CN113371233B - Anode structure and cusp field thruster - Google Patents
Anode structure and cusp field thruster Download PDFInfo
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- CN113371233B CN113371233B CN202110864829.6A CN202110864829A CN113371233B CN 113371233 B CN113371233 B CN 113371233B CN 202110864829 A CN202110864829 A CN 202110864829A CN 113371233 B CN113371233 B CN 113371233B
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- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 241000219000 Populus Species 0.000 description 1
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- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000004544 sputter deposition Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
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- 238000002207 thermal evaporation Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/409—Unconventional spacecraft propulsion systems
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Abstract
The invention relates to an anode structure and a cusp field cutting thruster. The anode includes: the ionization device comprises an anode main body and a through channel, wherein the through channel penetrates through the anode main body, and the through channel is used for inputting working media to be ionized. The invention can improve the utilization rate of the electron energy at the axis of the cusp field thruster.
Description
Technical Field
The invention relates to the technical field of electric thrusters, in particular to an anode structure and a cusp field cutting thruster.
Background
The cusp field thruster is an electrostatic analogy force device developed by a traveling wave tube, generally a space propulsion device which restrains electron movement ionization working medium to generate thrust by forming a cusp magnetic field by two-stage or three-stage permanent magnets with the same magnetic poles oppositely, the main structure of the cusp field thruster comprises a multi-stage strong permanent magnet, a magnetic shoe which improves the structure of the cusp magnetic field, a ceramic ionization chamber and an anode, the proportion of the permanent magnet from the anode to an outlet is generally 1:2:6 or 2:6, as shown in figure 1, the magnetic field near the anode is close to a parallel axis and is vertical to the end surface of the anode, the magnetic field of the structure causes a large amount of electrons to be concentrated at the axis, and because the cusp field thruster is radial air outlet, the end surface of the anode is a large sealing metal plane, high-energy electrons are directly discharged at the end surface, the energy of the electrons at the axis are wasted, so in order to improve the performance of the cusp field thruster, there is a need for efficient use of electron energy at the axis, and for this reason, there is a need to improve the structure of existing cusp field thrusters.
Disclosure of Invention
The invention aims to provide an anode structure and a cusp field cutting thruster, which can improve the utilization rate of electron energy at the axis of the cusp field thruster.
In order to achieve the purpose, the invention provides the following scheme:
an anode structure comprising: the ionization device comprises an anode main body and a through channel, wherein the through channel penetrates through the anode main body, and the through channel is used for inputting working media to be ionized.
Optionally, the through channel is a uniform cross-section through channel or a variable cross-section through channel.
Optionally, the variable cross-section through channel comprises: the device comprises an air inlet hole, a necking and an expansion hole which are sequentially connected, wherein the aperture of the air inlet hole is larger than the aperture of the necking, the aperture of the necking is smaller than the aperture of the expansion hole, and the air inlet hole is used for inputting a working medium to be ionized.
Optionally, the length of the necking is greater than or equal to the aperture of the expanded hole.
Optionally, the aperture range of the necking is as follows:
wherein d is k Denotes the pore diameter of the expanded pore, d s The caliber of the throat is indicated.
Optionally, the aperture range of the expanded pores is as follows:
wherein d is k Denotes the pore diameter of the expanded pore, d d Indicating the diameter of the ionization chamber.
Optionally, the diameter range of the uniform cross-section through channel is as follows:
wherein d is t Denotes the diameter of the constant cross-section through-channel, d d Indicating the diameter of the ionization chamber.
A cusp field thruster, comprising: an ionization chamber and the anode structure; the ionization chamber is connected with the output end of the through channel, and the axis of the ionization chamber penetrates through the through channel.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects: the anode structure comprises a poplar basic body and a through channel, wherein the anode is arranged to be hollow, and a working medium can be injected through the hollow, so that the working medium is discharged with electrons at the axis, and the utilization rate of electron energy at the axis of the cusp field thruster is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a magnetic field configuration of a conventional cusped field thruster;
FIG. 2 is a schematic diagram of an anode structure in which the through channel provided by the embodiment of the present invention is a variable cross-section through channel;
FIG. 3 is a schematic diagram of an anode structure in which the through channel provided by the embodiment of the present invention is a through channel with a uniform cross section;
FIG. 4 is a schematic diagram of the structure of the ionization chamber;
fig. 5 is a schematic structural diagram of a cusp field thruster provided in an embodiment of the present invention.
Description of the symbols:
1-expanding hole, 2-necking, 3-air inlet, 4-uniform cross section through channel, 5-anode end surface and 6-ionization chamber.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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 invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
The prior cusp field thruster deposits much energy at the anode, causing the anode to melt at high temperature, the reliability is very low and the plasma wall loss is more serious than other types due to the long and narrow ionization channel, in order to solve the above problems, the embodiment provides an anode structure, the anode comprises: the ionization device comprises an anode main body and a through channel, wherein the through channel penetrates through the anode main body, and the through channel is used for inputting working media to be ionized.
In practical application, the through channel is a uniform cross-section through channel 4 or a variable cross-section through channel.
In practical applications, when the through channel is a variable cross-section through channel, as shown in fig. 2, the through channel includes: the expansion hole 1, throat 2 and the inlet port 3 that connect gradually, the aperture (diameter) of inlet port 3 is greater than the bore (diameter) of throat 2, the bore of throat 2 is less than the aperture (diameter) of expansion hole 1 reduces at expansion hole 1 to the section between throat 2 doubly, and the section grow gradually between throat 2 to the inlet port 3, inlet port 3 is used for the input to treat the working medium of ionization, and the working medium gets into the positive pole from inlet port 3, later enters into expansion hole 1 through throat 2, gets into ionization chamber 6 at last, and inlet port 3 is darker, for processing throat 2, processes one section inlet port 3 of bigger aperture earlier, is favorable to alleviateing the quality of positive pole simultaneously.
In practical application, the problems of high-temperature melting caused by electron energy deposition and corrosion caused by long-time sputtering are prevented, and the length of the necking 2 is larger than or equal to the aperture of the expansion hole 1.
In practical application, the anode adopts good electric and thermal conductors without magnetic conductivity, such as stainless steel, molybdenum, graphite and the like.
In practical application, the aperture range of the necking is as follows:
wherein d is k Denotes the pore diameter of the expanded pore 1, d s The caliber of the throat 2 is shown.
In practical application, the aperture range of the expanded pores is as follows:
wherein d is k Denotes the pore diameter of the expanded pore 1, d d Showing the diameter of the ionization chamber 6. The specific diameter parameter of the expansion hole 1 can be determined according to the current ratio between the current received by the anode end face 5 and the current entering the expansion hole 1, the current shared by the latter occupies more than half of the total current, when the cusp thruster discharges, a large amount of electrons are concentrated near the axis of the ionization chamber 6, the expansion hole 1 is favorable for the electrons to enter the anode for discharging, the high-density working medium which is discharged from the contraction 2 at the expansion hole 1 moves in the opposite direction of the electrons, and compared with the electrons discharged at the anode end face 5, the electron energy entering the expansion hole 1 can be more fully utilized. The electron inside expansion hole 1 because the existence of the strong magnetic field of cusp field, the electron still receives obvious restraint downthehole, and the electron can be because the collision accomplishes the discharge in expansion hole 1 side gradually, and the degree of depth of expansion hole 1 can influence this process, and specific degree of depth is according to experiment and thruster axial dimensions restraint decision.
In practical application, as shown in fig. 3, the diameter range of the uniform-section through channel is as follows:
wherein d is t Denotes the diameter of the constant-section through-channel 4, d d The diameter of the ionization chamber 6 is shown, the cusp field thruster adopting the constant-section air-saving hole is more suitable for miniaturization, a large number of electrons can enter the working medium in the constant-section air inlet hole 3 to pre-ionize the hole after miniaturization, and the energy utilization rate of the electrons is improved.
The present embodiment also provides a cusp field thruster, as shown in fig. 4 and 5, including: an ionization chamber 6 and the anode structure described above; the ionization chamber 6 is connected with the output end of the through channel, and the axis of the ionization chamber 6 penetrates through the through channel.
The invention has the following technical effects:
1. the hollow anode can solve the problems of low working medium utilization rate and poor performance of the conventional tangential field thruster, and can also avoid the problem of anode melting caused by serious thermal deposition under high power.
2. The anode is axially discharged, the central axial gas supply just collides with high-energy electrons of the axis, the electrons can be more efficiently utilized, the axial size of the cusp-cut field thruster can be potentially shortened, and the size of the thruster can be reduced. And the magnetic field here is very strong, and the radial diffusion of electron receives the restraint, and the existence of expansion hole can let electron as long as possible in the hole collide with high density working medium, realizes better preionization effect.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (4)
1. An anode structure, comprising: the ionization device comprises an anode main body and a through channel, wherein the through channel penetrates through the anode main body and is used for inputting working media to be ionized; the through channel is a uniform cross section through channel or a variable cross section through channel; the variable cross-section through passage comprises: the device comprises an air inlet, a necking and an expansion hole which are connected in sequence, wherein the aperture of the air inlet is larger than the aperture of the necking, the aperture of the necking is smaller than the aperture of the expansion hole, and the air inlet is used for inputting a working medium to be ionized; the length of the necking is larger than or equal to the aperture of the expansion hole; the diameter range of the uniform-section through channel is as follows:
wherein d is t Denotes the diameter of the constant cross-section through-channel, d d Indicating the diameter of the ionization chamber.
2. An anode structure according to claim 1, wherein the aperture of the throat is in the range:
wherein d is k Denotes the pore diameter of the expanded pore, d s The caliber of the throat is indicated.
3. An anode structure according to claim 1, wherein the expanded pores have a pore size in the range of:
wherein d is k Denotes the pore diameter of the expanded pore, d d Indicating the diameter of the ionization chamber.
4. A cusp field thruster, comprising: an ionization chamber and an anode structure according to any one of claims 1 to 3; the ionization chamber is connected with the output end of the through channel, and the axis of the ionization chamber penetrates through the through channel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110864829.6A CN113371233B (en) | 2021-07-29 | 2021-07-29 | Anode structure and cusp field thruster |
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| CN202110864829.6A CN113371233B (en) | 2021-07-29 | 2021-07-29 | Anode structure and cusp field thruster |
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| CN113371233B true CN113371233B (en) | 2022-08-30 |
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| FR2651835A1 (en) * | 1988-02-10 | 1991-03-15 | Olin Corp | Jet thruster assisted by an electric arc |
| EP0464383A2 (en) * | 1990-06-26 | 1992-01-08 | Hauzer Techno Coating Europe Bv | Plasma neutralisation cathode |
| JP2008169779A (en) * | 2007-01-12 | 2008-07-24 | Osaka Univ | Pulsed plasma thruster |
| CN201839502U (en) * | 2010-10-12 | 2011-05-18 | 烟台龙源电力技术股份有限公司 | Anode of arc plasma generator |
| CN103397991A (en) * | 2013-08-21 | 2013-11-20 | 哈尔滨工业大学 | Plasma thruster based on multilevel tip cusped magnetic field |
| CN103775297A (en) * | 2014-03-04 | 2014-05-07 | 哈尔滨工业大学 | Multistage cusped magnetic field plasma thruster segmented ceramic channel |
| CN111536008A (en) * | 2019-02-18 | 2020-08-14 | 金群英 | Plasma thruster with cusped magnetic field |
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| EP0463408A3 (en) * | 1990-06-22 | 1992-07-08 | Hauzer Techno Coating Europe Bv | Plasma accelerator with closed electron drift |
| RU2084085C1 (en) * | 1995-07-14 | 1997-07-10 | Центральный научно-исследовательский институт машиностроения | Closed electron drift accelerator |
| US6448721B2 (en) * | 2000-04-14 | 2002-09-10 | General Plasma Technologies Llc | Cylindrical geometry hall thruster |
| CN103953518B (en) * | 2014-05-13 | 2016-08-17 | 哈尔滨工业大学 | A kind of anode of multistage cusped magnetic field plasma thruster |
| CN104675650A (en) * | 2015-01-23 | 2015-06-03 | 哈尔滨工业大学 | Hollow anode for plasma thruster of cusped magnetic field |
| US10823158B2 (en) * | 2016-08-01 | 2020-11-03 | Georgia Tech Research Corporation | Deployable gridded ion thruster |
| DE102017204590B3 (en) * | 2017-03-20 | 2018-08-02 | Airbus Defence and Space GmbH | Cusp-field engine |
| CN108005868A (en) * | 2017-11-29 | 2018-05-08 | 哈尔滨工业大学 | A kind of anode-cold air thruster combining air feeding cusped magnetic field plasma thruster |
| IL256341A (en) * | 2017-12-14 | 2018-01-31 | Technion Res & Development Found Ltd | Narrow channel hall thruster |
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| CN111605740B (en) * | 2020-04-28 | 2022-03-04 | 北京控制工程研究所 | Anode structure of electric arc thruster |
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2021
- 2021-07-29 CN CN202110864829.6A patent/CN113371233B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2651835A1 (en) * | 1988-02-10 | 1991-03-15 | Olin Corp | Jet thruster assisted by an electric arc |
| EP0464383A2 (en) * | 1990-06-26 | 1992-01-08 | Hauzer Techno Coating Europe Bv | Plasma neutralisation cathode |
| JP2008169779A (en) * | 2007-01-12 | 2008-07-24 | Osaka Univ | Pulsed plasma thruster |
| CN201839502U (en) * | 2010-10-12 | 2011-05-18 | 烟台龙源电力技术股份有限公司 | Anode of arc plasma generator |
| CN103397991A (en) * | 2013-08-21 | 2013-11-20 | 哈尔滨工业大学 | Plasma thruster based on multilevel tip cusped magnetic field |
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