EP1748248A2 - Fueltank - Google Patents
Fueltank Download PDFInfo
- Publication number
- EP1748248A2 EP1748248A2 EP20060006914 EP06006914A EP1748248A2 EP 1748248 A2 EP1748248 A2 EP 1748248A2 EP 20060006914 EP20060006914 EP 20060006914 EP 06006914 A EP06006914 A EP 06006914A EP 1748248 A2 EP1748248 A2 EP 1748248A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- tank
- fuel
- outlet
- collecting container
- 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.)
- Granted
Links
- 239000002828 fuel tank Substances 0.000 title claims abstract description 22
- 230000001154 acute effect Effects 0.000 claims abstract description 5
- 239000000446 fuel Substances 0.000 claims description 20
- 239000003380 propellant Substances 0.000 claims description 14
- 239000007788 liquid Substances 0.000 claims description 6
- 238000005070 sampling Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 12
- 230000005484 gravity Effects 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 3
- 238000005086 pumping Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000001307 helium Substances 0.000 description 2
- 229910052734 helium Inorganic materials 0.000 description 2
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
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- 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
- 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 particular 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.
- the fuel tank illustrated in FIG. 1 is a surface tension tank for receiving and storing aggressive storable fuels, such as MMH, N 2 O 4 and hydrazine, with a fuel removal device arranged at the bottom of the tank, in which a separation of the surface is made use of Fuel is caused by the propellant gas.
- a fuel removal device arranged at the bottom of the tank, in which a separation of the surface is made use of Fuel is caused by the propellant gas.
- 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.
- 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 sump 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 of FIG. 1 for the 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)
Abstract
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
Weiterhin ist aus der
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 particular 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.
- Fig. 1
- a perspective view of a fuel tank,
- Fig. 2
- a detailed view of the fuel tank according to FIG. 1 in the region of the tank outlet,
- Fig. 3
- a section along in Fig. 2, and
- Fig. 4
- a vertical section in the region of the longitudinal axis through the fuel tank of 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.The fuel tank illustrated in FIG. 1 is a surface tension tank for receiving and storing aggressive storable fuels, such as MMH, N 2 O 4 and hydrazine, with a fuel removal device arranged at the bottom of the tank, in which a separation of the surface is made use of Fuel is caused by the propellant gas. In the tank four
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 shown in Figures 2 and 3, the
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
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
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
Claims (2)
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 true EP1748248A2 (en) | 2007-01-31 |
EP1748248A3 EP1748248A3 (en) | 2017-04-19 |
EP1748248B1 EP1748248B1 (en) | 2018-07-04 |
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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)
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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)
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 |
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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 artificial 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 |
-
2005
- 2005-07-28 DE DE200510035356 patent/DE102005035356B3/en not_active Expired - Fee Related
-
2006
- 2006-03-31 EP EP06006914.3A patent/EP1748248B1/en active Active
- 2006-05-31 BR BRPI0601953-6A patent/BRPI0601953B1/en not_active IP Right Cessation
- 2006-06-13 CN CNB2006100926551A patent/CN100507293C/en not_active Expired - Fee Related
- 2006-06-21 US US11/472,627 patent/US7395832B2/en not_active Expired - Fee Related
- 2006-07-27 JP JP2006204812A patent/JP4585994B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
JP4585994B2 (en) | 2010-11-24 |
DE102005035356B3 (en) | 2006-10-19 |
EP1748248B1 (en) | 2018-07-04 |
CN1903660A (en) | 2007-01-31 |
US7395832B2 (en) | 2008-07-08 |
US20070084509A1 (en) | 2007-04-19 |
CN100507293C (en) | 2009-07-01 |
BRPI0601953A (en) | 2007-03-13 |
EP1748248A3 (en) | 2017-04-19 |
JP2007030874A (en) | 2007-02-08 |
BRPI0601953B1 (en) | 2018-01-23 |
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