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41. 发明申请

US20170167390A1 FUEL CONTROL SYSTEM 审中-公开
公开(公告)号：US20170167390A1
公开(公告)日：2017-06-15
申请号：US14965265
申请日：2015-12-10
申请人： Hamilton Sundstrand Corporation
发明人： Todd Haugsjaahabink
IPC分类号： F02C9/28 , F02C9/46 , F02C9/26 , F02C9/52 , F16K11/06 , B64D37/00
CPC分类号： F02C9/28 , B64D37/00 , F02C7/232 , F02C9/263 , F02C9/46 , F02C9/52 , F05D2220/323 , F05D2260/606 , F16K11/06
摘要： A bypass valve for a fuel control includes a sleeve, a spool, and a biasing member. The sleeve has a body extending between a first end and a second. The first end defines a first bypass valve port. The body defines a second bypass valve port, a third bypass valve port, and a shutoff port. The second end defines a fourth bypass valve port. The spool is received within the inner bore and is movable between a first position and a second position. The biasing member biases the spool toward the first position.

42. 发明授权

US09645004B2 Optical impedance modulation for fuel quantity measurement comprising a fiber encased by a tube having a longitudinal slot with a lens 有权
公开(公告)号：US09645004B2
公开(公告)日：2017-05-09
申请号：US14547828
申请日：2014-11-19
申请人： The Boeing Company
发明人： Tuong K. Truong , Dennis G. Koshinz , Eric Y. Chan , Todd C. Thomas , J. Everett Groat , Sigvard J. Wahlin , John L. Vento , Sham S. Hariram , Richard J. Nesting
IPC分类号： G01F23/292 , G01F22/00 , B64D37/00
CPC分类号： G01F23/292 , B64D37/005 , G01F22/00 , Y02T50/44
摘要： Systems and methods that use an optical impedance sensor that eliminates electricity for measuring fuel quantity in fuel tanks. The optical impedance sensor comprises two optical fibers spaced apart inside a meniscus tube, one to transmit light along its length and the other to receive light along its length. The meniscus tube minimizes the sloshing of fuel level. The fuel level in the tank modulates the optical impedance between the two optical fibers, resulting in changes in the total light received by an optical detector. Depending on fuel tank height, the optical impedance sensor may comprise different embodiments in which the detection apparatus shapes the light to be unidirectional (emitted and collected only on one side of the fiber) or omnidirectional (all directions).

43. 发明授权

US09630722B2 Support for routing conduits in an aircraft wing 有权
公开(公告)号：US09630722B2
公开(公告)日：2017-04-25
申请号：US13895731
申请日：2013-05-16
申请人： AIRBUS OPERATIONS (SAS)
发明人： Damien Fraysse , Christophe Casse
IPC分类号： B64D37/00 , F16L5/12 , F16L27/10 , F16L27/113 , B64C3/34
CPC分类号： B64D37/00 , B64C3/34 , B64D37/005 , F16L5/12 , F16L27/1021 , F16L27/113
摘要： A routing support (64) for a conduit line fastened in openings and the line includes a plurality of conduits connected end-to-end along a longitudinal axis. The routing support (64) incorporates an outer body (66) with a structure (68) for fastening the body in an opening. The routing support also includes a housing structure to accommodate the ends of two conduits in an end-to-end arrangement and the structure may include two separate structures (one for each conduit end (72)) or a single common structure (accommodating respective ends of the two conduits). The routing support also includes a flexible interface (74) connecting the housing structure (70) to the outer body (66). In addition, the flexible interface (74) and the outer body (66) and the housing structure (70) are integral. Embodiments include a line for transporting fuel with this routing support, and an aircraft wing in which such a line/support transports fuel.

44. 发明申请

US20170037856A1 INTEGRAL PUMP PRESSURE RELIEF VALVE 审中-公开
标题翻译：整体泵压力消除阀
公开(公告)号：US20170037856A1
公开(公告)日：2017-02-09
申请号：US15211244
申请日：2016-07-15
申请人： Parker-Hannifin Corporation
发明人： Thomas Sailer , David Jonathan Sandy
IPC分类号： F04D15/00 , F04D7/02 , B64D37/00 , F04D29/22 , F04D29/42 , F04D1/02 , F04D13/02
摘要： A fuel pump includes a cartridge removably received within a canister. The cartridge includes a motor assembly, and a pump assembly that includes a centrifugal pumping element and outlet porting from the centrifugal pumping element. The motor drives the centrifugal pumping element to generate a flow of fluid through a main flow pathway between a pump inlet and outlet through the outlet porting of the pump assembly. The cartridge further includes a pressure relief valve that is movable between a closed position and an open position, and defines a pressure relief flow pathway integrally within the cartridge from the outlet porting to inlet porting of the centrifugal pumping element. When pressure within the pump assembly exceeds a threshold pressure, the pressure relief valve moves from the closed position to the open position to permit a relief flow of fluid through the relief flow pathway. The fuel pump may be employed as part of an aircraft fuel system.
摘要翻译：燃料泵包括可移除地容纳在罐内的盒。该墨盒包括马达组件和泵组件，其包括离心泵送元件和离心泵送元件的出口。电动机驱动离心泵送元件以通过泵组件的出口端口产生通过泵入口和出口之间的主流动路径的流体流。所述筒还包括可在关闭位置和打开位置之间移动的压力释放阀，并且限定了从所述离心泵送元件的出口至入口端口的所述筒内的压力释放流动通路。当泵组件内的压力超过阈值压力时，压力释放阀从关闭位置移动到打开位置，以允许流体通过释放流动通道释放流动。燃料泵可以用作飞行器燃料系统的一部分。

45. 发明申请

US20160312938A1 LEVER QUICK CONNECT INTERCOM FITTING 有权
标题翻译： LEVER快速连接对讲机配件
公开(公告)号：US20160312938A1
公开(公告)日：2016-10-27
申请号：US15202596
申请日：2016-07-06
申请人： Zodiac Aerosafety Systems
发明人： Amine Sannadi , Nicolas Picco
IPC分类号： F16L37/12 , B64D37/00 , F16L37/18
CPC分类号： F16L37/12 , B64D37/005 , F16L37/18
摘要： Embodiments of the present invention provide a lever quick connect and disconnect fitting that provides a secure fit for tank-to-tank connections and prevents any leakage from occurring. The fitting provide two separate, independent locking features that can secure tank sleeves to one another. There is provided male and female components that are coupled together by a lever connect and by a safety ring.
摘要翻译：本发明的实施例提供了一种杠杆快速连接和断开配件，其提供了罐到罐连接的牢固配合，并防止发生任何泄漏。配件提供两个独立的独立锁定功能，可以将油箱套筒彼此固定。提供通过杠杆连接和安全环联接在一起的阳和阴部件。

46. 发明授权

US09416801B2 Ventilated drainage system 有权
标题翻译：通风排水系统
公开(公告)号：US09416801B2
公开(公告)日：2016-08-16
申请号：US14302676
申请日：2014-06-12
申请人： The Boeing Company
发明人： Robert Henry Willie , David F. Cerra
IPC分类号： F15D1/00 , B64D29/00 , B64D37/00 , B64C1/14 , B64D37/26 , F01D25/32
CPC分类号： F15D1/001 , B64C1/1453 , B64D29/00 , B64D37/005 , B64D37/26 , F01D25/32 , F02K1/82 , F05D2260/602 , F15D1/008 , Y02T50/672 , Y10T137/0391 , Y10T137/2082
摘要： A method and apparatus for draining fluid from a structure on an aircraft. The apparatus comprises a drainage tube, a housing, a number of inlet holes in the housing, and a number of outlet holes in the housing. The drainage tube has first end that connects to a structure on an aircraft and a second end opposite the first end. The housing connects to the structure. The drainage tube is located within the housing. Air flows into the housing during flight of the aircraft through the number of inlet holes in the housing. The air flows out of the housing during flight of the aircraft through the number of outlet holes. The air flowing into the housing through the number of inlet holes and out the housing through the number of outlet holes directs fluid out of the drainage tube and away from the structure during flight of the aircraft.
摘要翻译：一种用于从飞机上的结构排出流体的方法和装置。该装置包括排水管，壳体，壳体中的多个入口孔以及壳体中的多个出口孔。排水管具有连接到飞机上的结构的第一端和与第一端相对的第二端。外壳连接到结构。引流管位于外壳内。在飞行器飞行期间，空气通过壳体中的入口孔数进入壳体。在飞行器飞行期间，空气通过出口孔流出外壳。通过多个入口孔流入壳体的空气通过出口孔排出壳体，在飞行器飞行期间将流体引导出排水管并远离结构。

47. 发明授权

US09399510B2 Hat stringer closeout fitting and method of making same 有权
标题翻译：帽子纵梁配合及其制作方法
公开(公告)号：US09399510B2
公开(公告)日：2016-07-26
申请号：US14464098
申请日：2014-08-20
申请人： The Boeing Company
发明人： Corey A. Rolfes , Jeffrey F. Stulc
IPC分类号： B64C3/00 , B64C3/18 , B64C3/34 , B64D37/00 , B64D37/04 , B64D37/10
CPC分类号： B64C3/182 , B64C3/34 , B64D37/005 , B64D37/04 , B64D37/10
摘要： A closeout fitting for a hat stringer includes a cover that has a fitting surface. The fitting surface is substantially complementary to at least a portion of an outer surface of the hat stringer. The cover is configured to couple against the hat stringer outer surface. The cover also includes a first portion configured to extend across a gap defined in a cap portion of the hat stringer. The closeout fitting also includes an insert. The insert includes a first outer perimeter surface that is substantially complementary to at least a portion of an interior surface of a channel defined by the hat stringer. The insert is configured to couple against the channel interior surface proximate the hat stringer closeout portion. The insert and the cover are formed with a suitable stiffness to limit a deformation of the hat stringer proximate the closeout portion.
摘要翻译：用于帽子纵梁的封闭装置包括具有配合表面的盖。配合表面与帽子纵梁的外表面的至少一部分基本互补。盖子被配置成与帽子纵梁外表面联接。盖子还包括构造成延伸穿过限定在帽子纵梁的帽部分中的间隙的第一部分。封闭件还包括插入件。该插入件包括第一外周表面，该第一外周表面与由帽子纵梁限定的通道的内表面的至少一部分基本互补。插入件被配置为在靠近帽子纵梁关闭部分的情况下联接到通道内表面。插入件和盖子形成有适当的刚度，以限制靠近封闭部分的帽子纵梁的变形。

48. 发明申请

US20160153568A1 Electromagnetic Valve for High-Pressure Cryogenic Gas 有权
标题翻译：高压低温气体电磁阀
公开(公告)号：US20160153568A1
公开(公告)日：2016-06-02
申请号：US14839271
申请日：2015-08-28
申请人： Techspace Aero S.A.
发明人： Bernard Siméon , Cédric Frippiat , Olivier Dellis , Antoine Delille
IPC分类号： F16K11/056 , F16K31/06 , B64G1/40 , F16K1/36 , F16K1/52 , B64D37/00 , F16K1/14 , F16K31/10
CPC分类号： F16K11/056 , F16K1/14 , F16K11/161 , F16K31/0606 , F16K31/0631 , F16K31/082
摘要： The present application relates to an electromagnetic valve, in particular for high-pressure cryogenic gas for a rocket. The valve includes a body in which a passage is formed connecting an inlet to an outlet, a seat communicating with the passage, a ball sealing the seat when the valve is at rest, a magnetic circuit with a coil, a magnetic shell, and a plunger displacing the ball relative to the seat thereof in order to open and/or close the seat. The plunger is telescopic, i.e., extendable and retractable. The plunger includes two ferromagnetic portions that are movable relative to one another and relative to the passage. The portions are fitted one inside the other and define air gaps E2 and E3 therebetween. The valve includes a magnet and a spring on either side of a secondary portion to hold the secondary portion in the closed position, distancing a ball from the exhaust seat.
摘要翻译：本申请涉及电磁阀，特别是用于火箭的高压低温气体。该阀包括：主体，其中形成有将入口连接到出口的通道，与通道连通的座，当阀静止时密封座的球，具有线圈的磁路，磁性壳和柱塞相对于其座位移动球以便打开和/或关闭座椅。柱塞是可伸缩的，即可伸缩的。柱塞包括可相对于彼此并相对于通道移动的两个铁磁部分。这些部分一个安装在另一个内部并且在它们之间限定气隙E2和E3。该阀包括一个磁体和一个在次级部分两侧的弹簧，以将次级部分保持在关闭位置，使球与排气座隔开。

49. 发明授权

US09340279B2 Fluid transfer chamber for aircraft fluid transmission lines 有权
标题翻译：用于飞机流体传输线的流体传送室
公开(公告)号：US09340279B2
公开(公告)日：2016-05-17
申请号：US14267160
申请日：2014-05-01
申请人： Bell Helicopter Textron Inc.
发明人： Joseph Leachman
IPC分类号： B64D37/02 , B64C17/10 , B64D37/00
CPC分类号： B64C17/10 , B64C1/1453 , B64D37/00 , B64D37/005 , B64D37/32 , F16L55/07 , Y02T50/44 , Y10T137/6906
摘要： One example of an aircraft fuel transfer chamber includes a chamber housing including a first sub-chamber defining a first inlet to be connected to an outer tube of a first aircraft fuel line assembly. The first sub-chamber receives fuel leaked into the outer tube of the first aircraft fuel line assembly from an inner tube of the first aircraft fuel line assembly. The chamber housing also includes a second sub-chamber connected to the first sub-chamber, the second sub-chamber defining a second inlet to be connected to an outer tube of a second aircraft fuel line assembly. The second sub-chamber receives fuel leaked into the outer tube of the second aircraft fuel line assembly from an inner tube of the second aircraft fuel line assembly. The chamber housing defines an outlet connected to the first inlet and the second inlet to transfer leaked fuel toward a drain of the aircraft.
摘要翻译：飞机燃料传递室的一个示例包括腔室壳体，其包括限定要连接到第一飞行器燃料管路组件的外管的第一入口的第一子室。第一子室从第一飞行器燃料管路组件的内管接收从第一飞行器燃料管路组件的外管泄漏的燃料。腔室壳体还包括连接到第一子室的第二子室，第二子室限定要连接到第二飞行器燃料管路组件的外管的第二入口。第二子室从第二飞行器燃料管路组件的内管接收泄漏到第二飞行器燃料管路组件的外管中的燃料。腔室壳体限定了连接到第一入口和第二入口的出口，以将泄漏的燃料转移到飞行器的排水口。

50. 发明授权

US09315276B2 Outer fuel tank access cover, wing and aircraft description 有权
标题翻译：外燃油箱检修盖，机翼和飞机描述
公开(公告)号：US09315276B2
公开(公告)日：2016-04-19
申请号：US13828499
申请日：2013-03-14
申请人： AIRBUS OPERATIONS S.L.
发明人： Marcos Alazraki
IPC分类号： B64D37/32 , B64C1/14 , B64C3/34 , B64D37/00
CPC分类号： B64D37/32 , B64C1/14 , B64C1/1446 , B64C3/34 , B64D37/005 , Y02T50/44
摘要： An outer fuel access tank cover (FTAC) of an aircraft, a wing including such outer FTAC of an aircraft, and an aircraft are disclosed. The outer FTAC of an aircraft is related to designing auxiliary pieces in the wing of aircrafts to control the risk of gases from an explosion occurred in the FTAC entering the fuel tank.
摘要翻译：公开了一种飞机的外部燃料进入箱盖（FTAC），包括飞机的这种外部FTAC的飞翼和飞机。飞机的外部FTAC与飞机机翼中的辅助设备相关，以控制进入燃油箱的FTAC中发生的爆炸的气体的风险。

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