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公开(公告)号：US20200256282A1
公开(公告)日：2020-08-13
申请号：US16736474
申请日：2020-01-07
Applicant: Airbus Operations SAS
Inventor： Fabien MENOU , Laurent CAZEAUX , Benoit ORTEU
Abstract: A turbojet comprising a nacelle with a fixed cowl, a fan duct and a thrust reverser comprising a cowl movable between a stowed and a deployed position where the movable cowl is remote from the fixed cowl, at least one blocking flap movable between the closed position and a fixed position where the flap at least partially blocks the fan duct, and also a drive mechanism for moving the movable cowl and the blocking flap. The drive mechanism comprises a roller slide comprising a rail and a roller rotatable in the rail, a connecting rod with a first end movable on the roller and a second end movable on the blocking flap. The rail comprises a bearing surface extending parallel to a turbojet longitudinal axis to support the connecting rod during movement of the movable cowl from the stowed position to an intermediate position between the stowed and deployed positions.
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公开(公告)号：US20230192268A1
公开(公告)日：2023-06-22
申请号：US18081153
申请日：2022-12-14
Applicant: Airbus Operations SAS
Inventor： Jérôme DURAND , Benoit ORTEU
Abstract: An aircraft part has a fuselage portion and a floor, at least a part of which is joined to the fuselage portion via elastic link rods. Each elastic link rod is provided with a first end that is configured to be fixed to the floor and with a second end that is configured to be fixed to the fuselage portion. The elastic link rods are configured to exhibit a stiffness that makes it possible both to transmit loads between the floor and the fuselage portion and to absorb displacements brought about by deformations of the fuselage portion. The aircraft part thus making it possible, at a lower cost and with a lower mass, to obtain a connection between the floor and the fuselage portion that exhibits suitable elasticity to be able to transmit inertial loads while absorbing deformations of the fuselage portion.
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公开(公告)号：US20220315200A1
公开(公告)日：2022-10-06
申请号：US17712413
申请日：2022-04-04
Applicant: Airbus Operations SAS
Inventor： Benoit ORTEU , Damien SIRE
Abstract: A landing gear bay including a bottom wall which includes longitudinal beams and at least one panel forming an airtight barrier between first and second zones disposed on either side of the panel. The panel has first and second longitudinal edges each linked to one of the longitudinal beams. The second zone is configured to sustain a pressure greater than that of the first zone. The panel has a profile that is substantially constant in the longitudinal direction and includes at least one central part offset toward the second zone with respect to its first and second longitudinal edges. This solution makes it possible to limit the vertical stresses applied to the longitudinal beams by virtue of the pressure difference between the first and second zones.
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公开(公告)号：US20220289365A1
公开(公告)日：2022-09-15
申请号：US17572254
申请日：2022-01-10
Applicant: Airbus Operations SAS
Inventor： Benoit ORTEU , Damien SIRE
Abstract: An aircraft including two main landing gears and also a main landing gear bay configured to house, on either side of a vertical median plane, the two main landing gears in a retracted position, the main landing gear bay including a rear transverse wall, a front transverse wall and also an end wall that is approximately perpendicular to the rear and front transverse walls. The main landing gear bay includes at least one strut connecting the rear or front transverse wall and the end wall, approximately positioned in the vertical median plane.
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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
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.
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Patent Agency Ranking
6.发明申请公开(公告)号：US20200318574A1
公开(公告)日：2020-10-08
申请号：US16832344
申请日：2020-03-27
Applicant: Airbus Operations SAS
Inventor： Pascal GARDES , Frédéric RIDRAY , Benoit ORTEU
IPC: F02K1/72
Abstract: A turbofan with a secondary duct and including a fixed structure and a mobile assembly including a frame with openwork regions. The mobile assembly is translatable between advanced and retracted positions. The openwork regions are positioned across the window in the retracted position. A plurality of blocking doors is provided, each being mobile between stowed and deployed positions. An array of rams move the mobile assembly. A cascade grille mounts on the frame across the openwork region. The grille slides on the frame parallel to the translational direction. For each grille, a rear stop limits rearward movement, and a compression spring pushes the grille to the rear for abutment against a rear stop. For each grille, the fixed structure comprises a stop element against which the grille abuts upon movement from the advanced position to the retracted position.
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公开(公告)号：US20200240359A1
公开(公告)日：2020-07-30
申请号：US16745606
申请日：2020-01-17
Applicant: Airbus Operations SAS
Inventor： Pascal GARDES , Guillaume SEGUIN , Laurent TIZAC , Fabien MENOU , Frédéric RIDRAY , Benoit ORTEU , Romain CUSSET
Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.
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公开(公告)号：US20190135445A1
公开(公告)日：2019-05-09
申请号：US16180129
申请日：2018-11-05
Applicant: Airbus Operations SAS
Inventor： Stéphane COMBES , Jean GELIOT , Thomas DEFORET , Adeline SOULIE , Benoit ORTEU
IPC: B64D27/26
Abstract: An engine attachment system comprising an engine pylon with a top wall, a bottom wall and two lateral walls, and a front engine attachment with a beam which bears two connecting rods for fixing the engine. The engine attachment system also comprises an intermediate piece with a bottom wall and four lateral walls, wherein the beam is fixed against an outer face of the bottom wall, wherein the intermediate piece is fitted at a front-end face of the engine pylon in such a way that an inner face of the bottom wall comes against the front-end face of the engine pylon, and in such a way that the lateral walls of the intermediate piece are superposed with the walls of the engine pylon. In such an engine attachment system, the front engine attachment is thus located on the front-end face of the engine pylon, allowing a space saving.
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公开(公告)号：US20190106221A1
公开(公告)日：2019-04-11
申请号：US16138242
申请日：2018-09-21
Applicant: Airbus Operations SAS
Inventor： Stéphane COMBES , Jean GELIOT , Thomas DEFORET , Adeline SOULIE , Benoit ORTEU
Abstract: A dual-flow jet engine comprising a fixed structure, a central core, and a cowl comprising a fixed part and a mobile cowl mounted to be rotationally mobile on the fixed structure via hinges with swan neck fitting. The fixed part has a first edge and the mobile cowl has a second edge, in which, when the mobile cowl is in a closed position, the second edge extends against the first edge. For each hinge with swan neck fitting, the fixed part is hollowed at the first edge, so as to delimit a recess opposite the swan neck fitting and allow the passage of the swan neck fitting when the mobile cowl switches from the closed position to the open position. The recess for each hinge with swan neck fitting allows for a reduction of the dimensions of the swan neck during the movement of the mobile cowl.
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10.发明公开公开(公告)号：US20230150646A1
公开(公告)日：2023-05-18
申请号：US17985199
申请日：2022-11-11
Applicant: Airbus Operations SAS
Inventor： Benoit ORTEU , Ludovic MIL , Lionel LAGANIER , Dominique MARTY , Philippe ROBERT
Abstract: An aircraft floor including at least one hinge connecting movable and fixed floor parts, which has a pivot axis parallel to a longitudinal direction. The floor also includes at least two beams, each including first and second beam portions secured respectively to the fixed and movable floor parts and connected together by a pivot link, and at least one rail including at least one first rail portion secured to the movable floor part and at least one second rail portion secured to the fixed floor part of the floor, extending the first rail portion.
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