公开(公告)号：US20220411084A1

公开(公告)日：2022-12-29

申请号：US17849895

申请日：2022-06-27

Applicant: Airbus Operations SAS ,  Airbus SAS

Inventor： Pascal POME ,  Nicolas JOLIVET ,  Rémi AMARGIER ,  Lionel CZAPLA ,  Franck ALVAREZ ,  Kotaro FUKASAKU ,  Benoît PENVEN ,  Delphine JALBERT ,  Laurent LAFONT ,  Milan TASIC ,  Frédéric GOUPIL ,  Jean-Victor LAPEYRE ,  Emmanuel MERMOZ

IPC: B64D27/24 ,  B64D27/26

Abstract: A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

公开(公告)号：US20220411074A1

公开(公告)日：2022-12-29

申请号：US17849915

申请日：2022-06-27

Applicant: Airbus Operations SAS ,  Airbus Operations GmbH

Inventor： Florent HUET ,  Thomas JOSSET ,  Holger BAMMANN ,  Marion GOURGUES

IPC: B64D13/06 ,  B64D27/24

Abstract: An air supply system for a pneumatic de-icing assembly for de-icing surfaces of an aircraft, the aircraft comprising an air-conditioning system supplied by at least one first air compressor connected to a device for drawing in air outside the aircraft, the pneumatic de-icing assembly comprising an air supply inlet connected to an outlet of the first air compressor or to an outlet of the air-conditioning system. Thus, it is possible to supply air to a pneumatic de-icing system of an airplane equipped with electric motors or of what is referred to as “bleedless” type.

公开(公告)号：US20220404806A1

公开(公告)日：2022-12-22

申请号：US17841125

申请日：2022-06-15

Applicant: Airbus Operations SAS

Inventor： Julien BIGOT ,  Charly FOISSAC ,  Guillaume PICHON

IPC: G05B19/418 ,  B23Q3/16

Abstract: A method for assisting with the positioning of a drill bit for boring a component, which includes capturing images of a first component which has notable points, of calculating a digital representation from these images, of superposing the digital representation thus calculated and a digital design representation of the component, of evaluating the distances of the centers of bores to be created with respect to the notable points, and of positioning a drill bit with the aid of a camera and of the evaluated distances. The method continues in the same way for the other components to be assembled.

公开(公告)号：US20220390071A1

公开(公告)日：2022-12-08

申请号：US17830175

申请日：2022-06-01

Applicant: Airbus Operations SAS

Inventor： Bruno ESTEBE ,  Julien LAVERNE

IPC: F17C13/00

Abstract: A tank suitable for storing a product at a cryogenic temperature, including a fluid tight interior barrier, a fluid tight exterior barrier, surrounding the first interior barrier, an intermediary volume interposed between the interior and exterior barriers and at least one insulating layer positioned in the intermediary volume and including at least one thermal insulation mat, with very low thermal conductivity. The intermediary volume contains microspheres outside of the thermal insulation mats and has an enhanced level of vacuum. This solution makes it possible to maintain satisfactory performance in terms of thermal insulation even in the event of a loss of vacuum in the intermediary volume.

公开(公告)号：US11519362B2

公开(公告)日：2022-12-06

申请号：US17140707

申请日：2021-01-04

Applicant: Airbus Operations SAS

Inventor： Lionel Czapla ,  Benjamin Thubert ,  Julien Le Fanic

IPC: F02K1/72 ,  F02K1/76 ,  B64D29/02 ,  B64D29/06

Abstract: A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.

公开(公告)号：US11518532B2

公开(公告)日：2022-12-06

申请号：US16827008

申请日：2020-03-23

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Jean Geliot

IPC: B64D27/26 ,  B64F5/10

Abstract: An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.

公开(公告)号：US20220380057A1

公开(公告)日：2022-12-01

申请号：US17750715

申请日：2022-05-23

Applicant: Airbus Operations SAS

Inventor： Thomas BOISSON

IPC: B64D15/20

Abstract: A device for measuring the accretion of ice on a studied surface. The device has two aims, a first arm and a second arm, the second arm forming an enclosure for housing an image acquisition system disposed to acquire, through an orifice, images of a part of the studied surface located on the first arm. The device thus makes it possible to dissociate the support of the image acquisition system from that of the studied surface on which ice accumulates. Consequently, it is possible to place the second arm in the direction of the flow of the stream of air flowing along the aircraft while the first arm passes through the stream.

公开(公告)号：US20220355943A1

公开(公告)日：2022-11-10

申请号：US17737134

申请日：2022-05-05

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations GmbH ,  Airbus Operations S.L.

Inventor： Jorge CARRETERO BENIGNOS ,  Benedikt BAMMER ,  Olivier VERSEUX ,  Maria Del Sagrario JUANAS FERNANDEZ ,  Jorge MOLANO REMBIASZ ,  Thomas SCHERER ,  Alexander SOLNTSEV

IPC: B64D27/24 ,  B64D33/08

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

公开(公告)号：US20220355917A1

公开(公告)日：2022-11-10

申请号：US17735606

申请日：2022-05-03

Applicant: Airbus Operations Limited ,  Airbus Operations SAS

Inventor： Robert VENN ,  Andy MOUNTY ,  Matthew MARPLES ,  Laurent TIZAC

IPC: B64C25/10 ,  B64C25/04

Abstract: An aircraft landing gear is disclosed including a main leg, a foldable stay and a lock link configured to hold the foldable stay in position when the landing gear is extended. The foldable stay includes a first stay member and a second stay member, and the landing gear is configured such that the second stay member rotates in a first direction from a first position to a second position as the landing gear moves from a retracted configuration to an extended configuration. An end stop is arranged such that in the event the lock link fails, the second stay member rotates in the first direction from the second position to a third position in which the stay contacts the end stop thereby preventing further movement of the second stay member in the first direction and wherein the foldable stay goes over centre as the second stay member moves from the first position to the third position.

公开(公告)号：US11486335B2

公开(公告)日：2022-11-01

申请号：US17516251

申请日：2021-11-01

Applicant: Airbus Operations SAS

Inventor： Fabien Menou ,  Laurent Cazeaux ,  Thierry Gaches

IPC: F02K3/02 ,  F02K1/70 ,  F02K1/74

Abstract: A turbofan engine having a duct for a bypass flow and blades. Each blade is mobile between a stowed position and a deployed position. Each blade includes a rigid core a second, free end, and a sheath into which the core and the second end slide. Each sheath includes a first part which surrounds at least one part of the core and the second end, and an aileron which extends beyond the core facing the first part of the adjacent blade. The sheath is made of a flexible material such that the bypass flow causes the sheath to come into contact with the first part of the adjacent blade. A turbofan engine of this kind makes it possible to create blades whose production costs are low but whose aerodynamic behavior is effective.