CN105257491A - Hall thruster anode - Google Patents
Hall thruster anode Download PDFInfo
- Publication number
- CN105257491A CN105257491A CN201510861667.5A CN201510861667A CN105257491A CN 105257491 A CN105257491 A CN 105257491A CN 201510861667 A CN201510861667 A CN 201510861667A CN 105257491 A CN105257491 A CN 105257491A
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- China
- Prior art keywords
- ring
- inner ring
- anode
- hall thruster
- receiving
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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
- F03H1/0037—Electrostatic ion thrusters
- F03H1/0062—Electrostatic ion thrusters grid-less with an applied magnetic field
- F03H1/0075—Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift
Abstract
The invention discloses a Hall thruster anode, and relates to an electric propulsion Hall thruster. The problems that due to the fact that an existing Hall thruster anode is large in structure thermal load, and the deposition film coating phenomenon is serious, the electrical conductivity of the anode is lowered are solved. The Hall thruster anode comprises a bottom ring and a receiving ring connected into a whole. The Hall thruster anode further comprises an inner ring. The inner ring identical to the receiving ring in shape is fixedly connected into the receiving ring. The inner ring and the receiving ring form a circular concentric inner ring and outer ring structure. A gap is formed between the outer side face of the inner ring and the inner side face of the receiving ring. A gap is formed between the bottom face of the inner ring and the inner bottom face of the bottom ring. The Hall thruster anode is used for a Hall thruster.
Description
Technical field
The present invention relates to a kind of electric propulsion hall thruster, particularly a kind of hall thruster anode.
Background technique
Hall thruster (HallEffectThruster is called for short HET) is that one utilizes crossed electric and magnetic field to ionize and accelerates atom working medium, converts electrical energy into ion kinetic energy, obtains the electric thruster compared with high specific impulse.It has structure simple, than leaping high, efficiency is high, long working life, specific power are high, in-orbit active time the feature such as to grow, be applicable to the gesture stability of all kinds of astrovehicle, orbital exponent, Orbit Transformation, power compensation, position keep, reorientate, leave the right or normal track the tasks such as process, interplanetary probe and astronavigation, is the electric propulsion system that application is the most ripe at most in the world at present.
Anode is important composition parts in hall thruster body, is responsible for reception electronics, forms the critical function of discharge loop.Anode energy deposition is the pith of hall thruster power loss always, and this part energy deposition to cause anode own temperature higher, when deviation appears in thruster magnetic field configuration, when electromagnetic field is deteriorated to electron confinement, anode is directly subject to the bombardment of a large amount of high-energy electron, even there will be from molten phenomenon.At present, high-power hall thruster is electric propulsion study hotspot.And high-power what must bring is exactly high voltage and big current, for anode, the huge thermal loading problems that high voltage and large electronic current bring to be faced equally.Simultaneously experimentally experience and theory analysis, has different patterns under anode energy deposition and low voltage under high-voltage large current, under high voltage operating mode, not only finds that rubescent thermalization phenomenon appears in anode, even destroys anode construction time serious.In addition, the anode coating film formed due to foreign ion deposition is also the inevitable produced problem of hall thruster process of experimental, and it can cause anode conducting performance to decline, and affects thruster performance.Therefore, for anode energy deposition characteristic and plating--film meter, from anode construction angle, rational modification optimization must be carried out to it, make it no matter can both give play to superperformance under which kind of operating mode, thus improve thruster overall performance and functional reliability.
Summary of the invention
The present invention is that existing hall thruster anode construction thermal force is large, deposition plating phenomenon is serious in order to solve, and causes the problem that anode conducting performance declines, and then provides a kind of hall thruster anode.
The present invention is the technological scheme taked that solves the problem: a kind of hall thruster anode, it comprises the base ring and reception ring that connect as one, it also comprises inner ring, receive in ring and be connected with the inner ring identical with receiving ring-shaped, inner ring and the conglobate concentric internal and external double-circular structure of reception ring structure, have gap between the outer side surface of inner ring and the inner side surface receiving ring, the bottom surface of inner ring and the inner bottom surface of base ring have gap.
The invention has the beneficial effects as follows: the inner ring of hall thruster anode construction of the present invention and the conglobate concentric internal and external double-circular structure of reception ring structure, considerably increase the surface area of anode, reduce the Electron Heat deposition of average area at the same conditions, reduce the temperature of anode itself to a certain extent.Thermal force reduces, and deposition plating phenomenon obviously reduces, and anode conducting performance significantly improves.In magnetic field, carry out rational position layout to dicyclo anode during use, final effect is increased anode current receiving efficiency, improves thruster integral working.
Accompanying drawing explanation
Fig. 1 is existing hall thruster anode construction schematic diagram, Fig. 2 is the anode construction schematic diagram of a kind of concentric internal and external double-circular structure adopting floor to connect of the present invention, Fig. 3 is the plan view of Fig. 2, Fig. 4 is the anode construction schematic diagram of the concentric internal and external double-circular structure that the present invention's another kind adopts bridge like plate to connect, and Fig. 5 is the plan view of Fig. 4.
Embodiment
Embodiment one: composition graphs 2-Fig. 5 explanation, a kind of hall thruster anode of present embodiment, it comprises the base ring 4 and reception ring 5 that connect as one, it also comprises inner ring 6, receive in ring 5 and be connected with the inner ring 6 identical with receiving ring 5 shape, inner ring 6 and the conglobate concentric internal and external double-circular structure of reception ring 5 structure, have gap between the outer side surface of inner ring 6 and the inner side surface receiving ring 5, the bottom surface of inner ring 6 and the inner bottom surface of base ring 4 have gap.
Embodiment two: composition graphs 2-Fig. 5 illustrates, the upper-end surface of the inner ring 6 of present embodiment flushes with the upper-end surface receiving ring 5.Setting like this, when ensureing to use, anode top position is no more than zero field regions position of center line, and reception ring 5 internal surface and inner ring 6 outer surface directly can accept the magnetic line of force.Other is identical with embodiment one.
Embodiment three: composition graphs 2-Fig. 5 illustrates, the inner ring 6 of present embodiment and the material of reception ring 5 are metal molybdenum or magnetism-free stainless steel.Setting like this, selects non-magnetic rustproof Steel material under low-power, select Molybdenum metal materials industry under high power, is conducive to the thermal conduction characteristic improving anode, reduces own temperature.Other is identical with embodiment one or two.
Embodiment four: composition graphs 2-Fig. 3 illustrates, the anode of present embodiment also comprises several floors 7, and several floors 7 circumferentially uniform being arranged on receive between ring 5 and inner ring 6, and reception ring 5 and inner ring 6 are connected as one by floor 7.Setting like this, linkage structure is simple and easy to do, and different linkage structures also can be adopted to connect two rings.Other is identical with embodiment three.
Embodiment five: composition graphs 2-Fig. 3 illustrates, the floor 7 of present embodiment is rectangular plate.Setting like this, features simple structure is easy, and other is identical with embodiment four.
Embodiment six: composition graphs 4-Fig. 5 illustrates, the anode of present embodiment also comprises several bridge like plates 8, and several bridge like plates 8 are circumferentially uniform to be arranged on bottom inner ring 6, and reception ring 5 and inner ring 6 are connected as one by bridge like plate 8.Setting like this, linkage structure is simple and easy to do, and different linkage structures also can be adopted to connect two rings.Other is identical with embodiment three.
Embodiment seven: composition graphs 2-Fig. 5 illustrates, the thickness of the reception ring 5 of present embodiment is 2mm, and the height receiving ring 5 is 15mm-16mm, and the internal diameter receiving ring 5 is 134mm, and external diameter is 138mm.Present embodiment anode is applicable to the hall thruster of 5KW grade, and other model thruster dual-layered anode structure size is selected as required, ensures to receive ring and ceramic channel outer wall face 1-2mm distance during use.Other embodiment one, two, four, five or six identical.
Embodiment eight: composition graphs 2-Fig. 5 illustrates, the thickness of the inner ring 6 of present embodiment is 2mm, and the height of inner ring 6 is 10mm-11mm, and the internal diameter of inner ring 6 is 118mm or 102mm, and external diameter is 122mm or 106mm.Present embodiment anode is applicable to the hall thruster of 5KW grade, is conducive to the surface area increasing anode, and the Electron Heat deposition of unit area is less, ensures inner ring and ceramic vias inner walls face 1-2mm distance.The size of other model thruster bilayer anode is selected as required.When the anode of present embodiment uses, when inner ring is put in the middle of passage, the preferred 6mm in gap between the outer side surface of inner ring 6 and the inner side surface receiving ring 5; When inner ring puts position, vias inner walls face, the preferred 14mm in gap between the outer side surface of inner ring 6 and the inner side surface receiving ring 5.Other with embodiment one, two, four, five or six identical.
The present invention is totally the project organization adopting dicyclo anode, but by the connection configuration between change two ring, altogether completes two kinds of project organizations (as Fig. 2 and Fig. 4); In magnetic field, two kinds of mounting points are formed by changing two ring spacings.
Anode institute mounting point is positioned at zero field region position in the middle of bottom thruster discharge channel, concrete employing two kinds of magnetic field arrangements, its Anodic base is positioned over ceramic discharge passage bottom, two studs pass through the mounting hole of ceramic discharge channel bottom, fix at thruster base plate, and introduce anode supply line.In the region that stud passes through, carry out the insulating protection with thruster region of interest.
The present embodiment, for the anode of 5kW level hall thruster, introduces the Design Method applying for a patent structure.Fig. 1 is existing hall thruster anode design structure, Fig. 2 and Fig. 4 is design two schemes structure.The first design is on original structure, receive in ring and add an inner ring, specifically be of a size of and receive ring external diameter 138mm, receive ring internal diameter 134mm, reception ring thickness is 2mm, and width is 10mm, inner ring adopts four pieces of rib-slab structure to be connected with reception interannular, inner ring need be ensured and receive ring concentricity, and vertical with ceramic discharge passage bottom, see shown in Fig. 2 and Fig. 3.The second design is on the first design proposal basis, receives ring structure size and remains unchanged, and is connected to change into bottom inner ring to be connected by four bridge like plates, shown in concrete Placement reference Fig. 4 and Fig. 5 with the linkage structure of inner ring by fin-plate type.The difference of two kinds of design proposals is inner ring and receive the different of ring connection scheme, and namely bottom ring, bridge like connects and is connected with fin-plate type, but concrete as bottom connection configuration and floor configuration be changeable.
Adopt the anode construction in Fig. 2 or Fig. 4, the distance between the inside and outside ring changing dicyclo anode according to the hall thruster size of reality and magnetic field configuration.The bottom surface of the base ring 4 of the first embodiment anode of the present invention overlaps with ceramic discharge channel bottom, and two fixed bolts 9 cross the upper reserving installation hole of pottery, ensure anode and ceramic discharge passage concentricity.Gas distributor is positioned over base ring 4 top of anode and pushes down anode simultaneously.The reception ring 5 of anode presses close to ceramic discharge channel outer wall face, but keeps 1-2mm spacing according to actual needs, and inner ring 6 is positioned at internal face position, and inner ring 6 and reception ring 5 top remain on below in the middle part of zero field regions simultaneously.For ensureing that anode can reach desired effect in practice, during thruster structural design, first analog magnetic field configuration, then changes the concrete size of anode as required.
The second embodiment is on the first basis, keep most of structure constant, change inner ring 6 position of anode, be positioned over the zero vertical position of center line in field regions, can finely tune its position according to actual needs, other content is stated identical with the first scheme above-mentioned.
Contrasted by ANSYS software analysis, under identical operating mode, in Fig. 1, existing hall thruster temperature of anode scope is: 111.09 DEG C-317.54 DEG C; As shown in Figure 2, the temperature of anode scope adopting the concentric internal and external double-circular structure of rib structure is 91.16 DEG C-263.17 DEG C; As shown in Figure 4, the temperature of anode scope adopting the concentric internal and external double-circular structure of bridge like plate structure is 92.713 DEG C-270.13 DEG C.It can thus be appreciated that the anode of modified node method of the present invention, owing to adopting concentric internal and external double-circular structure, considerably increases surface area, under identical operating mode, greatly reduces the temperature of anode itself, improves hall thruster integral working, add electronics receiving efficiency.
Claims (8)
1. a hall thruster anode, it comprises the base ring (4) and reception ring (5) that connect as one, it is characterized in that: it also comprises inner ring (6), receive in ring (5) and be connected with the inner ring (6) identical with receiving ring (5) shape, inner ring (6) and the conglobate concentric internal and external double-circular structure of reception ring (5) structure, have gap between the outer side surface of inner ring (6) and the inner side surface receiving ring (5), the bottom surface of inner ring (6) and the inner bottom surface of base ring (4) have gap.
2. a kind of hall thruster anode according to claim 1, is characterized in that: the upper-end surface of inner ring (6) flushes with the upper-end surface receiving ring (5).
3. a kind of hall thruster anode according to claim 1 and 2, is characterized in that: the material of inner ring (6) and reception ring (5) is metal molybdenum or magnetism-free stainless steel.
4. a kind of hall thruster anode according to claim 3, it is characterized in that: it also comprises several floors (7), several floors (7) circumferentially uniform being arranged on receive between ring (5) and inner ring (6), and reception ring (5) and inner ring (6) are connected as one by floor (7).
5. a kind of hall thruster anode according to claim 4, is characterized in that: floor (7) is rectangular plate.
6. a kind of hall thruster anode according to claim 3, it is characterized in that: it also comprises several bridge like plates (8), several bridge like plates (8) are circumferentially uniform is arranged on inner ring (6) bottom, and reception ring (5) and inner ring (6) are connected as one by bridge like plate (8).
7. a kind of hall thruster anode according to claim 1,2,4,5 or 6, it is characterized in that: the thickness receiving ring (5) is 2mm, the height receiving ring (5) is 15mm-16mm, and the internal diameter receiving ring (5) is 134mm, and external diameter is 138mm.
8. a kind of hall thruster anode according to claim 1,2,4,5 or 6, it is characterized in that: the thickness of inner ring (6) is 2mm, the height of inner ring (6) is 10mm-11mm, the internal diameter of inner ring (6) is 118mm or 102mm, and external diameter is 122mm or 106mm.
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| CN201510861667.5A CN105257491B (en) | 2015-11-30 | 2015-11-30 | A kind of hall thruster anode |
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| CN201510861667.5A CN105257491B (en) | 2015-11-30 | 2015-11-30 | A kind of hall thruster anode |
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| CN105257491A true CN105257491A (en) | 2016-01-20 |
| CN105257491B CN105257491B (en) | 2017-11-03 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107795445A (en) * | 2017-09-01 | 2018-03-13 | 兰州空间技术物理研究所 | A kind of annular magnetic steel ring cutting field ion thruster structure and main support ring |
| CN108307576A (en) * | 2018-03-14 | 2018-07-20 | 哈尔滨工业大学 | A kind of magnetic structure design method under magnetic focusing hall thruster long-life design |
| CN110735775A (en) * | 2019-09-16 | 2020-01-31 | 北京控制工程研究所 | hollow anode structure for Hall thruster |
| CN113236516A (en) * | 2021-06-30 | 2021-08-10 | 哈尔滨工业大学 | Structure for preventing deposition in discharge chamber of micro ion thruster |
| CN113503234A (en) * | 2021-06-30 | 2021-10-15 | 中国长城工业集团有限公司 | Hall thruster capable of generating controllable torque |
| CN114320801A (en) * | 2021-12-28 | 2022-04-12 | 哈尔滨工业大学 | Cold cathode capable of being started quickly |
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| US4011719A (en) * | 1976-03-08 | 1977-03-15 | The United States Of America As Represented By The United States National Aeronautics And Space Administration Office Of General Counsel-Code Gp | Anode for ion thruster |
| CN1218541A (en) * | 1996-04-01 | 1999-06-02 | 空间动力公司 | Hall effect plasma accelerator |
| JP2007120424A (en) * | 2005-10-28 | 2007-05-17 | Mitsubishi Electric Corp | Hall thruster and aerospace vehicle |
| CN201160064Y (en) * | 2006-09-28 | 2008-12-03 | 北京镨玛时代科技有限公司 | Hall type ion source |
| CN102630277A (en) * | 2009-09-17 | 2012-08-08 | 斯奈克玛公司 | Hall-effect plasma thruster |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US4011719A (en) * | 1976-03-08 | 1977-03-15 | The United States Of America As Represented By The United States National Aeronautics And Space Administration Office Of General Counsel-Code Gp | Anode for ion thruster |
| CN1218541A (en) * | 1996-04-01 | 1999-06-02 | 空间动力公司 | Hall effect plasma accelerator |
| JP2007120424A (en) * | 2005-10-28 | 2007-05-17 | Mitsubishi Electric Corp | Hall thruster and aerospace vehicle |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107795445A (en) * | 2017-09-01 | 2018-03-13 | 兰州空间技术物理研究所 | A kind of annular magnetic steel ring cutting field ion thruster structure and main support ring |
| CN107795445B (en) * | 2017-09-01 | 2019-08-23 | 兰州空间技术物理研究所 | A kind of annular magnetic steel ring cutting field ion thruster structure and main support ring |
| CN108307576A (en) * | 2018-03-14 | 2018-07-20 | 哈尔滨工业大学 | A kind of magnetic structure design method under magnetic focusing hall thruster long-life design |
| CN108307576B (en) * | 2018-03-14 | 2020-02-21 | 哈尔滨工业大学 | Magnetic circuit structure design method under long-life design of magnetic focusing Hall thruster |
| CN110735775A (en) * | 2019-09-16 | 2020-01-31 | 北京控制工程研究所 | hollow anode structure for Hall thruster |
| CN110735775B (en) * | 2019-09-16 | 2021-02-09 | 北京控制工程研究所 | Hollow anode structure for Hall thruster |
| CN113236516A (en) * | 2021-06-30 | 2021-08-10 | 哈尔滨工业大学 | Structure for preventing deposition in discharge chamber of micro ion thruster |
| CN113503234A (en) * | 2021-06-30 | 2021-10-15 | 中国长城工业集团有限公司 | Hall thruster capable of generating controllable torque |
| CN113236516B (en) * | 2021-06-30 | 2022-03-04 | 哈尔滨工业大学 | Structure for preventing deposition in discharge chamber of micro ion thruster |
| CN114320801A (en) * | 2021-12-28 | 2022-04-12 | 哈尔滨工业大学 | Cold cathode capable of being started quickly |
| CN114320801B (en) * | 2021-12-28 | 2022-07-01 | 哈尔滨工业大学 | Cold cathode capable of being started quickly |
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| CN105257491B (en) | 2017-11-03 |
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Application publication date: 20160120 Assignee: Shanghai Yili Technology Co.,Ltd. Assignor: HARBIN INSTITUTE OF TECHNOLOGY Contract record no.: X2021230000046 Denomination of invention: An anode for Hall thruster Granted publication date: 20171103 License type: Exclusive License Record date: 20210708 |