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：US20250115365A1

公开(公告)日：2025-04-10

申请号：US18905523

申请日：2024-10-03

Applicant: Airbus Operations SAS

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

IPC: B64D27/40

Abstract: An aircraft comprising at least one engine attachment system connecting a primary structure of a pylon and a motor, having a right-hand interface connected to the right-hand lateral face of the primary structure, a left-hand interface connected to the left-hand lateral face of the primary structure, first and second shackles connecting the right-hand and left-hand interfaces to the motor by virtue of engine connection pins and interface connection pins, a right-hand emergency connection pin cooperating with the right-hand interface and the motor, and a left-hand emergency connection pin cooperating with the left-hand interface and the motor.

公开(公告)号：US20200307815A1

公开(公告)日：2020-10-01

申请号：US16826993

申请日：2020-03-23

Applicant: Airbus Operations SAS

Inventor： Isabelle PETRISSANS ,  Rémi LANSIAUX ,  Pascal FORICHON ,  Patrice PEREZ ,  Wan HU

IPC: B64D27/26

Abstract: An assembly for an aircraft, which includes a pylon with a bearing face and a contact face, an engine mount with a bearing face and a contact face bearing against the contact face of the pylon, at least two bolts comprising a threaded stem with a head and a nut bearing against the bearing face of the engine mount, for each head, a bearing washer with a first bearing face and a second bearing face, where the second bearing face of the bearing washer bears against the bearing face of the pylon, and where the head bears against the first bearing face of the bearing washer, a shoe, and, for each bearing washer, a clamp that is secured to the shoe and comprises a first branch and a second branch between which the bearing washer is clamped and is free to rotate.

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：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：US20200346772A1

公开(公告)日：2020-11-05

申请号：US16814475

申请日：2020-03-10

Applicant: Airbus Operations SAS

Inventor： Rémi LANSIAUX ,  Anthony MERTES ,  Pascal FORICHON ,  Patrice PEREZ

IPC: B64D27/26 ,  B64D27/02

Abstract: A rear engine attachment having a beam fixed to a pylon, a spreader pivotally mounted on the beam, the spreader comprising two ends situated on either side of a median plane, two rods located one on either side of the median plane, each rod having a first end fixed to one end of the spreader by a ball joint and a second end fixed to the engine, each ball joint comprising a clevis with two arms at the first end of the rod, a swivel bearing arranged on the end of the spreader, and a hinge pin passing through the two arms, the swivel bearing arranged between the two arms and fitted on the hinge pin. For each ball joint, an interface part is removably interposed between the end of the spreader and the first end of the rod and forms a contact surface between the spreader and the rod.

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.