CN112160884A - Integrated radio frequency ion propulsion device - Google Patents
Integrated radio frequency ion propulsion device Download PDFInfo
- Publication number
- CN112160884A CN112160884A CN202011012882.5A CN202011012882A CN112160884A CN 112160884 A CN112160884 A CN 112160884A CN 202011012882 A CN202011012882 A CN 202011012882A CN 112160884 A CN112160884 A CN 112160884A
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- Prior art keywords
- radio frequency
- ionization chamber
- grid
- neutralizer
- propulsion device
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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
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
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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
- F03H1/0018—Arrangements or adaptations of power supply systems
-
- 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
- F03H1/0025—Neutralisers, i.e. means for keeping electrical neutrality
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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 invention provides an integrated radio frequency ion propulsion device, which comprises: the device comprises a radio frequency power supply, a matcher, an integrated radio frequency antenna, a thruster ionization chamber, a neutralizer ionization chamber, an ion collector and a grid system, wherein the radio frequency power supply is connected with the matcher to form a radio frequency power source for providing energy for ionization of a working medium; the integrated radio frequency antenna surrounds the outside of the ionization chamber of the thruster and the ionization chamber of the neutralizer and is connected with a radio frequency power source, the grid system is provided with a screen grid and an accelerating grid from the outlet of the ionization chamber to the outside in sequence, and grid holes are formed in the screen grid and the accelerating grid; the screen grid is used for leading out positive ions, and the accelerating grid is used for accelerating the positive ions. The invention not only adopts the radio frequency neutralizer to replace the hollow cathode, prolongs the service life of the propulsion device, but also carries out integrated design on the thruster and the neutralizer antenna, reduces the power supply and saves the space.
Description
Technical Field
The invention relates to the technical field of propulsion of spacecraft, in particular to an integrated radio frequency ion propulsion device.
Background
The space propulsion technology is a key technology in the field of aerospace and provides power for an aircraft to complete space tasks. Compared with chemical propulsion, the electric propulsion has the advantages of higher specific impulse, long service life, compact structure and the like, is widely concerned, and has great potential as a satellite propulsion device in near-field exploration and deep space exploration tasks.
Among a plurality of electric thrusters, the radio frequency ion thruster is different from other types of thrusters in that an ionization chamber does not have any device, a permanent magnet or an electromagnetic coil is not arranged outside the ionization chamber, only a radio frequency coil is arranged, and the radio frequency ion thruster is simple in structure and small in occupied space. Meanwhile, the radio frequency source has the characteristics of low power consumption, high plasma density and the like, and has unique advantages as an ion source. Therefore, the radio frequency ion thruster has great research and application values.
The grid system for extracting and accelerating ions is arranged at the tail end of the discharge chamber of the radio frequency ion thruster, so that a neutralizer is required to be configured to emit electrons to neutralize ions in a plume region. At present, hollow cathodes are mostly used as neutralizers. However, the service life of the hollow cathode restricts the service life of the whole propulsion system, and the working medium is limited to inert gas, usually xenon, krypton and the like, which is low in natural content and expensive in price, and needs to be provided with a pressure reducing valve, a gas cylinder and other devices, so that the launching cost is increased, and the launching risk is increased.
Patent document CN104595140A discloses a stepped-gate rf ion propulsion device. The device of the invention comprises: the device comprises a radio frequency antenna, an ionization chamber, a screen grid, an accelerating grid and a neutralizer; the radio frequency antenna is surrounded outside the ionization chamber for arouse plasma, the ionization chamber provides plasma takes place the region, and the restriction plasma is in the region, the one end of ionization chamber is used for inputing working medium gas, the screen grid accelerate the grid with the neutralizer is located the other end of ionization chamber, the screen grid is used for drawing positive ions, it is used for accelerating to accelerate the grid the positive ions, and it is the notch cuttype structure to accelerate the grid cross-section, the neutralizer is used for the transmission neutralization the electron of positive ions. The patent still leaves room for improvement in structure and performance.
Disclosure of Invention
In view of the shortcomings of the prior art, it is an object of the present invention to provide an integrated rf ion propulsion device.
According to the invention, the integrated radio frequency ion propulsion device comprises: the device comprises a radio frequency power supply, a matcher, an integrated radio frequency antenna, a thruster ionization chamber, a neutralizer ionization chamber, an ion collector and a grid system; the radio frequency power supply is connected with the matcher to form a radio frequency power source which provides energy for ionization of the working medium; the integrated radio frequency antenna surrounds the thruster ionization chamber and the neutralizer ionization chamber, is connected with a radio frequency power source and is used for exciting a working medium to generate plasma; the tail end of the ionization chamber of the thruster is provided with a grid system; the ion collector is arranged on the axis of the ionization chamber of the neutralizer and used for collecting ions, and the ion collector is provided with a small vent hole.
Preferably, the gate system comprises: screen grids and acceleration grids; the screen grid and the accelerating grid are both provided with grid holes; the screen grid can be used for extracting positive ions, and the accelerating grid can be used for accelerating the positive ions. The grid system is provided with a screen grid and an accelerating grid from the outlet of the ionization chamber to the outside in sequence.
Preferably, the integral radio frequency antenna adopts any one of the following metals:
-copper;
-silver.
The integrated radio frequency antenna is made of metal with strong conductive capability, such as copper, silver and the like.
Preferably, the thruster ionization chamber is made of any one of the following materials:
-a ceramic;
-quartz;
preferably, the neutralizer ionization chamber is made of any one of the following materials:
-a ceramic;
-quartz;
the thruster ionization chamber and the neutralizer ionization chamber are made of high-temperature-resistant insulating materials such as ceramics, quartz and the like;
preferably, the ion collector is cylindrical or cylindrical.
Preferably, the ion collector is made of graphite.
Preferably, the screen and the accelerator grid in the grid system are made of a molybdenum or carbon based composite material.
Preferably, the front ends of the thruster ionization chamber and the neutralizer ionization chamber are provided with small vent holes;
the neutralizer ionization chamber has an electron emitting aperture at the end for neutralizing the thruster plume.
Compared with the prior art, the invention has the following beneficial effects:
1. the radio frequency neutralizer is adopted as an electron source to replace the hollow cathode, heating before the hollow cathode is started is avoided, the service life is short, and the selection of working media is limited by the constraints of inert gases and the like;
2. the radio frequency thruster antenna and the radio frequency neutralizer antenna are integrally designed, and radio frequency energy distribution is controlled through the number of turns of the antennas, so that the requirements of ionization energy of the thruster and the neutralizer can be met, the number of radio frequency sources is reduced, and the total load of the propulsion device is reduced;
3. the invention not only can adopt inert gases such as xenon, krypton and the like as working media, but also can adopt iodine which is stored in solid and can be sublimated into steam when being heated. When iodine is used as a working medium, devices such as a high-pressure gas cylinder, a pressure reducing valve and the like do not need to be configured, so that the mass of the propulsion device is reduced, and the launching cost is reduced;
4. the invention can meet the space task requirements of spacecrafts such as future satellite platforms, space stations, deep space detectors and the like, and has simple structure and feasible design principle and scheme.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic overall view of an integrated RF ion propulsion system according to the present invention;
FIG. 2 is a schematic diagram of a grid plate of the integrated RF ion propulsion device of the present invention;
fig. 3 is a schematic view of an ion accumulator of the integrated rf ion propulsion device of the present invention.
In the figure, 101 a thruster ionization chamber, 102 an integrated radio frequency antenna, 103 a grid system, 104 an ion collector, 105 a neutralizer ionization chamber, 106 a matcher, 107 a radio frequency power supply and 108 a radio frequency neutralizer are arranged.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Fig. 1 is a general schematic view of an integrated rf ion propulsion device according to the present invention, as shown in fig. 1, the device of the present embodiment includes:
an rf power supply 107, a matcher 106, an integral rf antenna 102, a thruster ionization chamber 101, a neutralizer ionization chamber 105, an ion collector 104, and a grid system 103. Wherein, the neutralizer ionization chamber 105, the ion collector 104 and a part of the integrated radio frequency antenna 102 jointly form the radio frequency neutralizer 108.
The radio frequency power supply 107 is connected with the matcher 106 to form a radio frequency power source for providing energy for ionization of the working medium; the integrated radio frequency antenna 102 surrounds the thruster ionization chamber 101 and the neutralizer ionization chamber 105, is connected with a radio frequency power source, and is used for exciting a working medium to generate plasma; the front ends of the thruster ionization chamber 101 and the neutralizer ionization chamber 105 are provided with small vent holes; the tail end of the thruster ionization chamber 101 is provided with a grid system, and the tail end of the neutralizer ionization chamber 105 is provided with an electron emission small hole for neutralizing the thruster plume; the ion collector 104 is positioned on the axis of the neutralizer ionization chamber 105 and is used for collecting ions, and a small vent hole is formed in the ion collector; the grid system 103 is sequentially provided with a screen grid and an accelerating grid from an outlet of the ionization chamber to the outside, and grid holes are formed in the screen grid and the accelerating grid; the screen grid is used for leading out positive ions, and the accelerating grid is used for accelerating the positive ions.
Further, the integrated rf antenna 102 is made of a metal material with high conductivity, such as copper, silver, etc.
Further, the thruster ionization chamber 101 and the neutralizer ionization chamber 105 are made of high temperature resistant insulating materials, such as ceramics, quartz, etc.
Further, the ion collector 104 has a cylindrical or cylindrical shape and is made of graphite.
Further, the screen and the accelerating grid in the grid system 103 are made of molybdenum or carbon-based composite material.
Fig. 2 is a schematic diagram of a gate plate of the integrated radio frequency ion propulsion device, as shown in fig. 2, the gate holes are arranged in order, and the materials and shapes of the screen gate plate and the acceleration gate plate are completely the same.
Fig. 3 is a schematic view of an ion collector of the integrated rf ion propulsion device of the present invention, and as shown in fig. 3, the cylindrical or cylindrical wall of the collector is provided with a small vent hole.
The invention works in the following way: the 13.56MHz radio frequency power supply 107 loads energy to the integrated radio frequency antenna 102 through the matcher 106, firstly, working medium gas is introduced into the neutralizer discharge chamber 105, and radio frequency energy is fed into the working medium to enable the working medium to be ionized into plasma. A dc bias voltage is applied between the screen and the ion collector 104, the screen connected to the positive pole of the dc power supply acts as a touch pole of the rf neutralizer 108 to extract electrons, and the ion collector 104 connected to the negative pole of the dc power supply attracts ions. Then, working medium gas is introduced into the thruster discharge chamber 101, radio frequency energy is fed into the working medium to ionize the working medium into plasma, negative voltage is applied to the accelerating grid at the moment, the voltage of the screen grid is adjusted to a proper value, ions in the thruster discharge chamber 101 are led out by the grid system 103 and accelerated to be sprayed out to generate thrust, and ions in the final plume region are neutralized into neutral particles by electrons emitted by the radio frequency neutralizer 108.
In this embodiment, the coil inner diameters of the integrated rf antennas 102 wound outside the thruster discharge chamber 101 and the neutralizer discharge chamber 105 are the same, and the rf energy ratio is linearly distributed according to the turn ratio, thereby realizing the integrated design of the antennas.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
An integrated radio frequency ion propulsion device. The invention comprises the following steps: the device comprises a radio frequency power supply, a matcher, an integrated radio frequency antenna, a thruster ionization chamber, a neutralizer ionization chamber, an ion collector and a grid system, wherein the radio frequency power supply is connected with the matcher to form a radio frequency power source for providing energy for ionization of a working medium; the integrated radio frequency antenna surrounds the thruster ionization chamber and the neutralizer ionization chamber, is connected with a radio frequency power source and is used for exciting a working medium to generate plasma; the front ends of the thruster ionization chamber and the neutralizer ionization chamber are provided with small vent holes; the tail end of the ionization chamber of the thruster is provided with a grid system, and the tail end of the ionization chamber of the neutralizer is provided with an electron emission small hole for neutralizing the plume of the thruster; the ion collector is positioned on the axis of the ionization chamber of the neutralizer and is used for collecting ions, and a small vent hole is formed in the ion collector; the grid system is provided with a screen grid and an accelerating grid from the outlet of the ionization chamber to the outside in sequence, and grid holes are formed in the screen grid and the accelerating grid; the screen grid is used for leading out positive ions, and the accelerating grid is used for accelerating the positive ions. The invention not only adopts the radio frequency neutralizer to replace the hollow cathode, prolongs the service life of the propulsion device, but also carries out integrated design on the thruster and the neutralizer antenna, reduces the power supply and saves the space.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (9)
1. An integrated radio frequency ion propulsion device, comprising: the device comprises a radio frequency power supply, a matcher, an integrated radio frequency antenna, a thruster ionization chamber, a neutralizer ionization chamber, an ion collector and a grid system;
the radio frequency power supply is connected with the matcher to form a radio frequency power source;
the integrated radio frequency antenna surrounds the outside of the thruster ionization chamber and the neutralizer ionization chamber and is connected with a radio frequency power source;
the tail end of the ionization chamber of the thruster is provided with a grid system;
the ion collector is arranged on the axis of the ionization chamber of the neutralizer;
the ion collector is provided with a small vent hole.
2. The integrated radio frequency ion propulsion device according to claim 1, wherein the grid system comprises: screen grids and acceleration grids;
the screen grid and the accelerating grid are both provided with grid holes;
the screen grid can be used for extracting positive ions, and the accelerating grid can be used for accelerating the positive ions.
3. The integrated rf ion propulsion device according to claim 1, wherein the integrated rf antenna is made of any one of the following metals:
-copper;
-silver.
4. The integrated radio frequency ion propulsion device according to claim 1, wherein the thruster ionization chamber is made of any one of the following materials:
-a ceramic;
-quartz.
5. The integrated radio frequency ion propulsion device according to claim 1, wherein the neutralizer ionization chamber is made of any one of the following materials:
-a ceramic;
-quartz.
6. The integrated radio frequency ion propulsion device according to claim 1, wherein the ion collector is cylindrical or cylindric.
7. The integrated radio frequency ion propulsion device according to claim 6, wherein the ion collector is made of graphite.
8. The integrated radio frequency ion propulsion device according to claim 2, wherein the screen and acceleration grid in the grid system are made of molybdenum or carbon-based composite material.
9. The integrated radio frequency ion propulsion device according to claim 1, characterized in that the front ends of the thruster ionization chamber and the neutralizer ionization chamber are provided with small vent holes;
the neutralizer ionization chamber has an electron emitting aperture at its end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011012882.5A CN112160884A (en) | 2020-09-24 | 2020-09-24 | Integrated radio frequency ion propulsion device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011012882.5A CN112160884A (en) | 2020-09-24 | 2020-09-24 | Integrated radio frequency ion propulsion device |
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| CN202011012882.5A Pending CN112160884A (en) | 2020-09-24 | 2020-09-24 | Integrated radio frequency ion propulsion device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| CN113404658A (en) * | 2021-06-30 | 2021-09-17 | 哈尔滨工业大学 | Self-neutralizing radio frequency ion thruster |
| CN114320799A (en) * | 2021-12-06 | 2022-04-12 | 兰州空间技术物理研究所 | Solid working medium radio frequency ion electric propulsion system |
| CN114352493A (en) * | 2021-12-06 | 2022-04-15 | 兰州空间技术物理研究所 | Integrated gas distribution and ion collection assembly for radio-frequency cathode |
| CN114837910A (en) * | 2022-06-09 | 2022-08-02 | 兰州空间技术物理研究所 | Integrated high-efficiency ionization ultrahigh specific impulse radio frequency ion thruster discharge structure |
| WO2023222626A1 (en) * | 2022-05-16 | 2023-11-23 | Leibniz-Institut für Oberflächenmodifizierung e.V. | Device and method for producing ions using a plasma |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| CN113404658A (en) * | 2021-06-30 | 2021-09-17 | 哈尔滨工业大学 | Self-neutralizing radio frequency ion thruster |
| CN113404658B (en) * | 2021-06-30 | 2022-03-18 | 哈尔滨工业大学 | Self-neutralizing radio frequency ion thruster |
| CN113357109B (en) * | 2021-06-30 | 2022-07-15 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| CN114320799A (en) * | 2021-12-06 | 2022-04-12 | 兰州空间技术物理研究所 | Solid working medium radio frequency ion electric propulsion system |
| CN114352493A (en) * | 2021-12-06 | 2022-04-15 | 兰州空间技术物理研究所 | Integrated gas distribution and ion collection assembly for radio-frequency cathode |
| WO2023222626A1 (en) * | 2022-05-16 | 2023-11-23 | Leibniz-Institut für Oberflächenmodifizierung e.V. | Device and method for producing ions using a plasma |
| CN114837910A (en) * | 2022-06-09 | 2022-08-02 | 兰州空间技术物理研究所 | Integrated high-efficiency ionization ultrahigh specific impulse radio frequency ion thruster discharge structure |
| CN114837910B (en) * | 2022-06-09 | 2023-09-29 | 兰州空间技术物理研究所 | Integrated high-efficiency ionization ultrahigh specific impulse radio frequency ion thruster discharging structure |
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Application publication date: 20210101 |