公开(公告)号：US20220411085A1

公开(公告)日：2022-12-29

申请号：US17621467

申请日：2020-06-09

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT

IPC: B64D27/26 ,  B64C3/18

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：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：US20210114741A1

公开(公告)日：2021-04-22

申请号：US17073688

申请日：2020-10-19

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Julien CAYSSIALS

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

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：US20250002166A1

公开(公告)日：2025-01-02

申请号：US18755122

申请日：2024-06-26

Applicant: Airbus Operations SAS

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

IPC: B64D27/40

Abstract: A front engine attachment system for an engine having an engine pylon with a nose having a male clevis and a cylindrical stud, two links that are fastened to the engine by a second ball-joint connection about a second axis, a first shaft establishing a first ball-joint connection of the links to the male clevis about a first axis, wherein the first axis and the second axis are in the same vertical plane, and wherein the cylindrical stud is mounted so as to be able to move, via an annular linear connection, with respect to the front casing.

公开(公告)号：US20250002165A1

公开(公告)日：2025-01-02

申请号：US18755025

申请日：2024-06-26

Applicant: Airbus Operations SAS

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

IPC: B64D27/40

Abstract: A system for attaching a front engine of an aircraft, having: a vertical median plane, an engine pylon with a nose having a main female clevis, and a cylindrical housing around a vertical axis, a main link fastened to a front casing of the engine by a secondary ball-joint connection about a secondary axis perpendicular to the median plane by a secondary shaft, a main shaft, perpendicular to the median plane and forming a main ball-joint connection of the main link in the main female clevis about a main axis, the main and secondary axes in the plane perpendicular to the median plane, and an outer cylinder, coaxial with the vertical axis and a first end of which fastened in the cylindrical housing and a second end of which mounted, via an annular linear connection, around the vertical axis with respect to the front casing.

公开(公告)号：US20250002164A1

公开(公告)日：2025-01-02

申请号：US18755108

申请日：2024-06-26

Applicant: Airbus Operations SAS

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

IPC: B64D27/40

Abstract: A front engine attachment system for an engine having an engine pylon with a nose having a main female clevis and a cylindrical housing, a main rod fastened to the engine by a secondary ball joint connection about a secondary axis, a main shaft realizing a main ball joint connection of the main rod in the main female clevis about a main axis, wherein the main axis and the secondary axis are in the same vertical plane, a hollow outer cylinder with a vertical axis, of which a first end is fastened in the cylindrical housing and of which a second end is mounted so as to be able to move, via an annular linear connection, with respect to the front casing and an inner cylinder threaded and fastened in the outer cylinder.

公开(公告)号：US20240336365A1

公开(公告)日：2024-10-10

申请号：US18626575

申请日：2024-04-04

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Jean-Baptiste VIGNES

IPC: B64D27/40

CPC classification number: B64D27/402

Abstract: An engine pylon has a structure for fastening an aircraft engine beneath a wing and has two lateral faces. The structure has a tunnel laterally passing through it, between and through the lateral faces, and the engine pylon has a spreader housed in the tunnel and fastened in an articulated manner to each lateral face. A first end of the spreader has a first bore. A second end of the spreader has two second bores each forming a connection point with the engine. A rod is fastened in an articulated manner to the first bore and has two third bores each forming a connection point with the engine. Such an engine pylon has the ability to attach the engine, with reduced vertical bulk and with less drag.

公开(公告)号：US20240327009A1

公开(公告)日：2024-10-03

申请号：US18618244

申请日：2024-03-27

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Philippe BONHOMME ,  Paul-Adrien TAVEAU

IPC: B64D27/40 ,  F16C11/04

CPC classification number: B64D27/404 ,  F16C11/04

Abstract: A central fastening system having a first central fitting as one with a structure of a wing, a second central fitting as one with a structure of a pylon, a first connection system and a second connection system, wherein each connection system is fastened to the first central fitting and to the second central fitting by clevis type connections and wherein the two connection systems cross between the first central fitting and the second central fitting.

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.