CN114837909A - Hall electric thruster anode gas distributor - Google Patents
Hall electric thruster anode gas distributor Download PDFInfo
- Publication number
- CN114837909A CN114837909A CN202210643079.4A CN202210643079A CN114837909A CN 114837909 A CN114837909 A CN 114837909A CN 202210643079 A CN202210643079 A CN 202210643079A CN 114837909 A CN114837909 A CN 114837909A
- Authority
- CN
- China
- Prior art keywords
- gas distributor
- anode
- electric thruster
- hall electric
- anode gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000003466 welding Methods 0.000 claims abstract description 13
- 238000010894 electron beam technology Methods 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 69
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 6
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 239000010935 stainless steel Substances 0.000 claims description 4
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- 229910052786 argon Inorganic materials 0.000 claims description 3
- 210000003437 trachea Anatomy 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 2
- 229910001004 magnetic alloy Inorganic materials 0.000 claims description 2
- 230000007935 neutral effect Effects 0.000 abstract description 5
- 239000002245 particle Substances 0.000 abstract 1
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
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 an anode gas distributor of a Hall electric thruster, which comprises an air inlet pipe, an air pipe connecting piece, an anode magnetic conduction ring, a primary gas distributor and a secondary gas distributor. Wherein, the bottom of the U-shaped annular anode magnetizer is provided with a first vent hole; the lower side of the I-shaped annular primary gas distributor is provided with a second vent hole, and the upper side of the I-shaped annular primary gas distributor is provided with a third vent hole; the inner side and the outer side of the reverse U-shaped secondary gas distributor are respectively provided with a fourth vent hole. The anode magnetic conduction ring, the primary gas distributor and the secondary gas distributor are respectively formed by welding through electron beams, and a three-stage buffer structure of a primary buffer cavity, a secondary buffer cavity and a three-stage buffer cavity is formed. Through the technical scheme of the invention, the flow of the anode gas entering the Hall electric thruster can be effectively controlled and distributed, so that the gas fluidity is more stable and uniform, and a stable and uniform neutral particle environment is provided for the Hall electric thruster.
Description
Technical Field
The invention belongs to the technical field of electric propulsion, and particularly relates to an anode gas distributor of a Hall electric thruster.
Background
The Hall electric thruster is an electric propulsion system which is most mature to be applied internationally at present, has the advantages of higher specific impulse, long service life, light weight and the like compared with chemical propulsion, and is applied to tasks of attitude control, orbit transfer and lifting, orbit correction, resistance compensation and the like of a spacecraft.
The anode gas distributor is an important component in the Hall electric thruster, and long-term experimental research on the Hall thruster finds that the uniform stability of neutral gas in an anode discharge channel environment has a remarkable influence on plasma discharge: when the neutral gas in the discharge channel is not uniform, the plasma discharge is not uniform, the efficiency of the electric thruster is reduced, and even the discharge stability is affected.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: in order to solve the problem that neutral gas in a discharge channel of the Hall electric thruster is not easy to stabilize and uniform, the invention provides the anode gas distributor of the Hall electric thruster, which integrates a primary gas distributor, a secondary gas distributor and an anode magnetic conduction ring into a whole in an electron beam welding mode, and forms a three-stage buffer cavity, so that the neutral gas is more stable and uniform when flowing to the discharge channel through the three-stage buffer cavity.
The technical scheme provided by the invention is as follows:
an anode gas distributor of a Hall electric thruster comprises an air inlet pipe, an air pipe connecting piece, an anode magnetic conduction ring, a primary gas distributor and a secondary gas distributor.
Preferably, the air inlet pipe and the air pipe connecting piece are fixed on the anode magnetic conduction ring in an argon arc welding mode.
Preferably, the anode magnetizer is in a U-shaped annular structure, and 1 first vent hole is arranged at the bottom of the U-shaped structure.
Preferably, the primary gas distributor is of an I-shaped structure, 2 uniformly distributed second vent holes are arranged on the lower side of the I-shaped structure, 12 uniformly distributed third vent holes are arranged on the upper side of the I-shaped structure, and the circle center connecting line of the 2 second vent holes on the lower side and the circle center connecting line of the 2 adjacent third vent holes on the upper side form an included angle of 90 degrees.
Preferably, the secondary gas distributor has an inverted U-shaped ring structure, and 96 fourth vent holes are uniformly distributed on the inner side and the outer side of the inverted U-shaped ring structure.
Preferably, the anode magnetic conductive ring, the primary gas distributor and the secondary gas distributor are respectively welded and connected through electron beams.
Preferably, the anode magnetizer material is electrician pure iron or soft magnetic alloy.
Preferably, the material of the primary gas distributor is nonmagnetic stainless steel.
Preferably, the material of the secondary gas distributor is nonmagnetic stainless steel.
The invention has the advantages that: the anode gas distributor of the Hall electric thruster adopts an anode integrated welding structure, and is simple to process and low in cost. The three parts of the anode magnetic conductive ring, the first-stage gas distributor and the second-stage gas distributor are formed by welding through electron beams respectively, a multi-stage buffer structure of a first-stage buffer cavity, a second-stage buffer cavity and a third-stage buffer cavity is formed, and experimental effects prove that the structure effectively improves the uniformity and stability of gas in an anode discharge channel, improves ionization performance and finally improves the overall performance of the Hall electric thruster.
Drawings
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic two-dimensional cross-sectional view of an anode gas distributor structure of a Hall electric thruster provided by the invention;
FIG. 2 is a schematic perspective cross-sectional view of an anode gas distributor structure of a Hall electric thruster according to the present invention;
FIG. 3 is a perspective view of a structure of a primary gas distributor and a secondary gas distributor of the Hall electric thruster anode gas distributor after being welded and combined;
FIG. 4 is a schematic perspective view of a primary gas distributor structure of a Hall electric thruster anode gas distributor according to the present invention;
FIG. 5 is a schematic perspective view of a two-stage gas distributor structure of the Hall electric thruster anode gas distributor according to the present invention;
the labels in the figure are as follows: 1. an air inlet pipe; 2. a trachea connector; 3. an anode magnetic conductive ring; 4. a primary gas distributor; 5. a secondary gas distributor; 6. a primary buffer chamber; 7. a secondary buffer cavity; and 8, three stages of buffer cavities.
Detailed Description
In order that the objects and advantages of the invention will be more clearly understood, the invention is further described below with reference to examples; it should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principles of the present invention, and do not limit the scope of the present invention.
The invention discloses an anode gas distributor of a Hall electric thruster, which is shown in figures 1-5 and comprises an air inlet pipe 1, an air pipe connecting piece 2, an anode magnetizer 3, a primary gas distributor 4 and a secondary gas distributor 5;
hall electricity thruster positive pole gas distributor is positive pole integral structure, passes through welding mode fixed connection between the part respectively, and intake pipe 1, trachea connecting piece 2 pass through argon arc welding mode fixed connection with positive pole magnetizer 3, pass through electron beam welding mode fixed connection between one-level gas distributor 4 and the second grade gas distributor 5, and positive pole magnetizer 3 and one-level gas distributor 4 pass through electron beam welding mode fixed connection.
As shown in fig. 2, the primary gas distributor 4 and the secondary gas distributor 5 are first welded and combined, and then the primary gas distributor 4 and the anode magnetizer 3 are fixedly connected by electron beam welding.
The working principle of the invention is as follows: hall electric thruster anode gas distributor welding assembly accomplishes the back, gaseous from the intake pipe 1 first air vent of flowing through after, under the homogeneous action of one-level cushion chamber 6, then get into second grade cushion chamber 7 through two symmetry second air vent of one-level gas distributor 4, after stable even in second grade cushion chamber 7, the third air vent of 12 equipartitions of gas fork through one-level gas distributor 4 flows into tertiary cushion chamber 8, after tertiary cushion chamber 8, at the fourth air vent of 96 array equipartitions through second grade gas distributor 5, finally flow into annular discharge passage. The gas realizes three-stage buffering and uniform distribution of the gas totally, and fully achieves the uniform flowing state of the gas in the discharge channel.
So far, the technical solutions of the present invention have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present invention is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the invention, and the technical scheme after the changes or substitutions can fall into the protection scope of the invention.
Claims (9)
1. The utility model provides a hall electric thruster positive pole gas distributor which characterized in that, includes intake pipe, trachea connecting piece, positive pole magnetic ring, one-level gas distributor, second grade gas distributor.
2. The hall electric thruster anode gas distributor as set forth in claim 1, wherein: the air inlet pipe and the air pipe connecting piece are fixed on the anode magnetic conduction ring in an argon arc welding mode.
3. The hall electric thruster anode gas distributor as set forth in claim 1, wherein: the anode magnetizer is in a U-shaped annular structure, and 1 first vent hole is formed in the bottom of the U-shaped structure.
4. The hall electric thruster anode gas distributor as set forth in claim 1, wherein: the first-stage gas distributor is of an I-shaped structure, 2 uniformly distributed second vent holes are formed in the lower side of the I-shaped structure, 12 uniformly distributed third vent holes are formed in the upper side of the I-shaped structure, and the circle center connecting line of the 2 second vent holes in the lower side and the circle center connecting line of the 2 adjacent third vent holes in the upper side form an included angle of 90 degrees.
5. The hall electric thruster anode gas distributor as set forth in claim 1, wherein: the second-stage gas distributor is of an inverted U-shaped annular structure, and 96 fourth vent holes are uniformly distributed on the inner side and the outer side of the inverted U-shaped annular structure in an array mode.
6. The hall electric thruster anode gas distributor as set forth in claim 1, wherein: the anode magnetic conductive ring, the primary gas distributor and the secondary gas distributor are respectively formed by welding and connecting electron beams.
7. The Hall electric thruster anode gas distributor of claim 3, wherein: the anode magnetizer is made of electrician pure iron or soft magnetic alloy.
8. The Hall electric thruster anode gas distributor of claim 4, wherein: the material of the primary gas distributor is nonmagnetic stainless steel.
9. The Hall electric thruster anode gas distributor of claim 5, wherein: the secondary gas distributor is made of nonmagnetic stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210643079.4A CN114837909A (en) | 2022-06-08 | 2022-06-08 | Hall electric thruster anode gas distributor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210643079.4A CN114837909A (en) | 2022-06-08 | 2022-06-08 | Hall electric thruster anode gas distributor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114837909A true CN114837909A (en) | 2022-08-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210643079.4A Pending CN114837909A (en) | 2022-06-08 | 2022-06-08 | Hall electric thruster anode gas distributor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114837909A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115681059A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Reverse air intake electric thruster, space equipment and propelling method thereof |
| CN115681061A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Anode magnetic screen assembly and Hall thruster |
| CN115681056A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Counter-injected gas distributor |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7624566B1 (en) * | 2005-01-18 | 2009-12-01 | The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration | Magnetic circuit for hall effect plasma accelerator |
| CN105822516A (en) * | 2016-04-18 | 2016-08-03 | 哈尔滨工业大学 | Gas flow control method for improving ionization efficiency of Hall thruster |
| CN108457827A (en) * | 2018-03-16 | 2018-08-28 | 哈尔滨工业大学 | A kind of eddy flow air outlet structure of magnetic focusing hall thruster |
| CN110617186A (en) * | 2019-09-05 | 2019-12-27 | 上海空间推进研究所 | Novel discharge chamber structure |
| CN114139304A (en) * | 2021-11-13 | 2022-03-04 | 国科大杭州高等研究院 | Design method of double-cavity type anode gas supply ring structure of Hall thruster |
-
2022
- 2022-06-08 CN CN202210643079.4A patent/CN114837909A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7624566B1 (en) * | 2005-01-18 | 2009-12-01 | The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration | Magnetic circuit for hall effect plasma accelerator |
| CN105822516A (en) * | 2016-04-18 | 2016-08-03 | 哈尔滨工业大学 | Gas flow control method for improving ionization efficiency of Hall thruster |
| CN108457827A (en) * | 2018-03-16 | 2018-08-28 | 哈尔滨工业大学 | A kind of eddy flow air outlet structure of magnetic focusing hall thruster |
| CN110617186A (en) * | 2019-09-05 | 2019-12-27 | 上海空间推进研究所 | Novel discharge chamber structure |
| CN114139304A (en) * | 2021-11-13 | 2022-03-04 | 国科大杭州高等研究院 | Design method of double-cavity type anode gas supply ring structure of Hall thruster |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115681059A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Reverse air intake electric thruster, space equipment and propelling method thereof |
| CN115681061A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Anode magnetic screen assembly and Hall thruster |
| CN115681056A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Counter-injected gas distributor |
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| PB01 | Publication | ||
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| 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 |
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