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公开(公告)号：US07493911B2
公开(公告)日：2009-02-24
申请号：US11150853
申请日：2005-06-10
IPC分类号： F16K23/00
CPC分类号： F16K1/22 , F16K27/0218 , F16K37/0066 , F16L39/005 , Y10T137/0318 , Y10T137/5762 , Y10T137/87153
摘要： A shrouded valve apparatus including an outer conduit, an inner conduit disposed within the outer conduit, and a valve member operable to regulate flow through the inner conduit. This apparatus is useful in shrouded aircraft fuel systems.
摘要翻译： 一种带盖的阀门装置，包括外部导管，设置在外部导管内部的内部导管，以及可操作以调节通过内部导管的流动的阀构件。 该装置在被覆盖的飞机燃料系统中是有用的。
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2.发明授权Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems 有权配有飞机燃油管路，燃油箱和其他系统的冗余密封件公开(公告)号：US07533850B2
公开(公告)日：2009-05-19
申请号：US11301131
申请日：2005-12-12
IPC分类号： B64D37/32
CPC分类号： B64D39/06 , F16L5/06 , F16L5/08 , F16L39/005 , F16L2201/30
摘要： Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems are disclosed. A fitting in accordance with one embodiment can be positioned adjacent to an aperture in a fuel tank wall having an inner surface and an outer surface. The fitting can include a first member having a flange and a barrel. The barrel can further include a passageway. A first flange seal can be positioned at a face of the flange and can be sealably coupled to a surface, for example, the tank wall. A second flange seal can be disposed outwardly from the first flange seal against the surface. The fitting can further include a second member (e.g., a sensor) positioned within the passageway of the barrel. The fitting can further include first and second barrel seals positioned between the barrel and the second member.
摘要翻译： 公开了具有用于飞机燃料管线，燃料箱和其它系统的冗余密封件的配件。 根据一个实施例的配件可以位于具有内表面和外表面的燃料箱壁中的孔附近。 配件可以包括具有凸缘和筒的第一构件。 枪管还可以包括通道。 第一凸缘密封件可以定位在凸缘的表面处，并且可以密封地联接到表面，例如罐壁。 第二凸缘密封件可以从第一凸缘密封件向外布置成抵靠表面。 配件还可以包括定位在筒的通道内的第二构件（例如，传感器）。 配件还可以包括位于筒和第二构件之间的第一和第二桶密封件。
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3.发明授权Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems 有权配有飞机燃油管路，燃油箱和其他系统的冗余密封件公开(公告)号：US08356842B2
公开(公告)日：2013-01-22
申请号：US12419970
申请日：2009-04-07
IPC分类号： F16L5/00
CPC分类号： B64D39/06 , F16L5/06 , F16L5/08 , F16L39/005 , F16L2201/30
摘要： Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems. A representative fitting includes a first member having a flange and a barrel. The barrel further includes a passageway. A first flange seal is positioned at a face of the flange and can be sealably coupled to a surface, for example, a tank wall. A second flange seal is disposed outwardly from the first flange seal to seal against the surface. The fitting further includes a second member positioned within the passageway of the barrel. The fitting further includes first and second barrel seals positioned between the barrel and the second member.
摘要翻译： 配有飞机燃油管路，燃油箱和其他系统的冗余密封件。 代表性的配件包括具有凸缘和桶的第一构件。 枪管还包括通道。 第一凸缘密封件定位在凸缘的表面处，并且可以密封地联接到表面，例如罐壁。 第二凸缘密封件从第一凸缘密封件向外设置以密封表面。 配件还包括位于筒的通道内的第二构件。 该配件还包括位于筒和第二构件之间的第一和第二桶密封件。
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4.发明申请Systems and Methods for Distributing Loads from Fluid Conduits, Including Aircraft Fuel Conduits 有权从流体管道，包括飞机燃油管道分配负载的系统和方法公开(公告)号：US20100024189A1
公开(公告)日：2010-02-04
申请号：US11768539
申请日：2007-06-26
IPC分类号： B23P11/00
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： 公开了用于从流体管道（包括飞机燃料管道）分配负载的系统和方法。 根据本发明的一个实施例构造的飞行器包括由机身部分和机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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5.发明申请FITTINGS WITH REDUNDANT SEALS FOR AIRCRAFT FUEL LINES, FUEL TANKS, AND OTHER SYSTEMS 有权配有飞机燃油管线，燃油箱和其他系统的冗余密封件公开(公告)号：US20090261583A1
公开(公告)日：2009-10-22
申请号：US12419970
申请日：2009-04-07
IPC分类号： F16L33/18
CPC分类号： B64D39/06 , F16L5/06 , F16L5/08 , F16L39/005 , F16L2201/30
摘要： Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems are disclosed. A fitting in accordance with one embodiment can be positioned adjacent to an aperture in a fuel tank wall having an inner surface and an outer surface. The fitting can include a first member having a flange and a barrel. The barrel can further include a passageway. A first flange seal can be positioned at a face of the flange and can be sealably coupled to a surface, for example, the tank wall. A second flange seal can be disposed outwardly from the first flange seal against the surface. The fitting can further include a second member (e.g., a sensor) positioned within the passageway of the barrel. The fitting can further include first and second barrel seals positioned between the barrel and the second member.
摘要翻译： 公开了具有用于飞机燃料管线，燃料箱和其它系统的冗余密封件的配件。 根据一个实施例的配件可以位于具有内表面和外表面的燃料箱壁中的孔附近。 配件可以包括具有凸缘和筒的第一构件。 枪管还可以包括通道。 第一凸缘密封件可以定位在凸缘的表面处，并且可以密封地联接到表面，例如罐壁。 第二凸缘密封件可以从第一凸缘密封件向外布置成抵靠表面。 配件还可以包括定位在筒的通道内的第二构件（例如，传感器）。 配件还可以包括位于筒和第二构件之间的第一和第二桶密封件。
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6.发明授权Systems 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：US07922122B2
公开(公告)日：2011-04-12
申请号：US11768539
申请日：2007-06-26
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. 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行器包括由机身部分和机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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7.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：US07581700B2
公开(公告)日：2009-09-01
申请号：US11440726
申请日：2006-05-24
IPC分类号： B64D39/06
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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8.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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9.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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10.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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