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公开(公告)号：US10124876B2
公开(公告)日：2018-11-13
申请号：US14952376
申请日：2015-11-25
Applicant: Airbus Operations S.L. , Airbus Operations SAS
Inventor： Esteban Martino Gonzalez , Diego Folch Cortes , Pablo Goya Abaurrea , Angel Pascual Fuertes , Sandra Linares Mendoza , Julien Guillemaut , Eric Bouchet , Jerome Colmagro , Jonathan Blanc
Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.
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公开(公告)号：US20160229513A1
公开(公告)日：2016-08-11
申请号：US15018481
申请日：2016-02-08
Applicant: Airbus Operations (SAS) , Airbus Operations GmbH , Airbus Operations S.L.
Inventor： Henning Scheel , Eric Bouchet , Julien Guillemaut , Esteban Martino-Gonzalez
CPC classification number: B64C1/1446 , B64C1/10 , B64C1/16 , B64D27/14 , B64D27/20 , B64D29/08 , B64D37/005 , B64D2041/002 , Y02T50/44
Abstract: An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.
Abstract translation: 飞机尾锥包括机身，其中安装有航空电子设备。 尾锥包括形成在机身中的两个横向舱口，至少一个舱口形成在机身的两个相对的两侧上。 每个舱口相对于机身可移除地安装，以便收起闭合的第一位置，其中舱口关闭机身中的侧向开口，以及打开的第二位置，打开的舱口允许进入尾锥体的内部 通过相应的开口需要定期检查和/或维护操作的航空电子设备被容纳在尾锥的一部分中，该尾锥可以通过机身中的两个侧向开口接近留在机身外部的人。
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Patent Agency Ranking
公开(公告)号：US11084596B2
公开(公告)日：2021-08-10
申请号：US16173190
申请日：2018-10-29
Applicant: Airbus Operations SAS
Inventor： Eric Bouchet , Jérôme Colmagro , Michel Garcia
Abstract: An aircraft which comprises a fuselage and at least one propulsion assembly linked to the fuselage by at least two connecting rods positioned at least partially in an inner zone of the air inlet of the nacelle of the propulsion assembly. Thus, the connecting rods do not interfere with the secondary flow flowing inside the nacelle and do not affect the aerodynamic performance levels of the propulsion assembly.
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公开(公告)号：US11254437B2
公开(公告)日：2022-02-22
申请号：US16150991
申请日：2018-10-03
Applicant: AIRBUS OPERATIONS SAS
Inventor： Frederic Journade , Eric Bouchet , Olivier Barbara , Pascal Pome
Abstract: An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.
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公开(公告)号：US11084597B2
公开(公告)日：2021-08-10
申请号：US16197726
申请日：2018-11-21
Applicant: Airbus Operations SAS
Inventor： Olivier Pautis , Eric Bouchet , Olivier Barbara
Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.
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公开(公告)号：US10647440B2
公开(公告)日：2020-05-12
申请号：US15823890
申请日：2017-11-28
Applicant: Airbus Operations SAS
Inventor： Eric Bouchet , Jérôme Colmagro , Rohan Nanda , Misael Hernandez Perez
Abstract: To allow the attachment of an engine of the “Open Rotor Puller” type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.
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公开(公告)号：US10183756B2
公开(公告)日：2019-01-22
申请号：US15641771
申请日：2017-07-05
Applicant: Airbus Operations SAS
Inventor： Frederic Journade , Eric Bouchet , Nicolas Grosseau , Antoine Mutin
Abstract: An aircraft engine mount which comprises first and second parts connected by connecting elements and wherein one of the two connected parts comprises at least one transverse hole opening onto an access face of the part and into which there open at least two passage holes each intended to house a threaded shank of one of the connecting elements. The engine mount comprises a transverse nut which comprises at least two bodies joined together each having a tapped hole configured to engage with one of the threaded shanks.
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