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公开(公告)号：US20240359789A1
公开(公告)日：2024-10-31
申请号：US18646050
申请日：2024-04-25
发明人： Alexei VICHNIAKOV
IPC分类号： B64C1/06
CPC分类号： B64C1/068
摘要： A fastener bracket configured to be installed on a holding structure. The fastener bracket is formed as a single piece comprising a plate portion and at least two pins protruding in parallel from a first surface of the plate portion. The at least two pins are at least partially made of a remoldable material. Also a fastener kit comprising such fastener bracket and at least one counter component. Moreover, an aircraft structure comprising at least one fastener bracket or fastener kit. Also an installation method of installing a fastener bracket.
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公开(公告)号：US20240294252A1
公开(公告)日：2024-09-05
申请号：US18663184
申请日：2024-05-14
IPC分类号： B64C29/02 , B64C1/00 , B64C1/06 , B64C3/10 , B64C3/16 , B64C11/28 , B64C27/08 , B64C27/12 , B64C27/50 , B64C29/00 , B64C39/00 , B64C39/02 , B64C39/06 , B64D27/02 , B64D27/24 , B64D31/00
CPC分类号： B64C29/02 , B64C1/068 , B64C3/10 , B64C3/16 , B64C11/28 , B64C27/08 , B64C27/12 , B64C27/50 , B64C29/0025 , B64C39/024 , B64C39/06 , B64C39/062 , B64D27/24 , B64D31/00 , B64C2001/0045 , B64C39/029 , B64D27/026
摘要： An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.
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公开(公告)号：US20240278910A1
公开(公告)日：2024-08-22
申请号：US18650650
申请日：2024-04-30
IPC分类号： B64C29/02 , B64C1/00 , B64C1/06 , B64C3/10 , B64C3/16 , B64C11/28 , B64C27/08 , B64C27/12 , B64C27/50 , B64C29/00 , B64C39/00 , B64C39/02 , B64C39/06 , B64D27/02 , B64D27/24 , B64D31/00
CPC分类号： B64C29/02 , B64C1/068 , B64C3/10 , B64C3/16 , B64C11/28 , B64C27/08 , B64C27/12 , B64C27/50 , B64C29/0025 , B64C39/024 , B64C39/06 , B64C39/062 , B64D27/24 , B64D31/00 , B64C2001/0045 , B64C39/029 , B64D27/026
摘要： The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.
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公开(公告)号：US12006037B2
公开(公告)日：2024-06-11
申请号：US18310198
申请日：2023-05-01
IPC分类号： B64C29/02 , B64C1/06 , B64C3/10 , B64C3/16 , B64C11/28 , B64C27/08 , B64C27/12 , B64C27/50 , B64C29/00 , B64C39/02 , B64C39/06 , B64D27/24 , B64D31/00 , B64C1/00 , B64C39/00 , B64D27/02
CPC分类号： B64C29/02 , B64C1/068 , B64C3/10 , B64C3/16 , B64C11/28 , B64C27/08 , B64C27/12 , B64C27/50 , B64C29/0025 , B64C39/024 , B64C39/06 , B64C39/062 , B64D27/24 , B64D31/00 , B64C2001/0045 , B64C39/029 , B64D27/026
摘要： An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.
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公开(公告)号：US20240043117A1
公开(公告)日：2024-02-08
申请号：US18310198
申请日：2023-05-01
IPC分类号： B64C39/06 , B64C11/28 , B64C27/50 , B64C3/16 , B64C3/10 , B64C27/08 , B64C29/00 , B64C27/12 , B64D27/24 , B64D31/00 , B64C29/02 , B64C1/06 , B64C39/02
CPC分类号： B64C39/062 , B64C11/28 , B64C27/50 , B64C3/16 , B64C3/10 , B64C27/08 , B64C29/0025 , B64C39/06 , B64C27/12 , B64D27/24 , B64D31/00 , B64C29/02 , B64C1/068 , B64C39/024 , B64C39/029
摘要： An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.
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公开(公告)号：US20240025562A1
公开(公告)日：2024-01-25
申请号：US18357808
申请日：2023-07-24
发明人： Jean-Marc DATAS , Thomas CARTEREAU , Jacques BOURIQUET , André AQUILA , Nicolas DARBONVILLE , Thomas AUTRET , Joël BARBOULE , Sébastien BAYONNE , Patrick GUERIN , Sjoerd VAN DER VEEN
IPC分类号： B64F5/10
摘要： An assembly platform configured to manipulate at least one aircraft lower shell without deforming it with a view to assembly of an aircraft fuselage barrel is disclosed including at least one rectangular chassis, at least two frames having an adjustable trim with respect to the rectangular chassis, at least two setting systems intended to adjust the trim of the frame and at least two cradles fixed onto the frames and intended to receive the lower shell and to hold the lower shell in a desired form. The cradles of the assembly platform make it possible to prevent a deformation of the lower shell during the assembly of the fuselage barrel.
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公开(公告)号：US11866201B2
公开(公告)日：2024-01-09
申请号：US17735426
申请日：2022-05-03
申请人： The Boeing Company
发明人： Santiago Mejia , Patrick James Macko , Byron James Autry , Paul Gabriel Werntges , Larry Scott Smotherman , David Raines , Sara Murphy
CPC分类号： B64F5/10 , B23P2700/01 , B64C1/061 , B64C1/068 , B64C1/12
摘要： A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.
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公开(公告)号：US11866200B2
公开(公告)日：2024-01-09
申请号：US17454285
申请日：2021-11-10
申请人： The Boeing Company
发明人： Daniel R. Smith , Darrell D. Jones
摘要： Systems and methods are provided for fabricating a fuselage of an aircraft. The method includes: disposing arcuate sections of fuselage at a track of a factory such that concavities of the arcuate sections of the fuselage face a floor of the factory, and bearing edges of the arcuate sections of fuselage directly contact the track; advancing the arcuate sections of fuselage synchronously along the track in a process direction; and performing work within concavities of the arcuate sections of fuselage during pauses between pulses of the arcuate section of fuselage via stations that are disposed beneath the concavities and that are directly mounted to the floor of the factory.
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公开(公告)号：US11780598B2
公开(公告)日：2023-10-10
申请号：US17694721
申请日：2022-03-15
发明人： Yuji Ishitsuka
摘要： An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.
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公开(公告)号：US20230303236A1
公开(公告)日：2023-09-28
申请号：US18185590
申请日：2023-03-17
发明人： Damien AGUERA , Salim CHALQI , Yannick LAMPURE
摘要： An aircraft having a systems cabinet positioned in an avionics bay to the rear of a landing gear compartment and connected to the fuselage by at least one lower connecting system. The systems cabinet and/or the lower connecting system comprises at least one longitudinal beam, which has a front end connected by a front connection to a wall separating the avionics bay and the landing gear compartment, the front connection comprising a sliding connection sliding in a direction substantially parallel to the longitudinal axis.
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