EP2806204B1 - Tank for the separation of liquids in orbit - Google Patents

Tank for the separation of liquids in orbit Download PDF

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Publication number
EP2806204B1
EP2806204B1 EP13002659.4A EP13002659A EP2806204B1 EP 2806204 B1 EP2806204 B1 EP 2806204B1 EP 13002659 A EP13002659 A EP 13002659A EP 2806204 B1 EP2806204 B1 EP 2806204B1
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EP
European Patent Office
Prior art keywords
tank
liquid
tank according
bodies
gas
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
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EP13002659.4A
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German (de)
French (fr)
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EP2806204A1 (en
Inventor
Dr. Kei Philipp Behruzi
Dr. Nicolas Fries
Burkhard Schmitz
Horst Köhler
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Airbus DS GmbH
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Astrium GmbH
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Classifications

    • 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
    • F17C11/00—Use of gas-solvents or gas-sorbents in vessels
    • 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
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/01—Shape
    • F17C2201/0104—Shape cylindrical
    • F17C2201/0119—Shape cylindrical with flat end-piece
    • 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
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/01—Shape
    • F17C2201/0147—Shape complex
    • F17C2201/0166—Shape complex divided in several chambers
    • 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
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/01—Shape
    • F17C2201/0147—Shape complex
    • F17C2201/0171—Shape complex comprising a communication hole between chambers
    • 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
    • F17C2201/00—Vessel construction, in particular geometry, arrangement or size
    • F17C2201/06—Vessel construction using filling material in contact with the handled fluid
    • 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
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
    • F17C2223/0146—Two-phase
    • F17C2223/0153—Liquefied gas, e.g. LPG, GPL
    • 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
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
    • F17C2223/0146—Two-phase
    • F17C2223/0153—Liquefied gas, e.g. LPG, GPL
    • F17C2223/0161—Liquefied gas, e.g. LPG, GPL cryogenic, e.g. LNG, GNL, PLNG
    • 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
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
    • F17C2227/01—Propulsion of the fluid
    • F17C2227/0192—Propulsion of the fluid by using a working fluid
    • 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
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
    • F17C2227/03—Heat exchange with the fluid
    • F17C2227/0302—Heat exchange with the fluid by heating
    • F17C2227/0304—Heat exchange with the fluid by heating using an electric heater
    • 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
    • F17C2227/00—Transfer of fluids, i.e. method or means for transferring the fluid; Heat exchange with the fluid
    • F17C2227/03—Heat exchange with the fluid
    • F17C2227/0367—Localisation of heat exchange
    • F17C2227/0369—Localisation of heat exchange in or on a vessel
    • F17C2227/0376—Localisation of heat exchange in or on a vessel in wall contact
    • F17C2227/0379—Localisation of heat exchange in or on a vessel in wall contact inside the vessel
    • 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
    • F17C2265/00—Effects achieved by gas storage or gas handling
    • F17C2265/03—Treating the boil-off
    • 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
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0186—Applications for fluid transport or storage in the air or in space
    • F17C2270/0194—Applications for fluid transport or storage in the air or in space for use under microgravity conditions, e.g. space

Definitions

  • the invention relates to a tank for separating a liquid from a gaseous phase and for storing the liquid separated from the gaseous phase for use in experiments in space under conditions of weightlessness, with a feed line through which a liquid, a gas or a mixture from both can be introduced into the tank, and with an outlet from the pure gas escapes.
  • the liquid introduced into such a tank which is generally referred to as a separator tank, is stored therein for the duration of a space experiment, the fuel metering being carried into this separator tank via an upstream tank.
  • a propellant usually an inert gas such as helium (He) or nitrogen (N 2 ), which is pressed under pressure into the upstream tank and in this way the liquid, the gas or a liquid Gas mixture through a piping system in the separator tank promotes.
  • a corresponding amount of gas is removed from the separator tank, these gases usually being discharged from the experiment module into the vacuum prevailing in orbit.
  • phase separators for the separation of a liquid from a gaseous phase has become known, wherein in this known device, a phase separator for operating states with low acceleration is used and the separation is carried out using superconducting magnets.
  • the describes US 48 48 987 A a phase separator in which pumps and a series of valves are provided.
  • a propeller which sets a liquid-gas mixture in rotation and in which a membrane of polyethylene or nylon, the liquid, in this case water, separated.
  • This latter known system is intended for use with fuel cells and is not suitable for separating cryogenic liquids.
  • US 44 35 196 A and the US 46 17 031 A Known devices are limited to use in the gravitational field of the earth.
  • a described arrangement is a porous bed structure in the form of a known Katalysatorbettn for generating gas from a liquid fuel, for example Hydrazine, provided.
  • a liquid / gas separator is described, in which a titanium mesh is arranged, which is intended to retain gas bubbles by the action of capillary forces and surface tension.
  • a diphasic cold gas propulsion system for a spacecraft as well as a suitable spherical tank known.
  • a lower portion of the tank has a porous structure which binds the two-phase fuel in its liquid phase by capillary forces. Via an outlet tube, the fuel can escape in gaseous phase.
  • a heating device is arranged, which heats the tank and thus also the fuel. As a result of the heating, the fuel in the upper region of the tank is in the superheated gaseous state and can escape through the outlet tube.
  • the invention has the object of providing such a tank in such a way that in a simple manner safe phase separation for both cryogenic and non-cryogenic propellants and liquids at accelerations, such as occur during a space experiment in a sounding rocket, is guaranteed and that the Once stored in this tank, liquid can not leave the tank through either the inlet or the outlet.
  • the invention solves this problem in that body are arranged in the tank of a spongy material in the form of a metal foam whose total pore volume is chosen to be greater than the volume of the liquid to be absorbed.
  • the formation of the tank according to the invention ensures that the liquid is absorbed capillary by the spongy material in the form of a metal foam and stored in this stable for the duration of the experiment.
  • the volume of the metal foam which is aluminum foam in a preferred embodiment of the tank according to the invention, is chosen larger than the volume of the total liquid to be absorbed according to the invention.
  • the liquid-gas mixture starting from the inlet opening, meandering guided by the acting as a separator tank tank according to the invention and thereby the liquid is discharged capillary into the sponge-like material.
  • a metal mesh In front of the outlet from the separator tank is a metal mesh, which prevents any particles of the sponge-like material that are being detached from undesirably entering the outlet opening.
  • the liquid is stored in this way in the serving as a reservoir tank, which may initially expelled in this tank located propellant gas and is replaced by the liquid.
  • the tank is inventively designed such that the liquid is stored in this due to the capillary action of the metal foam.
  • Metal foams are therefore also suitable for the type of storage of cryogenic liquids provided according to the invention, since they have a very low structural mass, so that only a small amount of structural mass has to be cooled by the liquid. Furthermore, the high capillary pressure of the metal foam has a positive effect, so that liquids can be safely held in the metal foam even at high interference accelerations. The storage capacity is reached when the bodies of metal foam are completely saturated with liquid.
  • the volume of the metal foam is dimensioned such that the maximum amount of liquid is less than the pore volume of the metal foam.
  • the invention is particularly well-suited for such space-saving experiments under weightlessness which require the use of cryogenic liquids.
  • a storage or test tank 3 is connected via a feed line 2 to a compressed gas tank 1.
  • the test tank 3 can be emptied, so that either liquid or gas is discharged from the test tank 3.
  • the liquid or gas is discharged via line 4 into a separator tank 5.
  • This separator tank 5 stores the introduced liquid and, via a line 6 and further via degassing lines 7, discharges the gas escaping from the separator tank 5.
  • the structure of the separator tank 5 is particularly made Fig. 2 seen. It consists of in the case of this embodiment, annular plate elements or bodies 8 made of a metal foam, wherein the metal foam in this case is aluminum. These bodies 8 are inserted into the separator tank 5, wherein the separator tank 5 is bounded by an upper 9 and a lower lid 10 and is enclosed by a cylindrical shell 11.
  • the outer shape of the separator tank 5 shown here serves only as an example and can generally be adapted to the geometric conditions in a spacecraft.
  • the in Fig. 3 illustrated in detail inlet region into the separator tank 5 consists of a supply line 12, which opens into a circumferential injection channel 13.
  • This injection channel 13 is connected in the direction of the cylindrical shell 11 through a gap 14 with the interior of the separator tank 5.
  • a sleeve 16 is arranged, which is located in front of the pore openings 17 in the body 8 made of metal foam.
  • a further sleeve 18 made of a metal fabric, which is connected to an outlet 19 of the separator tank 5 is connected.
  • This sleeve of metal fabric 18 has the function of a screen or filter cartridge, ie, any contamination downstream, not shown in the figures devices or valves by particles are avoided by this sleeve 18.
  • Fig. 5 the flow path 20 through the separator tank 5 is shown.
  • the separation of the liquid from the gas is carried out by the capillary penetration of the liquid 21 into the sponge-like body 8 made of metal foam, as in Fig. 6 is shown.
  • the liquid-impregnated region of the metal foam is in Fig. 6 indicated by a dashed area 22.
  • the lines 23 indicate the momentary boundary between the liquid (dashed area 22) and the gas (in the rest of the metal foam).
  • the flow direction of the liquid-gas mixture is indicated by the arrow 24.
  • the cross section 20 between the individual metal foam bodies is adjusted accordingly. This cross section 20 between the individual metal foam bodies is getting wider in the flow direction 24. Accordingly, the recesses 15 in the sponge-like bodies 8 made of metal foam in the direction of the center of the Separatortanks 5 are always deeper, as can be seen from Figures 4 and 5.
  • the separator tank described above is suitable for both cryogenic and non-cryogenic liquids.
  • the representation according to Fig. 7 Finally shows an arrangement in which the separator tank 5 is used for cryogenic liquids. It is important that the temperature of the separator tank 5 is close to the liquid temperature. Therefore, in this case, the separator tank 5 is disposed together with the test container 3 inside a cryostat 25 in which heaters 26 are further provided. Finally, a gas supply device 27 and a gas sampling device 28 are shown schematically in this figure.
  • the separator tank 5 is initially filled with liquid, the temperature of which can be adjusted by presetting a pressure which is predetermined according to the saturation curve. The liquid then evaporates over time, so that the separator tank 5 assumes cryogenic temperatures at the beginning of the actual use. When the liquid has completely evaporated, the separator can be used. To accelerate the evaporation process, a heating device 26 is additionally provided, which serves to prepare the separator tank 5.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Description

Die Erfindung betrifft einen Tank zur Trennung einer flüssigen von einer gasförmigen Phase und zur Lagerung der aus der gasförmigen Phase abgetrennten Flüssigkeit für einen Einsatz bei Experimenten im Weltraum unter den Bedingungen der Schwerelosigkeit, mit einer Zuleitung, durch die eine Flüssigkeit, ein Gas oder ein Gemisch aus beiden in den Tank einleitbar ist, und mit einem Auslass, aus dem reines Gas austritt.The invention relates to a tank for separating a liquid from a gaseous phase and for storing the liquid separated from the gaseous phase for use in experiments in space under conditions of weightlessness, with a feed line through which a liquid, a gas or a mixture from both can be introduced into the tank, and with an outlet from the pure gas escapes.

Die in einen solchen Tank, der im Allgemeinen als Separatortank bezeichnet wird, eingebrachte Flüssigkeit wird darin für die Dauer eines Weltraumexperimentes gelagert, wobei die Treibstoffzuhr in diesen Separatortank über einen vorgeschalteten Tank erfolgt. Zur Förderung der im vorgeschalteten Tank enthaltenen Flüssigkeit dient ein Treibgas, üblicherweise ein Inertgas wie Helium (He) oder Stickstoff (N2), das unter Druck in den vorgeschalteten Tank gepreßt wird und das auf diese Weise die Flüssigkeit, das Gas oder ein Flüssigkeits-Gas-Gemisch durch ein Rohrleitungssystem in den Separatortank fördert. Gleichzeitig wird aus dem Separatortank eine entsprechende Menge an Gas abgeführt, wobei diese Gase üblicherweise aus dem Experimentmodul in das im Orbit herrschende Vakuum entlassen werden. Wird jedoch bei diesem Vorgang ein Gas-Flüssigkeitsgemisch aus dem Tank in das Vakuum entlassen, so führen, je nach Mischungsverhältnis, die unterschiedlichen Dichten von Flüssigkeit und Gas zu einem nicht-konstanten Schubprofil, weshalb das Austreiben von Gemischen aus Flüssigkeit und Gas unerwünscht ist.The liquid introduced into such a tank, which is generally referred to as a separator tank, is stored therein for the duration of a space experiment, the fuel metering being carried into this separator tank via an upstream tank. To promote the liquid contained in the upstream tank is a propellant, usually an inert gas such as helium (He) or nitrogen (N 2 ), which is pressed under pressure into the upstream tank and in this way the liquid, the gas or a liquid Gas mixture through a piping system in the separator tank promotes. At the same time, a corresponding amount of gas is removed from the separator tank, these gases usually being discharged from the experiment module into the vacuum prevailing in orbit. However, if in this process a gas-liquid mixture is discharged from the tank into the vacuum, so lead, depending on the mixing ratio, the different densities of liquid and gas to a non-constant thrust profile, which is why the expulsion of mixtures of liquid and gas is undesirable.

Für eine sichere Trennung der Gas- und Flüssigkeitsphasen werden in der Raumfahrttechnik bisher die folgenden Verfahren angewandt:

  • Durch die Erwärmung des Treibstoffs wird die aus dem Treibstofftank austretende Flüssigkeit verdampft. Dieses Verfahren erfordert einen vergleichsweise hohen Energieaufwand für die Verdampfung der Flüssigkeit.
  • Es wird eine zusätzliche Beschleunigung aufgebracht, die bewirkt, dass sich der Treibstoff zum Zeitpunkt der Druckentlastung nicht am Gasauslaß befindet. Dies erfordert eine gerichtete Beschleunigung mittels eines zusätzlichen Antriebssystems, was im Falle eines Experimentes unter Schwerelosigkeit ausgeschlossen ist, da es die Randbedingungen des Experimentes beeinträchtigen würde.
For a safe separation of the gas and liquid phases, the following methods have been used in space technology so far:
  • The heating of the fuel vaporizes the liquid leaving the fuel tank. This Method requires a relatively high energy expenditure for the evaporation of the liquid.
  • An additional acceleration is applied, which causes the fuel at the time of depressurization is not located at the gas outlet. This requires a directional acceleration by means of an additional drive system, which is excluded in the case of an experiment in zero gravity, as it would affect the boundary conditions of the experiment.

Daneben ist aus der US 40 27 494 A die Verwendung von Phasenseparatoren zur Trennung einer flüssigen von einer gasförmigen Phase bekannt geworden, wobei in dieser bekannten Vorrichtung ein Phasenseparator für Betriebszustände mit geringer Beschleunigung zum Einsatz kommt und die Trennung unter Verwendung supraleitender Magnete erfolgt. Desweiteren beschreibt die US 48 48 987 A einen Phasenseparator, bei dem Pumpen und eine Reihe von Ventilen vorgesehen sind. Schließlich wird bei einem in der US 70 77 885 B2 beschriebenen Phasenseparator ein Propeller verwendet, der ein Flüssigkeits-Gasgemisch in Rotation versetzt und bei dem eine Membran aus Polyethylen oder Nylon die Flüssigkeit, in diesem Fall Wasser, abtrennt. Dieses letztgenannte bekannte System ist für einen Einsatz zusammen mit Brennstoffzellen vorgesehen und eignet sich nicht zur Trennung kryogener Flüssigkeiten. Weitere, aus der US 44 35 196 A und der US 46 17 031 A bekannt gewordene Vorrichtungen sind auf einen Einsatz im Schwerefeld der Erde beschränkt.Besides that is from the US 40 27 494 A the use of phase separators for the separation of a liquid from a gaseous phase has become known, wherein in this known device, a phase separator for operating states with low acceleration is used and the separation is carried out using superconducting magnets. Furthermore, the describes US 48 48 987 A a phase separator in which pumps and a series of valves are provided. Finally, at one in the US 70 77 885 B2 described phase separator used a propeller, which sets a liquid-gas mixture in rotation and in which a membrane of polyethylene or nylon, the liquid, in this case water, separated. This latter known system is intended for use with fuel cells and is not suitable for separating cryogenic liquids. Further, from the US 44 35 196 A and the US 46 17 031 A Known devices are limited to use in the gravitational field of the earth.

Weiterhin ist in der US 40 27 494 A eine Anordnung beschrieben, bei der reine, von etwaigen Gasbeimischungen gereinigte Flüssigkeit gefördert wird, weshalb bei dieser bekannten Anordnung eine wabenartige Struktur direkt über einem enstprechenden Auslass angeordnet ist Dadurch wird sichergestellt, dass kein Gas in die entsprechende Auslassleitung gelangt.Furthermore, in the US 40 27 494 A describes an arrangement in which pure, purified from any gas admixtures liquid is conveyed, which is why in this known arrangement, a honeycomb-like structure is disposed directly above a corresponding outlet This ensures that no gas enters the corresponding outlet.

Bei einer in der US 44 35196 A beschriebenen Anordnung ist eine poröse Bettstruktur in Form eines an sich bekannten Katalysatorbettn zur Erzeugung von Gas aus einem flüssigen Treibstoff, beispielsweise Hydrazin, vorgesehen. Zudem ist in dieser Druckschrift ein Flüssigkeits/Gas-Separator beschrieben, in dem ein Titannetz angeordnet ist, das dazu dienen soll, durch die Wirkung von Kapillarkräften und Oberflächenspannung Gasblasen zurückzuhalten.At one in the US 44 35196 A described arrangement is a porous bed structure in the form of a known Katalysatorbettn for generating gas from a liquid fuel, for example Hydrazine, provided. In addition, in this document, a liquid / gas separator is described, in which a titanium mesh is arranged, which is intended to retain gas bubbles by the action of capillary forces and surface tension.

Aus der DE 10 2007 005 539 B3 ist eine Anordnung der eingangs genannten Art bekannt geworden, bei der ein Separator als Bauteil in einem Treibstofftank angeordnet ist, wobei ein Flüssigkeits-Gas-Gemisch an verschiedenen Stellen des Treibstofftanks ein für die Lagerung vorgesehenes Reservoir erreichen kann.From the DE 10 2007 005 539 B3 an arrangement of the aforementioned type has become known, in which a separator is arranged as a component in a fuel tank, wherein a liquid-gas mixture can reach a reservoir provided for storage at different points of the fuel tank.

Schließlich ist aus der WO 2006/106204 A2 ein diphasisches Kaltgasantriebssystem für ein Raumfahrzeug, sowie ein dafür geeignetes sphärischer Tank bekannt. Ein unterer Bereich des Tanks weist eine poröse Struktur auf, welche den zweiphasigen Treibstoff in seiner flüssigen Phase durch Kapillarkräfte bindet. Über ein Ausgangsrohr kann der Treibstoff in gasförmiger Phase entweichen. Im oberen Bereich des Tanks ist eine Heizeinrichtung angeordnet, die den Tank und somit auch der Treibstoff erwärmt. Durch die Erwärmung befindet sich der Treibstoff im oberen Bereich des Tanks im überhitzten gasförmigen Zustand und kann durch das Ausgangsrohr entweichen.Finally, out of the WO 2006/106204 A2 a diphasic cold gas propulsion system for a spacecraft, as well as a suitable spherical tank known. A lower portion of the tank has a porous structure which binds the two-phase fuel in its liquid phase by capillary forces. Via an outlet tube, the fuel can escape in gaseous phase. In the upper part of the tank, a heating device is arranged, which heats the tank and thus also the fuel. As a result of the heating, the fuel in the upper region of the tank is in the superheated gaseous state and can escape through the outlet tube.

Der Erfindung liegt die Aufgabe zugrunde, einen derartigen Tank so auszubilden, dass auf einfache Weise eine sichere Phasentrennung sowohl für kryogene als auch für nicht kryogene Treibstoffe und Flüssigkeiten bei Beschleunigungen, wie sie beispielsweise wahrend eines Weltraumexperimentes in einer Höhenforschungsrakete auftreten, gewährleistet ist und dass die einmal in diesem Tank gespeicherte Flüssigkeit den Tank weder durch den Ein- noch durch den Auslass wieder verlassen kann.The invention has the object of providing such a tank in such a way that in a simple manner safe phase separation for both cryogenic and non-cryogenic propellants and liquids at accelerations, such as occur during a space experiment in a sounding rocket, is guaranteed and that the Once stored in this tank, liquid can not leave the tank through either the inlet or the outlet.

Die Erfindung löst diese Aufgabe dadurch, dass in dem Tank Körper aus einem schwammartigen Material in Form eines Metallschaums angeordnet sind, deren Gesamtporenvolumen größer gewählt ist als das Volumen der aufzunehmenden Flüssigkeit.The invention solves this problem in that body are arranged in the tank of a spongy material in the form of a metal foam whose total pore volume is chosen to be greater than the volume of the liquid to be absorbed.

Durch die Ausbildung des Tanks gemäß der Erfindung wird erreicht, dass die Flüssigkeit kapillar von dem schwammartigen Material in Form eines Metallschaums aufgenommen und in diesem für die Dauer des Experimentes stabil gelagert wird.The formation of the tank according to the invention ensures that the liquid is absorbed capillary by the spongy material in the form of a metal foam and stored in this stable for the duration of the experiment.

Das Volumen des Metallschaums, bei dem es sich in einer bevorzugten Ausführungsform des erfindungsgemäßen Tanks um Aluminiumschaum handelt, ist gemäß der Erfindung größer gewählt als das Volumen der insgesamt aufzunehmenden Flüssigkeit. Das Flüssigkeits-Gas-Gemisch wird, ausgehend von der Eintrittsöffnung, mäandernd durch den als Separatortank wirkenden Tank nach der Erfindung geführt und dabei wird die Flüssigkeit kapillar in das schwammartige Material abgeführt. Vor dem Auslass aus dem Separatortank befindet sich ein Metallgewebe, das verhindert, dass etwaige sich ablösende Partikel des schwammartigen Materials unerwünscht mit in die Auslassöffnung gelangen.The volume of the metal foam, which is aluminum foam in a preferred embodiment of the tank according to the invention, is chosen larger than the volume of the total liquid to be absorbed according to the invention. The liquid-gas mixture, starting from the inlet opening, meandering guided by the acting as a separator tank tank according to the invention and thereby the liquid is discharged capillary into the sponge-like material. In front of the outlet from the separator tank is a metal mesh, which prevents any particles of the sponge-like material that are being detached from undesirably entering the outlet opening.

Die Flüssigkeit wird auf diese Weise in dem als Reservoir dienenden Tank zwischengespeichert, wobei sich unter Umständen zunächst in diesem Tank befindliches Treibgas ausgetrieben und durch die Flüssigkeit ersetzt wird. Der Tank ist dabei erfindungsgemäß derart ausgeführt, dass die Flüssigkeit aufgrund von der Kapillarwirkung des Metallschaums in diesem gespeichert wird. Metallschäume eignen sich auch deshalb zu der gemäß der Erfindung vorgesehenen Art der Lagerung kryogener Flüssigkeiten, da sie eine sehr geringe strukturelle Masse besitzen, so dass nur wenig strukturelle Masse durch die Flüssigkeit gekühlt werden muss. Weiter wirkt sich der hohe Kapillardruck des Metallschaums positiv aus, so dass Flüssigkeiten auch bei hohen Störbeschleunigungen sicher im Metallschaum gehalten werden können. Die Speicherkapazität ist dann erreicht, wenn die Körper aus Metallschaum vollständig mit Flüssigkeit getränkt sind. Aus diesem Grund ist erfindungsgemäß das Volumen des Metallschaumes so dimensioniert, dass die maximale Flüssigkeitsmenge geringer als das Porenvolumen des Metallschaumes ist. Die Erfindung eignet sich besonders gut für solche Weltraumexperimente unter Schwerelosigkeit, die den Einsatz kryogener Flüssigkeiten erfordern.The liquid is stored in this way in the serving as a reservoir tank, which may initially expelled in this tank located propellant gas and is replaced by the liquid. The tank is inventively designed such that the liquid is stored in this due to the capillary action of the metal foam. Metal foams are therefore also suitable for the type of storage of cryogenic liquids provided according to the invention, since they have a very low structural mass, so that only a small amount of structural mass has to be cooled by the liquid. Furthermore, the high capillary pressure of the metal foam has a positive effect, so that liquids can be safely held in the metal foam even at high interference accelerations. The storage capacity is reached when the bodies of metal foam are completely saturated with liquid. For this reason, according to the invention, the volume of the metal foam is dimensioned such that the maximum amount of liquid is less than the pore volume of the metal foam. The invention is particularly well-suited for such space-saving experiments under weightlessness which require the use of cryogenic liquids.

Nachfolgend soll die Erfindung anhand von in der Zeichnung dargestellten Ausführungsbeispielen näher erläutert werden. Es zeigen:

Fig. 1
einen typischen Aufbau einer Tankanordnung für ein Weltraumexperiment mit einem Vorrats- und einem Separatortank in schematischer Darstellung,
Fig. 2
einen Schnitt durch den Separatortank gemäß Fig. 1,
Fig. 3
einen Schnitt durch ein Detail des Separatortanks gemäß Fig. 2,
Fig. 4
weitere Details des Separatortanks gemäß Fig. 2 in perspektivischer Darstellung,
Fig. 5
eine Darstellung des Strömungsverlaufs durch den Separatortank gemäß Fig. 2,
Fig. 6
eine Prinzipdarstellung der Separation der Flüssigkeit vom Gas in einem Separatortank gemäß Fig. 2 und
Fig. 7
eine schematische Darstellung einer Anordnung mit einem Separatortank und einem Testtank für eine Verwendung kryogener Flüssigkeiten.
The invention will be explained in more detail with reference to embodiments illustrated in the drawings. Show it:
Fig. 1
a typical construction of a tank arrangement for a space experiment with a storage tank and a separator tank in a schematic representation,
Fig. 2
a section through the separator tank according to Fig. 1 .
Fig. 3
a section through a detail of the separator tank according to Fig. 2 .
Fig. 4
Further details of the separator tank according to Fig. 2 in perspective,
Fig. 5
a representation of the flow path through the separator tank according to Fig. 2 .
Fig. 6
a schematic representation of the separation of the liquid from the gas in a separator tank according to Fig. 2 and
Fig. 7
a schematic representation of an arrangement with a separator tank and a test tank for use of cryogenic liquids.

In den Figuren sind gleiche bzw. einander entsprechende Bauteile mit den gleichen Bezugszeichen versehen.In the figures, the same or corresponding components are provided with the same reference numerals.

Bei der in Fig. 1 dargestellten Anordnung handelt es sich um eine typische Tankanordnung für ein Weltraumexperiment. Dabei ist ein Vorrats- oder Testtank 3 über eine Zuführleitung 2 mit einem Druckgastank 1 verbunden. Mithilfe des Druckgases kann der Testtank 3 entleert werden, so dass entweder Flüssigkeit oder Gas aus dem Testtank 3 abgeführt wird. Die Flüssigkeit oder das Gas werden über die Leitung 4 in einen Separatortank 5 abgeleitet. Dieser Separatortank 5 speichert die eingeleitete Flüssigkeit und führt über eine Leitung 6 und weiter über Entgasungsleitungen 7 das aus dem Separatortank 5 entweichende Gas ab.At the in Fig. 1 The arrangement shown is a typical tank arrangement for a space experiment. In this case, a storage or test tank 3 is connected via a feed line 2 to a compressed gas tank 1. By means of the compressed gas, the test tank 3 can be emptied, so that either liquid or gas is discharged from the test tank 3. The liquid or gas is discharged via line 4 into a separator tank 5. This separator tank 5 stores the introduced liquid and, via a line 6 and further via degassing lines 7, discharges the gas escaping from the separator tank 5.

Der Aufbau des Separatortanks 5 wird insbesondere aus Fig. 2 ersichtlich. Er besteht aus im Fall dieses Ausführungsbeispiels ringförmigen Plattenelementen oder Körpern 8 aus einem Metallschaum, wobei es sich bei dem Metallschaum in diesem Fall um Aluminium handelt. Diese Körper 8 sind in den Separatortank 5 eingesetzt, wobei der Separatortank 5 durch je einen oberen 9 und einen unteren Deckel 10 begrenzt ist und von einem zylindrischen Mantel 11 umschlossen ist. Die hier dargestellte äußere Form des Separatortanks 5 dient dabei nur als Beispiel und kann generell an die geometrischen Verhältnisse in einem Raumflugkörper angepasst werden.The structure of the separator tank 5 is particularly made Fig. 2 seen. It consists of in the case of this embodiment, annular plate elements or bodies 8 made of a metal foam, wherein the metal foam in this case is aluminum. These bodies 8 are inserted into the separator tank 5, wherein the separator tank 5 is bounded by an upper 9 and a lower lid 10 and is enclosed by a cylindrical shell 11. The outer shape of the separator tank 5 shown here serves only as an example and can generally be adapted to the geometric conditions in a spacecraft.

Der in Fig. 3 im Detail dargestellte Einlaufbereich in den Separatortank 5 besteht aus einer Zuführleitung 12, die in einen umlaufenden Einspritzkanal 13 mündet. Dieser Einspritzkanal 13 ist in Richtung des zylindrischen Mantels 11 durch einen Spalt 14 mit dem Inneren des Separatortanks 5 verbunden.The in Fig. 3 illustrated in detail inlet region into the separator tank 5 consists of a supply line 12, which opens into a circumferential injection channel 13. This injection channel 13 is connected in the direction of the cylindrical shell 11 through a gap 14 with the interior of the separator tank 5.

In die Körper 8 aus Metallschaum sind, von Körper zu Körper alternierend, im Bereich des unteren 10 und oberen Deckels 9 Ausnehmungen 15 eingebracht, wie dies aus Fig. 4 ersichtlich ist. Die Darstellung gemäß Fig. 2 zeigt ferner, dass im Zentrum des Separatortanks 5 eine Hülse 16 angeordnet ist, die sich vor den Porenöffnungen 17 im Körper 8 aus Metallschaum befindet. Im Inneren der Hülse 16 befindet sich wiederum eine weitere Hülse 18 aus einem Metallgewebe, die mit einem Auslass 19 des Separatortanks 5 verbunden ist. Diese Hülse aus Metallgewebe 18 hat die Funktion einer Sieb- oder Filterkartusche, d.h., etwaige Verschmutzungen nachgeschalteter, in den Figuren nicht dargestellter Geräte oder Ventile durch Partikel werden durch diese Hülse 18 vermieden.In the body 8 made of metal foam, alternately from body to body, 9 recesses 15 are introduced in the region of the lower 10 and upper lid, as can be seen from Fig. 4 is apparent. The representation according to Fig. 2 further shows that in the center of the separator tank 5, a sleeve 16 is arranged, which is located in front of the pore openings 17 in the body 8 made of metal foam. Inside the sleeve 16 is again a further sleeve 18 made of a metal fabric, which is connected to an outlet 19 of the separator tank 5 is connected. This sleeve of metal fabric 18 has the function of a screen or filter cartridge, ie, any contamination downstream, not shown in the figures devices or valves by particles are avoided by this sleeve 18.

Nachfolgend soll der Separationsprozess, der zu einer Abscheidung von Flüssigkeit aus einem Flüssigkeits-Gas-Gemisch führt, näher erläutert werden. Dazu ist in Fig. 5 der Strömungsverlauf 20 durch den Separatortank 5 dargestellt. Die Separation der Flüssigkeit vom Gas erfolgt durch das kapillare Eindringen der Flüssigkeit 21 in die schwammartigen Körper 8 aus Metallschaum, wie dies in Fig. 6 gezeigt ist. Der mit Flüssigkeit getränkte Bereich des Metallschaumes ist dabei in Fig. 6 durch einen gestrichelt dargestellten Bereich 22 gekennzeichnet. Mit zunehmender Flüssigkeitsmenge dringt die Flüssigkeit 21 immer weiter in die schwammartigen Körper 8 aus Metallschaum ein. Fig. 6 stellt einen solchen Zustand während des Eindringprozesses exemplarisch dar. Die Linien 23 kennzeichnen dabei die momentane Grenze zwischen der Flüssigkeit (gestrichelter Bereich 22) und dem Gas (im Rest des Metallschaumes). Die Strömungsrichtung des Flüssigkeits-Gas-Gemisches ist durch den Pfeil 24 gekennzeichnet.Subsequently, the separation process, which leads to a separation of liquid from a liquid-gas mixture, will be explained in more detail. This is in Fig. 5 the flow path 20 through the separator tank 5 is shown. The separation of the liquid from the gas is carried out by the capillary penetration of the liquid 21 into the sponge-like body 8 made of metal foam, as in Fig. 6 is shown. The liquid-impregnated region of the metal foam is in Fig. 6 indicated by a dashed area 22. With increasing amount of liquid, the liquid 21 penetrates ever further into the sponge-like body 8 made of metal foam. Fig. 6 represents such a state during the penetration process by way of example. The lines 23 indicate the momentary boundary between the liquid (dashed area 22) and the gas (in the rest of the metal foam). The flow direction of the liquid-gas mixture is indicated by the arrow 24.

Ist das Porenvolumen der schwammartigen Körper 8 aus Metallschaum mindestens so groß gewählt wie die Gesamtmenge der eindringenden Flüssigkeit 21, so erfolgt eine vollständige Speicherung der Flüssigkeit im Metallschaum. Um eine etwa konstante Strömungsgeschwindigkeit des Flüssigkeits-Gas-Gemisches 24 und damit ein gleichmäßiges Eindringen der Flüssigkeit 21 in die schwammartigen Körper 8 aus Metallschaum zu gewährleisten, wird der Querschnitt 20 zwischen den einzelnen Metallschaum-Körpern entsprechend angepasst. Dieser Querschnitt 20 zwischen den einzelnen Metallschaum-Körpern wird in Strömungsrichtung 24 immer breiter. Entsprechend werden auch die Ausnehmungen 15 in den schwammartigen Körpern 8 aus Metallschaum in Richtung auf das Zentrum des Separatortanks 5 immer tiefer, wie dies aus den Figuren 4 und 5 hervorgeht.If the pore volume of the sponge-like body 8 made of metal foam chosen at least as large as the total amount of the penetrating liquid 21, so there is a complete storage of the liquid in the metal foam. In order to ensure an approximately constant flow velocity of the liquid-gas mixture 24 and thus a uniform penetration of the liquid 21 into the sponge-like body 8 made of metal foam, the cross section 20 between the individual metal foam bodies is adjusted accordingly. This cross section 20 between the individual metal foam bodies is getting wider in the flow direction 24. Accordingly, the recesses 15 in the sponge-like bodies 8 made of metal foam in the direction of the center of the Separatortanks 5 are always deeper, as can be seen from Figures 4 and 5.

Der vorangehend beschriebene Separatortank ist sowohl für kryogene als auch für nicht-kryogene Flüssigkeiten geeignet. Die Darstellung gemäß Fig. 7 zeigt abschließend eine Anordnung, in der der Separatortank 5 für kryogene Flüssigkeiten verwendet wird. Dabei ist wichtig, dass die Temperatur des Separatortanks 5 nahe der Flüssigkeitstemperatur liegt. Deshalb wird in diesem Fall der Separatortank 5 zusammen mit dem Testbehälter 3 im Inneren eines Kryostaten 25 angeordnet, in dem ferner Heizer 26 vorgesehen sind. Schließlich sind in dieser Figur schematisch je eine Gaszuführvorrichtung 27 sowie eine Gasentnahmevorrichtung 28 eingezeichnet.The separator tank described above is suitable for both cryogenic and non-cryogenic liquids. The representation according to Fig. 7 Finally shows an arrangement in which the separator tank 5 is used for cryogenic liquids. It is important that the temperature of the separator tank 5 is close to the liquid temperature. Therefore, in this case, the separator tank 5 is disposed together with the test container 3 inside a cryostat 25 in which heaters 26 are further provided. Finally, a gas supply device 27 and a gas sampling device 28 are shown schematically in this figure.

Der Separatortank 5 wird zu Beginn mit Flüssigkeit gefüllt, deren Temperatur sich durch Vorgabe eines entsprechend der Sättigungskurve vorgegebenen Druckes einstellen lässt. Die Flüssigkeit verdampft daraufhin mit der Zeit, so dass der Separatortank 5 zu Beginn der eigentlichen Verwendung kryogene Temperaturen annimmt. Ist die Flüssigkeit vollständig verdampft, so ist der Separator verwendbar. Zur Beschleunigung des Verdampfungsprozesses ist zusätzlich eine Heizvorrichtung 26 vorgesehen, die der Vorbereitung des Separatortanks 5 dient.The separator tank 5 is initially filled with liquid, the temperature of which can be adjusted by presetting a pressure which is predetermined according to the saturation curve. The liquid then evaporates over time, so that the separator tank 5 assumes cryogenic temperatures at the beginning of the actual use. When the liquid has completely evaporated, the separator can be used. To accelerate the evaporation process, a heating device 26 is additionally provided, which serves to prepare the separator tank 5.

Claims (11)

  1. A tank for separating a liquid phase from a gaseous phase and for storing liquids for use in experiments in aerospace under the conditions of weightlessness, comprising a supply line through which a liquid, a gas or a mixture of both can be introduced into the tank, and comprising an outlet through which pure gas exits, characterized in that bodies (8) from a spongy material in the form of a metal foam are arranged in the tank (5), the total pore volume of which bodies is selected to be greater than the volume of the liquid (21) to be absorbed.
  2. The tank according to claim 1, characterized in that the metal foam is composed of aluminum.
  3. The tank according to any one of claims 1 or 2, characterized in that the tank is limited in each case by an upper (9) and a lower cover (10) and is enclosed by a cylindrical shell (11).
  4. The tank according to claim 3, characterized in that a supply line (12) ends in a circumferential injection channel (13) which, in the direction of the cylindrical shell (11), is connected to the interior of the tank (5) through a gap (14).
  5. The tank according to any one of claims 1 to 4, characterized in that the bodies (8) are formed as annular plates arranged lying inside of each other.
  6. The tank according to claim 5, characterized in that the bodies (8), at opposing ends thereof, are alternately provided with recesses (15).
  7. The tank according to claim 6, characterized in that the flow cross-section formed by the recesses (15) are constant with respect to the flow profile (20).
  8. The tank according to any one of claims 1 to 7, characterized in that in the center thereof a sleeve (16) having an extraction device (19) is arranged, which is located in front of the pore openings (17) in the spongy bodies (8).
  9. The tank according to claim 8, characterized in that the extraction device (19) is separated from the interior of the tank (5) by a sieve cartridge (18).
  10. The tank according to any one of claims 1 to 9, characterized in that for absorbing cryogenic liquids, the tank together with an upstream storage tank (3) is arranged in a cryostat (25).
  11. The tank according to claim 10, characterized in that a heating unit (26) is provided in the cryostat (25).
EP13002659.4A 2013-05-22 2013-05-22 Tank for the separation of liquids in orbit Not-in-force EP2806204B1 (en)

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