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：US20240351700A1

公开(公告)日：2024-10-24

申请号：US18641967

申请日：2024-04-22

Applicant: Airbus Operations GmbH ,  Airbus Operations Ltd.

Inventor： Stefan Wriede ,  Malte Vollmer ,  Frederic Gobin ,  Christopher Slack

IPC: B64D37/08 ,  B64D37/04 ,  B64D37/32

CPC classification number: B64D37/08 ,  B64D37/32 ,  B64D37/04

Abstract: A liner segment for a frame bay of a fuel tank structure includes a liner segment base body adapted to float on fuel in the fuel tank structure, a liner segment side wall extending from the liner segment base body, a multitude of drainage holes arranged in the liner segment base body, and adapted to provide a bidirectional fluid connection from an upper side to a bottom side of the liner segment facing the fuel tank structure, a valve, arranged in a cut out of the liner segment and adapted to provide an unidirectional fluid connection from the bottom side of the liner segment to the upper side of the liner segment, such that the unidirectional fluid connection is blocked in the opposite direction, such that a remaining portion of fuel within the fuel tank structure is reduced.

公开(公告)号：US20230339593A1

公开(公告)日：2023-10-26

申请号：US18127052

申请日：2023-03-28

Applicant: AIRBUS SAS ,  Airbus Operations SAS ,  AIRBUS OPERATIONS LTD ,  Airbus Operations SL ,  Airbus Operations GmbH

Inventor： Elisa Alvarez López-Herrero ,  Matthias Wolff ,  Alexander Broer ,  Rainer Tegtmeyer ,  Michael Wießmeier ,  Till Marquardt ,  André Anger ,  Anna-Katrin Wengorra ,  Marco Dias Figueiredo ,  Jose Luis Martinez Munoz ,  Alberto Gallegos Elvira ,  Kaya Sahin ,  Guillaume Gallant ,  Kasidit Leoviriyakit ,  Philip Wright

IPC: B64C1/10 ,  B64C1/06 ,  B64D37/04

CPC classification number: B64C1/068 ,  B64C1/10 ,  B64D37/04

Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.

公开(公告)号：US20230280269A1

公开(公告)日：2023-09-07

申请号：US18088403

申请日：2022-12-23

Applicant: AIRBUS OPERATIONS, S.L.U. ,  AIRBUS OPERATIONS LTD

Inventor： David VICENTE OLIVEROS ,  Christopher J. WOODS

IPC: G01N21/3504 ,  G01N21/85 ,  G08B21/12 ,  B64D45/00

CPC classification number: G01N21/3504 ,  G01N21/85 ,  G08B21/12 ,  B64D45/00 ,  B64D2045/009

Abstract: A gas detection system that detects gas inside an enclosed space of an aircraft system on board in an aircraft. The system is used in a method for determining the presence of a gas inside an aircraft system by means of a detection system installed on the aircraft system. The system monitors and/or detects a vacuum leak or of fire inside an aircraft system arranged in an aircraft.

公开(公告)号：US10800549B2

公开(公告)日：2020-10-13

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: B64D27/26 ,  B64F5/00

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：US20200055592A1

公开(公告)日：2020-02-20

申请号：US16556651

申请日：2019-08-30

Applicant: Airbus Operations Ltd.

Inventor： Martin Griffith ROWLANDS ,  Maxwell William JONES ,  Graham KING ,  Trevor Anthony BRIGHTON ,  Matthew GADD

IPC: B64C25/26 ,  B64C25/16

Abstract: A control system has first and second processing modules for controlling retraction and extension of an aircraft landing gear assembly. The processing modules operate independently providing redundancy. Each processing module is configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly. A step of switching control from one processing module to the other (e.g. an avionics side changeover step) is performed (a) as part of the first sequence of steps, but only after the landing gear assembly has been retracted, or (b) as part of the second sequence of steps. By ensuring that the step of switching control is performed at such times, and not for example between initiation of the first sequence of steps and the retraction of the landing gear assembly, the landing gear assembly may be retracted sooner after such initiation.

公开(公告)号：US20190184532A1

公开(公告)日：2019-06-20

申请号：US16224338

申请日：2018-12-18

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

Inventor： David PETIT ,  Geneviève SCHUBETZER ,  Damien FRAYSSE ,  Serge VERNET ,  Sophie GOURDON ,  Nicolas CHARMES ,  Mathieu TRINDADE ,  Joel ANTIC

IPC: B25B27/00 ,  F16L19/07 ,  F16L19/04

CPC classification number: B25B27/0028 ,  B25B5/147 ,  B25B27/10 ,  F16L19/046 ,  F16L19/07 ,  F16L21/035

Abstract: When coupling tubular parts by fitting, the seal interposed between them may roll on itself, be pinched or damaged. Now, a twisted or damaged seal no longer correctly ensures the seal-tightness and it is very difficult to detect this. The present application discloses a tool for installing a seal between two tubular parts, one male and one female, including a compression ring to encircle the male part and exert a compression on the seal before producing the join. The tool also includes a tongue that can be positioned at a chamfered surface of the female tubular part. The tongue makes it possible to offer the pre-compressed seal with the dimensions of the female part a continuous travel making it possible to prevent any twisting or other effect compromising the seal-tightness.

公开(公告)号：US20180334238A1

公开(公告)日：2018-11-22

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

CPC classification number: B64C3/56

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.