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公开(公告)号：US20200027362A1
公开(公告)日：2020-01-23
申请号：US16039490
申请日：2018-07-19
Applicant: The Boeing Company
Inventor： Stephen Dame , Dragos D. Margineantu , Nick S. Evans , Tyler C. Staudinger , Brian K. Rupnik , Matthew A. Moser , Kevin S. Callahan , Brain T. Whitehead
Abstract: Example implementations relate to autonomous airport runway navigation. An example system includes a first sensor and a second sensor coupled to an aircraft at a first location and a second location, respectively, and a computing system configured to receive sensor data from one or both of the first sensor and the second sensor to detect airport markings positioned proximate a runway. The computing system is further configured to identify a centerline of the runway based on the airport markings and receive sensor data from both of the first sensor and the second sensor to determine a lateral displacement that represents a distance between a reference point of the aircraft and the centerline of the runway. The computing system is further configured to control instructions that indicate adjustments for aligning the reference point of the aircraft with the centerline of the runway during subsequent navigation of the aircraft.
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公开(公告)号：US10458443B2
公开(公告)日：2019-10-29
申请号：US15090314
申请日：2016-04-04
Applicant: The Boeing Company
Inventor： Kevin S. Callahan , Christopher E. Plass , Matthew A. Moser
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.
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公开(公告)号：US10995776B2
公开(公告)日：2021-05-04
申请号：US16577033
申请日：2019-09-20
Applicant: THE BOEING COMPANY
Inventor： Kevin S. Callahan , Christopher E. Plass , Matthew A. Moser
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.
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公开(公告)号：US09771141B2
公开(公告)日：2017-09-26
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
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.
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公开(公告)号：US20160229522A1
公开(公告)日：2016-08-11
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
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.
Abstract translation: 这里描述了控制表面的闭环控制。 一个公开的示例性方法包括在飞行期间测量飞行器的飞行量度，并且使用处理器根据飞行量度来计算飞行器的控制表面的偏转。 所公开的示例性方法还包括基于所计算的偏转将偏转调整到有效偏转水平以减少飞行器的阻力系数。
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Patent Agency Ranking
公开(公告)号：US20150083852A1
公开(公告)日：2015-03-26
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: B64C13/34
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。
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公开(公告)号：US09254909B2
公开(公告)日：2016-02-09
申请号：US14034969
申请日：2013-09-24
Applicant: The Boeing Company
Inventor： Matthew A. Moser , Michael R. Finn , Benjamin M. Liu
Abstract: A system for optimizing a flap setting of an aircraft may include a flap optimizing computer configured to compute an optimum flap setting for one or more flaps of an aircraft. The system may further include a flap control system communicatively coupled to the flap optimizing computer. The flap control system may be operable to select any one of a plurality of flap settings including a designated flap setting. The flap control system may be configured to automatically command the one or more flaps from a first position to a second position corresponding to the optimum flap setting in response to the selection of one of the plurality of flap settings using the flap control system.
Abstract translation: 用于优化飞机的翼片设置的系统可以包括翼片优化计算机，其配置成计算飞行器的一个或多个翼片的最佳翼片设置。 系统还可以包括通风地连接到翼片优化计算机的翼片控制系统。 翼片控制系统可操作以选择包括指定翼片设置的多个翼片设置中的任一个。 翼片控制系统可以被配置为响应于使用翼片控制系统选择多个翼片设置之一来自动地将一个或多个翼片从第一位置命令对应于最佳翼片设置的第二位置。
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公开(公告)号：US20150088340A1
公开(公告)日：2015-03-26
申请号：US14034969
申请日：2013-09-24
Applicant: The Boeing Company
Inventor： Matthew A. Moser , Michael R. Finn , Benjamin M. Liu
IPC: B64C13/16
Abstract: A system for optimizing a flap setting of an aircraft may include a flap optimizing computer configured to compute an optimum flap setting for one or more flaps of an aircraft. The system may further include a flap control system communicatively coupled to the flap optimizing computer. The flap control system may be operable to select any one of a plurality of flap settings including a designated flap setting. The flap control system may be configured to automatically command the one or more flaps from a first position to a second position corresponding to the optimum flap setting in response to the selection of one of the plurality of flap settings using the flap control system.
Abstract translation: 用于优化飞机的翼片设置的系统可以包括翼片优化计算机，其配置成计算飞行器的一个或多个翼片的最佳翼片设置。 系统还可以包括通风地连接到翼片优化计算机的翼片控制系统。 翼片控制系统可操作以选择包括指定翼片设置的多个翼片设置中的任一个。 翼片控制系统可以被配置为响应于使用翼片控制系统选择多个翼片设置之一来自动地将一个或多个翼片从第一位置命令对应于最佳翼片设置的第二位置。
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公开(公告)号：US20150083853A1
公开(公告)日：2015-03-26
申请号：US14034946
申请日：2013-09-24
Applicant: THE BOEING COMPANY
Inventor： Matthew A. Moser , Michael R. Finn
IPC: B64C13/50
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.
Abstract translation: 用于飞行器的自适应后缘系统可以包括安装到后缘的自适应后缘元件。 具有电动机的电动机致动器可被配置为致动自适应后缘元件。 联动系统可以将电动机致动器耦合到自适应后缘元件以用于其致动。
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10.发明申请公开(公告)号：US20150083851A1
公开(公告)日：2015-03-26
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: B64C13/16
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。
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