of an aircraft comprises at least one closed frame constructed as a unitary body, and a horizontal tail plane comprising a box-type central element and two lateral torsion boxes, said horizontal tail plane trimmable with respect to a pivot axis. The horizontal tail plane is mounted at the closed frame and the pivot axis is contained in a horizontal plane below the lowest end of said closed frame.
Abstract translation: 飞行器的后部机身部分包括构造为整体的至少一个封闭框架，以及包括箱型中心元件和两个横向扭转箱的水平尾翼平面，所述水平尾翼平面相对于枢转轴线可修剪。 水平尾翼平面安装在闭合的框架上，枢转轴线包含在所述闭合框架的最下端下方的水平平面内。
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公开(公告)号：US20150034765A1
公开(公告)日：2015-02-05
申请号：US14445537
申请日：2014-07-29
Applicant: Airbus Operations S.L.
Inventor： Alfonso Gonzalez Gozalbo , Raul Carlos Llamas Sandin
CPC classification number: B64C1/068 , B64C1/10 , B64C1/26 , B64C5/02 , B64C5/16 , B64C7/00 , B64C9/00 , B64C25/00 , B64C2025/005
Abstract: A rear fuselage section of an aircraft comprises at least one closed frame constructed as a unitary body, and a horizontal tail plane comprising a box-type central element and two lateral torsion boxes, said horizontal tail plane trimmable with respect to a pivot axis. The horizontal tail plane is mounted at the closed frame and the pivot axis is contained in a horizontal plane below the lowest end of said closed frame.
Abstract translation: 飞行器的后部机身部分包括构造为整体的至少一个封闭框架，以及包括箱型中心元件和两个横向扭转箱的水平尾翼平面，所述水平尾翼平面相对于枢转轴线可修剪。 水平尾翼平面安装在闭合的框架上，枢转轴线包含在所述闭合框架的最下端下方的水平平面内。
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公开(公告)号：US11192639B2
公开(公告)日：2021-12-07
申请号：US16869798
申请日：2020-05-08
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Raul Carlos Llamas Sandin
Abstract: An aircraft (5) including an aerodynamic surface (6), an aerodynamics improvement device with a first electrode (27) embedded beneath and electrically isolated from the aerodynamic surface (6), a second electrode (28) electrically isolated from the first electrode (27), a voltage generator (30) adapted to apply a voltage between the first and the second electrode, further comprising a layer of electrically insulating material (26) between the second electrode (28) and the aerodynamic surface (6). Methods for detecting ice on and de-icing an aerodynamic surface (6), and for delaying a boundary layer transition and separation from the aerodynamic surface.
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公开(公告)号：US20180134406A1
公开(公告)日：2018-05-17
申请号：US15807857
申请日：2017-11-09
Applicant: Airbus Operations GmbH , Airbus Operations S.L.
Inventor： Daniel Reckzeh , Raul Carlos Llamas Sandin
CPC classification number: B64D33/02 , B64C5/02 , B64C7/02 , B64D27/20 , B64D27/26 , B64D2033/0226 , Y02T50/44
Abstract: An aircraft comprising a fuselage extending along a longitudinal axis between a fore section and an aft section, wings mounted to the fuselage, a tail unit mounted to the aft section of the fuselage, and a first propulsion unit and a second propulsion unit both mounted to the aft section of the fuselage in such a way that a first axis of rotation of the first propulsion unit and a second axis of rotation of the second propulsion unit both extend in a vertical center plane spanned by the longitudinal axis and a yaw axis. The provided centerline mounted double-engine aircraft allows for a simple manufacture, maintenance and retrofit of the engines, in that the first propulsion unit and/or the second propulsion unit are arranged outside the fuselage.
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