Nothing Special   »   [go: up one dir, main page]

EP1748248B1 - Fueltank - Google Patents

Fueltank Download PDF

Info

Publication number
EP1748248B1
EP1748248B1 EP06006914.3A EP06006914A EP1748248B1 EP 1748248 B1 EP1748248 B1 EP 1748248B1 EP 06006914 A EP06006914 A EP 06006914A EP 1748248 B1 EP1748248 B1 EP 1748248B1
Authority
EP
European Patent Office
Prior art keywords
tank
fuel
outlet
propellant gas
fuel tank
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.)
Active
Application number
EP06006914.3A
Other languages
German (de)
French (fr)
Other versions
EP1748248A3 (en
EP1748248A2 (en
Inventor
Kei Philipp Dr. Behruzi
Mark Dr. Michaelis
Gaston Dr. Netter
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.)
ArianeGroup GmbH
Original Assignee
ArianeGroup 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 ArianeGroup GmbH filed Critical ArianeGroup GmbH
Publication of EP1748248A2 publication Critical patent/EP1748248A2/en
Publication of EP1748248A3 publication Critical patent/EP1748248A3/en
Application granted granted Critical
Publication of EP1748248B1 publication Critical patent/EP1748248B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F17C3/00—Vessels not under pressure
    • F17C3/12—Vessels not under pressure with provision for protection against corrosion, e.g. due to gaseous acid
    • 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
    • F17C2201/0128—Shape spherical or elliptical
    • 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
    • F17C2201/05—Size
    • F17C2201/056—Small (<1 m3)
    • 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
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/014—Nitrogen
    • 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
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/016—Noble gases (Ar, Kr, Xe)
    • F17C2221/017—Helium
    • 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
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/08—Ergols, e.g. hydrazine
    • 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
    • F17C2223/0107—Single phase
    • F17C2223/0123—Single phase gaseous, e.g. CNG, GNC
    • 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
    • F17C2223/0107—Single phase
    • F17C2223/013—Single phase liquid
    • 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
    • F17C2223/03—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the pressure level
    • F17C2223/035—High pressure (>10 bar)
    • 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
    • F17C2260/00—Purposes of gas storage and gas handling
    • F17C2260/01—Improving mechanical properties or manufacturing
    • F17C2260/011—Improving strength
    • 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
    • F17C2260/00—Purposes of gas storage and gas handling
    • F17C2260/02—Improving properties related to fluid or fluid transfer
    • F17C2260/027—Making transfer independent of vessel orientation
    • 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
    • F17C2260/00—Purposes of gas storage and gas handling
    • F17C2260/05—Improving chemical properties
    • F17C2260/053—Reducing corrosion
    • 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
    • F17C2260/00—Purposes of gas storage and gas handling
    • F17C2260/05—Improving chemical properties
    • F17C2260/056—Improving fluid characteristics
    • 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
    • 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
    • F17C2270/0197—Rockets
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/2931—Diverse fluid containing pressure systems
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/8593—Systems
    • Y10T137/86348—Tank with internally extending flow guide, pipe or conduit

Definitions

  • the invention relates to a fuel tank, in particular a tank for storing aggressive liquids for the operation of spacecraft, with serving as a pumping medium propellant gas and at least one fuel sampling device consisting of at least one collecting container and a tank outlet, in which exploiting the surface tension, a separation of the fuel is brought from the propellant gas, wherein the removal device is arranged in the form of a refillable reservoir at the bottom of the fuel tank and connected via delivery lines to the interior of the fuel tank.
  • liquid propellants are used both for the engines that serve the attitude control in space, as well as for engines to perform the apogee maneuver carried in suitable containers and from these usually using a propellant gas be promoted into the combustion or reaction chambers of the corresponding engines.
  • propellants usually inert gases such as helium (He) or nitrogen (N 2 ) are used, which are pressed under pressure into the fuel tank and thereby press the fuel into the respective engine leading piping system.
  • He helium
  • N 2 nitrogen
  • US 4 595 398A discloses a fuel delivery device to be located in the area of a tank outlet.
  • the device should on the one hand ensure a uniform supply of fuel even with changing accelerations and on the other effect an effective discharge of gas and steam.
  • a standard way to separate liquids and gases is to use sieves that block the flow of gases up to a certain pressure difference.
  • these comparatively expensive screens may be dispensed with under certain circumstances.
  • a special and frequent requirement for such tanks is also the possibility of horizontal transport of the already filled fuel tank, integrated in the satellite, to the launch site, especially if no restrictions on the Tankstrullgrades are desired. Due to dynamic effects, the forces occurring during transport can exceed a multiple of the forces due to earth gravity. In the hitherto known tanks of this type, therefore, either the tank filling level is limited to smaller degrees of filling, so that the tank outlet is always surrounded by liquid, or the tank outlet is limited by a very narrow channel, but generates relatively high pressure losses during fuel extraction. The maximum allowable pressure losses are usually specified.
  • the object of the invention is to provide a tank according to the preamble in such a way that the fuel is kept stable even after a temporary horizontal orientation and low Tankstrullgrad in the fuel line and that thus always a bubble-free filling or refilling of the tank located in the tank is guaranteed ,
  • the invention solves this problem in that the tank outlet is provided with bores which connect an outlet pipe to the collecting container and which is provided with grooves in the region opposite the bores.
  • the manufacturing cost of the tank according to the invention are practically not increased over those of conventional tanks, so that at a constant cost, a considerable increase in flexibility in terms of handling on the ground and during rocket launches can be achieved.
  • the fuel tank according to the invention at the same time set so that it allows a safe and bubble-free promotion without screens.
  • the interior of the collecting container is formed at an acute angle with respect to a plane perpendicular to the symmetry axis of the tank.
  • fuel tank is a surface voltage tank for receiving and storage of aggressive storable fuels, such as MMH, N 2 O 4 and hydrazine, with a arranged on the tank bottom fuel sampling device, in which a separation of the fuel from the propellant gas is brought about by utilizing the surface tension.
  • baffles 1 are guided along the tank wall 2 and open into a sump 3 at the bottom of the fuel tank.
  • the fuel from this container 3 can be expelled by a propellant gas to a combustion or reaction chamber, not shown in the drawing.
  • propellant gas the inert gases helium (He) or nitrogen (N 2 ) are usually used, which press the fuel into the leading to the respective engine, not shown in the figure, piping system.
  • propellant gas the inert gases helium (He) or nitrogen (N 2 ) are usually used, which press the fuel into the leading to the respective engine, not shown in the figure, piping system.
  • the lower part 9 of the collecting container 3 is carried out at the tank outlet 4 as a rotating part, whereby in particular the manufacturing cost can be kept low.
  • a centrally located outlet pipe 10 connect three channels 11 with a diameter of about 2 mm on one side the interior 12 of the collecting container with the outlet pipe 10. Filling in the horizontal state is also possible if the connecting channels 11 against the acceleration of gravity upwards are directed.
  • the connection or opening channels 11 in the tank outlet are arranged inclined so that during the initial filling of the tank with fuel no propellant bubbles are trapped.
  • the interior of the collecting container 12 is formed in its geometry at an acute angle 15 with respect to a plane perpendicular to the axis of symmetry or longitudinal axis 13 of the tank, so as to extend both from the horizontal to the vertical position, e.g. after a horizontal transport with low tank filling levels, as well as in weightless condition due to the capillary action again completely and bubble-free fills.
  • the rapid filling is additionally supported by unilaterally cut grooves 14, so that it fills under weightlessness very quickly due to the acting capillary forces.
  • the configuration of the collecting container interior 12 with the acute angle 15 the filling process under the capillary pumping action is considerably improved.
  • a filling of the tank with fuel is usually carried out with vertically aligned tank, ie, the longitudinal axis 13 of the tank in this case runs parallel to the direction of earth gravity, the entire tank outlet 4 and the reservoir 3 are completely filled with fuel. If the fuel tank is subsequently tilted about the tank transverse axis such that the three openings 11 are aligned counter to the acting acceleration, the tank can be transported horizontally even at low tank filling levels.
  • the filled fuel tank according to Fig. 1 for subsequent transport, integrated, for example, in a satellite, stored horizontally to the launch site.
  • the tank outlet 4 of the filled Tanks is oriented perpendicular to the direction of the indicated in the figure with an arrow acceleration of gravity g, so that the fuel 5, especially at low levels, no longer wets the outlet 4, but its level at a distance h below this outlet 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)

Description

Die Erfindung betrifft einen Treibstofftank, insbesondere einen Tank zur Lagerung aggressiver Flüssigkeiten zum Betrieb von Raumflugkörpern, mit einem als Fördermedium dienenden Treibgas sowie mit wenigstens einer Treibstoffentnahmevorrichtung, bestehend aus wenigstens je einem Sammelbehälter und einem Tankauslaß, bei der unter Ausnutzung der Oberflächenspannung eine Separation des Treibstoffs vom Treibgas herbeigeführt wird, wobei die Entnahmevorrichtung in Form eines wiederbefüllbaren Reservoirs am Boden des Treibstofftanks angeordnet und über Förderleitungen mit dem Inneren des Treibstofftanks verbunden ist.The invention relates to a fuel tank, in particular a tank for storing aggressive liquids for the operation of spacecraft, with serving as a pumping medium propellant gas and at least one fuel sampling device consisting of at least one collecting container and a tank outlet, in which exploiting the surface tension, a separation of the fuel is brought from the propellant gas, wherein the removal device is arranged in the form of a refillable reservoir at the bottom of the fuel tank and connected via delivery lines to the interior of the fuel tank.

Bei Raumflugkörpern, wie Satelliten oder Orbitalstationen, werden sowohl für die Triebwerke, die der Lageregelung im All dienen, als auch für Triebwerke zur Durchführung des Apogäummanövers überwiegend flüssige Treibstoffe verwendet, die in hierfür geeigneten Behältern mitgeführt und aus diesen in der Regel unter Verwendung eines Treibgases in die Brenn- bzw. Reaktionskammern der entsprechenden Triebwerke gefördert werden. Als Treibgase werden üblicherweise Inertgase wie Helium (He) oder Stickstoff (N2) eingesetzt, die unter Druck in den Treibstoffbehälter gepreßt werden und die dadurch den Treibstoff in das zum jeweiligen Triebwerk führende Rohrleitungssystem pressen. Wichtig ist dabei eine vollständige und sichere Trennung zwischen dem als Fördermedium dienenden Treibgas und dem in das Triebwerk gelangenden Treibstoff, da letzterer bei Zündung unbedingt frei von Fremdgaseinlagerungen sein muß. Ein auf diesem Prinzip basierender Tank der eingangs genannten Art ist aus der DE 100 40 755 C2 bekannt geworden. US 4 595 398A offenbart eine Treibstoffbereitstellungsvorrichtung, die im Bereich eines Tankauslasses anzuordnen ist. Die Vorrichtung soll zum einen eine gleichmäßige Treibstoffzufuhr auch bei sich ändernden Beschleunigungen gewährleisten und zum anderen ein effektives Ableiten von Gas und Dampf bewirken. Weiterhin ist aus der US 5 293 895 ein Treibstofftank bekannt, wobei beim Auslaß das Auslaßrohr mittels vieler Bohrungen mit einem Sammelbehälter verbunden ist.In spacecraft, such as satellites or orbital stations, predominantly liquid propellants are used both for the engines that serve the attitude control in space, as well as for engines to perform the apogee maneuver carried in suitable containers and from these usually using a propellant gas be promoted into the combustion or reaction chambers of the corresponding engines. As propellants usually inert gases such as helium (He) or nitrogen (N 2 ) are used, which are pressed under pressure into the fuel tank and thereby press the fuel into the respective engine leading piping system. What is important is a complete and safe separation between serving as the pumped propellant gas and the reaching into the engine fuel, since the latter must be absolutely free of foreign gas deposits when ignited. A based on this principle tank of the type mentioned is from the DE 100 40 755 C2 known. US 4 595 398A discloses a fuel delivery device to be located in the area of a tank outlet. The device should on the one hand ensure a uniform supply of fuel even with changing accelerations and on the other effect an effective discharge of gas and steam. Furthermore, from the US 5,293,895 a fuel tank known, wherein at the outlet, the outlet pipe is connected by means of many holes with a collecting container.

Eine Standardmethode, Flüssigkeiten und Gase voneinander zu trennen, besteht in der Verwendung von Sieben, die bis zu einer bestimmten Druckdifferenz gegen den Durchsatz von Gasen sperren. Bei kleineren Satelliten mit geringem Treibstofförderstrom kann jedoch unter bestimmten Umständen auf diese vergleichsweise kostspieligen Siebe verzichtet werden. Eine besondere und häufige Anforderung an derartige Tanks ist zudem die Möglichkeit eines horizontalen Transports des bereits befüllten Treibstofftanks, integriert in den Satelliten, zum Startplatz, insbesondere dann, wenn keine Beschränkungen hinsichtlich des Tankfüllgrades erwünscht sind. Die während des Transportes auftretenden Kräfte können aufgrund dynamischer Effekte ein vielfaches der Kräfte durch die Erdgravitation überschreiten. Bei den bisher bekannten Tanks dieser Art ist deshalb entweder der Tankfüllgrad zu kleineren Füllgraden hin beschränkt, so daß der Tankauslaß stets mit Flüssigkeit umgeben ist, oder aber der Tankauslaß ist durch einen sehr engen Kanal eingeschränkt, der jedoch relativ hohe Druckverluste bei der Treibstoffentnahme erzeugt. Die dabei maximal zulässigen Druckverluste werden üblicherweise vorgegeben.A standard way to separate liquids and gases is to use sieves that block the flow of gases up to a certain pressure difference. For smaller satellites with low fuel flow, however, these comparatively expensive screens may be dispensed with under certain circumstances. A special and frequent requirement for such tanks is also the possibility of horizontal transport of the already filled fuel tank, integrated in the satellite, to the launch site, especially if no restrictions on the Tankfüllgrades are desired. Due to dynamic effects, the forces occurring during transport can exceed a multiple of the forces due to earth gravity. In the hitherto known tanks of this type, therefore, either the tank filling level is limited to smaller degrees of filling, so that the tank outlet is always surrounded by liquid, or the tank outlet is limited by a very narrow channel, but generates relatively high pressure losses during fuel extraction. The maximum allowable pressure losses are usually specified.

Eine weitere Anforderung an einen solchen Tank ist die Möglichkeit, daß Satelliten, die derartige Tanks enthalten, mit einer Ausrichtung quer zum Tankauslaß in den Orbit befördert werden sollen. Diese Möglichkeit ergibt sich insbesondere bei der Beförderung mehrerer kleiner Satelliten, die auf einer zentralen Trägerstruktur seitlich horizontal angebracht sind. Die beim Raketenstart auftretenden hohen dynamischen Lasten haben zur Folge, daß freiliegende Siebe und Öffnungen in der Regel kein Haltevermögen mehr haben, d.h., daß ein Eintreten von Treibgas in den Auslaß nicht unterbunden werden kann. Dies führt zu einem Versagen, wenn der Treibstofftank nicht vollständig gefüllt wird und sensible Bauteile wie Siebe und Öffnungen aus der Flüssigkeit herausragen. Treibgas kann dann bei hohen Belastungen durch die Siebe und Öffnungen zum Tankauslaß gelangen, was ebenfalls zu einem Versagen des Triebwerks führen kann. Ein Raketenstart mit horizontal ausgerichtetem Tank ist daher mit den bisher bekannten Tanks der eingangs genannten Art nicht möglich.Another requirement for such a tank is the possibility of satellites containing such tanks being conveyed into orbit transversely to the tank outlet. This possibility arises in particular in the transport of several small satellites, which are mounted laterally horizontally on a central support structure. The high dynamic loads which occur at rocket launch have the result that exposed screens and openings are generally no longer able to hold, i.e. that propellant gas can not be prevented from entering the outlet. This leads to failure if the fuel tank is not completely filled and sensitive components such as screens and openings protrude from the liquid. Propellant gas can then reach the tank outlet at high loads through the screens and openings, which can also lead to a failure of the engine. A rocket launch with horizontally aligned tank is therefore not possible with the previously known tanks of the type mentioned.

Aufgabe der Erfindung ist es, einen Tank gemäß dem Oberbegriff so auszubilden, daß der Treibstoff auch nach einer vorübergehenden horizontalen Orientierung und bei niedrigem Tankfüllgrad stabil in der Treibstoffleitung gehalten wird und daß damit stets eine blasenfreie Befüllung bzw. Wiederbefüllung des im Tank befindlichen Sammelbehälters gewährleistet ist.The object of the invention is to provide a tank according to the preamble in such a way that the fuel is kept stable even after a temporary horizontal orientation and low Tankfüllgrad in the fuel line and that thus always a bubble-free filling or refilling of the tank located in the tank is guaranteed ,

Die Erfindung löst diese Aufgabe dadurch, daß der Tankauslaß mit Bohrungen versehen ist, die ein Auslaßrohr mit dem Sammelbehälter verbinden und der den Bohrungen gegenüberliegende Bereich mit Nuten versehen ist.The invention solves this problem in that the tank outlet is provided with bores which connect an outlet pipe to the collecting container and which is provided with grooves in the region opposite the bores.

Die Herstellungskosten für den Tank nach der Erfindung sind dabei gegenüber denen herkömmlicher Tanks praktisch nicht erhöht, so daß bei gleich bleibenden Kosten eine erhebliche Steigerung der Flexibilität hinsichtlich der Handhabung am Boden und während des Raketenstarts erzielbar ist. Dabei ist der Treibstofftank gemäß der Erfindung zugleich so festgelegt, daß er ohne Siebe eine sichere und blasenfreie Förderung ermöglicht.The manufacturing cost of the tank according to the invention are practically not increased over those of conventional tanks, so that at a constant cost, a considerable increase in flexibility in terms of handling on the ground and during rocket launches can be achieved. In this case, the fuel tank according to the invention at the same time set so that it allows a safe and bubble-free promotion without screens.

Zur Verbesserung der Befüllung unter der kapillaren Pumpwirkung wird vorgeschlagen, daß der Innenraum des Sammelbehälters mit einem spitzen Winkel gegenüber einer zur Symmetrieachse des Tanks senkrecht liegenden Ebene ausgebildet ist.To improve the filling under the capillary pumping action, it is proposed that the interior of the collecting container is formed at an acute angle with respect to a plane perpendicular to the symmetry axis of the tank.

Nachfolgend soll der erfindungsgemäße Treibstofftank anhand eines in der Zeichnung dargestellten Ausführungsbeispiels näher erläutert werden. Es zeigen:

Fig. 1
eine perspektivische Darstellung eines Treibstofftanks,
Fig. 2
eine Detaildarstellung des Treibstofftanks gemäß Fig. 1 im Bereich des Tankauslasses,
Fig. 3
einen Schnitt entlang in Fig. 2, und
Fig. 4
einen vertikalen Schnitt im Bereich der Längsachse durch den Treibstofftank gemäß Fig. 1, der in diesem Fall für einen Start in horizontaler Position angeordnet ist.
Below, the fuel tank according to the invention will be explained in more detail with reference to an embodiment shown in the drawing. Show it:
Fig. 1
a perspective view of a fuel tank,
Fig. 2
a detailed view of the fuel tank according to Fig. 1 in the area of the tank outlet,
Fig. 3
a cut along in Fig. 2 , and
Fig. 4
a vertical section in the region of the longitudinal axis through the fuel tank according to Fig. 1 which is arranged in this case for a start in a horizontal position.

Bei dem in Fig. 1 dargestellten Treibstofftank handelt es sich um einen Oberflächenspannungstank für die Aufnahme und Lagerung von aggressiven lagerfähigen Treibstoffen, wie MMH, N2O4 und Hydrazin, mit einer am Tankboden angeordneten Treibstoffentnahmevorrichtung, bei der unter Ausnutzung der Oberflächenspannung eine Separation des Treibstoffs vom Treibgas herbeigeführt wird. Bei dem Tank sind vier Leitbleche 1 entlang der Tankwand 2 geführt und münden in einen Sammelbehälter 3 am Boden des Treibstofftanks. Über ein Auslaßrohr 4 läßt sich der Treibstoff aus diesem Behälter 3 durch ein Treibgas zu einer in der Zeichnung nicht dargestellten Brenn- bzw. Reaktionskammer austreiben. Als Treibgas werden dabei üblicherweise die Inertgase Helium (He) oder Stickstoff (N2) eingesetzt, die den Treibstoff in das zum jeweiligen Triebwerk führende, in der Figur nicht dargestellte Rohrleitungssystem pressen.At the in Fig. 1 shown fuel tank is a surface voltage tank for receiving and storage of aggressive storable fuels, such as MMH, N 2 O 4 and hydrazine, with a arranged on the tank bottom fuel sampling device, in which a separation of the fuel from the propellant gas is brought about by utilizing the surface tension. In the tank four baffles 1 are guided along the tank wall 2 and open into a sump 3 at the bottom of the fuel tank. Via an outlet pipe 4, the fuel from this container 3 can be expelled by a propellant gas to a combustion or reaction chamber, not shown in the drawing. As propellant gas, the inert gases helium (He) or nitrogen (N 2 ) are usually used, which press the fuel into the leading to the respective engine, not shown in the figure, piping system.

Wie in den Figuren 2 und 3 dargestellt, ist der untere Teil 9 des Sammelbehälters 3 am Tankauslaß 4 als Drehteil ausgeführt, wodurch insbesondere die Herstellungskosten gering gehalten werden können. Ausgehend von einem zentral angeordneten Auslaßrohr 10 verbinden drei Kanäle 11 mit einem Durchmesser von jeweils etwa 2 mm einseitig das Innere 12 des Sammelbehälters mit dem Auslaßrohr 10. Ein Befüllen im horizontalen Zustand ist dabei auch dann möglich, wenn die Verbindungskanäle 11 entgegen der Erdbeschleunigung nach oben gerichtet sind. Die Verbindungs- oder Öffnungskanäle 11 im Tankauslaß sind dabei derart geneigt angeordnet, daß während der Erstbefüllung des Tanks mit Treibstoff keine Treibgasblasen eingeschlossen werden.As in the Figures 2 and 3 shown, the lower part 9 of the collecting container 3 is carried out at the tank outlet 4 as a rotating part, whereby in particular the manufacturing cost can be kept low. Starting from a centrally located outlet pipe 10 connect three channels 11 with a diameter of about 2 mm on one side the interior 12 of the collecting container with the outlet pipe 10. Filling in the horizontal state is also possible if the connecting channels 11 against the acceleration of gravity upwards are directed. The connection or opening channels 11 in the tank outlet are arranged inclined so that during the initial filling of the tank with fuel no propellant bubbles are trapped.

Der Innenraum des Sammelbehälters 12 ist in seiner Geometrie mit einem spitzen Winkel 15 gegenüber einer zur Symmetrie- oder Längsachse 13 des Tanks senkrecht liegenden Ebene derart ausgebildet, daß sich dieser sowohl beim Drehen des Tanks von der horizontalen in die vertikale Position, z.B. nach einem horizontalem Transport mit geringen Tankfüllgraden, als auch in schwerelosem Zustand infolge der Kapillarwirkung wieder von selbst vollständig und blasenfrei füllt. Das schnelle Befüllen wird zusätzlich durch einseitig eingeschnittene Nuten 14 unterstützt, so daß dieser sich unter Schwerelosigkeit sehr schnell aufgrund der wirkenden Kapillarkräfte füllt. Infolge der Ausgestaltung des Sammelbehälterinnenraumes 12 mit dem spitzen Winkel 15 wird der Befüllvorgang unter der kapillaren Pumpwirkung erheblich verbessert.The interior of the collecting container 12 is formed in its geometry at an acute angle 15 with respect to a plane perpendicular to the axis of symmetry or longitudinal axis 13 of the tank, so as to extend both from the horizontal to the vertical position, e.g. after a horizontal transport with low tank filling levels, as well as in weightless condition due to the capillary action again completely and bubble-free fills. The rapid filling is additionally supported by unilaterally cut grooves 14, so that it fills under weightlessness very quickly due to the acting capillary forces. As a result of the configuration of the collecting container interior 12 with the acute angle 15, the filling process under the capillary pumping action is considerably improved.

Eine Befüllung des Tanks mit Treibstoff erfolgt meist bei vertikal ausgerichtetem Tank, d.h., die Längsachse 13 des Tanks verläuft in diesem Fall parallel zur Richtung der Erdgravitation, wobei der gesamte Tankauslaß 4 sowie der Sammelbehälter 3 vollständig mit Treibstoff gefüllt sind. Wird der Treibstofftank anschließend so um die Tankquerachse gekippt, daß die drei Öffnungen 11 entgegen der wirkenden Beschleunigung ausgerichtet sind, so kann der Tank auch bei geringen Tankfüllgraden horizontal transportiert werden. Bei der in Fig. 4 dargestellten Anordnung ist der befüllte Treibstofftank gemäß Fig. 1 für den anschließenden Transport, integriert beispielsweise in einen Satelliten, zum Startplatz horizontal gelagert. Der Tankauslaß 4 des befüllten Tanks ist dabei senkrecht zur Richtung der in der Figur mit einem Pfeil angedeuteten Erdbeschleunigung g orientiert, so daß der Treibstoff 5, insbesondere bei geringen Füllgraden, nicht mehr den Auslaß 4 benetzt, sondern sein Niveau im Abstand h unterhalb dieses Auslasses 4 liegt.A filling of the tank with fuel is usually carried out with vertically aligned tank, ie, the longitudinal axis 13 of the tank in this case runs parallel to the direction of earth gravity, the entire tank outlet 4 and the reservoir 3 are completely filled with fuel. If the fuel tank is subsequently tilted about the tank transverse axis such that the three openings 11 are aligned counter to the acting acceleration, the tank can be transported horizontally even at low tank filling levels. At the in Fig. 4 The arrangement shown is the filled fuel tank according to Fig. 1 for subsequent transport, integrated, for example, in a satellite, stored horizontally to the launch site. The tank outlet 4 of the filled Tanks is oriented perpendicular to the direction of the indicated in the figure with an arrow acceleration of gravity g, so that the fuel 5, especially at low levels, no longer wets the outlet 4, but its level at a distance h below this outlet 4.

Die Verwendung mehrerer Kanäle 11 im Auslaß führt zusätzlich zu einem im Vergleich zu den bislang bekannten Tanks dieser Art erheblich verminderten Druckverlust am Tankauslaß 4 während des Austreibens von Treibstoff. Die Modifikationen des Auslasses erlauben neben den erweiterten Anwendungsgebieten bzgl. eines horizontalen Transportes und horizontalen Starts zudem eine größere Reserve hinsichtlich der maximal tolerierbaren Druckverluste sowie ein schnelleres Befüllen und Entleeren des Tanks am Boden.The use of multiple channels 11 in the outlet in addition to a significantly reduced pressure loss at the tank outlet 4 during the expulsion of fuel compared to the previously known tanks of this type. The modifications of the outlet allow, in addition to the extended application areas with respect to a horizontal transport and horizontal take-off also a larger reserve in terms of maximum tolerable pressure losses and faster filling and emptying of the tank on the ground.

Claims (2)

  1. Fuel tank, in particular, a tank for storing aggressive liquids for the operation of spacecraft, with a propellant gas serving as conveying medium as well as at least one fuel withdrawal device, the or each fuel withdrawal device consisting of at least one collecting tank and a tank outlet, in which by utilizing the surface tension a separation of the fuel from the propellant gas is achieved, wherein the withdrawal device is arranged in the form of a refillable reservoir on the floor of the fuel tank and is connected via conveying lines to the interior of the fuel tank, wherein the tank outlet is provided with bore holes (11), which connect an outlet pipe (10) to the collecting tank (3), characterized in that the area opposite to the bore holes (11) is provided with grooves (14).
  2. Fuel tank according to Claim 1, characterized in that the interior space of the collecting tank (12) is designed with a sharp angle (15) with relation to a plane lying perpendicular to the symmetry axis (13) of the tank.
EP06006914.3A 2005-07-28 2006-03-31 Fueltank Active EP1748248B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200510035356 DE102005035356B3 (en) 2005-07-28 2005-07-28 Fuel tank for storing aggressive media used for powering spacecraft comprises an outlet with holes for connecting an outlet tube to a collecting container

Publications (3)

Publication Number Publication Date
EP1748248A2 EP1748248A2 (en) 2007-01-31
EP1748248A3 EP1748248A3 (en) 2017-04-19
EP1748248B1 true EP1748248B1 (en) 2018-07-04

Family

ID=36587363

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06006914.3A Active EP1748248B1 (en) 2005-07-28 2006-03-31 Fueltank

Country Status (6)

Country Link
US (1) US7395832B2 (en)
EP (1) EP1748248B1 (en)
JP (1) JP4585994B2 (en)
CN (1) CN100507293C (en)
BR (1) BRPI0601953B1 (en)
DE (1) DE102005035356B3 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005044534B3 (en) * 2005-09-17 2007-06-06 Astrium Gmbh Fuel tank for cryogenic liquids
DE102005062092B3 (en) * 2005-12-22 2007-03-29 Eads Space Transportation Gmbh Aggressive storable propellant e.g. hydrazine, receiving and storage tank for operation of e.g. satellite, has tank outlet with connecting-or opening channels and helical channel, where channels connect reservoir with outlet pipe of outlets
DE102007005539B3 (en) * 2007-02-03 2008-08-14 Astrium Gmbh Tank for storage of cryogenic liquids or storable liquid fuels
US7559509B1 (en) * 2007-02-12 2009-07-14 Thomas C. Taylor Large cryogenic tank logistics for in-space vehicles
US8899974B2 (en) * 2007-09-19 2014-12-02 The Aerospace Corporation Particulate mitigating propellant management tank device
DE102008026320B3 (en) * 2008-06-03 2009-12-03 Astrium Gmbh Tank for storage of cryogenic liquids and storable fuels
DE102009019002B3 (en) * 2009-04-16 2010-11-25 Astrium Gmbh Bubble trap for fuel tanks in spacecraft
US8245889B1 (en) 2009-11-03 2012-08-21 Jon Starns Portable pumpless fuel delivery system
US8511504B2 (en) * 2011-03-21 2013-08-20 Hamilton Sundstrand Corporation Demisable fuel supply system
US8534489B2 (en) * 2011-03-21 2013-09-17 Hamilton Sundstrand Space Systems International, Inc. Demisable fuel supply system
US10479532B2 (en) * 2015-05-07 2019-11-19 Keystone Engineering Company Stress relieved welds in positive expulsion fuel tanks with rolling metal diaphragms
US11092111B1 (en) 2018-12-10 2021-08-17 United Launch Alliance, L.L.C. Vapor retention device

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA683854A (en) 1964-04-07 Clark George Liquid reservoirs for aircraft
US2163988A (en) * 1937-10-21 1939-06-27 Stacey Cromwell Safety apparatus for motor vehicles
US2943815A (en) * 1954-11-19 1960-07-05 Sud Aviation Aerodynes, more particularly pilotless aerodynes
US3315845A (en) * 1965-09-27 1967-04-25 Bendix Corp Convoluted spherical barrier for liquid storage tank
US3854905A (en) * 1972-04-24 1974-12-17 Rca Corp Storage system for two phase fluids
FR2484961A1 (en) * 1980-06-20 1981-12-24 Europ Propulsion SURFACE TANK
DE3146262A1 (en) * 1981-11-21 1983-05-26 Erno-Raumfahrttechnik Gmbh, 2800 Bremen "FUEL TANK"
US4595398A (en) * 1984-05-21 1986-06-17 Mcdonnell Douglas Corporation Propellant acquisition device
US4790350A (en) * 1986-02-04 1988-12-13 Arnold Charles M Combat rapid assembly fuel tank
US4733531A (en) * 1986-03-14 1988-03-29 Lockheed Missiles & Space Company, Inc. Liquid-propellant management system with capillary pumping vanes
US4743278A (en) * 1986-06-16 1988-05-10 Ford Aerospace & Communications Corporation Passive propellant management system
US4768541A (en) * 1986-11-03 1988-09-06 Martin Marietta Corporation Means of expelling parallel tanks to low residuals
DE3837137A1 (en) * 1988-11-02 1990-05-03 Erno Raumfahrttechnik Gmbh FUEL TANK FOR STORING AGGRESSIVE LIQUIDS
FR2678895B1 (en) * 1991-07-08 1993-11-12 Propulsion Ste Europeenne SURFACE TANK, MULTIPLE OUTPUT FLOW RATES.
US5279323A (en) * 1991-12-19 1994-01-18 Lockheed Missiles & Space Company, Inc. Liquid management apparatus for spacecraft
JP3511313B2 (en) * 1994-06-29 2004-03-29 株式会社アイ・エイチ・アイ・エアロスペース Vane type surface tension tank
US6014987A (en) * 1998-05-11 2000-01-18 Lockheed Martin Corporation Anti-vortex baffle assembly with filter for a tank
DE10040755C2 (en) * 2000-08-19 2002-06-27 Astrium Gmbh fuel tank
JP2002137799A (en) * 2000-10-31 2002-05-14 Ishikawajima Harima Heavy Ind Co Ltd Propellant tank for satellite
DE10117557A1 (en) 2001-04-07 2002-10-17 Astrium Gmbh Containers for the storage of cryogenic liquids
DE102005062092B3 (en) * 2005-12-22 2007-03-29 Eads Space Transportation Gmbh Aggressive storable propellant e.g. hydrazine, receiving and storage tank for operation of e.g. satellite, has tank outlet with connecting-or opening channels and helical channel, where channels connect reservoir with outlet pipe of outlets

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP1748248A3 (en) 2017-04-19
DE102005035356B3 (en) 2006-10-19
BRPI0601953B1 (en) 2018-01-23
JP4585994B2 (en) 2010-11-24
EP1748248A2 (en) 2007-01-31
BRPI0601953A (en) 2007-03-13
US20070084509A1 (en) 2007-04-19
CN100507293C (en) 2009-07-01
CN1903660A (en) 2007-01-31
US7395832B2 (en) 2008-07-08
JP2007030874A (en) 2007-02-08

Similar Documents

Publication Publication Date Title
EP1748248B1 (en) Fueltank
EP1801011B1 (en) Propellant tank
DE102007005539B3 (en) Tank for storage of cryogenic liquids or storable liquid fuels
DE102008026320B3 (en) Tank for storage of cryogenic liquids and storable fuels
DE3786715T2 (en) Passive fuel management order.
EP2241505B1 (en) Bubble trap for propellant tanks in spacecraft
DE2458368C3 (en) Storage container for two fluids
DE2320245C2 (en) Storage tank
EP1924804B1 (en) Propellant for cryogenic liquids
DE3837137C2 (en)
DE19916385C2 (en) Vehicle with compressed gas tank as a vehicle tank
DE102011119921B3 (en) Rocket stage with liquid propellant system
DE69202928T2 (en) Surface tension tank with multiple outputs.
DE10040755C2 (en) fuel tank
DE10117557A1 (en) Containers for the storage of cryogenic liquids
DE19623017C1 (en) Propellant tank for corrosive fluids for driving space vehicle
DE4217051C2 (en) Fuel supply system for rocket engines
EP2806204B1 (en) Tank for the separation of liquids in orbit
DE102011122352B4 (en) Tank for the separation of liquids in orbit
DE4216954A1 (en) Containers, in particular fuel tanks
DE102018132828A1 (en) Extinguishing agent container
AT521398B1 (en) STORAGE TANK FOR VEHICLES
DE2916662C3 (en) Cluster weapon container
DE1906011A1 (en) Capillary partition
DE2533053A1 (en) Tank for storage of liqueified gases - has groups of tanks connected at lower ends via one way valves

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

RIC1 Information provided on ipc code assigned before grant

Ipc: F17C 3/12 20060101AFI20170314BHEP

Ipc: F17C 13/00 20060101ALI20170314BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170831

AKX Designation fees paid

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AXX Extension fees paid

Extension state: AL

Extension state: YU

Extension state: BA

Extension state: HR

Extension state: MK

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ARIANEGROUP GMBH

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180406

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1014900

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180715

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502006015939

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180704

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181104

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181004

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181005

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502006015939

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

26N No opposition filed

Effective date: 20190405

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190401

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181105

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1014900

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180704

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20060331

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230612

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240320

Year of fee payment: 19

Ref country code: GB

Payment date: 20240320

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240329

Year of fee payment: 19

Ref country code: FR

Payment date: 20240321

Year of fee payment: 19