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1.发明授权公开(公告)号：US11845565B2
公开(公告)日：2023-12-19
申请号：US16978682
申请日：2019-03-05
申请人： DESAUTEL
发明人： Claude Beck
摘要： Aircraft refuelling device including a fuel circulation pipe of which the downstream end is equipped with a wing coupling for connecting it to an inlet orifice of a fuel tank of the aircraft. The wing coupling includes a body which defines a fuel circulation duct at the end of the pipe, a sensor for measuring the value of a parameter indicative of a flow of fuel passing through the wing coupling, and at least one battery electrically powering the sensor. The sensor and the electrical power supply battery are housed in two half-shells mounted together around the body of the wing coupling.
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公开(公告)号：US20180155048A1
公开(公告)日：2018-06-07
申请号：US15880639
申请日：2018-01-26
发明人： Eric Surawski
CPC分类号： B64D37/32 , A62C3/065 , A62C3/08 , B64D37/02 , F02M21/06 , F02M27/02 , Y02T10/32 , Y02T50/44
摘要： Fuel tank inerting systems and methods for aircraft are provided. The systems include a fuel tank, a first reactant source fluidly connected to the fuel tank and arranged to receive fuel from the fuel tank, a second reactant source, a catalytic reactor arranged to receive a first and second reactants from the first and second sources, respectively, to generate an inert gas that is supplied to the fuel tank to fill a ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and downstream of the catalytic reactor, the heat exchanger arranged to at least one of condense and cool an output from the catalytic reactor to separate out an inert gas and a byproduct, and a cool air source arranged to supply cool air to the heat exchanger and then the catalytic reactor to provide thermal control of the catalytic reactor.
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公开(公告)号：US20170297734A1
公开(公告)日：2017-10-19
申请号：US15482056
申请日：2017-04-07
申请人： Zodiac Aerotechnics
发明人： Julien Vialle , Christophe Claris
CPC分类号： B64D37/32 , B64D37/005 , B64D37/02
摘要： A fuel manifold adapted to communicate with at least one fuel tank of an aircraft is presented. The manifold defines an enclosure adapted to be filled with fuel and to have an internal pressure P1 higher than the internal pressure P2 of the fuel tank. The enclosure includes at least one ceiling and at least one side wall provided with overflow holes adapted to communicate with the fuel tank. The manifold includes a mechanism for discharging an air pocket, trapped between the ceiling and the level of the overflow holes, to the fuel tank.
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4.发明申请公开(公告)号：US20170239615A1
公开(公告)日：2017-08-24
申请号：US15436089
申请日：2017-02-17
申请人： Zodiac Aerotechnics
发明人： Christophe Claris
CPC分类号： B01D53/226 , B01D71/028 , B01D2053/221 , B64D37/02 , B64D37/32
摘要： An inert gas generation system from a flow of air, notably for an inerting system for at least one aircraft fuel tank. The generation system includes an air circuit having an air inlet, an inert gas outlet, and a first and a second air separation module arranged in series on the air circuit to deplete oxygen within the air and to generate a nitrogen-enriched inert gas.
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公开(公告)号：US20170159569A1
公开(公告)日：2017-06-08
申请号：US15041224
申请日：2016-02-11
发明人： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
CPC分类号： F02C7/224 , B64D27/12 , B64D37/02 , B64D37/34 , F02C7/06 , F02C7/14 , F02C7/236 , F05D2220/32 , F05D2220/764 , F05D2240/35 , F05D2260/20 , F05D2260/205 , F05D2260/213 , F05D2260/98 , Y02T50/675
摘要： A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号：US20170129620A1
公开(公告)日：2017-05-11
申请号：US15342334
申请日：2016-11-03
发明人： Angus MORGAN , Christopher SLACK
摘要： An aircraft fuel system has a fuel tank for containing liquid fuel, the fuel tank having a base. The aircraft fuel system also has a fuel pump for drawing liquid fuel from the fuel tank, a fuel conduit having a fuel outlet through which fuel is permitted to flow from the fuel tank, and a filter defining a filtered fuel space enclosing the fuel outlet. The fuel conduit extends between the fuel outlet and the fuel pump, and the filter extends from the base to enclose the fuel outlet. The fuel conduit extends into the filtered space and the fuel outlet faces and is spaced from the base. This helps to minimise the quantity of unusable fuel in the aircraft fuel system. The present application also relates to an aircraft wing having an aircraft fuel system, and an aircraft having an aircraft fuel system.
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7.发明授权公开(公告)号：US09618029B2
公开(公告)日：2017-04-11
申请号：US14034140
申请日：2013-09-23
申请人： The Boeing Company
CPC分类号： F16B37/14 , B29C45/14336 , B29C45/14377 , B29C2045/14459 , B29L2001/00 , B29L2031/3076 , B64D37/02 , B64D37/32 , B64D45/02 , F16B21/04 , Y10T29/49826
摘要： A cap for use in covering a portion of a fastener protruding from a surface is provided. The portion includes threads. The cap includes an interior, a base that at least partially delimits the interior, a threaded receptacle on the interior configured to threadably engage the portion of the fastener, and a seal coupled to the base to engage the surface.
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公开(公告)号：US20170015433A1
公开(公告)日：2017-01-19
申请号：US14799145
申请日：2015-07-14
发明人： Catherine Thibaud
CPC分类号： B64D37/32 , B01D46/0036 , B01D53/04 , B01D53/229 , B01D53/8675 , B01D2053/221 , B01D2253/102 , B01D2253/204 , B01D2255/106 , B01D2256/10 , B01D2256/12 , B01D2257/102 , B01D2257/104 , B01D2257/106 , B01D2259/4575 , B64D37/02
摘要： An air separation system includes a feed air line for transporting feed air and an air separation module with a polymeric membrane. The air separation module is configured to receive feed air through the feed air line and separate the feed air into nitrogen-enriched air and oxygen-enriched air. The air separation system further includes a gaseous contaminant removal system upstream of the air separation module and configured to remove gaseous contaminants from the feed air received by the air separation module, and a nitrogen-enriched air line for transporting the nitrogen-enriched air from the air separation module to a fuel tank for inerting.
摘要翻译： 空气分离系统包括用于输送进料空气的进料空气管线和具有聚合物膜的空气分离组件。 空气分离模块被构造成通过进料空气管线接收进料空气并将进料空气分离成富氮空气和富氧空气。 空气分离系统还包括在空气分离模块的上游的气体污染物去除系统，并且构造成从空气分离模块接收的进料空气中除去气态污染物;以及富氮空气管线，用于将富氮空气从 空气分离模块到燃料箱进行惰化。
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公开(公告)号：US20170001731A1
公开(公告)日：2017-01-05
申请号：US14769889
申请日：2014-03-06
申请人： BOMBARDIER INC.
CPC分类号： B64D37/32 , B64D37/005 , B64D37/02
摘要： A tank wall connector system for use with a composite tank, the connector comprises a connector having a body extending from an interior of the tank to an exterior of the tank when installed through a hole in the composite tank. The connector has a first electrical conductivity property. An interface is positioned between the connector and a wall of the composite tank when installed to the tank thereby preventing physical contact between the connector and the tank wall in the interior of the tank, the interface having a second electrical conductivity property, different from the first electrical conductivity property.
摘要翻译： 一种与复合罐一起使用的罐壁连接器系统，连接器包括连接器，当通过复合罐中的孔安装时，该连接器具有从罐的内部延伸到罐的外部的主体。 连接器具有第一导电性。 当连接器和复合罐的壁安装在罐上时，接口被定位在复合罐的壁之间，从而防止连接器与罐内部的罐壁之间的物理接触，该界面具有第二导电性，不同于第一 导电性能。
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公开(公告)号：US20160167796A1
公开(公告)日：2016-06-16
申请号：US14966028
申请日：2015-12-11
申请人： AIRBUS GROUP SAS
CPC分类号： B64D27/24 , B64D37/02 , B64D41/00 , B64D2027/026 , F02B61/06 , F02B65/00 , Y02T50/64 , Y10S903/951
摘要： The aircraft (10) includes: at least one electric motor (135); at least one stand-alone electrical power supply (110, 120) supplying power to the electric motor; propulsion elements (130) referred to as “auxiliary propulsion elements”, included in the group including: a stand-alone electrical power supply (130) supplying power to the electric motor, a power supply converting thermal energy into electrical energy and supplying power to the electric motor, and an internal combustion engine; and a structure (100) configured to integrate each electric motor, each stand-alone electrical power supply and the auxiliary propulsion elements, the parameters of the structure being substantially identical regardless of the auxiliary propulsion elements. A method of fitting out such an aircraft is also described.
摘要翻译： 飞机（10）包括：至少一个电动机（135）; 向所述电动马达供电的至少一个独立电源（110,120）; 被称为“辅助推进元件”的推进元件（130）包括：向电动机供电的独立电源（130），将热能转换成电能并将电力供应到 电动机和内燃机; 以及构造成将每个电动机，每个独立电源和辅助推进元件集成的结构（100），所述结构的参数基本上相同，而与辅助推进元件无关。 还描述了装配这种飞行器的方法。
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