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1.发明授权公开(公告)号：US11820490B1
公开(公告)日：2023-11-21
申请号：US17751209
申请日：2022-05-23
申请人： The Boeing Company
发明人： Kevin Tsai , Mark S. Good
CPC分类号： B64C13/50 , B64C1/0009 , B64C1/38 , B64C9/02 , B64C9/06
摘要： Methods, apparatus, and articles of manufacture for actuating control surfaces of an aircraft are disclosed. An example apparatus to control a control surface of an aerodynamic body includes a track rotatable about a pivot of a support structure of the aerodynamic body, the control surface slidably coupled to the track, a first actuator operatively coupled to the track, the first actuator to cause rotation of the track and the flaperon about the pivot, and a second actuator operatively coupled to the control surface, the second actuator to cause translation of the control surface along the track.
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2.发明申请公开(公告)号：US20220396351A1
公开(公告)日：2022-12-15
申请号：US17693006
申请日：2022-03-11
申请人： The Boeing Company
发明人： Kevin Tsai , Jacob Makena Wagner
摘要： Truncated flap support fairings with active flow control system for aircraft and related methods are disclosed herein. An example aircraft includes a wing having a fixed wing portion, a flap moveably coupled to the fixed wing portion, a flap support fairing coupled to a bottom of the flap, the flap support fairing having an aft end, and an active flow control system including a nozzle. The nozzle is to eject high velocity air in a streamwise direction from the aft end of the flap support fairing.
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公开(公告)号：US20220388631A1
公开(公告)日：2022-12-08
申请号：US17830400
申请日：2022-06-02
申请人： The Boeing Company
发明人： Noah W. Gibson , Kevin Tsai
摘要： An actuation mechanism includes a control surface having a hinged end pivotally coupled to a wing structure, a first pivot arm and a second pivot arm coupled to the control surface, a first drive rod coupled to the first pivot arm, and a second drive rod coupled to the second pivot arm. A first bell crank is coupled via a first pivot pin to the wing structure at a first position and to the first drive rod. A second bell crank is coupled via a second pivot pin to the wing structure at a second position spaced apart from the first position and to the second drive rod. A coupling rod extends between the first bell crank and the second bell crank such that a rotation of the first bell crank is synchronized with a rotation of the second bell crank.
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公开(公告)号：US20210061443A1
公开(公告)日：2021-03-04
申请号：US16552466
申请日：2019-08-27
申请人： The Boeing Company
发明人： Bruce Dahl , Kevin Tsai
摘要： Flap actuation systems for aircraft are described herein. An example flap actuation system includes a fixed beam coupled to and extending downward from a fixed wing portion of an aircraft wing and a rocking lever plate pivotably coupled to the fixed beam. The rocking lever plate is coupled to a forward end of a flap bracket disposed on a bottom side of a flap of the wing. The flap actuation system also includes a crank arm, a crank rod coupled between the crank arm and the rocking lever plate, and a flap link coupled between the rocking lever plate and an aft end of the flap bracket, such that actuation of the crank arm pivots the rocking lever plate to move the flap between a stowed position and a deployed position relative to the fixed wing portion.
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公开(公告)号：US20210009255A1
公开(公告)日：2021-01-14
申请号：US16506206
申请日：2019-07-09
申请人： The Boeing Company
发明人： Bryan J. Gruner , Kevin Tsai
摘要： Disclosed herein is a system for actuating a flap coupled to a wing of an aircraft in a streamwise direction. The system comprises a geared rotary actuator comprising a drive gear that is rotatable about a first rotational axis. The system also comprises a crank shaft comprising a driven gear in gear meshing engagement with the drive gear of the geared rotary actuator to rotate the crank shaft about a second rotational axis. The second rotational axis is angled relative to the first rotational axis. The system further comprises a crank arm co-rotatably coupled to the crank shaft and configured to be coupled to the flap. Rotation of the crank shaft about the second rotational axis rotates the crank arm in a direction perpendicular to the second rotational axis.
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公开(公告)号：US11952106B2
公开(公告)日：2024-04-09
申请号：US17657859
申请日：2022-04-04
申请人： The Boeing Company
发明人： Joli K. Umetsu , Kevin Tsai
摘要： An aerial vehicle control surface actuation system comprises a rotary actuator having opposing output shaft ends that are coupled to first and second torque tubes via actuator universal joints. The first and second torque tubes extend angularly from the rotary actuator. The system further comprises first and second pivot joints that are coupled to a hinged end of a control surface. The first and second pivot joints are coupled to the first and second torque tubes, respectively, via control surface universal joints. In this configuration, rotation of the first and second torque tubes causes rotation of the control surface relative to a hinge axis.
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7.发明公开公开(公告)号：US20230373611A1
公开(公告)日：2023-11-23
申请号：US17751209
申请日：2022-05-23
申请人： The Boeing Company
发明人： Kevin Tsai , Mark S. Good
CPC分类号： B64C13/50 , B64C1/0009 , B64C1/38 , B64C9/06 , B64C9/02
摘要： Methods, apparatus, and articles of manufacture for actuating control surfaces of an aircraft are disclosed. An example apparatus to control a control surface of an aerodynamic body includes a track rotatable about a pivot of a support structure of the aerodynamic body, the control surface slidably coupled to the track, a first actuator operatively coupled to the track, the first actuator to cause rotation of the track and the flaperon about the pivot, and a second actuator operatively coupled to the control surface, the second actuator to cause translation of the control surface along the track.
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公开(公告)号：US20230365250A1
公开(公告)日：2023-11-16
申请号：US17744272
申请日：2022-05-13
申请人： The Boeing Company
发明人： Mark S. Good , Kevin Tsai
摘要： Assemblies for air vehicle control surfaces and related methods are disclosed. An example apparatus includes a control surface; a bullnose carried by the control surface, the bullnose moveable relative to the control surface; a first actuator operatively coupled to the control surface to cause the control surface to rotate; and a second actuator operatively coupled to the control surface, the second actuator to cause the bullnose to move from a first position to a second position to cause an opening to be formed relative to the control surface, the movement of the bullnose independent of rotation of the control surface.
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公开(公告)号：US11479343B2
公开(公告)日：2022-10-25
申请号：US16826544
申请日：2020-03-23
申请人： The Boeing Company
发明人： Kevin Tsai , Bret Alan Bowers
摘要： A gimbal having a split design, which can be used in an assembly for actuating an aerodynamic high lift device, is described. The gimbal enables a rotating load path when a force is transferred from the actuator to the high lift device via the gimbal. In particular, the split design can include two receivers which can be coupled to posts extending from a nut. The nut can be secured to a shaft which receives a force generated by the actuator. In one embodiment, the actuator can rotate the shaft to cause the gimbal to translate along the shaft. The split design provides a more compact form factor and is lighter in weight than traditional gimbal designs.
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公开(公告)号：US11254417B2
公开(公告)日：2022-02-22
申请号：US16216822
申请日：2018-12-11
申请人： THE BOEING COMPANY
发明人： Kevin Tsai , Lisa Schleuter
摘要： An aircraft spoiler mechanism includes a spoiler fore-section, a spoiler aft-section, and a reverse-motion linkage arm. The spoiler fore-section includes a forward end, a hinge end, an actuator coupling, and a pivot coupling to couple to a wing structure of an aircraft to enable rotation of the spoiler fore-section relative to the wing structure. The spoiler aft-section includes a hinge portion coupled to the hinge end of the spoiler fore-section and a crank-arm. The reverse-motion linkage arm includes a first end, a second end, and a pivot point coupled to the forward end of the spoiler fore-section. The spoiler mechanism also includes a first linkage to couple the first end of the reverse-motion linkage arm to the wing structure and a second linkage coupled to the second end of the reverse-motion linkage arm and to the crank-arm on the spoiler aft-section.
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