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公开(公告)号：US11807374B2
公开(公告)日：2023-11-07
申请号：US17947273
申请日：2022-09-19
Applicant: Airbus Operations (S.A.S.)
Inventor： Michael Berjot , Thomas Robiglio , Karla Mariana Arellanes Mendoza
CPC classification number: B64D27/26 , F02C7/20 , B64D2027/268
Abstract: A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.
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Patent Agency Ranking
2.发明申请AIRCRAFT ASSEMBLY COMPRISING A MOUNTING STRUT BUILT INTO THE NACELLE AND ARRANGED AT THE REAR SECTION OF THE FUSELAGE 审中-公开包括安装在内的飞机组件安装在NACELLE上并安装在FUSELAGE的后面部分公开(公告)号：US20150259074A1
公开(公告)日：2015-09-17
申请号：US14575332
申请日：2014-12-18
Applicant: Airbus Operations (S.A.S.)
Inventor： Julien Guillemaut , Sébastien Alby , Jérôme Colmagro , Pascal Pome , Jonathan Blanc , Thomas Robiglio , Tobias Sjostrom
CPC classification number: B64D27/26 , B64D27/20 , B64D2027/262
Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.
Abstract translation: 为了减少发动机变形，本文公开的主题提供了一种用于飞行器的组件，其包括飞行器后部，发动机，机舱和用于将发动机安装在后部上的安装支柱，该组件还包括安装 将发动机安装在支柱的刚性结构上，该安装件包括两个发动机支架，其被设计成反应由发动机产生的轴向推力。 根据本文公开的主题，支柱的刚性结构包括部分包围发动机的第一部分，该第一部分包括形成机舱的外部空气动力学表面的一部分的外部皮肤，并且两个发动机支架沿径向相对 彼此在刚性结构的后部附接到第一部分。
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公开(公告)号：US20230113400A1
公开(公告)日：2023-04-13
申请号：US17947273
申请日：2022-09-19
Applicant: Airbus Operations (S.A.S.)
Inventor： Michael Berjot , Thomas Robiglio , Karla Mariana Arellanes Mendoza
IPC: B64D27/26
Abstract: A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.
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公开(公告)号：US11554872B2
公开(公告)日：2023-01-17
申请号：US17386966
申请日：2021-07-28
Applicant: Airbus Operations (S.A.S.)
Inventor： Laurent Frenot , Olivier Pautis , Michael Berjot , Thomas Robiglio , Germain Gueneau
Abstract: A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.
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公开(公告)号：US20220033098A1
公开(公告)日：2022-02-03
申请号：US17386966
申请日：2021-07-28
Applicant: Airbus Operations (S.A.S.)
Inventor： Laurent Frenot , Olivier Pautis , Michael Berjot , Thomas Robiglio , Germain Gueneau
Abstract: A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.
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公开(公告)号：US10336458B2
公开(公告)日：2019-07-02
申请号：US14575332
申请日：2014-12-18
Applicant: Airbus Operations (S.A.S.)
Inventor： Julien Guillemaut , Sébastien Alby , Jérôme Colmagro , Pascal Pome , Jonathan Blanc , Thomas Robiglio , Tobias Sjostrom
Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.
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