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21. 发明授权

US07556223B2 Vent system for an aerospace vehicle 有权
标题翻译：航空航天器通风系统
公开(公告)号：US07556223B2
公开(公告)日：2009-07-07
申请号：US11566504
申请日：2006-12-04
申请人： Kurt E. Acheson , David S. Chambers , Brian S. Kornegay
发明人： Kurt E. Acheson , David S. Chambers , Brian S. Kornegay
IPC分类号： B64D37/00
CPC分类号： B64D37/10 , B64C1/1453 , B64D37/005 , Y02T50/44
摘要： An improved vent system for venting an internal cavity of an aerospace vehicle to an exterior surface of the aerospace vehicle generally includes a substantially concave vent inlet surface recessed with respect the exterior surface, and a duct opening formed therein. The vent inlet surface has a major axis substantially parallel to the local external flow direction. The upstream surface contour and the downstream surface contour of the vent inlet surface are substantially oblique to the local external flow direction. The placement and orientation of the duct opening, as well as the geometry of the vent inlet surface, may be selected to achieve a particular pressurization of the internal cavity with respect to the external environment under a variety of conditions.
摘要翻译：用于将航空航天车辆的内部空腔排放到航空航天车辆的外表面的改进的排气系统通常包括相对于外表面凹陷的基本上凹入的通气口入口表面和形成在其中的管道开口。排气入口表面具有基本上平行于局部外部流动方向的长轴。排气入口表面的上游表面轮廓和下游表面轮廓基本上与局部外部流动方向倾斜。可以选择管道开口的布置和取向以及排气入口表面的几何形状，以在各种条件下实现内腔相对于外部环境的特定加压。

22. 发明授权

US3377002A Constant pressure fluid systems 失效
标题翻译：恒压流体系统
公开(公告)号：US3377002A
公开(公告)日：1968-04-09
申请号：US57970866
申请日：1966-09-15
申请人： WRIGHT BARRY CORP
发明人： WEBER MILTON N
IPC分类号： B64D37/10 , B65D88/62 , F15B1/04
CPC分类号： F15B1/04 , B64D37/10 , B65D88/62 , F15B2201/205 , F15B2201/3151 , F15B2201/3156 , F15B2201/3158 , F15B2201/413 , F15B2201/415

23. 发明授权

US3100171A Method and apparatus for forming a pre-stressed hollow lined pressure vessel 失效
标题翻译：用于形成预应力中空衬里压力容器的方法和装置
公开(公告)号：US3100171A
公开(公告)日：1963-08-06
申请号：US73887858
申请日：1958-05-29
申请人： RALPH E LAZARUS
发明人： HARDESTY ETHRIDGE E
IPC分类号： B29C63/00 , B64D37/10
CPC分类号： B29C63/00 , B64D37/10

24. 发明授权

US2919711A Tank pressurizing in aerial craft 失效
标题翻译：坦克在航空兵中加压
公开(公告)号：US2919711A
公开(公告)日：1960-01-05
申请号：US72256358
申请日：1958-03-19
申请人： UNITED AIRCRAFT PROD
发明人： LORD THOMAS J , BOOTH HARRY T
IPC分类号： B64D37/10
CPC分类号： B64D37/10 , Y10T137/2012 , Y10T137/2607 , Y10T137/6579 , Y10T137/86919 , Y10T137/86984

25. 发明申请

US20180065756A1 AUTOMATIC ADJUSTING FUEL BOOST PUMP 审中-公开
公开(公告)号：US20180065756A1
公开(公告)日：2018-03-08
申请号：US15560421
申请日：2016-03-24
申请人： Sikorsky Aircraft Corporation
发明人： Adriano Cirioli , Daniel John Shields , Alex Meyer
IPC分类号： B64D37/10 , F02C7/236 , F02M37/10 , F02M37/18
CPC分类号： B64D37/10 , B64D37/00 , F02C7/236 , F02C9/26 , F02M37/10 , F02M37/103 , F02M37/106 , F02M37/18 , F04B49/065 , F04B2207/00 , F05D2270/301 , Y02T50/44
摘要： A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.

26. 发明申请

US20170175639A1 ENGINE FUEL SYSTEM FOR USE WITH COMPOSITE AIRCRAFT 审中-公开
公开(公告)号：US20170175639A1
公开(公告)日：2017-06-22
申请号：US14974010
申请日：2015-12-18
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Harris Shafique , David Waddleton
IPC分类号： F02C7/236 , F02C7/224
CPC分类号： F02C7/236 , B64D37/10 , F02C7/224 , F02C9/36 , Y02T50/672
摘要： A fuel system for a composite aircraft is described which includes an ejector pump having a vacuum inlet in communication with a fuel storage tank, an engine feed pump having an inlet in fluid communication with an outlet of the ejector pump, a primary outlet in communication with an engine, and a motive flow outlet, upstream of an oil-fuel heat exchanger, that is in fluid communication with an inlet of the ejector pump. A motive flow pump assembly is disposed between the motive flow outlet of the engine feed pump and the inlet of the ejector pump. The motive flow pump assembly includes an inlet screen and a motive flow pump, the inlet screen having a plurality of openings therein and a hydrophobic upstream surface. The openings are dimensioned to prevent passage of particles greater than a selected threshold size while allowing liquids to flow therethrough.

27. 发明授权

US09487081B2 Aircraft fuel tank system 有权
公开(公告)号：US09487081B2
公开(公告)日：2016-11-08
申请号：US12868904
申请日：2010-08-26
申请人： Christopher Lynas , Peter William James , Keith Macgregor
发明人： Christopher Lynas , Peter William James , Keith Macgregor
IPC分类号： B64D1/00 , B60K15/035 , B64D37/10 , B64D37/32
CPC分类号： B60K15/035 , B64D37/10 , B64D37/32
摘要： An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process.

28. 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。

29. 发明申请

US20150239570A1 Fluid Dynamic Vent Dam 有权
标题翻译：流体动力排水坝
公开(公告)号：US20150239570A1
公开(公告)日：2015-08-27
申请号：US14634818
申请日：2015-02-28
申请人： The Boeing Company
发明人： Kenneth L. Brook , Bonnie A. Keefe
IPC分类号： B64D37/00 , B64C3/34 , B64D37/10 , B64C3/18
CPC分类号： B64D37/005 , B64C3/182 , B64C3/34 , B64D37/06 , B64D37/10 , B64D37/32 , Y10T29/49622
摘要： The disclosure provides in one embodiment for a vent dam for use in a vent stringer in a fuel vent system. The vent dam is configured to mount to and within the vent stringer The vent dam has a contoured guiding surface for guiding fuel flow into and out of an interior of the vent stringer, wherein the vent dam, the vent stringer, and a tube attached to the vent stringer are in fluid communication with one or more fuel tanks. The vent dam further has one or more side flanges extending from the contoured guiding surface for providing attachment of the vent dam to one or more interior portions of the vent stringer, wherein the contoured guiding surface and the one or more side flanges are formed as one piece.
摘要翻译：本公开在一个实施例中提供了用于在燃料通风系统中的通风纵梁中使用的排气坝。通气坝被配置成安装到排气纵梁内和排气纵梁内。排气坝具有引导燃料流入和流出排气纵梁的内部的轮廓引导表面，其中通气孔，排气纵梁和连接到排气纵梁与一个或多个燃料箱流体连通。排气坝还具有从轮廓引导表面延伸的一个或多个侧凸缘，用于提供通气排水管连接到排气纵梁的一个或多个内部部分，其中轮廓引导表面和一个或多个侧凸缘形成为一个片。

30. 发明申请

US20150041011A1 INERTING DEVICE, TANK AND AIRCRAFT PROVIDED WITH SUCH A DEVICE, AND CORRESPONDING METHOD 有权
标题翻译：使用这种设备提供的设备，油罐和飞机以及相应的方法
公开(公告)号：US20150041011A1
公开(公告)日：2015-02-12
申请号：US14384441
申请日：2013-01-25
申请人： L'Air Liquide, Societe Anonyme pour I'Etude et I'Exploitation des Procedes Georges Claude
发明人： Xavier Tiger
IPC分类号： B64D37/32 , B64D37/10
CPC分类号： B64D37/32 , B64D37/10 , G05D16/204 , Y10T137/86485
摘要： The invention relates to an inerting device for a pressurized aircraft fuel tank, i.e. for a tank provided with a main vessel and a separate overflow space, the device including a generator of nitrogen-enriched gas, a circuit for transferring the nitrogen-enriched gas produced by the generator, the transfer circuit including an upstream end connected to the generator, a first downstream end which can be coupled to the main vessel and a second downstream end which can be coupled to the overflow space, the device including a sensor array for measuring information representative of a pressure differential between the interior of the overflow space and the exterior of the tank, the device further including an electronic logic unit receiving the measurements from the sensor array, the electronic logic unit being connected to the generator and/or to the transfer circuit, and being designed to control the supply of a nitrogen-enriched gas flow to the second downstream end when the pressure differential drops below a predetermined threshold S.
摘要翻译：本发明涉及一种用于加压飞机燃料箱的惰化装置，即用于具有主容器和独立溢流空间的罐，该装置包括富氮气体的发生器，用于输送产生的富氮气体的回路通过发电机，传输电路包括连接到发电机的上游端，可连接到主容器的第一下游端和可连接到溢流空间的第二下游端，该装置包括用于测量的传感器阵列表示溢流空间的内部与罐外部之间的压力差的信息，该装置还包括接收来自传感器阵列的测量值的电子逻辑单元，电子逻辑单元连接到发电机和/或传输电路，并且被设计成当压力di时控制向第二下游端供应富氮气流微分下降到预定阈值S以下

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