EP0541309A1 - Accélérateur de plasma avec parcours fermé d'électrons - Google Patents

Accélérateur de plasma avec parcours fermé d'électrons Download PDF

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Publication number
EP0541309A1
EP0541309A1 EP92309991A EP92309991A EP0541309A1 EP 0541309 A1 EP0541309 A1 EP 0541309A1 EP 92309991 A EP92309991 A EP 92309991A EP 92309991 A EP92309991 A EP 92309991A EP 0541309 A1 EP0541309 A1 EP 0541309A1
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Prior art keywords
external
magnetic
internal
discharge chamber
pole
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Application number
EP92309991A
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German (de)
English (en)
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EP0541309B1 (fr
Inventor
Boris A. Arkipov
Andrey M. Bishaev
Vladimir M. Gavriushin
Yuri M. Gorbachov
Vladimir P. Kim
Vjacheslav I. Kozlov
Konstantin N. Kozubbsky
Nikolai N. Maslennikov
Alexei I. Morozov
Dominic D. Sevruk
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Fakel Enterprise
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Fakel Enterprise
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Priority claimed from US07/866,149 external-priority patent/US5359258A/en
Application filed by Fakel Enterprise filed Critical Fakel Enterprise
Publication of EP0541309A1 publication Critical patent/EP0541309A1/fr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • F03H1/0037—Electrostatic ion thrusters
    • F03H1/0062—Electrostatic ion thrusters grid-less with an applied magnetic field
    • F03H1/0075—Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
    • H05H1/00—Generating plasma; Handling plasma
    • H05H1/54—Plasma accelerators

Definitions

  • the present invention relates to the field of plasma technology and can be used in the development of Accelerators with Closed Electron Drift (ACED) employed as Electric Propulsion Thrusters (EPT), or for ion plasma material processing in a vacuum.
  • ACD Accelerators with Closed Electron Drift
  • EPT Electric Propulsion Thrusters
  • thrusters with a closed electron drift.
  • These thrusters typically comprise a discharge chamber with an annular accelerating channel; an anode situated in the accelerating channel; a magnetic system; and a cathode.
  • These thrusters are effective devices for ionization and acceleration of different substances, and are used as EPT and as sources of accelerated ion flows.
  • they have a relatively low efficiency and insufficient lifetime to provide a solution of a number of problems.
  • the closest prior art approach to the present invention is a thruster with a closed electron drift comprising: a discharge chamber with an annular accelerating channel facing the exit part of the discharge chamber and formed by the inner and outer discharge chamber walls with closed cylindrical equidistant regions of working surfaces; an annular anode-distributor having small channels for a gas supply situated inside the accelerating channel at a distance from the exit ends of the discharge chamber walls that exceeds the width of the accelerating channel; a gas supply from the anode to the accelerating channel via a system of feedthrough holes on the anode exit surface; a magnetic system with external and internal poles placed at the exit part of the discharge chamber walls on the outside of the outer wall and inside the internal wall, respectively, to form an operating gap; a magnetic path with a central core, and with at least one outer and one inner source of magnetic field placed in the magnetic path circuit at the internal and external poles, respectively; and, a gas discharge hollow cathode placed outside the accelerating channel.
  • This thruster also has the a
  • the present invention increases the thruster efficiency and lifetime, and decreases the amount of contamination in the flow by using an optimal magnetic field structure in the accelerating channel and improvements in thruster design.
  • the present invention is a plasma thruster with closed electron drift comprising: a discharge chamber with an annular accelerating channel facing the exit part of the discharge chamber, said annular accelerating channel bounded by the internal and external walls of the discharge chamber with closed cylindrical equidistant regions of working surfaces and an exit part of the discharge chamber; an annular shaped anode gas-distributor situated inside of the accelerating channel at a distance from the exit plane of the discharge chamber exceeding the width of the accelerating channel with apertures for a gas supply to the accelerating channel via a feedthrough system of holes on the exit of the anode surface; a magnetic system with external and internal poles situated near the exit part of the discharge chamber walls, the external pole outside of the outer wall and the internal pole inside of the internal wall, and the poles forming an operating gap; a gas discharge hollow cathode placed outside the
  • Fig. 1 is a cross-sectional view of a preferred embodiment of a plasma accelerator with closed electron drift constructed according to the present invention.
  • Fig. 2 is a cross-sectional view of a plasma accelerator with magnetic screens placed with a gap relative to the magnetic path.
  • Fig. 3 is a preferred embodiment of a thruster with magnetic poles and screens divided in four parts and equipped with four systems of magnetic coils.
  • Fig. 4 shows an alternate embodiment of the thruster with plane parallel parts.
  • a preferred embodiment of a plasma thruster is comprised of: an anode gas-distributor 1 with gas distributing cavities 15 and feedthrough holes 16 for gas supply; a cathode 2; a discharge chamber 3 with exit end parts 3a and 3b; an internal magnetic screen 4; an external magnetic screen 5; an external pole 6 of the magnetic system, which can be assembled from the separate parts 6 I , 6 II ,6 III , 6 IV (Fig. 3 and 4); an internal pole 7 of the magnetic system; a magnetic path 8; an internal source of magnetic field_coil 9; an external source of magnetic field_coil 10, which can be comprised of several coils (10 I , 10 II , 10 III , 10 IV Fig.
  • the central core 12 can be constructed with a cavity 20.
  • the discharge chamber 3 may have plane parallel regions 21 (Fig. 4). In these regions there are planes of symmetry I and II (Fig. 3 and 4), and a generatrix III (Fig. 1) of a cone tangent to the internal edge of the exit end part 3b of the discharge chamber outer wall.
  • the external pole 6 and the external screen 5 should be comprised of parts (for example, 6 I , 6 II , 6 III and 6 IV in Fig. 3 and 4) symmetrical with respect to said planes I and II.
  • the external sources of magnetic field 10 should be constructed in four groups of magnetic coils (10 I , 10 II , 10 III , 10 IV in Fig. 3 and 4); each of the magnetic coils 10 in the magnetic circuit is connected with one of the external pole parts 6 I , 6 II 6 III and 6 IV .
  • the thruster is constructed with elongated pole parts 6 I and 6 III and a larger quantity of coils 10 I and 10 III (Fig. 3 and 4).
  • the central core 12 can be made with several cavities 20, and each one may have the cathode 2 (Fig. 4). It is evident that for a side placement, several cathodes 2 can be installed.
  • the discharge chamber 3 is preferably made out of thermally stable ceramic material with the annular accelerating channel formed by its walls.
  • the anode gas-distributor 1, the holder 17 and the thermal screens 13 are made of thermally stable, metallic, non-magnetic material, for example, stainless steel.
  • a high temperature stable wire is used to make the magnetic coils 10.
  • the magnetic path 8, the central core 12, and the cores of the magnetic coils 9 and 10 are constructed of a magnetically permeable material.
  • the cathode 2 can be located at the side of the discharge chamber 3, or can be placed centrally to the discharge chamber 3 (Fig. 1). In the central placement, the cathode 2 is in the cavity 20 of the central core 12.
  • the linear gaps ⁇ 1 and ⁇ 2 between the screens 4 and 5 and poles 7 and 6 do not exceed half of the distance ⁇ between the poles 6 and 7. It is preferable to construct the magnetic system in such a way that the internal pole 7 is placed a distance ⁇ 4 from the middle point of the accelerating channel that exceeds the distance ⁇ 3 from the internal magnetic screen 4 to said middle point of the accelerating channel.
  • the exit end parts 3a and 3b of the discharge chamber 3 have an increased thickness ( ⁇ 2 and ⁇ 1, respectively, in Fig. 1).
  • the end parts 3b and 3a of the discharge chamber are extended the distances ⁇ 5 and ⁇ 6, respectively, relative to the planes tangent to the exit surfaces of the magnetic system poles 6 and 7, respectively.
  • the holder 17 is in contact with the discharge chamber 3 and the magnetic system only in the places of direct contact, (i.e., the holder 17 represents a thermal resistance).
  • the thermal screens 13 cover the discharge chamber 3 and shield the magnetic system from the heat flow from the side of the discharge chamber 3.
  • one end of the cathode 2 is situated near the plane tangent to the edge of the wall behind the discharge chamber 3 (Fig. 2), in other words, a distance ⁇ 7 (Fig. 1 and Fig. 2) from the cathode exit end to the plane in the acceleration direction must not exceed 0.1d c , (Fig. 2) where d c is the cathode 2 diameter.
  • the cathode 2 is situated outside of the region of intensive influence of the accelerated flow of ions.
  • the magnetic screens 4 and 5 in the thruster can be installed with a gap respective to the magnetic path and interconnected with at least one bridge 19 made of magnetically permeable material as shown in Figure 2.
  • Figure 3 illustrates one embodiment of a thruster with the discharge chamber 3, the anode 1, and the magnetic system, which are symmetrical relative to two mutually perpendicular linear planes I and II.
  • the external pole 6 and the external magnetic screen 5 are designed with the opened cuttings symmetrical to the planes I and II, and dividing the pole 6 and screen 5 into four parts symmetrical to the said planes.
  • the external sources of the magnetic field 10 are in the form of 4 groups of magnet coils, each placed in the magnetic path circuit and connected with one part of the external pole 6.
  • the thruster it is preferable to design the thruster such that the exit end parts 3a and 3b of the discharge chamber 3, the poles 6, 7, and the magnetic screens 4, 5 are located in parallel planes perpendicular to the acceleration direction.
  • a cavity 20 is created by the central core of the magnetic path 12 and the internal pole 7.
  • the cathode 2 is placed in said cavity and the cathode exit end located with respect to the discharge chamber end at a distance not more than 0.1d c , where d c is the cathode diameter.
  • the thruster in such a way that the discharge chamber 3 is fastened to the external pole of the magnetic system 6 by a holder 17.
  • the holder 17 is connected to the discharge chamber 3 proximate the front part and is situated between the external magnetic screen 5 and the discharge chamber 3 with a gap between the latter except for the point of their connection.
  • the thruster operates in the following way.
  • the sources of the magnetic field 9 and 10 create in the exit part of the discharge chamber 3 a mainly radial magnetic field (transverse to the acceleration direction) with induction B.
  • the electric field with strength E along the acceleration direction is developed by applying a voltage between anode 1 and cathode 2.
  • the working gas is supplied through the tube 14 to the gas distributing cavities 15 inside the anode 1, which balance the gas distribution along the azimuth (anode ring), through the channel holes 16, and pass the gas into the accelerating channel.
  • a discharge is ignited in the hollow cathode 2.
  • the applied electric field gives the possibility for electrons to come into the accelerating channel.
  • the balance of energy acquisition and loss determines the average values of electron energy, which at sufficiently high voltages U d between cathode 2 and anode 1, and the electric field strength E, can be sufficient for effective gas ionization.
  • the generated ions are accelerated by the electric field and acquire velocities corresponding to the potential difference ⁇ U from the place of ion formation to the plasma region beyond the accelerating channel cross-section.
  • v (2q ⁇ U/M) 1/2 , where q and M are the ion charge and mass, respectively.
  • the accelerated ion flow at the thruster exit attracts an amount of electrons necessary for a neutralization of the space charge.
  • the ion flow out of the thruster creates the thrust.
  • the special feature of the thruster is that ion acceleration is realized by the electric field in a quasi-neutral media. That is why the measured ion current densities, j (roughly 100 mA/cm2 and more), significantly exceed the current densities in the electrostatic (ion) thrusters at comparable voltages (roughly 100 - 500 V).
  • the internal screen 4 covers the internal source of the magnetic field 9 and is located with a longitudinal gap relative to the internal pole 7 defined by ⁇ 2 (Fig. 1).
  • the external screen 5 is made with the end part located inside of the external source of the magnetic field 10 covering, at least, the exit part of the walls of the discharge chamber 3 and placed with a longitudinal gap relative to the external pole 6 defined by ⁇ 1 (Fig. 1).
  • a magnetic system of such design is far more capable of controlling magnetic field topography in the accelerating channel than earlier magnetic systems because screening a larger part of the accelerating channel allows for decreases in the magnetic field strength within the accelerating channel.
  • the magnetic system contemplated allows for necessary magnetic fields at increased gaps ⁇ between poles 6 and 7, if the gap values ⁇ 1 and ⁇ 2 between the end sides of magnetic screens 4 and 5 and corresponding poles 7 and 6 do not exceed ⁇ /2 (Fig. 1). If the gaps are increased more than ⁇ /2, a gradual lowering of thrust efficiency occurs. The best results are achieved at a minimal distance between the screens' end parts. That is, at the closest location to the discharge chamber 3 allowed by the design.
  • gaps ⁇ 1 and ⁇ 2 depends on the pole 6, 7 sizes, and on the ratio of distances between the screens' end parts ( ⁇ 3 on Fig. 1) and corresponding poles ( ⁇ 4 on Fig. 1) up to the channel half-length. Further movement of poles from the channel half-length, permits smaller longitudinal gaps between the screens 4 and 5 and the corresponding poles 7 and 6. It is also natural, when dealing with chosen sizes of poles 7, 6 and screens 4, 5, that the distances must be such that there will be no magnetic saturation of the screen material. The proper distances can be checked by calculations or by experiments.
  • the optimization of the magnetic field structure improves the focusing of the flow and decreases the general interaction intensity of the accelerated plasma flow with the discharge chamber walls. This results in an increase in thrust efficiency, a decrease in degradation, and, correspondingly, an increase in thruster lifetime and a decrease in the flow of sputtered particles (contamination) from the walls.
  • Higher thruster efficiency with an increased gap between the poles ⁇ allows increased thicknesses of the discharge chamber exit walls ( ⁇ 1 and ⁇ 2 on Fig. 1), thus prolonging the thruster lifetime.
  • the suggested magnetic system with screens also allows the exit end parts 3a, 3b of the discharge chamber 3 to move forward outside the pole plane to the distances ⁇ 5 and ⁇ 6 (Fig. 1), thus protecting the poles 6, 7 of the magnetic system from sputtering by the peripheral ion flows. Note that non-significant values of transverse and back ion flows is an important feature of the thruster operation.
  • the thruster efficiency can be increased if its scheme and design allow transverse deflection of the accelerated plasma flow. To realize such a deflection there are different schemes.
  • the division of the external pole 6 and the magnetic screen 5 allow a flow deflection with little change of other elements of construction.
  • the flow deflection is achieved because it is possible to develop different configurations of the magnetic field lines in different sections along the azimuth. For example, to increase the magnetizing currents in the coils of 10 I (see Fig.
  • a typical configuration is a thruster with plane ends of the sides of the discharge chamber 3 as the plane.
  • the central core cavity, and the placement of the cathode in it allows an increase of the azimuthal (in the direction of the electron drift) uniformity of the discharge, and greater efficiency of the thruster, though not significantly (i.e., several percent). It is appropriate to place the cathode exit side near the plane tangent to the plane of the wall end side of the discharge chamber. If the cathode 2 is extended from the central cavity to a distance exceeding 0.1d c , intensive erosion of the cathode external parts by accelerated ions of the main flow results. However, placing the cathode 2 in a cavity deeper than 0.1d c , leads to a sharp increase of the discharge voltage to ignite the thruster.
  • the fastening of the discharge chamber 3 with a special holder 17 to the external pole 6 of the magnetic system improves the thruster thermal scheme.
  • the main heat release takes place in the discharge chamber 3. That is why the introduction of the thermal resistance (through holder 17), and screens 4 and 5 between the discharge chamber 3 and the magnetic system, decreases the heat flow from the discharge chamber 3 to the magnetic system. It also improves the conditions of thermal release from the magnetic system due to the usage of a large surface of the external pole 6, and decreases the high temperature level due to the immediate heat removal directly to the heat disposal element. This effects a decrease in the energy loss of the magnetic system and an increase of its lifetime.
  • the suggested invention increases the efficiency and the lifetime of the thruster, and decreases the amount of impurities in the flow due to the sputtering of the elements of construction.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Plasma Technology (AREA)
EP19920309991 1991-11-04 1992-10-30 Accélérateur de plasma avec parcours fermé d'électrons Expired - Lifetime EP0541309B1 (fr)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
SU5018122 1991-11-04
SU5018122 1991-11-04
US07/866,149 US5359258A (en) 1991-11-04 1992-04-09 Plasma accelerator with closed electron drift
US866149 1992-04-09
SU5055718 1992-09-03
SU5055718 1992-09-03

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EP0541309A1 true EP0541309A1 (fr) 1993-05-12
EP0541309B1 EP0541309B1 (fr) 1996-01-17

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995000758A1 (fr) * 1993-06-21 1995-01-05 Societe Europeenne De Propulsion Moteur a plasma de longueur reduite a derive fermee d'electrons
WO1996006518A1 (fr) * 1994-08-25 1996-02-29 Aeorospatiale Societe Nationale Industrielle Accelerateur plasmatique a flux electronique ferme
EP0743669A1 (fr) * 1995-05-16 1996-11-20 VTD Vakuumtechnik Dresden GmbH Source d'ions
EP0800197A1 (fr) * 1996-04-01 1997-10-08 Matra Marconi Space France S.A. Accélérateur de plasma à effet Hall
DE19828704A1 (de) * 1998-06-26 1999-12-30 Thomson Tubes Electroniques Gm Plasmabeschleuniger-Anordnung
EP0982976A1 (fr) * 1998-08-25 2000-03-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Propulseur à plasma à dérive fermée d'électrons adapté à de fortes charges thermiques
US6075321A (en) * 1998-06-30 2000-06-13 Busek, Co., Inc. Hall field plasma accelerator with an inner and outer anode
FR2788084A1 (fr) * 1998-12-30 2000-07-07 Snecma Propulseur a plasma a derive fermee d'electrons a vecteur poussee orientable
US6150764A (en) * 1998-12-17 2000-11-21 Busek Co., Inc. Tandem hall field plasma accelerator
WO2000070928A2 (fr) * 1999-05-18 2000-11-30 Gosudarstvennoe Unitarnoe Predpriyatie 'vserossysky Elektrotekhnichesky Institut Imeni V.I. Lenina' Procede de formation et d'acceleration de plasma et accelerateur de plasma utilisant le courant d'electrons en circuit ferme
WO2001071185A2 (fr) * 2000-03-22 2001-09-27 Thales Electron Devices Gmbh Dispositif accelerateur de plasma
DE10130464A1 (de) * 2001-06-23 2003-01-02 Thales Electron Devices Gmbh Plasmabeschleuniger-Anordnung
US6864486B2 (en) 2001-05-16 2005-03-08 Veeco Instruments, Inc. Ion sources
RU2509918C2 (ru) * 2009-01-27 2014-03-20 Снекма Двигатель с замкнутым дрейфом электронов
CN108799032A (zh) * 2018-05-03 2018-11-13 兰州空间技术物理研究所 基于多孔金属材料的阳极组件及其制作方法
CN111120232A (zh) * 2018-11-01 2020-05-08 哈尔滨工业大学 一种可实现微调控放电性能的会切场等离子体推力器
CN111156140A (zh) * 2018-11-07 2020-05-15 哈尔滨工业大学 可提高推力分辨率和工质利用率的会切场等离子体推力器
WO2023038611A1 (fr) * 2021-09-13 2023-03-16 Частное Акционерное Общество "Фэд" Moteur ionique-plasmique stationnaire

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0463408A2 (fr) * 1990-06-22 1992-01-02 Hauzer Techno Coating Europe Bv Accélérateur de plasma avec parcours fermé d'électrons

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0463408A2 (fr) * 1990-06-22 1992-01-02 Hauzer Techno Coating Europe Bv Accélérateur de plasma avec parcours fermé d'électrons

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
SOVIET PHYSICS TECHNICAL PHYSICS. vol. 23, no. 9, September 1978, NEW YORK US pages 1055 - 1057 BISHAEV A. M. 'LOCAL PLASMA PROPERTIES IN A HALL-CURRENT ACCELERATOR WITH AN EXTENDED ACCELERATION ZONE' *

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5475354A (en) * 1993-06-21 1995-12-12 Societe Europeenne De Propulsion Plasma accelerator of short length with closed electron drift
WO1995000758A1 (fr) * 1993-06-21 1995-01-05 Societe Europeenne De Propulsion Moteur a plasma de longueur reduite a derive fermee d'electrons
WO1996006518A1 (fr) * 1994-08-25 1996-02-29 Aeorospatiale Societe Nationale Industrielle Accelerateur plasmatique a flux electronique ferme
US5798602A (en) * 1994-08-25 1998-08-25 Societe Nationale Industrielle Et Aerospatial Plasma accelerator with closed electron drift
EP0743669A1 (fr) * 1995-05-16 1996-11-20 VTD Vakuumtechnik Dresden GmbH Source d'ions
EP0800197A1 (fr) * 1996-04-01 1997-10-08 Matra Marconi Space France S.A. Accélérateur de plasma à effet Hall
EP0800196A1 (fr) 1996-04-01 1997-10-08 Matra Marconi Space France S.A. Accélérateur de plasma à effet Hall
DE19828704A1 (de) * 1998-06-26 1999-12-30 Thomson Tubes Electroniques Gm Plasmabeschleuniger-Anordnung
US6075321A (en) * 1998-06-30 2000-06-13 Busek, Co., Inc. Hall field plasma accelerator with an inner and outer anode
US6281622B1 (en) 1998-08-25 2001-08-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation - S.N.E.C.M.A Closed electron drift plasma thruster adapted to high thermal loads
EP0982976A1 (fr) * 1998-08-25 2000-03-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Propulseur à plasma à dérive fermée d'électrons adapté à de fortes charges thermiques
FR2782884A1 (fr) * 1998-08-25 2000-03-03 Snecma Propulseur a plasma a derive fermee d'electrons adapte a de fortes charges thermiques
US6150764A (en) * 1998-12-17 2000-11-21 Busek Co., Inc. Tandem hall field plasma accelerator
FR2788084A1 (fr) * 1998-12-30 2000-07-07 Snecma Propulseur a plasma a derive fermee d'electrons a vecteur poussee orientable
US6279314B1 (en) 1998-12-30 2001-08-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation-S.N.E.C.M.A. Closed electron drift plasma thruster with a steerable thrust vector
EP1101938A1 (fr) * 1998-12-30 2001-05-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Propulseur à plasma à dérivé fermée d'électrons à vecteur poussée orientable
WO2000070928A2 (fr) * 1999-05-18 2000-11-30 Gosudarstvennoe Unitarnoe Predpriyatie 'vserossysky Elektrotekhnichesky Institut Imeni V.I. Lenina' Procede de formation et d'acceleration de plasma et accelerateur de plasma utilisant le courant d'electrons en circuit ferme
WO2000070928A3 (fr) * 1999-05-18 2001-03-15 G Unitarnoe Predpr Vserossysky Procede de formation et d'acceleration de plasma et accelerateur de plasma utilisant le courant d'electrons en circuit ferme
WO2001071185A2 (fr) * 2000-03-22 2001-09-27 Thales Electron Devices Gmbh Dispositif accelerateur de plasma
DE10014033A1 (de) * 2000-03-22 2001-10-04 Thomson Tubes Electroniques Gm Plasma-Beschleuniger-Anordnung
DE10014033C2 (de) * 2000-03-22 2002-01-24 Thomson Tubes Electroniques Gm Plasma-Beschleuniger-Anordnung
WO2001071185A3 (fr) * 2000-03-22 2002-08-15 Thomson Tubes Electroniques Gm Dispositif accelerateur de plasma
US6803705B2 (en) 2000-03-22 2004-10-12 Thales Electron Devices Gmbh Plasma accelerator arrangement
US6864486B2 (en) 2001-05-16 2005-03-08 Veeco Instruments, Inc. Ion sources
DE10130464A1 (de) * 2001-06-23 2003-01-02 Thales Electron Devices Gmbh Plasmabeschleuniger-Anordnung
US7084572B2 (en) 2001-06-23 2006-08-01 Thales Electron Devices Gmbh Plasma-accelerator configuration
DE10130464B4 (de) * 2001-06-23 2010-09-16 Thales Electron Devices Gmbh Plasmabeschleuniger-Anordnung
RU2509918C2 (ru) * 2009-01-27 2014-03-20 Снекма Двигатель с замкнутым дрейфом электронов
CN108799032A (zh) * 2018-05-03 2018-11-13 兰州空间技术物理研究所 基于多孔金属材料的阳极组件及其制作方法
CN111120232A (zh) * 2018-11-01 2020-05-08 哈尔滨工业大学 一种可实现微调控放电性能的会切场等离子体推力器
CN111120232B (zh) * 2018-11-01 2021-08-03 哈尔滨工业大学 一种可实现微调控放电性能的会切场等离子体推力器
CN111156140A (zh) * 2018-11-07 2020-05-15 哈尔滨工业大学 可提高推力分辨率和工质利用率的会切场等离子体推力器
CN111156140B (zh) * 2018-11-07 2021-06-15 哈尔滨工业大学 可提高推力分辨率和工质利用率的会切场等离子体推力器
WO2023038611A1 (fr) * 2021-09-13 2023-03-16 Частное Акционерное Общество "Фэд" Moteur ionique-plasmique stationnaire

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Publication number Publication date
DE69207720D1 (de) 1996-02-29
EP0541309B1 (fr) 1996-01-17
DE69207720T2 (de) 1996-05-30

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