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WO1997037127A1 - Accelerateur plasmique a effet de hall - Google Patents

Accelerateur plasmique a effet de hall Download PDF

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Publication number
WO1997037127A1
WO1997037127A1 PCT/US1997/005264 US9705264W WO9737127A1 WO 1997037127 A1 WO1997037127 A1 WO 1997037127A1 US 9705264 W US9705264 W US 9705264W WO 9737127 A1 WO9737127 A1 WO 9737127A1
Authority
WO
WIPO (PCT)
Prior art keywords
channel
accelerator
magnetic body
magnetic field
source
Prior art date
Application number
PCT/US1997/005264
Other languages
English (en)
Other versions
WO1997037127B1 (fr
Inventor
Y. M. Yashnov
V. A. Petrosov
V. I. Baranov
A. I. Vasin
L. Talaalout
Original Assignee
International Scientific Products
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from RU9696105557A external-priority patent/RU2092983C1/ru
Application filed by International Scientific Products filed Critical International Scientific Products
Priority to CA002250913A priority Critical patent/CA2250913C/fr
Priority to JP53552197A priority patent/JP3982565B2/ja
Priority to IL12641397A priority patent/IL126413A0/xx
Publication of WO1997037127A1 publication Critical patent/WO1997037127A1/fr
Publication of WO1997037127B1 publication Critical patent/WO1997037127B1/fr

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/411—Electric propulsion
    • B64G1/413—Ion or plasma engines

Definitions

  • This invention relates to a Hall effect plasma accelerator, sometimes known as a closed electron drift accelerator.
  • the invention arose when considering the design of such accelerators for use as thrusters on satellites or other spacecraft. However, it is also applicable to accelerators intended for other uses, for example plasma etching and machining workpieces in a vacuum.
  • a conventional Hall effect accelerator comprises an annular accelerating channel extending circumferentially around an axis of the accelerator and also extending in an axial direction from a closed end to an open end.
  • An anode is located, usually at the closed end of the channel, and a cathode is positioned outside the channel close to its open end.
  • Means is provided for introducing a propellant, for example xenon gas, into the channel and this is often done through passages formed in the anode itself or close to the anode.
  • a magnetic system applies a magnetic field in the radial direction across the channel and this causes electrons emitted from the cathode to move circumferentially around the channel.
  • Some but not all of the electrons emitted from the cathode pass into the channel and are attracted towards the anode.
  • the radial magnetic field deflects the electrons in a circumferential direction so that they move in a spiral trajectory, accumulating energy as they gradually drift towards the anode.
  • the electrons collide with atoms of the propellant, causing lonization.
  • the resulting positively charged ions are accelerated by the electric field towards the open end of the channel, from which they are expelled at great velocity, thereby producing the desired thrust.
  • the ions have a much greater mass than the electrons, they are not so readily influenced by the magnetic field and their direction of acceleration is therefore primarily axial rather than circumferential with respect to the they are neutralized by those electrons from the cathode that do not pass into the channel.
  • upstream and downstream will be used for convenience to describe directions with reference to the movement of ions in the channel.
  • Russian Patent Specification 2022167 describes arrangements of up to sixteen coils and magnetic screens.
  • this invention provides a Hall effect plasma accelerator comprising a substantially annular accelerating channel having closed and open ends and a source of magnetic field positioned behind the closed end of the channel and having an axis extending in the same direction as the axis of the channel.
  • this invention provides a Hall effect plasma accelerator comprising a substantially annular accelerating channel having closed and open ends and a source of magnetic field positioned behind the closed end of the channel and extending around the axis of the channel.
  • a Hall effect accelerator with an optimum distribution of magnetic field inside the acceleration channel by means of a simpler and less heavy arrangement using a single source of magnetic field, such as a single coil or permanent magnet.
  • the simpler design which results is considered particularly suitable for relatively small accelerators and allows the source of magnetic field to be positioned away from the accelerating channel thereby reducing the heating effect in the coil resulting from heat transferred from the channel.
  • the position of the source of magnetic field behind the accelerating channel can also provide improved cooling of the source of magnetic field in operation, thereby further reducing the chance of damage through excessive heat. In pais aligned with an outer wall of the accelerator offers considerable heat advantages.
  • the shape of the substantially annular accelerating channel is not limited to a circular cross-section but could have an elongated, polygonal or irregular form.
  • the source of magnetic field (which might be a permanent magnet or an electromagnet depending upon the requirements) has an axis extending in the same direction as the axis of the channel, that is to say at least a component of the axis of the source of magnetic field extends in the direction of the axis of the channel.
  • the axis of the source of magnetic field does not have to be parallel to the axis of the channel.
  • the accelerator preferably includes a first magnetic body, which defines magnetic poles radially inwardly and outwardly of the channel.
  • This first magnetic body may substantially or partially enclose or merely be in proximity to the source of magnetic field, depending on the specific application. For example, a more open structure without the coil being substantially enclosed may be preferred where the cooling of the coil is critical.
  • the first magnetic body preferably includes two main inner and outer walls which may be generally cylindrical in form or of another suitable form as appropriate to the shape of the accelerating channel being used and which extend from respective poles close to the open end of the channel, respectively inside and outside of the channel, to positions rjehind the closed end of the channel.
  • a linking part of the first magnetic body behind the closed end of the channel may enclose the space between those walls to a fuller or lesser extent depending on the requirements for the magnetic field and for the reduction of heat levels in the particular application.
  • This linking part preferably defines, possibly in co ⁇ operation with the inner and/or outer, main wall (or an extension thereof) an annular space, co-axial with the axis of the channel.
  • This annular space houses the source of magnetic field and in a preferred arrangement, its outer wall is defined by an upstream extension of the main outer wall so that the source of magnetic field is located as far as reasonably possible from the source of heat and so that the surface area available for radiation of heat is maximized.
  • the actual shape of the linking part will depend on the form of magnetic source used and may comprise a single or a number of straight or curved sections.
  • a preferred feature of the invention is the inclusion of a second magnetic body magnetically separate from and enclosed within the first magnetic body.
  • This second magnetic body is preferably in the shape of a circle of "U" shaped cross-section arranged so that its "U" shape encloses the closed end of the channel thereby acting as a screen to reduce the magnetic field in the region of the anode.
  • Figure 1 shows an axial cross-section through a first embodiment of the invention, showing only one half of the cross-section, on one side of the axis, the other half on the other side of the axis being a mirror image;
  • Figure 2 shows in cross-sectional form equivalent to that of Figure 1 , a second, preferred embodiment of the invention and illustrates lines of magnetic field;
  • Figure 3 shows the second embodiment in a perspective view cut in half though its axis and with its ceramic accelerating channel removed to reveal features of internal construction.
  • the accelerator is generally symmetrical about an axis X-X. It comprises an annular accelerating channel 1 defined by a ceramic insert la extending from a closed, upstream end (the lower end as shown in Figure 1) to an open, downstream end. At the upstream end of the channel there is located a substantially circular anode 2 and a collector 3 which delivers propellant gas, typically xenon, to the channel in the vicinity of the anode 2.
  • a cathode 4 is mounted outside the channel, close to the downstream end and is supplied with a negative potential by a power supply 5.
  • a first hollow annular magnetic body 6 encloses all but the open, downstream end of the accelerating channel 1 and comprises a main outer cylindrical wall 7 radially external with respect to the annular channel. This wall 7 is associated with a radially inwardly extending pole-piece 7a.
  • the magnetic body 6 also has a second main inner cylindrical wall 8 radially internal with respect to the channel and an associated radially outwardly extending pole-piece 8a.
  • a linking part 9 joins the two walls 7 and 8 together at one end of the magnetic body 6 behind the closed end of the accelerating channel 1.
  • a second hollow annular magnetic body 10 is of U-shaped cross-section. It encloses the closed end of the channel 1 and is itself totally enclosed within the first magnetic body 6.
  • a source of magnetic field 11 in the form of an electromagnet coil having its physical and magnetic axes coincident with the axis X-X, is situated behind (i.e. axially upstream of) the closed end of channel 1 and is enclosed by the first magnetic body 6. In an alternative construction the coil 11 could be replaced by an annular permanent magnet of equivalent magnetic effect.
  • the second magnetic body 10 is supported by supports 14 to the first magnetic body 6.
  • the supports 14 are made of non-magnetic material i.e. a material which does not influence the magnetic field or, expressed another way, having a relative permeability close to unity. This ensures that the supports do not distort the distribution of the magnetic field in the channel 1.
  • the pole-pieces 7a and 8a create an optimal magnetic field radially across a region close to the open end of the accelerating channel 1 whilst the second magnetic body 10 serves to reduce or eliminate any magnetic field in the region of the anode 2. Dissipation of heat from the channel is encouraged by slots 12 provided in first wall 7.
  • Figures 2 and 3 show a second, preferred embodiment of the invention including, in Figure 2, magnetic field lines 13. These lines 13 illustrate the radial nature of magnetic field created across the accelerating channel 1. In Figure 2 the lines of magnetic field 13 have been omitted where they pass inside the magnetic bodies 6 and 10 and would be too close together to show clearly. It will be noted that in the embodiment of Figures 2 and 3 the coil is further away from the accelerating channel than its counte ⁇ art in Figure 1. This reduces heating of the coil still further.
  • the outer wall 7 of the first magnetic body 6 has a part 7b extending behind the closed end of the channel 1.
  • This is linked to the inner wall 8 by linking part 9 comprising sections 9a, 9b and 9c.
  • Section 9a extends radially inward with respect to the axis of the annular channel 1 before meeting section 9b which extends axially downstream towards the closed end of the channel thus defining a cavity for the magnetic coil 11.
  • the link between the outer and inner walls 7 and 8 is completed by section 9c of the linking part which extends from 9b to the end of the inner wall 8 situated behind the closed end of the channel 1. Because section 9b is substantially longer than 9a and because section 9c increases the diameter of the coil, its surface area is large, this assisting heat dissipation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)

Abstract

Cette invention concerne un accélérateur plasmique à effet de Hall, lequel comprend un canal d'accélération annulaire (1) qui possède des extrémités ouverte et fermée. Une source de champ magnétique (11), se trouvant dans un corps magnétique annulaire et creux (6), est disposée derrière l'extrémité fermée du canal, et possède un axe orienté dans la même direction que celui dudit canal. Ce système permet d'obtenir un accélérateur à effet de Hall offrant une répartition optimale du champ magnétique à l'intérieur du canal d'accélération, ceci à l'aide d'un dispositif simple et léger utilisant une seule source de champ magnétique, tel qu'une bobine unique ou un aimant permanent. Ce système permet également de réduire l'échauffement de la source de champ magnétique.
PCT/US1997/005264 1996-04-01 1997-03-31 Accelerateur plasmique a effet de hall WO1997037127A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CA002250913A CA2250913C (fr) 1996-04-01 1997-03-31 Accelerateur plasmique a effet de hall
JP53552197A JP3982565B2 (ja) 1996-04-01 1997-03-31 ホール効果プラズマ加速器
IL12641397A IL126413A0 (en) 1996-04-01 1997-03-31 A hall effect plasma accelerator

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
RU96105557 1996-04-01
RU9696105557A RU2092983C1 (ru) 1996-04-01 1996-04-01 Плазменный ускоритель
US08/760,952 US5751113A (en) 1996-04-01 1996-12-09 Closed electron drift hall effect plasma accelerator with all magnetic sources located to the rear of the anode
US08/760,952 1996-12-09

Publications (2)

Publication Number Publication Date
WO1997037127A1 true WO1997037127A1 (fr) 1997-10-09
WO1997037127B1 WO1997037127B1 (fr) 1997-11-20

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1997/005264 WO1997037127A1 (fr) 1996-04-01 1997-03-31 Accelerateur plasmique a effet de hall

Country Status (5)

Country Link
JP (1) JP3982565B2 (fr)
CN (1) CN1218541A (fr)
CA (1) CA2250913C (fr)
IL (1) IL126413A0 (fr)
WO (1) WO1997037127A1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999063221A3 (fr) * 1998-06-05 2000-02-24 Primex Aerospace Company Mise en forme du flux magnetique dans des accelerateurs d'ions a courant d'electrons ferme
US6075321A (en) * 1998-06-30 2000-06-13 Busek, Co., Inc. Hall field plasma accelerator with an inner and outer anode
US6208080B1 (en) 1998-06-05 2001-03-27 Primex Aerospace Company Magnetic flux shaping in ion accelerators with closed electron drift
US6215124B1 (en) 1998-06-05 2001-04-10 Primex Aerospace Company Multistage ion accelerators with closed electron drift
DE10153723A1 (de) * 2001-10-31 2003-05-15 Thales Electron Devices Gmbh Plasmabeschleuniger-Anordnung
US6612105B1 (en) 1998-06-05 2003-09-02 Aerojet-General Corporation Uniform gas distribution in ion accelerators with closed electron drift
US6870164B1 (en) * 1999-10-15 2005-03-22 Kaufman & Robinson, Inc. Pulsed operation of hall-current ion sources
RU2377441C1 (ru) * 2008-05-21 2009-12-27 Федеральное государственное унитарное предприятие "Опытное конструкторское бюро "Факел" Плазменный двигатель с замкнутым дрейфом электронов
RU2458490C2 (ru) * 2008-02-28 2012-08-10 Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт машиностроения" (ФГУП ЦНИИмаш) Способ регулирования ионных электрических ракетных двигателей и устройство для его осуществления (варианты)
US8778151B2 (en) 2007-12-18 2014-07-15 Canon Anelva Corporation Plasma processing apparatus
US10539122B2 (en) 2014-05-23 2020-01-21 Mitsubishi Heavy Industries, Ltd. Plasma accelerating apparatus and plasma accelerating method

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE60307418T2 (de) * 2003-03-20 2007-03-29 Elwing LLC, Wilmington Antriebssystem für Raumfahrzeuge
JP2006147449A (ja) 2004-11-24 2006-06-08 Japan Aerospace Exploration Agency 高周波放電プラズマ生成型二段式ホール効果プラズマ加速器
JP4816179B2 (ja) * 2006-03-20 2011-11-16 三菱電機株式会社 ホールスラスタ
DE102007062150A1 (de) * 2007-09-14 2009-04-02 Thales Electron Devices Gmbh Vorrichtung zur Ableitung von Verlustwärme sowie Ionenbeschleunigeranordnung und Wanderfeldröhrenanordnung mit einer Wärmeleitanordnung
FR2950115B1 (fr) * 2009-09-17 2012-11-16 Snecma Propulseur plasmique a effet hall
FR2976029B1 (fr) * 2011-05-30 2016-03-11 Snecma Propulseur a effet hall
CN103953517B (zh) * 2014-05-13 2016-08-31 哈尔滨工业大学 霍尔推进器改进装置
CN104290926B (zh) * 2014-09-05 2016-05-11 兰州空间技术物理研究所 一种电推力器耐高温励磁线圈
FR3032325A1 (fr) * 2015-01-30 2016-08-05 Snecma Propulseur a effet hall et engin spatial comprenant un tel propulseur
CN105257491B (zh) * 2015-11-30 2017-11-03 哈尔滨工业大学 一种霍尔推力器阳极
JP6583684B2 (ja) * 2016-01-08 2019-10-02 三菱重工業株式会社 プラズマ加速装置およびプラズマ加速方法
CN109707583A (zh) * 2018-04-23 2019-05-03 李超 脉冲式冲量循环发动机
CN110735776B (zh) * 2019-10-11 2021-06-18 大连理工大学 一种自冷式微波增强电推力器

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4862032A (en) * 1986-10-20 1989-08-29 Kaufman Harold R End-Hall ion source
US5359258A (en) * 1991-11-04 1994-10-25 Fakel Enterprise Plasma accelerator with closed electron drift

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4862032A (en) * 1986-10-20 1989-08-29 Kaufman Harold R End-Hall ion source
US5359258A (en) * 1991-11-04 1994-10-25 Fakel Enterprise Plasma accelerator with closed electron drift

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999063221A3 (fr) * 1998-06-05 2000-02-24 Primex Aerospace Company Mise en forme du flux magnetique dans des accelerateurs d'ions a courant d'electrons ferme
US6208080B1 (en) 1998-06-05 2001-03-27 Primex Aerospace Company Magnetic flux shaping in ion accelerators with closed electron drift
US6215124B1 (en) 1998-06-05 2001-04-10 Primex Aerospace Company Multistage ion accelerators with closed electron drift
US6612105B1 (en) 1998-06-05 2003-09-02 Aerojet-General Corporation Uniform gas distribution in ion accelerators with closed electron drift
US6075321A (en) * 1998-06-30 2000-06-13 Busek, Co., Inc. Hall field plasma accelerator with an inner and outer anode
US6870164B1 (en) * 1999-10-15 2005-03-22 Kaufman & Robinson, Inc. Pulsed operation of hall-current ion sources
DE10153723A1 (de) * 2001-10-31 2003-05-15 Thales Electron Devices Gmbh Plasmabeschleuniger-Anordnung
US8778151B2 (en) 2007-12-18 2014-07-15 Canon Anelva Corporation Plasma processing apparatus
RU2458490C2 (ru) * 2008-02-28 2012-08-10 Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт машиностроения" (ФГУП ЦНИИмаш) Способ регулирования ионных электрических ракетных двигателей и устройство для его осуществления (варианты)
RU2377441C1 (ru) * 2008-05-21 2009-12-27 Федеральное государственное унитарное предприятие "Опытное конструкторское бюро "Факел" Плазменный двигатель с замкнутым дрейфом электронов
US10539122B2 (en) 2014-05-23 2020-01-21 Mitsubishi Heavy Industries, Ltd. Plasma accelerating apparatus and plasma accelerating method

Also Published As

Publication number Publication date
JP2002516644A (ja) 2002-06-04
CN1218541A (zh) 1999-06-02
IL126413A0 (en) 1999-05-09
JP3982565B2 (ja) 2007-09-26
CA2250913C (fr) 2005-06-28
CA2250913A1 (fr) 1997-10-09

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