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公开(公告)号：US08701467B2
公开(公告)日：2014-04-22
申请号：US13041998
申请日：2011-03-07
申请人： James A. Carns , Theron L. Cutler , Mark A. Shelly
发明人： James A. Carns , Theron L. Cutler , Mark A. Shelly
IPC分类号： F16L55/00
CPC分类号： F16L23/167 , B64D37/005 , F16L23/003 , F16L39/005 , F16L2201/30 , G01M3/2815 , G01M3/283 , G01M3/2853
摘要： A leak detection feature for a fluid conduit. The leak detection feature facilitates the monitoring of fluid leaks at the interface of two adjoining conduit flange fittings. An embodiment of a flange fitting with a leak detection feature for a fluid conduit having an opening. The flange fitting includes a flange body around the opening of the fluid conduit, a leak detection passageway formed in the flange body, and a leak detection port formed in the flange body. The flange body has a sealing face surface configured to mate with a cooperating flange fitting, and the leak detection passageway terminates at the sealing face surface. The leak detection port is in fluid communication with the leak detection passageway, and the leak detection port is configured for fluid communication with a leak sensing apparatus.
摘要翻译： 流体导管的泄漏检测功能。 泄漏检测功能有助于监测两个邻接管道法兰接头的接口处的流体泄漏。 具有用于具有开口的流体导管的泄漏检测特征的凸缘的实施例。 凸缘配件包括围绕流体导管的开口的凸缘体，形成在凸缘体中的泄漏检测通道和形成在凸缘体中的泄漏检测口。 所述凸缘体具有密封面表面，所述密封面表面被配置为与配合的凸缘配件配合，并且所述泄漏检测通道在所述密封面表面处终止。 泄漏检测口与泄漏检测通路流体连通，泄漏检测口配置为与泄漏检测装置进行流体连通。
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公开(公告)号：US20130068889A1
公开(公告)日：2013-03-21
申请号：US13238800
申请日：2011-09-21
IPC分类号： B64D39/00
摘要： A refueling boom is described. The refueling boom includes a non-telescoping portion configured to be coupled to a fuel tanker vehicle and a telescoping portion that is extendable and retractable relative to the non-telescoping portion. The telescoping portion includes a fuel nozzle. The refueling boom also includes a wireless communication system operable to enable wireless communication between a first location of the telescoping portion to a second location of the non-telescoping portion. The refueling boom also includes a control unit coupled to the telescoping portion. The control unit is operable to send first information to the fuel tanker vehicle via the wireless communication system and to receive second information from the fuel tanker vehicle via the wireless communication system.
摘要翻译： 描述了加油繁荣。 加油吊杆包括非伸缩部分，该非伸缩部分构造成联接到燃料油罐车辆和可相对于非伸缩部分可伸缩的伸缩部分。 伸缩部分包括燃料喷嘴。 加油吊杆还包括无线通信系统，其可操作以实现伸缩部分的第一位置与非伸缩部分的第二位置之间的无线通信。 加油斗还包括耦合到伸缩部分的控制单元。 控制单元可操作以经由无线通信系统向燃料油罐车辆发送第一信息，并且经由无线通信系统从燃料油罐车辆接收第二信息。
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3.发明授权Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods 有权用于将支撑构件附接到流体管道的可调配件，包括飞机燃料管道以及相关的系统和方法公开(公告)号：US07946038B2
公开(公告)日：2011-05-24
申请号：US12538727
申请日：2009-08-10
IPC分类号： B21D51/16
CPC分类号： F16L3/1226 , B64D39/06 , Y10T29/494 , Y10T29/49826
摘要： Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, are disclosed herein. An aircraft system in accordance with one embodiment of the invention includes a fluid conduit carried by an aircraft and a housing fixedly attached to the fluid conduit. The housing can include a first attachment feature having one of a projection extending outwardly from the housing or an aperture extending at least partially through the housing. The system further includes a support member having an attachment portion positioned proximate to the attachment feature. The attachment portion includes a support member aperture positioned over at least a portion of the first attachment feature. An adjustable fitting couples the support member to the housing. The adjustable fitting can include a first side, a second side opposite the first side, and an engagement portion at the second side positioned within at least a portion of the support member aperture. The fitting can also include a second attachment feature mated with the first attachment feature. The second attachment feature includes the other one of the projection or the aperture. The second attachment feature has a center point eccentrically offset from a center point of the fitting.
摘要翻译： 本文公开了用于将支撑构件附接到流体导管（包括飞机燃料管道）的可调节配件。 根据本发明的一个实施例的飞行器系统包括由飞行器承载的流体导管和固定地连接到流体导管的壳体。 壳体可以包括第一附接特征，其具有从壳体向外延伸的突出部或至少部分延伸穿过壳体的孔。 该系统还包括具有靠近附接特征定位的附接部分的支撑构件。 附接部分包括位于第一附接特征的至少一部分上的支撑构件孔。 可调整的配件将支撑构件连接到壳体。 可调配合件可以包括第一侧，与第一侧相对的第二侧，以及位于支撑构件孔的至少一部分内的位于第二侧的接合部。 配件还可以包括与第一附接特征配合的第二附件特征。 第二附件特征包括另一个投影或光圈。 第二附件特征具有偏离配件中心点偏心的中心点。
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公开(公告)号：US07942452B2
公开(公告)日：2011-05-17
申请号：US11943460
申请日：2007-11-20
申请人： James A. Carns , Theron L. Cutler , Mark A. Shelly
发明人： James A. Carns , Theron L. Cutler , Mark A. Shelly
IPC分类号： F16L55/00
CPC分类号： F16L23/167 , B64D37/005 , F16L23/003 , F16L39/005 , F16L2201/30 , G01M3/2815 , G01M3/283 , G01M3/2853
摘要： A leak detection feature for a fluid conduit. The leak detection feature facilitates the monitoring of fluid leaks at the interface of two adjoining conduit flange fittings. An embodiment of a flange fitting with a leak detection feature for a fluid conduit having an opening. The flange fitting includes a flange body around the opening of the fluid conduit, a leak detection passageway formed in the flange body, and a leak detection port formed in the flange body. The flange body has a sealing face surface configured to mate with a cooperating flange fitting, and the leak detection passageway terminates at the sealing face surface. The leak detection port is in fluid communication with the leak detection passageway, and the leak detection port is configured for fluid communication with a leak sensing apparatus.
摘要翻译： 流体导管的泄漏检测功能。 泄漏检测功能有助于监测两个邻接管道法兰接头的接口处的流体泄漏。 具有用于具有开口的流体导管的泄漏检测特征的凸缘的实施例。 凸缘配件包括围绕流体导管的开口的凸缘体，形成在凸缘体中的泄漏检测通道和形成在凸缘体中的泄漏检测口。 所述凸缘体具有密封面表面，所述密封面表面被配置为与配合的凸缘配件配合，并且所述泄漏检测通道在所述密封面表面处终止。 泄漏检测口与泄漏检测通路流体连通，泄漏检测口配置为与泄漏检测装置进行流体连通。
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5.发明申请ADJUSTABLE FITTINGS FOR ATTACHING SUPPORT MEMBERS TO FLUID CONDUITS, INCLUDING AIRCRAFT FUEL CONDUITS, AND ASSOCIATED SYSTEMS AND METHODS 有权用于连接支持会员的可调节配件，用于流体流量，包括飞机燃料流量和相关系统和方法公开(公告)号：US20090293256A1
公开(公告)日：2009-12-03
申请号：US12538727
申请日：2009-08-10
IPC分类号： B23P11/00
CPC分类号： F16L3/1226 , B64D39/06 , Y10T29/494 , Y10T29/49826
摘要： Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, are disclosed herein. An aircraft system in accordance with one embodiment of the invention includes a fluid conduit carried by an aircraft and a housing fixedly attached to the fluid conduit. The housing can include a first attachment feature having one of a projection extending outwardly from the housing or an aperture extending at least partially through the housing. The system further includes a support member having an attachment portion positioned proximate to the attachment feature. The attachment portion includes a support member aperture positioned over at least a portion of the first attachment feature. An adjustable fitting couples the support member to the housing. The adjustable fitting can include a first side, a second side opposite the first side, and an engagement portion at the second side positioned within at least a portion of the support member aperture. The fitting can also include a second attachment feature mated with the first attachment feature. The second attachment feature includes the other one of the projection or the aperture. The second attachment feature has a center point eccentrically offset from a center point of the fitting.
摘要翻译： 本文公开了用于将支撑构件附接到流体导管（包括飞机燃料管道）的可调节配件。 根据本发明的一个实施例的飞行器系统包括由飞行器承载的流体导管和固定地连接到流体导管的壳体。 壳体可以包括第一附接特征，其具有从壳体向外延伸的突出部或至少部分延伸穿过壳体的孔。 该系统还包括具有靠近附接特征定位的附接部分的支撑构件。 附接部分包括位于第一附接特征的至少一部分上的支撑构件孔。 可调整的配件将支撑构件连接到壳体。 可调配合件可以包括第一侧，与第一侧相对的第二侧，以及位于支撑构件孔的至少一部分内的位于第二侧的接合部。 配件还可以包括与第一附接特征配合的第二附件特征。 第二附件特征包括另一个投影或光圈。 第二附件特征具有偏离配件中心点偏心的中心点。
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公开(公告)号：US07437952B2
公开(公告)日：2008-10-21
申请号：US11450925
申请日：2006-06-09
申请人： James A Carns , Theron L Cutler , Mark A Shelly
发明人： James A Carns , Theron L Cutler , Mark A Shelly
CPC分类号： G01F1/10 , G01F1/115 , G01F15/14 , G01F15/185 , G01N9/24
摘要： A shrouded body flow meter assembly includes an inner fluid-conducting conduit disposed in a spaced relation from and within an outer conduit. The shrouded flow meter assembly can be connected to other shrouded fluid-conducting apparatus and/or used to replace sections of a shrouded fluid-conducting apparatus system. The shrouded flow meter assembly maintains the integrity of the inner fluid-conducting conduits and outer conduits of the shrouded fluid-conducting apparatus.
摘要翻译： 被覆盖的身体流量计组件包括以与外导管间隔开的关系设置的内部流体导管。 被覆盖的流量计组件可以连接到其它被覆盖的流体传导装置和/或用于替换被覆盖的流体传导装置系统的部分。 被覆盖的流量计组件保持被覆盖的流体传导装置的内部导流管道和外部导管的完整性。
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7.发明授权System and methods for distributing loads from fluid conduits, including aircraft fuel conduits 有权用于从流体管道（包括飞机燃料管道）分配载荷的系统和方法公开(公告)号：US07293741B2
公开(公告)日：2007-11-13
申请号：US11150005
申请日：2005-06-09
IPC分类号： B64D39/00
CPC分类号： F16L3/00 , B64D39/06 , Y10T29/49826
摘要： Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits, are disclosed. An aircraft configured in accordance with one embodiment of the invention includes a fuselage portion, a wing portion, and a fuel tank carried by least one of the fuselage portion and the wing portion. The aircraft also includes a spar carried by at least one of the fuselage portion and the wing portion. The spar includes a first spar rib and a second spar rib spaced apart from the first spar rib. The aircraft further includes a fluid conduit proximate to the spar and operably coupled to the fuel tank. A support member carrying the fluid conduit is operably coupled to the spar. The support member can be positioned to transfer at least approximately all of the axial loads from the fluid conduit to at least one of the first spar rib and the second spar rib.
摘要翻译： 用于从流体管道（包括飞机燃料管道）分配载荷的系统和方法。 根据本发明的一个实施例构造的飞机包括由机身部分和翼部分中的至少一个承载的机身部分，翼部分和燃料箱。 飞机还包括由机身部分和机翼部分中的至少一个承载的翼梁。 翼梁包括与第一翼梁相隔开的第一翼梁和第二翼梁。 飞机还包括靠近翼梁的流体导管并且可操作地联接到燃料箱。 承载流体导管的支撑构件可操作地联接到翼梁。 支撑构件可以被定位成将来自流体导管的至少几乎所有轴向载荷传递到第一翼梁肋和第二翼梁中的至少一个。
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8.发明授权Valves for annular conduits including aircraft fuel conduits and associated systems and methods 有权用于环形导管的阀，包括飞机燃料管道及相关系统和方法公开(公告)号：US07213787B2
公开(公告)日：2007-05-08
申请号：US11147138
申请日：2005-06-07
IPC分类号： B64D37/02
CPC分类号： B64D39/06 , F16L3/1222 , F16L39/005 , F16L2201/30
摘要： Valves for annular conduits and associated systems and methods are disclosed. A fluid transmission system in accordance with one embodiment of the invention includes a first conduit having a first wall aligned with a flow direction in the first conduit and a second conduit disposed annularly around the first conduit with a second wall aligned with the flow direction. An access channel can be positioned to have an aperture in fluid communication with the first conduit and can be isolated from fluid communication with the second conduit. A valve element can be positioned in fluid communication with the access channel and can be movable between a first position and a second position, with the valve element being positioned to allow a first amount of flow through the access channel when in the first position and being positioned to allow no flow or a second amount of flow less than the first amount of flow through the access channel when in the second position. The valve can be installed in aircraft fuel lines or other systems.
摘要翻译： 公开了用于环形导管和相关系统和方法的阀。 根据本发明的一个实施例的流体传动系统包括第一管道，其具有与第一管道中的流动方向对准的第一壁和围绕第一管道设置的第二管道，第二管道具有与流动方向对准的第二壁。 进入通道可以被定位成具有与第一管道流体连通的孔，并且可以与第二管道的流体连通隔离。 阀元件可以定位成与进入通道流体连通，并且可以在第一位置和第二位置之间移动，其中阀元件被定位成允许在处于第一位置时通过进入通道的第一量的流量 定位成当处于第二位置时不允许流过或接近通道的第一流量小于第一流量。 阀门可以安装在飞机燃油管路或其他系统中。
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公开(公告)号：US08505761B2
公开(公告)日：2013-08-13
申请号：US13007159
申请日：2011-01-14
申请人： Tracy L Tweet , Mark A Shelly
发明人： Tracy L Tweet , Mark A Shelly
IPC分类号： F17C1/00
CPC分类号： B64D37/32 , B64D37/06 , Y10T29/49822 , Y10T29/49826
摘要： Apparatus and methods are provided to minimize the escape of fuel out of a fuel tank when a tank wall is penetrated by a bullet. In one embodiment, a pressure differential may be maintained between a pressure within a fuel tank cavity and another pressure outside the fuel tank cavity in order to minimize the loss of fuel upon penetration of the fuel tank. In another embodiment, a compressed rubber layer of fuel-reactive rubber may be provided which is adapted to be attached to a fuel tank wall and to swell upon contact with fuel in order to substantially seal a penetrated hole in the fuel tank wall.
摘要翻译： 提供了装置和方法，以便当罐壁被子弹穿透时，将燃料从燃料箱排出的最小化。 在一个实施例中，可以在燃料箱腔内的压力和燃料箱腔外部的另一个压力之间保持压力差，以便最小化燃料箱穿透时的燃料损失。 在另一个实施例中，可以提供燃料反应性橡胶的压缩橡胶层，其适于附接到燃料箱壁并且在与燃料接触时膨胀以便基本上密封燃料箱壁中的穿透孔。
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公开(公告)号：US08485474B2
公开(公告)日：2013-07-16
申请号：US12872696
申请日：2010-08-31
申请人： Lance A. Cutler , Mark A. Shelly
发明人： Lance A. Cutler , Mark A. Shelly
IPC分类号： B64D39/00
摘要： Apparatus and methods described herein provide for a boom/receiver-type aerial refueling system having a pressure regulator integrated into the system at the tanker boom nozzle. During refueling operations, pressure of the fuel at the interface between the nozzle at the distal end of the boom assembly and the fuel receptacle of the receiving aircraft is maintained by an integrated pressure regulator integrated into the nozzle or located inline of the fuel flow between the boom assembly and the nozzle. The integrated pressure regulator maintains the pressure of the fuel at the nozzle within a defined range regardless of the elevation azimuth of the boom assembly, the extended length of the telescoping extension, the temperature of the outside air or surfaces of the boom, and other factors that may affect the flow of fuel through the boom.
摘要翻译： 本文所述的装置和方法提供了一种具有在油罐吊杆喷嘴处集成到系统中的压力调节器的起重臂/接收器型空中加油系统。 在加油操作期间，在悬臂组件的远端处的喷嘴与接收飞机的燃料接收器之间的界面处的燃料的压力由集成在喷嘴中的集成的压力调节器维持，或者位于燃料流的位置之间 起重臂总成和喷嘴。 集成式压力调节器将喷嘴处的燃料压力保持在规定范围内，而不管吊臂组件的仰角方向，伸缩长度，伸缩长度，外部空气或悬臂表面的温度等因素 这可能会影响通过吊臂的燃料流。
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