公开(公告)号：US20250074610A1

公开(公告)日：2025-03-06

申请号：US18819052

申请日：2024-08-29

Applicant: Airbus Operations SAS

Inventor： Germain GUENEAU ,  Pierre-Antoine COMBES ,  Marc DE NICOLA

IPC: B64D27/40 ,  B64D27/18

Abstract: An assembly comprising a wing and a reactor mast fixed to the wing. The primary structure of the reactor mast comprises a first fixing lug and starboard and port fixing lugs, the wing carries a first fitting and starboard and port fittings, the fixing lugs being joined to the fittings with shackles having three fixing points, and the first lug being fixed to the first fitting.

公开(公告)号：US20250074611A1

公开(公告)日：2025-03-06

申请号：US18819000

申请日：2024-08-29

Applicant: Airbus Operations SAS

Inventor： Pierre-Antoine COMBES ,  Marc DE NICOLA

IPC: B64D27/40

Abstract: An assembly comprising a longitudinal member of an aircraft wing, where the longitudinal member has a contact wall which is penetrated by first bores, each passing through the contact wall parallel to a longitudinal direction, an engine pylon which is arranged at the end of the longitudinal member in the longitudinal direction and having an upper longitudinal member which, for each first bore, is penetrated by a second bore which is aligned with the first bore, and a nut and a screw for each pair of a first bore and a second bore, which are aligned, where the screw is screwed into the nut successively via the first bore and the second bore, sandwiching the upper longitudinal member and the contact wall.

公开(公告)号：US20240336365A1

公开(公告)日：2024-10-10

申请号：US18626575

申请日：2024-04-04

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Jean-Baptiste VIGNES

IPC: B64D27/40

CPC classification number: B64D27/402

Abstract: An engine pylon has a structure for fastening an aircraft engine beneath a wing and has two lateral faces. The structure has a tunnel laterally passing through it, between and through the lateral faces, and the engine pylon has a spreader housed in the tunnel and fastened in an articulated manner to each lateral face. A first end of the spreader has a first bore. A second end of the spreader has two second bores each forming a connection point with the engine. A rod is fastened in an articulated manner to the first bore and has two third bores each forming a connection point with the engine. Such an engine pylon has the ability to attach the engine, with reduced vertical bulk and with less drag.

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：US20250010998A1

公开(公告)日：2025-01-09

申请号：US18761974

申请日：2024-07-02

Applicant: Airbus Operations SAS

Inventor： Pierre-Antoine COMBES ,  Marc DE NICOLA ,  Germain GUENEAU ,  Olivier PAUTIS

IPC: B64D27/40 ,  B64D27/18

Abstract: An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.

公开(公告)号：US20240391581A1

公开(公告)日：2024-11-28

申请号：US18670164

申请日：2024-05-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Pierre-Antoine COMBES ,  Marc DE NICOLA

IPC: B64C3/32 ,  B64D27/40

Abstract: An assembly comprising a wing with a lower surface panel and an upper surface panel and an engine pylon comprising a primary structure fixed to the wing with a fixing base. The fixing base comprises fourth fixing yokes while the primary structure bears fourth fittings, the fourth fixing yokes being secured to the fourth fittings with fourth rods.