公开(公告)号：US20150083850A1

公开(公告)日：2015-03-26

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: B64C13/16

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：US10017243B2

公开(公告)日：2018-07-10

申请号：US14034946

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Michael R. Finn

IPC: B64C13/50 ,  B64C9/16 ,  B64C13/28 ,  B64C3/14

CPC classification number: B64C13/34 ,  B64C9/16 ,  B64C13/50 ,  B64C2003/145 ,  Y02T50/12 ,  Y02T50/32

Abstract: An adaptive trailing edge system for an aircraft may include an adaptive trailing edge element mounted to a trailing edge. An electric motor actuator having an electric motor may be configured to actuate the adaptive trailing edge element. A linkage system may couple the electric motor actuator to the adaptive trailing edge element for actuation thereof.

公开(公告)号：US09656741B2

公开(公告)日：2017-05-23

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 ,  B64C13/04

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.

公开(公告)号：US09327827B2

公开(公告)日：2016-05-03

申请号：US14035001

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Benjamin M. Liu ,  Michael R. Finn

IPC: B64C13/00 ,  B64C13/16 ,  B64C9/32 ,  B64C19/02 ,  G05D1/06

CPC classification number: B64C13/16 ,  B64C9/32 ,  B64C19/02 ,  G05D1/0607 ,  Y02T50/32

Abstract: An system for increasing the descent rate of an aircraft may include a flight control computer, an edge control system, and a speedbrake control device. The flight control computer may be configured to compute a first setting for a leading edge device and/or a trailing edge device of an aircraft wing. The edge control system may be communicatively coupled to the flight control computer and may include an edge control device having a plurality of control device positions including a cruise position. The speedbrake control device may include a plurality of speedbrake detents including a flight detent. The edge control system may be configured to automatically command the leading edge device, the trailing edge device, or both, to a deflection angle corresponding to the first setting if the edge control device is in the cruise position and the speedbrake control device is in the flight detent.

Abstract translation: 用于增加飞行器下降率的系统可以包括飞行控制计算机，边缘控制系统和速度制动器控制装置。 飞行控制计算机可以被配置为计算飞机机翼的前缘装置和/或后缘装置的第一设定。 边缘控制系统可以通信地耦合到飞行控制计算机，并且可以包括具有包括巡航位置的多个控制装置位置的边缘控制装置。 速度制动控制装置可以包括多个包括飞行制动器的制动器制动器。 边缘控制系统可以被配置为如果边缘控制装置处于巡航位置并且速度制动控制装置处于巡航位置，则将前缘装置，后缘装置或两者自动命令为对应于第一设定的偏转角度 飞行制动。

公开(公告)号：US09296475B2

公开(公告)日：2016-03-29

申请号：US14035030

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  David D. Leopold ,  Michael R. Finn

IPC: B64C25/42 ,  G05D1/00

CPC classification number: B64C25/426 ,  B64C9/12 ,  B64C13/28 ,  B64C25/423 ,  G05D1/0083 ,  Y02T50/32

Abstract: A system for reducing a stopping distance of an aircraft may include an edge control system configured to control a leading edge device mounted to a wing of an aircraft. The edge control system may be configured to automatically command extension of the leading edge device from a first position to a second position in response to deployment of a spoiler if a ground speed of the aircraft is greater than a threshold ground speed.

Abstract translation: 用于减少飞行器的停止距离的系统可以包括边缘控制系统，该边缘控制系统被配置为控制安装在飞机机翼上的前缘装置。 如果飞行器的地面速度大于阈值地面速度，边缘控制系统可以被配置为响应于扰流器的展开而自动地将前缘装置从第一位置延伸到第二位置。

公开(公告)号：US09180962B2

公开(公告)日：2015-11-10

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 ,  B64C9/24 ,  B64C13/50 ,  B64C13/00 ,  B64C13/16

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。

公开(公告)号：US20150102166A1

公开(公告)日：2015-04-16

申请号：US14035030

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  David D. Leopold ,  Michael R. Finn

IPC: B64C25/42

CPC classification number: B64C25/426 ,  B64C9/12 ,  B64C13/28 ,  B64C25/423 ,  G05D1/0083 ,  Y02T50/32

Abstract: A system for reducing a stopping distance of an aircraft may include an edge control system configured to control a leading edge device mounted to a wing of an aircraft. The edge control system may be configured to automatically command extension of the leading edge device from a first position to a second position in response to deployment of a spoiler if a ground speed of the aircraft is greater than a threshold ground speed.

Abstract translation: 用于减少飞行器的停止距离的系统可以包括边缘控制系统，该边缘控制系统被配置为控制安装在飞机机翼上的前缘装置。 如果飞行器的地面速度大于阈值地面速度，边缘控制系统可以被配置为响应于扰流器的展开而自动地将前缘装置从第一位置延伸到第二位置。

公开(公告)号：US20150083855A1

公开(公告)日：2015-03-26

申请号：US14035011

申请日：2013-09-24

Applicant: The Boeing Company

Inventor： Matthew A. Moser ,  Michael R. Finn ,  Duk Park ,  Christopher A. Konings

IPC: B64C23/00 ,  B64C13/16

CPC classification number: B64C9/16 ,  B64C9/20 ,  B64C9/22 ,  B64C9/24 ,  B64C13/28 ,  Y02T50/32 ,  Y02T50/44

Abstract: A slat control system for an aircraft may include a flight control computer configured to generate a gap command in response to an occurrence of a gap-command condition. The slat control system may further include an edge control system including an edge control device having a plurality of control device positions including at least one designated control device position. The slat control system may additionally include a device actuation system configured to move a leading edge device of an aircraft. The edge control system may be configured to automatically command the device actuation system to extend the leading edge device from a sealed position to a gapped position when the edge control device is in the designated control device position and the gap command is received by the edge control system.

Abstract translation: 用于飞行器的翼板控制系统可以包括飞行控制计算机，该飞行控制计算机被配置为响应于间隙命令条件的发生而产生间隙命令。 板条控制系统还可以包括边缘控制系统，该边缘控制系统包括边缘控制装置，该边缘控制装置具有包括至少一个指定的控制装置位置的多个控制装置位置。 板条控制系统可以另外包括被配置为移动飞行器的前缘装置的装置致动系统。 边缘控制系统可以被配置为当边缘控制装置处于指定的控制装置位置时，自动命令装置致动系统将前缘装置从密封位置延伸到间隙位置，并且通过边缘控制接收间隙命令 系统。

公开(公告)号：US20200011355A1

公开(公告)日：2020-01-09

申请号：US16577033

申请日：2019-09-20

Applicant: THE BOEING COMPANY

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

IPC: F15B15/14

Abstract: An actuator includes a piston and a housing. The piston includes a piston shaft that is configured to reciprocate within a chamber of the housing. The actuator includes a gland electrically coupled to the housing. The gland forms at least a portion of a first end of the chamber. The actuator also includes a first conductor positioned in the chamber. The first conductor is coupled to the gland and to a first side of the piston to electrically couple the piston to the housing.

公开(公告)号：US09821903B2

公开(公告)日：2017-11-21

申请号：US14330824

申请日：2014-07-14

Applicant: The Boeing Company

Inventor： Abraham J. Pachikara ,  Matthew A. Moser ,  Paul H. Carpenter ,  Michael R. Finn ,  Thomas S. Koch ,  Stefan R. Bieniawski ,  Brian T. Whitehead

IPC: B64C13/16 ,  B64C9/12 ,  G05D1/08 ,  B64C3/44 ,  B64C9/00 ,  B64D45/00

CPC classification number: B64C13/16 ,  B64C3/44 ,  B64C9/00 ,  B64C9/12 ,  B64D45/0005 ,  G05D1/0825 ,  Y02T50/32 ,  Y02T50/44

Abstract: Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.