CN107387348A - A kind of a wide range of adjustable plasma microthruster using solid working medium - Google Patents
A kind of a wide range of adjustable plasma microthruster using solid working medium Download PDFInfo
- Publication number
- CN107387348A CN107387348A CN201710822931.3A CN201710822931A CN107387348A CN 107387348 A CN107387348 A CN 107387348A CN 201710822931 A CN201710822931 A CN 201710822931A CN 107387348 A CN107387348 A CN 107387348A
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- CN
- China
- Prior art keywords
- anode
- working medium
- solid working
- wide range
- heater strip
- 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.)
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Links
- 239000007787 solid Substances 0.000 title claims abstract description 36
- 238000010438 heat treatment Methods 0.000 claims abstract description 21
- 239000002131 composite material Substances 0.000 claims abstract description 11
- 239000000919 ceramic Substances 0.000 claims abstract description 9
- 230000008016 vaporization Effects 0.000 claims abstract description 5
- 238000009834 vaporization Methods 0.000 claims abstract description 5
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- ZCYVEMRRCGMTRW-UHFFFAOYSA-N 7553-56-2 Chemical compound [I] ZCYVEMRRCGMTRW-UHFFFAOYSA-N 0.000 claims description 2
- 229910052740 iodine Inorganic materials 0.000 claims description 2
- 239000011630 iodine Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 239000010935 stainless steel Substances 0.000 claims description 2
- 239000002699 waste material Substances 0.000 abstract description 4
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 4
- 229910052721 tungsten Inorganic materials 0.000 description 4
- 239000010937 tungsten Substances 0.000 description 4
- BGPVFRJUHWVFKM-UHFFFAOYSA-N N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] Chemical compound N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] BGPVFRJUHWVFKM-UHFFFAOYSA-N 0.000 description 3
- 150000002500 ions Chemical class 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 206010037660 Pyrexia Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 229910052743 krypton Inorganic materials 0.000 description 1
- DNNSSWSSYDEUBZ-UHFFFAOYSA-N krypton atom Chemical compound [Kr] DNNSSWSSYDEUBZ-UHFFFAOYSA-N 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910052724 xenon Inorganic materials 0.000 description 1
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 description 1
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
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
Abstract
A kind of a wide range of adjustable plasma microthruster using solid working medium, belong to thruster field, of the invention is to solve the problem of existing cusp field thruster storage is big for system bulk, and complexity height causes waste of energy with anode heating.The present invention is provided with storage in ceramic channel bottom and supplies composite anode, the storage includes anode, heater strip and wire for composite anode, heat conductive rod is provided with the inner chamber of anode and is fixed on the top end cover inwall of anode, n venthole is provided with the top end cover of anode and is connected with inner chamber, n >=8；Solid working medium is stored in the inner chamber of anode；Heating chamber is provided with below the bottom plate of anode, heater strip is provided with heating chamber；Affixed two fairleads of bottom plate of heating chamber；Heater strip is realized with extraneous power supply by the wire passed through from fairlead and electrically connected；Heater strip heats to anode, and heat passes to solid working medium by heat conductive rod, enters after the heating vaporization of solid working medium from venthole in ceramic passage.
Description
Technical field
The invention belongs to thruster field, it is related to the working medium memory technology of cusp field plasma thruster.
Background technology
Cusp field plasma thruster is a kind of Novel electric propulsion plant occurred in the world, with main flow in electric propulsion
Hall thruster is compared with ion thruster, have it is simple and compact for structure, pushing force density is than high, a wide range of continuously adjustabe of thrust,
Wall loss is low, the advantage such as long lifespan, is had broad prospects in new space mission.Its operation principle is cusp field etc.
Unique magnet arrangements of gas ions thruster form cusped magnetic field in passage, and electronics is entered in passage by emission of cathode, quilt
The magnetic line of force captures, because Magnetic Mirror Effect moves reciprocatingly in the passage interior edge magnetic line of force in cusped magnetic field, and with entering in passage
The neutral collisions ionization of working medium, caused ion sprays after being accelerated by axial electric field from passage forms thrust.
Current international cusp field plasma thruster is mainly working medium by neutral gas such as xenon, Krypton, its valency
Lattice are expensive, and need single gas storage to carry out the storage of super-pressure for unit, carry out working substance supply for thruster, significantly
The weight of whole propulsion system, cost and complexity are added, reduces overall reliability.In requirements for high precision of new generation
Space mission in, it is necessary to structure is compacter, compact propulsion system.Meanwhile the anode of cusp field thruster is due to electronics
Bombard and generally existing heating problem, because heat loss causes the waste of electric energy, reduce the electric energy profit of integrated propulsion system
With rate.
The content of the invention
Big for system bulk the invention aims to solve existing cusp field thruster storage, complexity is high and anode generates heat
A kind of the problem of causing waste of energy, there is provided a wide range of adjustable plasma microthruster using solid working medium.
A kind of a wide range of adjustable plasma microthruster using solid working medium of the present invention, in ceramic channel bottom
It is provided with storage and supplies composite anode, the storage includes anode, heater strip and wire for composite anode, is provided with and leads in the inner chamber of anode
Hot pin is simultaneously fixed on the top end cover inwall of anode, and n venthole is provided with the top end cover of anode and is connected with inner chamber, and n >=
8；Solid working medium is stored in the inner chamber of anode；
Heating chamber is provided with below the bottom plate of anode, heater strip is provided with heating chamber；
Affixed two fairleads of bottom plate of heating chamber；
Heater strip is realized with extraneous power supply by the wire passed through from fairlead and electrically connected；
Heater strip heats to anode, and heat passes to solid working medium by heat conductive rod, after the heating vaporization of solid working medium
Enter from venthole in ceramic passage.
Preferably, the distribution mode of venthole is circumferentially distributed along the top end cover center of anode.
Preferably, space be present between the bottom of heat conductive rod and the bottom plate of anode.
Preferably, the material of solid working medium is iodine solid.
Preferably, anode uses stainless steel 1Cr18Ni9Ti or 303 stainless steels.
Preferably, fairlead is ambroin sleeve pipe.
Beneficial effects of the present invention：Bunker of the invention by the way that anode to be used as to solid working medium, when being run using thruster
Heat caused by anode come make solid working medium vaporize, and enter passage ionization operation scheme come solve existing for prior art lack
Fall into.
Anode construction is supplied using special storage, solid working medium is directly stored in anode interior, and replaced generally with tungsten filament
Supply type negative electrode, eliminate the gas supply system in propulsion system, greatly reduce system weight and complexity, make propulsion
System is simpler compact, adds the reliability of system.It is meanwhile constant maintaining former cusp field thruster basic structure
Under the premise of, take full advantage of thruster running Anodic caused by heat, reduce practical heater and carry out solid work
The electric energy that matter heating needs, avoids the waste of electric energy.
Brief description of the drawings
Fig. 1 is the stereochemical structure signal of a wide range of adjustable plasma microthruster of the present invention using solid working medium
Figure；
Fig. 2 is Fig. 1 sectional side elevation；
Fig. 3 is structural representation of the storage for composite anode；
Fig. 4 is thruster anode nearby magnetic field bit-type and heat conduction schematic diagram.
Embodiment
Embodiments of the present invention are described in detail below with reference to drawings and Examples, and how the present invention is applied whereby
Technological means solves technical problem, and the implementation process for reaching technique effect can fully understand and implement according to this.Need to illustrate
As long as not forming conflict, each embodiment in the present invention and each feature in each embodiment can be combined with each other,
The technical scheme formed is within protection scope of the present invention.
The present invention is the bunker by the way that anode to be used as to solid working medium, when being run using thruster heat caused by anode come
Solid working medium is vaporized, and enters the scheme of passage ionization operation.
Embodiment：
Solid working medium plasma thruster structure of the present invention includes tungsten cathode 1, cusp field thruster is tied substantially
Structure (including Exported Ceramics 2, shell 3, annular magnet 4, passage ceramics 5, magnetic tip pad 6 etc.), storage are for composite anode (including sun
Pole 7, solid working medium 8, heater strip 9 and wire 10 etc.).Wherein heater is sketch, only illustrates installation site and its structure
In heater strip 9 and wire 10.Inner chambers of the place heating chamber 7-3 of heater strip 9 not with anode 7 turns on.
Tungsten cathode 1 is arranged on the exit of passage ceramics 5, and for the bottom of composite anode, annular magnet 4 is three-level knot for storage
Structure, magnetic tip pad 6 is provided between adjacent two-stage.
Storage is supplied in composite anode structure, and there is n venthole 7-1 on the top of anode 7, and the distribution mode of venthole is along center week
To distribution, n >=8.There is heat conductive rod 7-2 at the center of anode 7.Heating chamber 7-3, heating chamber 7-3 and sun are provided with below the bottom plate of anode 7
The inner chamber of pole 7 is not connected, and heater strip 9 is provided with heating chamber 7-3.
Tungsten cathode 1 is arranged on spacecraft lifting force device near exit.Each part of thruster uses spiral shell by mounting hole 11 etc.
Bolt is mutually permanently connected or by respective outer side edges come location and installation.The top of anode 7 is concordant with the third level bottom of magnet 4.
Shown in Fig. 3 is structure of the storage for composite anode, and the top of anode 7 has along the circumferentially equally distributed venthole in center
7-1, inside have heat conductive rod 7-2 to extend into inside solid working medium to optimize heat transfer of the anode to working medium.Solid working medium 8 heats
Entered after vaporization by venthole 7-1 in passage.
Due to the special magnetic field bit-type of the thruster, electronics along the magnetic line of force move when, it is attached to be concentrated in the axis of passage 5
Closely, it is deposited on along the magnetic line of force at the center of anode 7, the central area of anode 7 is produced stronger fever phenomenon.At the center of anode 7
Heat caused by place is transferred to working medium 8 via heat conductive rod 7-2, as shown in Figure 4.
Heating vaporization, thruster are first carried out to solid working medium 8 by the heater strip 8 of the bottom of anode 7 when the thruster is lighted a fire
After normal operation, when anode 7 heating itself is enough, the electrical power of heater strip 9 can be closed or reduce, it is caused in itself using anode
Heat heats vapour working medium 8, maintains the normal operation of thruster.
Although disclosed herein embodiment as above, described content only to facilitate understand the present invention and adopt
Embodiment, it is not limited to the present invention.Any those skilled in the art to which this invention pertains, this is not being departed from
On the premise of the disclosed spirit and scope of invention, any modification and change can be made in the implementing form and in details,
But the scope of patent protection of the present invention, still should be subject to the scope of the claims as defined in the appended claims.
Claims (6)
1. a kind of a wide range of adjustable plasma microthruster using solid working medium, it is characterised in that in ceramic channel bottom
It is provided with storage and supplies composite anode, the storage includes anode (7), heater strip (9) and wire (10) for composite anode, anode (7)
Heat conductive rod (7-2) is provided with inner chamber and is fixed on the top end cover inwall of anode (7), n is provided with the top end cover of anode (7)
Individual venthole (7-1) simultaneously connects, n >=8 with inner chamber；Solid working medium (8) is stored in the inner chamber of anode (7)；
Heating chamber (7-3) is provided with below the bottom plate of anode (7), heater strip (9) is provided with heating chamber (7-3)；
Affixed two fairleads (7-4) of bottom plate of heating chamber (7-3)；
Heater strip (9) is realized with extraneous power supply by the wire (10) passed through from fairlead (7-4) and electrically connected；
Heater strip (9) heats to anode (7), and heat passes to solid working medium (8), solid working medium by heat conductive rod (7-2)
(8) enter after heating vaporization from venthole (7-1) in ceramic passage.
2. a kind of a wide range of adjustable plasma microthruster using solid working medium, its feature exist according to claim 1
In the distribution mode of venthole (7-1) is circumferentially distributed along the top end cover center of anode (7).
3. a kind of a wide range of adjustable plasma microthruster using solid working medium, its feature exist according to claim 1
In space being present between the bottom of heat conductive rod (7-2) and the bottom plate of anode (7).
4. a kind of a wide range of adjustable plasma microthruster using solid working medium, its feature exist according to claim 1
In the material of solid working medium (8) is iodine solid.
5. a kind of a wide range of adjustable plasma microthruster using solid working medium, its feature exist according to claim 1
In anode (7) uses stainless steel 1Cr18Ni9Ti or 303 stainless steels.
6. a kind of a wide range of adjustable plasma microthruster using solid working medium, its feature exist according to claim 1
In fairlead (7-4) is ambroin sleeve pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710822931.3A CN107387348B (en) | 2017-09-13 | 2017-09-13 | A kind of a wide range of adjustable plasma microthruster using solid working medium |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710822931.3A CN107387348B (en) | 2017-09-13 | 2017-09-13 | A kind of a wide range of adjustable plasma microthruster using solid working medium |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107387348A true CN107387348A (en) | 2017-11-24 |
| CN107387348B CN107387348B (en) | 2019-07-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710822931.3A Active CN107387348B (en) | 2017-09-13 | 2017-09-13 | A kind of a wide range of adjustable plasma microthruster using solid working medium |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108533469A (en) * | 2018-03-09 | 2018-09-14 | 中国科学院微电子研究所 | Self-heating type electric propulsion device working substance supply device and electric propulsion device |
| CN109236594A (en) * | 2018-09-14 | 2019-01-18 | 哈尔滨工业大学 | A kind of low-power magnetization electric propulsion hollow cathode thruster |
| CN110067712A (en) * | 2019-06-05 | 2019-07-30 | 中国人民解放军国防科技大学 | Magnetic plasma thruster for inducing axial magnetic field |
| CN111156140A (en) * | 2018-11-07 | 2020-05-15 | 哈尔滨工业大学 | Cusped field plasma thruster capable of improving thrust resolution and working medium utilization rate |
| CN111173698A (en) * | 2018-11-09 | 2020-05-19 | 哈尔滨工业大学 | Liquid working medium plasma thruster based on microwave enhancement |
| CN111232253A (en) * | 2020-01-14 | 2020-06-05 | 苏州纳飞卫星动力科技有限公司 | Storage and supply device for solid working medium |
| CN111561431A (en) * | 2020-04-20 | 2020-08-21 | 哈尔滨工业大学 | Heat radiation anode structure for removing condensation product of iodine working medium electric thruster |
| RU2798987C2 (en) * | 2019-03-15 | 2023-06-30 | Сафран Эркрафт Энджинз | Chamber bottom for plasma thrust rockets |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033346A (en) * | 2014-06-25 | 2014-09-10 | 哈尔滨工业大学 | Multistage cusped magnetic field plasma thruster with channel magnetic field guide structure |
| CN104675650A (en) * | 2015-01-23 | 2015-06-03 | 哈尔滨工业大学 | Hollow anode for plasma thruster of cusped magnetic field |
| FR3018316A1 (en) * | 2014-03-07 | 2015-09-11 | Snecma | PLASMIC PROPELLER WITH HALL EFFECT |
| US20150305132A1 (en) * | 2012-06-18 | 2015-10-22 | Manu Mitra | Basic electromagnetic force field |
| CN105736272A (en) * | 2016-03-17 | 2016-07-06 | 哈尔滨工业大学 | Variable cross-section channel structure of low-power cusped magnetic field plasma thruster |
-
2017
- 2017-09-13 CN CN201710822931.3A patent/CN107387348B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150305132A1 (en) * | 2012-06-18 | 2015-10-22 | Manu Mitra | Basic electromagnetic force field |
| FR3018316A1 (en) * | 2014-03-07 | 2015-09-11 | Snecma | PLASMIC PROPELLER WITH HALL EFFECT |
| CN104033346A (en) * | 2014-06-25 | 2014-09-10 | 哈尔滨工业大学 | Multistage cusped magnetic field plasma thruster with channel magnetic field guide structure |
| CN104675650A (en) * | 2015-01-23 | 2015-06-03 | 哈尔滨工业大学 | Hollow anode for plasma thruster of cusped magnetic field |
| CN105736272A (en) * | 2016-03-17 | 2016-07-06 | 哈尔滨工业大学 | Variable cross-section channel structure of low-power cusped magnetic field plasma thruster |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108533469A (en) * | 2018-03-09 | 2018-09-14 | 中国科学院微电子研究所 | Self-heating type electric propulsion device working substance supply device and electric propulsion device |
| CN109236594A (en) * | 2018-09-14 | 2019-01-18 | 哈尔滨工业大学 | A kind of low-power magnetization electric propulsion hollow cathode thruster |
| CN109236594B (en) * | 2018-09-14 | 2020-08-25 | 哈尔滨工业大学 | Low-power magnetized electric propulsion hollow cathode thruster |
| CN111156140B (en) * | 2018-11-07 | 2021-06-15 | 哈尔滨工业大学 | Cusped field plasma thruster capable of improving thrust resolution and working medium utilization rate |
| CN111156140A (en) * | 2018-11-07 | 2020-05-15 | 哈尔滨工业大学 | Cusped field plasma thruster capable of improving thrust resolution and working medium utilization rate |
| CN111173698A (en) * | 2018-11-09 | 2020-05-19 | 哈尔滨工业大学 | Liquid working medium plasma thruster based on microwave enhancement |
| RU2798987C2 (en) * | 2019-03-15 | 2023-06-30 | Сафран Эркрафт Энджинз | Chamber bottom for plasma thrust rockets |
| CN110067712A (en) * | 2019-06-05 | 2019-07-30 | 中国人民解放军国防科技大学 | Magnetic plasma thruster for inducing axial magnetic field |
| CN110067712B (en) * | 2019-06-05 | 2024-03-26 | 中国人民解放军国防科技大学 | Magnetic plasma thruster inducing axial magnetic field |
| CN111232253A (en) * | 2020-01-14 | 2020-06-05 | 苏州纳飞卫星动力科技有限公司 | Storage and supply device for solid working medium |
| CN111232253B (en) * | 2020-01-14 | 2021-08-17 | 苏州纳飞卫星动力科技有限公司 | Storage and supply device for solid working medium |
| CN111561431B (en) * | 2020-04-20 | 2021-03-12 | 哈尔滨工业大学 | Heat radiation anode structure for removing condensation product of iodine working medium electric thruster |
| CN111561431A (en) * | 2020-04-20 | 2020-08-21 | 哈尔滨工业大学 | Heat radiation anode structure for removing condensation product of iodine working medium electric thruster |
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Effective date of registration: 20240410 Address after: Room 1107, 11 / F, National University Science Park, Harbin Institute of technology, No. 434, youyou street, Nangang District, Harbin City, Heilongjiang Province Patentee after: Harbin Institute of Technology Asset Management Co.,Ltd. Country or region after: China Patentee after: Harbin Prashi Power Technology R&D Department (Limited Partnership) Address before: 150001 No. 92 West straight street, Nangang District, Heilongjiang, Harbin Patentee before: HARBIN INSTITUTE OF TECHNOLOGY Country or region before: China |