WO2017037062A1 - Propulseur ionique a grille avec agent propulsif solide integre - Google Patents
Propulseur ionique a grille avec agent propulsif solide integre Download PDFInfo
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- WO2017037062A1 WO2017037062A1 PCT/EP2016/070412 EP2016070412W WO2017037062A1 WO 2017037062 A1 WO2017037062 A1 WO 2017037062A1 EP 2016070412 W EP2016070412 W EP 2016070412W WO 2017037062 A1 WO2017037062 A1 WO 2017037062A1
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- Prior art keywords
- chamber
- voltage source
- propellant
- plasma
- extraction
- Prior art date
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Classifications
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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
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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
-
- 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
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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
- F03H1/0081—Electromagnetic plasma thrusters
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- 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 propellant comprising an integrated solid propellant.
- the invention more specifically relates to an ionic propellant, gate, 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 6kg and 100kg, possibly up to 500kg.
- a particularly interesting case of application is the "CubeSat" of which a module (U) base is less than 1 kg and has dimensions of 10cm * 10cm * 10cm.
- the plasma thruster of the invention may in particular be integrated in a 1 U 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.
- a solid propellant plasma propellant has already been proposed. They can be classified into two categories, depending on whether they implement a plasma chamber or not.
- teflon solid propellant
- This electrical discharge causes Teflon ablation its ionization and its acceleration mainly electromagnetically to generate an ion beam directly into the outer space.
- a laser beam is used to carry out the ablation and ionization of a solid propellant, for example PVC or Kapton®.
- the acceleration of the ions is generally carried out electromagnetically.
- an insulator is provided between an anode and a cathode, the whole being under vacuum.
- the metal cathode serves as ablation material to generate ions.
- the acceleration is effected electromagnetically.
- the solid propellant is abiaté, 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 are no separate means for controlling the plasma density induced by ablation of the solid propellant and the speed of the tones.
- the thrust and the specific impulse of the thruster can not be controlled separately.
- This type of inconvenience is generally not present when a plasma chamber is used.
- This power system is usable for any thruster implementing a plasma chamber.
- the solid propellant (iodine l 2l in this case) is stored in a tank.
- 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 tank and is directed to a chamber, remote from the tank, where it is ionized to form a plasma. Ionization is carried out, in this case, by Hall effect.
- the flow of gas entering the plasma chamber is controlled by a valve disposed between the reservoir and this chamber. We can thus realize a better control of the sublimation of the diode and the characteristics of the plasma, compared to the techniques described in the document D1.
- the characteristics of the ion beam exiting the chamber can then be controlled by a means for extracting and accelerating ions separated from the means used to sublimate the solid propellant and to generate the plasma.
- This plasma thruster based on Hall effect, is therefore likely to be more compact than that proposed in documents D2, D3 or D4. It is also likely to better control the evaporation of the propellant, the plasma and the extraction of ions, compared to the 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 reservoir,
- An object of the invention is to overcome at least one of the aforementioned drawbacks.
- the invention proposes an ionic propellant, characterized in that it comprises:
- a reservoir comprising a solid propellant, said reservoir being housed in the chamber and comprising a conductive envelope provided with at least one orifice;
- a set of means for forming an ion-electron plasma in the chamber said assembly being able to sublimate the solid propellant in the reservoir to form a propellant in the gas state, then to generate said plasma in the chamber from the propellant in the state of gas from the reservoir through said at least one orifice;
- said extraction and acceleration means comprising:
- DC voltage source or a radiofrequency AC voltage source arranged in series with a capacitor and adapted to generate a signal whose radiofrequency is between the plasma frequency of the ions and the electron plasma frequency, said DC or AC voltage source radiofrequency being connected, by one of its outputs, by means of extraction and acceleration of at least the plasma ions out of the chamber, and more precisely:
- said extraction and acceleration means and said direct or alternating radiofrequency voltage source making it possible to form, at the outlet of the chamber, a beam comprising at least ions.
- the thruster may also include at least one of the following features, taken alone or in combination:
- the voltage source connected to the extraction and acceleration means is a radio frequency alternating voltage source
- the set of means for forming the ion-electron plasma comprises at least one coil supplied by the same radio frequency alternating voltage source via means for managing the signal supplied by said radiofrequency voltage source towards, on the one hand, said at least one coil and secondly, extraction and acceleration means for forming an ion and electron beam at the outlet of the chamber;
- the set of means for forming the ion-electron plasma comprises at least one coil supplied by a radio frequency alternating voltage source different from the radiofrequency DC or DC voltage source connected to the extraction and acceleration means or at least one microwave antenna powered by a microwave AC voltage source;
- the voltage source connected to the extraction and acceleration means is a radiofrequency AC voltage source, to form, at the outlet of the chamber, a beam of ions and electrons;
- the extraction and acceleration means is an assembly of at least two grids located at one end of the chamber, the electron-neutrality of the ion-electron beam is obtained at least partly by adjusting the duration applying positive and / or negative potentials from the radiofrequency AC voltage source connected to the extraction and acceleration means;
- the extraction and acceleration means is an assembly of at least two grids located at one end of the chamber, the electron-neutrality of the ion-electron beam is obtained at least partly by adjusting the amplitude of positive and / or negative potentials from the radio frequency alternating voltage source connected to the extraction and acceleration means;
- the voltage source connected to the extraction and acceleration means is a DC voltage source, to form, at the outlet of the chamber, an ion beam, the thruster further comprising means for injecting electrons into said ion beam to ensure electroneutrality;
- the reservoir comprises a membrane located between the solid propellant and the envelope provided with at least one orifice, said membrane comprising at least one orifice, the surface of the or each orifice of the membrane being larger than the surface of the or each orifice of the tank shell;
- the or each grid has orifices whose shape is chosen from among the following forms: circular, square, rectangular or in the form of slits, in particular slots
- the or each grid has circular orifices, the diameter of which is between 0.2 mm and 10 mm, for example between 0.5 mm and 2 mm;
- the means for extracting and accelerating out of the chamber comprises an assembly of at least two grids situated at the end of the chamber, the distance between the two grids is between 0.2 mm and 10 mm, for example between 0.5mm and 2mm;
- the solid propellant is chosen from: diiodine, diiodine mixed with other chemical components, ferrocene, adamantane or arsenic.
- the invention also relates to a satellite comprising a thruster according to the invention and a power source, for example a battery or a solar panel, connected to ia or each DC or AC voltage source of the thruster.
- a power source for example a battery or a solar panel
- the invention also relates to a spatial probe comprising a thruster according to the invention and a power source, for example a battery or a solar panel, connected to ia or each DC or AC voltage source of the thruster.
- a power source for example a battery or a solar panel
- Figure 1 is a schematic view of a plasma thruster according to a first embodiment of the invention
- Figure 2 is a schematic view of an alternative to the first embodiment shown in Figure 1;
- Figure 3 is a schematic view of another alternative to the first embodiment shown in Figure 1;
- Figure 4 is a schematic view of another alternative to the first embodiment shown in Figure 1;
- FIG. 5 is a schematic view of a plasma thruster according to a second embodiment of the invention.
- Figure 6 is a schematic view of an alternative to the second embodiment shown in Figure 5;
- Figure 7 is a schematic view of another variant of the second embodiment shown in Figure 5;
- Figure 8 is a schematic view of another alternative to the second embodiment shown in Figure 5;
- FIG. 9 is a schematic view of an alternative embodiment of the plasma thruster shown in FIG. 8
- Figure 10 is a schematic view of a third embodiment of the invention.
- FIG. 11 is a sectional view of a solid propellant tank that can be used in a plasma propellant according to the invention, whatever the embodiment envisaged, with its environment allowing it to be mounted inside the plasma chamber;
- FIG. 12 is an exploded view of the reservoir shown in Fig. 9;
- FIG. 13 is a curve providing, in the case of the diode (I 2 ) used as a solid propellant, the evolution of the diode vapor pressure as a function of the temperature;
- FIG. 14 schematically represents a satellite comprising a plasma propellant according to the invention.
- FIG. 15 schematically represents a space probe comprising a plasma propellant according to the invention.
- a first embodiment of an ion thruster 100 according to the invention is shown in the figure.
- the thruster 100 comprises a plasma chamber 10 and a solid propellant tank PS housed in the chamber 10. More specifically, the tank 20 comprises a conductive envelope 21 comprising the solid propellant PS, this envelope 21 being provided with one or more orifices 22. Housing the solid propellant tank 20 in the chamber 10 provides the propellant with greater compactness.
- the thruster 100 also comprises a radiofrequency AC voltage source 30 and one or more coils 40 fed by the radiofrequency AC voltage source 30.
- the or each coil 40 may have one or more windings (s). In Figure 1, a single coil 40 having a plurality of windings is provided.
- the coil 40 powered by the radiofrequency AC voltage source 30, induces a current in the reservoir 20, which is conductive (eddy current).
- the current induced in the reservoir causes a Joule effect which heats the reservoir 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 sublimates it, the propellant thus being put in the gas state. Then, 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 to the state of gas that is in the 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, all the gas is not ionized to form the plasma).
- a same radio frequency AC voltage source 30 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. This causes sublimation of the solid propellant PS, within the tank 20, and consequently an increase in the propellant pressure P1 in the gas state within the tank 20 accompanying the temperature increase T1 in this 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 heated by the charged particles of the plasma, the coil (s) being screened by its 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.
- orifice (s) 22 on the reservoir 20, it does not matter. Only the total surface of the orifice or, if several orifices are provided, of all these orifices has an importance. Their dimensioning will depend on the nature of the solid propellant used, and the desired operating parameters for the plasma (temperature, pressure).
- This dimensioning will therefore be done on a case by case basis.
- the volume of the chamber 0 is first defined, as well as the desired nominal operating pressure P2 in this chamber 10 and the desired mass flow rate m 'of positive ions at the outlet of the chamber 10. These data can be obtained by numerical modeling or by routine tests. It should be noted that this mass flow rate (m ') is substantially the same as that found between the reservoir 20 and the chamber 0. Then, the desired temperature T1 for the tank 20 is chosen.
- diiodine (l 2 ) diiodine (l 2 )
- adamantane crude chemical formula: Ci 0 Hi 6
- 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 considered.
- diiod (1 2 ) as a solid propellant.
- FIG. 13 shows a curve providing, in the case of the diode (1 2 ), the evolution of the pressure P of the diode gas as a function of the temperature T.
- T the temperature in Kelvins.
- the temperature can be considered to increase by about 50K.
- the pressure of the diode gas substantially increases 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 amount of diode gas through or orifice (s) 22 in the direction of the chamber 10, when the thruster 100 is in nominal operation.
- a propellant 100 according to the invention using diode () as propellant does not need to implement a valve for the or each orifice, contrary to the document D2.
- the control of the propellant flow rate in the gas state is carried out by controlling the temperature of the reservoir 20, by means of the power supplied to the coil 40 by the radiofrequency AC voltage source 30 and possibly, as specified previously, by the presence of a heat exchanger connected to the reservoir 20.
- the control is different from that which is performed in the 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 gate 51 located at an end E (outlet) of the chamber 10 and an electrode 52 housed inside the chamber 10, this electrode 52 having by construction a larger surface than that of the gate 51
- the electrode 52 may be formed by the wall itself, which is conductive, of the tank 20.
- the electrode 52 is isolated from the wall of the chamber by an electrical insulator 58.
- the gate 51 may have orifices of different shapes, for example circular, square, rectangular or slot-shaped, in particular with parallel slots.
- the diameter of an orifice may be between 0.2 mm and 10 mm, for example between 0.5 mm and 2 mm.
- the means 50 is connected to the radiofrequency AC voltage source 30.
- the radiofrequency AC voltage source 30 thus additionally provides for the control of the means 50 for extracting and accelerating the charged particles off. of the chamber 10. This is particularly interesting because it makes it possible to increase the compactness of the thruster 100 a little more.
- this control of the means 50 for extraction and acceleration by the radiofrequency AC voltage source 30 makes it possible to to better control the beam 70 of charged particles, contrary to the techniques proposed in Article D1 in particular.
- this control also makes it possible to obtain a beam with a 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 plasma charged particles and the radio frequency alternating voltage source 30 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), especially a micro-sateilite (10kg-100kg) or a nano-sateilite (1kg-10kg), for example of the "CubeSat" type.
- the gate 51 is connected to the radio frequency voltage source 30 via means 60 for managing the signal supplied by said radio frequency voltage source 30 and the electrode 52 is connected to the radiofrequency voltage source. 30, in series, via a capacitor 53 and means 60 for managing the signal provided by said radio frequency voltage source 30.
- the gate 51 is also set to a reference potential 55, for example ground.
- the output of the radiofrequency AC voltage source 30, not connected to the means 60 is also set to the same reference potential 55, the mass according to the example.
- the reference potential may be that of the space probe or the satellite on which the thruster 100 is mounted.
- the means 60 for managing the signal supplied by said radiofrequency voltage source 30 thus forms a means 60 which makes it possible to transmit the signal supplied by the radiofrequency AC voltage source 30 to, on the one hand, the or each coil 40 and on the other hand, means 50 for extracting and accelerating the ions and electrons out of the chamber 10.
- the source 30 (RF - radio frequencies) is set to define a COR F pulse such that ⁇ ⁇ , ⁇ G) RF ⁇ ⁇ ⁇ , where:
- Ne ° np
- the frequency of the signal supplied by the source 30 can be between a few MHz and a few hundreds of 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 the ions and the piasma frequency of electrons.
- a frequency of 13.56 MHz is generally well suited, but one can also consider the following frequencies: 1 MHz, 2 MHz or 4 MHz.
- the electroneutrality of the beam 70 is provided by the capacitive nature of the extraction and acceleration system 50 because, because of the presence of the capacitor 53, i! There are on average as many positive ions as electrons that are extracted over time.
- the form of the signal produced by the radiofrequency AC voltage source 30 may be arbitrary. However, it will be possible for the signal supplied by the radiofrequency AC voltage source 30 to the electrode 52 to be rectangular or sinusoidal.
- the operating principle for the extraction and acceleration of charged plasma particles (ions and electrons) with the first embodiment is as follows.
- the electrode 52 has an upper surface, and generally much greater than that of the gate 51 located at the outlet of the chamber 10.
- the application of an RF voltage to an electrode 52 having a surface greater than the gate 51 has the effect of generating at the interface between the electrode 52 and the plasma on the one hand, and at the interface between the gate 51 and the plasma on the other hand, an additional potential difference, adding to the potential difference RF.
- This total potential difference is distributed over a sheath.
- the sheath is a space that is formed between the grid 51 or the electrode 52 on the one hand and the piasma on the other hand where the density of positive ions is higher than the electron density.
- This sheath has a variable thickness due to the variable RF signal applied to the electrode 52.
- the electrode-grid system can be seen as a capacitor with two asymmetrical walls in this case the potential difference is applied to the lower capacitance part of the lower surface area).
- the application of the RF signal has the effect of converting the RF voltage into a voltage DC constant due to the charge of the capacitor 53, mainly at the sheath of the grid 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. As a result, the positive ions of the plasma are constantly accelerated towards the gate 51 (at a reference potential) and thus extracted from the chamber 10 by this gate 51. The energy of the positive ions corresponds to this DC potential difference ( average energy).
- the variation of the RF voltage makes it possible to vary the potential difference RF + DC between the plasma and the gate 51.
- this results in a change in the thickness of this sheath.
- this thickness falls below 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 the value 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 links this critical potential to the critical thickness of the sheath below which this sheath disappears
- a good electroneutrality of the beam 70 of positive ions and electrons at the output of the plasma chamber can thus be obtained.
- FIG. 2 shows an alternative embodiment in the first embodiment shown in FIG. 1.
- the difference between the thruster shown in FIG. 2 with respect to the thruster illustrated in FIG. 1 lies in the fact that the electrode 52 housed inside the chamber 10 is eliminated and that a grid 52 'is added at the level of FIG. the end E (outlet) of the chamber 10.
- the means 50 for extracting and accelerating the charged plasma particles comprises a set of at least two grids 51, 52 'situated at one end E (exit) of the chamber 10, one At least 51 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 radio frequency voltage source 30 and the other 52 at least of the set of at least two gates 51, 52 'being connected to the radio frequency voltage source 30, in series, via a capacitor 53 and the means 60 for managing the signal supplied by said radiofrequency voltage source 30.
- connection of the gate 52 'to the radiofrequency voltage source 30 is, in FIG. 2, identical to the connection of the electrode 52 to this source 30, in FIG. 1.
- Each grid 51, 52 ' may have orifices of different shapes, for example circular, square, rectangular or slot-shaped, in particular with parallel slots.
- the diameter of an orifice may be between 0.2 mm and 10 mm, for example between 0.5 mm and 2 mm.
- the distance between the two grids 52 ', 51 can 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 via the source 30, the capacitor 53 is charged. The charge of the capacitor 53 then produces a DC DC voltage across the capacitor 53. At the terminals of the assembly formed by the source 30 and the capacitor 53, an RF + DC voltage is then obtained. The constant portion 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 single RF signal being zero. This DC value thus makes it possible to extract and accelerate the positive ions through the two grids 51, 52 ', continuously.
- the plasma follows the potential printed on the gate 52 ', which is in contact with the plasma, namely RF + DC As for the other gate 51 (reference potential 55, for example the mass), it is also in contact with the plasma, but only during the short time intervals during which the electrons are extracted with the positive ions, that is, when the RF + DC voltage is below a critical value below which the sheath disappears. This critical value is defined by the law of Child.
- the electroneutricity of the beam 70 of ions and electrons can be obtained at least partly by adjusting the duration of application of the positive potentials and / or This electroneutrality of the beam 70 of ions and electrons can also be obtained at least in part by adjusting the amplitude of the positive and / or negative potentials from the voltage source.
- alternative radio frequency 30 can be obtained at least partly by adjusting the duration of application of the positive potentials and / or This electroneutrality of the beam 70 of ions and electrons.
- the advantage of this variant is, compared to the embodiment illustrated in Figure 1 and implementing a grid 51 at the end E of the chamber 10 and an electrode 52 housed in the surface chamber larger than the grid 51 to provide better control of the trajectory of positive ions.
- This is related to the fact that a DC (continuous) potential difference is generated between the two gates 52 ', 51, under the action of the radiofrequency AC voltage source and the capacitor 53 in series and not at the level of ia sheath between the plasma and the gate 51 (see above) in the case of the first embodiment of FIG.
- the lifetime of the resulting propellant 100 is thus improved.
- the efficiency is improved because the positive ions can be focused by the set of at least two grids 51, 52 ', the flux of neutral species being reduced because the transparency to these neutral species increases. .
- FIG. 3 represents another variant of the first embodiment of FIG. 1, for which the gate 51 is connected at both ends to the radiofrequency AC voltage source 30.
- FIG. 4 represents an alternative embodiment of the variant shown in FIG. 2, for which the gate 51 is connected, at its two ends, to the radiofrequency AC voltage source.
- FIG. 5 represents a second embodiment of an ion thruster according to the invention.
- FIG. 1 This is an alternative to the first embodiment shown in FIG. 1 and for which a first radiofrequency AC voltage source 30 is provided to manage the extraction and acceleration of the plasma charged particles from the chamber. And a second AC voltage source 30 'distinct from the first RF AC voltage source.
- the means 60 for managing the signal provided by a single source of radio frequency alternating voltage 30 as proposed in support of FIGS. 1 to 4 is no longer of interest.
- the source 30 used for the extraction and acceleration of the charged particles out of the plasma remains a source of radiofrequency AC voltage whose frequency is between the plasma frequency of the ions and the plasma frequency of the electrons, the source 30 'can generate a different signal.
- the operating frequency of the source 1 may in particular be greater than that of the operating frequency of the source .
- FIG. 6 represents an alternative to the second embodiment shown in FIG. 5.
- the difference between the thruster 100 shown in FIG. 5 and that shown in FIG. 1 lies in the fact that the electrode 52 housed inside the chamber 10 is eliminated and that a grid 52 'is added to the level of the end E (output) of the chamber 10.
- FIG. 7 represents another variant of the second embodiment of FIG. 5, for which the gate 51 is connected to its radiofrequency AC voltage source. Everything else is the same and works the same way.
- FIG. 8 represents an alternative embodiment to the variant shown in FIG. 6, for which the gate 51 is connected to the radiofrequency AC voltage source 30.
- FIGS. 7 and 8 therefore do not imply the implementation of a reference potential 55 for the gate 51.
- a connection ensures an absence of parasitic currents circulating between on the one hand, the outer conductive parts of the spacecraft or the satellite on which the thruster 100 is mounted and on the other hand, the means 50 for extracting and accelerating the charged particles proper.
- FIG. 9 represents a variant embodiment of the thruster 100 illustrated in FIG.
- This embodiment variant differs from that shown in FIG. 8 in that the reservoir 20 comprises two propellant injection stages E1, E2 in the gas state towards the plasma chamber.
- the reservoir 20 comprises an envelope 21, one wall of which is provided with one or more orifice (s) 22, thereby defining a tank with a single floor.
- the reservoir further comprises a membrane 22 'comprising at least one orifice 22 "and separating the reservoir in two stages E1, E2. 22 'located between the solid propellant PS and the casing 21 provided with at least one orifice 22, said membrane 22' comprising at least one orifice 22 ", the surface of the or each orifice 22" of the membrane 22 'being more large than the surface of the or each orifice 22 of the casing 21 of the reservoir 20.
- This variant is of interest when, taking into account the dimensioning of the or each orifice 22 on the casing 21 of the reservoir 20 to obtain in particular the desired operating pressure P2 in the plasma chamber 10, it is possible to define too small orifices. 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 the 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 envelope 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 may be envisaged for all the embodiments described in support of FIGS. 1 to 7.
- FIG. 10 represents a third embodiment of an ion thruster according to the invention.
- FIG. 8 This figure is an alternative to the embodiment of Figure 8 (grids 52 'and 51' both connected to the voltage source). However, it also applies as an alternative to FIG. 6 (gate 52 'connected to source and gate 51 connected to ground), in FIG. 7 (electrode 52 and gate 51 both connected to the voltage source ), in FIG. 5 (electrode 52 connected to the source and gate 51 connected to ground) and in FIG. 9.
- the thruster 100 presented here makes it possible to form a beam 70 'of positive ions at the outlet of the plasma chamber.
- the radiofrequency AC voltage source 30 is replaced by a 30 "DC voltage source
- This device comprises a power source 80 supplying an electron generator 81.
- the electron beam 70 "coming out of the electron generator 81 is directed towards the beam 70 'of positive ions to ensure electroneutrality.
- FIGS. 11 and 12 represent a conceivable design for a plasma chamber 10 and its environment for a thruster 100 according to the embodiments of FIG. 1, FIG. 3, FIG. 5 or FIG.
- the plasma chamber 10 is recognized, the reservoir 20 with its envelope 21 and the orifices 22.
- the reservoir 20 also serves as an electrode 52. In the present case, three orifices are shown. 22, equidistributed around the axis of symmetry AX of the reservoir 20.
- the envelope 21 is made of a conductive material, for example metal (aluminum, zinc or a gold-coated metal material, for example) or in one metal alloy (stainless steel or brass, for example).
- a conductive material for example metal (aluminum, zinc or a gold-coated metal material, for example) or in one metal alloy (stainless steel or brass, for example).
- the chamber 10 is sandwiched between two rings 201, 202, mounted together via 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 rods can be done by bolts / nuts (not shown).
- the rings may 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 attachment of the chamber 10 and its environment, by means of additional pieces 207, 207 ', which sandwich one of them.
- 203 of the rings on a system (not shown in Figures 1 1 and 12) for receiving the thruster, for example a satellite or a space probe. Example of dimensioning.
- the plasma chamber and its environment are as described in support of Figures 11 and 12.
- the materials were selected for a maximum acceptable temperature of 300 ° C.
- the solid propellant PS used is diiodine (l 2 , dry mass of about 50 g).
- Several orifices 22 have been provided on the conductive casing 21 of the reservoir 20 to pass the diode gas from the reservoir 20 to the plasma chamber 10 (single-stage reservoir 20).
- a reference temperature T1 for the tank 20 was set at 60 ° C. This can be obtained with a power of 10W at the level of the radiofrequency AC 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 diode gas in the tank 20 is then known from FIG. 13 (case of I2, see the corresponding formula F1), which provides the link between P1 and T1.
- P1 is 10 Torr (about 1330 Pa).
- the pressure P2 in the chamber 10 must be between 7 Pa and 15 Pa with a mass flow rate m 'of gas diiodine less than 15sccm ( ⁇ 1: 8. 0 "6 kg. S" 1) between the tank 20 and the chamber 0.
- the diameter of the equivalent (circular) orifice is about 50 microns.
- the orifice When the orifice is single, it will have a diameter of 50 microns.
- the volume flow through the orifice 22 can be estimated by the relation:
- Pi is the pressure in the tank 20
- P 2 is the pressure in the chamber 0;
- v is the average velocity of the diode gas molecules, determined by the relation: kT t
- Ti is the temperature in the tank 20
- k is the Boltzmann constant (k “1 .38-10 " 23 J-K " );
- m is the mass of a molecule of the diode gas (m ( 1-2 ) ⁇ 4.25-10
- M is the molar mass of the diode (for l 2, M "254 u);
- R is the molar constant of the gases (R ⁇ 8.31 J / me-K),
- the orifice 22 is then dimensioned.
- the mass flow rate Iieak (kg / s) of diode gas leakage when the thruster 100 is stopped can be determined by the relation: m ⁇ HAg *] * u (R5) where:
- TQ is the temperature of thruster 100 at a standstill
- P 0 is the pressure of the gas in the tank 20 when the thruster is stopped, this pressure being provided by the formula F1 (see Figure 13) at the temperature T 0 ;
- the thruster 100 according to the invention can in particular be used for a satellite S or a spatial probe SP.
- FIG. 14 schematically represents 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 DC voltage source 30 ". or alternatively 30, 30 '(radiofrequency or microwave, as the case may be) of the propellant 100.
- an energy source SE for example a battery or a solar panel, connected to the or each DC voltage source 30 ". or alternatively 30, 30 '(radiofrequency or microwave, as the case may be) of the propellant 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 DC voltage source.
- an energy source SE for example a battery or a solar panel, connected to the or each DC voltage source.
- 30 or alternatively 30, 30 '(radiofrequency or microwave, as appropriate) of the thruster 00.
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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)
- Optics & Photonics (AREA)
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Abstract
Description
Claims
Priority Applications (11)
Application Number | Priority Date | Filing Date | Title |
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KR1020187007452A KR102635775B1 (ko) | 2015-08-31 | 2016-08-30 | 통합된 고체 추진제를 갖는 그리드 이온 스러스터 |
SG11201801545XA SG11201801545XA (en) | 2015-08-31 | 2016-08-30 | Gridded ion thruster with integrated solid propellant |
RU2018109227A RU2732865C2 (ru) | 2015-08-31 | 2016-08-30 | Сетчатый ионный двигатель с находящимся в нем твердым рабочим телом |
CA2996431A CA2996431C (fr) | 2015-08-31 | 2016-08-30 | Propulseur ionique a grille avec agent propulsif solide integre |
EP16760449.5A EP3344873B1 (fr) | 2015-08-31 | 2016-08-30 | Propulseur ionique a grille avec agent propulsif solide integre |
JP2018510837A JP6943392B2 (ja) | 2015-08-31 | 2016-08-30 | 一体型固体推進剤を備えたグリッド付きイオンスラスタ |
CN201690001163.4U CN209228552U (zh) | 2015-08-31 | 2016-08-30 | 离子推进器、卫星和空间探测器 |
US15/755,322 US11060513B2 (en) | 2015-08-31 | 2016-08-30 | Gridded ion thruster with integrated solid propellant |
ES16760449T ES2823276T3 (es) | 2015-08-31 | 2016-08-30 | Propulsor iónico de rejilla con agente de propulsión sólido integrado |
IL257700A IL257700B (en) | 2015-08-31 | 2018-02-25 | An ion pellet embedded with an integrated solid explosive |
HK18110604.7A HK1251281A1 (zh) | 2015-08-31 | 2018-08-17 | 利用集成固體推進劑的格柵化離子推進器 |
Applications Claiming Priority (2)
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FR1558071A FR3040442B1 (fr) | 2015-08-31 | 2015-08-31 | Propulseur ionique a grille avec propergol solide integre |
FR1558071 | 2015-08-31 |
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WO2017037062A1 true WO2017037062A1 (fr) | 2017-03-09 |
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PCT/EP2016/070412 WO2017037062A1 (fr) | 2015-08-31 | 2016-08-30 | Propulseur ionique a grille avec agent propulsif solide integre |
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US (1) | US11060513B2 (fr) |
EP (1) | EP3344873B1 (fr) |
JP (1) | JP6943392B2 (fr) |
KR (1) | KR102635775B1 (fr) |
CN (1) | CN209228552U (fr) |
CA (1) | CA2996431C (fr) |
ES (1) | ES2823276T3 (fr) |
FR (1) | FR3040442B1 (fr) |
HK (1) | HK1251281A1 (fr) |
IL (1) | IL257700B (fr) |
RU (1) | RU2732865C2 (fr) |
SG (1) | SG11201801545XA (fr) |
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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 |
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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 |
WO2020117354A2 (fr) * | 2018-09-28 | 2020-06-11 | Phase Four, Inc. | Propulseur ionique à grille à source rf optimisé et composants |
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 |
WO2021046044A1 (fr) * | 2019-09-04 | 2021-03-11 | Phase Four, Inc. | Système d'injecteur de gaz propulseur pour dispositifs de production de plasma et propulseurs |
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 |
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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-
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- 2015-08-31 FR FR1558071A patent/FR3040442B1/fr not_active Expired - Fee Related
-
2016
- 2016-08-30 RU RU2018109227A patent/RU2732865C2/ru active
- 2016-08-30 EP EP16760449.5A patent/EP3344873B1/fr active Active
- 2016-08-30 WO PCT/EP2016/070412 patent/WO2017037062A1/fr active Application Filing
- 2016-08-30 JP JP2018510837A patent/JP6943392B2/ja active Active
- 2016-08-30 SG SG11201801545XA patent/SG11201801545XA/en unknown
- 2016-08-30 CN CN201690001163.4U patent/CN209228552U/zh active Active
- 2016-08-30 KR KR1020187007452A patent/KR102635775B1/ko active IP Right Grant
- 2016-08-30 CA CA2996431A patent/CA2996431C/fr active Active
- 2016-08-30 ES ES16760449T patent/ES2823276T3/es active Active
- 2016-08-30 US US15/755,322 patent/US11060513B2/en active Active
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2018
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- 2018-08-17 HK HK18110604.7A patent/HK1251281A1/zh unknown
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Cited By (1)
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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 |
Also Published As
Publication number | Publication date |
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HK1251281A1 (zh) | 2019-01-25 |
RU2018109227A3 (fr) | 2020-01-31 |
US11060513B2 (en) | 2021-07-13 |
ES2823276T3 (es) | 2021-05-06 |
KR20180064385A (ko) | 2018-06-14 |
JP6943392B2 (ja) | 2021-09-29 |
US20180216605A1 (en) | 2018-08-02 |
IL257700B (en) | 2022-01-01 |
FR3040442A1 (fr) | 2017-03-03 |
IL257700A (en) | 2018-04-30 |
EP3344873B1 (fr) | 2020-07-22 |
KR102635775B1 (ko) | 2024-02-08 |
JP2018526570A (ja) | 2018-09-13 |
EP3344873A1 (fr) | 2018-07-11 |
FR3040442B1 (fr) | 2019-08-30 |
SG11201801545XA (en) | 2018-03-28 |
RU2732865C2 (ru) | 2020-09-23 |
CA2996431A1 (fr) | 2017-03-09 |
RU2018109227A (ru) | 2019-10-03 |
CA2996431C (fr) | 2023-12-05 |
CN209228552U (zh) | 2019-08-09 |
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