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公开(公告)号：US20240326982A1
公开(公告)日：2024-10-03
申请号：US18193518
申请日：2023-03-30
Applicant: The Boeing Company
Inventor： Kevin R. Tsai , Ramón A. Burin
Abstract: Aircraft assemblies comprise an aerostructure, a sealing structure, and a flexure spring. The aerostructure comprises an end surface. The flexure spring is operably coupled between the aerostructure and the sealing structure and is configured to urge the sealing structure away from the end surface of the aerostructure. The flexure spring has a neutral configuration and a range of deflected configurations. The flexure spring is biased toward the neutral configuration.
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公开(公告)号：US12043386B2
公开(公告)日：2024-07-23
申请号：US17967766
申请日：2022-10-17
Applicant: The Boeing Company
Inventor： Kevin R. Tsai
Abstract: Wing assemblies (100) comprise one or more wing support structures (24), an inboard-most flap (32), one or more flap supports (28) that operatively couple the inboard-most flap (32) to the one or more wing support structures (24), and one or more flap actuators (31) configured to operatively move the inboard-most flap (32) relative to the one or more flap supports (28). The flap support(s) (28) comprise at least an inboard-most inboard-flap support (106), the flap actuator(s) (31) comprise at least an inboard-most inboard-flap actuator (108) that is outboard of the inboard edge (102) of the inboard-most flap (32), and the inboard-most inboard-flap actuator (108) is spaced-away from the inboard-most inboard-flap support (106).
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公开(公告)号：US20240140589A1
公开(公告)日：2024-05-02
申请号：US17979425
申请日：2022-11-02
Applicant: The Boeing Company
Inventor： Kevin R. Tsai , Tu Q. Vo
Abstract: Wing assemblies comprise one or more wing support structures, an inboard-most flap, and one or more flap supports that operatively couple the inboard-most flap to the wing support structure(s). The flap support(s) comprise at least an inboard-most inboard-flap support that is outboard of the inboard edge of the inboard-most flap.
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4.发明授权公开(公告)号：US11873094B2
公开(公告)日：2024-01-16
申请号：US17661588
申请日：2022-05-02
Applicant: The Boeing Company
Inventor： Kevin R. Tsai
Abstract: A hinge mechanism for hingedly coupling a flight control member having a top surface to an aircraft component having a top surface includes a first hinge member pivotably coupled to the flight control member about a first axis and slidingly coupled to the aircraft component and a second hinge member pivotably coupled to the aircraft component about a second axis and slidingly coupled to the flight control member. The first hinge member is pivotably coupled to the second hinge member about a central axis. The first hinge member and the second hinge member are configured to cooperatively facilitate movement the flight control member relative to the aircraft component between at least a stowed position and a deployed position.
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公开(公告)号：US11427301B2
公开(公告)日：2022-08-30
申请号：US16900630
申请日：2020-06-12
Applicant: The Boeing Company
Inventor： Kevin R. Tsai
Abstract: A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted at a fixed rotational axis and has a pair of flanges, each flange having an aperture, and a channel extending aft from the pair of flanges. A fuse pin is received through the aperture in each flange. A coupler link is attached to an actuator at a first end and pivotally engaged to the carrier beam by the fuse pin. Extension of the coupler link by the actuator rotates the carrier beam from a stowed position to a deployed position. Responsive to a moment induced on the flap and carrier beam by a ground contact load, the fuse pin is frangible to shear releasing the coupler link to translate into the channel.
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Patent Agency Ranking
公开(公告)号：US11312474B2
公开(公告)日：2022-04-26
申请号：US16441426
申请日：2019-06-14
Applicant: The Boeing Company
Inventor： Kevin R. Tsai , Miranda Peterson
Abstract: A flap actuation system employed in an aircraft wing with a flap having an internal structure employs a drive link pivotally attached at a top end with a drive axle to a forward lug on the internal structure and pivotally attached at a bottom end with a first pivot axle to a flap support element. An actuator is operably coupled to the drive link intermediate the top end and bottom end. A trailing link is pivotally attached at a leading end with a second pivot axle to the flap support element and pivotally attached at a trailing end with a reaction axle to an aft fitting on the internal structure. A catcher link is pivotally attached at a bottom end to the flap support element and at a top end to an intermediate fitting engaged to the internal structure. The catcher link is unloaded in a typical operating condition and upon a failure in the drive link, first pivot axle, drive axle, forward lug, trailing link, second pivot axle, reaction axle or aft fitting a load is induced on the catcher link to accommodate the failure condition.
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公开(公告)号：US20210101671A1
公开(公告)日：2021-04-08
申请号：US16595448
申请日：2019-10-07
Applicant: The Boeing Company
Inventor： Kevin R. Tsai , John Thomas B. Homrich
Abstract: A flap support mechanism includes a track rotatably connected to an aft fitting of a wing. A forward roller and an aft roller extend laterally from a flap structure, the forward roller and aft roller constrained in a slot in the track. The slot has a profile configured to induce both translation and rotation in the flap, in concert with rotation of the track about the aft fitting, thereby passively mirroring motion of the flap induced by an actuator driven primary main flap support.
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公开(公告)号：US10737761B2
公开(公告)日：2020-08-11
申请号：US15957283
申请日：2018-04-19
Applicant: THE BOEING COMPANY
Inventor： Kevin R. Tsai
IPC: B64C3/50
Abstract: A camber adjustment system for a wing of an aircraft includes a droop panel that is configured to pivotally couple to a portion of a main body of a wing, a flap, and a coupler having a track that moveably couples the droop panel to the flap. The droop panel is configured to move in response to movement of the flap via the coupler.
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公开(公告)号：US12296954B2
公开(公告)日：2025-05-13
申请号：US17703025
申请日：2022-03-24
Applicant: The Boeing Company
Inventor： Kevin R. Tsai , Mark Steven Good
Abstract: A flap actuation mechanism incorporates a coupler rod eccentrically supported at an aft end and at a forward end. The coupler rod is configured to translate from an aft position to a forward position. An inboard crank arm is coupled to the rotary actuator and engaged to the aft end of the coupler rod. The inboard crank is configured rotate responsive to rotation of the rotary actuator thereby inducing translation of the coupler rod. An outboard crank arm engaged to a forward end of the coupler rod and is configured to rotate responsive to translation of the coupler rod. A flap drive arm is attached to the outboard crank arm and is configured to rotate with the outboard crank arm from a stowed position to a deployed position responsive to translation of the coupler rod from the aft position to the forward position.
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公开(公告)号：US12252235B2
公开(公告)日：2025-03-18
申请号：US18172569
申请日：2023-02-22
Applicant: The Boeing Company
Inventor： Samuel L. Block , Kevin R. Tsai
Abstract: A linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. The rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. The rib frame of the flap mechanism defines a width with a first and second web. A linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. The linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. As a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.
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