EP2813433A2 - Verfahren und Gerät zur Leerung eines Behälters eines Raumfahrzeugs - Google Patents

Verfahren und Gerät zur Leerung eines Behälters eines Raumfahrzeugs Download PDF

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Publication number
EP2813433A2
EP2813433A2 EP20140171603 EP14171603A EP2813433A2 EP 2813433 A2 EP2813433 A2 EP 2813433A2 EP 20140171603 EP20140171603 EP 20140171603 EP 14171603 A EP14171603 A EP 14171603A EP 2813433 A2 EP2813433 A2 EP 2813433A2
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EP
European Patent Office
Prior art keywords
pipe
pressure
outlet
spacecraft
emptying
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
Application number
EP20140171603
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English (en)
French (fr)
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EP2813433A3 (de
EP2813433B1 (de
Inventor
Thomas Lienart
Kilian Pfaab
Patrick Bravais
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.)
Centre National dEtudes Spatiales CNES
Air Liquide SA
LAir Liquide SA pour lEtude et lExploitation des Procedes Georges Claude
Original Assignee
Centre National dEtudes Spatiales CNES
Air Liquide SA
LAir Liquide SA pour lEtude et lExploitation des Procedes Georges Claude
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.)
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Publication of EP2813433A2 publication Critical patent/EP2813433A2/de
Publication of EP2813433A3 publication Critical patent/EP2813433A3/de
Application granted granted Critical
Publication of EP2813433B1 publication Critical patent/EP2813433B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C7/00—Methods or apparatus for discharging liquefied, solidified, or compressed gases from pressure vessels, not covered by another subclass
    • 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
    • F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
    • F17C2205/03—Fluid connections, filters, valves, closure means or other attachments
    • F17C2205/0302—Fittings, valves, filters, or components in connection with the gas storage device
    • F17C2205/0323—Valves
    • 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
    • F17C2223/03—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
    • 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
    • F17C2223/036—Very high pressure (>80 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
    • F17C2227/0114—Propulsion of the fluid with vacuum injectors, e.g. venturi
    • 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
    • F17C2260/025—Reducing transfer time
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0186—Applications for fluid transport or storage in the air or in space
    • F17C2270/0194—Applications for fluid transport or storage in the air or in space for use under microgravity conditions, e.g. space

Definitions

  • the invention relates to a method and a device for emptying a spacecraft enclosure containing a gaseous composition under a pressure P1 greater than that P2 prevailing in an environment outside the spacecraft located in the outer space ( designated "Space” throughout the text), the enclosure being connected to this external environment of the Space by at least one evacuation pipe. It extends to a spacecraft, such as an artificial satellite, equipped with at least one such emptying device.
  • the gaseous composition may comprise a non-zero proportion of water which, during expansion, may generate liquid droplets which disturb the emptying operation and may generate untimely variations. the thrust generated by the emptying, or even the phenomena of the type of water hammer producing untimely acceleration of the spacecraft. This is particularly the case when the gaseous composition comprises nitrogen.
  • the invention therefore aims to overcome all these drawbacks by proposing a method and a device for emptying a pressure vessel spacecraft, which are simple, inexpensive, and whose operation can be certified in all possible assumptions of pressure and temperature that may be encountered at the moment of triggering this emptying, especially at the end of the mission (normal or triggered).
  • the invention aims at providing such a method and such a device for emptying which make it possible to obtain a controlled emptying, in particular whose duration is controlled before it is triggered, and which is fast enough to be able to intervene before the production of other passivation steps.
  • the invention also aims at providing such a method and such a draining device that can be designed to generate a minimal disturbing thrust, theoretically almost zero, on the spacecraft during emptying.
  • the invention also aims at providing such a method and such a draining device in which the triggering of the emptying can be controlled simply and inexpensively, for example by a simple controlled valve (electromagnetic or pyrotechnic or other).
  • the invention also aims at providing such a method and such a draining device that can be used with all types of gaseous fluids.
  • the invention also aims to propose a solution that is robust, long-lasting, and compatible with the constraints of certification, manufacturing and use of space systems.
  • the invention relates to a method of emptying a spacecraft enclosure containing a gas composition under a pressure P1 greater than that P2 prevailing in an environment outside the spacecraft in space, the enclosure being connected to this external environment of the space by at least one evacuation line, characterized in that the gaseous composition circulating in each discharge line passes through at least one initial expansion device having at least one section throat disposed in each discharge line enters at least one inlet end of the discharge pipe in fluid communication with the interior of the enclosure and at least one narrow section outlet end of the exhaust pipe opening into said external environment, the pressure of the gas composition at the outlet of each initial expansion device being at a third value Pi intermediate between the first pressure P1 in the chamber and the second pressure P2 of the external environment.
  • pipe generally designates any device capable of ensuring fluid communication between at least one inlet of this device and at least one outlet of this device and furthermore hermetically isolated from the environment. outside.
  • a pipe may have several inputs and / or several outputs.
  • the term “enclosure” designates any hermetically sealed space capable of enclosing an at least partially gaseous composition; it may be in particular a tank as well as a plurality of tanks connected to each other by one or more pipes.
  • the expansion of the gaseous composition in each discharge pipe takes place in at least two successive stages: a first initial step inside the evacuation pipe, and a second step at the outlet of said discharge pipe, via each outlet end with a narrow section of the evacuation pipe opening into said external environment.
  • the initial expansion inside an exhaust pipe is mainly isenthalpic, while the expansion at the narrow section outlet of an exhaust pipe is mainly isentropic.
  • the invention extends to a device for implementing a method according to the invention. It therefore also concerns an initial expansion device for emptying a spacecraft enclosure containing a gaseous composition under a pressure P1 greater than that P2 prevailing in an environment outside the spacecraft in space, comprising at least one evacuation pipe connecting the enclosure to this outside environment of the space, characterized in that each evacuation pipe incorporates at least one device initial expansion device having at least one section throat disposed in each discharge line between at least one inlet end of the evacuation pipe in fluid communication with the interior of the enclosure and at least one outlet end with a narrow section of the evacuation pipe opening into said external environment, the pressure of the gas composition at the outlet of each initial expansion device being at a third value Pi intermediate between the first pressure P1 and the second pressure P2.
  • any expansion device having at least one sectional throat capable of being incorporated in a discharge pipe may be envisaged as an initial expansion device within the scope of the invention.
  • an initial expansion device is a completely static device, that is to say free of moving parts.
  • Such a throat section provides indeed an initial relaxation mainly isenthalpic, the wall of the discharge pipe being sufficiently thermally insulating, or even equipped with a heating system, to ensure mainly adiabatic relaxation conditions with a decrease in temperature as low as possible.
  • the advantage of such isenthalpic expansion is to allow to obtain a large decrease in pressure with a small variation in temperature, while maintaining the kinetic energy of the fluid (especially with a sufficient flow rate and without inducing residual thrust on the evacuation pipe).
  • Such an initial expansion device having at least one sectional throat also makes it possible to determine the output flow rate (as a function only of the value of the pressure at the inlet), and thus to obtain a minimal thrust at the outlet of the duct. evacuation and control the duration of the emptying so that it is determined with sufficient precision in advance (at the launch of the spacecraft).
  • any throat section can be considered in this respect (passage orifice or neck, preferably sonic (for the values provided by the pressure P1), capillary ).
  • at least one initial expansion device is a capillary pipe interposed in the discharge pipe so as to be traversed by the gas composition.
  • a capillary pipe is interposed in series in the discharge pipe so as to be traversed by all the gaseous composition circulating in the discharge pipe. It has an upstream orifice in which the gaseous composition is forced to penetrate under pressure, and a downstream orifice delivering in the evacuation pipe the gaseous composition expanded at the intermediate pressure Pi.
  • Such a capillary tube may advantageously be wound helically around the a rigid support incorporated in the evacuation pipe.
  • Such a capillary pipe has the particular advantage of being able to be manufactured accurately at low cost and to withstand high input pressure values.
  • each capillary tube has an internal diameter of between 10 ⁇ m and 100 ⁇ m, in particular of the order of 30 ⁇ m to 50 ⁇ m, and a developed length of between 1 cm. and 100 cm -particularly of the order of 4 cm to 20 cm-. Any other embodiment is conceivable.
  • the latter has a downstream portion extending between the outlet of the initial expansion device
  • the gaseous composition is ejected from each discharge pipe into the external environment by passing through at least one section-restricted outlet orifice -particularly a sonic exit orifice-from each outlet end of each evacuation pipe.
  • a sonic outlet opening at each outlet end of each discharge conduit provides a predominantly isentropic expansion between said intermediate pressure and the pressure of the external environment in space.
  • the invention also relates to a device for emptying an end-of-mission spacecraft enclosure containing a gaseous composition under a pressure P1 greater than that P2 prevailing in an environment outside the spacecraft in space.
  • the enclosure being connected to this external environment of the space by at least one evacuation pipe, characterized in that each discharge pipe has a downstream portion forming each outlet end of the discharge pipe, this portion downstream having at least one pair of sectionally restricted-sonically opposed-sectioned outlet ports for producing opposing or zero-output thrusts
  • said downstream portion is formed of at least one pair of coaxial tubes extending in opposite directions to each other, each tube of this downstream portion having an outlet orifice with a sectional throat - especially sonic -.
  • the downstream portion of each discharge line may be formed of a only pair of coaxial tubes in opposition, the evacuation pipe being in the general shape of T.
  • the evacuation pipe being in the general shape of T.
  • said downstream portion is connected in extension of an upstream section of the discharge pipe and each initial expansion device of the discharge pipe is incorporated in said upstream section.
  • At least one filtration device is disposed upstream of each initial expansion device with a sectional throat -particularly upstream of each capillary tube.
  • the gaseous composition circulating in each discharge line passes through at least one filtration device arranged upstream of an initial expansion device with a sectional throat -particularly upstream of an initial throttling device of section formed of a capillary pipe interposed in the discharge pipe so as to be traversed by the gaseous composition.
  • Such a filtering device is chosen so as to filter the particles capable of closing off such an initial expansion device with a narrow section.
  • a filtration device having a cutoff diameter smaller than the diameter of the sectional throat of the initial expansion device (capillary tube), preferably less than one-tenth of this diameter, in particular included between 0.1 ⁇ m and 10 ⁇ m.
  • the filtration device is adapted to have a maximum filtering surface and a negligible pressure drop.
  • the filtration device is disposed in the main tubular section of the portion downstream of each discharge pipe, upstream of each initial expansion device (capillary pipe in particular).
  • a drainage device advantageously comprises for each discharge pipe, at least one controlled valve adapted to close said discharge pipe, and to be able to open, on command, said evacuation pipe and put said enclosure in fluid communication with said external environment.
  • a controlled valve may be an electromagnetic valve or a pyrotechnic valve or any other valve that can be controlled by a control device integrated into the spacecraft or from the ground (remote control).
  • this controlled valve is disposed in the exhaust pipe as far upstream as possible, in particular upstream of each initial expansion device. None, however, prevents alternatively to have a valve controlled downstream of an initial expansion device, or even in the downstream portion of the exhaust pipe or at the outlet ends of the latter. If the discharge pipe has several inlet ends and / or several outlet ends, it is possible to provide a plurality of controlled valves.
  • the invention extends to a method implemented in a device according to the invention. It applies in particular to the emptying of a spacecraft enclosure in which the pressure difference between the pressure P1 prevailing in the chamber and the pressure P2 prevailing in the environment outside the spacecraft in the space is greater than 100,000 hPa, more particularly greater than 200,000 hPa, typically between 100,000 hPa and 1,000,000 hPa.
  • the invention also extends to a spacecraft - which may be in particular but not exclusively an artificial satellite - comprising at least one chamber containing a gaseous composition under a pressure and a device for emptying each chamber, characterized in that it comprises at least one emptying device according to the invention.
  • the invention also extends to a method of passivation at the end of the mission of a spacecraft according to the invention, characterized in that the emptying of each chamber of the spacecraft is carried out according to a method of emptying according to to the invention.
  • the invention also relates to a method and a device for emptying a spacecraft enclosure and a spacecraft characterized in combination by all or some of the characteristics mentioned above or below.
  • the spacecraft represented as an example on the figure 1 comprises a frame 10 carrying three reservoirs 11 of gas composition under pressure connected by different pipes to a device 12 for emptying comprising a controlled valve 13 and a pipe 14 of discharge.
  • the controlled valve 13 is connected on one side to the various lines in fluid communication with the tanks 11, and, on the other, at one end 16 of the inlet line 14 evacuation.
  • the controlled valve 13 may be a pyrotechnic valve or an electromagnetic valve which is normally closed and whose opening can be controlled by a control signal transmitted by a control unit (not shown) of the spacecraft or received from the ground ( remote control).
  • a control unit not shown
  • the controlled valve 13 When the valve 13 is closed, the gaseous composition contained in the tanks 11 can not escape through the evacuation pipe 14.
  • the valve 13 is open, the gaseous composition under pressure contained in the tanks 11 can flow through this valve 13 itself connected in fluid communication with the discharge pipe 14, the inside of the tanks 11 being in fluid communication with the external environment of the spacecraft (Interplanetary space when the spacecraft is an artificial satellite) which is at the pressure of the space vacuum.
  • the evacuation pipe 14 comprises an upstream section 15 connected to the valve 13 and extending from the latter, this upstream section 15 forming the inlet end 16 of the evacuation pipe 14, and having one end 18 downstream.
  • the evacuation pipe 14 is fixed to the frame 10 by a fastening tab 30, for example at the downstream end 18 of the upstream section 15.
  • the evacuation pipe 14 has a downstream portion 17 forming an outlet chamber and having at least one pair of outlet orifices 19a, 19b adapted to deliver gas flows at the outlet in directions opposite to each other, preferably at least substantially coaxial. In this way, the reaction thrusts formed by these gas flows are opposite, the result of the reaction forces of the emptying on the frame 10 being theoretically zero and in practice minimized.
  • the downstream portion 17 is formed of two tubes 17a, 17b extending in opposite directions to each other from the downstream end 18 of the upstream section, each tube 17a 17b of the downstream portion forming one of the outlet orifices 19a, 19b.
  • the upstream section 15 is, in the example shown, a straight tubular section. There is nothing to prevent the downstream section of the evacuation pipe 14 from having any other shape which is more or less curved, but in any case it is possible to define a longitudinal direction of the upstream section 15 at the end 18 downstream of the latter (tangent to the median line of the upstream section 15).
  • the two tubes 17a, 17b extend at least substantially orthogonally to this longitudinal direction of the upstream section 15 at the downstream end 18 of the latter so as to ensure a balanced distribution of the gas flow in each of the two tubes 17a, 17b .
  • the outlet orifices 19a, 19b are oriented relative to the frame 10 of the spacecraft so as to minimize the impact of any residual thrust produced by the gas flows escaping from the outlet orifices 19a, 19b. at the opening of the valve 13.
  • the device 12 for emptying according to the invention is mounted on the frame 10 of such so that the direction of the tubes is preferably parallel to the maximum direction of inertia of the frame 10 and / or the spacecraft.
  • the opposite directions of the outlet orifices 19a, 19b may be non-aligned on the maximum directions of inertia and see their directions determined according to the arrangement of the spacecraft in the vicinity holes. Indeed, the interaction of the fluid jets with the spacecraft can create a force and a resultant torque non-negligible, which should be minimized. Interactions with the spacecraft jets escaping ports 19a and 19b have no reason to be equal. Indeed, even if the orifices 19a and 19b have opposite directions, this symmetry can be destroyed by the arrangement of the spacecraft which may not be identical to the vicinity of the two orifices 19a and 19b. As a result, the interactions of each orifice with the spacecraft do not cancel each other out: a torque and a resultant force appear. This torque and force can be determined by software simulation and minimized in the same way.
  • the upstream section incorporates, from the inlet end 16, a particle filter 20 traversed by the gas composition from the tanks 11, and, downstream of the filter 20, an initial expansion device 21 also traversed by the gaseous composition from the tanks 11.
  • the initial expansion device 21 comprises a capillary tube 22 wound helically around a hollow cylindrical support 23 extending inside the evacuation pipe 14 from a collar 24 for fastening the device 21 for expansion. initially relative to the upstream section of the evacuation pipe 14.
  • the collar 24 is interposed between two cylindrical sleeves 31, 32 of outer wall forming the upstream portion 15, which reliably resists at any upstream pressure value.
  • the collar 24 is welded to the two sleeves 31, 32 of the upstream section 15 of the pipe 14 of discharge.
  • the support 23 has an orifice 25 allowing the passage of the capillary tube 22 inside the support 23, the capillary tube 22 being extended axially upstream through an axial bore 26 of the collar 24.
  • This bore 26 has an end 27 upstream traversed hermetically by the capillary pipe 22 which thus has an open upstream end 28 in the discharge pipe 14 immediately downstream of the filter 20, the gas composition can penetrate into this upstream end 28 of the capillary pipe 22.
  • the capillary pipe 22 also comprises a downstream end 29 open in the downstream discharge pipe 14 towards the downstream end 18 of the upstream section.
  • the gaseous composition that escapes from the end of the capillary pipe 22 supplies the downstream portion 17 of the evacuation pipe 14. It is then distributed in the two tubes 17a, 17b and is ejected via the orifices 19a, 19b output.
  • the filter 20 is chosen so as to filter the particles at the inlet of the capillary pipe 22, for example with a cut-off diameter of the order of costs less than 1 ⁇ m. It should be noted that such a filter 20 can also provide a mainly isenthalpic expansion of the gas composition, but is preferably chosen to have a maximum filtering surface and a minimal pressure drop, substantially without expansion of the fluid.
  • the gaseous composition from the tanks 11 thus circulates between the filter 20 and the downstream portion 17 through the capillary pipe 22, which constitute initial essentially isenthalpic expansion devices.
  • the capillary pipe 22 determines the flow rate of the gaseous composition flowing through the orifices 19a, 19b output of the discharge pipe 14 when the valve 13 is open.
  • the gaseous composition is at an intermediate pressure Pi between the pressure P1 of the gaseous composition in the tanks 11 and the pressure P2 of the external environment (vacuum pressure).
  • the outlet orifices 19a, 19b are sonic orifices in the form of isentropic tuyeres, that is to say they are adapted to provide a mainly isentropic expansion between the intermediate pressure Pi prevailing in the portion 17 downstream, and the substantially zero pressure P2 of the external environment in space.
  • the characteristics of the capillary pipe 22 can be adapted to provide an intermediate pressure value Pi which makes it possible to prevent any liquid phase formation. and / or solid in the evacuation pipe 14, and in particular at the outlet orifices 19a, 19b.
  • an intermediate pressure Pi is selected, avoiding any liquefaction of the residual water that may be contained in the gaseous composition.
  • the characteristics of the capillary pipe 22 and the outlet orifices 19a, 19b are, for one thing, determined from the maximum value that can be encountered for the pressure P1 of the gas composition coming from the tanks 11, that is to say when these reservoirs 11 are full when launching the spacecraft.
  • the characteristics of the capillary pipe 22 are also chosen so as to allow, moreover, the preceding conditions (relaxation mainly isenthalpic, absence of liquefaction during expansion) being fulfilled, obtaining a maximum discharge rate.
  • an only isentropic expansion not in accordance with the invention represented by the curve C1 causes the liquefaction of the gas composition at a pressure greater than 10 bar (10 000 hPa) and a temperature greater than 110 K.
  • an expansion only isentropic not according to the invention represented by the curve C5 causes the liquefaction of the gas composition at a pressure greater than 5 bar (5000 hPa) and a temperature of the order of 100 K.
  • the characteristics of the capillary pipe 22 and the diameter of the sonic outlet apertures 19a, 19b are advantageously chosen so that the intermediate pressure Pi is less than 5 bar (5000 hPa), more particularly less than 4 bar (4 bar).
  • 000 hPa) for a temperature of 243 K and less than 20 bar (20 000 hPa), more particularly less than 15 bar (15 000 hPa) for an initial temperature of 318 K.
  • the flow rate provided by such a capillary tube may be between 21 mg / s and 16 mg / s, in particular of the order of 20 mg / s.
  • the emptying time of tanks 11 having a total of 8.3 kg of gaseous composition is then between 65 days and 75 days, in particular of the order of 70 days (the emptying being considered complete once the pressure is considered enough low, ie of the order of 1 bar (10 5 Pa)).
  • the isenthalpic expansion produces a slight drop in temperature.
  • a gaseous composition having a low Joule-Thomson inversion temperature helium, hydrogen, etc.
  • the initial essentially isenthalpic expansion produces an increase in temperature, all the more so preventing the inadvertent formation of the liquid phase.
  • the invention thus makes it possible to carry out a fast, reliable emptying process in a simple and inexpensive manner.
  • the spacecraft may be subjected to a passivation process at the end of the mission according to the invention, the other general characteristics of which are described for example by FR2896773 and incorporating this emptying method according to the invention.
  • the filters 20 and the capillary tube 22 may be completed and / or replaced by any other section-throat device adapted to perform an initial mainly isenthalpic expansion (orifice (s) in a transverse plate ).
  • the downstream portion 17 may be formed otherwise than by two opposing tubes (cylindrical chamber with diametrically opposite orifices) ...
  • the spacecraft according to the invention may be formed of an artificial satellite intended to be placed in terrestrial orbit, or any other spacecraft (launcher, shuttle, space probe, orbital station, lunar or martian module ).

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Jet Pumps And Other Pumps (AREA)
EP14171603.5A 2013-06-11 2014-06-06 Verfahren und Gerät zur Leerung eines Behälters eines Raumfahrzeugs Active EP2813433B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1355398A FR3006672B1 (fr) 2013-06-11 2013-06-11 Procede et dispositif de vidange d'une enceinte d'engin spatial

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EP2813433A2 true EP2813433A2 (de) 2014-12-17
EP2813433A3 EP2813433A3 (de) 2015-05-20
EP2813433B1 EP2813433B1 (de) 2016-10-19

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FR (1) FR3006672B1 (de)

Cited By (1)

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WO2017017333A1 (fr) * 2015-07-30 2017-02-02 Airbus Safran Launchers Sas Dispositif et procédé d'aérofreinage et de passivation de satellite

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Publication number Priority date Publication date Assignee Title
FR2896773A1 (fr) 2006-01-31 2007-08-03 Cnes Epic Procede de passivation fluidique d'un satellite en fin de mission

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FR2730831B1 (fr) * 1995-02-22 1997-06-13 Centre Nat Etd Spatiales Dispositif de pressurisation d'un sous-systeme de propulsion biliquide unifie d'un satellite geostationnaire
US6141497A (en) * 1995-06-09 2000-10-31 Marotta Scientific Controls, Inc. Multilayer micro-gas rheostat with electrical-heater control of gas flow
FR2871441B1 (fr) * 2004-06-10 2006-09-15 Eads Astrium Sas Soc Par Actio Procedes de detection de la vidange complete d'un reservoir d'ergol et de gestion d'ergol a bord d'un satellite
GB2460443A (en) * 2008-05-29 2009-12-02 Inmarsat Global Ltd Propulsion system arrangement for decommissioning a satellite

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2896773A1 (fr) 2006-01-31 2007-08-03 Cnes Epic Procede de passivation fluidique d'un satellite en fin de mission

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017017333A1 (fr) * 2015-07-30 2017-02-02 Airbus Safran Launchers Sas Dispositif et procédé d'aérofreinage et de passivation de satellite
FR3039521A1 (fr) * 2015-07-30 2017-02-03 Centre Nat D'etudes Spatiales C N E S Dispositif et procede d'aerofreinage et de passivation de satellite

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FR3006672B1 (fr) 2016-12-09
EP2813433A3 (de) 2015-05-20
EP2813433B1 (de) 2016-10-19
FR3006672A1 (fr) 2014-12-12

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