CN115822904A - Microwave cathode ion thruster - Google Patents
Microwave cathode ion thruster Download PDFInfo
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- CN115822904A CN115822904A CN202211575904.8A CN202211575904A CN115822904A CN 115822904 A CN115822904 A CN 115822904A CN 202211575904 A CN202211575904 A CN 202211575904A CN 115822904 A CN115822904 A CN 115822904A
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Abstract
The application relates to the technical field of spacecraft propulsion, in particular to a microwave cathode ion thruster, which comprises an air inlet pipeline, a microwave power supply, a microwave neutralizer, a microwave cathode system, a thruster discharge chamber and a grid system, wherein: the air inlet pipeline comprises a first air inlet pipeline communicated with the microwave neutralizer, a second air inlet pipeline communicated with the microwave cathode system and a third air inlet pipeline communicated with the thruster discharge chamber; the microwave power supply is respectively connected with the microwave neutralizer and the microwave cathode system; the microwave cathode system is arranged at the input end of the thruster discharge chamber, and the grid system is arranged at the output end of the thruster discharge chamber; the microwave neutralizer is communicated with the thruster discharge chamber and is close to the output end of the thruster discharge chamber. According to the ultra-low earth orbit gas thruster, ultra-low earth orbit environment gas can be used as a working medium, the service life of the thruster is prolonged, the energy of electron flow can be improved, and the energy of original electrons can be effectively increased, so that the plasma ionization degree of a discharge chamber can be improved.
Description
Technical Field
The application relates to the technical field of spacecraft propulsion, in particular to a microwave cathode ion thruster.
Background
The air-breathing electric propulsion system uses the solar cell to provide energy, uses rarefied nitrogen, oxygen and oxygen atoms in the ultra-low earth orbit environment as working medium sources, generates thrust in the processes of ionization, accelerated ejection and the like, and uses the thrust as power for maintaining the orbit of the ultra-low earth orbit spacecraft, so that the spacecraft can stay and maneuver on the ultra-low earth orbit with less or no need of carrying the working medium, and the problem that the aircraft cannot stay and maneuver on the ultra-low orbit in the prior art can be solved. The technology has great significance for fully controlling and utilizing ultra-low orbit resources, and the air-breathing electric propulsion system can be widely applied to spacecraft platforms such as high-resolution earth observation satellites, earth gravitational field measurement satellites and ultra-high-speed communication satellites.
The air-breathing electric propulsion technology adopts ultra-low orbit environmental gas as a working medium, and the orbit environmental gas mainly comprises nitrogen, oxygen atoms and oxygen. The microwave cathode and the microwave neutralizer can work for a long time by using an oxygen-containing working medium, and the failure of the hollow cathode in the traditional thruster due to oxygen corrosion is avoided, so that the service life of the spacecraft is greatly prolonged.
Disclosure of Invention
The application provides a microwave cathode ion thruster, can prolong the life-span of adopting the electric thruster system of oxygen-containing working medium, improves the efficiency of oxygen-containing working medium electric thruster.
In order to achieve the above object, the present application provides a microwave cathode ion thruster, including an air inlet pipeline, a microwave power supply, a microwave neutralizer, a microwave cathode system, a thruster discharge chamber, and a grid system, wherein: the air inlet pipeline comprises a first air inlet pipeline, a second air inlet pipeline and a third air inlet pipeline; the first air inlet pipeline is communicated with the microwave neutralizer, the second air inlet pipeline is communicated with the microwave cathode system, and the third air inlet pipeline is communicated with the thruster discharge chamber; the microwave power supply is respectively connected with the microwave neutralizer and the microwave cathode system; the microwave cathode system is arranged at the input end of the thruster discharge chamber, and the grid system is arranged at the output end of the thruster discharge chamber; the microwave neutralizer is communicated with the thruster discharge chamber and is close to the output end of the thruster discharge chamber.
Further, microwave cathode system includes cathode chamber, microwave cathode permanent magnet, front yoke, back yoke, electron extraction board, reinforcing plate, microwave joint and microwave antenna, wherein: the cathode chamber is communicated with the discharge chamber of the thruster; the microwave cathode permanent magnets are arranged at two sides in the cathode chamber; the front end of the microwave cathode permanent magnet is provided with a front magnetic yoke, and the rear end of the microwave cathode permanent magnet is provided with a rear magnetic yoke; an electronic lead-out plate is arranged in front of the front magnetic yoke, and a reinforcing plate is arranged in front of the electronic lead-out plate; the microwave joint is arranged at the input end of the cathode chamber, one end of the microwave joint is connected with a microwave power supply, and the other end of the microwave joint is provided with a microwave antenna; the input end of the cathode chamber is also provided with an air inlet communicated with the second air inlet pipeline.
Furthermore, the thruster discharge chamber consists of a side wall and an anode wall which are sequentially connected, the input end of the thruster discharge chamber is communicated with the output end of the cathode chamber, and the side wall is provided with an air inlet communicated with a third air inlet pipeline.
Furthermore, thruster permanent magnets are uniformly distributed along the side wall and the outer wall of the anode wall.
Furthermore, the grid system comprises a screen grid and an accelerating grid, and the grid holes of the screen grid and the accelerating grid adopt a variable-aperture design mode.
Furthermore, a first valve is arranged in the first air inlet pipeline, a second valve is arranged in the second air inlet pipeline, and a third valve is arranged in the third air inlet pipeline.
Further, the diameter of the air inlet pipeline is in the order of cm.
Furthermore, the wall surface of the anode wall, the surface of the screen grid and the surface of the accelerating grid are all subjected to gold plating treatment.
The microwave cathode ion thruster provided by the invention has the following beneficial effects:
according to the microwave thruster, ultra-low earth orbit environment gas can be used as a working medium, the service life of the longer thruster is prolonged, and the microwave cathode and the microwave neutralizer are not corroded by oxygen and lose efficacy rapidly like a hollow cathode in a traditional thruster. In addition, the anode wall and the accelerating grid of the thruster are subjected to gold plating treatment, so that the thruster has good oxidation and corrosion resistance, and the service life of the thruster can reach 5 ten thousand hours or even longer. The introduction of the microwave cathode reinforcing plate can improve the energy of electron flow, the electromagnetic field of the discharge chamber of the thruster can effectively increase the energy of primary electrons, thereby being beneficial to improving the plasma ionization degree of the discharge chamber, the alternate change of the aperture of the grid system is beneficial to the efficient extraction of ions, and the working efficiency of the electric thruster utilizing the oxygen-containing working medium is improved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:
fig. 1 is a schematic structural diagram of a microwave cathode ion thruster provided according to an embodiment of the present application;
in the figure: 1-microwave power supply, 2-microwave neutralizer, 31-cathode chamber, 32-microwave cathode permanent magnet, 33-front magnetic yoke, 34-back magnetic yoke, 35-electronic leading-out plate, 36-reinforcing plate, 37-microwave joint, 38-microwave antenna, 4-thruster discharge chamber, 41-side wall, 42-anode wall, 43-thruster permanent magnet, 51-screen, 52-acceleration grid, 6-first air inlet pipeline, 61-first valve, 7-second air inlet pipeline, 71-second valve, 8-third air inlet pipeline and 81-third valve.
Detailed Description
In order to make the technical solutions of the present application better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only some embodiments of the present application, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
In addition, the term "plurality" shall mean two as well as more than two.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1, the present application provides a microwave cathode ion thruster, which includes an air inlet pipeline, a microwave power supply 1, a microwave neutralizer 2, a microwave cathode system, a thruster discharge chamber 4, and a grid system, wherein: the air inlet pipelines comprise a first air inlet pipeline 6, a second air inlet pipeline 7 and a third air inlet pipeline 8; a first air inlet pipeline 6 is communicated with the microwave neutralizer 2, a second air inlet pipeline 7 is communicated with the microwave cathode system, and a third air inlet pipeline 8 is communicated with the thruster discharge chamber 4; the microwave power supply 1 is respectively connected with the microwave neutralizer 2 and the microwave cathode system; the microwave cathode system is arranged at the input end of the thruster discharge chamber 4, and the grid system is arranged at the output end of the thruster discharge chamber 4; the microwave neutralizer 2 is communicated with the thruster discharge chamber 4 and is close to the output end of the thruster discharge chamber 4.
Specifically, the microwave cathode ion thruster provided by the embodiment of the present application uses the microwave cathode system as the thruster of the air-breathing electric propulsion system, and can use ultra-low orbit environmental gas (nitrogen, oxygen atom and oxygen) as the working medium, the microwave cathode system and the microwave neutralizer 2 can work for a long time by using the oxygen-containing working medium, and cannot lose effectiveness due to oxygen corrosion as easily as the conventional hollow cathode thruster, thereby substantially prolonging the service life of the spacecraft, and the microwave cathode structure provided by the embodiment of the present application is used, which is beneficial to the increase of the gas ionization degree in the thruster discharge chamber 4, and is beneficial to the improvement of the efficiency of the electric thruster, thereby improving the thrust-to-power ratio. In the embodiment of the present application, the first air inlet pipeline 6 is used for supplying air to the microwave neutralizer 2, the second air inlet pipeline 7 is used for supplying air to the microwave cathode system, and the third air inlet pipeline 8 is used for supplying air to the thruster discharge chamber 4; the microwave cathode system is arranged at the input end of the thruster discharge chamber 4, the electron flow emitted by the microwave cathode system ionizes a part of central gas in the thruster discharge chamber 4 to generate primary electrons, the energy of the primary electrons is enhanced under the action of an electromagnetic field of the thruster discharge chamber 4 to further ionize the gas in the thruster discharge chamber 4, and the discharge effect is expanded to the whole thruster discharge chamber 4; the grid system is arranged at the output end of the thruster discharge chamber 4, and is used for leading out ionized plasma ions and accelerating the ionized plasma ions so as to generate thrust; the microwave power supply 1 is used for supplying microwaves to the microwave neutralizer 2 and the microwave cathode system; the microwave neutralizer 2 is close to the output end of the thruster discharge chamber 4, the electron flow emitted by the microwave neutralizer 2 plays a role in neutralizing the plume ions diffused in the thruster discharge chamber 4, during work, environmental gas enters the microwave neutralizer 2 through the first air inlet pipeline 6, the microwave power supply 1 is started, meanwhile, the microwave neutralizer 2 works to generate and extract the electron flow, the plume ions diffused in the thruster discharge chamber 4 are neutralized, the whole spacecraft is guaranteed to be electrically neutral, meanwhile, positive charge accumulation caused at the downstream of a grid system is prevented, a high potential area is formed, and the extraction of subsequent ions is influenced.
Further, the microwave cathode system includes a cathode chamber 31, a microwave cathode permanent magnet 32, a front yoke 33, a back yoke 34, an electron extraction plate 35, a reinforcing plate 36, a microwave connector 37, and a microwave antenna 38, wherein: cathode chamber 31 is communicated with thruster discharge chamber 4; microwave cathode permanent magnets 32 are disposed at both sides of the inside of the cathode chamber 31; the front end of the microwave cathode permanent magnet 32 is provided with a front magnetic yoke 33, and the rear end is provided with a rear magnetic yoke 34; an electronic leading-out plate 35 is arranged in front of the front magnetic yoke 33, and a reinforcing plate 36 is arranged in front of the electronic leading-out plate 35; the microwave connector 37 is arranged at the input end of the cathode chamber 31, one end of the microwave connector 37 is connected with the microwave power supply 1, and the other end is provided with a microwave antenna 38; the input end of the cathode chamber 31 is also provided with an air inlet which is communicated with the second air inlet pipeline 7. In the embodiment of the present application, the microwave cathode permanent magnet 32, the front yoke 33, the back yoke 34, the electron exit plate 35, and the reinforcing plate 36 are disposed in two sets, symmetrically disposed on two sides of the inside of the cathode chamber 31, and the front yoke 33 and the back yoke 34 mainly serve as a guiding magnetic field, forming a magnetic field with a specific configuration to confine electrons. When the microwave cathode system works, the microwave power supply 1 emits microwaves, the microwaves are transmitted to the microwave antenna 38 inside the cathode chamber 31 through the microwave connector 37, under the action of a microwave electromagnetic field and a magnetic field generated by the two groups of microwave cathode permanent magnets 32, plasma discharge can occur in the ambient gas entering the cathode chamber 31 through the second air inlet pipe, electrons are led out through the electron leading-out plate 35 to generate electron flow, the reinforcing plate 36 is used for reinforcing the energy and the intensity of the led-out electron flow on one hand, and is used for shielding ions on the other hand to prevent a large amount of ions from entering the thruster discharge chamber 4, the reinforced electron flow enters the thruster discharge chamber 4 to ionize the ambient gas in the thruster discharge chamber 4 to generate original electrons.
Further, the thruster discharge chamber 4 is composed of a side wall 41 and an anode wall 42 which are connected in sequence, an input end of the thruster discharge chamber 4 is communicated with an output end of the cathode chamber 31, and an air inlet communicated with the third air inlet pipeline 8 is formed in the side wall 41.
Further, thruster permanent magnets 43 are uniformly distributed along the outer walls of the side walls 41 and the anode wall 42.
Specifically, the environmental gas enters the thruster discharge chamber 4 through the third air inlet pipe to participate in an ionization reaction, the anode wall 42 of the thruster discharge chamber 4 has a positive potential, the thruster permanent magnets 43 are uniformly arranged along the side wall 41 of the thruster discharge chamber 4 and the outer wall of the anode wall 42, under the action of the permanent magnets, an annular cusped magnetic field can be generated inside the thruster discharge chamber 4, electron flow emitted from the cathode chamber 31 is ionized with gas in the thruster discharge chamber 4 to generate primary electrons, the energy of the primary electrons is improved under the action of an electromagnetic field inside the thruster discharge chamber 4, the primary electrons collide with the internal gas to generate further ionization, and the environmental gas plasma is discharged and expanded to the whole thruster discharge chamber 4.
Further, the grid system comprises a screen 51 and an accelerating grid 52, and the grid holes of the screen 51 and the accelerating grid 52 adopt a variable-aperture design mode. The screen 51 is charged with positive potential, the accelerating grid 52 is charged with negative potential, and the electric field between the screen 51 and the accelerating grid 52 can extract positive ions at the output end of the thruster discharge chamber 4 and accelerate to generate thrust. Due to the presence of diatomic molecular ions, e.g. N, in the output plasma 2 + 、O 2 + Etc. also having nitrogen atom ions, e.g. N + 、O + And the ion extraction characteristics with different mass numbers are different greatly, so the requirements of the grid aperture are different, the screen grid 51 and the accelerating grid 52 adopt a variable aperture design mode, and even if the apertures are alternately designed, numerical calculation shows that the comprehensive extraction performance of the grid can be improved by adopting the variable aperture design mode, thereby the comprehensive extraction performance of the grid can be improved, and the ion extraction performance of the grid can be improvedThe overall efficiency of the electric thruster can be improved.
Further, the first valve 61 is provided in the first intake pipe 6, the second valve 71 is provided in the second intake pipe 7, and the third valve 81 is provided in the third intake pipe 8. The on-off between the first air inlet pipeline 6 and the microwave neutralizer 2 is controlled by the first valve 61, the on-off between the second air inlet pipeline 7 and the cathode chamber 31 is controlled by the second valve 71, and the on-off between the third air inlet pipeline 8 and the thruster discharge chamber 4 is controlled by the third valve 81. During operation, the valves are adjusted to supply air to the microwave neutralizer 2, the cathode chamber 31 and the thruster discharge chamber 4.
Furthermore, the diameter of the air inlet pipeline is in the cm order. The diameter of the air inlet pipeline of the traditional electric thruster is in mm magnitude, and in the embodiment of the application, the air pressure is 10 because of the environment of the track -4 The pressure of the gas entering the gas inlet pipeline after passing through the gas collecting and pressurizing device is 1Pa magnitude, so that the diameters of the first gas inlet pipeline 6, the second gas inlet pipeline 7 and the third gas inlet pipeline 8 are set to be cm magnitude, and are about one magnitude larger than the diameter of the gas inlet pipeline of the traditional electric thruster, and the gas inlet speed and the ionization efficiency of the thruster are greatly improved.
Further, the wall surface of the anode wall 42, the surface of the grid of the screen 51 and the surface of the grid of the acceleration grid 52 are all plated with gold.
Specifically, because the anode wall 42 of the thruster discharge chamber 4 is positively charged, in the ionization process, oxygen anions in the thruster discharge chamber 4 are attracted to the anode to move, and the oxygen anions are compounded into oxygen on the wall to corrode the wall, and experiments show that the wall of the anode wall 42 is corroded, and the screen 51 and the acceleration screen 52 are also corroded to a certain extent. When the surface of the anode wall 42 is corroded to a certain degree, the conductivity is reduced, the performance of the electric thruster is affected, even the discharge electricity is stopped, the conductivity is reduced due to the corrosion of the screen grid 51 and the accelerating grid 52, the extraction performance is reduced, the efficiency of the electric thruster is reduced, and in an extreme case, the grid system cannot extract beams, and the electric thruster fails. Therefore, the wall surface of the anode wall 42, the surface of the grid of the screen 51 and the surface of the grid of the acceleration grid 52 are plated with gold, so that the thrust device can effectively resist oxygen corrosion, thereby greatly prolonging the service life of the thrust device.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (8)
1. The microwave cathode ion thruster is characterized by comprising an air inlet pipeline, a microwave power supply, a microwave neutralizer, a microwave cathode system, a thruster discharge chamber and a grid system, wherein:
the air inlet pipelines comprise a first air inlet pipeline, a second air inlet pipeline and a third air inlet pipeline;
the first air inlet pipeline is communicated with the microwave neutralizer, the second air inlet pipeline is communicated with the microwave cathode system, and the third air inlet pipeline is communicated with the thruster discharge chamber;
the microwave power supply is respectively connected with the microwave neutralizer and the microwave cathode system;
the microwave cathode system is arranged at the input end of the thruster discharge chamber, and the grid system is arranged at the output end of the thruster discharge chamber;
the microwave neutralizer is communicated with the thruster discharge chamber and is close to the output end of the thruster discharge chamber.
2. The microwave cathode ion thruster of claim 1, wherein the microwave cathode system comprises a cathode chamber, a microwave cathode permanent magnet, a front yoke, a back yoke, an electron extraction plate, a reinforcing plate, a microwave joint, and a microwave antenna, wherein:
the cathode chamber is communicated with the thruster discharge chamber;
the microwave cathode permanent magnets are arranged on two sides of the inside of the cathode chamber;
the front end of the microwave cathode permanent magnet is provided with the front magnetic yoke, and the rear end of the microwave cathode permanent magnet is provided with the rear magnetic yoke;
the electronic leading-out plate is arranged in front of the front magnetic yoke, and the reinforcing plate is arranged in front of the electronic leading-out plate;
the microwave joint is arranged at the input end of the cathode chamber, one end of the microwave joint is connected with the microwave power supply, and the other end of the microwave joint is provided with a microwave antenna;
the input end of the cathode chamber is also provided with an air inlet communicated with the second air inlet pipeline.
3. The microwave cathode ion thruster according to claim 2, wherein the thruster discharge chamber is composed of a side wall and an anode wall which are connected in sequence, an input end of the thruster discharge chamber is communicated with an output end of the cathode chamber, and an air inlet which is communicated with the third air inlet pipeline is provided on the side wall.
4. The microwave cathode ion thruster of claim 3, wherein thruster permanent magnets are uniformly distributed along the outer walls of the side wall and the anode wall.
5. The microwave cathode ion thruster according to claim 3, wherein the grid system comprises a screen grid and an accelerating grid, and the grid holes of the screen grid and the accelerating grid are designed in a variable aperture manner.
6. The microwave cathode ion thruster according to claim 1, wherein a first valve is disposed inside the first air inlet pipeline, a second valve is disposed inside the second air inlet pipeline, and a third valve is disposed inside the third air inlet pipeline.
7. The microwave cathode ion thruster according to claim 6, wherein the diameter of the air inlet pipe is in the order of cm.
8. The microwave cathode ion thruster according to claim 5, wherein the wall surface of the anode wall, the surface of the screen grid and the surface of the accelerating grid are all plated with gold.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211575904.8A CN115822904A (en) | 2022-12-08 | 2022-12-08 | Microwave cathode ion thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211575904.8A CN115822904A (en) | 2022-12-08 | 2022-12-08 | Microwave cathode ion thruster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115822904A true CN115822904A (en) | 2023-03-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211575904.8A Pending CN115822904A (en) | 2022-12-08 | 2022-12-08 | Microwave cathode ion thruster |
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| CN (1) | CN115822904A (en) |
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- 2022-12-08 CN CN202211575904.8A patent/CN115822904A/en active Pending
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