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公开(公告)号：US11738857B2
公开(公告)日：2023-08-29
申请号：US17871892
申请日：2022-07-22
发明人： Ben Commis , Christopher Wright
CPC分类号： B64C23/069 , B64C7/00
摘要： A wing tip device having a first wing tip device element for attaching at a first wing tip device element root to a tip of an aircraft wing, and a second wing tip device element extending from a second wing tip device element root to a second wing tip device element tip, the second wing tip device element root outboard, when viewed in the wing planform direction, of the first wing tip device element root; the first wing tip device element having a first wing tip device element leading edge and a first wing tip device element trailing edge, and the second wing tip device element having a second wing tip device element leading edge and a second wing tip device element trailing edge; and a fairing between the first and second wing tip device element which extends aft from the second wing tip device element trailing edge.
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公开(公告)号：US20230258525A1
公开(公告)日：2023-08-17
申请号：US18167596
申请日：2023-02-10
CPC分类号： G01M3/28 , G01M5/0025
摘要： A method of testing a pipe system with a testing apparatus is disclosed including a container, a cooling chamber in the container, and a cold head in the cooling chamber. The method includes loading the pipe system into the container; cooling a fluid, such as Helium gas, in the cooling chamber with the cold head to generate a cooled fluid; feeding the cooled fluid into the pipe system in the container; and taking a test measurement of the pipe system containing the cooled fluid.
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公开(公告)号：US20230258238A1
公开(公告)日：2023-08-17
申请号：US18105622
申请日：2023-02-03
发明人： Kevin HOGG
CPC分类号： F16D65/0031 , B64C25/42
摘要： An aircraft landing gear assembly 1 includes a wheel 10, a disc brake 20 comprising one or more discs 21, 22 and a filter 30. The disc brake is operable to inhibit rotation of wheel 10 during a braking event thereby resulting in the formation of brake dust from the one or more discs 21, 22. The filter 30 is positioned relative to the disc brake 20 such that air flows over the one or more discs 21,22, through the filter 30 and away from the assembly 1, wherein the filter 30 is configured to separate and remove at least part of the brake dust from the air and while allowing the air to pass.
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公开(公告)号：US20230257101A1
公开(公告)日：2023-08-17
申请号：US18109672
申请日：2023-02-14
IPC分类号： B64C3/34
CPC分类号： B64C3/34
摘要： A fuel tank is disclosed including a lower cover and an upper cover. The lower cover or the upper cover includes a panel assembly. The panel assembly includes a panel and a stringer attached to the panel. The stringer includes a pair of portions which are spaced apart in a lengthwise direction of the stringer and connected to each other by a bridge. Each portion is connected to a respective end of the bridge, and each end of the bridge deviates away from the panel. The stringer includes reinforcement fibres which extend between the portions via the bridge. Each reinforcement fibre deviates away from the panel at each end of the bridge. The stringer includes a stringer recess between the bridge and the panel, and a flow passage in the stringer recess through which fluid can flow across the stringer.
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公开(公告)号：US20230219696A1
公开(公告)日：2023-07-13
申请号：US18096473
申请日：2023-01-12
发明人： Sam THOMPSON
IPC分类号： B64D45/02 , B32B5/02 , B32B15/14 , B32B3/06 , B32B15/02 , B32B15/20 , B32B15/04 , B32B5/26 , B64F5/10
CPC分类号： B64D45/02 , B32B5/02 , B32B15/14 , B32B3/06 , B32B15/02 , B32B15/20 , B32B15/043 , B32B5/26 , B64F5/10 , B32B2605/18 , B32B2260/023 , B32B2260/046 , B32B2307/202 , B32B2262/101 , B32B2262/106 , B29C70/68
摘要： A lightning strike protection layer for an aircraft is disclosed having a first portion and a second portion, the first portion includes a first fibre reinforced polymer composite layer and a first electrically conductive metal layer and the second portion includes a second fibre reinforced polymer composite layer and a second electrically conductive metal layer, and the first and second portions are joined at a butt joint, with the first and second fibre reinforced polymer composite layers abutting and the first and second electrically conductive metal layers abutting; and a butt-strap extending across the butt joint, the butt-strap comprising a third electrically conductive metal layer electrically connected to the first and second electrically conductive metal layers.
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公开(公告)号：US20230174217A1
公开(公告)日：2023-06-08
申请号：US17952900
申请日：2022-09-26
发明人： German IBANEZ-GIL
IPC分类号： B64C3/28
CPC分类号： B64C3/28
摘要： A kit of parts for forming an aerofoil assembly is disclosed having a torsion box structure including a first attachment point and a second attachment point, the first and second attachment points being separated from each other along a separation axis, and a fixed leading or trailing edge structure including corresponding first and second attachment points, wherein a first structure includes a slidebly mounted abutment piece slideable along a slide path extending in a direction parallel to the separation axis and a fixing mechanism for fixing the slidebly mounted abutment piece. A second structure includes a corresponding abutment feature having a first abutment surface facing in a direction parallel to the separation axis of the second structure, such that, in use, the abutment piece prevents relative movement of the first and second structures.
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公开(公告)号：US20230166831A1
公开(公告)日：2023-06-01
申请号：US17993176
申请日：2022-11-23
发明人： Daren HEALY
CPC分类号： B64C13/38 , B64C9/10 , B64C1/0009 , B64C21/08
摘要： An aerodynamic control surface assembly includes a structure (2) with an aerodynamic surface (8) and a curved aerodynamic control surface (20) configured to move between an extended (24) and a retracted position (22). The aerodynamic control surface is arranged to deploy through an aperture (18) in the aerodynamic surface and into an oncoming airflow (A). An actuation mechanism (52, 152, 252) coupled to the aerodynamic control surface (20) moves the aerodynamic control surface (20) between extended and retracted positions. The actuation mechanism (52, 152, 252) is configured such that the control surface (20) follows a curved kinematic path (40, 140, 240) as the control surface moves between the extended (24) and retracted positions (22). The actuation mechanism (52, 152, 252) remains fully behind the aerodynamic surface (8) throughout the movement of the aerodynamic control surface (20) between the extended (24) and retracted positions (22).
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公开(公告)号：US20230142588A1
公开(公告)日：2023-05-11
申请号：US17982301
申请日：2022-11-07
IPC分类号： B64C3/18
CPC分类号： B64C3/182
摘要： A stiffener is disclosed including a core and a shell which surrounds the core. The shell is formed from a fibre material, and the core includes first and second battens arranged side by side, and a foam spacer between the battens. The stiffener extends in a lengthwise direction, and the battens and the foam spacer have respective lengths which extend in the lengthwise direction of the stiffener. The core is assembled with the spacer between the battens, then surrounded with the shell. The stiffener may be a stringer for an aircraft wing.
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公开(公告)号：US20230131385A1
公开(公告)日：2023-04-27
申请号：US17970218
申请日：2022-10-20
发明人： Steven Paul SMITH
IPC分类号： B64F5/60
摘要： An emulator configured to emulate an automated aircraft assembly jig supporting an aircraft assembly is disclosed. The emulator connectable to an automated equipment module and configured to: send a first signal to an automated equipment module, wherein the first signal is representative of a communication to the automated equipment module; and receive a second signal from the automated equipment module representative of a communication from the automated equipment module, wherein the automated equipment module is arranged to operate autonomously on an aircraft assembly.
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50.发明申请公开(公告)号：US20230099541A1
公开(公告)日：2023-03-30
申请号：US17954196
申请日：2022-09-27
发明人： Ting Yu AU
摘要： A method of determining the position of one or more components of a landing gear assembly of an aircraft is disclosed including scanning the one or more components with a lidar system to generate a set of position data points, each position data point comprising a set of three orthogonal position values. The position data points are partitioned into one or more clusters using a distance metric. Each cluster is determined to represent a component of the landing gear assembly. The position of the components are then determined from the position data points in the clusters. The value of the distance metric for a first position data point and a second position data point is representative of the difference between a first position value of the three orthogonal position values of the first position data point and the corresponding first position value of the three orthogonal position values of the second position data point.
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