公开(公告)号：US20250002135A1

公开(公告)日：2025-01-02

申请号：US18344033

申请日：2023-06-29

Applicant: The Boeing Company

Inventor： Paul W. Dees ,  William M. Sampedro-Thompson ,  Bret Alan Bowers ,  Robert E. Grip ,  Neal A. Harrison ,  Alan C. Simonini ,  Theodore K. Rothaupt

IPC: B64C1/26

Abstract: Apparatus and articles of manufacture are disclosed of an aircraft comprising: a brace to support a wing of the aircraft, the brace including a first end coupled to the wing and a second end coupled to a fuselage of the aircraft, the brace including: a strut extending between the first end and the second end; and an airfoil having a cavity containing the strut.

公开(公告)号：US20200047874A1

公开(公告)日：2020-02-13

申请号：US16057511

申请日：2018-08-07

Applicant: The Boeing Company

Inventor： Bret Alan Bowers ,  Lisa Schleuter

IPC: B64C13/40 ,  B64C3/50 ,  B64C9/04 ,  B64C9/20 ,  F15B15/14 ,  F15B11/22 ,  F15B13/06 ,  F15B15/06

Abstract: Systems and methods for hydraulic droop control of an aircraft wing. One embodiment is a hydraulic droop panel system for an aircraft wing. The hydraulic droop panel system includes a first hydraulic actuator attached to a flap of the aircraft wing, and a second hydraulic actuator attached to a droop panel of the aircraft wing and fluidly coupled with the first hydraulic actuator. The second hydraulic actuator is configured to move the droop panel to a droop position corresponding with movement of the flap and the first hydraulic actuator.

公开(公告)号：US11001371B2

公开(公告)日：2021-05-11

申请号：US16057511

申请日：2018-08-07

Applicant: The Boeing Company

Inventor： Bret Alan Bowers ,  Lisa Schleuter

IPC: B64C13/40 ,  B64C3/50 ,  B64C9/04 ,  B64C9/20 ,  F15B11/22 ,  F15B13/06 ,  F15B15/06 ,  F15B15/14

Abstract: Systems and methods for hydraulic droop control of an aircraft wing. One embodiment is a hydraulic droop panel system for an aircraft wing. The hydraulic droop panel system includes a first hydraulic actuator attached to a flap of the aircraft wing, and a second hydraulic actuator attached to a droop panel of the aircraft wing and fluidly coupled with the first hydraulic actuator. The second hydraulic actuator is configured to move the droop panel to a droop position corresponding with movement of the flap and the first hydraulic actuator.

公开(公告)号：US10926864B2

公开(公告)日：2021-02-23

申请号：US16047094

申请日：2018-07-27

Applicant: THE BOEING COMPANY

Inventor： Kevin R. Tsai ,  Bret Alan Bowers

IPC: B64C9/02 ,  B64C9/12 ,  B64C9/16

Abstract: A camber adjustment system for a wing of an aircraft includes a droop panel that is configured to moveably couple to a portion of the wing, a flap, a cam rod moveably coupled to the droop panel, a bell crank cam arm moveably coupled to the flap, and a jackscrew interface between the cam rod and the bell crank cam arm. The droop panel is configured to move in response to movement of the flap via the jackscrew interface.

公开(公告)号：US20190315449A1

公开(公告)日：2019-10-17

申请号：US15953018

申请日：2018-04-13

Applicant: The Boeing Company

Inventor： Bret Alan Bowers ,  Kevin Tsai

IPC: B64C3/50 ,  B64C13/16

Abstract: Methods and apparatus to control camber are disclosed. A disclosed example apparatus includes a flap support to be coupled to a flap of an aircraft, where the flap is rotatable relative to an aerodynamic surface, a drive arm linkage rotatably coupled to the flap support at a first pivot of the flap support, where the drive arm linkage includes a second pivot at an end opposite the first end, and a flap support actuator operatively coupled to the flap support, where the flap support actuator is to rotate the drive arm linkage. The example apparatus also includes a camber control actuator rotatably coupled to the flap support at a third pivot of the flap support, where the camber control actuator is to be rotatably coupled to the flap at a fourth pivot.

公开(公告)号：US12179919B2

公开(公告)日：2024-12-31

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

IPC: B64C9/24 ,  B64C9/02 ,  B64C9/06 ,  B64C13/38

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.

公开(公告)号：US11479343B2

公开(公告)日：2022-10-25

申请号：US16826544

申请日：2020-03-23

Applicant: The Boeing Company

Inventor： Kevin Tsai ,  Bret Alan Bowers

IPC: B64C13/30 ,  F16M11/12 ,  F16C11/06 ,  F16H25/24

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.

公开(公告)号：US20200031453A1

公开(公告)日：2020-01-30

申请号：US16047094

申请日：2018-07-27

Applicant: THE BOEING COMPANY

Inventor： Kevin R. Tsai ,  Bret Alan Bowers

IPC: B64C9/16 ,  B64C9/04 ,  B64C9/02

Abstract: A camber adjustment system for a wing of an aircraft includes a droop panel that is configured to moveably couple to a portion of the wing, a flap, a cam rod moveably coupled to the droop panel, a bell crank cam arm moveably coupled to the flap, and a jackscrew interface between the cam rod and the bell crank cam arm. The droop panel is configured to move in response to movement of the flap via the jackscrew interface.

公开(公告)号：US10386254B2

公开(公告)日：2019-08-20

申请号：US15137366

申请日：2016-04-25

Applicant: The Boeing Company

Inventor： Lisa G. Schleuter ,  Kevin Christopher Klohe ,  Bret Alan Bowers

IPC: G01L5/00 ,  B64C9/02 ,  B64D45/00

Abstract: A fastener status detection system is presented. The fastener status detection system comprises a primary fastener, a secondary fastener, and a sensor. The secondary fastener is configured to be a back-up to the primary fastener. The sensor is positioned to measure at least a portion of a load between the primary fastener and the secondary fastener.

公开(公告)号：US11097829B2

公开(公告)日：2021-08-24

申请号：US15953018

申请日：2018-04-13

Applicant: The Boeing Company

Inventor： Bret Alan Bowers ,  Kevin Tsai

IPC: B64C3/50 ,  B64C13/16

Abstract: Methods and apparatus to control camber are disclosed. A disclosed example apparatus includes a flap support to be coupled to a flap of an aircraft, where the flap is rotatable relative to an aerodynamic surface, a drive arm linkage rotatably coupled to the flap support at a first pivot of the flap support, where the drive arm linkage includes a second pivot at an end opposite the first end, and a flap support actuator operatively coupled to the flap support, where the flap support actuator is to rotate the drive arm linkage. The example apparatus also includes a camber control actuator rotatably coupled to the flap support at a third pivot of the flap support, where the camber control actuator is to be rotatably coupled to the flap at a fourth pivot.