EP1520104B1 - Halleffecktplasmaantrieb - Google Patents

Halleffecktplasmaantrieb Download PDF

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Publication number
EP1520104B1
EP1520104B1 EP03763933A EP03763933A EP1520104B1 EP 1520104 B1 EP1520104 B1 EP 1520104B1 EP 03763933 A EP03763933 A EP 03763933A EP 03763933 A EP03763933 A EP 03763933A EP 1520104 B1 EP1520104 B1 EP 1520104B1
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EP
European Patent Office
Prior art keywords
permanent magnet
arms
plasma thruster
magnetic circuit
magnetic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP03763933A
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English (en)
French (fr)
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EP1520104A2 (de
Inventor
Vladimir Cagan
Patrice Renaudin
Marcel Guyot
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Centre National dEtudes Spatiales CNES
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Centre National dEtudes Spatiales CNES
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Classifications

    • 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

Definitions

  • the invention lies in the field of plasma thrusters, in particular Hall effect.
  • Such engines may for example be used in space for example to maintain a satellite in geostationary orbit, or to transfer a satellite between two orbits, or to compensate for drag forces on satellites in low orbit, or again for missions requiring low thrust over very long times such as during an interplanetary mission.
  • thrusters are known and have already been described, for example in the patent US-A-6,281,622 , or in the patent US5,359,258 .
  • the figure 1 represents an axial section of an example of such a propellant
  • the figure 2 is a perspective view from the rear of said propeller example.
  • the thruster has substantially a form of revolution about an axis OO '.
  • the cutting plan of the figure 1 includes this axis OO '.
  • a forward or reverse downstream direction in the axial direction is indicated by arrows E substantially representing the direction of an electric field created by the combination of an annular anode 1 placed at the rear of an annular channel 3 and a cathode 2 placed substantially in front of the annular channel 3, outside thereof and adjacent thereto.
  • the arrangement of the cathode 2 thus allows to create with the anode 1 an electric field oriented substantially in the axial direction OO ', while being outside the jet propulsion.
  • this cathode is in general, as shown figure 2 , doubled by a second redundant cathode.
  • the annular anode 1 has an annular bottom placed concentrically with the annular channel 3. This bottom has passages, for example in the form of through holes for the passage of a gas that can be ionized, for example xenon.
  • the thruster comprises a magnetic circuit 40 of ferro-magnetic material consisting of a plate 4 perpendicular to the axis OO 'of the thruster, a central arm 41 having axis axis OO', two circular cylindrical poles 63 and 64 having as their axis OO axis and outer peripheral arms 42, arranged in a symmetry of revolution about the axis OO ', outside the annular channel 3.
  • the peripheral arms 42 can be 2, 3, 4 or moreover, or be constituted by a single annular arm.
  • the central arm 41 is finished at its Upstream end by a central magnetic pole 49, and each of the outer peripheral arms 42, is terminated at its upstream end by a magnetic pole 48
  • the magnetic poles 48 are constituted by plates substantially perpendicular to the axial direction OO '. They can, as described in column 5 lines 51-62 of the patent US 6,281,622 already cited, be inclined for example between - 15 and +15 degrees with respect to a plane perpendicular to the axis OO '.
  • a central coil 51 centered on the central arm 41, and peripheral coils 52 wound around the outer magnetic arms 42 can create magnetic field lines joining the central pole 49 to the peripheral poles 48 and the pole 63 to the pole 64.
  • the field magnetic in the annular channel is thus substantially perpendicular to the axis OO '.
  • This direction of the magnetic field in the annular channel 3 is materialized, figure 1 By means of arrows M.
  • the magnetic field lines are not all parallel to each other.
  • the annular channel 3 is physically delimited by inner and outer annular walls 61, 62 respectively, both centered on the axis OO '. These walls are made of a refractory material as resistant as possible to ablation.
  • Electrons emitted by the cathode 2 go towards the anode 1 from upstream to downstream of the annular channel 3. Part of these electrons are trapped in the annular channel 3 by the inter-polar magnetic field. Shocks between electrons and gas molecules contribute to ionize the gas introduced into the channel 3 through the anode 1. The mixture of ions and electrons then constitutes a self-maintained ionized plasma. The ions are ejected downstream under the effect of the electric field, thus creating a thrust of the engine directed upstream. The jet is electrically neutralized by electrons from the cathode 2.
  • the ejection speed of the ions is of the order of 5 times higher than the ejection speed that can be obtained with chemical thrusters. It follows that with a much smaller ejected mass, improved thrust efficiency can be achieved.
  • the supply of the reels for creating the magnetic field requires a power supply generally consisting of solar panels.
  • the invention aims at a plasma thruster having, for the same thrust, a reduced consumption of electric current and therefore a decreased mass of electrical generators, a reduced mass and bulk. magnetic circuit, increased reliability and finally a reduced production cost.
  • the magnetic field creation coils have a reduced number of coils wound in special high temperature wire.
  • This reduced number of wound turns has the following advantages. Losses by Joule effect are reduced, which As a result of the reduction of the booster heating, the reliability of the thruster is increased because the special high temperature wire is fragile.
  • the total mass of the magnetic field producing elements is reduced, because of the reduction in the number of turns and the correlative bulk of the magnetic circuit.
  • the cost of production is reduced because the high temperature special wire is expensive, and because the coils whose role is then limited to a simple adjustment of the value of the magnetic field are simplified.
  • the thruster is also lightened by reducing the mass of power supplies made possible by the decrease in power consumption.
  • the invention relates to a Hall effect plasma thruster having the features of claim 1.
  • part of the arms of the magnetic circuit comprises a permanent magnet and another part of the arms of the magnetic circuit does not include permanent magnets.
  • all the arms of the magnetic circuit comprise a permanent magnet.
  • the magnetic circuit comprises an inductive coil it is wrapped around an arm having no permanent magnet.
  • No inductor coil is housed around the arms of the magnetic circuit having a permanent magnet.
  • circuits differ from the prior art in that one or more arms of the circuit comprise permanent magnets, for example rare earth elements.
  • This feature makes it possible to reduce the number of turns of the induction coils, possibly to suppress these coils or a part of these coils.
  • the reduction in the size of the coils that results from this modification makes it possible to reduce the transverse dimension of the magnetic circuit since the thickness of the coils to be housed can be reduced. It also reduces the axial dimension which is often determined by the number of turns to be housed around the central arm. It thus becomes possible to limit the axial length of the thruster to the minimum length of the ionization chamber.
  • an upstream plate 4 made of a soft magnetic material, placed perpendicularly to an axis OO 'of the circuit 40.
  • This plate is completed by a central arm 41 of cylindrical shape having as its axis the axis OO', by circular cylindrical poles 63 and 64 having axis axis OO ', arranged on either side of an annular channel 3 and by peripheral arms 42, 42' disposed in a symmetry of revolution about the axis OO 'outside the ring channel 3.
  • peripheral arms 42 there are four peripheral arms 42.
  • the number of arms can be different. He may in particular be greater than 4, as shown figure 5 A and B where this number is 8, due to the decrease in size resulting from the suppression or reduction of the size of the induction coils.
  • Each of the arms 41, 42 is terminated in its upstream part by a magnetic pole referenced 49 for the pole of the central arm 41 and 48 for each of the poles of the peripheral arms 42.
  • Each pole 49, 48 terminating an arm 41, 42 respectively, is arranged perpendicularly to the axis of said arm. The angle of inclination of the poles may be different as described in connection with the description of the prior art.
  • At least one of the arms comprises a permanent magnet constituting part of the axial length of the arm.
  • the arms comprising a permanent magnet carry the reference 41 'when it comes to the central arm and 42' when it is a peripheral arm.
  • the permanent magnet is referenced 54 when it is incorporated in a peripheral arm 42 'and 55 when incorporated in the central arm 41'.
  • all the peripheral arms 42 'thus consist of the downstream upstream of a downstream portion 43 of soft magnetic material in contact with the downstream plate 4, a rare earth magnet 54, an upstream portion 45 in soft magnetic material, this upstream portion 45 carrying the magnetic pole 48. It can be seen that a central portion of the arm adjacent to the downstream portion 43 and to the upstream portion 45 is constituted by said permanent magnet 54.
  • the central arm 41 is entirely of soft magnetic material.
  • a central coil 51 made as in the prior art by a special high temperature wire, comprising a metal sheath around a central conductor, allows adjustment of the inter-polar magnetic field. In this configuration no peripheral induction coil is arranged around the peripheral arms 42 '.
  • the peripheral arms 42 'each comprise a permanent magnet 54, and the central arm 41 is made solely of magnetic material, an inductor coil 51 being housed around said central arm 41.
  • peripheral arms 42 are made entirely of soft magnetic material.
  • An induction coil 52 is arranged around each of the arms 42.
  • the central arm 41 ' has a downstream portion 44 of soft magnetic material, a permanent magnet rare earth 55, and an upstream portion 46 of soft magnetic material, this upstream portion 46 carrying the magnetic pole 49.
  • the central arm 41 comprises a permanent magnet 55
  • the peripheral arms 42 are made only of material magnetic and an inductor coil 52 is housed around each of said peripheral arms 42.
  • Each of the arms 41 'or 42' comprising a permanent magnet 55, 54, respectively, comprises a peripheral jacket 47, external to said arm, of non-magnetic metal.
  • This sleeve 47 can mechanically hold together, for example by clamping, the downstream portions 43, 44, upstream 45, 46 and the magnet 54, 55 together forming an arm 42 '41' respectively.
  • the magnet 54, 55 is held in contact with the downstream portions 43, 44 and upstream 45, 46 respectively.
  • peripheral arms 42 ' which comprise, as in the embodiment described in connection with the Figures 3 A and B permanent magnets 54.
  • the central arm 41 ' has a downstream portion 44 of soft magnetic material, a permanent magnet rare earth 55, and an upstream portion 46 of soft magnetic material, this upstream portion 46 carrying the magnetic pole 49 A liner 47 provides mechanical cohesion of the parts together forming an arm 42 'or 41' and ensures that the magnetic core portions 43, 45 and the permanent magnet 54 are held coaxial.
  • the central arm 41 ' comprises a permanent magnet 55, and all the peripheral arms 42' comprise a permanent magnet 54.
  • the power of the magnets is adjusted so that the magnetic field has its optimum value in the expected range of operating temperature of the thruster.
  • the power of the magnets is further adjusted so that the number of turns is minimal.

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  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma Technology (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
  • Medicinal Preparation (AREA)
  • Cosmetics (AREA)
  • Medicines Containing Material From Animals Or Micro-Organisms (AREA)
  • Magnetic Resonance Imaging Apparatus (AREA)

Claims (9)

  1. Plasmaantrieb mit Hall-Effekt, der eine Längsachse (00') aufweist, die im wesentlichen parallel zu einer einen stromaufwärtigen Abschnitt und einen stromabwärtigen Abschnitt festlegenden Antriebsrichtung ist, und der umfasst:
    - einen ringförmigen Haupt-Ionisierungs- und Beschleunigungskanal (3), der aus einem feuerfesten Material hergestellt ist und von zwei zylindrischen kreisförmigen Magnetpolen (63,64) umgeben ist, wobei der ringförmige Kanal (3) an seinem stromaufwärtigen Ende offen ist,
    - eine ringförmige Gasverteilungsanode (1), welche Gas aus Verteilungsleitungen aufnimmt und mit Durchgängen versehen ist, um dieses Gas in den ringförmigen Kanal (3) eintreten zu lassen, wobei die ringförmige Anode (1) im Inneren des Kanals (3) in einem stromaufwärtigen Abschnitt dieses Kanals (3) angeordnet ist,
    - mindestens eine hohle Kathode (2), die außerhalb des ringförmigen Kanals (3) an diesen angrenzend angeordnet ist,
    - einen Magnetkreis (40), der stromaufwärtige Polenden (49,48) zum Erzeugen eines radialen Magnetfeldes in einem stromaufwärtigen Abschnitt des ringförmigen Kanals (3) zwischen diesen Polabschnitten (49,48) umfasst, wobei dieser Kreis (40) aus einer stromabwärtigen Platte (4) gebildet ist, von der stromaufwärts parallel zur Achse (00') ein in der Mitte des ringförmigen Kanals (3) befindlicher zentraler Arm (41), zwei kreisförmige zylindrische Pole (63,64) auf beiden Seiten des ringförmigen Kanals (3) sowie außerhalb des ringförmigen Kanals (3) und angrenzend an diesen gelegene periphere Arme (42) ausgehen, wobei mindestens einer der Arme (42',41') des Magnetkreises (40) einen Permanentmagneten (54,55) aufweist,
    dadurch gekennzeichnet, dass jeder Arm (41',42') des einen Permanentmagneten (55,54) aufweisenden Magnetkreises (40) von einem stromabwärtigen Abschnitt (43,44) in Kontakt mit der stromabwärtigen Platte (4), einem stromaufwärtigen Abschnitt (45,46), der einen Magnetpol (49,48) trägt, und einem zentralen Abschnitt angrenzend an den stromabwärtigen Abschnitt (43,44) und an den von dem Permanentmagneten (55,54) gebildeten stromaufwärtigen Abschnitt (45,46) gebildet ist.
  2. Plasmaantrieb nach Anspruch 1, dadurch gekennzeichnet, dass ein Abschnitt der Arme (41',42') des Magnetkreises (40) einen Permanentmagneten (55,54) aufweist, und dass ein anderer Abschnitt der Arme (41,42) des Magnetkreises (40) keine Permanentmagnete aufweist.
  3. Plasmaantrieb nach Antrieb 1, dadurch gekennzeichnet, dass ein Mantel (47) an jedem Arm (41',42') des einen Permanentmagneten (55,54) aufweisenden Magnetkreises (40) vorhanden ist.
  4. Plasmaantrieb nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass eine Induktionsspule (51,52) um Arme (42,41), die keine Permanentmagnete aufweisen, herumgewickelt ist.
  5. Plasmaantrieb nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass um die Arme (41',42') des Magnetkreises (40), der einen Permanentmagneten (55,54) aufweist, keine Induktionsspule angeordnet ist.
  6. Plasmaantrieb nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die peripheren Arme (42,42') gemäß einer Umdrehungssymmetrie um die Achse (00') angeordnet sind.
  7. Plasmaantrieb nach Anspruch 1, dadurch gekennzeichnet, dass die peripheren Arme (42') jeweils einen Permanentmagneten (54) aufweisen, dass der zentrale Arm (41) ausschließlich aus magnetischem Material hergestellt ist, und dass eine Induktionsspule (51) um den zentralen Arm (41) herum angeordnet ist.
  8. Plasmaantrieb nach Anspruch 1, dadurch gekennzeichnet, dass der zentrale Arm (41') einen Permanentmagneten (55) aufweist, dass die peripheren Arme (42) ausschließlich aus magnetischem Material hergestellt sind, und dass eine Induktionsspule (52) um jeden der peripheren Arme (42) herum angeordnet ist.
  9. Plasmaantrieb nach Anspruch 1, dadurch gekennzeichnet, dass der zentrale Arm (41') einen Permanentmagneten (55) aufweist, und dass alle peripheren Arme (42') einen Permanentmagneten (54) aufweisen.
EP03763933A 2002-07-09 2003-07-07 Halleffecktplasmaantrieb Expired - Lifetime EP1520104B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0208612 2002-07-09
FR0208612A FR2842261A1 (fr) 2002-07-09 2002-07-09 Propulseur plasmique a effet hall
PCT/FR2003/002100 WO2004007957A2 (fr) 2002-07-09 2003-07-07 Propulseur plasmique a effet hall

Publications (2)

Publication Number Publication Date
EP1520104A2 EP1520104A2 (de) 2005-04-06
EP1520104B1 true EP1520104B1 (de) 2008-05-07

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EP03763933A Expired - Lifetime EP1520104B1 (de) 2002-07-09 2003-07-07 Halleffecktplasmaantrieb

Country Status (9)

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US (1) US7543441B2 (de)
EP (1) EP1520104B1 (de)
AT (1) ATE394596T1 (de)
AU (1) AU2003263268A1 (de)
DE (1) DE60320795D1 (de)
ES (1) ES2306893T3 (de)
FR (1) FR2842261A1 (de)
RU (1) RU2319040C2 (de)
WO (1) WO2004007957A2 (de)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7624566B1 (en) * 2005-01-18 2009-12-01 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Magnetic circuit for hall effect plasma accelerator
FR2919755B1 (fr) 2007-08-02 2017-05-05 Centre Nat De La Rech Scient (C N R S ) Dispositif d'ejection d'electrons a effet hall
US20100146931A1 (en) * 2008-11-26 2010-06-17 Lyon Bradley King Method and apparatus for improving efficiency of a hall effect thruster
FR2945842B1 (fr) * 2009-05-20 2011-07-01 Snecma Propulseur a plasma a effet hall.
US20120180462A1 (en) * 2009-10-09 2012-07-19 Toyota Jidosha Kabushiki Kaisha Exhaust purification system of internal combustion engine
US8468794B1 (en) * 2010-01-15 2013-06-25 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Electric propulsion apparatus
CN104033346B (zh) * 2014-06-25 2016-08-24 哈尔滨工业大学 一种具有通道磁场引导结构的多级会切磁场等离子体推力器
CN105156290A (zh) * 2015-07-13 2015-12-16 兰州空间技术物理研究所 一种新型三环混合电推力器
CN105003408B (zh) * 2015-07-16 2018-05-08 兰州空间技术物理研究所 一种离子与霍尔混合型电推力器
FR3053784B1 (fr) * 2016-07-07 2020-01-17 Airbus Defence And Space Sas Procedes de determination et de regulation de la temperature d’un propulseur electrique
CN109779865B (zh) * 2019-03-14 2024-04-19 南华大学 永磁霍尔推力器点火装置
CN110594115B (zh) * 2019-10-17 2020-12-11 大连理工大学 一种无放电阴极的环型离子推力器
CN113202706A (zh) * 2021-04-25 2021-08-03 上海宇航系统工程研究所 一种用于geo轨道卫星的霍尔电推进系统

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0463408A3 (en) * 1990-06-22 1992-07-08 Hauzer Techno Coating Europe Bv Plasma accelerator with closed electron drift
US5359258A (en) * 1991-11-04 1994-10-25 Fakel Enterprise Plasma accelerator with closed electron drift
US5646476A (en) * 1994-12-30 1997-07-08 Electric Propulsion Laboratory, Inc. Channel ion source
US5763989A (en) * 1995-03-16 1998-06-09 Front Range Fakel, Inc. Closed drift ion source with improved magnetic field
RU2084085C1 (ru) * 1995-07-14 1997-07-10 Центральный научно-исследовательский институт машиностроения Ускоритель с замкнутым дрейфом электронов
RU2092983C1 (ru) * 1996-04-01 1997-10-10 Исследовательский центр им.М.В.Келдыша Плазменный ускоритель
FR2743191B1 (fr) * 1995-12-29 1998-03-27 Europ Propulsion Source d'ions a derive fermee d'electrons
FR2782884B1 (fr) * 1998-08-25 2000-11-24 Snecma Propulseur a plasma a derive fermee d'electrons adapte a de fortes charges thermiques

Also Published As

Publication number Publication date
ATE394596T1 (de) 2008-05-15
WO2004007957A3 (fr) 2004-05-13
FR2842261A1 (fr) 2004-01-16
WO2004007957A2 (fr) 2004-01-22
DE60320795D1 (de) 2008-06-19
ES2306893T3 (es) 2008-11-16
EP1520104A2 (de) 2005-04-06
RU2005103228A (ru) 2005-10-27
RU2319040C2 (ru) 2008-03-10
AU2003263268A1 (en) 2004-02-02
US7543441B2 (en) 2009-06-09
US20060010851A1 (en) 2006-01-19

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