公开(公告)号：US10124876B2

公开(公告)日：2018-11-13

申请号：US14952376

申请日：2015-11-25

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

Inventor： Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Angel Pascual Fuertes ,  Sandra Linares Mendoza ,  Julien Guillemaut ,  Eric Bouchet ,  Jerome Colmagro ,  Jonathan Blanc

IPC: B64C1/06 ,  B64C1/12 ,  B64C1/16 ,  B64C1/26 ,  B64C3/32

Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.

公开(公告)号：US09656736B2

公开(公告)日：2017-05-23

申请号：US14695731

申请日：2015-04-24

Applicant: Airbus Operations (S.A.S.) ,  Airbus Operations, S.L.

Inventor： Julien Guillemaut ,  Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Jerome Colmagro ,  Jonathan Blanc

IPC: B64C1/06 ,  B64C1/26

CPC classification number: B64C1/061 ,  B64C1/26 ,  B64D27/14

Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.

公开(公告)号：US12129041B2

公开(公告)日：2024-10-29

申请号：US17988862

申请日：2022-11-17

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Jonathan Blanc

IPC: B64D27/40 ,  F01D25/28 ,  F02C7/20 ,  B64D27/16

CPC classification number: B64D27/40 ,  F01D25/28 ,  F02C7/20 ,  B64D27/16 ,  B64D27/402

Abstract: An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.

公开(公告)号：US11465765B2

公开(公告)日：2022-10-11

申请号：US16933244

申请日：2020-07-20

Applicant: Airbus Operations SAS

Inventor： Jonathan Blanc ,  Olivier Pautis

IPC: B64D27/26 ,  B64D27/18

Abstract: An engine pylon for mounting a jet engine beneath a wing of an aircraft, the engine pylon having a primary structure having two internal lateral fittings that face one another and a rib that is fastened between the two internal lateral fittings and a primary box that at least partially surrounds the primary structure and comprises a first part made from a composite material.

公开(公告)号：US10189575B2

公开(公告)日：2019-01-29

申请号：US15357106

申请日：2016-11-21

Applicant: Airbus Operations SAS

Inventor： David Ewens ,  Jonathan Blanc ,  Yves Belloc

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

Abstract: An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.

公开(公告)号：US11952135B2

公开(公告)日：2024-04-09

申请号：US17851407

申请日：2022-06-28

Applicant: Airbus Operations SAS

Inventor： Cédric Poupon ,  Olivier Pautis ,  Jonathan Blanc

IPC: B64D27/26 ,  F16C11/06

CPC classification number: B64D27/26 ,  F16C11/0628 ,  B64D2027/262

Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

公开(公告)号：US11780599B2

公开(公告)日：2023-10-10

申请号：US17694747

申请日：2022-03-15

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Jonathan Blanc

IPC: B64D29/02 ,  B64D27/26 ,  B64D29/08

CPC classification number: B64D29/02 ,  B64D27/26 ,  B64D29/08 ,  B64D2027/264

Abstract: An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.

公开(公告)号：US20170152052A1

公开(公告)日：2017-06-01

申请号：US15357106

申请日：2016-11-21

Applicant: Airbus Operations SAS

Inventor： David Ewens ,  Jonathan Blanc ,  Yves Belloc

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

CPC classification number: B64D27/26 ,  B64C3/32 ,  B64D27/18 ,  B64D2027/264 ,  B64D2027/266 ,  B64D2027/268

Abstract: An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.