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公开(公告)号：US20240253798A1
公开(公告)日：2024-08-01
申请号：US18417339
申请日：2024-01-19
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Jean-François ALLIAS , Damien MARIOTTO
IPC: B64D27/35 , B64D35/021 , B64D35/08 , F01D15/02 , F01D15/12
CPC classification number: B64D27/35 , B64D35/021 , B64D35/08 , F01D15/02 , F01D15/12 , F05D2260/40
Abstract: An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.
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32.发明公开公开(公告)号：US20240234065A9
公开(公告)日：2024-07-11
申请号：US18482127
申请日：2023-10-06
Applicant: Airbus Operations SAS
Inventor： Jean-Marc LACOSTE , Vincent DUFLOS DE SAINT AMAND
IPC: H01H71/10
CPC classification number: H01H71/10
Abstract: An electrical protection device of circuit-breaker type including a casing, a severing system, positioned in the casing, configured to assume inactivated and activated states corresponding to the on and off states of the electrical protection device, respectively, and a connection system configured to assume an open state in which it allows the electrical cable to be inserted and a second, closed state in which it surrounds the electrical cable. The connection system and the severing system are configured and arranged such that, when the connection system is in the closed state, the severing system severs the electrical cable when passing from the inactivated state to the activated state.
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公开(公告)号：US12030659B2
公开(公告)日：2024-07-09
申请号：US16990214
申请日：2020-08-11
Applicant: Airbus Operations SAS
Inventor： Alain Porte , Jacques Lalane , Frédéric Vinches , Gregory Albet
IPC: B64D33/02
CPC classification number: B64D33/02 , B64D2033/0206
Abstract: An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.
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34.发明公开公开(公告)号：US20240208243A1
公开(公告)日：2024-06-27
申请号：US18501299
申请日：2023-11-03
Applicant: Airbus Operations SAS , Airbus SAS , Airbus Operations GmbH
Inventor： Boris MORINIERE , Olivier BURGY , Samuel LELEU , Fabian MAHLER
CPC classification number: B41J3/4073 , B41J2/30 , B41J11/0045 , B64C3/26
Abstract: A inkjet printing device including an articulated robot having a free end, a printing module including a first part linked to the free end of the articulated robot and a second part that is movable with respect to the first part and supporting at least one printhead, a first servocontrol loop configured to control the articulated robot, a second servocontrol loop configured to correct, if necessary, the position of the second part with respect to the first part, which has a correction frequency at least five times greater than that of the first servocontrol loop. This solution makes it possible to obtain an inkjet printing device suitable for complex surfaces of large dimensions, that is highly responsive and offers high print quality.
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35.发明公开公开(公告)号：US20240203272A1
公开(公告)日：2024-06-20
申请号：US18534947
申请日：2023-12-11
Applicant: Airbus Operations SAS
Inventor： Emilie Claudel , Isabelle Sentissi , Louise Faure
CPC classification number: G08G5/065 , G01S13/934 , G06V10/70 , G06V20/17 , G06V20/56 , G08G5/0021 , G08G5/045
Abstract: The system for assisting the avoidance of an excursion by an aircraft from a runway or taxiway of an aerodrome includes a unit for monitoring the aerodrome so as to allow the detection, by optical detection, of a characteristic element of a pathway, for determining a current relative position of a landing gear of the aircraft (AC) with respect to the detected characteristic element, and for detecting a future excursion from the pathway of the aerodrome by the aircraft (AC) on the basis of at least this current relative position, and a unit for assisting the implementation of an action for assisting the avoidance of said future excursion. The system is configured for providing assistance to the pilot of the aircraft by improving his awareness of a potential excursion, by warning and/or ground navigation aid messages, and by providing protection of last resort via automatic braking.
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Patent Agency Ranking
公开(公告)号：US20240199231A1
公开(公告)日：2024-06-20
申请号：US18530281
申请日：2023-12-06
Applicant: Airbus Operations SAS , Airbus Operations S.L.
Inventor： Günther DRESSLER , Asuncion BUTRAGUENO-MARTINEZ , Rodolphe TROUVE , Dirk FELTIN
CPC classification number: B64F5/10 , B64C1/1484 , B64C2001/0072
Abstract: A method of manufacturing an aircraft window frame, the frame having a first surface that has at least first and second faces extending all around the frame and connected by a curved junction zone, the frame being made of a composite material that includes fibers embedded in a resin matrix. The method includes steps of: assembling fiber layers and at least one reinforcement situated at the level of the junction zone and having first and second peripheral edges; consolidating or polymerizing of the assembly; and removing the frame from the mold. During the step of assembling, a barrier layer is positioned between the reinforcement and the first surface to cover the reinforcement and to form a barrier limiting propagation of resin in the direction of the first surface. A window frame obtained by using that method is provided as well as an aircraft including the frame.
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37.发明授权公开(公告)号：US12012911B2
公开(公告)日：2024-06-18
申请号：US18129507
申请日：2023-03-31
Applicant: AIRBUS OPERATIONS (SAS)
Inventor： Lauren Davis , Christophe Bourdeau , Frédéric Chelin
IPC: F02K1/72
CPC classification number: F02K1/72
Abstract: A deflector for an ejection structure of a thrust reverser is disclosed including a deflector plate configured to act on an aerodynamic flow, the deflector plate having a concave upstream face, a convex downstream face, an inlet end, and an outlet end. The upstream face and the downstream face of the deflector plate have different curved profiles, the deflector has a particular profile giving it properties allowing it to act effectively on the aerodynamic flow so as to enhance the performance of the thrust reverser in which it is mounted.
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公开(公告)号：US20240169849A1
公开(公告)日：2024-05-23
申请号：US18501361
申请日：2023-11-03
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Mohamed-Habib ESSOUSSI , Didier FOURCADE , Olivier FALIPOU
CPC classification number: G08G5/025 , G08G5/0021 , G08G5/0086 , G08G5/045
Abstract: The avionics computer comprises a processing unit configured to compare the distance between a first position and a second position with a predetermined distance, the first position corresponding to the position of an initial anchor point of an initial terminal segment and the second position corresponding to the position of a landing threshold point of the runway, to check whether the initial terminal segment of the virtual path crosses the threshold of the runway and, if the distance between the first position and the second position is less than the predetermined distance and if the initial terminal segment of the virtual path crosses the threshold of the runway, to define the landing threshold point as an anchor point of a terminal segment of a virtual path for a non-precision FLS approach mode, the avionics computer thus making it possible to increase availability to implement FLS mode.
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公开(公告)号：US11984839B2
公开(公告)日：2024-05-14
申请号：US17713581
申请日：2022-04-05
Applicant: Airbus Operations SAS
Inventor： Jean-François Allias , Olivier Raspati
Abstract: A propulsive electric motor set for aircraft includes an electrical energy source and an electric motor provided with a drive shaft on which is mounted a propeller. The electric motor includes a first set of windings linked to the electrical energy source to provide a rotational drive function for the drive shaft. The electric motor further includes a second set of windings which, when the drive shaft is driven in rotation by an electric powering of the first set of windings, provides an electric generation function configured to supply non-propulsive loads of the aircraft. Thus, the non-propulsive loads of the aircraft can be electrically powered without any overload compromising the aerodynamics of the aircraft.
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公开(公告)号：US11981446B2
公开(公告)日：2024-05-14
申请号：US17878360
申请日：2022-08-01
Applicant: Airbus Operations SAS
Inventor： Umberto Gastaldi , Wolfgang Brochard , Olivier Pautis
Abstract: An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.
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