WO2016164004A1 - Réservoir de propergol et chargement pour propulseur par électronébulisation - Google Patents

Réservoir de propergol et chargement pour propulseur par électronébulisation Download PDF

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Publication number
WO2016164004A1
WO2016164004A1 PCT/US2015/024827 US2015024827W WO2016164004A1 WO 2016164004 A1 WO2016164004 A1 WO 2016164004A1 US 2015024827 W US2015024827 W US 2015024827W WO 2016164004 A1 WO2016164004 A1 WO 2016164004A1
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WO
WIPO (PCT)
Prior art keywords
porous
tank
propellant
opening
beaker
Prior art date
Application number
PCT/US2015/024827
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English (en)
Inventor
Paulo C. LOZANO
Corey Patrick FUCETOLA
Original Assignee
Massachusetts Institute Of Technology
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 Massachusetts Institute Of Technology filed Critical Massachusetts Institute Of Technology
Priority to PCT/US2015/024827 priority Critical patent/WO2016164004A1/fr
Publication of WO2016164004A1 publication Critical patent/WO2016164004A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/405—Ion or plasma engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • F03H1/0006—Details applicable to different types of plasma thrusters
    • F03H1/0012—Means for supplying the propellant

Definitions

  • the technology generally relates to electrospray thrusters, and more specifically, to electrospray thruster tanks and methods and devices for loading propellant into electrospray thrusters.
  • Ionic liquids are molten salts at room temperature and exhibit extremely low vapor pressures. ILs are formed by positive and negative ions which can be directly extracted and accelerated to produce thrust when used in bipolar operation. ILs have been shown to emit a purely ionic current when exposed to a strong applied potential. ILs generate a substantially pure ionic emission and have a relatively low starting voltage (e.g., less than approximately 2 kV required to generate ions from the Taylor Cone). ILs allow for a scalable specific impulse of the electrospray emitter(s) from approximately 500 seconds to 5000+ seconds. Some ILs can display super-cooling tendencies in which they remain as liquids well below their nominal freezing points.
  • ILs exhibit appreciable electrical conductivity at room temperature, making them suitable for electrostatic deformation and subsequent Taylor Cone formation.
  • ILs are thermally stable over a wide range of temperatures (they do not boil, but decompose at temperatures ⁇ 250-500°C) and are apparently non-toxic being able to be used with applications with green standards, such as in the synthesis and catalysis of chemical reactions.
  • ILs have low vapor pressures at, or moderately above, their melting points. This allows for use in high vacuum equipment in open architectures such as externally wetted needles/emitters.
  • ion sources using ILs can be used to provide thrust in a variety of applications.
  • electrospray thrusters can use an array of needle-like tips in a porous substrate to emit ions, thereby providing thrust (e.g., to move small satellites). Ions can be delivered to the emitter tips by an ionic liquid propellant that is transported to the tips, e.g., by capillary forces.
  • the technology described herein relates to propellant tanks for electrospray thrusters and/or methods for filling such tanks with propellant.
  • some embodiments of the technology relate to propellant tanks for electrospray thrusters configured to permit gas to enter and leave the tanks in response to environmental changes.
  • embodiments of the technology can provide methods and apparatus for adding propellant to electrospray thruster tanks by imbibing porous structures in electrospray thrusters with propellant (e.g., ionic liquid) while facilitating minimizing trapped gases in the porous structures.
  • propellant e.g., ionic liquid
  • the thruster assembly includes a tank including a first opening and a second opening; a porous emitter array disposed over the first opening; a porous reservoir disposed substantially within an interior of the tank, wherein the porous reservoir is in fluid communication with the porous emitter array through the first opening.
  • the method includes disposing a first end of a beaker in the second opening of the tank, wherein the beaker contains propellant, and wherein the first end of the beaker includes a breakaway bottom.
  • the method includes placing the thruster assembly and beaker in a first environment, wherein the first environment is one of a substantial vacuum and/or an environment composed substantially of gases that can be absorbed by the propellant.
  • the method includes depressing a plunger in the beaker to cause the breakaway bottom of the beaker to break and cause the propellant to flow into the tank.
  • the method includes removing the thruster assembly from the first environment.
  • the method includes removing the beaker from the second opening.
  • the method can include affixing a cap to the second opening of the tank.
  • the cap includes a porous membrane that permits gas to pass therethrough and blocks the propellant from passing therethrough.
  • first pores of the porous membrane are larger than second pores of the porous emitter array.
  • the porous membrane is made from at least one of Teflon, peek and polyethylene.
  • the tank includes a porous membrane that permits gas to pass therethrough and blocks the propellant from passing therethrough.
  • the method can include extending the plunger into the tank to compress the porous reservoir, thereby at least partially submerging the porous reservoir in the propellant and retracting the plunger from the tank.
  • the assembly can include a thruster assembly.
  • the thruster assembly can include a tank including a first opening and a second opening; a porous emitter array disposed over the first opening; and a porous reservoir disposed substantially within an interior of the tank, wherein the porous reservoir is in fluid
  • the assembly can include a beaker having a first end including a breakaway bottom, wherein the first end of the beaker is disposed in the second opening.
  • the beaker is filled with propellant.
  • the assembly includes a plunger disposed in the beaker to cause the breakaway bottom of the beaker to break and cause the propellant to flow into the tank when depressed.
  • the thruster assembly includes a tank including a first opening and a vent.
  • the thruster assembly includes a porous emitter array disposed over the first opening.
  • the thruster assembly includes a porous reservoir disposed substantially within an interior of the tank, wherein the porous reservoir is in fluid
  • the vent includes a porous membrane that permits gas to pass therethrough and blocks a propellant from passing therethrough.
  • first pores of the porous membrane are larger than second pores of the porous emitter array.
  • the porous membrane is made from at least one of Teflon, peek and polyethylene.
  • the thruster assembly includes a tank including a first opening, wherein the tank is formed from one or more semi-permeable materials that permit gas to pass therethrough and block a propellant from passing therethrough.
  • the thruster assembly includes a porous emitter array disposed over the first opening.
  • the thruster assembly includes a porous reservoir disposed substantially within an interior of the tank, wherein the porous reservoir is in fluid communication with the porous emitter array through the first opening.
  • first pores of the tank are larger than second pores of the porous emitter array.
  • the tank is formed from at least one of porous PTFE and/or hydrophobic solgel.
  • the thruster assembly can include a propellant container disposed within the interior of the tank, wherein the propellant container is formed from second one or more semi-permeable materials that permit gas to pass therethrough and block a propellant from passing therethrough; and wherein the porous reservoir is disposed partially within an interior of the propellant container.
  • first pores of the propellant container are larger than second pores of the porous emitter array.
  • the propellant container is formed from at least one of porous PTFE or hydrophobic solgel.
  • FIG. 1 is a cross-section view of an illustrative electrospray thruster assembly.
  • FIG. 2 is a cross-section view of the electrospray thruster assembly and a beaker.
  • FIG. 3 is a cross-section view of the electrospray thruster assembly and the beaker in a vacuum chamber.
  • FIG. 4 is a cross-section view of the electrospray thruster assembly and the beaker in a vacuum chamber after a plunger has been depressed.
  • FIG. 5 is a cross-section view of the electrospray thruster assembly exposed to atmospheric pressure.
  • FIG. 6 is a cross-section view of the electrospray thruster assembly with a cap.
  • FIG. 7 is a cross-section view of an electrospray thruster assembly.
  • FIG. 1 is a cross-section view of an illustrative electrospray thruster assembly
  • Electrospray thruster assembly 100 includes porous emitter array 105. Porous emitter array 105 is mounted on emitter package 110. Emitter package 1 10 is mounted on tank 115. Porous reservoir material 120 is disposed in interior 125 of tank 115. Tank 115 includes a first opening 130 through which porous reservoir material 120 passes, permitting porous emitter array 105 to be disposed against and in fluid communication with porous reservoir material 120. Tank 115 also includes second opening 135 for adding propellant (e.g., ionic liquid) to tank 1 15.
  • propellant e.g., ionic liquid
  • each of the porous emitter array 105 and porous reservoir material 120 can include a pore size gradient that decreases in the direction from porous reservoir material 120 to porous emitter array 105, such that ionic liquid can be transported from porous reservoir material 120 to porous emitter array 105 through capillarity.
  • porous emitter array 105 can have smaller-sized pores than porous reservoir material 120.
  • porous emitter array 105 and porous reservoir material 120 imbibe propellant in tank 1 15.
  • emitter array 105 can be fabricated from a dielectric material (e.g., a polymeric, ceramic, glass, sol-gel, xerogel, aerogel, or other oxide material).
  • the emitter array 105 can be fabricated from a metal material (e.g., silver, stainless steel, tungsten, nickel, magnesium, molybdenum, titanium, any combination thereof, or any of these metals coated with a noble metal material such as platinum or gold).
  • porous reservoir material 120 can be fabricated from a dielectric material (e.g., a ceramic, glass, or other oxide material).
  • porous reservoir material 120 can be fabricated from a polymeric material (e.g., a polyurethane, or other open cell foam material).
  • porous reservoir material 120 can be made from a metal material (e.g., silver, stainless steel, tungsten, nickel, magnesium, molybdenum, titanium, any combination thereof, or any of these metals coated with a noble metal material such as platinum or gold).
  • Tank 1 15 can be fabricated from any material that is impermeable by the propellant (e.g., ionic liquid), such as PEEK, PTFE or other impermeable compatible materials.
  • electrospray thruster assembly 100 can use porous emitter array 105 to emit ions, which can provide thrust (e.g., to move small satellites). Ions are delivered to the tips of porous emitter array 105 in the form an ionic liquid that is transported to the tips by, e.g., capillary forces.
  • the operation of electrospray thrusters is described in greater detail in U.S. Application No. 13/839,064, filed March 15, 2013, the contents of which are hereby incorporated by reference.
  • porous emitter array 105 can imbibe ionic liquid during operation.
  • approximately perfect imbibation of the ionic liquid can beneficially increase performance of electrospray thruster assembly 100 (e.g., by more efficiently producing thrust) and mitigate contamination of the porous materials.
  • approximately perfect imbibation of the ionic liquid can extend the lifetime of electrospray thruster assembly 100. Poor imbibition (e.g., when gas is trapped within the pores of porous emitter array 105 and/or porous reservoir material 120) can reduce the efficiency and lifespan of electrospray thruster assembly 100.
  • the technology described herein can improve imbibition by porous emitter array 105 and/or porous reservoir material 120.
  • the technology can be used to add propellant to an electrospray thruster assembly (e.g., electrospray thruster assembly 100).
  • an electrospray thruster assembly e.g., electrospray thruster assembly 100.
  • a beaker with a breakaway bottom can be used to fill the tank of an electrospray thruster while it is under vacuum.
  • the pores of the porous materials in the electrospray thruster can be filled with propellant and the electrospray thruster can then be placed under atmospheric pressure.
  • the tank can then be sealed with a cap.
  • the tank can be vented to allow gases to enter and leave the tank in response to pressure changes in the surrounding environment.
  • FIG. 2 is a cross-section view of electrospray thruster assembly 100 and beaker
  • electrospray thruster assembly 100 and beaker 140 can be placed in vacuum chamber 160 to place electrospray thruster assembly 100 and beaker 140 under vacuum.
  • electrospray thruster assembly 100 and beaker 140 can be put under vacuum in vacuum chamber 160 for an amount of time sufficient to remove gas trapped in the parts of electrospray thruster assembly 100 (e.g., including inside porous emitter array 105, propellant 150, and porous reservoir material 120).
  • the pressure in the vacuum chamber can be monitored to determine when substantially all of the trapped gas has been removed.
  • the pressure in the vacuum chamber can fluctuate (e.g., when a small amount of trapped gas is released, the pressure in the vacuum chamber can go from le-7 to greater than le-6 Torr). In some embodiments, the subsiding of such fluctuations indicates substantially all of the trapped gas has been removed. In some embodiments a residual gas analyzer can monitor the chamber to determine when substantially all of the trapped gas has been removed. In some embodiments, electrospray thruster assembly 100 and beaker 140 can be placed in an environment composed substantially of gases that can be absorbed by the propellant instead of a vacuum.
  • plunger 145 can be depressed. In accordance with the technology, depressing plunger 145 can cause breakaway bottom 155 to break and force propellant 150 into tank 115. In some embodiments, the pressure created by compressing propellant 150 with plunger 145 can cause breakaway bottom 155 to break. In some embodiments, plunger 145 can be configured to pierce breakaway bottom 155 when depressed. In some embodiments, plunger 145 can be configured to extend into tank 115 to compress porous reservoir material 120 so that porous reservoir material 120 is submerged in propellant 150. In some embodiments, after the emitter has imbibed propellant, plunger 145 can be further configured to retract back into the beaker to allow the reservoir material 120 to sponge up (or imbibe) the propellant 150. FIG.
  • FIG. 4 is a cross-section view of electrospray thruster assembly 100 and beaker 140 in vacuum chamber 160 after plunger 145 has been depressed. As illustrated, after breakaway bottom 155 breaks, propellant 150 can enter tank 115 of electrospray thruster assembly 100. Beneficially, the pores of porous emitter array 105 and porous reservoir material 120 are evacuated so gas is not trapped in the pores when propellant 150 is added to tank 115.
  • FIG. 5 is a cross-section view of electrospray thruster assembly 100 exposed to atmospheric pressure.
  • the external atmospheric pressure can collapse voids inside porous emitter array 105 and porous reservoir material 120 created when propellant 150 filled tank 1 15 while under vacuum.
  • propellant 150 has been sponged up by and is contained within porous emitter array 105 and porous reservoir material 120.
  • propellant 150 can prevent atmospheric gases such as 2 from entering porous emitter array 105 and porous reservoir material 120. Instead, atmospheric gas can be trapped in second opening 135 and/or the space between porous reservoir material 120 and interior wall 165 of tank 115.
  • Propellant 150 can absorb atmospheric gases such as CO2 and H 2 0.
  • gas 150 can absorb atmospheric gases such as CO2 and H 2 0.
  • FIG. 6 is a cross-section view of electrospray thruster assembly 100 with cap 170 sealing second opening 135.
  • cap 170 can be inserted over and/or in second opening 135 to seal tank 115.
  • Cap 170 can be attached with epoxy, sealed with an o-ring and/or any other pressure tight seal.
  • Cap 170 includes at least one porous membrane 175 that permits gas to enter and leave tank 1 15 in response to pressure changes.
  • gas released from propellant 150 can move through the space between porous reservoir material 120 and interior wall 165 of tank 1 15 to exit tank 1 15 through porous membrane 175 of cap 170.
  • Cap 170 can include a barrier to prevent porous membrane 175 from being blocked by, sealed to, or in contact with propellant-filled reservoir 120.
  • Porous membrane 175 can be made from a porous material that is non-wettable by the propellant.
  • porous material can be made from Teflon, peek or polyethylene.
  • porous membrane 175 can be made of more than one layer of porous material.
  • porous membrane 175 can be a made of multiple layers of porous materials that are spaced apart to prevent fluid flow from one to the next while still allowing gas transport.
  • the pore size of porous membrane 175 can be larger than the pore size of emitter array 105. This can prevent gas inside tank 1 15 from causing the ejection of propellant 150 from emitter array 105. Beneficially, this can allow electrospray thruster assembly 100 to be exposed to a variety of atmospheric conditions while substantially eliminating leakage of propellant 150 outside of tank 1 15.
  • a portion or substantially the entire tank can be made of a porous material that is impermeable to the propellant, e.g., porous PTFE, hydrophobic sol-gel (aerogel or xerogel).
  • a permeable propellant container can be contained within an outer tank.
  • FIG. 7 is a cross-section view of electrospray thruster assembly 700.
  • Container 717 is disposed in tank 715.
  • Container 717 can be filled with propellant 750 as described above.
  • propellant 750 resides in tank 717 and porous material 720 can serve as a wick to deliver propellant 750 to porous emitter array 705 (e.g., via capillarity).
  • Container 717 can be made of a porous material that is impermeable to the propellant to permit gas to enter and leave container 717.
  • container 717 can be composed of multiple porous materials that can be spaced apart to prevent fluid flow from one to the next while still allowing gas transport.
  • Tank 715 can be made of a porous material that is impermeable to the propellant to permit gas to enter and leave tank 715.
  • the pore size of tank 715 and/or container 717 can be larger than the pore size of emitter array 705. This can prevent gas inside tank 715 and/or container 717 from causing the ejection of propellant 750 from emitter array 705.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)

Abstract

L'invention concerne des procédés et un appareil d'ajout de propergol dans un ensemble propulseur. Une première extrémité d'un bécher est disposée dans une ouverture du réservoir, le bécher contenant le propergol et la première extrémité du bécher comprenant un fond cassable. L'ensemble propulseur et le bécher sont placés dans un premier environnement, le premier environnement étant sensiblement un vide et/ou un environnement composé sensiblement de gaz qui peuvent être absorbés par le propergol. Un piston dans le bécher est enfoncé pour amener le fond cassable du bécher à se rompre et le propergol à s'écouler dans le réservoir de l'ensemble propulseur. L'ensemble propulseur est retiré du premier environnement et le bécher est retiré à partir de l'ouverture. Un capuchon est ajouté pour compléter l'assemblage. L'ensemble contient un évent pour permettre aux gaz de s'échapper de l'intérieur du réservoir.
PCT/US2015/024827 2015-04-08 2015-04-08 Réservoir de propergol et chargement pour propulseur par électronébulisation WO2016164004A1 (fr)

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PCT/US2015/024827 WO2016164004A1 (fr) 2015-04-08 2015-04-08 Réservoir de propergol et chargement pour propulseur par électronébulisation

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PCT/US2015/024827 WO2016164004A1 (fr) 2015-04-08 2015-04-08 Réservoir de propergol et chargement pour propulseur par électronébulisation

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019048497A1 (fr) 2017-09-05 2019-03-14 Centre National De La Recherche Scientifique Générateur de faisceau ionique à nanofils

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4855604A (en) * 1985-05-17 1989-08-08 Air Products And Chemicals, Inc. Ion Beam implant system
US5018634A (en) * 1989-09-12 1991-05-28 Aerospatiale Societe Nationale Industrielle Suspended skin for thermal insulation of cryogenic propellants
US20120024421A1 (en) * 2009-03-30 2012-02-02 Eric Boutet Device for fueling launcher thrusters
US20140054809A1 (en) * 2008-05-06 2014-02-27 Massachusetts Institute Of Technology Method and apparatus for a porous electrospray emitter

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4855604A (en) * 1985-05-17 1989-08-08 Air Products And Chemicals, Inc. Ion Beam implant system
US5018634A (en) * 1989-09-12 1991-05-28 Aerospatiale Societe Nationale Industrielle Suspended skin for thermal insulation of cryogenic propellants
US20140054809A1 (en) * 2008-05-06 2014-02-27 Massachusetts Institute Of Technology Method and apparatus for a porous electrospray emitter
US20120024421A1 (en) * 2009-03-30 2012-02-02 Eric Boutet Device for fueling launcher thrusters

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019048497A1 (fr) 2017-09-05 2019-03-14 Centre National De La Recherche Scientifique Générateur de faisceau ionique à nanofils
US11495429B2 (en) 2017-09-05 2022-11-08 Centre National De La Recherche Scientifique Ion beam generator with nanowires

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