公开(公告)号：US20250051020A1

公开(公告)日：2025-02-13

申请号：US18796631

申请日：2024-08-07

Applicant: Airbus Operations SAS

Inventor： Frédéric JOURNADE ,  Olivier PAUTIS ,  Jérôme COLMAGRO ,  Germain GUENEAU ,  Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Fabrice GRIMAL

IPC: B64D27/40

Abstract: A propulsion system comprising a turbojet with a fan casing and a central casing, a pylon with an upper spar, a front wall and on either side of a vertical median plane, a fitting rigidly fixed to the rigid structure, a cylindrical pin as one with the fan casing and inserted in a hole of the upper spar, a shackle with at the vertical median plane, an upper articulation between the shackle and the front wall and on either side of the vertical median plane, a lower articulation between the shackle and the central casing, and two reaction rods disposed on either side of the median plane, where each rod is articulated, at a front end, on the central casing, and, at rear end, on the fitting.

公开(公告)号：US20190202573A1

公开(公告)日：2019-07-04

申请号：US16230200

申请日：2018-12-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Jérôme COLMAGRO

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D27/18

Abstract: An aircraft comprising a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. The arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure of the attachment pylon, at least one securing member linking the first and second connecting portions, this securing member being articulated to the first connecting portion with the aid of a first pin system oriented substantially parallel to the front wing spar.

公开(公告)号：US20210269167A1

公开(公告)日：2021-09-02

申请号：US17114703

申请日：2020-12-08

Applicant: Airbus Operations SAS

Inventor： Jérôme COLMAGRO ,  Paolo MESSINA

IPC: B64D27/26 ,  B64F5/10 ,  F16C11/04

Abstract: An assembly including a link axis supported by first and second guiding rings positioned in first and second branches of a clevis, one of the guiding rings including a tubular extension, protruding with respect to an outer face of one of the branches, which has a threaded portion on its outer circumferential face. Complementing this, the assembly includes a nut configured to be screwed onto the threaded portion of the tubular extension and an immobilization system configured to immobilize the nut in translation and/or in rotation, the nut and the link axis being linked by a complete link that is non-removable or that forms a single-piece part. This solution makes it possible to reduce the number of parts forming the assembly. Also provided are an engine attachment and an aircraft including such an assembly.

公开(公告)号：US20190300186A1

公开(公告)日：2019-10-03

申请号：US16368305

申请日：2019-03-28

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Jérôme COLMAGRO

IPC: B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  F01D15/10 ,  F02C6/00

Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.

公开(公告)号：US20190160606A1

公开(公告)日：2019-05-30

申请号：US16199795

申请日：2018-11-26

Applicant: Airbus Operations SAS

Inventor： Jérôme COLMAGRO ,  Aurélien MAUCONDUIT ,  Julien MOULIS

IPC: B23P19/02 ,  F16C11/04

Abstract: A device for manipulating a hollow shaft configured to create a pivot link between a first element and a second element. The manipulation device comprises a cylindrical body having a diameter variable by radial contraction or radial expansion of the cylindrical body, a module for controlling the diameter of the cylindrical body configured so that the diameter of the cylindrical body has alternatively at least a first diameter suitable for the cylindrical body to be displaced in the hollow shaft and a second diameter suitable for the cylindrical body to be blocked in the hollow shaft. The cylindrical body comprises an end configured to protrude from the hollow shaft when the cylindrical body is blocked in the hollow shaft. The manipulation device allows the alignment of the orifices due to the end configuration of the cylindrical body.

公开(公告)号：US20220127010A1

公开(公告)日：2022-04-28

申请号：US17509113

申请日：2021-10-25

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Jérôme COLMAGRO

IPC: B64D27/26

Abstract: An engine mounting pylon for suspending a turbofan beneath an aircraft wing, including a primary structure, a fastening device for fastening to the turbofan, and a fastening device for fastening to the wing. The engine mounting pylon furthermore comprises multiple rigid braces that mechanically connect the primary structure to the wing of the aircraft, a first brace-attachment device that mechanically connects a first end of each brace to the wing, and a second brace-attachment device that mechanically connects a second end of each brace to the primary structure. This braced-pylon architecture makes it possible to reduce the dimensions of the primary structure and the various elements that constitute the first and second attachment devices.

公开(公告)号：US20240327008A1

公开(公告)日：2024-10-03

申请号：US18618130

申请日：2024-03-27

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Laurent AGOSTINI ,  Jérôme COLMAGRO

IPC: B64D27/40 ,  B64D27/18

CPC classification number: B64D27/402 ,  B64D27/18

Abstract: The invention relates to a propulsion assembly having a jet engine with an intermediate casing with a rear face and a core casing to the rear of the intermediate casing, and an attachment pylon with a frontal wall and two lateral walls, a front engine attachment having a front fitting fastened in an articulated manner via two lateral fastening points to the rear face and in a rigid manner via an upper fastening zone to the frontal wall, and an intermediate engine attachment comprising a front link rod and a rear link rod on each side. Each of the link rods is mounted in an articulated manner between the front fitting and the lateral wall. With such an arrangement, the bulk of the engine attachments is reduced in the bypass flow.

公开(公告)号：US20220379579A1

公开(公告)日：2022-12-01

申请号：US17824102

申请日：2022-05-25

Applicant: Airbus Operations SAS

Inventor： Jérôme COLMAGRO ,  Charles CARIOU ,  Florian RAVISE ,  Maxime GAUTHIER

IPC: B32B3/12 ,  B32B3/20 ,  B29C53/40

Abstract: A method for manufacturing a cellular structure having first and second faces, rows of cells each alternatingly having first cells, which are open in the direction of the first face, second cells, which are open in the direction of the second face, and also third cells formed between each row of cells, each row of cells comprising first and second strips of material placed against one another. The first and second strips of material are shaped by bending. By contrast to plastic deformation, shaping by bending makes it possible to expand the choice of materials and thicknesses for the first and second strips of material. An advantageous cellular structure is thus obtained as well as an acoustic absorption coating comprising such a cellular structure.

公开(公告)号：US20190233129A1

公开(公告)日：2019-08-01

申请号：US16264909

申请日：2019-02-01

Applicant: Airbus Operations SAS

Inventor： Laurent LAFONT ,  Stéphane DIDA ,  Jérôme COLMAGRO

IPC: B64D27/26 ,  B64C3/18

CPC classification number: B64D27/26 ,  B64C3/185 ,  B64C3/187 ,  B64D27/18 ,  B64D2027/264

Abstract: An assembly for an aircraft and comprising a wing comprising an airfoil box partly produced using a front spar, a mounting pylon arranged under the wing and comprising a primary structure formed as a primary box having a top spar extending at least partly under the airfoil box and having a slit, a bottom spar, lateral panels and a transverse reinforcing fixing rib, of which a bottom part is housed and fixed inside the primary structure and of which a top part passes through the slit. A fixing arrangement fixes the top part to the front spar. The fixing arrangement comprises a plurality of fixing bolts, where each fixing bolt fixes the top part to the front spar and has its axis at right angles to the fixing rib. Such an assembly allows the mounting pylon primary structure to be as close as possible to the wing.

公开(公告)号：US20190202572A1

公开(公告)日：2019-07-04

申请号：US16228966

申请日：2018-12-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Jérôme COLMAGRO

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D27/18

Abstract: An aircraft comprises a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. This arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure, at least one securing member articulated to each of the first and second connecting portions. Furthermore, the first connecting portions of the two fittings are made in one piece in a single wing connector extending over essentially the entire height of the front wing spar.