EP1248031A2 - Réservoir pour le stockage de liquides cryogéniques - Google Patents

Réservoir pour le stockage de liquides cryogéniques Download PDF

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Publication number
EP1248031A2
EP1248031A2 EP20010128582 EP01128582A EP1248031A2 EP 1248031 A2 EP1248031 A2 EP 1248031A2 EP 20010128582 EP20010128582 EP 20010128582 EP 01128582 A EP01128582 A EP 01128582A EP 1248031 A2 EP1248031 A2 EP 1248031A2
Authority
EP
European Patent Office
Prior art keywords
tank
liquid
reservoir
removal device
fuel
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.)
Withdrawn
Application number
EP20010128582
Other languages
German (de)
English (en)
Inventor
Gaston Dr. Netter
Kei Philipp Dr. Behruzi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
EADS Space Transportation GmbH
Original Assignee
Astrium GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Astrium GmbH filed Critical Astrium GmbH
Publication of EP1248031A2 publication Critical patent/EP1248031A2/fr
Withdrawn legal-status Critical Current

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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

Definitions

  • the invention relates to a container, in particular a tank for storing cryogenic liquids for the Operation of spacecraft, with one as a conveying medium serving propellant and at least one Removal device for the stored liquid, at which by means of seven and using the Surface tension a separation of the liquid from the Propellant gas is produced.
  • Such a container is a fuel tank from the DE 196 23 017 C1 became known.
  • spacecraft like satellites or orbital stations, are used for both the engines that serve to control the attitude in space as also for engines to carry out the Apogee maneuvers predominantly liquid fuels used in suitable containers carried and the from these usually under Use of a propellant in the fuel or Reaction chambers of the corresponding engines be promoted.
  • propellants Inert gases such as helium or nitrogen are used be pressed under pressure into the fuel tank and thereby the fuel into the respective Press engine-leading piping system.
  • Important is a complete and safe separation between the propellant and the the fuel entering the engine, because the latter must be absolutely free of foreign gas deposits got to.
  • cryogenic fuels are preferred to conventional liquid fuels such as monomethylhydrazine (MMH) wherever possible.
  • MMH monomethylhydrazine
  • a disadvantage of these cryogenic fuels is that, in contrast to conventional fuels, they can generally only be stored to a limited extent.
  • Liquid hydrogen (LH 2 ) changes to the gaseous state at a temperature of about 30 K, so that sufficient insulation of the fuel tank is absolutely necessary to ensure that this fuel can be stored for a sufficiently long period of time.
  • Bubble-free poses an important problem Fuel production under the state of Weightlessness. Such a bubble-free For example, fuel can be subsidized through a Achieve pre-acceleration using additional rockets to reorient the ones in the tank Liquid leads near the outlet pipe.
  • capillary sheets which are usually used for Fuel delivery can be used within the tank and their pumping action on a local change in Capillary pressure.
  • These capillary sheets are located mostly near the tank wall because Liquids in a state of weightlessness there prefer to invest. A cavitation near the Capillary plates can therefore interrupt the Pump effect, so that a special shape the sheets become necessary. Therefore, next to one the best possible thermal insulation of the reservoir to avoid gas formation within this Reservoirs the design of such capillary sheets special requirements for the formation of a tank for such fuels.
  • the object of the invention is to provide a container type mentioned so that even at cryogenic liquids are bubble-free guaranteed by utilizing the surface tension is.
  • the invention solves this problem by a container, in which the removal device in the form of a refillable reservoirs arranged at the bottom thereof is.
  • the reservoir is connected to the interior via delivery lines of the fuel tank connected.
  • the geometry of the Refillable provided according to the invention Reservoirs depend on the respective tank geometry or the liquid to be stored.
  • Two containers are provided as a fuel tank, which is after the Invention advantageously for storing liquid hydrogen (LH2 tank) and liquid Have oxygen (LOX tank) used.
  • LH2 tank liquid hydrogen
  • LOX tank liquid Have oxygen
  • the reservoirs can be refilled and emptied under weightless conditions most of the time when vacuuming under thrust, so that the remaining amount in the tank as far as possible is reduced. In the case of larger fill levels it is ensured that the reservoirs are also under Refill thrust.
  • the design of the containers according to the Invention device provided here has the advantage that they have a low mass and a have very low installation height and at the same time are inexpensive to manufacture.
  • the one through the Removal devices made possible a pre-acceleration before the start of the Withdrawal of fuel and thus the taking of Additional missiles allowed an essential one Weight saving and consequently higher payloads.
  • the fuel tank 1 shown in FIG. 1 is a surface tension tank for the uptake and storage of liquid hydrogen (LH2) as fuel for the top stage of a Rocket.
  • the tank consists of two approximated half-shelled sub-segments, the are welded together. In the interface of the The two half-shells form a relative tank wall strong curvature, so that the stored in the tank Fluid preferred in the state of weightlessness gathers in these areas. It is also in these Areas of capillary pressure particularly low, so that a pumping action occurs in the direction of the corners. This The area of the fuel tank is therefore particularly suitable for positioning a refillable Reservoirs 2.
  • the reservoir 2 has, as in particular with reference to Fig. 2 can be seen, the shape of an annular V-shaped tube. As further from the 4, it is connected to the tank interior 1 via sieves 7, 8.
  • the Mesh size of the sieves is designed so that only liquid penetrate into the reservoir 2 can keep gas bubbles away. To one sufficiently high flow rate through sieves 7 and 8 To ensure that the screen area is as large as possible selected and there are several sieves over the scope of the Reservoirs 2 distributed.
  • a removal device 3 is connected to the reservoir 2 connected and allows the removal of fuel. In order to form bubbles in the removal device 3 prevent, as shown in Fig. 3, is also a the extraction device 6 belonging to the extraction device 3 a heat exchanger 5 connected to the reservoir 2.
  • the gap between the sheet 11 and the sieves 7 and 8 is dimensioned so that the liquid in the vicinity of the sieves one if possible forms little free surface. This leaves the Evaporation of the liquid near the sieve surfaces minimal.
  • the plate 11 is attached to the reservoir 2. Important is in this context that the sheet 11 is not directly is connected to the tank wall 9, so that an excessive Heating of the sheet 11 is avoided.
  • the reservoir 2 is by means of a not shown in the figure thermal insulation attached to the tank wall 9. In this way it can be, depending on the mission, as Install additional component in tank 2.
  • FIG. 5 is a corresponding removal device with a reservoir 12 for use in a tank 21 for liquid oxygen, a so-called LOX tank, shown in the top stage of the missile.
  • This Tank 21 is in the case of the one shown here Embodiment shaped so that it is in the area one from the envelope of the previously described Fuel tanks 1 formed recess is integrated.
  • baffles 13 from a reservoir 12 serving as a removal device starting at right angles to each other along the Tank bottom. They cause the reservoir 12 fills with liquid.
  • the baffles are like this dimensioned so that the heat transfer from the wall minimize in the liquid. Occur in the Liquid cavitation bubbles on the tank wall, see above leads to the geometrical arrangement of the sheets the gas phase deposited on the wall into a Reduction of heat transfer and thus to one additional insulation between the tank wall and Liquid.
  • FIGS. 6 and 7 there is Removal device 12 from a base plate 22 and a cover 23 with a central opening 18.
  • Das Reservoir 12 is divided into two sections, the separated from each other by a conical wall 20 are. It is designed so that the first Volume below the cone 20 via four baffles 19 fills that on the top and bottom of the base plate 22 also at right angles to each other inside the Reservoirs 12 are attached.
  • the filling process is the flow direction in FIG. 7 of the incoming liquid oxygen by arrows indicated. Starting from the corners it fills up first the volume below the cone 20; then fills also the area above the cone.
  • the liquid oxygen flows through a sieve 17 a tank outlet in the form of an exhaust pipe 24.
  • the surface tension is formed by the close-meshed sieve 17, that is wetted by the liquid oxygen, one Barrier against propellant gas, so that only the bubble-free liquid oxygen through the exhaust pipe 24 in the direction the engine is promoted.
  • the screen 17 forms an additional security to the bubble-free To ensure oxygen production.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
EP20010128582 2001-04-07 2001-11-30 Réservoir pour le stockage de liquides cryogéniques Withdrawn EP1248031A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10117557 2001-04-07
DE2001117557 DE10117557A1 (de) 2001-04-07 2001-04-07 Behälter zur Lagerung kryogener Flüssigkeiten

Publications (1)

Publication Number Publication Date
EP1248031A2 true EP1248031A2 (fr) 2002-10-09

Family

ID=7680878

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20010128582 Withdrawn EP1248031A2 (fr) 2001-04-07 2001-11-30 Réservoir pour le stockage de liquides cryogéniques

Country Status (2)

Country Link
EP (1) EP1248031A2 (fr)
DE (1) DE10117557A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009019374A1 (fr) * 2007-08-07 2009-02-12 L'Air Liquide Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Réservoir cryogénique et lanceur spatial comprenant un tel réservoir
EP2143988A1 (fr) 2008-07-04 2010-01-13 Snecma Système de stockage de liquide cryogénique pour engin spatial

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005035356B3 (de) 2005-07-28 2006-10-19 Eads Space Transportation Gmbh Treibstofftank
DE102005044534B3 (de) 2005-09-17 2007-06-06 Astrium Gmbh Treibstofftank für kryogene Flüssigkeiten
DE102005062092B3 (de) 2005-12-22 2007-03-29 Eads Space Transportation Gmbh Treibstofftank
DE102007005539B3 (de) 2007-02-03 2008-08-14 Astrium Gmbh Tank zur Lagerung kryogener Flüssigkeiten oder lagerfähiger flüssiger Treibstoffe
DE102008026320B3 (de) 2008-06-03 2009-12-03 Astrium Gmbh Tank zur Lagerung kryogener Flüssigkeiten und lagerfähiger Treibstoffe

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009019374A1 (fr) * 2007-08-07 2009-02-12 L'Air Liquide Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Réservoir cryogénique et lanceur spatial comprenant un tel réservoir
FR2919852A1 (fr) * 2007-08-07 2009-02-13 Air Liquide Reservoir cryogenique et lanceur spatial comprenant un tel reservoir
EP2143988A1 (fr) 2008-07-04 2010-01-13 Snecma Système de stockage de liquide cryogénique pour engin spatial
RU2529084C2 (ru) * 2008-07-04 2014-09-27 Снекма Система хранения криогенной жидкости для космического аппарата

Also Published As

Publication number Publication date
DE10117557A1 (de) 2002-10-17

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