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公开(公告)号：US20250042566A1
公开(公告)日：2025-02-06
申请号：US18788352
申请日：2024-07-30
Applicant: Airbus Operations (S.A.S.)
Inventor： Umberto Gastaldi , Brice Saudel , Grégoire Smith , Julien Aubry
Abstract: An air intake that makes it possible to avoid stiffeners and a front frame includes a lip, at least one external panel extending the lip on the outer side, at least one internal panel extending the lip on the inner side, the wall of the air intake having a thickness of value e. The thickness of the wall of the air intake changes longitudinally and comprises a zone at the front longitudinal end having a thickness of value e2 greater than the thickness e. In this way, the thickness of the air intake is optimized according to the needs of the zone concerned. A nacelle and propulsive assembly are provided with such air intake.
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公开(公告)号：US20240417066A1
公开(公告)日：2024-12-19
申请号：US18740660
申请日：2024-06-12
Applicant: Airbus Operations Limited , Airbus Operations (S.A.S.)
Inventor： Oliver Family , Sébastien Blanc
Abstract: A wing defines a chord which runs from a leading edge to a trailing edge. The wing has a main portion and a flap which is movable relative to the main portion to change the aerodynamics of the wing, for instance to maximize lift, or to reduce drag at the expense of some loss of lift. The wing has a guide mechanism which guides movement of the flap. The guide mechanism uses a pair of runners which run along respective tracks. The tracks are positioned at different locations along the direction of the chord, but overlap one another in the direction of the chord.
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公开(公告)号：US20240400223A1
公开(公告)日：2024-12-05
申请号：US18673398
申请日：2024-05-24
Applicant: Airbus Operations (S.A.S.)
Inventor： Juan RIVERO SESMA
IPC: B64D45/08
Abstract: A method for assisting landing of an aircraft on a landing runway of a destination airport facility includes two successive determinations of the position of the aircraft with respect to the landing runway and based on a photographic image taken from the aircraft, respectively according to two different algorithms for determining the position of the aircraft, together with the supply of at least one piece of information representative of a difference between the two determined positions. It is thus possible to verify whether the destination landing runway observed from the photographic image taken from the aircraft is indeed the target destination runway on which a landing of the aircraft is planned, or whether there exists an error in positioning of the aircraft with respect to the destination landing runway.
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公开(公告)号：US20240393926A1
公开(公告)日：2024-11-28
申请号：US18664644
申请日：2024-05-15
Applicant: Airbus Operations (S.A.S.)
Inventor： Benjamin Mazoin
IPC: G06F3/04842 , G06F3/04812
Abstract: A display on a screen of human-machine interface of a cockpit of an aircraft includes a text entry region, a navigation chart region, and at least one other region. A specific pointing mode, active when text entry is in progress, and a normal pointing mode, active at all other times, are implemented. In normal pointing mode, a pointing action triggers the command if any associated with the location where the pointing action is carried out. In specific pointing mode, only a pointing action in the text entry region or in the navigation chart region triggers a command if any associated with the location where the pointing action is carried out, while a pointing action in the at least one other region triggers an abandonment of text entry. Thus, tasks requiring a pilot of the aircraft to enter text are simplified.
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公开(公告)号：US12110093B2
公开(公告)日：2024-10-08
申请号：US17982999
申请日：2022-11-08
Applicant: Airbus Operations (S.A.S.)
Inventor： Benoit Orteu , Ludovic Mil , Lionel Laganier , Dominique Marty , Philippe Robert
IPC: B64C1/20
CPC classification number: B64C1/20
Abstract: An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.
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Patent Agency Ranking
6.发明公开公开(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
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.
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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
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.
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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.
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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
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.
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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
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.
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