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公开(公告)号：US20240286732A1
公开(公告)日：2024-08-29
申请号：US18588545
申请日：2024-02-27
Applicant: Airbus Operations GmbH
Inventor： Bernhard SCHLIPF , Christoph WINKELMANN
IPC: B64C9/20
CPC classification number: B64C9/20
Abstract: A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly having a flap, and a connection assembly movably connecting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly includes a support element that is mounted to the flap and that is movably mounted to the main wing, such that the support element is movable relative to the main wing along a predefined path between a stowed position and a deployed position. The support element is formed as an elongate support beam that extends along a beam longitudinal axis between a front end and a rear end and has an intermediate portion between the front and rear ends.
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公开(公告)号：US11993376B2
公开(公告)日：2024-05-28
申请号：US17703653
申请日：2022-03-24
Applicant: Airbus Operations Ltd.
Inventor： William Tulloch
Abstract: A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.
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公开(公告)号：US11897611B2
公开(公告)日：2024-02-13
申请号：US17408019
申请日：2021-08-20
Applicant: The Boeing Company
Inventor： Neal V. Huynh
CPC classification number: B64C9/20 , B64C13/42 , B64C13/504 , B64C13/505
Abstract: Distributed trailing edge actuation systems and methods for aircraft are described herein. An example aircraft includes a wing, a flap coupled to the wing, the flap movable between a stowed position and a deployed position, and a distributed trailing edge (DTE) actuation system including a flap actuator coupled to the wing to move the flap. The flap actuator includes an integrated hydraulic powered actuator and electric powered actuator. The flap actuator is operable in a hydraulic powered mode in which the hydraulic powered actuator is activated to move the flap, an electric powered mode in which the electric powered actuator is activated to move the flap, and a hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap.
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4.发明公开公开(公告)号：US20240002038A1
公开(公告)日：2024-01-04
申请号：US17856794
申请日：2022-07-01
Applicant: The Boeing Company
Inventor： Kevin Raylin Tsai
Abstract: Wing assemblies (100) comprise an inboard flight control surface (102), an outboard flight control surface (104) positioned directly adjacent to and outboard of the inboard flight control surface (102), and a dual actuation assembly (106) coupled directly to and forming a linkage between the inboard flight control surface (102) and the outboard flight control surface (104). The dual actuation assembly (106) is configured to selectively transition the inboard flight control surface (102) and the outboard flight control surface (104), in tandem, amongst a retracted configuration (108) and a range of extended configurations (110).
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公开(公告)号：US20230322357A1
公开(公告)日：2023-10-12
申请号：US17658374
申请日：2022-04-07
Applicant: The Boeing Company
Inventor： Andrew J. Hubbard , Richard C. Potter
CPC classification number: B64C9/02 , B64C2009/005 , B64C9/20
Abstract: 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 rotating body coupled to the flight control surface. The rotating body is rotatable relative to the flight control surface between a stowed position and a deployed position to define a gap. The rotating body is rotated toward the main aerodynamic body while in the stowed position to close the gap. The rotating body is rotated away from the main aerodynamic body while in the deployed 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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Patent Agency Ranking
公开(公告)号：US20230271696A1
公开(公告)日：2023-08-31
申请号：US18173886
申请日：2023-02-24
Applicant: Airbus Operations GmbH
Inventor： Luc ANDREANI , Dennis KREY
CPC classification number: B64C13/28 , B64C9/20 , B64C13/0425
Abstract: A wing for an aircraft. The wing includes a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing. The trailing edge high lift assembly includes a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly is configured such that the flap is movable relative to the main wing in a linear and/or rotational manner. The connection assembly is configured such that the flap is movable relative to the main wing in a decoupled linear and rotational manner.
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公开(公告)号：US11673646B2
公开(公告)日：2023-06-13
申请号：US17526884
申请日：2021-11-15
Applicant: The Boeing Company
Inventor： Neal V. Huynh
Abstract: An example aircraft disclosed herein includes a wing, a spoiler rotatably coupled to the wing, the spoiler movable between a cruise position and an upward position and between the cruise position and a droop position, and a spoiler actuation system coupled to a hydraulic system of the aircraft, the spoiler actuation system including a first piston and a second piston, a rack coupled between the first piston and the second piston, the rack movable between a first position and a second position, a pinion coupled to the rack, the pinion to rotate between a third position and a fourth position when the rack moves between the first position and the second position, a first crank arm coupled to the pinion, the first crank arm to rotate with the pinion between the third position and the fourth position, and a second crank arm coupled to the first crank arm and to the spoiler, the second crank arm to move the spoiler between the cruise position and the upward position when the first crank arm rotates between the third position and the fourth position.
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公开(公告)号：US11673643B2
公开(公告)日：2023-06-13
申请号：US16062973
申请日：2017-03-23
Applicant: JP AEROSPACE GROUP, INC.
Inventor： John K. Markley , Jason Russell , Paul Bartlett
IPC: B64C1/00 , B64C5/02 , B64C39/04 , B64C9/20 , B64C3/50 , B64C3/14 , B64C5/06 , B64C25/00 , B64C9/00
CPC classification number: B64C1/0009 , B64C3/14 , B64C3/50 , B64C5/02 , B64C5/06 , B64C9/20 , B64C39/04 , B64C2001/0045 , B64C2009/005 , B64C2025/003
Abstract: A low stall or minimum control speed aircraft comprising a fuselage that has vertically flat sides; wings with high a lift airfoil profile of constant chord section set at zero degree planform sweep, twin booms having inner vertically flat surfaces, twin vertical stabilizers, a flying horizontal stabilizer; preferably twin engines having propellers and wherein each engine preferably has a thrust-line that is inclined nose-up to a maximum of +8 degrees, and is parallel to the wing chord underneath wing mounts and landing gear doors that provide surfaces for channeling propeller wash in a rearward direction; all working in concert so that the airplane has an extremely low stall speed and minimum control speed. The engines may be diesel, hydrogen fuel cell, electric fuel cell, diesel-electric, gas turbine or combinations thereof. The propellers may be counter-rotating.
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公开(公告)号：US20220324549A1
公开(公告)日：2022-10-13
申请号：US17526884
申请日：2021-11-15
Applicant: The Boeing Company
Inventor： Neal V. Huynh
Abstract: An example aircraft disclosed herein includes a wing, a spoiler rotatably coupled to the wing, the spoiler movable between a cruise position and an upward position and between the cruise position and a droop position, and a spoiler actuation system coupled to a hydraulic system of the aircraft, the spoiler actuation system including a first piston and a second piston, a rack coupled between the first piston and the second piston, the rack movable between a first position and a second position, a pinion coupled to the rack, the pinion to rotate between a third position and a fourth position when the rack moves between the first position and the second position, a first crank arm coupled to the pinion, the first crank arm to rotate with the pinion between the third position and the fourth position, and a second crank arm coupled to the first crank arm and to the spoiler, the second crank arm to move the spoiler between the cruise position and the upward position when the first crank arm rotates between the third position and the fourth position.
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公开(公告)号：US20220306282A1
公开(公告)日：2022-09-29
申请号：US17703653
申请日：2022-03-24
Applicant: Airbus Operations Ltd.
Inventor： William Tulloch
Abstract: A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.
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