公开(公告)号：US20220090518A1

公开(公告)日：2022-03-24

申请号：US17479540

申请日：2021-09-20

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

Inventor： Michael Berjot ,  Rémi Lansiaux ,  William Bras ,  Germain Gueneau

IPC: F01D25/28

Abstract: An assembly of an engine with a pylon, including a force reacting assembly having a connection device and two rods, the connection device including a shoe. A spreader extends between first and second ends and has a central part connected to the shoe by a main connection including a main rotation pin and axis in a plane of symmetry of the connection device. Two fittings are on either side of the plane of symmetry each having two arms between which the spreader is positioned. A first, respectively second, rod includes a front end fastened to the engine and a rear end fastened to the first, respectively second, end of the spreader and to the first, respectively second, fitting by a secondary connection. Two extensions of the spreader are each associated with a pair of elastic stops. For the first, respectively second, end of the spreader, each stop is between an arm of the first, respectively second, fitting and the extension.

公开(公告)号：US11239556B2

公开(公告)日：2022-02-01

申请号：US17032928

申请日：2020-09-25

Applicant: Office National d'Etudes et de Recherches Aérospatiales ,  AIRBUS OPERATIONS (S.A.S.)

Inventor： Cédric Martel

IPC: H01Q5/15 ,  H01Q5/357 ,  H01Q1/28 ,  H01Q1/38

Abstract: A multi-band antenna (100) including a metal base plate (10) forming an electrical ground plane, and a plurality of metal patches (1 to 3) superimposed on top of the metal base plate. The metal patches are connected in parallel between a signal lead wire (11A) and the metal base plate. The metal patches have respective surface areas which increase with the distance of each metal patch from the metal base plate. The antenna provides as many different resonant frequency values as there are patches.

公开(公告)号：US11215118B2

公开(公告)日：2022-01-04

申请号：US16712232

申请日：2019-12-12

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

Inventor： Bruno Medda ,  Thomas Stevens ,  Julien Cayssials ,  Adeline Soulie ,  Didier Poirier ,  Pierre-Alain Pinault ,  Esteban Martino González ,  Juan Tomas Prieto Padilla ,  Diego Barron Vega

IPC: F02C7/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  F02C7/047 ,  F02C6/08 ,  F02C7/14 ,  B64D13/06

Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

公开(公告)号：US11214348B2

公开(公告)日：2022-01-04

申请号：US16453119

申请日：2019-06-26

Applicant: Airbus Operations S.A.S.

Inventor： Marie-Anne De Smet

IPC: B64C1/06 ,  B64C7/00 ,  G01D11/24

Abstract: A sensor is fixed on an aircraft structure by a joining system which includes at least one enclosure in which is positioned at least one transducer, at least one passage configured to allow at least one conducting element to pass through the enclosure, at least one flexible connection connecting each transducer present in the enclosure to said enclosure and at least one binder joining together the enclosure and the structure. This joining system makes it possible to limit the spread of the deformations of the structure toward the transducer or transducers and ultimately the risks of malfunction.

公开(公告)号：US11187189B2

公开(公告)日：2021-11-30

申请号：US16695820

申请日：2019-11-26

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

Inventor： Frédéric Journade ,  Pierre Charon ,  Laurent Cazeaux ,  Pascal Gougeon

IPC: F02K1/72 ,  F02K1/76

Abstract: A propulsion system includes a bypass turbine engine and a pylon. The turbine engine includes an engine, two internal cowls, two outer cowls, a first lock for locking the internal cowls to the engine, cascades of vanes fixed to the outer cowl via hooping, wherein the outer cowls are movable in translation with respect to the engine, in which each outer cowl is able to slide parallel to a direction of translation on an internal cowl via a top guideway connection and a bottom guideway connection, and in which each outer cowl is mounted with the ability to slide parallel to the direction of translation on the pylon via an upper guideway connection. The propulsion system makes it possible during maintenance operations to move the outer cowl and the internal fixed structure towards the rear and therefore away from the front cowls to get at the engine.

公开(公告)号：US11155337B2

公开(公告)日：2021-10-26

申请号：US16410908

申请日：2019-05-13

Applicant: AIRBUS OPERATIONS S.A.S.

Inventor： Bernard Guering ,  Laurent Saint-Marc

IPC: B64C13/02 ,  B64C13/04 ,  B64C13/06

Abstract: Disclosed herein is a monobloc and removable pedal module for an aircraft rudder bar. The pedal module, which is intended for a rudder bar, includes a pedal, at least one integrated adjustment system, and a connection device which enables a removable connection of the pedal module to be produced. The pedal module is a monobloc component in order to simplify and facilitate its replacement via the removable connection obtained by the connection device.

公开(公告)号：US11124285B2

公开(公告)日：2021-09-21

申请号：US16037269

申请日：2018-07-17

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

Inventor： Rodolphe Trouve ,  Jean-Claude Lacombe ,  Julien Rodes ,  Thomas Schutz

IPC: B64C3/26 ,  B64C3/18 ,  B64C3/20 ,  B29D99/00 ,  B29L31/30

Abstract: An aerodynamic profile including a skin defining the outer surface of the aerodynamic profile, a leading edge, a trailing edge and a central portion representing at least 50% of the chord of the profile. The profile includes a hollow core of composite material reinforced with a textile having unidirectional fibers. The hollow core has, in cross section, an oblong shape that is rounded, in particular at each of its ends. The skin bears against the hollow core over the length of the central portion of the aerodynamic profile, both on the pressure side and on the suction side of the profile. The reinforcement with a textile having unidirectional fibers permits an ideal orientation of reinforcing fibers in order to optimize mechanical properties in certain directions. The shape of the hollow core, elongate along the chord of the profile and rounded, lends it great resistance to deformation.

公开(公告)号：US20210266091A1

公开(公告)日：2021-08-26

申请号：US17176757

申请日：2021-02-16

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

Inventor： Laurent Azoulai ,  Philippe Delga ,  François Tranchet ,  Rémy Lazzerini ,  Jean Pasquie ,  Ludovic Parisot ,  Philippe Merceron

IPC: H04K3/00 ,  H04B7/185 ,  G01S19/21

Abstract: A system includes at least one reception unit installed in an aircraft and configured for tracking satellites of the satellite navigation system of the GNSS type. The system includes a generation unit for generating an expected number corresponding to the number of satellites that the reception unit is expected to track, a detection unit including a comparison part for comparing the expected number with a tracked number corresponding to the number of satellites that the reception unit is actually tracking and a decision part for detecting a jamming, as a function of the result of the comparison made by the comparison part and transmitting detection data in the event of detection, and a transmission unit configured to transmit jamming detection data to at least one user device, the system making it possible to detect a jamming of a GNSS system in an automatic and reliable manner.

公开(公告)号：US11066994B2

公开(公告)日：2021-07-20

申请号：US16586075

申请日：2019-09-27

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

Inventor： Alain Porte ,  Jacques Lalane ,  François Pons

IPC: F02C7/045 ,  B64D33/02 ,  G10K11/16

Abstract: An assembly including two juxtaposed acoustic panels. Resistive faces of the acoustic panels are in the continuation of one another. A first resistive face extends as far as the first end wall of a first panel. The first end wall is in contact with a second end wall of a second panel in the region of the first resistive face and of the second resistive face. A connecting piece is interposed between the first end wall and the second end wall over a part of the length thereof so that the connecting piece does not extend as far as the first and second resistive faces. That makes it possible to form an acoustic cladding that is continuous, exhibiting no non-acoustic zone or reduced-acoustic zone at the junction between the acoustic panels of which it is formed. A nacelle of an aircraft propulsion unit is one application.

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.