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1. 发明申请

WO2018233274A1 基于膜分离法的飞机环境控制和油箱惰化耦合系统审中-公开
公开(公告)号：WO2018233274A1
公开(公告)日：2018-12-27
申请号：PCT/CN2018/000230
申请日：2018-06-22
申请人：北京航空航天大学 , 袁卫星 , 郑妍 , 尉斌
发明人：袁卫星 , 郑妍 , 尉斌
IPC分类号： B01D53/26 , B01D69/02 , B01D63/02 , F24F3/14
CPC分类号： B01D46/00 , B01D53/268 , B01D2257/80 , B01D2259/4566 , B64D13/06 , B64D37/32 , B64D2013/0662
摘要：一种基于膜分离法的飞机环境控制和油箱惰化耦合系统，依据膜对水蒸气/空气和氧气/氮气的选择透过性，分别实现了飞机环境控制系统中气体除湿环节以及油箱惰化系统中氧氮分离环节。在该耦合系统中，经过膜除湿换热器（5）的干燥气体一部分进入膜空气分离器（9），另一部分经过大膨胀涡轮（8）降温后通入座舱进行制冷；由膜空气分离器（9）产生的富氮气体通入油箱进行惰化，富氧气体和环控系统供气混合，提升了飞机座舱供气的含氧量。

2. 发明申请

WO2017124051A1 COMPRESSED NATURAL GAS VEHICLE SAFETY SYSTEM AND METHOD 审中-公开
标题翻译：压缩天然气车辆安全系统和方法
公开(公告)号：WO2017124051A1
公开(公告)日：2017-07-20
申请号：PCT/US2017/013600
申请日：2017-01-14
申请人： McNICHOLAS, Daniel
发明人： McNICHOLAS, Daniel
IPC分类号： B60K28/00 , B67D7/32 , B64D37/30 , B64D37/32
CPC分类号： B60K28/00 , B64D37/32
摘要： A multiply-redundant system that prevents a driver from starting and/or moving a vehicle if a compressed natural gas fill system is not correctly and completely disconnected from the vehicle. One or more sensors in combination with one or more optional microswitches combine to lock-out the vehicle's ignition or otherwise prevent it from starting and/or moving. For different levels of safety, different combinations of sensors can be used with the lowest level having a single proximity sensor sensing the presence or absence of a high-pressure fill hose. Also a multiply-redundant system that protects fueling of rockets, aircraft and other vehicles using Liquefied Natural Gas (LNG) along with an oxidizer such as Liquefied Oxygen. One or more sensors in combination with one or more optional microswitches combine to detect any leaks, fire or explosion hazards quickly locking out further fueling. For different levels of safety, different combinations of sensors can be used.
摘要翻译：如果压缩天然气加注系统未正确完全与车辆断开连接，则可防止驾驶员启动和/或移动车辆的多重冗余系统。一个或多个传感器与一个或多个可选微动开关组合可以锁定车辆的点火或阻止其启动和/或移动。对于不同的安全等级，可以使用不同的传感器组合，最低等级具有单个接近传感器来感测是否存在高压加注软管。此外还有一个多重冗余系统，可以保护使用液化天然气（LNG）和氧化剂（如液化氧）的火箭，飞机和其他车辆的燃料。一个或多个传感器与一个或多个可选微动开关相结合，可以检测到任何泄漏，火灾或爆炸危险，从而迅速锁定进一步加油。对于不同的安全等级，可以使用不同的传感器组合。

3. 发明申请

WO2017064209A3 FUEL TANK INERTING SYSTEM 审中-公开
标题翻译：燃油箱灌装系统
公开(公告)号：WO2017064209A3
公开(公告)日：2017-05-26
申请号：PCT/EP2016074630
申请日：2016-10-13
申请人： EATON LTD
发明人： SARKAR SUBRATA , MASSEY ALAN , GOLECHA KAILASH , JHA PRASANT
IPC分类号： B64D37/32 , A62C3/08 , B65D90/44
CPC分类号： B64D37/32 , A62C3/08
摘要： An aircraft fuel tank inerting system (100), comprising an oxygen absorption unit (30) containing a Cobalt or a Cobalt derived material.
摘要翻译：一种飞机燃料箱惰化系统（100），包括含有钴或钴衍生材料的氧气吸收单元（30）。

4. 发明申请

WO2017080854A1 AIRCRAFT FUEL SYSTEM 审中-公开
标题翻译：飞机燃油系统
公开(公告)号：WO2017080854A1
公开(公告)日：2017-05-18
申请号：PCT/EP2016/076145
申请日：2016-10-28
申请人： EATON LIMITED
发明人： WOOD, John
IPC分类号： B64D37/32
CPC分类号： B64D37/32 , Y02T50/44
摘要： An aircraft fuel system comprising at least one fuel tank; a source of inerting gas; an inlet for introducing the inerting gas into the at least one fuel tank; and a vent system arranged to allow the inward and outward venting of air from the fuel tank, wherein the vent system comprises: a vent; an inward vent pressure valve disposed between the vent and the at least one fuel tank and configured to enable the at least one fuel tank to increase by a predetermined pressure over ambient air pressure; and an outward vent pressure valve disposed between the at least one fuel tank and the vent and configured to enable the at least one fuel tank to decrease by a predetermined pressure below ambient air pressure.
摘要翻译：一种飞机燃料系统，其包括至少一个燃料箱; 惰性气体的来源; 用于将惰化气体引入至少一个燃料箱的入口; 以及排气系统，所述排气系统布置成允许从所述燃料箱向内和向外排出空气，其中所述排气系统包括：排气口; 设置在所述通风口和所述至少一个燃料箱之间的向内排气压力阀，所述向内排气口压力阀构造成使所述至少一个燃料箱能够相对于环境空气压力增加预定压力; 以及设置在所述至少一个燃料箱和所述通风口之间并构造成使所述至少一个燃料箱能够降低低于环境空气压力的预定压力的向外排气压力阀。

5. 发明申请

WO2017077100A1 FUEL TANK INERTING 审中-公开
标题翻译：燃油箱灌注
公开(公告)号：WO2017077100A1
公开(公告)日：2017-05-11
申请号：PCT/EP2016/076791
申请日：2016-11-07
申请人： EATON LIMITED
发明人： PANKAJ, Shireesh , JOSHI, Mahesh, Prabhakar , GUPTA, Swarnim , MASSEY, Alan, Ernest
IPC分类号： B64D37/32
CPC分类号： B64D37/32 , Y02T50/44
摘要： An aircraft fuel tank inerting system, comprising a paramagnetic pump arranged, in use, to apply a magnetic field to a source of gas so as to provide a motive force for removing oxygen from said gas.
摘要翻译：飞行器燃料箱惰化系统，包括顺磁泵，所述顺磁泵在使用中被布置为向气体源施加磁场以便提供用于从所述气体去除氧气的动力。 p>

6. 发明申请

WO2016115011A3 AIRCRAFT REFUELING SAFETY SYSTEM 审中-公开
标题翻译：飞机补救安全系统
公开(公告)号：WO2016115011A3
公开(公告)日：2016-10-13
申请号：PCT/US2016012804
申请日：2016-01-11
申请人： FLITELOGIX LLC
发明人： DUNN WALTER LEHMER JR , UNRAU CHAD JAMES , TINDELL VERNON LEE , HANKE THOMAS WALTER
IPC分类号： B64D37/32
CPC分类号： B64D37/32 , B64D37/16 , B64F1/28 , B67D7/348
摘要： A system ensures the correct type of fuel is dispensed in an aircraft while removing the introduction of human error in the refueling process. The system includes an RFID tag disposed at one or more aircraft that electronically stores data such as engine type, engine hours, fuel type, tail number, and pilot/subscriber data for the aircraft on which the RFID tag is disposed. An RFID reader is disposed at or near a fuel dispensing mechanism, such as a fuel truck or tank. A signal indicative of fuel type is emitted from the RFID tag to the RFID reader. RFID tags on aircraft that are enrolled in the system's subscription service enable aircraft to be recognized by a module operating the fuel dispensing mechanism. Based on a comparison performed by the module, authorization to begin fueling is either permitted or declined.
摘要翻译：系统确保在飞机中分配正确类型的燃料，同时消除在加油过程中引入人为错误。该系统包括设置在一个或多个飞行器处的RFID标签，其电子存储用于其上设置有RFID标签的飞行器的数据，例如发动机类型，发动机小时，燃料类型，尾数以及飞行员/订户数据。 RFID读取器设置在诸如燃料卡车或罐的燃料分配机构处或附近。指示燃料类型的信号从RFID标签发射到RFID读取器。登记在系统订阅服务中的飞机上的RFID标签使飞机能够被操作燃料分配机构的模块识别。根据模块进行的比较，允许或拒绝开始加油的授权。

7. 发明申请

WO2016116898A1 FUEL CELL DEVICES FOR FIRE PREVENTION ON-BOARD AIRCRAFT 审中-公开
标题翻译：燃料电池设备用于消防车载飞机
公开(公告)号：WO2016116898A1
公开(公告)日：2016-07-28
申请号：PCT/IB2016/050326
申请日：2016-01-22
申请人： ZODIAC AEROTECHNICS , KLASSEN, Samuel , MASSET, Franck , HOOGEVEEN, Andreas , ZRAAIA, Hanane , BOUILLO, Loic , THIRY, Christian , GAGER, Guillaume , FONCIN, Charles , LANDA, Jakub , SCHIPHORST, Remko
发明人： KLASSEN, Samuel , MASSET, Franck , HOOGEVEEN, Andreas , ZRAAIA, Hanane , BOUILLO, Loic , THIRY, Christian , GAGER, Guillaume , FONCIN, Charles , LANDA, Jakub , SCHIPHORST, Remko
IPC分类号： A62C3/08 , A62C99/00
CPC分类号： A62C99/0018 , A62C3/08 , A62C3/16 , A62C5/006 , B64D11/04 , B64D37/32 , B64D41/00 , B64D2041/005 , B64D2221/00
摘要： Described are inerting systems that may be used on board an aircraft or other passenger transportation vehicle to reduce a risk of fire due to electronic components or to other elements in a compartment and to assist in preventing or extinguishing any fire or hazardous condition that may occur. The systems include a source of inert gas such as oxygen depleted air generated from a fuel cell on board the aircraft. The oxygen depleted air or other inert gas is conveyed through ducts to compartments that house the electronics, thus changing the conditions in the compartment to be less conducive to fire.
摘要翻译：描述了可以在飞机或其他客运车辆上使用的惰化系统，以减少由于电子部件或隔室中的其他元件引起的火灾的危险，并且有助于防止或消除可能发生的任何火灾或危险状况。这些系统包括惰性气体源，例如由飞机上的燃料电池产生的贫氧空气。氧耗尽的空气或其他惰性气体通过管道输送到容纳电子器件的隔室，从而改变隔室中的条件以减少有害的火焰。

8. 发明申请

WO2015170095A1 BAFFLE 审中-公开
标题翻译：导流板
公开(公告)号：WO2015170095A1
公开(公告)日：2015-11-12
申请号：PCT/GB2015/051328
申请日：2015-05-06
申请人： BAE SYSTEMS PLC
发明人： BINGHAM, Christopher, Steven , IRWIN, Andrew, James
IPC分类号： B64D37/06 , B64D37/08 , B64D37/32 , B60K15/03 , F41H5/04
CPC分类号： B64D37/32 , B60K15/03 , B60K15/077 , B60K2015/03407 , B60K2015/0344 , B60K2015/0777 , B60Y2200/51 , B64D37/08 , B64D2037/325 , F41H5/0492
摘要： BAFFLE Disclosed is a baffle (40) for locating in a tank (16) for containing liquid (e.g. an aircraft fuel tank). The baffle (40) is a tubular member through which a liquid may flow. The baffle (40) comprises: a first tubular portion (42) providing a tubular outer wall, and a second tubular portion (44) located within the first tubular portion (42) and providing a tubular inner wall. The first and second tubular portions (42, 44) are substantially parallel. The first and second tubular portions (42, 44) are spaced apart to define a chamber (46)therebetween. The baffle (42, 44) further comprises radial side walls between the first and second tubular portions (42, 44) such that the chamber (46) is a sealed chamber. The chamber (46) may be filled with a compressible gas or gaseous mixture. (Figure 5)
摘要翻译： BAFFLE公开了一种用于定位在用于容纳液体（例如飞机燃料箱）的罐（16）中的挡板（40）。挡板（40）是液体可以流过的管状构件。挡板（40）包括：提供管状外壁的第一管状部分（42）和位于第一管状部分（42）内并提供管状内壁的第二管状部分（44）。第一和第二管状部分（42,44）基本上平行。第一和第二管状部分（42,44）间隔开以在其间限定一个腔室（46）。挡板（42,44）还包括在第一和第二管状部分（42,44）之间的径向侧壁，使得室（46）是密封室。腔室（46）可以填充有可压缩气体或气体混合物。（图5）

9. 发明申请

WO2015170088A1 LIQUID STORAGE TANK 审中-公开
标题翻译：液体储存罐
公开(公告)号：WO2015170088A1
公开(公告)日：2015-11-12
申请号：PCT/GB2015/051321
申请日：2015-05-06
申请人： BAE SYSTEMS PLC
发明人： MARTINDALE, Nicholas, John , PARK, Nicholas , JENKINS, Simon, Anthony , IRWIN, Andrew, James , BINGHAM, Christopher, Steven , CONSTANTINOU, Chrisostomos, Angelis
IPC分类号： B64D37/06 , B64D37/32 , B60K15/03 , F41H5/04
CPC分类号： B64D37/06 , B60K15/03 , B60K15/03006 , B60K15/03177 , B60K15/063 , B60K15/073 , B60K2015/03032 , B60K2015/03407 , B60K2015/03486 , B60K2015/03493 , B60Y2200/51 , B64D37/32 , B64D2037/325 , F41H7/00 , Y02T50/44
摘要： A liquid storage tank (16), for example an aircraft fuel tank, comprising a tank wall enclosing a liquid storage space (14), and a tie assembly located at least partially within the liquid storage space (14). The tie assembly comprises an elongate member (20), for example a wire or cable, and a plurality of attachment devices (22) fixed to an inner surface of the tank wall. The elongate member (20) includes a plurality of spaced part points along its length, each of the spaced apart points being fixed to a respective attachment device (22) such that the tie assembly resists outward deformation of the tank wall.
摘要翻译：液体储罐（16），例如飞机燃料箱，包括封闭液体储存空间（14）的罐壁和至少部分位于液体储存空间（14）内的连接组件。连接组件包括细长构件（20），例如电线或电缆，以及固定到罐壁的内表面的多个附接装置（22）。细长构件（20）沿着其长度包括多个间隔的部分点，每个间隔开的点被固定到相应的附接装置（22），使得连接组件抵抗罐壁的向外变形。

10. 发明申请

WO2015063401A3 METHOD FOR DETECTING A FAILURE IN A FUEL RETURN VALVE OF AN AIRCRAFT ENGINE FUEL CIRCUIT 审中-公开
标题翻译：检测飞机发动机燃油电路燃油回流阀故障的方法
公开(公告)号：WO2015063401A3
公开(公告)日：2015-09-11
申请号：PCT/FR2014052724
申请日：2014-10-27
申请人： SNECMA
发明人： VEYRAT-MASSON ANTOINE , GOMES NICOLAS , MOTTET LAURANNE
IPC分类号： B64D37/00 , B64D37/14 , B64D37/32
CPC分类号： F02C7/232 , B64D37/00 , B64D37/005 , B64D37/14 , B64D37/32 , F05D2260/80
摘要： The invention concerns a method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, said fuel circuit comprising: a fuel tank (10); an engine fuel system (20) connected to the fuel tank (10), said fuel system comprising a high-pressure pump (21) delivering a flow rate Q, depending on an engine speed of said engine, to an actuating cylinder (23) capable of actuating variable geometries, a cutoff valve (22) capable of feeding the actuating cylinder and disposed in a feed pipe (28) feeding the engine; a fuel return pipe (2) connected, on the one hand, downstream of the high-pressure pump (21) and upstream of the cutoff valve (22) and, on the other, to the fuel tank (10); a fuel return valve (30) arranged to switch between an open position and a closed position, said fuel return valve (30), in the closed position, being capable of blocking the fuel return pipe (2) and, in the open position, of bringing the fuel return pipe into communication with the fuel tank (10); the method comprising the following steps performed in a computer (28): starting (E1) the engine at an engine speed NO; increasing (E3) the engine speed until flow rate Q reaches a predefined value QO sufficient for opening the cutoff valve; measuring (E4, E5) the position of the actuating cylinder and engine speed N corresponding to the opening of said cutoff valve (22).
摘要翻译：本发明涉及一种用于检测飞机发动机燃料回路的燃料回流阀故障的方法，所述燃料回路包括：燃料箱（10）; 连接到所述燃料箱（10）的发动机燃料系统（20），所述燃料系统包括高压泵（21），所述高压泵将所述发动机的发动机速度的流量Q传递给致动缸（23）能够致动可变几何形状的截流阀（22），其能够馈送致动缸并设置在供给发动机的进料管（28）中; 燃料回流管（2）一方面连接在高压泵（21）的下游和截流阀（22）的上游，另一方面连接到燃料箱（10）。燃料回流阀（30），其布置成在打开位置和关闭位置之间切换，所述燃料回流阀（30）在关闭位置能够阻挡燃料返回管（2），并且在打开位置，使燃料返回管与燃料箱（10）连通; 该方法包括在计算机（28）中执行的以下步骤：以发动机转速NO启动（E1）发动机; 增加（E3）发动机转速，直到流量Q达到足以打开截止阀的预定值QO; 测量（E4，E5）致动气缸的位置和对应于所述截止阀（22）打开的发动机转速N.

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