GB1521327A - High-frequency plasma drive - Google Patents

High-frequency plasma drive

Info

Publication number
GB1521327A
GB1521327A GB4594075A GB4594075A GB1521327A GB 1521327 A GB1521327 A GB 1521327A GB 4594075 A GB4594075 A GB 4594075A GB 4594075 A GB4594075 A GB 4594075A GB 1521327 A GB1521327 A GB 1521327A
Authority
GB
United Kingdom
Prior art keywords
plasma
generator
resonator
discharge chamber
magnetic field
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
Application number
GB4594075A
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm 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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of GB1521327A publication Critical patent/GB1521327A/en
Expired legal-status Critical Current

Links

Classifications

    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01JELECTRIC DISCHARGE TUBES OR DISCHARGE LAMPS
    • H01J27/00Ion beam tubes
    • H01J27/02Ion sources; Ion guns
    • H01J27/16Ion sources; Ion guns using high-frequency excitation, e.g. microwave excitation
    • H01J27/18Ion sources; Ion guns using high-frequency excitation, e.g. microwave excitation with an applied axial magnetic field
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00Using plasma to produce a reactive propulsive thrust
    • F03H1/0081Electromagnetic plasma thrusters
    • HELECTRICITY
    • H05ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05HPLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
    • H05H1/00Generating plasma; Handling plasma
    • H05H1/24Generating plasma
    • H05H1/46Generating plasma using applied electromagnetic fields, e.g. high frequency or microwave energy

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Plasma & Fusion (AREA)
  • Electromagnetism (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)

Abstract

1521327 Jet propulsion plant MESSERSCHMITT-BÍLKOW-BLOHM GmbH 5 Nov 1975 [16 Nov 1974] 45940/75 Heading F1J [Also in Division H1] A high frequency plasma drive comprises a “ # high frequency generator 7 coaxially coupled to a “ # resonator 8 which forms part of an open ended discharge chamber 11 in which a uniform magnetic field is produced by coil 15 and in which propellant gas is ionized and the plasma subsequently accelerated, wherein the intensity of the magnetic field in the discharge chamber, the frequency of the generator and the density of the plasma are so arranged that the dielectric constant of the plasma is negative whereby Lorentz forces acting on the plasma are subject to resonance-like intensification. As shown, the generator and discharge chamber are formed by coaxial tubes 2, 3 inter-connected by a disc 4, all of silver plated copper, the generator 7 being energized by a planar-triode 5 through an isolating capacitor 6. The cylindrical cavity circuits i in the generator and resonator interconnected through an inductive coupling loop 9. Mercury vapour is introduced through a distributer 12 into the discharge chamber 11 which is closed at one end by a quartz disc 10. When drive is put into operation the gas discharge ignites in the electrical field of the resonator without a special ignition device and the plasma is accelerated from the chamber by Lorentz forces. The mechanism of this acceleration and the factors influencing it are theoretically discussed in some detail. In a modification, Fig. 2 (not shown), a quartz plasma boundary anchor (21) followed by acceleration and retardation electrodes (22) is provided at the open end of the resonator to accelerate the ions, which may be neutralized by electrons from an axially disposed hollow cathode (23). The current density may be varied by means of the intensity of the magnetic field.
GB4594075A 1974-11-16 1975-11-05 High-frequency plasma drive Expired GB1521327A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19742454458 DE2454458C3 (en) 1974-11-16 1974-11-16 High frequency plasma engine

Publications (1)

Publication Number Publication Date
GB1521327A true GB1521327A (en) 1978-08-16

Family

ID=5931045

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4594075A Expired GB1521327A (en) 1974-11-16 1975-11-05 High-frequency plasma drive

Country Status (2)

Country Link
DE (1) DE2454458C3 (en)
GB (1) GB1521327A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2229865A (en) * 1988-11-01 1990-10-03 Roger John Shawyer Electrical propulsion unit for spacecraft
GB2334761A (en) * 1998-04-29 1999-09-01 Roger John Shawyer Microwave thruster for spacecraft

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2952046C2 (en) * 1979-12-22 1982-04-15 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5300 Bonn Method and device for generating an electrical discharge in a gas flowing at supersonic speed
CN114810527B (en) * 2022-06-28 2022-09-09 国科大杭州高等研究院 Gas reverse injection distributor anode integrated structure of low-power Hall thruster

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2219545A1 (en) * 1972-04-21 1973-10-31 Messerschmitt Boelkow Blohm ION ENGINE

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2229865A (en) * 1988-11-01 1990-10-03 Roger John Shawyer Electrical propulsion unit for spacecraft
GB2229865B (en) * 1988-11-01 1993-05-05 Roger John Shawyer Electrical propulsion unit for spacecraft
GB2334761A (en) * 1998-04-29 1999-09-01 Roger John Shawyer Microwave thruster for spacecraft
GB2334761B (en) * 1998-04-29 2000-04-19 Roger John Shawyer Microwave thruster for spacecraft

Also Published As

Publication number Publication date
DE2454458B2 (en) 1981-04-02
DE2454458C3 (en) 1981-12-10
DE2454458A1 (en) 1976-05-20

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee