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71.发明公开
公开(公告)号：EP4275872A1
公开(公告)日：2023-11-15
申请号：EP23153964.4
申请日：2023-01-30
申请人： The Boeing Company
摘要： A rotating manifold (100) includes an axle (154), a hub (110) rotatable relative to the axle (154) about an axis of rotation (A) and a compressed air line (116) in fluid communication housed in the axle (154). The rotating manifold further includes a vacuum line (150) in fluid communication with the hub (110). The rotating manifold further includes a plurality of conduits (118) connected to the hub (110). Each conduit (118') of the plurality of conduits (118) is in fluid communication with the vacuum line (150) and houses a compressed air line arm (116') in fluid communication with the compressed air line (116).
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公开(公告)号：EP4270361A1
公开(公告)日：2023-11-01
申请号：EP22382402.0
申请日：2022-04-27
申请人： The Boeing Company
IPC分类号： G08G5/00
摘要： A device includes one or more processors configured to receive an indication that a geographical area is expected to be regulated during a particular time window. The one or more processors are also configured to perform a comparison of the geographical area to route segments of a filed flight plan of a flight of an aircraft. The one or more processors are further configured to, based on determining that a route segment of the filed flight plan traverses at least a portion of the geographical area during the particular time window, determine alternate flight plans that do not traverse the geographical area during the particular time window. The one or more processors are also configured to select one of the alternate flight plans that satisfies a selection criterion as an updated flight plan of the flight. The one or more processors are further configured to send the updated flight plan to a second device.
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公开(公告)号：EP4269107A1
公开(公告)日：2023-11-01
申请号：EP23181972.3
申请日：2020-11-20
申请人： The Boeing Company
发明人： Sahu, Megha , Prakash, Om
IPC分类号： B33Y30/00 , B29C64/118 , B29C64/209 , B33Y70/00 , C08K3/04 , C08K5/09 , C08L71/00
摘要： A material, an additively manufactured article, and a process for additive manufacture of an article comprises conveying a material through a heated nozzle to form a flowing mass of the material. The material comprises a polymer matrix including a plurality of polymeric chains and an alignment additive dispersible within the polymer matrix. The alignment additive is configured to align the plurality of polymeric chains in a flow direction of the flowing mass of the material. The process further comprises aligning at least a portion of the polymeric chains, via the alignment additive, along a direction of flow through the heated nozzle, releasing the flowing mass of the material from the heated nozzle, and allowing the material to solidify.
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74.发明公开
公开(公告)号：EP4261782A3
公开(公告)日：2023-11-01
申请号：EP23162252.3
申请日：2023-03-16
申请人： The Boeing Company
发明人： AFRASIABI, Amir , EVANS, Nick S.
IPC分类号： G06T7/70
摘要： Certain aspects of the present disclosure provide techniques for autonomous image acquisition. This includes determining a plurality of two-dimensional image perspectives for a plurality of image capture devices, and comparing the plurality of two-dimensional image perspectives with a generated two-dimensional representation of a target object, where the two-dimensional representation is generated based on a three-dimensional model of the target object. This further includes automatically moving at least one of the plurality of image capture devices, based on the comparing, to increase a portion of the target object captured by the plurality of image capture devices.
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75.发明公开
公开(公告)号：EP4234394A3
公开(公告)日：2023-11-01
申请号：EP23173640.6
申请日：2020-04-29
申请人： The Boeing Company
IPC分类号： B64C11/26 , B64C3/18 , B64C1/06 , B64C27/473 , B64C1/00 , B29D99/00 , B29C48/12 , B29C48/345
摘要： A method for fabricating a composite wing structural component for an aircraft is described. The method comprises extruding a filler material into each mold channel of a plurality of mold channels of a die to form a plurality of filler segments, removing the plurality of filler segments from the plurality of mold channels of the die, and arranging the plurality of filler segments in a space in the composite structural component, the space being defined by a radius of the composite structural component, such that the filler segments are in end-to-end contact. The method further comprises curing the plurality of filler segments in the space to fuse the plurality of filler segments.
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公开(公告)号：EP4261805A1
公开(公告)日：2023-10-18
申请号：EP22382357.6
申请日：2022-04-14
申请人： The Boeing Company
发明人： LA CIVITA, Marco
IPC分类号： G08G5/00
摘要： A method of generating an estimated initial mass of an aircraft includes obtaining a first sequence of instructions indicating aircraft intent for a particular phase of a flight. The first sequence of instructions includes multiple sequential tabular instructions for a set of segments of the particular phase, and operation of the aircraft according to the first sequence of instructions would result in a particular altitude profile during the particular phase. The method includes determining, using a bounded optimization operation, a first estimated mass of the aircraft and a throttle law instruction that, together, result in the particular altitude profile over a group of the segments. The method includes generating a second sequence of instructions that replaces the tabular instructions for the group of the segments with the throttle law instruction. The method also includes determining the estimated initial mass at least partially based on the first estimated mass.
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公开(公告)号：EP4261647A2
公开(公告)日：2023-10-18
申请号：EP23165676.0
申请日：2023-03-30
申请人： The Boeing Company
IPC分类号： G05D1/10
摘要： A method of guidance for an aircraft includes obtaining relative position data indicative of a direction from a location of the aircraft to a location of a moving target point. The method also includes determining, based on the relative position data, a location of a virtual leader based on projecting the location of the aircraft onto a virtual leader path, where the virtual leader path corresponds to a straight approach path to the location of the moving target point along a desired approach direction. The method further includes determining, based on the location of the virtual leader, a guidance input to cause the aircraft to follow the virtual leader.
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公开(公告)号：EP4261134A1
公开(公告)日：2023-10-18
申请号：EP23167184.3
申请日：2023-04-07
申请人： The Boeing Company
摘要： An engine attachment system includes a strut box. The strut box includes a longitudinal axis, a forward portion that extends along the longitudinal axis, and an aft portion that extends from the forward portion along the longitudinal axis. The engine attachment system includes a forward attachment apparatus that is coupled to the forward portion of the strut box and that is coupleable to a forward spar of the wing. The engine attachment system includes an aft attachment apparatus that is coupled to the aft portion of the strut box and that is coupleable to an aft spar of the wing. When the strut box is coupled to the wing by the forward attachment apparatus and the aft attachment apparatus, the aft portion of the strut box is positioned under the wing. The strut box is coupleable to an engine.
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公开(公告)号：EP4261133A1
公开(公告)日：2023-10-18
申请号：EP23164644.9
申请日：2023-03-28
申请人： The Boeing Company
摘要： A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector. The control unit is configured to receive the first icing signal from the first icing detector and the second icing signal from the second icing detector. The control unit is further configured to distinguish between presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.
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公开(公告)号：EP4235810A3
公开(公告)日：2023-10-18
申请号：EP23178386.1
申请日：2017-09-14
申请人： The Boeing Company
发明人： Rehder, Eric
IPC分类号： H01L31/05 , H01L31/02 , H01L31/054 , H01L31/0352 , H01L31/048 , H01L31/0687 , H01L31/044 , H01L31/041 , H01L31/042
摘要： A substrate for solar cells is configured such that an area of the substrate remains exposed when at least one solar cell having at least one cropped corner that defines a corner region is attached to the substrate, one or more electrical connections for the solar cell are made in the corner region resulting from the cropped corner of the solar cell, and at least one of the electrical connections, connecting a first interconnect in a first location, is repaired by connecting a second interconnect in a second location in the at least one of the electrical connections different from the first location.
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