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公开(公告)号：EP4459530A1
公开(公告)日：2024-11-06
申请号：EP24170359.4
申请日：2024-04-15
申请人： The Boeing Company
摘要： A method for computerized aircraft fault isolation includes, at a computing device, receiving a current maintenance-related pattern that includes a set of one or more digital maintenance messages reported during a flight of an aircraft. The current maintenance-related pattern is compared to a digital maintenance records database that includes a plurality of historical maintenance-related patterns observed during prior aircraft flights, each associated with an indication of one or more aircraft parts that, when replaced, resolved an underlying fault corresponding to the historical maintenance-related pattern. Based on an adaptive similarity threshold, a selected set of historical maintenance-related patterns are computer-identified as corresponding to the current maintenance-related pattern. A selected aircraft part associated with the selected set of historical maintenance-related patterns is computer-identified as a candidate for replacement on the aircraft to address the current maintenance-related pattern.
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公开(公告)号：EP4442929A1
公开(公告)日：2024-10-09
申请号：EP24159660.0
申请日：2024-02-26
申请人： The Boeing Company
CPC分类号： E04G5/14 , E04G21/3219 , E04G1/18 , B64F5/40 , B64F5/60
摘要： A system and a method include a cam locking assembly including a support rod having a rod body that extends along an axis, a first rail component having a rail body that extends along the axis and coupled with the support rod and a third rail component, a cam having an interior passage extending along the axis that receives a portion of the support rod and an exterior surface having plural recesses, and guide pins that extend into the plural recesses of the cam and control movement of the cam. Movement of the cam controls movement of the third rail component between a loaded position and an unloaded position.
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公开(公告)号：EP4410683A1
公开(公告)日：2024-08-07
申请号：EP23305125.9
申请日：2023-01-31
申请人： Airbus SAS
CPC分类号： B64D45/0005 , G06N20/00 , B64C25/00 , B64F5/40
摘要： A method for providing an operational state of a monitored landing gear of an aircraft comprises : obtaining (501) in real-time captured signals, such as images, of an actual position of the monitored landing gear; transforming (502) the captured signals in a descriptor vector using Principal Components Analysis; injecting (503) the descriptor vector in a machine learning-based model trained and configured to transform descriptor vectors into equivalent operational states of landing gears; and providing (504) the operational state of the monitored landing gear to avionics of the aircraft. Thus, a quantity of sensors used to monitor landing gears of aircrafts is reduced.
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公开(公告)号：EP4404115A1
公开(公告)日：2024-07-24
申请号：EP23220305.9
申请日：2023-12-27
申请人： The Boeing Company
发明人： PAUL, RANJAN K. , IRVAHN, JAN , DEITS, CHRISTOPHER D. , STURLAUGSON, LIESSMAN E. , KAMAT, AMEYA DEEPAK
CPC分类号： G06Q10/20 , G06Q10/06 , B64F5/40 , G05B23/0283 , G06Q50/40 , G05B23/024
摘要： An example method (300) performed by a computing system (100) for determining a maintenance interval (102) for a subject aircraft configuration (104) comprises obtaining sensor data (150) reported by an electronic system (144) of a population (140) of the subject aircraft configuration (104). The method (300) further comprises obtaining a failure mode definition (172) that identifies a set of failure modes (210) involving a component (221) of the subject aircraft configuration (104). The method (300) further comprises implementing a first predictive model (120, 122, 124) to determine a first lifetime-probability distribution (261) of a failure mode (211, 212, 213) involving the component (221) based on the sensor data (150). The method (300) further comprises implementing a second predictive model (120, 122, 124) that differs from the first predictive model (120, 122, 124) to determine a second lifetime-probability distribution (262) of a failure mode (211, 212, 213) involving the component (221) based on the sensor data (150). The method (300) further comprises determining a maintenance interval (102) for the component (221) based on the first lifetime-probability distribution (261) and the second lifetime-probability distribution (262).
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公开(公告)号：EP4393822A1
公开(公告)日：2024-07-03
申请号：EP22217306.4
申请日：2022-12-30
发明人： Lohmar, Jens
摘要： Die Erfindung betrifft ein Verfahren zur Nutzung eines Luftverteilungssystems in einem Flugzeugrumpf, mit den folgenden Verfahrensschritten: Bereitstellen 100 eines Luftverteilungssystems, das einen Luftverteilungsstrang umfasst, der zumindest teilweise aus einem fluiddichten und flexiblen Material gebildet ist, wobei der Luftverteilungsstrang, von einem ersten Zustand, in dem das flexible Material im Wesentlichen straff ist, in einen zweiten Zustand, in dem das flexible Material im Wesentlichen schlaff ist, wechseln kann, Anordnen 110 des Luftverteilungsstrangs an einem Einsatzort in dem Flugzeugrumpf, Einnehmen 120 des ersten Zustands des Luftverteilungsstrangs um das Luftverteilungssystem zu betreiben, oder Einnehmen 130 des zweiten Zustands des Luftverteilungsstrangs um einen räumlichen Bereich in der Nähe des Einsatzorts zu warten.
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公开(公告)号：EP4349719A1
公开(公告)日：2024-04-10
申请号：EP22199966.7
申请日：2022-10-06
IPC分类号： B64F5/40
摘要： Systems and methods for determining an operation time of an aircraft are described. The method includes the following steps: identifying (210) direct damage information on a surface of a metallic component (12) of an aircraft, wherein the direct damage information include a dimension of a damage area, an absolute position of the damage area on the aircraft, and a relative position of the damage area with regard to fasteners and/or other design features of the aircraft; determining (220) a knock-down-factor of the metallic component based on a database that includes an assignment of direct damage information and fatigue performance of the metallic component; determining (230) an operation time for the aircraft based on the knock-down-factor.
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公开(公告)号：EP3810372B1
公开(公告)日：2024-03-13
申请号：EP19735006.9
申请日：2019-06-13
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8.发明公开
公开(公告)号：EP4331990A1
公开(公告)日：2024-03-06
申请号：EP22192704.9
申请日：2022-08-29
发明人： Albers, Frederik , Müller, Hannes , Schneider, Frank , Rempe, Michael , Lübbert, Tim , Schreiner, Axel
摘要： The present invention relates to a method for operating an on-board water supply and distribution system of an aircraft for supplying water, the system comprising a central water (7) tank, a plurality of consumer assemblies (5), each consumer assembly (5) comprising a supply device and a buffer tank (37), a pump (21) being configured such that it may operate in a supply mode and a reverse mode, a filter device (23), and a high pressure conduit system (29), wherein the central water tank (7) is connected to the upstream side (25) of the pump (21) with the filter device (23) being arranged between the central water tank (7) and the upstream side (25), wherein the high pressure conduit system connects the downstream side (27) with the plurality of consumer assemblies (5), with the conduit system (29) being configured such that the pump (21), when operating in the supply mode, is capable of delivering water from the downstream side (27) to the buffer tank (37) of each of the consumer assemblies (5), wherein, when the pump (21) is operating in the reverse mode, it is capable of conveying water from the downstream side (27) to the upstream side (25), the method comprising the following steps: operating the pump (21) in the supply mode so that water from the central tank (7) is delivered to at least one of the consumer assemblies (5) in a first time interval wherein the buffer tank (37) of the at least one consumer assembly (5) is filled, and operating the pump (21) in the reverse mode in a second time interval so that water from the buffer tank (37) of the at least one of the consumer assemblies (5) passes through the filter device (23).
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公开(公告)号：EP3369661B1
公开(公告)日：2023-11-15
申请号：EP18158096.0
申请日：2018-02-22
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公开(公告)号：EP3694780B1
公开(公告)日：2023-04-12
申请号：EP18866117.7
申请日：2018-10-10
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