公开(公告)号：US20200369396A1

公开(公告)日：2020-11-26

申请号：US16879121

申请日：2020-05-20

Applicant: Airbus Operations SAS

Inventor： Christophe LABARTHE ,  Michael BERJOT ,  Thomas DEFORET

IPC: B64D27/26

Abstract: A rear engine attachment system for an aircraft engine. The attachment system has an engine pylon with a lower spar having a lower surface, and a rear engine attachment having a beam fixed against the lower surface and to which a pair of rods is fixed. Each rod is fixed to the beam by at least one first connection point and to the engine by at least one second connection point. The beam includes front and rear fittings, and an intermediate fitting with a shoe and an intermediate clevis. The shoe presses against the lower surface. The front fitting presses against the intermediate fitting at the front and the rear fitting presses against the intermediate fitting at the rear. The fixing to the lower spar is ensured by bolts, each passing through the front base or the rear base, the shoe and the lower spar.

公开(公告)号：US20200298986A1

公开(公告)日：2020-09-24

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：US20240150028A1

公开(公告)日：2024-05-09

申请号：US18502248

申请日：2023-11-06

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT ,  Pierre-Antoine COMBES ,  Paul-Adrien TAVEAU

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/264

Abstract: An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

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：US20200262571A1

公开(公告)日：2020-08-20

申请号：US16791094

申请日：2020-02-14

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Isabelle PETRISSANS

IPC: B64D27/26

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.

公开(公告)号：US20250010999A1

公开(公告)日：2025-01-09

申请号：US18761946

申请日：2024-07-02

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Rémi LANSIAUX ,  Jean-Baptiste VIGNES ,  Veronica PARASCHIV

IPC: B64D27/40

Abstract: A propulsion unit comprising an engine, a pylon, an engine mount system which connects a front part of the engine and the pylon, in addition to a suspension system which connects the pylon and a rear part of the engine which is offset toward the rear end of the engine relative to the engine mount system.

公开(公告)号：US20220355946A1

公开(公告)日：2022-11-10

申请号：US17756554

申请日：2020-11-16

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Jacky PUECH ,  Rémi LANSIAUX

IPC: B64D27/26

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：US20220106048A1

公开(公告)日：2022-04-07

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：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：US20250010997A1

公开(公告)日：2025-01-09

申请号：US18761912

申请日：2024-07-02

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT ,  Jean-Baptiste VIGNES

IPC: B64D27/40

Abstract: An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.