US3744247A - Single grid accelerator for an ion thrustor - Google Patents

Single grid accelerator for an ion thrustor Download PDF

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US3744247A
US3744247A US00180473A US3744247DA US3744247A US 3744247 A US3744247 A US 3744247A US 00180473 A US00180473 A US 00180473A US 3744247D A US3744247D A US 3744247DA US 3744247 A US3744247 A US 3744247A
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grid
ion
aluminum oxide
thrustor
accelerator
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P Margosian
S Nakanishi
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National Aeronautics and Space Administration NASA
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    • 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
    • F03H1/0043—Electrostatic ion thrusters characterised by the acceleration grid

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  • a single grid accelerator system for an ion thrustor A UeS- layer of dielectric material is interposed between 313/230, 3 355 metal grid and the chamber containing an ionized pro- [5 Int. Cl. .3 pellant for protecting the against puttering ero- [58] Field of Search 313/63, 207, 107, Siom 3 Claims, 3 Drawing Figures "QQQQQQQQQ - ⁇ QQQQQQQQQ PATENTED JUL polars INVENTORS PAUL M. MARGOSIAN SHIGEO NAKANISHI ATTORNEYS SINGLE GRID ACCELERATOR FOR AN ION THRUSTOR This is a continuation of application Ser. No. 758,540 filed Sept. 9, 1968, and now abandoned.
  • This invention is concerned with an improved ion extractor component for an ion thrustor.
  • the invention is particularly directed to a single grid accelerator system for an electron bombardment type ion thrustor.
  • Accelerator grid systems used in electronbombardment thrustors have depended on a screen grid and an accelerator grid as two main components. Both are made of stainless steel or molybdenum and are mounted at close spacing relative to each other. The grids are maintained at a potential difference of several thousand volts with respect to each other. This voltage applied over the close spacing provides an electric field required for the extraction of ions from the ionization chamber thereby providing thrust.
  • the screen grid is operated at a positive potential and the accelerator at a negative potential. This accel-decel mode of operation insures maximum ion extraction while preventing back streaming of neutralizing electrons into the thrustor.
  • a dielectric material is interposed between the grid and the thrustor ionization chamber.
  • a metal grid has its upstream surface covered with dielectric material, or a dielectric grid may have its downstream surface covered with a metal.
  • an object of the present invention to provide a single grid accelerator system for an electron bombardment ion thrustor.
  • Another object of the invention is to provide an improved accelerator grid for an ion thrustor which is readily fabricated.
  • a still further object of the invention is to provide an electron bombardment ion thrustor which accomplishes the ion extraction function in an improved manner.
  • FIG. I is an isometric view having parts broken away along an axial quarter section of an electron bombardment ion thrustor showing an accelerator system constructed in accordance with the present invention
  • FIG. 2 is an enlarged sectional view taken along the line 2-2 in FIG. 1, and
  • FIG. 3 is an enlarged sectional view similar to FIG. 2 but showing an alternate embodiment of the invention.
  • An electron bombardment ion thrustor of the type described in U.S. Pat. No. 3,156,090 utilizes mercury as a propellant.
  • Mercury vapor is supplied to an ionization chamber through a distributor plate, and atoms of mercury are bombarded by electrons emitted from a cathode.
  • An axial magnetic field is supplied to increase the path length traveled by electrons going from the cathode toward an anode thereby increasing the ionization by electron bombardment.
  • Such an electron bombardment ion thrustor utilizes both a screen grid and an accelerator grid in its ion extraction portion.
  • the screen grid serves to contain the discharge plasma forming the necessary ion optics to prevent direct impingement of accelerated ions onto the accelerator grid. Ions in the near vicinity of the screen grid have a high probability of being accelerated to openings in the grids because of the high electric fields present. Thrust is produced as these ions accelerate through the grid system.
  • FIG. 1 there is shown an electron bombardment ion thrustor 10 of the aforementioned type.
  • the ion thrustor 10 has an ionization chamber 12 for containing mercury propellant that has been ionized by electron bombardment in the manner previously described.
  • the ion thrustor further includes an accelerator system for accelerating propellant ions in the direction of the arrows in FIGS. 1 and 2.
  • This accelerator system utilizes a single grid 14 in the form of a perforated plate of an electrically conducting material.
  • the accelerated propellant ions pass through holes 16 in this plate.
  • the grid 14 is connected to a source of electrical,
  • the electrical power source 18 impresses a potential on the grid 14 and is highly negative relative to the ionization chamber 12.
  • An insulator 20 having an annular configuration extends about the periphery of the ionization chamber 12.
  • the insulator 20 serves to electrically isolate the single grid from the metal housing forming the ionization chamber 12.
  • the electrically conducting grid 14 has the surface that faces the ionization chamber 12 protected from sputtering erosion. This is accomplished by positioning a layer of insulating material 22 between the chamber 12 and the grid 14 as shown in FIGS. 1 and 2.
  • the grid 14 is electrically conductive to establish the proper electrostatic field for accelerating the ions in the chamber 12 in the direction of the arrow.
  • the grid 14 may be of a perforated metal plate having the upstream surface covered with dielectric material 22 as shown in FIG. 2.
  • a molybdenum grid 14 having a coating of aluminum oxide flame sprayed thereon to form the dielectric coating 22 may be utilized.
  • deposited dielectric materials exhibit some degree of porosity which could be significant in long duration applications.
  • the alternate embodiment shown in FIG. 3 is preferred where long operating life is of primary importance.
  • This embodiment utilizes a grid 14 in the form of a perforated metal plate which is identical with the grid shown in FIGS. 1 and 2.
  • the alternate embodiment utilizes layers of dielectric material 24 that are separated by layers of metal 26.
  • the metal layers 26 are nonporous.
  • Vapor deposition of the metal 26 is preferred because the thickness of this layer can be controlled. Such a deposition process enables larger overall potential differences between the positive plasma and the negative base metal grid to be maintained.
  • a perforated plate'of dielectric material 22 could be used at the start of fabrication.
  • the downstream surface of this dielectric plate would be covered with a metal to form the grid 14.
  • the single grid 14 mounts in the same location as the previous grid systems and serves the same purpose. However, this accelerator system accomplishes the ion extraction in an improved manner.
  • the single grid 14 is maintained at a negative potential by the electrical power source 18.
  • Thedielectric layer 22 which is exposed to the plasma in the ion chamber 12 assumes a positive potential nearly equal in value to that of the plasma potential.
  • the electric field necessary for ion extraction is established with a single component acceldecel grid system rather than the conventional two component system. Potential differences up to the break down limits of the dielectric material in the layer 22 are possible.
  • An electron bombardment ion thruster comprising a source of ions comprising a cylindrical housing forming a chamber
  • an aluminum oxide plate having a plurality of apertures therein mounted on said housing thereby covering one end of said chamber, said aluminum oxide plate having a first surface facing towards said chamber and a second surface facing away from said chamber, said apertures extending between said first and second surfaces, said aluminum oxide plate having a positive potential substantially equal to that of said plasma whereby said plasma covers said first surface and said apertures, I
  • annular insulator extending about the periphery of said chamber in contact with said housing and said first surface of said plate
  • an accelerator system comprising a layer of molybdenum covering said second surface of said aluminum oxide plate, and
  • An electron bombardment ion thruster having an accelerator system as claimed in claim 1 including a second aluminum oxide plate in contact with a surface of said molybdenum layer opposite said first named aluminum oxide plate, and
  • An electron bombardment ion thruster as claimed in claim 2 having a third aluminum oxide plate in contact with the surface of said second molybdenum layer opposite said second aluminum oxide plate, and

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Particle Accelerators (AREA)

Abstract

A single grid accelerator system for an ion thrustor. A layer of dielectric material is interposed between this metal grid and the chamber containing an ionized propellant for protecting the grid against sputtering erosion.

Description

C ilmted States Patent 1191 3,744,247 Margosianetal. 1 July 10, 1973 SINGLE GRID ACCELERATOR FOR AN ION [56] References Cited THRUSTOR UNITEDSTATESPATENTS 1 Inventors: Paul Margosian, Roslindale, 3,371,489 3/1968 Eckhardt 313/63 x Mass.; Shigeo Nakanishi, Berea, 2,913,617 11/1959 Tucker 313/355 X Ohio 3,021,446 2/1962 Ekkers et a1..." 313/218 X I 3,345,820 10/1967 Dryden 313/63 X 1 1 Asslgneel The Ulmed States of America as 3,500,122 3/1970 S0111 313/63 x represented by the Administrat r f 2,068,287 1 1937 Gabor 313 207 x the National Aeronautics and Space 2,094,450 9/1937 Geffcken et al. 313/207 X Administration, Washington, DC. 3,250,942 5/1966 Yoshida et al.. 313/107 X 3,297,902 l/1967 Beggs 313/355 X [22] F1led: Sept. 14, 1971 [21] Appl. No.: 180,473 Primary Examiner-Palmer C. Demeo Related Us. Application Data Attorney-N. T. Mus1al, Gene E. Shook et al.
63 C t' t' f S N 758,540, S t. 9, 1968, 1 352L313? er ep 7] AB T A T I A single grid accelerator system for an ion thrustor. A UeS- layer of dielectric material is interposed between 313/230, 3 355 metal grid and the chamber containing an ionized pro- [5 Int. Cl. .3 pellant for protecting the against puttering ero- [58] Field of Search 313/63, 207, 107, Siom 3 Claims, 3 Drawing Figures "QQQQQQQQQQQ -\QQQQQQQQQ PATENTED JUL polars INVENTORS PAUL M. MARGOSIAN SHIGEO NAKANISHI ATTORNEYS SINGLE GRID ACCELERATOR FOR AN ION THRUSTOR This is a continuation of application Ser. No. 758,540 filed Sept. 9, 1968, and now abandoned.
STATEMENT OF GOVERNMENT OWNERSHIP The invention described herein was made by employees of the United States Government and may be manufactured and used by or for the Government for governmental purposes without the payment of any royalties thereon or therefor.
BACKGROUND OF THE INVENTION This invention is concerned with an improved ion extractor component for an ion thrustor. The invention is particularly directed to a single grid accelerator system for an electron bombardment type ion thrustor.
Accelerator grid systems used in electronbombardment thrustors have depended on a screen grid and an accelerator grid as two main components. Both are made of stainless steel or molybdenum and are mounted at close spacing relative to each other. The grids are maintained at a potential difference of several thousand volts with respect to each other. This voltage applied over the close spacing provides an electric field required for the extraction of ions from the ionization chamber thereby providing thrust. The screen grid is operated at a positive potential and the accelerator at a negative potential. This accel-decel mode of operation insures maximum ion extraction while preventing back streaming of neutralizing electrons into the thrustor.
One type of grid system employs a parallel wire arrangement. Such a system is shown in U.S. Pat. No. 3,156,090. A pair of perforated plates having aligned holes has also been utilized. The overall weight of these double grid systems as well as the hardware required for proper mounting is objectionable. The required uniform gap of close spacing between the grids further creates fabrication problems.
SUMMARY OF THE INVENTION These problems have been solved by the single grid accelerator system constructed in accordance with the present invention. A dielectric material is interposed between the grid and the thrustor ionization chamber. A metal grid has its upstream surface covered with dielectric material, or a dielectric grid may have its downstream surface covered with a metal.
It is, therefore, an object of the present invention to provide a single grid accelerator system for an electron bombardment ion thrustor.
Another object of the invention is to provide an improved accelerator grid for an ion thrustor which is readily fabricated.
A still further object of the invention is to provide an electron bombardment ion thrustor which accomplishes the ion extraction function in an improved manner.
These and other objects of the invention will be apparent from the specification which follows and from the drawing wherein like numerals are used throughout to identify like parts.
DESCRIPTION OF THE DRAWING FIG. I is an isometric view having parts broken away along an axial quarter section of an electron bombardment ion thrustor showing an accelerator system constructed in accordance with the present invention,
FIG. 2 is an enlarged sectional view taken along the line 2-2 in FIG. 1, and
FIG. 3 is an enlarged sectional view similar to FIG. 2 but showing an alternate embodiment of the invention. I
DESCRIPTION OF THE PREFERRED EMBODIMENT An electron bombardment ion thrustor of the type described in U.S. Pat. No. 3,156,090 utilizes mercury as a propellant. Mercury vapor is supplied to an ionization chamber through a distributor plate, and atoms of mercury are bombarded by electrons emitted from a cathode. An axial magnetic field is supplied to increase the path length traveled by electrons going from the cathode toward an anode thereby increasing the ionization by electron bombardment.
Such an electron bombardment ion thrustor utilizes both a screen grid and an accelerator grid in its ion extraction portion. The screen grid serves to contain the discharge plasma forming the necessary ion optics to prevent direct impingement of accelerated ions onto the accelerator grid. Ions in the near vicinity of the screen grid have a high probability of being accelerated to openings in the grids because of the high electric fields present. Thrust is produced as these ions accelerate through the grid system.
Referring now to FIG. 1 there is shown an electron bombardment ion thrustor 10 of the aforementioned type. The ion thrustor 10 has an ionization chamber 12 for containing mercury propellant that has been ionized by electron bombardment in the manner previously described.
The ion thrustor further includes an accelerator system for accelerating propellant ions in the direction of the arrows in FIGS. 1 and 2. This accelerator system utilizes a single grid 14 in the form of a perforated plate of an electrically conducting material. The accelerated propellant ions pass through holes 16 in this plate.
The grid 14 is connected to a source of electrical,
power, such as a battery 18, as shown in FIG. 1. The electrical power source 18 impresses a potential on the grid 14 and is highly negative relative to the ionization chamber 12.
An insulator 20 having an annular configuration extends about the periphery of the ionization chamber 12. The insulator 20 serves to electrically isolate the single grid from the metal housing forming the ionization chamber 12.
An important feature of the invention is that the electrically conducting grid 14 has the surface that faces the ionization chamber 12 protected from sputtering erosion. This is accomplished by positioning a layer of insulating material 22 between the chamber 12 and the grid 14 as shown in FIGS. 1 and 2.
The grid 14 is electrically conductive to establish the proper electrostatic field for accelerating the ions in the chamber 12 in the direction of the arrow. The grid 14 may be of a perforated metal plate having the upstream surface covered with dielectric material 22 as shown in FIG. 2. A molybdenum grid 14 having a coating of aluminum oxide flame sprayed thereon to form the dielectric coating 22 may be utilized.
In general, deposited dielectric materials exhibit some degree of porosity which could be significant in long duration applications. The alternate embodiment shown in FIG. 3 is preferred where long operating life is of primary importance.
This embodiment utilizes a grid 14 in the form of a perforated metal plate which is identical with the grid shown in FIGS. 1 and 2. Instead of utilizing a single covering of dielectric material as shown in FIG. 2, the alternate embodiment utilizes layers of dielectric material 24 that are separated by layers of metal 26. The metal layers 26 are nonporous.
Vapor deposition of the metal 26 is preferred because the thickness of this layer can be controlled. Such a deposition process enables larger overall potential differences between the positive plasma and the negative base metal grid to be maintained.
It is further contemplated that a perforated plate'of dielectric material 22 could be used at the start of fabrication. The downstream surface of this dielectric plate would be covered with a metal to form the grid 14.
The single grid 14 mounts in the same location as the previous grid systems and serves the same purpose. However, this accelerator system accomplishes the ion extraction in an improved manner. The single grid 14 is maintained at a negative potential by the electrical power source 18. Thedielectric layer 22 which is exposed to the plasma in the ion chamber 12 assumes a positive potential nearly equal in value to that of the plasma potential. The electric field necessary for ion extraction is established with a single component acceldecel grid system rather than the conventional two component system. Potential differences up to the break down limits of the dielectric material in the layer 22 are possible.
While several preferred embodiments of the invention have been described, it will be appreciated that various modifications may be made to the disclosed structure without departing from the spirit of the invention or the scope of the subjoined claims. For example, the size of the grid as well as the geometry of the perforations may be varied. It is further contemplated that the geometry of the dielectric layer may be changed to meet the special requirements.
We claim:
1. An electron bombardment ion thruster comprising a source of ions comprising a cylindrical housing forming a chamber,
ionized mercury forming a plasma having a positive potential in said chamber,
an aluminum oxide plate having a plurality of apertures therein mounted on said housing thereby covering one end of said chamber, said aluminum oxide plate having a first surface facing towards said chamber and a second surface facing away from said chamber, said apertures extending between said first and second surfaces, said aluminum oxide plate having a positive potential substantially equal to that of said plasma whereby said plasma covers said first surface and said apertures, I
an annular insulator extending about the periphery of said chamber in contact with said housing and said first surface of said plate, and
an accelerator system comprising a layer of molybdenum covering said second surface of said aluminum oxide plate, and
means for applying a potential to said molybdenum that is highly negative to said plasma whereby ions from said plasma covering said apertures in said aluminum oxide plate are accelerated through said apertures to produce thrust.
2. An electron bombardment ion thruster having an accelerator system as claimed in claim 1 including a second aluminum oxide plate in contact with a surface of said molybdenum layer opposite said first named aluminum oxide plate, and
a second molybdenum layer covering said second aluminum oxide plate.
3. An electron bombardment ion thruster as claimed in claim 2 having a third aluminum oxide plate in contact with the surface of said second molybdenum layer opposite said second aluminum oxide plate, and
a third molybdenum layer in contact with said third aluminum oxide plate.

Claims (2)

  1. 2. An electron bombardment ion thruster having an accelerator system as claimed in claim 1 including a second aluminum oxide plate in contact with a surface of said molybdenum layer opposite said first named aluminum oxide plate, and a second molybdenum layer covering said second aluminum oxide plate.
  2. 3. An electron bombardment ion thruster as claimed in claim 2 having a third aluminum oxide plate in contact with the surface of said second molybdenum layer opposite said second aluminum oxide plate, and a third molybdenum layer in contact with said third aluminum oxide plate.
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Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3866414A (en) * 1972-04-21 1975-02-18 Messerschmitt Boelkow Blohm Ion engine
US4058748A (en) * 1976-05-13 1977-11-15 Hitachi, Ltd. Microwave discharge ion source
EP0021140A1 (en) * 1979-06-29 1981-01-07 International Business Machines Corporation Ion source in a vacuum chamber and method for its operation
US4329617A (en) * 1978-10-12 1982-05-11 Siemens Aktiengesellschaft Control plate for a flat plasma screen
US4507588A (en) * 1983-02-28 1985-03-26 Board Of Trustees Operating Michigan State University Ion generating apparatus and method for the use thereof
EP0106497A3 (en) * 1982-09-10 1986-08-06 Nippon Telegraph And Telephone Corporation Ion shower apparatus
EP0132015A3 (en) * 1983-07-14 1986-12-30 University Of Tokyo An ion beam machining device
US4695760A (en) * 1982-01-18 1987-09-22 General Electric Company Self-aligned double grids for vacuum tubes
US4778561A (en) * 1987-10-30 1988-10-18 Veeco Instruments, Inc. Electron cyclotron resonance plasma source
EP0230290A3 (en) * 1986-01-21 1988-11-09 Leybold Aktiengesellschaft Extraction grid for an ion source and method of manufacturing the same
US4937456A (en) * 1988-10-17 1990-06-26 The Boeing Company Dielectric coated ion thruster
US5269131A (en) * 1992-08-25 1993-12-14 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Segmented ion thruster
EP0733800A1 (en) * 1995-03-20 1996-09-25 Matra Marconi Space Uk Limited Ion thruster
US6964396B2 (en) * 2001-12-04 2005-11-15 The Boeing Company Automatic accel voltage tracking system for an ion thruster
US20050257515A1 (en) * 2004-05-18 2005-11-24 The Boeing Company A method of ionizing a liquid propellant and an electric thruster implementing such a method
US20070033920A1 (en) * 2005-08-11 2007-02-15 The Boeing Company Method of ionizing a liquid and an electrostatic colloid thruster implementing such a method
US11965494B2 (en) * 2021-02-17 2024-04-23 Accion Systems, Inc. Electrospray emission apparatus

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3866414A (en) * 1972-04-21 1975-02-18 Messerschmitt Boelkow Blohm Ion engine
US4058748A (en) * 1976-05-13 1977-11-15 Hitachi, Ltd. Microwave discharge ion source
US4329617A (en) * 1978-10-12 1982-05-11 Siemens Aktiengesellschaft Control plate for a flat plasma screen
EP0021140A1 (en) * 1979-06-29 1981-01-07 International Business Machines Corporation Ion source in a vacuum chamber and method for its operation
US4695760A (en) * 1982-01-18 1987-09-22 General Electric Company Self-aligned double grids for vacuum tubes
EP0106497A3 (en) * 1982-09-10 1986-08-06 Nippon Telegraph And Telephone Corporation Ion shower apparatus
US4507588A (en) * 1983-02-28 1985-03-26 Board Of Trustees Operating Michigan State University Ion generating apparatus and method for the use thereof
EP0132015A3 (en) * 1983-07-14 1986-12-30 University Of Tokyo An ion beam machining device
EP0230290A3 (en) * 1986-01-21 1988-11-09 Leybold Aktiengesellschaft Extraction grid for an ion source and method of manufacturing the same
US4778561A (en) * 1987-10-30 1988-10-18 Veeco Instruments, Inc. Electron cyclotron resonance plasma source
US4937456A (en) * 1988-10-17 1990-06-26 The Boeing Company Dielectric coated ion thruster
US5269131A (en) * 1992-08-25 1993-12-14 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Segmented ion thruster
EP0733800A1 (en) * 1995-03-20 1996-09-25 Matra Marconi Space Uk Limited Ion thruster
US6964396B2 (en) * 2001-12-04 2005-11-15 The Boeing Company Automatic accel voltage tracking system for an ion thruster
US20050257515A1 (en) * 2004-05-18 2005-11-24 The Boeing Company A method of ionizing a liquid propellant and an electric thruster implementing such a method
US6996972B2 (en) * 2004-05-18 2006-02-14 The Boeing Company Method of ionizing a liquid propellant and an electric thruster implementing such a method
US20070033920A1 (en) * 2005-08-11 2007-02-15 The Boeing Company Method of ionizing a liquid and an electrostatic colloid thruster implementing such a method
US20110007446A1 (en) * 2005-08-11 2011-01-13 The Boeing Company Electrostatic colloid thruster
US8122701B2 (en) 2005-08-11 2012-02-28 The Boeing Company Electrostatic colloid thruster
US11965494B2 (en) * 2021-02-17 2024-04-23 Accion Systems, Inc. Electrospray emission apparatus
US12435709B2 (en) 2021-02-17 2025-10-07 Accion Systems, Inc. Electrospray emission apparatus

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