法国专利FR3040442A1 GRID ION PROPELLER WITH INTEGRATED SOLID PROPERGOL

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专利摘要:
The invention relates to an ion propellant (100), comprising: - a chamber (10), - a reservoir (20), comprising a solid propellant (PS), housed in the chamber (10) and comprising a conductive envelope (21) provided with an orifice (22); means (30, 40) for forming an ion-electron plasma in the chamber (10), which are capable of subliming the solid propellant in the reservoir (20), then generating said plasma in the chamber (10) from sublimed propellant from the reservoir (20) through the orifice (22); means (50) for extracting and accelerating the ions and electrons of the plasma from the chamber (10), which comprises at least two gates (52 ', 51) at one end (E) of the chamber (10); ); a radiofrequency AC voltage source (30) for generating a radiofrequency signal comprised between the ion and electron plasmas frequencies, arranged in series with a capacitor (53) and connected, by one of its outputs and via this capacitor (53), to one (52 ') of the grids, the other gate (51) being connected to the other output of said voltage source (30); said extraction and acceleration means (50) and said voltage source (30) for forming, at the outlet of the chamber (10), an ion-electron beam (70).
公开号:FR3040442A1
申请号:FR1558071
申请日:2015-08-31
公开日:2017-03-03
发明作者:Dmytro Rafalskyi；Ane Aanesland
申请人:Centre National de la Recherche Scientifique CNRS；Ecole Polytechnique；
IPC主号:

专利说明:

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.
More particularly, the invention may find application for small satellites. Typically, 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 1kg and has dimensions of 10cm * 10cm * 10cm. The plasma thruster of the invention may in particular be integrated in 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.
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,
In the article by Keidar & al., "Electric propulsion for small satellites", Plasma Phys. Control. Fusion, 57 (2015) (D1), various techniques are described for generating a plasma from a solid propellant, all based on ablation of a solid propellant. The solid propellant gives directly on the outer space, namely the space for satellites or space probes, without plasma chamber.
According to a first technique, teflon (solid propellant) is available between an anode and a cathode between which an electric discharge is made. This electrical discharge causes Teflon ablation its ionization and its acceleration mainly electromagnetically to generate an ion beam directly into the outer space.
According to a second technique, 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.
According to a third technique, 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 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.
However, the consequence is that there is no separate control of the sublimation of solid propellant, plasma and ion beam.
In particular, 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 rate of ions. As a result, 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. The article of Polzin & a!., "lodine Hall Thruster Propellant Feed System for a CubeSat", American Institute of Aeronautics and Astronautics (D2) offers a solid propellant supply system for a Hall effect thruster.
This power system is usable for any thruster implementing a plasma chamber.
Indeed, in the article D2, the solid propellant (iodine 12, in this case) is stored in a tank. A heating means is associated with the reservoir. This heating means may be an element able to receive external radiation placed on the outside of the reservoir. Thus, when the tank is heated, 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. It is thus possible to better control the sublimation of the diode and the characteristics of the plasma, compared with the techniques described in document D1.
Furthermore, 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 generate the plasma.
This system therefore has many advantages over those described in document D1.
However, in document D2, the presence of such a power supply system makes the plasma thruster uncomplicated and, consequently, not very feasible for small satellites, in particular for a "CubeSat" type module.
In US 8,610,356 (D3), there is also provided a system using a propellant such as iodine (I2) stored in a reservoir located at a distance from a plasma chamber. The control of the flow of diode gas leaving the tank is achieved by temperature and pressure sensors installed at the outlet of the tank and connected to a control loop of the tank temperature. Here too, the system is not very compact.
In the same type of system as those proposed in documents D2 or D3, mention may also be made of US 6,609,363 (D4). it should be noted that a propellant plasma propellant integrated in a plasma chamber has already been proposed in US 7,059,111 (D5). 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. However, the propellant is stored in the liquid state and uses an additional electrode system to control the flow of gas leaving the tank.
An object of the invention is to overcome at least one of the aforementioned drawbacks.
To achieve this objective, the invention provides an ionic propellant, characterized in that it comprises: - a chamber, - a tank comprising a propergo! solid, 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; means for extracting and accelerating at least the plasma ions from the chamber, said extraction and acceleration means comprising: either an electrode housed in the chamber to which is associated a gate located at an end of the chamber, said electrode having a larger area than the surface of the grid; or an assembly of at least two grids at one end of the chamber; a 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 radio frequency 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: • to the electrode, • or to the one of the grids of said set of at least two grids, the grid associated with the electrode or, as the case may be, the other gate of said set of at least two grids being either set to a reference potential, or connected to the other outputs of said radio frequency alternating voltage source; 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, and 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 in the direction of, on the one hand, said at least one a coil and secondly, the extraction and acceleration means, to form a beam of ions and electrons 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 of parallel slits; 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; when 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 the or each DC or AC voltage source of the thruster. 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 the or each DC or AC voltage source of the thruster. The invention will be better understood and other objects, advantages and characteristics thereof will appear more clearly on reading the description which follows and which is made with reference to the appended figures, in which: FIG. 1 is a diagrammatic view 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; Figure 9 is a schematic view of an alternative embodiment of the plasma thruster shown in Figure 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 (12) 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 propellant 100 according to the invention is shown in FIG.
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. The 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. In this case, a single coil 40 is also used for this purpose. However, it is conceivable to provide several coils, for example a coil to sublimate the solid propellant PS and a coil to create the plasma. By using several coils 40, it is then possible to increase the length of the chamber 10.
More specifically, the chamber 10 and the reservoir 20 are initially at the same temperature.
When the source 30 is implemented, 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.
Ceia causes sublimation of the solid propellant PS, within the tank 20, and consequently an increase in the propellant pressure P1 in the state of gas within the tank 20 accompanying the temperature increase T1 in this tank.
Then, under the effect of the pressure difference between the reservoir 20 and the chamber 10, the propellant in the state of gas passes through the or each orifice 22 in the direction of the chamber 10.
When the temperature and pressure conditions are sufficiently high in the chamber 10, the assembly formed by the source 30 and the coil (s) 40 makes it possible to generate the plasma in the chamber 10. At this stage, the solid propellant PS is then more 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.
In the presence of the plasma (thruster in operation), it should be noted that 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 ports 22 may be provided 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.
In general, the sizing of the thruster according to the invention will resume the following steps.
The volume of the chamber 10 is firstly 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 (nV) is substantially the same as that found between the reservoir 20 and the chamber 10.
Then, the desired temperature T1 for the tank 20 is chosen.
Since this temperature T1 is 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 (see FIG. 13 in the case of diode 12).
Knowing P2, m ', P1 and T1, it is possible to deduce the surface A of the orifice or, if several orifices are provided, all the orifices. Advantageously, however, several orifices will be provided to ensure a more homogeneous distribution of the propellant in the state of gas within the chamber 10.
An example of sizing, however, is provided later.
It is then possible to estimate the propellant leak in the state of gas between the reservoir 20 and the chamber 10 when the thruster 100 is at a standstill. Indeed, in this case, the surface A of the orifices is known, just like P1, T1 and P2, which makes it possible to obtain m '(leakage rate). In practice, it turns out that when stopped, the leak is minimal compared to the propellant flow in the state of gas passing from the tank 20 to the chamber 10 in use. This is why, in the context of the invention, the presence of valves at the orifices is not mandatory.
For the solid propellant, diiode (12), a mixture of diiod (12) with other chemical components, adamantane (crude chemical formula: CioHie) or ferrocene (crude chemical formula: Fe ( C5H5) 2). Arsenic can also be used, but its toxicity makes it a solid propellant whose use is less considered.
Advantageously, diode (12) will be used as a solid propellant.
This propellant has indeed several advantages. FIG. 13 shows a curve providing, in the case of the diode (12), the evolution of the pressure P of the diode gas as a function of the temperature T. This curve can be approximated by the following formula:
Log (P) = - 3512.8 * (1 / T) - 2013 (1.0) + 13.374 (F1) with: P, Torr pressure; T, the temperature in Kelvins.
This formula can be obtained in "The Vapor Pressure lodine", G. P. Baxter, C.H. Hickey, W.C. Holmes, J. Am. Chem. Soc., 1907, 29 (2) pp. 12-136. This formula is also cited in "The Normal Vapor Pressure of Crystalline lodine," L.J. Gillespie, & al., J. Am. Chem Soc., 1936, vol. 58 (11), pp 2260-2263. This formula has been the subject of experimental verifications by various authors.
When the thruster switches from a stop mode to a nominal operating mode, the temperature can be considered to increase by about 50K. In the temperature range between 300K and 400K, it is noted in this figure 13 that the pressure of the diode gas substantially increases by a factor of 100, for a temperature increase of 50K.
Also, when the thruster is in stop mode, 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 passing through the orifice (s) 22 in the direction of 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 temperature at a standstill will only reduce the relative leakage losses of propellant in the gas state.
Consequently, a thruster 100 according to the invention using diode (b) as propellant does not need to implement a valve for the or each orifice, contrary to the document D2. This simplifies the design of the thruster and ensures good reliability. 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. In FIG. this means 50 comprises a gate 51 located at an end E (output) of the chamber 10 and an electrode 52 housed inside the chamber 10, this electrode 52 having by construction a larger surface area than that of the gate 51 In some cases, 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. In particular, in the case of circular orifices, the diameter of an orifice may be between 0.2 mm and 10 mm, for example between 0.5 mm and 2 mm.
To ensure this extraction and acceleration, 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. Moreover, 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. Finally, 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. In other words, 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), in particular a micro-satellite (10kg-100kg) or a nano-satellite (1kg-10kg) , for example of the "CubeSat" type. For this purpose, 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. Likewise, 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.
In practice, for applications in the space domain, 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 pulse corf such that
or :
is the plasma pulsation of the electrons and
plasma pulsation of positive ions; with: eo, the charge of the electron, εο, the permittivity of the vacuum, np, the density of the plasma, m ,, the mass of the ions and me, the mass of the electrons.
It should be noted that
because
In general, the frequency of the signal supplied by the source 30 may be between a few MHz and a few hundreds of MHz, depending on the propergo used for the formation of the plasma in the chamber 10, and this, to be between the plasma frequency of the ions and the plasma 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, there are on average as many positive ions as electrons which are extracted at course of time.
In this context, the shape 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.
By construction, 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.
In general, 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 plasma 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 RF signal, variable, applied to the electrode 52.
In practice, most of the effect of the application of an RF signal on the electrode 52 is however located in the sheath of the grid 51 (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).
In the presence of the capacitor 53 in series with the RF source, the application of the signa! RF has the effect of converting the RF voltage into DC constant voltage due to the charge of the capacitor 53, mainly at 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. 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. At the level of the sheath of the gate 51, this results in a change in the thickness of this sheath. When 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.
In practice, the plasma potential below which the electrons can be accelerated and extracted (= critical potential) is given by the Child's law, which links this critical potential to the critical thickness of the sheath below which this sheath disappears ("sheath collapse" according to the English terminology).
As long as the plasma potential is below the critical potential, then there is simultaneous acceleration and extraction of electrons and ions.
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 same references designate the same components.
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. end E (outlet) of the chamber 10.
In other words, the means 50 for extracting and accelerating the charged particles of the plasma comprises an assembly 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.
The 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.
Each grid 51, 52 'may have orifices of different shapes, for example circular, square, rectangular or slot-shaped, in particular with parallel slots. In particular, in the case of circular orifices, the diameter of an orifice may be between 0.2 mm and 10 mm, for example between 0.5 mm and 2 mm.
Furthermore, 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).
In this variant, the operation of the extraction and acceleration of the positive ions and the electrons is as follows.
When an RF voltage is applied via the source 30, the capacitor 53 charges. 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 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.
On the other hand, when this RF voltage is applied, the plasma follows the potential printed on the grid 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 brief time intervals during which the electrons are extracted with the positive ions, namely 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 electroneutrality of the beam 70 at the outlet of the chamber 10 is thus ensured.
It should also be noted that, for this embodiment of FIG. 2, 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 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. Radio frequency alternative 30. The advantage of this variant is, compared to the embodiment illustrated in Figure 1 and implementing a gate 51 at the end E of the chamber 10 and an electrode 52 housed in the surface chamber more large than 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 the sheath between the plasma and the gate 51 (see above) in the case of the first embodiment of FIG.
Therefore, with the embodiment variant shown in Figure 2, it is ensured that many more positive ions pass through the orifices of the grid 52 ', without touching the wall of this grid 52', with reference to what happens in the case of the first embodiment illustrated in FIG.
In addition, the positive ions passing through the orifices of the grid 52 'do not come to touch 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 . As a result, the life of the grids 52 ', 51 according to this variant embodiment is improved with respect to that of the grid 51 of the first embodiment of FIG. 1.
The lifetime of the resulting propellant 100 is thus improved.
Finally, 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.
Everything else is the same and works the same way.
FIG. 4 represents an alternative embodiment to the variant represented in FIG. 2, for which the gate 51 is connected, at its two ends, to the radiofrequency AC voltage source.
Everything else is the same and works the same way.
The variants illustrated in FIGS. 3 and 4 therefore do not imply the implementation of a reference potential for the gate 51. In the space domain, such a connection ensures an absence of parasitic currents flowing between, on the one hand, the external conductive parts of the spacecraft or satellite on which the thruster 100 is mounted and secondly, the means 50 for extracting and accelerating the charged particles proper.
FIG. 5 represents a second embodiment of an ion thruster according to the invention.
This is an alternative to the first embodiment shown in FIG. 1 and for which a first radiofrequency AC voltage source 30 is provided for managing 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 rest is the same and works the same way.
In this case, the means 60 for managing the signal provided by a single source of radiofrequency AC voltage 30 as proposed in support of FIGS. 1 to 4 is no longer of interest.
This alternative allows for more flexibility.
Indeed, if the source 30 used for the extraction and acceleration of 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.
For example, the source 30 'can generate a radio frequency alternating voltage signal, associated with one or more coil (s) 40 for heating the envelope 21 of the conductive reservoir 20 (made of a metallic material for example), evaporating the solid propellant and then generating a plasma in the chamber 10, whose frequency is different from that of the operating frequency of the source 30. The operating frequency of the source 30 'may in particular be greater than that of the operating frequency of the source 30 .
According to another example, the source 30 'can generate an alternating voltage signal in frequencies corresponding to the microwaves, associated with one or more microwave antenna (s) 40.
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.
The rest is the same and works the same way.
In other words, the difference between the variant shown in FIG. 6 and the second embodiment of FIG. 5 is the same as that presented previously between the variant represented in FIG. 2 and the first embodiment. of Figure 1.
FIG. 7 represents another variant of the second embodiment of FIG. 5, for which the gate 51 is connected to the radiofrequency AC voltage source 30.
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.
Everything else is the same and works the same way.
The variants illustrated in FIGS. 7 and 8 therefore do not imply the use of a reference potential 55 for the gate 51. As explained above, in the space domain, such 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.
Indeed, in FIG. 8, and moreover in all of FIGS. 1 to 7, 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.
In contrast, in the variant shown in Figure 9, the reservoir further comprises a membrane 22 'having at least one orifice 22 "and separating the reservoir in two stages E1, E2. More specifically, the reservoir 20 comprises a membrane 22 'located between the solid propellant PS and the envelope 21 provided with at least one orifice 22, the said membrane 22' comprising at least one orifice 22 ", the surface of the or each orifice 22 "of the membrane 22 'being larger 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, it is possible to define too small orifices. These orifices may then not be technically feasible. These orifices may also, although technically feasible, too small to ensure that solid propellant dust and more generally, impurities, will not block the orifices 22 in use.
In this case, 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.
Of course, 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.
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 the 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.
The thruster 100 presented here makes it possible to form a beam 70 'of positive ions at the outlet of the plasma chamber. For this purpose, the radiofrequency AC voltage source 30 is replaced by a source 30 '' of DC voltage (DC). In order to ensure the electroneutrality of the beam 70 ', electrons are injected into the beam 70' by an external device 80, 81 to the chamber 10. This device comprises a power source 80 supplying an electron generator 81, the The electron beam 70 "emerging from the electron generator 81 is directed to the beam 70 'of positive ions to provide electroneutrality.
Figures 11 and 12 show a possible design for a plasma chamber 10 and its environment for a thruster 100 according to the embodiments of Figure 1, Figure 3, Figure 5 or Figure 7.
In these figures, the plasma chamber, the tank 20 with its shell 21 and the orifices 22 are recognized. The tank 20 also serves as an electrode 52. In the case in point, three orifices 22, equidistributed around the axis of symmetry AX of the reservoir 20. The envelope 21 is made of a conductive material, for example metallic (aluminum, zinc or a metal material coated with gold, for example) or a metal alloy (stainless steel or brass, for example). As a result, eddy currents and consequently a Joule effect can be produced in the shell 21 of the tank 20 under the action of the alternating voltage source 30, 30 'and the coil 40 or, as the case may be, of the microwave antenna 40. The transmission of heat between the envelope 21 of the tank 20 and the solid propellant PS may be carried out by thermal conduction and / or thermal radiation.
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. As for 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 11 and 12) for receiving the thruster, for example a satellite or a space probe.
Example of dimensioning.
An ion propellant 100 in accordance with that shown in Figure 1 has been tested.
The plasma chamber and its environment are as described with reference to FIGS. 11 and 12. The materials were selected for a maximum acceptable temperature of 300.degree.
The solid propellant PS used is diiodine (12, dry weight of about 50 g).
Several orifices 22 have been provided on the conductive casing 21 of the tank 20 to pass the diode gas from the tank 20 to the plasma chamber 10 (single stage tank 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. In this case, P1 is 10 Torr (about 1330 Pa).
To obtain optimum efficiency, the pressure P2 in the chamber 10 must then be between 7 Pa and 15 Pa with a mass flow rate m 'of diode gas of less than 15 sccm (1.8 x 10 6 kg -1) between the tank 20 and the bedroom 10.
We can then estimate that the diameter of the equivalent (circular) orifice is about 50 microns. When the orifice is single, it will have a diameter of 50 microns. When several orifices are provided, which is the case in the test carried out, it is then necessary to determine the surface of this orifice and to distribute this surface over several orifices in order to obtain the diameter of each of the orifices, which will advantageously be the same. .
However, in order to give some additional dimensioning elements corresponding to the numerical values provided above, the following points can be noted, in the case of an orifice 22 of surface A.
The volume flow through the orifice 22 can be estimated by the relation:
(R1) where;
Pi is the pressure in the tank 20; P2 is the pressure in chamber 10; and v is the average velocity of the diode gas molecules, determined by the relation:
(R2) where: Τι is the temperature in the tank 20; k is the Boltzmann constant (A * 1.38-10'23 J-K'1); and m is the mass of a molecule of the diode gas (m (h) ® 4.25 · 10'25 kg).
The mass flow rate m 'of diode gas through the orifice 22 is then obtained by the relation:
(R3) where: M is the molar mass of the diode (for i2, M "254 u); and R is the molar constant of the gases (R ~ 8.31 J / molK).
By combining the relations (R1) and (R3), we deduce the surface A of the orifice 22 by the relation:
(R4) The orifice 22 is then dimensioned.
As can be seen in relation (R4), the temperature T2 in the plasma chamber 10 does not occur. A more accurate modeling could be obtained by taking into account this temperature T2. For more general data on this dimensioning, refer to: A. User Guide To Vacuum Technology, third ed., Johan F. O'Hanlon (John Wiley & Sons Inc., 2003).
Once the surface A of the orifice 22 is dimensioned, the mass flow meek (kg / s) of diode gas leak when the thruster 100 is stopped can be determined by the relation:
(R5) where: Το is the temperature of thruster 100 at a standstill;
Po 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 T0; and vo is obtained using the relation (R2) substituting T-ι by T0.
End of the example.
It should be noted that the positioning of the or each orifice, shown in the accompanying figures on one side of the shell of the tank 20 facing the plasma chamber, could be different. In particular, it is quite possible to arrange the or each orifice on the opposite face of the reservoir 20.
Finally, the thruster 100 according to the invention can in particular be used for a satellite S or a spatial probe SP.
Thus, 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.
As for FIG. 15, it shows schematically a spatial 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. 30 "or alternatively 30, 30 '(radiofrequency or microwave, as appropriate) of the propellant 100.

权利要求:
Claims (14)
[1" id="c-fr-0001]
1. Propellant (100) ionic, characterized in that it comprises: - a chamber (10), - a reservoir (20) comprising a solid propellant (PS), said reservoir (20) being housed in the chamber (10) and having a conductive envelope (21) provided with at least one orifice (22); a set of means (30, 30 ', 40) for forming an ion-electron plasma in the chamber (10), said assembly being able to sublimate the solid propellant in the tank (20) to form a propellant in the state of gas, then generating said plasma in the chamber (10) from the propellant in the state of gas from the reservoir (20) through said at least one orifice (22); means (50) for extracting and accelerating at least the plasma ions from the chamber (10), said extraction and acceleration means (50) comprising: either an electrode (52) housed in the chamber (10) with which is associated a grid (51) located at one end (E) of the chamber (10), said electrode (52) having a larger area than the surface of the grid (51), • a set of at least two grids (52 ', 51) located at one end (E) of the chamber (10); a DC voltage source (30 ") or a radiofrequency AC voltage source (30) arranged in series with a capacitor (53) and adapted to generate a signal whose radio frequency is between the plasma frequency of the ions and the plasma frequency electrons, said DC (30 ") or alternating radio frequency source being connected, by one of its outputs, to means (50) for extracting and accelerating at least the plasma ions from the chamber (10), and more precisely: either to the electrode (52), or to one (52 ') of the grids of said set of at least two grids (51, 52'), the grid (51) associated with the electrode (52) or, as the case may be, the other gate (51) of said set of at least two gates (52 ', 51) being either set to a reference potential (55) or connected to the other of the outputs of said radio frequency alternating voltage source (30); said extractio means (50); n and acceleration and said continuous or alternating radiofrequency voltage source (30, 30 ") making it possible to form, at the outlet of the chamber (10), a beam (70, 70 ') comprising at least ions.
[2" id="c-fr-0002]
The thruster (100) according to claim 1, wherein: • the voltage source connected to the extraction and acceleration means (50) is a radiofrequency AC voltage source (30), • the set of means ( 30, 40) for forming the ion-electron plasma comprises at least one coil (40) supplied by the same radio frequency AC voltage source (30) via means (60) for managing the signal supplied by said source radio frequency voltage sensor (30) in the direction of, on the one hand, said at least one coil (40) and, on the other hand, the extraction and acceleration means (50) for forming an ion beam (70) and electrons at the outlet of the chamber (10).
[3" id="c-fr-0003]
The thruster (100) according to claim 1, wherein the set of means (30, 40, 30 ') for forming the ion-electron plasma comprises: • at least one coil (40) powered by an AC voltage source radio frequency (30 ') different from the DC voltage source (30 ") or radio frequency AC (30) connected to the extraction and acceleration means (50); or • at least one microwave antenna (40) powered by a microwave AC voltage source (30 ').
[4" id="c-fr-0004]
4. Propeller (100) according to the preceding claim, wherein the voltage source connected to the means (50) of extraction and acceleration is a radio frequency alternating voltage source (30), to form, at the output of the chamber ( 10), a beam (70) of ions and electrons.
[5" id="c-fr-0005]
5. Propellant (100) according to one of claims 2 or 4, wherein, when the means (50) extraction and acceleration is a set of at least two grids (52% 51) located at one end (E) of the chamber (10), the electroneutrality of the beam (70) of ions and electrons is obtained at least in part by adjusting the duration of application of the positive and / or negative potentials from the source a radio frequency alternating voltage (30) connected to the extraction and acceleration means (50),
[6" id="c-fr-0006]
6. Propellant (100) according to one of claims 2 or 4, wherein, when the means (50) of extraction and acceleration is an assembly of at least two grids (52 ', 51) located at a end (E) of the chamber (10), the electroneutrality of the beam (70) of ions and electrons is obtained at least in part by adjusting the amplitude of the positive and / or negative potentials from the source of radio frequency alternating voltage (30) connected to the extraction and acceleration means (50).
[7" id="c-fr-0007]
7. Propellant (100) according to claim 3, wherein the voltage source connected to the means (50) of extraction and acceleration is a DC voltage source (30 "), to form at the output of the chamber ( 10), a beam (70 ') of ions, the propellant (100) further comprising means (80, 81) for injecting electrons into said beam (70') of ions to provide electroneutrality.
[8" id="c-fr-0008]
8. Propellant (100) according to one of the preceding claims, wherein the reservoir (20) comprises a membrane (22 ') between the solid propellant (PS) and the envelope (21) provided with at least one orifice (22), said membrane (22 ') having at least one orifice (22 "), the surface of the or each orifice (22") of the membrane (22') being greater than the surface of the or each orifice ( 22) of the casing (21) of the reservoir (20).
[9" id="c-fr-0009]
9. Propellant (100) according to one of the preceding claims, wherein the or each grid (51, 52 ') has orifices whose shape is chosen from the following forms: circular, square, rectangular or slot-shaped, in particular parallel slots.
[10" id="c-fr-0010]
10. Propellant (100) according to one of the preceding claims, wherein the or each grid (51, 52 ') has circular orifices, whose diameter is between 0.2mm and 10mm, for example between 0.5mm and 2mm.
[11" id="c-fr-0011]
11. Propellant (100) according to one of the preceding claims, wherein, when the means (50) of extraction and acceleration out of the chamber (10) comprises a set of at least two grids (52 ', 51) located at the end (E) of its chamber (10), the distance between the two grids (52 ', 51) is between 0.2mm and 10mm, for example between 0.5mm and 2mm.
[12" id="c-fr-0012]
12. Propellant (10) according to one of the preceding claims, wherein the solid propellant (PS) is selected from: the diiodine, the diiodine mixed with other chemical components, ferrocene, adamantane or arsenic.
[13" id="c-fr-0013]
13. Satellite (S) comprising a thruster (100) according to one of the preceding claims and a power source (SE), for example a battery or a solar panel, connected to the or each DC voltage source (30 " ) or alternatively (30, 30 ') of the thruster (100).
[14" id="c-fr-0014]
14. Spatial probe (SS) comprising a thruster (100) according to one of claims 1 to 12 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 ') of the propellant (100).

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同族专利:

公开号 | 公开日

RU2018109227A3|2020-01-31|

FR3040442B1|2019-08-30|

ES2823276T3|2021-05-06|

SG11201801545XA|2018-03-28|

EP3344873B1|2020-07-22|

CN209228552U|2019-08-09|

US11060513B2|2021-07-13|

EP3344873A1|2018-07-11|

JP2018526570A|2018-09-13|

IL257700A|2022-01-01|

IL257700D0|2018-04-30|

US20180216605A1|2018-08-02|

CA2996431A1|2017-03-09|

WO2017037062A1|2017-03-09|

HK1251281A1|2019-01-25|

JP6943392B2|2021-09-29|

RU2018109227A|2019-10-03|

RU2732865C2|2020-09-23|

KR20180064385A|2018-06-14|

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法律状态:
2016-08-31| PLFP| Fee payment|Year of fee payment: 2 |

2017-03-03| PLSC| Publication of the preliminary search report|Effective date: 20170303 |

2017-05-31| PLFP| Fee payment|Year of fee payment: 3 |

2018-07-30| PLFP| Fee payment|Year of fee payment: 4 |

2019-05-28| PLFP| Fee payment|Year of fee payment: 5 |

2020-07-08| PLFP| Fee payment|Year of fee payment: 6 |

2021-06-15| PLFP| Fee payment|Year of fee payment: 7 |

优先权:

申请号 | 申请日 | 专利标题

FR1558071A|FR3040442B1|2015-08-31|2015-08-31|GRID ION PROPELLER WITH INTEGRATED SOLID PROPERGOL|

FR1558071|2015-08-31|FR1558071A| FR3040442B1|2015-08-31|2015-08-31|GRID ION PROPELLER WITH INTEGRATED SOLID PROPERGOL|

PCT/EP2016/070412| WO2017037062A1|2015-08-31|2016-08-30|Gridded ion thruster with integrated solid propellant|

EP16760449.5A| EP3344873B1|2015-08-31|2016-08-30|Gridded ion thruster with integrated solid propellant|

RU2018109227A| RU2732865C2|2015-08-31|2016-08-30|Mesh ion engine with solid working medium in it|

KR1020187007452A| KR20180064385A|2015-08-31|2016-08-30|Grid ion thruster with integrated solid propellant|

CA2996431A| CA2996431A1|2015-08-31|2016-08-30|Gridded ion thruster with integrated solid propellant|

US15/755,322| US11060513B2|2015-08-31|2016-08-30|Gridded ion thruster with integrated solid propellant|

ES16760449T| ES2823276T3|2015-08-31|2016-08-30|Ionic Grid Propellant with Integrated Solid Propellant|

CN201690001163.4U| CN209228552U|2015-08-31|2016-08-30|Ion propeller, satellite and space probe|

JP2018510837A| JP6943392B2|2015-08-31|2016-08-30|Ion thruster with grid with integrated solid propellant|

IL257700A| IL257700A|2015-08-31|2018-02-25|Gridded ion thruster with integrated solid propellant|

HK18110604.7A| HK1251281A1|2015-08-31|2018-08-17|Gridded ion thruster with integrated solid propellant|

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