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公开(公告)号：US20200216168A1
公开(公告)日：2020-07-09
申请号：US16826544
申请日：2020-03-23
Applicant: The Boeing Company
Inventor： Kevin Tsai , Bret Alan Bowers
Abstract: 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：US10669013B2
公开(公告)日：2020-06-02
申请号：US15895742
申请日：2018-02-13
Applicant: The Boeing Company
Inventor： Kevin Tsai , Bret Alan Bowers
Abstract: 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：US10444128B2
公开(公告)日：2019-10-15
申请号：US15289310
申请日：2016-10-10
Applicant: The Boeing Company
Inventor： Lisa G. Schleuter , Bret Alan Bowers
Abstract: A load path status detection system comprising a primary fastener, a load sensor, a primary structural link, and a secondary structural link. The primary fastener extends through the primary structural link. The load sensor is associated with the primary structural link. The primary structural link carries a load when a primary load path, formed by the primary fastener and the primary structural link, is functioning. The secondary structural link is parallel to the primary structural link, wherein the secondary structural link does not carry a load when the primary load path is functioning.
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公开(公告)号：US20180100790A1
公开(公告)日：2018-04-12
申请号：US15289310
申请日：2016-10-10
Applicant: The Boeing Company
Inventor： Lisa G. Schleuter , Bret Alan Bowers
CPC classification number: G01N3/08 , B64C9/02 , B64D2045/0085 , G01L1/127 , G01L1/2287 , Y02T50/44
Abstract: A load path status detection system comprising a primary fastener, a load sensor, a primary structural link, and a secondary structural link. The primary fastener extends through the primary structural link. The load sensor is associated with the primary structural link. The primary structural link carries a load when a primary load path, formed by the primary fastener and the primary structural link, is functioning. The secondary structural link is parallel to the primary structural link, wherein the secondary structural link does not carry a load when the primary load path is functioning.
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公开(公告)号：US20240343383A1
公开(公告)日：2024-10-17
申请号：US18299491
申请日：2023-04-12
Applicant: The Boeing Company
Inventor： Emily Georgia Rayner , Kevin Raylin Tsai , Ramón Augustin Burin , Bret Alan Bowers
Abstract: The illustrative examples provide a slat movement system for use in an aircraft. An aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.
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Patent Agency Ranking
公开(公告)号：US12103703B2
公开(公告)日：2024-10-01
申请号：US17530545
申请日：2021-11-19
Applicant: THE BOEING COMPANY
Inventor： Samuel L. Block , Bret Alan Bowers , Kevin R. Tsai
CPC classification number: B64D45/0005 , B64C9/34 , B64D2045/001
Abstract: A jam detection system for a flap of a wing of an aircraft includes a linkage coupled to the flap and a support of the wing, and a sensor configured to detect a position of at least a portion of the linkage. The sensor is further configured to compare the position of the least a portion of the linkage to a jam threshold to determine if a jam condition exists. The linkage can also be coupled to a carriage moveably coupled to the support.
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公开(公告)号：US20230159183A1
公开(公告)日：2023-05-25
申请号：US17530545
申请日：2021-11-19
Applicant: THE BOEING COMPANY
Inventor： Samuel L. Block , Bret Alan Bowers , Kevin R. Tsai
CPC classification number: B64D45/0005 , B64C9/34 , B64D2045/001
Abstract: A jam detection system for a flap of a wing of an aircraft includes a linkage coupled to the flap and a support of the wing, and a sensor configured to detect a position of at least a portion of the linkage. The sensor is further configured to compare the position of the least a portion of the linkage to a jam threshold to determine if a jam condition exists. The linkage can also be coupled to a carriage moveably coupled to the support.
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公开(公告)号：US11192636B2
公开(公告)日：2021-12-07
申请号：US16813511
申请日：2020-03-09
Applicant: THE BOEING COMPANY
Inventor： Bret Alan Bowers , Scott Thomas Evoy
Abstract: An actuation system for a control surface of an aircraft includes a drive lever. The drive lever includes a coupling end configured to pivotably couple to a plurality of wing attach fittings and a lever end. The lever end includes a first actuator fitting configured to pivotably couple to a first actuator on a forward side of the drive lever; a second actuator fitting configured to pivotably couple to a second actuator on an aft side of the drive lever; a first drive link fitting configured to couple, via a first drive link, to a control surface of an aircraft; and a second drive link fitting configured to couple, via a second drive link, to the control surface of the aircraft.
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公开(公告)号：US20210276694A1
公开(公告)日：2021-09-09
申请号：US16813511
申请日：2020-03-09
Applicant: THE BOEING COMPANY
Inventor： Bret Alan Bowers , Scott Thomas Evoy
IPC: B64C13/28
Abstract: An actuation system for a control surface of an aircraft includes a drive lever. The drive lever includes a coupling end configured to pivotably couple to a plurality of wing attach fittings and a lever end. The lever end includes a first actuator fitting configured to pivotably couple to a first actuator on a forward side of the drive lever; a second actuator fitting configured to pivotably couple to a second actuator on an aft side of the drive lever; a first drive link fitting configured to couple, via a first drive link, to a control surface of an aircraft; and a second drive link fitting configured to couple, via a second drive link, to the control surface of the aircraft.
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公开(公告)号：US20190248474A1
公开(公告)日：2019-08-15
申请号：US15895742
申请日：2018-02-13
Applicant: The Boeing Company
Inventor： Kevin Tsai , Bret Alan Bowers
Abstract: 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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