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：US20220371743A1

公开(公告)日：2022-11-24

申请号：US17747200

申请日：2022-05-18

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations S.L.

Inventor： Julien ALLAIN ,  Thomas DEFORET ,  Julien LAVERNE ,  Emmanuel VARDELLE ,  Kotaro FUKASAKU ,  Carlos FLORES HERNANDEZ

IPC: B64D37/04 ,  B64D37/30

Abstract: A tank system for an aircraft, including a tank including an inner enclosure including a closed inner skin configured to store dihydrogen and an outer enclosure including an outer skin that surrounds the inner enclosure, a chassis including a front frame at a front end of the tank, and an attachment arrangement which attaches the outer skin of the outer enclosure to the front frame. A system of this kind makes it possible to react forces through the outer skin, thus reducing a complexity of the chassis.

公开(公告)号：US20200017227A1

公开(公告)日：2020-01-16

申请号：US16437260

申请日：2019-06-11

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Benoit ORTEU ,  Olivier GLEIZE

IPC: B64D27/26 ,  B64D27/18

Abstract: A mounting pylon comprising a structure that comprises two C-shaped semi-structures and comprising an upper spar, a lower spar and a lateral flank, an upper panel, a lower panel, a reacting attachment point, two bars attached between the reacting attachment point and a jet engine, and a front wing attachment point attached to a wing box. The lateral flank comprises joists that are aligned between the front wing attachment point and the reacting attachment point, and where the angles between two successive joists are equal.

公开(公告)号：US20190315477A1

公开(公告)日：2019-10-17

申请号：US16363513

申请日：2019-03-25

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE ,  Olivier DUBOIS

IPC: B64D27/26

Abstract: An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.

公开(公告)号：US20240417089A1

公开(公告)日：2024-12-19

申请号：US18740984

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

公开(公告)号：US20240417086A1

公开(公告)日：2024-12-19

申请号：US18740953

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.

公开(公告)号：US20240417085A1

公开(公告)日：2024-12-19

申请号：US18740948

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.

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.