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：US20200216185A1

公开(公告)日：2020-07-09

申请号：US16733783

申请日：2020-01-03

Applicant: Airbus Operations SAS

Inventor： Jacky PUECH ,  Thomas DEFORET ,  Julien CAYSSIALS

IPC: B64D27/26 ,  B64F5/10

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.

公开(公告)号：US20200031482A1

公开(公告)日：2020-01-30

申请号：US16431280

申请日：2019-06-04

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Jacky PUECH

IPC: B64D27/26

Abstract: An assembly for an aircraft comprising a pylon having a mounting plate having a front face and a rear face and through which there passes, between the front face and the rear face, at least one central bore, a front engine mount comprising a spar with a rear face bearing against the mounting plate front face and which, for each central bore, has a complementary central bore aligned with the central bore, and for each central bore, a mounting system. The mounting system comprises a shear pin inserted into the central bore and the complementary central bore from the rear face with a flange bearing against the rear face, a support with a central hole, the diameter of which is greater than the flange diameter and fixed to the rear face, and a cap fixed to the support closing off the central hole and bearing against the shear pin.

公开(公告)号：US20220055758A1

公开(公告)日：2022-02-24

申请号：US17407251

申请日：2021-08-20

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Thomas DEFORET ,  Jacky PUECH

IPC: B64D27/26

Abstract: A propulsion assembly including a primary structure of a pylon having right and left extensions projecting with respect to right and left lateral panels of the primary structure and also right and left brackets, each having a first flank connected to the right or left lateral panel of the primary structure and a second flank pressed against the right or left extension, a front engine mount having first and second links, each connected to an engine and directly to the front transverse reinforcement by a first or second reinforcement connection pin passing through the right or left extension and the second flank of the right or left bracket.

公开(公告)号：US20200216184A1

公开(公告)日：2020-07-09

申请号：US16733691

申请日：2020-01-03

Applicant: Airbus Operations SAS

Inventor： Jacky PUECH ,  Thomas DEFORET ,  Julien CAYSSIALS

IPC: B64D27/26 ,  B64F5/10

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove in such a manner as to immobilize the shear pin in translation.

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：US20200369394A1

公开(公告)日：2020-11-26

申请号：US16878034

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Rémi LANSIAUX ,  Olivier DUBOIS ,  Anthony MERTES ,  Jacky PUECH

IPC: B64D27/26

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having 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, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.