公开(公告)号：US20240327019A1

公开(公告)日：2024-10-03

申请号：US18616576

申请日：2024-03-26

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

Inventor： François Pons ,  Christian Flemin

IPC: B64D33/08 ,  H10N10/80

CPC classification number: B64D33/08 ,  H10N10/80

Abstract: An aircraft propulsion assembly with at least one ventilation device to cool at least one zone of the propulsion assembly. The ventilation device is regulated and includes at least one ventilation hole emerging in the zone to be cooled, at least one valve movable between a closed position where the valve shuts the ventilation hole and an open position where the valve at least partially frees the ventilation hole, at least one thermoelectric generator to generate an electric current and at least one automatic control to control the position of the valve by using the electrical current generated by the thermoelectric generator. The bleed air flow rate can be adjusted as a function of the cooling needs. An aircraft including at least one such propulsion assembly is disclosed.

公开(公告)号：US12017756B2

公开(公告)日：2024-06-25

申请号：US17983782

申请日：2022-11-09

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

Inventor： Benoit Orteu ,  Ludovic Mil ,  Lionel Laganier ,  Dominique Marty ,  Philippe Robert

IPC: B64C25/16 ,  B64C1/18 ,  B64C25/04 ,  B64C25/14

CPC classification number: B64C25/16 ,  B64C1/18 ,  B64C25/04 ,  B64C25/14

Abstract: A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmember parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.

公开(公告)号：US12011754B2

公开(公告)日：2024-06-18

申请号：US17871482

申请日：2022-07-22

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

Inventor： César Garnier

IPC: B21D26/021 ,  B21D53/92

CPC classification number: B21D26/021 ,  B21D53/92

Abstract: A method and a device for manufacturing a part starting from a cushion made of deformable material, in particular for an edge of an element of an aircraft. The device includes a preparation unit to create a cushion with two plates and, between the plates, an internal space with an opening, and a molding unit comprising a mold in which the cushion is positioned, the mold comprising two shells and an imprint corresponding to the shape of the part to be manufactured, the molding unit configured to inject a pressurized fluid into the internal space of the cushion through the opening to deform the cushion such that it matches the imprint and forms the part, the device being capable of manufacturing one-piece parts of various sizes, and in particular parts having complex shapes, in particular non-developable shapes.

公开(公告)号：US11987390B2

公开(公告)日：2024-05-21

申请号：US17165076

申请日：2021-02-02

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

Inventor： Cédric Godard ,  Florian Collado ,  Jacques Bouriquet ,  Jean-Marc Datas ,  Nicolas Darbonville

IPC: B64F5/10 ,  B64C1/00 ,  B64C1/18

CPC classification number: B64F5/10 ,  B64C2001/0045 ,  B64C1/18

Abstract: To make an aircraft assembly installation modulable, the latter includes a floor, assembly stations distributed on the floor, and structures for accessing the aircraft during their assembly, each structure being mobile on the ground. The access structures include at least one access structure at an orbital junction between two fuselage sections, at least one access structure at the two junctions between a fuselage section and each of the two aircraft wings, and at least one access structure at the junctions between a rear fuselage section and tail units. In addition, the installation is designed to be able to adopt several distinct configurations, each having a different distribution of the access structures between the assembly stations.

公开(公告)号：US20240151184A1

公开(公告)日：2024-05-09

申请号：US18519489

申请日：2023-11-27

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

Inventor： Petros Manaras ,  Brian Sagar

IPC: F02C7/232 ,  B64D37/00 ,  B64F5/60 ,  F16K37/00

CPC classification number: F02C7/232 ,  B64D37/005 ,  B64F5/60 ,  F16K37/0083 ,  F05D2260/80

Abstract: A method of determining an operating condition of a valve of an aircraft system includes obtaining a first time period associated with actuating the valve, and a second time period associated with actuating the valve. The method includes providing an indication of an altered operating condition associated with actuation of the valve based on the first and second time periods.

公开(公告)号：US20240124148A1

公开(公告)日：2024-04-18

申请号：US18333897

申请日：2023-06-13

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

Inventor： Frédéric Chelin ,  Christophe Bourdeau ,  Alexandre Bellanger ,  Lauren Davis

IPC: B64D29/06 ,  F02K1/76

CPC classification number: B64D29/06 ,  F02K1/763 ,  B64D2033/0206

Abstract: A nacelle includes a thrust reverser having a cowl movable in translation and an ejection structure also movable in translation and forming with the cowl a moving assembly, the moving assembly configured to moved, alternately, into a closed position in which the ejection structure is inserted into a housing formed in the nacelle and the cowl closes an ejection opening in the nacelle, and an open position in which the cowl releases the ejection opening in the nacelle and the ejection structure is located in this ejection opening, the positioning of the ejection structure in the housing in the closed position making it possible, in particular, to make space in the ejection opening and to reduce the size of the thrust reverser.

公开(公告)号：US11919259B2

公开(公告)日：2024-03-05

申请号：US17161062

申请日：2021-01-28

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

Inventor： Jago Pridie

IPC: B29C70/46 ,  B29K105/08 ,  B29K307/04 ,  B29L31/30

CPC classification number: B29C70/462 ,  B29K2105/089 ,  B29K2307/04 ,  B29L2031/3085

Abstract: A method for fabricating a central caisson of an aircraft wing including a frame formed from U-section crossmembers. Formation of at least one crossmember includes forming a stack comprising at least one layer of resin film applied to a layer of dry fibers, pressing this stack to confer on it a U-section form and such as to compress the layers thereof, and pre-polymerization and/or polymerization of the resin of the stack. The manipulated fiber layers are layers of dry fibers, such that manipulation thereof by an automated machine may be effected for a reasonable cost and at a high throughput. Deposition of resin films carried by removable leaves, i.e., of which one of the faces is not adhesive, likewise facilitates manipulation by an automated installation.

公开(公告)号：US11878809B2

公开(公告)日：2024-01-23

申请号：US16355999

申请日：2019-03-18

Applicant: Airbus Operations S.A.S.

Inventor： Camil Negulescu ,  Jean-Michel Rogero

IPC: B64D33/02 ,  F02K3/077 ,  B64C7/02 ,  F02K3/12 ,  B64D29/00 ,  F01D25/24 ,  F02K3/04 ,  B64D33/04 ,  B64D27/10 ,  B64D27/16

CPC classification number: B64D33/02 ,  B64C7/02 ,  B64D27/10 ,  B64D27/16 ,  B64D29/00 ,  B64D33/04 ,  F01D25/24 ,  F02K3/04 ,  F02K3/077 ,  F02K3/12 ,  B64D2033/0266 ,  F05D2220/323

Abstract: An aircraft propulsion assembly includes a first engine and a second engine that are adjacent and a nacelle in which the engines are installed. The nacelle includes a common air inlet lip for the first engine and the second engine, the air flow being divided between the first engine and the second engine by a median lip which extends, at least partly, set back from said common air inlet lip. The common are inlet lip includes, directly in line with the median lip, a bottom lobe and a top lobe extending forward of the nacelle. Such a configuration makes it possible to be able to provide a high aerodynamic form between the fairings of the engines, without the risk of generating overspeeds in the air flow.

公开(公告)号：US20230373134A1

公开(公告)日：2023-11-23

申请号：US18309374

申请日：2023-04-28

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

Inventor： Gérard Millet ,  Vincent Delpy ,  Simon Foucart-Gaudy

IPC: B29C39/10 ,  B64D37/04

CPC classification number: B29C39/10 ,  B64D37/04 ,  B29L2031/3076

Abstract: A tool for laying a sealing strip around a protruding part of a connecting element protruding from a bearing surface, the laying tool including an annular duct having an outer surface configured to delimit, with the bearing surface and the protruding part, a cavity when the annular duct is positioned around the protruding part and in contact with the bearing surface, the annular duct including at least one orifice for supplying pasty composition and outlet orifices for injecting the pasty composition into the cavity to form the sealing strip. A method for laying a sealing strip using the tool is disclosed and an aircraft with at least one sealing strip obtained using the method.

公开(公告)号：US20230365252A1

公开(公告)日：2023-11-16

申请号：US18317207

申请日：2023-05-15

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

Inventor： Jérôme Antypas

IPC: B64C25/16

CPC classification number: B64C25/16

Abstract: A set of doors includes two front doors and two rear doors to open or close the front landing gear bay of the aircraft to enable lowering or retraction of a landing gear, each of the front doors including at least one deflector arranged on an internal face of the front door near a rear leading edge thereof, the deflector extending along the rear leading edge, the set therefore enabling action on an aerodynamic flow between the front doors to disturb it in such a manner as significantly to attenuate undesirable transitory vibratory phenomena that can arise in a particular configuration in which the front doors are open and the rear doors are closed.