公开(公告)号：US20210197984A1

公开(公告)日：2021-07-01

申请号：US17131206

申请日：2020-12-22

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

Inventor： Jean-Marc Datas ,  Jacques Bouriquet ,  Jean-Mickael Brindeau ,  André Aquila ,  Patrick Guibert

IPC: B64F5/10 ,  B64F5/50

Abstract: To reduce the footprint of an installation for assembling a fuselage section, a support structure includes a chassis and a core mounted so that it can rotate relative to the chassis about an axis of rotation of the core. The core includes a fastener(s) for holding the longitudinal fuselage portions around the core, with a view to assembling them to form the fuselage section. The support structure includes one or more rolling elements provided on the chassis, in order to allow the movement of this support structure within the installation.

公开(公告)号：US10903645B2

公开(公告)日：2021-01-26

申请号：US16133545

申请日：2018-09-17

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Patrick Oms

IPC: H02H3/17 ,  H02H7/20 ,  G01R31/52 ,  G01R31/00 ,  H02H3/027

Abstract: An electrical link including a protective sheath surrounding at least two conductors each covered by an insulating jacket and an electrical protection system includes: a conductive sheath on each of the insulating jackets, a circuit breaker for each conductor; a direct current generator generating a direct current to be successively applied to each conductive sheath; and a leakage current detection circuit for each conductive sheath; a sequencer successively supplying the direct current to each conductive sheath; the detection circuit measures a current in each conductive sheath and compares a voltage proportional to the current to a first and second ranges of values, the detection circuit activating the circuit breaker if: the voltage is outside of the first range of values while the current generator generates a non-zero current; or the voltage is outside of the second range of values.

公开(公告)号：US20200369395A1

公开(公告)日：2020-11-26

申请号：US16878346

申请日：2020-05-19

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

Inventor： Thomas Deforet ,  Rémi Lansiaux ,  Olivier Dubois ,  Jacky Puech

IPC: B64D27/26 ,  B64D27/18

Abstract: A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

公开(公告)号：US10802039B2

公开(公告)日：2020-10-13

申请号：US16188764

申请日：2018-11-13

Applicant: Airbus Operations S.A.S.

Inventor： David Andissac ,  Maxime Semat

IPC: G01P13/02 ,  B64C13/50 ,  B64C9/16 ,  B64D43/00 ,  G01C9/00 ,  G05D1/08

Abstract: An estimation system includes a module for measuring a current angle of attack and current flight parameters of the aircraft, a module for estimating a current lift coefficient of the aircraft from the current flight parameters and from a mass of the aircraft, a module for estimating an angle of attack for a zero lift from the current angle of attack, from the current lift coefficient and from a slope of an affine part of at least one theoretical curve describing a lift coefficient of the aircraft as a function of an angle of attack, a module for estimating the current position of the flaps of the aircraft from the angle of attack for a zero lift and a module for sending the current position of the flaps to a user device.

公开(公告)号：US20200316900A1

公开(公告)日：2020-10-08

申请号：US16828302

申请日：2020-03-24

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

Inventor： Florian Ravise ,  Florent Mercat

IPC: B32B3/12 ,  G10K11/168

Abstract: An assembly constituting an acoustically absorbent material and including a first panel, a second panel pierced with holes, an intermediate panel pierced with through-holes and arranged between the first panel and the second panel, a first structure between the first panel and the intermediate panel and including first cages, a second structure between the second panel and the intermediate panel and including second cages, and for each through-hole of the intermediate panel, a tube opening out at the two ends thereof, where one of the ends of the tube is fixed to the intermediate panel at the through-hole, and where the other end of the tube is accommodated inside a first cage. Such an assembly makes it possible to obtain broad-band attenuation and is easy to manufacture.

公开(公告)号：US10759542B2

公开(公告)日：2020-09-01

申请号：US15801278

申请日：2017-11-01

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

Inventor： Jean Pierre Couffignal ,  Jérôme Cassagne ,  Didier Rovatti ,  Thomas Deforet ,  Benoit Orteu ,  Michael Belin ,  Miren Egana-Abarrategui

IPC: B64D27/26 ,  B64D45/00

Abstract: A rear engine attachment includes a beam attached to the reactor strut, a rudder mounted by a pivot connection on the beam about a main rotational axis, and two thrust rods each exhibiting a first end attached to the rudder and a second end attached to a front section of an engine, the two thrust rods and the rudder attached to the beam together defining a primary thrust path between the engine and the reactor strut to bear the engine thrust. For each thrust rod, the rear engine attachment exhibits a waiting fail-safe system activated in the event of a failure of the primary thrust path. The rear engine attachment includes, for each thrust rod, a break detector integral with the rudder which is provided to come into contact with the beam in the event of a failure of the primary thrust path. The attachment allows a quick inspection to be made to determine whether there has been a failure of the primary thrust path.

公开(公告)号：US20200269996A1

公开(公告)日：2020-08-27

申请号：US16785890

申请日：2020-02-10

Applicant: Airbus Operations S.A.S.

Inventor： Hervé Lasserre ,  Xavier Alquier ,  Aymeric Plo

IPC: B64F5/60 ,  B64C1/14 ,  B64D45/02

Abstract: A mobile machine includes a fuselage having at least one door, inside which is located a unit for processing measurements taken by at least one measurement device installed outside said fuselage. The system for communication between the processing unit and the measurement device includes a flex circuit that is affixed at least partially flat in the door corner between the door and the rim of the opening formed in the fuselage with which the door is associated and one of the ends, the internal end, of which is located inside the fuselage and the other, external, end of which is located outside. Since the flex circuit makes it possible to pass through the wall of the fuselage via the opening for doors, the need to make substantial modifications to the aircraft is avoided.

公开(公告)号：US20200247067A1

公开(公告)日：2020-08-06

申请号：US16779883

申请日：2020-02-03

Applicant: AIRBUS OPERATIONS S.A.S.

Inventor： Denis SOULA ,  Tanguy VERCAMER ,  Jago PRIDIE

IPC: B29C65/70 ,  B64C1/26 ,  B29C65/02 ,  B29C65/00 ,  B29C70/48

Abstract: A method is disclosed for manufacturing connecting members for connecting an aircraft wing to a center wing box, using preforms. The method involves a step of manufacturing at least one preform made of composite material forming the connecting member, and a step of assembling the preform or preforms by heat treatment to form the connecting member. The manufacturing method makes it possible, simply and quickly, to manufacture a connecting member that contributes to the connection between a center wing box of an aircraft and a wing of the aircraft.

公开(公告)号：US10732631B2

公开(公告)日：2020-08-04

申请号：US16121226

申请日：2018-09-04

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

Inventor： Bernard Barriety ,  Robin Vernay ,  Fabio Vetrano ,  Davide Cantiani

IPC: G05D1/00 ,  B64C13/04 ,  B64C13/16 ,  B64D43/00 ,  G01M9/06 ,  G05D1/06

Abstract: A method for alleviating and protecting loads of a lifting surface of an aircraft based on control of structural distortions of the lifting surface. The lifting surface includes a control surface, a maneuvering system for displacing the control surface and sensors which measure a dimensional characteristic linked to the distortion of the lifting surface. The method acquires characteristic data linked to the distortion of the lifting surface, determines a set of values of the shape, analyzes the value of the strain attribute and compares the set of values characterizing the shape to the values of the tolerance interval associated with the lifting surface. If the set of values characterizing the shape is outside of the interval, the process triggers an activation of the maneuvering system to displace the control surface from an initial position in order to alleviate the loads on the lifting surface.

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.