US3744738A - Zero gravity liquid transfer screen - Google Patents

Zero gravity liquid transfer screen Download PDF

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US3744738A
US3744738A US00180963A US3744738DA US3744738A US 3744738 A US3744738 A US 3744738A US 00180963 A US00180963 A US 00180963A US 3744738D A US3744738D A US 3744738DA US 3744738 A US3744738 A US 3744738A
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liquid
container
spiral shaped
shaped member
tank
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US00180963A
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F Howard
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National Aeronautics and Space Administration NASA
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/402—Propellant tanks; Feeding propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/008—Details of vessels or of the filling or discharging of vessels for use under microgravity conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C9/00—Methods or apparatus for discharging liquefied or solidified gases from vessels not under pressure

Definitions

  • a liquid transfer device for use in a zero gravity environment, such as outer space,for transferring liquid from one container to another.
  • the device includes a 244/1 gagggag spiral shaped screen type member which is carried in 58] g SS 135 the container for collecting the randomly dispersed liquid in the container and transferring such to an exit port.
  • This invention relates to a liquid transfer device for containers and the like, and in particular to a device which utilizes a spiral shaped screen for collecting and dispersing liquid from the container.
  • the main problem in transferring a liquid in outer space is that the liquid will separate into globules and float throughout the tank. While it is possible to accelerate and decelerate the container in order to collect and transfer the liquid, such is not practical in that it requires the use of the engines of the space vehicle and consumption of fuel for operating such.
  • This transfer screen includes the following basic parts: (I) A spiral shaped member carried in a container having a longitudinal axis in alignment with the exit port of the container from which the liquid is being carried, (2) constructing a spiral shaped member of a screen having a diameter corresponding to the internal diameter of the container, and (3) means for rotating the spiral shaped member so that the surface tension created between the liquid in the container and the spiral shaped member directs the liquid out an exit port.
  • the perforated screen is utilized so that when a back pressure is created greater than the pressure created by the spiral shaped member engaging the liquid, such allows the liquid to pass through the spiral shaped member, minimizing the back-pressure.
  • Another important object of the present invention is to provide a liquid transfer device which utilizes a lightweight perforated spiral shaped member for transferring the liquid from one container to another.
  • Another important object of the present invention is to provide a liquid transfer device which minimizes the pressure build-up in the container into which liquid is being transferred.
  • Another important object of the present invention is to provide a simple and lightweight liquid transfer device which collects randomly dispersed liquid carried in a tank and transfers such out an outlet port of the tank.
  • Still another important object of the present invention is to provide a liquid transfer device which adds very little heat to the liquid being transferred, minimizes the amount of venting required during transfer, and rapidly evacuates the tank.
  • FIG. 1 is a perspective view illustrating a space vehicle in outer space coupled to a transfer tank provided with a zero gravity liquid transfer screen constructed in accordance with the present invention
  • FIG. 2 is a perspective view with parts broken away to show the interior of the tank, illustrating a tank equipped with a zero gravity liquid transfer screen transferring liquid into another tank,
  • FIG. 3 is a transverse sectional view taken along lines 3-3 in FIG. 2 illustrating a support for the liquid transfer screen of FIG. 2, and
  • FIG. 4 is a longitudinal sectional view illustrating a modified form of the liquid transfer screen.
  • FIG. 1 illustrates a space vehicle, generally designated by the reference character 10, located in outer space docked with a refueling container 12 provided with a spiral shaped member 14 which collects the fuel in the container l2 and transfers such through a transfer pipe 16 into a tank shown by the reference character 18 associated with the space vehicle.
  • the space vehicle and the refueling container are provided with conventional coupling mechanisms (not shown) for maintaining such in fixed relation relative to each other during the fuel transfer operation.
  • the refueling container 12, illustrated in FIG. 1 is shown partially empty with the fuel 20 taking the form of globules, such as occurs when the tank is partially evacuated of fuel and is located in a zero gravity environment, such as outer space. By rotating the spiral shaped member such collects the randomly dispersed globules in the tank 12 and forces them out of the transfer pipe 16.
  • the spiral shaped member 14 is constructed of a material having small perforations, and in one particular embodiment consist of woven stainless steel wire.
  • the size of the perforations in the screen and the speed of rotation of the screen may vary according to the type liquid being transferred.
  • One suitable screen is constructed of 0.025 inch diameter woven stainless steel wire using ten strands of wire per linear inch.
  • Such pro of the tank in alignment with the longitudinal axis thereof.
  • the bearing 24 which supports the end of the rod 22 adjacent an exit port 26 of the tank is supported in a spoke circular collar 28.
  • the collar 28 is suitably mounted in the throat of the tank 12. In FIG. 1 the throat takes the form of a transfer pipe 16, while in FIG. 2 the throat is tubular in shape.
  • the 4 utilizes a frustoconical shaped throat 30.
  • the other end of the rod 22 is attached to a rotating shaft of an electric motor 32 carried adjacent the end of the tank.
  • the motor 32 may be powered by self-contained batteries, or in some applications plugged into a source of energy carried by the space vehicle which is being refueled.
  • a metal band 34 runs along the outer edge 'of the screen 14 for adding rigidity thereto.
  • Other suitable reinforcing members could be utilized if desired.
  • the diameter of the spiral shaped screen is substantially equal to the internal diameter of the tank 12 so that when such is rotated substantially all of the liquid globules in the tank are collected and moved to and out of the throat 30 of the tank. Since the perforations in the spiral shaped screen 14 are small, the overall surface area of the screen is large. When this large surface area contacts the liquid as the screen rotates, the surface tension and frictional forces therebetween cause the liquid to be set in motion and move out through the throat or exit port 30. In a zero gravity environment, these surface tension and frictional forces are substantial enough to impart the motion of the liquid needed to dispense it from the tank.
  • vent the receiving tank in some instances it may be desirable to vent the receiving tank, and such is accomplished by running a vent tube 36 from the receiving tank 18 back to the far end of the sending tank 12. Normally, however, the venting tube can be eliminated since the liquid is being moved by a perforated screen which in'itself allows a back-flow of pressure therethrough if the back pressure created during transfer exceeds the surface tension forces produced by the rotating spiral shaped member moving the liquid into the receiving tank.
  • a frusto-conical shaped spout 30 is provided on the end of the sending tank 12 which extends into the receiving tank 38.
  • the rod 22 is extended to the end of the spout.
  • the spiral shaped member 14 has a tapering portion 40 which extends from adjacent the spoke collar 28 to the end of the spout 30, and has a 7 diameter corresponding to the inner diameter of the spout. It is desirable both in the main sending tank and in the spout 30 to minimize the space between the spiral shaped screens 14 and 40, and the inner wall of the sending tank 12 so as to insure complete collection of the liquid being transferred from the sending tank.
  • a device for transferring liquid from said container through an exit port provided therein comprising:
  • said spiral shaped member being constructed of a material having small perforations therein normally capable of imparting a motion to said liquid by surface tension and frictional forces created therebetween when said material contacts said liquid;
  • said material being constructed so as to permit the passage of said liquid through said small perforations if the pressure buildup created by said spiral shaped member engaging said liquid becomes greater than said surface tension and frictional forces, thereby minimizing undesirable back pressures in said container.
  • said material consists of a woven metallic wire defining a perforated screen.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Loading And Unloading Of Fuel Tanks Or Ships (AREA)

Abstract

A liquid transfer device for use in a zero gravity environment, such as outer space, for transferring liquid from one container to another. The device includes a spiral shaped screen type member which is carried in the container for collecting the randomly dispersed liquid in the container and transferring such to an exit port.

Description

O Umted States Patent 1191 [111 3,744,738 Howard I July 10, 1973 ZERO GRAVITY L lQUlD TRANSFER [56] References Cited SCREEN UNITED STATES PATENTS [75] Inventor: Frank S. Howard, lndian Harbor 3,093,271 6/ I963 Douglas 222/413 Beach, Fla. 2,617,273 11/1952 Findlay 198/213 X [73] Assgnee: 2 123:; i fi zgzg' as Primary Examiner-Robert B. Reeves tics y d 8 Assistant Examiner-Larry Martin 339? gg i D C Attorney-James O. HarrelLJohn R. Manning et al.
9 a [22] Filed: Sept. 16, 1971 [57] ABSTRACT [21] Appl. No.: 180,963 A liquid transfer device for use in a zero gravity environment, such as outer space,for transferring liquid from one container to another. The device includes a 244/1 gagggag spiral shaped screen type member which is carried in 58] g SS 135 the container for collecting the randomly dispersed liquid in the container and transferring such to an exit port.
2 Claims, 4 Drawing Figures PAIENUEB JUL 1 0191s INVENTOR.
FRANK S. HOWARD ATTORNEK PAIEmmJm 3.744.738
sum 2 or 2 INVENTOR.
FRANK S. HOWARD 1:9 4 Q 1/ ATTORNEY.
ZERO GRAVITY LIQUID TRANSFER SCREEN This invention described herein was made by an employee of the United States Government, and may be manufactured and used by or for The Government for Govenrmental purposes without the payment of any royalties thereon or therefor.
This invention relates to a liquid transfer device for containers and the like, and in particular to a device which utilizes a spiral shaped screen for collecting and dispersing liquid from the container.
Heretofore, the transfer of liquid from one container to another has not been accomplished in a zero gravity environment except by use of a bladder. Bladders are not considered suitable for cryogenic liquids because of insufficient flexibility at cryogenic temperatures. Transfer can also be accomplished in a zero gravity environment where the container is being accelerated by rocket engines and the tank is being pressurized with gas to force the liquid out. However, this known pressurization technique will not work satisfactorily when the container is not experiencing acceleration because, without any gravitational or acceleration force, globules of the liquid would merely collect in various areas of the container and not be forced out by the inert gas.
Another disadvantage of utilizing inert gas to force the liquid from the container is that such added to the weight of the container due to the requirement of the storing of the inert gas. There also has to be some means of regulating the pressurized gas in order to prevent over pressurization of the containers.
Conventional pumps utilized on earth do not work satisfactory in outer space for the reason that generally they rely on gravity feed to the input of the pump. If such pumps were utilized in a zero gravity environment, globules of liquid would collect throughout the container preventing complete evacuation thereof.
The main problem in transferring a liquid in outer space is that the liquid will separate into globules and float throughout the tank. While it is possible to accelerate and decelerate the container in order to collect and transfer the liquid, such is not practical in that it requires the use of the engines of the space vehicle and consumption of fuel for operating such.
In accordance with the present invention, it has been found that difficulties encountered in transferring liquid from one container to another in outer space may be overcome by providing a novel zero gravity liquid transfer screen. This transfer screen, includes the following basic parts: (I) A spiral shaped member carried in a container having a longitudinal axis in alignment with the exit port of the container from which the liquid is being carried, (2) constructing a spiral shaped member of a screen having a diameter corresponding to the internal diameter of the container, and (3) means for rotating the spiral shaped member so that the surface tension created between the liquid in the container and the spiral shaped member directs the liquid out an exit port. The perforated screen is utilized so that when a back pressure is created greater than the pressure created by the spiral shaped member engaging the liquid, such allows the liquid to pass through the spiral shaped member, minimizing the back-pressure.
Accordingly, it is an important object of the present invention to provide a liquid transfer device for transferring liquid in a zero gravity environment, and in particular, outer space.
Another important object of the present invention is to provide a liquid transfer device which utilizes a lightweight perforated spiral shaped member for transferring the liquid from one container to another.
Another important object of the present invention is to provide a liquid transfer device which minimizes the pressure build-up in the container into which liquid is being transferred.
Another important object of the present invention is to provide a simple and lightweight liquid transfer device which collects randomly dispersed liquid carried in a tank and transfers such out an outlet port of the tank.
Still another important object of the present invention is to provide a liquid transfer device which adds very little heat to the liquid being transferred, minimizes the amount of venting required during transfer, and rapidly evacuates the tank.
Other objects and advantages of this invention will become more apparent from a reading of the following detailed description and appended claims taken in conjunction with the accompanying drawings wherein:
FIG. 1 is a perspective view illustrating a space vehicle in outer space coupled to a transfer tank provided with a zero gravity liquid transfer screen constructed in accordance with the present invention,
FIG. 2 is a perspective view with parts broken away to show the interior of the tank, illustrating a tank equipped with a zero gravity liquid transfer screen transferring liquid into another tank,
FIG. 3 is a transverse sectional view taken along lines 3-3 in FIG. 2 illustrating a support for the liquid transfer screen of FIG. 2, and
FIG. 4 is a longitudinal sectional view illustrating a modified form of the liquid transfer screen.
Referring in more detail to the drawings, FIG. 1 illustrates a space vehicle, generally designated by the reference character 10, located in outer space docked with a refueling container 12 provided with a spiral shaped member 14 which collects the fuel in the container l2 and transfers such through a transfer pipe 16 into a tank shown by the reference character 18 associated with the space vehicle. The space vehicle and the refueling container are provided with conventional coupling mechanisms (not shown) for maintaining such in fixed relation relative to each other during the fuel transfer operation. The refueling container 12, illustrated in FIG. 1, is shown partially empty with the fuel 20 taking the form of globules, such as occurs when the tank is partially evacuated of fuel and is located in a zero gravity environment, such as outer space. By rotating the spiral shaped member such collects the randomly dispersed globules in the tank 12 and forces them out of the transfer pipe 16.
The spiral shaped member 14 is constructed of a material having small perforations, and in one particular embodiment consist of woven stainless steel wire. The size of the perforations in the screen and the speed of rotation of the screen may vary according to the type liquid being transferred. One suitable screen is constructed of 0.025 inch diameter woven stainless steel wire using ten strands of wire per linear inch. Such pro of the tank in alignment with the longitudinal axis thereof. The bearing 24 which supports the end of the rod 22 adjacent an exit port 26 of the tank is supported in a spoke circular collar 28. The collar 28 is suitably mounted in the throat of the tank 12. In FIG. 1 the throat takes the form of a transfer pipe 16, while in FIG. 2 the throat is tubular in shape. The modified form of the invention illustrated in FIG. 4 utilizes a frustoconical shaped throat 30. The other end of the rod 22 is attached to a rotating shaft of an electric motor 32 carried adjacent the end of the tank. The motor 32 may be powered by self-contained batteries, or in some applications plugged into a source of energy carried by the space vehicle which is being refueled.
A metal band 34 runs along the outer edge 'of the screen 14 for adding rigidity thereto. Other suitable reinforcing members could be utilized if desired. The diameter of the spiral shaped screen is substantially equal to the internal diameter of the tank 12 so that when such is rotated substantially all of the liquid globules in the tank are collected and moved to and out of the throat 30 of the tank. Since the perforations in the spiral shaped screen 14 are small, the overall surface area of the screen is large. When this large surface area contacts the liquid as the screen rotates, the surface tension and frictional forces therebetween cause the liquid to be set in motion and move out through the throat or exit port 30. In a zero gravity environment, these surface tension and frictional forces are substantial enough to impart the motion of the liquid needed to dispense it from the tank. If, however, a back-pressure is created by the liquid being transferred will overcome the surface tension and frictional forces, the screen rotating too fast or a restriction in the flow through the throat 30, the and pass through the perforations in screen, minimizing a pressure build-up. Another advantage of utilizing a spiral shaped screen is that the liquid transfer is accomplished with a minimum addition of hardware weight to the liquid transfer system and tank 12.
Referring again to FIG. 1, in some instances it may be desirable to vent the receiving tank, and such is accomplished by running a vent tube 36 from the receiving tank 18 back to the far end of the sending tank 12. Normally, however, the venting tube can be eliminated since the liquid is being moved by a perforated screen which in'itself allows a back-flow of pressure therethrough if the back pressure created during transfer exceeds the surface tension forces produced by the rotating spiral shaped member moving the liquid into the receiving tank.
In FIG. 4 as previously mentioned, a frusto-conical shaped spout 30 is provided on the end of the sending tank 12 which extends into the receiving tank 38. In order to prevent the liquid from being transferred from collecting in the spout 30 the rod 22 is extended to the end of the spout. The spiral shaped member 14 has a tapering portion 40 which extends from adjacent the spoke collar 28 to the end of the spout 30, and has a 7 diameter corresponding to the inner diameter of the spout. It is desirable both in the main sending tank and in the spout 30 to minimize the space between the spiral shaped screens 14 and 40, and the inner wall of the sending tank 12 so as to insure complete collection of the liquid being transferred from the sending tank.
Since it is not necessary to utilize a receiving tank 38 that is to be used in outer space structurally as strong as a tank that would be used on earth, it is important to be aware of the problem of possibly rupturing the receiving tank by over pressurization. In applicants device such is minimized since when there is a pressure build-up such is relieved by the liquid passing through the screen 14 as it is rotated.
While a preferred embodiment of the invention has been described using specific terms, such description is for illustrative purposes only, and it is to be understood that changes and variations may be made without departing from the spirit or scope of the following claims. It is also to be understood that the coupling mechanism between the sending tank 12 and the receiving tank 38 have not been shown for purposes of clarity, since such does not form a part of this invention.
Iclaim:
I. In combination with a liquid container in a zero gravity environment such as outer space, a device for transferring liquid from said container through an exit port provided therein, comprising:
A. a spiral shaped member rotatably mounted in said container along a longitudinal axis in alignment with said exit port;
B. said spiral shaped member being constructed of a material having small perforations therein normally capable of imparting a motion to said liquid by surface tension and frictional forces created therebetween when said material contacts said liquid;
C. means for rotating said spiral shaped member to impart said motion of said liquid to direct said liquid out through said exit port;
D. said material being constructed so as to permit the passage of said liquid through said small perforations if the pressure buildup created by said spiral shaped member engaging said liquid becomes greater than said surface tension and frictional forces, thereby minimizing undesirable back pressures in said container.
2. The device as set forth in claim 1 wherein:
A. said material consists of a woven metallic wire defining a perforated screen.
i i t i 4

Claims (2)

1. In combination with a liquid container in a zero gravity environment such as outer space, a device for transferring liquid from said container through an exit port provided therein, comprising: A. a spiral shaped member rotatably mounted in said container along a longitudinal axis in alignment with said exit port; B. said spiral shaped member being constructed of a material having small perforations therein normally capable of imparting a motion to said liquid by surface tension and frictional forces created therebetween when said material contacts said liquid; C. means for rotating said spiral shaped member to impart said motion of said liquid to direct said liquid out through said exit port; D. said material being constructed so as to permit the passage of said liquid through said small perforations if the pressure buildup created by said spiral shaped member engaging said liquid becomes greater than said surface tension and frictional forces, thereby minimizing undesirable back pressures in said container.
2. The device as set forth in claim 1 wherein: A. said material consists of a woven metallic wire defining a perforated screen.
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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4168718A (en) * 1978-07-11 1979-09-25 Nasa Passive propellant system
US4397408A (en) * 1980-07-08 1983-08-09 Societe Europeenne De Propulsion Surface tension storage device with buffer-tank
US4553565A (en) * 1983-06-20 1985-11-19 Matra Liquid storage reservoir with capillary confinement
US4768541A (en) * 1986-11-03 1988-09-06 Martin Marietta Corporation Means of expelling parallel tanks to low residuals
US4848987A (en) * 1988-08-16 1989-07-18 Administrator, National Aeronautics And Space Administration Vortex motion phase separator for zero gravity liquid transfer
US5427334A (en) * 1993-09-17 1995-06-27 Martin Marieta Corporation Method for making nonmetallic pressure vessel with integral propellant management vane, and pressure vessel made by the method
US20070012821A1 (en) * 2004-08-11 2007-01-18 Buehler David B Launch vehicle crew escape system
US20070145194A1 (en) * 2005-12-22 2007-06-28 Behruzi Kei P Fuel tank with specialized tank outlet for spacecraft
EP1953445A1 (en) * 2007-02-03 2008-08-06 Astrium GmbH Tank for storing cryogenic fluids and storable fuels
US20080296395A1 (en) * 2005-12-22 2008-12-04 Webasto Ag Fuel Extraction System for an Auxiliary Heating Unit
US20090134170A1 (en) * 2005-09-17 2009-05-28 Kei Philipp Behruzi Propellant Tank for Cryogenic Liquids
US20090293729A1 (en) * 2008-06-03 2009-12-03 Astrium Gmbh Tank with a gas supply and extraction device for storing cryogenic liquid or fuel for spacecraft
US20100264275A1 (en) * 2009-04-16 2010-10-21 Kei Philipp Behruzi Bubble trap for a fuel tank in a spacecraft
US20140283936A1 (en) * 2011-10-18 2014-09-25 Astrium Sas Device for expelling/containing liquids for a spacecraft tank

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2617273A (en) * 1949-04-25 1952-11-11 Phillips Petroleum Co Continuous crystallization apparatus and process
US3093271A (en) * 1959-04-10 1963-06-11 H L Stoker Company Material-handling device

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2617273A (en) * 1949-04-25 1952-11-11 Phillips Petroleum Co Continuous crystallization apparatus and process
US3093271A (en) * 1959-04-10 1963-06-11 H L Stoker Company Material-handling device

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4168718A (en) * 1978-07-11 1979-09-25 Nasa Passive propellant system
US4397408A (en) * 1980-07-08 1983-08-09 Societe Europeenne De Propulsion Surface tension storage device with buffer-tank
US4553565A (en) * 1983-06-20 1985-11-19 Matra Liquid storage reservoir with capillary confinement
US4768541A (en) * 1986-11-03 1988-09-06 Martin Marietta Corporation Means of expelling parallel tanks to low residuals
US4848987A (en) * 1988-08-16 1989-07-18 Administrator, National Aeronautics And Space Administration Vortex motion phase separator for zero gravity liquid transfer
US5427334A (en) * 1993-09-17 1995-06-27 Martin Marieta Corporation Method for making nonmetallic pressure vessel with integral propellant management vane, and pressure vessel made by the method
US20070012821A1 (en) * 2004-08-11 2007-01-18 Buehler David B Launch vehicle crew escape system
US8381938B2 (en) 2005-09-17 2013-02-26 Astrium Gmbh Propellant tank for cryogenic liquids
US20090134170A1 (en) * 2005-09-17 2009-05-28 Kei Philipp Behruzi Propellant Tank for Cryogenic Liquids
US20080296395A1 (en) * 2005-12-22 2008-12-04 Webasto Ag Fuel Extraction System for an Auxiliary Heating Unit
US20070145194A1 (en) * 2005-12-22 2007-06-28 Behruzi Kei P Fuel tank with specialized tank outlet for spacecraft
US7621291B2 (en) * 2005-12-22 2009-11-24 Eads Space Transportation Gmbh Fuel tank with specialized tank outlet for spacecraft
JP2008189304A (en) * 2007-02-03 2008-08-21 Astrium Gmbh Cryogenic liquid and tank for storing storable fuel
US20080237099A1 (en) * 2007-02-03 2008-10-02 Kei Philipp Behruzi Tank with a gas extraction device for storing cryogenic liquid or fuel for spacecraft
DE102007005539B3 (en) * 2007-02-03 2008-08-14 Astrium Gmbh Tank for storage of cryogenic liquids or storable liquid fuels
US8048211B2 (en) 2007-02-03 2011-11-01 Astrium Gmbh Tank with a gas extraction device for storing cryogenic liquid or fuel for spacecraft
EP1953445A1 (en) * 2007-02-03 2008-08-06 Astrium GmbH Tank for storing cryogenic fluids and storable fuels
US20090293729A1 (en) * 2008-06-03 2009-12-03 Astrium Gmbh Tank with a gas supply and extraction device for storing cryogenic liquid or fuel for spacecraft
US8025721B2 (en) 2008-06-03 2011-09-27 Astrium Gmbh Tank with a gas supply and extraction device for storing cryogenic liquid or fuel for spacecraft
US20100264275A1 (en) * 2009-04-16 2010-10-21 Kei Philipp Behruzi Bubble trap for a fuel tank in a spacecraft
US8202357B2 (en) 2009-04-16 2012-06-19 Astrium Gmbh Bubble trap for a fuel tank in a spacecraft
US20140283936A1 (en) * 2011-10-18 2014-09-25 Astrium Sas Device for expelling/containing liquids for a spacecraft tank
US9517590B2 (en) * 2011-10-18 2016-12-13 Airbus Defence And Space Sas Device for expelling/containing liquids for a spacecraft tank

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