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公开(公告)号：US11603182B1
公开(公告)日：2023-03-14
申请号：US17881677
申请日：2022-08-05
发明人： Richard E Dooley
摘要： A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.
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公开(公告)号：US11591072B2
公开(公告)日：2023-02-28
申请号：US17491000
申请日：2021-09-30
申请人： The Boeing Company
摘要： Linkage assemblies for moving tabs on control surfaces of aircraft are disclosed herein. An example aircraft includes a wing including a fixed wing portion and a trailing edge control surface. The trailing edge control surface includes a fore panel rotatably coupled to the fixed wing portion and an aft panel rotatably coupled to the fore panel. The wing also includes a linkage assembly including a rocking lever rotatably coupled to a bottom side of the fore panel, a trailing edge link having a first end rotatably coupled to the fixed wing portion and a second end rotatably coupled to the rocking lever, and an aft panel link having a first end rotatably coupled to the rocking lever and a second end rotatably coupled to a bottom side of the aft panel.
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公开(公告)号：US20230026241A1
公开(公告)日：2023-01-26
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：US20220306277A1
公开(公告)日：2022-09-29
申请号：US17695973
申请日：2022-03-16
发明人： Rainer GARTELMANN
摘要： A wing for an aircraft, including a main wing, and a leading edge high lift assembly including a high lift body, and a connection assembly connecting the high lift body to the main wing such that the high lift body is movable relative to the main wing between a stowed position and a deployed position. The connection assembly includes at least one rotation element mounted to the high lift body and mounted to the main wing rotatably about an axis of rotation. The high lift body includes a rigid portion and a flexible skin portion. The rigid portion is mounted to the rotation element. The flexible skin portion is connected to a leading edge portion of an upper skin panel of the main wing and is connected to the rigid portion of the high lift body The flexible skin portion is configured to be deformed between a stowed deformation state and a deployed deformation state, when the high lift body is moved between the stowed position and the deployed position.
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公开(公告)号：US20220227480A1
公开(公告)日：2022-07-21
申请号：US17491000
申请日：2021-09-30
申请人： The Boeing Company
摘要： Linkage assemblies for moving tabs on control surfaces of aircraft are disclosed herein. An example aircraft includes a wing including a fixed wing portion and a trailing edge control surface. The trailing edge control surface includes a fore panel rotatably coupled to the fixed wing portion and an aft panel rotatably coupled to the fore panel. The wing also includes a linkage assembly including a rocking lever rotatably coupled to a bottom side of the fore panel, a trailing edge link having a first end rotatably coupled to the fixed wing portion and a second end rotatably coupled to the rocking lever, and an aft panel link having a first end rotatably coupled to the rocking lever and a second end rotatably coupled to a bottom side of the aft panel.
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公开(公告)号：US11312475B2
公开(公告)日：2022-04-26
申请号：US16711488
申请日：2019-12-12
发明人： Raphael Medina
摘要： A system for detecting and controlling the position of a spoiler of an aircraft wing is described herein comprising: a hydraulic actuator having a piston rod operably connected to the spoiler, the piston rod being moveable between a retracted position, a neutral position and an extended position; and means for providing power to said hydraulic actuator; and a mechanical device for detecting whether the piston rod is in the retracted position, the neutral position or the extended position; and means, operatively connected to the mechanical device, that is configured to provide a change in a load applied to said hydraulic actuator, wherein said means is configured to change said load based on whether said piston rod is detected as being in said retracted position or said extended position.
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公开(公告)号：US11225322B2
公开(公告)日：2022-01-18
申请号：US16289716
申请日：2019-03-01
申请人： Ratier-Figeac SAS
发明人： Pierre-Jacques Labry
IPC分类号： B64C25/44 , B64C13/04 , F16H21/44 , F16H51/00 , F16H57/00 , F16C11/06 , F16C7/00 , F16C11/04 , B64C13/30
摘要： A brake rod for a steering/braking mechanism includes a rod body having a longitudinal axis, a rod end at a first end of the rod body, the rod end having a bore therethrough having a bore axis arranged generally perpendicular to the rod longitudinal axis, and a rod end shield mounted to the rod and extending in a longitudinal direction axially beyond the rod end.
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公开(公告)号：US11225319B2
公开(公告)日：2022-01-18
申请号：US16801976
申请日：2020-02-26
申请人： The Boeing Company
发明人： Miranda Peterson , Kevin R. Tsai
摘要： A wing stall compensation mechanism employs an upper door having forward upper hinge end pivotally coupled to an upper wing structure for rotation about an upper axis and a free aft upper end. A lower door has a free aft lower end and a forward lower hinge end pivotally coupled to a lower wing structure for rotation about a lower axis and a 2-bar coupler linkage is disposed between and pivotally coupled to the upper door and lower door. Downward rotation of the upper door in response to wing surface airflow separation causes contraction of the coupler linkage inducing upward rotation of the lower door from a closed position that inhibits airflow through a flap slot to an open position that enables airflow through the flap slot, to thereby restore wing surface airflow effectiveness.
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公开(公告)号：US20210323656A1
公开(公告)日：2021-10-21
申请号：US16849096
申请日：2020-04-15
申请人： The Boeing Company
发明人： Arvin Shmilovich , Eric D. Dickey
摘要： Aircraft wing droop leading edge apparatus and methods are described. An example aircraft includes a wing having a front spar and an outer skin covering the front spar. The outer skin includes a forward portion located forward of the front spar. The forward portion of the outer skin includes a leading edge movable between a neutral position and a drooped position deflected downward relative to the neutral position. The forward portion of the outer skin has a continuous outer mold line when the leading edge is in the drooped position.
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公开(公告)号：US11117648B2
公开(公告)日：2021-09-14
申请号：US16256814
申请日：2019-01-24
发明人： Marc Hencke , Markus Gibbert , Florian Gehle
摘要： A linkage mechanism for a flaperon includes a support structure linkage, a droop panel linkage, and a flaperon linkage. The support structure linkage is pivotally attached to a support structure of a wing of an aircraft. The droop panel linkage is pivotally attached a droop panel. The flaperon linkage is pivotally attached to a flaperon. A second end of the droop panel linkage and a second end of the flaperon linkage are pivotally attached to a connecting section of the support structure linkage. The connecting section is spaced apart from the pivot end of the support structure linkage such that the linkage mechanism transfers a pivoting motion from the flaperon into a pivoting motion of the droop panel.
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