CN116771622A - Radio frequency ion thruster of milli-bovine magnitude - Google Patents
Radio frequency ion thruster of milli-bovine magnitude Download PDFInfo
- Publication number
- CN116771622A CN116771622A CN202211616789.4A CN202211616789A CN116771622A CN 116771622 A CN116771622 A CN 116771622A CN 202211616789 A CN202211616789 A CN 202211616789A CN 116771622 A CN116771622 A CN 116771622A
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- Prior art keywords
- grid
- radio frequency
- gas
- inlet pipe
- milli
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- 239000000919 ceramic Substances 0.000 claims abstract description 47
- 239000012212 insulator Substances 0.000 claims abstract description 13
- 230000001133 acceleration Effects 0.000 claims description 10
- 238000007789 sealing Methods 0.000 claims description 6
- 150000002500 ions Chemical class 0.000 abstract description 33
- 238000009434 installation Methods 0.000 abstract description 3
- 230000017525 heat dissipation Effects 0.000 abstract 1
- 238000000605 extraction Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 238000009413 insulation Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 108091092878 Microsatellite Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010884 ion-beam technique Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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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
- F03H1/0081—Electromagnetic plasma thrusters
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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
-
- 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
- F03H1/0012—Means for supplying the propellant
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)
- Electromagnetism (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a milli-bovine-magnitude radio frequency ion thruster, which comprises a ceramic base, wherein an electromagnetic shielding layer is arranged on the outer layer of the ceramic base, an accelerating grid is fixed at the upper end of the accelerating grid, a grid insulating ceramic block is arranged at the upper end of the accelerating grid, a screen grid for accelerating ions is fixed at the upper end of the grid insulating ceramic block, the screen grid faces a discharge chamber, a radio frequency coil is enclosed on the outer layer of the discharge chamber and is fixedly supported by a coil bracket, a gas distributor is arranged at the upper end of the discharge chamber, a gas insulator integrally welded with the gas distributor is arranged in the gas distributor, an air inlet pipe is arranged at the upper end of the gas distributor, and a flange for integrally fixing and installing is arranged at the upper end of the air inlet pipe. The invention ensures that the gas in the discharge chamber is uniformly distributed through the gas distributor, and has the characteristics of reasonable structure, simple and convenient installation, compact whole structure of the product, good heat dissipation, high performance and long service life.
Description
Technical Field
The invention relates to the field of aerospace thrusters, in particular to a milli-bovine-magnitude radio frequency ion thruster.
Background
The frequent activities in the space field of human beings increase the demands on the aerospace propulsion technology, and the electric propulsion gradually draws attention and importance of the aerospace world due to the advantages of high specific impulse, long service life, compact structure and the like. With the development of space exploration requirements and commercial aerospace, the technical requirements of electric propulsion systems are gradually changed into aspects of light weight, long service life, high total impact and the like. For microsatellites such as cubic satellites and plate satellites, the requirements on the quality and the volume of a propulsion system are more severe.
Although the main flow Hall thruster in the market has more mature engineering application experience and on-orbit verification, the main flow Hall thruster has no obvious performance advantage in the field of miniaturized electric propulsion, and even has the problems of low efficiency and unstable work after being miniaturized due to the complicated magnetic circuit limitation, so most research institutions at home and abroad are searching for a new electric propulsion technology to meet the market demand.
Chinese patent application with publication number CN114837910a, entitled "an integrated high-efficiency ionization ultra-high specific impulse radio frequency ion thruster discharge structure" discloses a radio frequency ion thruster, which comprises the common components of a general radio frequency ion thruster: in the patent application, the gas working medium pipeline is a long pipe which penetrates into the discharge chamber, and a plurality of air outlets are formed in the side wall and the top wall of the gas working medium pipeline. According to the application document, the structure can uniformly distribute bottom working medium gas, strengthen gas ionization and is convenient to clean, but according to the inventor, the technical measures of opening holes in the pipe wall and the top do not achieve the technical effect of uniformly distributing gas.
In the invention, an auxiliary ionization chamber is added, a main ionization chamber is connected with an ion extraction system, the auxiliary ionization chamber is connected with an electron extraction system, the main ionization chamber and the auxiliary ionization chamber share a set of radio frequency power source and impedance matching network, the electron extraction system and the ion extraction system share a direct current high voltage source, and the electrons extracted by the electron extraction system neutralize ions extracted by the ion extraction system. The inventor of the invention emphasizes that the structure simplifies the structure of the radio frequency ion thruster and achieves beneficial effects. However, according to the inventor, the auxiliary ionization chamber is added, so that the volume of the radio frequency ion thruster is obviously increased, but in the spacecraft, the space is not at all precious, and in addition, the auxiliary ionization chamber is added, so that a plurality of structures and components are added, and the structure of the radio frequency ion thruster cannot be simplified.
Disclosure of Invention
In view of the above, the present invention provides a milli-bovine rf ion thruster for solving the problems in the prior art.
The invention provides a milli-bovine-magnitude radio frequency ion thruster, comprising: the device comprises a ceramic base, a shielding layer arranged outside the ceramic base, an acceleration grid fixedly arranged on the ceramic base, an insulating ceramic block arranged on the acceleration grid, a screen grid fixedly arranged on the insulating ceramic block, a coil support arranged on the base, a radio frequency coil arranged on the coil support, a gas distributor, a gas inlet pipe, a gas insulator arranged between the gas inlet pipe and the gas distributor and a sealing cover flange. The accelerating grid, the coil support and the sealing cover flange enclose a discharge chamber, the shielding layer is folded up from the edge of the base to be right-angled upwards and finally fixedly connected with the sealing cover flange to form a circular cage body, the air inlet pipe penetrates into the discharge chamber from the center of the flange and then is connected and communicated with the gas distributor, and the gas distributor is internally provided with a gas insulator. The gas distributor is of a conical structure, the top of the cone is communicated with the gas inlet pipe, the bottom of the cone is a flat plate, and through holes are uniformly distributed in the flat plate.
Preferably, the grid insulating ceramic block is installed in cooperation with the ceramic base through an opposite circular arc of the grid insulating ceramic block, the screen grid is embedded into the upper surface of the grid insulating ceramic block, and the positioning modes of the screen grid and the acceleration grid are provided by base ceramic.
Preferably, the air inlet pipe, the gas insulator, the gas distributor and the discharge chamber are of an integrated welding structure.
The invention adopts a superposition mode, so that the installation of the product is simpler and more convenient, and the integrated welding design of the air inlet pipe, the gas insulator, the gas distributor and the discharge chamber ensures that the product has better air tightness and is easier to assemble; the product has a more compact structure under the optimized layout design of insulation, positioning and the like, and is simple and convenient to install, and the gas is distributed uniformly in the discharge chamber by adopting the gas distributor, so that the product performance is stable.
The radio frequency and the number of turns of the coil will generally vary with the size of the thruster, and the smaller the thruster, the higher the frequency and the number of turns of the coil will also increase. Therefore, the radio frequency and the number of turns of the coil of the radio frequency ion thruster can be adjusted according to actual needs, so that the radio frequency ion thruster has great flexibility and meets different condition requirements.
Drawings
FIG. 1 is a cross-sectional view of a radio frequency ion thruster of the present invention on the milli-newton scale;
FIG. 2 is a block diagram of a grid system assembly of the RF ion thruster of the present invention on the milli-bovine scale;
FIG. 3 is a schematic diagram of the ion acceleration of the RF ion thruster of milli-bovine magnitude of the present invention;
fig. 4 is a schematic diagram of a three-dimensional structure of a milli-bovine-scale rf ion thruster of the present invention.
The reference numerals in the figures are respectively: 1 shielding layer, 2 ceramic base, 3 accelerating grid, 4 grid insulating ceramic block, 5 screen grid, 6 discharge chamber, 7 radio frequency coil, 8 coil support, 9 gas distributor, 10 gas insulator, 11 flange, 12 intake pipe.
Detailed Description
In order that the objects and advantages of the invention will become more apparent, the invention will be further described with reference to the following examples; it should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1, the radio frequency ion thruster of the present invention comprises a shielding layer 1, a ceramic base 2, an accelerating grid 3, a grid insulating ceramic block 4, a screen grid 5, a discharge chamber 6, a radio frequency coil 7, a coil bracket 8, a gas distributor 9, a gas insulator 10, a flange 11 and a gas inlet pipe 12, wherein the shielding layer 1 is arranged outside the ceramic base 2, folded at the edge of the ceramic base 2 in a right angle upwards, and fixedly connected with the flange 11 on the upper surface to form a basic structure of the radio frequency ion thruster, and as can be seen from fig. 4, the radio frequency ion thruster of the present invention is a circular cage; the accelerating grid 3 is fixed on the ceramic base 2, and a grid insulation ceramic block 4 for insulation between grids is arranged on the accelerating grid; a screen grid 5 for ion acceleration is fixed on the grid insulating ceramic block 4; the coil bracket 8 is arranged on the ceramic base 2; the radio frequency coil 7 is arranged on the coil bracket 8, the air inlet pipe 12 is inserted from the hole of the flange 11 and is connected with the gas insulator 10 first, and is connected and communicated with the gas distributor 9 after passing through the gas insulator 10, the gas distributor 9 is of a conical structure, the gas insulator 10 is arranged inside the gas distributor, the top of the cone is communicated with the air inlet pipe 12, the bottom of the cone is a flat plate, through holes are uniformly distributed on the flat plate, and the discharge chamber 6 is enclosed by the accelerating grid 3, the coil bracket 8 and the sealing cover flange 11. In the embodiment, the grid insulating ceramic block 4 is installed on the upper surface of the accelerating grid 3, and the screen grid 5 is embedded in the upper surface of the grid insulating ceramic block 4 through the matching installation of the opposite circular arc of the accelerating grid 3 and the ceramic base 2, so that the positioning modes of the screen grid 5 and the accelerating grid 3 are provided by the base ceramic 2; the surface of the discharge chamber 6 is provided with a spiral groove with the same pitch as the radio frequency coil 7; the inlet pipe 12, the gas insulator 10, the gas distributor 8, and the discharge chamber 6 are welded together.
As shown in fig. 2, in order to install the gate system according to the present invention, the ceramic base 2, the accelerator gate 3, the gate insulating ceramic block 4, and the screen gate 5 are installed in this order. After the acceleration grid is installed on the ceramic base, the acceleration grid is fixed through the upper holes by using screws and nuts. After the accelerating grid 3 is fixed, the grid insulating ceramic block 4 is embedded into the ceramic base 2 and is in close contact with the accelerating grid 3, the screen grid 5 is finally installed on the upper surface of the grid insulating ceramic block 4, the screen grid 5 holes and the accelerating grid 3 holes are aligned, the screen grid 5 is finally fixed through the positioning holes by using screws, and the coil support 8 is also fixed on the ceramic base 2 through screws and nuts.
In a specific use process, the radio frequency ion thruster of milli-bovine magnitude of the invention firstly energizes the radio frequency coil 7 to ionize working medium and then accelerates ions to form thrust, the acceleration process of the ions mainly occurs in a grid system part, the principle of the double grid system is shown in figure 3, and ions in a plasma sheath layer formed at the holes of the grid 5 can be led out and accelerated under the specific voltage of the grid 5, so that ion beam current is formed by focusing. The screen grid 5 accelerates ions with positive high pressure, and the acceleration grid 3 is connected with negative high pressure to prevent electrons from flowing back, so that the pushing force of radio frequency ions is generated.
Thus far, the technical solution of the present invention has been described in connection with the preferred embodiments shown in the drawings, but the scope of protection of the present invention is obviously not limited to the present specific embodiment. Equivalent modifications and substitutions for related technical features may be made by those skilled in the art without departing from the principles of the present invention, and such modifications and substitutions will be within the scope of the present invention.
Claims (5)
1. The milli-bovine magnitude radio frequency ion thruster comprises a ceramic base, a shielding layer arranged outside the ceramic base, an accelerating grid fixed on the ceramic base, a grid insulating ceramic block arranged on the accelerating grid, a screen grid fixed on the grid insulating ceramic block, a radio frequency coil, a coil bracket for fixedly supporting the radio frequency coil, a flange and an air inlet pipe, wherein the shielding layer is arranged on the outer side of the ceramic base; the radio frequency coil, the screen grid and the flange enclose a discharge chamber; the air inlet pipe penetrates through the flange to enter the discharge chamber, the coil support is fixedly arranged on the ceramic base, the shielding layer is folded at the edge of the base to be right-angle upwards, and finally the shielding layer is fixedly connected with the flange sealing cover, and the air inlet pipe is characterized in that: the radio frequency ion thruster further comprises a gas distributor, wherein the gas distributor is communicated with the gas inlet pipe, and a gas insulator is arranged in the distributor and is arranged below the flange sealing cover.
2. A milli-bovine radio frequency ion thruster in accordance with claim 1, characterized in that: the gas distributor is conical, the top end of the cone is communicated with the gas inlet pipe, the bottom of the cone is a flat plate, and through holes are uniformly distributed on the flat plate.
3. A milli-bovine rf ion thruster in accordance with claim 1, wherein: the air inlet pipe, the gas insulator, the gas distributor and the discharge chamber are integrally welded and connected.
4. A milli-bovine rf ion thruster in accordance with claim 1, wherein: the coil support is fixed in the hole of the ceramic base through a screw and a nut.
5. A milli-bovine rf ion thruster in accordance with claim 1, wherein: the grid electrode insulating ceramic block is arranged on the upper surface of the acceleration grid electrode and is matched with the ceramic base through the opposite circular arc of the grid electrode insulating ceramic block, and the screen grid electrode is embedded into the upper surface of the grid electrode insulating ceramic block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211616789.4A CN116771622A (en) | 2022-12-13 | 2022-12-13 | Radio frequency ion thruster of milli-bovine magnitude |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211616789.4A CN116771622A (en) | 2022-12-13 | 2022-12-13 | Radio frequency ion thruster of milli-bovine magnitude |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116771622A true CN116771622A (en) | 2023-09-19 |
Family
ID=87986651
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211616789.4A Pending CN116771622A (en) | 2022-12-13 | 2022-12-13 | Radio frequency ion thruster of milli-bovine magnitude |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116771622A (en) |
-
2022
- 2022-12-13 CN CN202211616789.4A patent/CN116771622A/en active Pending
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Sun Jianning Inventor after: Pan Hailin Inventor after: Liu Qi Inventor after: Yao Yan Inventor before: Sun Jianning Inventor before: Pan Hailin Inventor before: Liu Qi Inventor before: Yao Yan |
|
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Country or region after: China Address after: Room 101, 5th Floor, Building 1, No. 4 Yongjia North Road, Haidian District, Beijing, 100000 Applicant after: Beijing Xingchen Space Technology Co.,Ltd. Address before: 100000 B301, block B, building 1, courtyard 4, Yongjia North Road, Haidian District, Beijing Applicant before: Beijing Xingchen Space Technology Co.,Ltd. Country or region before: China |