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公开(公告)号：US11572184B2
公开(公告)日：2023-02-07
申请号：US16878006
申请日：2020-05-19
发明人： Thomas Deforet , Rémi Lansiaux , Olivier Dubois , Jacky Puech
IPC分类号： B64D27/26
摘要： A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and a front engine attachment having a beam that is fixed against the front face and to which is fixed, on either side of a median plane, a rod system, wherein each rod system is fixed to the beam in an articulated manner by at least one first connection point, and is configured to be fixed to a front part of the engine in an articulated manner by at least one second connection point. Such a front engine attachment system thus has rod systems having two rods, allowing the shape of the rods and the shape of the beam to be simplified.
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公开(公告)号：US11535389B2
公开(公告)日：2022-12-27
申请号：US16878011
申请日：2020-05-19
发明人： Thomas Deforet , Rémi Lansiaux , Olivier Dubois , Jacky Puech
IPC分类号： B64D27/26
摘要： A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.
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公开(公告)号：US20210130001A1
公开(公告)日：2021-05-06
申请号：US17081193
申请日：2020-10-27
发明人： Julien Allain , Stéphane Dida , Jérome Colmagro , Olivier Dubois , Julien Moulis , Jacky Puech , Laurent Lafont
摘要： The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.
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公开(公告)号：US11807373B2
公开(公告)日：2023-11-07
申请号：US17081193
申请日：2020-10-27
发明人： Julien Allain , Stéphane Dida , Jérome Colmagro , Olivier Dubois , Julien Moulis , Jacky Puech , Laurent Lafont
CPC分类号： B64D27/26 , B64F5/10 , F16B5/08 , B64D2027/266
摘要： The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.
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公开(公告)号：US11377224B2
公开(公告)日：2022-07-05
申请号：US16778950
申请日：2020-01-31
发明人： Jean-Marc Cantin , Olivier Dubois
摘要： A system comprising a trolley which comprises a platform and wheels attached beneath the platform, an air intake of an aircraft engine, where the air intake rests on the platform so as to have its narrowest part at the top and its widest part at the bottom, and an inflatable protection item in the form of a closed envelope which is placed around the widest part of the air intake. A system of this kind makes it possible to protect the air intake from collisions that it might experience during movement of the trolley, and to increase safety by avoiding collisions between operators and the air intake.
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公开(公告)号：US11345479B2
公开(公告)日：2022-05-31
申请号：US16363513
申请日：2019-03-25
发明人： Jean Geliot , Thomas Deforet , Adeline Soulie , Olivier Dubois
IPC分类号： B64D27/26
摘要： An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.
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公开(公告)号：US11325715B2
公开(公告)日：2022-05-10
申请号：US16807351
申请日：2020-03-03
发明人： Thomas Deforet , Rémi Lansiaux , Olivier Dubois , Anthony Mertes , David Alric , Stéphane Nogues
IPC分类号： B64D27/26
摘要： A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.
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公开(公告)号：US12054271B2
公开(公告)日：2024-08-06
申请号：US17391825
申请日：2021-08-02
申请人： Airbus SAS , Airbus Operations SAS
发明人： Sebastien Alby , Jean Geliot , Thomas Deforet , Olivier Dubois , Joël Dedieu , Xavier Bardey
摘要： A method for assembling an aircraft pylon including a primary structure and at least one internal system positioned at least partially within the primary structure, wherein the assembly method includes a first step of assembling a part of the primary structure so that the interior of the primary structure remains accessible, a step of mounting an internal systems module including at least one support and at least one internal system connected to the support, a second step of assembling the internal systems module and the partially assembled primary structure, a third step of assembling any element of the primary structure not assembled in the first assembly step, and an aircraft pylon assembled by such a method.
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公开(公告)号：US11713128B2
公开(公告)日：2023-08-01
申请号：US17318454
申请日：2021-05-12
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/268
摘要： An assembly including a connecting device, connecting first and second parts, including first and second links positioned on respective opposite sides of the first and second parts and an interleaved stiffener, positioned between the first and second links, having a first contact face oriented toward the first link and a second contact face oriented toward the second link, parallel to the first face, the first and second contact faces being separated by a distance equal to that separating the first and second links. This interleaved stiffener makes it possible to limit the risks of bending of the links when they are loaded in compression.
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10.发明授权公开(公告)号：US11518534B2
公开(公告)日：2022-12-06
申请号：US16878034
申请日：2020-05-19
发明人： Thomas Deforet , Rémi Lansiaux , Olivier Dubois , Anthony Mertes , Jacky Puech
IPC分类号： B64D27/26
摘要： A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.
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