公开(公告)号：US20200231294A1

公开(公告)日：2020-07-23

申请号：US16739322

申请日：2020-01-10

Applicant: Airbus Operations S.A.S. ,  AIRBUS OPERATIONS LTD

Inventor： François Martinel ,  Joel Dedieu ,  Thierry Theron ,  Julien Moulis ,  Thomas Deforet ,  Audrey Benaben ,  Robert Whiffen

IPC: B64D27/26 ,  B64D27/18

Abstract: A method for assembling an aircraft pylon having a primary structure and at least one internal system at least partially positioned within the primary structure, wherein the internal system is positioned inside the primary structure before the last lateral panel of the primary structure is attached. The absence of one of the lateral panels facilitates the installation of the internal systems.

公开(公告)号：US20200023938A1

公开(公告)日：2020-01-23

申请号：US16193309

申请日：2018-11-16

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

Inventor： Saskia DEGE ,  Svenja JEGMINAT ,  Frank NIENABER ,  Jean GUILHAMET ,  Aeron Charles JONES

IPC: B64C3/56 ,  B64C13/16

Abstract: A method to control folding of a wing tip section about a fixed base wing section by a control system that automatically determines whether: (i) a command signal is received to fold the wing tip section, (ii) a first condition indicating signal indicates that the aircraft is on the ground; (iii) the current speed of the aircraft is no greater than a preset maximum speed, and (iv) the aircraft is not at gate in an airport.

公开(公告)号：US20180050790A1

公开(公告)日：2018-02-22

申请号：US15677434

申请日：2017-08-15

Applicant: Airbus Operations GmbH ,  Airbus Operations Ltd.

Inventor： Ian Roy WHITEHOUSE ,  Thomas EHLERS

IPC: B64C23/06

Abstract: A wing-lip arrangement couplable with a wing of an aircraft includes a connection region for coupling or integration with the wing end region, at least one tip, at least one upper surface and at least one lower surface, which extend between a leading edge and a trailing edge of the wing-tip arrangement from the connection region to the at least one tip, and at least one vortilon. The local dihedral of the wing-tip arrangement changes between the at least one tip and the connection region, such that at least a part of the wing-tip arrangement projects at an angle relative to the wing. The at least one vortilon includes a vortilon base and a vortilon tip. The vortilon base is attached to at least one of the at least one lower surface of the wing-tip arrangement. The vortilon tip faces in an upstream direction.

公开(公告)号：US20170355443A1

公开(公告)日：2017-12-14

申请号：US15619126

申请日：2017-06-09

Applicant: Airbus Operations GmbH ,  Airbus Operations Ltd.

Inventor： Christoph WINKELMANN ,  Johannes RUPP ,  Benjamin BISHOP

IPC: B64C3/56

CPC classification number: B64C3/56 ,  Y02T50/14

Abstract: A latching device for a wing including a support structure (29), a latching bolt (35) having a longitudinal axis (36) and being slidably supported by the support structure (29) such that the latching bolt (35) is movable between a retracted position and an extended position. The latching device (27) includes a first hydraulic actuator (47a) and a first connector assembly (38a) adapted to be connected to a first hydraulic system of an aircraft (1), and at least one second hydraulic actuator (47b) and a second connector assembly (38b) connected to a second hydraulic system. The first hydraulic actuator (47a) and the second hydraulic actuator (47b) are adapted to effect movement of the latching bolt (35) from the extended position into the retracted position independent of the other one of the at least one first hydraulic actuator (47a) and the at least one second hydraulic actuator (47b).

公开(公告)号：US12104724B2

公开(公告)日：2024-10-01

申请号：US17973622

申请日：2022-10-26

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations LTD

Inventor： Philippe Pedoussaut ,  Hervé Tressol ,  Najoua Erroui ,  Mouayiad Shebli

IPC: F16L23/18 ,  F16L23/028 ,  F16L23/16 ,  F16L23/24

CPC classification number: F16L23/24 ,  F16L23/0283 ,  F16L23/162 ,  F16L23/167 ,  F16L23/18

Abstract: A connection assembly between two portions of a line including an inner conduit for transporting a cryogenic fluid, the assembly including two flanges which are respectively arranged at the ends of the line portions and which are configured to be held in contact with one another by virtue of a fixing arrangement. The contact zone between the two flanges includes at least two grooves for positioning seals and at least one conduit opening out, for the one part, between the two seals and, for the other part, into an expansion chamber for the cryogenic fluid. The expansion chamber is arranged in one, or in the vicinity of one, of the first connection flange and the second connection flange. The expansion chamber includes a detector for detecting the presence of the cryogenic fluid in the expansion chamber or a recess configured for the installation of such a detector.

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：US12071239B2

公开(公告)日：2024-08-27

申请号：US17703733

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C9/02 ,  B64C7/00 ,  B64C9/16 ,  B64F5/10

CPC classification number: B64C9/02 ,  B64C7/00 ,  B64C9/16 ,  B64F5/10

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：US11845549B2

公开(公告)日：2023-12-19

申请号：US17703678

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C9/16 ,  B64C9/02 ,  B64F5/10

CPC classification number: B64C9/16 ,  B64C9/02 ,  B64F5/10

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 and a connector is movably mounted to the trailing edge panel on a bearing. A first end of a link is attached to the connector, and a second end of the link is attached to the support structure. During assembly, the connector is moved on the bearing from a first position to a second position where the connector is aligned with the first end of the link, then the connector at the second position is attached to the first end of the link. The connector may be moved by a rack-and-pinion mechanism.

公开(公告)号：US20230264804A1

公开(公告)日：2023-08-24

申请号：US18164119

申请日：2023-02-03

Applicant: Airbus Operations SAS ,  Airbus Operations LTD ,  Airbus Operations S.L.

Inventor： Bertrand DUTHILLE ,  Jonathan PRICE ,  Jago PRIDIE ,  Jose Manuel MENENDEZ MARTIN

IPC: B64C1/26 ,  B29C70/30

CPC classification number: B64C1/26 ,  B29C70/30 ,  B29D99/0014

Abstract: A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

公开(公告)号：US20220306283A1

公开(公告)日：2022-09-29

申请号：US17703678

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C9/16 ,  B64C9/02

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 and a connector is movably mounted to the trailing edge panel on a bearing. A first end of a link is attached to the connector, and a second end of the link is attached to the support structure. During assembly, the connector is moved on the bearing from a first position to a second position where the connector is aligned with the first end of the link, then the connector at the second position is attached to the first end of the link. The connector may be moved by a rack-and-pinion mechanism.