公开(公告)号：US11753177B2

公开(公告)日：2023-09-12

申请号：US17621467

申请日：2020-06-09

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Michael Berjot

IPC: B64D27/26 ,  B64C3/18

CPC classification number: B64D27/26 ,  B64C3/185 ,  B64D2027/262

Abstract: An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

公开(公告)号：US11702216B2

公开(公告)日：2023-07-18

申请号：US17073688

申请日：2020-10-19

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Julien Cayssials

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/266

Abstract: An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

公开(公告)号：US11975856B2

公开(公告)日：2024-05-07

申请号：US17756554

申请日：2020-11-16

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Jacky Puech ,  Rémi Lansiaux

IPC: B64D27/40 ,  B64D27/18

CPC classification number: B64D27/40 ,  B64D27/18

Abstract: A front engine attachment system for an engine of an aircraft. An engine pylon has a frontal rib with a front engine attachment with a first link rod which is fixed directly to the frontal rib by two connecting points. A second link rod is provided which has a first end fixed to the first link rod by a connecting point. The first link rod is fixed directly to an engine casing by at least two connecting points and a second end of the second link rod is fixed to the engine casing by a third connecting point. The first link rod may be made up of two adjoining plates that are fixed together. Also, an aircraft with such a front engine attachment system.

公开(公告)号：US11618579B2

公开(公告)日：2023-04-04

申请号：US17488540

申请日：2021-09-29

Applicant: Airbus Operations SAS

Inventor： Germain Gueneau ,  Thomas Robiglio ,  Michael Berjot

IPC: B64D27/26 ,  B64C3/18

Abstract: An assembly of a pylon and of a wing of an aircraft, the pylon including a primary structure with a rear face and an upper spar. The assembly includes a rear fastening system including a pair of vertical shackles articulated between the rear face of the primary structure and a first shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection, and a pair of transverse shackles articulated between the rear face of the primary structure and a second shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection. With such an assembly, the bulk of the rear fastening system is reduced.

公开(公告)号：US11459115B2

公开(公告)日：2022-10-04

申请号：US16819941

申请日：2020-03-16

Applicant: Airbus Operations SAS

Inventor： Julien Cayssials ,  Michael Berjot

IPC: B64D27/26

Abstract: A rear engine fastener for an aircraft connecting a primary structure and an engine of an aircraft, the rear engine fastener comprising a support configured to be connected to the primary structure, at least one main shackle connected to the support by first and second support link pins, which are symmetrical relative to a vertical longitudinal plane, and to the engine by a first lateral engine link pin and by a central engine link pin, and at least one secondary shackle connected to the engine by a second lateral engine link pin and to the main shackle by a secondary link pin.

公开(公告)号：US11713128B2

公开(公告)日：2023-08-01

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

CPC classification number: B64D27/26 ,  B64D2027/268

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：US11679886B2

公开(公告)日：2023-06-20

申请号：US17725641

申请日：2022-04-21

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Rémi Lansiaux ,  William Bras ,  Germain Gueneau ,  Sébastien Van Arendonk ,  Jacques Demange ,  Sébastien Commenge

IPC: B64D27/26 ,  B64D27/18 ,  F02C7/20

CPC classification number: B64D27/18 ,  F02C7/20 ,  B64D2027/268

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 having a central part connected to the support and a first and a second end that are connected to thrust rods, at least one limiting system for limiting the travel of the spreader having an upper and a lower stop between which is positioned the first or second end of the spreader, the upper and the lower stop being connected to one another so as to form a single part connected to a fitting secured to the support.

公开(公告)号：US11572186B2

公开(公告)日：2023-02-07

申请号：US17375393

申请日：2021-07-14

Applicant: Airbus Operations SAS

Inventor： Germain Gueneau ,  Michael Berjot ,  Olivier Pautis

IPC: B64D27/26 ,  B64C3/32 ,  B64D27/16 ,  B64C3/18

Abstract: An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

公开(公告)号：US11434016B2

公开(公告)日：2022-09-06

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：US11319082B2

公开(公告)日：2022-05-03

申请号：US16791094

申请日：2020-02-14

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Isabelle Petrissans

IPC: B64D27/26 ,  B64D27/18

Abstract: An assembly comprising a wing with lower spars, a mounting pylon having an upper spar and two lateral panels, a front fixing system and a rear fixing system, each comprising a beam pierced with a principal bore and, for each beam, an upper bore traversing the upper spar and a shear pin positioned in the upper bore and in the principal bore. The assembly also comprises, for each fixing system, bolts, the nut of which is accommodated in a secondary hole of the beam and the screw of which traverses the upper spar and the beam in order to be screwed into the nut.