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公开(公告)号：US11993371B2
公开(公告)日：2024-05-28
申请号：US17530233
申请日：2021-11-18
申请人： The Boeing Company
发明人： Grzegorz G. Bogucki , Matthew J. Osborn , Art Ma , Saad Dawood
摘要： Methods, apparatus, systems and articles of manufacture are disclosed for overheat prevention of anti-ice systems for aircraft. An example aircraft includes a wing, a slat movably coupled to the wing, the slat having a compartment to receive heated bleed air, the slat including a panel, an opening formed in the panel, a door in the opening of the panel of the slat, an edge of the door hingeably coupled to the panel, the door movable between a closed position and an open position, and a latch coupled to the panel, the latch to hold the door in the closed position, the latch constructed of a thermally sensitive material such that when a temperature inside of the compartment reaches a threshold temperature, the latch releases the door to enable the door to move to the open position to vent the heated bleed air from the compartment.
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公开(公告)号：US11845536B2
公开(公告)日：2023-12-19
申请号：US17385603
申请日：2021-07-26
申请人： THE BOEING COMPANY
摘要： Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.
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公开(公告)号：US20230348043A1
公开(公告)日：2023-11-02
申请号：US17734178
申请日：2022-05-02
申请人： THE BOEING COMPANY
发明人： Ira Mitchell
摘要： A system and a method include a flight control surface, an actuator configured to control motion of the flight control surface, and a brake configured to engage at least a portion of the flight control surface in response to the flight control surface disengaging from the actuator. The brake arrests unrestrained motion of the flight control surface when the brake engages the at least a portion of the flight control surface.
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公开(公告)号：US11780559B1
公开(公告)日：2023-10-10
申请号：US17658375
申请日：2022-04-07
申请人： The Boeing Company
CPC分类号： B64C9/02 , B64C2009/143
摘要： An aerodynamic device includes a main aerodynamic body having a leading edge and a trailing edge, a flight control surface coupled to the main aerodynamic body near the trailing edge of the main aerodynamic body, and a translating body coupled to the flight control surface. The translating body is moveable relative to the flight control surface between a sealed position and a retracted position to define a gap. The translating body is extended toward the main aerodynamic body while in the sealed position to close the gap. The translating body is retracted away from the main aerodynamic body while in the retracted position to widen the gap. The gap adjusts an airflow flowing between the main aerodynamic body and the flight control surface.
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公开(公告)号：US20220089277A1
公开(公告)日：2022-03-24
申请号：US17451289
申请日：2021-10-18
发明人： Neil John LYONS , Ben COMMIS
摘要： A method of retrofitting a wing of a fixed wing aircraft is disclosed including the steps of providing an existing aircraft wing with a main fixed wing portion, and the main fixed wing portion having a tip end and an existing movable flight control surface connected adjacent the tip end. The existing movable flight control surface is then removed from the main fixed wing portion, and a wing tip device and movable flight control surface are selected as a pair to replace the existing movable flight control surface, with the selected movable flight control surface having an aerodynamic surface of different shape to the shape of the flight control surface removed from the wing. The selected wing tip device and movable flight control surface are then fitted to the main fixed wing portion.
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公开(公告)号：US11192631B2
公开(公告)日：2021-12-07
申请号：US16442726
申请日：2019-06-17
发明人： Bernhard Schlipf , Florian Lorenz , Dennis Krey
摘要： A C-shaped connection assembly transmits loads in a load plane between a first and a second wing element. The connection assembly comprises a first and a second L-shaped load-bearing device. Each load-bearing device comprises a joint region and two legs extending parallel to the load plane and away from the joint region towards respective end regions. One leg of the first load-bearing device extends parallel to one leg of the second load bearing device. These legs are connected to one another. Two coupling portions which connect the connection assembly to the second wing element are formed in the respective joint regions of the load-bearing devices. Two further coupling portions which connect the connection assembly to the first wing element are formed in respective free end region of the load-bearing device and the joint region of the second load-bearing device.
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公开(公告)号：US11155329B2
公开(公告)日：2021-10-26
申请号：US16447143
申请日：2019-06-20
申请人： Bombardier Inc.
发明人： Farzad Mokhtarian
摘要： A variable camber system for an aircraft wing including a wing bracket extending downward from a wing, a flap bracket pivotably coupled to the wing bracket, and a flap pivotably coupled to the flap bracket such that the flap pivots around an axis of rotation through the flap. The variable camber system is configured to adjust position of both the flap and the flap bracket relative to the wing while maintaining position of the flap relative to the flap bracket. The variable camber system is also configured to adjust position of the flap relative to the flap bracket.
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公开(公告)号：US10926865B2
公开(公告)日：2021-02-23
申请号：US16216769
申请日：2018-12-11
申请人： THE BOEING COMPANY
发明人： Kevin Tsai , Donald Drew Reinhart
摘要： A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.
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公开(公告)号：US20190389558A1
公开(公告)日：2019-12-26
申请号：US16447143
申请日：2019-06-20
申请人： Bombardier Inc.
发明人： Farzad Mokhtarian
摘要： A variable camber system for an aircraft wing including a wing bracket extending downward from a wing, a flap bracket pivotably coupled to the wing bracket, and a flap pivotably coupled to the flap bracket such that the flap pivots around an axis of rotation through the flap. The variable camber system is configured to adjust position of both the flap and the flap bracket relative to the wing while maintaining position of the flap relative to the flap bracket. The variable camber system is also configured to adjust position of the flap relative to the flap bracket.
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公开(公告)号：US10480653B2
公开(公告)日：2019-11-19
申请号：US15379465
申请日：2016-12-14
发明人： Paul Blades
摘要： A seal is disclosed for a wing for providing an aerodynamic seal between a fixed aerofoil and a movable control surface.
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