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1. 发明授权

US12065244B2 Wing of an aircraft and a hold-down arrangement for a wing of an aircraft 有权
公开(公告)号：US12065244B2
公开(公告)日：2024-08-20
申请号：US17779933
申请日：2020-11-03
申请人： AIRBUS OPERATIONS GMBH
发明人： Stefan Bensmann
IPC分类号： B64C9/02 , B64C3/28 , B64C9/22
CPC分类号： B64C9/02 , B64C3/28 , B64C9/22
摘要： A wing (5) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold.

2. 发明公开

US20240270370A1 PRESSURE SEAL COUPLING DEVICE, PRESSURE SEAL, DOOR OF AN AIRCRAFT, AND METHOD FOR INSTALLING A PRESSURE SEAL 审中-公开
公开(公告)号：US20240270370A1
公开(公告)日：2024-08-15
申请号：US18440317
申请日：2024-02-13
申请人： Airbus Operations GmbH
发明人： Enno Houtrouw
IPC分类号： B64C1/14
CPC分类号： B64C1/1461
摘要： A pressure seal coupling device for coupling first and second seal body end regions of an elongate and at least partially resiliently deformable pressure seal to seal an opening providing access to a pressurizable interior space of an aircraft or spacecraft, when the opening is closed by a closure component. The coupling device includes a first coupling device portion at the first seal body end region and a second coupling device portion at the second seal body end region. The first and second coupling device portions are configured to engage with each other for coupling the first and second seal body end regions. A pressure seal includes such a coupling device, to a door of an aircraft including such a seal arranged on the door, and a method is disclosed for installing a pressure seal.

3. 发明授权

US12054291B2 Deformable shim and mounting arrangement 有权
公开(公告)号：US12054291B2
公开(公告)日：2024-08-06
申请号：US17454115
申请日：2021-11-09
申请人： Airbus Operations GmbH
发明人： Mika Bots , Matthias Hegenbart , Hermann Benthien
IPC分类号： B64F5/10 , B23P19/02 , B23P19/04 , B29C65/56 , B29C65/78 , B64C1/06 , B64C1/14
CPC分类号： B64F5/10 , B23P19/02 , B23P19/04 , B29C65/565 , B29C65/7823 , B64C1/069 , B23P2700/01 , B64C1/14
摘要： A method of providing a deformable shim that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.

4. 发明授权

US12054258B2 Wing for an aircraft and connecting assembly to movably connect a slat to a main wing 有权
公开(公告)号：US12054258B2
公开(公告)日：2024-08-06
申请号：US17615071
申请日：2020-07-10
申请人： Airbus Operations GmbH
发明人： Dort Daandels , Bernhard Schlipf
IPC分类号： B64C9/22 , B64C9/02
CPC分类号： B64C9/22 , B64C9/02
摘要： A wing for an aircraft, including a main wing, a slat, and a connecting assembly movably connecting the slat to the main wing, the slat being movable between retracted and extended positions. The connecting assembly includes a slat track and a roller bearing. A front section of the slat track is mounted to the slat. A rear section and an intermediate section of the slat track are mounted to the main wing via the roller bearing. The roller bearing includes a guide rail mounted to the main wing and a first roller which is rotatably mounted to the rear section of the slat track. The first roller engages a first engagement surface formed by the guide rail. The roller bearing includes a second roller which is rotatably mounted to the main wing. The second roller engages a second engagement surface formed by the intermediate section of the slat track. The first engagement surface comprises a first section, which is straight or is curved with a first radius of curvature and a first center of curvature, and the second engagement surface comprises a second section, which is straight or is curved with a second radius of curvature and a second center of curvature. When both the first section and the second section are curved, the first center of curvature and the second center of curvature are spaced from each other.

5. 发明授权

US12054236B2 Inflatable suspended ceiling for a vehicle compartment, in particular for a passenger cabin of an aircraft 有权
公开(公告)号：US12054236B2
公开(公告)日：2024-08-06
申请号：US17848902
申请日：2022-06-24
申请人： Airbus Operations GmbH
发明人： Robert Hogh
IPC分类号： B64C1/06 , B64D11/00
CPC分类号： B64C1/066 , B64D11/00 , B64D2011/0046
摘要： An inflatable suspended ceiling for a vehicle compartment, in particular for a passenger cabin of an aircraft, includes a flat fabric cover sheet configured to roof over at least a longitudinal section of an interior space along an extending direction of the vehicle compartment underneath a structural ceiling of the vehicle compartment, and a tensioning structure attached to the cover sheet to carry the cover sheet from above and having a flexible envelope enclosing at least one inflatable chamber configured to tension the cover sheet when inflated. Mounting members are attached to the tensioning structure to mount the tensioning structure to counter-mounting members on the structural ceiling in a hanged configuration.

6. 发明公开

US20240239510A1 AIRCRAFT FUEL STORAGE SYSTEM 审中-公开
公开(公告)号：US20240239510A1
公开(公告)日：2024-07-18
申请号：US18415000
申请日：2024-01-17
申请人： AIRBUS OPERATIONS LIMITED , AIRBUS OPERATIONS (S.A.S.) , AIRBUS OPERATIONS GmbH
发明人： Francesco GAMBIOLI , Kei Philipp BEHRUZI , Jörg KLATTE , Damien GUILLOTEAU
IPC分类号： B64D37/22 , B64D37/06
CPC分类号： B64D37/22 , B64D37/06
摘要： An aircraft fuel storage system is disclosed including a fuel tank comprising a chamber for storing fuel, the chamber comprising a first side, a second side, and a base connecting the first side to the second side; a collector; and a first conduit and a second conduit, each of the first and second conduits fluidically coupling the chamber to the collector so that fuel is freely passable from the chamber to the collector via the respective first and second conduits. The first and second conduits open into the chamber at respective first and second conduit openings, the first conduit opening is nearer to the first side than the second conduit opening is to the first side, and the second conduit includes a second conduit lock portion that is nearer to the first side than the second conduit opening is to the first side. Also disclosed is an aircraft including the aircraft fuel storage system.

7. 发明授权

US12037101B2 Drive system with integrated torque sensing device 有权
公开(公告)号：US12037101B2
公开(公告)日：2024-07-16
申请号：US17714534
申请日：2022-04-06
申请人： Airbus Operations GmbH
发明人： Jan Haserodt , Christoph Winkelmann , Andreas Fleddermann
IPC分类号： B64C13/28 , B64C9/14 , F16D41/02 , F16D47/02 , B64D45/00
CPC分类号： B64C13/28 , B64C9/14 , F16D41/02 , F16D47/02 , B64D2045/001
摘要： A drive system for driving a movable flow body having a drive unit, a shaft, a torque sensing device, a no-back friction unit, and an axial bearing. The drive unit is coupled with the shaft to rotate the shaft, the torque sensing device is coupled with at least one of the drive unit and the shaft to detect a torque transferred from the drive unit into the shaft, the no-back friction unit is arranged between the axial bearing and an axial support means of the shaft, such that an axial load of the shaft is supported by the axial bearing, and the no-back friction unit is configured to substantially not counteract a rotation of the shaft in a first direction of rotation of the shaft and to apply a friction-induced additional torque to the shaft in an opposite second direction of rotation.

8. 发明公开

US20240228073A9 AIRFOIL PROFILE FOR AN AIRCRAFT AND AERODYNAMIC SURFACES USING SAID AIRFOIL PROFILE 审中-公开
公开(公告)号：US20240228073A9
公开(公告)日：2024-07-11
申请号：US18489411
申请日：2023-10-18
申请人： Airbus Operations GmbH
发明人： Mihai Ioan ZECHERU
IPC分类号： B64U20/20 , B64C3/14 , B64C11/20
CPC分类号： B64U20/20 , B64C3/14 , B64C11/20 , B64U10/25
摘要： An airfoil profile for an aircraft, such as an unmanned aerial system. The airfoil profile includes a leading edge portion and a trailing edge portion that are spaced apart along a chordwise direction, an airfoil centroid; and an upper airfoil surface and a lower airfoil surface. The airfoil surfaces are shaped such that the pressure center of the lifting force is arranged at the same chord location as the airfoil centroid or closer to the trailing edge portion along the chordwise direction than the airfoil centroid. With this, a pitch-down momentum is generated that urges the leading edge portion towards a lower angle of attack.

9. 发明授权

US12032678B2 Information processing architecture for implementation in a vehicle 有权
公开(公告)号：US12032678B2
公开(公告)日：2024-07-09
申请号：US17215140
申请日：2021-03-29
申请人： Airbus Operations GmbH
发明人： Kai Möller , Christian Groth , Sören Hübner , Oliver Schalke , René Niedermowe
IPC分类号： G06F21/53 , G06F9/455 , G06F16/178
CPC分类号： G06F21/53 , G06F9/45558 , G06F16/178 , G06F2221/033
摘要： An information processing architecture for implementation in a vehicle includes a software segregation unit which is configured to provide a first security domain and a second security domain which are assigned in each case to different operational areas of the vehicle and have their own data processing environments which are segregated from one another to run a multiplicity of computer applications. The software segregation unit is further configured to provide a synchronization instance, wherein the synchronization instance has a central dataset which is synchronized with data generated in the respective security domains independently from one another via data exchange and is selectively readable by both security domains.

10. 发明公开

US20240208641A1 AIRCRAFT STRUCTURE COMPONENT FOR LAMINAR FLOW 审中-公开
公开(公告)号：US20240208641A1
公开(公告)日：2024-06-27
申请号：US18391208
申请日：2023-12-20
申请人： Airbus Operations GmbH , AIRBUS OPERATIONS LIMITED
发明人： Tobias SCHRECK , Peter ROSENECKER , Tim CHANT
IPC分类号： B64C21/10
CPC分类号： B64C21/10
摘要： An aircraft structure component (1) for laminar flow including an outer skin (3) having an aerodynamic surface (5), wherein the aerodynamic surface (5) has a leading edge portion (7) and a downstream portion (11) adjacently downstream from the leading edge portion (7), wherein the downstream portion (11) of the aerodynamic surface (5) comprises a paint layer (13) or a foil layer that is not present in the leading edge portion (7), so that a border line (15) is formed between the leading edge portion (7) and the downstream portion (11) by the beginning paint layer (13) or foil layer, and wherein the outer skin (3) comprises an attachment surface (17) to which the paint layer (13) or the foil layer is attached.

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