-
公开(公告)号：US20240318744A1
公开(公告)日：2024-09-26
申请号：US18595889
申请日：2024-03-05
Applicant: The Boeing Company
Inventor： Paul Jeremy Maue , Dustin Henry Ramsey , Benjamin A. Johnson , Elaine Cheng Wright , John Everett Groat
CPC classification number: F16K37/0083 , F16K5/0647
Abstract: A valve assembly that controls a flow of fluid along a fluid line. The valve assembly includes a valve body sized to fit within the fluid line with the valve configured to rotate within the fluid line between an open position and a closed position. A drive shaft is connected to and extends outward from a first side of the valve body. An actuator is connected to the drive shaft and configured to rotate the valve between the open position and the closed position. A sensor is configured to sense a rotation position of the valve with the sensor positioned at a second side of the valve away from the actuator.
-
公开(公告)号：US10112724B2
公开(公告)日：2018-10-30
申请号：US14461886
申请日：2014-08-18
Applicant: The Boeing Company
Inventor： Michael E. Rorabaugh , James P. Irwin , Benjamin A. Johnson , Erik W. Dowell
Abstract: A hydraulic joint is disclosed. The hydraulic joint includes a tube, a hydraulic fitting, and a tip seal. The hydraulic fitting may be positioned around the tube. The hydraulic fitting may include a first open end for receiving the tube. The tip seal may be configured to define an opening that allows for the passage of leaks. The tip seal may be positioned on the hydraulic fitting adjacent the open end and forming a mechanical barrier between the fitting and the tube.
-
公开(公告)号：US20170291717A1
公开(公告)日：2017-10-12
申请号：US15633735
申请日：2017-06-26
Applicant: The Boeing Company
Abstract: A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. In one illustrative embodiment, an apparatus comprises a transport member. The transport member is configured for use in the fluid transport system. The transport member is comprised of a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member.
-
公开(公告)号：US09162774B2
公开(公告)日：2015-10-20
申请号：US13747780
申请日：2013-01-23
Applicant: The Boeing Company
CPC classification number: B64D45/02 , B60R16/06 , B63B43/00 , F16L9/14 , F16L21/065 , F16L25/01 , F16L25/025 , F16L25/026 , F17D1/00 , F17D5/08 , H05F1/00 , Y10T137/8593
Abstract: A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. The fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport system has an electrical configuration. The intensity of the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle is reduced to within selected tolerances by the electrical configuration of the fluid transport system.
Abstract translation: 一种用于降低在航空航天车辆的流体输送系统内发生的放电强度的方法和装置。 航空航天车辆运行。 航空航天车辆中的流体输送系统由选择的材料组成，使得流体输送系统具有电气结构。 通过流体输送系统的电气配置，在航空航天车辆的运行期间在流体输送系统内发生的放电强度降低到选定的公差内。
-
公开(公告)号：US20150091293A1
公开(公告)日：2015-04-02
申请号：US14461886
申请日：2014-08-18
Applicant: The Boeing Company
Inventor： Michael E. Rorabaugh , James P. Irwin, III , Benjamin A. Johnson , Erik W. Dowell
CPC classification number: B64D37/32 , B64D45/02 , F16L25/03 , Y10T29/49227 , Y10T137/0402
Abstract: A hydraulic joint is disclosed. The hydraulic joint includes a tube, a hydraulic fitting, and a tip seal. The hydraulic fitting may be positioned around the tube. The hydraulic fitting may include a first open end for receiving the tube. The tip seal may be configured to define an opening that allows for the passage of leaks. The tip seal may be positioned on the hydraulic fitting adjacent the open end and forming a mechanical barrier between the fitting and the tube.
Abstract translation: 公开了一种液压接头。 液压接头包括管，液压接头和末端密封。 液压配件可以围绕管定位。 液压配件可以包括用于接收管的第一开口端。 尖端密封件可以构造成限定允许泄漏通过的开口。 尖端密封件可以位于邻近开口端的液压配件上，并且在配件和管之间形成机械屏障。
-
Patent Agency Ranking
公开(公告)号：US09885434B2
公开(公告)日：2018-02-06
申请号：US14733158
申请日：2015-06-08
Applicant: The Boeing Company
Inventor： James P. Irwin , David W. Minteer , Benjamin A. Johnson , Erik W. Dowell
IPC: F16L19/00 , F16L19/028 , F16L5/06 , F16L5/08 , B64C1/10 , F16L5/12 , F16L19/02 , F16L23/028 , F16L23/12 , F16L23/22 , F16L25/02 , F16L23/036 , F16L23/18 , F16L57/04
CPC classification number: F16L19/0286 , B64C1/10 , F16L5/06 , F16L5/08 , F16L5/12 , F16L19/02 , F16L23/028 , F16L23/036 , F16L23/12 , F16L23/18 , F16L23/22 , F16L25/026 , F16L57/04 , F16L2201/40 , Y10T29/49826 , Y10T29/49948
Abstract: A method of making a bulkhead fitting assembly may include joining a tube to a thermal shell of a mounting flange, the mounting flange shaped to be attached to a bulkhead and including an adapter; forming the thermal shell to have a portion spaced away from the tube to form an air pocket between the tube and the thermal shell adjacent the mounting flange; and placing a bushing on the adapter such that the bushing completes a current path from the tube to the adapter, from the adapter to the bushing, and from the bushing to the bulkhead.
-
公开(公告)号：US20150267846A1
公开(公告)日：2015-09-24
申请号：US14733158
申请日：2015-06-08
Applicant: The Boeing Company
Inventor： James P. Irwin , David W. Minteer , Benjamin A. Johnson , Erik W. Dowell
IPC: F16L23/028 , F16L25/02 , F16L23/22 , F16L19/02 , F16L23/12
CPC classification number: F16L19/0286 , B64C1/10 , F16L5/06 , F16L5/08 , F16L5/12 , F16L19/02 , F16L23/028 , F16L23/036 , F16L23/12 , F16L23/18 , F16L23/22 , F16L25/026 , F16L57/04 , F16L2201/40 , Y10T29/49826 , Y10T29/49948
Abstract: A method of making a bulkhead fitting assembly may include joining a tube to a thermal shell of a mounting flange, the mounting flange shaped to be attached to a bulkhead and including an adapter; forming the thermal shell to have a portion spaced away from the tube to form an air pocket between the tube and the thermal shell adjacent the mounting flange; and placing a bushing on the adapter such that the bushing completes a current path from the tube to the adapter, from the adapter to the bushing, and from the bushing to the bulkhead.
Abstract translation: 制造隔板装配组件的方法可以包括将管连接到安装凸缘的热壳上，该安装凸缘成形为附接到隔板并且包括适配器; 形成热壳以具有与管间隔开的部分，以在管和邻近安装凸缘的热壳之间形成气穴; 并将衬套放置在适配器上，使得衬套完成从管到适配器的电流路径，从适配器到衬套，以及从套管到隔板。
-
公开(公告)号：US20150267845A1
公开(公告)日：2015-09-24
申请号：US14733179
申请日：2015-06-08
Applicant: The Boeing Company
Inventor： James P. Irwin , David W. Minteer , Benjamin A. Johnson , Erik W. Dowell
CPC classification number: F16L19/0286 , B64C1/10 , F16L5/06 , F16L5/08 , F16L5/12 , F16L19/02 , F16L23/028 , F16L23/036 , F16L23/12 , F16L23/18 , F16L23/22 , F16L25/026 , F16L57/04 , F16L2201/40 , Y10T29/49826 , Y10T29/49948
Abstract: A method of sealing an opening in a bulkhead with a fitting assembly having a tube, a mounting flange, a thermal shell, an adapter, a bushing, and a jam nut may include inserting the tube through the opening; placing the mounting flange against the bulkhead, the mounting flange attached to the thermal shell, the thermal shell attached to the tube, and the mounting flange attached to the adapter so that the adapter extends away from the mounting flange and from the thermal shell through the opening; forming an air pocket by spacing a portion of the thermal shell away from the tube; placing the bushing on the adapter; and tightening the jam nut on the adapter to sandwich the bulkhead between the mounting flange and the bushing to form a seal between the mounting flange and the bushing to seal the opening.
Abstract translation: 用具有管，安装凸缘，热壳，适配器，衬套和阻塞螺母的配件组件密封隔板中的开口的方法可包括将管插入开口; 将安装凸缘放置在隔板上，安装法兰附接到热壳，附接到管的热壳和连接到适配器的安装凸缘，使得适配器远离安装凸缘并从热壳延伸通过 开口 通过将热壳的一部分与管隔开来形成气穴; 将衬套放置在适配器上; 并将紧固螺母拧紧在适配器上以将隔板夹在安装法兰和衬套之间，以在安装凸缘和衬套之间形成密封，以密封开口。
-
公开(公告)号：US20130329333A1
公开(公告)日：2013-12-12
申请号：US13747780
申请日：2013-01-23
Applicant: THE BOEING COMPANY
IPC: H05F1/00
CPC classification number: B64D45/02 , B60R16/06 , B63B43/00 , F16L9/14 , F16L21/065 , F16L25/01 , F16L25/025 , F16L25/026 , F17D1/00 , F17D5/08 , H05F1/00 , Y10T137/8593
Abstract: A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. The fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport system has an electrical configuration. The intensity of the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle is reduced to within selected tolerances by the electrical configuration of the fluid transport system.
Abstract translation: 一种用于降低在航空航天车辆的流体输送系统内发生的放电强度的方法和装置。 航空航天车辆运行。 航空航天车辆中的流体输送系统由选择的材料组成，使得流体输送系统具有电气结构。 通过流体输送系统的电气配置，在航空航天车辆的运行期间在流体输送系统内发生的放电强度降低到选定的公差内。
-
公开(公告)号：US09688419B2
公开(公告)日：2017-06-27
申请号：US13747761
申请日：2013-01-23
Applicant: The Boeing Company
CPC classification number: B64D45/02 , B60R16/06 , B63B43/00 , F16L9/14 , F16L21/065 , F16L25/01 , F16L25/025 , F16L25/026 , F17D1/00 , F17D5/08 , H05F1/00 , Y10T137/8593
Abstract: A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. In one illustrative embodiment, an apparatus includes a transport member. The transport member is configured for use in the fluid transport system. The transport member includes a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member.
-
-
-
-
-
-
-
-
-
Search Results
14
records
(took 0.017 seconds)
