WO2016046485A1 - Procédé et système de circulation de carburant dans un aéronef - Google Patents
Procédé et système de circulation de carburant dans un aéronef Download PDFInfo
- Publication number
- WO2016046485A1 WO2016046485A1 PCT/FR2015/052532 FR2015052532W WO2016046485A1 WO 2016046485 A1 WO2016046485 A1 WO 2016046485A1 FR 2015052532 W FR2015052532 W FR 2015052532W WO 2016046485 A1 WO2016046485 A1 WO 2016046485A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- fuel
- aircraft
- pump
- diaphragm pump
- tank
- Prior art date
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 97
- 238000000034 method Methods 0.000 title claims abstract description 34
- 239000012528 membrane Substances 0.000 description 17
- 238000012423 maintenance Methods 0.000 description 7
- 238000006073 displacement reaction Methods 0.000 description 5
- 239000007788 liquid Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 3
- 230000015556 catabolic process Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000009835 boiling Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000010079 rubber tapping Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/14—Filling or emptying
- B64D37/20—Emptying systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/14—Filling or emptying
- B64D37/16—Filling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B43/00—Machines, pumps, or pumping installations having flexible working members
- F04B43/02—Machines, pumps, or pumping installations having flexible working members having plate-like flexible members, e.g. diaphragms
- F04B43/04—Pumps having electric drive
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- the present invention relates to a method and a fuel circulation system in an aircraft, such as an airplane for example.
- the refueling of an aircraft is an operation performed to set up the quantity of fuel required for a next flight from a pressure line from a truck (+/- 100 m 3 / h to 2, 5 bars). This operation is also called "Pressure refuel”.
- Fuel transfer is a necessary operation in aircraft if they have more than one tank.
- the quantity of tanks varies according to the aircraft manufacturer and the configuration of the model in question, and a dump sequence is imposed.
- the transfer of fuel can occur when filling the collector, also called “Scavenge", which is fed continuously and with a higher flow rate than the consumption of the engines.
- the objective is to maintain this 100% full collector and with an overflow in another tank to ensure good power of the engines, whatever the flight conditions of the aircraft in roll and / or pitch.
- the transfer of fuel can also occur either during the transfer of fuel between two tanks located on each side of the aircraft to restore the center of gravity in case of overconsumption of one of the engines, and / or stopping the one of the engines, and / or non-homogeneous filling of the aircraft's tanks, which would result in an imbalance of the aircraft from one side or the other, either during the eventual transfer of fuel from a rear tank, also called “AFT Tank”, and / or from a front tank, also called “FWD Tank”, and / or from a central tank, also called “CTR Tank”, to optimize the position of the center of gravity of the aircraft which influences the aerodynamic characteristics of the flight and therefore on the fuel consumption induced.
- AFT Tank a front tank
- CTR Tank central tank
- the fuel supply of the engines is carried out by a feed pump which sucks the fuel from the collector to send it to the engine.
- a feed pump which sucks the fuel from the collector to send it to the engine.
- rotary-type pumps such as turbopumps and / or volumetric pumps, for example, powered by electric or hydraulic energy, or in effect pumps.
- Venturi injectors powered by a driving pressure.
- turbopumps also known as centrifugal pumps
- the volute receives the moving part or rotor which is formed of the impeller, said impeller being in the form of a paddle wheel, mounted on a shaft.
- the rotor is driven by a driving machine which can be an electric or hydraulic or thermal motor or a turbine.
- This type of pump has many disadvantages. In fact, in general, this type of pump has a poor energy efficiency, of the order of 30 to 70%, a bulk and a significant weight, a significant wear of rotating parts inducing frequent maintenance and sensitivity. to the phenomenon of cavitation. Cavitation is a noisy phenomenon that can destroy a machine in minutes.
- the liquid inside a centrifugal pump does not have a uniform pressure. In particular, there are areas with depressions more or less accentuated.
- the pumped liquid is sufficiently close to its boiling point, that is to say from the point of passage from the liquid state to the gaseous state, it can happen that the pressure at these points falls below its vapor pressure, so that vapor bubbles are formed in the pump.
- cavitation phenomena are very disadvantageous for so-called "sensitive” equipment because they generate mechanical degradation of equipment, degradation of efficiency, noise and in some cases introduction of gas bubbles. which may be problematic for jet engines.
- the conditions that lead to cavitation are the type of fuel with a density specific to each fuel, a low atmospheric pressure, that is to say when the aircraft is at high altitude, a high temperature of the fluid which facilitates the transition from the liquid state to the gaseous state and a high fluid velocity.
- One of the aims of the invention is therefore to remedy these drawbacks by proposing a method and a fuel circulation system in an aircraft having a good performance, requiring reduced maintenance, and not being sensitive to the phenomenon of cavitation.
- a first embodiment consists in using the at least one diaphragm pump with its intake pipe connected to an external fuel supply source, and with its exhaust pipe connected to a tank of the aircraft for refueling.
- a second embodiment consists in using the at least one diaphragm pump with its intake pipe connected to a tank, and with its exhaust pipe connected to another tank of the aircraft for the transfer of fuel between said tanks.
- a third embodiment consists in using the at least one diaphragm pump with its intake pipe connected to a tank, and with its exhaust pipe connected to an engine of the aircraft for its fuel supply.
- a fourth embodiment consists in using the at least one diaphragm pump with its intake pipe connected to a tank, and with its pipe exhaust connected to an auxiliary power unit of the aircraft for its fuel supply.
- a fifth embodiment consists in using the at least one diaphragm pump with its intake pipe connected to a tank, and with its exhaust pipe connected to an external fuel receiving source for emptying the tank. .
- a fuel circulation system in a remarkable aircraft in that it comprises at least one undulating diaphragm pump capable of waving, under the action of actuating means, between two flanges to circulate said fuel enters an intake pipe of the pump to an exhaust pipe of the pump.
- reduced maintenance is obtained due to the absence of rotating parts in the diaphragm pump and a high tolerance to cavitation and pollution phenomena.
- the implementation of the fuel circulation system is facilitated since the diaphragm pump allows self-priming of the pump.
- the intake pipe of the diaphragm pump is connected to an external fuel supply source, and the exhaust pipe is connected to a tank of the aircraft for filling it with fuel.
- the intake pipe of the diaphragm pump is connected to a tank, and the exhaust pipe is connected to another tank of the aircraft for the transfer of fuel between said tanks.
- the intake pipe of the diaphragm pump is connected to a tank, and the exhaust pipe is connected to a motor of the aircraft for its fuel supply.
- the intake pipe of the diaphragm pump is connected to a tank, and the exhaust pipe is connected to an auxiliary power unit of the aircraft for its fuel supply.
- the inlet pipe of the diaphragm pump is connected to a tank, and whose exhaust pipe is connected to an external fuel receiving source for emptying the tank.
- FIG. 1 is a schematic representation of the method and the fuel circulation system according to the invention for filling the tanks of an aircraft
- FIG. 2 is a schematic representation of the method and the fuel circulation system according to the invention for the transfer of fuel from a first tank to a second tank of an aircraft,
- FIG. 3 is a schematic representation of the method and the fuel circulation system according to the invention for supplying fuel to the reactors of an aircraft
- FIG. 4 is a schematic representation of the method and the fuel circulation system according to the invention for supplying an auxiliary power unit (APU) of an aircraft,
- APU auxiliary power unit
- FIG. 5 is a schematic representation of the method and the fuel circulation system according to the invention for emptying the tanks of an aircraft
- FIG. 6 is a side view of a first alternative embodiment of the pump used in the method according to the invention.
- FIG. 7 is a side view of a second alternative embodiment of the pump implemented in the method according to the invention.
- FIG. 8 is a side view of a third alternative embodiment of the pump implemented in the method according to the invention.
- the invention relates to a method and a fuel circulation system in an aircraft.
- the method consists in using at least one undulating diaphragm pump (1) capable of waving, under the action of actuating means, between two flanges for circulating said fuel between an intake pipe of the pump (1) to an exhaust pipe of the pump.
- the fuel circulation system comprises at least one diaphragm pump (1).
- the diaphragm pump comprises a cylindrical pump body (2) delimiting a cylindrical chamber into which an intake pipe (4) and an exhaust pipe (5) coaxial with the pump body ( 2), an undulating membrane having a central opening and extending into the cylindrical chamber between a fixed lower flange and a fixed upper flange, said flanges extending into said cylindrical chamber.
- the undulating membrane has the shape of a disk having a circular central opening.
- the undulating membrane is obtained in a deformable material such as a silicone elastomer for example or the like.
- the thickness of the undulating membrane is increasing from its central portion to its peripheral edge, and the circular central opening has a diameter substantially equal to the internal diameter of the exhaust pipe (5).
- the lower flange is secured to the bottom wall of the body (2) of the pump (1) and the upper flange is able to be moved vertically to vary the displacement of the pump as it will be detailed later.
- the walls of the lower and upper flanges forming the right side of the membrane are convex.
- the pump (1) comprises rigid support means of the membrane between the lower and upper flanges. Said support means cooperate in particular with the peripheral edge of the membrane. These support means consist, for example, in an annular ring bearing the peripheral edge of the membrane.
- the pump (1) comprises means for actuating the undulating membrane cooperating with the support means of the latter.
- Said actuating means consist, for example, in an electromagnetic linear actuator and damping means which delimit the travel of the electromagnetic actuator.
- the electromagnetic actuator consists, in turn, in a movable cylindrical ring extending coaxially with the exhaust pipe (5) above the upper flange and to the right of an excitation motor.
- the excitation motor is constituted by an internal so-called fixed cylindrical armature and a so-called external fixed cylindrical armature carrying an annular coil and two annular permanent magnets extending above and respectively below the annular coil, said coil ring is connected to a power supply circuit.
- the supply circuit comprises, for example, at least one power amplifier and a signal generator.
- the lower end of the movable cylindrical ring is integral with an annular ring provided with a shoulder, and engaged with a connecting piece secured to the support ring of the undulating membrane.
- the connecting piece maintains the undulating membrane when the actuator is at rest in particular.
- the upper flange is secured to a carriage slidable vertically relative to the inner fixed armature to vary the displacement of said pump (1).
- Said carriage consists, for example, in a circular part having a central recess for the passage of the exhaust pipe (5) and holes in which extend guides integral with the internal fixed armature.
- the latter comprises a cooperating tapping with a screw extending into a hole made in the internal fixed armature.
- the screw consists of a tubular piece of circular cross section having a thread on its outer wall, in its lower part.
- the upper flange is integral with the underside of said carriage so that, by varying the position of said carriage along the vertical axis of revolution of the pump (1), it is possible to vary the displacement of the pump by according to the need of the intended application.
- the intake pipe (4) and / or the exhaust pipe (5) may comprise at least one filter.
- the pump according to the invention may advantageously comprise at least one sensor such as a pressure sensor and / or a temperature sensor and / or a fuel presence sensor.
- the information measured by these sensors may be transmitted to the power supply circuit which may include management means for regulating the flow rate as a function of said information by modifying the supply characteristics of the electromagnetic linear actuator in particular.
- the movable cylindrical ring is moved alternately downwards and upwards, driving the undulating membrane downwards and upwards respectively to the frequency supplying the electromagnetic linear actuator.
- the membrane propagates a wavefront which provides the displacement of the fuel present in the cylindrical chamber to the exhaust pipe (5).
- the fuel circulation system incorporates a positive displacement diaphragm pump (1) that uses the reciprocating membrane, in which the fuel is displaced by trapping a fixed amount of fuel, and forcing the unloading of the trapped volume by the exhaust pipe (5).
- the diaphragm pump (1) therefore has good suction properties.
- the only moving part with which the fuel is in contact in the pump is the elastomeric membrane. All mechanical and electrical components are isolated from fuel exposure. This makes it possible to minimize the risk of trapping foreign bodies and to maximize the reliability of the method and fuel circulation system according to the invention. System maintenance is reduced.
- the intake pipe (4) extends on the opposite side to the exhaust pipe (5), and coaxially with the latter.
- the admission duct
- vents (29) in the cylindrical pump body (2) for communicating the cylindrical chamber with the outside pump (1).
- said vents (29) consist of longitudinal slots uniformly distributed over the circumference of the cylindrical pump body (2) and extend over the entire height of the cylindrical chamber.
- the shape of the pump does not limit the invention, said pump body (2), the chamber and the membrane may have any shape, such as a parallelepiped shape for the pump body (2) and the chamber, and a rectangular shape for the membrane without departing from the scope of the invention.
- the bottom line lies in the advantageous use of a diaphragm pump in a fuel circulation process in an aircraft.
- the method according to the invention allows the fueling of at least one of the tanks (30) of an aircraft.
- the intake pipe (4) of the circulation pump diaphragm pump (1) is connected to an external fuel supply source, and the exhaust pipe (5) is connected to a reservoir (30) of the aircraft for refueling.
- the method makes it possible to transfer fuel between at least two tanks (30 of the aircraft)
- the intake pipe (4) of the circulating pump (1) of the circulation system is connected to a tank (30)
- the exhaust pipe (5) is connected to another tank (30) of the aircraft for the transfer of fuel between said tanks (30).
- the method also makes it possible to supply fuel to at least one of the engines (31) from at least one of the tanks (30).
- the inlet pipe (4) of the circulation pump diaphragm pump (1) is connected to a tank (30), and the exhaust pipe (5) is connected to a motor (31). of the aircraft for fuel supply.
- the method makes it possible to supply fuel to at least one auxiliary power unit (APU) from at least one of the tanks (30).
- the inlet pipe (4) of the circulation pump diaphragm pump (1) is connected to a tank (30), and the exhaust pipe (5) is connected to an auxiliary power unit (32) of the aircraft for fuel supply.
- the method according to the invention also makes it possible, with reference to FIG. 5, to empty at least one of the tanks (30).
- the inlet pipe (4) of the circulation pump diaphragm pump (1) is connected to a tank (30) and the exhaust pipe (5) is connected to a receiving source external fuel for draining the tank (30).
- the system may include as many diaphragm pumps (1) as different fuel flow operations to achieve.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
- Reciprocating Pumps (AREA)
- Separation Using Semi-Permeable Membranes (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2017516137A JP2017530049A (ja) | 2014-09-24 | 2015-09-22 | 航空機における燃料循環のための方法およびシステム |
RU2017109887A RU2683050C2 (ru) | 2014-09-24 | 2015-09-22 | Способ и система для осуществления циркуляции топлива в воздушном судне |
EP15778374.7A EP3198143A1 (fr) | 2014-09-24 | 2015-09-22 | Procédé et système de circulation de carburant dans un aéronef |
BR112017005962A BR112017005962A2 (pt) | 2014-09-24 | 2015-09-22 | processo e sistema para circulação de combustível em uma aeronave. |
CA2962011A CA2962011A1 (fr) | 2014-09-24 | 2015-09-22 | Procede et systeme de circulation de carburant dans un aeronef |
US15/512,961 US20170320587A1 (en) | 2014-09-24 | 2015-09-22 | Method And System For The Circulation Of Fuel In An Aircraft |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1458982A FR3026091B1 (fr) | 2014-09-24 | 2014-09-24 | Procede et systeme de circulation de carburant dans un aeronef |
FR1458982 | 2014-09-24 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2016046485A1 true WO2016046485A1 (fr) | 2016-03-31 |
Family
ID=52465469
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2015/052532 WO2016046485A1 (fr) | 2014-09-24 | 2015-09-22 | Procédé et système de circulation de carburant dans un aéronef |
Country Status (8)
Country | Link |
---|---|
US (1) | US20170320587A1 (fr) |
EP (1) | EP3198143A1 (fr) |
JP (1) | JP2017530049A (fr) |
BR (1) | BR112017005962A2 (fr) |
CA (1) | CA2962011A1 (fr) |
FR (1) | FR3026091B1 (fr) |
RU (1) | RU2683050C2 (fr) |
WO (1) | WO2016046485A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3082311A1 (fr) * | 2018-06-07 | 2019-12-13 | Airbus Operations | Procede et systeme d'acquisition de caracteristiques de carburant a bord d'un aeronef |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3050178B1 (fr) | 2016-04-13 | 2018-04-06 | Zodiac Aerotechnics | Collecteur de carburant pour reservoir d'un aeronef |
US11724799B2 (en) | 2021-09-17 | 2023-08-15 | Blended Wing Aircraft, Inc. | Aircraft having a controllable center of gravity and method of use |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR585187A (fr) * | 1923-10-19 | 1925-02-23 | Pompe d'alimentation auto-régulatrice | |
FR634537A (fr) * | 1927-05-17 | 1928-02-20 | Henri Et Maurice Farman Soc | Perfectionnements aux pompes à membrane déformable |
FR880481A (fr) * | 1941-11-22 | 1943-03-26 | Ets A Guiot | Pompe à membrane, à commande électrique, sur réservoir |
FR2891321A1 (fr) * | 2005-09-26 | 2007-03-30 | Inergy Automotive Systems Res | Pompe a membrane vibrante |
WO2010012887A1 (fr) * | 2008-08-01 | 2010-02-04 | Ams R&D Sas | Pompe a membrane ondulante de rendement ameliore |
WO2010012889A1 (fr) * | 2008-08-01 | 2010-02-04 | Ams R&D Sas | Pompe a membrane ondulante perfectionnee |
EP2708729A1 (fr) * | 2011-05-13 | 2014-03-19 | Mikuni Corporation | Dispositif de pompe à carburant haute pression |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0764391B2 (ja) * | 1986-10-11 | 1995-07-12 | 昭和飛行機工業株式会社 | 燃料給油車の給油制御装置 |
RU4733U1 (ru) * | 1996-03-29 | 1997-08-16 | Акционерное общество открытого типа "Московский вертолетный завод им.М.Л.Миля" | Топливная система вертолета |
RU2140379C1 (ru) * | 1997-12-10 | 1999-10-27 | Акционерное общество открытого типа "ОКБ Сухого" | Топливная система самолета |
US6371740B1 (en) * | 1999-05-11 | 2002-04-16 | Jansen's Aircraft Systems Controls, Inc. | Jet engine fuel delivery system with non-pulsating diaphragm fuel metering pump |
US8486261B2 (en) * | 2011-05-23 | 2013-07-16 | The Boeing Company | Fuel scavenge water removal system |
US9316157B2 (en) * | 2012-02-01 | 2016-04-19 | Hamilton Sundstrand Corporation | Fuel system for starting an APU using a hybrid pump arrangement |
-
2014
- 2014-09-24 FR FR1458982A patent/FR3026091B1/fr active Active
-
2015
- 2015-09-22 RU RU2017109887A patent/RU2683050C2/ru active
- 2015-09-22 BR BR112017005962A patent/BR112017005962A2/pt not_active Application Discontinuation
- 2015-09-22 WO PCT/FR2015/052532 patent/WO2016046485A1/fr active Application Filing
- 2015-09-22 JP JP2017516137A patent/JP2017530049A/ja active Pending
- 2015-09-22 CA CA2962011A patent/CA2962011A1/fr not_active Abandoned
- 2015-09-22 EP EP15778374.7A patent/EP3198143A1/fr not_active Withdrawn
- 2015-09-22 US US15/512,961 patent/US20170320587A1/en not_active Abandoned
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR585187A (fr) * | 1923-10-19 | 1925-02-23 | Pompe d'alimentation auto-régulatrice | |
FR634537A (fr) * | 1927-05-17 | 1928-02-20 | Henri Et Maurice Farman Soc | Perfectionnements aux pompes à membrane déformable |
FR880481A (fr) * | 1941-11-22 | 1943-03-26 | Ets A Guiot | Pompe à membrane, à commande électrique, sur réservoir |
FR2891321A1 (fr) * | 2005-09-26 | 2007-03-30 | Inergy Automotive Systems Res | Pompe a membrane vibrante |
WO2010012887A1 (fr) * | 2008-08-01 | 2010-02-04 | Ams R&D Sas | Pompe a membrane ondulante de rendement ameliore |
WO2010012889A1 (fr) * | 2008-08-01 | 2010-02-04 | Ams R&D Sas | Pompe a membrane ondulante perfectionnee |
EP2708729A1 (fr) * | 2011-05-13 | 2014-03-19 | Mikuni Corporation | Dispositif de pompe à carburant haute pression |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3082311A1 (fr) * | 2018-06-07 | 2019-12-13 | Airbus Operations | Procede et systeme d'acquisition de caracteristiques de carburant a bord d'un aeronef |
US11480113B2 (en) | 2018-06-07 | 2022-10-25 | Airbus Operations (S.A.S.) | Method and a system for characterizing the fuel on board an aircraft |
Also Published As
Publication number | Publication date |
---|---|
CA2962011A1 (fr) | 2016-03-31 |
JP2017530049A (ja) | 2017-10-12 |
RU2017109887A3 (fr) | 2018-10-24 |
BR112017005962A2 (pt) | 2017-12-19 |
FR3026091B1 (fr) | 2023-10-06 |
EP3198143A1 (fr) | 2017-08-02 |
RU2017109887A (ru) | 2018-10-24 |
RU2683050C2 (ru) | 2019-03-26 |
FR3026091A1 (fr) | 2016-03-25 |
US20170320587A1 (en) | 2017-11-09 |
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