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公开(公告)号：US11286055B2
公开(公告)日：2022-03-29
申请号：US17232994
申请日：2021-04-16
申请人： Neoex Systems, Inc.
摘要： A system and method for the transfer of cryogenic fluid fuel includes a nozzle positionable with respect to fuel tank inlet, e.g., of an unmanned aerial vehicle (UAV), a seal to seal the area where the nozzle and inlet are connected, a collapsible and expandable bellows providing an isolation volume where the fluid is transferred from the nozzle into the inlet; a vacuum is provided in the volume to avoid accumulation of fuel or other species in the volume.
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公开(公告)号：US10981666B1
公开(公告)日：2021-04-20
申请号：US16987602
申请日：2020-08-07
申请人： Neoex Systems, Inc.
IPC分类号： B64D39/00 , F17C5/02 , B64D39/06 , F17C5/00 , B64D37/14 , B64F1/28 , B64C39/02 , B60S5/02 , B64D41/00
摘要： A system and method for the transfer of cryogenic fluid fuel includes a nozzle positionable with respect to fuel tank inlet, e.g., of an unmanned aerial vehicle (UAV), a seal to seal the area where the nozzle and inlet are connected, a collapsible and expandable bellows providing an isolation volume where the fluid is transferred from the nozzle into the inlet; a vacuum is provided in the volume to avoid accumulation of fuel or other species in the volume.
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公开(公告)号：US10773820B2
公开(公告)日：2020-09-15
申请号：US15969270
申请日：2018-05-02
摘要： A liquid tank system comprises a main liquid tank, an outlet communicating between a fluid circuit and the main liquid tank, an inlet communicating between the fluid circuit and the main liquid tank, and an auxiliary cavity. First vent passage and second vent passage(s) communicate between the main liquid tank and the auxiliary cavity and allows liquid and gas to flow from the main liquid tank to the auxiliary cavity. The second vent passage has a flow control device regulating flow through the second vent passage and having a set point at which it allows liquid and gas to flow from the main liquid tank to the auxiliary cavity only when a pressure in the main liquid tank is beyond a threshold. The liquid tank system has an attitude envelope in which the liquid tank system is configured such that, in use, the flow control device blocks flow through the second vent passage when an end of the first vent passage in the main liquid tank is above a liquid level, and the flow control device allows gas and/or fluid flow through the second vent passage when main fluid tank pressure is above the threshold and the end of the first vent passage in the main liquid tank is below the liquid level.
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公开(公告)号：US10082444B2
公开(公告)日：2018-09-25
申请号：US15033007
申请日：2014-10-27
IPC分类号： F02C7/22 , G01M15/00 , B64D37/00 , B64D37/14 , B64D37/32 , F02C7/232 , F16K37/00 , B64D37/02 , G01L19/00
CPC分类号： G01M15/00 , B64D37/00 , B64D37/005 , B64D37/02 , B64D37/14 , B64D37/32 , F02C7/232 , F05D2260/80 , F16K37/00 , F16K37/005 , G01L19/0092
摘要： A method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit including a fuel tank, an engine fuel system connected to the fuel tank capable of delivering a flow of fuel to the engine depending on a speed of the engine, a fuel return pipe connected between the engine fuel system and the fuel tank, a fuel return valve arranged to switch between an open and closed position, the valve being capable of blocking the fuel return pipe in the closed position, and of bringing the fuel return pipe into communication with the fuel tank in the open position, the method including measuring a pressure of the flow of fuel from the fuel tank, and if the measured pressure is lower than a predefined threshold, measuring the engine speed.
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公开(公告)号：US10036326B2
公开(公告)日：2018-07-31
申请号：US15032821
申请日：2014-10-27
申请人： SNECMA
CPC分类号： F02C7/232 , B64D37/00 , B64D37/005 , B64D37/14 , B64D37/32 , F05D2260/80
摘要： A method detects a failure in a fuel return valve of an aircraft engine fuel circuit. A fuel system is connected to a fuel tank of the circuit and includes a high-pressure pump delivering a flow rate to an actuating cylinder, a cutoff valve capable of feeding the actuating cylinder disposed in a feed pipe of the engine; a fuel return pipe; a fuel return valve arranged to switch between an open position and a closed position. The method includes starting the engine at an engine speed; increasing the engine speed until a flow rate reaches a predefined value sufficient for opening the cutoff valve; measuring the position of the actuating cylinder and an engine speed corresponding to the opening of said cutoff valve.
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公开(公告)号：US20180086475A1
公开(公告)日：2018-03-29
申请号：US15277640
申请日：2016-09-27
CPC分类号： B64D37/08 , B64D37/14 , B64D37/32 , B65D90/34 , Y10T137/86324
摘要： A liquid tank system comprises a main liquid tank, an outlet communicating between a fluid circuit and the main liquid tank, an inlet communicating between the fluid circuit and the main liquid tank, and an auxiliary cavity. First vent passage and second vent passage(s) communicate between the main liquid tank and the auxiliary cavity and allows liquid and gas to flow from the main liquid tank to the auxiliary cavity. The second vent passage has a flow control device regulating flow through the second vent passage and having a set point at which it allows liquid and gas to flow from the main liquid tank to the auxiliary cavity only when a pressure in the main liquid tank is beyond a threshold. The liquid tank system has an attitude envelope in which the liquid tank system is configured such that, in use, the flow control device blocks flow through the second vent passage when an end of the first vent passage in the main liquid tank is above a liquid level, and the flow control device allows gas and/or fluid flow through the second vent passage when main fluid tank pressure is above the threshold and the end of the first vent passage in the main liquid tank is below the liquid level.
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公开(公告)号：US09809319B2
公开(公告)日：2017-11-07
申请号：US14795481
申请日：2015-07-09
发明人： Stephen Burnell , Tim Leigh
摘要： The invention provides an aircraft fuel system comprising a fuel storage facility for storing fuel and ullage, a separate ullage storage facility for storing ullage, and a transfer arrangement for transferring ullage between the fuel storage facility and the ullage storage facility, wherein the transfer arrangement is capable of controlling the transfer of ullage based on a pressure input to the transfer arrangement. The invention also provides an aircraft with such a fuel system and a method of operating an aircraft.
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公开(公告)号：US20130032672A1
公开(公告)日：2013-02-07
申请号：US13549820
申请日：2012-07-16
申请人： Stephen Fenton
发明人： Stephen Fenton
IPC分类号： B64D37/14
摘要： A vehicle fuel delivery system for liquid fueled vehicles including a vehicle housing a pressure vessel for receiving, discharging and containing fuel. The vehicle fuel delivery system includes fuel lines for communicating fuel to the pressure vessel, and fuel lines for communicating fuel from the pressure vessel to a fuel delivery device. The vehicle fuel delivery system always maintaining positive fuel pressure throughout the delivery system.
摘要翻译： 一种用于液体燃料车辆的车辆燃料输送系统，包括容纳用于接收，排出和容纳燃料的压力容器的车辆。 车辆燃料输送系统包括用于将燃料传送到压力容器的燃料管线和用于将来自压力容器的燃料连通到燃料输送装置的燃料管线。 车辆燃料输送系统在整个输送系统中始终保持正的燃料压力。
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公开(公告)号：US07665479B2
公开(公告)日：2010-02-23
申请号：US12252585
申请日：2008-10-16
申请人： Theron L. Cutler , Mark A. Shelly
发明人： Theron L. Cutler , Mark A. Shelly
IPC分类号： B64D37/14
CPC分类号： B64D39/00 , Y10T137/0318 , Y10T137/4673 , Y10T137/4857
摘要： A method for operating an aircraft refueling system, where the aircraft refueling system has a computer system, a plurality of fuel tanks containing a fuel, a plurality of fuel pumps, a plurality of motor operated valves, and at least one refueling connection. The method may involve using the computer system to signal at least one of the motor operated valves to open; initiating a flow of the fuel to the at least one of the refueling connections using at least one of the pumps; sensing a flow condition of the fuel; signaling the flow condition to the computer system; and varying an operating quantity of the pumps in response to the flow condition.
摘要翻译： 一种用于操作飞行器加油系统的方法，其中所述飞机加油系统具有计算机系统，包含燃料的多个燃料箱，多个燃料泵，多个电动操作阀以及至少一个加油连接。 所述方法可以包括使用所述计算机系统来发送所述马达操作的阀中的至少一个打开; 使用所述泵中的至少一个启动燃料流到所述加油连接中的至少一个; 感测燃料的流动状况; 向计算机系统发信号通知状态; 并且响应于流动条件改变泵的操作量。
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10.发明申请Aircraft fuel tanks, systems and methods for increasing an aircraft's on-board fuel capacity 有权飞机燃料箱，系统和方法，用于增加飞机的机载燃料容量公开(公告)号：US20090050743A1
公开(公告)日：2009-02-26
申请号：US11637922
申请日：2006-12-13
CPC分类号： B64D37/04 , B64C17/10 , B64D37/08 , B64D37/32 , Y02T50/44 , Y10T137/86324 , Y10T137/86348
摘要： Aircraft fuel tanks, systems and methods increase an aircraft's fuel capacity. The fuel tanks have a tank body defining an interior space for holding aircraft fuel, and a relief manifold assembly operatively associated to the tank body to prevent an overpressure condition within the interior space of the fuel tank body. The relief manifold assembly preferably includes a buffer vessel defining a buffer chamber in fluid communication with the interior space defined by the fuel tank body. The buffer vessel may advantageously be fixed to the tank body within the interior space thereof. At least one of a fuel vent manifold assembly for venting the interior space of the fuel tank and a fuel refill/transfer manifold assembly for supplying fuel to and withdrawing fuel from the interior space of the fuel tank. At least one control box (e.g., containing valves, pumps and/or sensors) external of the fuel tank may be provided so as to fluid-connect the at least one fluid manifold assembly to the main fuel system of the aircraft. A plurality of aircraft fuel tanks may therefore be positioned adjacent to one another, preferably within the fuselage (e.g., a cargo compartment) of the aircraft so as to be disposed generally along a longitudinal axis of the aircraft.
摘要翻译： 飞机燃料箱，系统和方法增加了飞机的燃料容量。 燃料箱具有限定用于保持飞行器燃料的内部空间的罐体，以及与罐体可操作地相关联的减压歧管组件，以防止燃料箱体的内部空间内的过压状态。 排气歧管组件优选地包括限定与由燃料箱体限定的内部空间流体连通的缓冲室的缓冲容器。 缓冲容器可以有利地在其内部空间内固定到罐体上。 用于排放燃料箱的内部空间的燃料排放歧管组件和用于向燃料箱的内部空间供应燃料和从燃料箱的内部空间排出燃料的燃料补充/转运歧管组件中的至少一个。 可以设置燃料箱外部的至少一个控制箱（例如，包含阀，泵和/或传感器），以将至少一个流体歧管组件流体连接到飞行器的主燃料系统。 因此，多个飞行器燃料箱可以彼此相邻地定位，优选地位于飞行器的机身（例如，货舱）内，以便大致沿飞机的纵向轴线布置。
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