公开(公告)号：US20140224782A1

公开(公告)日：2014-08-14

申请号：US13763706

申请日：2013-02-10

Applicant: The Boeing Company

Inventor： Paul S. Nordman ,  Richard J. Loftis ,  Andy Armatorio

IPC: H05B3/00

CPC classification number: H05B3/22 ,  B32B3/30 ,  B32B9/005 ,  B32B9/041 ,  B32B9/045 ,  B32B15/18 ,  B32B15/20 ,  B32B27/38 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2307/202 ,  B32B2307/206 ,  B32B2307/718 ,  B32B2605/18 ,  B64D15/12 ,  H05B2214/02 ,  Y10T29/49826

Abstract: A structural substrate for an aircraft structure and methods are presented. A multi-layer hybrid composite material comprises an outermost layer, an intermediate layer, and an innermost layer. The outermost layer comprises an electrically conductive metal matrix composite that conducts electricity to provide electric heating. The intermediate layer comprises an electrical insulator coupled to the outermost layer. The innermost layer comprises a composite coupled to the intermediate layer. The intermediate layer electrically insulates the outermost layer from the innermost layer.

Abstract translation: 提出了一种飞机结构和方法的结构基板。 多层混合复合材料包括最外层，中间层和最内层。 最外层包括传导电力以提供电加热的导电金属基质复合材料。 中间层包括耦合到最外层的电绝缘体。 最内层包括耦合到中间层的复合体。 中间层将最外层与最内层电绝缘。

公开(公告)号：US09253823B2

公开(公告)日：2016-02-02

申请号：US13763706

申请日：2013-02-10

Applicant: The Boeing Company

Inventor： Paul S. Nordman ,  Richard J. Loftis ,  Andy Armatorio

IPC: B60L1/02 ,  H05B3/22 ,  B64D15/12 ,  B32B9/00 ,  B32B9/04 ,  B32B15/18 ,  B32B15/20 ,  B32B27/38 ,  B32B3/30

CPC classification number: H05B3/22 ,  B32B3/30 ,  B32B9/005 ,  B32B9/041 ,  B32B9/045 ,  B32B15/18 ,  B32B15/20 ,  B32B27/38 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2307/202 ,  B32B2307/206 ,  B32B2307/718 ,  B32B2605/18 ,  B64D15/12 ,  H05B2214/02 ,  Y10T29/49826

Abstract: A structural substrate for an aircraft structure and methods are presented. A multi-layer hybrid composite material comprises an outermost layer, an intermediate layer, and an innermost layer. The outermost layer comprises an electrically conductive metal matrix composite that conducts electricity to provide electric heating. The intermediate layer comprises an electrical insulator coupled to the outermost layer. The innermost layer comprises a composite coupled to the intermediate layer. The intermediate layer electrically insulates the outermost layer from the innermost layer.

Abstract translation: 提出了一种飞机结构和方法的结构基板。 多层混合复合材料包括最外层，中间层和最内层。 最外层包括传导电力以提供电加热的导电金属基质复合材料。 中间层包括耦合到最外层的电绝缘体。 最内层包括耦合到中间层的复合体。 中间层将最外层与最内层电绝缘。

公开(公告)号：US20210392317A1

公开(公告)日：2021-12-16

申请号：US17038493

申请日：2020-09-30

Applicant: The Boeing Company

Inventor： Andy Armatorio ,  Richard J. Loftis ,  Gary A. Ray ,  Tuan A. Nguyen ,  Robert P. Higgins

IPC: H04N13/246 ,  H04N13/243 ,  G08G5/00 ,  G06T7/593 ,  H04N13/239 ,  G08G5/04 ,  G06T7/32 ,  G06K9/00 ,  B64D47/08

Abstract: An aircraft includes a fuselage, a first wing coupled to the fuselage and including a first wingtip that is movable relative to the fuselage during flight, and a second wing coupled to the fuselage, opposite the first wing, and including a second wingtip that is movable relative to the fuselage and relative to the first wingtip during flight. The aircraft also includes a first camera mounted to the first wingtip of the first wing and a second camera mounted to the second wingtip of the second wing. The aircraft further includes a processing unit configured to determine a real-time distance between the first camera and the second camera as the first camera and the second camera move relative to each other and relative to the fuselage during flight.

公开(公告)号：US20180091797A1

公开(公告)日：2018-03-29

申请号：US15277411

申请日：2016-09-27

Applicant: The Boeing Company

Inventor： Andy Armatorio ,  Richard J. Loftis ,  Gary A. Ray ,  Tuan A. Nguyen ,  Robert P. Higgins

IPC: H04N13/02 ,  G06T7/00 ,  G06T7/20 ,  B64D47/08

CPC classification number: H04N13/246 ,  B64D45/08 ,  B64D47/08 ,  G06K9/0063 ,  G06K9/00805 ,  G06T7/32 ,  G06T7/593 ,  G06T2207/10012 ,  G06T2207/10024 ,  G06T2207/10032 ,  G06T2207/30252 ,  G06T2207/30261 ,  G08G5/0021 ,  G08G5/0078 ,  G08G5/045 ,  H04N13/239 ,  H04N13/243

Abstract: A method is provided of compensating for variations in distance and orientation between first and second wing-mounted cameras of an aircraft due to flexing of at least one aircraft wing. The method comprises determining a first distance and orientation between the first wing-mounted camera and the second wing-mounted camera during a neutral wing condition of the aircraft. The method further comprises determining a second distance and orientation between the first wing-mounted camera and the second wing-mounted camera during a flexed wing condition of the aircraft. The method also comprises processing the difference between the first and second distances and orientations to provide a real-time varying distance and orientation for use in providing a compensated distance between the first and second wing-mounted cameras.