CN106542122B - A kind of tricyclic Vacuum Arc thruster - Google Patents
A kind of tricyclic Vacuum Arc thruster Download PDFInfo
- Publication number
- CN106542122B CN106542122B CN201611117618.1A CN201611117618A CN106542122B CN 106542122 B CN106542122 B CN 106542122B CN 201611117618 A CN201611117618 A CN 201611117618A CN 106542122 B CN106542122 B CN 106542122B
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- Prior art keywords
- insulator
- cathode
- outer ring
- thruster
- common anode
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- 239000012212 insulator Substances 0.000 claims abstract description 34
- 239000002184 metal Substances 0.000 claims abstract description 5
- 230000015572 biosynthetic process Effects 0.000 description 2
- -1 common anode 4 Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000010406 cathode material Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910021645 metal ion Inorganic materials 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
-
- 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
- B64G1/405—Ion or plasma engines
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
A kind of tricyclic Vacuum Arc thruster, the thruster include the cylindrical cathodes for being placed in center, which is successively arranged concentrically insulator II, common anode, insulator I and outer ring cathode；The cylindrical cathodes, insulator II, common anode, insulator I and outer ring cathode are sequentially arranged in the cylindrical cathodes mounting groove of mounting seat, insulator II mounting base, common anode mounting groove, insulator I mounting base and outer ring cathode mounting groove；The outer end face of the mounting seat sets gradually cylindrical cathodes binding post, common anode binding post and outer ring cathode terminal from center outward；The cathode terminal and outer ring cathode terminal are connected to the cathode of power supply, and common anode binding post is connected to the anode of power supply；Metal conductive film is coated on the end face that insulator I and insulator II is in mounting seat.The present invention improves the efficiency of thruster and increases the service life of thruster.
Description
Technical field
The present invention relates to a kind of tricyclic Vacuum Arc thrusters for space, belong to spacecraft propulsion technical field.
Background technique
Satellite develops towards low cost, distributed direction in recent years.Micro-nano satellite have it is at low cost, the lead time is short,
The advantages that extended capability is strong, radiation pattern is flexible, micro-nano satellite all have civil and military important application prospect and strategy
Meaning.Microsatellite, the fast-developing of micro-nano satellite propose very high requirement for propulsion.Vacuum Arc thruster (VAT) because
Its quality is small, than leaping high, the advantages such as structure is simple and become the ideal electric propulsion type of micro-nano satellite.Small propulsion can mainly expire
The propulsion demand of sufficient micro-nano satellite specifically includes that (1) damping compensation, track lifting, position is kept and motor-driven, gesture stability, hair
Penetrate error correction etc.；(2) thrust can wide scope quickly adjust, such as without towing control, precise formation flight.Vacuum Arc thruster
Performance and the service life be of great significance for meeting the propulsion demand of micro-nano satellite.Current single cathode and single anode are coaxially true
Empty arc thruster is small by cathode burning corrosion area, causes the service life of thruster shorter, and reliability is lower, while plume is due to space electricity
Lotus effect and the angle of divergence is larger, influence the performance of thruster.Design has long-life, highly reliable, high performance Vacuum Arc thrust
Device has the important meaning.It is expected to increase considerably the life and reliability of Vacuum Arc thruster by increasing number of poles, simultaneously
The performance of thruster is improved, and is had to high-power scalability.
Summary of the invention
The present invention proposes a kind of tricyclic Vacuum Arc thruster, facilitates the raising in thruster performance and service life.
The technical scheme adopted by the invention is as follows:
A kind of tricyclic Vacuum Arc thruster, the thruster include the cathode for being placed in center, which successively sets with one heart
Set insulator II, common anode, insulator I and outer ring cathode；The cathode, insulator II, common anode, insulator I and outer
Ring cathode is sequentially arranged at the cathode mounting groove of mounting seat, insulator II mounting base, common anode mounting groove, insulator I peace
It fills in seat and outer ring cathode mounting groove；The outer end face of the mounting seat sets gradually cathode terminal, common from center outward
Anode terminal and outer ring cathode terminal；The cathode terminal and outer ring cathode terminal are connected to the cathode of power supply, jointly
Anode terminal is connected to the anode of power supply；Metal is coated on the end face that insulator I and insulator II is in mounting seat to lead
Electrolemma.
The cathode is column construction.
The present invention is based on the coaxial type Vacuum Arc thruster technology of current relative maturity, a kind of the general of tricyclic VAT is proposed
It reads, the intension of this concept is to be improved to single cathode, single anode construction altogether on the basis of current mature coaxial type VAT is designed
The twin cathode structure of anode.When thruster works, the Voltage Peak that power supply processing unit generates punctures between two groups of anode and cathodes simultaneously
Conductive film on insulator induces the main discharge between two groups of anode and cathodes.Two cathode end faces generate cathode protection, cathode simultaneously
The electronics of transmitting causes the ionization of the metallic atom of transmitting to generate plasma, and plasma is in pneumatic and electronics-ionic friction
Etc. mechanism accelerate lower to generate thrust.The invention has the advantages that (1) increased outer ring cathode increases the uniform of cathode burning corrosion
Property, be conducive to the service life for increasing thruster；(2) increased outer ring cathode reduces plume ion current density, can reduce space
Charge effect reduces the plume angle of divergence, and increased thrust improves the efficiency of thruster, and can reduce plume metal ion pair
The pollution on spacecraft surface；(3) it can further be developed to more multiring structure based on structure of the invention, thruster can be expanded
Power, expand the application range of thruster.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is mounting seat structural schematic diagram of the present invention；
Fig. 3 is binding post position view of the present invention.
Specific embodiment
The invention will be further described below in conjunction with the accompanying drawings.
Embodiment 1, referring to Fig.1,2,3, a kind of tricyclic Vacuum Arc thruster, the thruster includes the cylindricality yin for being placed in center
Pole 6(cylindrical cathodes structure is conducive to the uniform ablation of cathode material, to extend the service life of thruster), outside the cylindrical cathodes 6
Zhou Yici is arranged concentrically insulator II5, common anode 4, insulator I3 and outer ring cathode 2；The cylindrical cathodes 6, insulator
II5, common anode 4, insulator I3 and outer ring cathode 2 are sequentially arranged at cylindrical cathodes mounting groove 11, the insulator of mounting seat
In II mounting base 10, common anode mounting groove 9, insulator I mounting base 8 and outer ring cathode mounting groove 7；The cylindrical cathodes installation
Slot 11, common anode mounting groove 9, outer ring cathode 7 threes of mounting groove are contour.The outer end face of the mounting seat from center outward according to
Secondary setting cylindrical cathodes binding post 14, common anode binding post 13 and outer ring cathode terminal 12；The cathode terminal 14 and outer
Ring cathode terminal 12 is connected to the cathode of power supply 1, and common anode binding post 13 is connected to the anode of power supply 1；Insulator I3 and
Metal conductive film is coated on the end face that insulator II5 is in mounting seat in favor of voltage breakdown.
Embodiment 2 successively increases dead ring as needed and cathode loop forms multiring structure on the basis of embodiment 1
Vacuum Arc thruster expand the application range of thruster to expand the power of thruster.
When thruster works, the metal that the Voltage Peak that power supply processing unit generates punctures simultaneously on two insulator end faces is led
Electrolemma induces the main discharge between two groups of anode and cathodes to occur.The plasma ion of generation is rubbed by pneumatic and electronics-ion
The mechanism such as wiping accelerate, and then generate thrust.
The present invention largely improves the life and reliability of Vacuum Arc thruster, reduces plume ion dispersion angle,
The performance of thruster is improved, the pollution to spacecraft surface is mitigated.It the composite can be widely applied to micro-nano satellite and skin satellite
Position holding, transmission error amendment, track sphering, leaves the right or normal track and the tasks such as satellite formation flying at Orbit Transformation.
Claims (2)
1. a kind of tricyclic Vacuum Arc thruster, it is characterised in that: the thruster includes the cathode (6) for being placed in center, the cathode (6)
Periphery is successively arranged concentrically insulator II(5), common anode (4), insulator I(3) and outer ring cathode (2)；The cathode (6),
Insulator II(5), common anode (4), insulator I(3) and outer ring cathode (2) be sequentially arranged at the cathode mounting groove of mounting seat
(11), insulator II mounting base (10), common anode mounting groove (9), insulator I mounting base (8) and outer ring cathode mounting groove (7)
In；The outer end face of the mounting seat set gradually outward from center cathode terminal (14), common anode binding post (13) and
Outer ring cathode terminal (12)；The cathode terminal (14) and outer ring cathode terminal (12) are connected to the cathode of power supply (1), altogether
Same anode terminal (13) is connected to the anode of power supply (1)；Insulator I(3) and insulator II(5) it is in the end in mounting seat
Metal conductive film is coated on face.
2. a kind of tricyclic Vacuum Arc thruster according to claim 1, it is characterised in that: the cathode (6) is cylindricality knot
Structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611117618.1A CN106542122B (en) | 2016-12-07 | 2016-12-07 | A kind of tricyclic Vacuum Arc thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611117618.1A CN106542122B (en) | 2016-12-07 | 2016-12-07 | A kind of tricyclic Vacuum Arc thruster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106542122A CN106542122A (en) | 2017-03-29 |
| CN106542122B true CN106542122B (en) | 2019-03-15 |
Family
ID=58396249
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611117618.1A Active CN106542122B (en) | 2016-12-07 | 2016-12-07 | A kind of tricyclic Vacuum Arc thruster |
Country Status (1)
| Country | Link |
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| CN (1) | CN106542122B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106545479A (en) * | 2016-12-07 | 2017-03-29 | 兰州空间技术物理研究所 | A kind of Vacuum Arc thruster, multimode architecture, multi-mode implementation |
| CN113511348B (en) * | 2021-07-15 | 2022-10-25 | 兰州空间技术物理研究所 | Eddy current damping vibration-damping heat-insulating device of vertical thruster |
| CN114658564B (en) * | 2022-04-21 | 2022-09-23 | 哈尔滨工业大学 | Wide-range thrust-adjusting electric control solid thruster |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6818853B1 (en) * | 2003-05-30 | 2004-11-16 | Alameda Applied Sciences Corp. | Vacuum arc plasma thrusters with inductive energy storage driver |
| JP2008169779A (en) * | 2007-01-12 | 2008-07-24 | Osaka Univ | Pulsed plasma thruster |
| CN105156290A (en) * | 2015-07-13 | 2015-12-16 | 兰州空间技术物理研究所 | Novel three-annulus mixed electric thruster |
| CN105163475A (en) * | 2015-08-03 | 2015-12-16 | 兰州空间技术物理研究所 | Bidirectional gas supplying device for discharging chamber of ion thruster |
| CN106545479A (en) * | 2016-12-07 | 2017-03-29 | 兰州空间技术物理研究所 | A kind of Vacuum Arc thruster, multimode architecture, multi-mode implementation |
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| CN106542122A (en) | 2017-03-29 |
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