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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Применить Всего найдено 1277. Отображено 192.
27-09-2014 дата публикации

ТОПЛИВОЗАПРАВЩИК И СПОСОБ ЗАПРАВКИ ТОПЛИВОМ ЛЕТАТЕЛЬНОГО АППАРАТА ПРИ ПОМОЩИ ТАКОГО ТОПЛИВОЗАПРАВЩИКА

Номер: RU2529102C2
Автор: БЕК Клод (FR)
Принадлежит: ДЕЗОТЕЛЬ (FR)

FIELD: transport. SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft fuelling systems. Tanker comprises pipeline equipped with means for connection to fuel tank, means to define the magnitudes of at least one parameter of the flow flowing via connection means, transmitter of signal describing the parameter magnitude, electronic unit to receive the signal and to control at least one adjustment device and/or flow control subject to signal received by receiver. Means for determination of magnitude are arranged level with or nearby means of connection with fuel tank. EFFECT: higher reliability. 12 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (51) МПК B64F 1/28 (11) (13) 2 529 102 C2 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2011149197/11, 04.05.2010 (24) Дата начала отсчета срока действия патента: 04.05.2010 (72) Автор(ы): БЕК Клод (FR) (73) Патентообладатель(и): ДЕЗОТЕЛЬ (FR) Приоритет(ы): (30) Конвенционный приоритет: (43) Дата публикации заявки: 10.06.2013 Бюл. № 16 R U 05.05.2009 FR 0952974 (45) Опубликовано: 27.09.2014 Бюл. № 27 10.11.2006. RU 2234441 C1, 20.08.2004 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 05.12.2011 (86) Заявка PCT: FR 2010/050854 (04.05.2010) 2 5 2 9 1 0 2 (56) Список документов, цитированных в отчете о поиске: US 5921266, 13.07.1999. RU 58099 U1, 2 5 2 9 1 0 2 R U WO 2010/128246 (11.11.2010) Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" (54) ТОПЛИВОЗАПРАВЩИК И СПОСОБ ЗАПРАВКИ ТОПЛИВОМ ЛЕТАТЕЛЬНОГО АППАРАТА ПРИ ПОМОЩИ ТАКОГО ТОПЛИВОЗАПРАВЩИКА (57) Реферат: Изобретение относится к области авиации, в электронный блок, выполненный с возможностью частности к системам заправки летательных приема сигнала и с возможностью управления по аппаратов. Топливозаправщик содержит меньшей мере одним устройством регулирования трубопровод, оборудованный средствами и/или ...

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19-09-2022 дата публикации

УСТРОЙСТВО И СПОСОБЫ ЗАПРАВКИ ЛЕТАТЕЛЬНЫХ АППАРАТОВ

Номер: RU2780102C2
Автор: БЕК, Клод (FR)
Принадлежит: ДЕЗОТЕЛЬ (FR)

Изобретение относится к устройству для заправки летательных аппаратов (ЛА), а также к способам заправки ЛА с помощью такого устройства. Устройство для заправки летательного аппарата содержит трубопровод для подачи топлива, на дальнем конце которого установлен крыльевой разъем для соединения трубопровода с входным отверстием топливного бака летательного аппарата, содержащий корпус и передний клапан, установленный с возможностью перемещения относительно корпуса. При этом крыльевой разъем содержит по меньшей мере один обнаруживающий элемент для определения положения переднего клапана и электрическую или электронную систему передачи для передачи в блок обработки информации сигнала, характеризующего положение переднего клапана, определенное обнаруживающим элементом. При этом устройство для заправки содержит блок для подсчета количества операций с крыльевым разъемом и/или фактической продолжительности использования крыльевого разъема по сигналу, характеризующему обнаруженное положение переднего ...

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07-02-2023 дата публикации

МАЛОГАБАРИТНАЯ МОБИЛЬНАЯ СТАНЦИЯ ВАКУУМИРОВАНИЯ РЕЗЕРВУАРОВ

Номер: RU216473U1

Полезная модель относится к области авиации, в частности к аэродромному оборудованию для обслуживания резервуаров для хранения и транспортирования криогенных продуктов. Станция содержит корпус, насос вакуумный пластинчато-роторный, насос вакуумный двухроторный, источник энергии для привода насосов и обеспечения работоспособности станции, клапаны вакуумные, клапаны, вакуумный датчик, соединенные между собой трубопроводами, панель управления процессом вакуумирования с контрольно-измерительной аппаратурой, размещенные в корпусе станции, согласно техническому решению, источник энергии для привода насосов и обеспечения работоспособности станции выполнен в виде двигателя внутреннего сгорания, соединенного кинематически с вакуумными насосами. Корпус станции выполнен в виде малогабаритного блок-контейнера, имеющего вид трехмерной геометрической фигуры, содержащей верхнюю крышку, нижнее основание, боковые стенки, выполненные с возможностью радиального перемещения и фиксации, устройства для подъема ...

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22-02-2019 дата публикации

Номер: RU2018103765A3
Автор:
Принадлежит:

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06-12-2021 дата публикации

СУДОВОЙ МОДУЛЬ ДЛЯ РАЗМЕЩЕНИЯ ОБОРУДОВАНИЯ ДЛЯ ЗАПРАВКИ ЛЕТАТЕЛЬНОГО АППАРАТА АВИАЦИОННЫМ ТОПЛИВОМ

Номер: RU208160U1

Полезная модель относится к судовому модулю заправки летательного аппарата авиационным топливом, применяемому в судовых системах авиатопливообеспечения. Судовой модуль (1) для размещения оборудования для заправки летательного аппарата авиационным топливом содержит выполненный с возможностью установки на палубе судна корпус (2) с четырьмя стенками (3,4,5) и крышей (6). Корпус (2) изготовлен из стали повышенной прочности судового применения, в передней стенке (3) и одной из боковых стенок (4) корпуса выполнены дверные проемы (7), оснащенные распашными дверцами (8), и с внутренней стороны крыша (6), стенки (3,4,5) и дверцы (8) оснащены усиливающими стальными пластинами (9). Достигается повышение эксплуатационных свойств модуля в суровых климатических условиях.

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23-12-2020 дата публикации

СПОСОБ ПОДАЧИ ТОПЛИВА В ЗАПРАВЛЯЮЩУЮ ТРУБУ БАКА ЛЕТАТЕЛЬНОГО АППАРАТА И КЛАПАН, СОЕДИНЕННЫЙ С ТРУБОЙ ДЛЯ ОСУЩЕСТВЛЕНИЯ УКАЗАННОГО СПОСОБА

Номер: RU2739369C1

FIELD: aviation. SUBSTANCE: invention relates to aircraft engineering. Method of supplying fuel to refuelling pipe (2) of aircraft tank. Method according to the invention includes automatic and mechanical change of the fuel flow passage until the fuel reaches the maximum speed threshold. To implement said method, valve (1) is connected to filling pipe (2) for aircraft fuel tank. According to the present invention, it comprises a fuel flow passage limiting device (7) capable of automatically changing the fuel flow passage in pipe (2), until the fuel speed reaches the maximum threshold value. EFFECT: minimization of time and safety of refuelling. 11 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 739 369 C1 (51) МПК B64F 1/28 (2006.01) F16K 1/22 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК B64F 1/28 (2020.08); F16K 1/22 (2020.08) (21)(22) Заявка: 2020106553, 18.07.2018 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): ЗОДИАК АЭРОТЕКНИКС (FR) Дата регистрации: 23.12.2020 31.08.2017 FR 1758036 (45) Опубликовано: 23.12.2020 Бюл. № 36 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 12.02.2020 (86) Заявка PCT: 2 7 3 9 3 6 9 R U (87) Публикация заявки PCT: WO 2019/043306 (07.03.2019) Адрес для переписки: 123242, Москва, пл. Кудринская, д. 1, а/я 35, "Михайлюк, Сороколат и партнеры патентные поверенные" (54) СПОСОБ ПОДАЧИ ТОПЛИВА В ЗАПРАВЛЯЮЩУЮ ТРУБУ БАКА ЛЕТАТЕЛЬНОГО АППАРАТА И КЛАПАН, СОЕДИНЕННЫЙ С ТРУБОЙ ДЛЯ ОСУЩЕСТВЛЕНИЯ УКАЗАННОГО СПОСОБА (57) Реферат: Изобретение относится к области летательных топливного бака летательного аппарата. аппаратов. Способ подачи топлива в Согласно настоящему изобретению он содержит заправляющую трубу (2) бака летательного ограничительное устройство (7) для проходного аппарата. Способ согласно изобретению сечения для топлива, способное при подаче включает автоматическое и механическое топлива в трубу (2) автоматически изменять изменение ...

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30-04-2021 дата публикации

СПОСОБ ПОДАЧИ ТОПЛИВА В ЗАПРАВОЧНУЮ ТРУБУ БАКА ЛЕТАТЕЛЬНОГО АППАРАТА И КЛАПАН, СОЕДИНЕННЫЙ С ТРУБОЙ ДЛЯ ОСУЩЕСТВЛЕНИЯ УКАЗАННОГО СПОСОБА

Номер: RU2739369C9

FIELD: aviation.SUBSTANCE: invention relates to aircraft engineering. Method of supplying fuel into charge tube (2) of aircraft tank. Method according to the invention includes automatic and mechanical change of the fuel flow passage until the fuel reaches the maximum speed threshold. To implement said method, valve (1) is connected to charge tube (2) for aircraft fuel tank. According to the present invention, it comprises a fuel flow passage limiting device (7) capable of automatically changing the fuel flow passage in pipe (2), until the fuel speed reaches the maximum threshold value.EFFECT: minimization of time and safety of refuelling.11 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 739 369 C9 (51) МПК B64F 1/28 (2006.01) F16K 1/22 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) СКОРРЕКТИРОВАННОЕ ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ Примечание: библиография отражает состояние при переиздании (52) СПК B64F 1/28 (2020.08); F16K 1/22 (2020.08) (21)(22) Заявка: 2020106553, 18.07.2018 18.07.2018 (73) Патентообладатель(и): ЗОДИАК АЭРОТЕКНИКС (FR) Приоритет(ы): (30) Конвенционный приоритет: (56) Список документов, цитированных в отчете о поиске: US 2307273 A, 05.01.1943. RU 113539 U1, 20.02.2012. RU 23856 U1, 20.07.2002. RU 2435972 C1, 10.12.2011. RU 2125656 C1, 27.01.1999. US 2864410 A1, 16.12.1958. SU 848389 A1, 23.07.1981. (45) Опубликовано: 23.12.2020 (15) Информация о коррекции: Версия коррекции №1 (W1 C1) (48) Коррекция опубликована: 30.04.2021 Бюл. № 13 (86) Заявка PCT: C 9 C 9 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 12.02.2020 FR 2018/051834 (18.07.2018) 2 7 3 9 3 6 9 (87) Публикация заявки PCT: R U 2 7 3 9 3 6 9 31.08.2017 FR 1758036 R U (24) Дата начала отсчета срока действия патента: (72) Автор(ы): РОССИ, Сильвен (FR), ЛУБЕ, Пьер-Ив (FR) WO 2019/043306 (07.03.2019) Адрес для переписки: 123242, Москва, пл. Кудринская, д. 1, а/я 35, "Михайлюк, Сороколат и партнеры патентные поверенные" (54) СПОСОБ ПОДАЧИ ТОПЛИВА В ...

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10-04-2012 дата публикации

ОПОРНАЯ МАЧТА ДЛЯ ПОДДЕРЖАНИЯ И ПЕРЕМЕЩЕНИЯ ПАНТОГРАФА

Номер: RU2010140786A
Принадлежит:

... 1. Опорная мачта (10) для поддержания и перемещения пантографа (2), причем она выполнена с возможностью телескопического выдвигания и с возможностью фиксации в частично или полностью выдвинутом состоянии посредством по меньшей мере одного тормозного механизма (14, 28). ! 2. Мачта по п.1, отличающаяся тем, что она выполнена с возможностью пассивного выдвигания с помощью подъемной площадки и предпочтительно не имеет собственного привода. ! 3. Мачта по п.1 или 2, отличающаяся тем, что она выполнена без возможности опускания (вдвигания) в фиксированном состоянии, однако предпочтительно с возможностью дальнейшего выдвигания. ! 4. Мачта по п.1 или 2, отличающаяся тем, что она содержит по меньшей мере один тормозной модуль (14), включающий в себя соединенную с ее подвижной секцией (11, 12) и выполненную с возможностью движения с ней опорную штангу (15), а также две прижимаемые к опорной штанге тормозные колодки (16), причем каждая тормозная колодка соединена с зубчатой пластиной (18), зубчатые ...

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10-08-1989 дата публикации

Номер: DE0003734010C2

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16-09-1999 дата публикации

Unterflurhydrantengehäuse

Номер: DE0029912370U1
Автор:

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18-11-2004 дата публикации

ÜBERWACHUNGSSYSTEM FÜR EIN PIPELINESYSTEM

Номер: DE0059910849D1
Автор: HUEBNER WOLFGANG
Принадлежит: FLUGHAFEN MUENCHEN GMBH

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02-02-1984 дата публикации

SCHLAUCH, INSBESONDERE BETANKUNGSSCHLAUCH

Номер: DE0008331111U1
Автор:

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10-05-2017 дата публикации

Fueling station

Номер: GB0002544045A
Принадлежит:

A fuelling station 10 for a fuel generator 22 having a fuel generator reservoir 24 forms part of a ground station 1 for UAVs 20, 21. The fuelling station comprises a station reservoir 11 for storing at least one reactant for fuel generation and includes a fuelling interface 14 configured to engage with the fuel generator reservoir and dispense the at least one reactant to the fuel generator reservoir. The fuel generator reservoir may comprise two compartments 26, 28 for storing different reactants from separate compartments 12, 13 in the station reservoir. A controller 18 is configured to receive a parameter indicative of an intended use of the fuel generator and control the fuelling interface to dispense the at least one reactant in accordance with the parameter.

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13-09-2017 дата публикации

Fuelling method

Номер: GB0002548179A
Принадлежит:

A fuelling method for fuelling or re-fuelling aircraft, trains, lorries, ships, other vehicles of other tanks and containers, especially aircraft. The method comprises the steps: of dispensing an initial quantity of fuel to a fuel tank 18; waiting for a predetermined settling period for the fuel dispensed to the fuel tank to homogenise and settle 24; after the predetermined settling period has elapsed, taking a fuel quantity reading using a fuel gauge associated with the fuel tank 26; calculating a differential volume of fuel between the fuel gauge reading and a desired final fuel quantity 30; dispensing to the fuel tank a volume of fuel substantially equivalent to the differential volume 32 using a dispensing apparatus including a fuel volume meter and informing an officer of the total quantity of fuel. The step of calculating preferably takes into account the density of the fuel being dispensed. The dispensing apparatus may include a fuel density meter, alternatively, a fuel density reading ...

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27-03-1963 дата публикации

Fuel containers

Номер: GB0000922122A
Автор:
Принадлежит:

... 922,122. Discharging static electricity. GOODYEAR TIRE & RUBBER CO. Nov. 16, 1959 [Jan. 22, 1958], No. 38719/59. Class 35. [Also in Groups XXIX and XXXIII] The risk of static discharges of energies exceeding the explosive level of vapour of a high resistivity fuel in a container is minimized by providing at least one semi-conductive element projecting into the interior of the container and having a resistance sufficient to limit the electrical energy flow therethrough to a value below such level. In the rolling transporter 1, Fig. 1, containing jet fuel 2, the axle 4, Fig. 2, and hub plates 8 are covered by a plurality of such elements 6 which comprise conical bodies extending from a base and are of loaded plastics, resins, elastomers, or preferably conductive rubber. The bodies may be cast or moulded and alternatively may be of cylindrical shape or screwed directly to the axle. Suitable resistance and resistivity values for the elements are disclosed. In other embodiments, not shown, the ...

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23-07-1958 дата публикации

Improvements in or relating to pressure regulating devices

Номер: GB0000798709A
Автор:
Принадлежит:

... 798,709. Fluid-pressure servomotor-control systems; valves. STRUVER GES AGGREGATEBAU, A. April 20, 1956 [April 23, 1955], No. 12169/56. Class 135. In a fuelling arrangement in which a single pump supplies a plurality of independent systems, a valve shut-off device is provided at the end of each delivery pipe and a control shut-off device operated in accordance with the pressure in the constriction of a venturi tube is located before the delivery pipe. A pump (not shown) supplies two independent systems through a pipe 1, Fig. 1, which divides into two branches 2, 3 leading to two systems. Each branch contains a control shut-off device, e.g. a valve 4 and a venturi 7. The valve 4 has a housing 11 containing two closure members 12, 13. The member 12 controls the flow from the inlet 15 to the outlet 16 and the member 13 the flow from the inlet 15 to the by-pass 20. Fluid under pressure is taken from a tapping 45 in the branch 3 via pipes 46, 47 to the orifice of a pilot valve 6 the closure ...

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13-02-1963 дата публикации

Improvements in or relating to pump installations

Номер: GB0000918579A
Автор: SHOOSMITH GUY TAITE
Принадлежит:

... 918,579. Dispensing liquids. PLENTY & SON Ltd. April 23, 1959 [Jan. 24, 1958; Jan. 23, 1959], Nos. 2445/58 and 2611/59. Class 116. [Also in Group XXVI] A pump installation for withdrawing liquid from a tank and delivering it to storage containers, comprises a pump 10, Fig. 1, which is either a variablecapacity rotary pump of the sliding-vane type, as shown, or a centrifugal pump, and a liquid level detecting means 34 connected at its lower end to a tanker 50 and comprising float-operated electric switches 36 which when the level of the liquid, e.g., aviation fuel, in the tanker falls to a predetermined level operates through a junction-box 58 an electric motor 60. The motor 60, connected through reduction gearing and a shaft 64, Fig. 2, moves a sliding- block 10 to reduce pump capacity, either step by step (as shown) or gradually, to prevent air being drawn through the pump with the liquid. A two-way valve 26 connects the outlet pipe 30 from the detecting means through a filter 24 to the ...

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11-12-1957 дата публикации

Improvements in liquid tanks or reservoirs

Номер: GB0000787530A
Автор:
Принадлежит:

... 787,530. Gravity-separation apparatus. MULLER, J. Oct. 25, 1955 [Feb. 16, 1954 ; Dec. 12, 1955], No. 30522/55. Class 46. [Also in Group XVII] A tank construction in which the main supply and withdrawal pipe is automatically closed when the tank is full and in which said pipe is also closed when the tank has been emptied to a level at which settled impurities or denser liquids may commence to be withdrawn comprises a pivoted extension of said pipe in the form of a floating arm following the variation of the liquid level in the tank, and a cut off device in the pipe or its extension that is closed when the floating arm is at its permitted upper or lower positions. Fig 9. The floating arm 15 is coupled to a sliding piston 63 in an extension 102 of the main pipe 14. The piston 63 is by-passed by a side passage 105 that is closed whenever the floating arm 15 causes the piston 63 to rise or fall sufficiently. When the tank is being emptied via the arm 15 and pipe 14, the piston 63 descends until ...

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04-08-1960 дата публикации

Automatic engine cut-off more especially for pump-equipped tank truck vehicles

Номер: GB0000843015A
Автор: POWELL WILLIAM GRANT
Принадлежит:

... 843,015. Engine stop-gear. SCULLY SIGNAL CO. Feb. 6, 1957, No. 4045/57. Class 122 (4). [Also in Group XXVIII] Emergency stop-gear for an internal combustion engine driving a liquid pump comprises switching means responsive to a predetermined pump discharge pressure to establish an electric circuit in parallel with the breaker points of the engine ignition system which is thereby rendered ineffective. The invention is shown applied to the pumping system of a tank vehicle in which the liquid to be delivered is pumped from the vehicle storage tank to a discharge line 10 by a pump 6 driven, through clutch mechanism, from the vehicle engine 1. The pumping equipment is protected against destructive pressures that occur if the pump is driven at speeds above those at which the normal pump relief valve 7 is effective by a pressure-responsive engine cut-off switch 13 which is connected by a pipe 12 with the discharge line 10 and comprises a pressure responsive element 15 which, when the pump pressure ...

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15-05-1994 дата публикации

VEHICLE FOR THE DISPOSAL OF THE TOILETS OF PASSENGER AIRLINES

Номер: AT0000155093A
Автор:
Принадлежит:

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15-11-1992 дата публикации

UP ONE AND ABBEWEGBARE FUEL DELIVERY DEVICE, INTENDED FOR TANK CARS FOR REFUELLING AIRPLANES.

Номер: AT0000082226T
Принадлежит:

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15-06-1993 дата публикации

DEVICE FOR SUCKING OFF LIQUIDS.

Номер: AT0000090408T
Принадлежит:

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15-10-2004 дата публикации

MONITOR FOR A PIPELINE SYSTEM

Номер: AT0000279719T
Принадлежит:

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15-06-2004 дата публикации

COOLED FUEL FOR ENGINES

Номер: AT0000267735T
Принадлежит:

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20-05-2021 дата публикации

Aerial vehicle with enhanced pitch control and interchangeable components

Номер: AU2019388299A1
Принадлежит:

An aircraft capable of vertical take-off and landing comprises a fuselage, at least one processor carried by the fuselage and a pair of aerodynamic, lift-generating wings extending from the fuselage. A plurality of vectoring rotors are rotatably carried by the fuselage so as to be rotatable between a substantially vertical configuration relative to the fuselage for vertical take-off and landing and a substantially horizontal configuration relative to the fuselage for horizontal flight. The vectoring rotors are unsupported by the first pair of wings. The wings may be modular and removably connected to the fuselage and configured to be interchangeable with an alternate pair of wings. A cargo container may be secured to the underside of the fuselage, and the cargo container may be modular and interchangeable with an alternate cargo container.

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19-07-1999 дата публикации

Inert loading jet fuel

Номер: AU0003448299A
Принадлежит:

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04-06-2009 дата публикации

APPARATUS AND METHOD FOR FUELLING AN AIRCRAFT TANK SYSTEM

Номер: CA0002705395A1
Принадлежит:

An apparatus (10) for fuelling an aircraft, in particular during performing a tank leakage test on the aircraft, comprises a fuel supply line (14) for supplying fuel to an aircraft tank system (12), at least one pressure sensor (26) for sensing a pressure within the aircraft tank system (12) and for providing a signal indicative of the pressure within the aircraft tank system (12), an electronic control unit (ECU) for processing the signal of the pressure sensor (26) and for generating an emergency shut-off signal, if the pressure within the aircraft tank system (12) exceeds a first predetermined level, and an emergency shut-off device (24) which is controlled by the electronic control unit (ECU) and which is adapted to interrupt the supply of fuel to the aircraft tank system (12) in response to the emergency shut-off signal from the electronic control unit (ECU).

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23-10-1994 дата публикации

AIRCRAFT REFUELLING INSTALLATION

Номер: CA0002120830A1
Принадлежит:

DESCRIPTIVE In order to carry out the refuelling of an aircraft, use is made of an installation associated with the loading bridge (10) used for the transfer of passengers between the air terminal and the aircraft. The installation comprises a retractable extension mechanism (24) supported by the loading bridge (10) and a deformable hose (40) permanently connecting a pressure intake (22) of a fuel distribution network to a coupling (28) carried by the extension mechanism (24). The installation is controlled by the energy available on the loading bridge (10) from a console (54). It can be partly or totally automated. (Fig. 1) ...

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15-11-1963 дата публикации

Hydrogen, fuel tank in particular

Номер: FR0001343326A
Автор:
Принадлежит:

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13-12-2019 дата публикации

METHOD FOR CIRCULATING FUEL IN A CONDUIT FOR FILLING A TANK OF AN AIRCRAFT, AND VALVE CONNECTED TO A CONDUIT FOR SAID METHOD WORK

Номер: FR0003070375B1
Принадлежит: Zodiac Aerotechnics SAS

Procédé de circulation de carburant dans une conduite (2) de remplissage d'un réservoir d'un aéronef. Selon l'invention il consiste à faire varier automatiquement et mécaniquement la section de passage du carburant jusqu'à ce que le carburant atteigne une vitesse seuil maximale. Vanne (1) connectée à une conduite (2) de remplissage d'un réservoir de carburant d'un aéronef pour la mise en œuvre dudit procédé. Selon l'invention elle comprend un dispositif de restriction (7) de la section de passage du carburant, apte, lorsque du carburant circule dans la conduite (2), à faire varier automatiquement la section de passage du carburant jusqu'à ce que la vitesse du carburant atteigne une valeur seuil maximale. Method of circulating fuel in a pipe (2) for filling a tank of an aircraft. According to the invention, it consists in automatically and mechanically varying the fuel passage section until the fuel reaches a maximum threshold speed. Valve (1) connected to a line (2) for filling an aircraft fuel tank for the implementation of said method. According to the invention, it comprises a device for restricting (7) the fuel passage section, capable, when fuel flows in the line (2), of automatically varying the fuel passage section until the fuel speed reaches a maximum threshold value.

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13-04-1956 дата публикации

Device intended for the fuel supply of two systems independent one of the other by means of a pump

Номер: FR0001114508A
Автор:
Принадлежит:

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23-09-1983 дата публикации

INSTALLATION DE VIDANGE, NOTAMMENT POUR SANITAIRES D'AVION

Номер: FR0002523617A
Автор:
Принадлежит:

L'INVENTION CONCERNE UNE INSTALLATION DE VIDANGE, NOTAMMENT POUR SANITAIRES D'AVION. LE PROBLEME TECHNIQUE POSE CONSISTE A FOURNIR UNE TELLE INSTALLATION EXTREMEMENT SIMPLE, FIABLE ET EFFICACE. SUIVANT L'INVENTION, CETTE INSTALLATION QUI EST FORMEE D'UN CHARIOT MOBILE 1 PORTANT UN RESERVOIR DE COLLECTE 12, COMPORTE DES MOYENS 18, 19 DE MISE EN DEPRESSION RACCORDES AU RESERVOIR 12 DE COLLECTE, AFIN D'Y CREER LE VIDE ET DES MOYENS DE PRELEVEMENT 14 MONTES DANS UN SUPPORT 15 APTES A ETRE CONNECTES TEMPORAIREMENT AUX SANITAIRES DE L'AVION POUR LE TRANFERT DES MATIERES ET EAUX USEES DANS LE RESERVOIR 12, LES MOYENS 18, 19, DE MISE EN DEPRESSION DU RESERVOIR, LES MOYENS 14 DE PRELEVEMENT ET LE RESERVOIR 12 ETANT DISPOSES SUR LE CHASSIS 4 DU CHARIOT 1 SOUS LA FORME D'UN ENSEMBLE COMPACT INSCRIT DANS LE CADRE DU CHASSIS 4. L'INVENTION EST PRINCIPALEMENT UTILISEE POUR LA VIDANGE RAPIDE DES SANITAIRES D'AVION.

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01-06-1962 дата публикации

Apparatus of transport of the fluids

Номер: FR0001295073A
Принадлежит:

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11-12-1970 дата публикации

Номер: FR0002034100A7
Автор:
Принадлежит:

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13-10-2017 дата публикации

SYSTEM FOR FILLING AT LEAST ONE FLUID TANK FOR A COMPONENT OF A PLATFORM AND FILLING METHOD

Номер: FR0003018772B1
Автор: CHAISE JEREMIE
Принадлежит: DASSAULT AVIATION

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01-03-2019 дата публикации

METHOD FOR CIRCULATING FUEL IN A CONDUIT FOR FILLING A TANK OF AN AIRCRAFT, AND VALVE CONNECTED TO A CONDUIT FOR SAID METHOD WORK

Номер: FR0003070375A1
Принадлежит: Zodiac Aerotechnics SAS

Procédé de circulation de carburant dans une conduite (2) de remplissage d'un réservoir d'un aéronef. Selon l'invention il consiste à faire varier automatiquement et mécaniquement la section de passage du carburant jusqu'à ce que le carburant atteigne une vitesse seuil maximale. Vanne (1) connectée à une conduite (2) de remplissage d'un réservoir de carburant d'un aéronef pour la mise en œuvre dudit procédé. Selon l'invention elle comprend un dispositif de restriction (7) de la section de passage du carburant, apte, lorsque du carburant circule dans la conduite (2), à faire varier automatiquement la section de passage du carburant jusqu'à ce que la vitesse du carburant atteigne une valeur seuil maximale. A method of circulating fuel in a pipe (2) for filling a tank of an aircraft. According to the invention it consists in automatically and mechanically varying the fuel passage section until the fuel reaches a maximum threshold speed. Valve (1) connected to a pipe (2) for filling a fuel tank of an aircraft for carrying out said method. According to the invention it comprises a device for restricting (7) the fuel passage section, adapted, when fuel circulates in the pipe (2), to automatically vary the fuel passage section until the fuel speed reaches a maximum threshold value.

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04-05-1973 дата публикации

TROLLEY FOR sUPPORTS OF A fLEXIBLE ONEpIPE

Номер: FR0002153720A5
Автор:
Принадлежит:

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30-01-1957 дата публикации

Improvements with the devices with valve

Номер: FR0001130058A
Автор:
Принадлежит:

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18-04-2017 дата публикации

dispositivo para uma plataforma de helicóptero

Номер: BR112014008547A2
Автор: KARL JOHAN RØD
Принадлежит:

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29-04-2021 дата публикации

UNMANNED VEHICLE

Номер: SG11202102709YA
Принадлежит:

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04-02-2010 дата публикации

FUEL QUALITY TRACEABLE AND REMOTE SYSTEM

Номер: WO2010013084A1
Принадлежит:

A fuel quality traceable and remote system for monitoring and controlling fuel characteristics during transport from a fuel supply to a supplied device is provided. The system includes one or more subsystems that include at least one sensor monitoring the characteristics of the fuel. The sensor operably sends the data relating to the characteristics to a data register-transmitter which sends the data to a base station that uploads the data to a remote server. The remote server is remotely accessible by a user. The system can also generate warning messages to warn a user when the characteristics are outside a tolerable range. Further, the system can automatically or manually interrupt fuel transport when the characteristics are outside a tolerable range.

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13-08-2009 дата публикации

AIRCRAFT TANK SYSTEM REFUELLING UNIT AND METHOD FOR REFUELLING AN AIRCRAFT

Номер: WO2009098012A2
Принадлежит:

An aircraft tank system (10) comprises a tank cell for housing fuel, a fuel line (12), connecting the tank cell to fuel inlet connector (14) and a venting device (16), which connects the tank cell to the environment for venting. A shut-off valve (18, 20) for the venting device (16) is designed to open a connection between the tank cell and the environment in the open position and to shut the connection between the tank cell and the environment in the closed position. The aircraft tank system (10) further comprises an exhaust air outlet connector (24) connected to the venting device (16) designed to be connected to a venting connector (32) of storage tank (28) in a refuelling unit (26) on filling the tank cell with fuel.

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16-02-2006 дата публикации

APPARATUS FOR THE MAINTENANCE OF AIRCRAFT

Номер: WO2006016853A1
Принадлежит:

A maintenance unit (10) for facilitating maintenance of an aircraft comprising a housing air driven equipment said equipment including a fuel vapour purging device (75) and operator breathing apparatus (25) wherein the equipment are mounted to the housing for storage and transportation as a unitary device.

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02-04-1963 дата публикации

Номер: US0003083644A1
Автор:
Принадлежит:

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30-06-1981 дата публикации

Full span shipboard fueling system for aircraft

Номер: US0004275860A1
Автор: Brabazon; Jack A.
Принадлежит:

A shipboard system that provides safe storage and complete quality control of aviation fuels from acceptance of the fuel at shipside to delivery of clean, dry fuel at a shipborne aircraft includes a storage tank disposed in a closed chamber defined by a cofferdam. The tank is mounted in the chamber to provide an airspace around all sides which is vented to the atmosphere and maintains any concentration of fuel vapor in the chamber below a predetermined lean limit. Fire protection apparatus of the system is actuated by a rate of temperature rise detector and releases an agent that floods the chamber to terminate the combustion cycle in the event of a fire. Conduit runs include filters to remove contaminants when fuel is pumped through and also include a closed-circuit filtered conduit through which the fuel is frequently recirculated to control deterioration of the system and degradation of the fuel caused by long term storage and intermittent use of the system. The conduits lead downwardly ...

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03-08-1976 дата публикации

Aircraft refueling system

Номер: US0003972448A1
Автор: Brown; Albert W.

This disclosure relates to a hydrant coupling device including a pressure control valve which, due to its portability, may be connected to any one of a plurality of hydrants to regulate the flow of liquid therefrom, and additionally including a pit valve which is interlocked with the pressure control valve body to prevent the spilling of liquid if the control valve is accidentally forced loose from the pit valve.

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29-07-1913 дата публикации

GAS-REGULATING MEANS.

Номер: US1069084A
Автор:
Принадлежит:

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26-07-1932 дата публикации

Service equipment for aviation fields

Номер: US1868497A
Автор:
Принадлежит:

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27-02-1996 дата публикации

Fluid containing and dispensing system

Номер: US0005494191A
Автор:
Принадлежит:

A container and dispenser for fluids, especially hydraulic and engine oil fluids for aircraft. The container, which is preferably made of a recyclable polymer such as high density polyethylene, is rectangularly parallepipedal, with a crowned top to minimize contamination by water or particulate matter. A pump is mounted on the top of the container, and various filters, check valves, and quick disconnect couplings are provided to further minimize contamination. In use, the container is mounted on a 2-wheeled cart that is especially designed to accommodate it.

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04-06-2020 дата публикации

AERIAL VEHICLE WITH ENHANCED PITCH CONTROL AND INTERCHANGEABLE COMPONENTS

Номер: US20200172236A1
Принадлежит:

An aircraft capable of vertical take-off and landing comprises a fuselage, at least one processor carried by the fuselage and a pair of aerodynamic, lift-generating wings extending from the fuselage. A plurality of vectoring rotors are rotatably carried by the fuselage so as to be rotatable between a substantially vertical configuration relative to the fuselage for vertical take-off and landing and a substantially horizontal configuration relative to the fuselage for horizontal flight. The vectoring rotors are unsupported by the first pair of wings. The wings may be modular and removably connected to the fuselage and configured to be interchangeable with an alternate pair of wings. A cargo container may be secured to the underside of the fuselage, and the cargo container may be modular and interchangeable with an alternate cargo container.

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07-08-2014 дата публикации

AUTOMATED FUEL QUALITY DETECTION AND DISPENSER CONTROL SYSTEM AND METHOD, PARTICULARLY FOR AVIATION FUELING APPLICATIONS

Номер: US2014216602A1
Принадлежит:

A fuel quality monitoring system and method to automatically and/or continuously monitor quality of fuel dispensed and control the operation of the fuel dispenser. The control system monitors fuel quality to prevent unsafe refuelings when the fuel quality is unacceptable. In one embodiment, a combination of a differential pressure sensor and a fuel quality monitoring device. If fuel quality is at an acceptable level although not ideal, the control system can allow fueling with the generation of reports and alarms. If the fuel quality is unacceptable, fuel flow can be stopped. If the differential pressure across the filter indicates a high degree of debris and/or water retention, the control system can automatically lower the flow rate to reduce the risk of filter breakdown without completely preventing fueling until the filter can be replaced.

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04-04-2023 дата публикации

Self-aligning liquid coupler systems and related methods

Номер: US0011618563B2
Принадлежит: Deere & Company

Methods, apparatus, systems and articles of manufacture are disclosed for a first link to rotate about a pin joint, a second link rotatably coupled to the first link, the second link having a nozzle at a first end and a weight at a second end opposite the first end, and a fluid inlet including a funnel portion and an opening, the funnel portion having a conical taper converging towards the opening.

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22-06-2023 дата публикации

PILOT VALVE ASSEMBLY

Номер: US20230194002A1
Принадлежит:

The present disclosure relates to an improved pilot valve assembly for a hydrant pit valve. The pilot valve assembly includes a poppet that is movable between an open position and a closed position. The poppet has a molded seal with an interlock feature to hold the seal rigidly. The pilot valve assembly also includes a manually reset mechanism. The reset mechanism can be horizontally positioned and can function to reset the pilot actuator for the next refueling operation. A lanyard can be connected to the poppet to be used a deactuation mechanism.

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11-08-1965 дата публикации

Improvements in and relating to fluid delivery systems

Номер: GB0001000972A
Автор:
Принадлежит:

Подробнее
04-01-2017 дата публикации

Refuelling arrangement

Номер: GB0201619571D0
Автор:
Принадлежит:

Подробнее
13-09-2006 дата публикации

Operational ground support system having automated primary servicing

Номер: GB0000615367D0
Автор:
Принадлежит:

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23-03-2011 дата публикации

Air-to-air refuelling drogue assemblies

Номер: GB0201102184D0
Автор:
Принадлежит:

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09-11-2016 дата публикации

System and method

Номер: GB0201616123D0
Автор:
Принадлежит:

Подробнее
03-02-1960 дата публикации

Control of liquid supply pressure

Номер: GB0000827293A
Автор: DAVIS ALBERT HENRY
Принадлежит:

... 827,293. Fluid-pressure servomotor-control systems; valves. ZWICKY Ltd. March 22, 1957 [March 22, 1956], No. 9012/56. Class 135. A device for maintaining a substantially constant pressure of liquid in a delivery conduit irrespective of variations in demand and applicable, e.g. to a fuel distribution system on an aerodrome, comprises a variable orifice valve 3 in the conduit, a circuit 7 extending from a point upstream of the valve to a point downstream thereof and including a constriction 17, an hydraulic servomotor 4, 5 subject to the pressure in the circuit upstream of the constriction acting to open the valve and to the pressure downstream of the constriction tending to close the valve, and a diaphragm actuated valve 14 controlling egress from the circuit 7 in response to the pressure downstream of the valve 3. As shown, the inlet to the circuit 7 includes a stabilizing valve 11 controlled by a diaphragm 12 subject to the pressure downstream of the valve 11 acting in the valve-closing ...

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15-06-2004 дата публикации

PROTECTING BEACON

Номер: AT0000267431T
Принадлежит:

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15-05-2009 дата публикации

DEFINITION AND ßTANKERINGß an OPTIMAL ADDITIONAL ONE FUEL QUANTITY

Номер: AT0000430092T
Автор: TORE REIMERS
Принадлежит:

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15-12-1992 дата публикации

FAHRZEUG ZUR WARTUNG VON FLUGZEUGEN

Номер: ATA194291A
Автор:
Принадлежит:

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15-09-2010 дата публикации

REGENERATION OF KEROSENE STEAMS AT AIRPORTS AND ENERGY RECOVERY OF EMISSIONS OF VOLATILE ORGANIC COMPOUNDS

Номер: AT0000478004T
Принадлежит:

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25-08-1993 дата публикации

Aircraft maintenance vehicle

Номер: AT0000396354B
Автор:
Принадлежит:

An aircraft maintenance vehicle 1, in particular for emptying toilets in passenger aircraft, has a working platform 4 which is fitted in the rear area of the vehicle and can be adjusted using a lifting device 8 from a rest position close to the ground to its working height. At least one container 16 is provided, which has at least one connection 17 for an emptying pipe which can be connected to an emptying opening on the aircraft and is preferably at least partially flexible, and this container can be emptied via this connection 17 or via a specific outlet 18. In order to allow, in particular, aircraft where the bottom of the fuselage is low to be emptied using simple means, the container 16 is fitted in the bottom area of the platform 4, and can be raised and lowered with the platform. ...

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15-12-1992 дата публикации

VEHICLE FOR MAINTENANCE OF AIRPLANES

Номер: AT0000194291A
Автор:
Принадлежит:

Подробнее
15-03-2006 дата публикации

FUEL CONTAINER

Номер: AT0000319615T
Принадлежит:

Подробнее
27-10-1994 дата публикации

Aircraft refuelling installation

Номер: AU0005936494A
Автор: MAGNE MICHEL, MICHEL MAGNE
Принадлежит:

Подробнее
01-12-2011 дата публикации

Contoured surface defueling fitting

Номер: AU2006333586B2
Принадлежит:

A method and apparatus for defueling an aircraft. The apparatus includes a defueling fitting comprising one or more structural connectors, which may include one or more suction cups. The suction cups are disposed in a mount. The suction cups may be raised from a surface in the mount and arranged in a non-circular pattern to facilitate connection to contoured surfaces. An actuator assembly may be attached to the mount for opening an aircraft defueling valve. The suction cups may be operatively connected to a vacuum source to connect the defueling fitting to an aircraft body, with the actuator assembly positioned at the aircraft defueling valve. The defueling fitting facilitates safe and convenient defueling of aircraft, even aircraft with significantly contoured surfaces.

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22-01-2013 дата публикации

CONTOURED SURFACE DEFUELING FITTING

Номер: CA0002608006C
Автор: KUNTZ, JAMES P.
Принадлежит: SPOKANE INDUSTRIES, INC.

... ²²²A method and apparatus for defueling an aircraft. The apparatus includes a ²defueling fitting comprising one or more structural connectors, which may ²include one or more suction cups. The suction cups are disposed in a mount. ²The suction cups may be raised from a surface in the mount and arranged in a ²non-circular pattern to facilitate connection to contoured surfaces. An ²actuator assembly may be attached to the mount for opening an aircraft ²defueling valve. The suction cups may be operatively connected to a vacuum ²source to connect the defueling fitting to an aircraft body, with the actuator ²assembly positioned at the aircraft defueling valve. The defueling fitting ²facilitates safe and convenient defueling of aircraft, even aircraft with ²significantly contoured surfaces.² ...

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13-10-2009 дата публикации

APPARATUS FOR PROVIDING CONVENIENCE SERVICES TO STATIONARY VEHICLES

Номер: CA0002398960C
Принадлежит: IDLEAIRE TECHNOLOGIES CORPORATION

An apparatus for providing convenience services to stationary vehicles (120) independent of the vehicle electncal system. At least one conduit (106) is attached to a stationary housing (104) for transferring the services to a supply panel (108). The supply panel includes a face on which the various controls and connectors associated with the supplied convenience services, such as heating, cooling, telephone, and television, are disposed. The supply panel (108) is dimensioned to interface with the stationary vehicle (120) through an opening in the vehicle, such as a window or service door, and includes means for providing a substantially airtight seal for climate control.

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30-09-1990 дата публикации

PORTABLE FUELING FACILITY

Номер: CA0002000681A1
Принадлежит:

Подробнее
21-11-2017 дата публикации

FLUID TRANSPORT SYSTEM FOR PREVENTING ELECTRICAL DISCHARGE

Номер: CA0002814430C
Принадлежит: THE BOEING COMPANY, BOEING CO

A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. The fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport system has an electrical configuration. The intensity of the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle is reduced to within selected tolerances by the electrical configuration of the fluid transport system.

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08-12-2013 дата публикации

FLUID TRANSPORT SYSTEM FOR PREVENTING ELECTRICAL DISCHARGE

Номер: CA0002814430A1
Принадлежит:

A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. The fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport system has an electrical configuration. The intensity of the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle is reduced to within selected tolerances by the electrical configuration of the fluid transport system.

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27-06-2000 дата публикации

SHIELDED ASSEMBLY FOR THE DELIVERY OF FUEL ENTIRELY DISAPPEARING INTO THE GROUND AND DIRECTLY CONNECTED TO THE FUEL TANK THROUGH A MANHOLE

Номер: CA0002063735C
Принадлежит: Cutore, Gaetano

Shielded assembly for the delivery of fuel entirely disappearing into the ground and adapted to be used as gasoline pump in civil, in particular military, airports and heliports, bus stations, garages, gas station, said assembly comprising a gasoline pump (12) vertically displaceable between an operative position and a concealed, shielded rest position in which it is entirely received in a casing (10) buried in the ground and closed by a rugged manhole cover (13) which is effraction-free, the vertical movements of the displaceable pump (12) being controlled by a hydraulic cylinder and piston assembly coaxial with the telescopic pipes (43) supplying the gasoline pump with the fuel of the tank (11).

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05-10-1979 дата публикации

Valve for emptying aircraft fuel tanks - has electromagnetically operated jaws to grip collar of valve shaft

Номер: FR0002350250B1
Автор: [UNK]
Принадлежит: CONST AERO NAVALES

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07-12-2012 дата публикации

MACHINE Of FUELLING AND PROCESS Of FUELLING Of an AIRCRAFT WHILE CARBURIZING BY MEANS OF SUCH a MACHINE

Номер: FR0002945273B1
Автор: BECK CLAUDE
Принадлежит: DESAUTEL

Подробнее
21-11-1932 дата публикации

Post for the fuel supply, particularly for airports

Номер: FR0000736210A
Автор:
Принадлежит:

Подробнее
14-02-1986 дата публикации

DISPOSITIF DE RAVITAILLEMENT POUR HELICOPTERES ET AVIONS A DECOLLAGE VERTICAL EN VOL STATIONNAIRE

Номер: FR0002568852A
Автор:
Принадлежит:

CE DISPOSITIF 100 COMPREND UNE BRIDE DE BASE 10 MUNIE D'UNE TUBULURE 11 D'ALIMENTATION POUR L'ARRIVEE DE CARBURANT, ET UNE TUYAUTERIE 20 DE RAVITAILLEMENT EN POSITION VERTICALE, ELASTIQUEMENT RELIEE A LA TUBULURE 11, ET QUI PEUT SE PLACER AUTOMATIQUEMENT EN POSITION VERTICALE A PARTIR D'UNE POSITION DECALEE OU REPLIEE, CETTE TUYAUTERIE DE RAVITAILLEMENT EN POSITION VERTICALE EST COMPOSEE D'UN FLEXIBLE 25 SANS SPIRALE D'UN RESERVOIR SOUS PRESSION POUR LE RAVITAILLEMENT D'AERONEFS ET D'UN ENROULEMENT 21 ELASTIQUE PLACE AUTOUR DU FLEXIBLE DU RESERVOIR SOUS PRESSION, CET ENROULEMENT EST FIXE PAR SES DEUX EXTREMITES 21A, 21B AU VOISINAGE DES DEUX EXTREMITES 25A, 25B DU FLEXIBLE 25 DU RESERVOIR SOUS PRESSION POUR EMPECHER TOUT DEPLACEMENT, ET CE FLEXIBLE 25 EST EQUIPE A SA PARTIE SUPERIEURE 25A D'UN RACCORD 30 LUI-MEME EQUIPE D'UN DISPOSITIF D'ACCOUPLEMENT 31 POUR LE RAVITAILLEMENT EN VOL. CE DISPOSITIF, MONTE SUR UN CAMION-CITERNE OU UN NAVIRE, PERMET DE RAVITAILLER AISEMENT EN CARBURANT DES ...

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25-05-1960 дата публикации

Apparatus and process for the elimination of the dangerous vapors during fuelling of a plane

Номер: FR0001220508A
Принадлежит:

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09-09-1936 дата публикации

Transportable cistern, in particular for aviation

Номер: FR0000802605A
Автор:
Принадлежит:

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18-12-1957 дата публикации

Drain for liquids

Номер: FR0001148913A
Автор:
Принадлежит:

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09-11-2018 дата публикации

FLUID COUPLER

Номер: FR0003066005A1
Принадлежит:

Un coupleur de fluide comporte un boîtier avec un orifice d'entrée et un orifice de sortie, un piston disposé dans le boîtier et configuré pour commander l'écoulement de fluide entre l'orifice d'entrée et l'orifice de sortie, et un dispositif de retenue de piston disposé dans le boîtier. Un piston peut comporter au moins un élément de support s'étendant radialement, et l'élément de support s'étendant radialement peut comporter une ouverture. L'au moins un élément de support s'étendant radialement peut être sensiblement plan.

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15-04-2011 дата публикации

DEVICE AND PROCESS OF CONNECTION HAVE a PIPING END FUEL DUMP VALVE Of AIRCRAFT

Номер: FR0002951241A1
Автор: MATEO STEPHANE

Le dispositif de connexion à un embout de vidage (1) tuyauterie vide-vite d'aéronef, ledit embout de vidage (1) comportant un tube souple sensiblement cylindrique (4), et une pièce rigide (3) formant interface entre le tube cylindrique (4) et la structure de l'aéronef, ladite pièce rigide (3) présentant un diamètre généralement croissant de la structure de l'aéronef vers le tube cylindrique (4), se compose de deux éléments disjoints : - une pièce d'interface (7) destinée à venir s'assembler autour de la pièce rigide (3), - un tuyau d'évacuation (14), présentant en une première extrémité un diamètre interne supérieur au diamètre externe du tube cylindrique (4), ledit tuyau d'évacuation (14) comportant en cette première extrémité des moyens de fixation réversible sur la pièce d'interface (7), et dans sa partie intérieure des moyens (23, 24, 28, 29) d'assurer une étanchéité autour du tube cylindrique (4).

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13-09-2019 дата публикации

DEVICE FOR REFUELING AN AIRCRAFT AND METHOD OF MANUFACTURING A CATCHER WING FOR SUCH A DEVICE

Номер: FR0003078684A1
Автор: BECK CLAUDE, BECK, CLAUDE
Принадлежит:

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19-02-2020 дата публикации

DOUBLE DOOR STRUCTURE FOR UNDERGROUND HYDRANT SERVICE PIT

Номер: KR0102079025B1
Автор: JEE SUNG KEUN
Принадлежит:

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02-02-2012 дата публикации

APPARATUS AND METHOD OF RECOVERING VAPORS

Номер: WO2012015377A1
Принадлежит:

An apparatus and method is disclosed for recovering a flammable vapor emanating from a vent of a tank. The apparatus comprises an input conduit for connecting to the vent of the tank. An input manifold connects the input conduit to an input of a compressor with an output manifold connecting an output of the compressor to an input of a storage tank. An output conduit connects an output of the storage tank to the turbine generator for generating electrical power by processing the flammable vapor. An electrical connector directs electrical power from the turbine generator to drive the apparatus as well as to supply surplus power to an external load.

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17-11-2005 дата публикации

AIRCRAFT DEFUELING SYSTEM

Номер: WO2005108206A2
Автор: KUNTZ, James, P.
Принадлежит:

An apparatus and method for defueling and aircraft. The apparatus includes a vacuum fuel tank comprising a first vacuum generator, a defueling hose in fluid communication with the vacuum fuel tank, a first defueling fitting attached to the first defueling hose, and a second vacuum generator operatively connected to the first defueling fitting. By providing both a first and a second vacuum generator, the defueling fitting can be attached and detached from an aircraft independent of the suction used to withdraw fuel from an aircraft. According to some embodiments, there may be multiple defueling hoses and additional vacuum generators. Further, some embodiments include a telescoping funnel that can be selectively isolated from the vacuum fuel tank so that the tank can be held at vacuum pressure.

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11-05-1982 дата публикации

Pressure fueling adapter

Номер: US0004328844A1
Принадлежит: Parker-Hannifin Corporation

A pressure fueling adapter for aircraft has spring loaded primary and secondary nested poppets for controlling fluid flow therethrough, the primary poppet operable by engagement with the position lever of a fuel nozzle and the secondary poppet responsive to pressure differentials to allow inlet fluid flow and check back flow. A cam interengagement mechanism may be manually actuated to connect the primary and secondary poppets for simultaneous movement by the position lever of the fuel nozzle to defeat the secondary poppet check, for defueling purposes.

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30-07-2019 дата публикации

Automated water and particle detection for dispensing fuel including aviation fuel, and related apparatuses, systems, and methods

Номер: US0010364139B2

A fuel dispensing apparatus and method for delivering fuel from a fuel source, including, without limitation, delivering aircraft fuel from a fuel tank to an aircraft is disclosed. The fuel dispensing apparatus also includes an electronic control system in communication with a particle detector and configured to receive fuel quality sensor information corresponding to at least one detected fuel quality characteristic in real time. The electronic control system is configured to determine, based on the received fuel quality sensor information, a particle ratio defined as an approximate ratio of a measurement of total water and particulate per unit volume of fuel, and a first water characteristic indicative of a presence or absence of a threshold amount of water per unit volume of fuel. Based on the first water characteristic and on the particle ratio, the electronic control system is configured to determine whether to initiate at least one corrective action.

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02-08-1910 дата публикации

EXHAUST-MUFFLER CUT-OUT VALVE.

Номер: US966345A
Автор:
Принадлежит:

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30-07-2020 дата публикации

EN ROUTE FLUID TRANSMITTING APPARATUS

Номер: US20200239154A1
Принадлежит: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

An en route fluid transmitting apparatus for transmitting a fluid from a transmitting entity to a probe of a receiving vehicle includes a funnel, a hose and a thrust producing device. Thrust producing device includes a main body that is rigidly attached to the funnel, and at least two rotors that are connected to the main body for producing thrust. The thrust producing device is adapted to move the funnel freely in any direction to a predetermined position relative to the probe where the funnel engages with the probe. 1. An en route fluid transmitting apparatus for transmitting a fluid from a transmitting entity to a probe of a receiving vehicle , comprising:a funnel that is adapted to engage with the probe; a first end that is attached to the transmitting entity, and', 'a second end, that is attached to the funnel, wherein the hose is adapted to convey the fluid from the transmitting entity to the funnel; and, 'a hose, comprising a main body that is rigidly attached to the funnel, and', 'at least two rotors that are connected to the main body for producing thrust,, 'a thrust producing device, comprising'}wherein the thrust producing device is adapted to move the funnel freely in any direction to a predetermined position relative to the probe where the funnel engages with the probe.2. The en route fluid transmitting apparatus of claim 1 , wherein the thrust producing device further comprises:a control system that communicates with the probe and directs the thrust producing de-vice to move the funnel to the predetermined position relative to the probe.3. The en route fluid transmitting apparatus of claim 2 , wherein the control system controls the thrust producing device to maintain the funnel in the predetermined position relative to the probe for a predetermined period of time.4. The en route fluid transmitting apparatus of claim 2 , wherein the control system further comprises:a machine vision device that is adapted to identify a trajectory from a current position ...

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30-08-1989 дата публикации

Automatic shut-off and self-locking refueling nozzle

Номер: EP0000330318A1
Принадлежит:

The invention pertains to an automatic shut-off refueling nozzle (10) particularly suitable for use with military vehicles employing a nozzle having a liquid level sensor (20,22) operating a flow valve (12), the nozzle includes a lug plate (60) attachable to the inlet (74) of the tank receptacle being filled wherein once attached to the tank inlet (74) the presence of an operator is not required during refueling. A diverger (26) on the nozzle spout (14) improves flow characteristics within the tank inlet (74) to prevent immature release of the nozzle flow valve (12) and the nozzle prevents contamination during refueling and prevents spillage of volatile fuels even though unattended. An embodiment of the invention utilizes a secondary control valve (138) preventing fluid flow until the nozzle has been fully connected to the tank inlet.

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20-07-2015 дата публикации

ПРОВОДЯЩИЙ СОЕДИНИТЕЛЬ В СБОРЕ

Номер: RU2556837C2
Принадлежит: ДЗЕ БОИНГ КОМПАНИ (US)

Группа изобретений относится к способу и устройству для обеспечения прохождения электрического тока между первым транспортировочным элементом и вторым транспортировочным элементом. В одном представленном варианте осуществления соединитель в сборе содержит первый фитинг, соединенный с первым концом первого транспортировочного элемента, второй фитинг, соединенный со вторым концом второго транспортировочного элемента, и уплотнение. Уплотнение сконструировано для размещения вокруг первого фитинга и второго фитинга, когда первый конец первого транспортировочного элемента позиционирован относительно второго конца второго транспортировочного элемента. Уплотнение дополнительно сконструировано для уплотнения границы раздела между первым транспортировочным элементом и вторым транспортировочным элементом. Уплотнение состоит из материала, выбранного таким образом, чтобы уплотнение обладало уровнем проводимости в пределах выбранного диапазона, и чтобы был сформирован проводящий канал между первым транспортировочным ...

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10-09-2000 дата публикации

СПОСОБ ЗАПРАВКИ ТОПЛИВОМ КОСМИЧЕСКОГО АППАРАТА И УСТРОЙСТВО ДЛЯ ЕГО ОСУЩЕСТВЛЕНИЯ

Номер: RU2155705C2
Принадлежит: МОТОРОЛА, ИНК. (US)

Изобретение относится к способу заправки топливом космического аппарата и к устройству для его осуществления, в частности, к загрузке топливом типа гидразина из объединенного заправочного модуля в топливный бак космического аппарата. Объединенный заправочный модуль (10) содержит бак переноса топлива (14), вакуумный бак (12) и бак с компрессионным веществом (16). Заполненный бак переноса топлива (14) транспортируется на стартовую позицию к заправочному модулю (10). Перед стартом заправочный модуль (10) присоединяется к космическому аппарату (50). Топливо перекачивается под действием компрессионного вещества в топливный бак (52) космического аппарата. Компрессионное вещество создает в топливном баке (52) полетное давление. Все оставшееся топливо удаляется из соединителя (45) и линий передачи топлива (42) при помощи вакуумного бака (12). Такой способ заправки космического аппарата и устройство для его осуществления уменьшают вероятность возникновения утечек топлива. 3 с. и 7 з.п.ф-лы, 2 ил ...

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20-04-2023 дата публикации

Устройство выдачи топлива в воздушное судно

Номер: RU217827U1

Полезная модель относится к техническим средствам выдачи партии топлива в воздушное судно с необходимыми присадками, в частности с противоводокристаллизационной жидкостью. Требуемый технический результат заключается в повышении качества выдаваемого топлива с необходимыми присадками, достигается в устройстве, содержащем блок фильтрации топлива, снабженный водоотделителем, входной патрубок которого выполнен с возможностью соединения с трубопроводом приема топлива из цистерн и транспортных мер вместимости, блок ввода в топливо присадки и раздаточный рукав, выполненный с возможностью соединения через наконечник нижней заправки к средствам приема топлива воздушного судна, расходомер-счетчик массовый, соединенный входным трубопроводом с выходным патрубком блока фильтрации, а выходным трубопроводом соединенный со входом раздаточного рукава, а также блок учета и управления, первый вход которого соединен с информационным входом датчика температуры, установленным во входном трубопроводе расходомера-счетчика ...

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09-08-2012 дата публикации

Air-to-air refueling drogue assemblies

Номер: US20120199696A1
Принадлежит: Flight Refuelling Ltd

An air to air refuelling drogue assembly includes a reception coupling and a drogue canopy connected to the reception coupling by connection means which hold the canopy in an operative, drag producing, position relative to the reception coupling during refuelling. The drogue assembly is arranged to controllably fail so as to reduce the drag load produced by the drogue when a drag load on the canopy exceeds a predetermined threshold.

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28-03-2013 дата публикации

FUELLING ARRANGEMENT AND METHOD

Номер: US20130075532A1
Принадлежит: FUEL MATRIX LTD

A method of fuelling an aircraft for a flight to a predetermined destination in which the aircraft is loaded, the actual zero fuel weight of the loaded aircraft is determined, the fuel requirement of the loaded aircraft for that destination is calculated by fuel calculation software on the basis of operational flight plan data, said actual zero fuel weight, and further data relevant to fuel consumption for that instance of the flight to the predetermined destination, said further data being processed interactively by the user by means of a user interface to said fuel calculation software, and subsequently fuel to meet said fuel requirement is uplifted to the aircraft under the control of said user. 1. A method of fuelling an aircraft for a flight to a predetermined destination wherein the aircraft is loaded , the actual zero fuel weight of the loaded aircraft is determined , the fuel requirement of the loaded aircraft for that destination is calculated by fuel calculation software on the basis of operational flight plan data , said actual zero fuel weight , and further data relevant to fuel consumption for that instance of the flight to the predetermined destination , said further data being processed interactively by the user by means of a user interface to said fuel calculation software , and subsequently fuel to meet said fuel requirement is uplifted to the aircraft under the control of said user.2. A method according to wherein the user interface is on the aircraft.3. A method according to wherein said further data is entered at said user interface by the user.4. A method according to wherein the operational flight plan data includes statistical data based on previous instances of flights to said destination and the method includes means for reporting actual fuel consumption data after said flight.5. A method according to wherein actual fuel consumption data is processed by a user during said reporting.6. A method according to wherein said further data takes ...

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16-05-2013 дата публикации

Refuel control system and method of refuelling

Номер: US20130119202A1
Автор: Clive Robert French
Принадлежит: Airbus Operations Ltd

The invention provides a refuel control system for controlling refuel of at least one tank ( 111,112,113, 14,115,116 ) onanaircraft 100, the refuel control system comprising monitoring apparatus ( 241, 242, 280, 371, 372, 380, 311, 312, 313, 314, 315, 316, 221 ) for monitoring data relevant to the refuel process, a control device ( 330 ) for receiving said data from the monitoring apparatus, and a refuel valve ( 130 ) for controlling flow of fuel to the tank wherein said refuel valve is controllable by the control device such that refuel of the tank can be controlled based on the monitored data. The invention also provides a method of refuelling at least one fuel tank on an aircraft.

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12-12-2013 дата публикации

Conductive Coupling Assembly

Номер: US20130327888A1
Принадлежит: Boeing Co

A method and apparatus for conducting an electrical current between a first transport member and a second transport member. In one illustrative embodiment, a coupling assembly comprises a first fitting associated with a first end of a first transport member, a second fitting associated with a second end of a second transport member, and a seal. The seal is configured for placement around the first fitting and the second fitting when the first end of the first transport member is positioned relative to the second end of the second transport member. The seal is further configured to seal an interface between the first transport member and the second transport member. The seal is comprised of a material configured such that the seal has a level of conductivity within a selected range and such that a conductive pathway is formed between the first transport member and the second transport member.

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12-12-2013 дата публикации

Composite Tubes for a Fluid Transport System

Номер: US20130328307A1
Принадлежит: Boeing Co

A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. In one illustrative embodiment, an apparatus comprises a transport member. The transport member is configured for use in the fluid transport system. The transport member is comprised of a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member.

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10-02-2022 дата публикации

UNMANNED VEHICLE

Номер: US20220041299A1
Принадлежит:

The application provides an autonomous refueling vehicle for a hydrogen-electric aircraft, which includes two or more wings. The wings are provided with one or more removable electric propulsion pods. The autonomous refueling vehicle includes a hydrogen refueling module adapted to connect to the propulsion pods and to a hydrogen source. The autonomous refueling vehi-cle includes also includes a propulsion pod handling device, which is adapted to remove the propulsion pod from the wings and to position the propulsion pods on the hydrogen refueling module such that the propulsion pods are connected to the hy-drogen refueling module. The autonomous refueling vehicle is also adapted to autonomously move itself to the hydrogen source to allow the hydrogen refueling module to removably connect to the hydrogen source for refueling of the propulsion pods. 1. An autonomous refueling vehicle for a hydrogen-electric aircraft , wherein the hydrogen-electric aircraft comprisesat least two wings, and a body that comprises a hydrogen refueling interface for receiving hydrogen, and', 'a lock and unlock mechanism being adapted to removably attach the body to one of the two wings,, 'at least one removable electric propulsion pod that is attached to one of the two wings, the at least one removable electric propulsion pod comprising'} a hydrogen refueling module being adapted to connect to the hydrogen refueling interface and to a hydrogen source, and', 'a propulsion pod handling device being adapted to activate the lock and unlock mechanism to remove the at least one removable electric propulsion pod from one of the two wings, and to position the at least one removable electric propulsion pod on the hydrogen refueling module such that the hydrogen refueling interface is connected to the hydrogen refueling module,, 'the autonomous refueling vehicle comprising'}wherein the autonomous refueling vehicle is adapted to autonomously move itself to the hydrogen source to allow the hydrogen ...

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17-02-2022 дата публикации

Aircraft refueling system

Номер: US20220048644A1
Принадлежит: Eaton Intelligent Power Ltd

An aircraft refueling system ( 10 ) includes a master controller ( 12 ), a fleet controller ( 14 ) in communication with the master controller, a platform controller ( 18 ) in communication with the fleet controller, and a fuel control system ( 16 ) in communication with the platform controller. Embodiments of an aircraft refueling system may include a primary pressure controller ( 20 ), a secondary pressure controller ( 22 ), a programmable logic controller ( 24 ), and a data logger controller ( 26 ). The master controller may be configured to receive and analyze data from at least one of the fleet controller, the platform controller, and the fuel control system; and to modify operational parameters or upgrade the fuel control system based at least in part on the analysis of received data.

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31-01-2019 дата публикации

FUELLING METHOD

Номер: US20190031364A1
Принадлежит: I6 GROUP LIMITED

A fuelling method is described which comprises the steps of dispensing an initial quantity of fuel to a fuel tank, waiting for a predetermined settling period for the fuel dispensed to the fuel tank to homogenise and settle, after the predetermined settling period has elapsed, taking a fuel quantity reading using a fuel gauge associated with the fuel tank, calculating a differential volume of fuel between the fuel gauge reading and a desired final fuel quantity, and dispensing to the fuel tank a volume of fuel substantially equivalent to the differential volume using a dispensing apparatus including a fuel volume meter. 1. A fuelling method comprising the steps of:dispensing an initial quantity of fuel to a fuel tank;waiting for a predetermined settling period for the fuel dispensed to the fuel tank to homogenise and settle;after the predetermined settling period has elapsed, taking a fuel quantity reading using a fuel gauge associated with the fuel tank;calculating a differential volume of fuel between the fuel gauge reading and a desired final fuel quantity;dispensing to the fuel tank a volume of fuel substantially equivalent to the differential volume using a dispensing apparatus including a fuel volume meter; andnotifying an officer associated with the apparatus of the total fuel quantity contained within the fuel tank, the fuel quantity comprising a combination of the fuel quantity read using the fuel gauge after dispensing the initial quantity of fuel and waiting for the settling period to elapse, and the differential volume measured using the fuel volume meter.2. A method according to claim 1 , wherein the step of calculating takes into account the density of the fuel being dispensed.3. A method according to claim 2 , wherein the dispensing apparatus includes a fuel density meter.4. A method according to claim 1 , and used in the fuelling of an aircraft.5. A method according to claim 4 , wherein claim 4 , after dispensing of the differential volume claim 4 , ...

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04-02-2021 дата публикации

AUTOMATED FUELING PRESET CONVERSION AND CONTROLS

Номер: US20210031946A1
Принадлежит: Liquid Controls LLC

An improved fluid transfer accuracy, information collection, and overall management. A system may utilize a pump to transfer fluid from a source to a target vessel, a meter for measuring an amount of fluid transferred, a density meter to detect actual fluid density, and a control unit to determine actual fluid transfer amount based on density. As an example, a fluid flow meter can be coupled with a flow conduit to determine fluid volume, along with the density meter to detect real-time density of transferred fluid. During a fluid transfer event, such as aircraft refueling, LPG fueling, or other refined fuels or valuable liquids, fluid volume can be converted to fluid weight in real-time based on actual density. The real-time fluid weight can be used to determine if a target fluid weight has been reached, and fluid flow can be shut off at the appropriate time. 1. A system for accurately delivering fuel to a target fluid vessel , comprising:a fluid flow meter disposed in line of a fuel delivery conduit to measure an amount of a flow of fuel passing through the conduit;a density measuring device comprising a body at least a portion of which is disposed in the conduit to operably determine the real-time density of the fuel that passes through the fluid flow meter; and convert the measured volume of fuel to a unit of mass of fuel that passes through the fluid flow meter; and', 'determine an amount of fuel to be dispensed in real-time to reach a target total mass of fuel, based at least upon an existing mass of fuel in a target aircraft and the target total mass of fuel., 'a control unit comprising a processor, the control unit receiving data indicative of the amount of fuel measured by the fluid flow meter in volume, and receiving data indicative of the real-time density of the fuel from the density measuring device, the control unit using the processor to2. The system of claim 1 , comprising a shut-off that operably claim 1 , automatically shuts off the flow of fuel ...

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11-02-2016 дата публикации

HYDRANT COUPLER WITH ARTICULATING HANDLE ASSEMBLY

Номер: US20160039538A1
Автор: Freeth Gilbert Peter
Принадлежит: EATON CORPORATION

A hydrant coupler () is disclosed that includes a coupler body (), an actuating collar () movable relative to the coupler body () and a handle assembly () connected to the actuating collar (). The handle assembly () includes an upper arm component () and a lower arm component () separated by a handle articulating feature () that connects the upper and lower arm components (), but permits relative motion therebetween. 1. A hydrant coupler comprising:a coupler body;an actuating collar movable relative to the coupler body; anda handle assembly connected to the actuating collar, the handle assembly including an upper arm component and a lower arm component separated by a handle articulating feature that connects the upper and lower arm components, but permits relative motion therebetween.2. The hydrant coupler of claim 1 , wherein a portion of the handle articulating feature is removably secured to the upper arm component.3. The hydrant coupler of claim 1 , wherein a portion of the handle articulating feature is integral with the upper arm component.4. The hydrant coupler of claim 1 , wherein the handle articulating feature comprises a first slot sized to allow passage of a fastener claim 1 , the fastener extending through the first slot and secured to the lower arm component in a manner that connects the upper arm component to the lower arm component claim 1 , but permits relative motion therebetween.5. The hydrant coupler of claim 4 , wherein the handle articulating feature further comprises a second slot and the lower arm component comprises a pin claim 4 , and wherein at least a portion of the pin extends through the second slot so that movement of the upper arm component is guided by the interaction between the pin and the second slot.6. The hydrant coupler of claim 5 , wherein the second slot is generally semi-circular or kidney shaped.7. The hydrant coupler of claim 5 , wherein the second slot comprises an upper locking portion and a lower locking portion and ...

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06-02-2020 дата публикации

REFUELLING SYSTEM

Номер: US20200039660A1
Автор: Mills Richard
Принадлежит:

A refuelling system is disclosed having a fuel conduit, a variable-position valve for controlling a rate of flow of fuel leaving the conduit, and a controller. The controller is configured to receive from a sensor arrangement a measurement of an electrostatic condition in a fuel tank being fuelled by the system. The controller is configured to control the variable-position valve to control the rate of flow of fuel based at least in part on the measurement received from the sensor arrangement. 1. A refuelling system , the system comprising:a fuel conduit;a variable-position valve for controlling a rate of flow of fuel leaving the conduit; anda controller; whereinthe controller is configured to receive from a sensor arrangement a measurement of an electrostatic condition in a fuel tank being fuelled by the system and the controller is configured to control the variable-position valve to control the rate of flow of fuel based at least in part on the measurement received from the sensor arrangement.2. The refuelling system of wherein the variable-position valve is a shutter valve which defines a variable sized opening arranged for fuel to flow through claim 1 , and wherein the controller is configured to control the size of the opening defined by the shutter valve to control the rate of flow of fuel.3. The refuelling system of claim 1 , wherein the measurement of the electrostatic condition in the fuel tank is based on an electric field measurement.4. The refuelling system of claim 1 , wherein the measurement of the electrostatic condition in the fuel tank is based on a streaming current measurement.5. The refuelling system of wherein the controller is configured to receive a determination of a level of fuel in the tank claim 1 , and wherein the controller is configured to control the variable-position valve based on the measurement of the electrostatic condition in the fuel tank and based on the determined level of fuel in the tank.6. The refuelling system of wherein ...

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18-02-2021 дата публикации

FUELLING ARRANGEMENT AND METHOD

Номер: US20210047054A1
Принадлежит:

A method of fuelling an aircraft for a flight to a predetermined destination in which the aircraft is loaded, the actual zero fuel weight of the loaded aircraft is determined, the fuel requirement of the loaded aircraft for that destination is calculated by fuel calculation software on the basis of operational flight plan data, said actual zero fuel weight, and further data relevant to fuel consumption for that instance of the flight to the predetermined destination, said further data being processed interactively by the user by means of a user interface to said fuel calculation software, and subsequently fuel to meet said fuel requirement is uplifted to the aircraft under the control of said user. 1. (canceled)2. A method of fuelling an aircraft for a single instance of a flight from a departure point to a predetermined destination in order to minimize fuel consumption and COemissions for that single instance of a flight , wherein the method comprises:setting an initial total quantity of fuel based on an operational flight plan two or three hours before take-off which is based upon an estimated zero fuel weight; andsubsequently determining what the actual zero fuel weight of the aircraft will be when it is loaded; operational flight plan data for that instance of the flight;', 'said actual zero fuel weight; and', 'second data relevant to fuel consumption for that instance of the flight to the predetermined destination, said second data being data liable to change after the time an operational flight plan is produced using operational flight plan data, said second data comprising one or more of taxi time to runway, taxi time at destination, holding time at destination, contingency fuel, implementation of low visibility procedures, and weather at departure point, en route and at destination, said second data being processed interactively by a member of flight crew for that instance of the flight by means of a user interface to said fuel calculation software, said ...

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08-05-2014 дата публикации

INTELLIGENT SELF-LEVELING DOCKING SYSTEM

Номер: US20140124621A1
Принадлежит:

A docking system for an unmanned aerial vehicle (UAV) is described that provides a stable landing and take-off area as well as, in some embodiments, refueling and/or data transfer capabilities. The docking system may be portable to provide a ready docking area for a UAV in areas that may not otherwise be suitable for UAV operation. The docking system may include a landing surface, an orientation mechanism that adjusts the landing surface to provide a level landing area, and an alignment mechanism coupled with the landing surface that moves a UAV resting on the landing surface to a predetermined location on the landing surface for automated refueling of the UAV. A latching mechanism may secure the UAV to the landing surface when the UAV is located at the predetermined location. 1. An unmanned aerial vehicle (UAV) docking apparatus , comprising:a landing surface;an orientation mechanism coupled with the landing surface configured to adjust the orientation of the landing surface; andan alignment mechanism coupled with the landing surface configured to move a UAV resting on the landing surface to a predetermined location on the landing surface.2. The apparatus of claim 1 , wherein the orientation mechanism is configured to adjust the landing surface to provide a level surface during UAV landing and take-off.3. The apparatus of claim 2 , wherein the orientation mechanism comprises a level sensor and two or more actuators configured to selectively rotate and tilt the landing surface based on feedback from the level sensor.4. The apparatus of claim 1 , wherein the alignment mechanism comprises two or more wipers coupled with the landing surface and operable to contact the UAV and move the UAV along the landing surface to the predetermined location.5. The apparatus of claim 4 , wherein the wipers are interconnected with linear actuators.6. The apparatus of claim 1 , wherein the orientation mechanism and alignment mechanism each comprise pneumatic linear actuators coupled ...

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25-02-2021 дата публикации

ASSET UTILIZATION MANAGEMENT FOR AIRCRAFT GROUND REFUELING EQUIPMENT

Номер: US20210053700A1
Принадлежит:

A system for monitoring components of an aircraft ground refueling system includes a first computing device and a second computing device hosting a data base. The first computing device is caused to read a component identification tag secured to a component of an aircraft ground refueling system; the tag contains a unique component identifier. The first computing device transmits the component identifier to the second computing device which verifies that the component identifier is active in the data. The first computer, responsive to the verification, displays a user interface to receive data representative of an operational status of the component and transmits the operational status. The second computing device stores the data in the database to create an operational history of the component. The second computing device analyzes the history of the data to determine a characteristic operational parameter of the component of the aircraft ground refueling system. 1. A method for monitoring components of an aircraft ground refueling system comprising:generating a unique component identification for each one of a plurality of components of an aircraft ground refueling system;tagging each one of the plurality of components with an electronically readable tag containing the unique component identification;deploying each of the tagged components into active use in a specific aircraft ground refueling system;storing the unique component identification in a database of a first computing device;electronically reading at least one of the tags of one of the plurality of components with a second computing device;receiving data reflective of an interaction with the one of the plurality of components at the second computing device, associating the received data with the unique component identification of the one of the plurality of components at the second computing device, and transmitting the unique component identification along with the data from the second computing device ...

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25-02-2021 дата публикации

Gas Blanketing Management of Low-Pressure Hydrocarbon Tanks

Номер: US20210053755A1
Принадлежит: TERRA PRIMORIS HOLDINGS, L.L.C.

A hydrocarbon tank system environment corrosion inhibitor includes use of inert gas, preferably Nitrogen, to blanket ullage and interstice through the tank system. Blanket gas is provided is controller into coupling to access ullages. Blanket gas is provided upon fueling events to stabilize the pressure m the system and prevent entry of atmospheric air and water (vapor). Blanket gas may be continuously run into the ullage and/or other spaces in tank system. A controlled system allows for monitoring of pressures in the tank, and thereby identifies pressure events and even leaks in system due to unusual events, or general loss of pressure. 1. A method for protecting deterioration of a small or medium sized underground fuel storage tank , said method comprising:(a) providing a source of Nitrogen Mas under pressure through a conduit interconnecting an ullage of the tank ullage and an annular compartment about the tank;(b) controlling flow of the Nitrogen gas via a valve to alternately or concurrently supply the Nitrogen gas through the conduit into the ullage and/or annular space;(c) maintaining pressure within the tank via a pressure vacuum valve separate from ambient atmospheric pressure;(d) refilling the tank with fuel; and(e) venting exhaust Nitrogen gas from the ullage upon said step of refilling through the pressure vacuum valve.2. The method of further comprising the steps of:(f) controlling release of Nitrogen gas from the pressure vacuum valve via a controller; and(g) monitoring pressure within the tank; and(h) sending information regarding the pressure readings from said step of monitoring to the controller.2. The method of further comprising the step of:(i) programming the controller to respond to drops in pressure in the tank; and(j) supplying a predetermined amount of Nitrogen gas into the tank to stabilize pressure within the tank based on preprogrammed indicated drop sensed in said step of monitoring.4. The method of claim 2 , whereby the controller ...

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13-02-2020 дата публикации

FLUID SYSTEM

Номер: US20200047909A1
Принадлежит:

A fluid system includes a controller, a control valve, and a fluid manifold. At least one solenoid may be connected to the fluid manifold, the control valve, and/or the controller. A first pressure sensor may be in fluid communication with an output of the control valve. A second pressure sensor may be in fluid communication with the fluid manifold. The controller may be configured to control operation of the control valve via the at least one solenoid according to a first fluid pressure obtained via the first pressure sensor and according to a second fluid pressure obtained via the second pressure sensor. 1. A fluid system , comprising:a controller;a control valve;a fluid manifold;at least one solenoid connected to the fluid manifold, the control valve, and the controller;a first pressure sensor in fluid communication with an output of the control valve; anda second pressure sensor in fluid communication with the fluid manifold;wherein the controller is configured to control operation of the control valve via the at least one solenoid according to a first fluid pressure obtained via the first pressure sensor and according to a second fluid pressure obtained via the second pressure sensor.2. The fluid system of claim 1 , wherein the control valve includes a piston claim 1 , the controller is configured to determine a position of the piston claim 1 , and the controller is configured to control operation of the control valve according to the position of the piston.3. The fluid system of claim 2 , wherein the controller is configured to determine the position of the piston according to a spring constant claim 2 , a spring length of a spring of the control valve claim 2 , and the second fluid pressure.4. The fluid system of claim 1 , including a calibration pressure sensor connected to a fluid chamber of the control valve and configured to sense a fluid pressure in the control valve.5. The fluid system of claim 1 , including a second controller and a second control ...

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21-02-2019 дата публикации

HYDRAULIC FUEL PUMP APPARATUS FOR A FUEL DELIVERY CHASSIS, SUITABLE FOR REFUELING AIRCRAFT, AND RELATED DEVICES, SYSTEMS AND METHODS

Номер: US20190056754A1
Принадлежит:

Embodiments include a modular fuel pump apparatus for an aircraft refueling chassis and related devices, systems and methods. In one exemplary embodiment, a pump module includes a hydraulic motor driven by a hydraulic pump connected to a chassis motor. A chassis engine is operated at a substantially constant RPM, which causes the hydraulic pump to output hydraulic fluid to the pump module at a substantially constant hydraulic pressure. The speed of the hydraulic motor can be varied by a proportional flow control valve disposed between the hydraulic pump and the hydraulic motor, thereby varying the speed of the fuel pump and the flow rate of the fuel. A controller is configured to operate the pressure control valve such that the flow of the fuel is maintained at a predetermined flow rate. 1. A pump module for a fuel delivery chassis , comprising:a proportional flow control valve configured to receive hydraulic fluid at a first hydraulic fluid flow rate from a hydraulic pump driven by a vehicle engine, the proportional flow control valve configured to allow at least a portion of the hydraulic fluid to pass through at a second hydraulic fluid flow rate;a hydraulic motor configured to receive and be driven by the hydraulic fluid passing through the proportional flow control valve at the second hydraulic fluid flow rate, the hydraulic motor configured to rotate at a rotational rate corresponding to the second hydraulic fluid flow rate;a fuel pump configured to be driven by the hydraulic motor, the fuel pump configured to pump fuel from a fuel storage receptacle to at least one fuel delivery hose assembly at a fuel flow rate corresponding to the rotational rate of the hydraulic motor; anda controller configured to control the proportional flow control valve to adjust the second hydraulic fluid flow rate to maintain the fuel flow rate within a predetermined flow rate range.2. The pump module of claim 1 , wherein the at least one fuel delivery hose assembly comprises at ...

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11-03-2021 дата публикации

Stackable housing containers and related systems

Номер: US20210074170A1
Принадлежит: Deere and Co

Methods, apparatus, systems, and articles of manufacture are disclosed to house a vehicle, including a first container leg disposed on a first corner of a first container, a second container leg disposed on a second corner of the first container, a third container leg disposed on a third corner of the first container, a fourth container leg disposed on a fourth corner of the first container, at least one of the first, second, third, and fourth container legs each having an upper portion with a ramped receiving slot and a lower portion with a first ramped foot, and wherein the ramped receiving slot is to receive a protrusion associated with a second ramped foot of a second container different from the first container.

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18-03-2021 дата публикации

AIRCRAFT REFUELING SYSTEM WITH FLOW BOOSTER AND METHOD OF USING SAME

Номер: US20210078728A1
Принадлежит:

A flow booster for optimizing flow of fuel passing into an aircraft. The flow booster includes a fuel intake fluidly coupled to the fuel circuit, and includes a housing and a piston. The piston has a piston head slidably movable in the housing to define h a variable fuel inlet to receive the fuel. The fuel applies a fuel force to the piston. An intake tuner is operatively connected to the fuel M intake, and has a tuning force applied to the piston against the fuel force. A trigger is coupled to the intake tuner to vary the tuning force applied by the intake tuner. The flow regulator is coupled to sensors to receive fuel measurements. A flow regulator is operatively connected to the trigger to activate the trigger in response to the fuel measurements whereby the flow of the fuel into the aircraft is continuously adjustable during refueling. 1. A flow booster for optimizing flow of a fuel passing into an aircraft via a refueling unit , the refueling unit comprising a fuel circuit , the flow booster comprising:a fuel intake fluidly coupled to the fuel circuit, the fuel intake comprising a housing and a piston, the piston comprising a piston head slidably movable in the housing to define a variable fuel inlet to receive the fuel therethrough and into the fuel circuit, wherein the fuel has a fuel force applied to the piston;an intake tuner operatively connected to the fuel intake, the intake tuner having a tuning force applied to the piston against the fuel force;a trigger coupled to the intake tuner to selectively vary the tuning force applied by the intake tuner; anda flow regulator coupled to sensors positioned about the refueling unit to receive fuel measurements therefrom, the flow regulator operatively connected to the trigger to selectively activate the trigger in response to the fuel measurements whereby the flow of the fuel into the aircraft is continuously adjustable during refueling.2. The flow booster of claim 1 , wherein the piston is urged toward a fully ...

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14-03-2019 дата публикации

Fueling Station

Номер: US20190077521A1
Принадлежит: Intelligent Energy Limited

The application relates to a fueling station for a fuel generator having a fuel generator reservoir, the fueling station comprising: a station reservoir () for storing at least one reactant for fuel generation; a fueling interface () configured to engage with the fuel generator reservoir and dispense the at least one reactant to the fuel generator reservoir; and a controller () configured to: receive a parameter indicative of an intended use of the fuel generator; and control the fueling interface to dispense the at least one reactant in accordance with the parameter. 1. A fueling station for a fuel generator having a fuel generator reservoir , the fueling station comprising:a station reservoir for storing at least one reactant for fuel generation;a fueling interface configured to engage with the fuel generator reservoir and dispense the at least one reactant to the fuel generator reservoir; anda controller configured to:receive a parameter indicative of an intended use of the fuel generator;control the fueling interface to dispense a quantity of the at least one reactant in accordance with the parameter; andwherein the fueling interface is configured to receive data from the reactant cartridge.2. The fueling station of in which the station reservoir has a plurality of compartments claim 1 , each compartment comprising a different reactant.3. The fueling station of in which the fueling interface comprises a mixing device configured to mix the different reactants during dispensation of the different reactants to the fuel generator reservoir.4. The fueling station of in which the fuel generator reservoir and the station reservoir each has a plurality of corresponding compartments claim 2 , each compartment comprising a different reactant claim 2 , and in which the fueling interface is configured to dispense the different reactants into the corresponding compartments of the fuel generator reservoir.5. The fueling station of in which the at least one reactant comprises ...

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12-03-2020 дата публикации

AIRCRAFT FUEL TANK INERTING

Номер: US20200079522A1
Автор: JOMAIN Pierre
Принадлежит:

A method of determining whether it is necessary to inert an aircraft fuel tank is disclosed including providing a temperature value indicative of a temperature of the fuel (F) in a fuel tank after refuelling or indicative of the temperature at the aircraft's predicted departure time and location, and based on the temperature value, determining whether or not it is necessary to inert the aircraft fuel tank. A method of controlling the supply of inerting gas to the fuel tank, and an aircraft fuel tank inerting control system are disclosed. 1. A method of determining whether it is necessary to inert a refuelled aircraft fuel tank containing fuel , the method comprising providing a temperature value indicative of a temperature of the fuel after refuelling , and based on said temperature value , determining whether or not it is necessary to inert the aircraft fuel tank.2. A method according to comprising determining whether or not it is necessary to inert the aircraft fuel tank for substantially all of the immediately forthcoming flight.3. A method according to in which the temperature value indicative of a temperature of the fuel after refuelling is a measured temperature value or a predicted temperature value.4. A method according to in which providing said temperature value comprises measuring a temperature of the fuel in the fuel tank during or after the fuelling process claim 1 , or comprises measuring a temperature of the fuel before it is provided to the fuel tank claim 1 , or wherein the measurement occurs before commencing a flight.5. (canceled)6. A method according to in which determining whether or not it is necessary to inert the fuel tank comprises comparing said indicative temperature value with a predetermined temperature value claim 1 , the predetermined value being related to a property of the aircraft fuel claim 1 , or in which the comparison comprises calculating a difference between the predetermined value and the indicative temperature value claim 1 ...

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25-03-2021 дата публикации

METHOD AND SYSTEM FOR HOUSING A DRONE FOR AUTONOMOUS LONG RANGE DRONE OPERATIONS

Номер: US20210086913A1
Принадлежит:

An autonomous drone system is provided. The autonomous drone system may comprise a drone station for automatically connecting a drone to the station for recharging. The automatic connection comprises determining a position of the drone on a platform of the station, rotating the platform based on the determined position, positioning an arm of the station in line with a connection port of the drone, and extending the arm towards the drone for connecting an end of the arm to the connection port of the drone. 1. A remote station for landing and storage of a drone , the station comprising:a housing structure having doors on a top surface to provide an open area sufficient to receive a drone;a platform comprising a landing area for receiving the drone and a mechanism for raising the landing area out of the housing through the open area of the doors and lowering the landing area into the housing through the open area of the doors;an imaging or ranging system within the housing to locate a connection port of the drone on the landing platform; andan extendable arm within the housing having a working end configured to connect to the connection port of the drone.2. The remote station of claim 1 , wherein the platform further comprises a rotating mechanism capable of rotating the landing area with the drone.3. The remote station of claim 2 , wherein the landing area is capable of being rotated to position the connection port of the drone at a location accessible to the working end of the extendable arm based on information from the imaging or ranging system.4. The remote station of claim 1 , further comprising a gantry assembly within the housing.5. The remote station of claim 3 , wherein the extendable arm is mounted on the gantry assembly.6. The remote station of claim 4 , wherein the gantry assembly comprises two stages providing movement is orthogonal directions.7. The remote station of claim 1 , wherein the imaging system comprises a laser range finder capable of scanning ...

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25-03-2021 дата публикации

HYDRANT VALVE WITH INTERNAL SHUT-OFF VALVE

Номер: US20210088150A1
Автор: Wong Tak-Yiu
Принадлежит:

A hydrant valve with an internal automatic shut-off valve. The internal valve blocks communication between a piston chamber and a hydrant chamber when in a closed position. An upper valve opens the internal valve against its biasing force permitting the flow of fluid between the hydrant chamber and the piston chamber. The internal valve closes in response to a disconnection of the upper valve. 1. A hydrant valve comprising:a hydrant chamber having an inlet and an outlet;a piston in the hydrant chamber moveable between open and closed positions relative to the inlet and a chamber disposed within the piston in communication with the inlet and the hydrant chamber;an upper valve movable between open and closed positions relative to the outlet, the upper valve having a biasing member that biases the upper valve toward the closed position, in the closed position the upper valve restricts fluid flow through the outlet and in the open position the upper valve permits fluid flow through the outlet;an internal valve movable between open and closed positions in response to a movement of the upper valve, in the open position the internal valve permits fluid flow between the hydrant chamber and the piston chamber and in the closed position the internal valve restricts fluid flow between the hydrant chamber and the piston chamber.2. The hydrant valve of further comprising:a pilot valve movable between open and closed positions, in the open position the pilot valve allows flow between the inlet and the internal valve and in the closed position the pilot valve allows flow between the inlet and the piston chamber.3. The hydrant valve of claim 1 , wherein the valve further comprises an upper portion.4. The hydrant valve of claim 3 , wherein at least one frangible connector secures the upper portion.5. The hydrant valve of claim 1 , wherein the internal valve moves towards the closed position in response to the upper valve moving towards the closed position.6. The hydrant valve of ...

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21-03-2019 дата публикации

Rapid store load system for aircraft and method of operation thereof

Номер: US20190084680A1
Автор: Victor A. Grossman
Принадлежит: Individual

A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft.

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04-04-2019 дата публикации

UNMANNED AERIAL VEHICLE (UAV) RECHARGING/REFUELLING STATION

Номер: US20190100331A1
Автор: Wright Colin
Принадлежит:

A recharging/refuelling station for an unmanned aerial vehicle (UAV) and a network of the same are provided. Optionally the recharging/refuelling stations are network with a central control. Individual recharging/refuelling stations include a landing platform that includes a UAV capture system and a recharging or refuelling system. The recharging/refuelling stations may be equipped with a variety of sensors or modules to facilitate UAV landing and recharging/refuelling. 1. A recharging/refuelling station for an unmanned aerial vehicle (UAV) comprising a landing platform comprising a UAV capture system and a recharging or refuelling system.2. The station according to claim 1 , wherein the landing platform is elevated.3. The station according to claim 2 , wherein the landing platform is mounted on a pole or frame extending vertically from the ground.4. The station according to claim 3 , wherein the landing platform is rotatable or pivotably mounted on the pole or frame.5. The station according to claim 4 , wherein the landing platform comprises a weather vane and wherein the platform is optionally configured to pivot into the wind.6. The station according to claim 1 , wherein the UAV capture system comprises a tether guide and tether arresting gear.7. The station according to claim 6 , wherein the tether guide is a slot in the landing platform.8. The station according to claim 1 , comprising one or more station sensors or monitors.9. The station according to claim 8 , wherein the one or more stations sensors or monitors include power level sensors claim 8 , tamper alarms claim 8 , battery charge sensors claim 8 , recharge voltage and current draw sensor claim 8 , liquid fuel sensors claim 8 , fuel pump sensors claim 8 , fuel pressure and flow sensors claim 8 , arresting gear monitors claim 8 , wind speed and direction sensors claim 8 , one or more cameras claim 8 , GPS transponder claim 8 , LIDAR approach guidance claim 8 , radar situational awareness claim 8 , ...

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02-06-2022 дата публикации

HELIPORT DOCKING SYSTEM

Номер: US20220169399A1
Принадлежит: Textron Innovations Inc.

A heliport docking system provides automated transport, fueling, maintenance, and logistical management of VTOLs. The heliport docking system can include a plurality of helipads that can be autonomously transported from area-to-area to assist in the logistics of heliport management and control. The helipad system can include a surface on which a VTOL can land and a controller that can perform functions related to routing, maintenance, object detection, and transport, among others. The helipad system can releasably secure the VTOL to the helipad and transport the VTOL to different areas of the heliport system. The helipad system can also fuel the VTOL by providing, electricity, combustible fuel, or other suitable energy source, and perform a maintenance check of the VTOL and create maintenance crew of any VTOL irregularities. 1. A helipad configured to transport an aircraft , comprising:an aircraft landing surface configured to receive an aircraft;a plurality of connectors configured to selectively secure the aircraft to the helipad;an aircraft fueling mechanism configured to provide the aircraft with an energy source;an aircraft maintenance device configured to receive maintenance data from the aircraft; anda transport mechanism configured to transport the aircraft from a landing area to a destination area.2. The helipad of claim 1 , wherein the transport mechanism includes a plurality of rail wheels configured to move along a railway track along the surface.3. The helipad of claim 1 , wherein the transport mechanism includes a plurality of wheels.4. The helipad of claim 1 , wherein the aircraft fueling mechanism is configured to supply the aircraft with fuel to power a combustion engine of the aircraft.5. The helipad of claim 1 , wherein the aircraft fueling mechanism is configured to supply the aircraft with electricity to power an electric engine of the aircraft.6. The helipad of claim 5 , wherein the electricity is supplied by a static electrical connection.7. ...

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04-04-2019 дата публикации

Nanoparticle dispersing system

Номер: US20190101056A1
Принадлежит: United Technologies Corp

A system for dispersing a catalyst in a fuel includes a first reservoir containing the fuel, and a second reservoir including an agitator and containing a quantity of the catalyst suspended in the fuel. The system also includes a first conduit extending from the first reservoir, a second conduit extending from the second reservoir, and a mixing nozzle connected to the first conduit and the second conduit. The mixing nozzle includes a first meter positioned within the first conduit, a second meter positioned within the second conduit, a valve positioned upstream from the second meter within the second conduit, a junction in flow communication with the first conduit and the second conduit, a mixer downstream from the junction, a sensor positioned between the mixer and an outlet; and a controller connected to the valve and the first and second meters, the controller receiving feedback from the sensor.

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24-07-2014 дата публикации

METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT

Номер: US20140203140A1
Принадлежит: AEROVEL CORPORATION

Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus. 1. A flying object capturing apparatus , said flying object capturing apparatus comprising:(a) a base;(b) a docking station supported by the base and configured to receive a portion of a flying object;(c) a member holder supported by the base and configured to receive a member of the flying object; and(d) two arms supported by and extending from the base and defining an opening therebetween configured to admit the member of the flying aircraft into the member holder.2. The flying object capturing apparatus of claim 1 , which includes a member mover configured to after the member holder receives the member of the flying object claim 1 , move the member relative to the docking station until the docking station receives the portion of the flying object.3. The flying object capturing apparatus of claim 2 , which includes a sensor configured to detect when the docking station receives the portion of the flying object claim 2 , and wherein the member mover is configured to stop moving the member relative to the docking station when the ...

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25-08-2022 дата публикации

AUTONOMOUS SEABASED RESUPPLY SYSTEM

Номер: US20220266962A1
Принадлежит: Textron Innovations Inc.

A seabased resupply system includes a fuel containment structure containing fuel and extending fore and aft along a longitudinal axis, a pump on the fuel containment structure operable to pump the fuel, containers located on an exterior of opposite lateral sides of the fuel containment structure, and an operating system located inside one or more of the containers, the operating system comprising at least one selected from a power supply, a communication system, and a control processor. 1. A seabased resupply system , the seabased resupply system comprising:a fuel containment structure containing fuel and extending fore and aft along a longitudinal axis;a pump on the fuel containment structure operable to pump the fuel;containers located on an exterior of opposite lateral sides of the fuel containment structure; andan operating system located inside one or more of the containers, the operating system comprising at least one selected from a power supply, a communication system, and a control processor.2. The seabased resupply system of claim 1 , wherein the containers extend parallel to the longitudinal axis.3. The seabased resupply system of claim 2 , wherein the containers extend approximately a length of the fuel containment structure.4. The seabased resupply system of claim 1 , wherein the operating system is a power supply.5. The seabased resupply system of claim 4 , wherein the containers extend approximately a length of the fuel containment structure.6. The seabased resupply system of claim 1 , further comprising a landing pad for an aircraft located on a top surface of the fuel containment structure.7. The seabased resupply system of claim 6 , wherein the containers extend approximately a length of the fuel containment structure.8. The seabased resupply system of claim 7 , wherein the operating system is a power supply.9. The seabased resupply system of claim 6 , further comprising a keel on a bottom surface of the fuel containment structure.10. The seabased ...

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10-05-2018 дата публикации

FLUID SYSTEM

Номер: US20180127109A1
Принадлежит:

A fluid system includes a controller, a control valve, and a fluid manifold. A first solenoid may be connected to the fluid manifold, the control valve, and/or the controller. A second solenoid may be connected to the fluid manifold, the control valve, and/or the controller. A first pressure sensor may be in fluid communication with an output of the control valve. A second pressure sensor may be in fluid communication with the fluid manifold. The controller may be configured to control operation of the control valve via the first solenoid and the second solenoid according to a first fluid pressure obtained via the first pressure sensor and according to a second fluid pressure obtained via the second pressure sensor. 1. A fluid system , comprising:a controller;a control valve;a fluid manifold;a first solenoid connected to the fluid manifold, the control valve, and the controller;a second solenoid connected to the fluid manifold, the control valve, and the controller;a first pressure sensor in fluid communication with an output of the control valve; anda second pressure sensor in fluid communication with the fluid manifold;wherein the controller is configured to control operation of the control valve via the first solenoid and the second solenoid according to a first fluid pressure obtained via the first pressure sensor and according to a second fluid pressure obtained via the second pressure sensor.2. The fluid system of claim 1 , wherein the control valve includes a piston claim 1 , the controller is configured to determine a position of the piston claim 1 , and the controller is configured to control operation of the control valve according to the position of the piston.3. The fluid system of claim 2 , wherein the controller is configured to determine the position of the piston according to a spring constant claim 2 , a spring length of a spring of the control valve claim 2 , and the second fluid pressure.4. The fluid system of claim 1 , including a calibration ...

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09-05-2019 дата публикации

FUELLING ARRANGEMENT AND METHOD

Номер: US20190135452A1
Принадлежит:

A method of fuelling an aircraft for a flight to a predetermined destination in which the aircraft is loaded, the actual zero fuel weight of the loaded aircraft is determined, the fuel requirement of the loaded aircraft for that destination is calculated by fuel calculation software on the basis of operational flight plan data, said actual zero fuel weight, and further data relevant to fuel consumption for that instance of the flight to the predetermined destination, said further data being processed interactively by the user by means of a user interface to said fuel calculation software, and subsequently fuel to meet said fuel requirement is uplifted to the aircraft under the control of said user. 1. A method of fuelling an aircraft for a flight to a predetermined destination wherein the aircraft is loaded, the actual zero fuel weight of the loaded aircraft is determined, the fuel requirement of the loaded aircraft for that destination is calculated by fuel calculation software on the basis of operational flight plan data, said actual zero fuel weight, and further data relevant to fuel consumption for that instance of the flight to the predetermined destination, said further data being processed interactively by the user by means of a user interface to said fuel calculation software, and subsequently fuel to meet said fuel requirement is uplifted to the aircraft under the control of said user. The present invention relates to a fuelling arrangement and method, particularly but not exclusively for fuelling an aircraft, such as a passenger or cargo-carrying commercial airliner or a military aircraft for example.Airline operators face severe challenges in operating profitably. Airlines also face increasing pressure to reduce carbon emissions and the associated footprint. A key factor in this is reducing fuel consumption to the lowest level possible, consistent with safety.Preparations are in place for emissions trading in Europe (and in other parts of the world). ...

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09-05-2019 дата публикации

HYDRANT VALVE WITH INTERNAL SHUT-OFF VALVE

Номер: US20190136993A1
Автор: Wong Tak-Yiu
Принадлежит:

A hydrant valve with an internal automatic shut-off valve. The internal valve blocks communication between a piston chamber and a hydrant chamber when in a closed position. An upper valve opens the internal valve against its biasing force permitting the flow of fluid between the hydrant chamber and the piston chamber. The internal valve closes in response to a disconnection of the upper valve. 1. A hydrant valve comprising:a hydrant chamber having an inlet and an outlet;a piston in the hydrant chamber moveable between open and closed positions relative to the inlet and a chamber disposed within the piston in communication with the inlet and the hydrant chamber;an upper valve movable between open and closed positions relative to the outlet, the upper valve having a biasing member that biases the upper valve toward the closed position, in the closed position the upper valve restricts fluid flow through the outlet and in the open position the upper valve permits fluid flow through the outlet;an internal valve movable between open and closed positions in response to a movement of the upper valve, in the open position the internal valve permits fluid flow between the hydrant chamber and the piston chamber and in the closed position the internal valve restricts fluid flow between the hydrant chamber and the piston chamber.2. The hydrant valve of further comprising:a pilot valve movable between open and closed positions, in the open position the pilot valve allows flow between the inlet and the internal valve and in the closed position the pilot valve allows flow between the inlet and the piston chamber.3. The hydrant valve of claim 1 , wherein the valve further comprises an upper portion.4. The hydrant valve of claim 3 , wherein at least one frangible connector secures the upper portion.5. The hydrant valve of claim 1 , wherein the internal valve moves towards the closed position in response to the upper valve moving towards the closed position.6. The hydrant valve of ...

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24-05-2018 дата публикации

Device for Servicing an Aircraft on the Ground

Номер: US20180141778A1
Автор: Dreyer Thomas
Принадлежит:

A device for servicing an aircraft on the ground includes: a steerable carriage; a first reel mounted along a first lateral side of the steerable carriage for unwinding a first hose or a cable onto a ground surface, wherein the first hose or a cable has a drop off point near this first lateral side; and a second reel mounted along a second lateral side of the steerable carriage for unwinding a second hose or a cable onto the ground surface, wherein the second hose or a cable has a drop off point near this second lateral side. A control system controls the unwinding speed of the cable or hose from of each of the reels in such a way that in a curve, the control system makes the outer reel unwind faster than the inner reel. 1. A device for servicing an aircraft on the ground comprising:a steerable carriage having a first lateral side and an opposite second lateral side;a first reel mounted along the first lateral side of the steerable carriage configured to unwind a first hose or a cable onto a ground surface, wherein the first hose or a cable has a drop off point near the first lateral side of the steerable carriage;a second reel mounted along the second lateral side of the steerable carriage configured to unwind a second hose or a cable onto the ground surface, wherein the second hose or a cable has a drop off point near the second lateral side of the steerable carriage; anda control system configured to control the unwinding speed of the cable or hose from of each of the reels in such a way that in a curve, the control system makes the outer reel unwind faster than the inner reel.2. The device according to claim 1 , wherein:the control system is configured to determine the speed relative to the ground surface of the drop off point of the first hose or cable and the speed relative to the ground surface of the drop off point of the second hose or cable and to control the unwinding speed of the first hose or cable and the second hose or cable in such a way that the ...

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16-06-2016 дата публикации

PUMP SYSTEMS FOR CONTROLLING PRESSURE LOADS

Номер: US20160167806A1
Принадлежит:

A pump system for controlling a pressure load delivered to an aircraft interface included in the pump system is disclosed. The pump system includes a pump circuit, a pump, and a valve system. The pump is coupled with the conduits and is configured to provide a pressure load to the aircraft interface to move fuel from a fuel reservoir through the conduits toward the aircraft interface in a fueling mode and to move fuel from the aircraft interface through the conduits toward the fuel reservoir in a defueling mode. The valve system is coupled to the conduits and configured to control the pressure load delivered to the aircraft interface to block the pressure load from exceeding either of a high-pressure threshold and a delta-pressure threshold. 1. A fuel cart for fueling and defueling an aircraft , the fuel cart comprising:a mobile fuel reservoir configured to store and transport fuel,a single pump configured to move between a fueling mode in which the pump is configured to move fuel from the fuel reservoir to an aircraft and a defueling mode in which the pump is configured to move fuel from the aircraft to the fuel reservoir,a pump circuit including (i) a first three-way valve coupled to a first port of the pump and coupled to the fuel reservoir by a fuel withdraw conduit, (ii) a second three-way valve coupled to the first three-way valve by an intermediate conduit, coupled to a second port of the pump, and coupled to the fuel reservoir by a fuel return conduit, and (iii) an aircraft interface fluidly coupled to the intermediate conduit between the first three-way valve and the second three-way valve to conduct fuel from the fuel reservoir into the aircraft when the pump is in the fueling mode and to conduct fuel from the aircraft toward the fuel reservoir when the pump is in the defueling mode, anda valve system fluidly coupled to the intermediate conduit by a bypass conduit and fluidly coupled to the fuel withdraw conduit by a relief conduit and the valve system ...

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01-07-2021 дата публикации

BASE STATION AND VEHICLE THEREOF

Номер: US20210197983A1
Автор: Wang Hao, WANG Peng, Zhang Song
Принадлежит:

The present disclosure provides a base station in wireless communication with a UAV. The base station includes an operating platform; a landing platform, the landing platform and the operating platform being independent of each other and the landing platform being adjacent to the operating platform; a transfer mechanism at least partially disposed on the landing platform to send the UAV landed on the landing platform into the operating platform and/or transfer the UAV stored in the operating platform onto the landing platform; and a controller configured to trigger the base station to perform a UAV recovery operation or a UAV releasing operation when a state of the UAV meets a specific strategy or when a dispatch instruction is received; and control the operating platform to perform one or more operations of: UAV power source update, UAV part replacement, UAV payload supplementation, UAV data exchange, and UAV storage. 1. A base station in wireless communication with a UAV , comprising:an operating platform;a landing platform, the landing platform and the operating platform being independent of each other and the landing platform being adjacent to the operating platform;a transfer mechanism at least partially disposed on the landing platform to send the UAV landed on the landing platform into the operating platform and/or transfer the UAV stored in the operating platform onto the landing platform; anda controller configured to trigger the base station to perform a UAV recovery operation or a UAV releasing operation when a state of the UAV meets a specific strategy or when a dispatch instruction is received; and control the operating platform to perform one or more operations of: UAV power source update, UAV part replacement, UAV payload supplementation, UAV data exchange, and UAV storage.2. The base station of claim 1 , further comprising:a guiding mechanism disposed on the landing platform and movably arranged relative to the transfer mechanism; anda first power ...

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28-05-2020 дата публикации

Rapid store load system for aircraft and method of operation thereof

Номер: US20200164985A1
Автор: Victor A. Grossman
Принадлежит: Individual

secure the one or more stores to the aircraft.

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05-07-2018 дата публикации

FUELING NOZZLE ADAPTOR

Номер: US20180186465A1
Автор: Gammon James H.
Принадлежит:

A nozzle adapter for coupling a fueling nozzle to an underwing type servicing adapter having a radially outward extending tab and a notch formed in an open end thereof comprises an outer body including a neck portion having a first conduit formed therein and a substantially cylindrical cap portion, the cap portion including at least one slot formed therein. An inner body has a second conduit formed therein and is disposed within the cap portion of the outer body and an annular channel is formed between the cap portion and the inner body. The at least one tab is received in the at least one slot and a rotation of the nozzle adapter relative to the servicing adapter causes a first aperture configured to receive a locking device therein to be aligned with the at least one notch of the servicing adapter. 1. A method of coupling a nozzle adapter to an underwing type servicing adapter , the method comprising the steps of:providing the underwing servicing adapter having at least one radially outward extending tab formed in an open end thereof;providing the nozzle adapter having a channel and at least one slot formed therein;inserting the open end of the underwing servicing adapter into the channel and the at least one tab into the at least one slot; androtating the nozzle adapter relative to the underwing servicing adapter to form a fluid tight connection therebetween.2. The method of claim 1 , wherein the inserting step causes the at least one tab to traverse a first leg of the at least one slot in an axial direction and the rotating step causes the at least one tab to traverse a second leg of the at least one slot arranged transverse to the first leg.3. The method of claim 1 , wherein the underwing servicing adapter further includes at least one notch formed in the open end thereof and the nozzle adapter further includes a first aperture formed therein claim 1 , wherein after the inserting step and the rotating step a locking device is disposed in the first aperture and ...

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20-06-2019 дата публикации

Aircraft refueling safety system

Номер: US20190185177A1
Принадлежит: Flightlogix LLC

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.

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11-06-2020 дата публикации

AUTONOMOUS HYDROGEN REFUELING

Номер: US20200180782A1
Автор: Rainville Joseph Dean
Принадлежит: Bell Helicopter Textron Inc.

A system and a method for autonomous hydrogen refueling of vertical lift aircraft using a landing pad with sensors, a hydrogen storage tank, a refueling arm configured to couple the hydrogen storage tank to the aircraft and a controller configured to control a flow of fuel from the hydrogen storage tank to the aircraft. 1. A system for autonomous hydrogen refueling of an aircraft , comprising:a landing pad;a hydrogen storage tank;a refueling arm configured to couple the hydrogen storage tank to the aircraft; anda controller configured to control a flow of fuel from the hydrogen storage tank to the aircraft.2. The system of claim 1 , further comprising:a compressor located between the hydrogen storage tank and the controller;wherein the compressor is configured to increase a pressure of the fuel from the hydrogen storage tank.3. The system of claim 1 , further comprising:an actuator located between the landing pad and the refueling arm;wherein the refueling arm translates vertically in response to the controller.4. The system of claim 1 , further comprising:at least one sensor located on the landing pad;wherein the at least one sensor is configured to detect a proximity of the aircraft relative to the landing pad.5. The system of claim 1 , further comprising:a wireless system coupled to the controller;wherein the wireless system is configured to relay fueling data between the controller and the aircraft.6. The system of claim 1 , further comprising:a recessed receptacle located on an underside surface of the aircraft.7. The system of claim 6 , wherein the recessed receptacle clamps onto the refueling arm.8. The system of claim 6 , wherein the refueling arm clamps onto the recessed receptacle.9. A method for autonomous refueling of an aircraft comprising:providing a refueling arm having a nozzle;landing the aircraft on the nozzle;coupling the nozzle to the aircraft;flowing fuel to the aircraft through the refueling arm; anddecoupling the nozzle from the aircraft.10. ...

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11-06-2020 дата публикации

MOBILE AUTONOMOUS HYDROGEN REFUELING STATION

Номер: US20200180940A1
Автор: Rainville Joseph Dean
Принадлежит: Bell Helicopter Textron Inc.

A system and a method for mobilized autonomous hydrogen refueling of vertical lift aircraft using a framed landing pad with sensors, an onboard hydrogen storage tank, an onboard refueling arm configured to couple the hydrogen storage tank to the aircraft and an onboard controller configured to control a flow of fuel from the hydrogen storage tank to the aircraft. 1. A system for autonomous hydrogen refueling of an aircraft , comprising:a frame;a power source carried by the frame;a hydrogen storage tank carried by the frame;a refueling arm configured to couple the hydrogen storage tank to the aircraft; anda controller carried by the frame, the controller configured to control a flow of fuel from the hydrogen storage tank to the aircraft.2. The system of claim 1 , further comprising:a compressor carried by the frame;wherein the compressor is configured to increase a pressure of fuel from the hydrogen storage tank.3. The system of claim 1 , further comprising:an upper plate carried by the frame;an actuator located between the upper plate and the refueling arm;wherein the refueling arm translates vertically in response to the controller.4. The system of claim 1 , further comprising:at least one sensor located on the upper plate;wherein the at least one sensor is configured to detect a proximity of the aircraft relative to the upper plate.5. The system of claim 1 , further comprising:a wireless system coupled to the controller;wherein the wireless system is configured to relay fueling data between the controller and the aircraft.6. The system of claim 1 , further comprising:a recessed receptacle carried by an underside surface of the aircraft.7. The system of claim 6 , wherein the recessed receptacle clamps onto the refueling arm.8. The system of claim 6 , wherein the refueling arm clamps onto the recessed receptacle.9. The system of claim 3 , further comprising:a plurality of attachment members carried by the upper plate.10. The system of claim 1 , wherein the frame is ...

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18-06-2020 дата публикации

HELIPORT DOCKING SYSTEM

Номер: US20200189767A1
Принадлежит: Textron Innovations Inc.

A heliport docking system provides automated transport, fueling, maintenance, and logistical management of VTOLs. The heliport docking system can include a plurality of helipads that can be autonomously transported from area-to-area to assist in the logistics of heliport management and control. The helipad system can include a surface on which a VTOL can land and a controller that can perform functions related to routing, maintenance, object detection, and transport, among others. The helipad system can releasably secure the VTOL to the helipad and transport the VTOL to different areas of the heliport system. The helipad system can also fuel the VTOL by providing, electricity, combustible fuel, or other suitable energy source, and perform a maintenance check of the VTOL and create maintenance crew of any VTOL irregularities. 1. A heliport docking system , comprising: a VTOL fueling mechanism configured to provide a VTOL with an energy source, and', 'a VTOL maintenance device configured to obtain maintenance data from the VTOL;, 'a helipad, including a helipad routing module adapted to determine a destination of the helipad and a route to the destination,', 'a VTOL maintenance module adapted to receive the maintenance data from the VTOL maintenance device and generate an alert based upon the maintenance data, and', 'a VTOL fueling module configured to control the amount of fuel delivered to the VTOL aircraft by the fueling mechanism; and, 'a helipad controller operably coupled to the helipad, includinga transport mechanism operably coupled to the helipad and the helipad controller and configured to transport the VTOL to the destination along the route.2. The heliport docking system of claim 1 , the helipad further including:a VTOL sensor configured to detect the presence of the VTOL proximate the helipad,a VTOL securing device configured to secure the VTOL to the helipad, andan obstacle sensor configured to detect objects proximate the helipad.3. The heliport docking ...

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04-08-2016 дата публикации

Automated water and particle detection for dispensing fuel including aviation fuel, and related apparatuses, systems, and methods

Номер: US20160221817A1
Принадлежит: Individual

A fuel dispensing apparatus and method for delivering fuel from a fuel source, including, without limitation, delivering aircraft fuel from a fuel tank to an aircraft is disclosed. The fuel dispensing apparatus also includes an electronic control system in communication with a particle detector and configured to receive fuel quality sensor information corresponding to at least one detected fuel quality characteristic in real time. The electronic control system is configured to determine, based on the received fuel quality sensor information, a particle ratio defined as an approximate ratio of a measurement of total water and particulate per unit volume of fuel, and a first water characteristic indicative of a presence or absence of a threshold amount of water per unit volume of fuel. Based on the first water characteristic and on the particle ratio, the electronic control system is configured to determine whether to initiate at least one corrective action.

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19-08-2021 дата публикации

RAPID STORE LOAD SYSTEM FOR AIRCRAFT AND METHOD OF OPERATION THEREOF

Номер: US20210253252A1
Автор: Grossman Victor A.
Принадлежит:

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft. 120.-. (canceled)21. An aircraft store loading system , comprising:at least one actuator;one or more lift portions;at least one sensor configured to form sensor information; and control a position of an aircraft;', 'load one or more stores onto the one or more corresponding lift portions;', 'position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from the at least one sensor; and', 'secure the one or more stores to the aircraft., 'control at least one actuator to, 'a controller configured to22. The system of claim 21 , wherein the one or more stores are secured to at least one hardpoint (HP) of the aircraft.23. The system of claim 21 , wherein the controller further enables an automatic store attachment mode to automatically control the at least one actuator to secure the one or more stores to the aircraft.24. The system of claim 21 , wherein the controller is further configured to obtain requested store information (RSI) from a memory of the system claim 21 , the RSI including information related to the one or more stores.25. The system of claim 24 , wherein the controller is further configured to control the at least one actuator to automatically retrieve the one or more stores.26. The system of claim 21 , wherein the controller is further configured to control the at least one actuator to retract the corresponding lift portions of the one or more lift portions after the one or more stores are secured.27. ...

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30-10-2014 дата публикации

Device for a Helicopter Deck

Номер: US20140319273A1
Автор: Rod Karl Johan
Принадлежит: MARINE ALUMINIUM AS

A device is for a helicopter deck comprising a supporting, fluid-tight floor. The helicopter deck comprises an overlying, draining top cover formed out of at least two top-cover sections arranged side by side. Each of the top-cover sections comprise a surface portion provided with several drain openings and at least one channel wall projecting downwards, provided with a foot portion which is arranged to be positioned on the surface of the floor. At least one drain channel is defined by the top cover, the floor and two adjacent channel walls. The drain channel is provided with a mouth portion which is connected to a collecting channel. Fluid-transport paths are formed through the at least one drain channel between the drain openings and a drain in the collecting channel. The top-cover sections are detachable from the floor and adjacent top-cover sections. 1. A device for a helicopter deck comprising a supporting , fluid-tight floor and an overlying , draining top cover formed out of at least two top-cover sections arranged side by side , each of the top-cover sections comprising a surface portion provided with several drain openings and at least one channel wall projecting downwards , provided with a foot portion which is arranged to be positioned on the surface of the floor , wherein the helicopter deck further comprises:at least one drain channel defined by the top cover, the floor and two adjacent channel walls, the drain channel being provided with a mouth portion which is connected to a collecting channel;fluid-transport paths being formed through the at least one drain channel between the drain openings and a drain in the collecting channel; andthe top-cover sections being detachable from the floor and adjacent top-cover sections.2. The device in accordance with claim 1 , wherein claim 1 , except for the drain openings claim 1 , the fluid-transport paths are airtight towards the ambient atmosphere.3. The device in accordance with claim 1 , wherein claim 1 , in ...

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16-08-2018 дата публикации

Intelligent aircraft ground support unit

Номер: US20180229860A1
Принадлежит: Guinault Sa

An aircraft ground support unit ( 1 ) for supplying a service to an aircraft ( 3 ) on the ground according to a specific servicing program is provided that includes reception means ( 5 ) suitable for identifying an aircraft ( 3 ) in motion or parked on the ground by receiving information emitted by a transponder ( 7 ) of said aircraft including an instantaneous GPS coordinates of the position of the aircraft, the identity of the aircraft, the type of aircraft, and the company of the aircraft, aircraft status data. A microprocessor is provided that is suitable for selecting and implementing a predefined servicing program stored in a database corresponding to the type and company of the thus identified aircraft ( 3 ) on the basis of the information received by the reception means. A data record device is also provided that is to store the events, aircraft status data, ground unit data for airlines operation optimization.

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22-08-2019 дата публикации

System and Process

Номер: US20190256219A1
Автор: Dubenski Paul Jerzy
Принадлежит:

A refuelling system suitable for use with an overwing fuelled aircraft comprising: (b) a stored fuel grade identification means for identifying the fuel grade stored in the fuel storage vessel and available type(s) of delivery of the fuel to the aircraft; (d) an aircraft fuel grade identification means being attached to, or forming part of, an overwing fuelled aircraft, wherein said aircraft fuel grade identification means represents the fuel grade requirement of the aircraft and is readable from the exterior of the aircraft; (g) a transmission and receiving system which enables information regarding the fuel grade that had previously been supplied to the aircraft having the aircraft registration number inputted into the computer interface and the type of delivery of fuel which may be used by said aircraft to be retrieved from a remote database; (i) an automated cross-check system which is configured to retrieve the fuel grades identified by the fuel identification means in (b), retrieve the fuel grade identified in (d) from the hand-held device, retrieve the type(s) of delivery of fuel identified by the fuel identification means in (b) and by the system of element (g), and the previous fuel grade supplied to the aircraft identified by the system in element (g) which can generate a positive response signal if all of the fuel grades identified are compatible with each other and the type(s) of delivery of fuel to the aircraft are compatible 1. A refuelling system suitable for use with an overwing fuelled aircraft comprising:(a) a fuel storage vessel capable of storing aircraft fuel;(b) a stored fuel grade identification means for identifying the fuel grade stored in the fuel storage vessel and available type(s) of delivery of the fuel to the aircraft;(c) a fuel dispensing system fluidly connected to the fuel storage vessel comprising a means of delivering fuel to an overwing fuelled aircraft and a mechanism that permits or prevents the dispensing of the stored ...

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20-09-2018 дата публикации

HIGH WING COMPENSATION SYSTEM

Номер: US20180265221A1
Принадлежит:

The present disclosure includes a fluid system that may include a fluid conduit () that may be configured for connection with a fluid source () and a fluid destination (). The system may include a fluid regulator () that may be configured to regulate fluid flow between said fluid source () and said fluid destination (). The system may include a nozzle () that may be connected to the fluid conduit and may configured to connect the fluid conduit with said fluid destination. The system may include a first sensor () that may be connected to the fluid conduit, and a second sensor () that may be configured to acquire information from which a height of the nozzle can be determined. The system may include a controller () that may be configured to control operation of the fluid regulator according to (i) an output of the first sensor and (ii) the information acquired by the second sensor. 1. A fluid system comprising:a fluid conduit configured for connection with a fluid source and a fluid destination;a fluid regulator connected to the fluid conduit and configured to regulate fluid flow between said fluid source and said fluid destination;a nozzle connected to the fluid conduit and configured to connect the fluid conduit with said fluid destination;a first sensor connected to the fluid conduit;a second sensor, the second sensor configured to acquire information from which a height of the nozzle can be determined; anda controller configured to control operation of the fluid regulator according to (i) an output of the first sensor and (ii) the information acquired by the second sensor.2. The fluid system of claim 1 , wherein said fluid destination includes an aircraft fuel tank.3. The fluid system of claim 1 , wherein the first sensor includes a fluid pressure sensor claim 1 , and the output of the first sensor corresponds to a pressure of fluid in the fluid conduit downstream of the fluid regulator.4. The fluid system of claim 1 , wherein the controller is configured to ...

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12-10-2017 дата публикации

Composite Tubes for a Fluid Transport System

Номер: US20170291717A1
Принадлежит: Boeing Co

A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. In one illustrative embodiment, an apparatus comprises a transport member. The transport member is configured for use in the fluid transport system. The transport member is comprised of a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member.

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11-10-2018 дата публикации

SKY TREE AND SKY FOREST FOR UNMANNED AERIAL VEHICLES

Номер: US20180290763A1
Автор: Huang Shihwa
Принадлежит:

A sky tree for unmanned aerial vehicles includes a trunk, a flight platform, an elevator, a parking room, a command center, and a supply station. The sky tree is arranged in a geographic region to provide the unmanned aerial vehicles in the region for certain application field with logistics support integrating command dispatching, application monitoring, communication relay, and replenishment. A sky forest for unmanned aerial vehicles includes a plurality of sky trees for unmanned aerial vehicles arranged in a geographic region, and a control center. The sky forest becomes part of the public property in the geographic region, provides logistics support for all unmanned aerial vehicles in the region, and controls flights of the unmanned aerial vehicles in an orderly manner. 1. A sky tree for unmanned aerial vehicles , comprising:a trunk extending from a lower portion to a high altitude, an inner portion of the trunk having a hollow structure;a flight platform located at a top end of the trunk for take-off and landing of the unmanned aerial vehicles;an elevator provided inside the trunk for carrying the unmanned aerial vehicles up or down between the lower portion and the flight platform;parking rooms for parking of the unmanned aerial vehicles; anda command center to control flights of the unmanned aerial vehicles using radio communication.2. The sky tree for unmanned aerial vehicles according to claim 1 , further comprising a supply station to recharge or refuel the unmanned aerial vehicles.3. The sky tree for unmanned aerial vehicles according to claim 1 , wherein the command center uses 2G claim 1 , 3G or 4G mobile communication claim 1 , global positioning system (GPS) communication claim 1 , or specific channel radio communication.4. The sky tree for unmanned aerial vehicles according to claim 1 , wherein the sky tree for unmanned aerial vehicles is in an overall shape of a tower claim 1 , and the parking rooms are provided on the trunk to form a multi-layer ...

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08-11-2018 дата публикации

FLUID COUPLER

Номер: US20180319514A1
Принадлежит:

A fluid coupler includes a housing with an inlet port and an outlet port, a piston disposed in the housing and configured to control fluid flow between the inlet port and the outlet port, and a piston retainer disposed in the housing. A piston may include at least one radially-extending support member, and the radially-extending support member may include an aperture. The at least one radially-extending support member may be substantially planar. 1. A fluid coupler , comprising:a housing including an inlet port and an outlet port;a piston disposed in the housing and configured to control fluid flow between the inlet port and the outlet port; anda piston retainer disposed in the housing;wherein the piston includes at least one radially-extending support member, and a radially-extending support member of the at least one radially-extending support member includes an aperture.2. The fluid coupler of claim 1 , wherein the at least one radially-extending support member is substantially planar.3. The fluid coupler of claim 1 , wherein the at least one radially-extending support member is substantially parallel to a plane defined by an axial direction and a radial direction relative to a central axis of the piston.4. The fluid coupler of claim 1 , wherein the at least one radially-extending support member includes four radially-extending support members.5. The fluid coupler of claim 1 , wherein the aperture includes a first portion and a second portion claim 1 , and the first portion includes a greater axial extent than the first portion.6. The fluid coupler of claim 1 , wherein the aperture includes a radial extent that is at least half as a radial extent of the radially-extending support member.7. The fluid coupler of claim 1 , wherein the piston is keyed with a connecting member; and the connecting member is disposed at partially in an inner portion of the piston and at least partially in a collar of the piston retainer.8. The fluid coupler of claim 1 , wherein the ...

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23-11-2017 дата публикации

AIRCRAFT REFUELING SAFETY SYSTEM

Номер: US20170334572A1
Принадлежит:

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. 1. An aircraft refueling safety module , the module comprising:a memory, and [ data identifying the aircraft, and', 'a type of fuel required by the aircraft;, 'compare data wirelessly received from a first data source comprising at least one aircraft data source, the aircraft data source data comprising at least one of, data identifying the aircraft, and', 'the type of fuel required by the aircraft;, 'to data received from a second data source comprising at least one data source not located at the aircraft, the second data source data comprising at least one of, 'determine, based on the comparison, if the aircraft data source data matches the second data source data; and', 'if the aircraft data source data matches the second data source data, allow fuel to be dispensed to the aircraft, or', 'if the aircraft data source data does not match the second data source data, prevent fuel from being dispensed to the aircraft., 'one or more processors in communication with the memory, the one or more processors configured to2. The module of where the one or more processors is further configured to: data identifying the aircraft, and', 'the type of fuel required ...

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23-11-2017 дата публикации

Aerial Vehicle Refueling System incorporating a Universal Refueling Interface

Номер: US20170334581A1
Принадлежит:

A system for autonomously replacing batteries or fuel cells on small aerial vehicles such as Unmanned Aerial Vehicles (UAVs) or radio-controlled aircraft (RC) is described. At the core of this system is a “universal battery receptacle” that can be added to a variety of unmanned aircraft platforms and provides a uniform interface for battery or fuel cell replacement in the form of a commensurately designed “universal fuel cell”. 1. A method of standardizing the battery receptacle over a range of aerial vehicle designs such that a single refueling platform can be used to service a range of vehicles and applications;where it is understood that “battery” in this sense could represent a variety of aerial vehicle energy storage methods (DC chemical cell, hydrogen fuel cell, combustible gas, etc.) in a standardized package.2. A method for standardizing aerial vehicle energy storage devices such that autonomous or largely automated refueling of a variety of vehicles is enabled.3. A method of establishing an automated or autonomous landing pad system that accepts , refuels , and re-launches small aerial vehicles that are equipped with a universal battery receptacle or receptacles.4. A method of wherein a standardized fuel cell housing is used for automated extraction and replacement of universal fuel cells.5. A method of wherein any one of many fuel cell designs claim 1 , technologies (battery chemistry or liquid fuel) claim 1 , or specifications (such as weight and cost) are standardized for automated refueling of aerial vehicles.6. A method for wherein the universal battery receptacle provides both energy storage access and mechanical interfacing to a handling system for small aerial vehicles.7. A method of wherein data associated with the aerial vehicle claim 2 , its history claim 2 , or energy consumption is stored or coded into the battery receptacle for enabling automated handling claim 2 , refueling claim 2 , or control.8. A method for wherein the universal battery ...

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24-10-2019 дата публикации

AUTOMATED WATER AND PARTICLE DETECTION FOR DISPENSING FUEL INCLUDING AVIATION FUEL, AND RELATED APPARATUSES, SYSTEMS, AND METHODS

Номер: US20190322519A1
Принадлежит:

A fuel dispensing apparatus and method for delivering fuel from a fuel source, including, without limitation, delivering aircraft fuel from a fuel tank to an aircraft is disclosed. The fuel dispensing apparatus also includes an electronic control system in communication with a particle detector and configured to receive fuel quality sensor information corresponding to at least one detected fuel quality characteristic in real time. The electronic control system is configured to determine, based on the received fuel quality sensor information, a particle ratio defined as an approximate ratio of a measurement of total water and particulate per unit volume of fuel, and a first water characteristic indicative of a presence or absence of a threshold amount of water per unit volume of fuel. Based on the first water characteristic and on the particle ratio, the electronic control system is configured to determine whether to initiate at least one corrective action. 1. A fuel dispensing apparatus for delivering fuel , comprising:a flow conduit defining a fluid flow path from a fuel source to an outlet where fuel is dispensed;a particle detector configured to detect particles in the fuel and generate raw particle counts for each of a plurality of predetermined particle size ranges in real time as the fuel passes through the flow conduit, the plurality of predetermined particle size ranges comprising a first predetermined particle size range and a second predetermined particle size range, the particle detector unable to directly detect the particles as being specific to particulate contamination or water contamination; andan electronic control system in communication with the particle detector, determine, based on the raw particle counts for each of the plurality of predetermined particle size ranges, a first particle count of a first set of the particles in the first predetermined particle size range and a second particle count of a second set of the particles in the second ...

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10-12-2015 дата публикации

RAPID STORE LOAD SYSTEM FOR AIRCRAFT AND METHOD OF OPERATION THEREOF

Номер: US20150353300A1
Автор: Grossman Victor A.
Принадлежит:

A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft. 1. A method to load stores on an aircraft using plurality of lift portions , the method controlled by a controller , the method comprising acts of:receiving the stores at corresponding lift portions of the plurality of lift portions;determining positions of each of a of plurality of hardpoints (HPS) of the aircraft;controlling corresponding lift portions to position the received stores relative to corresponding HPs of the plurality of HPs of the aircraft; andsecuring the stores to corresponding HPs of the plurality of HPs.2. The method of claim 1 , further comprising an act of selecting the stores to be received by the corresponding lift portions in accordance with one or more of an identification (ID) of the aircraft and an identification of the stores.3. The method of claim 1 , wherein the act of selecting the stores further comprises acts of:determining a configuration of the aircraft; andcontrolling one or more of the lift portions in accordance with the determined configuration of the aircraft.4. The method of claim 3 , wherein the configuration of the aircraft comprises information related to one or more of aircraft type claim 3 , aircraft identification (ID) claim 3 , aircraft block number claim 3 , selected stores claim 3 , flight data link (FDL) type claim 3 , hardpoint configuration claim 3 , HP type claim 3 , HP location claim 3 , HP rack unit (RU) claim 3 , RU location claim 3 , pylon information claim 3 , launcher information.5. The method of claim 1 , wherein the act of securing the stores comprises attaching the stores to corresponding HPs of the plurality of HPs in accordance ...

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30-11-2017 дата публикации

RECEIVER SURGE TEST TOOL ASSEMBLY, SYSTEM, AND METHOD

Номер: US20170344034A1
Принадлежит:

A receiver surge test tool (STT) assembly, system and method for receiver surge pressure testing. The receiver STT assembly has a receiver surge test tool (STT) configured to simulate surge pressure conditions of a receiver aircraft, and to measure one or more surge pressures generated when receiving a fuel flow of fuel from a refueling source during the receiver surge pressure testing that is ground based. The receiver STT has a pipe manifold structure with inlet port(s), outlet port(s), and one or more flow lines disposed therebetween. Each flow line includes a flow meter, a pressure transducer, a shutoff valve having varying valve close rates, and a manual back pressure valve. The receiver STT assembly has a control system for controlling open and close positions of the shutoff valve, and the receiver STT, and has a data system for collecting and recording data generated during the receiver surge pressure testing. 1. A receiver surge test tool (STT) assembly for receiver surge pressure testing , the receiver STT assembly comprising: one or more inlet ports configured to receive the fuel flow from the refueling source;', 'one or more outlet ports configured for connection to a fuel return system; and', a flow meter for measuring a flow rate of the fuel flow through the flow line;', 'a pressure transducer for measuring the surge pressure of the fuel flow through the flow line;', 'a shutoff valve having varying valve close rates and having two sets of valve position indicators for indicating an open position and a close position; and', 'a manual back pressure valve for adjusting back pressure;, 'one or more flow lines disposed between the one or more inlet ports and the one or more outlet ports, each flow line configured to move the fuel flow from the one or more inlet ports to the one or more outlet ports, and each flow line comprising], 'a receiver surge test tool (STT) configured to simulate surge pressure conditions of a receiver aircraft, and configured to ...

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15-12-2016 дата публикации

FUEL DELIVERY SYSTEM AND METHOD FOR TRANSFERRING FUEL USING COMPRESSED AIR TO FORCE FUEL FROM A TANK TO A REFUELED ITEM

Номер: US20160362195A1
Принадлежит:

A fuel delivery system for transferring fuel using pressurized air includes a vehicle having a fuel tank supported by the vehicle, the fuel tank including a volume of fuel and a volume of pressurized air. A compressor supported on the vehicle and in fluid communication with the fuel tank operates to maintain a pressure of the pressurized air by monitoring a pressure of the air within the tank using a pressure sensor. A fuel transfer hose in fluid communication with the interior of the tank transfers the fuel to an item to be refueled using only a force of the pressurized air acting on the fuel when a tank valve of the tank is in the open position. 1. A fuel delivery system comprising:a fuel tank including a fuel portion occupied by a volume of a fuel and a pressurized air portion occupied by a volume of pressurized air;a compressor in fluid communication with the pressurized air portion; anda controller configured to maintain a pressure of the pressurized air portion between a low pressure threshold value and a high pressure threshold value by selectively operating the compressor.2. The fuel delivery system of claim 1 , wherein the controller is configured to monitor a pressure of the pressurized air portion using a pressure sensor disposed in the pressurized air portion.3. The fuel delivery system of claim 2 , wherein the controller is configured to begin operation of the compressor in response to the pressure sensor sensing that the pressure of the pressurized air portion is below the low pressure threshold value.4. The fuel delivery system of claim 3 , wherein the controller is configured to cease operation of the compressor in response to the pressure sensor sensing that the pressure of the pressurized air portion is at the high pressure threshold value.5. The fuel delivery system of claim 1 , wherein the compressor is disposed in a vehicle carrying the fuel tank claim 1 , the compressor driven by a motor of the vehicle.6. The fuel delivery system of claim 5 , ...

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05-11-2020 дата публикации

RAPID STORE LOAD SYSTEM FOR AIRCRAFT AND METHOD OF OPERATION THEREOF

Номер: US20200346755A1
Автор: Grossman Victor A.
Принадлежит:

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft. 120.-. (canceled)21. A system to load stores on an aircraft , comprising:at least one actuator;one or more lift portions;at least one sensor configured to form sensor information; and assign one or more stores to the aircraft; and', control a position of the aircraft;', 'load the one or more stores onto the one or more corresponding lift portions;', 'position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from the at least one sensor; and', 'secure the one or more stores to the aircraft., 'control at least one actuator to], 'a controller configured to22. The system of claim 21 , wherein the stores are secured to at least one hardpoint (HP) of the aircraft.23. The system of claim 21 , wherein the controller further enables an automatic store attachment mode to automatically control the at least one actuator to secure the one or more stores to the aircraft.24. The system of claim 21 , wherein the controller is further configured to obtain requested store information (RSI) from a memory of the system claim 21 , the RSI including information related to the one or more stores.25. The system of claim 24 , wherein the controller is further configured to control the at least one actuator to automatically retrieve the one or more stores.26. The system of claim 21 , wherein the controller is further configured to control the at least one actuator to retract the corresponding lift portions of the one or more lift ...

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12-11-2020 дата публикации

AIRCRAFT REFUELING SAFETY SYSTEM

Номер: US20200354074A1
Принадлежит:

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. 1. An aircraft refueling safety module , comprising:a memory, and [ data identifying the aircraft, and', 'a type of fuel required by the aircraft;, 'compare data wirelessly received from a first data source comprising at least one aircraft data source, the aircraft data source data comprising at least one of, data identifying the aircraft, and', 'the type of fuel required by the aircraft;, 'to data received from a second data source comprising at least one data source not located at the aircraft, the second data source data comprising at least one of, 'determine, based on the comparison, if the first data source data matches the second data source data; and', 'if the first data source data matches the second data source data, allow fuel to be dispensed to the aircraft., 'one or more processors in communication with the memory, the one or more processors configured to2. The aircraft refueling safety module of where the one or more processors is further configured to: data identifying the aircraft, and', 'the type of fuel required by the aircraft;, 'compare the aircraft data source data and the second data source data to data received from an enterprise, ...

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27-12-2018 дата публикации

REFUELLING ARRANGEMENT

Номер: US20180370788A1
Принадлежит: I6 GROUP LIMITED

A refuelling method having instructing a refuelling operator to dispense a quantity of fuel to, and maintaining, during dispensing of the fuel, at least intermittent, substantially real time communication with an officer responsible for the aircraft to advise the officer of the status of the refuelling process. A system having a refuelling module and an officer module, the refuelling module configured to receive instructions to dispense a quantity of fuel to an aircraft, an at least intermittent, substantially real time communications link being maintained between the refuelling module and the officer module during dispensing of fuel to the aircraft, the refuelling module being adapted to transmit to the officer module information relating to the status of the refuelling process, and the officer module being adapted to display to an output indicative of the status of the refuelling process. The method and system permits modification of the instruction during refuelling. 1. A refuelling method comprising instructing a refuelling operator to dispense a quantity of fuel to a fuel tank of an apparatus , and maintaining , during dispensing of the fuel , at least intermittent , substantially real time communication with an officer responsible for the apparatus to advise the officer of the status of the refuelling process , wherein the communication with the officer is a two-way communication , allowing the officer to modify the instruction to dispense a quantity of fuel , or to transmit an alternative , updated instruction , whilst fuel is being dispensed.2. The method according to claim 1 , wherein the communications link is maintained between a refuelling module used by the refuelling operator and an officer module used by the officer.3. The method according to claim 2 , wherein the communication is undertaken by way of a wireless communications link claim 2 , providing wireless communication between the refuelling module used by the refuelling operator and the officer ...

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24-12-2020 дата публикации

AIRCRAFT REFUELLING DEVICE, COMMISSIONING METHOD, AND REFUELLING METHOD USING SUCH A DEVICE

Номер: US20200399000A1
Автор: Beck Claude
Принадлежит:

Aircraft refueling device including a deformable pipe for the circulation of fuel, the downstream end of which is provided with a wing fastener for the connection thereof onto an intake port of the aircraft fuel tank. The device includes a first sensor for measuring the pressure values, in the vicinity of the wing fastener, of a fuel flow in the deformable pipe, and means for determining the flow rate in the deformable pipe. The device further includes a second sensor for measuring the pressure values of the flow upstream of the deformable pipe, a unit for calculating the pressure drop of the flow in the deformable pipe, based on the pressure values measure by the first and second sensors. The device also includes a unit for comparing the calculated pressure drop value with a reference value, established during the commissioning phase, for example, for the same flow rate. 1. An aircraft refueling device comprising:a deformable pipe for circulation of fuel, the downstream end of which is provided with a wing fastener for connection thereof onto an intake port of an aircraft fuel tank;a first sensor for measuring pressure values in the vicinity of said wing fastener, of a fuel flow in said deformable pipe;a member for determining the rate of the flow in said deformable pipe;a second sensor for measuring pressure values of the flow upstream of said deformable pipe;a calculating unit for calculating a value of the pressure drop of the flow in said deformable pipe, based on the pressure values measured by said first and second sensors; anda comparison unit for comparing the calculated pressure drop value with a reference value established for the same flow rate.2. The refueling device according to claim 1 , further comprising:a pressure regulator installed on the path of the flow, upstream of said deformable pipe; anda control loop of said pressure regulator comprising said first sensor, said calculating unit, and said comparison unit.3. The refueling device according to ...

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24-12-2020 дата публикации

AIRCRAFT REFUELLING DEVICE AND METHOD FOR MANUFACTURING A WING COUPLING FOR SUCH A DEVICE

Номер: US20200399001A1
Автор: Beck Claude
Принадлежит:

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. 1. An aircraft refueling device , this comprising a pipe for the circulation of fuel , the downstream end of which is provided with a wing coupling for connection thereof onto an intake port of an aircraft fuel tank , the wing coupling comprising:a body;a sensor for measuring the value of a parameter representative of a flow of fuel passing through said wing coupling; andat least one battery electrically powering said sensor, wherein said sensor and said at least one battery are housed in two half-shells mounted together around said body of said wing coupling.2. The refueling device according to claim 1 , wherein said sensor is mounted in a first one of said two half-shells claim 1 , and said at least one battery is mounted in a second one of said two half-shells.3. The refueling device according to claim 2 , wherein electrical connection members between said sensor and said at least one battery are provided in an interface area between said two half-shells.4. The refueling device according to claim 1 , wherein said two half-shells are mounted removably around said body of said wing coupling.5. The refueling device according to claim 1 , wherein said two half-shells are connected to one another by clamping members of said two half-shells on said body of said wing coupling.6. The refueling device according to claim 1 , wherein said two half-shells have a different color from that of ...

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31-12-2020 дата публикации

SYSTEM AND METHOD FOR PROVIDING SERVICE ON GOLF COURSE USING FUEL CELL DRONE

Номер: US20200407059A1
Автор: Kim Ji Young
Принадлежит:

A system and a method for providing service on a golf course using a fuel cell drone using a hydrogen fuel cell as a power source to provide various services while preventing a rounding delay of golfers are provided. A fuel cell drone of a system for providing service on a golf course may include a hydrogen fuel tank in which hydrogen is charged, a power pack configured to generate power to drive the fuel cell drone using the hydrogen in the hydrogen fuel tank, and a controller configured to move the fuel cell drone to a docking station or a gas supply place in response to determining that an amount of hydrogen remaining in the hydrogen fuel tank is below a set value. 1. A fuel cell drone of a system for providing service on a golf course comprising:a hydrogen fuel tank in which hydrogen is charged;an external diffuser guide;a power pack configured to generate power to drive the fuel cell drone using the hydrogen in the hydrogen fuel tank; anda controller configured to move the fuel cell drone to a docking station or a gas supply place in response to determining that an amount of hydrogen remaining in the hydrogen fuel tank is below a set value.2. The fuel cell drone of claim 1 ,wherein the controller blocks a drive power output of the power pack after the fuel cell drone is docked in the docking station.3. The fuel cell drone of claim 1 ,wherein the hydrogen fuel tank comprises a main hydrogen fuel tank and a sub-hydrogen fuel tank,wherein the fuel cell drone further comprises a hydrogen supply valve configured to selectively supply the hydrogen from the main hydrogen fuel tank and the sub-hydrogen fuel tank to the power pack, andwherein the controller controls, in response to determining that the amount of hydrogen remaining in the main hydrogen fuel tank is less than the set value, the hydrogen supply valve to block the hydrogen supply from the main hydrogen fuel tank to the power pack and to supply the hydrogen in the sub-hydrogen fuel tank to the power pack.4. ...

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09-11-2007 дата публикации

Refueling apparatus for aircraft with circualation line

Номер: KR100775276B1
Автор: 박윤소, 심점석
Принадлежит: 주식회사 엔케이

A refueling apparatus for an aircraft with a circulation line is provided to convey fuel discharged from a second circulation line to a fuel storage part and readily perform exchange and flushing of fuel between an oil feeding part and a tank. A refueling apparatus for an aircraft with a circulation line includes a fuel storage part(10), a filtering part(20), a fuel feeding part(30), a drain part(40), a first fuel supply line(60), a second fuel supply line(70), a third fuel supply line(80), a first discharge line(110), a second discharge line(120), a first circulation line(90), a second circulation line(100), and a third circulation line(130). The fuel storage part is connected to a fuel supply source(50) by the first fuel supply line. The fuel storage part is connected to the filtering part by the second fuel supply line. The filtering part is connected to the oil feeding part by the third fuel supply line.

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04-12-2018 дата публикации

fire suspension drone for skyscrapers

Номер: KR101925078B1
Автор: 이길도
Принадлежит: 대신아이브(주)

본 발명은 초고층건물에서 발생된 화재를 효과적으로 진압할 수 있도록 된 새로운 구조의 초고층건물 화재진압용 드론에 관한 것이다. 본 발명에 따른 초고층건물 화재 진압용 드론은 화재가 발생될 경우, 화재가 발생된 높이까지 날아올라가 분사노즐(40)을 통해 화재현장에 직접 물을 분사함으로, 종래의 소방차에서 물을 분사할 수 없는 높은 층에서 발생된 화재를 효과적으로 진압할 수 있는 장점이 있다.

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14-06-2000 дата публикации

Hydrant servicer cart

Номер: CN1256669A

一种飞机加油服务车,包括具有接地轮(11,12)的底盘(10),用于飞机加油操作者站立的加油平台(20)。平台(20)由一剪式作用机构(22)安装到底盘(10)上,剪式作用机构通常是由液压装置致动。可伸张的液体输送软管(14)具有用于连接到机场燃油输送龙头上的联接器(15)。燃油输送支架(24)从液体输送软管向平台(20)上的一个或多个燃油软管(26)输送燃油。燃油软管(26)将燃油输送给飞机。该燃油服务车可停留在特定飞机站台处的停机坪上,并且可容易地从飞机的一侧移动到另一侧,而且可以服务于可使用其所停靠的站台的全部范围的飞机。这是通过平台(20)的可变高度调节能力达到的。

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10-07-1956 дата публикации

Fuel filling adapter

Номер: US2753884A
Автор: Griffith W Lindsay
Принадлежит: Buckeye Iron and Brass Works

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15-05-1962 дата публикации

Hydrant valve

Номер: US3034544A
Автор: Donald G Griswold
Принадлежит: Individual

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23-04-1963 дата публикации

Servicing nozzle

Номер: US3086565A
Автор: James K Mosher
Принадлежит: Schulz Tool and Manufacturing Co

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04-01-1949 дата публикации

Underwing fueling system

Номер: US2458245A
Автор: Lawrence J Bordelon
Принадлежит: Consolidated Vultee Aircraft Corp

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23-02-1989 дата публикации

Patent DE8900046U1

Номер: DE8900046U1
Автор: [UNK]

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18-07-1978 дата публикации

Aircraft flight line servicing system

Номер: US4101100A
Принадлежит: Value Engineering Co

In an aircraft flight line servicing system there is provided an electrical power unit and an air compressor from which extend respectively a plurality of electrical and air distribution lines and a plurality of service islands are each connected to all of the electrical and air distribution lines. Each service island is provided with components for supplying both starting air and cooling air and electricity to aircraft. The distribution lines and service islands may be detachably mounted upon the surface of the flight line and have such a height and shape so as to enable aircraft tires to pass thereover.

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08-03-2007 дата публикации

Operational ground support system having automated primary servicing

Номер: US20070051852A1
Принадлежит: Boeing Co

An aircraft servicing system ( 10 ) includes a tarmac-servicing system ( 500 ). The tarmac-servicing system ( 500 ) includes an aircraft-mating element ( 510 ) that is mounted and extendible from within an area of a tarmac ( 502 ) to couple with an aircraft ( 504 ). The tarmac-servicing system ( 500 ) supplies primary services to the aircraft ( 504 ), such as fuel, air, electrical power, water, coolant, potable water, and gray water. A method of servicing the aircraft ( 504 ) includes aligning a primary servicing port ( 512 ) of the aircraft ( 504 ) over a primary servicing area of a tarmac ( 502 ). A tarmac-servicing element ( 510 ) is extended out from the tarmac ( 502 ) to the aircraft ( 504 ). The tarmac-servicing element ( 510 ) is aligned and connected to the primary servicing port ( 512 ). Primary services are supplied and removed to and from the aircraft ( 504 ) in response to the tarmac-servicing element connection with the primary servicing port ( 512 ).

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03-03-2011 дата публикации

Ground support service cart apparatus and methods

Номер: US20110048572A1
Принадлежит: Spokane Industries LLC

A equipment service apparatus suited for use in servicing ground support equipment (GSE) or aircraft ground equipment (AGE). The apparatus includes a plurality of features for use in servicing and maintaining the GSE/AGE where the GSE/AGE is in use servicing an aircraft so that the GSE/AGE is not itself required to be transported to a remote location for servicing and/or maintenance. The apparatus may be constructed as a towable cart. The apparatus may include a fuel tank, a pump system configured to add fuel to or remove fuel from the fuel tank, and a fuel valve assembly operable to control fuel flow into and out of the fuel tank. The apparatus may also include a container storage portion configured to retain a plurality of removable fluid storage containers, at least one power source, and a power control system operable to control power from the at least one power source to operate at least some features of the equipment service apparatus.

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01-07-2003 дата публикации

Vented compartment inerting system

Номер: US6585192B2
Автор: Karl S. Beers

1. An inerting system for a vented controlled atmosphere container, for inerting a flammable gas comprising a flammable vapor and oxygen, comprising:(i) a container;(ii) an outlet in the container for the flammable gas;(iii) a compressor, in fluid communication with the outlet, which compresses the flammable gas from the container;(iv) a separator, in fluid communication with the compressor, for removing oxygen from the flammable gas to produce an oxygen-depleted flammable gas;(v) an inlet in the container, which is in fluid communication with the separator; through which the oxygen-depleted flammable gas is fed into the container.

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08-03-2023 дата публикации

Device for helicoter fuel supply with de-fueling function using ejector

Номер: KR20230033061A
Принадлежит: 주식회사 나브텍

본 발명에 따른 이젝터를 이용한 배유 기능을 갖춘 헬리콥터 연료공급 장치는, 연료유를 저장하는 연료저장부, 연료이송라인에 의해 상기 연료저장부와 연결되어 상기 연료저장부에 저장된 연료유를 펌핑하여 수분 및 불순물을 제거하고 연료공급부로 수분 및 불순물이 제거된 연료유를 이송시키는 펌프필터부, 상기 연료이송라인에 의해 상기 펌프필터부와 연결되어 상기 펌프필터부로부터 상기 연료유를 공급받아 연료공급라인을 통해 헬리콥터로 급유가 가능한 연료공급부, 상기 연료공급부 내에 구비되되 제1 유체유입구에 상기 연료이송라인이 분기되어 연결되고 제2 유체유입구에 상기 연료공급라인으로부터 분기되는 연료회수라인이 연결되고 유체분출구에 연료배출라인이 연결되는 이젝터, 및 상기 이젝터로의 유체 흐름을 제어하여 상기 연료공급부를 상기 연료공급부가 헬리콥터로 급유가 가능한 상태 또는 헬리콥터 내 연료유를 배유 가능한 상태로 전환하는 제어부를 포함한다.

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09-12-2022 дата публикации

Aviation Fuel System

Номер: KR102475195B1
Автор: 도외철, 최준원
Принадлежит: 대양전기공업 주식회사

본 발명은 선박용 항공기 급유 장치 모니터링 시스템에 관한 것으로, 선박에 이착륙하는 헬리콥터 등 항공기의 연료를 선박에서 급유하는 데 있어서 선박용 항공기 급유 장치의 밸브 등 각종 장비들의 압력 등 현재 상태를 측정하여 사용자가 모니터링할 수 있도록 터치패널 알림표시부에 장비별 버튼으로 표시하고 기설정된 기준범위를 초과하는 압력 등 비정상 상태가 장비에서 감지되면 터치패널 알림표시부의 시각적 알림이 발생하고 부저에서 소리가 울림으로써 터치패널 알림표시부가 설치된 선박 내 장소에서 사용자가 급유 장치 장비들의 비정상 상태를 원거리에서도 용이하게 파악하고, 연료의 누출이나 폭발 등의 사고를 미연에 방지할 수 있도록 하는 선박용 항공기 급유 장치 모니터링 시스템에 관한 것이다. The present invention relates to a system for monitoring an aircraft refueling device for a ship, in which a user can monitor the current conditions such as pressures of various equipment such as valves of a refueling device for a ship aircraft in refueling aircraft fuel from a ship, such as a helicopter taking off and landing on a ship. When an abnormal condition, such as pressure exceeding the preset standard range, is detected in the equipment, a visual notification is generated in the touch panel notification display unit and a buzzer sounds, so that the touch panel notification display unit The present invention relates to an aircraft refueling device monitoring system for a ship that allows a user to easily grasp the abnormal state of refueling device equipment even from a long distance at a place in an installed ship and prevent accidents such as fuel leakage or explosion in advance.

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04-06-2019 дата публикации

Fuel tank system and method

Номер: US10307708B2
Принадлежит: Hamilton Sundstrand Corp

A fuel tank system is disclosed that includes a fuel tank and a first fluid flow path between a gas space in the fuel tank and outside of the fuel system. A gas separation membrane is disposed with a first side in communication with the first fluid flow path and a second side in communication with a second fluid flow path. A fluid control device is in communication with the second fluid flow path and is configured to provide fluid flow from the second fluid flow path to a liquid space in the fuel tank or to outside of the fuel system. A prime mover is disposed in communication with the second fluid flow path, and is configured to move fluid on the second fluid flow path from the second side of the separation membrane to the fuel tank liquid space or to outside of the fuel system.

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22-12-2020 дата публикации

Portable aircraft fuel refueling cart

Номер: KR102193431B1
Автор: 이정두
Принадлежит: (주)리즈코포레이션

The present invention relates to a portable aircraft fuel supply cart which helps supply aircraft fuel without any additional equipment under any worst conditions. That is, currently, when a user needs to supply fuel to an aircraft, the user has to use a fuel supply vehicle equipped with a fuel supply system or use a dispense vehicle at a fuel supply facility installed with an underground transfer pipe. The present invention aims to settle the issue, to develop equipment to help supply fuel to an aircraft under any poor circumstances, and to contribute to helping agencies and workers for work related to aircraft make the best choice. The greatest feature of this equipment is to allow the user to supply high-quality fuel for aircraft in a broad range at the minimum cost with an optimized system while observing the regulations for supplying fuel to aircraft. According to the present invention, the portable aircraft fuel supply cart comprises a pump, a filter, a fuel supply nozzle, and a cart.

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12-04-2023 дата публикации

Device for helicoter fuel supply with de-fueling function using ejector

Номер: KR102520489B1
Принадлежит: 주식회사 나브텍

본 발명에 따른 이젝터를 이용한 배유 기능을 갖춘 헬리콥터 연료공급 장치는, 연료유를 저장하는 연료저장부, 연료이송라인에 의해 상기 연료저장부와 연결되어 상기 연료저장부에 저장된 연료유를 펌핑하여 수분 및 불순물을 제거하고 연료공급부로 수분 및 불순물이 제거된 연료유를 이송시키는 펌프필터부, 상기 연료이송라인에 의해 상기 펌프필터부와 연결되어 상기 펌프필터부로부터 상기 연료유를 공급받아 연료공급라인을 통해 헬리콥터로 급유가 가능한 연료공급부, 상기 연료공급부 내에 구비되되 제1 유체유입구에 상기 연료이송라인이 분기되어 연결되고 제2 유체유입구에 상기 연료공급라인으로부터 분기되는 연료회수라인이 연결되고 유체분출구에 연료배출라인이 연결되는 이젝터, 및 상기 이젝터로의 유체 흐름을 제어하여 상기 연료공급부를 상기 연료공급부가 헬리콥터로 급유가 가능한 상태 또는 헬리콥터 내 연료유를 배유 가능한 상태로 전환하는 제어부를 포함한다. Helicopter fuel supply device having an oil drain function using an ejector according to the present invention is connected to the fuel storage unit by a fuel storage unit for storing fuel oil and a fuel transfer line, and pumps the fuel oil stored in the fuel storage unit to water. and a pump filter unit that removes impurities and transfers the fuel oil from which moisture and impurities are removed to the fuel supply unit. It is connected to the pump filter unit by the fuel transfer line and receives the fuel oil from the pump filter unit, and the fuel supply line A fuel supply unit capable of refueling by a helicopter through the fuel supply unit, provided in the fuel supply unit, the fuel transfer line is branched and connected to the first fluid inlet, and the fuel recovery line branched from the fuel supply line is connected to the second fluid inlet and the fluid outlet It includes an ejector to which a fuel discharge line is connected, and a control unit for controlling the flow of fluid to the ejector to switch the fuel supply unit to a state in which the fuel supply unit can refuel a helicopter or a state in which fuel oil in a helicopter can be discharged.

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28-02-2002 дата публикации

Multiple control system of aircraft refueling vehicle

Номер: KR100314423B1
Автор: 황선건
Принадлежит: 가나공항산업주식회사, 황선건

본 발명은 항공기급유차의 다중제어시스템에 관한 것으로서, 더욱 상세하게는 비행기일 수 있는 주유대상물과의 주유시 급유차의 유동을 방지할 뿐만 아니라 급유이상시 급유시스템을 제어하므로서 안정된 급유를 할 수 있도록 한 항공기 급유차의 다중제어시스템에 관한 것이다. The present invention relates to a multiple control system of an aircraft refueling vehicle, and more particularly, it is possible not only to prevent the flow of the refueling vehicle when refueling with the refueling object that may be an airplane, but also to control the refueling system in the event of refueling, thereby providing stable refueling The present invention relates to a multiple control system for an aircraft refueling vehicle. 즉, 급유차 일측의 연료저장용 어뎁터 및 노즐 연동방지용 홀더와, 그리고 급유차 후방의 노즐 연동방지용 홀더 및 승강장치에 제동시스템을 동작시킬 수 있는 제동수단들을 각각 설치하여 주유대상물에 주유를 할 때나 급유차의 탱크조에 유류를 공급할 때 각 부분에서 에어압을 해제시켜 급유차의 제동시스템을 완벽하게 제동하므로서 유류의 누출을 방지하여 대형사고나 유류낭비를 방지한 항공기 급유차의 다중제어시스템을 제공하는데 그 목적이 있으며, 따라서 본 발명은 급유차에 있어 소정길이의 저장호스(미도시)와 연결되어 급유차의 탱크조(1)로 유류를 주입할 수 있는 연료저장용 어뎁터(2a) 및 급유차 측방에 설치되어 노즐을 안정되게 고정하여주는 노즐 연동방지용 홀더(3b)와, 그리고 급유차 후방에 설치되어 노즐을 안정되게 고정하여주는 노즐 연동방지용 홀더(4) 및 승강장치(5)의 적소에 에어탱크로 부터 공급되고 있는 에어가 해제 또는 공급되도록 다수의 연료저장용 에어밸브(130a) 및 노즐 연동 에어밸브(130b)(130c)(130d)를 순차적으로 연결 설치한 다음, 상기 연료저장용 에어밸브(130a), 노즐 연동 에어밸브(130b)(130c)(130d)들을 브레이크조작밸브(140)와 연통되게 연결시키고, 상기 브레이크 조작밸브(140)를 제동시스템의 브레이크 셋 밸브(150)와 연결시켜 다수의 밸브(130a)(130b)(130c)(130d)중 어느 하나만 동작되더라도 브레이크 셋 밸브(150)가 동작되도록 한 제동제어시스템(100)과; 상기 에어탱크의 에어에 의해 제어되게 통기구밸브(220)를 구비한 통기구조작밸브(210)가 설치되고 상기 통기구조작밸브(210)는 컨트롤밸브오퍼레이터(230)가 연통 설치하여, 상기 컨트롤밸브오퍼레이터(230)는 각각의 압력조절밸브(240a)(24 0b)를 거쳐 급유시스템의 인라인밸브(250)와 바이패스밸스(260)로 연결되는 한편, 상기 에어탱크로 부터 에어가 공급되는 다수의 비상밸브(270a)(270b)(270c)가 설치되고, 상기 비상밸브(270a)(270b)(270c)들은 비상정지밸브(280)와 연결되며, 상기 비상정지밸브(280)는 각각의 압력조절밸브(240a)(240b)와 연통되게 설치되는 급유제어시스템(200); 등으로 구성되는 것을 특징으로 한 것이다. In other words, the fuel storage adapter and nozzle interlocking prevention holder on one side of the refueling vehicle, and the nozzle interlocking prevention holder and the lifting device at the rear of the refueling vehicle are provided with braking means for operating the ...

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13-01-2022 дата публикации

Systems and methods for storing, transporting, and using hydrogen

Номер: US20220009648A1
Принадлежит: Universal Hydrogen Co

The present disclosure provides systems and methods for storing, transporting, and using hydrogen. In some embodiments, the method may comprise (a) storing hydrogen fuel in one or more fuel storage modules; (b) transporting the one or more fuel storage modules to a vehicle fueling site, wherein one or more hydrogen fuel compatible vehicles are located at or near the vehicle fueling site; (c) loading the one or more fuel storage modules into the one or more hydrogen fuel compatible vehicles, wherein the one or more fuel storage modules are configured to be releasably coupled to the one or more hydrogen fuel compatible vehicles; and (d) decoupling the one or more fuel storage modules from the one or more hydrogen fuel compatible vehicles after the one or more fuel storage modules are depleted or partially depleted.

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02-12-1977 дата публикации

Valve for emptying aircraft fuel tanks - has electromagnetically operated jaws to grip collar of valve shaft

Номер: FR2350250A1
Автор: [UNK]
Принадлежит: CONST AERO NAVALES

The device is notably for the carburation tank of an aircraft which contains fuel pressurised by gas which may need emptying rapidly. the opening of the device comprises a support bearing for a valve which is held elastically against the bearing and is fitted into a stop valve, formed like a cover. The stop valve is mounted on a shaft, which is guided centrally in the device and can be moved between two positions one corresponding to the valve being open and the other corresponding to the valve being shut. This occurs when a a collar on the shaft is gripped in jaws moved by an electromagnet.

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02-05-2014 дата публикации

DEVICE FOR FILLING A TANK BY GRAVITY OR PRESSURE

Номер: FR2955572B1
Принадлежит: Eurocopter France SA, Eurocopter SA

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24-03-2023 дата публикации

AIRCRAFT COMPRISING A DIHYDROGEN TRANSPORT PIPE AND A BURIAL CHANNEL FOR SAID TRANSPORT PIPE

Номер: FR3127203A1
Принадлежит: AIRBUS OPERATIONS SAS

AÉRONEF COMPORTANT UNE CANALISATION DE TRANSPORT DE DIHYDROGÈNE ET UN CANAL D’ENFOUISSEMENT DE LADITE CANALISATION DE TRANSPORT L’invention concerne un aéronef comportant au moins une canalisation de transport (112a-b) dans laquelle s’écoule du dihydrogène et pour chaque canalisation de transport (112a-b), un canal d’enfouissement (200a-b) dans lequel est logée ladite canalisation de transport (112a-b), où le canal d’enfouissement (200a-b) comporte un caniveau (202) qui comporte un fond et une ouverture à l’opposé du fond et un couvercle (204) qui recouvre l’ouverture du caniveau (202), où le couvercle (204) constitue une paroi extérieure de l’aéronef en contact direct avec un air extérieur entourant l’aéronef et où le couvercle (204) est percé des fenêtres de ventilation (206) qui permettent le passage du dihydrogène vers l’extérieur. Avec un tel arrangement, même en cas de fuite de dihydrogène dans le canal d’enfouissement, le dihydrogène s’évacue automatiquement vers l’extérieur. Fig. 4 AIRCRAFT COMPRISING A DIHYDROGEN TRANSPORT PIPE AND A BURIAL CHANNEL FOR SAID TRANSPORT PIPE The invention relates to an aircraft comprising at least one transport pipe (112a-b) in which dihydrogen flows and for each (112a-b), a burial channel (200a-b) in which said transport pipeline (112a-b) is housed, wherein the burial channel (200a-b) comprises a channel (202) which comprises a bottom and an opening opposite the bottom and a cover (204) which covers the opening of the drain (202), where the cover (204) constitutes an exterior wall of the aircraft in direct contact with an external air surrounding the aircraft and where the cover (204) is pierced with ventilation windows (206) which allow the passage of hydrogen to the outside. With such an arrangement, even in the event of a dihydrogen leak in the burial channel, the dihydrogen is automatically evacuated to the outside. Fig. 4

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21-09-1984 дата публикации

Patent FR2523617B1

Номер: FR2523617B1
Автор: [UNK]
Принадлежит: Defontaine SA

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23-06-1967 дата публикации

Advanced device for refueling aircraft with liquid fuel

Номер: FR1486155A
Автор:

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25-07-1997 дата публикации

FIXED FUEL SUPPLY SYSTEM FOR AIRCRAFT

Номер: FR2733732B1
Автор: Michel Magne
Принадлежит: Elf Antar France

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28-08-1987 дата публикации

REFUELING DEVICE FOR HELICOPTERS AND VERTICAL TAKE OFF AIRCRAFT

Номер: FR2568852B3
Автор: [UNK]
Принадлежит: Babeurs Jean

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05-04-2013 дата публикации

FLUID RECOVERY DEVICE FOR AN AIRCRAFT

Номер: FR2972177B1
Принадлежит: AIRBUS OPERATIONS SAS

Un dispositif (1) de récupération de fluide pour un aéronef, le dispositif (1) comportant des moyens (2) de stockage de fluide, un entonnoir (6) de récupération de fluide et des moyens (7) de canalisation reliant l'entonnoir (6) aux moyens de stockage (2) de manière à guider le fluide récupéré par l'entonnoir (6) dans les moyens de stockage (2), le dispositif (1) comportant des moyens (8) de basculement de l'entonnoir (6) agencés pour déplacer l'entonnoir (6) entre une position de travail (PT) dans laquelle l'entonnoir (6) s'étend sensiblement verticalement et une position de repos (PR) dans laquelle l'entonnoir (6) s'étend obliquement par rapport à la direction verticale. A fluid recovery device (1) for an aircraft, the device (1) comprising fluid storage means (2), a fluid recovery funnel (6) and pipe means (7) connecting the funnel (6) to the storage means (2) so as to guide the fluid recovered by the funnel (6) in the storage means (2), the device (1) comprising means (8) for tilting the funnel (6) arranged to move the funnel (6) between a working position (PT) in which the funnel (6) extends substantially vertically and a rest position (PR) in which the funnel (6) s 'extends obliquely from the vertical direction.

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26-08-2016 дата публикации

DEVICE AND METHOD FOR CONNECTING AN AIRCRAFT EMPTY-PIPING PIPE

Номер: FR2951241B1
Автор: Stephane Mateo
Принадлежит: AIRBUS OPERATIONS SAS

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21-10-1960 дата публикации

Filter assemblies and water separators for fuels or other liquids

Номер: FR1244036A
Автор:
Принадлежит: Bendix Aviation Corp

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12-11-2010 дата публикации

FISHING MACHINE AND METHOD OF FUELING A FUEL AIRCRAFT USING SUCH A GEAR

Номер: FR2945273A1
Автор: Claude Beck
Принадлежит: Desautel SAS

Cet engin d'avitaillement d'un aéronef en carburant comprend un conduit (40) équipé de moyens (42) de raccordement sur un orifice d'entrée (301) d'un réservoir de carburant d'un aéronef (400). Cet engin comprend en outre, au niveau ou au voisinage des moyens de raccordement (42), des moyens (501) de détermination de la valeur d'au moins un paramètre représentatif d'un écoulement de carburant (E) transitant par les moyens de raccordement et des moyens (503, 504) d'émission, vers au moins un récepteur embarqué sur l'engin d'avitaillement, d'un signal (S (P)) représentatif d'une valeur de paramètre déterminée par les moyens de détermination (501). Le procédé d'avitaillement comprend des étapes consistant, au cours d'une opération d'avitaillement, à déterminer la valeur d'au moins un paramètre représentatif de l'écoulement (E) au niveau ou au voisinage des moyens de raccordement (42), et à émettre vers au moins un récepteur embarqué sur l'engin d'avitaillement un signal (S (P)) représentatif d'une valeur de paramètre déterminée lors de l'étape précédente. This refueling machine of an aircraft in fuel comprises a conduit (40) equipped with means (42) for connection to an inlet port (301) of a fuel tank of an aircraft (400). This machine further comprises, at or near the connection means (42), means (501) for determining the value of at least one parameter representative of a fuel flow (E) passing through the means of connection and means (503, 504) for transmitting, to at least one receiver on board the refueling machine, a signal (S (P)) representative of a parameter value determined by the determination means (501). The refueling process comprises the steps of, during a refueling operation, determining the value of at least one parameter representative of the flow (E) at or near the connecting means (42). , and transmit to at least one receiver on board the refueling craft a signal (S ( ...

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