ES2092314T3 - Motor de plasma de longitud reducida con deriva cerrada de electrones. - Google Patents

Motor de plasma de longitud reducida con deriva cerrada de electrones.

Info

Publication number
ES2092314T3
ES2092314T3 ES93913165T ES93913165T ES2092314T3 ES 2092314 T3 ES2092314 T3 ES 2092314T3 ES 93913165 T ES93913165 T ES 93913165T ES 93913165 T ES93913165 T ES 93913165T ES 2092314 T3 ES2092314 T3 ES 2092314T3
Authority
ES
Spain
Prior art keywords
anode
magnetic field
current
main channel
channel
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
ES93913165T
Other languages
English (en)
Inventor
Dominique Valentian
Alexei Morozov
Antonina Bougrova
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.)
Societe Europeenne de Propulsion SEP SA
Original Assignee
Societe Europeenne de Propulsion SEP SA
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 Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Application granted granted Critical
Publication of ES2092314T3 publication Critical patent/ES2092314T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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

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)
  • Electron Sources, Ion Sources (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Abstract

LOSMEDIOS (31 A 33, 34 A 38) DE CREACION DE UN CAMPO MAGNETICO EN EL CANAL PRINCIPAL (24) DEL MOTOR DE PLASMA SE ADAPTAN PARA PRODUCIR EN ESTE CANAL PRINCIPAL (24) UN CAMPO MAGNETICO ESENCIALMENTE RADIAL CON EL EXTREMO CORRIENTE ABAJO (225) DEL CANAL (24) Y CUYA INDUCCION ES MAXIMA A ESTE NIVEL, PRESENTANDO ESTE CAMPO MAGNETICO UNA INDUCCION MINIMA EN LA ZONA DE TRANSICION SITUADA CERCA DEL ANODO (25), AUMENTANDO EL VALOR ABSOLUTO DE LA INDUCCION DE ESTE CAMPO DE NUEVO CORRIENTE ARRIBA DEL ANODO (25), AL NIVEL DE LA CAMARA TAMPON (23) PARA REALIZAR UN EFECTO DE ESPEJO MAGNETICO, PRESENTANDO LAS LINEAS DE CAMPO ENTRE EL ANODO (25) Y EL EXTREMO CORRIENTE ABAJO (225) DEL CANAL (24) UNA CONCAVIDAD DIRIGIDA HACIA LA CORRIENTE ABAJO QUE PROVOCA UN ENFOQUE DE LOS IONES, CON UNA REGION DE DENSIDAD DE IONIZACION MAXIMA SITUADA CORRIENTE ABAJO DEL ANODO (25) Y EN QUE LOS MEDIOS DE CREACION DE UN CAMPO MAGNETICO COMPRENDEN VARIOS MEDIOS DISTINTOS (31 A 33) DE CREACION DE UN CAMPO MAGNETICO Y DE LAS PIEZAS RADIALES PLANAS (34, 35) INTERNA (35) Y EXTERNA (34) DISPUESTAS AL NIVEL DE LA CARA DE SALIDA POR AMBAS PARTES DEL CANAL PRINCIPAL (24) Y CONECTADAS ENTRE SI POR UN ALMA CENTRAL (38), UNA CULATA (36) Y UN CIRCUITO MAGNETICO PERIFERICO (37) DISPUESTO AXIALMENTE AL EXTERIOR DEL CANAL PRINCIPAL (24). LA CULATA (36) ESTA CONSTITUIDA POR ELEMENTOS RADIALES SITUADOS INMEDIATAMENTE EN LAS INMEDIACIONES DEL ANODO (25) Y QUE ATRAVIESA LA CAMARA TAMPON ANULAR (23) DISPONIENDO ENTRE SI ESPACIOS DE COMUNICACION (13) ENTRE LA CAMARA TAMPON ANULAR (23) Y EL CANAL PRINCIPAL (24).
ES93913165T 1993-06-21 1993-06-21 Motor de plasma de longitud reducida con deriva cerrada de electrones. Expired - Lifetime ES2092314T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/FR1993/000612 WO1995000758A1 (fr) 1993-06-21 1993-06-21 Moteur a plasma de longueur reduite a derive fermee d'electrons

Publications (1)

Publication Number Publication Date
ES2092314T3 true ES2092314T3 (es) 1996-11-16

Family

ID=9443268

Family Applications (1)

Application Number Title Priority Date Filing Date
ES93913165T Expired - Lifetime ES2092314T3 (es) 1993-06-21 1993-06-21 Motor de plasma de longitud reducida con deriva cerrada de electrones.

Country Status (8)

Country Link
US (1) US5475354A (es)
EP (1) EP0662195B1 (es)
JP (1) JP3609407B2 (es)
DE (1) DE69304336T2 (es)
ES (1) ES2092314T3 (es)
RU (1) RU2107837C1 (es)
UA (1) UA27921C2 (es)
WO (1) WO1995000758A1 (es)

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US6735935B2 (en) * 2000-12-14 2004-05-18 Busek Company Pulsed hall thruster system
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KR100599094B1 (ko) 2004-11-29 2006-07-12 삼성전자주식회사 코일의 권선수 조절에 의한 전자기 유도 가속장치
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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
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JP4816179B2 (ja) * 2006-03-20 2011-11-16 三菱電機株式会社 ホールスラスタ
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RU2543103C2 (ru) * 2013-06-24 2015-02-27 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Ионный двигатель
US9706633B2 (en) * 2013-07-02 2017-07-11 Nihon University Magnetized coaxial plasma generation device
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US10273944B1 (en) * 2013-11-08 2019-04-30 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Propellant distributor for a thruster
RU2565646C1 (ru) * 2014-03-18 2015-10-20 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Ионный двигатель
CN109074998A (zh) * 2016-04-29 2018-12-21 雷特罗萨米科技有限责任公司 Vhf z线圈等离子体源
RU2682962C1 (ru) * 2018-06-14 2019-03-25 федеральное государственное автономное образовательное учреждение высшего образования "Санкт-Петербургский политехнический университет Петра Великого" (ФГАОУ ВО "СПбПУ") Ионный ракетный двигатель космического аппарата
CN111120112B (zh) * 2019-12-04 2022-06-14 中国人民解放军空军工程大学 基于燃烧室二次流的多阳极滑动弧等离子体点火器及点火方法
CN112788825B (zh) * 2020-12-15 2024-09-10 成都金创立科技有限责任公司 一种一体化多极式等离子发生器
US12504006B2 (en) * 2024-05-17 2025-12-23 California Institute Of Technology Gas distributor for electric propulsion systems

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Also Published As

Publication number Publication date
DE69304336T2 (de) 1997-01-23
EP0662195B1 (fr) 1996-08-28
RU2107837C1 (ru) 1998-03-27
UA27921C2 (uk) 2000-10-16
DE69304336D1 (de) 1996-10-02
JP3609407B2 (ja) 2005-01-12
JPH08500699A (ja) 1996-01-23
WO1995000758A1 (fr) 1995-01-05
RU95107039A (ru) 1996-11-20
EP0662195A1 (fr) 1995-07-12
US5475354A (en) 1995-12-12

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