EP3344873B1 - Propulseur ionique a grille avec agent propulsif solide integre - Google Patents

Propulseur ionique a grille avec agent propulsif solide integre Download PDF

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Publication number
EP3344873B1
EP3344873B1 EP16760449.5A EP16760449A EP3344873B1 EP 3344873 B1 EP3344873 B1 EP 3344873B1 EP 16760449 A EP16760449 A EP 16760449A EP 3344873 B1 EP3344873 B1 EP 3344873B1
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EP
European Patent Office
Prior art keywords
chamber
voltage source
thruster
plasma
radiofrequency
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EP16760449.5A
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German (de)
English (en)
French (fr)
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EP3344873A1 (fr
Inventor
Dmytro RAFALSKYI
Ane Aanesland
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Centre National de la Recherche Scientifique CNRS
Ecole Polytechnique
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Centre National de la Recherche Scientifique CNRS
Ecole Polytechnique
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    • 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
    • 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
    • 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
    • F03H1/0037—Electrostatic ion thrusters
    • F03H1/0043—Electrostatic ion thrusters characterised by the acceleration grid
    • 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
    • F03H1/0081—Electromagnetic plasma thrusters
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
    • H05H1/00—Generating plasma; Handling plasma
    • H05H1/54—Plasma accelerators

Definitions

  • the invention relates to a plasma thruster comprising an integrated solid propellant.
  • the invention relates more precisely to an ionic thruster, grid, comprising an integrated solid propellant.
  • the invention may find application for a satellite or a space probe.
  • the invention may find application for small satellites.
  • the invention will find an application for satellites having a mass of between 6 kg and 100 kg, possibly up to 500 kg.
  • a particularly interesting application case concerns the “CubeSat”, of which a basic module (U) weighs less than 1 kg and has dimensions of 10cm ⁇ 10cm ⁇ 10cm.
  • the plasma thruster according to the invention can in particular be integrated into a 1U module or a half-module (1 / 2U) and used in stacks of several modules by 2 (2U), 3 (3U), 6 (6U), 12 (12U) or more.
  • propellant is used here to denote a propellant in an ionic propellant, and not a product consisting of one or more propellants capable of supplying the propulsion energy of a rocket motor by chemical reaction.
  • a solid propellant plasma thruster has already been proposed. They can be classified into two categories, depending on whether they use a plasma chamber or not.
  • Teflon solid propellant
  • This electric discharge causes the ablation of the Teflon, its ionization and its acceleration mainly by electromagnetic means to generate an ion beam directly in the external space.
  • a laser beam is used to ablate and ionize a solid propellant, for example PVC. or Kapton®.
  • the acceleration of the ions is generally carried out electromagnetically.
  • an insulator is placed between an anode and a cathode, the whole being under vacuum.
  • the cathode metallic, serves as ablation material to generate ions.
  • the acceleration takes place electromagnetically.
  • the techniques described in this document make it possible to obtain a relatively compact propellant. Indeed, the solid propellant is ablated, ionized and the ions are accelerated to provide propulsion with an all-in-one device.
  • the ion beam is more or less controlled because there is no separate means for controlling the density of the plasma induced by the ablation of the solid propellant and the speed of the ions. Accordingly, the thrust and specific impulse of the thruster cannot be controlled separately.
  • This supply system can be used for any thruster using a plasma chamber.
  • the solid propellant (iodine I 2 , in this case) is stored in a tank.
  • a heating means is associated with the tank. This heating means may be an element capable of receiving external radiation, placed on the outside of the tank.
  • the diode is sublimated.
  • the diode in the gas state leaves the reservoir and is directed to a chamber, located remote from the reservoir, where it is ionized to form a plasma.
  • the ionization is carried out, in this case, by the Hall effect.
  • the flow of gas entering the plasma chamber is controlled by a valve arranged between the reservoir and this chamber. We can thus achieve better control of the sublimation of the diode and of the characteristics of the plasma, compared with the techniques described in document D1.
  • the characteristics of the ion beam exiting the chamber can then be controlled by means for extracting and accelerating the ions separated from the means used to sublimate the solid propellant and generate the plasma.
  • a propellant plasma thruster integrated in a plasma chamber has already been proposed in US 7,059,111 (D5).
  • This plasma thruster based on the Hall effect, is therefore likely to be more compact than that proposed in documents D2, D3 or D4. It is also capable of better controlling the evaporation of the propellant, the plasma and the extraction of the ions, compared to document D1.
  • the propellant is stored in the liquid state and uses an additional system of electrodes to control the flow of gas leaving the tank.
  • An objective of the invention is to overcome at least one of the aforementioned drawbacks.
  • the invention also relates to a satellite comprising a thruster according to the invention and an energy source, for example a battery or a solar panel, connected to the or each source of direct or alternating voltage of the thruster.
  • an energy source for example a battery or a solar panel
  • the invention also relates to a space probe comprising a thruster according to the invention and an energy source, for example a battery or a solar panel, connected to the or each source of direct or alternating voltage of the thruster.
  • an energy source for example a battery or a solar panel
  • FIG. 1 A first embodiment of an ion propellant 100 according to the invention is shown in figure 1 .
  • the propellant 100 comprises a plasma chamber 10 and a reservoir 20 of solid propellant PS housed in the chamber 10. More precisely, the reservoir 20 comprises a conductive envelope 21 comprising the solid propellant PS, this envelope 21 being provided with one or more orifices 22. The fact of accommodating the solid propellant reservoir 20 in the chamber 10 gives the propellant greater compactness.
  • the thruster 100 also includes a radiofrequency alternating voltage source 30 and one or more coils 40 supplied by the radiofrequency alternating voltage source 30.
  • the or each coil 40 may have one or more windings.
  • a single coil 40 comprising several windings is provided.
  • the coil 40 supplied by the radiofrequency alternating voltage source 30, induces a current in the reservoir 20, which is conductive (eddy current).
  • the current induced in the tank causes a Joule effect which heats the tank 20.
  • the heat thus produced is transmitted to the solid propellant PS by thermal conduction and / or thermal radiation. Heating the solid propellant PS then makes it possible to sublimate the latter, the propellant thus being put into the state of gas.
  • the propellant in the gas state then passes through the orifice (s) 22 of the reservoir 20, in the direction of the chamber 10.
  • This same assembly 30, 40 also makes it possible to generate a plasma in the chamber 10. by ionizing the propellant in the gas state which is in chamber 10.
  • the plasma thus formed will generally be an ion-electron plasma (it should be noted that, the plasma chamber will also include neutral species - propellant in the state of gas - because generally not all gas is ionized to form plasma).
  • the same source 30 of radiofrequency alternating voltage is therefore used to sublimate the solid propellant PS and create the plasma in the chamber 10.
  • a single coil 40 is also used for this purpose.
  • the chamber 10 and the reservoir 20 are initially at the same temperature.
  • the temperature of the reservoir 20, heated by the coil (s) 40 increases.
  • the temperature of the solid propellant PS also increases, the propellant being in thermal contact with the shell 21 of the tank.
  • the assembly formed by the source 30 and the coil (s) 40 makes it possible to generate the plasma in the chamber 10.
  • the solid propellant PS is then more fully heated by the charged particles of the plasma, the coil (s) being screened by the presence of the sheath in the plasma (skin effect) as well as by the presence of the charged particles themselves within the plasma.
  • the temperature of the tank 20 can be better controlled by the presence of a heat exchanger (not shown) connected to the tank 20.
  • One or more orifice (s) 22 can be provided on the reservoir 20, this does not matter. Only the total area of the orifice or, if several orifices are provided, of all of these orifices is of importance. Their size will depend on the nature of the solid propellant used, and the desired operating parameters for the plasma (temperature, pressure).
  • This sizing will therefore be carried out on a case-by-case basis.
  • the sizing of the propellant according to the invention will take up the following steps.
  • the volume of the chamber 10 is first of all defined, as well as the nominal operating pressure P2 desired in this chamber 10 and the mass flow rate m 'of positive ions desired at the outlet of the chamber 10. These data can be obtained by numerical modeling or by routine testing. It should be noted that this mass flow rate (m ′) corresponds substantially to that which is found between the reservoir 20 and the chamber 10.
  • the temperature T1 desired for the tank 20 is chosen.
  • This temperature T1 being fixed, it is possible to know the propellant pressure in the corresponding gas state, namely the pressure P1 of this gas in the tank 20 (cf. figure 13 in the case of diode I 2 ).
  • diiodine (I 2 ) diiodine (I 2 )
  • I 2 diodine
  • adamantane gross chemical formula: C 10 H 16
  • ferrocene formula crude chemical: Fe (C 5 H 5 ) 2
  • Arsenic can also be used, but its toxicity makes it a solid propellant whose use is less envisaged.
  • diiodine (I 2 ) will be used as solid propellant.
  • T the temperature in Kelvins.
  • the temperature can be considered to increase by about 50K.
  • the pressure of the iodine gas increases practically by a factor of 100, for a temperature increase of 50K.
  • the leakage of diode gas through the or each orifice 22 is very small, and of the order of 100 times less than the quantity of diode gas passing through the orifice (s) 22. towards the chamber 10, when the thruster 100 is in nominal operation.
  • a greater difference between the nominal operating temperature of the propellant according to the invention and its stopping temperature will only reduce the relative losses by leakage of propellant in the gas state.
  • a propellant 100 according to the invention using the diode (I 2 ) as propellant does not need to implement a valve for the or each orifice, unlike document D2.
  • the flow control of propellant in the gas state is carried out by controlling the temperature of the tank 20, by means of the power supplied to the coil 40 by the radiofrequency alternating voltage source 30 and possibly, as specified. previously, by the presence of a heat exchanger connected to the tank 20. The check is therefore different from that which is carried out in document D3.
  • the thruster 100 also comprises a means 50 for extracting and accelerating the charged particles of the plasma, positive ions and electrons, out of the chamber 20 to form a beam 70 of charged particles at the outlet of the chamber 20.
  • this means 50 comprises a grid 51 located at one end E (outlet) of the chamber 10 and an electrode 52 housed inside the chamber 10, this electrode 52 having by construction a larger area than that of the grid 51
  • the electrode 52 can be formed by the wall itself, conductive, of the reservoir 20.
  • the electrode 52 is isolated from the wall of the chamber by an electrical insulator 58.
  • the grid 51 may have orifices of different shapes, for example circular, square, rectangular or in the form of slots, in particular parallel slots.
  • the diameter of an orifice may be between 0.2mm and 10mm, for example between 0.5mm and 2mm.
  • the means 50 is connected to the radiofrequency alternating voltage source 30.
  • the radiofrequency alternating voltage source 30 therefore ensures, in addition, the control of the means 50 for extracting and accelerating the charged particles outside. of the chamber 10. This is particularly advantageous because it makes it possible to further increase the compactness of the thruster 100.
  • this control of the means 50 of extraction and acceleration by the source 30 of radiofrequency alternating voltage makes it possible to better control the beam 70 of charged particles, unlike the techniques proposed in article D1 in particular.
  • this control also makes it possible to obtain a beam with very good electroneutrality at the outlet of the chamber 10, without using any external device for this purpose.
  • the assembly formed by the means 50 for extracting and accelerating the charged particles from the plasma and the radiofrequency alternating voltage source 30 therefore also makes it possible to obtain a neutralization of the beam 70 at the outlet of the chamber 10.
  • compactness of the thruster 10 is thus increased, which is particularly advantageous for the use of this thruster 100 for a small satellite ( ⁇ 500kg), in particular a micro-satellite (10kg-100kg) or a nano-satellite (1kg-10kg), for example of the “CubeSat” type.
  • the gate 51 is connected to the radiofrequency voltage source 30 by means of a means 60 for managing the signal supplied by said radiofrequency voltage source 30 and the electrode 52 is connected to the radiofrequency voltage source. 30, in series, by means of a capacitor 53 and of the means 60 for managing the signal supplied by said radiofrequency voltage source 30.
  • the gate 51 is also placed at a reference potential 55, for example ground.
  • the output of the radiofrequency alternating voltage source 30, not connected to the means 60 is also set to the same reference potential 55, the ground according to the example.
  • the reference potential may be that of the space probe or of the satellite on which the thruster 100 is mounted.
  • the means 60 for managing the signal supplied by said radiofrequency voltage source 30 therefore forms a means 60 which makes it possible to transmit the signal supplied by the source 30 of radiofrequency alternating voltage in the direction of, on the one hand, or of each coil 40 and of 'on the other hand, the means 50 for extracting and accelerating the ions and electrons from the chamber 10.
  • the frequency of the signal supplied by the source 30 can be between a few MHz and a few hundred MHz, depending on the propellant used for the formation of the plasma in the chamber 10 and this, to be between the plasma frequency of ions and the plasma frequency of electrons.
  • a frequency of 13.56MHz is generally well suited, but the following frequencies can also be considered: 1MHz, 2MHz or even 4 MHz.
  • the electroneutrality of the beam 70 is ensured by the capacitive nature of the extraction and acceleration system 50 because, due to the presence of the capacitor 53, there are on average as many positive ions as there are electrons which are extracted at the over time.
  • the shape of the signal produced by the radiofrequency alternating voltage source 30 may be arbitrary. However, provision may be made for the signal supplied by the source 30 of the radiofrequency alternating voltage to the electrode 52 to be rectangular or sinusoidal.
  • the principle of operation for the extraction and acceleration of charged particles from the plasma (ions and electrons) with the first embodiment is as follows.
  • the electrode 52 has a surface which is greater, and generally significantly greater, than that of the grid 51 located at the outlet of the chamber 10.
  • the application of an RF voltage to an electrode 52 having a larger surface area than the gate 51 has the effect of generating at the level of the interface between the electrode 52 and the plasma on the one hand, and at the level of the interface between the gate 51 and the plasma on the other hand, an additional potential difference, adding to the RF potential difference.
  • This total potential difference is distributed over a sheath.
  • the cladding is a space which is formed between the grid 51 or the electrode 52 on the one hand and the plasma on the other hand where the density of positive ions is higher than the density of electrons.
  • This sheath has a variable thickness due to the variable RF signal applied to the electrode 52.
  • the electrode-gate system can be seen as a capacitor with two asymmetric walls , in this case the potential difference is applied to the part of lower capacitance and therefore of smaller surface).
  • the application of the RF signal has the effect of converting the RF voltage to voltage.
  • constant DC due to the charge of the capacitor 53, mainly at the level of the sheath of the gate 51.
  • This constant DC voltage in the sheath of the gate 51 implies that the positive ions are constantly extracted and accelerated (continuously). Indeed, this DC potential difference has the effect of making the plasma potential positive. Consequently, the positive ions of the plasma are constantly accelerated in the direction of the gate 51 (to a reference potential) and therefore extracted from the chamber 10 by this gate 51. The energy of the positive ions corresponds to this difference in DC potential (average energy).
  • the variation of the RF voltage makes it possible to vary the difference in RF + DC potential between the plasma and the gate 51. At the level of the sheath of the gate 51, this results in a change in the thickness of this sheath. When this thickness becomes less than a critical value, which happens for a period of time at regular intervals given by the frequency of the RF signal, the potential difference between the gate 51 and the plasma approaches zero (therefore the plasma potential approaches the reference potential), which makes it possible to extract electrons.
  • critical potential the plasma potential below which the electrons can be accelerated and extracted
  • Child's law which relates this critical potential to the critical thickness of the cladding below which this cladding disappears (“sheath collapse” according to Anglo-Saxon terminology).
  • FIG 2 there is shown an alternative embodiment to the first embodiment shown in figure 1 .
  • the means 50 for extracting and accelerating the charged particles from the plasma comprises a set of at least two grids 51, 52 ′ located at one end E (outlet) of the chamber 10, one 51 at least of the set of at least two gates 51, 52 'being connected to the radiofrequency voltage source 30 via the means 60 for managing the signal supplied by said radiofrequency voltage source 30 and the other 52 'at least of the set of at least two gates 51, 52' being connected to the radiofrequency voltage source 30, in series, by means of a capacitor 53 and of the means 60 for managing the signal supplied by said radio frequency voltage source 30.
  • connection of the gate 52 'to the source 30 of radiofrequency voltage is, on the figure 2 , identical to the connection of the electrode 52 to this source 30, on the figure 1 .
  • Each grid 51, 52 ' may have orifices of different shapes, for example circular, square, rectangular or in the form of slots, in particular parallel slots.
  • the diameter of an orifice may be between 0.2mm and 10mm, for example between 0.5mm and 2mm.
  • the distance between the two grids 52 ′, 51 may be between 0.2mm and 10mm, for example between 0.5mm and 2mm (the exact choice depends on the DC voltage and the density of the plasma).
  • the capacitor 53 When an RF voltage is applied through the source 30, the capacitor 53 charges. The charge of the capacitor 53 then produces a DC voltage at the terminals of the capacitor 53. An RF + DC voltage is then obtained at the terminals of the assembly formed by the source 30 and the capacitor 53. The constant part of the RF + DC voltage then makes it possible to define an electric field between the two gates 52 ', 51, the average value of the RF signal alone being zero. This DC value therefore makes it possible to extract and accelerate the positive ions through the two gates 51, 52 ', continuously.
  • the plasma follows the potential printed at the gate 52 ', which is in contact with the plasma, namely RF + DC.
  • the other gate 51 reference potential 55, for example the mass
  • it is also in contact with the plasma, but only during the brief time intervals during which the electrons are extracted with the positive ions, namely when the RF + DC voltage is less than a critical value below which the sheath disappears. This critical value is defined by Child's law.
  • the electroneutrality of the beam 70 of ions and electrons can be obtained at least in part by adjusting the duration of application of the positive and / or negative potentials from the radiofrequency alternating voltage source 30.
  • This electroneutrality of the beam 70 ions and electrons can also be obtained at least in part by adjusting the amplitude of the positive and / or negative potentials coming from the radiofrequency alternating voltage source 30.
  • the advantage of this variant is, compared to the embodiment illustrated in figure 1 and implementing a gate 51 at the E end of chamber 10 and an electrode 52 housed in the chamber having a larger surface area than gate 51 to provide better control of the positive ion trajectory.
  • This is linked to the fact that a DC (continuous) potential difference is generated between the two gates 52 ', 51, under the action of the source 30 of radiofrequency alternating voltage and of the capacitor 53 in series and not at the level of the cladding between the plasma and the grid 51 (cf. previously) in the case of the first embodiment of the figure 1 .
  • the positive ions passing through the orifices of the grid 52 'do not come into contact with the wall of the grid 51 which is visible, from the point of view of these ions, only through the orifices of the grid 52. '. Accordingly, the service life of the grids 52 ', 51 according to this variant embodiment is improved compared to that of the grid 51 of the first embodiment of the figure 1 .
  • the life of the resulting propellant 100 is therefore improved.
  • the efficiency is improved because the positive ions can be focused by the set of at least two gates 51, 52 ', the flow of neutral species being reduced because the transparency to these neutral species increases. .
  • the figure 3 shows another variant of the first embodiment of the figure 1 , for which the gate 51 is connected, by its two ends to the source 30 of radiofrequency alternating voltage.
  • the figure 4 shows an alternative embodiment to the variant shown in figure 2 , for which the gate 51 is connected, by its two ends, to the radiofrequency alternating voltage source.
  • the figure 5 represents a second embodiment of an ion propellant according to the invention.
  • the source 30 used for the extraction and acceleration of the charged particles out of the plasma remains a source of radiofrequency alternating voltage whose frequency is between the plasma frequency of the ions and the plasma frequency of the electrons, the source 30 'may generate a different signal.
  • the operating frequency of the source 30 ′ may in particular be greater than that of the operating frequency of the source 30. .
  • the figure 6 shows a variant of the second embodiment shown in figure 5 .
  • the difference between the propellant 100 shown in the figure 5 and the one shown on the figure 1 lies in the fact that the electrode 52 housed inside the chamber 10 is omitted and that a grid 52 'is added at the level of the end E (outlet) of the chamber 10.
  • the difference between the variant shown in the figure 6 and the second embodiment of the figure 5 is the same as that which was presented previously between the variant shown on the figure 2 and the first embodiment of the figure 1 .
  • the figure 7 shows another variant of the second embodiment of the figure 5 , for which the gate 51 is connected to the source 30 of radiofrequency alternating voltage.
  • the figure 8 shows an alternative embodiment to the variant shown in figure 6 , for which the gate 51 is connected to the source 30 of radiofrequency alternating voltage.
  • the figure 9 represents an alternative embodiment of the thruster 100 illustrated in figure 8 .
  • This variant embodiment differs from that shown in the figure 8 in that the reservoir 20 comprises two stages E1, E2 for injecting propellant in the gas state to the plasma chamber 10.
  • the reservoir 20 comprises a casing 21, one wall of which is provided with one or more orifice (s) 22, thereby defining a reservoir with a single stage.
  • the reservoir further comprises a membrane 22 ′ comprising at least one orifice 22 ′′ and separating the reservoir into two stages E1, E2.
  • the reservoir 20 comprises a membrane 22 ′ situated between the solid propellant PS and the envelope 21 provided with at least one orifice 22, said membrane 22 'comprising at least one orifice 22 ", the area of the or each orifice 22" of the membrane 22' being greater than the area of the or each orifice 22 of the envelope 21 of the tank 20.
  • This variant is of interest when, taking into account the sizing of the or each orifice 22 on the casing 21 of the reservoir 20 in order to obtain in particular the desired operating pressure P2 in the plasma chamber 10, the result is to define orifices that are too small. These orifices may then not be technically feasible. These holes can also, although technically feasible, too small to ensure that solid propellant dust and more generally impurities, will not block orifices 22 in use.
  • the or each orifice 22 "of the membrane 22 ' is dimensioned so that it is larger than the or each orifice 22 made on the casing 21 of the reservoir 20, the or each orifice 22 remaining dimensioned to obtain the desired operating pressure P2 in the plasma chamber 10.
  • a double-stage tank 20 can be envisaged for all of the embodiments described in support of the figures 1 to 7 .
  • the figure 10 represents a third embodiment of an ion propellant according to the invention.
  • FIG. 8 This figure is presented as an alternative to the realization of the figure 8 (grids 52 'and 51' both connected to the voltage source). However, it also applies as a variant to the figure 6 (grid 52 'connected to the source and grid 51 connected to ground), to the figure 7 (electrode 52 and gate 51 both connected to the voltage source), to the figure 5 (electrode 52 connected to the source and gate 51 connected to ground) and to the figure 9 .
  • the propellant 100 presented here makes it possible to form a beam 70 ′ of positive ions at the outlet of the plasma chamber 10.
  • the radiofrequency alternating voltage source 30 is replaced by a direct voltage (DC) source 30 ".
  • DC direct voltage
  • electrons are injected into the beam 70' by an external device 80 , 81 to chamber 10.
  • This device comprises a power source 80 supplying an electron generator 81.
  • the electron beam 70 ′′ leaving the electron generator 81 is directed towards the beam 70 ′ of positive ions to ensure electroneutrality.
  • the figures 11 and 12 represent a possible design for a plasma chamber 10 and its environment for a thruster 100 in accordance with the achievements of the figure 1 , of the figure 3 , of the figure 5 or the figure 7 .
  • the casing 21 is made of a conductive material, for example metallic (aluminum, zinc or a metallic material coated with gold, for example) or of a metal alloy (stainless steel or brass, for example).
  • a conductive material for example metallic (aluminum, zinc or a metallic material coated with gold, for example) or of a metal alloy (stainless steel or brass, for example).
  • the chamber 10 is clamped between two rings 201, 202, mounted together by means of rods 202, 204, 205 extending along the chamber 10 (longitudinal axis AX).
  • the chamber 10 is made of a dielectric material, for example ceramic.
  • the fixing of the rings and the rods can be made by bolts / nuts (not shown).
  • the rings can be made of a metallic material, for example aluminum.
  • the rods they are for example made of ceramic or a metallic material.
  • the assembly thus formed by the rings 201, 203 and the rods 202, 204, 205 allows the fixing of the chamber 10 and its environment, by means of additional parts 207, 207 ', which sandwich one 203 rings, on a system (not shown on the figures 11 and 12 ) intended to accommodate the thruster, for example a satellite or a space probe.
  • the plasma chamber and its environment conform to what has been described in support of the figures 11 and 12 .
  • the materials were chosen for a maximum acceptable temperature of 300 ° C.
  • the solid PS propellant used is diodine (I 2 , dry mass of about 50 g).
  • a reference temperature T1 for tank 20 has been set at 60 ° C. This can be obtained with a power of 10W at the level of the radiofrequency alternating voltage source 30.
  • the frequency of the signal supplied by the source 30 is chosen to be between the plasma frequency of the ions and the plasma frequency of the electrons, in this case. 13.56MHz.
  • the pressure P1 of the iodine gas in the reservoir 20 is then known by the figure 13 (case of I 2 ; cf. the corresponding formula F1), this one providing the link between P1 and T1.
  • P1 is 10 Torr (approximately 1330 Pa).
  • the pressure P2 in chamber 10 must then be between 7Pa and 15Pa with a mass flow m 'of iodine gas less than 15sccm ( ⁇ 1.8.10 -6 kg.s -1 ) between the tank 20 and room 10.
  • the diameter of the equivalent (circular) orifice is about 50 microns.
  • the orifice When the orifice is single, it will therefore have a diameter of 50 microns.
  • the orifice 22 is then dimensioned.
  • the thruster 100 according to the invention can in particular be used for a satellite S or a space probe SP.
  • FIG 14 represents, schematically, a satellite S comprising a thruster 100 according to the invention and an energy source SE, for example a battery or a solar panel, connected to the or each source of direct voltage 30 "or alternating voltage 30, 30 '(radio frequency or microwave, as the case may be) of the thruster 100.
  • an energy source SE for example a battery or a solar panel, connected to the or each source of direct voltage 30 "or alternating voltage 30, 30 '(radio frequency or microwave, as the case may be) of the thruster 100.
  • FIG 15 it schematically represents a space probe SS comprising a thruster 100 according to the invention and an energy source SE, for example a battery or a solar panel, connected to the or each source of direct voltage 30 "or alternating voltage 30 , 30 '(radiofrequency or microwave, as the case may be) from the thruster 100.
  • an energy source SE for example a battery or a solar panel

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  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Optics & Photonics (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Electromagnetism (AREA)
  • Plasma Technology (AREA)
EP16760449.5A 2015-08-31 2016-08-30 Propulseur ionique a grille avec agent propulsif solide integre Active EP3344873B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1558071A FR3040442B1 (fr) 2015-08-31 2015-08-31 Propulseur ionique a grille avec propergol solide integre
PCT/EP2016/070412 WO2017037062A1 (fr) 2015-08-31 2016-08-30 Propulseur ionique a grille avec agent propulsif solide integre

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EP3344873A1 EP3344873A1 (fr) 2018-07-11
EP3344873B1 true EP3344873B1 (fr) 2020-07-22

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EP (1) EP3344873B1 (ru)
JP (1) JP6943392B2 (ru)
KR (1) KR102635775B1 (ru)
CN (1) CN209228552U (ru)
CA (1) CA2996431C (ru)
ES (1) ES2823276T3 (ru)
FR (1) FR3040442B1 (ru)
HK (1) HK1251281A1 (ru)
IL (1) IL257700B (ru)
RU (1) RU2732865C2 (ru)
SG (1) SG11201801545XA (ru)
WO (1) WO2017037062A1 (ru)

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FR3062545B1 (fr) * 2017-01-30 2020-07-31 Centre Nat Rech Scient Systeme de generation d'un jet plasma d'ions metalliques
RU2696832C1 (ru) * 2018-07-24 2019-08-06 Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Система хранения и подачи иода (варианты) и способ определения расхода и оставшейся массы иода в ней
WO2020117354A2 (en) * 2018-09-28 2020-06-11 Phase Four, Inc. Optimized rf-sourced gridded ion thruster and components
SE542881C2 (en) * 2018-12-27 2020-08-04 Nils Brenning Ion thruster and method for providing thrust
FR3092385B1 (fr) 2019-02-06 2021-01-29 Thrustme Réservoir de propulseur avec système de commande marche-arrêt du flux de gaz, propulseur et engin spatial intégrant un tel système de commande
CN110469474B (zh) * 2019-09-04 2020-11-17 北京航空航天大学 一种用于微小卫星的射频等离子体源
EP4026159A4 (en) * 2019-09-04 2024-03-20 Phase Four, Inc. FUEL INJECTION SYSTEM FOR PLASMA PRODUCTION DEVICES AND THRUNES
CN111140450B (zh) * 2019-12-24 2022-10-25 兰州空间技术物理研究所 一种霍尔推力器用碘介质地面供气装置及使用方法
CN111322213B (zh) * 2020-02-11 2021-03-30 哈尔滨工业大学 一种可变间距的压电栅极
CN111287922A (zh) * 2020-02-13 2020-06-16 哈尔滨工业大学 一种双频双天线小型波电离离子推进装置
CN112795879B (zh) * 2021-02-09 2022-07-12 兰州空间技术物理研究所 一种离子推力器放电室镀膜蓄留结构
CN114320799A (zh) * 2021-12-06 2022-04-12 兰州空间技术物理研究所 一种固态工质射频离子电推进系统
US20240018951A1 (en) * 2022-07-12 2024-01-18 Momentus Space Llc Chemical-Microwave-Electrothermal Thruster

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Also Published As

Publication number Publication date
SG11201801545XA (en) 2018-03-28
US20180216605A1 (en) 2018-08-02
HK1251281A1 (zh) 2019-01-25
KR20180064385A (ko) 2018-06-14
US11060513B2 (en) 2021-07-13
EP3344873A1 (fr) 2018-07-11
JP2018526570A (ja) 2018-09-13
JP6943392B2 (ja) 2021-09-29
CA2996431A1 (fr) 2017-03-09
FR3040442B1 (fr) 2019-08-30
WO2017037062A1 (fr) 2017-03-09
RU2018109227A3 (ru) 2020-01-31
CA2996431C (fr) 2023-12-05
CN209228552U (zh) 2019-08-09
FR3040442A1 (fr) 2017-03-03
IL257700B (en) 2022-01-01
RU2732865C2 (ru) 2020-09-23
KR102635775B1 (ko) 2024-02-08
RU2018109227A (ru) 2019-10-03
ES2823276T3 (es) 2021-05-06
IL257700A (en) 2018-04-30

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