EP0978651A1 - Propulseur ionique - Google Patents

Propulseur ionique Download PDF

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Publication number
EP0978651A1
EP0978651A1 EP99110818A EP99110818A EP0978651A1 EP 0978651 A1 EP0978651 A1 EP 0978651A1 EP 99110818 A EP99110818 A EP 99110818A EP 99110818 A EP99110818 A EP 99110818A EP 0978651 A1 EP0978651 A1 EP 0978651A1
Authority
EP
European Patent Office
Prior art keywords
cathode
anode
gas
engine
additional electrode
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.)
Granted
Application number
EP99110818A
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German (de)
English (en)
Other versions
EP0978651B1 (fr
Inventor
Stephan Dr. Walther
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
EADS Space Transportation GmbH
Original Assignee
DaimlerChrysler Aerospace AG
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
Application filed by DaimlerChrysler Aerospace AG filed Critical DaimlerChrysler Aerospace AG
Publication of EP0978651A1 publication Critical patent/EP0978651A1/fr
Application granted granted Critical
Publication of EP0978651B1 publication Critical patent/EP0978651B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F03H1/0006—Details applicable to different types of plasma thrusters
    • F03H1/0025—Neutralisers, i.e. means for keeping electrical neutrality

Definitions

  • the invention relates to an ion engine, in particular for satellites and spacecraft, with one Ionization device for a fuel gas, at least an accelerator for the fuel ions as well as one with a gas flow through hollow cathode and an anode equipped electron source, the beam for neutralization in the fuel ion beam can be coupled.
  • the cathode In such an arrangement, the gas discharge between To start the anode and the cathode, the cathode must be heated up comparatively strongly so that the emerging Electrons due to the applied anode voltage are able to ionize the gas flowing through and thus initiate the discharge process.
  • a cathode which usually consists of a Material with high electron emission capability, for example, impregnated tungsten Temperature of about 1200 ° Celsius can be brought. This but not only requires a substantial one Energy consumption, but the high cathode temperature leads at the same time also to a heavy material load and premature material fatigue.
  • this known device requires high Gas flow rates to cause ignition.
  • a generic electrostatic engine as Ion engine for satellites and spacecraft is off US 4,838,021 and US 5,146,742 A.
  • an ionization device for a fuel gas provided, it being known that an acceleration device is arranged for the fuel ions as well one with a gas-flow hollow cathode and one Anode equipped electron source, the beam for Neutralization can be coupled into the fuel jet.
  • US 5,369,953 shows an ion engine for Satellites and spacecraft according to the aforementioned State of the art, in front of the cathode Electron source a starter electrode is arranged a discharge is ignited between and the cathode becomes. There is also one in front of the cathode Neutralizer arranged a starter electrode.
  • the object of the invention is an engine of the beginning mentioned type so that it is as possible low material stress and therefore high reliability has and that allows an interpretation that is as close as possible to the stationary operating state, after ignition, is oriented.
  • the invention solves this problem by providing one such engine provides that in the area of the cathode an additional electrode is arranged between the and the cathode a pulse discharge to ignite the gas discharge can be initiated between anode and cathode.
  • the additional electrode consists of a cylindrical pin in the longitudinal axis of the hollow cathode is arranged.
  • the advantages of the invention Engine consist mainly in that for the ignition required cathode temperature because of the much lower required electron current significantly below that of conventional engines of this kind can lie. This in turn results in the lower heating temperature also lower heating energy, which has to be used for the ignition. At the same time, the one required for this process can also be used Gas throughput through the hollow cathode significantly reduced become.
  • a reservoir 1 via a frit 2 an entrained Gas, in the case of the embodiment described here XENON, in a trained as an ionizer Chamber.
  • This chamber 3 is from one Permanent magnets 4 and one with an oscillating circuit 5 coupled coil-shaped induction cathode 6 surrounded. Inside the chamber 3 there is also an extraction anode 7 arranged.
  • the end of the chamber 3 facing away from the gas inlet is with Provide outlet openings in front of which an extraction cathode 8 and, at a distance from this, a braking or Shielding electrode 9 are arranged. Furthermore, in this Area a neutralizer 10 in the form of an electron source arranged, its structure with reference to FIG. 2 is explained.
  • the ion engine is wired in the usual way, i.e., a positive one at the extraction anode 7 Voltage of, for example, 4.5 kV is present while on the extraction electrode 8 an acceleration voltage of -2 kV is applied, the brake electrode 9 is on Zero potential. Because of this circuit arrangement and the induction device 4, 5, 6 surrounding the chamber 3 is that entering the chamber 3 from the reservoir Gas ionizes, the electrons from the Extraction anode 7 are sucked off and the positively charged Gas ions under the action of between the Extraction anode 7 and cathode 8 existing acceleration field the chamber 3 with high energy through the outlet openings leave where by means of the Electron source 10 neutralized electron beam supplied become.
  • this electron source 10 is inside as Housing 11 trained anode, also referred to as a keeper, a cathode tube 12 is arranged, the 11 exit area located from the actual Cathode 13 is limited and surrounded by a heating coil 14 is.
  • a pin-shaped additional electrode 15 attached to a bracket 16 via an insulation insert 17 electrically isolated in the cathode tube 12 is.
  • the inlet opening of the cathode tube 12 is finally, indicated by a massive arrow in the figure, of a gas, in the case of the one described here Embodiment XENON, that the Flows through cathode tube 12 and through a central Bore the cathode 13 into the chamber Anode housing 11 occurs.
  • Anode 11, cathode 12 and additional electrode 15 are, as indicated in the figure, connected to one another by an electrical circuit 18 in which the operating voltage is between the anode 11 and the cathode tube 12, and thus also at the cathode 13 which is electrically conductively connected to the latter U ke is present.
  • a pulse discharge Us / Is is triggered briefly between the additional electrode 15, which then acts as a kind of auxiliary anode, and the cathode tube 12.
  • the gas discharge is ignited between the anode 11 and the cathode 13.

Landscapes

  • 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)
  • Plasma Technology (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
EP99110818A 1998-08-06 1999-06-05 Propulseur ionique Expired - Lifetime EP0978651B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19835512 1998-08-06
DE19835512A DE19835512C1 (de) 1998-08-06 1998-08-06 Ionentriebwerk

Publications (2)

Publication Number Publication Date
EP0978651A1 true EP0978651A1 (fr) 2000-02-09
EP0978651B1 EP0978651B1 (fr) 2006-09-27

Family

ID=7876636

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99110818A Expired - Lifetime EP0978651B1 (fr) 1998-08-06 1999-06-05 Propulseur ionique

Country Status (6)

Country Link
US (1) US6195980B1 (fr)
EP (1) EP0978651B1 (fr)
JP (1) JP2000054951A (fr)
CN (1) CN1121553C (fr)
DE (2) DE19835512C1 (fr)
RU (1) RU2243408C2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003105543A2 (fr) * 2002-06-05 2003-12-18 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Procede et dispositif pour reduire la tension d'allumage de plasmas

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6449941B1 (en) * 1999-04-28 2002-09-17 Lockheed Martin Corporation Hall effect electric propulsion system
US7838850B2 (en) * 1999-12-13 2010-11-23 Semequip, Inc. External cathode ion source
DE10130464B4 (de) * 2001-06-23 2010-09-16 Thales Electron Devices Gmbh Plasmabeschleuniger-Anordnung
FR2838102B1 (fr) 2002-04-08 2004-11-26 Agence Spatiale Europeenne Systeme de propulsion combine destine a un engin spatial
US7464777B2 (en) * 2003-05-21 2008-12-16 Gonzalez Encarnacion H Power system for electrically powered land vehicle
US7791260B2 (en) * 2006-07-26 2010-09-07 The Regents Of The University Of Michigan Gas-fed hollow cathode keeper and method of operating same
US7870720B2 (en) * 2006-11-29 2011-01-18 Lockheed Martin Corporation Inlet electromagnetic flow control
DE102008022181B4 (de) 2008-05-05 2019-05-02 Arianegroup Gmbh Ionentriebwerk
DE102008058212B4 (de) * 2008-11-19 2011-07-07 Astrium GmbH, 81667 Ionenantrieb für ein Raumfahrzeug
RU2503848C2 (ru) * 2011-06-16 2014-01-10 Федеральное государственное унитарное предприятие "Научно-исследовательский институт машиностроения" (ФГУП "НИИМаш") Импульсный электрический реактивный двигатель
FR2985292B1 (fr) * 2011-12-29 2014-01-24 Onera (Off Nat Aerospatiale) Propulseur plasmique et procede de generation d'une poussee propulsive plasmique
DE102012016225A1 (de) 2012-08-14 2014-03-13 Jürgen Blum Elektro-Feldenergie auf der Basis von zweidimensionalen Elektronensystemen, mit der Energiemasse in dem koaxialen Leitungs- und Spulensystem des koaxialen Generators und Transformators
US9181934B2 (en) * 2012-11-21 2015-11-10 The Boeing Company Rotary switch assembly for ion propulsion system
CN104269336B (zh) * 2014-09-04 2016-08-31 兰州空间技术物理研究所 一种离子推力器放电室磁极结构及其设计方法
RU2644798C1 (ru) * 2016-03-18 2018-02-14 Владимир Дмитриевич Шкилев Импульсный детонационный ракетный двигатель
RU2720602C2 (ru) * 2017-08-07 2020-05-12 Акционерное общество "НАУЧНО-ИССЛЕДОВАТЕЛЬСКИЙ ИНСТИТУТ МАШИНОСТРОЕНИЯ" (АО "НИИМаш") Импульсный плазменный электрический реактивный двигатель
CN107633986B (zh) * 2017-08-25 2023-09-05 金华职业技术学院 一种产生电子束的方法
RU2702773C1 (ru) * 2018-04-16 2019-10-11 Владимир Дмитриевич Шкилев Пинчевый светоэрозионный ракетный двигатель
RU2709231C1 (ru) * 2018-12-01 2019-12-17 федеральное государственное автономное образовательное учреждение высшего образования "Санкт-Петербургский политехнический университет Петра Великого" (ФГАОУ ВО "СПбПУ") Мембранный ионно-плазменный ракетный двигатель космического аппарата
RU2721923C1 (ru) * 2019-06-14 2020-05-25 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Способ запуска маршевого двигателя управляемой ракеты и устройство для его осуществления
CN113266542B (zh) * 2021-06-29 2022-05-17 哈尔滨工业大学 一种霍尔推力器磁路散热结构
CN114658624B (zh) * 2022-03-24 2022-09-09 哈尔滨工业大学 一种适合大功率高比冲的霍尔推力器磁路结构及设计方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838021A (en) * 1987-12-11 1989-06-13 Hughes Aircraft Company Electrostatic ion thruster with improved thrust modulation
EP0463815A1 (fr) * 1990-06-22 1992-01-02 Kabushiki Kaisha Toshiba Source lumineuse d'ultraviolet sous vide
US5146742A (en) * 1989-10-31 1992-09-15 Nec Corporation Ion thruster for interplanetary space mission
US5465023A (en) * 1993-07-01 1995-11-07 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Carbon-carbon grid for ion engines

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FR2145012A5 (fr) * 1971-07-06 1973-02-16 Thomson Csf
US4264813A (en) * 1979-06-29 1981-04-28 International Business Machines Corportion High intensity ion source using ionic conductors
US4783595A (en) * 1985-03-28 1988-11-08 The Trustees Of The Stevens Institute Of Technology Solid-state source of ions and atoms
US4719355A (en) * 1986-04-10 1988-01-12 Texas Instruments Incorporated Ion source for an ion implanter
US5211006A (en) * 1991-11-12 1993-05-18 Sohnly Michael J Magnetohydrodynamic propulsion system
US5369953A (en) * 1993-05-21 1994-12-06 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Three-grid accelerator system for an ion propulsion engine
CN1235569A (zh) * 1996-11-01 1999-11-17 乔治·H·米利 利用惯性静电约束放电等离子体的等离子体喷射源
US5947421A (en) * 1997-07-09 1999-09-07 Beattie; John R. Electrostatic propulsion systems and methods

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838021A (en) * 1987-12-11 1989-06-13 Hughes Aircraft Company Electrostatic ion thruster with improved thrust modulation
US5146742A (en) * 1989-10-31 1992-09-15 Nec Corporation Ion thruster for interplanetary space mission
EP0463815A1 (fr) * 1990-06-22 1992-01-02 Kabushiki Kaisha Toshiba Source lumineuse d'ultraviolet sous vide
US5465023A (en) * 1993-07-01 1995-11-07 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Carbon-carbon grid for ion engines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003105543A2 (fr) * 2002-06-05 2003-12-18 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Procede et dispositif pour reduire la tension d'allumage de plasmas
WO2003105543A3 (fr) * 2002-06-05 2004-04-01 Fraunhofer Ges Forschung Procede et dispositif pour reduire la tension d'allumage de plasmas

Also Published As

Publication number Publication date
CN1121553C (zh) 2003-09-17
JP2000054951A (ja) 2000-02-22
EP0978651B1 (fr) 2006-09-27
DE19835512C1 (de) 1999-12-16
US6195980B1 (en) 2001-03-06
DE59913875D1 (de) 2006-11-09
CN1245868A (zh) 2000-03-01
RU2243408C2 (ru) 2004-12-27

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