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US3620018A - Ion thruster magnetic field control - Google Patents

Ion thruster magnetic field control Download PDF

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Publication number
US3620018A
US3620018A US67815A US3620018DA US3620018A US 3620018 A US3620018 A US 3620018A US 67815 A US67815 A US 67815A US 3620018D A US3620018D A US 3620018DA US 3620018 A US3620018 A US 3620018A
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United States
Prior art keywords
magnetic field
thruster
ion thruster
chamber
shunting
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Expired - Lifetime
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US67815A
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Bruce A Banks
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National Aeronautics and Space Administration NASA
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National Aeronautics and Space Administration NASA
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01J—ELECTRIC DISCHARGE TUBES OR DISCHARGE LAMPS
    • H01J27/00—Ion beam tubes
    • H01J27/02—Ion sources; Ion guns
    • H01J27/08—Ion sources; Ion guns using arc discharge
    • H01J27/14—Other arc discharge ion sources using an applied magnetic field
    • 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
    • F03H1/0056—Electrostatic ion thrusters with an acceleration grid and an applied magnetic field

Definitions

  • This invention is concerned with controlling the magnetic field of an ion thruster for improved starting and to enable adjacent magnetic field sensing devices to properly sense the natural magnetic field.
  • the invention is particularly directed to a temperature controlled magnetic shunting system that is self-control and operates without power.
  • An electron bombardment ion engine of the type shown in U.S. Pat. No. 3,156,090 has a chamber in which a vaporized propellant is ionized by high velocity electrons emitted by a cathode.
  • a magnetic field is used to increase the path traveled by the high velocity electrons so that more electrons will collide with propellant particles in the chamber.
  • An electromagnet has been used to produce the required magnetic field. While an electromagnet provides accurate control of the magnitude of the magnetic field it consumes power and requires power conditioning equipment. This equipment adds weight and complexity to the thruster.
  • Electrostatic ion thrusters of the type shown in U.S. Pat. No. 3,238,715 utilize permanent magnets to produce the required magnetic field. While these permanent magnets require no power there is no control of the magnetic field.
  • a thruster is provided with a permanent magnet shunting structure that functions automatically.
  • the required magnetic field is provided by a permanent magnet.
  • the thruster is not operating the magnetic field is confined to a very small region to eliminate stray field lines which might interfere with the natural magnetic field found by adjacent magnetic field sensors.
  • FIG. 1 is an axial sectional view of an ion thruster having a magnetic field control constructed in accordance with the invention
  • FIG. 2 is a sectional view taken along the line 2-2 in FIG. 1;
  • FIG. 3 is a partial view illustrating an alternate embodiment of the present invention.
  • FIG. 1 an electron bombardment ion thruster 10 having an ionization chamber 12 within a tubular housing 14.
  • a distributor 16 in the form of a mild steel plate is mounted at one end of the chamber 12.
  • An accelerator system 18 is mounted at the opposite end of the ionization chamber 12.
  • the accelerator system 18 may be of the double grid type disclosed in U.S. Pat. No. 3,156,090. This system may also be of the single grid type disclosed in application Ser. No. 758,390 which was filed Sept. 9, 1968
  • a gaseous propellant such as mercury
  • a gaseous propellant discharges from the end of a hollow cathode 20 and passes through a baffle 22 into the chamber 12.
  • a potential is applied between a keeper cap 24 and the cathode 20. Electrons emitted from the heated cathode initiate an arc discharge as described in copending application Ser. No. 38,262 entitled Ion Thruster Cathode which was filed May 18, 1970.
  • An anode 26 mounted in the chamber 12 receives electrons from the cathode 20 as described in U.S. Pat. No. 3,156,090.
  • the electron paths are lengthened by a suitable magnetic field within the chamber 12.
  • a suitable magnetic field is formed between a cathode pole piece 28 and a grid pole piece 30.
  • the cathode pole piece 28 is mounted on the distributor plate 16 in surrounding relationship relative to the bafile 22.
  • the grid pole piece 30 is mounted adjacent the grid 18. Both pole pieces 28, 30 are preferably of mild steel to guide the magnetic lines of flux which flow between the pole pieces 28, 30.
  • the magnetic field is established by high ferromagnetic Curie temperature permanent magnets 32 which are mounted adjacent of the housing 14 as shown in FIG. 1. These magnets 32 extend between the distributor plate 16 and the grid pole piece 30.
  • Each permanent magnet 32 is completely surrounded by a low ferromagnetic Curie temperature alloy shunt 3 4 as shown in FIGS. 1 and 2.
  • the low ferromagnetic Curie temperature alloy 34 provides a magnetic shunt for the magnetic flux which would normally go through the pole pieces 30 and into the ionization chamber 12. In this manner the magnetic field lines stay essentially confined to each permanent magnet and the shunt alloys surrounding it when the thruster is cool.
  • the temperature of the thruster 10 is well below the ferromagnetic Curie temperature of the surrounding shunt alloy 34 when the thruster is not operating.
  • the housing 14 When a weak discharge is obtained between the cathode 20 and the anode 26 the housing 14, the anode, the permanent magnets 32, and a low Curie temperature alloy 34 begin to heat. When this occurs the shunt formed by the alloy 34 begins to lose permeability and does not divert as much of the permanent magnet flux as it did when it was cool. When the shunt 34 heats up to or above its Curie temperature it becomes paramagnetic, and all of the permanent flux as if the shunt were not there.
  • the magnet system When the thruster is hot the magnet system allows the normal operating flux to pass through the ionization chamber 12. When the thruster is cool the flux is confined to the shunt-magnet system.
  • the shunt material 34 may be a nickel-iron alloy.
  • One satisfactory alloy of approximately 34% nickel and 70% iron has a Curie temperature of about 300 F.
  • the permanent magnet 32 may be alnico 5.
  • This material has a Curie temperature of about 1634 F.
  • FIG. 3 there is shown an alternate embodiment of the invention.
  • a shunting material 36 not only surrounds each permanent magnet 32, but also forms the housing of the thruster. In this embodiment no other housing structure is utilized.
  • the anode 26 is adjacent the shunting material 36.
  • the anode 26 may also be made of the shunting alloy.
  • the body of the thruster may be fabricated in the form of concentric cylinders of permanent magnet and shunting alloys.
  • the cathode pole piece may be fabricated in the form of concentric cylinders of permanent magnet and shunting alloys.
  • An electron bombardment ion thruster comprising:
  • a housing forming the peripheral wall of the chamber for containing an ionizable propellant
  • a cathode for emitting high velocity electrons to said anode for bombarding said propellant to form ions
  • an apertured grid positioned at one end of said chamber to accelerate said ions away from said thruster
  • a plurality of permanent magnets adjacent said housing 4 to form a magnetic field about said anode and cathode whereby the paths of said high velocity electrons are lengthened to increase the rate of collision of said electrons with particles of said propellant, and means in close proximity with said permanent magnets for shunting said magnetic field only when the temperature in said chamber is below a predetermined minimum value.
  • An electron bombardment ion thruster as claimed in claim 2 wherein the means for shunting the magnetic field comprises a low ferromagnetic Curie temperature material adjacent the permanent magnets.

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  • 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)

Abstract

THE MAGNETIC FIELD OF AN ION THRUSTER IS AUTOMATICALLY SHUNTED WHEN THE THRUSTER IS NOT OPERATING.

Description

NOV.- 16, 1971 BANKS 3,620,018
ION THRUSTER MAGNETIC FIELD CONTROL Filed Aug. 28, 1970 ////,& 2g/// mvzmons BRUCE A. BANKS BY in ATTORNEY United States Patent 3,620,018 ION THRUSTER MAGNETIC FIELD CONTROL Bruce A. Banks, Olmsted Township, Cuyahoga County,
Ohio, assignor to the United States of America as represented by the Administrator of the National Aeronautics and Space Administration Filed Aug. 28, 1970, Ser. No. 67,815 Int. Cl. F03h 5/00 U.S. Cl. 60-202 Claims ABSTRACT OF THE DISCLOSURE The magnetic field of an ion thruster is automatically shunted when the thruster is not operating.
ORIGIN OF THE INVENTION The invention described herein was made by an employee 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 controlling the magnetic field of an ion thruster for improved starting and to enable adjacent magnetic field sensing devices to properly sense the natural magnetic field. The invention is particularly directed to a temperature controlled magnetic shunting system that is self-control and operates without power.
An electron bombardment ion engine of the type shown in U.S. Pat. No. 3,156,090 has a chamber in which a vaporized propellant is ionized by high velocity electrons emitted by a cathode. A magnetic field is used to increase the path traveled by the high velocity electrons so that more electrons will collide with propellant particles in the chamber.
Transient difficulties have been encountered with start-- ing a thruster having a high magnetic field. Also satellites and planetary probes using electron bombardment ion thrusters may carry magnetic field sensing devices. The natural magnetic field will not be properly sensed if the sensing device is influenced by the ion thruster.
An electromagnet has been used to produce the required magnetic field. While an electromagnet provides accurate control of the magnitude of the magnetic field it consumes power and requires power conditioning equipment. This equipment adds weight and complexity to the thruster.
Electrostatic ion thrusters of the type shown in U.S. Pat. No. 3,238,715 utilize permanent magnets to produce the required magnetic field. While these permanent magnets require no power there is no control of the magnetic field.
SUMMARY OF THE INVENTION These problems have been solved by the present invention wherein a thruster is provided with a permanent magnet shunting structure that functions automatically. During operation of the thruster the required magnetic field is provided by a permanent magnet. When the thruster is not operating the magnetic field is confined to a very small region to eliminate stray field lines which might interfere with the natural magnetic field found by adjacent magnetic field sensors.
OBJECTS OF THE INVENTION It is, therefor, an object of the present invention to provide an automatic control for the magnetic field of an ion thruster.
3,620,018 Patented Nov. 16, 1971 ice DESCRIPTION OF THE DRAWING FIG. 1 is an axial sectional view of an ion thruster having a magnetic field control constructed in accordance with the invention;
FIG. 2 is a sectional view taken along the line 2-2 in FIG. 1;
FIG. 3 is a partial view illustrating an alternate embodiment of the present invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to the drawing there is shown in FIG. 1 an electron bombardment ion thruster 10 having an ionization chamber 12 within a tubular housing 14. A distributor 16 in the form of a mild steel plate is mounted at one end of the chamber 12.
An accelerator system 18 is mounted at the opposite end of the ionization chamber 12. The accelerator system 18 may be of the double grid type disclosed in U.S. Pat. No. 3,156,090. This system may also be of the single grid type disclosed in application Ser. No. 758,390 which was filed Sept. 9, 1968 In operation, a gaseous propellant, such as mercury, discharges from the end of a hollow cathode 20 and passes through a baffle 22 into the chamber 12. A potential is applied between a keeper cap 24 and the cathode 20. Electrons emitted from the heated cathode initiate an arc discharge as described in copending application Ser. No. 38,262 entitled Ion Thruster Cathode which was filed May 18, 1970.
An anode 26 mounted in the chamber 12 receives electrons from the cathode 20 as described in U.S. Pat. No. 3,156,090. The electron paths are lengthened by a suitable magnetic field within the chamber 12. Such a magnetic field is formed between a cathode pole piece 28 and a grid pole piece 30.
The cathode pole piece 28 is mounted on the distributor plate 16 in surrounding relationship relative to the bafile 22. The grid pole piece 30 is mounted adjacent the grid 18. Both pole pieces 28, 30 are preferably of mild steel to guide the magnetic lines of flux which flow between the pole pieces 28, 30.
According to the present invention the magnetic field is established by high ferromagnetic Curie temperature permanent magnets 32 which are mounted adjacent of the housing 14 as shown in FIG. 1. These magnets 32 extend between the distributor plate 16 and the grid pole piece 30.
Each permanent magnet 32 is completely surrounded by a low ferromagnetic Curie temperature alloy shunt 3 4 as shown in FIGS. 1 and 2. When the thruster 10 is not operating the thruster housing 14 and magnet system are cool. Because the thruster is cool the low ferromagnetic Curie temperature alloy 34 provides a magnetic shunt for the magnetic flux which would normally go through the pole pieces 30 and into the ionization chamber 12. In this manner the magnetic field lines stay essentially confined to each permanent magnet and the shunt alloys surrounding it when the thruster is cool. The temperature of the thruster 10 is well below the ferromagnetic Curie temperature of the surrounding shunt alloy 34 when the thruster is not operating.
When a weak discharge is obtained between the cathode 20 and the anode 26 the housing 14, the anode, the permanent magnets 32, and a low Curie temperature alloy 34 begin to heat. When this occurs the shunt formed by the alloy 34 begins to lose permeability and does not divert as much of the permanent magnet flux as it did when it was cool. When the shunt 34 heats up to or above its Curie temperature it becomes paramagnetic, and all of the permanent flux as if the shunt were not there.
When the thruster is hot the magnet system allows the normal operating flux to pass through the ionization chamber 12. When the thruster is cool the flux is confined to the shunt-magnet system.
The shunt material 34 may be a nickel-iron alloy. One satisfactory alloy of approximately 34% nickel and 70% iron has a Curie temperature of about 300 F.
With such a shunting material the permanent magnet 32 may be alnico 5. This material has a Curie temperature of about 1634 F.
DESCRIPTION OF THE ALTERNATE EMBODIMENT Referring now to FIG. 3 there is shown an alternate embodiment of the invention. In this embodiment a shunting material 36 not only surrounds each permanent magnet 32, but also forms the housing of the thruster. In this embodiment no other housing structure is utilized. The anode 26 is adjacent the shunting material 36.
While the preferred embodiment of the invention has been shown and described it will be appreciated that various structural modifications may be made without departing from the spirit of the invention or the scope of the subjoined claims. By way of example, the anode 26 may also be made of the shunting alloy. Also the body of the thruster may be fabricated in the form of concentric cylinders of permanent magnet and shunting alloys. It is further contemplated that the cathode pole piece may be fabricated in the form of concentric cylinders of permanent magnet and shunting alloys.
What is claimed is:
1. An electron bombardment ion thruster comprising:
a housing forming the peripheral wall of the chamber for containing an ionizable propellant,
a source of said propellant in communication with said chamber,
an anode within said chamber,
a cathode for emitting high velocity electrons to said anode for bombarding said propellant to form ions, an apertured grid positioned at one end of said chamber to accelerate said ions away from said thruster,
a plurality of permanent magnets adjacent said housing 4 to form a magnetic field about said anode and cathode whereby the paths of said high velocity electrons are lengthened to increase the rate of collision of said electrons with particles of said propellant, and means in close proximity with said permanent magnets for shunting said magnetic field only when the temperature in said chamber is below a predetermined minimum value.
2. An electron bombardment ion thruster as claimed in claim 11 wherein the magnetic field is established by high ferromagnetic Curie temperature permanent magnets spaced about the chamber.
3. An electron bombardment ion thruster as claimed in claim 2 wherein the permanent magnets are of an aluminum-nickel alloy.
4. An electron bombardment ion thruster as claimed in claim 2 wherein the means for shunting the magnetic field comprises a low ferromagnetic Curie temperature material adjacent the permanent magnets.
5. An electron bombardment ion thruster as claimed in claim 4 wherein the shunting material is a nickel-iron alloy.
6. An electron bombardment ion thruster as claimed in claim 5 wherein the nickel-iron alloy contains about 30% nickel and 70% iron by weight.
7. An electron bombardment ion thruster as claimed in claim 4 wherein the shunting material surrounds the permanent magnets.
8. An electron bombardment ion thruster as claimed in claim 7 wherein the low ferromagnetic Curie temperature material forms the housing of the thruster.
9. An electron bombardment ion thruster as claimed in claim 1 wherein the anode is of a low ferromagnetic Curie temperature shunting material.
10. An electron bombardment ion thruster as claimed in claim 1 wherein the housing is in the form of concentric cylinders of permanent magnetic and shunting alloy materials.
References Cited UNITED STATES PATENTS 3,238,715 3/1966 Reader et a1. 202 3,243,954 4/1966 Cann 60-202 3,412,559 11/1968 Sohl 60202 3,262,262 7/1966 Reader et a1. 60-202 3,156,090 11/1964 Kaufman 60202 DOUGLAS HART, Primary Examiner R. B. ROTHMAN, Assistant Examiner US. Cl. X.R. 3 l3-16l
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3728861A (en) * 1971-12-20 1973-04-24 Nasa Ion thruster with a combination keeper electrode and electron baffle
US4277939A (en) * 1979-04-09 1981-07-14 Hughes Aircraft Company Ion beam profile control apparatus and method
US4466242A (en) * 1983-03-09 1984-08-21 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Ring-cusp ion thruster with shell anode
JPH02130271A (en) * 1988-11-07 1990-05-18 Natl Aerospace Lab Electron impact type cusp type ion engine
US4937456A (en) * 1988-10-17 1990-06-26 The Boeing Company Dielectric coated ion thruster
US5231824A (en) * 1991-08-09 1993-08-03 Dick Robert C Van Ion beam and ion jet stream motor
US6619028B2 (en) * 2001-12-05 2003-09-16 The Boeing Co. Electric thruster made with surface treatments for improved thermal management
US9657725B2 (en) 2014-02-23 2017-05-23 Gil Berl Ion thruster
US10378521B1 (en) 2016-05-16 2019-08-13 United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Solid electrolyte-based microthrusters

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3728861A (en) * 1971-12-20 1973-04-24 Nasa Ion thruster with a combination keeper electrode and electron baffle
US4277939A (en) * 1979-04-09 1981-07-14 Hughes Aircraft Company Ion beam profile control apparatus and method
US4466242A (en) * 1983-03-09 1984-08-21 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Ring-cusp ion thruster with shell anode
US4937456A (en) * 1988-10-17 1990-06-26 The Boeing Company Dielectric coated ion thruster
JPH02130271A (en) * 1988-11-07 1990-05-18 Natl Aerospace Lab Electron impact type cusp type ion engine
JPH0747947B2 (en) 1988-11-07 1995-05-24 航空宇宙技術研究所長 Electron impact type cusp type ion engine
US5231824A (en) * 1991-08-09 1993-08-03 Dick Robert C Van Ion beam and ion jet stream motor
US6619028B2 (en) * 2001-12-05 2003-09-16 The Boeing Co. Electric thruster made with surface treatments for improved thermal management
US9657725B2 (en) 2014-02-23 2017-05-23 Gil Berl Ion thruster
US10378521B1 (en) 2016-05-16 2019-08-13 United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Solid electrolyte-based microthrusters

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