公开(公告)号：US10994827B2

公开(公告)日：2021-05-04

申请号：US15979806

申请日：2018-05-15

Applicant: Airbus Operations GmbH ,  Airbus Operations Ltd

Inventor： Christoph Winkelmann ,  Wilfried Ellmers ,  Stephen Briancourt ,  David Brakes

IPC: B64C3/54 ,  B64C3/56 ,  F16B45/02

Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

公开(公告)号：US10597139B2

公开(公告)日：2020-03-24

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

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：US20190112074A1

公开(公告)日：2019-04-18

申请号：US16149210

申请日：2018-10-02

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

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

IPC: B64F5/00 ,  B64D27/26

Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.

公开(公告)号：US20170001703A1

公开(公告)日：2017-01-05

申请号：US15201762

申请日：2016-07-05

Applicant: Airbus Operations S.L. ,  Airbus Operations Ltd.

Inventor： Jesús Javier VAZQUEZ CASTRO ,  Fernando PEREIRA MOSQUEIRA ,  Juan José GUTIERREZ SANTIAGO ,  Anthony LANGLEY ,  Guy TOTHILL ,  Davood SARCHAMY ,  Miguel MARÍN MUÑOS

IPC: B64C1/12 ,  B64C7/00 ,  B64C1/06

CPC classification number: B64C1/12 ,  B64C1/061 ,  B64C1/064 ,  B64C1/34 ,  B64C3/26 ,  B64C7/00 ,  B64C7/02

Abstract: An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.

Abstract translation: 飞机（例如整流罩）的外部部件包括以柔性材料制成的皮肤，所述柔性材料连接到至少两个方向上布置的刚性支撑元件（例如龙骨和框架）。 皮肤包括由刚性支撑元件和/或外部可充气面板界定的所有托架中的内部充气面板。 皮肤被接合到支撑元件，使得其外表面符合空气动力学要求。

公开(公告)号：US09011062B2

公开(公告)日：2015-04-21

申请号：US14265994

申请日：2014-04-30

Applicant: Airbus Operations (SAS) ,  Airbus Operations Ltd

Inventor： Clement Chirol ,  Philip Cresswell ,  Florian Dapot

IPC: F16B37/14 ,  F16B33/00 ,  B64D45/02 ,  F16B5/02 ,  F16B19/05 ,  F16B39/02

CPC classification number: F16B33/004 ,  B64D45/02 ,  F16B5/025 ,  F16B19/05 ,  F16B33/02 ,  F16B37/14 ,  F16B39/025 ,  Y10T29/49925

Abstract: An assembly comprising at least two non-metal components which are fixed to each other using at least one fixing system. The fixing system includes a fixing device with a fixing element which is provided with a head and a rod, and a crimping ring which is in contact with one of the components. A protection device is a part of the fixing system which delimits a cavity for confining gas around a portion of the device comprising the crimping ring. In order to improve the repeatability of the operation for positioning the protection device, a guiding device is provided which includes an assembly element on the portion of the fixing device, and an element for guiding the protection device.

Abstract translation: 一种组件，其包括使用至少一个固定系统彼此固定的至少两个非金属部件。 固定系统包括具有固定元件的固定装置，该固定元件设置有头部和杆，以及与其中一个部件接触的压接环。 保护装置是定影系统的一部分，其限定用于围绕包括压接环的装置的一部分围绕气体的空腔。 为了提高用于定位保护装置的操作的重复性，提供了一种引导装置，其包括在固定装置的部分上的组件元件和用于引导保护装置的元件。

公开(公告)号：US11993376B2

公开(公告)日：2024-05-28

申请号：US17703653

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C9/02 ,  B64C9/20 ,  B64C13/34 ,  B64F5/10

CPC classification number: B64C9/02 ,  B64C9/20 ,  B64C13/34 ,  B64F5/10

Abstract: A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

公开(公告)号：US11506561B2

公开(公告)日：2022-11-22

申请号：US16711886

申请日：2019-12-12

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

Inventor： Alessio Cipullo ,  Sy-Dat Le ,  Carlos Bueno Vazquez

IPC: G01M3/04 ,  G01K11/3206 ,  B64D45/00 ,  G01K11/32 ,  G01K13/024 ,  G01M3/00 ,  G01M3/38

Abstract: An overheat detection system for an aircraft, the system comprising a first bleed monitoring computer, BMC1, configured to identify leakages in a pneumatic system, the BMC1 including a first optical controller, a second bleed monitoring computer, BMC2, the BMC2 including a second optical controller, an optical fiber link connecting the first optical controller of the BMC1 and the second optical controller of the BMC2 for communication between the BMC1 and the BCM2 and between the first optical controller and the second optical controller, wherein the first and the second optical controllers are configured to detect overheat of the optical fiber link based on a wavelength shift of a modulated optical signal transmitted through the optical fiber link, and transmit signals to the first BMC1 and the second BMC2 based at least on the detected overheat.

公开(公告)号：US20220306282A1

公开(公告)日：2022-09-29

申请号：US17703653

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C9/02 ,  B64C9/20 ,  B64F5/10 ,  B64C13/34

Abstract: A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

公开(公告)号：US20220306279A1

公开(公告)日：2022-09-29

申请号：US17703701

申请日：2022-03-24

Applicant: Airbus Operations Ltd.

Inventor： William Tulloch

IPC: B64C3/28 ,  B64C7/00 ,  B64C9/00 ,  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. 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：US11027819B2

公开(公告)日：2021-06-08

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 ,  B64D45/00

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.