CN111140454B - Ignition device of miniature electron cyclotron resonance ion thruster - Google Patents
Ignition device of miniature electron cyclotron resonance ion thruster Download PDFInfo
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- CN111140454B CN111140454B CN202010091498.2A CN202010091498A CN111140454B CN 111140454 B CN111140454 B CN 111140454B CN 202010091498 A CN202010091498 A CN 202010091498A CN 111140454 B CN111140454 B CN 111140454B
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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
- F03H1/0006—Details applicable to different types of plasma thrusters
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Abstract
The invention provides a micro electron cyclotron resonance ion thruster ignition device, which comprises a cylindrical discharge cavity, a magnetic yoke, an antenna, a radioactive sheet, a shielding ring, a screen grid and an accelerating grid, wherein the magnetic yoke is positioned at the bottom of the cylindrical discharge cavity, the screen grid and the accelerating grid are sequentially fixed at the top of the cylindrical discharge cavity, and an inner magnetic ring and an outer magnetic ring are arranged in the magnetic yoke; the center of the magnetic yoke is connected with the waveguide, and an antenna is screwed at one end of the waveguide close to the screen grid; two shielding rings are arranged in parallel on the inner wall surface of a cylindrical discharge cavity between an antenna and a screen grid, a gap is formed between the two shielding rings, the two shielding rings are coaxially arranged with the cylindrical discharge cavity, and a radioactive sheet is placed in the gap between the two shielding rings; an insulating layer is arranged between the screen grid and the accelerating grid. The invention increases the number of electrons in the discharge cavity of the ECR ion thruster, so that the electrons collide with neutral gas more, the plasma density is increased, and the ECR ion thruster is easy to ignite.
Description
Technical Field
The invention belongs to the field of plasma thrusters, and particularly relates to an ignition device of a miniature electron cyclotron resonance ion thruster.
Background
In recent years, with the continuous development of deep space exploration, space science research and small commercial satellites, the requirements for a high-precision and large-range thrust adjustable micro-Newton thruster are more and more increased, and for a main propulsion system of the micro-satellite, an attitude control task for executing precise orbit control of various satellites and needing a quick start and close process and the like, a micro electron cyclotron resonance ion thruster (ECR ion thruster for short) is distinguished by the characteristics of higher specific impulse, no cathode ablation, capability of generating plasma under low flow and low microwave power, long service life and the like. However, in practical operation, the ECR ion thruster is difficult to ignite, particularly in the case of low flow and low microwave power, the analysis is that the ECR ion thruster is difficult to ignite because of the low density of generated plasma due to the few 'seed' electrons and neutral gas. The ignition starting process is the first step of the on-orbit operation of the thruster and is also the most critical step, and the problem of reliable stability of the ignition of the ECR ion thruster is solved, so that the ignition starting process is of great importance to space tasks.
Disclosure of Invention
In view of this, the present invention is directed to provide an ignition device for a micro electron cyclotron resonance ion thruster, which increases the number of electrons in a discharge cavity of an ECR ion thruster, so that the electrons collide more with a neutral gas under a specific magnetic field, and the plasma density is increased, thereby facilitating ignition of the ECR ion thruster.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a miniature electron cyclotron resonance ion thruster ignition device comprises a cylindrical discharge cavity, a magnetic yoke, an antenna, a radioactive sheet, a shielding ring, a screen grid and an accelerating grid, wherein the magnetic yoke is positioned at the bottom of the cylindrical discharge cavity, the screen grid and the accelerating grid are sequentially fixed at the top of the cylindrical discharge cavity, an inner magnetic ring and an outer magnetic ring are arranged in the magnetic yoke, the bottom of the magnetic yoke extends out of an air guide pipe, gas enters the magnetic yoke through the air guide pipe and then uniformly enters the cylindrical discharge cavity through a small hole in the magnetic yoke, the center of the magnetic yoke is connected with a waveguide, the antenna is screwed at one end of the waveguide close to the screen grid and extends out of the inner magnetic ring, the other end of the waveguide is connected with a microwave power supply, and microwaves are fed into the antenna through the;
two shielding rings are arranged in parallel on the inner wall surface of the cylindrical discharge cavity between the antenna and the screen grid, a gap is formed between the two shielding rings, the two shielding rings are coaxially arranged with the cylindrical discharge cavity, and a radioactive sheet is placed in the gap between the two shielding rings; and an insulating layer is arranged between the screen grid and the accelerating grid.
Further, the radioactive thin slice is of a ring-shaped structure.
Furthermore, the internal diameter of cylindrical discharge cavity is 20mm, and the external diameter is 22mm, and the height is 11mm, and the material is stainless steel.
Furthermore, a shielding ring is spot-welded at the position of 0.5mm-1mm away from the end face of the antenna on the inner wall surface of the cylindrical discharge cavity, the width of a gap between the two shielding rings is 2mm, the inner diameter of each shielding ring is 18mm, the outer diameter of each shielding ring is 20mm, the width of each shielding ring is 0.5mm, and the materials are all aluminum; the radioactive thin slice with the outer diameter of 20mm, the thickness of 0.1mm and the width of 2mm is placed at the gap between the two shielding rings, a gap is arranged between the shielding ring far away from the antenna and the screen grid, and the width of the gap is 1 mm.
Further, the magnetic yoke is in interference fit with the cylindrical discharge cavity.
Further, the inner magnetic ring and the outer magnetic ring are both permanent magnets and are made of samarium cobalt.
Furthermore, the magnet yoke is made of soft iron, and 12 small holes with the diameter of 1mm are uniformly distributed in the ring direction between the double-ring magnets on the magnet yoke.
Furthermore, the screen grid and the accelerating grid form an ion optical system, the screen grid and the accelerating grid are identical in structure, are both disc-shaped structures with the diameter of 30mm and the thickness of 0.5mm and are made of stainless steel, central hole regions with the diameter of 20mm are arranged on the screen grid and the accelerating grid, a plurality of small holes are uniformly distributed in the central hole regions, and the plurality of small holes formed in the central hole regions on the screen grid are different from the plurality of small holes formed in the central hole regions on the accelerating grid in pore diameter, but are arranged in a one-to-one correspondence manner.
Further, the insulating layer is an annular ceramic gasket, has a thickness of 0.25mm, and is coaxially arranged with the screen grid and the accelerating grid.
Furthermore, the accelerating grid, the insulating layer, the screen grid and the discharging cavity are all connected through bolts, and each threaded hole for bolt connection is a ceramic threaded hole.
Compared with the prior art, the ignition device of the micro electron cyclotron resonance ion thruster has the following advantages:
the invention applies the radioactive isotope technology to the field of plasma propulsion, and provides a stable and reliable ignition device of a miniature electron cyclotron resonance ion thruster.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural diagram of an ignition device of a micro electron cyclotron resonance ion thruster according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a micro ECR ion thruster ignition device with a screen, an acceleration grid and an insulating layer removed according to the present invention;
fig. 3 is a partial enlarged view of the radioactive sheet and the shielding ring.
Description of reference numerals:
1-discharge chamber, 2-magnetic yoke, 3-inner magnetic ring, 4-outer magnetic ring, 5-antenna, 6-gas guide tube, 7-shielding ring, 8-radioactive sheet, 9-shielding grid, 10-accelerating grid and 11-insulating layer.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1-3, a micro electron cyclotron resonance ion thruster ignition device comprises a cylindrical discharge cavity 1, a magnetic yoke 2, an antenna 5, a radioactive sheet 8, a shielding ring 7, a screen 9 and an accelerating grid 10, wherein the magnetic yoke 2 is positioned at the bottom of the cylindrical discharge cavity 1, the screen 9 and the accelerating grid 10 are sequentially fixed at the top of the cylindrical discharge cavity 1, an inner magnetic ring 3 and an outer magnetic ring 4 are arranged inside the magnetic yoke 2 to generate a specific magnetic field, a gas guide tube 6 extends out from the bottom of the magnetic yoke 2, gas enters a gas homogenizing cavity inside the magnetic yoke 2 through the gas guide tube 6 and then uniformly enters the cylindrical discharge cavity 1 through a small hole on the magnetic yoke 2, the center of the magnetic yoke 2 is connected with a waveguide, the antenna 5 is screwed at one end of the waveguide close to the screen 9, the antenna 5 extends out of the inner magnetic ring 3, and the other end of the waveguide is connected with a microwave power supply, the microwave is fed into the antenna 5 through the waveguide to generate electromagnetic waves;
two shielding rings 7 are arranged on the inner wall surface of the cylindrical discharge cavity 1 between the antenna 5 and the screen 9 in parallel, a gap is arranged between the two shielding rings 7, the two shielding rings 7 are coaxially arranged with the cylindrical discharge cavity 1, and a radioactive sheet 8 is arranged in the gap between the two shielding rings 7.
A radioactive thin slice 8 is arranged between the two shielding rings 7, electrons generated by decay move under a specific magnetic field, and when the electron movement cyclotron frequency is equal to the frequency of an external microwave, resonance is generated, and the electrons are accelerated and collided and ionized with neutral gas. Two shielding rings 7 are spot-welded on the inner wall surface of the cylindrical discharge cavity 1, so as to prevent beta rays generated by the radioactive thin sheet 8 from corroding other elements in the thruster and fix the radioactive thin sheet 8.
An insulating layer 11 is arranged between the screen 9 and the accelerating grid 10, the screen 9 is connected with positive high voltage, the accelerating grid 10 is connected with negative voltage, and the screen is generally connected with positive high voltage as follows: 1kV to 1.5kV, the accelerating grid is connected with negative voltage, generally-300V, and the potential difference formed between the screen grid and the accelerating grid on one hand draws out ions in plasma in the discharging cavity and accelerates to spray out to generate thrust; on the other hand, the electron in the discharge cavity can be prevented from overflowing and the short circuit caused by the fact that the plume and the electrons enter the discharge chamber can be avoided.
The radioactive foil 8 is of a ring-shaped configuration. The inner diameter of the cylindrical discharge cavity 1 is 20mm, the outer diameter is 22mm, the height is 11mm, and the material is stainless steel. Spot-welding a shielding ring 7 at a position of 0.5mm-1mm from the end face of the antenna 5 on the inner wall surface of the cylindrical discharge cavity 1, wherein the width of a gap between the two shielding rings 7 is 2mm, the inner diameter of each shielding ring 7 is 18mm, the outer diameter is 20mm, the width is 0.5mm, and the materials are all aluminum; the radioactive thin slice 8 with the outer diameter of 20mm, the thickness of 0.1mm and the width of 2mm is arranged at the gap between the two shielding rings 7, a gap is arranged between the shielding ring far away from the antenna 5 and the screen grid 9, the width of the gap is 1mm, namely the inner end face of the screen grid 9 is 1.5mm away from the annular radioactive thin slice 8. By arranging the radioactive thin slice 8 to be as close to the antenna 5 as possible, electrons generated by decay of the radioactive thin slice 8 can participate in the movement of a specific magnetic field more, so that the electrons collide with neutral gas for ionization, and the generated ions are ejected at high speed; by arranging the radioactive thin sheet 8 and the screen 9 to have a certain distance, a buffering space is provided for electron ionization, more electron ionization is completed, and more ions are generated to ensure that the ion thruster is easy to ignite.
The magnetic yoke 2 is in interference fit with the cylindrical discharge cavity 1. The magnetic ring 3 and the outer magnetic ring 4 are both permanent magnets and are made of samarium cobalt. The magnetic yoke 2 is made of soft iron, and 12 small holes with the diameter of 1mm are uniformly distributed in the annular direction between the double-ring magnets on the magnetic yoke 2.
The insulating layer 11 is an annular ceramic gasket, the thickness of the insulating layer is 0.25mm, the insulating layer and the screen grid 9 and the accelerating grid 10 are coaxially arranged, the ion optical system is prevented from being broken down due to the insulating layer 11, and the normal operation of the thruster is guaranteed.
The accelerating grid 10, the insulating layer 11, the screen grid 9 and the cylindrical discharge cavity 1 are all connected through bolts, and each threaded hole for bolt connection is a ceramic threaded hole.
The working principle of the invention is as follows:
microwave is fed into a cylindrical discharge cavity 1 through an antenna 5, electrons generated by decay of a radioactive sheet 8 do rotary motion along a specific magnetic field generated by an inner magnetic pole 3 and an outer magnetic pole 4, when the input microwave frequency is equal to the electronic rotary frequency, the microwave resonates with the electrons in the magnetic field, the electrons are accelerated and collide with neutral gas for ionization, and the generated ions are ejected at high speed under the action of potential difference of positive high voltage connected to a screen grid 9 and negative voltage connected to an accelerating grid 10. The application provides be applied to the electric propulsion field with radionuclide decay, increased the electron number in the ECR ion thruster discharge cavity, make it collide with neutral gas more under specific magnetic field, increased plasma density to it is easy to make ECR ion thruster ignition, this provides reliable and stable solution for the implementation of space task.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A miniature electron cyclotron resonance ion thruster ignition device is characterized in that: comprises a cylindrical discharge cavity (1), a magnetic yoke (2), an antenna (5), a radioactive sheet (8), a shielding ring (7), a screen grid (9) and an accelerating grid (10), wherein the magnetic yoke (2) is positioned at the bottom of the cylindrical discharge cavity (1), the screen grid (9) and the accelerating grid (10) are sequentially fixed at the top of the cylindrical discharge cavity (1), an inner magnetic ring (3) and an outer magnetic ring (4) are arranged inside the magnetic yoke (2), an air duct (6) extends out of the bottom of the magnetic yoke (2), gas enters the magnetic yoke (2) through the air duct (6) and then uniformly enters the cylindrical discharge cavity (1) through small holes in the magnetic yoke (2), the center of the magnetic yoke (2) is connected with a waveguide, the antenna (5) is screwed at one end of the waveguide close to the screen grid (9), the antenna (5) extends out of the inner magnetic ring (3), and the other end of the waveguide is connected with a microwave power supply, the microwave is fed into the antenna (5) through the waveguide to generate electromagnetic waves;
two shielding rings (7) are arranged in parallel on the inner wall surface of the cylindrical discharge cavity (1) between the antenna (5) and the screen grid (9), a gap is arranged between the two shielding rings (7), the two shielding rings (7) are coaxially arranged with the cylindrical discharge cavity (1), and a radioactive sheet (8) is placed in the gap between the two shielding rings (7); an insulating layer (11) is arranged between the screen grid (9) and the accelerating grid (10).
2. The ignition device of a micro electron cyclotron resonance ion thruster according to claim 1, wherein: the radioactive thin slice (8) is of a ring-shaped structure.
3. The ignition device of a micro electron cyclotron resonance ion thruster according to claim 2, wherein: the inner diameter of the cylindrical discharge cavity (1) is 20mm, the outer diameter is 22mm, the height is 11mm, and the material is stainless steel.
4. The ignition device of micro electron cyclotron resonance ion thruster of claim 3, wherein: spot-welding a shielding ring (7) at a position of 0.5-1 mm away from the end face of the antenna (5) on the inner wall surface of the cylindrical discharge cavity (1), wherein the width of a gap between the two shielding rings (7) is 2mm, the inner diameter of each shielding ring (7) is 18mm, the outer diameter is 20mm, the width is 0.5mm, and the shielding rings are made of aluminum; a radioactive thin sheet (8) with the outer diameter of 20mm, the thickness of 0.1mm and the width of 2mm is placed at the gap between the two shielding rings (7), a gap is arranged between the shielding ring far away from the antenna (5) and the screen (9), and the width of the gap is 1 mm.
5. The ignition device of a micro electron cyclotron resonance ion thruster according to claim 1, wherein: the magnetic yoke (2) is in interference fit with the cylindrical discharge cavity (1).
6. The ignition device of a micro electron cyclotron resonance ion thruster according to claim 1, wherein: the inner magnetic ring (3) and the outer magnetic ring (4) are both permanent magnets and are made of samarium cobalt.
7. The ignition device of micro electron cyclotron resonance ion thruster of claim 6, wherein: the magnetic yoke (2) is made of soft iron, and 12 small holes with the diameter of 1mm are uniformly distributed in the annular direction between the double-ring magnets on the magnetic yoke (2).
8. The ignition device of a micro electron cyclotron resonance ion thruster according to any one of claims 3 to 7, wherein: the screen grid (9) and the acceleration grid (10) form an ion optical system, the screen grid (9) and the acceleration grid (10) are identical in structure, are of disc-shaped structures with the diameters of 30mm and the thicknesses of 0.5mm and are made of stainless steel, central hole regions with the diameters of 20mm are arranged on the screen grid (9) and the acceleration grid (10), a plurality of small holes are uniformly distributed in the central hole regions, and the apertures of the small holes formed in the central hole regions on the screen grid (9) are different from those of the small holes formed in the central hole regions on the acceleration grid (10) and are arranged in a one-to-one correspondence manner.
9. The ignition device of a micro electron cyclotron resonance ion thruster according to any one of claims 1 to 7, wherein: the insulating layer (11) is an annular ceramic gasket, has the thickness of 0.25mm, and is coaxially arranged with the screen grid (9) and the accelerating grid (10).
10. The ignition device of a micro electron cyclotron resonance ion thruster of claim 9, wherein: the accelerating grid (10), the insulating layer (11), the screen grid (9) and the cylindrical discharge cavity (1) are all connected through bolts, and each threaded hole for connecting the bolts is a ceramic threaded hole.
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| CN202010091498.2A CN111140454B (en) | 2020-02-13 | 2020-02-13 | Ignition device of miniature electron cyclotron resonance ion thruster |
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| CN111140454B true CN111140454B (en) | 2021-05-04 |
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| CN112555113B (en) * | 2020-11-06 | 2022-06-14 | 兰州空间技术物理研究所 | Integrated insulation structure of grid component of ion thruster |
| CN112638023A (en) * | 2020-12-11 | 2021-04-09 | 中国人民解放军战略支援部队航天工程大学 | Coaxial double-coil radio-frequency driving gas discharge device |
| CN113279930B (en) * | 2021-06-30 | 2022-07-12 | 哈尔滨工业大学 | Grid component assembly structure and assembly method of micro ion thruster |
| CN113236516B (en) * | 2021-06-30 | 2022-03-04 | 哈尔滨工业大学 | Structure for preventing deposition in discharge chamber of micro ion thruster |
| CN114562436A (en) * | 2022-02-28 | 2022-05-31 | 北京航空航天大学 | Sputtering pollution resistant insulation enhanced grid system |
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