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公开(公告)号：US11319079B2
公开(公告)日：2022-05-03
申请号：US16228966
申请日：2018-12-21
Applicant: Airbus Operations SAS
Inventor： Olivier Pautis , Jérôme Colmagro
Abstract: An aircraft comprises a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. This arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure, at least one securing member articulated to each of the first and second connecting portions. Furthermore, the first connecting portions of the two fittings are made in one piece in a single wing connector extending over essentially the entire height of the front wing spar.
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公开(公告)号：US11897622B2
公开(公告)日：2024-02-13
申请号：US16368305
申请日：2019-03-28
Applicant: Airbus Operations SAS
Inventor： Patrick Lieven , Jérôme Colmagro
CPC classification number: B64D27/02 , B64D27/12 , B64D27/24 , F01D15/10 , F02C6/00 , B64D2027/026 , F05D2220/323 , F05D2220/76
Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.
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公开(公告)号：US11840347B2
公开(公告)日：2023-12-12
申请号：US17114703
申请日：2020-12-08
Applicant: Airbus Operations SAS
Inventor： Jérôme Colmagro , Paolo Messina
CPC classification number: B64D27/26 , B64F5/10 , F16C11/045 , B64D2027/268 , Y10T403/32909
Abstract: An assembly including a link axis supported by first and second guiding rings positioned in first and second branches of a clevis, one of the guiding rings including a tubular extension, protruding with respect to an outer face of one of the branches, which has a threaded portion on its outer circumferential face. Complementing this, the assembly includes a nut configured to be screwed onto the threaded portion of the tubular extension and an immobilization system configured to immobilize the nut in translation and/or in rotation, the nut and the link axis being linked by a complete link that is non-removable or that forms a single-piece part. This solution makes it possible to reduce the number of parts forming the assembly. Also provided are an engine attachment and an aircraft including such an assembly.
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公开(公告)号：US11987029B2
公开(公告)日：2024-05-21
申请号：US17824102
申请日：2022-05-25
Applicant: Airbus Operations SAS
Inventor： Jérôme Colmagro , Charles Cariou , Florian Ravise , Maxime Gauthier
CPC classification number: B32B3/12 , B32B3/20 , B32B37/146 , B32B38/0004 , B32B38/0012 , B32B2250/03 , B32B2305/024 , B32B2307/102 , B32B2605/18 , B64D29/00
Abstract: A method for manufacturing a cellular structure having first and second faces, rows of cells each alternatingly having first cells, which are open in the direction of the first face, second cells, which are open in the direction of the second face, and also third cells formed between each row of cells, each row of cells comprising first and second strips of material placed against one another. The first and second strips of material are shaped by bending. By contrast to plastic deformation, shaping by bending makes it possible to expand the choice of materials and thicknesses for the first and second strips of material. An advantageous cellular structure is thus obtained as well as an acoustic absorption coating comprising such a cellular structure.
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公开(公告)号：US11027852B2
公开(公告)日：2021-06-08
申请号：US16264909
申请日：2019-02-01
Applicant: Airbus Operations SAS
Inventor： Laurent Lafont , Stéphane Dida , Jérôme Colmagro
Abstract: An assembly for an aircraft and comprising a wing comprising an airfoil box partly produced using a front spar, a mounting pylon arranged under the wing and comprising a primary structure formed as a primary box having a top spar extending at least partly under the airfoil box and having a slit, a bottom spar, lateral panels and a transverse reinforcing fixing rib, of which a bottom part is housed and fixed inside the primary structure and of which a top part passes through the slit. A fixing arrangement fixes the top part to the front spar. The fixing arrangement comprises a plurality of fixing bolts, where each fixing bolt fixes the top part to the front spar and has its axis at right angles to the fixing rib. Such an assembly allows the mounting pylon primary structure to be as close as possible to the wing.
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Patent Agency Ranking
公开(公告)号：US10994380B2
公开(公告)日：2021-05-04
申请号：US16199795
申请日：2018-11-26
Applicant: Airbus Operations SAS
Inventor： Jérôme Colmagro , Aurélien Mauconduit , Julien Moulis
IPC: B23P19/02 , B23P19/10 , B23P19/12 , B64F5/10 , B25B27/02 , B25B27/14 , F16C11/04 , B64D27/26 , B21D39/20
Abstract: A device for manipulating a hollow shaft configured to create a pivot link between a first element and a second element. The manipulation device comprises a cylindrical body having a diameter variable by radial contraction or radial expansion of the cylindrical body, a module for controlling the diameter of the cylindrical body configured so that the diameter of the cylindrical body has alternatively at least a first diameter suitable for the cylindrical body to be displaced in the hollow shaft and a second diameter suitable for the cylindrical body to be blocked in the hollow shaft. The cylindrical body comprises an end configured to protrude from the hollow shaft when the cylindrical body is blocked in the hollow shaft. The manipulation device allows the alignment of the orifices due to the end configuration of the cylindrical body.
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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：US11840348B2
公开(公告)日：2023-12-12
申请号：US17509113
申请日：2021-10-25
Applicant: Airbus Operations SAS
Inventor： Olivier Pautis , Jérôme Colmagro
CPC classification number: B64D27/26 , F02C7/20 , B64D2027/264 , B64D2027/266 , B64D2027/268
Abstract: An engine mounting pylon for suspending a turbofan beneath an aircraft wing, including a primary structure, a fastening device for fastening to the turbofan, and a fastening device for fastening to the wing. The engine mounting pylon furthermore comprises multiple rigid braces that mechanically connect the primary structure to the wing of the aircraft, a first brace-attachment device that mechanically connects a first end of each brace to the wing, and a second brace-attachment device that mechanically connects a second end of each brace to the primary structure. This braced-pylon architecture makes it possible to reduce the dimensions of the primary structure and the various elements that constitute the first and second attachment devices.
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公开(公告)号：US11319080B2
公开(公告)日：2022-05-03
申请号：US16230200
申请日：2018-12-21
Applicant: Airbus Operations SAS
Inventor： Olivier Pautis , Jérôme Colmagro
Abstract: An aircraft comprising a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. The arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure of the attachment pylon, at least one securing member linking the first and second connecting portions, this securing member being articulated to the first connecting portion with the aid of a first pin system oriented substantially parallel to the front wing spar.
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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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