Method of neutralising spatial charge of ion stream. RU patent 2520270.

FIELD: physics.

SUBSTANCE: invention relates to beam engineering and can be used to compensate (neutralise) for spatial charge of a beam of positive ions of electro-jet engines, particularly for use in propulsion devices of micro- and nanosatellites. The method of neutralising spatial charge of an ion stream of an electro-jet propulsion device by emitting electrons through multiple autoemission sources. Sources are placed around each of the electro-jet engines of said device. Emission currents of separate autoemission sources or groups of said multiple autoemission sources are controlled independent of each other.

EFFECT: reduced consumption the working medium of an electro-jet engine, including a multimode electro-jet engine or a multi-engine apparatus, minimum time for switching to neutralisation operating mode and fast switching of electron current according to the operating mode of said electro-jet engine, optimising transfer of electrons into the neutralisation region in order to reduce divergence of the ion beam or deviation thereof, thereby changing the direction of ion thrust.

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The technical field.

The invention relates to the line technology and can be used to charge (neutralization) of the space charge of the beam ions electro-engines, in particular, for use in the engine installations micro - and nano-satellites.

Prior art.

In ion rocket engines to ensure normal work in space conditions necessary injection of ions and electrons in equal amounts to SPACECRAFT (SC) was not charged negatively and this charge is not hindered ions during the ion engine due to electrostatic interaction. This problem can be solved by application of special devices - Converter, which is the source of electrons, which is installed at the outlet from the accelerator system ion flow electric-discharge of the engine (propulsion).

The goal of the invention is to implement the neutralization (compensation) of the space charge of the ion flow ERD thus, to further ensure the attainment of the optimum of the functional parameters and characteristics of electric propulsion for small satellites, for example to reduce the consumption of the working fluid ERD and thus prolong the life of such SPACECRAFT, during which it is possible to make maneuvering for a more accurate positioning in space. It is especially important to realize these purposes in the case of micro - and nano-satellites weighing from a few tens units kg and less, because the stock of a working body ERS (usually, xenon or, less frequently, krypton or their mixture) such KA limited. It is also significant, particularly in multi-mode ERD be able to ensure the minimum time of an exit for operating conditions of neutralization and fast switching electron current in coordination with working hours of such families. It is also desirable that implemented the method for the elimination of the space charge of an ion flow in ERD was also due to the electrostatic interaction issued a negative charge with the flow of ions to reduce the divergence of the beam, or to reject it, thus altering the direction vector ion thrust.

Compensation (neutralization) of the space charge of the beam ions in the General case of ion-beam technologies is carried out the introduction into the flow of ions of free electrons and/or electronegative molecules or atoms with high affinity to electron and large sections of the formation of negative ions in a collision with free electrons, respectively. Flows of free electrons and electronegative molecules or atoms support such that the density of the positive charge of the beam, at least not exceed the density of negative charge present in it of electrons and educated negative ions. Examples of means of neutralization of the positive charge of ion beams for technological applications, especially in technology surface treatment by ion beam and ion implantation, described in detail, including the contained numerous citations, for example, in the U.S. patent N5531420 "ION sent from the other device ELECTRON NEUTRALIZER", publ. 02.07.1996 year, the U.S. patent N5703375 "METHOD AND APPARATUS FOR ION BEAM NEUTRALIZATION", publ. 30.12.1997 year, the patent of the Russian Federation N2105368 "METHOD of NEUTRALIZARII space CHARGE of the BEAM IONS", publ. 20.02.1998 year, the U.S. patent N 6329650 "SPACE CHARGE NEUTRALIZATION OF AN ION BEAM", publ. 11.12.2001 year, the U.S. patent N 6359286 "METHOD AND APPARATUS FOR NEUTRALIZING SPACE CHARGE IN AN ION BEAM", publ. 19.03.2002 year, the U.S. patent N 6515408 "ION BEAM APPARATUS AND A METHOD FOR NEUTRALIZING SPACE CHARGE IN AN ION BEAM", publ. 04.02.2003 year, the U.S. patent N 6815697 "ION BEAM CHARGE NEUTRALIZER METHOD AND THEREFORE", publ. 09.11.2004 the year, the U.S. patent N 6872959 "THERMOELECTRON GENERATING SOURCE AND ION BEAM RADIATING APPARATUS WITH THE SAME", publ. 29.03.2005 year, the U.S. patent N 7276711 "BEAM SPACE CHARGE COMPENSATION DEVICE AND ION IMPLANTATION SYSTEM HAVING THE SAME", publ. 02.10.2007, providing General information about the methods of neutralization of electrostatic charge of the ion flux in such technologies.

Note that in the U.S. patent N6762423 "METHODS AND APPARATUS FOR ION BEAM NEUTRAEIZATTON IN MAGNETS", publ. 13.07.2004, described, in particular, methods of neutralization of the space charge of the beam electrons emitted in the direction perpendicular to the axis of the beam placed in an array or matrix along the path of the beam along its width multiple emission sources. All emission sources are connected to the power source and work in common for all mode autoemission.

In the vast majority of current and evolving electric propulsion engines (ERD) jet stream is formed accelerated flow of positive ions, as a rule, xenon or, less frequently, krypton or argon. Accordingly, the electrical charge of the ion beam, new electric propulsion motor must be compensated for by electrons emitted in the region of existence of volume of a positive charge. But, unlike the problem of compensation of a positive ion flow solved in the process of terrestrial plants, which is important to prevent the accumulation of the positive charge on the processed ion beam surface, electro-engines neutral goal is the removal of electrostatic charges on the body of the spacecraft (SC), which leads to certain differences in the ways and devices neutralize the flow of ions. Typical examples of implementation of the method described, in particular in the patent of Russian Federation N 2092983 "PLASMA ACCELERATOR", publ. 10.10.1997 year, the U.S. patent N6195980 "ELECTROSTATIC PROPULSION ENGINE WITH NEUTRALIZING ION SOURCE", publ. 06.03.2001, For the purposes of the present invention is important to note that all the above electro motor apply the method for the elimination of the space charge of the ion flow, emission of electrons by a single source - neutralizer, as a rule, on the basis of plasma of the electric discharge in the hollow cathode, initiated by the electrons emitted thermal emission cathode. Various structural features of the plasma chamber Converter ERD used in implementations of this method for the elimination of the space charge of the ion flow are described in detail, for example, in the Russian Federation patents N2168793 "KATOD-COMPENSATOR", publ. 10.06.2001 g, N 2173001 "KATOD-COMPENSATOR", publ. 27.08.2001,, N 2173002 "KATOD-COMPENSATOR", publ. 27.08.2001, in the U.S. patent N 6336318 "ION THRUSTER HAVING A HOLLOW CATHODE ASSEMBLY WITH AN ENCAPSULATED HEATER, AND ITS FABRICATION", publ. 08.01.2002, patents of the Russian Federation N 2287203 "PLASMA CATHODE-COMPENSATOR", publ. 10.11.2006,, N 2454046 "PLASMA ELECTRON EMITTER", publ. 27.01.2011 g, N 2410567 "UNIT CATHODE-COMPENSATOR", publ. 13.01.2011, also Known variants of the method based on the use of the plasma electron source based on capacitive high frequency (HF) electric arc. For example, in the U.S. patent N6870321 "HIGH-FREQUENCY ELECTRON SOURCE", publ. 22.03.2005, describes the Converter on the basis of RF plasma frequency in the range 100 kHz to 50 MHz. It should be noted, however, that this method of excitation of discharge requires the use of a matching wave load device, which complicates the design of the Converter. To completely eliminate the use of electrodes when creating a plasma source of electrons is possible due to the excitation of HF plasma not capacitive and magnetic induction discharge, as proposed in the U.S. patent N 7498592 "NON-AMBIPOLAR RADIO-FREQUENCY PEASMA EEECTRON SOURCE AND SYSTEMS AND METHODS FOR GENERATING EEECTRON BEAMS", publ. 03.03.2009, and N 7875867 "NON-AMBIPOEAR RADIO-FREQUENCY PEASMA EEECTRON SOURCE AND SYSTEMS AND METHODS FOR GENERATING EEECTRON BEAMS", publ. 25.01.2011, The disadvantage of this solution is that the use of the magnetic system in such a source is significantly increases its weight and size characteristics. In addition, to maintain plasma spent working gas, which makes this technology is hardly applicable in small CL because of the severe restrictions on weight and power consumption.

Options for implementation of methods of neutralization of the space charge of ion beams with respect to ion propulsion without the use of a thermionic cathode also describes, for example, patent RF N 2429591 "METHOD of NEUTRALIZATION of the space CHARGE of ION BEAMS IN ION ELECTRIC ROCKET ENGINES AND DEVICE FOR ITS IMPLEMENTATION (VARIANTS)", publ. 20.09.2011, and N2458490 "METHOD of REGULATION of ION ELECTRIC ROCKET ENGINE AND DEVICE FOR ITS IMPLEMENTATION (VARIANTS)", publ. 10.08.2012, The method is based on excitation by means of auxiliary energy source in the Autonomous cavity Converter gas discharge plasma and use plasma for emission of electrons in the neutralization of the space charge of ion beams. As an auxiliary source of energy use pulsed laser. The laser beam focusing send offline cavity Converter, is filled with a gas influx working substance ion engine, where in the area near the focus in the volume getprotocol working substance excite discharge, create the plasma and carry out the emission of electrons in the accelerated ion beam with the internal borders of plasma under action of external electric field. In a variant of the method is additionally sent to the Autonomous cavity Converter cesium vapor. The device neutralization of the space charge of ion beams contains an auxiliary source of energy on the basis of a pulsed laser. The disadvantage of this approach is the excessive complexity of the design, thereby potentially reducing its fault tolerance.

However, with the development of the concept of the use of micro-and nano-satellites weighing up to units of kilograms appeared the need to create specialized propulsion systems, which must be different low-power, low weight and high efficiency working body. An example of this electric propulsion engine is described, for example, in the U.S. patent N 6960888 "METHOD OF PRODUCING AND ACCELERATING AN ION BEAM" publ. 01.10.2005, It is obvious that the traditional ways of compensation of the space of a positive ion flow in electric propulsion motor installation of micro - and nano-satellites and implement these methods converters PA basis of plasma of an electric discharge of little use, because the weight and size characteristics of such converters become comparable with the engine and can't be improved substantially. In addition, their functioning implies consumption unused to produce thrust of the working gas, which also limits the applicability implemented with the help of the methods of neutralization of the space charge of an ion flow in ERD micro - and nano-satellites.

The method for the elimination of the space charge of an ion flow in ERD, carried out with the assistance of the Converter on the basis autoemission cathode, allows a more efficient electric propulsion thrusters with the required mass-dimension parameters and power consumption, unattainable with conventional methods of neutralizing charge of the ion flow. For example, there is a method of neutralization of the space charge of an ion flow in electric propulsion motor installation emission of electrons multiple emission sources arranged in a matrix of individual emitters. In articles "Field emission performance of multiwalled carbon nanotubes for a low-power spacecraft neutralizek", Acta Astronautica, v.64 (2009), pp.875-881, "Field emission cathode with electron optics for use in Hall thrusters", J.Appl.Phys. v.108, 054507 (2010) and the application PA receive U.S. patent N 2011/0005191 "COLD CATHODLS AND ION THRUSTERS AND METHODS OF MAKING AND USING SAME", publ. 13.01.2011, to implement the method used field emission emitters based on arrays of carbon nanotubes, and in the article "the Use of coated silicon field emitters as neutralizers for fundamental physics space missions", Advances in Space Research, v.48 (2011), pp.1265-1273 - emitters based on silicon nanostray that besieged improving autoemission and heat sink film coverings. However, we note that the use of microgstring field emission cathodes are not allowed to create converters, ensuring long service life due to the fact that microstrip in the process of emission subjected to extreme heat and ion bombardment that when working at pressure of the surrounding gas above 10 -5 Torr leads to swift topline and, thus, to reduction of the local electric field strength and the fall of the current autoemission. In the U.S. patent N 8080930 "SELF-REGENERATING NANOTIPS FOR LOW-POWER ELECTRIC PROPULSION (EP) CATHODES", publ. 20.12.2011, the method of recovery of microstoria feed him for microcapillary drops fusible metal, which freezes in the applied electric field, forming the desired profile microstoria to continue its operation in the mode effective autoemission. The disadvantage of this method is that to maintain the optimum conditions necessary tank with fusible metal, pulsed heater for its melting and power supply system to the heater and shaper profile the edge of the cold drops in strong polarizing field. All these nodes increases the mass and power Converter that limits the application of this technology of micro - and nano-satellites. In addition, when working with multiple field emission microstraining sources technically difficult to implement individual recovery of individual microstrip or groups of microstrip.

Another chosen as a prototype, an analogue of the proposed method for the elimination of the space charge of an ion flow in electric propulsion engine emission of electrons multiple sources described in the application for a patent USA N 2012/0085918 "ION BEAM IRRADIATION DEVICE AND METHOD FOR SUPPRESSING ION BEAM DIVERGENCE", publ. 12.04.2012, involving two or more emission sources of electrons around the ion flow electro motor direction issued by electrons at a tangent to the direction of magnetic field lines in the region of the gradient of the magnetic field. The implementation of such a method for the elimination of the space charge of an ion flow in electric propulsion engine allows you to reduce the divergence of the ion beam, which allows to improve the efficiency of the propulsion. The disadvantage of this method is the inability to control of emission sources in such a way as to be able to shape the field of locally excessive volume of negative charge, which are located along and beyond the axis of the beam, and alternating-time pulse, pulse-periodic regimes or constant current mode, which will allow for the account of electrostatic interactions such locally excessive volume of negative charge emitted electrons surround the positive charge of the ion flow focusing or reject ion flow, promptly varying thus the direction of the thrust vector ERD.

An additional objective of the present invention is an opportunity in its implementation to implement the change in vector direction ion thrust. The ability to change the direction of the thrust vector is one of the important characteristics considered in the development of advanced electro-propulsion systems for spacecraft.

Known widely used way to control the size and direction of thrust vector generated electric propulsion propulsion system, which is to unite in a single module few ERD, usually placed at an angle to each other and managed independently from each other. Changing the configuration and behavior of the individual for the electric propulsion system, you can control the size and direction of the vector is created thrust. Options for implementation of such method is described, for example, patent RF N 2134220 ELECTRIC TRACTION SYSTEM (OPTIONS), spacecraft (OPTIONS) AND The WAY of the APPLICATION, SELECT TRACTIVE EFFORT (VARIANTS)", publ. 10.08.1999 year, the U.S. patent N 6279314 "CLOSED ELECTRON DRIFT PLASMA THRUSTER WITH A STEERABEE THRUST VECTOR", publ. 28.08.2001, in the patent of Russian Federation N 2196396 "METHOD THRUST VECTOR CONTROL electric propulsion ENGINE AND DEVICE FOR ITS REALIZATION", publ. 10.01.2003, in the U.S. patent N 7459858 "HALL THRUSTER WITH SHARED MAGNETIC STRUCTURE", publ. 02.12.2008 year, the application for a patent USA N 2009/0308049 "ELECTRIC PROPULSION SYSTEM", publ. 17.12.2009 year, the U.S. patent N 7690187 "MODULAR MICROPROPULSION DEVICE AND SYSTEM", publ. 06.04.2010 year, the application for a patent USA N 2011/0073713 "DRIVE ARRANGEMENT IN A SPACECRAFT", publ. 31.03.2011,

The disadvantages of these analogues is nonoptimality of implementation of low-thrust mode, in which the scheme is formed as a difference between vector thrust opposing impulses of individual families. However, in the case of small spacecrafts hosting multiple propulsion systems may not always be justified due to the significant increase in the weight and size of the propulsion system. Therefore, in some cases it is expedient to use the ion flux deflecting system. For example, patent RF N 2196397 "METHOD AND DEVICE FOR ION ACCELERATION IN PLAZMENNYKH ACCELERATORS HALL TYPE, publ. 10.01.2003, and the application for a patent USA N 2012/0167548 "PLASMA THRUSTERS", publ. 05.07.2012, describe the options method of controlling the direction of ion flow and, consequently, thrust vector ERD change the configuration of the magnetic field changes of the current system of electromagnets. The nearest analogue is the way deviations ion flow implemented in ERD, described in the patent of the Russian Federation 2088802 "HALL ENGINE", publ. 27.08.1997, in which the output cutoff engine installed additional electrodes and with the filing of their potential and simultaneous connection of additional electromagnetic sources of the magnetic field is created radial electric field, deflecting the ion flux. This design ERD allows you to reject the vector ion thrust to within a few degrees, but differs excessive complexity.

The proposed method of neutralization of the space charge of the ion flux electric propulsion engines is possible correction of the direction of ions due to optimization of transport of electrons autoemission in the area of neutralization that is achieved by the fact that electrons can be issued by all or part of emission sources. Depending on the mode control the operation of multiple emission sources placed around ERD, the formation of the field of locally excessive volume of negative charge along or outside the axes of ion beams included in ERD, ensuring due to electrostatic interaction excess negative charge emitted electrons surround the positive charge of the ion flow is additionally focusing or reject the ion flow, promptly, thereby adjusting the direction of the thrust vector ERD. Therefore, an important distinctive feature of the proposed method of neutralization is that he is placed around each of electro-engine propulsion system on ion-powered multiple emission sources with the ability to control current issue of individual emission sources or groups of emission sources independently from each other, and consistently with the duty of the individual for the electric propulsion system. Additional installation around the nozzle such electro engines multiple emission sources with the possibility control current issue of individual emission sources or groups of emission sources independently of each other will allow the region to locally excessive volume of negative charge mainly along the axis of the beam, in concert with changes in the direction of the flow of ions ERD or off-axis of the beam, and alternating-time pulse, pulse-periodic regimes or constant current mode, which will allow for the account of electrostatic interactions focusing or reject the ion flux in ERD, thus while the space charge neutralization ion flow and, optionally, promptly adjusting the direction of the vector ion thrust.

Known methods of independent power management of individual units electro-propulsion. Thus, in the U.S. patent N 6724160 "ION-SOURCE NEUTRALIZATION WITH A HOT-FILAMENT CATHODE-NEUTRALIZER", publ. 20.04.2004, describes automatic adjustment of the intensity of the electron source based on thermionic cathode Converter ion charge ERD in dynamic change of the amount of positive charge, which must be compensated, and in the U.S. patent N 6948305 "METHOD AND APPARATUS FOR BALANCING THE EMISSION CURRENT OF NEUTRALIZERS IN ION The THRUSTER ARRAYS", publ. 27.09.2005, describes the ways of optimization of modes of operation of converters, in multidwelling reactive systems so that at decrease of the ion flow of some of engines, producing the corresponding redistribution of the electron current separate converters to electronic current separate neutralizers decreased while maintaining the integral value of the electron current. Given essentially nonlinear dependence of life; from operating temperature, this method of current control of individual neutralizers leads to increase of their resource and, accordingly, the propulsion system in General. In the General case are multifunctional power sources simultaneously provide and the ERD, and Converter - all channel power: and on the establishment and maintenance of plasma, the creation of a magnetic field, the work of the Converter. This approach, in particular, described in U.S. patent N 8024917 “MULTI-FUNCTIONAL POWER SUPPLY FOR A HALL THRUSTER”, publ. 27.09.2011, or in the application for a patent USA N 2011/0258981 "MICRO-CATHODE THRUSTER AND A METHOD OF INCREASING THRUST OUTPUT FOR A MICRO-CATHODE THRUSTER", publ. 27.10.2011, However, all such systems assume that each Converter is a single device for which therefore does not provide options multimode operation of individual components of its sources, while maintaining the integral value of the electron current Converter.

It is also known that the use of emission sources based on carbon nanotubes are the problems of the period of trouble-free operation, as described, for example, in the article "Lifetime and failure mechanisms of'an being arrayed carbon nanotube field emission cathode", IEEE Transaction on Electron Devices, v.57 (2010), pp.3163-3168. Based on the above, the optimal material for the formation of emission sources and ensure reliable and uninterrupted operation of the neutralizer space charge of the ion flow in electric propulsion propulsion installation is nanocrystalline graphite thin film material, deposited on technology of gas-phase synthesis of the DC discharge without use of catalysts and with a characteristic microreserves texture formed mainly vertically oriented graphite plates of different thickness and containing a number of nanotubes and nanowhiskers (moustache) ("nano-crystalline graphite is a promising field emission material", Integral, №3(65), 2012, p.14-16). In structure of nanocrystalline graphite film may include education following morphology: graphite crystals, graphene plane, carbon nanotubes, nano-diamond crystals, amorphous carbon.

In General, it is important to emphasize that the use in the implementation of methods of neutralization of the space charge of the ion flux of electron sources on the basis of plasma in electric propulsion low-thrust causes weight and dimension parameters of the Converter and the electric become comparable. In addition, due to the fact that the work of the Converter on the basis of plasma source of electrons implies a particular gas flow rate, which is not used to produce thrust, ERD low-thrust is increased relative share of the non-functional losses. Realization of the method for the elimination of the space charge of the ion flux of electron sources on the basis of multiple field emission cathodes allows a more efficient propulsion low-thrust with functional parameters, unattainable when using standard technical solutions.

Disclosure of the invention.

Neutralization (compensation) of the space charge of the ion flow ERS on the proposed method is implemented so that to reduce the consumption of the working fluid ERD, including multimode ERD or multi-engine installation, ensure the minimum time of an exit for operating conditions of neutralization and fast switching electron current in coordination with working hours of such ERD, optimizing the transport of electrons in the area of neutralization, in order to reduce the divergence of the beam, or reject it, thus altering the direction vector ion thrust.

To achieve these goals, we propose a method of neutralization of the space charge of the ion flow electro-propulsion emission of electrons multiple emission sources located around each of electric propulsion engines of this setup, wherein, management of current emissions of individual emission sources or groups specified multiple emission sources produce independently from each other.

The electron emission of individual emission sources or groups of emission sources independently from each other produce, in the General case, the method in different modes and their combinations, including variable time in pulse, pulse-periodic regimes or constant current mode pulse, pulse-periodic regimes or constant current mode.

In addition, electron beams emitted individual emission sources or groups of emission sources, oriented in the direction of movement of ions thus to form near the axis of the beam area locally excessive volume of negative charge.

In the first case of application of a method for the elimination of the space charge of the ion flow formed emitted by the electrons in the field of locally excessive volume of negative charge feature along the axis of the flow of ions electric propulsion engine, compensating for the account of the electrostatic interaction with the flow of ions its divergence.

In other variant of application of the method of neutralization of the space charge of the ion flow formed emitted by the electrons in the field of locally excessive volume of negative charge have off-axis of the flow of ions electric propulsion engine, rejecting the flow of ions through the electrostatic interaction.

Finally, for the implementation of this method for the elimination of the space charge of the ion flow multiple emission sources preferably made on the basis of nano-crystalline graphite.

The implementation of the invention.

Ideally, the implementation of the proposed method for the elimination of the space charge of the ion flow multiple avtoemissionnye sources preferably made on the basis of nano-crystalline graphite (NKG), formed on conductive substrate by the method of plasma-chemical synthesis is formed film (layer) NANOKRISTALLIChESKOGO graphite in the form of three-dimensional nano-structure, which includes education different morphology: graphite crystals, graphene plane, carbon nanotubes, nano-diamond crystals, amorphous carbon, etc.

As a conductive substrate can be used: the glass carbon, carbon fabric, foil made of titanium, as well as from transition metals and alloys.

Synthesis NKG film is in the plasma of the electric direct current discharge in the chamber, provided with a distribution system that ensures supply and control of the working gas mixture containing carbonic gas and hydrogen. DC discharge is ignited between two metal electrodes attached to the system power supply. The substrate on which it is supposed to synthesize NKG film, is located on the anode. For example, DC discharge light with a current density of 0.15 to 1 A/cm2 , sedimentation NKG film is produced when the vapour pressure of the gas mixture 50-300 Top and the temperature of the substrate 800-1400°C. the concentration of carbonic gas in the mixture varies from 3% to 15%. As carbonic gas can be selected: methane, propane and other hydrocarbons or mixtures thereof. The working gas mixture can also include a pair of alcohols. Also working gas mixture can be diluted up to 75% inert gas such as argon, while maintaining full gas pressure in the reactor plasma-chemical synthesis.

Optimal three-dimensional nano-structure of the film NKG are an ordered or unordered array mainly properly oriented to the substrate graphite nano - and microfiber with the characteristic height of up to 300 microns and density of the PA substrate 0,1% to 100 microns -2 . In structure of nanocrystalline graphite film may include education following morphology: graphite crystals, graphene plane, carbon nanotubes, nano-diamond crystals, amorphous carbon, etc.

The proposed method for the elimination of the space charge of the ion flux electric propulsion engines PA the basis of automitter of nano-crystalline graphite and individual-group manage such autohemotherapy located around generating ion flows of parts and components electro-propulsion, embodies the most advanced engineering solutions, capable to achieve optimal functional parameters and characteristics ERD for small space, first of all, to minimize the consumption of the working fluid ERD and thus extend the life of the SPACECRAFT, especially micro-and nano-satellites weighing from several tens to units of kilograms and less than during which may make maneuvering for a more accurate positioning in space.

Manage multiple emission sources PA basis described above NKG of avtomatov located around the electric propulsion engine propulsion ion thrust, with the ability to control current issue of individual emission sources or groups of emission sources independently from each other, and consistently with the duty of the individual for the electric propulsion system, implemented with the help of specialized electronic circuits. In the example of the method for the control system of multiple emission sources of electrons is composed of 40 takasogawa high-voltage switches. Each key controls individual avtokarta or group of avtomatov and its mode is set independently. To compensate for the possible spread of the parameters of individual emission sources provided by the current job for each key. Current assignment of the key 8-channel digital-to-analog Converter, which is dynamically loaded programmable logic integrated circuit (FPGA). FPGA also provides control of high-voltage keys set time parameters.

The values of currents and time parameters of pulses are single-chip microcontroller. Also envisaged is the job of these settings from a Central computer via optically isolated RS-232 interface. The microcontroller also takes real-time values of currents that allows you to monitor system activity. All of these functions are implemented in one adapted microcontroller software.

The management system of multiple emission sources provides the opportunity to work with several such modules in one system. This includes synchronization modules of the control system using fibre channel. The set of implemented technical solutions allows to optimize the work of the Converter on the basis of multiple emission sources of electrons due to mnogorazemny his work while maintaining total value of electronic current autoemission.

Thus, when implementing the described method can optimise transport electron autoemission in the area of neutralization, including that there is a possibility to form excessive volume negative charge in the required field, in particular, mainly along or outside the axes of ion beams included in ERD, and in the General case, the method in different modes and their combinations, including variable time in pulse, pulse-periodic regimes or constant current mode, which further allows for the account of electrostatic interactions locally excessive volume of negative charge emitted electrons and positive volume charge of the ion flow focusing or reject the ion flux, changing the direction of the thrust vector ERD.

1. Methods of neutralization of the space charge of the ion flow electro-propulsion emission of electrons multiple emission sources located around each of electric propulsion engines of this setup, wherein the management of current emissions of individual emission sources or groups specified multiple emission sources produce independently from each other.

2. The method according to claim 1, characterized in that the emission of electrons individual emission sources or groups of emission sources independently from each other produce in pulse, pulse-periodic regimes or constant current mode.

3. The method according to claim 1 or 2, wherein the electron beams emitted individual emission sources or groups of emission sources, oriented in the direction of movement of ions thus to form near the axis of the beam area locally excessive volume of negative charge.

4. The method according to claim 3, wherein formed emitted by the electrons in the field of locally excessive volume of negative charge feature along the axis of the flow of ions electric propulsion engine, compensating for the account of the electrostatic interaction with the flow of ions its divergence.

5. The method according to claim 3, wherein formed emitted by the electrons in the field of locally excessive volume of negative charge have off-axis of the flow of ions electric propulsion engine, rejecting the flow of ions through the electrostatic interaction.

6. The method according to claim 1, characterized in that these multiple emission sources is made on the basis of nano-crystalline graphite.