公开(公告)号：US12172751B2

公开(公告)日：2024-12-24

申请号：US17952900

申请日：2022-09-26

Applicant: Airbus Operations Limited

Inventor： German Ibanez-Gil

IPC: B64C3/28

Abstract: A kit of parts for forming an aerofoil assembly is disclosed having a torsion box structure including a first attachment point and a second attachment point, the first and second attachment points being separated from each other along a separation axis, and a fixed leading or trailing edge structure including corresponding first and second attachment points, wherein a first structure includes a slidebly mounted abutment piece slideable along a slide path extending in a direction parallel to the separation axis and a fixing mechanism for fixing the slidebly mounted abutment piece. A second structure includes a corresponding abutment feature having a first abutment surface facing in a direction parallel to the separation axis of the second structure, such that, in use, the abutment piece prevents relative movement of the first and second structures.

公开(公告)号：US12097953B2

公开(公告)日：2024-09-24

申请号：US17703701

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C3/28 ,  B64C3/18 ,  B64C7/00 ,  B64C9/00 ,  B64F5/10

CPC classification number: B64C3/28 ,  B64C7/00 ,  B64C9/00 ,  B64F5/10 ,  B64C3/185

Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox. A kinked link includes a first arm, a second arm, and a corner where the first and second arms meet. The first arm of the kinked link is pivotally attached to the trailing edge panel at a first pivot joint, and the second arm of the kinked link is pivotally attached to the support structure at a second pivot joint.

公开(公告)号：US11975832B2

公开(公告)日：2024-05-07

申请号：US17425266

申请日：2020-05-25

Applicant: Airbus Operations GmbH

Inventor： Marcus Erban

IPC: B64C3/28 ,  B64C9/24 ,  B64D15/04

CPC classification number: B64C3/28 ,  B64C9/24 ,  B64D15/04

Abstract: A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.

公开(公告)号：US11858616B2

公开(公告)日：2024-01-02

申请号：US17162172

申请日：2021-01-29

Applicant: Goodrich Actuation Systems Limited

Inventor： Jeremy Kracke

IPC: B64C9/22 ,  B64C13/00 ,  B64C3/28 ,  B64C3/38 ,  B64C9/16

CPC classification number: B64C13/00 ,  B64C3/28 ,  B64C3/38 ,  B64C9/16 ,  B64C9/22

Abstract: An actuator system for controlling movement of a plurality of panels. The system includes two lifting mechanisms connected to each panel at two separate locations on the panel, and, for each panel: an actuator in engagement with a first of the lifting mechanisms to drive the lifting mechanism to move the panel, and a torque tube having a first end in engagement with the actuator so as to be rotated by the actuator as the actuator drives the lifting mechanism, the torque tube having a second end in engagement with the other of the two lifting mechanisms to drive the lifting mechanism due to rotation of the torque tube.

公开(公告)号：US20220306277A1

公开(公告)日：2022-09-29

申请号：US17695973

申请日：2022-03-16

Applicant: Airbus Operations GmbH

Inventor： Rainer GARTELMANN

IPC: B64C3/28 ,  B64C9/02 ,  B64C9/04 ,  B64C3/26 ,  B64C13/30

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 a stowed position and a deployed position. The connection assembly includes at least one rotation element mounted to the high lift body and mounted to the main wing rotatably about an axis of rotation. The high lift body includes a rigid portion and a flexible skin portion. The rigid portion is mounted to the rotation element. The flexible skin portion is connected to a leading edge portion of an upper skin panel of the main wing and is connected to the rigid portion of the high lift body The flexible skin portion is configured to be deformed between a stowed deformation state and a deployed deformation state, when the high lift body is moved between the stowed position and the deployed position.

公开(公告)号：US20220306274A1

公开(公告)日：2022-09-29

申请号：US17703733

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C3/18 ,  B64C3/14 ,  B64C3/28

Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, and a rear spar. A lower trailing edge panel is provided with a leading edge attached to the wingbox. The wing includes a flap, a flap deployment mechanism which is configured to deploy the flap, and a fairing which covers the flap deployment mechanism. A first end of a link is pivotally attached to the lower trailing edge panel at a first pivot joint, and a second end of the link is pivotally attached to the fairing at a second pivot joint. The second pivot joint is lower than the first pivot joint.

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：US11247766B2

公开(公告)日：2022-02-15

申请号：US16195630

申请日：2018-11-19

Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS GMBH

Inventor： Llifon Williams ,  Ross Salisbury ,  Marcus Rafla ,  Hugh Theobald ,  Christopher Payne ,  Robert McCormick ,  Heinz Hansen ,  Timothy Evans

IPC: B64C3/28 ,  B64C3/00 ,  B64C3/18 ,  B64C3/24 ,  B64C3/14

Abstract: A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.

公开(公告)号：US20220024557A1

公开(公告)日：2022-01-27

申请号：US17154213

申请日：2021-01-21

Applicant: Lanping JI

Inventor： Lanping JI ,  Jia JI ,  Xu WANG

IPC: B64C3/56 ,  B64C3/18 ,  B64C3/26 ,  B64C3/28 ,  B64C3/30 ,  B64C9/02 ,  B64C9/20 ,  B64C13/38

Abstract: A foldable wing with foldable trailing edge flap, that includes a main wing and a foldable trailing edge flap. The main wing includes a wing supporting skeleton and a plurality of skin supporting ribs. The foldable trailing edge flap includes a plurality of crank-shaped flap supporting ribs, a flexible flap skin, a connecting shaft, and a return spring. The plurality of crank-shaped flap supporting ribs are hinged with lower surfaces of corresponding plurality of skin supporting ribs through the connecting shaft to form a foldable trailing edge flap supporting skeleton that relies on the plurality of skin supporting ribs. The return spring makes an upper surface of a long side of each crank-shaped flap supporting rib attach closely to a lower surface of each skin supporting rib. The flexible flap skin is attached to an upper surface of the foldable trailing edge flap supporting skeleton.

公开(公告)号：US11052988B2

公开(公告)日：2021-07-06

申请号：US16417988

申请日：2019-05-21

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

Inventor： Mathias Farouz-Fouquet

IPC: B64C3/28

Abstract: An element including a leading edge forming a box delimited by a skin forming a lower surface and an upper surface and pierced with holes, in which the skin includes an inner wall and an outer wall that are electrically conductive and an electrically insulating intermediate wall, a pump for expelling or injecting air from or into the box. Each hole is equipped with an anti-clogging system including a conductive base, a needle made of piezoelectric material, one end of which is secured to the base, an electrical generator generating an electrical current in the needle, in which the form of the needle is such that a space is created between the needle and the edges of the hole, and in which the base has a recess in the extension of the space. Such an installation makes it possible to eliminate the residues which are lodged in the holes.