公开(公告)号：US20170284427A1

公开(公告)日：2017-10-05

申请号：US15090314

申请日：2016-04-04

Applicant: The Boeing Company

Inventor： Kevin S. Callahan ,  Christopher E. Plass ,  Matthew A. Moser

IPC: F15B15/14 ,  B64C13/24

CPC classification number: F15B15/1423 ,  B64C13/24 ,  F15B15/1433 ,  F15B2215/305

Abstract: An actuator includes a piston and a housing. The piston includes a piston shaft that is configured to reciprocate within the housing. The actuator also includes a conductor coupled to the piston within the housing and configured to electrically couple the piston to the housing as the piston reciprocates within the housing.

公开(公告)号：US09359065B2

公开(公告)日：2016-06-07

申请号：US14034920

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Michael R. Finn ,  Mark J. Gardner ,  Robert M. Murphy ,  Adam Thoreen

IPC: B64C3/38 ,  B64C13/16 ,  B64C9/16 ,  B64C13/04

CPC classification number: B64C13/16 ,  B64C9/16 ,  B64C13/04 ,  Y02T50/32 ,  Y02T50/44

Abstract: A system for optimizing performance of an aircraft may include a flight control computer for computing an optimum flap setting based on aircraft data. The system may further include a flap control system having a flap control device. The system may additionally include a flap actuation system coupled to the flap control system for positioning the trailing edge device at the optimum flap setting.

Abstract translation: 用于优化飞机性能的系统可以包括用于基于飞行器数据计算最佳翼片设置的飞行控制计算机。 该系统还可以包括具有翼片控制装置的翼片控制系统。 该系统可以另外包括连接到翼片控制系统的翼片致动系统，用于将后缘装置定位在最佳翼片设置。

公开(公告)号：US09193440B2

公开(公告)日：2015-11-24

申请号：US14034940

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Michael R. Finn ,  Mark J. Gardner ,  Mark S. Good ,  Sarah A. Jones

IPC: B64C3/50 ,  B64C13/34 ,  B64C9/14 ,  B64C13/26

CPC classification number: B64C13/34 ,  B64C3/50 ,  B64C9/06 ,  B64C9/12 ,  B64C9/14 ,  B64C13/26 ,  Y02T50/32

Abstract: A variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.

Abstract translation: 用于飞行器的可变外倾角系统可以包括位于内侧装置和外侧装置之间的可变外倾角装置单元（VCTU）。 内侧装置和外侧装置可以安装到机翼的前缘和后缘中的至少一个。 VCTU可以包括速度和齿轮箱，其具有联接到内侧装置的内侧轴和联接到外侧装置的外侧轴。 VCTU可以另外包括接合到速度和齿轮箱的VCTU电动机。 VCTU电动机可以选择性地与速度总和齿轮箱一起操作，以独立于内侧轴旋转外侧轴，使得外部装置独立于内侧装置被致动。

公开(公告)号：US20150105945A1

公开(公告)日：2015-04-16

申请号：US14035048

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Michael R. Finn ,  Adam Thoreen

IPC: B64C13/16 ,  B64C9/28

CPC classification number: B64C13/16 ,  B64C9/28 ,  B64C13/04 ,  Y02T50/32

Abstract: A system for controlling a high-lift device of an aircraft may include an interface for placement in a flight deck of an aircraft. The interface may include an edge control device for controlling a position of the high-lift device. The interface may be operable to select any of a plurality of control device positions. Each one of the plurality of control device positions may correspond to a different flight phase of the aircraft. The edge control device may be operable to engage, in response to a selection of a first control device position, a command mode for actuating the high-lift device in an automated manner based on the flight phase associated with the first control device position.

Abstract translation: 用于控制飞机的高升降装置的系统可以包括用于放置在飞行器的驾驶舱中的接口。 接口可以包括用于控制高升程装置的位置的边缘控制装置。 接口可操作以选择多个控制装置位置中的任何一个。 多个控制装置位置中的每一个可对应于飞机的不同飞行阶段。 边缘控制装置可操作以响应于第一控制装置位置的选择而接合基于与第一控制装置位置相关联的飞行阶段以自动方式致动高升降装置的命令模式。

公开(公告)号：US20150083867A1

公开(公告)日：2015-03-26

申请号：US14034987

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Mark J. Gardner ,  Michael R. Finn ,  Mark S. Good ,  Adam P. Malachowski ,  Monica E. Thommen ,  Stephen R. Amorosi ,  Dan Onu

IPC: B64C3/50 ,  B64C13/16 ,  B64C13/00

CPC classification number: B64C3/50 ,  B64C9/06 ,  B64C9/12 ,  B64C9/24 ,  B64C13/00 ,  B64C13/16 ,  B64C13/26 ,  B64C13/503 ,  Y02T50/32 ,  Y02T50/44

Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.

Abstract translation: 用于改变飞机机翼的机翼弯曲的系统可以包括联接到机翼的前缘装置。 前缘装置可以被构造成相对于前缘装置的缩回位置沿向上的方向和向下的方向被致动。