公开(公告)号：US20240101262A1

公开(公告)日：2024-03-28

申请号：US18471721

申请日：2023-09-21

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Germain GUENEAU ,  Pierre-Antoine COMBES ,  Paul-Adrien TAVEAU

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: A propulsion assembly for an aircraft, having a turbomachine, a pylon, and a device for reacting thrust forces having a main fitting, a spreader pivoting on the main fitting and having an opening, two rods articulated to the turbomachine and to the spreader, a secondary fitting fastened beneath the pylon and having a secondary female clevis constituted of two secondary arms passed through by holes of oblong shape and aligned along a secondary axis (R2), wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis (R2), and a backup connection pin inserted with a tight fit into the opening and with clearance into the holes. Also an aircraft with such a propulsion assembly.

公开(公告)号：US20250074610A1

公开(公告)日：2025-03-06

申请号：US18819052

申请日：2024-08-29

Applicant: Airbus Operations SAS

Inventor： Germain GUENEAU ,  Pierre-Antoine COMBES ,  Marc DE NICOLA

IPC: B64D27/40 ,  B64D27/18

Abstract: An assembly comprising a wing and a reactor mast fixed to the wing. The primary structure of the reactor mast comprises a first fixing lug and starboard and port fixing lugs, the wing carries a first fitting and starboard and port fittings, the fixing lugs being joined to the fittings with shackles having three fixing points, and the first lug being fixed to the first fitting.

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：US20220340293A1

公开(公告)日：2022-10-27

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

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：US20220017229A1

公开(公告)日：2022-01-20

申请号：US17375393

申请日：2021-07-14

Applicant: Airbus Operations SAS

Inventor： Germain GUENEAU ,  Michael BERJOT ,  Olivier PAUTIS

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

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：US20250051020A1

公开(公告)日：2025-02-13

申请号：US18796631

申请日：2024-08-07

Applicant: Airbus Operations SAS

Inventor： Frédéric JOURNADE ,  Olivier PAUTIS ,  Jérôme COLMAGRO ,  Germain GUENEAU ,  Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Fabrice GRIMAL

IPC: B64D27/40

Abstract: A propulsion system comprising a turbojet with a fan casing and a central casing, a pylon with an upper spar, a front wall and on either side of a vertical median plane, a fitting rigidly fixed to the rigid structure, a cylindrical pin as one with the fan casing and inserted in a hole of the upper spar, a shackle with at the vertical median plane, an upper articulation between the shackle and the front wall and on either side of the vertical median plane, a lower articulation between the shackle and the central casing, and two reaction rods disposed on either side of the median plane, where each rod is articulated, at a front end, on the central casing, and, at rear end, on the fitting.

公开(公告)号：US20250010998A1

公开(公告)日：2025-01-09

申请号：US18761974

申请日：2024-07-02

Applicant: Airbus Operations SAS

Inventor： Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Germain GUENEAU ,  Olivier PAUTIS

IPC: B64D27/40 ,  B64D27/18

Abstract: An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.

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.