公开(公告)号：US20210354839A1

公开(公告)日：2021-11-18

申请号：US17318454

申请日：2021-05-12

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT ,  Olivier DUBOIS ,  Germain GUENEAU

IPC: B64D27/26

Abstract: 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.

公开(公告)号：US20200369393A1

公开(公告)日：2020-11-26

申请号：US16878011

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Rémi LANSIAUX ,  Olivier DUBOIS ,  Jacky PUECH

IPC: B64D27/26

Abstract: 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.

公开(公告)号：US20200369394A1

公开(公告)日：2020-11-26

申请号：US16878034

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Rémi LANSIAUX ,  Olivier DUBOIS ,  Anthony MERTES ,  Jacky PUECH

IPC: B64D27/26

Abstract: 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.

公开(公告)号：US20200346771A1

公开(公告)日：2020-11-05

申请号：US16807351

申请日：2020-03-03

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Rémi LANSIAUX ,  Olivier DUBOIS ,  Anthony MERTES ,  David ALRIC ,  Stéphane NOGUES

IPC: B64D27/26

Abstract: 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.

公开(公告)号：US20200331619A1

公开(公告)日：2020-10-22

申请号：US16849293

申请日：2020-04-15

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Olivier DUBOIS

IPC: B64D27/26

Abstract: An engine attachment system for an engine including an engine nacelle. The engine attachment system includes an engine pylon with a starboard face and a port face, a starboard shoe having a starboard sole fixed to the starboard face and a starboard wall secured to the starboard sole, a port shoe having a port sole fixed to the port face and a port wall secured to the port sole, a starboard link fixed in an articulated manner by one of its ends to the starboard wall and configured to be articulatedly fixed by the other of its ends to the engine nacelle, a port link articulatedly fixed by one of its ends to the port wall and configured to be atriculatedly fixed by the other of its ends to the engine nacelle, and a fixing arrangement that fixes each sole to the corresponding face of the engine pylon.

公开(公告)号：US20200262572A1

公开(公告)日：2020-08-20

申请号：US16778950

申请日：2020-01-31

Applicant: Airbus Operations SAS

Inventor： Jean-Marc CANTIN ,  Olivier DUBOIS

IPC: B64D33/02 ,  B64F5/10

Abstract: 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.

公开(公告)号：US20190315477A1

公开(公告)日：2019-10-17

申请号：US16363513

申请日：2019-03-25

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE ,  Olivier DUBOIS

IPC: B64D27/26

Abstract: 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.

公开(公告)号：US20180178923A1

公开(公告)日：2018-06-28

申请号：US15849243

申请日：2017-12-20

Applicant: Airbus Operations SAS

Inventor： Isabelle PETRISSANS-LLOVERAS ,  Guillaume GALLANT ,  Olivier GLEIZE ,  Olivier DUBOIS ,  Aurelien PANTEL

IPC: B64D27/26 ,  B64D27/18 ,  B64F5/10

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/264 ,  B64F5/10 ,  Y02T50/44

Abstract: Fixation of an aircraft engine attachment pylon to the wing of an aircraft by means of an attachment device attached to a wing structure by means of first attachment through-members. The attachment device and the attachment pylon have respective junction surfaces clamped to each other by means of second attachment through-members. The junction surfaces extend along a plane forming an angle of less than 45 degrees with a vertical direction of the aircraft. A method for assembling the attachment pylon to the wing includes the positioning of the attachment pylon facing the attachment device, and then the clamping of the respective junction surfaces of the attachment device and of the attachment pylon to each other via the second attachment through-members.