公开(公告)号：US20220126978A1

公开(公告)日：2022-04-28

申请号：US17425271

申请日：2020-05-26

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Martin FEES

IPC: B64C3/28 ,  B64C3/18 ,  B64C9/00

Abstract: A leading-edge component for an aircraft includes at least a part of a flow body having a front skin, a hollow space at least partially delimited by the front skin and at least one separate retention device. The at least one retention device comprises a flexible structure with a mesh, a web, a fabric or a plurality of strings. The retention device is arranged behind the front skin in a distance thereto and extends along a main extension direction of at least a section of the front skin. The retention device is configured to retain a front skin that deforms to move into the hollow space upon an impact of a foreign object.

公开(公告)号：US20240174344A1

公开(公告)日：2024-05-30

申请号：US18501226

申请日：2023-11-03

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Martin FEES

IPC: B64C3/26 ,  B64C3/18

CPC classification number: B64C3/26 ,  B64C3/187 ,  B64C3/28

Abstract: A flow body for an aircraft includes a front skin having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, at least one rib arranged inside the flow body and having a first side and a second side. The at least one rib comprises two independent flanges. The two flanges extend from a common junction section, which is arranged between the first side and the second side, to the first side. The two flanges diverge towards the first side. Each flange comprises an attachment strap at the first side for attaching the respective flange to the front skin. The respective attachment strap has a shape corresponding to the shape of the inner surface of the front skin.

公开(公告)号：US20220119094A1

公开(公告)日：2022-04-21

申请号：US17425264

申请日：2020-06-24

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Marcus ERBAN ,  Martin FEES

IPC: B64C9/26 ,  B64C3/50 ,  B64D15/04

Abstract: A leading-edge arrangement for an aircraft is proposed, comprising a plurality of movable flow bodies, a supply duct, an air transfer duct, and at least one perforated tube. The movable flow bodies are arranged in a consecutive arrangement to form a row with a first end and a second end. The supply duct reaches into an interior of one of the flow bodies at the first end. The air transfer duct connects to the supply duct and extends at least through the interior of the respective flow body in the direction towards the second end. The at least one perforated tube is arranged inside at least one of the flow bodies that directly follows on. The at least one perforated tube is in fluid communication with the transfer duct. The transfer duct is configured to transfer air from the supply duct into the at least one perforated tube.

公开(公告)号：US20200346738A1

公开(公告)日：2020-11-05

申请号：US16861714

申请日：2020-04-29

Applicant: Airbus Operations GmbH

Inventor： Marcus ERBAN ,  Martin FEES ,  Stefan BENSMANN

IPC: B64C9/24 ,  B64D27/18 ,  B64D15/04 ,  B64D13/06

Abstract: A leading-edge device for an aircraft, the device comprising a flow body having a front skin, a back skin, a spar and an air inlet. The front skin is curved around a spanwise axis to form a bottom section and a top section.A leading edge of the flow body is arranged between the bottom section and the top section. The spar extends from the bottom section to the top section. The front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet. An outlet portion is arranged at least directly adjacent to the bottom section of the front skin. The outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets.

公开(公告)号：US20240326981A1

公开(公告)日：2024-10-03

申请号：US18602477

申请日：2024-03-12

Applicant: Airbus Operations GmbH

Inventor： Bernhard SCHLIPF ,  Martin FEES

IPC: B64C7/00 ,  B64C9/02 ,  B64C9/26

CPC classification number: B64C7/00 ,  B64C9/02 ,  B64C9/26

Abstract: A sealing strip for sealing a gap between convexly curved aerodynamic surface elements of an aircraft. The sealing strip has a convexly curved outer side, welting sections at both longitudinal edges of the sealing strip for fixing the sealing strip at the aerodynamic surface elements, and a mid-seal section between the welting sections. The welting sections protrude on an inner side from the mid-seal section. The sealing strip has a first, second, and third length regions, the second length region being located longitudinally between the first and third length region. The welting sections are omitted in the second length region or the welting sections in the second length region are less rigid than the welting sections in the first and third length regions. Further, a control surface arrangement, a wing and an aircraft with such a sealing strip.

公开(公告)号：US20230064922A1

公开(公告)日：2023-03-02

申请号：US17897563

申请日：2022-08-29

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Martin FEES

IPC: B64C3/28 ,  B64C9/26

Abstract: A wing for an aircraft, including a main wing, and a leading edge high lift assembly including a high lift body, and a connection assembly connecting the high lift body to the main wing such that the high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes a first connection element mounted to the high lift body and movably mounted to the main wing. The connection assembly includes a second connection element mounted to the high lift body spaced apart from the first connection element in a span direction, and movably mounted to the main wing. The connection assembly includes an additional support device arranged spaced apart from the first and second connection elements and configured to support the high lift body at the main wing against movement or deformation of the high lift body relative to the main wing.

公开(公告)号：US20220219803A1

公开(公告)日：2022-07-14

申请号：US17615068

申请日：2020-07-07

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Marcus ERBAN ,  Martin FEES

IPC: B64C9/02 ,  B64C9/04 ,  B64C13/28

Abstract: A movable flow body device for an aircraft including an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a second position and a third mechanical interface in a third position. The first mechanical interface may be a master interface arranged in a central region, while the second and third mechanical interfaces are slave interfaces. Preferably, in the outboard position, a link plate between a support lever and a support rib of the flow body is inverted compared to the further inboard mechanical interface, which allows for supporting slimmer and longer flow bodies in the outboard region and providing a rigging hinge line through the whole flow body.

公开(公告)号：US20240174345A1

公开(公告)日：2024-05-30

申请号：US18519459

申请日：2023-11-27

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Martin FEES ,  Alexander BURCHARD

IPC: B64C9/02 ,  B64C9/24

CPC classification number: B64C9/02 ,  B64C9/24

Abstract: A movable flow body for an aircraft including a front skin having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, at least one load introduction rib having a skin interface side and a drive side, at least one coupling element arranged on the drive side for coupling with a drive mechanism, and at least one interface element removably attached to the front skin interface side. The at least one interface element includes a bonding surface having a shape corresponding to the shape of the inner surface of the front skin. The at least one interface element is materially bonded to the inner surface of the front skin.

公开(公告)号：US20230406481A1

公开(公告)日：2023-12-21

申请号：US18333964

申请日：2023-06-13

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Martin FEES

IPC: B64C9/02 ,  B64C9/22 ,  B64D15/04

CPC classification number: B64C9/02 ,  B64D15/04 ,  B64C9/22

Abstract: A support arrangement for a leading-edge high lift device comprising a support arm for movably supporting the leading-edge high lift device on a wing structure. In order to accommodate the supply of the leading-edge high lift device with a fluid such as an anti-ice fluid, for example pressurized hot air, the support arm is configured as a fluid conduit for feeding fluid to and/or from the leading-edge high lift device. The leading-edge high lift device may be configured as a droop nose device.

公开(公告)号：US20220324578A1

公开(公告)日：2022-10-13

申请号：US17718899

申请日：2022-04-12

Applicant: Airbus Operations GmbH

Inventor： Stefan BENSMANN ,  Marcus ERBAN ,  Martin FEES

IPC: B64D15/04

Abstract: A piccolo tube for de-icing an airfoil structure of an aircraft is disclosed having a shape extending in a longitudinal direction and is configured for installation in an airfoil structure of an aircraft in the longitudinal direction of the airfoil structure. The piccolo tube includes a connector element for receiving heated air from a supply source, and a longitudinally extending air duct having a plurality of outlet openings arranged along the air duct, for supplying and distributing the heated air along the inner side of the airfoil structure. The piccolo tube is curved and its curvature is adapted to a curvature of the airfoil structure in its longitudinal direction. A de-icing system includes the piccolo tube and a supply source for supplying heated air to the piccolo tube. An airfoil structure includes the piccolo tube and/or the de-icing system.