公开(公告)号：US20240200707A1

公开(公告)日：2024-06-20

申请号：US18538069

申请日：2023-12-13

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

Inventor： Gérard Millet ,  Vincent Delpy ,  Simon Foucart-Gaudy ,  Marc-Antoine Brocard

IPC: F16L41/08

CPC classification number: F16L41/08

Abstract: A sleeve fastening system fastened to a joist pierced with a hole and receiving two pipes and including a cylinder fitted into the hole of which each end receives a pipe, wherein the wall of the cylinder has cut into it at least one tunnel, a flange, each tunnel having openings that emerge on either side of the flange that has a bearing face bearing against the joist and a free face, and for each tunnel, a holding system having a link, a shoe and a locking system, the link being housed in the tunnel with the shoe blocked in a first opening on the side of the free face and wherein the link exits via a second opening on the side of the bearing face and wherein the locking system attaches.

公开(公告)号：US11984970B2

公开(公告)日：2024-05-14

申请号：US17176757

申请日：2021-02-16

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

Inventor： Laurent Azoulai ,  Philippe Delga ,  François Tranchet ,  Rémy Lazzerini ,  Jean Pasquie ,  Ludovic Parisot ,  Philippe Merceron

IPC: H04K3/00 ,  G01S19/21 ,  H04B7/185

CPC classification number: H04K3/22 ,  G01S19/21 ,  H04B7/18506 ,  H04B7/18521

Abstract: A system includes at least one reception unit installed in an aircraft and configured for tracking satellites of the satellite navigation system of the GNSS type. The system includes a generation unit for generating an expected number corresponding to the number of satellites that the reception unit is expected to track, a detection unit including a comparison part for comparing the expected number with a tracked number corresponding to the number of satellites that the reception unit is actually tracking and a decision part for detecting a jamming, as a function of the result of the comparison made by the comparison part and transmitting detection data in the event of detection, and a transmission unit configured to transmit jamming detection data to at least one user device, the system making it possible to detect a jamming of a GNSS system in an automatic and reliable manner.

公开(公告)号：US20240025562A1

公开(公告)日：2024-01-25

申请号：US18357808

申请日：2023-07-24

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Jean-Marc DATAS ,  Thomas CARTEREAU ,  Jacques BOURIQUET ,  André AQUILA ,  Nicolas DARBONVILLE ,  Thomas AUTRET ,  Joël BARBOULE ,  Sébastien BAYONNE ,  Patrick GUERIN ,  Sjoerd VAN DER VEEN

IPC: B64F5/10

CPC classification number: B64F5/10 ,  B64C1/068

Abstract: An assembly platform configured to manipulate at least one aircraft lower shell without deforming it with a view to assembly of an aircraft fuselage barrel is disclosed including at least one rectangular chassis, at least two frames having an adjustable trim with respect to the rectangular chassis, at least two setting systems intended to adjust the trim of the frame and at least two cradles fixed onto the frames and intended to receive the lower shell and to hold the lower shell in a desired form. The cradles of the assembly platform make it possible to prevent a deformation of the lower shell during the assembly of the fuselage barrel.

公开(公告)号：US20240025559A1

公开(公告)日：2024-01-25

申请号：US18357741

申请日：2023-07-24

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Jean-Marc DATAS ,  Thomas CARTEREAU ,  Jacques BOURIQUET ,  André AQUILA ,  Nicolas DARBONVILLE ,  Thomas AUTRET ,  Joël BARBOULE ,  Sébastien BAYONNE ,  Patrick GUERIN ,  Sjoerd VAN DER VEEN

IPC: B64F5/10

CPC classification number: B64F5/10

Abstract: An aircraft floor grid transport system for assembling an aircraft fuselage barrel and method of calibrating the transport system are disclosed. The transport system includes a rectangular beam, a stabilizer device to be associated with referential positioning devices of an assembly platform and a plurality of fixing devices to be fixed to the floor grid, each of the fixing devices having a vertically adjustable length. The transport system makes it possible to handle the floor grid without deforming it in order to assemble a fuselage barrel.

公开(公告)号：US11848486B2

公开(公告)日：2023-12-19

申请号：US17749479

申请日：2022-05-20

Applicant: Airbus Operations GmbH ,  Airbus Operations S.A.S.

Inventor： Thomas Düde ,  Christian Schaupmann ,  Rubén Bancalero Santolaya

IPC: H01Q1/28 ,  H01Q1/40

CPC classification number: H01Q1/286 ,  H01Q1/405

Abstract: An antenna arrangement for an aircraft includes an antenna unit, a radome structure covering the antenna unit, and a mounting device for mounting the antenna arrangement to an outer surface of an aircraft component. The antenna unit is mounted to or integrally formed with the radome structure and the radome structure is mounted to or integrally formed with the mounting device.

公开(公告)号：US20230399116A1

公开(公告)日：2023-12-14

申请号：US18328679

申请日：2023-06-02

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Jean-François ALLIAS

IPC: B64D27/24 ,  B60L50/70 ,  B64D33/08 ,  B60L58/33 ,  B64D35/02 ,  B64D35/08 ,  H01M8/04111 ,  H01M8/04014 ,  H02P25/22 ,  H02P29/028

CPC classification number: B64D27/24 ,  B60L50/70 ,  B64D33/08 ,  B60L58/33 ,  B64D35/02 ,  B64D35/08 ,  H01M8/04111 ,  H01M8/04014 ,  H02P25/22 ,  H02P29/028 ,  B60L2200/10 ,  H01M2250/20

Abstract: The electrical supply system (10) of an electrical propulsion system (4) of an aircraft (1) includes: two first sets of fuel cells (FC11, FC12), configured to supply electrically an electric motor driving a propulsion propeller; a first compressor (C1) configured to supply compressed air to at least part of the at least two first sets of fuel cells (FC11, FC12); and a first electric motor (M1) designed to drive the first compressor. The first electric motor (M1) includes electrical windings (W1a, W1b), each electrical winding supplied electrically by a set of distinct fuel cells from amongst the at least two first sets of fuel cells (FC11, FC12).

公开(公告)号：US11820089B2

公开(公告)日：2023-11-21

申请号：US17092696

申请日：2020-11-09

Applicant: AIRBUS SAS ,  Airbus Operations S.A.S.

Inventor： Julien Charles ,  Franck Dobigeon ,  Guillaume Ferrer ,  Anthony Rince

IPC: B29C35/00 ,  B29C73/00 ,  B29C73/10 ,  B29C35/08 ,  B29L31/30

CPC classification number: B29C73/10 ,  B29C35/08 ,  B29C2795/002 ,  B29K2995/002 ,  B29L2031/3076

Abstract: An assembly includes a bag and of a composite panel exhibiting a damaged region to be repaired by polymerization of a repair piece using the bag. The bag includes a sheet intended to be laid over the panel. When the panel and the sheet are laid one atop of the other, the sheet exhibits regions capable of absorbing heat emitted by radiation onto it in a proportion that is dependent on the polymerization temperature needed for that region of the panel that corresponds to it, the radiation being partially absorbed by suitable colouration of the sheet in the region concerned. Determining those regions of the panel in which radiation is less well absorbed than in others means that the heating can be adapted to suit the needs of polymerization in terms of repair and that even polymerization can thus be obtained over the entire damaged region, thereby consolidating the repair.

公开(公告)号：US11745887B2

公开(公告)日：2023-09-05

申请号：US17091604

申请日：2020-11-06

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

Inventor： Alain Porte ,  Jacques Lalane ,  Arnaud Bourhis ,  Florent Mercat

IPC: B64D33/02 ,  G10K11/172 ,  G10K11/168

CPC classification number: B64D33/02 ,  G10K11/168 ,  G10K11/172 ,  B64D2033/0206

Abstract: An acoustic panel for an aircraft nacelle includes, from a central axis of the nacelle to the exterior thereof, a resistive skin perforated with sound-absorbing micro-perforations, a first attenuation stage, a septum perforated with holes, a second attenuation stage, and a back skin configured to provide the mechanical strength of the acoustic panel. The septum is a planar wall having a thickness greater than that of the resistive skin, preferably greater than 4 mm. Such a panel is configured to attenuate several frequency ranges one of which being a low-frequency range, while optimizing the weight, the cost and the air intake functions. The thickness of the septum, the dimensions of the holes in the septum, the OAR of the septum and the height of the second attenuation stage are adjusted to match the mean attenuated low frequency to the vibration frequency of the aircraft engine.

公开(公告)号：US11735860B2

公开(公告)日：2023-08-22

申请号：US17121164

申请日：2020-12-14

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

Inventor： Olivier Raspati ,  Thomas Jomier ,  David Rousset

IPC: H01R13/53 ,  H01H1/66 ,  B64D37/06 ,  B64D37/30

CPC classification number: H01R13/53 ,  B64D37/06 ,  B64D37/30 ,  H01H1/66 ,  H01R2201/26

Abstract: Use of a hydrogen tank of a vehicle such as an aircraft for protecting at least one electrical connection device linked to at least one electrical device. At least one connection device is placed in a tank or in a sealed enclosure supplied with hydrogen by a tank or by any other source of hydrogen supply of the vehicle. The use of a tank that already exists in the vehicle makes it possible to avoid having to use specific chambers incorporated in a complex manner with the connection device.

公开(公告)号：US11731756B2

公开(公告)日：2023-08-22

申请号：US17731735

申请日：2022-04-28

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

Inventor： Alena Kaufmann ,  Jérôme Robillard

IPC: B64C13/36 ,  B64C9/08

CPC classification number: B64C13/36 ,  B64C9/08

Abstract: A control system for an aircraft includes a hydraulic pump, first hydraulic line, second hydraulic line, a first actuator coupled with a first control surface, a second actuator coupled with a second control surface, and a third actuator coupled with a third control surface. The first control surface and the second control surface are at a distance to each other and symmetrically relative to a symmetry axis. The third control surface is substantially on the symmetry axis, and the first hydraulic line and the second hydraulic line are connected to the hydraulic pump. The first actuator is connected to the first hydraulic line, and the second actuator is connected to the second hydraulic line. The third actuator is connected to the first hydraulic line downstream of the first actuator at a junction point, and the first hydraulic line at least partially includes a larger diameter than the second hydraulic line.