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.

公开(公告)号：US20240150028A1

公开(公告)日：2024-05-09

申请号：US18502248

申请日：2023-11-06

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT ,  Pierre-Antoine COMBES ,  Paul-Adrien TAVEAU

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/264

Abstract: An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

公开(公告)号：US20230030853A1

公开(公告)日：2023-02-02

申请号：US17868161

申请日：2022-07-19

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA ,  Olivier PAUTIS

IPC: B64D27/18

Abstract: A propulsion assembly having a jet engine with a central casing, an attachment pylon having a rigid structure, a front engine attachment and a device for reacting the thrust forces. The front engine attachment has, on either side of a median plane, a front rod articulated via a connection point respectively to the rigid structure and to the central casing, and the reaction device has two central rods, two first fittings as one with the rigid structure and two second fittings as one with the central casing, wherein the two first fittings are independent of one another and wherein each central rod is articulated between a first fitting and a second fitting.

公开(公告)号：US20220297845A1

公开(公告)日：2022-09-22

申请号：US17694747

申请日：2022-03-15

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Jonathan BLANC

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

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：US20210354839A1

公开(公告)日：2021-11-18

申请号：US17318454

申请日：2021-05-12

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT ,  Olivier DUBOIS ,  Germain GUENEAU

IPC: B64D27/26

Abstract: An assembly including a connecting device, connecting first and second parts, including first and second links positioned on respective opposite sides of the first and second parts and an interleaved stiffener, positioned between the first and second links, having a first contact face oriented toward the first link and a second contact face oriented toward the second link, parallel to the first face, the first and second contact faces being separated by a distance equal to that separating the first and second links. This interleaved stiffener makes it possible to limit the risks of bending of the links when they are loaded in compression.

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：US20190152616A1

公开(公告)日：2019-05-23

申请号：US16197726

申请日：2018-11-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Eric BOUCHET ,  Olivier BARBARA

IPC: B64D27/26

Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

公开(公告)号：US20180066606A1

公开(公告)日：2018-03-08

申请号：US15693735

申请日：2017-09-01

Applicant: Airbus Operations (SAS)

Inventor： Olivier PAUTIS ,  Jerome COLMAGRO

IPC: F02K1/72 ,  F02K1/76

CPC classification number: F02K1/72 ,  F02K1/763 ,  F05D2260/50

Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.