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RU2140381C1 - Aircraft system for refuelling receiver aircraft - Google Patents

Aircraft system for refuelling receiver aircraft Download PDF

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Publication number
RU2140381C1
RU2140381C1 RU97120800A RU97120800A RU2140381C1 RU 2140381 C1 RU2140381 C1 RU 2140381C1 RU 97120800 A RU97120800 A RU 97120800A RU 97120800 A RU97120800 A RU 97120800A RU 2140381 C1 RU2140381 C1 RU 2140381C1
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RU
Russia
Prior art keywords
fuel
aircraft
unit
line
pump
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Application number
RU97120800A
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Russian (ru)
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RU97120800A (en
Inventor
И.В. Емельянов
Е.В. Ковановский
Г.А. Королев
Ю.И. Пичугин
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Акционерное общество открытого типа "ОКБ Сухого"
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Priority to RU97120800A priority Critical patent/RU2140381C1/en
Publication of RU97120800A publication Critical patent/RU97120800A/en
Application granted granted Critical
Publication of RU2140381C1 publication Critical patent/RU2140381C1/en

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Abstract

FIELD: in-flight refuelling systems; tanker aircraft equipped with suspended refuelling unit. SUBSTANCE: aircraft refuelling system includes suspended refuelling unit with self-contained drive of booster pump arranged inside unit, branching main and hydraulically-driven pump. Suction inlet of this pump is communicated with fuel compartment of tanker aircraft by means of inter-unit pipe and aircraft fuel line. Delivery outlet of this pump is communicated with fuel inlet of hose drum of unit means of inter-unit delivery line. Branching main communicates inter-unit delivery line with fuel compartment of tanker aircraft. Suction inlet of hydraulically-driven pump is located in fuel compartment of tanker aircraft. Delivery output of this pump is communicated with above-mentioned inter-aircraft fuel line. Inlet of pump hydraulic drive is communicated with branching main of suspended refuelling unit. EFFECT: reliable and smooth delivery of fuel to pump of suspended refuelling unit. 2 cl, 1 dwg

Description

Изобретение относится к средствам заправки топливом в полете и предназначено для реализации на самолете-заправщике, оборудованном подвесным агрегатом заправки. The invention relates to in-flight fueling facilities and is intended for sale on a refueling aircraft equipped with an overhead refueling unit.

При заправке самолетом-заправщиком другого самолета важен высокий темп заправки, требующий надежного и равномерного подвода топлива из емкостей самолета-заправщика к насосу подвесного агрегата заправки. Известные источники (RU патент N 1778977, 20.05.95) не раскрывают, каким образом это возможно. When refueling with a refueling aircraft of another aircraft, a high refueling rate is important, requiring a reliable and even supply of fuel from the capacities of the refueling aircraft to the pump of the refueling suspension unit. Known sources (RU patent N 1778977, 05.20.95) do not disclose how this is possible.

В основу изобретения положено решение задачи обеспечить надежный и равномерный подвод заправляемого топлива к насосу подвесного агрегата заправки, имеющего автономный привод насоса. The basis of the invention is the solution to the problem of providing a reliable and uniform supply of refuelable fuel to the pump of a suspended refueling unit having an autonomous pump drive.

Решение задачи обеспечивается тем, что самолетная система дозаправки другого самолета, содержащая подвесной агрегат заправки с автономным приводом внутриагрегатного подкачивающего насоса, имеющего всасывающий вход, сообщенный посредством внутриагрегатной трубы и внутрисамолетного топливопровода с топливным отсеком самолета, и нагнетательный выход, сообщенный внутриагрегатной линией нагнетания с топливовводом шлангового барабана агрегата, и отводную магистраль, сообщающую внутриагрегатную линию нагнетания с топливным отсеком самолета, согласно изобретению снабжена гидроприводным насосом, в котором всасывающий вход расположен в топливном отсеке самолета, нагнетательный выход сообщен с указанным внутрисамолетным топливоприводом, а вход гидропривода сообщен с отводной магистралью подвесного агрегата заправки. The solution to the problem is provided by the fact that the aircraft refueling system of another aircraft, comprising a hanging refueling unit with an autonomous drive of an internal unit booster pump having a suction inlet communicated via an internal unit pipe and an in-flight fuel line with an aircraft fuel compartment, and a discharge outlet communicated by an in-line discharge line of a hose with a fuel line the drum of the unit, and a bypass line communicating the in-house discharge line with the fuel compartment ca The jet according to the invention is equipped with a hydraulic drive pump, in which the suction inlet is located in the fuel compartment of the aircraft, the discharge outlet is in communication with the indicated in-flight fuel supply, and the hydraulic input is in communication with the discharge line of the refueling suspension unit.

Излишняя мощность автономного привода подвесного агрегата заправки расходуется на обеспечение подкачки заправляемого топлива внутрисамолетным насосом, привод которого осуществляется топливом повышенного давления из насоса подвесного агрегата заправки. The excessive power of the stand-alone drive of the refueling suspension unit is spent on providing pumping of the refueling fuel with an in-flight pump, which is driven by high-pressure fuel from the pump of the refueling suspension unit.

В некоторых случаях целесообразно, чтобы нагнетательный выход гидроприводного насоса был сообщен с указанным внутрисамолетным топливопроводом через магистраль топливопитания маршевого двигателя самолета, а выход гидропровода этого же насоса сообщен с расходным отсеком топливной системы самолета. In some cases, it is advisable that the discharge output of the hydraulic pump is communicated with the indicated in-flight fuel line through the fuel supply line of the main engine of the aircraft, and the output of the hydraulic line of the same pump is connected to the consumable compartment of the aircraft fuel system.

В магистрали топливопитания маршевого двигателя устойчиво поддерживается необходимые давление и расход топлива. In the fuel supply line of the marching engine, the necessary pressure and fuel consumption are stably maintained.

В дальнейшем изобретение поясняется конкретными примерами его выполнения со ссылками на прилагаемый чертеж, на котором изображена самолетная система дозаправки другого самолета. The invention is further illustrated by specific examples of its implementation with reference to the accompanying drawing, which shows an aircraft refueling system of another aircraft.

Описываемая система содержит подвесной агрегат заправки 1, внутриагрегатный подкачивающий насос 2 с автономным приводом 3. Всасывающий вход внутриагрегатного подкачивающего насоса сообщен посредством внутриагрегатной трубы 4 и внутрисамолетного трубопровода 5 с топливным отсеком 6 самолета. Магистральный выход подкачивающего насоса 2 сообщен внутриагрегатной линией нагнетания 7 с топливоводом 8 шлангового барабана 9. The described system contains a suspension unit for refueling 1, an internal unit booster pump 2 with an independent drive 3. The suction inlet of the internal unit booster pump is communicated by means of the internal unit pipe 4 and the in-flight pipe 5 with the fuel compartment 6 of the aircraft. The main output of the booster pump 2 is communicated by the in-line discharge line 7 with the fuel line 8 of the hose reel 9.

Система снабжена гидроприводным насосом 10. Всасывающий вход этого насоса расположен в топливном отсеке 6, нагнетательный выход насоса сообщен с внутрисамолетным топливопроводом 5, а вход гидропривода насоса сообщен с отводной магистралью 11 подвесного агрегата заправки 1. The system is equipped with a hydraulic pump 10. The suction inlet of this pump is located in the fuel compartment 6, the pump discharge outlet is in communication with the in-flight fuel line 5, and the pump hydraulic inlet is connected to the bypass line 11 of the refueling suspension unit 1.

Перекачка топлива из очередных баков 12, 13, 14, 15, 16 в топливоотсек 6 производится перекачивающими насосами 17, 18, 19, 20, 21, 22, 29. В магистраль топливопитания 23 маршевых двигателей топливо из топливного отсека 6 подается подкачивающими насосами 24. The fuel is pumped from the next tanks 12, 13, 14, 15, 16 to the fuel compartment 6 by the transfer pumps 17, 18, 19, 20, 21, 22, 29. The fuel from the fuel compartment 6 is supplied with boost pumps 24 to the fuel supply line of 23 main engines.

Управление дозаправкой осуществляется при помощи отсечных клапанов 25, установленных в топливопроводе 5 и во внутриагрегатной линии 7. Расходомер 26 обеспечивает контроль количества заправленного топлива. Клапан 27 обеспечивает при необходимости перепуск топлива из отводной магистрали 11 подвесного агрегата заправки во внутриагрегатную трубу 4 перед подкачивающим насосом 2. Дренаж подкачивающего насоса 2 осуществляется в топливный отсек самолета посредством линии 29. Refueling is controlled by shut-off valves 25 installed in the fuel line 5 and in the unit line 7. The flow meter 26 provides control of the amount of refueling. The valve 27 provides, if necessary, a fuel bypass from the bypass line 11 of the outboard refueling unit to the inlet pipe 4 in front of the booster pump 2. The booster pump 2 is drained into the fuel compartment of the aircraft via line 29.

Claims (2)

1. Самолетная система дозаправки другого самолета, содержащая подвесной агрегат заправки с автономным приводом внутриагрегатного подкачивающего насоса, имеющего всасывающий вход, сообщенный посредством внутриагрегатной трубы и внутрисамолетного топливопровода с топливным отсеком самолета-заправщика, и нагнетательный выход, сообщенный внутриагрегатной линией нагнетания с топливовводом шлангового барабана агрегата, и отводную магистраль, сообщающую внутриагрегатную линию нагнетания с топливным отсеком самолета-заправщика, отличающаяся тем, что система снабжена гидроприводным насосом, в котором всасывающий вход расположен в топливном отсеке самолета-заправщика, нагнетательный выход сообщен с указанным внутрисамолетным топливопроводом, а вход гидропривода сообщен с отводной магистралью подвесного агрегата заправки. 1. Aircraft refueling system of another aircraft, comprising a refueling suspension unit with an autonomous drive of an internal unit booster pump having a suction inlet communicated by an intra-unit pipe and an in-flight fuel line with a fuel compartment of a refueling aircraft, and a discharge outlet communicated by an in-line discharge line of the hose unit , and a branch line connecting the in-line discharge line with the fuel compartment of the refueling aircraft, schayasya in that the system is provided with a hydraulically driven pump, wherein the suction port is located in the fuel compartment of the tanker aircraft, the discharge outlet communicated with said vnutrisamoletnym fuel line, and the input hydraulic drive communicates with discharge manifold outboard refueling unit. 2. Система по п.1, отличающаяся тем, что нагнетательный выход гидроприводного насоса сообщен с указанным внутрисамолетным топливопроводом через магистраль топливопитания маршевого двигателя самолета-заправщика, а выход гидропривода этого же насоса сообщен с расходным отсеком топливной системы самолета-заправщика. 2. The system according to claim 1, characterized in that the discharge output of the hydraulic drive pump is in communication with the indicated in-flight fuel line through the fuel supply line of the main engine of the refueling aircraft, and the hydraulic output of the same pump is communicated with the consumable compartment of the fuel system of the refueling aircraft.
RU97120800A 1997-12-10 1997-12-10 Aircraft system for refuelling receiver aircraft RU2140381C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU97120800A RU2140381C1 (en) 1997-12-10 1997-12-10 Aircraft system for refuelling receiver aircraft

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Application Number Priority Date Filing Date Title
RU97120800A RU2140381C1 (en) 1997-12-10 1997-12-10 Aircraft system for refuelling receiver aircraft

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RU97120800A RU97120800A (en) 1999-09-27
RU2140381C1 true RU2140381C1 (en) 1999-10-27

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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7188807B2 (en) 2005-03-11 2007-03-13 The Boeing Company Refueling booms with multiple couplings and associated methods and systems
US7213787B2 (en) 2005-06-07 2007-05-08 The Boeing Company Valves for annular conduits including aircraft fuel conduits and associated systems and methods
US7219857B2 (en) 2005-06-20 2007-05-22 The Boeing Company Controllable refueling drogues and associated systems and methods
US7293741B2 (en) 2005-06-09 2007-11-13 The Boeing Company System and methods for distributing loads from fluid conduits, including aircraft fuel conduits
US7309047B2 (en) 2005-02-25 2007-12-18 The Boeing Company Systems and methods for controlling flexible communication links used for aircraft refueling
US7458543B2 (en) 2005-06-10 2008-12-02 The Boeing Company Aerial refueling system
US7469863B1 (en) 2005-03-24 2008-12-30 The Boeing Company Systems and methods for automatically and semiautomatically controlling aircraft refueling
US7472868B2 (en) 2005-09-01 2009-01-06 The Boeing Company Systems and methods for controlling an aerial refueling device
US7533850B2 (en) 2005-06-09 2009-05-19 The Boeing Company Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems
US7581700B2 (en) 2005-06-09 2009-09-01 The Boeing Company Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods
US7637458B2 (en) 2005-06-08 2009-12-29 The Boeing Company Systems and methods for providing back-up hydraulic power for aircraft, including tanker aircraft
RU2514978C1 (en) * 2012-11-15 2014-05-10 Открытое акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" Buddy-refuelling unit control system
RU2667984C1 (en) * 2017-10-26 2018-09-25 Акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" System and method for speed control of hose retraction-extension on suspension refueling units
RU2798950C1 (en) * 2022-08-10 2023-06-29 Акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" Suspended in-flight fueling unit

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Лещинер Л.Б. и др. Топливные системы современных самолетов. - М.: Военное издательство Министерства обороны СССР, 1964, с.190-195. *

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7309047B2 (en) 2005-02-25 2007-12-18 The Boeing Company Systems and methods for controlling flexible communication links used for aircraft refueling
US7188807B2 (en) 2005-03-11 2007-03-13 The Boeing Company Refueling booms with multiple couplings and associated methods and systems
US7469863B1 (en) 2005-03-24 2008-12-30 The Boeing Company Systems and methods for automatically and semiautomatically controlling aircraft refueling
US7213787B2 (en) 2005-06-07 2007-05-08 The Boeing Company Valves for annular conduits including aircraft fuel conduits and associated systems and methods
US7637458B2 (en) 2005-06-08 2009-12-29 The Boeing Company Systems and methods for providing back-up hydraulic power for aircraft, including tanker aircraft
US7533850B2 (en) 2005-06-09 2009-05-19 The Boeing Company Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems
US8356842B2 (en) 2005-06-09 2013-01-22 Carns James A Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems
US7946038B2 (en) 2005-06-09 2011-05-24 The Boeing Company Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods
US7293741B2 (en) 2005-06-09 2007-11-13 The Boeing Company System and methods for distributing loads from fluid conduits, including aircraft fuel conduits
US7581700B2 (en) 2005-06-09 2009-09-01 The Boeing Company Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods
US7922122B2 (en) * 2005-06-09 2011-04-12 The Boeing Company Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits
US7665479B2 (en) 2005-06-10 2010-02-23 The Boeing Company Aerial refueling system
US7458543B2 (en) 2005-06-10 2008-12-02 The Boeing Company Aerial refueling system
US7887010B2 (en) 2005-06-20 2011-02-15 The Boeing Company Controllable refueling drogues and associated systems and methods
US7219857B2 (en) 2005-06-20 2007-05-22 The Boeing Company Controllable refueling drogues and associated systems and methods
US7472868B2 (en) 2005-09-01 2009-01-06 The Boeing Company Systems and methods for controlling an aerial refueling device
RU2514978C1 (en) * 2012-11-15 2014-05-10 Открытое акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" Buddy-refuelling unit control system
RU2667984C1 (en) * 2017-10-26 2018-09-25 Акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" System and method for speed control of hose retraction-extension on suspension refueling units
RU2798950C1 (en) * 2022-08-10 2023-06-29 Акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" Suspended in-flight fueling unit

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Effective date: 20130527